Aeronautical Engineering

NASA SP-7037 (262) February 1991

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

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(NASA-SP-7037(262)) AERONAUTICAL N91-2307A ENGINEERING: A CONTINUING BIBLIOGRAPHY WITH INDEXES (SUPPLEMENT 262) (NASA) 142 p CSCL 01B Unclas .' 00/01 0012235 NASA SP-7037 (262) February 1991

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHY WITH INDEXES

National Aeronautics and Space Administration Office of Management IWNSA Scientific and Technical Information Program Washington, DC 1991 INTRODUCTION

This issue of Aeronautical Engineering—A Continuing Bibliography (NASA SP-7037) lists 474 reports, journal articles, and other documents originally announced in January 1991 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). Accession numbers cited in this issue are: S7/4.f?(N-10000 Series) N91-10001 -N91-11665 IAA (A-10000 Series) A91-10001 - A91-12944 The coverage includes documents on the engineering and theoretical aspects of design, con- str(uction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the publication consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged by the first nine STAR specific categories and the remaining STAR major categories. This arrangement offers the user the most advantageous breakdown for individual objectives. The citations include the original accession numbers 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 1991 will be published in early 1992. Information on availability of documents listed, addresses of organizations, and NTIS price schedules are located at the back of this issue. CONTENTS

Category 01 Aeronautics (General) 1

Category 02 Aerodynamics 2 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery.

Category 03 Air Transportation and Safety 25 Includes passenger and cargo air transport operations; and aircraft accidents.

Category 04 Aircraft Communications and Navigation 28 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 35 Includes aircraft simulation technology.

Category 06 Aircraft Instrumentation 44 Includes cockpit and cabin display devices; and flight instruments.

Category 07 Aircraft Propulsion and Power 44 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and onboard auxiliary power plants for aircraft.

Category 08 Aircraft Stability and Control 49 Includes aircraft handling qualities; piloting; flight controls; and autopilots.

Category 09 Research and Support Facilities (Air) 51 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.

Category 10 Astronautics 54 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; space communications, spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power.

Category 11 Chemistry and Materials 55 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.

Category 12 Engineering 57 Includes engineering (general); communications and radar; electronics and electrical engineering; fluid mechanics and heat transfer; instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; and structural mechanics. Category 13 Geosciences 63 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.

Category 14 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 65 Includes mathematical and computer sciences (general); computer operations and hardware; computer programming and software; computer systems; cybernetics; numerical analysis; statistics and probability; systems analysis; and theoretical mathematics. •

Category 16 Physics 66 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics.

Category 17 Social Sciences 77 Includes social sciences (general); administration and management; documentation and information science; economics and cost analysis; law, political science, and space policy; and urban technology and transportation.

Category 18 Space Sciences N.A. Includes space sciences (general); astronomy; astrophysics; lunar and planet- ary exploration; solar physics; and space radiation.

Category 19 General N.A.

Subject Index A-1 Personal Author Index B-1 Corporate Source Index C-1 Foreign Technology Index D-1 Contract Number Index ; E-1

Report Number Index ; '. F-1 Accession Number Index ;.. G-1 Appendix APP-1 TYPICAL REPORT CITATION AND ABSTRACT

NASA SPONSORED ON MICROFICHE

ACCESSION NUMBER • -N91-10010*# Institute for Computer Applications in Science • CORPORATE SOURCE and Engineering, Hampton, VA. . .- ' TITLE • -TURBULENT FLOW CALCULATIONS USING UNSTRUCTURED AND ADAPTIVE MESHES Final Report . ' PUBLICATION DATE AUTHOR -DIMITRI J. MAVRIPLIS Sep. 1990 32 p Submitted for publication . • ,: • CONTRACT NUMBER • -(Contract NAS1-18605) REPORT NUMBERS -(NASA-CR-182102; NAS 1.26:182102; ICASE-90-61) Avail: NTIS- - AVAILABILITY SOURCE HC/MFA03 CSCL01A-. - COSATI CODE PRICE CODE A method of efficiently computing turbulent compressible flow over: • complex two dimensional configurations is presented. The method . makes use of fully unstructured meshes throughout the entire flowfield, thus enabling the treatment of'arbitrarily complex geometries and the use of adaptive meshing techniques throughout both viscous" and inviscid regions of flow-field. Mesh generation is based on a locally mapped Delaunay technique in order to generate unstructured meshes with highly-stretched elements in the viscous regions. The flow equations are discretized1 using a finite element Navier-Stokes solver, and rapid convergence to steady-state is achieved using an unstructured multigrid algorithm.. Turbulence modeling is performed 'using an inexpensive algebraic- model, implemented for use on unstructured and adaptive meshes. Compressible turbulent flow solutions about multiple-element airfoil geometries are computed and compared with experimental data. ' " Author

TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT

NASA SPONSORED ON MICROFICHE

ACCESSION NUMBER -A91-11198** Oklahoma State Univ., Stillwater. - CORPORATE SOURCE TITLE - FLOW AND ACOUSTIC PROPERTIES OF LOW REYNOLDS NUMBER UNDEREXPANDED SUPERSONIC JETS AUTHORS -TIEH-FENG HU and D. K.. MCLAUGHLIN (Oklahoma State - AUTHORS' AFFILIATION University, Stillwater) Journal of Sound and Vibration JISSN •0022-460X), vol. 141, Sept. 22, 1990, p. 485-505. • refs CONTRACT NUMBERS -(Contract NAG1-10; NAG1-159) JOURNAL TITLE Copyright An experimental program to investigate the flow and acoustic properties of model underexpanded supersonic jets was conducted. In particular, the role played by large-scale organized fluctuations in the flow evolution and acoustic production processes was examined in detail. The experimental conditions were chosen as low-Reynolds- number (Re = 8000) Mach 1.4 and 2.1 underexpanded jets exhausting from convergent nozzles. A consequence of performing the experiments at low Reynolds number is that the broad and shock- associated noise is suppressed. The focus of the present study is on the generation of noise by large-scale instabilities in the presence of strong shock cell structures. It is demonstrated that the production of screech is related to the modulation and decay of large-scale turbulence structures. Author AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 262)

FEBRUARY 1991

01 (Academie Nationale de I'Air et de I'Espace, Toulouse, France) IN: European Symposium on the Future of High Speed Air AERONAUTICS (GENERAL) Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. 14-29. In French. Copyright A review of the SST programs conducted by the United States, France, Great Britain and the USSR during the 1960s is presented. A91-10114# The designs that evolved considered such questions as the supersonic boom and other noise related problems that were THE APPLICATION OF COMMERCIAL AIRPLANE AVIONICS directly related to environmental and public opinion issues. TECHNIQUES TO ADVANCED SPACE TRANSPORTATION Development of the Concorde program is discussed, and a brief MICHAEL RAFTERY and VINCENT A. CALUORI, JR. (Boeing Co., outline of the TU 144 project and the discontinued U.S. SST Seattle, WA) AIAA, Space Programs and Technologies competition is presented. Some aspects of initial Concorde Conference, Huntsville, AL, Sept. 25-27, 1990. 7 p. refs operational problems are also described. R.E.P. (AIAA PAPER 90-3722) Copyright Operating practices for commercial aircraft are compared with those of partially reuseable space systems. Current commercial A91-10953* National Aeronautics and Space Administration. regulations for maintaining high levels of safety and dispatch reliably Hugh L. Dryden Flight Research Facility, Edwards, CA. are discussed as they pertain to potential application in a space NACA/NASA SUPERSONIC FLIGHT RESEARCH transportation avionics system. The fundamental manufacturing and T. G. AYERS (NASA, Flight Research Center, Edwards, CA) IN: operating strategies applied in air and space are compared and European Symposium on the Future of High Speed Air Transport, the flow through manufacturing, integration, test, and operations Strasbourg, France, Nov. 6-8,1989, Proceedings. Toulouse, France, for aircraft and spacecraft is presented. It is noted that redundancy Cepadues-Editions, 1990, p. 34-41. is used to protect against failure of critical and essential systems. Copyright An example of application of redundant hardware is presented The use of experimental and testbed vehicles and their showing the flight critical navigation and air data systems and contributions to fundamental problem solving and overall vehicle illustrating several aspects of the flight hardware design. Aircraft characteristics are presented. A chronological description of aircraft computer maintenance programs are discussed, noting that they from the first supersonic flight in the X-1 through the development are developed to take advantage of the extensive onboard test of the F-100 series, the X-15, and the B-1 is given. One of the and diagnostic capabilities. L.K.S. early significant contributions made was the development of the all-moving stabilizer that solved the problem associated with A91-10951 high-speed tuck and the trim requirements of entry into the EUROPEAN SYMPOSIUM ON THE FUTURE OF HIGH SPEED supersonic regime. Some wind tunnel/flight drag characteristics AIR TRANSPORT, STRASBOURG, FRANCE, NOV. 6-8, 1989, studies associated with the B-1 bomber involving .flexibility effects PROCEEDINGS [SYMPOSIUM EUROPEEN SUR L'AVENIR DU and wind tunnel effects are shown. Finally, the evolution of digital TRANSPORT AERIEN A HAUTE VITESSE, STRASBOURG, systems to enhance maintainability and reliability and to reduce FRANCE, NOV. 6-8, 1989, ACTES] the work load in the cockpit are described. R.E.P. PH. POISSON-QUINTON, ED. (Academie Nationale de I'Air et de I'Espace, Toulouse, France) Symposium organized by Academie A91-10961* National Aeronautics and Space Administration. Nationale de I'Air et de I'Espace; Sponsored by CEC, Ministere Langley Research Center, Hampton, VA. de la Recherche et de la Technologie, Direction Generale de THE POTENTIAL FOR A NEW ERA OF SUPERSONIC AND ('Aviation Civile, et al. Toulouse, France, Cepadues-Editions, 1990, HYPERSONIC AVIATION 375 p. In French and English. For individual items see A91-10952 ROY V. HARRIS (NASA, Langley Research Center, Hampton, to A91-10978. VA) IN: European Symposium on the Future of High Speed Air Copyright Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Topics presented include the SST programs in the sixties, Toulouse, France, Cepadues-Editions, 1990, p. 100-108. refs NACA/NASA supersonic flight research, Air France experience as Copyright a supersonic transport airline, and a NASA view on key technical A new era of supersonic and hypersonic aviation is envisioned. issues for an advanced high speed commercial transport. Also The potential for supersonic and hypersonic flight vehicles in this presented are the sonic boom problem, the advantages and new era is analyzed. Technology challenges that must be met in problems of cryogenic fuels for high speed transport, future order to bring in this new era of flight are discussed. The current supersonic transport propulsion optimization, hypersonic transport technical- status and future potential are cited in the areas of optimization, the optimization of hybrid propulsion systems, and aerodynamics, propulsion, and structural materials. A next major the need for a hypersonic demonstrator. R.E.P. step in the development of high-speed air transportation is suggested. Author A91-10952 SUPERSONIC AIR TRANSPORT PROGRAMS IN THE 60'S A91-10964 [LES PROGRAMMES DE TRANSPORT SUPERSONIQUE DANS THE SONIC BOOM PROBLEM LES ANNEES SOIXANTE] A. AURIOL, C. LECOMTE, and C. THERY (ONERA, Chatillon, J. FORESTIER, P. LECOMTE, and PH. POISSON-QUINTON France) IN: European Symposium on the Future of High Speed 01 AERONAUTICS (GENERAL)

Air Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. SURESH MENON and WEN-HUEI JOU (Quest Integrated, Inc., Toulouse, France, Cepadues-Editipns,. 1990, p. 149-*154. refs Kent; WA) , Journal of Propulsion and Power (ISSN 0748-4658), Copyright .! . , . ,,'.."• vol. 6, SepL-Oct. 1990, p. 525-534. Previously cited in issue 19, An overview of the sonic boom problem is presented including 'p. 2942, Accession no. A87-44949. refs •' a description of the .physical phenomenon, results on sonic boom (Contract N00014-84-C-0359) effects, and considerations for the aircraft designer. Detailed Copyright ' ; ' ••' graphs, descriptions and results of various sonic boom tests are provided. It is shown that the weight and the volume of the .aircraft A91-10330# play an important role in the intensity of the boom. The part due MODES OF OSCILLATION IN A NONREACTING RAMJET to the volume' is of particular,importance as it deteriorates rapidly COMBUSTOR FLOW with altitude. It is also shown'that Mach number (except close to WEN-HUEI JOU and SURESH MENON (Quest Integrated, Ina, Mach 1) has little influence'on. the. intensity of the^ boom beneath Kent.'WA) Journal of "Propulsion and Power (ISSN 0748-4658), the flight path. However, it has a considerable"effect on the width volr 6, Sept:-Oct. 1990, p: 535-543. Previously-cited in issue 19, of the boom path. The most important problem to, overcome is p. 2942, Accession no. A87-44950. refs the startle effect on humans and intensive research in this area (Contract N00014-84-C-0359) ' ' will be required. It is concluded that a diminution of the sonic Copyright '.-.•••-. boom path could be achieved and this would "lead to a decrease of supersonic flight restricted areas.. . ' " R.E.P. A91-10337# PERIODIC ROTOR-BLADE AERODYNAMICS INCLUDING A91-10971 . , LOADING EFFECTS HYPERSONIC AIRCRAFT STUDIES ,.,".,' STEVEN R, MANWARING and SANFORD FLEETER (Purdue D. COLLARD (Aerospatiale, Division Avibns, Paris,,France) .IN: University, West Lafayette," IN) Journal of Propulsion and Power European Symposium on the Future of High .Speed Air Transport, (ISSN 0748-4658), vol! 6, Sept.-Oct. 1990, p.'590-597, Previously Strasbourg, France, Nov. 6-8,1989, Proceedings. Toulouse, France, cited in issue 20, p. 3347, Accession no. A88-48962. refs Cepadues-Editions, 1990, p. 251-256. . -...,.-,' (Contract F49620-88-C-0022) ••• - - Copyright . , Copyright ••••.. , • ..;•••' Various aspects of studies being conducted on the design of A91-10339*# National Aeronautics -and Space Administration. a hypersonic commercial transport are presented. The baseline Lewis Research Center, Cleveland, OH. . •• • '. • ,• configuration comprises a slender wing and sufficient volume to OSCILLATING CASCADE AERODYNAMICS BY AN , carry cryogenic fuels. It is powered by four turbofan/ramjet EXPERIMENTAL INFLUENCE COEFFICIENT TECHNIQUE combined engines grouped under the rear fuselage, and its cruise DANIEL H. BUFFUM (NASA, Lewis Research Center, Cleveland, performance is deemed satisfactory. However, the -off-design OH) and SANFORD FLEETER (Purdue University, West Lafayette, performance, considered in a realistic operational ..and IN)- Journal of Propulsion and Power (ISSN 0748-4658), vol. 6, environmental framework, shows it could only operate on a few Sept.-Oct. 1990, p. 612-620. Previously cited in. issue 03, p. 262, routes. Structural weight, particularly due to powerplant installation, Accession no. A89-.14976. • refs • ... tends to erode the payload completely. Detailed considerations Copyright are also. addressed for longitudinal and lateral aerodynamic characteristics, engine installation, low-speed lift/drag ratios, 'and A91-10340# thermal heating problems. . .R-E..P. STATOR/ROTOR INTERACTION IN A TRANSONIC TURBINE MICHAEL B. GILES (MIT,' Cambridge, MA) Journal of.Propulsion N91-10001# Office of .the Under .Secretary of Defense and Power (ISSN 0748-4658), vol. 6, S.ept.-Oct. 1990, p. 621-627. (Acquisitions), Washington, DC. -,, .-' , '.''.'' Research, supported by the Rolls-Royce,1 PLC. Previously.cited in DOD RESPONSIBILITIES ON FEDERAL AVIATION AND issue 23, p. 3758; Accession no. A88-53140. refs NATIONAL AIRSPACE SYSTEM MATTERS .,.'." Copyright R. NAKAMURA 22 Jun. 1989 9p ' .-...,'. (PB90-218827; DOD-D-5030:19) Avail: NTIS HC/MF A02 A91-11151 " ~ '_ .'...'. '.'.'''".'"' CSCL01B THE EFFECTS OF AEROFOIL1 PROFILE ON WING BUFFET AT The directive reissues Department of Defense (PpD) Directive LOW SPEEDS , 5030.19 and supersedes'.DoD Directive .5030.17."''it 'updates D'oD C/A. LUCAS (Australian Artificial Intelligence Institute, Carlton, policy and procedures to address peacetime^, wartime,,-and Australia) and D. J. MAULL :(Cambridge, University, England) emergency relationships between DoD, DoT, FAA, and other Aeronautical Journal (ISSN 0001 ^9240), .vol. 94, March 1990, p. government agencies. The DoD organizational structure is .86-90., .'...... ".. ., ' . .. , described for interface with the DoT, FAA, and other agencies on Copyright , . ' , , ;;. . ' air traffic control and airspace matters, NAS matters, joint system .The unsteady |oads on two wings, one exhibiting a trailing acquisitions, and oversight of airlift service provided to the DoD edge separation, the other a,leading edge separation have been by civil air earners. DoD policy and planning guidance is provided measured. It has been found that there are differences between for comprehensive DoD airspace planning and .the relationships the two wing loads, .one having a .large scale viscous-inviscid between the DoD, DoT, FAA, other government, agencies, state interaction producing high loads at a low frequency. Author governments, and civil communities. • Author A91-11157 TRANSONIC .BUFFET ON A SUPERCRITICAL AEROFOIL B. H. K. LEE (National Aeronautical Establishment, Ottawa, • ,..-..,. 02 • • •-,,.;..:• Canada) Aeronautical Journal (ISSN 0001-9240), vol. 94, May 1990, p. 143-152. refs AERODYNAMICS Copyright ' ' •' The buffet characteristics of a supercritical aerofoil were Includes aerodynamics of bodies, combinations," wings, rotors, and investigated in the High Reynolds, Number Twp-Dimensional Test control surfaces; and internal flow in ducts and turbomachinery. Facility of'the National Aeronautical Establishment (NAE). The test was performed quite'deep into the buffet regime. The buffet onset boundary,,was.determined from the 'divergence of the unsteady A91-10329# ,. balance' normal force. Steady and unsteady pressure NUMERICAL SIMULATIONS' OF OSCILLATORY COLD FLOWS .measurements were obtained for shock-induced separation with IN AN AXISYMMETRIC RAMJET COMBUSTOR, reattachment as well as fully separated flows. For flow conditions 02 AERODYNAMICS

where discrete shock wave oscillations occurred, ensemble- separation for both laminar and turbulent layers is determined by averaging of the unsteady pressures determined the prop- matching the pressure at the upper and lower separation points. agation velocity of the pressure wave induced by periodic This iterative procedure yields a solution for the separation lines, Shock motion. A model of the self-sustained oscillatory shock the positions of the vortices, and the vortex lift of the body. Control motion due to shock-boundary layer interaction was formulated. of separation is achieved by blowing tangentially from slots located Broad-band cross-correlations of the pressure field determined the symmetrically along the cone generators. B.P. downstream convection velocities of the turbulent eddies of separated flows. Author A91-11198* Oklahoma State Univ., Stillwater. FLOW AND ACOUSTIC PROPERTIES OF LOW REYNOLDS A91-11159 NUMBER UNDEREXPANDED SUPERSONIC JETS THE AERODYNAMIC INTERFERENCE BETWEEN TANKER TIEH-FENG HU and D. K. MCLAUGHLIN (Oklahoma State AND RECEIVER AIRCRAFT DURING AIR-TO-AIR REFUELLING University, Stillwater) Journal of Sound and Vibration (ISSN A. W. BLOY and V. TROCHALIDIS (Manchester, Victoria University, 0022-460X), vol. 141, Sept. 22, 1990, p. 485-505. refs England) Aeronautical Journal (ISSN 0001-9240), vol. 94, May (Contract NAG1-10; NAG1-159) 1990, p. 165-171. Research supported by SERC and Ministry of Copyright Defence, refs An experimental program to investigate the flow and acoustic Copyright properties of model underexpanded supersonic jets was conducted. Wind tunnel data from a tanker wing and receiver aircraft In particular, the role played by large-scale organized fluctuations model at varying vertical separation have been compared with in the flow evolution and acoustic production processes was theoretical results. In the aerodynamic model the tanker wing is examined in detail. The experimental conditions were chosen as represented by a horseshoe vortex while the aerodynamic loads low-Reynolds-number (Re = 8000) Mach 1.4 and 2.1 on the receiver are determined by the vortex lattice method and underexpanded jets exhausting from convergent nozzles. A lifting-line theory, although an approximate method is used to consequence of performing the experiments at low Reynolds determine the side force on the fin. In the longitudinal case, data number is that the broadband shock-associated noise is were obtained for low, mid and high tailplane positions and, with suppressed. The focus of the present study is on the generation the exception of the pitching moment results, fairly good agreement of noise by large-scale instabilities in the presence of strong shock is obtained between theory and experiment. The lateral cell structures. It is demonstrated that the production of screech aerodynamic interference was determined by banking the tanker is related to the modulation and decay of large-scale turbulence wing and displacing it sideways and by yawing the receiver model. structures. Author Fairly good agreement is obtained between the theory and experiment for the most significant terms which are the rolling A91-11347 moments due to bank and sideways displacement. The effect of APPLICATION OF THE VORTEX CLOUD METHOD TO the sidewash due to the tanker wake on the receiver in yaw is CASCADES found to be relatively insignificant. Over the range of bank, yaw R. I. LEWIS International Journal of Turbo and Jet-Engines (ISSN and sideways displacements tested, the results are almost linear. 0334-0082), vol. 6, no. 3-4, 1989, p. 231-245. refs Author Copyright The vortex cloud method for modeling the Navier-Stokes A91-11160 equations in two-dimensional flow is extended to the simulation of SOLUTION OF THE EULER EQUATIONS ON UNSTRUCTURED viscous flow through turbine or compressor cascades. For a turbine GRIDS FOR TWO-DIMENSIONAL COMPRESSIBLE FLOW cascade, the predicted surface pressure agrees well with the L. STOLCIS and L. J. JOHNSTON (Von Karman Institute for Fluid experimental values, but losses are overpredicted. In the case of Dynamics, Rhode-Saint-Genese, Belgium) Aeronautical Journal a compressor cascade, problems arise due to the onset of (ISSN 0001-9240), vol. 94, June-July 1990, p. 181-195. refs premature stall for diffusing flows. A hybrid method is proposed Copyright which alleviates this problem through the introduction of potential A method for the numerical solution of the two-dimensional flow restrictions to the suction surface. V.L. Euler equations on unstructured grids has been developed. The cell-centered symmetric finite-volume spatial discretization is A91-11701# applied in a general formulation that allows the use of arbitrary BASIC HELICOPTER AERODYNAMICS polygonal computational cells. The integration in time, to a J. SEDDON Washington, DC/London, England, American Institute Steady-state solution, is performed using an explicit, multi-stage of Aeronautics and Astronautics/Blackwell Scientific Publications, procedure, with standard convergence acceleration techniques 1990, 154 p. refs such as local time stepping, enthalpy damping and implicit residual Copyright smoothing. Accuracy of solution, in terms of minimizing spurious The basic principles of helicopter design are examined in a entropy production, is achieved through careful treatment of the brief introduction for engineering students. Chapters are devoted artificial dissipative terms near boundaries. Standard test cases to momentum theory and wake analysis for a rotor in vertical for both subcritical and supercritical flows, including single- and flight; blade element theory; rotor mechanisms and rotor multi-element aerofoils have been used to validate the method. aerodynamics for forward flight; aerodynamic design; performance; Author trim, stability, and control. Diagrams, graphs, and photographs are provided. T.K. A91-11162 . CONTROL OF VORTICAL SEPARATION ON A CIRCULAR A9M1755# CONE COMPARISON OF DIFFERENT CALCULATION METHODS AS N. J. MOURTOS (San Jose State University, CA) Aeronautical APPLIED TO A FUSELAGE OF LENTICULAR SECTION Journal (ISSN 0001-9240), vol. 94, June-July 1990, p. 213-219. [COMPARAISON DE DIFFERENTES METHODES DE CALCUL refs APPLIQUEES A UN FUSELAGE DE SECTION LENTICULAIRE] Copyright P. D'ESPINEY (ONERA, Chatillon, France) (NATO, AGARD, A theoretical model for the analysis of the flow around conical Symposium on Missiles Aerodynamics, Friedrichshafen, Federal bodies at moderate angles of attacks is discussed. A single Republic of Germany, Apr. 23-26, 1990) ONERA, TP no. 1990-66, line-vortex model is initially used to compute the outer inviscid 1990, 16 p. In French, refs field for specified separation lines; a 3-D boundary layer is (ONERA, TP NO. 1990-66) represented by a momentum equation for the cross-flow, analogous Measurements from wind tunnel tests conducted on 'a to that for a plane boundary layer, and a von Karman/Pohlhausen noncircular body representative of nonconventional missile shapes approximation is applied to solve the equation. The cross-flow are analyzed. Mach numbers from 0.4 to 4.5 at angles of attack 02 AERODYNAMICS

up to 20 degrees with sideslip angles up to 10 degrees were (China Aerodynamics Research and Development Centre, studied. The data base consists of wall static pressure Mianyang, People's Republic of China) Acta Aerodynamica Sinica measurements and also of flowfield measurements at Mach-2 for (ISSN 0258-1825), vol. 8, Sept. 1990, p. 235-246. In Chinese, angles of attack of 10 and 20 degrees. Comparisons between with abstract in English, refs experimental data and calculations obtained with different codes A new technique for 'handling the pressure gradient in the are presented, discussing the advantages and drawbacks as to streamwise momentum equation of parabolized Navier-Stokes accuracy and time cost. R.E.P. equations has been developed in order to compute the supersonic •viscous flow over bodies using- a noniterative, implicit, A91-11777# , ...... space-marching finite difference method. The stability conditions DETAILED MEASUREMENTS OF THE FLOW FIELD AT THE for the method are derived from model equations using a new OUTLET OF A BACKSWEPT TRANSONIC CENTRIFUGAL technique. Stable space-marching schemes without a minimum IMPELLER EQUIPPED WITH A VANED DIFFUSER allowable step size are given and used to compute supersonic CH. FRADIN and G. JANSSENS (ONERA, Chatillon, France) flow over an axisymmetric blunt cone. The results are compared ONERA, TP no. 1990-101, 1990, 7 p. refs with those from conventional marching methods using other (ONERA, TP NO. 1990-101) techniques for treating the streamwise pressure gradient term. The Two-focus laser velocimetry is presently used to study the flow present technique exhibits superior capabilities for accurate and field development at the impeller outlet of a transonic-flow stable calculations. C.D. centrifugal compressor whose impeller incorporates splitter blades and an advanced, backswept blade geometry, while the'vaned A91-11836# diffuser employs curved vanes. Velocity profiles and angles are A STUDY OF CYLINDRICAL INTERACTION OF TURBULENT obtained for different relative locations'.of impeller blades and BOUNDARY LAYER/SHOCK WITH SWEPT COMPRESSION diffuser vanes. Due to the high flow distortion in the impeller and CORNERS '••• in the blade passages, highly unsteady flow angle and Mach number XUEYING DENG and ZHIZHONG LIU (Beijing University of fluctuations emerge in both the axial and blade-to-blade directions; Aeronautics and Astronautics, People's Republic of China) Acta these fluctuations also arise, with comparable amplitudes, in the Aerodynamica Sinica (ISSN 0258-1825), vol. 8, Sept. 1990, p. vaned diffuser throat. O.C. 280-285. In Chinese, with abstract in English, refs The three-dimensional shock wave and turbulent boundary layer A91-11779# interaction with swept compression corners is experimentally DETERMINATION OF KINETIC HEATING ON WIND TUNNEL studied. The swept angles range from 0 to 60 deg and the MODELS BY THE SURFACE TEMPERATURE METHOD streamwise corner angles from 10 to 30 deg. Freestream Mach [DETERMINATION DES ECHAUFFEMENTS CINETIQUES SUR numbers of 1.79, 2.04, and 2.50 are used with Reynolds numbers MAQUETTES EN SOUFFLERIES PAR LA METHODE DES of (2.42-2.47) x 10 to the 7th/m. The results indicate the existence TEMPERATURES SUPERFICIELLES] of cylindrical and conical flow regimes in the interactions over the H. CONSIGNY and Y. LE SANT (ONERA, Chatillon, France) given Mach number range. The boundary of the cylindrical/conical (Journees d'Etudes sur les Mesures de Temperatures, Paris, regime occurs at higher alpha(s), gamma value with increasing France, June 19, 20, 1990) ONERA, TP no. 1990-104, 1990, 26 free-stream Mach number. The upstream influence length in the p. In French, refs cylindrical regime can be correlated with that of the two-dimensional (ONERA, TP NO. 1990-104) . . - compression corner. The Mach number effect and crossflow effect A review is presented of the surface temperature method used on this correlation are examined. - C.D. to measure kinetic heating on wind tunnel models. The specific instrumentation used and the techniques.employed to obtain these A91-11838# ' "• ' measurements are described.-. These methods permit the analysis FINITE ELEMENT METHOD FOR COMPUTATION OF of the effects of thickness, curvature and thermal characteristics. TRANSONIC FLOW ABOUT WINGS FROM THE PRESSURE Particular, attention is given to recently developed methodology MINIMUM INTEGRAL :' for determining thermal characteristics and to the modeling of the YIZHAO WU and ZUOSHENG YANG (Nanjing Aeronautical sensor units using a two-dimensional finite element code. It is Institute, People's Republic of-China) Acta Aerodynamica Sinica shown that the effect of lateral conduction can be significant. (ISSN 0258-1825), vol. 8, Sept. 1990, p. 293-300. In Chinese, R.E.P. with abstract in English, refs Starting with the full potential equation, a finite-element method A91-11782# for computing transonic flow about wings is given, using the ESTIMATION OF THE TURBULENT SPECTRAL DENSITIES OF pressure minimum integral. FORTRAN programs are worked out. THE MASS-DENSITY USING TWO-DIMENSIONAL FOURIER A mesh generation technique, 'which is suitable for the FEM, is TRANSFORM OF DIGITIZED SCHLIEREN PICTURES presented. The SLOR method and the successive division method R. DERON and J. P. FALENI (ONERA, Chatillon, France) are-employed. Numerical results for an M6 wing and a delta wing (European Turbulence Conference, 3rd, Stockholm, Sweden, July are given. Author 3-6, 1990) ONERA, TP no. 1990-110, 1990, 9 p. ••refs • (ONERA, TP NO. 1990-110) A91-11839# The analysis of quantitatively digitized- schlieren photographs AN EFFICIENT METHOD FOR SOLVING TRANSONIC FLOW according to a two-dimensional Fourier space approach is shown ABOUT PLANE CASCADES WITH A LARGE NOSING to result in a method furnishing two-dimensional calibrated QIUSHENG LIU and MENGYU SHEN (Tsinghua University, Beijing, cross-sections of three-dimensional mass-density spectral den- People's Republic of China) Acta Aerodynamica Sinica (ISSN 'sities. Turbulent aerodynamic-flow images have been thus 0258-1825), vol. 8, Sept. 1990, p.'301-307. In Chinese, with abstract obtained in wind tunnel experiments, using the single-beam in English, refs "' z-shaped schlieren technique. While the -11/3 Kolmogorov power This paper proposes an;'efficient numerical method predicting law is obtained in a transverse direction to the mean flow, exactly the pressure distribution on the blade surfaces, especially discrepancies from the law appear in other directions. Also in the nosing region. Reforming the aerodynamic equations from determined are rms data for spectral mass density fluctuations an arbitrary normal curve coordinate system into that of von Mises, and for the outer scale of the turbulence. O.C. the streamline governing equation is obtained and solved efficiently in a quasi-boundary-layer coordinate system with a line-relaxation A91-11831# •-'.•• .•-.,• method. The numerical results for RA blades agree well with the A STUDY OF IMPLICIT SPACE-MARCHING METHOD FOR THE experiment and show that, among all the methods known, the SUPERSONIC VISCOUS FLOW OVER THE BLUNT CONE present one has the best accuracy and takes the least CPU time. HANXIN ZHANG, HUI YAO,'SHUCHUN GAO, and QING SHEN -• ' 'Author 02 AERODYNAMICS

A91-11840# vortex grid arranged on a series of concentric multiangular CALCULATION OF BOUNDARY-LAYER FLOWS ON LOW cylindrical surfaces. The ground effect is simulated by an REYNOLDS NUMBER AND TRANSONIC AIRFOILS image-vortex system. The effect of wing-wake vortex deflection QIN E (Northwestern Polytechnics! University, Xian, People's on horizontal tail and vertical tail is discussed. Comparison. with Republic of China) Acta Aerodynamica Sinica (ISSN 0258-1825), other theoretical and experimental results confirms that the method vol. 8, Sept. ,1990, p. 308-314. In Chinese, with abstract in has enough accuracy for engineering applications. Author English, refs In this paper, the laminar and turbulent boundary-layer flows on transonic and low-Reynolds-number airfoils are calculated A91-11845# using a compressible-momentum and mean-flow kinetic-energy AN APPROXIMATE CALCULATING METHOD OF inverse-integral boundary-layer equation method. A transition SUPERSONIC/HYPERSONIC UNSTEADY AERODYNAMIC prediction formulation of the e exp 9 type is employed to evaluate FORCES OF AIRFOILS the location of transition with laminar separation bubbles, and an JINGSONG CHEN and JUN CAO (Nanjing Aeronautical Institute, extra lag equation is included in the turbulent formulation to account People's Republic of China) Acta Aerodynamica Sinica (ISSN for lags in the response of the turbulent stresses. Good agreement 0258-1825), vol. 8, Sept. 1990, p. 339-344. In Chinese, with abstract with experiment is obtained. Author in English, refs A local-flow piston theory is described. Using this theory, A91-11841# formulas are developed which are used for calculating pressure A THREE-DIMENSIONAL INCOMPRESSIBLE EULER FLOW distributions and oscillating derivatives of airfoils in super- SOLUTION IN TURBOMACHINERY sonic/hypersonic flow. The numerical results are compared YAONAN HUA (Chinese Academy of Sciences, Institute of with experimental data and .the results of other theories. It is Engineering Thermophysics, Beijing, People's Republic of China) shown from the examples that, although the piston theory is not Acta Aerodynamica Sinica (ISSN 0258-1825), vol. 8, Sept. 1990, valid for cases with M delta(max) greater than 1, the method p. 315r320. In Chinese, with abstract in English, refs based on local-flow piston theory can still give reasonable results. Using an ADI scheme to solve the Euler equation of primitive Author variables, the three-dimensional .incompressible flowfield in turbomachinery is solved. After the pseudocompressibility is A91-118480 introduced in the continuity equation, the system of governing APPLICATION OF LU-ADI ALGORITHM IN TWO-DIMENSION equations is changed from undefined type into hyperbolic type. TRANSONIC FLOW Giving initial values and boundary conditions, the system of FENG LI and YIYUN WANG (Beijing Institute of Aerodynamics, equations can be solved by use of a time-marching method to People's Republic of China) Acta Aerodynamica Sinica (ISSN get a stable solution. The threerdimensional flowfield within the 0258-1825), vol. 8, Sept. 1990, p. 358-362. In Chinese, with abstract rotor of a single-stage axial compressor is calculated. The prediction in English. results, agree with experimental data. Author

A91-11843# A91-11900# VORTEX DEVELOPMENT ON CRUCIFORM CANARD LOW MACH NUMBER EULER COMPUTATIONS CONFIGURATIONS AT SUPERSONIC SPEEDS D. W. ZINGG (Toronto, University, Downsview, Canada) Canadian JINSEN HONG (Beijing Institute of Aerodynamics, People's Aeronautics and Space Journal (ISSN 0008-2821), vol. 36, Sept. Republic of China) Acta Aerodynamica Sinica (ISSN 0258-1825), 1990, p: 146-152. refs vol. 8, Sept. 1990, p. 327-334. In Chinese, with abstract in ' Numerical solutions of the'Euler equations for two-dimensional English, refs •; . airfoil flows at low Mach numbers are compared with analytical The vapor-screen.technique was used at supersonic speeds solutions for incompressible potential flow. The Euler solutions to determine the development of the longitudinal vortices. Four were obtained using the computer code ARC2D, which employs vortices originating from the trailing edge of canard fins, which •the Beam and Warming implicit approximate factorization algorithm tend to 'leapfrog' in a crossflow plane, or two vortices of the in generalized co-ordinates. Analytical solutions for incom- dihedral fins and a pair of symmetric body vortices, which tend to pressible potential flow were calculated through Karman-Trefftz 'hybrid leapfrog' in another crossflow plane, could be observed. transformations. Effects of free-stream Mach number, artificial Phenomena of vortex unstability appeared when .vortices dissipation, and grid clustering are presented. At a free-stream approached the leapfrog distance. Predicted vortex trajectories Mach number of 0.05, the numerical results obtained using a 249 based on slender-body. theory,- were also compared to the by 49 grid show excellent agreement with the analytical solutions. experimental data. The mathematical model predicted the paths Author of the individual vortices that developed over the missile, provided their initial locations and relative strengths were appropriately specified. Author A91-11909 A THREE-DIMENSIONAL BOUNDARY LAYER ON BODIES A91-11844# WITH A SLIGHT CROSS-SECTIONAL ASYMMETRY AT SMALL THE CALCULATION METHOD FOR SUBSONIC ANGLES OF ATTACK [PROSTRANSTVENNYI POGRANICHNYI LONGITUDINAL AND LATERAL AERODYNAMIC SLOI NA TELAKH S MALOI ASIMMETRIEI POPERECHNOGO CHARACTERISTICS OF COMPLETE AIRCRAFT SECHENIIA PRI NEBOL'SHIKH UGLAKH ATAKI] CONFIGURATION A. D. KHON'KIN and V. I. SHAlAEV Akademiia Nauk SSSR, . MINGSHENG MA and QIDE YANG (China Aerodynamics Research Doklady (ISSN 0002-3264), vol. 313, no. 5, 1990, p. 1067-1071. and Development Centre, Mianyang, People's Republic of China) In Russian, refs Acta Aerodynamica Sinica (ISSN 0258-1825), vol. 8, Sept. 1990, Copyright p. 335-338. In Chinese, with abstract in English. Equations of a three-dimensional boundary layer are analyzed This paper presents a vortex-lattice method which is suitable asymptotically in a rigorous manner, including linear (with respect for the calculation of subsonic longitudinal and lateral aerodynamic to cross-sectional asymmetry and angles of attack) effects. It is characteristics of aircraft. In the method, the lifting surface is shown that, in this case, the problem is reduced to that of solving simulated by a single vortex-lattice layer arranged on the average a set of two-dimensional problems. Singular solutions are obtained surface of the wing mean-camber surface, or by a double for the equations of flow which are valid in the vicinity of sharp vortex-lattice layer arranged on the average surfaces of the upper and blunt apexes. The results of the study make it possible to surface and the lower surface of the wing. The body is simulated significantly simplify the calculation of the boundary layer on the by quadrangular vortex rings arranged on the surface, or by a fuselage under cruising flight conditions. V.L. 02 AERODYNAMICS

A91-12014 -....,-.. flow and a plane' obstacle. For a certain limiting process, flow AN EXPERIMENTAL STUDY OF THE LAMINAR-TURBULENT from one of the sources can be reduced to a uniform supersonic TRANSITION BEHIND THREE-DIMENSIONAL ROUGHNESS IN gas flow. In this case, the problem is reduced to that of uniform A BOUNDARY LAYER ON A SHARP CONE "'. ' gas flow around a source. Astrophysical applications of the problem [EKSPERIMENTAL'NOE ISSLEDOVANIE ' are briefly discussed. V.L. LAMINARNO-TURBULENTNOGO PEREKHODA ZA TREKHMERNOI NEROVNOST'IU V POGRANICHNOM SLOE NA A91-12019 OSTROM KONUSE] FLUCTUATIONS OF A SHOCK WAVE GENERATED BY A. S. SKURATOV and A. V. FEDOROV Akademiia Nauk SiSSR, BOUNDARY LAYER SEPARATION [O KOLEBANIIAKH Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. SKACHKA UPLOTNENIIA, INDUTSIROVANNOGO OTRYVOM 1990, p. 60-66. In Russian, refs POGRANICHNOGO SLOIA] Copyright V. N. BIBKO, B. M. EFIMTSOV, V. G. KORKACH, and V. B. The laminar-turbulent transition behind three-dimensional KUZNETSOV. Akademiia Nauk SSSR, Izvestiia, Mekhanika surface roughness in a nongradient boundary, layer is investigated Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1990, p. 168-170. for a high supersonic velocity of the incoming flow with emphasis In Russian. on the qualitative characteristics of the transition. Quantitative data Copyright on the heat transfer coefficient distribution near the roughness The mechanisms of shock wave fluctuations induced by and in its wake are determined. Data on the position of the separation in supersonic flow past a forward-facing step were laminar-turbulent transition are compared against'the correlations investigated experimentally by measuring the spatial correlations used in practice. . J V.L. of wall pressure pulsations in a low-noise wind tunnel for Mach 2.0 and 4.0. An analysis of the results obtained indicates that A91-12016 turbulent pulsations of the unperturbed boundary layer have little EFFECT OF ENERGY RELEASE IN THE SHOCK LAYER ON, ; effect on the fluctuations of the separation-induced shock wave. SUPERSONIC FLIGHT [VLJIANIE ENERGOVYDELENIIA V From a more general standpoint, the experimental results provide UDARNOM SLOE NA SVERKHZVUKOVOI POLET] additional evidence for the self-organization of separated flows, S. I. ARAFAILOV Akademiia Nauk SSSR,. Izvestiia, Mekhanika which is observed in this particular case as a certain behavior of Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1990,.p. 142-151. the nonstationary flow characteristics. V.L. In Russian, refs . • • , . .. Copyright . '...-.. A91-12020 Supersonic flow past an extended axisymmetric body is FLOW OF A RAREFIED GAS AROUND A SPHERE IN THE investigated analytically ,fpr the case where an energy release PRESENCE OF INJECTION [OBTEKANIE SFERY region is present between the body surface and the shock wave. RAZREZHENNYM GAZOM PRI NALICHII VDUVA] Such regions can be used to change the aerodynamic K. V. NIKOLAEV Akademiia Nauk SSSR, Izvestiia, Mekhanika characteristics of flying bodies and to influence the flight through Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1990, p. 175-179. a decrease or an increase in the drag coefficient or through the In Russian, refs generation of an additional lifting force or an .aerodynamic moment. Copyright Here, a simple model of stationary flow past a body with an energy Hypersonic flow of a rarefied gas past the .windward side of a release source is used to determine the energy source parameters sphere, with distributed injection from its surface, is investigated corresponding to a maximum control (lift) force per unit time for a using direct statistical modeling by the Monte Carlo method. It is given energy consumption rate. . V.L. shown, in particular, that gas injection from the sphere surface can be used to reduce both the .heat flow and the body resistance A91-12017 for Reynolds numbers greater than 1. The efficiency of injection SHOCK WAVE FORMATION DURING INTERACTION WITH A increases with the Reynolds number, in agreement with results WEAK DISCONTINUITY AT THE BOUNDARY OF A LOCAL based on the continuum theory.' ' V.L. SUBSONIC REGION [FORMIROVANIE UDARNOI VOLNY PRI VZAIMODEISTVII SO SLABYM RAZRYVOM NA GRANITSE A91-12226# MESTNOI DOZVUKOVOI ZONY] AERODYNAMIC HEATING IN THE INTERACTION REGIONS S. A. SHCHERBAKOV Akademiia Nauk SSSR, Izvestiia, OF SHOCK WAVES AND TURBULENT BOUNDARY LAYERS Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. 1990, p. INDUCED BY SWEPTBACK BLUNT FINS 152-158. In Russian, refs SHIGERU ASO (Kyushu University, Fukuoka, Japan), KURANAGA Copyright • ••• .•••„•• SEISHI (Mitsubishi Heavy Industries, Ltd., Tokyo; Japan), and For the Tricomi equation of plane potential flow in velocity SHIGEHIDE NAKAO Kyushu University, Faculty of Engineering, hodograph variables, a self-similar solution is'obtained which Memoirs (ISSN 0023-6160), vol. 50, June 1990, p. 121-134. refs explains the formation of a shock wave of-the strong family (the Aerodynamic heating phenomena in three-dimensional boundary Mach number behind the wave is less than 1) at the sonic line. layers are discussed. The experimental conditions include The intensity of the shock wave varies along its .generatrix in sweptback blunt fins, a thin-film heat-transfer gage with high spatial accordance with a power law with an exponent close to one. At resolution and fast response, Mach number of 4, wall temperature the interaction point, the discontinuity of the derivatives along the ratio (Tw/To) of 0.65, and Reynolds number of 1.2 x 10 to the flow lines equals infinity. * " V.L. 7th. Blunt fins having semicylindrical leading edges and sweep angles of 0, 15, 30, and 45 deg are tested, and the flow around A91-12018 them is made visible using oil techniques. The surface pressure INTERACTION OF TWO SUPERSONIC RADIAL GAS FLOWS and heat flux distributions in the interaction regions of the shock [VZAIMODEISTVIE DVUKH SVERKHZVUKOVYKH waves and the turbulent boundary layers have two peaks at smaller RADIAL'NYKH POTOKOV GAZA] sweep angles and one peak at larger angles, respectively. With M. G, LEBEDEV and A. V. MIASNIKOV Akademiia Nauk SSSR, the increase of the sweep angle of the fin, the size of the interaction Hzvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), July-Aug. region decreases, the maximum peak pressure and the heating 1990, p. 159-165. In Russian, refs ....'.' rate decrease to an even greater extent, and the shock structure Copyright ' ' • _\~ becomes simpler and stable. B.P. The flow resulting from the impact of two spherically symmetric supersonic gas. flows generated by ^three-dimensional sources is A91-12434# investigated using a nonviscous ideal gas model'.. In the case where NUMERICAL SIMULATION OF VORTEX-WEDGE the characteristics'of both sources are the same; the problem Is INTERACTION reduced to that of the interaction between a' spherically symmetric DUCK-JOO LEE (Korea Advanced Institute of Science and 02 AERODYNAMICS

Technology, Seoul, Republic of .Korea). YOUNG-NAM KIM, and stationary hot film probe mounted between the forward and aft JIN-HO PARK AIAA, Aeroacoustics Conference, 13th, rotors of a model CRP. Data were obtained at several locations Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs between rotors.'To establish the rotor-rotor interaction flow (AIAA PAPER 90-3918) mechanism, a method of conditional sampling has been developed Interaction between vortical flows and a solid surface .is one which effectively fixes the forward rotor position in time or space of the primary sources of noise and unsteady loading. The and permits averaging the mean wake at any fixed rotor angular mechanism of the interaction is studied numerically for a single location. By 'fixing' the position of the forward blades, one can Rankine vortex impinging on a wedge. An Euler-Lagrangian method track the disturbance of the forward rotor as the rear rotor moves is employed to calculate the unsteady incompressible viscous'flows by. The decay and spreading o1 the forward blade wakes and the in two dimensions. A hybrid vortex sheet and a random vortex upstream propagation of the rear blade disturbance are shown method are used to describe the vorticity fields. The flows away along with the interaction of the flow disturbances from the two from the wedge surface and near the surface' are modeled as sets of blades. ' Author vortex blobs and vortex sheets, respectively. Vortex trajectories are presented at selected times for both the inviscid and the viscous interactions. The incident vortex distorts and splits when A91-12512*# MCAT Inst., San Jose, CA. the vortex nears the wedge, and a secondary vortex is shed near APPLICATION OF CFD TO SONIC BOOM NEAR AND MID the leading edge of the wedge. Author FLOW-FIELD PREDICTION SAMSON H. CHEUNG (MCAT Institute, San Jose, CA), THOMAS A91-12472# A. EDWARDS, and SCOTT L. LAWRENCE (NASA, Ames Research NUMERICAL SIMULATION OF 3-D SUPERSONIC FREE SHEAR Center, Moffett Field, CA) AIAA, Aeroacoustics Conference, 13th, LAYERS Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs I. TUNCER and L. N. SANKAR (Georgia Institute of Technology, (AIAA PAPER 90-3999) Copyright Atlanta) AIAA, Aeroacoustics Conference, ,13th, Tallahassee, A three-dimensional parabplized Navier-Stpkes (PNS) code has FL, Oct. 22-24, 1990. 13 p. refs been used to calculate the supersonic overpressures from three (Contract N00014-89-J-1319) . different geometries at near- and mid-flow fields. Wind-tunnel data (AIAA PAPER 90-3958) Copyright ... is used for code validation. Comparison of the computed results The temporal stability and growth characteristics of three- with different grid refinements is shown in this paper. It is observed dimensional supersonic shear layers are numerically investi- that a large number of grid points is needed to resolve the tail gated. An explicit time marching scheme that is second order shock/expansion fan interaction. Therefore, an adaptive grid accurate in time and fourth order accurate in space is used approach is employed to calculate the flow field. The agreement to study this problem. The shear jayer is.excited by random initial between the numerical results and the wind-tunnel data confirms disturbances or instability waves 'computed from a linear stability that computational fluid dynamics can be applied to the problem analysis. It is observed that the temporal growth is a strong function of sonic boom prediction. Author of the convective Mach number of the eddies. At low convective Mach numbers organized spanwise structures develop both for A91-12513*# Grumman Aerospace Corp., Bethpage,'NY. the random disturbance and the modal disturbance cases. At AN EULER CODE PREDICTION OF NEAR FIELD TO MIDFIELD superosnic convective Mach numbers, vortical structures with SONIC BOOM PRESSURE SIGNATURES significant streamwise components were found to occur. Author M. J. SICLARI (Grumman Corporate Research Center, Bethpage, NY) and C. M. DARDEN (NASA, Langley Research Center, A91-12473*# Sandia National Labs., Albuquerque, NM. Hampton, VA) . AIAA, Aeroacoustics Conference, 13th, INSTABILITY OF A SUPERSONIC SHOCK-FREE ELLIPTIC JET Tallahassee, FL, Oct. 22-24, 1990. 15 p. refs ROY S. BATY (Sandia National Laboratories, Albuquerque, NM), (AIAA PAPER 90-4000) Copyright ;. . JOHN M. SEINER, and MICHAEL K. PONTON (NASA, Langley A new approach, is presented for computing sonic boom Research Center, Hampton, VA) AIAA, Aeroacoustics Conference, pressure signatures in the near field to midfield that utilizes a fully 13th, Tallahassee, FL, Oct. 22-24, 1990. 15 p. refs three-dimensional Euler finite volume code capable'of analyzing (Contract NAG 1-657) complex geometries. Both linear and nonlinear sonic.boom (AIAA PAPER 90-3959) .... methodologies exist but for the most part rely primarily on equivalent A comparison of the measured and the computed spatial stability area distributions for the prediction of far field pressure signatures. properties of an aspecf ratio 2, supersonic, shock .free, elliptic jet This is due to the absence of a flexible nonlinear methodology is presented. The shock free nature of the elliptic jet furnishes a that can predict near field pressure signatures generated, by perfect test of the validity of modeling the large scale coherent three-dimensional aircraft geometries. It is the intention of the structures in the initial.mixing region of noncircular supersonic jets present study to present a nonlinear Euler method than can fill with the linear hydrodynamic stability theory. Aerodynamic and this gap and supply the needed near field signature data for many acoustic data are measured to compute the mean velocity profiles of the existing.sonic boom codes. Author and to provide a description of the spatial composition of pressure waves in the elliptic jet. The measured mean velocity profiles are employed to provide a qualitative .model for the cross sectional A91-1252T# National Aeronautics and Space Administration. geometry and the smooth velocity profiles utilized in the stability Lewis Research Center, Cleveland, OH. analysis. It is shown that the measured frequency associated with EFFECT OF ACOUSTIC EXCITATION ON STALLED FLOWS peak amplitude noise radiation agrees with that frequency predictea OVER AN AIRFOIL to dominate the large scale structure near the end of the potential K. B. M. Q. ZAMAN (NASA, Lewis Research Center, Cleveland, core. .. R.E.P. OH) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 12 p. refs A91-12489*# North Carolina State Univ., Raleigh. (AIAA PAPER 90-4009) Copyright INTERACTION BETWEEN ROTORS OF A COUNTER The effect of acoustic excitation on poststalled flows over an ROTATING PROPELLER airfoil, i.e., flows that are fully separated from near the leading JIN-DEOG CHUNG, JOSEPH HOUGH, and ROBERT T. NAGEL edge, is investigated. The excitation results in a tendency toward (North Carolina State University, Raleigh) AIAA, Aeroacoustics reattachment, which is accompanied by an increased lift and Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 10 p. reduced drag, although the flow may still remain fully separated. Research supported by McDonnell Douglas Corp. refs . It is found that with increasing excitation amplitude, the effect (Contract NAG3-855) becomes more pronounced but shifts to a Strouhal number which (AIAA PAPER 90-3976) Copyright is much lower than that expected from linear, inviscid instability of Thermal anemometer measurements were obtained from a the separated shear layer. Author 02 AERODYNAMICS

A91-12530# A unified unsteady lifting-line theory is presented. The solution SUPPRESSION OF FLOW-INDUCED PRESSURE of the integral equation of the problem yields an asymptotic OSCILLATIONS IN CAVITIES expansion which is uniformly valid with respect to the frequency R. L. SARNO and M. E. FRANKE (USAF, Institute of Technology, of perturbations. The wing may be curved or inclined with respect Wright-Patterson AFB, OH) AIAA, Aeroacoustics Conference, to the flow. Author 13th, Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs (AIAA PAPER 90-4018) A91-12690*# Analytical Services and Materials, Inc., Hampton, Experimental methods for suppressing flow-induced pressure VA. oscillations in a shallow open cavity resulting from tangential flows APPLIED ASPECTS OF LAMINAR-FLOW TECHNOLOGY over the cavity are described. The effects of manipulating the A. L. BRASLOW (Analytical Services and Materials, Inc., Hampton, shear layer over the cavity leading edge are examined. Static and VA), D. V. MADDALON, D. .W. BARTLETT, R. D. WAGNER (NASA, pulsating fences and steady and pulsating flow injection at the Langley Research Center, Hampton, VA), and F. S. COLLIER, JR. leading edge are studied for their effect on cavity sound pressure (High Technology Corp., Hampton, VA) IN: Viscous drag reduction levels. Both subsonic and supersonic flow conditions are in boundary layers. Washington,. DC, American Institute of considered. Of the methods tested static fences at the leading Aeronautics and Astronautics, Inc., 1990, p. 47-78. refs edge were found to provide the most suppression. Suppression Copyright was dependent on the frequency mode and the flow Mach An account is given of the development status and performance number. Author levels achieved with natural laminar flow (NLF), extended wing chord laminar flow control (LFC), and hybrid laminar flow control A91-12535# (HLFC) concepts combining NLF and partial-chord LFC in the > NUMERICAL SIMULATION OF SUPERSONIC MIXING LAYER leading-edge region. Attention is given to NLF wing structure USING HIGH RESOLUTION SCHEME construction methods capable ofy achieving the requisite PONG-JEU LU and KUEN-CHUAN WU (National Cheng Kung surface-irregularity tolerances, LFC through wing surface suction University, Tainan, Republic of China) AIAA, Aeroacoustics slots or perforated skins, and the deleterious effects of insects, Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 15 p. ice crystals, and noise disturbance inputs on the ability of NLF, Sponsorship: National Science Council of the Republic of China. LFC, and HLFC wings to maintain effective laminar flow refs operation. O.C. (Contract NSC-79-0401-E006-44) (AIAA PAPER 90-4025) Copyright A91-12692# Two-dimensional direct numerical simulations for a confined APPLICATION OF CFD TO REDUCTION OF SKIN-FRICTION inviscid spatially-growing supersonic mixing layer have been DRAG conducted. The nonlinear shear-layer development and the TUNCER CEBECI (Douglas Aircraft Co., Long Beach, CA) IN: corresponding flow structures are examined on the basis of Viscous drag reduction in boundary layers. Washington, DC, numerical flow visualizations and Favre-averaged turbulence American Institute of Aeronautics and Astronautics, Inc., 1990, p. results. It is determined that the numerically visualized downstream 115-178. refs compression/expansion wave system explains the 'strange waves' Copyright observed in experiments and is responsible for the rapid growth The present development status evaluation of practical of the mixing layer in that region. It is found that shock induced techniques for the reduction of skin-friction drag and their mixing improvement is local and may be followed by saturation in associated, CFD-employing design processes gives attention to turbulent energy which impedes the further growth of the shear such aircraft structure components as wings and fuselages, but is layer. This and subsequent observations suggest that broadly relevant to all vehicle classes. The optimization of a compressibility effects may behave in a considerably different geometrical configuration to minimize drag involves the calculation manner as the underlying instability mechanism changes from the of drag for a range of geometries and surface conditions subsonic Kelvin-Helmholtz type to the present supersonic instability encompassing cooling, suction, and injection; this is best conducted wall type. L.K.S. with a computer-based method of known reliability, and may involve the computation of flows for many configurational alternatives and A91-12559 their boundary conditions. O.C. THEORY OF SLIGHTLY BLUNTED AXISYMMETRIC POWER-LAW BODIES AT SMALL ANGLE OF ATTACK IN A91-12695*# National Aeronautics and Space Administration. HYPERSONIC FLOW [THEORIE DES FAIBLES INCIDENCES Langley Research Center, Hampton, VA. EN HYPERSONIQUE POUR LES CORPS AXISYMETRIQUES OUTER-LAYER MANIPULATORS FOR TURBULENT DRAG EN LOI DE PUISSANCE ET A EMOUSSEMENT FAIBLE] REDUCTION ALAIN MERLEN (ONERA; Lille I, Universite, France) Academie J. B. ANDERS, JR. (NASA, Langley Research Center, Hampton, des Sciences, Comptes Rendus, Serie II - Mecanique, Physique, VA) IN: Viscous drag reduction in boundary layers. Washington, Chimie, Sciences de la Terre et de I'Univers (ISSN 0764-4450), DC, American Institute of Aeronautics and Astronautics, Inc., 1990, vol. 310, no. 5, March 1, 1990, p. 465-470. In French, refs p. 263-284. refs Copyright Copyright As a generalization of the nonstationary analogy, the The last ten years have yielded intriguing research results on noninstantaneous explosion of an infinite rectilinear wire in a aerodynamic boundary outer-layer manipulators as local skin friction uniform flow is related to the hypersonic flow around a slightly reduction devices at low Reynolds numbers; net drag reduction blunted axisymmetric power-law body at small angle of attack. device systems for entire aerodynamic configurations are Aerodynamic coefficients are analytically calculated and compared nevertheless noted to remain elusive. Evidence has emerged for to the results of the Newtonian theory.. Author dramatic alterations of the structure of a turbulent boundary layer which persist for long distances downstream and reduce wall shear A91-12575 as a results of any one of several theoretically possible A UNIFIED UNSTEADY LIFTING-LINE THEORY [UNE THEORIE mechanisms. Reduced effectiveness at high Reynolds numbers UNIFIEE DE LA LIGNE PORTANTE] may, however, limit the applicability of outer-layer manipulators to JEAN-LUC GUERMOND and ANTOINE SELLER (Bassin d'Essais practical aircraft drag reduction. O.C. des Carenes, Paris, France) Academie des Sciences, Comptes Rendus, Serie II - Mecanique, Physique, Chimie, Sciences de la A91-12696*# National Aeronautics and Space Administration. Terre et de I'Univers (ISSN 0764-4450), vol. 311, no. 1, July 5, Langley Research Center, Hampton, VA. 1990, p. 21-26. In French, rels CONVEX CURVATURE CONCEPT OF VISCOUS DRAG Copyright REDUCTION 02 AERODYNAMICS

PROMODE R. BANDYOPADHYAY (NASA, Langley Research and the theory of functions of a complex variable. The linear Center, Hampton, VA) IN: Viscous drag reduction in boundary nature of the potential-flow problem invites use of the principle of layers. Washington, DC, American Institute of Aeronautics and superposition to construct solutions to problems through the Astronautics, Inc., 1990, p. 285-324. refs summing of simpler solutions; the bodies thus discretized are said (Contract WAS 1-18235; NAS1-18599) to be composed of 'panels'. The boundary conditions for a panel Copyright method consist of (1) the zero normal-velocity boundary condition Experiments have indicated that for certain convex aerodynamic applied to one control point for each panel on the body surface; surface curvature ratios, wall-shear stresses remain low over (2) the Kutta condition applied to the trailing edges of lifting portions considerable streamwide distances even after curvature is removed. of the configuration; and'(3) the zero normal velocity and zero The research whose progress is presently evaluated was first pressure jump conditions applied along the trailing vortex wake. suggested by Bushnell (1983), who proposed that the O.C. convex-surface curvature be used in axisymmetric bodies to ascertain whether the viscous component of total drag is reduced. Attention is given to the evolution of the concept's implementation A9M2755* in an axisymmetric nose-body combination for passive viscous GRID-GENERATION METHODOLOGY IN APPLIED drag reduction. • O.C. AERODYNAMICS JOHN P. STEINBRENNER (General Dynamics Corp., Fort Worth, A91-12698*# National Aeronautics and Space Administration. TX) and DALE A. ANDERSON (Texas, University, Arlington) IN: Langley Research Center, Hampton, VA. Applied computational aerodynamics. Washington, DC, American VISCOUS DRAG REDUCTION VIA SURFACE MASS Institute of Aeronautics and Astronautics, Inc., 1990, p. 91-130. INJECTION refs ' " - JERRY N. HEFNER and DENNIS M. BUSHNELL (NASA, Langley Copyright Research Center, Hampton, VA) IN: Viscous drag reduction in The present account of CFD grid-generation methodology boundary layers. Washington, DC, American Institute of Aeronautics proceeds by considering such elements of flowfield domain and Astronautics, Inc., 1990, p. 457-476. refs discretization as structured and unstructured grid concepts and Copyright single- and multiple-block concepts. Attention is then given to Slot injection systems on the surfaces of aerodynamic bodies various currently employed methods of grid generation with a view have been noted to consistently furnish substantial local skin friction to their aerodynamic applications. Discussions are restricted to reductions which are predictable on the basis of current numerical steady-state flows, and adaptive gridding methods being developed methods. Only crude systems studies, however, have been thus for time-accurate problems are treated only from a static standpoint far completed. The most common configuration for slot ingestion in which an approximately converged flow solution is used to modify in the literature involves tangential injection of air along a the original grid to enhance overall accuracy. O.C. two-dimensional surface on which air constitutes the mainstream flow; attention is presently given to slot injection in low-speed and high-speed flows, as well as a discussion of aircraft applications A91-127S6# and an evaluation of prospective possibilities for practical SUBSONIC AIRFOIL DESIGN drag-reduction systems. O.C. ROBERT H. LIEBECK (Douglas Aircraft Co., Long Beach, CA) IN: Applied computational aerodynamics. Washington, DC, A91-12751 American Institute of Aeronautics and Astronautics, Inc., 1990, p. APPLIED COMPUTATIONAL AERODYNAMICS 133-165. refs P. A. HENNE, ED. (Douglas Aircraft Co., Long Beach, CA) Copyright Washington, DC, American Institute of Aeronautics and The James (1971) subsonic airfoil design methodology, whose Astronautics, Inc. (Progress- in Astronautics and Aeronautics. applications-development history is presented, furnishes exact Volume 125), 1990, 951 p. For individual items see A91-12752 to solutions to the direct and inverse airfoil design problems. In the A91-12775. inverse case, the desired airfoil velocity distribution, described as Copyright a function of arc length along the airfoil surface itself, is employed. The present volume discusses the original development of the Leading and trailing edge singularities are treated exactly by the panel method, the mapping solutions and singularity distributions James method, with the input velocity distribution defining the of linear potential schemes, the capabilities of full-potential, Euler, trailing edge angle. Applications illustrating the use of the method and Navier-Stokes schemes, the use of the grid-generation encompass low Reynolds number airfoils, wind turbine blade methodology in applied aerodynamics, subsonic airfoil design, sections, acrobatic aircraft wings, sailboat rudders, race car inverse airfoil design for transonic applications, the divergent spoilers, and pterosaur model wings. O.C. trailing-edge airfoil innovation in CFD, Euler and potential computational results for selected aerodynamic configurations, and the application of CFD to wing high-lift systems. Also discussed A91-12757# are high-lift wing modifications for an advanced-capability EA-6B ELEMENTS OF AIRFOIL DESIGN METHODOLOGY aircraft, Navier-Stokes methods for internal and integrated MARK DRELA (MIT, Cambridge, MA) IN: Applied computational propulsion system flow predictions, the use of zonal techniques aerodynamics. Washington, DC, American Institute of Aeronautics for analysis of rotor-stator interaction, CFD applications to complex and Astronautics, Inc., 1990, p. 167-189. Research supported by configurations, CFD applications in component aerodynamic design MIT. refs of the V-22, Navier-Stokes computations of a complete F-16, CFD Copyright at supersonic/hypersonic speeds, and future CFD developments. An account is given of the state-of-the-art in two-dimensional O.C. CFD airfoil design methodology. The two very different airfoil design cases presented are illustrative of the numerous and complex A91-127530 decisions that must be made in the course of airfoil profile definition, LINEAR POTENTIAL SCHEMES and of the essential role played by a fast viscous analysis method. J. L HESS (Douglas Aircraft Co., Long Beach, CA) IN: Applied Attention is given to the currently most popular viscous analysis computational aerodynamics. Washington, DC, American Institute methods; it is noted that Navier-Stokes methods are at present of Aeronautics and Astronautics, Inc., 1990, p, 21-36. refs unsuitable for routine aircraft design work, due to excessive Copyright computational requirements. The importance of furnishing The present account of linear potential schemes notes their designers with the greatest possible airfoil-modification flexibility mapping solutions to be based on the intimate connection between and graphics-based interactive input/output systems is empha- any problem governed by the two-dimensional Laplace equation sized. O.C. 02 AERODYNAMICS

A91-12758# presently given of the character and performance of viscous INVERSE AIRFOIL DESIGN - A CLASSICAL APPROACH methods devised for the analysis of multielement slotted airfoils; UPDATED FOR TRANSONIC APPLICATIONS these methods are classifiable as (1) coupled attached flow; (2) G. VOLPE (Grumman Corporate Research Center, Bethpage, NY) coupled separated flow; (3) Navier-Stokes; and (4) design and IN: Applied computational aerodynamics. Washington, DC, optimization. The nature of the flow around three-dimensional American Institute of Aeronautics and Astronautics, Inc., 1990, p. high-lift airfoil configurations is further complicated by the geometric 191-220. refs complexities of part-span slotted flaps and their supporting tracks, Copyright wing and flap sweep, spanwise geometry variations, and engine In the inverse airfoil design methodology presented, three free nacelles. .' O.C. parameters are numerically adjusted in order to drive the freestream speed and trailing-edge gap dimensions to prescribed values. These A91-12762*# National 'Aeronautics and Space Administration. trailing-edge parameters are introduced in such a fashion that Langley Research Center; Hampton, VA. only one of the design constraints is primarily affected, allowing DEVELOPMENT OF HIGH-LIFT WING MODIFICATIONS FOR the formulation of an iterative scheme of iterative type in which AN ADVANCED CAPABILITY EA-6B AIRCRAFT the three parameters can be ascertained on the basis of three EDGAR G. WAGGONER (NASA, Langley Research Center, uncoupled one-dimensional relaxation methods. The overall effect Hampton, VA) IN: Applied computational aerodynamics. of these method components is a robustness which yields speed Washington, DC, American Institute of Aeronautics and distributions closely approximating an arbitrarily prescribed ideal. Astronautics, Inc., 1990, p. 435-457. refs O.C. Copyright NASA-Langley has been in a development program aimed at A91-12759# improvements of the EA-6B electronic countermeasures aircraft's INNOVATION WITH COMPUTATIONAL AERODYNAMICS - maneuvering capabilities; one objective of this effort is the THE DIVERGENT TRAILING-EDGE AIRFOIL investigation of relatively simple wing design modifications which P. A. HENNE (Douglas Aircraft Co., Long Beach, CA) IN: Applied could yield improved low speed high lift performance with minimum computational aerodynamics. Washington, DC, American Institute degradation of higher-speed performance. Various two- and of Aeronautics and Astronautics, Inc., 1990, p. 221-261. refs three-dimensional low speed and transonic CFD techniques have Copyright accordingly been used during the design effort, which involved The divergent trailing-edge (DTE) airfoil concept emerged from leading-edge slat and trailing-edge flap contour evaluations by both a CFD study conducted in 1981, which predicted enhanced computation and wind tunnel experiment. Significant low-speed effectiveness from small variations in airfoil contour near the trailing maximum-lift enhancements were obtained without cruise-speed edge. In addition to witnessing airfoil design and testing, the years deterioration. O.C. since these initial discoveries have seen wing-development efforts concerned with three-dimensional, swept-wing transport aircraft A91-12763# applications of DTE predicated on high performance supercritical NAVIER-STOKES METHODS FOR INTERNAL AND wing configurations. Since the DTE airfoil will generate a significant INTEGRATED FLOW PREDICTION increase in circulation over a conventional airfoil, spanwise-loading RAYMOND R. COSNER (McDonnell Douglas Corp., Saint Louis, changes will result from partial-span application of the DTE concept. MO) IN: Applied computational aerodynamics. Washington, DC, The availability of powerful CFD resources has been invaluable to American Institute of Aeronautics and Astronautics, Inc., 1990, p. DTE development. O.C. 461-478. refs Copyright . . A91-12760*# National Aeronautics and Space Administration. The most important phenomena encountered in internal Ames Research Center, Moffett Field, CA. aerodynamic flows are most effectively addressed by means of EULER AND POTENTIAL COMPUTATIONAL RESULTS FOR CFD methods based on the Reynolds-averaged Navier-Stokes SELECTED AERODYNAMIC CONFIGURATIONS equations. Currently, problems are being treated using single-zone R. M. HICKS, S. E. CLIFF, J. E. MELTON, R. G. LANGHI, A. M. and multizone methods whose boundary conditions are appropriate GOODSELL (NASA, Ames Research Center, Moffett Field, CA) et for internal flow. The split flow paths, bifurcated ducts, inlet bleed, al. IN: Applied computational aerodynamics. Washington, DC, secondary air removal/addition, and other flow-path complexities American Institute of Aeronautics and Astronautics, Inc., 1990, p. encountered in internal flows have entailed the modification of 263-385. refs existing codes developed for simpler problems. As with all CFD Copyright applications, the use of these tools is impeded by the high cost A selection of CFD successes and failures is evaluated, on of analysis; in order to justify such high computational costs, the the basis of experimental data/CFD result correlations involving solutions must apply to the exact geometry and furnish full-potential and Euler computations of the aerodynamics of four high-confidence answers. O.C. commercial transport wings and two low aspect ratio delta wings. An effort is made to ascertain optimum values for grid density A91-12764*# Sterling Federal Systems, Inc., Palo Alto, CA. and distribution, artificial dissipation, Courant-Friedrichs-Lewy COMPUTATIONAL ANALYSIS OF ROTOR-STATOR number, enthalphy damping, and a multigrid scheme for each flow INTERACTION IN TURBOMACHINERY USING ZONAL condition and configuration analyzed. It is demonstrated that CFD TECHNIQUES solutions can assist the experimentalist prior to a test by indicating NATERI K. MADAVAN (Sterling Federal Systems, Inc., Palo Alto, the locations of high pressure gradients and projecting test CA) and MAN MOHAN RAI (NASA, Ames Research Center, Moffett condition limitations due to balance design limits. O.C. Field, CA) IN: Applied computational aerodynamics. Washington, DC, American Institute of Aeronautics and Astronautics, Inc., 1990, A91-12761# p. 481-529. Research supported by the U.S. Navy, refs COMPUTATIONAL AERODYNAMICS APPLIED TO HIGH-LIFT Copyright SYSTEMS The development of CFD zonal techniques which allow more . G. W. BRUNE and J. H. MCMASTERS (Boeing Co., Seattle, WA) intensive computational treatment in some regions than in others, IN: Applied computational aerodynamics. Washington, DC, in conjunction with robust, high-accuracy algorithms for the American Institute of Aeronautics and Astronautics, Inc., 1990, p. numerical solution of the Navier-Stokes equations, is presently 389-433. refs shown to have facilitated the investigation of rotor-stator Copyright interactions in turbomachinery. Attention is given to integration Confluent boundary layers and flow separatipn are critical schemes with two and three spatial dimensions, the conservative differences from cruise-lift airfoil configurations which must be 'patched' and the nonconservative zonal boundary schemes, and treated by high-lift airfoil designers using CFD. An account is such natural boundary conditions as those of the endwall, the

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stator inlet, the airfoil surface, and the rotor exit. Illustrative American Institute of Aeronautics and Astronautics, Inc., 1990, p. three-dimensional rotor-stator interaction calculations are pre- 637-678. refs sented. O.C. Copyright An account is given of the CFD methods used to develop the A9M2765# aerodynamic contours of the V-22 tilt-rotor vehicle, where distinct EULER/NAVIER-STOKES CALCULATIONS OF THE problems were posed by rotor blade design, wing design, fuselage FLOWFIELD OF A HELICOPTER ROTOR IN HOVER AND fairing contours, nacelle inlet optimization, and airload distributions FORWARD FLIGHT over the entire configuration. The CFD codes used encompassed RAMESH K. AGARWAL and JERRY E. DEESE (McDonnell Douglas GRUMFOIL, ARC2D, VSAERO, and NASTRAN. Both wing and Research Laboratories, Saint Louis, MO) IN: Applied rotor airfoil profiles were treated with the Aerodynamic Design computational aerodynamics. Washington, DC, American Institute and Analysis Methodology. The CFD results obtained not only of Aeronautics and Astronautics, Inc., 1990, p. 533-555. refs direct the tailoring of aerodynamic contours in the direction of Copyright performance specifications, but furnish aerodynamic loads The Euler/Navier-Stokes code designated 'MDROTH' has been information to structural systems designers. O.C. developed for calculating the flowfield of a multibladed helicopter rotor in hover and forward flight. The code obtains the flowfield A91-12769# by solving the three-dimensional Euler/Navier-Stokes equations in AERODYNAMIC ANALYSIS USING EULER EQUATIONS • a rotating coordinate system on body-conforming curvilinear grids CAPABILITIES AND LIMITATIONS around the blades. The equations are solved for the absolute-flow PRADEEP RAJ (Lockheed Aeronautical Systems Co., Burbank, variables by employing Jameson's (1981) finite-volume explicit CA) IN: Applied computational aerodynamics. Washington, DC, Runge-Kutta time-stepping scheme. Viscous effects are modeled American Institute of Aeronautics and Astronautics, Inc., 1990, p. via the thin-layer approximation to the Reynolds-averaged 679-700. Research supported by the Lockheed Aeronautical Navier-Stokes equations, in conjunction with the Baldwin-Lomax Systems Co. refs algebraic turbulence model. O.C. Copyright An evaluation is presented of the capabilities of a representative A91-12766# Euler CFD code, the Three-dimensional Euler/Navier-Stokes CFD APPLICATIONS TO COMPLEX CONFIGURATIONS - A Aerodynamic Method, 'TEAM', in light of three criteria: configuration SURVEY geometry, flow conditions, and solution accuracy. For many cases, EDWARD N. TINOCO (Boeing Co., Seattle, WA) IN: Applied sensitivity to grid density, numerical dissipation, and boundary computational aerodynamics. Washington, DC, American Institute condition treatment are also evaluated. The six illustrative test of Aeronautics and Astronautics, Inc., 1990, p. 559-615. refs cases considered are the NLR 7301 airfoil, a transonic Copyright maneuvering-optimized fighter wing, a 74-deg delta wing, a An account is given of state-of-the-art, primarily inviscid CFD cone-derived Mach 6 waverider configuration, a canard-wing-body applications to complex aircraft configurations. The ability of panel configuration, and an Advanced Nozzle Concept fighter methods to model complex configurations without recourse to configuration. The TEAM code is found to accommodate patched flowfield grid generation, as well as their comparative computational multizone structured grids of arbitrary topologies, thereby facilitating economy, has led to their adoption in many applications. Such complex configuration analyses. O.C. linear panel methods as A502/PAN AIR, HISS, and QUADPAN, can employ the same paneling model for both subsonic and A91-12770*# National Aeronautics and Space Administration. supersonic analysis. As a configuration is further refined, CFD Ames Research Center, Moffett Field, CA. can be used to ascertain control effectiveness, viscous effects, TOWARD THE ROUTINE AERODYNAMIC ANALYSIS OF wake and flowfield characteristics, weapons store behavior, and COMPLEX CONFIGURATIONS engine/airframe integration effects. Attention is given to 747-300 MICHAEL D. MADSON and LARRY L ERICKSON (NASA, Ames flight test comparisons with CFD data, 737-300 wind tunnel Research Center, Moffett Field, CA) IN: Applied computational comparisons with CFD data, and CFD studies of propfan aerodynamics. Washington, DC, American Institute of Aeronautics installations. O.C. and Astronautics, Inc., 1990, p. 701-751. refs (Contract NAS2-12513) A91-12767# Copyright COMPUTATIONAL AERODYNAMICS APPLIED TO GENERAL An evaluation is made of the ability of the TranAir CFD code AVIATION/BUSINESS AIRCRAFT to routinely compute the aerodynamic characteristics of complex NEAL J. PFEIFFER (Beech Aircraft Corp., Wichita, KS) IN: Applied subsonic and supersonic aircraft configurations. TranAir solves the computational aerodynamics. Washington, DC, American Institute full-potential equation for transonic flow about completely arbitrary of Aeronautics and Astronautics, Inc., 1990, p. 617-635. refs geometries, using the surface-paneling PanAir technique in Copyright geometry definition. The uniform global grid may be locally refined After an account of the difficulties and requirements for the in regions where flow properties are rapidly changing, such as integration of CAD data on aircraft designs with CFD analyses of regions where shocks arise, and around wing leading edges. Unlike their aerodynamic characteristics, attention is given to a panel method codes, TranAir solutions are not undermined by NASA-Langley method which appears uniquely suited to the CFD small-perturbation assumptions. Illustrative results are presented characterization of business turboprop configurations with aft for such configurations as the F-16A with wingtip-mounted missiles fuselage nacelles located close to the wings, such as the and undenting fuel tanks, a generic fighter configuration, and a canard-configuration Beech Starship. This method allows the direct model of NASA-Ames' 12-ft Pressure Wind Tunnel. O.C. tailoring of the wing for close proximity of the nacelle through a definition of target pressure distributions. VSAERO has been used A91-12771# to analyze the entire configuration and generate aerodynamic loads. COMPUTATIONAL AERODYNAMIC SIMULATION EXPERIENCE Attention is given to the effects of canard flow on wing and nacelle E. BONNER, C. J. WOAN, and G. J. SOVA (Rockwell International flow. O.C. Corp., Los Angeles, CA) IN: Applied computational aerodynamics. Washington, DC, American Institute of Aeronautics and A91-12768# Astronautics, Inc., 1990, p. 753-776. refs APPLICATION OF COMPUTATIONAL FLUID DYNAMIC Copyright METHODS TO THE COMPONENT AERODYNAMIC DESIGN OF Advancements in CFD algorithms and computer hardware are THE V-22 OSPREY TILT ROTOR VEHICLE leading to substantial progress in numerical aircraft simulation and J. C. NARRAMORE (Bell Helicopter Textron, Inc., Fort Worth, TX) design methodologies. Recent aeroelastic and separated flow IN: Applied computational aerodynamics. Washington, DC, simulation results are indicative of emerging capabilities for

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additional design problems, although grid generation capability is when both the gust and the wake drift with the freestream, showing noted to remain an advancement-pacing factor in such simulation that for inviscid flow the Kutta condition is satisfied automatically efforts generally, and an altogether critical factor in complex as the gust pases the trailing edge by allowing the flow to continue geometry/viscous flow resolution. Early inputs from numerical as if the edge were not present. Author analyses into design programs entail a compatibility of overall grid size limits with conceptual development activity, in terms of both A91-12886# the time and computational resources available. O.C. FORMULATION OF THREE-DIMENSIONAL HODOGRAPH METHOD AND SEPARABLE SOLUTIONS FOR NONLINEAR A91-12772*# National Aeronautics and Space Administration. TRANSONIC FLOWS Ames Research Center, Moffett Field, CA. GABRIEL OYIBO (Polytechnic University, Farmingdale, NY) AIAA NAVIER-STOKES COMPUTATIONS ABOUT COMPLEX Journal (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1745-1750. CONFIGURATIONS INCLUDING A COMPLETE F-16 AIRCRAFT refs TERRY L. HOLST, JOLEN FLORES, NEAL M. CHADERJIAN Copyright (NASA, Ames Research Center, Moffett Field, CA), and UNVER The three-dimensional hodograph technique presently for- KAYNAK (Sterling Software, Inc., Palo Alto, CA) IN: Applied mulated transforms the full nonlinear potential transonic flow computational aerodynamics. Washington, DC, American Institute equation from physical space into an equivalent linear counterpart of Aeronautics and Astronautics, Inc., 1990, p. 777-815. refs in the hodograph plane. It is established that a mild constraint on Copyright the energy equation allows the separation of an aircraft wing's Transonic Navier-Stokes (TNS) code solutions gathered from nonlinear flow equations into a sectional and a spanwise the literature for three-dimensional geometries, including two component; the consequent 'three-dimensional' sectional equation different wings and a complete F-16A aircraft, are presently is eventually transformed onto the hodograph plane, where it discussed. The TNS codes use a zonal grid approach whose becomes linear. With one further, transformation into the number of zones vary from four to 54. The Euler equations are characteristic hodograph plane, it becomes possible to obtain the solved in zones away from no-slip surfaces, and the thin-layer nonlinear flowfield for a particular set of boundary conditions by TNS equations are solved in all zones immediately adjacent to solving a set of first-order characteristic equations. O.C. no-slip surfaces. In the case of 'corner' zones possessing no-slip boundary conditions on two different surfaces, a thin-layer formulation along both directions is employed. Employing these A91-12896# features, a zonal construction with the requisite set of boundary LOCALIZED LINEARIZATION METHOD FOR WINGS AT HIGH conditions can be devised for almost any application. O.C: ANGLE OF ATTACK LING-CHENG ZHAO (Northwestern Polytechnical University, Xian, People's Republic of China) and ZHENG-YIN YE AIAA Journal A91-12773# (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1820-1822. COMPUTATIONAL FLUID DYNAMICS DESIGN APPLICATIONS Copyright AT SUPERSONIC/HYPERSONIC SPEEDS A localized linearization method is devised which extends the H. ROBERT WELGE (Douglas Aircraft Co., Long Beach, CA) IN: use of the vortex lattice method (VLM) for the case of wings at Applied computational aerodynamics. Washington, DC, American high angle of attack and subcritical Mach number. The method Institute of Aeronautics and Astronautics, Inc., 1990, p. 817-838. preserves the VLM's advantages without involving the flowfield refs discretization, thereby remaining a surface boundary-element Copyright formulation. Illustrative delta and rectangular planform wings of Four cases are presented and discussed, in order of increasing small aspect ratio are calculated by means of this method for complexity, to illustrate the impact of advanced CFD methods on different Mach numbers. O.C. supersonic/hypersonic cruise aircraft design. The first case demonstrates the use of interactive computer graphics to visualize complex flowfields in conjunction with CFD methods; the second A91-12899# case treats sonic boom ground-level pressure signal prediction EULER SOLUTIONS FOR DELTA WINGS via CFD, with attention to hypersonic speeds and nonslender ANDREW B. WARDLAW, JR. and STEPHEN F. DAVIS (U.S. Navy, configurations which cannot be dealt with under linear assumptions. Naval Surface Warfare Center, Silver Spring, MD) AIAA Journal The third case is the design of a wing for Mach 2.2 cruise which (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1826-1829. Research incorporates laminar boundary-layer flow and increased supported by the U.S. Navy, refs leading-edge suction. Finally, attention is given to the complex Numerical experiments with Euler solutions for delta wings of internal flows of a Mach 5 engine inlet; these involve strong shocks varying thickness, with different meshes, varying levels of artificial and viscous interactions with high three-dimensionality. O.C. viscosity, and upwind as opposed to centrally differenced schemes, have yielded conflicting solution types for the same given problem. A91-12882# An examination is presently conducted of the conditions under GUST RESPONSE FOR FLAT-PLATE AIRFOILS AND THE which the separated solutions form. The evolution of the separated KUTTA CONDITION solution is traced, and the numerical factors influencing the inviscid R. K. AMIET (AMI, Wooster, OH) AIAA Journal (ISSN 0001-1452), solution type are characterized. . O.C. vol. 28, Oct. 1990, p. 1718-1727. refs Copyright A91-12903*# State Univ. of New York, Buffalo. The case of a flat plate airfoil encountering a gust in PREDICTION OF INVISCID STAGNATION PRESSURE LOSSES incompressible flow is analyzed, with the generalization that the IN SUPERSONIC INLET FLOWS shed vorticity in the wake as well as the incident gust can convert DAVID J. AZEVEDO, CHING SHI LIU, and WILLIAM J. RAE (New at arbitrary velocity relative to the freestream. Bound vorticity and York, State University, Buffalo) AIAA Journal (ISSN 0001-1452), loading are calculated. At high frequency the bound vorticity is vol. 28, Oct. 1990, p. 1834-1836. refs shown to be equivalent to an image of the incident gust, and (Contract NAGW-966) drifts with the gust, except near the leading edge, and if the gust Copyright velocity is unequal to the wake velocity, near the trailing edge. An effort is made to quantify the stagnation pressure losses When the wake moves relative to the freestream, there is a loading associated with shock-wave systems that may be present in' such on the wake which forces nonzero loading at the trailing edge. A high Mach number flows as those of scramjet hypersonic diffusers. recent vortex chopping model is shown to depend explicitly on If the shock-related contribution turns out to be much larger than this fictitioius wake loading, raising questions about the resulting that attributable to viscous effects, a designer could introduce noise prediction. A clarification in the application of the Kutta methods for the minimization of the shock system's scale; in condition is given for the case of high frequency gust disturbances particular, the size of the normal shock should be reduced. The

12 02 AERODYNAMICS angles presently treated may be approached during vehicle measurement of air power by a balance of an external mount maneuvering or other transients. • • O.C. type (six percent balance), a unit for eliminating the influence of the piping was manufactured by way of trial. Factors which influence A91-12904# the piping measurement of air power- are as follows: effect of air TRANSONIC COMPUTATIONS ON A NATURAL GRID pressure in the piping, influence by the twisting and warping of R. M. BARRON (Windsor, University, Canada) and R. K. NAEEM the piping as a result of a change in the stance of the model, AIAA Journal (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1836-1838. influence by the division of air power between the balance and Research supported by NSERC. refs ' the piping due rigidity of the piping itself, influence of thermal Copyright' elongation and contraction of the piping, influence of the flow of The natural grid system generated by Barren and Naeem's compressed air in the piping. To minimize these influences, use (1989) von Mises'transformation for the finite-difference-solution was made of a combination of Zimbal bellow, high-pressure rubber of transonic full-potential flows yields a 'finest grid, for the case of hose, and apherical joint was made for eliminating the influence a NACA 0012 airfoil at Mach 0.8, which provides about 30 surface of the piping on an experimental basis which was checked for grid points. This leads to problems in near-surface calculations in effect by conducting a wind-tunnel test with and without introduction the supersonic region. "Attention is presently given to a simple of air.-' ' NASDA scheme precluding this grid-refinement problem. O.C. N91-10006 .Georgia Inst. of Tech., Atlanta. A91-12911 APPLICATION OF A STATE-SPACE WAKE MODEL TO PRACTICAL AERODYNAMICS AND FLIGHT DYNAMICS OF ELASTIC BLADE FLAPPING IN HOVER Ph.D. Thesis YAK-52 AND YAK-55 AIRCRAFT [PRAKTICHESKAIA AY SU 1989 -1.45 p AERODINAMIKA I DINAMIKA POLETA SAMOLETOV IAK-52 I Avail: Univ. Microfilms Order No. DA9014871 IAK-55] .A finite-state-inflow, model is developed that models the ANATOLM E. KOROVIN and IURII F. NOVIKOV Moscow, three-dimensional rotor inflow in hover, axial flight, or forward flight. Izdatel'sWo DOSAAF SSSR,'.1989, 360 p. In Russian. The basis of the model is an acceleration potential with a skewed Copyright ,,-.'.' cylindrical wake. The scope and objectives of the present research The principal aerodynamic, performance, and handling revolve around the development of this theoretical basis into a characteristics of Yak-52 and Yak-55 aircraft are reviewed in a useful research and design tool for hover and axial flight. First, systematic manner, with emphasis on the underlying physical we establish the harmonic and radial convergence characteristics principles. The discussion covers the geometry of the aircraft, of the model. One-bladed and four-bladed rotors are used in this aerodynamic characteristics of the wing and the airframe, analysis. Second, this model is coupled with elastic-blade flap characterization-of the power plant and propeller aerodynamics, equations in hover and also in axial flight in order to determine its and climb and cruising flight characteristics. 'Attention is also given effect on aerodynamic damping. Third, the role of periodic to aircraft stability,'takeoff and landing characteristics, and coefficients in the dynamic response is investigated. A multi-blade maneuverability. V.L.- coordinate transformation technique is used to transform the flap equations from the rotating to the nonrotating system. Similarly, A91-12913 . ' the induced flow can be written in either the rotating or the JETS AND LIFTING SURFACES: COMPUTER SIMULATION nonrotating system. The effect of periodic coefficients is dependent [STRUI I NESUSHCHIE POVERKHNOSTI: MODELIROVANIE upon which set of blade equations is coupled with which set of NA EVM] inflow equations. Fourth, we related the generalized forces in the VLADIMIR I. BABKIN, SERGEI M. BELOTSERKOVSKII, VALERII inflow equations to the generalized .forces already being used for V. GULIAEV, and ALEKSANDR V. DVORAK Moscow/ Izdatel'stvo structural response by constructing intermediate transformation Nauka, 1989, 208 p. In Russian, refs matrices. Results obtained from these tasks show that the present Copyright model - converges with 3 shape functions, per harmonic and has The interaction of jets with lifting surfaces and obstacles is high computational efficiency as compared to •.unsteady investigated through systematic computer simulations using the vortex-filament models. More importantly, results indicate that discrete vortex method.' The, discussion covers the general unsteady .inflow is an important physical phenomenon that changes properties of jet flows and problems with liquid boundaries; the the qualitative nature of rotor dynamics in hover and in axial principles of the discrete vortex method; and application of the flight. . - - Dissert. Abstr. discrete vortex method to thin jet problems and stationary problems for jets of finite thickness. Attention is also given to the aerodynamic N91-10007*# National Aeronautics and Space Administration. characteristics of .wings with allowance for interference with the Ames Research Center, Moffett Field, CA. operating power plant; aerodynmic characteristics.of an airfoil in TRANSONIC FLOW ANALYSIS FOR ROTORS. PART 3: the path of a jet flow; and two- and three-dimensional jets of an THREE-DIMENSIONAL, QUASI-STEADY, EULER ideal liquid. - ' • . V.L CALCULATION I-CHUNG CHANG Jun. 1990 23 p N91-10003 National Aerospace Lab., Tokyo (Japan). (NASA-TP-2375; A-86374-PT-3; NAS 1.60:2375) Avail: NTIS CHARACTERISTICS OF PIPING INTERFERENCE ELIMINATION HC/MF A03 "CSCL 01A UNIT USED IN THE HIGH-SPEED WIND TUNNEL TEST OF A new method is presented for calculating the quasi-steady ASUKA SEVEN PERCENT SEMI-BORN PROTOTYPE [ASUKA transonic flow over a lifting or non-lifting rotor blade in both hover NANA PASENTO HANSETSU MOKEI NO KOUSOKU FUUDOU and forward flight by using Euler equations. The approach is to SHIKEN Nl MOCHIITAHAIKAN KANSHOU JOKYO SOUCHI NO solve Euler equations in a rotor-fixed frame of reference using a TOKUSEI Nl TSUITE] finite volume'method. A computer program was developed and NOBUYUKI HOSOE, TOSHIO KARASAWA, KEISUKE ASAI, was then verified by comparison with wind-tunnel data. In all cases SYOUJI SUENAGA, YO KOIKE, HIROKAZU SUZUKI, MASAYOSHI considered, good agreement was found with published experimental NAKAMURA, and SUSUMU MITSUBORI Jun. 1988 17 p In data. ' Author JAPANESE (NAL-TM-588; ISSN-0452-2982; JTN-90-80015) Avail: NTIS HC/MF A03 ... , N91-10008# Los Alamos National Lab., NM. In the high-speed aerodynamic test using a seven percent OPTIMUM HYPERSONIC AIRFOIL WITH POWER LAW SHOCK semiborne model for the low-noise STOL test aircraft, two TPS WAVES (Turbine Powered Simulators) were mounted for use in order to B. A. WAGNER 1990 10 p Presented at the 1st International simulate the drive of an actual aircraft. In order to suppress the Hypersonic Waverider Symposium, College Park, MD, Oct. 1990 influence of the piping for supplying compressed air to the TPS (Contract W-7405-ENG-36)

13 02 AERODYNAMICS

(DE90-014903; LA-UR-90-2437; CONF-9010154-1) Avail: NTIS infinity) = 7.0 and Reynolds number of 4.4 x 10(exp 6) at angles HC/MF A03 of attack alpha = 0, 10, and 20 deg. Numerical results are The flow field over a class of 2-D lifting surfaces is examined compared with experimental heat transfer measurements by the from the viewpoint of inviscid, hypersonic small disturbance theory infrared system developed in the hypersonic wind tunnel (HWT) (HSDT). It is well known that a flow field in which the shock at NAL. Author shape S(x) is similar to the body shape F(x) is only possible for F(x) = x sup k and the freestream Mach number M sub infinity N91-10013*# National Aeronautics and Space < Administration. = infinity. This self-similar flow has been studied for several Ames Research Center, Moffett Field, CA. decades as it represents one of the few existing exact solutions WAKE COUPLING TO FULL POTENTIAL ROTOR ANALYSIS of the equations of HSDT. Detailed discussions are found for CODE example in papers by Cole, Mirels, Chernyi and Gersten and Nicolai FRANCISCO J. TORRES, I-CHUNG CHANG, and BYUNG K. OH but they are limited to convex body shapes, that is, k less than or (Boeing Computer Services Co., Philadelphia, PA.) Aug. 1990 = 1. The only study of concave body shapes was attempted by 23 p Sullivan where only special cases were considered. The method (NASA-TM-102805; A-90117; NAS 1.15:102805) Avail: NTIS used here shows that similarity also exists for concave shapes HC/MF A03 CSCL01A and a complete solution of the flow field for any k greater than The wake information from a helicopter forward flight code is 2/3 is given. The effect of varying k on C sub L sup 3/2 C sub D coupled with two transonic potential rotor codes. The induced is then determined and an optimum shape is found. Furthermore, velocities for the near-, mid-, and far-wake geometries are extracted a wider class of lifting surfaces is constructed using the streamlines from a nonlinear rigid wake of a standard performance and analysis of the basic flow field and analysed with respect to the effect on code. These, together with the corresponding inflow angles, C sub L sup 3/2 C sub D. DOE computation points, and azimuth angles, are then incorporated into the transonic potential codes. The coupled codes can then N91-10010*# Institute for Computer Applications in Science provide an improved prediction of rotor blade loading at transonic and Engineering, Hampton, VA. speeds. " Author TURBULENT FLOW CALCULATIONS USING UNSTRUCTURED AND ADAPTIVE MESHES Final Report N91-10014*# National Aeronautics and Space Administration. DIMITRI J. MAVRIPLIS Sep. 1990 32 p Submitted for Ames Research Center, Moffett Field, CA. publication EULER AND POTENTIAL EXPERIMENT/CFD CORRELATIONS (Contract NAS1-18605) FOR A TRANSPORT AND TWO DELTA-WING (NASA-CR-182102; NAS 1.26:182102; ICASE-90-61) Avail: NTIS CONFIGURATIONS Technical Memorandum HC/MF A03 CSCL 01A R. M. HICKS, S. E. CLIFF, J. E. MELTON, R. G. LANGHI, A. M. A method of efficiently computing turbulent compressible flow GOODSELL, D. D. ROBERTSON, and S. A. MOYER Aug. 1990 over complex two dimensional configurations is presented. The 180 p Original contains color illustrations method makes use of fully unstructured meshes throughout the (NASA-TM-102208; A-89197; NAS 1.15:102208) Avail: NTIS entire flow-field, thus enabling the treatment of arbitrarily complex HC/MF A09; 2 functional color pages CSCL 01A geometries and the use of adaptive meshing techniques throughout A selection of successes and failures of Computational Fluid both viscous and inviscid regions of flow-field. Mesh generation is Dynamics (CFD) is discussed. Experiment/CFD correlations based on a locally mapped Delaunay technique in order to generate involving full potential and Euler computations of the aerodynamic unstructured meshes with highly-stretched elements in the viscous characteristics of four commercial transport wings and two low regions. The flow equations are discretized using a finite element aspect ratio, delta wing configurations are shown. The examples Navier-Stokes solver, and rapid convergence to steady-state is consist of experiment/CFD comparisons for aerodynamic forces, achieved using an unstructured multigrid algorithm. Turbulence moments, and pressures. Navier-Stokes equations are not modeling is performed using an inexpensive algebraic model, considered. " Author implemented for use on unstructured and adaptive meshes. Compressible turbulent flow solutions about multiple-element airfoil N91-10015*# National Aeronautics and Space Administration. geometries are computed and compared with experimental data. Ames Research Center, Moffett Field, CA. Author APPLICATION OF CFD TO SONIC BOOM NEAR AND MID FLOW-FIELD PREDICTION N91-10011# National Aerospace Lab., Tokyo. (Japan). SAMSON H. CHEUNG (MCAT Inst., San Jose, CA.), THOMAS A. Aerodynamics Div. EDWARDS, and SCOTT L. LAWRENCE Aug. 1990 13 p NUMERICAL SIMULATION OF HYPERSONIC FLOW AROUND Presented at the 13th AIAA Aeroacoustic Conference, Tallahassee, A SPACE PLANE. PART 3: ANALYSIS OF FL, 22-24 Oct. 1990 AEROTHERMODYNAMIC HEATING (NASA-TM-102867; A-90246; NAS 1.15:102867) Avail: NTIS YUKIMITSU YAMAMOTO, HARUHIKO ARAKAWA, and RYUJI HC/MF A03 CSCL 01A YOSHIDA (Mitsubishi Heavy-Industries Ltd., Tokyo, Japan ) Aug. A 3-D parabolized Navier-Stokes (PNS) code was used to 1989 30 p calculate the supersonic overpressures from three different (NAL-TR-1027T; ISSN-0389-4010) Avail: NTIS HC/MF A03 geometries at near- and mid-flow fields. Wind tunnel data is used The evaluation of hypersonic aerothermodynamic heating along for code validation. Comparison of the computed results with the wing leading edge of the space plane is very important for different grid refinements is shown. It is observed that a large preliminary aerothermal structural design, because severe local number of grid points is needed to resolve the tail shock/expansion peak heating is caused there by recompression or shock fan interaction. Therefore, an adaptive grid approach is employed impingement at low angles of attack. In the present numerical to calculate the flow field. The agreement between the numerical simulation, this local peak heating has been analyzed for the three results and the wind tunnel data confirms that computational fluid space plane configurations proposed by the National Aerospace dynamics can be applied to the problem of sonic boom Laboratory (NAL). The proposed models have different wing leading prediction. Author edge sweep angles, and effects of the sweep angles on local peak heating were investigated in detail. In addition, two of the N91-10016# Institut Franco-Allemand de Recherches, Saint-Louis proposed configurations have tip fin controllers, and their heating (France). characteristics were also investigated. As the numerical approach, MODELING BLADE/VORTEX INTERACTIONS a flux split upwind TVD scheme was adopted by using thin layer [MODELISATION D'INTERACTIONS PALE/TOURBILLON] Navier-Stokes equations in a finite volume formulation. An implicit .P. GNEMMI, JACQUES HAERTIG, and CH. JOHE 24 May 1989 approximately factored ADI method has been used as the solution 43 p In FRENCH Original contains color illustrations algorithm. Numerical computations were carried out at M(sub (ISL-R-107/89; ETN-90-97569) Avail: NTIS HC/MF A03 ,

14 02 AERODYNAMICS

The development of an electron emitter based on a shallow 1990 Previously announced in IAA as A90-29376 pn-junction made of gallium arsenide is reported. Desirable (NASA-TM-102733; NAS 1.15:102733; AIAA-90-1032) Avail: properties of an electron gun are outlined and the attractive aspects NTIS HC/MF A03 CSCL 01A and specific possibilities of the Avalanche Electron Emitting Diode Modifications to the CFL3D three dimensional unsteady (AEED) are discussed. Fabrication, including the self-made Euler/Navier-Stokes code for the aeroelastic analysis of wings gold-germanium sputter and gold evaporation equipment, is are described. The modifications involve including a deforming explained. Ultrahigh vacuum measurement and cleaning setup and mesh capability which can move the mesh to continuously conform properties of the low energy argon ion sputter source and method to the instantaneous shape of the aeroelastically deforming wing, of measurement are presented. Experimental results and theoretical and including the structural equations of motion for their calculations are given. The Ga AEED device is concluded to be simultaneous time-integration with the governing flow equations. of not good enough quality for fair comparison to the silicon Calculations were performed using the Euler equations to verify AEED. ESA the modifications to the code and as a first step toward aeroelastic analysis using the Navier-Stokes equations. Results are presented for the NACA 0012 airfoil and a 45 deg sweptback wing to N91-10018# Institut Franco-Allemand de Recherches, Saint-Louis demonstrate applications of CFL3D for generalized force (France). computations and aeroelastic analysis. Comparisons are made with ROTOR LOADS COMPUTATION USING SINGULARITY 'published Euler results for the NACA 0012 airfoil and with METHODS AND APPLICATION TO THE NOISE PREDICTION experimental flutter data for the 45 deg sweptback wing to assess MARTIN SCHAFFAR and JACQUES HAERTIG 1990 13 p the accuracy of the present capability. These comparisons show Presented at 3rd International Congress of Fluid Mechanics, Cairo, good agreement and, thus, the CFL3D code may be used with Egypt, 2-4 Jan. 1990 (ISL-PU-301/90; ETN-90-97577) Avail: NTIS HC/MF A03 confidence for aeroelastic analysis of wings. Author In the two dimensional space, two singularity methods are described and applied to the profile/vortex interaction. The results N91-10022*# Institute for Computer Applications in Science show a good agreement with experiments in a water tunnel. In and Engineering, Hampton, VA. the three dimensional space, the vortex lattice method, with a VORTEX INSTABILITIES IN 3D BOUNDARY LAYERS: THE local conformal mapping, is described and applied in order to RELATIONSHIP BETWEEN GOERTLER AND CROSSFLOW predict the aerodynamic loads on a thick two bladed rotor. The VORTICES Final Report pressure coefficients obtained for the thick rotor are fed into an ANDREW BASSOM and PHILIP HALL (Exeter Univ., England ) acoustic code which is based on the Ffowcs-Williams-Hawkings Oct. 1990 76 p Submitted for publication Sponsored in part by equation. The results obtained with this method show the Science Research Council and AF importance of the rotor and flight parameters. They are compared (Contract NAS1-18605) with results found for a two bladed rotor in hovering and advancing (NASA-CR-187456; NAS 1.26:187456; ICASE-90-72) Avail: NTIS flight. The comparison shows a good agreement and shows that HC/MF A05 CSCL 01A the cut off length used to smooth the singularity of the Biot and The inviscid and viscous stability problems are addressed for Savart law must be chosen carefully. ESA a boundary layer which can support both Goertler and crossflow vortices. The change in structure of Goertler vortices is found when the parameter representing the degree of three-dimensionality N91-10019*# Iowa State Univ. of Science and Technology, of the basic boundary layer flow under consideration is increased. Ames. Engineering Research Inst. It is shown that crossflow vortices emerge naturally as this NUMERICAL COMPUTATION OF VISCOUS FLOW ABOUT parameters increased and ultimately become the only possible UNCONVENTIONAL AIRFOIL SHAPES Final Report vortex instability of the flow. It is shown conclusively that at S. AHMED and J. C. TANNEHILL Oct. 1990 82 p sufficiently large values of the crossflow there are no unstable (Contract NAG 1-645; ERI PROJ. 1874) Goertler vortices present in a boundary layer which, in the zero (NASA-CR-187343; MAS 1.26:187343; ISU-ERI-AMES-91-110; crossflow case, is centrifugally unstable. The results suggest that CFD-24) Avail: NTIS HC/MF A05 CSCL 01A in many practical applications Goertler vortices cannot be a cause A new two-dimensional computer code was developed to of transition because they are destroyed by the 3-D nature of the analyze the viscous flow around unconventional airfoils at various basic state. In swept wing flows the Goertler mechanism is probably Mach numbers and angles of attack. The Navier-Stokes equations not present for typical angles of sweep of about 20 degrees. are solved using an implicit, upwind, finite-volume scheme. Both Some discussion of the receptivity problem for vortex instabilities laminar and turbulent flows can be computed. A new nonequilibrium in weakly 3-D boundary layers is given; it is shown that inviscid turbulence closure model was developed for computing turbulent modes have a coupling coefficient marginally smaller than those flows. This two-layer eddy viscosity model was motivated by the of the fastest growing viscous modes discussed recently by Denier, success of the Johnson-King model in separated flow regions. Hall, and Seddougui (1990). However the fact that the growth The influence of history effects are described by an ordinary rates of the inviscid modes are the largest in most situations differential equation developed from the turbulent kinetic energy means that they are probably the most likely source of transition. equation. The performance of the present code was evaluated by Author solving the flow around three airfoils using the Reynolds time-averaged Navier-Stokes equations. Excellent results were N91-10023# Helsinki Univ. Technology, Otaniemi (Finland). obtained for both attached and separated flows about the NACA Aerodynamics Lab. 0012 airfoil, the RAE 2822 airfoil, and the Integrated Technology THREE-DIMENSIONAL VISCOUS/INVISCID COUPLING IN A 153W airfoil. Based on the comparison of the numerical solutions SUBSONIC FLOW with the available experimental data, it is concluded that the present ZIQUIANG ZHU, SEPPO LAINE, and ESA SALMINEN 1990 code in conjunction with the new nonequilibrium turbulence model 27 p gives excellent results. Author (REPT-B-24; ISBN-951-22-0248-4; ISSN-0358-2620) Avail: NTIS HC/MF A03 N91-10020*# National Aeronautics and Space Administration. Coupling MBB low-order panel code for three-dimensional Langley Research Center, Hampton, VA. compressible subsonic potential flow and Stock's boundary layer AEROELASTIC ANALYSIS OF WINGS USING THE EULER method for three-dimensional compressible laminar or turbulent EQUATIONS WITH A DEFORMING MESH flow is proposed. The resulting computer program is valid only for BRIAN A. ROBINSON, JOHN T. BATINA, and HENRY T. Y. YANG simple wings. The panel model may also contain body-like (Purdue Univ., West Lafayette, IN.) Nov. 1990 11 p Presented components, however. The friction drag of the wing is obtained at the AIAA/ASME/ASCE/AHS/ASC 31 st Structures, Structural as a result of the computations. The effect of the displacement Dynamics, and Materials Conference, Long Beach, CA, 2-4 Apr. thickness on the potential solution is simulated iteratively using a

15 02 AERODYNAMICS surface transpiration model. A comparison with experimental results N91-10027# Deutsche Forschungsanstalt fuer Luft- und shows that the method predicts the trend of the boundary layer Raumfahrt; Cologne (Germany, F.R.). Hauptabt. Windkanaele. effect correctly, although underestimates its magnitude. Author WIND TUNNEL INVESTIGATIONS OF THE APPEARANCE OF SHOCKS IN THE WINDWARD REGION OF BODIES WITH CIRCULAR CROSS SECTION AT ANGLE OF ATTACK HELMUT ESCH 15.Mar. 1990 . 63 p In GERMAN; ENGLISH N91-10024# Helsinki Univ. Technology, Otaniemi (Finland)! summary Report will also be announced as translation Aerodynamics Lab. CALCULATION OF THREE-DIMENSIONAL VISCOUS/INVISCID (ESA-TT-1226) - • INTERACTION IN SUBSONIC FLOW , , (DLR-FB-90-15; ISSN-017.1-1342; ETN-90-97629; AD-B147243L) Avail: NTIS HC/MF A04;.DLR, VB-PL-DO, Postfach 90 60 58, ZIQIANG ZHU, SEPPO LAINE, and ESA SALMINEN 1990 5000 Cologne, Fed. Republic • ' 36 p . ' (REPT-B-25; ISBN-951 -22-0329-4; ISSN-0358-2620) Avail: NTIS Conditions causing the• primary embedded shock to deviate into the windward region of a circular cylinder at angle of attack HC/MF A03' ...... '' • were investigated by use of Schlieren photos, oil flow pictures, The development of a method to obtain the subsonic viscous flow solution for three-dimensional geometries, using the and surface pressure distribution measurements. The critical range viscous/inviscid interaction technique, is described. A 3-D panel of crossflow Mach number greater than or equal to 0.3 • and less method (MBB) for calculating three-dimensional inviscid flow is than or equal to 0.6 was covered at free stream Mach numbers coupled iteratively with a two-dimensional, inverse integral boundary between Ma = 1.25 and 2.5. Reynolds numbers based on body layer method, in which small .separation bubbles can be handled. diameter varied between 3 x 10(exp 5) and 1.3 x 10(exp 6). Cross flow is ignored in the boundary layer calculations,. which - • . . ESA are carried out along chordwise strips of the wing. The 'surface transpiration'approach is used .in the coupling. Numerical results, N91-10839*# National Aeronautics and Space Administration. indicate that good agreement with experimental data can be Ames Research Center, Moffett Field, CA. obtained up to an angle of attack near maximum lift. Author NASA COMPUTATIONAL FLUID DYNAMICS CONFERENCE. VOLUME 1: SESSIONS 1-6 Sep. 1989 475 p . Conference held at Moffett Field, CA, 7-9 Mar. 1989 Original contains color illustrations N91-10025# Helsinki Univ. Technology, Otaniemi (Finland). (NASA-CP-10038-VOL-1; A-89160-VOL-1; NAS Aerodynamics Lab. • . • 1.55:10038-VOL-1) Avail: NTIS HC/MF A20; 25 functional color', EVALUATION OF THE ZONA51D PROGRAM pages CSCL 01/1 • • ;.: KARI FtENKO 1990 43 p Presentations given at the NASA Computational Fluid Dynamics (REPT-B-28; ISBN-951-22-0398-7; ISSN-0358-2620) Avail: NTIS (CFD) Conference held at .the NASA Ames Research Center, HC/MF A03 • • , . • Moffett Field, California, March 7-9, 1989 are given. Topics covered ZONA51D is a computer program which determines the include research facility overviews of CFD research and unsteady aerodynamic forces acting on a lifting surface system in applications, validation programs, direct simulation of compressible supersonic flow. The program is based on the harmonic gradient turbulence, turbulence modeling, advances in Runge-Kutta formulation. The ZONA51D code is installed into the IBM schemes for solving 3-D Navier-Stokes equations, grid generation 3090-180E VF computer at the Helsinki University of Technology. and invicid flow computation around aircraft geometries, numerical Modifications are made to the code to ease its operation and the simulation of rotorcraft, and viscous'drag prediction for rotor post-processing of the results.. The proper operation of the code blades. • • ' • . • • and the accuracy of the results is verified by running several test cases and comparing the results to analytical solutions, N91-10840*# National Aeronautics' and Space Administration. experimental results, and other representative computations. Ames Research Center, Moffett Field, CA. ' • • ' Author COMPUTATIONAL FLUID DYNAMICS PROGRAM AT NASA AMES RESEARCH CENTER ! TERRY L. HOLST In its NASA Computational Fluid Dynamics N91-10026# ' Deutsche Forschungsanstalt fuer 'Luft- und Conference. Volume 1: Sessions 1-6 p 3-34 'Sep. 1989 •' Raumfahrt, Goettingen (Germany, F.R.). Abt. fuer Numerische Avail: NTIS'HC/MF A20; 25 functional color pages CSCL 01 /I Stroemungsmechanik. The Computational' Fluid Dynamics (CFD) Program'at NASA A CONTRIBUTION TO THE NUMERICAL SOLUTION OF Ames Research Center is reviewed and discussed. The technical TRANSONIC FLOW AROUND A DELTA WING BY SOLVING elements of the CFD Program are listed and briefly discussed. NAVIER-STOKES EQUATIONS Ph.D. Thesis - Karlsruhe Univ. These elements include algorithm research, research and pilot ACHIM HILGENSTOCK Dec. 1989 101 p In GERMAN; code development;-scientific visualization, advanced surface ENGLISH summary Report will also be announced as translation' representation, volume grid generation, and numerical optimization. (ESA-TT-1225) Original contains color illustrations - : Next, the discipline of CFD is briefly djscussed and related-to (DLR-FB-90-13;'ISSN-0171-1342; ETN-90-97628; AD-B146522L)1 ••> other areas of research, at NASA Ames including experimental Avail: NTIS HC/MF A06; DLR, VB-OL-DO, Postfach 90 60 58; fluid dynamics, computer science research, computational 5000 Cologne, Fed. Republic chemistry, and numerical aerodynamic simulation. These areas The turbulent flow around a delta wing at incidence-is simulated combine with CFD to form a larger area of research, which might numerically using a finite volume Navier-Stokes method. The collectively be called computational technology. The ultimate goal methods for selecting the optimal grid and-the grid generation are of computational technology research at NASA Ames is to increase outlined. The numerical simulation makes use of a simple algebraic the physical understanding of the wbrld-in which we live, solve turbulence'model. Using" a sharp leading edge delta wing, the problems of national importance, and increase' the technical influence of grid refinement is investigated. The realistic wing body capabilities of the aerospace community. Next, the major programs configuration with round leading edge is used to discuss the at NASA Ames that either use CFD technology or perform research influence of the position of the transition line. Experimental and in CFD. are listed and discussed. Briefly, this list ' includes numerical data are compared to validate the numerical method. turbulent/transition physics and modeling, 'high-speed real gas The topological structure of the flow is interpreted. An explanation flows, interdisciplinary research, turbomachinery demonstration is given for the low particle density area close to the primary computations, complete aircraft aerodynamics, rotorcraft ap- vortex as it is visualized by laser light sheet technique. The plications,'powered lift flows, high alpha flows, multiple body distribution of Mach number, velocity, temperature, pressure and aerodynamics, and incompressible flow applications. Some of the total pressure is discussed in connection with' 'the' streamlines for individual problems actively being worked in each of these areas the primary vortex. • • 'ESA is listed to help define the breadth or extent of CFD'involvement

16 02 AERODYNAMICS

in each of these major programs. State-of-the-art examples of A thin-layer Navier-Stokes has been developed for solving hig.i various CFD applications are presented to highlight most of these Reynolds number, turbulent flows past aircraft components under areas. The main emphasis of this portion of the presentation is transonic flow conditions. The computer code has been validated on examples which will not otherwise be treated at this conference through data comparisons for flow past isolated wings, wing-body by the individual presentations. Finally, a list of principal current configurations, prolate spheroids and wings mounted inside limitations and expected future directions is given. Author wind-tunnels. The basic code employs an explicit Runge-Kutta time-stepping scheme to obtain steady state solution to the N91-10841*# National Aeronautics and Space Administration. unsteady governing equations. Significant gain in the efficiency of Langley Research Center, Hampton, VA. the code has been obtained by implementing a multigrid COMPUTATIONAL FLUID DYNAMICS RESEARCH AND acceleration technique to achieve steady-state solutions. The APPLICATIONS AT NASA LANGLEY RESEARCH CENTER improved efficiency of the code has made it feasible to conduct JERRY C. SOUTH, JR. In NASA, Ames Research Center, NASA grid-refinement and turbulence model studies in a reasonable Computational Fluid Dynamics Conference. Volume 1: Sessions amount of computer time. The non-equilibrium turbulence model 1-6 p 35-47 Sep. 1989 of Johnson and King has been extended to three-dimensional Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 flows and excellent agreement with pressure data has been Information on computational fluid dynamics (CFD) research obtained for transonic separated flow over a transport type of and applications carried out at the NASA Langley Research Center wing. Author is given in viewgraph form. The Langley CFD strategy, the five-year plan in CFD and flow physics, 3-block grid topology, -the effect of N91-10855*# National Aeronautics and Space Administration. a patching algorithm, F-18 surface flow, entropy and vorticity effects Ames Research Center, Moffett Field, CA. that improve accuracy of unsteady transonic small disturbance CFD FOR APPLICATIONS TO AIRCRAFT AEROELASTICITY theory, and the effects of reduced frequency on first harmonic GURU P. GURUSWAMY In its NASA Computational Fluid components of unsteady pressures due to airfoil pitching are among Dynamics Conference. Volume 1: Sessions 1-6 p 271-286 Sep. the topics covered. Author 1989 Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 N91-10850*# National Aeronautics and Space Administration. Strong interactions of structures and fluids are common in Ames Research Center, Moffett Field, CA. many engineering environments. Such interactions can give rise MORE ACCURATE PREDICTIONS WITH TRANSONIC to physically important phenomena such as those occurring for NAVIER-STOKES METHODS THROUGH IMPROVED aircraft due to aeroelasticity. Aeroelasticity can significantly TURBULENCE MODELING influence the safe performance of aircraft. At present exact DENNIS A. JOHNSON In its NASA Computational Fluid Dynamics methods are available for making aeroelastic computations when Conference. Volume 1: Sessions 1-6 p 193-204 Sep. 1989 flows are in either the linear subsonic or supersonic range. Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 However, for complex flows containing shock waves, vortices and Significant improvements in predictive accuracies for off-design flow separations, computational methods are still under conditions are achievable through better turbulence modeling; and, development. Several phenomena that can be dangerous and limit without necessarily adding any significant complication to the the performance of an aircraft occur due to the interaction of numerics. One well established fact about turbulence is it is slow these complex flows with flexible aircraft components such as to respond to changes in the mean strain field. With the 'equilibrium' wings. For example, aircraft with highly swept wings experience algebraic turbulence models no attempt is made to model this vortex induced aeroelastic oscillations. Correct understanding of characteristic and as a consequence these turbulence models these complex aeroelastic phenomena requires direct coupling of exaggerate the turbulent boundary layer's ability to produce fluids and structural equations. Here, a summary is presented of turbulent Reynolds shear stresses in regions of adverse pressure the development of such coupled methods and applications to gradient. As a consequence, too little momentum loss within the aeroelasticity since about 1978 to present. The successful use'of boundary layer is predicted in the region of the shock wave and the transonic small perturbation theory (TSP) coupled with along the aft part of the airfoil where the surface pressure structures is discussed. This served as a major stepping stone for undergoes further increases. Recently, a 'nonequilibrium' algebraic the current stage of aeroelasticity using computational fluid turbulence model was formulated which attempts to capture this dynamics. The need for the use of more exact Euler/Navier-Stokes important characteristic of turbulence. This 'nonequilibrium' (ENS) equations for aeroelastic problems is explained. The current algebraic model employs an ordinary differential equation to model development of unsteady aerodynamic and aeroelastic procedures the slow response of the turbulence to changes in local flow based on the ENS equations are discussed. Aeroelastic results conditions. In its original form, there was some question as to computed using both TSP and ENS equations are discussed. whether this 'nonequilibrium' model performed as well as the Author 'equilibrium' models for weak interaction cases. However, this turbulence model has since been further improved wherein it now N91-10856*# National Aeronautics and Space Administration. appears that this turbulence model performs at least as well as Langley Research Center, Hampton, VA. the 'equilibrium' models for weak interaction cases and for strong APPLICATION OF UNSTRUCTURED GRID METHODS TO interaction cases represents a very significant improvement. The STEADY AND UNSTEADY AERODYNAMIC PROBLEMS performance of this turbulence model relative to popular JOHN T. BATINA In NASA, Ames Research Center, NASA 'equilibrium' models is illustrated for three airfoil test cases of the Computational Fluid Dynamics Conference. Volume 1: Sessions 1987 AIAA Viscous Transonic Airfoil Workshop, Reno, Nevada. A 1-6 p 287-308 Sep. 1989 Original contains color illustrations form of this 'nonequilibrium' turbulence model is currently being Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 applied to wing flows for which similar improvements in predictive The purpose is to describe the development of unstructured accuracy are being realized. Author grid methods which have several advantages when compared to methods which make use of structured grids. Unstructured grids, N91-10851*# National Aeronautics and Space Administration. for example, easily allow the treatment of complex geometries, Langley Research Center, Hampton, VA. allow for general mesh movement for realistic motions and RECENT ADVANCES IN RUNGE-KUTTA SCHEMES FOR structural deformations of complete aircraft configurations which SOLVING 3-D NAVIER-STOKES EQUATIONS is important for aeroelastic analysis, and enable adaptive mesh' VEER N. VATSA, BRUCE W. WEDAN, and RIDHA ABID In refinement to more accurately resolve the physics of the flow. NASA, Ames Research Center, NASA Computational Fluid Steady Euler calculations for a supersonic fighter configuration to Dynamics Conference. Volume 1: Sessions 1-6 p 207-221 Sep. demonstrate the complex geometry capability; unsteady Euler 1989 Original contains color illustrations calculations for the supersonic fighter undergoing harmonic Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 oscillations in a complete-vehicle bending mode to demonstrate

17 02 AERODYNAMICS the general mesh movement capability; and vortex-dominated all aircraft surfaces. Zonal grids extend inside the F-16A inlet and conical-flow calculations for highly-swept delta wings to up to the compressor face while power on conditions are modeled demonstrate the adaptive mesh refinement capability are discussed. by employing a zonal grid extending from the exhaust nozzle to The basic solution algorithm is a multi-stage Runge-Kutta the far field. Computations are compared with existing experimental time-stepping scheme with a finite-volume spatial discretization data and are in fair agreement. Computations for the F-16A in based on an unstructured grid of triangles in 2D or tetrahedra in side slip are also presented. Author 3D. The moving mesh capability is a general procedure which models each edge of each triangle (2D) or tetrahedra (3D) with a N91-10859*# National Aeronautics and Space Administration. spring. The resulting static equilibrium equations which result from Ames Research Center, Moffett Field, CA. a summation of forces are then used to move the mesh to allow NUMERICAL SIMULATION OF F-18 FUSELAGE FOREBODY it to continuously conform to the instantaneous position or shape FLOWS AT HIGH ANGLES OF ATTACK of the aircraft. The adaptive mesh refinement procedure enriches LEWIS B. SCHIFF, RUSSELL M. CUMMINGS, REESE L. the unstructured mesh locally to more accurately resolve the SORENSON, and YEHIA M. RIZK (Sterling Software, Palo Alto, vortical flow features. These capabilities are described in detail CA.) In its NASA Computational Fluid Dynamics Conference. along with representative results which demonstrate several Volume 1: Sessions 1 -6 p 345-359 Sep. 1989 advantages of unstructured grid methods. The applicability of the Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 unstructured grid methodology to steady and unsteady aerodynamic Fine-grid Navier-Stokes solutions were obtained for flow over problems and directions for future work are discussed. Author the fuselage forebody and wing leading edge extension of the F/A-18 High Alpha Research Vehicle at large incidence. The N91-10857*# National Aeronautics and Space Administration. resulting flows are complex, and exhibit cross flow separation from Langley Research Center, Hampton, VA. the sides of the forebody and from the leading edge extension. A GRID GENERATION AND INVISCID FLOW COMPUTATION well-defined vortex pattern is observed in the leeward-side flow. ABOUT AIRCRAFT GEOMETRIES Results obtained for laminar flow show good agreement with flow ROBERT E. SMITH In NASA, Ames Research Center, NASA visualizations obtained in ground-based experiments. Further, Computational Fluid Dynamics Conference. Volume 1: Sessions turbulent flows computed at high Reynolds-number flight-test 1-6 p 311-326 Sep. 1989 Original contains color illustrations conditions show good agreement with surface and off-surface Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 visualizations obtained in flight. Author Grid generation and Euler flow about fighter aircraft are described. A fighter aircraft geometry is specified by an area ruled N91-10860*# National Aeronautics and Space Administration. fuselage with an internal duct, cranked delta wing or strake/wing Langley Research Center, Hampton, VA. combinations, canard and/or horizontal tail surfaces, and vertical NAVIER-STOKES SOLUTIONS ABOUT THE F/A-18 tail surfaces. The initial step before grid generation and flow FOREBODY-LEX CONFIGURATION computation is the determination of a suitable grid topology. The FARHAD GHAFFARI, JAMES M. LUCKRING, JAMES L. THOMAS, external grid topology that has been applied is called a dual-block and BRENT L. BATES (Vigyan Research Associates, Inc., Hampton, topology which is a patched C (exp 1) continuous multiple-block VA.) In NASA, Ames Research Center, NASA Computational system where inner blocks cover the highly-swept part of a cranked Fluid Dynamics Conference. Volume 1: Sessions 1-6 p 361-383 wing or strake, rearward inner-part of the wing, and tail components. Sep. 1989 Original contains color illustrations Outer-blocks cover the remainder of the fuselage, outer-part of Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 the wing, canards and extend to the far field boundaries. The grid Three-dimensional viscous flow computations are presented-for generation is based on transfinite interpolation with Lagrangian the F/A-18 forebody-LEX (Leading Edge Extensions) geometry. blending functions. This procedure has been applied to the Langley Solutions are obtained from an algorithm for the compressible experimental fighter configuration and a modified F-18 Navier-Stokes equations which incorporates an upwind-biased, configuration. Supersonic flow between Mach 1.3 and 2.5 and flux-difference-splitting approach along with longitudinally-patched angles of attack between 0 degrees and 10 degrees have been grids. Results are presented for both laminar and fully turbulent computed with associated Euler solvers based on the finite-volume flow assumptions and include correlations with wind tunnel as approach. When coupling geometric details such as boundary layer well as flight-test results. A good quantitative agreement for the diverter regions, duct regions with inlets and outlets, or slots with forebody surface pressure distribution is achieved between the the general external grid, imposing C (exp 1) continuity can be turbulent computations and wind tunnel measurements at Mach extremely tedious. The approach taken here is to patch blocks number 0.6. The computed turbulent surface flow patterns on the together at common interfaces where there is no grid continuity, forebody qualitatively agree well with in-flight surface flow patterns but enforce conservation in the finite-volume solution. The key to obtained on an F/A-18 aircraft at Mach number 0.34. Author this technique is how to obtain the information required for a conservative interface. The Ramshaw technique which automates N91-10861*# National Aeronautics and Space Administration. the computation of proportional areas of two overlapping grids on Langley Research Center, Hampton, VA. a planar surface and is suitable for coding was used. Researchers NAVIER-STOKES SOLUTIONS FOR FLOWS RELATED TO generated internal duct grids for the Langley experimental fighter STORE SEPARATION configuration independent of the external grid topology, with a OKTAY BAYSAL (Old Dominion Univ., Norfolk, VA.), ROBERT L conservative interface at the inlet and outlet. Author STALLINGS, JR., and ELIZABETH B. PLENTOVICH In NASA, Ames Research Center, NASA Computational Fluid Dynamics N91-10858*# National Aeronautics and Space Administration. Conference. Volume 1: Sessions 1-6 p 385-410 Sep. 1989 Ames Research Center, Moffett Field, CA. Original contains color illustrations A ZONAL NAVIER-STOKES METHODOLOGY FOR FLOW Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 SIMULATION ABOUT A COMPLETE AIRCRAFT The objective is developing CFD capabilities to obtain solutions JOLEN FLORES In its NASA Computational Fluid Dynamics for viscous flows about generic configurations of internally and Conference. Volume 1: Sessions 1-6 p 327-343 Sep. 1989 externally carried stores. The emphasis is placed on the supersonic Original contains color illustrations flow regime with extensions being made to the transonic regime. Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 The project is broken into four steps: (1) Cavity flows for internal The thin layer, Reynolds-averaged, Navier-Stokes equations are carriage configurations; (2) High angle of attack flows, which may used to simulate the transonic viscous flow about the complete be experienced during the separation of the stores: (3) Flows F-16A fighter aircraft. These computations demonstrate how about a body near a flat plate for external carriage configurations; computational fluid dynamics can be used to simulate turbulent and (4) Flows about a body inside or in the proximity of a cavity. viscous flow about realistic aircraft geometries. A zonal grid Three-dimensional unsteady cavity flow solutions are obtained by approach is used to provide adequate viscous grid clustering on an explicit, MacComiack algorithm, EMCAV3, for open, close, and

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transitional cavities. High angle of attack flows past cylinders are impossible to set up in physical experiments. As a prelude to solved by an implicit, upwind algorithm. All the results compare studies of rotor-body aerodynamic interactions, a preliminary grid favorably with the experimental data. For flows about multiple body topology and moving-interface strategy were developed. A new configurations, the Chimera embedding scheme is modified for Euler/Navier-Stokes code using these techniques computes the finite-volume and multigrid algorithms, MaGGiE. Then a finite vortical wake directly, rather than modeling it, as in most previous volume, implicit, upwind, multigrid Navier-Stokes solver which uses rotorcraft studies. Several hover cases were run for conventional on overlapped/embedded and zonal grids, VUMXZ3, is developed and advanced-geometry blades. Numerical schemes using from the CFL3D code. Supersonic flows past a cylinder near a multi-zones and/or adaptive grids appear to be necessary to flat plate are computed using this code. The results are compared simulate the complex vortical flows in rotor wakes. Author with the experimental data. Currently the VUMXZ3 code is being modified to accomplish step 4 of this project. Wind tunnel N91-10864*# Sterling Federal Systems, Inc., Moffett Field, CA. experiments are also being conducted for validation purposes. CALCULATION OF THE ROTOR INDUCED DOWNLOAD ON Author AIRFOILS C. S. LEE In NASA, Ames Research Center, NASA Computational N91-10862'# National Aeronautics and Space Administration. Fluid Dynamics Conference. Volume 1: Sessions 1-6 p 447-458 Ames Research Center, Moffett Field, CA. Sep. 1989 TRANAIR: RECENT ADVANCES AND APPLICATIONS Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 MICHAEL D. MADSON In its NASA Computational Fluid Dynamics Interactions between the rotors and wing of a rotary wing Conference. Volume 1: Sessions 1-6 p 411-427 Sep. 1989 aircraft in hover have a significant detrimental effect on its payload Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 performance. The reduction of payload results from the wake of TranAir is a computer code which solves the full-potential lifting rotors impinging on the wing, which is at 90 deg angle of equation for transonic flow about very general and complex attack in hover. This vertical drag, often referred as download, configurations. Piecewise flat surface panels are used to describe can be as large as 15 percent of the total rotor thrust in hover. the surface geometry. This paneled definition is then embedded The rotor wake is a three-dimensional, unsteady flow with in an unstructured cartesian flow field grid. Finite elements are concentrated tip vortices. With the rotor tip vortices impinging on used in the discretization of the flow field grid in a manner which the upper surface of the wing, the flow over the wing is not only is fully conservative and second-order accurate. Since geometries three-dimensional and unsteady, but also separated from the may be defined with relative ease, and since the user is not leading and trailing edges. A simplified two-dimensional model was involved in the generation of the flow field grid, computational developed to demonstrate the stability of the methodology. The results may be generated rather quickly for a wide range of flow model combines a panel method to represent the rotor and geometries. For transonic cases in the cruise angle-of-attack range, the wing, and a vortex method to track the wing wake. A parametric TranAir has generated results which are in generally good study of the download on a 20 percent thick elliptical airfoil below agreement with both Euler results and wind tunnel data. A typical a rotor disk of uniform inflow was performed. Comparisons with transonic case runs in 1 to 2 CPU hours on a Cray X-MP. For experimental data are made where the data are available. This subcritical cases, the code runs in 15 to 30 CPU minutes, even approach is now being extended to three-dimensional flows. for geometries in which several thousand surface panels are used Preliminary results on a wing at 90 deg angle of attack in free in the definition. This ability to rapidly and accurately provide both stream is presented. Author subsonic and transonic predictions about very complex aircraft configurations gives TranAir the potential of being a very powerful N91-10865*# National Aeronautics and Space Administration. and widely used design tool. ' Author Ames Research Center, Moffett Field, CA. THREE-DIMENSIONAL VISCOUS DRAG PREDICTION FOR N91-10863*# National Aeronautics and Space Administration. ROTOR BLADES Ames Research Center, Moffett Field, CA. CHING S. CHEN (National Academy of Sciences - National NUMERICAL SIMULATION OF ROTORCRAFT Research Council, Washington, DC.) In its NASA Computational WILLIAM J. MCCROSKEY (Army Aviation Systems Command, Fluid Dynamics Conference. Volume 1: Sessions 1-6 p 459-472 Moffett Field, CA.) In its NASA Computational Fluid Dynamics Sep. 1989 Conference. Volume 1: Sessions 1-6 p 431-446 Sep. 1989 Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 Original contains color illustrations The state-of-the-art in rotor blade drag prediction involves the Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 use of two-dimensional airfoil tables to calculate the drag force The objective of the research is to develop and validate on the blade. One of the most serious problems with the current accurate, user-oriented viscous CFD codes (with inviscid options) methods is that they cannot be used for airfoils that have yet to for three-dimensional, unsteady aerodynamic flows about arbitrary be tested. Most of the drag prediction methods also do not take rotorcraft configurations. Unsteady, three-dimensional Euler and the Reynolds number or the rotational effects of the blade into Navier-Stokes codes are developed, adapted, and extended to account, raising doubts about the accuracy of the results. These rotor-body combinations. Flow solvers are coupled with zonal grid problems are addressed with the development of an analytical topologies, including rotating and nonrotating blocks. Special grid method which includes the shape of airfoil, the effects of Reynolds clustering and wave-fitting techniques were developed to capture number, and the rotational motion of the blade. Author low-level radiating acoustic waves. Significant progress was made in computing the propagation of acoustic waves due to the N91-10866*# National Aeronautics and Space Administration. interaction of a concentrated vortex and a helicopter airfoil. The Lewis Research Center, Cleveland, OH. need for higher-order schemes was firmly established in relatively PROGRESS TOWARD THE DEVELOPMENT OF AN AIRFOIL inexpensive two-dimensional calculations. In three dimensions, the ICING ANALYSIS CAPABILITY number of grid points required to capture the low-level acoustic MARK G. POTAPCZUK, COLIN S. BIDWELL, and BRIAN M. waves becomes very large, so that large supercomputer memory BERKOWITZ (Sverdrup Technology, Inc., Mayfield, OH.) In NASA, becomes essential. Good agreement was obtained between the Ames Research Center, NASA Computational Fluid Dynamics numerical results obtained with a thin-layer Navier-Stokes code Conference. Volume 1: Sessions 1-6 p 473-487 Sep. 1989 and experimental data from a model rotor. In addition, several Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 nonrotating configurations that are sometimes proposed to simulate The NASA-Lewis aircraft icing analysis program is composed rotor blade tips in conventional wind tunnels were examined, and of three major sub-programs. These sub-programs are ice accretion the complex flow around the radical tip shape of the world's fastest simulation, performance degradation evaluation, and ice protection helicopter is under investigation. These studies demonstrate the system evaluation. These topics cover all areas of concern related flexibility and power of CFD to gain physical insight, study novel to the simulation of aircraft icing- and its consequences. The ideas, and examine various possibilities that might be difficult or motivation for these activities is twofold, reduction of time and

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effort required in experimental programs and the ability to provide finite-difference technique of MacCormack. All of these codes used reliable information for aircraft certification in icing, over the the same algebraic eddy-viscosity turbulence model. In the complete range of environmental conditions. In addition to the experiment, the cowl lip was slightly blunted; however, for the analytical activities associated with development of these codes, computations, a sharp cowl leading edge was used to simplify the several experimental programs are underway to provide verification construction of the grid. The second test problem was the information for existing codes. These experimental programs are supersonic (Mach 3.0) flow in a three-dimensional corner formed also used to investigate the physical processes associated with by the intersection of two wedges with equal wedge angles of ice accretion and removal for improvement of present analytical 9.48 degrees. The flow in such a corner is representative of the models. The NASA-Lewis icing analysis program is thus striving flow in the corners of a scramjet inlet. Calculations were made to provide a full range of analytical tools necessary for evaluation for both laminar and turbulent flow and compared with experimental of the consequences of icing and of ice protection systems. data. The three-dimensional versions of the three codes used for Author the inlet study (CFL3D, USA-PG3, and SCRAMIN, respectively) were used for this case. For the laminar corner flow, a fourth N91-10867*# National Aeronautics and Space Administration. code, LAURA, which also uses recently-developed upwind Lewis Research Center, Cleveland, OH. technology, was also utilized. The final test case is the THE BREAKUP OF TRAILING-LINE VORTICES two-dimensional hypersonic flow over a compression ramp. The DAVID JACQMIN In NASA, Ames Research Center, NASA flow is laminar with a free-stream Mach number of 14.1. In the Computational Fluid Dynamics Conference. Volume 1: Sessions experiment, the ramp angle was varied to change the strength of 1-6 p 489-494 Sep. 1989 the ramp shock and the extent of the viscous-inviscid interaction. Avail: NTIS HC/MF A20; 25 functional color pages CSCL 01/1 Calculations were made for the 24-degree ramp configuration which It is now known that Batchelor's trailing-line vortex is extremely produces a large separated-flow region that extends upstream of unstable to small amplitude disturbances for swirl numbers in the the corner. Author neighborhood of 0.83. The results of numerical calculations are presented that show the response of the vortex in this range of N91-10873*# National Aeronautics and Space Administration. swirl numbers to finite amplitude, temporal, helical disturbances. Langley Research Center, Hampton, VA. Phenomena observed include: (1) ejection of axial vorticity and APPLICATION OF CFD CODES FOR THE SIMULATION OF momentum from the core resulting in the creation of secondary, SCRAMJET COMBUSTOR FLOWFIELDS separate vortices; (2) a great intensification of core axial vorticity TAWIT CHITSOMBOOM (Vigyan Research Associates, Inc., and a weakening of core momentum; and (3) the production of Hampton, VA.) and G. BURTON NORTHAM In NASA, Ames azimuthal vorticity in the form of a tightly wrapped spiral wave. Research Center, NASA Computational Fluid Dynamics The second phenomenon eventually stablizes the vortex, which Conference. Volume 2: Sessions 7-12 p 75-89 Sep. 1989 then smooths and gradually returns to an axisymmetric state. The Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 calculations are mixed spectral-finite-difference, fourth-order An overview of CFD activities in the Hypersonic Propulsion accurate, and have been carried out at Reynolds numbers of 1000 Branch is given. Elliptic and PNS codes that are being used for to 2000. Some linearized results are also discussed in an attempt the simulation of hydrogen-air combusting flowfields for scramjet to explain the process of vortex intensification. Author applications are discussed. Results of the computer codes are shown in comparison with those of the experiments where N91-10868*# National Aeronautics and Space Administration. applicable. Two classes of experiments will be presented: parallel Ames Research Center, Moffett Field, CA. injection of hydrogen into vitiated supersonic air flow; and normal NASA COMPUTATIONAL FLUID DYNAMICS CONFERENCE. injection of hydrogen into supersonic crossflow of vitiated air. VOLUME 2: SESSIONS 7-12 Author Sep. 1989 525 p Conference held at Moffett Field, CA, 7-9 Mar. 1989 Original contains color illustrations N91-10881*# National Aeronautics and Space Administration. (NASA-CP-10038-VOL-2; A-89160-VOL-2; NAS Ames Research Center, Moffett Field, CA. 1.55:10038-VOL-2) Avail: NTIS HC/MF A22; 30 functional color PREDICTION OF TURBINE ROTOR-STATOR INTERACTION pages CSCL 01/1 USING NAVIER-STOKES METHODS The objectives of the conference were to disseminate CFD NATERI K. MADAVAN, MAN MOHAN RAI, and SHARAD GAVALI research results to industry and university CFD researchers, to (Amdahl Corp., Sunnyvale, CA.) In its NASA Computational Fluid promote synergy among NASA CFD researchers, and to permit Dynamics Conference. Volume 2: Sessions 7-12 p 205-216 Sep. feedback from researchers outside of NASA on issues pacing 1989 the discipline of CFD. The focus of the conference was on the Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 application of CFD technology but also included fundamental Flows in turbomachinery are|generally complex and do not activities. easily lend themselves to numerical computation. The flows are three-dimensional and inherently' unsteady. Complicated blade N91-10869*# National Aeronautics and Space Administration. geometries and flow phenomena such as separation and periodic Langley Research Center, Hampton, VA. transition from laminar to turbulent flow add to the numerical A COMPARATIVE STUDY OF NAVIER-STOKES CODES FOR complexity. Nevertheless, the accurate numerical analysis of such HIGH-SPEED FLOWS flows is a problem of considerable interest and practical importance DAVID H. RUDY, JAMES L THOMAS, AJAY KUMAR, PETER A. to the turbomachinery community. Much of the early work in GNOFFO, and SUKUMAR R. CHAKRAVARTHY (Rockwell turbomachinery flow prediction focussed on airfoil cascades. While International Science Center, Thousand Oaks, CA.) In NASA, such analyses of flows in isolated airfoil rows have helped improve Ames Research Center, NASA Computational Fluid Dynamics understanding of the flow phenomena and have gained widespread Conference. Volume 2: Sessions 7-12 p 3-18 Sep. 1989 acceptance in the industrial community as a design tool, they do Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 not yield any information regarding the unsteady effects arising A comparative study was made with four different codes for out of rotor-stator aerodynamic interaction. These interaction solving the compressible Navier-Stokes equations using three effects become increasingly important as the distance between different test problems. The first of these cases was hypersonic successive stator and rotor rows is decreased. Thus, the need flow through the P8 inlet, which represents inlet configurations exists for analytical tools that treat the rotor and stator airfoils as typical of a hypersonic airbreathing vehicle. The free-stream Mach a system and provide information regarding the magnitude and number in this case was 7.4. This 2-D inlet was designed to the impact of the unsteady effects. The focus a three-dimensional, provide an internal compression ratio of 8. Initial calculations were time-accurate, thin-layer Navier-Stokes code that was recently made using two state-of-the-art finite-volume upwind codes, CFL3D developed to study rotor-stator interaction problems. A system of and USA-PG2, as well as NASCRIN, a code which uses the unsplit patched and overlaid grids that move relative to each other is

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used to discretize the flow field and the governing equations are N91-10888*# National Aeronautics and Space Administration. integrated using a third-order upwind scheme set in an iterative, Lewis Research Center, Cleveland, OH. implicit framework. The code was used to simulate subsonic flow CFD ANALYSIS FOR HIGH SPEED INLETS through an axial turbine configuration for which .considerable TOM BENSON In NASA, Ames Research Center, NASA experimental data exists. Grid refinement studies were also Computational Fluid Dynamics Conference. Volume 2: Sessions conducted as part of the code validation process. The current 7-12 p 311-319 Sep. 1989 status of the research, along with planned future directions, are Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 also discussed. Author The increased national interest in high speed flight has increased research for high speed propulsion components. The N91-10883*# National Aeronautics and Space Administration. highly 3-D flows present in supersonic/hypersonic inlets are Lewis Research Center, Cleveland, OH. currently being studied at NASA-Lewis both experimentally and AUTOMATED DESIGN OF CONTROLLED DIFFUSION BLADES computationally using a family of steady Parabolized Navier-Stokes JOSE M. SANZ In NASA, Ames Research Center, NASA (PNS) and Navier-Stokes (NS) solvers and unsteady NS solvers. Computational Fluid Dynamics Conference. Volume 2: Sessions Some of the results of these efforts are presented with an emphasis 7-12 p 231-244 Sep. 1989 Previously announced in IAA as on the comparison of the computational and experimental results. A89-15967 The flow in high speed inlets typically involves the interaction of Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 compression shock waves and boundary layers on the internal A numerical automation procedure was developed to be used surfaces. The fundamentals of these interactions have been studied in conjunction with an inverse hodograph method for the design experimentally for many years, while more recently, computations of controlled diffusion blades. With this procedure a cascade of have been used to study these complex 3-D flow fields. Attempts airfoils with a prescribed solidity, inlet Mach No., inlet air flow to control the flow through boundary layer bleed are being angle and air flow turning can be produced automatically. The investigated computationally prior to wind tunnel experiments. The trailing edge thickness of the airfoil, an important quantity in inverse ultimate goal is the higher performing inlets required for high speed methods, is also prescribed. The automation procedure consists flight. Author of a multi-dimensional Newton iteration in which the objective design conditions are achieved by acting on the hodograph input N91-10889*# National Aeronautics and Space Administration. parameters of the underlying inverse code. The method, although Langley Research Center, Hampton, VA. more general in scope, is applied to the design of axial flow THE USE OF A NAVIER-STOKES CODE IN THE WING DESIGN turbomachinery blade sections, both compressors and turbines. A PROCESS collaborative effort with U.S. Engine Companies to identify designs S. NAOMI MCMILLIN In NASA, Ames Research Center, NASA of interest to the industry will be described. Author Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12 p 321-342 Sep. 1989 Original contains color illustrations N91-10886*# National Aeronautics and Space Administration. Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 Ames Research Center, Moffett Field, CA. The feasibility was determined of incorporating the SIMULATION OF POWERED-LIFT FLOWS Navier-Stokes computational code, CFL3D, into the supersonic WILLIAM R. VANDALSEM, KALPANA CHAWLA, KARLIN R. ROTH, wing design process. The approach taken is of two steps. The MERRITT H. SMITH, KUDITIPUDI V. RAO, and THOMAS C. BLUM first step was to calibrate CFL3D against existing experimental (Boeing Co., Seattle, WA.) In its NASA Computational Fluid data sets obtained on thin sharp edged delta wings. The Dynamics Conference. Volume 2: Sessions 7-12 p 275-290 Sep. experimental data identified six flow types which are dependent 1989 on the similarity parameters of Mach number and angle of attack Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 normal to the leading edge. The calibration showed CFL3D capable The primary objective is to expose government, industry, and of simulating these various separated and attached flow conditions. academic scientists to work underway at NASA-Ames towards The second step was to use CFL3D to study the initial formation the application of CFD to the powered lift area. One goal is to of leading edge separation over delta wings at supersonic speeds. produce the technologies which will be required in the application This consisted of examining solutions obtained on a 65 deg delta of numerical techniques to, for example, the Supersonic STOVL wing at Mach number of 1.6 with varying cross sectional shapes. program. The progress to date on the following specific projects Reynolds number was held constant at 1000000 and the is presented: Jet in ground effect with crossflow; Jet in a crossflow; Baldwin-Lomax turbulence model was used. The study showed Delta planform with multiple jets in ground effect; Integration of that through the use of leading edge radius and/or camber, the CFD with thermal and acoustic analyses; Improved flow onset of leading edge separation can be delayed to a higher visualization techniques for unsteady flows; YAV-8B Harrier angle of attack than observed on a flat sharp edged wing. Based simulation program; and E-7 simulation program. Author on the geometries studied, three wind tunnel models are being designed to verify these results. Author N91-10887*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. N91-10890*# National Aeronautics and Space Administration. A NUMERICAL STUDY OF THE HOT GAS ENVIRONMENT Langley Research Center, Hampton, VA. AROUND A STOVL AIRCRAFT IN GROUND PROXIMITY APPLICATIONS OF A TRANSONIC WING DESIGN METHOD THOMAS J. VANOVERBEKE and JAMES D. HOLDEMAN In RICHARD L. CAMPBELL and LEIGH A. SMITH In NASA, Ames NASA, Ames Research Center, NASA Computational Fluid Research Center, NASA Computational Fluid Dynamics Dynamics Conference. Volume 2: Sessions 7-12 p 291-310 Sep. Conference. Volume 2: Sessions 7-12 p 343-358 Sep. 1989 1989 Previously announced in IAA as A88-48752 Original Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 contains color illustrations A method for designing wings and airfoils at transonic speeds Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01 /1 using a predictor/corrector approach was developed. The The development of Short Takeoff Vertical Landing (STOVL) procedure iterates between an aerodynamic code, which predicts aircraft has historically been an empirical- and experienced-based the flow about a given geometry, and the design module, which technology. A 3-D turbulent flow CFD code was used to calculate compares the calculated and-target pressure distributions and the hot gas environment around an STOVL aircraft operating in modifies the geometry using an algorithm that relates differences ground proximity. Preliminary calculations are reported for a typical in pressure to a change in surface curvature. The modular nature STOVL aircraft configuration to identify key features of the flow of the design method makes it relatively simple to couple it to field, and to demonstrate and assess the capability of current 3-D any analysis method. The iterative approach allows the design CFD codes to calculate the temperature of the gases ingested at process and aerodynamic analysis to converge in parallel, the engine inlet as a function of flow and geometric conditions. significantly reducing the time required to reach a final design. Author Viscous and static aeroelastic effects can also be accounted for

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'during the design or as a post-design correction. Results from required. The generation of a 3-D grid is accomplished in several several pilot design codes indicated that the method accurately steps.-First the boundaries of the domain to be gridded must be reproduced pressure distributions as well as the coordinates of a described by two-, three- or four-sided surface patches. Next, a given airfoil or wing by modifying an initial contour. The codes background mesh is required to control the grid spacing and were applied to supercritical as well as conventional airfoils, stretching throughout the domain. This coarse tetrahedral grid is forward- and aft-swept transport wings, and moderate-to-highly not required to conform to any of the boundaries. Next, each of swept fighter wings. The design method was found to be robust the patches is mapped to 2-D, triangulated by the advancing front and efficient, even for cases having fairly strong shocks. Author technique and mapped back to 3-D. These triangles form the initial front for the generation of the final tetrahedral mesh. N91-10891*# National Aeronautics and Space Administration. Author Langley Research Center, Hampton, VA. AN EMBEDDED GRID FORMULATION APPLIED TO DELTA N91-10902*# National Aeronautics and Space Administration. WINGS Langley Research Center, Hampton, VA. JAMES L. THOMAS and SHERRIE L KRIST (Vigyan Research PREDICTION OF EFFECTS OF WING CONTOUR Associates, Inc., Hampton, VA.) In NASA, Ames Research Center, MODIFICATIONS ON LOW-SPEED MAXIMUM LIFT AND NASA Computational Fluid Dynamics Conference. Volume 2: TRANSONIC PERFORMANCE FOR THE EA-6B AIRCRAFT Sessions 7-12 p 361-377 Sep. 1989 DENNIS O. ALLISON and E. G. WAGGONER Washington Nov. Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 1990 48 p An embedded grid algorithm for the Euler and/or Navier-Stokes (NASA-TP-3046; L-16741; NAS 1.60:3046) Avail: NTIS HC/MF equations is developed and applied to delta wings at high angles A03 CSCL 01/1 .. of attack in low speed flow. The Navier-Stokes code is an implicit, Computational predictions of the effects of wing contour finite volume algorithm, using flux difference splitting for the modifications on maximum lift and transonic performance were convective and pressure terms and central differencing for the made and verified against low speed and transonic wind tunnel viscous and heat transfer terms. Calculations are compared with data. This effort was part of a program to improve the maneuvering detailed experimental results over an angle of attack range up to capability of the EA-6B electronics countermeasures aircraft, which and beyond the maximum lift coefficient, corresponding to vortex evolved from the A-6 attack aircraft. The predictions were based breakdown at the trailing edge, for a delta wing nominally of unit on results from three computer codes which all include viscous aspect ratio. The results indicate'that the overall flowfield, including effects: MCARF, a 2-D subsonic panel code; TAWFIVE, a transonic surface pressures, surface streamlines, and vortex trajectories, can full potential code; and WBPPW, a transonic small disturbance be simulated accurately with the global grid version of the present potential flow code. The modifications were previously designed algorithm. However, comparison of computed velocities and vorticity with the aid of these and other codes. The wing modifications with experimentally measured off-body values at an angle of attack consists of contour changes to the leading edge slats and trailing of 20.5 deg indicates the core region is substantially more diffuse edge flaps and were designed for increased maximum lift with in the computations than that measured with either a five-hole minimum effect on transonic performance. The prediction of the probe or a laser velocimeter. Embedded grids, used to improve the numerical discretization in the core region, are formulated within effects of the modifications are presented, with emphasis on verification through comparisons with wind tunnel data from the the framework of the implicit, upwind-biased multi-grid algorithm. National Transonic Facility. Attention is focused on increments in Structured levels of local nested refinements are made. low speed maximum lift and increments in transonic lift, pitching Three-dimensional results for both Euler and Navier-Stokes moment, and drag resulting from the contour modificatipns. calculations are shown, with up to 3 levels of embedded refinement. Author The embedding procedure was effective in eliminating a crossflow secondary separation produced in the Euler solutions on coarse grids. • Author N91-10904*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. N91-10892*# National Aeronautics and Space Administration. CONICAL EULER SIMULATION AND ACTIVE SUPPRESSION Ames Research Center, Moffett Field, CA. OF DELTA WING ROCKING MOTION UNSTRUCTURED MESH SOLUTION OF THE EULER AND ELIZABETH M. LEE and JOHN T. BATINA Oct. 1990 34 p NAVIER-STOKES EQUATIONS (NASA-TM-102683; NAS 1.15:102683) Avail: NTIS HC/MF A03 TIMOTHY J. BARTH In its NASA Computational Fluid Dynamics CSCL 01/1 Conference. Volume 2: Sessions 7-12 p 379-393 Sep. 1989 A conical Euler code was developed to study unsteady Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 ' vortex-dominated flows about rolling highly-swept delta wings, Mesh generation procedures as well as solution algorithms for undergoing either forced or free-to-roll motions including active solving the Euler and Navier-Stokes equations on unstructured roll suppression. The flow solver of the code involves a multistage meshes are presented. The solution algorithms discussed utilize Runge-Kutta time-stepping scheme which uses a finite volume approximate Riemann solver, upwind differencing to achieve high spatial discretization of the Euler equations on an unstructured spatial accuracy. Numerical results for Euler flow over single and grid of triangles. The code allows for the additional analysis of multi-element airfoils-are presented. • Author the free-to-roll case, by including the rigid-body equation of motion for its simultaneous time integration with the governing flow N91-10893*# National Aeronautics and Space Administration. equations. Results are presented for a 75 deg swept sharp leading Langley Research Center, Hampton, VA. edge delta wing at a freestream Mach number of 1.2 and at THREE DIMENSIONAL UNSTRUCTURED GRIDS FOR THE alpha equal to 10 and 30 deg angle of attack. A forced harmonic SOLUTION OF THE EULER EQUATIONS analysis indicates that the rolling moment coefficient provides: (1) CLYDE GUMBERT, P. PARIKH, S. PIRZADEH, and R. LOEHNER a positive damping at the lower angle of attack equal to 10 deg, (George Washington Univ., Hampton, VA.) In NASA, Ames which is verified in a free-to-roll calculation; (2) a negative damping Research Center, NASA Computational Fluid Dynamics at the higher angle of attack equal to 30 deg at the small roll Conference. Volume 2: Sessions 7-12 p 395-436 Sep. 1989 amplitudes. A free-to-roll calculation for the latter case produces Original contains color illustrations an initially divergent response, but as the amplitude of motion Avail: NTIS HC/MF A22; 30 functional color pages CSCL 01/1 grows with time, the response transitions to a wing-rock type of The advancing front technique is being used to develop a limit cycle oscillation. The wing rocking motion may be actively code to generate grids around complex 3-D configurations for use suppressed, however, through the use of a rate-feedback control in computing the invisid flow solutions by the Euler equations. By law and antisymmetrically deflected leading edge flaps. The the advancing front technique points are introduced concurrently descriptions of the conical Euler flow solver and the free-to-roll with the connectivity information so that a separate library is not analysis are presented. Results are also presented which give

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insight into the flow physics associated with unsteady vortical flows because grid generation is a prominent limitation in computational about forced and free-to-roll delta wings, including the active roll problems involving complex geometries. One direction of grid suppression of this wing-rock phenomenon. Author generation research is the multiblock approach where the domain is decomposed into simple, non-overlapping sub-regions. Multiblock N91-10906 Colorado Univ., Boulder. grids for non-trivial, three-dimensional aircraft configurations with COMPUTATION OF TRANSONIC FLOW OVER ELASTIC solutions have been generated in the past. Yet, the procedures ROTOR BLADE Ph.D. Thesis used are not automatic, and require substantial human intervention LIE-MINE GEA 1989 121 p to determine the overall block structure, and grid point distribution. Avail: Univ. Microfilms Order No. DA9024828 Automation of this procedure is necessary before these methods The understanding of the aeroelastic behavior of transonic can come into common usage. A novel algorithm was developed rotor blades is essential in the design of advanced vertical-takeoff and investigated for substantially automating the decomposition and landing vehicles such as the tilt-rotor and x-wing aircraft. A of arbitrary two-dimensional domains into non-overlapping, computational tool is developed by coupling an aerodynamic code topologically rectangular blocks. To demonstrate the technique, with a structural dynamic code, which can be used to predict the solutions to the Euler equations for several multi-element airfoil performance of an elastic rotor blade when operating at transonic configurations are presented, including a four element landing speeds. The full-potential transonic rotor flow code TFAR2, based configuration. Further, accuracy estimates for the grids are on the finite-difference approach, is used to compute the inviscid, developed analytically, and approximated numerically to isentropic, and irrotational flow field in a blade-fixed coordinate demonstrate the accuracy characteristics of the singularities which system. On the other hand, the finite-element approach based on occur in the grids. Dissert. Abstr. beam theory is employed in the structural dynamic code. Flutter equations are solved in time domain instead of in frequency domain N91-10910 North Carolina State Univ., Raleigh. of using modal analysis, and a global-local transformation matrix AERODYNAMIC INTERACTION OF COUNTER ROTATING is derived to improve the accuracy for large blade deflections. PROPELLERS Ph.D. Thesis The computer natural frequencies of a modal blade in the first YOONSANG LEE 1989 81 p five modes (three flapping, one lagging, and one torsion) agree Avail: Univ. Microfilms Order No. DA9017689 very well with experimental data. To demonstrate the capability of Axial and circumferential flow velocity components were this computational tool, both hovering and forward flight cases for measured at discrete points between rotors of a 28 cm diameter the model blade are examined. Numerical results are presented counter rotating propeller using both a single and a two-component separately to show the differences between rigid and elastic blade hot-film anemometer. The tests were performed in an open-jet calculations. The comparison reveals that the blade elasticity plays anechoic wind tunnel with a 0.61 m x 0.61 m square nozzle and an important role in the transonic regime, especially when the a free-stream speed of 0.09 Mach number. Primary test variables rotor is in forward flight. Dissert. Abstr. were radial and axial positions of the hot-film sensor and rotor-to-rotor spacing' of the CRP.- Axial flow measurements from N91-10907 Colorado Univ., Boulder. a single sensor agreed well with those of a two-component X-probe. EXPERIMENTAL INVESTIGATION OF THE MECHANISMS Single sensor and X-probe measurements of circumferential flow UNDERLYING VORTEX KINEMATICS IN UNSTEADY did not agree as well. Axial mean flow data show significant SEPARATED FLOWS Ph.D. Thesis upstream influence of the aft rotor. The circumferential mean flow SCOTT JEFFREY SCHRECK 1989 155 p between rotors appears relatively uninfluenced by the aft rotor. Avail: Univ. Microfilms Order No. DA9024868 Turbulence intensity abruptly increased near the blade tip Current research in the area of unsteady separated flows has suggesting a possible tip vortex from the forward rotor. Turbulence been strongly motivated by potential enhancements to air vehicle intensity decreased between rotors as rotor-to-rotor spacing performance. Dynamic motions of lifting surfaces give rise to the increased. The analysis was extended to determine the velocity emergence and fleeting presence of energetic, large-scale vortical fluctuations at the blade passing frequencies and the blade structures characteristic of unsteady separated flow fields. While interaction frequency. Velocity fluctuation at each of these discrete present over the lifting surface, these vortices substantially augment frequencies were observed, including the forward-aft rotor lift and moment coefficients and exact only modest penalties in interaction frequencies. Dissert. Abstr. terms of elevated drag coefficients. However, the feasibility of utilizing unsteady separation relies upon thorough comprehension N91-10913 George Washington Univ., Washington, DC. of the fluid dynamic mechanisms responsible for vortex presence EJECTOR THRUST AUGMENTORS: PULSE-STARTING and behavior. To date, these mechanisms remain relatively obscure. APPROACH TO THE SECOND SOLUTION Ph.D. Thesis Unsteady separated flow fields in the vicinity of a flat plate MOHAMED AHMED ABDEL-WAHAB 1990 156 p oscillating sinusoidally in pitch about the quarterchord were Avail: Univ. Microfilms Order No. DA9020742 investigated for a broad range of pitching parameters. Phase locked While the steady flow supersonic solution to the ejector problem photograph of smoke flow visualization was employed in has been studied analytically, experimental validation has been conjunction with hotwire anemometry to quantify vortex elusive. Lack of validation may be explained by the possibility that development as well as some of the primary boundary layer localized processes may violate the second law of thermodynamics interactions contributing to the observed vortex kinematics. Leading even though there is no overall violation. To, detect the process edge vortex development was strongly influenced by both the mechanism, a pulse-starting simulation, analogous to the one used freestream and boundary layer flows. These and other observations to analyze supersonic and hypersonic shock tunnels, was used to facilitated formulation of a conceptual model which accounts for analyze the dynamics of the ejector. Compared to the steady flow many of these observations. Quantitative refinement of such a CFD approach, this method greatly reduces the uncertainties model is one methodology through which unsteady separation may associated with simulating mixing processes. The computation eventually be understood, predicted, and controlled for employment analysis used can reveal local violation of the second law of in future air vehicles. Dissert. Abstr. thermodynamics that cannot be detected by control volume analysis and that would rule out a second solution even when the associated N91-10908 Princeton Univ., NJ. overall entropy increment is positive. Analysis also reveals NONOVERLAPPING COMPOSITE MESHES FOR important details of the mechanism by which momentum and energy MULTI-ELEMENT AIR-FOILS Ph.D. Thesis are exchanged in flow induction devices operating on the basis of MARK ERIC MICHAEL STEWART 1990 157 p wave processes. To illustrate the application of the proposed Avail: Univ. Microfilms Order No. DA9024542 method, the method of analysis was applied to a specific set of Developing the ability to place grids for numerical calculations boundary conditions that would, according to control volume in geometrically complex regions is a problem of current interest analysis, lead to a second solution only marginally permitted by in many engineering and scientific disciplines. Its importance arises the second law. Analysis is performed until the front of the

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advancing flow is a substantially normal shock. The study validates Improved algorithm for the solution of the time-dependent the analysis and its conclusions for one case by a double-flow Euler equations are presented for unsteady aerodynamic analysis shock tube experiment. Dissert. Abstr. involving unstructured dynamic meshes. The improvements were developed recently to the spatial and temporal discretizations used N91-10915 Oxford Univ. (England). by unstructured grid flow solvers. The spatial discretization involves THE AERODYNAMIC EFFECTS OF NOZZLE GUIDE VANE a flux-split approach which is naturally dissipative and captures SHOCK WAVE AND WAKE PASSING ON A TRANSONIC shock waves sharply with at most one grid point within the shock TURBINE ROTOR Ph.D. Thesis structure. The temporal discretization involves an implicit A. B. JOHNSON 1988 233 p time-integration scheme using a Gauss-Seidel relaxation procedure Avail: Univ. Microfilms Order No. BRD-89420 which is computationally efficient for either steady or unsteady Flow perturbations are intrinsic in the operation of any turbine flow problems. For example, very large time steps may be used and are often associated with the periodic chopping of the wakes for rapid convergence to steady state, and the step size for from an upstream blade row by the next row. The effect of these unsteady cases may be selected for temporal accuracy rather perturbations on the aerodynamic performance of the passage, than for numerical stability. Steady and unsteady flow results are the thermal loading of the blades and the blade profile losses presented for the NACA 0012 airfoil to demonstrate applications needs to be understood. An experimental study of some of these of the new Euler solvers. The unsteady results were obtained for effects was made using a nozzle guide vane wake and trailing the airfoil pitching harmonically about the quarter chord. The edge shock wave simulator. Measurements of time resolved and resulting instantaneous pressure distributions and lift and moment time averaged surface pressures and heat transfer rates were coefficients during a cycle of motion compare well with experimental made, together with schlieren photography flow visualization tests. data. A description of the Euler solvers is presented along with This was supported by tests made in a 9x3 inch induced flow results and comparisons which assess the capability. Author transonic tunnel to examine the characteristics of the wakes and shock waves being tested by the simulation. The results were used to study the propagation of the shock waves and wakes N91-10919*# National Aeronautics and Space Administration. through the rotor passage. Shock wave passing was shown to Langley Research Center, Hampton, VA. nucleate a vortex and separation bubble at the leading edge of TEMPORAL-ADAPTIVE EULER/NAVIER-STOKES ALGORITHM the blade and cause a novel shock wave pressure surface FOR UNSTEADY AERODYNAMIC ANALYSIS OF AIRFOILS interaction. The interaction between the shock wave and blade USING UNSTRUCTURED DYNAMIC MESHES boundary layer can cause large, rapid fluctuations in the surface WILLIAM L. KLEB, JOHN T. BATINA, and MARC H. WILLIAMS heat transfer rate, and a negative heat transfer rate in some cases. (Purdue Univ., West Lafayette, IN.) Nov. 1990 10 p Presented A theoretical model was proposed to explain this phenomenon. at the 21st AIAA Fluid Dynamics, Plasma Dynamics, and Lasers The passing of the wake over the pressure surface was shown to Conference, Seattle, WA, 18-20 Jun. 1990 Previously announced cause both positive and negative fluctuations in the surface heat in IAA as A90-38778 transfer rate. Two computational fluid dynamics codes were tested (NASA-TM-102734; NAS 1.15:102734; AIAA-90-1650) Avail: to predict the steady and unsteady flows. A sensitivity to the NTIS HC/MF A02 CSCL 01/1 effects of surface discontinuities was identified in one code. The A temporal adaptive algorithm for the time-integration of the results were compared with those found in the equivalent two-dimensional Euler or Navier-Stokes equations is presented. experimental tests with very good agreement. Dissert. Abstr. The flow solver involves an upwind flux-split spatial discretization for the convective terms and central differencing for the N91-10916 Illinois Univ. at Urbana-Champaign, Savoy. shear-stress and heat flux terms on an unstructured mesh of NUMERICAL CALCULATIONS FOR FLOWS PAST AN triangles. The temporal adaptive algorithm is a time-accurate UNCONVENTIONAL AIRFOIL Ph.D. Thesis integration procedure which allows flows with high spatial and PING-HOTSAI 1990 122 p temporal gradients to be computed efficiently by advancing each Avail: Univ. Microfilms Order No. DA9021770 grid cell near its maximum allowable time step. Results indicate A computer program was developed for both 2-D compressible that an appreciable computational savings can be achieved for and incompressible turbulent flows around airfoils. Numerical both inviscid and viscous unsteady airfoil problems using solutions were obtained by solving the steady state unstructured meshes without degrading spatial or temporal Reynolds-averaged Navier-Stokes equations in primitive variable accuracy. . Author form. The standard k-epsilon turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the N91-10920# Deutsche Forschungsanstalt fuer Luft- und discretized transport equations were solved either by a hybrid or Raumfahrt,. Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. a second-order upwind differencing scheme. A multiple pressure CONTRIBUTIONS IN THE FIELD OF AEROELASTICS ON THE correction procedure with implicit density treatment was used. The OCCASION OF THE 60TH ANNIVERSARY OF PROFESSOR solutions were obtained through an under-relaxed iterative process. DR.-ING. HABIL. HANS WILHELM FOERSCHING [BEITRAEGE Various cases of flow past NACA 0012 and 4412 airfoils were AUS DEM BEREICH DER AEROELASTIK ZUM 60. examined first. The results were good when compared with GEBURTSTAG VON PROFESSOR DR.-ING. HABIL. HANS experimental data. Many cases of incompressible and compressible WILHELM FOERSCHING] flows past an unconventional airfoil were then computed. The • Apr. 1990 287 p In ENGLISH and GERMAN . general behavior of the unconventional airfoil is presented. (ETN-90-97630) Avail: NTIS HC/MF A13 Dissert. Abstr. A numerical procedure for the calculation of unsteady transonic flow about oscillating airfoils is presented. The status of stuctural N91-10918*# National Aeronautics and Space Administration. dynamics qualification of spacecraft is depicted. Aeroelastics and Langley Research Center, Hampton, VA. dynamics of wind turbines are treated. The structural analysis and IMPLICIT FLUX-SPLIT EULER SCHEMES FOR UNSTEADY optimization of a propfan blade were studied using the finite element AERODYNAMIC ANALYSIS INVOLVING UNSTRUCTURED method. The derivative balance for a transonic wind tunnel was DYNAMIC MESHES designed. The pressure distribution on an oscillating airfoil in JOHN T. BATINA Nov. 1990 11 p Presented at the 31st incompressible flow was calculated. Unsteady aerodynamic forces AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, on engines were determined with a view to flutter investigations. and Materials Conference, Long Beach, CA, 2-4 Apr. 1990 Unsteady wind tunnel wall interferences in subsonic and transonic Previously announced in IAA as A90-29362 profile flows were studied theoretically. Adaptive digital real time (NASA-TM-102732; NAS 1.15:102732; AIAA-90-0936) Avail: filtering in strutural dynamics was investigated. The nonlinear NTIS HC/MF A03 CSCL01/1 vibration of large, imperfect space structures was studied.

24 03 AIR TRANSPORTATION AND SAFETY

N91-10921# Deutsche Forschungsanstalt fuer Luft- und very well with other numerical results and with results obtained Raumfahrt, Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. from experiment and thereby demonstrate the accuracy of the THE CALCULATION OF UNSTEADY COMPRESSIBLE FLOW viscous solution. The interaction of a simulated rotor wake with ABOUT OSCILLATING AIRFOIL PROFILES USING THE EULER the flow about 2-D bodies, representing cross sections of fuselage UPWIND METHOD [DIE BERECHNUNG VON components, was calculated to address the vortex interaction INSTATIONAEREN KOMPRESSIBLEN STROEMUNGEN UM problem. The vortex interaction was calculated for the flow about SCHWINGENDE PROFILE MIT HILFE EINES a circular and an elliptic cylinder at 45 and 90 degrees incidence. EULER-UPWIND-VERFAHRENS] The results demonstrate the significant variation in lift and drag VOLKER CARSTENS In its Contributions in the Field of on the 2-D bodies during the vortex interaction. Author Aeroelastics on the Occasion of the 60th Anniversary of Professor Dr.-lng. Habil. Hans Wilhelm Foersching p 13-38 Apr. 1990 In N91-10934*# Stanford Univ., CA. Dept. of Aeronautics and GERMAN; ENGLISH summary Astronautics. Avail: NTIS HC/MF A13 A NUMERICAL STUDY OF THE EFFECTS OF WIND TUNNEL A numerical procedure for the calculation of the unsteady WALL PROXIMITY ON AN AIRFOIL MODEL transonic flow about oscillating airfoils, based on the Euler MARK POTSDAM and LEONARD ROBERTS Sep. 1990 72 p equations in conservative form is presented. The selected solution (Contract NCC2-055) method, called flux vector splitting, is similar to a characteristic (NASA-CR-187322; NAS 1.26:187322; JIAA-TR-99) Avail: NTIS method, and is characterized by the use of spatially one sided HC/MF A04 CSCL01/1 differences (upwinding). This method has a good numerical stability A procedure was developed for modeling wind tunnel flows and excellent shock capturing properties. The wall boundary using computational fluid dynamics. Using this method, a numerical conditions at the profile surface, and, in the case of unsteady study was undertaken to explore the effects of solid wind tunnel flow, the nonreflecting boundary conditions at the outer grid wall proximity and Reynolds number on a two-dimensional airfoil boundary were implemented in a numerical algorithm. The close model at low speed. Wind tunnel walls are located at varying agreement between numerical results and experimental data is wind tunnel height to airfoil chord ratios and the results are illustrated by an AGARD standard test case. Numerical results for compared with freestream flow in the absence of wind tunnel reduced frequencies give an impression of the influence of the walls. Discrepancies between the constrained and unconstrained reduced frequency on unsteady pressure and lift. ESA flows can be attributed to the presence of the walls. Results are for a Mach Number of 0.25 at angles of attack through stall. A N91-10926# Deutsche Forschungsanstalt fuer Luft- und typical wind tunnel Reynolds number of 1,200,000 and full-scale Raumfahrt, Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. flight Reynolds number of 6,000,000 were investigated. At this CALCULATION OF THE PRESSURE DISTRIBUTION ON AN low Mach number, wind tunnel wall corrections to Mach number OSCILLATING AIRFOIL IN INCOMPRESSIBLE FLOW and angle of attack are supported. Reynolds number effects are CONSIDERING NONLINEAR EFFECTS Ph.D. Thesis seen to be a consideration in wind tunnel testing and wall LORENZ TICHY In its Contributions in the Field of Aeroelastics interference correction methods. An unstructured grid Navier- on the Occasion of the 60th Anniversary of Professor Dr.-lng. Stokes code is used with a Baldwin-Lomax turbulence model. Habil. Hans Wilhelm Foersching p 127-139 Apr. 1990 The numerical method is described since unstructured flow Avail: NTIS HC/MF A13 solvers present several difficulties and fundamental differences Panel methods were used to calculate the pressure on a two from structured grid codes, especially in the area of turbulence dimensional airfoil which performs harmonic plunging and pitching modeling and grid generation. Author oscillations in an incompressible potential flow. Two panel methods are described which allow the examination of the influence of profile and wake geometries on pressure distribution and aerodynamic coefficients. The first method operates in the 03 frequency domain; it only takes into account the nonlinear influences resulting from the slope of the airfoil contour (i.e., from airfoil thickness and angle of attack). The second method is AIR TRANSPORTATION AND SAFETY applicable in the time domain; it provides a more exact description of the wake geometry. Comparisons of the results from both Includes passenger and cargo air transport operations; and aircraft methods with the linear flat plate solution demonstrate the accidents. significance of the above mentioned influences. ESA i N91-10933*# National Aeronautics and Space Administration. A91-10959 Ames Research Center, Moffett Field, CA. TWENTY YEARS OF CONCORDE - THE EXPERIENCE OF AIR THE CALCULATION OF ROTOR/FUSELAGE INTERACTION FRANCE [VINGT ANS DE CONCORDE - L'EXPERIENCE D'AIR FOR TWO-DIMENSIONAL BODIES FRANCE] PAUL M. STREMEL Aug. 1990 35 p Presented at the 16th PIERRE KLEITZ (Air France, Paris) IN: European Symposium on European Rotorcraft Forum, Glasgow, Scotland, 18-21 Sep. 1990 the Future of High Speed Air Transport, Strasbourg, France, Nov. (NASA-TM-102855; A-90256; MAS 1.15:102855) Avail: NTIS 6-8, 1989, Proceedings. Toulouse, France, Cepadues-Editions, HC/MF A03 CSCL01/1 1990, p. 85-89. In French. Unsteady rotor wake interactions with the empennage, tail Copyright boom, and other aerodynamic surfaces have a significant influence The technical, commercial and economic aspects of Air France's on the aerodynamic performance of the helicopter, ride quality, operational experience with the Concorde are presented. From and vibration. A Computational Fluid Dynamic (CFD) method for the technical point of view engine reliability from both the computing the aerodynamic interaction between an interacting operational and maintenance aspects is less than that for vortex wake and the viscous flow about arbitrary 2-D bodies was conventional aircraft though dispatch reliability has been developed to address this helicopter problem. The vorticity and satisfactory. Fuel consumption and total operating cost have been flow field velocities are calculated on a body-fitted computational high however, some commercial profitability has been achieved. mesh'using an uncoupled iterative solution. The interacting vortex Specific noise abatement procedures in supersonic flight and wake is represented by an array of discrete vortices which, in around airports forced severe operational restrictions including turn, are represented by a finite core model. The evolution of the subsonic cruise limitations over populated areas. It is concluded interacting vortex wake is calculated by Lagrangian techniques. that the Concorde experience has resulted in valuable operational The flow around circular and elliptic cylinders in the absence of and technical experience that will prove useful in future SST an interacting vortex wake was calculated. These results compare commercial transport designs. R.E.P.

25 03 AIR TRANSPORTATION AND SAFETY

A91-10960 N91-10941*# National Aeronautics and Space Administration. BRITISH AIRWAYS OPERATIONAL EXPERIENCE WITH Langley Research Center, Hampton, VA. CONCORDE AVIATION SAFETY/AUTOMATION PROGRAM OVERVIEW DAVID A. MACDONALD (British Airways, PLC, London, England) SAMUEL A. MORELLO In its Aviation Safety/Automation Program IN: European Symposium on the Future of High Speed Air Conference p 67-73 Oct. 1990 Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Avail: NTIS HC/MF A12 CSCL 01/3 Toulouse, France, Cepadues-Editions, 1990, p. 90-94. The goal is to provide a technology base leading to improved Copyright safety of the national airspace system through the development Since 1976 British Airways has operated Concorde aircraft on and integration of human-centered automation technologies for a variety of routes. During that period more supersonic operating aircraft crews and air traffic controllers. Information on the experience than any other organization has been accumulated, to problems, specific objectives, human-automation interaction, a total of more than 80,000 flying hours. The key to Concorde's intelligent error-tolerant systems, and air traffic control/cockpit success, however, has been in the marketplace where its unique integration is given in viewgraph form. Author capabilities have ensured a niche against which there is currently no real competition. With thirty four scheduled and many charter N91-10946*# National Aeronautics and Space Administration. services operated each week perhaps the greatest challenge will Ames Research Center, Moffett Field, CA. be maintaining the integrity of operation as the aircraft progresses ASSESSING INFORMATION TRANSFER IN FULL MISSION into the later stages of its life. Author FLIGHT SIMULATIONS ALFRED T. LEE In NASA, Langley Research Center, Aviation Safety/Automation Program Conference p 127-130 Oct. 1990 N91-10028# Federal Aviation Administration, Long Beach, CA. Avail: NTIS HC/MF A12 CSCL 01/3 Northwest Mountain Region. Considerable attention must be given to the important topic SEAT DYNAMIC PERFORMANCE STANDARDS FOR A RANGE of aircrew situation awareness in any discussion of aviation safety OF SIZES and flight deck design. Reliable means of assessing this important STEPHEN SOLTIS Aug. 1990 27 p aspect of crew behavior without simultaneously interfering with (DOT/FAA/CT-TN90/23) Avail: NTIS HC/MF A03 the behavior are difficult to develop. Unobtrusive measurement of A summary is presented of the rationale that was used to crew situation awareness is particularly important in the conduct determine the crash impact characteristics for a range of aircraft of full mission simulations where considerable effort and cost is sizes and places emphasis on developing seat dynamic expended to achieve a high degree of operational fidelity. An performance standards that might be used for commuter category unobtrusive method of assessing situational awareness is described size aircraft. The existing crash dynamics data base which includes here which employs a topical analysis of intra-crew twin engine general aviation aircraft, rotorcraft, narrow body and communications. The communications were taken from videotapes wide body transport aircraft were used in this study. The crash of crew behavior prior to, during, and following an encounter with impact characteristic of typical airframe structure will be related to a microburst/windshear event. The simulation scenario re-created the geometric size of the airframe. Author an actual encounter with an event during an approach into Denver Stapleton Airport. The analyses were conducted on twelve N91-10029# Federal Aviation Administration, Atlantic City, NJ. experienced airline crews with the objective of determining the TESTS OF THE GENERAL FIRE SUPPRESSION effect on situation awareness of uplinking ground-based information CONCENTRATE PYROCAP B-136 of the crew during the approach. The topical analysis of crew GEORGE B. GEYER, JOSEPH A. WRIGHT, DUNG DO, and communication was conducted on all references to weather or LAWRENCE HAMPTON Aug. 1990 34 p weather-related topics. The general weather topic was further (DOT/FAA/CT-TN90/21) Avail: NTIS HC/MF A03 divided into weather subtopical references such as surface winds, Fire extinguishing effectiveness of the general fire suppression windshear, precipitation, etc., thereby allowing for an assessment concentrate identified as Pyrocap B-136 was determined by of the relative frequency of subtopic reference during the scenario. laboratory experiments and large-scale fire tests. This agent Reliable differences were found between the relative frequency of demonstrated strong emulsifying properties toward Jet A (kerosene subtopic references when comparing the communications of crews fuel), JP-4 (kerosene and gasoline fuel blend), and avgas (aviation receiving a cockpit display of ground-based information to the gasoline fuel). At 6 percent concentration, Pyrocap B-136 communications of a control group. The findings support the utility extinguished large Jet A fuel fires when applied at the rate of of this method of assessing situation awareness and information 0.052 gallon per minute per square foot. At 30 percent value in full mission simulations. A limiting factor in the use of concentration, the agent was effective in extinguishing magnesium this measure is that crews vary in the amount of intra-crew aircraft wheel fires at a low application rate. Author communications that may take place due to individual differences and other factors associated with crew coordination. This factor must be taken into consideration when employing this measure. N91-10936*# National Aeronautics and Space Administration. Viewgraphs are given. Author Langley Research Center, Hampton, VA. AVIATION SAFETY/AUTOMATION PROGRAM CONFERENCE N91-10951*# National Aeronautics and Space Administration. SAMUEL A. MORELLO, comp. Washington Oct. 1990 270 p Langley Research Center, Hampton, VA. Conference held in Virginia Beach, VA, 11-12 Oct. 1989 FAULT DIAGNOSIS (NASA-CP-3090; L-16840; NAS 1.55:3090) Avail: NTIS HC/MF KATHY ABBOTT In its Aviation Safety/Automation Program A12 CSCL01/3 Conference p 165-174 Oct. 1990 The Aviation Safety/Automation Program Conference - 1989 Avail: NTIS HC/MF A12 CSCL 01 /3 was sponsored by the NASA Langley Research Center on 11 to The objective of the research in this area of fault management 12 October 1989. The conference, held at the Sheraton Beach is to develop and implement a decision aiding concept for Inn and Conference Center, Virginia Beach, Virginia, was chaired diagnosing faults, especially faults which are difficult for pilots to by Samuel A. Morello. The primary objective of the conference identify, and to develop methods for presenting the diagnosis was to ensure effective communication and technology transfer information to the flight crew in a timely and comprehensible by providing a forum for technical interchange of current operational manner. The requirements for the diagnosis concept were identified problems and program results to date. The Aviation by interviewing pilots, analyzing actual incident and accident cases, Safety/Automation Program has as its primary goal to improve and examining psychology literature on how humans perform the safety of the national airspace system through the development diagnosis. The diagnosis decision aiding concept developed based and integration of human-centered automation technologies for on those requirements takes abnormal sensor readings as input, aircraft crews and air traffic controllers. as identified by a fault monitor. Based on these abnormal sensor

26 03 AIR TRANSPORTATION AND SAFETY readings, the diagnosis concept identifies the cause or source of functions and the corresponding objectives. If no success path the fault and all components affected by the fault. This concept exists that can satisfy the critical functions/objectives, then the was implemented for diagnosis of aircraft propulsion and hydraulic next level of critical functions/objectives must be selected and subsystems in a computer program called Draphys (Diagnostic the process repeated. Information is given in viewgraph form. Reasoning About Physical Systems). Draphys is unique in two Author important ways. First, it uses models of both functional and physical relationships in the subsystems. Using both models enables the N91-10955*# National Aeronautics and Space Administration. diagnostic reasoning to identify the fault propagation as the faulted Langley Research Center, Hampton, VA. system continues to operate, and to diagnose physical damage. INFLIGHT REPLANNING FOR DIVERSIONS Draphys also reasons about behavior of the faulted system over MICHAEL PALMER In its Aviation Safety/Automation Program time, to eliminate possibilities as more information becomes Conference p 209-218 Oct. 1990 available, and to update the system status as more components Avail: NTIS HC/MF A12 CSCL01/3 are affected by the fault. The crew interface research is examining Current procedures for handling flight plan diversions can display issues associated with presenting diagnosis information to require too much of the crew's resources. This increases workload the flight crew. One study examined issues for presenting system and may compromise safety and cause delays in modifying the status information. One lesson learned from that study was that flight plan. The goal of NASA Langley Research Center's Diverter pilots found fault situations to be more complex if they involved research program is to develop guidelines for a prototype pilot multiple subsystems. Another was pilots could identify the faulted decision aid for diversions that will reduce cognitive workload, systems more quickly if the system status was presented in pictorial improve safety, increase capacity and traffic flow, and increase or text format. Another study is currently under way to examine aircraft efficiency. The Diverter program has been partitioned into pilot mental models of the aircraft subsystems and their use in five phases, the first three of which were performed under contract diagnosis tasks. Future research plans include piloted simulation by Lockheed Aeronautical Systems Company, Marietta, GA. In evaluation of the diagnosis decision aiding concepts and crew the first two'phases, which have been completed, the system interface issues. Information is given in viewgraph form. . Author requirements and desired functions were defined and a prototype decision-making aid was implemented and demonstrated on a N91-10952*# BBN Systems and Technologies Corp., Cambridge, workstation. In phase three, which is currently under way, the MA. pilot/vehicle interface is being defined and the capability of the FAULT RECOVERY RECOMMENDATION prototype is being improved. In the last two phases, which will be EVA HUDLICKA and KEVIN CORKER In NASA, Langley Research performed at NASA Langley Research Center, the interface will Center, Aviation Safety/Automation Program Conference p 175-185 be implemented, tied into the prototype aiding software, and Oct. 1990 installed in an advanced simulation facility for testing. In addition, Avail: NTIS HC/MF A12 CSCL01/3 significant implementation issues may be addressed through flight Information on Recovery Recommendation System (RECORS) testing on NASA research aircraft. Information is given in viewgraph is given in viewgraph form. The system goal is to provide intelligent form.' • Author aiding for monitoring, diagnosis and response to aircraft system failures. Information is given on levels of abstraction, RECORS N91-10956*# Ohio State Univ., Columbus. implementation, and architecture. Author GRAPHICAL INTERFACES FOR COOPERATIVE PLANNING SYSTEMS N91-10953*# National Aeronautics and Space Administration. PHILIP J. SMITH, CHUCK LAYTON, and C. ELAINE MCCOY (San Ames Research Center, Moffett Field, CA. Jose State Univ., CA.) In NASA, Langley Research Center, Aviation A FUNCTION-BASED APPROACH TO COCKPIT PROCEDURE Safety/Automation Program Conference p 219-228 Oct. 1990 AIDS Avail: NTIS HC/MF A12 CSCL01/3 . ANIL V. PHATAK, PARVEEN JAIN (Expert-EASE Systems, Inc., Based on a cognitive task analysis of 5 airline flight crews in Belmont, "CA.), and EVERETT PALMER In NASA, Langley a simulator study, researchers have designed a testbed for studying Research Center, Aviation Safety/Automation Program Conference computer aids for en route flight path planning. This testbed runs p 187-197 Oct. 1990 : on a Mac II controlling three color monitors, and is being used to Avail: NTIS HC/MF A12 CSCL01/3 study the design of aids for both dispatchers and flight crews. The objective of this research is to develop and test a cockpit Specifically, the research focuses on design concepts for procedural aid that can compose and present procedures that are developing cooperative problem-solving-systems. We use en route appropriate for the given flight situation. The procedure would flight planning (selecting alternate routes or destinations due to indicate the status of the aircraft engineering systems, and the unanticipated weather, traffic, malfunctions, etc.) as the context environmental conditions. Prescribed procedures already exist-for for studying the design of such systems. Researchers are currently normal as well as for a number of non-normal and' emergency exploring three questions in this test environment: (1) When situations, and can be presented to the crew using an interactive interacting with a flight planning aid, how does the role of the cockpit display. However, no procedures are prescribed or pilot influence overall system performance; (2) Can the architecture recommended for a host of plausible flight situations involving for a cooperative planning system be built around Sacerdoti's multiple malfunctions compounded by adverse environmental (1983) concept of an abstraction hierarchy, where the pilot can conditions. Under these circumstances, the cockpit procedural aid interact with the system at many different levels of detail (but must review the prescribed procedures for the individual malfunction where the computer aid by default handles lower level details (when available), evaluate the alternatives or options, and present that the pilot has chosen not to deat with); and (3) Can graphical one or more composite procedures (prioritized or unprioritized) in displays and direct manipulation of these displays provide response to the given situation. A top-down function-based perceptual enhancements (Larkin and Simon, 1987) of the pilot's conceptual approach towards composing and presenting cockpit problem-solving activities. Information is given in viewgraph form. procedures is being investigated. This approach is. based upon Author the thought process that an operating crew must go through while attempting to meet the flight objectives given the current flight N91-10961*# National Aeronautics and Space Administration. situation. In order to accomplish the flight objectives, certain critical Langley Research Center, Hampton, VA. functions must be maintained during each phase of the flight, INFORMATION MANAGEMENT using the appropriate procedures or success paths. The viability WENDELL RICKS and KEVIN CORKER (BBN Systems and of these procedures depends upon the availability of required Technologies Corp., Cambridge, MA.) In its Aviation resources. If resources available are not sufficient to meet the Safety/Automation Program Conference p 275-288 Oct. 1990 requirements, alternative procedures (success paths) using the Avail: NTIS HC/MF A12 CSCL 01/3 available resources must be constructed to maintain the critical Primary Flight Display (PFD) information management and

27 03 AIR TRANSPORTATION AND SAFETY cockpit display of information management research is presented The problem of wind shear in aviation was addressed. On the in viewgraph form. The information management problem in the basis of a suitable safety criterion which relates the aircraft's energy cockpit, information management burdens, the key characteristics deviation to a permitted energy deviation level, uncontrolled, of an information manager, the interface management system controlled and manual landing approach are analyzed. The wind handling the flow of information and the dialogs between the system disturbances employed are simplified simulations of horizontal wind and the pilot, and overall system architecture are covered. shears, vertical winds and thunderstorm conditions. From the Author description of the repercussions of wind shear on the aircraft's energy budget, theoretical solutions for open/closed loop control N91-10962*# National Aeronautics and Space Administration. producing increased flight safety are derived. Suitable measurement Langley Research Center, Hampton, VA. and filtering methods are selected. Advantages over conventional A FLIGHT TEST FACILITY DESIGN FOR EXAMINING DIGITAL flight directors are exhibited by the concrete facilities for decreasing INFORMATION TRANSFER wind shear effects. The use of energy and performance error CHARLES E. KNOX In its Aviation Safety/Automation Program signals from instruments modified in relation to conventional Conference p 289-296 Oct. 1990 specification give improvement in manual flight. Experimental Avail: NTIS HC/MF A12 CSCL 01/3 investigations using a cockpit simulator prove that wind shear Information is given in viewgraph form on a flight test facility hazard can be reduced by suitable instrumentation. ESA design for examining digital information transfer. Information is given on aircraft/ground exchange, data link research activities, data link display format, a data link flight test, and the flight test setup. 04 Author

N91-10963# Allgemeiner Deutscher Automobil-Club-e.V., Munich AIRCRAFT COMMUNICATIONS AND NAVIGATION (Germany, F.R,)- Luftrettung. AIR RESCUE IN THE FEDERAL REPUBLIC OF GERMANY Includes digital and voice communication with aircraft; air navigation [LUFFTRETTUNG IN DER BUNDESREPUBLIK DEUTSCHLAND] systems (satellite and ground based); and air traffic control. INGO KARGER 1990 7 p In GERMAN (ETN-90-97878) Avail: NTIS HC/MF A02 The air rescue system currently developed in the Federal N91-10030 National Aerospace Lab., Tokyo (Japan). Republic of Germany is such that any human being living there THE ESTABLISHMENT AND PERFORMANCE TEST OF PAPI can be rescued within 8 to 15 minutes, using a rescue helicopter. (PRECISION APPROACH PATH INDICATOR) SYSTEM FOR The origin and operation of the rescue system are explained. The NAL STOL AIRCRAFT same rescue system is being developed in East Germany. ESA YOSHITAKA MURAKAMI, YUSHI TERUI, TAKESHI HANAMATSU, KENJI SAITO, SHINTARO YOKOYAMA, and TOSHIHARU N91-10964*# Atlantic Research Corp., Landover, MD. INAGAKI Jan. 1988 48 p In JAPANESE; ENGLISH summary Professional Services Group. (NAL-TM-579; ISSN-0452-2982; JTN-90-80007) Avail: NTIS CURRENT EMERGENCY LOCATOR TRANSMITTER (ELT) HC/MF A03 DEFICIENCIES AND POTENTIAL IMPROVEMENTS UTILIZING Flight tests of NAL QSTOL experimental aircraft are being TSO-C91A ELTS Report, 1988-1990 conducted at Gifu airfield. The PAPI (Precision Approach Path BERNARD J. TRUDELL and RYLAND R. DREIBELBIS Oct. Indicator) system was placed at the left side of runway 28 at Gifu 1990 108 p airfield as a visual approach guidance aid both STOL and CTOL (Contract NASW-4228; NASW-4518) landings. This system is composed of eight-light units arranged in (NASA-CR-4330; NAS 1.26:4330) Avail: NTIS HC/MF A06 a line perpendicular to the runway. The beam angle of four units' CSCL 01/3 is set at six degrees for STOL approach and that of the other An analysis was conducted of current ELT problems and four units is set at three degrees for CTOL approach. The potential improvements that could be made by employing the establishment and performance test results of the PAPI system TSO-C91a ELTs to replace the current TSO-C91 ELTs. The scope are summarized. NASDA of the study included the following: (1) validate the problems; (2) determine specific failure causes; (3) determine false alarm causes; N91-10031 National Aerospace Lab., Tokyo (Japan). (4) estimate improvements from TSO-C91a; (5) estimate benefits APPLICATION OF FLIGHT PATH RECONSTRUCTION from replacement of the current ELTs; and (6) determine need ALGORITHMS FOR FLIGHT DATA OF HELICOPTER and benefits for improved ELT inspection and maintenance. A SHUICHI SASAKI Mar. 1988 25 p In JAPANESE; ENGLISH detailed comparison between the two requirements documents summary (TSO-C91 and -91 a) was made to assess improved performance (NAL-TM-582; ISSN-0452-2982; JTN-90-80010) Avail: NTIS of the ELT in each category of failure cause and each cause of HC/MF A03 false alarms. The comparison and analysis resulted in projecting The maximum-likelihood algorithm, the Kalman filter, and a success of operation rate approximately 3 times the current smoother algorithms were applied to real flight data from a CH-47 rate and a reduction in false alarms to 0.25 of those generated helicopter (two flights) to estimate motion (attitude, position, and by TSO-C91 ELTs. These improvements led to a projection of velocity) and sensor parameters (gains and biases of the rate benefits of approximately 25 additional lives to be saved each gyros and accelerometers) of the craft. Performances of the year with TSO-C91a ELTs and an improved inspection and algorithms were compared. Some attempts were also made to maintenance program. Author estimate sensor noise parameters. NASDA

N91-10965# European Space Agency, Paris (France). N91-10032# Federal Aviation Administration, Washington, DC. CONTRIBUTIONS TO THE IMPROVEMENT OF FLIGHT NATIONAL AIRSPACE SYSTEM: IN-FLIGHT ASSISTANCE SAFETY IN WIND SHEAR OPERATIONAL CONCEPT REINHARD KOENIG (Deutsche Forschungs- und Versuchsanstalt 27 Jul. 1989 38 p fuer Luft- und Raumfahrt, Brunswick, Germany, F.R.) Aug. 1990 (PB90-233115; NAS-SR-1328) Avail: NTIS HC/MF A03 CSCL 193 p Transl. into ENGLISH of Beitraege zur Erhoehung der 17/7 Flugsicherheit in Windscherungen (Brunswick, Fed. Republic of This operational concept describes how in-flight assistance will Germany, DFVLR), Dec. 1988 186 p Original language document be delivered in the National Airspace System (NAS). It is intended was announced as N89-25144 as a tool for systems designers, analysts, and operational test (ESA-TT-1141; DFVLR-FB-88-49; ETN-90-98003) Avail: NTIS planners in determining if and how well the NAS design and its HC/MF A09 implementation meet the NAS requirements for in-flight assistance.

28 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

In addition, management and technical personnel of the FAA and DAVID H. WILLIAMS In its Aviation Safety/Automation Program other involved organizations are provided with a general description Conference p 261-269 Oct. 1990 of how the In-flight Assistance service of the NAS operates. Avail: NTIS HC/MF A12 CSCL 17/7 Author Information on a time-based aircraft/air traffic control (ATC) operations study is given in viewgraph form. Study objectives are N91-10033# Federal Aviation Administration, Atlantic City, NJ. to develop and evaluate procedures for incorporating 4D-equiped OPERATIONAL EVALUATION OF INITIAL DATA LINK AIR aircraft into a 4D ATC system, determine the impact on the system TRAFFIC CONTROL SERVICES. VOLUME 2: APPENDICES of dissimilar airborne and ground 4D speed strategies, and evaluate Final Report the effectiveness of airborne time guidance. Information is given NICHOLAS J. TALOTTA, CLARK SHINGLEDECKER, and MIKE on future plans, separation conflict induced by dissimilar speed REYNOLDS (Midwest Systems Research, Inc., Dayton, OH.) Feb. schedules, and airborne 4D procedures. Author 1990 207 p (DOT/FAA/CT-90/1-VOL-2) Avail: NTIS HC/MF A10 N91-10966# National Aerospace Lab., Tokyo (Japan). STOL The results of an operational evaluation of Initial Data Link Air Aircraft Project Team. Traffic Control (ATC) Services are detailed. The Operational FLIGHT EVALUATION TEST OF THE PAPI (PRECISION Evaluation was conducted at the Federal Aviation Administration APPROACH PATH INDICATOR) SYSTEM (FAA) Technical Center utilizing the Data Link test bed. Initial KEIJI TANAKA, YUUSHI TERUI, and TOSHIHARU INAGAKI Jul. Data Link services were evaluated in order to identify service 1988 14 p In JAPANESE; ENGLISH summary delivery methods which optimize controller acceptance, perfor- (NAL-TM-592; ISSN-0452-2982; JTN-90-80135) Avail: NTIS mance, and workload. Author HC/MF A03 The National Aerospace Laboratory (NAL) quiet short takeoff and landing (QSTOL) experimental aircraft, ASUKA, is being tested N91-10034# Federal Aviation Administration, Atlantic City, NJ. at Gifu Airfield. Flight tests were conducted to evaluate the DIFFERENTIAL GLOBAL POSITIONING SYSTEM (DGPS) TEST Precision Approach Path Indicator (PAPI) system, which Gifu Airfield PLAN Technical Report, Nov. 1989 - May 1990 recently installed. In order to support the ASUKA's flight test L. FRANK PERSELLO Aug. 1990 16 p program, this PAPI has been designed to provide two reference (DOT/FAA/CT-TN90/15) Avail: NTIS HC/MF A03 approach path angles: three degrees (conventional takeoff and The Federal Aviation Administration (FAA) Technical Center landing type) and six degrees (STOL type). The flight evaluation will conduct Differential Global Positioning System (GPS) tests to of the PAPI is evaluated here. The NAL experimental airplane, address the demands for high levels of accuracy in the terminal B65, in which a high-resolution type video tape recorder (VTR) area. The tests employed a Convair 580 (CV-580) and two Motorola camera was installed, was utilized to obtain images of PAPI lights. Eagle Mini Rangers. With the advent of the maturing GPS The tracing radar system on the ground recorded the traces of constellation, the FAA is assuming a more intensive stance in the 865 position. VTR images and radar data were then addressing the many questions/problems associated with GPS. synchronized to confirm setting angles of PAPI lighting units, which These Differential GPS -.tests investigate the obtainable accuracy can be estimated by the aircraft positions at the instant of color under static and dynamic conditions. The static tests will employ transition of each PAPI light. The results of the analysis as well surveyed points as a base line. The dynamic tests will incorporate as pilot comments, such as that PAPI has decreased pilot workload, terminal area flightpaths and non-precision approaches using a proved the effectiveness and performance of the PAPI system. laser tracker as a base line. The Differential tests will be conducted NASDA in an effort to build an FAA Differential GPS data base to aid in addressing GPS questions/problems. Author N91-10967# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seine (France). Guidance and Control N91-10957*# National Aeronautics and Space Administration. Panel. Ames Research Center, Moffett Field, CA. AIRCRAFT TRAJECTORIES: COMPUTATION, PREDICTION, ATC AUTOMATION CONCEPTS CONTROL, VOLUME 1. PART 1: FUNDAMENTALS. PART 2: HEINZ ERZBERGER In NASA, Langley Research Center, Aviation FLIGHT IN CRITICAL ATMOSPHERIC CONDITIONS. PART 3: Safety/Automation Program Conference p 231-247 Oct. 1990 IMPACT OF NEW ON-BOARD TECHNOLOGIES ON AIRCRAFT Avail: NTIS HC/MF A12 JDSCL 01/3 OPERATION Information on the design of human-centered tools for terminal ANDRE BENOIT, ed. Mar. 1990 267 p In ENGLISH and area air traffic control (ATC) is given in viewgraph form. Information FRENCH is given on payoffs and products, guidelines, ATC as a team (AGARD-AG-301 -VOL-1 -PT-1 -3; ISBN-92-835-0547-6; process, automation tools for ATF, and the traffic management AD-A223568) Copyright Avail: NTIS HC/MF A12; Non-NATO advisor. Author Nationals requests available only from AGARD/Scientific Publications Executive N91-10958*# National Aeronautics and Space Administration. This volume (part of a set of three) is composed of a preface Ames Research Center, Moffett Field, CA. and 11 papers covering respectively: fundamentals - general TIME-BASED OPERATIONS IN AN ADVANCED ATC outline, optimal trajectories, and nonlinear models of aircraft; flight ENVIRONMENT in critical atmospheric conditions - genesis of wind and influence STEVEN M. GREEN In NASA, Langley Research Center, Aviation on airplane trajectories, flight control in windshear, and flight Safety/Automation Program Conference p 249-260 Oct. 1990 simulation; and impact of new on-board technologies on aircraft Avail: NTIS HC/MF A12 CSCL 17/7 operation - flight management in air transport, and crew/automation Information on time-based operations in an advanced air traffic interface. control (ATC) environment is given in viewgraph form. The objectives are to develop and evaluate procedures and clearances N91-10968*# Rice Univ., Houston, TX. Aero-Astronautics for 4D equipped aircraft, study the effect of dissimilar airborne Group. and ground based speed strategies, and evaluate the effectiveness OPTIMAL TRAJECTORIES OF AIRCRAFT AND SPACECRAFT and acceptability of ATC automation tools. Information is given on A. MIELE In AGARD, Aircraft Trajectories: Computation, ATC simulation, ATC automation tools, Denver arrival airspace, Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Flight time-based ATC procedures, and future plans. Author in Critical Atmospheric Conditions. Part 3: Impact of New On-Board Technologies on Aircraft Operation 56 p Mar. 1990 Sponsored N91-10959*# National Aeronautics and Space Administration. in part by Boeing Commercial Airplane Co.; Air Line Pilots Langley Research Center, Hampton, VA. Association, International; United States Aviation Underwriters; and TIME-BASED AIRCRAFT/ATC OPERATIONS STUDY Boeing Military Airplane Development

29 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

(Contract NAG1-516; JPL-956415) airport capacity needs. The committee was charged with four tasks: Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals (1)'to'examine long-term airport capacity needs and measures to requests available only from AGARD/Scientific Publications me^t'these needs; (2) to formulate alternative strategies reflecting Executive CSCL 17/7 • varying^ assumptions about the growth'of air traffic and intercity Work done on algorithms for the numerical solutions of optimal travel demand, technological development, government roles, and control problems and their application to the computation of optimal institutional arrangements;'(3) to identify the advantages and flight trajectories of aircraft and spacecraft is summarized. General disadvantages of these strategies; and (4) to recommend strategies considerations on calculus of variations, optimal control, numerical for further analysis and evaluation by FAA. The committee identified algorithms; and applications of these algorithms to real-world an array of actions or options that could be taken to meet demand; problems are presented. The sequential gradient-restoration Seven strategies, made up of various combinations of these algorithm (SGRA) is examined for the numerical solution of'optimal options, were devised and assessed under three growth scenarios. control problems of the. Bolza type. Both the primal formulation These .scenarios, designated High Growth, Maturing Economy.'and and the dual formulation are discussed. Aircraft trajectories,- in Economic Difficulty; embrace a range of plausible assumptions particular, the application of the dual sequential gradient-restoration about .the state of the economy, the cost of air travel, propensity algorithm (DSGRA) to the determination of optimal flight trajectories for travel, and technological .innovation in air and surface in the presence of windshear are described. Both take-off transportation. Each is described. The strategies are as follows: trajectories and abort landing trajectories are discussed. Take-off (1) continue on present course; (2) build more airports; (3) centralize trajectories are optimized by minimizing the peak deviation of the system management; (4) build an expanded, centrally managed absolute path inclination from a reference .value. Abort landing system; (5) let the market decide; (6) reconfigure the airport system; trajectories are optimized by minimizing the peak drop of altitude and (7) revolutionize the intercity transportation technology. The from a reference value. Abort landing trajectories are optimized' study evaluates the strategies suggested. . Author by minimizing the peak drop of altitude from a reference value. The survival capability of an aircraft in a .severe windshear is N91-10982# European Organization for the Safety of Air discussed, and the optimal trajectories are found to be superior Navigation, Brussells (Belgium). Engineering Directorate. to both constant pitch trajectories and maximum angle, of attack OPTIMUM ON-LINE HANDLING OF AIR TRAFFIC OVER trajectories. Spacecraft trajectories, in particular, the application WESTERN EUROPE of the primal sequential gradient-restoration algorithm, (PSGRA) to ANDRE BENOIT and SIP SWIERSTRA . In AGARD, Aircraft the determination of optimal flight trajectories for .aeroassisted Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic orbital transfer are examined. Both the coplanar case and the Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic noncoplanar case are discussed within the frame of three problems: Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained minimization of the total characteristic velocity; minimization of Environment. Surveillance. Part 7: Meteorological Forecasts. Part the time integral of the square of the path inclination; and 8: Aircraft Operation in Air Traffic Handling Simulation .6 p May minimization of the peak heating, rate. The solution of the second 1990 .Presented, at the-International Seminar ATC 2000, problem is called nearly-grazing solution, and its merits are pointed Luxembourg, 23-25 Feb. 1988 ... : out as a useful engineering compromise between energy, Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests requirements and aerodynamics heating requirements. Author available only from AGARD/Scientific Publications Executive For today's airlines, Western Europe is not very large and the N91-10978# Advisory Group for Aerospace Research and flights they make within it do not last very long. Consequently it Development, Neuilly-Sur-Seine (France). Guidance and Control should be possible within such an area as Western Europe to Panel. . . - arrange Air Traffic Control (ATC) clearances and instructions so AIRCRAFT TRAJECTORIES: COMPUTATION, PREDICTION, that any flight will, from departure clearance to touch-down be CONTROL, VOLUME 3. PART 9: BOOK OF ABSTRACTS. conducted in accordance with airline policy and without the changes PART 10: BIBLIOGRAPHY. PART 11: LIST OF to route and profile due to short term planning which are so CONTRIBUTORS v disruptive to air traffic. An approach is recommended for the on-line ANDRE BENOIT, ed. . May 1990 155 p .In .ENGLISH and handling of air traffic over such an area, covering in particular the FRENCH . .,..-• integration of control phases from departure to destination! This (AGARD-AG-301-VOL-3-PT-9-11; ISBN-92-835-0563-8; leads to a central on-iine optimal definition of departure/arrival AD-A225266) Copyright Avail: NTIS HC/MF A08; Non-NATO sequences and essential characteristics of all flights, and a series Nationals requests available only from AGARD/Scientific of regional units to implement the relevant proposals/directives. Publications Executive . • This should provide the optimum .integration of adjacent Zones of This volume (part of a set of three) is composed of;a short Convergence in which the time and altitude at which aircraft enter introduction, a Book of Abstracts of 39 papers included in the and leave each Zone, are precisely controlled and are affected by overall work, an extensive Bibliography which incorporate, in the traffic conditions in.their corresponding space/time sphere of particular,. most of the references cited by the 56 ..authors, and influence. As a prerequisite to the above, a system, is proposed co-authors, and a List of Contributors ordered by countries for the purpose of accurately predicting and controlling the 4-D alphabetically. Both the Bibliography and the List of Contributors trajectory of ;an aircraft over any part of a flight, and in particular are each completed by an adequate index. Author that part which extends from entry into until exit from the airspace of a given control center. . Author N91-10979# National Academy of Sciences -.National Research Council, Washington, DC. Committee for the Study of Long-Term N91-10983# European Organization for the Safety of Air Airport Capacity Needs. , . • Navigation, Brussells (Belgium). Engineering Directorate. AIRPORT SYSTEM CAPACITY STRATEGIC CHOICES THE EUROCONTROL FUTURE ATS SYSTEM CONCEPT AND 1990 145 p ••.•-•••-. THE PROGRAMME OF STUDIES, TESTS, AND TRIALS (SR-226; ISBN-0-309-04956-3; ISSN-0360-859X; LC-90-34787) . . V. VACHIERY In AGARD, Aircraft. Trajectories: Computation, Avail: NTIS HC/MF A07 Prediction, . Control, Volume 2: Air Traffic Handling and The study reports on one element of overall future air transport Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. systems needs: airport capacity. It was requested by the Federal Part 5: Guidance of Aircraft in a Time-Based Constrained Aviation Administration (FAA) to assist in a major undertaking by Environment. Surveillance. Part 7: Meteorological Forecasts. Part FAA and the U.S. Department of Transportation .(DOT) that will 8: Aircraft Operation in Air Traffic Handling Simulation 11 p May lead to a national strategy for meeting long-term capacity needs. 1990 . The Transportation Research ,Board (TRB) of the.National Copyright Avail: NTIS HC/MF A20;. Non-NATO Nationals requests Research Council assembled an'expert committee to provide advice available only, from AGARD/Scientific Publications Executive on alternative strategies that might be adopted to meet long-term . • The era of parallel, uncoordinated development of. ground

30 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION systems and guidance, navigation and communications avionics is capable of displaying 16 colors. A circular display similar to most at an end. The pursuit of optimum economic operating conditions, existing radar scopes could of course be used if it had equivalent coupled with the need to handle an increasing volume of traffic, resolution and color characteristics. The management directives demand that those responsible for Air Traffic Management apply and orders for guidance are presented to the operator, area solutions that easily combine available ground and air technologies. manager or controller of an individual sector as part of the set of Cooperation between pilot and controller actions constitutes one data displayed on the radar surveillance and control scope without of the keystones of the future systems. It is possible to increase the use of additional special tabular displays. Author the capacity and efficiency of air traffic management, while at the same time maintaining essential safety requirements, only by N91-10990# European Organization for the Safety of Air making more use of automation for control planning functions. It Navigation, Brussells (Belgium). Engineering Directorate. is considered that increased automation cannot provide real THE 4-D CONTROL OF CURRENT AIR CARRIERS IN THE advantages, however, unless the accuracy of aircraft trajectory PRESENT ENVIRONMENT: OBJECTIVES, STATUS, AND prediction is greatly improved. This was made clear in the PLANS description of the Future ATS Concept drawn up by ANDRE BENOIT In AGARD, Aircraft Trajectories: Computation, EURO-CONTROL. The Concept is presented in broad outline. Its Prediction, Control, Volume 2: Air Traffic Handling and implementation will call for a number of studies and trials, and a Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. rundown is given of EUROCONTROL's program. The program Part 5: Guidance of Aircraft in a Time-Based Constrained places great emphasis on analysis of the conditions that need to Environment. Surveillance. Part 7: Meteorological Forecasts. Part be met to enable ground systems in future to have available 8: Aircraft Operation in Air Traffic Handling Simulation 7 p May facilities for the acquisition and exploitation of aircraft state vector 1990 parameters. The key aspects of the program are: (1) Improvement Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests of the surveillance system; (2) Improvement of Air/Ground available only from AGARD/Scientific Publications Executive communications (Automatic data link); (3) Increased automation; The accurate control of the time of arrival of aircraft will play and (4) Improvement of evaluation methods by using a realistic an essential role in the efficient conduct of air traffic in terms of representation of the airborne side. Author both economy and capacity. A technique was developed to select efficiently and control accurately each aircraft trajectory inbound N91-10988# Consiglio Nazionale delle Ricerche, Rome (Italy). to medium to high density traffic airports. The selection is made Progetto Finalizzato Trasporti and 1st. di Analisi del Sistemi ed in terms of the overall traffic on the basis of the airline or Informatica. pilot-preferred criterion, either cost, consumption or time, and the OPTIMIZATION MODELS AND TECHNIQUES TO IMPROVE subsequent control is made in a ground/air co-operative manner, AIR TRAFFIC MANAGEMENT using whenever applicable speed and/or track corrections. The LUCIO BIANCO In AGARD, Aircraft Trajectories: Computation, 4-D control is studied along with individual trajectories as applicable Prediction, Control, Volume 2: Air Traffic Handling and to current air carriers in the present environment directly adaptable Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. to future automated air/ground digital communications. The overall Part 5: Guidance of Aircraft in a Time-Based Constrained control loop was simulated in an environment representing in Environment. Surveillance. Part 7: Meteorological Forecasts. Part particular the Belgian airspace configuration, using various flight 8: Aircraft Operation in Air Traffic Handling Simulation 22 p May simulators in conjunction with airline pilots and air traffic controllers. 1990 The results obtained to date make it possible to envisage on-line Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests tests in the near future, aiming at a 10-second accuracy at the available only from AGARD/Scientific Publications Executive runway threshold for current commercial aircraft. Author A survey of earlier works is given with particular emphasis on' optimization models and solution techniques. First, a multilevel N91-10991# Centre d'Etudes et de Recherches, Toulouse model of the different ATC functions is proposed. Then, attention (France). is devoted to the on-line control functions (flow control, on-line FOUR DIMENSIONAL NAVIGATION IN AIR TRAFFIC WITH 4-D strategic control of flights and aircraft sequencing in the terminal NAVIGATION AIRCRAFT [NAVIGATION 4-D EN CIRCULATION area); for each problem, an optimization model is established and AERIENNE AIRCRAFT 4-D NAVIGATION] a solution technique is illustrated. The numerical behavior is also NICOLE IMBERT and MARC J. PELEGRIN In AGARD, Aircraft discussed. Author Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic N91-10989# European Organization for the Safety of Air Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained Navigation, Brussells (Belgium). Engineering Directorate. Environment. Surveillance. Part 7: Meteorological Forecasts. Part THE HIGH-RESOLUTION GRAPHIC DISPLAY: A POSSIBLE 8: Aircraft Operation in Air Traffic Handling Simulation 16 p May MAN/MACHINE INTERFACE FOR A COMPUTER ASSISTED 1990 In FRENCH; ENGLISH summary ATC MANAGEMENT SYSTEM Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests CARLOS GARCIA AVELLO In AGARD, Aircraft Trajectories: available only from AGARD/Scientific Publications Executive Computation, Prediction, Control, Volume 2: Air Traffic Handling Bearing in mind that the waiting times before landing are and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. always increasing while the maximum landing rates are not reached, Part 5: Guidance of Aircraft in a Time-Based Constrained the monitoring of one more parameter during the approach is Environment. Surveillance. Part 7: Meteorological Forecasts. Part suggested. This is, in fact, two speed corrections and one heading 8: Aircraft Operation in Air Traffic Handling Simulation 6 p May correction (Nav. 4D, 3 space dimension + time). The first problem 1990 to be solved is the choice of the mathematical model to be used Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests to simulate a plane. A model as complete as possible (in fact of available only from AGARD/Scientific Publications Executive the 18th order) was the starting point and it was degraded until a An application is described of high resolution graphic display criterion was no longer satisfied. This criterion was a measurement in the field of management and control of air traffic in an extended of the error between the complete model and the degraded model area including a major terminal, the radius of the area being liable along a reference trajectory (Roissy approach) of 54 km extension. to vary from 150 to 300 nm. Reference is made to air traffic It was assumed that the error due to the use of a simpler model management and 4-D guidance techniques for individual aircraft should not reach + or - 320 m at the ILS entry beacon. A 6th in a Zone of Convergence (ZOC) in the knowledge that the graphic order model was declared acceptable. After a number of simulations display techniques are applicable virtually to all systems affording it was shown that corrections must arise after the entrance in the the controller assistance at the decision making level. For the zone of convergence (ZOC) during the flight at constant level purpose of presenting data to the controller, a graphic rectangular (speed correction) in the middle of the descent flown at constant display is employed having a resolution of 1280 by 1024 points, indicated speed, (speed correction) and during the last leg before

31 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION the ILS capture (heading correction). By a management method . Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic using a mathematical model on a fast time basis, an optimal time Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic of arrival at the ILS entrance beacon can be determined, Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained corresponding to an easy to fly trajectory. A model of the Environment. Surveillance. Part 7: Meteorological Forecasts. 'Part atmosphere must be used and it was checked that the robustness 8: Aircraft Operation in Air Traffic Handling Simulation 22 p May of the method (3 corrections) with regard to this model is correct. 1990 It was also checked that the time when the final beacon is reached Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests is not sensitive to the mass of the plane at the entrance point. available only from AGARD/Scientific Publications Executive Author CSCL 17/7 NASA-Langley has been conducting and sponsoring research N91-10992# European Organization for the Safety of Air in airborne energy management for a number of years. During the Navigation, Brussells (Belgium). Engineering Directorate. course of this research, two fundamental techniques for the THE CONTROL OF INBOUND FLIGHTS generation of 4D (fixed time) descent trajectories have emerged ANDRE BENOIT and SIP SWIERSTRA In AGARD, Aircraft as viable candidates for advanced flight management systems. Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic The first technique utilizes speed schedules of constant Mach Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic number transitioning to constant calibrated airspeed chosen Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained empirically to produce minimum fuel usage. The second technique Environment. Surveillance. Part 7: Meteorological Forecasts. Part computes cost optimized speed schedules of variable airspeed 8: Aircraft Operation in Air Traffic Handling Simulation 10 p May developed through application of optimal control theory. Both 1990 techniques have been found to produce reasonable and flyable Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests descent trajectories. The formulation of the algorithms for each available only from AGARD/Scientific Publications Executive technique is evaluated and their suitability for operations in .realistic The basic principles are described of the method to guide conditions is discussed. Operational factors considered include: aircraft accurately down to the runway in a time-of-arrival airplace speed, thrust, and altitude rate constaints; wind, constrained environment. The method is designed to be used in a temperature, and pressure variations; Air Traffic Control altitude, Zone of Convergence context or in any similar advanced Air Traffic speed, and time constaints; and pilot interface and guidance Control (ATC) system characterized by the integration of control considerations. Time flexibility, fuel usage, and airborne phases over an extended area on the one hand and true computer computational requirements were the primary performance assistance to the air traffic controller on the other, Le., assistance measures. Author provided at the decision making level through the automatic generation of guidance advisories. The method includes two closely N91-10995# Massachusetts Inst. of Tech., Cambridge. Flight coupled basic components, namely, a predictor, which computes Transportation Lab. a trajectory once initial conditions and plans are known, and a EXPERT SYSTEMS FOR THE GENERATION OF THERMAL profile manager, which adapts the plans to meet the time constraint AREA ARRIVAL PATHS FOR CIVIL TRANSPORT and generates the guidance directives on the basis of present ROBERT W. SIMPSON In AGARD, Aircraft Trajectories: position, actual surveillance information, aircraft operation and route Computation, Prediction, Control, Volume 2: Air Traffic Handling constraints. Author and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained N91-10993*# National Aeronautics and Space Administration. Environment. Surveillance. Part 7: Meteorological Forecasts. Part Langley Research Center, Hampton, VA. 8: Aircraft Operation in Air Traffic Handling Simulation 14 p May GUIDANCE CONCEPTS FOR TIME-BASED FLIGHT 1990 OPERATIONS Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests DAN D. VICROY In AGARD, Aircraft Trajectories: Computation, available only from AGARD/Scientific Publications Executive Prediction, Control, Volume 2: Air Traffic Handling and Efficiencies can be gained from dynamic scheduling of the Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. takeoff and landing operations for the system of runways at a Part 5: Guidance of Aircraft in a Time-Based Constrained major civil airport. It is then necessary to be able to generate a Environment. Surveillance. Part 7: Meteorological Forecasts. Part conflict-free set of flight paths which implements this schedule, 8: Aircraft Operation in Air Traffic Handling Simulation 12 p May and which can be easily changed. For landing arrival aircraft, these 1990 flight paths start at a known time, point and speed in the descent Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests towards the airport, and end at a reduced speed and time at the available only from AGARD/Scientific Publications Executive outer marker of the final approach to the assigned runway where CSCL 17/7 desired in-trail separations must be achieved. To generate sets of Airport congestion and the associated delays are severe in conflict-free arrival paths, an expert systems computer program today's airspace system and are expected to increase. NASA and finds.and selects a path feasible within the performance limits of the FAA is investigating various methods of alleviating this problem each aircraft from a set of patterns which are easily understandable through new technology and operational procedures. One concept by the human controller. This technique is easily adaptable to the for improving airspace productivity is time-based control of aircraft. geometric characteristics of different terminal areas and runway Research to date has focused. primarily on the development of configurations, and easily accepts rules and procedural limitations time-based flight management, systems and Air Traffic Control which can be specified and implemented by ATC controllers operational procedures. Flight • operations may, however, require themselves, as desired. Author special onboard guidance in order to satisfy the Air Traffic Control imposed time constraints. The results are presented of a simulation N91-10996*# National Aeronautics and Space Administration. study aimed at evaluating several time-based guidance concepts Langley Research Center, Hampton, VA. in terms of tracking performance, pilot workload, and subjective A DESCRIPTION AND EVALUATION OF TIMER: A preference. The guidance concepts tested varied in complexity TIME-BASED TERMINAL FLOW-CONTROL CONCEPT from simple digital time-error , feedback to an advanced LEONARD CREDEUR and WILLIAM R. CAPRON (PRC Kentron, time-referenced-energy guidance scheme: Author Inc., Hampton, VA.) In AGARD, Aircraft Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic Handling and N91-10994*# National Aeronautics and Space Administration. Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. Langley Research Center, Hampton, VA. Part 5: Guidance of Aircraft in a Time-Based Constrained THE 4-D DESCENT TRAJECTORY GENERATION Environment. Surveillance. Part 7: Meteorological Forecasts. Part TECHNIQUES UNDER REALISTIC OPERATING CONDITIONS 8: Aircraft Operation in Air Traffic Handling Simulation 42 p May DAVID.H. WILLIAMS and CHARLES E. KNOX In AGARD, Aircraft 1990

32 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests N91-10998# European Organization for the Safety of Air available only from AGARD/Scientific Publications Executive Navigation, Brussells (Belgium). Enguneering Directorate. CSCL 17/7 AIR TRAFFIC MANAGEMENT AND AIRCRAFT GUIDANCE IN A description of a time-based ATC concept called TIMER A ZONE OF CONVERGENCE (Traffic Intelligence for the Management of Efficient Runway- ANDRE BENOIT and SIP SWIERSTRA In AGARD, Aircraft scheduling) and the results of a fast time and real time com- Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic puter evaluation are presented. The concept was designed to Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic improve the efficiency Of extended terminal area operations (en Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained route approach, transition, and terminal flight to the runway). TIMER Environment. Surveillance. Part 7: Meteorological Forecasts. Part integrates en route metering, fuel efficient cruise and profile 8: Aircraft Operation in Air Traffic Handling Simulation 4 p May descents, terminal sequencing and spacing together with 1990 computer-generated controller aids, in order to fully use runway Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests capacity and improve efficiency of delay absorption. The concept, available only from AGARD/Scientific Publications Executive by using simplified aircraft models, accommodates both 4-D and The basic principles of air traffic management and guidance of non 4-D equipped aircraft and is designed for integration into the individual aircraft in a Zone of Convergence (ZOC) have been manual; voice linked ATC system in an evolutionary manner and presented in previous papers at successive stages in the still be able to accommodate proposed system upgrade features development of the project. These principles are summarized as such as data link and further ground automation. Fast time and is their applicability to the actual operational environment, real time computer simulation results identify and show the effects compatibility with present technology and direct adaptability to and interactions of such key variables as horizon of control, future developments, the quality of the interfaces involving the air metering fix and final approach delivery time errors, aircraft . traffic controller and the aircraft crew and the resultant benefits separation requirements, delay discounting, wind, flight technical to the community in terms of economy, use of available capacity error, and knowledge of aircraft final approach speed. The current and safety. Author ATC system has a runway interarrival-error standard deviation of approx. 26 seconds. Simulation results indicate that, with computer N91-10999# European Organization for the Safety of Air aiding, the runway interarrival-error standard deviation for non 4-D Navigation, Brussells (Belgium). Engineering Directorate. equipped traffic can be reduced to the region of 8 to 12 seconds GROUND-BASED 4-D GUIDANCE OF FLIGHTS IN STRONG if expected final approach speed is known; however, the reduction WIND is only in the region of 16 to 20 seconds if expected final approach ANDRE BENOIT and SIP SWIERSTRA In AGARD, Aircraft speed is unknown. Another major finding is that en route metering Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic fix delivery-error standard deviation should be kept to-less than a Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic number somewhere between 35 to 45 seconds to achieve full Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained runway capacity. This requirement implies the need for either Environment. Surveillance. Part 7: Meteorological Forecasts. Part airborne automation or assistance to the controller since the current 8: Aircraft Operation in Air Traffic Handling Simulation 13 p May manual performance in_ today's en route metering environment is 1990 in the order of 1.5 minutes. : Author Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive N91-10997# Boeing Commercial Airplane Co., Seattle, WA. In strong wind, groundspeed may vary appreciably during a USE OF 4-D RNAV IN TIME-BASED EN ROUTE ARRIVAL turn, just as for example in the case of a landing after a U-turn METERING preceding the localizer intercept. Such conditions are critical for R. L ERWIN and K. H. IZUMI In AGARD, Aircraft Trajectories: maximum use of the runway, -.and render human estimation of Computation, Prediction, Control, Volume 2: Air Traffic Handling aircraft motion extremely difficult. The tests are summarized which and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. were conducted using a ground-based 4D guidance program, Part 5: Guidance of Aircraft in a Time-Based Constrained developed to assist the air traffic controller in maintaining the Environment. Surveillance. Part 7: Meteorological Forecasts. Part predicted landing time sequence with an accuracy better than 10 8: Aircraft Operation in Air Traffic Handling Simulation 19 p May seconds for each arrival. Author 1990 Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests N91-11000*# National Aeronautics and Space Administration. available only from AGARD/Scientific Publications Executive Ames Research Center, Moffett Field, CA. Arrival metering in en route airspace can match the demand A PILOTED SIMULATOR EVALUATION OF A GROUND-BASED rate to the airport acceptance rate. Air traffic control (ATC) is 4-D DESCENT ADVISOR ALGORITHM evolving time-based control techniques to facilitate en route arrival THOMAS J. DAVIS, STEVEN M. GREEN, and HEINZ metering. This allows fuel savings by using speed reduction to ERZBERGER In AGARD, Aircraft Trajectories: Computation, absorb delay. The logic for en route arrival metering: (1) estimates Prediction, Control, Volume 2: Air Traffic Handling and the undelayed landing time of each arrival; (2) assigns the earliest Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. available landing time; and (3) controls each arrival to its terminal Part 5: Guidance of Aircraft in a Time-Based Constrained area arrival (feeder) fix according to the common schedule Environment. Surveillance. Part 7: Meteorological Forecasts. Part developed for all arrivals. The airplane flight management system 8: Aircraft Operation in Air Traffic Handling Simulation 10 p May (FMS), used along with the ATC computer as part of a distributed 1990 Previously announced in IAA as A87-50525 data processing system, can define a minimum fuel cruise-and Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests descent flight profile which is consistent with ATC constraints. A available only from AGARD/Scientific Publications Executive study of four-dimensional area navigation (4D RNAV) operational CSCL 17/7 requirements for use in en route arrival metering has determined A ground-based, four dimensional (4D) descent-advisor the functions and time-guidance accuracies needed for ATC algorithm is under development at NASA-Ames. The algorithm compatible operations. A 4D RNAV capability is most easily combines detailed aerodynamic, propulsive, and atmospheric achieved by wrapping a time navigation capability around a 3D models with an efficient numerical integration scheme to generate FMS. Concepts for controlling a mix of 4D RNAV equipped and 4D descent advisories. The ability is investigated of the 4D descent unequipped aircraft in a time-based en route arrival metering system advisor algorithm to provide adequate control of arrival time for have been the subject of on-going analyses and simulations by aircraft not equipped with on-board 4D guidance systems. A piloted NASA-Ames. The use of 4D RNAV in en route arrival metering simulation was conducted to determine the precision with which operations can save the operator fuel, reduce both pilot and the descent advisor could predict the 4D trajectories of typical controller workload, and rec'uce terminal airspace congestion. straight-in descents flown by airline pilots under different wind Author conditions. The effects of errors in the estimation of wind and

33 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION initial aircraft weight were also studied. A description of the descent N91-11003# National Aerospace Lab., Amsterdam advisor as well as the result of the simulation studies are (Netherlands). presented. Author BAYESIAN MULTI-SENSOR TRACKING FOR ADVANCED AIR TRAFFIC CONTROL SYSTEMS H. A. P. BLOM, R. A. HOGENDOORN, and-F. J. VANSCHAIK N91-11001# European Organization for the Safety of Air In AGARD, Aircraft Trajectories: Computation, Prediction, Control, Navigation, Brussells (Belgium).- Engineering Directorate. Volume 2: Air Traffic Handling and Ground-Based Guidance of THE AIR TRAFFIC CONTROLLER FACING AUTOMATION: Aircraft. Part 4: Air Traffic Handling. Part 5: Guidance of Aircraft CONFLICT OR COOPERATION in a Time-Based Constrained Environment. Surveillance. Part 7: ANDRE BENOIT, SIP SWIERSTRA, and RENE DEWISPELAERE Meteorological Forecasts. Part 8: Aircraft Operation in Air Traffic (Eurocontrol Agency, Brussels, Belgium ) In AGARD, Aircraft Handling Simulation 8 p May 1990 Sponsored by Dutch Civil Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic Aviation Board Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests Handling. Part 5: Guidance of Aircraft in a Time-Based Constrained available only from AGARD/Scientific Publications Executive Environment. Surveillance. Part 7: Meteorological Forecasts. Part An overview is given o1 a Bayesian tracking system tor a 8: Aircraft Operation- in Air Traffic Handling Simulation 7 p May multi-sensor environment. The main modules perform track 1990 Presented at the International Conference NAV 1987, initiation, track continuation arid systematic error estimation, London, England, 29 Sep. - 1 Oct. 1987 respectively. The track continuation module plays for Air Traffic Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests Control the most important role. It consists of a combination of available only from AGARD/Scientific Publications Executive those approximate Bayesian methods that proved to be the most Today, developments in ground-based and on-board efficient for the main problems of track continuation: computers, navigation and digital air/ground/air communications Extended-Kalman filtering for nonlinear dynamics, Probabilistic Data make it possible to envision, for tomorrow, extensive automation Association for unassociated measurements and Interacting- of the overall air traffic control process, always provided that Multiple-Model filtering for sudden maneuvers. Comparisons reliability, safety and responsibilities can be absolutely covered in of this new tracking system with alpha-beta Kalman based and all possible eventualities, however remote. Accordingly, before state-of-the-art tracking systems show its superiority for ap- tomorrow, an appreciable amount of traffic will cross our skies plication to Air Traffic Control surveillance. It provides better and be handled by air traffic controllers without the support of track continuity, more accurate expectations of position and velocity advanced automated tools. Nevertheless, at the same time, the and more complete additional information in the form of probabilities potential of automation will continue to increase. This subject is of modes of flight (turning, accelerating and straight modes) and discussed in the light of the experience gained during the consistent estimates of its own accuracy. With this track development of an approach to the definition, assessment and information, advanced Air Traffic Control systems may better cope testing in an operational environment of a procedure suitable for with the many uncertainties that are inherent to air traffic. guiding aircraft along 4-D trajectories illustrative of the next system Author generation of ATC. The essential aspects are examined of the computer/controller/pilot/aircraft chain of dialogues, placing the emphasis on the interface between the computer and the controller, N91-11004# Technical Univ. of Crete, Athens (Greece). the intelligent interpretation of the surveillance information by the THE USE OF DOWNLINKED MEASUREMENTS TO TRACK computer, the definition, generation, and relay of guidance CIVIL AIRCRAFT directives to the pilot and finally, the use of navigation aids. The C. C. LEFAS In AGARD, Aircraft Trajectories: Computation, integration of the ground-based 4-D guidance and control system Prediction, Control, Volume 2: Air Traffic Handling and messages on a standard ATC radar display is shown, illustrating Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. this for the guidance of flights conducted by SABENA crews Part 5: Guidance of Aircraft in a Time-Based Constrained operating B-737 and DC-10 aircraft. Author Environment. Surveillance. Part 7: Meteorological Forecasts. Part 8: Aircraft Operation in Air Traffic Handling Simulation 21 p May 1990 N91-11002# European Organization for the Safety of Air Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests Navigation, Brussells (Belgium). Engineering Directorate. available only from AGARD/Scientific Publications Executive AIRCRAFT TRAJECTORY RECONSTITUTION ON THE BASIS The use is described of measurements made on board civil OF MULTI-RADAR PLOT INFORMATION aircraft to improve tracking accuracy in air traffic control (ATC) P. VANDERKRAAN In AGARD, Aircraft Trajectories: Computation, systems. The measurements are transmitted to the ground station Prediction, Control, Volume 2: Air Traffic Handling and via the Secondary Surveillance Radar (SSR) mode S data link. Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. First the widely used alpha-beta filter and the first order Kalman Part 5: Guidance of Aircraft in a Time-Based Constrained filter are reviewed. Next the problem of maneuver handling is Environment. Surveillance. Part 7: Meteorological Forecasts. Part described and it is established that significant improvements, in 8: Aircraft Operation in Air Traffic Handling Simulation 2 p May terms of tracking accuracy, are expected when tracking 1990 maneuvering aircraft. The shape of maneuvers is examined using Copyright Avail: NTIS HC/MF A20-, Non-NATO Nationals requests recordings made on board civil aircraft during normal scheduled available only from AGARD/Scientific Publications Executive services. The on-board measurements considered are roll angle, A short description of the various techniques in use for the heading, and true air speed (TAS). Roll angle and the rate of establishment of aircraft reference trajectories is presented. Then change of heading are theoretically equivalent, since they are a description of the principles and operation of the EUROCONTROL related though aircraft velocity. Maneuver tracking filters using program MURATREC (Multi-Radar Trajectory Recpnstitution) either roll angle or heading are described and compared. It is follows, covering in particular: (1) estimation of systematic radar shown that the filter using heading provides a better performance errors; (2) curve fitting by the use of B-splines and dynamically in the event of missing replies, since changes of heading are adaptable spline steps; (3) accuracy of the reconstructed positional eventually detected. Both filters cannot track longitudinally information; and (4) reconstitution of altitude, accelerations and accelerating targets. Next the use of velocity measurements, speed. Applications of the MURATREC program are outlined, derived from TAS and heading, is considered. A filter is described including application for the analysis of radar plot and track that is capable of estimating the wind speed in the vicinity of the accuracy (examples) and possible applications for incident aircraft. The same filter provides satisfactory tracking accuracy investigations, on-line alignment of multi-radar information and during maneuvers and can handle longitudinal accelerations. Under simulation of aircraft trajectories in a given radar environment. monoradar coverage, where the data rate and accuracy are fairly Author constant, the filters reduce to a particularly simple form, that may

34 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

be regarded as an enhanced alpha-beta filter. The performance Simulation 16 p May 1990 of the filters is evaluated using data recorded during normal Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests scheduled services. Author available only from AGARD/Scientific Publications Executive During peak hours almost all major commercial airports operate N91-11005# Service Technique de la Navigation Aerienne, Paris close to their capacity limits. Moreover, the traffic demand often (France). Dept. Radiocommunication et Radioguidage. exceeds the offered capacities leading to more or less stringent CONTRIBUTION OF THE SATELLITE TECHNIQUES TO THE restrictions in slot allocation. The purpose of the fast-time air traffic SURVEILLANCE OF AIR TRAFFIC [L'APPORT DES simulations, was to analyze and assess the performance and the TECHNIQUES SATELLITAIRES A LA SURVEILLANCE DE LA practicability of automated time-based approach concepts, currently NAVIGATION AERIENNE] developed to optimize the terminal area air traffic process with OLIVIER CAREL In AGARD, Aircraft Trajectories: Computation, respect to safety, capacity and economy. The developed program Prediction, Control, Volume 2: Air Traffic Handling and system TASIMD (Terminal Area SIMulation considering the aircraft Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. Dynamics) simulates flight operations of arriving aircraft within a Part 5: Guidance of Aircraft in a Time-Based Constrained terminal area during a specific time interval. TASIMD models all Environment. Surveillance. Part 7: Meteorological Forecasts. Part major elements of a TMA scenario related to the control and 8: Aircraft Operation in Air Traffic Handling Simulation 13 p May operations of automated approach procedures, on the ground and 1990 In FRENCH; ENGLISH summary in the air (e.g., surveillance, control procedures, aircraft dynamics, Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests flight guidance). The aircraft fly along 4D-trajectories, described available only from AGARD/Scientific Publications Executive by a horizontal profile, an altitude profile and a speed profile to The International Civil Aviation Organization asked a special integrate the time element, considering influences on the path committee FANS (Future Air Navigation Systems) to study satellite following accuracy in space and time. Sources of error impact system implementation for communication navigation and are: entry fix time deviation, navigation, wind, airspeed error and surveillance applications. This committee recently issued its final profile management algorithm error. Errors are modeled in report. FANS work is presented and the consequences are Monte-Carlo technique. Two types of automated approach analyzed of satellite system implementation in case of the procedures were developed and analyzed: a variable path speed surveillance of air traffic. The most important element will be control concept (VPSC) and a fixed path speed control concept Automatic Dependent Surveillance (ADS) which implies the (FPSC). Both concepts presume a shared air/ground responsibility automatic air to ground return transmission of various airborne for profile control. Author measured parameters, i.e., mainly aircraft position as supplied by the aircraft navigation equipments. This concept allows a much more efficient air traffic control in every area lacking a ground infrastructure. In continents areas with heavy air traffic, satellites 05 will not substitute the secondary surveillance radar. The new techniques however will allow a flexible design of the ground AIRCRAFT DESIGN, TESTING AND infrastructure. Author PERFORMANCE N91-11007# European Organization for the Safety of Air Navigation, Brussells (Belgium). Engineering Directorate. Includes aircraft simulation technology. INTEGRATION OF AIRCRAFT CAPABILITY IN AIR TRAFFIC HANDLING SIMULATIONS ANDRE BENOIT, SIP SWIERSTRA, and YVES DELNATTE (Belgian A91-10341# Toledo Univ., OH. World Airlines, Brussels.) In AGARD, Aircraft Trajectories: THERMAL ANALYSIS OF ENGINE INLET ANTI-ICING Computation, Prediction, Control, Volume 2: Air Traffic Handling SYSTEMS and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. THEO G. KEITH, JR., KENNETH J. DEWITT (Toledo, University, Part 5: Guidance of Aircraft in a Time-Based Constrained OH), JAMES K. NATHMAN (Analytical Methods, Inc., Redmond, Environment. Surveillance. Part 7: Meteorological Forecasts. Part WA), DONALD A. DIETRICH (General Electric Co., Cincinnati, OH), 8: Aircraft Operation in Air Traffic Handling Simulation 7 p May and KAMEL M. AL-KHALIL Journal of Propulsion and Power 1990 (ISSN 0748-4658), vol. 6, Sept.-Oct. 1990, p. 628-634. Research Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests supported by General Electric Co. and NASA. Previously cited in available only from AGARD/Scientific Publications Executive issue 09, p. 1291, Accession no. A89-25565. refs The incorporation of airline/aircrew/aircraft specific procedures Copyright and performances into simulations and air traffic handling operations is a prerequisite for the next generation of management A91-10956 and control techniques. This matter is analyzed in the light of the CONCORDE - 1958-1975 shortcomings inherent in the present situation, in order to meet G. CORMERY IN: European Symposium on the Future of High operators' demands in terms of capacity and efficiency. A practical Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, approach is then proposed which includes the operators Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. (aircrew/aircraft/avionics) in the overall ground/air/ground control 58-65. loop at development, assessment, validation, and real time Copyright simulation levels. As an illustration of the potential offered, this An overview of Concorde research, design, and development approach is used to assess a ground/air coordinated 4-D guidance evolution is presented. The various airframe geometries considered technique, and the results are summarized. Author for attaining a Mach 2.2 max cruise limit imposed by various temperature limitations are described. Final selection of a delta N91-11008# Technische Univ., Brunswick (Germany, F.R.). Inst. wing plus a foreplane resulted after a number of wing, fuselage of Aeronautics and Astronautics. and empennage combinations were evaluated. Other areas SIMULATION OF AUTOMATED APPROACH PROCEDURES requiring advanced research and design that had to be solved CONSIDERING DYNAMIC FLIGHT OPERATIONS included: jet engine type selection, number and positioning, visibility MANFRED FRICKE and ANDREAS HOERMANN In AGARD, problems in landing and takeoff attitudes that led to adoption of Aircraft Trajectories: Computation, Prediction, Control, Volume 2: the droop nose, systems integration with particular regard to flight Air Traffic Handling and Ground-Based Guidance of Aircraft. Part controls and the automatic flight control system, and the evolution 4: Air Traffic Handling. Part 5: Guidance of Aircraft in a Time-Based of the air intake system to accommodate operation over the entire Constrained Environment. Surveillance. Part 7: Meteorological flight envelope. Finally, a general assessment of Concorde Forecasts. Part 8: Aircraft Operation in Air Traffic Handling commercial operation is presented. R.E.P.

35 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

A91-10957 together with their description in regard with undamped and COMMERCIAL SUPERSONIC OPERATIONS - THIRTEEN artificially damped system. In both cases, stability criteria are YEARS OF EXPERIENCE WITH CONCORDE discussed with special regard to simplified calculation methods. S. J. SWADLING (British Aerospace/Commercial Aircraft/, Ltd., Mass center motion of the revolving rotor is considered using the Filton, England) IN: European Symposium on the Future of High double complex numbers calculations. Author • Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. A91-11724# 66-71. SIMULATION INVESTIGATIONS OF THE HELICOPTER Copyright GROUND RESONANCE [BADANIA SYMULACYJNE This paper is intended to give a brief overview of Concorde REZONANSU NAZIEMNEGO] in-service operations as viewed by the manufacturer. It identifies MAREK S2RAJER Instytut Lotnictwa, Prace (ISSN 0509-6669), the features peculiar to Concorde as a supersonic transport and no. 119, 1989, p. 48-67. In Polish. problems and major incidents encountered during development On the basis of a relatively simply numerical model of the flying and operation. Finally it covers in-service experience and helicopter resonance, a possibility of computer simulation methods identifies the most troublesome items. Author for the solution of complex relevant problems is shown. Sample simulation calculations made on an IBM PC microcomputer using A91-10967 the program given by Szrajer (1989) are presented. In the SST AIRFRAME INTEGRATION FOR A MACH 2 TRANSPORT simulation, a possibility of defects and nonlinearity of some D. COLLARD (Aerospatiale, Division Avions, Paris, France) IN: helicopter construction elements are considered. It is also possible European Symposium on the Future of High Speed Air Transport, to simulate a pilot reaction to a dangerous helicopter vibration Strasbourg, France, Nov. 6-8,1989, Proceedings. Toulouse, France, amplitude increase. Graphical presentation of the results simplifies Cepadues-Editions, 1990, p. 188-198. analysis. To check the assumed model of the resonance, the Copyright results from Zerek (1984), based on analytical calculations and The development of Aerospatiale's ATSF future supersonic accepted in practice, were used. The results indicate that the transport is presented. Initial design methods call for a Mach 2 method can be used for more complex models of the helicopter cruise level to permit constant verification between actual flight ground resonance. . Author experience and new design concepts. Details of aerodynamics, structural design , materials available, and powerplant installation A91-11725# are discussed. Configuration development, cruise lift/drag THE GROUND RESONANCE OF A HELICOPTER WITH A improvement, structural layout, and cockpit design modifications ROTOR OF IDEAL AND APPROXIMATE SYMMETRY are described. Engine selection considerations involving candidate CONSIDERING THE ROTOR-BLADE VIBRATION IN THE engine cycles, engine installation and intake development are also THRUST PLANE [REZONANS NAZIEMNY SMIGLOWCA Z described. The improvements being made in low speed WIRNIKIEM O DOSKONALEJ I PRZYBLIZONEJ SYMETRII Z performance and engine noise emission appear likely to achieve UWZGLEDNIENIEM DRGAN LOPAT W PLASZCZYZNIE today's noise criteria by 2005. R.E.P. CIAGU] LUDWIK ZEREK Instytut Lotnictwa, Prace (ISSN 0509-6669), A91-11715 no. 119, 1989, p. 68-98. In Polish, refs HARRIER - THE NEXT 30 YEARS Basic theoretical problems of the helicopter ground resonance SIMON ELLIOT Flight International (ISSN 0015-3710), vol. 138, with one rotor of an ideal and approximate axis symmetry is Sept. 18, 1990, p. 50-54, 56, 57. discussed. The vibrations of rotor blades in the thrust plane are Copyright considered. Physical and mathematical models of a helicopter and A review of the Harrier aircraft history from the first external influences are shown. Methods of the motion equations vectored-thrust V/STOL flight to today's advanced versions is statement and of their stability investigation are given. Classification presented. The growth and lifting capacity of the aircraft is shown of special cases important in practice is presented. Author to be in great part due to the vectored-thrust engine that has more than doubled in thrust in the thirty years since its first flight. A91-11863# Current Harriers in their various land/sea versions have become X-31 WILL TURN ON A DIME full-fledged combat aircraft capable of carrying military weaponry RICHARD DEMEIS Aerospace America (ISSN 0740-722X), vol. loads that once required long runways just to get off the ground. 28, Oct. 1990, p. 26-29. Sea Harriers are presently operational aboard aircraft carriers of Copyright the U.S., Britain, Spain, and India, and the AV-8B night-attack The current status of the X-31 project is reviewed with particular version of the USMC has been operating since 1989. Some aspects reference to the aims of the project, history of development, and of a study for a supersonic advanced short-takeoff/vertical landing general design concept. The X-31, an Enhanced Fighter aircraft for service early next century are discussed. R.E.P. Maneuverability aircraft, will operate in the low supersonic region (maximum speed Mach 1.3) and engage in aerial combat at angles A91-11723# of attack approaching 70 deg. Wind tunnel test results are HELICOPTER GROUND RESONANCE [REZONANS NAZIEMNY examined, and the future of the project is briefly discussed. V.L SMIGLOWCA] JERZY BOJANOWSKI (Warszawa, Politechnika, Warsaw, Poland) A91-12062 Instytut Lotnictwa, Prace (ISSN 0509-6669), no. 119, 1989, p. 3-47. THE ATF BATTLE SHAPES UP In Polish, refs BILL SWEETMAN Interavia Aerospace Review (ISSN 0020-6512), The description of a helicopter ground resonance given here vol. 45, Oct. 1990, p. 862-865. contains relatively full set of relevant specific topics. For brevity, Copyright the description is constrained to a model of a rotor with n not Basic data for the YF-22/-23 prototypes that will compete in. less than 3 rigid blades fixed elasticly to the rotor hub. Simplified the Advanced Tactical Fighter competition are presented. Though model of the tensor rigidity of an undercarriage, useful mainly to both aircraft will be using the same engines and other similarities ski landing gear, is assumed. Evaluation of motion equations of a exist such as avionics systems designed to use the same single blade is given. Their linearization and superposition lead to architecture, the two are radically different. The YF-22 has a single the motion equations of the whole rotor in the scope which is body structure beneath a shoulder-mounted wing, engines set close needed to complete all motion equations used in resonance together, two large canted vertical tails and separate horizontal description. Also, the motion equations of a fuselage connected stabilizers. The wing planform is described as a trapezoid/clipped to a ski landing gear situated on the ground is presented. Exact delta with some forward sweep on the trailing edge. The YF-23 is solutions of the set of differential motion equations are given considerably longer with the engine nacelles and forward fuselage

36 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

blended together in the center of a midset wing having a diamond A91-12894*# California Univ., Los Angeles. shape planform with equal sweep back on the leading and trailing INFLUENCE OF UNSTEADY AERODYNAMICS ON ROTOR edges. A pair of V-tails provides pitch and yaw control, and four BLADE AEROELASTIC STABILITY AND RESPONSE large trailing edge surfaces act as flaperons and speedbrakes. P. P. FRIEDMANN (California, University, Los Angeles) and L. H. Stealth features are given high priority in both aircraft as specified ROBINSON (McDonnell Douglas Helicopter Co., Mesa, AZ) by the USAF. Possibly the most significant difference in the two (International Conference on Rotorcraft Basic Research, 2nd, designs is the incorporation of thrust vectoring in the YF-22. This College Park, MD, Feb. 16-18, 1988, Proceedings) AIAA Journal paper also provides some description of weapons systems and (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1806-1812. Previously bays. R.E.P. cited in issue 22, p. 3645, Accession no. A88-51765. refs (Contract NAG2-209; NAG2-477) Copyright A91-12063 A SUPERLATIVE FROM SUKHOI - THE SU-27 A91-12919 ROY BRAYBROOK Air International (ISSN 0306-5634), vol. 39, DIAGNOSTICS OF AVIATION ELECTRIC MACHINES Oct. 1990, p. 203-208. [DIAGNOSTIROVANIE AVIATSIONNYKH ELEKTRICHESKIKH Copyright MASHIN] A background review of the Sukhoi design bureau is first VLADIMIR N. POTAPOV Moscow, Izdatel'stvo Transport, 1989, presented along with the progressive aircraft types that have led 104 p. In Russian, refs to the present SU-27 fighter-interceptor. The original design of Copyright this aircraft had a fixed wing of moderate sweep, and the fuselage The operating conditions of electric machines used in aviation was raised above the wing to leave a channel between the engines are analyzed, as are the major causes of failures, physical in which two large air-to-air missiles could be mounted in tandem. processes associated with the occurrence of defects, and A comparison with the F-14/15 fighters appears to place them on characteristic symptoms preceding failures. A method is proposed a roughly equal performance footing. However, the SU-27 has the for the experimental evaluation of the parameters of diagnostic added advantage of the agility and lift/drag ratio benefits of a models. Structural schemes are presented which illustrate the FBW system and longitudinal instability. Some additional principles of implementation of diagnostic methods. Various aspects information is given in regard to weaponry and avionics as well of the automation of diagnostic procedures using computerized as a detailed cutaway diagram. R.E.P. measurement and signal processing systems are discussed. V.L.

N91-10038 National Aerospace Lab., Tokyo (Japan). STOL A91-12165 Aircraft Project Group. EXTENSIVE MD-11 AUTOMATION ASSISTS PILOTS, CUTS THE ACTUATOR FOR THE LOW-NOISE STOL TEST PLANE WORKLOAD FLIGHT CONTROL SYSTEM AND ITS DEVELOPMENT TEST DAVID HUGHES Aviation Week and Space Technology (ISSN [TEISOUON SUTORU JIKKENKI HIKOU SEIGYO SHISUTEMU 0005-2175), vol. 133, Oct. 22, 1990, p. 34-41, 45. YOU AKUCHUETA TO SONOKAIHATSU GIJUTSU SHIKEN] Copyright May 1987 172 p In JAPANESE The automated flight management system incorporated in the (NAL-TM-574; ISSN-0452-2892; JTN-90-80003) Copyright MD-11 aircraft includes such advanced features as automatic Avail: NTIS HC/MF A08 augmentation in pitch, roll and yaw. An autothrottle portion of the In total, 54 actuators (28 types) are used for the flight control automatic flight system keeps the pilot from unintentionally flying system of the low-noise experimental STOL craft. Prior to too fast or too slow in a given configuration. The system also application to the experimental craft, a development technology provides automatic navigation in both lateral and vertical test was carried out on the parts other than the C-1 common dimensions and will control optimum speeds and altitudes, including parts of these actuators. The test was composed of a function step climbs to cruise altitude, to achieve the most efficient fuel and performance test which consisted in confirming the adaptability consumption on a particular route. In the cockpit, a dynamic fuel of the parts to the requirements of the craft on the one hand, system diagram is displayed that tracks fuel levels in the various and of a weather proofing test which consisted in verifying their tanks and notes with changing colors when fuel pumps are on or adaptability to the operational circumstances of the craft on the off. Any portion of the automated system can be converted to other hand. This report explains the general characters of all the manual operation as desired. The systems display features a actuators used initially for the experimental STOL craft as well as cathode ray tube that presents all of the data necessary for an the summary of the results of the development technology test ICAO position report, plus additional useful information. This paper carried out. NASDA also provides a technical table of MD-11 aircraft and engine details. R.E.P. N91-10039*# College of William and Mary, Williamsburg, VA. Dept. of Computer Science. AUTOMATIC DETERMINATION OF FAULT EFFECTS ON A91-12224# AIRCRAFT FUNCTIONALITY Semiannual Progress Report, 17 MOTION ANALYSIS OF RPRVS USING ON-BOARD AND Feb. - 17 Aug. 1989 GROUND-BASED MEASUREMENTS STEFAN FEYOCK 1989 40 p AKIRA SAKURAI and SHUICHI NAKAYAMA Kyushu University, (Contract NCC1-122) Technology Reports (ISSN 0023-2718), vol. 63, Aug. 1990, p. (NASA-CR-181352; NAS 1.26:181352) Avail: NTIS HC/MF A03 343-349. In Japanese, with abstract in English, refs CSCL01/3 A low-cost flight test system using RPRVs (Remotely-Piloted The problem of determining the behavior of physical systems Research Vehicles) is under development. In this system, the subsequent to the occurrence of malfunctions is discussed. It is acceleration and angular velocity of aircraft are detected with established that while it was reasonable to assume that the most on-board acceleration and angular rate sensors with a high important fault behavior modes of primitive components and simple sampling rate, while the flight path and attitude are photographically subsystems could be known and predicted, interactions within determined using a pair of optical trackers with a much lower composite systems reached levels of complexity that precluded sampling rate. A method of combining these two types of data the use of traditional rule-based expert system techniques. has been developed, in which the initial values and several other Reasoning from first principles, i.e., on the basis of causal models sensor-related parameters necessary for the integration of the of the physical system, was required. The first question that arises acceleration and angular velocity are determined in such a way is, of course, how the causal information required for such that the calculated flight path and attitude of the aircraft show reasoning should be represented. The bond graphs presented here best least-square fit with the tracker results. Author occupy a position intermediate between qualitative and quantitative

37 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

models, allowing the automatic derivation of Kuipers-like qualitative DEREK G. ASTRIDGE, ed. and M. SAVAGE, ed. (Akron Univ., constraint models as well as state equations. Their most salient OH.) Jun. 1990 83 p feature, however, is that entities corresponding to components (AGARD-R-775; ISBN-92-835-0540-9; AD-A226496) Copyright and interactions in the physical system are explicitly represented Avail: NTIS HC/MF A05; Non-NATO Nationals requests available in the bond graph model, thus permitting systematic model updates only from AGARD/Scientific Publications Executive to reflect malfunctions. Researchers show how this is done, as This is a portion of a intended volume on Transmission Systems well as presenting a number of techniques for obtaining qualitative for Power Transfer in Helicopters and Turboprops. Lessons learned information from the state equations derivable from bond graph from accident data of large civil transport helicopters are examined, models. One insight is the fact that one of the most important as are recent improvements in design and component technology, advantages of the bond graph ontology is the highly systematic including recommendations and safety benefits achievable by approach to model construction it imposes on the modeler, who monitoring systems. A statistical analysis was made of drive system is forced to classify the relevant physical entities into a small life and reliability. A proper evaluation was made of drive systems number of categories, and to look for two highly specific types of design and the understanding and control of mean life and life interactions among them. The systematic nature of bond graph scatter of a drive system at the design stage. model construction facilitates the process to the point where the guidelines are sufficiently specific to be followed by modelers who N91-10043# Astridge (Derek) and Associates, Langport are not domain experts. As a result, models of a given system (England). constructed by different modelers will have extensive similarities. HELICOPTER TRANSMISSIONS: DESIGN FOR SAFETY AND Researchers conclude by pointing out that the ease of updating RELIABILITY bond graph models to reflect malfunctions is a manifestation of DEREK G. ASTRIDGE In AGARD, Rotorcraft Drivetrain Life the systematic nature of bond graph construction, and the regularity Safety and Reliability p 1-34 Jun. 1990 Previously announced of the relationship between bond graph models and physical in IAA as A90-20608 reality. ' Author Copyright Avail: NTIS HC/MF A05; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive N91-10040*# Ohio State Univ., Columbus. Dept. of Aeronautical An analysis of the UK CAA's world wide helicopter accident and Astronautical Engineering. data indicates that transmissions accounted for 22. percent of PROJECT HYBUJET Final Report potentially airworthiness related accidents in 'civil helicopters of TOM RAMSAY, BILL COLLET, KARYN IGAR, DEWAYNE more than 4550 kg gross weight. An evaluation is made of design KENDALL, DAVE MIKLOSOVIC, ROBYN REUSS, MARK RINGER, and technology advancements over the last decade which should and TONY SCHEIDT May 1990 166 p Prepared in cooperation benefit helicopter transmission safety and reliability. These with Universities Space Research Association, Houston, TX encompass improved steels with superior fatigue performance, S/N Sponsored by NASA curve refinement, computer aided design analysis systems, (NASA-CR-187011; NAS 1.26:187011) Avail: NTIS HC/MF A08 CAD/CAM, improved lubricants and filtration systems, and expert CSCL 01/3 systems retaining a collective memory with regard to design A conceptual Hypersonic Business Jet (HyBuJet) was examined. practices'relationship to service experience.; E.R. The main areas of concentration include: aerodynamics, propulsion, stability and control, mission profile, and atmospheric heating. In N91-10044# Akron Univ., OH. order to optimize for cruise conditions, a waverider configuration DRIVE SYSTEM LIFE AND RELIABILITY was chosen for the high lift drag ratio and low wave drag. The M. SAVAGE In AGARD, Rotorcraft Drivetrain Life Safety and leading edge and lower surface of a waverider was mapped out Reliability p 35-71 Jun. 1990 from a known flow field and optimized for cruising at Mach 6 and Copyright Avail: NTIS HC/MF A05; Non-NATO Nationals requests at high altitudes. The Shockwave generated by a waverider remains available only from AGARD/Scientific Publications Executive attached along the entire leading edge, allowing for a larger Fuel efficiency is an important objective in aircraft propulsion. compression along the lower surface. Three turbofan ramjets were In design, the requirements of light weight and high reliability chosen as the propulsion of the aircraft due to the combination conflict. Designers use highly stressed, high quality alloy steels in of good subsonic performance along with high speed propulsive the major load bearing components to resolve the conflict. One capabilities. A combination of liquid silicon convective cooling for estimate for the service needs of a drive system comes from its the leading edges with a highly radiative outer skin material was life and reliability models. The design objectives of long life between chosen to reduce the atmospheric heating to acceptable level. repairs and high reliability are design goals. The statistics of drive Author system life and reliability are discussed. The statistics develop reliability models for repair prediction. The modes of failure which N91-10041*# Ohio State Univ., Columbus. Dept. of Aeronautical are the basis for these models are also discussed. Coverage of and Astronautical Engineering. the two parameter Weibull distribution model for component and OVRHYP, SCRAMJET TEST AIRCRAFT Final Report system life is detailed. Similar coverage is made of the Miner J. ASLAN, T. BISARD, S. DALLINGA, K. DRAPER, G. HUFFORD, Palmgren load-life model. Based on this model, the theory of W. PETERS, and J. ROGERS May 1990 127 p Prepared in mission spectrum averaging is presented. Mission spectrum cooperation with Universities Space Research Association, averaging determines the equivalent constant load which has the Houston, TX Sponsored by NASA same life as the mission spectrum. Also the component life and (NASA-CR-187009; NAS 1.26:187009) Avail: NTIS HC/MF A07 reliability models for bearings and gears are described. On-bdard CSCL 01/3 monitoring systems are described. Estimates of the drive system A preliminary design for an unmanned hypersonic research failure rate and replacement needs are still essential at the design vehicle to test scramjet engines is presented. The aircraft will be stage. . E.R. launched from a carrier aircraft at an altitude of 40,000 feet at Mach 0.8. The vehicle will then accelerate to Mach 6 at an altitude N91-10045*# National Aeronautics and Space Administration. of 100,000 feet. At this stage the prototype scramjet will be Ames Research Center, Moffett Field, CA. employed to accelerate the vehicle to Mach 10 and maintain Mach ROTOR SYSTEMS RESEARCH AIRCRAFT RISK-REDUCTION 10 flight for 2 minutes. The aircraft will then decelerate and safely SHAKE TEST land. Author J. BRENT WELLMAN Washington Aug. 1990 356 p (NASA-TM-4186; A-88316; NAS 1.15:4186; N91-10042# Advisory Group for Aerospace Research and AVSCOM-TR-88-A-003) Avail: NTIS HC/MF A16 CSCL 01/3 Development, Neuilly-Sur-Seine (France). Propulsion and A shake test and an extensive analysis of results were Energetics Panel. performed to evaluate the possibility of and the method for ROTORCRAFT DRIVETRAIN LIFE SAFETY AND RELIABILITY dynamically calibrating the Rotor Systems Research Aircraft

38 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

(RSRA). The RSRA airframe was subjected to known vibratory N91-10049"# National Aeronautics and Space Administration. loads in several degrees of freedom and the responses of many Ames Research Center, Moffett Field, CA. aircraft transducers were recorded. Analysis of the transducer BODY WEIGHT OF HYPERSONIC AIRCRAFT, PART 1 responses using the technique of dynamic force determination MARK D. ARDEMA Oct. 1988 62 p showed that the RSRA, when used as a dynamic measurement (NASA-TM-101028; A-88279-PT-1; NAS 1.15:101028) Avail: system, could predict, a posteriori, an excitation force in a single NTIS HC/MF A04 CSCL 01/3 axis to an accuracy of about 5 percent and sometimes better. As The load bearing body weight of wing-body and all-body the analysis was broadened to include multiple degrees of freedom hypersonic aircraft is estimated for a wide variety of structural for the excitation force, the predictive ability of the measurement, materials and geometries. Variations of weight with key design system degraded to about 20 percent, with the error occasionally and configuration parameters are presented and discussed. Both reaching 100 percent. The poor performance of the measurement hot and cool structure approaches are considered in isotropic, system is explained by the nonlinear response of the RSRA to organic composite, and metal matrix composite materials; structural vibratory forces and the inadequacy of the particular method used shells are sandwich or skin-stringer. Conformal and pillow-tank in accounting for this nonlinearity. Author designs are investigated for the all-body shape. The results identify the most promising hypersonic aircraft body structure design approaches and their weight trends. Geometric definition of vehicle N91-10046# Oak Ridge National Lab., TN. Center for shapes and structural analysis methods are presented in Transportation Analysis. appendices. Author ENERGY EFFICIENCY IMPROVEMENT POTENTIAL OF COMMERCIAL AIRCRAFT TO 2010 N91-10051# Federal Aviation Administration, Atlantic City, NJ. DAVID L GREENE Jun. 1990 42 p STRUCTURAL TESTS OF AIRCRAFT WINDOW ASSEMBLY (Contract DE-AC05-84OR-21400) EQUIPPED WITH SMOKE EVACUATION VALVE (DE90-014767; ORNL-6622) Avail: NTIS HC/MF A03 ANTHONY WILSON and WILLIAM CAVAGE, JR. Sep. 1990 Aircraft are second only to motor vehicles in the use of motor 20 p fuels. Furthermore, air travel is growing twice as fast as highway (DOT/FAA/CT-TN89/44) Avail: NTIS HC/MF A03 travel. Clearly, the importance of energy use by commercial aircraft The results of three tests performed on a window and window will continue to increase. Since 1970, air travel has more then frame of a Boeing 707 are presented. The purpose of the test, tripled, but the growth of fuel use has been restrained by a near conducted at the Federal Aviation Administration Technical Center, doubling of efficiency, from 26.2 seat miles per gallon (SMPG) in was to determine the maximum moment the window could 1970 to about 49 SMPG in 1989. This paper explores the potential withstand before becoming dislodged from its frame due to the for future efficiency improvements via the replacement of existing failure of the window retention clips. The window assembly was aircraft with 1990's generation and post 2000 aircraft incorporating modified to fit into a load machine. The loads were measured advances in engine and airframe technology. Today, new with a load cell and recorded on a Honeywell Test Management commercial passenger aircraft deliver 50 to 70 SMPG. New aircraft System. Author types scheduled for delivery in the early 1990's are expected to achieve 65 to 80 SMPG. Industry and government researchers have identified technologies capable of boosting aircraft efficiencies N91-10052# Federal Aviation Administration, Atlantic City, NJ. to the 100 to 150 SMPG range. Under current industry plans, AIRPLANE SYSTEMS MODIFICATIONS FOR IMPROVED which do not include a post-2000 generation of new aircraft, the CABIN SMOKE EVACUATION total aircraft fleet should reach the vicinity of 65 SMPG by 2010. THOR I. EKLUND Sep. 1990 20 p A new generation of 100 to 150 SMPG aircraft introduced in 2005 (DOT/FAA/CT-TN90/24) Avail: NTIS HC/MF A03 could raise the fleet average efficiency to 75 to 80 SMPG in Two concepts for improved aircraft in-flight smoke evacuation 2010. In any case, fuel use will likely continue to grow at from were analyzed and tested. The concept definition and evaluation 0.8 percent/y to 1.8 percent/y through 2010. DOE efforts involved an additional ventilation outflow valve on the aircraft underside along with either increased ventilation air volume from the engine compressors or a supplemental ram air supply. Subsequent test aircraft modification involved addition of a pressure N91-10047*# Georgia Inst. of Tech., Atlanta. School of controlling outflow valve on the top of the fuselage and upgraded Aerospace Engineering. engine bleed air volume flow for cabin air-conditioning. Ground NONLINEAR FEEDBACK CONTROL FOR HIGH ALPHA and flight tests were conducted on a test B757 with buoyant and FLIGHT Final Report, Jan. 1989 - Apr. 1990 nonbuoyant theatrical smokes generated continuously in various HAROLD STALFORD Apr. 1990 15 p places in the passenger cabin. Buoyant smoke could be localized (Contract NAG 1-959) only when generated in the vicinity of the upper lobe outflow (NASA-CR-186545; NAS 1.26:186545) Avail: NTIS HC/MF A03 valve. Nonbuoyant smoke could be localized only when generated CSCL01/3 in the vicinity of an outflow valve, whether the valve was on the Analytical aerodynamic models are derived from a high alpha top or bottom of the fuselage. The buoyant smoke was formulated 6 DOF wind tunnel model. One detail model requires some to have the same type flow behavior as a plume from the visible interpolation between nonlinear functions of alpha. One analytical flames of a burning surface. The nonbuoyant smoke might be model requires no interpolation and as such is a completely more representative of a smoldering material. Author continuous model. Flight path optimization is conducted on the basic maneuvers: half-loop, 90 degree pitch-up, and level turn. The optimal control analysis uses the derived analytical model in N91-10053# National Aerospace Lab., Tokyo (Japan). the equations of motion and is based on both moment and force A CONSIDERATION ON FLIGHT PATHS FOR equations. The maximum principle solution for the half-loop is MICROWAVE-POWERED AIRPLANES poststall trajectory performing the half-loop in 13.6 seconds. The KINGO TAKASAWA and FUMIKO ITOH Jan. 1990 30 p In agility induced by thrust vectoring capability provided a minimum JAPANESE; ENGLISH summary effect on reducing the maneuver time. By means of thrust vectoring (NAL-TR-1051; ISSN-0389-4010) Avail: NTIS HC/MF A03 control the 90 degrees pitch-up maneuver can be executed in a Flight paths for microwave-powered airplanes were investigated small place over a short time interval. The agility capability of under uniform wind conditions. Some techniques for deducing flight thrust vectoring is quite beneficial for pitch-up maneuvers. The paths are discussed. The loci of airspeed vectors which lead to level turn results are based currently on only outer layer solutions preferable flight paths are sorted into four types. The effects of of singular perturbation. Poststall solutions provide high turn rates added higher harmonic components are discussed. For each type but generate higher losses of energy than that of classical sustained of airspeed vector loci, three kinds of solving methods are applied solutions. Author and 12 solutions are obtained. Examples of flight paths are

39 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE illustrated with their mathematical expressions, and characteristics N91-10937*# Boeing Commercial Airplane Co., Seattle, WA. are discussed. Preferable flight paths from the view point of airplane BOEING FLIGHT DECK DESIGN PHILOSOPHY design are described. Author HARTY STOLL In NASA, Langley Research Center, Aviation Safety/Automation Program Conference p 17-25 Oct. 1990 N91-10054# National Aerospace Lab., Tokyo (Japan).. Avail: NTIS HC/MF A12 CSCL 01/3 PRACTICAL FLIGHT PATHS FOR MICROWAVE-POWERED Information relative to Boeing flight deck design philosophy is AIRPLANES given in viewgraph form. Flight deck design rules, design TAKESHI ITO Jan. 1990 15 p considerations, functions allocated to the crew, redundancy and (NAL-TR-1052T; ISSN-0389-4010) Avail: NTIS HC/MF A03 automation concerns, and examples of accident data that were Although some types of closed flight paths have been proposed reviewed are listed. Author for microwave powered airplanes, they have unfavorable features from the viewpoint of airplane designers, especially under strong wind conditions. Here, by working out several methods of defining N91-10939*# Douglas Aircraft Co., Inc., Long Beach, CA. the airspeed vector, smooth practical periodic flight paths are DOUGLAS FLIGHT DECK DESIGN PHILOSOPHY deduced. Author PAUL OLDALE In NASA, Langley Research Center, Aviation Safety/Automation Program Conference p 45-53 Oct. 1990 N91-10055# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich Avail: NTIS HC/MF A12 CSCL 01/3 (Germany, F.R.). Helicopter Div. The systems experience gained from 17 years of DC-10 MSB'S BO 108 DESIGN AND DEVELOPMENT operation was used during the design of the MD-11 to automate HELMUT B. HUBER and CLAUS SCHICK May 1990 15 p system operation and reduce crew workload. All functions, from Presented at 46th American Helicopter Society Annual Forum and preflight to shutdown at the termination of flight, require little input Technology Display, Washington, DC, 21-23 May 1990 from the crew. The MD-11 aircraft systems are monitored for proper (MBB-UD-0568-90-PUB; ETN-90-97838; OTN-027636) Avail: operation by the Aircraft Systems Controllers (ASC). In most cases, NTIS HC/MF A03 system reconfiguration as a result of a malfunction is automated. The development by MBB of a new light twin, multipurpose Manual input is required for irreversible actions such as engine helicopter, designated as the BO-108 is described. The design shutdown, fuel dump, fire agent discharge, or Integrated Drive .requirements and the technology advances in terms of the various Generator (IDG) disconnect. During normal operations, when the components involved (rotor systems, drive system, anti-vibration cockpit is configured for flight, all annunciators on the overhead system, control system, airframe, cockpit and cabin) are presented. panel will be extinguished. This Dark Cockpit immediately confirms An overview on the current status of bench and in-flight testing is to the crew that the panels are correctly configured and that no given and the progress achieved in the fields of performance, abnormalities are present. Primary systems annunciations are flying qualities, noise and vibrations, weight, reliability and safety shown in text on the Alert Area of the Engine and Alert Display is assessed. Studies for increasing the aircraft's capabilities are (EAD). This eliminates the need to scan the overhead. The MD-11 described and a prospective about the future program plans is aircraft systems can be manually controlled from the overhead given. ESA area of the cockpit. The center portion of the overhead panel is composed of the primary aircraft systems panels, which include N91-10056* Rolls-Royce Ltd., Bristol (England). FUEL, AIR, Electrical (ELEC) and Hydraulic (HYD) systems, which PROGRESS IN CERTIFYING F402-RR-408: THE IMPROVED are easily accessible from both flight crew positions. Each Aircraft PEGASUS ENGINE FOR AV-8B AND HARRIER 2 PLUS Systems Controller (ASC) has two automatic channels and a DAVID J. MARTIN Derby, England 19 Sep. 1989 10 p manual mode. All rectangular lights are annunciators. All square Presented at Tactical V/STOL Aircraft, New Bern, NC, 19-21 Sep. lights are combined switches and annunciators called switch/lights. 1989 Sponsored by Ministry of Defence, London, England Red switch/lights on the overhead (Level 3 alerts) are for conditions (PNR-90719; ETN-90-97945) Copyright Avail: NTIS HC/MF requiring immediate crew action. Amber (Level 2 or Level 1 alerts) A02 indicates a fault or switch out of position requiring awareness or The operational background of the Harrier/AV8 family of aircraft crew interaction. Overhead switches used in normal operating was used to define a demonstrator program for improved conditions will illuminate blue when in use (Level 0 alerts) such performance. The XG15 demonstrator program was completed in as WING ANTI-ICE - ON. An overhead switch/light with BLACK April 1988. The results formed the basis of the improved LETTERING on an amber or red background indicates a system F402-RR-408 engine. The validation test program commenced with failure and that crew interaction is required. A switch/light with an .engine roll out in June 1988 and is due for completion in May blue or amber lettering and a BLACK BACKGROUND indicates a 1990. A summary of technical issues and program status is given. switch out of normal position and that crew action is necessary ESA only if the system is in manual operation. Author

N91-10932# Deutsche Airbus G.m.b.H., Bremen (Germany, F.R.). N91-10949*# National Aeronautics and Space Administration. A QUARTER OF A CENTURY OF AEROELASTIC Langley Research Center, Hampton, VA. COOPERATION BETWEEN RESEARCH AND INDUSTRY (A OVERVIEW OF ERROR-TOLERANT COCKPIT RESEARCH REVIEW). PART 2: TRANSPORT AIRPLANES AND OTHER Abstract Only CIVIL APPLICATIONS KATHY ABBOTT In its Aviation Safety/Automation Program S. VOGEL, H. ZIMMERMANN, and K. KOENIG In DLR, Conference p 153-156 • Oct. 1990 Contributions in the Field of Aeroelastics on the Occasion of the Avail: NTIS HC/MF A12 CSCL 01/3 60th Anniversary of Professor Dr.-lng. Habil. Hans Wilhelm The objectives of research in intelligent cockpit aids and Foersching p 271-287 Apr. 1990 intelligent error-tolerant systems are stated. In intelligent cockpit Avail: NTIS HC/MF A13 aids research, the objective is to provide increased aid and support Studies and developments in the field of civil aviation by the to the flight crew of civil transport aircraft through the use of German aircraft industry and the DLR Institute of Aeroelasticity artificial intelligence techniques combined with traditional are described. The application of aerolasticity to wind turbine automation. In intelligent error-tolerant systems, the objective is to systems for energy supply is outlined. Aeroservoelasticity and active develop and evaluate cockpit systems that provide flight crews control technology are introduced. Methods for the calculation of with safe and effective ways and means to manage aircraft systems, unsteady aerodynamic forces in the transonic domain are plan and replan flights, and respond to contingencies. A subsystems presented. The measurement of unsteady aerodynamic loads is fault management functional diagram is given. All information is in discussed. ESA viewgraph form. Author

40 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

N91-10969# Technische Univ., Brunswick (Germany, F.R.). Pilots should avoid a take-off into a thunderstorm. In moderate COMPARISON OF A MATHEMATICAL ONE-POINT MODEL downbursts a practicable escape maneuver is to maintain the flight AND A MULTI-POINT MODEL OF AIRCRAFT MOTION IN level at a low height to pass, the core of the downburst before MOVING AIR starting the climb. This procedure can also be applied on -the R. BROCKHAUS In AGARD, Aircraft Trajectories: Computation, go-around. Author Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Right in Critical Atmospheric Conditions. Part 3: Impact of New On-Board N91-10973# Southampton Univ. (England). Technologies on Aircraft Operation 17 p Mar. 1990 AIRCRAFT FLIGHT IN WIND-SHEAR Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests D. MCLEAN In AGARD, Aircraft Trajectories: Computation, available only from AGARD/Scientific Publications Executive Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Flight The steadily growing capacity of computers favors increasingly in Critical Atmospheric Conditions. Part 3: Impact of New On-Board exact simulation of even complex processes. On the other hand, Technologies on Aircraft Operation 10 p Mar. 1990 ' parameter identification and state estimation require much more Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests precise models than are generally used for the design of feedback available only from AGARD/Scientific Publications Executive systems. A multi-point model of the aircraft motion is proposed in A brief account of wind-shear and some representations is which the different coupling effects between the two sub-processes, given before discussing the effects of wind-shear on aircraft motion. aircraft and air flow, can be modeled with much higher accuracy A procedure for estimating the vertical and horizontal velocity than is obtained by using the ordinary one-point model, where .all components of a wind-shear 'microburst, based on observer theory the force, moment, and velocity vectors are referred to the aircraft is developed, and a brief discussion of flying in wind-shear center of gravity. The modeling of the effects of aircraft rotation, concludes the paper. . Author wing down-wash, wind gradients, and other unstationary effects should be greatly improved by a multi-point approach, provided N91-10974# Airbus Industrie, Blagnac (France). that the aerodynamic effects on the aircraft components can be HOW TO FLY WINDSHEAR described appropriately. The nonlinear equations of the total PAUL CAMUS In Agard, Aircraft Trajectories: Computation, process are set up for the one-point and multi-point models and Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Flight compiled into block diagrams, from which the physical background • in Critical Atmospheric Conditions. Part 3: Impact of New On-Board of the interrelations between air and aircraft motion can be seen Technologies on Aircraft Operation 10 p Mar. 1990 very clearly. The possible improvement in model quality and the Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests additional, computer capacity needed' are estimated by comparing available only from AGARD/Scientific Publications Executive the two approaches. . • . Author Aviation safety history is a long fight against severe environmental constaint. Modern aircraft are able to face safely N91-10971# Toronto Univ. (Ontario). Inst.-for Aerospace most of them but one still remains a potential killer, that is what Studies. is generally described as a windshear situation. What can be done, CRITICAL ASPECTS OF TRAJECTORY PREDICTION: FLIGHT necessarily fall either in how to timely detect such a situation in IN NON-UNIFORM WIND order'to avoid it or/and what tools could be given to the'crew to BERNARD ETKIN and 'DAVID ALEXANDER ETKIN (Canadian" better escape should they are trapped in. Latest state of build-in Climate Centre, Downsview, Ontario ) In AGARD, Aircraft. equipment, 3-D Navigation, electronic displays and flight control, Trajectories:'Computation, Prediction, Control, Volume 1. Part 1: provide now all necessary tools to develop an efficient in-board Fundamentals. Part 2: Flight in Critical Atmospheric Conditions.' detection and protection system. Such a system will be described Part 3: Impact of New On-Board Technologies on Aircraft Operation altogether with a"review of some fundamental criteria to be 12 p Mar. 1990 • • - • considered when assessing their efficiency. Author Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive N91-10976# Smiths Industries, Inc., Grand Rapids, Ml. The genesis of natural wind is described from a meteorological AIRCRAFT TRAJECTORY: PREDICTION AND CONTROL IN standpoint. Its influence on aircraft trajectories is discussed with THE AIR TRANSPORT FLIGHT MANAGEMENT COMPUTER reference to steady winds, turbulence, and wind shear. The main SYSTEMS problems' exist when flight is close to the ground, during landing, PETER J. HOWELLS .In AGARD, Aircraft Trajectories: take-off, or terrain following. A model for analysis and simulation Computation, Prediction, Control, Volume 1. Part 1: Fundamentals. is presented consisting of four components - dynamics, kinematics Part 2: Flight in Critical Atmospheric Conditions. Part 3: Impact of and transformations, aerodynamics, and wind. The axis systems New On-Board Technologies on Aircraft Operation 13 p Mar. chosen are well suited to simulation of landing and take-off. 1990 Author Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive N91-10972# Technische Univ., Brunswick (Germany, F.R.). Inst. The declining cost of computing power and memory has of Flight Guidance and Control. enabled avionic manufacturers to develop sophisticated airborne EFFECT OF WIND AND WIND VARIATION ON AIRCRAFT computing systems. One of the most complex aircraft systems on FLIGHT-PATHS . modem air transport aircraft is the Flight Management Computer K.-U. HAHN, T. HEINTSCH, B. KAUFMANN, G. SCHAENZER, and. System (FMCS). The FMCS has reduced pilot workload by taking M. SWOLINSKY In AGARD, Aircraft Trajectories: Computation, over the more mundane but complex functions, such as calculating Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Flight the most economical speed, and, together with improvements in in Critical Atmospheric Conditions. Part 3: Impact of New On-Board cockpit displays and monitoring systems, has allowed the transition Technologies on Aircraft Operation 27 p Mar. 1990 Sponsored, from the three to two crew airline cockpit. The FMCS can compute by DFG the most economical path from one airport to another and then Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests fly the aircraft along that path. To achieve this the computer must available only from AGARD/Scientific Publications Executive be able to select the most economical speed schedules for each Wind shear accidents during landing and approach could phase of flight, then predict the complex vertical and horizontal generally be avoided by using modern flight control systems. The profile that the aircraft would fly and, when connected to the problem is to inform the pilot by an adequate wind shear warning aircraft's autopilot, control the aircraft along that three dimensional display, that he can understand the reaction of the control system. flight path. The forth dimension of time can also be selected as a Wind shear is particularly dangerous if it occurs in a height of control criteria, and the FMCS will compute the speed schedules approximately 80 to 120 m, where the attention of the cockpit and flight path based on a required time of a arrival at a selected crew is affected by getting view contact,to the ground. Wind shear point along the flight plan. In addition to reducing pilot workload, during take-off and go-around is a pure flight performance problem. air traffic control efficiency is increased because the airborne

41 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE navigation data base can be used to select and accurately fly Prediction, Control, Volume 2: Air Traffic Handling and published arrival and departure procedures without supervision from Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. the ground controllers. The algorithms used for the Smiths Part 5: Guidance of Aircraft in a Time-Based Constrained Industries 737 FMCS prediction and control functions are described. Environment. Surveillance. Part 7: Meteorological Forecasts. Part The requirements for successful implementation and some of the 8: Aircraft Operation in Air Traffic Handling Simulation 19 p May difficulties that may be encountered are identified. Author 1990 Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests N91-10981# Advisory Group for Aerospace Research and available only from AGARD/Scientific Publications Executive Development, Neuilly-Sur-Seine (France). Guidance and Control The equations of motion of airplanes in the context of Air Panel. Traffic Control (ATC) are discussed. The basic laws of mechanics AIRCRAFT TRAJECTORIES: COMPUTATION, PREDICTION, are examined together with a mathematical model of mechanical CONTROL, VOLUME 2: AIR TRAFFIC HANDLING AND systems which is suitable for airborne systems; the generally GROUND-BASED GUIDANCE OF AIRCRAFT. PART 4: AIR accepted (but often implicit) assumptions of usual models are TRAFFIC HANDLING. PART 5: GUIDANCE OF AIRCRAFT IN A pointed out. A simplified description of the main dynamical effects TIME-BASED CONSTRAINED ENVIRONMENT. PART 6: (gravity and aerodynamical interactions) are given together with a SURVEILLANCE. PART 7: METEOROLOGICAL FORECASTS. complete kinematical description of the system. The coherence PART 8: AIRCRAFT OPERATION IN AIR TRAFFIC HANDLING with ISO norms (ISO - 1985) are respected as far as possible; SIMULATION some dynamical short commings of these norms are mentioned. ANDRE BENOIT, ed. May 1990 453 p In ENGLISH and Author FRENCH (AGARD-AG-301-VOL-2-PT-4-8; ISBN-92-835-0562-X; N91-10987# European Organization for the Safety of Air AD-A225265) Copyright Avail: NTIS HC/MF A20; Non-NATO Navigation, Brussells (Belgium). Engineering Directorate. Nationals requests available only from AGARD/Scientific GENERATION OF AIRCRAFT TRAJECTORIES FOR ON-LINE Publications Executive OPERATION: METHODS, TECHNIQUES, AND TOOLS This volume (part of a set of three) is composed of a preface ANDRE BENOIT and SIP SWIERSTRA In AGARD, Aircraft and 28 papers covering respectively, the following topics. (1) Air Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic traffic handling: Integration of control phases; A future European Handling and Ground-Based Guidance of Aircraft. Part 4: Air Traffic ATC concept; On-line prediction of aircraft trajectories; and Air Habdling. Part 5: Guidance of Aircraft in a Time-Based Constrained traffic management. (2) Guidance of aircraft in a time based Environment. Surveillance. Part 7: Meteorological Forecasts. Part constrained environment: Guidance and control principles and 8: Aircraft Operation in Air Traffic Handling Simulation 12 p May concepts; Conduct of Air Traffic Control in a Zone of Convergence; 1990 Ground-based 4-D guidance of aircraft in moving atmosphere; and Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests The Computer/Controller/Pilot dialogs. (3) Surveillance: Radar available only from AGARD/Scientific Publications Executive tracking; and Satellite techniques. (4) Meteorological forecasts: An appreciable amount of work has been conducted at the Impact of forecasts quality on trajector prediction; .and Flight EUROCONTROL Agency's Engineering Directorate in the division operations within a terminal area. (5) Aircraft operation in air traffic engaged in the Study of Long Term Air Traffic Control (ATC) handling simulation: Realistic operation and motion of aircraft; and System Requirements in order to generate accurate aircraft Flight operations within a terminal area. trajectory predictions for use in both ATC on-line operation arid real time simulations in current and realistic conditions, human N91-10984# Royal Radar Establishment, Malvern (England). interfaces included. The basic approach developed for two distinct PREDICTION OF AIRCRAFT TRAJECTORIES classes of application are outlined: (1) the on-line generation of STANLEY RATCLIFFE In AGARD, Aircraft Trajectories: predictions for use in actual operation and, accessorily, real time Computation, Prediction, Control, Volume 2: Air Traffic Handling ATC simulations; and (2) the introduction of realistic aircraft and Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. response and motion into ATC simulations, with pilot/auto-pilot Part 5: Guidance of Aircraft in a Time-Based Constrained interfaces included. Author Environment. Surveillance. Part 7: Meteorological Forecasts. Part 8: Aircraft Operation in Air Traffic Handling Simulation 40 p May N91-11009 Kansas Univ., Lawrence. 1990 CALCULATION OF AERODYNAMIC CHARACTERISTICS OF Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests AIRPLANE CONFIGURATIONS AT HIGH ANGLE OF ATTACK available only from AGARD/Scientific Publications Executive IN STEADY AND UNSTEADY FLOW Ph.D. Thesis Air traffic management, in designing route structures, drawing HOMAYOUN EMDAD 1989 117 p up rules for flight in various types of airspace, and in framing the Avail: Univ. Microfilms Order No. DA9024169 instructions for air traffic controllers, are concerned with predicting A computational method for steady and unsteady lateral the behavior, often on worst case assumptions, of each class of directional aerodynamics of fighter configurations is developed. traffic with which they may have to deal. The problems are The leading-edge vortices are represented by free vortex filaments examined of on-line trajectory prediction to a time-horizon perhaps which are adjusted iteratively to satisfy the force-free condition. a little longer than the estimated time of the flight or as short as The forebody vortex separation, both symmetrical and asym- a few tens of seconds, the object being to predict and avoid metrical, is calculated with slender body theory. The effect collision with terrain or with another aircraft, and to ensure that of the boundary layer separation on lifting surfaces is accounted any in-flight delays due to traffic congestion along the route are for by using the effective sectional angles of attack. Results for absorbed as economically as possible. Military aircraft are several fighter configurations are employed for comparison with concerned with the avoidance of anti-aircraft missiles and in available data. It is shown that the present steady-flow method intercepting airborne targets. This latter problem may, very loosely, produces reasonable results in predicting slideslip derivatives, while be regarded as collision avoidance in reverse, and is briefly roll- and yaw-rate derivatives do not compare very well with discussed, as is the problem of terrain-following by high forced-oscillation test data at high angles of attack. To account performance low flying military aircraft. The conclusion draws for unsteady aerodynamics, a theoretical method is developed to attention to areas where further R and D would seen desirable. determine the aerodynamic derivatives due to pitching, plunging, Author flapping, side movement, rolling, and yawing for a wing in a compressible flow. The present method is based on the frequency N91-10985# Universite Catholique de Louvain (Belgium). Dept. approach, instead of time-domain integration. The wing is de Mecanique. represented by a series of oscillatory horseshoe vortices, and the AIRCRAFT DYNAMICS FOR AIR TRAFFIC CONTROL leading-edge vortices are represented by oscillatory line vortices. P.-Y. WILLEMS In AGARD, Aircraft Trajectories: Computation, Results for 60 and 80 deg delta wings are compared with

42 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

experimental data. It is shown that the present method produces several parameters on vibratory hub loads and body vibration are reasonable results for roll damping derivatives before occurrence investigated, including blade stiffness, rotor/body clearance, hub of vortex breakdown. Other dynamic derivatives were not location, fuselage stiffness and advance ratio. A significant compared. Dissert. Abstr. influence of body upwash on the rotor disk in causing vibratory hub shear is shown, an effect which generally increases with smaller N91-11010 Purdue Univ., West Lafayette, IN. rotor/body clearance. Tuning of rotor and body natural modes DEVELOPMENT AND APPLICATION OF THE TIME DOMAIN substantially reduces vibration levels. Elastic deflections of the PANEL METHOD Ph.D. Thesis body have considerable influence on vibratory hub loads. Analyses MAXWELL BLAIR 1989 196 p assuming clamped body motion (wind tunnel condition) or rigid Avail: Univ. Microfilms Order No. DA9018788 body motion yield inadequate vibration predictions for the The utility of the Time Domain Panel (TOP) algorithm for wing rotor/body system. Dissert. Abstr. design and analysis is developed and demonstrated. This is a linear unsteady aerodynamic method for simulating loads on an N91-11013 Tennessee Univ., Knoxville. oscillating wing in subsonic compressible flow. This time stepping AERODYNAMIC DESIGN OPTIMIZATION USING simulation is based on Guderley's integral formulae. Other current COMPUTATIONAL FLUID DYNAMICS Ph.D. Thesis work, which is similar in application, is either based on DAVID HOWARD HUDDLESTON 1989 122 p computationally expensive nonlinear finite difference schemes, or Avail: Univ. Microfilms Order No. DA9021023 is based on inverse transforms of linear harmonic aerodynamic An aerodynamic design optimization technique is presented loads. The TOP method is a direct integral (panel) method which that couples direct optimization algorithms with the analysis has the efficiency of linear aerodynamics but is in a suitable form capability provided by appropriate computational fluid dynamics for developing simulation models with nonlinear structural dynamics (CFD) programs. This technique is intended to be an aid in or nonlinear controls. This is a linear time stepping method which designing the aerodynamic shapes and establishing test conditions falls between linear harmonic aerodynamic methods and higher required for the successful simulation of aircraft engine inlet order nonlinear time stepping aerodynamic methods. The conditions in a ground test environment. However, the method is developmental details in numerically implementing Guderley's also applicable to other aerodynamic design problems such as integral formula is given here. Several applications are presented airfoil design, turbomachinery cascade design, and nozzle design. in .order to provide confidence that the TOP method is practical The approach involves minimization of a nonlinear least-squares and numerically accurate. Dissert. Abstr. objective function which may be defined in a region remote to the geometric surface being optimized. Finite-difference Euler and N91-11011 Stanford Univ., CA. Navier-Stokes codes were applied to obtain the objective function CONTROLLED VORTICAL FLOW ON DELTA WINGS evaluations, although the applied optimization method can be THROUGH UNSTEADY LEADING EDGE BLOWING Ph.D. coupled with any appropriate CFD analysis technique. Using CFD Thesis to compute design space gradients within an optimization algorithm KYUNG-TAE LEE 1990 147 p has received little prior attention in the literature. It is demonstrated, Avail: Univ. Microfilms Order No. DA9024343 that CFD can be used in this manner by applying the developed The vortical flow over a delta wing contributes an important design technique to a variety of aerodynamic design problems. part of the lift - the so called nonlinear lift. Controlling this vortical Results are presented for several typical aerospace examples, flow with its favorable influence would enhance aircraft including algebraic test functions, inviscid and viscous flow over maneuverability at high angle of attack. Several previous studies airfoils, flows in convergent/divergent nozzles in both two and have shown that control of the vortical flow field is possible through three dimensions, and supersonic flow about a planar forebody the use of blowing jets. Vortical flow control is studied by applying simulator. Dissert. Abstr. a new blowing scheme to the rounded leading edge of a delta wing; this blowing scheme is called Tangential Leading Edge Blowing (TLEB). Vortical flow response both to steady blowing N91-11014 California Inst. of Tech., Pasadena. and to unsteady blowing is investigated. It is found that TLEB can APPLICATION OF DYNAMICAL SYSTEMS THEORY TO redevelop stable, strong vortices even in the post-stall angle of NONLINEAR AIRCRAFT DYNAMICS Ph.D. Thesis attack regime. Analysis of the steady data shows that the effect CRAIG CHARLES JAHNKE 1990 281 p of leading edge blowing can be interpreted as an effective change Avail: Univ. Microfilms Order No. DA9022286 in angle of attack. The examination of the fundamental time scales A continuation method was used to determine the steady for vortical flow re-organization after the application of blowing for states of three nonlinear aircraft models: a general aviation aircraft differential initial states of the flow field is studied. Different time with a canard configuration, a generic jet fighter, and the F-14. scales for flow re-organization are shown to depend upon the The continuation method calculated the steady states of the aircraft effective angle of attack. A faster response time can be achieved as functions of the control surface deflections. Bifurcations of these at angles of attack beyond stall by a suitable choice of the initial steady states were determined and shown to cause instabilities blowing momentum strength. Consequently, TLEB shows the which resulted in qualitative changes in the state of,the aircraft. A potential of controlling the vortical flow over a wide range of angles longitudinal instability which resulted in a deep stall was determined of attack; i.e., in both for pre-stall and post-stall conditions. for the general aviation aircraft. Roll-coupling and high angle of Dissert. Abstr. attack instabilities were determined for the generic jet fighter, and wing rock, directional divergence and high angle of attack instabilities were determined for the F-14. Knowledge of the control N91-11012 Maryland Univ., College.Park. . COUPLED ROTOR/AIRFRAME VIBRATION ANALYSIS Ph.D. surface deflections at which bifurcations occurred was used to either put limits on the control surface deflections or to program Thesis the control surface deflections at which bifurcations occur could SHMUELFLEDEL 1989 171 p Avail: Univ. Microfilms Order No. DA9021500 not be attained. Simple control systems were included in the aircraft A consistent finite-element formulation developed for the models to determine the effects of control systems on the prediction of vibration in rotor/body helicopter systems in forward instabilities of each aircraft. Steady spin modes were determined for each aircraft. A successful recovery technique was determined flight, taking into account interactional rotor/body aerodynamic for the general aviation aircraft, but no successful recovery loads and dynamic coupling is presented. The rotor blades are assumed to be elastic beams undergoing flap and lag bending, technique could be found for the F-14. Dissert. Abstr. torsion and axial deflections. The coupled analysis is formulated retaining nonlinear structural, inertial and aerodynamic terms N91-11015# Federal Aviation Administration, Atlantic City, NJ. in a consistent manner. Rotor excitation includes rotor/body GENERATION OF A BUOYANT PLUME OF ARTIFICIAL interactional loads and fuselage dynamic coupling. Effects of SMOKE FOR AIRPLANE TESTS Final Report

43 06 AIRCRAFT INSTRUMENTATION

THOR I. EKLUND Sep. 1990 28 p ; operations of the data link system flight tested in 1990 are (DOT/FAA/CT-90/9) Avail: NTIS HC/MF A03 ' • described. . Author ' A buoyant artificial smoke generator was developed for airplane test applications. In the device, theatrical smoke is mixed with a N91-10938*# Honeywell, Inc., Minneapolis, MN. mixture of helium and air. The total gas flow, the helium 'to air COCKPIT AVIONICS INTEGRATION AND AUTOMATION ratio, and the theatrical smoke particulate generation rate can all KEITH M. PISCHKE In NASA, Langley Research Center, Aviation be varied in the device.'A' gas mixture of 50 percent each-of Safety/Automation Program Conference p 27-44 Oct. 1990' helium and air has the buoyancy properties of air, alone, heated Avail: NTIS HC/MF A12 CSCL01/3 ' to 475 F. The device was used in cabin smoke evacuation tests Information on cockpit avionics integration and automation is in'a modified Boeing 757 aircraft. Generation of the buoyant smoke given in viewgraph form, with a number-of photographs. Th'e in an aircraft resulted in dramatically different behavior from that benefits of cockpit integration are listed. The MD-1-1 flight previously observed with nonbuoyant theatrical smoke. The buoyant guidance/flight deck system is illustrated. Author smoke spread further through the aircraft in a 'manner that was . r • not predicted by an analytical model on cabin smoke spread. N9.1-10942*# National Aeronautics and Space' Administration. Besides being used to assess airplane cabin smoke evacuation Ames Research Center, Moffett Field, CA. capability, the buoyant smoke generator has been used to evaluate SUMMARY OF THE INDUSTRY/NASA/FAA WORKSHOP ON smoke detector performance and optimal location in Air Force jet PHILOSOPHY OF AUTOMATION: PROMISES AND REALITIES aircraft. ' • - • Author SUSAN D. NORMAN In NASA, Langley Research Center, Aviation Safety/Automation Program Conference'p 77-82 Oct. 1990 Avail: NTIS HC/MF A12 CSCL01/3 ' ' Issues of flight deck automation are multi-faceted and complex. 06 The rapid introduction of advanced computer based technology on to the flight deck of 'transport category aircraft has had AIRCRAFT INSTRUMENTATION considerable impact on both aircraft operations and the flight crew. As part of NASA's responsibility to facilitate an active exchange of ideas and information between members1 of the aviation Includes cockpit and cabin display devices; and flight instruments. 1 community, an Industry/NASA/FAA workshop was conducted in August 1988. One of the most important conclusions to emerge from the workshop was: that the introduction of automation has N91-10057 National Aerospace Lab., Tokyo (Japan). • clearly benefited aviation and has substantially improved the WIND TUNNEL TEST OF REDUNDANT VANE-TYPE operational safety and efficiency of our air transport system. For FLOW-DIRECTION SENSING SYSTEMS [YABANE O example, one carrier stated that they have been flying the Boeing MOCHIITA JOUCHOUGATA KIRYUU HOUKOU SOKUTEI 767 (one of the first aircraft to employ substantial automation) SOUCHI NO FUUDOUSHIKEN Nl KANSURU HOUKOKU] since 1982, and they have never had an accident or incident TAKEO KIMURA, MINORU TAKIZAWA, TADAO UCHIDA, resulting in damage to the aircraft. Notwithstanding its benefits, ATSUTOSHI FUJIEDA, AKIHITO IWASAKI, TOSHIMI FUJITA, and many issues associated with, the design, certification, and operation TERUO SOMEYA Jul. 1988 41 p In JAPANESE of automated aircraft were identified. For example two key (NAL-TM-590; ISSN-0452-2982; JTN-90-80017) Avail: NTIS : conceptual issues were the need for the crew to have a thorough HC/MF A03 .••••• ,,-..- understanding of the system and the importance of defining the Trial fabrication of a triaxial sensor system, in which alpha is pilot's role. With respect to certification, a fundamental issue is the front angle and beta is the side angles, and performance of the lack of comprehensive human factors- requirements in the wind tunnel tests are presented. An experiment based on the current regulations. Operational considerations, which have been two-dimensional vector volume measurement method using a blast a factor in incidents involving automation, were also cited. wind tunnel was performed to prove the measurement theory, of Viewgraphs used in the' presentation are given. Author the triaxial alpha/beta sensor system and.to compare the measurement accuracy between the results obtained from a normally functioning sensor and a malfunctioning or out-of-order N91-10950*# National Aeronautics and Space Administration. sensor. Values and errors were calculated from data obtained Langley Research Center, Hampton, VA. from three sensors under four different wind velocities-of 10, 20, FAULT MONITORING 30, and 40 m/s against a fixed air current of alpha -zero beta PAUL SCHUTTE In its Aviation Safety/Automation Program zero in the wind tunnel. The accuracy of. measurement was Conference p 157-163 Oct. 1990 ' determined by comparing the measured data with the second and Avail: NTIS HC/MF A.12 CSCL 01/3 ' third sensor, first and third sensor, and .first and second sensor. Information on fault monitoring of aircraft systems is given in The results of the experiment indicated that the measurement of viewgraph form. Information is. given on monitor architecture and this system was extremely accurate: Even -if one of the sensors benefits, .implementation characteristics, and ah engine monitoring becomes defective, the accuracy will not reduce the reliability limit and control system., . , Author as the other sensors functioned normally. Thus the feasibility of this system has been acknowledged. • • • -• NASDA 07 N91-10058*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. NASA TRANSPORT SYSTEMS RESEARCH VEHICLE B-737 AIRCRAFT PROPULSION AND POWER DATA LINK SYSTEM AND DISPLAY FORMATS CHARLES E. KNOX and CHARLES H. SCANLON Aug. 1990 Includes prime propulsion systems and systems components, e:g'., 22 p . ' - gas turbine engines and compressors; and on-board auxiliary power (NASA-TM-102717; NAS 1.15:102717) Avail: NTIS HC/MF A03 plants for aircraft. • ' CSCL01/3 A data link system was designed to support flight tests in the NASA Transport Systems Research Vehicle B-737 airplane. The A91-10245* Case Western Reserve Univ., Cleveland, OH. purpose of the flight tests was to'evaluate pilot acceptance of BIFURCATION ANALYSIS OF AXIAL FLOW COMPRESSOR using data link as the primary source of communications for STABILITY strategic and tactical air traffic control clearances; weather F. E. MCCAUGHAN (Case Western Reserve University, Cleveland, information, and company messages, the airborne functional -OH) SIAM Journal on Applied Mathematics (ISSN 0036-1399),

44 07 AIRCRAFT PROPULSION AND POWER

vol. 50. Oct. 1990, p. 1232-1253. refs NO(x) result mainly from high thrust operating conditions. (Contract NAG3-349) Continuing technological development has se.rved to radically Copyright reduce smoke, HC, and CO emissions so that, at present, cruise With a one-mode truncation it is possible to reduce the NO(x) emissions are the only significant category remaining. Moore-Greitzer model for compressor instability to a set of three Modeling studies show that the NO(x) cruise operating emissions ordinary differential equations. These are approached from the of SST and HST transport aircraft engines may have possible point of view of bifurcation theory. Most of the bifurcations emerge adverse effects on the stratospheric ozone layer. Therefore, the from a degenerate Takens-Bogdanov bifurcation point. The development of SST engine combustors capable of satisfactory bifurcation sets are completed using the numerical branch tracking operation with significantly reduced NO(x) levels than those of scheme AUTO. Despite the severity of the truncation, the present technology combustors is necessary. R.E.P. agreement with experimental results is excellent. Author A91-10968 A91-10954 FUTURE SUPERSONIC TRANSPORT PROPULSION DEVELOPMENT OF THE GRIFFON II TURBO-RAMJET [LE OPTIMISATION DEVELOPPEMENT DU TURBOSTATOREACTEUR DE L'AVION B. W. LOWRIE (Rolls-Royce, PLC, Filton, England) IN: European GRIFFON II] Symposium on the Future of High Speed Air Transport, Strasbourg, A. GOZLAN IN: European Symposium on the Future of High France, Nov. 6-8, 1989, Proceedings. Toulouse, France, Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, Cepadues-Editions, 1990, p. 203-209. refs Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. 45-52. Copyright In French, refs In order to achieve the optimum cruise performance and airport Copyright noise requirements, various variable cycle propulsion systems for First flight of the experimental Griffon II aircraft in 1957 was a supersonic transport are studied. Fundamental installation the result of seven years of development that began with purely requirements show that opportunities to drive the additional flow semiempirical research using various ground testing laboratories, by turbomachinery can be either front fan, aft fan, or mid fan, and wind tunnels, and flying test beds. The turbojet was meant to be that ejector systems must also be considered. The benefits of utilized principally for takeoff and subsonic acceleration. At about these different systems are compared. It is shown that the best Mach 0.5 the ramjet was started to increase thrust during transonic projected cruise performance between Mach 2.0 and 2.5 can be acceleration and for supersonic flight. The ramjet represented only achieved with a bypass ratio of 0.8 to 0.5. As a conventional 30 percent of the total engine weight. Details and graphs are engine of this type produces very high jet velocities at takeoff provided of performance realized over the 330 test flights and adequate silencing is not likely, engines with cycle variability conducted through Mach 2.2 extending over a large flight envelope, of magnitude much greater than the Olympus 593 are required to restricted only by thermal problems with the aluminum alloy swallow greater mass flow and lower jet velocity at takeoff. It is structure. R.E.P. concluded that for an isolated installation the tandem fan engine concept is the best. R.E.P. A91-10958 THE ROLLS ROYCE/SNECMA OLYMPUS 593 ENGINE A91-10969 OPERATIONAL EXPERIENCE AND THE LESSONS LEARNED THE VARIABLE-CYCLE ENGINE - A SOLUTION TO THE G. LAVIEC (SNECMA, Paris, France) and G. GANLEY (Rolls-Royce, ECONOMICAL AND ENVIRONMENTAL CHALLENGE OF THE PLC, Bristol, England) IN: European Symposium on the Future FUTURE SUPERSONIC TRANSPORT of High Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, ALAIN HA8RARD (SNECMA, Paris, France) IN: European Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. Symposium on the Future of High Speed Air Transport, Strasbourg, 73-80. France, Nov. 6-8, 1989, Proceedings. Toulouse, France, Copyright Cepadues-Editions, 1990, p. 211-218. refs A review of the 13 years of Concorde engine design and Copyright development are presented. Particular attention is devoted to the The optimization- of a variable-cycle engine designed for the reliability aspects of this engine running in very severe ambient Mach 2 cruise regime is presented. Principal areas of study include conditions as compared to a conventional subsonic engine. Specific specific fuel consumption; the requirements for noise attenuation operational requirements called for an engine to produce sufficient on the ground, during takeoff and in cruise; by-pass ratios, the thrust to takeoff with 11 tons of payload for a distance of 3500 reduction of pollutant emissions; adaptive combustors; and a nm at Mach 2. To achieve this goal it became necessary to add specific variable-cycle engine concept. A variable-cycle engine an afterburner to a conventional twin spool engine and to add a would have a cycle different for takeoff and subsonic operation variable secondary nozzle and a thrust reverser. An electronic from the supersonic regime. As an example, a double-flow cycle analog fuel control system was adopted to control the engine to with a bypass ratio of 1 to 2 could be used during takeoff while a the required turbine inlet temperature appropriate to the thrust single-flow cycle would operate in cruise. The specific variable-cycle required while ensuring that all limitations are not exceeded and engine concept discussed corresponds to a good compromise that crew handling be minimal. Details and graphs are presented between engine complexity and air inlet/nozzle complexity. Thus for engine operational experience covering utilization rates, shop it is possible to achieve necessary installed performance and also visit rates, inflight shutdowns, and the effects of supersonic meet current noise regulations without resorting to new unproven operations. R.E.P. devices. R.E.P.

A91-10965 A91-10975 SUPERSONIC/HYPERSONIC PROPULSION SYSTEMS - PROPULSION SYSTEMS FOR HYPERSONIC EXHAUST EMISSION CHARACTERISTICS AND ABATEMENT TRANSPORTATION TECHNOLOGY J. DARDARE (SEP, Suresnes, France) and P. SENECHAL DONALD W. BAHR (GE Aircraft Engines, Cincinnati, OH) IN: (SNECMA, Paris, France) IN: European Symposium on the Future European Symposium on the Future of High Speed Air Transport, of High Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Toulouse, France, Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. Cepadues-Editions, 1990, p. 167-170. 277-279. refs Copyright Copyright A study of pollutant emissions of aircraft turbine engines is Propulsion systems for hypersonic transport aircraft are a new presented. These pollutants consist primarily of smoke, unburned challenge for engine manufacturers. High temperatures at the hydrocarbons and oxides of nitrogen. The HC and CO emissions engine inlet, the use of cryogenic fuels, and the necessity of are principally produced at low thrust levels while smoke and covering a wide range of Mach numbers lead to the use of a

45 07 AIRCRAFT PROPULSION AND POWER

variety of airbreathing engines combining turbo, rocket and ramjet A91-11351 concepts. In France, appropriate studies have been carried out HOLOGRAPHIC INTERFEROMETRY FOR FLOW for three years by SNECMA, SEP, and ONERA and aim at defining VISUALIZATION STUDIES IN HIGH SPEED FANS the propulsion of a winged launcher. This paper presents a selection R. J. PARKER (Rolls-Royce, PLC, Advanced Research Laboratory, of the combined engines currently studied which could bring the Derby, England) International Journal of Turbo and Jet-Engines technologies applicable to the propulsion of a hypersonic transport (ISSN 0334-0082), vol. 6, no. 3-4, 1989, p. 281-303. Research aircraft. However, mass transportation systems and launcher have supported by the Ministry of Defence Procurement Executive of quite different requirements, resulting in different optimization England. Previously announced in STAR as N88-28072. refs criteria which are discussed. Finally, some considerations about Copyright environment and installation effects are given. Author Holography was developed as a technique for routine use in the evaluation of fan designs for aero-engines. It is used to A91-10976 investigate aerodynamic and mechanical behavior of the rotating fan. Holographic flow visualization provides clear, three-dimensional OPTIMISATION OF HYBRID PROPULSION SYSTEMS R. R. SCHWAB (MTU Motoren- und Turbinen-Union Muenchen images of the transonic flow region between the fan blades. Flow features such as shocks, shock/boundary layer interaction, and GmbH, Munich, Federal Republic of Germany) and F. A. HEWITT (Rolls-Royce, PLC, Bristol, England) IN: European Symposium over-tip leakage vortices can be observed and measured. Examples on the Future of High Speed Air Transport, Strasbourg, France, of the use of this technique at rotational speeds up to and in Nov. 6-8, 1989, Proceedings. Toulouse, France, Cepadues-Editions, excess of 10,000 rpm are given. Holography provides valuable information used to verify and improve numerical modeling of the 1990, p. 282-288. Research supported by ESA. refs fan behavior and is successful in evaluating the achievement of Copyright Very high speed transport, with cruise at velocities beyond design intent. Author Mach 3, only yields practical returns in saved time for very long ranges (assuming modest levels of acceleration and deceleration): A91-12446# With the probable levels of airtrame lift/drag ratio (5-7) and NUMERICAL SIMULATION AND ACTIVE CONTROL OF propulsion system specific fuel consumption from Mach 4 onward, COMBUSTION INSTABILITY IN A RAMJET COMBUSTOR this implies major changes in both fueling and powerplant design SURESH MENON (Quest Integrated, Inc., Kent, WA) AIAA, from those required for subsonic or even supersonic cruise. Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. Powerplant operating in dual modes, with complex interactions 15 p. refs between the variable intakes and nozzles and the core engines (Contract N00014-90-C-0089) and burners seem inevitable. This paper discusses some of the (AIAA PAPER 90-3930) Copyright installation and optimization aspects of such powerplant, and A large-eddy simulation model has been developed to study highlights some of the areas requiring major effort before such combustion instability in a ramjet combustor. A model for premixed systems can be considered. Author combustion is employed in the numerical scheme that explicitly uses the local turbulent flame speed in the governing equation. Combustion instability in the ramjet has been numerically simulated. A91-11348 Two types of instability are observed: a small-amplitude PREDICTION OF TURBULENCE GENERATED RANDOM high-frequency instability and a large-amplitude low-frequency VIBRATIONAL RESPONSE OF TURBOMACHINERY BLADING instability. Both such instabilities have been experimentally THOMAS E. BOOTH and SANFORD FLEETER (Purdue University, observed, and various computed flow features are in good West Lafayette, IN) International Journal of Turbo and Jet-Engines qualitative agreement with experimental observations. Author (ISSN 0334-0082), vol. 6, no. 3-4, 1989, p. 247-255. Research sponsored by USAF. refs A91-12488# Copyright PROCUREMENT AND TESTING OF A 1/5 SCALE ADVANCED An analysis is developed to predict the turbulence generated COUNTER ROTATING PROPFAN MODEL single-degree-of-freedom bending and torsion mode vibrational T. J. KIRKER (Rolls-Royce, PLC, Derby, England) AIAA, response of a turbomachine blade row operating in a subsonic Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. compressible flow field. The turbulence is assumed to be random 13 p. refs in the neighborhood of the blade natural frequency of interest (AIAA PAPER 90-3975) Copyright and to generate a large number of constant amplitude, harmonic, A 1 /5 scale model of an advanced counterrotating • propfan unsteady aerodynamic lift forces and moments on the blading engine was designed and manufactured. The model, which with equally distributed frequencies. The resulting random airfoil incorporates many state-of-the-art measurement techniques used vibrations thus occur at the blade natural frequency. The unsteady to acquire noise, performance, and detailed aerodynamic data, aerodynamics generated by the blade response, i.e., the was designed to allow variations of major design parameters which aerodynamic damping, as well as the effect of blade aerodynamic could influence the performance and/or noise of a propfan coupling are also considered. Author powerplant. Samples of test data are presented from three major test series: a series of 'shake-down tests' with no forward speed A91-11349 simulated, to prove the model and all its support systems; the OPTIMIZATION OF THE ARRANGEMENT OF THE FRONT AND phase I wind tunnel tests, in which basic performance and noise REAR BLADE ROWS OF A TANDEM BLADE CASCADE measurements were acquired; and the phase II wind tunnel tests, GUOCHUAN WU and Ql FENG (Nanjing Aeronautical Institute, in which detailed aerodynamic studies were carried out using laser People's Republic of China) International Journal of Turbo and anemometry and holography. I.S. Jet-Engines (ISSN 0334-0082), vol. 6, no. 3-4, 1989, p. 257-270. refs A91-12524# Copyright SPACE-STRUCTURE DETERMINATION OF THE ACOUSTIC A simple approximate method is proposed for calculating the FIELD GENERATED BY A HELICOPTER TURBOSHAFT minimum-loss relative displacement in the peripheral direction of ENGINE tandem cascades for any given blade configuration and inlet D. BLACODON and S. LEWY (ONERA, Chatillon, France) AIAA, conditions. Predictions based on the method are found to be in Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. good agrement with experimental results obtained for the Turmo 13 p. Research supported by Service Technique des Programmes Illc cascade. In contrast to other method, the approach proposed Aeronautiques and Turbomeca. refs here avoids the need for calculating the tandem cascade flow (AIAA PAPER 90-4012) Copyright field, thus reducing the computational effort. The method has been In order to determine the spinning-mode structure of the implemented in software written in FORTRAN IV. . V.L. acoustic field at each frequency, the nozzle of a Turbomeca TM

46 07 AIRCRAFT PROPULSION AND POWER

333 turboshaft engine was equipped with an array of fixed SCRAMjet diffuser. The cooling requirements and system are microphones. Taking into account the problem of high background covered along with the topics of materials and the hydrogen fuel noise due to the very turbulent internal flow, several methods for tanks and insulation system. A cost analysis is presented and the data processing are tested by numerical simulations. Among these appendices include: information about the subsonic wind tunnel methods is one based on the angular Fourier transform of the test, shock expansion calculations, and an aerodynamic heat flux cross-spectral matrix; however, the output noise remains high. An program. M.G. improvement in this method is observed by canceling the diagonal noise terms in the cross-spectral matrix by a three-signal coherent N91-10064# Aeronautical Research Labs., Melbourne technique. It is shown that the experimental results successfully (Australia). retrieve the theoretical cut-off properties introduced by the nozzle FLIGHT TESTING OF TWO ALLISON T56 ENGINES MODIFIED and the predicted noise generation by the two transonic turbines. TO THE ARL DEVELOPED LOW SMOKE CONFIGURATION R.E.P. P. N. DOOGOOD Jun. 1990 19 p (ARL-PROP-TM-449; AR-006-100) Avail: NTIS HC/MF A03 N91-10059 National Aerospace Lab., Tokyo (Japan). Two Allison T56 engines were modified to the ARL developed EFFECTS OF COOLANT INJECTION ON TURBINE low smoke configuration and placed on wing of separate RAAF AERODYNAMIC CHARACTERISTICS. PART 1: TEST TURBINE P-3C Orion aircraft for extensive flight testing. The initial tests are AND APPARATUS reported and it is concluded that the modification had no adverse SHIGEO INDUE, HIROSHI USUI, MITSUHIRO MINODA, and effect on the performance of the engine. Author HIROYUKI NOSE May 1988 21 p In JAPANESE; ENGLISH summary (NAL-TM-585-PT-1; ISSN-0452-2982; JTN-90-80013) Avail: NTIS N91-10065*# Hamilton Standard, Windsor Locks, CT. HC/MF A03 MEASUREMENT OF UNSTEADY BLADE SURFACE PRESSURE Effects of coolant injection on turbine aerodynamic charac- ON A SINGLE ROTATION LARGE SCALE ADVANCED teristics were investigated with a test turbine. The main air PROP-FAN WITH ANGULAR AND WAKE INFLOW AT MACH flow was unheated and the temperature was about 100 C. The NUMBERS FROM 0.02 TO 0.70 Final Report coolant (secondary air) temperature was kept at about 100 C, P. BUSHNELL, M. GRUBER, and D. PARZYCH Oct. 1988 nearly the same as that of the main flow. The present investigation 45 p MF as supplement is concerned with effects of coolant injected from the following (Contract NAS3-23051) parts on turbine aerodynamic characteristics; (1) stator blades, (2) (NASA-CR-182123; E-4137; NAS 1.26:182123) Avail: NTIS both stator and rotor blades, (3) stator casing, and (4) rotor casing HC/MF A03 CSCL 21/5 (shroud ring). The test facility, the test turbine, and the measuring Unsteady blade surface pressure data for the Large-Scale systems are described. NASDA Advanced Prop-Fan (LAP) blade operation with angular inflow, wake inflow and uniform flow over a range of inflow Mach numbers N91-10060 National Aerospace Lab., Tokyo (Japan). of 0.02 to 0.70 is provided. The data are presented .as Fourier EXPERIMENTAL INVESTIGATION ON THE EFFECT OF coefficients for the first 35 harmonics of shaft rotational frequency. COOLANT INJECTION ON TURBINE AERODYNAMIC Also presented is a brief discussion of the unsteady blade response CHARACTERISTICS. PART 2: EFFECTS OF INJECTION FROM observed at takeoff and cruise conditions with angular and wake ROTOR CASING WITH 30 DEG SLANTED HOLES inflow. Author HIROSHI USUI, SHIGEO INOUE, MITSUHIRO MINODA, and HIROYUKI NOUSE Jun. 1988 25 p In JAPANESE; ENGLISH N91-10066# Rolls-Royce Ltd., Derby (England). summary AERO ENGINE DESIGN FACTORS FOR A LOW FUEL PRICE (NAL-TM-587-PT-2; ISSN-0452-2982; JTN-90-80014) Avail: NTIS SCENARIO HC/MF A03 . • S. J. HARTROPP 15 May 1989 20 p Presented at Canadian Using a test turbine, the effect of coolant injection was Aeronautics and Space Institute, Ottawa, Ontario, 15-17 May investigated on turbine aerodynamic characteristics. The effects 1989 of the coolant injection from a rotor casing with 30 deg slanted (PNR-90681; ETN-90-97928) Copyright Avail: NTIS HC/MF holes are described. The discussed turbine efficiency introduced A03 is based on torque, rotational speed, mass flow rate, and the v The driving parameters for aero engine design were reassessed radial and tangential distributions of total pressure and flow angles. to account for the stabilization of fuel price in the vicinity of 50 It may be concluded that there are some reductions in total pressure cents per gallon. A program embracing studies in the fields of losses and increases in outlet flow angles in the tip region caused operating cost analysis, reliability research and engine specific by the coolant injection. . NASDA thrust effects established principles reflecting the importance of engine direct operating cost. The same factors influence the aircraft N91-10061*# Ohio State Univ., Columbus. Dept. of Aeronautical life cycle cost, and as legislative compliance, operator acceptance and Astronautical Engineering. and passenger appeal. The effect of applying these principles to SUPERSONIC COMBUSTION ENGINE TESTBED, HEAT a new powerplant and the ongoing development of current LIGHTNING Final Report powerplants is evaluated. ESA D. HOYING, C. KELBLE, A. LANGENBAHN, M. STAHL, M. TINCHER, M. WALSH, and S. WISLER May 1990 112 p Prepared in cooperation with Universities Space Research N91-10068# Rolls-Royce Ltd., Derby (England). Association, Houston, TX Sponsored by NASA THE EVOLUTION OF THE BYPASS ENGINE (NASA-CR-187010; NAS 1.26:187010) Avail: NTIS HC/MF A06 G. M. LEWIS 27 Oct. 1989 14 p Presented at DGLR CSCL 21/5 Symposium on 50 Years of Jet-Powered Flight, Munich, Fed. The design of a supersonic combustion engine testbed (SCET) Republic of Germany, 26-27 Oct. 1989 aircraft is presented. The hypersonic waverider will utilize both (PNR-90707; ETN-90-97939) Copyright Avail: NTIS HC/MF supersonic combustion ramjet (SCRAMjet) and turbofan-ramjet A03 engines. The waverider concept, system integration, electrical The by-pass principle was understood in the early days of the power, weight analysis, cockpit, landing skids, and configuration jet engine. Exploitation of the known concepts progressed as the modeling are addressed in the configuration considerations. The inherent design problems were solved. The advances which subsonic, supersonic and hypersonic aerodynamics are presented reduced the mechanical design problems of aircraft engines and along with the aerodynamic stability and landing analysis of the components are summarized. Engine designs representing aircraft. The propulsion design considerations include: engine significant steps in the evolution of the by-pass engine are selection, turbofan ramjet inlets, SCRAMjet inlets and the identified. ESA

47 07 AIRCRAFT PROPULSION AND POWER

N91-10070# Rolls-Royce Ltd., Bristol (England). K. GODDARD 6 Apr. 1990 7 p Presented at Avmark Services TECHNOLOGY UPDATE OF EARLY GAS TURBINE DESIGNS Ltd. 1990 Update Aircraft Noise Attenuation Conference, 4-6 Apr. ALAN RHODES Derby, England 21 Sep. 1989 12 p Presented 1990 at Tactical V/STOL Aircraft Symposium, New Bern, NC, 19-21 (PNR-90755; ETN-90-97959) Copyright Avail: NTIS HC/MF Sep. 1989 A02 (PNR-90710; ETN-90-97941) Copyright Avail: NTIS HC/MF A study to show that re-engining is the only satisfactory way A03 in converting today's noisy stage 2 airliners to give stage 3 The power plant of the Pegasus gas turbine is described. The compliance with clear and comfortable margins, together with service hours of Pegasus from 1969 to 1989 in different countries enhanced performance and improved fuel consumption is are presented. The design evolution of several modules and presented. The importance of eliminating stage 2 operations for subassemblies are shown. The improvements obtained by the total the benefit of the community is summarized. The advantages and package of changes introduced through the Pegasus update driving force behind previous post war re-engining programs are program are summarized. The application of up to date technology described. ESA to the system provides a cost effective way of bringing to the operator a competitive product. ESA N91-10076# Rolls-Royce, Inc., Atlanta, GA. DESIGN/DEVELOPMENT ISSUES FOR HIGH BYPASS RATIO N91-10071# Rolls-Royce Ltd., Bristol (England). FANS FUTURE SUPERSONIC TRANSPORT POPULSION R. R. MORITZ and D. J. NICHOLAS (Rolls-Royce Ltd., Derby, OPTIMIZATION England ) Derby, England 15 May 1990 16 p Presented at B. W. LOWRIE Derby, England 8 Nov. 1989 8 p Presented 371h Annual General Meeting and 2nd Symposium on Propulsion, ar European Symposium on Future Supersonic/Hypersonic Toronto, Ontario, 15 May 1990 Transport, Strasbourg, France, 8-9 Nov. 1989 (PNR-90758; ETN-90-97960) Copyright Avail: NTIS HC/MF (PNR-90737; ETN-90-97950) Copyright Avail: NTIS HC/MF A03 A02 Some of the lessons learned in the course of the generation The interest in second generation supersonic transport is of the RB211 series of engines are presented. The early stages considered. The propulsion systems necessary for a commercially of RB211 development are underlined. Recent experience from and environmentally acceptable aircraft are identified. It is shown present day RB211 program staff is stressed. The RB211 family that for an isolated installation the tandem fan concept is the of engine is compared to other high bypass ratio civil engines. best. A feature of most other systems is the increased installation The most obvious differences is in its use of lower aspect ratio cross section required at a cruise and this causes penalizing levels fan blades. This feature is credited with a wide range of benefits of ware drag of an isolated system. Typical weight penalities are including better performance, durability and cost of ownership. found to be of less importance than the wave drag. The need to These and other points are developed. ESA consider integrated rather than isolated installations is emphasized. ESA N91-10927# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Goettingen (Germany,, F.R.). Inst. fuer Aeroelastik. N91-10072# Rolls-Royce Ltd., Bristol (England). DETERMINATION OF UNSTEADY AERODYNAMIC FORCES APPLICATIONS OF THERMALLY SPRAYED COATING ON ENGINES WITH A VIEW TO FLUTTER INVESTIGATIONS SYSTEMS IN AERO ENGINES [BESTIMMUNG INSTATIONAERER T. N. RHYS-JONES Derby, England 15 Sep. 1989 16 p TRIEBWERKSLUFTKRAEFTE FUER DIE ANWENDUNG BEI Presented at 12th International Conference on Thermal Spraying, FLATTERUNTERSUCHUNGEN] London, England, 1989 HERMANN TRIEBSTEIN, GUENTER SCHEWE, and HARTMUT (PNR-90750; ETN-90-97955) Copyright Avail: NTIS HC/MF ZINGEL (Messerschmitt-Boelkow-Blohm G.m.b.H., Bremen, A03 Germany, F.R. ) In its Contributions in the Field of Aeroelastics The principle thermal spray coating process used in aero engine on the Occasion of the 60th Anniversary of Professor Dr.-lng. applications are oultlined. Particular attention is given to high Habil. Hans Wilhelm Foersching p 141-168 Apr. 1990 In velocity combustion and plasma spray techniques. The use of GERMAN; ENGLISH summary coatings for wear resistance, clearance control, environmental Avail: NTIS HC/MF A13 degradation resistance and thermal barrier applications are Experimental investigations of the steady and unsteady described. The characteristics of the coatings exhibit a marked aerodynamic forces were performed on an ejector engine model dependence on the thermal spray technique itself, the source of and a wing/engine combination in the subsonic and transonic materials used and the spray process parameters. ESA regimes. The aim was to find out how well the commonly used aerodynamic models for flutter calculations correspond to the actual N91-10074# Rolls-Royce Ltd., Derby (England). conditions observed in engines. The comparison of experimental HEAT TRANSFER IN AERO ENGINE GAS TURBINES, PART 1 and theoretical results shows that the linear lifting surface theory C. T. J. SCRIVENER 15 Jun. 1990 37 p Submitted for provides quite accurate unsteady aerodynamic forces. The effects publication of Mach number and reduced frequency are correctly described. (PNR-90754-PT-1; ETN-90-97958) Copyright Avail: NTIS For the wing/engine combination the unsteady interference effect HC/MF A03 for engine oscillation on the lower side of the wing is strongly Some turbine blade designs, and some important aspects of influenced by flow separation at the wing/pylon connection. In airfoil internal heat transfer are described. The airfoil external heat general, the unsteady aerodynamic forces on the wing are small transfer is discussed. For the rotor blades of high temperature and, at this order of magitude, can be correctly calculated with gas turbines, modern multipass cooling configurations provide the linear lifting surface theory. The interference effect on the efficient effective cooling. They can provide low coolant flow, oscillating wing on the engine is much more significant. ESA consistent with this high temperature capability. The heat transfer in airfoil internal passages is well understood. This includes both N91-11018# Stuttgart Univ. (Germany, F.R.). Inst. fuer plain passages, and the characteristics of bends, and enhancement Luftfahrtantriebe. by ribs, pedestals and impingement. The areas where future heat TEST LAUNCH FOR TURBOAIRCRAFT ENGINE. transfer research is required, in order to understand the basic DESCRIPTION OF THE INSTALLATION process involved, are summarized. ESA [HOCHENPRUEFSTAND FUER TURBOFLUGTRIEBWERKE. BESCHREIBUNG DER ANLAGE] N91-10075# Rolls-Royce Ltd., Derby (England). 1987 23 p In GERMAN RE-ENGINING: REAL STAGE 3 COMPLIANCE PLUS OTHER (ILA-87-A-02; ETN-90-97879) Avail: NTIS HC/MF A03 BENEFITS In the framework of aeronautical research, a test bench for

48 08 AIRCRAFT STABILITY AND CONTROL aircraft engine was built. Using different economic principles, such 08 as compact construction, it was possible to build a modern test installation at relatively low cost. The environmental noise problem AIRCRAFT STABILITY AND CONTROL was particularly studied and solved. ESA Includes aircraft handling qualities; piloting; flight controls; and autopilots.

A91-10955 ALL-ELECTRIC FLIGHT CONTROL EXPERIMENTS AND EXPERIMENTS WITH A SIDESTICK ON THE CONCORDE N91-11019# Universitaet der Bundeswehr, Hamburg (Germany, [EXPERIMENTATION SUR CONCORDE D'UN SYSTEME DE F.R.). Fachbereich Maschinenbau. COMMANDES DE VOL TOUT ELECTRIQUE ET D'UN INTEGRATION OF MODEL AND KNOWLEDGE BASED MINI-MANCHE] DIAGNOSIS, WITH THE EXAMPLE OF A TURBOJET ENGINE Y. NEGRE (Aerospatiale, Toulouse, France) and G. CORMERY Ph.D. Thesis [INTEGRATION VON MODELLBEZOGENER UND IN: European Symposium on the Future of High Speed Air WISSENSBASIERTER DIAGNOSE AM BEISPIEL EINES Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. TURBOFLUGTRIEBWERKES] Toulouse, France, Cepadues-Editions, 1990, p. 53-57. In French. UWE WILLAN 1990 169 p In GERMAN Sponsored by Copyright Bundesministerium der Verteidigung The framework in which experiments were made on the (ETN-90-97900) Avail: NTIS HC/MF A08 supersonic Concorde aircraft to study electrical digital flight controls The early detection of failures in technical processes in general, required to overcome longitudinal instability is presented. and in aircraft engines in particular is of great importance. Besides Installation of a sidestick to replace normal wheel and stick the precise statement of place and size of a failure already apparent commands also became part of this study. Ergonometric (diagnosis), it is also of interest to predict its occurrence (prediction). evaluations were carried out to achieve an optimum configuration The aim of this investigation is to utilize for an actual project, of the sidestick from the pilot-aircraft symbiotic viewpoint. This various processes which are able to fulfill these tasks. The point experimental system also considered active control of wing is the possible utilization of a microcomputer. Two basic principles aerodynamic loads, the control of wing camber, and the increase are carried out, the model based diagnosis and the knowledge in flutter speeds. Two flight control principles evolved from these based diagnosis. The two systems are presented with some criteria tests: (1) the stick load in pitch should be constant throughout for the choice of the system more adapted for use in precise the flight envelope, and (2) the load applied to the stick to give a actual cases. A work developed in this connection for an aircraft given roll rate should be roughly constant throughout the flight engine has led to the production of largely automatized model envelope. R.E.P. which is valid for any gas turbine. The design of an expert system for the diagnosis of the part of an aircraft which cannot be modeled, is stated. Various processes suitable for connecting together both A91-11155 types of diagnosis are presented and discussed. The resulting PERFORMANCE-ROBUSTNESS TRADE OFF OF integrated system unites the advantages of both methods, not EIGENSTRUCTURE ASSIGNMENT APPLIED TO ROTORCRAFT taking into account their drawbacks. ESA M. INNOCENTI and C. STANZIOLA (Pisa, Universita, Italy) Aeronautical Journal (ISSN 0001-9240), vol. 94, April 1990, p. 124-131. refs Copyright The eigenstructure assignment (EA) method, used in the past for synthesis of helicopter flight control systems in the time domain, is discussed, and its properties are compared with the standard linear quadratic regulator (LQR) method in order to define a loop N91-11022# Advisory Group for Aerospace Research and transfer recovery procedure similar to that of the LQG/LTR. The Development, Neuilly-Sur-Seine (France). Propulsion and EA method is considered simpler, since it offers a trial and error Energetics Panel. procedure, in which the closed loop system is expressed by the TEST CASES FOR COMPUTATION OF INTERNAL FLOWS IN shape of the system's response, but the method does not AERO ENGINE COMPONENTS guarantee the stability margins. The LQR method uses a functional LEONHARD FOTTNER, ed. (Universitaet der Bundeswehr minimization procedure, requiring long iterations, but it guarantees Muenchen, Neubiberg, Germany, F.R. ) Jul. 1990 393 p the stability margins. Synthesis by both methods is compared for (AGARD-AR-275; ISBN-92-835-0573-5) Copyright Avail: NTIS two applications. The two systems show similar results in terms HC/MF A17; Non-NATO Nationals requests available only from of robustness. It is concluded that the EA method, although it is AGARD/Scientific Publications Executive not capable of guaranteeing minimum stability margins, may still An analytical and experimental data base intended as support play an important role in flight control system analysis when in the development of new and the refinement of existing codes robustness issues are of major concern. B.P. for computing internal flows in aero engine components, specifically in cascades, compressors, turbines and ducts ahead of and A91-11158 between them is presented. All the analytical test cases described PILOT MODELLING TECHNIQUES FOR THE ANALYSIS OF are relevant to steady, 2-dimensional, inviscid flow calculations. AIRCRAFT LINEAR DYNAMIC BEHAVIOUR The experimental test cases are relevant to steady 2-dimensional, M. INNOCENTI (Auburn University, AL) and R. L. MINCIOTTI (Pisa, quasi- or fully 3-dimensional flow calculations for viscous flows in Universita, Italy) Aeronautical Journal (ISSN 0001-9240), vol. 94, axial turbo-machinery components. These data are believed to May 1990, p. 153-164. Research sponsored by CNR. refs represent the highest quality analytical and experimental test cases Copyright available today. However, in appraising the large amount of The evaluation of aircraft flying qualities has always required a experimental data submitted, the Working Group necessarily had high level of integration between aircraft dynamic response and to consider what the requirements for a satisfactory test case are human operator properties. Today, the linear pilot-aircraft behavior and what experimental precautions and problems have to be is a mature technology summarized by the publication of the military addressed and overcome. It also became apparent where gaps specifications MIL-STD-1797. The present paper outlines the exist in the available test cases and what is required for the contribution of pilot modeling techniques to such endeavor and future. Author their use as a tool in the prediction of aircraft handling qualities

49 08 AIRCRAFT STABILITY AND CONTROL characteristics by verifying their output in a Neal-Smith criterion (NAL-TM-576; ISSN-0452-2982; JTN-90-80005) Avail: NTIS framework. The objective is to complete the understanding of HC/MF A03 • handling qualities in the linear part of .the flight envelope (such as • Experimental oscillation test equipment of NAL (National tracking) and to initiate work in the large amplitude maneuvers. Aerospace Laboratory) was used for the whole-craft-terrestrial The results have produced an interactive computer-aided software oscillation test of the low-noise experimental STOL craft. The main useful for pilot-in-the-loop analysis. . Author components of the equipment include a system for analyzing multi-point applied oscillation, an oscillation data control system A91-11820 and a model'analyzer. An oscillation test of the actual craft will MATHEMATICAL MODELLING FOR ANALYSIS OF need the exchange between several large scale or personal NONLINEAR AIRCRAFT DYNAMICS computers of the data obtained in the oscillation analyses and A. L. GONZALEZ BLAZQUEZ (ESA, Paris, France). (George the experimental • oscillation test. The oscillation control system Washington University, University of Virginia, and NASA, assures the interexchange of data between different data types Symposium on Computational Technology for Flight Vehicles, and the conversion of information media. This report presents the Washington, DC, Nov. 5-7, 1990) Computers and Structures (ISSN configuration and funtions of the system for analyzing multi-point 0045-7949), vol. 37, no. 2, 1990, p. 193-197. refs applied oscillation and describes the role of the oscillation data Copyright control system in the whole-craft oscillation test. The report also A model for the analysis of the •nonlinear motion of a swept-wing described the developed software and its actual applications. aircraft at high angles of attack is presented. The most difficult . . NASDA part of the mathematical formulation and the main source of the highly nonlinear motion is. the aerodynamic behavior of. the aircraft: N91-10078*# National Aeronautics and Space Administration. In order to understand it, the basic aerodynamic phenomena of Langley Research Center, Hampton, VA. delta- and swept-wing aircraft are reviewed, deriving the main DETERMINATION OF THE PRESSURE DRAG OF AIRFOILS BY aspects affecting the motion dynamics. Aerodynamic data obtained INTEGRATION OF SURFACE PRESSURES from wind-tunnel tests have been analyzed and used to obtain WILLIAM H. PHILLIP'S Oct.'1990 26 p (NASA-TM-102722; NAS 1.15:102722) Avail: NTIS HC/MF A03 the force. and moment modeling. A general formulation of the : dynamic equations valid for high angles of attack and sideslip is CSCL01/3 ..... presented. . . --.. Author A study was conducted of the causes of pressure drag of subsonic airfoils. In a previous paper by the author, the pressure drag is obtained by calculating the total drag from the momentum A91-12928* defect in the boundary .layer at the trailing 'edge .and subtracting DESIGN TECHNOLOGIES UTILIZED IN THE DEVELOPMENT the friction drag obtained from integration of surface friction along OF THE B-2 FLIGHT CONTROL SYSTEM the chord. Herein, the pressure drag is obtained by integrating J. F. MOYNES (Northrop Corp., B-2 Div., Pico Rivera, CA) AIAA, the streamwise components.of surface pressure around the airfoil. AHS, and ASEE, Aircraft Design, Systems, and Operations Studies were made to verify, the accuracy of the integration Conference, Dayton, OH, Sept. 17-19, 1990. 10 p. procedure. The values of pressure drag were much smaller than (AIAA PAPER 90-3254) Copyright . i those obtained by the previous method. This lack of agreement is This paper presents an overview of the holistic issues involved attributed to the difficulty of calculating boundary .layer conditions in developing a flight control system for a high performance, relaxed in the vicinity of the trailing edge and to the extreme sensitivity of static stability,, stealth aircraft such as the B-2. The paper touches the circulation and lift to the trailing edge conditions. The results on the conflicts and trades which are presented by low observables, of these studies are compared with those of previous performance, mission requirements, structural loads and dynamics, investigations. . . Author ride quality, and stability and control. For purposes of illustration a design example is presented addressing how the principal stability feedbacks were chosen and how they influenced the flight control N91-10079*# National Aeronautics and Space Administration. system architecture. • Author Hugh L. Dryden Flight Research Facility, Edwards, CA. FLIGHT CHARACTERISTICS OF A MODIFIED SCHWEIZER SGS1-36 SAILPLANE AT LOW AND VERY HIGH ANGLES OF A91-12929# ' ATTACK THE DESIGN APPROACH USED IN THE SYNTHESIS OF THE ALEXG..SIM Jul. 1990 48 p • ' B-2 LATERAL-DIRECTIONAL CONTROL LAWS (NASA-TP-3022; H-1563; NAS 1.60:3022) Avail: NTIS HC/MF P. W. SAUNDERS and D. A. HAGEMEYER (Northrop Corp., B-2 A03 CSCL 01 /3 Div., Pico Rivera, CA) AIAA, AHS, and ASEE, Aircraft Design, A manned flight research program using a modified sailplane Systems, and Operations Conference, Dayton; OH, Sept: 17-19, was conducted to very high angles of attack at the NASA-Ames. 1990. 11 p. • •- . . !-. ••••..-• Piloting techniques were established that enabled the pilot to attain (AIAA PAPER 90-3255) Copyright and stabilize on an angle of attack in the 30 to 72 deg range. The B-2 bomber mission requirements dictated revolutionary Aerodynamic derivatives were estimated from the flight data-for changes in the aircraft's configuration which led to the rebirth of both low and very high angles of attack and are compared-to the earlier Northrop all-wing design concept. Inherent in the wind'tunnel data. In addition, limited performance and trim data application of all-wing aircraft are some fundamental lateral- are presented. - ' • Author directional controllability problems due to the lack of vertical surfaces. To address these problems, modern control theory was N91-11023 Oklahoma State Univ., Stillwater. applied to define a stability-augmentation system that would operate A NEW APPROACH TO THE FLIGHT CONTROL SYSTEM in a highly reliable fly-by-wire flight-control system. This has led to RECONFIGURATION FOLLOWING A BATTLE DAMAGE significant improvements in the flying qualities and utility of the AND/OR GENERIC FAILURE ON A CONTROL SURFACE Ph.D. flying wing, as is evident in the early flight test results of the B-2. Thesis . • •• Author MARCELLO ROSARIO NAPOLITANO 1989 200 p • Avail: Univ. Microfilms Order No. DA9019502 N91-10077 National Aerospace Lab.,'Tokyo (Japan). STOL Battle damages and/or generic failures are the cause of many Aircraft Project Group. ' ' accidents involving the loss of aircraft. Particular'approaches for THE FULL-BODY GROUND VIBRATION TESTS USING THE three tasks of the overall flight control system reconfiguration LOW-NOISE STOL TEST PLANE [TEISOUON SUTORU problem are considered. These tasks are: damaged model JIKKENKI NO ZENKI CHIJOU SHINDOU SHIKEN (SHINDOU estimation, reconfiguration law design'and'feedback structure DETA KANRISHISUTEMU)] redesign. First, the estimated model of the damaged aircraft is Oct. 1987 30 p In JAPANESE obtained by using a multiple model 'Kalman filtering approach.

50 09 RESEARCH AND SUPPORT FACILITIES (AIR)

Then, a particular algorithm is applied to the flight control 09 reconfiguration. The determination of the desired control law, which can adapt in a very short period of time to a major damage on a RESEARCH AND SUPPORT FACILITIES (AIR) main control surface, is obtained by making use of the recent control and response time histories. Furthermore, a particular 0 approach is proposed in order to calculate a new set of feedback Includes airports, hangars and runways; aircraft repair and overhaul gains of the flight control system such that dynamic uncoupling facilities; wind tunnels; shock tube facilities; and engine test and desirable handling qualities are retained even after the damage. blocks. The model estimation, the control algorithm, and the feedback gains updating process were codified in computer simulation programs for a 6 degrees of freedom aircraft model. The simulation A91-11758# results of the reconfiguration are presented. Dissert. Abstr. COMPARISON OF AFTERBODY TEST SETUPS FOR COMBAT AIRCRAFT MODEL M. HUGOUVIEUX, M. LYONNET, and J. P. LEDY (Supersonic Tunnel Association, Semi-annual Meeting, 73rd, Urbana, IL, Mar. 26, 27, 1990) ONERA, TP no. 1990-70, 1990, 8 p. (ONERA, TP NO. 1990-70) The process of defining test setups for the S2MA wind tunnel N91-11024 Oxford Univ. (England). to compare twin-engine combat aircraft afterbody drag for shape H INFINITY-DESIGN AND THE IMPROVEMENT OF optimization purposes is studied. The propulsion system is HELICOPTER HANDLING QUALITIES Ph.D. Thesis simulated by compressed-air jets. Preliminary research consisted ANDREW YUE 1988 245 p of afterbody pressure measurement, local weighing of the afterbody, Avail: Univ. Microfilms Order No. BRD-89468 and global weighing of the model and support assembly in order The results of a study into the use of H(infinity)-optimization to determine the drag coefficient. Two types of model setup for the design of feedback control laws for improving the handling, systems were considered. To validate the useful Mach range of qualities of a Lynx helicopter are presented. An important these measuring techniques with each of the two setups, improvement to the H(infinity)-optimization procedure is the preliminary tests in the S3MA wind tunnel were conducted with a reduction in the number of iterative steps in the gamma iteration model-support system half the scale of the one planned for S2MA. before convergence to the optimal gamma. Some new algorithms Results of the S3MA are given and the S2MA qualification tests are derived which significantly reduce the computation time for are described. Drag differences of 0.0002 on afterbody shapes of the gamma iteration. Both 2-block and 4-block cases are combat aircraft with jet engine simulation were measured. L.K.S. considered. Control laws are designed for precise control of pitch and roll attitude, yaw rate and heave velocity. Analysis of the raw A91-11760# helicopter showed the need for a stability augmentation system THE CEPRA 19 ANECHOIC WIND TUNNEL [LA SOUFFLERIE as the dynamic characteristics of the unaugmented helicopter do ANECHOIQUE CEPRA 19] not comply with military helicopter handling qualities requirements. G. FOURNIER (ONERA, Chatillon, France) (Groupe Results from current research on helicopter handling qualities were Franco-Sovietique, Sous-Groupe de used as guidelines in order to define the required dynamic Aerodynamique-Structure-Acoustique, Reunion, Chatillon, France, characteristics. A six-degree of freedom nonlinear simulation was June 25-27, 1990) ONERA, TP no. 1990-72, 1990, 15 p. In used to analyze the helicopter dynamic time histories. A possible French. solution to the problem of incorporating helicopter handling qualities (ONERA, TP NO. 1990-72) in the design of robust controllers is to use a two-degree of freedom A review of the development and recent additions and controller structure. This is illustrated using both H2 and refinements to the CEPRA 19 anechoic wind tunnel are presented. H(infinity)-optimization. A piloted simulation study to assess the Airflow speeds of 100 m/s are attained in the 2-m-diameter section effectiveness of advanced control laws was initiated at the Royal and 50 m/s in the 3-m section. The turbulence and acoustic Aerospace Establishment (RAE), Bedford. The trials were carried disturbance levels are very low. The principal tests have been out in the single seat cockpit flight simulator, at the Flight Research made on the noise of helicopter rotors and jet engine exhausts. Division and represent the first ever real-time piloted simulation The characteristics of this wind tunnel are described, and some using a H(infinity)-controller. Dissert. Abstr. sample test results are presented. • R.E.P. ' ' i A91-11766# S4MA HYPERSONIC FACILITY - FLOW ANGULARITIES MEASUREMENTS IN THE S4MA WIND TUNNEL M. GRANDJACQUES (ONERA, Modane, France) (Supersonic N91-11025# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich Tunnel Association, Semi-annual Meeting, 73rd, Urbana, IL, Mar. (Germany, F.R.). Aircraft Div. 26, 27, 1990) ONERA, TP no. 1990-85, 1990, 16 p. REVIEW OF ACTIVE STRUCTURAL CONTROL SYSTEMS AND (ONERA, TP NO. 1990-85) FLIGHT TEST TECHNIQUES FOR DYNAMIC STABILITY In order to gain better knowledge about the Mach 6.4 nozzle INVESTIGATIONS of the Hermes spaceplane, flow angularities measurements were OTTO SENSBURG Apr. 1989 36 p Presented at Gabriel conducted in the S4MA hypersonic wind tunnel of ONERA, in Coupry Memorial Lecture April 1989. The test was done in three parts by means of five-holed (MBB/FYT256/S/PUB/361/A; ETN-90-97845) Copyright Avail: hemispherical probes mounted on a rake. The first part consisted NTIS HC/MF A03 of calibrating the probes. Probe coefficients of sensitivity to the The influence of G. Coupry on aerolastics with focus on his flow direction were determined by varying the rake angle of attack studies of dynamic response to atmospheric turbulence with the and sideslip. Manufacturing defects in the probe were also introduction of a non cyclindrical gust, gust alleviation with an determined by rotating them 180 deg on axis. During the second open loop flight control system, and vibration testing by transient part of the test, clinometric probing of the test section was excitation for application to flight flutter tests is reported. His work conducted. The same probe rake was mounted on a device allowing on dynamic response to atmospheric turbulence proved that for it to be moved longitudinally in the jet without varying the probe modern transport airplanes a non cyclindrical gust must be used direction. The tests produced coherent results and showed flow to achieve a weight optional design. The methods he developed convergence toward the nozzle axis in the sound core, with for identification of dynamic stability parameters finally led to the angularities of approximately 0.5 deg at the edge and decreasing way to an integrated flight test procedure. ESA on the vanishing axis. L.K.S.

51 09 RESEARCH AND SUPPORT FACILITIES (AIR)

A91-12536*# National Aeronautics and Space Administration. N91-10082 National Aerospace Lab., Tokyo (Japan). Langley Research Center, Hampton, VA. FUNCTION AND PERFORMANCE OF VISUAL SIMULATION THE DESIGN OF TWO SONIC BOOM WIND TUNNEL MODELS UNIT OF FLIGHT SIMULATION TEST FACILITY FROM CONCEPTUAL AIRCRAFT WHICH CRUISE AT MACH KAORU WAKAIRO, HIROYASU KAWAHARA, AKIRA WATANABE, NUMBERS OF 2.0 AND 3.0 and MASANORI OKABE Feb. 1988 28 p In JAPANESE ROBERT J. MACK (NASA, Langley Research Center, Hampton, (NAL-TM-581; ISSN-0452-2982; JTN-90-80009) Avail: NTIS VA) and KATHY E. NEEDLEMAN (Lockheed .Engineering and HC/MF A03 Sciences Co., Hampton, VA) .AIAA, Aeroacoustics Conference, The visual simulation unit with CGI (Computer Generated 13th, Tallahassee, FL, Oct. 22-24, 1990. 8 p. refs Imagery) enables a simulation of natural conditions by obtaining a (AIAA PAPER 90-4026) Copyright wide view thanks to an increase in the number of display channels A method for designing wind tunnel models of conceptual, which catch-sight of a wider range of flight. It is characterized by low-boom, supersonic cruise aircraft is presented. Also included is the ability to indicate an object in motion within sight as well as a review of the procedures used to design the conceptual low-boom to add, delete, change, or otherwise revise the configuration of aircraft. In the discussion, problems unique to, and encountered the ground or buildings generated as a simulated vision. The during, the design of both the conceptual aircraft and the wind configuration, function, and capacity of the visual simulation unit tunnel models are outlined. The sensitivity of low-boom with the CGI was introduced in consideration of the necessity to characteristics in the aircraft design to control the volume and lift cope with a simulation test intended for the research and equivalent area distributions was emphasized. Solutions to these development of a new aircraft model including STOL at the National problems are reported; especially the two which led to the design' Aerospace Laboratory (NAL). Attention was paid in the designing of the wind tunnel model support stings. Author of the unit to the ease of preparation of a three-dimensional visual model, the ability to simulate a daytime sight in color and nighttime A91-12724 lights of various kinds, the ability to easily simulate natural APPLICATION OF CRYOGENIC WIND TUNNEL WITH LIQUID conditions and the ease of maintenance. NASDA NITROGEN AND SELECTION OF ITS TEMPERATURE LEVEL GUANG-HUA Jl (Xian Jiaotong University, People's Republic of N91-10083*# Nevada Univ., Reno. Engineering Research and China) (International Cryogenic Engineering Committee, Development Center. International Institute of Refrigeration, Chinese Association of NUMERICAL INVESTIGATIONS IN THREE-DIMENSIONAL Refrigeration, et al., International . Cryogenic Engineering INTERNAL FLOWS Semiannual Status Report, 1 Jan. - 30 Conference, 13th, Beijing, People's Republic of China, Apr. 24-27, Jun. 1990 ' '•'• 1990) Cryogenics, Supplement (ISSN 0011-2275), vol. 30, Sept. WILLIAM C. ROSE 11 Sep. 1990 29 p - 1990, p. 183-186. refs (Contract NCC2-507) Copyright (NASA-CR-186958; NAS 1.26:186958) Avail: NTIS HC/MF A03 An account is given of the essential features and advantages CSCL 14/2 of cryogenic wind tunnels, which allow the testing of models at The flow in the transonic test facility 'was investigated using • full scale Reynolds numbers as well as the appropriate. Mach the three dimensional computational fluid dynamics techniques. numbers. Attention is given to the design and results of a cryogenic The application of the full Navier-Stokes three dimensional code wind tunnel operational characterization experiment involving the to the flow qualities in the contraction section of transonic wind effects of nitrogen vapor condensation, which degrades the degree tunnel is discussed. Initially, two dimensional solutions indicated of analogous behavior between the cryogenic fluid employed and the possibility for large secondary flow to exist as a result of the atmospheric air. The experimental results obtained establish that asymmetries involved in the contraction section as it is constructed. the lower limit of cryogenic fluid temperatures must be the The results of a full three dimensional solution indicate that only homogeneous condensation temperature of nitrogen. O.C. minor pressure variations actually occur in the contraction section within any given cross flow plane. -Further analysis of the three A91-1289Q# dimensional solution indicated that these slight lateral pressure RESIDUAL INTERFERENCE AND WIND-TUNNEL WALL gradients lead to negligible secondary flows, except within a small ADAPTATION region in the corners within the boundary layer. On the basis of M. MOKRY (National Research Council of Canada, High Speed present solution, it would not be expected that any flow Aerodynamics Laboratory, Ottawa) AIAA Journal (ISSN asymmetries and/or secondary flow present within contraction 0001-1452), vol. 28, Oct. 1990, p. 1772-1781. Previously cited in section are associated with the methods by which the contraction issue 09, p. 1294, Accession no. A89-25130. refs is implemented in its present configuration. Author Copyright N91-10084# Federal Aviation Administration, Atlantic City, NJ. N91-10080 National Aerospace Lab., Tokyo (Japan). FAA AIR TRAFFIC OPERATIONAL EVALUATION OF CONFIGURATION, FUNCTION AND PERFORMANCE OF THE AUTOMATED SURFACE OBSERVING SYSTEM (ASOS) FLIGHT SIMULATION TEST FACILITY AND ITS MOTION ELIZABETH TURCICH and BRUCE E. WARE Oct. 1990 35 p SIMULATION SYSTEM [HIKOU SHIMYURESHON SHIKEN (DOT/FAA/CT-TN90/42) Avail: NTIS HC/MF A03. SETSUBI MOSHON MOGI SOUCHI NO KOUSEI OYOBI The results of the Federal Aviation Administration (FAA) Air KINOUSEINOU] Traffic Operational Evaluation of Automated Surface Observing HIROYASU KAWAHARA, MASANORI OKABE, AKIRA System (ASOS) at the Tulsa International Airport, Oklahoma are WATANABE, TOSHIO BANDO, and KAORU WAKAIRO Jun. detailed. The evaluation was conducted in order to obtain 1987 38 p In JAPANESE operational air traffic controller reaction to the AAI Corporation (NAL-TM-575; ISSN-0452-2982; JTN-90-80004) Avail: NTIS preproduction ASOS. The evaluation resulted in numerous HC/MF A03 recommendations to improve the ASOS prior to production. The National Aerospace Laboratory (NAL) has fixed the Author simulation control unit, the visual simulation unit and the motion simulation unit over a period of three years and four months since 1980. The present report explains the configuration, function, and N91-10086# Institut Franco-Allemand de Recherches, Saint-Louis capacity of the motion simulation unit. For multi-freedom-degree (France). motion simulation units, various kinds of systems have been THE ISL HYPERSONIC SHOCK TUNNEL AND ITS developed and are in use such as Zimbal method, joint-motion INSTRUMENTATION suspension method, joint-motion support method, and special drive G. SMEETS 1 Jun. 1989 22 p Presented at VKI (AGARD method. The joint-motion six-freedom-degree support method was Ad-Hoc Study Group on Hypersonic'Technology-Subgroup, on adopted. NASDA Hypersonic Wind Tunnel Instrumentation) Conference, 16 May

52 09 RESEARCH AND SUPPORT FACILITIES (AIR)

1989 and landing approach. The effects of wind results in a modified (ISL-CO-213/89; ETN-90-97572) Avail: NTIS HC/MF Ap3 dynamic response of the aircraft as well as in flight performance Th ISL hypersonic shock tunnel is described and the variation. In each case flight path deviation can occur, more or characteristics of hypersonic flows which can be produced in the less controlled by the pilot. For the analysis of the aircraft behavior shock tunnel are given. The five essential measuring techniques in a changing wind field, a mathematical model of the aircraft is developed or collected during the last three decades when used including the wind effects. It can be said, that gusts and operating the tunnel, are presented: differential interferometry for turbulence will have more influence on the pilot workload and flow vizualization and/or quantitative flow density measurements; reaction to this short scale wind disturbances. Large scale wind laser differential interferometry for precise measurements of optical variations can produce significant flight path safety problems. An paths in a low density gas medium; heat flux measurements with important aspect for the flight safety is the energy situation of an thin film resistance thermometers; laser Ooppler velocimetry; and aircraft affected by wind. Therefore this was chosen as a useful the measurement of aerodynamic forces and moments in criterion for the determination of the influences of the wind and milliseconds. ESA wind variation. Author

N91-10925# Deutsche Forschungsanstalt fuer Luft- und N91-11026# National Aerospace Lab., Tokyo (Japan). Raumfahrt, Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. FLIGHT SIMULATOR EVALUATION TEST OF DESIGN OF THE DERIVATIVE BALANCE FOR THE MULTI-FUNCTIONAL DISPLAY UNIT [TAKINO HYOJI SOCHI TRANSONIC WIND TUNNEL [KONSTRUKTIVE AUSLEGUNG NO HIKO SHIMYURE-SHON HYOKASHIKEN] DER TRANSKANAL-DERIVATIVAWAAGE (TRAD)] HIROYASU KAWAHARA, AKIRA WATANABE, KAORU WAKAIRO, EBERHARD SCHMIDT and JOACHIM WAGENER In its and KEIJI TANAKA Oct. 1988 34 p In JAPANESE Contributions in the Field of Aeroelastics on the Occasion of the (NAL-TM-596; ISSN-0452-2982; JTN-90-80122) Avail: NTIS 60th Anniversary of Professor Dr.-Ing. Habil. Hans Wilhelm HC/MF A03 Foersching p 105-125 Apr. 1990 In GERMAN; ENGLISH As a part of the design of the new cockpit, in order to make summary clear the efficiency and the technical feasibility of the cathode ray Avail: NTIS HC/MF A13 tube-type display system, the simulation test for both the headdown The design of a dynamic derivative balance for a transonic display system and the digital map display system was made to wind tunnel is presented. Several technical problems had to be evaluate results. The evaluation test was made using the overcome to obtain, despite the extremely high model loads (normal multi-purpose flight simulator of the National Aerospace Laboratory force of 2800 N at an angle of attack of 32 deg), oscillatory in Japan. As a result, some items which need to be improved for model motions with constant amplitudes, while limiting the rig the headdown display unit were suggested. They are as follows: diameter within the model to that of a conventional strain gauge (1) the improvement of the scale of the bank angle and the bank force balance. The final construction of the five component balance, pointer, (2) the improvement of the display of digits on the magnified the spring element bearings for pitch and roll oscillations, and the digital display, (3) the improvement of the magnified display of forcing mechanisms for the sinusoidal motions using a stepping velocity, (4) the change of the shape of both the glide slope and motor drive are described. These technical details may be useful the pointer localizer, (5) to keep the stability of a color tone on for the design of other dynamic test installations or special industrial brightness regulation function, and (6) to study the edge-smoothing machinery. ESA technique. For the digital map display system, the following items needed for improvement were suggested: (1) introduction of the N91-10928# Deutsche Forschungsanstalt fuer Luft- und scale-up and -down function, (2) moving down the symbol of an Raumfahrt, Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. airplane itself from the center of a display, (3) to make colors of UNSTEADY WIND TUNNEL WALL INTERFERENCES IN each displayed item recognizable, (4) to display the higher mountain SUBSONIC AND TRANSONIC PROFILE FLOWS and obstacles by using warning colors and to make-one pay (INSTATIONAERE WINDKANALWAND-INTERFERENZEN BEI attention to them by using flickering light, (5) to use a three SUB- UND TRANSSONISCHER PROFILUMSTROEMUNG] dimensional display technique, and (6) to improve the resolution RALPH VOSS In its Contributions in the Field of Aeroelastics on of it by increasing scanning lines. NASDA the Occasion of the 60th Anniversary of Professor Dr.-lng. Habil. Hans Wilhelm Foersching p 169-185 Apr. 1990 In GERMAN; N91-11027*# Physical Sciences, Inc., Andover, MA. ENGLISH summary PROPULSION SIMULATION FOR MAGNETICALLY Avail: NTIS HC/MF A13 SUSPENDED WIND TUNNEL MODELS Final Report, Jan.-Sep. Unsteady wind tunnel wall interference effects in subsonic and 1988 transonic flows about oscillating 2-D airfoils were theoretically PRAKASH B. JOSHI, HENRY P. BEERMAN, JAMES CHEN, investigated using a panel method and a finite difference time ROBERT H. KRECH, ANDREW L. LINTZ, and DAVID I. ROSEN marching method. The results show strong effects on magnitude Oct. 1990 73 p and phase of unsteady pressure and lift coefficients. Transonic (Contract NAS1-18616) interference effects are even stronger than the well known subsonic (NASA-CR-182093; NAS 1.26:182093; PSI-2055/TR-859) Avail: ones. Tunnel resonance appears in subsonic and transonic flows NTIS HC/MF A04 CSCL 14/2 for the same flow parameters. Based on the subsonic panel method The feasibility of simulating propulsion-induced aerodynamic transonic measurements can be approximately corrected for effects on scaled aircraft models in wind tunnels employing unsteady interference effects, if pressure distributions at the walls Magnetic Suspension and Balance Systems. The investigation are known. ESA concerned itself with techniques of generating exhaust jets of appropriate characteristics. The objectives were to: (1) define thrust N91-10975# Technische Univ., Brunswick (Germany, F.R.). Inst. and mass flow requirements of jets; (2) evaluate techniques for of Flight Guidance and Control. generating propulsive gas within volume limitations imposed by WIND MODELS FOR FLIGHT SIMULATION magnetically-suspended models; (3) conduct simple diagnostic K.-U. HAHN, T. HEINTSCH, B. KAUFMANN, G. SCHAENZER, and experiments for techniques involving new concepts; and (4) M. SWOLINSKY In AGARD, Aircraft Trajectories: Computation, recommend experiments for demonstration of propulsion simulation Prediction, Control, Volume 1. Part 1: Fundamentals. Part 2: Flight techniques. Various techniques of generating exhaust jets of in Critical Atmospheric Conditions. Part 3: Impact of New On-Board appropriate characteristics were evaluated on scaled aircraft Technologies on Aircraft Operation 32 p Mar. 1990 Sponsored models in wind tunnels with MSBS. Four concepts of by DFG remotely-operated propulsion simulators were examined. Three Copyright Avail: NTIS HC/MF A12; Non-NATO Nationals requests conceptual designs involving innovative adaptation of convenient available only from AGARD/Scientific Publications Executive technologies (compressed gas cylinders, liquid, and solid Wind shear, downdraft, and turbulence can endanger takeoff propellents) were developed. The fourth innovative concept,

53 10 ASTRONAUTICS

namely, the laser-assisted thruster, which can potentially simulate and strength, corrosion resistance, durability, and a construction both inlet and exhaust flows, was found to require very high power adequate for inspection, maintenance and repair. Current aircraft levels for small thrust levels. .Author construction requirements are significantly extended for hypersonic vehicles. Additional consideration is given to long-duration temperature resistance of the airframe structure, the integration of large-volume cryogenic fuel tanks, computational tools, structural 10 design, polymer matrix composites, and advanced manufacturing technologies. R.E.P. ASTRONAUTICS A91-10977* National Aeronautics and Space Administration. Includes astronautics (general); astrodynamics; ground support Hugh L. Dryden Flight Research Facility, Edwards, CA. systems and facilities (space); launch vehicles and space vehicles; THE NEED FOR A HYPERSONIC DEMONSTRATOR space transportation; spacecraft communications, command and T. G. AYERS (NASA, Flight Research Center, Edwards, CA) IN: tracking; spacecraft design, testing and performance; spacecraft European Symposium on the Future of High Speed Air Transport, •'instrumentation; and spacecraft propulsion and power. Strasbourg, France, Nov. 6-8,1989, Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. 290-296. Copyright A91-10972 The requirement for research aircraft and demonstrator vehicles SYSTEM OPTIMIZATION STRUCTURE AND PROPULSION OF has been seriously challenged by tight budgets and erroneous A HYPERSONIC SPACE TRANSPORTATION SYSTEM impressions that aeronautical technology has matured to a point (SAENGER) where the value added by flight research and/or demonstration is DIETRICH E. KOELLE (MBB GmbH, Ottobrunn, Federal Republic not sufficient to offset the costs. While this issue may be debatable of Germany) IN: European Symposium on the Future of High with respect to subsonic/transonic speeds, such is not the case Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, for high-speed (supersonic and hypersonic) operation. The Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. aerodynamic performance, weight/payload fractions, and ther- 257-262. refs modynamic problems are such that small margins of error Copyright can be tantamount to the vehicle being unable to reach its design The paper presents the design status of the Saenger launch point or so inefficient as to render it useless. This paper addresses vehicle concept, which comprises a hypersonic aircraft-type first some of the critical design considerations and operational stage with turboramjet propulsion. The vehicle is conceived for constraints which make it mandatory to carry out flight research Mach 4.4 cruise speed (28 km altitude) and Mach 6.6 stage and develop a demonstrator vehicle in order that the risks be separation velocity in 37 km altitude. Aerodynamical, thermal, reduced to an acceptable level to assure technology readiness structural and propulsion design features are discussed as they for viable hypersonic flight. Author have evolved after 3 years of study work. Author A91-10978 A91-10973 HYPERSONIC SPACE TRANSPORT SYSTEM - CRUISER OR THE CASE OF A HYPERSONIC FLIGHT DEMONSTRATOR ACCELERATOR? W. B. HERBST and P. SACHER (MBB GmbH, Munich, Federal J. M. ROUBERTIE and M. RIGAULT (AMDBA, S.A., Saint-Cloud, Republic of Germany) IN: European Symposium on the Future France) IN: European Symposium on the Future of High Speed of High Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, Air Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. Toulouse, France, Cepadues-Editions, 1990, p. 264-267. refs 298-300. Copyright Copyright Some considerations on airbreathing launchers are presented A new high speed research vehicle is planned to be developed and similarities, differences, and potential synergies with hypersonic and flight tested which would explore the flight regime up to M = commercial transport aircraft are discussed. A hypersonic transport 6 and which would be powered by an airbreathing turbo-ram aircraft is essentially a cruiser as acceleration and deceleration propulsion system. It would form the technological basis for the are a relatively small portion of the flight. It is shown that strong lower stage of a future two-stage spaceplane. The paper is taking commonality between a hypersonic passenger aircraft and an reference to historical and current experimental aircraft and outlines airbreathing launcher is not likely, but the analogies are enough the engineering challenge of designing a hypersonic research to justify a synergy in the feasibility and development phases vehicle. Author (Rigault, 1989) due to common technological requirements. The material development effort should have some common needs. A91-11737 Other areas in the fields of aerodynamics, cryogenic fuel storage SOVIET SPACE PLANES and management, and propulsion may also rely on similar DENNIS NEWKIRK Spaceflight (ISSN 0038-6340), vol. 32, Oct. developments. Common test facilities may also be used for all 1990, p. 350-355. refs these technologies. R.E.P. Copyright , The development history of the Soviet shuttle-type spacecraft A91-10974 which led to the development and November 1988 launch of the BASIC MATERIALS AND STRUCTURES ASPECTS FOR Buran orbiter is reviewed. It is pointed out that new evidence HYPERSONIC TRANSPORT VEHICLES (HTV) indicates that early Soviet plans to develop such a craft in the E: STEINHEIL and W. UHSE (Dornier GmbH, Friedrichshafen, 1960s were of greater magnitude than similar plans proposed in Federal Republic of Germany) IN: European Symposium on the the U.S. It is noted that both countries can trace their shuttle Future of High Speed Air Transport, Strasbourg, France, Nov. 6-8, development back to German studies of the Antipodal Bomber. • 1989, Proceedings. Toulouse, France, Cepadues-Editions, 1990, Soviet developments are seen as a response to similar p. 269-275. developments in the U.S., with the U.S. Dyna-Soar program Copyright apparently prompting the Soviet Project 50/50 which produced A Mach 5 transport design is used to illustrate structural designs for the 8 x 7.4 x 3.5-m 10,3000-kg folded-wing spacecraft concepts and criteria for materials selections and also key Lapot. The continued work on the Lapot from 1974-79 is recounted, technologies that must be followed in the areas of computational and its contribution to the BOR-4 program (1982-1984) is detailed. methods, materials and construction methods. Aside from the The known flight history of BOR-4, beginning with the Cosmos primary criteria of low weight, low costs, and conceivable risks, a 1374 launched on June 3, 1982 from Kapustin Yar by an SL-8 number of additional requirements must be met, including stiffness booster, is reviewed. L.K.S.

54 11 CHEMISTRY AND MATERIALS

N91-11035# National Aerospace Lab., Tokyo (Japan). Control from the established global hydrocarbon energy economy to a Systems Div. potential global hydrogen energy economy, in which aviation and FLIGHT SIMULATION PROGRAMS FOR SPACE PLANE [UCHU aerospace could have a trailblazer function, is. necessary, OKANKI HIKO SHIMYURE-SHON PUROGURAMU] achievable, and urgent. Author MASAAKI YANAGIHARA Aug. 1988 45 p In JAPANESE (NAL-TM-594; ISSN-0452-2982; JTN-90-80120) Avail: NTIS A91-11751 HC/MF A03 THERMAL BARRIER COATINGS - MICROSTRUCTURAL A flight simulation program that could simulate the flight of an INVESTIGATION AFTER ANNEALING spaceplane from the ground surface to the orbit around the earth L LELAIT, S. ALPERINE, C. DIOT, and M. MEVREL (ONERA, was developed. This program is the advanced version of the. Chatillon, France) (Materials Science and Engineering, Part A - general purpose program for the flight simulation which has been Structural Materials: Properties, Microstructure and Processing, vol. developed in the National Aerospace Laboratory of Japan. Two A121. 1989, p. 475-482) ONERA, TP no. 1990-62, 1990. 9 p. programs are available to analyze the rigid body motion with six refs degrees of freedom or the mass point motion with three degrees (ONERA, TP NO. 1990-62) Copyright of freedom. They are written in FORTRAN. The merits and A study is conducted of the microstructures of plasma-sprayed limitations of the program are as follows: (1) it is composed of (as-sprayed and annealed) yttria-partially stabilized zirconia two package programs, that is, fuselage models and onboard thermal-barrier coatings representative of the state-of-the-art in calculations (these packages are replaceable and thus the program thermal-barrier coatings for gas turbine hot-section components. is widely usable); (2) the heating rates of the fuselage, load factors The phase transformations observed upon annealing are typical and dynamic pressures are calculated along the flight path and of a slow return toward the phase-diagram equilibrium. TEM studies are used for the assessment of the path; (3) the earth is assumed of perpendicularly observed thin foil specimens reveal fine to be a sphere and the revolution is neglected (the angular velocity microstructures which coarsen upon annealing; the character and of the rotation is assumed to be constant); (4) a U.S. 62 standard morphology of these structures may be due. to the precipitation of atmosphere table is used; (5) it contains the models of the westerly a high yttria-content t-double-prime phase which is due to wind, the steady wind in the low altitude, the gusts and the wind strain-induced coarsening upon annealing. This phase may account shears. The contents of the program and the construction of the for the great toughness of these ceramic coatings, in its function mathematical model are described and the good results of- the as a 'microcomposite'. ' O.C. evaluation are presented in which the three degrees of freedom flight simulation program was tested using the data of the space A91-11770# shuttle of U.S.A. . ' NASDA RESEARCH AND DEVELOPMENT OF HIGH-PRESSURE-EXPONENT FUEL-RICH PROPELLANTS [RECHERCHE ET DEVELOPPEMENT DE PROPERGOLS AEOBIES A FORT EXPOSANT DE PRESSION] 11 BERTRAND FOUREST and CHRISTIAN MASSON (ONERA, Chatillon, France) (ICT, International Congress, 21st, Karlsruhe, CHEMISTRY AND MATERIALS Federal Republic of Germany, July 3-6, 1990) ONERA, TP no. 1990-91, 1990, 15 p. In French.. Includes chemistry and materials (general); composite materials;, (ONERA, TP NO. 1990-91) ' ... inorganic and physical chemistry; metallic materials; nonmetallic In order to adjust the fuel mass flow rate for the cruise conditions materials; and propellants and fuels. of rocket ramjets the pressure exponent of fuel-rich propellants must be high (or greater than 0.5). The burn-rate characteristics and the. material component qualities required to maintain these A91-10345# high pressures are presented. Also, a study of ammonium THREE-DIMENSIONAL COMBUSTOR PERFORMANCE perchlorate particle size is presented, and the effects of additives VALIDATION WITH HIGH-DENSITY FUELS on the burn-rate are discussed. Numerical results of a burn-rate N. K. RIZK and H. C. MONGIA (General Motors Corp., Indianapolis, temperature sensitivity model and a steady-state combustion model IN) Journal of Propulsion and Power (ISSN 0748-4658), vol. 6, are also, presented. . R.E.P. Sept.-Oct. 1990, p. 660-667. Previously cited in issue 09, p. 1326, Accession no. A89-25193. refs A91-11776# (Contract F33615-86-C-2604) INFLUENCE OF CHROMIUM AND MOLYBDENUM ON THE Copyright STRUCTURAL STABILITY Op A HIGH STRENGTH DAMAGE TOLERANT P/M NICKEL BASED ALLOY FOR TURBINE A91-10966 DISKS HYDROGEN IN HIGH-SPEED AIR TRANSPORTATION MICHEL MARTY, GILLES HUG, and ANDRE WALDER (ONERA, CARL-JOCHEN WINTER (DLR, Stuttgart, Federal Republic.of Direction des Materiaux, Chatillon, France) (Materials Research Germany) IN: European Symposium on the Future of High Speed Society, Spring Meeting, San Francisco, CA, Apr. 16-20, 1990) Air Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings. ONERA, TP no. 1990-100, 1990, 7 p. Toulouse, France, Cepadues-Editions, 1990, p. 172-180.. refs (ONERA, TP NO. 1990-100) Copyright Six P/M Ni-based alloys applicable to turbine disk fabrication This paper briefly reviews the history of hydrogen use in aviation have been produced with Cr and. Mo concentrations higher than and aerospace and goes on to discuss current international those of the N18 alloy, for the sake of solid-solution strengthening, developments, which are centered around plans for super- along lines recommended by the 'New-Phacomp' correlation sonic/hypersonic aircraft using hydrogen as a fuel. The de- method. In both N18's case and those of the modified alloys, the velopment work which must be accomplished before the first low volume fraction of phases rich in Cr, Mo, and Co which appear test flights can take place, possibly at the end of this century, after long-term 700 C isothermal treatment is found not to induce includes rather straightforward technological challenges relating brittleness. The creep rate is increased due to a decreasing volume to components, systems and infrastructures and to safety and fraction of the ultrafine gamma-prime, although the elongation-to- security considerations. A more complex challenge includes rupture remains unchanged. The effect of Cr is more important achieving environmental .compatibility for this technology, which is than that of Mo. O.C. well possible in the areas of producing and handling hydrogen fuel, but probably not in the area .of end use, if the benefits of A91-11806 this fuel are to be fully exploited. Another formidable.-precondition THE ROLE OF PRIMARY CARBIDES IN FATIGUE CRACK is achieving an international political consensus that a transition PROPAGATION IN AEROENGINE BEARING STEELS

55 11 CHEMISTRY AND MATERIALS

A. -IQBAL (University College, Muzaffarabad, Pakistan) and J. E. N91-10168# Rolls-Royce Ltd., Bristol (England). KING (Cambridge, University, England) International Journal of CASTING ALLOYS FOR THE JET AGE Fatigue (ISSN 0142-1123), vol. 12, July 1990, p. 234-244. Research M.H.GRIFFITHS Derby, England 22Jun. 1989 10 p Presented supported by British Gas, PLC. refs at POS Jnl (IBF) Meeting, Stratford-upon-Avon, England, 22 Jun. Copyright , . 1989 Fatigue crack'propagation, tensile'and fracture toughness data (PNR-90723; ETN-90-97948) Copyright Avail: NTIS HC/MF for four aircraft engine bearing steels are reported. The steels A02 involved are the through-hardened tool steels 18-4-1 (T1) and The historical development of casting alloys applied to jet aero M50, and two similar carburized steels, RBD and Volvic. Crack engines is summarized. Special attention is given to nickel based growth, data have been obtained at 20 C and 280 C to cover the superalloys. Relevant developments are discussed highlighting range of oil temperatures experienced in aeroengine bearing important milestones achieved in terms of the effects of alloying operations. At 20 C, threshold Delta-K(th) values ranged between elements and their constituent phases. The investment casting 3.5 and 4.5 MPa sq rt m with Paris exponents (m) of between 2.0 route is described. References to the various processing techniques and 3.5. The lowest m-values were seen in the carburizing steels, now employed are made. These include directional solidification, which also exhibited lower Paris regime crack growth rates than single crystals, heat treatment and ceramic core technology. M50 and 18-4-1. For all the steels, growth rates were higher at Current limitations and future developments designed to improve 280 C than 20 C, although there was a slight tendency for foundry practices are underlined. ESA Delta-K(th) values to increase, probably associated with oxide-induced closure at 280 C. The effects of primary carbides, N91-10188# Pennsylvania State Univ., University Park. strength and toughness on fatigue crack growth behavior are THERMAL STABILITY OF JET FUEL Final Report, Sep. 1988 - discussed, in relation to the importance of static-mode cracking. Dec. 1989 Author SEMIH ESER, CHUNSHAN SONG, RONALD M. COPENHAVER, JANICE PERISON, and HAROLD H. SCHOBERT 1990 125 p A91-11883 (Contract DE-AC22-88PC-88827) A PROCESS MODEL FOR AGE HARDENING OF ALUMINIUM (DE90-016801; DOE/PC-88827/T5) Avail: NTIS HC/MF A06 ALLOYS. I - THE MODEL The principal objectives of this study were to investigate the H. R. SHERCLIFF and M. F. ASHBY (Cambridge, University, thermal stability of a suite of alkylated phenols as typical trace England) Acta Metallurgica et Materialia (ISSN 0956-7151), vol. contaminants in jet fuels and to determine the thermal stability of 38, Oct. 1990, p. 1789-1812. Research supported by SERC. various fractions of a coal-derived and a petroleum-derived JP-8 refs jet fuel as well as the thermal stability of the unfractionated fuels. Copyright The thermal treatment experiments were carried out in nitrogen and air atmospheres (100 psig cold) using 15 ml microautoclave N91-10139# Rolls-Royce Ltd., Derby (England). reactors. The reactors were heated in a fluidized sand bath at MULTI INDUSTRY APPLICATION OF ADVANCED MATERIALS temperatures ranging from 150 C to 450 C. The samples of the JOHN F. COPLIN 31 May 1989 20 p Presented in Japan, 31 coal-derived and petroleum-derived jet fuels were separated into May 1989 five distillate fractions and these fractions were characterized by (PNR-90764; ETN-90-97963) Copyright Avail: NTIS HC/MF high-resolution gas chromatography-mass spectrometry (GC-MS). A03 The thermal treatment products from the alkylated phenols were Applications and market evolution of materials for aero engines analyzed by 1-H and 13-C Nuclear Magnetic Resonance are summarized. Early days market was provided by military spectroscopy and gas chromatograhpy/mass spectroscopy. engines. Civil airline market contributed to the market pull. Extra DOE market pull can be provided by automotive industry. Technology developments, and production of high temperature/high resistance materials require new market pulls. At a time when military spending N91-11107# Rolls-Royce Ltd., Derby (England). is going down in real money, and when a lower portion is going INFLUENCE OF HEAT TREATMENT ON MICROSTRUCTURE into aircraft and engines, it is found that lower cost machines AND PROPERTIES OF AN ADVANCED HIGH TEMPERATURE made possible by ceramics and metal matrix developments can TITANIUM ALLOY replace conventional concepts in the future. ESA M. A. DAEUBLER (Motoren- und Turbinen-Union Muenchen G.m.b.H., Germany, F.R. ), N. A. WALKER, and M. T. COPE 22 N91-10141 Illinois Univ., Chicago. Nov. 1989 6 p Presented at EUROMAT 1989, European THE INSTABILITY OF COMBUSTION IN PROPULSION Conference on Advanced Materials and Processes, Aachen, Fed. Republic of Germany, 22-24 Nov. 1989 ENGINES Ph.D. Thesis CHUN-PAO KUO 1989 219 p . (PNR-90689; ETN-90-97932) Copyright Avail: NTIS HC/MF A02 Avail: Univ. Microfilms Order No. DA9015753 The proposed theory provides a theoretical prediction of the The influence of the quench rate, aging treatment and aerothermochemical sources of acoustic excitation, growth of re-solution heat treatment on the tensile behavior at 20, 600, and 600 C creep behavior of IMI 834 disc material is described. IMI instability, propagation, and resonant pressure oscillation as well as the transition instability model. The thesis presents the 834 is a near alpha alloy with applications in aircraft engines as a description of four major aerothermochemical sources: (1) compressor disc and blade material. IMI 834 offers considerable monopole; (2) dipole; (3) quadrupole sources, which are benefits over previous coarse grained beta processed alloys IMI respectively due to the non-steady propellant vaporization, 685 and IMI 829 in terms of strength, low cycle fatigue and creep combustion, aerodynamic drag and turbulence; and (4) the resistance. The alloy is designed to be processed within the alpha mechanical dilation caused by the time dependent convective plus beta phase field, for optimizing the balance of mechanical motion of multi-phase flow. This is followed by the presentation of properties through microstructural modifications. ESA comprehensive analytical techniques to predict the strength of each aerothermochemical source by the theoretical procedure N91-11128# Idaho National Engineering Lab., Idaho Falls. devised in non-steady spray group combustion and acoustic THREE-DIMENSIONAL FLUID FLOW IN JFTOT (JET FUEL response of propellant injection/atomization, and properties of THERMAL OXIDATION TESTER) propellant. The numerical simulation of the detailed development C. H. OH, B. J. MERRILL, and R. P. WADKINS 1990 23 p of engine start-up instability is presented to demonstrate the Presented at the International Symposium on Gas-Liquid dynamic growth of instability sources and the corresponding Two-Phase Flows in Conjunction with the Winter Annual Meeting evolution of an acoustic instability during the start-up of a liquid-gas of the ASME, Dallas, TX, 25-30 Nov. 1990 propulsion engine. . Dissert. Abstr. (Contract DE-AC07-76ID-01570)

56 12 ENGINEERING

(DE90-010929; EGG-M-90041; CONF-901109-3) Avail: NTIS contours. It is concluded that holographic flow visualization is highly HC/MF A03 versatile and that it can be used in a variety of engineering This paper describes flow and temperature distributions in the applications. K.K. Jet Fuel Thermal Oxidation Tester (JFTOT), a standard qualification apparatus for examining thermal stability of jet fuels. A A91-11199 three-dimensional numerical analysis is presented in this paper LARGE-AMPLITUDE VIBRATIONS OF FREE-FREE TAPERED performed with the KIVA code. This work represents a preliminary BEAMS attempt to calibrate a Computational Fluid Dynamics/Chemistry B. NAGESWARA RAO and G. VENKATESWARA RAO (ISRO, (CFDC) model using existing data from a modified JFTOT. Due to Vikram Sarabhai Space Centre, Trivandrum, India) Journal of the limited amount of data, the deposition model used in this Sound and Vibration (ISSN 0022-460X), vol. 141, Sept. 22, 1990, study is a global type Arrhenius relationship. Upon the findings of p. 511-515. refs ' ". • • ••' future JFTOT experiments, the relevant parameters to mass Copyright transfer, heat transfer, and fluid dynamics can be combined to The nonlinearity due to large deflections of beams of tapered define the thermal stability of jet fuel with a higher degree of configuration is examined by considering the exact moment- accuracy. ' DOE curvature relations. It is noted that this type of nonlinearity differs from that of Kuo-Kuang Hu and Kirmser (1971), where the moment is expressed as a cubic polynomial of linear curvature. The combined effects of the axial and transverse inertia terms in 12 the equation of motion are also taken into account in the present formulation. The present nonlinear two-point boundary value problem is solved on the basis of a simple and reliable iterative ENGINEERING numerical procedure. Natural frequency parameters for three types of tapered beams are also presented. It is determined that the Includes engineering (general); communications; electronics and effect of the geometric nonlinearity is of a softening type similar electrical engineering; fluid mechanics and heat transfer; to that discussed by Kuo-Kuang Hu and Kirmser. L.K.S. instrumentation and photography; lasers and masers; mechanical engineering; quality assurance and reliability; -and structural A91-11201 mechanics. SYSTEMS RELIABILITY ASSESSMENT A. G. COLOMBO, ED. (CEC, Joint Research Centre, Ispra, Italy) and A. SAIZ DE BUSTAMANTE, ED. (Madrid, Universidad A91-10336# Politecnica, Spain) Dordrecht, Netherlands, Kluwer Academic PYROMETRY FOR TURBINE BLADE DEVELOPMENT Publishers, 1990, 318 p. For individual items see A91-11202 to E. SUAREZ and H. R. PRZIREMBEL (Pratt and Whitney Group, A91-11204. West Palm Beach, FL) Journal of Propulsion and Power (ISSN Copyright 0748-4658), vol. 6, Sept.-Oct. 1990, p. 584-589. Research Theoretical and practical aspects of systems-reliability analysis supported by the Pratt and Whitney Group. Previously cited in are examined in reviews and reports. Topics addressed include issue 18, p. 3068, Accession no. A88-44736. stochastic processes, Markov chains, and systems availability; the (Contract F33657-84-C-2137) Monte Carlo method, a practical approach to systems availability Copyright in the aircraft industry; reliability in nuclear-power-plant operations; fault-tree and event-tree analysis methods; systems modeling with A91-11027# Petri nets; and reliability modeling for failure-delay systems. AN ACCURATE ACOUSTIC EMISSION LOCATION METHOD Consideration is given to the Dylam approach to systems safety ADAPTED FOR COMPOSITE MATERIALS analysis, the analysis of protection-systems software, human A. BOUHERAOUA (AMDBA..S.A., Velizy-Villacoublay, France) IN: reliability models, fixation errors, theories of mechanical reasoning AECM-3: International Symposium on Acoustic Emission from under uncertainty, reliability parameter estimation by combination Composite Materials, 3rd, Paris, France, July 17-21, 1989, of data from various sources, and uncertainty modeling. T.K.. Symposium Papers. Columbus, OH, American Society for Nondestructive Testing, Inc., 1989, p. 375-379. A91-11202 A method which takes the anisotropy behavior of the material AVAILABILITY • A PRACTICAL APPROACH ON AEROSPACE into consideration and which is based on calibrating the structure INDUSTRY. by exciting stimuli all over it is discussed. The stimulus is created S. SANZ FERNANDEZ DE CORDOBA (Construcciones by using an acoustic shock wave generated by an electric arc Aeronauticas, S.A., Madrid, Spain) IN: Systems reliability over the structure. The method includes an amplitude correction assessment. Dordrecht, Netherlands, Kluwer Academic Publishers, of each event by an attenuation grid. The accuracy is less than 1 1990, p. 45-64. refs cm, using a 2 cm step length and 1 s resolution, but can be Copyright increased by reducing the step length and changing the DT • In the present paper, the concepts of reliability, maintainability triggering mode. The method can be applied on complex structures and availability when used in connection to each other are reviewed. like plane wings. B.P. Mathematical models for availability of single and multiple systems are shown, and the dependence from reliability, maintainability A91-11152 and (for multisystems) the number of units involved is considered. PRACTICAL DEVELOPMENTS IN HOLOGRAPHIC Differences when dealing with plants or vehicles are reviewed. INTERFEROMETRY Author R. J. PARKER (Rolls-Royce, PIC, Advanced Research Laboratory, Derby, England) (Meeting on Flow Visualisation Using Laser A91-11219 Techniques, University of Warwick, Coventry, England, May 10, COMPARISON OF MODAL PARAMETER ESTIMATION 1989) Aeronautical Journal (ISSN 0001-9240), vol. 94, March 1990, TECHNIQUES ON AIRCRAFT STRUCTURAL DATA p. 91-98. Research supported by the Ministry of Defence J. E. COOPER (Royal Aerospace Establishment, Farnborough, Procurement Executive, refs England) Mechanical.-Systems and Signal Processing (ISSN Copyright 0888-3270), vol. 4, March 1990, p. 157-172. refs The use of holography for studying compressible flows is studied Copyright with attention given to applications to both two- and Five global time domain parameter estimation methods, least three-dimensional flow fields. A comparison is made between a squares, double least squares, total least squares, correlation fit holographic isodensity map and computer-generated density and Smith least squares were compared using the same set of

57 12 ENGINEERING impulse responses taken from the ground vibration test of an in the Ariane 5 VEB structure, partitioning based on symmetry aircraft structure. The behavior of the modal parameter estimates transformations, an FEM approach to adaptive reliability'assurance, was investigated for changes in the solution order and number of and time-domain FEMs for the large rotational dynamics 'of data points analyzed. The techniques produced comparable results multibody systems.' T.K. for the dominant modes, although there were some differences in the estimates of the other modes. The correlation fit and Smith A91-11974 least squares approaches found equivalent estimates to the other DETECTION OF CONCEALED CORROSION DAMAGE IN methods while using much smaller computational model orders. AIRCRAFT STRUCTURES USING THE EDDY CURRENT • ' "'-.-' "••' . ''Author METHOD [OBNARUZHENIE SKRYTYKH KORROZIONNYKH POVREZHDENII AVIATSIONNYKH KONSTRUKTSII A91-11752# VIKHRETOKOVYM METODOM] . CALCULATIONS OF THE SERVICE LIFE OF COMPONENTS V.!.N. UCHANIN and V. N. TSIRG (AN USSR, Fiziko-Mekhanicheskii UNDER SEVERE THERMOMECHANICAL LOADS [CALCULS Institut, .Lvov, Ukrainian SSR) Fiziko-Khirnicheskaia Mekhanika DE DUREE DE VIE DES STRUCTURES SOUMISES A DES Materialov (ISSN 0430-6252), vol. 26, July-Aug. 1990, p. 103, 104. CHARGEMENTS THERMOMECANIQUES SEVERES] In Russian, refs J. L. CHABOCHE (Journees sur la Science et la Defense, Paris, Copyright France, May 15, 16, .1990) ONERA, TP no. 1990-63, 1990- 6 p. The objective of the study was to investigate the possibility of In French, refs . . ' •< ' using the eddy current method, to detect the initial stage of pitting (ONERA, TP NO. 1990-63) : corrosion between stringers and skin panels without disassembling A study of proposed calculation methods for obtaining -more riveted joints or removing the paint. It is shown that eddy current reliable estimates of the service lives of aircraft or rocket engines fault detectors are. capable of detecting corrosion pits deeper than subjected to high thermal stress is presented.-Particular attention 0.16 mm (about 5 percent of the thickness) without joint is given to a method employing inelastic analyses which is based disassembly or paint removal. A procedure for the eddy current on the definition of the cyclic stability of the material and on the detection of local corrosion damage on the inaccessible surfaces existence • of a pseudpperiodic response -of. the structure. of airframe structures has been developed. • V!L. Consideration is also given to simulation methods which take into account the true material response with, either .softening or hardening unstable cycling and coupling effects between A91-12036 ' ;' , , v deformation and damage. Detailed .examples .of the proposed RELIABILITY OF RESULTS OF THE CAPILLARY TESTING OF methodology are presented, including the V-SEP joint of the Vulcain GAS TURBINE ENGINE COMPONENTS DURING REPAIRS engine. ' . . . R.E.P. [DOSTOVERNOST REZUL'TATOV KAPILLIARNOGO • KONTROLIA DETALEI GAZOTURBINNYKH DVIGATELEI PRI REMONTE] , A91-11773# IU. A. G'LAZKOV Defektoskopiia,(ISSN 0130-3082), no. 7, 1990, L.D.V. APPLIED TO MEASUREMENTS BETWEEN TWO DISCS p. 62-70. In Russian, refs -, . IN HIGH SPEED ROTATION Copyright J. LABBE, P.-J. MICHARD, and M..IZARD (ONERA,'Chatillon, The problem of the reliability of capillary testing in gas turbine France) (International Symposium .on Applications of-Laser repair is examined with allowance for the particular technological Techniques to Fluid Mechanics, 5th, Lisbon, Portugal, July 9-12, route adopted during the repair. Examples of repair procedures 199.0) .ONERA, TP no. 1990-94, 1990, 5 p. that may affect the reliability of the results of capillary inspection (ONERA, TP NO. 1990-94) . ' are presented. These include chemical and mechanical stripping, LDV is used on the 'CRETE' test rig in order to investigate grinding, polishing, heat treatment, deposition of chemical, diffusion, the influence of the drag flow between two disks (about 600. mm and other coatings, surface hardening treaments, and corrosion diameter) in high rotation speed. Measurements are performed at protection treatments. . . • V.L. room temperature in vertical planes parallel to axis of rotation. Results are compared to those obtained from a five holes pressure probe and a computation using 2D Nayier Stokes code. Several A91-12421 configurations of injection flow are' used and the rotation speed A TECHNIQUE FOR MEASURING UNSTEADY varied up to 12 000 rpm. • ' ' • v •>. . • Author AERODYNAMICS IN TURBOMACHINERY [DEVELOPPEMENT D'UNE TECHNIQUE DE MESURE INSTATIONNAIRE DANS LES A91-11813 National Aeronautics and Space Administration. TURBOMACHINES] , . . * Langley Research Center, Hampton, VA. J. HUARD (ONERA, Chatillon, France) (DRET and Societe COMPUTATIONAL TECHNOLOGY FOR FLIGHT VEHICLES; Francaise des Mecaniciens, Journees, Paris,. France, Apr. 26, 27, PROCEEDINGS OF THE SYMPOSIUM, WASHINGTON, DC, 1990) Revue Francaise de Mecanique (ISSN 0373-6601), no. 3, NOV. 5-7, 1990 !.•„••..--.._ 1990, p. 173-184. In French. AHMED K. NOOR, ED. (NASA, Langley Research Center, Hampton; Copyright • . , Virginia, University, Charlottesville) and SAMUEL L VENNERi; ED. A technique is presented that measures unsteady pressure (NASA, -Materials and Structures Div., Washington, DC) downstream from the transonic rotor utilizing a total pressure probe Symposium sponsored by George Washington University, University with a high response pressure transducer. The development of of Virginia, and NASA. Computers and Structures (ISSN new computation codes, permits the unsteady characteristics-of 0045-7949), vol. 37, no. 2, 1990, 130 p. For individual items see the flow to be obtained. Test results are described that show, the A91-11814 to A91-11824. unsteady.measurements obtained downstream of a transonic rotor Copyright . , • • - ' '- with inlet distortion. Algorithms used in the analyses are discussed Recent advances in computational fluid mechanics are in detail. It is also shown that static pressure can be determined discussed in reviews and reports. Sections are devoted to (1) the with this system by taking into account the position angle of the modeling of local phenomena and edge effects in solids, (2) transducer. It is concluded that the test analyses confirm the validity stochastic modeling and simulation of fracture toughness, and (3) of this aerodynamic measuring technique. R.E.P. partioning strategy and new finite-elements. Particularatten- tion is given to global and local finite-element/spectral-bound- A91-12688* National- Aeronautics and Space 'Administration. ary-element techniques for failure analysis; simulations of Langley .Research Center, Hampton, VA. microfracture in metal-matrix composites,, fatigue analysis VISCOUS DRAG REDUCTION IN BOUNDARY LAYERS of cracked anisotropic plates under stochastic loading, math- DENNIS M. BUSHNELL, ED. and JERRY N. HEFNER, ED. (NASA, ematical modeling for the analysis of nonlinear aircraft dynam- Langley Research Center, Hampton, VA) ' Washington, DC, ics, physical and mathematical modeling of wave propagation American Institute of Aeronautics and Astronautics, Inc. (Progress

58 12 ENGINEERING in Astronautics and Aeronautics. Volume 123), 1990. 531 p. For acceleration schemes, (3) grid resolution, which may not capture individual items see A91-12689 to A91-12699. the scale of physical phenomena, and (4) physical models Copyright representing little-understood phenomena. The refinements The present volume discusses trie development status of required in each such respect are discussed in conjunction with stability theory for laminar flow control design, applied aspects of anticipated computer software and hardware developments. laminar-flow technology, transition delays using compliant walls, O.C. the application of CFD to skin friction drag-reduction, active-wave control of boundary-layer transitions, and such passive A91-12824 turbulent-drag reduction methods as outer-layer manipulators and DETECTION OF AIRPLANES IN AERIAL IMAGERY complex-curvature concepts. Also treated are such active turbulent ROBERT H. MEYER and KEVIN K. TONG (Hughes Aircraft Co., drag-reduction technique applications as those pertinent to MHD Electro-Optical and Data Systems Group, El Segundo, CA) IN: flow drag reduction, as well as drag reduction in liquid boundary Applications of digital image processing XII; Proceedings of the layers by gas injection, drag reduction by means of polymers and Meeting, San Diego, CA, Aug. 8-11, 1989. Bellingham, WA, Society surfactants, drag reduction by particle addition, viscous drag of Photo-Optical Instrumentation Engineers, 1989, p. 456-467. reduction via surface mass injection, and interactive wall-turbulence refs control. O.C. Copyright A proof-of-concept system for detecting aircraft in aerial imagery A91-12694*# National Aeronautics and Space Administration. using their general shape is described. The method, which is based Langley Research Center, Hampton, VA. on a general two-dimensional object model suitable for aerial views, RIBLETS partly overcomes the problems of occlusion and poor object MICHAEL J. WALSH (NASA, Langley Research Center, Hampton, contrast. The method seems relatively insensitive to view angle VA) IN: Viscous drag reduction in boundary layers. Washington, and object orientation. . C.D. DC, American Institute of Aeronautics and Astronautics, Inc., 1990, p. 203-261. refs A91-12887# Copyright SHOCK CAPTURING USING A PRESSURE-CORRECTION In addition to characterizing the various concepts reported in METHOD the literature on longitudinally-ribbed surface for aerodynamic JAMES J. MCGUIRK and GARY J. PAGE (Imperial College of surface drag reduction, the present development status evaluation Science, Technology, and Medicine, London, England) AIAA of this technology correlates all available experimental data. An Journal (ISSN 0001-1452), vol. 28, Oct. 1990, p. 1751-1757. analysis of these data is then conducted to ascertain the Research supported by the Ministry of Defence Procurement parameters most directly involved in drag reduction, and to evaluate Executive of England. Previously cited in issue 09, p. 1350, the effects which have thus far been exerted on turbulent boundary Accession no. A89-25450. refs layer structures. Such advanced riblet techniques as compound Copyright and three-dimensional riblets, riblets in combination with large-eddy breakup devices, and riblets with suction/blowing, are also A91-12888# discussed. O.C. EXPERIMENTAL STUDY OF INSTABILITY MODES IN A THREE-DIMENSIONAL BOUNDARY LAYER A91-12754# H. BIPPES and P. NITSCHKE-KOWSKY (DLR, Institut fuer FULL-POTENTIAL, EULER, AND NAVIER-STOKES SCHEMES Experimentelle Stroemungsmechanik, Goettingen, Federal Republic ANTONY JAMESON (Princeton University, NJ) IN: Applied of Germany) AIAA Journal (ISSN 0001-1452), vol. 28, Oct. computational aerodynamics. Washington, DC, American Institute 1990, p. 1758-1763. Previously cited in issue 18, p. 2854, Accession of Aeronautics and Astronautics, Inc., 1990, p. 39-88. refs no. A87-42396. refs Copyright Copyright The present development status evaluation of CFD schemes solving the full-potential, Euler, and Navier-Stokes equations for purposes of aerodynamic characteristics prediction gives attention A91-12900# to upwind differencing and convergence acceleration in algorithms VERTEX-BASED FINITE-VOLUME SOLUTION OF THE for potential flow, the treatment of complex geometry, the TWO-DIMENSIONAL NAVIER-STOKES EQUATIONS time-dependent formulation and space discretization of the Euler SUNIL KUMAR CHAKRABARTTY (National Aeronautical equations, total variation diminishing and time-stepping schemes, Laboratory, Bangalore, India) AIAA Journal (ISSN 0001-1452), and boundary layer corrections in viscous flow calculations. vol. 28, Oct. 1990, p. 1829-1831. refs Solutions of the Reynolds-averaged Navier-Stokes equations are Copyright noted to be entirely feasible for both two- and three-dimensional A nodal point finite-volume space discretization scheme is flows; in addition, basic numerical algorithms for the treatment of presently used to solve the two-dimensional Reynolds-averaged viscous and compressible flows with shock waves are now Navier-Stokes equations with a thin-layer type of approximation available. O.C. and a simple two-layer algebraic eddy viscosity model. The highly efficient Runge-Kutta scheme is also used in conjunction with A91-12775# convergence-acceleration techniques. The results obtained for FUTURE DIRECTIONS FOR APPLIED COMPUTATIONAL turbulent flow past a NACA 0012 airfoil are compared with available FLUID DYNAMICS numerical and experimental results. . O.C. RICHARD G. BRADLEY (General Dynamics Corp., Fort Worth, TX) IN: Applied computational aerodynamics. Washington, DC, N91-10232# National Aeronautical Lab., Bangalore (India). American Institute of Aeronautics and Astronautics, Inc., 1990, p. Computational and Theoretical Fluid Dynamics Div. 889-901. Research supported by the General Dynamics Corp. WALL INTERFERENCE STUDIES Closing Report, Apr. 1983 - refs Jun. 1989 Copyright R. GOPINATH Jun. 1990 25 p In order for CFD to fulfill its emerging destiny as the supreme (PD-CF-9012) Avail: NTIS HC/MF A03 aerodynamic design method, attention must be given to several A closing report on the activity, Wall Interference Studies, is major practical design-requirement considerations. It is noted that presented. Codes were developed to assess wall interference both the accuracy of a CFD solution is subject to limitation by (1) the for 2-D and 3-D cases, where the test section is ventilated, and appropriateness of its governing equations' representation of validated. TSFOIL code was adapted for operation on the Univac dominant flow features, (2) the numerical algorithm, which can be computer. Instrumentation was developed for measuring the a source of numerical error in smoothing and convergence pressures on a control surface in the 1.2 m facility and once this

59 12 ENGINEERING is installed in the above facility, correcting the data from it for N91-10303*# Technion - Israel Inst. of Tech., Haifa. Faculty of wall interference effects should be a routine affair. Author Aerospace Engineering. REPEATED BUCKLING OF COMPOSITE SHEAR PANELS N91-10268*# National Aeronautics and Space Administration. JOSEF SINGER and TANCHUM WELLER In NASA, Langley Ames Research Center, Moffett Field, CA. Research Center, Research in Structures, Structural Dynamics and A LASER-SHEET FLOW VISUALIZATION TECHNIQUE FOR Materials, 1990 p 37-42 Mar. 1990 THE LARGE WIND TUNNELS OF THE NATIONAL Avail: NTIS HC/MF A13 CSCL 20/11 FULL-SCALE AERODYNAMICS COMPLEX Failures in service of aerospace structures and research at M. S. REINATH and J. C. ROSS Sep. 1990 15 p the Technion Aircraft Structures Laboratory have revealed that (NASA-TM-102793; A-90082; MAS 1.15:102793) Avail: NTIS repeatedly buckled stiffened shear panels might be susceptible to HC/MF A03 CSCL 14/2 premature fatigue failures. Extensive experimental and analytical A flow visualization technique for the large wind tunnels of the studies have been performed at Technion on repeated buckling, National Full Scale Aerodynamics Complex (NFAC) is described. far in excess of initial buckling, for both metal and composite The technique uses a laser sheet generated by the NFAC Long shear panels with focus on the influence of the surrounding Range Laser Velocimeter (LRLV) to illuminate a smoke-like tracer structure. The core of the experimental investigation consisted of in the flow. The LRLV optical system is modified slightly, and a repeated buckling and postbuckling tests on Wagner beams in a scanned mirror is added to generate the sheet. These modifications three-point loading system under realistic test conditions. The are described, in addition to the results of an initial performance effects of varying sizes of stiffeners, of the magnitude of initial test conducted in the 80- by 120-Foot Wind Tunnel. During this buckling loads, of the panel aspect ratio and of the cyclic shearing test, flow visualization was performed in the wake region behind force, V sub eye, were studied. The cyclic to critical shear buckling a truck as part of a vehicle drag reduction study. The problems ratios, (V sub cyc/V sub cr) were on the high side, as needed for encountered during the test are discussed, in addition to the efficient panel design, yet all within possible flight envelopes. The recommended improvements needed to enhance the performance experiments were supplemented by analytical and numerical of the technique for future applications. Author analyses. For the metal shear panels the test and numerical results were synthesized into prediction formulas, which relate the life of the metal shear panels to two cyclic load parameters. The N91-10297# Rolls-Royce Ltd., Derby (England). composite shear panels studied were hybrid beams with INTRODUCTION: NEEDS AND APPROACHES TO RELIABILITY graphite/epoxy webs bonded to aluminum alloy frames. The test AND QUALITY ASSURANCE IN DESIGN AND MANUFACTURE results demonstrated that composite panels were less fatigue A. C. PICKARD 6 Oct. 1989- 8 p Presented at AGARD sensitive than comparable metal ones, and that repeated buckling, Damage Tolerance Concept Review Conference, Brussels, even when causing extensive damage, did not reduce the residual Belgium, 1-6 Oct. 1989 strength by more than 20 percent. All the composite, panels (PNR-90683; ETN-90-97930) Copyright Avail: NTIS HC/MF sustained the specified fatigue life of 250,000 cycles. The effect A02 of local unstiffened holes on the durability of repeatedly buckled In the damage tolerance approach, for improving the integrity shear panels was studied for one series of the metal panels. of aero engines, reliability, and quality assurance issues are Tests on 2024 T3 aluminum panels with relatively small unstiffened discussed. The implications of the following aspects on the damage holes in the center of the panels demonstrated premature fatigue tolerance concept are investigated: component material failure, compared to panels without holes. Preliminary tests on specifications and standards, controls on manufacturing processes, two graphite epoxy shear panels with small holes in the center design systems and quality assurance. The subjects reviewed in showed no similar fatigue life degradation and no shift in failure the workshop on reliability and quality assurance are given. ESA mode. Further tests on the effect of holes are in progress. Author N91-10298# Rolls-Royce Ltd., Derby (England). TOTAL QUALITY MANAGEMENT AT ROLLS-ROYCE PLC N91-10316*# National Aeronautics and Space Administration. R. H. WEDGE 15 Sep. 1990 10 p Submitted for publication Langley Research Center, Hampton, VA. (PNR-90759; ETN-90-97961) Copyright Avail: NTIS HC/MF DIRECT USE OF LINEAR TIME-DOMAIN AERODYNAMICS IN A02 AEROSERVOELASTIC ANALYSIS: AERODYNAMIC MODEL The Rolls-Royce concept concerning quality and quality J. A. WOODS and MICHAEL G. GILBERT In its Research in management is reviewed. The work is focused on the business Structures, Structural Dynamics and Materials, 1990 p 207-220 associated with aircraft gas turbine manufacture. The reasons for Mar. 1990 the adoption of quality assurance methods and the company's Avail: NTIS HC/MF A13 CSCL 20/11 targets are justified. The distribution of responsibilities and tasks The work presented here is the first part of a continuing effort in the quality assurance chain. is explained. Resulting from the to expand existing capabilities in aeroelasticity by developing the management plans, more effort is accorded to elimination and methodology which is necessary to utilize unsteady time-domain prevention, so that less time is spent on detection and correction. aerodynamics directly in aeroservoelastic design and analysis. The ESA ultimate objective is to define a fully integrated state-space model of an aeroelastic vehicle's aerodynamics, structure and controls N91-10301*# National Aeronautics and Space Administration. which may be used to efficiently determine the vehicle's Langley Research Center, Hampton, VA. aeroservoelastic stability. Here, the current status of developing a RESEARCH IN STRUCTURES, STRUCTURAL DYNAMICS AND state-space model for linear or near-linear time-domain indicial MATERIALS, 1990 aerodynamic forces is presented. > Author JEAN-FRANCOIS M. BARTHELEMY, comp. and AHMED K. NOOR, comp. (George Washington Univ., Hampton, VA.) Washington N91-10317*# National Aeronautics and Space Administration. Mar. 1990 283 p The 31st conference was held in Long Langley Research Center, Hampton, VA. Beach, CA, 2-4 Apr. 1990; sponsored by AIAA, ASME, ASCE, COMPUTATION OF MAXIMUM GUST LOADS IN NONLINEAR AHS, and ASC AIRCRAFT USING A NEW METHOD BASED ON THE (NASA-CP-3064; L-16735; NAS 1.55:3064) Avail: NTIS HC/MF MATCHED FILTER APPROACH AND NUMERICAL A13 CSCL 20/11 OPTIMIZATION The Structural Dynamics and Materials (SDM) Conference was ANTHONY S. POTOTZKY (Lockheed Engineering and Sciences held on April 2 to 4, 1990 in Long Beach, California. This publication Co., Hampton, VA.), JENNIFER HEEG, and BOYD PERRY, III In is a compilation of presentations of the work-in-progress sessions its Research in Structures, Structural Dynamics and Materials, 1990 and does not contain papers from the regular sessions since those p 221-229 Mar. 1990 papers are published by AIAA in the conference proceedings. Avail: NTIS HC/MF A13 CSCL 20/11

60 12 ENGINEERING

Time-correlated gust loads are time histories of two or more are projected to failure using the crack growth characteristics for load quantities due to the same disturbance time history. Time that location to find the life when it will be at critical length. correlation provides knowledge of the value (magnitude and sign) Greater-than-critical length cracks are projected back to determine of one load when another is maximum. At least two analysis the life at failure, that is, when it was at critical length. The same methods have been identified that are capable of computing process is used as in the case of a non-critical crack except that maximized time-correlated gust loads for linear aircraft. Both the projection goes the other direction. These points, along with methods solve for the unit-energy gust profile (gust velocity as a the critical length cracks are used to determine the failure function of time) that produces the maximum load at a given distribution. To be able to use data from different aircraft to build location on a linear airplane. Time-correlated gust loads are a common failure distribution, a consistent life variable must be obtained by re-applying this gust profile to the airplane and used. Aircraft life varies with the severity of the usage; therefore computing multiple simultaneous load responses. Such time the number of flight hours for a particular aircraft must be modified histories are physically realizable and may be applied to aircraft by its usage factor to obtain a normalized life which can be structures. Within the past several years there has been much compared with that from other aircraft. Author interest in obtaining a practical analysis method which is capable of solving the analogous problem for nonlinear aircraft. Such an N91-10333*# California Univ., San Diego, La Jolla. Dept. of analysis method has been the focus of an international committee Applied Mechanics and Engineering Sciences. of gust loads specialists formed by the U.S. Federal Aviation COMPARISON OF NASTRAN ANALYSIS WITH GROUND Administration and was the topic of a panel discussion at the VIBRATION RESULTS OF UH-60A NASA/AEFA TEST Gust and Buffet Loads session at the 1989 SDM Conference in CONFIGURATION Final Report Mobile, Alabama. The kinds of nonlinearities common on modern FLORENTINO IDOSOR and FRIEDER SEIBLE Sep. 1990 transport aircraft are indicated. The Statical Discrete Gust method 101 p Original contains color illustrations is capable of being, but so far has not been, applied to nonlinear (Contract NCC2-598) aircraft. To make the method practical for nonlinear applications, (NASA-CR-184565; NAS 1.26:184565; SSRP-90/03) Avail: NTIS a search procedure is essential. Another method is based on HC/MF A06; 4 functional color pages CSCL 20/11 Matched Filter Theory and, in its current form, is applicable to Preceding program flight tests, a ground vibration test and modal linear systems only. The purpose here is to present the status of test analysis of a UH-60A Black Hawk helicopter was conducted an attempt to extend the matched filter approach to nonlinear by Sikorsky Aircraft to complement the UH-60A test plan and systems. The extension uses Matched Filter Theory as a starting NASA/ARMY Modern Technology Rotor Airloads Program. The point and then employs a constrained optimization algorithm to 'NASA/AEFA' shake test configuration was tested for modal attack the nonlinear problem. Author frequencies and shapes and compared with its NASTRAN finite element model counterpart to give correlative results. Based upon N91-10320*# National Aeronautics and Space Administration. previous findings, significant differences in modal data existed and Langley Research Center, Hampton, VA. were attributed to assumptions regarding the influence of secondary STATIC AND DYNAMIC AEROELASTIC CHARACTERIZATION structure contributions in the preliminary NASTRAN modeling. An OF AN AERODYNAMICALLY HEATED GENERIC HYPERSONIC analysis of an updated finite element model including several AIRCRAFT CONFIGURATION secondary structural additions has confirmed that the inclusion of JENNIFER HEEG, MICHAEL G. GILBERT, and ANTHONY S. specific secondary components produces a significant effect on POTOTZKY In its Research in Structures, Structural Dynamics modal frequency and free-response shapes and improves and Materials, 1990 p 249-261 Mar. 1990 correlations at lower frequencies with shake test data. Author Avail: NTIS HC/MF A13 CSCL 20/11 This work-in-progress presentation describes an ongoing research activity at the NASA Langley Research Center to develop N91-10335*# Florida Atlantic Univ., Boca Raton. Dept. of Ocean analytical methods for the prediction of aerothermoelastic stability Engineering. of hypersonic aircraft including active control systems. The EXPERIMENTAL MEASUREMENT OF STRUCTURAL POWER objectives of this research include application of aerothermal loads FLOW ON AN AIRCRAFT FUSELAGE Progress Report to the structural finite element model, determination of the thermal J. M. CUSCHIERI Jun. 1989 29 p effects on flutter, and assessment of active controls technology (Contract NAG1-685) applied to overcome any potential adverse aeroelastic stability or (NASA-CR-187352; NAS 1.26:187352) Avail: NTIS HC/MF A03 response problems due to aerodynamic heating- namely flutter CSCL 20/11 suppression and ride quality improvement. For this study, a generic An experimental technique is used to measure the structural hypersonic aircraft configuration was selected which incorporates power flow through an aircraft fuselage with the excitation near wing flaps, ailerons and all-moveable fins to be used for active the wing attachment location. Because of the large number of control purposes. The active control systems would use onboard measurements required to analyze the whole of an aircraft fuselage, sensors in a feedback loop through the aircraft flight control it is necessary that a balance be achieved between the number computers to move the surfaces for improved structural dynamic of measurement transducers, the mounting of these transducers, response as the aircraft encounters atmospheric turbulence. and the accuracy of the measurements. Using four transducers Author mounted on a bakelite platform, the structural intensity vectors at locations distributed throughout the fuselage are measured. To minimize the errors associated with using a four transducers N91-10321*# McDonnell Aircraft Co., Saint Louis, MO. Structural technique the measurement positions are selected away from Research Div. STRUCTURAL RISK ASSESSMENT AND AIRCRAFT FLEET bulkheads and stiffeners. Because four separate transducers are used, with each transducer having its own drive and conditioning MAINTENANCE HERB SMITH, JR., C. R. SAFF, and TOM F. CHRISTIAN (Air amplifiers, phase errors are introduced in the measurements that can be much greater than the phase differences associated with Force Logistics Command, Robins AFB, GA.) In NASA, Langley the measurements. To minimize these phase errors two sets of Research Center, Research in Structures, Structural Dynamics and measurements are taken for each position with the orientation of Materials, 1990 p 263-274 Mar. 1990 the transducers rotated by 180 deg and an average taken between Avail: NTIS HC/MF A13 CSCL 20/11 the two sets of measurements. Results are presented and In the present analysis, deterministic flaw growth analysis is discussed. Author used to project the failure distributions from inspection data. Inspection data is reported for each critical point in the aircraft. The data will indicate either a crack of a specific size or no N91-11140 Southampton Univ. (England). crack. The crack length may be either less than, equal to, or VOICE COMMUNICATIONS IN THE COCKPIT NOISE greater than critical size for that location. Non-critical length cracks ENVIRONMENT: THE ROLE OF ACTIVE NOISE REDUCTION

61 12 ENGINEERING

Ph.D. Thesis two dimensional Navier-Stokes equations in stream function and PETER DAVID WHEELER 1986 259 p vorticity function formulation. High precision finite difference Avail: Univ. Microfilms Order No. BRDX88858 schemes and Alternating Directions Implicit (ADI) techniques are The topic of voice Communications in the cockpit noise combined. The algorithm was implemented on a multiprocessor to environment of modern fast-jet aircraft and helicopters is cope with the parallelism required by ADI methods. The addressed, and in particular, research undertaken in support of parallelization of the algorithm and performance levels of the the development of a system for reducing the noise level at the parallel code are set out. Pulsed-start numerical simulations on a operators' ear is described by acoustic cancellation within the ear NACA 0012 airfoil were performed for various airfoil incidence defender, known as active noise reduction (ANR). The internal angles and for Reynolds number up to 10 to the 5th power. The noise spectra of today's high performance fast-jet aircraft and phenomena obtained, the influence of the calculation parameters military helicopters is described, and the complex interaction of are discussed and comparison between numerical and acoustic noise transmission, speech, and microphone noise pick-up, experimentally visualized results validates the method. ESA which produces the total acoustic environment at the aircrews' ears, is discussed. Means of mathematically modelling the audio N91-11243# Laboratorio Nacional de Engenharia e Tecnologia channel, quantifying the components identified above, and Industrial, Lisbon (Portugal). identifying areas of shortfall in performance are derived, leading SHORT CRACK BEHAVIOUR IN AL-LI ALLOY 2090 to a procedure for the development of attenuation requirements, M. HELENA CARVALHO and M. DEFREITAS (Lisbon Univ., described as the communications audit. A model of the Portugal ) In AGARD, Short-Crack Growth Behaviour in Various electroacoustic characteristics of the ANR ear defender assembly Aircraft Materials 17 p Aug. 1990 is presented and the sound field distribution within the ear Copyright Avail: NTIS HC/MF A09; Non-NATO Nationals requests defender/ear cavity, and its effect upon cancellation performance, available only from AGARD/Scientific Publications Executive is discussed. The extensive laboratory and flight -testing of the Within the AGARD Cooperative Test Program on the behavior ANR system that was undertaken is reviewed, paying particular of short cracks, a common airframe aluminium alloy (2024-T3) attention to the measurement and analysis techniques employed was investigated and the significance of the short crack effect in such testing. Finally, the performance characteristics of ANR analyzed from tests conducted on a single edge notched fatigue are discussed and compared with the requirements previously specimens of sheet material. The follow up Supplemental Test established. Design limitations placed upon the systerrf by the Program dealt with other alloys such a Ti6AI4V, steel 4340, Al constraints of its area of application are described,, and the scope 7075 and AI-Li 2090, all of them of interest AI-Li alloy at for future improvements is considered. Dissert. Abstr. LNETI/CEMUL are described. Author

N91-11174 Colorado Univ., Boulder. N91-11246# Aeronautical Research Inst. of Sweden, Bromma. APPLICATION OF COMPUTATIONAL FLUID DYNAMICS TO Dept. of Structures. THREE-DIMENSIONAL BODIES IN HYPERSONIC FLOW Ph.D. SHORT CRACK GROWTH UNDER REALISTIC FLIGHT Thesis LOADING: MODEL PREDICTIONS AND EXPERIMENTAL JAMES STEVENSON RYAN 1989 '85 p RESULTS FOR AL 2024 AND AL-LI 2090 Avail: Univ. Microfilms Order No. DA9024865 A. F. BLOM In AGARD, Short-Crack Growth Behaviour in Various Hypersonic aircraft are now being designed. For that work to Aircraft Materials 15 p Aug. 1990 Sponsored by Defense be completed, improved computational tools are required. The Materials Administration flow simulation capabilities which are needed are being sought. In Copyright Avail: NTIS HC/MF A09; Non-NATO Nationals requests order to accomplish this, features of several existing codes were available only from AGARD/Scientific Publications Executive combined and enhanced. The Compressible Navier-Stokes (CNS) The Swedish contribution to the AGARD effort on short fatigue computer code solves the thin-layer Navier-Stokes equations .in crack growth includes various experimental investigations on the three dimensions for arbitrary vehicle shapes. The solver can aluminum alloys Al 2024-T3 and AI-Li 2090-T8E41. These two capture strong or weak shocks, and can model separated flow. materials were subjected both to constant amplitude loading, at Boundary-layer turbulence is accounted for empirically by use of stress ratios R = -2, -1, 0, and 0.5 and also to spectrum loading the Baldwin-Lomax turbulence model. The code uses ideal gas with the standardized load sequences FALSTAFF and TWIST, assumptions or an equilibrium real gas model. Geometries are representative for the lower wing surface of fighter and civil aircraft, gridded in a zonal fashion, allowing for flexible convergence respectively. The TWIST sequence was also used to generate strategies and use of the best available equation set. for each long crack growth data for the two alloys. The experimental results zone. The grid on which the computations are performed is critical are summarized and numerical predictions by means of a modified to the efficient generation of accurate solutions. Some of the criteria Dugdale-Barenblatt model originally proposed by Newman are also for grid quality are discussed, and,a simple method of adapting included. Numerical results correspond well to the observed grids to supersonic flow fields is presented. The code was tested experimental behavior for most of the performed tests. Author against analytical, experimental, and numerical results, and shows excellent agreement for critical .quantities such as heat transfer N91-11247*# National Aeronautics and Space Administration. and skin friction. The zonal approach of the code and its modular Langley Research Center, Hampton, VA. structure allow for future inclusion of internal flow options, more THE GROWTH OF SHORT CRACKS IN 4340 STEEL AND complex geometrical models, nonequilibrium air chemistry, ALUMINUM-LITHIUM 2090 combustion chemistry, and other improvements. • Dissert. Abstr. M. H. SWAIN, R. A. EVERETT (Army Aviation Systems Command, Hampton, VA.), JAMES C. NEWMAN, JR., and E. P. PHILLIPS N91-11197# European Space Agency, Paris (France). In AGARD, Short-Crack Growth Behaviour in Various Aircraft PARALLELIZATION ON A MULTI-PROCESSOR SYSTEM OF A Materials 30 p Aug. 1990 Sponsored by NASA SOLVING METHOD FOR THE UNSTEADY NAVIER-STOKES Copyright Avail: NTIS HC/MF A09; Non-NATO Nationals requests EQUATIONS AT HIGH REYNOLDS NUMBERS available only from AGARD/Scientific Publications Executive LAURE MANE Aug. 1990 144 p Transl. into ENGLISH of CSCL 20/11 Parallelisation sur un Systeme Multiprocesseur d'une Methode de The objectives were to investigate crack initiation Resolution des Equations de Navier-Stokes Instationnaires a characteristics and short crack growth behavior for AI-Li 2090 Grands Nombres de Reynolds (Paris, France, ONERA), 1987 111 and for 4340 steel and to evaluate the ability of a closure-based p Original language document was announced as N88-26632 crack-growth model to predict fatigue crack growth rates and total (ESA-TT-1116; ONERA-NT-1987-8; ETN-90-97999) Avail: NTIS fatigue lives for the steel. Single-edge-notched tension specimens HC/MF A07 . • of each alloy were used to obtain the short crack growth rate A method for the simulation of viscous incompressible flows information via an acetate replica technique. In addition to constant around an airfoil is presented which provides resolution of the amplitude loading, tests on the steel were conducted using the

62 13 GEOSCIENCES

Felix/28 variable amplitude spectrum (a shortened form of a 13 standard loading sequence for fixed or semi-rigid helicopter rotors). The short crack growth rates were compared to those for long GEOSCIENCES cracks grown under similar loading conditions. Metallurgical features associated with crack initiation are discussed. For AI-Li 2090 under R = -1 loading, the short cracks grew well below the Includes geosciences (general); earth resources; energy production long crack threshold and grew at acute angles to the loading and conversion; environment pollution; geophysics; meteorology axis. For 4340 steel under constant amplitude loading at R = 0.5 and climatology; and oceanography. and 0 and for the Felix/28 spectrum loading, short-crack growth rates agreed well with long-crack growth rates, even near the long-crack threshold. A slight short-crack effect, growth below the A91-11072# long-crack threshold, was observed at R = -1. Fatigue lives were TIME SERIES AND CORRELATION OF PULSATIONS found to depend on the size and type of initiation site, especially OBSERVED SIMULTANEOUSLY BY TWO AIRCRAFT for the Felix/28 loading sequence. A semi-empirical crack-growth ANDREW R. OCHADLICK, JR. (U.S. Navy, Naval Air Development model incorporating crack-closure effects was used to predict crack Center, Warminster, PA) Geophysical Research Letters (ISSN growth rates and total, fatigue lives of notched 4340 steel 0094-8276), vol. 17, Oct. 1990, p. 1889-1892. ..refs specimens. An initial defect size and shape typical of those - Two aircraft were used as mobile geomagnetic observatories identified in this steel was assumed for the life predictions. For all to study the similarity of 2-25-s pulsations as a function of aircraft loading conditions, reasonable agreement was found between separation (1.6-4600 km). An analysis of the results obtained measured and predicted values for both crack growth rates and indicates that the strong similarity of pulsations weakens quickly fatigue lives. Author at a distance of about 150 km, which is close to the ionospheric height and thus suggestive of a strong ionospheric control of the spatial coherence of pulsations. V.L.

A91-12537*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. AIRCRAFT EN ROUTE NOISE ANNOYANCE DAVID A. M.CCURDY (NASA, Langley Research Center, Hampton, VA) AIAA,- Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs N91-11248# National Aerospace Lab., Amsterdam (AIAA PAPER 90-4028) Copyright (Netherlands). ^ . Results are reported from a laboratory experiment conducted SHORT AND LONG FATIGUE CRACK GROWTH IN 2024-T3 in order to quantify the annoyance experienced by people on the UNDER FOKKER 100 SPECTRUM LOADING ground in response to en route noise (ERN) generated' by aircraft R. J. H. WANHILL and L. SCHRA In AGARD, Short-Crack Growth at cruise conditions. Objectives included the comparison of Behaviour in Various Aircraft Materials 26 p Aug. 1990 annoyance responses to ERN with the annoyance responses to Sponsored by Netherlands Agency for Aerospace Programs takeoff and landing noise; the comparison of the annoyance Copyright Avail: NTIS HC/MF A09; Non-NATO Nationals requests responses to advanced turboprop aircraft ERN with those of the available only from AGARD/Scientific Publications Executive turbofan ERN; and also the ability of aircraft noise measurement The behavior of short and long fatigue cracks in the widely procedures and corrections to predict annoyance to ERN. Tests used damage tolerant aluminum alloy 2024-T3 was compared using were conducted at the Langley Acoustics Research Laboratory flight simulation loading representatives for the Fokker 100 on 32 human subjects selected at random. Subjects judged the wing/fuselage structure. The results showed that the apparently annoyance level of 24 Propfan Test Assessment advanced anomalous behavior of short cracks is not significant for durability turboprop ERN stimuli, 18 conventional turbofan ERN stimuli, and analysis of the current wing/fuselage structure. Also the data 60 conventional turboprop and turbofan takeoff and landing noise provide a reference for evaluating new, candidate materials for stimuli. Analysis of resulting data compared annoyance responses durable wing/fuselage structures in transport aircraft. Author to different aircraft types and operations, examined the ability of current noise measurement and correction procedures to predict annoyance ERN, and calculated optimum duration correction magnitudes for ERN. " L.K.S.

A91-12538# SOUND INSULATION OF DWELLINGS AROUND AIRPORTS - OBJECTIVE AND SUBJECTIVE MEASURES AND FINDINGS DAVID BROWN (Wyle Laboratories, El Segundo, CA) AIAA, N91-11266# Rolls-Royce Ltd., Bristol (England). Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. EXPERIENCES IN THE USE OF ABACUS FOR CREEP 7 p. refs ANALYSIS ' - (AIAA PAPER 90-4029) Copyright E. O. A. PREMPEH Derby, England 7 Sep. 1989 12 p Aircraft noise is a major problem'to many residents living near Presented at ABAQUS Users Meeting, Harwell, England, 7 Sep. airports. This problem includes disruption of many activities such 1989 as reading, conversation, listening to TV or radio, and sleep. The (PNR-90705; ETN-90-97937) Copyright Avail: NTIS HC/MF retrofit application of sound insulation to dwellings near various A03 • airports in the U.S. has recently become one of the more viable Some of the experiences gained in the use of ABAQUS program and rewarding means of noise mitigation, mainly due to its for creep analysis are reported. The ABAQUS program was used demonstrated effectiveness and the availability of funding to determine the creep behavior of aircraft engine components mechanisms. This paper presents results from a number of projects subject to elevated temperatures and stress. Considerable difficulty in terms of objective (noise metric) evaluations and subjective was experienced in obtaining any creep solution in the initial stages. (opinion survey) attitudes which illustrate the primary benefits to Once the causes of the difficulties were identified and resolved, affected residents. Author the creep law subroutine became properly synchronized with the ABAQUS program. Comparisons of the results with solutions of A91-12541# creep analyses using other programs were found to be satisfactory. SONIC BOOM ENVIRONMENT UNDER A SUPERSONIC A suggestion for improving the ABAQUS user manual is MILITARY OPERATING AREA presented. ESA KENNETH J. PLOTKIN, VIJAY R. DESAI, MICHAEL J. LUCAS,

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CAREY L MOULTON (Wyle Laboratories, Arlington, VA), and from the microburst event. Analyses of crew communications and RUBEN G. GARZA AIAA, Aeroacoustics Conference, 13th, decision times showed a marked improvement in both situation Tallahassee, FL, Oct. 22-24, 1990. 9 p. Research sponsored by awareness and decision-making with visually displayed USAF. refs ground-based radar information. Substantial reductions in the (AIAA PAPER 90-4032) Copyright variability of decision times among crews in the visual display The paper examines results of a six-month sonic boom groups were also found. These findings suggest that crew measurement program conducted in the Lava/Mesa airspace at performance will be enhanced and individual differences among the White Sands Missile Range, New Mexico which is used for crews due to differences in training and prior experience are supersonic air combat maneuver (ACM) training, primarily by F-15s significantly reduced by providing real-time, graphic display of from Holloman AFB. All flight activity data for the airspace were terminal weather hazards. Author reviewed and correlated with measured booms, and a sample of ACMI tracking data was obtained for detailed analysis of particular events and to develop an understanding of how and when supersonic events occur. The measurement program is described in detail, and statistical analysis of sonic booms identified with ACM activity is performed. Analyses include development of models for the long-term C-weighted day-night level and frequency of occurrence of booms at various locations in the airspace, and the N91-11006# European Organization for the Safety of Air probability distribution of boom amplitudes at a given location. Navigation, Brussells (Belgium). Engineering Directorate. The nature of sonic booms occurring in the airspace was also DEVELOPMENTS TO ENHANCE METEOROLOGICAL examined in order to resolve the differences between FORECASTING FOR AIR TRAFFIC SERVICES measurements and earlier predictions. L.K.S. M. E. COX and D. A. FORRESTER (Meteorological Office, Bracknell, England) In AGARD, Aircraft Trajectories: Computation, Prediction, Control, Volume 2: Air Traffic Handling and N91-10548*# Electro Magnetic Applications, Inc., Denver, CO. Ground-Based Guidance of Aircraft. Part 4: Air Traffic Handling. DEVELOPMENT AND APPLICATION OF LINEAR AND Part 5: Guidance of Aircraft in a Time-Based Constrained NONLINEAR METHODS FOR INTERPRETATION OF Environment. Surveillance. Part 7: Meteorological Forecasts. Part LIGHTNING STRIKES TO IN-FLIGHT AIRCRAFT Final Report 8: Aircraft Operation in Air Traffic Handling Simulation 12 p May TERENCE RUDOLPH, RODNEY A. PERALA, CALVIN C. 1990 EASTERBROOK, and STEVEN L. PARKER Sep. 1986 441 p Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests (Contract NAS1-17748) available only from AGARD/Scientific Publications Executive (NASA-CR-3974; NAS 1.26:3974; EMA-85-R-37) Avail: NTIS In the future, the quality of the meteorological data available HC/MFA19 CSCL04/2 for use both in ground-based systems and on aircraft will become Since 1980, NASA has been collecting direct strike lightning even more important as ATC strives to handle increasing volumes data by flying an instrumented F-106B aircraft into thunderstorms. of traffic in the most efficient manner. An indication of the effect The continuing effort to interpret the measured data is reported of errors in meteorological data on the precision of predictions of here. Both linear and nonlinear finite difference modeling aircraft trajectories is discussed and the variability of wind and techniques are applied to the problem of lightning triggered by an temperature is examined, showing the influence of location, altitude aircraft in a thunderstorm. Five different aircraft are analyzed to and season, in the European area. An outline of present-day determine the effect of aircraft size and shape on lightning forecasting methods follows (the data used and accuracies triggering. The effect of lightning channel impedance on aircraft achieved are included). Potential sources of improvements are response is investigated. The particle environment in thunderstorms then discussed with the emphasis being placed on the use of and electric field enhancements by typical ice particles is also aircraft-derived data (details are given of the accuracy of such investigated. Author data, possible methods of recovery, and their application within the Meteorological Services). The impact is described of turbulence N91-10960*# National Aeronautics and Space Administration. on both the safety of air traffic and the accuracy of flight profile Ames Research Center, Moffett Field, CA. predictions (possible methods of providing aircraft with the means TERMINAL WEATHER INFORMATION MANAGEMENT for the automatic reporting of turbulence are included). Some Abstract Only experimental work either performed or being planned in the ALFRED T. LEE In NASA, Langley Research Center, Aviation European area is also described, aimed at improving the quality Safety/Automation Program Conference p 271-274 Oct. 1990 of the meteorological data made available for ATS purposes as a Avail: NTIS HC/MF A12 CSCL 04/2 result of using data recovered from aircraft through both satellite Since the mid-1960's, microburst/windshear events have and ground-based (Mode S SSR) systems. Author caused at least 30 aircraft accidents and incidents and have killed more than 600 people in the United States alone. This study evaluated alternative means of alerting an airline crew to the presence of microburst/windshear events in the terminal area. Of particular interest was the relative effectiveness of conventional and data link ground-to-air transmissions of ground-based radar and low-level windshear sensing information on microburst/ windshear avoidance. The Advanced Concepts Flight Sim- N91-11307# Rolls-Royce Ltd., Derby (England). ulator located at Ames Research Center was employed in a COMMERCIAL AIRCRAFT AND THE ENVIRONMENT line oriented simulation of a scheduled round-trip airline flight from ANTHONY B. WASSEL 15 Mar. 1990 15 p Presented at Salt Lake City to Denver Stapleton Airport. Actual weather en Aeropropulsion 1990, Paris, France, Mar. 1990 route and in the terminal area was simulated using recorded data. (PNR-90687; ETN-90-97931) Copyright Avail: NTIS HC/MF The microburst/windshear incident of July 11, 1988 was re-created A03 for the Denver area operations. Six experienced airline crews The impact of both noise and emission control on engine design currently flying scheduled routes were employed as test subjects is considered. New technology developed to meet the regulatory for each of three groups: (1) A baseline group which received objectives are underlined. The reduction of noise in turbofan alerts via conventional air traffic control (ATC) tower transmissions; engines is discussed. Conflicting requirements and considerations (2) An experimental group which received alerts/events displayed of safety are stressed. Subsonic and supersonic noise generation visually and aurally in the cockpit six miles (approx. 2 min.) from and regulations proposed are reviewed. The reduction in CO2 the microburst event; and (3) An additional experimental group and other emissions from aircraft propulsion systems are received displayed alerts/events 23 linear miles (approx. 7 min.) investigated. . ESA 15 MATHEMATICAL AND COMPUTER SCIENCES

15 prediction results in the system are listed, including data distribution rules, presentation of estimated times of arrival, boundary MATHEMATICAL AND COMPUTER SCIENCES estimates, and, in particular, long term detection of conflicts for overflying aircraft, planning of inbound traffic for Schiphol airport, and planning of departure times for an efficient engine start-up Includes mathematical and computer sciences (general); computer procedure. Author operations and hardware; computer programming and software; computer systems; cybernetics; numerical analysis; statistics and probability; systems analysis; and theoretical mathematics. N91-11416# Rolls-Royce Ltd., Derby (England). THE ROLE OF PROCESS MODELLING IN MANUFACTURE AND DESIGN A91-11154 G. J. S. HIGGINBCTHAM 9 Sep. 1989 20 p Presented at MIXED STRUCTURED-UNSTRUCTURED MESHES FOR the 9th ISABE Symposium, Athens, Greece, 4-9 Sep. 1989 AERODYNAMIC FLOW SIMULATION (PNR-90702; ETN-90-97936) Copyright Avail: NTIS HC/MF N. P. WEATHERILL (Swansea, University College, Wales) A03 Aeronautical Journal (ISSN 0001-9240), vol. 94, April 1990, p. The relationship between the design and manufacturing 111-123. Research supported by the Aircraft Research Association functions in the development of aircraft- engine components is and Royal Aerospace Establishment, refs examined. The design manufacturing interface is addressed from Copyright a total engineering process point of view. It identifies how the A composite approach in computational aerodynamics, which introduction of computer modeling of manufacturing processes can uses both structured and unstructured mesh generation for lead to reduced lead times and speedier introduction of new aerodynamic flow simulation, and the possible benefits of this components, processes or alloys into applications for aircraft engine approach, are discussed. An algorithm which can solve Euler power plants, and compares this approach with the traditional equations for inviscid flow on such meshes is suggested. Three iterative development process. The target for computer modeling applications of the approach are described, which include: (1) use are to simultaneously achieve a right first time design while of regions of assembled triangles to improve a structured mesh establishing clear process manufacturing rules. It is shown that in of poor quality, (2) use of local regions of unstructured mesh, this way, both risk and cost can be reduced. ESA within a globally structured mesh, to obtain discrete regions in geometrically complicated aerodynamic configurations, and (3) use N91-11424# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich of mesh/flow adaptivity within a structured mesh. B.P. (Germany, F.R.). Hubschrauber und Flugzeuge. USE OF THE VP-200 COMPUTER FOR A91-11353 AEROTHERMODYNAMIC PROBLEMS A SELF-ORGANIZING STOCHASTIC CONTROL SYSTEM LUCIANO FORNASIER 8 Dec. 1989 11 p Presented at ADAPTABLE TO CHANGING PERTURBATION International Workshop on Supercomputing Tools for Science and CHARACTERISTICS [SAMOORGANIZUIUSHCHAIASIA Engineering, Pisa, Italy, 4-7 Dec. 1989 STOKHASTICHESKAIA SISTEMA UPRAVLENIIA, (MBB/FE122/S/PUB/388; ETN-90-97848) Copyright Avail: PRISPOSABLIVAIUSHCHAIASIA K IZMENIA1USHCHIMSIA NTIS HC/MF A03 KHARAKTERISTIKAM VOZMUSHCHENII] The implementation and application of four aerodynamic flow A. I. PETROV and G. O. STETSKO (Moskovskii Aviatsionnyi Institut, solvers on the Siemens VP-200 vector processor is presented. Moscow, USSR) Akademiia Nauk SSSR, Doklady (ISSN The experience from all cases demonstrates the benefits of vector 0002-3264), vol. 312, no. 2, 1990, p. 284-288. In Russian, refs processing for aerodynamic codes characterized by very large Copyright < computational effort. The high autovectorization level obtainable The problem of the synthesis of adaptive control laws for by the VP-200 allows optimal performance to be achieved with systems with a stochastic structure functioning under conditions speedup factors between 20 to 30 while requiring very marginal of uncontrolled non-Gaussian perturbations with randomly varying code modifications. ESA characteristics is examined with particular reference to the development of high-precision control systems for flight vehicles. N91-11430*# Institute for Computer Applications in Science An optimal solution to the problem is obtained in a class of and Engineering, Hampton, VA. self-organizing systems. Studies of synthesized self-organizing PARALLELIZED RELIABILITY ESTIMATION OF control systems indicate that the algorithms proposed here ensure RECONFIGURABLE COMPUTER NETWORKS Final Report adaptability to the effect of perturbations and to changes in their DAVID M. NICOL, SUBHENDU DAS (College of William and Mary, characteristics, making it possible to improve the precision of flight Williamsburg, VA.), and DAN PALUMBO Sep. 1990 25 p vehicle control. V.L. Submitted for publication (Contract NAS1-18605; NAG1-787; NAG1-1132; NSF N91-10986# National Aerospace Lab., Amsterdam ASC-88-19373) (Netherlands). (NASA-CR-182101; ICASE-90-60; NAS 1.26:182101) Avail: NTIS THE APPLICATION OF TRAJECTORY PREDICTION HC/MF A03 CSCL 09/2 ALGORITHMS FOR PLANNING PURPOSES IN THE A parallelized system, ASSURE, for computing the reliability of NETHERLANDS ATC-SYSTEM embedded avionics flight control systems which are able to J. N. P. BEERS, T. B. DALM, J. M. TENHAVE, and H. VISSCHER reconfigure themselves in the event of failure is described. ASSURE (Department of Civil Aviation, An Hoofddorp, Netherlands ) In accepts a grammar that describes a reliability semi-Markov AGARD, Aircraft Trajectories: Computation, Prediction, Control, state-space. From this it creates a parallel program that Volume 2: Air Traffic Handling and Ground-Based Guidance of simultaneously generates and analyzes the state-space, placing Aircraft. Part 4: Air Traffic Handling. Part 5: Guidance of Aircraft upper and lower bounds on the probability of system failure. in a Time-Based Constrained Environment. Surveillance. Part 7: ASSURE is implemented on a 32-node Intel iPSC/860, and has Meteorological Forecasts. Part 8: Aircraft Operation in Air Traffic achieved high processor efficiencies on real problems. Through a Handling Simulation 11 p May 1990 Previously announced as combination of improved algorithms, exploitation of parallelism, and N89-20115 use of an advanced microprocessor architecture, ASSURE has Copyright Avail: NTIS HC/MF A20; Non-NATO Nationals requests reduced the execution time on substantial problems by a factor of available only from AGARD/Scientific Publications Executive one thousand over previous workstation implementations. The Netherlands ATC-environment, the basic set-up of the Furthermore, ASSURE's parallel execution rate on the iPSC/860 trajectory prediction module, improvements realized, and the is an order of magnitude faster than its serial execution rate on a performance figures are presented. Applications of the trajectory Cray-2 supercomputer. While dynamic load balancing is necessary

65 15 MATHEMATICAL AND COMPUTER SCIENCES

for ASSURE's good performance, it is needed only infrequently; 16 the particular method of load balancing used does not substantially affect performance. Author PHYSICS

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

A91-11786# EXPERIMENTAL STUDY OF HIGH-SPEED IMPULSIVE ROTOR N91-11433 California Univ., Los Angeles. NOISE IN A WIND TUNNEL CONSTRAINED OPTIMIZATION APPROACH TO FEEDBACK JEAN PRIEUR (ONERA, Chatillon, France)" (European Rotorcraft CONTROL OF STATE-AUGMENTED SYSTEMS Ph.D. Thesis Forum, 16th, Glasgow, Scotland, Sept. 18-21, 1990) ONERA, TP WON-ZON CHEN 1990 124 p no. 1990-123, 1990, 12 p. refs Avail: Univ. Microfilms Order No. DA9022003 (ONERA, TP NO. 1990-123) The Linear/Quadratic (LQ) optimal control theory, introduced Results are presented from high-speed impulsive noise (HSIN) by Kalman, has attracted much attention due to the guaranteed tests of two model rotors, conducted in an acoustically-lined wind control optimality with respect to a quadratic performance measure, tunnel. While one of the rotors has rectangular planform blades, and its inherent capability to handle Multiple-Input-Multiple Output the other uses 30-deg sweptback tips of 'F30' configuration. The (MIMO) systems. The LQ design process can be automated through F30 tips are found to yield substantial noise reduction in the an array of analytical procedures, greatly easing the design efforts. direction of maximum HSIN generation, in virtue of the delay of However, unsatisfactory performance and lack of robustness were delocalization toward higher tip speeds; this, in turn, is a experienced with the LQ design method. Numerous methods have consequence of the suppression of transonic effects obtained by been proposed in the past attempting to solve either the the sweptback tips. It is stressed that blade tip geometry may performance and/or the robustness problems of LQ optimal control strongly influence noise radiation through the modification of shock theory. A method that combines the merits of time-domain and surface geometries. O.C. frequency-domain techniques for designing feedback control systems is studied. The approach involves the use of state augmentation to introduce dynamic compensators for performance A91-12427*# Notre Dame Univ., IN. enhancement first and, then, optimize a quadratic cost functional ACOUSTIC RADIATION FROM LIFTING AIRFOILS IN with the constraint of minimum multivariable stability margins. This COMPRESSIBLE SUBSONIC FLOW ; robustness constrained optimization of quadratic performance HAFIZ M. ATASSI, SHANKAR SUBRAMANIAM (Notre Dame, measure approach is direct and matches well with the formulation University, IN), and JAMES R. SCOTT (NASA, Lewis Research and design objectives of real-life design problems. Multivariable Center, Cleveland, OH) AIAA, Aeroacoustics Conference, 13th, examples of designing aircraft flight control laws with state feedback Tallahassee, FL, Oct. 22-24, 1990. 21 p. refs and output feedback are included to illustrate and demonstrate (Contract NAG3-732) the effectiveness of the approach. The subject of how to augment (AIAA PAPER 90-3911) Copyright the state of a dynamic system for performance enhancement is The far field acoustic radiation from a lifting airfoil in a also examined from the standpoint of controllability, feedback three-dimensional gust is studied. The acoustic pressure is equivalence, and minimum order. Dissert. Abstr. calculated using the Kirchhoff method, instead of using the classical acoustic analogy approach due to Lighthill. The pressure on the Kirchhoff surface is calculated using an existing numerical solution of the unsteady flow field. The far field acoustic pressure is calculated in terms of these values using Kirchhoff's formula. The method is validated against existing semi-analytical results for a flat plate. The method is then used to study the problem of an airfoil in a harmonic three-dimensional gust, for a wide range pf Mach numbers. The effect of variation of the airfoil thickness and N91-11473# European Space Agency, Paris (France). angle of attack on the acoustic far field is studied. The changes SOLUTION OF THE TWO-DIMENSIONAL EULER EQUATIONS in the mechanism of sound generation and propagation due to BY A FINITE VOLUME DISCRETIZATION ON UNSTRUCTURED the presence of steady loading and non-uniform mean flow are TRIANGULAR MESHES also studied. Author ARNO RONZHEIMER Aug. 1990 97 p Transl. into ENGLISH of Loesung der Zweidimensionalen Euler-Gleichungen Durch Eine Finite-Volumen-Diskretisierung auf Unstrukturierten Netzen A91-12428*# Arizona Univ., Tucson. (Brunswick, Fed. Republic of Germany, DFVLR), Jul. 1988 82 p INFLUENCE OF AIRFOIL NOSE RADIUS ON SOUND Original language document was announced as N89-15672 GENERATED BY GUST INTERACTIONS (ESA-TT-1135; DFVLR-FB-88-34; ETN-90-98001) Avail: NTIS C. T. TSAI and E. J. KERSCHEN (Arizona, University, Tucson) HC/MF A05; original German version available from DFVLR, AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, Wissenschaftliches Berichtwesen, Postfach 90 60 58, 5000 1990. 12 p. refs Cologne, Fed. Republic of Germany, 28 Deutsches marks (Contract NAG3-357) The main reason for using unstructured grids is the possibility (AIAA PAPER 90-3912) Copyright of simulating flows around complicated geometries, for which the The sound radiated by interaction of a short wavelength gust generation of structured grids fitted to the body is substantially (k much greater than 1) with a symmetric thin airfoil is analyzed. more expensive. The starting point of the study is a solution method The theory is based on a linearization of the Euler equations based on a two dimensional cell corner scheme for structured about the subsonic mean flow past the airfoil. The sound generation grids. The various components of the solution procedure were mechanism is found to be concentrated in a local region adapted to the special requirements of unstructured triangular grids. surrounding the parabolic nose of the airfoil; the size of this local The solution method described is checked by calculating subsonic region scales on the gust wavelength. Airfoil thickness produces and transonic flows around aerofoils. The effects of artificial terms of relative order O(sq rt S) in the far field sound, where S dissipation are investigated and the influence of several is a Strouhal number based on the airfoil nose radius. At low acceleration techniques is discussed. ESA Mach numbers, entropy gusts generate much less sound than

66 16 PHYSICS vorticity gusts. However, for O(1) Mach numbers and moderate A91-12438*# Virginia Polytechnic Inst. and State Univ., values of S, entropy and vorticity gusts produce similar sound Blacksburg. levels. Author ACTIVE CONTROL OF INTERIOR NOISE IN MODEL AIRCRAFT FUSELAGES USING PIEZOCERAMIC ACTUATORS C. R. FULLER (Virginia Polytechnic Institute and State University, A91-12430*# United Technologies Corp., Windsor Locks, CT. Blacksburg), C. H. HANSEN (Adelaide, University, Australia), R. J. UNSTEADY AIRLOADING PANEL METHOD FOR PROP-FANS SILCOX (NASA, Langley Research Center, Hampton, VA), and S. D. B. HANSON (United Technologies Corp., Hamilton Standard D. SNYDER AIAA, Aeroacoustics Conference, 13th, Tallahassee, Div., Windsor Locks, CT) AIAA, Aeroacoustics Conference, 13th, FL, Oct. 22-24, 1990. 8 p. refs Tallahassee, FL, Oct. 22-24, 1990. 12 p. refs (AIAA PAPER 90-3922) Copyright (Contract NAS3-23720) Active control of interior noise in model aircraft fuselages using (AIAA PAPER 90-3914) Copyright piezoceramic actuators is experimentally studied. The actuators An unsteady, linear, compressible, three dimensional lifting are bonded directly to the structure and error information is taken surface panel method is presented for use with propellers and from up to two microphones located in the interior acoustic field. prop-fans. Both gust and blade vibration problems can be treated. The results demonstrate that global attenuation of the order of 10 Derivation of the theory is based on the acceleration potential to 15 dB of interior noise can be achieved with piezoceramic method and can be considered a generalization of the analogous actuators, irrespective of whether the shell system is vibrating at wing theory to include rotation and multiple blades. As with the an acoustic or structural resonant frequency. The work also proves wing methods, the integral equation is discretized and solved by that active control using vibration (moment) inputs works well when matrix inversion. Sample calculations are use to explore the a floor simulating that of an aircraft is installed in the model. This difference between 2D and 30 results and the significance of result suggests that the technique will be successful in controlling unsteadiness in angular inflow calculations for propellers. It is interior noise in realistic aircraft structures. Author shown at the once-per-revolution frequency of propellers, that quasi-steady methods should be adequate. At the high frequencies A91-12440# of interest in noise analysis, 2D strip methods give adequate results RECENT ADVANCES IN ACTIVE NOISE CONTROL away from blade tips. For flutter, frequencies lie in an intermediate K. K. AHUJA (Georgia Institute of Technology, Atlanta) and J. C. range where a full 3D unsteady technique seems to be required. STEVENS AIAA, Aeroacoustics Conference, 13th, Tallahassee, Author FL, Oct. 22-24, 1990.14 p. Research supported by Georgia Institute of Technology, refs (AIAA PAPER 90-3924) Copyright A91-12433# Recent progress in the field of Active Noise Control is reviewed. APPLICATION OF COMPUTATIONAL METHODS IN The advent of the digital computer and subsequent speed and AEROACOUSTICS capacity improvements have made active noise control more G. SENGUPTA, R. H. BURKHART, J. E. BUSSOLETTI, F. T. practical and encouraged rapid advancement in research. Several JOHNSON, R. G. MELVIN (Boeing Commercial Airplanes, Seattle, surveys of research have been done in the past, so emphasis is WA) et al. AIAA, Aeroacoustics Conference, 13th, Tallahassee, placed on the newest and most innovative research. In particular, FL, Oct. 22-24, 1990. 14 p. refs the advancement of research on active noise control during the (AIAA PAPER 90-3917) Copyright decade of the eighties is reviewed. Author Several applications of a computational code for predicting acoustic scattering effects to problems in aeroacoustics are presented. First, the problem of sound generation by an incident A91-12442*# Douglas Aircraft Co., Inc., Long Beach, CA. vortical field interacting with an airfoil is considered by examining ESTIMATION OF THE TURBULENT BOUNDARY LAYER the analogous problem of the scattering of an incident plane wave PRESSURE WAVENUMBER-FREQUENCY SPECTRUM USING by a flat plate. In the second application, the propagation of sound A FIXED PROBE PAIR through ducts was examined, where there is an abrupt change in GOPAL P. MATHUR and MARK R. CANNON (Douglas Aircraft duct cross section. Finally, the scattering of propeller noise by an Co., Long Beach, CA) AIAA, Aeroacoustics Conference, 13th, aircraft was considered, where the propeller noise was simulated Tallahassee, FL, Oct. 22-24, 1990. 8 p. refs by using a distribution of axial and circumferential dipoles. (Contract NAS1-18037) Preliminary predictions showed a significant degree of scattering, (AIAA PAPER 90-3926) Copyright qualitatively similar to some wind-tunnel test data. I.S. The turbulent boundary layer (TBL) pressure fluctuations represent a dominant source of aircraft interior noise during cruise. The wavenumber-frequency characteristics of the TBL pressure field become important when determining its coupling with the A91-12436# aircraft structure and the resulting sound radiation into the interior NUMERICAL SIMULATION OF ACOUSTIC DIFFRACTION OF of the aircraft. A technique is presented to estimate the TBL TWO-DIMENSIONAL RIGID BODIES IN ARBITRARY FLOWS pressure wavenumber-frequency spectrum using a fixed probe pair K. S. HUH (McDonnell Douglas Research Laboratories, Saint Louis, consisting of two microphones. Flight test data from the McDonnel MO; MIT, Cambridge, MA), R. K. AGARWAL (McDonnell Douglas Douglas Ultra High Bypass Demonstrator aircraft were used to Research Laboratories, Saint Louis, MO), and S. E. WIDNALL estimate the TBL pressure wavenumber-frequency spectra. These (MIT, Cambridge, MA) AIAA, Aeroacoustics Conference, 13th, data were compared with selected wall pressure prediction models Tallahassee, FL, Oct. 22-24, 1990. 21 p. Research supported by based on the existing wind tunnel data. The estimated in-flight McDonnell Douglas Corp. refs spectral levels for the Demonstrator aircraft were in good (AIAA PAPER 90-3920) Copyright agreement with the TBL wall pressure prediction models in the Aeroacoustic perturbation quantities about various two- medium wavenumber range. The estimated TBL wavenumber dimensional rigid bodies have been computed by solving the spectral levels were found to be on the higher side in the low Euler equations in the complex domain. The governing equations wavenumber region when compared with the predicted levels. are derived by linearizing the perturbation Euler equations, and by Author assuming a single frequency disturbance. A pseudo-time variable is introduced, and the entire set of equations is driven to convergence by an explicit, 5-stage Runge-Kutta, time-marching, A91-12444# finite volume scheme. A combination of radiation and characteristic THERMOACOUSTICS OF UNSTEADY COMBUSTION boundary conditions is used in the far-field. Some comparisons JAYESH M. MEHTA, P. MUNGUR, W. DODDS, D. BAHR (GE are made with known analytic solutions and with previous Aircraft Engines, Cincinnati, OH), and STEVE CLOUSER (U.S. Navy, investigators. Author Naval Air Propulsion Center, Trenton, NJ) AIAA, Aeroacoustics

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Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 19 p. refs based on tip speed considerations were 5 and 9.5 dB, respectively, (Contract N00140-87-C-9901) for the two altered blade setting angles. Author (AIAA PAPER 90-3928) A longitudinal mode of combustion instability has been studied experimentally and analytically for an advanced aircraft engine A91-12450*# Lockheed Engineering and Sciences Co., Hampton, combustor system. For the tested configuration, a simple VA. longitudinal acoustic mode consisting of a bulk mode in the inlet STATE-OF-THE-ART OF HIGH-SPEED PROPELLER NOISE section and a traveling wave in the combustor sector section has PREDICTION - A MULTIDISCIPLINARY APPROACH AND been identified. The frequencies of oscillations covered a range COMPARISON WITH MEASURED DATA of 150-380 Hz. A linear combustion instability prediction code was MARK H. DUNN (Lockheed Engineering and Sciences Co., exercised to predict and interpret the acoustic behavior of the Hampton, VA) and F. FARASSAT (NASA, Langley Research combustor. A salient feature of the analysis was the observation Center, Hampton, VA) AIAA, Aeroacoustics Conference, 13th, that the combustor inlet side reflection coefficient was found to Tallahassee, FL, Oct. 22-24, 1990. 27 p. refs have significant influence on combustor resonance frequency. The (AIAA PAPER 90-3934) Copyright analysis was found to yield good agreement between computations The results of NASA's Propeller Test Assessment program and measured acoustic spectra and distributions of amplitudes involving extensive flight tests of a large-scale advanced propeller and phase of the first longitudinal acoustic wave. Author are presented. This has provided the opportunity to evaluate the current capability of advanced propeller noise prediction utilizing principally the exterior acoustic measurements for the prediction A91-12448*# National Aeronautics and Space Administration. of exterior noise. The principal object of this study was to evaluate Lewis Research Center, Cleveland, OH. the state-of-the-art of noise prediction for advanced propellers THE EFFECT OF SWIRL RECOVERY VANES ON THE CRUISE utilizing the best available codes of the disciplines involved. The NOISE OF AN ADVANCED PROPELLER effects of blade deformation on the aerodynamics and noise of JAMES H. DITTMAR (NASA, Lewis Research Center, Cleveland, advanced propellers were also studied. It is concluded that blade OH) and DAVID G. HALL (NASA, Lewis Research Center; Sverdrup deformation can appreciably influence propeller noise and Technology, Inc., Brook Park, OH) AIAA, Aeroacoustics aerodynamics, and that, in general, centrifugal and blade forces Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 16 p. refs must both be included in the calculation of blade forces. It is (AIAA PAPER 90-3932) Copyright noted that the present capability for free-field noise prediction of The SR-7A propeller was acoustically tested with and without the first three harmonics for advanced propellers is fairly good. downstream swirl recovery vanes to determine if any extra noise Detailed data and diagrams of the test results are presented. was caused by the interaction of the propeller wakes and vortices R.E.P. with these vanes. No additional noise was observed at the cruise condition over the angular range tested. The presence of the swirl recovery vanes did unload the propeller and some small peak noise reductions were observed from lower propeller loading A91-12451# noise. The propeller was also tested alone to investigate the ANALYSIS OF THE PTA EXTERNAL NOISE DATA AND behavior of the peak propeller noise with helical tip Mach number. COMPARISON WITH PREDICTIONS As observed before on other propellers, the peak noise first rose P. L. SPENCE (Lockheed Engineering and Sciences Co., Hampton, with helical tip Mach number and then leveled off or decreased VA) and P. J. W. BLOCK (Vigyan Research Associates, Inc., at higher helical tip Mach numbers. Detailed pressure-time histories Hampton, VA) AIAA, Aeroacoustics Conference, 13th, indicate that a portion of the primary pressure pulse is progressively Tallahassee, FL, Oct. 22-24, 1990. 24 p. refs cancelled by a secondary pulse as the helical tip Mach number is (AIAA PAPER 90-3935) Copyright increased. This cancellation appears to be responsible for the Analyses of the Propfan Test Assessment external fuselage peak noise behavior at high helical tip Mach numbers. Author noise data and external boom data are presented. Data analysis was focused on an array of 45 microphones located on the external fuselage surface that are arranged into two line arrays, one around A91-12449*# National Aeronautics and Space Administration. the fuselage at the plane of rotation, and the other along the Lewis Research Center, Cleveland, OH. fuselage side nearest to the propeller. A third group comprises a AEROACOUSTIC EFFECTS OF REDUCED AFT TIP SPEED AT surface array of 39 microphones covering from top to bottom of CONSTANT THRUST FOR A MODEL COUNTERROTATION the fuselage and from one diameter upstream to one diameter TURBOPROP AT TAKEOFF CONDITIONS downstream of the plane of rotation. The data obtained from this RICHARD P. WOODWARD and CHRISTOPHER E. HUGHES surface array and the developed color contours of the noise (NASA, Lewis Research Center, Cleveland, OH) AIAA, intensity on the fuselage are presented. Also included are two Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. flight test predictions and the comparison with measured data. 19 p. refs R.E.P. (AIAA PAPER 90-3933) Copyright A model high-speed, advanced counterrotation propeller, F7/A7, was tested in the NASA Lewis Research Center's 9- by A91-12452# 15-foot anechoic wind tunnel at simulated takeoff and approach PREDICTED VS. SCALE MODEL AND FLIGHT TEST UDF conditions of Mach 0.2. The propeller was operated in a baseline ENGINE NOISE configuration with the forward and aft rotor blade setting angles C. E. WHITFIELD and P. R. GLIEBE (GE Aircraft Engines, (36.2deg and 35.4 deg) and forward and aft rotational speeds Cincinnati, OH) AIAA, Aeroacoustics Conference, 13th, essentially equal. Two additional configurations were tested with Tallahassee, FL, Oct. 22-24, 1990. 11 p. refs the aft rotor at increased blade setting angles and the rotational (AIAA PAPER 90-3936) Copyright speed reduced to achieve overall performance similar to that of This paper presents an overview of the development of a the baseline configuration. The aft rotor blade angles were adjusted frequency-domain, noncompact-source noise prediction model for such that the thrust and power absorption for each rotor remained the unducted fan (UDF) engine. A brief description of the acoustic the same as for the baseline configuration. Acoustic data were modeling approach and basic equations employed is given, together taken with an axially translating microphone probe that was with a summary of the aerodynamic characteristics utilized in the attached to the tunnel floor. Concurrent aerodynamic data were noise prediction model. Scale model test results obtained from taken to define propeller operating conditions. The aft rotor both low-speed and high-speed wind tunnel measurements are fundamental tone was about 6 dB lower with the 36.2 deg and compared with the prediction model, and comparisons of predicted 38.4 deg blade setting angles, and about 9 dB lower with the vs measured flight noise characteristics for the full-scale engine 36.2 and 41.4 deg blade setting angles. Predicted noise reductions are also discussed. Author

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A91-12457# Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. SUPPRESSION OF FATIGUE INDUCING CAVITY ACOUSTIC 8 p. refs MODES ON TURBO FAN ENGINES (Contract N00014-87-K-0837) R. H. BENNER (Rohr Industries, Inc., Chula Vista, CA) AIAA, (AIAA PAPER 90-3948) Copyright Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. Flow induced noise generation mechanisms in a centrifugal 9 p. refs turbomachine are investigated in this study. To isolate the noise (AIAA PAPER 90^3941) -Copyright generation mechanisms of interest, a simplified discharge This.paper.discusses several methods of suppressing shear configuration was selected. The unsteady flowfield discharging from layer excitation of cavity acoustic modes on turbofan engines. the rotating impeller has been measured with stationary hot-wire The methods include the use of a Helmholtz resonator, reducing sensors. A space and time cross-correlation technique using two the cavity impingement length with vane-like dividers, and drawing stationary hot-wire sensors was developed to simulate a rotating the shear layer into the cavity. Empirical data and closed-form hot-wire measurement. The simulated auto-spectrum of the solutions were used to design baseline structures employed in discharged velocity shows a similar pattern to that observed in each method. Full scale turbofan engine tests were used to the spectrum from an impeller mounted rotating pressure sensor. measure their effectiveness. Each method significantly reduced Experimental results demonstrate how the unsteady flow in the the level to which cavity acoustic modes were excited by shear impeller passages, modulated by a mild rotating stall pattern, layer flow. . . . Author interacts with the trailing edge of the impeller blades, and generates noise. Author A91-12460*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. A91-12466# BOUNDARY ELEMENT ANALYSIS OF SOUND SCATTERED BY EXPERIMENTAL STUDY OF NOISE SOURCES AND ACOUSTIC A MOVING SURFACE PROPAGATION IN A TURBOFAN MODEL M. K. MYERS and J. S. HAUSMANN (George Washington S. LEWY, S. CANARD-CARUANA (ONERA, Chatillon, France), and University, Hampton, VA) AIAA, Aeroacoustics Conference, 13th, J. JULLIARD (SNECMA, Moissy-Cramayel, France) AIAA, Tallahassee, FL, Oct. 22-24, 1990. 13 p. refs • Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,.1990. (Contract NCC1-14) 16 p. Research supported by the Service Technique des (AIAA. PAPER 90-3944) Copyright Programmes Aeronautiques. refs . ?A solution, for the acoustic field scattered from a uniformly (AIAA PAPER 90-3950) Copyright moving rigid body in the presence of a harmonic incident source Experimental studies of the acoustic radiation of subsonic fans has been obtained using a boundary integral method. A derivation mainly due to blade and vane presure fluctuations were performed of the Kirchhoff formula given by Farassat and Myers (1988) for in the SNECMA 5C2 compressor anechoic facility. A brief moving surfaces forms the basis for the analysis, and the description of the test rig is presented noting that the CAS turbojet development of a boundary integral method for the solution of engine model fan has a diameter of 47 cm, 48 blades, and a scattering problems from moving rigid bodies is described. Finite nominal rotation speed of 12,600 rpm. The two chief experiments elements are used in conjunction with-the Galerkin method in discussed are the measurement of blade and vane pressure order to solve the integral equation that results from the Kirchhoff fluctuations by thin-film transducers and the spinning mode analysis formula when the observer point.is placed on the moving-body of the sound field propagating in the intake duct. Several examples surface., Once appropriate surface field values are known they of applications are discussed, and it is shown that an inflow control are inserted back into the formula in order to predict the field device, as expected, reduces the aerodynamic disturbances by scattered off the body. Tests, including the so called superposition about 10 dB. Rotor-stator interaction tones are determined by the method, are carried out in order to validate the technique and to modal analysis, and it is found that a 'duct lining with a length of establish some confidence in its accuracy. Application of the one duct radius could give an insertion loss up to 20 dB in flight. superposition method to;moving bodies is-presented, and results ' L.K.S. of the two approaches are discussed. Sample calculations of scattering from a simple body are presented to illustrate the effects A91-12467# of-variations in relevant parameters. L.K.S. ROTOR WAKE/STATOR INTERACTION NOISE-PREDICTIONS VERSUS DATA A91-12463*# National Aeronautics and Space Administration. D. A. TOPOL (Pratt and Whitney Group, East Hartford, CT) AIAA, Langley Research Center/Hampton, VA. Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. REMOVING SPURIOUS REFLECTIONS FROM CFD 14 p. refs SOLUTIONS BY USING THE COMPLEX CEPSTRUM (AIAA PAPER 90-3951) Copyright KRISTINE R. MEADOWS and JAY C. HARDIN (NASA, Langley A rotor wake/stator interaction noise prediction method is Research Center, Hampton, VA) AIAA,,Aeroacoustics Conference, presented and evaluated with fan rig and full-scale engine data. 13th, Tallahassee, FL, Oct. 22-24, 1990. 11 p. refs The noise prediction method uses a two-dimensional (2D) (AIAA PAPER 90-3947) Copyright semi-empirical wake model and an analytical stator response The Complex Cepstrum is shown to remove spurious reflections function and noise calculation. The stator response function is a from artificial boundaries in computational fluid dynamic (CFD) 2D strip theory which is linked to a noise calculation formulated solutions. First, the Complex Cepstrum theory is presented. A model in a constant area annular duct with mean axial flow. Comparisons time sequence consisting of a direct signal and reflections is are made with data from an Advanced Ducted Propeller (ADP) analyzed theoretically with the Complex Cepstrum, and it is shown fan rig which is a next-generation turbofan engine design. A that the direct signal uncontaminated by reflections may be calibration of the prediction model is attempted using this rig data. recovered in the time domain. Next, the Complex Cepstrum is The calibrated model is subsequently utilized to calculate and applied to one- and three-dimensional CFD solutions, and spurious compare with noise test data from a 4.1-inch diameter fan rig and reflections from the boundary .conditions are removed. By from a full-scale turbofan engine configuration. The results indicate eliminating spurious reflections introduced by artificial boundary the method has promise, but that further improvement is conditions, the applicability of CFD methods to aeroacoustic desirable. • Author problems is greatly enhanced. Author A91-12468# A91-12464* EXPERIMENTAL/THEORETICAL INVESTIGATION OF THE EXPERIMENTS ON THE AERODYNAMIC NOISE SOURCES IN SOUND FIELD OF AN ISOLATED PROPELLER, INCLUDING CENTRIFUGAL TURBOMACHINERY ANGLE OF INCIDENCE EFFECTS DENNIS K. MCLAUGHLIN, DONALD E. THOMPSON (Pennsylvania T. ZANDBERGEN (Nationaal Lucht- en Ruimtevaartlaboratorium, State University, University Park), and JONG-SOO CHOI AIAA, Amsterdam, Netherlands), S. L. SARIN (Fokker Aircraft, Schiphol,

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Netherlands), and R. P. DONNELLY (Dowty Aerospace Gloucester, Tallahassee, FL, Oct. 22-24, 1990. 21 p. Research supported by Ltd., England) AIAA, Aeroacpustics Conference, 13th, United Technologies Corp. refs Tallahassee, FL, Oct. 22-24, 1990. 9 p. refs (AIAA PAPER 90-3955) Copyright (AIAA PAPER 90-3952) Copyright Far field propeller loading noise equations are developed using A detailed experimental acoustic investigation was carried out the free-space Green function for the convected wave equation in the German/Dutch low speed wind tunnel DNW on a 6 bladed to represent both axial and transverse Mach number components. 1:5 scale model propeller. Both the propeller near field and the Inflow angularity influences noise in two distinct ways. First, loading far field were measured with axially traversing in-flow microphones is modulated causing generation of more efficient radiation modes. and comparisons of test data and predictions have previously been Second, the radiation modes themselves are modified, causing a reported for zero propeller incidence. Also included were tests further noise increase. The first effect is well known; the second under non-zero angle of attack,.and sideslip angle, in order to effect has only recently been recognized and is the subject of obtain also data for a noise prediction method for propeller this paper. The noise formulas exhibit the same spinning mode installation effects. In this report near field experimental data are behavior seen in previous analyses but with higher levels radiated compared with theoretical data, to show the capability of such a into the crossflow. Since the modes are no longer purely spinning, prediction scheme, and with the aim of indicating the behavior of the term 'wobbling mode' has been coined to describe their the main parameters that are believed to control the noise changes behavior. This paper explores the radiation formulas in detail, with angle of incidence. Author compares them with related theoretical treatments, and presents some calculations that explore the magnitude of the effect. A91-12469*# Sverdrup Technology, Inc., Brook Park, OH. Author NEAR-FIELD NOISE OF A SINGLE ROTATION PROPFAN AT AN ANGLE OF ATTACK A91-12475*# AeroChem Research Labs., Inc., Princeton, NJ. M. NALLASAMY, E. ENVIA (Sverdrup Technology, Inc., Brook Park, TIME-DEPENDENT JET FLOW AND NOISE COMPUTATIONS OH), B. J. CLARK, and J. F. GROENEWEG (NASA, Lewis Research C. H. BERMAN (AeroChem Research Laboratories, Inc., Princeton, Center, Cleveland, OH) AIAA, Aeroacoustics Conference, 13th, NJ), J. I. RAMOS (Carnegie-Mellon University, Pittsburgh, PA), G. Tallahassee, FL, Oct. 22-24, 1990. 18 p. refs E. KARNIADAKIS, and S. A. ORSZAG (Princeton University, NJ) (AIAA PAPER 90-3953) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, The near-field noise characteristics of a propfan operating at 1990. 10 p. refs an angle of attack are examined utilizing the unsteady pressure (Contract NAS3-25829; NAS1-18849) field obtained from a three-dimensional Euler simulation of the (AIAA PAPER 90-3961) Copyright propfan flowfield. The near-field noise is calculated employing three Methods for computing jet turbulence noise based on the different procedures: a direct computation method in which the time-dependent solution of Lighthill's (1952) differential equation noise field is extracted directly from the Euler solution, and two are demonstrated. A key element in this approach is a flow code acoustic-analogy-based frequency domain methods which utilize for solving the time-dependent Navier-Stokes equations at relatively the computed unsteady pressure distribution on the propfan blades high Reynolds numbers. Jet flow results at Re = 10,000 are as the source term. The inflow angles considered are -0.4, 1.6, presented here. This code combines a computationally efficient and 4.6 degrees. The results of the direct computation method spectral element technique and a new self-consistent turbulence and one of the frequency domain methods show qualitative subgrid model to supply values for Lighthill's turbulence noise agreement with measurements. They show that an increase in source tensor. Author the inflow angle is accompanied by an increase in the sound pressure level at the outboard wing boom locations and a decrease A91-12476# in the sound pressure level at the (inboard) fuselage locations. INSTABILITY CHARACTERISTICS OF A LOW ASPECT RATIO The trends in the computed azimuthal directivities of the noise RECTANGULAR JET field also conform to the measured and expected results. Author C. SHIH, S. GOGINENI, and A. KROTHAPALLI (Florida Agricultural and Mechanical University; Florida State University, Tallahassee) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, A91-12470*# National Aeronautics and Space Administration. 1990. 12 p. refs Lewis Research Center, Cleveland, OH. (AIAA PAPER 90-3962) Copyright PREDICTION OF THE NOISE FROM A PROPELLER AT ANGLE The instability characteristics of a low (4 to 1) aspect ratio OF ATTACK rectangular jet were investigated at exit Mach numbers ranging EUGENE A. KREJSA (NASA, Lewis Research Center, Cleveland, from low subsonic to moderate supersonic (between 0.03 and OH) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, 1.5). It was found that the variation of the most amplified instability Oct. 22-24, 1990. 20 p. refs mode (preferred mode) in the jet exhibits four distinct regions. (AIAA PAPER 90-3954) Copyright These were identified (according to the arrangement of the flow An analysis is presented to predict the noise of a propeller at structures with respect to the jet centerline) as (1) region I (from angle of attack. The analysis is an extension of that reported by 1 to 20 m/sec), in which the flow instability is dominated by the Mani (1990) which predicted the change in noise due to angle of vortex merging interactions in the shear layer; (2) region II (Mach attack due to both unsteady loading and to azimuthal variation of numbers between 0.1 and 0.6), in which antisymmetric flow the radiation efficiency of steady noise sources. Mani's analysis, structures dominate the flow development; (3) region III (Mach however, was limited to small angles of attack. The analysis numbers between 0.6 and 0.85), where both antisymmetric and reported herein removes this small angle limitation. Results from symmetric structures exist; and (4) region IV (Mach numbers higher the analysis are compared with^the data of Woodward (1987, than 1.2), a symmetric mode region. I.S. 1988), for a single rotation propeller and for a counter rotating propeller. The comparison shows that including the effect of angle A91-12477*# University of Southern California, Los Angeles. of attack on the steady noise sources significantly improves the COHERENT STRUCTURE INDUCED PRESSURE agreement with data. Including higher order effects of angle of FLUCTUATIONS IN AN ELLIPTIC JET attack, while changing the predicted noise at far forward and aft S. SCHRECK and C. M. HO (Southern California, University, Los angles, has little effect near the propeller plane. . Author Angeles, CA) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 6 p. refs A91-12471# (Contract NAG1-1096) NOISE RADIATION OF PROPELLER LOADING SOURCES (AIAA PAPER 90-3963) Copyright WITH ANGULAR INFLOW The fluctuating pressure near an M — 0.5 elliptic jet was D. B. HANSON (United Technologies Corp., Hamilton Standard examined. Layered structures of the pressure field were found. Div., Windsor Locks, CT) AIAA, Aeroacoustics Conference, 13th, Just outside of the jet edge, the pressure is mainly produced by

70 16 PHYSICS the passing vortices. A short distance away from this layer, the A91-12483# pressure fluctuations originating from the end of the potential core AN EXPERIMENTAL TECHNIQUE OF SEPARATING become dominant and are the source of the far field noise. AIRBORNE AND STRUCTURE-BORNE NOISE USING Author WAVENUMBER-FREQUENCY SPECTRUM GOPAL P. MATHUR, BRYCE K. GARDNER, JAMES E. PHILLIPS, and PAUL L. BURGE (Douglas Aircraft Co., Long Beach, CA) A91-12479*# National Aeronautics and Space Administration. AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, Langley Research Center, Hampton, VA. 1990. 8 p. refs NOISE TRANSMISSION CHARACTERISTICS OF A LARGE (AIAA PAPER 90-3969) Copyright SCALE COMPOSITE FUSELAGE MODEL An experimental technique for separating airborne and TODD 8. BEYER and RICHARD J. SILCOX (NASA, Langley structure-borne noise components using the wavenumber- Research Center, Hampton, VA) AIAA, Aeroacoustics Conference, frequency spectral mapping of the radiated sound field is de- 13th, Tallahassee, FL, Oct. 22-24, 1990. 11 p. refs scribed. In the experiments, the wavenumber-frequency spec- (AIAA PAPER 90-3965) Copyright tra of the vibrational response and the radiated sound field Results from an experimental test undertaken to study the basic of a flat plate subjected to a uniform acoustic field and a point noise transmission characteristics of a realistic, built-up composite mechanical input were determined using modal expansion and fuselage model are presented. The floor-equipped stiffened boundary element methods. It is shown that the wavenumber- composite cylinder was exposed to a number of different exterior frequency spectra of the vibration response and sound radiation noise source configurations in a large anechoic chamber. These from the plate reveal the basic mechanisms of airborne and struc- exterior source configurations included two point sources located ture-borne sound radiation, making it possible to separate the two in the same plane on opposite sides of the cylinder, a single noise components. I.S. point source and a propeller simulator. The results indicate that the interior source field is affected strongly by exterior noise source phasing. Sidewall treatment is.seen to reduce the overall interior sound pressure levels and dampen dominant acoustic resonances so that other acoustic modes can affect interior noise distribution. A91-12484*# National Aeronautics and Space Administration. R.E.P. Langley Research Center, Hampton, VA. SOME FAR-FIELD ACOUSTICS CHARACTERISTICS OF THE XV-15 TILT-ROTOR AIRCRAFT A91-12480# ROBERT A. GOLUB, DAVID A. CONNER (NASA, Langley STRUCTURE-BORNE NOISE TRANSMISSION IN THE Research Center, Hampton, VA), LAWRENCE E. BECKER, C. PROPFAN TEST ASSESSMENT AIRCRAFT KENDALL RUTLEDGE, and RITA A. SMITH (Lockheed Engineering JAMES F. UNRUH-(Southwest Research Institute, San Antonio, and Sciences Co., Hampton, VA) AIAA, Aeroacoustics Conference, TX) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, 13th, Tallahassee, FL, Oct. 22-24, 1990. 15 p. refs Oct. 22-24, 1990. 7 p. refs (AIAA PAPER 90-3971) Copyright (AIAA PAPER 90-3966) Copyright Far-field acoustics tests have been conducted on an Estimates of the level of structure-borne noise transmission in instrumented XV-15 tilt-rotor aircraft. The purpose of these acoustic the Propfan Test Assessment (PTA) aircraft were carried out for measurements was .to create an encompassing, high confidence the first three blade passage frequencies. The procedure used (90 percent), and accurate (-1.47 +1/8 dB theoretical confidence combined the frequency response functions of cabin sound interval) far-field acousitcs data base to validate ROTONET and pressure level to wing strain response obtained during ground other current rotorcraft noise prediction computer codes. This paper test of the PTA aircraft with in-flight measured wing strain response describes the flight techniques used, with emphasis on the care data. The estimated structure-borne noise levels varied from 64 taken to obtain high-quality far-field acoustic data. The quality and to 84 dB showing very little dependence on engine/propeller power, extensiveness of the data base collected are shown by presentation flight altitude, or flight Mach number. In general, the bare cabin of ground acoustic contours for level flyovers for the airplane in-flight noise levels decreased with increasing propeller tone giving flight mode and for several forward velocities and nacelle tilts for rise to a plausible structure-borne noise transmission problem at the transition mode and helicopter flight mode. Acoustic pressure the higher blade passage tones. Without knowledge of the effects time-histories and fully analyzed ensemble averaged far-field data of a high insertion loss.side wall treatment on structure-borne results (spectra) are shown for each of the ground contour cases. noise transmission of the bare cabin no quantitative conclusions Author could be made on the level of structure-borne noise transmission in a treated production aircraft. Author

A91-12482*# Douglas Aircraft Co., Inc., Long Beach, CA. A91-12485* THE USE OF SPATIAL COHERENCE TECHNIQUES FOR NOISE MECHANISMS OF TRANSONIC VORTEX AIRFOIL IDENTIFYING NOISE TRANSMISSION PATHS ON THE INTERACTION MDC-UHB DEMONSTRATOR AIRCRAFT H.-M. LENT, K. F. LOEHR, G. E. A. MEIER, K. J. MUELLER, U. BOI N. TRAN and MYLES A. SIMPSON (Douglas Aircraft Co., SCHIEVELBUSCH (Max-Planck-lnstitut fuer Stroemungsforschung, Long Beach, CA) AIAA, Aeroacoustics Conference, 13th, Goettingen, Federal Republic of Germany) et al. AIAA, Tallahassee, FL, Oct. 22-24, 1990. 8 p. refs Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. (Contract NAS1-18037) 12 p. refs (AIAA PAPER 90-3968) Copyright (AIAA PAPER 90-3972) Copyright Application of partial coherence techniques to determination of Experiments on the compressible vortex-airfoil interaction were the transmission paths of sound into an airplane cabin interior performed in a compressible flow. For this investigation two different has been studied. Accurate quantitative information on the experimental setups were used to obtain a two-dimensional dominant paths of acoustic energy transmission can be obtained interaction which was mainly observed with interferometric with this technique as well as the relative contributions from techniques. During the interaction two mechanisms for the airborne and structure-borne paths. This information is useful in generation of soundwaves were found. For both mechanisms making design changes in the fuselage to reduce the interior cabin simple models were constructed which can explain the onset and noise. The techniques are successfully applied to noise and particularly the strength of these waves. Besides the vibration data collected during flight tests of the McDonnel Douglas soundgeneration, viscosity effects of the flow were observed such Ultra-High Bypass Demonstrator aircraft, and these results are as separation of the flow at the leading edge and secondary compared with other data measured during the flight program. vortices at the shoulder of the airfoil. But these effects seem not Author to govern the sound emission. Author

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A91-12486*# Virginia Polytechnic Inst. and State Univ.',- A91-12492# Blacksburg. A MODAL EVALUATION OF NOISE GENERATED BY THE THE IDENTIFICATION OF HELICOPTER NOISE USING A • FRONT ROTOR OF A COUNTER-ROTATING PROP-FAN NEURAL NETWORK DAVID . J. PARZYCH (United Technologies Corp., Hamilton RANDOLPH H. CABELL, CHRIS R. FULLER, and WALTER F. Standard Div., Windsor Locks, CT) AIAA, Aeroacoustics O'BRIEN (Virginia Polytechnic Institute and State University, Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 6 p. Research Blacksburg) AIAA, Aeroacoustics Conference, 13th, Tallahassee, supported by the United Technologies Corp. refs FL, Oct. 22-24, 1990. 10 p. refs (AIAA PAPER 90-3979) Copyright - (Contract NAS1-18471) The noise generated by the upstream rotor of a counterrotating (AIAA PAPER 90-3973) Copyright propfan (CRP) was estimated using a 10 x 8 bladed 22-in CRP Experiments were carried out to demonstrate the ability of an model installed in a wind tunnel. The tests were designed artificial neural network (ANN) system to distinguish between the specifically to isolate the contribution of noise produced by the noise of two helicopters. The ANN is taught to identify helicopters front orthe rear rotors of the CRP. In the tests, the front rotor's by using two types of features: one that is associated with the blade angle was held constant, and the rear rotor's blade angle ratio of the main-rotor to tail-rotor blade passage frequency (BPF), was varied; this arrangement provided a constant source of wakes and the ohter that describes the distribution of peaks-in the from the front rotor, but allowed the upstream potential'field main-rotor spectrum, which is independent of the tail-rotor. It is associated with the rear rotor to vary. The results show that a shown that the ability of the ANN to identify helicopters is significant amount of aerodynamic interacton noise is produced comparable to that of a conventional recognition system using by the front rotor of a CRP, due to the upstream potential field of the ratio of the main-rotor BPF to the tail-rotor BPF (when both the rear rotor. ' • I.S. the main- and the tail-rotor noise are present), but the performoance • of ANN exceeds the conventional-method performance when the tail-rotor noise is absent. In addition, the results of ANN can be A91-12493# obtained as a function of propagation distance. I.S. THE SCREECH OF ROUND CHOKED JETS, REVISITED ALAN POWELL (Houston, University, TX), Y. UMEDA, and R. ISHII (Kyoto University, Japan) AIAA, Aeroacoustics Conference, 13th, A91-124900 '.',..•• Tallahassee, FL, Oct 22-24, 1990. 5 p. Research supported by THE ROLE OF LEADING EDGE VORTEX FLOWS IN the Texas Advanced Research Program -and , University of PROP-FAN INTERACTION NOISE Houston.- refs •' . •' - "• •..,--- J. C. SIMONICH, D. C. MCCORMICK, and P. L. LAVRICH (United (AIAA PAPER 90-3980) Copyright . • • •••••'• • Technologies Research Center, East Hartford, CT) AIAA, The screech modes of round choked -jets issued from a Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. convergent 1-cm-diam circular nozzle are-studied using two 12 p. Research supported by the United Technologies Corp. microphones, located at a radius of 7.7. cm upstream of the face refs . . ... of the nozzle: one kept in a fixed position, and the other rotated (AIAA PAPER 90-3977) Copyright . about the axis in 15-deg increments up to 180 deg relative to the A simulation study to investigate the interaction mechanisms first one. The signal outputs were recorded in the, 100 Hz to 100 associated with .wakes from both aft-swept and forward-swept kHz band and were analyzed using a digital correlator and an vanes incident on rotating prop-fan blades is presented. The analyzer. Results of correlation measurements showed that, as forward-swept vane caused the leading edge vortex and an the pressure ratio increased, the unstable screech modes of associated core velocity defect to move inboard toward the hub oscillation of round jets were toroidal (lateral), toroidal again, and away from the high speed tip region of the prop-fan. The sinuous, helical, and then- sinuous again; while one mode aft-swept vane, however, directed the leading edge vortex out dominates, another one may occur weakly and simultaneously, its towards the tip, and led a large axial velocity disturbance to be frequency variation being a smooth continuation of that when it swept toward the tip region of the prop-fan. Noise measurements dominates. The frequency of the dominant helical mode was found show that the forward-swept vane wakes generated relatively lower to be greater than that of the concurrent secondary or adjacent interaction noise than the aft-swept vane wakes at equivalent vane dominant sinuous modes. . - I.S. loadings. It is suggested that by reducing the sweep, or changing the spanwise loading on the blades, it may be possible to control the magnitude and/or location of the velocity defect that is associated with the leading edge vortex. ' 'R.E.P. A91-12495*# Georgia Inst. of Tech., Atlanta. AN EVALUATION OF VARIOUS CONCEPTS OF REDUCING SUPERSONIC JET NOISE A91-12491# K. K. AHUJA (Georgia Institute of Technology, Atlanta), J. P. VORTEX STRUCTURE OF WAKES BEHIND AN ADVANCED MANES, K. C. MASSEY, and A. B. GALLOWAY AIAA, PROPELLER AT TAKEOFF LOAD CONDITIONS Aeroacoustics Conference, T3th, Tallahassee, FL, Oct. 22-24,1990. PHILIP L. LAVRICH; DUANE C: MCCORMICK (United Technologies 22 p. refs " • • Research Center, East Hartford, CT), and DAVID J. PARZYCH (Contract NAG3-1066) (United Technologies Corp., Hamilton Standard Div., Windsor (AIAA PAPER 90-3982) Copyright - Locks, CT) AIAA, Aeroacoustics Conference, 13th, Tallahassee, Acoustic and flow visualization data from nozzles mounted on FL, Oct. 22-24, 1990. 18 p. Research supported by the United the same facility were acquired, and a total of 10 different concepts Technologies Corp. refs of jet noise suppression were evaluated relative to one another (AIAA PAPER 90-3978) Copyright and also a round nozzle. All nozzles had the same exit area. The This paper examines the vortical structure of the wake suppressors included noncircular shapes; nozzles fitted with downstream of a single advanced propeller Prop-Ran rotor at notches, tabs, and ejectors; and coaxial rectangular nozzles. simulated takeoff conditions. Flow visualization and three Narrow-band noise data were acquired by a microphone located component velocity measurements were performed. The wake was in the plane of the jet exit. In general, it is found that, for a found to consist of a vortical structure consisting of merged leading constant exit area, the round nozzle is the noisiest. Just about edge and tip vortex as well as inboard viscous wakes. It is likely any modification of this round nozzle around its periphery reduces that the leading edge vortex core on the Prop-Fan blade is burst, the broadband shock-associated noise and, in most instances; leading to a large core size, reduced tangential velocities, and modifies the screech frequency and levels. Coaxial rectangular large streamwise velocity defect. A semi-empirical model is nozzles, nozzles fitted with-two tabs and operated with ejectors, presented which was formulated to predict vortex-core velocities. and a rectangular C-D nozzles with perforated walls are identified This model made significant improvements to wake predictions of to be the most promising concepts worthy of further investigation. highly loaded, swept airfoils. Author . Author

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A91-12496*# National Aeronautics and Space Administration. A91-12505*# Virginia Polytechnic Inst. and State Univ., Lewis Research Center, Cleveland, OH. Blacksburg. NOISE MEASUREMENTS FROM AN EJECTOR SUPPRESSOR IDENTIFICATION OF AEROSPACE ACOUSTIC SOURCES NOZZLE IN THE NASA LEWIS 9- BY 15-FOOT LOW SPEED USING SPARSE DISTRIBUTED ASSOCIATIVE MEMORY WIND TUNNEL E. A. SCOTT, C. R. FULLER, and W. F. O'BRIEN (Virginia EUGENE A. KREJSA, BETH A. COOPER (NASA, Lewis Research Polytechnic Institute and State University, Blacksburg) AIAA, Center, Cleveland, OH), DAVID G. HALL, and ABBAS KHAVARAN Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. (NASA, Lewis Research Center; Sverdrup Technology, Inc., Brook 12 p. refs Park, OH) AIAA, Aeroacoustics Conference, 13th, Tallahassee, (Contract NAG 1-762) FL, Oct. 22-24, 1990. 61 p. refs (AIAA PAPER 90-3992) Copyright (AIAA PAPER 90-3983) Copyright A pattern recognition system has been developed to classify Acoustic results are presented on nozzle test experiments five different aerospace acoustic sources. In this paper the conducted in the NASA Lewis 9 x 15-ft anechoic wind tunnel on performance of two new classifiers, an associative memory a 'nypermix' nozzle concept, a two-dimensional lobed mixer nozzle classifier and a neural network classifier, is compared to the followed by a short ejector section designed to promote rapid performance of a previously designed system. Sources are mixing of the nozzle flow with the flow induced by the ejector. classified using features calculated from the time and frequency Acoustic and aerodyanmic measurements were carried out to domain. Each classifier undergoes a training period where it learns determine the amount of ejector pumping, the degree of mixing, to classify sources correctly based on a set of known sources. and the noise reduction achieved. Spectra from various nozzle After training the classifier is tested with unknown sources. Results configurations were compared to show the effect of the nozzle show that over 96 percent of sources were identified correctly geometry on nozzle-alone noise, the benefit of adding an ejector with the new associative memory classifier. The neural network to the mixer nozzles, and the effect of the ejector geometry on classifier identified over 81 percent of the sources correctly. ejector/suppressor noise level. I.S. Author

A91-12506# RADIATION INTEGRALS FOR SOUND GENERATION BY THE A91-12502*# National Aeronautics and Space Administration. LIGHTHILL QUADRUPOLES IN PROPELLER ACOUSTICS Ames Research Center, Moffett Field, CA. N. PEAKE and D. G. CRIGHTON (Cambridge, University, SOME AEROACOUSTIC AND AERODYNAMIC APPLICATIONS England) AIAA, Aeroacoustics Conference, 13th, Tallahassee, OF THE THEORY OF NONEQUILIBRIUM THERMODYNAMICS FL, Oct. 22-24, 1990. 14 p. Research supported by Rolls-Royce, W. CLIFTON HORNE, CHARLES A. SMITH (NASA, Ames Research PLC. refs Center, Moffett Field, CA), and KRISHNAMURTY KARAMCHETI (AIAA PAPER 90-3993) Copyright (Florida State University, Tallahassee) AIAA, Aeroacoustics This paper considers a number of features of Hanson's Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 22 p. refs frequency domain radiation integrals for propeller acoustics. First, (AIAA PAPER 90-3989) Copyright the use of the thin blade approximation in the surface noise source, An exact equation is derived for the dissipation function of a a common feature of Hanson's work, involving a repositioning of homogeneous, isotropic, Newtonian fluid, with terms associated the surface terms onto a mean plane, is considered in detail, and with irreversible compression or expansion, wave radiation, and shown to introduce errors into the higher derivatives of the real the square of the vorticity. This and other forms of the dissipation time wave form. Second, a corrected version of Hanson's integral function are used to identify simple flows, such as incompressible for the Lighthill quadrupole radiation is presented. Finally, channel flow, the potential vortex with rotational core, and asymptotic analysis is applied and various features of the new incompressible, irrotational flow as minimally dissipative surface source integrals are revealed. Author distributions. A comparison of the hydrodynamic and thermodynamic stability characteristics of a parallel shear flow A91-12507# suggests that an association exists between flow stability and the DIFFRACTION PATTERNS IN THE ACOUSTIC FIELD OF A variation of net dissipation with disturbance amplitude, and that PROPELLER nonlinear effects, such as bounded disturbance amplitude, may C. J. CHAPMAN (Cambridge, University, England) AIAA, be examined from a thermodynamic basis. Author Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. 11 p. Research supported by the Royal Aircraft Establishment. refs (AIAA PAPER 90-3994) Copyright A91-12504*# National Aeronautics and Space Administration. Certain aspects of high-speed propeller acoustics can be readily Langley Research Center, Hampton, VA. understood by means of the classical theory of diffraction. An SOUND TRANSMISSION THROUGH A HIGH-TEMPERATURE account is given of the main features of this theory by considering ACOUSTIC PROBE TUBE three illustrative examples from optics and acoustics; it is then TONY L. PARROTT and WILLIAM E. ZORUMSKI (NASA, Langley shown how the theory applies to multibladed propellers and the Research Center, Hampton, VA) AIAA, Aeroacoustics Conference, high harmonics of any propeller. The stationary phase method is 13th, Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs ideal for deriving asymptotic formulas for such acoustic fields, (AIAA PAPER 90-3991) and leads to a decomposition of both the near and far field into An investigation was conducted of acoustic transmission different types of quiet and loud zones. Author through a tube subjected to an intense thermal gradient along its axis. The results are of interest in the interpretation of acoustic A91-12509*# Texas A&M Univ., College Station. data from probe tube configurations designed to measure ON THE PREDICTION OF FAR FIELD COMPUTATIONAL fluctuating pressures in high temperature environments. The AEROACOUSTICS OF ADVANCED PROPELLERS measured transfer function across a localized heated region in STEPHEN M. JAEGER (McDonnell Douglas Technologies, Inc., the tube was compared to a computed transfer function based on San Diego, CA) and KENNETH D. KORKAN (Texas A&M a theoretical analysis of propagation through strong temperature University, College Station) AIAA, Aeroacoustics Conference, gradients. Over the frequency range 0.4 kHz to 6.0 kHz, generally 13th, Tallahassee, FL, Oct. 22-24, 1990. 10 p. refs good agreement was obtained between the measured and (Contract NAG3-354) calculated attenuation across the heated region with some (AIAA PAPER 90-3996) Copyright discrepancy occurring at the attenuation minima. Agreement A numerical method for determining the acoustic far field between measured and calculated phase difference was excellent generated by a high-speed subsonic aircraft propeller was to within the measurement resolution. Author developed. The approach used in this method was to generate

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the entire three-dimensional pressure field about the propeller critical for the verification of not only numerical predictive models (using an Euler flowfield solver) and then to apply a solution of but also of concepts for sonic boom alleviation. Variations in aircraft the wave equation on a cylindrical surface enveloping the propeller. flight paths and speed as well as organized atmospheric structures The method is applied to generate the three-dimensional flowfield in the acoustic propagation path further complicate this between two blades of an advanced propeller. The results are measurement problem. This paper reviews past experimental compared with experimental data obtained in a wind-tunnel test approaches, pointing out measurement needs; suggests at a Mach number of 0.6. I.S. possibilities in the form of new instruments, processing, and concepts that could be applied; and indicates the opportunities A91-12514*# Mississippi Univ., University. that exist or are being planned for facilities and networks that COMPARISON OF SHOCK WAVE RISE TIME PREDICTION could provide data for initializing predictive models on a nationwide TECHNIQUES basis, or provide sites for field experiments. Author RICHARD RASPET and HENRY E. BASS (Mississippi, University, University) AIAA, Aeroacoustics Conference, 13th, Tallahassee, A91-12519# FL, Oct. 22-24, 1990. 5 p. Research supported by NASA. CONTROLLING PLUME DEFLECTION BY ACOUSTIC (AIAA PAPER 90-4001) Copyright EXCITATION - AN EXPERIMENTAL DEMONSTRATION Two techniques for predicting sonic-boom rise times are K. K. AHUJA (Georgia Institute of Technology, Atlanta) AIAA, described, and the values of the rise time (defined as the time Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. required for the shock front to go from 10 percent to 90 percent 12 p. Research supported by Georgia Institute of Technology and of the maximum overpressure) predicted when using the two Lockheed Corp. refs approaches are compared. The results are applied to the prediction (AIAA PAPER 90-4006) Copyright of the rise time from two hypothetical supersonic transport aircraft. Effect of imposing an external sound field on a Coanda jet In both cases, the rise time predicted at the ground was much was investigated experimentally. It was found that the exhaust greater than that predicted for a conventional SST. I.S. angle of a Coanda plume can be varied by changing the level of excitation. Limited experiments were also performed in a wind A91-12515*# Stanford Univ., CA. tunnel to study the effects of flight simulation on plume deflection THE SONIC BOOM OF AN OBLIQUE FLYING WING controllability by sound using a hollow airfoil fitted with a Coanda ILAN KROO (Stanford University, CA) and ALEX VAN DER jet. Pressure coefficients are measured over this airfoil with, and VELDEN AIAA, Aeroacoustics Conference, 13th, Tallahassee, without acoustic excitation of the Coanda Jet. This exploratory FL, Oct. 22-24, 1990. 10 p. Research supported by NASA, refs study provided a number of new ideas for future work for controlling (AIAA PAPER 90-4002) Copyright flow over curved surfaces. Author An analysis of sonic boom characteristics of an oblique flying wing is presented. The wing, represented by a slewed lift and A91-12520*# National Aeronautics and Space Administration. area-distribution as well as a panel geometry, promises a reduction Langley Research Center, Hampton, VA. of sonic boom signature. For every azimuth angle these distributions TRANSITION CONTROL OF INSTABILITY WAVES OVER A are represented by an equivalent body. The near-field pressure FLEXIBLE SURFACE IN THE PRESENCE OF AN ACOUSTIC signature is determined by using the Whitham F-function with a FIELD correction to account for nonlinear wave propagation. The L. MAESTRELLO (NASA, Langley Research Center, Hampton, VA) geometric asymmetry leads to an asymmetrical sonic boom beneath and F. W. GROSVELD (NASA, Langley Research Center; Lockheed the flight track with bow shocks between 1.0 and 1.5 PSF. Due Engineering and Sciences Co., Hampton, VA) AIAA, Aeroacoustics to favorable volume-lift interference the aft shock has only half Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 9 p. refs the amplitude of the bow shock. A fast numerical method is (AIAA PAPER 90-4008) Copyright described to calculate the perceived loudness. R.E.P. Experimental results are presented which demonstrate the coupling of a laminar boundary layer flow with a typical flexible A91-12516# aircraft panel. It is shown that the boundary layer induces plate SONIC BOOM FOCAL ZONES DUE TO TACTICAL AIRCRAFT oscillations which, in turn, perturb the flow at the same frequencies. MANEUVERS This feedback mechanism is an inherent property of laminar KENNETH J. PLOTKIN (Wyle Laboratories, Inc., Arlington, VA) boundary layer flow passing over a flexible plate. As a result, the AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, flexibility of the plate becomes a source of early transition. The 1990. 11 p. refs laminar boundary layer at the leading edge of the plate reacts to (Contract F49642-83-C-0223) small, upstream, unsteady disturbances due to a streamwise (AIAA PAPER 90-4003) Copyright pressure gradient. The experiments demonstrate that a nominal A study has been conducted of the focal zone 'superbooms' sound pressure incident at the leading edge triggers early transition. associated with tactical maneuvers of military supersonic aircraft. It is shown that transition can be delayed by activating a heat Focal zone footprints were computed for 21 tactical maneuvers: source at the leading edge of the plate which results in downstream two for the SR-71 and 19 for fighters engaged in air combat cooling. Author maneuver (ACM) training. These footprints provide quantitative results which may be used for environmental planning. A key finding A91-12522# of this study is that focus factors and footprint areas for high-g FORCING LEVEL EFFECT OF INTERNAL ACOUSTIC fighter maneuvers are substantially smaller than those for gentle EXCITATION ON THE IMPROVEMENT OF AIRFOIL maneuvers associated with larger aircraft. Author PERFORMANCE F. B. HSIAO (National Cheng Kung University, Tainan, Republic A91-12517# of China), R. C. CHANG (CSIST, Aeronautical Research Laboratory, THE MEASUREMENT OF SONIC BOOM WAVEFORMS AND Taichung, Republic of China), and R. N. SHYU AIAA, PROPAGATION CHARACTERISTICS - TECHNIQUES AND Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. CHALLENGES 9 p. Sponsorship: National Science Council of the Republic of ALFRED J. BEDARD, JR. (NOAA, Wave Propagation Laboratory, China, refs Boulder, CO) AIAA, Aeroacoustics Conference, 13th, Tallahassee, (Contract NSC-79-0210-D006-03) FL, Oct. 22-24, 1990. 10 p. refs (AIAA PAPER 90-4010) Copyright (AIAA PAPER 90-4004) The effects of internal acoustic excitation on the leading edge The measurement of sonic boom waveforms in a turbulent separated boundary layers and the aerodynamic performance over atmosphere with complex nonstationary profiles and three- an airfoil of NACA 63(3)-018 cross section are examined as a dimensional structures of temperature, wind, and humidity function of excitation amplitude and frequency. Tests are conducted presents a difficult challenge. Representative measurements are in an open-type suction wind tunnel at the Reynolds number of

74 16 PHYSICS

300,000. Experimental results indicate that the flow separation is confirms that fountain impingement is responsible for the greatest suppressed at the angles lower than the stalled angle by using unsteady loading. Author small-amplitude excitation with the frequency near the shear layer instability frequency. As the forcing level is increased to some A91-12533"# National Aeronautics and Space Administration. extent, the velocity fluctuations produced by the unsteady pulsing Lewis Research Center, Cleveland, OH. of fluid are demonstrated to be the primary governing parameter UNSTEADY BLADE PRESSURE MEASUREMENTS FOR THE for modifying the separated flow properties. The data also show SR-7A PROPELLER AT CRUISE CONDITIONS that the effective forcing frequency extends over a wider range L. J. HEIDELBERG (NASA, Lewis Research Center, Cleveland, as compared to the lower level excitation. Author OH) and M. NALLASAMY (NASA, Lewis Research Center; Sverdrup Technology, Inc., Brook Park, OH) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, 1990. 16 p. refs A91-1252S*# Florida Atlantic Univ., Boca Raton. (AIAA PAPER 90-4022) Copyright A RAY-ACOUSTICS APPROACH TO FUSELAGE SCATTERING OF ROTOR NOISE The unsteady blade surface pressures were measured on the SR-7A propeller. The freestream Mach number, inflow angle, and NOUREDDINE ATALLA and STEWART A. L. GLEGG (Florida advance ratio were varied while measurements were made at nine Atlantic University, Boca Raton) AIAA, Aeroacoustics Conference, blade stations. At a freestream Mach number of 0.8, the data in 13th, Tallahassee, FL, Oct. 22-24, 1990. 11 p. refs terms of unsteady pressure coefficient versus azimuth angle are (Contract NAG 1-715) compared to an unsteady three-dimensional Euler solution, yielding (AIAA PAPER 90-4013) Copyright very encouraging results. The code predicts the shape (phase) of A ray acoustics approach to fuselage scattering of rotor noise the waveform very well, while the 'magnitude is over-predicted in is considered. The method is based on a combination of classical many cases. At tunnel Mach numbers below 0.6, an unusually geometrical acoustics and the paraxial ray approximation. The large response on the suction surface at 0.15 chord and 0.88 method can handle scattering by objects of arbitrary shapes and radius was observed. The behavior of this response suggests the can be applied in an inhomogeneous moving medium. Applications presence of a leading-edge vortex. Author to aeroacoustics include the scattering of blade vortex interaction (BVI) pulses by rigid scattering objects. The BVI is modeled by a rotating impulsive point force. It has been found that scattering A91-12534# effects of rotating sources cannot be ignored. Flow has also been INSTALLATION EFFECTS ON COUNTER ROTATING found to cause a modification and displacement of the directivity PROPELLER NOISE pattern and the shadow zones behind scatterers. Author B. N. SHIVASHANKARA, D. P. JOHNSON, and R. D. CUTHBERTSON (Boeing Commercial Airplanes, Seattle, WA) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, A91-12526# 1990. 8 p. NOISE CHARACTERISTICS OF THE JAPAN'S EXPERIMENTAL (AIAA PAPER 90-4023) Copyright POWERED LIFT STOL AIRCRAFT A test of a scale model of the Ultra-high bypass open rotor MASATAKA MAITA, KATSUMI TAKEDA (National Aerospace engine (the UDF engine) at a typical takeoff power condition was Laboratory, Chofu, Japan), MASAKI SAITOH, and KEN OHSUMI conducted at the German-Dutch wind tunnel (DNW) in'Holland in (Kawasaki Heavy Industries, Ltd., Kakamigahara, Japan) AIAA, order to determine the possible noise increase of the engine Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24,1990. installation on the aft end of the fuselage. The effects of pylon, 11 p. refs aft-body, and empennage were examined individually and in (AIAA PAPER 90-4014) Copyright combination. For most.of the configurations the number of blades The extensive flight noise data available for the Quiet Short in the forward rotor row was different from that in the aft rotor Take Off and Landing Experimental Aircraft (QSTOL), ASKA, are row so that it was possible to distinguish steady and .interaction summarized. Flight test results, compared with prior subscale tones in the narrow band spectra. Results were taken at a tunnel model/theoretical data, have been used to provide and refine the Mach number of 0.22 and at an inflow sideline distance of 8.16 powered-lift aircraft noise prediction method, which was extended ft. Test results include evidence that the addition of the pylon to generate noise exposure level (footprints) and predict noise upstream of the propulsor increases the blade passage frequency abatement flight operation. It is argued that estimated contours of by as much as 10-12 dB but has a negligible effect on interaction equal noise exposure level shows that STOL operation has potential tones. Data taken at the Boeing Transonic Wind Tunnel facility for reducing noise footprints, as compared with conventional agreed reasonably well with those taken at DNW. L.K.S. aircraft. Schematic diagrams are provided of the noise data instrumentation and data processing system, and a noise data A91-12540*# Pennsylvania State Univ., University Park. analysis program flow chart is presented. . L.K.S. WEAK SHOCK PROPAGATION THROUGH A TURBULENT ATMOSPHERE A91-12528*# Illinois Inst. of Tech., Chicago. ALLAN D. PIERCE and VICTOR W. SPARROW (Pennsylvania State AEROACOUSTIC ENVIRONMENT OF AN ADVANCED STOVL University, University Park) AIAA, Aeroacoustics Conference, 13th, AIRCRAFT IN HOVER Tallahassee, FL, Oct. 22-24, 1990. 10 p. Research supported by RICHARD W. WLEZIEN (Illinois Institute of Technology, Chicago) NASA, refs and PETER J. FERRARO (McDonnell Aircraft Co., Saint Louis, (AIAA PAPER 90-4031) Copyright MO) AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Consideration is given to the propagation through turbulence Oct. 22-24, 1990. 12 p. refs of transient pressure waveforms whose initial onset at any given (Contract NAS1-18745) point is an abrupt shock. The work is motivated by the desire to (AIAA PAPER 90-4016) Copyright eventually develop a mathematical model for predicting statistical The near-field aeroacoustic environment of a 6.02 pet scale features, such as peak overpressures and spike widths, of sonic advanced short takeoff and vertical landing aircraft is investigated booms generated by supersonic aircraft. It is argued that the in proximity to a simulated ground plane. The screech and transient waveform received at points where x greater than 0 will impingement-tone characteristics of twin supersonic round and begin with a pressure jump and a formulation is developed for rectangular plumes are shown to be highly dependent on nozzle predicting the amount of this jump and the time derivatives of the geometry and height above the ground plane. Shadowgraph and pressure waveform immediately following the jump. Author laser-sheet flow visualization are used to clarify the flowfield mechanisms responsible for time-dependent loads due to screech, A91-12543*# National Aeronautics and Space Administration. impingement tones, and unsteady impingement of the upwash Ames Research Center, Moffett Field, CA. on the fuselage undersurface. Detailed dynamic pressure THE ACOUSTIC RESULTS OF A UNITED TECHOLOGIES measurements from an array of transducers on the fuselage SCALE MODEL HELICOPTER ROTOR TESTED AT DNW

75 16 PHYSICS

SANDY R. LIU (NASA, Ames Research Center; U.S. Army, N91-10704# Rolls-Royce Ltd., Derby (England). Aeroflightdynamics Directorate, Moffett Field, CA) and MICHAEL DO WE REALLY NEED 57 WAYS OF RATING AIRCRAFT A. MARCOLINI (NASA, Langley Research Center, Hampton, VA) NOISE AIAA, Aeroacoustics Conference, 13th, Tallahassee, FL, Oct. 22-24, M. J. T. SMITH 13 Aug. 1990 5 p Presented at the 1990 1990. 22 p. refs International Conference on Noise Control Engineering, Goteberg, (AIAA PAPER 90-4035) Copyright Sweden, 13-15 Aug. 1990 An initial summary is presented of the acoustic measurements (PNR-90720; ETN-90-97946) Copyright Avail: NTIS HC/MF acquired for some of the different configurations of a 1/6 A01 geometrically and aeroelastically scaled UTC model helicopter rotor The difficulties encountered for measuring and quantifying the which was tested in the open-jet anechoic test section of the effects of aircraft noise are analyzed. The impact of the noise Duits-Nederlandse Windtunnel in the Netherlands. Of particular measurement results on the air transport business community is interest are high-speed impulsive noise and blade-vortex interaction. discussed. The common elements between all noise measurements An analysis is provided of baseline swept tip rotor acoustic and control methodologies are given. The relationship between characteristics in the regimes of high-speed forward flight, where absolute level and footprint area of constant noise level is high-speed impulsive noise dominates, and low-speed descent, presented. The noise certification standards are determined. where severe blade vortex interaction noise occurs. Also discussed ESA are more recent studies of data which involve the animation of the acoustic field upstream of the rotor to evaluate the detailed N91-11488*# Duke Univ., Durham, NC. Dept. of Mechanical radiation patters caused by BVI and HSI noise sources. The trends Engineering and Materials Science. of these primary noise sources are examined as the first step in AIRCRAFT INTERIOR NOISE REDUCTION BY ALTERNATE validating the data for release and application. L.K.S. RESONANCE TUNING Progress Report, period ending June 1990 DONALD B. BLISS, JAMES A. GOTTWALD, RAMAKRISHNA N91-10699*# National Aeronautics and Space Administration. SRINIVASAN, and MARK B. GUSTAVESON Aug. 1990 41 p Langley Research Center, Hampton, VA. (Contract NAG 1-722) HELICOPTER FAR-FIELD ACOUSTIC LEVELS AS A (NASA-CR-186879; NAS 1.26:186879) Avail: NTIS HC/MF A03 FUNCTION OF REDUCED MAIN-ROTOR ADVANCING CSCL 20/1 BLADE-TIP MACH NUMBER Existing interior noise reduction techniques for aircraft fuselages ARNOLD W. MUELLER, CHARLES D. SMITH, and PHILIP perform reasonably well at higher frequencies, but are inadequate LEMASURIER (Sikorsky Aircraft, Stratford, CT.) Jul. 1990 28 p at lower frequencies, particularly. with respect to the low blade (NASA-TM-102684; NAS 1.15:102684) Avail: NTIS HC/MF A03 passage harmonics with high forcing levels found in propeller CSCL 20/1 aircraft. A method is being studied which considers aircraft fuselage During the design of a helicopter, the weight, engine, rotor lined with panels alternately tuned to frequencies above and below speed, and rotor geometry are given significant attention when the frequency that must be attenuated. Adjacent panels would considering the specific operations for which the helicopter will be oscillate at equal amplitude, to give equal source strength, but used. However, the noise radiated from the helicopter and its with opposite phase. Provided these adjacent panels are relationship to the design variables is currently not well modeled acoustically compact, the resulting cancellation causes the interior with only a limited set of full-scale field test data to study. In acoustic modes to become cutoff, and therefore be general, limited field data have shown that reduced main-rotor non-propagating and evanescent. This interior noise reduction advancing blade-tip Mach numbers result in reduced far-field noise method, called Alternate Resonance Tuning (ART), is currently levels. The status of a recent helicopter noise research project is being investigated both theoretically and experimentally. This new reviewed. It is designed to provide flight experimental data which concept has potential application to reducing interior noise due to may be used to further understand helicopter main-rotor advancing the propellers in advanced turboprop aircraft as well as for existing blade-tip Mach number effects on far-field acoustic levels. aircraft configurations. Author Preliminary results are presented relative to tests conducted with a Sikorsky S-76A helicopter operating with both the rotor speed N91-11493*# National Aeronautics and Space Administration. and the flight speed as the control variable. The rotor speed was Lewis Research Center, Cleveland, OH.- operated within the range of 107 to 90 percent NR at nominal NOISE MEASUREMENTS FROM AN EJECTOR SUPPRESSOR forward speeds of 35, 100, and 155 knots. Author NOZZLE IN THE NASA LEWIS 9- BY 15-FOOT LOW SPEED WIND TUNNEL EUGENE A. KREJSA, BETH A. COOPER, DAVID G. HALL, and N91-10703*# National Aeronautics and Space Administration. ABBAS KHAVARAN (Sverdrup Technology, Inc., Brook Park, Lewis Research Center, Cleveland, OH. OH.) Oct. 1990 62 p Presented at the 13th Aeroacoustics AEROACOUSTIC EFFECTS OF REDUCED AFT TIP SPEED AT Conference, Tallahassee, FL, 22-24 Oct. 1990; sponsored in part CONSTANT THRUST FOR A MODEL COUNTERROTATION by AIAA TURBOPROP AT TAKEOFF CONDITIONS (NASA-TM-103628; E-5717; NAS 1.15:103628; AIAA-90-3983) RICHARD P. WOODWARD and CHRISTOPHER E. HUGHES Oct. Avail: NTIS HC/MF A04 CSCL 20/1 1990 21 p Presented at the 13th Aeroacoustics Conference, Acoustic results are presented of a cooperative nozzle test Tallahassee, FL, 22-24 Oct. 1990; sponsored in part by AIAA 'program between NASA and Pratt and Whitney, conducted in the (NASA-TM-103608; E-5732; NAS 1.15:103608; AIAA-90-3933) NASA-Lewis 9 x 15 ft Anechoic Wind Tunnel. The nozzle tested Avail: NTIS HC/MF A03 CSCL 20/1 was the P and W Hypermix Nozzle concept, a 2-D lobed mixer A model high-speed, advanced counterrotation propeller, F7/A7, nozzle followed by a short ejector section made to promote rapid was tested in the anechoic wind tunnel at simulated takeoff and mixing of the induced ejector .nozzle flow. Acoustic and approach conditions of Mach 0.2. The propeller was operated in aerodynamic measurements were made to determine the amount a baseline configuration with the forward and aft rotor blade setting of ejector pumping, degree of mixing, and noise reduction achieved. angles and forward and aft rotational speeds essentially equal. A series of tests were run to verify the acoustic quality of this Two additional configurations were tested with the aft rotor at tunnel. The results indicated that the tunnel test section is increased blade setting angles and the rotational speed reduced reasonably anechoic but that background noise can limit the to achieve overall performance similar to that of the baseline amount of suppression observed from suppressor nozzles. Also, configuration. Acoustic data were taken with an axially translating a possible internal noise was observed in the air supply system, microphone probe that was attached to the tunnel floor. Concurrent the P and W ejector suppressor nozzle demonstrated the potential aerodynamic data were taken to define propeller operating of this concept to significantly reduce jet noise. Significant reduction conditions. Author in low frequency noise was achieved by increasing the peak jet

76 17 SOCIAL SCIENCES noise frequency. This was accomplished by breaking the jet into on the Future of High Speed Air Transport, Strasbourg, France, segments with smaller dimensions than those of the baseline Nov. 6-8, 1989, Proceedings. Toulouse, France, Cepadues-Editions, nozzle. Variations in ejector parameters had little effect on the 1990, p. 113-121. refs noise for the geometries and the range of temperatures and Copyright pressure ratios tested. Author A review of the mechanistic methods used to produce high speed civil transport (HSCT) fleet forecasts in past years is N91-11494*# National Aeronautics and Space Administration. presented. The economic terms of the market for air travel services Lewis Research Center, Cleveland, OH. and the need for market research studies to estimate the probable THE EFFECT OF SWIRL RECOVERY VANES ON THE CRUISE fleet size for an HSCT are discussed. It is shown that previous NOISE OF AN ADVANCED PROPELLER methodologies to predict the HSCT market do not provide reliable JAMES H. DITTMAR and DAVID G. HALL (Sverdrup Technology, procedures for estimating future fleet sizes. Therefore, it will be Inc., Brook Park, OH.) 1990 18 p Presented at the 13th necessary to perform accurate market research surveys of travel Aeroacoustics Conference, Tallahassee, FL, 22-24 Oct. 1990; patterns in using subsonic wide body sleeper aircraft, sponsored by AIAA teleconferencing, and HSCT in the future as a guide to forecasting (NASA-TM-103625; E-5731; MAS 1.15:103625; AIAA-90-3932) the requirement for high speed commercial transports. R.E.P. Avail: NTIS HC/MF A03 CSCL 20/1 The SR-7A propeller was acoustically tested with and without A91-10963 downstream swirl recovery vanes to determine if any extra noise THE HIGH SPEED MARKET IN THE NEXT THREE DECADES was caused by the interaction of the propeller wakes and vortices L Dl GIORGIO (Alitalia S.p.A., Rome, Italy) IN: European with these vanes. No additional noise was observed at the cruise Symposium on the Future of High Speed Air Transport, Strasbourg, condition over the angular range tested. The presence of the France, Nov. 6-8, 1989, Proceedings. Toulouse, France, swirl recovery vanes did unload the propeller and some small Cepadues-Editions, 1990, p. 127-130. peak noise reductions were observed from lower propeller loading Copyright noise. The propeller was also tested alone to investigate the The commercial and technological requirements that will be behavior of the peak propeller noise with helical tip Mach number. demanded of a supersonic transport program are presented. As observed before on other propellers, the peak noise first rose Predominant efforts will be needed in long range capability, direct with helical tip Mach number and then leveled off or decreased operating costs that are comparable to subsonic aircraft, and at higher helical tip Mach numbers. Detailed pressure-time histories seating capacity of over 300. Technology is continually being indicate that a portion of the primary pressure pulse is progressively improved to achieve greater benefits in reduced specific fuel cancelled by a secondary pulse as the helical tip Mach number is consumption and thrust-to-weight ratios to achieve the continuously increased. This cancellation appears to be responsible for the increasing air transport range requirements. It is concluded that peak noise behavior at high helical tip Mach numbers. Author priority in research should be devoted to sonic boom reduction, the ozone depletion problem, reduction of side line noise, N91-11495*# National Aeronautics and Space Administration. supersonic laminar flow control, and materials, components and Lewis Research Center, Cleveland, OH. systems to sustain supersonic cruise at Mach 3. R.E.P. PREDICTION OF THE NOISE FROM A PROPELLER AT ANGLE OF ATTACK A91-10970 EUGENE A. KREJSA Oct. 1990 22 p Presented at the 13th A CASE STUDY IN FOSTERING INTERNATIONAL HSCT Aeroacoustics Conference, Tallahassee, FL, 22-24 Oct. 1990; COLLABORATION sponsored in part by AIAA JAMES P. LOOMIS and ROBERT F. BESTGEN (Battelle Memorial (NASA-TM-103627; E-5795; NAS 1.15:103627; AIAA-90-3954) Institute, Columbus, OH) IN: European Symposium on the Future Avail: NTIS HC/MF A03 CSCL 20/1 of High Speed Air Transport, Strasbourg, France, Nov. 6-8, 1989, An analysis is presented to predict the noise of a propeller at Proceedings. Toulouse, France, Cepadues-Editions, 1990, p. angle of attack. The analysis is an extension of that reported by 231-236. Mani which predicted the change in noise due to angle of attack Copyright to both unsteady loading and to azimuthal variation of the radiation The factors that led Battelle to establish its Center for High efficiency of steady noise sources. Mani's analysis, however, was Speed Commercial Flight, the international inquiry phase, and the limited to small angles of attack. The analysis reported herein conclusions reached are presented. The characteristics and removes this small angle limitation. Results from the analysis are purposes of an international collaboration program that was defined compared with the data of Woodward for a single rotation propeller and marketed, and how well this was received, are discussed. and a counter rotating propeller. The comparison shows that U.S. manufacturers, financial institutions, operators, and including the effect of angle of attack on the steady noise sources government institutions were provided with a joint forum as they significantly improves the agreement with data. Including higher pursued the possibilities of developing a commercially viable, order effects of angle of attack, while changing the predicted environmentally acceptable high speed commercial transport. The noise at far forward and aft angles, has little effect near the Center's program and its outcome are described, along with the propeller plane. Author prospects for international collaboration. R.E.P.

A91-12233# 17 CONFIGURATION CONTROL AND AIRWORTHINESS MANAGEMENT YOSHIYUKI FUJITSUNA and KENTARO TAKE SOCIAL SCIENCES Ishikawajima-Harima Engineering Review (ISSN 0578-7904), vol. 30, July 1990, p. 296-299. In Japanese, with abstract in English. Includes social sciences (general); administration and management; Based upon V2500-A1 engine development and production documentation and information science; economics and cost experiences, the concept and policy of civil engine configuration analysis; law and political science; and urban technology and control and airworthiness management are described together with transportation. actual process and procedure. First of all, in order to help reader' understanding, general program of civil engine development activities is explained. Then, as for development engine A91-10962 configuration control, the essence of the VIZ type design definition ASSESSING THE MARKET FOR HIGH SPEED AIR TRAVEL IN is described. On the other hand, production engine configuration THE 21ST CENTURY control is characterized by 3-staged engineering change R. W. SIMPSON (MIT, Cambridge, MA) IN: European Symposium management system in addition to substantiation process-similarity,

77 17 SOCIAL SCIENCES analysis or test. As for airworthiness management, the legal background is shown and what was done practically in V2500 certification tests is reported. Finally, future target of configuration control and airworthiness management are noted. Author

N91-10931# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Goettingen (Germany, F.R.). Inst. fuer Aeroelastik. A QUARTER OF A CENTURY OF AEROELASTIC COOPERATION BETWEEN RESEARCH AND INDUSTRY (A REVIEW). PART 1: FIGHTER AIRPLANES AND HELICOPTERS O. SENSBURG, J. BECKER, H. HOENLINGER, and G. STREHLOW In its Contributions in the Field of Aeroelastics on the Occasion of the 60th Anniversary of Professor Dr.-lng. Habil. Hans Wilhelm Foersching p 223-270 Apr. 1990 Avail: NTIS HC/MF A13 Tests and developments which enabled the German aircraft industry and the DLR Institute of Aeroelasticity to become competitive again with other leading nations are described. The first steps, the development of the first German vertical takeoff airplane VJ 101 are depicted. The Tornado fighter airplane aeroelastic investigations are reviewed. Developments and tests for the introduction of active control technology into aircraft design are described. The research work for the European fighter aircraft is outlined. Helicopter aeroelasticity investigations are presented. ESA

78 SUBJECT INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

Typical Subject Index Listing Forcing level effect of internal acoustic excitation on AEROACOUSTICS the improvement ol airfoil performance The CEPRA 19 anechoic wind tunnel | AIAA PAPER 90-4010] p 74 A91-12522 IONERA.TP NO. 1990-72| p 51 A91-11760 The instability of combustion in propulsion engines Application of computational methods in aeroacoustics p56 N91-10141 (AIAA PAPER 90-3917] p 67 A91-12433 SUBJECT HEADING ACOUSTIC FATIGUE Numerical simulation of acoustic diffraction of The sonic boom problem p1 A91-10964 two-dimensional rigid bodies in arbitrary flows Suppression of fatigue inducing cavity acoustic modes | AIAA PAPER 90-39201 p 67 A91-12436 on turbo fan engines Aeroacoustic effects of reduced aft tip speed at constant | AIAA PAPER 90-3941 | p 69 A91-12457 COMPUTER SYSTEMS PROGRAMS thrust for a model counterrotation turboprop at takeoff ACOUSTIC MEASUREMENT — Parallelized reliability estimation o( reconfigurable conditions computer networks Some far-field acoustics characteristics of the XV-15 | AIAA PAPER 90-3933] p 68 A91-12449 (NASA-CR-1S2101I p65 N9t-11430 tilt-rotor aircraft I AIAA PAPER 90-3971] p 71 A91-12484 State-of-the-art of high-speed propeller noise prediction Sound transmission througha high-temperature acoustic - A multidisciplinary approach and comparison with V" measured data probe tube TITLE REPORT PAGE ACCESSION | AIAA PAPER 90-39341 p 68 A91-12450 NUMBER NUMBER NUMBER |AIAAPAPER90-3991| p73 A91-12504 ACOUSTIC PROPAGATION Predicted vs. scale model and flight test UDF engine noise Experimental study of noise sources and acoustic propagation in a turbofan model (AIAA PAPER 90-39361 p 68 A91-12452 | AIAA PAPER 90-39501 p 69 A91-12466 Removing spurious reflections from CFD solutions by The measurement of sonic boom waveforms and using the Complex Cepstrum The subject heading is a key to the subject content | AIAA PAPER 90-39471 p 69 A91 -12463 of the document. The title is used to provide a propagation characteristics - Techniques and challenges | AIAA PAPER 90-4004 | p 74 A91-12517 Experimental/theoretical investigation of the sound field of an isolated propeller, including angle of incidence description of the subject matter. When the title is ACOUSTIC PROPERTIES insufficiently descriptive of document content, a Thermoacoustics of unsteady combustion effects | AIAA PAPER 90-39521 p 69 A9M2468 title extension is added, separated from the title | AIAA PAPER 90-39281 p 67 A91 -12444 Aircraft interior noise reduction by alternate resonance Noise radiation of propeller loading sources with angular by three hyphens. The accession number and the tuning inflow page number are included in each entry to assist INASA-CR-186879) p 76 N91-11488' | AIAA PAPER 90-3955] p 70 A91-12471 ACOUSTIC SCATTERING Some far-field acoustics characteristics of the XV-15 the user in locating the abstract in the abstract tilt-rotor aircraft section. If applicable, a report number is also in- Application of computational methods in aeroacoustics I AIAA PAPER 90-3917| p 67 A91-12433 | AIAA PAPER 90-3971] p 71 A91-12484 cluded as an aid in identifying the document. Under Boundary element analysis of sound scattered by a The role of leading edge vortex flows in prop-fan interaction noise any one subject heading, the accession numbers moving surface I AIAA PAPER 90-3977) p 72 A91-12490 are arranged in sequence. | AIAA PAPER 90-3944 ] p 69 A91-12460 A ray-acoustics approach to fuselage scattering of rotor Some aeroacoustic and aerodynamic applications of the theory of nonequilibrium thermodynamics noise [AIAA PAPER 90-40131 p 75 A91-12525 | AIAA PAPER 90-3989) p 73 A91-12502 ACOUSTIC VELOCITY Radiation integrals for sound generation by the Lighthill Prediction of the noise from a propeller at angle of quadrupoles in propeller acoustics attack I AIAA PAPER 90-3993 ] p 73 A91-12506 |NASA-TM-!03627| p 77 N91-11495 Diffraction patterns in the acoustic field of a propeller ACTIVE CONTROL | AIAA PAPER 90-3994] p 73 A91-12507 Active control of interior noise in model aircraft fuselages On the prediction of far field computational ABORT TRAJECTORIES aeroacoustics of advanced propellers Optimal trajectories ot aircraft and spacecraft using piezoceramic actuators I AIAA PAPER 90-3922] p 67 A91-12438 | AIAA PAPER 90-3996] p 73 A91-12509 p29 N91-10968 Comparison of shock wave rise time prediction Recent advances in Active Noise Control ABSTRACTS techniques | AIAA PAPER 90-39241 P 67 A91-12440 Aircraft trajectories: Computation, prediction, control, | AIAA PAPER 90-40011 p 74 A91 -12514 Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. Numerical simulation and active control of combustion Controlling plume deflection by acoustic excitation - An Part 11: List of contributors instability in a ramjet combustor experimental demonstration |AGARD-AG-301-VOL-3-PT-9-11| p 30 N9M0978 | AIAA PAPER 90-3930] p 46 A91-12446 I AIAA PAPER 90-40061 p 74 A91 • 12519 ACCIDENT. PREVENTION Computation of maximum gust loads in nonlinear aircraft Transition control of instability waves over a flexible Current Emergency Locator Transmitter (ELT) using a new method based on the matched filter approach surface in the presence of an acoustic field deficiencies and potential improvements utilizing and numerical optimization p 60 N91-10317 [AIAA PAPER 90-4008) p 74 A9M2520 TSO-C91a ELTs Static and dynamic aeroelastic characterization of an Aeroacoustic environment of an advanced STOVL INASA-CR-4330) p 28 N91-10964 aerodynamically heated generic hypersonic aircraft aircraft in hover configuration p 61 N91-10320 | AIAA PAPER 90-4016] p 75 A91-12528 ACOUSTIC ATTENUATION Installation effects on counter rotating propeller noise Sound insulation of dwellings around airports - Objective A quarter of a century of aeroelastic cooperation between research and industry (a review). Part 1: Fighter (AIAA PAPER 90-4023] p 75 A91-12534 and subjective measures and findings AERODYNAMIC BALANCE IAIAA PAPER 90-4029] p 63 A91-12538 airplanes and helicopters p 78 N91-10931 A quarter of a century of aeroelastic cooperation Design of the derivative balance for the transonic wind Voice communications in the cockpit noise environment: between research and industry (a review). Part 2: Transport tunnel p 53 N91-10925 The role of active noise reduction p 61 N91-11140 airplanes and other civil applications p 40 N9M0932 AERODYNAMIC CHARACTERISTICS ACOUSTIC DUCTS Voice communications in the cockpit noise environment: The calculation method for subsonic longitudinal and Space-structure determination of the acoustic field The role of active noise reduction p61 N91-11140 lateral aerodynamic characteristics of complete aircraft generated by a helicopter turboshaft engine configuration p5 A9t-11844 ACTUATORS | AIAA PAPER 90-4012) p 46 A91-12524 Instability of a supersonic shock-free elliptic jet Active control of interior noise in model aircraft fuselages I AIAA PAPER 90-39591 p7 A91-12473 ACOUSTIC EMISSION using piezoceramic actuators Applied aspects of laminar-flow technology An accurate acoustic emission location method adapted | AIAA PAPER 90-39221 p 67 A91-12438 for composite materials p 57 A91-11027 p 8 A91-12690 The actuator for the low-noise STOL test plane flight Inverse airfoil design - A classical approach updated ACOUSTIC EXCITATION control system and its development test for transonic applications p 10 A91-12758 Suppression of fatigue inducing cavity acoustic modes |NAL-TM-574| p 37 N91-10038 Innovation with computational aerodynamics - The on turbo fan engines ADAPTIVE CONTROL divergent trailing-edge airfoil p 10 A91-12759 |AIAAPAPER90-3941| p69 A91-12457 Temporal-adaptive Euler/Navier-Stokes algorithm for Development of high-lift wing modifications for an Controlling plume deflection by acoustic excitation - An unsteady aerodynamic analysis of airfoils using advanced capability EA-6B aircraft p 10 A91-12762 experimental demonstration unstructured dynamic meshes Euler/Navier-Stokes calculations of the flowfield of a | AIAA PAPER 90-40061 P 74 A91-12519 |NASA-TM-102734| p 24 N91-10919 helicopter rotor in hover and toward flight Eftect of acoustic excitation on stalled flows over an AERIAL PHOTOGRAPHY p 11 A91-12765 airfoil Detection ol airplanes in aerial imagery Computational aerodynamics applied to general | AIAA PAPER 90-40091 p7 A91-12521 p59 A91-12824 aviation/business aircraft pit A91-12767

A-1 AERODYNAMIC COEFFICIENTS SUBJECT INDEX

Aerodynamic analysis using Euler equations - Aerodynamic heating in the interaction regions of shock Aeroelastic analysis of wings using the Euler equations Capabilities and limitations p11 A91-12769 waves and turbulent boundary layers induced by with a deforming mesh Toward the routine aerodynamic analysis of complex sweptback blunt fins p6 A91-12226 [NASA-TM-102733] p 15 N91-10020 configurations p11 A91-12770 Optimal trajectories of aircraft and spacecraft Evaluation of the ZONA51D program Computational aerodynamic simulation experience p29 N91-10968 [REPT-B-28] p 16 N91-10025 p11 A91-12771 AERODYNAMIC INTERFERENCE Direct use of linear time-domain aerodynamics in Practical aerodynamics and flight dynamics of Yak-52 The aerodynamic interference between tanker and aeroservoelastic analysis: Aerodynamic model and Yak-55 aircraft — Russian book p 13 A91-12911 receiver aircraft during air-to-air refuelling p60 N91-10316 Euler and potential experiment/CFD correlations for a p3 A91-11159 Static and dynamic aeroelastic characterization of an transport and two delta-wing configurations Residual interference and wind-tunnel wall adaptation aerodynamically heated generic hypersonic aircraft [NASA-TM-102208] p 14 N9M0014 configuration p 61 N91-10320 p 52 A91-12890 Application of flight path reconstruction algorithms for CFD for applications to aircraft aeroelasticity Wall interference studies flight data of helicopter p17 N91-10855 (NAL-TM-582) p 28 N91-10031 [PD-CF-9012] p59 N91-10232 Application of unstructured grid methods to steady and Nonlinear feedback control for high alpha flight Unsteady wind tunnel wall interferences in subsonic and unsteady aerodynamic problems p 17 N91-10856 [NASA-CR-186545] p 39 N91-10047 transonic profile flows p 53 N91-10928 Computation of transonic flow over elastic rotor blade Effects of coolant injection on turbine aerodynamic A numerical study of the effects of wind tunnel wall p23 N91-10906 characteristics. Part 1: Test turbine and apparatus proximity on an airfoil model Contributions in the field of aeroelastics on the occasion [NAL-TM-585-PT-1] p 47 N91-10059 [NASA-CR-187322] p 25 N91-10934 of the 60th anniversary of Professor Dr.-lng. Habil. Hans Experimental investigation on the effect of coolant AERODYNAMIC LOADS Wilhelm Foersching injection on turbine aerodynamic characteristics. Part 2: Periodic rotor-blade aerodynamics including loading [ETN-90-97630] p 24 N91-10920 Effects of injection from rotor casing with 30 deg slanted effects p 2 A91-10337 A quarter of a century of aeroelastic cooperation holes All-electric flight control experiments and experiments between research and industry (a review). Part 1: Fighter [NAL-TM-587-PT-2] p 47 N91-10060 with a sidestick on the Concorde p 49 A91-10955 airplanes and helicopters p 78 N91-10931 The evolution of the bypass engine Unsteady airloading panel method for prop-fans A quarter of a century of aeroelastic cooperation [PNR-90707] p47 N91-10068 [AIAA PAPER 90-3914] p 67 A91-12430 between research and industry (a review). Part 2: Transport Aeroacoustic effects of reduced aft tip speed at constant airplanes and other civil applications p 40 N91-10932 Noise radiation of propeller loading sources with angular thrust for a model counterrotation turboprop at takeoff inflow AEROMAGNETISM conditions [AIAA PAPER 90-3955] p 70 A91-12471 Time series and correlation of pulsations observed [NASA-TM-103608] p 76 N91-10703 simultaneously by two aircraft p 63 A91-11072 Calculation of aerodynamic characteristics of airplane Vortex structure of wakes behind an advanced propeller AERONAUTICAL ENGINEERING at takeoff load conditions configurations at high angle of attack in steady and Test launch for turboaircraft engine. Description of the [AIAA PAPER 90-3978] p 72 A91-12491 unsteady flow p 42 N91-11009 installation Aerodynamic design optimization using computational Short crack growth under realistic flight loading: Model [ILA-87-A-02]. p48 N91-11018 fluid dynamics p 43 N91-1T013 predictions and experimental results for Al 2024 and Al-Li AEROSPACE INDUSTRY Application of dynamical systems theory to nonlinear 2090 p62 N91-11246 Availability - A practical approach on aerospace aircraft dynamics p 43 N91-11014 Short and long fatigue crack growth in 2024-T3 under industry p 57 A91-11202 AERODYNAMIC COEFFICIENTS Fokker 100 spectrum loading p 63 N91 -11248 Total quality management at'Rolls-Royce PLC Harrier - The next 30 years p 36 A91 -11715 AERODYNAMIC NOISE [PNR-90759] p60 N91-10298 AERODYNAMIC CONFIGURATIONS Experimental study of high-speed impulsive rotor noise Computational Fluid Dynamics Program at NASA Ames Mixed structured-unstructured meshes for aerodynamic in a wind tunnel Research Center p 16 N91-10840 flow simulation p 65 A91-11154 [ONERA, TP NO. 1990-123] p 66 A91-11786 AEROSPACE PLANES Applied computational aerodynamics — Book Numerical simulation of vortex-wedge interaction Soviet space planes p 54 A91-11737 p9 A91-12751 [AIAA PAPER 90-3918] p6 A91-12434 Numerical simulation of hypersonic flow around a space Euler and potential computational results for selected Experiments on the aerodynamic noise sources in plane. Part 3: Analysis of aerothermodynamic heating aerodynamic configurations p 10 A91-12760 centrifugal turbomachinery [NAL-TR-1027T] p 14 N91-10011 Computational aerodynamics applied to high-lift [AIAA PAPER 90-3948] p 69 A91-12464 AEROSPACE VEHICLES systems p 10 A91-12761 The screech of round choked jets, revisited Flight simulation programs for space plane CFD applications to complex configurations - A survey [AIAA PAPER 90-3980] ' p 72 A91-12493 [NAL-TM-594] p 55 N91-11035 p11 A91-12766 A ray-acoustics approach to fuselage scattering of rotor AEROTHERMOCHEMISTRY Application of computational fluid dynamic methods to noise The instability of combustion in propulsion engines the component aerodynamic design of the V-22 Osprey [AIAA PAPER 90-4013] p 75 A91-12525 p56 N91-10141 tilt rotor vehicle p11 A91-12768 Unsteady blade pressure measurements for the SR-7A AEROTHERMODYNAMICS Future directions for applied computational fluid propeller at cruise conditions Determination of kinetic heating on wind tunnel models dynamics p 59 A91-12775 [AIAA PAPER 90-4022] p 75 A91-12533 by the surface temperature method Euler and potential experiment/CFD correlations 1or a AERODYNAMIC STABILITY [ONERA, TP NO. 1990-104] p4 A91-11779 transport and two delta-wing configurations Instability characteristics of a low aspect ratio Sound transmission through a high-temperature acoustic (NASA-TM-102208] p 14 N91-10014 rectangular jet probe tube Project HyBuJET [AIAA PAPER 90-3962 ] p 70 A91-12476 [AIAA PAPER 90-3991 ] p 73 A91 -12504 [NASA-CR-187011] p 38 N91-10040 Flight characteristics of a modified Schweizer SGS1-36 Numerical simulation of hypersonic flow around a space Body weight of hypersonic aircraft, part 1 sailplane at low and very high angles of attack plane. Part 3: Analysis of aerothermodynamic heating [NASA-TM-101028] p 39 N91-10049 [NASA-TP-3022] p 50 N91-10079 [NAL-TR-1027T) p 14 N91-10011 The evolution of the bypass engine AERODYNAMIC STALLING Static and dynamic aeroelastic characterization of an [PNR-90707] p47 N91-10068 Effect of acoustic excitation on stalled flows over an aerodynamically heated generic hypersonic aircraft Design/development issues for high bypass ratio fans airfoil configuration p 61 N91-10320 [PNR-90758] p48 N91-10076 [AIAA PAPER 90-4009] p7 A91-12521 Use of the VP-200 computer for aerothermodynamic A comparative study of Navier-Stokes codes for AERODYNAMICS problems high-speed flows p 20 N91 -10869 The CEPRA 19 anechoic wind tunnel [MBB/FE122/S/PU8/388] p 65 N91-11424 Calculation of aerodynamic characteristics of airplane [ONERA, TP NO. 1990-72] p 51 A91-11760 AEROTHERMOELASTICITY configurations at high angle of attack in steady and Estimation of the turbulent spectral densities of the Static and dynamic aeroelastic characterization of an unsteady flow p 42 N91 -11009 mass-density using two-dimensional Fourier transform of aerodynamically heated generic hypersonic aircraft AERODYNAMIC DRAG digitized schlieren pictures configuration p 61 N91-10320 Riblets — for aerodynamic drag reduction of'turbulent (ONERA, TP NO. 1990-110] p4 A91-11782 AFTERBODIES skin friction p 59 A91-12694 Application of LU-ADI algorithm in two-dimension Comparison of afterbody test setups for combat aircraft Viscous drag reduction via surface mass injection transonic flow p5 A91-11848 model p 9 A91-12698 Some aeroacoustic and aerodynamic applications of the [ONERA, TP NO. 1990-70] p 51 A91-11758 AERODYNAMIC FORCES theory of nonequilibrium thermodynamics AGING (METALLURGY) An approximate calculating method of (AIAA PAPER 90-3989] p 73 A91-12502 supersonic/hypersonic unsteady aerodynamic forces of A process model for age hardening of aluminium alloys. Grid-generation methodology in applied aerodynamics I-The model p 56 A91-11883 airfoils p5 A91-11845 p9 A91-12755 Influence of heat treatment on microstructure and Evaluation of the ZONA51D program Energy efficiency improvement potential of commercial [REPT-B-28] p 16 N91-10025 aircraft to 2010 properties of an advanced high temperature titanium Direct use of linear time-domain aerodynamics in [DE90-014767] p 39 N91-10046 alloy [PNR-90689] p56 N91-11107 aeroservoelastic analysis: Aerodynamic model Measurement of unsteady blade surface pressure on p60 N91-10316 a single rotation large scale advanced prop-fan with AIR FLOW Determination of unsteady aerodynamic forces on angular and wake inflow at Maori numbers from 0.02 to Effects of coolant injection on turbine aerodynamic engines with a view to flutter investigations 0.70 characteristics. Part 1: Test turbine and apparatus p48 N91-10927 [NASA-CR-182123] p 47 N91-10065 1NAL-TM-585-PT-1) p 47 N91-10059 AERODYNAMIC HEAT TRANSFER Comparison of a mathematical one-point model and a Experimental investigation on the effect of coolant The aerodynamic effects of nozzle guide vane shock multi-point model of aircraft motion in moving air injection on turbine aerodynamic characteristics. Part 2: wave and wake passing on a transonic turbine rotor p41 N91-10969 Effects of injection from rotor casing with 30 deg slanted p24 N91-10915 Aerodynamic design optimization using computational holes AERODYNAMIC HEATING fluid dynamics p 43 N91-11013 [NAL-TM-587-PT-2] p 47 N91-10060 Determination of kinetic heating on wind tunnel models AEROELASTICITY AIR NAVIGATION by the surface temperature method Influence of unsteady aerodynamics on rotor blade Extensive MD-11 automation assists pilots, cuts [ONERA, TP NO. 1990-104] p4 A91-11779 aeroelastic stability and response p 37 A91 -12894 workload p 37 A91-12165

A-2 SUBJECT INDEX AIRCRAFT ENGINES

Four dimensional navigation in air traffic with 4-D Aircraft trajectory reconstitution on the basis of Nonoverlapping composite meshes for multi-element navigation aircraft p31 N91-10991 multi-radar ptol information p34 N9I-11002 air-foils p23 N91-10908 Contribution of the satellite techniques to the Bayesian multi-sensor tracking for advanced air traffic Aircraft interior noise reduction by alternate resonance surveillance of air traffic p 35 N91-11005 control systems p 34 N91 -11003 tuning AIR POLLUTION The use of downlinked measurements to track civil [NASA-CR-186879) p 76 N91-11488 Commercial aircraft and the environment aircraft p 34 N91-11004 AIRCRAFT CONTROL |PNR-90687| p64 N91-11307 Contribution of the satellite techniques to the Pilot modelling techniques for the analysis of aircraft AIR TO AIR REFUELING surveillance of air traffic p 35 N91-11005 linear dynamic behaviour p 49 A91-11158 The aerodynamic interference between tanker and Developments to enhance meteorological forecasting Computation of maximum gust loads in nonlinear aircraft receiver aircraft during air-to-air refuelling for air traffic services p 64 N91 -11006 using a new method based on the matched filter approach p3 A91-11159 Integration of aircraft capability in air traffic handling and numerical optimization p 60 N91-10317 AIR TRAFFIC simulations p 35 N91-11007 Contributions to the improvement of flight safety in wind Inflight replanning for diversions p 27 N91-10955 Simulation of automated approach procedures shear Graphical interlaces for cooperative planning systems considering dynamic flight operations [ESA-TT-1141) p28 N91-10965 p27 N91-10956 p35 N91-11008 Guidance concepts for time-based flight operations Airport system capacity strategic choices AIR TRAFFIC CONTROLLERS (PERSONNEL) p 32 N91-10993 |SR-226| p30 N91-10979 Aviation safety/automation program overview Ground-based 4-D guidance of flights in strong wind AIR TRAFFIC CONTROL p26 N91-10941 p 33 N91-10999 DOD responsibilities on Federal aviation and national ATC automation concepts p 29 N91-10957 Developments to enhance meteorological forecasting airspace system matters The air traffic controller facing automation: Conflict or for air traffic services p 64 N91 -11006 [PB90-218827I p2 N91-10001 cooperation p 34 N91 -11001 A new approach to the flight control system National airspace system: In-flight assistance AIR TRANSPORTATION reconfiguration following a battle damage and/or generic operational concept Airport system capacity strategic choices failure on a control surface p 50 N91-11023 |PB90-233115| p28 N91-10032 [SR-226] P30 N91-10979 AIRCRAFT DESIGN Operational evaluation of initial data link air traffic control AIRBORNE/SPACEBORNE COMPUTERS Concorde-1958-1975 p 35 A91-10956 services. Volume 2: Appendices Extensive MD-11 automation assists pilots, cuts Basic materials and structures aspects for hypersonic |DOT/FAA/CT-90/1-VOL-2| p 29 N91-10033 workload p 37 A91-12165 transport vehicles (HTV) p 54 A91-10974 FAA air traffic operational evaluation of Automated - Static and dynamic aeroelastic characterization of an Soviet space planes p 54 A91-11737 Surface Observing System (ASOS) aerodynamically heated generic hypersonic aircraft Mathematical modelling for analysis of nonlinear aircraft |DOT/FAA/CT-TN90/42| p 52 N91-10084 configuration p 61 N91-10320 dynamics p 50 A91-11820 Aviation Safety/Automation Program Conference AIRCRAFT ACCIDENTS The ATF battle shapes up p 36 A91-12062 [NASA-CP-3090] p 26 N91-10936 Terminal weather information management A superlative from Sukhoi - The SU-27 ATC automation concepts p 29 N91-10957 p64 N9M0960 p37 A91-I2063 Time-based operations in an advanced ATC Effect of wind and wind variation on aircraft Subsonic airfoil design p9 A91-12756 environment p 29 N91 -10958 flight-paths p41 N91-10972 Elements of airfoil design methodology Time-based aircraft/ATC operations study AIRCRAFT APPROACH SPACING p 9 A91-12757 p29 N91-10959 Optimization models and techniques to improve air traffic Inverse airfoil design - A classical approach updated Terminal weather information management management p 31 N91-10988 for transonic applications p 10 A91-12758 p64 N91-10960 The 4-D control of current air carriers in the present Innovation with computational aerodynamics - The A flight test facility design for examining digital environment: Objectives, status, and plans divergent traifing-edge airfoil p 10 A91-12759 information transfer p 28 N91 -10962 p 31 N91-10990 Development of high-lift wing modifications for an Aircraft trajectories: Computation, prediction, control. The control of inbound flights p 32 N91-10992 advanced capability EA-6B aircraft p 10 A91-12762 Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. Expert systems for the generation of thermal area arrival Navier-Stokes methods for internal and integrated flow Part 11: List of contributors paths for civil transport p 32 N91-10995 prediction p 10 A91-12763 IAGARD-AG-301-VOL-3-PT-9-11] p 30 N91-10978 Simulation of automated approach procedures CFD applications to complex configurations - A survey Airport system capacity strategic choices considering dynamic flight operations p11 A91-12766 (SR-226] p30 N91-10979 p35 N9M1008 Computational aerodynamics applied to general Aircraft trajectories: Computation, prediction, control, AIRCRAFT COMPARTMENTS aviation/business aircraft p 11 A91-12767 volume 2: Air traffic handling and ground-based guidance Active control of interior noise in model aircraft fuselages Application of computational fluid dynamic methods to of aircraft. Part 4: Air traffic handling. Part 5: Guidance using piezoceramic actuators the component aerodynamic design of the V-22 Osprey of aircraft in a time-based constrained environment. Part [AIAA PAPER 90-3922] p 67 A91-12438 tilt rotor vehicle p11 A91-12768 6: Surveillance. Part 7: Meteorological forecasts. Part 8: Estimation of the turbulent boundary layer pressure Navier-Stokes computations about complex Aircraft operation in air traffic handling simulation wavenumber-frequency spectrum using a fixed probe configurations including a complete F-16 aircraft IAGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 pair p 12 A91-12772 Optimum on-line handling of air traffic over Western [AIAA PAPER 90-3926] p 67 A91-12442 Computational fluid dynamics design applications at Europe p 30 N91-10982 Generation of a buoyant plume of artificial smoke for supersonic/hypersonic speeds p 12 A91-12773 The EUROCONTROL future ATS system concept and airplane tests Design technologies utilized in the development of the the programme of studies, tests, and trials IDOT/FAA/CT-90/9] p 43 N91-11015 B-2 flight control system p30 N91-10983 Voice communications in the cockpit noise environment: (AIAA PAPER 90-3254] p 50 A91-12928 Prediction of aircraft trajectories p 42 N91 -10984 The role of active noise reduction p 61 N91-11140 The design approach used in the synthesis of the B-2 Aircraft dynamics for air traffic control Aircraft interior noise reduction by alternate resonance lateral-directional control laws p42 N91-10985 tuning [AIAA PAPER 90-3255] p 50 A91-12929 The application of trajectory prediction algorithms for [NASA-CR-186879] p 76 N91-11488 Project HyBuJET planning purposes in tne Netherlands ATC-system AIRCRAFT CONFIGURATIONS [NASA-CR-1870111 p 38 N9I-10040 p65 N91-10986 SST airframe integration for a Mach 2 transport OVRhyp, scramjet test aircraft Generation of aircraft trajectories for on-line operation: p 36 A91-10967 [NASA-CR-187009] p 38 N91-10041 Methods, techniques, and tools p 42 N91-10987 The calculation method for subsonic longitudinal and Body weight of hypersonic aircraft, part 1 Optimization models and techniques to improve air traffic lateral aerodynamic characteristics of complete aircraft [NASA-TM-101028) p 39 N91-10049 management p 31 N91-10988 configuration p5 A91-11844 Supersonic combustion engine testbed, heat lightning The high-resolution graphic display: A possible The ATF battle shapes up p 36 A91-12062 INASA-CR-187010] p 47 N91-10061 man/machine interface for a computer assisted ATC Computational aerodynamics applied to high-lift Computation of maximum gust loads in nonlinear aircraft management system p 31 N91-10989 systems p 10 A91-12761 using a new method based on the matched filter approach The 4-0 control of current air carriers in the present Aerodynamic analysis using Euler equations - and numerical optimization p 60 N91-10317 environment: Objectives, status, and plans Capabilities and limitations p11 A91-12769 Contributions in the field of aeroelastics on the occasion p 31 N91-10990 Toward the routine aerodynamic analysis of complex of the 60th anniversary of Professor Dr.-lng. Habil. Hans Four dimensional navigation in air traffic with 4-D configurations p11 A91-12770 Wilhelm Foersching navigation aircraft p 31 IM91-10991 Navier-Stokes computations about complex [ETN-90-97630] p 24 N91-10920 The control of inbound flights p 32 N91 -10992 configurations including a complete F-16 aircraft A quarter of a century of aeroelastic cooperation Guidance concepts for time-based flight operations p 12 A91-12772 between research and industry (a review). Part 1: Fighter p 32 N91-10993 Detection of airplanes in aerial imagery airplanes and helicopters p 78 N91 -10931 The 4-D descent trajectory generation techniques under p59 A91-12824 A quarter of a century of aeroelastic cooperation realistic operating conditions p 32 N91-10994 Re-engining: Real stage 3 compliance plus other between research and industry (a review). Part 2: Transport Expert systems for the generation of thermal area arrival benefits airplanes and other civil applications p 40 N91-10932 paths for civil transport p 32 N91-10995 (PNR-90755J p48 N91-10075 Boeing flight deck design philosophy p40 N91-10937 A description and evaluation of TIMER: A time-based Static and dynamic aeroelastic characterization of an Development and application of the time domain panel terminal flow-control concept p 32 N91-10996 aerodynamically heated generic hypersonic aircraft method p 43 N91-11010 Use of 4-D RNAV in time-based en route arrival configuration P 61 N91-10320 metering p 33 N91-10997 Application of dynamical systems theory to nonlinear Application of unstructured grid methods to steady and Air traffic management and aircraft guidance in a zone aircraft dynamics p43 N91-11014 unsteady aerodynamic problems p 17 N91-10856 of convergence P 33 N91-10998 AIRCRAFT ENGINES A zonal Navier-Stokes methodology for flow simulation Ground-based 4-D guidance of flights in strong wind Thermal analysis of engine inlet anti-icing systems about a complete aircraft p 18 N9t-t0858 p33 N91-10999 p35 A91-10341 A piloted simulator evaluation of a ground-based 4-O Navier-Stokes solutions about the F/A-18 loretxxty-LEX Holographic interferometry for flow visualization studies descent advisor algorithm p 33 N91-11000 configuration P 18 N91-10860 in high speed fans p 46 A9M1351 The air traffic controller facing automation: Conflict or TranAir: Recent advances and applications The role of primary carbides in fatigue crack propagation cooperation p 34 N91-1100! p 19 N91-10862 in aeroengine bearing steels p 55 A91-11806

A-3 AIRCRAFT EQUIPMENT SUBJECT INDEX

Configuration control and airworthiness management AIRCRAFT MODELS Terminal weather information management p 77 A91-12233 The ground resonance of a helicopter with a rotor of p64 N91-10960 Thermoacoustics of unsteady combustion ideal and approximate symmetry considering the Current Emergency Locator Transmitter (ELT) | AIAA PAPER 90-3928] p 67 A91-12444 rotor-blade vibration in the thrust plane deficiencies and potential improvements utilizing Experimental/theoretical investigation ol the sound field p36 A91-11725 TSO-C91aELTs of an isolated propeller, including angle of incidence A new approach to the flight control system (NASA-CR-4330] p 28 N91-10964 effects reconfiguration following a battle damage and/or generic How to fly windshear p 41 N91 -10974 (AIAA PAPER 90-39521 p 69 A91-12468 failure on a control surface p 50 N91-11023 AIRCRAFT STABILITY Procurement and testing of a 1/5 scale advanced AIRCRAFT NOISE Static and dynamic aeroelastic characterization of an counter rotating propfan model Influence of airfoil nose radius on sound generated by aerodynamically heated generic hypersonic aircraft [AIAA PAPER 90-3975] p 46 A91-12488 gust interactions configuration p 61 N91-10320 Progress in certifying F402-RR-408: The improved (AIAA PAPER 90-3912) p 66 A91-12428 AIRCRAFT STRUCTURES Pegasus engine for AV-8B and Harrier 2 plus Active control of interior noise in model aircraft fuselages Large-amplitude vibrations of free-free tapered beams (PNR-90719) p40 N91-10056 using piezoceramic actuators p57 A91-11199 Aero engine design factors for a low fuel price | AIAA PAPER 90-3922) p 67 A91-12438 Comparison of modal parameter estimation techniques scenario Recent advances in Active Noise Control on aircraft structural data p 57 A91-11219 IPNR-90681] p47 N91-10066 | AIAA PAPER 90-39241 p 67 A91-12440 Structure-borne noise transmission in the propfan test The evolution of the bypass engine Estimation ol the turbulent boundary layer pressure assessment aircraft [PNR-90707] p47 N9M0068 wavenumber-frequency spectrum using a fixed probe (AIAA PAPER 90-3966] p 71 A91-12480 Applications of thermally sprayed coating systems in pair Seat dynamic performance standards for a range of aero engines (AIAA PAPER 90-3926] p 67 A91-12442 sizes (PNR-90750] p48 N91-10072 Aeroacoustic effects of reduced aft tip speed at constant (DOT/FAA/CT-TN90/23] p 26 N91-10028 Casting alloys for the jet age thrust for a model counterrotation turboprop at takeoff Introduction: Needs and approaches to reliability and [PNR-90723] p56 N91-10168 conditions quality assurance in design and manufacture Total quality management at Rolls-Royce PLC | AIAA PAPER 90-3933] p 68 A91-12449 (PNR-90683) p60 N91-10297 (PNR-90759] p60 N91-10298 Near-field noise of a single rotation propfan at an angle Repeated buckling of composite shear panels Fault monitoring p 44 N91-10950 of attack p60 N91-10303 Fault diagnosis p 26 N91-10951 1 AIM PAPER 90-39531 p 70 A91-12469 Computation ot maximum gust loads in nonlinear aircraft Test launch for turboaircraft engine. Description of the The use of spatial coherence techniques for identifying using a new method based on the matched filter approach installation noise transmission paths on the MDC-UHB demonstrator and numerical optimization p 60 N91-10317 (ILA-87-A-02J p48 N91-11018 aircraft Fault diagnosis p 26 N91-10951 Test cases for computation of internal flows in aero (AIAA PAPER 90-3968] p 71 A91-12482 AIRCRAFT WAKES engine components An experimental technique of separating airborne and Application of a state-space wake model to elastic blade |AGARD-AR-275| p 49 N91-11022 structure-borne noise using wavenumber-frequency flapping in hover p 13 N91-10006 The role of process modelling in manufacture and spectrum AIRFOIL OSCILLATIONS design (AIAA PAPER 90-3969] p 71 A91-12483 Aeroelastic analysis of wings using the Euler equations IPNR-90702] p65 N91-11416 The identification of helicopter noise using a neural with a deforming mesh AIRCRAFT EQUIPMENT networK (NASA-TM-1027331 p 15 N91-10020 The actuator for the low-noise STOL test plane flight (AIAA PAPER 90-3973] p 72 A91-12486 Calculation of the pressure distribution on an oscillating control system and its development test Identification of aerospace acoustic sources using airfoil in incompressible flow considering nonlinear [NAL-TM-574I p 37 N91-10038 sparse distributed associative memory effects p25 N91-10926 AIRCRAFT FUELS (AIAA PAPER 90-3992] p 73. A91-12505 AIRFOIL PROFILES Tests of the general fire suppression concentrate The measurement of sonic boom waveforms and The effects of aerofoil profile on wing buffet at low Pyrocap B-136 propagation characteristics - Techniques and challenges speeds p2 A91-11151 [DOT/FAA/CT-TN90/21] p 26 N91-10029 (AIAA PAPER 90-4004] p 74 A91-12517 Noise mechanisms of transonic vortex airfoil AIRCRAFT GUIDANCE Noise characteristics of the Japan's experimental interaction Time-based aircraft/ATC operations study powered lift STOL aircraft | AIAA PAPER 90-39721 p 71 A91-12485 p29 N91-10959 (AIAA PAPER 90-4014 ] p 75 A91 -12526 Forcing level effect ol internal acoustic excitation on The 4-D control of current air carriers in the present Installation effects on counter rotating propeller noise the improvement of airfoil performance environment: Objectives, status, and plans | AIAA PAPER 90-4023] p 75 A91-12534 (AIAA PAPER 90-4010] p 74 A91-12522 p31 N91-10990 Aircraft en route noise annoyance Subsonic airfoil design p9 A91-12756 The control of inbound flights p 32 N91-10992 (AIAA PAPER 90-4028] p 63 A91-12537 Elements of airfoil design methodology Guidance concepts for time-based flight operations Sound insulation of dwellings around airports - Objective p9 A91-12757 p32 N91-10993 and subjective measures and findings Inverse airfoil design - A classical approach updated Air traffic management and aircraft guidance in a zone [AIAA PAPER 90-4029] p 63 A91-12538 for transonic applications p 10 A91-12758 of convergence p 33 N91-10998 Re-engining: Real stage 3 compliance plus other Innovation with computational aerodynamics - The Ground-based 4-D guidance of flights in strong wind benefits divergent trailing-edge airfoil p 10 A91-12759 p33 N91-10999 IPNR-90755) p48 N91-10075 Gust response for flat-plate airfoils and the Kutta A piloted simulator evaluation of a ground-based 4-D Do we really need 57 ways of rating aircraft noise condition p 12 A91-12882 descent advisor algorithm p 33 N91-11000 [PNR-90720] p76 N91-10704 Optimum hypersonic airfoil with power law shock The air traffic controller facing automation: Conflict or Aircraft interior noise reduction by alternate resonance waves cooperation p 34 N91-11001 tuning (DE90-014903) p 13 N91-10008 AIRCRAFT INSTRUMENTS (NASA-CR-186879] p 76 N91-11488 Modeling blade/vortex interactions Time series and correlation of pulsations observed AIRCRAFT PARTS simultaneously by two aircraft p 63 A91-11072 Detection of concealed corrosion damage in aircraft IISL-R-107/69) pU N91-10016 Automatic determination of fault effects on aircraft structures using the eddy current method Determination of the pressure drag of airfoils by functionality p58 A91-11974 integration of surface pressures [NASA-CR-1813521 p 37 N91-10039 Fault recovery recommendation p 27 N91-10952 INASA-TM-102722] p 50 N91-10078 Boeing flight deck design philosophy AIRCRAFT PERFORMANCE Numerical calculations for flows past an unconventional p40 N91-10937 Integration of aircraft capability in air traffic handling airfoil p24 N91-10916 Flight simulator evaluation test of multi-functional display simulations p 35 N91-11007 Temporal-adaptive Euler/Navier-Stokes algorithm for unit AIRCRAFT PILOTS unsteady aerodynamic analysts of airfoils using [NAL-TM-596] p 53 N91-11026 Pilot modelling techniques for the analysis of aircraft unstructured dynamic meshes AIRCRAFT LANDING linear dynamic behaviour p 49 A91-11158 (NASA-TM-102734] p 24 N91-10919 Four dimensional navigation in air traffic with 4-D AIRCRAFT POWER SUPPLIES The calculation of unsteady compressible flow about navigation aircraft P 31 N91-10991 Diagnostics of aviation electric machines — Russian oscillating airfoil profiles using the Euler upwind method The control of inbound flights p 32 N91-10992 book p37 A91-12919 p 25 N91-10921 Expert systems for the generation ol thermal area arrival Practical flight paths for microwave-powered airplanes AIRFOILS paths for civil transport p 32 N91-10995 [NAL-TR-1052T] p 40 N91-10054 Calculation of boundary-layer flows on low Reynolds Ground-based 4-D guidance of flights in strong wind AIRCRAFT RELIABILITY number and transonic airfoils p5 A91-11840 p33 N91-10999 Configuration control and airworthiness management An approximate calculating method of AIRCRAFT MAINTENANCE p77 A91-12233 supersonic/hypersonic unsteady aerodynamic forces of Structural risk assessment and aircraft fleet AIRCRAFT SAFETY airfoils p5 A91-11845 maintenance p 61 N91-10321 Development and application of linear and nonlinear Acoustic radiation from lifting airfoils in compressible AIRCRAFT MANEUVERS methods for interpretation of lightning strikes to in-flight X-31 will turn on a dime p 36 A91-11863 aircraft subsonic flow [AIAA PAPER 90-3911] p 66 A91-12427 Sonic boom focal zones due to tactical aircraft [NASA-CR-3974] p 64 N91-10548 maneuvers Aviation Safety/Automation Program Conference Influence of airfoil nose radius on sound generated by (AIAA PAPER 90-4003) p 74 A91-12516 (NASA-CP-3090] p26 N91-10936 gust interactions Sonic boom environment under a supersonic military Boeing flight deck design philosophy [AIAA PAPER 90-3912] p 66 A91-12428 operating area p40 N91-10937 Effect of acoustic excitation on stalled flows over an (AIAA PAPER 90-40321 p 63 A91-12541 Aviation safety/automation program overview airfoil Comparison of a mathematical one-point model and a p26 N91-10941 [AIAAPAPER90-4009] p7 A91-12521 multi-point model of aircraft motion in moving air Summary of the industry/NASA/FAA workshop on Vertex-based finite-volume solution of the p 41 N91-10969 philosophy of automation: Promises and realities two-dimensional Navier-Stokes equations Aircraft flight in wind-shear p 41 N91-10973 p44 N91-10942 p59 A91-12900

A-4 SUBJECT INDEX BLADE SLAP NOISE

Numerical computation of viscous flow about ALUMINUM ALLOYS AUGMENTATION unconventional airfoil shapes A process model for age hardening of aluminium alloys. Constrained optimization approach to feedback control INASA-CR-187343] p 15 N91-10019 1-The model p 56 A91-11883 of state-augmented systems p 66 N91-11433 Heat transfer in aero engine gas turbines, part 1 Short crack behaviour in AI-LJ alloy 2090 AUTOMATED EN ROUTE ATC (PNR-90754-PT-1I p 48 N9M0074 p62 N9M1243 A description and evaluation of TIMER: A time-based Calculation of the rotor induced download on airfoils Short crack growth under realistic flight loading: Model terminal flow-control concept p 32 N91-10996 p 19 N91-10864 predictions and experimental results for Al 2024 and AI-LJ Use of 4-D RNAV in time-based en route arrival 2090 p62 N91-11246 Progress toward the development of an airfoil icing metering p33 N91-10997 The growth of short cracks in 4340 steel and analysis capability p 19 N91 -10866 AUTOMATED PILOT ADVISORY SYSTEM aluminum-lithium 2090 p 62 N91-11247 Prediction of turbine rotor-stator interaction using A piloted simulator evaluation of a ground-based 4-D ANGLE OF ATTACK Navier-Stokes methods p 20 N91-10881 descent advisor algorithm p 33 N91-11000 A three-dimensional boundary layer on bodies with a AUTOMATIC CONTROL Nonoveriapping composite meshes for multi-element slight cross-sectional asymmetry at small angles of Automatic determination of fault effects on aircraft air-foils p23 N91-10908 attack p5 A91-11909 functionality A numerical study of the effects of wind tunnel wall Near-field noise of a single rotation propfan at an angle [NASA-CR-181352] p 37 N91-10039 proximity on an airfoil model of attack | NASA-CR-187322] p 25 N91-10934 [AIAA PAPER 90-3953] p 70 A91-12469 Automated design of controlled diffusion blades Aerodynamic design optimization using computational Prediction of the noise from a propeller at angle of p21 N91-10883 fluid dynamics p 43 N91-11013 attack Cockpit avionics integration and automation Parallelization on a multi-processor system of a solving (AIAA PAPER 90-39541 p 70 A91-12470 p 44 N91-10938 method for the unsteady Navier-Stokes equations at high Theory of slightly blunted axisymmetric power-law Aviation safety/automation program overview Reynolds numbers bodies at small angle of attack in hypersonic flow p26 N91-10941 (ESA-TT-1116] p62 N91-11197 p8 A91-12559 Summary of the industry/NASA/FAA workshop on AIRFRAMES Localized linearization method for wings at high angle philosophy of automation: Promises and realities Rotor systems research aircraft risk-reduction shake of attack p 12 A91-12896 p 44 N91-10942 test Flight characteristics of a modified Schweizer SGS1-36 ATC automation concepts p 29 N91-10957 sailplane at low and very high angles of attack (NASA-TM-4186] p 38 N91-10045 Time-based operations in an advanced ATC [NASA-TP-3022] p 50 N91-10079 Coupled rotor/airframe vibration analysis environment p 29 N91-10958 Calculation of aerodynamic characteristics of airplane p43 N91-11012 The air traffic controller facing automation: Conflict or configurations at high angle of attack in steady and AIRLINE OPERATIONS cooperation p 34 N91-11001 unsteady flow p 42 N91-11009 British Airways operational experience with Concorde AUTOMATIC FLIGHT CONTROL Prediction of the noise from a propeller at angle of p26 A91-10960 Concorde - 1958-1975 p 35 A91-10956 attack Extensive MD-11 automation assists pilots, cuts Aircraft trajectory: Prediction and control in the air [ NASA-TM-103627] p 77 N91-11495 workload p 37 A91-12165 transport flight management computer systems ANNEALING AUTOMATIC WEATHER STATIONS p41 N91-10976 Thermal barrier coatings - Microstructural investigation FAA air traffic operational evaluation of Automated Optimum on-line handling of air traffic over Western after annealing Surface Observing System (ASOS) Europe p 30 N91-10982 [ONERA, TP NO. 1990-62] p 55 A91-11751 [DOT/FAA/CT-TN90/

A-5 BLADE-VORTEX INTERACTION SUBJECTINDEX

BLADE-VORTEX INTERACTION BOUNDARY LAYER SEPARATION Optimization of the arrangement of the front and rear Noise mechanisms of transonic vortex airfoil Control of vortical separation on a circular cone blade rows of a tandem blade cascade interaction p3 A91-11162' p46 A91-11349 | AIAA PAPER 90-39721 p 71 A91-12485 Fluctuations of a shock wave generated by boundary An efficient method for solving transonic flow about Interaction between rotors of a counter rotating layer separation p6 A91-12019 plane cascades with a large nosing p 4 A91-11839 propeller Forcing level effect of internal acoustic excitation on A three-dimensional incompressible Euler flow solution | AIAA PAPER 90-3976] p7 A91-12489 the improvement of airfoil performance in turbomachinery p5 A91-11841 Vortex structure of wakes behind an advanced propeller [AIAA PAPER 90-4010] p 74 A91-12522 .CASTING at takeoff load conditions CFO for applications to aircraft aeroelasticity Casting alloys for the jet age | AIAA PAPER 90-3978] p 72 A91-12491 p 17 N91-10855 [PNR-90723] p 56 N91-10168 Influence of unsteady aerodynamics on rotor blade BOUNDARY LAYER STABILITY CAVITIES aeroelastic stability and response p 37 A91-12894 A study of cylindrical interaction of turbulent boundary Suppression of flow-induced pressure oscillations in Modeling blade/vortex interactions layer/shock with swept compression corners cavities (ISL-R-107/89J p 14 N91-10016 p4 A91-11836 [AIAA PAPER 90-4018] p 8 A91-12530 The aerodynamic effects of nozzle guide vane shock Transition control of instability waves .over a flexible CENTRIFUGAL COMPRESSORS wave and wake passing on a transonic turbine rotor surface in the presence of an acoustic field Detailed measurements of the flow field at the outlet p24 N91-10915 [AIAA PAPER 90-4008] p 74 A91-12520 of a backswept transonic centrifugal impeller equipped with The calculation o! rotor/fuselage interaction for a vaned diffuser Experimental study of instability modes in a two-dimensional bodies [ONERA.TP NO. 1990-101] p4 A91-11777 three-dimensional boundary layer p 59 A91 -12888 [NASA-TM-102855) p 25 N91-10933 Vortex instabilities in 3D boundary layers: The CENTRIFUGAL PUMPS BLASIUS FLOW relationship between Goertler and crossflow vortices Experiments on the aerodynamic noise sources in Application of the vortex cloud method to cascades [NASA-CR-187456] p 15 N91-10022 centrifugal turbomachinery p3 A91-11347 BOUNDARY LAYER TRANSITION [AIAA PAPER 90-3948] p 69 A91-12464 BLOWING An experimental study of the laminar-turbulent transition CEPSTRAL ANALYSIS Control of vortical separation on a circular cone behind three-dimensional roughness in a boundary layer Removing spurious reflections from CFD solutions by p3 A91-11162 using the Complex Cepstrum on a sharp cone p6 A91-12014 Controlled vortical flow on delta wings through unsteady Shock wave formation during interaction with a weak I AIAA PAPER 90-3947] p 69 A91-12463 leading edge blowing p 43 N91 -11011 discontinuity at the boundary of a local subsonic region CERAMIC COATINGS BLUFF BODIES p6 A91-12017 Pyrometry for turbine blade development Application of the vortex cloud method to cascades Transition control of instability waves over a flexible p57 A91-10336 p3 A91-11347 CH-47 HELICOPTER surface in the presence of an acoustic field BLUNT BODIES [AIAA PAPER 90-4008] p 74 A91-12520 Application of flight path reconstruction algorithms for A study of implicit space-marching method for the Experimental study of instability modes in a flight data of helicopter supersonic viscous flow over the blunt cone tNAL-TM-582] p 28 N91-10031 three-dimensional boundary layer p 59 A91-12888 p4 A91-11831 CHROMIUM ALLOYS BOWS Aerodynamic heating in the interaction regions of shock The sonic boom of an oblique flying wing Influence of chromium and molybdenum on the structural waves and turbulent boundary layers induced by [AIM PAPER 90-4002] p 74 A91-12515 stability of a high strength damage tolerant P/M nickel sweptback blunt fins p6 A91-12226 based alloy for turbine disks BRANCHING (MATHEMATICS) BODY-WING CONFIGURATIONS Bifurcation analysis of axial flow compressor stability [ONERA, TP NO. 1990-100) p 55 A91-11776 Computational aerodynamic simulation experience p44 A91-10245 CIRCULAR CONES pll A91-12771 BRISTOL-SIDDELEY BS 53 ENGINE Control of vortical separation on a circular cone A contribution to the numerical solution of transonic flow Progress in certifying F402-RR-408: The improved p3 A91-11162 around a delta wing by solving Navier-Stokes equations Pegasus engine for AV-8B and Harrier 2 plus CIRCULAR CYLINDERS [DLR-FB-90-13] p 16 N91-10026 Wind tunnel investigations of the appearance of shocks [PNR-90719] p40 N91-10056 Recent advances in Runge-Kutta schemes for solving Technology update of early gas turbine designs in the windward region of bodies with circular cross section 3-D Navier-Stokes equations p 17 N91-10851 (PNR-90710) p 48 N91-10070 at angle of attack BOEING 737 AIRCRAFT [DLR-FB-90-15] p 16 N91-10027 BRISTOL-SIDDELEY OLYMPUS 593 ENGINE NASA transport systems research vehicle B-737 data The Rolls Royce/SNECMA Olympus 593 engine CITIES Sound insulation of dwellings around airports - Objective link system and display formats operational experience and the lessons learned [NASA-TM-102717] . p 44 N91-10058 p45 A91-10958 and subjective measures and findings BOEING 757 AIRCRAFT BUCKLING [AIAA PAPER 90-4029] p 63 A91-12538 Generation of a buoyant plume of artificial smoke for CIVIL AVIATION Research in Structures. Structural Dynamics and airplane tests Materials, 1990 DOD responsibilities on Federal aviation and national [DOT/FAA/CT-90/9] p 43 N91-11015 [NASA-CP-3064] p 60 N91-10301 airspace system matters BOLZA PROBLEMS Repeated buckling of composite shear panels [PB90-21B827] p2 N91-10001 National airspace system: In-flight assistance Optimal trajectories of aircraft and spacecraft p60 N91-10303 p 29 N91-10968 BUFFETING operational concept BOMBER AIRCRAFT [PB90-233115] p28 N91-10032 The effects of aerofoil profile on wing buffet at low Design technologies utilized in the development of the speeds p2 A91-11151 A quarter of a century of aeroelastic cooperation between research and industry (a review). Part 2: Transport B-2 flight control system Transonic buffet on a supercritical aerofoil (AIAA PAPER 90-3254] p 50 A91-12928 airplanes and other civil applications p 40 N91 -10932 p2 A91-11157 The use of downlinked measurements to track civil The design approach used in the synthesis of the B-2 Computation of maximum gust loads in nonlinear aircraft lateral-directional control laws using a new method based on the matched filter approach aircraft p 34 N91-11004 [AIAA PAPER 90-3255] p 50 A91-12929 and numerical optimization p 60 N91-10317 CLOSURE LAW BOND GRAPHS BUOYANCY Numerical computation of viscous flow about Automatic determination of fault effects on aircraft Generation of a buoyant plume of artificial smoke for unconventional airfoil shapes [NASA-CR-187343] p 15 N91-10019 functionality airplane tests [NASA-CR-181352] p 37 N91-10039 [DOT/FAA/CT-90/9] p 43 N91-11015 COANDA EFFECT Controlling plume deflection by acoustic excitation - An BOUNDARY ELEMENT METHOD BYPASS RATIO experimental demonstration Boundary element analysis of sound scattered by a The evolution of the bypass engine moving surface [PNR-90707] p47 N91-10068 [AIAA PAPER 90-4006] 'p 74 A91-12519 [AIAA PAPER 90-3944] p 69 A91-12460 Design/development issues for high bypass ratio fans COCKPIT SIMULATORS Localized linearization method for wings at high angle [PNR-90758] p48 N91-10076 Flight simulator evaluation test of multi-functional display of attack p 12 A91-12896 unit BOUNDARY LAYER CONTROL [NAL-TM-596] p 53 N9M1026 Control of vortical separation on a circular cone COCKPITS p3 A91-11162 Aviation Safety/Automation Program Conference BOUNDARY LAYER EQUATIONS CALIBRATING [NASA-CP-3090] p 26 N91-10936 Computational aerodynamic simulation experience Rotor systems research aircraft risk-reduction shake Cockpit avionics integration and automation p11 A91-12771 test p44 N91 -10938 BOUNDARY LAYER FLOW [NASA-TM-4186] p 38 N91-10045 Douglas flight deck design philosophy Transonic buffet on a supercritical aerofoil CANARD CONFIGURATIONS p40 N91-10939 p2 A91-11157 Vortex development on cruciform canard configurations Assessing information transfer in full mission flight Calculation of boundary-layer flows .on low Reynolds at supersonic speeds p5 A91 -11843 simulations p 26 N91-10946 number and transonic airfoils p 5 A91 -11840 Grid generation and inviscid flow computation about Overview of error-tolerant cockpit research Viscous drag reduction in boundary layers — Book aircraft geometries p 18 N91-10857 p40 N91 -10949 p 58 A91-12688 Application of dynamical systems theory to nonlinear A function-based approach to cockpit procedure aids Determination of the pressure drag of airfoils by aircraft dynamics p 43 N91-11014 p 27 N91-10953 integration of surface pressures CARBIDES Terminal weather information management INASA-TM-102722) p 50 N91-10078 The role of primary carbides in fatigue crack propagation p64 N91-10960 Numerical investigations in three-dimensional internal in aeroengine bearing steels p 55 A91-11806 Information management p 27 N91-10961 flows CASCADE FLOW Voice communications in the cockpit noise environment: [NASA-CR-186958] p 52 N91-10083 Oscillating cascade aerodynamics by an experimental The role of active noise reduction p 61 N91-11140 Experimental investigation of the mechanisms influence coefficient technique p2 A91 -10339 COGNITION underlying vortex kinematics in unsteady separated Application of the vortex cloud method to cascades Graphical interfaces for cooperative planning systems flows p 23 N91-10907 p3 A91-11347 p27 N91-10956

A-6 SUBJECTINDEX COMPUTATIONAL GRIDS

COHERENT ACOUSTIC RADIATION COMPUTATIONAL CHEMISTRY Application of CFD to sonic boom near and mid flow-field The use of spatial coherence techniques for identifying Computational Fluid Dynamics Program at NASA Ames prediction noise transmission paths on the MOC-UHB demonstrator Research Center p 16 N91 -10840 [NASA-TM-102867] p 14 N91-10015 aircraft COMPUTATIONAL FLUID DYNAMICS Aeroelastic analysis of wings using the Euler equations [AIAA PAPER 90-3968] p 71 A91-12482 Modes of oscillation in a nonreacting ramjet combustor with a deforming mesh COMBUSTIBLE FLOW now p 2 A91-10330 [NASA-TM-102733] p 15 N91-10020 Numerical simulations ol oscillatory cold flows in an Stator/rotor interaction in a transonic turbine • Three-dimensional viscous/inviscid coupling in subsonic axisymmetric ramjet combustor p2 A91-10329 p 2 A91-10340 now COMBUSTION Mixed structured-unstructured meshes for aerodynamic [REPT-B-24] p 15 N91-10023 Airplane systems modifications for improved cabin flow simulation p 65 A91 -11154 Numerical investigations in three-dimensional internal smoke evacuation Solution of the Euler equations on unstructured grids flows (DOT/FAA/CT-TN90/24) p 39 N91-10052 for two-dimensional compressible now p3 A91-11160 [NASA-CR-186958) p 52 N91-10083 COMBUSTION CHAMBERS L.D.V. applied to measurements between two discs in NASA Computational Fluid Dynamics Conference. Numerical simulations of oscillatory cold flows in an high speed rotation Volume 1: Sessions 1-6 axisymmetric ramjet combustor p2 A91-10329 [ONERA. TP NO. 1990-94] p 58 A91-11773 [ NASA-CP-10038- VOL-1) p 16 N91 -10839 Modes of oscillation in a nonreacting ramjet combustor A three-dimensional incompressible Euler flow solution Computational Fluid Dynamics Program at NASA Ames flow p2 A91-10330 . in turbomachinery p5 A91-11841 Research Center p 16 N91 -10840 Three-dimensional combustor performance validation Low Mach number Euler computations Computational fluid dynamics research and applications with high-density fuels p 55 A91-10345 p5 A91-11900 at NASA Langley Research Center p 17 N91-10841 Numerical simulation and active control of combustion A three-dimensional boundary layer on bodies with a CFD for applications to aircraft aeroelasticity instability in a ramjet combustor slight cross-sectional asymmetry at small angles of p 17 ' N91-10855 [AIAA PAPER 90-3930) p 46 A91-12446 attack p5 A91-11909 Grid generation and inviscid flow computation about COMBUSTION EFFICIENCY Application of computational methods in aeroacoustics aircraft geometries p 18 N91 -10857 Three-dimensional combustor performance validation (AIAA PAPER 90-3917] p 67 A91-12433 A zonal Navier-Stokes methodology for flow simulation with high-density fuels p 55 A91-10345 Numerical simulation of vortex-wedge interaction about a complete aircraft . p 18 N91-10858 COMBUSTION PHYSICS [AIAA PAPER 90-3918] p 6 A91-12434 Numerical simulation of F-18 fuselage forebody flows Thermoacoustics of unsteady combustion Numerical simulation of acoustic diffraction of at high angles of attack p 18 N91 -10859 [AIAA PAPER 90-3928] p 67 A91-12444 two-dimensional rigid bodies in arbitrary flows Navier-Stokes solutions about the F/A-18 forebody-LEX COMBUSTION STABILITY [AIAA PAPER 90-3920] p 67 A91-12436 configuration p 18 N91-10860 Numerical simulation and active control of combustion Removing spurious reflections from CFD solutions by Navier-Stokes solutions for flows related to store instability in a ramjet combustor using the Complex Cepstrum separation p 18 N91-10861 [AIAA PAPER 90-3930] p 46 A91-12446 [AIAA PAPER 90-3947] p 69 A91-12463 TranAir Recent advances and applications The instability of combustion in propulsion engines Time-dependent jet now and noise computations p 19 N91-10862 p56 N9I-1014I [AIAA PAPER 90-3961 ] p 70 A91-12475 Numerical simulation of rotorcraft p 19 N91-10863 COMMERCIAL AIRCRAFT Application of CFD to sonic boom near and mid flow-field Three-dimensional viscous drag prediction for rotor The application of commercial airplane avionics prediction blades p 19 N91-10865 techniques to advanced space transportation [AIAA PAPER 90-3999] p 7 A91-12512 Progress toward the development of an airfoil icing [AIAA PAPER 90-3722] p1 A9M0114 An Euler code prediction of near field to midfield sonic analysis capability p 19 N91-10866 Assessing the market for high speed air travel in the boom pressure signatures The breakup of trailing-line vortices 21st century p 77 A91-10962 [AIAA PAPER 90-4000] p7 A91-12513 p20 N91-10867 Computational aerodynamics applied to general Numerical simulation of supersonic mixing layer using NASA Computational Fluid Dynamics Conference. aviation/business aircraft p 11 A91-12767 high resolution scheme Volume 2: Sessions 7-12 Energy efficiency improvement potential of commercial [AIAA PAPER 90-4025] p8 A91-12535 [NASA-CP-10038-VOL-2] p 20 N91-10868 aircraft to 2010 Application of CFD to reduction of skin-friction drag Application of CFD codes for the simulation of scramjet [DE90-014767] p 39 N91-10046 p8 A91-12692 combustor flowflelds p 20 N91-10873 Commercial aircraft and the environment Applied computational aerodynamics — Book Prediction of turbine rotor-stator interaction using [PNR-90687] p64 N91-11307 p9 A91-12751 Navier-Stokes methods p 20 N91-10881 COMPONENT RELIABILITY Linear potential schemes — for incompressible inviscid CFD analysis for high speed inlets p 21 N91-10888 Drive system life and reliability p 38 N91-10044 flow p9 A91-12753 The use of a Navier-Stokes code in the wing design COMPOSITE MATERIALS Full-potential, Euler, and Navier-Stokes schemes process p 21 N91-10889 An accurate acoustic emission location method adapted p59 A91-12754 An embedded grid formulation applied to delta wings for composite materials p 57 A91-11027 Grid-generation methodology in applied aerodynamics p 22 N91-10891 Multi industry application of advanced materials p9 A91-12755 ,. Conical Euler simulation and active suppression of delta [PNR-90764] p 56 N91-10139 Innovation with computational aerodynamics - The wing rocking motion COMPOSITE STRUCTURES divergent trailing-edge airfoil p 10 A91-12759 [NASA-TM-102683] p 22 N91-10904 Noise transmission characteristics of a large scale Euler and potential computational results for selected Nonovertapping composite meshes for multi-element composite fuselage model aerodynamic configurations p 10 A91-12760 air-foils p23 N91 -10908 [AIAA PAPER 90-3965] p 71 A91-12479 Computational aerodynamics applied to high-lift Implicit flux-split Euler schemes for unsteady Research in Structures, Structural Dynamics and systems p 10 A91-12761 aerodynamic analysis involving unstructured dynamic Materials, 1990 Development of high-lift wing modifications for an meshes [NASA-CP-3064] p 60 N91-10301 advanced capability EA-6B aircraft p 10 A91-12762 [NASA-TM-102732] p 24 N91-10918 Repeated buckling of composite shear panels Computational analysis of rotor-stator interaction in The calculation of unsteady compressible flow about p60 N91-10303 turbomachinery using zonal techniques oscillating airfoil profiles using the Euler upwind method COMPRESSIBLE FLOW p 10 A91-12764 p25 N91 -10921 Practical developments in holographic interferometry CFD applications to complex configurations - A survey A numerical study of the effects of wind tunnel wall p57 A91-11152 p11 A91-12766 proximity on an airfoil model Solution of the Euler equations on unstructured grids Computational aerodynamics applied to general [NASA-CR-187322] p 25 N91-10934 for two-dimensional compressible flow p 3 A91-11160 aviation/business aircraft p11 A91-12767 Aerodynamic design optimization using computational Prediction of turbulence generated random vibrational Application of computational fluid dynamic methods to fluid dynamics . p 43 N91-11013 response of turbomachinery blading p 46 A91-11348 the component aerodynamic design of the V-22 Osprey Application of. computational fluid dynamics to Acoustic radiation from lifting airfoils in compressible tilt rotor vehicle pit A91-12768 three-dimensional bodies in hypersonic now subsonic flow Aerodynamic analysis using Euler equations - p62 N91-11174 [AIAA PAPER 90-3911] p 66 A91-12427 Capabilities and limitations pli A91-12769 COMPUTATIONAL GEOMETRY . Noise mechanisms of transonic vortex airfoil Navier-Stokes computations about complex Future directions for applied computational fluid interaction configurations including a complete F-16 aircraft dynamics p 59 A91-12775 [AIAA PAPER 90-3972] p 71 A91-12485 p 12 A91-12772 COMPUTATIONAL GRIDS Turbulent flow calculations using unstructured and Computational fluid dynamics design applications at Mixed structured-unstructured meshes for aerodynamic adaptive meshes supersonic/hypersonic speeds p 12 A91-12773 now simulation p 65 A91-11154 [NASA-CR-182102] p 14 N91-10010 Future directions for applied computational fluid Turbulent flow calculations using unstructured and Numerical calculations for flows past an unconventional dynamics p 59 A91-12775 adaptive meshes airfoil p24 N91-10916 Shock capturing using a pressure-correction method [NASA-CR:182102J p 14 N91-10010 The calculation of unsteady compressible flow about p59 A91-12887 Application of CFD to sonic boom near and mid now-fleld oscillating airfoil profiles using the Euler upwind method Localized linearization method for wings at high angle prediction p25 N91-10921 of attack p 12 A91-12896 [NASA-TM-102867] p 14 N91-10015 COMPRESSOR BLADES Euler solutions for delta wings p 12 A91-12899 Numerical investigations in three-dimensional internal Automated design of controlled diffusion blades flows Vertex-based finite-volume solution of the p21 N91-10883 [NASA-CR-186958] p 52 N91-10083 COMPUTATION two-dimensional Navier-Stokes equations NASA Computational Fluid Dynamics Conference. p 59 A91-12900 Rotor loads computation using singularity methods and Volume 1: Sessions 1-6 application to the noise prediction Transonic computations on a natural grid [NASA-CP-10038- VOL-1) p 16 N91-10839 [ISL-PU-301/90] p 15 N91-10018 p 13 A91-12904 Computational fluid dynamics research and applications Aircraft trajectories: Computation, prediction, control, Application of a state-space wake model to elastic blade at NASA Langley Research Center p 17 N91-10841 volume 1. Part 1: Fundamentals. Part 2: Right in critical napping in hover p 13 N91-10006 Application of unstructured grid methods to steady and atmospheric conditions. Part 3: Impact of new on-board Euler and potential experiment/CFD correlations for a unsteady aerodynamic problems p 17 N91-10856 technologies on aircraft operation transport and two delta-wing configurations Grid generation and inviscid flow computation about [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 | NASA-TM-102208] p 14 N91-10014 aircraft geometries p 18 N91:10857

A-7 COMPUTER AIDED DESIGN SUBJECT INDEX

Numerical simulation of F-18 fuselage forebody flows Numerical calculations for flows past an unconventional NASA Computational Fluid Dynamics Conference. at high angles of attack p 18 N91-10859 airfoil P 24 N91-10916 Volume 1: Sessions 1 -6 Navier-Stokes solutions about the Ft A-18 forebody-LEX Test cases for computation of internal flows in aero [NASA-CP-10038-VOL-1] p 16 N91-10839 configuration p 18 N91-10860 engine components NASA Computational Fluid Dynamics Conference. Navier-Stokes solutions for flows related to store [AGARD-AR-275] p 49 N91-11022 Volume 2: Sessions 7-12 separation p 18 N91-10861 COMPUTER SYSTEMS PERFORMANCE [NASA-CP-10038-VOL-2] p 20 N91-10868 TranAir: Recent advances and applications The full-body ground vibration tests using the low-noise Aviation Safety/ Automation Program Conference p 19 N91-10862 STOL test plane [NASA-CP-3090) p 26 N91-10936 Numerical simulation of rotorcraft p 19 N91 -10863 [NAL-TM-576] p 50 N91-10077 CONICAL FLOW Calculation of the rotor induced download on airfoils Parallelized reliability estimation of reconfigurable Conical Euler simulation and active suppression of delta p 19 N91-10864 computer networks wing rocking motion Prediction of turbine rotor-stator interaction using [NASA-CR-182101] p 65 N91-11430 [NASA-TM-102683] p 22 N91-10904 Navier-Stokes methods p 20 N91-10881 COMPUTER SYSTEMS PROGRAMS CONTOURS Simulation of powered-lift flows p 21 N91-10886 Simulation of automated approach procedures Prediction of effects of wing contour modifications on An embedded grid formulation applied to delta wings considering dynamic flight operations low-speed maximum lift and transonic performance for the p22 N91-10891 p35 N91-11008 EA-6B aircraft Unstructured mesh solution of the Euler and Experiences in the use of ABAQUS for creep analysis [NASA-TP-3046] p 22 N91-10902 Navier-Stokes equations p 22 N91 -10892 [PNR-90705] p63 N91-11266 CONTRAROTATING PROPELLERS Three dimensional unstructured grids for the solution COMPUTER VISION Installation effects on counter rotating propeller noise of the Euler equations p 22 N91-10893 Function and performance of visual simulation unit of [AIAA PAPER 90-4023] p 75 A91-12534 Implicit flux-split Euler schemes for unsteady flight simulation test facility Aerodynamic interaction of counter rotating propellers aerodynamic analysis involving unstructured dynamic [NAL-TM-581] p 52 N91-10082 p23 N91-10910 meshes COMPUTERIZED SIMULATION CONTROL CONFIGURED VEHICLES [NASA-TM-102732] p 24 N91-10918 Computational technology for flight vehicles: Configuration control and airworthiness management Solution of the two-dimensional Euler equations by a Proceedings of the Symposium. Washington, DC, Nov. 5-7, p77 A91-12233 finite volume discretization on unstructured triangular 1990 p58 A91-11813 CONTROL SIMULATION meshes Numerical simulation of 3-D supersonic free shear Pilot modelling techniques for the analysis of aircraft [ESA-TT-1135] p66 N91-11473 layers linear dynamic behaviour p 49 A91-11158 COMPUTER AIDED DESIGN [AIAA PAPER 90-3958] p 7 A91-12472 A new approach to the flight control system Future directions for applied computational fluid Vortex structure of wakes behind an advanced propeller reconfiguration following a battle damage and/or generic dynamics p 59 A91-12775 at takeoff load conditions failure on a control surface p 50 N91 -11023 The role of process modelling in manufacture and [AIAA PAPER 90-3978] p 72 A91-12491 CONTROL STABILITY design On the prediction of far field computational Performance-robustness trade off of eigenstructure [PNR-90702] p65 N91-11416 aeroacoustics of advanced propellers assignment applied to rotorcraft p 49 A91 -11155 COMPUTER AIDED MANUFACTURING [AIAA PAPER 90-3996] p 73 A91-12509 H infinity-design and the improvement of helicopter The role of process modelling in manufacture and Aerodynamic analysis using Euler equations handling qualities p 51 N91-11024 design Capabilities and limitations p11 A91-12769 CONTROL SURFACES [PNR-90702] p65 N91-11416 Computational aerodynamic simulation experience Project HyBuJET COMPUTER GRAPHICS p11 A91-12771 [NASA-CR-187011] p 38 N91-10040 Graphical interfaces for cooperative planning systems Jets and lifting surfaces: Computer simulation Wall interference studies p 27 N91-10956 p 13 A91-12913 [PD-CF-9012] p59 N91-10232 The high-resolution graphic display: A possible Function and performance of visual simulation unit of Application of dynamical systems theory to nonlinear man/machine interface for a computer assisted ATC flight simulation test facility aircraft dynamics p 43 N91-11014 management system p 31 N91-10989 [NAL-TM-581] p 52 N91-10082 CONTROL SYSTEMS DESIGN COMPUTER NETWORKS Computational Fluid Dynamics Program at NASA Ames Performance-robustness trade off of eigenstructure The application of trajectory prediction algorithms for Research Center p 16 N91-10840 assignment applied to rotorcraft p 49 A91-11155 planning purposes in the Netherlands ATC-system A zonal Navier-Stokes methodology for flow simulation Design technologies utilized in the development of the p 65 N91-10986 about a complete aircraft p 18 N91-10858 8-2 flight control system Parallelized reliability estimation of reconfigurable Numerical simulation of F-18 fuselage forebody flows [AIAA PAPER 90-3254] p 50 A91-12928 computer networks at high angles of attack p 18 N91 -10859 The design approach used in the synthesis of the B-2 [NASA-CR-182101] p65 N91-11430 Numerical simulation of rotorcraft p 19 N91-10863 lateral-directional control laws COMPUTER PROGRAMS The breakup of trailing-line vortices [AIAA PAPER 90-3255] p 50 A91-12929 Application of LU-ADI algorithm in two-dimension p 20 N91-10867 Research in Structures, Structural Dynamics and transonic flow p5 A91-11848 Application of CFD codes for the simulation of scramjet Materials, 1990 Transonic flow analysis for rotors. Part 3: combustor flowfields p 20 N91-10873 [NASA-CP-3064] p60 N91-10301 Three-dimensional, quasUsteady, Euler calculation Guidance concepts for time-based flight operations Contributions to the improvement of flight safety in wind [NASA-TP-2375] p 13 N91-10007 p>32 N91-10993 shear Wake coupling to full potential rotor analysis code Integration of aircraft capability in air traffic handling [ESA-TT-1141] p28 N91-10965 [NASA-TM-102805] p 14 N91-10013 simulations p 35 N91-11007 A description and evaluation of TIMER: A time-based Application of CFD to sonic boom near and mid flow-field Simulation of automated approach procedures terminal flow-control concept p 32 N91-10996 prediction considering dynamic flight operations H infinity-design and the improvement of helicopter [NASA-TM-102867] p 14 N91-10015 p35 N91-11008 handling qualities p 51 N91-11024 Numerical computation of viscous flow about Aerodynamic design optimization using computational CONTROL THEORY unconventional airfoil shapes fluid dynamics p 43 N91-11013 A self-organizing stochastic control system adaptable [NASA-CR-187343] p 15 N9M0019 Flight simulation programs for space plane to changing perturbation characteristics Aeroelastic analysis of wings using the Euler equations [NAL-TM-594] p 55 N91-11035 p65 A91-11353 with a deforming mesh Application of computational fluid dynamics to The design approach used in the synthesis of the B-2 [NASA-TM-102733] p 15 N91-10020 three-dimensional bodies in hypersonic flow lateral-directional control laws Three-dimensional viscous/inviscid coupling in subsonic p62 N91-11174 [AIAA PAPER 90-3255] p 50 A91-12929 flow The role of process modelling in manufacture and Constrained optimization approach to feedback control [REPT-B-24] p15 N91-10023 design of state-augmented systems p 66 N91-11433 Calculation of three-dimensional viscous/inviscid [PNR-90702] p65 N91-11416 CONTROLLABILITY interaction in subsonic flow CONCORDE AIRCRAFT Pilot modelling techniques for the analysis of aircraft [REPT-B-25] p 16 N91-10024 All-electric flight control experiments and experiments linear dynamic behaviour p 49 A91-11158 Evaluation of the ZONA51D program with a sidestick on the Concorde p 49 A91-10955 Integration of aircraft capability in air traffic handling [REPT-B-28] p 16 N91-10025 Concorde - 1958-1975 p 35 A91-10956 simulations p 35 N91-11007 Wall interference studies Commercial supersonic operations - Thirteen years of H infinity-design and the improvement of helicopter [PD-CF-9012] p 59 N91-10232 experience with Concorde p 36 A91-10957 handling qualities p 51 N91-11024 Recent advances in Runge-Kutta schemes for solving The Rolls Royce/SNECMA Olympus 593 engine CONTROLLERS 3-D Navier-Stokes equations p 17 N91-10851 operational experience and the lessons learned 'Numerical simulation of hypersonic flow around a space TranAir: Recent advances and applications p45 A91-10958 plane. Part 3: Analysis of aerothermodynamic heating p 19 N91-10862 Twenty years of Concorde - The experience of Air [NAL-TR-1027T] p 14 N91-10011 Progress toward the development of an airfoil icing France p 25 A91-10959 Douglas flight deck design philosophy analysis capability p 19 N91-10866 British Always operational experience with Concorde p40 N91-10939 Application of CFD codes for the simulation of scramjet p26 A91-10960 Fault monitoring p 44 N91-10950 combustor flowfields p 20 N91-10873 CONFERENCES The use of a Navier-Stokes code in the wing design European Symposium on the Future of High Speed Air CONVERGENT NOZZLES process p 21 N91-10889 Transport, Strasbourg, France, Nov. 6-8, 1989, Flow and acoustic properties of low Reynolds number An embedded grid formulation applied to delta wings Proceedings p 1 A91-10951 underexpanded supersonic jets p 3 A91 -11198 p 22 N91-10891 Systems reliability assessment p 57 A91 -11201 CONVEXITY Three dimensional unstructured grids for the solution Computational technology for flight vehicles: Convex curvature concept of viscous drag reduction of the Euler equations p 22 N91-10893 Proceedings of the Symposium, Washington, DC, Nov. 5-7, p8 A91-12696 Prediction of effects of wing contour modifications on 1990 p58 A91-11813 CORNER FLOW low-speed maximum lift and transonic performance for the Research in Structures, Structural Dynamics and A study of cylindrical interaction of turbulent boundary EA-6B aircraft Materials. 1990 layer/shock with swept compression corners [NASA-TP-3046] p 22 N91-10902 [NASA-CP-3064] p 60 N91-10301 p4 A91-11836

A-8 SUBJECT INDEX DRAG REDUCTION

CORRELATION CYCLIC LOADS DESCENT TRAJECTORIES Euler and potential experiment/CFD correlations for a Repeated buckling of composite shear panels The 4-O descent trajectory generation techniques under transport and two delta-wing configurations p 60 N91-10303 realistic operating conditions p 32 N91-10994 (NASA-TM-1022081 p 14 N91-10014 A piloted simulator evaluation of a ground-based 4-D CORROSION TESTS descent advisor algorithm p 33 N91-11000 Detection of concealed corrosion damage in aircraft DESIGN ANALYSIS structures using the eddy current method Holographic interferometry for flow visualization studies p58 A91-11974 DAMAGE ASSESSMENT An accurate acoustic emission location method adapted in high speed fans p46 A91-11351 COST ANALYSIS for composite materials p 57 A91-11027 The design of two sonic boom wind tunnel models from Aero engine design factors for a low fuel price A new approach to the flight control system conceptual aircraft which cruise at Mach numbers of 2.0 scenario reconfiguration following a battle damage and/or generic and 3.0 [PNR-906811 p47 N91-10066 failure on a control surface p 50 N91-11023 [AIAA PAPER 90-4026] p 52 A91-12536 COUNTER ROTATION DATA BASE MANAGEMENT SYSTEMS Boeing flight deck design philosophy Procurement and testing of a 1/5 scale advanced The full-body ground vibration tests using the low-noise p40 N91-10937 counter rotating propfan model STOL test plane Douglas flight deck design philosophy [AIAA PAPER 90-39751 p 46 A91-12488 [NAL-TM-576] p 50 N91-10077 p40 N91-10939 Interaction between rotors of a counter rotating DATA BASES Aerodynamic design optimization using computational propeller Seat dynamic performance standards for a range of fluid dynamics p43 N91-11013 | AIAA PAPER 90-3976J p7 A91-12489 sizes Constrained optimization approach to feedback control A modal evaluation of noise generated by the front rotor IDOT/FAA/CT-TN90/231 p 26 N91-10028 of state-augmented systems p66 N91-11433 of a counter'rotating prop-fan DATA CONVERTERS DETECTION |AIAA PAPER 90-3979] p 72 A91-12492 The full-body ground vibration tests using the low-noise Terminal weather information management STOL test plane Aeroacoustic effects of reduced aft tip speed at constant p64 N91-10960 [NAL-TM-576] p 50 N91-10077 thrust for a model counterrotation turboprop at takeoff DIAGNOSIS DATA LINKS conditions Integration of model and knowledge based diagnosis, Operational evaluation of initial data link air traffic control [NASA-TM-103608 ] p 76 N91-10703 with the example of a turbojet engine services. Volume 2: Appendices COUPLED MODES [ETN-90-97900] p 49 N91-11019 [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 Influence of unsteady aerodynamics on rotor blade DIFFERENTIAL EQUATIONS NASA transport systems research vehicle B-737 data aeroelastic stability and response p 37 A91-12894 More accurate predictions with transonic Navier-Stokes link system and display formats COUPLING methods through improved turbulence modeling INASA-TM-102717] p 44 N91-10058 Wake coupling to full potential rotor analysis code p 17 N91-10850 Terminal weather information management (NASA-TM-102805] p 14 N91-10013 DIFFRACTION PATTERNS Three-dimensional viscous/inviscid coupling in subsonic p 64 N91-10960 Diffraction patterns in the acoustic field of a propeller A flight test facility design for examining digital flow [AIAA PAPER 90-3994] p 73 A91-12507 information transfer p 28 N91-10962 |REPT-B-24| p15 N91-10023 DIFFUSERS The EUROCONTROL future ATS system concept and CRACK PROPAGATION Detailed measurements of the flow field at the outlet the programme of studies, tests, and trials The role of primary carbides in fatigue crack propagation of a backswept transonic centrifugal impeller equipped with in aeroengine bearing steels p 55 A91-11806 p30 N91-10983 a vaned diffuser The use of downlinked measurements to track civil Structural risk assessment and aircraft fleet [ONERA, TP NO. 1990-101] p4 A91-11777 aircraft p 34 N91-11004 maintenance p 61 N91-10321 DIFFUSION DATA PROCESSING Short crack behaviour in AI-LJ alloy 2090 Automated design of controlled diffusion blades Experiences in the use of ABAOUS for creep analysis p62 N91-11243 p 21 N91-10883 (PNR-90705] p63 N91-11266 Short crack growth under realistic flight loading: Model DIGITAL SYSTEMS DATA TRANSMISSION predictions and experimental results for Al 2024 and AI-Li A flight test facility design for examining digital Operational evaluation of initial data link air traffic control 2090 p 62 N91-11246 information transfer p 28 N91-10962 services. Volume 2: Appendices The growth of short cracks in 4340 steel and DIMENSIONAL ANALYSIS [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 aluminum-lithium 2090 p 62 N91-11247 Numerical investigations in three-dimensional internal DECISION MAKING Short and long fatigue crack growth in 2024-T3 under flows Fault diagnosis p 26 N91-10951 Fokker 100 spectrum loading p 63 N91-11248 [NASA-CR-186958] p 52 N91-10083 Inflight replanning for diversions p 27 N91-10955 CRACKING (FRACTURING) DIRECTIONAL CONTROL Graphical interfaces for cooperative planning systems Reliability of results of the capillary testing of gas turbine The design approach used in the synthesis of the B-2 engine components during repairs p 58 A91-12036 p27 N91-10956 lateral-directional control laws Terminal weather information management CRACKS [AIAA PAPER 90-3255] p 50 A91-12929 p64 N91-10960 Structural risk assessment and aircraft fleet DISPLAY DEVICES maintenance p 61 N91-10321 DEFECTS NASA transport systems research vehicle B-737 data CRASHES Structural risk assessment and aircraft fleet link system and display formats Seat dynamic performance standards for a range of maintenance p 61 N91-10321 INASA-TM-102717] p 44 N91-10058 sizes Fault monitoring p 44 N91-10950 Function and performance of visual simulation unit of [DOT/FAA/CT-TN90/23] p 26 N91-10028 Fault recovery recommendation p 27 N91-10952 flight simulation test facility CREEP RUPTURE STRENGTH DEFENSE PROGRAM [NAL-TM-581] p 52 N91-10082 Experiences in the use of ABAQUS for creep analysis DOD responsibilities on Federal aviation and national FAA air traffic operational evaluation of Automated IPNR-90705] p63 N91-11266 airspace system matters Surface Observing System (ASOS) CREEP STRENGTH [PB90-218827J p2 N91-10001 [DOT/FAA/CT-TN90/42] p 52 N91-10084 Influence of heat treatment on microstructure and DEICING Graphical interfaces for cooperative planning systems properties of an advanced high temperature titanium Progress toward the development of an airfoil icing p27 N91-10956 alloy analysis capability p 19 N91-10866 Terminal weather information management IPNR-90689] p56 N9M1107 DELTA WINGS p64 N91-10960 Experiences in the use of ABAOUS for creep analysis Concorde - 1958-1975 p 35 A91-10956 Information management p27 N91-10961 IPNR-90705) p63 N91-11266 How to fly windshear p 41 N91-10974 Mathematical modelling for analysis of nonlinear aircraft CROSS FLOW Aircraft trajectory: Prediction and control in the air dynamics p 50 A91-11820 Vortex instabilities in 3D boundary layers: The transport flight management computer systems relationship between Goertler and crossflow vortices Finite element method for computation of transonic flow p41 N91-10976 |NASA-CR-187456| p 15 N91-10022 about wings from the pressure minimum integral Flight simulator evaluation test of multi-functional display CRUCIFORM WINGS p4 A91-11838 unit Vortex development on cruciform canard configurations Localized linearization method for wings at high angle [NAL-TM-596] p 53 N91-11026 at supersonic speeds p5 A91-11843 of attack p 12 A91 -12896 DISTRIBUTED PROCESSING CRUISING FLIGHT Euler solutions for delta wings p 12 A91 -12899 Use of 4-D RNAV in time-based en route arrival The effect of swirl recovery vanes on the cruise noise A contribution to the numerical solution of transonic flow metering p 33 N91-10997 of an advanced propeller around a delta wing by solving Navier-Stokes equations DOPPLER EFFECT | AIAA PAPER 90-3932! P 68 A91-12448 IDLR-FB-90-13] p 16 N91-10026 Coherent structure induced pressure fluctuations in an The design of two sonic boom wind tunnel models from Grid generation and inviscid flow computation about elliptic jet conceptual aircraft which cruise at Mach numbers o1 2.0 aircraft geometries p 18 N91-10857 I AIAA PAPER 90-3963) p 70 A91-12477 and 3.0 The use of a Navier-Stokes code in the wing design DOWNLINKING I AIAA PAPER 90-40261 p 52 A91-12536 process p 21 N91-10889 The use of downlinked measurements to track civil CRYOGENIC TEMPERATURE aircraft p 34 N91-11004 An embedded grid formulation applied to delta wings Application of cryogenic wind tunnel with liquid nitrogen DRAG p22 N91-10891 and selection of its temperature level p 52 A91-12724 Calculation of the rotor induced download on airfoils CRYOGENIC WIND TUNNELS Conical Euler simulation and active suppression of delta p 19 N9I-10864 Application of cryogenic wind tunnel with liquid nitrogen wing rocking motion DRAG COEFFICIENTS and selection of its temperature level p 52 A91-12724 [ NASA-TM-1026831 p 22 N91 -10904 Comparison of afterbody test setups for combat aircraft CURVATURE Calculation of aerodynamic characteristics of airplane model Large-amplitude vibrations of free-free tapered beams configurations at high angle of attack in steady and (ONERA, TP NO. 1990-70) p 51 A91-11758 p57 A91-11199 unsteady flow p 42 N91-11009 DRAG REDUCTION Convex curvature concept of viscous drag reduction Controlled vortical flow on delta wings through unsteady Viscous drag reduction in boundary layers — Book p8 A91-12696 leading edge blowing p 43 N91-11011 p 58 A91-12688

A-9 DUCTS SUBJECT INDEX

Application of CFD to reduction of skin-friction drag ELECTRIC MOTORS ENVIRONMENTAL TESTS p8 A91-12692 Diagnostics of aviation electric machines — Russian The actuator for the low-noise STOL test plane flight Riblets — for aerodynamic drag reduction of turbulent book p37 A91-12919 control system and its development test skin friction p 59 A91-12694 EMERGENCIES [NAL-TM-574] p 37 N91-10038 Outer-layer manipulators for turbulent drag reduction Fault recovery recommendation p 27 N91-10952 EPOXY RESINS. p8 A91-12695 A function-based approach to cockpit procedure aids Repeated buckling of composite shear panels Convex curvature concept of viscous drag reduction p27 N91-10953 p60 N91-10303 EQUATIONS OF MOTION p 8 A91-12696 EMERGENCY LOCATOR TRANSMITTERS Aircraft dynamics for air traffic control Viscous drag reduction via surface mass injection Current Emergency Locator Transmitter (ELT) p42 N91-10985 p9 A91-12698 deficiencies and potential improvements utilizing EQUIPMENT SPECIFICATIONS DUCTS TSO-C91a ELTs Effects of coolant injection on turbine aerodynamic Application of computational methods in aeroacoustics [NASA-CR-43301 p 28 N91-10964 [AIAA PAPER 90-3917) p 67 A91-12433 characteristics. Part 1: Test turbine and apparatus EMULSIONS DURABILITY [NAL-TM-585-PT-1] p 47 N91-10059 Tests of the general fire suppression concentrate Repeated buckling of composite shear panels Configuration, function and performance of the flight Pyrocap B-136 p60 N91-10303 simulation test facility and its motion simulation system (DOT/FAA/CT-TN90/21] p 26 N91-10029 DYNAMIC RESPONSE (NAL-TM-575] p 52 N91-10080 Research in Structures, Structural Dynamics and ENERGY CONSERVATION ERROR ANALYSIS Materials. 1990 Energy efficiency improvement potential of commercial Fault diagnosis p 26 N91-10951 (NASA-CP-3064) p60 N91-10301 aircraft to 2010 Bayesian multi-sensor tracking for advanced air traffic Static and dynamic aeroelastic characterization of an [DE90-014767] p 39 N91-10046 control systems p 34 N91-11003 aerodynamically heated generic hypersonic aircraft ENERGY DISSIPATION EULER EQUATIONS OF MOTION configuration p61 N91-10320 Effect of energy release in the shock layer on supersonic Mixed structured-unstructured meshes tor aerodynamic Wind models for flight simulation p 53 N91-10975 flight p6 A91-12016 flow simulation p 65 A91-11154 Development and application of the time domain panel ENERGY REQUIREMENTS Solution of the Euler equations on unstructured grids method p 43 N91-11010 Optimal trajectories of aircraft and spacecraft for two-dimensional compressible flow p 3 A91-11160 DYNAMIC STABILITY p29 N91-10968 Low Mach number Euler computations Review of active structural control systems and flight ENGINE AIRFRAME INTEGRATION p5 A91-11900 test techniques for dynamic stability investigations SST airframe integration for a Mach 2 transport An Euler code prediction of near field to midfield sonic [ MBB/FYT256/S/PUB/361 /A ] p 51 N91 -11025 p 36 A91-10967 boom pressure signatures DYNAMIC STRUCTURAL ANALYSIS ENGINE CONTROL [AIAA PAPER 90-4000] p7 A91-12513 Large-amplitude vibrations of free-free tapered beams Fault monitoring p 44 N91-10950 Full-potential, Euler, and Navier-Stokes schemes p59 A91-12754 p57 A91-11199 ENGINE DESIGN Euler and potential computational results for selected Calculations of the service life of components under Suppression of fatigue inducing cavity acoustic modes aerodynamic configurations p 10 A91-12760 severe thermomechanical loads on turbo fan engines [ONERA, TP NO. 1990-63] p 58 A91-11752 [AIAA PAPER 90-3941] p 69 A91-12457 Euler/Navier-Stokes calculations of the flowfield of a The CEPRA 19 anechoic wind tunnel helicopter rotor in hover and forward flight Energy efficiency improvement potential of commercial [ONERA, TP NO. 1990-72] p 51 A91-11760 p11 A91-12765 aircraft to 2010 Research in Structures, Structural Dynamics and Aerodynamic analysis using Euler equations - [DE90-014767] p 39 N91-10046 Materials, 1990 Capabilities and limitations p11 A91-12769 [ NASA-CP-3064 J p 60 N91-10301 Aero engine design factors for a low fuel price Euler solutions for delta wings p 12 A91-12899 Contributions in the field of aeroelastics on the occasion scenario Transonic flow analysis for rotors. Part 3: of the 60th anniversary of Professor Dr.-lng. Habil. Hans [PNR-90681] p47 N91-10066 Three-dimensional, quasi-steady, Euler calculation Wilhelm Foersching Design/development issues for high bypass ratio fans [NASA-TP-2375] p 13 N91-10007 (ETN-90-97630) p 24 N91-10920 [PNR-90758] p 48 N91-10076 Unstructured mesh solution of the Euler and Development and application of the time domain panel Introduction: Needs and approaches to reliability and Navier-Stokes equations p 22 N91 -10892 method p 43 N91-11010 quality assurance in design and manufacture Three dimensional unstructured grids for the solution Coupled rotor/arrframe vibration analysis [PNR-90683J p 60 N9M0297 of the Euler equations p 22 N9t-10893 p43 N91-11012 Automated design of controlled diffusion blades Conical Euler simulation and active suppression of delta DYNAMIC TESTS p 21 N91-10883 wing rocking motion Differential Global Positioning System (DGPS) test Commercial aircraft and the environment [NASA-TM-102683] p 22 N91-10904 plan [PNR-90687] p64 N91-11307 Implicit flux-split Euler schemes for unsteady [DOT/FAA/CT-TN90/15] p 29 N91-10034 aerodynamic analysis involving unstructured dynamic ENGINE INLETS DYNAMICAL SYSTEMS Thermal analysis of engine inlet anti-icing systems meshes Application of dynamical systems theory to nonlinear p 35 A91-10341 [NASA-TM-102732] p 24 N9M0918 aircraft dynamics p 43 N91-11014 Temporal-adaptive Euler/Navier-Stokes algorithm for A comparative study of Navier-Stokes codes for unsteady aerodynamic analysis of airfoils using high-speed flows p 20 N91-10869 unstructured dynamic meshes A numerical study of the hot gas environment around [NASA-TM-102734] p 24 N91-10919 a STOVL aircraft in ground proximity p 21 N91-10887 The calculation of unsteady compressible flow about EAR PROTECTORS CFD analysis for high speed inlets p 21 N91-10888 oscillating airfoil profiles using the Euler upwind method Voice communications in the cockpit noise environment: ENGINE NOISE p25 N91-10921 The role of active noise reduction p 61 N91-11140 Predicted vs. scale model and flight test UDF engine Solution of the two-dimensional Euler equations by a ECONOMIC ANALYSIS noise finite volume discretization on unstructured triangular Energy efficiency improvement potential of commercial [AIAA PAPER 90-3936] p 68 A91-12452 meshes aircraft to 2010 Boundary element analysis of sound scattered by a (ESA-TT-1135] p66 N91-11473 [DE90-014767] p 39 N91-10046 moving surface EVOLUTION (DEVELOPMENT) EIGENVECTORS [AIAA PAPER 90-3944] p 69 A91-12460 The evolution of the bypass engine Performance-robustness trade off of eigenstructure Experimental study of noise sources and acoustic [PNR-90707] p47 N91-10068 assignment applied to rotorcraft p 49 A91-11155 propagation in a turbofan model EXHAUST EMISSION EJECTORS (AIAA PAPER 90-3950] p 69 A91-12466 Supersonic/hypersonic propulsion systems - Exhaust Noise measurements from an ejector suppressor nozzle Rotor wake/stator interaction noise-predictions versus emission characteristics and abatement technology in the NASA Lewis 9- by 15-foot low speed wind tunnel data p45 A91-10965 I AIAA PAPER 90-3983] p 73 A91-12496 [AIAA PAPER 90-3951 ] p 69 A91-12467 Flight testing of two Allison T56 engines modified to Ejector thrust augmentors: Pulse-starting approach to Near-field noise of a single rotation propfan at an angle the ARL developed low smoke configuration the second solution p 23 N91-10913 of attack [ARL-PROP-TM-449] p 47 N91-10064 Noise measurements from an ejector suppressor nozzle [AIAA PAPER 90-3953] p 70 A91-12469 in the NASA Lewis 9- by 15-foot low speed wind tunnel Commercial aircraft and the environment ENGINE PARTS [NASA-TM-103628] p 76 N91-11493 (PNR-90687] p64 N91-11307 Calculations of the service life of components under EXHAUST GASES ELASTIC DAMPING severe thermomechanical loads Application of a state-space wake model to elastic blade Supersonic/hypersonic propulsion systems - Exhaust [ONERA, TP NO. 1990-63] p 58 A91-11752 flapping in hover p 13 N91-10006 emission characteristics and abatement technology The role of process modelling in manufacture and p 45 A91-10965 ELASTIC PROPERTIES design Computation of transonic flow over elastic rotor blade EXHAUST NOZZLES [PNR-90702] p65 N91-11416 Noise measurements from an ejector suppressor nozzle p23 N91-10906 ENGINE TESTS in the NASA Lewis 9- by 15-foot low speed wind tunnel ELECTRIC DISCHARGES OVRhyp. scramjet test aircraft (NASA-TM-103628) p 76 N91-11493 Development and application of linear and nonlinear (NASA-CR-187009J p 38 N91-10041 methods for interpretation of lightning strikes to in-flight Flight testing of two Allison T56 engines modified to EXHAUST SYSTEMS aircraft the ARL developed low smoke configuration Navier-Stokes methods for internal and integrated flow [NASA-CR-3974] p 64 N91-10548 [ARL-PROP-TM-449] p 47 N91-10064 prediction p 10 A91 -12763 ELECTRIC EQUIPMENT Test cases for computation of internal flows in aero EXPERT SYSTEMS Diagnostics of aviation electric machines — Russian engine components Automatic determination of fault effects on aircraft book p37 A91-12919 [AGARD-AR-275] p 49 N91-11022 functionality ELECTRIC GENERATORS ENVIRONMENT POLLUTION INASA-CR-181352] p 37 N91-10039 Diagnostics of aviation electric machines — Russian Commercial aircraft and the environment Fault recovery recommendation p 27 N91-10952 book p37 A91-12919 [PNR-90687] p64 N91-11307 Information management p 27 N91-10961

A-10 SUBJECT INDEX FLIGHT PATHS

Expert systems for the generation of thermal area arrival Development and application of the time domain panel FLIGHT CREWS paths for civil transport p 32 N91-I0995 method p43 N91-11010 Douglas flight deck design philosophy Integration of model and knowledge based diagnosis, Parallelization on a multi-processor system of a solving p40 N91-10939 with the example of a turbojet engine method for the unsteady Navier-Stokes equations at high Aviation safety/automation program overview (ETN-90-97900I P 49 N91-11019 Reynolds numbers p 26 N91-10941 [ESA-TT-1116] p62 N91-11197 Assessing information transfer in full mission flight FINITE ELEMENT METHOD simulations p 26 N91-10946 Comparison of NASTRAN analysis with ground vibration Overview of error-tolerant cockpit research results of UH-60A NASA/AEFA test configuration p40 N91-10949 F-106 AIRCRAFT (NASA-CR-184565J p 61 N91-10333 Fault diagnosis p 26 N91-10951 Development and application of linear and nonlinear Computation of transonic flow over elastic rotor blade methods for interpretation of lightning strikes to in-flight p23 N91-10906 Graphical interfaces for cooperative planning systems aircraft Coupled rotor/airframe vibration analysis p27 N91-10956 [NASA-CR-3974J p 64 N91-10548 p43 N91-11012 FLIGHT INSTRUMENTS F-16 AIRCRAFT FINITE VOLUME METHOD NASA transport systems research vehicle B-737 data Navier-Stokes compulations about complex Solution of the Euler equations on unstructured grids link system and display formats configurations including a complete F-16 aircraft for two-dimensional compressible flow p 3 A91 -11160 [NASA-TM-102717] p 44 N91-10058 p 12 A91-12772 Vertex-based finite-volume solution of the A function-based approach to cockpit procedure aids A zonal Navier-Stokes methodology for flow simulation two-dimensional Navier-Stokes equations p 27 N91-10953 about a complete aircraft p 18 N91-10858 p59 A91-12900 FLIGHT MANAGEMENT SYSTEMS F-18 AIRCRAFT Transonic flow analysis for rotors. Part 3: Differential Global Positioning System (DGPS) test Numerical simulation of F-18 fuselage forebody flows Three-dimensional, quasi-steady, Euler calculation plan at high angles of attack p 18 N91-10859 [NASA-TP-2375] p 13 N91-10007 [DOT/FAA/CT-TN90/15] p 29 N91-10034 Navier-Stokes solutions about the fl A-18 forebody-LEX Solution of the two-dimensional Euler equations by a Aircraft trajectories: Computation, prediction, control, configuration p 18 N91-10860 finite volume discretization on unstructured triangular volume 1. Part 1: Fundamentals. Part 2: Flight in critical FAILURE meshes atmospheric conditions. Part 3: Impact of new on-board Repeated buckling of composite shear panels [ESA-TT-1135] p66 N9M1473 technologies on aircraft operation p60 N91-10303 FIRE EXTINGUISHERS [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 Current Emergency Locator Transmitter (ELT) Tests of the general fire suppression concentrate Aircraft trajectory: Prediction and control in the air deficiencies and potential improvements utilizing PyrccapB-136 transport flight management computer systems TSO-C913 ELTS IDOT/FAA/CT-TN90/21] p 26 N91-10029 p 41 N91-10976 (NASA-CR-4330] p 28 N91-10964 FLAT PLATES Aircraft trajectories: Computation, prediction, control, Integration of model and knowledge based diagnosis, Application of computational methods in aeroacoustics volume 2: Air traffic handling and ground-based guidance with the example of a turbojet engine [AIAA PAPER 90-3917] p 67 A91-12433 of aircraft. Part 4: Air traffic handling. Part 5: Guidance [ETN-90-97900] p 49 N91-11019 Gust response for flat-plate airfoils and the Kutta of aircraft in a time-based constrained environment. Part FAILURE ANALYSIS condition p 12 A91-12882 6: Surveillance. Part 7: Meteorological forecasts. Part 8: Diagnostics of aviation electric machines — Russian FLAT SURFACES Aircraft operation in air traffic handling simulation book p37 A91-12919 TranAir: Recent advances and applications [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 Structural tests of aircraft window assembly equipped p 19 N91-10862 The EUROCONTROL future ATS system concept and with smoke evacuation valve FLEXIBLE BODIES the programme of studies, tests, and trials [DOT/FAA/CT-TN89/44] p 39 N91-10051 Transition control of instability waves over a flexible p30 N91-10983 FALSE ALARMS surface in the presence of an acoustic field Optimization models and techniques to improve air traffic Current Emergency Locator Transmitter (ELT) [AIAA PAPER 90-4008] p 74 A91-12520 management p 31 N91-10988 deficiencies and potential improvements utilizing FLIGHT CHARACTERISTICS The 4-D descent trajectory generation techniques under TSO-C91a ELTS Practical aerodynamics and flight dynamics of Yak-52 realistic operating conditions p 32 N91-10994 (NASA-CR-4330] p 28 N91-10964 and Yak-55 aircraft — Russian book p 13 A91-12911 A description and evaluation of TIMER: A time-based FAN BLADES Application of flight path reconstruction algorithms for terminal flow-control concept p 32 N91-10996 Design/development issues for high bypass ratio fans flight data of helicopter Use of 4-D RNAV in time-based en route arrival [PNR-90758) p48 N91-10076 [NAL-TM-582] p 28 N91-10031 metering p 33 N91-10997 FAR FIELDS Flight characteristics of a modified Schweizer SGS1-36 FLIGHT MECHANICS Some far-field acoustics characteristics of the XV-15 sailplane at low and very high angles of attack Practical aerodynamics and flight dynamics of Yak-52 tilt-rotor aircraft [NASA-TP-3022] p 50 N91-10079 and Yak-55 aircraft — Russian book p 13 A91-12911 [AIAA PAPER 90-3971] p 71 A91-12484 Effect of wind and wind variation on aircraft Aircraft dynamics for air traffic control Helicopter far-field acoustic levels as a function of flight-paths p 41 N91-10972 p42 N91-10985 reduced main-rotor advancing blade-tip Mach number Wind models for flight simulation p 53 N91-10975 FLIGHT OPERATIONS [NASA-TM-102684] p 76 N91-10699 Application of dynamical systems theory to nonlinear Commercial supersonic operations - Thirteen years of FATIGUE LIFE aircraft dynamics p43 N91-11014 experience with Concorde p 36 A91-10957 Calculations of the service life of components under FLIGHT CONTROL National airspace system: In-flight assistance severe thermomechanical loads All-electric flight control experiments and experiments operational concept [ONERA, TP NO. 1990-63] p 58 A91-11752 with a sidestick on the Concorde p 49 A91-10955 [PB90-233115] p28 N91-10032 Repeated buckling of composite shear panels Performance-robustness trade off of eigenstructure Summary of the industry/NASA/FAA workshop on p60 N91-10303 assignment applied to rotorcraft p 49 A91 -11155 philosophy of automation: Promises and realities FAULT TOLERANCE Design technologies utilized in the development of the p44 N91-10942 Overview of error-tolerant cockpit research B-2 flight control system Aircraft trajectories: Computation, prediction, control, p40 N91-10949 [AIAA PAPER 90-3254] p 50 A91-12928 volume 1. Part 1: Fundamentals. Part 2: Flight in critical FEEDBACK The actuator for the low-noise STOL test plane flight atmospheric conditions. Part 3: Impact of new on-board Comparison of a mathematical one-point model and a control system and its development test technologies on aircraft operation multi-point model of aircraft motion in moving air [NAL-TM-574] p 37 N91-10038 [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 p41 N91-10969 Static and dynamic aeroelastic characterization of an Guidance concepts for time-based flight operations FEEDBACK CONTROL aerodynamically heated generic hypersonic aircraft p32 N91-10993 Nonlinear feedback control for high alpha flight configuration p 61 N91-10320 Air traffic management and aircraft guidance in a zone (NASA-CR-186545] p 39 N91-10047 Aircraft trajectories: Computation, prediction, control, of convergence p 33 N91-10998 A new approach to the flight control system volume 1. Part 1: Fundamentals. Part 2: Flight in critical Simulation of automated approach procedures reconfiguration following a battle damage and/or generic atmospheric conditions. Part 3: Impact of new on-board considering dynamic flight operations failure on a control surface p 50 N91-11023 technologies on aircraft operation p35 N91-11008 H infinity-design and the improvement of helicopter [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 FLIGHT OPTIMIZATION handling qualities p 51 N91-11024 Effect of wind and wind variation on aircraft Practical flight paths for microwave-powered airplanes Constrained optimization approach to feedback control flight-paths p41 N91-10972 [NAL-TR-1052T] p 40 N91-10054 of state-augmented systems p 66 N91-11433 Aircraft flight in wind-shear p 41 N91-10973 Optimum on-line handling of air traffic over Western FIGHTER AIRCRAFT How to fly windshear p41 N91-10974 Europe p 30 N91-10982 X-31 will turn on a dime p 36 A91-11863 The EUROCONTROL future ATS system concept and Aircraft trajectories: Computation, prediction, control. The ATF battle shapes up p 36 A91-12062 the programme of studies, tests, and trials Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. A superlative from Sukhoi - The SU-27 p30 N91-10983 Part 11: List of contributors p37 A91-12063 FLIGHT PATHS [AGARO-AG-301-VOL-3-PT-9-11] p 30 N91-10978 Sonic boom focal zones due to tactical aircraft Motion analysis of RPRVs using on-board and The 4-D control of current air carriers in the present maneuvers ground-based measurements p 37 A91 -12224 [AIAA PAPER 90-4003] p 74 A91-12516 environment: Objectives, status, and plans The establishment and performance test of PAPI p 31 N91-10990 Application of unstructured grid methods to steady and (Precision Approach Path Indicator) System for NAL STOL unsteady aerodynamic problems p 17 N91-10856 A new approach to the flight control system aircraft Grid generation and inviscid flow computation about reconfiguration following a battle damage and/or generic (NAL-TM-579] p 28 N91-10030 aircraft geometries p 18 N91-10857 failure on a control surface p 50 N91-11023 Application of flight path reconstruction algorithms for FINITE DIFFERENCE THEORY Review of active structural control systems and flight night data of helicopter A comparative study of Navier-Stokes codes for test techniques for dynamic stability investigations [NAL-TM-582] p 28 N91-10031 high-speed flows P 20 N91 -10869 [MBB/FYT256/S/PUB/361/A] p 51 N91-11025 A consideration on flight paths for microwave-powered Computation of transonic flow over elastic rotor blade Constrained optimization approach to feedback control airplanes p 23 N91-10906 of state-augmented systems p 66 N91-11433 [NAL-TR-1051] P39 N91-10053

A-11 FLIGHT PLANS SUBJECTINDEX

Practical flight paths for microwave-powered airplanes Airplane systems modifications for improved cabin Numerical calculations for flows past an unconventional |NAL-TR-1052T| p 40 N91-10054 smoke evacuation airfoil p24 N91-10916 Graphical interlaces tor cooperative planning systems |DOT/FAA/CT-TN90/24| p 39 N91-10052 Unsteady wind tunnel wall interferences in subsonic and p27 N91-10956 NASA transport systems research vehicle B-737 data transonic profile flows p 53 N91-10928 Aircraft trajectories: Computation, prediction, control, link system and display formats Controlled vortical flow on delta wings through unsteady volume 1. Part 1: Fundamentals. Pan 2: Flight in critical |NASA-TM-102717| p 44 N91-10058 leading edge blowing p 43 N91-11011 atmospheric conditions. Part 3: Impact of new on-board Flight testing of two Allison T56 engines modified to Use of the VP-200 computer for aerothermodynamic technologies on aircraft operation the ARL developed low smoke configuration problems IAGARD-AG-301-VOL-1-PT-1-3) p 29 N91-10967 IARL-PROP-TM-449) p 47 N91-10064 (MBB/FE122/S/PUB/388) p 65 N91-11424 Optimal trajectories of aircraft and spacecraft Development and application of linear and nonlinear FLOW EQUATIONS p29 N91-10968 methods for interpretation of lightning strikes to in-flight An efficient method for solving transonic flow about Critical aspects of trajectory prediction: Flight in aircraft plane cascades with a large nosing p 4 A91-11839 non-uniform wind p 41 N91-10971 | NASA-CR-3974 ] p 64 N91-10548 FLOW GEOMETRY Effect of wind and wind variation on aircraft A flight test facility design for examining digital S4MA hypersonic facility - Flow angularities flight-paths p 41 N91-10972 information transfer p 28 N91-10962 measurements in the S4MA wind tunnel Aircraft flight in wind-shear p 41 N91-10973 Flight evaluation test of the PAPI (Precision Approach IONERA.TP NO. 1990-85] p 51 A91-11766 Wind models for flight simulation p 53 N91-10975 Path Indicator) System Instability of a supersonic shock-free elliptic jet Aircraft trajectory: Prediction and control in the air |NAL-TM-592| p 29 N91-10966 [AIAA PAPER 90-39591 p7 A91-12473 transport flight management computer systems FLIGHT VEHICLES Calculation of three-dimensional viscous/inviscid p41 N9M0976 Computational technology for flight vehicles; interaction in subsonic flow Aircraft trajectories: Computation, prediction, control. Proceedings of the Symposium. Washington, DC, Nov. 5-7, IREPT-B-25] p 16 N91-10024 Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. 1990 p58 A91-11813 FLOW MEASUREMENT Part 11: List of contributors FLOW CHARACTERISTICS Detailed measurements of the flow field at the outlet IAGARD-AG-301-VOL-3-PT-9-11] p 30 N91-10978 Experimental investigation on the effect of coolant of a backswept transonic centrifugal impeller equipped with Optimum on-line handling of air traffic over Western injection on turbine aerodynamic characteristics. Part 2: a vaned diffuser Europe p 30 N91-10982 Effects of injection from rotor casing with 30 deg slanted IONERA.TP NO. 1990-101] p4 A91-11777 The EUROCONTROL future ATS system concept and holes A technique for measuring unsteady aerodynamics in the programme of studies, tests, and trials |NAL-TM-587-PT-2| p 47 N91-10060 turbomachinery p 58 A91-12421 p30 N91-10983 A numerical study of the effects of wind tunnel wall Experimental measurement of structural power flow on Prediction of aircraft trajectories p 42 N91-10984 proximity on an airfoil model an aircraft fuselage The application of trajectory prediction algorithms for INASA-CR-187322] p 25 N91-10934 [NASA-CR-187352] p 61 N91-10335 planning purposes in the Netherlands ATC-system FLOW DIRECTION INDICATORS FLOW STABILITY p65 N91-10986 Wind tunnel test of redundant vane-type flow-direction Instability of a supersonic shock-free elliptic jet Generation of aircraft trajectories for on-line operation: sensing systems | AIAA PAPER 90-3959] p7 A91-12473 Methods, techniques, and tools p 42 N91-10987 INAL-TM-590] p 44 N91-10057 FLOW THEORY Optimization models and techniques to improve air traffic FLOW DISTRIBUTION Theory of slightly blunted axisymmetric power-law management p 31 N91-10988 Modes of oscillation in a nonreacting ramjet combustor bodies at small angle of attack in hypersonic flow The 4-0 control of current air carriers in the present flow p2 A91-10330 environment: Objectives, status, and plans Optimization of the arrangement of the front and rear p8 A91-12559 p31 N91-10990 blade rows of a tandem blade cascade FLOW VELOCITY Expert systems lor the generation of thermal area arrival p46 A91-11349 Aerodynamic interaction of counter rotating propellers paths for civil transport p 32 N91-10995 Detailed measurements of.the flow field at the outlet p23 N91-10910 FLIGHT PLANS of a backswept transonic centrifugal impeller equipped with FLOW VISUALIZATION Inflight replanning for diversions p 27 N91-10955 a vaned diffuser Practical developments in holographic interferometry Graphical interfaces for cooperative planning systems (ONERA. TP NO. 1990-101 | p4 A91-11777 p57 A91-11152 p27 N91-10956 Effect of acoustic excitation on stalled flows over an Holographic interferometry for flow visualization studies FLIGHT SAFETY airfoil in high speed fans p 46 A91-11351 Contributions to the improvement of flight safety in wind | AIAA PAPER 90-4009] p7 A91-12521 Vortex development on cruciform canard configurations shear Navier-Stokes methods for internal and integrated flow at supersonic speeds p5 A91-11843 IESA-TT-11411 p28 N91-10965 prediction p 10 A91-12763 An evaluation of various concepts of reducing FLIGHT SIMULATION Optimum hypersonic airfoil with power law shock supersonic jet noise The need for a hypersonic demonstrator waves [AIAA PAPER 90-3982] p 72 A91-12495 p54 A91-10977 IDE90-014903] p 13 N91-10008 A laser-sheet flow visualization technique for the large Configuration, function and performance of the flight Turbulent flow calculations using unstructured and wind tunnels of the National Full-Scale Aerodynamics simulation test facility and its motion simulation system adaptive meshes Complex |NAL-TM-575| p 52 N91-10080 [NASA-CR-1821021 p 14 N91-10010 INASA-TM-102793] p 60 N91-10268 Function and performance of visual simulation unit of Application of CFD to sonic boom near and mid flow-field flight simulation test facility prediction Simulation of powered-lift flows p 21 N91-10886 |NAL-TM-581| p 52 N91-I0082 (NASA-TM-f02867| p 14 N91-10015 FLUID DYNAMICS Assessing information transfer in full mission flight Experimental investigation on the effect of coolant More accurate predictions with transonic Navier-Stokes simulations p 26 N91 -10946 injection on turbine aerodynamic characteristics. Part 2: methods through improved turbulence modeling Aircraft trajectories: Computation, prediction, control, Effects of injection from rotor casing with 30 deg slanted p 17 N91-10850 volume 1. Part 1: Fundamentals. Part 2: Flight in critical holes Recent advances in Runge-Kutta schemes for solving atmospheric conditions. Part 3: Impact of new on-board INAL-TM-587-PT-2] p 47 N91-10060 3-D Navier-Stokes equations p 17 N91-10851 technologies on aircraft operation Determination of the pressure drag of airfoils by FLUID PRESSURE |AGARD-AG-301-VOL-1-PT-1-3| p 29 N91-10967 integration of surface pressures Shock capturing using a pressure-correction method Critical aspects of trajectory prediction: Flight in [NASA-TM-102722] p 50 N91-10078 p59 A91-12887 non-uniform wind p 41 N91-10971 Numerical investigations in three-dimensional internal FLUTTER Wind models for flight simulation p 53 N91-10975 flows Static and dynamic aeroelastic characterization of an Flight simulator evaluation test of multi-functional display [NASA-CR-1869581 p 52 N91-10083 aerodynamically heated generic hypersonic aircraft unit A laser-sheet flow visualization technique for the large configuration p 61 N91-10320 | NAL-TM-596 ] p 53 N91 -11026 wind tunnels of the National Full-Scale Aerodynamics FLUX VECTOR SPLITTING Flight simulation programs for space plane Complex Implicit flux-split Euler schemes for unsteady . INAL-TM-594] p 55 N91-11035 INASA-TM-102793] p 60 N91-10268 aerodynamic analysis involving unstructured dynamic FLIGHT SIMULATORS Application of CFD codes for the simulation of scramjet meshes Configuration, function and performance of the flight combustor flowfields p 20 N91-10873 [NASA-TM-102732] p 24 N91-10918 Prediction of turbine rotor-stator interaction using simulation test facility and its motion simulation system FOREBODIES Navier-Stokes methods p 20 N91-10881 INAL-TM-575] p 52 N91-10080 Numerical simulation of F-18 fuselage forebody flows A numerical study of the hot gas environment around Function and performance of visual simulation unit of at high angles of attack p 18 N91-10859 a STOVL aircraft in ground proximity p 21 N91-10887 flight simulation test facility Navier-Stokes solutions about the F/A-18 forebody-LEX CFD analysis for high speed inlets p 21 N91-10888 |NAL-TM-581| p 52 N91-10082 configuration p 18 N91-10860 The use of a Navier-Stokes code in the wing design FLIGHT STABILITY TESTS process p 21 N91-10889 FOURIER SERIES Review of active structural control systems and flight Applications of a transonic wing design method Computation of maximum gust loads in nonlinear aircraft test techniques for dynamic stability investigations p 21 N91-10890 using a new method based on the matched filter approach [MBB/FYT256/S/PUB/361/AI p 51 N91-11025 An embedded grid formulation applied to delta wings and numerical optimization p 60 N91-10317 FLIGHT TESTS p 22 N91-10891 FOURIER TRANSFORMATION Motion analysis of RPRVs using on-board and Unstructured mesh solution of the Euler and Estimation of the turbulent spectral densities of the ground-based measurements p 37 A91-12224 Navier-Stokes equations p 22 N91-10892 mass-density using two-dimensional Fourier transform of Predicted vs. scale model and flight test UDF engine Three dimensional unstructured grids for the solution digitized schlieren pictures noise of the Euler equations . p 22 N91-10893 (ONERA.TP NO. 1990-110] p4 A91-11782 [AIAA PAPER 90-3936] p 68 A91-12452 Experimental investigation of the mechanisms FRACTURE STRENGTH CFD applications to complex configurations - A survey underlying vortex kinematics in unsteady separated Influence of chromium and molybdenum on the structural p11 A91-12766 flows p23 N91-10907 stability of a high strength damage tolerant P/M nickel OVRhyp, scramjet test aircraft Ejector thrust augmentors: Pulse-starting approach to based alloy for turbine disks INASA-CR-187009] p 38 N91-10041 the second solution p 23 N91-10913 [ONERA, TP NO. 1990-100] p 55 A91-11776

A-12 SUBJECTINDEX HELICOPTER PERFORMANCE

FRAMES GENERAL AVIATION AIRCRAFT Comparison of modal parameter estimation techniques Structural tests of aircraft window assembly equipped Computational aerodynamics applied to general on aircraft structural data p 57 A91 -11219 with smoke evacuation valve aviation/business aircraft p1i A91-12767 Airplane systems modifications for improved cabin IDOT/FAA/CT-TN89/44] p 39 N91-10051 GEOMAGNETIC PULSATIONS smoke evacuation FREQUENCY STANDARDS Time series and correlation of pulsations observed [DOT/FAA/CT-TN90/24I p 39 N9M0052 Do we really need 57 ways of rating aircraft noise simultaneously by two aircraft p 63 A91-11072 The full-body ground vibration tests using the low-noise [PNR-90720] p 76 N91-10704 GEOMETRICAL ACOUSTICS STOL test plane FUEL COMBUSTION A ray-acoustics approach to fuselage scattering of rotor [NAL-TM-576] p 50 N91-10077 noise Three-dimensional combustor performance validation Comparison of N ASTRAN analysis with ground vibration | AIAA PAPER 90-40131 p 75 A91-12525 with high-density fuels p 55 A91-10345 results of UH-60A NASA/AEFA test configuration GLIDERS FUEL CONSUMPTION (NASA-CR-1845651 p 61 N91-10333 Twenty years of Concorde - The experience of Air Flight characteristics of a modified Schweizer SGS1-36 sailplane at low and very high angles of attack GROUND-AIR-GROUND COMMUNICATION France P 25 A91-10959 x INASA-TP-3022] p 50 N91-10079 Contribution of the satellite techniques to the The variable-cycle engine - A solution to the economical GLOBAL POSITIONING SYSTEM surveillance of air traffic p 35 N91-11005 and environmental challenge of the future supersonic Differential Global Positioning System (OGPS) test GUST LOADS transport P 45 A91-10969 plan Influence of airfoil nose radius on sound generated by Optimisation of hybrid propulsion systems IDOT/FAA/CT-TN90/15] p 29 N91-10034 gust interactions p46 A91-10976 Contribution of the satellite techniques to the (AIAA PAPER 90-3912) p 66 A91-12428 Prediction of the noise from a propeller at angle of surveillance of air traffic p 35 N91-11005 Computation of maximum gust loads in nonlinear aircraft attack GOERTLER INSTABILITY using a new method based on the matched filter approach | AIAA PAPER 90-3954] p 70 A91-12470 Vortex instabilities in 3D boundary layers: The and numerical optimization p 60 ' N91-10317 Energy efficiency improvement potential of commercial relationship between Goertler and crossflow vortices GUSTS aircraft to 2010 INASA-CR-187456) p 15 N91-10022 Gust response for flat-plate airfoils and the Kurta [DE90-014767] p 39 N91-10046 GOVERNMENT/INDUSTRY RELATIONS condition p 12 A91-12882 The 4-D descent trajectory generation techniques under The sonic boom problem p1 A91-10964 realistic operating conditions p 32 N91-10994 GRAPHITE FULL SCALE TESTS Repeated buckling of composite shear panels H Helicopter far-field acoustic levels as a function of p 60 N91-10303 reduced main-rotor advancing blade-tip Mach number GRAPHITE-EPOXY COMPOSITES HARMONIC OSCILLATION INASA-TM-102684] p 76 N91-10699 Repeated buckling of composite shear panels Application of unstructured grid methods to steady and FUNCTIONAL DESIGN SPECIFICATIONS p60 N91-10303 unsteady aerodynamic problems p 17 N91-10856 Basic materials and structures aspects for hypersonic GRID GENERATION (MATHEMATICS) HARMONICS transport vehicles (HTV) p 54 A91-10974 Mixed structured-unstructured meshes for aerodynamic Aircraft interior noise reduction by alternate resonance flow simulation p 65 A91-11154 FUSELAGES tuning Comparison of different calculation methods as applied Grid-generation methodology in applied aerodynamics (NASA-CR-186879) p 76 N91-11488 to a fuselage of lenticular section p9 A91-12755 HARRIER AIRCRAFT | ONER A, TP NO. 1990-66] p3 A91-11755 Toward the routine aerodynamic analysis of complex Harrier - The nexl 30 years p 36 A91-11715 configurations p11 A91-12770 A three-dimensional boundary layer on bodies with a Progress in certifying F402-RR-408: The improved slight cross-sectional asymmetry at small angles of Transonic computations on a natural grid Pegasus engine for AV-8B and Harrier 2 plus attack p5 A91-11909 p 13 A91-12904 (PNR-90719] p40 N91-10056 Active control of interior noise in model aircraft fuselages Turbulent flow calculations using unstructured and HAZARDS adaptive meshes using piezoceramic actuators Terminal weather information management (AIAA PAPER 90-3922] p 67 A91-12438 (NASA-CR-182102] p 14 N91-10010 p64 N91-10960 Analysis 01 Ihe PTA external noise data and comparison Aeroelastic analysis of wings using the Euler equations HEAT TRANSFER with a deforming mesh with predictions Pyrometry for turbine blade development (NASA-TM-102733) p 15 N91-10020 | AIAA PAPER 90-3935] p 68 A91-12451 p57 A91-10336 Noise transmission characteristics of a large scale NASA Computational Fluid Dynamics Conference. Numerical simulation of hypersonic flow around a space Volume 1: Sessions 1-6 composite fuselage model plane. Part 3: Analysis of aerothermodynamic heating | AIAA PAPER 90-3965] p 71 A91-12479 INASA-CP-10038-VOL-1] p 16 N91-10839 [NAL-TR-1027T] p 14 N91-10011 A ray-acoustics approach to fuselage scattering of rotor Computational Fluid Dynamics Program at NASA Ames Heat transfer in aero engine gas turbines, part 1 Research Center p 16 N91-10840 noise (PNR-90754-PT-1) p48 N91-10074 IAIAA PAPER 90-4013] p 75 A91-12525 Application of unstructured grid methods to steady and Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Airplane systems modifications for improved cabin unsteady aerodynamic problems p 17 N91-10856 Oxidation Tester) Grid generation and inviscid flow computation about smoke evacuation (DE90-010929] p 56 N91-11128 IDOT/FAA/CT-TN90/24] p 39 N91-10052 aircraft geometries p 18 N91-10857 HEAT TRANSFER COEFFICIENTS Experimental measurement of structural power flow on Unstructured mesh solution of the Euler and An experimental study of the laminar-turbulent transition Navier-Stokes equations p 22 N91-10892 an aircraft fuselage behind three-dimensional roughness in a boundary layer INASA-CR-187352] p 61 N91-10335 Three dimensional unstructured grids lor the solution on a sharp cone p6 A91-12014 Grid generation and inviscid flow computation about of the Euler equations p 22 N91-10893 HEATING Nonoverlapping composite meshes for multi-element aircraft geometries p 18 N91-10857 Numerical simulation of hypersonic flow around a space . air-foils p 23 N91-10908 Numerical simulation of F-18 fuselage forebody flows plane. Part 3: Analysis of aerothermodynamic heating Implicit flux-split Euler schemes for unsteady at high angles of attack p 18 N91-10859 [NAL-TR-1027T] p 14 N91-10011 aerodynamic analysis involving unstructured dynamic HELICOPTER CONTROL meshes Rotor loads computation using singularity methods and | NASA-TM-102732] p 24 N91-10918 application to the noise prediction Temporal-adaptive Euler/Navier-Stokes algorithm for (ISL-PU-30W90) p15 N91-10018 GAS FLOW unsteady aerodynamic analysis of airfoils using H infinity-design and the improvement of helicopter Interaction of two supersonic radial gas flows unstructured dynamic meshes handling qualities p 51 N91-11024 p6 A91-12018 (NASA-TM-102734] p 24 N91-10919 HELICOPTER DESIGN Flow of a rarefied gas around a sphere in the presence Solution of the two-dimensional Euler equations by a Basic helicopter aerodynamics — Book Of injection p6 A91 -12020 finite volume discretization on unstructured triangular p3 A91-11701 GAS TURBINE ENGINES meshes Helicopter ground resonance p 36 A91-11723 Three-dimensional combustor performance validation [ESA-TT-1135] p66 N91-11473 Simulation investigations of the helicopter ground 1 with high-density fuels p 55 A91-10345 GROUND EFFECT (AERODYNAMICS) resonance p 36 A91-11724 Reliability of results of the capillary testing of gas turbine Simulation of powered-litt flows p 21 N91-10886 The ground resonance of a helicopter with a rotor of engine components during repairs p 58 A91-12036 A numerical study of the hot gas environment around ideal and approximate symmetry considering the Heat transfer in aero engine gas turbines, part 1 a STOVL aircraft in ground proximity p 21 N91-10887 rotor-blade vibration in the thrust plane (PNR-90754-PT-1I p48 N91-10074 GROUND EFFECT MACHINES p36 A91-11725 GAS TURBINES Aeroacoustic environment of an advanced STOVL Helicopter transmissions: Design for safety and Effects of coolant injection on turbine aerodynamic aircraft in hover reliability p 38 N91-10043 characteristics. Part 1: Test turbine and apparatus (AIAA PAPER 90-40161 p 75 A91-12528 MBB'S BO 108 design and development (NAL-TM-585-PT-1) p 47 N91-10059 GROUND RESONANCE [MBB-UD-0568-90-PUB] p 40 N91-10055 Experimental investigation on the effect of coolant Helicopter ground resonance p 36 A91-11723 Helicopter-far-field acoustic levels as a function of injection on turbine aerodynamic characteristics. Part 2: Simulation investigations of the helicopter ground reduced main-rotor advancing blade-tip Mach number Effects of injection from rotor casing with 30 deg slanted resonance p 36 A91-11724 [NASA-TM-102684] p 76 N91-10699 holes The ground resonance of a helicopter with a rotor of A quarter of a century of aeroelastic cooperation INAL-TM-587-PT-2] P 47 N91-10060 ideal and approximate symmetry considering the between research and industry (a review). Part 1: Fighter Total quality management at Rolls-Royce PLC rotor-blade vibration in the thrust plane airplanes and helicopters p 78 N91-10931 IPNR-90759] P60 N91-10298 p36 A91-11725 HELICOPTER ENGINES GAS-SOLID INTERACTIONS GROUND SPEED Space-structure determination of the acoustic field Influence of airfoil nose radius on sound generated by Ground-based 4-D guidance of flights in strong wind generated by a helicopter turboshaft engine gust interactions p33 N91 -10999 [AIAA PAPER 90-4012] p 46 A91-12524 [AIAA PAPER 90-3912) P 66 A91-12428 GROUND TESTS HELICOPTER PERFORMANCE Numerical simulation of vortex-wedge interaction Development of the Griffon II turbo-ramjet Basic helicopter aerodynamics — Book (AIAA PAPER 90-3918] p6 A91-12434 p45 A91-10954 p3 A91-11701

A-13 HELICOPTER PROPELLER DRIVE SUBJECT INDEX

Rotorcraft drivetrain life safety and reliability Euler/Navier-Stokes calculations of the flowfield of a A comparative study of Navier-Stokes codes for [AGARD-R-775] p 38 N91-10042 helicopter rotor in hover and forward flight high-speed flows p 20 N91-10869 MSB'S BO 108 design and development p11 A91-12765 HYPERSONIC WIND TUNNELS (MBB-UD-0568-90-PUB) p 40 N91-10055 HUMAN FACTORS ENGINEERING S4MA hypersonic facility - Flow angularities The calculation of rotor/fuselage interaction for Aviation Safety/Automation Program Conference measurements in the S4MA wind tunnel two-dimensional bodies [NASA-CP-3090] p 26 N91-10936 [ONERA, TP NO. 1990-85] p 51 A91-11766 [NASA-TM-102855] p 25 N91-10933 Douglas flight deck design philosophy Characteristics of piping interference elimination unit HELICOPTER PROPELLER DRIVE p 40 N91-10939 used in the high-speed wind tunnel test of ASUKA seven Rotorcraft drivetrain life safety and reliability Aviation safety/automation program overview percent semi-born prototype [AGARD-R-775J p 38 N91-10042 p26 N91-10941 [NAL-TM-588] p 13 N91-10003 Helicopter transmissions: Design for safety and The ISL hypersonic shock tunnel and its Summary of the industry/NASA/FAA workshop on reliability p 38 N91-10043 instrumentation philosophy of automation: Promises and realities HELICOPTER WAKES [ISL-CO-213/89] p52 N91-10086 p44 N91-10942 Wake coupling to full potential rotor analysis code Ejector thrust augmentors: Pulse-starting approach to INASA-TM-102805] p 14 N91-10013 HYBRID PROPULSION the second solution p 23 N91-10913 HELICOPTERS . Optimisation of hybrid propulsion systems HYPERSONICS The identification of helicopter noise using a neural p46 A91-10976 NASA Computational Fluid Dynamics Conference. network HYDROGEN ENGINES Volume 2: Sessions 7-12 [AIAA PAPER 90-39731 p 72 A91-12486 Hydrogen in high-speed air transportation [NASA-CP-10038-VOL-2] p 20 N91-10868 MBB'S BO 108 design and development p55 A91-10966 [MBB-UD-0568-90-PUBJ p 40 N91-10055 HYDROGEN FUELS Numerical simulation of rotorcraft p 19 N91-10863 Hydrogen in high-speed air transportation Air rescue in the Federal Republic of Germany p 55 A91-10966 [ETN-90-97878] p 28 N91-10963 HYPERCUBE MULTIPROCESSORS ICE FORMATION Progress toward the development of an airfoil icing H infinity-design and the improvement of helicopter Parallelized reliability estimation of reconfigurable analysis capability p 19 N91-10866 handling qualities p 51 N91-11024 computer networks ICE PREVENTION HERMES MANNED SPACEPLANE [NASA-CR-182101] p 65 N91-11430 Thermal analysis of engine inlet anti-icing systems S4MA hypersonic facility - Flow angularities HYPERSONIC AIRCRAFT p 35 A91-10341 measurements in the 54MA wind tunnel The potential for a new era of supersonic and hypersonic Progress toward the development of an airfoil icing [ONERA, TP NO. 1990-85] p 51 A91-11766 aviation p1 A91-10961 analysis capability p 19 N91-10866 HIERARCHIES Hydrogen in high-speed air transportation Graphical interfaces for cooperative planning systems p55 A91-10966 IMAGE ANALYSIS Estimation of the turbulent spectral densities of the p27 N91-10956 Hypersonic aircraft studies p2 A91-10971 mass-density using two-dimensional Fourier transform of HIGH ENERGY PROPELLANTS Propulsion systems for hypersonic transportation Research and development of high-pressure-exponent p45 A91-10975 digitized schlieren pictures fuel-rich propellants Body weight of hypersonic aircraft, part 1 [ONERA, TP NO. 1990-110] p4 A91-11782 [ONERA, TP NO. 1990-91] p 55 A91-11770 [NASA-TM-101028] p 39 N91-10049 IMAGE PROCESSING HIGH PRESSURE Supersonic combustion engine testbed, heat lightning Detection of airplanes in aerial imagery p 59 A91-12824 Research and development of high-pressure-exponent [NASA-CR-187010] p 47 N91-10061 fuel-rich propeltants Static and dynamic aeroelastic characterization of an Function and performance of visual simulation unit of (ONERA, TP NO. 1990-91] p 55 A91-11770 aerodynamically heated generic hypersonic aircraft flight simulation test facility HIGH REYNOLDS NUMBER configuration p 61 N91-10320 [NAL-TM-581] p 52 N91-10082 Time-dependent jet flow and noise computations Application of computational fluid dynamics to IMPACT DAMAGE [AIAA PAPER 90-396) ] p 70 A9M2475 three-dimensional bodies in hypersonic flow Seat dynamic performance standards for a range of HIGH STRENGTH STEELS p62 N91-11174 sizes The role of primary carbides in fatigue crack propagation HYPERSONIC FLIGHT [DOT/FAA/CT-TN90/23] p 26 N91-10028 in aeroengine bearing steels p 55 A91-11806 European Symposium on the Future of High Speed Air IMPELLERS Detailed measurements of the flow field at the outlet HIGH TEMPERATURE Transport, Strasbourg, France, Nov. 6-8, 1989, of a backswept transonic centrifugal impeller equipped with Sound transmission through a high-temperature acoustic Proceedings p 1 A91-10951 a vaned diffuser probe tube System optimization structure and propulsion of a [ONERA, TP NO. 1990-101] p4 M91-11777 [AIAA PAPER 90-3991 ] p 73 A91-12504 hypersonic space transportation system (Saenger) IN-FLIGHT MONITORING HIGH TEMPERATURE AIR p54 A91-10972 The need for a hypersonic demonstrator Commercial supersonic operations - Thirteen years of Thermal analysis of engine inlet anti-icing systems experience with Concorde p 36 A91-10957 p35 A91-10341 p 54 A9M0977 The Rolls Royce/SNECMA Olympus 593 engine The case of a hypersonic flight demonstrator HIGH TEMPERATURE ENVIRONMENTS operational experience and the lessons learned p 54 A91-10978 Propulsion systems for hypersonic transportation p45 A91-10958 p45 A91-10975 Computational - fluid dynamics design applications at supersonic/hypersonic speeds p 12 A91-12773 INCOMPRESSIBLE FLOW Heat transfer in aero engine gas turbines, part 1 A three-dimensional incompressible Euler flow solution [PNR-90754-PT-1] p 48 N91-10074 HYPERSONIC FLOW An approximate calculating method of in turbomachinery p5 A91-11841 A unified unsteady lifting-line theory p8 A91-12575 HISTORIES supersonic/hypersonic unsteady aerodynamic forces of . A quarter of a century of aeroelastic cooperation airfoils p5 A91-11845 Linear potential schemes — for incompressible inviscid between research and industry (a review). Part 2: Transport Flow of a rarefied gas around a sphere in the presence flow p9 A91-12753 airplanes and other civil applications p 40 N91-10932 of injection p6 A91-12020 Gust response for flat-plate airfoils and the Kutta HODOGRAPHS Theory of slightly blunted axisymmetric power-law condition • p 12 A91-12882 Formulation of three-dimensional hodograph method bodies at small angle of attack in hypersonic flow Parallelization on a multi-processor system of a solving and separable solutions for nonlinear transonic flows p 8 A91-12559 method for the unsteady Navier-Stokes equations at high p12 A91-12886 Optimum hypersonic airfoil with power law shock Reynolds numbers HOLOGRAPHIC INTERFEROMETRY waves [ESA-TT-1116] p62 N91-11197 Practical developments in holographic interferometry [DE90-014903] p 13 N91-10008 INDICATING INSTRUMENTS p57 A91-11152 Numerical simulation of hypersonic flow around a space Flight simulator evaluation test of multi-functional display Holographic interferometry for flow visualization studies plane. Part 3: Analysis of aerothermodynamic heating unit in high speed fans p 46 A91 -11351 [NAL-TR-1027T] p 14 N91-10011 [NAL-TM-596] p 53 N91-11026 HORIZONTAL FLIGHT The ISL hypersonic shock tunnel and its INFLUENCE COEFFICIENT Application of a state-space wake model to elastic blade instrumentation Oscillating cascade aerodynamics by an experimental flapping in hover p 13 N91-10006 [ISL-CO-213/89] p 52 N91-10086 influence coefficient technique p2 A91-10339 HORIZONTAL TAIL SURFACES A comparative study of Navier-Stokes codes for INFORMATION Grid generation and inviscid flow computation about high-speed flows p 20 N91-10869 Information management p 27 N91-10961 aircraft geometries p 18 N91-10857 Application of computational fluid dynamics to INFORMATION MANAGEMENT three-dimensional bodies in hypersonic flow HOT-FILM ANEMOMETERS Fault recovery recommendation p 27 N91-10952 p62 N91-11174 Interaction between rotors of a counter rotating Terminal weather information management propeller HYPERSONIC INLETS p64 N91-10960 CFD analysis for high speed inlets p 21 N91-10888 • [AIAA PAPER 90-3976] p 7 A91-12489 Information management p 27 N91-10961 HYPERSONIC SPEED HOVERCRAFT GROUND EFFECT MACHINES Supersonic/hypersonic propulsion systems - Exhaust INFORMATION TRANSFER Calculation of the rotor induced download on airfoils emission characteristics and abatement technology Assessing information transfer in full mission flight p 19 N91-10864 p45 A91-10965 simulations p 26 N91-10946 HOVERING HYPERSONIC VEHICLES INGESTION (ENGINES) Application of a state-space wake model to elastic blade Hypersonic space transport system - Cruiser or A numerical study of the hot gas environment around flapping in hover p 13 N91-10006 accelerator? p 54 A91-10973 a STOVL aircraft in ground proximity p 21 N91-10887 Computation of transonic flow over elastic rotor blade Basic materials and structures aspects for hypersonic INLET AIRFRAME CONFIGURATIONS p23 N91-10906 transport vehicles (HTV) p 54 A91-10974 Concorde - 1958-1975 p 35 A91-10956 HOVERING STABILITY Project HyBuJET INLET FLOW Aeroacoustic environment of an advanced STOVL [NASA-CR-1870t1] p38 N91-10040 Optimization of the arrangement of the front and rear aircraft in hover OVRhyp, scramjet test aircraft blade rows of a tandem blade cascade [AIAA PAPER 90-4016) p 75 A91-12528 [NASA-CR-187009] p 38 N91-10041 p46 A91-11349

A-14 SUBJECT INDEX LIQUID ROCKET PROPELLANTS

Prediction of inviscid stagnation pressure losses in A laser-sheet flow visualization technique for the large supersonic inlet (lows p 12 A91-12903 wind tunnels of the National Full-Scale Aerodynamics INSPECTION JET AIRCRAFT NOISE Complex Structural risk assessment and aircraft fleet Time-dependent jet flow and noise computations [NASA-TM-102793] p 60 N91-10268 maintenance p 61 N91-10321 [AIAA PAPER 90-3961] p 70 A91-12475 LATERAL CONTROL INSTALLING Coherent structure induced pressure fluctuations in an The design approach used in the synthesis of the B-2 Test launch for turboaircraft engine. Description of the elliptic jet lateral-directional control laws installation [ AIAA PAPER 90-39631 p 70 A91 -12477 [AIAA PAPER 90-3255) p 50 A91-12929 [ILA-87-A-02] p48 N91-11018 Structure-borne noise transmission in the preplan test LATERAL STABILITY INSTRUMENT APPROACH assessment aircraft The calculation method for subsonic longitudinal and [AIAA PAPER 90-3966] p 71 A91-12480 Simulation of automated approach procedures lateral aerodynamic characteristics of complete aircraft An evaluation of various concepts of reducing considering dynamic flight operations configuration p5 A91-11844 p35 N91-11008 supersonic jet noise LAUNCH VEHICLES [AIAA PAPER 90-3982] p 72 A91-12495 System optimization structure and propulsion of a INSTRUMENT ERRORS JET ENGINE FUELS hypersonic space transportation system (Saenger) Wind tunnel test of redundant vane-type flow-direction Tests of the general fire suppression concentrate p54 A91-10972 sensing systems PyrocapB-136 LAUNCHING [NAL-TM-590] p 44 N91-10057 [DOT/FAA/CT-TN90/21] p 26 N91-10029 Flight simulation programs for space plane INSTRUMENT LANDING SYSTEMS Thermal stability of jet fuel [NAL-TM-594] p 55 N91-11035 Flight evaluation test of the PAPI (Precision Approach [DE90-016801] p56 N91-10188 LEADING EDGE SWEEP Path Indicator) System Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Numerical simulation of hypersonic flow around a space (NAL-TM-592) p 29 N91-10966 Oxidation Tester) plane. Part 3: Analysis of aerothermodynamic heating INTAKE SYSTEMS [DE90-010929] p 56 N91-11128 [NAL-TR-1027T] p 14 N91-10011 A numerical study of the hot gas environment around JET ENGINES LEADING EDGES a STOVL aircraft in ground proximity p 21 N91-10887 Thermal analysis of engine inlet anti-icing systems The effects of aerofoil profile on wing buffet at low INTEGRAL EQUATIONS p35 A91-10341 speeds p2 A91-11151 Finite element method for computation of transonic flow The evolution of the bypass engine The role of leading edge vortex flows in prop-fan about wings from the pressure minimum integral [PNR-90707] p47 N91-10068 interaction noise p4 A91-11838 Determination of unsteady aerodynamic forces on [AIAA PAPER 90-3977] p 72 A91-12490 INTERACTIONAL AERODYNAMICS engines with a view to flutter investigations Forcing level effect of internal acoustic excitation on Stator/rotor interaction in a transonic turbine p48 N91-10927 the improvement of airfoil performance p2 A91-10340 JET EXHAUST [AIAA PAPER 90-4010] p 74 A91-12522 A study of cylindrical interaction of turbulent boundary Controlling plume deflection by acoustic excitation - An Project HyBuJET layer/shock with swept compression corners experimental demonstration [NASA-CR-187011] p 38 N91-10040 p4 A91-11B36 [AIAA PAPER 90-4006] p 74 A91-12519 Numerical simulation of F-18 fuselage forebody flows JET FLOW Interaction of two supersonic radial gas flows at high angles of attack p 18 N91-10859 Time-dependent jet flow and noise computations p6 A91-12018 Navier-Stokes solutions about the F/A-18 torebody-LEX [AIAA PAPER 90-3961 ] p 70 A91-12475 configuration p 18 N91-10860 Aerodynamic heating in the interaction regions of shock Instability characteristics of a low aspect ratio Controlled vortical flow on delta wings through unsteady waves and turbulent boundary layers induced by rectangular jet leading edge blowing p 43 N91-11011 sweptback blunt fins p6 A91-12226 [AIAA PAPER 90-3962] p 70 A91-12476 LEAST SQUARES METHOD Rotor wake/stator interaction noise-predictions versus The screech of round choked jets, revisited Comparison of modal parameter estimation techniques data [AIAA PAPER 90-3980] p 72 A91-12493 on aircraft structural data p 57 A91-11219 [AIAA PAPER 90-3951] p 69 A91-12467 Jets and lifting surfaces: Computer simulation LENTICULAR BODIES The role of leading edge vortex flows in prop-fan p13 A91-12913 Comparison of different calculation methods as applied interaction noise Propulsion simulation for magnetically suspended wind to a fuselage of lenticular section (AIAA PAPER 90-3977] p 72 A91-12490 tunnel models [ONERA.TP NO. 1990-66] p3 A91-11755 Computational analysis of rotor-stator interaction in [NASA-CR-182093] p 53 N91-11027 LIFT turbomachinery using zonal techniques JET IMPINGEMENT Stator/rotor interaction in a transonic turbine p 10 A91-12764 Shock capturing using a pressure-correction method p2 A91-10340 Jets and lifting surfaces: Computer simulation p59 A91-12887 Acoustic radiation from lifting airfoils in compressible p 13 A91-12913 JET PROPULSION subsonic flow Modeling blade/vortex interactions Future supersonic transport propulsion optimisation [AIAA PAPER 90-3911] p 66 A91-12427 [ISL-R-107/89] p 14 N91-10016 p45 A91-10968 A unified unsteady lifting-line theory p8 A91-12575 JUDGMENTS Aerodynamic interaction of counter rotating propellers LIFT DRAG RATIO Fault diagnosis p 26 N91-10951 p23 N91-10910 Computational aerodynamics applied to high-lift systems p 10 A91-12761 The calculation of rotor/fuselage interaction for LIFTING BODIES two-dimensional bodies K Development of high-lift wing modifications for an [NASA-TM-102855] p 25 N91-10933 advanced capability EA-6B aircraft p 10 A91-12762 Aircraft dynamics for air traffic control KINEMATICS Jets and lifting surfaces: Computer simulation p42 N91-10985 Experimental investigation of the mechanisms p 13 A91-12913 underlying vortex kinematics in unsteady separated INTERFERENCE IMMUNITY Evaluation of the ZONA51D program flows p23 N91-10907 Characteristics of piping interference elimination unit [REPT-B-28J p16 N91-10025 used in the high-speed wind tunnel test of ASUKA seven Critical aspects of trajectory prediction: Flight in LIFTING ROTORS non-uniform wind - p41 N91-10971 percent semi-bom prototype Transonic flow analysis for rotors. Part 3: KNOWLEDGE BASES (ARTIFICIAL INTELLIGENCE) [NAL-TM-588] p 13 N91-10003 Three-dimensional, quasi-steady, Euler calculation The control of inbound flights p 32 N91 -10992 INTERNATIONAL COOPERATION [NASA-TP-2375] p 13 N91-10007 A case study in fostering international HSCT KUTTA-JOUKOWSKI CONDITION Calculation of the rotor induced download on airfoils collaboration p 77 A91-10970 Full-potential. Euler, and Navier-Stokes schemes p 19 N91-10864 p59 A91-12754 INVISCID FLOW Three-dimensional viscous drag prediction for rotor Gust response for flat-plate airfoils and the Kutta Mixed structured-unstructured meshes for aerodynamic blades p 19 N91-10865 condition p 12 A91-12882 flow simulation p 65 A91 -11154 LIGHTNING Linear potential schemes — for incompressible inviscid Development and application of linear and nonlinear flow p9 A91-12753 methods for interpretation of lightning strikes to in-flight Prediction of inviscid stagnation pressure losses in aircraft supersonic inlet flows p 12 A91-12903 LAMINAR BOUNDARY LAYER [NASA-CR-3974] p 64 N91-10548 LINEAR EQUATIONS Three-dimensional viscous/inviscid coupling in subsonic Control of vortical separation on a circular cone Linear potential schemes — for incompressible inviscid flow p3 A91-11162 flow p9 A91-12753 [REPT-B-24] p 15 N91-10023 Transition control of instability waves over a flexible LINEAR QUADRATIC REGULATOR Calculation of three-dimensional viscous/inviscid surface in the presence of an acoustic field Performance-robustness trade off of eigenstructure [AIAA PAPER 90-4008] p 74 A91-12520 interaction in subsonic flow assignment applied to rotorcraft p49 A91-11155 [REPT-B-25] p 16 N91-10024 LAMINAR FLOW LINEARIZATION Applied aspects of laminar-flow technology Grid generation and inviscid flow computation about Localized linearization method for wings at high angle p8 A91-12690 aircraft geometries p 18 N91-10857 of attack p 12 A91-12896 Numerical simulation of rotorcraft p 19 N91-10863 LANDING GEAR LIQUID NITROGEN Test cases for computation of internal flows in aero Helicopter ground resonance p 36 A91-11723 Application of cryogenic wind tunnel with liquid nitrogen engine components LANDING INSTRUMENTS and selection of its temperature level p 52 A91 -12724 (AGARD-AR-275) p 49 N91-11022 Flight evaluation test of the PAPI (Precision Approach LIQUID PROPELLANT ROCKET ENGINES ITERATION Path Indicator) System The instability of combustion in propulsion engines Applications of a transonic wing design method [NAL-TM-592) p 29 N91-10966 p56 N91-10141 p21 N91-10890 LASER DOPPLER VELOCIMETERS LIQUID ROCKET PROPELLANTS ITERATIVE SOLUTION LO.V. applied to measurements between two discs in Propulsion simulation for magnetically suspended wind Large-amplitude vibrations of free-free tapered beams high speed rotation tunnel models p57 A91-11199 [ONERA.TP NO. 1990-94] p 58 A91-11773 [NASA-CR-182093) p 53 N91-11027

A-15 LITHIUM ALLOYS SUBJECTINDEX

LITHIUM ALLOYS Aircraft trajectories: Computation, prediction, control, A numerical study of the effects of wind tunnel wall Short crack behaviour in AI-Li alloy 2090 volume 2: Air traffic handling and ground-based guidance proximity on an airfoil model p62 N91-11243 of aircraft. Part 4: Air traffic handling. Part 5: Guidance [NASA-CR-187322] p 25 N91-10934 Short crack growth under realistic flight loading: Model of aircraft in a time-based constrained environment. Part Comparison of a mathematical one-point model and a predictions and experimental results for Al 2024 and AI-Li 6: Surveillance. Part 7: Meteorological forecasts. Part 8: multi-point model of aircraft motion in moving air 2090 p62 N91-11246 Aircraft operation in air traffic handling simulation p 41 N91-10969 The growth of short cracks in 4340 steel and [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 Wind models for flight simulation p 53 N91-10975 aluminum-lithium 2090 p 62 N91-11247 The high-resolution graphic display: A possible Aircraft trajectories: Computation, prediction, control. LOADING MOMENTS man/machine interface for a computer assisted ATC Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. The effects of aerofoil profile on wing buffet at low management system p 31 N91-10989 Part 11: List of contributors speeds p2 A9M1151 The air traffic controller facing automation: Conflict or [AGARD-AG-301-VOL-3-PT-9-11] p 30 N91-10978 LOADS (FORCES) cooperation p 34 N91-11001 Aircraft dynamics for air traffic control 042 N91-10985 Seat dynamic performance standards for a range of MANAGEMENT SYSTEMS Optimization models and techniques to improve air traffic sizes Operational evaluation of initial data link air traffic control management p 31 N91-10988 [DOT/FAA/CT-TN90/23] p 26 N91-10028 services. Volume 2: Appendices Four dimensional navigation in air traffic with 4-D Research in Structures, Structural Dynamics and [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 Materials, 1990 navigation aircraft p 31 N91-10991 Structural tests of aircraft window assembly equipped [NASA-CP-3064] p 60 N91-10301 Generation of a buoyant plume of artificial smoke for with smoke evacuation valve Experimental measurement of structural power flow on airplane tests [DOT/FAA/CT-TN89/44] p 39 N91-10051 an aircraft fuselage [DOT/FAA/CT-90/9] p 43 N91-11015 [NASA-CR-187352] p 61 N91-10335 Information management p 27 N91-10961 A new approach to the flight control system LOCI MANEUVERABILITY reconfiguration following a battle damage and/or generic . A consideration on flight paths for microwave-powered X-31 will turn on a dime p 36 A91-11863 failure on a control surface p 50 N91-11023 airplanes Nonlinear feedback control for high alpha flight Flight simulation programs for space plane [NAL-TR-1051] p39 N91-10053 [NASA-CR-186545] p 39 N91-10047 [NAL-TM-594] p 55 N91-11035 LONGITUDINAL STABILITY Prediction of effects of wing contour modifications on Voice communications in the cockpit noise environment: All-electric flight control experiments and experiments low-speed maximum lift and transonic performance for the The role of active noise reduction p 61 N91-11140 with a sidestick on the Concorde p 49 A91-10955 EA-6B aircraft MCDONNELL DOUGLAS AIRCRAFT The calculation method for subsonic longitudinal and [NASA-TP-3046] p 22 N91-10902 Extensive MD-11 automation assists pilots, cuts lateral aerodynamic characteristics of complete aircraft Controlled vortical flow on delta wings through unsteady workload p 37 A91-12165 configuration p5 A91-11644 leading edge blowing p 43 N9M1011 MEASURING INSTRUMENTS LOW ASPECT RATIO MANIPULATORS Characteristics of piping interference elimination unit Instability characteristics of a low aspect ratio Outer-layer manipulators for turbulent drag reduction used in the high-speed wind tunnel test of ASUKA seven rectangular jet p8 A91-12695 percent semi-born prototype [AIAA PAPER 90-3962] p 70 A91-12476 MANUFACTURING [NAL-TM-588] p 13 N91-10003 Wind tunnel test of redundant vane-type flow-direction LOW REYNOLDS NUMBER Casting alloys for the jet age sensing systems Calculation of boundary-layer flows on low Reynolds [PNR-90723] p 56 N91-10168 [NAL-TM-590] p 44 N91-10057 number and transonic airfoils p 5 A91-11840 The role of process modelling in manufacture and design Effects of coolant injection on turtine aerodynamic LOW SPEED WIND TUNNELS characteristics. Part 1: Test turbine and apparatus Noise measurements from an ejector suppressor nozzle [PNR-90702] p65 N91-11416 MAP MATCHING GUIDANCE [NAL-TM-585-PT-1] p 47 N91-10059 in the NASA Lewis 9- by 15-foot low speed wind tunnel Flight simulator evaluation test of multi-functional display The ISL hypersonic shock tunnel and its [AIAA PAPER 90-3983] p 73 A91-12496 unit instrumentation [NAL-TM-596] p 53 N91-11026 [ISL-CO-213/89] p52 N91-10086 MARKET RESEARCH MECHANICAL DRIVES M Assessing the market for high speed air travel in the Drive system life and reliability p 38 N91-10044 21st century p 77 A91-10962 MECHANICAL SHOCK MACH NUMBER The high speed market in the next three decades S4MA hypersonic facility - Flow angularities Wind tunnel investigations of the appearance of shocks p77 A91-10963 in the windward region of bodies with circular cross section measurements in the S4MA wind tunnel Multi industry application of advanced materials [ONERA, TP NO. 1990-85] p 51 A91-11766 at angle of attack [PNR-90764] p56 N91-10139 [DLR-FB-90-15] p 16 N91-10027 Low Mach number Euler computations MATCHED FILTERS p5 A91-11900 MENTAL PERFORMANCE Computation of maximum gust loads in nonlinear aircraft Graphical interfaces for cooperative planning systems Coherent structure induced pressure fluctuations in an using a new method based on the matched filter approach p27 N91-10956 elliptic jet and numerical optimization p 60 N91-10317 METAL FATIGUE [AIAA PAPER 90-3963] p 70 A91-12477 MATHEMATICAL MODELS The role of primary carbides in fatigue crack propagation Shock capturing using a pressure-correction method Numerical simulations of oscillatory cold flows in an in aeroengine bearing steels p 55 A91-11806 p59 A91-12887 axisymmetric ramjet combustor p2 A91-10329 Short crack growth under realistic flight loading: Model MAGNESIUM Availability - A practical approach on aerospace predictions and experimental results for Al 2024 and AI-Li Tests of the general fire suppression concentrate industry p 57 A91-11202 2090 p62 N91-11246 Pyrocap B-136 Mathematical modelling for analysis of nonlinear aircraft [DOT/FAA/CT-TN90/21] p 26 N91-10029 dynamics p 50 A91-11820 The growth of short cracks in 4340 steel and aluminum-lithium 2090 p 62 N91-11247 MAGNETIC SUSPENSION A process model for age hardening of aluminium alloys. Propulsion simulation for magnetically suspended wind I - The model p 56 A91 -11883 Short and long fatigue crack growth in 2024-T3 under Fokker 100 spectrum loading p 63 N91 -11248 tunnel models Numerical simulation and active control of combustion [NASA-CR-182093] p 53 N91-11027 instability in a ramjet combustor METAL SURFACES MAGNETOMETERS [AIAA PAPER 90-3930] p 46 A91-12446 Detection of concealed corrosion damage in aircraft Space-structure determination of the acoustic field Time series and correlation of pulsations observed structures using the eddy current method generated by a helicopter turboshaft engine simultaneously by two aircraft p 63 A91-11072 p58 A91-11974 [AIAA PAPER 90-4012] p 46 A91-12524 MAINTAINABILITY METAL WORKING Application of a state-space wake model to elastic blade Casting alloys for the jet age Availability - A practical approach on aerospace flapping in hover p 13 N91-10006 industry p 57 A91-11202 [PNR-90723] p56 N91-10168 Optimum hypersonic airfoil with power law shock METEOROLOGICAL PARAMETERS MALFUNCTIONS waves Automatic determination of fault effects on aircraft Developments to enhance meteorological forecasting [DE90-014903] p 13 N91-10008 for air traffic services p 64 N91-11006 functionality Turbulent flow calculations using unstructured and METEOROLOGY [NASA-CR-181352] p 37 N91-10039 adaptive meshes Aircraft trajectories: Computation, prediction, control, Douglas flight deck design philosophy [NASA-CR-182102] p 14 N91-10010 volume 1. Part 1: Fundamentals. Part 2: Flight in critical p40 N91-10939 Numerical computation of viscous flow about atmospheric conditions. Part 3: Impact of new on-board MAN MACHINE SYSTEMS unconventional airfoil shapes technologies on aircraft operation Pilot modelling techniques for the analysis of aircraft [NASA-CR-187343] p 15 N91-10019 [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 linear dynamic behaviour p 49 A91 -11158 Drive system life and reliability p 38 N91-10044 MICROSTRUCTURE FAA air traffic operational evaluation of Automated Direct use of linear time-domain aerodynamics in Thermal barrier coatings - Microstructural investigation Surface Observing System (ASOS) aeroservoelastic analysis: Aerodynamic model after annealing [DOT/FAA/CT-TN90/42] p 52 N91-10084 p60 N91-10316 [ONERA, TP NO. 1990-62] p 55 A91-11751 Aviation Safety/Automation Program Conference Comparison of NASTRAN analysis with ground vibration Influence of heat treatment on microstructure and [NASA-CP-3090] p 26 N91-10936 results of UH-60A NASA/AEFA test configuration properties of an advanced high temperature titanium ATC automation concepts p 29 N91-10957 [NASA-CR-184565] p 61 N91-10333 NASA Computational Fluid Dynamics Conference. alloy MAN-COMPUTER INTERFACE Volume 1: Sessions 1-6 [PNR-90689] p56 N91-11107 Aviation Safety/Automation Program Conference [NASA-CP-10038-VOL-1] p 16 N91-10839 MICROWAVE POWER BEAMING [NASA-CP-3090] p 26 N91-10936 A comparative study of Navier-Stokes codes for A consideration on flight paths for microwave-powered Aviation safety/automation program overview high-speed flows p 20 N91-10869 airplanes p26 N91-10941 The aerodynamic effects of nozzle guide vane shock [NAL-TR-1051] p39 N91-10053 Fault recovery recommendation p 27 N91-10952 wave and wake passing on a transonic turbine rotor Practical flight paths for microwave-powered airplanes Information management p 27 N91-10961 p24 N91-10915 [NAL-TR-1052T] p 40 N91-10054

A-16 SUBJECTINDEX NOISE REDUCTION

MILITARY AIRCRAFT Vertex-based finite-volume solution of the Do we really need 57 ways of rating aircraft noise Comparison of afterbody test setups for combat aircraft two-dimensional Navier-Stokes equations [PNR-90720] . p 76 N91-10704 model p59 A91-12900 Noise measurements from an ejector suppressor nozzle [ONERA, TP NO. 1990-70) p 51 A91-11758 Numerical computation of viscous flow about in the NASA Lewis 9- by 15-foot low speed wind tunnel Sonic boom environment under a supersonic military unconventional airfoil shapes [NASA-TM-103628] p 76 N91-11493 operating area [NASA-CR-187343] p 15 N91-10019 NOISE POLLUTION [AIAA PAPER 90-4032] p 63 A91-12541 A contribution to the numerical solution of transonic flow Re-engining: Real stage 3 compliance plus other Development of high-lift wing modifications for an around a delta wing by solving Navier-Stokes equations benefits advanced capability EA-6B aircraft p 10 A91 -12762 [DLR-FB-90-13] P 16 N91-10026 [PNR-90755] p48 N91-10075 MILITARY HELICOPTERS Numerical investigations in three-dimensional internal Do we really need 57 ways of rating aircraft noise The acoustic results of a United Techologtes scale model flows [PNR-90720] p 76 N91-10704 (NASA-CR-186958] p 52 N91-10083 helicopter rotor tested at DNW Commercial aircraft and the environment [AIAA PAPER 90-4035] p 75 A91-12543 More accurate predictions with transonic Navier-Stokes (PNR-90687) p64 N91-11307 MISSILE CONFIGURATIONS methods through improved turbulence modeling NOISE PREDICTION p 17 N91-10850 Comparison of different calculation methods as applied Some far-field acoustics characteristics of the XV-15 to a fuselage of lenticular section Recent advances in Runge-Kutta schemes for solving tilt-rotor aircraft [ONERA, TP NO. 1990-66] p3 A91-11755 3-D Navier-Stokes equations p 17 N91-10851 [AIAA PAPER 90-3971] p 71 A91-12484 CFD for applications to aircraft aeroelastitity MIXING LAYERS (FLUIDS) On the prediction of far field computational p 17 N91-10855 Numerical simulation of supersonic mixing layer using aeroacoustics of advanced propellers Navier-Stokes solutions about the F/A-18 forebody-LEX high resolution scheme [AIAA PAPER 90-3996] p 73 A91-12509 [AIAA PAPER 90-4025] p8 A91-12535 configuration p 18 N91 -10860 NOISE PREDICTION (AIRCRAFT) MODAL RESPONSE Navier-Stokes solutions for flows related to store The sonic boom problem p1 A91-10964 separation p 18 N91-10861 Comparison of modal parameter estimation techniques The variable-cycle engine - A solution to the economical on aircraft structural data p 57 A91-11219 A comparative study of Navier-Stokes codes for and environmental challenge of the future supersonic high-speed flows p 20 N91-10869 MODELS transport p 45 A91-10969 Application of CFD codes for the simulation of scramjet Integration of model and knowledge based diagnosis, State-of-the-art of high-speed propeller noise prediction with the example of a turbojet engine combustor flowfields p 20 N91-10873 A multidisciplinary approach and comparison with Prediction of turbine rotor-stator interaction using [ETN-90-97900] p 49 N91-11019 measured data Navier-Stokes methods p 20 N91-10881 MOLYBDENUM ALLOYS [AIAA PAPER 90-3934] p 68 A91-12450 Simulation of powered-lift flows p 21 N91-10886 I nf luence of chromium and molybdenum on the structural Analysis of the PTA external noise data and comparison The use of a Navier-Stokes code in the wing design stability of a high strength damage tolerant P/M nickel with predictions process p 21 N91 -10889 based alloy for turbine disks [AIAA PAPER 90-3935] p 68 A91-12451 Unstructured mesh solution of the Euler and [ONERA, TP NO. 1990-100] p 55 A91-11776 Predicted vs. scale model and flight test UDF engine Navier-Stokes equations p 22 N91-10892 MONITORS noise Fault monitoring p 44 N91-10950 Temporal-adaptive Euler/Navier-Stokes algorithm for [AIAA PAPER 90-3936] p 68 A91-12452 Fault recovery recommendation p 27 N91 -10952 unsteady aerodynamic analysis of airfoils using Boundary element analysis of sound scattered by a unstructured dynamic meshes MOTION SIMULATION moving surface [NASA-TM-102734] p 24 N91-10919 Configuration, function and performance of the flight [AIAA PAPER 90-3944] p 69 A91 -12460 Parallelization on a multi-processor system of a solving simulation test facility and its motion simulation system Rotor wake/stator interaction noise-predictions versus method for the unsteady Navier-Stokes equations at high [NAL-TM-575] p 52 N91-10080 data MOTION SIMULATORS Reynolds numbers [AIAA PAPER 90-3951 ] p 69 A91-12467 [ESA-TT-1116] p62 N91-11197 Configuration, function and performance of the flight Experimental/theoretical investigation of the sound field NAVIGATION AIDS simulation test facility and its motion simulation system of an isolated propeller, including angle of incidence How to fly windshear p 41 N91 -10974 [NAL-TM-575] p 52 N91-10080 effects NEAR FIELDS MULTIGRID METHODS [AIAA PAPER 90-3952] p 69 A91-12468 Near-field noise of a single rotation propfan at an angle Nonoveriapping composite meshes for multi-element Prediction of the noise from a propeller at angle of of attack air-foils p 23 N91-10908 attack [AIAA PAPER 90-3953] p 70 A91-12469 [AIAA PAPER 90-3954] p 70 A91-12470 NEURAL NETS Time-dependent jet flow and noise computations N The identification of helicopter noise using a neural [AIAA PAPER 90-3961 ] p 70 A91-12475 network Comparison of shock wave rise time prediction NASA PROGRAMS [AIAA PAPER 90-3973] p 72 A91-12486 techniques NACA/NASA supersonic flight research Identification of aerospace acoustic sources using (AIAA PAPER 90-4001] p 74 A91-12514 p 1 A91:10953 sparse distributed associative memory A ray-acoustics approach to fuselage scattering of rotor Development and application of linear and nonlinear [AIAA PAPER 90-3992] p 73 A91-12505 noise methods for interpretation of lightning strikes to in-flight NICKEL ALLOYS [AIAA PAPER 90-4013] p 75 A91-12525 aircraft Pyrometry for turbine blade development Noise characteristics of the Japan's experimental [NASA-CR-3974] p 64 N91-10548 p57 A91-10336 powered lift STOL aircraft NASTRAN Influence of chromium and molybdenum on the structural [AIAA PAPER 90-4014] p 75 A91-12526 Comparison of NASTRAN analysis with ground vibration stability of a high strength damage tolerant P/M nickel Installation effects on counter rotating propeller noise results of UH-60A NASA/AEFA test configuration based alloy for turbine disks [AIAA PAPER 90-4023] p 75 A91-12534 [NASA-CR-184565] p 61 N91-10333 [ONERA, TP NO. 1990-100] p 55 A91-11776 Rotor loads computation using singularity methods and NATIONAL AIRSPACE SYSTEM Casting alloys for the jet age application to the noise prediction DOD responsibilities on Federal aviation and national [PNR-90723] p56 N91-10168 [ISL-PU-301/90] p 15 N91-10018 airspace system matters NOISE GENERATORS Application of flight path reconstruction algorithms for [PB90-218827] p2 N91-10001 Experiments on the aerodynamic noise sources in flight data of helicopter National airspace system: In-flight assistance centrifugal turbomachinery [NAL-TM-582] p 28 N91-10031 operational concept [AIAA PAPER 90-3948] p 69 A91-12464 Prediction of the noise from a propeller at angle of [PB90-233115] p28 N91-10032 Coherent structure induced pressure fluctuations in an attack Aviation safety/automation program overview elliptic jet [NASA-TM-103627] p 77 N91-11495 p26 N91-10941 [AIAA PAPER 90-3963] p 70 A91-12477 NOISE PROPAGATION Airport system capacity strategic choices Noise mechanisms of transonic vortex airfoil Noise radiation of propeller loading sources with angular [SR-226] p30 N91-10979 interaction inflow NATIONAL AVIATION SYSTEM [AIAA PAPER 90-3972] p 71 A91-12485 [AIAA PAPER 90-3955) p 70 A91-12471 Supersonic air transport programs in the 60's A modal evaluation of noise generated by the front rotor Structure-borne noise transmission in the propfan test p1 A91 -10952 of a counter-rotating prop-fan assessment aircraft Airport system capacity strategic choices [AIAA PAPER 90-3979] p 72 A91-12492 [AIAA PAPER 90-3966] p 71 A9M2480 [SR-226] p30 N91-10979 Aircraft en route noise annoyance The use of spatial coherence techniques for identifying NAVIER-STOKES EQUATION [AIAA PAPER 90-4028] p 63 A91-12537 noise transmission paths on the MDC-UHB demonstrator aircraft Low Mach number Euler computations NOISE INTENSITY p5 A91-11900 The sonic boom problem p1 A91-10964 [ AIAA PAPER 90-3968 ] p 71 A91 -12482 Time-dependent jet How and noise computations NOISE REDUCTION NOISE MEASUREMENT [AIAA PAPER 90-3961 ] p 70 A91-12475 Experimental study of noise sources and acoustic Experimental study of high-speed impulsive rotor noise Application of CFD to sonic boom near and mid flow-field propagation in a turbofan model in a wind tunnel prediction [AIAA PAPER 90-3950] p 69 A91-12466 (ONERA, TP NO. 1990-123] p 66 A91-11786 [AIAA PAPER 90-3999] p7 A91-12512 An evaluation of various concepts of reducing Full-potential, Euler. and Navier-Stokes schemes Noise measurements from an ejector suppressor nozzle supersonic jet noise p59 A91-12754 in the NASA Lewis 9- by 15-foot low speed wind tunnel [AIAA PAPER 90-3982] p 72 A91-12495 Navier-Stokes methods for internal and integrated flow [ AIAA PAPER 90-3983] p 73 A91-12496 Noise measurements from an ejector suppressor nozzle prediction p 10 A91-12763 Helicopter far-field acoustic levels as a function of in the NASA Lewis 9- by 15-foot low speed wind tunnel Euler/Navier-Stokes calculations of the flowfield of a reduced main-rotor advancing blade-tip Mach number [AIAA PAPER 90-3983] p 73 A91-12496 helicopter rotor in hover and forward flight (NASA-TM-102684] p 76 N91-10699 The sonic boom of an oblique frying wing pit A91-12765 Aeroacoustic effects of reduced aft tip speed at constant [AIAA PAPER 90-4002] p 74 A91-12515 Navier-Stokes computations about complex thrust for a model counterrotation turboprop at takeoff Sound insulation of dwellings around airports - Objective configurations including a complete F-16 aircraft conditions and subjective measures and findings p 12 A91-12772 [NASA-TM-103608] p 76 N91-10703 [AIAA PAPER 90-4029) p 63 A91-12538

A-17 NOISE SPECTRA SUBJECT INDEX

The actuator for the low-noise STOL test plane flight PARAMETER IDENTIFICATION control system and its development test Comparison of modal parameter estimation techniques [NAL-TM-574] p 37 N91-10038 ON-LINE SYSTEMS on aircraft structural data p 57 A91-11219 The full-body ground vibration tests using the low-noise Optimum on-line handling of air traffic over Western Flight characteristics of a modified Schweizer SGS1-36 STOL test plane Europe p 30 N91-10982 sailplane at low and very high angles of attack [NAL-TM-576] p 50 N91-10077 Prediction of aircraft trajectories p 42 N91-10984 [NASA-TP-3022] p 50 N91-10079 Comparison of a mathematical one-point model and a Test launch for turboaircraft engine. Description of the Generation of aircraft trajectories for on-line operation: multi-point model of aircraft motion in moving air installation Methods, techniques, and tools p 42 N91-10987 [ILA-87-A-02) p48 N91-11018 p41 N91-10969 Optimization models and techniques to improve air traffic PATTERN RECOGNITION Voice communications in the cockpit noise environment: management p 31 N91-10988 The role of active noise reduction p 61 N91-11140 Identification of aerospace acoustic sources using The air traffic controller facing automation: Conflict or sparse distributed associative memory Aircraft interior noise reduction by alternate resonance cooperation p 34 N91-11001 [AIAA PAPER 90-3992] p 73 A91-12505 tuning OPERATING COSTS PERFORMANCE PREDICTION [NASA-CR-186879] p 76 N91-11488 Twenty years of Concorde - The experience of Air Three-dimensional combustor performance validation Noise measurements from an ejector suppressor nozzle France p 25 A91-10959 with high-density fuels p 55 A91-10345 in the NASA Lewis 9- by 15-foot low speed wind tunnel The high speed market in the next three decades Progress in certifying F402-RR-408: The improved [ NASA-TM-103628 ] p 76 N91 -11493 p77 A91-10963 Pegasus engine for AV-8B and Harrier 2 plus The effect of swirl recovery vanes on the cruise noise OPERATIONAL PROBLEMS [PNR-90719] p40 N91-10056 of an advanced propeller The Rolls Royce/SNECMA Olympus 593 engine Prediction of effects of wing contour modifications on [ N ASA-TM-103625 ] p 77 N91 -11494 operational experience and the lessons learned low-speed maximum lift and transonic performance for the Prediction of the noise from a propeller at angle of p45 A91-10958 EA-6B aircraft attack British Airways operational experience with Concorde INASA-TP-3046] p 22 N91-10902 [ N ASA-TM-103627] p77 N91-11495 p 26 A91-10960 Short crack growth under realistic flight loading: Model NOISE SPECTRA OPERATOR PERFORMANCE predictions and experimental results for Al 2024 and AI-Li Estimation of the turbulent boundary layer pressure Operational evaluation of initial data link air traffic control 2090 p62 N91-11246 wavenumber-frequency spectrum using a fixed probe services. Volume 2: Appendices PERFORMANCE TESTS Forcing level effect of internal acoustic excitation on pair [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 [AIAA PAPER 90-3926] p 67 A91-12442 the improvement of airfoil performance OPTIMAL CONTROL [AIAA PAPER 90-4010] p 74 A91-12522 An experimental technique of separating airborne and Pilot modelling techniques for the analysis of aircraft Characteristics of piping interference elimination unit structure-borne noise using wavenumber-frequency linear dynamic behaviour p 49 A91-11158 spectrum used in the high-speed wind tunnel test of ASUKA seven Nonlinear feedback control for high alpha flight [AIAA PAPER 90-3969] p 71 A91-12483 percent semi-born prototype [NASA-CR-186545] p 39 N91-10047 NONDESTRUCTIVE TESTS [NAL-TM-588] p 13 N91-10003 Optimal trajectories of aircraft and spacecraft , Reliability of results of the capillary testing of gas turbine The establishment and performance test of PAPI p29 N91-10968 engine components during repairs p 58 A91-12036 (Precision Approach Path Indicator) System for NAL STOL H infinity-design and the improvement of helicopter aircraft NONEOUILIBRIUM THERMODYNAMICS handling qualities p 51 N91-11024 [NAL-TM-579] p 28 N91-10030 Some aeroacoustic and aerodynamic applications of the The actuator for the low-noise STOL test plane flight theory of nonequiiibrium thermodynamics Constrained optimization approach to feedback control control system and its development test [AIAA PAPER 90-3989] p 73 A91-12502 of state-augmented systems p 66 N91-11433 [NAL-TM-574] p 37 N91-10038 NONLINEAR EQUATIONS OPTIMIZATION Future supersonic transport populsion optimization Wind tunnel test of redundant vane-type flow-direction Formulation of three-dimensional hodograph method sensing systems and separable solutions for nonlinear transonic flows [PNR-90737] p48 N91-10071 Computation of maximum gust loads in nonlinear aircraft [NAL-TM-590] p 44 N91-10057 p 12 A91-12886 Flight evaluation test of the PAPI (Precision Approach Comparison of a mathematical one-point model and a using a new method based on the matched filter approach and numerical optimization p 60 N91-10317 Path Indicator) System multi-point model of aircraft molion in moving air [NAL-TM-592] p 29 N91-10966 p 41 N91-10969 Aerodynamic design optimization using computational fluid dynamics p 43 N91-11013 Flight simulator evaluation test of multi-functional display NONLINEAR FEEDBACK Constrained optimization approach to feedback control unit Nonlinear feedback control for high alpha flight of state-augmented systems p 66 N91-11433 [NAL-TM-596] p 53 N91-11026 [NASA-CR-186545] p 39 N91-10047 OSCILLATIONS PERTURBATION THEORY NONLINEAR SYSTEMS Oscillating cascade aerodynamics by an experimental CFD for applications to aircraft aeroelasticity Computation of maximum gust loads in nonlinear aircraft influence coefficient technique p2 A91 -10339 p 17 N91-10855 using a new method based on the matched filter approach OVERPRESSURE PILOT PERFORMANCE and numerical optimization p 60 N91-10317 Application of CFD to sonic boom near and mid flow-field Flight characteristics of a modified Schweizer SGS1-36 Calculation of the pressure distribution on an oscillating prediction sailplane at low and very high angles of attack airfoil in incompressible flow considering nonlinear [AIAA PAPER 90-3999] p7 A91-12512 [NASA-TP-3022] p 50 N91-10079 effects p25 N91-10926 OXIDATION Assessing information transfer in full mission flight simulations p 26 N91-10946 NONLINEARITY Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Computation of maximum gust loads in nonlinear aircraft Oxidation Tester) Fault diagnosis p 26 N91-10951 using a new method based on the matched filter approach (DE90-010929] p 56 N91-11128 PISTON THEORY and numerical optimization p60 N91-10317 An approximate calculating method of supersonic/hypersonic unsteady aerodynamic forces of Application of dynamical systems theory to nonlinear airfoils p5 A91-11845 aircraft dynamics p 43 N91-11014 PLUMES NONUNIFORMITY PANEL METHOD (FLUID DYNAMICS) Controlling plume deflection by acoustic excitation - An Critical aspects of trajectory prediction: Flight in Unsteady airloading panel method for prop-fans experimental demonstration non-uniform wind p41 N91-10971 [AIAA PAPER 90-3914] p 67 A91-12430 (AIAA PAPER 90-4006] p 74 A91-12519 NOZZLE DESIGN Three-dimensional viscous/inviscid coupling in subsonic Generation of a buoyant plume of artificial smoke for Aerodynamic design optimization using computational flow airplane tests fluid dynamics p 43 N91-11013 [REPT-B-24] p 15 N91-10023 [DOT/FAA/CT-90/9] p 43 N91-11015 NOZZLE FLOW Calculation of three-dimensional viscous/inviscid POSITION (LOCATION) Navier-Stokes methods for internal and integrated flow interaction in subsonic flow Aircraft 'trajectory reconstitution on the basis of prediction p 10 A91-12763 [REPT-B-25] p 16 N91-10024 multi-radar plot information p 34 N91-11002 Noise measurements from an ejector suppressor nozzle Prediction of effects of wing contour modifications on Generation of a buoyant plume of artificial smoke for in the NASA Lewis 9- by 15-foot low speed wind tunnel low-speed maximum lift and transonic performance for the airplane tests [NASA-TM-103628] p 76 N91-11493 EA-6B aircraft (DOT/FAA/CT-90/9] p 43 N91-11015 NOZZLE GEOMETRY INASA-TP-3046] p 22 N91-10902 POSITION INDICATORS An evaluation of various concepts of reducing Development and application of the time domain panel Flight simulator evaluation test of multi-functional display supersonic jet noise method p 43 N91-11010 unit [AIAA PAPER 90-3982] p 72 A91-12495 PANELS [NAL-TM-596] p 53 N91-11026 Noise measurements from an ejector suppressor nozzle Repeated buckling of composite shear panels POTENTIAL FLOW in the NASA Lewis 9- by 15-foot low speed wind tunnel p60 N91-10303 Shock wave formation during interaction with a weak [AIAA PAPER 90-3983] p 73 A91-12496 TranAir: Recent advances and applications discontinuity at the boundary of a local subsonic region p6 A91-12017 Aeroacoustic environment of an advanced STOVL p 19 N91-10862 Linear potential schemes — for incompressible inviscid aircraft in hover Douglas flight deck design philosophy flow p9 A91-12753 [AIAA PAPER 90-4016] p 75 A91-12528 p40 N91-10939 PARALLEL PROCESSING (COMPUTERS) Full-potential, Euler, and Navier-Stokes schemes NUMERICAL FLOW VISUALIZATION Parallelized reliability estimation of reconfigurable p 59 A91-12754 Modes of oscillation in a nonreacting ramjet combustor computer networks Subsonic airfoil design p 9 A91 -12756 flow p2 A91-10330 [NASA-CR-182101] p 65 N91-11430 Euler and potential computational results for selected Mixed structured-unstructured meshes for aerodynamic PARALLEL PROGRAMMING aerodynamic configurations p 10 A91 -12760 flow simulation p 65 A91-11154 Parallelization on a multi-processor system of a solving POWERED LIFT AIRCRAFT Numerical simulation of supersonic mixing layer using method for the unsteady Navier-Stokes equations at high Noise characteristics of the Japan's experimental high resolution scheme Reynolds numbers powered lift STOL aircraft [AIAA PAPER 90-4025] p 8 A91-12535 [ESA-TT-1116] p62 N91-11197 [AIAA PAPER 90-4014] p 75 A91-12526

A-18 SUBJECT INDEX RADAR NETWORKS

Simulation o! powered-lift flows p 21 N91-10886 Analysis of the PTA external noise data and comparison PROPELLERS PRECIPITATION HARDENING with predictions Aeroacoustic effects of reduced aft tip speed at constant A process model (or age hardening of aluminium alloys. [AIAA PAPER 90-3935] p 68 A91-12451 thrust for a model counterrotauon turboprop at takeoff I • The model p 56 ASM 1833 Near-field noise of a single rotation propfan at an angle conditions PREDICTION ANALYSIS TECHNIQUES of attack [AIAA PAPER 90-3933] p 68 A91-12449 Prediction of inviscid stagnation pressure losses in [AIAA PAPER 90-3953) p 70 A91-12469 Diffraction patterns in the acoustic field of a propeller supersonic inlet flows p 12 A91-12903 Structure-borne noise transmission in the propfan test [AIAA PAPER 90-3994] p 73 A91-12507 Aircraft trajectory: Prediction and control in the air assessment aircraft The effect of swirl recovery vanes on the cruise noise transport flight management computer systems [AIAA PAPER 90-3966] p 71 A91-12480 of an advanced propeller p41 N91-10976 Procurement and testing of a 1/5 scale advanced [NASA-TM-103625] p 77 N91-11494 counter rotating propfan model PREDICTIONS PROPULSION [AIAA PAPER 90-3975] p 46 A91-12488 More accurate predictions with transonic Navier-Stokes Propulsion simulation for magnetically suspended wind Vortex structure of wakes behind an advanced propeller methods through improved turbulence modeling tunnel models at takeoff load conditions [NASA-CR-182093] p 53 N91-11027 p17 N91-10850 [AIAA PAPER 90-3978) p 72 A91-12491 PRESSURE A modal evaluation of noise generated by the front rotor PROPULSION SYSTEM CONFIGURATIONS The variable-cycle engine - A solution to the economical Measurement of unsteady blade surface pressure on of a counter-rotating prop-fan a single rotation large scale advanced prop-fan with [AIAA PAPER 90-3979] p 72 A91-12492 and environmental challenge of the future supersonic angular and wake inflow at Mach numbers from 0.02 to transport p 45 A91 -10969 Measurement of unsteady blade surface pressure on 0.70 a single rotation large scale advanced prop-fan with Propulsion systems for hypersonic transportation [NASA-CR-182123] p 47 N91-10065 angular and wake inflow at Mach numbers from 0.02 to p45 A91-10975 PRESSURE DISTRIBUTION 0.70 Configuration control and airworthiness management Finite element method for computation of transonic flow [NASA-CR-182123] p 47 N91-10065 p77 A91-12233 about wings from the pressure minimum integral PROPELLANT ADDITIVES Technology update of early gas turbine designs p4 A91-11838 Research and development of high-pressure-exponent [PNR-90710] p48 N91-10070 Estimation of the turbulent boundary layer pressure fuel-rich propellants Future supersonic transport populsion optimization wavenumber-frequency spectrum using a fixed probe [ONERA, TP NO. 1990-91] p 55 A91-11770 [PNR-90737] p48 N91-10071 pair PROPELLANT COMBUSTION PROPULSION SYSTEM PERFORMANCE [AIAA PAPER 90-3926] p 67 A91-12442 The instability of combustion in propulsion engines Future supersonic transport propulsion optimisation The screech of round choked jets, revisited p56 N91-10141 p45 A91-10968 [AIAA PAPER 90-3980] p 72 A91-12493 PROPELLER BLADES Optimisation of hybrid propulsion systems Wall interference studies The effect of swirl recovery vanes on the cruise noise p46 A91-10976 [PD-CF-9012] p59 N91-10232 of an advanced propeller Configuration control and airworthiness management Applications of a transonic wing design method [AIAA PAPER 90-3932] p 68 A91-12448 p77 A91-12233 p 21 N91-10890 Calculation of the pressure distribution on an oscillating Structure-borne noise transmission in the propfan test Technology update of early gas turbine designs assessment aircraft airfoil in incompressible flow considering nonlinear (PNR-90710) p 48 N9M0070 [AIAA PAPER 90-3966] p 71 A91-12480 effects p25 N91-10926 PROPULSIVE EFFICIENCY PRESSURE DRAG Unsteady blade pressure measurements for the SR-7A Progress in certifying F402-RR-408: The improved Determination of the pressure drag of airfoils by propeller at cruise conditions Pegasus engine for AV-8B and Harrier 2 plus integration of surface pressures [AIAA PAPER 90-4022] p 75 A91-12533 [PNR-90719] p40 N91-10056 [NASA-TM-102722] p 50 N91-10078 Measurement of unsteady blade surface pressure on PROTECTIVE COATINGS PRESSURE EFFECTS a single rotation large scale advanced prop-fan with Thermal barrier coatings • Microstructural investigation An Euler code prediction of near field to midfield sonic angular and wake inflow at Mach numbers from 0.02 to after annealing boom pressure signatures 0.70 [ONERA, TP NO. 1990-62] p 55 A91-T1751 [AIAA PAPER 90-4000] p7 A91-12513 [NASA-CR-182123] p 47 N91-10065 PROTOTYPES PRESSURE GRADIENTS PROPELLER FANS Inflight replanning for diversions p 27 N91 -10955 A study of implicit space-marching method for the The role of leading edge vortex flows in prop-fan PUMP IMPELLERS supersonic viscous flow over the blunt cone interaction noise Experiments on the aerodynamic noise sources in p4 A91-11831 [AIAA PAPER 90-3977] p 72 A91-12490 centrifugal turbomachinery PRESSURE MEASUREMENT Aeroacoustic effects of reduced aft tip speed at constant [AIAA PAPER 90-3948] p 69 A91-12464 Unsteady blade pressure measurements for the SR-7A thrust for a model counterrotation turboprop at takeoff PYROMETERS propeller at cruise conditions conditions Pyrometry for turbine blade development . [AIAA PAPER 90-4022] p 75 A91-12533 [NASA-TM-103608] p 76 N91-10703 p 57 A91-10336 PRESSURE OSCILLATIONS PROPELLER NOISE Modes of oscillation in a nonreacting ramjet combustor Application of computational methods in aeroacoustics flow p2 A91-10330 (AIAA PAPER 90-3917] p 67 A91-T2433 Coherent structure induced pressure fluctuations in an The effect of swirl recovery vanes on the cruise noise elliptic jet of an advanced propeller QUADRUPOLES [AIAA PAPER 90-3963] p 70 A91-12477 [AIAA PAPER 90-3932] p 68 A91-12448 Radiation integrals for sound generation by the Lighthill Suppression of flow-induced pressure oscillations in State-of-the-art of high-speed propeller noise prediction quadrupoles in propeller acoustics cavities - A multidisciplinary approach and comparison with [AIAA PAPER 90-3993] p 73 A91-12506 [AIAA PAPER 90-4018] p8 A91-12530 QUALITY CONTROL The instability of combustion in propulsion engines measured data [AIAA PAPER 90-3934] p 68 A91-12450 Introduction: Needs and approaches to reliability and p56 N91-10141 quality assurance in design and manufacture PRESSURE SENSORS Experimental/theoretical investigation of the sound field of an isolated propeller, including angle of incidence [PNR-90683] p60 N91-10297 Unsteady blade pressure measurements for the SR-7A Total quality management at Rolls-Royce PLC propeller at cruise conditions effects [AIAA PAPER 90-3952] p 69 A91-12468 [PNR-90759] p 60 N91-10298 [AIAA PAPER 90-4022) p 75 A91-12533 QUENCHING (COOLING) Prediction of the noise from a propeller at angle of PROBLEM SOLVING Influence of heat treatment on microstructure and attack Graphical interfaces for cooperative planning systems properties of an advanced high temperature titanium [AIAA PAPER 90-3954] p 70 A91-12470 p 27 N91-10956 alloy Use of the VP-200 computer for aerothermodynamic Noise radiation of propeller loading sources with angular [PNR-90689] p56 N91-11107 problems inflow [MBB/FE122/S/PUB/388] p 65 N91-11424 [AIAA PAPER 90-3955] p 70 A91-12471 PROCEDURES Structure-borne noise transmission in the propfan test A function-based approach to cockpit procedure aids assessment aircraft p27 N91-10953 [AIAA PAPER 90-3966] p 71 A91-12480 RADAR DATA Time-based aircraft/ATC operations study Interaction between rotors of a counter rotating Aircraft trajectories: Computation, prediction, control, p29 N91-10959 propeller volume 2: Air traffic handling and ground-based guidance PROCESS CONTROL (INDUSTRY) [AIAA PAPER 90-3976] p 7 A91-12489 of aircraft. Part 4: Air traffic handling. Part 5: Guidance Introduction: Needs and approaches to reliability and Radiation integrals'for sound generation by the Lighthill of aircraft in a time-based constrained environment. Part quality assurance in design and manufacture quadruples in propeller acoustics 6: Surveillance. Part 7: Meteorological forecasts. Part 8: [PNR-90683] p60 N91-10297 [AIAA PAPER 90-3993) p73A91-12506 Aircraft operation in air traffic handling simulation PRODUCTION MANAGEMENT [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 On the prediction of far field computational Total quality management at Rolls-Royce PLC RADAR FILTERS aeroacoustics of advanced propellers (PNR-90759] p60 N91-10298 The use of downlinked measurements to track civil [AIAA PAPER 90-3996) p 73 A91-12509 PROJECT MANAGEMENT aircraft p 34 N91-11004 Multi industry application of advanced materials Installation effects on counter rotating propeller noise RADAR IMAGERY [PNR-90764I p56 N91-10139 (AIAA PAPER 90-4023) p 75 A91-12534 Aircraft trajectory reconstitution on the basis of PROJECT PLANNING The effect of swirl recovery vanes on the cruise noise multi-radar plot information p 34 N91 -11002 The case of a hypersonic flight demonstrator of an'advanced propeller RADAR NETWORKS p54 A91-10978 [NASA-TM-103625] p 77 N91-11494 Aircraft trajectory reconstitution on the basis of PROP-FAN TECHNOLOGY Prediction of the noise from a propeller at angle of mufti-radar plot information p 34 N91-11002 Unsteady airioading panel method for prop-fans attack Bayesian multi-sensor tracking for advanced air traffic [AIAA PAPER 90-3914] p 67 A91-12430 [NASA-TM-103627] p 77 N91-11495 control systems p 34 N91-11003

A-19 RADAR RESOLUTION SUBJECT INDEX

RADAR RESOLUTION Computational fluid dynamics research and applications A modal evaluation of noise generated by the front rotor The high-resolution graphic display: A possible at NASA Langley Research Center p 17 N91-10841 of a counter-rotating prop-fan man/machine interface for a computer assisted ATC RESEARCH VEHICLES [AIAA PAPER 90-3979] p 72 A91-12492 management system p 31 N91-10989 OVRhyp, scramjet test aircraft Application of a state-space wake model to elastic blade RADAR TRACKING [NASA-CR-187009] p 38 N91-10041 flapping in hover p 13 N91-10006 Aircraft trajectories: Computation, prediction, control, NASA transport systems research vehicle B-737 data Transonic flow analysis for rotors. Part 3: volume 2: Air traffic handling and ground-based guidance link system and display formats Three-dimensional, quasi-steady, Euler calculation of aircraft. Part 4: Air traffic handling. Part 5: Guidance [NASA-TM-102717] p 44 N91-10058 [NASA-TP-2375] p 13 N91-10007 of aircraft in a time-based constrained environment. Part RESONANCE Wake coupling to full potential rotor analysis code 6: Surveillance. Part 7: Meteorological forecasts. Part 8: Aircraft interior noise reduction by alternate resonance [NASA-TM-102805] p 14 N91-10013 Aircraft operation in air traffic handling simulation tuning Aerodynamic interaction of counter rotating propellers [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 [NASA-CR-186879] p 76 N91-11488 p23 N91-10910 Bayesian multi-sensor tracking for advanced air traffic The aerodynamic effects of nozzle guide vane shock RESONANT VIBRATION control systems p 34 N91-11003 wave and wake passing on a transonic turbine rotor Large-amplitude vibrations of free-free tapered beams RADARSCOPES p24 N91-10915 p 57 A91-11199 The high-resolution graphic display: A possible The calculation of rotor/fuselage interaction for man/machine interface for a computer assisted ATC RETARDING two-dimensional bodies management system p 31 N91-10989 Suppression of flow-induced pressure oscillations in [NASA-TM-102855] p 25 N91-10933 RADIAL FLOW cavities ROTOR BLADES Interaction of two supersonic radial gas flows [ AIAA PAPER 90-4018 ] p 8 A91 -12530 Periodic rotor-blade aerodynamics including loading p6 A91-12018 RETROFITTING effects p2 A91-10337 RADIATION DISTRIBUTION Re-engining: Real stage 3 compliance plus other Basic helicopter aerodynamics — Book Radiation integrals for sound generation by the Lighthill benefits p3 A91-11701 quadrupoles in propeller acoustics [PNR-90755] p 48 N91-10075 Helicopter ground resonance p 36 A91-11723 [AIAA PAPER 90-3993] p 73 A91-12506 REUSABLE SPACECRAFT Interaction between rotors of a counter rotating RAMJET ENGINES The application of commercial airplane avionics propeller Numerical simulations of oscillatory cold flows in an techniques to advanced space transportation [AIAA PAPER 90-3976] p 7 A91-12489 axisymmetric ramjet combustor p2 A91-10329 [AIAA PAPER 90-3722) p1 A91-10114 Computational analysis of rotor-stator interaction in Modes of oscillation in a nonreacting ramjet combustor REVISIONS turbomachinery using zonal techniques flow p 2 A91 -10330 Inflight replanning for diversions p 27 N91-10955 p 10 A91-12764 Research and development of high-pressure-exponent RIBLETS Influence of unsteady aerodynamics on rotor blade fuel-rich propellants Riblets — for aerodynamic drag reduction of turbulent aeroelastic stability and response p 37 A91-12894 [ONERA, TP NO. 1990-91] p 55 A91-11770 skin friction p 59 A91-12694 Computation of transonic flow over elastic rotor blade Numerical simulation and active control of combustion RIGID ROTORS p 23 N91-10906 instability in a ramjet combustor A ray-acoustics approach to fuselage scattering of rotor ROTOR BLADES (TURBOMACHINERY) [AIAA PAPER 90-3930] p 46 A91-12446 noise Aeroacoustic effects of reduced aft tip speed at constant RANDOM VIBRATION [AIAA PAPER 90-4013] p 75 A91-12525 thrust for a model counterrotation turboprop at takeoff Prediction of turbulence generated random vibrational conditions RIGID STRUCTURES response of turbomachinery blading p 46 A91-11348 [AIAA PAPER 90-3933] p 68 A91-12449 Numerical simulation of acoustic diffraction of RAPID TRANSIT SYSTEMS ROTOR BODY INTERACTIONS two-dimensional rigid bodies in arbitrary flows Hydrogen in high-speed air transportation Computational analysis of rotor-stator interaction in [AIAA PAPER 90-3920] p 67 A91-12436 p55 A91-10966 turbomachinery using zonal techniques RAREFIED GAS DYNAMICS Coupled rotor/airframe vibration analysis p 10 A91-12764 Flow of a rarefied gas around a sphere in the presence p43 N91-11012 The calculation of rotor/fuselage interaction for of injection p 6 A91-12020 RISK two-dimensional bodies REAL TIME OPERATION Structural risk assessment and aircraft fleet [NASA-TM-102855] p 25 N91-10933 Generation of aircraft trajectories for on-line operation: maintenance p 61 N91-10321 ROTOR DYNAMICS Methods, techniques, and tools p 42 N91-10987 ROBUSTNESS (MATHEMATICS) Rotor wake/stator interaction noise-predictions versus A description and evaluation of TIMER: A time-based Performance-robustness trade off of eigenstructure data terminal flow-control concept p 32 N91-10996 assignment applied to rotorcraft p 49 A91-11155 [AIAA PAPER 90-3951 ] p 69 A91-12467 RECTANGULAR WINGS ROCKET ENGINES Application of a state-space wake model to elastic blade Localized linearization method for wings at high angle Research and development of high-pressure-exponent flapping in hover p 13 N91-10006 of attack p 12 A91-12896 fuel-rich propellants ROTOR SYSTEMS RESEARCH AIRCRAFT REFRACTORY MATERIALS [ONERA, TP NO. 1990-91] p 55 A91-11770 Rotor systems research aircraft risk-reduction shake Multi industry application of advanced materials ROLL test [PNR-90764] p56 N91-10139 Conical Euler simulation and active suppression of delta [NASA-TM-4186] p 38 N91-10045 RELIABILITY wing rocking motion ROTORS Introduction: Needs and approaches to reliability and [NASA-TM-102683] p 22 N91-10904 Experimental study of high-speed impulsive rotor noise quality assurance in design and manufacture ROTARY WING AIRCRAFT in a wind tunnel [PNR-90683] p60 N91-10297 Performance-robustness trade off of eigenstructure [ONERA. TP NO. 1990-123] p 66 A91-11786 Parallelized reliability estimation of reconfigurable assignment applied to rotorcraft p 49 A91-11155 computer networks Calculation of the rotor induced download on airfoils A technique for measuring unsteady aerodynamics in [NASA-CR-182101] p 65 N91-11430 p 19 N91-10864 turbomachinery p 58 A91-12421 RELIABILITY ANALYSIS Three-dimensional viscous drag prediction for rotor Experimental investigation on the effect of coolant Twenty years of Concorde - The experience of Air blades p 19 N91-10865 injection on turbine aerodynamic characteristics. Part 2: France p 25 A91-10959 The breakup of trailing-line vortices Effects of injection from rotor casing with 30 deg slanted Systems reliability assessment p 57 A91-11201 p20 N91-10867 holes RELIABILITY ENGINEERING ROTARY WINGS [NAL-TM-587-PT-2] p 47 N91-10060 Rotorcraft drivetrain life safety and reliability The ground resonance of a helicopter with a rotor of Prediction of turbine rotor-stator interaction using [AGARD-R-775] p 38 N91-10042 ideal and approximate symmetry considering the Navier-Stokes methods p 20 N91-10881 Helicopter transmissions: Design for safety and rotor-blade vibration in the thrust plane Coupled rotor/airframe vibration analysis reliability p 38 N91-10043 p36 A91-11725 p43 N91-11012 Drive system life and reliability p 38 N91-10044 The acoustic results of a United Techologies scale model ROUTES Progress in certifying F402-RR-408: The improved helicopter rotor tested at DNW Graphical interfaces for cooperative planning systems Pegasus engine for AV-8B and Harrier 2 plus [AIAA PAPER 90-4035] p 75 A91-12543 p27 N91-10956 [PNR-90719] p40 N91-10056 Euler/Navier-Stokes calculations of the flowfield of a RUNGE-KUTTA METHOD REMOTELY PILOTED VEHICLES helicopter rotor in hover and forward flight Euler/Navier-Stokes calculations of the flowfield of a Motion analysis of RPRVs using on-board and p11 A91-12765 helicopter rotor in hover and forward flight ground-based measurements p 37 A91-12224 Application of a state-space wake model to elastic blade p11 A91-12765 flapping in hover p 13 N91 -10006 RESCUE OPERATIONS Recent advances in Runge-Kutta schemes for solving Wake coupling to full potential rotor analysis code Air rescue in the Federal Republic of Germany 3-D Navier-Stokes equations p 17 N91-10851 [ETN-90-97878] p 28 N91-10963 [NASA-TM-102805] p 14 N91-10013 Rotor loads computation using singularity methods and RUNWAY LIGHTS RESEARCH AIRCRAFT application to the noise prediction Flight evaluation test of the PAPI (Precision Approach The need for a hypersonic demonstrator [ISL-PU-301/90] p 15 N91-10018 Path Indicator) System p54 A91-10977 [NAL-TM-592] p 29 N91-10966 ROTATING DISKS The case of a hypersonic flight demonstrator LD.V. applied to measurements between two discs in p54 A91-10978 high speed rotation Motion analysis of RPRVs using on-board and [ONERA, TP NO. 1990-94] p 58 A91-11773 ground-based measurements p 37 A91-12224 ROTOR AERODYNAMICS Supersonic combustion engine testbed, heat lightning Periodic rotor-blade aerodynamics including loading SAFETY FACTORS [NASA-CR-187010] p 47 N91-10061 effects p 2 A91-10337 Rotorcraft drivetrain life safety and reliability RESEARCH FACILITIES Stator/rotor interaction in a transonic turbine [AGARD-R-775] p 38 N91-10042 Configuration, function and performance of the flight p 2 A91-10340 Helicopter transmissions: Design for safety and simulation test facility and its motion simulation system Basic helicopter aerodynamics — Book reliability p 38 N91-10043 [NAL-TM-575] p 52 N91-10080 p3 A91-11701 Wind models for flight simulation p 53 N91-10975

A-20 SUBJECT INDEX SOUND TRANSMISSION

SATELLITE COMMUNICATION The aerodynamic effects of nozzle guide vane shock Generation of a buoyant plume of artificial smoke for Contribution of the satellite techniques to the wave and wake passing on a transonic turbine rotor airplane tests surveillance of air traffic p 35 N91 -11005 p24 N91-10915 IDOT/FAA/CT-90/9] p 43 N91-11015 SCALE MODELS SHOCK WAVES SMOKE ABATEMENT Experimental study of noise sources and acoustic Effect of energy release in the shock layer on supersonic Flight testing of two Allison T56 engines modified to propagation in a turbofan model flight p 6 A91-12016 the ARL developed low smoke configuration [AIAA PAPER 90-3950) P 69 A91-12466 Shock wave formation during interaction with a weak [ARL-PROP-TM-449] p 47 N91-10064 SCHEDULING discontinuity at the boundary of a local subsonic region SMOKE DETECTORS Time-based aircraft/ATC operations study p6 A91-12017 Generation of a buoyant plume of artificial smoke for p29 N91-10959 Comparison of shock wave rise time prediction airplane tests SCHLIEREN PHOTOGRAPHY techniques [DOT/FAA/CT-90/9] p 43 N91-11015 [AIAA PAPER 90-4001] p 74 A91-12514 Estimation of the turbulent spectral densities of the SOFTWARE TOOLS Optimum hypersonic airfoil with power law shock mass-density using two-dimensional Fourier transform of Time-based operations in an advanced ATC waves digitized schlieren pictures environment p 29 N91-10958 [DE90-014903J p 13 N91-10008 IONERA.TP NO. 1990-110) p4 A91-11782 Air traffic management and aircraft guidance in a zone More accurate predictions with transonic Navier-Stokes SEATS of convergence p 33 N91 -10998 methods through improved turbulence modeling Seat dynamic performance standards for a range of p 17 N91-10850 Application of computational fluid dynamics to sizes SHORT CRACKS three-dimensional bodies in hypersonic flow (DOT/FAA/CT-TN90/23] p 26 N91-10028 Short crack behaviour in AI-LJ alloy 2090 p62 N91-11174 SECONDARY INJECTION p62 N91-11243 Experiences in the use of ABAOUS for creep analysis Experimental investigation on the effect of coolant The growth of short cracks in 4340 steel and [PNR-90705] p63 N91-11266 injection on turbine aerodynamic characteristics. Part 2: aluminum-lithium 2090 p 62 N91 -11247 SOLID PROPELLANTS Effects of injection from rotor casing with 30 deg slanted Short and long fatigue crack growth in 2024-T3 under Propulsion simulation for magnetically suspended wind holes Fokker 100 spectrum loading p 63 N91-11248 tunnel models (NAL-TM-587-PT-2| p 47 N91-10060 SHORT TAKEOFF AIRCRAFT [NASA-CR-182093] p 53 N91-11027 SELF ORGANIZING SYSTEMS Noise characteristics of the Japan's experimental SONIC BOOMS A self-organizing stochastic control system adaptable powered lift STOL aircraft Supersonic air transport programs in the 60's to changing perturbation characteristics [AIAA PAPER 90-4014] p 75 A91-12526 p1 A91-10952 p65 A91-11353 The establishment and performance test of PAPI The sonic boom problem p1 A91-10964 SEPARATED FLOW (Precision Approach Path Indicator) System for NAL STOL Application of CFD to sonic boom near and mid flow-field Effect of acoustic excitation on stalled flows over an aircraft prediction airfoil [NAL-TM-579] p 28 N91-10030 [AIAA PAPER 90-3999 ] p7 A91-12512 [AIAA PAPER 90-4009] p 7 A91-12521 The actuator for the low-noise STOL test plane flight An Euler code prediction of near field to midfield sonic Computational aerodynamic simulation experience control system and its development test boom pressure signatures p11 A91-12771 [NAL-TM-574) p 37 N91-10038 [AIAA PAPER 90-4000] p7 A91-12513 Numerical computation of viscous flow about The full-body ground vibration tests using the low-noise Comparison of shock wave rise time prediction unconventional airfoil shapes STOL test plane techniques (NASA-CR-1873431 p 15 N91-10019 [NAL-TM-576] p 50 N91-10077 [ AIAA PAPER 90-4001 ] p 74 A91 -12514 Recent advances in Runge-Kutta schemes for solving NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12 The sonic boom of an oblique flying wing 3-D Navier-Stokes equations p 17 N91-10851 [NASA-CP-10038-VOL-2] p 20 N91-10868 [AIAA PAPER 90-4002] p 74 A91-12515 CFD for applications to aircraft aeroelasticity SHROUDED PROPELLERS Sonic boom focal zones due to tactical aircraft p 17 N91-10855 Rotor wake/stator interaction noise-predictions versus maneuvers Experimental investigation of the mechanisms data [AIAA PAPER 90-4003] p 74 A91-12516 underlying vortex kinematics in unsteady separated [AIAA PAPER 90-3951] p 69 A91-12467 The measurement of sonic boom waveforms and flows p 23 N91-10907 SHROUDS propagation characteristics - Techniques and challenges SERVICE LIFE Experimental investigation on the effect of coolant [AIAA PAPER 90-4004] p 74 A91-12517 Calculations of the service life of components under injection on turbine aerodynamic characteristics. Part 2: The design of two sonic boom wind .tunnel models from severe thermomechanical loads Effects of injection from rotor casing with 30 deg slanted conceptual aircraft which cruise at Mach numbers of 2.0 [ONERA. TP NO. 1990-63] p 58 A91-11752 holes and 3.0 Rotorcraft drivetrain lile safety and reliability [NAL-TM-587-PT-2] p 47 N91-10060 [AIAA PAPER 90-4026] p 52 A91-12536 [AGARD-R-775] p 38 N91-10042 SIMULATION Weak shock propagation through a turbulent Drive system life and reliability p 38 N91 -10044 NASA Computational Fluid Dynamics Conference. atmosphere SHEAR LAYERS Volume 1: Sessions 1-6 [AIAA PAPER 90-4031] p 75 A91-12540 Numerical simulation of 3-D supersonic free shear [NASA-CP-10038-VOL-1] p 16 N91-10839 Sonic boom environment under a supersonic military layers Time-based operations in an advanced ATC operating area [AIAA PAPER 90-3958] p7 A91-12472 environment p 29 N91-10958 [AIAA PAPER 90-4032) p 63 A91-12541 SHEARING Propulsion simulation for magnetically suspended wind Application of CFD to sonic boom near and mid flow-field Repeated buckling of composite shear panels tunnel models prediction p60 N91-10303 (NASA-CR-182093] p 53 N91-11027 [NASA-TM-102867] p 14 N91-10015 SHOCK LAYERS Parallelization on a multi-processor system of a solving SOUND FIELDS Effect of energy release in the shock layer on supersonic method for the unsteady Navier-Stokes equations at high Experimental/theoretical investigation of the sound field flight p6 A91-12016 Reynolds numbers of an isolated propeller, including angle of incidence SHOCK LOADS [ESA-TT-1116] p62 N91-11197 effects An accurate acoustic emission location method adapted SINGULARITY (MATHEMATICS) [AIAA PAPER 90-3952] p 69 A91-12468 for composite materials p 57 A91-11027 Rotor loads computation using singularity methods and Diffraction patterns in the acoustic field of a propeller SHOCK TESTS application to the noise prediction [AIAA PAPER 90-3994] p 73 A91-12507 Flow and acoustic properties of low Reynolds number [ISL-PU-301/90] p 15 N91-10018 SOUND GENERATORS underexpanded supersonic jets p 3 A91-11198 SKIN FRICTION Radiation integrals for sound generation by the Lighthill SHOCK TUNNELS Application of CFD to reduction of skin-friction drag quadruples in propeller acoustics The ISL hypersonic shock tunnel and its p8 A91-12692 [AIAA PAPER 90-3993] p 73 A91-12506 instrumentation Riblets — for aerodynamic drag reduction of turbulent Space-structure determination of the acoustic field [ISL-CO-213/89] p52 N91-10086 skin friction p 59 A91-12694 generated by a helicopter turboshaft engine SHOCK WAVE ATTENUATION SLENDER BODIES [AIAA PAPER 90-4012] p 46 A91-12524 Shock capturing using a pressure-correction method Vortex development on cruciform canard configurations SOUND PRESSURE p59 A91-12887 at supersonic speeds p5 A91-11843 Helicopter far-field acoustic levels as a function of Wind tunnel investigations of the appearance of shocks reduced main-rotor advancing blade-tip Mach number SLENDER CONES in the windward region of bodies with circular cross section [NASA-TM-102684] p 76 N91-10699 An experimental study of the laminar-turbulent transition at angle of attack SOUND PROPAGATION behind three-dimensional roughness in a boundary layer [DLR-FB-90-15] p 16 N91-10027 Application of computational methods in aeroacoustics on a sharp cone p6 A91-12014 SHOCK WAVE INTERACTION [AIAA PAPER 90-3917] p 67 A91-12433 SLOTS Transonic buffet on a supercritical aerofoil SOUND TRANSMISSION Viscous drag reduction via surface mass injection p2 A91-11157 Noise transmission characteristics of a large scale p9 A9M2698 A study of cylindrical interaction of turbulent boundary composite fuselage model layer/shock with swept compression corners SMALL PERTURBATION FLOW [AIAA PAPER 90-3965] p 71 A91-12479 p4 A91-11836 Optimum hypersonic airfoil with power law shock The use of spatial coherence techniques for identifying Fluctuations of a shock wave generated by boundary waves noise transmission paths on the MDC-UHB demonstrator layer separation p6 A91-12019 [DE90-014903] P 13 N91-10008 aircraft Aerodynamic heating in the interaction regions of shock SMOKE [AIAA PAPER 90-3968] p 71 A91-12482 waves and turbulent boundary layers induced by Structural tests of aircraft window assembly equipped Sound transmission through a high-temperature acoustic sweptback blunt fins p6 A91-12226 with smoke evacuation valve probe tube SHOCK WAVE PROPAGATION [DOT/FAA/CT-TN89/44] p 39 N91-10051 [AIAA PAPER 90-3991 ] p 73 A91-12504 Weak shock propagation through a turbulent Airplane systems modifications for improved cabin Aircraft interior noise reduction by alternate resonance atmosphere smoke evacuation tuning [AIAA PAPER 90-4031 ] P 75 A91-12540 [DOT/FAA/CT-TN90/24) p 39 N91-10052 [NASA-CR-186879] p 76 N91-11488

A-21 SOUND WAVES SUBJECT INDEX

SOUND WAVES Prediction of turbine rotor-stator interaction using Use of the VP-200 computer for aerothermodynamic Acoustic radiation from lifting airfoils in compressible Navier-Stokes methods p 20 N91-10881 problems subsonic flow STEADY FLOW [MBB/FE122/S/PUB/388] p 65 N91-11424 [AIAA PAPER 90-3911] p 66 A91-12427 Ejector thrust augmentors: Pulse-starting approach to SUPERCRITICAL AIRFOILS Thermoacoustics of unsteady combustion the second solution p 23 N91-10913 Transonic buffet on a supercritical aerofoil [AIAA PAPER 90-3928] p 67 A91-12444 Calculation of aerodynamic characteristics of airplane p2 A91-11157 An experimental technique of separating airborne and configurations at high angle of attack in steady and SUPERSONIC AIRCRAFT structure-borne noise using wavenumber-frequency unsteady flow p 42 N91-11009 The potential for a new era of supersonic and hypersonic spectrum Test cases for computation of internal flows in aero aviation p 1 A91-10961 [AIAA PAPER 90-3969] p 71 A91-12483 engine components The ATF battle shapes up p 36 A91-12062 Noise mechanisms of transonic vortex airfoil [AGARD-AR-275] p 49 N91-11022 A superlative from Sukhoi - The SU-27 interaction STEELS p 37 A91-12063 (AIAA PAPER 90-3972] p 71 A91-12485 The growth of short cracks in 4340 steel and Sonic boom focal zones due to tactical aircraft Transition control of instability waves over a flexible aluminum-lithium 2090 p 62 N91-11247 maneuvers surface in the presence of an acoustic field STOCHASTIC PROCESSES [AIAA PAPER 90-4003] p 74 A91-12516 [AIAA PAPER 90-4008] p 74 A91-12520 A self-organizing stochastic control system adaptable The design of two sonic boom wind tunnel models from SPACE TRANSPORTATION to changing perturbation characteristics conceptual aircraft which cruise at Mach numbers of 2.0 The application of commercial airplane avionics p65 A91-11353 and 3.0 techniques to advanced space transportation STRESS CORROSION CRACKING [AIAA PAPER 90-4026) p 52 A91-12536 [AIAA PAPER 90-3722] p1 A91-10114 Detection of concealed corrosion damage in aircraft Sonic boom environment under a supersonic military SPACE TRANSPORTATION SYSTEM structures using the eddy current method operating area System optimization structure and propulsion of a p58 A91-11974 [AIAA PAPER 90-4032] p 63 A91-12541 hypersonic space transportation system (Saenger) STRUCTURAL ANALYSIS Computational fluid dynamics design applications at p54 A91-10972 Body weight of hypersonic aircraft, part 1 supersonic/hypersonic speeds p 12 A91-12773 Hypersonic space transport system - Cruiser or [NASA-TM-101028] p 39 N91-10049 Application of unstructured grid methods to steady and accelerator? p 54 A91-10973 Structural tests of aircraft window assembly equipped unsteady aerodynamic problems p 17 N91 -10856 SPACECRAFT DESIGN with smoke evacuation valve SUPERSONIC COMBUSTION RAMJET ENGINES NASA Computational Fluid Dynamics Conference. [DOT/FAA/CT-TN89/44] p 39 N91-10051 Development of the Griffon II turbo-ramjet Volume 2: Sessions 7-12 Comparison of NASTRAN analysis with ground vibration p45 A91-10954 [NASA-CP-10038-VOL-2] p 20 N91-10868 results of UH-60A NASA/AEFA test configuration Numerical simulation of 3-D supersonic free shear Contributions in the field of aeroelastics on the occasion [NASA-CR-184565] p 61 N91-10333 layers of the 60th anniversary of Professor Dr.-lng. Habil. Hans Experimental measurement of structural power flow on [AIAA PAPER 90-3958) p7 A91-12472 Wilhelm Foersching an aircraft fuselage OVRhyp, scramjet test aircraft [ETN-90-97630] p 24 N91-10920 [NASA-CR-187352) p 61 N91-10335 [NASA-CR-187009] p 38 N91-10041 SPACECRAFT REENTRY STRUCTURAL STABILITY Supersonic combustion engine testbed, heat lightning Flight simulation programs for space plane Bifurcation analysis of axial flow compressor stability [NASA-CR-187010] p 47 N91-10061 [NAL-TM-594] p 55 N91-11035 p44 A91-10245 Application of CFD codes for the simulation of scramjet SPACECRAFT TRAJECTORIES Influence of chromium and molybdenum on the structural combustor flowfields p 20 N91-10873 Optimal trajectories of aircraft and spacecraft stability of a high strength damage tolerant P/M nickel SUPERSONIC COMMERCIAL AIR TRANSPORT p29 N91-10968 based alloy for turbine disks European Symposium on the Future of High Speed Air SPATIAL MARCHING [ONERA, TP NO. 1990-100] p 55 A91-11776 Transport, Strasbourg, France, Nov. 6-8, 1989, A study of implicit space-marching method for the STRUCTURAL VIBRATION Proceedings p1 A91-10951 supersonic viscous flow over the blunt cone Large-amplitude vibrations of free-free tapered beams Supersonic air transport programs in the 60's p4 A91-11831 p57 A91-11199 p 1 A91-10952 SPEED CONTROL Simulation investigations of the helicopter ground Commercial supersonic operations - Thirteen years of Four dimensional navigation in air traffic with 4-D resonance p 36 A91-11724 experience with Concorde p 36 A91-10957 navigation aircraft p 31 N91-10991 STRUCTURAL WEIGHT Twenty years of Concorde - The experience of Air SPHEROIDS Body weight of hypersonic aircraft, part 1 France p 25 A91-10959 Flow of a rarefied gas around a sphere in the presence [NASA-TM-101028] p 39 N91-10049 The potential for a new era of supersonic and hypersonic of injection p6 A91-12020 SUBSONIC AIRCRAFT aviation p 1 A91-10961 SPRAYED COATINGS The calculation method for subsonic longitudinal and The high speed market in the next three decades Applications of thermally sprayed coating systems in lateral aerodynamic characteristics of complete aircraft p77 A91-10963 aero engines configuration p5 A91-11844 A case study in fostering international HSCT [PNR-90750] p48 N91-10072 Analysis of the PTA external noise data and comparison collaboration p 77 A91-10970 STAGE SEPARATION with predictions Hypersonic aircraft studies p2 A91-10971 System optimization structure and propulsion of a [AIAA PAPER 90-3935] p 68 A91-12451 Future supersonic transport populsion optimization hypersonic space transportation system (Saenger) Subsonic airfoil design p9 A91-12756 [PNR-90737] p48 N91-10071 p54 A91-10972 SUBSONIC FLOW SUPERSONIC CRUISE AIRCRAFT RESEARCH STAGNATION PRESSURE Prediction of turbulence generated random vibrational Commercial supersonic operations - Thirteen years of Prediction of inviscid stagnation pressure losses in response of turbomachinery blading p 46 A91-11348 experience with Concorde p 36 A91-10957 supersonic inlet flows p 12 A91-12903 Shock wave formation during interaction with a weak SST airframe integration for a Mach 2 transport STANDARDIZATION discontinuity at the boundary of a local subsonic region p36 A91-10967 Short crack growth under realistic flight loading: Model p6 A91-12017 SUPERSONIC FLIGHT predictions and experimental results for Al 2024 and AI-Li Acoustic radiation from lifting airfoils in compressible NACA/NASA supersonic flight research 2090 p62 N91-11246 subsonic flow p 1 A91 -10953 STANDARDS [AIAA PAPER 90-3911] p 66 A91-12427 Effect of energy release in the shock layer on supersonic Seat dynamic performance standards for a range of Coherent structure induced pressure fluctuations in an flight p6 A91-12016 sizes elliptic |et SUPERSONIC FLOW [DOT/FAA/CT-TN90/23] p 26 N91-10028 [ AIAA PAPER 90-3963 ] p 70 A91 -12477 Flow and acoustic properties of low Reynolds number STATE ESTIMATION Three-dimensional viscous/inviscid coupling in subsonic underexpanded supersonic jets p 3 A91 -11198 Comparison of a mathematical one-point model and a flow A study of implicit space-marching method for the multi-point model of aircraft motion in moving air [REPT-B-24] P15 N91-10023 supersonic viscous flow over the blunt cone p41 N91-10969 Calculation of three-dimensional viscous/inviscid p4 A91-11831 Vortex development on cruciform canard configurations STATIC STABILITY interaction in subsonic flow at supersonic speeds p5 A91-11843 Design technologies utilized in the development of the [REPT-B-25] p 16 N91-10024 B-2 flight control system Determination of the pressure drag of airfoils by An approximate calculating method of [AIAA PAPER 90-3254] p 50 A91-12928 integration of surface pressures supersonic/hypersonic unsteady aerodynamic forces of [NASA-TM-102722] p 50 N91-1u"078 airfoils p5 A91-11845 STATIC TESTS Unsteady wind tunnel wall interferences in subsonic and An accurate acoustic emission location method adapted An experimental study of the laminar-turbulent transition transonic profile flows p 53 N91-10928 for composite materials ' p 57 A91-11027 behind three-dimensional roughness in a boundary layer SUBSONIC FLUTTER on a sharp cone p6 A91-12014 Differential Global Positioning System (DQPS) test Determination of unsteady aerodynamic forces on Interaction of two supersonic radial gas flows plan engines with a view to flutter investigations [DOT/FAA/CT-TN90/15] p 29 N91-10034 p6 A91-12018 p48 N91-10927 Fluctuations of a shock wave generated by boundary STATISTICAL ANALYSIS SUBSONIC SPEED layer separation p6 A91-12019 Application of flight path reconstruction algorithms for Aeroacoustic effects of reduced aft tip speed at constant Numerical simulation of 3-D supersonic free shear flight data of helicopter thrust for a model counterrotation turboprop at takeoff [NAL-TM-582] p 28 N91-10031 conditions layers STATOR BLADES [NASA-TM-103608] p 76 N91-10703 [AIAA PAPER 90-3958] p7 A91-12472 Computational analysis of rotor-stator interaction in SUPERCOMPUTERS Numerical simulation of supersonic mixing layer using turbomachinery using zonal techniques NASA Computational Fluid Dynamics Conference. high resolution scheme p10 A91-12764 Volume 1: Sessions 1-6 [AIAA PAPER 90-4025] p8 A91-12535 STATORS [NASA-CP-10038-VOL-1] p 16 N91-10839 Prediction of inviscid stagnation pressure losses in Rotor wake/stator interaction noise-predictions versus NASA Computational Fluid Dynamics Conference. supersonic inlet flows p 12 A91-12903 data Volume 2: Sessions 7-12 Evaluation of the ZONA51D program [AIAA PAPER 90-3951 ] p 69 A91-12467 [NASA-CP-10038-VOL-2] p 20 N91-10868 [REPT-B-28] p 16 N91-10025

A-22 SUBJECTINDEX THRUST-WEIGHT RATIO

Navier-Stokes solutions for flows related to store Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal separation p 18 N91 -10861 Oxidation Tester) Application of CFD codes for the simulation of scramjet T-56 ENGINE [DE90-010929] p 56 N91-11128 combustor flowfields p 20 N91-10873 Flight testing of two Allison T56 engines modified to THERMAL STRESSES the ARL developed low smoke configuration Calculations of the service life of components under SUPERSONIC INLETS [ARL-PROP-TM-449] p 47 N91-10064 CFO analysis for high speed inlets p 21 N91-10888 severe thermomechanica) loads TAIL ASSEMBLIES (ONERA. TP NO. 1990-63] p 58 A91-11752 SUPERSONIC JET FLOW Grid generation and inviscid flow computation about THREE DIMENSIONAL BODIES Instability of a supersonic shock-free elliptic jet aircraft geometries P 18 N91-10857 Application of computational fluid dynamics to [AIAA PAPER 90-3959] p7 A91-12473 TAILLESS AIRCRAFT three-dimensional bodies in hypersonic flow An evaluation of various concepts of reducing The sonic boom of an oblique frying wing p62 N91-11174 [AIAA PAPER 90-4002] p 74 A91-12515 supersonic jet noise THREE DIMENSIONAL BOUNDARY LAYER (AIAA PAPER 90-3982] p 72 A91-12495 TAKEOFF A three-dimensional boundary layer on bodies with a Vortex structure of wakes behind an advanced propeller SUPERSONIC SPEED slight cross-sectional asymmetry at small angles of Application of CFD to sonic boom near and mid flow-field at takeoff load conditions attack p5 A91-11909 [AIAA PAPER 90-3978] p 72 A91-12491 prediction An experimental study of the laminar-turbulent transition [AIAA PAPER 90-3999] p7 A91-12512 Optimal trajectories of aircraft and spacecraft p 29 N91-10968 behind three-dimensional roughness in a boundary layer SUPERSONIC TRANSPORTS Wind models for night simulation p 53 N91-10975 on a sharp cone p6 A9M2014 SST airframe integration for a Mach 2 transport Experimental study of instability . modes in a p36 A91-10967 Expert systems for the generation of thermal area arrival paths for civil transport p 32 N91 -10995 three-dimensional boundary layer p 59 A91-12888 Future supersonic transport propulsion optimisation Flight simulation programs for space plane THREE DIMENSIONAL FLOW p45 A91-10968 [NAL-TM-594] p 55 N91-11035 Practical developments in holographic interferometry The variable-cycle engine - A solution to the economical TANKER AIRCRAFT p57 A91-11152 and environmental challenge of the future supersonic The aerodynamic interference between tanker and A three-dimensional incompressible Euler flow solution transport p 45 A91-10969 receiver aircraft during air-to-air refuelling in turbomachinery p5 A91-11841 SUPERSONIC TURBINES p3 A91-11159 Numerical simulation of 3-D supersonic free shear The aerodynamic effects of nozzle guide vane shock TARGET RECOGNITION layers wave and wake passing on a transonic turbine rotor Detection of airplanes in aerial imagery [AIAA PAPER 90-3958] p 7 A91-12472 p24 N91-10915 p 59 A91-12824 An Euler code prediction of near field to midfield sonic SUPERSONIC WIND TUNNELS TECHNOLOGICAL FORECASTING boom pressure signatures NACA/NASA supersonic flight research Assessing the market for high speed air travel in the [AIAA PAPER 90-4000] p 7 A91-12513 p 1 A91-10953 21st century p 77 A91-10962 Formulation of three-dimensional, hodograph method The high speed market in the next three decades Ejector thrust augmentors: Pulse-starting approach to and separable solutions for nonlinear transonic flows p77 A91-10963 the second solution p 23 N9M0913 p 12 A9M2886 SURFACE FINISHING Hypersonic space transport system - Cruiser or accelerator? p 54 A91-10973 Modeling blade/vortex interactions Applications of thermally sprayed coating systems in [ISL-R-107/89] p 14 N91-10016 aero engines Future directions for applied computational fluid Aeroelastic analysis of wings using the Euler equations [PNR-90750] p48 N91-10072 dynamics p 59 A91-12775 with a deforming mesh SURFACE ROUGHNESS TECHNOLOGY TRANSFER The application of commercial airplane avionics [NASA-TM-102733] p 15 N91-10020 Viscous drag reduction via surface mass injection Three-dimensional viscous/inviscid coupling in subsonic p9 A91-12698 techniques to advanced space transportation [AIAA PAPER 90-3722] pi A91-10114 flow SURFACE TEMPERATURE TECHNOLOGY UTILIZATION [REPT-B-24] p 15 N91-10023 Determination of kinetic heating on wind tunnel models Design technologies utilized in the development of the Calculation of three-dimensional viscous/inviscid by the surface temperature method B-2 flight control system interaction in subsonic flow [ONERA, TP NO. 1990-104] p4 A91-11779 [AIAA PAPER 90-3254] p 50 A91-12928 [REPT-B-25] p16 N91-10024 SURVEILLANCE RADAR Technology update of early gas turbine designs Numerical investigations in three-dimensional internal The use of downlinked measurements to track civil [PNR-90710] p48 N91-10070 flows aircraft p 34 N91-11004 Multi industry application of advanced materials [ NASA-CR-186958) p 52 N91-10083 Contribution of the satellite techniques to the [PNR-90764] p 56 N91-10139 Recent advances in Runge-Kutta schemes for solving surveillance of air traffic p 35 N91-11005 TEMPERATURE EFFECTS 3-D Navier-Stokes equations p 17 N91-10851 SWEEP ANGLE Numerical simulation of hypersonic flow around a space Navier-Stokes solutions about the F/A-18 forebody-LEX Aerodynamic heating in the interaction regions of shock plane. Part 3: Analysis of aerothermodynamic heating configuration p 18 N91-10860 waves and turbulent boundary layers induced by [NAL-TR-1027T] p 14 N91-10011 Calculation of the rotor induced download on airfoils sweptback blunt fins p6 A91-12226 Developments to enhance meteorological forecasting p 19 N91-10864 SWEPT WINGS for air traffic services p 64 N91 -11006 CFD analysis for high speed inlets p 21 N91-10888 Mathematical modelling for analysis of nonlinear aircraft TENSILE PROPERTIES dynamics p 50 A91-11820 Influence of heat treatment on microstructure and Test cases for computation of internal flows in aero engine components Experimental study of instability modes in a properties of an advanced high temperature titanium [AGARD-AR-275] p 49 N91-11022 three-dimensional boundary layer p 59 A91-12888 alloy [PNR-90689] P56 N91-11107 Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Vortex instabilities in 3D boundary layers: The Oxidation Tester) relationship between Goertler and crossflow vortices TENSILE TESTS Short crack behaviour in AI-LJ alloy 2090 [DE90-010929] p 56 N91-11128 [NASA-CR-187456] p 15 N91-10022 p62 N91-11243 THREE DIMENSIONAL MODELS CFD for applications to aircraft aeroelasticity TEST FACILITIES Three-dimensional combustor performance validation p 17 N91-10855 Effects of coolant injection on turbine aerodynamic with high-density fuels p 55 A91-10345 SWIRLING characteristics. Part 1: Test turbine and apparatus Modeling blade/vortex interactions The effect of swirl recovery vanes on the cruise noise [NAL-TM-585-PT-1] p 47 N91-10059 [ISL-R-107/89] p 14 N91-10016 of an advanced propeller Aviation Safety/Automation Program Conference Numerical simulation of rotorcraft p 19 N91-10863 [AIAA PAPER 90-3932] p 68 A91-12448 [NASA-CP-3090] P26 N91-10936 SWITCHES A flight test facility design for examining digital Three-dimensional viscous drag prediction for rotor Douglas flight deck design philosophy information transfer p 28 N91-10962 blades p 19 N91-10865 p40 N91-10939 Test launch for turboaircratt engine. Description of the Three dimensional unstructured grids for the solution SYSTEM FAILURES installation of the Euler equations p 22 N91 -10893 Automatic determination of fault effects on aircraft [ILA-87-A-02] p48 N91-11018 THRUST functionality TEST STANDS Aeroacoustic effects of reduced aft tip speed at constant [NASA-CR-181352] p 37 N91-10039 Supersonic combustion engine testbed. heat lightning thrust for a model counterrotation turboprop at takeoff Drive system life and reliability p 38 N91-10044 [NASA-CR-187010] p47 N91-10061 conditions Douglas flight deck design philosophy THERMAL ANALYSIS (AIAA PAPER 90-3933] p 68 A91-12449 p40 N91-10939 Thermal analysis of engine inlet anti-icing systems THRUST AUGMENTATION p35 A91-10341 Development of the Griffon II turbo-ramjet Fault recovery recommendation p 27 N91-10952 THERMAL DEGRADATION p 45 A91-10954 Parallelized reliability estimation of reconfigurable Thermal stability of jet fuel Ejector thrust augmentors: Pulse-starting approach to computer networks [DE90-016801] p56 N91-10188 the second solution p 23 N91-10913 [NASA-CR-182101] p 65 N91-11430 THERMAL FATIGUE THRUST CONTROL SYSTEMS ENGINEERING Calculations of the service life of components under Aero engine design factors for a low fuel price Design of the derivative balance for the transonic wind severe thermomechanical loads scenario tunnel p 53 N91 -10925 [ONERA, TP NO. 1990-63] p 58 A91-11752 [PNR-90681] p47 N9M0066 Cockpit avionics integration and automation THERMAL PROTECTION THRUST VECTOR CONTROL p44 N91 -10938 Thermal barrier coatings • Microstructural investigation Harrier - The next 30 years p 36 A91-11715 SYSTEMS INTEGRATION after annealing Nonlinear feedback control for high alpha flight Cockpit avionics integration and automation [ONERA, TP NO. 1990-62] p 55 A91-11751 [NASA-CR-186545] p 39 N91-10047 p44 N91-10938 THERMAL STABILITY THRUST-WEIGHT RATIO Integration of aircraft capability in air traffic handling Thermal stability of jet fuel Optimisation of hybrid propulsion systems simulations p 35 N91-11007 [DE90-016801 ] p56 N91-10188 p46 A91-10976

A-23 THUNDERSTORMS SUBJECT INDEX

THUNDERSTORMS The application of trajectory prediction algorithms for Computation of maximum gust loads in nonlinear aircraft Development and application of linear and nonlinear planning purposes in the Netherlands ATC-system using a new method based on the matched filter approach methods for interpretation of lightning strikes to in-flight p65 N91-10986 and numerical optimization p 60 N91-10317 aircraft Generation of aircraft trajectories for on-line operation: A quarter of a century of aeroelastic cooperation INASA-CR-3974] p 64 N91-10548 Methods, techniques, and tools p 42 N91 -10987 between research and industry (a review). Part 2: Transport TILT ROTOR AIRCRAFT The 4-D descent trajectory generation techniques under airplanes and other civil applications p 40 N91-10932 Some far-field acoustics characteristics of the XV-15 realistic operating conditions p 32 N91-10994 Summary of the industry/NASA/FAA workshop on tilt-rotor aircraft Expert systems for the generation of thermal area arrival philosophy of automation: Promises and realities | AIAA PAPER 90-3971] p 71 A91-12484 paths for civil transport p 32 N91-10995 p44 N91-10942 Application of computational fluid dynamic methods to Air traffic management and aircraft guidance in a zone Overview of error-tolerant cockpit research the component aerodynamic design of the V-22 Osprey of convergence p 33 N91-10998 p40 N91-10949 tilt rotor vehicle p 11 A91-12768 Developments to enhance meteorological forecasting TRANSPORTATION NETWORKS TIME for air traffic services p 64 N91-11006 Airport system capacity strategic choices Time-based operations in an advanced ATC TRANSIENT PRESSURES [SR-226] p30 N91-10979 environment p 29 N91-10958 Weak shock propagation through a turbulent TRIANGULATION TIME DEPENDENCE atmosphere Solution of the two-dimensional Euler equations by a The 4-D descent trajectory generation techniques under [AIAA PAPER 90-4031J p 75 A91-12540 finite volume discretization on unstructured triangular realistic operating conditions p 32 N91 -10994 TRANSMISSIONS (MACHINE ELEMENTS) meshes A description and evaluation of TIMER: A time-based Helicopter transmissions: Design for safety and [ESA-TT-1135] p66 N91-11473 terminal flow-control concept p 32 N91-10996 reliability p 38 N91-10043 TUNING . Use of 4-D RNAV in time-based en route arrival TRANSONIC FLOW Aircraft interior noise reduction by alternate resonance metering p 33 N91-10997 Stator/rotor interaction in a transonic turbine tuning TIME SERIES ANALYSIS p2 A91-10340 [NASA-CR-186879] p 76 N91-11488 Time series and correlation of pulsations observed Transonic buffet on a supercritical aerofoil TURBINE BLADES simultaneously by two aircraft p 63 A91 -11072 p2 A91-11157 Pyrometry for turbine blade development TIP SPEED Detailed measurements of the flow field at the outlet p 57 A91-10336 Aeroacoustic effects of reduced aft tip speed at constant of a backswept transonic centrifugal impeller equipped with Optimization of the arrangement of the front and rear thrust for a model counterrotation turboprop at takeoff a vaned diffuser blade rows of a tandem blade cascade conditions [ONERA, TP NO. 1990-101] p4 A91-11777 p46 A91-11349 [NASA-TM-103608] p 76 N91-10703 Finite element method for computation of transonic flow An efficient method for solving transonic flow about TITANIUM ALLOYS about wings from the pressure minimum integral plane cascades with a large nosing p 4 A91-11839 Influence of heat treatment on microstructure and p4 A91-11838 Reliability of results of the capillary testing of gas turbine properties of an advanced high temperature titanium An efficient method for solving transonic flow about engine components during repairs p 58 A91-12036 alloy plane cascades with a large nosing p4 A91-11839 Heat transfer in aero engine gas turbines, part 1 [PNR-90689] p56 N91-11107 Calculation of boundary-layer flows on low Reynolds [PNR-90754-PT-1] p 48 N91-10074 TOLERANCES (MECHANICS) number and transonic airfoils p 5 A91-11840 Design/development issues for high bypass ratio fans Introduction: Needs and approaches to reliability and Application of LU-ADI algorithm in two-dimension [PNR-90758] p48 N91-10076 quality assurance in design and manufacture transonic flow p5 A91-11848 TURBINE ENGINES [PNR-90683] p 60 N91-10297 Inverse airfoil design - A classical approach updated Stator/rotor interaction in a transonic turbine Short and long fatigue crack growth in 2024-T3 under for transonic applications p 10 A91-12758 p2 A91-10340 Fokker 100 spectrum loading p 63 N91-11248 Formulation of three-dimensional hodograph method Supersonic/hypersonic propulsion systems - Exhaust TORSIONAL VIBRATION and separable solutions for nonlinear transonic flows emission characteristics and abatement technology Prediction of turbulence generated random vibrational p 12 A91-12886 p 45 A91-10965 response of turbomachinery blading p 46 A91-11348 Shock capturing using a pressure-correction method The evolution of the bypass engine TRACKING (POSITION) p 59 A91-12887 [PNR-90707] p47 N91-10068 Differential Global Positioning System (DGPS) test Transonic computations on a natural grid TURBINE WHEELS plan p13 A91-12904 Influence of chromium and molybdenum on the structural [DOT/FAA/CT-TN90/15] p 29 N91-10034 Transonic flow analysis for rotors. Part 3: stability of a high strength damage tolerant P/M nickel TRACKING FILTERS Three-dimensional, quasi-steady, Euler calculation based alloy for turbine disks Bayesian multi-sensor tracking for advanced air traffic [NASA-TP-2375] p 13 N91-10007 [ONERA, TP NO. 1990-100] p 55 A91-11776 control systems . p 34 N91-11003 Wake coupling to full potential rotor analysis code TURBINES TRAILING EDGES [NASA-TM-102805] p 14 N91-10013 Prediction of turbine rotor-stator interaction using The effects of aerofoil profile on wing buffet at low A contribution to the numerical solution of transonic flow Navier-Stokes methods p 20 N91-10881 speeds p2 A91-11151 around a delta wing by solving Navier-Stokes equations TURBOCOMPRESSORS Innovation with computational aerodynamics - The [DLR-FB-90-13] p 16 N91-10026 Bifurcation analysis of axial flow compressor stability divergent trailing-edge airfoil p 10 A91-12759 Recent advances in Runge-Kutta schemes for solving p44 A91-10245 TRAINING AIRCRAFT 3-D Navier-Stokes equations p 17 N91-10851 Automated design of controlled diffusion blades Practical aerodynamics and flight dynamics of Yak-52 A zonal Navier-Stokes methodology for flow simulation p21 N91-10883 and Yak-55 aircraft — Russian book p 13 A91-12911 about a complete aircraft p 18 N91-10858 TURBOFAN AIRCRAFT TRAJECTORY ANALYSIS Navier-Stokes solutions for flows related to store Aircraft en route noise annoyance Aircraft trajectory reconstitution on the basis of separation p 18 N91-10861 [AIAA PAPER 90-4028] p 63 A91-12537 multi-radar plot information p 34 N91-11002 TranAir: Recent advances and applications TURBOFAN ENGINES TRAJECTORY CONTROL p 19 N91-10862 Future supersonic transport propulsion optimisation Prediction of aircraft trajectories p 42 N91-10984 Prediction of effects of wing contour modifications on p45 A91-10968 The application of trajectory prediction algorithms for low-speed maximum lift and transonic performance for the Suppression of fatigue inducing cavity acoustic modes planning purposes in the Netherlands ATC-system EA-6B aircraft on turbo fan engines p 65 N91-10986 [NASA-TP-3046] p 22 N91-10902 [AIAA PAPER 90-3941] p 69 A91-12457 The 4-D control of current air carriers in the present Computation of transonic flow over elastic rotor blade Experimental study of noise sources and acoustic environment: Objectives, status, and plans p23 N91-10906 propagation in a turbofan model p 31 N91-10990 The aerodynamic effects of nozzle guide vane shock [AIAA PAPER 90-3950] p 69 A91-12466 TRAJECTORY OPTIMIZATION wave and wake passing on a transonic turbine rotor Re-engining: Real stage 3 compliance plus other Aircraft trajectories: Computation, prediction, control, p24 N91-10915 benefits volume 1. Part 1: Fundamentals. Part 2: Flight in critical Implicit flux-split Euler schemes for unsteady [PNR-90755] .p48 N91-10075 atmospheric conditions. Part 3: Impact of new on-board aerodynamic analysis involving unstructured dynamic TURBOFANS technologies on aircraft operation meshes Holographic interferometry for flow visualization studies (AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 [NASA-TM-102732] p 24 N91-10918 in high speed fans p 46 A91-11351 Critical aspects of trajectory prediction: Flight in Unsteady wind tunnel wall interferences in subsonic and Space-structure determination of the acoustic field non-uniform wind p 41 N91-10971 transonic profile flows p 53 N91 -10928 generated by a helicopter turboshaft engine [AIAA PAPER 90-4012] p 46 A91-12524 Aircraft trajectory: Prediction and control in the air TRANSONIC FLUTTER Future supersonic transport populsion optimization transport flight management computer systems Determination of unsteady aerodynamic forces on engines with a view to flutter investigations [PNR-90737] p48 N91-10071 p 41 N91-10976 p48 N91-10927 Re-engining: Real stage 3 .compliance plus other Aircraft trajectories: Computation, prediction, control. TRANSONIC SPEED benefits Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. Applications of a transonic wing design method [PNR-90755] p48 N91-10075 Part 11: List of contributors p21 N91-10890 Design/development issues for high bypass ratio fans [AGARD-AG-301-VOL-3-PT-9-11] p 30 N91-10978 TRANSONIC WIND TUNNELS [PNR-90758] p48 N91-10076 Aircraft trajectories: Computation, prediction, control, Design of the derivative balance for the transonic wind TURBOJET ENGINES volume 2: Air traffic handling and ground-based guidance tunnel p 53 N91-10925 Experimental study of noise sources and acoustic of aircraft. Part 4: Air traffic handling. Part 5: Guidance TRANSPORT AIRCRAFT. propagation in a turbofan model of aircraft in a time-based constrained environment. Part Hypersonic aircraft studies p2 A91-10971 [AIAA PAPER 90-3950] p 69 A91-12466 6: Surveillance. Part 7: Meteorological forecasts. Part 8: Hypersonic space transport system - Cruiser or TURBOMACHINE BLADES Aircraft operation in air traffic handling simulation accelerator? p 54 A91-10973 Prediction of turbulence generated random vibrational [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 Basic materials and structures aspects for hypersonic response of turbomachinery blading p 46 A91-11348 Optimum on-line handling of air traffic over Western transport vehicles (HTV) p 54 A91-10974 TURBOMACHINERY Europe p 30 N91 -10982 Propulsion systems for hypersonic transportation A technique for measuring unsteady aerodynamics in Prediction of aircraft trajectories p 42 N91-10984 p45 A91-10975 turbomachinery p 58 A91-12421

A-24 SUBJECT INDEX VIBRATION

Computational analysis of rotor-stator interaction in Aerodynamic interaction of counter rotating propellers Application of unstructured grid methods to steady and turbomachinery using zonal techniques p23 N91-10910 unsteady aerodynamic problems p 17 N91-10856 p 10 A91-12764 Numerical calculations for flows past an unconventional Conical Euler simulation and active suppression of delta Prediction of turbine rotor-stator interaction using airfoil p24 N91-10916 wing rocking motion Navier-Stokes methods p 20 N91-10881 TURBULENT JETS [NASA-TM-102683] p 22 N91-10904 Flow and acoustic properties of low Reynolds number TURBOPROP AIRCRAFT Implicit flux-split Euler schemes for unsteady underexpanded supersonic jets p 3 A91 -11198 Prediction of the noise from a propeller at angle of aerodynamic analysis involving unstructured dynamic attack Time-dependent jet flow and noise computations [AIAA PAPER 90-3961 ] p 70 A91-12475 meshes [AIAA PAPER 90-3954] p 70 A91-12470 [NASA-TM-102732] p 24 N91-10918 Aircraft en route noise annoyance TVD SCHEMES Temporal-adaptive Euler/Navier-Stokes algorithm for [AIAA PAPER 90-4028] p 63 A91-12537 Numerical simulation of hypersonic flow around a space unsteady aerodynamic analysis of airfoils using TURBORAMJET ENGINES plane. Part 3: Analysis of aerothermodynamic heating unstructured dynamic meshes Hypersonic aircraft studies p 2 A91-10971 [NAL-TR-1027T] p 14 N91-10011 [NASA-TM-102734] p 24 N91-10919 System optimization structure and propulsion of a TWO DIMENSIONAL BODIES hypersonic space transportation system (Saenger) Numerical simulation of acoustic diffraction of Contributions in the field of aeroelastics on the occasion p54 A91-10972 two-dimensional rigid bodies in arbitrary flows of the 60th anniversary of Professor Or.-lng. Habil. Hans The case of a hypersonic flight demonstrator [AIAA PAPER 90-3920] p 67 A91-12436 Wilhelm Foersching pS4 A91-10978 The calculation of rotor/fuselage interaction for [ETN-90-97630] p 24 N91-10920 TURBULENCE two-dimensional bodies Determination of unsteady aerodynamic forces on More accurate predictions with transonic Navier-Stokes [NASA-TM-102855] p 25 N91-10933 engines with a view to flutter investigations methods through improved turbulence modeling TWO DIMENSIONAL FLOW p 48 N91-10927 p 17 N91-10850 Practical developments in holographic imerferometry Calculation of aerodynamic characteristics of airplane TURBULENCE EFFECTS p57 A91-11152 configurations at high angle of attack in steady and Static and dynamic aeroelastic characterization of an Solution of the Euler equations on unstructured grids unsteady How p 42 N91-11009 aerodynamically heated generic hypersonic aircraft for two-dimensional compressible flow p 3 A91 -11160 Development and application of the time domain panel configuration p61 N91-10320 L.D.V. applied to'measurements between two discs in method p 43 N91-11010 TURBULENCE MODELS high speed rotation UNSTEADY FLOW [ONERA. TP NO. 1990-94] p 58 A91-11773 Numerical computation of viscous flow about A technique for measuring unsteady aerodynamics in Application of LU-ADI algorithm in two-dimension unconventional airfoil shapes turbomachinery p 58 A91-12421 transonic flow p5 A91 -11848 [NASA-CR-187343] p 15 N91-10019 Suppression of flow-induced pressure oscillations in NASA Computational Fluid Dynamics Conference. Low Mach number Euler computations p5 A91-11900 cavities Volume 1: Sessions 1-6 [AIAA PAPER 90-4018] p8 A91-12530 [NASA-CP-10038-VOL-1] p 16 N91-10839 Vertex-based finite-volume solution of the Unsteady blade pressure measurements for the SR-7A More accurate predictions with transonic Navier-Stokes two-dimensional Navier-Stokes equations propeller at cruise conditions methods through improved turbulence modeling p59 A91-12900 [AIAA PAPER 90-4022] p 75 A91-12533 p 17 N91-10850 Modeling blade/vortex interactions Recent advances in Runge-Kutta schemes for solving [ISL-R-107/89] p 14 N91-10016 Measurement of unsteady blade surface pressure on 3-0 Navier-Stokes equations p 17 N91-10851 Numerical calculations for flows past an unconventional a single rotation large scale advanced prop-fan with A comparative study of Navier-Stokes codes for airfoil p24 N91-10916 angular and wake inflow at Mach numbers from 0.02 to high-speed flows p 20 N91-10869 Temporal-adaptive Euler/Navier-Stokes algorithm for 0.70 The use of a Navier-Stokes code in the wing design unsteady aerodynamic analysis of airfoils using [NASA-CR-182123] , p 47 N91-10065 process p 21 N91-10889 unstructured dynamic meshes Numerical simulation of rotorcraft p 19 N91 -10863 A numerical study of the effects of wind tunnel wall [NASA-TM-102734] p 24 N91-10919 Experimental investigation of the mechanisms proximity on an airfoil model Solution of the two-dimensional Euler equations by a underlying vortex kinematics in unsteady separated [ NASA-CR-187322] p 25 N91-10934 finite volume discretization on unstructured triangular flows p 23 N91-10907 Application of computational fluid dynamics to meshes The calculation of unsteady compressible flow about three-dimensional bodies in hypersonic flow [ESA-TT-1135] p66 N91-11473 oscillating airfoil profiles using the Euler upwind method p62 N91-11174 TWO DIMENSIONAL MODELS p25 N91-10921 Turbulent flow calculations using unstructured and TURBULENT BOUNDARY LAYER Unsteady wind tunnel wall interferences in subsonic and Control of vortical separation on a circular cone adaptive meshes transonic profile flows p 53 N91-10928 p3 A91-11162 [NASA-CR-182102] p 14 N91-10010 A study of cylindrical interaction of turbulent boundary A numerical study of the effects of wind tunnel wall layer/shock with swept compression comers proximity on an airfoil model p4 A91-11836 [NASA-CR-187322] p 25 N91-10934 Aerodynamic heating in the interaction regions of shock V-22 AIRCRAFT waves and turbulent boundary layers induced by u Application of computational fluid dynamic methods to sweptback blunt fins p6 A91-12226 the component aerodynamic design of the V-22 Osprey Estimation of the turbulent boundary layer pressure tilt rotor vehicle p 11 A91 • 12768 wavenumber-frequency spectrum using a fixed probe U.S.S.R. Soviet space planes p 54 A91-11737 V/STOL AIRCRAFT pair A superlative from Sukhoi - The SU-27 Noise characteristics of the Japan's experimental [AIAA PAPER 90-3926] p 67 A91-12442 p37 A91-12063 powered lift STOL aircraft Riblets — for aerodynamic drag reduction of turbulent [AIAA PAPER 90-4014] p 75 A91-12526 skin friction p 59 A91-12694 UH-60A HELICOPTER Comparison of NASTRAN analysis with ground vibration Outer-layer manipulators for turbulent drag reduction Aeroacoustic environment of an advanced STOVL p8 A91-12695 results of UH-60A NASA/AEFA test configuration aircraft in hover [NASA-CR-184565] p 61 . N91-10333 More accurate predictions with transonic Navier-Stokes [AIAA PAPER 90-4016] p 75 A91-12528 UNSTEADY AERODYNAMICS methods through improved turbulence modeling Simulation of powered-lift flows p 21 N91-10886 Periodic rotor-blade aerodynamics including loading p17 N91-10850 A numerical study of the hot gas environment around effects p2 A91-10337 TURBULENT FLOW a STOVL aircraft in ground proximity p 21 N91-10887 Oscillating cascade aerodynamics by an experimental Prediction of turbulence generated random vibrational VALVES influence coefficient technique p2 A91-10339 response of turbomachinery blading p 46 A91-11348 Mathematical modelling for analysis of nonlinear aircraft Structural tests of aircraft window assembly equipped Estimation of the turbulent spectral densities of the dynamics p 50 A91-11820 with smoke evacuation valve mass-density using two-dimensional Fourier transform of [DOT/FAA/CT-TN89/44] p 39 N91-10051 An approximate calculating method of digitized schlieren pictures supersonic/hypersonic unsteady aerodynamic forces of VANES [ONERA, TP NO. 1990-110] p4 A91-11782 airfoils p5 A91-11845 The effect of swirl recovery vanes on the cruise noise The role of leading edge vortex flows in prop-fan Acoustic radiation from lifting airfoils in compressible of an advanced propeller - interaction noise subsonic flow [AIAA PAPER 90-3932] p 68 A91-12448 [ AIAA PAPER 90-3977 ] p 72 A91 -12490 [AIAA PAPER 90-3911 ] p 66 A91-12427 The effect of swirl recovery vanes on the cruise noise Vertex-based finite-volume solution of the Unsteady airioading panel method for prop-fans of an advanced propeller two-dimensional Navier-Stokes equations [AIAA PAPER 90-3914] p 67 A91-12430 [NASA-TM-103825] p 77 N91-11494 p59 A91-12900 Numerical simulation of vortex-wedge interaction VARIABLE CYCLE ENGINES Turbulent flow calculations using unstructured and [AIAA PAPER 90-3918] p6 A91-12434 The variable-cycle engine • A solution to the economical adaptive meshes A unified unsteady lifting-line theory p8 A91-12575 and environmental challenge of the future supersonic [NASA-CR-182102] p 14 N91-10010 Influence of unsteady aerodynamics on rotor blade transport p 45 A91-10969 Numerical computation of viscous flow about aeroelastic stability and response p 37 A91-12894 unconventional airfoil shapes VECTOR PROCESSING (COMPUTERS) Aeroelastic analysis of wings using the Euler equations [NASA-CR-187343] p 15 N91-10019 Use of the VP-200 computer for aerothermodynamic with a deforming mesh More accurate predictions with transonic Navier-Stokes problems [NASA-TM-102733] p 15 N91-10020 methods through improved turbulence modeling [MBB/FE122/S/PUB/388] p 65 N91-11424 p 17 N91-10850 Evaluation of the ZONA51D program VENTILATION Recent advances in Runge-Kutta schemes for solving [REPT-B-28] p 16 N91-10025 Airplane systems modifications for improved cabin 3-D Navier-Stokes equations p 17 N91 -10851 Direct use of linear time-domain aerodynamics in smoke evacuation A zonal Navier-Stokes methodology for flow simulation aeroservoelastic analysis: Aerodynamic model [DOT/FAA/CT-TN90/24J p 39 N91-10052 about a complete aircraft p 18 N91-10858 p60 N91-10316 VIBRATION A numerical study of the hot gas environment around CFD for applications to aircraft aeroelastitity Coupled rotor/airframe vibration analysis a STOVL aircraft in ground proximity p 21 N91-10887 p 17 N91-10855 p43 N91-11012

A-25 VIBRATION DAMPING SUBJECTINDEX

VIBRATION DAMPING VORTEX GENERATORS WEATHER FORECASTING The ground resonance of a helicopter with a rotor of Noise mechanisms of transonic vortex airfoil Developments to enhance meteorological forecasting ideal and approximate symmetry considering the interaction for air traffic services p 64 N91-11006 rotor-blade vibration in the thrust plane [AIAA PAPER 90-3972] p 71 A91-12485 WEDGES p36 A91-11725 VORTEX SHEDDING Numerical simulation of vortex-wedge interaction Suppression of fatigue inducing cavity acoustic modes Gust response for flat-plate airfoils and the Kutta [AIAA PAPER 90-3918) p 6 A91-12434 on turbo fan engines condition p 12 A91 -12882 WEST GERMANY [AIAA PAPER 90-3941] p 69 A91-12457 VORTICES Air rescue in the Federal Republic of Germany VIBRATION SIMULATORS Application of the vortex cloud method to cascades [ETN-90-97878] p 28 N91-10963 The full-body ground vibration tests using the low-noise p3 A91-11347 WIND EFFECTS STOL test plane Vortex development on cruciform canard configurations Practical flight paths for microwave-powered airplanes [NAL-TR-1052T] p 40 N91-10054 [NAL-TM-576] P 50 N91-10077 at supersonic speeds p5 A91-11843 VIBRATION TESTS Contributions to the improvement of flight safety in wind Numerical simulation of vortex-wedge interaction Comparison of modal parameter estimation techniques shear [AIM PAPER 90-3918] p6 A91-12434 on aircraft structural data p 57 A91-11219 [ESA-TT-1141] p28 N91-10965 Rotor systems research aircraft risk-reduction shake Vortex instabilities in 3D boundary layers: The Critical aspects of trajectory prediction: Flight in test relationship between Goertler and crossflow vortices non-uniform wind p 41 N91-10971 [NASA-TM-4186] p 38 N91-10045 [NASA-CR-187456] p 15 N91-10022 Effect of wind and wind variation on aircraft The full-body ground vibration tests using the low-noise CFO for applications to aircraft aeroelasticity flight-paths p 41 N91-10972 STOL test plane p17 N91-10855 Aircraft flight in wind-shear p 41 N91-10973 [NAL-TM-576] p 50 N91-10077 The breakup of trailing-line vortices Wind models for flight simulation p 53 N91-10975 Comparison of NASTRAN analysis with ground vibration p20 N91-10867 Ground-based 4-D guidance of flights in strong wind results of UH-60A NASA/AEFA test configuration Conical Euler simulation and active suppression of delta " p 33 N91-10999 [ NASA-CR-184565] p 61 N91-10333 wing rocking motion Developments to enhance meteorological forecasting Review of active structural control systems and flight [NASA-TM-102683] p 22 N91-10904 for air traffic services p 64 N91-11006 test techniques for dynamic stability investigations Experimental investigation of the mechanisms WIND SHEAR [MBB/FYT256/S/PUB/361/A] p 51 N91-11025 underlying vortex kinematics in unsteady separated Assessing information transfer in full mission flight VIBRATORY LOADS flows p23 N91-10907 simulations p 26 N91-10946 Rotor systems research aircraft risk-reduction shake Calculation of aerodynamic characteristics of airplane Terminal weather information management test configurations at high angle of attack in steady and p 64 N91-10960 [NASA-TM-4186] p 38 N91-10045 unsteady flow p 42 N91-11009 Contributions to the improvement of flight safety in wind VIDEO TAPES Controlled vortical flow oh delta wings through unsteady shear Assessing information transfer in full mission flight leading edge blowing p 43 N91 -11011 [ESA-TT-1141] p28 N91-10965 simulations p 26 N91-10946 VORTICITY Aircraft flight in wind-shear p 41 N91-10973 VISCOUS DRAG Control of vortical separation on a circular cone How to fly windshear p 41 N91-10974 Viscous drag reduction in boundary layers — Book p3 A91-11162 WIND TUNNEL APPARATUS p58 A91-12688 The role of leading edge vortex flows in prop-fan Characteristics of piping interference elimination unit Convex curvature concept of viscous drag reduction interaction noise used in the high-speed wind tunnel test of ASUKA seven p8 A91-12696 [AIAA PAPER 90-3977] p 72 A91-12490 percent semi-born prototype, Viscous drag reduction via surface mass injection The breakup of trailing-line vortices [NAL-TM-588] p 13 N91-10003 • p9 A91-12698 p20 N91-10867 WIND TUNNEL MODELS Three-dimensional viscous drag prediction for rotor VORTICITY EQUATIONS Determination of kinetic heating on wind tunnel models blades < p 19 N91-10865 Parallelization on a multi-processor system of a solving by the surface temperature method [ONERA, TP NO. 1990-104] p4 A91-11779 VISCOUS FLOW method for the unsteady Navier-Stokes equations at high Application of the vortex cloud method to cascades Reynolds numbers The design of two sonic boom wind tunnel models from p3 A91-11347 [ESA-TT-1116] p62 N91-11197 conceptual aircraft which cruise at Mach numbers of 2.0 A study of implicit space-marching method for the and 3.0 supersonic viscous flow over the blunt cone [AIAA PAPER 90-4026] p 52 A91-12536 p4 A91-11831 w WIND TUNNEL TESTS Numerical computation of viscous flow about NACA/NASA supersonic flight research unconventional airfoil shapes WAKES p1 A91-10953 [NASA-CR-187343] p 15 N91-10019 Application of the vortex cloud method to cascades Development of the Griffon II turbo-ramjet Three-dimensional viscous/inviscid coupling in subsonic p3 A91-11347 p45 A91-10954 flow The aerodynamic effects of nozzle guide vane shock Transonic buffet on a supercritical aerofoil [REPT-B-24] , p 15 N91-10023 wave and wake passing on a transonic turbine rotor p2 A91-11157 Calculation of three-dimensional viscous/inviscid p24 N91-10915 Comparison of different calculation methods as applied interaction in subsonic flow WALL FLOW to a fuselage of lenticular section [REPT-B-25] p 16 N91-10024 Riblets — for aerodynamic drag reduction of turbulent [ONERA, TP NO. 1990-66] p3 A91-11755 A zonal Navier-Stokes methodology for flow simulation skin friction p 59 A91-12694 Comparison of afterbody test setups for combat aircraft about a complete aircraft p 18 N91 -10858 Residual interference and wind-tunnel wall adaptation model Navier-Stokes solutions for flows related to store p52 A91-12890 [ONERA, TP NO. 1990-70] p 51 A91-11758 separation p 18 N91-10861 Wall interference studies The CEPRA 19 anechoic wind tunnel Applications of a transonic wing design method [PD-CF-9012] p59 N91-10232 [ONERA, TP NO. 1990-72] p 51 A91-11760 p 21 N91-10890 A numerical study of the effects of wind tunnel wall The calculation of rotor/fuselage interaction for proximity on an airfoil model Experimental study of high-speed impulsive rotor noise two-dimensional bodies [NASA-CR-187322] p 25 N91-10934 in a wind tunnel [NASA-TM-102855] P 25 N91-10933 WALL PRESSURE [ONERA, TP NO. 1990-123] p 66 A91-11786 Test cases for computation of internal flows in aero Fluctuations of a shock wave generated by boundary The design of two sonic boom wind tunnel models from engine components layer separation p6 A91-12019 conceptual aircraft which cruise at Mach numbers of 2.0 [AGARD-AR-275] p 49 N91-11022 Wall interference studies and 3.0 Parallelization on a multi-processor system of a solving [PD-CF-9012] p59 N91-10232 [AIAA PAPER 90-4026] p 52 A91-12536 method for the unsteady Navier-Stokes equations at high WAVE DIFFRACTION The acoustic results of a United Techologies scale model Reynolds numbers Numerical simulation of acoustic diffraction of helicopter rotor tested at DNW [ESA-TT-1116] p62 N91-11197 two-dimensional rigid bodies in arbitrary flows [AIAA PAPER 90-4035] p 75 A91-12543 VISUAL AIDS [AIAA PAPER 90-3920] p 67 A91-12436 Elements of airfoil design methodology Function and performance of visual simulation unit of WAVE PROPAGATION . p9 A91-12757 flight simulation test facility The sonic boom of an oblique frying wing Euler and potential computational results for selected [NAL-TM-581] p 52 N91-10082 [AIAA PAPER 90-4002] p 74 A91-12515 aerodynamic configurations p 10 A91-12760 VISUAL FIELDS WAVEFORMS Navier-Stokes methods for internal and integrated flow Function and performance of visual simulation unit of Weak shock propagation through a turbulent prediction p 10 A91-12763 flight simulation test facility atmosphere CFD applications to complex configurations - A survey [NAL-TM-581] p 52 N91-10082 I AIAA PAPER 90-4031) p 75 A91-12540 p11 A91-12766 VISUAL FLIGHT WAVERIDERS The establishment and performance test of PAPI Project HyBuJET Experimental study of instability modes in a (Precision Approach Path Indicator) System for NAL STOL [NASA-CR-187011] p 38 N91-10040 three-dimensional boundary layer p 59 A91-12888 aircraft Supersonic combustion engine testbed, heat lightning Characteristics of piping interference elimination unit [NAL-TM-579] p 28 N91-10030 [NASA-CR-187010] p 47 N91-10061 used in the high-speed wind tunnel test of ASUKA seven VOICE COMMUNICATION WEAR RESISTANCE percent semi-born prototype A flight test facility design for examining digital Applications of thermally sprayed coating systems in [NAL-TM-588] p 13 N91-10003 information transfer p 28 N91-10962 aero engines Euler and potential experiment/CFD correlations for a Voice communications in the cockpit noise environment: [PNR-90750] p48 N91-10072 transport and two delta-wing configurations The role of active noise reduction p 61 N91-11140 WEATHER [NASA-TM-102208] p 14 N91-10014 VORTEX FILAMENTS Terminal weather information management Wind tunnel investigations of the appearance of shocks Calculation of aerodynamic characteristics of airplane p64 N91-10960 in the windward region of bodies with circular cross section configurations at high angle of attack in steady and A flight test facility design for examining digital at angle of attack unsteady flow p 42 N91-11009 information transfer p 28 N91-10962 [DLR-FB-90-15] p 16 N91-10027

A-26 SUBJECT INDEX YTTRIUM OXIDES

Wind tunnel test of redundant vane-type flow-direction sensing systems (NAL-TM-590) p 44 N91-100S7 XV-15 AIRCRAFT Measurement of unsteady blade surface pressure on Some far-field acoustics characteristics of the XV-15 a single rotation large scale advanced prop-fan with tilt-rotor aircraft angular and wake inflow at Mach numbers from 0.02 to [AIAA PAPER 90-3971] p 71 A91-12484 0.70 [NASA-CR-182123] p 47 N91-10065 A laser-sheet flow visualization technique for the large wind tunnels of the National Full-Scale Aerodynamics YTTRIUM OXIDES Complex Thermal barrier coatings - Microstructural investigation [NASA-TM-102793] p 60 N91-10268 after annealing Prediction of effects of wing contour modifications on [ONERA, TP NO. 1990-62] p 55 A91-11751 low-speed maximum lift and transonic performance for the EA-6B aircraft [NASA-TP-30461 p 22 N91-10902 A numerical study of the effects of wind tunnel wall proximity on an airfoil model (NASA-CR-187322] p 25 N91-10934 Noise measurements from an ejector suppressor nozzle in the NASA Lewis 9- by 15-foot low speed wind tunnel (NASA-TM-103628] p 76 N91-11493 The effect of swirl recovery vanes on the cruise noise of an advanced propeller [NASA-TM-103625] p 77 N91-11494 WIND TUNNEL WALLS Residual interference and wind-tunnel wall adaptation p52 A91-12890 Wall interference studies (PD-CF-9012) p59 N91-10232 Unsteady wind tunnel wall interferences in subsonic and transonic profile flows p 53 N91-10928 A numerical study of the effects of wind tunnel wall proximity on an airfoil model [NASA-CR-187322] p 25 N91-10934 WIND TUNNELS The CEPRA 19 anechoic wind tunnel [ONERA, TP NO. 1990-72] p 51 A91-11760 WIND VARIATIONS Effect of wind and wind variation on aircraft flight-paths p 41 N91-10972 Wind models for flight simulation p 53 N91-10975 WINDOWS (APERTURES) Structural tests of aircraft window assembly equipped, with smoke evacuation valve IDOT/FAA/CT-TN89/44] p 39 N91-10051 WING CAMBER . All-electric flight control experiments and experiments with a sidestick on the Concorde p 49 A91-10955 WING FLAPS Static and dynamic aeroelastic characterization of an aerodynamically heated generic hypersonic aircraft configuration p 61 N91-10320 WING OSCILLATIONS Conical Euler simulation and active suppression of delta wing rocking motion [NASA-TM-102683] p 22 N91-10904 WING PROFILES Development of high-lift wing modifications for an advanced capability EA-6B aircraft p 10 A9M2762 Euler and potential experiment/CFD correlations for a transport and two delta-wing configurations [NASA-TM-102208 ] p 14 N91-10014 The use of a Navier-Stokes code in the wing design process p 21 N91 -10889 Prediction of effects of wing contour modifications on low-speed maximum lift and transonic performance for the EA-6B aircraft [NASA-TP-3046] p 22 N91-10902 WINGS Calculation of three-dimensional viscous/inviscid interaction in subsonic flow IREPT-B-25] p 16 N91-10024 Experimental measurement of structural power flow on an aircraft fuselage | NASA-CR-187352) p 61 N91-10335 More accurate predictions with transonic Navier-Stokes methods through improved turbulence modeling p 17 N91-10850 Recent advances in Runge-Kutta schemes for solving 3-D Navier-Stokes equations p 17 N91-10851 Applications of a transonic wing design method p21 N91-10890 Development and application of the time domain panel method p 43 N91-11010 WORKLOADS (PSYCHOPHYSIOLOGY) Douglas flight deck design philosophy p40 N91-10939 Inflight replanning for diversions p 27 N91 -10955

A-27 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

Typical Personal Author Index Listing AMIET, R. K. BARRON, R. M. Gust response for flat-plate airfoils and the Kutta Transonic computations on a natural grid condition p 12 A91-12882 p 13 A91-12904 ANDERS, J. B., JR. BARTH, TIMOTHY J. PERSONAL AUTHOR Outer-layer manipulators for turbulent drag reduction Unstructured mesh solution of the Euler and p8 A91-12695 Navier-Stokes equations p 22 N91-10892 ANDERSON, DALE A. BARTHELEMY, JEAN-FRANCOIS M. Grid-generation methodology in applied aerodynamics Research in Structures, Structural Dynamics and BASSOM, ANDREW p9 A91-12755 Materials, 1990 — Vortex instabilities in 3D boundary layers: The ARAFAILOV, S. I. [NASA-CP-3064] p60 N91-10301 relationship between Goertier and crossflow vortices Effect of energy release in the shock layer on supersonic BARTLETT, D. W. INASA-CR-187456] p 15 N91-10022 flight p6 A91-12016 Applied aspects of laminar-flow technology ARAKAWA, HARUHIKO p8 A91-12690 Numerical simulation of hypersonic flow around a space BASS, HENRY E. plane. Part 3: Analysis of aerothermodynamic heating Comparison of shock wave rise time prediction REPORT PAGE TITLE ACCESSION [NAL-TR-1027T] p 14 N91-10011 techniques NUMBER NUMBER NUMBER ARDEMA, MARK D. [AIAA PAPER 90-4001 ] p 74 A91-12514 Body weight of hypersonic aircraft, part 1 BASSOM, ANDREW [NASA-TM-101028] p 39 N91-10049 Vortex instabilities in 3D boundary layers: The ASAI, KEISUKE relationship between Goertier and crossflow vortices [NASA-CR-187456] p 15 N91-10022 Listings in this index are arranged alphabetically Characteristics of piping interference elimination unit used in the high-speed wind tunnel test of ASUKA seven BATES, BRENT L. by personal author. The title of the document pro- percent semi-born prototype Navier-Stokes solutions about the F/A-18 forebody-LEX vides the user with a brief description of the subject [NAL-TM-588] p 13 N91-10003 configuration p 18 N91-10860 matter. The report number helps to indicate the ASHBY, M. F. BATINA, JOHN T. Aeroelastic analysis of wings using the Euler equations type of document listed (e.g., NASA report, trans- A process model for age hardening of aluminium alloys. I-The model p 56 A91-11883 with a deforming mesh lation, NASA contractor report). The page and ac- ASLAN, J. [NASA-TM-102733] p 15 N91-10020 cession numbers are located beneath and to the OVRhyp, scramjet test aircraft Application of unstructured grid methods to steady and right of the title. Under any one author's name the [NASA-CR-187009] p 38 N91-10041 unsteady aerodynamic problems p 17 N91-10856 ASO, SHIGERU Conical Euler simulation and active suppression of delta accession numbers are arranged in sequence. Aerodynamic heating in the interaction regions of shock wing rocking motion waves and turbulent boundary layers induced by [NASA-TM-102683] p 22 N91-10904 sweptback blunt fins p6 A91-12226 Implicit flux-split Euler schemes for unsteady ASTRIDGE, DEREK G. aerodynamic analysis involving unstructured dynamic Rotorcraft drivetrain life safety and reliability meshes [AGARD-R-775] p 38 N91-10042 [NASA-TM-102732] p 24 N91-10918 ABBOTT, KATHY Helicopter transmissions: Design for safety and Temporal-adaptive Euler/Navier-Stokes algorithm for Overview ot error-tolerant cockpit research reliability p 38 N91-10043 unsteady aerodynamic analysis of airfoils using p40 N91-10949 ATALLA, NOUREDDINE unstructured dynamic meshes Fault diagnosis p 26 N91-10951 A ray-acoustics approach to fuselage scattering of rotor [NASA-TM-102734] p 24 N91-10919 noise ABDEL-WAHAB, MOHAMEO AHMED BATY, ROY S. Ejector thrust augmentors: Pulse-starting approach to [AIAA PAPER 90-4013] p 75 A91-12525 Instability of a supersonic shock-free elliptic jet the second solution p 23 N91-10913 ATASSI, HAFIZ M. [AIAA PAPER 90-3959] p7 A91-12473 Acoustic radiation from lifting airfoils in compressible ABID, R1DHA BAYSAL, OKTAY subsonic flow Recent advances in Runge-Kutta schemes tor solving Navier-Stokes solutions for flows related to store [AIAA PAPER 90-3911] p 66 A91-12427 3-D Navier-Stokes equations p 17 N91-10851 separation p 18 N91-10861 AURIOL, A. AQARWAL, R. K. The sonic boom problem p1 A91-10964 BECKER, J. Numerical simulation of acoustic diffraction of AVELLO, CARLOS GARCIA A quarter of a century of aeroelastic cooperation two-dimensional rigid bodies in arbitrary flows The high-resolution graphic display: A possible between research and industry (a review). Part 1: Fighter [AIAA PAPER 90-3920] p 67 A91-12436 man/machine interface for a computer assisted ATC airplanes and helicopters p 78 N91-10931 AGARWAL, RAMESH K. management system p31 N91-10989 BECKER, LAWRENCE E. Euler/Navier-Stokes calculations of the flowfield of a AVERS, T. G. Some far-field acoustics characteristics of the XV-15 helicopter rotor in hover and forward flight NACA/NASA supersonic flight research tilt-rotor aircraft p11 A91-12765 p 1 A91-10953 [AIAA PAPER 90-3971 ] p 71 A91-12484 AHMED, S. The need for a hypersonic demonstrator BEDARD, ALFRED J., JR. Numerical computation of viscous flow about p 54 A91-10977 The measurement of sonic boom waveforms and unconventional airfoil shapes AZEVEDO, DAVID J. propagation characteristics - Techniques and challenges [NASA-CR-187343] p 15 N91-10019 Prediction of inviscid stagnation pressure losses in | AIAA PAPER 90-4004] p 74 A91-12517 AHUJA, K. K. supersonic inlet flows p 12 A91-12903 BEERMAN, HENRY P. Recent advances in Active Noise Control Propulsion simulation for magnetically suspended wind [AIAA PAPER 90-3924] p 67 A91-12440 tunnel models An evaluation of various concepts of reducing B [NASA-CR-182093] p 53 N91-11027 supersonic jet noise BEERS, J. N. P. BABKIN, VLADIMIR I. [AIAA PAPER 90-3982] p 72 A91-12495 The application of trajectory prediction algorithms for Jets and lifting surfaces: Computer simulation Controlling plume deflection by acoustic excitation - An planning purposes in the Netherlands ATC-system p 13 A91-12913 experimental demonstration p65 N91 -10986 BAHR, D. [AIAA PAPER 90-4006) p 74 A91-12519 Thermoacoustics of unsteady combustion BELOTSERKOVSKII, SERGEI M. AL-KHALIL, KAMEL M. [AIAA PAPER 90-3928] p 67 A91-12444 Jets and lifting surfaces: Computer simulation p 13 A9M2913 Thermal analysis of engine inlet anti-icing systems BAHR, DONALD W. p35 A91-10341 Supersonic/hypersonic propulsion systems - Exhaust BENNER, R. H. ALLISON, DENNIS O. emission characteristics and abatement technology Suppression of fatigue inducing cavity acoustic modes Prediction of effects of wing contour modifications on p45 A9M0965 on turbo fan engines low-speed maximum lift and transonic performance for the BANDO, TOSHIO [AIAA PAPER 90-39411 p 69 A9M2457 EA-6B aircraft Configuration, function and performance of the flight BENOIT, ANDRE [NASA-TP-3046] p 22 N91-10902 simulation test facility and its motion simulation system Aircraft trajectories: Computation, prediction, control. ALPERINE, S. [NAL-TM-575] p 52 N91-10080 volume 1. Part 1: Fundamentals. Part 2: Flight in critical Thermal barrier coatings - Microstructural investigation BANDYOPADHYAY, PROMODE R. atmospheric conditions. Part 3: Impact of new on-board after annealing Convex curvature concept of viscous drag reduction technologies on aircraft operation | ONERA. TP NO. 1990-62] p 55 A91-11751 p8 A9M2696 ' [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-I0967

B-1 BENSON, TOM PERSONAL AUTHOR INDEX

Aircraft trajectories: Computation, prediction, control. BRADLEY, RICHARD G. CEBECI, TUNCER Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. Future directions for applied computational fluid Application of CFD to reduction of skin-friction drag Part 11: List of contributors dynamics p 59 A91-12775 pa A91-12692 [AGARD-AG-301-VOL-3-PT-9-11] p 30 N91-10978 BRASLOW, A. L CHABOCHE, J. L. Aircraft trajectories: Computation, prediction, control, Applied aspects of laminar-flow technology Calculations of the service life of components under volume 2: Air traffic handling and ground-based guidance p8 A91-12690 severe thermomechanical loads of aircraft. Part 4: Air traffic handling. Part 5: Guidance BRAYBROOK, ROY [ONERA, TP NO. 1990-63] p 58 A91-11752 of aircraft in a time-based constrained environment. Part A superlative from Sukhoi - The SU-27 CHADERJIAN, NEAL M. 6: Surveillance. Part 7: Meteorological forecasts. Part 8: p37 A91-12063 Navier-Stokes computations about complex Aircraft operation in air traffic handling simulation BROCKHAUS, R. configurations including a complete F-16 aircraft [AGARD-AG-301-VOL-2-PT-4-8] p 42 N91-10981 Comparison of a mathematical one-point model and a p 12 A91-12772 Optimum on-line handling of air traffic over Western multi-point model of aircraft motion in moving air CHAKRABARTTY, SUNIL KUMAR Europe p 30 N91-10982 p41 N91-10969 Vertex-based finite-volume solution of the BROWN, DAVID Generation of aircraft trajectories for on-line operation: two-dimensional Navier-Stokes equations Sound insulation of dwellings around airports - Objective Methods, techniques, and tools p 42 N91-10987 p59 A91-12900 and subjective measures and findings The 4-D control of current air carriers in the present CHAKRAVARTHY, SUKUMAR R. [AIAA PAPER 90-4029] p 63 A91-12538 environment: Objectives, status, and plans A comparative study of Navier-Stokes codes for BRUNE, G. W. p 31 N91-10990 high-speed flows p 20 N91-10869 The control of inbound flights p 32 N91-10992 Computational aerodynamics applied to high-lift CHANG, I-CHUNG Air traffic management and aircraft guidance in a zone systems p 10 A91-12761 Transonic flow analysis for rotors. Part 3: of convergence p 33 N91-10998 BUFFUM, DANIEL H. Three-dimensional, quasi-steady, Euler calculation Ground-based 4-D guidance of flights in strong wind Oscillating cascade aerodynamics by an experimental [NASA-TP-2375] p 13 N91-10007 p 33 N91-10999 influence coefficient technique p2 A91-10339 The air traffic controller facing automation: Conflict or BURGE, PAUL L. Wake coupling to full potential rotor analysis code cooperation p 34 N91-11001 An experimental technique of separating airborne and [NASA-TM-102805] p 14 N91-10013 Integration of aircraft capability in air traffic handling structure-borne noise using wavenumber-frequency CHANG, R. C. . simulations p 35 N91-11007 spectrum Forcing level effect of internal acoustic excitation on BENSON, TOM [AIAA PAPER 90-3969] p 71 A91-12483 the improvement of airfoil performance CFD analysis for high speed inlets p 21 N91-10888 BURKHART, R. H. [AIAA PAPER 90-4010] p 74 A91-12522 BERKOWITZ, BRIAN M. Application of computational methods in aeroacoustics CHAPMAN, C. J. Progress toward the development of an airfoil icing [AIAA PAPER 90-3917] p 67 A91-12433 Diffraction patterns in the acoustic field of a propeller analysis capability p 19 N91-10866 BUSHNELL, DENNIS M. [AIAA PAPER 90-3994] p 73 A91-12507 BERMAN, C. H. Viscous drag reduction in boundary layers CHAWLA, KALPANA Time-dependent jet flow and noise computations p58 A91-12688 Simulation of powered-lift flows p 21 N91 -10886 Viscous drag reduction via surface mass injection [AIAA PAPER 90-3961] p 70 A91-12475 CHEN, CHING S. BESTGEN, ROBERT F. p9 A91-12698 Three-dimensional viscous drag prediction for rotor BUSHNELL, P. A case study in fostering international HSCT blades p 19 N91-10865 collaboration p 77 A91-10970 Measurement of unsteady blade surface pressure on CHEN, JAMES BEYER, TODD B. a single rotation large scale advanced prop-fan with angular and wake inflow at Mach numbers from 0.02 to Propulsion simulation for magnetically suspended wind Noise transmission characteristics of a large scale tunnel models composite fuselage model 0.70 [NASA-CR-182093] p 53 N91-11027 [AIAA PAPER 90-3965] p 71 A91-12479 [NASA-CR-182123] p 47 N91-10065 CHEN, JINGSONG BIANCO, LUCIO BUSSOLETTI, J. E. An approximate calculating method of Optimization models and techniques to improve air traffic Application of computational methods in aeroacoustics management p 31 N91-10988 [AIAA PAPER 90-3917] p 67 A91-12433 supersonic/hypersonic unsteady aerodynamic forces of BIBKO, V. N. airfoils p5 A91-11845 Fluctuations of a shock wave generated by boundary CHEN, WON-ZON layer separation p6 A91-12019 Constrained optimization approach to feedback control BIDWELU COLIN S. of state-augmented systems p 66 N91-11433 CABELL, RANDOLPH H. Progress toward the development of an airfoil icing CHEUNG, SAMSON H. The identification of helicopter noise using a neural analysis capability p 19 N91-10866 Application of CFD to sonic boom near and mid flow-field network BIPPES, H. prediction [AIAA PAPER 90-3973] p 72 A91-12486 Experimental study of instability modes in a [AIAAPAPER90-3999] p7 A91-12512 CALLOWAY, A. B. three-dimensional boundary layer p 59 A91-12888 Application of CFD to sonic boom near and mid flow-field An evaluation of various concepts of reducing BISARD, T. prediction supersonic jet noise OVRhyp, scramjet test aircraft [NASA-TM-102867] p 14 N91-10015 [AIAA PAPER 90-3982] p 72 A91-12495 [NASA-CR-187009] p 38 N9M0041 CALUORI, VINCENT A., JR. CHITSOMBOOM, TAWIT BLACODON, D. The application of commercial airplane avionics Application of CFD codes for the simulation of scramjet Space-structure determination of the acoustic field techniques to advanced space transportation combustor flowfields p 20 N91-10873 generated by a helicopter turboshaft engine [AIAA PAPER 90-3722] p1 A91-10114 CHOI, JONG-SOO [AIAA PAPER 90-4012] p 46 A91-12524 CAMPBELL, RICHARD L. Experiments on the aerodynamic noise sources in BLAIR, MAXWELL Applications of a transonic wing design method centrifugal turbomachinery Development and application of the time domain panel p21 N91-10890 [AIAA PAPER 90-3948] p 69 A91-12464 method p 43 N91-11010 CAMUS, PAUL CHRISTIAN, TOM F. BLISS, DONALD B. How to fly windshear p 41 N91-10974 Structural risk assessment and aircraft fleet Aircraft interior noise reduction by alternate resonance CANARD-CARUANA, S. maintenance p 61 N91-10321 tuning Experimental study of noise sources and acoustic [NASA-CR-186879] p 76 N91-11488 CHUNG, JIN-DEOG propagation in a turbofan model Interaction between rotors of a counter rotating BLOCK, P. J. W. [AIAA PAPER 90-3950] p 69 A91-12466 propeller Analysis of the PTA external noise data and comparison CANNON, MARK R. with predictions [AIAA PAPER 90-3976] p 7 A91-12489 Estimation of the turbulent boundary layer pressure [AIAA PAPER 90-3935] p 68 A91-12451 CLARK, B. J. wavenumber-frequency spectrum using a fixed probe BLOM, A. F. Near-field noise of a single rotation preplan at an angle pair Short crack growth under realistic flight loading: Model of attack [AIAA PAPER 90-3926] p 67 A91-12442 predictions and experimental results for Al 2024 and AI-U [AIAA PAPER 90-3953] p 70 A91-12469 CAO, JUN 2090 p62 N91-11246 CLIFF, S. E. An approximate calculating method of BLOM, H. A. P. Euler and potential computational results for selected supersonic/hypersonic unsteady aerodynamic forces of Bayesian multi-sensor tracking for advanced air traffic aerodynamic configurations p 10 A91 -12760 airfoils p5 A91-11845 control systems p 34 N91-11003 Euler and potential experiment/CFD correlations for a CAPRON, WILLIAM R. BLOY, A. W. transport and two delta-wing configurations A description and evaluation of TIMER: A time-based The aerodynamic interference between tanker'and [NASA-TM-102208] p 14 N91-10014 terminal flow-control concept p 32 N91 -10996 receiver aircraft during air-to-air refuelling CLOUSER, STEVE CAREU OLIVIER p3 A91-11159 Thermoacoustics of unsteady combustion Contribution of the satellite techniques to the BLUM, THOMAS C. [AIAA PAPER 90-3928] p 67 A91-12444 surveillance of air traffic p 35 N91-11005 Simulation of powered-lift flows p 21 N91-10886 COLLARD, D. BOJANOWSKI, JERZY CARSTENS, VOLKER SST airtrame integration lor a Mach 2 transport Helicopter ground resonance p 36 A91-11723 The calculation of unsteady compressible flow about p36 A91-10967 BONNER, E. oscillating airfoil profiles using the Euler upwind method Hypersonic aircraft studies p2 A91-10971 Computational aerodynamic simulation experience p 25 N91-10921 COLLET, BILL p11 A91-12771 CARVALHO, M. HELENA Project HyBuJET BOOTH, THOMAS E. Short crack behaviour in AI-Li alloy 2090 [NASA-CR-187011] p38 N91-10040 Prediction of turbulence generated random vibrational p6;: N91-11243 COLLIER, F. S., JR. response of turbomachinery blading p 46 A91-11348 CAVAGE, WILLIAM, JR. Applied aspects of laminar-flow technology BOUHERAOUA, A. Structural tests of aircraft window asset ibl equipped p6 A91-12690 An accurate acoustic emission location method adapted with smoke evacuation valve COLOMBO, A. G. for composite materials p 57 A91-11027 [DOT/FAA/CT-TN89/44] p3 J91-10051 Systems reliability assessment p 57 A91-11201

B-2 PERSONAL AUTHOR INDEX FLEETER, SANFORD

CONNER, DAVID A. DEESE, JERRY E. EDWARDS, THOMAS A. Some far-field acoustics characteristics of the XV-15 Euler/Navier-Stokes calculations of the flowfield of a Application of CFO to sonic boom near and mid flow-field tilt-rotor aircraft helicopter rotor in hover and forward flight prediction [AIAA PAPER 90-3971] p 71 A91-12484 p11 A91-12765 [AIAA PAPER 90-3999] p 7 A91-12512 CONSIGNY, H. OEFREITAS, M. Application of CFD to sonic boom near and mid flow-field Determination of kinetic heating on wind tunnel models Short crack behaviour in AI-LJ alloy 2090 prediction by the surface temperature method p62 N91-11243 [NASA-TM-102867] p 14 N91-10015 [ONERA, TP NO. 1990-104] p4 A91-11779 DELNATTE, YVES EFIMTSOV, B. M. COOPER, BETH A. Integration of aircraft capability in air traffic handling Fluctuations of a shock wave generated by boundary Noise measurements from an ejector suppressor nozzle simulations p 35 N91-11007 layer separation p6 A91-12019 in the NASA Lewis 9- by 15-foot low speed wind tunnel DEMEIS, RICHARD EKLUND, THOR I. [AIAA PAPER 90-3983] p 73 A91-12496 X-31 will turn on a dime p 36 A91-11863 Airplane systems modifications for improved cabin Noise measurements from an ejector suppressor nozzle smoke evacuation in the NASA Lewis 9- by 15-foot low speed wind tunnel DENG, XUEYING [DOT/FAA/CT-TN90/24] p 39 N91-100S2 A study of cylindrical interaction of turbulent boundary [NASA-TM-103628] p 76 N91-11493 Generation of a buoyant plume of artificial smoke for layer/shock with swept compression comers COOPER, J. E. airplane tests p4 A91-11836 Comparison of modal parameter estimation techniques [DOT/FAA/CT-90/9] P 43 N91-11015 on aircraft structural data p 57 A91-11219 DERON, R. ELLIOT, SIMON COPE, M. T. Estimation of the turbulent spectral densities of the Harrier - The next 30 years p 36 A91-11715 Influence of heat treatment on microstructure and mass-density using two-dimensional Fourier transform of EMDAD, HOMAYOUN properties of an advanced high temperature titanium digitized schlieren pictures Calculation of aerodynamic characteristics of airplane alloy [ONERA, TP NO. 1990-110] p4 A91-11782 configurations at high angle of attack in steady and [PNR-90689] p56 N91-11107 DESAI, VIJAY R. unsteady flow p 42 N91-11009 COPENHAVER, RONALD M. Sonic boom environment under a supersonic military ENVIA, E. Thermal stability of jet fuel operating area Near-field noise of a single rotation preplan at an angle [DE90-016801] p56 N91-10188 [ AIAA PAPER 90-4032 ] p 63 A91 -12541 of attack COPLIN, JOHN F. DEWISPELAERE, RENE [AIAA PAPER 90-3953] p 70 A91-12469 Multi industry application of advanced materials The air traffic controller facing automation: Conflict or ERICKSON, LARRY L [PNR-90764] p56 N91-10139 cooperation p 34 N91-11001 Toward the routine aerodynamic analysis of complex CORKER, KEVIN DEWITT, KENNETH J. configurations p 11 A91-12770 Fault recovery recommendation p 27 N91-10952 Thermal analysis of engine inlet anti-icing systems ERWIN, R. l_ Information management p 27 N91-10961 p 35 A91-10341 Use of 4-D RNAV in time-based en route arrival CORMERY, G. Dl GIORGIO, L metering p 33 N91-10997 All-electric flight control experiments and experiments The high speed market in the next three decades ERZBERGER, HEINZ with a sidestick on the Concorde p 49 A91-10955 p 77 A91-10963 ATC automation concepts p 29 N91-10957 Concorde - 1958-1975 p 35 A91-10956 DIETRICH, DONALD A. A piloted simulator evaluation of a ground-based 4-D descent advisor algorithm p 33 N91-11000 COSNER, RAYMOND R. Thermal analysis of engine inlet anti-icing systems Navier-Stokes methods for internal and integrated flow p35 A91-10341 ESCH, HELMUT prediction p 10 A91-12763 DIOT, C. Wind tunnel investigations of the appearance of shocks COX, M. E. Thermal barrier coatings - Microstructural investigation in the windward region of bodies with circular cross section Developments to enhance meteorological forecasting after annealing at angle of attack for air traffic services p 64 N91-11006 [ONERA, TP NO. 1990-62] p 55 A91-11751 [DLR-FB-90-15] p 16 N91-10027 CREDEUR, LEONARD DITTMAR, JAMES H. ESER, SEMIH A description and evaluation of TIMER: A time-based The effect of swirl recovery vanes on the cruise noise Thermal stability of jet fuel terminal flow-control concept p 32 N91 -10996 of an advanced propeller [DE90-016801] p56 N91-10188 CRIGHTON, D. G. [AIAA PAPER 90-3932] p 68 A9M2448 ETKIN, BERNARD Radiation integrals for sound generation by the LJghthill The effect of swirl recovery vanes on the cruise noise Critical aspects of trajectory prediction: Flight in quadruples in propeller acoustics of an advanced propeller non-uniform wind p 41 N91-10971 [AIAA PAPER 90-3993] p 73 A91-12506 [NASA-TM-103625] p 77 N91-11494 ETKIN, DAVID ALEXANDER CUMMINGS, RUSSELL M. DO, DUNG Critical aspects of trajectory prediction: Flight in Numerical simulation of F-18 fuselage forebody flows Tests of the general fire suppression concentrate non-uniform wind p 41 N91-10971 at high angles of attack p 18 N91-10859 Pyrocap B-136 EVERETT, R. A. CUSCHIERI, J. M. [DOT/FAA/CT-TN90/21] p 26 N91-10029 Experimental measurement of structural power flow on The growth of short cracks in 4340 steel and DODDS, W. aluminum-lithium 2090 p 62 N91-11247 an aircraft fuselage Thermoacoustics of unsteady combustion [NASA-CR-187352] p 61 N91-10335 [AIAA PAPER 90-3928] p 67 A91-12444 CUTHBERTSON, R. D. DONNELLY, R. P. Installation effects on counter rotating propeller noise Experimental/theoretical investigation of the sound field [AIAA PAPER 90-4023] p 75 A91-12534 of an isolated propeller, including angle of incidence FALENI, J. P. effects Estimation of the turbulent spectral densities of the [AIAA PAPER 90-3952] p 69 A91-12468 mass-density using two-dimensional Fourier transform of DOOGOOD, P. N. digitized schlieren pictures Flight testing of two Allison T56 engines modified to [ONERA, TP NO. 1990-110] p4 A91-11782 D'ESPINEY, P. the ARL developed low smoke configuration Comparison of different calculation methods as applied [ARL-PROP-TM-449] p 47 N91-10064 FARASSAT, F. to a fuselage ol lenticular section DRAPER, K. State-of-the-art of high-speed propeller noise prediction [ONERA, TP NO. 1990-66] p 3 A91-11755 OVRhyp, scramjet test aircraft - A multidisciplinary approach and comparison with DAEUBLER, M. A. [NASA-CR-187009] p 38 N91-10041 measured data Influence of heat treatment on microstructure and DREIBELBIS, RYLAND R. [AIAA PAPER 90-3934] p 68 A91-12450 properties of an advanced high temperature titanium Current Emergency Locator Transmitter (ELT) FEDOROV, A. V. alloy deficiencies and potential improvements utilizing An experimental study of the laminar-turbulent transition [PNR-90689] p56 N91-11107 TSO-C91a ELTs behind three-dimensional roughness in a boundary layer DALLINGA, S. [NASA-CR-4330] p28 N91-10964 on a sharp cone p6 A91-12014 OVRhyp, scramjet test aircraft DRELA MARK FENG, Ol [NASA-CR-187009] p 38 N91-10041 Elements of airfoil design methodology Optimization of the arrangement of the front and rear DALM, T. B. p9 A91-12757 blade rows of a tandem blade cascade The application of trajectory prediction algorithms for DUNN, MARK H. p46 A91-11349 planning purposes in the Netherlands ATC-system State-of-the-art of high-speed propeller noise prediction FERRARO, PETER J. p65 N91 -10986 - A multidisciplinary approach and comparison with Aeroacoustic environment of an advanced STOVL DARDARE, J. measured data aircraft in hover Propulsion systems for hypersonic transportation [AIAA PAPER 90-3934] p 68 A91-12450 [AIAA PAPER 90-4016] p 75 A91-12528 p45 A91-10975 DVORAK, ALEKSANDR V. FEYOCK, STEFAN DARDEN, C. M. Jets and lifting surfaces: Computer simulation Automatic determination of fault effects on aircraft An Euler code prediction of near field to midfield sonic p 13 A91-12913 functionality boom pressure signatures [NASA-CR-181352] p 37 N91-10039 (AIAA PAPER 90-4000] p7 A91-12513 FLEDEL, SHMUEL DAS, SUBHENDU Coupled rotor/airirame vibration analysis Parallelized reliability estimation of reconfigurable E, QIN p43 N91-11012 computer networks Calculation of boundary-layer flows on low Reynolds FLEETER, SANFORD [NASA-CR-182101] p 65 N91-11430 number and transonic airfoils p5 A91-11840 Periodic rotor-blade aerodynamics including loading DAVIS, STEPHEN F. EASTERBROOK, CALVIN C. effects p 2 A91-10337 Euler solutions for delta wings p 12 A91 -12899 Development and application of linear and nonlinear Oscillating cascade aerodynamics by an experimental DAVIS, THOMAS J. methods for interpretation of lightning strikes to in-flight influence coefficient technique p2 A91-10339 A piloted simulator evaluation of a ground-based 4-D aircraft Prediction of turbulence generated random vibratonal descent advisor algorithm p 33 N91-11000 [NASA-CR-3974] p 64 N91-10548 response of turbomachinery blading p 46 A91-11348

B-3 FLORES, JOLEN PERSONAL AUTHOR INDEX

FLORES, JOLEN GHAFFARI, FARHAD GUMBERT, CLYDE Navier-Slokes computations about complex Navier-Stokes solutions about the F/A-18 forebody-LEX Three dimensional unstructured grids for the solution configurations including a complete F-16 aircraft configuration p 18 N91-10860 of the Euler equations p 22 N91-10893 p 12 A9M2772 GILBERT, MICHAEL G. GURUSWAMY, GURU P. A zonal Navier-Stokes methodology for flow simulation Direct use of linear time-domain aerodynamics in CFD for applications to aircraft aeroelasticity about a complete aircraft p 18 N91-10858 aeroservoelastic analysis: Aerodynamic model p 17 N91-10855 FORESTIER, J. p60 N91-10316 GUSTAVESON, MARK B. Supersonic air transport programs in the 60's Static and dynamic aeroelastic characterization of an Aircraft interior noise reduction by alternate resonance p 1 A91-10952 aerodynamically heated generic hypersonic aircraft tuning configuration p 61 N91-10320 FORNASIER, LUCIANO [NASA-CR-186879] p 76 N91-11488 GILES, MICHAEL B. Use of the VP-200 computer for aerothermodynamic Stator/rotor interaction in a transonic turbine problems p2 A91-10340 [MBB/FE122/S/PUB/388] p 65 N91-11424 H GLAZKOV, IU. A. FORRESTER, D. A. Reliability of results of the capillary testing of gas turbine Developments to enhance meteorological forecasting HABRARD, ALAIN engine components during repairs p 58 A91-12036 for air traffic services p 64 N91 -11006 The variable-cycle engine - A solution to the economical GLEGG, STEWART A. L, FOTTNER, LEONHARD and environmental challenge of the future supersonic A ray-acoustics approach to fuselage scattering of rotor Test cases for computation of internal flows in aero transport p 45 A91-10969 noise engine components HAERTIG, JACQUES [ AIAA PAPER 90-4013 ] p 75 A91 -12525 IAGARD-AR-275] p 49 N91-11022 Modeling blade/vortex interactions GLIEBE, P. R. FOUREST, BERTRANO [ISL-R-107/89] p 14 N91-10016 Predicted vs. scale model and flight test UDF engine Research and development of high-pressure-exponent noise Rotor loads computation using singularity methods and fuel-rich propellants [AIAA PAPER 90-3936] p 68 A91-12452 application to the noise prediction | ONERA, TP NO. 1990-91] p 55 A91-11770 GNEMMI, P. [ISL-PU-301/90] p 15 N91-10018 FOURNIER, G. Modeling blade/vortex interactions HAGEMEYER, D. A. The CEPRA 19 anechoic wind tunnel [ISL-R-107/89] p 14 N91-10016 The design approach used in the synthesis of the B-2 IONERA.TP NO. 1990-721 p 51 A91-11760 GNOFFO, PETER A. lateral-directional control laws FRADIN, CH. A comparative study of Navier-Stokes codes for (AIAA PAPER 90-3255] p 50 A91-12929 Detailed measurements of the flow field at the outlet high-speed flows p 20 N91-10869 HAHN, K.-U. of a backswept transonic centrifugal impeller equipped with GODDARD, K. Effect of wind and wind variation on aircraft a vaned diffuser Re-engining: Real stage 3 compliance plus other flight-paths p 41 N91-10972 | ONERA. TP NO. 1990-1011 p4 A91-11777 FRANKE, M. E. benefits Wind models for flight simulation p 53 N91-10975 [PNR-90755] p48 N91-10075 Suppression of flow-induced pressure oscillations in HALL, DAVID G. GOGINENI, S. cavities The effect of swirl recovery vanes on the cruise noise Instability characteristics of a low aspect ratio (AIAA PAPER 90-40181 P8 A91-12530 of an advanced propeller rectangular jet FRICKE, MANFRED [AIAA PAPER 90-3932] p 68 A91-12448 (AIAA PAPER 90-3962] p 70 A91-12476 Simulation of automated approach procedures Noise measurements from an ejector suppressor nozzle GOLUB, ROBERT A. considering dynamic flight operations in the NASA Lewis 9- by 15-foot low speed wind tunnel Some far-field acoustics characteristics of the XV-15 p35 N91-11008 [AIAA PAPER 90-3983] p 73 A91-12496 tilt-rotor aircraft FRIEDMANN, P. P. Noise measurements from an ejector suppressor nozzle [ AIAA PAPER 90-3971 ] p 71 A91 -124B4 Influence of unsteady aerodynamics on rotor blade in the NASA Lewis 9- by 15-fooi low speed wind tunnel GONZALEZ BLAZOUEZ, A. L. aeroelastic stability and response p 37 A91-12894 [NASA-TM-103628] p 76 N91-11493 Mathematical modelling for analysis of nonlinear aircraft FUJIEDA, ATSUTOSHI The effect of swirl recovery vanes on the cruise noise dynamics p 50 A91-11820 Wind tunnel test of redundant vane-type flow-direction of an advanced propeller GOODSELL. A. M. sensing systems | NASA-TM-103625] p 77 N91-11494 Euler and potential computational results for selected [NAL-TM-590] p 44 N91-10057 HALL, PHILIP aerodynamic configurations p 10 A91-12760 FUJITA, TOSHIMI Vortex instabilities in 3D boundary layers: The Euler and potential experiment/CFD correlations for a Wind tunnel test of redundant vane-type flow-direction relationship between Goertler and crossflow vortices transport and two delta-wing configurations sensing systems [NASA-CR-187456] p 15 N91-10022 [NASA-TM-102208] p 14 N91-10014 [NAL-TM-590I p 44 N91-10057 HAMPTON, LAWRENCE GOPINATH, R. FUJITSUNA, YOSHIYUKI Tests of the general fire suppression concentrate Wall interference studies Configuration control and airworthiness management Pyrocap B-136 [PD-CF-9012] p59 N91-10232 p 77 A91-12233 [DOT/FAA/CT-TN90/21] p 26 N91-10029 GOTTWALD, JAMES A. FULLER, C. R. HANAMATSU, TAKESHI Aircraft interior noise reduction by alternate resonance Active control of interior noise in model aircraft fuselages The establishment and performance test of PAPI tuning using piezoceramic actuators (Precision Approach Path Indicator) System for NAL STOL [NASA-CR-186879] p 76 N91-11488 [AIM PAPER 90-3922] p 67 A91-12438 aircraft GOZLAN, A. Identification of aerospace acoustic sources using (NAL-TM-579] p 28 N91-10030 Development of the Griffon II turbo-ramjet sparse distributed associative memory HANSEN, C. H. p45 A91-10954 [AIAA PAPER 90-3992] p 73 A91-12505 Active control of interior noise in model aircraft fuselages GRANDJACOUES, M. FULLER, CHRIS R. using piezoceramic actuators S4MA hypersonic facility - Flow angularities The identification of helicopter noise using a neural [AIAA PAPER 90-3922] p 67 A91-12438 measurements in Ihe S4MA wind tunnel network HANSON, D. B. [ONERA. TP NO. 1990-85) p 51 A91-11766 [AIAA PAPER 90-3973] p 72 A91-12486 Unsteady airloading panel method for prop-fans GREEN, STEVEN M. [AIAA PAPER 90-3914] p 67 A91-12430 Time-based operations in an advanced ATC Noise radiation of propeller loading sources with angular environment p 29 N91-10958 inflow A piloted simulator evaluation of a ground-based 4-D [AIAA PAPER 90-3955] p 70 A91-12471 GANLEY, G. descent advisor algorithm p 33 N91-11000 HARDIN, JAY C. Tne Rolls Royce/SNECMA Olympus 593 engine GREENE, OAVID L. Removing spurious reflections from CFD solutions by operational experience and the lessons learned Energy efficiency improvement potential of commercial • using the Complex Cepstrum p45 A91-10958 aircraft to 2010 [AIAA PAPER 90-3947] p 69 A91-12463 GAO, SHUCHUN [DE90-014767] p 39 N91-10046 HARRIS, ROY V. A study of implicit space-marching method for the GRIFFITHS, M. H. The potential for a new era of supersonic and hypersonic supersonic viscous flow over the blunt cone Casting alloys for the jet age aviation p 1 A91-10961 p4 A91-11831 (PNR-90723] p56 N91-10168 HARTROPP, S. J. GARDNER, BRYCE K. GROENEWEG, J. F. Aero engine design factors for a low fuel price An experimental technique of separating airborne and Near-field noise of a single rotation propfan at an angle scenario structure-borne noise using wavenumber-frequency of attack [PNR-90681] p47 N91-10066 spectrum (AIAA PAPER 90-3953] p 70 A91-12469 HAUSMANN, J. S. [AIAA PAPER 90-3969] p 71 A91-12483 GROSVELO, F. W. Boundary element analysis of sound scattered by a GARZA, RUBEN G. Transition control of instability waves over a flexible moving surface Sonic boom environment under a supersonic military surface in the presence of an acoustic field [AIAA PAPER 90-3944] p 69 A91-12460 operating area [AIAA PAPER 90-4008] p 74 A91-12520 HEEG, JENNIFER [AIAA PAPER 90-4032] p 63 A91-12541 GRUBER, M. Computation of maximum gust loads in nonlinear aircraft GAVALI, SHARAD Measurement of unsteady blade surface pressure on using a new method based on the matched filter approach Prediction of turbine rotor-stator interaction using a single rotation large scale advanced prop-fan with and numerical optimization p 60 N91-10317 Navier-Stokes methods p 20 N91-10881 angular and wake inflow at Mach numbers from 0.02 to Static and dynamic aeroelastic characterization of an GEA, LIE-MINE 0.70 aerodynamically heated generic hypersonic aircraft Computation of transonic flow over elastic rotor blade (NASA-CR-182123] p 47 N91-10065 configuration p 61 N91-10320 p23 N91-10906 GUERMCND, JEAN-LUC HEFNER, JERRY N. GEYER, GEORGE B. A unified unsteady lifting-line theory p8 A91-12575 Viscous drag reduction in boundary layers Tests of the general fire suppression concentrate GULIAEV, VALERII V. p58 A91-12688 Pyrocap B-136 Jets and lifting surfaces: Computer simulation Viscous drag reduction via surface mass injection [DOT/FAA/CT-TN90/21] p 26 N91-10029 p 13 A91-12913 p9 A91-12698

B-4 PERSONAL AUTHOR INDEX KAYNAK, UNVER

HEIDELBERG. L. J. HUBER, HELMUT B. Unsteady blade pressure measurements for the SR-7A MSB'S BO 108 design and development propeller at cruise conditions IMBB-UD-0568-90-PUB) p 40 N91-10055 JACOMIN, DAVID IAIAA PAPER 90-4022) p 75 A91-12533 HUDDLESTON, DAVID HOWARD The breakup of trailing-line vortices HEIMTSCH, T. Aerodynamic design optimization using computational p 20 N91-10867 Effect of wind and wind variation on aircraft fluid dynamics p 43 N91-11013 JAEGER, STEPHEN M. flight-paths p 41 N91-10972 HUDLICKA, EVA On the prediction of far field computational Wind models for flight simulation p 53 N91-10975 Fault recovery recommendation p 27 N91-10952 aeroacoustics of advanced propellers [AIAA PAPER 90-3996) p 73 A91-12509 HENNE, P. A. HUFFORD, G. Applied computational aerodynamics OVRhyp, scramjet test aircraft JAHNKE, CRAIG CHARLES Application of dynamical systems theory to nonlinear p9 A91-12751 (NASA-CR-187009) p 38 N91-10041 Innovation with computational aerodynamics - The HUG, GILLES aircraft dynamics p 43 N91-11014 divergent trailing.edge airtoil p 10 A91-12759 Influence of chromium and molybdenum on the structural JAIN, PARVEEN HERBST, W. B. stability of a high strength damage tolerant P/M nickel A function-based approach to cockpit procedure aids The case of a hypersonic flight demonstrator p27 N91-10953 based alloy for turbine disks JAMESON, ANTONY p54 A91-10978 [ONERA, TP NO. 1990-100] p 55 A91-11776 HESS, J. L. HUGHES, CHRISTOPHER E. Full-potential. Euler. and Navier-Stokes schemes p 59 A91-12754 Linear potential schemes p 9 A91-12753 Aeroacoustic effects of reduced aft tip speed at constant JANSSENS, G. HEWITT, F. A. thrust for a model counterrotation turboprop at takeoff Optimisation of hybrid propulsion systems Detailed measurements of the flow field at the outlet conditions p 46 A91-10976 of a backswept transonic centrifugal impeller equipped with [AIAA PAPER 90-3933) p 68 A91-12449 a vaned diffuser HICKS, R. M. Aeroacoustic effects of reduced aft tip speed at constant [ONERA. TP NO. 1990-101] p4 A91-11777 Euler and potential computational results for selected thrust for a model counterrotation turboprop at takeoff aerodynamic configurations p 10 A91-12760 Jl, GUANG-HUA conditions Euler and potential experiment/CFD correlations for a Application of cryogenic wind tunnel with liquid nitrogen [NASA-TM-103608) p 76 N91-10703 and selection of its temperature level p 52 A91-12724 transport and two delta-wing configurations HUGHES, DAVID JOHE, CH. (NASA-TM-102208] p 14 N91-10014 Extensive MD-11 automation assists pilots, cuts HIGGINBOTHAM, G. J. S. Modeling blade/vortex interactions workload p 37 A91-12165 The role of process modelling in manufacture and (ISL-R-107/89] p 14 N91-10016 HUGOUVIEUX, M. JOHNSON, A. B. design Comparison of afterbody test setups for combat aircraft [PNR-90702] p65 N91-11416 model The aerodynamic effects of nozzle guide vane shock wave and wake passing on a transonic turbine rotor HILGENSTOCK, ACHIM [ONERA, TP NO. 1990-70] p 51 A91-11758 A contribution to the numerical solution of transonic flow p24 N91-10915 HUH, K. S. JOHNSON, O. P. around a delta wing by solving Navier-Stokes equations Numerical simulation of acoustic diffraction of [DLR-FB-90-13] p 16 N91-10026 Installation effects on counter rotating propeller noise two-dimensional rigid bodies in arbitrary flows [AIAA PAPER 90-4023] p 75 A91-12534 HO, C. M. (AIAA PAPER 90-3920] p 67 A91-12436 Coherent structure induced pressure fluctuations in an JOHNSON, DENNIS A. elliptic jet More accurate predictions with transonic Navier-Stokes [AIAA PAPER 90-3963) p 70 A91-12477 methods through improved turbulence modeling HOENLINGER, H. p 17 N91-10850 A quarter of a century of aeroelastic cooperation IDOSOR, FLORENTINO JOHNSON, F. T. between research and industry (a review). Part 1: Fighter Comparison of NASTRAN analysis with ground vibration Application of computational methods in aeroacoustics airplanes and helicopters p 78 N91-10931 results of UH-60A NASA/AEFA test configuration [AIAA PAPER 90-3917] p 67 A91-12433 HOERMANN, ANDREAS [NASA-CR-184565] p 61 N91-10333 JOHNSTON, l_ J. Simulation of automated approach procedures IGAR, KARYN Solution of the Euler equations on unstructured grids considering dynamic flight operations Project HyBuJET for two-dimensional compressible flow p3 A91-11160 p35 N91-11008 [NASA-CR-187011] p 38 N91-10040 JOSHI, PRAKASH B. HOGENDOORN, R. A. IMBERT, NICOLE Propulsion simulation for magnetically suspended wind Bayesian multi-sensor tracking for advanced air traffic Four dimensional navigation in air traffic with 4-D tunnel models control systems p 34 N91-11003 navigation aircraft p 31 N91-10991 [NASA-CR-182093] p 53 N91-11027 HOLDEMAN, JAMES D. INAGAKI, TOSHIHARU JOU, WEN-HUEI A numerical study of the hot gas environment around The establishment and performance test of PAPI Numerical simulations of oscillatory cold flows in an a STOVL aircraft in ground proximity p 21 N91-10887 (Precision Approach Path Indicator) System for NAL STOL axisymmetric ramjet combustor p2 A91-10329 HOLST, TERRY L aircraft Modes of oscillation in a nonreacting ramjet combustor Navier-Stokes computations about complex [NAL-TM-579] p 28 N91-10030 . flow p 2 A91-10330 configurations including a complete F-16 aircraft Flight evaluation test of the PAPI (Precision Approach JULLIARD, J. p 12 A91-12772 Path Indicator) System Experimental study of noise sources and acoustic Computational Fluid Dynamics Program at NASA Ames [NAL-TM-592] p 29 N91-10966 propagation in a turbofan model Research Center p 16 N91-10840 INNOCENT), M. [AIAA PAPER 90-3950] p 69 A91-12466 HONG, JINSEN Performance-robustness trade off of eigenstructure Vortex development on cruciform canard configurations assignment applied to rotorcraft p 49 A91-11155 - at supersonic speeds p5 A91-11843 Pilot modelling techniques for the analysis of aircraft K HORNE, W. CLIFTON linear dynamic behaviour p 49 A91 -11158 KARAMCHETI, KRISHNAMURTY Some aeroacoustic and aerodynamic applications of the INOUE, SHIGEO Some aeroacoustic and aerodynamic applications of the theory of nonequilibrium thermodynamics Effects of coolant injection on turbine aerodynamic theory of nonequilibrium thermodynamics [AIAA PAPER 90-3989] p 73 A91-12502 characteristics. Part 1: Test turbine and apparatus [AIAA PAPER 90-3989) p 73 A91-12502 HOSOE, NOBUYUKI [NAL-TM-585-PT-1] p 47 N91-10059 KARASAWA, TOSHIO Characteristics of piping interference elimination unit Experimental investigation on the effect of coolant Characteristics of piping interference elimination unit used in the high-speed wind tunnel test of ASUKA seven injection on turbine aerodynamic characteristics. Part 2: used in the high-speed wind tunnel test of ASUKA seven percent semi-born prototype Effects of injection from rotor casing with 30 deg slanted percent semi-born prototype (NAL-TM-588) p 13 N91-10003 holes [NAL-TM-588] p 13 N91-10003 HOUGH, JOSEPH [NAL-TM-587-PT-2] p 47 N91-10060 IQBAL, A. KARGER, INGO Interaction between rotors of a counter rotating Air rescue in the Federal Republic of Germany propeller The role of primary carbides in fatigue crack propagation in aeroengine bearing steels p 55 A91-11806 [ETN-90-97878] p 28 N9M0963 [AIAA PAPER 90-3976) p 7 A91-12489 KARNIADAKIS, G. E. HOWELLS, PETER J. ISHII, R. The screech of round choked jets, revisited Time-dependent jet flow and noise computations Aircraft trajectory: Prediction and control in the air IAIAA PAPER 90-3961) p 70 A91-12475 [AIAA PAPER 90-3980) p 72 A91-12493 transport flight management computer systems KAUFMANN, B. ITO, TAKESHI p41 N91-10976 Effect of wind and wind variation on aircraft Practical flight paths for microwave-powered airplanes HOYING, D. flight-paths p 41 N91-10972 [NAL-TR-1052T] p 40 N91-10054 Supersonic combustion engine testbed. heat lightning Wind models for flight simulation p 53 N91 -10975 ITOH, FUMIKO [NASA-CR-187010] p 47 N91-10061 KAWAHARA, HIROYASU A consideration on flight paths for microwave-powered Configuration, function and performance of the flight HSIAO, F. B. airplanes simulation test facility and its motion simulation system Forcing level effect of internal acoustic excitation on [NAL-TR-1051] p39 N91-10053 [NAL-TM-575] p 52 N91-10080 the improvement of airtoil performance IWASAKI, AKIHITO [AIAA PAPER 90-4010) p74 A91-12522 Wind tunnel test of redundant vane-type flow-direction Function and performance of visual simulation unit of HU, TIEH-FENG sensing systems flight simulation test facility Flow and acoustic properties of low Reynolds number INAL-TM-590) p 44 N91-10057 [NAL-TM-581] p 52 N91-10082 underexpanded supersonic jets p3 A91-11198 IZARD, M. Flight simulator evaluation test of multi-functional display HUA, YAONAN L.D.V. applied to measurements between two discs in unit A three-dimensional incompressible Euler flow solution high speed rotation [NAL-TM-596] p 53 N91-11026 in turbomachinery p 5 A91 -11841 [ONERA. TP NO. 1990-94] p 58 A91-11773 KAYNAK, UNVER HUARD, J. IZUMI, K. H. Navier-Stokes computations about complex A technique for measuring unsteady aerodynamics in Use of 4-D RNAV in time-based en route arrival configurations including a complete F-16 aircraft turbomachinery P 58 A91 -12421 metering p 33 N91-10997 p 12 A91-12772

B-5 KEITH, THEO G., JR. PERSONAL AUTHOR INDEX

KEITH, THEO G., JR. Prediction of the noise from a propeller at angle of LEE, DUCK-JOO Thermal analysis of engine inlet anti-icing systems attack Numerical simulation of vortex-wedge interaction p35 A9M0341 (NASA-TM-103627] p 77 N91-11495 [AIAA PAPER 90-3918] p6 A91-12434 KELBLE, C. KRIST, SHERRIE L. LEE, ELIZABETH M. Supersonic combustion engine testbed, heat lightning An embedded grid formulation applied to delta wings Conical Euler simulation and active suppression of delta [NASA-CR-187010] p 47 N9M0061 p22 N91-10891 wing rocking motion KENDALL, DEWAYNE KROO, I LAN [NASA-TM-102683] p 22 N91-10904 Project HyBuJET The sonic boom of an oblique flying wing LEE, KYUNG-TAE [NASA-CR-187011] p 38 N91-10040 [AIAA PAPER 90-4002] p 74 A91-12515 Controlled vortical flow on delta wings through unsteady KROTHAPALLI, A. KERSCHEN, E. J. leading edge blowing p 43 N91-11011 Instability characteristics of a low aspect ratio Influence of airfoil nose radius on sound generated by LEE, YOONSANG rectangular jet gust interactions Aerodynamic interaction of counter rotating propellers [AIAA PAPER 90-3962] p 70 A91-12476 [AIAA PAPER 90-3912] p 66 A91-12428 p23 N91-10910 KUMAR, AJAY KHAVARAN, ABBAS A comparative study of Navier-Stokes codes for LEFAS, C. C. Noise measurements from an ejector suppressor nozzle high-speed flows p 20 N91-10869 The use of downlinked measurements to track civil in the NASA Lewis 9- by 15-foot low speed wind tunnel aircraft p 34 N91-11004 KUO, CHUN-PAO [AIAA PAPER 90-3983] p 73 A91-12496 The instability of combustion in propulsion engines LELAIT, L. Noise measurements from an ejector suppressor nozzle p56 N91-10141 Thermal barrier coatings - Microstructural investigation in the NASA Lewis 9- by 15-foot low speed wind tunnel KUZNETSOV, V. B. after annealing INASA-TM-103628] p 76 N91-11493 Fluctuations of a shock wave generated by boundary [ONERA. TP NO. 1990-62] p 55 A91-11751 KHON'KIN, A. D. layer separation p6 A91-12019 LEMASURIER, PHILIP A three-dimensional boundary layer on bodies with a Helicopter far-field acoustic levels as a function of slight cross-sectional asymmetry at small angles of reduced main-rotor advancing blade-tip Mach number attack p5 A91-11909 [NASA-TM-102684] p 76 N91-10699 KIM, YOUNG-NAM LENT, H.-M. Numerical simulation of vortex-wedge interaction LABBE, J. Noise mechanisms of transonic vortex airfoil [AIAA PAPER 90-3918] p6 A91-12434 LD.V. applied to measurements between two discs in interaction high speed rotation KIMURA, TAKEO (AIAA PAPER 90-3972] p 71 A91-12485 [ONERA. TP NO. 1990-94] p 58 A91-11773 Wind tunnel test of redundant vane-type flow-direction LEWIS, G. M. LAINE, SEPPO sensing systems The evolution of the bypass engine [NAL-TM-590] p44 N91-10057 Three-dimensional viscous/inviscid coupling in subsonic [PNR-90707] p47 N91-10068 flow KING, J. E. [REPT-B-24] p 15 N91-10023 LEWIS, R. I. The role of primary carbides in fatigue crack propagation Application of the vortex cloud method to cascades in aeroengine bearing steels p 55 A91-11806 Calculation of three-dimensional viscous/inviscid interaction in subsonic flow p3 A91-11347 KIRKER, T. J. [REPT-B-25] p 16 N91-10024 LEWY, S. Procurement and testing of a 1/5 scale advanced Experimental study of noise sources and acoustic counter rotating preplan model LANGENBAHN, A. Supersonic combustion engine testbed, heat lightning propagation in a turbofan model (AIAA PAPER 90-3975] p 46 A91-12488 [AIAA PAPER 90-3950] p 69 A91-12466 KLEB, WILLIAM L [NASA-CR-187010J p 47 N91-10061 LANGHI, R. G. Space-structure determination of the acoustic field Temporal-adaptive Euler/Navier-Stokes algorithm for Euler and potential computational results for selected generated by a helicopter turboshaft engine unsteady aerodynamic analysis of airfoils using [AIAA PAPER 90-40121 p 46 A91-12524 unstructured dynamic meshes aerodynamic configurations p 10 A91-12760 [NASA-TM-102734] p 24 N91-10919 Euler and potential experiment/CFD correlations for a LI, FENG transport and two delta-wing configurations Application of LU-ADI algorithm in two-dimension KLEITZ, PIERRE Twenty years of Concorde - The experience of Air [NASA-TM-102208] p 14 N91-10014 transonic flow p 5 A91 -11848 LAVIEC, G. France P 25 A91-10959 LIEBECK, ROBERT H. KNOX, CHARLES E. The Rolls Royce/SNECMA Olympus 593 engine Subsonic airfoil design p9 A91-12756 NASA transport systems research vehicle B-737 data operational experience and the lessons learned LINTZ, ANDREW L link system and display formats p45 A91-10958 Propulsion simulation for magnetically suspended wind LAVRICH, P. L [NASA-TM-102717] p 44 N91-10058 tunnel models A flight test facility design for examining digital The role of leading edge vortex flows in prop-fan [NASA-CR-182093] p 53 N91-11027 interaction noise information transfer p 28 N91-10962 LIU, CHING SHI [AIAA PAPER 90-3977] p 72 A91-12490 The 4-D descent trajectory generation techniques under Prediction of inviscid stagnation pressure losses in LAVRICH, PHILIP L realistic operating conditions p 32 N91-10994 supersonic inlet flows p 12 A91-12903 Vortex structure of wakes behind an advanced propeller KOELLE, DIETRICH E. LIU, OIUSHENG at takeoff load conditions System optimization structure and propulsion of a An efficient method for solving transonic flow about [AIM PAPER 90-3978] p 72 A9M2491 hypersonic space transportation system (Saenger) plane cascades with a large nosing p4 A91-11839 LAWRENCE, SCOTT L p54 A91-10972 Application of CFO to sonic boom near and mid flow-field LIU, SANDY R. KOENIG, K. prediction The acoustic results of a United Techologies scale model A quarter of a century of aeroelastic cooperation (AIAA PAPER 90-3999] p7 A91-12512 helicopter rotor tested at DNW between research and industry (a review). Part 2: Transport [AIAA PAPER 90-4035] p 75 A91-12543 airplanes and other civil applications p 40 N91-10932 Application of CFD to sonic boom near and mid flow-field prediction LIU, ZHIZHONG KOENIG, REINHARD [NASA-TM-102867] p 14 N91-10015 A study of cylindrical interaction of turbulent boundary ContriDutions to the improvement of flight safety in wind LAYTON, CHUCK layer/shock with swept compression corners shear p4 A91-11836 [ESA-TT-1141] p28 N91-10965 Graphical interfaces for cooperative planning systems LOEHNER, R. KOIKE, YO p 27 N91-10956 Characteristics of piping interference elimination unit LE SANT, Y. Three dimensional unstructured grids for the solution used in the high-speed wind tunnel test of ASUKA seven Determination of kinetic heating on wind tunnel models of the Euler equations p 22 N91-10893 percent semi-born prototype by the surface temperature method LOEHR, K. F. (NAL-TM-588] p 13 N91-10003 [ONERA. TP NO. 1990-104] p4 A91-11779 Noise mechanisms of transonic vortex airfoil KORKACH, V. G. LEBEDEV, M. G. interaction Fluctuations of a shock wave generated by boundary Interaction of two supersonic radial gas flows [AIAA PAPER 90-3972] p 71 A91-12485 layer separation p6 A91-12019 p6 A91-12018 LOOMIS, JAMES P. KORKAN, KENNETH D. LECOMTE, C. A case study in fostering international HSCT On me prediction of far field computational The sonic boom problem p1 A91-10964 collaboration p 77 A91 -10970 aeroacoustics of advanced propellers LECOMTE, P. LOWRIE, B. W. [AIAA PAPER 90-3996] p 73 A91-12509 Supersonic air transport programs in the 60's Future supersonic transport propulsion optimisation KOROVIN, ANATOLII E. p 1 A91-10952 p45 A91-10968 Practical aerodynamics and flight dynamics of Yak-52 LEDY, J. P. Future supersonic transport populsion optimization and Yak-55 aircraft p 13 A91-12911 Comparison of afterbody test setups for combat aircraft [PNR-90737] p48 N91-10071 KRECH, ROBERT H. model LU, PONG-JEU Propulsion simulation for magnetically suspended wind (ONERA. TP NO. 1990-70] p 51 A91-11758 Numerical simulation of supersonic mixing layer using tunnel models high resolution scheme LEE, ALFRED T. [NASA-CR-182093] p 53 N91-11027 (AIAA PAPER 90-4025] p 8 A91-12535 Assessing information transfer in full mission flight KREJSA, EUGENE A. LUCAS, C. A. simulations p 26 N91-10946 Prediction of the noise from a propeller at angle of The effects of aerofoil profile on wing buffet at low attack Terminal weather information management speeds p2 A91-11151 [AIAA PAPER 90-3954] p 70 A91-12470 p64 N91-10960 LUCAS, MICHAEL J. Noise measurements from an ejector suppressor nozzle LEE, B. H. K. Sonic boom environment under a supersonic military in the NASA Lewis 9- by 15-foot low speed wind tunnel Transonic buffet on a supercritical aerofoil operating area [AIAA PAPER 90-3983] p 73 A91-12496 p2 A91-11157 [AIAA PAPER 90-4032] p 63 A91-12541 Noise measurements from an ejector suppressor nozzle LEE, C. S. LUCKRING, JAMES M. in the NASA Lewis 9- by 15-foot low speed wind tunnel Calculation of the rotor induced download on airfoils Navier-Stokes solutions about the F/A-18 f orebody-LEX [NASA-TM-103628] p 76 N91-11493 p 19 N91 -10864 configuration p 18 N91 -10860

B-6 PERSONAL AUTHOR INDEX NAKAYAMA, SHUICHI

LYONNET, H. MCCORMICK, D. C. MINODA, MITSUHIRO Comparison of aftertody test setups for combat aircraft The role of leading edge vortex flows in prop-fan Effects of coolant injection on turbine aerodynamic model interaction noise characteristics. Part 1: Test turbine and apparatus (ONERA. TP NO. 1990-70) p 51 A91-11758 [AIAA PAPER 90-3977) p 72 A91-12490 [NAL-TM-585-PT-1] p 47 N91-10059 MCCORMICK, DUANE C. Experimental investigation on the effect of coolant Vortex structure of wakes behind an advanced propeller injection on turbine aerodynamic characteristics. Part 2: M at takeoff load conditions Effects of injection from rotor casing with 30 deg slanted [AIAA PAPER 90-3978] p 72 A91-12491 holes MA, MINGSHENG [NAL-TM-587-PT-2] p 47 N91-10060 The calculation method for subsonic longitudinal and MCCOY, C. ELAINE Graphical interfaces for cooperative planning systems MITSUBORI, SUSUMU lateral aerodynamic characteristics of complete aircraft p27 N91-10956 Characteristics of piping interference elimination unit configuration pS A91-11844 used in the high-speed wind tunnel test of ASUKA seven MACDONALD. DAVID A. MCCROSKEY, WILLIAM J. Numerical simulation of rotorcrafl p 19 N91-10863 percent semi-bom prototype British Airways operational experience with Concorde [NAL-TM-588] p 13 N91-10003 p26 A91-10960 MCCURDY, DAVID A. MACK. ROBERT J. Aircraft en route noise annoyance MOKRY, M. Residual interference and wind-tunnel wall adaptation The design of two sonic boom wind tunnel models from [AIAA PAPER 90-4028] p 63 A91-12537 p 52 A91 -12890 conceptual aircraft which cruise at Mach numbers of 2.0 MCGUIRK, JAMES J. and 3.0 Shock capturing using a pressure-correction method MONGIA, H. C. [AIAA PAPER 90-4026] p 52 A91-12536 p59 A91-12887 Three-dimensional combustor performance validation with high-density fuels p 55 A91-10345 MADAVAN, NATERI K. MCLAUGHLIN, D. K. Computational analysis of rotor-stator interaction in Flow and acoustic properties of low Reynolds number MORELLO, SAMUEL A. turbomachinery using zonal techniques underexpanded supersonic jets p3 A91-11198 Aviation Safety/Automation Program Conference [NASA-CP-3090] p 26 N91-10936 p 10 A91-12764 MCLAUGHLIN, DENNIS K. Prediction of turbine rotor-stator interaction using Experiments on the aerodynamic noise sources in Aviation safety/automation program overview Navier-Stokes methods p 20 N91-10881 centrifugal turbomachinery p26 N91-10941 MADDALON, D. V. [AIAA PAPER 90-3948] p 69 A91-12464 MORITZ, R. R. Applied aspects of laminar-flow technology MCLEAN, D. Design/development issues for high bypass ratio fans p8 A91-12690 Aircraft flight in wind-shear p 41 N91-10973 [PNR-90758] p48 N91-10076 MADSON, MICHAEL D. MCMASTERS, J. H. MOULTON, CAREY l_ Toward the routine aerodynamic analysis of complex Computational aerodynamics applied to high-lift Sonic boom environment under a supersonic military configurations p 11 A91-12770 systems p 10 A91-12761 operating area [AIAA PAPER 90-4032] p 63 A91-12541 TranAir Recent advances and applications MCMILLIN, S. NAOMI p 19 N91-10862 The use of a Navier-Stokes code in the wing design MOURTOS, N. J. MAESTRELLO, L. process p 21 N91-10889 Control of vortical separation on a circular cone p3 A91-11162 Transition control of instability waves over a flexible MEADOWS, KRISTINE R. surface in the presence of an acoustic field Removing spurious reflections from CFD solutions by MOVER, S. A. [AIAA PAPER 90-4008] P 74 A91-12520 using the Complex Cepstrum Euler and potential experiment/CFD correlations for a MAITA, MASATAKA [AIAA PAPER 90-3947] p 69 A91-12463 transport and two delta-wing configurations [NASA-TM-102208] p 14 N91-10014 Noise characteristics of the Japan's experimental MEHTA, JAYESH M. powered lift STOL aircraft Thermoacoustics of unsteady combustion MOYNES, J. F. [AIAA PAPER 90-4014] p 75 A91-12526 [AIAA PAPER 90-3928] p 67 A91-12444 Design technologies utilized in the development of the MANE, LAURE B-2 flight control system MEIER, G. E. A. Parallelization on a multi-processor system of a solving [AIAA PAPER 90-3254] p 50 A9M2928 Noise mechanisms of transonic vortex airfoil method for the unsteady Navier-Stokes equations at high interaction MUELLER, ARNOLD W. Reynolds numbers [AIAA PAPER 90-3972] p 71 A91-12485 Helicopter far-field acoustic levels as a function of [ESA-TT-1116] p62 N91-11197 reduced main-rotor advancing blade-tip Mach number MELTON, J. E. [NASA-TM-102684] p 76 N91-10699 MANES, J. P. Euler and potential computational results for selected An evaluation of various concepts of reducing aerodynamic configurations p 10 A91-12760 MUELLER, K. J. supersonic jet noise Noise mechanisms of transonic vortex airfoil Euler and potential experiment/CFD correlations for a [AIM PAPER 90-3982] p 72 A91-12495 interaction transport and two delta-wing configurations [AIAA PAPER 90-3972] p 71 A91-12485 MANWARING, STEVEN R. [NASA-TM-102208] p 14 N91-10014 Periodic rotor-blade aerodynamics including loading MUNGUR, P. MELVIN, R. G. effects p 2 A91-10337 Thermoacoustics of unsteady combustion Application of computational methods in aeroacoustics [AIAA PAPER 90-3928] p 67 A91-12444 MARCOLINI, MICHAEL A. [AIAA PAPER 90-3917] p 67 A91-12433 The acoustic results of a United Techologies scale model MURAKAMI, YOSHITAKA MENON, SURESH helicopter rotor tested at DNW The establishment and performance test of PAPI Numerical simulations of oscillatory cold flows in an [AIAA PAPER 90-4035] p 75 A91-12543 (Precision Approach Path Indicator) System for NAL STOL axisymmetric ramjet combustor p 2 A91-10329 MARTIN, DAVID J. aircraft Modes of oscillation in a nonreacting ramjet combustor Progress in certifying F402-RR-408: The improved [NAL-TM-579] p 28 N91-10030 rlow p 2 A91-10330 Pegasus engine for AV-8B and Harrier 2 plus MYERS, M. K. [PNR-90719] p40 N91-10056 Numerical simulation and active control of combustion Boundary element analysis of sound scattered by a MARTY, MICHEL instability in a ramjet combustor moving surface Influence of chromium and molybdenum on the structural [AIAA PAPER 90-3930] p 46 A91-12446 [AIAA PAPER 90-3944] p 69 A91-12460 stability of a high strength damage tolerant P/M nickel MERLEN, ALAIN based alloy for turbine disks Theory of slightly blunted axisymmetric power-law [ONERA, TP NO, 1990-100] p 55 A91-11776 bodies at small angle of attack in hypersonic flow N p8 A91-12559 MASSEY, K. C. An evaluation of various concepts of reducing MERRILL, B. J. NAEEM, R. K. supersonic jet noise Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Transonic computations on a natural grid [AIAA PAPER 90-3982] p 72 A91-12495 Oxidation Tester) p 13 A91-12904 [DE90-010929] p 56 N91-11128 MASSON, CHRISTIAN NAGEL, ROBERT T. Research and development of high-pressure-exponent MEVREL, M. Interaction between rotors of a counter rotating fuel-rich propellants Thermal barrier coatings - Microstructural investigation propeller [ONERA, TP NO, 1990-91] p 55 A91-11770 after annealing [AIAA PAPER 90-3976] p 7 A91-12489 [ONERA, TP NO. 1990-62] p 55 A91-11751 MATHUR, GOPAL P. NAGESWARA RAO, B. MEYER, ROBERT H. Estimation of the turbulent boundary layer pressure Large-amplitude vibrations of free-free tapered beams Detection of airplanes in aerial imagery wavenumber-frequency spectrum using a fixed probe p57 A91-11199 p 59 A91-12824 pair NAKAMURA, MASAYOSHI MIASNIKOV, A. V. . [AIAA PAPER 90-3926] p 67 A91-12442 Characteristics of piping interference elimination unit Interaction of two supersonic radial gas flows used in the high-speed wind tunnel test of ASUKA seven An experimental technique of separating airborne and p6 A91-12018 structure-borne noise using wavenumber-frequency percent semi-bom prototype MICHARD, P.-J. [NAL-TM-588] p 13 N91-10003 spectrum L.D.V. applied to measurements between two discs in (AIAA PAPER 90-3969] p 71 A91-12483 high speed rotation NAKAMURA, R. MAULL, D. J. [ONERA, TP NO. 1990-94] p 58 A91-11773 DOD responsibilities on Federal aviation and national The effects of aerofoil profile on wing buffet at low MIELE, A. airspace system matters speeds p2 A91-11151 Optimal trajectories of aircraft and spacecraft [PB90-218827] p2 N91-10001 MAVRIPLIS, DIMITRI J. p 29 N91-10968 NAKAO, SHIGEHIDE Turbulent flow calculations using unstructured and MIKLOSOVIC, DAVE Aerodynamic heating in the interaction regions of shock adaptive meshes Project HyBuJET waves and turbulent boundary layers induced by [NASA-CR-182102] P 14 N91-10010 [NASA-CR-187011] p 38 N91-10040 sweptback blunt fins p6 A91 -12226 MCCAUGHAN, F. E. MINCIOTTI, R. l_ NAKAYAMA, SHUICHI Bifurcation analysis of axial flow compressor stability Pilot modelling techniques for the analysis of aircraft Motion analysis of RPRVs using on-board and p44 A91-10245 linear dynamic behaviour p 49 A91-11156 ground-based measurements p 37 A91-12224

B-7 NALLASAMY, M. PERSONAL AUTHOR INDEX

NALLASAMY, M. OHSUMI, KEN PETROV, A. I. Near-field noise of a single rotation propfan at an angle Noise characteristics of the Japan's experimental A self-organizing stochastic control system adaptable of attack powered lift STOL aircraft to changing perturbation characteristics (AIAA PAPER 90-3953] p 70 A91-12469 [AIAA PAPER 90-4014] p 75 A91-12526 p65 A91-11353 Unsteady blade pressure measurements for the SR-7A OKABE, MASANORI PFEIFFER, NEAL J. propeller at cruise conditions Configuration, function and performance of the flight Computational aerodynamics applied to general [AIAA PAPER 90-4022] p 75 A91-12533 simulation test facility and its motion simulation system aviation/business aircraft p11 A91-12767 NAPOLITANO, MARCELLO ROSARIO [NAL-TM-575] p 52 N91-10080 PHATAK, ANIL V. A new approach to the flight control system Function and performance of visual simulation unit of A function-based approach to cockpit procedure aids reconfiguration following a battle damage and/or generic flight simulation test facility p27 N91-10953 [NAL-TM-581) p 52 N91-10082 failure on a control surface p 50 N91-11023 PHILLIPS, E. P. OLOALE, PAUL NARRAMORE, J. C. The growth of short cracks in 4340 steel and Douglas flight deck design philosophy Application of computational fluid dynamic methods to aluminum-lithium 2090 p 62 N91-11247 p40 N91-10939 the component aerodynamic design of the V-22 Osprey PHILLIPS, JAMES E. ORSZAG, S. A. tilt rotor vehicle p 11 A91-12768 An experimental technique of separating airborne and Time-dependent jet flow and noise computations NATHMAN, JAMES K. structure-borne noise using wavenumber-frequency [AIAA PAPER 90-3961 ] p 70 A91-12475 spectrum Thermal analysis of engine inlet anti-icing systems OYIBO, GABRIEL [AIAA PAPER 90-3969] p 71 A91-12483 p 35 A91-10341 Formulation of three-dimensional hodograph method PHILLIPS, WILLIAM H. NEEDLEMAN, KATHY E. and separable solutions for nonlinear transonic flows Determination of the pressure drag of airfoils by The design of two sonic boom wind tunnel models from p 12 A91-12886 conceptual aircraft which cruise at Mach numbers of 2.0 integration of surface pressures and 3.0 [NASA-TM-102722] p 50 N91-10078 [AIAA PAPER 90-4026] p 52 A91-12536 PICKARD, A. C. NEGRE, Y. Introduction: Needs and approaches to reliability and All-electric flight control experiments and experiments PAGE, GARY J. quality assurance in design and manufacture with a sidestick on the Concorde p 49 A91-10955 Shock capturing using a pressure-correction method [PNR-90683] p60 N91-10297 PIERCE, ALLAN D. NEWKIRK, DENNIS p59 A91-12887 Weak shock propagation through a turbulent Soviet space planes p 54 A91-11737 PALMER,EVERETT A function-based approach to cockpit procedure aids atmosphere NEWMAN, JAMES C., JR. p27 N91-10953 [AIAA PAPER 90-4031 ] p 75 A91-12540 The growth of short cracks in 4340 steel and PIRZADEH, S. . aluminum-lithium 2090 p 62 N91-11247 PALMER, MICHAEL Inflight replannig for diversions p 27 N91-10955 Three dimensional unstructured grids for the solution NICHOLAS, D. J. PALUMBO, DAN of the Euler equations p 22 N91-10893 Design/development issues for high bypass ratio fans Parallelized reliability estimation of reconfigurable' PISCHKE, KEITH M. [PNR-90758] p48 N91-10076 computer networks Cockpit avionics integration and automation NICOL, DAVID M. [NASA-CR-182101] p65 N91-11430 p44 N91-10938 Parallelized reliability estimation of reconfigurable PARIKH, P. PLENTOVICH, ELIZABETH B. computer networks Three dimensional unstructured grids for the solution Navier-Stokes solutions for flows related to store [NASA-CR-182101] p 65 N91-11430 of the Euler equations p 22 N91-10893 separation p 18 N91-10861 NIKOLAEV, K. V. PARK, JIN-HO PLOTKIN, KENNETH J. Flow of a rarefied gas around a sphere in the presence Numerical simulation of vortex-wedge interaction Sonic boom focal zones due to tactical aircraft of injection p6 A91-12020 [AIAA PAPER 90-3918] p6 A91-12434 maneuvers NITSCHKE-KOWSKY, P. PARKER, R. J. [AIAA PAPER 90-4003] p 74 A91-12516 Experimental study of instability modes in a Practical developments in holographic interferometry Sonic boom environment under a supersonic military three-dimensional boundary layer p 59 A91-12888 p57 A91-11152 operating area NOOR, AHMED K. Holographic interferometry for flow visualization studies [AIAA PAPER 90-4032] p 63 A91-12541 Computational technology for flight vehicles; in high speed fans p 46 A91 -11351 POISSON-dUINTON, PH. Proceedings of the Symposium, Washington, DC, Nov. 5-7. PARKER, STEVEN l_ European Symposium on the Future of High Speed Air 1990 p58 A91-11813 Development and application of linear and nonlinear Transport, Strasbourg, France, Nov. 6-8, 1989, Proceedings p 1 A91-10951 Research in Structures, Structural Dynamics and methods for interpretation of lightning strikes to in-flight Supersonic air transport programs in the 60's Materials, 1990 aircraft p 1 A91-10952 [NASA-CP-3064] p60 N91-10301 [NASA-CR-3974] p 64 N91-10548 PARROTT, TONY L PONTON, MICHAEL K. NORMAN, SUSAN D. Sound transmission through a high-temperature acoustic Instability of a supersonic shock-free elliptic jet Summary of the industry/NASA/FAA workshop on [AIAA PAPER 90-3959] p7 A91-12473 philosophy of automation: Promises and realities probe tube [AIAA PAPER 90-3991 ] p 73 A91-12504 POTAPCZUK, MARK G. p44 N91-10942 PARZYCH, D. Progress toward the development of an airfoil icing NORTHAM, G. BURTON Measurement of unsteady blade surface pressure on analysis capability p 19 N91-10866 Application of CFD codes for the simulation of scramjet a single rotation large scale advanced prop-fan with POTAPOV, VLADIMIR N. combustor flowfields p 20 N91-10873 angular and wake inflow at Mach numbers from 0.02 to Diagnostics of aviation electric machines NOSE, HIROYUKI 0.70 p37 A91-12919 Effects of coolant injection on turbine aerodynamic [NASA-CR-182123] p 47 N91-10065 POTOTZKY, ANTHONY S. characteristics. Part 1: Test turbine and apparatus PARZYCH, DAVID J. Computation of maximum gust loads in nonlinear aircraft [NAL-TM-585-PT-1] p 47 N91-10059 Vortex structure of wakes behind an advanced propeller using a new method based on the matched filter approach NOUSE, HIROYUKI at takeoff load conditions and numerical optimization p 60 N91-10317 Experimental investigation on the effect of coolant [AIM PAPER 90-3978] p 72 A91-12491 Static and dynamic aeroelastic characterization of an injection on turbine aerodynamic characteristics. Part 2: A modal evaluation of noise generated by the front rotor aerodynamically heated generic hypersonic aircraft Effects of injection from rotor casing with 30 deg slanted of a counter-rotating prop-fan configuration p 61 N91-10320 holes [AIAA PAPER 90-3979] p 72 A91-12492 POTSDAM, MARK [NAL-TM-587-PT-2] p 47 N91-10060 PEAKE, N. A numerical study of the effects of wind tunnel wall NOVIKOV, IURII F. Radiation integrals for sound generation by the Lighthill proximity on an airfoil model Practical aerodynamics and flight dynamics of Yak-52 quadrupoles in propeller acoustics [NASA-CR-187322] p 25 N91-10934 and Yak-55 aircraft p 13 A91-12911 [AIAA PAPER 90-3993] p 73 A91-12506 POWELL, ALAN PELEGRIN, MARC J. The screech of round choked jets, revisited Four dimensional navigation in air traffic with 4-D [AIAA PAPER 90-3980] p 72 A91-12493 navigation aircraft p 31 N91-10991 PREMPEH, E. O. A. PERALA. RODNEY A. Experiences in the use of ABACUS for creep analysis O'BRIEN, W. F. Development and application of linear and nonlinear [PNR-90705] p63 N91-11266 Identification of aerospace acoustic sources using methods for interpretation of lightning strikes to in-flight PRIEUR, JEAN sparse distributed associative memory aircraft Experimental study of high-speed impulsive rotor noise [AIAA PAPER 90-3992] p 73 A91-12505 [NASA-CR-3974] p 64 N91-10548 in a wind tunnel [ONERA, TP NO. 1990-123] p 66 A91-11786 O'BRIEN, WALTER F. PERISON, JANICE PRZIREMBEL, H. R. The identification of helicopter noise using a neural Thermal stability of jet fuel Pyrometry for turbine blade development network [DE90-016801] p56 N91-10188 p 57 A91-10336 [AIAA PAPER 90-3973] p 72 A91-12486 PERRY, BOYD, III OCHADLICK, ANDREW R., JR. Computation of maximum gust loads in nonlinear aircraft Time series and correlation of pulsations observed using a new method based on the matched filter approach simultaneously by two aircraft p 63 A91 -11072 and numerical optimization p 60 N91-10317 OH, BYUNG K. PERSELLO, L FRANK RAE, WILLIAM J. Wake coupling to full potential rotor analysis code Differential Global Positioning System (DGPS) test Prediction of inviscid stagnation pressure losses in [NASA-TM-102805] p 14 N91-10013 plan supersonic inlet flows p 12 A91-12903 OH, C. H. [DOT/FAA/CT-TN90/15] p 29 N91-10034 RAFTERY, MICHAEL Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal PETERS, W. The application of commercial airplane avionics Oxidation Tester) OVRhyp, scramjet test aircraft techniques to advanced space transportation [DE90-010929] p 56 N91-11128 [NASA-CR-187009] p 38 N91-10041 [AIAA PAPER 90-3722] p1 A91-10114

B-8 PERSONAL AUTHOR INDEX SHEN, QING

RAI, MAN MOHAN ROTH, KARUN R. SCHEIDT, TONY Computational analysis of rotor-stator interaction in Simulation ol powered-Wt flows p 21 N91-10886 Project HyBuJET turbomachinery using zonal techniques ROUBERTIE, J. M. (NASA-CR-187011] p38 N91-10040 p 10 A91-12764 Hypersonic space transport system - Cruiser or SCHEWE, GUENTER Prediction of turbine rotor-stator interaction using accelerator? p 54 A91-10973 Determination of unsteady aerodynamic forces on Navier-Stokes methods p 20 N91-10881 RUDOLPH, TERENCE engines with a view to flutter investigations RAJ, PRADEEP Development and application of linear and nonlinear p48 N91-10927 Aerodynamic analysis using Euler equations methods for interpretation of lightning strikes to in-flight SCHICK, CLAUS Capabilities and limitations p 11 A9M2769 aircraft MSB'S BO 108 design and development RAMOS, J. I. [NASA-CR-3974] p 64 N91-10548 [MBB-UD-0568-90-PUB] p 40 N91-10055 Time-dependent jet flow and noise computations SCHIEVELBUSCH, U. RUDY, DAVID H. Noise mechanisms of transonic vortex airfoil (AIAA PAPER 90-3961 ] p 70 A91-12475 A comparative study of Navier-Stokes codes for interaction RAMSAY, TOM high-speed flows p 20 N91-10869 Project HyBuJET (AIAA PAPER 90-3972] p 71 A91-12485 [NASA-CR-tB7011] p38 N91-10040 RUTLEDGE, C. KENDALL SCHIFF, LEWIS B. Some far-field acoustics characteristics of the XV-15 RAO, KUDITIPUDI V. Numerical simulation of F-18 fuselage forebody flows tilt-rotor aircraft Simulation of powered-lift flows p 21 N91-10886 at high angles of attack p 18 N91-10859 [AIAA PAPER 90-3971] p 71 A91-12484 RASPET, RICHARD SCHMIDT, EBERHARD Comparison of shocK wave rise time prediction RYAN, JAMES STEVENSON Design of the derivative balance for the transonic wind techniques Application of computational fluid dynamics to tunnel p 53 N91-10925 [AIAA PAPER 90-4001 ] p 74 A91-12514 three-dimensional bodies in hypersonic flow SCHOBERT, HAROLD H. RATCUFFE, STANLEY p62 N91-11174 Thermal stability of jet fuel Prediction ol aircraft trajectories p 42 N91-10984 [DE90-016801] p 56 N91-10188 REINATH, M. S. SCHRA.L. A laser-sheet flow visualization technique for the large Short and long fatigue crack growth in 2024-T3 under wind tunnels of the National Full-Scale Aerodynamics Fokker 100 spectrum loading p 63 N91-11248 Complex SACHER, P. SCHRECK, S. [NASA-TM-102793] p 60 N91-10268 The case of a hypersonic flight demonstrator Coherent structure induced pressure fluctuations in an RENKO, KARI p54 A91-10978 elliptic jet Evaluation of the ZONAS1D program SAFF, C. R. [AIAA PAPER 90-3963] p 70 A91-12477 [REPT-B-28] p16 N91-10025 Structural risk assessment and aircraft fleet SCHRECK, SCOTT JEFFREY REUSS, ROBYN maintenance p 61 N91-10321 Experimental investigation of the mechanisms Project HyBuJET SAITO, KENJI underlying vortex kinematics in unsteady separated [NASA-CR-187011] p38 N91-10040 The establishment and performance test of PAPI flows p23 N91-10907 REYNOLDS, MIKE (Precision Approach Path Indicator) System for NAL STOL SCHUTTE, PAUL Operational evaluation of initial data link air traffic control aircraft Fault monitoring p 44 N91-10950 services. Volume 2: Appendices [NAL-TM-579] p 28 N91-10030 SCHWAB, R. R. [DOT/FAA/CT-90/1-VOL-2) p 29 N91-10033 SAITOH, MASAKI Optimisation of hybrid propulsion systems RHODES, ALAN Noise characteristics of the Japan's experimental p46 A91 -10976 Technology update of early gas turbine designs powered lift STOL aircraft SCOTT, E. A. [PNR-90710] p 4B N91-10070 [AIAA PAPER 90-4014] p 75 A91-12526 Identification of aerospace acoustic sources using RHYS-JONES, T. N. SAIZ DE BUSTAMAMTE, A. sparse distributed associative memory Applications of thermally sprayed coating systems in Systems reliability assessment p 57 A91-11201 [AIAA PAPER 90-3992] p 73 A91-12505 aero engines SAKURAI, AKIRA SCOTT, JAMES R. [PNR-90750] p48 N91-10072 Motion analysts of RPRVs using on-board and Acoustic radiation from lifting airfoils in compressible RICKS, WENDELL ground-based measurements p 37 A91-12224 subsonic flow Information management p 27 N91-10961 SALMINEN, ESA (AIAA PAPER 90-3911] p 66 A91-12427 RIGAULT, M. Three-dimensional viscous/inviscid coupling in subsonic SCRIVENER, C. T. J. Hypersonic space transport system - Cruiser or flow Heat transfer in aero engine gas turbines, part 1 accelerator? p 54 A91-10973 [REPT-B-24] p 15 N91-10023 [PNR-90754-PT-1] p 48 N91-10074 RINGER, MARK Calculation of three-dimensional viscous/inviscid SEDDON, J. Project HyBuJET interaction in subsonic flow Basic helicopter aerodynamics p3 A91-11701 [NASA-CR-187011] p38 N91-10040 [REPT-B-25] p16 N91-10024 SEIBLE, FRIEDER RIZK, N. K. SANKAR, L. N. Comparison of N ASTR AN analysis with ground vibration Three-dimensional conrtbustor performance validation Numerical simulation of 3-D supersonic free shear results of UH-60A NASA/AEFA test configuration with high-density fuels p 55 A91 -10345 layers [NASA-CR-184565] p 61 N91-10333 RIZK, YEHIA M. [AIAA PAPER 90-3958) p7 A91-12472 SEINER, JOHN M. Numerical simulation of F-18 fuselage forebody flows SANZ FERNANDEZ DE CORDOBA, S. at high angles of attack p 18 N91-108S9 Availability - A practical approach on aerospace Instability of a supersonic shock-free elliptic jet ROBERTS, LEONARD industry p 57 A91-11202 [AIAA PAPER 90-3959] p7 A91-12473 A numerical study of the effects of wind tunnel wall SANZ, JOSE M. SEISHI, KURANAGA proximity on an airfoil model Automated design of controlled diffusion blades Aerodynamic heating in the interaction regions of shock [NASA-CR-187322] p 25 N91-10934 p 21 N91-10883 waves and turbulent boundary layers induced by ROBERTSON, D. D. SARIN, S. L sweptback blunt fins p 6 A91-12226 Euler and potential expenment/CFD correlations for a Experimental/theoretical investigation of the sound field SELLIER, ANTOINE transport and two delta-wing configurations of an isolated propeller, including angle of incidence A unified unsteady lifting-line theory p8 A91-12575 [NASA-TM-102208] p 14 N91-10014 effects SENECHAL, P. ROBINSON, BRIAN A. [AIM PAPER 90-3952] p 69 A91-12468 Propulsion systems for hypersonic transportation Aeroelastic analysis of wings using the Euler equations SARNO, R. L. p45 A91-10975 with a deforming mesh Suppression of flow-induced pressure oscillations in SENGUPTA, G. [NASA-TM-102733] p 15 N91-10020 cavities Application of computational methods in aeroacoustics ROBINSON, L. H. [AIAA PAPER 90-4018] p8 A91-12530 [AIAA PAPER 90-3917] p 67 A91-12433 Influence of unsteady aerodynamics on rotor blade SASAKI, SHUICHI SENSBURG, O. aeroelastic stability and response p 37 A91-12894 Application of flight path reconstruction algorithms for A quarter of a century of aeroelastic cooperation flight data of helicopter ROGERS, J. between research and industry (a review). Part 1: Fighter [NAL-TM-582] p 28 N91-10031 OVRhyp, scramjet test aircraft airplanes and helicopters p78 N91-10931 SAUNDERS, P. W. [NASA-CR-187009] p 38 N91-10041 SENSBURG, OTTO The design approach used in the synthesis of the B-2 Review of active structural control systems and flight RONZHEIMER, ARNO lateral-directional control laws test techniques for dynamic stability investigations Solution of the two-dimensional Euler equations by a (AIAA PAPER 90-3255] p 50 A91-12929 [MBB/FYT256/S/PUB/361/A] p 51 N91-11025 finite volume discretization on unstructured triangular SAVAGE, M. SHALAEV, V. I. meshes Rotorcraft drivetrain life safety and reliability [ESA-TT-1135] p66 N91-11473 [AGARD-R-775] p 38 N91-10042 A three-dimensional boundary layer on bodies with a ROSE, WILLIAM C. Drive system life and reliability p 38 N91-10044 slight cross-sectional asymmetry at small angles of Numerical investigations in three-dimensional internal SCANLON, CHARLES H. attack p5 A91-11909 flows NASA transport systems research vehicle B-737 data SHCHERBAKOV, S. A. [NASA-CR-186958] P 52 N91-10083 link system and display formats Shock wave formation during interaction with a weak ROSEN, DAVID I. [NASA-TM-102717] p 44 N91-10058 discontinuity at the boundary of a local subsonic region Propulsion simulation for magnetically suspended wind SCHAENZER, G. p6 A91-12017 tunnel models Effect of wind and wind variation on aircraft SHEN, MENGYU [NASA-CR-182093] p 53 N91-11027 flight-paths p41 N91-10972 An efficient method for solving transonic flow about ROSS, J. C. Wind models lor flight simulation p 53 N91-10975 plane cascades with a large nosing p 4 A91-11839 A laser-sheet flow visualization technique for the large SCHAFFAR, MARTIN SHEN, OING wind tunnels of the National Full-Scale Aerodynamics Rotor loads computation using singularity methods and A study of implicit space-marching method for the Complex application to the noise prediction supersonic viscous flow over the blunt cone [NASA-TM-102793] P 60 N91-10268 [ISL-PU-301/90] p 15 N91-10018 p4 A91-11831

B-9 SHERCLIFF, H. R. PERSONAL AUTHOR INDEX

SHERCLIFF, H. R. SOLTIS, STEPHEN SWADLING, S. J. A process model for age hardening of aluminium alloys. Seat dynamic performance standards for a range of Commercial supersonic operations - Thirteen years of I-The model p 56 A91-11883 sizes experience with Concorde p 36 A9V10957 SHIM, C. [DOT/FAA/CT-TN90/23] p 26 N91-10028 SWAIN, M. H. Instability characteristics of a low aspect ratio SOMEYA, TERUO The growth of short cracks in 4340 steel and rectangular jet Wind tunnel test of redundant vane-type flow-direction aluminum-lithium 2090 p 62 N91M1247 [AIAA PAPER 90-3962] p 70 A91-12476 sensing systems SWEETMAN, BILL SHINGLEDECKER, CLARK [NAL-TM-590] p 44 N91-10057 The ATF battle shapes up p 36 A91-12062 Operational evaluation of initial data link air traffic control SONG, CHUNSHAN SWIERSTRA, SIP services. Volume 2: Appendices Thermal stability of jet fuel Optimum on-line handling of air traffic over Western [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 [DE90-016801] p56 N91-10188 Europe p 30 N91-10982 SORENSON, REESE L. SHIVASHANKARA, B. N. Generation of aircraft trajectories for on-line operation: Numerical simulation of F-18 fuselage forebody flows Installation effects on counter rotating propeller noise Methods, techniques, and tools p 42 N91-10987 at high angles of attack p 18 N91-10859 [AIAA PAPER 90-4023] p 75 A91-12534 The control of inbound flights p 32 N91 -10992 SOUTH, JERRY C., JR. Air traffic management and aircraft guidance in a zone SHYU, R. N. Computational fluid dynamics research and applications Forcing level effect of internal acoustic excitation on of convergence p 33 N91-10998 at NASA Ungley Research Center p 17 N91-10841 Ground-based 4-0 guidance of flights in strong wind the improvement of airfoil performance SOVA, G. J. [AIAA PAPER 90-4010] p 74 A91-12522 p33 N91-10999 Computational aerodynamic simulation experience The air traffic controller facing automation: Conflict or SICLARI, M. J. p11 A91-12771 An Euler code prediction of near field to midfield sonic cooperation p 34 N91-11001 SPARROW, VICTOR W. Integration of aircraft capability in air traffic handling boom pressure signatures Weak shock propagation through a turbulent [AIAA PAPER 90-4000) p 7 A91-12513 simulations p 35 N91-11007 atmosphere SWOLINSKY, M. SILCOX, R. J. [AIAA PAPER 90-4031 ] p 75 A91-12540 Effect of wind and wind variation on aircraft Active control of interior noise in mode) aircraft fuselages SPENCE, P. L. flight-paths p41 N91-10972 using piezoceramic actuators Analysis of the PTA external noise data and comparison Wind models for flight simulation p 53 N91-10975 [AIAA PAPER 90-3922] p 67 A91-12438 with predictions SZRAJER, MAREK SILCOX, RICHARD J. [AIAA PAPER 90-3935] p 68 A91-12451 Simulation investigations of the helicopter ground SRINIVASAN, RAMAKRISHNA Noise transmission characteristics of a large scale resonance p 36 A91-11724 composite fuselage model Aircraft interior noise reduction by alternate resonance [AIAA PAPER 90-3965] p 71 A91-12479 tuning SIM, ALEX G. [NASA-CR-186879] p 76 N91-11488 Flight characteristics of a modified Schweizer SGS1-36 STAHU M. sailplane at low and very high angles of attack Supersonic combustion engine testbed, heat lightning TAKASAWA, KINGO [NASA-TP-3022] p 50 N91-10079 [NASA-CR-187010] p 47 N91-10061. A consideration on flight paths for microwave-powered SIMONICH, J. C. STALFORD, HAROLD airplanes The role of leading edge vortex flows in prop-fan Nonlinear feedback control for high alpha flight [NAL-TR-1051] p39 N91-10053 interaction noise [NASA-CR-186545] p 39 N91-10047 TAKE, KENTARO [AIAA PAPER 90-3977] p 72 A91-12490 STALLINGS, ROBERT l_, JR. Configuration control and airworthiness management Navier-Stokes solutions for flows related to store SIMPSON, MYLES A. p77 A91-12233 separation p 18 N91-10861 The use of spatial coherence techniques for identifying TAKEDA, KATSUMI noise transmission paths on the MDC-UHB demonstrator STANZIOLA, C. Noise characteristics of the Japan's experimental aircraft Performance-robustness trade off of eigenstructure powered lift STOL aircraft [AIAA PAPER 90-3968] p 71 A91-12482 assignment applied to rotorcraft p 49 A91-11155 [AIAA PAPER 90-4014] p 75 A91-12526 TAKIZAWA, MINORU SIMPSON, R. W. STEINBRENNER, JOHN P. Wind tunnel test of redundant vane-type flow-direction Assessing the market for high speed air travel in Ihe Grid-generation methodology in applied aerodynamics sensing systems 21st century p 77 A91-10962 p9 A91-12755 [NAL-TM-590] p 44 N91-10057 SIMPSON, ROBERT W. STEINHEIL, E. Basic materials and structures aspects for hypersonic TALOTTA, NICHOLAS J. Expert systems for the generation of thermal area arrival Operational evaluation of initial data link air traffic control paths for civil transport p 32 N91-10995 transport vehicles (HTV) p 54 A91-10974 STETSKO, G. O. services. Volume 2: Appendices SINGER, JOSEF [DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 A self-organizing stochastic control system adaptable Repeated buckling of composite shear panels TANAKA, KEIJI to changing perturbation characteristics p60 N91-10303 Flight evaluation test of the PAPI (Precision Approach p65 A91-11353 SKURATOV, A. S. Path Indicator) System An experimental study of the laminar-turbulent transition STEVENS, J. C. [NAL-TM-592] p 29 N91-10966 behind three-dimensional roughness in a boundary layer Recent advances in Active Noise Control Flight simulator evaluation test of multi-functional display [AIAA PAPER 90-3924] p 67 A91-12440 on a sharp cone p6 A91-12014 unit SHEETS, G. STEWART, MARK ERIC MICHAEL [NAL-TM-596] p 53 N91-11026 The ISL hypersonic shock tunnel and its Nonoveriapping composite meshes for multi-element TANNEHILL, J. C. instrumentation air-foils p 23 N91-10908 Numerical computation of viscous flow about [ISL-CO-213/89] p52 N91-10086 STOLCIS, L unconventional airfoil shapes SMITH, CHARLES A. Solution of the Euler equations on unstructured grids [NASA-CR-187343] p 15 N91-10019 Some aeroacoustic and aerodynamic applications of the for two-dimensional compressible flow p 3 A91-11160 TENHAVE, J. M. theory of nonequilibrium thermodynamics STOLL, HARTY The application of trajectory prediction algorithms for [AIAA PAPER 90-3989] p 73 A91-12502 Boeing flight deck design philosophy planning purposes in the Netherlands ATC-system SMITH, CHARLES D. p 40 N91-10937 p65 N91 -10986 Helicopter far-field acoustic levels as a function of STHEHLOW, G. TERUI, YUSHI reduced main-rotor advancing blade-tip Mach number A quarter of a century of aeroelastic cooperation The establishment and performance test of PAPI [NASA-TM-102684] p 76 N91-10699 between research and industry (a review). Part 1: Fighter (Precision Approach Path Indicator) System for NAL STOL aircraft SMITH, HERB, JR. airplanes and helicopters p 78 N91-10931 [NAL-TM-579] p 28 N91-10030 Structural risk assessment and aircraft fleet STREMEL, PAUL M. TERUI, YUUSHI maintenance p 61 N91-10321 The calculation of rotor/fuselage interaction for two-dimensional bodies Flight evaluation test of the PAPI (Precision Approach SMITH, LEIGH A. Path Indicator) System Applications of a transonic wing design method [NASA-TM-102855] p 25 N91-10933 SU, AY [NAL-TM-592] p 29 N91-10966 p21 N91 -10890 THERY, C. SMITH, M. J. T. Application of a state-space wake model to elastic blade flapping in hover p 13 N91-10006 The sonic boom problem p1 A91-10964 Do we really need 57 ways of rating aircraft noise THOMAS, JAMES l_ SUAREZ, E. [PNR-90720] p76 N91-10704 Navier-Stokes solutions about the F/A-18 forebody-LEX Pyrometry for turbine blade development SMITH, MERRITT H. configuration p 18 N91-10860 Simulation of powered-lift flows p 21 N91-10886 p57 A91-10336 A comparative study of Navier-Stokes codes for SMITH, PHILIP J. SUBRAMANIAM, SHANKAR high-speed flows p 20 N91-10869 Graphical interfaces for cooperative planning systems Acoustic radiation from lifting airfoils in compressible An embedded grid formulation applied to delta wings p 27 N91-10956 subsonic flow p22 N91-10891 SMITH, RITA A. [AIAA PAPER 90-3911] p 66 A91-12427 THOMPSON, DONALD E. Some far-field acoustics characteristics of the XV-15 SUENAGA, SYOUJI Experiments on the aerodynamic noise sources in tilt-rotor aircraft Characteristics of piping interference elimination unit centrifugal turbomachinery [AIAA PAPER 90-3971 ] p 71 A9M2484 used in the high-speed wind tunnel test of ASUKA seven [AIAA PAPER 90-3948] p 69 A91-12464 SMITH, ROBERT E. percent semi-bom prototype TICHY, LORENZ Grid generation and inviscid flow computation about [NAL-TM-588] p 13 N91-10003 Calculation of the pressure distribution on an oscillating aircraft geometries p 18 N91-10857 SUZUKI, HIROKAZU airfoil in incompressible flow considering nonlinear SNYDER, S. D. Characteristics of piping interference elimination unit effects p25 N91-10926 Active control of interior noise in model aircraft fuselages used in the high-speed wind tunnel test of ASUKA seven TINCHER, M. using piezoceramic actuators percent semi-born prototype Supersonic combustion engine testbed, heat lightning [AIAA PAPER 90-3922] p 67 A91-12438 [NAL-TM-588] p 13 N91-10003 [NASA-CR-187010] p 47 N9M0061

B-10 PERSONAL AUTHOR INDEX WOODWARD, RICHARD P.

TINOCO, EDWARD N. VANDERKRAAN, P. WARE, BRUCE E. CFD applications to complex configurations - A survey Aircraft trajectory reconstitution on the basis of FAA air traffic operational evaluation of Automated p11 A91-12766 multi-radar plot information p 34 N91-11002 Surface Observing System (ASOS) TONG, KEVIN K. VANOVERBEKE, THOMAS J. [DOT/FAA/CT-TN90/42] p 52 N91-10084 Detection of airplanes in aerial imagery A numerical study of the hot gas environment around WASSEL, ANTHONY B. p59 A91-12824 a STOVL aircraft in ground proximity p 21 N91-10887 Commercial aircraft and the environment TOPOL, D. A. VANSCHAIK, F. J. [PNR-90687] p64 N91-11307 Rotor wake/stator interaction noise-predictions versus Bayesian multi-sensor tracking for advanced air traffic WATANABE, AKIRA data control systems p 34 N91-11003 Configuration, function and performance of the flight [AIAA PAPER 90-3951] p 69 A91-12467 simulation test facility and its motion simulation system VATSA, VEER N. [NAL-TM-575] p 52 N91-10080 TORRES, FRANCISCO J. Recent advances in Runge-Kutta schemes for solving Wake coupling to full potential rotor analysis code Function and performance of visual simulation unit ot 3-D Navier-Stokes equations p 17 N91-10851 [NASA-TM-102805] p 14 . N91-10013 flight simulation test facility THAN, BOI N. VENKATESWARA RAO, G. (NAL-TM-581] p 52 N91-10082 Large-amplitude vibrations of free-free tapered beams The use of spatial coherence techniques for identifying Right simulator evaluation test of multi-functional display p57 A91-11199 noise transmission paths on the MDC-UHB demonstrator unit aircraft VENNERI, SAMUEL l_ [NAL-TM-596] p 53 N91-11026 [AIAA PAPER 90-3968] P 71 A91-12482 Computational technology for flight vehicles; WEATHERILL, N. P. TRIEBSTEIN, HERMANN Proceedings of the Symposium, Washington, DC. Nov. 5-7. Mixed structured-unstructured meshes for aerodynamic Determination of unsteady aerodynamic forces on 1990 p58 A91-11813 flow simulation p 65 A91-11154 engines with a view to flutter investigations VICROY, DAN D. WEDAN, BRUCE W. p48 N91-10927 Guidance concepts for time-based flight operations Recent advances in Runge-Kutta schemes for solving TROCHALIDIS, V. p32 N91-10993 3-D Navier-Stokes equations p 17 N91-10851 The aerodynamic interference between tanker and VISSCHER, H. WEDGE, R. H. receiver aircraft during air-to-air refuelling The application of trajectory prediction algorithms for Total quality management at Rolls-Royce PLC p3 A91-11159 planning purposes in the Netherlands ATC-system [PNR-90759] p60 N91-10298 TRUDELL, BERNARD J. p65 N91-10986 WELGE, H. ROBERT Current Emergency Locator Transmitter (ELT) VOGEL, S. Computational fluid dynamics design applications at deficiencies and potential improvements utilizing A quarter of a century of aeroelastic cooperation supersonic/hypersonic speeds p 12 A91-12773 TSO-C91a ELTs between research and industry (a review). Part 2: Transport WELLER, TANCHUM [NASA-CR-4330] p 28 N91-10964 airplanes and other civil applications p 40 N91-10932 Repeated buckling of composite shear panels TSAI, C. T. VOLPE, G. p60 N91-10303 Influence of airfoil nose radius on sound generated by Inverse airfoil design - A classical approach updated WELLMAN, J. BRENT gust interactions for transonic applications p 10 A91 -12758 Rotor systems research aircraft risk-reduction shake test [AIAA PAPER 90-3912] p 66 A91-12428 VOSS, RALPH TSAI, PING-HO Unsteady wind tunnel wall interferences in subsonic and [NASA-TM-4186] p 38 N91-10045 WHEELER, PETER DAVID Numerical calculations for flows past an unconventional transonic profile flows p S3 N91 -10928 airfoil p24 N91-10916 Voice communications in the cockpit noise environment: The role of active noise reduction p 61 N91 -11140 TSIRG, V. N. Detection of concealed corrosion damage in aircraft w WHITFIELD, C. E. structures using the eddy current method Predicted vs. scale model and flight test UDF engine p58 A91-11974 WADKINS, R. P. noise TUNCER, I. Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal [AIAA PAPER 90-3936] p 68 A91-12452 Numerical simulation of 3-D supersonic free shear Oxidation Tester) WIDNALU S. E. layers [DE90-010929] p 56 N91-11128 Numerical simulation of acoustic diffraction of WAGENER, JOACHIM [AIAA PAPER 90-3958] P 7 A91-12472 two-dimensional rigid bodies in arbitrary flows Design of the derivative balance for the transonic wind [AIAA PAPER 90-3920] p 67 A91-12436 TURCICH, ELIZABETH tunnel p 53 N91-10925 FAA air traffic operational evaluation of Automated WILLAN, UWE WAGGONER, E. G. Integration of model and knowledge based diagnosis, Surface Observing System (ASOS) Prediction of effects of wing contour modifications on [OOT/FAA^CT-TN90/42] p 52 N91-10084 with the example of a turbojet engine low-speed maximum lift and transonic performance for the [ETN-90-97900] p 49 N91-11019 EA-6B aircraft WILLEMS, P.-Y. u [NASA-TP-3046] p 22 N91-10902 Aircraft dynamics for air traffic control WAGGONER, EDGAR G. p42 N91-10985 Development of high-lift wing modifications for an UCHANIN, V. N. advanced capability EA-6B aircraft p 10 A91-12762 WILLIAMS, DAVID H. Time-based aircraft/ATC operations study Detection of concealed corrosion damage in aircraft WAGNER, B. A. structures using the eddy current method Optimum hypersonic airfoil with power law shock p29 N91-10959 p58 A91-11974 waves The 4-D descent trajectory generation techniques under UCHIDA, TADAO [DE90-014903] p 13 N91-10008 realistic operating conditions p 32 N91-10994 Wind tunnel test of redundant vane-type flow-direction WAGNER, R. D. WILLIAMS, MARC H. sensing systems Applied aspects of laminar-flow technology Temporal-adaptive Euler/Navier-Stokes algorithm for [NAL-TM-590] p 44 N91-10057 p 8 A91-12690 unsteady aerodynamic analysis of airfoils using UHSE, W. WAKAIRO, KAORU unstructured dynamic meshes Basic materials and structures aspects for hypersonic Configuration, function and performance of the flight [NASA-TM-102734] p 24 N91-10919 transport vehicles (HTV) p 54 A91-10974 simulation test facility and its motion simulation system WILSON, ANTHONY UMEDA, Y. [NAL-TM-575] p 52 N91-10080 Structural tests of aircraft window assembly equipped The screech of round choked jets, revisited Function and performance of visual simulation unit of with smoke evacuation valve [AIAA PAPER 90-3980] P 72 A91-12493 flight simulation test facility [DOT/FAA/CT-TN89/44] p 39 N91-10051 UNRUH, JAMES F. [NAL-TM-581] p 52 N91-10082 WINTER, CARL-JOCHEN Structure-borne noise transmission in the preplan test Flight simulator evaluation test of multi-functional display Hydrogen in high-speed air transportation assessment aircraft unit p 55 A91-10966 [AIAA PAPER 90-3966] p 71 A91-12480 [NAL-TM-596] p 53 N91-11026 WISLER, S. WALDER, ANDRE USUI, H1BOSHI Supersonic combustion engine testbed, heat lightning Influence of chromium and molybdenum on the structural Effects of coolant injection on turbine aerodynamic [NASA-CR-187010] p 47 N91-10061 stability of a high strength damage tolerant P/M nickel characteristics. Part 1: Test turbine and apparatus WLEZIEN, RICHARD W. based alloy for turbine disks [NAL-TM-585-PT-1] p 47 N91-10059 Aeroacoustic environment of an advanced STOVL [ONERA. TP NO. 1990-100] p 55 A91-11776 aircraft in hover Experimental investigation on the effect of coolant WALKER, N. A. [AIAA PAPER 90-4016] p 75 A91-12528 injection on turbine aerodynamic characteristics. Part 2: Influence of heat treatment on microstructure and Effects of injection from rotor casing with 30 deg slanted properties of an advanced high temperature titanium WOAN, C. J. holes alloy Computational aerodynamic simulation experience p11 A91-12771 [NAL-TM-587-PT-2] P 47 N91-10060 [PNR-90689]' p56 N91-11107 WALSH, M. WOODS, J. A. Supersonic combustion engine testbed, heat lightning Direct use of linear time-domain aerodynamics in [NASA-CR-187010] p47 N91-10061 aeroservoelastic analysis: Aerodynamic model WALSH, MICHAEL J. p60 N91-10316 VACHIERY, V. Riblets p59 A91-12694 WOODWARD, RICHARD P. The EUROCONTROL future ATS system concept and WANG, YIYUN Aeroacoustic effects of reduced aft tip speed at constant the programme of studies, tests, and trials Application of LU-AOI algorithm in two-dimension thrust for a model counterrotation turboprop at takeoff p30 N91-10983 transonic flow p5 A91-11848 conditions VAN DER VELDEN, ALEX WANHILL, R. J. H. [AIAA PAPER 90-3933] p 68 A91-12449 The sonic boom of an oblique flying wing Short and long fatigue crack growth in 2024-T3 under Aeroacoustic effects of reduced aft tip speed at constant [AIAA PAPER 90-4002] P 74 A91-12515 Fokker 100 spectrum loading p 63 N91-11248 thrust for a model counterrotation turboprop at takeoff VANDALSEM, WILLIAM R. WARDLAW, ANDREW B., JR. conditions Simulation of powered-lift flows P 21 N91-10886 Euler solutions for delta wings p 12 A91-12899 [NASA-TM-103608] p 76 N91-10703

B-11 WRIGHT, JOSEPH A. PERSONAL AUTHOR INDEX

WRIGHT, JOSEPH A. ZINGEU HARTMUT Tests of the general fire suppression concentrate Determination of unsteady aerodynamic forces on Pyrocap B-136 engines with a view to flutter investigations [DOT/FAA/CT-TN90/21] p 26 N9M0029 p48 N91-10927 WU, GUOCHUAN ZINGG, D. W. Optimization of the arrangement of the front and rear Low Mach number Euler computations blade rows of a tandem blade cascade p5 A91-11900 p 46 A91-11349 ZORUMSKI, WILLIAM E. WU, KUEN-CHUAN Sound transmission through a high-temperature acoustic Numerical simulation of supersonic mixing layer using probe tube high resolution scheme [AIAA PAPER 90-3991 ] p 73 A91-12504 [AIAA PAPER 90-4025] p8 A91-12535 WU, YIZHAO Finite element method for computation of transonic flow about wings from the pressure minimum integral p4 A91-11838

YAMAMOTO, YUKIMITSU Numerical simulation of hypersonic flow around a space plane. Part 3: Analysis of aerothermodynamic heating [NAL-TR-1027T] p 14 N91-10011 YANAGIHARA, MASAAKI Flight simulation programs for space plane [NAL-TM-594] p 55 N91-11035 YANG, HENRY T. Y. Aeroelastic analysis of wings using the Euler equations with a deforming mesh [NASA-TM-102733] p 15 N91-10020 YANG, QIDE The calculation method for subsonic longitudinal and lateral aerodynamic characteristics of complete aircraft configuration p5 A91-11844 YANG, ZUOSHENG Finite element method for computation of transonic flow about wings from the pressure minimum integral p4 A91-11838 YAO, HUI A study of implicit space-marching method for the supersonic viscous flow over the blunt cone p4 A91-11831 YE, ZHENG-YIN Localized linearization method for wings at high angle of attack p 12 A91-12896 YOKOYAMA, SHINTARO The establishment and performance test of PAPI (Precision Approach Path Indicator) System for NAL STOL aircraft [NAL-TM-579] p 28 N91-10030 YOSHIDA, RYUJI Numerical simulation of hypersonic flow around a space plane. Part 3: Analysis of aerothermodynamic heating [NAL-TR-1027T] p 14 N91-10011 YUE, ANDREW H infinity-design and the improvement of helicopter handling qualities p 51 N91-11024

ZAMAN, K. B. M. O. Effect of acoustic excitation on stalled flows over an airfoil [AIAA PAPER 90-4009] p7 A91-12521 ZANDBERGEN, T. Experimental/theoretical investigation of the sound field of an isolated propeller, including angle of incidence effects [AIAA PAPER 90-3952] p 69 A91-12468 ZEREK, LUDWIK The ground resonance of a helicopter with a rotor of ideal and approximate symmetry considering the rotor-blade vibration in the thrust plane p36 A91-11725 ZHANG, HANXIN A study of implicit space-marching method for the supersonic viscous flow over the blunt cone p4 A91-11831 ZHAO, LING-CHENG Localized linearization method for wings at high angle of attack p 12 A91-12896 ZHU, ZIQIANG Calculation of three-dimensional viscous/inviscid interaction in subsonic flow [REPT-B-25] p 16 N91-10024 ZHU, ZIQUIANG Three-dimensional viscous/inviscid coupling in subsonic flow [REPT-B-24] p15 N91-10023 ZIMMERMANN, H. A quarter of a century of aeroelastic cooperation between research and industry (a review). Part 2: Transport airplanes and other civil applications p 40 N91 -10932

B-12 CORPORATE SOURCE INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

Airbus Industrie, Blagnac (France). How to fly windshear p41 N91-10974 Akron Univ., OH. Deutsche Airbus G.m.b.H., Bremen (Germany, F.R.). Typical Corporate Source Drive system life and reliability p 38 N91-10044 A quarter of a century of aeroelastic cooperation Allgemeiner Deutscher Automobil-Club-e.V., Munich between research and industry (a review). Part 2: Transport Index Listing (Germany, F.R.). airplanes and other civil applications p 40 N91 -10932 Air rescue in the Federal Republic of Germany Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, IETN-90-97878] p 28 N91-10963 Cologne (Germany, F.R.). Analytical Methods, Inc., Redmond, WA. Wind tunnel investigations of the appearance of shocks in the windward region of bodies with circular cross section CORPORATE SOURCE^ Thermal analysis of engine inlet anti-icing systems p 35 A91-10341 at angle of attack [DLR-FB-90-15] p 16 N91-10027 Analytical Services and Materials, Inc., Hampton, VA. Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Applied aspects of laminar-flow technology Goettingen (Germany, F.R.). p8 A91-12690 Duke Univ., Durham, NC. A contribution to the numerical solution of transonic flow Aircraft interior noise reduction by alternate resonance Arizona Univ., Tucson. around a delta wing by solving Navier-Stokes equations tuning Influence of airfoil nose radius on sound generated by (OLR-FB-90-13] p 16 N91-10026 [NASA-CR-186879] p 76 N91-11488 gust interactions Contributions in the field of aeroelastics on the occasion IAIAA PAPER 90-3912] p 66 A91-12428 of the 60th anniversary of Professor Dr.-lng. Habil. Hans Army Aviation Systems Command, Moffett Field, CA. Wilhelm Foersching The acoustic results of a United Techologies scale model IETN-90-97630] p 24 N91-10920 TITLE REPORT PAGE ACCESSION helicopter rotor tested at DNW The calculation of unsteady compressible flow about NUMBER NUMBER NUMBER (AIAA PAPER 90-4035] p 75 A91-12543 oscillating airfoil profiles using the Euler upwind method Astridge (Derek) and Associates, Langport (England). p25 N91-10921 Helicopter transmissions: Design for safety and Design of the derivative balance for the transonic wind reliability p 38 N91-10043 tunnel p 53 N91-10925 Listings in this index are arranged alphabetically Atlantic Research Corp., Landover, MD. Calculation of the pressure distribution on an oscillating Current Emergency Locator Transmitter (ELT) airfoil in incompressible flow considering nonlinear by corporate source. The title of the document is deficiencies and potential improvements utilizing effects p 25 N91-10926 used to provide a brief description of the subject TSO-C91aELTs Determination of unsteady aerodynamic forces on matter. The page number and the accession INASA-CR-4330] p 28 N91-10964 engines with a view to flutter investigations p48 N91-10927 number are included in each entry to assist the Unsteady wind tunnel wall interferences in subsonic and user in locating the abstract in the abstract section. B transonic profile flows p 53 N91-10928 If applicable, a report number is also included as A quarter of a century of aeroelastic cooperation BBN Systems and Technologies Corp., Cambridge, MA. an aid in identifying the document. between research and industry (a review). Part 1: Fighter Fault recovery recommendation p 27 N91-10952 airplanes and helicopters p 78 N91-10931 Boeing Commercial Airplane Co., Seattle, WA. Douglas Aircraft Co., Inc., Long Beach, CA. Boeing flight deck design philosophy Estimation of the turbulent boundary layer pressure p 40 N91-10937 wavenumber-frequency spectrum using a fixed probe Use of 4-D RNAV in time-based en route arrival pair metering p 33 N91-10997 IAIAA PAPER 90-3926] p 67 A91-12442 The use of spatial coherence techniques for identifying Adelaide Univ. (Australia). noise transmission paths on the MDC-UHB demonstrator Active control of interior noise in model aircraft fuselages aircraft using piezoceramic actuators | AIAA PAPER 90-3968] p 71 A9M2482 California Inst. of Tech., Pasadena. | AIAA PAPER 90-3922] p 67 A91-12438 Douglas flight deck design philosophy Application of dynamical systems theory to nonlinear Advisory Group for Aerospace Research and aircraft dynamics p 43 N91-11014 p40 N91-10939 Development, Neuilly-Sur-Seine (France). California Univ., Los Angeles. Duke Univ., Durham, NC. Rotorcraft drivetrain life safety and reliability Influence of unsteady aerodynamics on rotor blade Aircraft interior noise reduction by alternate resonance IAGARD-R-775] p 38 N91-10042 aeroelastic stability and response p 37 A91-12894 tuning Aircraft trajectories: Computation, prediction, control, Constrained optimization approach to feedback control |NASA-CR-186879] p 76 N91-11488 volume 1. Part 1: Fundamentals. Part 2: Flight in critical of state-augmented systems p 66 N91-11433 atmospheric conditions. Part 3: Impact of new on-board California Univ., San Diego, La Jolla. technologies on aircraft operation Comparison of NASTRAN analysis with ground vibration [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 results of UH-60A NASA/AEFA test configuration Aircraft trajectories: Computation, prediction, control. INASA-CR-184565] p 61 N91-10333 Electro Magnetic Applications, Inc., Denver, CO. Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. Carnegie-Mellon Univ., Pittsburgh, PA. Development and application of linear and nonlinear Part 11: List of contributors Time-dependent jet flow and noise computations methods for interpretation of lightning strikes to in-flight (AGARD-AG-301-VOL-3-PT-9-11I p 30 N91-10978 IAIAA PAPER 90-3961 ] p 70 A91-12475 aircraft Aircraft trajectories: Computation, prediction, control, Case Western Reserve Univ., Cleveland, OH. (NASA-CR-3974) p 64 N91-10548 volume 2: Air traffic handling and ground-based guidance Bifurcation analysis of axial flow compressor stability European Organization for the Safety of Air of aircraft. Part 4: Air traffic handling. Part 5: Guidance p44 A91-10245 Navigation, Brussells (Belgium). of aircraft in a time-based constrained environment. Part Centre d'Etudes et de Recherches, Toulouse (France). Optimum on-line handling of air traffic over Western 6: Surveillance. Part 7: Meteorological forecasts. Part 8: Four dimensional navigation in air traffic with 4-D Europe p 30 N91-10982 Aircraft operation in air traffic handling simulation navigation aircraft p 31 N91-10991 The EUROCONTROL future ATS system concept and (AGARD-AG-301-VOL-2-PT-4-8) p 42 N91-10981 College of William and Mary, Williamsburg, VA. the programme of studies, tests, and trials Test cases for computation of internal flows in aero Automatic determination of fault effects on aircraft p30 N91-10983 engine components functionality Generation of aircraft trajectories for on-line operation: [AGARD-AR-275] p 49 N91-11022 INASA-CR-181352) p 37 N91-10039 Methods, techniques, and tools p 42 N91-10987 Colorado Univ., Boulder. AeroChem Research Labs., Inc., Princeton, NJ. The high-resolution graphic display: A possible Computation of transonic flow over elastic rotor blade Time-dependent jet flow and noise computations man/machine interface for a computer assisted ATC p 23 N91-10906 (AIAA PAPER 90-3961] p 70 A91-12475 management system p 31 N91-10989 Experimental investigation of the mechanisms Aeronautical Research Inst. of Sweden, Bromma. underlying vortex kinematics in unsteady separated The 4-D control of current air carriers in the present Short crack growth under realistic flight loading: Model flows p 23 N91-10907 environment: Objectives, status, and plans predictions and experimental results for Al 2024 and AI-Li Application of computational fluid dynamics to p31 N91-10990 2090 p62 N91-11246 three-dimensional bodies in hypersonic flow The control of inbound flights p 32 N91-10992 Aeronautical Research Labs., Melbourne (Australia). p62 N91-11174 Air traffic management and aircraft guidance in a zone Flight testing of two Allison T56 engines modified to Consiglio Nazionale delle Ricerche, Rome (Italy). of convergence p 33 N91-10998 the ARL developed low smoke configuration Optimization models and techniques to improve air traffic Ground-based 4-D guidance of flights in strong wind |ARL-PROP-TM-449| p 47 N91-10064 management p 31 N91 -10988 p33 N91-10999 C-1 ESA CORPORA TE SOURCE

The air traffic controller facing automation: Conflict or Helsinki Univ. Technology, Otaniemi (Finland). M cooperation p 34 N91-11001 Three-dimensional viscous/inviscid coupling in subsonic Aircraft trajectory reconstitution on the basis of flow Maryland Univ., College Park. multi-radar plot information p 34 N91-11002 IREPT-B-24) p15 N91-10023 Coupled rotor/airframe vibration analysis Developments to enhance meteorological forecasting Calculation of three-dimensional viscous/inviscid p43 N91-11012 for air traffic services p 64 N91 -11006 interaction in subsonic flow Massachusetts Inst. of Tech., Cambridge. Integration of aircraft capability in air traffic handling [REPT-B-25] p 16 N91-10024 Expert systems for the generation of thermal area arrival simulations p 35 N91-11007 Evaluation of the ZONA51D program paths for civil transport p 32 N91-10995 European Space Agency, Paris (France). [REPT-B-28] p 16 N91-10025 MCAT Inst, San Jose, CA. Contributions to the improvement of flight safety in wind High Technology Corp., Hampton, VA. Application of CFD to sonic boom near and mid flow-field shear Applied aspects of laminar-flow technology prediction (ESA-TT-1141) p28 N91-10965 p8 A91-12690 [AIAA PAPER 90-3999] p7 A91-12512 Parallelization on a multi-processor system of a solving Honeywell, Inc., Minneapolis, MN. McDonnell Aircraft Co., Saint Louis, MO. method for the unsteady Navier-Stokes equations at high Cockpit avionics integration and automation Aeroacoustic environment of an advanced STOVL Reynolds numbers p44 N91-10938 aircraft in hover IESA-TT-1116] p62 N91-11197 (AIAA PAPER 90-4016] p 75 A91-12528 Solution of the two-dimensional Euler equations by a finite volume discretization on unstructured triangular Structural risk assessment and aircraft fleet meshes maintenance p 61 N91-10321 [ESA-TT-1135] p66 N91-11473 Idaho National Engineering Lab., Idaho Falls. McDonnell-Douglas Helicopter Co., Mesa, AZ. Three-dimensional fluid flow in JFTOT (Jet Fuel Thermal Influence of unsteady aerodynamics on rotor blade Oxidation Tester) aeroelastic stability and response p 37 A91-12894 [DE90-010929] p 56 N91-11128 Messerschmitt-Boelkow-Blohm G.m.b.H., Munich Illinois Inst. of Tech., Chicago. (Germany, F.R.). Federal Aviation Administration, Atlantic City, NJ. Aeroacoustic environment of an advanced STOVL MSB'S BO 108 design and development Tests of the general fire suppression concentrate aircraft in hover [MBB-UD-0568-90-PUB] p 40 N91-10055 Pyrocap B-136 [AIAA PAPER 90-4016] p 75 A91-12528 Review of active structural control systems and flight IDOT/FAA/CT-TN90/21] p 26 N91-10029 Illinois Univ., Chicago. test techniques for dynamic stability investigations Operational evaluation of initial data link air traffic control The instability of combustion in propulsion engines [MBB/FYT256/S/PUB/361/A] p 51 N91-11025 services. Volume 2: Appendices p56 N91-10141 Use of the VP-200 computer for aerothermodynamic (DOT/FAA/CT-90/1-VOL-2] p 29 N91-10033 Illinois Univ. at Urbana-Champaign, Savoy. problems Differential Global Positioning System (DGPS) test Numerical calculations for flows past an unconventional [MBB/FE122/S/PUB/388] p 65 N91-11424 plan airfoil p 24 N91-10916 [DOT/FAA/CT-TN90/15] p 29 N91-10034 Mississippi Univ., University. Institut Franco-Allemand de Recherches, Saint-Louis Structural tests of aircraft window assembly equipped Comparison of shock wave rise time prediction with smoke evacuation valve (France). techniques [DOT/FAA/CT-TN89/44] p 39 N91-10051 Modeling blade/vortex interactions [AIAA PAPER 90-4001] p 74 A91-12514 Airplane systems modifications for improved cabin [ISL-R-107/89] p 14 N91-10016 smoke evacuation Rotor loads computation using singularity methods and [DOT/FAA/CT-TN90/24] p 39 N91-10052 application to the noise prediction N [ISL-PU-301/90] p15 N91-10018 FAA air traffic operational evaluation of Automated National Academy of Sciences - National Research The ISL hypersonic shock tunnel and its Surface Observing System (ASOS) Council, Washington, DC. instrumentation [DOT/FAA/CT-TN90/42J p 52 N91-10084 Airport system capacity strategic choices [ISL-CO-213/89] p52 N91-10086 Generation of a buoyant plume of artificial smoke for [SR-226] p30 N91-10979 Institute for Computer Applications In Science and airplane tests National Aeronautical Lab., Bangalore (India). [DOT/FAA/CT-90/9] p 43 N91-11015 Engineering, Hampton, VA. Wall interference studies Federal Aviation Administration, Long Beach, CA. Turbulent flow calculations using unstructured and [ PD-CF-9012] P59N91-10232 Seat dynamic performance standards for a range of adaptive meshes National Aeronautics and Space Administration, [NASA-CR-182102] p 14 N91-10010 sizes Washington, DC. (DOT/FAA/CT-TN90/23) p 26 N91-10028 Vortex instabilities in 3D boundary layers: The Computational technology for flight vehicles; Federal Aviation Administration, Washington, DC. relationship between Goertler and crossflow vortices Proceedings of the Symposium, Washington, DC. Nov. 5-7, National airspace system: In-flight assistance [NASA-CR-187456] p 15 N91-10022 1990 p58 A91-11813 operational concept Parallelized reliability estimation of reconfigurable National Aeronautics and Space Administration. Ames [PB90-233115J p28 N91-10032 computer networks Research Center, Moffett Field, CA. Florida Atlantic Univ., Boca Raton. [NASA-CR-182101] p 65 N91-11430 Some aeroacoustic and aerodynamic applications of the A ray-acoustics approach to fuselage scattering of rotor Iowa State Univ. of Science and Technology, Ames. theory of nonequilibrium thermodynamics noise Numerical computation of viscous flow about [AIAA PAPER 90-3989] p 73 A91-12502 IAIAA PAPER 90-4013] p 75 A91-12525 unconventional airfoil shapes Application of CFD to sonic boom near and mid flow-field Experimental measurement of structural power flow on [NASA-CR-187343] p 15 N91-10019 prediction an aircraft fuselage [AIAA PAPER 90-3999] p7 A91-12512 [NASA-CR-187352] p 61 N91-10335 The acoustic results of a United Techologies scale model Florida State Univ., Tallahassee. helicopter rotor tested at DNW Some aeroacoustic and aerodynamic applications of the K [AIAA PAPER 90-4035] p 75 A91-12543 theory of nonequilibrium thermodynamics Euler and potential computational results for selected [AIAA PAPER 90-3989] p 73 A91-12502 Kansas Univ., Lawrence. Calculation of aerodynamic characteristics of airplane aerodynamic configurations p 10 A91-12760 configurations at high angle of attack in steady and Computational analysis of rotor-stator interaction in unsteady flow p 42 N91-11009 turbomachinery using zonal techniques p 10 A91-12764 General Electric Co., Cincinnati, OH. Toward the routine aerodynamic analysis of complex Thermal analysis of engine inlet anti-icing systems configurations pit A91 -12770 p35 A91-10341 Navier-Stokes computations about complex George Washington Univ., Washington, DC. Laboratorio Naclonal de Engenharia e Tecnologia configurations including a complete F-16 aircraft Ejector thrust augmentors: Pulse-starting approach to Industrial, Lisbon (Portugal). p 12 A9M2772 the second solution p 23 N91-10913 Short crack behaviour in AI-Li alloy 2090 Transonic flow analysis for rotors. Part 3: Georgia Inst of Tech., Atlanta. p62 N91-11243 Three-dimensional, quasi-steady, Euler calculation An evaluation of various concepts of reducing Lockheed Engineering and Sciences Co., Hampton, [NASA-TP-2375] p 13 N91-10007 supersonic jet noise VA. Wake coupling to full potential rotor analysis code [AIAA PAPER 90-3982] p 72 A91-12495 State-of-the-art of high-speed propeller noise prediction [NASA-TM-102805] p 14 N91-10013 Application of a state-space wake model to elastic blade - A multidisciplinary approach and comparison with Euler and potential experiment/CFD correlations for a flapping in hover p 13 N91 -10006 measured data transport and two delta-wing configurations Nonlinear feedback control for high alpha flight [AIAA PAPER 90-3934] p 68 A91-12450 [NASA-TM-102208] p 14 N91-10014 [NASA-CR-186545] p 39 N9M0047 Application of CFD to sonic boom near and mid flow-field Some far-field acoustics characteristics of the XV-15 prediction Grumman Aerospace Corp., Bethpage, NY. tilt-rotor aircraft An Euler code prediction of near field to midfield sonic [NASA-TM-1028671 p 14 N91-10015 [AIAA PAPER 90-3971 ] p 71 A91-12484 Rotor systems research aircraft risk-reduction shake boom pressure signatures Transition control of instability waves over a flexible [AIAA PAPER 90-4000] p7 A91-12513 test surface in the presence of an acoustic field [NASA-TM-4186] p 38 N91-10045 [AIAA PAPER 90-4008] p 74 A91-12520 Body weight of hypersonic aircraft, part 1 H The design of two sonic boom wind tunnel models from [NASA-TM-101028] p 39 N91-10049 conceptual aircraft which cruise at Mach numbers of 2.0 A laser-sheet flow visualization technique for the large Hamilton Standard, Windsor Locks, CT. and 3.0 wind tunnels of the National Full-Scale Aerodynamics Measurement of unsteady blade surface pressure on [AIAA PAPER 90-4026] p 52 A91-12536 Complex a single rotation large scale advanced prop-fan with Los Alamos National Lab., NM. [NASA-TM-102793) p 60 N91-10268 angular and wake inflow at Mach numbers from 0.02 to Optimum hypersonic airfoil with power law shock NASA Computational Fluid Dynamics Conference. 0.70 waves Volume 1: Sessions 1-6 [NASA-CR-182123] p 47 N91-10065 [DE90-014903] p 13 N91-10008 [NASA-CP-10038-VOL-1] p 16 N91-10839

C-2 CORPORA TE SOURCE NAL

Computational Fluid Dynamics Program at NASA Ames Viscous drag reduction in boundary layers The growth of short cracks in 4340 steel and Research Center p 16 N91-10840 p58 A91-12688 aluminum-lithium 2090 p 62 N91 -11247 More accurate predictions with transonic Navier-Stokes Applied aspects of laminar-flow technology National Aeronautics and Space Administration. Lewis methods through improved turbulence modeling p8 A91-12690 Research Center, Cleveland, OH. p17 N91-10850 Riblets p59 A91 -12694 Oscillating cascade aerodynamics by an experimental CFO (or applications to aircraft aeroelasticity Outer-layer manipulators for turbulent drag reduction influence coefficient technique p2 A91-10339 p17 N91-10855 p8 A91-12695 Acoustic radiation from lifting airfoils in compressible A zonal Navier-Stokes methodology for flow simulation Convex curvature concept of viscous drag reduction subsonic flow about a complete aircraft p 18 N91-10858 p8 A91 -12696 [AIAA PAPER 90-3911 ] p 66 A91-12427 Numerical simulation of F-18 fuselage forebody flows Viscous drag reduction via surface mass injection The effect of swirl recovery vanes on the cruise noise at high angles of attack p 18 N91 -10859 p9 A91-12698 of an advanced propeller TranAir: Recent advances and applications Development of high-lift wing modifications for an [AIAA PAPER 90-3932) p 68 A91-12448 p 19 N91 -10862 advanced capability EA-6B aircraft p 10 A91-12762 Aeroacoustic effects of reduced aft tip speed at constant Numerical simulation of rotorcraft p 19 N91-10863 Aeroelastic analysis of wings using the Euler equations thrust for a model counterrotation turboprop at takeoff Three-dimensional viscous drag prediction for rotor with a deforming mesh conditions blades • p 19 N9MOB65 [NASA-TM-102733) p 15 N91-10020 (AIAA PAPER 90-3933) p 68 A91-12449 NASA Computational Fluid Dynamics Conference. NASA transport systems research vehicle 8-737 data Near-field noise of a single rotation propfan at an angle Volume 2: Sessions 7-12 link system and display formats of attack [NASA-CP-10038-VOL-2] p 20 N91-10868 [NASA-TM-102717] p 44 N91-10058 [AIAA PAPER 90-3953] p 70 A91-12469 Prediction of turbine rotor-stator interaction using Determination of the pressure drag of airfoils by Prediction of the noise from a propeller at angle of Navier-Stokes methods p 20 N91-10881 integration of surface pressures attack Simulation of powered-litt flows p 21 N91-10886 [NASA-TM-102722] p 50 N91-10078 (AIAA PAPER 90-3954) p 70 A91-12470 Unstructured mesh solution of the Euler and Research in Structures. Structural Dynamics and Noise measurements from an ejector suppressor nozzle Navier-Stokes equations p 22 N91-10892 Materials, 1990 in the NASA Lewis 9- by 15-foot low speed wind tunnel The calculation of rotor/fuselage interaction for [NASA-CP-3064] p 60 N91-10301 [AIAA PAPER 90-3983] p 73 A91-12496 two-dimensional bodies Direct use of linear time-domain aerodynamics in Effect of acoustic excitation on stalled flows over an [NASA-TM-102855J p 25 N91-10933 aeroservoelastic analysis: Aerodynamic model airfoil Summary of the industry/NASA/FAA workshop on p60 N91-10316 .(AIAA PAPER 90-4009] p 7 A91-12521 philosophy of automation: Promises and realities Computation of maximum gust loads in nonlinear aircraft Unsteady blade pressure measurements for the SR-7A p 44 N91-10942 using a new method based on the matched filter approach propeller at cruise conditions Assessing information transfer in full mission flight and numerical optimization p 60 N91-10317 [AIAA PAPER 90-4022] p 75 A91-12533 simulations p 26 N91-10946 Static and dynamic aeroelastic characterization of an Aeroacoustic effects of reduced aft tip speed at constant A function-based approach to cockpit procedure aids aerodynamically heated generic hypersonic aircraft thrust for a model counterrotation turboprop at takeoff p27 N91-10953 configuration p 61 N91-10320 conditions ATC automation concepts p 29 N91-10957 Helicopter far-field acoustic levels as a function of (NASA-TM-103608) p 76 N91-10703 Time-based operations in an advanced ATC reduced main-rotor advancing blade-tip Mach number Progress toward the development of an airfoil icing environment p 29 N91-10958 [NASA-TM-1026841 p 76 N91-10699 analysis capability p 19 N91-10866 Terminal weather information management Computational fluid dynamics research and applications The breakup of trailing-line vortices 1 p64 N91-10960 at NASA Langley Research Center p 17 N91-10841 p20 N91-10867 A piloted simulator evaluation of a ground-based 4-D Recent advances in Runge-Kutta schemes for solving Automated design of controlled diffusion blades descent advisor algorithm p 33 N91-11000 3-D Navier-Stokes equations p 17 N91-10851 p 21 N91-10883 National Aeronautics and Space Administration. Hugh Application of unstructured grid methods to steady and A numerical study of the hot gas environment around L. Dryden Flight Research Facility, Edwards, CA. unsteady aerodynamic problems p 17 N91-10856 a STOVL aircraft in ground proximity p 21 N91-10887 NACA/NASA supersonic flight research Grid generation and inviscid flow computation about CFD analysis for high speed inlets p 21 N91-10888 p 1 A91-10953 aircraft geometries p 18 N91-10857 Noise measurements from an ejector suppressor nozzle The need for a hypersonic demonstrator Navier-Stokes solutions about the F/A-18 forebody-LEX in the NASA Lewis 9- by 15-foot low speed wind tunnel p54 A91-10977 configuration p 18 N91-10860 [NASA-TM-103628] p 76 N91-11493 Flight characteristics of a modified Schweizer SGS1-36 Navier-Stokes solutions for flows related to store The effect of swirl recovery vanes on the cruise noise sailplane at low and very high angles of attack. separation p 18 N91-10861 of an advanced propeller [NASA-TP-3022] p 50 IM91-10079 A comparative study of Navier-Stokes codes for [NASA-TM-103625] p 77 N91-11494 National Aeronautics and Space Administration. high-speed flows p 20 N91 -10869 Prediction of the noise from a propeller at angle of Langley Research Center, Hampton, VA. Application of CFD codes for the simulation of scramjet attack The potential for a new era of supersonic and hypersonic combustor flowfields p 20 N91-10873 (NASA-TM-103627] p 77 N91-11495 aviation p 1 A91-10961 The use of a Navier-Stokes code in the wing design National Aerospace Lab., Amsterdam (Netherlands). Computational technology for flight vehicles; process p 21 N91-10889 The application of trajectory prediction algorithms for Proceedings of the Symposium. Washington. DC. Nov. 5-7, Applications of a transonic wing design method planning purposes in the Netherlands ATC-system 1990 p58 A91-11813 p21 N91-10890 p65 N91-10986 Active control of interior noise in model aircraft fuselages An embedded grid formulation applied to delta wings Bayesian multi-sensor tracking for advanced air traffic using piezoceramic actuators p22 N91-10891 control systems p 34 N91-11003 (AIAA PAPER 90-3922] p 67 A91-12438 Three dimensional unstructured grids for the solution Short and long fatigue crack growth in 2024-T3 under State-of-the-art of high-speed propeller noise prediction of the Euler equations p 22 N91-10893 Fokker 100 spectrum loading p 63 N91-11248 - A multidisciplinary approach and comparison with Prediction of effects of wing contour modifications on National Aerospace Lab., Tokyo (Japan). measured data low-speed maximum lift and transonic performance for the Characteristics of piping interference elimination unit [AIAA PAPER 90-3934] p 68 A91-12450 EA-6B aircraft used In the high-speed wind tunnel test of ASUKA seven Boundary element analysis of sound scattered by a [NASA-TP-3046] p 22 N91-10902 percent semi-born prototype moving surface Conical Euler simulation and active suppression of delta [NAL-TM-588] p 13 N91-10003 [AIAA PAPER 90-3944] p 69 A91-12460 wing rocking motion ( Numerical simulation of hypersonic flow around a space Removing spurious reflections from CFD solutions by [NASA-TM-102683] p 22 N91-10904 plane. Part 3: Analysis of aerothermodynamic heating using the Complex Cepstrum Implicit flux-split Euler schemes for unsteady [NAL-TR-1027T] p 14 N91-10011 [AIAA PAPER 90-3947] p 69 A91-12463 aerodynamic analysis involving unstructured dynamic The establishment and performance test of PAPI Instability of a supersonic shock-free elliptic jet meshes (Precision Approach Path Indicator) System for NAL STOL [AIAA PAPER 90-3959] p 7 A91-12473 [NASA-TM-102732] p 24 N91-10918 aircraft Noise transmission characteristics of a large scale Temporal-adaptive Euler/Navier-Stokes algorithm for [NAL-TM-579] p 28 N91-10030 composite fuselage model unsteady aerodynamic analysis of airfoils using Application of flight path reconstruction algorithms for [AIAA PAPER 90-3965] p 71 A91-12479 unstructured dynamic meshes flight data of helicopter Some far-field acoustics characteristics of the XV-15 [NASA-TM-102734) p 24 N91-10919 [NAL-TM-582] p 28 N91-10031 tilt-rotor aircraft Aviation Safety/Automation Program Conference The actuator for the low-noise STOL test plane flight [AIAA PAPER 90-39711 p 71 A91-12484 [NASA-CP-3090) p26 N91-10936 control system and its development test Sound transmission through a high-temperature acoustic Aviation safety/automation program overview [NAL-TM-574] p 37 N91-10038 probe tube p26 N91-10941 A consideration on flight paths for microwave-powered (AIAA PAPER 90-3991] p 73 A91-12504 Overview of error-tolerant cockpit research airplanes An Euler code prediction of near field to midfield sonic p40 N91-10949 [NAL-TR-1051) p39 N91-10053 boom pressure signatures Fault monitoring p 44 N91-10950 Practical flight paths for microwave-powered airplanes [AIAA PAPER 90-40001 p7 A91-12513 Fault diagnosis p 26 N91-10951 [NAL-TR-1052T] p 40 N91-10054 Transition control of instability waves over a flexible Inflight replanning for diversions p 27 N91-10955 surface in the presence of an acoustic field Time-based aircraft/ATC operations study Wind tunnel test of redundant vane-type flow-direction | AIAA PAPER 90-40081 p 74 A91-12520 p 29 N91-10959 sensing systems The design of two sonic boom wind tunnel models from Information management p 27 N91-10961 (NAL-TM-590) p 44 N91-10057 conceptual aircraft which cruise at Mach numbers of 2.0 A flight test facility design for examining digital Effects of coolant injection on turbine aerodynamic and 3.0 information transfer p 28 N91-10962 characteristics. Part 1: Test turbine and apparatus I AIAA PAPER 90-4026] p 52 A91-12536 Guidance concepts for time-based flight operations [NAL-TM-585-PT-1] p 47 N91-10059 Aircraft en route noise annoyance p32 N91-10993 Experimental investigation on the effect of coolant [AIAA PAPER 90-4028) p 63 A91-12537 The 4-D descent trajectory generation techniques under injection on turbine aerodynamic characteristics. Pan 2: The acoustic results of a United Techologies scale model realistic operating conditions p 32 N91-10994 Effects of injection from rotor casing with 30 deg slanted helicopter rotor tested at DNW A description and evaluation of TIMER: A time-based holes [AIAA PAPER 90-4035) p 75 A91-12543 terminal flow-control concept p 32 N91-10996 (NAL-TM-587-PT-2) p 47 N91-10060

C-3 Nevada Univ. CORPORA TE SOURCE

The full-body ground vibration tests using the low-noise Rolls-Royce, Inc., Atlanta, GA. Sverdrup Technology, Inc., Brook Park, OH. STOL test plane Design/development issues for high bypass ratio fans The effect of swiri recovery vanes on the cruise noise (NAL-TM-576] p 50 N91-10077 [PNR-90758] p48 N91-10076 of an advanced propeller Configuration, function and performance of the flight Rolls-Royce Ltd., Bristol (England). [AIAA PAPER 90-3932] p 68 A91-12448 simulation test facility and its motion simulation system Progress in certifying F402-RR-408: The improved Near-field noise of a single rotation propfan at an angle [NAL-TM-575] p 52 N91-10080 Pegasus engine for AV-8B and Harrier 2 plus of attack Function. and performance of visual simulation unit of [PNR-90719] p 40 N91-10056 [AIAA PAPER 90-3953] p 70 A91-12469 flight simulation test facility Technology update of early gas turbine designs Noise measurements from an ejector suppressor nozzle [NAL-TM-581] p 52 N91-10082 [PNR-90710] p48 N91-10070 in the NASA Lewis 9- by 15-foot low speed wind tunnel Future supersonic transport populsion optimization [AIAA PAPER 90-3983] p 73 A91-12496 Flight evaluation test of the PAPI (Precision Approach [PNR-90737] p48 N91-10071 Unsteady blade pressure measurements for the SR-7A Path Indicator) System Applications of thermally sprayed coating systems in propeller at cruise conditions [NAL-TM-592] p 29 N91-10966 aero engines [AIAA PAPER 90-4022] p 75 A91-12533 Flight simulator evaluation test of multi-functional display [PNR-90750] p48 N91-10072 unit Casting alloys for the jet age [NAL-TM-596] p 53 N91-11026 [PNR-90723] p56 N91-10168 Flight simulation programs for space plane Experiences in the use of ABAQUS for creep analysis [NAL-TM-594] p 55 N91-11035 [PNR-90705] p63 N91-11266 Technical Univ. of Crete, Athens (Greece). Nevada Univ., Reno. Rolls-Royce Ltd., Derby (England). The use of downlinked measurements to track civil Numerical investigations in three-dimensional internal Aero engine design factors for a low fuel price aircraft p 34 N91-11004 flows scenario Technlon - Israel Inst. of Tech., Haifa. (NASA-CR-186958] p 52 N91-10083 [PNR-90681] p47 N91-10066 Repeated buckling of composite shear panels North Carolina State Univ., Raleigh. The evolution of the bypass engine p60 N91-10303 Interaction between rotors of a counter rotating [PNR-90707] p47 N91-10068 Technlsche Univ., Brunswick (Germany, F.R.). propeller Heat transfer in aero engine gas turbines, part 1 Comparison of a mathematical one-point model and a [AIAA PAPER 90-3976) p7 A91-12489 [PNR-90754-PT-1] p 48 N91-10074 multi-point model of aircraft motion in moving air Aerodynamic interaction of counter rotating propellers Re-engining: Real stage 3 compliance plus other p 41 N91-10969 p23 N91-10910 benefits Effect of wind and wind variation on aircraft Notre Dame Univ., IN. [PNR-90755] p48 N91-10075 flight-paths p 41 N91-10972 Acoustic radiation from lifting airfoils in compressible Multi industry application of advanced materials Wind models for flight simulation p 53 N91-10975 subsonic flow [PNR-90764] p 56 N91-10139 Simulation of automated approach procedures [AIAA PAPER 90-3911] p66 A91-12427 Introduction: Needs and approaches to reliability and considering dynamic flight operations quality assurance in design and manufacture p35 N91-11008 [PNR-90683] p 60 N91-10297 Tennessee Univ., Knoxville. Total quality management at Rolls-Royce PLC Aerodynamic design optimization using computational [PNR-90759] p60 N91-10298 fluid dynamics p 43 N91-11013 Oak Ridge National Lab., TN. Do we really need 57 ways of rating aircraft noise Texas MM Univ., College Station. Energy efficiency improvement potential of commercial [PNR-90720] p76 N91-10704 On the prediction of far field computational aircraft to 2010 Influence of heat treatment on microstructure and aeroacoustics of advanced propellers [OE90-014767] p 39 N91-10046 properties of an advanced high temperature titanium [AIAA PAPER 90-3996] p 73 A91-12509 Office of the Under Secretary of Defense alloy Toledo Univ., OH. (Acquisitions), Washington, DC. [PNR-90689] p56 N91-11107 Thermal analysis of engine inlet anti-icing systems DOD responsibilities on Federal aviation and national Commercial aircraft and the environment p35 A91-10341 airspace system matters [PNR-90687] p64 N91-11307 Toronto Univ. (Ontario). Critical aspects of trajectory prediction: Flight in [PB90-218827] p 2 N91-10001 The role of process modelling in manufacture and non-uniform wind p 41 N91-10971 Ohio State Univ., Columbus. design Project HyBuJET [PNR-90702] p65 N91-11416 [NASA-CR-187011] p 38 N91-10040 Royal Radar Establishment, Malvem (England). OVRhyp, scramjet test aircraft u Prediction of aircraft trajectories p 42 N91-10984 [NASA-CR-187009] p 38 N91-10041 Supersonic combustion engine testbed, heat lightning United Technologies Corp., Windsor Locks, CT. [NASA-CR-187010] p 47 N91-10061 Unsteady airioading panel method for prop-fans Graphical interfaces for cooperative planning systems [AIAA PAPER 90-3914] p 67 A91-12430 p27 N91-10956 Unlversltaet der Bundeswehr, Hamburg (Germany, Oklahoma State Univ., Stlllwater. Sandla National Labs., Albuquerque, NM. F.R.). Flow and acoustic properties of low Reynolds number Instability of a supersonic shock-free elliptic jet Integration of model and knowledge based diagnosis, underexpanded supersonic jets p 3 A91-11198 [AIAA PAPER 90-3959] p 7 A91-12473 with the example of a turbojet engine A new approach to the flight control system Service Technique de la Navigation Aerienne, Paris [ETN-90-97900] p 49 N91-11019 reconfiguration following a battle damage and/or generic (France). Unlverslte Cathollque de Louvaln (Belgium). failure on a control surface p 50 N91-11023 Contribution of the satellite techniques to the Aircraft dynamics for air traffic control Oxford Univ. (England). surveillance of air traffic p 35 N91-11005 p42 N91-10985 The aerodynamic effects of nozzle guide vane shock Smiths Industries, Inc., Grand Rapids, Ml. Universities Space Research Association, Houston, TX. wave and wake passing on a transonic turbine rotor Aircraft trajectory: Prediction and control in the air Project HyBuJET p24 N91-10915 transport flight management computer systems [NASA-CR-187011] p38 N91-10040 H infinity-design and the improvement of helicopter p41 N91-10976 OVRhyp, scramjet test aircraft [NASA-CR-187009] p 38 N91-10041 handling qualities p 51 N91-11024 Southampton Univ. (England). Aircraft flight in wind-shear p 41 N91-10973 Supersonic combustion engine testbed, heat lightning [NASA-CR-187010] p 47 N91-10061 Voice communications in the cockpit noise environment: University of Southern California, Los Angeles. The role of active noise reduction p 61 N91 -11140 Coherent structure induced pressure fluctuations in an Pennsylvania State Univ., University Park. Stanford Univ., CA. elliptic jet Weak shock propagation through a turbulent The sonic boom of an oblique flying wing [AIAA PAPER 90-3963] p 70 A91-12477 atmosphere [AIAA PAPER 90-4002] p 74 A91-12515 [AIAA PAPER 90-4031 ] p 75 A91-12540 A numerical study of the effects of wind tunnel wall Thermal stability of jet fuel proximity on an airfoil model [DE90-016801] p56 N91-10188 [NASA-CR-187322] p 25 N91-10934 Physical Sciences, Inc., Andover, MA. Controlled vortical flow on delta wings through unsteady Virginia Polytechnic Inst and State Univ., Blacksburg. Propulsion simulation for magnetically suspended wind leading edge blowing p 43 N91-11011 Active control of interior noise in model aircraft fuselages using piezoceramic actuators tunnel models State Univ. of New York, Buffalo. [AIAA PAPER 90-3922] p 67 A91-12438 [NASA-CR-182093] p 53 N91-11027 Prediction of inviscid stagnation pressure losses in The identification of helicopter noise using a neural Princeton Univ., NJ. supersonic inlet flows p 12 A91-12903 network Time-dependent jet flow and noise computations Sterling Federal Systems, Inc., Moffett Field, CA. [AIAA PAPER 90-3973] p 72 A91-12486 [AIAA PAPER 90-3961 ] p 70 A91-12475 Calculation of the rotor induced download on airfoils Identification of aerospace acoustic sources using Nonoveriapping composite meshes for multi-element p 19 N91-10864 air-foils p 23 N91-10908 sparse distributed associative memory Sterling Federal Systems, Inc., Palo Alto, CA. [AIAA PAPER 90-3992] p 73 A91-12505 Purdue Univ., West Lafayette, IN. Computational analysis of rotor-stator interaction in Oscillating cascade aerodynamics by an experimental Virginia Univ., Charlottesville. turbomachinery using zonal techniques Computational technology for flight vehicles; influence coefficient technique p2 A91-10339 p 10 A91-12764 Development and application of the time domain panel Proceedings of the Symposium, Washington, DC. Nov. 5-7, Sterling Software, Palo Alto, CA. method p 43 N91-11010 1990 p58 A91-11813 Navier-Stokes computations about complex configurations including a complete F-16 aircraft p12 A91-12772 Stuttgart Univ. (Germany, F.R.). Rice Univ., Houston, TX. Test launch for turboaircraft engine. Description of the Optimal trajectories of aircraft and spacecraft installation p 29 N91-10968 [ILA-87-A-02] p48 N91-11018

C-4 FOREIGN TECHNOLOGY INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

Inlegration of aircraft capability in air traffic handling The variable-cycle engine - A solution to the economical simulations p 35 N91-11007 and environmental challenge of the future supersonic Typical Foreign Technology transport p 45 A91-10969 Index Listing Hypersonic aircraft studies p2 A91-10971 Hypersonic space transport system - Cruiser or CANADA accelerator? p 54 A91-10973 Transonic buffet on a supercritical aerofoil Propulsion systems for hypersonic transportation p2 A91-11157 p45 A91-10975 Low Mach number Euler computations An accurate acoustic emission location method adapted pS A91-11900 for composite materials p 57 A91-11027 Residual interference and wind-tunnel wall adaptation Thermal barrier coatings - Microstructural investigation p52 A91-12890 after annealing Transonic computations on a natural grid AUSTRALIA (ONERA, TP NO. 1990-62) p 55 A91-11751 p 13 A91-12904 The effects of aerofoil profile on wing buffet at low Calculations of the service life of components under Critical aspects of trajectory prediction: Flight in speeds p2 A91-11151 severe thermomechanical loads non-uniform wind p41 N91-10971 [ONERA, TP NO. 1990-63] p 58 A91-11752 CHINA, PEOPLE'S REPUBLIC OF Comparison of different calculation methods as applied Optimization of the arrangement of the front and rear to a fuselage of lenticular section blade rows of a tandem blade cascade [ONERA, TP NO. 1990-66) p3 A91-11755 p46 A91-11349 Comparison of afterbody test setups for combat aircraft A study of implicit space-marching method for the model supersonic viscous flow over the blunt cone [ONERA, TP NO. 1990-70] p 51 A91-11758 p4 A91-11831 A study of cylindrical interaction of turbulent boundary The CEPRA 19 anechoic wind tunnel layer/shock with swept compression corners [ONERA. TP NO. 1990-72] p 51 A91-11760 Listings in this index are arranged alphabetically p4 A91-11836 S4MA hypersonic facility - Flow angularities measurements in the S4MA wind tunnel by country of intellectual origin. The title of the Finite element method for computation of transonic flow about wings from the pressure minimum integral [ONERA, TP NO. 1990-85] p 51 A91-11766 document is used to provide a brief description of p4 A91-11838 Research and development of high-pressure-exponent the subject matter. The page number and the ac- An efficient method for solving transonic flow about fuel-rich propellents cession number are included in each entry to assist plane cascades with a large nosing p4 A91-11839 [ONERA, TP NO. 1990-91] p 55 A91-11770 Calculation of boundary-layer flows on low Reynolds L.D.V. applied to measurements between two discs in the user in locating the citation in the abstract sec- number and transonic airfoils p5 A91-11840 high speed rotation tion. If applicable, a report number is also included A three-dimensional incompressible Euler flow solution [ONERA, TP NO. 1990-94] p 58 A91-11773 as an aid in identifying the document. in turbomachinery p5 A91-11841 Influence ol chromium and molybdenum on the structural Vortex development on cruciform canard configurations stability of a high strength damage tolerant P/M nickel at supersonic speeds p5 A91-11843 based alloy for turbine disks The calculation method for subsonic longitudinal and [ONERA. TP NO. 1990-100] p 55 A91-11776 lateral aerodynamic characteristics of complete aircraft Detailed measurements of the flow field at the outlet configuration p5 A91-11844 of a backswept transonic centrifugal impeller equipped with An approximate calculating method of a vaned diffuser supersonic/hypersonic unsteady aerodynamic forces of [ONERA, TP NO. 1990-101] p4 A91-11777 airfoils p5 A91-11845 Determination of kinetic heating on wind tunnel models Application of LU-ADI algorithm in two-dimension AUSTRALIA by the surface temperature method transonic flow p5 A91-11848 The effects of aerofoil profile on wing buffet at low (ONERA, TP NO. 1990-104] p4 A91-11779 Application of cryogenic wind tunnel with liquid nitrogen speeds p2 A91-11151 Estimation of the turbulent spectral densities of the and selection of its temperature level p 52 A91-12724 mass-density using two-dimensional Fourier transform of Flight testing of two Allison T56 engines modified to Localized linearization method for wings at high angle the ARL developed low smoke configuration digitized schlieren pictures of attack p12 A91-12896 [ARL-PROP-TM-449] p 47 N91-10064 (ONERA, TP NO. 1990-110] p4 A91-11782 Experimental study of high-speed impulsive rotor noise in a wind tunnel B [ONERA, TP NO. 1990-123] p 66 A91-11786 FINLAND A technique for measuring unsteady aerodynamics in BELGIUM Three-dimensional viscous/inviscid coupling in subsonic turbomachinery p 58 A91-12421 Optimum on-line handling of air traffic over Western flow Experimental study of noise sources and acoustic Europe p 30 N91-10982 [REPT-B-24] p15 N91-10023 propagation in a turbofan model The EUROGONTROL future ATS system concept and Calculation of three-dimensional viscous/inviscid (AIAA PAPER 90-3950] p 69 A91-12466 interaction in subsonic flow the programme of studies, tests, and trials Space-structure determination of the acoustic field p30 N91-10983 [REPT-B-251 p 16 N91-10024 generated by a helicopter turboshaft engine Aircraft dynamics for air traffic control Evaluation of the ZONA51D program [AIAA PAPER 90-4012] p 46 A91-12524 [REPT-B-28) p 16 N91-10025 p42 N9M0985 Theory of slightly blunted axisymmetric power-law FRANCE Generation of aircraft trajectories for on-line operation: bodies at small angle of attack in hypersonic flow European Symposium on the Future of High Speed Air Methods, techniques, and tools p 42 N91-10987 p8 A91-12559 Transport, Strasbourg, France. Nov. 6-8, 1989, The high-resolution graphic display: A possible Proceedings p 1 A91-10951 A unified unsteady lifting-line theory p8 A91-12575 man/machine interlace for a computer assisted ATC Supersonic air transport programs in the 60's Modeling blade/vortex interactions management system p 31 N91-10989 p 1 A91-10952 (ISL-R-107/89) p14 N91-10016 The 4-D control of current air carriers in the present Development of the Griffon II turbo-ramjet Rotor loads computation using singularity methods and environment: Objectives, status, and plans p45 A91-10954 application to the noise prediction p31 N91-10990 [ISL-PU-301/90] p 15 N91-10018 All-electric flight control experiments and experiments The control of inbound flights p 32 N91-10992 Rotorcraft drivetrain life safety and reliability with a sidestick on the Concorde p 49 A91-10955 Air traffic management and aircraft guidance in a zone [AGARD-R-775] P 38 N91-10042 Concorde - 1958-1975 p 35 A91-10956 of convergence p 33 N91-10998 The ISL hypersonic shock tunnel and its The Rolls Royce/SNECMA Olympus 593 engine Ground-based 4-D guidance of flights in strong wind instrumentation operational experience and the lessons teamed p 33 N91-10999 IISL-CO-213/891 p52 N91-10086 p 45 A91-10958 The air traffic controller facing automation: Conflict or Aircraft trajectories: Computation, prediction, control, cooperation p 34 N91-11001 Twenty years of Concorde - The experience of Air volume 1. Part 1: Fundamentals. Part 2: Flight in critical Aircraft trajectory reconstitution on the basis of France p 25 A91-10959 atmospheric conditions. Part 3: Impact of new on-board multi-radar plot information p 34 N91 -11002 The sonic boom problem p1 A91-10964 technologies on aircraft operation Developments to enhance meteorological forecasting SST airframe integration for a Mach 2 transport [AGARD-AG-301-VOL-1-PT-1-3] p 29 N91-10967 for air traffic services p 64 N91-11006 p36 A91-10967 How to fly windshear p41 N91-10974

D-1 GERMANY.FEDERAL REPUBLIC OF FOREIGN TECHNOLOGY INDEX

Aircraft trajectories: Computation, prediction, control. Review of active structural control systems and flight Flight evaluation test of the PAPI (Precision Approach Volume 3. Part 9: Book of abstracts. Part 10: Bibliography. test techniques for dynamic stability investigations Path Indicator) System Part 11: List of contributors [MBB/FYT256/S/PUB/361/A] p 51 N91-11025 [NAL-TM-592] p 29 N91-10966 (AGARD-AG-301-VOL-3-PT-9-11) p 30 N91-10978 Use of the VP-200 computer for aerothermodynamic Flight simulator evaluation test of multi-functional display Aircraft trajectories: Computation, prediction, control, problems unit volume 2: Air traffic handling and ground-based guidance [MBB/FE122/S/PUB/388] p 65 N91-11424 [NAL-TM-596] p 53 N91-11026 ol aircraft. Pan 4: Air traffic handling. Part 5: Guidance Solution of the two-dimensional Euler equations by a Flight simulation programs for space plane of aircraft in a time-based constrained environment. Part finite volume discretization on unstructured triangular [NAL-TM-594] p 55 N91-11035 6: Surveillance. Part 7: Meteorological forecasts. Part 8: meshes Aircraft operation in air traffic handling simulation [ESA-TT-1135] p66 N91-11473 IAGARD-AG-301-VOL-2-PT-4-8) p 42 N91-10981 GREECE Four dimensional navigation in air traffic with 4-D The use of downlinked measurements to track civil KOREA(SOUTH) navigation aircraft p 31 N91-10991 aircraft p 34 N91-11004 Contribution of the satellite techniques to the Numerical simulation of vortex-wedge interaction surveillance of air traffic p 35 N91-11005 [AIAA PAPER 90-3918] p6 A91-12434 Test cases for computation of internal flows in aero engine components [AGARD-AR-275] p 49 N91-11022 N Parallelization on a multi-processor system of a solving INDIA Large-amplitude vibrations of free-free tapered beams NETHERLANDS method for the unsteady Navier-Stokes equations at high p57 A91-11199 Experimental/theoretical investigation of the sound field Reynolds numbers of an isolated propeller, including angle of incidence [ESA-TT-1116] p62 N91-11197 Vertex-based finite-volume solution of the two-dimensional Navier-Stokes equations effects p 59 A91-12900 [AIAA PAPER 90-3952] p 69 A91-12468 The application of trajectory prediction algorithms for Wall interference studies planning purposes in the Netherlands ATC-system [PD-CF-9012] p59 N91-10232 p65 N91-10986 GERMANY.FEDERAL REPUBLIC OF INTERNATIONAL ORGANIZATION Bayesian multi-sensor tracking for advanced air traffic Hydrogen in high-speed air transportation Solution of the Euler equations on unstructured grids pSS A91-10966 control systems p 34 N91-11003 for two-dimensional compressible flow p 3 A91-11160 Short and long fatigue crack growth in 2024-T3 under System optimization structure and propulsion of a Systems reliability assessment p 57 A91-11201 hypersonic space transportation system (Saenger) Fokker 100 spectrum loading p 63 N91-11248 Mathematical modelling for analysis of nonlinear aircraft p54 A91-10972 dynamics p 50 A91-11820 Basic materials and structures aspects for hypersonic transport vehicles (HTV) p 54 A91-10974 ITALY The high speed market in the next three decades Optimisation of hybrid propulsion systems PAKISTAN .p46 A91-10976 p77 A91-10963 Performance-robustness trade off of eigenstructure The role of primary carbides in fatigue crack propagation The case of a hypersonic flight demonstrator in aeroengine bearing steels p 55 A91-11806 p 54 A91-10978 assignment applied to rotorcraft p 49 A91 -11155 Optimization models and techniques to improve air traffic POLAND Noise mechanisms of transonic vortex airfoil Helicopter ground resonance p 36 A91 -11723 interaction management p 31 N91-10988 Simulation investigations of the helicopter ground [AIAA PAPER 90-3972] p 71 A91-12485 resonance p 36 A91-11724 Experimental study of instability modes in a The ground resonance of a helicopter with a rotor of three-dimensional boundary layer p 59 A91-12888 ideal and approximate symmetry considering the A contribution to the numerical solution of transonic flow JAPAN rotor-blade vibration in the thrust plane around a delta wing by solving Navier-Stokes equations Motion analysis of RPRVs using on-board and p36 A91-11725 [DLR-FB-90-13] p16 N91-10026 ground-based measurements p 37 A91-12224 PORTUGAL Wind tunnel investigations of the appearance of shocks Aerodynamic heating in the interaction regions of shock Short crack behaviour in AI-Li alloy 2090 in the windward region of bodies with circular cross section waves and turbulent boundary layers induced by p62 N91-11243 at angle of attack sweptback blunt fins p6 A91 -12226 [DLR-FB-90-15] p 16 N91-10027 Configuration control and airworthiness management MSB'S BO 108 design and development p 77 A91-12233 [MBB-UD-0568-90-PUB] p 40 N91-10055 Noise characteristics of the Japan's experimental Contributions in the field of aeroelastics on the occasion powered lift STOL aircraft SPAIN of the 60th anniversary of Professor Dr.-lng. Habil. Hans [AIAA PAPER 90-4014] p 75 A91-12526 Availability - A practical approach on aerospace Wilhelm Foersching Characteristics of piping interference elimination unit industry p 57 A91-11202 [ETN-90-97630] p 24 N91-10920 used ;n the high-speed wind tunnel test of ASUKA seven SWEDEN The calculation of unsteady compressible flow about percent semi-born prototype Short crack growth under realistic flight loading: Model oscillating airfoil profiles using the Euler upwind method [NAL-TM-588] p 13 N91-10003 predictions and experimental results for Al 2024 and AI-Li p25 N91-10921 Numerical simulation of hypersonic flow around a space 2090 p62 N91-11246 Design of the derivative balance for the transonic wind plane. Part 3: Analysis of aerothermodynamic heating tunnel p 53 N91-10925 [NAL-TR-1027T] p 14 N91-10011 Calculation of the pressure distribution on an oscillating The establishment and performance test of PAPI airfoil in incompressible flow considering nonlinear (Precision Approach Path Indicator) System for NAL STOL TAIWAN effects p 25 N91-10926 aircraft Determination of unsteady aerodynamic forces on Forcing level effect of internal acoustic excitation on [NAL-TM-579) p 28 N91-10030 the improvement of airfoil performance engines with a view to flutter investigations Application of flight path reconstruction algorithms for p48 N91-10927 [AIAA PAPER 90-4010! p 74 A91-12522 flight data of helicopter Numerical simulation of supersonic mixing layer using Unsteady wind tunnel wall interferences in subsonic and [NAL-TM-582] p 28 N91-10031 high resolution scheme transonic profile flows p 53 N9M0928 The actuator for the low-noise STOL test plane flight [AIAA PAPER 90-4025] p8 A91-12535 A quarter of a century of aeroelastic cooperation control system and its development test between research and industry (a review). Part 1: Fighter [NAL-TM-574] p 37 N91-10038 airplanes and helicopters p 78 N91-10931 A consideration on flight paths for microwave-powered u A quarter of a century of aeroelastic cooperation airplanes between research and industry (a review). Part 2: Transport [NAL-TR-1051] p39 N91-10053 U.S.S.R. airplanes and other civil applications p 40 N91 -10932 Practical flight paths for microwave-powered airplanes A self-organizing stochastic control system adaptable Air rescue in the Federal Republic of Germany [NAL-TR-1052T] p 40 N91-10054 to changing perturbation characteristics [ETN-90-97878] p 28 N91-10963 Wind tunnel test of redundant vane-type flow-direction p65 A91-11353 Contributions to the improvement of flight safety in wind sensing systems A three-dimensional boundary layer on bodies with a shear [NAL-TM-590] p 44 N91-10057 slight cross-sectional asymmetry at small angles of [ESA-TT-1141] p28 N91-10965 Effects of coolant injection on turbine aerodynamic attack p5 A91-11909 Comparison of a mathematical one-point model and a characteristics. Part 1: Test turbine and apparatus Detection of concealed corrosion damage in aircraft multi-point model of aircraft motion in moving air [NAL-TM-585-PT-1] p 47 N91-10059 structures using the eddy current method p 41 N91-10969 Experimental investigation on the effect of coolant p58 A91-11974 injection on turbine aerodynamic characteristics. Part 2: Effect of wind and wind variation on aircraft An experimental study of the laminar-turbulent transition Effects of injection from rotor casing with 30 deg slanted flight-paths p 41 N91-10972 behind three-dimensional roughness in a boundary layer holes Wind models for flight simulation p 53 N91-10975 on a sharp cone p 6 A91 -12014 [NAL-TM-587-PT-2] p 47 N91-10060 Simulation of automated approach procedures The full-body ground vibration tests using the low-noise Effect of energy release in the shock layer on supersonic flight p6 A91-12016 considering dynamic flight operations STOL test plane p35 N91-11008 [NAL-TM-576] • p 50 N91-10077 Shock wave formation during interaction with a weak Test launch for turboaircraft engine. Description of the Configuration, function and performance of the flight discontinuity at the boundary of a local subsonic region installation simulation test facility and its motion simulation system p6 A91-12017 [ILA-87-A-02] p48 N91-11018 [NAL-TM-575] p 52 N91-10080 Interaction of two supersonic radial gas flows Integration of model and knowledge based diagnosis, Function and performance of visual simulation unit of p6 A91-12018 with the example of a turbojet engine flight simulation test facility Fluctuations of a shock wave generated by boundary [ETN-90-97900] p 49 N91-11019 [NAL-TM-581] p 52 N91-10082 layer separation p6 A91-12019

D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM

Flow of a rarefied gas around a sphere in the presence The role of process modelling in manufacture and of injection p6 A91-12020 design Reliability of results of the capillary testing of gas turbine [PNR-90702] p65 N91-11416 engine components during repairs p 58 A91 -12036 Practical aerodynamics and flight dynamics of Yak-52 and Yak-55 aircraft p 13 A91-12911 Jets and lifting surfaces: Computer simulation p 13 A91-12913 Diagnostics of aviation electric machines p37 A91-12919 UNITED KINGDOM Commercial supersonic operations - Thirteen years of experience with Concorde p 36 A91-10957 British Airways operational experience with Concorde p26 A91 -10960 Future supersonic transport propulsion optimisation p45 A91 -10968 Practical developments in holographic interferometry p57 A91-11152 Mixed structured-unstructured meshes for aerodynamic flow simulation p 65 A91 -11154 The aerodynamic interference between tanker and receiver aircraft during air-to-air refuelling p3 A91-11159 Comparison of modal parameter estimation techniques on aircraft structural data p 57 A91-11219 Application of the vortex cloud method to cascades p3 A91-11347 Holographic interferometry for flow visualization studies in high speed fans p 46 A91-11351 Harrier - The next 30 years p 36 A91-11715 Soviet space planes p 54 A91-11737 A process model for age hardening of aluminium alloys. I - The model p 56 A91-11883 A superlative from Sukhoi - The SU-27 p37 A91-12063 Procurement and testing of a 1/5 scale advanced counter rotating propfan model [AIAA PAPER 90-3975] p 46 A91-12488 Radiation integrals for sound generation by the Lighthill quadruples in propeller acoustics [AIAA PAPER 90-3993] p 73 A91-12506 Diffraction patterns in the acoustic field of a propeller [AIAA PAPER 90-3994] p 73 A91-12507 Shock capturing using a pressure-correction method p59 A91-12887 Helicopter transmissions: Design for safety and reliability p 38 N91-10043 Progress in certifying F402-RR-408: The improved Pegasus engine for AV-8B and Harrier 2 plus [PNR-90719] p40 N91-10056 Aero engine design factors for a low fuel price scenario [PNR-90681] p47 N91-10066 The evolution of the bypass engine [PNR-90707] p 47 N91-10068 Technology update of early gas turbine designs [PNR-90710] p.48 N91-10070 Future supersonic transport populsion optimization (PNR-90737] p48 N91-10071 Applications of thermally sprayed coating systems in aero engines [PNR-90750] p48 N91-10072 Heat transfer in aero engine gas turbines, part 1 [PNR-90754-PT-1] p 48 N91-10074 Re-engining: Real stage 3 compliance plus other benefits [PNR-90755] p48 N91-10075 Multi industry application of advanced materials (PNR-90764] p56 N91-10139 Casting alloys for the jet age [PNR-90723] p56 N91-10168 Introduction: Needs and approaches to reliability and quality assurance in design and manufacture [PNR-90683] p60 N91-10297 Total quality management at Rolls-Royce PLC [PNR-90759] p60 N91-10298 Do we really need 57 ways of rating aircraft noise [PNR-90720] p76 N91-10704 The aerodynamic effects of nozzle guide vane shock wave and wake passing on a transonic turbine rotor p24 N91-10915 Aircraft flight in wind-shear p 41 N91-10973 Prediction of aircraft trajectories p 42 N91-10984 H infinity-design and the improvement of helicopter handling qualities p 51 N91-11024 Influence of heat treatment on microstructure and properties of an advanced high temperature titanium alloy [PNR-90689] p56 N91-11107 Voice communications in the cockpit noise environment: The role of active noise reduction p 61 N91-11140 Experiences in the use of ABAOUS for creep analysis [PNR-90705] p63 N91-11266 Commercial aircraft and the environment [PNR-90687] p64 N91-11307

D-3 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

NCC2-055 p25 N91-10934 Typical Contract Number NCC2-507 p 52 N91-10083 Index Listing NCC2-598 p61 N91-10333 NSC-79-0210-0006-03 p 74 A91-12522 NSC-79-0401-E006-44 p8 A91-12535 NSF ASC-88-19373 p 65 N91-11430 N00014-84-C-0359 p2 A91-10329 NAS1-18616 .. )53 N91-11027 p2 A91-10330 N00014-87-K-0837 p 69 A91-12464 N00014-89-J-1319 p7 A91-12472 N00014-90-C-0089 p 46 A91-12446 N00140-87-C-9901 p 67 A91-12444 ACCESSION W-7405-ENG-36 p 13 N91-10008 NUMBER 324-01-00 p 53 N91-11027 505-03-01 p47 N91-10065 505-34-13-34 p64 N91-10548 505-45-21 pSO N91-10079 505-60-00 p 14 N91-10013 Listings in this index are arranged alphanumeri- 505-60-01 p 16 N91-10839 cally by contract number. Under each contract p20 N91-10868 number, the accession numbers denoting docu- 505-61-01 p60 N91-10268 ments that have been produced as a result of re- 505-61-21-03 p22 N91-10902 505-61-21 p 14 N91-10014 search done under the contract are shown. The 505-61-51 p 13 N91-10007 accession number denotes the number by which p38 N91-10045 the citation is identified in the abstract section. p25 N91-10933 505-62-4D p76 N91-10703 Preceding the accession number is the page p77 N91-11495 number on which the citation may be found, 505-62-40 p76 N91-11493 505-63-01-07 p 60 N91-10301 505-63-21-01 p22 N91-10904 505-63-50-12 p 15 N91-10020 DE-AC05-84OR-21400 p 39 N91-10046 p24 N91-10918 DE-AC07-76ID-01570 p 56 N91-11128 p24 N91-10919 DE-AC22-88PC-88827 p 56 N91-10188 505-66-01-02 p 50 N91-10078 ERI PROJ. 1874 P 15 N91-10019 505-66-41 p44 N91-10058 F33615-86-C-2604 p 55 A91-10345 505-67-21-07 p 26 N91-10936 F33657-84-C-2137 p 57 A91-10336 505-90-21-01 p 14 N91-10010 F49620-88-C-0022 p2 A91-10337 p 15 N91-10022 F49642-83-C-0223 p 74 A91-12516 p65 N91-11430 JPL-956415 •-. P 29 N91-10968 532-06-01-09 p76 N91-10699 NAGW-966 P 12 A91-12903 535-03-10 p 77 N91-11494 NAG1-1096 '. P 70 A91-12477 537-03-21 p 14 N91-10015 NAG1-10 p3 A91-11198 763-01-61 p 39 N91-10049 NAG1-1132 p65 N91-11430 NAG1-159 p3 A91-11198 NAG1-516 p29 N91-10968 NAG1-645 P 15 N91-10019 NAG1-657 p7 A91-12473 NAG1-685 p61 N91-10335 NAG1-715 p75 A91-12525 NAG1-722 P 76 N91-11488 NAG1-762 P 73 A91-12505 NAG1-787 p65 N91-11430 NAG1-959 p39 N91-10047 NAG2-209 P 37 A91-12894 NAG2-477 P 37 A91-12894 NAG3-1066 P 72 A91-12495 NAG3-349 P 44 A91-10245 NAG3-354 p73 A91-12509 NAG3-357 P 66 A91-12428 NAG3-732 P 66 A91-12427 NAG3-855 p7 A91-12489 NASW-4228 p28 N9M0964 NASW-4518 p28 N91-10964 NAS1-17748 p64 N91-10548 NAS1-18037 p67 A91-12442 p 71 A91-12482 NASt-18235 p8 A91-12696 NAS1-18471 p72 A91-12486 NAS1-18599 P 8 A91-12696 NAS1-18605 P 14 N91-10010 p 15 N9M0022 p65 N9I-11430 NAS1-18616 p53 N91-11027 NAS1-18745 p75 A91-12528 NAS1-18849 p70 A91-12475 NAS2-12513 P'l A91-12770 NAS3-23051 P 47 N91-10065 NAS3-23720 P 67 A91-12430 NAS3-25829 P 70 A91-12475 NCC1-122 p37 N91-10039 NCC1-14 p69 A91-12460

E-1 REPORT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

Typical Report Number Index Listing AIAA PAPER 90-3955 p 70 A91-12471 # OOE/PC-88827/T5 p 56 N91-10I88 # AIAA PAPER 90-3958 p 7 . A91-12472 tt AIAA PAPER 90-3959 p 7 A91-12473 • tt DOT/FAA/CT-TN89/44 p 39 N91-10051 AIAA PAPER 90-3961 p 70 A91-12475 ' tt DOT/FAA/CT-TN90/15 p 29 N91-10034 AIAA PAPER 90-3962 p 70 A91-12476 tt OOT/FAA/CT-TN90/21 p 26 N9M0029 AIAA PAPER 90-3963 p 70 A9M2477 • tt DOT/FAA/CT-TN90/23 p 26 N91-10028 AIAA PAPER 90-3965 p 71 A91-12479 • tt DOT/FAA/CT-TN90/24 p 39 N91-10052 AIAA PAPER 90-3966 p 71 A91-12480 tt DOT/FAA/CT-TN90/42 p 52 N91-10084 NASA-CR-181352 p 37 AIAA PAPER 90-3968 p 71 A91-12482 • ft AIAA PAPER 90-3969 p 71 A91-12483 # DOT/FAA/CT-90/1 -VOL-2 p29 N91-10033 AIAA PAPER 90-3971 p 71 A91-12484 ' tt OOT/FAA/CT-90/9 p43 N91-11015 AIAA PAPER 90-3972 p 71 A9M2485 tt AIAA PAPER 90-3973 p 72 A91-12486 '# E-4137 p 47 N91-10065 ' AIAA PAPER 90-3975 p 46 A9M2488 tt E-5717 p 76 N91-11493 ' AIAA PAPER 90-3976 p7 A91-12489 ' tt E-5731 p 77 N91-11494 ' AIAA PAPER 90-3977 p 72 A91-12490 tt E-5732 p 76 N91-10703 ' AIAA PAPER 90-3978 p 72 A91-12491 tt E-5795 p 77 N91-11495 ' Listings in this index are arranged alphanumeri- AIAA PAPER 90-3979 p 72 A9M2492 # cally by report number. The page number indicates AIAA PAPER 90-3980 p 72 A9M2493 tt EGG-M-90041 p56 N91-11128 tt AIAA PAPER 90-3982 p 72 A91-12495 ' tt the page on which the citation is located. The ac- AIAA PAPER 90-3983 p 73 A91-12496 ' tt EMA-85-R-37 p 64 N91-10548 ' # cession number denotes the number by which the AIAA PAPER 90-3989 p 73 A91-12502 ' tt AIAA PAPER 90-3991 p 73 A91-12504 • tt citation is identified. An asterisk (') indicates that ESA-TT-1116 p62 N91-11197 # AIAA PAPER 90-3992 p 73 A91-12505 ' tt ESA-TT-1135 p 66 N91-11473 tt the item is a NASA report. A pound sign (#) indi- AIAA PAPER 90-3993 ...-. p 73 A91-12506 tt ESA-TT-1141 p28 N91-10965 tt cates that the item is available on microfiche. AIAA PAPER 90-3994 p 73 A91-12507 # AIAA PAPER 90-3996 p 73 A91-12509 *# ETN-90-97569 p 14 N91-10016 # AIAA PAPER 90-3999 p 7 A91-T2512 * ft ETN-90-97572 p 52 N91-10086 # N91-10007 ' A-86374-PT-3 p 13 AIAA PAPER 90-4000 p7 A91-12513 • # ETN-90-97577 p 15 N91-10018 tt AIAA PAPER 90-4001 p 74 A91-12514 • # A-88279-PT-1 p 39 N91-10049 ' ETN-90-97628 p 16 N91-10026 tt A-88316 P 38 N9M0045 ' AIAA PAPER 90-4002 p 74 A9M2515 • # ETN-90-97629 p 16 N91-10027 # AIAA PAPER 90-4003 p 74 A91-12516 tt A-89160-VOL-1 p 16 N9M0839 ' ETN-90-97630 p 24 N91-10920 tt AIAA PAPER 90-4004 p 74 A91-12517 # A-89160-VOL-2 p 20 N91-10868 ' ETN-90-97838 p 40 N91-10055 # AIAA PAPER 90-4006 p 74 A91-12519 tt ETN-90-97845 p 51 N91-11025 # A-89197 p H N91-10014 ' AIAA PAPER 90-4008 p 74 A91-12520 -ft ETN-90-97848 p 65 N91-11424 # A-90082 p 60 N91-10268 ' AIAA PAPER 90-4009 p7 A91-12521 '# A-90117 p M N9M0013 ' ETN-90-97878 p 28 N91-10963 tt AIAA PAPER 90-4010 p 74 A9M2522 ft ETN-90-97879 p 48 N91-11018 tt A-90246 P 1" N91-10015 ' AIAA PAPER 90-4012 p 46 A91-12524 tt ETN-90-97900 p 49 N91-11019 ft A-90256 P 25 N91-10933 ' AIAA PAPER 90-4013 p 75 A91-12525 • tt ETN-90-97928 p 47 N91-10066 ft AIAA PAPER 90-4014 p 75 A91-12526 # ETN-90-97930 p 60 N91-10297 # AD-A223568 p 29 N91- 10967 # AIAA PAPER 90-4016 p 75 A91-12528 ' # ETN-90-97931 p 64 N91-11307 # AD-A225265 p 42 N91-10981 ft AIAA PAPER 90-4018 p 8 A91-12530 # ETN-90-97932 p 56 N91-11107 tt AD-A225266 p 30 N91-10978 tt AIAA PAPER 90-4022 p 75 A91-12533 * # ETN-90-97936 p 65 N91-11416 tt AD-A226496 p 38 N91-10042 # AIAA PAPER 90-4023 p 75 A91-12534 # ETN-90-97937 p 63 N91-11266 # AIAA PAPER 90-4025 p8 A91-12535 # AO-B146522L p 16 N91-10026 ETN-90-97939 p 47 N91-10068 # AIAA PAPER 90-4026 p 52 A91-12536 ' # ETN-90-97941 p 48 N91-10070 tt AD-B147243L p 16 N91-10027 AIAA PAPER 90-4028 p 63 A91-12537 • # ETN-90-97945 p 40 N91-10056 # AIAA PAPER 90-4029 p 63 A91-12538 # ETN-90-97946 p 76. N91-10704 # AGARO-AG-301-VOL-1-PT-1-3 .... p 29 N91-10967 # AIAA PAPER 90-4031 p 75 A91-12540 * # ETN-90-97948 p 56 N91-10168 tt AGARD-AG-301-VOL-2-PT-4-8 .... p 42 N91-10981 tt AIAA PAPER 90-4032 p 63 A9M2541 # AGARO-AG-301-VOL-3-PT-9-11 .. p 30 N91-10978 ft ETN-90-97950 p 48 N91-10071 tt AIAA PAPER 90-4035 p 75 A9M2543 ' # ETN-90-97955 p 48 N91-10072 # ETN-90-97958 p 48 N91-10074 tt AGARD-AR-275 p 49 N91-11022 tt AIAA-90-0936 p 24 N91-10918 • # ETN-90-97959 p 48 N91-10075 tt AIAA-90-1032 p 15 N91.10020 • # ETN-90-97960 p 48 N91-10076 tt \ AGARO-R-775 p 38 N91-10042 # AIAA-90-1650 p 24 N91-10919 • ft ETN-90-97961 p 60 N91-10298 AIAA-90-3932 p 77 N91-11494'# AIAA PAPER 90-3254 p 50 A91-12928 ETN-90-97963 p 56 N91-10139 AIAA-90-3933 p 76 N9M0703 * tt ETN-90-97999 p 62 N91-1I197 # AIAA PAPER 90-3255 p 50 A91-12929 AIAA-90-3954 p 77 N91-11495 • ft ETN-90-98001 p66 N91-11473 tt AIAA PAPER 90-3722 p 1 A91-10114 AIAA-90-3983 p 76 N9M1493'# AIAA PAPER 90-3911 p 66 A91-12427 ' ETN-90-98003 p 28 N91-10965 # AIAA PAPER 90-3912 p 66 A9I-12428 ' AR-006-100 p47 N91-10064 § AIAA PAPER 90-3914 p 67 A91-12430 ' H-1563 p50 N91-10079'# AIAA PAPER 90-3917 p 67 A91-12433 ARL-PROP-TM-449 p 47 N91-10064 tt AIAA PAPER 90-3918 p6 A91-12434 ICASE-90-60 p65 N91-11430' ICASE-90-61 P14 N91-10010 ' AIAA PAPER 90-3920 p 67 A91-12436 AVSCOM-TR-88-A-003 p 38 N91-10045 • # AIAA PAPER 90-3922 p 67 A91-12438 ' ICASE-90-72 p 15 N91-10022 ' tt AIAA PAPER 90-3924 p 67 A91-12440 CFD-24 p15 N91-10019 ' ft AIAA PAPER 90-3926 p 67 A91-12442 ' ILA-87-A-02 p48 N91-11018 tt \ AIAA PAPER 90-3928 p 67 A91-12444 CONF-9010154-1 p 13 N91-10008 tt ISBN-0-309-04956-3 p 30 N91-10979 AIAA PAPER 90-3930 p 46 A91-12446 CONF-901109-3 p 56 N9M1128 tt AIAA PAPER 90-3932 p 68 A91-12448 ' ISBN-92-835-0540-9 p 38 N91-10042 ISBN-92-835-0547-6 p 29 N91-10967 AIAA PAPER 90-3933 p 68 A91-12449 ' OE90-010929 p 56 N91-11128 # ISBN-92-835-0562-X p 42 N91-10981 AIAA PAPER 90-3934 p 68 A91-12450 ' DE90-014767 p 39 N91-10046 # ISBN-92-835-0563-8 p 30 N91-10978 AIAA PAPER 90-3935 p 68 A91-12451 DE90-014903 p 13 N91-10008 tt ISBN-92-835-0573-5 p 49 N91-11022 AIAA PAPER 90-3936 p 68 A91-12452 DE90-016801 p 56 N91-10188 # AIAA PAPER 90-3941 p 69 A91-12457 ISBN-951-22-0248-4 p 15 N91-10023 ISBN-951-22-0329-4 p 16 N91-10024 AIAA PAPER 90-3944 p 69 A9I-12460 OFVLR-F8-88-34 p 66 N9T-t1473 tt ISBN-951-22-0398-7 p 16 N91-10025 AIAA PAPER 90-3947 p 69 A91-12463 ' DFVLR-FB-88-49 p 28 N91-10965 tt AIAA PAPER 90-3948 p 69 A91-12464 AIAA PAPER 90-3950 p 69 A91-12466 ISL-CO-213/89 p52 N91-10086 tt DLR-FB-90-13 p 16 N91-10026 tt AIAA PAPER 90-3951 p 69 A91-12467 DLR-FB-90-15 p 16 N91-10027 # AIAA PAPER 90-3952 p 69 A91-12468 ISL-PU-301/90 p15 N91-10018 tt AIAA PAPER 90-3953 p 70 A91-12469 AIAA PAPEfl 90-3954 p 70 A91-12470 DOD-O-5030.19 p2 N91-10001 # ISL-R-107/89 p 14 N91-10016 tt

F-1 ISSN-017M342 REPORT NUMBER INDEX

ISSN-0171-1342 p 16 N91-10026 ft NAS 1.26:184565 p 61 N91-10333 * ft PNR-90683 p60 N91-10297 ft ISSN-0171-1342 p16 N91-10027 # NAS 1.26:186545 p 39 N91-10047 • ft PNH-90687 P64 N91-11307 ft ISSN-0358-2620 p 15 N91-10023 ft NAS 1.26:186879 p 76 N91-11488 * ft PNR-90689 P56 N91-11107 ft ISSN-0358-2620 p 16 N91-10024 ft NAS 1.26:186958 p 52 N91-10083 ' ft PNR-90702 p65 N91-11416 ft ISSN-0358-2620 p 16 N91-10025 ft NAS 1.26:187009 p 38 N91-10041 • ft PNR-90705 p63 N91-11266 ft ISSN-0360-859X p 30 N91-10979 # NAS 1.26:187010 p 47 N91-10061 • ft PNR-90707 P 47 N91-10068 ft 1SSN-03B9-4010 p 14 N91-10011 # NAS 1.26:187011 p 38 N91-10040 ' ft PNR-90710 P 48 N91 -10070 # ISSN-0389-4010 p 39 N91-10053 ft NAS 1.26:187322 p 25 N91-10934 • ft PNR-90719 p40 N91-10056 ft ISSN-0389-4010 p 40 N91-10054 # NAS 1.26:187343 p 15 N91-10019 ' ft PNH-90720 p76 N91-10704 ft ISSN-0452-2892 P 37 N91-10038 NAS 1.26:187352 p 61 N91-10335 ' ft PNR-90723 P 56 N91-10168 ft ISSN-0452-2982 p 13 N91-10003 NAS 1.26:187456 p 15 N91-10022 • ft PNR-90737 P48 N91-10071 ft ISSN-0452-2982 p 28 N91-10030 NAS 1.26:3974 p 64 N91-10548 ' # PNR-90750 p48 N91 -10072 ft ISSN-0452-2982 P 28 N91-10031 NAS 1.26:4330 p 28 N91-10964 • ft PNR-90754-PT-1 p48 N91 -10074 tt ISSN-0452-2982 p 44 N91-10057 NAS 1.55:10038-VOL-1 p 16 N91-10839 " ft PNR-90755 p 48 N91-10075 ft ISSN-0452-2982 p 47 N91-10059 NAS 1.55:10038-VOL-2 p 20 N91-10868 ' ft PNR-90758 p 48 N91-10076 ft ISSN-0452-2982 p 47 N91-10060 NAS 1.55:3064 p 60 N91-10301 • ft PNR-90759 p60 N91-10298 ft ISSN-0452-2982 P 50 N91-10077 NAS 1.55:3090 p 26 N91-10936 • ft PNR-90764 P 56 N91-10139 ft ISSN-0452-2982 p 52 N91-10080 NAS 1.60:2375 p 13 N91-10007 ' # ISSN-0452-2982 p 52 N91-10082 NAS 1.60:3022 p 50 N91-10079 ' ft PSI-2055/TR-859 p 53 N91-11027' ISSN-0452-2982 p 29 N91-10966 # NAS 1.60:3046 p 22 N91-10902 * ft ISSN-0452-2982 p 53 N91-11026 ft REPT-B-24 P15 N91-10023 ISSN-0452-2982 p 55 N91-11035 ft NAS-SR-1328 p 28 N91-10032 ft REPT-B-25 p 16 N91-10024 REPT-B-28 . p16 N91-10025 ISU-ER1-AMES-91-110 p15 N91-10019 " # NASA-CP-10038-VOL-1 p 16 N91-10839 * ft NASA-CP-10038-VOL-2 p 20 N91-10868 * ft SR-226 . p 30 N91-10979 ft JIAA-TR-99 p25 N91-10934 ' # NASA-CP-3064 p60 N91-10301 ' ft NASA-CP-3090 p26 N91-10936 ' ft SSRP-90/03 p 61 N91-10333 * ft JTN-90-80003 P 37 N91-10038 JTN-90-80004 P 52 N91-10080 NASA-CR-181352 p 37 N91-10039 ' ft JTN-90-80005 P 50 N91-10077 NASA-CR-182093 p 53 N91-11027 * ft JTN-90-80007 P 28 N91-10030 NASA-CR-182101 p 65 N91-11430 * ft JTN-90-80009 P 52 N91-10082 NASA-CR-182102 p 14 N91-10010 • ft JTN-90-80010 P28 N91-10031 NASA-CR-182123 p 47 N91-10065 • ft JTN-90-80013 P47 N91-10059 NASA-CR-184565 p 61 N91-10333 • ft JTN-90-80014 p47 N91-10060 NASA-CR-186545 p 39 N91-10047 * f> JTN-90-80015 P 13 N91-10003 NASA-CR-186879 p 76 N91-11488 ' ft JTN-90-80017 p44 N91-10057 NASA-CR-186958 p 52 N91-10083 ' ft JTN-90-80120 P55 N91-11035 # NASA-CR-187009 p 38 N91-10041 '# JTN-90-80122 P 53 N91-11026 # NASA-CR-187010 p 47 N91 -10061 '# JTN-90-80135 P 29 N91-10966 ft NASA-CR-187011 p38 N91-10040 ' ft NASA-CR-187322 p 25 N91-10934 * ft L-16735 p60 N91-10301 * ft NASA-CR-187343 p 15 N91-10019 ' ft L-16741 P 22 N91-10902 " ft NASA-CR-187352 p 61 N91-10335 * ft L-16840 P26 N91-10936 ' # NASA-CR-187456 p 15 N91-10022 ' # NASA-CR-3974 p 64 N91-10548 ' ft LA-UR-90-2437 p 13 N91-10008 # NASA-CR-4330 p 28 N91-10964 • ft

LC-90-34787 P30 N91-10979 ft NASA-TM-101028 p 39 N91-10049 • ft NASA-TM-102208 p 14 N91-10014 • ft MBB-UD-0568-90-PUB p 40 N91-10055 ft NASA-TM-102683 p 22 N91-10904 • ft NASA-TM-102684 p 76 N91-10699 ' ft MBB/FE122/S/PUB/388 p 65 N91-11424 ft NASA-TM-102717 p44 N91-10058 ' ft NASA-TM-102722 p 50 N91-10078 * ft MBB/FYT256/S/PUB/361/A p 51 N91-11025 # NASA-TM-102732 p 24 N91-10918 * ft NASA-TM-102733 p15 N91-10020 • # NAL-TM-574 P 37 N91-10038 NASA-TM-102734 p 24 N91 -10919 "ft NAL-TM-575 P 52 N91-10080 NASA-TM-102793 p 60 N91-10268 ' ft NAL-TM-576 P 50 N91-10077 NASA-TM-102805 p 14 N91-10013 " ft NAL-TM-579 P 28 N91-10030 NASA-TM-102855 p25 N91-10933 ' ft NAL-TM-581 P 52 N91-10082 NASA-TM-102867 p 14 N91-10015 * ft NAL-TM-582 P 28 N91-10031 NASA-TM-103608 p 76 N91-10703 * ft NAL-TM-585-PT-1 p 47 N91-10059 NASA-TM-103625 p 77 N91-11494'# NAL-TM-587-PT-2 p 47 N91-10060 NASA-TM-103627 p 77 N91-11495'* NAL-TM-588 P 13 N9M0003 NASA-TM-103628 p 76 N91-11493'* NAL-TM-590 P44 N91-10057 NASA-TM-4186 p 38 N91-10045 ' ft NAL-TM-592 P 29 N91-10966 # NAL-TM-594 P 55 N91-11035 ft NASA-TP-2375 p 13 N91-10007 ' ft NAL-TM-596 P 53 N91-11026 ft NASA-TP-3022 p 50 N91-10079 ' ft NASA-TP-3046 p 22 N91-10902 * ft NAL-TR-1027T P 14 N91-10011 ft NAL-TR-1051 P 39 N91-10053 # ONERA-NT-1987-8 p 62 N91-11197 ft NAL-TR-1052T p40 N91-10054 ft ONERA, TP NO. 1990-100 p55 A91-11776 NAS 1.15:101028 p 39 N91-10049 * ft ONERA. TP NO. 1990-101 p 4 A91-11777 NAS 1.15:102208 p 14 N91-10014 * ft ONERA, TP NO. 1990-104 p4 A91-11779 NAS 1.15:102683 p 22 N91-10904 " ft ONERA, TP NO. 1990-110 p4 A91-11782 NAS 1.15:102684 p 76 N91-10699 * ft ONERA, TP NO. 1990-123 p66 A91-11786 NAS 1.15:102717 p 44 N91-10058 * ft ONERA, TP NO. 1990-62 p55 A91-11751 NAS 1.15:102722 p 50 N91-10078 " # ONERA, TP NO. 1990-63 p 58 A91-11752 NAS 1.15:102732 p 24 N91-10918 ' ft ONERA, TP NO. 1990-66 p3 A91-11755 NAS 1.15:102733 p 15 N91-10020 ' # ONERA, TP NO. 1990-70 p 51 A91-11758 NAS 1.15:102734 p 24 N91-10919 ' ft ONERA, TP NO. 1990-72 p51 A91-11760 NAS 1.15:102793 p 60 N91-10268 ' ft ONERA, TP NO. 1990-85 p51 A91-11766 NAS 1.15:102805 p 14 N91-10013 ' # ONERA, TP NO. 1990-91 p 55 A91-11770 NAS 1.15:102855 p 25 N91-10933 " ft ONERA, TP NO. 1990-94 p58 A91-11773 NAS 1.15:102867 p 14 N91-10015 * ft NAS 1.15:103608 p 76 N91-10703 * ft ORNL-6622 p39 N91-10046 ft NAS 1.15:103625 p 77 N91-11494 * ft NAS 1.15:103627 p 77 N91-11495 " ft OTN-027636 p 40 N91-10055 # NAS 1.15:103628 p 76 N91-11493'* NAS 1.15:4186 p38 N91-10045 * ft PB90-218827 p 2 N91-10001 ft NAS 1.26:181352 p 37 N91-10039 * ft PB90-233115 p28 N91-10032 ft NAS 1.26:182093 p 53 N91-11027'# NAS 1.26:182101 p 65 N91-11430'# PD-CF-9012 p 59 N91-10232 ft NAS 1.26:182102 p 14 N91-10010 ' ft NAS 1.26:182123 p 47 N91-10065 ' ft PNR-90681 p47 N91-10066 ft

F-2 ACCESSION NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 262) February 1991

39 Typical Accession Number A91 -12427 •tt p66 A91-12696 •tt P8 N91 -10052 tt P Index Listing A91-12428 •it p66 A91 -12698 •ft p9 N91-10053 ft p39 p67 N91-10054 » p40 A91-12430 •ft A91 -12724 P52 N91-10055 tt p40 A91-12433 tt p67 A91-12751 p9 A91-12434 it p6 N91-10056 # p40 A91 -12753 it P9 A91 -12436 tt p67 N91-10057 p44 N91-10007 • # p13 A91 -12754 tt p59 A91-12438 •tt p67 N91-10058 •tt P44 A91-12755 it p9 A91-12440 tt p67 N91 -10059 p47 A91-12756 tt p9 A91 -12442 •tt p67 N9 1-1 0060 p47 A91-12757 tt p9 A91-12444 it p67 N91-10061 '» P47 I A91-12758 tt p 10 A91 -12446 tt p46 N9 1-1 0064 « p47 A91-12759 tt p 10 NASA ON PAGE A91 -12448 •it p68 N91 -10065 •ft p47 ACCESSION A91-12760 •tt p 10 NUMBER SPONSORED MICROFICHE NUMBER A91-12449 •tt p68 N91 -10066 it P47 A91-12761 tt p 10 A91 -12450 •# p68 N91-10068 # p47 A91-12762 •tt p 10 A91-12451 tt p68 N91-10070 » p48 A91 -12763 # p 10 A91 -12452 tt p68 N91-10071 tt p48 A91-12764 '# p 10 A91-12457 tt p69 N91-10072 tt p48 A91 -12765 tt p11 Listings in this index are arranged alphanumeri- A91-12460 •tt p69 N91-10074 tt p48 A91 -12766 » p11 A91-12463 •# p69 N91-10075 tt p48 cally by accession number. The page number listed A91-12767 tt A91-12464 tt p69 P" N91-10076 tt p48 to the right indicates the page on which the citation A91-12768 tt p11 A91-12466 # p69 N91-10077 p50 A91 -12769 tt p11 is located. An asterisk (") indicates that the item A91 -12467 tt p69 N91-10078 •it p50 A91-12770 •# is a NASA report. A pound sign (#) indicates that A91 -12468 tt p69 P" N91 -10079 'tt P50 A91-12771 # P11 A91 -12469 •tt p70 N91-10080 P52 the item is available on microfiche. A91 -12772 •tt P12 A91-12470 •tt p70 N91-10082 P52 A91 -12773 tt p12 A91-12471 # p70 N91-10083 '# P52 A91-12775 tt p59 A91 -12472 tt P7 N91-10084 tt p52 A91-12824 p59 A91-12473 •ft P? N91- 10086 tt P52 A91-12882 tt P12 A91-10114 tt P1 A91-11348 p46 A91-12475 •tt p70 N91-10139 tt P56 A91 -12886 tt P12 A91 -10245 p44 A91-11349 p46 A91-12476 tt p70 N91-10141 P56 A91-12887 tt p59 A91 -10329 tt P2 A91-11351 p46 A91-12477 •tt p70 N91-10168 tt p56 A91 -12888 tt p59 A91 -10330 tt P2 A91-12479 •tt p71 N91-10188 tt p56 A91-11353 p65 A91-12890 # 52 A91-10336 tt p57 A91-12480 it P71 P N91 -10232 # p59 A91-11701 tt P3 A91 -12894 '# p37 A91-10337 it P2 A91 -12482 •tt P71 N91 -10268 •tt p60 A91-11715 p36 A91-12896 tt P12 A91 -10339 • # p2 A91 -12483 tt P71 N91-10297 tt p60 A91-11723 tt P36 A91-12899 tt P12 A91 -10340 tt P2 A91 -12484 •# p71 N91-10298 tt p60 A91-11724 tt p36 A91-12900 tt p59 A91-10341 # p35 A91-12485 tt p71 N91-10301 •tt p60 A91-11725 tt p36 A91-12903 •# p12 A91-10345 tt p55 A91 -12486 'tt p72 N91 -10303 •ft p60 A91-11737 p54 A91-12904 tt p13 A91-10951 P1 A91-12488 tt p46 N91-10316 •tt p60 A91-11751 p55 A91-12911 p13 A91-10952 P1 A91 -12489 •tt P7 N91-10317 '# p60 A91-11752 tt p58 A91-12913 p13 A91-10953 ' P1 A91 -12490 tt P72 N91-10320 'tt p 61 A91-11755 tt p3 A91-12919 p37 A91-10954 p45 A91-12491 tt P72 N91-10321 •# p61 A91-11758 # p51 A91-12928 tt p50 A91 -10955 p49 A91-12492 tt p72 N91-10333 •# p 61 A91-11760 tt p51 A91-12929 tt p50 A91 -10956 p35 A91-12493 tt p72 N91-10335 •# p61 A91-11766 # p51 A91-10957 p36 A91-12495 •# P72 N91 -10548 •# p64 A91-11770 # p55 N91-10001 # A91 -10958 p45 A91-12496 •tt p73 P2 N91-10699 'tt p76 A91-11773 # p58 N91-10003 P13 A91-10959 p25 A91-12502 •tt p73 N91-10703 •# p76 A91-11776 it P55 N91-10006 p 13 A91 -10960 p26 A91-12504 '# p73 N91-10704 # p76 A91-11777 tt p4 N91-10007 •tt P13 A91-10961 • P1 A91-12505 '# p73 N91-10839 •tt p 16 A91-11779 tt p4 N91-10008 tt P13 A91 -10962 p77 A91-12506 tt P73 N91-10840 •tt p 16 A91-11782 tt p4 N91-10010 •tt p 14 A91 -10963 P77 A91-12507 tt p73 N91-10841 'tt p17 A91-11786 # p66 N91-10011 tt p14 A91 -10964 P1 A91-12509 •# p73 N91-10850 •it p17 A91-11806 p55 N91-10013 '# p 14 A91-10965 p45 A91-12512 '# p7 N91-10851 •tt P17 A91-11813 p58 N91-10014 •tt p 14 A91-10966 P55 A91-12513 •tt P7 N91 -10855 'tt P17 A91-11820 p50 N91-10015 •# p 14 A91-10967 p36 A91-12514 •tt P74 N91 -10856 •# P17 A91-11831 tt P4 N91-10016 # p 14 A91-10968 P45 A91-12515 •tt p74 N91-10857 •tt p 18 A91-11836 tt p4 N91-10018 tt p15 A91-10969 p45 A91-12516 it p74 N91-10858 •ft p 18 A91-11836 4 N91-10019 p15 A91-10970 p77 tt P A91-12517 tt p74 '# N91 -10859 •tt p 18 A91-11839 it P4 N91-10020 •tt P15 A91-10971 P2 A91-12519 tt p74 N91-10860 •ft p 18 A91-11840 tt p5 N91 -10022 •# P15 A91 -10972 p 54 A91 -12520 •it P74 N91-10861 •# p 18 A91-11841 It p5 N91-10023 tt P15 A91 -10973 P54 A91-12521 •tt P7 N91 -10862 •# p19 A91-11843 tt p5 N91-10024 tt p 16 A91 -10974 p54 A91 -12522 tt p74 N91-10863 •tt p19 A91-11844 tt p5 N91-10025 # p 16 A91 -10975 P45 A91 -12524 tt p46 N91-10864 •tt p19 A91-11845 tt p5 N91-10026 tt p 16 A91 -10976 p46 A91-12525 •It p75 N91 -10865 •tt P19 A91-11848 tt p5 N91-10027 # p 16 A91 -10977 • p54 A91 -12526 tt p75 N91-10866 •tt p19 A91-11863 tt p36 N91-10028 it p26 A91 -10978 p54 A91 -12528 •tt P75 N91-10867 •tt p20 A91-11883 p56 N91 -10029 tt p26 A91-11027 tt p57 A91-12530 tt p8 N91-10868 •tt p20 A91-11900 tt P5 N91 -10030 p28 A91-11072 tt p63 A91 -12533 •tt P75 N91 -10869 •tt p20 A91-11909 p5 N91-10031 p28 A91-11151 P2 A91 -12534 tt P75 N91 -10873 •tt p20 A91-11974 p58 N91-10032 tt p28 A91-11152 p57 A91-12535 tt p8 N9 1-1 0881 •tt p20 A91-12014 p6 N91-10033 it p29 A91-11154 p65 A91 -12536 •ft P52 N91 -10883 •tt P21 A91-12016 P6 N91 -10034 tt p29 A91-11155 p49 A91-12537 'tt p63 N91 -10886 •it P21 A91-12017 p6 N91-10038 p37 A91-11157 p2 A91-12538 tt p63 N91 -10887 •tt p21 A91-12018 p6 N91 -10039 •tt p37 A91-11158 p49 A91-12540 •tt p75 N91 -10888 •it p21 A91-12019 P6 N91-10040 •tt p38 A91-11159 p3 A91-12541 tt p63 N91 -10889 •ft P21 A91 -12020 p6 N91-10041 •# p38 A91-11160 P3 A91-12543 •tt P75 N9 1-10890 •tt p21 A91-12036 p58 N91 -10042 it p38 A91-11162 P3 A.91-12559 8 N91-10891 •tt p22 A91-12062 p36 P N91-10043 tt p38 A91-11198 • P3 A91-12575 p8 N9 1-10892 •ft P22 A91-12063 p37 N91-10044 tt p38 A91-11199 pS7 A91-12688 ' p58 N91 -10893 •tt p22 A91-12165 p37 N91-10045 •tt p38 A91-11201 57 A91-12690 •tt p8 N91 -10902 •tt P22 P A91 -12224 # P37 N91-10046 tt p39 N91-10904 p22 A91-11202 pS7 A91 -12226 tt P6 A91-12692 tt P8 N91-10047 •ft p39 •tt p23 A91-11219 p57 A91 -12233 tt p77 A91-12694 •tt P59 N91-10049 • tt p39 N9 1-10906 A91 -11347 p3 A91-12421 p58 A91-12695 •It p8 N91-10051 it p39 N91-10907 p23

G-1 N91-10908 ACCESSION NUMBER INDEX

N91- 10908 P23 N91-11107 tt p56 N91-10910 p23 N91-11128 # p56 N91-11140 p61 N91-10913 P23 N91-11174 p62 N91-10915 p24 N91-11197 # p62 N91-10916 p24 N91-11243 ft p62 N91-10918 p24 '# N91-11246 # p62 N91-10919 '# p24 N91-11247 '# p62 N91 -10920 P24 # N91-11248 # p63 N91-10921 p25 # N91-11266 # p63 N91 -10925 # p53 N91-11307 tt p64 N91-10926 # p25 N91-11416 # p65 N91-10927 # p48 N91-11424 tt p65 N91 -10928 tt p53 N91-11430 'ft p65 N91-10931 p78 # N91-11433 p66 N91 -10932 # p40 N91-11473 # p66 N91 -10933 •tt p25 N91-11488 •tt p76 N91 -10934 '# p25 N91-11493 '# p76 N91 -10936 •tt p26 N91-11494 '# P77 N9M0937 '# p40 N91 -11495 '# P77 N91-10938 •# p44 N91-10939 •# p40 N91-10941 •tt p26 N91-10942 •# p 44 N91 -10946 •# p26 N91 -10949 •# p40 N91 -10950 •# p 44 N91-10951 '# p26 N91 -10952 •# P27 N91 -10953 •# p27 N91 -10955 '# P27 N91 -10956 •# P27 N91 -10957 •# p29 N91 -10958 '# p29 N91 -10959 •# p29 N91 -10960 •# p64 N91-10961 '# p27 N91 -10962 •# p28 N91 -10963 # p28 N91 -10964 'tt p28 N91 -10965 # p28 N91 -10966 # P29 N91 -10967 # p29 N91-10968 •# p29 N91-10969 # P41 N91-10971 # P41 N91 -10972 # P41 N91 -10973 # P41 N91 -10974 # p41 N91 -10975 # p53 N91 -10976 # p41 N91 -10978 # p30 N91-10979 # p30 N91-10981 # p42 N91-10982 # p30 N91-10983 # p30 N91-10984 tt P42 N91 -10985 # p42 N91-10986 # p65 N91-10987 tt P42 N91 -10988 # P31 N91-10989 # p31 N91 -10990 tt p31 N91-10991 # p31 N91 -10992 # p32 N91 -10993 '# p32 N91-10994 '# p32 N91-10995 tt p32 N91-10996 '# p32 N91 -10997 # p33 N91 -10998 tt p33 N91 -10999 tt p33 N91-11000 'ft P33 N91-11001 # p34 N91 -11002 # p34 N91-11003 # p34 N91 -11004 tt p34 N91-11005 # p35 N91-11006 tt p64 N91-11007 tt p35 N91-11008 tt p35 N91-11009 p42

N91-11010 P43 N91-11011 p43 N91-11012 p43 N91-11013 p43 N91-11014 p43 N91-11015 tt p43 N91-11018 tt p48 N91-11019 # p49 N91-11022 # p49 N91-11023 p50

N91-11024 P51 N91-11025 # P51 N91-11026 it p53 N91-11027 •# P53 N91-11035 # p55

G-2 AVAILABILITY OF CITED PUBLICATIONS

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Schedule A STANDARD PRICE DOCUMENTS AND MICROFICHE-

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Schedule E EXCEPTION PRICE DOCUMENTS AND MICROFICHE-

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App-5 * U.S. GOVERNMENT PRINTING OFFICE:! 9 9 1 .527 -06 »/ 26020 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037(262) 4. Title and Subtitle 5. Report Date Aeronautical Engineering February 1991 A Continuing Bibliography (Supplement 262) 6. Performing Organization Code NTT 7. Author(s) 8. Performing Organization Report No.

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13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Special Publication National Aeronautics and Space Administration Washington, DC 20546 14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract This bibliography lists 474 reports, articles and other documents introduced into the NASA scientific and technical information system in January 1991.

17. Key Words (Suggested by Authors(s)) 18. Distribution Statement Aeronautical Engineering Unclassified - Unlimited Aeronautics Subject Category - 01 Bibliographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price * Unclassified Unclassified 146 A07/HC

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