NASASP-7037(315)March 1995

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

<NASA-SP-7037<315)) AERONAUTICALENGINEERING: A CONTINUINGBIBLIOGRAPHY WITH INDEXES(SUPPLEMENT 315) (NASA) 84 p

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mal Aeronautics and;e Administration

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NASASP-7037(315)March 1995

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

National Aeronautics and Space AdministrationScientific and Technical Information Office

Washington, DC 1995

This publication was prepared by the NASA Center for AeroSpace Information,800 Elkridge Landing Road, Linthicum Heights, MD 21090-2934, (301) 621-0390.

INTRODUCTION

This issue of Aeronautical Engineering—A Continuing Bibliography with Indexes (NASA SP-7037)lists 217 reports, journal articles, and other documents recently announced in the NASA STIDatabase.

Accession numbers cited in this issue include:Scientific and Technical Aerospace Reports (STAR) (N-10000 Series) N95-13610 — N95-15918Open Literature (A-60000 Series) A95-61680 — A95-62970

The coverage includes documents on the engineering and theoretical aspects of design, construc-tion, evaluation, testing, operation, and performance of aircraft (including aircraft engines) andassociated components, equipment, and systems. It also includes research and development inaerodynamics, aeronautics, and ground support equipment for aeronautical vehicles.

Each entry in the publication consists of a standard bibliographic citation accompanied, in mostcases, by an abstract. The listing of the entries is arranged by the first nine STAR specific cate-gories and the remaining STAR major categories. This arrangement offers the user the mostadvantageous breakdown for individual objectives. The citations include the original accessionnumbers from the respective announcement journals.

Seven indexes—subject, personal author, corporate source, foreign technology, contract number,report number, and accession number—are included.

A cumulative index for 1995 will be published in early 1996.

The NASA CASI price code table, addresses of organizations, and document availability informa-tion are located at the back of this issue.

TABLE OF CONTENTS

Category 01 Aeronautics 65

Category 02 Aerodynamics 66Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces;and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 77Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation N.A.Includes digital and voice communication with aircraft; air navigation systems(satellite and ground based); and air traffic control.

Category 05 Aircraft Design, Testing and Performance 78Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 82Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 82Includes prime propulsion systems and systems components, e.g., gas turbineengines and compressors; and onboard auxiliary power plants for aircraft.

Category 08 Aircraft Stability and Control 83Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 84Includes airports, hangars and runways; aircraft repair and overhaul facilities; windtunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 85Includes astronautics (general); astrodynamics; ground support systems andfacilities (space); launch vehicles and space vehicles; space transportation; spacecommunications, spacecraft communications, command and tracking; spacecraftdesign, testing and performance; spacecraft instrumentation; and spacecraftpropulsion and power.

Category 11 Chemistry and Materials N.A.Includes chemistry and materials (general); composite materials; inorganic andphysical chemistry; metallic materials; nonmetallic materials; propellants and fuels;and materials processing.

Category 12 Engineering 88Includes engineering (general); communications and radar; electronics and electri-cal engineering; fluid mechanics and heat transfer; instrumentation and photogra-phy; lasers and masers; mechanical engineering; quality assurance and reliability;and structural mechanics.

Category 13 Geosciences 98Includes geosciences (general); earth resources and remote sensing; energyproduction and conversion; environment pollution; geophysics; meteorology andclimatology; and oceanography.

Cateogory14 Life Sciences N.A.Includes life sciences (general); aerospace medicine; behavioral sciences; man/system technology and life support; and space biology.

Category 15 Mathematical and Computer Sciences 98Includes mathematical and computer sciences (general); computer operations andhardware; computer programming and software; computer systems; cybernetics;numerical analysis; statistics and probability; systems analysis; and theoreticalmathematics.

Category 16 Physics 100Includes physics (general); acoustics; atomic and molecular physics; nuclear andhigh-energy; optics; plasma physics; solid-state physics; and thermodynamics andstatistical physics.

Category 17 Social Sciences N.A.Includes social sciences (general); administration and management; documenta-tion and information science; economics and cost anaylsis; law, political science,and space policy; and urban technology and transportation.

Category 18 Space Sciences 101Includes space sciences (general); astronomy; astrophysics; lunar and planetaryexploration; solar physics; and space radiation.

Category 19 General 102

Subject Index A-1

Personal Author Index B-1Corporate Source Index C-1

Foreign Technology Index D-1

Contract Number Index E-1

Report Number Index F-1

Accession Number Index G-1Appendix APP-1

vi

TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSOREDION MICROFICHElotU

ACCESSION NUMBER -» N95-10318*# Dow Chemical Co., Midland, Ml. <- CORPORATE SOURCETITLE -» NOVEL MATRIX RESINS FOR COMPOSITES FOR AIRCRAFT

PRIMARY STRUCTURES, PHASE 1 Final Report, Apr. 1989 -Mar. 1992

AUTHORS -» EDMUND P. WOO, P. M. PUCKETT, S. MAYNARD, M. T. BISHOP,K.J.BRUZA,J.P.GODSCHALX,ANDM.J.MULLINS Aug.1992<- PUBLICATION DATE164 p

CONTRACT NUMBERS -» (Contracts NAS1-18841; RTOP 510-02-11-02)REPORT NUMBERS -» (NASA-CR-189657;NAS1.26:189657) Avail: CASI HCA08/MFA02 «- AVAILABILITY AND

The objective of the contract is the development of matrix resins PRICE CODEwith improved processability and properties for composites for primarilyaircraft structures. To this end, several resins/systems were identifiedfor subsonic and supersonic applications. For subsonic aircraft, aseries of epoxy resins suitable for RTM and powder prepreg was shownto give composites with about 40 ksi compressive strength after impact(CAI) and 200 F/wet mechanical performance. For supersonic applica-tions, a thermoplastic toughened cyanate prepreg system has demon-strated excellent resistance to heat aging at 360 F for 4000 hours, 40ksi CAI and useful mechanical properties at greater than or equal to 310F. An AB-BCB-maleimide resin was identified as a leading candidate forthe HSCT. Composite panels fabricated by RTM show CAI of approxi-mately 50 ksi, 350 F/wet performance and excellent retention ofmechanical properties after aging at 400 F for 4000 hours. Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED

iACCESSION NUMBER -> A95-60192* National Aeronautics and Space Administration. Ames. «- CORPORATE SOURCE

Research Center, Moffett Field, CA.TITLE -» AERODYNAMIC INTERACTIONS BETWEEN A ROTOR AND

WING IN HOVERAUTHORS -» FORT F. FELKER NASA. Ames Research Center, Moffett Field, <- AUTHOR'S AFFILIATION

CA, US and JEFFREY S. LIGHT NASA. Ames Research Center,Moffett Field, CA, US Journal of the American Helicopter Society <- JOURNAL TITLE

PUBLICATION DATE -» 2Jun. 1986 p. 53-61REPORT NUMBER -» (HTN-94-00714) Copyright

An experimental investigation of rotor/wing aerodynamic interac-tions in hover is described. The investigation consisted of both a large-scale and a small-scale test. A 0.658-scale V-22 rotor and wing wasused in the large-scale test. Wing download, wing surface pressure,rotor performance, and rotor downwash data from the large-scale testare presented. A small-scale experiment was conducted to determinehow changes in the rotor/wing geometry affected the aerodynamicinteractions. These geometry variations included the distance betweenthe rotor and wing, wing incidence angle, wing flap angle, rotor rotationdirection, and configurations both with the rotor axis at the tip of the wing(tilt rotor configuration) and with the rotor axis at the center of the wing(compound helicopter configuration). Author (Hemer)

vii

AERONAUTICALENGINEERING A Continuing Bibliography (Suppl. 315)

March 1995

01AERONAUTICS (GENERAL)

A95-61734ADVANCEMENTS IN AUTOMATIC FASTENINGTECHNOLOGYAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 9 September 1993 p. 7-9(BTN-94-EIX94461290277) Copyright

By using machines that merge the latest in electronic control andfeedback devices with innovative mechanical design, manufacturingcost can be reduced while productivity and quality are increased. Onemachine which does just that is the Gemcor wing fastening systemwhich uses a six-position upper head - a closed loop servo controlledmechanism that employs a linear encoder and precision linear guidebearings to obtain a high degree of positioning accuracy. El

N95-13642*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.MODIFICATION OF THE AMES 40- BY 80-FOOT WINDTUNNEL FOR COMPONENT ACOUSTIC TESTING FOR THESECOND GENERATION SUPERSONIC TRANSPORTF. H. SCHMITZ. J. R. ALLMEN, and P. T. SODERMAN Oct 199441 p(Contract(s)/Grant(s): RTOP 505-38-13)(NASA-TM-108850; A-94143; NAS 1.15:108850) Avail: CASIHC A03/MFA01

The development of a large-scale anechoic test facility wherelarge models of engine/airframe/high-fift systems can be tested for bothimproved noise reduction and minimum performance degradation isdescribed. The facility development is part of the effort to investigateeconomically viable methods of reducing second generation highspeed civil transport noise during takeoff and climb-out that is nowunder way in the United States. This new capability will be achievedthrough acoustic modifications of NASA's second largest subsonicwind tunnel: the 40-by 80-Foot Wind Tunnel at the NASA AmesResearch Center. .Three major items are addressed in the design of thislarge anechoic and quiet wind tunnel: a new deep (42 inch (107 cm)) testsection (iner, expansion of the wind tunnel drive operating envelope atlow rpm to reduce background noise, and other promising methods ofimproving signal-to-noise levels of inflow microphones. Current testingplans supporting the U.S. high speed civil transport program are alsooutlined. Author

N95-13662*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Field, CA.USER'S GUIDE FOR ENSAERO: A MULTIDISCIPLINARYPROGRAM FOR FLUID/STRUCTURAL/CONTROLINTERACTION STUDIES OF AIRCRAFT (RELEASE 1)GURU P. GURUSWAMY Oct. 1994 47 p(Contract(s)/Grant(s): RTOP 509-10-11)(NASA-TM-108853; A-94148; NAS 1.15:108853) Avail: CASI HCA03/MFA01

Strong interactions can occur between the flow about an aero-

space vehicle and its structural components resulting in several impor-tant aeroelastic phenomena. These aeroelastic phenomena can signifi-cantly influence the performance of the vehicle. At present, closed-formsolutions are available for aeroelastic computations when flows are ineitherthe linear subsonic or supersonic range. However, for aeroelasticityinvolving complex nonlinear flows with shock waves, vortices, flowseparations, and aerodynamic heating, computational methods are stillunder development. These complex aeroelastic interactions can bedangerous and limit the performance of aircraft. Examples of thesedetrimental effects are aircraft with highly swept wings experiencingvortex-induced aeroelastic oscillations, transonic regime at which theflutter speed is low, aerothermoelastic loads that play a critical role inthe design of high-speed vehicles, and flow separations that often leadto buffeting with undesirable structural oscillations. The simulation ofthese complex aeroelastic phenomena requires an integrated analysisof fluids and structures. This report presents a summary of thedevelopment, applications, and procedures to use the multidisciplinarycomputer code ENSAERO. This code is based on the Euler/Navier-Stokes flow equations and modal/finite-element structural equations.

Author

N95-13891*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Field, CA.DYNAMICS OF THE MCDONNELL-DOUGLAS LARGESCALE DYNAMIC RIG AND DYNAMIC CALIBRATION OFTHE ROTOR BALANCEKHANH NGUYEN and BENTON LAU Oct. 1994 28 p(Contract(s)/Grant(s): RTOP 505-59-36)(NASA-TM-108855; A-94007; NAS 1.15:108855) Avail: CASI HC A03/MFA01

A shake test was performed on the Large Scale Dynamic Rig inthe 40- by 80-Foot Wind Tunnel in support of the McDonnell DouglasAdvanced Rotor Technology (MDART) Test Program. The shake testidentifies the hub modes and the dynamic calibration matrix of the rotorbalance. For hub mode identification, three configurations were tested:wind tunnel scale unlocked with dampers engaged and disengaged,and wind tunnel scale locked. Test data were analyzed with a multi-degree-of-freedom time domain algorithm to identify the modal proper-ties of the hub modes. The damping of the low frequency hub modes(ground resonance modes) increases significantly with the wind tunneldampers engaged. For dynamic calibration of the rotor balance, theshake test was performed only with the wind tunnel dampers engaged.The dynamic calibration matrix, computed from the shake test datausing a least squares error method, is used to correct the five-per-revvibratory balance readings. The corrections are large for the side force,moderate for the axial force and inplane hub moments, and small for thenormal force. Author

N95-14144# Air Force Inst. of Tech., Wright-Patterson AFB, OH.School of Engineering.DAMAGE TOLERANT REPAIR TECHNIQUES FORPRESSURIZED AIRCRAFT FUSELAGES M.S. ThesisROBERT S. FREDELL 1994 280 p(AD-A281982; AFIT/CI/CIA-94-095) Avail: CASI HC A13/MF A03

Concerns over the safety of the continued use of aging transportaircraft have been voiced in the industry. A key component in the

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01 AERONAUTICS (GENERAL)

structural integrity of aging aircraft is the damage tolerance of fuselagestructural repairs. The investigation focuses on the analysis and testingof contemporary repair methods and develops two improvements. Thefirst technique, known as soft patching, is appropriate for damagetolerant riveted repairs to incidental fuselage damage. Soft patchinginvolves the use of high strength, moderate elastic modulus GLARE 3fiber metal laminate patches. They extend the fatigue life of rivetedrepairs to monolithic aluminum fuselages while reducing life cyclecosts. The second technique involves bonded crack patching of intactfatigue cracks in fuselage skins. An easy to use analysis program ispresented along with analytical and test results of a low cost, highperformance patch material known as GLARE 2. The findings demon-strate that GLARE 2 can replace the expensive boron/epoxy compos-ites used in fuselage crack patching applications. DTIC

N95-14419*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Field, CA.HIGHER HARMONIC CONTROL ANALYSIS FOR VIBRATIONREDUCTION OF HELICOPTER ROTOR SYSTEMSKHANH Q. NGUYEN Oct 1994 138 p(Contract(s)/Grant(s): RTOP 505-61-51)(NASA-TM-103855; A-91113; NAS1.15:103855) Avail: CASIHC A07/MFA02

An advanced higher harmonic control (HHC) analysis has beendeveloped and applied to investigate its effect on vibration reductionlevels, blade and control system fatigue loads, rotor performance, andpower requirements of servo-actuators. The analysis is based on afinite element method in space and time. A nonlinear time domainunsteady aerodynamic model, based on the indicial response formula-tion, is used to calculate the airloads. The rotor induced inflow iscomputed using a free wake model. The vehicle trim controls and bladesteady responses are solved as one coupled solution using a modifiedNewton method. A linear frequency-domain quasi-steady transfermatrix is used to relate the harmonics of the vibratory hub loads to theharmonics of the HHC inputs. Optimal HHC is calculated from theminimization of the vibratory hub loads expressed in term of a quadraticperformance index. Predicted vibratory hub shears are correlated withwind tunnel data. The fixed-gain HHC controller suppresses completelythe vibratory hub shears for most of steady or quasi-steady flightconditions. HHC actuator amplitudes and power increase significantlyat high forward speeds (above 100 knots). Due to the applied HHC, theblade torsional stresses and control loads are increased substantially.For flight conditions where the blades are stalled considerably, the HHCinput-output model is quite nonlinear. For such cases, the adaptive-gaincontroller is effective in suppressing vibratory hub loads, even thoughHHC may actually increase stall areas on the rotor disk. The fixed-gaincontroller performs poorly for such flight conditions. Comparison studyof different rotor systems indicates that a soft-inplane hingeless rotorrequires less actuator power at high speeds (above 130 knots) than anarticulated rotor, and a stiff-inplane hingeless rotor generally requiresmore actuator power than an articulated or a soft-inplane hingelessrotor. Parametric studies for a hingeless rotor operating in a transitionflight regime and for an articulated rotor operating at the level-flightboundary (high speed and high thrust conditions) indicate that bladeparameters including flap, lag, torsion stiffness distributions, linearpretwist, chordwise offset of center-of-mass from elastic axis andchordwise offset of elastic axis from aerodynamic center can beselected to minimize the actuator power requirements for HHC.

Author

Avail: CASI HC A03/MF A04This paper presents an overview of the structural aspects of the

design and development of a local reinforcement designed to lower thestresses in a region of the F-111C wing fitting which is prone to cracking.The stress analysis, with particular emphasis on the use of a unifiedconstitutive model for the cyclic inelastic response of the structure,representative specimen testing, thermal analysis and full scale statictesting of this design are summarized. Author

N95-14921 *# National Aeronautics and Space Administration. AmesResearch Center, Moffett Field, CA.AIR-BREATHING AEROSPACE PLANE DEVELOPMENTESSENTIAL: HYPERSONIC PROPULSION FLIGHT TESTSUNMEEL B. MEHTA Nov. 1994 16 p Presented at the SecondEuropean Symposium on Aerothermodynamics for Space Vehicles,ESTEC, Noordwijk (The Netherlands), 21-23 Nov. 1994(Contract(s)/Grant(s): RTOP 505-59-53)(NASA-TM-108857; A-95017; NAS 1.15:108857) Avail: CASI HC A03/MFA01

Hypersonic air-breathing propulsion utilizing scramjets can funda-mentally change transatmospheric accelerators for low earth-to-orbitand return transportation. The value and limitations of ground tests, offlight tests, and of computations are presented, and scramjet develop-ment requirements are discussed. It is proposed that near full-scalehypersonic propulsion flight tests are essential for developing a proto-type hypersonic propulsion system and for developing computational-design technology so that it can be used for designing this system. Inorder to determine how these objectives should be achieved, somelessons learned from past programs are presented. A conceptual two-stage-to-orbit (TSTO) prototype/experimental aerospace plane is rec-ommended as a means of providing access-to-space and for conductingflight tests. A road map for achieving these objectives is also presented.

Author

N95-15331* Sytronics, Inc., Dayton, OH.MORE SUPPORTABLE T-38A ENHANCEMENT STUDY FinalReport, Dec. 1993 - Jun. 1994WILLIAM T. KILPATRICK 20 Jun. 1994 312 p(Contract(s)/Grant(s): F33657-93-C-2440)(AD-A283671; DOC-0710-001) Avail: CASI HC A14/MF A03

The purpose of the More Supportable T-38A Enhancement Studywas to investigate methods of improving T-38A fleet readiness andreduce operational support costs. A comparative and functional analy-sis approach was utilized to identify specific T-38A aircraft design andsystem support deficiencies that could be improved through a redesigneffort or maintenance procedural changes. Several aircraft compo-nents were identified and targeted as potential redesign candidates.These T-38A components are also common to the F-5 and improve-ments to these components will enhance both T-38 and F-5 support-ability. DTIC

02

AERODYNAMICS

Includes aerodynamics of bodies, combinations, wings, rotors, andcontrol surfaces; and internal flow in ducts and turbomachinery.

N95-14477*# Monash Univ., Clayton (Australia). Dept of Mechani-cal Engineering.DEVELOPMENT OF A COMPOSITE REPAIR AND THEASSOCIATED INSPECTION INTERVALS FOR THE F-111CSTIFFENER RUNOUT REGIONR. JONES, L. MOLENT, J. PAUL, T. SAUNDERS, and W. K. CHIU InNASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabilityand Damage Tolerance p 339-350 Sep. 1994

A95-61728COMPOSITE PROPELLER SYSTEM FOR DORNIER 328LINDA E. TREGO Aerospace Engineering (Warrendale, Pennsylva-nia) (ISSN 0736-2536) vol. 13, no. 12 December 1993 p. 7-29(BTN-94-EIX94461290506) Copyright

The composite propeller system HD-E6 was selected for theDomier 328 regional airliner. It was chosen because it best met thestringest noise, weight and performance requirements of the aircraft

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AERODYNAMICS 02

Domier 328. The system features a propeller control unit, lightweightaluminum hub design, dual-acting cylinder, and lightweight compositeblades. El

N95-13701*# Old Dominion Univ., Norfolk, VA. Dept of MechanicalEngineering.AERODYNAMIC SHAPE OPTIMIZATION OF A HSCT TYPECONFIGURATION WITH IMPROVED SURFACE DEFINITIONProgress Report, 1 May 1993 - 30 Jun. 1994ALMUTTIL M. THOMAS and SURENDRA N. TIWARI Oct. 199432 p(Contract(s)/Grant(s): NCC1-68)(NASA-CR-197011; NAS 1.26:197011) Avail: CASI HC A03/MF A01

Two distinct parametrization procedures of generating free-formsurfaces to represent aerospace vehicles are presented. The firstprocedure is the representation using spline functions such as nonuni-form rational b-splines (NURBS) and the second is a novel (geometri-cal) parametrization using solutions to a suitably chosen partial differentialequation. The main idea is to develop a surface which is more versatileand can be used in an optimization process. Unstructured volume gridis generated by an advancing front algorithm and solutions obtainedusing an Euler solver. Grid sensitivity with respect to surface designparameters and aerodynamic sensitivity coefficients based on potentialflow is obtained using an automatic differentiator precompiler softwaretool. Aerodynamic shape optimization of a complete aircraft with twentyfour design variables is performed. High speed civil transport aircraft(HSCT) configurations are targeted to demonstrate the process.

Author

N95-13719*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.VUV SHOCK LAYER RADIATION IN AN ARC-JET WINDTUNNEL EXPERIMENTROGER A. CRAIG (MCAT Inst., Moffett Reid, CA.), GIUSEPPEPALUMBO (Eloret Corp., Santa Clara, CA.), and ARMANDOCARRASCO In MCAT Inst, Planetary Entry Experiments 27 p Jul.1994(Contract(s)/Grant(s): NCC2-653)Avail: CASI HC A03/MF A02

Measurements were made of the radiating gas cap of a blunt bodyin a NASA-Ames 20 MW arc-jet wind tunnel. The test gas was air.Spectra of the flux incident on a small aperture centered at thestagnation region were obtained. A helium-cooled, magnesium fluoridewindow transmitted the flux into an evacuated collimating system thatfocused the aperture onto the entrance slit of a spectrometer. Data wereobtained with films and by photomultipliers. The spectral rangescovered were the vacuum ultraviolet, VUV, (120 nm to 200 nm) and theultravioletto near infrared (200 nm to 900 nm) with resolutions from 0.05nm to 0.5 nm. This paper presents the preliminary VUV results from theexperiment. Results from the 200 nm to 900 nm spectral range havebeen presented elsewhere. Representative spectral records from 120nm to 200 nm are shown. The intense atomic oxygen and nitrogen lineswhich are of concern to hypersonic flight are measured. Carbon linesare are also seen. These results will be used to help develop andvalidate aerothermodynamic computational models of arc-jet windtunnel performance and help to assess the importance of VUV heatingto entering spacecraft Author

N95-13720*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.MEASURED AND CALCULATED SPECTRAL RADIATIONFROM A BLUNT BODY SHOCK LAYER IN AN ARC-JETWIND TUNNELDIKRAN S. BABIKIAN (Eloret Corp., Palo Alto, CA.), GIUSEPPEPALUMBO (EloretCorp.,PaloAlto,CA.),ROGERA.CRAIG (MCATInst., Moffett Field, CA.), CHUL PARK, GRANT PALMER, andSURENDRA P. SHARMA In MCAT Inst, Planetary Entry Experi-ments 11 p Jul. 1994 Presented at the 32d Aerospace SciencesMeeting, Reno, NV, 10-13 Jan. 1994; sponsored by AIAA

(Contract(s)/Grant(s): NCC2-653)(AIAA PAPER 94-0086) Avail: CASI HC A03/MF A02

Spectra of the shock layer radiation incident on the stagnationpoint of a blunt body placed in an arc-jet wind tunnel were measuredover the wavelength range from 600 nm to 880 nm. The test gas wasa mixture of 80 percent air and 20 percent argon by mass, and the runwas made in a highly nonequilibrium environment. The observedspectra contained contributions from atomic lines of nitrogen, oxygen,and argon, of bound-free and free-free continue, and band systems ofN2 and N2(+). The measured spectra were compared with the syntheticspectra, which were obtained through four steps: the calculation of thearc-heater characteristics, of the nozzle flow, of the blunt-body flow, andthe nonequilibrium radiation processes. The results show that theatomic lines are predicted approximately correctly, but all other sourcesare underpredicted by orders of magnitude. A possible explanation forthe discrepancy is presented. Author

N95-14103# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Ruid Dynamics Panel.SCALE EFFECTS ON AIRCRAFT AND WEAPONAERODYNAMICS [LES EFFETS D'ECHELLE ETL'AERODYNAMIQUE DES AERONEFS ET DES SYSTEMESD'ARMES]A. BARRY HAINES (Aircraft Research Association Ltd., Bedford,England.) and A. D. YOUNG Jul. 1994 247 p(AGARD-AG-323;ISBN-92-835-0754-1) Copyright Avail: CASI HCA11/MF A03

The present state of knowledge on scale effects at high lift and lowspeeds, at transonic speeds, and on aircraft drag are presented. Inaddition, scale effects in various important specific scale-sensitiveareas such as forebody vortex flows, the flow in and near open cavities,the flow into an air intake, the flow over propellers, and on ice accretionsimulation testing are discussed. The emphasis is on scale effects thathave been observed in flight-tunnel comparisons for specific aircraft. Itis concluded that much has been learned about scale effects; however,precise prediction can still be difficult. Twenty recommendations forfurther research are mentioned. This AQARDograph has been pro-duced at the request of the Fluid Dynamics Panel of AGARD.

Author

N95-14197# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Ruid Dynamics Panel.QUALITY ASSESSMENT FOR WIND TUNNEL TESTING[L'APPRECIATION DE LA QUALITE POUR LES ESSAIS ENSOUFFLERIE]Jul. 1994 92 p(AGARD-AR-304; ISBN-92-835-0753-3) Copyright Avail: CASI HCA05/MF A01

The wind tunnel continues to be the main instrument for providingexperimental aerodynamic data to the aerospace industry and theaerodynamic researcher for the purpose of load and performanceevaluation of theoretical results. In both cases, it is imperative that theuser has confidence in the quality of the results, which means that hemust have information of what accuracy to attach to the data. This reportdescribes a practical approach for assessing the uncertainty of experi-mental measurements. Although it concentrates on aerodynamic refer-ences data, the approach presented can be used to report data andassociated uncertainties for any other condition. The methodologydescribed is designed to facilitate communications and to encourageprofessional and practical analyses of complex problems. The mostrecent accepted technical concepts have been included in the method-ology. This report presents the results of a study by Working Group 15of the AGARD Ruid Dynamics Panel. Author

N95-14229*# National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.FOURTH HIGH ALPHA CONFERENCE, VOLUME1 Jul. 1994 212 p Conference held at Edwards, CA, 12-14 Jul. 1994(Contract(s)/Grant(s): RTOP 505-68-30)

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02 AERODYNAMICS

(NASA-CP-10143-VOL-1; H-2007-VOL-1; MAS 1.55:10143-VOL-1)Avail: CASI HC A10/MF AQ3

The goal of the Fourth High Alpha Conference was to focus on theflight validation of high angle-of-attack technologies and provide an in-depth review of the latest high angle-of-attack activities. Areas thatwere covered include: high angle-of-attack aerodynamics, propulsionand inlet dynamics, thrust vectoring, control laws and handling quali-ties, tactical utility, and forebody controls. For individual titles, see N95-14230 through N95-14238.

N95-14230*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.HIGH ALPHA TECHNOLOGY PROGRAM (HATP) GROUNDTEST TO FLIGHT COMPARISONS Status ReportR. M. HALL, D. W. BANKS, DAVID F. FISHER, F. GHAFFARI, D. G.MURRI, J. C. ROSS, and WENDY R. LANSER In NASA. DrydenRight Research Center, Fourth High Alpha Conference, Volume 125 p Jul. 1994Avail: CASI HC A03/MF A03

This status paper reviews the experimental ground test programof the High Alpha Technology Program (HATP). The reasons forconducting this ground test program had their origins during the 1970'swhen several difficulties were experienced during the developmentprograms of both the F-18 and F-16. A careful assessment of groundtest to flight correlations appeared to be important for reestablishing ahigh degree of confidence in our ground test methodology. The currentpaper will then focus on one aspect of the HATP program that isintended to improve the correlation between ground test and flight, high-alpha gritting. The importance of this work arises from the sensitivity ofconfigurations with smooth-sided fore bodies to Reynolds number. Aftergiving examples of the effects of Reynolds number, the paper willhighlight efforts at forebody gritting. Finally, the paper will conclude bysummarizing the charter of the HATP Experimental AerodynamicsWorking Group and future experimental testing plans. Author

Conference, Volume 1 33 p Jul. 1994Avail: CASI HC A03/MF A03

The current research is aimed at developing and extendingnumerical methods to accurately predict the high Reynolds number flowabout the NASA F-18 HARV at large angles of attack. The resultingcodes are validated by comparison of the numerical results with in-flightaerodynamic measurements and flow visualization obtained on theHARV. Further, computations have been used to provide an analysisand numerical optimization of a pneumatic slot blowing concept, and amechanical strake concept, for use as potential forebody flow controldevices in improving high-alpha maneuverability. Author

N95-14233'# Analytical Services and Materials, Inc., Hampton, VA.HYBRID STRUCTURED/UNSTRUCTURED GRIDCOMPUTATIONS FOR THE F/A-18 AT HIGH ANGLE OFATTACKROBERT T. BIEDRON and DAVID L. WHITAKER In NASA. DrydenRight Research Center, Fourth High Alpha Conference, Volume 117 p Jul. 1994Avail: CASI HC A03/MF A03

At high angles of attack, vortical flows play a crucial role in themaintenance of lift for fighter aircraft However, under certain condi-tions, the vortical flow can have an adverse effect on the aircraft. On theF/A-18 the LEX vortex can impinge on the tail; at high angles of attackthe unsteady flow from vortex bursting can cause structural fatigue onthe vertical tails. At high angles of attack, the flow field can be quitecomplex, and a computational analysis challenging. A full configurationanalysis with viscous structured grids can be computationally expen-sive and the task of generating the requisite grids can be quite difficult.To mitigate these difficulties and provide a medium-fidelity analysistool, a hybrid structured/unstructured approach was adopted for thiswork. In this analysis, the formation and roll-up of the LEX vortex iscomputed with a structured Navier-Stokes solver, and the resultingvortex propagated downstream with an unstructured Euler solver.

Author

N95-14231*# National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.FLIGHT AND FULL-SCALE WIND-TUNNEL COMPARISONOF PRESSURE DISTRIBUTIONS FROM AN F-18 AIRCRAFTAT HIGH ANGLES OF ATTACKDAVID F. FISHER and WENDY R. LANSER In its Fourth High AlphaConference, Volume 1 20 p Jul. 1994Avail: CASI HC A03/MF A03

Pressure distributions were obtained at nearly identical fuselagestations and wing chord butt lines in flight on the F-18 HARV at NASADryden Right Research Center and in the NASA Ames ResearchCenter's 80 by 120 ft wind tunnel on a full-scale F/A-18 aircraft. Thestatic pressures were measured at the identical five stations on theforebody, three stations on the left and right leading-edge extensions,and three spanwise stations on the wing. Comparisons of the flight andwind-tunnel pressure distributions were made at alpha=30 deg, 45 deg,and 60 deg/59 deg. In general, very good agreement was found. Minordifferences were noted at the forebody at alpha = 45 deg and 60 deg inthe magnitude of the vortex footprints and a Mach number effect wasnoted at the leading-edge extension at alpha = 30 deg. The inboardleading edge flap data from the wind tunnel at alpha = 59 deg showeda suction peak that did not appear in the flight data. This was the resultof a vortex from the comer of the leading edge flap whose path wasaltered by the lack of an engine simulation in the wind tunnel. Author

N95-14232*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.NUMERICAL SIMULATION OF THE FLOW ABOUT AN F-18AIRCRAFT IN THE HIGH-ALPHA REGIMESCOTT M. MURMAN (MCAT Inst., Moffett Reid, CA.) and YEHIA M.RIZK In NASA. Dryden Flight Research Center, Fourth High Alpha

N95-14234*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.COMPARISON OF X-31 FLIGHT, WIND-TUNNEL, ANDWATER-TUNNEL YAWING MOMENT ASYMMETRIES ATHIGH ANGLES OF ATTACKBRENT R. COBLEIGH (Planning Research Corp., Edwards, CA.),MARK A. CROOM, and B. F. TAMRAT In NASA. Dryden RightResearch Center, Fourth High Alpha Conference, Volume 1 p 21Jul. 1994Avail: CASI HC A03/MF A03

The X-31 aircraft are being used in the enhanced fighter maneu-verability (EFM) research program, which is jointly funded by the (U.S.)Advanced Research Projects Agency (ARPA) and Germany's FederalMinistry of Defense (FMOD). The flight test portion of the program,which involves two aircraft, is being conducted by an International TestOrganization (ITO) comprising the National Aeronautics and SpaceAdministration (NASA), the U.S. Navy, the U.S. Air Force, RockwellInternational, and Deutsche Aerospace (DASA). The goals of the flightprogram are to demonstrate EFM technologies, investigate close-in-combat exchange ratios, develop design requirements, build a data-base for application to future fighter aircraft, and develop and validatelow-cost prototype concepts. For longitudinal control the X-31 usescanards, symmetrical movement of the trailing-edge flaps, and pitchdeflection of the thrust vectoring system. The trim, inertial coupling, andengine gyroscopic coupling compensation tasks are performed prima-rily by the trailing-edge flaps. For lateral-directional control the aircraftuses differential deflection of the trailing-edge flaps for roll coordinationand a conventional rudder combined with the thrust vectoring systemto provide yaw control. The rudder is only effective up to about 40 degangle of attack (alpha), after which the thrust vectoring becomes theprimary yaw control effector. Both the leading-edge flaps and the inletlip are scheduled with the angle of attack to provide best performance.

Author

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N95-14235*# Deutsche Forschungs- und Versuchsanstalt fuer Luft-und Raumfahrt, Brunswick (Germany). Inst. of Right Mechanics.PARAMETER IDENTIFICATION FOR X-31A AT HIGHANGLES OF ATTACKS. WEISS, D. ROHLF, and ERMIN PLAETSCHKE In NASA. DrydenRight Research Center, Fourth High Alpha Conference, Volume 112 p Jul. 1994Avail: CASI HC A03/MF A03

The U.SVGerman experimental aircraft X-31A was designed andconstructed to demonstrate enhanced fighter maneuverability. Post-stall maneuvering is enabled by applying new technologies such ashigh angle of attack aerodynamics and flight control system integratedthrust vectoring. Two demonstrator aircraft have been built by the maincontractors, Rockwell International and Deutsche Aerospace (formerlyMBB). Right testing started in October 1990 and before the end of 1992both aircraft had accomplished a significant number of flights coveringthe entire AoA regime from about -5 to 70 deg. Throughout the envelopeexpansion, DLR Institute of Right Mechanics conducted parameteridentification (PID) to determine the aerodynamic parameters of theaircraft from flight test data and to compare the results to the predictionsfrom the aerodynamic dataset (ADS). The application of systemidentification to high AoA / post-stall flight data raises some majorproblems, which are discussed in this paper. Results from bothlongitudinal and lateral-directional motion will be presented. Author

N95-14236*# Bihrie Applied Research, Inc., Jericho, NY.VALIDATION OF THE NASA DRYDEN X-31 SIMULATIONAND EVALUATION OF MECHANIZATION TECHNIQUESEDWARD DICKES, JACOB KAY, and JOHN RALSTON In NASA.Dryden Flight Research Center, Fourth High Alpha Conference,Volume 1 23 p Jul. 1994Avail: CASI HC A03/MF A03

This paper shall discuss the evaluation of the original Dryden X-31 aerodynamic math model, processes involved in the justification andcreation of the modified data base, and comparison time history resultsof the model response with flight test Author

N95-14237*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.FREE-TO-ROLL TESTS OF X-31 AND F-18 SUBSCALEMODELS WITH CORRELATION TO FLIGHT TEST RESULTSDAVID L. WILLIAMS, II (Notre Dame Univ., IN.), ROBERT C.NELSON (Notre Dame Univ., IN.), and DAVID F. FISHER /nNASA.Dryden Flight Research Center, Fourth High Alpha Conference,Volume 1 28 p Jul. 1994Avail: CASI HC A03/MF A03

This presentation will concentrate on a series of low-speed windtunnel tests conducted on a 2.5 percent subscale F-18 model and a 2percent subscale X-31 model. The model's control surfaces wereunaugmented; and for the most part, were deflected at a constant anglethroughout the tests. The tests consisted mostly of free-to-roll experi-ments conducted with the use of an air-bearing, surface pressuremeasurements, off-surface flow visualization, and force-balance tests.Where possible the results of the subscale tests have been comparedto flight test data, or to other wind tunnel data taken at higher Reynoldsnumbers. Author

N95-14238*# Eidetics Aircraft, Inc., Torrance, CA.STATIC AND DYNAMIC FORCE/MOMENT MEASUREMENTSIN THE EIDETICS WATER TUNNELCARLOS J. SUAREZ and GERALD N. MALCOLM In NASA. DrydenRight Research Center, Fourth High Alpha Conference, Volume 124 p Jul. 1994(Contract(s)/Grant(s): NAS2-13571)Avail: CASI HC A03/MF A03

Water tunnels have been utilized in one form or another to explorefluid mechanics and aerodynamics phenomena since the days ofLeonardo da Vinci. Water tunnel testing is attractive because of therelatively low cost and quick turn-around time to perform flow visualiza-

tion experiments and evaluate the results. The principal limitation of awater tunnel is that the low flow speed, which provides for detailedvisualization, also results in very small hydrodynamic (aerodynamic)forces on the model, which, in the past, have proven to be difficult tomeasure accurately. However, the advent of semi-conductor straingage technology and devices associated with data acquisition such aslow-noise amplifiers, electronic filters, and digital recording have madeaccurate measurements of very low strain levels feasible. The principalobjective of this research effort was to develop a multi-component straingage balance to measure forces and moments on models tested in flowvisualization water tunnels. A balance was designed that allowsmeasuring normal and side forces, and pitching, yawing and rollingmoments (no axial force). The balance mounts internally in the modeland is used in a manner typical of wind tunnel balances. The keydifferences between a water tunnel balance and a wind tunnel balanceare the requirement for very high sensitivity since the loads are very low(typical normal force is 0.2 Ibs), the need for water proofing the gageelements, and the small size required to fit into typical water tunnelmodels. Author

N95-14239*# National Aeronautics and Space Administration. HughL. Dryden Flight Research Center, Edwards, CA.FOURTH HIGH ALPHA CONFERENCE, VOLUME 2Jul. 1994 235 p Conference held at Edwards, CA, 12-14 Jul.1994(Contract(s)/Grant(s): RTOP-505-68-30)(NASA-CP-10143-VOL-2; H-2007-VOL-2; NAS 1.55:10143-VOL-2)Avail: CASI HC A11/MF A03

The goal of the Fourth High Alpha Conference, held at the NASADryden Right Research Center on July 12-14,1994, was to focus on theflight validation of high angle of attack technologies and provide an in-depth review of the latest high angle of attack activities. Areas that werecovered include high angle of attack aerodynamics, propulsion and inletdynamics, thrust vectoring, control laws and handling qualities, andtactical utility. For individual titles, see N95-14240 through N95-14250.

N95-14240** National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.F-18 HIGH ALPHA RESEARCH VEHICLE: LESSONSLEARNEDALBION H. BOWERS, VICTORIA A. REGENIE, and BRADLEY C.FLICK In its Fourth High Alpha Conference, Volume 2 15 pJul. 1994Avail: CASI HC A03/MF A03

The F-18 High Alpha Research Vehicle has proven to be a usefulresearch tool with many unique capabilities. Many of these capabilitiesare to assist in characterizing flight at high angles of attack, while someprovide significant research in their own right. Of these, the thrustvectoring system, the unique ability to rapidly reprogram flight controls,the reprogrammable mission computer, and a reprogrammable onboardexcitation system have allowed an increased utility and versatility of theresearch being conducted. Because of this multifaceted approach toresearch in the high angle of attack regime, the capabilities of the F-18High Alpha Research Vehicle were designed to cover as many highalpha technology bases as the program would allow. These areasinclude aerodynamics, controls, handling qualities, and propulsion.

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N95-14241 *# National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.DESIGN AND DEVELOPMENT OF AN F/A-18 INLETDISTORTION RAKE: A COST AND TIME SAVING SOLUTIONANDREW J. YUHAS, RONALD J. RAY, RICHARD R. BURLEY,WILLIAM G. STEENKEN, LEON LECHTENBERG, and DONTHORNTON In its Fourth High Alpha Conference, Volume 2 17 pJul. 1994Avail: CASI HC A03/MF A03

An innovative inlet total-pressure distortion measurement rake

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has been designed and developed for the F/A-18 A/B/C/D aircraft inletThe design was conceived by NASA and General Electric AircraftEngines (Evendale, Ohio). This rake has been flight qualified and flownin the F-18 High Alpha Research Vehicle (HARV) at NASA DrydenRight Research Center. The rake's eight-legged, one-piece wagonwheel design was developed at a reduced cost and offers reducedinstallation time compared with traditional designs. The rake features40 dual measurement ports for both low- and high-frequency pressuremeasurements with the high-frequency transducer mounted at the portThe high-frequency transducer offers direct absolute pressure mea-surements from low frequency to the highest frequency of interestthereby allowing the rake to be used during highly dynamic aircraftmaneuvers. Outstanding structural characteristics are inherent to thedesign through its construction and use of lightweight materials.

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N95-14242*# Naval Air Warfare Center, Patuxent River, MD. AircraftDiv.X-31 POST-STALL ENVELOPE EXPANSION AND TACTICALUTILITY TESTINGDAVE CANTER In NASA. Dryden Right Research Center, FourthHigh Alpha Conference, Volume 2 19 p Jul. 1994Avail: CASI HC A03/MF A03

Technical and nontechnical lessons learned from the X-31 aircraftprogram are described in this viewgraph presentation. The tacticalutility of high angle of attack flight and thrust vector control is discussed.

CASI

N95-14243** Deutsche Aerospace A.G., Munich (Germany).X-31 QUASI-TAILLESS FLIGHT DEMONSTRATIONPETER HUBER and HARVEY G. SCHELLENGER friNASA. DrydenRight Research Center, Fourth High Alpha Conference, Volume 214 p Jul. 1994Avail: CASI HC A03/MF A03

The primary objective of the quasi-tailless flight demonstration isto demonstrate the feasibility of using thrust vectoring for directionalcontrol of an unstable aircraft. By using this low-cost low-risk approachit is possible to get information about required thrust vector controlpower and deflection rates from an inflight experiment as well as insightin low-power thrust vectoring issues. The quasi-tailless flight demon-stration series with the X-31 began in March 1994. The demonstrationflight condition was Mach 1.2 at 37,500 feet. A sen'es of basic flyingquality maneuvers, doublets, bank to bank rolls, and wind-up-tumshave been performed with a simulated 100% vertical tail reduction.Right test and supporting simulation demonstrated that the quasi-tailless approach is effective in representing the reduced stability oftailless configurations. The flights also demonstrated that thrust vector-ing could be effectively used to stabilize a directionally unstableconfiguration and provide control power for maneuver coordination.

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N95-14244'# National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.X-31 HIGH ANGLE OF ATTACK CONTROL SYSTEMPERFORMANCEPETER HUBER (Deutsche Aerospace A.G., Munich, Germany.) andPATRICIA SEAMOUNT In its Fourth High Alpha Conference,Volume 2 19 p Jul. 1994Avail: CASI HC A03/MF A03

The design goals for the X-31 flight control system were: (1) level1 handling qualities during post-stall maneuvering (30 to 70 degreesangle-of-attack); (2) thrust vectoring to enhance performance acrossthe flight envelope; and (3) adequate pitch-down authority at high angle-of-attack. Additional performance goals are discussed. A description ofthe flight control system is presented, highlighting flight control systemfeatures in the pitch and roll axes and X-31 thrust vectoring character-istics. The high angle-of-attack envelope clearance approach will bedescribed, including a brief explanation of analysis techniques andtools. Also, problems encountered during envelope expansion will bediscussed. This presentation emphasizes control system solutions toproblems encountered in envelope expansion. An essentially 'care free'

envelope was cleared for the close-in-combat demonstrator phase.High angle-of-attack flying qualities maneuvers are currently beingflown and evaluated. These results are compared with pilot opinionsexpressed during the close-in-combat program and with results ob-tained from the F-18 HARV for identical maneuvers. The status andpreliminary results of these tests are discussed. Derived from text

N95-14245*# Lockheed Corp., Fort Worth, TX.FLIGHT TEST RESULTS OF THE F-16 AIRCRAFT MODIFIEDWITH THE AXISYMMETRIC VECTORING EXHAUST NOZZLEPAUL D. ANNA and DAVID S. KIDMAN In NASA. Dryden RightResearch Center, Fourth High Alpha Conference, Volume 2 15 pJul. 1994Avail: CASI HC A03/MF A03

The results of the envelope expansion phase of the F-16 Multi-Axis Thrust Vectoring (MAW) program are presented in viewgraphformat. The objectives and test approach are presented followed byresults of testing with the initial control law configuration. The revisedflight control laws are discussed followed by test results with the revisedcontrol laws. Additional testing added to the program, nose chines,parameter identification maneuvers, and the extended range angle ofattack cones are briefly discussed. Derived from text

N95-14246*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.FLIGHT VALIDATION OF GROUND-BASED ASSESSMENTFOR CONTROL POWER REQUIREMENTS AT HIGHANGLES OF ATTACKMARILYN E. OGBURN, HOLLY M. ROSS, JOHN V. FOSTER, JO-SEPH W. PAHLE, CHARLES A. STERNBERG, R1CARDO TRAVEN,JAMES B. LACKEY, and TROY D. ABBOTT In NASA. Dryden RightResearch Center, Fourth High Alpha Conference, Volume 2 20 pJul. 1994Avail: CASI HC A03/MF A03

A review is presented in viewgraph format of an ongoing NASA/U.S. Navy study to determine control power requirements at highangles of attack for the next generation high-performance aircraft. Thispaper focuses on recent flight test activities using the NASA High AlphaResearch Vehicle (HARV), which are intended to validate results ofprevious ground-based simulation studies. The purpose of this study isdiscussed, and the overall program structure, approach, and objectivesare described. Results from two areas of investigation are presented:(1) nose-down control power requirements and (2) lateral-directionalcontrol power requirements. Selected results which illustrate issuesand challenges that are being addressed in the study are discussedincluding test methodology, comparisons between simulation andflight and general lessons learned. Derived from text

N95-14247*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.HIGH ANGLE OF ATTACK FLYING QUALITIES CRITERIAFOR LONGITUDINAL RATE COMMAND SYSTEMSDAVID J. WILSON (McDonnell-Douglas Aerospace, Saint Louis,MO.), KEVIN D. CITURS (McDonnell-Douglas Aerospace, SaintLouis, MO.), and JOHN B. DAVIDSON In NASA. Dryden FlightResearch Center, Fourth High Alpha Conference, Volume 2 14 pJul. 1994Avail: CASI HC A03/MF A03

This study was designed to investigate flying qualities require-ments of alternate pitch command systems for fighter aircraft at highangle of attack. Flying qualities design guidelines have already beendeveloped for angle of attack command systems at 30, 45, and 60degrees angle of attack, so this research fills a similar need for ratecommand systems. Flying qualities tasks that require post-stall maneu-vering were tested during piloted simulations in the McDonnell DouglasAerospace Manned Air Combat Simulation facility. A generic fighteraircraft model was used to test angle of attack rate and pitch ratecommand systems for longitudinal gross acquisition and tracking tasksat high angle of attack. A wide range of longitudinal dynamic variationswere tested at 30,45, and 60 degrees angle of attack. Pilot comments,Cooper-Harper ratings, and pilot induced oscillation ratings were taken

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from five pilots from NASA, USN, CAP, and McDonnell DouglasAerospace. This data was used to form longitudinal design guidelinesfor rate command systems at high angle of attack. These criteriaprovide control law design guidance for fighter aircraft at high angle ofattack, low speed flight conditions. Additional time history analyseswere conducted using the longitudinal gross acquisition data to look atpotential agility measures of merit and correlate agility usage to flyingqualities boundaries. This paper presents an overview of this research.

Author (revised)

N95-14248** Lockheed Corp., Fort Worth, TX.VISTA/F-16 MULTI-AXIS THRUST VECTORING (MATV)CONTROL LAW DESIGN AND EVALUATIONW. D. ZWERNEMAN and B. G. ELLER In NASA. Dryden FlightResearch Center, Fourth High Alpha Conference, Volume 2 19 pJul. 1994Avail: CASI HC A03/MF A03

For the Multi-Axis Thrust Vectoring (MATV) program, a newcontrol law was developed using multi-axis thrust vectoring to augmentthe aircraft's aerodynamic control power to provide maneuverabilityabove the normal F-16 angle of attack limit. The control law architecturewas developed using Lockheed Fort Worth's offline and piloted simu-lation capabilities. The final flight control laws were used in flight test todemonstrate tactical benefits gained by using thrust vectoring in air-to-air combat. Differences between the simulator aerodynamics data baseand the actual aircraft aerodynamics led to significantly different lateral-directional flying qualities during the flight test program than thoseidentified during piloted simulation. A 'dial-a-gain' flight test control lawupdate was performed in the middle of the flight test program. Thisapproach allowed for inflight optimization of the aircraft's flying qualities.While this approach is not preferred over updating the simulatoraerodynamic data base and then updating the control laws, the finalselected gain set did provide adequate lateral-directional flying qualitiesover the MATV flight envelope. The resulting handling qualities and thedeparture resistance of the aircraft allowed the 422nd_squadron pilotsto focus entirely on evaluating the aircraft's tactical utility.

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N95-14249*# National Aeronautics and Space Administration. HughL Dryden Right Research Center, Edwards, CA.MULTI-APPLICATION CONTROLS: ROBUST NONLINEARMULTIVARIABLE AEROSPACE CONTROLS APPLICATIONSDALE F. ENNS (Honeywell, Inc., Minneapolis, MM.), DANIEL J.BUGAJSKI (Honeywell, Inc., Minneapolis, MN.), JOHN CARTER,and BOB ANTONIEWICZ In its Fourth High Alpha Conference,Volume 2 26 p Jul. 1994Avail: CASI HC A03/MF A03

This viewgraph presentation describes the general methodologyused to apply Honywell's Multi-Application Control (MACH) and thespecific application to the F-18 High Angle-of-Attack Research Vehicle(HARV) including piloted simulation handling qualities evaluation. Thegeneral steps include insertion of modeling data for geometry and massproperties, aerodynamics, propulsion data and assumptions, require-ments and specifications, e.g. definition of control variables, handlingqualities, stability margins and statements for bandwidth, controlpower, priorities, position and rate limits. The specific steps includechoice of independent variables for least squares fits to aerodynamicand propulsion data, modifications to the management of the controlswith regard to integrator windup and actuation limiting and priorities, e.g.pitch priority over roll, and command limiting to prevent departures and/or undesirable inertia! coupling or inability to recover to a stable trimcondition. The HARV control problem is characterized by significantnonlineatfties and multivariable interactions in the low speed, highangle-of-attack, high angular rate flight regime. Systematic approachesto the control of vehicle motions modeled with coupled nonlinearequations of motion have been developed. This paper will discuss thedynamic inversion approach which explicity accounts for nonlinearitiesin the control design. Multiple control effectors (including aerodynamic

control surfaces and thrust vectoring control) and sensors are used tocontrol the motions of the vehicles in several degrees-of-freedom.Several maneuvers will be used to illustrate performance of MACH inthe high angle-of-attack flight regime. Analytical methods for assessingthe robust performance of the multivariable control system in thepresence of math modeling uncertainty, disturbances, and commandshave reached a high level of maturity. The structured singular value(mu) frequency response methodology is presented as a method foranalyzing robust performance and the mu-synthesis method will bepresented as a method for synthesizing a robust control system. Thepaper concludes with the author's expectations regarding future appli-cations of robust nonlinear multivariable controls. Author (revised)

N95-14251'# National Aeronautics and Space Administration. HughL. Dryden Right Research Center, Edwards, CA.FOURTH HIGH ALPHA CONFERENCE, VOLUME3Jul. 1994 191 p Conference held at Edwards, CA, 12-14Jul. 1994(Contract(s)/Grant(s): RTOP-505-68-30)(NASA-CP-10143-VOL-3; H-2007-VOL-3; NAS 1.55:10143-VOL-3)Avail: CASI HC A09/MF A02

The goal of this conference was to focus on the flight validation ofhigh-angle-of-attack technologies and provide an in-depth review of thelatest high-angle-of-attack activities. Areas covered include: (1) high-angle-of-attack aerodynamics; (2) propulsion and inlet dynamics; (3)thrust vectoring; (4) control laws and handling qualities; (5) tacticalutility; and (6) forebody controls. For individual titles, see N95-14252through N95-14259.

N95-14252*# Naval Air Warfare Center, Patuxent River, MD.NAVY AND THE HARV: HIGH ANGLE OF ATTACKTACTICAL UTILITY ISSUESCHARLES A. STERNBERG, RICARDO TRAVEN, and JAMES B.LACKEY In NASA. Dryden Right Research Center, Fourth High AlphaConference, Volume 3 19 p Jul. 1994Avail: CASI HC A03/MF A02

This presentation will highlight results from the latest Navy evalu-ation of the HARV (March 1994) and focus primarily on the impressionsfrom a piloting standpoint of the tactical utility of thrust vectoring. Issueto be addressed will be mission suitability of high AOA flight, visual andmotion feedback cues associated with operating at high AOA, and theadaptability of a pilot to effectively use the increased control powerprovided by the thrust vectoring system. Derived from text

N95-14253*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Field, CA.COMPUTATIONAL ANALYSIS OF FOREBODY TANGENTIALSLOT BLOWINGKEN GEE (MCAT Inst, Moffett Reid, CA.), ROXANA M. AGOSTA-GREENMAN, YEHIA M. RIZK, LEWIS B. SCHIFF, and RUSSELL M.CUMMINGS In NASA. Dryden Right Research Center, Fourth HighAlpha Conference, Volume 3 22 p Jul. 1994Avail: CASI HC A03/MF A02

An overview of the computational effort to analyze forebodytangential slot blowing is presented. Tangential slot blowing generatesside force and yawing moment which may be used to control an aircraftflying at high-angle-of-attack. Two different geometries are used in theanalysis: (1) The High Alpha Research Vehicle; and (2) a generic chinedforebody. Computations using the isolated F/A-18 forebody are ob-tained at full-scale wind tunnel test conditions for direct comparison withavailable experimental data. The effects of over- and under-blowing onforce and moment production are analyzed. Time-accurate solutionsusing the isolated forebody are obtained to study the force onset timelagof tangential slot blowing. Computations using the generic chinedforebody are obtained at experimental wind tunnel conditions, and theresults compared with available experimental data. This computationalanalysis compliments the experimental results and provides a detailedunderstanding of the effects of tangential slot blowing on the flow fieldabout simple and complex geometries. Derived from text

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N95-14254*# Bdetics Aircraft, Inc.. Torrance, CA.F/A-18 AND F-16 FOREBODY VORTEX CONTROL, STATICAND ROTARY-BALANCE RESULTSBRIAN KRAMER and BROOKE SMITH In NASA. Dryden RightResearch Center, Fourth High Alpha Conference, Volume 3 22 pJul. 1994Avail: CASI HC A03/MF A02

The results from research on forebody vortex control on both theF/A-18 and the F-16 aircraft will be shown. Several methods of forebodyvortex control, including mechanical and pneumatic schemes, will bediscussed. The wind tunnel data includes both static and rotary balancedata for forebody vortex control. Time lags between activation ordeactivation of the pneumatic control and when the aircraft experiencesthe resultant forces are also discussed. The static (non-rotating) forcesand pressures are then compared to similar configurations tested in theNASA Langley and DTRC Wind Tunnel, the NASA Ames 80'x120' WindTunnel, and in flight on the High Angle of Attack Research Vehicle(HARV). Derived from text

N95-14255*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.COMPARISON OF FULL-SCALE, SMALL-SCALE, AND CFDRESULTS FOR F/A-18 FOREBODY SLOT BLOWINGWENDY R. LANSER, LARRY A. MEYN, and KEVIN D. JAMES InNASA. Dryden Right Research Center, Fourth High Alpha Conference,Volumes 19 p Jul. 1994Avail: CASI HC A03/MF A02

It has been shown experimentally that forebody flow controldevices provide a significant increase in yaw control for fighter aircraftat high angle-of-attack. This study presents comparisons of the variousexperimental and computational results for tangential slot blowing onthe F/A-18 configuration. Experimental results are from the full-scaleand 6 percent-scale model test and computational solutions are fromboth isolated forebody and and full aircraft configurations. The empha-sis is on identifying trends in the variation of yawing moment withblowing-slot exit conditions. None of the traditional parameters (massflow ratio, blowing momentum coefficient, velocity ratio) succeeded incollapsing all of the results into a common curve. Several factors mayeffect the agreement between the 6 percent- and full-scale resultsincluding Reynolds number effects, sensitivity of boundary layer tran-sition from laminar to turbulent flow, and poor geometric fidelity,particularly of the blowing slot. The disagreement between the full-scaleand computed yawing moments may be due to a mismatch in the slotexit conditions for the same mass flow ratio or aircraft configurationmodeling. The general behavior of slot blowing on the 6 percent-scaleand computational models is correct, but neither matches the full-scaleresults. Author

N95-14256*# McDonnell-Douglas Research Labs., Saint Louis, MO.LOW-ENERGY PNEUMATIC CONTROL OF FOREBODYVORTICESFREDERICK W. ROOS In NASA. Dryden Right Research Center,Fourth High Alpha Conference, Volume 3 16 p Jul. 1994Avail: CASI HC A03/MF A02

This research will be exploring the prospect of employing blunt-ness, known to suppress the tendency toward asymmetry on slenderforebodies, jointly with pneumatic manipulation as a system of forebodyasymmetry control. The influences of jet location and direction, blowingrate, relative noise bluntness, angle of attack, and state of flowseparation feeding the vortices (laminar vs. turbulent) will be evaluated.

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N95-14257*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.PREPARATIONS FOR FLIGHT RESEARCH TO EVALUATEACTUATED FOREBODY STRAKES ON THE F-18 HIGH-ALPHA RESEARCH VEHICLEDANIEL G. MURRI, GAUTAM H. SHAH, and DANIEL J. DICARLO

In NASA. Dryden Right Research Center, Fourth High Alpha Confer-ence, Volumes 20 p Jul. 1994Avail: CASI HC A03/MF A02

As part of the NASA High-Angle-of-Attack Technology Program(HATP), flight tests are currently being conducted with a multi-axisthrust vectoring system applied to the NASA F-18 High Alpha ResearchVehicle (HARV). A follow-on series of flight tests with the NASA F-18HARV will be focusing on the application of actuated forebody strakecontrols. These controls are designed to provide increased levels ofyaw control at high angles of attack where conventional aerodynamiccontrols become ineffective. The series of flight tests are collectivelyreferred to as the Actuated Nose Strakes for Enhanced Rolling (ANSER)Right Experiment. The development of actuated forebody strakecontrols for the F-18 HARV is discussed and a summary of the groundtests conducted in support of the flight experiment is provided. Asummary of the preparations for the flight tests is also provided.

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N95-14258*# McDonnell-Douglas Corp., Saint Louis, MO.INTEGRATION OF A MECHANICAL FOREBODY VORTEXCONTROL SYSTEM INTO THE F-15RICHARD E. BOALBEY, KEVIN D. CITURS, WAYNE L. ELY, STEPHENP. HARBAUGH, WILLIAM B. HOLLINGSWORTH, and RONALD LPHILLIPS In NASA. Dryden Right Research Center, Fourth HighAlpha Conference, Volume 3 20 p Jul. 1994Avail: CASI HC A03/MF A02

The goal of the F-15 Forebody Vortex Control (FVC) program is todevelop a production FVC system for the F-15. The system may consistof either a mechanically actuated device such as the strakes developedfor the HARV program, or a pneumatic device such as the port blowingsystem being tested on the X-29. Both types of systems are beingevaluated under this program. Background information on the F-15 anda description and overview of forebody vortex controls (FVC) will bepresented. Derived from text

N95-14259** Wright Lab., Wright-Patterson AFB, OH.FLIGHT EVALUATION OF PNEUMATIC FOREBODYVORTEX CONTROL IN POST-STALL FLIGHTLAWRENCE A. WALCHLI /nNASA. Dryden Right Research Center,Fourth High Alpha Conference, Volume 3 24 p Jul. 1994Avail: CASI HC A03/MF A02

The following topics are discussed: (1) X-29 description; VortexRow Control (VFC) technology description; (3) X-29 VFC wind tunnelresults (forebody only); (4) X-29 VFC wind tunnel results (full configu-ration yawing moment); (5) X-29 VFC wind tunnel results (full configu-ration C(sub n) with sideslip); (6) X-29VFC wind tunnel results (fullconfiguration pitching moment); (7) VFC optimized nozzle details; (8) X-29 forebody nozzle configuration; (9) X-29 VFC system stored gasschematic; (10) X-29 VFC system stored gas installation; (11) VFCeffectiveness at zero sideslip; (12) VFC effectiveness at 35 AOA withsideslip; (13) VFC Roll' at 40 AOA; (14) Effects of VFC on wing rock;(15) Integrated controls C(sub n) prediction; (16) Proposed F-15 withlateral control laws with active VFC; (17) Simulated F-15 roll perfor-mance with active VFC; (18) Simulated F-15 spin recovery with activeVFC; (19) Test team restructuring; (20) testbed selection; (21) Simula-tion for risk reduction; (22) Benefits of high pressure system; and (23)Advanced weapon system integration. Derived from text

N95-14264# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Ruid Dynamics Panel.COMPUTATIONAL AERODYNAMICS BASED ON THEEULER EQUATIONS [L'AERODYNAMIQUE NUMERIQUE APARTIR DES EQUATIONS D'EULER]J. W. SLOOFF, ed. (National Aerospace Lab., Amsterdam, Nether-lands.) and W. SCHMIDT, ed. (Deutsche Aerospace A.G., Munich,Germany.) Sep. 1994 250 p Original contains color illustrations(AGARD-AG-325; ISBN-92-836-1005-9) Copyright Avail: CASI HCA11/MFA03

A survey of the state of the art of Computational Aerodynamics

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based on the Euler Equations is presented. For the major Euler Codesthat are currently in use in the NATO countries, numerical schemes,algorithms, grid generation, physical and numerical aspects, as well asa wide range of applications are included. Background material re-quired for understanding the physics modelled by the Euler Equationsis also presented. Areas of application concentrate on numericalsimulation of external flows about aerospace vehicles. Internal flowsand turbomachinery applications are not extensively treated but touchedupon where considered appropriate. Author

N95-14297*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.A CARTESIAN, CELL-BASED APPROACH FORADAPTIVELY-REFINED SOLUTIONS OF THE EULER ANDNAVIER-STOKES EQUATIONSWILLIAM J. COIRIER and KENNETH G. POWELL Nov. 1994 16 pPresented at the 33rd Aerospace Sciences Meeting and Exhibit, Reno,NV, 9-12 Jan. 1995; sponsored by AIAA(Contract(s)/Grant(s): RTOP 505-62-52)(NASA-TM-106786; E-9241; NAS 1.15:106786; AIAA PAPER 95-0566) Copyright Avail: CASI HC A03/MF A01

A Cartesian, cell-based approach foradaptively-refined solutionsof the Euler and Navier-Stokes equations in two dimensions is devel-oped and tested. Grids about geometrically complicated bodies aregenerated automatically, by recursive subdivision of a single Cartesiancell encompassing the entire flow domain. Where the resulting cellsintersect bodies, N-sided 'cuf cells are created using polygon-clippingalgorithms. The grid is stored in a binary-tree structure which providesa natural means of obtaining cell-to-cell connectivity and of carrying outsolution-adaptive mesh refinement. The Euler and Navier-Stokesequations are solved on the resulting grids using a finite-volumeformulation. The convective terms are upwinded: a gradient-limited,linear reconstruction of the primitive variables is performed, providinginput states to an approximate Riemann solver for computing the fluxesbetween neighboring cells. The more robust of a series of viscous fluxfunctions is used to provide the viscous fluxes at the cell interfaces.Adaptively-refined solutions of the Navier-Stokes equations using theCartesian, cell-based approach are obtained and compared to theory,experiment, and other accepted computational results for a series oflow and moderate Reynolds number flows. Author

N95-14418*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.AXIS SWITCHING AND SPREADING OF AN ASYMMETRICJET: ROLE OF VORTICITY DYNAMICSK. B. M. Q. ZAMAN Nov. 1994 18 p Presented at the 33rdAerospace Sciences Meeting and Exhibit, Reno, NV, 9-12 Jan. 1995;sponsored by AIAA(Contract(s)/Grant(s): RTOP 505-62-52)(NASA-TM-106385; E-9230; NAS 1.15:106385; AIAA PAPER 95-0889) Copyright Avail: CASI HC A03/MF A01

The effects of vortex generators and periodic excitation on vortic-ity dynamics and the phenomenon of axis switching in a free asymmet-ric jet are studied experimentally. Most of the data reported are for a 3:1rectangular jet at a Reynolds number of 450,000 and a Mach numberof 0.31. The vortex generators are in the form of 'delta tabs', triangularshaped protrusions into the flow, placed at the nozzle exit. With suitableplacement of the tabs, axis switching could be either stopped oraugmented. Two mechanisms are identified governing the phenom-enon. One, as described by previous researchers and referred to hereas the omega(sub theta)-induced dynamics, is due to difference ininduced velocities for different segments of a rolled up azimuthalvortical structure. The other, omega(sub x)-induced dynamics, is dueto the induced velocities of streamwise vortex pairs in the flow. Bothdynamics can be active in a natural asymmetric jet; the tendency foraxis switching caused by the omegafsub theta)-induced dynamics maybe, depending on the streamwise vorticity distribution, either resisted orenhanced by the omega(sub x)-induced dynamics. While this simple

framework qualitatively explains the various observations made on axisswitching, mechanisms actually in play may be much more complex.The two dynamics are not independent as the flow field is replete withboth azimuthal and streamwise vortical structures which continuallyinteract. Phase averaged flow field data for a periodically forced case,over a volume of the flow field, are presented and discussed in an effortto gain insight into the dynamics of these vortical structures. Author

N95-14445* Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Fluid Dynamics Panel.MISSILE AERODYNAMICS [L'AERODYNAMIQUE DESMISSILES]Jun. 1994 341 p Special course held in Rhode-Saint-Genese,Belgium, 6-10 Jun. 1994 and in Ankara, Turkey, 13-17 Jun. 1994;sponsored by AGARD and VKI(AGARD-R-804; ISBN-92-835-0752-5) Copyright Avail: CASI HCA15/MFA03

Lecture notes for the AGARD Fluid Dynamics Panel (FDP)Special Course on 'Missile Aerodynamics' have been assembled in thisreport. The aim and scope of this course was to present the current stateof the art on specific topics of tactical missile aerodynamics. Specifi-cally, topics and methods covered include: Aeromechanical Design ofModem Missiles, Semi-empirical Predictive Tools, Lateral Jet Control,High Angle of Attack Aerodynamics, Analysis and Modelling of MissileInfrared Radiation, Navier-Stokes Computations for Complete MissileConfigurations, and Navier-Stokes and Euler Computations for Super-sonic Air Intakes. The material assembled in this report was preparedunder the combined sponsorship of the AGARD Fluid Dynamics Panel,the Consultant and Exchange Program of AGARD, and the von KarmanInstitute (VKI) for Fluid Dynamics. For individual titles, see N95-14446through N95-14452.

N95-14446# Deutsche Aerospace A.G., Munich (Germany). MissileSystems Div.AEROMECHANICAL DESIGN OF MODERN MISSILESP. HENNIG and P. G. LACAU In AGARD, Missile Aerodynamics76 p Jun. 1994Copyright Avail: CASI HC A05/MF A03

The changes in the political and strategic situation in the world,especially in Europe, result in new kinds of military scenarios and indifferent approaches to well-known scenarios. In combination withtechnological advances and with new mathematical and physicalsolutions for system component design and for improvements insystem performance this leads to a request for advanced and new typesof missiles with corresponding design goals and criteria. From suchmore general demands associated with the overall system design newrequirements for the aerodynamical and aeromecnanical design goalscan be derived in correspondence. Advanced experimental and theo-retical tools support the project aerodynamicist in coping with these newproblems. Examples for the demands for new missile types and for thenewsystemrequirementsare given. The mostimportantaeromechanicalwork packages in the design procedure of modem missiles are identi-fied and methods to get solutions sufficient for qualitative answers inearly project phases are presented. Author

N95-14447# Naval Surface Warfare Center, Dahlgren, VA. WeaponsSystems DeptENGINEERING CODES FOR AEROPREDICTION: STATE-OF-THE-ART AND NEW METHODSFRANK G. MOORE In AGARD, Missile Aerodynamics 82 pJun. 1994Copyright Avail: CASI HC A05/MF A03

This paperdiscussesthepros and cons of numerical, semiempirical,and empirical aeroprediction codes. It then summarizes many of themore popular approximate analytical methods used in state-of-the-art(SOTA) semiempirical aeroprediction codes. It also summarizes somerecent new nonlinear semiempirical methods that allow more accuratecalculation of static aerodynamics on complete missile configurations

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to higher angles of attack. Results of static aerodynamic calculations oncomplete missile configurations compared to wind tunnel data areshown for several configurations at various flight conditions. Calcula-tions show the new nonlinear methods being far superior to some of theformer linear technology when used at angles of attack greater thanabout 15 degrees. Author

N95-14450# Office National d'Etudes et de Recherches Aerospatiales,Paris (France).HIGH ANGLE OF ATTACK AERODYNAMICSP.CHAMPIGNY /nAGARD, Missile Aerodynamics 19p Jun. 1994Copyright Avail: CASI HC A03/MF A03

The demand for continually increased performance of missilesand aircraft leads to considering flight at very high angles of attackwhere control is very difficult. This is mainly due to the shedding ofasymmetric vortices from the forebody, producing side forces even atzero sideslip. The purpose of this paper is not to make a review ofmissile aerodynamics at high angle of attack, but to focus on anunderstanding of the phenomena which give rise to asymmetric vorti-ces, from an experimental as well as a theoretical point of view.

Author

N95-14451* Army Research Lab., Aberdeen Proving Ground, MD.Propulsion and Right Div.NAVIER-STOKES PREDICTIONS OF MISSILEAERODYNAMICSPAUL WEINACHT and JUBARAJ SAHU In AGARD, Missile Aerody-namics 48 p Jun. 1994Copyright Avail: CASI HC A03/MF A03

This paper discusses the application of Navier-Stokes computa-tional methods to the prediction of the aerodynamics of missile configu-rations. The governing equations, turbulence models, and numericalapproaches used to solve these equations are briefly described. Thepaper focuses mainly on aerodynamic coefficient prediction. Static anddynamic aerodynamic derivative prediction methods and applicationsare presented for axisymmetric and finned bodies and comparisons aremade with experimental data. Results of validation studies are alsopresented for the purpose of demonstrating the accuracy as well aspotential shortcomings of these techniques. The paper also discussesthe application of Navier-Stokes methods in the prediction of base flow.Application of these techniques to unpowered, base bleed, and pow-ered configurations is shown. Author

N95-14452* Aerospatiale, verrieres-L-Buisson (France).COMPUTATION OF SUPERSONIC AIR-INTAKESR. G. LACAU, P. GARNERO, and F. GAIBLE In AGARD, MissileAerodynamics 21 p Jun. 1994Copyright Avail: CASI HC A03/MF A03

The aim of this paper is to present how some CFD tools can beused to compute external and internal flowfields involved in the designof supersonic air-intakes. These tools help the designer to betterunderstand flow phenomena, to determine favorable intake locations,and to predict air-intake performances such as pressure recovery andmass flow ratio. As supersonic intakes are mainly used on ramjetmissiles, we limit this paper to ramjet air-intakes. After a brief overviewof the existing types of air-intakes, we describe the way their perfor-mances are quantified. Then we present the CFD tools used to evaluateair-intake characteristics. Finally, selected applications of these toolsdemonstrate how a comprehensive study of air-intake may be achievedthrough CFD. Both external and internal flowfield computations arepresented, which allows predictions of air-intake performances.

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N95-14612*# MCAT Inst, San Jose, CA.NUMERICAL SIMULATION OF THE SOFIA FLOWFIELDAnnual ReportSTEPHEN P. KLOTZ Jul. 1994 75 p Original contains colorillustrations(Contract(s)/Grant(s): NCC2-636)(NASA-CR-197025; NAS 1.26:197025) Avail: CASI HC A04/MF A01;

1 functional color pageThis report provides a concise summary of the contribution of

computational fluid dynamics (CFD) to the SOFIA (StratosphericObservatory for Infrared Astronomy) project at NASA Ames andpresents results obtained from closed- and open-cavity SOFIA simula-tions. The aircraft platform is a Boeing 747SP and these are the firstSOFIA simulations run with the aircraft empennage included in thegeometry database. In the open-cavity run the telescope is mountedbehind the wings. Results suggest that the cavity markedly influencesthe mean pressure distribution on empennage surfaces and that 110-140 decibel (db) sound pressure levels are typical in the cavity and onthe horizontal and vertical stabilizers. A strong source of sound wasfound to exist on the rim of the open telescope cavity. The presence ofthis source suggests that additional design work needs to be performedin order to minimize the sound emanating from that location. A fluiddynamic analysis of the engine plumes is also contained in this reportThe analysis was part of an effort to quantify the degradation oftelescope performance resulting from the proximity of the port engineexhaust plumes to the open telescope bay. Author

N95-14613*# MCAT Inst., San Jose, CA.CONTROL OF UNSTEADY SEPARATED FLOWASSOCIATED WITH THE DYNAMIC STALL OF AIRFOILSAnnual ReportM.C. WILDER 31 Jul. 1994 69p Original contains color illustrations(Contract(s)/Grant(s): NCC2-637)(NASA-CR-197024; NAS 1.26:197024; MCAT-94-20) Avail: CASI HCA04/MF A01; 1 functional color page

A unique active flow-control device is proposed for the control ofunsteady separated flow associated with the dynamic stall of airfoils.The device is an adaptive-geometry leading-edge which will allowcontrolled, dynamic modification of the leading-edge profile of an airfoilwhile the airfoil is executing an angle-of-attack pitch-up maneuver. Acarbon-fiber composite skin has been bench tested, and a wind tunnelmodel is under construction. A baseline parameter study of compress-ible dynamic stall was performed for flow over an NACA 0012 airfoil.Parameters included Mach number, pitch rate, pitch history, andboundary layer tripping. Dynamic stall data were recorded via point-diffraction interferometry and the interferograms were analyzed with in-house developed image processing software. A new high-speedphase-locked photographic image recording system was developed forreal-time documentation of dynamic stall. Author

N95-14614*# MCAT Inst, San Jose, CA.NUMERICAL SIMULATION OF THE FLOW ABOUT THE F-18HARV AT HIGH ANGLE OF ATTACK Annual ReportSCOTT M. MURMAN Aug. 1994 7 p Original contains colorillustrations(Contract(s)/Grant(s): NCC2-729)(NASA-CR-197023; NAS 1.26:197023; MCAT-94-11) Avail: CASI HCA02/MF A01; 2 functional color pages

As part of NASA's High Alpha Technology Program, research hasbeen aimed at developing and extending numerical methods to accu-rately predict the high Reynolds number flow about the NASA F-18 HighAlpha Research Vehicle (HARV) at large angles of attack. The HARVaircraft is equipped with a bidirectional thrust vectoring unit whichenables stable, controlled flight through 70 deg angle of attack.Currently, high-fidelity numerical solutions for the flow about the HARVhave been obtained at alpha = 30 deg, and validated against flight-testdata. It is planned to simulate the flow about the HARV through alpha= 60 deg, and obtain solutions of the same quality as those at the lowerangles of attack. This report presents the status of work aimed atextending the HARV computations to the extreme angle of attackrange. Derived from text

N95-14646# Kossel (Horst), Shrewsbury, MA.ACTIVATED BUOYANCY PROPULSION = PARADOXPOWER (TM)HORST KOSSEL In Huntsville Association of Technical Societies,TABES 1994: 10th Annual Technical and Business Exhibition and

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Symposium 7 p 1994(TABES PAPER 94-619) Avail: CASI HC A02/MF ACM

The PARADOX POWER(tm) concept recognizes molecular activ-ity/heat of all fluids as an unlimited source of dean kinetic energy,accessible to do 'work' within the lower atmosphere and open water. Byexpending minimal energy to selectively subtract from the molecularimpulse (pressure) on a surface of a macroscopic body, acceleration isprovided by momentum transfer to the normal (opposite) surface,directly by ambient pressure. Energy from a separate source is used toincrease the parallel velocity of microscopic size particles, within theinvisible Attached Ionized Boundary Layer (U.S. Pat. Appl. No. 106,867).Controllable, super efficient vehicle operation results, doubling micro-scopic oscillation velocity increases the atmospheric propulsive forcefour times; deceleration functions similarly. Molecular oscillation byrapidly reversing alternating current, causing an imbalance, providesclean, quiet, controlled 'buoyancy* propulsion. Author

N95-14803*# Georgia Inst. of Tech., Atlanta, GA. School of Aero-space Engineering.NUMERICAL STUDY OF THE EFFECTS OF ICING ONVISCOUS FLOW OVER WINGS Final ReportL. N. SANKAR Oct. 1994 156p(Contract(s)/Grant(s): NAG3-768)(NASA-CR-197102; NAS 1.26:197102) Avail: CASI HC A08/MF A02

An improved hybrid method for computing unsteady compressibleviscous flows is presented. This method divides the computationaldomain into two zones. In the outer zone, the unsteady full-potentialequation (FPE) is solved. In the inner zone, the Navier-Stokes equa-tions are solved using a diagonal form of an alternating-direction implicit(ADI) approximate factorization procedure. The two zones are tightlycoupled so that steady and unsteady flows may be efficiently solved.Characteristic-based viscous/inviscid interface boundary conditionsare employed to avoid spurious reflections at that interface. Theresulting CPU times are less than 60 percent of that required for a full-blown Navier-Stokes analysis for steady flow applications and about 60percent of the Navier-Stokes CPU times for unsteady flows in non-vector processing machines. Applications of the method are presentedfor a rectangular NACA 0012 wing in low subsonic steady flow atmoderate and high angles of attack, and for an F-5 wing in steady andunsteady subsonic and transonic flows. Steady surface pressures arein very good agreement with experimental data and are essentiallyidentical to Navier-Stokes predictions. Density contours show thatshocks cross the viscous/inviscid interface smoothly, so that theaccuracy of full Navier-Stokes equations can be retained with asignificant savings in computational time. Author

N95-14878*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.HIGH-SPEED RESEARCH: 1994 SONIC BOOM WORKSHOP:ATMOSPHERIC PROPAGATION AND ACCEPTABILITYSTUDIESDAVID A. MCCURDY, ed. Oct. 1994 222 p The 3rd workshopwas held in Hampton, VA, 1-3 Jun. 1994(Contract(s)/Grant(s): RTOP 537-03-21-03)(NASA-CP-3279; L-17434; NAS 1.55:3279) Avail: CASI HC A10/MFA03

The workshop proceedings include papers on atmospheric propa-gation and acceptability studies. Papers discussing atmospheric ef-fects on the sonic boom waveform addressed several issues. It has longbeen assumed that the effects of molecular relaxation are adequatelyaccounted for by assuming that a steady state balance betweenabsorption and nonlinear wave steepening exists. It was shown that theunsteadiness induced by the nonuniform atmosphere precludes attain-ing this steady state. Further, it was shown that the random atmosphereacts as a filter, effectively filtering out high frequency components of thedistorted waveform. Several different propagation models were com-pared, and an analysis of the sonic boom at the edge of the primarycarpet established that the levels there are bounded. Finally, a discus-

sion of the levels of the sonic boom below the sea surface waspresented. For individual titles, see N95-14879 through N95-14892.

N95-14880'# Texas Univ., Austin, TX. Dept. of MechanicalEngineering.EFFECT OF STRATIFICATION AND GEOMETRICALSPREADING ON SONIC BOOM RISE TIMEROBIN O. CLEVELAND, MARK F. HAMILTON, and DAVID T.BLACKSTOCK In NASA. Langley Research Center, High-SpeedResearch: 1994 Sonic Boom Workshop: Atmospheric Propagationand Acceptability Studies p 19-38 Oct. 1994Avail: CASI HC A03/MF A03

The purpose of our investigation is to determine the effect ofunsteadiness (not associated with turbulence) on rise time. The un-steadiness considered here is due to (1) geometrical spreading, (2)stratification, which includes variation in density, temperature, andrelative humidity, and (3) N shaped waveform. A very general Burgersequation, which includes all these effects, is the propagation model forour study. The equation is solved by a new computational algorithm inwhich all the calculations are done in the time domain. The presentpaper is a progress report in which some of the factors contributing tounsteadiness are studied, namely geometrical spreading and variationin relative humidity. The work of Pierce and Kang, which motivated ourstudy, is first reviewed. We proceed with a discussion of the Burgersequation model and the algorithm for solving the equation. Somecomparison tests to establish the validity of the algorithm are presented.The algorithm is then used to determine the distance required for asteady-state shock, on encountering an abrupt change in relativehumidity, to reach a new steady state based on the new humidity. It isfound that the transition distance tor plane shocks of amplitude 70 Pais about 4 km when the change in relative humidity is 10 percent. Shocksof amplitude 140 Pa require less distance. The effect of spherical andcylindrical spreading is also considered. We demonstrate that a spread-ing shock wave never reaches steady state and that its rise time will beless than the equivalent steady state shock. Finally we show that an Nwave has a slightly shorter rise time than a step shock of the sameamplitude. Author

N95-14894# Pennsylvania State Univ., University Park, PA. Dept.of Aerospace Engineering.WAKE TURBULENCEBARNES W. MCCORMICK In AGARD, Flight in an AdverseEnvironment 15 p Nov. 1994Copyright Avail: CASI HC A03/MF A02

Wake turbulence is a misnomer. Turbulence implies a randomprocess whereas the term 'wake turbulence' refers to the hazard posedto smaller airplanes by the ordered, rotational flow in the trailing vortexsystems behind larger airplanes. This lecture begins by examining therelationship of aircraft size, geometry and operating conditions to thestrength of an aircraft's trailing vortex system. Next, the velocity fieldinitially induced close behind the generating airplane by its trailingvortex system is defined. This is followed by a discussion of the variousways in which a vortex system can dissipate and the many factors whichaffect the dissipation. In particular, the effects of atmospheric turbu-lence, ground proximity and vortex bursting on the ensuing behavior ofthe vortex system are considered. The paper continues with a study ofthe dynamics of an aircraft encountering the wake of a larger airplane.The degree to which an aircraft is threatened by a given vortex systemof known characteristics is analyzed and the hazard posed by a givenvortex system to a following aircraft quantified. Finally, the paperconcludes with recommendations on possible ways to alleviate thesafety and operational problems associated with wake turbulence.

Author

N95-15319# Naval Postgraduate School, Monterey, CA.LOW-SPEED WIND TUNNEL TESTING OF THE NPS ANDNASA AMES MACH 6 OPTIMIZED WAVERIDER M.S. ThesisMARK E. CEDRUN 16 Jun. 1994 106 p(AD-A283585) Avail: CASI HC A06/MF A02

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Low-speed wind tunnel tests were conducted to determine thesubsonic aerodynamic characteristics of an optimized supersonic(Mach 6) conical-flow waverider designed for a deck-launched interceptmission. These tests are part of the continuing waverider researchbeing conducted by the Naval Postgraduate School and the NASAAmes Research Center. The tests consisted of performing Alpha andBeta sweeps, at different dynamic pressures, with a 15 inch aluminumwaverider model in the NPS low-speed wind tunnel. Force and momentdata were then collected using a six-degree-of-freedom sting balance.Coefficients of lift, drag and pitch were calculated from the data andcompared to theory and existing waverider subsonic aerodynamicperformance data. Row visualization using tufts was also done. Theresults of the experiments show that waverider exhibits high lift charac-teristics at positive angles of attack. The design also comparesfavorably with both subsonic thin airfoil theory and the results of thedelta wing and subsonic waverider analysis done by Vanhoy. However,flow visualization showed that vortex bursting occurred at a dynamicpressure of 12.11 bf at +/-15 degrees angle of attack. Based upon thedata collected in this analysis, the development of an actual waverideraircraft using the NPS/NASA Ames waverider design as a baseline isa plausible endeavor. DTIC

N95-15465 Wright Lab., Wright-Patterson AFB, OH.PRESSURE MEASUREMENTS ON AN F/A-18 TWINVERTICAL TAIL IN BUFFETING FLOW. VOLUME 2: STEADYAND UNSTEADY RMS PRESSURE DATA Final ReportCHRIS PETTIT, DANSEN BROWN, MICHAEL BANFORD. and EDPENDLETON 1 Aug. 1994 383 p Limited Reproducibility: Morethan 20% of this document may be affected by microfiche quality(AD-A281581; WL-TM-94-3065-VOL-2) Avail: CASI HC A17

Buffeting pressure measurements were made on the vertical tailsurface of a full scale F/A-18 aircraft model in the National Full ScaleAerodynamics Complex at NASA Ames Research Center. Test vari-ables included aircraft angle-of-attack, aircraft sideslip angle, anddynamic pressure. Accelerometers were used to obtain vertical tailaccelerations. Pressure transducers were mounted on the starboardvertical tail. Steady and unsteady pressures were obtained. Unsteadypressure data were reduced to PSD and CSD forms. Both steady andunsteady RMS pressure coefficients are also presented. Volume 1contains the general description of the model, the test program, andhighlights of the reduced data. Volume 2 contains steady and unsteadyRMS data. Volume 3 contains unsteady PSD results. Volume 4contains unsteady CSD results. DTIC

N95-15762*# California Polytechnic State Univ., San Luis Obispo,CA. Dept. of Aeronautical Engineering.NUMERICAL DESIGN OF ADVANCED MULTI-ELEMENTAIRFOILS Final ReportDONOVAN L. MATHIAS and RUSSELL M. CUMMINGS Oct. 1994105 p(Contract(sXGrant(s): NCC2-813)(NASA-CR-197135; NAS 1.26:197135) Avail: CASI HC A06/MFA02

The current study extends the application of computational fluiddynamics to three-dimensional high-lift systems. Structured, oversetgrids are used in conjunction with an incompressible Navier-Stokesflow solver to investigate flow over a two-element high-lift configuration.The computations were run in a fully turbulent mode using the one-equation Baldwin-Barth turbulence model. The geometry consisted ofan unswept wing which spanned a wind tunnel test section. Rows overfull and hart-span Fowler flap configurations were computed. Gridresolution issues were investigated in two dimensional studies of theflapped airfoil. Results of the full-span flap wing agreed well withexperimental data and verified the method. Flow over the wing with thehalf-span was computed to investigate the details of the flow at the freeedge of the flap. The results illustrated changes in flow streamlines,separation locations, and surface pressures due to the vortex shed fromthe flap edge. Author

N95-15852*# NYMA, Inc., Brook Park, OH. Engineering ServicesDiv.RESONANT INTERACTION OF A LINEAR ARRAY OFSUPERSONIC RECTANGULAR JETS: AN EXPERIMENTALSTUDY Final ReportGANESH RAMAN and RAY TAGHAVI Cleveland, OH NASA Nov.1994 25 p Presented at the 33rd Aerospace Sciences Meeting andExhibit, 9-12 Jan. 1994; sponsored by the AIAA(Contract(s)/Grant(s): NAS3-27186; RTOP 537-02-22)(NASA-CR-195398; E-9128; NAS 1.26:195398) Copyright Avail: CASIHC A03/MF A01

This paper examines a supersonic multi jet interaction problemthat we believe is likely to be important for mixing enhancement andnoise reduction in supersonic mixer-ejector nozzles. We demonstratethat it is possible to synchronize the screech instability of four rectan-gular jets by precisely adjusting the inter jet spacing. Our experimentaldata agrees with a theory that assumes that the phase-locking ofadjacent jets occurs through a coupling at the jet lip. Although thesynchronization does not change the frequency of the screech tone, itsamplitude is augmented by 10 dB. The synchronized multi jets exhibithigher spreading than the unsynchronized jets, with the single jetspreading the least. We compare the nearfield noise of the four jets withsynchronized screech to the noise of the sum of four jets operatedindividually. Our noise measurements reveal that the more rapid mixingof the synchronized multi jets causes the peak jet noise source to moveup stream and to radiate noise at larger angles to the flow direction.Based on our results, we believe that screech synchronization isadvantageous for noise reduction internal to a mixer-ejector nozzle,since the noise can now be suppressed by a shorter acoustically linedejector. Author

N95-15853*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.AN APPROACH FOR DYNAMIC GRIDSJOHN W. SLATER, MENG-SING LIOU, and RICHARD G. HINDMANNov. 1994 11 p Presented at the 32nd Aerospace Sciences Meetingand Exhibit, Reno, NV, 10-13 Jan. 1994; sponsored by the AIAA(Contract(s)/Grant(s): NGT-50441; RTOP 505-62-52)(NASA-TM-106774; E-9124-1; NAS 1.15:106774; AIAA PAPER 94-0319) Avail: CASI HC A03/MF A01

An approach is presented for the generation of two-dimensional,structured, dynamic grids. The grid motion may be due to the motion ofthe boundaries of the computational domain or to the adaptation of thegrid to the transient, physical solution. A time-dependent grid iscomputed through the time integration of the grid speeds which arecomputed from a system of grid speed equations. The grid speedequations are derived from the time-differentiation of the grid equationsso as to ensure that the dynamic grid maintains the desired qualities ofthe static grid. The grid equations are the Euler-Lagrange equationsderived from a variational statement for the grid. The dynamic gridmethod is demonstrated for a model problem involving boundarymotion, an inviscid flow in a converging-diverging nozzle during startup,and a viscous flow over a flat plate with an impinging shock wave. It isshown that the approach is more accurate for transient flows than anapproach in which the grid speeds are computed using a finite differ-ence with respect to time of the grid. However, the approach requiressignificantly more computational effort Author

N95-15912*# Toledo Univ., OH.ENHANCED CAPABILITIES AND UPDATED USERSMANUAL FOR AXIAL-FLOW TURBINE PRELIMINARYSIZING CODE TURBAN Final ReportARTHUR J. CLASSMAN Nov. 1994 18 p(Contract(s)/Grant(s): NAG3-1165; RTOP 505-69-50)(NASA-CR-195405; E-9252; NAS 1.26:195405) Avail: CASI HC A03/MFA01

Several modifications have been made to the axial-flow turbinepreliminary sizing code TURBAN. Turbine cooling has been added tothe analysis. New alternative input options allow direct specification of

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stage reaction, stage work factor, and stage work split. The Reynoldsnumber loss dependency was modified and an internal calculation of airviscosity was added. A complete description of input and output alongwith sample cases are included. Author

development. It does not deal with the testing of particular systems, butit is hoped that readers will find the principles described readilyapplicable to specific cases. This document has been sponsored by theRight Mechanics Panel of AGARD. Author (revised)

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AIR TRANSPORTATION AND SAFETY

Includes passenger and cargo air transport operations; and aircraftaccidents.

A95-61733CERAMIC BLANKET REDUCES MAINTENANCE COSTSAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 9 September 1993 p. 11-12(BTN-94-EIX94461290278) Copyright

In 1981, removable fire shield blankets were developed. Theblanket is attached on the reverser 'hot side' to provide fire protectionand prevent thermal stress, in compliance with FAA regulations. Theseceramic blankets are still in use, and their application has expanded.The blanket reduces maintenance costs. El

N95-14179* National Inst. of Standards and Technology, Gafthersburg,MD. Building and Fire Research Lab.RISK ANALYSIS FOR THE FIRE SAFETY OF AIRLINEPASSENGERSR. L. SMITH Jun. 1994 40 p(Contract(s)/Grant(s):DTFA03-92-Z-00018)(PB94-194065; NISTIR-5441) Avail: CASI HC A03/MF A01

The purpose of this report is to describe the National Institute ofStandards and Technology's work to date relating to the generalmethodology being developed for the project Risk Analysis for the FireSafety of Airline Passengers and the software being used to facilitatethis methodology. The approach selected involved the use of influencediagrams. Therefore, a brief discussion of influence diagrams is given.The status of.their application to the water mist system for passengerplanes is given and the overall approach to carrying out the project isdescribed. An example is included that shows how the process works,but the case is fictional, not intended to be realistic. NTIS

N95-14199# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Right Mechanics Panel.THE PRINCIPLES OF FLIGHT TEST ASSESSMENT OFFLIGHT-SAFETY-CRITICAL SYSTEMS IN HELICOPTERS[LES PRINCIPES DE DEVALUATION, DANS LE CADREDES ESSAIS EN VOL, DES SYSTEMES INDISPENSABLESA LA SECURITE DE VOL DES HELICOPTERES]J. D. L. GREGORY Aug. 1994 29 p Right Test Techniques Series(AGARD-AG-300-VOL-12; ISBN-92-836-1001-6) Copyright Avail:CASI HC A03/MF A01

Modem helicopters usually incorporate many engineering sys-tems (including pilot-aiding systems such as autostabilizers and flightdirectors) which are essential to the safe and effective use of thehelicopter. Where the helicopter can be endangered by failure of asystem (or of one of its units), that system is termed flight-safety-critical.In general, the use of those systems should not incur a higher probabilityof hazard to the helicopter than that considered acceptable fromconsiderations of structural or mechanical failure. In assessing thesuitability of a helicopter for its intended mission(s), it has becomeincreasingly important to consider the effects of the various systemsprovided. In particular, assessments of the implications of systemsperformance and failures derived from calculation and ground testshould be validated by flight tests. This paper seeks to establish thegeneral principles applicable to the testing in flight of any flight-safety-critical system, with emphasis on certification rather than system

N95-14350* Federal Aviation Administration, Atlantic City, NJ.PROCEEDINGS OF THE FAA INSPECTION PROGRAMAREA REVIEW Final ReportCHRISTOPHER SMITH Jul. 1994 922 p Review held in Ames,IA, 5-7 Apr. 1994(AD-A283849; DOT/FAA/CT-94/64) Avail: CASI HC A99/MF A10

This publication is a compendium of the Proceedings, of the FAAInspection Program Are Review Presentations given at the Center forAviation Systems Reliability held at Iowa State University at Ames,Iowa on April 5-7,1994. DTIC

N95-14893* Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Right Vehicle Integration Panel.FLIGHT IN AN ADVERSE ENVIRONMENT [LE VOL ENENVIRONNEMENT HOSTILE]Nov. 1994 161 p Lecture series held in Brunswick, Germany, 7-8 Nov. 1994, in Lisbon, Portugal, 10-11 Nov. 1994, and in Atlantic City,NJ, 15-16 Nov. 1994(AGARD-LS-197; ISBN-92-836-1006-7) Copyright Avail: CASI HCA08/MF A02

The environment in which an airplane must operate is a majorcause of aircraft accidents. This lecture series focuses on specificaspects of the environment, both natural and man-made, which are themajor contributors to these accidents as follows: (1) wake turbulenceand the generation of trailing vortex systems; (2) the results of anextensive flight test program concerning winter storms off the east coastof Canada including effect on aircraft operations; (3) electromagneticeffects including electrical discharge properties, in-flight test program,in-flight lightning models and lightning simulation techniques; (4) re-sponse of an aircraft to wind shear and methods of detection andquantifying this natural hazard; (5) heavy rain effects on aircraftsystems performances in the light of full scale and model tests; (6)measurements of atmospheric turbulence, treatment of aircraft re-sponse to random turbulence and discrete gusts. For individual titles,see N95-14894 through N95-14900.

N95-14897*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.ICING: ACCRETION, DETECTION, PROTECTIONJOHN J. REINMANN In AGARD, Right in an Adverse Environment27 p Nov. 1994Copyright Avail: CASI HC A03/MF A02

The global aircraft industry and its regulatory agencies are cur-rently involved in three major icing efforts: ground icing; advancedtechnologies for in-flight icing; and tailplane icing. These three majoricing topics correspondingly support the three major segments of anyaircraft flight profile: takeoff; cruise and hold; and approach and land.This lecture addressess these three topics in the same sequence asthey appear in flight, starting with ground deicing, followed by advancedtechnologies for in-flight ice protection, and ending with tailplane icing.

Derived from text

N95-14898* Woodfield (Alan A.), Bedford (England).WIND SHEAR AND ITS EFFECTS ON AIRCRAFTALAN A. WOODFIELD In AGARD, Right in an Adverse Environment31 p Nov. 1994Copyright Avail: CASI HC A03/MF A02

Wind shear has been responsible for several major accidents andmany incidents during landing and take off. In aviation terms, windchanges that cause flight path deviations (wind shear) are mainly thoseoccurring over distances between about 150 and 3000m, i.e. approxi-mately 3 to 40 sec. at approach speeds. General characteristics of

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many forms of wind shear are described together with measured dataon the probability of meeting headwind shears of different magnitudes.This is followed by analysis of the basic response of aircraft to bothhorizontal wind changes and downdrafts, and discussion of aircraftsensitivity to wind shear. Several recorded examples of wind shear inboth normal operational and accident scenarios are presented. Therelevance of different ways of quantifying wind shear severity isexamined, including a calculation of height loss that can be used whena wind shear is fully defined, and the 'F factor, which is used withreactive wind shear measuring systems. Some insight into the prob-abilities of false or missed warnings with each system is derived usingthe measured probability data. A brief outline is given of the relevantcharacteristics of different wind shear prediction and detection sys-tems. The lecture concludes with a study of the ways in which pilots canbe trained and assisted to survive most wind shear encounters and,hopefully, avoid those which could be catastrophic. It is concluded that,given appropriate training and aircraft systems, it is possible to surviveencounters with nearly all those wind shears that caused fatal accidentsin previous years. New predictive detection systems offer the possibilityto warn an aircraft before it attempts to penetrate those extremely rarewind shears that are beyond its performance capability. Author

N95-14899*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.HEAVY RAIN EFFECTSR. EARL DUNHAM, JR. In AGARD, Right in an Adverse Environment17 p Nov. 1994Copyright Avail: CASI HC A03/MF A02

This paper summarizes the current state of knowledge of theeffect of heavy rain on airplane performance. Although the effects ofheavy rain on airplane systems and engines are generally known, onlyrecently has the potential aerodynamic effect of heavy rain beenrecognized. In 1977 the United States Federal Aviation Administration(FAA) conducted a study of 25 aircraft accidents and incidents whichoccurred between 1964 and 1976 in which low-altitude wind shear couldhave been a contributing factor. Of the 25 cases (23 approach or landingand 2 take-off) in the study, ten cases had occurred in a rain environ-ment, and in five cases these were classified as intense or heavy rainencounters. These results led to the reconsideration of high-intensity,short-duration rainfall as a potential weather-related aircraft safetyhazard, particularly in the take-off and/or approach phases of flight

Author

N95-14916* National Transportation Safety Board, Washington, DC.AIRCRAFT ACCIDENT REPORT: OVERSPEED AND LOSSOF POWER ON BOTH ENGINES DURING DESCENT ANDPOWER-OFF EMERGENCY, LANDING SIMMONS AIRLINES,INC., D/B/A, AMERICAN EAGLE FLIGHT 3641, N349SBFALSE RIVER AIR PARK, NEW ROADS, LOUSIANA, 1FEBRUARY 199427 Sep. 1994 80 pAvail: CASI HC A05/MF A01

This report explains the emergency landing of American Eagleflight 3641, a Saab 340B airplane, at False River Air Park, New Roads,Louisiana, on February 1,1994. The safety issues in the report focusedon the safety hazards involved with the inflight operation of propellersin the beta mode in airplanes for which such operation is prohibited. TheSafety Board reiterated Safety Recommendation A-94-62, which isintended to prevent the in-flight beta operation unless the airplane iscertified for such use. Author

N95-15066* National Transportation Safety Board, Washington, DC.ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA: US AIRCARRIER OPERATIONS, CALENDAR YEAR 199215 Sep. 1994 72 pAvail: CASI HC A04/MF A01

This publication presents the record of aviation accidents involv-ing revenue operations of U.S. Air Carriers including Commuter AirCarriers and On Demand Air Taxis for calendar year 1992. The report

is divided into three major sections according to the federal regulationsunder which the flight was conducted -14 CFR121, Scheduled 14 CFR135, or Nonscheduled 14 CFR 135. In each section of the report tablesare presented to describe the losses and characteristics of 1992accidents to enable comparison with prior years. Author

N95-15439 Midwest Research Inst, Kansas City, MO.DEVELOPMENT OF ANTI-ICING TECHNOLOGYR. R. BLACKBURN, E. J. MCGRANE, C. C. CHAPPELOW, D. W.HARWOOD, and E. J. FLEEGE Apr. 1994 497 p See alsoPB253268, PB271250, PB88-233705 and PB88-233713 Prepared incooperation with Minnesota Dept. of Transportation, Duluth, MN(Contract(s)/Grant(s): DOT-SHRP-H-208A)(PB94-195369; SHRP-H-385; ISBN-0-309-05761 -2) Copyright Avail:Issuing Activity

Scandinavian and other European countries have shown thatapplying a chemical freezing-point depressant on a highway pavementprior to, or very quickly after, the start of frozen participation minimizesthe formation of an ice-pavement bond. Nine state highway agenciesconducted anti-icing experiments when possible during the 1991-92and 1992-93 winters. These tests were used to develop a betterunderstanding of both the conditions under which anti-icing will beeffective and how to conduct anti-icing efficiently to ensure the greatestsuccess. Prewetted salt and liquid chemicals were used during the anti-icing experiments. The project also involved evaluating specializedequipment for applying controlled quantities of solid, prewetted or liquidchemicals at minimum application rates required for effective anti-icingtreatment. NTIS

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AIRCRAFT DESIGN, TESTING ANDPERFORMANCE

Includes aircraft simulation technology.

A95-61739EVOLUTION OF A NOSE-WHEEL STEERING SYSTEMCHARLES A. SMITH Vickers, Inc., Los Angeles, CA AerospaceEngineering (Warrendale, Pennsylvania) (ISSN 0736-2536) vol. 13,no. 6 June 1993 p. 23-25(BTN-94-EIX94461047056) Copyright

A digital nose-wheel steering system is used to control theMcDonnell Douglas T-45 aircraft during takeoff and landing as well aslow-speed taxiing and parking. Author (El)

A95-61740ELECTRORHEOLOGICALLY CONTROLLED LANDINGGEARZHENG LOU, ROBERT D. ERVIN, FRANK E. FILISKO, and CHRIS-TOPHER B. WINKLER Aerospace Engineering (Warrendale, Penn-sylvania) {ISSN 0736-2536) vol. 13, no. 6 June 1993 p. 17-22(BTN-94-EIX94461047055) Copyright

When using an electrorheological (ER) fluid with a yield stress of7 kPa, the energy absorption efficiency of an ER-controlled landing gearcan reach almost 100% at various sink rates. Author (El)

A95-62633THE EFFECT OF ROTATING LOADS SUSPENDED UNDER AHELICOPTER ON THEIR AMPLITUDE-FREQUENCYCHARACTERISTICSB. F. TYURIN Akademiya GA, Saint Peterburg (Russia), S. V.SIPAROV, E. S. STELMAKOV, and K. A. NOVOZHILOV IzvestiyaVUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4 October-December 1993 p. 81-84 In RUSSIAN

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(BTN-94-EIX94461407959) CopyrightThe twisting of a load on the outer suspension of a helicopter is

regarded as a way to provide its transportation stability during the flightBasic physics of the load stabilization is discussed. The experimentalresearch results have been presented to determine amplitude-fre-quency characteristics and aerodynamic coefficients of rotating loads.The loads have the form of a parallelepiped and a ring cylinder. Threefactors affect the stabilization of a rotating load. They are: the gyro-scopic effect, symmetrization of the load shape, and mismatch inoscillation frequencies. El

N95-13703*# Universities Space Research Association, Columbia,MD.VIPERL. E. PAUL GILBERT, CASSIE BERRY, DANA LAMBORN, JACKMURPHY, and CHRIS OKELLY 8 Dec. 1993 19 p(Contract(s)/Grant(s): NASW-4435)(NASA-CR-197191; MAS 1.26:197191; F93-2B-OR15) Avail: CASIHCA03/MF A01

A Viper aircraft was redesigned with a new airfoil and engine toverify if improvements can be made to the baseline configuration. Thetwo major redesigning processes were: replacing the baseline aircraft'sNACA 652-415 airfoil with an NLF 0414 Natural Laminar Flow airfoil,and the baseline aircraft's Lycoming 0-235 engine with a TeledyneContinental GR-36 rotary combustion engine. As a result of thesechanges: (1) the Viper aircraft becomes smaller in most respects (grossweight, wing platform area, and horizontal tail area); (2) overall drag ofthe aircraft decreased (due to reduction in area and the reduced drugof the new airfoil); (3) cruise velocity, the maximum rate of climb at sealevel, and takeoff distance (but not landing distance) decreased; and (4)cost increased. Although the overall drag decreased, the performanceremained about the same due to the reduced horsepower availablefrom the Teledyne Continental engine. CASI

N95-13981 Federal Aviation Administration, Kansas City, MO.Aircraft Certification Service.FATIGUE EVALUATION OF EMPENNAGE, FORWARDWING, AND WINGLETS/TIP FINS ON PART 23 AIRPLANESFinal Technical Report15 Feb. 1994 64 p Limited Reproducibility: More than 20% of thisdocument may be affected by microfiche quality(PB94-196813; FAA/ACE-100-01) Avail: Issuing Activity (NationalTechnical Information Service (NTIS))

This report provides technical guidance for complying with thefatigue evaluation requirements of Part 23 (small and commutercategory airplanes) of the Federal Aviation Regulations, Section 23.572,pertaining to empennage, forward wing, and winglets/tip fins. Detailedprocedures are described for developing empennage repeated loadsusing published airplane centerof-gravity normal acceleration spectrain conjunction with basic airplane data. An alternate approach thateliminates calculating applied loads uses empirically derived stressequations from measured flight strain survey data, coupled with theairplane center-of-gravtty normal acceleration spectra and proposedairplane usage data. NTIS

N95-14102# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Flight Mechanics Panel.IDENTIFICATION OF DYNAMIC SYSTEMS. VOLUME 3:APPLICATIONS TO AIRCRAFT. PART 2: NONLINEARANALYSIS AND MANOEUVRE DESIGN [̂ IDENTIFICATIONDES SYSTEMES DYNAMIQUES: APPLICATIONS AUXAERONEFS. TITRE 2: L'ANALYSE NON-LINEAIRE ET LACONCEPTION DE LA MANOEUVRE]J. A. MULDER (Technische Univ., Delft, Netherlands.), J. K.SRIDHAR (Technische Univ., Delft, Netherlands.), and J. H.BREEMAN (National Aerospace Lab., Amsterdam, Netherlands.)May 1994 213 p Flight Test Techniques Series

(AGARD-AG-300-VOL-3-PT-2; ISBN-92-835-0748-7) Copyright Avail:CASI HC A10/MF A03

This AGARDograph is a sequel to the previous AGARDographspublished in the AGARD Right Test Techniques Series, Volume 2 on'Identification of Dynamic Systems' and Volume 3 on 'Identification ofDynamic Systems - Applications to Aircraft - Part 1: The Output ErrorApproach1 both written by R.E. Maine and K.W. Iliff. The intention of thepresent document is to cover some of those areas which were eitherabsent or only briefly mentioned in those volumes. These areas areRight Path Reconstruction, Nonlinear Model Identification, OptimalInput Design and Flight Test Instrumentation. The present approach toidentification is rather different from that presented in the earlierAGARDographs in the sense that the identification problem is decom-posed into a state estimation and a parameter identification part. Thisapproach is referred to as the Two-Step Method (TSM), although onewill find other names like Estimation Before Modelling (EBM) in theliterature. It will be shown in the present AGARDograph that thisapproach has significant practical advantages over methods which noattempt is made to decompose the joint parameter-state estimationproblem. The two-step method is generally applicable to flight vehiclessuch as fixed wing aircraft and rotorcraft which are equipped with stateof the art inertial reference systems. The theoretical developments inthe present AGARDograph will be illustrated with examples of a flighttest program with the De Havilland DHC-2 Beaver aircraft, the experi-mental aircraft of the Delft University of Technology which has beenused for almost two decades to test new ideas in the science of aircraftparameter identification. Author

N95-14205# Naval Air Warfare Center, Patuxent River, MD.Aircraft Div.ADD A DIMENSION TO YOUR ANALYSIS OF THEHELICOPTER LOW AIRSPEED ENVIRONMENTHERMAN KOLWEY 1994 30 p(AD-A283982) Avail: CASI HC A03/MF A01

We have long strived to better define the low airspeed relative windlimits of the helicopter and also to define the helicopter performance ina 3-dimensional (3-D) format. These concepts were first presented inan AHS paper in 1977 also published as NAVAIRTESTCEN TechnicalMemorandum TM 77-2 RW of 29 April 1977. Recent analysis of the lowairspeed environment for purposes of defining deficiencies and evalu-ating an Unanticipated Right Yaw (URY) or Loss of Tail Rotor Effective-ness (LTE) problem have developed a new method of reducing andpresenting critical azimuth test data. A new method of reducing test datawas presented to the Society of Right Test Engineers in a 1992 paperand involved the automatic handling of test data along with including theoscillatory component of the trim point. In our opinion, presentationformats were more logical than the classical methods of presentationof critical azimuth data, but they were still presented in a 2-dimensional(2-D) format. Dispersion data on the plot gave indications of the thirddimension of workload as has been presented by the Army in theirreports, but still on a 2-D plot. The location of interference effects couldbe determined by looking at six or seven 2-D plots of the type presentedin the prior paper. DTIC

N95-14306# Loral Systems, Inc., Orlando, FL. Adst Program Office.ADVANCED DISTRIBUTED SIMULATION TECHNOLOGYADVANCED ROTARY WING AIRCRAFT. STUDYCOMPARING APPROACHES TO MODELING THE ARWAMAIN ROTORROGER BRANSON 18 Mar. 1994 19 p(Contract(s)/Grant(s): N61339-91 -D-0001)(AD-A280824; ADST/TR-94-003280) Avail: CASI HC A03/MF A01

The Advanced Distributed Simulation Technology (ADST) Ad-vanced Rotary Wing Aircraft (ARWA) study comparing approaches tomodeling the ARWA main rotor provides details of technical ap-proaches for both a blade element model and a rotor disk model tosimulate the flying qualities of the ARWA simulation system. A back-ground of aeromodeling and discussion of the technical and cost meritsfor both approaches is provided. DTIC

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N95-14469*# Rockwell International Corp., El Segundo, CA.EXTRACTING A REPRESENTATIVE LOADING SPECTRUMFROM RECORDED FLIGHT DATAANTHONY G. DENVER In NASA. Langley Research Center, FAA/NASA International Symposium on Advanced Structural IntegrityMethods for Airframe Durability and Damage Tolerance p 225-240Sep. 1994Avail: CASI HC A03/MF A04

One of the more important ingredients when computing the life ofa structure is the loading environment. This paper describes thedevelopment of an aircraft loading spectrum that closely matches theservice experience, thus allowing a more accurate assessment of thestructural life. The paper outlines the flight loads data collection system,the procedures developed to compile and interpret the service recordsand the techniques used to define a spectrum suitable for structural lifeanalysis. The areas where the procedures were tailored to suit thespecial situation of the USAF B-1B bomber are also discussed. Theresults of the methodology verification, achieved by comparing thegenerated spectra with the results of strain gage monitoring duringservice operations, are also presented. Author

N95-14481*# Aeronautical Systems Div., Wright-Patterson AFB, OH.CHALLENGES FOR THE AIRCRAFT STRUCTURALINTEGRITY PROGRAMJOHN W. LINCOLN In NASA. Langley Research Center, FAA/NASAInternational Symposium on Advanced Structural Integrity Methods forAirframe Durability and Damage Tolerance p 409-423 Sep. 1994Avail: CASI HC A03/MF A04

Thirty-six years ago the United States Air Force established theUSAF Aircraft Structural Integrity Program (ASIP) because flight safetyhad been degraded by fatigue failures of operational aircraft. This initialprogram evolved, but has been stable since the issuance of MIL-STD-1530A in 1975. Today, the program faces new challenges because ofa need to maintain aircraft longer in an environment of reduced fundinglevels. Also, there is increased pressure to reduce cost of the acquisi-tion of new aircraft. It is the purpose of this paper to discuss thechallenges for the ASIP and identify the changes in the program that wilmeet these challenges in the future. Author

N95-14486*# Academy of Sciences (USSR), Moscow (USSR).Central Aerohydrodynamic Inst.ADVANCED METHOD AND PROCESSING TECHNOLOGYFOR COMPLICATED SHAPE AIRFRAME PART FORMINGP. V. MIODUSHEVSKY and G. A. RAJEVSKAYA fr?NASA. LangleyResearch Center, FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability and DamageTolerance p 497-503 Sep. 1994Avail: CASI HC A02/MF A04

Slow deformation modes of forming give considerably higherresidual fatigue life of the airframe part. It has experimentally proventhat fatigue life of complicated shape integral airframe panels made ofhigh strength aluminum alloys is significantly increased after creepdeformation process. To implement the slow deformation mode formingmethods, universal automated equipment was developed. Multichan-nel forming systems provide high accuracy of airframe part shapeeliminating residual stresses and spring effect. Forming processmultizone control technology was developed and experimentally provedthat static/fatigue properties of formed airframe parts are increased.

Author

N95-14604*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.GRAPHICAL USER INTERFACE FOR THE NASA FLOPSAIRCRAFT PERFORMANCE AND SIZING CODETHOMAS M. LAVELLE and BRIAN P. CURLETT Oct 1994 39 p(Contract(s)/Grant(s): RTOP 505-69-50)(NASA-TM-106649; E-8957; NAS 1.15:106649) Avail: CASI HC A03/MFA01

XFLOPS is an X-Windows/Motif graphical user interface for theaircraft performance and sizing code FLOPS. This new interface

simplifies entering data and analyzing results, thereby reducing analy-sis time and errors. Data entry is simpler because input windows areused for each of the FLOPS namelists. These windows contain fieldsto input the variable's values along with help information describing thevariable's function. Analyzing results is simpler because output data aredisplayed rapidly. This is accomplished in two ways. First, because theoutput file has been indexed, users can view particular sections with theclick of a mouse button. Second, because menu picks have beencreated, users can plot engine and aircraft performance data. Inaddition, XFLOPS has a built-in help system and complete on-linedocumentation for FLOPS. Author

N95-14794*# Rockwell International Corp., Downey, CA. SpaceSystems Div.REQUIREMENTS REPORT FOR SSTO VERTICAL TAKE-OFFAND HORIZONTAL LANDING VEHICLEH. S. GREENBERG 4 Nov. 1994 156 p(Contract(s)/Grant(s): NCC1-193; NCC2-9003; NCC8-39)(NASA-CR-197029; NAS 1.26:197029; SSD94D0217B) Avail: CASIHC A08/MF A02

This document describes the detailed design requirements anddesign criteria to support Structures/TPS Technology development forSSTO winged vehicle configurations that use vertical take-off andhorizontal landing and delivers 25,000 Ib payloads to a 220 nm circularorbit at an inclination of 51.6 degrees or 40,000 Ib payloads to a 150 nmcircular orbit at a 28.5 degree inclination. Derived from text

N95-14849S Naval Postgraduate School, Monterey, CA.ARTIFICIAL NEURAL NETWORK MODELING OF DAMAGEDAIRCRAFT M.S. ThesisCLIFFORD A. BRUNGER Mar. 1994 109 p(AD-A283227) Avail: CASI HC A06/MF A02

Aircraft design and control techniques rely on the proper modelingof the aircraft's equations of motion. Many of the variables used in theseequations are aerodynamic coefficients which are obtained from scalemodels in wind tunnel tests. In order to model damaged aircraft, everyaerodynamic coefficient must be determined for every possible dam-age mechanism in every flight condition. Designing a controller for adamaged aircraft is particularly burdensome because knowledge of theeffect of each damage mechanism on the model is required before thecontroller can be designed. Also, a monitoring system must be em-ployed to decide when and how much damage has occurred in order toreconfigure the controller. Recent advances in artificial intelligencehave made parallel distributed processors (artificial neural networks)feasible. Modeled on the human brain, the artificial neural network'sstrength lies in its ability to generalize from a given model. This thesisexamines the robustness of the artificial neural network as a model fordamaged aircraft DTIC

N95-14852*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.SPATIAL AWARENESS COMPARISONS BETWEEN LARGE-SCREEN, INTEGRATED PICTORIAL DISPLAYS ANDCONVENTIONAL EFIS DISPLAYS DURING SIMULATEDLANDING APPROACHESRUSSELL V. PARRISH, ANTHONY M. BUSQUETS, STEVEN P.WILLIAMS, and DEAN E. NOLD Oct. 1994 25 p Prepared incooperation with Army Communications-Electronics Command, FortMonmouth, NJ(Contract(s)/Grant(s): RTOP 505-64-53-03; DA PROJ. 1L1-62211-A-47-A)(NASA-TP-3467; L-17356; NAS 1.60:3467; CECOM-TR^94-E-1) Avail:CASI HC A03/MF A01

An extensive simulation study was performed to determine andcompare the spatial awareness of commercial airline pilots on simu-lated landing approaches using conventional flight displays with theirawareness using advanced pictorial 'pathway in the sky' displays.Sixteen commercial airline pilots repeatedly made simulated complex

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microwave landing system approaches to closely spaced parallelrunways with an extremely short final segment. Scenarios involvingconflicting traffic situation assessments and recoveries from flight pathoffset conditions were used to assess spatial awareness (own shipposition relative the the desired flight route, the runway, and othertraffic) with the various display formats. The situation assessment toolsare presented, as well as the experimental designs and the results. Theresults demonstrate that the integrated pictorial displays substantiallyincrease spatial awareness over conventional electronic flight informa-tion systems display formats. Author

N95-14909*# Mississippi State Univ., State College, MS. Computa-tional Fluid Dynamics Lab.PROPULSION/AIRFRAME INTERFERENCE FOR DUCTEDPROPFAN ENGINES WITH GROUND EFFECT Final Report,Mar. 1993 - Feb. 1995ABDOLLAH ARABSHAHI and RAMESH PANKAJAKSHAN 11 Nov.1994 17 p Prepared in cooperation with NSF, Washington, DC(Contract(s)/Grant(s): NAG1-226)(NASA-CR-197110; MAS 1.26:197110) Avail: CASI HC A03/MF A01

The advanced propfan propulsion systems design of the next-generation subsonic transport aircraft has been of interest to manyairline companies in the past several years. This is due to the studieswhich indicate that an efficient ducted propfan engine technology offersa significant reduction in aircraft fuel consumption. However, becauseof the geometric complexity of the configuration, one challenge is theintegration of the ducted propfan engine with the airframe so thataerodynamic interference effects frequently encountered near thenacelle can be minimized, or perhaps, optimized. To understand thisinteraction phenomenon better, it is desirable to have a reliable andefficient computational tool that can predict propeller effects on theflowfield around complex configurations. Derived from text

N95-15451 RAND Corp., Santa Monica, CA.THE F-16 MULTINATIONAL STAGED IMPROVEMENTPROGRAM: A CASE STUDY OF RISK ASSESSMENT ANDRISK MANAGEMENTFRANK CAMM 1993 123p Limited Reproducibility: More than20% of this document may be affected by microfiche quality(Contract(s)/Grant(s): F49620-91-C-0003)(AD-A281706; RAND/N-3619-AF) Avail: CASI HC A06

The F-16 Multinational Staged Improvement Program (MSIP) isthe development program that the F-16 program has used to movebeyond the F-16A/B. Its primary product has been the F-16C/D, anaircraft whose design evolves over time as new technological capabili-ties become available or attractive to incorporate in its design. MSIP isthe program that F-16C/D developers have used to introduce thesecapabilities over time. The prime contractor for the F-16, GeneralDynamics, and the F-16 System Program Office (SPO) formallyinitiated the program in 1980. This study examines MSIP, giving specialattention to means of assessing and managing the risks associatedwith system development. It is one of seven case studies conducted byRAND for the Air Force to examine the Air Force's management of riskin development programs during the 1980's. DTIC

N95-15742*# Universities Space Research Association, Columbia,MD.THE ALUMINUM FALCON: A LOW COST MODERNCOMMERCIAL TRANSPORTMARK BRYANT, ESTELA HERNANDEZ, GREGORY KING, ALEXCHOUA LOR, JANA MUSSER, DEANNE TRIGS, and SUSAN YEE6Jun. 1994 109 p(Contract(s)/Grant(s): NASW-4435)(NASA-CR-197180; NAS 1.26:197180) Avail: CASI HC A06/MF A02

The American Institute of Aeronautics and Astronautics (AIAA)

released a Request For Proposal (RFP) in the form of an undergraduatedesign competition for a 153 passenger jet transport with a range of3,000 nautical miles. The primary requirement for this aircraft was lowcost, both in acquisition and operation, with a technology availabilitydate of the year 2000. This report presents the Non-Solo DesignGroup's response to the RFP, the Aluminum Falcon (AF-1). Non-Solo'sapproach to development was to take the best elements of sevenindividual preliminary designs, then combine and refine them. Theresulting aircraft meets or exceeds all requirements of both the RFP andthe Federal Aviation Administration (FAA). Highlights include a revolu-tionary wing planform, known as an M-wing, which offers manyadvantages over a conventional aft swept wing. For example, the M-wing lessens the travel in the aircraft center of gravity caused by fuelbeing stored in the wing. It also reduces the amount of torque imposedon the center wing box because more of the lifting load acts near thefuselage joint, rather than behind it. In essence, the M-wing offers thebest of both worlds: using a forward swept wing root places theaerodynamic center of the wing further forward and allows the landinggear to be placed without the use of a yahudi. At the same time, with theoutboard section swept backward the tip retains an amount of aeroelasticdampening that is lost on a completely forward swept wing. The resultis a wing which has many advantages of a straight, unswept wingswithout the severe compressibility effects at high Mach numbers. Otherhighlights include judicious use of composites, giving recognition to theimportance of weight and its effect on aircraft cost and performance,and an advanced passenger entertainment system which can be usedas a source of revenue for the airlines. This aircraft meets the low-costdoctrine with an acquisition cost of $29 million and a direct operatingcost of 3.5 cents per seat mile. The AF-1 incorporates new ideas withexisting technology to result in an aircraft that will retain market viabilitywell into the next century. Author

N95-15815# Army Test and Evaluation Command, AberdeenProving Ground, MD.TEST OPERATION PROCEDURE (TOP): VIBRATIONTESTING OF HELICOPTER EQUIPMENT Final Report26 Aug. 1994 42 p(AD-A284433; TOP-7-3-531) Avail: CASI HC A03/MF A01

This TOP provides guidelines and procedures for helicoptervibration calibration and measurements. Guides are provided forvibration frequencies and magnitudes to be expected. Procedures aredeveloped for transducer selection and placement, instrumentationsystem design, and data collection. Emphasis is placed on use ofpiezoelectric accelerometers for vibration measurement and taperecorders for data storage. Step-by-step procedures are provided foraccelerometer sensitivity measurement and calibration, instrumenta-tion system adjustments and calibrations, and data collection andhandling. DTIC

N95-15821 Technische Hochschule, Aachen (Germany). Inst. fuerMechanik.PREDICTION OF ROTOR-BLADE DEFORMATIONS DUE TOUNSTEADY AIRLOADS Interim Report No. 1, May 1994 -Jun. 1995J. BALLMANN and S. SCHLECHTRIEM 31Jul.1994 9p LimitedReproducibility: More than 20% of this document may be affected bymicrofiche quality(Contract(s)/Grant(s): N68171-94-C-9068)(AD-A284467; R/D-7213-AN-01) Avail: Issuing Activity (DefenseTechnical Information Center (DTIC))

SOFIA, a computer code for aeroelastic computations, wasapplied to predict the rotor blade deformations due to unsteady airloadscaused by blade-vortex interaction (BVI) and to investigate appropriatecontrol movements to minimize vibration and noise. The computationof the unsteady, compressible, inviscid flow about rotor-blades uses anEuler CFD code, while a quasi one-dimensional structural solver is usedto compute the deformation of the rotor blades. DTIC

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06 AIRCRAFT INSTRUMENTATION

06AIRCRAFT INSTRUMENTATION

Includes cockpit and cabin display devices; and flight instruments.

A95-61741ON-BOARD AVIONICS MAINTENANCEAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 6 June 1993 p. 13-15(BTN-94-EIX94461047054) Copyright

As avionics standards evolve, there is increasing interactionbetween technology and the line mechanic and, at the same time, lessemphasis on the line mechanic as the knowledge base for maintenanceinformation. Author (El)

N95-14518* National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.AIRCRAFT MANEUVER ENVELOPE WARNING SYSTEMPatentCOURTLAND C. BIVENS, inventor (to NASA), JOEL M. ROSADO,inventor (to NASA), and BURNETT LEE, inventor (to NASA) 25 Oct1994 9p Red 16 Mar. 1993(NASA-CASE-ARC-11953-1; US-PATENT-5,359,326; US-PATENT-APPL-SN-032067; US-PATENT-CLASS-340-971; US-PATENT-CLASS-340-945; US-PATENT-CLASS-340-978; INT-PATENT-CLASS-G01C-21/00) Avail: US Patent and Trademark Office

A maneuver envelope warning system for an aircraft havingoperating limits, operating condition sensors and an indicator driver.The indicator driver has a plurality of visual indicators. The indicatordriver determines a relationship between sensed operating conditionsand the operating limits; such as, a ratio therebetween. The indicatordriver illuminates a number of the indicators in proportion to thedetermined relationship. The position of the indicators illuminatedrepresents to a pilot in an easily ascertainable manner whether theoperational conditions are approaching operational limits of the aircraft,and the degree to which operational conditions lie within or exceedoperational limits. Author

cockpit was about 12 dB greater than the NSWCDD MSC. Theobserved stirring ratios (ratio of maximum received signal to minimumreceived signal at a particular frequency as the tuner rotates) weregenerally less than 10 dB up to about 800 MHz. OTIC

07

AIRCRAFT PROPULSION AND POWER

Includes prime propulsion systems and systems components, e.g., gasturbine engines and compressors; and on-board auxiliary power plantsfor aircraft

A95-61727TRENT ENGINE DEVELOPMENTSTUART BIRCH Aerospace Engineering (Warrendale, Pennsylva-nia) (ISSN 0736-2536) vol. 13, no. 12 December 1993 p. 30-32(BTN-94-EIX94461290507) Copyright

The design, development and certification of a new civil aeroengine by Rolls-Royce is described. The new three-shaft turbofanengine, called the Trent, is scheduled to fly in 1994, with an in-servicedate of January 1955. It combines both proven and advanced technol-ogy, including hollow, diffusion bonded, and superplastically formed fanblades. El

A95-61732FOIL BEARINGS FOR GAS TURBINE ENGINESAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 9 September 1993 p. 15-19(BTN-94-EIX94461290279) Copyright

Various design factors are considered which affect a foil bearing'sdynamic stiffness and damping characteristics. It is shown that optimiz-ing a foil bearing can have a significant effect on the stability of a typicalrotor in the hot end of an auxilliary power unit or gas turbine. This is anecessary tool to ensure successful integration and production trans-ition of high-temperature foil bearings into gas turbine engines. El

N95-15392 Naval Surface Warfare Center, Dahlgren, VA.ELECTROMAGNETIC REVERBERATIONCHARACTERISTICS OF A LARGE TRANSPORT AIRCRAFTFinal ReportMICHAEL O. HATFIELD, GUSTAV J. FREYER, D. M. JOHNSON, andCHARLES L. FARTHING Jul. 1994 95 p Limited Reproducibility.More than 20% of this document may be affected by microfiche quality(AD-A282923; NSWCDD/TR-93/339) Avail: CASI HC A05

A demonstration test to investigate the reverberation characteris-tics of the avionics bay and cockpit of a typical commercial aircraft wasconducted on a decommissioned Boeing 707-720B aircraft. The air-craft, located at the Aerospace Maintenance and Regeneration Center,Davis Monthan Air Force Base, Arizona, had a significant fraction of itselectronics equipment remaining in the avionics bay and cockpit andthe passenger compartment was essentially intact A simulated avion-ics box was placed in an equipment rack and a trace on an internalcircuit board was monitored. The simulated avionics box was alsotested in the Naval Surface Warfare Center, Dahlgren Division(NSWCDD) mode stirred chamber (MSC). The avionics bay andcockpit were internally excited from 100 MHz to 18 GHz using a pair ofhorn and wire antennas placed in several locations. Aluminum foiltuners, each 2 x 2 ft, were located in the avionics bay and the cockpitThe internal electromagnetic environment was measured by a horn anda wire antenna placed successively in several locations in the avionicsbay and cockpit Limited measurements of the local ambient environ-ment, both external to the aircraft and within the aircraft, were obtainedfor the FM band (88 to 108 MHz) and the VHF/UHF bands (100 MHz to1 GHz). Cavity losses were characterized by comparing the receivedpower to the input power. The cavity loss for the avionics bay was about15 dB greater than the loss in the NSWCDD MSC. The loss for the

A95-61736SMALL GAS TURBINES IN THE 21ST CENTURYAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 8 August 1993 p. 17-20(BTN-94-EIX94461290241) Copyright

Today's small gas turbine engines have five times the power atabout the same weight and half the fuel consumption of the earlyengines. In addition, the reliability and durability of today's engines areat least five time better. Modifications to the cycles of small gas turbinescan produce significant improvements in power density and fuelconsumption. El

A95-61737TURBOFAN PROPULSION SIMULATORAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2533)vol. 13, no. 8 August 1993 p. 11 -16(BTN-94-EIX94461290240) Copyright

An ultra-high-bypass turbofan propulsion simulator (UPS) is usedto evaluate fan aero performance, source noise and acoustic treatmenteffectiveness, high-angle-of-attack inlet fan operability performance,and aeromechanics. The UPS is a pneumatically powered single-shaft,ducted-fan-engine model propulsion simulator. It can accommodatefans of a nominal 0.6 m tip diameter. El

A95-62264ON PROFILING A CAM OF AN AXIAL AVIATION DIESELENGINE BY PERIODIC SPLINESA. A. RYZHOV NPP Motor, Ufa (Russia) and YU. S. SHATALOV

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Izvestiya VUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4October-December 1993 p. 28-33 In RUSSIAN(BTN-94-EIX94461407946) Copyright

A method has been developed to construct a profile, based on atwo-parametric periodic spline, with continuous up to the second orderderivatives along the turn angle. The spline should be selected so thatthe inertia force of the rod be a continuous function; the force acting onthe rod should have a minimal amplitude and be positive. An examplecalculation is given. El

A95-62638PROFILING OF THE WORKING SURFACE OFELECTRODES-TOOLS FOR CIRCLE ELECTROCHEMICALDIMENSIONAL TREATMENT OF COMPRESSOR BLADESYU. M. VAKHITOV KazNIlD, Kazan (Russia), V. F. GERASIMOV, A.I. ALMAN, and A. KH. KARIMOV Izvestiya VUZ: AviatsionnayaTekhnika (ISSN 0579-2975) no. 4 October-December 1993p. 100-103 In RUSSIAN(BTN-94-EIX94461407964) Copyright

Compressor blades of advanced aviation engines should bemanufactured according to the first-second classes of accuracy of thestandard 102571-86. The blades mentioned cannot be manufacturedusing the traditional technology. The paper offers a method to profileelectrodes for the electrochemical dimensional treatment of blades ofgas turbine engines. The test results have been presented. El

N95-14645# Spectra Research Systems, Inc., Huntsville, ALA GRAPHICAL USER INTERFACE FOR DESIGN ANDANALYSIS OF AIR BREATHING PROPULSION SYSTEMSCHARLES P. DEPLACHETT and RICHARD K. STEINBERG InHuntsville Association of Technical Societies, TABES 1994: 10thAnnual Technical and Business Exhibition and Symposium 7p 1994Sponsored by Army Missile Command(TABES PAPER 94-616) Avail: CASI HC A02/MF A04

Existing air breathing propulsion engine analysis software re-quires extensive training to use. Therefore, a need exists for a userfriendly computer simulation which is capable of analyzing air breathingpropulsion cycles quickly and efficiently. Human factors studies havebeen performed for real-time interactive computer displays for DODsystems. The technologies resulting from these real-time displaydesigns are being used to produce an optimal graphical user interface(GUI) which will provide a means for interactive design and/or modifi-cation of air breathing propulsion systems. Author

N95-15683# Purdue Univ., West Lafayette, IN. ResearchFoundation.GAS TURBINE PREDIFFUSER-COMBUSTORPERFORMANCE DURING OPERATION WITH AIR-WATERMIXTURE Interim Report, 10 May 1992 - 20 Aug. 1993P. LAING and S. N. B. MURTHY Aug. 1994 139p(Contract(sXGrant(s): FAA-92-G-002)(DOT/FAA/CT-93/52; M/FAA/002-93-1) Avail: CASI HC A07/MF A02

In a continuing effort to establish performance changes due towater ingestion into an aircraft gas turbine engine and possible designimprovements, an experimental investigation was performed with amodel gas turbine prediffuser-combustor sector utilizing a number ofmixture and flow conditions in a tunnel operating with a two-phase, air-liquid film-droplet mixture. For given entry conditions into the prediffuser(which can be related to the exit conditions of the core compressor ina bypass engine, and, therefore, also to ingestion conditions at theengine face) the two main issues are (1) the amount of water enteringthe primary zone of the combustor, and (2) the local reduction intemperature, flame-water interactions, and the vitiation caused by thevaporizing of water. Row visualization and estimates of water flow anddroplet size in the primary zone have been undertaken under cold flowconditions. The amount of water entering the primary zone has beenfound to be a complex function of (1) the air-water mixture conditions atentry to the prediffuser, and (2) the effects of gravity on the flowfield forgiven geometry of the prediffuser-combustor, and the flow split betweenthe primary and the coolant streams in the combustor. Combustiontests have been carried out to establish the effects on performance,occurrence of flameout, and recoverability of combustor exit tempera-ture by enhancement of one or both of the fuel equivalence ratio and theoxygen content of air. It was tentatively concluded that the observedeffects of the presence of water are a result of the interactive effects ofheat transfer to water, vitiation by water vapor on combustion, and thetotal heat release in the primary zone, the latter being the dominantfactor in stabilizing the flame with a large increase in combustor exittemperature, as found in the tests with the addition of both fuel andoxygen to a given burning mixture. Author

08

AIRCRAFT STABILITY AND CONTROL

Includes aircraft handling qualities; piloting; flight controls; andautopilots.

N95-15329* Naval Postgraduate School, Monterey, CA.COMBUSTION EFFICIENCY IN A DUAL-INLET SIDE-DUMPRAMJET COMBUSTOR M.S. ThesisMARTIN W. DEPPE Jun. 1994 50 p(AD-A283564) Avail: CASI HC A03/MF A01

A dual, axially-in-line, side-dump, liquid-fueled ramjet combustorwas designed and tested with varying fuel-air ratios, atomizer types,and air distributions between the two inlets. Particle size distributionsproduced by the atomizers were measured at the inlet duct plane. Whenoperated in a centra-flow direction, all of the atomizers producedexcellent atomization with a Sauter mean diameter less than 14microns. The dual, in-line inlets provided improved flammability limitsand combustion efficiencies at lean fuel-air ratios when compared tosingle side-dump performance. Direct injection of approximately 20percent of the fuel flow into the dome region was found to provideimproved lean flammability limits for the single side-dump, but was notrequired with the dual inlets. The fuel distribution in the inlet ductrequired for good flammability limits and combustion efficiency wasopposite to that required to prevent pressure oscillations, indicating thata dump plane aero-grid will often be necessary. A dump angle of 45 degresulted in lower than desired combustion efficiencies, apparently dueto poor mixing with the air from the aft inlet DTIC

A95-62631LOCAL-OPTIMAL CONTROL OF A FLYING VEHICLE, WITHFINAL STATE OPTIMIZEDV. I. SMAGINTGU, Tomsk (Russia) Izvestiya VUZ: AviatsionnayaTekhnika (ISSN 0579-2975) no. 4 October-December 1993 p. 74-76 In RUSSIAN(BTN-94-EIX94461407957) Copyright

The problem of the horizontal gliding of a flying vehicle at theheight given is solved by an algorithm and by the numerical optimizationof the terminal criterion. The algorithm is designed for the local-optimalcontrol of a moving point. The control mechanism is formed as anonlinear feedback. An equation for the movement of a flying vehicle inthe longitudinal plane has been given. It is meant that the flying vehicleis landing in the atmosphere. El

N95-14343 Carnegie-Mellon Univ., Pittsburgh, PA. Dept of Com-puter Science.COMPUTING QUANTITATIVE CHARACTERISTICS OFFINITE-STATE REAL-TIME SYSTEMSS. CAMPOS, E. CLARKE, W. MARRERO, and M. MINEA 4 May 199423 p Limited Reproducibility: More than 20% of this document may be

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08 AIRCRAFT STABILITY AND CONTROL

affected by microfiche quality(Contract(s)/Grant(s): MDA972-90-C-0035)(AD-A282839; CMU-CS-94-147) Avail: CASI HC A03

Current methods for verifying real-time systems are essentiallydecision procedures that establish whether the system model satisfiesa given specification. We present a general method for computingquantitative information about finite-state real-time systems. We havedeveloped algorithms that compute exact bounds on the delay betweentwo specified events and on the number of occurrences of an event inany given interval. This technique allows us to determine performancemeasures such as schedulability, response time, and system load. Ouralgorithms produce more detailed information than traditional methods.This information leads to a better understanding of system behavior, inaddition to determining its correctness. We also show that our tech-nique can be extended to a more general representation of real-timesystems, namely, timed transition graphs. The algorithms presented inthis paper have been incorporated into the SMV model checker andused to verify a model of an aircraft control system. The results obtaineddemonstrate that our method can be successfully applied in theverification of real-time system designs DTIC

N95-14448# Office National d'Etudes et de Recherches Aerospatiales,Paris (France).LATERAL JET CONTROL FOR TACTICAL MISSILESP. CHAMPIGNY and R. G. LACAU In AGARD, Missile Aerodynamics57 p Jun. 1994Copyright Avail: CASI HC A04/MF A03

The aim of this paper is to give a survey of lateral jets as controlsystem of tactical missiles. The paper is divided into four parts. The firstpart gives a brief analysis of new control requirements pertaining totactical missiles, presents the advantages of lateral jet control, anddescribes two types of applications for missiles designed and devel-oped by Aerospatiale-Missiles. The first example relates to the ground/surface-to-air missile ASTER which has antimissile capability; thesecond example concerns the antitank missile ERYX. The second partpresents in detail the phenomenological aspects of lateral jets and theinfluence of various flow parameters and missile geometry on controlsystem performance. The third part describes some wind-tunnel testingproblems. The fourth and last part is dedicated to computation forvaluation and understanding of the aerodynamic interactions.

Derived from text

N95-14815# Technische Univ., Delft (Netherlands). Faculty of Aero-space Engineering.A SIMULINK ENVIRONMENT FOR FLIGHT DYNAMICS ANDCONTROL ANALYSIS: APPLICATION TO THE DHC-2BEAVER. PART 1: IMPLEMENTATION OF A MODELLIBRARY IN SIMULINK. PART 2: NONLINEAR ANALYSISOF THE BEAVER AUTOPILOT (Diskette Supplement) M.S.ThesisMARCO.RAUW Sep. 1993 265 p Diskette supplement: 3.5-inchDSDD(NONP-NASA-SUPPL-DK-94-28027) Avail: CASI SET A19 (HC.DK)

The design of advanced Automatic Aircraft Control Systems(AACS's) can be improved upon considerably if the designer canaccess all models and tools required for control system design andanalysis through a graphical user interface, from within one softwareenvironment. This MSc-thesis presents the first step in the develop-ment of such an environment, which is currently being done at theSection for Stability and Control of Delft University of Technology,Faculty of Aerospace Engineering. The environment is implementedwithin the commercially available software package MATLAB/SIMULINK. The report consists of two parts. Part 1 gives a detaileddescription of the AACS design environment The heart of this environ-ment is formed by the SIMULINK implementation of a nonlinear aircraftmodel in block-diagram format The model has been worked out for theold laboratory aircraft of the Faculty, the DeHavilland DHC-2 "Beaver",but due to its modular structure, it can easily be adapted for other

aircraft. Part 1 also describes MATLAB programs which can be appliedfor finding steady-state trimmed-flight conditions and for linearization ofthe aircraft model, and it shows how the built-in simulation routines ofSIMULINK have been used for open-loop analysis of the aircraftdynamics. Apart from the implementation of the models and tools, athorough treatment of the theoretical backgrounds is presented. Part 2of this report presents a pan of an autopilot design process for the'Beaver* aircraft, which dearly demonstrates the power and flexibility ofthe AACS design environment from part 1. Evaluations of all longitudi-nal and lateral control laws by means of nonlinear simulations aretreated in detail. A floppy disk containing all relevant MATLAB programsand SIMULINK models is provided as a supplement

Author (revised)

N95-14900* Technische Univ., Brunswick (Germany). Inst. of RightGuidance and Control.TURBULENCE: ENGINEERING MODELS, AIRCRAFTRESPONSEMANFRED SWOLINSKY In AGARD, Right in an Adverse Environ-ment 20 p Nov. 1994Copyright Avail: CASI HC A03/MF A02

This paper covers problems of flight in a turbulent atmosphere. Arealistic simulation of aircraft behavior in turbulent air requires differentengineering models. On one hand, this means a mathematical descrip-tion of random turbulence or short scale gusts. For simple problems, acomputation of the turbulence velocity vector only at the trajectory of theaircraft is sufficient. In cases of detailed investigations, the generationof a 3-dimensional spatial turbulence field is necessary. Additional realtime requirements imply special approaches, such as the realization ofa matrix wind model. On the other hand the description of the interactionbetween turbulence or short scale gusts and aircraft may requirecomplex aerodynamic models especially if the gust scale and theaircraft scale are in the same order of magnitude. The presented multipoint or lifting surface models consider the wind vector at several pointsalong the wing span under real time constraints. Based on simulationresults and flightiest data, the dynamic aircraft response is discussed.Single gust effects are demonstrated by examples of cross flightsthrough the updraft of a powerplant cooling tower. Author

09RESEARCH AND SUPPORT FACILITIES (AIR)

Includes airports, hangars and runways; aircraft repair and overhaulfacilities; wind tunnels; shock tube facilities; and engine test blocks.

A95-61735FLIGHT SIMULATIONAerospace Engineering (Warrendale, Pennsylvania) (ISSN 0736-2536)vol. 13, no. 8 August 1993 p. 21-24(BTN-94-EIX94461290242) Copyright

To keep pace with advancing aeronautical technologies, thecapability for dynamically simulating high-quality flight on the ground isneeded. Ground simulation is a critical step in the process of air vehicledevelopment. The Combined Acceleration Right Simulator (CAFS) willfulfill that requirement El

N95-13687* Wright Lab., Wright-Patterson AFB, OH.DEVELOPMENTS IN LASER-BASED DIAGNOSTICS FORWIND TUNNELS IN THE AEROMECHANICS DIVISION: 1987-1992 Final Report, Jan. 1987 - Dec. 1992UNDA G. SMITH, MARK S. MAURICE, CHARLES TYLER, JOHN D.SCHMISSEUR, and GEORGE L. SEIBERT May 1994 107 p(Contract(s)/Grant(s): AF PROJ. 2404){AD-A283011; WL-TR-94-3054) Avail: CASI HC A06/MF A02

The Aero-Diagnostics Research Section of the AeromechanicsDivision develops and advances laser-based diagnostic techniques for

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ASTRONAUTICS 10

use in a variety of subsonic through hypersonic wind tunnel facilities.These include laser velocimetry, laser induced fluorescence, Rayleighscattering, phase shift holographic interferometry, and chemilumines-cence. The purpose of this report is to bring the reader up to date on thestatus of these and other techniques under development in the Aero-mechanics Division at the Wright Laboratory. DTIC

N95-14415* National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.AIRPLANE TAKEOFF AND LANDING PERFORMANCEMONITORING SYSTEM PatentDAVID B. MIDDLETON, inventor (to NASA), RAGHAVACHARISRIVATSAN, inventor (to NASA), and LEE H. PERSON, JR., inventor(to NASA) 4 Oct. 1994 28 p Filed 6 Apr. 1993 Continuation ofabandoned US-Patent-Appl-SN-755248, filed 5 Sep. 1991 which is acontinuation-in-partof US-Patent-Appl-SN-192562, filed 11 May 1988which is a continuation-in-part of US-Patent-Appl-SN-082766, filed 6Aug. 1987(NASA-CASE-LAR-14745-2-SB; US-PATENT-5,353,022; US-PATENT-APPL-SN-045337; US-PATENT-APPL-SN-755248; US-PATENT-APPL-SN-192562; US-PATENT-APPL-SN-082766; US-PATENT-CLASS-340-959; US-PATENT-CLASS-73-178T; US-PATENT-CLASS-364-427; INT-PATENT-CLASS-G08B-21/00) Avail:US Patent and Trademark Office

The invention is a real-time takeoff and landing performancemonitoring system for an aircraft which provides a pilot with graphic andmetric information to assist in decisions related to achieving rotationspeed (VR) within the safe zone of a runway, or stopping the aircraft onthe runway after landing or take-off abort. The system processesinformation in two segments: a pretakeoff segment and a real-timesegment. One-time inputs of ambient conditions and airplane configu-ration information are used in the pretakeoff segment to generatescheduled performance data. The real-time segment uses the sched-uled performance data, runway length data and transducer measuredparameters to monitor the performance of the airplane throughout thetakeoff roll. Airplane acceleration and engine-performance anomaliesare detected and annunciated. A novel and important feature of thissegment is that it updates the estimated runway rolling friction coeffi-cient. Airplane performance predictions also reflect changes in headwind occurring as the takeoff roll progresses. The system provides ahead-down display and a head-up display. The head-up display isprojected onto a partially reflective transparent surface through whichthe pilot views the runway. By comparing the present performance ofthe airplane with a continually predicted nominal performance basedupon given conditions, performance deficiencies are detected by thesystem and conveyed to pilot in form of both elemental information andintegrated information.

Official Gazette of the U.S. Patent and Trademark Office

N95-15328* Systems Control Technology, Inc., Arlington, VA.VERTICAL FLIGHT TERMINAL OPERATIONALPROCEDURES. A SUMMARY OF FAA RESEARCH ANDDEVELOPMENT Final ReportRAYMOND H. MATTHEWS Jul. 1994 53 p(Contract(s)/Grant(s): DTFA01-87-C-00014)(AD-A283550; SCT-92-RR-9; DOT/FAA/RD-94/24) Avail: CASI HCA04/MF A01

Common-carrier operations by helicopters are becoming increas-ingly routine. Prospects for their future utilization are promising as thevariety of uses continues to grow and public acceptance expands. TheFederal Aviation Administration (FAA) and industry are working to morefully integrate vertical flight vehicles in to the National Airspace System(NAS). Rotorcraft, including tiltrotor, tiltwing, and helicopters, areunique and each offers potential benefits that may provide relief to thedelay problems being experienced throughout the NAS. Before theseadvantages can be fully exploited, a myriad of untested areas must beexplored through research and development (R and D) activities toprove their viability. One important area is safety in terminal area

operations. Safety includes such diversified subjects as approach anddeparture procedures, one-engine-inoperative (OEI) operations, lossof engine during critical flight phases, and landing site qualifications andcapabilities. Pilot qualification, training of pilots and ground servicepersonnel, precision approach glideslope angles, obstruction avoid-ance, etc., are also important safety concerns. Some of these topicshave been addressed, others are currently under investigation, whileothers are still in the planning stages. DTIC

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ASTRONAUTICS

Includes astronautics (general); astrodynamics; ground support sys-tems and facilities (space); launch vehicles and space vehicles; spacetransportation; spacecraft communications, command and tracking;spacecraft design, testing and performance; spacecraft instrumenta-tion; and spacecraft propulsion and power.

A95-62259SOFT LANDING ON THE SLOPE SURFACE OF A LANDINGVEHICLE WITH AN AIR SHOCK-ABSORBER OF FORCEDPRESSURIZATIONS. S. KOMAROV UGATU, Ufa (Russia) and N. I. MISKAKTINIzvestiya VUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4October-December 1993 p. 3-9 In RUSSIAN(BTN-94-EIX94461407941) Copyright

Based on the solution of the optimization problem, the stability ofa spacecraft landing is estimated. The spacecraft is equipped with aconical pressurized shock-absorber. Dynamics of spacecraft landingwith an air shock-absorber of forced pressurization has been investi-gated. The flat movement of a device with a soft foundation has beenstudied. The foundation changes its shape, due to the contact with thelanding platform. El

A95-62657VARIATIONS OF PERTURBATIONS IN PERIGEE HEIGHTWITH ECCENTRICITY FOR ARTIFICIAL EARTH'SSATELLITES DUE TO AIR DRAGY. E. HELALI Helwan Institute of Astronomy and Geophysics, Cairo,Egypt and H.M.BASURAH K.A.A.U.,Jeddah,Saudia Arabia Earth,Moon, and Planets (ISSN 0167-9295) vol. 64, no. 2 February 1994p. 133-137(HTN-95-40013) Copyright

The variations of perturbations in perigee distance for differentvalues of the orbital eccentricity for artificial Earth's satellites due to airdrag have been studied. The analytical solution of deriving theseperturbations, using the TD model (Total Density) have been applied,(Helali; 1987). The theory is valid for altitudes ranging from 200 to 500km above the Earth's surface and for solar 10.7 cm flux. Numericalexamples are given to illustrate the variations of the perturbations inperigee distance with changing eccentricity (e less than 0.2). A strongeperturbations in the perigee distance have been shown when theeccentricity in the range 0.001 less than e less than 0.05, especially forperigee distance 200 km. Author (Hemer)

N95-13718** MCAT Inst, Moffett Reid, CA.SCIENCE OBJECTIVES AND PERFORMANCE OF ARADIOMETER AND WINDOW DESIGN FOR ATMOSPHERICENTRY EXPERIMENTSROGER A. CRAIG, WILLIAM C. DAVY, and ELLIS E. WHITING Inits Planetary Entry Experiments 41 p Jul. 1994Avail: CASI HC A03/MF A02

The Radiative Heating Experiment, RHE, aboard the AeroassistRight Experiment, AFE, (now cancelled) was to make in-situ measure-ments of the stagnation region shock layer radiation during an aerobraking

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maneuver from geosynchronous to low earth orbit. The measurementswere to provide a data base to help develop and validate aerotherm-odynamic computational models. Although cancelled, much work wasdone to develop the science requirements and to successfully meetRHE technical challenges. This paper discusses the RHE scientificobjectives and expected science performance of a small sapphirewindow for the RHE radiometers. The spectral range required was from170 to 900 nm. The window size was based on radiometer sensitivityrequirements including capability of on-orbit solar calibration. Author

N95-14089*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.SIMULATION OF SHUTTLE LAUNCH G FORCES ANDACOUSTIC LOADS USING THE NASA AMES RESEARCHCENTER 20G CENTRIFUGET. L. SHAW, J. M. CORLISS, D. P. GUNDO, G. M. MULENBURG, G.A. BREIT, and J. B. GRIFFITH In NASA. Goddard Space FlightCenter, Eighteenth Space Simulation Conference: Space MissionSuccess Through Testing p 349-371 Nov. 1994Avail: CASI HC A03/MF A04

The high cost and long times required to develop researchpackages for space flight can often be offset by using ground testtechniques. This paper describes a space shuttle launch and reentrysimulating using the NASA Ames Research Center's 20G centrifugefacility. The combined G-forces and acoustic environment duringshuttle launch and landing were simulated to evaluate the effect on apayload of laboratory rates. The launch G force and acoustic profilesare matched to actual shuttle launch data to produce the required G-forces and acoustic spectrum in the centrifuge test cab where the ratswere caged on a free-swinging platform. For reentry, only G force issimulated as the aero-acoustic noise is insignificant compared to thatduring launch. The shuttle G-force profiles of launch and landing areachieved by programming the centrifuge drive computer to continu-ously adjust centrifuge rotational speed to obtain the correct launch andlanding G forces. The shuttle launch acoustic environment is simulatedusing a high-power, low-frequency audio system. Accelerometer datafrom STS-56 and microphone data from STS-1 through STS-5 are usedas baselines for the simulations. This paper provides a description ofthe test setup and the results of the simulation with recommendationsfor follow-on simulations. Author

N95-14096*# Industrieanlagen-Betriebsgesellschaft m.b.H.,Ottobrunn (Germany).THERMOACOUSTIC ENVIRONMENTS TO SIMULATEREENTRY CONDITIONSGERHARD BAYERDOERFER In NASA. Goddard Space RightCenter, Eighteenth Space Simulation Conference: Space MissionSuccess Through Testing p 441 -450 Nov. 1994 Sponsored byBMFTAvail: CASI HC A02/MF A04

Aerothermal environments as encountered during the reentry ofspaceplanes or during the cruise of hypersonic aircrafts representcomplex loading conditions for the external structures of those vehicles.In order to shield against the aerodynamic heating a special ThermalProtection System (IPS) is required which is designed as a light weightstructure to reduce the weight penalty. TPS is therefore vulnerable tovibroacoustic fatigue caused by the pressure fluctuations of the envi-ronment. Because of the complex interactions between the loadingforces and the resulting structural response which make an analyticaltreatment difficult and in order to provide means for fatigue testing IABGhas designed and built a thermoacoustic facility which recently becameoperational. The facility is capable to produce surface temperatures upto 1.300 C at sound pressure levels up to 160 dB. This paper describesthe design of the facility, some operational test work it also deals withproblems associated with the facility instrumentation. Author

N95-14162*# Fairchild Space Co., Germantown, MD. Communica-tions, Data Handling, and Power Systems.EVOLUTIONARY TELEMETRY AND COMMANDPROCESSOR (TCP) ARCHITECTURE

JOHN R. SCHNEIDER In Research Inst. for Computing andInformation Systems, RICIS Symposium 1992: Mission and SafetyCritical Systems Research and Applications 20 p 30 Oct. 1992Avail: CASI HC A03/MF A03

A low cost, modular, high performance, and compact Telemetryand Command Processor (TCP) is being built as the foundation ofcommand and data handling subsystems for the next generation ofsatellites. The TCP product line will support command and telemetryrequirements for small to large spacecraft and from low to high rate datatransmission. It is compatible with the latest TDRSS, STDN and SGLStransponders and provides CCSDS protocol communications in addi-tion to standard TDM formats. Its high performance computer providescomputing resources for hosted flight software. Layered and modularsoftware provides common services using standardized interfaces toapplications thereby enhancing software re-use, transportability, andinteroperability. The TCP architecture is based on existing standards,distributed networking, distributed and open system computing, andpacket technology. The first TCP application is planned for the 94 SDIOSPAS 3 mission. The architecture enhances rapid tailoring of functionsthereby reducing costs and schedules developed for individual space-craft missions. Author (revised)

N95-14282*# Texas Univ., Austin, TX. Center for Space Research.PRECISION ORBIT DETERMINATION OF ALTIMETRICSATELLITESC. K. SHUM, JOHN C. RIES, and BYRON D. TAPLEY In NASA.Goddard Space Right Center, Satellite Laser Ranging in the 1990s:Report of the 1994 Belmont Workshop p 65-70 Nov. 1994Avail: CASI HC A02/MF A02

The ability to determine accurate global sea level variations isimportant to both detection and understanding of changes in climatepatterns. Sea level variability occurs over a wide spectrum of temporaland spatial scales, and precise global measurements are only recentlypossible with the advent of spacebome satellite radar altimetry mis-sions. One of the inherent requirements for accurate determination ofabsolute sea surface topography is that the altimetric satellite orbits becomputed with sub-decimeter accuracy within a well defined terrestrialreference frame. SLR tracking in support of precision orbit determina-tion of altimetric satellites is significant. Recent examples are the useof SLR as the primary tracking systems for TOPEX/Poseidon and forERS-1 precision orbit determination. The current radial orbit accuracyfor TOPEX/Poseidon is estimated to be around 3-4 cm, with geographi-cally correlated orbit errors around 2 cm. The significance of the SLRtracking system is its ability to allow altimetric satellites to obtainabsolute sea level measurements and thereby provide a link to otheraltimetry measurement systems for long-term sea level studies. SLRtracking allows the production of precise orbits which are well centeredin an accurate terrestrial reference frame. With proper calibration of theradar altimeter, these precise orbits, along with the altimeter measure-ments, provide long term absolute sea level measurements. The U.S.Navy's Geosat mission is equipped with only Doppler beacons andlacks laser retroreflectors. However, its orbits, and even the Geosatorbits computed using the available full 40-station Tranet trackingnetwork, yield orbits with significant north-south shifts with respect tothe IERS terrestrial reference frame. The resulting Geosat sea surfacetopography will be tilted accordingly, making interpretation of long-termsea level variability studies difficult Author (revised)

N95-14639'# Auburn Univ., AL Space Power InstHYPERVELOCITY IMPACT TEST FACILITY: A GUN FORHIRECALVIN R. JOHNSON, M. F. ROSE, D. C. HILL, S. BEST, T.CHALOUPKA, G. CRAWFORD, M. CRUMPLER, and B. STEPHENSIn Huntsville Association of Technical Societies, TABES 1994: 10thAnnual Technical and Business Exhibition and Symposium 7p 1994(Contract(s)/Grant(s): NAG 1-1329; DNA001-90-C-0127)(TABES PAPER 94-605) Avail: CASI HC A02/MF A04

An affordable technique has been developed to duplicate thetypes of impacts observed on spacecraft, including the Shuttle, by useof a certified Hypervelocity Impact Facility (HIF) which propels particu-

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lates using capacitor driven electric gun techniques. The fully opera-tional facility provides a flux of particles in the 10-100 micron diameterrange with a velocity distribution covering the space debris andinterplanetary dust particle environment. HIF measurements of particlesize, composition, impact angle and velocity distribution indicate thatsuch parameters can be controlled in a specified, tailored test designedfor or by the user. Unique diagnostics enable researchers to fullydescribe the impact for evaluating the targets' under full power or load.Users regularly evaluate space hardware, including solar cells, coat-ings, and materials, exposing selected portions of space-qualifieditems to a wide range of impact events and environmental conditions.Benefits include corroboration of data obtained from impact events,flight simulation of designs, accelerated aging of systems, and devel-opment of manufacturing techniques. Author (revised)

N95-14653*# National Aeronautics and Space Administration. MarshallSpace Right Center, Huntsville, AL.BUILDING COMPLEX SIMULATIONS RAPIDLY USINGMATRIX(X): THE SPACE STATION REDESIGNC. K. CARRINGTON In Huntsville Association of TechnicalSocieties, TABES 1994:10th Annual Technical and Business Exhi-bition and Symposium 7 p 1994(TABES PAPER 94-632) Avail: CASI HC A02/MF A04

MSFC's quick response to the Space Station redesign effort lastyear required the development of a computer simulation to model theattitude and station-keeping dynamics of a complex body with rotatingsolar arrays in orbit around the Earth. The simulation was written usinga rapid-prototyping graphical simulation and design tool called MATRIX(x)and provided the capability to quickly remodel complex configurationchanges by icon manipulation using a mouse. The simulation deter-mines time-dependent Inertia properties, and models forces and torquesfrom gravity-gradient, solar radiation, and aerodynamic disturbances.Surface models are easily built from a selection of beams, plates,tetrahedrons, and cylinders. An optimization scheme was written todetermine the torque equilibrium attitudes that balance gravity-gradientand aerodynamic torques over an orbit, and propellant-usage esti-mates were determined. The simulation has been adapted to model theattitude dynamics for small spacecraft Author

N95-14850 Naval Postgraduate School, Monterey, CA.EVALUATION OF ENERGY-SINK STABILITY CRITERIA FORDUAL-SPIN SPACECRAFT M.S. ThesisVINCENT M. ORTIZ Jun. 1994 152p Limited Reprodutibility:More than 20% of this document may be affected by microfiche quality(AD-A283228) Avail: Issuing Activity (Defense Technical InformationCenter (DTIC))

The nutational stability of a dual-spin, quasi-rigid, axisymmetricspacecraft containing a driven rotor is analyzed. The purpose is toexamine a revised energy-sink stability theory that property accountsfor the energy contribution of the motor. An inconsistency in thedevelopment disproves the existing energy-sink theory's assumptionthat the motor of the system contributes exactly enough energy to offsetthe frictional losses between the rotor and the platform. Using theconcept of core energy, the revised stability criteria for a dual-spin,quasi-rigid, axisymmetric spacecraft containing a driven rotor is de-rived. An expression for nutation angle as a function of core energy overtime is then determined. Numerical simulations are used to verify therevised energy-sink stability theory. The dual-spin, quasi-rigid,axisymmetric system presented by D. L Mingori was chosen for thesimulation. Equations for angular momentum and total energy werenecessary to validate the numerical simulation and confirm aspects ofthe revised energy-sink stability theory. These equations are derivedfrom the first principles of dynamics and are included in the analysis. Anexplicit relationship for core energy as a function of time does not existVarious models postulating core energy are presented and analyzed.The numerical simulations of the computed nutation angles as afunction of the postulated core energy compare well with the actual

nutation angles of the system to confirm the revised energy-sinkstability criteria. DTIC

N95-14363* Lockheed Aeronautical Systems Co., Marietta, GA.THERMALLY STABLE ORGANIC POLYMERS InterimTechnical Report, 1 Feb. 1993-15 May 1994R. H. BOSCHAN, MATTHEW MARROCCO, and JAMES MCGRATH1 Jun. 1994 19 p(Contract(s)/Grant(s): DAAL03-92-C-0021)(AD-A281380; LG94ER0099; ARO-30357.1 -MS) Avail: CASI HC A03/MFA01

Environmentally durable high temperature polymer matrix resinsare critical in the design of near-term high performance supersonicaircraft. Currently available 6F based polymers are thermally stable, butare expensive and difficult to process into void-free laminates. 3Fpolymers have demonstrated equivalent thermal stability andprocessability, but are amenable to more facile, environmentally ac-ceptable synthetic procedures. In the current program, semi-interpen-etrating polymer network (SIPN) blends of ethynyl and phenylethynylterminated 3F polymers have been formulated and evaluated. A seriesof test panels were fabricated, using dielectric monitoring procedures,from a 1:1 3F SIPN blend of phthalic anhydride terminated thermoplas-tic 3F oligomer with a phenylethynyl terminated thermosetting 3Foligomer. Solution prepregging techniques were used to prepare IM7fiber prepreg tape. The void content of these laminates was somewhathigher than acceptable, probably due to the high melt viscosity.

DTIC

N95-14409* Aeronautical Research Labs., Melbourne (Australia).RESIDUAL STRENGTH OF COMPOSITES WITH MULTIPLEIMPACT DAMAGEJ. J. PAUL, S. C. GALEA, and R. JONES Mar. 1994 27 p(AD-A284230; ARL-RR-13; DODA-AR-008-383) Avail: CASI HC A03/MFA01

In recent years the issue of damage interaction, with particularemphasis on multi-site damage, has been of concern to the aircraftindustry. Whilst most attention focused on fuselage lap joints, relatedproblems occur in composite structures which are subjected to multipleimpact damage. This paper reveals that, for the cases of multiple impactdamage in composite structures investigated, little interaction betweendamaged regions was observed. Thus a simple repair methodology,previously developed for single impact damaged structures, wasapplied. This methodology was verified via a coupon test program andan experimental evaluation of two damaged F/A-18 horizontal stabilators.

DTIC

N95-14465*# Lehigh Univ., Bethlehem, PA. Dept. of MechanicalEngineering and Mechanics.CORROSION AND CORROSION FATIGUE OF AIRFRAMEALUMINUM ALLOYSG. S. CHEN, M. GAO, D. G. HARLOW, and R. P. WEI In NASA.Langley Research Center, FAA/NASA International Symposium onAdvanced Structural Integrity Methods for Airframe Durability andDamage Tolerance p 157-173 Sep. 1994(Contract(s)/Grant(s): FAA-92-G-0006)Avail: CASI HC A03/MF A04

Localized corrosion and corrosion fatigue crack nucleation andgrowth are recognized as degradation mechanisms that effect thedurability and integrity of commercial transport aircraft. Mechanicallybased understanding is needed to aid the development of effectivemethodologies for assessing durability and integrity of airframe compo-nents. As a part of the methodology development, experiments onpitting corrosion, and on corrosion fatigue crack nucleation and earlygrowth from these pits were conducted. Pitting was found to beassociated with constituent particles in the alloys and pit growth ofteninvolved coalescence of individual particle-nucleated pits, both laterallyand in depth. Fatigue cracks typically nucleated from one of the largerpits that formed by a cluster of particles. The size of pit at which fatiguecrack nucleates is a function of stress level and fatigue loading

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frequency. The experimental results are summarized, and their impli-cations on sen/ice performance and life prediction are discussed.

Author

N95-14482*# Utah Univ., Salt Lake City, UT.THE EFFECTS OF PITTING ON FATIGUE CRACKNUCLEATION IN 7075-T6 ALUMINUM ALLOYLI MA and DAVID W. HOEPPNER In NASA. Langley ResearchCenter, FAA/NASA International Symposium on Advanced Struc-tural Integrity Methods for Airframe Durability and Damage Toler-ance p 425-440 Sep. 1994 Sponsored by Boeing CommercialAirplane Co.Avail: CASI HC A03/MF A04

A high-strength aluminum alloy, 7075-T6, was studied to quanti-tatively evaluate chemical pitting effects of its corrosion fatigue life. Thestudy focused on pit nucleation, pit growth, and fatigue crack nude-aton. Pitting corrosion fatigue experiments were conducted in 3.5percent NaCI aqueous solution under constant amplitude sinusoidalloading at two frequencies, 5 and 20 Hz. Smooth and unnotchedspecimens were used in this investigation. A video recording systemwas developed to allow in situ observation of the surface changes of thespecimens during testing. The results indicated that pitting corrosionconsiderably reduces the fatigue strength by accelerating fatigue cracknucleation. A metallographic examination was conducted on the speci-mens to evaluate the nature of corrosion pits. First, the actual shapesof the corrosion pits were evaluated by cross-sectioning the pits.Secondly, the relation between corrosion pits and microstructure wasalso investigated. Finally, the possibility of another corrosion mecha-nism that might be involved in pitting was explored in this investigation.The fractography of the tested specimens showed that comer corrosionpits were responsible for fatigue crack nucleation in the material due tothe associated stress concentration. The pits exhibited variance ofmorphology. Fatigue life for the experimental conditions appeared to bestrongly dependent on pitting kinetics and the crack nucleation stage.

Author

N95-14920*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.THE CHARACTERIZATION OF WIDESPREAD FATIGUEDAMAGE IN FUSELAGE STRUCTUREROBERT S. PIASCIK, SCOTT A. WILLARD, and MATTHEW MILLERSep. 1994 16 p(Contract(s)/Grant(s): RTOP 538-02-10-01)(NASA-TM-109142; NAS 1.15:109142} Avail: CASI HC A03/MFA01

The characteristics of widespread fatigue damage (WSFD) infuselage riveted structure were established by detailed nondestructiveand destructive examinations of fatigue damage contained in a full sizefuselage test article. The objectives of this were to establish anexperimental data base for validating emerging WSFD analyticalprediction methodology and to identify first order effects that contributeto fatigue crack initiation and growth. Detailed examinations wereperformed on a test panel containing four bays of a riveted lap splicejoint. The panel was removed from a full scale fuselage test article afterreceiving 60,000 full pressurization cycles. The results of in situexaminations document the progression of fuselage skin fatigue crackgrowth through crack linkup. Detailed tear down examinations andfractography of the lap splice joint region revealed fatigue crackinitiation sites, crack morphology, and crack linkup geometry. From thislarge data base, distributions of crack size and locations are presentedand discussions of operative damage mechanisms are offered.

Author

N95-15415 Pratt and Whitney Aircraft, West Palm Beach, FL. Gov-ernment Engines and Space Propulsion.FATIGUE IN SINGLE CRYSTAL NICKEL SUPERALLOYSD. P. DELUCA and CHARLES ANNIS 15 Oct. 1993 30 p LimitedReprodutibility: More than 20% of this document may be affected bymicrofiche quality(Contract(s)/Grant(s): N00014-91-C-0124)(AD-A282917; FR2198-20) Avail: CASI HC A03

This program investigates the seemingly unusual behavior ofsingle crystal airfoil materials. The fatigue initiation processes in singlecrystal (SC) materials are significantly more complicated and involvedthan fatigue initiation and subsequent behavior of a (single) macrocrackin conventional, isotropic, materials. To understand these differencesis the major goal of this project DTIC

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ENGINEERING

Includes engineering (general); communications; electronics and elec-trical engineering; fluid mechanics and heat transfer; instrumentationand photography; lasers and masers; mechanical engineering; qualityassurance and reliability; and structural mechanics.

A95-61720DISCRETE SHAPE SENSITIVITY EQUATIONS FORAERODYNAMIC PROBLEMSGENE J. W. HOU Old Dominion Univ., Norfolk, VA, ARTHUR C.TAYLOR, and VAMSHIM. KORIVI International Journal for NumericalMethods in Eng ineering (ISSN 0029-5981) vol. 37, no. 13 July 15,1994 p. 2251-2266 refs(BTN-94-EIX94451393721) Copyright

This paper presents a part of such an effort to develop a sensitivityanalysis methodology that enables the sensitivity equations to beimplemented into existing CFD codes with minimal code modification.The methodology is based upon a pre-elimination procedure whichaccounts for consistently linearized boundary conditions. Formulationsof both the direct differentiation and the adjoint variable methods will bepresented in the paper. Author (revised by El)

A95-61795NEW STRATEGY COMBINING BACKWARD INFERENCEWITH FORWARD INFERENCE IN MONITORING ANDDIAGNOSING TECHNIQUES FOR HYDRODYNAMICBEARING-ROTOR SYSTEMSYOU-YUN ZHANG Xi'an Jiaotong Univ., Xian (China) and YOU-BAI XIE Wear (ISSN 0043-1648) vol. 173, no. 1-2 April 1994p. 31-37 refs(BTN-94-EIX94331336949) Copyright

A new strategy for the techniques of monitoring and diagnosinghydrodynamic bearing-rotor systems is recommended in this paper.The strategy integrates the traditional technique of spectrum andstatistics analysis (backward inference) with the application of knowl-edge and information of rotor-bearing dynamics and tribology (forwardinference). This strategy has been used to develop a monitoring anddiagnosing system for rotating machinery and examples of the suc-cessful application of the system are given. Author (El)

A95-62265ON CALCULATED MODELS FOR IMPELLERS OFCENTRIFUGAL COMPRESSORSS. K. CHERNIKOV KFTI, Kazan (Russia), S. V. KULAGIN, and E.V. KASUMOV Izvestiya VUZ: AviatsionnayaTekhnika (ISSN 0579-2975) no. 4 October-December 1993 p. 33-38 In RUSSIANrefs(BTN-94-EIX94461407947) Copyright

A variety of calculated schemes for impellers of centrifugalcompressors has been analysed. It has been shown that the assess-ment of the stress-deformed state of the impeller leads to significanterrors, if the mutual effects of its elements are ignored. To calculate theimpeller of the compressor, the finite element method was used. Inorder to simplify the problem, a concept of cyclic symmetry wasintroduced. El

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A95-62267HEAT TRANSFER IN THE FLOW-THROUGH PART OFAXIAL COMPRESSORSV. I. LOKAJ KGTU, Kazan (Russia), A. G. KARIMOVA, and L. B.SHIGIN Izvestiya VUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975)no. 4 October-December 1993 p. 43-47 In RUSSIAN refs(BTN-94-EIX94461407949) Copyright

If no valid data on the temperature state of heat stressed units areavailable, it is impossible to assess the strength reserves of pieces.Also, it is impossible, in this case, to develop efficient cooling systemsand systems for controlling radial clearances. That's why the paperpresents experimental results, showing heat transfer on the surface ofthe blade profile and on the end surfaces of the interblade channel offlat compressor lattices. Dependences, considering the effect of geo-metric and regime parameters on heat transfer, have been obtained.

El

A95-62625INVESTIGATION OF HEAT TRANSFER IN A ROTATINGRING GAP WITH THE AXIAL FLOW OF A COOLANTDURING THE ROTATION OF THE CENTRAL SHAFTN. N. SALOV SPI, Sevastopol, (Ukraine) Izvestiya VUZ:Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4 October-Decem-ber 1993 p. 51-54 In RUSSIAN refs(BTN-94-EIX94461407951) Copyright

Heat transfer of a cylindrical surface inside a rotating ring gap ofthe rotor of a turbine rocket engine has been experimentally studied.The rotor is of the disc-drum type. The studies were conducted with theaxial flow of a coolant and with variations of the rotational speed andchanges in the direction of rotation of the central shaft. The test resultshave been generalized on the basis of the similarity theory. Test dataon the opposite rotation of the shaft and gap are in good agreement withdependences obtained. El

A95-62627MECHANISM AND TECHNOLOGICAL PARTICULARFEATURES OF THERMOMAGNETIC HARDENINGS. M. BOROVSKIJ UGATU, Ufa (Russia) and V. S. MUKHINIzvestiya VUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4October-December 1993 p. 60-63 In RUSSIAN(BTN-94-EIX94461407953) Copyright

The particular features of mechanism associated with piecehardening of gas-turbine engines are analyzed. This mechanism isconnected with the change of conditions for phase equilibrium andkinetics of transformations. It is important to estimate the nature of theformation of new ferromagnetic centers at phase transitions, whenpermanent, pulsed, or periodic magnetic fields act. Two factors shouldbe taken into account: the power effect of the magnetic field and theincrease of 'magnetic segregation1 of a source nonferromagneticmatrix. El

N95-13665*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.COMPUTATIONAL ANALYSIS IN SUPPORT OF THE SSTOFLOWPATH TESTBEVERLY S. DUNCAN (NYMA, Inc., Brook Park, OH.) andCHARLES J. TREFNY Oct. 1994 24 p(Contract(s)/Grant(s): NAS3-27186; RTOP 505-70-59)(NASA-TM-106757; E-9179; NAS1.15:106757) Avail: CASIHC A03/MFA01

A synergistic approach of combining computational methods andexperimental measurements is used in the analysis of a hypersonicinlet. There are four major focal points within this study which examinethe boundary layer growth on a compression ramp upstream of the cowllip of a scramjet inlet. Initially, the boundary layer growth on the NASPConcept Demonstrator Engine (CDE) is examined. The follow-up studydetermines the optimum diverter height required by the SSTO Rowpathtest to best duplicate the CDE results. These flow field computations are

then compared to the experimental measurements and the massaverage Mach number is determined for this inlet Author

N95-13892*# National Aeronautics and Space Administration. HughL. Dryden Right Research Facility, Edwards, CA.NUMERICAL MODELING OF A CRYOGENIC FLUID WITHINA FUEL TANKDONALD S. GREER Washington Oct. 1994 15 p Presentedat the Second Thermal Structures Conference, Charlottesville, VA, 18-21 Oct. 1994(Contract(sVGrant(s): RTOP 505-70-63)(NASA-TM-4651;H-2029;NAS 1.15:4651) Copyright Avail:CASINGA03/MF A01

The computational method developed to study the cryogenic fluidcharacteristics inside a fuel tank in a hypersonic aircraft is presented.The model simulates a rapid draining of the tank by modeling the ullagevapor and the cryogenic liquid with a moving interface. A mathematicaltransformation was developed and applied to the Navier-Stokes equa-tions to account for the moving interface. The formulation of thenumerical method is a transient hybrid explicit-implicit technique wherethe pressure term in the momentum equations is approximated to firstorder in time by combining the continuity equation with an ideal equationof state. Author

N95-14127* Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Propulsion and Energetics Panel.TURBOMACHINERY DESIGN USING CFD [LA CONCEPTIONDES TURBOMACHINES PAR L'AERODYNAMIQUENUMERIQUE]May 1994 251 p Lecture series held in OH, 24-25 May 1994, inAnkara, Turkey, 6-7 Jun. 1994, and in Munich, Germany, 9-10 Jun.1994 Original contains color illustrations(AGARD-LS-195; ISBN-92-835-0749-5) Copyright Avail: CASI HCA12/MFA03

Computational Ruid Dynamics (CFD) has become a major designtool for designers of turbomachinery. The progress in this area is fast,and the use of 3-D methods is becoming increasingly applicable to thedesign process. This Lecture Series will include: (1) Computationalmethods for preliminary design and geometry definitions; (2) Methodsfor computing through-flows, blade-to-blade flows and geometry gen-eration; (3) Optimization strategies; (4) Designing in three dimensions;(5) Code validation, mesh influence on solution accuracy; (6) Turbu-lence and transition modelling; (7) Comparison of time averaged flowsolvers and 3-D unsteady CFD codes; (8) Industrial use of CFD and thepoints of view of the designers. For individual titles, see N95-14128through N95-14136.

N95-14128* Sulzer Innotec A.G., Winterthur (Switzerland). FluidDynamics Lab.COMPUTATIONAL METHODS FOR PRELIMINARY DESIGNAND GEOMETRY DEFINITION IN TURBOMACHINERYM. V. CASEY In AGARD, Turbomachinery Design Using CFD22 p May 1994Copyright Avail: CASI HC A03/MF A03

A review of the turbomachinery preliminary design process isgiven with particular emphasis on axial and radial compressors. Thereview covers the selection of machine type, mean-line analysis andcorrelations, stagestacking calculations and the use of design chartsand optimization techniques to find optimum values for design param-eters. A comparison is made between the most successful correlationsfor endwall losses in axial compressors to highlight the differentapproaches that are possible. The preliminary design process providesan initial definition of the skeletal geometry of the blading and theannulus of the turbomachine. Turbomachinery design systems are thenbased on design by analysis, whereby the blading is assessed usingCFD codes and is rteratively refined. A numerically based parametricblade geometry definition system makes the use of CFD considerablymore effective. Examples of modem turbomachinery geometry defini-tion methods involving Bezier surfaces and B-spfines are described.

Author

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N95-14129* General Electric Co., Cincinnati, OH. Aircraft EnginesDiv.ELEMENTS OF A MODERN TURBOMACHINERY DESIGNSYSTEMIAN K. JENNIONS In AGARD, Turbomachinery Design Using CFD22 p May 1994Copyright Avail: CASI HC A03/MF A03

The aerodynamic design system at GE Aircraft Engines (GEAE)consists of many parts: throughflow, secondary flow, geometry genera-tors, blade-to-blade and fully three-dimensional (3D) analysis. Thispaper describes each of these elements and discusses optimizationand computer architecture issues. Emphasis is placed on those areasin which the company is thought to have special capability. Author

N95-141300 Cambridge Univ., Cambridge (England). Dept. ofEngineering.DESIGNING IN THREE DIMENSIONSJ. D. DENTON In AGARD, Turbomachinery Design Using CFD14 p May 1994Copyright Avail: CASI HC A03/MF A03

This lecture advocates the direct use of three-dimensional flowcalculations for turbomachinery design. The limitations of the usualquasi-three dimensional approach are discussed and it is shown thatfully 3D calculations overcome the modelling limitations inherent inthem. Fully 3D calculations also avoid the need to iterate betweenthroughflow and blade to blade calculations. This leads to fewer routineoperations (e.g. data transfers) being needed during the design processand hence more efficient use of the designer's time. With a flexiblegeometrical package, able to generate blade sections and transfer theirgeometry directly to a 3D data set, changes of stage geometry can bemade in minutes. An outline of such a package is given. Modem 3Dcalculation methods, Ref(11), enable complete stage solutions, withadequate accuracy for design purposes, to be obtained in the order ofI hour on a workstation. Hence several design iterations per day can beeasily be performed for a single stage of a machine. An exampleused to design a very high pressure ratio (3:1) axial fan is given anddiscussed. Author (revised)

N95-14132# Pratt and Whitney Aircraft, East Hartford, CT.UNSTEADY FLOWS IN TURBINES: IMPACT ON DESIGNPROCEDUREO. P. SHARMA, R. H. Nl, and S. TANRIKUT In AGARD,Turbomachinery Design Using CFD 27 p May 1994 Originalcontains color illustrationsCopyright Avail: CASI HC A03/MF A03

The impact of recent research activities in unsteady flows and flowsimulation methods used in the turbine design process are outlined.Results from a number of experimental investigations are described toquantify the effect of unsteadiness on the time-averaged flows inturbines. Results from numerical simulations, obtained by using 3-Dunsteady Computational Ruid Dynamics (CFD) codes, are also shownto indicate that some of the unsteady flow features can be fairlyaccurately predicted. An overall discussion is presented to distinguishflow parameters that can be modeled with existing steady CFD codes,from those that require unsteady codes. Author

N95-14133* Sulzer Innotec A.G., Wmterthur (Switzerland). RuidDynamics Lab.THE INDUSTRIAL USE OF CFD IN THE DESIGN OFTURBOMACHINERYM. V. CASEY In AGARD, Turbomachinery Design Using CFD24 p May 1994Copyright Avail: CASI HC A03/MF A03

The numerical simulation of the internal flowfield now plays amajor role in all turbomachinery aerodynamic designs, from aero-engines to hydraulic turbines and pumps. With the help of CFD codesan experienced designer is able to produce more adventurous, betterengineered and more clearly understood designs more rapidly at lowercost. This paper reviews the use of CFD as an engineering tool in

modem turbomachinery design from the standpoint of aturbomachinerydesigner. Particular attention is given to the current limitations withregard to performance prediction. The necessary engineering criteriaused by turbomachinery designers to overcome these limitations andto assess the weak points of their designs using CFD flowfield compu-tations are discussed. Examples of the application of these generalaerodynamic design criteria to most classes of turbomachines using avariety of different CFD codes are given. Author

N95-14134# Societe Nationals d'Etude et de Construction de Moteursd'Aviation, Moissy-Cramayel (France). Div. Recherches et EtudesAvancees.NEW METHODS, NEW METHODOLOGY: ADVANCED CFDIN THE SNECMA TURBOMACHINERY DESIGN PROCESSCHRISTOPHE VUILLEZ and BERTRAND PETOT In AGARD,Turbomachinery Design Using CFD 26 p May 1994 Originalcontains color illustrationsCopyright Avail: CASI HC A03/MF A03

CFD tools represent a significant source of improvements in thedesign process of turbomachinery components, leading to higherperformances, cost and cycle savings as well as lower associated risks.Such methods are the backbone of compressor and turbine designmethodologies at Snecma. In the 80's, the use of 3D Euler solvers wasa key factor in designing fan blades with very high performance level.Counter rotating high speed propellers designed with this methodologyreached measured performances very dose to their ambitious objec-tive from the first test series. In the late 80's and the beginning of the90's, new, more powerful methods were rapidly developed and are nowcommonly used in the design process: a quasi-3D, compressible,transonic inverse method; quasi-3D and 3D Navier-Stokes solvers; 3Dunsteady Euler solvers. As an example, several hundred 3D Navier-Stokes computations are run yearly for the design of low and highpressure compressor and turbine blades. In addition to their modellingcapabilities, the efficient use of such methods in the design processcomes from their dose integration in the global methodology and froman adequate exploitation environment. Their validation, their calibra-tion, and the correlations between different levels of modelling are ofcritical importance to an actual improvement in design know-how. Theintegration of different methods in the design process is described.Several examples of application illustrate their practical utilization.Comparisons between computational results and test results showtheir capabilities as well as their present limitations. The prospectslinked to new developments currently under way are discussed.

Author

N95-14135* General Electric Co., Cincinnati, OH. Aircraft EnginesDiv.THE ROLE OF CFD IN THE DESIGN PROCESSIAN K. JENNIONS In AGARD, Turbomachinery Design Using CFD34 p May 1994Copyright Avail: CASI HC A03/MF A03

Over the last decade the role played by CFD codes inturbomachinery design has changed remarkably. While convergence/stability or even the existence of unique solutions was discussedfervently ten years ago, CFD codes now form a valuable part of anoverall integrated design system and have caused us to re-think muchof what we do. The geometric and physical complexities addressedhave also evolved, as have the number of software houses competingwith in-house developers to provide solutions to daily design problems.This paper reviews how GE Aircraft Engines (GEAE) uses CFD in theturbomachinery design process and examines many of the issuesfaced in successful code implementation. Author

N95-14136* Technische Univ., Munich (Germany).AERO DESIGN OF TURBOMACHINERY COMPONENTS:CFD IN COMPLEX SYSTEMSKLAUS BROICHHAUSEN In AGARD, Turbomachinery DesignUsing CFD 23 p May 1994Copyright Avail: CASI HC A03/MF A03

The importance of CFD in the design of turbocomponents is no

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longer a matter of discussion. Since the fundamental publications of Wuand the first successful attempts to determine the potential 2D flow inblade rows the position of computational fluid dynamics in the designof jet-engine turbocomponents has increased continuously. This mainlyhas been driven by the two factors lime' and 'cost'. As a result thedesign engineer of today can rely on a mature set of numericalapproaches for the aerodynamic optimization of turbomachines. Thisdesign system is structured differently in the specific companies.Generally, however, an inverse correlation between the complexity ofthe problem and the complexity of the numerical approach can beobserved: The most complex problems rely on relatively simple codeswith a big portion of empiricism and vice versa. An overview of thedesign problems and the application of computational methods is given.

Author

N95-14139*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.SPIRAL MICROSTRIP ANTENNA WITH RESISTANCE PatentApplicationDAVID G. SHIVELY, inventor (to NASA) 28 Jun. 1994 20 p(NASA-CASE-LAR-15088-1; NAS 1.71 :LAR-15088-1; US-PATENT-APPL-SN-269268) Avail: CASI HC A03/MF A01

The present invention relates to microstrip antennas, and moreparticularly to wide bandwidth spiral antennas with resistive loading. Aspiral microstrip antenna having resistor element embedded in each ofthe spiral arms is provided. The antenna is constructed using aconductive back plane as a base. The back plane supports a dielectricslab having a thickness between one-sixteenth and one-quarter of aninch. A square spiral, having either two or four arms, is attached to thedielectric slab. Each arm of the spiral has resistor elements therebydissipating an excess energy not already emitted through radiation. Theentire configuration provides a thin, flat, high gain, wide bandwidthantenna which requires no underlying cavity. The configuration allowsthe antenna to be mounted conformably on an aircraft surface.

NASA

N95-14183** National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.BASE PASSIVE POROSITY FOR DRAG REDUCTION PatentApplicationSTEVEN X. S. BAUER, inventor (to NASA) and RICHARD M. WOOD,inventor (to NASA) 19 Oct. 1994 13 p(NASA-CASE-LAR-15246-1; NAS 1.71 :LAR-15246-1; US-PATENT-APPL-SN-327061) Avail: CASI HC A03/MF A01

A device for controlling drag on a ground vehicle is presented. Thedevice consists of a porous skin mounted on the trailing surface of theground vehicle. The porous skin may be separated from the vehiclesurface by a distance of at least two times the boundary layer formedon the surface. Alternately, the trailing surface of the ground vehiclemay be porous. The device minimizes the strength of the separation inthe base and wake regions of the ground vehicle, thus reducing drag.

NASA

N95-14201# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France). Fluid Dynamics Panel.A SELECTION OF EXPERIMENTAL TEST CASES FOR THEVALIDATION OF CFD CODES, VOLUME 1 [RECUEIL DECAS D'ESSAI EXPERIMENTAUX POUR LA VALIDATIONDES CODES DE L'AERODYNAMIQUE NUMERIQUE]Aug. 1994 152 p See also 95N-17846 and diskette supplementAGARD-AR-303-Suppl(AGARD-AR-303-VOL-1; ISBN-92-836-1002-4) Copyright Avail: CASIHC A08/MF A02

This report presents the results of a study by Working Group 14of the AGARD Ruid Dynamics Panel. This group was formed toestablish an accessible, detailed experimental data base for thevalidation of Computational Ruid Dynamics (CFD) codes. The thirtynine test cases that are documented cover the subsonic, transonic, andsupersonic flow regimes and five classes of geometries. Included in thefive classes of geometries are: two dimensional airfoils; three dimen-

sional wings, designed for predominantly attached flow conditions;slender bodies, typical of missile type configurations; delta wings,characterized by a conical type of vortex flow; and complex configura-tions, either in a geometrical sense or because of complicated flowinteractions. The report is presented in two volumes. Volume 1 providesa review of the theoretical and experimental requirements, a generalintroduction and summary of the test cases, and recommendations forthe future. Volume 2 contains detailed information on the test cases.The relevant data of all test cases has been compiled on floppy disks,which can be obtained through National Centers. Author

N95-14299*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.HYPERSONIC ENGINE LEADING EDGE EXPERIMENTS IN AHIGH HEAT FLUX, SUPERSONIC FLOW ENVIRONMENTHERBERT J. GLADDEN and MATTHEW E. MELIS Oct. 199413 p Presented at the Winter Annual Meeting, Chicago, IL, 6-11Nov. 1994; sponsored by the ASME Original contains colorillustrations(Contract(s)/Grant{s): RTOP 505-62-52)(NASA-TM-106742; E-9152; NAS 1.15:106742) Avail: CASI HC A03/MF A01; 2 functional color pages

A major concern in advancing the state-of-the-art technologies forhypersonic vehicles is the development of an aeropropulsion systemcapable of withstanding the sustained high thermal loads expectedduring hypersonic flight. Three aerothermal load related concerns arethe boundary layer transition from laminar to turbulent flow, articulatingpanel seals in high temperature environments, and strut (or cowl)leading edges with shock-on-shock interactions. A multidisciplinaryapproach is required to address these technical concerns. A hydrogen/oxygen rocket engine heat source has been developed at the NASALewis Research Center as one element in a series of facilities atnational laboratories designed to experimentally evaluate the heattransfer and structural response of the strut (or cowl) leading edge. Arecent experimental program conducted in this facility is discussed andrelated to cooling technology capability. The specific objective of theexperiment discussed is to evaluate the erosion and oxidation charac-teristics of a coating on a cowl leading edge (or strut leading edge) ina supersonic, high heat flux environment. Heat transfer analyses of asimilar leading edge concept cooled with gaseous hydrogen is includedto demonstrate the complexity of the problem resulting from plasticdeformation of the structures. Macro-photographic data from a coatedleading edge model show progressive degradation over several ther-mal cycles at aerothermal conditions representative of high Machnumber flight. Author

N95-14351# Air Force Inst. of Tech., Wright-Patterson AFB, OH.EFFECT OF SURFACE ROUGHNESS ON LOCAL FILMCOOLING EFFECTIVENESS AND HEAT TRANSFERCOEFFICIENTS Ph.D. ThesisDOUGLAS N. BARLOW Aug. 1994 297 p(AD-A283854; AFIT/CI/CIA-94-033D) Avail: CASI HC A13/MF A03

In high temperature gas turbine engines, the life cycle of the hotsection is extremely dependent on accurate design prediction ofcomponent temperature distribution. Particular attention must be paidto the film cooling performance of the first stage turbine stator vaneswhere the highest heat loads are encountered. Recent investigationshave determined during operation the smooth surface of high pressureturbine vanes become rough due to corrosion, oxidation and paniculateimpact. A transient experimental method has been developed to obtainboth local heat transfer and cooling effectiveness information down-stream of a row of film cooling holes on a rough flat plate. Thisinvestigation provides information on the effects of roughness on filmcooling heat transfer for a Reynolds number and dimensionless bound-ary layer momentum thickness which match conditions applicable tothe pressure side of the first stage turbine vane of the Pratt and Whit-ney F-100-PW229 engine. Data for film cooling on rough surfaces areextremely limited in the literature. However, comparison with theavailable data is made. DTIC

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N95-14405 Naval Air Warfare Center, Patuxent River, MD. AircraftDiv.COMPOSITE WAVEFORM GENERATION FOR EMP ANDLIGHTNING DIRECT-DRIVE TESTINGC. M. GRAVES, JR. (United International Engineering, Inc., Waldorf,MD.) and S. J. FRAZIER 1994 110p Limited Reproduribility:More than 20% of this document may be affected by microfiche quality(AD-A284159) Avail: Issuing Activity (Defense Technical InformationCenter (DTIQ)

An integral portion of electromagnetic transient (EMT) testing isthe survivability assessment. The ultimate goal of the survivabilityassessment is to establish the margin of survivability for the systemunder test The margin of survivability is the ratio of system strength toanticipated stress. Within the EMP (electromagnetic pulses) commu-nity, the anticipated stress reflects the responses induced by thesimulated EMP environment and extrapolated to the Bell Laboratory'sGeneralized High-Altitude EMP Waveform; the system strength re-flects the stress level required to upset or damage the system undertest. One key approach to determine system strength is direct-drivetesting. Direct-drive testing involves re-injecting amplified versions ofthe maximum response waveform at each test point until an operationalupset occurs or an accepted drive level is attained. The maximumresponse waveforms are acquired by measuring defined test points forvarious simulated EMP environments with the system under test invarious orientations and operational configurations. DTIC

N95-14453*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.FAA/NASA INTERNATIONAL SYMPOSIUM ON ADVANCEDSTRUCTURAL INTEGRITY METHODS FOR AIRFRAMEDURABILITY AND DAMAGE TOLERANCECHARLES E. HARRIS, ed. Sep. 1994 506 p Symposium heldin Hampton, VA, 4-6 May 1994 Sponsored by NASA, Washington andFAA(Contract(s)/Grant(S): RTOP 538-02-10-01)(NASA-CP-3274-PT-1; L-17432-PT-1; MAS 1.55:3274-PT-1) Avail:CASI HC A22/MF A04

International technical experts in durability and damage toleranceof metallic airframe structures were assembled to present and discussrecent research findings and the development of advanced design andanalysis methods, structural concepts, and advanced materials. Thesymposium focused on the dissemination of new knowledge and thepeer-review of progress on the development of advanced methodolo-gies. Papers were presented on: structural concepts for enhanceddurability, damage tolerance, and maintainability; new metallic alloysand processing technology; fatigue crack initiation and small crackeffects; fatigue crack growth models; fracture mechanics failure, criteriafor ductile materials; structural mechanics methodology for residualstrength and life prediction; development of flight load spectra fordesign and testing; and advanced approaches to resist corrosion andenvironmentally assisted fatigue. For individual titles, see N95-14454through N95-14486.

N95-14454*# Engineering Software Research and Development, Inc.,Saint Louis, MO.ELASTIC-PLASTIC MODELS FOR MULTI-SITE DAMAGERICARDO L. ACTIS and BARNA A. SZABO In NASA. LangleyResearch Center, FAA/NASA International Symposium on Ad-vanced Structural Integrity Methods for Airframe Durability andDamage Tolerance p 1-16 Sep. 1994(Contract(s)/Grant(s): NAG9-622)Avail: CASI HC A03/MF A04

This paper presents recent developments in advanced analysismethods for the computation of stress site damage. The method ofsolution is based on the p-version of the finite element method. Itsimplementation was designed to permit extraction of linear stressintensity factors using a superconvergent extraction method (known asthe contour integral method) and evaluation of the J-integral followingan elastic-plastic analysis. Coarse meshes are adequate for obtaining

accurate results supported by p-convergence data. The elastic-plasticanalysis is based on the deformation theory of plasticity and the vonMises yield criterion. The model problem consists of an aluminum platewith six equally spaced holes and a crack emanating from each hole.The cracks are of different sizes. The panel is subjected to a remotetensile load. Experimental results are available for the panel. Theplasticity analysis provided the same limit load as the experimentallydetermined load. The results of elastic-plastic analysis were compared

. with the results of linear elastic analysis in an effort to evaluate howplastic zone sizes influence the crack growth rates. The onset of net-section yielding was determined also. The results show that crackgrowth rate is accelerated by the presence of adjacent damage, and thecritical crack size is shorter when the effects of plasticity are taken intoconsideration. This work also addresses the effects of alternativestress-strain laws: The elastic-ideally-plastic material model is com-pared against the Ramberg-Osgood model. Author

N95-14455*# United Technologies Research Center, East Hartford,CT.SMALL CRACK TEST PROGRAM FOR HELICOPTERMATERIALSBAL ANNIGERI and GEORGE SCHNEIDER In NASA. LangleyResearch Center, FAA/NASA International Symposium on Ad-vanced Structural Integrity Methods for Airframe Durability andDamage Tolerance p 17-32 Sep. 1994(Contract(s)/Grant(s): F09603-89-G-0096)Avail: CASI HC A03/MF A04

Crack propagation tests were conducted to determine crackgrowth behavior in five helicopter materials for surface cracks between0.005 to 0.020 inches in depth. Constant amplitude tests were con-ducted at stress ratios R equals 0.1 and 0.5, and emphasis was placedon near threshold data (i.e., 10-8 to 10-6 inches/cycle). Spectrum testswere conducted using a helicopter spectrum. The test specimen was anunnotched tension specimen, and cracks were initiated from a smallEDM notch. An optical/video system was used to monitor crack growth.The material for the test specimens was obtained from helicopter partforgings. Testing was conducted at stresses below yield to reflect actualstresses in helicopter parts. Author

N95-14456*# Purdue Univ., West Lafayette, IN. School of Aeronau-tics and Astronautics.BENDING EFFECTS OF UNSYMMETRIC ADHESIVELYBONDED COMPOSITE REPAIRS ON CRACKED ALUMINUMPANELSCORY ARENDT and C. T. SUN In NASA. Langley Research Center,FAA/NASA International Symposium on Advanced Structural IntegrityMethods for Airframe Durability and Damage Tolerance p 33-48 Sep.1994(Contract(s)/Grant(s): AF PROJ. 1397)Avail: CASI HC A03/MF A04

The bending effects of unsymmetrically bonded composite re-pairs on cracked aluminum panels were quantified using a plate linearfinite element model. Stress intensity factors and strain energy releaserates were obtained from the model twice, once with out-of-planedisplacement suppressed and another time without these restrictions.Several configurations were examined, crack growth stability wasidentified, and the effect of a debond was considered. The maximumstress intensity factor was also analyzed. Previous work by otherauthors was found to underpredict the bending effect Author

N95-1445r# Textron Specialty Materials, Lowell, MA.EVALUATION OF BONDED BORON/EPOXY DOUBLERSFOR COMMERCIAL AIRCRAFT ALUMINUM STRUCTURESBRUCE BELASON, PAUL RUTHERFORD, MATTHEW MILLER, andSHREERAM RAJ In NASA. Langley Research Center, FAA/NASAInternational Symposium on Advanced Structural Integrity Methods forAirframe Durability and Damage Tolerance p 49-60 Sep. 1994Avail: CASI HC A03/MF ACM

An 18 month laboratory test and stress analysis program wasconducted to evaluate bonded boron/epoxy doublers for repairing

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cracks on aluminum aircraft structures. The objective was to obtain acore body of substantiating data which will support approval for use oncommercial transports of a technology that is being widely used by themilitary. The data showed that the doublers had excellent performance.

Author

N95-14458*# Federal Aviation Administration, Cambridge, MA.National Transportation Systems Center.INSPECTING FOR WIDESPREAD FATIGUE DAMAGE: ISPARTIAL DEBONDING THE KEY?JOHN BREWER In NASA. Langley Research Center, FAA/NASAInternational Symposium on Advanced Structural Integrity Methods forAirframe Durability and Damage Tolerance p 61-70 Sep. 1994Avail: CASI HC A02/MF A04

Experimental and analytical results indicate that cracks caninitiate, grow, and coalesce more rapidly in fuselage lap joints that haveexperienced partial or complete debonding. Computational analysis inthis paper shows that stress concentrations and stress intensity factorsat the rivet holes are far less severe when the bond is intact. Debondinghastens the initiation of widespread fatigue cracks and significantlyincreases crack growth rate. Thus, debonded regions serve as "breed-ing grounds" for widespread fatigue damage. Therefore, the effective-ness of lap joint inspection programs may be enhanced if detailedinspections are focused on areas in which debonding has beendetected. Author

N95-14460*# FractuResearch, Inc., Galena, OH.TESTING AND ANALYSIS OF FLAT AND CURVED PANELSWITH MULTIPLE CRACKSDAVID BROEK, DAVID Y. JEONG, and DOUGLAS THOMSON InNASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabilityand Damage Tolerance p 85-98 Sep. 1994Avail: CASI HC A03/MF A04

An experimental and analytical investigation of multiple crackingin various types of test specimens is described in this paper. The testingphase is comprised of a flat unstiffened panel series and curvedstiffened and unstiffened panel series. The test specimens containedvarious configurations for initial damage. Static loading was applied tothese specimens until ultimate failure, while loads and crack propaga-tion were recorded. This data provides the basis for developing andvalidating methodologies for predicting linkup of multiple cracks, pro-gression to failure, and overall residual strength. The results fromtwelve flat coupon and ten full scale curved panel tests are presented.In addition, an engineering analysis procedure was developed topredict multiple crack linkup. Reasonable agreement was found be-tween predictions and actual test results for linkup and residual strengthfor both flat and curved panels. The results indicate that an engineeringanalysis approach has the potential to quantitatively assess the effectof multiple cracks in the arrest capability of an aircraft fuselagestructure. Author

N95-14461*# Israel Aircraft Industries Ltd., Tashan (Israel).Engineering Center.PROBABILISTIC INSPECTION STRATEGIES FORMINIMIZING SERVICE FAILURESABRAHAM BROT In NASA. Langley Research Center, FAA/NASAInternational Symposium on Advanced Structural Integrity Methods forAirframe Durability and Damage Tolerance p 99-109 Sep. 1994Avail: CASI HC A03/MF A04

The INSIM computer program is described which simulates the'limited fatigue life' environment in which aircraft structures generallyoperate. The use of INSIM to develop inspection strategies which aimto minimize service failures is demonstrated. Damage-tolerance meth-odology, inspection thresholds and customized inspections are simu-lated using the probability of failure as the driving parameter. Author

N95-14464*# Defence Research Agency, Famborough, Hampshire(England).A METHOD OF CALCULATING THE SAFE FATIGUE LIFE

OF COMPACT, HIGHLY-STRESSED COMPONENTSARTHUR W. CARDICK and VERA J. PIKE In NASA. LangleyResearch Center, FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability and Damage Toler-ance p 145-156 Sep. 1994Avail: CASI HC A03/MF A04

This paper describes a method which has been developed forestimating the safe fatigue life of compact, highly-stressed and inacces-sible components for aeroplanes and helicopters of the Royal Air Force.It is explained why the Design Requirements for British Military Aircraftdo not favor the use of a damage-tolerance approach in these circum-stances. Author

N95-14466*# Stevens Inst. of Tech., Hoboken, NJ. Dept. ofMechanical Engineering.COMPUTATIONAL PREDICTIVE METHODS FOR FRACTUREAND FATIGUEJ. CORDES, A. T. CHANG, N. NELSON, and Y. KIM In NASA.Langley Research Center, FAA/NASA International Symposium onAdvanced Structural Integrity Methods for Airframe Durability andDamage Tolerance p 175-192 Sep. 1994Avail: CASI HC A03/MF A04

The damage-tolerant design philosophy as used by aircraft indus-tries enables aircraft components and aircraft structures to operatesafely with minor damage, small cracks, and flaws. Maintenance andinspection procedures insure that damages developed during serviceremain below design values. When damage is found, repairs or designmodifications are implemented and flight is resumed. Design andredesign guidelines, such as military specifications MIL-A-83444, havesuccessfully reduced the incidence of damage and cracks. However,fatigue cracks continue to appear in aircraft well before the design lifehas expired. The F16 airplane, for instance, developed small cracks inthe engine mount, wing support, bulk heads, the fuselage upper skin,the fuel shelf joints, and along the upper wings. Some cracks were foundafter 600 hours of the 8000 hour design service life and designmodifications were required. Tests on the F16 plane showed that thedesign loading conditions were close to the predicted loading condi-tions. Improvements to analytic methods for predicting fatigue crackgrowth adjacent to holes, when multiple damage sites are present, andin corrosive environments would result in more cost-effective designs,fewer repairs, and fewer redesigns. The overall objective of theresearch described in this paper is to develop, verify, and extend thecomputational efficiency of analysis procedures necessary for damagetolerant design. This paper describes an elastic/plastic fracture methodand an associated fatigue analysis method for damage tolerant design.Both methods are unique in that material parameters such as fracturetoughness, R-curve data, and fatigue constants are not required. Themethods are implemented with a general-purpose finite element pack-age. Several proof-of-concept examples are given. With further devel-opment, the methods could be extended for analysis of multi-sitedamage, creep-fatigue, and corrosion fatigue problems. Author

N95-14467*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.INFLUENCE OF CRACK HISTORY ON THE STABLETEARING BEHAVIOR OF A THIN-SHEET MATERIAL WITHMULTIPLE CRACKSD. S. DAWICKE (Analytical Services and Materials, Inc., Hampton,VA.), J. C. NEWMAN, JR., M. A. BUTTON, and B. E. AMSTUTZ Inits FAA/NASA International Symposium on Advanced Structural Integ-rity Methods for Airframe Durability and Damage Tolerance p 193-212Sep. 1994Avail: CASI HC A03/MF A04

Fracture tests were conducted on 2.3mm thick, 305mm widesheets of 2024-T3 aluminum alloy with from one to five collinear cracks.The cracks were introduced (crack history) into the specimens by threemethods: saw cutting, fatigue precracking at a low stress range, andfatigue precracking at a high stress range. For the single crack tests, the

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initial crack history influenced the stress required for the onset of stablecrack growth and the first 10mm of crack growth. The effect on failurestress was about 4 percent or less. For the multiple crack tests, the initialcrack history was shown to cause differences of more than 20 percentin the link-up stress and 13 percent in failure stress. An elastic-plasticfinite element analysis employing the CTOA fracture criterion was usedto predict the fracture behavior of the single and multiple crack tests.The numerical predictions were within 7 percent of the observed link-up and failure stress in all the tests. Author

N95-14468*# Rutgers Univ., Piscataway, NJ. Federal AviationAdministration for Computational Modeling of Aircraft Structures.STUDY OF MULTIPLE CRACKS IN AIRPLANE FUSELAGEBY MICROMECHANICS AND COMPLEX VARIABLESMITSUNORI DENDAandY.F. DONG /nNASA. LangleyResearchCenter, FAA/NASA International Symposium on Advanced Struc-tural Integrity Methods for Airframe Durability and Damage Toler-ance p 213-223 Sep. 1994Avail: CASI HC A03/MF A04

Innovative numerical techniques for two dimensional elastic andelastic-plastic multiple crack problems are presented usingmicromechanics concepts and complex variables. The simplicity andthe accuracy of the proposed method will enable us to carry out themultiple-site fatigue crack propagation analyses for airplane fuselageby incorporating such features as the curvilinear crack path, plasticdeformation, coalescence of cracks, etc. Author

N95-14470*# Utah Univ., Salt Lake City, UT. Quality and IntegrityDesign Engineering Center.THE ROLE OF FRETTING CORROSION AND FRETTINGFATIGUE IN AIRCRAFT RIVET HOLE CRACKING StatusReportCHARLES B. ELLIOTT, III, MARK MOESSER, and DAVID W.HOEPPNER In NASA. Langley Research Center, FAA/NASAInternational Symposium on Advanced Structural Integrity Methods forAirframe Durability and Damage Tolerance p 241-246 Sep. 1994(Contract(s)/Grant(s): FAA-92-G-0004; FAA-93-G-0068)Avail: CASI HC A02/MF ACM

Personnel in the Quality and Integrity Design Engineering Center(QIDEC) at the University of Utah are working under a two year grantfrom the FAA to better understand the role of fretting corrosion andfretting fatigue in aircraft rivet hole cracking. The current programfollows a one year grant program which was completed in 1993. Thispaper provides a status report on the results of these grant programs.Recent effort has been focused on developing basic fretting fatiguemodels which consider variation in the coefficient of friction with timeand location within the fretting interface. This is a very importantcharacteristic of the Ql DEC model because coefficient of friction variessignificantly during the fretting fatigue process. Copies of QIDECdocuments discussed in this paper can be obtained by contacting theauthors. Author

N95-14473*# National Aeronautics and Space Administration. LyndonB. Johnson Space Center, Houston, TX.DEVELOPMENT OF THE NASA/FLAGRO COMPUTERPROGRAM FOR ANALYSIS OF AIRFRAME STRUCTURESR. G. FORMAN, V. SHIVAKUMAR. and J. C. NEWMAN, JR. InNASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabil-ity and Damage Tolerance p 277-288 Sep. 1994Avail: CASI HC A03/MF A04

The NASA/FLAGRO (NASGRO) computer program was devel-oped for fracture control analysis of space hardware and is currently thestandard computer code in NASA, the U.S. Air Force, and the EuropeanAgency (ESA) for this purpose. The significant attributes of trie NASGROprogram are the numerous crack case solutions, the large materials file,the improved growth rate equation based on crack closure theory, andthe user-friendly promptive input features. In support of the NationalAging Aircraft Research Program (NAARP); NASGRO is being furtherdeveloped to provide advanced state-of-the-art capability for damage

tolerance and crack growth analysis of aircraft structural problems,including mechanical systems and engines. The project currentlyinvolves a cooperative development effort by NASA, FAA, and ESA.The primary tasks underway are the incorporation of advanced meth-odology for crack growth rate retardation resulting from spectrumloading and improved analysis for determining crack instability. Also,the current weight function solutions in NASGRO or nonlinear stressgradient problems are being extended to more crack cases, and the 2-d boundary integral routine for stress analysis and stress-intensityfactor solutions is being extended to 3-d problems. Lastly, effort isunderway to enhance the program to operate on personal computersand work stations in a Windows environment Because of the increas-ing and already wide usage of NASGRO, the code offers an excellentmechanism for technology transfer for new fatigue and fracture me-chanics capabilities developed within NAARP. Author

N95-14475*# Northwestern Univ., Evanston, IL. School of Engineer-ing and Applied Science.FATIGUE RELIABILITY METHOD WITH IN-SERVICEINSPECTIONSH. H. HARKNESS, M. FLEMING, B. MORAN, and T. BELYTSCHKOIn NASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabilityand Damage Tolerance p 307-326 Sep. 1994 Sponsored in partby National Inst for Standards and Technology and FAAAvail: CASI HC A03/MF A04

The first reliability method (FORM) has traditionally been appliedin a fatigue reliability setting to one inspection interval at a time, so thatthe random distribution of crack lengths must be recharacterizedfollowing each inspection. The FORM presented here allow eachanalysis to span several inspection periods without explicit character-ization of the crack length distribution upon each inspection. Themethod thereby preserves the attractive feature of FORM in thatrelatively few realizations in the random variable space need to beconsidered. Examples are given which show that the present method-ology gives estimates which are in good agreement with Monte Carlosimulations and is efficient even for complex components. Author

N95-14476** Federal Aviation Administration, Cambridge, MA. Re-search and Special Programs Administration.NONLINEAR BULGING FACTOR BASED ON R-CURVEDATADAVID Y. JEONG and PIN TONG In NASA. Langley ResearchCenter, FAA/NASA International Symposium on Advanced Struc-tural Integrity Methods for Airframe Durability and Damage Toler-ance p 327-338 Sep. 1994Avail: CASI HC A03/MF A04

In this paper, a nonlinear bulging factor is derived using a strainenergy approach combined with dimensional analysis. The functionalform of the bulging factor contains an empirical constant that isdetermined using R-curve data from unstiffened flat and curved paneltests. The determination of this empirical constant is based on theassumption that the R-curve is the same tor both flat and curved panels.

Author

N95-14479*# Washington Univ., Seattle, WA. Dept of MechanicalEngineering.AXIAL CRACK PROPAGATION AND ARREST INPRESSURIZED FUSELAGEM. KOSAI, A. SHIMAMOTO, C.-T. YU, S. I. WALKER, A. S.KOBAYASHI, and P. TAN In NASA. Langley Research Center.FAA/NASA International Symposium on Advanced Structural In-tegrity Methods for Airframe Durability and Damage Tolerancep 375-392 Sep. 1994(Contract(s)/Grant(s): FAA-92-G-0005)Avail: CASI HC A03/MF A04

The crack arrest capability of a tear strap in a pressurizedprecracked fuselage was studied through instrumented axial rupturetests of small scale models of an idealized fuselage. Upon pressuriza-tion, rapid crack propagation initiated at an axial through crack along the

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stringer and immediately kinked due to the mixed modes 1 and 2 statecaused by the one-sided opening of the crack flap. The diagonallyrunning crack further turned at the tear straps. Dynamic finite elementanalysis of the rupturing cylinder showed that the crack kinked and alsoran straight in the presence of a mixed mode state according to amodified two-parameter crack kinking criterion. Author

N95-14480*# Georgia Inst of Tech., Atlanta, GA. School of Me-chanical Engineering.FRACTURE MECHANICS VALIDITY LIMITSDENNIS M. LAMBERT and HUGO A. ERNST In NASA. LangleyResearch Center, FAA/NASA International Symposium on Ad-vanced Structural Integrity Methods for Airframe Durability andDamage Tolerance p 393-407 Sep. 1994Avail: CASI HC A03/MF A04

Fracture behavior is characteristics of a dramatic loss of strengthcompared to elastic deformation behavior. Fracture parameters havebeen developed and exhibit a range within which each is valid forpredicting growth. Each is limited by the assumptions made in itsdevelopment: all are defined within a specific context. For example, thestress intensity parameters, K, and the crack driving force, G, arederived using an assumption of linear elasticity. To use K or G, the zoneof plasticity must be small as compared to the physical dimensions ofthe object being loaded. This insures an elastic response, and in thiscontext, K and G will work well. Rice's J-integral has been used beyondthe limits imposed on K and G. J requires an assumption of nonlinearelasticity, which is not characteristic of real material behavior, but isthought to be a reasonable approximation if unloading is kept to aminimum. As well, the constraint cannot change dramatically (typically,the crack extension is limited to ten-percent of the initial remainingligament length). Rice, et al investigated the properties required of J-type parameters, J(sub x), and showed that the time rate, dJ(sub x)/dt,must not be a function of the crack extension rate, da/dt. Ernst devisedthe modified-J parameter, J(sub M), that meets this criterion. J(sub M)correlates fracture data to much higher crack growth than does J.Ultimately, a limit of the validity of J(sub M) is anticipated, and this hasbeen estimated to be at a crack extension of about 40-percent of theinitial remaining ligament length. None of the various parameters canbe expected to describe fracture in an environment of gross plasticity,in which case the process is better described by deformation param-eters, e.g., stress and strain. In the current study, various schemes toidentify the onset of the plasticity-dominated behavior, i.e., the end offracture mechanics validity, are presented. Each validity limit param-eter is developed in detail, and then data is presented and the variousschemes for establishing a limit of the validity are compared. Theselected limiting parameter is applied to a set of fracture data showingthe improvement of correlation gained. Author (revised)

N95-14484** Southwest Research Inst., San Antonio, TX.ANALYSIS OF SMALL CRACK BEHAVIOR FOR AIRFRAMEAPPLICATIONSR. C. MCCLUNG, K. S. CHAN, S. J. HUDAK, JR., and D. L. DAVIDSONIn NASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabilityand Damage Tolerance p 463-479 Sep. 1994 Sponsored in part byAFOSR; AFWAL; ARO; and ONRAvail: CASI HC A03/MF A04

The small fatigue crack problem is critically reviewed from theperspective of airframe applications. Different types of small cracks-microstructural, mechanical, and chemical-are carefully defined andrelevant mechanisms identified. Appropriate analysis techniques, in-cluding both rigorous scientific and practical engineering treatments,are briefly described. Important materials data issues are addressed,including increased scatter in small crack data and recommended smallcrack test methods. Key problems requiring further study are high-lighted. Author

N95-14485*# Boeing Co., Seattle, WA.FULL-SCALE TESTING AND ANALYSIS OF FUSELAGESTRUCTUREM. MILLER, M. L. GRUBER, K. E. WILKINS, and R. E. WORDEN In

NASA. Langley Research Center, FAA/NASA International Sympo-sium on Advanced Structural Integrity Methods for Airframe Durabilityand Damage Tolerance p 481 -496 Sep. 1994Avail: CASI HC A03/MF A04

This paper presents recent results from a program in the BoeingCommercial Airplane Group to study the behavior of cracks in fuselagestructures. The goal of this program is to improve methods for analyzingcrack growth and residual strength in pressurized fuselages, thusimproving new airplane designs and optimizing the required structuralinspections for current models. The program consists of full-scaleexperimental testing of pressurized fuselage panels in both wide-bodyand narrow-body fixtures and finite element analyses to predict theresults. The finite element analyses are geometrically nonlinear withmaterial and fastener nonlinearity included on a case-by-case basis.The analysis results are compared with the strain gage, crack growth,and residual strength data from the experimental program. Most of thestudies reported in this paper concern the behavior of single or multiplecracks in the lap joints of narrow-body airplanes (such as 727 and737 commercial jets). The phenomenon where the crack trajectory iscurved creating a Hap' and resulting in a controlled decompression is-discussed. Author

N95-14556*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.CHARACTERIZATION OF ANNULAR TWO-PHASE GAS-LIQUID FLOWS IN MICROGRAVITYW. SCOTT BOUSMAN (Houston Univ., TX.) and JOHN B.MCQUILLEN /n ;'fsSecond Microgravity Fluid Physics Conferencep 227-232 Aug. 1994(Contract(s)/Grant(s): NAG3-510)Avail: CASI HC A02/MF A04; 2 functional color pages

A series of two-phase gas-liquid flow experiments were developedto study annular flows in microgravity using the NASA Lewis Learjet. Atest section was built to measure the liquid film thickness around theperimeter of the tube permitting the three dimensional nature of the gas-liquid interface to be observed. A second test section was used tomeasure the film thickness, pressure drop and wall shear stress inannular microgravity two-phase flows. Three liquids were studied todetermine the effects of liquid viscosity and surface tension. The resultof this study provide insight into the wave characteristics, pressure dropand droplet entrainment in microgravity annular flows. Author

N95-14563*# Carnegie-Mellon Univ., Pittsburgh, PA.TRANSPORT PHENOMENA IN STRATIFIED MULTI-FLUIDFLO W IN THE PRESENCE AND ABSENCE OF GRAVITYNORMAN CHIGIER, MIN XU, DAVID SQUARER, and NASSERRASHIDNIA In NASA. Lewis Research Center, Second MicrogravityFluid Physics Conference p 273-278 Aug. 1994Avail: CASI HC A02/MF A04; 2 functional color pages

An experiment is being conducted to study the effects of buoyancyon planar stratified flows. A wind tunnel has been designed andconstructed to generate planar flows with separate heating for the topand bottom planar air jets emerging from slot nozzles separated by aninsulating splitter plate. The objective is to generate planar jet flows withwell defined and well controlled velocity and temperature profiles.Magnitudes of velocity and temperature will be varied separately ineach flow for both laminar and turbulent flow conditions. Both stably andunstably stratified flows will be studied by changing the temperaturedistributions in each air stream. This paper reports on the design of theapparatus and initial measurements of velocity and turbulence made bylaser Doppler velocimetry. Author

N95-14617*# National Aeronautics and Space Administration. AmesResearch Center, Moffett Reid, CA.EXPERIMENTAL/ANALYTICAL APPROACH TOUNDERSTANDING MISTUNING IN A TRANSONIC WINDTUNNEL COMPRESSORTERI KAISER, REED S. HANSEN, NHAN NGUYEN, ROY W. HAMP-TON, DOUG MU2ZIO, MLADEN K. CHARGIN, ROY GUIST, KENHAMM, and LEN WALKER Jun. 1994 16 p

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(NASA-TM-108833; A-94104; NAS1.15:108833) Avail: CASIHC A03/MFA01

This paper will briefly set forth some of the basic tenets of mistunedrotating bladed-disk assemblies. The experience with an existing threestage compressor in a transonic wind tunnel will be documented. Themanner in which the theoretical properties manifest themselves in thisnon-ideal compressor will be described. A description of mistimingbehaviors that can and cannot be accurately substantiated will bediscussed. Author

N95-14658 Naval Postgraduate School, Monterey. CA. Dept. ofMechanical Engineering.SPECTRAL ANALYSIS OF VORTEX/FREE-SURFACEINTERACTION M.S. ThesisGLENN D. HOFERT Jun. 1994 73 p Limited Reproducibility:More than 20% of this document may be affected by microfichequality(AD-A283210) Avail: CASI HC A04

The unsteady flow phenomena resulting from the interaction ofvorticity with a free surface has been investigated through the use of athree-color Laser Doppler-Velocimeter. The vorticity field was providedby a single tip vortex generated by an airfoil, placed in the test sectionof a recirculating water tunnel at a suitable angle of attack. All of thestatistical quantities of flow such as turbulence and Reynolds stressesand in particular the spectrum of the fluctuations have been measuredand analyzed. The results have shown that the free surface redistrib-utes part or all of the normal turbulent kinetic energy into streamwiseand spanwise components. Furthermore, the energy spectra have alsoshown that there exists an energy gradient on the free surface, on eitherside of the vertical passing through the original vortex. It is believed thatthe scars observed on the free surface are a consequence of thematching of the Bragg wave length with the wave length of the surfacesignatures within a particular spectrum. DTIC

N95-14879*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.AN OPTICAL TECHNIQUE FOR EXAMINING AIRCRAFTSHOCK WAVE STRUCTURES IN FLIGHTLEONARD M.WEINSTEIN In its High-Speed Research: 1994 SonicBoom Workshop: Atmospheric Propagation and Acceptability Studiesp 1-17 Oct 1994Avail: CASI HC A03/MF A03

The detailed properties of sonic booms have to be better under-stood before commercial, next generation, supersonic and hypersonicaircraft can be properly developed. Experimental tests and measure-ments are needed to help sort the physical details of the flows at realistictest conditions. Some of these tests can be made in wind tunnels, butthe need for full flight conditions simulation, the problem of tunnel wallinterference, and the short distance the shocks can be examined fromthe aircraft, limit the usefulness of wind tunnel tests. Previous measure-ment techniques for examining the flow field of aircraft in flight haveincluded pressure measurements on the aircraft, ground based pres-sure measurements, and flow field measurements made with chaseaircraft. Obtaining data with chase planes is a slow and difficult process,and is limited in how close it can be obtained to the test aircraft A needclearly existed for a better technique to examine the shock structurefrom the plane to large distances from the plane. A new technique hasbeen recently developed to obtain schlieren photographs of aircraft inflight (SAP). Preliminary results have been obtained, and the techniqueholds promise as a tool to study the shape and approximate strength ofthe shock wave structure around the test aircraft, and examine shockwave details all the way from the aircraft to near the ground. The currentpaper describes this approach, and gives some preliminary test results.

Author

N95-14912*# Lockheed Engineering and Sciences Co., Hampton,VA.AN APPROXIMATE RIEMANN SOLVER FOR THERMAL AND

CHEMICAL NONEOUILIBRIUM FLOWSRAMADAS K. PRABHU Oct. 1994 18 p(Contract(s)/Grant(s): NAS1-19000; RTOP 232-01-04-06)(NASA-CR-195003; NAS 1.26:195003) Avail: CASI HC A03/MF A01

Among the many methods available for the determination ofinviscid fluxes across a surface of discontinuity, the flux-difference-splitting technique that employs Roe-averaged variables has beenused extensively by the CFD community because of its simplicity andits ability to capture shocks exactly. This method, originally developedfor perfect gas flows, has since been extended to equilibrium as well asnonequilibrium flows. Determination of the Roe-averaged variables forthe case of a perfect gas flow is a simple task; however, for thermal andchemical nonequilibrium flows, some of the variables are not uniquelydefined. Methods available in the literature to determine these variablesseem to lack sound bases. The present paper describes a simple, yetaccurate, method to determine all the variables for nonequilibrium flowsin the Roe-average state. The basis for this method is the requirementthat the Roe-averaged variables form a consistent set of thermody-namic variables. The present method satisfies the requirement that thesquare of the speed of sound be positive. Author

N95-14922*# Eloret Corp., Palo Alto, CA.DEVELOPMENT AND APPLICATION OF STRUCTURALDYNAMICS ANALYSIS CAPABILITIES Final TechnicalReport, 1 Feb. 1988 - 30 Sep. 1994KLAUS W. HEINEMANN and SHIG HOZAKI 15 Nov. 1994 240 p(Contract(s)/Grant(s): NCC2-518)(NASA-CR-197229; NAS 1.26:197229) Avail: CASI HC A11/MF A03

Extensive research activities were performed in the area ofmultidisciplinary modeling and simulation of aerospace vehicles thatare relevant to NASA Dryden Right Research Facility. The effortsinvolved theoretical development, computer coding, and debugging ofthe STARS code. New solution procedures were developed in suchareas as structures, CFD, and graphics, among others. Furthermore,systems-oriented codes were developed for rendering the code trulymultidisciplinary and rather automated in nature. Also, work wasperformed in pre- and post-processing of engineering analysis data.

Author

N95-15306* National Aeronautics and Space Administration. LyndonB. Johnson Space Center, Houston, TX.LANDING GEAR ENERGY ABSORPTION SYSTEM PatentCHRISTOPHER P. HANSEN, inventor (to NASA) 22 Nov. 19947 p Filed 1 Dec. 1993 Supersedes N94-29448 (32 - 8. p 3300)(NASA-CASE-MSC-22277-1; US-PATENT-5,366,181; US-PATENT-APPL-SN-159606; US-PATENT-CLASS-244-104R; US-PATENT-CLASS-244-100R; US-PATENT-CLASS-188-381; INT-PATENT-CLASS-B64C-25/58) Avail: US Patent and Trademark Office

A landing pad system is described for absorbing horizontal andvertical impact forces upon engagement with a landing surface wherecircumferentially arranged landing struts respectively have a cleviswhich receives a slidable rod member and where the upper portion ofa slidable rod member is coupled to the clevis by friction washers whichare force fit onto the rod member to provide for controlled constant forceenergy absorption when the rod member moves relative to the clevis.The lower end of the friction rod is pivotally attached by a ball and socketto a support plate where the support plate is arranged to slide in atransverse direction relative to a housing which contains an energyabsorption material for absorbing energy in a transverse direction.

Official Gazette of the U.S. Patent and Trademark Office

N95-15547 Wright Lab., Wright-Patterson AFB, OH.LARGE AMPLITUDE NONLINEAR RESPONSE OF FLATALUMINUM, AND CARBON FIBER PLASTIC BEAMS ANDPLATES Interim Report, 1 Oct. 1992-1 Sep. 1993HOWARD F. WOLFE and CYNTHIA A. SHROYER Jun. 199492 p Limited Reproducibility: More than 20% of this document maybe affected by microfiche quality(Contract(s)/Grant(s): AF PROJ. 2401)

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(AD-A282440; WL-TM-94-3077) Avail: Issuing Activity (DefenseTechnical Information Center (OTIC))

This progress report presents the results of a continuing study toimprove the understanding of nonlinear dynamic behavior of aerospacestructures subjected to high levels of excitation. Tests were continuedwith a damped-clamped (C-C) aluminum beam. A summary of theresults is presented. Tests were conducted with a C-C carbon fiberreinforced plastic (CFRP) beam and a pinned-pinned (P-P) aluminumbeam. A summary of these results is also presented. Flat plate testsbegan with an aluminum plate. The shapes of the total, axial, andbending strain power spectral densities for the C-C aluminum and theCFRP beams were quite similar. Both showed a small frequencyincrease and slight peak broadening as the levels of excitation in-creased. The nonlinear displacement shapes for the two cases werealso quite similar. Further analysis is needed for the P-P aluminumbeam case. Finally, a method of estimating the RMS stress for themultimodal response of a panel is presented. DTIC

N95-15604*# Lockheed Engineering and Sciences Co., Hampton,VA.LAMINAR AND TURBULENT FLOW COMPUTATIONS OFTYPE 4 SHOCK-SHOCK INTERFERENCE AEROTHERMALLOADS USING UNSTRUCTURED GRIDSGURURAJA R. VEMAGANTI Oct. 1994 58 p(Contract(s)/Grant(s): NAS1-19000; RTOP 232-01-04-06)(NASA-CR-195008; NAS 1.26:195008) Avail: CASI HC A04/MF A01

This report presents computations for the Type 4 shock-shockinterference flow under laminar and turbulent conditions using unstruc-tured grids. Mesh adaptation was accomplished by remeshing, refine-ment, and mesh movement. Two two-equation turbulence models wereused to analyze turbulent flows. The mean flow governing equationsand the turbulence governing equations are solved in a coupledmanner. The solution algorithm and the details pertaining to its imple-mentation on unstructured grids are described. Computations wereperformed at two differentf reestream Reynolds numbers at a freest reamMach number of 11. Effects of the variation in the impinging shocklocation are studied. The comparison of the results in terms of wall heatflux and wall pressure distributions is presented. Author

N95-15728** Cincinnati Univ., OH. Dept. of Aerospace Engineeringand Engineering Mechanics.ASSESSMENT OF CTAS ETA PREDICTION CAPABILITIESAnnual ReportMICHAEL A. BOLENOER 1 Nov. 1994 42 p(Contract(s)/Grant(s): NCC2-669)(NASA-CR-197224; NAS 1.26:197224) Avail: CASI HC A03/MF A01

This report summarizes the work done to date in assessing thetrajectory fidelity and estimated time of arrival (ETA) prediction capabil-ity of the NASA Ames Center TRACON Automation System (CTAS)software. The CTAS software suite is a series of computer programsdesigned to aid air traffic controllers in their tasks of safely schedulingthe landing sequence of approaching aircraft, in particular, this reportconcerns the accuracy of the available measurements (e.g., position,altitude, etc.) that are input to the software, as well as the accuracy ofthe final data that is made available to the air traffic controllers.

Derived from text

N95-15785*# Cincinnati Univ., OH. Dept. of Aerospace Engineeringand Engineering Mechanics.GROUNDSPEED FILTERING FOR CTASGARY L. SLATER 11 Nov. 1994 16 p(Contract(s)/Grant(s): NCC2-669)(NASA-CR-197223; NAS 1.26:197223) Avail: CASI HC A03/MFA01

Ground speed is one of the radar observables which is obtainedalong with position and heading from NASA Ames Center radar. Withinthe Center TRACON Automation System (CTAS), groundspeed isconverted into airspeed using the wind speeds which CTAS obtainsfrom the NOAA weather grid. This airspeed is then used in the trajectory

synthesis logic which computes the trajectory for each individualaircraft. The time history of the typical radar groundspeed data isgenerally quite noisy, with high frequency variations on the order of fiveknots, and occasional 'outliers' which can be significantly different fromthe probable true speed. To try to smooth out these speeds and makethe ETA estimate less erratic, filtering of the ground speed is done withinCTAS. In its base form, the CTAS filter is a 'moving average' filter whichaverages the last ten radar values. In addition, there is separate logicto detect and correct for 'outliers', and acceleration logic which limits thegroundspeed change in adjacent time samples. As will be shown, theseadditional modifications do cause significant changes in the actualgroundspeed filter output. The conclusion is that the current groundspeed filter logic is unable to track accurately the speed variationsobserved on many aircraft. The Kalman filter logic however, appears tobe an improvement to the current algorithm used to smooth groundspeed variations, while being simpler and more efficient to implement.Additional logic which can test for true 'outliers' can easily be added bylooking at the difference in the a priori and post priori Kalman estimates,and not updating if the difference in these quantities is too large.

Derived from text

N95-15898*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.WIND-TUNNEL BLOCKAGE AND ACTUATION SYSTEMSTEST OF A TWO-DIMENSIONAL SCRAMJET INLETUNSTART MODEL AT MACH 6SCOTT D. HOLLAND Nov. 1994 38 p See also videotapesupplement L-0194-41(Contract(s)/Grant(s): RTOP 763-23-35-08)(NASA-TM-109152; NAS 1.15:109152) Avail: CASI HC A03/MF A01

The present study examines the wind-tunnel blockage and actua-tion systems effectiveness in starting and forcibly unstarting a two-dimensional scramjet inlet in the NASA Langley 20-Inch Mach 6 Tunnel.The intent of the overall test program is to study (both experimentallyand computationally) the dynamics of the inlet unstart; however, priorto the design and fabrication of an expensive, instrumented wind-tunnelmodel, it was deemed necessary first to examine potential wind-tunnelblockage issues related to model sizing and to examine the adequacyof the actuation systems in accomplishing the start and unstart. Themodel is equipped with both a moveable cowl and aft plug. Windows inthe inlet sidewalls allow limited optical access to the internal shockstructure; schlieren video was used to identify inlet start and unstart. Achronology of each actuation sequence is provided in tabular formalong with still frames from the schlieren video. A pitot probe monitoredthe freestream conditions throughout the start/unstart process todetermine if there was a blockage effect due to the model start orunstart. Because the purpose of this report is to make the phase I(blockage and actuation systems) data rapidly available to the commu-nity, the data is presented largely without analysis of the internal shockinteractions or the unstart process. This series of tests indicated that themodel was appropriately sized for this facility and identified operabilitylimits required first to allow the inlet to start and second to force theunstart. Author

N95-15899* National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.TWO-DIMENSIONAL SCRAMJET INLET UNSTART MODEL:WIND-TUNNEL BLOCKAGE AND ACTUATION SYSTEMSTEST (Videotape Supplement)SCOTT D. HOLLAND Nov. 1994 See also NASA-TM-109152Videotape supplement: 10 min. 52 sec. playing time, in color, in VHSand Beta formats(Contract(s)/Grant(s): RTOP 763-23-35-08)(NASA-TM-109984; NONP-NASA-SUPPL-VT-94-32020) Avail: CASIVHS A02/BETA A22

This supplement to NASA TM109152 shows the Schlieren video(10 min. 52 sec., color, Beta and VHS) of the external flow field and aportion of the internal flow field of a two-dimensional scramjet inlet

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model in the NASA Langley 20-Inch Mach 6 Tunnel. The intent of theoveralltest program is to study (both experimentally and computationally)the dynamics of the inlet unstart; this (phase I) effort examines potentialwind-tunnel blockage issues related to model sizing and the adequacyof the actuation systems in accomplishing the start and unstart. Themodel is equipped with both a moveable cowl and aft plug. Windows inthe inlet sidewalJs allow limited optical access to the internal shockstructure. In the video, flow is from right to left, and the inlet is orientedinverted with respect to flight, i.e., with the cowl on top. The plug motionis obvious because the plug is visible in the aft window. The cowl motion,however, is not as obvious because the cowl is hidden from view by theinlet s'dewall. The end of the cowl actuator arm, however, becomesvisible above the inlet sidewalls between the windows when the cowl isup (see figure 1 b of the primary document). The model is injected intothe tunnel and observed though several actuation sequences with twoplug configurations over a range of unit freestream Reynolds numberat a nominal freestream Mach number of 6. The framing rate and shutterspeed of the camera were too slow to fully capture the dynamics of theunstart but did prove sufficient to identify inlet start and unstart. Thisseries of tests indicated that the model was appropriately sized for thisfacility and identified operability limits required first to allow the inlet tostart and second to force the unstart. Author

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Includes geosciences (general); earth resources; energy productionand conversion; environment pollution; geophysics; meteorology andclimatology; and oceanography.

A95-62279* National Aeronautics and Space Administration. John F.Kennedy Space Center, Cocoa Beach, FL.APPLICATION OF AIRBORNE FIELD MILL DATA FOR USEIN LAUNCH SUPPORTRAY HARRIS-HOBBS Aeromet, Inc., Tulsa, OK, US, KATHY GIORISRI International, Menlo Park, CA, US, MICHAEL BELLMOREAeromet, Inc., Tulsa, OK, US, and ARLEEN LUNSFORD Aeromet,Inc., Tulsa, OK, US Journal of Atmospheric and Oceanic Technology(ISSN 0739-0572) vol. 11, no. 3 June 1994 p. 738-750(Contract(s)/Grant(s): DASG60-84-C-0117; DASG60-89-C-0147;F04701-90-C-0023; NAS10-11853)(HTN-95-50054) Copyright

An airborne field mill (ABFM) system was implemented on aLeaflet 36A and was used to collect electric-field and microphysicaldata for summertime convective clouds near Cape Canaveral and theKennedy Space Center. This system is described and the method usedfor calibrating it is outlined. Data from this ABFM system were used toinvestigate the relationship between the strengths of electric fields atthe boundaries of summer maritime convective clouds and the dis-tances from these cloud where the fields could first be detected by thissystem. The relationship between the electric-field strengths at theboundaries of convective clouds and selected radar-measurable pa-rameters of these clouds were also investigated. This study showspromise that the radar volume of these clouds can be used to estimatethe order of magnitude electric-field intensity. It is possible that selectedremote radar measurements could be incorporated into the launchcommit criteria as a means of providing greater confidence andflexibility for determining safe stand-off distances for launch vehiclesfrom convective clouds. Author (Hemer)

N95-13725*# Cincinnati Univ., OH. Dept of Aerospace Engineeringand Engineering Mechanics.ATMOSPHERIC AND WIND MODELING FOR ATC FinalReport

GARY L SLATER Nov. 1990 48 p(Contract(s)/Grant(s): NAG2-175)(NASA-CR-196786; NAS 1.26:196786) Avail: CASI HC A03/MF A01

The section on atmospheric modeling covers the following topics:the standard atmosphere, atmospheric variations, atmosphere require-ments for ATC, and implementation of a software model for Center/Tracon Advisory System (CTAS). The section on wind modeling coversthe following topics: wind data — NOAA profiler system; wind profileestimation; incorporation of various data types into filtering scheme;spatial and temporal variation; and software implementation into CTAS.The appendices contain Matiab codes for atmospheric routines and forwind estimation. CASI

N95-13885*# Aerojet-General Corp., Azusa, CA.EARTH OBSERVING SYSTEM (EOS)/ADVANCEDMICROWAVE SOUNDING UNIT-A (AMSU-A) SOFTWAREASSURANCE PLAN Final Report, 1-28 Feb. 1994ROBERT SCHWANTJE and CLAUDE SMITH Aug. 1994 51 p(Contract(s)/Grant(s): NAS5-32314)(NASA-CR-196059; NAS 1.26:196059; CRDL-309; REPT-10428A)Avail: CASI HC A04/MF A01

This document defines the responsibilities of Software QualityAssurance (SOA) for the development of the flight software installed inEOS/AMSU-A instruments, and the ground support software used inthe test and integration of the EOS/AMSU-A instruments. Author

N95-15749# Massachusetts Inst. of Tech., Cambridge. Lincoln Lab.TDWR SCAN STRATEGY IMPLEMENTATIONDANIEL P. HYNEK 2 Sep. 1994 19 p(Contract(s)/Grant(s): DTFA01-93-Z-02012; F19628-90-C-0002)(AD-A284877; ATC-222) Avail: CASI HC A03/MF A01

The Terminal Doppler Weather Radars (TDWR's) installed atmajor airports around the country are intended to enhance the safety ofair travel by the detection and timely warning of hazardous wind shearconditions in the airport terminal area. To meet these objectives, scanstrategies to efficiently cover the protected airspace were developedafter extensive testing at several sites with different meteorologicalenvironments. Since the topology and geometry differ at each TDWRlocation, special considerations were necessary to define the specificscan sequences for each site. This report describes the criteria used toestablish these scan sequences, including the determination of thelowest practicable elevation angle for each site - the 'surface scan,'which is used to detect microburst surface outflows, and other specialscans such as the 'MTS scan,' which is used to illuminate the remoteMoving Target Simulator (MTS). DTIC

15

MATHEMATICAL AND COMPUTER SCIENCESIncludes mathematical and computer sciences (general); computeroperations and hardware; computer programming and software; com-puter systems; cybernetics; numerical analysis; statistics and probabil-ity; systems analysis; and theoretical mathematics.

A95-62262STABILIZATION OF OBJECTS WITH UNKNOWNNONSTATIONARY PARAMETERS, USING ADAPTIVENONLINEAR CONTINUOUS CONTROL SYSTEMSB. V. ULANOV UPI, Uralsk (Russia) Izvestiya VUZ: AviatsionnayaTekhnika (ISSN 0579-2975) no. 4 October-December 1993 p. 21 -24 In RUSSIAN refs(BTN-94-EIX94461407944) Copyright

In solving problems associated with flight control, adaptive sys-

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MATHEMATICAL AND COMPUTER SCIENCES 15

terns are widely employed. To meet practical requirements such aslimitations for the amount and continuity of control, adaptive nonlinearcontinuous control has been synthesized. Such control stabilizes anobject with unknown nonstationary parameters, varying arbitrarily butwithin a limited range. The nonlinear type of control gives the opportu-nity to withstand limitations for the amount of control. El

N95-13727** Texas A&M Univ., College Station, TX. Dept. of Elec-trical Engineering.KNOWLEDGE-BASED PROCESSING FOR AIRCRAFTFLIGHT CONTROLJOHN H. PAINTER, EMILY GLASS, GREGORY ECONOMIDES, andPAUL RUSSELL Hampton, VA NASA Oct. 1994 97 p(Contract(s)/Grant(s): NAG1-1066; RTOP 505-64-52-01)(NASA-CR-194976; NAS 1.26:194976) Avail: CASI HC A05/MF A02

This Contractor Report documents research in Intelligent Controlusing knowledge-based processing in a manner dual to methods foundin the classic stochastic decision, estimation, and control discipline.Such knowledge-based control has also been called Declarative, andHybid. Software architectures were sought, employing the parallelisminherent in modem object-oriented modeling and programming. Theviewpoint adopted was that Intelligent Control employs a class ofdomain-specific software architectures having features common overa broad variety of implementations, such as management of aircraftflight, power distribution, etc. As much attention was paid to softwareengineering issues as to artificial intelligence and control issues. Thisresearch considered that particular processing methods from thestochastic and knowledge-based worlds are duals, that is, similar in abroad context. They provide architectural design concepts which serveas bridges between the disparate disciplines of decision, estimation,control, and artificial intelligence. This research was applied to thecontrol of a subsonic transport aircraft in the airport terminal area.

Author

N95-13895* Galaxy Scientific Corp., Pleasantville, NJ.ARTIFICIAL INTELLIGENCE WITH APPLICATIONS FORAIRCRAFT Final ReportL. HARRISON, P. SAUNDERS, and J. JANOWITZ Aug. 1994374 p(Contract(s)/Grant(s): DTFAO3-89-C-00043)(DOT/FAA/CT-94/41) Avail: CASI HC A16/MF A03

This report provides an overview of artificial intelligence (Al)technology, one of the more complex applications of digital systems.This report examines Al-based technology, focusing on three fields:neural networks, fuzzy logic, and expert systems. This report providesthe reader with the background and a basic understanding of thefundamentals of these fields. Another section examines aspects of theAl development environment, including languages, tools, and Al-basedhardware components. Some of the proposed aviation-related applica-tions for both civil and military aircraft, including pilot assistants anddiagnostic aids, are surveyed. Additionally, certification issues, includ-ing regulations, guidelines, and verification and validation techniquesare examined. Human factors issues relating to the use of this technol-ogy are identified and reviewed. In addition, the report identifies safetyissues and concerns over the use of this technology in airbornesystems. Author

N95-14159*# Rome Lab., Griffiss AFB, NY.GENERIC ARCHITECTURES FOR FUTURE FLIGHTSYSTEMSRICHARD J. WOOD In Research Inst. for Computing and InformationSystems, RICIS Symposium 1992: Mission and Safety Critical Sys-tems Research and Applications 16 p 30 Oct. 1992Avail: CASI HC A03/MF A03

Generic architecture for future flight systems must be based onopen system architectures (OSA). This provides the developer and

integrator the flexibility to optimize the hardware and software systemsto match diverse and unique applications requirements. When devel-oped properly OSA provides interoperability, commonality, gracefulupgradability, survivability and hardware/software transportability togreatly minimize life cycle costs and supportability. Architecture flexibil-ity can be achieved to take advantage of commercial developments bybasing these developments on vendor-neutral commercially acceptedstandards and protocols. Rome Laboratory presently has a programthat addresses requirements for OSA. Author

N95-14161*# Lockheed Engineering and Sciences Co., Houston,TX.SPACE GENERIC OPEN AVIONICS ARCHITECTURE(SGOAA): OVERVIEWRICHARD B. WRAY and JOHN R. STOVALL In Research Inst. forComputing and Information Systems, RICIS Symposium 1992: Mis-sion and Safety Critical Systems Research and Applications 16 p30 Oct. 1992Avail: CASI HC A03/MF A03

A space generic open avionics architecture created for NASA isdescribed. It will serve as the basis for entities in spacecraft coreavionics, capable of being tailored by NASA for future space programavionics ranging from small vehicles such as Moon ascent/descentvehicles to large ones such as Mars transfer vehicles or orbitingstations. The standard consists of: (1) a system architecture; (2) ageneric processing hardware architecture; (3) a six class architectureinterface model; (4) a system services functional subsystem architec-tural model; and (5) an operations control functional subsystem archi-tectural model. Author (revised)

N95-14357# Loral Systems, Inc., Orlando, FL. Advanced Distribu-tion Simulation Technology Program Office.ADST ARWA VISUAL SYSTEM MODULE SOFTWAREDESIGN DOCUMENTROBERT ANSCHUETZ 28 Feb. 1994 67 p(Contract(s)/Grant(s): N61339-91-D-0001)(AD-A283874; ADST/WDL/TR-94-00325) Avail: CASI HC A04/MFA01

The ADST ARWA Visual System Module Software Design Docu-ment describes the system design of the VSM CSCI. This SoftwareDesign Document outlines the structure and composition of the CSCIsub-functions (CSC's and CSU's) and provides a detailed descriptionof each. DTIC

N95-14652# Rockwell International Corp., Huntsville.AL RocketdyneDiv.AUTOMATED TEST ENVIRONMENT FOR A REAL-TIMECONTROL SYSTEMRONALD O. HALL In Huntsville Association of Technical Societies,TABES 1994: 10th Annual Technical and Business Exhibition andSymposium 5 p 1994(TABES PAPER 94-631) Avail: CASI HC A01/MF A04

An automated environment with hardware-in-the-loop has beendeveloped by Rocketdyne Huntsville for test of a real-time controlsystem. The target system of application is the man-rated real-timesystem which controls the Space Shuttle Main Engines (SSME). Theprimary use of the environment is software verification and validation,but it is also useful for evaluation and analysis of SSME avionicshardware and mathematical engine models. It provides a test bed forthe integration of software and hardware. The principles and skills uponwhich it operates may be applied to other target systems, such as thoserequiring hardware-in-the-loop simulation and control system develop-ment. Potential applications are in problem domains demanding highlyreliable software systems requiring testing to formal requirements andverifying successful transition to/from off-nominal system states.

Author

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16 PHYSICS

16PHYSICS

Includes physics (general); acoustics; atomic and molecular physics;nuclear and high-energy physics; optics; plasma physics; solid-statephysics; and thermodynamics and statistical physics.

A95-62635ON INTRODUCTION OF ARTIFICIAL INTELLIGENCEELEMENTS TO HEAT POWER ENGINEERINGA. F. DREGALIN KGTU, Kazan (Russia) and R. R. NAZYROVAIzvestiya VUZ: Aviatsionnaya Tekhnika (ISSN 0579-2975) no. 4October-December 1993 p. 90-94 In RUSSIAN refs(BTN-94-EIX94461407961) Copyright

The basic problems of the thermodynamic intelligence' of per-sonal computers have been outlined. The themnodynamic intellect ofpersonal computers as a concept has been introduced to heat pro-cesses occurring in engines of flying vehicles. In particular, the thermo-dynamic intellect of computers is determined by the possibility ofderiving formal relationships between thermodynamic functions. Inchemical thermodynamics, a concept of a characteristic function hasbeen introduced. El

N95-14610*# Pratt and Whitney Aircraft, East Hartford, CT.ULTRA-HIGH BYPASS RATIO JET NOISE Final ReportJOHNK. C. LOW Cleveland, OH NASA Oct. 1994 64 p(Contract(s)/Grant(s): NAS3-26618; RTOP 538-03-11)(NASA-CR-195394; E-9172; NAS 1.26:195394) Avail: CASI HC A04/MFA01

The jet noise from a 1/15 scale model of a Pratt and WhitneyAdvanced Ducted Propulsor (ADP) was measured in the UnitedTechnology Research Center anechoic research tunnel (ART) under arange of operating conditions. Conditions were chosen to match engineoperating conditions. Data were obtained at static conditions and atwind tunnel Mach numbers of 02, 0.27, and 0.35 to simulate inflighteffects on jet noise. Due to a temperature dependence of the secondarynozzle area, the model nozzle secondary to primary area ratio variedfrom 7.12 at 100 percent thrust to 7.39 at 30 percent thrust. The bypassratio varied from 10.2 to 11.8 respectively. Comparison of the data withpredictions using the current Society of Automotive Engineers (SAE)Jet Noise Prediction Method showed that the current prediction methodoverpredicted the ADP jet noise by 6 decibels. The data suggest thata simple method of subtracting 6 decibels from the SAE Coaxial JetNoise Prediction for the merged and secondary flow source compo-nents would result in good agreement between predicted and mea-sured levels. The simulated jet noise flight effects with wind tunnel Machnumbers up to 0.35 produced jet noise inflight noise reductions up to 12decibels. The reductions in jet noise levels were across the entire jetnoise spectra, suggesting that the inflight effects affected all sourcenoise components. Author

N95-14618*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.NOISE RADIATION BY INSTABILITY WAVES IN COAXIALJETSMILO D. DAHL and PHILIP J. MORRIS 1994 16 p Presentedat the 25th Ruid Dynamics Conference, Colorado Springs, CO, 20-23Jun. 1994; sponsored by AIAA(Contract(s)/Grant(s): RTOP 505-62-52)(NASA-TM-106738; E-9141; NAS 1.15:106738; AIAA PAPER 94-2190) Avail: CASI HC AOa/MF A01

In this paper predictions are made for the noise radiation fromsupersonic coaxial jets. The noise in the downstream arc of a super-sonic jet is dominated by highly directional radiation from the supersoni-cally convecting large scale structures in the jet mixing layer. Since themean flow is not described easily in terms of simple analytic functions,a numerical prediction is made for its development. The compressible

Reynolds-averaged boundary layer equations in cylindrical polar coor-dinates are solved. A mixing length turbulence model is used. Empiricalcorrelations are developed the effects of velocity and temperature ratioand Mach number. Both normal and inverted velocity profiles areconsidered. Comparisons with measurements for both single andcoaxial jets show good agreement. The large scale structures aremodeled as instability waves. The noise radiation generated by theinstability waves is determined by a matching between the innerinstability wave solution and the outer acoustic solution. Predictions aremade for the differences between the noise radiated by coaxial jets withdifferent operating conditions and a single equivalent jet with the sameexit area, thrust, and mass-flow. Author

N95-14638# Army Strategic Defense Command, Huntsville.AL. Tech-nology Integration and Matrix Management Office.AERO-OPTICS SYSTEM INTEGRATIONTROY A. STREET In Huntsville Association of Technical Societies,TABES 1994: 10th Annual Technical and Business Exhibition andSymposium 4p 1994 Sponsored by Secretary of the Army(TABES PAPER 94-604) Avail: CASI HC A01/MF A04

A Delphi study has been conducted in the field of aero-opticsresearch and development. The study includes the system compo-nents of aerodynamics, optical materials, optical analytics, opticalseekers, and aero-optical integration of the system components into anaero-optical system. The Delphi forecast data is divided into short,medium, and long range periods for planning purposes. The studyresults are applicable to the stated planning periods for endoatmosphericinterceptors with full range infrared guidance systems. Author

N95-14886*# Mississippi Univ., University, MS. Dept. of Physics andAstronomy.ATMOSPHERIC EFFECTS ON THE RISETIME ANDWAVESHAPE OF SONIC BOOMSRICHARD RASPET, HENRY E. BASS, and PATRICE BOULANGERIn NASA. Langley Research Center, High-Speed Research: 1994Sonic Boom Workshop: Atmospheric Propagation and AcceptabilityStudies p 123-136 Oct 1994Avail: CASI HC A03/MF A03

Accurate prediction of human response to sonic booms fromproposed HSCT aircraft depends on a knowledge of the waveshapeand risetime of the boom at the ground. In previous work, we havedeveloped a numerical technique to predict the combined effects ofmolecular absorption and finite wave distortion on the sonic boom as itpropagates from the aircraft to the top of the turbulent boundary layer.We have more recently developed a scattering center based model tocalculate the effects of turbulence on the sonic boom waveform as itpropagates through this boundary layer. Calculations have been per-formed using single scales of turbulence and compared to measure-ments at Edwards AFB in the late 1960's. A model of the atmosphereinvolving two scales each for convective and mechanical turbulencehas been developed and fit to meteorological data collected duringJAPE 2. Scattering calculations employing this model underpredict thenumber of unperturbed waveforms. In order to develop a more realisticmodel of the atmosphere, the JAPE 2 meteorological data has been fitto a von Karman spectrum. Results of scattering using this multi-scalemodel will be presented. The combination of finite wave effects withturbulent scattering predictions includes the principal effects of theatmosphere on the sonic boom from the HSCT. Author

N95-14887*# Pennsylvania State Univ., University Park, PA.THE EFFECT OF AIRCRAFT SPEED ON THE PENETRATIONOF SONIC BOOM NOISE INTO A FLAT OCEANVICTOR W. SPARROW In NASA. Langley Research Center, High-Speed Research: 1994 Sonic Boom Workshop: Atmospheric Propaga-tion and Acceptability Studies p 137-156 Oct. 1994Avail: CASI HC A03/MF A03

As U.S. aircraft manufacturers now have focused their HSCTefforts on overwater supersonic flight, a great deal more must be knownabout sonic booms propagating overwater and interacting with theocean. For example, it is thought that atmospheric turbulence effects

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are often much less severe over water than over land. Anotherimportant aspect of the overwater flight problems is the penetration ofthe sonic boom noise into the ocean, where there could be anenvironmental impact on sea life. This talk will present a brief review onthe penetration of sonic boom noise into a large body of water with a flatsurface. It has been determined recently that faster supersonic speedsimply greater penetration of sonic boom noise into the ocean. The newtheory is derived from the original Sawyers paper and from theknowledge that for level flight a boom's duration is proportional to thequantity M/(M(exp 2)-1)(exp 3/8) where M is the Mach number. It isfound that for depths of 10 m or less, the peak SPL varies less than 6dB over a wide range of M. For greater depths, 100 m for example,increased Mach numbers may increase the SPL by 15 dB or more.

Author

ratios and Mach number. Both normal and inverted velocity profilecoaxial jets are considered. Comparisons with measurements for bothsingle and coaxial jets show good agreement. The results from meanflow and stability calculations are used to predict the noise radiationfrom coaxial jets with different operating conditions. Comparisons aremade between different coaxial jets and a single equivalent jet with thesame total thrust, mass flow, and exit area. Results indicate that normalvelocity profile jets can have noise reductions compared to the singleequivalent jet. No noise reductions are found for inverted velocity profilejets operated at the minimum noise condition compared to the singleequivalent jet. However, it is inferred that changes in area ratio mayprovide noise reduction benefits for inverted velocity profile jets.

Author

N95-14889** Wyfe Labs., Inc., Arlington, VA.USAF SINGLE-EVENT SONIC BOOM PREDICTION MODEL:PCBOOM3KENNETH J. PLOTKIN, MICAH DOWNING, and JULIET A. PAGE InNASA. Langley Research Center, High-Speed Research: 1994 SonicBoom Workshop: Atmospheric Propagation and Acceptability Studiesp 171-184 Oct. 1994Avail: CASI HC A03/MF A03

The Air Force has developed PCBoomS, a general-purpose,single-event sonic boom prediction model. The model operates on anIBM PC or compatible, under DOS or Windows. It is accessed via anintegrated environment which controls building of input cases, runningboom calculations, displaying contours and signatures, and managingall associated data. The primary boom calculation is via a variation ofFOBOOM, the focus-boom extension of Thomas's program. Aircraftinput is either via a user-provided F-function, or simple N-wave F-functions tabulated for about 20 current aircraft. A fast boom calcula-tion, based on Plotkin's SBORT algorithms, is included for simpleN-wave F-functions in a windless atmosphere and flight altitudes up to60,000 feet. After a run is complete, the user can access an indexidentifying significant events (focal zones, beginning of footprint, etc.),then plot boom amplitude contours and signatures or spectra at anypoint in the footprint. The primary uses of this program are expected tobe operational planning and boom incident investigation. However,because of the commonality between FOBOOM and the MDBOOMprogram currently being used for low boom configuration design, thisprogram is of interest to the HSCT community, especially as supersonicroute planning activity increases. The Air Force recently conducted aflight test program to evaluate the focal zone capabilities of PCBoomS.Initial results of that program validate the prediction of focal zonegeometry, amplitudes, and waveforms. Author

N95-15059*# National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.THE AEROACOUSTICS OF SUPERSONIC COAXIAL JETSMILO D. DAHL Nov. 1994 182 p(Contract(s)/Grant(s): RTOP 505-52-52)(NASA-TM-106782; E-9235; NAS 1.15:106782) Avail: CASI HC A09/MFA02

Instability waves have been established as the dominant sourceof mixing noise radiating into the downstream arc of a supersonic jetwhen the waves have phase velocities that are supersonic relative toambient conditions. Recent theories for supersonic jet noise have usedthe concepts of growing and decaying linear instability waves forpredicting radiated noise. This analysis is extended to the prediction ofnoise radiation from supersonic coaxial jets. Since the analysis requiresa known mean flow and the coaxial jet mean flow is not described easilyin terms of analytic functions, a numerical prediction is made for itsdevelopment. The Reynolds averaged, compressible, boundary layerequations are solved using a mixing length turbulence model. Empiricalcorrelations are developed for the effects of velocity and temperature

N95-15743*# Allied-Signal Aerospace Co., Phoenix, AZ.ADVANCED TURBINE TECHNOLOGY APPLICATIONSPROJECT (ATTAP) Annual Report, 1993Jul. 1994 57 p(Contract(s)/Grant(s): DEN3-335; RTOP 778-32-21)(NASA-CR-195393; E-9171; REPT-31 -12089; NAS 1.26:195393) Avail:CASI HC A04/MF A01

Reports technical effort by AlliedSignal Engines in sixth year ofDOE/NASA funded project. Topics include: gas turbine engine designmodifications of production API) to incorporate ceramic components;fabrication and processing of silicon nitride blades and nozzles; com-ponent and engine testing; and refinement and development of criticalceramics technologies, including: hot corrosion testing and environ-mental life predictive model; advanced NDE methods for internal flawsin ceramic components; and improved carbon pulverization modelingduring impact. ATTAP project is oriented toward developing high-risktechnology of ceramic structural component design and fabrication tocarry forward to commercial production by 'bridging the gap' betweenstructural ceramics in the laboratory and near-term commercial heatengine application. Current ATTAP project goal is to support acceler-ated commercialization of advanced, high-temperature engines forhybrid vehicles and other applications. Project objectives are to provideessential and substantial early field experience demonstrating ceramiccomponent reliability and durability in modified, available, gas turbineengine applications; and to scale-up and improve manufacturing pro-cesses of ceramic turbine engine components and demonstrate appli-cation of these processes in the production environment. Author

18

SPACE SCIENCES

Includes space sciences (general); astronomy; astrophysics; lunar andplanetary exploration; solar physics; and space radiation.

N95-13717** MCAT Inst., Moffett Field, CA.PLANETARY ENTRY EXPERIMENTS Final ReportROGER A. CRAIG San Jose, CA Jul. 1994 128p(Contract(s)/Grant(s): NCC2-762)(NASA-CR-194215; NAS 1.26:194215; MCAT-94-005) Avail: CASIHC A07/MF A02

The final report summarizes the results from three research areas:(1) window design for the radiometric measurement of the forebodyradiative heating experienced by atmospheric entry spaceraft; (2)survey of the current understanding of chemical species on selectedsolar system bodies and assess the importance of measurements withregard to vehicle environment and with regard to understanding ofplanetary atmospheres with emphasis on Venus, Mars, and Titan; and(3) measure and analyze the radiation (VUV to near-IR) from the shockheated gas cap of a blunt body in an Ames arc Jet wind-tunnel facility.For individual titles, see N95-13718 through N95-13721.

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GENERAL

N95-13640# Advisory Group for Aerospace Research and Develop-ment, Neuilly-Sur-Seine (France).AGARD HIGHLIGHTS 94/21994 46p(AGARD-HIGHLIGHTS-94/2) Copyright Avail: CASIHCA03/MFA01

Various aspects of research and development in aerospacesciences are discussed. Specific topics considered include: aircraftengine technology transfer; lessons learned from a historical review ofaircraft operations; and pilot vertigo. CASI

N95-13663** National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.A REVIEW OF 50 YEARS OF AERODYNAMIC RESEARCHWITH NACA/NASAM. LEROY SPEARMAN Oct 1994 12 p(Contract(sXGrant(s): RTOP 505-69-20-01)(NASA-TM-109163; NAS 1.15:109163) Avail: CASI HC A03/MF A01

Contfhuous improvements in flight systems have occurred overthe past 50 years due, in part, to continuous improvements in aerody-namic research techniques and capabilities. This paper traces thatresearch from the first-hand perspective of the author who, beginningin 1944, has taken part in the NACA/NASA aerodynamic research effortthrough studies in low-speed wind tunnels, high-speed subsonic tun-nels, transonic tunnels, supersonic tunnels, and hypersonic tunnels.New problems were found as systems advanced from low-speedpropeller-driven designs to more sophisticated high-speed jet- androcket-propelled designs. The paper reviews some of these problemsand reflects on some of the solutions that have been developed in thecourse of various aerodynamic research programs in the past Some ofthe factors, both technical and nontechnical, that have influenced theaerodynamic design, research, and development of various flightsystems will be mentioned. Author (revised)

N95-15065*# National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.RESEARCH AND TECHNOLOGY HIGHLIGHTS, 1993Aug. 1994 264 p Contains NCSA Mosaic window view and accessinstructions as supplement(NASA-TM-4575; L-17397; NAS 1.15:4575) Avail: CASI HC A12/MFA03

This report contains highlights of the major accomplishments andapplications that have been made by Langley researchers and by ouruniversity and industry colleagues during the past year. The highlightsillustrate both the broad range of the research and technology activitiessupported by NASA Langley Research Center and the contributions ofthis work toward maintaining United States leadership in aeronauticsand space research. This report also describes some of the Center'smost important research and testing facilities. Author (revised)

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SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Subject Index Listing

SUBJECT HEADING

AIRCRAFT ENGINES— High performance parallel analysis of coupled problems

for aircraft propulsion[NASA-CR-195355) p 23 N95-10132

REPORTNUMBER

The subject heading is a key to the subjectcontent of the document. The title is used toprovide a description of the subject matter. Whenthe title is insufficiently descriptive of documentcontent, a title extension is added, separatedfrom the title by three hyphens. The accessionnumber and the page number are included ineach entry to assist the user in locating theabstract in the abstract section. If applicable, areport number is also included as an aid in iden-tifying the document. Under any one subjectheading, the accession numbers are arranged insequence.

ACCELERATED LIFE TESTSHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639

ACCELEROMETERSTest Operation Procedure (TOP): Vibration testing of

helicopter equipment[AD-A284433] p 81 N95-15815

ACCEPTABILITYHigh-Speed Research: 1994 Sonic Boom Workshop:

Atmospheric Propagation and Acceptability Studies|NASA-CP-3279| p 75 N95-14878

ACOUSTIC FATIGUESimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

ACOUSTIC SCATTERINGAtmospheric effects on the risetime and waveshape of

sonic booms p 100 N95-14886

ACOUSTICSModification of the Ames 40- by 80-fcot wind tunnel

for component acoustic testing for the second generationsupersonic transport[NASA-TM-108850] p 65 N95-13642

ACTIVE CONTROLControl of unsteady separated flow associated with the

dynamic stall of airfoils[NASA-CR-197024] . p 74 N95-14613

ACTUATORSWind-tunnel blockage and actuation systems test of a

two-dimensional scramjet inlet unstart model at Mach 6INASA-TM-109152] p 97 N95-15898

ADAPTIVE CONTROLStabilization of objects with unknown nonstationary

parameters, using adaptive nonlinear continuous controlsystemsIBTN-94-EIX94461407944] p 98 A95-62262

ADHESIVE BONDINGDamage tolerant repair techniques tor pressurized

aircraft fuselages| AD-A281982] p 65 N95-14144

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p92 N95-14456AOJOINTS

Discrete shape sensitivity equations for aerodynamicproblems[BTN-94-EIX94451393721] p 88 A95-61720

AEROACOUSTICSSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

Ultra-high bypass ratio jet noise[NASA-CR-195394] p 100 N95-14610

Numerical simulation of the SOFIA flowfield[NASA-CR-197025] p 74 N95-14612

Noise radiation by instability waves in coaxial jets[NASA-TM-106738] P 100 N95-14618

The aeroacoustics of supersonic coaxial jets(NASA-TM-1067821 p 101 N95-15059

AEROASSISTScience objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

AERODYNAMIC BALANCEFree-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237Static and dynamic force/ moment measurements in the

Eidetics water tunnel p 69 N95-14238AERODYNAMIC CHARACTERISTICS

Numerical simulation of the flow about an F-18 aircraftin the high-alpha regime p 68 N95-14232

Fourth High Alpha Conference, volume 2(NASA-CP-10143-VOL-2) p 69 N95-14239

Building complex simulations rapidly using MATRIX(x):The Space Station redesign[TABES PAPER 94-632] p 87 N95-14653

Turbulence: Engineering models, aircraft responsep84 N95-14900

Low-speed wind tunnel testing of the NPS and NASAAmes Mach 6 optimized waverider[AD-A283585] p 75 N95-15319

AERODYNAMIC COEFFICIENTSNavier-Stokes predictions of missile aerodynamics

p 74 N95-14451Low-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waverider[AD-A283585] p 75 N95-15319

AERODYNAMIC CONFIGURATIONSAerodynamic shape optimization of a HSCT type

configuration with improved surface definition(NASA-CR-197011) p67 N95-13701

Viper — Design modification[NASA-CR-197191] p 79 N95-13703

Fatigue evaluation of empennage, forward wing, andwinglets/tip fins on part 23 airplanes[PB94-196813] p 79 N95-13981

A selection ol experimental test cases for the validationof CFD codes, volume 1[AGARD-AR-303-VOL-1] p 91 N95-14201

Computational aerodynamics based on the Eulerequations(AGARD-AG-325] p 72 N95-14264

AERODYNAMIC DRAGVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air drag[HTN-95-400131 p 85 A95-62657

Scale effects on aircraft and weapon aerodynamics[AGARD-AG-3231 p 67 N95-14103

AERODYNAMIC FORCESStatic and dynamic force/moment measurements in the

Eidetics water tunnel - p 69 N95-14238AERODYNAMIC HEATING

Science objectives and performance of a radiometerand window design for atmospheric entry experiments

p85 N95-13718Thermoacoustic environments to simulate reentry

conditions P 86 N95-14096

AERODYNAMIC INTERFERENCELateral jet control for tactical missiles

p 84 N95-14448Propulsion/airframe interference for ducted preplan

engines with ground effect[NASA-CR-197110] p81 N95-14909

AERODYNAMIC LOADSDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance[NASA-TM-108855] p 65 N95-13891

Fatigue evaluation of empennage, forward wing, andwinglets/tip fins on part 23 airplanes(PB94-196813I p 79 N95-13981

Higher harmonic control analysis lor vibration reductionof helicopter rotor systems[NASA-TM-1038551 p 66 N95-14419

Extracting a representative loading spectrum fromrecorded flight data p 80 N95-14469

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281581] p 76 N95-1S465

Prediction of rotor-blade deformations due to unsteadyairloads[AD-A284467I p 81 N95-15821

AERODYNAMIC STABILITYAdd a dimension to your analysis of the helicopter low

airspeed environmentIAD-A283982] p 79 N95-14205

The Aluminum Falcon: A low cost modern commercialtransport[NASA-CR-1971801 p81 N95-15742

AERODYNAMIC STALLINGControl of unsteady separated flow associated with the

dynamic stall of airfoils[NASA-CR-197024 ] p74 N95-14613

AERODYNAMICSTurbofan propulsion simulator

[BTN-94-EIX94461290240 ] p 82 A95-61737A review of 50 years of aerodynamic research with

NACA/NASA[NASA-TM-109163] p 102 N95-13663

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992[AD-A283011] p84 N95-13687

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N95-13719

Scale effects on aircraft and weapon aerodynamics[AGARD-AG-323] p 67 N95-14103

Quality assessment tor wind tunnel testing| AGARD-AR-3041 p 67 N95-14197

Fourth High Alpha Conference, volume 1[NASA-CP-10143-VOL-1) p 67 N95-14229

Preparations for flight research to evaluate actuatedforebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Computational aerodynamics based on the Eulerequations| AGARD-AG-325] p 72 N95-14264

Missile AerodynamicsIAGARD-R-804) p73 N95-14445

Aeromechanical design of modern missilesp 73 N95-14446

Engineering Codes for aeroprediction: State-of-the-artand new methods p 73 N95-14447

High angle of attack aerodynamics p 74 N95-14450Navier-Stokes predictions of missile aerodynamics

p74 N95-14451Aero-optics system integration

[TABES PAPER 94-604) p 100 N95-14638The Aluminum Falcon: A low cost modem commercial

transport| NASA-CR-1971801 p 81 N95-15742

AEROELASTICITYUser's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)| NASA-TM-1088531 p 65 N95-13662

Development and application of structural dynamicsanalysis capabilities| NASA-CR-197229 ] p 96 N95-14922

A-1

AERONAUTICAL ENGINEERING SUBJECTINDEX

Prediction of rotor-blade deformations due to unsteadyairloads(AD-A284467] p 81 N95-15821

AERONAUTICAL ENGINEERINGFlight simulation

[BTN-94-EIX94461290242] p 84 A95-61735AGARD highlights 94/2

IAGARD-HIGHUGHTS-94/2) p 102 N95-13640Artificial intelligence with applications for aircraft

[DOT/FAA/CT-94/41] p 99 N95-13895AERONAUTICS

Proceedings of the FAA Inspection Program AreaReview(AD-A283849] p 77 N95-14350

Research and technology highlights. 1993(NASA-TM-4575I p 102 N95-15065

AEROSPACE ENGINEERINGA review of 50 years of aerodynamic research with

NACA/NASA|NASA-TM-109163| p 102 N95-13663

AEROSPACE PLANESTherrnoacoustic environments to simulate reentry

conditions P 86 N95-14096Air-breathing aerospace plane development essential:

Hypersonic propulsion flight tests(NASA-TM-1088571 p 66 N95-14921

AEROSPACE TECHNOLOGY TRANSFERAGARD highlights 94/2

(AGARD-H1GHLIGHTS-94/2I p 102 N95-13640AEROSPACE VEHICLES

Aerodynamic shape optimization of a HSCT typeconfiguration with improved surface definitionINASA-CR-1970111 p 67 N95-13701

Development and application of structural dynamicsanalysis capabilities(NASA-CR-197229] p 96 N95-14922

AEROTHERMODYNAMICSPlanetary entry experiments

INASA-CR-194215) p 101 N95-13717Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

Thermoacoustic environments to simulate reentryconditions p 86 N95-14096

An approximate Riemann solver for thermal andchemical nonequilibrium flowsI NASA-CR-1950031 p 96 N95-14912

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured gridsI NASA-CR-1950081 p 97 N95-15604

AGING (MATERIALS)Hypervelocity Impact Test Facility: A gun for hire

(TABES PAPER 94-605) p 86 N95-14639AIR BREATHING ENGINES

A graphical user interface for design and analysis ofair breathing propulsion systemsI TABES PAPER 94-616] p 83 N95-14645

AIR CARGOThe effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristics| BTN-94-EIX94461407959] p 78 A95-62633

AIR FLOWTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563AIR INTAKES

Combustion efficiency in a dual-inlet side-dump ramjetcombustor[AD-A283564] p 83 N95-15329

AIR JETSTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563AIR TRAFFIC CONTROL

Atmospheric and wind modeling for ATC| NASA-CR-1967861 p 98 N95-13725

Assessment of CTAS ETA prediction capabilitiesINASA-CR-197224] p 97 N95-15728

Groundspeed filtering for CTAS| NASA-CR-197223] p 97 N95-15785

AIRBORNE EQUIPMENTApplication of airborne field mill data for use in launch

supportIHTN-95-50054] p 98 A95-62279

Extracting a representative loading spectrum fromrecorded flight data p 80 N95-14469

AIRCRAFT ACCIDENT INVESTIGATIONAircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency,landing Simmons Airlines, Inc., d/b/a. American EagleFlight 3641, N349SB False River Air Park. New Roads.Lousiana, 1 February 1994 p 78 N95-14916

AIRCRAFT ACCIDENTSAGARD highlights 94/2

IAGARD-HIGHLIGHTS-94 /2 ] p 102 N95-13640Flight in an Adverse Environment

IAGARD-LS-197] p 77 N95-14893

Aircraft accident report: Overspeed and loss of poweron both engines during descent and power-off emergency,landing Simmons Airlines, 'nc., d/b/a, American EagleFlight 3641, N349SB False River Air Park, New Roads.Lousiana. 1 February 1994 p 78 N95-14916

Annual review of aircraft accident data: US air carrieroperations, calendar year 1992 p 78 N95-15066

AIRCRAFT ANTENNASSpiral microstrip antenna with resistance

INASA-CASE-LAR-15088-1] p91 N95-14139AIRCRAFT COMPARTMENTS

Electromagnetic reverberation characteristics of a largetransport aircraft[AD-A282923] P 82 N95-15392

AIRCRAFT CONFIGURATIONSAerodynamic shape optimization of a HSCT type

configuration with improved surface definitionINASA-CR-1970111 p 67 N95-13701

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-14255

AIRCRAFT CONSTRUCTION MATERIALSThermally stable organic polymers

(AD-A281380I p87 N95-14363Residual strength of composites with multiple impact

damageIAD-A284230] p 87 N95-14409

The Aluminum Falcon: A low cost modern commercialtransport[NASA-CR-197180] p 81 N95-15742

AIRCRAFT CONTROLFourth High Alpha Conference, volume 1

[NASA-CP-10143-VOL-1] p 67 N95-14229Comparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp 68 N95-14234

Parameter identification for X-31A at high angles ofattack p69 N95-14235

Fourth High Alpha Conference, volume 2[NASA-CP-10143-VOL-2] p 69 N95-14239

X-31 high angle of attack control system performancep 70 N95-14244

Flight test results of the F-16 aircraft modified with theaxisymmetric vectoring exhaust nozzle

p70 N95-14245Flight validation of ground-based assessment (or control

power requirements at high angles of attackp70 N95-14246

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249Computing quantitative characteristics of finite-state

real-time systemsIAD-A282839] p 83 N95-14343

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802] p 84 N95-14815

AIRCRAFT DESIGNFlight simulation

[8TN-94-EIX94461290242] p 84 A95-61735Aerodynamic shape optimization of a HSCT type

configuration with improved surface definitionINASA-CR-197011] p 67 N95-13701

Viper — Design modification(NASA-CR-197191) p 79 N95-13703

Identification of dynamic systems. Volume 3:Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2] p 79 N95-14102

Probabilistic inspection strategies for minimizing servicefailures p93 N95-14461

Computational predictive methods for fracture andfatigue p93 N95-14466

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Full-scale testing and analysis of fuselage structurep95 N95-14485

Graphical user interface for the NASA FLOPS aircraftperformance and sizing codeINASA-TM-106649] p 80 N95-14604

A SIMULINK environment for night dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802) p 84 N95-14815

Artificial neural network modeling of damaged aircraftIAD-A283227) p 80 N95-14849

Research and technology highlights. 1993INASA-TM-4575I P 102 N95-15065

More supportable T-38A enhancement study[AD-A283671] p 66 N95-15331

The F-16 multinational staged improvement program:A case study of risk assessment and risk management[AD-A281706I P 81 N95-15451

The Aluminum Falcon: A low cost modem commercialtransport| NASA-CR-197180] p81 N95-15742

AIRCRAFT ENGINESTrent engine development

| BTN-94-EIX94461290507] p 82 A95-61727On profiling a cam of an axial aviation diesel engine

by periodic splinesIBTN-94-EIX94461407946] p 82 A95-62264

On introduction ol artificial intelligence elements to heatpower engineeringIBTN-94-EIX94461407961] p 100 A95-62635

AGARD highlights 94/2IAGARD-HIGHUGHTS-94/21 p.102 N95-13640

Viper -- Design modification(NASA-CR-197191] p79 N95-13703

Turbomachinery Design Using CFDIAGARD-LS-195) p 89 N95-14127

Computational methods for preliminary design andgeometry definition in turbomachinery

p89 N95-14128Elements of a modem turbomachinery design system

p90 N95-14129Designing in three dimensions p 90 N95-14130The industrial use of CFD in the design of

turbomachinery p 90 N95-14133New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp 90 N95-14134

The role of CFD in the design processp90 N95-14135

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

AIRCRAFT HAZARDSIcing: Accretion, detection, protection

p 77 N95-14897Heavy rain effects P 78 N95-14899Aircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency.landing Simmons Airlines, Inc.. d/b/a, American EagleFlight 3641, N349SB False River Air Park, New Roads.Lousiana. 1 February 1994 p 78 N95-14916

AIRCRAFT ICINGIcing: Accretion, detection, protection

p77 N95-14897AIRCRAFT INDUSTRY

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

AIRCRAFT LANDINGAirplane takeoff and landing performance monitoring

system[NASA-CASE-LAR-14745-2-SB] p 85 N95-14415

Assessment of CTAS ETA prediction capabilitiesINASA-CR-197224J P 97 N95-15728

AIRCRAFT MAINTENANCEOrvboard avionics maintenance

(BTN-94-EIX944610470541 p 82 A95-61741Damage tolerant repair techniques for pressurized

aircraft fuselages[AD-A281982] p 65 N95-14144

Proceedings of the FAA Inspection Program AreaReview[AD-A283849] p 77 N95-14350

More supportable T-38A enhancement study[AD-A283671] p 66 N95-15331

AIRCRAFT MANEUVERSComparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp68 N95-14234

X-31 post-stall envelope expansion and tactical utilitytesting p 70 N95-14242

X-31 high angle of attack control system performancep 70 N95-14244

AIRCRAFT MODELSAdvanced distributed simulation technology advanced

rotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotorIAD-A280824] p 79 N95-14306

AIRCRAFT PARTSAdvanced method and processing technology for

complicated shape airframe part formingp80 N95-14486

AIRCRAFT PERFORMANCEViper — Design modification

INASA-CR-197191] p 79 N95-13703Scale effects on aircraft and weapon aerodynamics

(AGARD-AG-323] p 67 N95-14103High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230Numerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232

A-2

SUBJECTINDEX ATMOSPHERIC EFFECTS

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p68 N95-14234Flight validation of ground-based assessment lor control

power requirements at high angles of attackp 70 N95-14246

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Airplane takeoff and landing performance monitoringsystemINASA-CASE-LAH-14745-2-SBI p 85 N95-14415

Aircraft maneuver envelope warning system(NASA-CASE-ARC-11953-11 p 82 N95-14518

Graphical user interface for me NASA FLOPS aircraftperformance and sizing code[NASA-TM-1066491 p 80 N95-14604

Flight in an Adverse EnvironmentIAGARD-LS-197] p 77 N95-14893

Wind shear and its effects on aircraftp 77 N95-14898

Heavy rain effects p 78 N95-14899Turbulence: Engineering models, aircraft response

p84 N95-14900AIRCRAFT RELIABILITY

A method of calculating the safe fatigue life of compact,highly-stressed components p 93 N95-14464

AIRCRAFT SAFETYAGARD highlights 94/2

|AGARD-HIGHLIGHTS-94/2| p 102 N95-13640Risk analysis for the fire safety of airline passengers

IPB94-194065] p77 N95-14179The principles of flight test assessment of

flight-safety-critical systems in helicopters[AGARD-AG-300-VOL-12I p 77 N95-14199

Flight in an Adverse Environment|AGARD-LS-197| p 77 N95-14893

Heavy rain effects p 78 N95-14899Aircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency,landing Simmons Airlines, inc., d/b/a, American EagleFlight 3641. N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

TDWR scan strategy implementationIAD-A284877] p 98 N9S-15749

AIRCRAFT STABILITYStatic and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238AIRCRAFT STRUCTURES

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage ToleranceI NASA-CP-3274-PT-11 p 92 N95-14453

Elastic-plastic models tor multi-site damagep 92 N95-144S4

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p92 N95-144S6Evaluation of bonded boron/epoxy doublers for

commercial aircraft aluminum structuresp92 N95-14457

Inspecting (or widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

Testing and analysis of flat and curved panels withmultiple cracks p 93 N95-14460

Probabilistic inspection strategies tor minimizing servicefailures p 93 N95-14461

A method of calculating the safe fatigue life of compact,highly-stressed components p 93 N95-14464

Computational predictive methods for fracture andfatigue p 93 N95-14466

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p 93 N95-14467Extracting a representative loading spectrum from

recorded flight data p 80 N95-.14469The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470Fatigue reliability method with in-service inspections

p94 N95-14475Nonlinear bulging factor based on R-curve data

p 94 N95-14476Fracture mechanics validity limits p 95 N95-14480Challenges for the aircraft structural integrity program

p 80 N9S-14481The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482Large amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and plates(AD-A282440I p 96 N95-f5547

AIRCRAFT SURVIVABILITYComposite waveform generation for EMP and lightning

direct-drive testingIAD-A284159] p 92 N95-14405

AIRCRAFT WAKESWake turbulence p 75 N95-14894

AIRFOILSA selection of experimental test cases for the validation

of CFD codes, volume 1IAGARD-AR-303-VOL-1] P 91 N95-14201

Computational aerodynamics based on the EulerequationsIAGARD-AG-325) P 72 N95-14264

Control of unsteady separated flow associated with thedynamic stall of airfoils[NASA-CR-197024] p 74 N95-14613

Spectral analysis of vortex/free-surface interaction(AD-A283210I P 96 N95-14658

AIRFRAMESEvaluation of bonded boron/epoxy doublers for

commercial aircraft aluminum structuresp 92 N95-14457

Corrosion and corrosion fatigue of airframe aluminumalloys p87 N95-14465

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Advanced method and processing technology forcomplicated shape airframe part forming

p80 N95-14486AIRLINE OPERATIONS

Risk analysis for the fire safety of airline passengers|PB94-194065| p 77 N95-14179

AIRSPEEDAdd a dimension to your analysis of the helicopter low

airspeed environment|AD-A283982| p 79 N95-14205

Groundspeed filtering for CTASINASA-CR-197223] p 97 N95-15785

ALGORITHMSComputational aerodynamics based on the Euler

equationsIAGARD-AG-3251 p 72 N95-14264

Computing quantitative characteristics of finite-statereal-time systems(AD-A282839) p 83 N95-14343

ALUMINUMComposite propeller system for Dornier 328

[BTN-94-EIX94461290506] p 66 A95-61728Low-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waverider|AD-A283S85| p 75 N95-15319

Large amplitude nonlinear response of flat aluminum,and carbon fiber plastic beams and plates|AD-A282440| p 96 N95-15547

ALUMINUM ALLOYSCorrosion and corrosion fatigue of airframe aluminum

alloys p87 N95-14465Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

The effects of pitting on fatigue crack nucleation in7075-T6 aluminum alloy P 88 N95-14482

ANALYSIS (MATHEMATICS)Computational analysis of forebody tangential slot

blowing p 71 N95-14253ANECHOIC CHAMBERS

Modification of the Ames 40- by 80-foot wind tunnelfor component acoustic testing for the second generationsupersonic transportINASA-TM-108850J p 65 N95-13642

ANGLE OF ATTACKFourth High Alpha Conference, volume 1

INASA-CP-10143-VOL-1) p 67 N95-14229High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230Flight and full-scale wind-tunnel comparison of pressure

distributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p68 N95-14231

Numerical simulation of the flow about an F-16 aircraftin the high-alpha regime p 68 N95-14232

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p 68 N95-14234Parameter identification for X-31A at high angles of

attack p69 N95-14235Validation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp69 N95-14236

Fourth High Alpha Conference, volume 2[NASA-CP-10143-VOL-2] p 69 N95-14239

F-18 high alpha research vehicle: Lessons learnedp 69 N95-14240

X-31 high angle of attack control system performancep 70 N95-14244

Flight validation of ground-based assessment for controlpower requirements at high angles of attack

p 70 N95-14246

High angle of attack frying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Vcsta/F-16 Multi-Axis Thrust Vectoring (MATV) controllaw design and evaluation p 71 N95-14248

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p71 N95-14249Fourth High Alpha Conference, volume 3

[NASA-CP-10143-VOL-3I p71 N95-14251Navy and the HARV: High angle of attack tactical utility

issues p 71 N95-14252F/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255Low-energy pneumatic control of forebody vortices

p 72 N95-14256Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N9S-14257

Integration ot a mechanical forebody vortex controlsystem into the F-15 p 72 N95-14258

Engineering Codes for aeroprediction: State-of-the-artand new methods P 73 N95-14447

High angle of attack aerodynamics p 74 N95-14450Numerical simulation of the flow about the F-18 HARV

at high angle of attack(NASA-CR-1970231 p 74 N95-14614

ANNULAR FLOWCharacterization of annular two-phase gas-liquid flows

in micrograviry p 95 N95-14556APPLICATIONS PROGRAMS (COMPUTERS)

Earth Observing System (EOS)/Advanced MicrowaveSounding Unit-A (AMSU-A) software assurance plan[NASA-CR-1960591 p 98 N95-13885

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilot(NONP-NASA-SUPPL-DK-94-2802) p 84 N95-14815

Assessment of CTAS ETA prediction capabilitiesINASA-CR-1972241 p 97 N95-15728

Enhanced capabilities and updated users manual foraxial-flow turbine preliminary sizing code TURBANINASA-CR-1954051 p 76 N95-15912

APPROACH CONTROLAssessment of CTAS ETA prediction capabilities

| N ASA-CR-1972241 p97N95-15728APPROACH INDICATORS

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA.TP-3467I p 80 N95-14852

ARCHITECTURE (COMPUTERS)Elements of a modem turbomachinery design system

p 90 N95-14129Generic architectures for future flight systems

p99 N95-14159Space Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161Evolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162Automated test environment for a real-time control

system(TABES PAPER 94-631] p 99 N95-14652

ARTIFICIAL INTELLIGENCEOn introduction of artificial intelligence elements to heat

power engineering|BTN-94-EIX94461407961| p 100 A95-62635

Knowledge-based processing for aircraft flight control(NASA-CR-1949761 p 99 N95-13727

Artificial intelligence with applications for aircraft[DOT/FAA/CT-94/411 p 99 N95-I3895

Artificial neural network modeling of damaged aircraft|AD-A283227| p 80 N95-14849

ASSEMBLINGAdvancements in automatic fastening technology

|BTN-94-EIX94461290277| p 65 A95-61734ASSESSMENTS

The F-16 multinational staged improvement program:A case study of risk assessment and risk managementIAD-A281706] p 81 N95-15451

ASYMMETRYLow-energy pneumatic control of forebody vortices

p 72 N95-14256ATMOSPHERIC CIRCULATION

Atmospheric and wind modeling for ATC[NASA-CR-196786] p 98 N95-13725

ATMOSPHERIC EFFECTSHigh-Speed Research: 1994 Sonic Boom Workshop:

Atmospheric Propagation and Acceptability StudiesI NASA-CP-32791 p 75 N95-14878

A-3

ATMOSPHERIC ELECTRICITY SUBJECT INDEX

Atmospheric effects on the risetime and waveshape ofsonic booms p 100 N95-14886

ATMOSPHERIC ELECTRICITYApplication ol airborne field mill data for use in launch

supportIHTN-95-50054] p98 A95-62279

ATMOSPHERIC ENTRYPlanetary entry experiments

(NASA-CR-1942151 p 101 N95-13717Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel(AIAA PAPER 94-0086 ] p 67 N95-13720

ATMOSPHERIC MODELSAtmospheric and wind modeling for ATC

INASA-CR-1967861 p 98 N95-13725ATMOSPHERIC SOUNDING

Application of airborne field mill data for use in launchsupportIHTN-95-500541 p 98 A95-62279

ATMOSPHERIC TURBULENCEAtmospheric effects on the risetime and waveshape of

sonic booms p 100 N95-14886The effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887Turbulence: Engineering models, aircraft response

p84 N95-14900ATOMIC SPECTRA

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnelIAIAA PAPER 94-0086 ] p 67 N95-13720

ATOMIZERSCombustion efficiency in a dual-inlet side-dump ramjet

combustor(AD-A2835641 p 83 N95-15329

ATTITUDE (INCLINATION)Building complex simulations rapidly using MATRIX(x):

The Space Station redesignI TABES PAPER 94-6321 p87 N95-14653

AUTOMATIC PILOTSA SIMULINK environment for flight dynamics and control

analysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802I p 84 N95-14815

AUTOMATIONAdvancements in automatic fastening technology

IBTN-94-EIX94461290277) p 65 A95-61734AVIATION METEOROLOGY

Flight in an Adverse Environment|AGARD-LS-197| p 77 N95-14893

AVIONICSOn-board avionics maintenance

(BTN-94-EIX94461047054| p 82 A95-61741Artificial intelligence with applications for aircraft

|DOT/FAA/CT-94/4t| p 99 N95-13895Space Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161Electromagnetic reverberation characteristics ol a large

transport aircraft|AD-A282923| p 82 N95-15392

AXIAL FLOWInvestigation of heat transfer in a rotating ring gap with

the axial flow of a coolant during the rotation of the centralshaftIBTN-94-EIX94461407951] p 89 A95-62625

AXIAL FLOW TURBINESEnhanced capabilities and updated users manual for

axial-flow turbine preliminary sizing code TURBAN[NASA-CR-195405] p 76 N95-15912

AXISYMMETRIC BODIESEvaluation of 0nergy-sink stability criteria for dual-spin

spacecraft(AD-A263228I p 87 N95-14850

AZIMUTHAdd a dimension to your analysis of the helicopter low

airspeed environmentIAD-A283982J p 79 N95-14205

BBASE FLOW

Base passive porosity for drag reductionINASA-CASE-LAR-15246-1] p 91 N9S-14183

BEAMS (SUPPORTS)Large amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and platesIAD-A2824401 p 96 N95-15547

BEARINGSNew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systemsIBTN-94-EIX94331336949] p 88 A9S-61795

BENDINGBending effects of unsymmetric adhesively bonded

composite repairs on cracked aluminum panelsp 92 N95-14456

BLADE-VORTEX INTERACTIONPrediction of rotor-blade deformations due to unsteady

airloadsIAD-A284467) P 81 N95-15821

BLOCKING rWind-tunnel blockage and*actuation systems test of a

two-dimensional scramjet inlet unstart model at Mach 6INASA-TM-109152) P 97 N95-15898

BLOWERSIntegration of a mechanical forebody vortex control

system into the F-15 P 72 N95-14258BLOWING

Computational analysis of forebody tangential slotblowing P 71 N95-14253

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-14255

Low-energy pneumatic control of forebody vorticesp 72 N95-14256

BOEING 707 AIRCRAFTElectromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923I P 82 N95-15392

BOEING 747 AIRCRAFTNumerical simulation of the SOFIA flowfield

INASA-CR-1970251 P 74 N95-14612BORON-EPOXY COMPOSITES

Evaluation of bonded boron/epoxy doublers forcommercial aircraft aluminum structures

p92 N95-14457BOUNDARY CONDITIONS

Discrete shape sensitivity equations for aerodynamicproblems(BTN-94-EIX94451393721J p 88 A95-61720

Computational aerodynamics based on the EulerequationsIAGARD-AG-325] P 72 N95-14264

BOUNDARY LAYER CONTROLControl of unsteady separated flow associated with the

dynamic stall of airfoils[NASA-CR-197024] p 74 N95-14613

BOUNDARY LAYER FLOWComputational analysis in support of the SSTO flowpath

test[NASA-TM-1067571 p 89 N95-13665

BOUNDARY VALUE PROBLEMSDiscrete shape sensitivity equations for aerodynamic

problemsIBTN-94-EIX94451393721] p 88 A95-61720

BUFFETINGPressure measurements on an F/A-16 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281581] P 76 N95-15465

BULGINGNonlinear bulging factor based on R-curve data

p 94 N95-14476BUOYANCY

Activated buoyancy propulsion = Paradox Power (tm)[TABES PAPER 94-619] p 74 N95-14646

BURGER EQUATIONEffect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880BURNING RATE

Gas turbine prediffuser-combustor performance duringoperation with air-water mixture[DOT/FAA/CT-93/52] P 83 N95-15683

BYPASS RATIOUltra-high bypass ratio jet noise

INASA-CR-195394J p 100 N95-14610

CALIBRATINGDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance(NASA-TM-108855) p 65 N9S-13891

CAMSOn profiling a cam of an axial aviation diesel engine

by periodic splines[BTN-94-EIX944614079461 p 82 A95-62264

CANARD CONFIGURATIONSFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-196813J P 79 N95-13981

CAPACITORSHypervelocity Impact Test Facility: A gun for hire

I TABES PAPER 94-6051 p 86 N95-14639

CARBON FIBER REINFORCED PLASTICSLarge amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and plates(AD-A282440) P96 N95-15547

CARTESIAN COORDINATESA Cartesian, cell-based approach for adaptrvely-refined

solutions of the Euler and Navier-Stokes equationsINASA-TM-106786] P 73 N95-14297

CASCADE FLOWHeat transfer in the flow-through part of axial

compressors|BTN-94-EIX94461407949| P 89 A95-62267

CENTER OF GRAVITYFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes|PB94-196813| P79 N95-13981

CENTRIFUGAL COMPRESSORSOn calculated models for impellers of centrifugal

compressors(BTN-94-EIX94461407947I p 88 A95-62265

CENTRIFUGESSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep 86 N95-14089

CERAMICSCeramic blanket reduces maintenance costs

IBTN-94-EIX94461290278I p 77 A95-61733Advanced Turbine Technology Applications Project

(ATTAP)INASA-CR-195393] p 101 N95-15743

CHEMILUMINESCENCEDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992|AO-A283011| p84 N95-13687

CIRCUIT BOARDSElectromagnetic reverberation characteristics of a large

transport aircraft(AD-A282923J p 82 N95-15392

CIVIL AVIATIONAircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency,landing Simmons Airlines, Inc.. d/b/a. American EagleFlight 3641. N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

Research and technology highlights. 1993[NASA-TM-45751 p 102 N95-15065

CLEAN ENERGYActivated buoyancy propulsion = Paradox Power (tm)

[ TABES PAPER 94-619) P 74 N95-14646COAXIAL FLOW

Noise radiation by instability waves in coaxial jets[NASA-TM-1067381 P 100 N95-14618

The aeroacoustics of supersonic coaxial jets[NASA-TM-106782] P 101 N95-15059

COAXIAL NOZZLESNoise radiation by instability waves in coaxial jets

[NASA-TM-106738] P 100 N95-14618COCKPITS

Electromagnetic reverberation characteristics of a largetransport aircraftIAD-A282923I p 82 N95-15392

COEFFICIENT OF FRICTIONThe role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470COMBAT

Aircraft maneuver envelope warning system[NASA-CASE-ARC-11953-11 p 82 N95-14518

COMBUSTION CHAMBERSCombustion efficiency in a dual-inlet side-dump ramjet

combustor[AD-A283564] p 83 N95-15329

Gas turbine prediffuser-combustor performance duringoperation with air-water mixture[DOT/FAA/CT-93/521 p 83 N95-15683

COMBUSTION EFFICIENCYCombustion efficiency in a dual-inlet side-dump ramjet

combustor|AD-A283564| p 83 N95-15329

COMMAND AND CONTROLEvolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162COMMERCIAL AIRCRAFT

Proceedings of the FAA Inspection Program AreaReview[AD-A283849I p 77 N95-14350

Evaluation ol bonded boron/epoxy doublers forcommercial aircraft aluminum structures

P92 N95-14457Annual review of aircraft accident data: US air carrier

operations, calendar year 1992 p 78 N95-15066The Aluminum Falcon: A low cost modem commercial

transport[NASA-CR-1971BOI p 81 N95-15742

A-4

SUBJECTINDEX CONICAL FLOW

COMMUTER AIRCRAFTFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-196813] p 79 N95-13981

COMPARISONSmall gas turbines in the 21st century

[BTN-94-EIX94461290241] p 82 A95-61736Flight and full-scale wind-tunnel comparison of pressure

distributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p 68 N95-14231

COMPLEX SYSTEMSAero design of turbomachinery components: CFD in

complex systems p 90 N95-14136COMPLEX VARIABLES

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p 94 N95-14468COMPOSITE MATERIALS

Composite propeller system for Dornier 328IBTN-94-EIX94461290506] p 66 A95-61728

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

COMPOSITE STRUCTURESResidual strength of composites with multiple impact

damageIAD-A284230] p 87 N95-14409

COMPRESSIBLE BOUNDARY LAYERNoise radiation by instability waves in coaxial jets

|NASA-TM-106738| p 100 N95-14618COMPRESSIBLE FLOW

Numerical study of the effects of icing on viscous flowover wingsINASA-CR-197102] p 75 N95-14803

COMPRESSOR BLADESHeat transfer in the flow-through part of axial

compressors[BTN-94-EIX94461407949] p 89 A95-62267

Profiling of the working surface of electrodes-tools torcircle electrochemical dimensional treatment ofcompressor blades(BTN-94-EIX94461407964| p 83 A95-62638

Elements of a modern turbomachinery design systemp90 N95-14129

Designing in three dimensions p 90 N95-14130The industrial use ot CFD in the design of

turbomachinery p 90 N95-14133New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

Experimental/analytical approach to understandingmistyping in a transonic wind tunnel compressor(NASA-TM-1088331 p 95 N95-14617

COMPRESSORSExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

Gas turbine prediffuser-combustor performance duringoperation with air-water mixture|DOT/FAA/CT-93/52| p 83 N95-15683

COMPUTATIONAL FLUID DYNAMICSDiscrete shape sensitivity equations for aerodynamic

problems|BTN-94-EIX94451393721| p 88 A95-61720

User's guide for ENSAERO: A multidisciplinary programfor fluid/structural/control interaction studies of aircraft(release 1)[NASA-TM-108853] p 65 N95-13662

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992IAD-A283011) p84 N95-13687

Numerical modeling of a cryogenic fluid within a fueltankINASA-TM-4651] p 89 N95-13892

Turbomachinery Design Using CFDIAGARD-LS-1951 p 89 N95-14127

Computational methods for preliminary design andgeometry definition in turbomachinery

p89 N95-14128Designing in three dimensions p 90 N95-14130Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132The industrial use of CFD in the design of

turbomachinery p go N95-14133New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

The role of CFD in the design processp90 N95-14135

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

A selection of experimental test cases for the validationot CFD codes, volume 1|AGARD-AR-303-VOL-1| p 91 N95-14201

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

Computational aerodynamics based on the EulerequationsIAGARD-AG-325] P 72 N95-14264

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equations(NASA-TM-1067861 P 73 N9S-14297

Engineering Codes for aeroprediction: State-of-the-artand new methods P 73 N95-14447

Navier-Stokes predictions of missile aerodynamicsp 74 N95-14451

Computation of supersonic air-intakesp 74 N95-14452

Numerical simulation of the flow about the F-18 HARVat high angle of attackINASA-CR-1970231 P 74 N95-14614

Numerical study of the effects ot icing on viscous flowover wingsINASA-CR-197102] P 75 N95-14803

An approximate Riemann solver for thermal andchemical nonequilibrium flowsINASA-CR-195003] p 96 N95-14912

Development and application of structural dynamicsanalysis capabilities[NASA-CR-197229) P 96 N95-14922

Numerical design of advanced multi-element airfoils(NASA-CR-197135] P 76 N95-15762

An approach for dynamic grids(NASA-TM-1067741 p 76 N95-15853

COMPUTATIONAL GEOMETRYAerodynamic shape optimization of a HSCT type

configuration with improved surface definitionINASA-CR-197011] p67 N95-13701

Computational methods for preliminary design andgeometry definition in turbomachinery

p89 N95-14128COMPUTATIONAL GRIDS

Turbomachinery Design Using CFD[AGARD-LS-195] p 89 N95-14127

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equations[NASA-TM-106786] p 73 N95-14297

An approach for dynamic grids[NASA-TM-106774 ] p 76 N95-15853

COMPUTER AIDED DESIGNAdvancements in automatic fastening technology

[BTN-94-EIX94461290277] p 65 A95-61734Aerodynamic shape optimization of a HSCT type

configuration with improved surface definition[NASA-CR-197011) p67 N95-13701

Turbomachinery Design Using CFD| AGARD-LS-195] p89 N95-14127

Designing in three dimensions p 90 N95-14130New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802) p 84 N95-14815

COMPUTER GRAPHICSThe role of CFD in the design process

p90 N95-14135Spatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approachesINASA-TP-3467) p 80 N95-14852

COMPUTER PROGRAM INTEGRITYEarth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance planI NASA-CR-196059] p 98 N95-13B85

Automated test environment for a real-time controlsystem[TABES PAPER 94-631 ] p 99 N95-14652

COMPUTER PROGRAMMINGKnowledge-based processing for aircraft flight control

INASA-CR-194976] p 99 N95-13727Earth Observing System (EOS)XAdvanced Microwave

Sounding Unit-A (AMSU-A) software assurance plan[NASA-CR-196059] p 98 N95-13885

Elements of a modem turbomachinery design systemp 90 N95-14129

New methods, new methodology: Advanced CFD in theSnecma turbomachinery design process

p90 N95-14134ADST ARWA visual system module software design

documentIAD-A283874] p 99 N95-14357

COMPUTER PROGRAMSThe role of CFD in the design process

p 90 N95-14135Aero design of turbomachinery components: CFD in

complex systems p 90 N95-14136Generic architectures for future flight systems

p 99 N95-14159Artificial neural network modeling of damaged aircraft

IAD-A283227) p 80 N95-14849USAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889COMPUTER SYSTEMS PERFORMANCE

Earth Observing System (EOS)/Advanced MicrowaveSounding Unit-A (AMSU-A) software assurance planI NASA-CR-1960591 p 98 N95-13885

Generic architectures for future flight systemsp 99 N95-14159

Space Generic Open Avionics Architecture (SGOAA):Overview p 99 N95-14161

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

Computing quantitative characteristics of finite-statereal-time systemsIAD-A282839) p 83 N95-14343

COMPUTER TECHNIQUESOn introduction of artificial intelligence elements to heat

power engineeringIBTN-94-EIX94461407961] p 100 A95-62635

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p 94 N95-14468Extracting a representative loading spectrum from

recorded flight data p 80 N95-14469A graphical user interface for design and analysis of

air breathing propulsion systems[TABES PAPER 94-6161 p 83 N95-14645

Building complex simulations rapidly using MATRIX(x):The Space Station redesign[TABES PAPER 94-6321 p 87 N95-14653

Enhanced capabilities and updated users manual foraxial-flow turbine preliminary sizing code TURBANINASA-CR-195405] p 76 N95-15912

COMPUTERIZED SIMULATIONThe role of CFD in the design process

p 90 N95-14135ADST ARWA visual system module software design

document[AD-A283874] p 99 N95-14357

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

Fatigue reliability method with in-service inspectionsp 94 N95-14475

Numerical simulation of the SOFIA flowfield| NASA-CR-1970251 p 74 N95-14612

A graphical user interface for design and analysis ofair breathing propulsion systems[TABES PAPER 94-616] p 83 N95-14645

Automated test environment for a real-time controlsystem[TABES PAPER 94-6311 p 99 N95-14652

Building complex simulations rapidly using MATRIX(x):The Space Station redesign[TABES PAPER 94-632] p 87 N95-14653

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis ot the Beaver autopilot[NONP-NASA-SUPPL-DK-94-2802] p 84 N95-14815

Evaluation of energy-sink stability criteria for dual-spinspacecraftIAD-A283228] p 87 N95-14850

Development and application of structural dynamicsanalysis capabilities[NASA-CR-197229] p 96 N95-14922

CONFERENCESFourth High Alpha Conference, volume 1

[NASA-CP-10143-VOL-1] p 67 N95-14229Fourth High Alpha Conference, volume 2

INASA-CP-10143-VOL-2] p 69 N95-14239Fourth High Alpha Conference, volume 3

[NASA-CP-10143-VOL-3] p 71 N95-14251Proceedings of the FAA Inspection Program Area

Review[AD-A283849] p 77 N95-14350

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

High-Speed Research: 1994 Sonic Boom Workshop:Atmospheric Propagation and Acceptability Studies(NASA-CP-3279) p 75 N95-14878

CONICAL FLOWLow-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waverider(AD-A283585] p 75 N95-15319

A-5

CONTINUUM MODELING SUBJECT INDEX

CONTINUUM MODELINGDamage tolerant repair techniques for pressurized

aircraft fuselages|AD-A281982| p 65 N95-14144

CONTROLKnowledge-based processing for aircraft flight control

INASA-CR-1949761 p 99 N95-13727CONTROL EQUIPMENT

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-14255

CONTROL STABILITYStabilization of objects with unknown nonstationary

parameters, using adaptive nonlinear continuous controlsystems|BTN-94-EIX94461407944| p 98 A95-62262

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249CONTROL SURFACES

Free-to-roll tests of X.31 and F-18 subscale models withcorrelation to flight test results p 69 N95-14237

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249CONTROL SYSTEMS DESIGN

Generic architectures for future flight systemsp99 N95-14159

Space Generic Open Avionics Architecture (SGOAA):Overview p 99 N95-14161

X-31 high angle of attack control system performancep70 N95-14244

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Vista/F-16 Multi-Axis Thrust Vectoring (MATV) controllaw design and evaluation p 71 N95-14248

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p71 N95-14249Automated test environment for a real-time control

systemITABES PAPER 94-6311 p 99 N95-14652

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilot| NONP-NASA-SUPPL-OK-94-28021 p 84 N95-14815

CONTROL THEORYFourth High Alpha Conference, volume 1

INASA-CP-10143-VOL-1] p 67 N95-14229Fourth High Alpha Conference, volume 3

|NASA-CP-10143-VOL-3| p 71 N95-14251CONTROLLABILITY

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249CONVECTION CLOUDS

Application of airborne field mill data for use in launchsupport| HTN-95-500541 p 98 A95-62279

COOLANTSInvestigation of heat transfer in a rotating ring gap with

the axial flow of a coolant during the rotation of the centralshaft|BTN-94-EIX94461407951| p 89 A95-62625

CORRELATIONComputational methods tor preliminary design and

geometry definition in turbomachineryp 89 N95-14128

CORROSIONEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

Corrosion and corrosion fatigue of airframe aluminumalloys p 87 N95-14465

The effects of pitting on fatigue crack nucleation in7075-T6 aluminum alloy p 88 N95-14482

CORROSION TESTSAdvanced Turbine Technology Applications Project

(ATTAP)INASA-CR-195393] p 101 N95-15743

COST REDUCTIONCeramic blanket reduces maintenance costs

IBTN-94-EIX94461290J78J p 77 A95-61733More supportable T-38A enhancement study

|AO-A283671| p 66 N95-15331COSTS

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p86 N95-14089COWLINGS

Computational analysis in support of the SSTO flowpathtestINASA-TM-106757) p 89 N95-13665

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6|NASA-TM-109152| p 97 N95-15898

CRACK ARRESTDevelopment of the NASA/FLAGRO computer program

for analysis of airframe structures p 94 N95-14473Axial crack propagation and arrest in pressurized

fuselage P94 N95-14479CRACK GEOMETRY

Corrosion and corrosion fatigue of airframe aluminumalloys P 87 N95-14465

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p 94 N95-14468The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470Fracture mechanics validity limits p 95 N95-14480

CRACK INITIATIONInspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458The characterization of widespread fatigue damage in

fuselage structure(NASA-TM-109142) p 88 N95-14920

Fatigue in single crystal nickel superalloys|AD-A282917| p 88 N95-15415

CRACK PROPAGATIONFAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage ToleranceINASA-CP-3274-PT-11 p 92 N95-14453

Elastic-plastic models for multi-site damagep92 N95-14454

Small crack test program for helicopter materialsp 92 N95-14455

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p 92 N95-14456Evaluation of bonded boron/epoxy doublers for

commercial aircraft aluminum structuresP92 N95-14457

Inspecting for widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

Testing and analysis ol flat and curved panels withmultiple cracks p 93 N95-14460

Corrosion and corrosion fatigue of airirame aluminumalloys p87 N95-14465

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p 93 N95-14467Study of multiple cracks in airplane fuselage by

micromechanics and complex variablesp 94 N95-14468

Development of the NASA/FLAGRO computer programtor analysis of airframe structures p 94 N95-14473

Fatigue reliability method with in-service inspectionsp94 N95-14475

Nonlinear bulging factor based on R-curve datap 94 N95-14476

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

Fracture mechanics validity limits p 95 N95-14480Analysis of small crack behavior for airframe

applications p 95 N95-14484Full-scale testing and analysis of fuselage structure

p 95 N95-14485The characterization of widespread fatigue damage in

fuselage structureI NASA-TM-109142] p 88 N95-14920

Fatigue in single crystal nickel superalloys(AD-A282917] p 88 N95-15415

CRACK TIPSStudy of multiple cracks in airplane fuselage by

micromechanics and complex variablesp 94 N95-14468

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

Full-scale testing and analysis ol fuselage structurep 95 N95-14485

CRACKING (FRACTURING)Fatigue in single crystal nickel superalloys

(AD-A282917] p 88 N95-15415CRACKS

Testing and analysis of flat and curved panels withmultiple cracks p 93 N95-14460

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p 93 N95-14467Challenges for the aircraft structural integrity program

p 80 N95-U481CRASH LANDING

Aircraft accident report: Overspeed and loss ol poweron both engines during descent and power-off emergency,landing Simmons Airlines, Inc.. d/b/a. American EagleFlight 3641, N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

CRYOGENIC FLUIDSNumerical modeling of a cryogenic fluid within a fuel

tank[NASA-TM-4651] P 89 N95-13892

CRYSTAL DISLOCATIONSFatigue in single crystal nickel superalloys

[AD-A2829171 p 88 N95-15415CRYSTAL SURFACES

Fatigue in single crystal nickel superalloys(AD-A2829171 p 88 N95-15415

CURVED PANELSTesting and analysis of flat and curved panels with

multiple cracks p 93 N95-14460Nonlinear bulging factor based on R-curve data

p 94 N95-14476

DAMAGEElastic-plastic models for multi-site damage

p92 N95-14454DAMAGE ASSESSMENT

Inspecting for widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

Probabilistic inspection strategies for minimizing servicefailures p 93 N95-14461

A method of calculating the safe fatigue fife of compact.highly-stressed components p 93 N95-14464

Computational predictive methods for fracture andfatigue p 93 N95-14466

Development of the NASA/FLAGRO computer programtor analysis of airframe structures p 94 N95-14473

Challenges for the aircraft structural integrity programp80 N95-14481

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Full-scale testing and analysis of fuselage structurep95 N95-14485

Artificial neural network modeling of damaged aircraft[AD-A2832271 p 80 N95-14849

DAMPERSDynamics ol the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalanceINASA-TM-108855] p 65 N95-13891

DATA BASESA selection of experimental test cases for the validation

of CFD codes, volume 1IAGARD-AR-303-VOL-1] p 91 N95-14201

DATA SMOOTHINGNew methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

DATA STRUCTURESKnowledge-based processing for aircraft flight control

| NASA-CR-1949761 p 99 N95-13727DEBONDING (MATERIALS)

Inspecting for widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

DECISION MAKINGRisk analysis lor the fire safety of airline passengers

IPB94-194065] p77 N95-14179DEGREES OF FREEDOM

Low-speed wind tunnel testing of the NPS and NASAAmes Mach 6 optimized waveriderIAD-A283585] p 75 N95-15319

DEICERSDevelopment of anti-icing technology

IPB94-195369] p 78 N95-15439DEICING

Icing: Accretion, detection, protectionp 77 N95-14897

DELPHI METHOD (FORECASTING)Aero-optics system integration

[TABES PAPER 94-604] p 100 N95-14638DELTA WINGS

A selection ol experimental test cases for the validationof CFD codes, volume 1(AGARD-AR-303-VOL-1J p 91 N95-14201

DESIGN ANALYSISFoil bearings for gas turbine engines

IBTN-94-EIX94461290279) p 82 A95-61732Small gas turbines in the 21st century

IBTN-94-EIX94461290241) _ p 82 A95-61736Computational methods for preliminary design and

geometry definition in turbomachineryp89 N95-14128

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

The role of CFD in the design processp90 N95-14135

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

A-6

SUBJECTINDEX EULER EQUATIONS OF MOTION

Building complex simulations rapidly using MATRIX(x):The Space Station redesign[TABES PAPER 94-632) p87 N95-14653

Requirements report for SSTO vertical take-off andhorizontal landing vehicleINASA-CR-1970291 p 80 N95-14794

The Aluminum Falcon: A low cost modem commercialtransportINASA-CR-1971801 p 81 N95-15742

DHC 2 AIRCRAFTA SIMULINK environment for flight dynamics and control

analysis: Application to the OHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802] p 84 N95-148I5

DIAGNOSISDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A2830111 p 84 N95-13687

OIAMINESThermally stable organic polymers

[AD-A281380I p87 N95-14363DIESEL ENGINES

On profiling a cam of an axial aviation diesel engineby periodic splinesIBTN-94-EIX94461407946] p 82 A95-62264

DIFFERENTIAL EQUATIONSDiscrete shape sensitivity equations for aerodynamic

problemsIBTN-94-EIX94451393721) p 88 A95-61720

Computational aerodynamics based on the EulerequationsIAGARD-AG-325] p 72 N95-14264

DIGITAL SYSTEMSEvolution of a nose-wheel steering system

IBTN-94-EIX94461047056] p 78 A95-61739DIMENSIONAL ANALYSIS

Nonlinear bulging factor based on R-curve datap94 N9S-14476

DIRECTIONAL CONTROLX-31 quasi-tailless flight demonstration

p70 N95-14243DIRECTIONAL STABILITY

X-31 quasi-tailless flight demonstrationp 70 N95-14243

DISCRETE FUNCTIONSComputational aerodynamics based on the Euler

equationsIAGARD-AG-3251 p 72 N95-14264

DISPLAY DEVICESAircraft maneuver envelope warning system

[NASA-CASE-ARC-11953-11 p 82 N95-14518A graphical user interface for design and analysis of

air breathing propulsion systems[ TABES PAPER 94-6161 p 83 N95-14645

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approaches| NASA-TP.34671 p 80 N95-14B52

DISSIPATIONWake turbulence p 75 N95-14894

DIVERTERSComputational analysis in support of the SSTO flowpath

testINASA-TM-106757] p 89 N95-13665

DOCUMENTATIONEnhanced capabilities and updated users manual for

axial-flow turbine preliminary sizing code TURBANINASA-CR-1954051 p 76 N95-15912

DOPPLER RADARTDWR scan strategy implementation

|AD-A284877| . p98 N95-15749DORNIER AIRCRAFT

Composite propeller system for Domier 328IBTN-94-EIX94461290506I p 66 A95-61728

DRAG REDUCTIONBase passive porosity for drag reduction

[NASA-CASE-LAR-15246-11 p 91 N95-14183DRAINAGE

Numerical modeling of a cryogenic fluid within a fueltankINASA-TM-4651) p 89 N95-13892

DUAL SPIN SPACECRAFTEvaluation of energy-sink stability criteria for dual-spin

spacecraftIAD-A283228] p 87 N95-14850

DUCTED FAN ENGINESTurbofah propulsion simulator

[BTN-94-EIX944612902401 p 82 A95-61737DUCTED FANS

Propulsion/airframe interference for ducted propfanengines with ground effectINASA-CR-1971101 p 81 N95-14909

DYNAMIC CHARACTERISTICSFoil bearings for gas turbine engines

IBTN-94-EIX94461290279] p 82 A95-61732

DYNAMIC PRESSURELow-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waveriderIAD-A283S85] P 75 N95-15319

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A281581I P 76 N95-15465

DYNAMIC RESPONSETurbulence: Engineering models, aircraft response

p84 N95-14900DYNAMIC STABILITY

The effect of rotating loads suspended under a helicopteron their amplitude-frequency characteristics(BTN-94-EIX94461407959I P 78 A95-62633

DYNAMIC STRUCTURAL ANALYSISUser's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)INASA-TM-108853) P 65 N95-13662

Development and application of structural dynamicsanalysis capabilitiesINASA-CR-197229] P 96 N95-14922

Prediction of rotor-blade deformations due to unsteadyairloadsIAD-A284467] p 81 N95-15821

DYNAMIC TESTSLarge amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and plates|AD-A282440| p96 N95-15547

DYNAMICAL SYSTEMSIdentification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2) p 79 N95-14102

EARTH ATMOSPHEREVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air dragIHTN-95-40013] p 85 A95-62657

EARTH OBSERVING SYSTEM (EOS)Earth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance planINASA-CFM96059) p 98 N95-13885

EARTH ORBITSVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air dragIHTN-95-400131 p 85 A95-62657

ECCENTRIC ORBITSVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air dragIHTN-95-400131 p 85 A95-62657

EDUCATIONA graphical user interface for design and analysis of

air breathing propulsion systems[TABES PAPER 94-616] p 83 N95-14645

EFFICIENCYSmall gas turbines in the 21st century

[BTN-94-EIX94461290241] p 82 A95-61736Electrorheologically controlled landing gear

[BTN-94-EIX94461047055] p 78 A95-61740Computing quantitative characteristics of finite-state

real-time systemsIAD-A2828391 p 83 N95-14343

ELASTIC DEFORMATIONPrediction of rotor-blade deformations due to unsteady

airloads[AD-A284467J P 81 N95-15821

ELASTIC PROPERTIESElastic-plastic models for multi-site damage

p 92 N95-144S4ELECTRIC FIELD STRENGTH

Application ol airborne field mill data for use in launchsupportIHTN-95-500541 p 98 A95-62279

ELECTRIC FIELDSApplication of airborne field mill data for use in launch

support| HTN-95-500541 p 98 A95-62279

ELECTRICAL MEASUREMENTApplication of airborne field mill data for use in launch

support| HTN-95-500541 p 98 A95-62279

ELECTROCHEMICAL MACHININGProfiling of the working surface of electrodes-tools for

circle electrochemical dimensional treatment ofcompressor blades| BTN-94-EIX94461407964) p 83 A95-62638

ELECTRODESProfiling of the working surface of electrodes-tools for

circle electrochemical dimensional treatment ofcompressor blades[BTN-94-EIX94461407964] p 83 A95-62638

ELECTROMAGNETIC COMPATIBILITYElectromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923] p 82 N95-15392

ELECTROMAGNETIC NOISE MEASUREMENTElectromagnetic reverberation characteristics of a large

transport aircraft|AD-A282923| p 82 N95-15392

ELECTROMAGNETIC PULSESComposite waveform generation for EMP and lightning

direct-drive testing[AD-A284159) p 92 N9S-14405

ELECTRORHEOLOGICAL FLUIDSElectrorheologically controlled landing gear

|BTN-94-EIX94461047055| p 78 A95-61740ENERGY ABSORPTION

Landing gear energy absorption system[NASA-CASE-MSC-22277-1I p 96 N95-15306

ENERGY DISSIPATIONEvaluation of energy-sink stability criteria for dual-spin

spacecraft[AD-A283228I p 87 N95-14850

ENGINE AIRFRAME INTEGRATIONPropulsion/airframe interference for ducted propfan

engines with ground effect|NASA-CR-197110| p 81 N95-14909

ENGINE DESIGNTrent engine development

[BTN-94-EIX94461290507I p 82 A95-61727Foil bearings for gas turbine engines

[BTN-94-EIX94461290279I p 82 A95-61732Small gas turbines in the 21 st century

[BTN-94-EIX944612902411 p 82 A95-61736Turbomachinery Design Using CFD

[AGARD-LS-1951 p 89 N95-14127Computational methods for preliminary design and

geometry definition in turbomachineryp89 N95-14128

Elements of a modern turbomachinery design systemp90 N95-14129

Designing in three dimensions p 90 N95-14130Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp 90 N95-14134

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

Computational predictive methods for fracture andfatigue p 93 N95-14466

The Aluminum Falcon: A low cost modern commercialtransport[NASA-CR-197180] p 81 N95-15742

Advanced Turbine Technology Applications Project(ATTAP)[NASA-CR-1953931 p 101 N95-15743

ENGINE INLETSComputational analysis in support of the SSTO flowpath

test[NASA-TM-106757) p 89 N95-13665

Computation of supersonic air-intakesp 74 N95-14452

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6[NASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test(NASA-TM-1099841 p 97 N95-15899

ENGINE TESTSAdvanced Turbine Technology Applications Project

(ATTAP)[NASA-CR-195393] p 101 N95-15743

ENVIRONMENT EFFECTSThe effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887ENVIRONMENTAL SURVEYS

The effect of aircraft speed on the penetration of sonicboom noise into a flat ocean p 100 N95-14887

ERROR ANALYSISQuality assessment for wind tunnel testing

[AGARD-AR-304) p 67 N95-14197ESTIMATES

Fatigue reliability method with in-service inspectionsp 94 N95-14475

EULER EQUATIONS OF MOTIONUser's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)[NASA-TM-108853) p 65 N95-13662

The role of CFD in the design processp90 N9S-14135

Computational aerodynamics based on the Eulerequations[AGARD-AG-325] p 72 N95-14264

A-7

EULER-LAGRANGE EQUATION SUBJECTINDEX

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equationsINASA-TM-106786) p 73 N95-14297

EULER-LAGRANGE EQUATIONAn approach for dynamic grids

(NASA-TM-106774J p 76 N95-15853EXHAUST NOZZLES

Ultra-high bypass ratio jet noiseINASA-CR-195394) p 100 N95-14610

EXPERIMENT DESIGNSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

EXPERT SYSTEMSKnowledge-based processing for aircraft flight control

INASA-CR-194976J p 99 N95-13727Artificial intelligence with applications for aircraft

IDOT/FAA/CT-94/41] p 99 N95-13895EXTERNAL STORES

The effect of rotating loads suspended under a helicopteron their amplitude-frequency characteristicsIBTN-94-EIX944614079S9) p 78 A95-62633

F-111 AIRCRAFTDevelopment of a composite repair and the associated

inspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

F-15 AIRCRAFTIntegration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258Flight evaluation of pneumatic forebody vortex control

in post-Stall flight p 72 N95-14259F-16 AIRCRAFT

Flight test results of the F-16 aircraft modified with theaxisymmetric vectoring exhaust nozzle

p70 N95-14245Vista/F-16 Multi-Axis Thrust Vectoring (MATV) control

law design and evaluation p 71 N95-14248F/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254The F-16 multinational staged improvement program:

A case study of risk assessment and risk management[AD-A281706I p 81 N95-15451

F-18 AIRCRAFTFlight and full-scale wind-tunnel comparison of pressure

distributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p 68 N95-14231

Numerical simulation of the flow about an F-18 aircraftin the high-alpha regime p 68 N95-14232

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

Free-to-roll tests of X-31 and F-18 subscale models withcorrelation to flight test results p 69 N95-14237

F-18 high alpha research vehicle: Lessons learnedp 69 N95-14240

Design and development of an F/A-18 inlet distortionrake: A cost and time saving solution

p69 N95-14241Flight validation of ground-based assessment for control

power requirements at high angles of attackp 70 N95-14246

Navy and the HARV: High angle of attack tactical utilityissues p 71 N95-14252

Preparations for flight research to evaluate actuatedforebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Numerical simulation of the flow about the F-18 HARVat high angle of attack[NASA-CR-1970231 p 74 N95-14614

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume J: Steady and unsteady RMSpressure dataIAD-A281581] p 76 N95-15465

FABRICATIONAdvanced Turbine Technology Applications Project

(ATTAP)INASA-CR-195393) p 101 N95-15743

FAILURE ANALYSISInfluence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracks -p93 N95-14467

FAILURE MODESFAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

Probabilistic inspection strategies for minimizing servicefailures p 93 N95-14461

FAR ULTRAVIOLET RADIATIONPlanetary entry experiments

INASA-CR-1942151 p 101 N95-13717

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N9S-13719

FATIGUE (MATERIALS)FAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage Tolerance(NASA-CP-3274-PT-1] p 92 N95-14453

Inspecting for widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p94 N95-14468The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482Analysis of small crack behavior for airtrame

applications P 95 N95-14484The characterization of widespread fatigue damage in

fuselage structureINASA-TM-109142] p 88 N95-14920

FATIGUE LIFEInspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458Probabilistic inspection strategies for minimizing service

failures p 93 N95-14461A method of calculating the safe fatigue life of compact,

highly-stressed components p 93 N95-14464Corrosion and corrosion fatigue of airtrame aluminum

alloys p87 N95-14465Computational predictive methods for fracture and

fatigue p 93 N95-14466Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp 93 N95-14467

Extracting a representative loading spectrum fromrecorded flight data p80 N95-14469

The role of fretting corrosion and fretting fatigue inaircraft rivet hole cracking p 94 N95-14470

Fatigue reliability method with in-service inspectionsp 94 N95-14475

The effects of pitting on fatigue crack nucleation in7075-T6 aluminum alloy p 88 N95-14482

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Full-scale testing and analysis of fuselage structurep 95 N95-14485

Advanced method and processing technology forcomplicated shape airframe part forming

pBO N95-14486FATIGUE TESTS

The characterization of widespread fatigue damage infuselage structureINASA-TM-109142] p 88 N95-14920

Fatigue in single crystal nickel superalloysIAD-A282917] p 88 N95-15415

FAULT TOLERANCEChallenges for the aircraft structural integrity program

p 80 N95-14481FEEDBACK

Navy and the HARV: High angle of attack tactical utilityissues p71 N95-14252

FEEDBACK CONTROLLocal-optimal control of a flying vehicle, with final state

optimized[BTN-94-EIX94461407957] p 83 A95-62631

FIGHTER AIRCRAFTHigh angle of attack flying qualities criteria for

longitudinal rate command systems p 70 N95-14247Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255FILM COOLING

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

FILM THICKNESSCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556FINITE DIFFERENCE THEORY

Numerical modeling of a cryogenic fluid within a fueltank[NASA-TM-4651] p 89 N95-13892

An approach for dynamic grids[NASA-TM-106774 J p 76 N95-15853

FINITE ELEMENT METHODHigher harmonic control analysis for vibration reduction

of helicopter rotor systemsINASA-TM-103855] p 66 N95-14419

Elastic-plastic models for multi-site damagep92 N95-14454

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p92 N95-14456Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

Full-scale testing and analysis of fuselage structurep95 N95-14485

FINSFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-196813) P 79 N95-13981

FIRE PREVENTIONCeramic blanket reduces maintenance costs

[BTN-94-EIX944612902781 p 77 A95-61733Risk analysis for the fire safety of airline passengers

(PB94-194065I p 77 N95-14179FLAMEOUT

Gas turbine prediffuser-combustor performance duringoperation with air-water mixtureIDOT/FAA/CT-93/52I p 83 N95-15683

FLIGHT CHARACTERISTICSParameter identification for X-31A at high angles of

attack p69 N95-14235Validation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp69 N95-14236

Free-to-roll tests of X-31 and F-18 subscale models withcorrelation to flight test results p 69 N95-14237

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Fourth High Alpha Conference, volume 3INASA-CP-10143-VOL-3] p 71 N95-14251

Flight in an Adverse Environment[AGARD-LS-197] p 77 N95-14893

Turbulence: Engineering models, aircraft responsep 84 N95-14900

FLIGHT CONDITIONSFlighl in an Adverse Environment

IAGARD-LS-197] p 77 N95-14893Icing: Accretion, detection, protection

p 77 N95-14897Wind shear and its effects on aircraft

p 77 N95-14898FLIGHT CONTROL

Stabilization of objects with unknown nonstationaryparameters, using adaptive nonlinear continuous controlsystems[BTN-94-EIX94461407944] p 98 A95-62262

Local-optimal control of a flying vehicle, with final stateoptimizedIBTN-94-EIX94461407957] p 83 A95-62631

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

The principles of flight test assessment offlight-safety-critical systems in helicoptersIAGAHD-AG-300-VOL-12I p 77 N95-14199

Add a dimension to your analysis of the helicopter lowairspeed environment[AD-A283982I p 79 N95-14205

FLIGHT ENVELOPESX-31 post-stall envelope expansion and tactical utility

testing p 70 N95-14242Flight test results of the F-16 aircraft modified with the

axisymmetric vectoring exhaust nozzlep 70 N95-14245

Composite waveform generation for EMP and lightningdirect-drive testingIAD-A284159] p 92 N9S-14405

FLIGHT HAZARDSAircraft maneuver envelope warning system

(NASA-CASE-ARC-11953-11 p 82 N95-14518Flight in an Adverse Environment

| AGARD-LS-1971 p 77 N95-14893Wake turbulence p 75 N95-14894Icing: Accretion, detection, protection

p 77 N95-14897Heavy rain effects p 78 N95-14899

FLIGHT MANAGEMENT SYSTEMSThe principles of flight test assessment of

flight-safety-critical systems in helicoptersIAGARD-AG-300-VOL-12] p 77 N95-14199

Airplane takeoff and landing performance monitoringsystem[NASA-CASE-LAR-14745-2-SBI p 85 N95-14415

FLIGHT PATHSIdentification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2) p 79 N95-14102

Assessment of CTAS ETA prediction capabilities| NASA-CR-197224) p 97 N95-15728

FLIGHT SAFETYThe principles of flight test assessment of

ffight-safety-critical systems in helicopters(AGARD-AG-300-VOL-12I p 77 N95-14199

Flight in an Adverse Environment1 AGARD-LS-1971 p 77 N95-14893

Wind shear and its effects on aircraftp 77 N95-14898

Annual review of aircraft accident data: US air carrieroperations, calendar year 1992 p 78 N95-15066

TDWR scan strategy implementation[AD-A284877I p 98 N95-15749

A-8

SUBJECT INDEX GRAPHICAL USER INTERFACE

FLIGHT SIMULATIONFlight simulation

| BTN-94-EIX94461290242] p 84 A9S-6173SValidation of the NASA On/den X-31 simulation and

evaluation of mechanization techniquesp69 N95-14236

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Vista/F-16 Multi-Axis Thrust Vectoring (MATV) controllaw design and evaluation p 71 N95-14248

Advanced distributed simulation technology advancedrotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotor|AD-A280824| p 79 N9S-14306

Hypervelocity Impact Test Facility: A gun for hire(TABES PAPER 94-605] p 86 N95-14639

Turbulence: Engineering models, aircraft responsep84 N95-14900

FLIGHT SIMULATORSFlight simulation

IBTN-94-EIX94461290242] p 84 A95-61735Vertical flight terminal operational procedures. A

summary of FAA research and developmentIAD-A283550] p 85 N95-15328

FLIGHT TEST INSTRUMENTSIdentification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2] p 79 N95-14102

FLIGHT TESTSIdentification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre design[AGARD-AG-300-VOL-3-PT-2I p 79 N95-14102

The principles of flight test assessment offlight-safety-critical systems in helicoptersIAGARD-AG-300-VOL-12I p 77 N95-14199

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120ft wind tunnel p 68 N95-14231

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p68 N95-14234Parameter identification for X-31A at high angles of

attack p69 N95-14235Free-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237Fourth High Alpha Conference, volume 2

(NASA-CP-10143-VOL-2] p 69 N95-14239F-18 high alpha research vehicle: Lessons learned

p69 N95-14240X-31 post-stall envelope expansion and tactical utility

testing p 70 N95-14242X-31 quasi-tailless flight demonstration

p 70 N95-14243Flight test results of the F-16 aircraft modified with the

axisymmetric vectoring exhaust nozzlep 70 N95-14245

Flight validation of ground-based assessment for controlpower requirements at high angles of attack

p 70 N95-14246Vista/F-16 Multi-Axis Thrust Vectoring (MATV) control

law design and evaluation p 71 N95-14248Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Flight evaluation of pneumatic forebody vortex controlin post-stall flight p 72 N95-14259

An optical technique for examining aircraft shock wavestructures in flight p 96 N95-14879

Flight in an Adverse Environment[AGARD-LS-197] p 77 N95-14893

Air-breathing aerospace plane development essential:Hypersonic propulsion flight testsINASA-TM-108857) p 66 N95-14921

Test Operation Procedure (TOP): Vibration testing ofhelicopter equipment[AD-A284433] p 81 N95-15815

FLOW CHARACTERISTICSUnsteady flows in turbines: Impact on design

procedure p 90 N95-14132The industrial use of CFD in the design of

turbomachinery p 90 N95-14133FLOW COEFFICIENTS

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-14255

FLOW DISTRIBUTIONThe industrial use of CFD in the design of

turbomachinery p 90 N95-14133Numerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232Hybrid structured/unstructured grid computations for the

F/A-18 at high angle of attack p 68 N95-14233

Axis switching and spreading of an asymmetric jet: Roleof vorticrty dynamics[NASA-TM-106385] P 73 N95-14418

Computation of supersonic air-intakesp 74 N95-14452

Numerical simulation of the SOFIA flowfieldINASA-CR-197025) P 74 N95-14612

An optical technique for examining aircraft shock wavestructures in flight P 96 N95-14879

Propulsion/airframe interference for ducted preplanengines with ground effect[NASA-CR-197110] P 81 N95-14909

Gas turbine prediffuser-combustor performance duringoperation with air-water mixtureIDOT/FAA/CT-93/52] P 83 N95-15683

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test(NASA-TM-109984) p 97 N95-15899

FLOW GEOMETRYElements of a modern turbomachinery design system

p 90 N95-14129FLOW MEASUREMENT

Quality assessment for wind tunnel testing(AGARD-AR-304) p 67 N95-14197

Design and development of an F/A-18 inlet distortionrake: A cost and time saving solution

p 69 N95-14241FLOW STABILITY

Noise radiation by instability waves in coaxial jetsINASA-TM-106738) p 100 N95-14618

FLOW VISUALIZATIONNumerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232Free-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237An optical technique for examining aircraft shock wave

structures in flight p 96 N95-14879Gas turbine prediffuser-combustor performance during

operation with air-water mixture[DOT/FAA/CT-93/52] p 83 N95-15683

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test| NASA-TM-109984] p 97 N95-15899

FLUID FILMSCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556FOIL BEARINGS

Foil bearings for gas turbine enginesIBTN-94-EIX94461290279] p 82 A95-61732

FORCE DISTRIBUTIONFree-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237FOREBODIES

High Alpha Technology Program (HATP) ground testto flight comparisons P 68 N95-14230

Fourth High Alpha Conference, volume 3INASA-CP-10143-VOL-3] p 71 N95-14251

Computational analysis of forebody tangential slotblowing p 71 N95-14253

F/A-18 and F-16 forebody vortex control, static androtary-balance results p 72 N95-14254

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-142S5

Low-energy pneumatic control of forebody vorticesp 72 N95-14256

Preparations for flight research to evaluate actuatedforebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Integration of a mechanical forebody vortex controlsystem into the F-15 p 72 N95-14258

Flight evaluation of pneumatic forebody vortex controlin post-stall flight P 72 N95-14259

FORM FACTORSNonlinear bulging factor based on R-curve data

p94 N95-14476FORMING TECHNIQUES

Advanced method and processing technology forcomplicated shape airframe part forming

p80 N95-14486FRACTURE MECHANICS

Computational predictive methods for fracture andfatigue p 93 N95-14466

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p93 N95-14467Development of the NASA/FLAGRO computer program

for analysis of airframe structures p 94 N95-14473Fracture mechanics validity limits p 95 N95-14480Challenges for the aircraft structural integrity program

p 80 N95-14481Fatigue in single crystal nickel superalloys

IAD-A282917] p 88 N95-15415FREE FLOW

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test| NASA-TM-1099841 p 97 N95-15899

FREE JETSAxis switching and spreading of an asymmetric jet: Role

of vorticity dynamics[NASA-TM-106385] P 73 N95-14418

FRETTINGThe role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking P 94 N95-14470FRETTING CORROSION

The role of fretting corrosion and fretting fatigue inaircraft rivet hole cracking P 94 N95-14470

FUEL TANKSNumerical modeling of a cryogenic fluid within a fuel

tank| NASA-TM-46511 P 89 N95-13892

FULL SCALE TESTSComputational analysis of forebody tangential slot

blowing p 71 N95-14253Testing and analysis of flat and curved panels with

multiple cracks P 93 N9S-14460FUSELAGES

Damage tolerant repair techniques for pressurizedaircraft fuselagesIAD-A281982] p 65 N95-14144

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p94 N95-14468Axial crack propagation and arrest in pressurized

fuselage p 94 N95-14479Full-scale testing and analysis of fuselage structure

p95 N95-14485The characterization of widespread fatigue damage in

fuselage structure(NASA-TM-109142] P 88 N95-14920

FUZZY SYSTEMSArtificial intelligence with applications for aircraft

|DOT/FAA/CT-94/41| p 99 N95-13895

GAS FLOWAn approximate Riemann solver for thermal and

chemical nonequilibrium flowsINASA-CR-195003] p 96 N95-14912

GAS JETSThe aeroacoustics of supersonic coaxial jets

INASA-TM-106782] p 101 N95-15059Resonant interaction of a linear array of supersonic

rectangular jets: An experimental studyINASA-CR-195398] p 76 N95-15852

GAS TURBINE ENGINESFoil bearings for gas turbine engines

(BTN-94-EIX94461290279) p 82 A95-61732Small gas turbines in the 21 st century

| BTN-94-EIX94461290241] p 82 A95-61736Mechanism and technological particular features of

thermomagnetic hardening(BTN-94-EIX94461407953I p 89 A95-62627

Profiling of the working surface of electrodes-tools forcircle electrochemical dimensional treatment ofcompressor blades[BTN-94-EIX94461407964] p 83 A95-62638

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

Gas turbine prediffuser-combustor performance duringoperation with air-water mixtureIDOT/FAA/CT-93/52] p 83 N95-15683

Advanced Turbine Technology Applications Project(ATTAP)INASA-CR-195393] p 101 N95-15743

GAS TURBINESTurbomachinery Design Using CFD

IAGARD-LS-195] p 89 N95-14127GAS-LIQUID INTERACTIONS

Characterization of annular two-phase gas-liquid flowsin microgravity p 95 N95-14556

GENERAL OVERVIEWSA review of 50 years of aerodynamic research with

NACA/NASA(NASA-TM-109163] p 102 N95-13663

GLIDE LANDINGSLocal-optimal control of a flying vehicle, with final state

optimized[BTN-94-EIX94461407957] p 83 A95-62631

GLIDINGLocal-optimal control of a flying vehicle, with final state

optimizedIBTN-94-EIX94461407957] p 83 A95-62631

GOVERNMENT/INDUSTRY RELATIONSResearch and technology highlights, 1993

INASA-TM-4575] p 102 N95-15065GRAPHICAL USER INTERFACE

Graphical user interface for the NASA FLOPS aircraftperformance and sizing code[NASA-TM-106649] p 80 N95-14604

A-9

GRAPHITE-EPOXY COMPOSITES SUBJECTINDEX

A graphical user interface for design and analysis ofair breathing propulsion systems(TABES PAPER 94-616) p 83 N95-14645

GRAPHITE-EPOXY COMPOSITESResidual strength of composites with multiple impact

damageIAD-A284230) p 87 N95-14409

GRAVITATIONTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563GRID GENERATION (MATHEMATICS)

Aerodynamic shape optimization of a HSCT typeconfiguration with improved surface definition(NASA-CR-1970111 p 67 N95-13701

The role of CFD in the design processp90 N95-14135

Computational aerodynamics based on the Eulerequations|AGARD-AG-325| p 72 N95-14264

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equations[NASA-TM-106786] p 73 N95-14297

An approach for dynamic grids[NASA-TM-106774] p 76 N95-15853

GROUND EFFECT (AERODYNAMICS)Propulsion/airframe interference for ducted preplan

engines with ground effectINASA-CR-197110] p 81 N95-14909

GROUND SPEEDGroundspeed filtering for CTAS

|NASA-CR-197223| p 97 N95-15785GROUND TESTS

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p86 N95-14089High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230GUIDANCE SENSORS

Aero-optics system integration| TABES PAPER 94-604) p 100 N95-14638

GYROSCOPIC STABILITYEvaluation of energy-sink stability criteria for dual-spin

spacecraft| AD-A2832281 p 87 N95-14850

HHARDENING (MATERIALS)

Mechanism and technological particular features ofthermomagnetic hardening[BTN-94-EIX94461407953 ] p 89 A95-62627

HARMONIC CONTROLHigher harmonic control analysis for vibration reduction

of helicopter rotor systemsINASA-TM-103855] p 66 N95-14419

HEAD-UP DISPLAYSAirplane takeoff and landing performance monitoring

systemINASA-CASE-LAR-14745-2-SB) p 85 N95-14415

HEAT ENGINESAdvanced Turbine Technology Applications Project

(ATTAP)INASA-CR-195393) p 101 N95-15743

HEAT FLUXHypersonic engine leading edge experiments in a high

heat flux, supersonic flow environment| NASA-TM-1067421 p 91 N95-14299

HEAT GENERATIONOn introduction of artificial intelligence elements to heat

power engineering| BTN-94-EIX94461407961] p 100 A95-62635

HEAT RESISTANT ALLOYSFatigue in single crystal nickel superalloys

|AD-A282917| p 88 N95-15415HEAT TRANSFER

Heat transfer in the flow-through part of axialcompressorsIBTN-94-EIX94461407949) p 89 A95-62267

Investigation of heat transfer in a rotating ring gap withthe axial flow of a coolant during the rotation of the centralshaft[BTN-94-EIX94461407951] p 89 A95-62625

HEAT TRANSFER COEFFICIENTSEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficientsIAO-A283854) p 91 N95-14351

HELICOPTER PERFORMANCEThe effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristicsIBTN-94-EIX94461407959) p 78 A95-62633

Add a dimension to your analysis of the helicopter lowairspeed environment| AD-A2839B2] p 79 N95-14205

HELICOPTERSThe principles of flight test assessment of

flight-safety-critical systems in helicoptersIAGARD-AG-300-VOL-12] p 77 N95-14199

Higher harmonic control analysis for vibration reductionof helicopter rotor systems| NASA-TM-1038551 p 66 N95-14419

Small crack test program for helicopter materialsp92 N95-14455

A method of calculating the safe fatigue lite of compact,highly-stressed components p 93 N95-14464

Vertical flight terminal operational procedures. Asummary of FAA research and developmentIAD-A283550) P 85 N95-15328

Test Operation Procedure (TOP): Vibration testing ofhelicopter equipmentIAD-A284433I P 81 N95-15815

HIGH PRESSUREEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

HIGH REYNOLDS NUMBERNumerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232Numerical simulation of the flow about the F-18 HARV

at high angle of attackINASA-CR-197023) p 74 N95-14614

HIGH SPEEDHigh-Speed Research: 1994 Sonic Boom Workshop:

Atmospheric Propagation and Acceptability Studies(NASA-CP-3279] p 75 N95-14878

HIGH TEMPERATURE ENVIRONMENTSHypersonic engine leading edge experiments in a high

heat flux, supersonic flow environment| NASA-TM-106742) p 91 N95-14299

HISTORIESA review of 50 years of aerodynamic research with

NACA/NASAINASA-TM-109163] p 102 N95-13663

HOLOGRAPHIC INTERFEROMETRYDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A283011] p84 N95-13687

HUBSComposite propeller system for Domier 328

| BTN-94-EIX94461290506] p 66 A95-61728Dynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance| NASA-TM-108855] p 65 N95-13891

HUMAN FACTORS ENGINEERINGAircraft maneuver envelope warning system

[ NASA-CASE-ARC-11953-1 ] p 82 N95-14518A graphical user interface for design and analysis of

air breathing propulsion systems(TABES PAPER 94-616] p 83 N95-14645

HUMAN-COMPUTER INTERFACEA graphical user interface for design and analysis of

air breathing propulsion systems[TABES PAPER 94-616] . p 83 N95-14645

HUMIDITYEffect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880HYDRAULIC EQUIPMENT

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

HYDRODYNAMICSNew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systems[BTN-94-EIX94331336949] p 88 A95-61795

HYPERSONIC AIRCRAFTNumerical modeling of a cryogenic fluid within a fuel

tank(NASA-TM-4651) p 89 N95-13892

HYPERSONIC FLIGHTHypersonic engine leading edge experiments in a high

heat flux, supersonic flow environment[NASA-TM-106742] p 91 N95-14299

Air-breathing aerospace plane development essential:Hypersonic propulsion flight tests| NASA-TM-108857] p 66 N95-14921

HYPERSONIC FLOWThermoacoustic environments to simulate reentry

conditions p 86 N95-14096Laminar and turbulent flow computations of Type 4

shock-shock interference aerothermal loads usingunstructured grids[NASA-CR-195008] p 97 N95-15604

HYPERSONIC HEAT TRANSFERHypersonic engine leading edge experiments in a high

heat flux, supersonic flow environment| NASA-TM-1067421 p91 N95-14299

HYPERSONIC INLETSComputational analysis in support of the SSTO flowpath

test| NASA-TM-1067571 p89N95-13665

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjel inlet unstart model at Mach 6| NASA-TM-1091521 p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test[NASA-TM-109984] p 97 N95-15899

HYPERSONIC SPEEDLow-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waverider[AD-A283585] p 75 N95-15319

HYPERSONIC WIND TUNNELSWind-tunnel blockage and actuation systems test of a

two-dimensional scramjet inlet unstart model at Mach 6[NASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test[ NASA-TM-109984] p 97 N95-15899

HYPERSONICSAn approximate Riemann solver for thermal and

chemical nonequilibrium flows| NASA-CR-1950031 p 96 N95-14912

HYPERVELOCITY IMPACTHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639

ICE PREVENTIONIcing: Accretion, detection, protection

p 77 N95-14897Development of anti-icing technology

(PB94-195369] p 78 N95-15439IMAGE CONVERTERS

Hypervelocity Impact Test Facility: A gun for hire[TABES PAPER 94-605] p 86 N95-14639

IMPACT DAMAGEResidual strength of composites with multiple impact

damageIAD-A284230] p 87 N95-14409

IMPACT TESTSHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639IMPELLERS

On calculated models for impellers of centrifugalcompressors| BTN-94-EIX94461407947] p 88 A95-62265

IN SITU MEASUREMENTApplication of airborne field mill data for use in launch

supportIHTN-95-50054] p 98 A95-62279

Science objectives and performance of a radiometerand window design for atmospheric entry experiments

p85 N95-13718IN-FLIGHT MONITORING

Design and development of an F/A-1B inlet distortionrake: A cost and time saving solution

p 69 N95-14241Airplane takeoff and landing performance monitoring

system[NASA-CASE-LAR-14745-2-SB] p 85 N95-14415

Test Operation Procedure (TOP): Vibration testing ofhelicopter equipmentIAD-A284433) p81 N95-15815

INFERENCENew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systems[BTN-94-EIX943313369491 p 88 A95-61795

INFRARED INSTRUMENTSAero-optics system integration

I TABES PAPER 94-604] p 100 N95-14638INJECTION

Combustion efficiency in a dual-inlet side-dump ramjetcombustor[AD-A283564] p 83 N95-15329

INLET FLOWComputational analysis in support of the SSTO flowpath

test[NASA-TM-106757] p 89 N95-13665

Design and development of an F/A-18 inlet distortionrake: A cost and time saving solution

p69 N95-14241Wind-tunnel blockage and actuation systems test of a

two-dimensional scramjet inlet unstart model at Mach 6[NASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test| NASA-TM-109984] p 97 N95-15899

A-10

SUBJBCTINDEX MATHEMATICAL MODELS

INSPECTIONProceedings of the FAA Inspection Program Area

ReviewIAD-A283849) p 77 N95-14350

Probabilistic inspection strategies for minimizing servicefailures P 93 N95-14461

A method of calculating the safe fatigue lite of compact,highly-stressed components p 93 N95-14464

Computational predictive methods for fracture andfatigue P 93 N95-14466

Fatigue reliability method with in-service inspectionsp 94 N95-14475

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

Full-scale testing and analysis of fuselage structurep 95 N95-14485

INTERPLANETARY DUSTHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639INVISCID FLOW

An approximate Riemann solver for thermal andchemical nonequilibrium flowsINASA-CR-1950031 p 96 N95-14912

ITERATIVE SOLUTIONAero-optics system integration

| TABES PAPER 94-604 ] p 100 N95-14638

J INTEGRALElastic-plastic models for multi-site damage

p92 N95-14454JET AIRCRAFT

The Aluminum Falcon: A low cost modern commercialtransportINASA-CR-1971801 p 81 N95-15742

JET AIRCRAFT NOISEUltra-high bypass ratio jet noise

[NASA-CR-195394! p 100 N95-14610Noise radiation by instability waves in coaxial jets

|NASA-TM-106738| p 100 N95-14618The aeroacoustics of supersonic coaxial jets

|NASA-TM-106782| p 101 N95-15059JET CONTROL

Lateral jet control lor tactical missilesp84 N95-14448

JET FLOWLateral jet control for tactical missiles

p84 N95-14448JET MIXING FLOW

Axis switching and spreading of an asymmetric jet: Roleof vorticity dynamicsINASA-TM-106385] p 73 N95-14418

Noise radiation by instability waves in coaxial jets[NASA-TM-1067381 p 100 N95-14618

JOINTS (JUNCTIONS)The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470

KALMAN FILTERSGroundspeed filtering for CTAS

INASA-CR-1972231 p 97 N95-15785KINETIC ENERGY

Activated buoyancy propulsion = Paradox Power (tm)[TABES PAPER 94-619] p 74 N95-14646

Spectral analysis of vortex/free-surface interaction[AD-A283210] p 96 N95-14658

KNOWLEDGE BASED SYSTEMSOn-board avionics maintenance

|BTN-94-EIX94461047054| p 82 A95-61741KNOWLEDGE BASES (ARTIFICIAL INTELLIGENCE)

Knowledge-based processing for aircraft flight control[NASA-CR-1949761 p 99 N95-13727

LAMINAR FLOWTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563Laminar and turbulent flow computations of Type 4

shock-shock interference aerothermal loads usingunstructured grids[NASA-CR-195008] p 97 N95-15604

LAMINAR FLOW AIRFOILSViper — Design modification

[NASA-CR-1971911 p 79 N95-13703LAMINATES

Damage tolerant repair techniques tor pressurizedaircraft fuselages(AD-A281982] p 65 N95-14144

LANDING AIDSAssessment of CTAS ETA prediction capabilities

[NASA-CR-197224] p 97 N95-15728LANDING GEAR

Electrorheologically controlled landing gear(BTN-94-EIX94461047055] p 78 A95-61740

Soft landing on the slope surface of a landing vehiclewith an air shock-absorber of forced pressurization[BTN-94-EIX94461407941] p 85 A95-62259

Landing gear energy absorption systemINASA-CASE-MSC-22277-1] p 96 N95-15306

The Aluminum Falcon: A low cost modem commercialtransport[NASA-CR-1971801 p81 N95-15742

LANDING LOADSLanding gear energy absorption system

INASA-CASE-MSC-22277-1 | p 96 N95-15306LANDING SIMULATION

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approaches| NASA-TP-34671 p 80 N95-14852

LAP JOINTSFull-scale testing and analysis of fuselage structure

p 95 N95-14485The characterization of widespread fatigue damage in

fuselage structureINASA-TM-109142] P 88 N95-14920

LASER DOPPLER VELOCIMETERSDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A283011) p84 N95-13687

LASER INDUCED FLUORESCENCEDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992| AD-A2830111 p 84 N95-13687

LASER RANGE FINDERSPrecision orbit determination of altimetric satellites

p86 N95-14282LASERS

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992|AD-A283011| p84 N95-13687

LATERAL CONTROLFlight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259Lateral jet control for tactical missiles

p84 N95-14448LAUNCH VEHICLE CONFIGURATIONS

Requirements report for SSTO vertical take-off andhorizontal landing vehicleINASA-CR-197029] p 80 N95-14794

LEADING EDGE FLAPSHybrid structured/unstructured grid computations for the

F/A-18 at high angle of attack p 68 N95-14233LEADING EDGES

Hypersonic engine leading edge experiments in a highheat flux, supersonic flow environmentINASA-TM-106742] p 91 N95-14299

Control of unsteady separated flow associated with thedynamic stall of airfoils|NASA-CR-197024| p 74 N95-14613

LEAR JET AIRCRAFTApplication of airborne field mill data for use in launch

supportIHTN-95-50054 ] p 98 A95-62279

Characterization of annular two-phase gas-liquid flowsin microgravity p 95 N95-14556

LIFE (DURABILITY)Effect of surface roughness on local film cooling

effectiveness and heat transfer coefficients|AD-A283854| p 91 N95-14351

LIFE CYCLE COSTSGeneric architectures for future flight systems

p 99 N95-14159LIFT

Scale effects on aircraft and weapon aerodynamicsIAGARD-AG-323] p 67 N95-14103

Numerical design of advanced multi-element airfoilsI NASA-CR-197135] p 76 N95-15762

LIGHTNINGApplication of airborne field mill data for use in launch

support| HTN-95-50054 J p 98 A95-62279

Composite waveform generation for EMP and lightningdirect-drive testingIAD-A284159] p 92 N95-14405

LINE SPECTRAVUV shock layer radiation in an arc-jet wind tunnel

experiment p 67 N95-13719LINEAR ARRAYS

Resonant interaction of a linear array of supersonicrectangular jets: An experimental studyINASA-CR-195398] p 76 N95-15852

LIQUID-GAS MIXTURESCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556LIQUID-VAPOR INTERFACES

Numerical modeling of a cryogenic fluid within a fueltank[NASA-TM-46511 p 89 N95-13892

Characterization of annular two-phase gas-liquid flowsin microgravity p 95 N95-14556

LOADS (FORCES)The effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristics|BTN-94-EIX94461407959| p 78 A95-62633

Fatigue evaluation of empennage, forward wing, andwinglets/tip fins on part 23 airplanes(PB94-196813] p79 N95-13981

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p 86 N95-14089LOGISTICS

More supportable T-38A enhancement study(AD-A283671] p 66 N95-15331

LONGITUDINAL CONTROLComparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp 68 N95-14234

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

LOW SPEEDLow-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waverider[AD-A283585] p 75 N95-15319

MMAGNETIC FIELDS

Mechanism and technological particular features ofthermomagnetic hardening[BTN-94-EIX94461407953] p 89 A95-62627

MAINTENANCECeramic blanket reduces maintenance costs

IBTN-94-EIX94461290278] p 77 A95-61733MANAGEMENT PLANNING

The F-16 multinational staged improvement program:A case study of risk assessment and risk managementIAD-A281706] p 81 N95-15451

MANEUVERABILITYParameter identification for X-31A at high angles of

attack p 69 N95-14235Vcsta/F-16 Multi-Axis Thrust Vectoring (MATV) control

law design and evaluation p 71 N95-14248MANEUVERS

Aircraft maneuver envelope warning systemINASA-CASE-ARC-11953-1] p 82 N95-14518

MANUALSEnhanced capabilities and updated users manual for

axial-flow turbine preliminary sizing code TURBAN[NASA-CR-195405] p 76 N95-15912

MARINE ENVIRONMENTSThe effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887MASS FLOW

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody slot blowing p 72 N95-14255

MATHEMATICAL MODELSOn calculated models for impellers of centrifugal

compressors[BTN-94-EIX944614079471 p 88 A95-62265

Numerical modeling of a cryogenic fluid within a fueltankINASA-TM-4651 ] p 89 N95-13892

Unsteady flows in turbines: Impact on designprocedure p 90 N95-14132

Add a dimension to your analysis of the helicopter lowairspeed environment[AD-A283982I p 79 N95-14205

Numerical simulation of the flow about an F-18 aircraftin the high-alpha regime p 68 N95-14232

Validation of the NASA Dryden X-31 simulation andevaluation of mechanization techniques

p 69 N95-14236Higher harmonic control analysis for vibration reduction

of helicopter rotor systems[NASA-TM-103855] p 66 N95-14419

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

Elastic-plastic models for multi-site damagep 92 N95-14454

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p 92 N95-14456The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470

A-11

MATRICES (MATHEMATICS) SUBJECT INDEX

Development of a composite repair and the associatedinspection intervals for the F-111C stillener runoutregion p 66 N95-14477

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

Fracture mechanics validity limits p 95 N95-14480Noise radiation by instability waves in coaxial jets

[NASA-TM-106738] p 100 N95-14618USAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889MATRICES (MATHEMATICS)

Higher harmonic control analysis for vibration reductionof helicopter rotor systems[NASA-TM-103855) p 66 N95-14419

MATRIX MATERIALSThermally stable organic polymers

|AD-A281380| p 87 N95-14363MCDONNELL DOUGLAS AIRCRAFT

Evolution of a nose-wheel steering systemIBTN-94-EIX944610470S6I p 78 A95-61739

MEASURING INSTRUMENTSApplication of airborne field mill data for use in launch

supportIHTN-95-50054] p 98 A95-62279

METAL FATIGUEFatigue in single crystal nickel superalloys

|AD-A282917| p 88 N95-15415METAL FIBERS

Damage tolerant repair techniques for pressurizedaircraft fuselages(AD-A2B1982] p 65 N95-14144

METAL SHEETSInfluence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

METALLOGRAPHYThe effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482METEOROLOGICAL RADAR

TDWR scan strategy implementationIAD-A284877] p 98 N95-15749

MICROGRAVITYCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556MICROMECHANICS

Study of multiple crack; in airplane fuselage bymicromechanics and complex variables

p 94 N95-14468MICROPARTICLES

Activated buoyancy propulsion = Paradox Power (tm)| TABES PAPER 94-619] p 74 N95-14646

MICROSTRIP ANTENNASSpiral microstrip antenna with resistance

|NASA-CASE-LAR-1S088-1| p 91 N95-14139MICROSTRUCTURE

Analysis of small crack behavior for airframeapplications p 95 N95-14484

MICROWAVE LANDING SYSTEMSSpatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-34671 p 80 N95-14852

MILITARY AIRCRAFTProceedings of the FAA Inspection Program Area

Review|AD-A283849| p 77 N95-14350

Research and technology highlights, 1993INASA-TM-4575I p 102 N95-15065

MILITARY HELICOPTERSAdvanced distributed simulation technology advanced

rotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotor| AD-A280824] p 79 N95-14306

MISSILE CONFIGURATIONSA selection of experimental test cases for the validation

of CFD codes, volume 1(AGARD-AR-303-VOL-1I p 91 N95-14201

Missile AerodynamicsIAGARD-R-804) p 73 N95-14445

Engineering Codes for aeroprediction: State-of-the-artand new methods p 73 N95-14447

Navier-Stokes predictions of missile aerodynamicsp 74 N95-14451

MISSILE CONTROLLateral jet control for tactical missiles

p84 N95-14448MISSILE DESIGN

Aeromechanical design of modem missilesp73 N95-14446

MISSILESMissile Aerodynamics

IAGARD-R-804] p 73 N95-14445Aeromechanical design of modem missiles

p 73 N95-14446Engineering Codes for aeroprediction: State-of-the-art

and new methods p 73 N95-14447

High angle of attack aerodynamics p 74 N95-14450Navier-Stokes predictions of missile aerodynamics

p 74 N95-14451MISSION PLANNING

Generic architectures for future flight systemsp99 N95-14159

Space Generic Open Avionics Architecture (SGOAA):Overview p 99 N95-14161

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

MIXING LAYERS (FLUIDS)Resonant interaction of a linear array of supersonic

rectangular jets: An experimental studyINASA-CR-1953981 p 76 N95-15852

MODAL RESPONSEDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalanceINASA-TM-1088551 p 65 N95-13891

MODESExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressor[NASA-TM-108833) p 95 N95-14617

MOLECULAR OSCILLATIONSActivated buoyancy propulsion = Paradox Power (tm)

[TABES PAPER 94-619) p 74 N95-14646MOMENTUM TRANSFER

Activated buoyancy propulsion = Paradox Power (tm)I TABES PAPER 94-619) p 74 N95-14646

MONTE CARLO METHODFatigue reliability method with in-service inspections

p94 N95-14475MOTION SIMULATION

Flight simulation(BTN-94-EIX944612902421 p 84 A95-61735

NNASA PROGRAMS

A review ol 50 years of aerodynamic research withNACA/NASA| NASA-TM-109163) p 102 N95-13663

Research and technology highlights, 1993[NASA-TM-4575] p 102 N95-15065

NASA SPACE PROGRAMSSpace Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161NATIONAL AIRSPACE SYSTEM

Vertical flight terminal operational procedures. Asummary of FAA research and development[AD-A283550] p 85 N95-15328

NAVIER-STOKES EQUATIONUser's guide for ENSAERO: A multidisciplinary program

tor fluid/structural/control interaction studies of aircraft(release 1)INASA-TM-108853] p 65 N95-13662

Numerical modeling of a cryogenic fluid within a fueltank| NASA-TM-4651 ] p 89 N95-13892

The role of CFD in the design processp90 N95-14135

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equations(NASA-TM-106786] p 73 N95-14297

Navier-Stokes predictions of missile aerodynamicsp74 N95-14451

Numerical study of the effects of icing on viscous flowover wings(NASA-CR-197102] p 75 N95-14803

NAVIGATION AIDSSpatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approachesINASA-TP-3467) p 80 N95-14852

NAVYNavy and the HARV: High angle of attack tactical utility

issues p 71 N95-14252NEAR INFRARED RADIATION

VUV shock layer radiation in an arc-jet wind tunnelexperiment p67 N95-13719

NEURAL NETSArtificial intelligence with applications for aircraft

[DOT/FAA/CT-94/411 p 99 N95-13895Artificial neural network modeling of damaged aircraft

IAD-A283227) p 80 N95-14849NEWTON METHODS

Higher harmonic control analysis for vibration reductionof helicopter rotor systems(NASA-TM-103855] p 66 N95-14419

NICKEL ALLOYSFatigue in single crystal nickel superalloys

IAD-A282917J p 88 N95-15415

NOISE GENERATORSNoise radiation by instability waves in coaxial jets

(NASA-TM-106738) P 100 N95-14618Resonant interaction of a linear array of supersonic

rectangular jets: An experimental study[NASA-CR-195398] P 76 N95-15852

NOISE INTENSITYUltra-high bypass ratio jet noise

| NASA-CR-195394) P 100 N95-14610NOISE PREDICTION

Noise radiation by instability waves in coaxial jets| NASA-TM-1067381 P 100 N95-14618

NOISE PREDICTION (AIRCRAFT)Ultra-high bypass ratio jet noise

INASA-CR-195394) p 100 N95-14610The aeroacoustics of supersonic coaxial jets

| NASA-TM-1067821 P 101 N95-15059NOISE REDUCTION

Modification of the Ames 40- by 80-foot wind tunnelfor component acoustic testing for the second generationsupersonic transport(NASA-TM-1088501 P 65 N95-13642

Ultra-high bypass ratio jet noiseINASA-CR-1953941 p 100 N95-14610

The aeroacoustics of supersonic coaxial jets(NASA-TM-1067821 P 101 N95-15059

Resonant interaction of a linear array of supersonicrectangular jets: An experimental studyI NASA-CR-195398) P 76 N95-15852

NONDESTRUCTIVE TESTSAnalysis of small crack behavior for airframe

applications P 95 N95-14484Advanced Turbine Technology Applications Project

(ATTAP)INASA-CR-1953931 p 101 N95-15743

NONEOUILIBRIUM FLOWAn approximate Riemann solver for thermal and

chemical nonequilibrium flows(NASA-CR-195003] p 96 N95-14912

NONEOUILIBRIUM RADIATIONMeasured and calculated spectral radiation from a blunt

body shock layer in an arc-jet wind tunnel(AIAA PAPER 94-0086) p 67 N95-13720

NONLINEAR SYSTEMSIdentification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2] p 79 N95-14102

NONLINEAR ITYFracture mechanics validity limits p 95 N95-14480

NOSE WHEELSEvolution of a nose-wheel steering system

(BTN-94-EIX94461047056] p 78 A95-61739NOZZLE GEOMETRY

Ultra-high bypass ratio jet noiseINASA-CR-195394] p 100 N95-14610

OBJECT-ORIENTED PROGRAMMINGKnowledge-based processing for aircraft flight control

(NASA-CR-194976] p 99 N95-13727OCEAN SURFACE

Precision orbit determination of altimetric satellitesp 86 N95-14282

OPTICAL MATERIALSAero-optics system integration

(TABES PAPER 94-604) p 100 N95-14638OPTIMAL CONTROL

Local-optimal control of a flying vehicle, with final stateoptimized(BTN-94-EIX94461407957I p 83 A95-62631

OPTIMIZATIONTurbomachtnery Design Using CFD

(AGARD-LS-195] p 89 N95-14127Computational methods for preliminary design and

geometry definition in turbomachineryp89 N95-14128

Elements of a modern turbomachinery design systemp90 N95-14129

ORBIT CALCULATIONPrecision orbit determination of altimetric satellites

p86 N95-14282ORBITAL MECHANICS

Variations of perturbations in perigee height witheccentricity for artificial Earth's satellites due to air drag(HTN-95-40013] p 85 A95-62657

OXIDATIONEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficients(AD-A283854I p 91 N95-14351

A-12

SUBJECTINDEX REAL TIME OPERATION

PANELSBending effects of unsymmetric adhesively bonded

composite repairs on cracked aluminum panelsp 92 N95-14456

Full-scale testing and analysis of fuselage structurep 95 N95-14485

Advanced method and processing technology forcomplicated shape airframe part forming

p BO N95-14486PARALLEL PROCESSING (COMPUTERS)

Artificial neural network modeling of damaged aircraft[AD-A283227] p 80 N95-14849

PARAMETER IDENTIFICATIONIdentification of dynamic systems. Volume 3:

Applications to aircraft. Pan 2: Nonlinear analysis andmanoeuvre design|AGARD-AG-300-VOL-3-PT-2| p 79 N95-14102

Parameter identification for X-31A at high angles ofattack p 69 N95-14235

PARTICULATESHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-6051 p 86 N95-14639PASSENGER AIRCRAFT

The Aluminum Falcon: A low cost modern commercialtransportINASA-CR-1971801 p 81 N95-15742

PAVEMENTSDevelopment of anti-icing technology

IPB94-195369] p 78 N95-15439PERFORMANCE PREDICTION

The industrial use of CFD in the design ofturfaomachinery p 90 N95-14133

Airplane takeoff and landing performance monitoringsystemINASA-CASE-LAR-14745-2-SBJ p 85 N95-14415

PERFORMANCE TESTSTurbofan propulsion simulator

|BTN-94-EIX94461290240| p 82 A95-61737PERIGEES

Variations of perturbations in perigee height witheccentricity for artificial Earth's satellites due to air dragIHTN-95-400131 p 85 A95-62657

PERIODIC FUNCTIONSOn profiling a cam of an axial aviation diesel engine

by periodic splines[BTN-94-EIX94461407946J p 82 A95-62264

PHASE SHIFTDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992|AD-A283011| p84 N95-13687

PHASE TRANSFORMATIONSMechanism and technological particular features of

thermomagnetic hardening[BTN-94-EIX94461407953] p 89 A95-62627

PIEZOELECTRIC TRANSDUCERSTest Operation Procedure (TOP): Vibration testing of

helicopter equipment|AD-A284433| p 81 N95-15815

PILOT TRAININGVertical flight terminal operational procedures. A

summary of FAA research and developmentIAD-A283550] p 85 N95-15328

PITCHING MOMENTSStatic and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238Flight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259PITTING

The effects of pitting on fatigue crack nucleation in7075-T6 aluminum alloy p 88 N95-14482

PLANETARY ATMOSPHERESPlanetary entry experiments

INASA-CR-194215I p 101 N95-13717PLASTIC BODIES

Large amplitude nonlinear response of flat aluminum,and carbon fiber plastic beams and platesIAD-A282440I p 96 N95-15547

PLASTIC PLATESLarge amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and plates[AD-A282440) p 96 N95-15547

PLASTIC PROPERTIESElastic-plastic models for multi-site damage

p92 N95-14454PNEUMATIC CONTROL

F/A-18 and F-16 forebody vortex control, static androtary-balance results p 72 N95-14254

Low-energy pneumatic control of forebody vorticesp72 N95-14256

Flight evaluation of pneumatic forebody vortex controlin post-stall flight p 72 N95-14259

PNEUMATIC EQUIPMENTTurbofan propulsion simulator

[BTN-94-EIX944612902401 p 82 A95-61737

PNEUMATICSF/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254Low-energy pneumatic control of forebody vortices

p 72 N95-14256Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258POLYIMIDES

Thermally stable organic polymersIAD-A281380] p 87 N95-14363

POLYMER BLENDSThermally stable organic polymers

|AD-A281380| p 87 N95-14363POLYMER MATRIX COMPOSITES

Thermally stable organic polymers(AD-A281380] p 87 N95-14363

POROSITYBase passive porosity for drag reduction

INASA-CASE-LAR-15246-1) p 91 N95-14183POSITION (LOCATION)

Low-energy pneumatic control of forebody vorticesp72 N95-14256

POSITION ERRORSPrecision orbit determination of altimetric satellites

p 86 N95-14282POSITION INDICATORS

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approachesINASA-TP-3467] p 80 N95-14852

POWER LOSSAircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency,landing Simmons Airlines. Inc.. d/b/a, American EagleFlight 3641. N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

PREDICTION ANALYSIS TECHNIQUESComputational predictive methods for fracture and

fatigue p 93 N95-14466USAF single-event sonic boom prediction model:

PCBoom3 p 101 N95-14889PREDICTIONS

Fracture mechanics validity limits p 95 N95-14480Aero-optics system integration

[TABES PAPER 94-604) p 100 N95-14638Wind shear and its effects on aircraft

p77 N95-14898PRESSURE DISTRIBUTION

Base passive porosity for drag reduction[NASA-CASE-LAR-15246-1] p 91 N95-14183

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p 68 N95-14231

Numerical simulation of the SOFIA flowfield[NASA-CR-1970251 p 74 N95-14612

Activated buoyancy propulsion = Paradox Power (tm)[TABES PAPER 94-619] p 74 N95-14646

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A281581] p 76 N95-15465

PRESSURE MEASUREMENTDesign and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure data(AD-A281581J p 76 N95-15465

PRESSURE SENSORSDesign and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

PROBABILITY THEORYProbabilistic inspection strategies for minimizing service

failures p 93 N95-14461PRODUCT DEVELOPMENT

Trent engine development(BTN-94-EIX94461290507) p 82 A95-61727

PROFILOMETERSOn profiling a cam of an axial aviation diesel engine

by periodic splines[BTN-94-EIX94461407946] p 82 A95-62264

Profiling of the working surface of electrodes-tools forcircle electrochemical dimensional treatment ofcompressor blades[BTN-94-EIX94461407964) p 83 A95-62638

PROGRAM VERIFICATION (COMPUTERS)Automated test environment for a real-time control

system[TABES PAPER 94-631 ] p 99 N95-14652

PROP-FAN TECHNOLOGYPropulsion/airframe interference for ducted propfan

engines with ground effect[NASA-CR-1971101 p 81 N95-14909

PROPELLER BLADESComposite propeller system for Dornier 328

[BTN-94-EIX94461290506] p 66 A95-61728PROPELLER FANS

Propulsion/airframe interference for ducted propfanengines with ground effect[NASA-CR-197110] p 81 N95-14909

PROPELLERSComposite propeller system for Dornier 328

(BTN-94-EIX944612905061 p 66 A95-61728Aircraft accident report: Overspeed and loss of power

on both engines during descent and power-off emergency,landing Simmons Airlines. Inc.. d/b/a. American EagleFlight 3641. N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

PROPULSIONActivated buoyancy propulsion = Paradox Power (tm)

[TABES PAPER 94-619] p 74 N95-14646PROPULSION SYSTEM CONFIGURATIONS

Computational aerodynamics based on the Eulerequations[AGARD-AG-325] p 72 N95-14264

PROPULSION SYSTEM PERFORMANCEFourth High Alpha Conference, volume 1

[NASA-CP-10143-VOL-1] p 67 N95-14229A graphical user interface for design and analysis of

air breathing propulsion systems[TABES PAPER 94-616] p 83 N95-14645

Gas turbine prediffuser-combustor performance duringoperation with air-water mixture[DOT/FAA/CT-93/52] p 83 N95-15583

PROTOCOL (COMPUTERS)Generic architectures for future flight systems

p 99 N95-14159Space Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161Evolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162

QUALITY CONTROLEarth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance plan[NASA-CR-196059] p 98 N95-13885

RADAR FILTERSGroundspeed filtering for CTAS

[NASA-CR-197223] p 97 N95-15785RADIANT HEATING

Science objectives and performance ol a radiometerand window design for atmospheric entry experiments

p85 N95-13718VUV shock layer radiation in an arc-jet wind tunnel

experiment p 67 N95-13719RADIATION SPECTRA

Science objectives and performance of a radiometerand window design for atmospheric entry experiments

p85 N95-13718RADIO ALTIMETERS

Precision orbit determination of altimetric satellitesp86 N95-14282

RADIOMETERSPlanetary entry experiments

[NASA-CR-1942151 p 101 N95-13717Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

RAINHeavy rain effects p 78 N95-14899

RAMJET ENGINESCombustion efficiency in a dual-inlet side-dump ramjet

combustor[AD-A283564] p 83 N95-15329

RAMJET MISSILESComputation of supersonic air-intakes

p 74 N95-14452RATS

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p86 N95-14089RAYLEIGH SCATTERING

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992|AD-A283011| p84 N9S-13687

REAL TIME OPERATIONComputing quantitative characteristics of finite-state

real-time systems[AD-A282839I p 83 N95-14343

Airplane takeoff and landing performance monitoringsystem| NASA-CASE-LAR-14745-2-SB | p 85 N95-14415

A-13

REENTRY EFFECTS SUBJECTINDEX

A graphical user interface for design and analysis ofair breathing propulsion systems[TABES PAPER 94-616] p 83 N95-14645

Automated test environment for a real-time controlsystemI TABES PAPER 94-631] P 99 N95-14652

REENTRY EFFECTSScience objectives and performance of a radiometer

and window design for atmospheric entry experimentspSS N95-13718

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N95-13719

REENTRY SHIELDINGThermoacoustic environments to simulate reentry

conditions p 86 N95-14096REFRACTORY MATERIALS

Thermally stable organic polymers[AD-A261380I p 87 N95-14363

REGULATIONSFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-1968I3I p 79 N95-13981

RELIABILITYFatigue reliability method with in-service inspections

p 94 N95-14475RELIABILITY ENGINEERING

The principles of flight test assessment offlight-safety-critical systems in helicoptersIAGARD-AG-300-VOL-12I p 77 N95-14199

RESEARCH AIRCRAFTFourth High Alpha Conference, volume 2

INASA-CP-10143-VOL-2] p 69 N95-14239F-18 high alpha research vehicle: Lessons learned

p69 N95-14240Design and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

Flight test results of the F-16 aircraft modified with theaxisymmetric vectoring exhaust nozzle

p70 N95-14245Flight validation of ground-based assessment for control

power requirements at high angles of attackp 70 N95-14246

Numerical simulation of the flow about the F-18 HARVat high angle of attackINASA-CR-197023] p 74 N95-14614

RESEARCH AND DEVELOPMENTA review of SO years of aerodynamic research with

NACA/NASAINASA-TM-109163] p 102 N95-13663

Research and technology highlights, 1993[NASA-TM-«7S| p 102 N95-15065

Vertical flight terminal operational procedures. Asummary of FAA research and development[AD-A2835SOI p 85 N95-15328

RESEARCH FACILITIESSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep 86 N95-14089

Thermoacoustic environments to simulate reentryconditions p 86 N95-14096

Research and technology highlights. 1993INASA-TM-457S] p 102 N95-15065

RESEARCH VEHICLESPreparations for flight research to evaluate actuated

lorebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

RESIDUAL STRENGTHResidual strength of composites with multiple impact

damageIAO-A2B4230] p 87 N95-14409

Testing and analysis of flat and curved panels withmultiple cracks p 93 N95-14460

RESIDUAL STRESSResidual strength of composites with multiple impact

damageIAD-A284230] p 87 N95-14409

Advanced method and processing technology forcomplicated shape airframe part forming

pBO N95-14486RESIN MATRIX COMPOSITES

Thermally stable organic polymers(AD-A281380) p 87 N95-14363

RESISTORSSpiral rrucrostnp antenna with resistance

[ NASA-CASE-LAR-15088-1] p 91 N95-14139RESONANT FREQUENCIES

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

RESPONSE TIME (COMPUTERS)Computing quantitative characteristics of finite-state

real-time systems[AD-A282839] p 83 N95-14343

REVERBERATIONElectromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923] P 82 N95-15392

REYNOLDS NUMBERScale effects on aircraft and weapon aerodynamics

IAGARD-AG-323] P 67 N95-14103High Alpha Technology Program (HATP) ground test

to flight comparisons P 68 N95-14230RHEOLOGY

Electrorheologically controlled landing gear| BTN-94-EIX94461047055] p 78 A95-61740

RIEMANN WAVESComputational aerodynamics based on the Euler

equationsIAGARD-AG-325] P 72 N95-14264

RIGID ROTORSHigher harmonic control analysis for vibration reduction

of helicopter rotor systemsINASA-TM-103855] P 66 N95-14419

RISKRisk analysis for the fire safety of airline passengers

IPB94-194065] p77 N95-14179The F-16 multinational staged improvement program:

A case study of risk assessment and risk managementIAD-A281706] p 81 N95-15451

RIVETED JOINTSThe characterization of widespread fatigue damage in

fuselage structure(NASA-TM-109142] p 88 N95-14920

RIVETINGDamage tolerant repair techniques for pressurized

aircraft fuselages(AD-A281982J p 65 N95-14144

RIVETSThe role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470ROBUSTNESS (MATHEMATICS)

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249ROCKET ENGINES

Investigation of heat transfer in a rotating ring gap withthe axial flow of a coolant during the rotation of the centralshaflIBTN-94-EIX94461407951] p 89 A95-62625

ROLLING MOMENTSStatic and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238ROTARY STABILITY

F/A-18 and F-16 lorebody vortex control, static androtary-balance results p 72 N95-14254

ROTARY WING AIRCRAFTADST ARWA visual system module software design

documenttAD-A283874] p 99 N95-14357

Vertical flight terminal operational procedures. Asummary of FAA research and developmentIAD-A283550] p 85 N95-15328

ROTARY WINGSAdvanced distributed simulation technology advanced

rotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotorIAD-A280824] p 79 N95-14306

Higher harmonic control analysis for vibration reductionof helicopter rotor systemsINASA-TM-103855] p 66 N95-14419

Prediction of rotor-blade deformations due to unsteadyairloads(AD-A284467] p 81 N95-15821

ROTATING BODIESThe effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristics[BTN-94-EIX94461407959] p 78 A95-62633

Building complex simulations rapidly using MATRIX(x):The Space Station redesign(TABES PAPER 94-632] p 87 N95-14653

ROTATING SHAFTSInvestigation of heat transfer in a rotating ring gap with

the axial flow of a coolant during the rotation of the centralshaftIBTN-94-EIX94461407951] p 89 A95-62625

ROTATIONExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

ROTOR AERODYNAMICSDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalanceINASA-TM-108855] p 65 N95-13891

ROTOR BLADES (TURBOMACHINERY)Unsteady flows in turbines: Impact on design

procedure P 90 N95-14132

ROTOR DYNAMICSOn calculated models for impellers of centrifugal

compressorsIBTN-94-EIX94461407947] p 88 A95-62265

Advanced distributed simulation technology advancedrotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotor[AD-A280824I p 79 N95-14306

ROTOR SPEEDExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressorINASA-TM-1088331 p 95 N95-14617

ROTORSNew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systems(BTN-94-EIX94331336949] p 88 A95-61795

Evaluation of energy-sink stability criteria for dual-spinspacecraftIAD-A283228] p 87 N95-14850

RUNGE-KUTTA METHODThe role of CFD in the design process

p 90 N95-14135

SAFETY DEVICESRisk analysis for the fire safety of airline passengers

IPB94-194065] p77 N95-14179SAFETY FACTORS

Generic architectures for future flight systemsp99 N95-14159

Wake turbulence p 75 N95-14894SALT SPRAY TESTS

The effects of pitting on fatigue crack nucleation in7075-T6 aluminum alloy p 88 N95-14482

SATELLITE ALTIMETRYPrecision orbit determination of altimetric satellites

p86 N95-14282SATELLITE COMMUNICATION

Space Generic Open Avionics Architecture (SGOAA):Overview p 99 N95-14161

SATELLITE NAVIGATION SYSTEMSGeneric architectures for future flight systems

p99 N95-14159SATELLITE ORBITS

Variations of perturbations in perigee height witheccentricity for artificial Earth's satellites due to air dragIHTN-95-40013] p 85 A95-62657

Precision orbit determination of altimetric satellitesp 86 N95-14282

SATELLITE PERTURBATIONVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air drag(HTN-95-40013) p 85 A95-62657

SCALE EFFECTScale effects on aircraft and weapon aerodynamics

IAGARD-AG-323] p 67 N95-14103SCANNERS

TDWR scan strategy implementation[AD-A284877] p 98 N95-15749

SCHLIEREN PHOTOGRAPHYAn optical technique for examining aircraft shock wave

structures in flight p 96 N95-14B79Two-dimensional scramjet inlet unstart model:

Wind-tunnel blockage and actuation systems test| NASA-TM-109984] p 97 N95-15899

SEA LEVELPrecision orbit determination of altimetric satellites

p 86 N95-14282SECONDARY FLOW

Elements of a modem turbomachinery design systemp90 N95-14129

SENSITIVITYDiscrete shape sensitivity equations for aerodynamic

problems| BTN-94-EIX94451393721] p 88 A95-61720

SEPARATED FLOWControl of unsteady separated flow associated with the

dynamic stall of airfoilsINASA-CR-197024] p 74 N95-14613

SERVICE LIFEFAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage Tolerance|NASA-CP-3274-PT-1| p 92 N95-14453

Probabilistic inspection strategies for minimizing servicefailures p 93 N95-14461

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

Challenges for the aircraft structural integrity programp80 N95-14481

A-14

SUBJECT INDEX STREAMLINING

SHAPE FUNCTIONSDiscrete shape sensitivity equations for aerodynamic

problemsIBTN-94-EIX94451393721] p 88 A95-61720

SHAPESAdvanced method and processing technology for

complicated shape airframe part formingp80 N95-14486

SHIELDINGCeramic blanket reduces maintenance costs

[BTN-94-EIX94461290278] p 77 A95-61733SHOCK ABSORBERS

Soft landing on the slope surface of a landing vehiclewith an air shock-absorber of forced pressurizationIBTN-94-EIX94461407941] p 85 A95-62259

Landing gear energy absorption system|NASA-CASE-MSC-22277-1| p 96 N95-15306

SHOCK LAYERSScience objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N95-13719

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel| AIAA PAPER 94-00861 P 67 N95-13720

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured grids|NASA-CR-195008| p 97 N95-15604

SHOCK WAVE INTERACTIONAtmospheric effects on the risetime and waveshape of

sonic booms p 100 N95-14886The effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887Laminar and turbulent flow computations of Type 4

shock-shock interference aerothermal loads usingunstructured grids(NASA-CR-1950081 p 97 N95-15604

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6INASA-TM-109152] p 97 N95-15898

SHOCK WAVE PROPAGATIONUSAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889SHOCK WAVES

An optical technique for examining aircraft shock wavestructures in flight p 96 N95-14879

SIDESLIPFlight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259SILICON NITRIDES

Advanced Turbine Technology Applications Project(ATTAP)INASA-CR-195393] p 101 N95-15743

SIMULATORSTurbofan propulsion simulator

IBTN-94-EIX94461290240J p 82 A95-61737SINGLE CRYSTALS

Fatigue in single crystal nickel superalloys[AD-A282917] p 88 N95-15415

SINGLE STAGE TO ORBIT VEHICLESRequirements report for SSTO vertical take-off and

horizontal landing vehicleINASA-CR-197029] p 80 N95-14794

SIZE DISTRIBUTIONCombustion efficiency in a dual-inlet side-dump ramjet

combustor|AO-A283564| p 83 N95-15329

SLENDER BODIESA selection of experimental test cases for the validation

of CFO codes, volume 1(AGARD-AR-303-VOL-11 p 91 N95-14201

SLOTSComputational analysis of forebody tangential slot

blowing p 71 N95-14253Comparison of full-scale, small-scale, and CFO results

for F/A-18 forebody slot blowing p 72 N95-14255SOFIA (AIRBORNE OBSERVATORY)

Numerical simulation of the SOFIA flowfieldINASA-CR-197025) p 74 N95-14612

SOFT LANDINGSoft landing on the slope surface of a landing vehicle

with an air shock-absorber of forced pressurization[BTN-94-EIX94461407941] p 85 A95-62259

SOFTWARE ENGINEERINGKnowledge-based processing for aircraft flight control

INASA-CR-194976] p 99 N95-13727Earth Observing System (EOS)XAdvanced Microwave

Sounding Unit-A (AMSU-A) software assurance plan| NASA-CR-196059] p 98 N95-13885

Generic architectures for future flight systemsp 99 N95-14159

ADST ARWA visual system module software designdocument[AD-A283874] p 99 N95-14357

Automated test environment for a real-time controlsystem[TABES PAPER 94-6311 P 99 N95-14652

SOFTWARE RELIABILITYSpace Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161Evolutionary Telemetry and Command Processor (TCP)

architecture P 86 N95-14162SOFTWARE TOOLS

Automated test environment for a real-time controlsystem[TABES PAPER 94-6311 P 99 N95-14652

SOLAR ARRAYSBuilding complex simulations rapidly using MATRIX(x):

The Space Station redesign[TABES PAPER 94-632) P 87 N95-14653

SONIC BOOMSHigh-Speed Research: 1994 Sonic Boom Workshop:

Atmospheric Propagation and Acceptability Studies[NASA-CP-3279I P 75 N95-14878

Effect of stratification and geometrical spreading onsonic boom rise time P 75 N95-14880

Atmospheric effects on the risetime and waveshape ofsonic booms P 100 N95-14886

The effect of aircraft speed on the penetration of sonicboom noise into a flat ocean p 100 N95-14887

USAF single-event sonic boom prediction model:PCBoom3 P 101 N95-14889

SOUND PRESSURENumerical simulation of the SOFIA flowfield

INASA-CR-1970251 p 74 N95-14612SPACE DEBRIS

Hypervelocity Impact Test Facility: A gun for hire[TABES PAPER 94-605] p 86 N95-14639

SPACE ENVIRONMENT SIMULATIONSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

Thermoacoustic environments to simulate reentryconditions P 86 N95-14096

Hypervelocity Impact Test Facility: A gun for hire[TABES PAPER 94-605] P 86 N95-14639

SPACE PERCEPTIONSpatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-3467] p 80 N95-14852

SPACE SHUTTLE MAIN ENGINEAutomated test environment for a real-time control

system[TABES PAPER 94-631] P 99 N95-14652

SPACE STATIONSBuilding complex simulations rapidly using MATRIX(x):

The Space Station redesign[TABES PAPER 94-632] p 87 N95-14653

SPACE TRANSPORTATIONAir-breathing aerospace plane development essential:

Hypersonic propulsion flight tests[NASA-TM-108857] p 66 N95-14921

SPACECRAFT DESIGNBuilding complex simulations rapidly using MATRIX(x):

The Space Station redesign[TABES PAPER 94-632] p 87 N95-14653

Requirements report for SSTO vertical take-off andhorizontal landing vehicle[NASA-CR-197029] p 80 N95-14794

SPACECRAFT LANDINGSoft landing on the slope surface of a landing vehicle

with an air shock-absorber of forced pressurization[BTN-94-EIX94461407941] p 85 A95-62259

Landing gear energy absorption system[NASA-CASE-MSC-22277-1] p 96 N95-15306

SPACECRAFT LAUNCHINGSimulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

SPACECRAFT STABILITYEvaluation of energy-sink stability criteria for dual-spin

spacecraft[AD-A283228] p 87 N95-14850

SPECIFICATIONSComputational predictive methods for fracture and

fatigue p 93 N95-14466SPECTRA

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnelI AIAA PAPER 94-0086] P 67 N95-13720

SPECTRUM ANALYSISSpectral analysis of vortex/free-surface interaction

[AD-A283210] P96 N95-14658SPIRAL ANTENNAS

Spiral microstnp antenna with resistance[NASA-CASE-LAR-15088-1] p 91 N95-14139

SPLINE FUNCTIONSOn profiling a cam of an axial aviation diesel engine

by periodic splinesIBTN-94-EIX94461407946] P 82 A95-62264

SPREADINGEffect of stratification and geometrical spreading on

sonic boom rise time P 75 N95-14880STABILITY

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p93 N95-14467STABILIZATION

The effect of rotating loads suspended under a helicopteron their amplitude-frequency characteristicsIBTN-94-EIX94461407959] p 78 A95-62633

STABILIZERS (FLUID DYNAMICS)X-31 quasi-tailless flight demonstration

p 70 N95-14243Pressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281581] p 76 N95-15465

STANDARDIZATIONEvolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162STATIC AERODYNAMIC CHARACTERISTICS

Engineering Codes for aeroprediction: State-of-the-artand new methods p 73 N95-14447

STATIC PRESSUREFlight and full-scale wind-tunnel comparison of pressure

distributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p 68 N95-14231

STATIC TESTSDevelopment of a composite repair and the associated

inspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

STATIONKEEPINGBuilding complex simulations rapidly using MATRIX(x):

The Space Station redesign(TABES PAPER 94-632] p 87 N95-14653

STATORSEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficients[AD-A283854] p 91 N95-14351

STDN (NETWORK)Evolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162STEADY STATE

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor[NASA-TM-108833] p 95 N95-14617

STEERINGEvolution of a nose-wheel steering system

(BTN-94-EIX94461047056) p 78 A95-61739STIFFNESS

Foil bearings for gas turbine engines[BTN-94-EIX94461290279] p 82 A95-61732

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

STRAIN ENERGY METHODSNonlinear bulging factor based on R-curve data

p94 N95-14476STRAIN ENERGY RELEASE RATE

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p 92 N95-14456STRAIN GAGE BALANCES

Static and dynamic force/moment measurements in theEidetics water tunnel p 69 N95-14238

STRAIN GAGESStatic and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238Extracting a representative loading spectrum from

recorded flight data p 80 N9S-14469STRAIN MEASUREMENT

Static and dynamic force/moment measurements in theEidetics water tunnel p 69 N95-14238

STRAKESPreparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Integration of a mechanical forebody vortex controlsystem into the F-15 p 72 N95-14258

STRAPSAxial crack propagation and arrest in pressurized

fuselage p 94 N95-14479STRATIFICATION

Effect of stratification and geometrical spreading onsonic boom rise time p 75 N95-14880

STREAMLININGAero design of turbomachinery components: CFD in

complex systems p 90 N95-14136

A-15

STRESS ANALYSIS SUBJECT INDEX

STRESS ANALYSISFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-196813] p 79 N95-13981

Composite waveform generation for EMP and lightningdirect-drive testing[AD-A284159) p 92 N95-14405

A method of calculating the safe fatigue life of compact.highly-stressed components P 93 N95-14464

Development ol a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

STRESS DISTRIBUTIONDevelopment of the NASA/FLAGRO computer program

for analysis of airframe structures p 94 N95-14473STRESS INTENSITY FACTORS

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

Elastic-plastic models for multi-site damagep 92 N95-14454

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p 92 N95-14456Inspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458Fracture mechanics validity limits p 95 N95-14480Challenges for the aircraft structural integrity program

p80 N95-14481The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482STRESS-STRAIN RELATIONSHIPS

Elastic-plastic models for multi-site damagep92 N95-14454

Small crack test program for helicopter materialsp92 N95-14455

Evaluation of bonded boron/epoxy doublers forcommercial aircraft aluminum structures

p 92 N95-14457Inspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458Corrosion and corrosion fatigue of airframe aluminum

alloys p87 N95-14465STRUCTURAL ANALYSIS

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage ToleranceINASA-CP-3274-PT-1] p92 N95-14453

Elastic-plastic models for multi-site damagep 92 N95-14454

Small crack test program lor helicopter materialsp92 N95-14455

Bending effects of unsymmetric adhesively bondedcomposite repairs on cracked aluminum panels

p 92 N95-14456Evaluation of bonded boron/epoxy doubters for

commercial aircraft aluminum structuresp92 N95-14457

Inspecting for widespread fatigue damage: Is partialdebonding the key? p 93 N95-14458

Testing and analysis of flat and curved panels withmultiple cracks p 93 N95-14460

Probabilistic inspection strategies for minimizing servicefailures p 93 N95-14461

A method of calculating the safe fatigue life of compact,highly-stressed components p 93 N95-14464

Corrosion and corrosion fatigue of airframe aluminumalloys p 87 N95-14465

Computational predictive methods for fracture andfatigue p 93 N95-14466

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p93 N9S-14467Study of multiple cracks in airplane fuselage by

micromechanics and complex variablesp94 N95-14468

Extracting a representative loading spectrum fromrecorded flight data p 80 N95-14469

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

Fatigue reliability method with in-service inspectionsp94 N95-14475

Nonlinear bulging factor based on R-curve datap94 N95-14476

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

Fracture mechanics validity limits p 95 N95-14480Challenges for the aircraft structural integrity program

p80 N95-14481The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Full-scale testing and analysis of fuselage structurep95 N95-14485

Advanced method and processing technology forcomplicated shape airtrame part forming

p80 N95-14486STRUCTURAL DESIGN

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage ToleranceINASA-CP-3274-PT-1) p 92 N95-14453

Requirements report for SSTO vertical take-oft andhorizontal landing vehicle|NASA-CR-197029} p 80 N95-14794

STRUCTURAL DESIGN CRITERIAHigher harmonic control analysis for vibration reduction

of helicopter rotor systems|NASA-TM-103855| p 66 N95-14419

STRUCTURAL FAILUREDamage tolerant repair techniques for pressurized

aircraft fuselagesIAD-A281982I p 65 N95-14144

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airframe Durability andDamage ToleranceINASA-CP-3274-PT-1] p 92 N95-14453

Challenges for the aircraft structural integrity programp 80 N95-14481

STRUCTURAL VIBRATIONLarge amplitude nonlinear response of flat aluminum,

and carbon fiber plastic beams and plates[AD-A282440] p 96 N95-15547

SUBSONIC FLOWAxis switching and spreading of an asymmetric jet: Role

of vorticity dynamics[NASA-TM-1063851 p 73 N95-14418

SUBSONIC SPEEDUltra-high bypass ratio jet noise

[NASA-CR-195394] p 100 N95-14610SUBSONIC WIND TUNNELS

Modification of the Ames 40- by 80-foot wind tunnelfor component acoustic testing for the second generationsupersonic transportINASA-TM-108850] p 65 N95-13642

SUPERSONIC COMBUSTION RAMJET ENGINESAir-breathing aerospace plane development essential:

Hypersonic propulsion flight testsINASA-TM-108857] p 66 N95-14921

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6INASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test[NASA-TM-109984] p 97 N95-15899

SUPERSONIC FLIGHTThe effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887SUPERSONIC INLETS

Computation of supersonic air-intakesp 74 N95-14452

SUPERSONIC JET FLOWNoise radiation by instability waves in coaxial jets

| NASA-TM-106738) p 100 N95-14618The aeroacoustics of supersonic coaxial jets

(NASA-TM-106782] p 101 N95-15059Resonant interaction of a linear array of supersonic

rectangular jets: An experimental study(NASA-CR-195398) p 76 N95-15852

SUPERSONIC NOZZLESResonant interaction of a linear array of supersonic

rectangular jets: An experimental study| NASA-CR-195398] p 76 N95-15852

SUPERSONIC TRANSPORTSModification of the Ames 40- by 80-foot wind tunnel

for component acoustic testing for the second generationsupersonic transportINASA-TM-108850] p 65 N95-13642

Aerodynamic shape optimization of a HSCT typeconfiguration with improved surface definition| NASA-CR-197011] p 67 N95-13701

SURFACE CRACKSSmall crack test program for helicopter materials

p92 N95-14455SURFACE ROUGHNESS EFFECTS

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficients[AD-A2B3854] p 91 N95-14351

SURFACE VEHICLESBase passive porosity for drag reduction

(NASA-CASE-LAR-15246-1] p 91 N95-14183SWEPT FORWARD WINGS

The Aluminum Falcon: A low cost modem commercialtransport(NASA-CR-197180] p 81 N95-15742

SYSTEM FAILURESThe principles of flight test assessment of

flight-safety-critical systems in helicopters(AGARD-AG-300-VOL-12) p 77 N95-14199

SYSTEMS ENGINEERINGADST ARWA visual system module software design

document(AD-A283874J p 99 N95-14357

Aeromechanical design of modem missilesp73 N95-14446

Automated test environment for a real-time controlsystem(TABES PAPER 94-631 ] p 99 N95-14652

SYSTEMS INTEGRATIONAero-optics system integration

[TABES PAPER 94-6041 p 100 N95-14638

T-38 AIRCRAFTMore supportable T-38A enhancement study

[AD-A283671] p 66 N95-15331TABS (CONTROL SURFACES)

Axis switching and spreading of an asymmetric jet: Roleof vorticity dynamics| NASA-TM-1063851 p 73 N95-14418

TAIL ASSEMBLIESFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes[PB94-196813I p 79 N95-13981

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure data(AD-A281581] p76 N95-15465

TAIL SURFACESPressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A281581I p 76 N95-15465

TAILLESS AIRCRAFTX-31 quasi-tailless flight demonstration

p 70 N95-14243TAKEOFF

Airplane takeoff and landing performance monitoringsystem[NASA-CASE-LAR-14745-2-SB] p 85 N95-14415

TECHNOLOGY TRANSFERResearch and technology highlights, 1993

(NASA-TM-4575) p 102 N95-15065TELEMETRY

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

TEMPERATURE CONTROLTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563TEMPERATURE DISTRIBUTION

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficients(AD-A283854) p 91 N95-14351

TEMPERATURE EFFECTSAdvanced Turbine Technology Applications Project

(ATTAP)| NASA-CR-195393] p 101 N95-15743

TEMPERATURE PROFILESTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563TERMINAL FACILITIES

TDWR scan strategy implementationIAD-A284877] p 98 N95-15749

TEST CHAMBERSCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556TEST EQUIPMENT

Small crack test program for helicopter materialsp 92 N95-14455

TEST FACILITIESHypervelocity Impact Test Facility: A gun for hire

ITABES PAPER 94-605] p 86 N95-14639THERMAL ANALYSIS

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

THERMAL PROTECTIONThermoacoustic environments to simulate reentry

conditions p 86 N95-14096Requirements report for SSTO vertical take-off and

horizontal landing vehicle[NASA-CR-197029] p 80 N95-14794

THERMAL STABILITYThermally stable organic polymers

[AD-A281380) p 87 N95-14363THERMAL STRESSES

Hypersonic engine leading edge experiments in a highheat flux, supersonic flow environment(NASA-TM-106742) p 91 N95-14299

A-16

SUBJECTINDeX VISCOUS FLOW

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured grids[NASA-CR-195008J p 97 N9S-156O4

THERMAL VACUUM TESTSThermoacoustic environments to simulate reentry

conditions p 86 N95-14096THERMODYNAMICS

On introduction of artificial intelligence elements to heatpower engineering(BTN-94-EIX94461407961) p 100 A95-62635

THERMOMAGNETIC EFFECTSMechanism and technological particular features of

thermomagnetic hardening|BTN-94-EIX94461407953| p 89 A95-62627

THREE DIMENSIONAL FLOWDesigning in three dimensions p 90 N95-14130Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132Aero design of turbomachinery components: CFD in

complex systems p 90 N95-14136Numerical design of advanced multi-element airfoils

(NASA-CR-1971351 p 76 N95-15762THREE DIMENSIONAL MODELS

Turbomachinery Design Using CFDIAGARD-LS-1951 p 89 N95-14127

Designing in three dimensions p 90 N95-14130Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132The role of CFD in the design process

p90 N95-1413SAdd a dimension to your analysis of the helicopter low

airspeed environment| AD-A2839821 p 79 N95-14205

THRUST VECTOR CONTROLFourth High Alpha Conference, volume 1

|NASA-CP-10143-VOL-1| p67 N95-14229Parameter identification for X-31A at high angles of

attack p69 N95-1423SFourth High Alpha Conference, volume 2

INASA-CP-10143-VOL-2] p 69 N95-14239F-f8 high alpha research vehicle: Lessons learned

p69 N95-14240X-31 post-stall envelope expansion and tactical utility

testing p 70 N95-14242X-31 quasi-tailless flight demonstration

p70 N95-14243X-31 high angle of attack control system performance

p 70 N95-14244Flight test results of the F-16 aircraft modified with the

axisymmetric vectoring exhaust nozzlep 70 N95-14245

Vista/F-16 Multi-Axis Thrust Vectoring (MATV) controllaw design and evaluation p 71 N95-14248

Multi-application controls: Robust nonlinearmultivariable aerospace controls applications

p 71 N95-14249Navy and the HARV: High angle of attack tactical utility

issues p71 N95-14252Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

TIME DEPENDENCEAn approach for dynamic grids

|NASA-TM-106774| p 76 N95-15853TIME LAG

F/A-18 and F-16 forebody vortex control, static androtary-balance results p 72 N95-14254

TOLERANCES (MECHANICS)FAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1J p 92 N95-14453

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

TRAINING AIRCRAFTViper — Design modification

1NASA-CR-197191] p 79 N95-13703TRANSIENT OSCILLATIONS

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor| NASA-TM-108833] p 95 N95-14617

TRANSONIC SPEEDScale effects on aircraft and weapon aerodynamics

[AGARD-AG-323J p 67 N95-14103TRANSONIC WIND TUNNELS

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor| NASA-TM-1088331 p 95 N95-14617

TRANSPONDERSEvolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162TRANSPORT AIRCRAFT

Numerical design of advanced multi-element airfoilsINASA-CR-197135) p 76 N95-15762

TRANSPORT PROPERTIESTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563TUNING

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor[NASA-TM-108833] P 95 N95-14617

TURBINE BLADESThe industrial use of CFD in the design of

turbomachinery p 90 N95-14133New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

TURBINE ENGINESEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

TURBINESEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficientsIAD-A283854] p 91 N95-14351

TURBOCOMPRESSORSHeat transfer in the flow-through part of axial

compressorsIBTN-94-EIX94461407949] p 89 A95-62267

Investigation of heat transfer in a rotating ring gap withthe axial flow of a coolant during the rotation of the centralshaftIBTN-94-EIX94461407951 | p 89 A95-62625

Computational methods for preliminary design andgeometry definition in turbomachinery

p69 N95-14128Elements of a modem turbomachinery design system

p 90 N95-14129TURBOFAN ENGINES

Trent engine developmentIBTN-94-EIX94461290507] p 82 A95-61727

Turtaofan propulsion simulatorIBTN-94-EIX94461290240) p 82 A95-61737

Gas turbine prediffuser-combustor performance duringoperation with air-water mixtureIDOT/FAA/CT-93/52] p 83 N95-15683

TURBOMACHINERYTurbomachinery Design Using CFD

|AGARD-LS-195| p 89 N95-14127Designing in three dimensions p 90 N95-14130The industrial use of CFD in the design of

turbomachinery p 90 N95-14133New methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

The role of CFD in the design processp90 N95-14135

Aero design of turbomachinery components: CFD incomplex systems p 90 N95-14136

TURBULENCESpectral analysis of vortex/free-surface interaction

[AD-A283210] p 96 N95-14658TURBULENCE EFFECTS

Atmospheric effects on the risetime and waveshape ofsonic booms p 100 N95-14886

The effect of aircraft speed on the penetration of sonicboom noise into a flat ocean p 100 N95-14887

Wake turbulence p 75 N95-14894TURBULENCE MODELS

Turbulence: Engineering models, aircraft responsep 84 N95-14900

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured gridsINASA-CR-195008] p 97 N95-15604

TURBULENT BOUNDARY LAYERAtmospheric effects on the risetime and waveshape of

sonic booms p 100 N95-14886TURBULENT FLOW

Transport phenomena in stratified multi-fluid flo w in thepresence and absence of gravity p 95 N95-14563

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured gridsINASA-CR-195008) P 97 N95-15604

TWO PHASE FLOWCharacterization of annular two-phase gas-liquid flows

in microgravity P 95 N95-14556Gas turbine prediffuser-combustor performance during

operation with air-water mixtureIDOT/FAA/CT-93/521 P 83 N95-15683

uUNITED STATES

Annual review of aircraft accident data: US air carrieroperations, calendar year 1992 p 78 N95-15066

UNSTEADY AERODYNAMICSUser's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)| NASA-TM-108853] p 65 N95-13662

Higher harmonic control analysis for vibration reductionof helicopter rotor systems[NASA-TM-103855] p 66 N95-14419

UNSTEADY FLOWUnsteady flows in turbines: Impact on design

procedure p 90 N95-14132Aero design of turbomachinery components: CFD in

complex systems p 90 N95-14136Control of unsteady separated flow associated with the

dynamic stall of airfoils[NASA-CR-197024] p 74 N95-14613

Spectral analysis of vortex/free-surface interactionIAD-A283210] p 96 N95-14658

Numerical study of the effects of icing on viscous flowover wingsINASA-CR-1971021 p 75 N95-14803

Prediction of rotor-blade deformations due to unsteadyairloadsIAD-A2844671 p 81 N95-15821

UNSWEPT WINGSNumerical design of advanced multi-element airfoils

INASA-CR-1971351 p 76 N95-15762UPWIND SCHEMES (MATHEMATICS)

Computational aerodynamics based on the Eulerequations|AGARD-AG-325| p 72 N95-14264

USER MANUALS (COMPUTER PROGRAMS)User's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)INASA-TM-108853] p 65 N95-13662

Graphical user interface for the NASA FLOPS aircraftperformance and sizing code|NASA-TM-106649| p 80 N95-14604

Enhanced capabilities and updated users manual foraxial-flow turbine preliminary sizing code TURBANINASA-CR-195405] p 76 N95-15912

VALIDITYFracture mechanics validity limits p 95 N95-14480

VANESEffect of surface roughness on local film cooling

effectiveness and heat transfer coefficients[AD-A283854J p 91 N95-14351

VARIATIONSVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air drag[ HTN-95-40013] p 85 A95-62657

VELOCITY DISTRIBUTIONTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563VELOCITY MEASUREMENT

Groundspeed filtering for CTAS|NASA-CR-197223| p 97 N95-15785

VERTICAL FLIGHTVertical flight terminal operational procedures. A

summary of FAA research and development(AD-A2B3550] p 85 N95-15328

VERTICAL LANDINGVertical flight terminal operational procedures. A

summary of FAA research and developmentIAD-A283550] p 85 N95-15328

VIBRATION DAMPINGHigher harmonic control analysis for vibration reduction

of helicopter rotor systems| NASA-TM-103855] p 66 N95-14419

VIBRATION MEASUREMENTTest Operation Procedure (TOP): Vibration testing of

helicopter equipment(AD-A284433] p 81 N95-15815

VIBRATION TESTSDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance| NASA-TM-108855] p 65 N95-13891

Advanced Turbine Technology Applications Project(ATTAP)| NASA-CR-195393) p 101 N95-15743

Test Operation Procedure (TOP): Vibration testing ofhelicopter equipmentIAD-A284433] p 81 N95-15815

VIBRATORY LOADSHigher harmonic control analysis for vibration reduction

of helicopter rotor systems[NASA-TM-103855] p 66 N95-14419

VISCOUS FLOWAero design of turbomachinery components: CFD in

complex systems p 90 N95-14136

A-17

VORTEX GENERATORS SUBJECT INDEX

Numerical study of the effects of icing on viscous flowover wings(NASA-CR-197102) p 75 N95-14803

VORTEX GENERATORSAxis switching and spreading of an asymmetric jet: Role

of vorticity dynamics(NASA-TM-10638SJ p 73 N95-14418

VORTEX SHEDDINGHigh angle of attack aerodynamics p 74 N95-14450

VORTICESHybrid structured/unstructured grid computations for the

F/A-18 at high angle of attack p 68 N95-14233F/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254Low-energy pneumatic control of forebody vortices

p72 N95-14256Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258Flight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259Computational aerodynamics based on the Euler

equationsIAGARD-AG-325] p 72 N95-14264

Axis switching and spreading of an asymmetric jet: Roleof vorticity dynamicsINASA-TM-1063851 p 73 N95-14418

High angle of attack aerodynamics p 74 N95-14450Spectral analysis of vortex/free-surface interaction

IAO-A283210I p 96 N95-14658Wake turbulence p 75 N95-14894

VORTICITYAxis switching and spreading of an asymmetric jet: Role

of vorticity dynamicsINASA-TM-106385] p 73 N95-14418

wWARNING SYSTEMS

Aircraft maneuver envelope warning systemINASA-CASE-ARC-11953-1] p 82 N95-14518

WATER TUNNEL TESTSComparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp 68 N95-14234

Static and dynamic force/moment measurements in theEidetics water tunnel p 69 N95-14238

Spectral analysis of vortex/free-surface interaction|AD-A283210| p 96 N95-14658

WATER VAPORGas turbine prediffuser-combustor performance during

operation with air-water mixtureIDOT/FAA/CT-93/52] p 83 N95-1S683

WAVEFORMSComposite waveform generation for EMP and lightning

direct-drive testingIAD-A284159I p 92 N95-14405

Effect of stratification and geometrical spreading onsonic boom rise time p 75 N95-14880

Atmospheric effects on the risetime and waveshape ofsonic booms p 100 N95-14886

WAVERIDERSLow-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waveriderIAD-A283585I p 75 N95-15319

WAVESNoise radiation by instability waves in coaxial jets

INASA-TM-106738) p 100 N95-14618WEAPONS

Scale effects on aircraft and weapon aerodynamics(AGARD-AG-323J p 67 N95-14103

WEATHER RECONNAISSANCE AIRCRAFTApplication of airborne field mill data tor use in launch

supportIHTN-95-50054I p 98 A95-62279

WIND (METEOROLOGY)Atmospheric and wind modeling for ATC

INASA-CR-196786] p 98 N95-13725WIND PROFILES

Atmospheric and wind modeling for ATCINASA-CR-196786] p 98 N95-13725

WIND SHEARWind shear and its effects on aircraft

p77 N95-14898Heavy rain effects p 78 N95-14899TDWR scan strategy implementation

IAD-A2848771 p 98 N95-15749WIND TUNNEL TESTS

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N95-13719

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel(AIAA PAPER 94-00861 p 67 N95-13720

Dynamics of the McDonnell-Douglas Large ScaleDynamic Rig and dynamic calibration of the rotorbalanceINASA-TM-108855] p 65 N95-13891

Scale effects on aircraft and weapon aerodynamics[AGARD-AG-323] p 67 N95-14103

Quality assessment for wind tunnel testing(AGARD-AR-304) p 67 N95-14197

A selection of experimental test cases for the validationof CFD codes, volume 1IAGARD-AR-303-VOL-1] p 91 N95-14201

High Alpha Technology Program (HATP) ground testto flight comparisons p 68 N95-14230

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles of attack— Conducted in NASA Ames Research Center's 80 by120 ft wind tunnel p 68 N95-14231

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p68 N95-14234Free-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237Computational analysis of forebody tangential slot

blowing p 71 N95-14253F/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254Ultra-high bypass ratio jet noise

INASA-CR-195394] p 100 N95-14610Control of unsteady separated flow associated with the

dynamic stall of airfoilsINASA-CR-197024] p 74 N95-14613

Low-speed wind tunnel testing of the NPS and NASAAmes Mach 6 optimized waveriderIAD-A283585I p 75 N95-15319

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281581] p 76 N95-15465

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6INASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems testINASA-TM-109984] p 97 N95-15899

WIND TUNNELSDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A283011 ] p 84 N95-13687

Quality assessment for wind tunnel testing[AGARD-AR-304] p 67 N95-14197

Computational analysis of forebody tangential slotblowing p 71 N95-14253

F/A-1B and F-16 forebody vortex control, static androtary-balance results p 72 N95-14254

Flight evaluation of pneumatic forebody vortex controlin post-stall flight p 72 N95-14259

Research and technology highlights. 1993[NASA-TM-4575] p 102 N95-15065

Low-speed wind tunnel testing of the NPS and NASAAmes Mach 6 optimized waveriderIAD-A283585) p 75 N95-15319

WIND VELOCITYGroundspeed filtering for CTAS

(NASA-CR-1972231 p 97 N95-15785WINDOWS (APERTURES)

Science objectives and performance of a radiometerand window design for atmospheric entry experiments

p85 N95-13718WING FLAPS

Numerical design of advanced multi-element airfoilsI NASA-CR-197135] p 76 N95-15762

WING ROOTSThe Aluminum Falcon: A low cost modem commercial

transport[NASA-CR-197180] p 81 N95-15742

WINGLETSFatigue evaluation of empennage, forward wing, and

winglets/tip fins on part 23 airplanes(PB94-196813) p79 N95-13981

WINGSAdvancements in automatic fastening technology

IBTN-94-EIX94461290277] p 65 A95-61734Computational aerodynamics based on the Euler

equations(AGARD-AG-325] p 72 N95-14264

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

Numerical study of the effects of icing on viscous flowover wingsINASA-CR-197102) p 75 N95-14803

X-29 AIRCRAFTIntegration of a mechanical forebody vortex control

system into the F-15 P 72 N95-14258Flight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259X-31 AIRCRAFT

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p 68 N95-14234Parameter identification for X-31A at high angles of

attack p69 N95-14235Validation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp 69 N95-14236

Free-to-roll tests of X-31 and F-18 subscale models withcorrelation to flight test results p 69 N95-14237

X-31 post-stall envelope expansion and tactical utilitytesting p 70 N95-14242

X-31 quasi-tailless flight demonstrationp 70 N95-14243

X-31 high angle of attack control system performancep70 N95-14244

YAWComparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

YAWING MOMENTSComparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp68 N95-14234

Validation of the NASA Dryden X-31 simulation andevaluation of mechanization techniques

p69 N95-14236Static and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238Computational analysis of forebody tangential slot

blowing p 71 N95-14253Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255Flight evaluation of pneumatic forebody vortex control

in post-stall flight p 72 N95-14259

A-18

PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Personal AuthorIndex Listing

| PERSONAL AUTHOR |

CLASSMAN, ARTHUR J.I— Modeling improvements and users manual for axial-flow

turbine off-design computer code AXOD(NASA-CR-195370) p8 N95-10853

Listings in this index are arranged alphabeticallyby personal author. The title of the documentis used to provide a brief description of thesubject matter. The report number helps toindicate the type of document (e.g., NASAreport, translation, NASA contractor report). Thepage and accession numbers are locatedbeneath and to the right of the title. Under anyone author's name the accession numbers arearranged in sequence.

ABBOTT, TROY D.Flight validation of ground-based assessment for control

power requirements at high angles of attackp70 N95-14246

ACTIS, RICARDO l_Elastic-plastic models for multi-site damage

p 92 N95-14454

AGOSTA-GREENMAN, ROXANA M.Computational analysis of forebody tangential slot

blowing p 71 N95-14253

ALLMEN. J. R.Modification of the Ames 40- by 80-foot wind tunnel

for component acoustic testing for the second generationsupersonic transportI NASA-TM-108850] p 65 N95-13642

ALMAN, A. I.Profiling of the working surface of electrodes-tools for

circle electrochemical dimensional treatment ofcompressor bladesI BTN-94-EIX94461407964] p 83 A95-62638

AMSTUTZ, B. E.Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

ANNA, PAUL D.Flight test results of the F-16 aircraft modified with the

axisymmetric vectoring exhaust nozzlep 70 N95-14245

ANNIGERI, BALSmall crack test program for helicopter materials

p92 N95-14455ANNIS, CHARLES

Fatigue in single crystal nickel superalloys|AD-A282917| p 88 N95-15415

ANSCHUETZ, ROBERTADST ARWA visual system module software design

document|AD-A283874| p 99 N95-14357

ANTONIEWICZ, BOBMulti-application controls: Robust nonlinear

multivariable aerospace controls applicationsp 71 N95-14249

ARABSHAHI, ABDOLLAHPropulsion/airframe interference for ducted propfan

engines with ground effect[NASA-CR-197110] p8t N95-14909

ARENDT, CORYBending effects of unsymmetric adhesively bonded

composite repairs on cracked aluminum panelsp 92 N95-14456

BBABIKIAN, DIKRAN S.

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnelIAIAA PAPER 94-00861 p 67 N95-13720

BALLMANN, J.Prediction of rotor-blade deformations due to unsteady

airloads|AD-A284467| p 81 N95-15821

BANFORD, MICHAELPressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A2B1581] p 76 N95-15465

BANKS, D. W.High Alpha Technology Program (HATP) ground test

to flight comparisons P68 N95-14230BARLOW, DOUGLAS N.

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficients(AD-A283854J p 91 N95-143S1

BASS, HENRY E.Atmospheric effects on the nsetime and waveshape of

sonic booms p 100 N95-14886BASURAH, H. M.

Variations of perturbations in perigee height witheccentricity for artificial Earth's satellites due to air dragIHTN-95-40013] p 85 A95-62657

BAUER, STEVEN X. S.Base passive porosity for drag reduction

[NASA-CASE-LAR-15246-1 | p 91 N95-14183BAYERDOERFER, GERHARD

Thermoacoustic environments to simulate reentryconditions p 86 N95-14096

BELASON, BRUCEEvaluation of bonded boron/epoxy doubters for

commercial aircraft aluminum structuresp 92 N95-14457

BELLMORE, MICHAELApplication of airborne field mill data for use in launch

support[HTN-95-50054] p 98 A95-62279

BELYTSCHKO, T.Fatigue reliability method with in-service inspections

p 94 N95-14475

BERRY. CASSIEViper

INASA-CR-197191] p 79 N95-13703BEST, S.

Hypervelocity Impact Test Facility: A gun for hire[TABES PAPER 94-605] p 86 N95-14639

BIEORON, ROBERT T.Hybrid structured/unstructured grid computations for the

F/A-18 at high angle of attack p 68 N95-14233BIRCH, STUART

Trent engine development[BTN-94-EIX94461290507] p 82 A95-61727

BIVENS, COURTLAND C.Aircraft maneuver envelope warning system

[NASA-CASE-ARC-11953-1] p 82 N95-14518BLACKBURN, R. R.

Development of anti-icing technology[PB94-195369) p 78 N95-15439

BLACKSTOCK, DAVID T.Effect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880BOALBEY, RICHARD E.

Integration of a mechanical forebody vortex controlsystem into the F-15 p 72 N95-14258

BOLENDER, MICHAEL A.Assessment of CTAS ETA prediction capabilities

INASA-CR-197224] p 97 N95-15728BOROVSKIJ, S. M.

Mechanism and technological particular features ofthermomagnetic hardeningIBTN-94-EIX94461407953] p 89 A95-62627

BOSCHAN, R. H.Thermally stable organic polymers

(AD-A281380] p 87 N95-14363BOULANGER, PATRICE

Atmospheric effects on the nsetime and waveshape ofsonic booms p 100 N95-14886

BOUSMAN, W. SCOTTCharacterization of annular two-phase gas-liquid flows

in microgravity p 95 N95-14556BOWERS, ALBION H.

F-18 high alpha research vehicle: Lessons learnedp 69 N95-14240

BRANSON, ROGERAdvanced distributed simulation technology advanced

rotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotorIAD-A280824) p 79 N95-14306

BREEMAN, J. H.Identification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre design[AGARD-AG-300-VOL-3-PT-2] p 79 N95-14102

BREIT, G. A.Simulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep 86 N95-14089

BREWER, JOHNInspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458BROEK, DAVID

Testing and analysis of flat and curved panels withmultiple cracks p 93 N95-14460

BROICHHAUSEN, KLAUSAero design of turbomachinery components: CFD in

complex systems p 90 N95-14136BROT, ABRAHAM

Probabilistic inspection strategies for minimizing servicefailures p 93 N95-14461

BROWN, DANSENPressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281581] p 76 N95-15465

BRUNGER, CLIFFORD A.Artificial neural network modeling of damaged aircraft

I AD-A2832271 p 80 N95-14849BRYANT, MARK

The Aluminum Falcon: A low cost modern commercialtransportINASA-CR-197180] p 81 N95-15742

BUGAJSKI, DANIEL J.Multi-application controls: Robust nonlinear

multivariable aerospace controls applicationsp71 N95-14249

BURLEY. RICHARD R.Design and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

BUSOUETS, ANTHONY M.Spatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches(NASA-TP-3467) p 80 N95-14852

CAMM, FRANKThe F-16 multinational staged improvement program:

A case study of risk assessment and risk management[AD-A281706] p 81 N95-15451

CAMPOS, S.Computing quantitative characteristics of finite-state

real-time systems[AD-A282839] p 83 N95-14343

B-1

CANTER, DAVE

CANTER, DAVEX-31 post-stall envelope expansion and tactical utility

testing p 70 N95-14242CAROICK, ARTHUR W.

A method of calculating the safe fatigue life of compact,highly-stressed components p 93 N95-14464

CARRASCO, ARMANDOVUV shock layer radiation in an arc-jet wind tunnel

experiment p 67 N95-13719CARRINGTON, C. K.

Building complex simulations rapidly using MATRIX(x):The Space Station redesignITABES PAPER 94-6321 p 87 N95-146S3

CARTER, JOHNMulti-application controls: Robust nonlinear

multrvariable aerospace controls applicationsp 71 N95-14249

CASEY, M, V.Computational methods for preliminary design and

geometry definition in turbomachineryp 89 N9S-14128

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

CEDRUN, MARK E.Low-speed wind tunnel testing of the NPS and NASA

Ames Mach 6 optimized waveriderIAD-A28358S] p 75 N95-15319

CHALOUPKA, T.Hypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639CHAMPIGNY, P.

Lateral jet control tor tactical missilesp84 N95-14448

High angle of attack aerodynamics p 74 N95-14450CHAN, K. S.

Analysis of small crack behavior for airframeapplications P95 N95-14484

CHANG, A. T.Computational predictive methods for fracture and

fatigue p 93 N95-14466CHAPPELOW, C. C.

Development of anti-icing technology[PB94-195369] p78 N95-15439

CHARGIN, MLADEN K.Experimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressor|NASA-TM-108833| p 95 N95-14617

CHEN, G. S.Corrosion and corrosion fatigue of airframe aluminum

alloys p 87 N95-14465CHERNIKOV, S. K.

On calculated models for impellers of centrifugalcompressors| BTN-94.EIX94461407947) p 88 A95-62265

CHIGIER. NORMANTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563CHIU, W. K.

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

CITURS, KEVIN D.High angle of attack flying qualities criteria for

longitudinal rate command systems p 70 N95-14247Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258CLARKE, E.

Computing quantitative characteristics of finite-statereal-time systemsIAD-A282839] p 83 N95-14343

CLEVELAND, ROBIN 0.Effect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880COBLEIGH, BRENT R.

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p 68 N95-14234COIRIER, WILLIAM J.

A Cartesian, cell-based approach for adaptrvely-refinedsolutions of the Euler and Navier-Stokes equations|NASA-TM-106786| p 73 N95-14297

CORDES, J.Computational predictive methods for fracture and

fatigue p 93 N95-14466CORLISS, J. M.

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p86 N95-14089CRAIG, ROGER A.

Planetary entry experiments(NASA-CR-194215] p 101 N95-13717

Science objectives and performance of a radiometerand window design for atmospheric entry experiments

p85 N95-13718VUV shock layer radiation in an arc-jet wind tunnel

experiment p 67 N95-13719

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel[AIAA PAPER 94-0086] p 67 N95-13720

CRAWFORD, G.Hypervelocity Impact Test Facility: A gun for hire

ITABES PAPER 94-605) p 86 N95-14639CROOM, MARK A.

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p68 N95-14234CRUMPLER, M.

Hypervelocity Impact Test Facility: A gun for hire(TABES PAPER 94-605) p 86 N95-14639

CUMMINGS, RUSSELL M.Computational analysis of forebody tangential slot

blowing p 71 N95-14253Numerical design of advanced multi-element airfoils

|NASA-CR-197135| p 76 N95-15762CUHLETT, BRIAN P.

Graphical user interface for the NASA FLOPS aircraftperformance and sizing code|NASA-TM-106649| p 80 N95-14604

DAHL, MILO D.Noise radiation by instability waves in coaxial jets

INASA-TM-106738) p 100 N95-14618The aeroacoustics of supersonic coaxial jets

(NASA-TM-106782) p 101 N95-15059

DAVIDSON, D. L.Analysis of small crack behavior for airframe

applications p 95 N95-14484

DAVIDSON, JOHN B.High angle of attack flying qualities criteria for

longitudinal rate command systems p 70 N95-14247

DAVY, WILLIAM C.Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp 85 N95-13718

DAWICKE, D. S.Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

DELUCA, D. P.Fatigue in single crystal nickel superalloys

IAD-A282917) p 88 N95-15415

DENDA, MITSUNORIStudy of multiple cracks in airplane fuselage by

micromechanics and complex variablesp 94 N95-14468

DENTON, J. D.Designing in three dimensions p 90 N95-14130

DENVER, ANTHONY G.Extracting a representative loading spectrum from

recorded flight data p 80 N95-14469DEPLACHETT, CHARLES P.

A graphical user interface for design and analysis ofair breathing propulsion systems[TABES PAPER 94-616] p 83 N95-14645

DEPPE, MARTIN W.Combustion efficiency in a dual-inlet side-dump ramjet

combustor[AD-A283564) p 83 N95-15329

DICARLO, DANIEL J.Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

DICKES, EDWARDValidation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp 69 N95-14236

DONG, Y. F.Study of multiple cracks in airplane fuselage by

micromechanics and complex variablesp 94 N95-14468

DOWNING, MICAHUSAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889

DREGALJN, A. F.On introduction of artificial intelligence elements to heat

power engineering(BTN-94-EIX94461407961) p 100 A95-62635

DUNCAN, BEVERLY S.Computational analysis in support of the SSTO flowpath

test(NASA-TM-1067571 p 89 N95-13665

DUNHAM, R. EARL, JR.Heavy rain effects p 78 N95-14899

PERSONAL AUTHOR INDEX

EECONOMIDES, GREGORY

Knowledge-based processing tor aircraft flight controlINASA-CR-194976] p 99 N95-13727

ELLER, B. G.Vista/F-16 Multi-Axis Thrust Vectoring (MATV) control

law design and evaluation p 71 N95-14248ELLIOTT, CHARLES B, III

The role of fretting corrosion and fretting fatigue inaircraft rivet hole cracking p 94 N95-14470

ELY, WAYNE LIntegration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258ENNS, DALE F.

Multi-application controls: Robust nonlinearmultrvariable aerospace controls applications

p 71 N95-14249ERNST, HUGO A.

Fracture mechanics validity limits p 95 N95-14480ERVIN, ROBERT D.

Electrorheologically controlled landing gear[BTN-94-EIX94461047055I p 78 A95-61740

FARTHING, CHARLES LElectromagnetic reverberation characteristics of a large

transport aircraft| AD-A282923 ] p 82 N95-15392

FILISKO, FRANK E.Electrorheologically controlled landing gear

(BTN-94-EIX944610470551 p 78 A95-61740FISHER, DAVID F.

High Alpha Technology Program (HATP) ground testto flight comparisons p 68 N95-14230

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles ofattack p68 N95-14231

Free-to-roll tests of X-31 and F-18 subscale models withcorrelation to flight test results p 69 N95-14237

FLEECE, E. J.Development of anti-icing technology

IPB94-195369] p 78 N95-15439FLEMING, M.

Fatigue reliability method with in-service inspectionsp94 N95-14475

FLICK, BRADLEY C.F-18 high alpha research vehicle: Lessons learned

p69 N95-14240FORMAN, R. G.

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

FOSTER, JOHN V.Flight validation of ground-based assessment for control

power requirements at high angles of attackp70 N95-14246

FRAZIER, S. J.Composite waveform generation for EMP and lightning

direct-drive testing(AD-A284159) p 92 N95-14405

FREDELL, ROBERT S.Damage tolerant repair techniques for pressurized

aircraft fuselages[AD-A281982I p 65 N95-14144

FREYER, GUSTAV J.Electromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923) p 82 N95-15392

GAIBLE, F.Computation of supersonic air-intakes

p 74 N95-14452GALEA, S. C.

Residual strength of composites with multiple impactdamage[AD-A284230I p 87 N95-14409

GAO. M.Corrosion and corrosion fatigue of airframe aluminum

alloys p87 N95-14465GARNERO, P.

Computation of supersonic air-intakesp 74 N95-14452

GEE, KENComputational analysis of forebody tangential slot

blowing p 71 N95-14253GERASIMOV, V. F.

Profiling of the working surface of electrodes-tools forcircle electrochemical dimensional treatment of .compressor bladesIBTN-94-EIX94461407964] p 83 A95-62638

B-2

PERSONAL AUTHOR INDEX LACAU, P. G.

GHAFFARI, F.High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230GILBERT, L. f.. PAUL

Viper[NASA-CR-197191] p79 N95-13703

GIORI, KATHYApplication of airtxime field mill data for use in launch

support[HTN-95-50054] p 98 A95-62279

GLADDEN, HERBERT J.Hypersonic engine leading edge experiments in a high

heat flux, supersonic flow environmentINASA-TM-1067421 p 91 N95-14299

GLASS, EMILYKnowledge-based processing for aircraft flight control

INASA-CR-194976] p 99 N95-13727CLASSMAN, ARTHUR J.

Enhanced capabilities and updated users manual foraxial-flow turbine preliminary sizing code TURBAN[NASA-CR-195405] p 76 N95-15912

GRAVES, C. M., JR.Composite waveform generation for EMP and lightning

direct-drive testingIAD.A284159] p 92 N95-14405

GREENBERG. H. S.Requirements report for SSTO vertical take-off and

horizontal landing vehicleINASA-CR-197029) p 80 N95-14794

GREER, DONALD S.Numerical modeling of a cryogenic fluid within a fuel

tankINASA-TM-46511 p89 N95-13892

GREGORY, J. D. L.The principles of flight test assessment of

flight-safety-critical systems in helicoptersIAGARD-AG-300-VOL-12] p 77 N95-14199

GRIFFITH, J. B.Simulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 206 centrifugep86 N95-14089

GRUBER, M. L.Full-scale testing and analysis of fuselage structure

p9S N95-14485GUIST, ROY

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

GUNDO, D. P.Simulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

GURUSWAMY, GURU P.User's guide for ENSAERO: A multidisciplinary program

for fluid/structural/control interaction studies of aircraft(release 1)INASA-TM-108853] p 65 N95-13662

HHAINES, A. BARRY

Scale effects on aircraft and weapon aerodynamicsIAGARD-AG-323I p 67 N95-14103

HALL, R. M.High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230HALL, RONALD O.

Automated test environment for a real-time controlsystemI TABES PAPER 94-631] p 99 N95-14652

HAMILTON, MARK F.Effect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880HAMM, KEN

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor[NASA-TM-1088331 p 95 N95-14617

HAMPTON, ROY W.Experimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressor[NASA-TM-108833) p 95 N95-14617

HANSEN, CHRISTOPHER P.Landing gear energy absorption system

[NASA-CASE-MSC-22277-1] p 96 N95-15306HANSEN, REED S.

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

HARBAUGH, STEPHEN P.Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258HARKNESS, H. H.

Fatigue reliability method with in-service inspectionsp 94 N95-14475

HARLOW, D. G.Corrosion and corrosion fatigue of airframe aluminum

alloys p87 N95-14465HARRIS-HOBBS, RAY

Application of airborne field mill data for use in launchsupport[HTN-95-50054] p 98 A95-62279

HARRIS, CHARLES E.FAA/NASA International Symposium on Advanced

Structural Integrity Methods for Airframe Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

HARRISON, L.Artificial intelligence with applications for aircraft

[DCT/FAA/CT-94/41) p 99 N95-13895HARWOOD, D. W.

Development of anti-icing technology(PB94-195369) P 78 N95-15439

HATFIELD, MICHAEL O.Electromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923] P 82 N95-15392

HEINEMANN, KLAUS W.Development and application ol structural dynamics

analysis capabilitiesINASA-CR-1972291 p 96 N95-14922

HELALI, Y. E.Variations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air dragIHTN-95-40013) p 85 A95-62657

HENNIG, P.Aeromechanical design of modem missiles

p73 N95-14446HERNANDEZ, ESTELA

The Aluminum Falcon: A low cost modern commercialtransport[NASA-CR-197180] p 81 N95-15742

HILL, D. C.Hypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639HINDMAN, RICHARD G.

An approach for dynamic gridsI NASA-TM-1067741 p 76 N95-15853

HOEPPNER, DAVID W.The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p94 N95-14470The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p88 N95-14482HOFERT, GLENN D.

Spectral analysis of vortex/free-surface interactionIAD-A283210] p 96 N95-14658

HOLLAND, SCOTT D.Wind-tunnel blockage and actuation systems test of a

two-dimensional scramjet inlet unstart model at Mach 6[NASA-TM-109152] p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test[NASA-TM-109984] p 97 N95-15899

HOLUNGSWORTH, WILLIAM B.Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258HOU, GENE J. W.

Discrete shape sensitivity equations for aerodynamicproblemsIBTN-94-EIX94451393721] p 88 A95-61720

HOZAKI, SHIGDevelopment and application of structural dynamics

analysis capabilities[ NASA-CR. 197229] p 96 N95-14922

HUBER, PETERX-31 quasi-tailless flight demonstration

p70 N95-14243X-31 high angle of attack control system performance

p70 N95-14244HUDAK, S. J., JR.

Analysis of small crack behavior for airframeapplications p 95 N95-14484

HYNEK, DANIEL P.TDWR scan strategy implementation

[AD-A284877) p 98 N95-15749

JAMES, KEVIN D.Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255JANOWITZ, J.

Artificial intelligence with applications for aircraftIDOT/FAA/CT-94/41] p 99 N95-13895

JENNIONS, IAN K.Elements of a modern turbomachinery design system

p90 N95-14129The role of CFD in the design process

p90 N95-14135

JEONG, DAVID Y.Testing and analysis of flat and curved panels with

multiple cracks p 93 N95-14460Nonlinear bulging factor based on R-curve data

p94 N95-14476JOHNSON, CALVIN R.

Hypervelocity Impact Test Facility: A gun for hireI TABES PAPER 94-605] p 86 N95-14639

JOHNSON, D. M.Electromagnetic reverberation characteristics of a large

transport aircraftIAD-A282923] p 82 N95-15392

JONES, R.Residual strength of composites with multiple impact

damageIAD-A284230] p 87 N95-14409

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

KKAISER, TERI

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor[NASA-TM-108833] p 95 N95-14617

KARIMOV, A. KH.Profiling of the working surface of electrodes-tools for

circle electrochemical dimensional treatment ofcompressor blades(BTN-94-EIX94461407964] p 83 A95-62638

KARIMOVA, A. G.Heat transfer in the flow-through part of axial

compressors(BTN-94-EIX94461407949) p 89 A95-62267

KASUMOV, E. V.On calculated models for impellers of centrifugal

compressors[BTN-94-EIX94461407947] p 88 A95-62265

KAY, JACOBValidation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp 69 N95-14236

KIDMAN, DAVID S.Flight test results of the F-16 aircraft modified with the

axisymmelnc vectoring exhaust nozzlep 70 N95-14245

KILPATRICK, WILLIAM T.More supportable T-38A enhancement study

[AD-A283671] p 66 N95-15331KIM, Y.

Computational predictive methods for fracture andfatigue p 93 N95-14466

KING, GREGORYThe Aluminum Falcon: A low cost modern commercial

transport[NASA-CR-197180] p81 N95-15742

KLOTZ, STEPHEN P.Numerical simulation of the SOFIA flowfield

[NASA-CR-197025] p 74 N95-14612KOBAYASHI, A. S.

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

KOLWEY, HERMANAdd a dimension to your analysis of the helicopter low

airspeed environment[AD-A283982] p 79 N95-14205

KOMAROV, S. S.Soft landing on the slope surface of a landing vehicle

with an air shock-absorber of forced pressurization[ BTN-94-EIX94461407941] p 85 A95-62259

KORIVI. VAMSHI M.Discrete shape sensitivity equations for aerodynamic

problems[BTN-94-EIX94451393721] p 88 A95-61720

KOSAI, M.Axial crack propagation and arrest in pressurized

fuselage p 94 N95-14479KOSSEL, HORST

Activated buoyancy propulsion = Paradox Power (tm)[TABES PAPER 94-619] p 74 N95-14646

KRAMER, BRIANF/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254KULAGIN, S. V.

On calculated models for impellers of centrifugalcompressors[BTN-94-EIX944614079471 p 88 A95-62265

LACAU, P. G.Aeromechanical design of modem missiles

p 73 N95-14446

B-3

LACAU, R. G. PERSONAL AUTHOR INDEX

LACAU, R. G.Lateral jet control for tactical missiles

p 84 N95-14448Computation of supersonic air-intakes

p74 N95-14452LACKEY, JAMES B.

Flight validation of ground-based assessment for controlpower requirements at high angles of attack

p70 N95-14246Navy and the HARV: High angle of attack tactical utility

issues p 71 N95-14252LAING, P.

Gas turbine prediffuser-combustor performance duringoperation with air-water mixture(DOT/FAA/CT-93/52) p 83 N95-15683

LAMBERT, DENNIS M.Fracture mechanics validity limits p 95 N95-14480

LAMBORN, DANAViper

INASA-CR-197191) p 79 N95-13703LANSER, WENDY R.

High Alpha Technology Program (HATP) ground testto flight comparisons p 68 N95-14230

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles ofattack p 68 N95-14231

Comparison of full-scale, small-scale, and CFD resultsfor F/A-18 forebody Slot blowing p 72 N95-14255

LAU, BENTONDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance(NASA-TM-1088551 p 65 N95-13891

LAVELLE, THOMAS M.Graphical user interface for the NASA FLOPS aircraft

performance and sizing code| NASA-TM-106649] p 80 N95-14604

LECHTENBERG, LEONDesign and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

LEE, BURNETTAircraft maneuver envelope warning system

| NASA-CASE-ARC-11953-1) p 82 N95-14518LINCOLN, JOHN W.

Challenges for the aircraft structural integrity programp80 N95-14481

LIOU, MENG-SINGAn approach for dynamic grids

INASA-TM-106774] p 76 N95-15853LOKAJ, V. I.

Heat transfer in the flow-through part of axialcompressorsIBTN-94-EIX94461407949) p 89 A95-62267

LOR, ALEX CHOUAThe Aluminum Falcon: A low cost modem commercial

transportINASA-CR-197180) p 81 N95-15742

LOU, ZHENGElectrorheologically controlled landing gear

[BTN-94-EIX94461047055) p 78 A95-61740LOW, JOHN K. C.

Ultra-high bypass ratio jet noiseINASA-CR-195394) p 100 N95-14610

LUNSFORD. ARLEENApplication of airborne field mill data for use in launch

support[HTN-95-50054] p 98 A95-62279

MMA.LJ

The effects of pitting on fatigue crack nudeation in7075-T6 aluminum alloy p 88 N95-14482

MALCOLM, GERALD N.Static and dynamic force/moment measurements In the

Eidetics water tunnel p 69 N95-14238MARRERO, W.

Computing quantitative characteristics of finite-statereal-time systems(AD-A282839I p 83 N95-14343

MARROCCO, MATTHEWThermally stable organic polymers

IAD-A281380] p 87 N95-14363MATTHIAS, DONOVAN L.

Numerical design of advanced multi-element airfoilsINASA-CR-197135] p 76 N95-15762

MATTHEWS, RAYMOND H.Vertical flight terminal operational procedures. A

summary of FAA research and developmentIAD-A283550J p 85 N95-15328

MAURICE, MARK S.Developments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992[AD-A283011] p84 N95-13687

MCCLUNG, R. C.Analysis of small crack behavior for airframe

applications p 95 N95-14484MCCORMICK, BARNES W.

Wake turbulence p 75 N95-14894MCCURDY, DAVID A.

High-Speed Research: 1994 Sonic Boom Workshop:Atmospheric Propagation and Acceptability Studies[NASA-CP-3279] p 75 N95-14878

MCGRANE, E. J.Development of anti-icing technology

[PB94-195369] P 78 N95-15439MCGRATH, JAMES

Thermally stable organic polymers(AD-A281380I P87 N95-14363

MCOUILLEN, JOHN B.Characterization of annular two-phase gas-liquid flows

in micro-gravity p 95 N95-14556MEHTA. UNMEEL B.

Air-breathing aerospace plane development essential:Hypersonic propulsion flight testsI NASA-TM-108857] p 66 N95-14921

MELIS, MATTHEW E.Hypersonic engine leading edge experiments in a high

heat flux, supersonic flow environment[NASA-TM-106742) p 91 N95-14299

MEYN, LARRY A.Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255MIDDLETON, DAVID B.

Airplane takeoff and landing performance monitoringsystem[NASA-CASE-LAR-14745-2-SB1 p 85 N95-14415

MILLER, M.Full-scale testing and analysis of fuselage structure

p95 N95-14485MILLER, MATTHEW

Evaluation of bonded boron/epoxy doubters forcommercial aircraft aluminum structures

p 92 N95-14457The characterization of widespread fatigue damage in

fuselage structure[NASA-TM-1091421 p 88 N95-14920

MINEA, M.Computing quantitative characteristics of finite-state

real-time systemsIAD-A282839J p 83 N95-14343

MIODUSHEVSKY, P. V.Advanced method and processing technology for

complicated shape airframe part formingp80 N95-14486

MISKAKTIN, N. I.Soft landing on the slope surface of a landing vehicle

with an air shock-absorber of forced pressurizationIBTN-94-EIX94461407941) p 85 A95-62259

MOESSER, MARKThe role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p94 N95-14470MOLENT, L.

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p66 N95-14477

MOORE, FRANK G.Engineering Codes for aeroprediction: State-of-the-art

and new methods p 73 N95-14447HORAN, B.

Fatigue reliability method with in-service inspectionsp 94 N95-14475

MORRIS, PHILIP J.Noise radiation by instability waves in coaxial jets

(NASA-TM-106738J p 100 N95-14618MUKHIN, V. S.

Mechanism and technological particular features ofthermomagnetic hardening(BTN-94-EIX944614079531 p 89 A95-62627

MULDER, J. A.Identification of dynamic systems. Volume 3:

Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre design(AGARD-AG-300-VOL-3-PT-21 p 79 N95-14102

MULENBURG, G. M.Simulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

HURMAN, SCOTT M.Numerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232Numerical simulation of the flow about the F-18 HARV

at high angle of attack(N AS A-CR-197023] p 74 N95-14614

MURPHY, JACKViper

[ NASA-CR-197191 ] p 79 N95-13703MURRI, D. G.

High Alpha Technology Program (HATP) ground testto flight comparisons p 68 N95-14230

MURRI, DANIEL G.Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle P 72 N95-14257

MURTHY, S. N. B.Gas turbine prediffuser-combustor performance during

operation with air-water mixture[DOT/FAA/CT-93/52) p 83 N95-15683

MUSSER, JANAThe Aluminum Falcon: A low cost modem commercial

transportINASA-CR-197180] p 81 N95-15742

MUZZIO, DOUGExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressor| NASA-TM-1088331 p 95 N95-14617

NNAZYROVA, R. R.

On introduction of artificial intelligence elements to heatpower engineering| BTN-94-EIX94461407961) p 100 A95-62635

NELSON, N.Computational predictive methods for fracture and

fatigue p 93 N95-14466NELSON. ROBERT C.

Free-to-roll tests of X-31 and F-18 subscale models withcorrelation to night test results p 69 N95-14237

NEWMAN, J. C., JR.Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp 93 N95-14467

Development of the NASA/FLAGRO computer programfor analysis of airframe structures p 94 N95-14473

NGUYEN, KHANHDynamics of the McDonnell-Douglas Large Scale

Dynamic Rig and dynamic calibration of the rotorbalance(NASA-TM-1088551 p 65 N95-13891

NGUYEN, KHANH O.Higher harmonic control analysis for vibration reduction

of helicopter rotor systems(NASA-TM-1038551 p 66 N95-14419

NGUYEN, NHANExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressor(NASA-TM-1088331 P 95 N95-14617

Nl, R. H.Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132MOLD, DEAN E.

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-3467] p 80 N95-14852

NOVOZHILOV, K. A.The effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristics| BTN-94-EIX94461407959] p 78 A95-62633

OGBURN, MARILYN E.Flight validation of ground-based assessment for control

power requirements at high angles of attackp70 N95-14246

OKELLY, CHRISViper

[NASA-CR-197191] p 79 N95-13703ORTIZ, VINCENT M.

Evaluation of energy-sink stability criteria for dual-spinspacecraft(AD-A283228] p 87 N95-14850

PAGE, JULIET A.USAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889PAHLE, JOSEPH W.

Right validation of ground-based assessment for controlpower requirements at high angles of attack

p70 N95-14246PAINTER, JOHN H.

Knowledge-based processing for aircraft flight controlINASA-CR-194976) p 99 N95-13727

PALMER, GRANTMeasured and calculated spectral radiation from a blunt

body shock layer in an arc-jet wind tunnel| AIAA PAPER 94-0086] p 67 N95-13720

PALUMBO, GIUSEPPEVUV shock layer radiation in an arc-jet wind tunnel

experiment p 67 N95-13719

B-4

PERSONAL AUTHOR INDEX SMITH, CLAUDE

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel| AIAA PAPER 94-0086] p 67 N95-13720

PANKAJAKSHAN, RAMESHPropulsion/airframe interference tor ducted propfan

engines with ground effect|NASA-CR-197110| p 81 N95-14909

PARK, CHULMeasured and calculated spectral radiation from a blunt

body shock layer in an arc-jet wind tunnel(AIAA PAPER 94-0086) P 67 N95-13720

PARRISH, RUSSELL V.Spatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-3467) p 80 N95-14852

PAUL. J.Development of a composite repair and the associated

inspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

PAUL, J. J.Residual strength of composites with multiple impact

damage[AD-A284230] p 87 N95-14409

PENDLETON, EDPressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure dataIAD-A281561I p 76 N95-15465

PERSON, LEE H., JR.Airplane takeoff and landing performance monitoring

systemINASA-CASE-LAR-14745-2-SB) p 85 N95-14415

PETOT, BERTRANDNew methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp 90 N95-14134

PETTTT, CHRISPressure measurements on an F/A-18 twin vertical tail

in buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A281581) p 76 N95-15465

PHILLIPS, RONALD L.Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258PIASCIK, ROBERT S.

The characterisation of widespread fatigue damage infuselage structureINASA-TM-109142] p 88 N95-14920

PIKE, VERA J.A method of calculating the safe fatigue life of compact,

highly-stressed components p 93 N95-14464PLAETSCHKE, ERMIN

Parameter identification tor X-31A at high angles ofattack p 69 N95-14235

PLOTKIN, KENNETH J.USAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889POWELL, KENNETH G.

A Cartesian, cell-based approach for adaptivery-refinedsolutions of the Euler and Navier-Stokes equations[NASA-TM-1067861 p 73 N95-14297

PRABHU, RAMADAS K.An approximate Riemann solver for thermal and

chemical nonequilibrium flowsINASA-CR-1950031 p 96 N95-14912

RAJ, SHREERAMEvaluation of bonded boron/epoxy doublers for

commercial aircraft aluminum structuresp92 N95-144S7

RAJEVSKAYA. G. A.Advanced method and processing technology for

complicated shape airlrame part formingp 80 N95-14486

RALSTON, JOHNValidation of the NASA Dryden X-31 simulation and

evaluation of mechanization techniquesp 69 N95-14236

RAMAN. GANESHResonant interaction of a linear array of supersonic

rectangular jets: An experimental study(NASA-CR-195398] p 76 N95-15852

RASHIDNIA, NASSERTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563RASPET, RICHARD

Atmospheric effects on the risetime and waveshape ofsonic booms p 100 N95-14886

RAUW, MARC 0.A SIMULINK environment for flight dynamics and control

analysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Pan 2:Nonlinear analysis of the Beaver autopilotINONP-NASA-SUPPL-DK-94-2802] p 84 N95-14815

RAY, RONALD J.Design and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

REGENIE, VICTORIA A.F-18 high alpha research vehicle: Lessons learned

p69 N95-14240REINMANN, JOHN J.

Icing: Accretion, detection, protectionp 77 N95-14897

RIES, JOHN C.Precision orbit determination of altimetric satellites

p86 N95-14282RIZK, YEHIA M.

Numerical simulation of the flow about an F-18 aircraftin the high-alpha regime p 68 N95-14232

Computational analysis of forebody tangential slotblowing p 71 N95-14253

ROHLF, D.Parameter identification for X-31A at high angles of

attack p 69 N95-14235ROOS, FREDERICK W.

Low-energy pneumatic control of forebody vorticesp72 N95-14256

ROSADO, JOEL M.Aircraft maneuver envelope warning system

[NASA-CASE-ARC-11953-11 p 82 N95-14518ROSE, M. F.

Hypervelocity Impact Test Facility: A gun for hireI TABES PAPER 94-6051 p 86 N95-14639

ROSS, HOLLY M.Flight validation of ground-based assessment for control

power requirements at high angles of attackp 70 N95-14246

ROSS, J. C.High Alpha Technology Program (HATP) ground test

to flight comparisons p 68 N95-14230RUSSELL, PAUL

Knowledge-based processing for aircraft flight control[NASA-CR-194976] p 99 N95-13727

RUTHERFORD, PAULEvaluation of bonded boron/epoxy doublers for

commercial aircraft aluminum structuresp 92 N95-14457

RYZHOV, A. A.On profiling a cam of an axial aviation diesel engine

by periodic splines[BTN-94-EIX94461407946] p 82 A95-62264

SAHU, JUBARAJNavier-Stokes predictions of missile aerodynamics

p 74 N95-14451SALOV, N. N.

Investigation of heat transfer in a rotating ring gap withthe axial flow of a coolant during the rotation of the centralshaftIBTN-94-EIX94461407951] p 89 A95-62625

SANKAR, L. N.Numerical study of the effects of icing on viscous flow

over wings[NASA-CR-197102] p75 N95-14803

SAUNDERS, P.Artificial intelligence with applications for aircraft

[DOT/FAA/CT-94/41] p 99 N95-13895SAUNDERS, T.

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

SCHELLENGER, HARVEY G.X-31 quasi-tailless flight demonstration

p 70 N95-14243SCHIFF, LEWIS B.

Computational analysis of forebody tangential slotblowing ' P 71 N95-14253

SCHLECHTRIEM, S.Prediction of rotor-blade deformations due to unsteady

airloads[AD-A284467] p 81 N95-15821

SCHMIDT, W.Computational aerodynamics based on the Euler

equationsIAGARD-AG-325] p 72 N95-14264

SCHMISSEUR, JOHN D.Developments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A283011] p84 N95-13687

SCHMITZ, F. H.Modification of the Ames 40- by 80-foot wind tunnel

for component acoustic testing for the second generationsupersonic transportINASA-TM-108850] p 65 N95-13642

SCHNEIDER, GEORGESmall crack test program for helicopter materials

p92 N95-14455SCHNEIDER, JOHN R.

Evolutionary Telemetry and Command Processor (TCP)architecture p 86 N95-14162

SCHWANTJE, ROBERTEarth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance plan[NASA-CR-1960591 P 98 N95-13885

SEAMOUNT, PATRICIAX-31 high angle of attack control system performance

p70 N95-14244SEIBERT, GEORGE L.

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992| AD-A2830111 p 84 N95-13687

SHAH, GAUTAM H.Preparations for flight research to evaluate actuated

forebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

SHARMA, O. P.Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132SHARMA, SURENDRA P.

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel| AIAA PAPER 94-00861 p 67 N95-13720

SHATALOV, YU. S.On profiling a cam of an axial aviation diesel engine

by periodic splines[BTN-94-EIX944614079461 p 82 A95-62264

SHAW, T. L.Simulation of Shuttle launch G forces and acoustic loads

using the NASA Ames Research Center 20G centrifugep86 N95-14089

SHIGIN, L. B.Heat transfer in the flow-through part of axial

compressors[BTN-94-EIX94461407949] p 89 A95-62267

SHIMAMOTO, A.Axial crack propagation and arrest in pressurized

fuselage p 94 N95-14479SHIVAKUMAR, V.

Development of the NASA/FLAGRO computer programfor analysis of airlrame structures p 94 N95-14473

SHIVELY, DAVID G.Spiral microstrip antenna with resistance

INASA-CASE-LAR-15088-11 p 91 N95-14139SHROYER, CYNTHIA A.

Large amplitude nonlinear response of flat aluminum,and carbon fiber plastic beams and plates[AD-A282440] p 96 N95-15547

SHUM, C. K.Precision orbit determination of altimetric satellites

p86 N95-14282SIPAROV, S. V.

The effect of rotating loads suspended under a helicopteron their amplitude-frequency characteristics[BTN-94-EIX944614079591 p 78 A95-62633

SLATER, GARY L.Atmospheric and wind modeling for ATC

[NASA-CR-196786) p 98 N95-13725Groundspeed filtering for CTAS

[NASA-CR-197223) p 97 N95-15785SLATER, JOHN W.

An approach tor dynamic grids(NASA-TM-106774] p 76 N95-15853

SLOOFF. J. W.Computational aerodynamics based on the Euter

equations[AGARD-AG-325] p 72 N95-14264

SMAGIN, V. I.Local-optimal control of a flying vehicle, with final state

optimized[ BTN-94-EIX94461407957] p 83 A95-62631

SMITH, BROOKEF/A-18 and F-16 forebody vortex control, static and

rotary-balance results p 72 N95-14254SMITH, CHARLES A.

Evolution of a nose-wheel steering system(BTN-94-EIX94461047056] p 78 A95-61739

SMITH, CHRISTOPHERProceedings of the FAA Inspection Program Area

ReviewIAD-A283849] p 77 N95-14350

SMITH, CLAUDEEarth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance plan[NASA-CR-196059] p 98 N95-13885

B-5

SMITH, LINDA G. PERSONAL AUTHOR INDEX

SMITH, LINDA G.Developments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992[AD-A283011] p84 N95-13687

SMITH, R. URisk analysis for the fire safety of airline passengers

(PB94-194065) p77 N95-14179SOOERMAN, P. T.

Modification of the Ames 40- by 80-foot wind tunnelfor component acoustic testing for the second generationsupersonic transportINASA-TM-108850] p 65 N95-13642

SPARROW, VICTOR W.The effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887SPEARMAN, M. LEROY

A review of 50 years of aerodynamic research withNACA/NASAINASA-TM-1091631 p 102 N95-13663

SOUARER, DAVIDTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563SRIDHAR, J. K.

Identification of dynamic systems. Volume 3:Applications to aircraft. Part 2: Nonlinear analysis andmanoeuvre design|AGARD-AG-300-VOL-3-PT-2| p 79 N95-14102

SRIVATSAN, RAGHAVACHARIAirplane takeoff and landing performance monitoring

systemINASA-CASE-LAR-14745-2-SB] p 85 N95-14415

STEENKEN, WILLIAM G.Design and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

STEINBERG, RICHARD K.A graphical user interface for design and analysis of

air breathing propulsion systems(TABES PAPER 94-616) p 83 N95-14645

STELMAKOV, E. S.The effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristicsIBTN-94-EIX94461407959] p 78 A95-62633

STEPHENS, B.Hypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-6051 p 86 N95-14639STERNBERG, CHARLES A.

Flight validation of ground-based assessment for controlpower requirements at high angles of attack

p 70 N95-14246Navy and the HARV: High angle of attack tactical utility

issues p 71 N95-14252STOVALL, JOHN R.

Space Generic Open Avionics Architecture (SGOAA):Overview p 99 N95-14161

STREET, TROY A.Aero-optics system integration

| TABES PAPER 94-6041 p 100 N95-14638SUAREZ, CARLOS J.

Static and dynamic force/moment measurements in theEidetics water tunnel p 69 N95-14238

SUN, C. T.Bending effects of unsymmetric adhesively bonded

composite repairs on cracked aluminum panelsp92 N95-14456

SUTTON, M. A.Influence of crack history on the stable tearing behavior

of a thin-sheet material with multiple cracksp93 N95-14467

SWOLINSKY, MANFREDTurbulence: Engineering models, aircraft response

p84 N95-14900SZABO, BARNA A.

Elastic-plastic models for multi-site damagep92 N95-14454

TAGHAVI, RAYResonant interaction of a linear array of supersonic

rectangular jets: An experimental studyINASA-CR-1953981 p 76 N95-15852

TAMRAT, B. F.Comparison of X-31 flight, wind-tunnel, and water-tunnel

yawing moment asymmetries at high angles of attackp 68 N95-14234

TAN, P.Axial crack propagation and arrest in pressurized

fuselage p 94 N95-14479TANRIKUT, S.

Unsteady flows in turbines: Impact on designprocedure p 90 N95-14132

TAPLEY, BYRON D.Precision orbit determination of altimetric satellites

p86 N95-14282

TAYLOR, ARTHUR C.Discrete shape sensitivity equations for aerodynamic

problems(BTN-94-EIX94451393721] p 88 A95-61720

THOMAS, ALMUTTIL M.Aerodynamic shape optimization of a HSCT type

configuration with improved surface definitionINASA-CR-197011) P 67 N95-13701

THOMSON, DOUGLASTesting and analysis of flat and curved panels with

multiple cracks p 93 N95-14460THORNTON, DON

Design and development of an F/A-18 inlet distortionrake: A cost and time saving solution

p 69 N95-14241TIWARI, SURENDRA N.

Aerodynamic shape optimization of a HSCT typeconfiguration with improved surface definition(NASA-CR-1970111 p 67 N95-13701

TONG, PINNonlinear bulging factor based on R-curve data

p 94 N95-14476TRAVEN, RICARDO

Flight validation of ground-based assessment for controlpower requirements at high angles of attack

p 70 N95-14246Navy and the HARV: High angle of attack tactical utility

issues P 71 N95-14252TREFNY, CHARLES J.

Computational analysis in support of the SSTO flowpathtestINASA-TM-1067571 p 89 N95-13665

TREGO, LINDA E.Composite propeller system for Domier 328

[BTN-94-EIX944612905061 p 66 A95-61728TRIGS, DEANNE

The Aluminum Falcon: A low cost modem commercialtransportINASA-CR-197180) p 81 N95-15742

TYLER, CHARLESDevelopments in laser-based diagnostics for wind

tunnels in the Aeromechanics Division: 1987-1992IAD-A283011] p84 N95-13687

TYURIN, B. F.The effect of rotating loads suspended under a helicopter

on their amplitude-frequency characteristics(BTN-94-EIX944614079591 p 78 A95-62633

UULANOV, B. V.

Stabilization of objects with unknown nonstationaryparameters, using adaptive nonlinear continuous controlsystems[BTN-94-EIX94461407944] p 98 A95-62262

VAKHITOV, YU. M.Profiling of the working surface of electrodes-tools for

circle electrochemical dimensional treatment ofcompressor blades[BTN-94-EIX94461407964] p 83 A95-62638

VEMAGANTt, GURURAJA R.Laminar and turbulent flow computations of Type 4

shock-shock interference aerothermal loads usingunstructured grids[NASA-CR-195008) p 97 N95-15604

VUILLEZ, CHRISTOPHENew methods, new methodology: Advanced CFD in the

Snecma turbomachinery design processp90 N95-14134

WWALCHU, LAWRENCE A.

Flight evaluation of pneumatic forebody vortex controlin post-stall flight p 72 N95-14259

WALKER, LENExperimental/analytical approach to understanding

mistuning in a transonic wind tunnel compressorINASA-TM-108833] p 95 N95-14617

WALKER, S. I.Axial crack propagation and arrest in pressurized

fuselage p 94 N95-14479WEI, R. P.

Corrosion and corrosion fatigue of airframe aluminumalloys P 87 N95-14465

WEINACHT, PAULNavier-Stokes predictions of missile aerodynamics

p 74 N95-14451WEINSTEIN, LEONARD M.

An optical technique for examining aircraft shock wavestructures in flight p 96 N95-14879

WEISS, S.Parameter identification for X-31A at high angles of

attack p69 N95-14235WHITAKER, DAVID L.

Hybrid structured/unstructured grid computations for theF/A-18 at high angle of attack p 68 N95-14233

WHITING, ELLIS E.Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp85 N95-13718

WILDER, M. C.Control of unsteady separated How associated with the

dynamic stall of airfoils[ N AS A-CR-197024] p 74 N95-14613

WILKINS, K. E.Full-scale testing and analysis of fuselage structure

p95 N95-14485WILLARD, SCOTT A.

The characterization of widespread fatigue damage infuselage structure(NASA-TM-1091421 p 88 N95-14920

WILLIAMS, DAVID l_ IIFree-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237WILLIAMS, STEVEN P.

Spatial awareness comparisons between large-screen,integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-3467| p 80 N95-14852

WILSON, DAVID J.High angle of attack flying qualities criteria for

longitudinal rate command systems p 70 N95-14247WINKLER, CHRISTOPHER B.

Electrorheologically controlled landing gear[BTN-94-EIX944610470551 p 78 A95-61740

WOLFE, HOWARD F.Large amplitude nonlinear response of flat aluminum.

and carbon fiber plastic beams and platesIAD-A282440] p 96 N95-15547

WOOD, RICHARD J.Generic architectures for future flight systems

p99 N95-14159WOOD, RICHARD M.

Base passive porosity for drag reduction| NASA-CASE-LAR-15246-1] p 91 N95-14183

WOODFIELD, ALAN A.Wind shear and its effects on aircraft

p 77 N95-14898WORDEN, R. E.

Full-scale testing and analysis of fuselage structurep95 N95-14485

WRAY, RICHARD B.Space Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161

XIE, YOU-BAINew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systems[BTN-94-EIX94331336949] p 88 A95-61795

XU, MINTransport phenomena in stratified multi-fluid flo w in the

presence and absence of gravity p 95 N95-14563

YEE, SUSANThe Aluminum Falcon: A low cost modern commercial

transportINASA-CR-197180J p81 N95-15742

YOUNG, A. D.Scale effects on aircraft and weapon aerodynamics

[AGARD-AG-323] p 67 N95-14103YU, C.-T.

Axial crack propagation and arrest in pressurizedfuselage p 94 N95-14479

YUHAS, ANDREW J.Design and development of an F/A-18 inlet distortion

rake: A cost and time saving solutionp69 N95-14241

ZAMAN, K. B. M. O.Axis switching and spreading of an asymmetric jet: Role

of vorticity dynamics| NASA-TM-106385] p 73 N95-14418

ZHANG, YOU-YUNNew strategy combining backward inference with

forward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systemsIBTN-94-EIX94331336949J p 88 A95-61795

B-6

PERSONAL AUTHOR INDEX ZWERNEMAN, W. D.

ZWERNEMAN, W. D.Vista/F-16 Multi-Axis Thrust Vectoring (MATV) control

law design and evaluation p 71 N95-14248

B-7

CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Corporate SourceIndex Listing

CORPORATE SOURCE

Colorado Univ., Boulder, CO.— High performance parallel analysis of coupled problems

for aircraft propulsion[NASA-CR-195355] p 23 N95-10132

Listings in this index are arranged alphabeticallyby corporate source. The title of the document isused to provide a brief description of the subjectmatter. The page number and the accessionnumber are included in each entry to assistthe user in locating the abstract in the abstractsection. If applicable, a report number is alsoincluded as an aid in identifying the document.

Academy of Sciences (USSR), Moscow (USSR).Advanced method and processing technology for

complicated shape airframe part formingp80 N95-14486

Advisory Group for Aerospace Research andDevelopment, Neuilly-Sur-Selne (France).

AGARD highlights 94/2IAGARD-HIGHLIGHTS-94/2] p 102 N95-13640

Identification of dynamic systems. Volume 3:Applications to aircraft. Part 2; Nonlinear analysis andmanoeuvre design|AGARD-AG-300-VOL-3-PT-2| p 79 N95-14102

Scale effects on aircraft and weapon aerodynamicsIAGARD-AG-323] p 67 N95-14103

Turbomachinery Design Using CFDIAGARD-LS-195] p 89 N95-14127

Quality assessment for wind tunnel testingIAGARD-AR-304] p 67 N95-14197

The principles of flight test assessment offlight-safety-critical systems in helicopters[AGARD-AG-300-VOL-12] p 77 N95-14199

A selection of experimental test cases for the validationof CFD codes, volume 1IAGARD-AR-303-VOL-1] p 91 N95-14201

Computational aerodynamics based on the EulerequationsIAGARD-AG-325I p 72 N95-14264

Missile Aerodynamics(AGARD-R-804] p 73 N95-14445

Flight in an Adverse Environment[AGARD-LS-197] p 77 N95-14893

Aerojet-General Corp., Azusa, CA.Earth Observing System (EOS)/Advanced Microwave

Sounding Unit-A (AMSU-A) software assurance planINASA-CR-196059] p 98 N95-13885

Aeronautical Research Labs., Melbourne (Australia).Residual strength of composites with multiple impact

damage|AD-A284230| p 87 N95-14409

Aeronautical Systems Dlv., Wright-Patterson AFB, OH.Challenges for the aircraft structural integrity program

p80 N95-14481Aerospatiale, Verrieres-L-Buisson (France).

Computation of supersonic air-intakesp 74 N95-14452

Air Force Inst. of Tech., Wright-Patterson AFB, OH.Damage tolerant repair techniques for pressurized

aircraft fuselages|AD-A281982| p 65 N9S-14144

Effect of surface roughness on local film coolingeffectiveness and heat transfer coefficientsIAD-A283854J p 91 N95-14351

Allied-Signal Aerospace Co., Phoenix, AZ.Advanced Turbine Technology Applications Project

(ATTAP)| NASA-CR-1953931 p 101 N95-15743

Analytical Services and Materials, Inc., Hampton, VA.Hybrid structured/unstructured grid computations for the

F/A-18 at high angle of attack p 68 N95-14233Army Communications-Electronics Command, Fort

Monmouth, NJ.Spatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches|NASA-TP-3467| p 80 N95-14852

Army Research Lab., Aberdeen Proving Ground, MD.Navier-Stokes predictions of missile aerodynamics

p 74 N95-14451Army Strategic Defense Command, Huntsvllle, AL

Aero-optics system integration[TABES PAPER 94-604) p 100 N95-14638

Army Test and Evaluation Command, AberdeenProving Ground, MD.

Test Operation Procedure (TOP): Vibration testing ofhelicopter equipmentIAD-A284433J p 81 N95-15815

Auburn Univ., ALHypervelocity Impact Test Facility: A gun for hire

[TABES PAPER 94-605] p 86 N95-14639

BBlhrte Applied Research, Inc., Jericho, NY.

Validation of the NASA Dryden X-31 simulation andevaluation of mechanization techniques

p 69 N95-14236Boeing Co., Seattle, WA.

Full-scale testing and analysis of fuselage structurep 95 N95-14485

California Polytechnic State Univ., San Luis Obispo,CA.

Numerical design of advanced multi-element airfoils[NASA-CR-197135] p 76 N95-15762

Cambridge Univ., Cambridge (England).Designing in three dimensions p 90 N95-14130

Carnegie-Mellon Univ., Pittsburgh, PA.Computing quantitative characteristics of finite-state

real-time systems[AD-A282839] p 83 N95-14343

Transport phenomena in stratified multi-fluid flo w in thepresence and absence of gravity p 95 N95-14563

Cincinnati Univ., OH.Atmospheric and wind modeling for ATC

[NASA-CR-1967861 p 98 N95-13725Assessment of CTAS ETA prediction capabilities

| NASA-CR-197224] p 97 N95-15728Groundspeed filtering for CTAS

I NASA-CR-197223] p 97 N95-15785

Defence Research Agency, Famborough, Hampshire(England).

A method of calculating the safe fatigue life of compact,highly-stressed components p 93 N95-14464

Deutsche Aerospace A.G., Munich (Germany).X-31 quasi-tailless flight demonstration

p70 N95-14243Aeromechantcal design of modern missiles

p 73 N95-14446Deutsche Forschungs- und Versuchsanstalt fuer Luft-

und Raumfahrt, Brunswick (Germany).Parameter identification for X-31 A at high angles of

attack p69 N95-14235

Eidettcs Aircraft, Inc., Torrance, CA.Static and dynamic force/moment measurements in the

Eidetics water tunnel p 69 N95-14238F/A-18 and F-16 forebody vortex control, static and

rotary-balance results P 72 N95-14254Eloret Corp., Palo Alto, CA.

Development and application of structural dynamicsanalysis capabilitiesI NASA-CR-1972291 p 96 N95-14922

Engineering Software Research and Development,Inc., Saint Louis, MO.

Elastic-plastic models for multi-site damageP92 N95-14454

Fairchild Space Co., Germantown, MD.Evolutionary Telemetry and Command Processor (TCP)

architecture p 86 N95-14162Federal Aviation Administration, Atlantic City, NJ.

Proceedings of the FAA Inspection Program AreaReviewIAD-A283849] p 77 N95-14350

Federal Aviation Administration, Cambridge, MA.Inspecting for widespread fatigue damage: Is partial

debonding the key? p 93 N95-14458Nonlinear bulging factor based on R-curve data

p 94 N95-14476Federal Aviation Administration, Kansas City, MO.

Fatigue evaluation of empennage, forward wing, andwinglets/tip fins on part 23 airplanes[PB94-196813I p 79 N95-13981

FractuResearch, Inc., Galena, OH.Testing and analysis of flat and curved panels with

multiple cracks p 93 N95-14460

Galaxy Scientific Corp., Pleasantville, NJ.Artificial intelligence with applications for aircraft

(DOT/FAA/CT-94/411 p 99 N95-13895General Electric Co., Cincinnati, OH.

Elements of a modern turbomachinery design systemp 90 N95-14129

The role of CFD in the design processP90 N95-14135

Georgia Inst. of Tech., Atlanta, GA.Fracture mechanics validity limits p 95 N95-14480Numerical study of the effects of icing on viscous flow

over wings[NASA-CR-197102] p75 N95-14803

Industrteanlagen-Betriebsgesellschaftm.b.H.,Ottobrunn (Germany).

Thermoacoustic environments to simulate reentryconditions p 86 N95-14096

Israel Aircraft Industries Ltd., Tashan (Israel).Probabilistic inspection strategies for minimizing service

failures p 93 N95-14461

KKossel (Horst), Shrewsbury, MA.

Activated buoyancy propulsionI TABES PAPER 94-6191

Paradox Power (tm)p 74 N95-14646

C-1

Lehigh Univ. CORPORA TE SOURCE

Lehigh Univ., Bethlehem, PA.Corrosion and corrosion fatigue of airframe aluminum

alloys p87 N95-14465Lockheed Aeronautical Systems Co, Marietta, GA.

Thermally stable organic polymers[AD-A281380] p 87 N95-14363

Lockheed Corp., Fort Worth, TX.Flight test results of the F-16 aircraft modified with the

axtsymmetric vectoring exhaust nozzlep 70 N95-14245

Vista/F-16 Multi-Axis Thrust Vectoring (MATV) controllaw design and evaluation p 71 N9S-14248

Lockheed Engineering and Sciences Co, Hampton,VA.

An approximate Riemann solver for thermal andchemical nonequilibrium flows[NASA-CR-19S003I p 96 N95-14912

Laminar and turbulent flow computations of Type 4shock-shock interference aerothermal loads usingunstructured grids| NASA-CR-195008] p 97 N95-15604

Lockheed Engineering and Sciences Co., Houston, TX.Space Generic Open Avionics Architecture (SGOAA):

Overview p 99 N95-14161Loral Systems, Inc., Orlando, Fl_

Advanced distributed simulation technology advancedrotary wing aircraft. Study comparing approaches tomodeling the ARWA main rotorIAD-A280824] p 79 N95-14306

ADST ARWA visual system module software designdocumentIAD-A283874] p 99 N95-14357

MMassachusetts InsL of Tech., Cambridge.

TOWR scan strategy implementationIAD-A284877] p 98 N95-15749

MCAT InsL, Mofiett Field, CA.Planetary entry experiments

INASA-CR-194215) p 101 N95-13717Science objectives and performance of a radiometer

and window design for atmospheric entry experimentsp 85 N95-13718

MCAT InsL, San Jose, CA.Numerical simulation of the SOFIA flowfield

INASA-CR-1970251 p 74 N95-14612Control of unsteady separated flow associated with the

dynamic stall of airfoilsINASA-CR-197024] p 74 N95-14613

Numerical simulation of the flow about the F-18 HARVat high angle of attackINASA-CR-197023] p 74 N95-14614

McDonnell-Douglas Corp, Saint Louis, MO.Integration of a mechanical forebody vortex control

system into the F-15 p 72 N95-14258McDonnell-Douglas Research Labs, Saint Louis, MO.

Low-energy pneumatic control of forebody vorticesp72 N95-14256

Midwest Research InsL, Kansas City, MO.Development of anti-icing technology

[PB94-195369) p 78 N95-15439Minnesota Dept of Transportation, Ouluth, MN.

Development of anti-icing technology|PB94-195369| p 78 N95-15439

Mississippi State Univ., State College, MS.Propulsion/airframe interference for ducted proptan

engines with ground effect[NASA-CR-197110J p81 N95-14909

Mississippi Univ., University, MS.Atmospheric effects on the risetime and waveshape of

sonic booms p 100 N9S-14886Monash Univ., Clayton (Australia).

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

NNational Aeronautics and Space Administration. Ames

Research Center, Moffett Field, CA.Modification of the Ames 40- by 80-foot wind tunnel

for component acoustic testing for the second generationsupersonic transport(N AS A-TM-108850] p 65 N95-13642

User's guide for ENSAERO: A multidisciplinary programfor fluid/structural/control interaction studies of aircraft(release 1)| NASA-TM-108853) p 65 N95-13662

VUV shock layer radiation in an arc-jet wind tunnelexperiment p 67 N95-13719

Measured and calculated spectral radiation from a bluntbody shock layer in an arc-jet wind tunnel[ AIAA PAPER 94-0086] p 67 N95-13720

Dynamics of the McDonnell-Douglas Large ScaleDynamic Rig and dynamic calibration of the rotorbalance| NASA-TM-108855] P 65 N95-13891

Simulation of Shuttle launch G forces and acoustic loadsusing the NASA Ames Research Center 20G centrifuge

p 86 N95-14089Numerical simulation of the flow about an F-18 aircraft

in the high-alpha regime p 68 N95-14232Free-to-roll tests of X-31 and F-18 subscale models with

correlation to flight test results p 69 N95-14237Computational analysis of forebody tangential slot

blowing P 71 N95-14253Comparison of full-scale, small-scale, and CFD results

for F/A-18 forebody slot blowing p 72 N95-14255Higher harmonic control analysis for vibration reduction

of helicopter rotor systems[NASA-TM-1038551 p 66 N95-14419

Aircraft maneuver envelope warning systemI NASA-CASE-ARC-11953-1] p 82 N95-14518

Experimental/analytical approach to understandingmistuning in a transonic wind tunnel compressor[NASA-TM-108833] p 95 N95-14617

Air-breathing aerospace plane development essential:Hypersonic propulsion flight testsI NASA-TM-108857] p 66 N95-14921

National Aeronautics and Space Administration. HughL. Dryden Flight Research Center, Edwards, CA.

Fourth High Alpha Conference, volume 1INASA-CP-10143-VOL-1] p 67 N95-14229

Flight and full-scale wind-tunnel comparison of pressuredistributions from an F-18 aircraft at high angles ofattack p 68 N95-14231

Fourth High Alpha Conference, volume 2(NASA-CP-10143-VOL-2) p 69 N95-14239

F-18 high alpha research vehicle: Lessons learnedp69 N95-14240

Design and development of an F/A-18 inlet distortionrake: A cost and time saving solution

p69 N95-14241X-31 high angle of attack control system performance

p 70 N95-14244Multi-application controls: Robust nonlinear

multivariable aerospace controls applicationsp 71 N95-14249

Fourth High Alpha Conference, volume 3INASA-CP-10143-VOL-3] p 71 N95-14251

National Aeronautics and Space Administration. HughL Dryden Flight Research Facility, Edwards, CA.

Numerical modeling of a cryogenic fluid within a fueltankINASA-TM-4651] p 89 N95-13892

National Aeronautics and Space Administration. JohnF. Kennedy Space Center, Cocoa Beach, Fl_

Application of airborne field mill data for use in launchsupport(HTN-95-50054) p 98 A95-62279

National Aeronautics and Space Administration.Lyndon B. Johnson Space Center, Houston, TX.

Development of the NASA/FLAGRO computer programtor analysis of airframe structures p 94 N95-14473

Landing gear energy absorption system(NASA-CASE-MSC-22277-1 ] p 96 N95-15306

National Aeronautics and Space Administration.Langley Research Center, Hampton, VA.

A review of 50 years of aerodynamic research withNACA/NASA(NASA-TM-109163J p 102 N95-13663

Spiral microstrip antenna with resistanceINASA-CASE-LAR-15088-1J p 91 N95-14139

Base passive porosity for drag reductionINASA-CASE-LAR-15246-1] p 91 N95-14183

High Alpha Technology Program (HATP) ground testto flight comparisons p 68 N95-14230

Comparison of X-31 flight, wind-tunnel, and water-tunnelyawing moment asymmetries at high angles of attack

p68 N95-14234Flight validation of ground-based assessment for control

power requirements at high angles of attackp 70 N95-14246

High angle of attack flying qualities criteria forlongitudinal rate command systems p 70 N95-14247

Preparations for flight research to evaluate actuatedforebody strakes on the F-18 high-alpha researchvehicle p 72 N95-14257

Airplane takeoff and landing performance monitoringsystemINASA-CASE-LAR-14745-2-SB) p 85 N95-14415

FAA/NASA International Symposium on AdvancedStructural Integrity Methods for Airfrarne Durability andDamage Tolerance[NASA-CP-3274-PT-1] p 92 N95-14453

Influence of crack history on the stable tearing behaviorof a thin-sheet material with multiple cracks

p 93 N95-14467Spatial awareness comparisons between large-screen,

integrated pictorial displays and conventional EFISdisplays during simulated landing approaches[NASA-TP-3467] p 80 N95-14852

High-Speed Research: 1994 Sonic Boom Workshop:Atmospheric Propagation and Acceptability StudiesINASA-CP-3279] p 75 N95-14878

An optical technique for examining aircraft shock wavestructures in (light p 96 N95-14879

Heavy rain effects p 78 N95-14899The characterization of widespread fatigue damage in

fuselage structure(NASA-TM-109142] p 88 N95-14920

Research and technology highlights, 1993INASA-TM-4575) p 102 N95-15065

Wind-tunnel blockage and actuation systems test of atwo-dimensional scramjet inlet unstart model at Mach 6| NASA-TM-1091521 p 97 N95-15898

Two-dimensional scramjet inlet unstart model:Wind-tunnel blockage and actuation systems test(NASA-TM-109984] p 97 N95-15899

National Aeronautics and Space Administration. LewisResearch Center, Cleveland, OH.

Computational analysis in support of the SSTO flowpathtest[NASA-TM-106757] p 89 N95-13665

A Cartesian, cell-based approach for adaptively-refinedsolutions of the Euler and Navier-Stokes equations| NASA-TM-1067861 p 73 N95-14297

Hypersonic engine leading edge experiments in a highheat flux, supersonic flow environment[NASA-TM-106742] p 91 N95-14299

Axis switching and spreading of an asymmetric jet: Roleof vorticity dynamics[NASA-TM-106385] p 73 N95-14418

Characterization of annular two-phase gas-liquid flowsin microgravity p 95 N95-14556

Graphical user interface for the NASA FLOPS aircraftperformance and sizing code[NASA-TM-1066491 p 80 N95-14604

Noise radiation by instability waves in coaxial jets(NASA-TM-106738) p 100 N95-14618

Icing: Accretion, detection, protectionp 77 N95-14897

The aeroacoustics of supersonic coaxial jets| NASA-TM-106782] p 101 N95-15059

An approach for dynamic grids[NASA-TM-106774] p 76 N95-15853

National Aeronautics and Space Administration.Marshall Space Flight Center, Huntsville, AL.

Building complex simulations rapidly using MATRIX(x):The Space Station redesign[TABES PAPER 94-632) p 87 N95-14653

National InsL of Standards and Technology,Gaithersburg, MD.

Risk analysis for the fire safety of airline passengers(PB94-194065] p77 N95-14179

National Science Foundation, Washington, DC.Propulsion/airframe interference for ducted propfan

engines with ground effect(NASA-CR-197110) p 81 N95-14909

National Transportation Safety Board, Washington,DC.

Aircraft accident report: Overspeed and loss of poweron both engines during descent and power-off emergency.landing Simmons Airlines. Inc., d/b/a, American EagleFlight 3641, N349SB False River Air Park. New Roads.Lousiana. 1 February 1994 p 78 N95-14916

Annual review of aircraft accident data: US air carrieroperations, calendar year 1992 p 78 N95-15066

Naval Air Warfare Center, Patuxent River, MD.Add a dimension to your analysis of the helicopter low

airspeed environmentIAD-A283982] p 79 N95-14205

X-31 post-stall envelope* expansion and tactical utilitytesting p 70 N95-14242

Navy and the HARV: High angle of attack tactical utilityissues p 71 N95-14252

Composite waveform generation for EMP and lightningdirect-drive testing(AD-A284159) p 92 N95-14405

Naval Postgraduate School, Monterey, CA.Spectral analysis of vortex/free-surface interaction

[AD-A283210] p 96 N95-14658Artificial neural network modeling of damaged aircraft

[AD-A283227] p 80 N95-14849Evaluation of energy-sink stability criteria for dual-spin

spacecraft[AD-A283228) p 87 N95-14850

Low-speed wind tunnel testing of the NPS and NASAAmes Mach 6 optimized waverider(AD-A283585) p 75 N95-15319

C-2

CORPORA TE SOURCE Wyle Labs., Inc.

Combustion efficiency in a dual-inlet side-dump ramjetcombustor[AD-A283564] p 83 N9S-1S329

Naval Surface Warfare Center, Dahlgren, VA.Engineering Codes for aeroprediction: State-of-the-art

and new methods p 73 N95-14447Electromagnetic reverberation characteristics of a large

transport aircraft[AD-A282923] p 82 N9S-15392

Northwestern Univ., Evanston, ll_Fatigue reliability method with in-service inspections

p94 N95-14475NYMA, Inc., Brook Park, OH.

Resonant interaction of a linear array of supersonicrectangular jets: An experimental studyINASA-CR-195398] p 76 N95-158S2

Office National d'Etudes et de RecherchesAerospatiales, Paris (France).

Lateral jet control for tactical missilesp84 N9S-14448

High angle of attack aerodynamics p 74 N95-14450Old Dominion Univ., Norfolk, VA.

Aerodynamic shape optimization of a HSCT typeconfiguration with improved surface definitionINASA-CR-197011] p 67 N95-13701

Pennsylvania State Univ., University Park, PA.The effect of aircraft speed on the penetration of sonic

boom noise into a flat ocean p 100 N95-14887Wake turbulence p 75 N95-14894

Pratt and Whitney Aircraft, East Hartford, CT.Unsteady flows in turbines: Impact on design

procedure p 90 N95-14132Ultra-high bypass ratio jet noise

[NASA-CR-19S394] p 100 N95-14610Pratt and Whitney Aircraft, West Palm Beach, Fl_

Fatigue in single crystal nickel superalloys|AD-A282917| p 88 N95-15415

Purdue Univ., West Lafayette, IN.Bending effects of unsymmetric adhesively bonded

composite repairs on cracked aluminum panelsp92 N95-14456

Gas turbine prediffuser-combustor performance duringoperation with air-water mixtureIDOT/FAA/CT-93/52] p 83 N95-15683

RAND Corp., Santa Monica, CA.The F-16 multinational staged improvement program:

A case study of risk assessment and risk management|AD-A281706| p 81 N9S-15451

Rockwell International Corp., Downey, CA.Requirements report for SSTO vertical take-off and

horizontal landing vehicleINASA-CR-1970291 p 80 N95-14794

Rockwell International Corp., El Segundo, CA.Extracting a representative loading spectrum from

recorded flight data p 80 N95-14469Rockwell International Corp., Huntsvllle, AL.

Automated test environment for a real-time controlsystem[TABES PAPER 94-631 | p 99 N95-14652

Rome Lab., Griffiss AFB, NY.Generic architectures for future flight systems

p99 N95-141S9Rutgers Univ., Piscataway, NJ.

Study of multiple cracks in airplane fuselage bymicromechanics and complex variables

p 94 N95-14468

Soclete Nationale d'Etude et de Construction deMoteurs deviation, Molssy-Cramayel (France).

New methods, new methodology: Advanced CFD in theSnecma turbomachinery design process

p90 N95-14134Southwest Research Inst, San Antonio, TX.

Analysis of small crack behavior for airframeapplications p 95 N95-14484

Spectra Research Systems, Inc., Huntsvllle, ALA graphical user interface tor design and analysis of

air breathing propulsion systems[TABES PAPER 94-616) p 83 N95-14645

Stevens Inst. of Tech., Hoboken, NJ.Computational predictive methods for fracture and

fatigue p 93 N95-14466

Sutzer Innotec A.GM Wlnterthur (Switzerland).Computational methods for preliminary design and

geometry definition in turbomachineryp89 N95-14128

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

Systems Control Technology, Inc., Arlington, VA.Vertical flight terminal operational procedures. A

summary of FAA research and developmentIAD-A2835501 P 85 N95-15328

Sytronlcs, Inc., Dayton, OH.More supportable T-38A enhancement study

IAD-A283671] p 66 N95-15331

Technische Hochschule, Aachen (Germany).Prediction of rotor-blade deformations due to unsteady

airloadsIAD-A284467] p 81 N95-15821

Technische Univ., Brunswick (Germany).Turbulence: Engineering models, aircraft response

p84 N9S-14900Technische Univ., Delft (Netherlands).

A SIMULINK environment for flight dynamics and controlanalysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilot[NONP-NASA-SUPPL-DK-94-2802I p 84 N95-14815

Technische Univ., Munich (Germany).Aero design of turbomachinery components: CFD in

complex systems p 90 N95-14136Teias ASM Univ., College Station, TX.

Knowledge-based processing for aircraft flight controlINASA-CR-1949761 p 99 N95-13727

Texas Univ., Austin, TX.Precision orbit determination of alt/metric satellites

p 86 N95-14282Effect of stratification and geometrical spreading on

sonic boom rise time p 75 N95-14880Textron Specialty Materials, Lowell, MA.

Evaluation of bonded boron/epoxy doubters forcommercial aircraft aluminum structures

p 92 N95-14457Toledo Univ., OH.

Enhanced capabilities and updated users manual foraxial-flow turbine preliminary sizing code TURBAN[ NASA-CR-195405] p 76 N95-15912

uUnited Technologies Research Center, East Hartford,

CT.Small crack test program for helicopter materials

p 92 N95-14455Universities Space Research Association, Columbia,

MD.Viper

(NASA-CR-1971911 p 79 N95-13703The Aluminum Falcon: A low cost modem commercial

transport[NASA-CR-1971801 p 81 N95-15742

Utah Univ., Salt Lake City, UT. 'The role of fretting corrosion and fretting fatigue in

aircraft rivet hole cracking p 94 N95-14470The effects of pitting on fatigue crack nucleation in

7075-T6 aluminum alloy p 88 N95-14482

wWashington Univ., Seattle, WA.

Axial crack propagation and arrest in pressurizedfuselage p94 N95-14479

Woodfield (Alan A.), Bedford (England).Wind shear and its effects on aircraft

p77 N95-14898Wright Lab., Wright-Patterson AFB, OH.

Developments in laser-based diagnostics for windtunnels in the Aeromechanics Division: 1987-1992IAD-A283011] pB4 N95-13687

Flight evaluation of pneumatic forebody vortex controlin post-stall flight p 72 N95-14259

Pressure measurements on an F/A-18 twin vertical tailin buffeting flow. Volume 2: Steady and unsteady RMSpressure data[AD-A281581J p 76 N95-15465

Large amplitude nonlinear response of flat aluminum,and carbon fiber plastic beams and plates[AD-A282440I p 96 N95-15547

Wyte Labs., Inc., Arlington, VA.USAF single-event sonic boom prediction model:

PCBoomS p 101 N95-14889

C-3

FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Foreign TechnologyIndex Listing

[COUNTRY OF INTELLECTUAL ORIGIN]

FRANCEI Numerical study of Gortter instability Application to the

design of a quiet supersonic wind tunnel[PB94-1B4B011 p21 N95-10844

i_iTm- I REPORTH TITLE | NUMBER

Listings in this index are arranged alphabeticallyby country of intellectual origin. The title of thedocument is used to provide a brief descriptionof the subject matter. The page number andaccession number are included in each entryto assist the user in locating the abstract inthe abstract section. If applicable, a report num-ber is also included as an aid in identifyingthe document.

AUSTRALIAResidual strength of composites with multiple impact

damage|AD-A284230| p 87 N95-14409

Development of a composite repair and the associatedinspection intervals for the F-111C stiffener runoutregion p 66 N95-14477

New methods, new methodology: Advanced CFD in theSnecma turbomachinery design process

p90 N95-14134Quality assessment for wind tunnel testing

IAGARD-AR-304] p 67 N95-14197The principles of flight test assessment of

flight-safety-critical systems in helicopters[AGARD-AG-300-VOL-12I p 77 N95-14199

A selection of experimental test cases for the validationof CFD codes, volume 1[AGARD-AR-303-VOL-1] p 91 N95-14201

Computational aerodynamics based on the EulerequationsIAGARD-AG-325I p 72 N95-14264

Missile Aerodynamics(AGARD-R-804) p 73 N95-14445

Lateral jet control for tactical missilesp 84 N9S-14448

High angle of attack aerodynamics p 74 N95-14450Computation of supersonic air-intakes

p74 N95-14452Flight in an Adverse Environment

IAGARD-LS-197] p 77 N95-14893

GERMANYThermoacoustic environments to simulate reentry

conditions p 86 N95-14096Aero design of turbomachinery components: CFD in

complex systems p 90 N95-14136Parameter identification for X-31A at high angles of

attack p69 N9S-14235X-31 quasi-tailless flight demonstration

p70 N95-14243Aeromechanical design of modern missiles

p 73 N95-14446Turbulence: Engineering models, aircraft response

p84 N95-14900Prediction of rotor-blade deformations due to unsteady

airloadsIAD-A284467] p 81 N95-15821

ISRAELProbabilistic inspection strategies for minimizing sen/ice

failures p 93 N95-14461

Mechanism and technological particular features ofthermomagnetic hardening(BTN-94-EIX94461407953] p 89 A95-62627

Local-optimal control of a flying vehicle, with final stateoptimized[BTN-94-EIX94461407957 ] p 83 A95-62631

The effect of rotating loads suspended under a helicopteron their amplitude-frequency characteristics[BTN-94-EIX944614079591 p 78 A95-62633

On introduction of artificial intelligence elements to heatpower engineering[BTN-94-EIX94461407961I p 100 A95-62635

Profiling of the working surface of electrodes-tools forcircle electrochemical dimensional treatment ofcompressor blades|BTN-94-EIX94461407964| p 83 A95-62638

SWITZERLANDComputational methods for preliminary design and

geometry definition in turbo-machineryp89 N95-14128

The industrial use of CFD in the design ofturbomachinery p 90 N95-14133

uUKRAINE

Investigation of heat transfer in a rotating ring gap withthe axial flow of a coolant during the rotation of the centralshaft[BTN-94-EIX94461407951] p 89 A95-62625

UNITED KINGDOMDesigning in three dimensions p 90 N95-14130A method of calculating the safe fatigue life of compact,

highly-stressed components p 93 N95-14464Wind shear and its effects on aircraft

p 77 N95-14898USSR

Advanced method and processing technology forcomplicated shape airframe part forming

p80 N95-14486

NCHINA

New strategy combining backward inference withforward inference in monitoring and diagnosing techniquesfor hydrodynamic bearing-rotor systemsIBTN-94-EIX94331336949) p 88 A95-61795

NETHERLANDSA SIMULINK environment for flight dynamics and control

analysis: Application to the DHC-2 Beaver. Part 1:Implementation of a model library in SIMULINK. Part 2:Nonlinear analysis of the Beaver autopilot[NONP-NASA-SUPPL-DK-94-2802] p 84 N95-14815

EGYPTVariations of perturbations in perigee height with

eccentricity for artificial Earth's satellites due to air drag[HTN-95-40013] p 85 A95-62657

FRANCEAGARD highlights 94/2

IAGARD-HIGHLIGHTS-94/2) p 102 N95-13640Identification of dynamic systems. Volume 3:

Applications to aircraft. Part Z: Nonlinear analysis andmanoeuvre designIAGARD-AG-300-VOL-3-PT-2J p 79 N95-14102

Scale effects on aircraft and weapon aerodynamics[AGARD-AG-323] p 67 N95-14103

Turbomachinery Design Using CFD[AGARD-LS-195J p 89 N95-14127

RUSSIASoft landing on the slope surface of a landing vehicle

with an air shock-absorber of forced pressurization[BTN-94-EIX94461407941J p 85 A95-62259

Stabilization of objects with unknown nonstationaryparameters, using adaptive nonlinear continuous controlsystems(BTN-94-EIX94461407944) p 98 A95-62262

On profiling a cam of an axial aviation diesel engineby periodic splines[BTN-94-EIX94461407946] p 82 A95-62264

On calculated models for impellers of centrifugalcompressors(BTN-94-EIX94461407947] p 88 A95-62265

Heat transfer in the flow-through part of axialcompressorsIBTN-94-EIX94461407949J p 89 A95-62267

D-1

CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Contract NumberIndex Listing

N00014.82-K.Q165 p 22 N95-10231

CONTRACTNUMBER

Listings in this index are arranged alphanumeri-cally by contract number. Under each contractnumber the accession numbers denoting docu-ments that have been produced as a result ofresearch done under the contract are shown. Theaccession number denotes the number by whichthe citation is identified in the abstract section.Preceding the accession number is the pagenumber on which the citation may be found.

AFPROJ. 1397 p92 N95-14456AF PROJ. 2401 p 96 N95-15547AF PROJ. 2404 p 84 N95-13687DA PROJ. 1L1-62211-A-47-A p 80 N9S-14852DAAL03-92-C-0021 p 87 N95-14363DASG60-84-C-0117 p 98 A95-62279DASG60-89-C-0147 p 98 A95-62279DEN3-335 P101 N95-15743DNA001-90-C-0127 p B6 N95-14639DOT-SHRP-H-208A p 78 N95-15439DTFAO3-89-C-00043 p 99 N95-13895DTFA01-87-C-00014 p 85 N95-15328DTFA01-93-Z-02012 p 98 N95-15749DTFA03-92-2-00018 p 77 N95-14179FAA-92-G-0004 p 94 N95-14470FAA-92-G-0005 p 94 N95-14479FAA-92-G-0006 p 87 N95-14465FAA-92-G-002 p 83 N9S-15683FAA-93-G-0068 p 94 N95-14470F04701-90-C-0023 p 98 A95-62279F09603-89-G-0096 p 92 N95-14455F19628-90-C-0002 p 98 N95-15749F33657-93-C-2440 p 66 N95-15331F49620-91-C-0003 p 81 N95-15451MDA972-90-C-0035 p 83 N95-14343NAG1-1066 p99 N95-13727NAG1-1329 _ p86 N95-14639NAG1-226 p 81 N95-14909NAG2-175 p 98 N95-13725NAG3-1165 p76 N95-15912NAG3-510 p 95 N95-14556NAG3-768 p 75 N95-14803NAG9-622 p 92 N95-14454NASW-4435 p79 N95-13703

p81 N95-1S742NAS1-19000 p96 N95-14912

p97 N95-15604NAS10-11853 p98 A95-62279NAS2-13571 p69 N95-14238NAS3-26618 p 100 N95-14610NAS3-27186 p 89 N95-13665

p76 N95-15852NASS-32314 p 98 N95-13885NCC1-193 p 80 N95-14794NCC1-68 p67 N95-13701NCC2-518 p 96 N95-14922NCC2-636 p 74 N95-14612NCC2-637 p 74 N95-14613NCC2-653 p67 N95-13719

p67 N95-13720NCC2-669 : p 97 N95-1S728

p97 N95-15785NCC2-729 P 74 N9S-14614NCC2-762 P 101 N95-13717NCC2-813 P76 N95-15762NCC2-9003 pBO N95-14794NCC8-39 pBO N95-14794NGT-50441 p 76 N95-15853N00014-91-C-0124 p88 N95-15415N61339-91-D-0001 p 79 N95-14306

p 99 N95-14357N68171-94-C-9068 p 81 N95-15821RTOP 232-01-04-06 p 96 N95-14912

p 97 N95-15604RTOP 505-38-13 p 65 N95-13642RTOP 505-52-52 p 101 N95-15059RTOP 505-59-36 p 65 N95-13891RTOP 505-59-53 p 66 N95-14921RTOP 505-61-51 p66 N95-14419RTOP 505-62-52 p 73 N95-14297

p91 N95-14299p73 N95-14418p 100 N95-14618p 76 N95-15853

RTOP 505-64-52-01 p 99 N95-13727RTOP 505-64-53-03 p 80 N95-14852RTOP 505-68-30 p 67 N95-14229RTOP 505^9-20-01 p 102 N95-13663RTOP 505-69-50 p 80 N95-14604

p 76 N95-15912RTOP 505-70-59 p 89 N95-13665RTOP 505-70-63 p 89 N95-13892RTOP 509-10-11 p65 N95-13662RTOP 537-02-22 p 76 N95-15852RTOP 537-03-21-03 p 75 N95-14878RTOP 538-02-10-01 p92 N95-14453

p88 N95-14920RTOP 538-03-11 p 100 N95-14610RTOP 763-23-35-08 p 97 N95-15898

p97 N95-15899RTOP 778-32-21 p 101 N95-1S743RTOP-505-68-30 p 69 N95-14239

p 71 N95-14251

E-1

REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Report NumberIndex Listing

NASA(SPONSORED

T

ONMICROFICHE

NASA-CR-186030..

REPORTNUMBER

. p 13 N95-11410 ' *

PAGENUMBER

ACCESSIONNUMBER

Listings in this index are arranged alphanumeri-cally by report number. The page numberindicates the page on which the citation islocated. The accession number denotes the num-ber by which the citation is identified. An aster-isk (*) indicates that the item is a NASA report.A pound sign (#) indicates that the item is avail-able on microfiche.

A-91113 p66 N95-14419 ' HIA-S4007 p65 N95-13891 ' #A-94104 p95 N95-14617 ' #A-94143 p65 N95-13642 ' #A-94148 p65 N95-13662 ' #A-95017 p66 N95-14921 ' tt

AD-A280824 p 79 N95-14306 #AD-A281380 p 87 N95-14363 #AD-A281581 p 76 N95-15465AD-A281706 p 81 N95-15451AD-A281982 p 65 N95-14144 #AQ-A282440 p 96 N95-15547AD-A282839 p 83 N95-14343AD-A282917 p 88 N95-15415AD-A282923 p 82 N95-15392AD-A283011 p84 N95-13687 #AD-A283210 p 96 N95-1465BAD-A283227 p 80 N95-14849 #AD-A283228 p 87 N95-14850AD-A283550 p 85 N95-15328 ttAD-A283564 p 83 N95-15329 #AD-A283585 p 75 N95-15319 #AD-A283671 p 66 N95-15331 #AD-A283B49 p 77 N95-14350 #AD-A283854 p 91 N95-14351 ttAD-A283874 p 99 N95-14357 #AD-A283982 p 79 N95-14205 #AD-A284159 p 92 N95-14405AD-A284230 p 87 N95-14409 ttAQ-A284433 p 81 N95-15815 #AD-A284467 p 81 N95-15821AD-A284877 p 98 N95-15749 #

ADST/TR-94-003280 p 79 N95-14306 #

ADST/WDL/TR-94-00325 p 99 N95-14357 tt

ART/CI/CIA-94-033D p 91 N95-14351 #AFIT/CI/CIA-94-095 p 65 N95-14144 #

AGARD-AG-300-VOL-12 p 77 N95-14199 ttAGARD-AG-300-VOL-3-PT-2 p 79 N9S-14102 #AGARO-AG-323 p 67 N95-14103 ItAGARD-AG-325 p 72 N95-14264 tf

AGARD-AR-303-VOL-1 p 91 N95-14201 ttAGARD-AR-304 p 67 N95-14197 #

AGARD-HIGHLIGHTS-94/2 p 102 N95-13640 tt

AGARD-LS-195 p 89 N95-14127 ttAGARD-LS-197 p 77 N95-14893 tt

AGARD-R-804 p 73 N95-14445 tt

AIAA PAPER 94-0086 P 67 N95-13720 ' #AIAA PAPER 94-0319 P 76 N95-15853 " ttAIAA PAPER 94-2190 p 100 N95-14618 ' ttAIAA PAPER 95-0566 P 73 N95-14297 • ttAIAA PAPER 95-0889 P 73 N95-14418 ' tt

ARL-RR-13 P 87 N95-14409 tt

ARO-30357.1-MS P 87 N95-14363 tt

ATC-222 p98 N95-15749 tt

BTN-94-EIX94331336949 p 88 A95-61795BTN-94-EIX94451393721 p 88 A95-61720BTN-94-EIX94461047054 p 82 A95-61741BTN-94-EIX94461047055 p 78 A95-61740BTN-94-EIX94461047056 p 78 A95-61739BTN-94-EIX94461290240 p 82 A95-61737BTN-94-EIX94461290241 p 82 A95-61736BTN-94-EIX94461290242 p 84 A95-61735BTN-94-EIX94461290277 p 65 A95-61734BTN-94-EIX94461290278 p 77 A95-61733BTN-94-EIX94461290279 p 82 A95-61732BTN-94-EIX94461290506 p 66 A95-61728BTN-94-EIX94461290507 p 82 A95-61727BTN-94-EIX94461407941 p 85 A95-62259BTN-94-EIX94461407944 p 98 A95-62262BTN-94-EIX94461407946 p 82 A95-62264BTN-94-EIX94461407947 p 88 A95-62265BTN-94-EIX94461407949 p 89 A95-62267BTN-94-EIX94461407951 p 89 A95-62625BTN-94-EIX94461407953 p 89 A95-62627BTN-94-EIX94461407957 p 83 A95-62631BTN-94-EIX94461407959 p 78 A95-62633BTN-94-EIX94461407961 p 100 A95-62635BTN-94-EIX94461407964 p 83 A95-62638

CECOM-TR-94-E-1 p 80 N95-14852 " tt

CMU-CS-94-147 p83 N95-14343

CRDL-309 p98 N95-13885 * #

DOC-0710-001 p66 N95-15331 tt

DODA-AR-008-383 p 87 N95-14409 tt

DOT/FAA/CT-93/52 p 83 N95-15683 ttDOT/FAA/CT-94/41 p 99 N95-13895 ttDOT/FAA/CT-94/64 p 77 N95-14350 tt

DOT/FAA/RD-94/24 p 85 N95-15328 tt

E-8957 p 80 N95-14604 ' ttE-9124-1 p 76 N95-15853 ' ttE-9128 p 76 N95-15852 • ttE-9141 p 100 N95-14618 * ttE-9152 p91 N95-14299 * ttE-9171 p 101 N95-15743 * ttE-9172 p 100 N95-14610 * ttE-9179 p89 N95-13665 • ttE-9230 p 73 N95-14418 • ttE-9235 p 101 N95-15059 ' ttE-9241 p 73 N95-14297 ' ttE-9252 p 76 N95-15912 ' tt

FAA/ACE-100-01 p 79 N95-13981

FR2198-20 p 88 N95-15415

F93-2B-OR15 p 79 N95-13703 • #

H-2007-VOL-1 p67 N95-14229 ' ttH-2007-VOL-2 p 69 N95-U239 * #H-2007-VOL-3 p 71 N95-14251 • ttH-2029 p 89 N95-13892 • tt

HTN-95-40013 p 85 A95-62657HTN-95-50054 p 98 A95-62279 •

INT-PATENT-CLASS-B64C-25/58 p 96 N95-15306 '

INT-PATENT-CLASS-G01C-21/00 p 82 N95-14518 *

INT-PATENT-CLASS-G08B-21/00 p 85 N95-14415 '

ISBN-0-309-05761-2 p 78 N95-15439ISBN-92-835-0748-7 p 79 N95-14102 #ISBN-92-835-0749-5 p 89 N95-14127 #ISBN-92-835-0752-5 p 73 N95-14445 #ISBN-92-835-0753-3 p 67 N95-14197 ttISBN-92-835-0754-1 p 67 N95-14103 #ISBN-92-836-1001-6 p 77 N95-14199 #ISBN-92-836-1002-4 p 91 N95-14201 ttISBN-92-836-1005-9 p 72 N95-14264 #ISBN-92-836-1006-7 p 77 N95-14893 tt

L-17356 p80 N95-14852 ' ttL-17397 p 102 N95-15065 • ttL-17432-PT-1 p 92 N95-14453 ' ttL-17434 p 75 N95-14878 ' tt

LG94ER0099 p87 N95-14363 tt

M/FAA/002-93-1 p 83 N95-15683 tt

MCAT-94-005 P 101 N95-13717 • ffMCAT-94-11 p74 N95-14614 • ttMCAT-94-20 p 74 N95-14613 ' #

NAS 1.15:103855 p 66 N95-14419 • #NAS 1.15:106385 p 73 N95-14418 ' ttNAS 1.15:106649 p 80 N95-14604 • ttNAS 1.15:106738 p 100 N95-14618 ' ttNAS 1.15:106742 p 91 N95-14299 ' ttNAS 1.15:106757 p 89 N95-13665 ' ttNAS 1.15:106774 p 76 N95-15853 ' ttNAS 1.15:106782 p 101 N95-15059 ' ttNAS 1.15:106786 p 73 N95-14297 ' ttNAS 1.15:108833 p 95 N95-14617 • ttNAS 1.15:108850 p 65 N95-13642 ' ttNAS 1.15:108853 p 65 N95-13662 ' ttNAS 1.15:108855 p 65 N95-13891 ' ttNAS 1.15:108857 p 66 N95-14921 ' ttNAS 1.15:109142 p 88 N95-14920 ' #NAS 1.15:109152 p 97 N95-15898 • ttNAS 1.15:109163 p 102 N95-13663 ' ttNAS 1.15:4575 p 102 N95-15065 ' ttNAS 1.15:4651 p 89 N95-13892 * ttNAS 1.26:194215 p 101 N95-13717 • 0NAS 1.26:194976 p 99 N95-13727 ' ttNAS 1.26:195003 p 96 N95-14912 ' ttNAS 1.26:195008 p 97 N95-15604 • ttNAS 1.26:195393 p 101 N95-15743 ' ttNAS 1.26:195394 p 100 N95-14610 ' ttNAS 1.26:195398 p 76 N95-15852 ' #NAS 1.26:195405 p 76 N95-15912 * ttNAS 1.26:196059 p 98 N95-13885 ' ttNAS 1.26:196786 p 98 N95-13725 ' ttNAS 1.26:197011 p 67 N95-13701 ' ttNAS 1.26:197023 p 74 N95-14614 • ttNAS 1.26:197024 p 74 N95-14613 ' ttNAS 1.26:197025 p 74 N95-14612 ' ttNAS 1.26:197029 p 80 N95-14794 • #NAS 1.26:197102 p 75 N95-14803 • #NAS 1.26:197110 p 81 N95-14909 • #NAS 1.26:197135 p 76 N95-15762 ' »NAS 1.26:197180 p 81 N95-15742 ' ttNAS 1.26:197191 p 79 N95-13703 ' ttNAS 1.26:197223 p 97 N95-15785 ' #NAS 1.26:197224 p 97 N95-15728 • #NAS 1.26:197229 p 96 N95-14922 • ttNAS 1.55:10143-VOL-1 p 67 N95-14229 " ttNAS 1.55:10143-VOL-2 p 69 N95-14239 * ttNAS1.55:10143-VOL-3 p 71 N95-14251 ' ttNAS 1.55:3274-PT-1 p 92 N95-14453 ' ttNAS 1.55:3279 p 75 N95-14878 ' ttNAS 1.60:3467 p 80 N95-14852 ' ttNAS 1.71 :LAR-15088-1 p 91 N95-14139 ' ttNAS 1.71:LAR-15246-1 p 91 N95-14183 • tt

NASA-CASE-ARC-11953-1

NASA-CASE-LAR-14745-2-SBNASA-CASE-LAR-15088-1NASA-CASE-LAR-15246-1

p 82 N95-14518 •

p85P91p91

N95-14415 'N95-14139 'N95-14183 '

F-1

NASA-CASE-MSC-22277-1

NASA-CASE-MSC-22277-1 ........... p 96 N95-15306 '

REPORT NUMBER INDEX

NASA-CP-10143-VOL-1 ................ p 67 N95-14229 'NASA-CP-10143-VOL-2 ................ p 69 N95-14239 *NASA-CP-10143-VOL-3 ................ p 71 N95-14251 *NASA-CP-3274-PT-1 ..................... p 92 N95-14453 "NASA-CP-3279 ............................... p 75 N95-14878 '

PB94-194065 p 77PB94-195369 p 78PB94-196813 p79

N95-14179N95-15439N95-13981

N95-15821R/D-7213-AN-01 p 81

RAND/N-3619-AF p 81 N95-15451

REPT-10428A p 98REPT-31-12089 p 101

N95-13885 'N95-15743 '

TABES PAPER 94-604TABES PAPER 94-605TABES PAPER 94-616TABES PAPER 94-619TABES PAPER 94-631TABES PAPER 94*32

. p 100p86p83p74p99p87

N95-14638N95-14639 'N95-14645N95-14646N95-14652N95-14653 '

NASA-CR-194215 .......................... p 101 N95-13717 • fjtNASA-CR-194976 .......................... p 99 N95-13727 ' ttN AS A-CR- 195003 .......................... p 96 N95-14912 ' ttNASA-CR-1 95008 .......................... p 97 N95- 15604 ' ttNASA-CR-195393 .......................... p 101 N95-15743 ' ttNASA-CR-195394 .......................... p 100 N95-14610 ' #NASA-CR-1 95398 .......................... p 76 N95-15852 ' »NASA-CR-195405 .......................... p 76 N95-15912 ' ttNASA-CR-196059 .......................... p 98 N95-13885 ' ttNASA-CR-1 96786 .......................... p 98 N95-13725 ' ttNASA-CR-197011 .......................... p 67 N95-13701 ' ttNASA-CR-197023 .......................... p 74 N95-14614 ' #NASA-CR-1 97024 .......................... p 74 N95-14613 ' #NASA-CR-1 97025 .......................... p 74 N95-14612 * ttNASA-CR-1 97029 .......................... p 80 N95-14794 • ttNASA-CR-197102 .......................... p 75 N95-14803 " #NASA-CR-197110 .......................... p 81 N95-14909 ' #NASA-CR-197135 .......................... p 76 N95-15762 * ttNASA-CR-197180 .......................... p 81 N95-15742 ' ttNASA-CR-197191 .......................... p 79 N95-13703 ' #NASA-CR-197223 .......................... p 97 N95-15785 ' ttNASA-CR-197224 .......................... p 97 N95-15728 ' ttNASA-CR-1 97229 .......................... p 96 N95-14922 " #

NASA-TM-103855 ........ . ................. p 66 N95-14419 ' ttNASA-TM-106385 .......................... p 73 N95-14418 ' #NASA-TM-106649 .......................... p 80 N95-14604 • #NASA-TM- 106738 .......................... p 100 N95-14618 ' #NASA-TM-1 06742 .......................... p 91 N95-14299 * ttNASA-TM-106757 .......................... p 89 N95-13665 ' #NASA-TM- 106774 .......................... p 76 N95-158S3 * #NASA-TM-106782 .......................... p 101 N95-15059 • ttNASA-TM-106786 .......................... p 73 N95-14297 ' #NASA-TM- 108833 .......................... p 95 N95-14617 * itNASA-TM-108850 .......................... p 65 N95-13642 ' #NASA-TM- 108853 .......................... p 65 N95-13662 ' #NASA-TM- 108855 .......................... p 65 N95-13891 ' #NASA-TM-1 08857 .......................... p 66 N95-14921 ' ttNASA-TM-109142 .......................... p 88 N95-14920 * ttNASA-TM-109152 .......................... p 97 N95-15898 • #NASA-TM- 109 163 .......................... p 102 N95-13663 ' #NASA-TM-109984 .......................... p 97 N9S-15899 'NASA-TM-4575 .............................. p 102 N95-15065 ' #NASA-TM-4651 .............................. p 89 N95-13892 ' #

NASA-TP-3467 ............................... p 80 N95-14852 * tt

NISTIR-5441 ................................... p 77 N95-14179 tt

NONP-NASA-SUPPL-DK-94-28027 p 84 N95-14815 tt

NONP-NASA-SUPPL-VT-94-32020 p 97 N95-15899 '

NSWCDD/TR-93/339 .................... p 82 N95- 15392

SCT-92-RR-9 p 85 N95-15328 ff

SHRP-H-385 p 78 N95-15439

SSD94D0217B p 80 N95-14794 ' #

TOP-7-3-531 p81 N95-15815 tt

US-PATENT-APPL-SN-032067 p 82 N95-14518 •US-PATENT-APPL-SN-045337 p 85 N9S-14415'US-PATENT-APPL-SN-082766 p 85 N95-14415 'US-PATENT-APPL-SN-159606 p 96 N95-15306 •US-PATENT-APPL-SN-192562 p 85 N95-14415 •US-PATENT-APPL-SN-269268 p 91 N95-14139 ' ttUS-PATENT-APPL-SN-327061 p 91 N95-14183 • tt

US-PATENT-APPL-SN-755248 p 85 N95-14415'

US-PATENT-CLASS-188-381 ...US-PATENT-CLASS-244-100RUS-PATENT-CLASS-244-104RUS-PATENT-CLASS-340-945 ...US-PATENT-CLASS-340-959 ...US-PATENT-CLASS-340-971 ...US-PATENT-CLASS-340-978 ...US-PATENT-CLASS-364-427 ...US-PATENT-CLASS-73-178T ...

US-PATENT-5.353,022US-PATENT-5.359.326US-PATENT-5.366.181

WL-TM-94-3065-VOL-2WL-TM-94-3077

p96P96p96P82p85P82p82p85p85

p85p82p96

p76

P96

N95-15306 'N95-15306 'N95-15306 'N95-14518 'N95-14415 'N95-14518 'N95-14518 *N95-14415 'N95-14415 '

N95-14415 •N95-14518 'N95-15306 '

N95-15465N95-15547

WL-TR-94-3054 p 84 N95-136B7 tt

F-2

ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 315) March 1995

Typical Accession NumberIndex Listing

Listings in this index are arranged alphanumericallyby accession number. The page number indicates thepage on which the citation is located. The accessionnumber denotes the number by which the citation isidentified. An asterisk (*) indicates that the item is aNASA report. A pound sign (#) indicates that the itemis available on microfiche.

A95-61720A95-61727A95-61728A95-61732A95-61733A95-61734A95-61735A95-61736A95-61737A95-61739A95-61740A95-61741A95-61795A95-62259A95-62262A95-62264A95-62265A95-62267A95-62279A95-62625A95-62627A95-62631A95-62633A95-62635A95-62638A95-62657

N95- 13640N95-13642N95-13662N95- 13663N95- 13665N95-13687N95-13701N95-13703N95-13717N95-13718N95-13719IM95-13720N9S- 13725N95-13727N95-13885N95-13891N95-13892N95- 13895N95-13981N95-14089N95-14096N95-14102N95-14103N95-14127N95-14128N95-14129N95-14130N95-14132

•

tt•tt'#'#•tt

tt'tt•#'tt'#'it•tt•tt'#'#'#'Itit

•tt~tt

tttttttttttttt

p88p82p66p82p77p65p84p82p82p78p78p82p88p85p98p82p88p89p98p89p89p83p78p100

P83pB5

p102p65p65p 102p89p84p67p79p 101p85p67p67p98p99p98p65p89p99P79p86p86p79p67

p89p89

p90p90p90

N95-14133 ttN95-14134 ttN95-14135 ttN95-14136 ttN95-14139 ' #N95-14144 ttN95-14159'*N95-14161 '#N95-14162 ' ttN95-14179 #N95-141B3 •#N95-14197 #N95-14199 ttN95-14201 ttN95-14205 #N95-14229 • #N95-14230'*N95-14231 •#N95-14232 ' #N95-14233 * #N95-14234 • ttN95-14235 *#N95-14236 ' ttN95-14237 • ttN95-14238 ' ttN95-14239 • ttN95-14240 ' #N95-14241 •#N95-14242 ' ttN95-14243 • #N95-14244 ' #N95-14245 '#N95-14246 ' ttN95-14247 • ttN95-14248 • ttN95-14249 ' ttN95-14251 '#N95-14252 ' ttN95-14253 * ttN95-14254 ' #N95-14255 ' ttN95-14256 ' ttN95-14257 • #N95-14258 * ttN95-14259 * #N95-14264 ttN95-14282 ' ttN95- 14297 '#N95-14299 * ttN95-14306 ttN95-14343N95-14350 #N95-14351 ttN95-143S7 ttN95- 14363 #

p90p90

p90p90

p91p65p99p99pB6P77p91p67p77

P91p79p67p68p68p68p68p68p69p69p69p69p69p69p69p70p70p70p70p70p70p71p71p71P71

P71p72p72P72P72p72p72P72p86p73p91p79p83p77p91p99p87

N95- 14405N95- 14409 #N95-14415 'N95-14418 '#N95-14419 •#N95-14445 ttN95-14446 ttN95- 14447 ttN95- 14448 ttN95- 14450 ttN95-14451 #N95-14452 ttN95-14453 '#N95-14454 ' #N95- 14455 • ttN95-14456'«l

N95- 14457 ' ttN95- 14458 '#N95-14460 '#N95-14461 ' ttN95- 14464 " ttN95-14465'*N95-14466 ' ttN95-14467 ' ttN95- 14468 * ftN95-14469 * ttN95-14470 ' ttN95-14473'*N95-14475 ' ttN95- 14476 '#N95-14477 ' ttN95-14479 • ttN95-14480 ' #N95-14481 '#N95- 14482 ' ttN95-14484 * ttN95-14485 • ttN95-14486 " ttN95-14518 *N95-14556'*N95-14563 * ttN95-14604 ' ttN95-14610 * ttN95-14612 ' ttN95-14613 ' ttN95-14614 ' ttN95-14617 '#N95-14618 '#N95-14638 ttN95-14639 • ttN95-14645 ttN95- 14646 ttN95- 14652 ttN95-14653 • ttN95-14658N95- 14794 • ttN95-14803 ' ttN95-14815 #N95-14849 ttN95-14850N95-14852 * ttN95- 14878 ' ttN95-14879 '#N95-14880 '#N95-14886 ' ttN95-14887 • ttN95-14889 * ttN95- 14893 ttN95- 14894 ttN95-14897 '#N95-14898 #N95-14899 ' ttN95-14900 ttN95-14909 ' #N95-14912 •#N95-14916 ttN95-14920 •#N9S-14921 "#N95-14922 " ttN95- 15059 •#N95- 15065 •#N95- 15066 #N95-15306 '

p92p87p85p73p66p73P73P73P84

P74p74p74p92p92p92p92p92p93p93

P93p93p87p93p93P94p80P94p94p94P94p66P94p95p80p88P95P95p80p82p95P95p80p100

P74p74p74p95p 100p 100p86p83p74p99p87p96p80P75P84p80p87p80p75P96p75p 100p 100p 101P77p75P77p77p78p84p81P96p78p88p66p96

p 101p102

p78

P96

N95-15319 ttN95-15328 ttN95-15329 ttN95-15331 ttN95-15392N95-15415N95-15439N95-15451N95-15465N95-15547N95-15604 •#N95-15683 ttN95-15728 ' ttN95-15742 •#N95-15743 ' ttN95-15749 ttN95-15762 ' ttN95-15785 '#N95-15815 ttN95-15821N95-15852 " ttN95-15853 ' ttN95-15898 ' ttN95-1S899 'N95-15912 ' #

p75p85p83p66p82p88p78p81p76P96p97p83P97p81p 101p98p76p97p61p81p76p76P97P97p76

G-1

AVAILABILITY OF CITED PUBLICATIONS

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APP-1

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APP-2

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76344 Eggenstein-Leopoldshafen, Germany

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APP-3

NASA CASI PRICE CODE TABLE(Effective January 1,1995)

CASIPRICECODE

A01

A02

A03

A04-A05

A06-A09

A10-A13

A14-A17

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A99

NORTHAMERICAN

PRICE

$6.00

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27.00

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Call For Price

FOREIGNPRICE

$ 12.00

18.00

35.00

39.00

54.00

73.00

89.00

104.00

122.00

Call For Price

IMPORTANT NOTICE

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Rev. 1/95 APP-5

REPORT DOCUMENT PAGE1. Report No.

NASASP-7037(315)

2. Government Accession No. 3. Recipient's Catalog No.

4. Title and Subtitle

Aeronautical EngineeringA Continuing Bibliography (Supplement 315)

5. Report Date

March 19956. Performing Organization Code

JTT7. Authors) 6. Performing Organization Report No.

10. Work Unit No.

9. Performing Organization Name and Address

NASA Scientific and Technical Information Office 11. Contract or Grant No.

12. Sponsoring Agency Name and Address

National Aeronautics and Space AdministrationWashington, DC 20546-0001

13. Type of Report and Period Covered

Special Publication

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

This report lists 217 reports, articles and other documents recently announced in the NASASTI Database.

17. Key Words (Suggested by Authors))

Aeronautical EngineeringAeronauticsBibliographies

18. Distribution Statement

Unclassified - UnlimitedSubject Category - 01

9. Security Classil. (of this report)

Unclassified

20. Security Classif. (of this page)

Unclassified21. No. of Pages

90

22. Price

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For sale by the NASA Center for AeroSpace Information, 800 Elkridge Landing Road, Linthicum Heights, MD 21090-2934

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CONNECTICUTCONNECTICUT STATE LIBRARY231 Capitol AvenueHartford, CT 06106(203) 566-4971 Fax: (203) 566-3322

FLORIDAUNIV. OF FLORIDA LIBRARIESDocuments Dept.240 Library WestGainesville, FL 32611-2048(904) 392-0366 Fax: (904) 392-7251

GEORGIAUNIV. OF GEORGIA LIBRARIESGovl. Documents Dept.Jackson StreetAthens, GA 30602-1645(706) 542-8949 Fax: (706) 542-4144

HAWAIIUNIV. OF HAWAIIHamilton LibraryGovt. Documents Collection2550 The MallHonolulu, HI 96822(808) 948-8230 Fax: (808) 956-5968

IDAHOUNIV. OF IDAHO LIBRARYDocuments SectionRayburn StreetMoscow, ID 83844-2353(208) 885-6344 Fax: (208) 885-6817

ILLINOISILLINOIS STATE LIBRARYFederal Documents Dept.300 South Second StreetSpringfield, IL 62701-1796(217) 782-7596 Fax: (217) 782-6437

INDIANAINDIANA STATE LIBRARYSerials/Documents Section140 North Senate AvenueIndianapolis. IN 46204-2296(317) 232-3679 Fax: (317) 232-3728

IOWAUNIV. OF IOWA LIBRARIESGovl. PublicationsWashington & Madison StreetsIowa City, IA 52242-1166(319) 335-5926 Fax: (319) 335-5900

KANSASUNIV. OF KANSASGovt. Documents & Maps Library6001 Malott HallLawrence, KS 66045-2800(913) 864-4660 Fax: (913) 864-3855

KENTUCKYUNIV. OF KENTUCKYKing Library SouthGovt. Publications/Maps Dept.Patterson DriveLexington. KY 40506-0039(606) 257-3139 Fax: (606) 257-3139

LOUISIANALOUISIANA STATE UNIV.Middleton LibraryGovt. Documents Dept.Baton Rouge, LA 70803-3312(504) 388-2570 Fax: (504) 388-6992

LOUISIANA TECHNICAL UNIV.Prescott Memorial LibraryGovt. Documents Dept.Ruston, LA 71272-0046(318) 257-4962 Fax: (318) 257-2447

MAINEUNIV. OF MAINERaymond H. Fogler LibraryGovt. Documents Dept.Orono, ME 04469-5729(207) 581-1673 Fax: (207) 581-1653

MARYLANDUNIV. OF MARYLAND - COLLEGE PARKMcKeldin LibraryGovt. Documents/Maps UnitCollege Park, MD 20742(301) 405-9165 Fax: (301) 314-9416

MASSACHUSETTSBOSTON PUBLIC LIBRARYGovt. Documents666 Boylston StreetBoston. MA 02117-0286(617) 536-5400, ext. 226Fax: (617) 536-7758

MICHIGANDETROIT PUBLIC LIBRARY5201 Woodward AvenueDetroit, Ml 48202-4093(313) 833-1025 Fax: (313) 833-0156

LIBRARY OF MICHIGANGovt. Documents UnitP.O. Box 30007717 West Allegan StreetLansing, Ml 48909(517) 373-1300 Fax: (517) 373-3381

MINNESOTAUNIV. OF MINNESOTAGovt. Publications409 Wilson Library309 19th Avenue SouthMinneapolis, MN 55455(612) 624-5073 Fax: (612) 626-9353

MISSISSIPPIUNIV. OF MISSISSIPPIJ.D. Williams Library106 Old Gym Bldg.University, MS 38677(601) 232-5857 Fax: (601) 232-7465

MISSOURIUNIV. OF MISSOURI - COLUMBIA106B Ellis LibraryGovt. Documents Sect.Columbia, MO 65201-5149(314) 882-6733 Fax: (314) 882-8044

MONTANAUNIV. OF MONTANAMansfield LibraryDocuments DivisionMissoula, MT 59812-1195(406) 243-6700 Fax: (406) 243-2060

NEBRASKAUNIV. OF NEBRASKA - LINCOLND.L. Love Memorial LibraryLincoln, NE 68588-0410(402) 472-2562 Fax: (402) 472-5131

NEVADATHE UNIV. OF NEVADA

LIBRARIESBusiness and Govt. Information

CenterReno, NV 89557-0044(702) 784-6579 Fax: (702) 784-1751

NEW JERSEYNEWARK PUBLIC LIBRARYScience Div. - Public AccessP.O. Box 630Five Washington StreetNewark, NJ 07101-7812(201) 733-7782 Fax: (201) 733-5648

NEW MEXICOUNIV. OF NEW MEXICOGeneral LibraryGovt. Information Dept.Albuquerque. NM 87131-1466(505) 277-5441 Fax: (505) 277-6019

NEW MEXICO STATE LIBRARY325 Don Caspar AvenueSanta Fe, NM 87503(505) 827-3824 Fax: (505) 827-3888

NEW YORKNEW YORK STATE LIBRARYCultural Education CenterDocuments/Gift & Exchange SectionEmpire State PlazaAlbany, NY 12230-0001(518) 474-5355 Fax: (518) 474-5786

NORTH CAROLINAUNIV. OF NORTH CAROLINA -CHAPEL HILL

Walter Royal Davis LibraryCB 3912, Reference Dept.Chapel Hill, NC 27514-8890(919)962-1151 Fax: (919) 962-4451

NORTH DAKOTANORTH DAKOTA STATE UNIV. LIB.DocumentsP.O. Box 5599Fargo, ND 58105-5599(701) 237-8886 Fax: (701) 237-7138

UNIV. OF NORTH DAKOTAChester Fritz LibraryUniversity StationP.O. Box 9000 - Centennial and

University AvenueGrand Forks, ND 58202-9000(701) 777-4632 Fax: (701) 777-3319

OHIOSTATE LIBRARY OF OHIODocuments Dept.65 South Front StreetColumbus, OH 43215-4163(614) 644-7051 Fax: (614) 752-9178

OKLAHOMAOKLAHOMA DEPT. OF LIBRARIESU.S. Govt. Information Division200 Northeast 18th StreetOklahoma City, OK 73105-3298(405)521-2502,ext.253Fax: (405) 525-7804

OKLAHOMA STATE UNIV.Edmon Low Library

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OREGONPORTLAND STATE UNIV.Branford P. Millar Library934 Southwest HarrisonPortland, OR 97207-1151(503) 725-4123 Fax: (503) 725-4524

PENNSYLVANIASTATE LIBRARY OF PENN.Govt. Publications Section116 Walnut & Commonwealth Ave.Harrisburg, PA 17105-1601(717) 787-3752 Fax: (717) 783-2070

SOUTH CAROLINACLEMSONUNIV.Robert Muldrow Cooper LibraryPublic Documents UnitP.O. Box 343001Clemson, SC 29634-3001(803) 656-5174 Fax: (803) 656-3025 '•'

UNIV. OF SOUTH CAROLINA'Thomas Cooper Library ,:.Green and Sumter StreetsColumbia, SC 29208(803) 777-4841 Fax: (803) 777-9503

TENNESSEEUNIV. OF MEMPHIS LIBRARIESGovt. Publications Dept.Memphis, TN 38152-0001(901) 678-2206 Fax: (901) 678-2511

TEXASTEXAS STATE LIBRARYUnited States DocumentsP.O. Box 12927 - 1201 BrazosAustin, TX 78701-0001(512) 463-5455 Fax: (512) 463-5436

TEXAS TECH. UNIV. LIBRARIESDocuments Dept.Lubbock, TX 79409-0002(806) 742-2282 Fax: (806) 742-1920

UTAHUTAH STATE UNIV.Merrill Library Documents Dept.Logan, UT 84322-3000(801) 797-2678 Fax: (801) 797-2677

VIRGINIAUNIV. OF VIRGINIAAlderman LibraryGovt. DocumentsUniversity Ave. & McCormick Rd.Charlottesville, VA 22903-2498(804) 824-3133 Fax: (804) 924-4337

WASHINGTONWASHINGTON STATE LIBRARYGovt. PublicationsP.O. Box 4247816th and Water StreetsOlympia, WA 98504-2478(206) 753-4027 Fax: (206) 586-7575

WEST VIRGINIAWEST VIRGINIA UNIV. LIBRARY'Govt. Documents SectionP.O. Box 6069 -1549 University Ave.Morgantown, WV 26506-6069(304) 293-3051 Fax: (304) 293-6638

WISCONSINST. HIST. SOC. OF WISCONSIN LIBRARYGovt. Publication Section816 State StreetMadison, Wl 53706(608) 264-6525 Fax: (608) 264-6520

MILWAUKEE PUBLIC LIBRARYDocuments Division814 West Wisconsin AvenueMilwaukee, Wl 53233(414) 286-3073 Fax: (414) 286-8074

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