NASA SP-7037 (245) November 1989 with Indexes
National Aeronautics and Space Adniinistration NASA SP-7037(245)
AERONAUTICAL ENGINEERING
A CONTINUING BIBLIOGRAPHY WITH INDEXES
(Supplement 245)
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in October 1989 in
Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA).
National Aeronautics and Space Administration Office of Management NASA Scientific and Technical Information Division Washington. DC 1989 This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A07. INTRODUCTION
This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 537 reports, journal articles and other documents originally announced in October 1989 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, 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 bibliography 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. The IAA items will precede the STAR items within each category. Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cumulative index will be published.
Information on the availability of cited publications including addresses of organizations and NTlS price schedules is located at the back of this bibliography.
iii TABLE OF CONTENTS
Page Category 01 Aeronautics (General) 637
Category 02 Aerodynamics 639 Includes aerodynamics of bodies, combinations, wings, rotors, and control sur- faces; and internal flow in ducts and turbomachinery.
Category 03 Air Transportation and Safety 657 Includes passenger and cargo air transport operations; and aircraft accidents.
Category 04 Aircraft Communications and Navigation 659 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 661 Includes aircraft simulation technology.
Category 06 Aircraft Instrumentation 673 Includes cockpit and cabin display devices; and flight instruments.
Category 07 Aircraft Propulsion and Power 674 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 686 Includes aircraft handling qualities; piloting; flight controls; and autopilots.
Category 09 Research and Support Facilities (Air) 691 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.
Category 10 Astronautics 694 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 695 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing. Category 12 Engineering 697 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 709 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; mankystem technology and life support; and space biology.
Category 15 Mathematical and Computer Sciences 710 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 71 2 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics: and ther- modynamics and statistical physics.
Category 17 Social Sciences 714 Includes social sciences (general); administration and management; documen- tation and information science; economics and cost analysis; law, political sci- ence, 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
vi TYPICAL REPORT CITATION AND ABSTRACT
NASASPONSORED ON MICROFICHE
ACCESSION NUMBER -N8%10029*# North Carolina State Univ., Raleigh. Dept. of -CORPORATE SOURCE MechanicalIr and Aerospace Engineering. TITLE -A TRANSONIC INTERACTIVE BOUNDARY-LAYER THEORY FOR LAMINAR AND TURBULENT FLOW OVER SWEPT WINGS Final Report AUTHORS-SHAWN H. WOODSON and FRED R. DEJARNETTE Washington Oct. 1988 82 p CONTRACT NUMBER-(Contract NCC1-22) PUBLICATION DATE REPORT NUMBERS-(NASA-CR-4185; NAS 1.26:4185) Avail: NTlS HC AOS/MF A01 -PRICE CODE COSATI CODE -CSCL 01 A AVAILABILITY SOURCE A 3-D laminar and turbulent boundary-layer method is developed for compressible flow over swept wings. The governing equations and curvature terms are derived in detail for a nonorthogonal, curvilinear coordinate system. Reynolds shear-stress terms are modeled by the Cebeci-Smith eddy-viscosity formulation. The governing equations are descretized using the second-order accurate, predictor-corrector finite-difference technique of Matsuno, which has the advantage that the crossflow difference formulas are formed independent of the sign of the crossflow velocity component. The method is coupled with a full potential wingbody inviscid code (FLO-30) and the inviscid-viscous interaction is performed by updating the original wing surface with the viscous displacement surface calculated by the boundary-layer code. The number of these global iterations ranged from five to twelve depending on Mach number, sweep angle, and angle of attack. Several test cases are computed by this method and the results are compared with another inviscid- viscous interaction method (TAWFIVE) and with experimental data. Author
TYPICAL JOURNAL ARTICLE CITATION AND ABSTRACT
NASASPONSORED I ON MICROFICHE
ACCESSION NUMBER -A89-12562'# National Aeronautics and Space Administration. Langley ReSearch Center, Hampton, Va. TITLE -EFFICIENT VIBRATION MODE ANALYSIS OF AIRCRAFT WITH MULTIPLE EXTERNAL STORE CONFIGURATIONS AUTHOR -M. KARPEL (NASA, Langley Research Center, Hampton, VA; Israel Aircraft Industries, Ltd., Lod) Journal of Aircraft (ISSN 0021 -8669),- JOURNAL TITLE vol. 25, Aug. 1988, p. 747-751. refs A coupling method for efficient vibration mode analysis of aircraft with multiple external store configurations is presented. A set of low- frequency vibration modes, including rigid-body modes, represent the aircraft. Each external store is represented by its vibration modes with clamped boundary conditions, and by its rigid-body inertial properties. The aircraft modes are obtained from a finite-element model loaded by dummy rigid external stores with fictitious masses. The coupling procedure unloads the dummy stores and loads the actual stores instead. The analytical development is presented, the effects of the fictitious mass magnitudes are discussed, and a numerical example is given for a combat aircraft with external wing stores. Comparison with vibration modes obtained by a direct (full- size) eigensolution shows very accurate coupling results. Once the aircraft and stores data bases are constructed, the computer time for analyzing any external store configuration is two to three orders of magnitude less than that of a direct solution. Author
vii I AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 245)
NOVEMBER 1989
01 support planning and implementation. Experiences gained with ESM during the introduction of complex aircraft weapons systems are AERONAUTICS (GENERAL) also reviewed. C.D. A0945032 AEROSPATIALE’S SHORT-TERM AND INTERMEDIATE-TERM PLACE IN THE INTERNATIONAL SCENE [PLACE D’AEROSPATIALE DANS LE CONTEXTE INTERNATIONAL A A09-44641# COURT ET MOYEN TERMES] JET OR PROP REQUIRED FOR FUTURE REGIONAL HENRl MARTRE (Aerospatiale, Paris, France) L’Aeronautique et TRANSPORTS? I’Astronautique (ISSN 0001-9275), no. 136-137, 1989, p. 5-8. In JOSEPH SIMMERL Dornier Post (ISSN 0012-5563), no. 2, 1989, French. p. 24, 25. ’ Aerospatiale’s present and future place in the European and This article discusses the question whether a jet propulsion or world-wide aeronautics industry is discussed. Cooperative prop propulsion system is more advantageous for a new generation FrenchIEuropean ventures include Concorde, Ariane, Airbus, ATR, of commuter aircraft. The issues addressed include comfort, safety, the FrenchIBritish helicopters Gazelle, Lynx, and Puma, and the pollution, flexibility in the ATC environment, range, speed, and French/German Hot, Milan, and Roland missiles. Special attention direct operating cost. The outlook for the commuter airline industry is given to the impact on the aeronautics industry of the conflicting on this issue is considered. C.D. European tendencies toward nationalization and international cooperation. The changing roles of the European countries in the A09-44642# production of military aircraft and missiles is discussed in detail. TECHNOLOGY OF STRUCTURES MAINTAINS HIGH R.R. STANDARDS HERBERT KELLER, KARL FRIEDRICH SAHM, and A0945033 HANS-WOLFGANG SCHROEDER Dornier Post (ISSN DASSAULT, LEADER IN EUROPEAN MILITARY AND 0012-5563), no. 2, 1989, p. 44-48. BUSINESS AIRCRAFT [DASSAULT, LEADER DES AVIONS Materials for new aircraft structure technologies are discussed. D’AAMES ET DES AVIONS D’AFFAIRS EN EUROPE] Aluminum-lithium alloys and superplastic forming and diffusion SERGE DASSAULT (Avions Marcel Dassault Breguet Aviation, S.A., bonding technologies are described and their aircraft structure Vaucresson, France) L‘Aeronautique et I’Astronautique (ISSN applications are examined. Advanced materials for corrosion and 0001-9275), no. 136-137, 1989, p. 9-11. In French. surface protection and metals for use at high temperatures are France’s place in the international aeronautics industry in the considered. The use of fiber-compound structures is discussed, past, present, and future is discussed. French contributions to the and the use of nonmetals for extreme temperatures is addressed. industry include the achievement of vertical take-off and prolonged Multifunctional structures are discussed. C.D. Mach 2 flight, along with the development of variable-geometry vehicles, the ramjet engine, and the STS. Also considered are A09-44643# the Mirage 2000, Falcon 20, Falcon 50, Falcon 900, Rafale, and DORNIER’S ROLE IN THE ’EUROPEAN FIGHTER AIRCRAFT’ ATF aircraft. R.R. EFA PROGRAM Dornier Post (ISSN 0012-5563), no. 2, 1989, p. 49-52. A8945034 This paper describes the required performances and system THE SNECMA GROUP TODAY AND TOMORROW [LE capabilities of the European Fighter Aircraft (EFA) which is to GROUPE SNECMA AUJOURDHUI ET DEMAIN] fulfill the harmonized requirements of the air forces of the German BERNARD CAPILLON (SNECMA, Paris, France) L‘Aeronautique Federal Republic, Great Britain, Italy, and Spain, as expressed in et I’Astronautique (ISSN 0001-9275), no. 136-137, 1989, p. 12-14. the joint document ’the European Staff Requirements’. The In French. industrial arrangements that have been made to develop the EFA Marketing aspects and characteristics of three French are summarized, and Dornier’s participation in that development aerospace technologies are discussed: (1) the M88 engine, is addressed. In particular, management and technical development developed for Rafale; (2) the CFM56, developed for civil aircraft; aspects are considered. C.D. and (3) Ariane 5. The Ariane 5 vehicle, to be used for Hermes, delivers 600 tons of thrust with its two solid-propellant boosters A09-44644# and 10 tens of thrust with its central cryogenic engine. THE PHASED ESTABLISHMENT OF SUPPORT MATURITY French/American cooperation on such ventures as the CF6 engine FOR THE EUROPEAN FIGHTER AIRCRAFT (EFA) and the development of a propfan is considered. R.R. JUERGEN KRAWCZAK Dornier Post (ISSN 0012-5563), no. 2, 1989, p. 53-57. A0945035 A conceptual approach for a phased establishment of support FROM AVIONICS TECHNOLOGY TO ARCHITECTURAL maturity (ESM) for the European Fighter Aircraft is outlined. CONCEPTS [DE LA TECHNOLOGIE AUX CONCEPTS Packages of phased support options, on-call ordering of single ARCHITECTURAUX DE L‘AVIONIQUE] interim support measures, and phased support management are ANDRE DERRE L‘Aeronautique et I’Astronautique (ISSN discussed. Risk assessment and prognosis for full support maturity 0001-9275), no. 136-137, 1989, p. 15-18. In French. or phased support is shown along with an example of phased The impact of recent digital electronic technological innovations
637 01 AERONAUTICS (GENERAL)
on aircraft systems is discussed, with emphasis on the development A89-47326 of integrated avionics systems for navigation, weapons control, AEROSPACE BEHAVIORALTECHNOLOGYCONFERENCE and engine control. It is noted that the use of high-reliability AND EXPOSITION, TTH, ANAHEIM, CA, OCT. 3-6, 1988, high-flexibility VHSlCs will overcome many of the problems PROCEEDINGS encountered in present integrated systems. Also considered are Conference and Exposition sponsored by SAE. Warrendale, PA, the contributions of optoelectronics technologies (notably IR Society of Automotive Engineers, Inc. (SAE P-216), 1989, 183 p. imaging) and composite and ceramic materials (including For individual items see A89-47327 to A89-47342. carbon-carbon composites) to avionics architectures. R.R. (SAE P-216) Topics discussed in these proceedings include those on the A89-45037 cockpit, space, workload, crew awareness, air transport system AERONAUTICAL RESEARCH IN THE EUROPEAN FUTURE [LA automation, fitness for duty, concerns of the international pilots, RECHERCHE AERONAUTIQUE A L'HEURE EUROPEENNE] training technologies, and graphic tools for cockpit design. Papers PH. POISSON-QUINTON L'Aeronautique et I'Astronautique (ISSN are presented on display requirements for a threat response 0001-9275), no. 136-137, 1989, p. 28-41. In French. system; flight crew displays for Space Station proximity operations; The joint study of European Cooperative Measures for EVA design integration for Space Station assembly; an assessment Aeronautical Research and Technology is discussed, covering such of crew workload procedures in full fidelity; the definition, topics as the present European role in international aerospace measurement, and enhancement of the situational awareness in research, the market potential for the next 25 years, and the the commercial flight deck; and current and future trends in advancement of European competitivity through the development automation in transport aircraft. Attention is also given to the design of key (primarily civil) aircraft technologies. Emphasis is placed on of crew rest quarters, airline operations and the contaminated the need for standardization in such areas of development as runway, the role of flight planning in aircrew decision performance, new materials, fabrication technologies, aerodynamics, acoustics, requirements for rapid prototyping of crew station displays, and avionics systems, and integrated propulsion systems. R.R. human factors engineering workstation for model-based cockpit design. I.S. A89-45143 AIRCRAFT DEVELOPMENT TEST AND EVALUATION - AN N89-25113# Federal Aviation Administration, Washington, DC. OFFICE OF THE SECRETARY OF DEFENSE PERSPECTIVE Office of Management Systems. CHARLES E. ADOLPH (DOD, Washington, DC) IN: Society of FAA STATISTICAL HANDBOOK OF AVIATION: CALENDAR Flight Test Engineers, Annual Symposium, 19th, Arlington, TX, Aug. YEAR 1987 14-18, 1988, Proceedings. Lancaster, CA, Society of Flight Test 1987 212 p Engineers, 1988. p. VI-1.1 to VI-1.4. (AD-A200917) Avail: NTlS HC AlO/MF A01 CSCL 01/3 The development of aircraft test and evaluation programs over Statistical information is presented pertaining to the Federal the last two decades is reviewed. Aircraft flight test emphasis has Aviation Administration, the National Airspace System, Airports, recently shifted from airworthiness and aerodynamics testing to Airport Activity, US. Civil Air Carrier Fleet, U.S. Civil Air Carrier avionics subsystem test and integration. Technical problems Operating Data, Airmen, General Aviation Aircraft, Aircraft involved with the integration of aircraft systems and test programs Accidents, Aeronautical Production and Imports/Exports. A are considered. The impact of advances in weapon systems Glossary of the terms used in this publication is contained. GRA technology on the aircraft test process is examined. The importance of simulators and other hardware-in-the-loop ground test facilities N89-25948# Federal Aviation Administration, Washington, DC. for the evaluation of software-intensive systems is emphasized. Office of Aviation Policy and Plans. R.R. FAA (FEDERAL AVIATION ADMINISTRATION) AVIATION FORECASTS FISCAL YEARS 1989-2000 AW-46078 Mar. 1989 252 p THE EEC SUPPORTS AIR TRANSPORT RESEARCH [EG (AD-A206716; FAA-APO-89-1) Avail: NTlS HC Al2/MF A01 FOERDERT LUFTFAHRTFORSCHUNG] CSCL 0112 STEPHAN VON WELCK Luft- und Raumfahrt (ISSN 0173-6264), This report contains forecasts of aviation activity at FAA vol. 10, 2nd Quarter, 1989, p. 28-30. In German. facilities. These include airports with FAA control towers, air route The report of the Ministry for European Community on the air traffic control centers, and flight service stations. Detailed forecasts transport industry is discussed. The preparations surrounding the were made for the four major users of the NAtional Aviation System: study which led to the report are reviewed, and the proposals air carriers, air taxi/commuters, general aviation and the military. made by the report are critically examined. The essential elements The forecasts were prepared to meet the budget and planning of the research program proposed by the report are summarized, needs of the constituent units of the FAA and to provide information and the requirements which need to be met to carry out the that can be used by state and local authorities, by the aviation program are discussed. C.D. industry, and by the general public. The overall outlook for the forecast period is for continued economic growth, rising real fuel A89-46496 prices, and moderate inflation. Based upon these assumptions, HORNET MAINTENANCE aviation activity by fiscal year 2000 is forecast to increase by HERBERT A. CHASE (McDonnell Aircraft Co., Saint Louis, MO) 31.0 percent at towered airports (commuters, 51.8 percent; air IN: Annual Reliability and Maintainability Symposium, Atlanta, GA, carriers, 34.6 percent; general aviation, 27.5 percent; military, 0.0 Jan. 24-26, 1989, Proceedings. New York, Institute of Electrical percent), 32.0 percent at air route traffic control centers and Electronics Engineers, Inc., 1989, p. 405-408. refs (commuters, 55.2 percent; air carriers, 33.7 percent; general A step toward life-cycle-cost reduction was the introduction of aviation, 30.0 percent military, 0.0 percent, and 7.8 percent in a Flight Incident Recording and Aircraft Monitoring Set (FIRAMS) flight services performed. Hours flown by general aviation are in the F/A-18 Hornet. FIRAMS provides onboard nonvolatile forecast to increase 14.9 percent and helicopter hours flown, 82.6 storage of operational flight information and maintenance percent. Scheduled domestic revenue passenger miles (RPM's) parameters. It also integrates fuel and engine displays and performs are forecast to increase 73.6 percent, with scheduled international the fuel gaging and transfer functions. FIRAMS also promotes the RPM's forecast to increase by 104.9 percent; and regionals/ concept of using onboard computers for air vehicle system commuters RPM's forecast to increase by 158.7 percent. GRA management. This concept was implemented into a large portion of the F/A-l8C/D fuel system. The FIRAMS subsystem uses a complex correlation of data for fuel control. Future applications of N89-25949# Logistics Management Inst., Bethesda. MD. the experience gained in the FIRAMS program include onboard AIRCRAFT SUSTAINABILITY MODEL VERSION 1.5: USERS fault detection and fault isolation. I.E. MANUAL
638 02 AERODYNAMICS
FRANK L. EICHORN Mar. 1989 45 p (ISSN 0748-4658), vol. 5, July-Aug. 1989, p. 457-468. Research (Contract MDA903-85-C-0139) supported by United Technologies Corp. Previously cited in issue (AD-A207015; LMI-AF801R2) Avail: NTlS HC A03/MF A01 20, p. 2917, Accession no. A86-42822. refs CSCL 15/5 (Contract NO0014-84-C-0354) The Aircraft Sustainability Model (ASM) is an item-specific inventory model that relates investments for spares to aircraft sortie A89-44114# generation capability during a conflict. An important advantage of TRANSONIC CASCADE FLOW SOLVED BY THE COMBINED the ASM is its ability to produce an entire curve relating a wide SHOCK-CAPTURING AND SHOCK-FITTING METHOD range of investment levels to the resulting sortie generation JIANZHONG XU and WENYAN NI (Chinese Academy of Sciences, capability, allowing Air Force planners to trade off spares Institute of Engineering Thermophysics, Beijing, People’s Republic investment and capability. Moreover, the algorithm that builds the of China) Journal of Propulsion and Power (ISSN 0748-4658), curve explicitly trades off investment in line replaceable units vol. 5, July-Aug. 1989, p. 476-481. Previously cited in issue 18, p. installed directly on aircraft versus their constituent shop 2804. Accession no. A87-42333. refs replaceable unit subassemblies. These features, together with the computational efficiency of the code, have led to rapid acceptance of the ASM within the Air Force Logistics Command (AFLC). AFLC A89-44116# is now incorporating the ASM into the Requirements Execution HYPERSONIC VEHICLE PROPULSION - A COMPUTATIONAL Availability Logistics Module (REALM) of the Weapon System FLUID DYNAMICS APPLICATION CASE STUDY Management Information System (WSMIS). The ASM is being used THOMAS J. BARBER (United Technologies Research Center, East in WSMWREALM to compute item requirements and to execute Hartford, CT) and G. B. COX, JR. (United Technologies Corp.. the Air Force budget for the reparable spares portion of War Pratt and Whitney Group, West Palm Beach, FL) Journal of Reserve Materiel (WRM). This users manual explains the use of Propulsion and Power (ISSN 0748-4658), vol. 5, July-Aug. 1989, the PC-version of the ASM, Version 1.5. GRA p. 492-501. Research supported by United Technologies Corp. and USAF. Previously cited in issue 07, p. 936, Accession no. A88-22350. refs 02 A89-44319# SOLUTION OF EULER EQUATIONS BY A FINITE ELEMENT AERODYNAMICS METHOD APPLICATION TO SUPERSONIC FLOWS DANIEL KALFON and DOMINIQUE VOLPERT (ONERA, Centre Includes aerodynamics of bodies, combinations, wings, rotors, and d’Etudes et de Recherches de Toulouse, France) La Recherche control surfaces; and internal flow in ducts and turbomachinery. Aerospatiale (English Edition) (ISSN 0379-380X), no. 6, 1988, p. 1-11. Research supported by CEA. refs An attempt was made to obtain a finite element code capable A8943722 of computing complex flows around axisymmetrical bodies. The THE MIXING OF THREE-DIMENSIONAL TURBULENT WAKES results reveal that Galerkin’s continuous method with adaptive IN BOUNDARY LAYERS meshes is very promising. The stiff shocks are captured without A. MOGHADAM and L. C. SQUIRE (Cambridge, University, oscillation and the computation times per iteration are acceptable. England) Aeronautical Journal (ISSN 0001-9240), vol. 93, May K.K. 1989, p. 153-161. refs The three-dimensional aspects of the wake/boundary layer A89-44322# interaction (particularly, slat-wake/wing boundary layer interaction) GENERALIZATION OF THE ROE SCHEME FOR COMPUTING are investigated with reference to measurements of mean velocity FLOWS OF MIXED GASES WITH VARIABLE and Reynolds stress tensor components obtained by using a CONCENTRATIONS specially developed digital system with a triple-wire hot probe. An REMI ABGRALL (ONERA, Chatillon-sous-Bagneux, France) La important finding of the study is the rapid decay of the crossflow Recherche Aerospatiale (English Edition) (ISSN 0379-38OX). no. downstream of the trailing edge. For nominally two-dimensional 6, 1988, p. 31-43. refs and quasi-three-dimensionalflows, comparisons are made between A generalization of the Roe scheme is presented for computing experimental results and theoretical predictions using the flows by solution of the Euler equations, in the case of a mixture two-dimensional form of the K-epsilon model and algebraic stress of inviscid gases having spatially variable concentrations. The models of turbulence. Tests on an isolated wake are also mixture is taken to be an ideal gas, but with variable specific reported. V.L. heats. The problem of automatically capturing the contact surfaces between two nonreactive ideal gases with different specific heat A8943724 ratios is considered. The method is tested on the Riemann problem LOPAN - A LOW-ORDER PANEL METHOD FOR SUBSONIC and an application to a jet problem is presented. Author AND SUPERSONIC FLOWS T. D. RUBIN (Israel Aircraft Industries, Ltd., Lod) Aeronautical Journal (ISSN 0001 -9240), vol. 93, May 1989, p. 177-182. refs A8944390 LOPAN, a low-order panel method for calculating subsonic or INVISCID TRANSONIC FLOW OVER A WAVY WALL supersonic linear flow about general configurations, is presented. DECAYING DOWNSTREAM In common with other internal Dirichlet methods, LOPAN allows JEONG-JOO PARK and KEUN-SHIK CHANG (Korea Advanced for a condition on the outward conormal component of the flow Institute of Science and Technology, Seoul, Republic of Korea) velocity. LOPAN makes it possible to implement, during the same Communications in Applied Numerical Methods (ISSN 0748-8025), computer run, either the conormal or the normal condition without vol. 5, May 1989, p. 219-228. refs the need for an expanded matrix. This is achieved using a simple Inviscid transonic flow over a wavy wall with either subsonic iterative procedure which should be easily applicable to any code or supersonic freestream speeds is studied by solving the Euler using the internal Dirichlet formulation. V.L. equations numerically. The streamwise flow development through a series of shock waves and entropy production are investigated A89441 12# in depth. In the case of supersonic freestream, isentropy contours MULTI-STAGE COMPRESSOR AIRFOIL AERODYNAMICS. I - of both horseshoe and staircase forms are found. The limitations AIRFOIL POTENTIAL FLOW ANALYSIS and validity of this inviscid rotational flow model are discussed by H. D. JOSLYN and R. P. DRlNG (United Technologies Research comparing the results with those for viscous turbulent flow Center, East Hartford, CT) Journal of Propulsion and Power calculated previously. Author
639 02 AERODYNAMICS
AW-44637 which provides secondary flow predictions along flow-path walls PREDICTION OF THE STABILITY LIMIT OF MULTISTAGE of axial compressors. This model has been validated with detailed AXIAL COMPRESSORS [PREDICTION DE LA LlMlTE DE measurements of experimental compressors and used to design STABlLlTE DES COMPRESSEURS AXIAUX MULTI-ETAGES] blade rows with ends adapted to the actual flow. The high pressure P. GILLANT (Societe Bertin et Cie., Plaisir, France) Revue compressor for the THR/GE 36 engine includes such a design Francaise de Mecanique (ISSN 0373-6601), no. 4, 1988, p. 47-53. for stators, and test results have confirmed the advantages of In French. this technique. Author (Contract DRET-80-098; DRET-82-096; DRET-84-307) The calculation method presented intends to predict the stability limit of a multistage axial compresor, starting from the knowledge ~89-44898 of its complete geometry and from the aerodynamical CALCULATIONOFTHETOTALPRESSURE LOSS characteristics of the blading of each stage. The stability of the COEFFICIENT WITH THREE MODELS FOR FOUR flow is studied on each stream surface by applying the Liapunov SUPERSONIC AXIAL-FLOW COMPRESSORS [ BERECHNUNG theory to the partial differential equations system established from DES TOTALDRUCK-VERLUSTKOEFFIZIENTEN MIT DREl the continuity, momentum, and energy unsteady equations and MODELLEN FUER VIER TRANSSCHALL-AXIALVERDICHTER] linearized around the steady state running point under HORST STOFF and RENE WAELCHLI (Asea Brown Boveri AG. consideration. Satisfactory results are obtained and the short Baden, Switzerland) Forschung im lngenieurwesen (ISSN calculation delay involved in the numerical model allows thorough 0015-7899), vol. 55. May 1989, p. 77-79. In German. refs parametrical studies to be performed during the early phase of Three semiempirical numerical models are evaluated in Author development of new jet engines. computations of the total pressure loss in four commercial axial-flow compressors. The theoretical bases of the models are briefly A8944638 reviewed, and the results are compared with measurement data PREDICTION OF TURBOMACHINERY PERFORMANCE - in graphs. Best agreement is obtained with the simplest of the APPLICATION TO A CENTRIFUGAL PUMP, A CENTRIFUGAL models applied, the subsonic model of Messenger and Kennedy COMPRESSOR, AND A RADIAL INFLOW TURBINE (1972); it is pointed out, however, that the more elaborate model [PREVISION DES CARACTERISTIQUES DES of Strinning and Dunker (1977) permits selective variation of the TURBOMACHINES - APPLICATION A UNE POMPE design parameters to achieve an optimum configuration. T.K. CENTRIFUGE, UN COMPRESSEUR CENTRIFUGE ET UNE TURBINE CENTRIPETE] M. FRIBERG, M. MAHIEDDINE, M. TOUSSAINT, and M. FRELIN (Conservatoire National des Arts et Metiers, Paris, France) Revue ~a9-44972# Francaise de Mecanique (ISSN 0373-6601),no. 4, 1988, p. 55-66. EXPERIMENTAL STUDY ON AERODYNAMIC In French. CHARACTERISTICS OF HYPERSONIC TRANSPORT A simple method for pump and compressor performance CONFIGURATION evaluation is presented. This method only requires a knowledge NORIKAZU SUDANI. SHlGEAKl NOMURA, KOlCHl HOZUMI. of the geometry of the machine. The pressurelmass flow AKlRA MURAKAMI, and YASUHIKO AIHARA Japan Society for characteristic and the efficiency are computed. The torque is Aeronautical and Space Sciences, Journal (ISSN 0021 -4663), vol. derived by using Euler’s equation. Losses taken into account are 37, no. 423, 1989, p. 178-185. In Japanese, with abstract in due to friction, flow separation, off design angles of attack, and English. refs leakage between rotor and stator. In the case of a radial turbine, An experimental study has been carried out on aerodynamics operated at high temperature, evaluation of the performance can of a cruising type hypersonic transport (HST) configuration, be deduced from measurements obtained during cold flow assuming to cruise at a height of 30 km at Mach number 7. The operation. Author hypersonic flow over the double-delta wing, which is a basic wing shape of HST, has been investigated. The results of the flow AW-44639 visualization and the quantitative measurements (static pressure THEORETICAL AND EXPERIMENTAL STUDY OF TURBINE and heat transfer) show that the vortices of the leeward side of AERODYNAMICS [ETUDE THEORIQUE ET EXPERIMENTALE the double-delta wing influence aerodynamic forces, and that they DE L‘AERODYNAMIQUE DES TURBINES] are associated with the intense local heating along the center P. BRY (SNECMA. Moissy-Cramayel, France) Revue Francaise line. From the wind tunnel test of the HST model at Mach number de Mecanique (ISSN 0373-6601), no. 4, 1988, p. 67-80. In 7. it is confirmed that the geometry of the model almost satisfies French. refs the requirements of aerodynamic characteristics under hypersonic Theoretical and experimental techniques employed in the design cruising. In parallel with the experiments, a basic study on of jet engine turbines are reviewed. Optimization of the shape aerothermodynamic control of the performance has been of the inner and outer casings is performed analytically. Tur- performed. The results show that the static pressure rises with bomachinery design is based upon flow calculations which take heat addition to the stream beneath the afterbody of the HST, into account the radial variations of losses and angular momentum. and suggest possibility of improving lift-to-drag ratio. Author Blade profiles are developed using an iterative procedure based upon inverse and direct two-dimensional and three-dimensional calculation codes for subsonic, transonic, or supersonic flows. AW-45045 These design methods also include boundary layer calculations. HELICOPTER BLADES [LES PALES D’HELICOPTERE] Experimental techniques are used to validate the predicted turbine RENE MOUILLE (Aerospatiale, Division Helicopteres, Marignane, performance characteristics and to calibrate the various theoretical France) L‘Aeronautique et I’Astronautique (ISSN 0001 -9275), methods. R.R. no. 136-137, 1989, p. 109-115. In French. The aerodynamics, optimization, and fabrication of helicopter AW-44640 blades are reviewed. It is noted that the efficiency in steady flight, DESIGN OF VANE TIPS IMPROVING AXIAL COMPRESSOR as indicated by figures of merit, for modern helicoptor rotors (such PERFORMANCE [DESSIN D’EXTREMITES DAUBES as the AS 365 N and the AS 332) has approached 0.80, and that AMELIORANT LES PERFORMANCES DES COMPRESSEURS power requirements have been reduced by close to 20 percent AXIAUX] over the past 30 years. The use of composite materials has MARIUS GOUTINES (SNECMA, Moissy-Cramayel, France) Revue permitted the optimization of blade aerodynamics, along with the Francaise de Mecanique (ISSN 0373-6601). no. 4, 1988, p. 109, minimization of blade vibration. Flight load estimations are used 110. In French. to calculate the static and dynamic stresses in order to determine Since several years SNECMA has developed a numerical model the operating life of the blades. R.R.
640 02 AERODYNAMICS
A89-45187# A89-45359 A NEW VARIATIONAL METHOD FOR THE GENERATION OF A FLOW-FIELD SOLVER USING OVERLYING AND EMBEDDED TWO- AND THREE-DIMENSIONAL ADAPTED GRIDS IN MESHES TOGETHER WITH A NOVEL COMPACT EULER COMPUTATIONAL FLUID DYNAMICS ALGORITHM OLIVIER-PIERRE JACQUOTTE and JEAN CABELLO (ONERA, C. M. ALBONE and GAYNOR JOYCE (Royal Aerospace Chatillon-sous-Bagneux, France) (International Conference on Establishment, Farnborough, England) IN: International Finite Element Method in Flow Problems, 7th, Huntsville, AL, Apr. Conference on Numerical Methods in Fluid Dynamics, 11th, 3-7, 1989) ONERA, TP no. 1989-31, 1989, 7 p. refs Williamsburg, VA, June 27July 1, 1988, Proceedings. Berlin and (ONERA, TP NO. 1989-31) New York, Springer-Verlag, 1989, p. 106-110. refs A variational method for the optimization and adaptation of Two-dimensional flow problems involving complex multielement structured grids is presented. This method is applicable to two- or airfoils are solved numerically using a novel mesh-generation three-dimensional structured mesh as well as to surface mesh. It procedure and the explicit split-coefficient-matrix upwind Euler relies upon the introduction of a proper measure of a cell algorithm of Chakravarthy et al. (1980). The discretization combines deformation that is derived form basic principles of continuum a Cartesian main mesh (density controlled by embedding) with mechanics. Several properties are prescribed, which guarantee curvilinear meshes aligned with configuration or flow features; the well-posedness of the mesh optimization problem and the information is exchanged between the two meshes to establish efficiency of the solution algorithm. The ability of the method for the boundary conditions. Results for a three-element airfoil at Mach the mesh adaptation is also described. Examples of two- and 0.2 and angle of attack 20 deg are presented in graphs and three-dimensional grids are shown and illustrate the success of briefly discussed. T.K. the presented method. Author A89-45360 A89-45260*# Vigyan Research Associates, Inc., Hampton, VA. MULTIDIMENSIONAL ADAPTIVE EULER SOLVER STUDIES OF VORTEX FLOW AERODYNAMICS USING CFD RENZO ARlNA (CNR, Centro di Studio sulla Dinamica dei Fluidi, FLOW VISUALIZATIONS Turin, Italy), BERNARD0 FAVlNl (Roma I, Universita, Rome, Italy), GH. HSU, P.-M. HARTWICH (Vigyan Research Associates, Inc., and LUCA ZANNEll-I (Torino, Politecnico, Turin, Italy) IN: Hampton, VA), and C. H. LIU (NASA, Langley Research Center, International Conference on Numerical Methods in Fluid Dynamics, Hampton, VA) Asian Congress of Fluid Mechanics, 4th, Hong 11 th, Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin Kong, Aug. 21-25, 1989, Paper. 5 p. refs and New York, Springer-Verlag, 1989, p. 111-1 15. refs Navier-Stokes computations of three-dimensional vortical flows The fundamental principles of the Euler solver proposed by over a round-edgeddouble-delta wing and a tangent-ogive forebody Favini and Zannetti (1987) are summarized and illustrated with are performed using an implicit upwind finite-difference scheme. sample results. The shock-capture method combines Lambda and Computed particle traces are compared with experimental oil-flow flux-vector splitting, and the adaptive-grid-generationmethod is that streaks. Author of Arina (1988). Results for regular shock reflection at a wall and supersonic flow past a circular cylinder are presented graphically and briefly characterized. It is shown that the grid adaptation affects A89-45262'# High Technology Corp., Hampton, VA. the ability of the upwind scheme to model the flowfield. T.K. WIND-TUNNEL INVESTIGATIONS OF WINGS WITH SERRATED SHARP TRAILING EDGES A89-45363 P. M. H. W. VIJGEN (High Technology Corp., Hampton, VA), C. NUMERICAL STUDY OF THE 3D SEPARATING FLOW ABOUT P. VAN DAM (California, University, Davis), B. J. HOLMES, and F. OBSTACLES WITH SHARP CORNERS G. HOWARD (NASA, Langley Research Center, Hampton, VA) NOBUHIRO BABA and HlDEAKl MIYATA (Tokyo, University, Conference on Low-Reynolds Number Aerodynamics, University Japan) IN: International Conference on Numerical Methods in of Notre Dame, IN, June 5-7, 1989, Paper. 20 p. refs Fluid Dynamics, llth, Williamsburg, VA, June 27-July 1, 1988, (Contract NAG1-345; NAS1-18240) Proceedings. Berlin and New York, Springer-Verlag, 1989, p. Exploratory wind-tunnel force measurements are presented for 126-130. refs two wing geometries with small-scale planar and nonplanar serrated The formation and evolution of vortices in incompressible flows trailing-edge devices (chord-Reynolds numbers ranged from 1.O around structures with sharp corners are investigated by means to 3.7 million). The planar serrated trailing-edge extensions reduced of numerical simulations based on the finite-difference the drag at conditions when trailing-edge separation occurred at Navier-Stokes solver of Baba and Miyata (1987). The treatment low angles of attack. The introduction of serrations reduced or of flow over a double step and over a rectangular cylinder is eliminated the drag penalty, due to the small (1-2 percent of the outlined, and the numerical results are presented graphically and chord length) nonplanar trailing-edge flaps, while maintaining the compared with experimental flow visualizations. It is shown that effects of increase in camber. The presence of streamwise vortices counterrotating streamwise vortices are superimposed on the immediately downstream of the serrated trailing edges is believed spanwise-organized vortical structure and affect the transition to to have favorably affected the boundary-layer flow approaching turbulence. Also discussed are the significant effects of numerical the trailing edge and the near-wake development, resulting in errors arising from the nonlinear terms; a rotational formulation reduced pressure (form) drag. Author with kinetic-energy and momentum conservation is found to be most robust in this regard. T.K. A89-45355' National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. A89-45366* Scientific Research Associates, Inc., Glastonbury, CFD FOR HYPERSONIC AIRBREATHING AIRCRAFT CT. AJAY KUMAR (NASA, Langley Research Center, Hampton, VA) SOLUTION OF THE INCOMPRESSIBLE NAVIER-STOKES IN: International Conference on Numerical Methods in Fluid EQUATIONS USING ARTIFICIAL COMPRESSIBILITY Dynamics, 11th, Williamsburg, VA, June 27-July 1, 1988, METHODS Proceedings. Berlin and New York, Springer-Verlag, 1989, p. W. R. BRILEY, R. C. BUGGELN, and H. MCDONALD (Scientific 40-56. refs Research Associates, Inc., Glastonbury, CT) IN: International A general discussion is given on the use of advanced Conference on Numerical Methods in Fluid Dynamics, 11th, computational fluid dynamics (CFD) in analyzing the hypersonic Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and flow field around an airbreathing aircraft. Unique features of the New York, Springer-Verlag, 1989, p. 156-160. Research supported hypersonic flow physics are presented and an assessment is given by NASA. refs of the current algorithms in terms of their capability to model A modified artificial compressibility formulation is derived from hypersonic flows. Several examples of advanced CFD applications a preconditioned low Mach number compressible formulation, and are then presented. Author these two methods are compared on a two-dimensional laminar
64 1 02 AERODYNAMICS leading edge flow using a LBIIADI solution algorithm. The two A 89- 4 53 7 4 methods are essentially equivalent with appropriate preconditioning AN IMPLICIT TIME-MARCHING METHOD FOR SOLVING THE parameters and have the same convergence rates and efficiency, 3-D COMPRESSIBLE NAVIER-STOKES EQUATIONS giving 4 orders of residual reduction in about 75 iterations with a HlSAAKl DAlGUJl and SATORU YAMAMOTO (Tohoku University, vectorized CRAY-XMP run time of 20 seconds for 3000 grid Sendai, Japan) IN: International Conference on Numerical points. Author Methods in Fluid Dynamics, 11 th, Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and New York, Springer-Verlag, 1989, p. 210-214. refs A89-45368 The implicit time-marching finite-difference method developed COMPUTATION OF HYPERSONIC VORTEX FLOWS WITH AN by Daiguji et al. (1986) for the Euler equations of steady EULER MODEL three-dimensional compressible flow is extended to solve the CHARLES-HENRI BRUNEAU, JACQUES LAMlNlE (Paris XI, Navier-Stokes equations, with diffusion terms accounted for. The Universite, Orsay, France), and JEAN-JACQUES CHA’ITOT derivation for the case of relative flow through the impeller of a (Aerospatiale, Les Mureaux, France) IN: International Conference turbomachine in general curvilinear coordinates is outlined, and on Numerical Methods in Fluid Dynamics, 11th, Williamsburg, VA, results for two-dimensional and three-dimensional cascade flows June 27-July 1, 1988, Proceedings. Berlin and New York, are presented in graphs and briefly characterized. It is shown that Springer-Verlag. 1989, p. 177-181. Research supported by DRET the important features of the flows are captured despite the use and Ecole Polytechnique. refs of relatively coarse grids. T.K. A least-squares formulation of the energy equation is used to extend the variational Euler solver of Bruneau et al. (1986) to A89-45375 supersonic and hypersonic flow problems. The derivation and LOW-STORAGE IMPLICIT UPWIND-FEM SCHEMES FOR THE numerical implementation are outlined. and results are presented EULER EQUATIONS graphically for a thin delta wing at freestream Mach numbers 0.7 A. DERVIEUX. L. FEZOUI, H. STEVE (Institut National de or 2.0 and angle of attack 10 deg. The solution for 80,000 unknowns Recherche en lnformatique et en Automatique, Valbonne. France), at Mach 0.7 converges in 50 iterations and required about 30 min J. PERIAUX, and B. STOUFFLET (Avions Marcel Dassault-Breguet on one processor of a Cray 2 supercomputer; in a test computation Aviation, Saint-Cloud, France) IN: International Conference on for Mach 5.0, however, a 200,000-point computation required Numerical Methods in Fluid Dynamics, 11 th, Williamsburg, VA, June 100,000 megawords of storage and 8 h of CPU time. T.K. 27-July 1, 1988, Proceedings. Berlin and New York, Springer-Verlag, 1989, p. 215-219. refs New versions of the linearized implicit scheme are presented. A89-45369 Among others, there are the following improvements: (1) at most, A HIGH RESOLUTION FINITE VOLUME SCHEME FOR only the block-diagonal terms of the matrix are stored, and (2) STEADY EXTERNAL TRANSONIC FLOW nonrecurrent solution algorithms are applied, making it possible to D. M. CAUSON (Manchester Polytechnic, England) IN: adapt the schemes to supercomputers. The convergence to the International Conference on Numerical Methods in Fluid Dynamics, steady solution is fast and mesh adaptation is combined without 11 th, Williamsburg, VA, June 27-July 1, 1988, proceedings. Berlin losing efficiency in the solution. K.K. and New York, Springer-Verlag, 1989, p. 182-186. Research supported by the Ministry of Defence Procurement Executive. A89-45378 refs COMPUTATION OF VISCOUS UNSTEADY COMPRESSIBLE An improved Euler solver is presented for computing steady FLOW ABOUT AIRFOILS external transonic flows around projectiles and aircraft forebodies. K. DORTMANN (Aachen, Rheinisch-Westfaelische Technische The method solves the unsteady Euler equations by time-marching Hochschule, Federal Republic of Germany) IN: International using operator-splitting in conjunction with a finite volume Conference on Numerical Methods in Fluid Dynamics, llth, formulation. The resolution of captured shock waves is improved Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and by the use of a total variation diminishing (TVD) version of the New York, Springer-Verlag, 1989, p. 230-234. refs well-known MacCormack scheme and artificial compression The formation of vortices near the trailing edge of a NACA techniques. Existing production code implementations of 441 2 airfoil in unsteady-subsonic flow with time-dependent inflow MacCormack’s method can be updated easily, as described, to conditions is investigated analytically. An explicit five-step reflect recent advances in one-dimensional schemes. Author Runge-Kutta time-stepping scheme is adopted to resolve the time scales required for characterization of the inflow, the gasdynamic regime, and the wake flow. Near the trailing edge, the inviscid A89-45370 and viscous forces are treated using a cell-vertex discretization DEVELOPMENT OF A HIGHLY EFFICIENT AND ACCURATE and a node-centered scheme, respectively, and particular attention 3D EULER FLOW SOLVER is given to the preservation of spatial and temporal accuracy in H. C. CHEN and N. J. YU (Boeing Commercial Airplanes, Seattle, the application of numerical damping. The results are presented WA) IN: International Conference on Numerical Methods in Fluid graphically and shown to be in good general agreement with Dynamics. llth, Williamsburg, VA, June 27-July 1, 1988, published experimental data. T.K. Proceedings. Berlin and New York, Springer-Verlag. 1989, p. 187-191. refs A8945381 The theoretical basis and performance of a cell-centered COMPUTER SJMULATION OF SOME TYPES OF FLOWS out-of-core multigrid solution algorithm for the Euler equations (Vu ARISING AT INTERACTIONS BETWEEN A SUPERSONIC et al., 1988) are reviewed. The method incorporates a finite-volume FLOW AND A BOUNDARY LAVER spatial discretization, successive mesh refinement and multigrid T. G. ELIZAROVA and B. N. CHETVERUSHKIN (AN SSSR, lnstitut acceleration, and a Runge-Kutta time integration; the hardware Prikladnoi Matematiki, Moscow, USSR) IN: International implementation involves block-by-block computation of flowfield Conference on Numerical Methods in Fluid Dynamics, 1lth, data stored on a solid-state disk, with conservation of fluxes across Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and interblock boundaries. Results for a wing-body/winglet configuration New York, Springer-Verlag. 1989, p. 245-250. refs at freestream Mach number M = 0.7 and alpha = 2.08 deg and Numerical simulation results obtained for nonstationary periodic an NLR7301 airfoil at Mach 0.721 and alpha = -0.194 deg are flows with front separation zones arising in a supersonic flow around presented graphically and discussed in detail. It is demonstrated a spiked cylinder are presented. Both the stationary and oscillatory that the solution method is insensitive to grid quality and dissipation regimes of the first and second kind were calculated as a function parameters and converges well with respect to mesh refinement. of the free stream velocity and the geometry of the body. Numerical T.K. results obtained for a supersonic gasdynamic flow around a
642 02 AERODYNAMICS
cylindrical tube closed from one end and mounted by its open turbulence model for unstructured grids is described and its end toward a supersonic free stream are presented as well. accuracy is evaluated. For unsteady simulations, it is shown how K.K. a spatial variation of the time steps can be allowed while simultaneously maintaining time accuracy. A conservative interface A89-45384" National Aeronautics and Space Administration. treatment is presented and compared with a nonconservative Ames Research Center, Moffett Field, CA. treatment for steady state problems in both subsonic and ACCURATE SIMULATION OF VORTICAL FLOWS supersonic flow. C.D. KOZO FUJI1 (NASA, Ames Research Center, Moffett Field, CA; Institute of Space and Astronautical Science, Sagamihara, Japan) A89-45393 IN: International Conference on Numerical Methods in Fluid RNS SOLUTIONS FOR THREE-DIMENSIONAL STEADY Dynamics, 11 th, Williamsburg, VA, June 27-July 1, 1988, INCOMPRESSIBLE FLOWS Proceedings. Berlin and New York, Springer-Verlag, 1989, p. P. K. KHOSLA, S. G. RUBIN, and A. HIMANSU (Cincinnati, 268-272. refs University, OH) IN: International Conference on Numerical Even with recent supercomputers having a large memory, Methods in Fluid Dynamics, 11th, Williamsburg, VA, June 27-July Navier-Stokes simulations for vortical flows do not provide 1, 1988, Proceedings. Berlin and New York, Springer-Verlag, 1989, satisfactory results because of the lack of grid resolution to p. 331-336. refs accurately simulate the strength of separation vortices. To (Contract F49620-85-C-0027) overcome this problem, a zonal method is proposed to increase Laminar, three-dimensional, separated-flow reduced Navier- the number of grid points locally. Interface scheme which is critical Stokes (FINS) solutions are obtained for a trough and a parabolic- for an efficient and stable zonal method is based on the Fortified arc airfoil. A sparse-matrix solver is combined with a march- Navier-Stokes concept. Application to both two-dimensional conical ing or relaxation procedure. Comparisons are made with and three-dimensional delta wing problems indicates this simple two-dimensional solutions and a finite recirculation bubble is found zonal method can improve the accuracy of vortical flow for the three-dimensional cases. C.D. simulations. Author A89-45394' National Aeronautics and Space Administration. A89-45390 Ames Research Center, Moffett Field, CA. NUMERICAL SIMULATION OF THE FLOW ABOUT A WING NUMERICAL STUDY OF UNSTEADY VISCOUS HYPERSONIC WITH LEADING-EDGE VORTEX FLOW BLUNT BODY FLOWS WITH AN IMPINGING SHOCK J. M. J. W. JACOBS, H. W. M. HOEIJMAKERS, J. I. VAN DEN G. H. KLOPFER (NEAR, Inc., Mountain View, CA), H. C. YEE, BERG, and J. W. BOERSTOEL (Nationaal Lucht- en and P. KUTLER (NASA, Ames Research Center, Moffett Field, Ruimtevaartlaboratorium, Amsterdam, Netherlands) IN: CA) IN: International Conference on Numerical Methods in Fluid International Conference on Numerical Methods in Fluid Dynamics, Dynamics, 11th, Williamsburg, VA, June 27-July 1, 1988, 11th, Williamsburg, VA, June 27-July 1, 1988, proceedings. Berlin Proceedings. Berlin and New York, Springer-Verlag, 1989, p. and New York, Springer-Verlag, 1989, p. 31 1-317. Research 337-343. refs supported by the Nederlands lnstituut voor Vliegtuigontwikkeling A complex two-dimensional, unsteady, viscous hypersonic shock en Ruimtevaart. refs wave interaction is numerically simulated by a high-resolution, The compressible flow about a cropped 65-deg swept second-order fully implicit shock-capturing scheme. The physical sharp-edged delta wing featuring leading-edge vortex flow is model consists of a nonstationary oblique shock impinging on the computed. Numerical results are experimental data are compared bow shock of a blunt body. Studies indicate that the unsteady for a transonic and for a subsonic case. Attention is given to the flow patterns are slightly different from their steady counterparts. influence of grid density and grid point distribution. C.D. However, for the sample cases investigated the peak surface pressures for the unsteady flows seem to occur at very different A89-45391 impingement locations than for the steady flow cases. Author MULTIGRID CALCULATIONS FOR CASCADES ANTONY JAMESON and FENG LIU (Princeton University, NJ) IN: A89-45402 International Conference on Numerical Methods in Fluid Dynamics, ASYMMETRIC SEPARATED FLOWS ABOUT SHARP CONES IN 11th, Williamsburg, VA, June 27-July 1, 1988, proceedings. Berlin A SUPERSONIC STREAM and New York, Springer-Verlag, 1989, p. 318-325. refs F. MARCONI (Grumman Corporate Research Center, Bethpage. A finite volume method with a multistage time-stepping scheme NY) IN: International Conference on Numerical Methods in Fluid is used here to calculate two-dimensional cascade flow. The Dynamics, 11th, Williamsburg, VA, June 27-July 1, 1988, stability limit of the explicit scheme is extended to using implicit Proceedings. Berlin and New York, Springer-Verlag, 1989, p: residual averaging. Convergence is accelerated by using locally 395-402. refs varying time steps, enthalpy damping, and an effective multigrid (Contract F49620-84-C-0036) method. Adaptive numerical dissipation is used for capturing The inviscid flow separation model is used to investigate shocks. Results for the NACA 0012 cascade, the Hobson whether lateral instability in slender-nosed aircraft flying at high shock-free cascade, and the supersonic wedge cascade show angle of attack is a viscous or inviscid phenomenon. The excellent accuracy and convergence in comparison to results by geometries considered are slender right circular cones. The Euler other investigators. C.D. code, used in conjunction with a flow-separation model, indicates that the phenomenon is inviscid in nature. Preliminary results A89-45392 indicate that the asymmetry of the vortex flow is caused by mutual UNSTEADY AND TURBULENT FLOW USING ADAPTATION interference of the starboard and port vortices. C.D. METHODS JOHN G. KALLINDERIS and JUDSON R. BARON (MIT, Cambridge, A89-45404 MA) IN: International Conference on Numerical Methods in Fluid INVERSE METHOD FOR THE DETERMINATION OF Dynamics, 11th, Williamsburg, VA. June 27-July 1, 1988, TRANSONIC BLADE PROFILES OF TURBOMACHINERIES Proceedings. Berlin and New York, Springer-Verlag, 1989, p. B. MICHAUX (Indiana University, Bloomington) IN: International 326-330. refs Conference on Numerical Methods in Fluid Dynamics, 11th, Previous adaptation methodology and numerical schemes are Williamsburg, VA, June 27-July 1, 1988, proceedings. Berlin and applied here to complex flows such as those involving airfoils in New York, Springer-Verlag, 1989, p. 408-412. Research supported turbulent flow. A detection procedure is used which tracks both by SNECMA and Indiana University. flow features and their directionality and defines embedding patches (Contract AF-AFOSR-88-103) which act as filters to reduce the number of randomly embedded A new numerical method allowing the computation of transonic cells. A new and general way for implementing an algebraic blade profile geometry for turbomachineries is presented. An
643 02 AERODYNAMICS equivalence of the constraints by Lighthill (1 945) is investigated in 494-500. refs order to obtain the existence of a closed profile. An extension of (Contract AF-AFOSR-87-0074) the method by Stanitz for a fluid verifying the exact isentropicity A Navier-Stokes analysis has been developed for simulating law is developed. C.D. unsteady flows using general clustered conformal coordinates and a three-level multigrid procedure for the stream-function equation. A89-45405 The mathematical formulation is outlined and the numerical INTERACTION OF AN OBLIQUE SHOCK WAVE WITH procedure is described. The leading edge separation encountered SUPERSONIC TURBULENT BLUNT BODY FLOWS in high-incidenceflows is examined by considering a model problem YOUNG J. MOON and MAURICE HOLT (California, University, of the flow past a semiinfinite body with finite thickness and a Berkeley) IN: International Conference on Numerical Methods in sharp shoulder. C.D. Fluid Dynamics, 11th. Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and New York, Springer-Verlag, 1989, p. A8945419 418-423. refs TRANSONIC ANALYSIS OF ARBITRARY CONFIGURATIONS A numerical study of shock-on-shock interactions near a USING LOCALLY REFINED GRIDS cylindrical body, representative of the engine inlet cowl of the SATISH S. SAMANT (Boeing Commercial Airplanes, Seattle, WA), National Aerospace Plane (NASP), is presented. Among the six JOHN E. BUSSOLETTI. FORRESTER T. JOHNSON (Boeing principal shock interference patterns depending upon the Advanced Systems, Seattle, WA), ROBIN G. MELVIN, and DAVID intersection point, noted by Edney, the most critical cases, of P. YOUNG (Boeing Computer Services, Seattle, WA) IN: types 111 and IV, are considered in the present study. In these International Conference on Numerical Methods in Fluid Dynamics, cases, anomalous amplifications of peak pressure and heat flux 11th, Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin occur at the shear layer and supersonic jet impingement points, and New York, Springer-Verlag, 1989, p. 518-522. respectively. The primary goal of this study is to calculate the An approach is presented to solve the full potential equation entire flow field numerically, capturing all the interacting shocks about arbitrary configurations. A hierarchical refinement of a globally and complicated shock-layer flows. The finite volume formulation uniform rectangular grid is superimposed over a boundary described of Van Leer's flux-vector splitting MUSCL scheme, in generalized by networks of panels. The finite element method is used to obtain coordinates, is used to solve the full Navier-Stokes equations in discrete operators for irregularly shaped regions near the boundary. strong conservative form. Author The implementation of grid refinement and some results obtained using this approach are described. Author A89-45413' University Colt. of Swansea (Wales). ADAPTIVE NUMERICAL SOLUTIONS OF THE EULER A89-45422 EQUATIONS IN 3D USING FINITE ELEMENTS NAVIER-STOKES SIMULATION OF TRANSONIC FLOW ABOUT J. PERAIRE, J. PEIRO, L. FORMAGGIA, and K. MORGAN WINGS USING A BLOCK STRUCTURED APPROACH (Swansea, University College, Wales) IN: International Conference D. SCHWAMBORN (DNLR, lnstitut fuer theoretische on Numerical Methods in Fluid Dynamics, 11 th, Williamsburg, VA, Stroemungsmechanik, Goettingen, Federal Republic of Germany) June 27-July 1, 1988, Proceedings. Berlin and New York, IN: International Conference on Numerical Methods in Fluid Springer-Verlag, 1989, p. 469-473. Research supported by the Dynamics, 11th, Williamsburg, VA. June 27-July 1, 1988, Research Corp. refs Proceedings. Berlin and New York, Springer-Verlag, 1989, p. (Contract NAGW-478; SERC-GR/E/61762) 533-537. The development of an adaptive mesh solution for a flow An explicit finite volume method for the integration of the involving shock interaction on a swept cylinder and an initial solution Navier-Stokes equations is presented. The method is cast into a for a flow past a complex fighter configuration is reported. The very flexible block-structured approach. Results are presented for finite element solution algorithm, the mesh generation, and the the simulation of the DFVLR-F5 experiment which has been adaptivity of the solution are described. Sample results for the designed to serve as a well defined boundary value problem for flow past an F-18 configuration at Mach 0.9 and alpha of 3 deg transonic viscous flow computations. Author and for shock interaction on a swept cylinder at Mach 8.04 are summarized. C.D. A89-45425 INVISCID AND VISCOUS FLOW SIMULATIONS AROUND THE A89-45414 ONERA-M6 BY TVD SCHEMES SIMULATION OF INVISCID HYPERSONIC REAL GAS FLOWS YOKO TAKAKURA (Fujitsu, Ltd., Scientific Systems Dept., Tokyo, M. PFITZNER, C. WEILAND, and G. HARTMANN Japan), SATORU OGAWA, and TOMIKO ISHIGURO (National (Messerschmitt-Boelkow-Blohm GmbH, Ottobrunn, Federal Aerospace Laboratory, Chofu, Japan) IN: International Conference Republic of Germany) IN: International Conference on Numerical on Numerical Methods in Fluid Dynamics, 11th, Williamsburg, VA, Methods in Fluid Dynamics, 11 th, Williamsburg, VA, June 27-July June 27-July 1, 1988, Proceedings. Berlin and New York, 1, 1988. Proceedings. Berlin and New York, Springer-Verlag,1989, Springer-Verlag. 1989, p. 553-557. refs p. 479-483. refs The flow around the Onera-M6 wing poses significant Two-dimensional and three-dimensional calculations of inviscid aerodynamical problems, involving interaction between shock supersonic and hypersonic flows about a variety of configurations, waves, between shock waves and boundary layers, and between including orbiters and missiles, as well as flows through nozzles, two-wall boundary layers and the wing tip vortex. The extent to are presented. Equilibrium real gas and ideal gas results are which NDschemes can treat these phenomena is examined here compared and the differences are discussed. The supersonic part using inviscid and viscous flow simulations. The results indicate of the flow field is calculated with a pseudospace marching method that the TVD schemes are applicable to both inviscid and viscous which uses the algorithm for the unsteady Euler equations as a flow problems. The solutions of the Euler equations in the low relaxation procedure. Shock-fitting and shock-capturing capabilities attack angle case are excellent. Improvements of the left-hand-side for the ideal and real gas cases are demonstrated. C.D. operators and the practicalization of large eddy simulation are also reported. C.D. A89454 15 SIMULATION OF UNSTEADY FLOW PAST SHARP A89-45428' Mississippi State Univ., Mississippi State. SHOULDERS ON SEMI-INFINITE BODIES TRANSONIC FLOW SOLUTIONS ON GENERAL 3D REGIONS A. RAMAMURTI, U. GHIA, and K. N. GHIA (Cincinnati, University, USING COMPOSITE-BLOCK GRIDS OH) IN: International Conference on Numerical Methods in Fluid JOE F. THOMPSON and DAVID L. WHITFIELD (Mississippi State Dynamics, 11th, Williamsburg, VA, June 27-July 1, 1988, University, Mississippi State) IN: International Conference on Proceedings. Berlin and New York, Springer-Verlag. 1989, p. Numerical Methods in Fluid Dynamics, 11th, Williamsburg, VA, June
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27-July 1, 1988, Proceedings. Berlin and New York, Springer-Verlag, A89-45468' National Aeronautics and Space Administration. 1989, p. 568-572. Research supported by USAF. refs Lewis Research Center, Cleveland, OH. (Contract NAG3-767) A NEWTON/UPWIND METHOD AND NUMERICAL STUDY OF The construction of computational fluid dynamics (CFD) codes SHOCK WAVE/BOUNDARY LAYER INTERACTIONS for complicated regions is greatly simplified by a composite-block MENG-SING LlOU (NASA, Lewis Research Center, Cleveland, grid structure since, with the use of a surrounding layer of points OH) International Journal for Numerical Methods in Fluids (ISSN on each block, a flow code is then only required basically to 0271-2091), vol. 9, July 1989, p. 747-761. refs operate on rectangular computational regions. The necessary The objective of the paper is two-fold. First, an upwind/central correspondence of points on the surrounding layers (image points) differencing method for solving the steady Navier-Stokes equations with interior points (object points) is set up by the grid code and is described. The symmetric line relation method is used to solve made available to the CFD solution code. Author the resulting algebraic system to achieve high computational efficiency. The grid spacings used in the calculations are determined from the triple-deck theory, in terms of Mach and A89-45434 Reynolds numbers and other flow parameters. Thus the accuracy NONISENTROPIC POTENTIAL CALCULATION FOR 2-D AND of the numerical solutions is improved by comparing them with 3-D TRANSONIC FLOW experimental, analytical, and other computational results. Secondly, ZI-QIANG ZHU and XUE-SONG BAl (Beijing Institute of Aeronautics the shock wavelboundary layer interactions are studied numerically, and Astronautics, People's Republic of China) IN: International with special attention given to the flow separation. The concept Conference on Numerical Methods in Fluid Dynamics, 11th, of free interaction is confirmed. Although the separated region Williamsburg, VA, June 27-July 1, 1988, Proceedings. Berlin and varies with Mach and Reynolds numbers, it is found that the New York, Springer-Verlag, 1989, p. 618-622. refs transverse velocity component behind the incident shock, which A shock point operator is introduced to account for the entropy has not been identified heretofore, is also an important parameter. change across a shock wave. The operator satisfies conservation A small change of this quantity is sufficient to eliminate the flow relations which are consistent with the shock jump condition. A separation entirely. Author full potential code with such a nonisentropic formulation allows more accurate flow computations around airfoils and wings. A89-45560# Numerical calculations indicate that the present formulation yields INVESTIGATION ON UNSTEADY FLOW FIELD AND ENDWALL results that are close to the Euler solution and experimental data. BOUNDARY LAYER IN AXIAL FLOW COMPRESSOR WITH The computation time required is only a fraction of that required HOT-WIRE ANEMOMETER using the Euler code. C.D. QlXUN LIN, NINGFANG GUO, YAPING LI, and NINGFANG XlAO (Northwestern Polytechnical University, Xian, People's Republic of China) Journal of Aerospace Power (ISSN 1000-EO%), vol. 4, A89-45437" National Aeronautics and Space Administration. April 1989, p. 141-1 44, 195. In Chinese, with abstract in English. Lewis Research Center, Cleveland, OH. The measurement method for rotating stall is presented. The A NATURAL LOW-FREQUENCY OSCILLATION OF THE FLOW time difference between two signals and its frequency are OVER AN AIRFOIL NEAR STALLING CONDITIONS determined correctly on the basis of cross-correlation and spectrum K. B. M. Q. ZAMAN, D. J. MCKlNZlE (NASA, Lewis Research analysis. Then, the rotating stall regime, its spread velocity, and Center, Cleveland, OH), and C. L. RUMSEY (NASA, Langley its form are obtained. The methods of the two-dimensional unsteady Research Center, Hampton, VA) Journal of Fluid Mechanics flow measurement are described. The velocity distribution of the (ISSN 0022-1120), vol. 202, May 1989, p. 403-442. refs unsteady flow, for example a rotating-stall cell, is obtained. A An experimental and computational study of the low-frequency rotating single wire method is applied to measuring the oscillation observed in the flow over an airfoil at the onset of two-dimensional boundary layer. The results measured behind a static stall is presented. Wind-tunnel results obtained with single rotor and a stator are shown in the paper. The contamination two-dimensional airfoil models show that this phenomena takes from dirt, the influence of air flow temperature, and the boundary place only with a transitional state of the separating boundary layer flow field disturbance caused by probe hole, are considered. layer. It is noted that the flowfield does not involve a Karman Author vortex street. The experimental results agree well with the results of a two-dimensional Navier-Stokes code. The present study A89-45565# demonstrates that the low-frequency oscillations produce intense EFFECTS OF AXIAL VELOCITY DENSITY RATIO ON flow fluctuations which impart much larger unsteady forces to the CASCADE PERFORMANCES airfoil than experienced by bluff-body shedding and which may QlANZHl LIU and RUQUN YAN (Northwestern Polytechnical represent the primary aerodynamics of stall flutter of blades and University, Xian, People's Republic of China) Journal of Aerospace wings. R.R. Power (ISSN 1000-8055), vol. 4. April 1989, p. 161-164, 196. In Chinese, with abstract in English. refs In turbomachinery cascade flows, the effects of Axial Velocity A89-45458 Density Ratio (AVDR) on cascade performances are very important. PRESSURE FLUCTUATIONS ON AN OSCILLATING TRAILING The theoretical and experimental studies of the problem are EDGE presented in this paper. The theoretical correlations of major THOMAS STAUBLI and DONALD ROCKWELL (Lehigh University, cascade performances with AVDR are obtained. The comparisons Bethlehem, PA) Journal of Fluid Mechanics (ISSN 0022-1120), of calculations and experiments are in good agreement. Author vol. 203, June 1989, p. 307-346. Research supported by SNSF, US. Navy, NSF, and Stiftung Volkswagenwerk. refs A89-45906" National Aeronautics and Space Administration. The surface loading and near-wake flow structure that are Ames Research Center, Moffett Field, CA. inherent to vortex formation from both blunt trailing edges and INTERACTION OF AN OSCILLATING VORTEX WITH A cylindrical bodies are investigated. Turbulent boundary layers TURBULENTBOUNDARYLAYER separating from a blunt trailing edge are shown to give rise to R. V. WESTPHAL (NASA, Ames Research Center, Moffett Field, organized vortical structures in the downstream wake, and the CA) and R. D. MEHTA (Stanford University, CA) Experiments in perturbation of this inherent flow instability by controlled oscillations Fluids (ISSN 0723-4864), vol. 7, no. 6, June 1989, p. 405-411. of the edge produces corresponding organized components of refs unsteady surface pressure along the edge. Flow visualizations are (Contract NCC2-294) performed in order to determine the phasing of the organized An oscillating vortex embedded within a turbulent boundary vortical structures shed from the trailing edge relative to the edge layer was generated experimentally by forcing a periodic lateral displacement. R.R. translation of a half-delta wing vortex generator. The objective of
645 02 AERODYNAMICS the experiment was to investigate the possibility that a natural A09-46262# oscillation, or meander, might be responsible for flattened vortex DESIGN AND ANALYSIS OF AIRFOILS IN TRANSONIC cores observed in previous work, which could also have VISCOUS FLOW contaminated previous turbulence measurements. The effect of PING LIU and SHIJUN LUO (Northwestern Polytechnical University, this forced oscillation was characterized by comparison of Xian, People’s Republic of China) Acta Aerodynamica Sinica measurements of the mean velocities and Reynolds stresses at (ISSN 0258-1825), vol. 7, no. 2, 1989, p. 235-239. In Chinese, two streamwise stations, for cases with and without forcing. The with abstract in English. refs Reynolds stresses were affected significantly by the forced A numerical method has been employed to design and analyze oscillation, mainly through contributions from the individual airfoils in transonic viscous flow. The results show that the production terms, provided that the vortex was not too diffuse. agreement of present method and the wind tunnel experiment is Author good both for weak interaction cases of shock wavelboundary layer and for strong cases. When the separation occurs, however, the agreement is poor downstream of the shock wave. Author A0946190 DIFFERENCE METHODS FOR INITIAL-BOUNDARY-VALUE A09-46263# PROBLEMS AND FLOW AROUND BODIES (REVISED RADIATIVE CHARACTERISTICS OF HYPERSONIC CONE EDITION) WAKE YOU-LAN ZHU, XI-CHANG ZHONG, BING-MU CHEN, and XUEHUA ZHOU and GUOYING CHAO (Chinese Academy of ZUO-MIN ZHANG (Chinese Academy of Sciences, Computing Sciences, Institute of Mechanics, Beijing, People’s Republic of Center, Beijing, People’s Republic of China) Berlin and New China) Acta Aerodynamica Sinica (ISSN 0258-1825), vol. 7, no. York. Springer-Verlag, 1988, 608 p. Translation. refs 2, 1989, p. 240-244. In Chinese, with abstract in English. refs This book presents a detailed description of a new difference A finite explicit difference method was applied to the method for quasi-linear hyperbolic systems of partial differential axisymmetric boundary layer equations of a hypersonic air wake equations. The method is highly accurate, even for problems with in the chemical nonequilibrium behind a hypersonic cone. A singularities such as shocks, contact discontinuities, rarefaction two-dimensional distribution of the temperature, density, con- waves, and detonations. The mathematical foundation of the centration, and electron density was obtained. The radiation method and the method’s application to supersonic flow around intensity and quantity were calculated for the species which are bodies are discussed. C.D. the source of the wake radiation. K.K.
A0946266# A89-46256# THE COMPUTED RESULTS OF AIRFOIL NEAR THE AN INTEGRATED DESIGN COMPUTATIONAL METHOD FOR FREESTREAM MACH NUMBER ONE THE WING OPTIMIZATION CAMBER AND TWIST AT LONGDE HE (Chinese Academy of Sciences, Institute of SUBSONIC AND SUPERSONIC FLOW Mechanics, Beijing, People’s Republic of China) Acta DEHUA LIO, CHANGYOU HUANG, GOLlN ZHU (China Aerodynamica Sinica (ISSN 0258-1825), vol. 7, no. 2, 1989, p. Aerodynamic Research and Development Centre, Sichuan, 255-257. In Chinese, with abstract in English. refs People’s Republic of China), YUPU LI, and GUANGMING SHE The range of freestream Mach numbers over which the local (611 Aircraft Design Institute, People’s Republic of China) Acta Mach number is frozen for a NACA0012 airfoil at alpha = 0 and Aerodynamica Sinica (ISSN 0258-1825), vol. 7, no. 2, 1989, p. 2 deg is determined. The distances between the detached shock 192-199. In Chinese, with abstract in English. refs and airfoil leading edge are determined at Mach numbers in the An integrated design computational method based on an range of 1.05 to 1.30. K.K. element solution method is presented for the wing optimization camber and twist at subsonic and supersonic flow. A wing design A09-46267# was selected by choosing the design points in subsonic and THE INDUCED POWER BASED ON LEADING EDGE SUCTION supersonic flow. K.K. FOR A HELICOPTER IN HOVERfNG ZHENHAO LI (Chinese Helicopter Research and Development A09-46259# Institute, Chinese Republic of China) Acta Aerodynamica Sinica EXPERIMENTAL STUDY OF VORTEX AND AERODYNAMIC (ISSN 0258-1825), vol. 7, no. 2, 1989, p. 258-261. In Chinese, CHARACTERISTICS OF STACK WINGS WITH SIDESLIP with abstract in English. GUOHUA BAO (Northwestern Polytechnical University, Xian, A new formula for induced power based on the leading edge People’s Republic of China) Acta Aerodynamica Sinica (ISSN suction for a helicopter in hovering is derived in this paper. A 0258-1825), vol. 7, no. 2, 1989, p. 215-219. In Chinese, with abstract simple example shows its applicability. This formula can be used in English. for aerodynamic optimization of rotor blade. Author Experimental results on stack wings are presented. The effect of the bursting and twisting of vortices on the aerodynamic A09-46694# characteristics is analyzed. The results show that sideslip delays BEHAVIOR OF VORTEX STREET IN THE WAKE BEHIND A twisting of the vortices on the upwind side but accelerates it on CIRCULAR CYLINDER UNDER CONTROLLED EXCITATION the backwind side. K.K. MUNESHIGE OKUDE and TATSUYA MATSUI Japan Society for Aeronautical and Space Sciences, Journal (ISSN 0021-4663), vol. 37, no. 424, 1989, p. 228-237. In Japanese, with abstract in A09-46260# English. refs FLOW CHARACTERISTICS IN AN SSHAPED The behavior of vortex street in the wake behind a circular RECTANGULAR-ROUND DIFFUSER AT HIGH INCIDENCE cylinder under controlled excitation was investigated with the QI LIN and RONGWEI GUO (Nanjing Aeronautical Institute, techniques both of hot-wire and of flow visualization at the Reynolds People’s Republic of China) Acta Aerodynamica Sinica (ISSN numbers lower than 160 in the pure Karman vortex street range. 0258-1825), vol. 7, no. 2, 1989, p. 220-226. In Chinese, with abstract The response frequencies of the velocity fluctuation indicated the in English. nonlinear interaction among the disturbances of the frequency of The flow in an S-shaped rectangular-round diffuser in the 0 to primary vortex street, of the most amplified frequency in the wake 85 deg incidence range is studied experimentally. The diffuser and of the forcing frequency. When the wake flow is forced with was tested in the working section of a blowdown tunnel. The the disturbance of the intermediate frequency lower than that of study reveals that, with increasing incidence, the average total the primary vortex street, the velocity fluctuation at far downstream pressure coefficient and swirl coefficient increase and the air flow location had two modes of the frequency caused by the nonlinear coefficient decreases continuously. K.K. effect. One of them led to merging of two vortices in the primary
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vortex street, and the other led to merging of three vortices, i.e., A89-46839# merging of two vortices followed by joining of another vortex A VALIDATION OF A NAVIER-STOKES 2D SOLVER FOR afterward. The width of the wake was rapidly increased by the TRANSONIC TURBINE CASCADE FLOWS vortex merging. Author S. COLANTUONI, A. TERLlZZl (Alfa Romeo Avio S.p.A., Naples, Italy), and F. GRASS0 (Roma I, Universita, Rome, Italy) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, A89-46763"# Applied and Theoretical Mechanics, Inc., Oakland, Monterey, CA, July 10-13, 1989. 10 p. refs CA. (AIAA PAPER 89-2451) MODELING OF TURBULENCE FOR COMPRESSION CORNER In the present work a solver for the solution of the compressible FLOWS AND INTERNAL FLOWS Navier Stokes equations for transonic turbine cascade flows is J. M. CHAMPNEY (Applied and Theoretical Mechanics, Inc., validated. The model here presented employs a finite volume Oakland, CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion 3-stage Runge-Kuttaalgorithm with symmetric discretization of both Conference, 25th, Monterey, CA, July 10-13, 1989. 12 p. refs inviscid and viscous terms. Test cases are presented for the (Contract NAS2-12778) computation of flows through three different cascades for which (AIAA PAPER 89-2344) experimental data are available. Author A compressible Reynolds averaged Navier-Stokes code is applied to examine the performances of basic turbulence models for unseparated and separated flows. The turbulence models A89-46840*# National Aeronautics and Space Administration. considered are a zero-equation model and several two-equation Ames Research Center, Moffett Field, CA. models, including a new k-epsilon model with an eddy viscosity TWO-DIMENSIONAL COMPUTATIONS OF MULTI-STAGE damping function depending upon the Reynolds number and the COMPRESSOR FLOWS USING A ZONAL APPROACH distance from the wall. The turbulence models are assessed using KAREN L. GUNDY-BURLET, MAN MOHAN RAI (NASA, Ames the following experimental flows: a channel flow, a backward facing Research Center, Moffett Field, CA), and ROBERT P. DRlNG step, and a two-dimensional compression corner at Mach 2.8. (United Technologies Research Center, East Hartford, CT) AIAA, Discussions and comparisons of the experimental and numerical ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, results are given. Mesh refinement is shown to have a significant Monterey, CA, July 10-13, 1989. 11 p. refs beneficial effect on free shear layer flow results obtained with (AIAA PAPER 89-2452) two-equation turbulence models. The results illustrate the A clear understanding of the fluid dynamics associated with usefulness of several turbulence models as a design tool for fluid rotor/stator configurations can be very helpful when optimizing engineering systems. Author the performance of turbomachinery. In this study, a two- dimensional, implicit, thin-layer, Navier-Stokes zonal approach has been used to investigate the flow within a 2 1/2-stage A89-46769*# National Aeronautics and Space Administration. compressor. Relative motion between the rotor and stator airfoils Lewis Research Center, Cleveland, OH. is made possible with the use of systems of patched and overlaid MACH 5 INLET CFD AND EXPERIMENTAL RESULTS grids that move with respect to each other. The treatment of LOIS J. WEIR (NASA, Lewis Research Center, Cleveland, OH), D. multistage turbomachines with arbitrary numbers of airfoils per row R. REDDY, and GEORGE D. RUPP (NASA, Lewis Research Center; is made possible by the use of a flexible database system. Results Sverdrup Technology, Inc., Cleveland, OH) AIAA, ASME, SAE, in the form of instantaneous pressure and entropy contours and and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July time-averaged pressures are presented for the 2 1/2-stage 10-13, 1989. 15 p. refs compressor. Time-averaged pressures and pressure amplitudes (AIAA PAPER 89-2355) for a single-stage turbine configuration are also presented. The An experimental research program was conducted in the NASA numerical results compare well with experimental data. Author Lewis Research Center 10 ft. by 10 ft. supersonic wind tunnel. The two-dimensional inlet model was designed to study the Mach 3.0 to 5.0 speed range for an 'over-under' turbojet plus ramjet A89-46842# propulsion system. The model was extensively instrumented to COMPUTATIONAL AND EXPERIMENTAL STUDY OF STALL provide both analytical code validation data as well as inlet PROPAGATION IN AXIAL COMPRESSORS performance information. Support studies for the program include S. JONNAVITHULA, S. THANGAM, and F. SISTO (Stevens Institute flow field predictions with both three-dimensional parabolized of Technology, Hoboken, NJ) AIAA, ASME. SAE, and ASEE, Navier-Stokes (PNS) and three-dimensional full Navier-Stokes Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. (FNS) analytical codes. Analytical predictions and experimental 9 p. refs results are compared. Author (Contract N00014-86-K-0315;N62271-87-M-0204) (AIAA PAPER 89-2454) The paper presents a numerical and experimental study of A89-46771*# National Aeronautics and Space Administration. stall propagation in axial compressors. In the numerical study, the Lewis Research Center, Cleveland, OH. compressor blades are represented as an isolated linear cascade RECTANGULAR NOZZLE PLUME VELOCITY MODELING FOR of airfoils and the stall propagation is simulated using a vortex USE IN JET NOISE PREDICTION tracking method. This method involves the use of periodic vortex U. H. VON GLAHN (NASA, Lewis Research Center, Cleveland, arrays to simulate infinite cascades, the use of a vortex merging OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, algorithm to allow computations for large times, the imposition of 25th, Monterey, CA, July 10-13, 1989. 21 p. Previously announced the no slip and the impenetrabilityboundary conditions in an integral in STAR as N89-22577. refs sense, the use of integral boundary layer methods to locate the (AIAA PAPER 89-2357) separation points and the use of Fourier analysis techniques to A modeling technique for predicting the axial and transverse compute the velocities of the propagating stall. Detailed parametric velocity characteristics of rectangular nozzle plumes is developed. studies of the influence of flow parameters like the inflow angle In this technique, modeling of the plume cross section is initiated and stall wavelength, and geometric parameters like cascade at the nozzle exit plane. The technique is demonstrated for the solidity, blade camber and stagger have been performed. The plume issuing from a rectangular nozzle having an aspect ratio of experimental investigations were conducted in a single stage axial 6.0 and discharging into quiescent air. Application of the present compressor test-rig. The occurrence of rotating stall in this research procedures to a nozzle discharging into a moving airstream (flight compressor was demonstrated, and some experimental studies effect) are then demonstrated. The effects of plume shear layer on the effect of various flow parameters on the stall propagation structure modification on the velocity flowfield are discussed and were conducted. The computational and experimental results are modeling procedures are illustrated by example. Author compared and are shown to be in qualitative agreement. Author
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A89-46843'# Pennsylvania State Univ., University Park. A study of helium jets injected into a Mach 3 airflow through AN EXPERIMENTAL STUDY OF THE EFFECT OF circular sonic nozzles angled downstream at 15 and 30 deg is STREAMWISE VORTICITY ON SUPERSONIC MIXING presented. An aspirating hot-film probe was employed to measure ENHANCEMENT helium concentrations. The results of Schlieren and nonoshad- J. W. NAUGHTON, L. N. CATTAFESTA, and G. S. SETTLES owgraph photography show the presence of large-scale turbu- (Pennsylvania State University, University Park) AIAA, ASME, lent structures in the high pressure jets. Concentration data SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, reveal some asymmetries both in tHe cross section of the je! and CA, July 10-13, 1989. 24 p. refs in the ?rajectory of the jet relative to the centerline of the jet. (Contract NAG1-872) Plotting the decay of maximum concentration with axial distance, (AIAA PAPER 89-2456) it is found that the mixing rate can be increased significantly by An initial experimental study of the effect of streamwise vorticity increasing the pressure ratio. These low angle jets display good on supersonic turbulent mixing has been carried out. A Mach 3 cross-stream penetration. R.R. streamwise vortex is generated using a strutmounted swirl injector and is injected into a Mach 3.5 freestream. The resulting flowfield A89-46924# is investigated using both five-hole angularity probe and total COMPUTATIONAL ANALYSIS OF TURBOMACHINERY FLOWS temperature probe surveys. The results are compared to identical USING FLOFIVE experiments with a baseline, swirl-free Mach 3 jet. Laser Light LINDA M. RINK (Morton Thiokol, Inc., Brigham City, UT) and MARK Sheet (LLS) images are used to observe the mixing phenomena. A. CARROLL (U.S. Navy, Naval Ocean Systems Center, San Diego, The entrainment of energy and mass is used to evaluate the CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, degree of mixing between the two streams for both the vortex 25th, Monterey, CA, July 10-13, 1989. 10 p. Research supported and jet cases. The results reveal that streamwise vorticity does by Sundstrand Turbomach, NSF, and San Diego Supercomputer lead to a modest mixing enhancement of about 34 percent for Center. refs the conditions tested. Author (AIAA PAPER 89-2559) A three-dimensional compressible Navier-Stokes solver, A89-46845# FLOFIVE, is evaluated. Simulation results have been compared to EXPERIMENTAL STUDY OF SPREADING RATE five-hole spherical total probe experimental results for a ENHANCEMENT OF HIGH MACH NUMBER TURBULENT straight-walled two-dimensional diffuser, along with LDV mea- SHEAR LAYERS surements for a curved duct and a centrifugal compressor D. S. DOLLING (Texas, University, Austin) and Y. R. SHAU AIAA, impeller. FLOFIVE is shown to accurately predict the boundary ASME, SAE, and ASEE, Joint Propulsion Conference, 25th. layer growth and pressure recovery coefficient for the case of the Monterey, CA, July 10-13, 1989. 12 p. refs diffuser, and to reproduce the experimentally observed secondary (Contract NOOOl 4-89-J-1221) flows and gapwise and spanwise velocity values for the case of (AIAA PAPER 89-2458) the curved duct. Although the code could reproduce the strong The effects of initial conditions on the spreading rate of a high wakes in the impellar, the computational pressure ratio values Reynolds number compressible turbulent shear layer have been overpredicted the experimental value by 10 percent. R.R. experimentally investigated in a Mach 5 blowdown tunnel. The results show that a shock incident on the shear layer has no A89-46933'# Purdue Univ., West Lafayette, IN. measureable effect on the local thickness or spreading rate, or L2F 8 LDV VELOCIMETRY MEASUREMENT AND ANALYSIS on the spreading rate further downstream. Changes in the initial OF THE 3-D FLOW FIELD IN A CENTRIFUGAL COMPRESSOR conditions due to the shock impinging on the plate boundary layer JOHN R. FAGAN, JR. and SANFORD FLEETER (Purdue University, are found to provide a significant increase in the spreading rate West Lafayette, IN) AIAA, ASME, SAE, and ASEE, Joint Propulsion near the shear layer origin. Cross-correlations of fluctuating pitot Conference, 25th, Monterey, CA, July 10-13, 1989. 10 p. Research pressures reveal little evidence of any changes in the shear layer supported by NASA. refs large-scale structure orientation under disturbed conditions. R.R. (AIAA PAPER 89-2572) The flow field in the Purdue Research Centrifugal Compressor A89-46847'# Ohio State Univ., Columbus. is studied using a laser two-focus (L2F) velocimeter. L2F data are COMPRESSIBILITY AND SHOCK WAVE INTERACTION obtained which quantify: (1) the compressor inlet flow field; (2) EFFECTS ON FREE SHEAR LAYERS the steady-state velocity field in the impeller blade passages; and M. SAMMY (Ohio State University, Columbus), D. E. ERWIN, and (3) the flow field in the radial diffuser. The L2F data are compared G. S. ELLIOlT AIAA, ASME, SAE, and ASEE, Joint Propulsion with both laser Doppler velocimetry (LDV) data and predictions Conference, 25th, Monterey, CA, July 10-13, 1989. 13 p. refs from three-dimensional inviscid and viscous flow models. In (Contract NOOOl 4-87-K-0169; NAG3-764) addition, a model is developed to calculate the effect on the (AIAA PAPER 89-2460) measurement volume geometry of refraction by curved windows. Two compressible free shear layers with convective Mach Finally, the advantages and disadvantages of using the L2F for numbers of .51 and .86 were studied as baseline configurations turbomachinery measurements is discussed in terms of to investigate the effects of compressibility on the turbulence measurement accuracy, ease of use, including sample time per characteristics. These shear layers were then disturbed by the correlated event and the ability to make measurements in regions placement of an obstruction in the shear layer in an attempt to of high noise due to stray radiation from wall reflections. Author enhance the shear layer growth rate. These models produced a curved shock in the supersonic side of the shear layer. The results A89-46935# indicate a significant reduction in turbulence levels with increased APPLICATION OF SIMPLE WAVE THEORY TO THE compressibility. However, there are not any significant changes RADIATIVE BOUNDARY CONDITIONS REQUIRED FOR AN due to the bow shock interaction with the shear layer. Author INTERNAL FLOW EULER SOLVER MARK A. DRIVER (USAF, Institute of Technology, Wright-Patterson A8446848'# Virginia Polytechnic Inst. and State Univ., AFB, OH) and ROBERT E. GRAY (USAF, Aero Propulsion and Blacksburg. Power Laboratory, Wright-PattersonAFB, OH) AIAA, ASME, SAE, LOW ANGLE INJECTION INTO A SUPERSONIC FLOW and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July R. B. MAYS, R. H. THOMAS, and J. A. SCHETZ (Virginia 10-13, 1989. 15 p. refs Polytechnic Institute and State University, Blacksburg) AIAA, (AIAA PAPER 89-2577) ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, A numerical algorithm is developed with the capability of Monterey, CA, July 10-13, 1989. 10 p. Research supported by capturing shocks in the internal blade passages of a modern gas NASA. refs turbine. The algorithm uses MacCormack's explicit finite difference (AIAA PAPER 89-2461) scheme to solve the two-dimensional form of the Euler equations.
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Simple wave theory is rigorously developed for application to the boundary layer makes this matching process more difficult. Design radiative boundary value problem. The computed solution is rules for cowl matching with secondary shocks are presented, compared with experimental data for a high-work low aspect ratio though it is never possible to fix them against changes in angle turbine. The ability to obtain a reasonably accurate blade loading of attack. It is also shown that dynamic motion effects are less diagram within a practical execution time is demonstrated. Two significant in affecting shock position and associated oblique shocks, typical of those formed at the trailing edge of a thermodynamic properties than the steady-state effects. Author transonic rotor blade, are captured. These shocks are smeared over several grid points, as expected with a shock capturing ~a9-47009# scheme, but their influence on the blade loading diagram is NUMERICAL AND EXPERIMENTAL INVESTIGATION OF evident. Author AIRFRAME-INTEGRATED INLET FOR HIGH VELOCITIES V. A. VINOGRADOV, V. A. STEPANOV (Tsentral’nyi ~a9-4700~ Nauchno-lssledovatel’skii lnstitut Aviatsionnogo Motorostroeniia, PERFORMANCE AND FLOW FIELD OF A DUCTED Moscow, USSR), and E. V. ALEKSANDROVICH (Tsentral’nyi PROPELLER Aerogidrodinamicheskii Institut, Zhukovski, USSR) AIAA. ASME, R. GANESH RAJAGOPALAN and ZHAOXING ZHANG (Iowa State SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, University of Science and Technology, Ames) AIAA, ASME, SAE, CA, July 10-13, 1989. 9 p. refs and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July (AIAA PAPER 89-2679) 10-13, 1989. 9 p. Research supported by the Iowa State University Godunov’s (1976) steady state scheme is the basis of the of Science and Technology. refs present numerical investigation of airframe-integrated, three- (AIAA PAPER 89-2673) dimensional fixed-geometry inlets for hypersonic operation The steady incompressible laminar Navier-Stokes equations to Mach 6. The inlet configurations examined are similar to Trexler’s have been solved in an axisymmetric coordinate system in order (1975) designs, with and without struts; two of these to analyze the performance and flowfield of a ducted propeller. In three-dimensional inlet configurations, one possessing struts and the method, the duct and nacelle are considered as axisymmetric the other without these, were experimentally tested in the solid bodies and are represented by blocked off regions in the freestream Mach 2-6 range. Experimental results are compared flow with all three velocity components set to zero. Results are with those obtained numerically. O.C. presented for propellers with several advance ratios. The flow through the duct alone is calculated in order to assess changes ~a9-47010# in the the surface pressure distribution of the shroud due to the MACH 4 TESTING OF SCRAMJET INLET MODELS propeller. The present method takes into account all the TAKESHI KANDA, TOMOYUKI KOMURO, GORO MASUYA, KENJI interference effects between the duct, the propeller, and the KUDO, ATSUO MURAKAMI (National Aerospace Laboratory, nacelle, and it can be used to optimize blade tip-clearance and Kakuda, Japan) et al. AIAA, ASME, SAE, and ASEE, Joint lip shape. R.R. Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 9 p. refs ~a9-47004# (AIAA PAPER 89-2680) COMPUTATIONAL MODELING OF AXISYMMETRIC Six scramjet inlet models were tested in a Mach 4 wind tunnel. PROPELLER-HULL INTERACTION IN SLENDER LOW DRAG Wall pressure was measured, pitot pressure was measured at the BODIES throat, and schlieren photographs were taken. Parameters of these R. DECHER (Washington, University, Seattle), J. C. HERMANSON models are side plate sweep angle, contraction ratio, and cowl (United Technologies Research Center, East Hartford, CT), and geometry. The shock pattern inside one of the models as shown P. Y. HO AIAA, ASME, SAE, and ASEE, Joint Propulsion by schlieren photographs coincides with calculations. Both mass Conference, 25th, Monterey, CA, July 10-13, 1989. 12 p. refs capture ratio and total pressure recovery are 50 - 70 percent. (Contract NO0014-81 -K-0095) There seems to be an optimum sweep angle and an optimum (AIAA PAPER 89-2674) cowl length for maximum total pressure recovery. Author Computational approaches to modeling the propeller-hull interaction for low drag hull shapes are examined. Inviscid ~a9-47oii# interaction effects is modeled as a simple combination of INVISCID ANALYSIS OF A DUAL MODE SCRAMJET INLET sources/sinks and an actuator disk. A full Navier-Stokes equations Y.4. HSIA, BEN GROSS, and J. PAUL ORTWERTH (Rockwell is deemed necessary to include viscous effects. Unreliable results International Corp., Rocketdyne Div., Canoga Park, CA) AIAA, obtained from the axial source technique are discussed. The ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, solution of the full Navier-Stokes equations is seen to be sensitive Monterey, CA, July 10-13, 1989. 9 p. to grid nonorthogonality when the grid is concentrated near the (AIAA PAPER 89-2681) surface of the low drag body. This phenomenon needs to be A three-dimensional inviscid flow computation was made on better understood before this technique can be successfully applied the Marquardt dual mode scramjet inlet which was tested for Air to model the propeller-hull interaction on low drag bodies. Force Aero-Propulsion Laboratory in 1966. An Euler solver based Author on high accuracy TVD scheme was used to carry out the analysis. The objective was to establish three-dimensional scramjet inlet ~a9-4700~ CFD capability and to evaluate the applicability of Euler solutions BOW SHOCK MATCHING WITH VISCOUS EFFECTS ON for inlet performance calculation. The computations were made HYPERSONIC FOREBODIES for freestream Mach numbers 2 and 5. A post-processor was MARK J. LEWIS (Maryland, University, College Park) and DANIEL developed to calculate the inlet performance. Comparison between E. HASTINGS (MIT, Cambridge, MA) AIAA, ASME, SAE, and computed and available test data showed that Euler analysis was ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, able to predict the trend of the inlet performance and provide 1989. 16 p. Research supported by the Charles Stark Draper insight of the flow field. ‘ Author Laboratory, Inc. refs (AIAA PAPER 89-2678) ~a9-4701~ The desire to match the bow shock of a hypersonic vehicle to SURGE AND ROTATING STALL IN AXIAL COMPRESSORS the lip of the engine cowl provides for a design constrain on the H. ISH11 and Y. KASHIWABARA (Hitachi, Ltd., Mechanical hypersonic forebody. For inviscid flow, it is shown that there is Engineering Research Laboratory, Tsuchiura, Japan) AIAA, ASME, one particular wedge angle which provides for shock matching SAE, and ASEE, Joint Propulsion Conference, 25th. Monterey, which is insensitive to steady-state changes in vehicle angle of CA, July 10-13, 1989. 10 p. refs attack, though it is not possible to match against changes in flight (AIAA PAPER 89-2683) Mach number. The angle of attack sensitivity of a hypersonic This paper briefly summarizes the features of surge and rotating
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stall in multistage compressors based on test results, and describes stall. Overall and individual stage performance comparisons a numerical method for representing both surge and rotating stall between model and experimental results exhibit excellent in axial compressors for practical application. The test results show agreement. Both sets of results have indicated extensive possibilities of simultaneous occurrence of surge and rotating stall. compressor-recovery hysteresis in part-speed operation, largely The present method, expanding on a theoretical model by Moore influenced by staging effects. The model predicts improved (1985) which assumes inlet distortion, aims to represent unsteady recoverability and hysteresis reduction through enlargement of the behaviors observed in real machines. The method deals with the rear stage flowpath, and the addition of a bleed outflow downstream fluid equations of two-dimensional unsteady incompressible flow of the middle stages. O.C. in the axial and circumferential directions. A set of differential equations is solved by Galerkin’s method with circumferential flow A89-47026’# National Aeronautics and Space Administration. distortion expressed in the form of a high-order Fourier series to Lewis Research Center, Cleveland, OH. take into account the nonlinearity of the equations about the angular LARGE SCALE ADVANCED PROPELLER BLADE PRESSURE variable. The method is used to evaluate various relations, including DISTRIBUTIONS - PREDICTION AND DATA that between compressor parameters and unsteady behavior M. NALLASAMY, 0. YAMAMOTO, S. WARS1 (NASA, Lewis modes, and that between inlet distortion and onset point. Finally, Research Center; Sverdrup Technology, Inc., Cleveland, OH), and the usefulness of the method is examined by comparisons with L. J. BOBER (NASA, Lewis Research Center, Cleveland, OH) test results obtained from a 3-stage axial compressor. Author AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA. July 10-13, 1989. 22 p. refs A89-47014# (AIAA PAPER 89-2696) ROTATING STALL PERFORMANCE AND RECOVERABILITY Two Euler analysis techniques, finite difference and finite OF A HIGH-SPEED 10-STAGE AXIAL-FLOW COMPRESSOR volume, are employed to predict the blade surface pressure W. W. COPENHAVER (USAF, Aero Propulsion and Power distributions of a large scale advanced propeller. The predicted Laboratory, Wright-Patterson AFB, OH) and T. H. OKllSHl (Iowa pressure distributions are compared with wind tunnel data. Both State University of Science and Technology, Ames) AIAA, ASME, techniques produced blade pressure distributions which are in fairly SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, good agreement with the data over the range of test Mach numbers CA, July 10-13, 1989. 17 p. Research supported by USAF. refs of 0.2 to 0.78. However, the numerical simulations fail to predict (AIAA PAPER 89-2684) correctly the measured pressure distributions for the low Mach A high-speed, 10-stage compressor component was tested number, high power case which seem to have a leading edge while operating in-stall to investigate parameters that affect the vortex. A discussion of the compressibility effects is also overall recoverability of a multistage compressor. The compressor presented. Author was tested at different in-stall operating conditions by varying compressor shaft speed, discharge throttle, and variable geometry A89-47027# settings to determine the effect of each variable on rotating-stall HOT WIRE MEASUREMENTS DOWNSTREAM OF A PROP-FAN performance and recoverability. Test results suggest that the stall T. G. TILLMAN, J. C. SIMONICH, and J. H. WAGNER (United cell may not extend the full length of the compressor but instead Technologies Research Center, East Hartford, CT) AIAA, ASME, can be confined to a portion, here the rear stages, of the SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, compressor. Author CA, July 10-13, 1989. 20 p. Research supported by United Technologies Corp. refs A89-47016# (AIAA PAPER 89-2698) MODEL PREDICTIONS OF FAN RESPONSE TO INLET The present analysis of a propfan’s near-field aerodynamics TEMPERATURE TRANSIENTS AND SPATIAL TEMPERATURE examined the wake structure of a contrarotating propfan model DlSTORTfON operating in the single-rotation mode, in order to obtain benchmark CONSTANCE A. DOWLER. KEITH M. BOYER, and NORMAN POTI data defining the rotor-synchronized downstream flowfield for (USAF, Aero Propulsion and Power Laboratory, Wright-Patterson simulated cruise conditions. Three components of blade- AFB, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion synchronized periodic velocity were obtained at various radial Conference, 25th, Monterey, CA, July 10-13, 1989. 10 p. refs locations over the course of blade passage, using high frequency 4AIAA PAPER 89-2686) response hot-wire anemometry; attention was given to the blade-tip A three-stage axial flow fan model was used to study the region and the leading-edge vortex features. The existence of a effects of inlet temperature transients (with and without distortion), vortex core axial-velocity defect is documented. O.C. steady-state spatial temperature distortion, and instantaneous temperature drop on fan performance. When circumferential A89-47028# distortion was present, the critical temperature rise (the NAVIER-STOKES SIMULATIONS AROUND A PROPFAN USING face-averaged temperature rise just prior to system instability) was HIGHER-ORDER UPWIND SCHEMES found to be greater for larger circumferential extents and lower CHUlCHl ARAKAWA (Tokyo, University, Japan), SHIGERU SAITO, magnitudes of distortion. Larger circumferential extents and lower HlROSHl KOBAYASHI, and YUlCHl MATSUO (National Aerospace magnitudes were also shown to result in less loss in stall margin. Laboratory. Chofu, Japan) AIAA, ASME, SAE, and ASEE, Joint The results have been used to derive procedures for the safe Propulsion Conference, 25th. Monterey, CA, July 10-13, 1989. 10 and efficient operation of a hydrogen fueled burner. R.R. p. refs (AIAA PAPER 89-2699) A89-47017# Viscous transonic flows around a typical single-rotation Propfan MODEL PREDICTIONS FOR IMPROVED RECOVERABILITY OF are simulated by solving time-averaged Navier-Stokes equations. A MULTISTAGE AXIAL-FLOW COMPRESSOR An implicit finite-difference code based on a higher-order upwind KEITH M. BOYER (USAF, Aero Propulsion and Power Laboratory, TVD formulation with a practical two-equation model of turbulence Wright-Patterson AFB, OH) and WALTER F. O’BRIEN (Virginia is developed and applied. Computations are performed at cruise Polytechnic Institute and State University, Blacksburg) AIAA, conditions of Mach number of 0.8. Viscous flow field structures ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, around the propeller are made clear in detail. Predicted Monterey, CA. July 10-13, 1989. 13 p. refs aerodynamic performances show good agreement with experimental (AIAA PAPER 89-2687) data. Author A ten-stage axial flow compressor rig recently tested at Wright-Patterson AFB Compressor Research Facility can be A89-47156*# Toledo Univ.. OH. represented by means of a one-dimensional stage-by-stage model RAREFIED GAS FLOW THROUGH TWO-DIMENSIONAL employing a control-volume approach to the simulation of steady NOZZLES state and transient system operation, including surge and rotating KENNETH J. DE WITT, DUEN-REN JENG, THE0 G. KEITH, JR.
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(Toledo, University, OH), and CHAN-HONG CHUNG AIAA, ASME, concerning the control of shock boundary layer interactions in SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, supersonic inlets by means of boundary-bleed has extablished CA, July 10-13, 1989. 12 p. refs that surface and pitot pressure data support the possibility of (Contract NAG3-577) boundary layer separation control. Contradictions are noted, (AIAA PAPER 89-2893) however, between several different investigations' results on the A kinetic theory analysis is made of the flow of a rarefied gas effectiveness of bleed configurations at the shock, upstream of from one reservoir to another through two-dimensional nozzles the shock, or downstream of the shock, in controlling separation. with arbitrary curvature. The Boltzmann equation simplified by a Turbulence measurements indicate significant changes in model collision integral is solved by means of finite-difference turbulence across the shock boundary layer interaction, especially approximations with the discrete ordinate method. The physical if the flow separates. O.C. space is transformed by a general grid generation technique and the velocity space is transformed to a polar coordinate system. A A89-47184# numerical code is developed which can be applied to any BLOCK-STRUCTURED SOLUTION OF TRANSONIC FLOWS two-dimensional passage of complicated geometry for the flow AROUND WING/PYLON/NACELLE CONFIGURATIONS regimes from free-molecular to slip. Numerical values of flow A. ECER, J. T. SPYROPOULOS (Purdue University, Indianapolis, quantities can be calculated for the entire physical space including IN), R. K. ROUT, and S. S. BADESHA (GE Aircraft Engines, both inside the nozzle and in the outside plume. Predictions are Cincinnati, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion made for the case of parallel slots and compared with existing Conference, 25th, Monterey, CA, July 10-13, 1989. 8 p. Research literature data. Also, results for the cases of convergent or divergent supported by IBM Corp. refs slots and two-dimensional nozzles with arbitrary curvature at (AIAA PAPER 89-2940) arbitrary knudsen number are presented. Author Block-structured finite element grid generation is combined with Euler solution schemes to analyze the flows around isolated and A89-47160'# Analytical Services and Materials, Inc., Hampton, installed nacelles at incidence. In the present method, the solution VA. domain is divided in a structured distribution of subdomains, and THE APPLICATION OF 3D MARCHING SCHEME FOR THE the geometry of each block is then approximated by a finite element PREDICTION OF SUPERSONIC FREE JETS superelement of mixed order in order to generate grids of KHALED S. ABDOL-HAMID (Analytical Services and Materials, Inc., second-order continuity in each block. Geometric irregularities such Hampton, VA) AIAA, ASME, SAE, and ASEE, Joint Propulsion as void blocks, slits, or coupled surfaces are included at the block Conference, 25th, Monterey, CA, July 10-13, 1989. 10 p. refs boundaries. Following a Clebsch transformation of the velocity (Contract NASl-18599) field, the equations for the conservation of mass and entropy are (AIAA PAPER 89-2897) solved in each block, relaxing boundary conditions at the interblock A modified version of the upwind flux-difference scheme of boundaries at every iteration. R.R. Roe for supersonic flow solution is described. This efficient iterative Space Marching Scheme (SMS) is used to solve the A89-47185# three-dimensional, Reynolds-averagedNavier-Stokes equations, for STEADY-STATE AND TIME-DEPENDENT AERODYNAMICS IN underexpanded and overexpanded supersonic free jet with a single AN ANNULAR TURBINE CASCADE OPERATING AT HIGH time sweep. Comparisons with experimental data and the SUBSONIC MACH NUMBERS Parabolized Navier-Stokes (PNS) solutions are presented. These A. EZZAT, T. H. FRANSSON, and F. JOLLES (Lausanne, Ecole results show that the present scheme gives good agreement with Polytechnique Federale, Switzerland) AIAA, ASME, SAE, and experimental data in less computer time and the convergence ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, history of the SMS is much faster than the PNS solution. Author 1989. 17 p. Research supported by Ansaldo Componenti S.p.A. and Franco Tosi lndustriale S.p.A. refs A89-47 177# (AIAA PAPER 89-2941) REDUCTION OF 1-P AERODYNAMIC LOADS ON TRACTOR An experimental investigation has been conducted of the AIRCRAFT ENGINE INSTALLATIONS steady-state and time-dependent aerodynamic characteristics of a F. L. GATES and A. A. SMAILYS (Pratt and Whitney Canada, low-pressure steam turbine blade's two-dimensional section, where Mississauga) AIAA, ASME, SAE, and ASEE, Joint Propulsion the section in question is from the upper part of the blade, where Conference, 25th, Monterey, CA, July 10-13, 1989. 7 p. the nominal flow conditions are subsonic at the inlet and supersonic (AIAA PAPER 89-2924) at the outlet. The experimental steady-state and time-dependent Sources of asymmetry in the flow of air through a propeller aerodynamic data presented correspond to three steady-state are reviewed, and the flight conditions giving rise to high loadings, with a total inlet flow angle variation of 14 deg. The once-per-revolution (1P) cyclic loads are investigated. An algorithm results obtained indicate that the blading, in its present form, is for the prediction of 1-P moments and forces for any composition susceptible to blade flutter in the first bending mode. The of wings and nacelles is proposed. The predictions agree well leading-edge form of the blade is identified as one of the primary with inflow angles and 1-P moments at low speeds determined reasons for the undesirable unsteady flow effects. O.C. experimentally in a wind tunnel, but are somewhat compromised at moderate and high speeds due to cross-flow deficiencies in A89-47187'# National Aeronautics and Space Administration. the algorithm. It is pointed out that this shortcoming can be Lewis Research Center, Cleveland, OH. overcome by introducing the effect of cross flow induced by AVERAGE-PASSAGE SIMULATION OF COUNTER-ROTATING span-wise loading and its mutually-dependent effect on the PROPFAN PROPULSION SYSTEMS AS APPLIED TO CRUISE presence and placement of nacelles into the algorithm. R.R. MISSILES RICHARD A. MULAC (NASA, Lewis Research Center; Sverdrup A89-47183# Technology, Inc., Cleveland, OH), JON C. SCHNEIDER (McDonnell SURVEY AND ASSESSMENT OF VALIDATION DATA BASE Douglas Astronautics Co., Saint Louis, MO), and JOHN J. FOR SHOCKWAVE BOUNDARY LAYER INTERACTIONS IN ADAMCZYK (NASA, Lewis Research Center, Cleveland, OH) SUPERSONIC INLETS AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, A. HAMED (Cincinnati, University, OH) and J. S. SHANG (USAF, Monterey, CA, July 10-13, 1989. 11 p. Previously announced in Flight Dynamics Laboratory, Wright-Patterson AFB, OH) AIAA, STAR as N89-23416. refs ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, (AIAA PAPER 89-2943) Monterey, CA, July 10-13, 1989. 17 p. Research supported by Counter-rotating propfan (CRP) propulsion technologies are UES. refs currently being evaluated as cruise missile propulsion systems. (AIAA PAPER 89-2939) The aerodynamic integration concerns associated with this A comprehensive critical evaluation of extant experimental data application are being addressed through the computational
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modeling of the missile body-propfan flowfield interactions. The A89-47360# work described in this paper consists of a detailed analysis of the INVESTIGATION OF THE FLOW STRUCTURE AROUND A aerodynamic interactions between the control surfaces and the RAPIDLY PITCHING AIRFOIL propfan blades through the solution of the average-passage MIGUEL R. VISBAL and J. S. SHANG (USAF, Wright Aeronautical equation system. Two baseline configurations were studied, the Laboratories, Wright-Patterson AFB, OH) AlAA Journal (ISSN control fins mounted forward of the counter-rotating propeller and 0001-1452), vol. 27. Aug. 1989, p. 1044-1051. Previously cited in the control fins mounted aft of the counter-rotating propeller. In issue 19, p. 2942, Accession no. A87-44951. refs both cases, control fin-propfan separation distance and control fin deflection angle were varied. Author A89-47372*# San Diego State Univ., CA. AERODYNAMICS OF HIGH-LIFT, LOW-ASPECT-RATIO A89-47351"# Loral Defense Systems, Akron, OH. UNSWEPT WINGS ANALYSIS OF LOW REYNOLDS NUMBER SEPARATION JOSEPH KATZ (San Diego State University, CA) AlAA Journal BUBBLES USING SEMIEMPIRICAL METHODS (ISSN 0001-1452), vol. 27, Aug. 1989, p. 1123. 1124. refs GORDON S. SCHMIDT (Loral Corp., Akron, OH) and THOMAS J. (Contract NCC2-458) MUELLER (Notre Dame, University, IN) AIM Journal (ISSN It is presently demonstrated that highly cambered, low aspect 0001-1452). vol. 27, Aug. 1989, p. 993-1001. Research supported ratio airfoil configurations can be neither experimentally nor by the University of Notre Dame. refs numerically developed on the basis of two-dimensional methods; (Contract NSG-1419) the strong dependency of airfoil shape on aspect ratio requires The formation and growth of transitional separation bubbles the definition of a planform to be conducted first, in order to can significantly affect boundary-layer development on airfoils serve as input for three-dimensional optimization methods. It is operating at low chord Reynolds numbers. Of primary concern is found that even the simplified three-dimensional computational the change in boundary-layer thickness between laminar separation method presently employed can accelerate a multielement-airfoil and turbulent reattachment. This can be estimated using wing development. O.C. semiempirical methods, such as the one devised by Horton (1968), which are based on solutions to the integral forms of the A89-47373# boundary-layer equations. The applicability of these methods at DIFFUSER PERFORMANCE OF TWO-STREAM SUPERSONIC low Reynolds numbers was investigated using hot-wire WIND TUNNELS measurements of bubbles formed on an NACA 66(3)-018 airfoil at DlMlTRl PAPAMOSCHOU (California Institute of Technology, chord Reynolds numbers of 50,000-200.000. The momentum Pasadena) AlAA Journal (ISSN 0001-1452). vol. 27, Aug. 1989, thickness growth between separation and transition was found to p. 1124-1 127. Research supported by the Rockwell International be similar to that predicted for a laminar half-jet and appears to Foundation Trust. refs be influenced by the momentum thickness Reynolds number at (Contract NO001 4-85-K-0646) separation. This parameter also was found to have a noticeable A theoretical model has been developed which determines the effect on the Reynolds number based on the length of a bubble's inviscid, steady-state diffuser performance of a wind tunel having laminar portion. Author two plane parallel supersonic streams that come into contact downstream of a splitter plate to form an infinitely thin interface. A89-47352# Model predictions are applicable to the design and operation of FLOW STRUCTURE AND SCALING LAWS IN LATERAL both two-stream supersonic wind tunnels and aircraft engines in WING-TIP BLOWING which flow mixing occurs at supersonic speeds. The calculations C. S. LEE, D. TAVELLA, N. J. WOOD, and L. ROBERTS (Stanford presented reflect idealized conditions under which the shear-layer University, CA) AlAA Journal (ISSN 0001-1452), vol. 27, Aug. and boundary layer growth rates are taken to be zero. O.C. 1989, p. 1002-1007. Previously cited in issue 17, p. 2462, Accession no. A86-37831. refs A89-47376# UNSTEADY TRANSITION LOCATION A8947356# KENNETH F. STETSON (USAF, Wright Aeronautical Laboratories, VISCOUS AERODYNAMIC ANALYSIS OF AN OSCILLATING Wright-Patterson AFB, OH) AlAA Journal (ISSN 0001-1452). vol. FLAT-PLATE AIRFOIL 27, Aug. 1989, p. 1135-1137. refs LINDA M. SCHROEDER and SANFORD FLEETER (Purdue Results were obtained in the USAF Flight Dynamics Laboratory University. West Lafayette, IN) AlAA Journal (ISSN 0001 -1452), Mach 6 wind tunnel which furnish additional evidence of nosetip vol. 27, Aug. 1989, p. 1021-1022. Abridged. Research sponsored threshold conditions that determine when a nosetip will generate by USAF. Previously cited in issue 07, p. 928, Accession no. low frustum transition Reynolds numbers. The example treated A88-22092. also illustrates a case of unsteady transition location for this early frustum transition condition. Transition moved steadily rearward A89-47357'# Washington Univ., Seattle. with increasing time; in 2.5 sec, both sides of the model has a FURTHER EXPERIMENTS ON SUPERSONIC TURBULENT completely laminar boundary layer. O.C. FLOW DEVELOPMENT IN A SQUARE DUCT D. 0. DAVIS and F. B. GESSNER (Washington, University, NE925117*# National Aeronautics and Space Administration. Seattle) AlAA Journal (ISSN 0001-1452), vol. 27, Aug. 1989, p. Langley Research Center, Hampton, VA. 1023-1030. Previously cited in issue 18, p. 2806, Accession no. EFFECT OF MILLING MACHINE ROUGHNESS AND WING A87-42362. refs DIHEDRAL ON THE SUPERSONIC AERODYNAMIC (Contract NCA2-IR-850-401) CHARACTERISTICS OF A HIGHLY SWEPT WING CHRISTINE M. DARDEN Washington Aug. 1989 88 p A89-47358'# Old Dominion Univ., Norfolk, VA. (NASA-TP-2918; L-16546; NAS 1.60:2918) Avail: NTlS HC UNSTEADY TRANSONIC AIRFOIL COMPUTATION USING A05f MF A01 CSCL 01 f 1 IMPLICIT EULER SCHEME ON BODY-FIXED GRID An experimental investigation was conducted to assess the OSAMA A. KANDIL and H. ANDREW CHUANG (Old Dominion effect of surface finish on the longitudinal and lateral aerodynamic University, Norfolk, VA) (Developments in theoretical and applied characteristics of a highly-swept wing at supersonic speeds. A mechanics. Volume 14; Proceedings of the Fourteenth study of the effects of wing dihedral was also made. Included in Southeastern Conference on Theoretical and Applied Mechanics, the tests were four wing models: three models having 22.5 degrees Biloxi, MS, Apr. 18, 19, 1988, p. 37-46) AlAA Journal (ISSN of outboard dihedral, identical except for surface finish, and a 0001-1452), vol. 27, Aug. 1989, p. 1031-1037. Previously cited in zero-dihedral, smooth model of the same planform for reference. issue 01, p. 0006, Accession no. A89-11153. refs Of the three dihedral models, two were taken directly from the (Contract NAG1-648) milling machine without smoothing: one having a maximum scallop
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height of 0.002 inches and the other a maximum scallop height to angle-of-attack. The propeller net efficiency, though, was fairly of 0.005 inches. The third dihedral model was handfinished to a insensitive to any changes in the propeller flowfield conditions smooth surface. Tests were conducted in Test Section 1 of the near the take-off target operating points. Author Unitary Plan Wind Tunnel at NASA-Langley over a range of Mach numbers from 1.8 to 2.8, a range of angle of attack from -5 to 8 N89-25122*# Kansas Univ. Center for Research, Inc., degrees, and at a Reynolds numbers per foot of 2 x lO(6). Selected Lawrence. data were also taken at a Reynolds number per foot of 6 x lO(6). SPANWISE LIFT DISTRIBUTIONS AND WAKE VELOCITY Drag coefficient increases, with corresponding lift-drag ratio SURVEYS OF A SEMI-SPAN WING WITH A DISCONTINUOUS decreases were the primary aerodynamic effects attributed to TWIST increased surface roughness due to milling machine grooves. These HlROYUKl KUMAGAI May 1989 208 p drag and lift-drag ratio increments due to roughness increased as (Contract NCC2-175) Reynolds number increased. Author (NASA-CR-177532; NAS 1.26:177532) Avail: NTlS HC AlO/MF A01 CSCL 01/1 N89-25119*# National Aeronautics and Space Administration. A wind tunnel test was conducted in the NASA-Ames 7 x 10 Lewis Research Center, Cleveland, OH. ft wind tunnel to investigate the lift distribution on a semispan NUMERICAL ANALYSIS OF SUPERSONIC FLOW THROUGH wing with a discontinuous change in spanwise twist. The semispan OSCILLATING CASCADE SECTIONS BY USING A wing had a tip with an adjustable pitch angle independent on the DEFORMING GRID inboard section pitch angle simulating the free tip rotor blade when DENNIS L. HUFF and T. S. R. REDDY (Toledo Univ., OH.) its free tip is at a deflected position. The spanwise lift distribution 1989 18 p Presented at the 25th Joint Propulsion Conference, over the wing and the tip were measured and three component Monterey, CA, 10-12 Jul. 1989; cosponsored by the AIAA, ASME, velocity surveys behind the wing were obtained with a 3-D laser SAE and ASEE Doppler velocimeter (LV) with the wing at one angle of attack (NASA-TM-102053; E-4805; NAS 1.15:102053; AIAA-89-2805) and the tip deflected at different pitch angles. A six-component Avail: NTlS HC AOWMF A01 CSCL 01 11 internal strain gage balance was also used to measure total forces A finite difference code was developed for modeling inviscid, and moments on the tip. The 3-D lift was computed from the 2-0 unsteady supersonic flow by solution of the compressible Euler liff distributions obtained from the LV and from the strain gage equations. The code uses a deforming grid technique to capture balance. The results from both experimental methods are shown the motion of the airfoils and can model oscillating cascades with to be in agreement with predictions made by a steady, 3-D panel any arbitrary interblade phase angle. A flat plate cascade is code, VSAERO. Author analyzed, and results are compared with results from a small-perturbation theory. The results show very good agreement N89-25125# Deutsche Forschungs- und Versuchsanstalt fuer for both the unsteady pressure distributions and the integrated Luft- und Raumfahrt, Goettingen (Germany, F.R.). Abteilung force predictions. The reason for using the numerical Euler code Instationaere Aerodynamik. over a small-perturbation theory is the ability to model real airfoils TWO-DIMENSIONAL ELLIPTIC GRID GENERATION FOR that have thickness and camber. Sample predictions are presented AIRFOILS AND CASCADES for a section of the rotor on a supersonic throughflow compressor VOLKER CARSTENS Dec. 1988 77 p designed at NASA Lewis Research Center. Preliminary results (DFVLR-FB-88-52; ISSN-0171-1342; ETN-89-94638) Avail: NTlS indicate that two-dimensional, flat plate analysis predicts HC A05/MF A01; DFVLR, VB-PL-DO, Postfach 90 60 58, 5000 conservative flutter boundaries. Author Cologne, Fed. Republic of Germany, DM 28.50 Based on the solution of two coupled transformed Poisson equations, a method to generate two-dimensional grids for airfoils N89-25121*# National Aeronautics and Space Administration. and cascades is presented. With the method it is possible to Lewis Research Center, Cleveland, OH. control line spacing and intersection angle of the grid lines at the LOW-SPEED WIND TUNNEL PERFORMANCE OF HIGH-SPEED physical boundaries by a particular choice of inhomogeneous terms COUNTERROTATION PROPELLERS AT ANGLE-OF-AlTACK in the Poisson equations. The numerical solution of the grid CHRISTOPHER E. HUGHES and JOHN A. GAZZANIGA (Sverdrup generating equations is performed by a Newton relaxation algorithm Technology, Inc., Cleveland, OH.) 1989 47 p Presented at which significantly improves stability and convergence of the the 25th Joint Propulsion Conference, Monterey, CA, 10-12 Jul. numerical solution compared to the classical SLOR method. 1989; cosponsored in part by AIAA. ASME, SAE, and ASEE Examples of airfoil and cascade grids demonstrate the efficiency (NASA-TM-102292; E-4883; NAS 1.I 511 02292; AIAA-89-2583) of the existing procedure. ESA Avail: NTlS HC AO3/MF A01 CSCL 01 /1 The low-speed aerodynamic performance characteristics of two advanced counterrotation pusher-propeller configurations with N89-25126# Technische Hochschule, Aachen (Germany, F.R.). cruise design Mach numbers of 0.72 were investigated in the Sonderforschungsbereich 25. NASA Lewis 9- by 15-Foot Low-Speed Wind Tunnel. The tests VORTEX FLOWS IN FLYING TECHNIQUE were conducted at Mach number 0.20, which is representative of [WIRBELSTROEMUNGEN IN DER FLUGTECHNIK] the aircraft take-offllanding flight regime. The investigation 1988 378 p In GERMAN IUTAM Symposium: On Fundamental determined the effect of nonuniform inflow on the propeller Aspects of Vortex Motion held in 1987 performance characteristics for several blade angle settings and (ETN-89-94428) Avail: NTlS HC A17/MF A01 a range of rotational speeds. The inflow was varied by yawing the Flows with free vortices were investigated by the integration of propeller model to angle-of-attack by as much as plus or minus the conservation equations. The mechanisms leading to vortex 16 degrees and by installing on the counterrotation propeller test breakdown were clarified. Velocity fields in vortex structures were rig near the propeller rotors a model simulator of an aircraft engine measured. Strongly unsteady vortex fields at elastic helicopter rotor support pylon and fuselage. The results of the investigation blades were studied. The interaction between compression shocks indicated that the low-speed performance of the counterrotation and vertical flows, the dissipation of vortex power in longitudinal propeller configurations near the take-off target operating points flow on wings, and vortex structures in the wake of transonic were reasonable and were fairly insensitive to changes in model flow about profiles were investigated. Flow field changes of wing angle-of-attack without the aircraft pylon/fuselage simulators profiles in unsteady flow and unsteady flow on profiles in a installed on the propeller test rig. When the aircraft pylon/fuselage liquid tunnel are treated. The effect of winglets on the loading simulators were installed, small changes in propeller performance mechanics and wing assembly reactions and the reduction of the were seen at zero angle-of-attack, but fairly large changes in total adverse effects of wing tip vortices by modifying the wing tips power coefficient and very large changes of aft-to-forward-rotor were studied. torque ratio were produced when the propeller model was taken ESA
653 02 AERODYNAMICS
N89-25129# Technische Hochschule, Aachen (Germany, F.R.). by flow velocity changes. Unsteady pressure distributions and UNSTEADY PHENOMENA ON DELTA WINGS WITH boundary layer profiles were measured in a wind tunnel. Despite PARTIALLY BROKEN-DOWN VORTEX REGIONS the different test conditions, the fundamental similarity between [INSTATIONAERE VORGAENGE AN DELTAFLUEGELN MIT the flow in the wind and the water tunnel was demonstrated. The TElLWElSE AUFGEPLATZTEN WIRBELBEREICHEN] measurement of the unsteady pressure distributions allows the BERND STECKEMETZ ln its Vortex Flows in Flying Technique determination of the unsteady lift coefficient. A force and moment p 41-68 1988 In GERMAN measurement was performed to determine the aerodynamic forces Avail: NTlS HC A17/MF A01 on the profile. ESA Delta wings were investigated in water and wind tunnels to clarify unsteady flow phenomena in the vortex system of the delta wing occurring during wing maneuvers and in gust fields. The N89-25137# Technische Hochschule, Aachen (Germany, F.R.). investigations in the water tunnel concentrated on the visualization EFFECT OF WINGLETS ON LOADING MECHANICS AND of the leading vortex; the pictures show the temporal shift of the WING ASSEMBLY REACTIONS [EINFLUSS VON WINGLETS vortex and breakdown positions for the different test parameters. AUF DIE BELASTUNGS MECHANIK UND The pressure distribution measurements in the subsonic wind tunnel TRAGWERKSREAKTIONEN] can be directly compared with the water tunnel test data, while GRAHAM BUTand ATHANASSIOS DAFNIS In its Vortex Flows the force and moment measurements in steady flow provide data in Flying Technique p 223-260 1988 In GERMAN on the total wing. Assuming quasi-stationarity, the effects of Avail: NTlS HC A17/MF A01 breakdown and heading phenomena on the force and moment The structural mechanical effects of winglets on the lifting balance of the wing were assessed using the coupled water and structure of wings were investigated on the laboratory aircraft wind tunnel data, and verified by unsteady force and moment Morane Rallye. The pressure distribution on the Morane wing was measurements. ESA calculated. A six-component force measurement was performed on the Morane model with and without winglets. The structural N89-25131# Technische Hochschule, Aachen (Germany, F.R.). data of the Morane wings were obtained. Flutter calculations with STRONGLY UNSTEADY VORTEX FIELDS AT ELASTIC three degrees of freedom were made. The unsteady aerodynamic HELICOPTER ROTOR BLADES [STARK INSTATIONAERE forces were measured on the vibration test stand in the wind WIRBELFELDER AN ELASTISCHEN tunnel. ESA HUBSCHRAUBERROTORBLAETTERN3 ln its Vortex Flows in Flying Technique p K. GRUENSPAHN N89-25138# Technische Hochschule, Aachen (Germany, F.R.). 89-113 1988 In GERMAN DAMPING OF WING TIP VORTEX SYSTEMS BY THE Avail: NTlS HC A17/MF A01 MODIFICATION OF THE WING TIPS [ABSCHWAECHUNG VON Unsteady flow phenomena at helicopter rotor blades during RANDWIRBELSYSTEMENDURCH MODlFlKATlON DER forward flight were studied in the framework of two-dimensional FLUEGELSPITZEN] profile theory. The flow medium was assumed to be compressible, T. SCHERER and T. VlTTlNG ln its Vortex Flows in Flying inviscid, and heat-conduction free. Starting from the Euler Technique p 261-287 1988 In GERMAN equations, a numerical bicharacteristic method of a second order Avail: NTlS HC A17/MF A01 for the calculation of two-dimensional, unsteady, compressible flow The reduction of the adverse effects of wing tip vortices by was developed, allowing the simulation of flow about accelerating the design of wing tips and by active and passive control of the profiles. Fast angle-of-attack oscillations of a profile and profile evolution of the vortex orbit, was investigated. The aim was to motions with translatory acceleration were analyzed; the results prevent the formation of single vortices or the perturbation of are in good agreement with the Jameson stationary transonic ordered wortex structures by self-induction. The vortex behavior potential method. ESA was described using water tunnel experiments and simulation calculations. The results show that the highest circumferential N89-25134# Technische Hochschule, Aachen (Germany, F.R.). velocity in the wing tip vortex can be reduced by more than 60 VORTEX STRUCTURES IN THE WAKE OF TRANSONIC FLOW percent if the vortex formation process can be hindered or if the ABOUT PROFILES [WIRBELNSTRUKTUREN IM NACHLAUF ordered vortex structures can be perturbed by self-induction. SCHALLNAH ANGESTROEMTER PROFILE] Experiments and simulations show that behind semi-delta winglets H.-J. ROMBERG In its Vortex Flows in Flying Technique p 143-157 with small angle of attack, double vortices are built which lead to 1988 In GERMAN strongly reduced circumferential velocities. Winglets were Avail: NTlS HC A17/MF A01 developed for the Dromedar aircraft, providing a clearly improved Measurements were performed on wing profiles in transonic spray distribution. ESA and supersonic wind tunnels with a view to the investigation of the mechanisms responsible for the formation of vortex structures. The measuring chambers of the wind tunnels are equipped with N89-25139# Technische Hochschule, Aachen (Germany, F.R.). adaptive walls to minimize wall interferences. The pressure MECHANICAL REACTION OF WINGS MOVING THROUGH A distributions with and without adaptive walls were measured and VORTEX REGION [MECHANISCHE REAKTIONEN VON compared with Navier-Stokes calculations. Pressure distribution and FLUEGELN, DIE DURCH EIN WIRBELGEBIET BEWEGT pressure variations in the wake were also measured. The WERDEN] measurements were correlated with the numerical evaluation of DIETER HOLZDEPPE and HANS-WERNER LINDERT ln its Vortex Mach-Zehnder recordings, which clarifies the mechanisms and the Flows in Flying Technique p 289-312 1988 In GERMAN quantities affecting the formation of vortex structures. ESA Avail: NTlS HC A17/MF A01 The dynamic reactions of rotor blades on loading by vortex N89-25135# Technische Hochschule, Aachen (Germany, F.R.). perturbations were investigated. The principal item in the structural FLOW ABOUT TRAILING EDGES IN UNSTEADY FLOW dynamic calculations is the reconstruction of the exciting functions [HINTERKANTENUMSTROEMUNG IN INSTATIONAERER from a few measured structural responses such as cutting ANSTROEMUNG] moments, displacements, and accelerations. By modelling the rotor B. SCHWEITZER and K. DORTMANN ln its Vortex Flows in blade as a beam structure, the distribution of the resulting Flying Technique p 159-182 1988 In GERMAN aerodynamic forces over the rotor blade length can be Avail: NTlS HC A17/MF A01 reconstructed. The reconstruction of the aerodynamic moments The flow field changes at wing profiles in an unsteady flow from simultaneously measured torsion torques also provide the and constant angle of attack were investigated experimentally as position of the resulting aerodynamic forces with respect to the well as numerically. Water tunnel experiments show clearly that profile depth. The results can also be used to improve the analytical the profile flow and especially the separation domain are affected unsteady aerodynamic force models. ESA
654 02 AERODYNAMICS
N89-25198*# National Aeronautics and Space Administration. N89-25952# Toronto Univ., Downsview (Ontario). Inst. for Langley Research Center, Hampton, VA. Aerospace Studies. FINITE ELEMENT FLOW-THERMAL-STRUCTURAL ANALYSIS FLOW CHARACTERISTICS ABOUT A TRAILING EDGE Ph.D. OF AERODYNAMICALLY HEATED LEADING EDGES Thesis PRAMOTE DECHAUMPHAI, ALLAN R. WIETING, and AJAY K. DWAYNE S. SMITH Mar. 1989 112 p PANDEY (Planning Research Corp., Hampton, VA.) ln its Recent (UTIAS-TN-270: ISSN-0082-5263) Avail: NTlS HC AO6/MF A01 Advances in Multidisciplinary Analysis and Optimization, Part 2 p The mandate was to determine the mean and turbulent flow 971-990 Apr. 1989 quantities of an attached, fully-developed boundary layer of an Avail: NTlS HC A22/MF A01 CSCL 01/1 aft-loaded airfoil. The steady, two-dimensional flow characteristics Hypersonic vehicles operate in a hostile aerothermal of the near and far wake were also studied. This was done to environment which has a significant impact on their aerother- gain an understanding of the viscous effects near the trailing edge mostructural performance. Significant coupling occurs be- of the airfoil in the hope of providing accurate data for airfoil tween the aerodynamic flow field, structural heat transfer, and performance models. Tests were conducted at a Reynolds number structural response creating a multidisciplinary interaction. A long of 1.7 million based on chord and a Mach number of 0.14. The term goal of the Aerothermal Loads Branch at the NASA Langley airfoil model on loan from Boeing of Canada's deHavilland Division Research Center is to develop a computational capability for was restricted to zero incidence and the boundary layer was integrated fluid, thermal and structural analysis of aerodynamically artificially tripped at 0.075~. Artificial tripping was employed to heated structures. The integrated analysis capability includes the provide a well-defined transition location over that of free transition coupling between the fluid and the structure which occurs primarily for numerical analysis. The hot-wire anemometer measurements through the thermal response of the structure, because: (1) the taken in the boundary layer and wake near the trailing edge reveal surface temperature affects the external flow by changing the that a complex interaction takes place just aft of the airfoil where amount of energy absorbed by the structure, and (2) the the upper and lower surface flows combine. The boundary layer temperature gradients in the structure result in structural thickness was found to increase quickly over the last few percent deformations which alter the flow field and attendant surface chord with a corresponding increase in turbulence intensity. The pressures and heating rates. In the integrated analysis, a finite extreme asymmetry in the near wake profile was seen to transform element method is used to solve: (1) the Navier-Stokes equations into an essentially symmetric profile by approximately X/C= 1.075. for the flow solution, (2) the energy equation of the structure for such as, skin friction coefficients, displacement Author the temperature response, and (3) the equilibrium equations of the structure for the structural deformation and stresses. Author
N89-25953'# Eloret Corp., Sunnyvale, CA. N89-25950# National Aerospace Lab., Tokyo (Japan). EXPERIMENTAL AND COMPUTATIONAL FLOW-FIELD A NUMERICAL SOLUTION OF TRANSONIC FLOW USING RESULTS FOR AN ALL-BODY HYPERSONIC AIRCRAFT DISCONTINUOUS SHOCK WAVE RELATIONSHIP Technical Progress Report, 1 Oct. 1988 31 Mar. 1989 MASAYOSHI NAKAMURA Sep. 1988 18 p In JAPANESE: - JOSEPH W. CLEARY 7 Jun. 1989 30 p Presented at the ENGLISH summary 6th National Aero-Space Plane Technology Symposium, 24-28 Apr. (NAL-TR-997; ISSN-0389-4010) Avail: NTlS HC A03/MF A01 1989 It is the purpose of this study to obtain solutions, which contain (Contract NCC2-416) complete discontinuities of shock waves, of the potential equations (NASA-CR-185347: NAS 1.26:185347) Avail: NTlS HC AOS/MF for transonic airfoils using numerical techniques. For iterative A01 CSCL 01/1 calculations, the potential equations are transformed into a more A comprehensive test program is defined which is being convenient form of simultaneous equations having two variables, implemented in the NASA/Ames 3.5 foot Hypersonic Wind Tunnel velocity potential and Mach number. The solutions with the for obtaining data on a generic all-body hypersonic vehicle for complete discontinuities of shock waves satisfying shock wave computational fluid dynamics (CFD) code validation. Computational relationship are obtained by the iterative calculations without methods (approximate inviscid methods and an upwind parabolized divergencies or high frequencies under a grid system in the physical Navier-Stokes code) currently being applied to the all-body model plane. Numerical results of the present techniques, and of another are outlined. Experimental and computational results on surface method for the transonic flow over an airfoil of NACA0012 with pressure distributions and Pitot-pressure surveys for the basic shock wave, are used as test cases for comparison. Author sharp-nose model (without control surfaces) at a free-stream Mach number of 7 are presented. K.C.D. N89-25951'# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. STEADY-STATE AND TRANSITIONAL AERODYNAMIC CHARACTERISTICS OF A WING IN SIMULATED HEAVY RAIN N89-25954*# National Aeronautics and Space Administration. BRYAN A. CAMPBELL and GAUDY M. BEZOS Washington Ames Research Center, Moffett Field, CA. Aug. 1989 95 p THE ACOUSTICS OF A SMALL-SCALE HELICOPTER ROTOR (NASA-TP-2932; L-16576; NAS 1.60:2932) Avail: NTlS HC IN HOVER A05/MF A01 CSCL 01 /1 CAHIT KITAPLIOGLU Apr. 1989 96 p The steady-state and transient effects of simulated heavy rain (NASA-TM-101058: A-89015; NAS 1.15:101058) Avail: NTlS HC on the subsonic aerodynamic characteristics of a wing model were AOWMF A01 CSCL 0111 determined in the Langley 14- by 22-Foot Subsonic Tunnel. The A 2.1 m diameter, 1/6-scale model helicopter main rotor was 1.29 foot chord wing was comprised of a NACA 23015 airfoil and tested in hover in the test section of the NASA Ames 40- by had an aspect ratio of 6.10. Data were obtained while test variables 80-foot wind tunnel. Performance and noise data on a small-scale of liquid water content, angle of attack, and trailing edge flap rotor at various thrust coefficients and tip Mach numbers were angle were parametrically varied at dynamic pressures of 10, 30, obtained for comparison with existing data on similar full-scale and 50 psf (i.e., Reynolds numbers of .76x10(6), 1.31~10(6),and helicopter rotors. These data form part of a data base to permit 1.69~10(6)).The experimental results showed reductions in lift and the estimation of scaling effects on various rotor noise mechanisms. increases in drag when in the simulated rain environment. Another objective was to contribute to a data base that will permit Accompanying this was a reduction of the stall angle of attack by the estimation of facility effects on acoustic testing. Acoustic approximately 4 deg. The transient aerodynamic performance 1/3-octave-band spectra are presented, together with variations during transition from dry to wet steady-state conditions varied of overall acoustic levels with rotor performance, microphone between a linear and a nonlinear transition. Author distance, and directivity angle. Author
655 02 AERODYNAMICS
N89-25957’# National Aeronautics and Space Administration. and the cessation of aerodynamic stall. These data may be useful Lewis Research Center, Cleveland, OH. in high angle of attack applications such as the enhanced INFLUENCE OF THICKNESS AND CAMBER ON THE maneuverability concept for fighter aircraft. GRA AEROELASTIC STABILITY OF SUPERSONIC THROUGHFLOW FANS AN ENGINEERING APPROACH N89-25965# Winzen International. Inc.. San Antonio, TX. JOHN K. RAMSEY Jun. 1989 22 p LONG DURATION BALLOON TECHNOLOGY SURVEY, PHASE (NASA-TM-101949; E-4642; NAS 1.15:101949) Avail: NTlS HC 1 Final Report, 11 Aug. 1988 - 28 Feb. 1989 A03/MF A01 CSCL 01 /1 PAMELA G. SCOT, THOMAS M. LEW, JAMES S. WILBECK, An engineering approach was used to include the nonlinear JAMES L. RAND, and RICHARD H. BREZINSKY 17 Mar. 1989 effects of thickness and camber in an analytical aeroelastic analysis 66 P of cascades in supersonic acial flow (supersonic leading-edge (Contract DAAH01-88-C-0715;ARPA ORDER 5916) locus). A hybrid code using Lighthill’s nonlinear piston theory and (AD-A206975; Wll-9942-01-TR-01) Avail: NTlS HC A04/MF A01 Lanes’s linear potential theory was developed to include these CSCL 01/3 nonlinear effects. Lighthill’s theory was used to calculate the This feasibility study addresses the design and fabrication of a unsteady pressures on the noninterference surface regions of the long endurance balloon vehicle capable of supporting 50 pounds airfoils in cascade. Lane’s theory was used to calculate the at 120.000 feet for up to one year. The concept makes use of unsteady pressures on the remaining interference surface regions. the experience gained by the scientific community over the past Two airfoil profiles was investigated (a supersonic throughflow fan two decades in flying smaller payloads for long periods of time. design and a NACA 66-206 airfoil with a sharp leading edge). The result of the effort is a prototype balloon which has a better Results show that compared with predictions of Lane’s potential lift to weight ratio than previous designs. This was achieved by theory. for flat plates, the inclusion of thickness (with or without the use of a novel shape (multiple intersecting spheres) and the camber) may increase or decrease the aeroelastic stability, use of a material new in the area of ballooning (Emblem, a biaxially depending on the airfoil geometry and operating conditions. When oriented Nylon 6). This film demonstrates very high strength without thickness effects are included in the aeroelastic analysis, inclusion displaying the susceptibility of prior films to pinholing. Other results of camber will influence the predicted stability in proportion to the of the effort are two analytical tools and specialized fabrication magnitude of the added camber. The critical interblade phase angle, techniques. The analytical tools are a heat transfer model for depending on the airfoil profile and operating conditions, may also predicting maximum and minimum super-temperatures of the be influenced by thickness and camber. Compared with predictions balloon gas, and mechanical model to design the superpressure of Lane’s linear potential theory, the inclusion of thickness and balloons for particular flight scenarios. GRA camber decreased the aerodynamic stifness and increased the aerodynamic damping at Mach 2 and 2.95 for a cascade of N89-25966# lnstitut Franco-Allemand de Recherches, Saint-Louis supersonic throughflow fan airfoils oscillating 180 degrees out of (France). phase at a reduced frequency of 0.1. Author VORTICES AND PRESSURE WAVES AT PLATES, CYLINDERS AND WIND PROFILES [WIRBEL UND DRUCKWELLEN AN PLAlTEN, ZYLINDERN UND TRAGFLUEGELPROFILEN] N89-25958’# National Aeronautics and Space Administration. F. SEILER, J. SRULIJES, and A. GEORGE 19 Jan. 1988 37 p Ames Research Center, Moffett Field, CA. In GERMAN PERFORMANCE AND LOADS DATA FROM AN OUTDOOR (ISL-R-102/88; ETN-89-94853) Avail: NTlS HC AO3/MF A01 HOVER TEST OF A LYNX TAIL ROTOR Vortex behavior and Karman vortex street formation behind DAVID B. SIGNOR, GLORIA K. YAMAUCHI, CHARLES A. SMITH, wing profiles in a shock tube are studied and visualized by and MARTIN J. HAGEN Jun. 1989 63 p differential interferometry. Precise image quality flow visualization (NASA-TM-101057; A-89014; NAS 1.15:101057) Avail: NTlS HC allows observation of recompression shock waves together with A04/MF A01 CSCL 01 /1 pressure waves. For a wing profile in a hard incident subsonic A Lynx tail rotor was tested in hover at the Outdoor Aerodynamic flow an asymmetric vortex distribution around the wings is observed. Research Facility at NASA Ames Research Center. The test Pressure waves are determined on the underside of the wing; the objectives were to measure the isolated rotor performance to upward side is free of shock and pressure waves. ESA provide a baseline for subsequent testing, and to operate the rotor throughout the speed and collective envelope before testing N89-25969# Manchester Univ. (England). Aeronautical Group. in the NFAC 40- by 80-Foot Wind Tunnel. Rotor forces and blade AN INITIAL ASSESSMENT OF THE IMPACT OF BOUNDARY bending moments were measured at ambient wind conditions from LAYER CONTROL ON SST zero to 6.23 m/sec. The test envelope was limited to rotor speeds D. I. A. POLL and S. R. BUNTING 1988 17 p of 1550 to 1850 rpm and minus 13 deg to plus 20 deg of blade (AERO-REPT-8802; ETN-89-94953) Avail: NTlS HC A03/MF collective pitch. The isolated rotor performance and blade loads data are presented. Author A0 1 The implications of establishing laminar flow on a vehicle traveling at supersonic speed are considered. A simple analysis is N89-25964# Ohio Univ., Athens. Dept. of Mechanical used to estimate the magnitudes of the different components which Engineering. make up the total aircraft drag and to determine how the relative AN EXPERIMENTAL INVESTIGATION OF HIGH LIFT/HIGH importance of each component changes with increasing flight Mach RATE AERODYNAMICS OF AN UNSTEADY AIRFOIL Final number. Special consideration is given to the effect of laminarization Report, 1 Sep. 1987 - 31 Dec. 1988 on the equilibrium surface temperatures and an attempt is made G. M. GRAHAM Mar. 1989 49 p to assess the impact of the observed changes on the vehicle (Contract AF-AFOSR-0312-87; AF PROJ. 2307) design. Results indicate that substantial improvements in (AD-A206964; AFOSR-89-0438TR) Avail: NTlS HC A03/MF A01 performance are available for vehicles flying at up to Mach 4. CSCL 0111 ESA An experimental study of a two dimensional NACA 0015 airfoil undergoing both positive and negative constant pitch rate motions N89-25970# Manchester Univ. (England). Dept. of Aeronautical at high angles of attack was conducted in the Ohio University tow Engineering. tank facility. Nondimensional pitch rates in the range of 0.1 greater AN INTRODUCTION TO THE PROBLEM OF AERODYNAMIC than K greater than 0.7 and Reynolds numbers in the range of HEATING 141,000 greater than Re greater than 342,000 were considered. D. I. A. POLL 1989 17 p Test results consist of lift and drag force coefficients and flow (AERO-REPT-8901; ETN-89-94956) Avail: NTlS HC A03/MF visualizations. The results of this study provide insight into the A0 1 airfoil-dynamic stall vortex interaction during the pitch down motion Aerodynamic heat transfer to a body travelling at high speed
656 03 AIR TRANSPORTATION AND SAFETY
is reviewed. The various sources of thermal energy which act Mexico. A brief description is given of the facility and the techniques upon the outer surface are identified and their relative importance used in escape system testing. An explanation is given of the test is examined. Special consideration is given to the convective heat analysis philosophy and procedures. The testing described includes transfer from the body boundary layer. The complete boundary most of the escape systems now in the Air Force inventory as layer problem is described and an approximate solution method is well as some presently in use by other governmental agencies presented. A generalized evaluation of the heating loads is and foreign governments. Ejection seats, crew modules, and developed and the results suggest that, for high speed devices extraction seat escape systems have been tested. Author flying at low altitude, the boundary layer convective heat load is the dominant term. This suggests that the surface temperatures A89-45296# and heat loads can only be evaluated by a simultaneous solution AGING AIRCRAFT of the boundary layer flow and internal unsteady heat conduction RICHARD DEMEIS Aerospace America (ISSN 0740-722X), vol. problems. ESA 27, July 1989, p. 38-42. The first 290 8737 airliners built employed a cold-bonding N89-25972# Deutsche Forschungs- und Versuchsanstalt fuer adhesive where the skin running along the top of the fuselage Luft- und Raumfahrt, Brunswick (Germany, F.R.). Abteilung overlaps the adjacent skin panel; subsequent aircraft were Trans-Ueberschall-Entwuresaerodynamik. hot-bonded in an autoclave; investigators have found that surface A LIFTING SURFACE METHOD FOR THE CALCULATION OF preparation before application of the cold-bonding adhesive failed STEADY AND UNSTEADY, INCOMPRESSIBLE PROPELLER to ensure adequate bonding to the skin. As a result, bonds AERODYNAMICS Ph.D. Thesis - Technlsche Univ., Brunwsick degraded and shifted all shear loads to the countersunk rivets JUERGEN SCHOENE Jan. 1989 120 p In GERMAN; ENGLISH which pass through the lap joint to attach the panels to a stringer, summary overstressing the adjacent skin and leading to extensive crack (DFVLR-FB-89-04; ISSN-0171-1342; ETN-89-94980) Avail: NTlS formation and growth. These factors are held responsible for the HC AO6/MF A01; DFVLR, VB-PL-DO, Postfach 90 60 58, 5000 peeling off of a 6737’s upper fuselage in flight on April 28, 1988. Cologne, Fed. Republic of Germany, DM 40 An account is presently given of additional, corrosion-related fatigue . A lifting surface method for steady and unsteady propeller failures in older aircraft. O.C. aerodynamics which allows the calculation of the lift distribution of single and counter-rotating propellers in axial onflow is described. A0945337 The integral equation for lifting surfaces with time dependent lift AN AIR PHOTO ANALYSIS OF AN AIRPLANE CRASH distribution is derived, based on the acceleration potential of J. N. RINKER, J. H. GARSTANG, D. EDWARDS, and J. J. DEL Prandtl. A solution method for this equation is developed. The VECCHIO (US. Army, Engineer Topographic Laboratories, Fort lifting surfaces of the propeller blades are subdivided into panels. Belvoir, VA; Canadian Aviation Safety Board, Ottawa, Canada) On a panel, doublets are located along a line. The doublet strength Aviation, Space, and Environmental Medicine (ISSN 0095-6562), is developed into a Fourier series. A set of linear algebraic vol. 60, July 1989, p. A6-Al5. refs equations has to be solved. Calculations for wings, for single Crash patterns such as cut and damaged vegetation, gouges, propellers with steady and unsteady lift distributions and for debris scatter and burn areas, and their spatial relations can be counter-rotating propellers are shown. ESA effectively evaluated by the analysis of stereo aerial photographs. Results from the Canadian Aviation Safety Board’s use of aerial N89-25973’# Continuum Dynamics, Inc., Princeton, NJ. photography in the Gander, Nfld., crash of December 12, 1985, FEASIBILITY OF PREDICTING PERFORMANCE show that the technique can lend direct support to an investigation DEGRADATION OF AIRFOILS IN HEAVY RAIN Final Report in several ways. It provides an overall perspective view of the A. J. BILANIN, T. R. QUACKENBUSH, and A. FEO Jun. 1989 regional relations of the crash patterns and helps direct ground 44 P activities. In tree-covered areas, it can help establish aircraft attitude (Contract NASI -18302) and orientation. When combined with debris plots and attitude (NASA-CR-181842; NAS 1.26:181842; CDI-89-04) Avail: NTlS determinations, it can help establish the breakup sequence. And, HC A03f MF A01 CSCL 01f 1 when coupled to photogrammetric procedures,it can assign The heavy rain aerodynamic performance penalty program is dimensional values to attitude, descent path, areas and lengths. detailed. This effort supported the design of a fullscale test program Author as well as examined the feasibility of estimating the degradation of performance of airfoils from first principles. The analytic efforts A8 9 -4 65 9 3 were supplemented by a droplet splashback test program in an FAST BRAKE attempt to observe the physics of impact and generation of ejecta. JAKE PAGE Air and Space (ISSN 0886-2257), vol. 4, Aug.-Sept. These tests demonstrated that the interaction of rain with an airfoil 1989, p. 46-51. is a highly complex phenomenon and this interaction is not likely The development of high-performance parachutes is discussed, to be analyzed analytically with existing tools. Author focusing on the F-11 1 parachute system. Computer models, wind tunnel tests, rocket sled tests, and air drops from a 8-52 are used in the design and testing of the parachute system. The requirements for the F-11 1 system include carrying a module load 03 of 3,300 pounds with a rate of descent of about 25 ftfs. The design is based on a cluster of three light-weight parachutes with AIR TRANSPORTATION AND SAFETY a central disreef system to ensure that the cluster disreefs simultaneously so that none of the three parachutes is subjected Includes passenger and cargo air transport operations; and aircraft to excessive loads. R.B. accidents. A8947334 AUTOMATION IN TRANSPORT AIRCRAFT - CURRENT AND A8945129 FUTURETRENDS SLED TESTING OF U.S. AIR FORCE ESCAPE SYSTEMS A. G. LIDDLE (British Air Line Pilots Association, Harlington, C. D. GRAGG (USAF, Holloman AFB, NM) IN: Society of Flight England) IN: Aerospace Behavioral Technology Conference and Test Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, Exposition, 7th, Anaheim, CA, Oct. 3-6, 1988, Proceedings. 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, Warrendale, PA, Society of Automotive Engineers, Inc., 1989, p. 1988, p. 11-1.1 to 11-1.7. refs 73-77. Tests to verify the safety of escape systems are conducted at (SA€ PAPER 881468) the High Speed Test Track at Holloman Air Force Base, New Current automation technology for transport aircrafts, from the
657 03 AIR TRANSPORTATION AND SAFETY design stage to the operational use, is discussed together with From the description of the wind shear effects on the energy human factors involved. Recently introduced automation systems state of the aircraft, measures are derived in order to define a AB7571767 and A320 are assessed with respect to their controller that improves flight safety. In comparison to a instrumentation, and the advantages and disadvantages of these conventional flight control system, this approach presents aircraft are discussed and compared with those of older systems. advantages for reducing windshear effects. The actual windshear The danger of overautomation is emphasized. IS. problem stems from neither the controlled flight nor the limited aircraft performance, but rather from manual flight. The pilot is A89-47339 unable to perform with conventional instrumentation the necessary AIRLINE OPERATIONS AND THE CONTAMINATED RUNWAY measures, such as setting the thrust at the right time and level. KNUT ANFINDSEN (International Federation of Air Line Pilots’ Indicating the energy and power loss via signals sent into modified Associations, Egham, England) IN: Aerospace Behavioral instruments leads to an improvement in flight performance during Technology Conference and Exposition, 7th, Anaheim, CA, Oct. windshear. It is therefore shown that through suitable 3-6, 1988, Proceedings. Warrendale, PA, Society of Automotive instrumentation modifications the effects of wind shear can be Engineers, Inc., 1989, p. 119, 120. reduced. ESA (SAE PAPER 881460) Problems related to airline operations on a runway contaminated N89-25974# National Transportation Safety Board, Washington, by hard-packed snow overlaid with glazed ice and water are DC. highlighted, and methods that can be used for reducing risk on a GENERAL AVIATION ACCIDENTS INVOLVING VISUAL slippery runway are discussed. It is often suggested that the ICAO FLIGHT RULES FLIGHT INTO INSTRUMENT standard for the aircraft performance operating limitations (5.2.6) METEOROLOGICAL CONDITIONS cannot be strictly implemented because it is difficult to measure 8 Feb. 1989 39 p friction by ground measuring equipment and then use these (PB89-917001; NTSB/SR-89/01) Avail: NTlS HC A03/MF A01 measurements to predict the aircraft-stopping performance. CSCL 01/3 However, experience shows that a reliable runway friction-measuring A statistical compilation is presented of data from the National equipment can significantly contribute to improved safety of winter Transportation Safety Board’s Aviation Accident Data System. The operations. 1,s. data includes 361 general aviation accidents that occurred between 1983 and early 1987. In all of these accidents, visual flight rule N89-25142# Federal Aviation Administration, Atlantic City, NJ. flight into instrument meteorological conditions was listed as a NOTICE TO AIRMEN (NOTAM) SYSTEM OPERATIONAL probable cause or a related factor. There were 276 fatal accidents CONCEPT Final Report which resulted in 583 fatalities. Ninety-four percent of the aircraft BETTY K. FALATO Dec. 1988 56 p involved in these accidents were airplanes; the remainder were (DOT/FAA/CT-TN89/10; DOT/FAA/DS-89/05) Avail: NTlS HC helicopters. Author A04/MF A01 A requirement for the National Airspace System (NAS) to N89-25976# Boeing Co., Seattle, WA. Commercial Airplanes. provide timely knowledge to users of information which is essential AIRPLANE TESTS OF ENHANCED EMERGENCY SMOKE to safety of flight is identified in the NAS System Requirement VENTING Final Report Specification, NAS-SR-1000. The primary method of providing ELLIOTT L. MAYLOR Mar. 1989 60 p timely aeronautical information is via the Notice to Airmen (NOTAM) (Contract DTFA03-88-C-00056) system. A concept of operations is presented for the NOTAM (D218N301; DOT/FAA/CT-89/9) Avail: NTlS HC A04/MF A01 system. It describes NOTAM system capabilities and shows the This airplane test program evaluated the capability of certain relationships between subsystems, facilities, information, and air conditioning (environmental control) system modifications to operators/users. It is intended to provide a common perspective enhance the venting of neutral or buoyant smoke that may be for personnel involved in NOTAM-related activities, assist in continuously injected into the passenger cabin during an inflight determining whether the NOTAM system meets formal fire emergency. The program used a Boeing 757 airplane modified requirements, and support coordination among the organizations by adding an outflow valve in the forward upper lobe fuselage involved with the NOTAM system. Author and changing to high-flow control valves in both air conditioning packs. Artificially generated smoke, neutral and with helium added N89-25143 Civil Aviation Authority, London (England). to simulate buoyancy, was released at various passenger cabin UK AIRMISSES INVOLVING COMMERCIAL AIR TRANSPORT locations. Data from the ground tests showed that an upper lobe Dec. 1988 73 p outflow valve controls either neutral or buoyant smoke. (CAA-3/88; ISSN-0951-6301; ETN-89-94326) Avail: Civil Aviation Cruise/descent/land test results showed that neutral smoke can Authority, Greville House, 37 Gratton Road, Cheltenham, England, be controlled with either an upper or lower lobe outflow valve if 5 sterling pounds the outflow valve and the smoke source are at the same end of Statistics on commercial air transport airmisses in United the passenger cabin; this capability is not changed significantly by Kingdom airspace from 1978 to Apr. 1988 are presented. Numbers a 30 percent increase to the current pack flow rate. The results of incidents; aircraft involved; and airmisses related to flying hours also showed that maintaining pack flow while doors are open for are shown. Incident reports for the period Jan. to Apr. 1988 are passenger evacuation causes an undesirable increase in the rate reproduced. During this period, there were 21 incidents, involving of smoke spreading into the smoke free portions of the cabin. a total of 31 aircraft, giving an average 3.8 commercial air transport Author aircraft in risk-bearing airmisses per 100,000 hr flown. ESA N89-25977’# National Aeronautics and Space Administration. N89-25144# Deutsche Forschungs- und Versuchsanstalt fuer Ames Research Center, Moffett Field, CA. Luft- und Raumfahrt, Brunswick (Germany, F.R.). Abteilung ANALYSIS OF SEVERE ATMOSPHERIC DISTURBANCES Glaechenflugzeuge. FROM AIRLINE FLIGHT RECORDS CONTRIBUTIONS TO THE IMPROVEMENT OF FLIGHT R. C. WINGROVE, R. E. BACH, JR., and T. A. SCHULTZ Jun. SAFETY IN WIND SHEAR Ph.D. Thesis - Technische Univ., 1989 10 p Presented at the AGARD Flight Mechanics Panel Brunswick Symposium-Flight in Adverse Environmental Conditions, Gol, REINHARD KOENIG Dec. 1988 186 p In GERMAN; ENGLISH Norway, 8-1 1 May 1989 summary Report will also be announced as translation (NASA-TM-102186; A-89111; NAS 1.15:102186) Avail: NTlS HC (ESA-TT-1141) A02lMF A01 CSCL 01/3 (DFVLR-FB-88-49; ISSN-0171-1342; ETN-89-94635) Avail: NTlS Advanced methods were developed to determine time varying HC AO9/MF A01; DFVLR, VB-PL-DO, Postfach 90 60 58, 5000 winds and turbulence from digital flight data recorders carried Cologne, Fed. Republic of Germany, DM 65.50 aboard modern airliners. Analysis of several cases involving severe
658 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
clear air turbulence encounters at cruise altitudes has shown that prediction, intrail spacing, and metering. In order to evaluate the the aircraft encountered vortex arrays generated by destabilized DA, a real time simulation was conducted using both current and wind shear layers above mountains or thunderstorms. A model retired controller subjects. Controllers operated in teams of two, was developed to identify the strength, size, and spacing of vortex as they do in the present environment; issues of training and arrays. This model is used to study the effects of severe wind team interaction will be discussed. Evaluations by controllers hazards on operational safety for different types of aircraft. The indicated considerable enthusiasm for the DA aid, and provided study demonstrates that small remotely piloted vehicles and specific recommendations for using the tool effectively. Author executive aircraft exhibit more violent behavior than do large airliners during encounters with high-altitude vortices. Analysis of digital flight data from the accident at Dallas/Ft. Worth in 1985 indicates that the aircraft encountered a microburst with rapidly 04 changing winds embedded in a strong outflow near the ground. A multiple-vortex-ring model was developed to represent the AIRCRAFT COMMUNICATIONS AND NAVIGATION microburst wind pattern. This model can be used in flight simulators to better understand the control problems in severe microburst Includes digital and voice communication with aircraft; air navigation encounters. Author systems (satellite and ground based); and air traffic control.
N89-25979# Test Wing (4950th), Wright-Patterson AFB, OH. Aeronautical Systems Div. A89-43827# EC-l8B/BOEING 707 SMOKE VENTING FLIGHT TEST Final DEVELOPMENT AND VERIFICATION OF SOFTWARE FOR Report, Jan. - Jul. 1988 FLIGHT SAFETY CRITICAL STRAPDOWN SYSTEMS DANIEL J. MOKRIS 27 Mar. 1989 75 p WOLFGANG HASSENPFLUG and HOSSEIN AFZALI (LITEF (AD-A206601; REPT-4950/FTR-88-05-03) Avail: NTlS HC GmbH, Freiburg, Federal Republic of Germany) IN: Symposium A04/MF A01 CSCL 01/2 Gyro Technology 1988; Proceedings of the Symposium, Stuttgart, . This report presents the results of the smoke venting flight Federal Republic of Germany, Sept. 20,21, 1988. Stuttgart/Duessel- test on a USAF C-18, and a modified 8-707 aircraft. A 3-in. x dorf, Universitaet StuttgaWDeutsche Gesellschaft fuer Ortung und 4-in. smoke elimination valve (SEV) was installed in a metal window Navigation, 1988, p. 2.0-2.12. plug in a fuselage window forward of the wing's leading edge. A software-development methodology is described which was The SEV consisted of a hinged flat plate that extended out into proven to work satisfactorily to produce highly reliable software the slipstream. The local airflow accelerated around the plate, for flignt safety critical strapdown systems. Present in-service decreasing pressure in the area, and creating a draw that pulled results indicate that the design goal of less than or equal to 10 to smoke from the cabin of the aircraft. The objective of the test the -9th failures per flying hour can be achieved with a very high was to prove the feasibility of the SEV for venting smoke. The degree of confidence. The methodology was approved by most of aircraft was instrumented with smoke density detecting light meters the civil aviation agencies of the Western world and was accepted and a computerized data collection system. First, a baseline test by military agencies to reach flight clearance for an inherently of the aircraft's pressurization and air conditioning system was unstable fighter aircraft demonstrator. IS. conducted. Then the SEV was opened to assess its smoke clearing capabilities. Smoke clearing time constants were developed to A89-43828# gauge the system's performance and ranged from 57 to 555 NEW KALMAN FILTER ALGORITHMS FOR HYBRID seconds, depending on the test condition. While the SEV did NAVIGATION, FLIGHTPATH COMPUTATION AND INERTIAL exhaust smoke, complex airflow within the cabin appeared to cause GEODESY air stagnation in certain areas. This in turn forced the time constants H.-J. HOTOP (DNLR, lnstitut fuer Flugfuehrung, Brunswick, to increase when the SEV was opened, a trend exactly opposite Federal Republic of Germany) IN: Symposium Gyro Technology of what was expected. Recommendations were made to 1988; Proceedings of the Symposium, Stuttgart, Federal Republic re-accomplish the tests using a more realistic scenario, repeat of Germany, Sept. 20, 21, 1988. Stuttgart/Duesseldorf, Universitaet runs to increase reliability of data collected, and use some means StuttgarVDeutsche Gesellschaft fuer Ortung und Navigation, 1988, to visualize local flow patterns in certain key areas around the p. 3.0-3.19. refs cabin. GRA A new numerically stable Kalman filter algorithm, based on orthogonal transformations, is developed and verified by an N89-25981'# National Aeronautics and Space Administration. application to a laser strapdown inertial navigation system. A Ames Research Center, Moffett Field, CA. comparison of simulation results obtained with the new Kalman CONTROLLER EVALUATIONS OF THE DESCENT ADVISOR filter to those of the conventional algorithm, the Joseph algorithm, AUTOMATION AID and the Bierman algorithm (executed using the IBM 4381, IBM LEONARD TOBIAS, UWE VOLCKERS (Deutsche Forschungs- und 3090, and GRAY-XMP) showed that the new Kalman algorithm is Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick, Germany, superior with regard to the speed of computing process and the F.R. ), and HElNZ ERZBERGER Jun. 1989 13 p Presented ability to handle correlated measurements without the need for at the AlAA American Control Conference, Pittsburgh, PA, Jun. additional transformations. It is suggested that the new algorithm 1989 will find applications in long-duration hybrid navigation, flight (NASA-TM-102197; A-89150; NAS 1.15:102197) Avail: NTlS HC guidance, and inertial geodesy. I.S. A03/MF A01 CSCL 01/3 An automation aid to assist air traffic controllers in efficiently A8943891 spacing traffic and meeting arrival times at a fix has been developed NAVIGATION AIDS TO AIRCRAFT ALL-WEATHER LANDING at NASA Ames Research Center. The automation aid, referred to JOHN CHARNLEY (Royal Institute of Navigation, London, as the descent advisor (DA), is based on accurate models of England) (Royal Institute of Navigation, Annual General Meeting, aircraft performance and weather conditions. The DA generates 42nd, London, England, Oct. 26, 1988) Journal of Navigation (ISSN suggested clearances, including both top-of-descent point and 0373-4633), vol. 42, May 1989, p. 161-186. refs speed profile data, for one or more aircraft in order to achieve Progress made in aids to aircraft all-weather operation is specific time or distance separation objectives. The DA algorithm reviewed, starting from early attempts made during World War I is interfaced with a mouse-based. menu-driven controller display to the current capability in which the safe landing of modern civil that allows the air traffic controller to interactively use its accurate transport aircraft in very low visibility is regarded as a relatively predictive capability to resolve conflicts and issue advisories to routine operation. Particular attention is given to various fail-safe arrival aircraft. This paper focuses on operational issues concerning techniques for the protection against the effects of failure in the the utilization of the DA, specifically, how the DA can be used for critical landing period, improvements in the instrument landing
659 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
system, and the subject of software integrity. Finally, future storage, and distribution. Instead, the System 500 brings functions developments are discussed with emphasis on the microwave to the source in a distributed architecture. Data is captured, landing system. V.L. decommutated. processed in real time by traditional or user-created algorithms, displayed on color graphics workstations, and stored A8443893 on very high performance media or transferred to a central OMEGA NAVIGATION IN THE SHADOW OF ANTARCTICA computer for use in traditional analysis and distribution. Author R. BARR (Department of Scientific and Industrial Research, Physics and Engineering Laboratory, Wellington, New Zealand) and K. B. A8445138 YOUNG (Royal New Zealand Air Force, Whenuapai) Journal of A SIMPLE LOW-COST TELEMETRY SYSTEM FOR THOSE OF Navigation (ISSN 0373-4633), vol. 42, May 1989, p. 236-247. MODEST MEANS refs DAVID B. BUSHNELL, WILLIAM C. SCHINSTOCK, and WILLIAM A series of measurements are examined to determine the G. SCHWEIKHARD (Kohlman Systems Research, Lawrence, KS) physical processes responsible for positional fix errors obtained IN: Society of Flight Test Engineers, Annual Symposium, 19th, from the Omega navigation system at high southern latitudes (70-75 Arlington, TX, Aug. 14-18, 1988, Proceedings. Lancaster, CA, deg S). Optimal strategies are suggested for station selection and Society of Flight Test Engineers, 1988, p. IV-3.1 to IV-3.10. rejection which should improve significantly the accuracy of the A simple low-cost low-data-rate telemetry system has been Omega navigation system, bringing it to levels accepted for developed and flight tested. The telemetry system consists of an low-latitude navigation. V.L. airborn modem and transmitter, and a ground-based receiver, modem, and computer. Data to be telemetered is entered in RS-232 A8943894 format and is used to frequency modulate an RF transmiter. It is EVALUATING ILS AND MLS SITES WITHOUT FLIGHT TESTS shown that the 10-W S-band transmitter can provide a telemetry P. R. MAHAPATRA (Indian Institute of Science, Bangalore, India) range in excess of 100 nautical miles and that the system can and M. M. POULOSE (National Airports Authority of India, record 87 parameters at one sample per second. The ground-based Bangalore, India) Journal of Navigation (ISSN 0373-4633), vol. system stores, processes, and displays the telemetered data in 42, May 1989. p. 278-290. refs engineering units. R.R. Instrument landing systems (ILS) and the upcoming microwave landing systems (MLS) are (or are planned to be) very important navigational aids at most major airports of the world. However, A89-45221 their performance is directly affected by the features of the site in SOME ASPECTS OF INTERFERENCE ON LORAN-C which they are located. Currently, validation of the ILS performance L. P. REMMERSWAAL (Philips Telecommunications and Data is through costly and time-consuming experimental methods. This Systems, Netherlands) and D. VAN WlLLlGEN (Delft, Technische paper outlines a powerful and versatile analytical approach for Universiteit. Netherlands) IEE Proceedings, Part F: Radar and performing the site evaluation, as an alternative to the experimental Signal Processing (ISSN 0956-375X), vol. 136, pt. F, no. 3, June methods. The approach combines a multi-plate model for the terrain 1989, p. 109-117. Research supported by Stichting voor de with a powerful and exhaustive ray-tracing technique and a versatile Technische Wetenschappen. refs and accurate formulation for estimating the electromagnetic fields The expansion of Loran-C in Europe with its already heavily due to the array antenna in the presence of the terrain. It can loaded LF frequency spectrum is a challenge to the receiver model the effects of the undulation, the roughness and the designer. The number of continuous wave (CW) interferences often impedance (depending on the soil type) of the terrain at the site. exceeds the number of notch filters available in Loran-C receivers. The results computed from the analytical method are compared Thus, decisions have to be made about which interfering signals with the actual measurements and good agreement is shown. are to be suppressed. However, the complex nature of the Considerations for site effects on MLS are also outlined. Author disturbance of phase and envelope of Loran-C signals by CW interference makes understanding of the process difficult. Therefore, a practical vector-analysis method is outlined which A8945065 helps to explain the effects of asynchronous and various types of A KNOWLEDGE-BASED EN ROUTE MONITOR FOR AIR synchronous interferences and noise. The net result on the phase TRAFFIC CONTROL and envelope tracking process is demonstrated with the Loran CHIN E. LIN and M. C. HONG (National Cheng Kung University, Simulation Program LOSP which runs on a personal computer. Tainan, Republic of China) IEEE Transactions on Aerospace and Electronic Systems 0018-9251), vol. 25, May 1989, p. Finally, some general ideas on interference-reduction techniques (ISSN are discussed. Author 392-400. refs The en route monitor system (ERMS), which is a software system designed to assist human controllers, was developed as a A89-45875 tool for the control center. A domain-specific knowledge-based RADIO TECHNICAL COMMISSION FOR AERONAUTICS, design approach was used. The system is implemented in Turbo ANNUAL ASSEMBLY MEETING AND TECHNICAL Prolog. The problem and solution techniques are discussed in SYMPOSIUM, WASHINGTON, DC, NOV. 28-30, 1988, detail, and examples and simulations are demonstrated to show PROCEEDINGS the potential application of the ERMS in air traffic control. LE. JOANN C. JAGO, ED. (Radio Technical Commission for Aeronautics, Washington, DC) Meeting and Symposium sponsored A8945134 by the Radio Technical Commission for Aeronautics. Washington, THE SYSTEM 500, A REAL-TIME FLIGHT TEST TELEMETRY DC. Radio Technical Commission for Aeronautics, 1988, 288 p. SYSTEM No individual items are abstracted in this volume. PAUL J. FRIEDMAN and GALE L. WILLIAMSON (Loral Technological and standardization problems in the development Instrumentation, San Diego. CA) IN: Society of Flight Test of communication avionics are examined in reviews and reports. Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18. Particular attention is given to ICAO planning for future aeronautical 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, communication standards, digital voice communication techniques, 1988, p. 111-4.1 to 111-4.7. communication systems for next-generation commercial aircraft, The System 500 is a distributed architecture, real-time telemetry extending data communication to oceanic routes, RTCA mode-S data acquisition, processing, and graphics display system data-link standardization, AEEC satellite-systems standardization, developed specifically for flight test applications. It was designed air communication using Inmarsat, and FAA support for future for flight test engineers to make real-time decisions on quality air-ground digital communication. Also included is a panel and safety of maneuver and to evaluate vehicle and system discussion presenting user perspectives on aeronautical performance. Traditional system solutions make extensive use of telecommunication. Diagrams, drawings, and tables of numerical large, powerful, and expensive computers for processing, data data are provided. T.K.
660 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
A89-47335 guidance in locating a heliport. From these results, there does AIR TRAFFIC CONTROL - NO EASY SOLUTIONS IN A not appear to be reasonable cause for opposing adoption of the COMPLEX TERMINAL ENVIRONMENT proposed strobe beacon as an ICAO standard. Furthermore, there JOHN BENNETT (Luton International Airport, Ltd., London, does not appear to be any compelling reason to change the present England) IN: Aerospace Behavioral Technology Conference and United States standard for heliport identification beacons at this Exposition, 7th, Anaheim, CA, Oct. 3-6, 1988, Proceedings. time. Author Warrendale, PA, Society of Automotive Engineers, Inc., 1989, p. 79-85. N89-25985# Federal Aviation Administration, Atlantic City, NJ. (SAE PAPER 881469) EVALUATION OF A PROJECTION ALGORITHM FOR THE Traffic control problems in a busy terminal area are discussed, STEREOGRAPHIC REPRESENTATION OF AIRCRAFT IN AN with particular consideration given to control problems specific for AIR TRAFFIC CONTROL SYSTEM the Luton International Airport, which lies 30 miles north of London. ROBERT G. MULHOLLAND Apr. 1989 27 p Factors which affect the air traffic (such as noise preferential routes, (DOT/FAA/CT-TN89/20) Avail: NTlS HC A03/MF A01 night restrictions, and flight-coordination schedules) are discussed In an air traffic control system such as the National Airspace along with the present equipment and procedures used in the System (NAS) horizontal control is effected from a ground facility traffic control and the effect of automatic data processing. It is through the separation of aircraft in at least one of the dimensions concluded that the sectorization of airspace according to route, of latitude and longitude. Ideally, these dimensions are obtained together with the introduction of free-flow systems separate from indirectly in real time by means of a projection algorithm that other outbound and inbound routes, would allow more capacity maps raw surveillance information into the stereographic for air traffic; however, these measures will lead to diminished representation of aircraft latitude and longitude on a plane surface. flexibility, making the air traffic structure very rigid in ’slot time’, In practice, there is always some processing delay and some route, and level terms. IS. difference between the algorithm output and the actual stereographic representation of aircraft position. In addition, the A89-47336 accuracy is affected by the orientation of the plane relative to the RESEARCH IN AUTOMATION FOR AIR TRAFFIC CONTROL - control jurisdiction of the facility. While the projection algorithm UNITED KINGDOM WORK AND ASSOCIATED EUROPEAN currently employed in NAS is capable of timely delivery of output PROJECTS due to its structural simplicity, it cannot meet the accuracy ARTHUR G. THORNING (Civil Aviation Authority, London, requirement of the Advanced Automation System. The accuracy England) IN: Aerospace Behavioral Technology Conference and of a simple modification of the NAS algorithm that does meet this Exposition, 7th, Anaheim, CA, Oct. 3-6, 1988, Proceedings. requirement is evaluated by means of a technique that avoids Warrendale, PA, Society of Automotive Engineers, Inc., 1989, p. determination of the geometric relationship of the plane and the 87-94. control jurisdiction. Author (SAE PAPER 881470) Research work in the United Kingdom aimed at developing N89-25986# Federal Aviation Administration, Atlantic City, NJ. the benefits of automation in Air Traffic Management is described. Technical Center. To emphasize the systematic and international nature of such CONTROLLER EVALUATION OF INITIAL DATA LINK AIR work, related projects are also outlined. The paper gives a broad TRAFFIC CONTROL SERVICES. VOLUME 2: MINI STUDY 2 overview of projects in UK and Europe rather than much detail Final Report and as such is aimed at stimulating interest in and understanding NICHOLAS J. TALOTA, CLARK SHINGLEDECKER, THOMAS of the ATC aspects of automation. Author ZURINSKAS, KAROL KERNS, PRESTON CRATCH (Mitre Corp., Atlantic City, NJ.), and HENRY R. MAREK Mar. 1989 73 p A89-47340 (DOT/FAA/CT-89/14-VOL-2) Avail: NTlS HC AO4/MF A01 MICROWAVE LANDING SYSTEM INSTRUMENTATION - A The results of Mini Study 2 are given. This Mini Study was PILOT’S VIEWPOINT conducted at the Federal Aviation Administration (FAA) Technical N. J. DUNSFORD (International Federation of Air Line Pilots’s Center utilizing the Data Link test bed. Initial Data Link air traffic Associations, Egham, England) IN: Aerospace Behavioral control services were evaluated under part task simulation Technology Conference and Exposition, 7th, Anaheim, CA, Oct. conditions in order to identify service delivery methods which 3-6, 1988, Proceedinw. Warrendale. PA, Society of Automotive optimize controller acceptance, performance, and workload. Engineers, Inc., 1989,~.121 -1 30. Author (SAE PAPER 881461) This paper presents a pilot’s viewpoint of the Microwave Landing System (MLS), which is being developed as a replacement for 05 the Instrument Landing System (ILS) as the ICAO standard approach landing aid. The basic and advanced MLS procedures are outlined, and all the steps to be followed in an MLS approach AIRCRAFT DESIGN, TESTING AND procedure are described in detail, with special consideration given PERFORMANCE to the role of the aircraft crew during the approach. It is shown that the MLS has a degree of flexibility not allowed by the ILS. Includes aircraft simulation technology. IS.
N89-25984# Federal Aviation Administration, Atlantic City, NJ. A89-43884 HELIPORT IDENTIFICATION BEACON DAMAGE TOLERANCE ANALYSIS AND STRUCTURAL PAUL H. JONES Apr. 1989 14 p INTEGRITY IN AIR FORCE AIRCRAFT (DOT/FAA/CT-TN89/31) Avail: NTIS HC A03/MF A01 ALFRED G. HANSEN Aerospace Engineering (ISSN 0736-2536), The International Civil Aviation Organization (ICAO) has vol. 9, June 1989, p. 19-21. proposed the adoption of a standard international heliport beacon. Damage tolerance analysis (DTA) of high-performance aircraft This beacon consists of a white strobe light coded to display a structures proceeds on the assumption that flaws exist which sequence of four flashes that signify the Morse code letter H. For cannot always be detected. The flaws are initially due to the evaluation purposes, the proposed strobe beacon was compared manufacturing process, which through subsequent service trauma to the United States standard three-color rotating beacon. Pilots grow into cracks that degrade structural strength. By analyzing completed post-flight questionnaires after viewing both beacons. the growth pattern for a given load history, DTA allows engineers Without any clear-cut choice as to which beacon was the best, to predict how large the crack can become before safety is pilot responses indicated that both beacons provide adequate jeopardized, as well as the time remaining before that point is
66 1 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE reached. In the course of DTA testing, full-scale aircraft are MIKE GAINES Flight International (ISSN 0015-3710), vol. 135, subjected to millions of load applications to discover unanticipated June 10, 1989, p. 80, 81, 84 (3 ff.). problem areas and define their solution. O.C. An account is given of the design features, variants, economic viability, performance capabilities and weapons suites of the French A8943887 next-generation fighter aircraft, Rafale. Air-to-air, air-to-ground, and TUPOLEV’S NEW TWIN air-to-sea missions are envisioned. The last of these will be the ALAN POSTLETHWAITE Flight International (ISSN 0015-371 0), preserve of a carrier-based naval variant, the Rafale M or ’maritime’; vol. 135, May 20, 1989, p. 44-46. the other variant, Rafale D, or ’discrete’, will be operated by the The Tu-204 is the first Soviet airliner to incorporate a fly-by-wire French Air Force and is optimized for stealthyness. Although the control system without mechanical backup; it also employs such current, Rafale A technology-demonstrator is powered by two 6757-equivalent technologies as all-graphics-display cockpit U.S.-built F404-GE-400 engine, Rafales M and D will be powered instrumentation, a supercritical-airfoil geometry wing, winglets, and by M-88-2 augmented turbofans ultimately capable of producing AI-Li alloy primary structures. Derivatives of the Tu-204 currently 23,600 Ibs of thrust on afterburner. SPF/DB Ti and AI-Li alloys planned involve the use of ultrahigh-bypass turbofans, and even are employed in the airframe primary structure. O.C. the accommodation of cryotankage for the use of liquefied natural gas as fuel. A primary design task has been the reduction of A8945041 direct operating costs; with this in view, routine overhauls have THE ACE/RAFALE [L’ACE/RAFALE] been eliminated, and units will be changed only upon failure. Service BRUNO REVELLIN-FALCOZ (Avions Marcel Dassault Breguet life is projected to be 20 years of use at an annual utilization of Aviation, S. A., Vaucresson, France) L’Aeronautique et up to 3000 hours. O.C. I’Astronautique (ISSN 0001-92754, no. 136-137, 1989, p. 72-78. In French. A8943888 The characteristics and flight results of the Rafale A tech- ILYUSHIN GOES THE DISTANCE nology demonstrator are discussed. The ACElRafale employs ALAN POSTLETHWAITE Flight International (ISSN 0015-371 0). large-aspect-ratio delta wings, a large all-flying canard surface, vol. 135, May 20, 1989, p. 49-51. and semiventral air intakes. The flight control system includes a The USSR’s 11-96-300, which is a 300-seat wide-body airliner new control approach mode (drag-thrust control), large-incidence optimized for long-range flights of 9000 km with full passenger control, and a velocity-vector holding mode. Composite materials load, is that nation’s first fly-by-wire commercial aircraft and appears and other advanced materials make up 35 percent of the aircraft to be intended for a production run of at least 100 units. Like the mass. Also considered are the M88 engine and man-machine A340-300 aircraft to which it is approximately comparable, the interfaces of the aircraft. R.R. 11-96-300 is a four-turbofan aircraft with winglets and six color-coded graphics CRTs that serve as cockpit instrument displays. A A09-45043 stretch-version capable of accommodating 400 passengers is being AIRBUS -THE NEW FAMILIES [AIRBUS - LES NOUVELLES contemplated. The excellent range characteristics are substantially FAMILLES] due to the use of advanced aluminum alloy and composite airframe JACQUES MORISSET L’Aeronautique et I’Astronautique (ISSN components. The fly-by-wire system used is claimed to offer 0001-9275), no. 136-137, 1989, p. 89-98. In French. performance comparable to that of the A320 airliner. O.C. The characteristics of the A320, A320 Stretch, A330, and A340 aircraft are described. The A320, with a seating capacity of 150-170, A8944375 has a wider diameter than the 8727, 8737, and 8757 and employs ILYUSHIN’S NEW WORKHORSE an electronic flight control system. The A320 stretch, with a seating ALAN POSTLETHWAITE Flight International (ISSN 0015-371 0), capacity of 186-200, is proposed as an alternative to the 6757. vol. 135, May 13, 1989, p. 29-31. The A320 stretch uses double-slotted high-lift flaps, and it employs The 11-114 60-seat regional airliner, which will have its first more powerful engines (13.15 tons of thrust for the CFM56-5B flight some time in 1989, is expected to offer half the fuel and 12.7 tons of thrust for the V2500-A5) than the A320. The consumption/passenger-km of the 52-seat An-24 transport that it A330 and A340 aircraft, variants of the A320, will have seating will be replacing on routes of about 1000-km range. The two capacities of 295-335, and will employ optimized aerodynamic wing lsotov TV7-117 turboprop engines employed drive six-bladed profiles, AI-Li alloys and composite materials, and an optimized synchronized propellers. Although the primary structure is entirely cockpit design. R.R. of conventional aluminum alloys, extensive use is made of composites in secondary structures. The planned production run A89-45044 is intensive, with 500 aircraft being manufactured in the first 5 THE SYSTEMS OF THE FUTURE AIRBUS A330 AND A340 years in two factories in the USSR; components are expected to AIRCRAFT [LES SYSTEMES DES FUTURS AVIONS AIRBUS be supplied by East European subcontractors. O.C. A.330 ET A.3401 JEAN-PIERRE LABORIE (Aerospatiale, Division Avions, Toulouse, A89-44975# France) L‘Aeronautique et I’Astronautique (ISSN 0001-9275), A SIMPLE THEORY OF AEROSPACEPLANE no. 136-137, 1989, p. 99-108. In French. RYOJIRO AKIBA Japan Society for Aeronautical and Space The A330 and A340 aircraft, using the power generation Sciences, Journal (ISSN 0021-4663). vol. 37, no. 423, 1989, p. technology and avionics of the A320. are described in detail. The 202-204. In Japanese, with abstract in English. CFM 56-5C2 engine has been selected for the A340 (providing Simplified equations of energy and momentum conservation 31,200 Ibs of take-off thrust), while three engines are considered lead to a closed form expression of effective exhaust velocity of for the A330: (1) the CF6 80-El (providing 65.500 Ibs of take-off an air-breathing engine which characterizes an aerospace plane. thrust); (2) the PW4164 (providing 64,000 Ibs of take-off thrust); Following features of hypervelocity propulsion are disclosed. First, and (3) the RB 211-524L (providing 65,000 Ibs of take-off thrust). the intake air is effective as an oxygen carrier, a momentum carrier, Other features of the A330 and A340 aircraft include a rocking and an energy carrier, depending on the flight velocity. Second, bogie design for the landing gear system and optimized actual thermochemical values allow only hydrogen to be the fuel aerodynamic surfaces. R.R. of an aerospace plane. Third, the efficiency of energy utilization for intake air must exceed 90 percent in order to reach near an A8945126 orbital speed. Author SOCIETY OF FLIGHT TEST ENGINEERS, ANNUAL SYMPOSIUM, 19TH, ARLINGTON, TX, AUG. 14-18, 1988, A8945030 PROCEEDINGS RAFALE - DASSAULT’S NEW DAWN Symposium sponsored by the Society of Flight Test Engineers.
662 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Lancaster, CA, Society of Flight Test Engineers, 1988, 220 p. For JOSEPH N. BEASLEY and RICHARD T. BLACK (USAF, Flight individual items see A89-45127 to A89-45146. Test Center, Edwards AFB, CA) IN: Society of Flight Test The present symposium includes such topics as powered lift Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, aircraft takeoff, air-to-air combat helicopter development, the flight 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, testing of a multimegawatt wind turbine, and outer wing residual 1988, p. 111-5.1 to 111-5.7. strength testing of the C-130 Hercules. Papers are also presented The application of AI technology to flight testing has been on a real-time flight test telemetry system, the establishment of motivated by such problems as the recent data explosion, increased AI technology in a flight test environment, a video-based noncontact flying schedules, inexperienced engineers, and engineer attrition. system for motion measurement, and low-cost equipment for flight Special attention is given to the development of an expert system test film and video evaluation. Also considered are a new flight that identifies flight maneuvers (such as sidelip, 1-g roll, windup flutter excitation system, the measurement of linear and angular turning, maximum g roll, slowdown turning, and 1-g deceleration) displacement in prototype aircraft, and aircraft development test from flight data. It is pointed out that the knowledge base for the and evaluation. R.R. event identifier is simple, readable, and easily modified. Limitations of the system are addressed. R.R. A89-45127 POWERED LIFT AIRCRAFT TAKE OFF CLIMB A89-45139 PERFORMANCE WITH ONE ENGINE INOPERATIVE NUMERICAL MODELLING OF FLIGHT DYNAMICS AND JAMES R. ARNOLD and MICHELLE M. CORNING (FAA, FLIGHT TEST DATA IDENTIFICATION OF A JET TRAINER Washington, DC) IN: Society of Flight Test Engineers, Annual AIRPLANE Symposium, 19th, Arlington, TX, Aug. 14-18, 1988, proceedings. ZBlGNlEW DZYGADLO (Instytut Lotnictwa, Warsaw, Poland) and Lancaster, CA, Society of Flight Test Engineers, 1988, p. 1-2.1 to JERZY MARYNIAK (Warszawa, Politechnika, Warsaw, Poland) IN: 1-2.5. Society of Flight Test Engineers, Annual Symposium, 19th, An analytical method for predicting the one engine inoperative Arlington, TX, Aug. 14-18, 1988, proceedings. Lancaster. CA, takeoff climb performance of a powered lift aircraft is presented. Society of Flight Test Engineers, 1988, p. IV-4.1 to IV-4.11. refs The analysis is intended to include the possibility of a major aircraft Flight test data identification methods and digital simulation configuration conversion and to highlight potential safety critical techniques are used to model the flight dynamics and identify the takeoff flight envelopes. The level flight data of the Bell XV-15 aerodynamic performance and handling qualities of a jet trainer Tilt Rotor is used to illustrate the method, and the results of this airplane. Wind tunnel test data, theoretical analysis results, and analysis is compared to the FAA Proposed Powered Lift Criteria. flight test results are used as input to nonlinear mathematical Author models. The method has been successfully demonstrated using the example of the TS-11 lskra jet trainer airplane. R.R. A89-45128 COST-EFFECTIVE APPROACH TO FLIGHT TESTING THE A89-45140 'CASMU SKYSHARK' A STAND-OFF WEAPON DISPENSER A NEW FLIGHT FLUlTER EXCITATION SYSTEM G. FERRE'ITI and P. DURANTI (Aeritalia S.p.A., Turin, Italy) IN: WILMER H. REED, Ill (Dynamic Engineering, Inc., Newport News, Society of Flight Test Engineers, Annual Symposium, 19th, VA) IN: Society of Flight Test Engineers, Annual Symposium, Arlington, TX, Aug. 14-18, 1988, Proceedings. Lancaster, CA, 19th, Arlington, TX, Aug. 14-18, 1988, Proceedings. Lancaster, Society of Flight Test Engineers, 1988, p. 1-3.1 to 1-3.13. CA, Society of Flight Test Engineers, 1988, p. V-1.1 to V-1.7. The planning, designing, and carrying-out of the preliminary refs flight test program of the stand-off weapon dispenser Skyshark An aerodynamic vane-type excitation system is described which are discussed. The goals of the demonstration phase include can be powered by a small dc motor and readily installed on a proof-of-concept testing, the definition of the final aerodynamic test aircraft. The system consists of a fixed vane with a rotating configuration, and the assessement of the effectiveness of the slotted cylinder installed at the trailing edge. In the system, the flight control and armament systems. The most cost-effective sinusoidal excitation frequency is determined by the cylinder's mission sequence is found to be: (1) release from the parent rotation frequency, and the dynamic force amplitude by the degree aircraft; (2) separation; (3) controlled flight and deceleration; (4) of slot opening. Results obtained from wind tunnmel exciter model firing of submunitions; (5) climb; (6) parachute deployment; (7) tests performed as low subsonic and transonic speeds show that sinking and alighting on water; and (8) retrieval via helicopter. the present system is capable, with very little electrical power, of R.R. producing dynamic forces comparable to those produced by conventional oscillating-vane systems. R.R. A89-45 132# C-130 HERCULES OUTER WING RESIDUAL STRENGTH A89-45141' National Aeronautics and Space Administration. Flight TESTS Research Center, Edwards, CA. ANDREW T. ZIMMERMAN (Lockheed Aeronautical Systems Co., CURRENT FLIGHT TEST EXPERIENCE RELATED TO Marietta, GA) IN: Society of Flight Test Engineers, Annual STRUCTURAL DIVERGENCE OF FORWARD-SWEPT WINGS Symposium, 19th, Arlington, TX, Aug. 14-18, 1988, Proceedings. LAWRENCE S. SCHUSTER and WILLIAM A. LOKOS (NASA, Flight Lancaster, CA, Society of Flight Test Engineers, 1988, p. 11-4.1 to Research Center, Edwards, CA) IN: Society of Flight Test 11-4.12. Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, Static test were performed to calculate the residual strength 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, of used outer wings removed from four operational C-130E and 1988. p. V-2.1 to V-2.10. Previously announced in STAR as one C-130A aircraft. The results showed one of the three C-130E NEE-24633. test specimens with in-service repairs to the wing structure to fail Flight testing the X-29A forward-swept wing aircraft has required at slightly less than the limit load and the other two to fail at less development of new flight test techniques to accomplish subcritical than 150 percent. The C-130E test specimen with no repairs failed extrapolations to the actual structural divergence dynamic pressure at 171 percent of the limit load. Existing USAF NDI procedures of the aircraft. This paper provides current experience related to could not detect fatigue cracks which were the cause of test applying these techniques to analysis of flight data from the specimen failures at less than 150 percent of the design limit forward-swept wing in order to assess the applicability of these load, and new NDI methods were developed to improve detection techniques to flight test data. The measurements required, of critical fatigue damage in the wing structure. R.R. manuevers flown, and flight test conditions are described. Supporting analytical predictions for the techniques are described A89-45135 and the results using flight data are compared to these predictions. ESTABLISHING ARTIFICIAL INTELLIGENCE TECHNOLOGY IN Use of the results during envelope expansion and the resulting A FLIGHT TEST ENVIRONMENT modifications to the techniques are discussed. Some of the analysis
663 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE challenges that occurred are addressed and some preliminary DAFICS system is discussed, and operational experience using conclusions and recommendations are made relative to the DAFICS is described. C.D. usefulness of these techniques in the flight test environment. Author A89-45163 A LOOK AT THE MODEL 360 DEVELOPMENT A8945145 RON MECKLIN (Boeing Helicopters, Philadelphia, PA) IN: 1988 THE MILITARY DASH 8 FLIGHT TEST PROGRAM report to the aerospace profession; Society of Experimental Test PAUL F. W. ADAMS and J. D. COLE (De Havilland Aircraft Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, Company of Canada, Ltd., Downsview) IN: Society of Flight Test proceedings. Lancaster, CA, Society of Experimental Test Pilots, Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, 1988, p. 207-222. 1988, proceedings. Lancaster, CA, Society of Flight Test Engineers, The Model 360 helicopter is a new technology flight 1988, p. VI-3.1 to VI-3.5. demonstrator used to investigate the extensive use of composite Differences between the civil and military versions of the Dash materials. This paper presents a description of the aircraft along 8 aircraft are pointed out, and results of the military Dash 8 flight with unique tooling and fabrication methods used to assemble the test program are discussed. The stability and control tests included composite airframe and components. Simulation activities sidelip, stall, longitudinal stability, and response to sudden engine conducted prior to flying this new aircraft and the flight test results failure. The avionics system tests included bearing operation, beam obtained to date are described. C. D. tilting, antenna stabilization, and power density measurement. The navigation training system instruments include a ground mapping A89-45167 system, an inertial navigation system, and a dead reckoning A SUPERSONIC CRUISE FIGHTER DESIGN computer. Test results have confirmed the effectiveness of the C EVEREST E. RlCClONl (Northrop Corp., Aircraft Div., Hawthorne, 142 Transport and the CT 142 Navigation Trainer. R.R. CA) IN: 1988 report to the aerospace profession; Society of Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. A8945146 13-15, 1988, proceedings. Lancaster, CA, Society of Experimental SERVICE SUITABILITY TESTING OF THE F/A-l8A FOR USE Test Pilots, 1988, p. 321-333. BY THE BLUE ANGELS NAVY FLIGHT DEMONSTRATION A design is presented for an affordable, reasonably small fighter TEAM which has supersonic mobility, defined as the ability quickly to EUGENE J. FRASER and BRUCE A. KAPLAN (US. Navy, Naval generate high supersonic speeds and to persist in flying at those Air Test Center, Patuxent River, MD) IN: Society of Flight Test speeds. The performance, supersonic persistence, and supersonic Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, range of this supersonic cruise fighter (SCF) are examined. The 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, value of supersonic mobility in battle and the SCF's remarkable 1988, p. VI-4.1 to VI-4.16. potential for intercept are briefly addressed. C.D. The results of continuous horizontal and vertical roll tests, along with flying quality and fuel system studies, for the FIA-18A aircraft A89-45168 (selected for the Blue Angels Flight Demonstration Team) are X-15 PILOT-IN-THE-LOOP AND REDUNDANT/EMERGENCY reported. The longitudinal trim system, the mechanical SYSTEMS EVALUATION characteristics of the FCS, the static longitudinal stability, the RICHARD E. SMITH (Honeywell, Inc., Defense Avionics Systems maneuvering longitudinal stability, and the formation flight behavior Div., Albuquerque, NM) IN: 1988 report to the aerospace of the FIA-18A were investigated for the case of aircraft employing profession; Society of Experimental Test Pilots, Symposium, 32nd, an artificial force system for position control. The results show Beverly Hills, CA, Oct. 13-15, 1988, Proceedings. Lancaster, CA, that the small pitch and heading oscillations and small lateral Society of Experimental Test Pilots, 1988, p. 334-357. displacements produced by the near body axis roll improved the The results are reported of a study of the first 47 free flights aesthetic qualities of the continuous horizontal roll maneuver. of the X-15 Research Airplane through Jaunuary 15, 1962 are R.R. reviewed. It is concluded that a pilot in the control loop and redundantlemergency systems in the X-15 provided dramatic net A8945 156 benefits in terms of mission success and safe aircraft recovery. THE ATF IS ON ITS WAY There were also some detrimental effects, but these were JAY JABOUR and DON NEWMAN (USAF, Advanced Tactical overshadowed by the pilot nad redundancy benefits. C.D. Fighter System Program Office, Edwards AFB, CA) IN: 1988 report to the aerospace profession; Society of Experimental Test A8945207 Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, FULL SCALE FATIGUE CRACK GROWTH TEST OF Proceedings. Lancaster, CA, Society of Experimental Test Pilots, ADVANCED JET TRAINER AT-3 1988, p. 90-108. S. S. WANG and R. C. CHU (Aeronautical Industry Development This paper presents an overview of the development of the Center, Taichung, Republic of China) Theoretical and Applied USAF's next air superiority fighter - the Advanced Tactical Fighter Fracture Mechanics (ISSN 0167-8442), vol. 11, May 1989, p. (ATF). The management of the DemonstrationIValidation phase 71-91. refs of the ATF is discussed, and the avionics approach of the ATF is The test equipment, procedures, and results of full-scale fatigue examined. The testing that will be done in the DemonstrationNalida- tests on the AT-3 jet trainer aircraft are described in detail and tion phase is described. C.D. illustrated with extensive diagrams, drawings, graphs, photographs, and tables of numerical data. The tests included 30,000 h of a A8945160 training-mission spectrum, 7500 h of special-service load spectra, DIGITAL FLIGHT AND INLET CONTROL IN THE SR-71 and 6170 cycles of 6-G symmetrical pull-up to full-scale fatigue THOMAS V. TILDEN (USAF, Logistics Command, Wright-Patterson load. Particular attention is given to the design of the test program, AFB, OH) IN: 1988 report to the aerospace profession; Society the NDE and fatigue-life analysis methods applied, and the of Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, damage-tolerant crack-control strategy. The service life of the AT-3 Oct. 13-15, 1988, Proceedings. Lancaster, CA, Society of is estimated as more than 7500 h. T.K. Experimental Test Pilots, 1988, p. 167-181. refs The original analog controls in SR-71 for stability augmentation, A89-46278# autopilot, inlet control, air data computation, and pitch warning OPTIMIZATION DESIGN FOR SUPPRESSING 'GROUND functions were replaced by a single three-computer digital control RESONANCE OF HELICOPTERS system. The Digital Automatic Flight and Inlet Control System ZHONGQUAN GU (Nanjing Aeronautical Institute, People's (DAFICS) is described in this paper. Computer self-testing in the Republic of China) Acta Aeronautica et Astronautica Sinica (ISSN
664 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
1000-6893), vol. 10, March 1989. p. A113-A118. In Chinese, with An investigation of the stability characteristics of the F-16 abstract in English. MCID-771 inlet was conducted as a result of an inlet shock The design problem for suppressing 'ground resonance' of instability which occurred during flight test. Wind tunnel test data helicopters is studied. A method for optimally designing the stiffness for the production F-16 vehicle configuration indicated that the and damping parameters of the system with specified requirements inlet operation should be stable for conditions corresponding to based on pole region placement in control theory and optimization those of the flight test incident. However, a flight test air data is presented. Effective design criteria and procedures are presented probe (ADP), which is larger than the ADP used on production according to the 'ground resonance' principle. Three typical aircraft, was found to create a disturbance in the forebody flow calculation models are examined as examples. C.D. field which can adversely interact with the inlet shock. This interaction between the shock and the disturbance created by the A89-46470 ADP causes shock instabilities to occur at higher inlet corrected PROBABILISTIC ANALYSIS OF AIRCRAFT STRUCTURE airflow than with the production ADP. The effect of the ADP was PAUL A. ZlELlNSKl (Boeing Military Airplane Co., Wichita, KS) predominant at negative and low positive values of angle-of-attack. IN: Annual Reliability and Maintainability Symposium, Atlanta, GA, As a result of the investigation, new inlet operational airflow limits Jan. 24-26, 1989, Proceedings. New York, Institute of Electrical were developed for the aircraft configuration with the flight test and Electronics Engineers, Inc., 1989, p. 140-145. refs ADP installed. Author Probabilistic structural mechanics (PSM) has been promoted for use in the design of products. The author presents the practical A89-46853# methods for applying PSM to critical aircraft component fault-tree 1-4 INLETIENGINE COMPATIBILITY FLIGHT TEST RESULTS analysis. The B-1B Common Strategic Rotary Launcher (CSRL) TADAYUKI HAMADA, MASAHIRO AKAGI (Japan Defense Agency, fault-tree analysis is used as a demonstative example of mechanical Technical Research and Development Institute, Gifu), DAISUKE component failure probabilities calculated using PSM. The CSRL TODA (Air Self-Defense Force, Tokyo, Japan), HlROSHl components demonstrate how this methodology accounts for SHlMAZAKl (Kawasaki Heavy Industries Co., Ltd, Japan), and aircraft limit loads, limit load exceedances per flight hour, material MITSUHARU OHMOMO (Ishikawajima-Harima Heavy Industries properties, and stress analysis or structural test results. I.E. Co., Ltd., Tokyo, Japan) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 8 A89-46705# P. EASY METHOD OF MATCHING FIGHTER ENGINE TO (AIAA PAPER 89-2466) AIRFRAME FOR USE IN AIRCRAFT ENGINE DESIGN Results are presented on the flight tests conducted to evaluate COURSES the enginelinlet compatibility for the F3-30 engine developed for JACK D. MATTINGLY (USAF, Aero-Propulsion and Power the T-4 intermediate trainer. The test program included all the Laboratory and Institute of Technology, Wright-Patterson AFB, critical maneuvering conditions (including spin flight) involved in OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, the T-4 training missions. Measurements of the pressure distortion 25th, Monterey, CA, July 10-13, 1989. 14 p. refs level and the pressure recovery factor were performed by an inlet (AIAA PAPER 89-2260) rake which had 30 pressure probes (six-leg five-ring configuration) The proper match of the engine(s) to the airframe affects both installed at the engine face. The results of T-4/F3-30 flight tests aircraft size and life cycle cost. A fast and straightforward method showed no engine stalls or flame-outs beyond the design goal is developed and used for the matching of fighter engine(s) to envelopes; the engine operation was satisfactory to 60-deg of the airframes during conceptual design. A thrust-lapse equation is angle-of-attack and 40-deg sideslip at idle rating. IS. developed for the dual-spool, mixed-flow, afterburning turbofan type of engine based on the installation losses of 'Aircraft Engine Design' A89-46864'# National Aeronautics and Space Administration. and the performance predictions of the cycle analysis programs Langley Research Center, Hampton, VA. ONX and OFFX. Using system performance requirements, the NACELLE/PYLON INTERFERENCE STUDY ON A effects of aircraft thrust-to-weight, wing loading, and engine cycle 1/17TH-SCALE, TWIN-ENGINE, LOW-WING TRANSPORT on takeoff weight are analyzed and example design course results MODEL presented. Author ODlS C. PENDERGRAFT, JR., ANTHONY M. INGRALDI, RICHARD J. RE (NASA, Langley Research Center, Hampton, VA), and TIMMY A89-46773'# National Aeronautics and Space Administration. T. KARIYA (Vigyan Research Associates, Inc., Hampton, VA) Langley Research Center, Hampton, VA. AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, NOISE CONSIDERATIONS FOR TILTROTOR Monterey, CA. July 10-13, 1989. 10 p. refs ROBERT J. HUSTON, ROBERT A. GOLUB, and JAMES G. YU (AIAA PAPER 89-2480) (NASA, Langley Research Center, Hampton, VA) AIAA, ASME, NASA-Langley has conducted wind tunnel tests of a twin-engine, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, low-wing transport aircraft configuration with 10.8-aspect ratio CA, July 10-13, 1989. 15 p. refs supercritical wing, in order to ascertain and compare the (AIAA PAPER 89-2359) winghacelle interference effects of through-flow nacelled A projection is made of the technology-development simulating 'superfan' very high bypass ratio (BPR =20) turbofans requirements faced by aircraft designers contemplating the and current-technology (BPR=6) turbofans. Measurements of evolution of V-22-type tilt-rotor aircraft technology into a civilian model forces and moments have been obtained, together with tilt-rotor commuter aircraft of the requisite scale and payload. These extensive external static pressure measurement on the model's research challenges are noted to often involve the reduction of wings, nacelles, and pylons in the Mach 0.5-0.8range, at angles noise level to values tolerated by passengers within the cabin of attack in the -4 to +8 deg range. The superfan nacelles exhibit and communities in the vicinity of airports, especially during hover a significant advantage over current-technology turbofan nacelles, and in the course of transition from vertical to horizontal flight when the superfan's SFC gains are taken into account. O.C. (and vice-versa). Noise-generation and noise-radiation characteris- tics research has been undertaken using the XV-15 tilt-rotor proof-of- A89-46866# concept aircraft. O.C. AERODYNAMIC DESIGN AND TESTING OF FOKKER 50 NACELLE AND INTAKE DUCTS A89-46852# J. VAN HENGST, N. VOOGT, and G. J. SCHIPHOLT (Fokker F-16 INLET STABILITY INVESTIGATION Aircraft, Amsterdam, Netherlands) AIAA, ASME, SAE, and ASEE, B. N. MCCALLUM (General Dynamics Corp., Fort Worth, TX) AIAA, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. ASME, SAE, and ASEE, Joint Propulsion Conference, 25th. 8 P. Monterey, CA, July 10-13, 1989. 8 p. (AIAA PAPER 89-2483) . (AIAA PAPER 89-2465) The paper describes the aerodynamic design process of the
665 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Fokker 50 nacelle and its intake ducts for engine and oil cooler. methodology is coded on IBM PC in BASIC language. Samples of Much emphasis has been given to the prediction and prevention the design and off-design performance analysis of generic of ice accretion inside and around the duct. CFD is shown to play hypersonic vehicles are presented. Author an important role complementary to wind tunnel and flight testing. Author A89-47101# FIGHTER AIRCRAFT AFFORDABILITY, SURVIVABILITY, AND A89-46867# EFFECTIVENESS THROUGH MULTI-FUNCTION NOZZLES DESIGN AND TESTING OF A COMMON ENGINE AND PAUL W. HERRICK (United Technologies Corp., Pratt and Whitney NACELLE FOR THE FOKKER 100 AND GULFSTREAM GIV Group, West Palm Beach, FL) AIAA, ASME, SAE, and ASEE, AIRPLANES Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. H. NAWROCKI (Gulfstream Aerospace Corp., Savannah, GA), J. 9 p. refs VAN HENGST, and L. DE HAlJ (Fokker Aircraft, Amsterdam, (AIAA PAPER 89-2815) Netherlands) AIAA, ASME, SAE, and ASEE, Joint Propulsion Next-generation fighters will be able to maneuver at higher Conference, 25th, Monterey, CA, July 10-13, 1989. 14 p. angles of attack, higher angular rotation rates and accelerations, (AIAA PAPER 89-2486) and quicker flight path turn and deceleration rates, through the The design of an engine-nacelle configuration suitable for use incorporation of multifunction nozzles (MFNs) that allow pitch and in two aircraft (a commercial airline jet and a business jet) that yaw thrust vectoring, thrust reversing, and the ability to optimize differ in both the configuration and flight envelope is described. nozzle area ratios. These performance enhancements call for a The configuration, the flight and inlet flow angle envelopes, and fundamental change in fighter aircraft design philosophy, involving the engine selected for both aircraft are examined, and, on the the supplementing or entire obviation of empennage surfaces by basis of these characteristics, the design requirements for a the use of MFNs. Fighter affordability is expected to be enhanced common nacelle (Le., those of the intake, nacelle, exhaust, mass through reductions in airframe size and cost, greater fuel efficiency, flow, and intake flow) are established. Based on these less stringent basing requirements, lower peacetime attrition, and requirements, the preliminary nacelle dimensions were selected reduced pilot training requirements; survivability will also be and wind-tunnel tested. The final configuration of the common enhanced through reductions in detectability and vulnerability. engine nacelle selected on the basis of the results of flight testing O.C. is presented. IS. A89-47165*# National Aeronautics and Space Administration. A89-46937# Ames Research Center, Moffett Field, CA. CONFIGURATION STUDIES FOR A REGIONAL AIRLINER LARGE-SCALE WIND TUNNEL TESTS OF AN EJECTOR-LIFT USING OPEN-ROTOR ULTRA-HIGH-BYPASS-RATIO ENGINES STOVL AIRCRAFT MODEL B. FISCHER and H. G. KLUG (Messerschmitt-Boelkow-Blohm VICTOR CORSIGLIA. MICHAEL DUDLEY, BRIAN SMITH (NASA, GmbH, Hamburg, Federal Republic of Germany) AIAA, ASME, Ames Research Center, Moffett Field, CA), and JOSEPH SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, FARBRIDGE (Boeing Canada, de Havilland Aircraft Div., Toronto) CA, July 10-13, 1989. 8 p. AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, (AIAA PAPER 89-2580) Monterey, CA, July 10-13, 1989. 13 p. refs This paper reviews aspects of using open-rotor ultrahigh bypass (AIAA PAPER 89-2905) engines in regional aircraft. Favorable and less favorable The initial results of a test program conducted on an characteristics are discussed. Typical problems caused by ejector-augmented-lift STOVL aircraft design in the NASA-Ames open-rotor engines as to configuration, structure, and systems are 40-by-80-Foot Wind Tunnel has established the efficient presented. To assess the overall effect upon economics, two performance of this full-scale aircraft realization of the aircraft defined to perform the same mission, but using open-rotor propulsion-system configuration. It has also been noted that the engines and turbofan engines respectively, are compared. Direct generation of larger lift-augmentation ratios in this form than in operating cost differences are found to be relatively small, component tests. In addition, it is found that configurations depending upon operational and economic conditions (e.g., aircraft possessing thrust/weight ratios and wing loadings representative utilization, fuel price). Under fuel prices higher than current ones, of current practice could, when outfitted with the present propulsion there is a clear case for the regional airliner powered by open-rotor scheme, produce adequate level-flight acceleration through ultrahigh bypass engines. Author transition from VTOL hover to wingborne flight. O.C.
A89-47012# N89-25146'# National Aeronautics and Space Administration. RAPID METHODOLOGY FOR DESIGN AND PERFORMANCE Langley Research Center, Hampton, VA. PREDICTION OF INTEGRATED SCRAMJET/HYPERSONIC RECENT ADVANCES IN MULTIDISCIPLINARY ANALYSIS AND VEHICLE OPTIMIZATION, PART 1 HIDE0 IKAWA (Northrop Corp., Aircraft Div., Hawthorne, CA) JEAN-FRANCOIS M. BARTHELEMY, ed. Washington Apr. AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, 1989 527 p Symposium held in Hampton, VA, 28-30 Sep. Monterey, CA, July 10-13, 1989. 13 p. Research supported by 1988; sponsored by NASA, Langley Research Center, NASA, Northrop Corp. Lewis Research Center, and Wright Research Development Center (Contract F33615-87-C-3606) (NASA-CP-3031-PT-1; L-16568-PT-1; NAS 1.5513031-PT-1) (AIAA PAPER 89-2682) Avail: NTlS HC A23/MF A01 CSCL 01/3 The design integration of a supersonic combustion ramjet with This three-part document contains a collection of technical the airframe dictates the mission success of transatmosphericboost papers presented at the Second NASA/Air Force Symposium on or hypersonic cruise vehicle. The special interest must be given Recent Advances in Multidisciplinary Analysis and Optimization, for the hypersonic atmospheric boost phase of the mission where held September 28-30, 1988 in Hampton, Virginia. The topics most of the energy is expanded. For this purpose, the effective covered include: helicopter design, aeroelastic tailoring, control of specific impulse and the thrust to weight ratio of accelerating vehicle aeroelastic structures, dynamics and control of flexible structures, play the key role in establishing the operational efficiency. A structural design, design of large engineering systems, application methodology that permits a quick performance evaluation of an of artificial intelligence, shape optimization, software development idealized, integrated scramjet/hypersonic vehicle for preliminary and implementation, and sensitivity analysis. design analysis is discussed. The methodology capability includes: (1) designing an integrated vehicle consisting of the forebody inlet, N89-25147'# Grumman Aerospace Corp., Bethpage, NY. Aircraft supersonic flow combustor, and afterbody expansion nozzle; (2) Systems Div. generating the design and off-design performance data; and (3) APPLICATIONS OF INTEGRATED DESIGN/ANALYSIS performing many design iterations for trade-off study. The SYSTEMS IN AEROSPACE STRUCTURAL DESIGN
666 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
PHILIP MASON, EDWIN LERNER, and LAWRENCE SOBEL ln N89-25152'# California Univ., Los Angeles. Dept. of Mechanical, NASA. Langley Research Center, Recent Advances in Aerospace and Nuclear Engineering. Multidisciplinary Analysis and Optimization, Part 1 p 3-37 Apr. STRUCTURAL OPTIMIZATION OF ROTOR BLADES WITH 1989 STRAIGHT AND SWEPT TIPS SUBJECT TO AEROELASTIC Avail: NTlS HC A23/MF A01 CSCL 01/3 CONSTRAINTS Integrated structural analysis and design systems and structural PERETZ P. FRIEDMANN and ROBERTO CELl (Maryland Univ., optimization procedures are being used in a production College Park.) ln NASA. Langley Research Center, Recent environment. Successful use of these systems requires experienced Advances in Multidisciplinary Analysis and Optimization, Part 1 p personnel. Interactive computer graphics can and will play a 145-162 Apr. 1989 significant role in the analysis, optimization, design and Avail: NTlS HC A23/MF A01 CSCL 01/3 manufacturing areas. Practical structural optimization procedures The main conclusions obtained in the present study are are tools that must be made available to the team. Much work summarized. Their application to the structural optimization of a still needs to be done to tie finite-element modeling to actual helicopter blade should be limited by the assumptions used in design details which are being tracked on systems such as CADAM obtaining the numerical results presented here. The optimum design or CATIA. More work needs to be done to automate the detailed procedure described here is very efficient, and can produce design and analysis process. More emphasis should be placed on improved designs with a very limited number of precise analyses. the real design problems. Author The method of constructing the approximate problem is such that previously conducted aeroelastic analyses can be reused in a new optimization problem. For example, if an optimization study is preceded by a parametric study in which the effect of various N89-25150'# National Aeronautics and Space Administration. combinations of blade design parameters is examined, all the Langley Research Center, Hampton, VA. aeroelastic analyses performed for the parametric study can be OVERVIEW OF DYNAMICS INTEGRATION RESEARCH (DIR) reutilized in the optimization study. This is not possible when the PROGRAM AT LANGLEY RESEARCH CENTER approximate problem is built from Taylor series expansions. The STEVEN M. SLIWA and IRVING ABEL ln its Recent Advances results of the optimization are quite sensitive to the aeroelastic in Multidisciplinary Analysis and Optimization, Part 1 p 79-105 Apr. stability margins required of the blade. In the optimization of case 1989 2, changing the aeroelastic stability constraints from simply requiring Avail: NTlS HC A23/MF A01 CSCL 01 /3 that the blade be stable in hover, to requiring that the stability Research goals and objectives for an ongoing activity at Langley margins be maintained during the course of the optimization, Research Center (LaRC) are described. The activity is aimed reduced the gains in n/rev vibration levels by more than 50 percent. principally at dynamics optimization for aircraft. The effort involves The introduction of tip sweep can reduce the n/rev vertical hub active participation by the Flight Systems, Structures, and shears beyond the level that can be obtained by just modifying Electronics directorates at LaRC. The Functional Integration the mass and stiffness distributions of the blade. Author Technology (FIT) team has been pursuing related goals since 1985. A prime goal has been the integration and optimization of vehicle N89-25153"# Georgia Inst. of Tech., Atlanta. School of dynamics through collaboration at the basic principles or equation Aerospace Engineering. level. Some significant technical progress has been accomplished OPTIMIZATION OF ROTOR BLADES FOR COMBINED since then and is reflected here. An augmentation for this activity, STRUCTURAL, PERFORMANCE, AND AEROELASTIC Dynamics Integration Research (DIR), has been proposed to NASA CHARACTERISTICS Headquarters and is being considered for funding in FY 1990 or DAVID A. PETERS and Y. P. CHENG ln NASA. Langley Research FY 1991. Author Center, Recent Advances in Multidisciplinary Analysis and Optimization, Part 1 p 163-180 Apr. 1989 Avail: NTlS HC A23/MF A01 CSCL 01 /3 N89-25151"# National Aeronautics and Space Administration. The strategies whereby helicopter rotor blades can be optimized Langley Research Center, Hampton, VA. for combined structural, inertial, dynamic, aeroelastic, and AN INITIATIVE IN MULTIDISCIPLINARY OPTIMIZATION OF aerodynamic performance characteristics are outlined. There are ROTORCRAFT three key ingredients in the successful execution of such an HOWARD M. ADELMAN and WAYNE R. MANTAY (Army interdisciplinary optimization. The first is the definition of a Aerostructures Directorate, Hampton, VA.) ln its Recent Advances satisfactory performance index that combines all aspects of the in Multidisciplinary Analysis and Optimization, Part 1 p 109-144 problem without too many constraints. The second element is the Apr. 1989 Previously announced as N89-15108 judicious choice of computationally efficient analysis tools for the Avail: NTlS HC A23/MF A01 CSCL 01/3 various quantitative components in both the cost functional and Described is a joint NASA/Army initiative at the Langley constraints. The third element is an effective strategy for combining Research Center to develop optimization procedures aimed at the various disciplines either in parallel or sequential improving the rotor blade design process by integrating appropriate optimizations. Author disciplines and accounting for important interactions among the disciplines. The activity is being guided by a Steering Committee N89-25154'# McDonnell-Douglas Helicopter Co., Mesa, AZ. made up of key NASA and Army researchers and managers. The TRANSONIC AIRFOIL DESIGN FOR HELICOPTER ROTOR committee, which has been named IRASC (Integrated Rotorcraft APPLICATIONS Analysis Steering Committee), has defined two principal foci for AHMED A. HASSAN and B. JACKSON ln NASA. Langley the activity: a white paper which sets forth the goals and plans of Research Center, Recent Advances in Multidisciplinary Analysis the effort; and a rotor design project which will validate the basic and Optimization, Part 1 p 181-193 Apr. 1989 constituents, as well as the overall design methodology for Avail: NTlS HC A23/MF A01 CSCL 0113 multidisciplinary optimization. The optimization formulation is Despite the fact that the flow over a rotor blade is' strongly described in terms of the objective function, design variables, and influenced by locally three-dimensional and unsteady effects, constraints. Additionally, some of the analysis aspects are practical experience has always demonstrated that substantial discussed and an initial attempt at defining the interdisciplinary improvements in the aerodynamic performance can be gained by couplings is summarized. At this writing, some significant progress improving the steady two-dimensional charateristics of the airfoil(s) has been made, principally in the areas of single discipline employed. The two phenomena known to have great impact on optimization. Results are given which represent accomplishments the overall rotor performance are: (1) retreating blade stall with in rotor aerodynamic performance optimization for minimum hover the associated large pressure drag, and (2) compressibility effects horsepower, rotor dynamic optimization for vibration reduction, and on the advancing blade leading to shock formation and the rotor structural optimization for minimum weight. Author associated wave drag and boundary-layer separation losses. It
667 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
was concluded that: optimization routines are a powerful tool for N89-25157*# McDonnell-Douglas Helicopter Co., Mesa, AZ. finding solutions to multiple design point problems; the optimization MULTI-OBJECTIVE/LOADlNGOPTIMIZATION FOR ROTATING process must be guided by the judicious choice of geometric and COMPOSITE FLEXBEAMS aerodynamic constraints; optimization routines should be BRIAN K. HAMILTON and JAMES R. PETERS ln NASA. Langley appropriately coupled to viscous, not inviscid, transonic flow Research Center, Recent Advances in Multidisciplinary Analysis solvers; hybrid design procedures in conjunction with optimization and Optimization, Part 1 p 235-256 Apr. 1989 routines represent the most efficient approach for rotor airfroil Avail: NTlS HC A23/MF A01 CSCL 01 /3 design; unsteady effects resulting in the delay of lift and moment With the evolution of advanced composites, the feasibility of stall should be modeled using simple empirical relations; and inflight designing bearingless rotor systems for high speed, demanding optimization of aerodynamic loads (e.g., use of variable rate maneuver envelopes, and high aircraft gross weights has become blowing, flaps, etc.) can satisfy any number of requirements at a reality. These systems eliminate the need for hinges and heavily design and off-design conditions. Author loaded bearings by incorporating a composite flexbeam structure which accommodates flapping, lead-lag, and feathering motions by bending and twisting while reacting full blade centrifugal force. The flight characteristics of a bearingless rotor system are largely N89-25155'# Maryland Univ., College Park. Dept. of Aerospace dependent on hub design, and the principal element in this type Engineering. of system is the composite flexbeam. As in any hub design, trade EFFICIENT SENSITIVITY ANALYSIS AND OPTIMIZATION OF off studies must be performed in order to optimize performance, A HELICOPTER ROTOR dynamics (stability). handling qualities, and stresses. However, JOON W. LIM and INDERJIT CHOPRA ln NASA. Langley since the flexbeam structure is the primary component which will Research Center, Recent Advances in Multidisciplinary Analysis determine the balance of these characteristics, its design and and Optimization, Part 1 p 195-208 Apr. 1989 fabrication are not straightforward. It was concluded that: pitchcase Avail: NTlS HC A23/MF A01 CSCL 01/3 and snubber damper representations are required in the flexbeam Aeroelastic optimization of a system essentially consists of model for proper sizing resulting from dynamic requirements; the determination of the optimum values of design variables which optimization is necessary for flexbeam design, since it reduces minimize the objective function and satisfy certain aeroelastic and the design iteration time and results in an improved design; and geometric constraints. The process of aeroelastic optimization inclusion of multiple flight conditions and their corresponding fatigue analysis is illustrated. To carry out aeroelastic optimization allowables is necessary for the optimization procedure. Author effectively, one needs a reliable analysis procedure to determine steady response and stability of a rotor system in forward flight. The rotor dynamic analysis used in the present study developed N89-25159'# Hall (David) Consulting, Sunnyvale, CA. at of finite inhouse the University Maryland is based on elements DEVELOPMENT OF A MICROCOMPUTER BASED in space and time. The analysis consists of two major phases: INTEGRATED DESIGN SYSTEM FOR HIGH ALTITUDE LONG vehicle trim and rotor steady response (coupled trim analysis), ENDURANCE AIRCRAFT and aeroelastic stability of the blade. For a reduction of helicopter DAVID W. HALL and J. EDWARD ROGAN ln NASA. Langley vibration, the optimization process requires the sensitivity Research Center, Recent Advances in Multidisciplinary Analysis derivatives of the objective function and aeroelastic stability and Optimization, Part 1 p 275-296 Apr. 1989 Previously constraints. For this, the derivatives of steady response, hub loads announced in IAA as A88-53734 and blade stability roots are calculated using a direct analytical Avail: NTlS HC A23/MF A01 CSCL 0113 approach. An automated optimization procedure is developed by A microcomputer-basedintegration of aircraft design disciplines coupling the rotor dynamic analysis, design sensitivity analysis and has been applied theoretically to sailplane, microwave-powered constrained optimization code CONMIN. Author aircraft, and High Altitude Long-Endurance (HALE) aircraft configurational definition efforts. Attention is presently given to the further development of such integrated-discipline approaches N89-25156'# National Aeronautics and Space Administration. through the incorporation of AI techniques; these are then applied Langley Research Center, Hampton, VA. to the aforementioned case of the HALE. The windFrame language STRUCTURAL OPTIMIZATION OF ROTOR BLADES WITH used, which is based on HyperTalk, will allow designers to write INTEGRATED DYNAMICS AND AERODYNAMICS programs using a highly graphical, user interface-oriented ADIT1 CHATTOPADHYAY (Analytical Services and Materials, Inc., environment. Author Hampton, VA.) and JOANNE L. WALSH ln its Recent Advances in Multidisciplinary Analysis and Optimization, Part 1 p 209-233 Apr. 1989 Previously announced as N89-15110 N89-25167'# General Dynamics Corp., Fort Worth, TX. Avail: NTlS HC A23/MF A01 CSCL 0113 AEROLASTIC TAILORING AND INTEGRATED WING DESIGN The problem of structural optimization of helicopter rotor blades MIKE H. LOVE and JON BOHLMANN ln NASA. Langley Research with integrated dynamic and aerodynamic design considerations Center, Recent Advances in Multidisciplinary Analysis and is addressed. Results of recent optimization work on rotor blades Optimization, Part 1 p 431-444 Apr. 1989 for minimum weight with constraints on multiple coupled natural Avail: NTlS HC A23/MF A01 CSCL 0113 flap-lag frequencies, blade autorotational inertia and centrifugal Much has been learned from the TSO optimization code over stress has been reviewed. A strategy has been defined for the the years in determining aeroelastic tailoring's place in the ongoing activities in the integrated dynamic/aerodynamic integrated design process. Indeed, it has become apparent that optimization of rotor blades. As a first step, the integrated aeroelastic tailoring is and should be deeply embedded in design. dynamic/airload optimization problem has been formulated. To Aeroelastic tailoring can have tremendous effects on the design calculate system sensitivity derivatives necessary for the loads, and design loads affect every aspect of the design process. optimization recently developed, Global Sensitivity Equations (GSE) While optimization enables the evaluation of design sensitivities, are being investigated. A need for multiple objective functions for valid computational simulations are required to make these the integrated optimization problem has been demonstrated and sensitivities valid. Aircraft maneuvers simulated must adequately various techniques for solving the multiple objective function cover the plane's intended flight envelope, realistic design criteria optimization are being investigated. The method called the Global must be included, and models among the various disciplines must Criteria Approach has been applied to a test problem with the be calibrated among themselves and with any hard-core (e.g., blade in vacuum and the blade weight and the centrifugal stress wind tunnel) data available. The information gained and benefits as the multiple objectives. The results indicate that the method is derived from aeroelastic tailoring provide a focal point for the quite effective in solving optimization problems with conflicting various disciplines to become involved and communicate with one objective functions. Author another to reach the best design possible. Author
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N89-25168"# National Aeronautics and Space Administration. structure is used with upper and lower skins, spar and rib Langley Research Center, Hampton, VA. thicknesses, and spar cap and vertical post cross-sectional areas INTEGRATED AERODYNAMIC-STRUCTURAL DESIGN OF A as the design parameters. Incompressible aerodynamic strip theory FORWARD-SWEPT TRANSPORT WING is used to derive the constraint formulations, and aerodynamic RAPHAEL T. HAFTKA, BERNARD GROSSMAN, PIJEN KAO, load matrices. A Sequential Unconstrained Minimization Technique DAVID M. POLEN (Virginia Polytechnic Inst. and State Univ., (SUMT) algorithm is used to optimize the wing structure to meet Blacksburg.), and JAROSLAW SOBIESZCZANSKI-SOBIESKI In the desired performance constraints. Author its Recent Advances in Multidisciplinary Analysis and Optimization, Part 1 p 445-463 Apr. 1989 Avail: NTlS HC A23/MF A01 CSCL 0113 N89-25172'# National Aeronautics and Space Administration. The introduction of composite materials is having a profound Langley Research Center, Hampton, VA. effect on aircraft design. Since these materials permit the designer OPTIMUM DESIGN OF SWEPT-FORWARD to tailor material properties to improve structural, aerodynamic and HIGH-ASPECT-RATION GRAPHITE-EPOXY WINGS acoustic performance, they require an integrated multidisciplinary MARK J. SHUART, RAPHAEL T. HAFTKA, and R. L. CAMPBELL design process. Futhermore, because of the complexity of the ln its Recent Advances in Multidisciplinary Analysis and design process, numerical optimization methods are required. The Optimization, Part 1 p 509-525 Apr. 1989 utilization of integrated multidisciplinary design procedures for Avail: NTlS HC A23/MF A01 CSCL 01 13 improving aircraft design is not currently feasible because of An analytical investigation of a swept-forward high-aspect-ratio software coordination problems and the enormous computational graphite-epoxy transport wing is described. The objectives of this burden. Even with the expected rapid growth of supercomputers investigation are to illustrate an effective usage of the unique and parallel architectures, these tasks will not be practical without properties of composite materials by exploiting material tailoring the development of efficient methods for cross-disciplinary and to demonstrate an integrated multidisciplinary approach for sensitivities and efficient optimization procedures. The present conducting this investigation. Author research is part of an on-going effort which is focused on the processes of simultaneous aerodynamic and structural wing design N89-25173'# National Aeronautics and Space Administration. as a prototype for design integration. A sequence of integrated wing design procedures has been developed in order to investigate Langley Research Center, Hampton, VA. RECENT ADVANCES IN MULTIDISCIPLINARY ANALYSIS AND various aspects of the design process. Author OPTIMIZATION, PART 2 JEAN-FRANCOIS M. BARTHELEMY, ed. Washington Apr. N89-25 170'# National Aeronautics and Space Administration. 1989 501 p Symposium held in Hampton, VA, 28-30 Sep. Langley Research Center, Hampton, VA. 1988; sponsored by NASA, Langley Research Center, NASA, Lewis EFFECTS OF NONLINEAR AERODYNAMICS AND STATIC Research Center, and Wright Research Development Center AEROELASTICITY ON MISSION PERFORMANCE (NASA-CP-3031-PT-2; L-16568-PT-2; NAS 1.55:3031 -PT-2) CALCULATIONS FOR A FIGHTER AIRCRAFT Avail: NTlS HC A22/MF A01 CSCL 01 /3 GARY L. GILES, KENNETH E. TATUM (Planning Research Corp., This three-part document contains a collection of technical Hampton, VA.), and WILLARD E. FOSS, JR. ln its Recent papers presented at the Second NASA/Air Force Symposium on Advances in Multidisciplinary Analysis and Optimization, Part 1 p Recent Advances in Multidisciplinary Analysis and Optimization, 477-496 Apr. 1989 held September 28-30, 1988 in Hampton, Virginia. The topics Avail: NTlS HC A231MF A01 CSCL 01 13 covered include: helicopter design, aeroelastic tailoring, control of During conceptual design studies of advanced aircraft, the aeroelastic structures, dynamics and control of flexible structures, usual practice is to use linear theory to calculate the aerodynamic structural design, design of large engineering systems, application characteristics of candidate rigid (nonflexible) geometric external of artificial intelligence, shape optimization, software development shapes. Recent developments and improvements in computational and implementation, and sensitivity analysis. methods, especially computational fluid dynamics (CFD), provide significantly improved capability to generate detailed analysis data for the use of all disciplines involved in the evaluation of a proposed N89-25190'# National Aeronautics and Space Administration. aircraft design. A multidisciplinary application of such analysis Langley Research Center, Hampton, VA. methods to calculate the effects of nonlinear aerodynamics and RESULTS OF INCLUDING GEOMETRIC NONLINEARITIES IN static aeroelasticity on the mission performance of a fighter aircraft AN AEROELASTIC MODEL OF AN F/A-18 concept is described. The aircraft configuration selected for study CAREY S. BUTTRILL In its Recent Advances in Multidisciplinary was defined in a previous study using linear aerodynamics and Analysis and Optimization, Part 2 p 815-836 Apr. 1989 rigid geometry. The results from the previous study are used as a Avail: NTlS HC A221MF A01 CSCL 0113 basis of comparison for the data generated herein. Aerodynamic An integrated, nonlinear simulation model suitable for characteristics are calculated using two different nonlinear theories, aeroelastic modeling of fixed-wing aircraft has been developed. potential flow and rotational (Euler) flow. The aerodynamic While the author realizes that the subject of modeling rotating, calculations are performed in an iterative procedure with an elastic structures is not closed, it is believed that the equations of equivalent plate structural analysis method to obtain lift and drag motion developed and applied herein are correct to second order data for a flexible (nonrigid) aircraft. These static aeroelastic data and are suitable for use with typical aircraft structures. The are then used in calculating the combat and mission performance equations are not suitable for large elastic deformation. In addition, characteristics of the aircraft. Author the modeling framework generalizes both the methods and terminology of non-linear rigid-body airplane simulation and N89-25171*# Air Force Wright Aeronautical Labs., traditional linear aeroelastic modeling. Concerning the importance Wright-Patterson AFB, OH. of angular1elastic inertial coupling in the dynamic analysis of OPTIMUM STRUCTURAL DESIGN WITH STATIC fixed-wing aircraft, the following may be said. The rigorous inclusion AEROELASTIC CONSTRAINTS of said coupling is not without peril and must be approached with KEITH B BOWMAN, RAMANA V. GRANDHI, and F. E. EASTEP care. In keeping with the same engineering judgment that guided (Dayton Univ., OH.) ln NASA. Langley Research Center, Recent the development of the traditional aeroelastic equations, the effect Advances in Multidisciplinary Analysis and Optimization, Part 1 p of non-linear inertial effects for most airplane applications is 497-508 Apr. 1989 expected to be small. A parameter does not tell the whole story, Avail: NTlS HC A231MF A01 CSCL 01 13 however, and modes ftagged by the parameter as significant also The static aeroelastic performance characteristics, divergence need to be checked to see if the coupling is not a one-way path, velocity, control effectiveness and lift effectiveness are considered Le., the inertially affected modes can influence other modes. in obtaining an optimum weight structure. A typical swept wing Author
669 ~
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
N89-25192'# National Aeronautics and Space Administration. of artificial intelligence, shape optimization, software development Langley Research Center, Hampton, VA. and implementation, and sensitivity analysis. AEROELASTIC MODELING FOR THE FIT (FUNCTIONAL INTEGRATION TECHNOLOGY) TEAM F/A-lE SIMULATION NE9-25205'# Missouri Univ.. Columbia. Design Productivity THOMAS A. ZEILER (Planning Research Corp., Hampton, VA.) Center. and CAROL D. WIESEMAN ln its Recent Advances in MULTILEVEL DECOMPOSITION OF COMPLETE VEHICLE Multidisciplinary Analysis and Optimization, Part 2 p 861-877 Apr. CONFIGURATION IN A PARALLEL COMPUTING 1989 ENVIRONMENT Avail: NTlS HC A22/MF A01 CSCL 01 /3 VINAY BHAU and K. M. RAGSDELL ln NASA. Langley Research As part of Langley Research Center's commitment to developing Center, Recent Advances in Multidisciplinary Analysis and multidisciplinary integration methods to improve aerospace Optimization, Part 3 p 1069-1082 Apr. 1989 systems, the Functional Integration Technology (FIT) team was Avail: NTlS HC A22/MF A01 CSCL 01/3 established to perform dynamics integration research using an This research summarizes various approaches to multilevel existing aircraft configuration, the F/A-18. An essential part of decomposition to solve large structural problems. A linear this effort has been the development of a comprehensive simulation decomposition scheme based on the Sobieski algorithm is selected modeling capability that includes structural, control, and propulsion as a vehicle for automated synthesis of a complete vehicle dynamics as well as steady and unsteady aerodynamics. The configuration in a parallel processing environment. The research structural and unsteady aerodynamics contributions come from an is in a developmental state. Preliminary numerical results are aeroelastic mode. Some details of the aeroelastic modeling done presented for several example problems. Author for the Functional Integration Technology (FIT) team research are presented. Particular attention is given to work done in the area N89-25206'# Kansas Univ., Lawrence. Dept. of Aerospace of correction factors to unsteady aerodynamics data. Author Engineering. DESIGN OPTIMIZATION OF AXISYMMETRIC BODIES IN NONUNIFORM TRANSONIC FLOW N89-25194'# California Univ., Los Angeles. Dept. of Mechanical, C. EDWARD IAN In NASA. Langley Research Center, Recent Aerospace and Nuclear Engineering. Advances in Multidisciplinary Analysis and Optimization, Part 3 p AN INTEGRATED APPROACH TO THE OPTIMUM DESIGN OF 1085-1095 Apr. 1989 ACTIVELY CONTROLLED COMPOSITE WINGS Avail: NTlS HC A22/MF A01 CSCL 01/3 E. LIVNE ln NASA. Langley Research Center, Recent Advances An inviscid transonic code capable of designing an axisymmetric in Multidisciplinary Analysis and Optimization, Part 2 p 897-918 body in a uniform or nonuniform flow was developed. The design Apr. 1989 was achieved by direct opthiation by coupling an analysis code (Contract F49620-87-K-0003) with an optimizer. Design examples were provided for axisymmetric 01 Avail: NTlS HC A22/MF A01 CSCL /3 bodies with fineness ratios of 8.33 and 5 at different Mach numbers. The importance of interactions among the various disciplines It was shown that by reducing the nose radius and increasing the in airplane wing design has been recognized for quite some time. afterbody thickness of initial shapes obtained from symmetric NACA With the introduction of high gain, high authority control systems four-digit airfoil contours, wave drag could be reduced by 29 percent and the design of thin, flexible, lightweight composite wings, the for a body of fineness ratio 8.33 in a nonuniform transonic flow of integrated treatment of control systems, flight mechanics and M = 0.98 to 0.995. The reduction was 41 percent for a body of dynamic aeroelasticity became a necessity. A research program fineness ratio 5 in a uniform transonic flow of M = 0.925 and 65 is underway now aimed at extending structural synthesis concepts percent for the same body but in a nonuniform transonic flow of and methods to the integrated synthesis of lifting surfaces, spanning M = 0.90 to 0.95. Author the disciplines of structures, aerodynamics and control for both analysis and design. Mathematical modeling techniques are NE9-25210'# National Aeronautics and Space Administration. carefully selected to be accurate enough for preliminary design purposes of the complicated, built-up lifting surfaces of real aircraft Langley Research Center, Hampton, VA. with their multiple design criteria and tight constraints. The HYPERSONIC AIRBREATHING VEHICLE CONCEPTUAL presentation opens with some observations on the multidisciplinary DESIGN (FOCUS ON AERO-SPACE PLANE) JAMES L. HUNT and JOHN G. MARTIN (Planning Research Corp., nature of wing design. A brief review of some available state of Hampton. VA.) ln Recent Advances in MultidisciplinaryAnalysis the art practical wing optimization programs and a brief review of its current research effort in the field serve to illuminate the motivation and Optimization, Part 3 p 1157-1 194 Apr. 1989 Avail: NTlS HC A22/MF A01 and support the direction taken in our research. The goals of this CSCL 01 /3 The airbreathing single stage to orbit (SSTO) vehicle design research effort are presented, followed by a description of the environment is variable-rich, intricately networked and sensitivity analysis and behavior sensitivity techniques used. The presentation concludes with a status report and some forecast of upcoming intensive. As such, it represents a tremondous technology challenge. Creating a viable design will require sophisticated progress. Author configuration/synthesis and the synergistic integration of advanced technologies across the discipline spectrum. In design exercises, N89-25201'# National Aeronautics and Space Administration. reductions in the fuel weight-fraction requirements projected for Langley Research Center, Hampton, VA. an orbital vehicle concept can result from improvements in RECENT ADVANCES IN MULTIDISCIPLINARY ANALYSIS AND aerodynamics/controls, propulsion efficiencies and trajectory OPTIMIZATION, PART 3 optimization; also, gains in the fuel weight-fraction achievable for JEAN-FRANCOIS M. BARTHELEMY, ed. Washington Apr. such a concept can result from improvements in structural design, 1989 513 p Symposium held in Hampton, VA, 28-30 Sep. heat management techniques, and material properties. As these 1988; sponsored by NASA, Langley Research Center, NASA, Lewis technology advances take place, closure on a viable vehicle design Research Center, and Wright Research Development Center will be realizable. Author (NASA-CP-3031-PT-3; L-16568-PT-3; NAS 1.55:3031 -PT-3) Avail: NTlS HC A22/MF A01 CSCL 0113 NE92521 1'# National Aeronautics and Space Administration. This three-part document contains a collection of technical Langley Research Center, Hampton, VA. papers presented at the Second NASA/Air Force Symposium on OPTIMIZING CONCEPTUAL AIRCRAFT DESIGNS FOR Recent Advances in Multidisciplinary Analysis and Optimization, MINIMUM LIFE CYCLE COST held September 28-30, 1988 in Hampton, Virginia. The topics VICKI S. JOHNSON ln its Recent .Advances in Multidisciplinary covered include: aircraft design, aeroelastic tailoring, control of Analysis and Optimization, Part 3 p 1195-1217 Apr. 1989 aeroelastic structures, dynamics and control of flexible structures, Avail: NTlS HC A22/MF A01 CSCL 01/3 structural design, design of large engineering systems, application A life cycle cost (LCC) module has been added to the FLight
670 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Optimization System (FLOPS), allowing the additional optimization N89-25232*# National Aeronautics and Space Administration. variables of life cycle cost, direct operating cost, and acquisition Langley Research Center, Hampton, VA. cost. Extensive use of the methodology on short-, medium-, and TIME-CORRELATED GUST LOADS USING MATCHED-FILTER medium-to-long range aircraft has demonstrated that the system THEORY AND RANDOM-PROCESSTHEORY: A NEW WAY OF works well. Results from the study show that optimization parameter LOOKING AT THINGS has a definite effect on the aircraft, and that optimizing an aircraft ANTHONY S. POTOTZKY, THOMAS A. ZEILER, and BOYD for minimum LCC results in a different airplane than when optimizing PERRY, 111 (Planning Research Corp., Hampton, VA.) Apr. 1989 for minimum take-off gross weight (TOGW), fuel burned, direct 11 p Presented at the AIAA 30th Structures, Structural Dynamics operation cost (DOC), or acquisition cost. Additionally, the economic and Materials Conference, Mobile, AL, 3-5 Apr. 1989 Previously assumptions can have a strong impact on the configurations announced in IAA as A89-30849 optimized for minimum LCC or DOC. Also, results show that (NASA-TM-101573; NAS 1.15:101573) Avail: NTlS HC AOWMF advanced technology can be worthwhile, even if it results in higher A01 CSCL 0113 manufacturing and operating costs. Examining the number of Two ways of performing time-correlated gust-load calculations engines a configuration should have demonstrated a real payoff are described and illustrated. The first is based on Matched Filter of including life cycle cost in the conceptual design process: the Theory; the second on Random Process Theory. Both approaches minimum TOGW of fuel aircraft did not always have the lowest yield theoretically identical results and represent novel applications life cycle cost when considering the number of engines. Author of the theories, are computationally fast, and may be applied to other dynamic-response problems. A theoretical development and N89-25212"# Stanford Univ., CA. Dept. of Aeronautics and example calculations using both Matched Filter Theory and Random Astronautics. Process Theory approaches are presented. Author AIRCRAFT DESIGN OPTIMIZATION WITH MULTIDISCIPLINARY PERFORMANCE CRITERIA N89-25233'# California Univ., Berkeley. STEPHEN MORRIS and ILAN KROO In NASA. Langley Research THE CONCEPTUAL DESIGN OF A MACH 2 OBLIQUE FLYING Center, Recent Advances in Multidisciplinary Analysis and WING SUPERSONIC TRANSPORT Optimization, Part 3 p 1219-1235 Apr. 1989 ALEXANDER J. M. VANDERVELDEN May 1989 39 p Avail: NTlS HC A22/MF A01 CSCL 0113 (Contract NAG2-471) The method described here for aircraft design optimization with (NASA-CR-177529; NAS 1.26:177529) Avail: NTlS HC AOWMF dynamic response considerations provides an inexpensive means A01 CSCL 01/3 of integrating dynamics into aircraft preliminary design. By defining This paper is based on a performance and economics study a dynamic performance index that can be added to a conventional of a Mach two oblique flying wing transport aircraft that is to objective function, a designer can investigate the trade-off between replace the 87478. In order to fairly compare our configuration performance and handling (as measured by the vehicle's unforced with the 87478 an equal structural technology level is assumed. response). The procedure is formulated to permit the use of control It will be shown that the oblique flying wing configuration will system gains as design variables, but does not require full-state equal or outperform the 8747 in speed, economy and comfort feedback. The examples discussed here show how such an while a modern stability and control system will balance the aircraft approach can lead to significant improvements in the design as and smooth out gusts. The aircraft is designed to comply with the compared with the more common sequential design of system FAR25 airworthiness requirements and FAR36 stage 3 noise and control law. Author regulations. Geometry, aerodynamics, stability and control parameters of the oblique flying wing transport are discussed. Author N89-25221'# McDonnell-Douglas Corp., Long Beach, CA. AN OVERVIEW OF THE DOUGLAS AIRCRAFT COMPANY N89-25234 Department of the Air Force, Washington, DC. AEROELASTIC DESIGN OPTIMIZATION PROGRAM (ADOP) FLAP SYSTEM FOR SHORT TAKEOFF AND LANDING ' ALAN J. DODD In NASA. Langley Research Center, Recent AIRCRAFT Patent Advances in Multidisciplinary Analysis and Optimization, Part 3 p GERALD T. BRINE, inventor (to AF) 15 Nov. 1988 9 p Filed 1359-1369 Apr. 1989 10 Nov. 1986 Avail: NTlS HC A22/MF A01 CSCL 01 /3 (AD-DO13981; US-PATENT-4,784,355; From a program manager's viewpoint, the history, scope and US-PATENT-APPL-SN-928350) Avail: US Patent and Trademark architecture of a major structural design program at Douglas Aircraft Office CSCL 01 /3 Company called Aeroelastic Design Optimization Program (ADOP) A flap system for deploying high lift flaps on short takeoff and are described. ADOP was originally intended for the rapid, accurate, landing aircraft is presented. The flap system utilizes an activating cost-effective evaluation of relatively small structural models at mechanism that is used to extend a flap, a vane and a spoiler for the advanced design level, resulting in improved proposal maximum lift. The mechanism utilizes relatively few linkage pieces competitiveness and avoiding many costly changes later in the which are attached to the flap at single pivot points. The flap is design cycle. Before release of the initial version in November supported by an actuator and a flap hinge support bracket. 1987, however, the program was expanded to handle very large Increased mechanism rigidity and single pivot mountings allow use production-type analyses. Author of roller and track guides at flap ends to smoothly guide flap movement and provide a fail-safe system in case of pivot mounting N89-25222'# McDonnell-Douglas Corp., Long Beach, CA. failure. Spherical bearings are utilized for mounting of rollers and MEETING THE CHALLENGES WITH THE DOUGLAS actuators in order to compensate for misalignment of the flap and AIRCRAFT COMPANY AEROELASTIC DESIGN OPTIMIZATION the flap mechanism when used with tapered flaps on swept wing PROGRAM (ADOP) aircraft. The spoiler is joined by a guide link that adjusts spoiler BRUCE A. ROMMEL In NASA. Langley Research Center, Recent position with flap movement in order to maximize lift. The spoiler Advances in Multidisciplinary Analysis and Optimization, Part 3 p can also be used conventionally by activation of the actuator. 1369-1378 Apr. 1989 GRA Avail: NTlS HC A22/MF A01 CSCL 0113 An overview of the Aeroelastic Design Optimization Program N89-25235'# California Univ., Berkeley. (ADOP) at the Douglas Aircraft Company is given. A pilot test AN ECONOMIC MODEL FOR EVALUATING HIGH-SPEED program involving the animation of mode shapes with solid AIRCRAFT DESIGNS rendering as well as wire frame displays, a complete aircraft model ALEXANDER J. M. VANDERVELDEN May 1989 38 p of a high-altitude hypersonic aircraft to test ADOP procedures, a (Contract NAG2-471) flap model, and an aero-mesh modeler for doublet lattice (NASA-CR-177530; NAS 1.26:177530) Avail: NTlS HC AO3/MF aerodynamics are discussed. R.J.F. A01 CSCL 0113
67 1 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
A Class 1 method for determining whether further development the turbine outer casing duct adjacent to the turbine frame. Multiple of a new aircraft design is desirable from all viewpoints is presented. support posts are mounted to the turbine frame and roller means For the manufacturer the model gives an estimate of the total are rotatably attached to each support post. The roller means are cost of research and development from the preliminary design to aligned to rotate on a contact surface of the outer casing duct. the first production aircraft. Using Wright’s law of production, one Movement of the rollers on the contact surface is caused by the can derive the average cost per aircraft produced for a given relative movement of the turbine frame and outer casing duct. break-even number. The model will also provide the airline with a GRA good estimate of the direct and indirect operating costs. From the viewpoint of the passenger, the model proposes a tradeoff between N89-25994# Federal Aviation Administration, Atlantic City, NJ. ticket price and cruise speed. Finally all of these viewpoints are FUEL CONTAINMENT SYSTEM CONCEPT TO REDUCE combined in a Comparative Aircraft Seat-kilometer Economic SPILLAGE Index. Author ROBERT F. SALMON Jun. 1989 28 p (DOT/FAA/CT-TN89/22) Avail: NTlS HC AOWMF A01 N89-25237 George Washington Univ., Washington, DC. The purpose is to describe a new concept in aircraft fuel tank PROBABILISTIC DAMAGE TOLERANCE METHODS FOR design to reduce the spillage from an aircraft fuel tank which has METALLIC AEROSPACE STRUCTURES Ph.D. Thesis been ruptured during what could be considered a survivable crash. MARGERY E. ARTLEY 1989 132 p The time element is very critical for survival after a crash. By Avail: Univ. Microfilms Order No. DA8906814 reducing the amount of fuel spilled during the first minute after Damage tolerance analysis, based on fracture mechanics, is the aircraft comes to rest, the probability of passenger survival an important tool for ensuring the safety of flight of airframes. can be greatly enhanced. Author Traditionally, these analyses are deterministic in nature, but probabilistic methods have been applied to damage tolerance N89-25995# Nondestructive Testing Information Analysis Center, analysis in limited cases. The purpose of this dissertation is to San Antonio, TX. Dept. of Mechanical Sciences. formulate probabilistic damage tolerance analyses for metallic NONDESTRUCTIVE QUALIFICATION OF UH-1 REPLACEMENT structural components, based on US. Air Force damage tolerance PARTS COMPLETION ENHANCEMENT Final Report, Sep. philosophy for slow crack growth and fail safe components. A 1986 Dec. 1987 survey of the literature was conducted on probabilistic durability - ROGER L. BESSEY 7 Nov. 1988 5 p and damage tolerance methods. The important elements of the methods are covered; including the initial fatigue quality, the (Contract DLA900-84-C-0910; SWRl PROJ. 17-7958-832) (AD-A206674) Avail: NTlS HC AO2/MF A01 CSCL 01/3 variability in crack growth rate, and the probability of crack A listing of data packages completed on this program and detection. A probabilistic damage tolerance analysis was performed with a deterministic crack growth rate and then a stochastic crack breakout/feasibility studies which were performed, are presented. growth rate, based on a probabilistic durability method. Examples GRA of slow crack growth and fail safe structures are presented. As an example of a slow crack growth component, a lug from an N89-25996# Virginia Polytechnic Inst. and State Univ., aircraft subjected to an 80-flight fighter/trainer wing lower surface Blacksburg. spectrum was selected. A stiffened panel from a lower wing skin RELAXATION OSCILLATIONS IN AIRCRAFT CRUISE-DASH of a tanker was selected as an example of a fail-safe component. OPTIMIZATION Technical Paper Aug. 1986 - Mar. 1988 Crack arrest in the panel, followed by catastrophic failure of the U. J. SHANKAR, H. J. KELLEY (RCA Astro-Electronics Div., stiffener was considered as the failure mechanism. The model Princeton, NJ.), and E. M. CLIFF 15 Aug. 1988 35 p formulated here can be used to decide on the frequency and (Contract F08635-86-K-0390) quality of the inspection of a component needed to keep the (AD-A206722; AFATL-TP-89-03) Avail: NTlS HC AO3/MF A01 probability of failure at acceptable levels. Results of this study CSCL 0111 can serve as bases for decision making for inspection maintenance Periodic solutions in energy approximation are sought for and fleet management. Dissert. Abstr. aircraft optimal cruise-dash problems. The cost functional is the weighted sum of the time taken and the fuel used average over N89-25990# National Aerospace Lab., Tokyo (Japan). the cycle. It is known from previous work that in energy-state LONGITUDINAL NONLINEAR AERODYNAMIC MODEL FORM approximation, relaxed-steady-statecontrol gives lower costs than FOR USB-STOL AIRCRAFT the steady-state solution. However, this control is not Sep. 1988 52 p In JAPANESE; ENGLISH summary implementable. Higher approximations to this are sought via (NAL-TR-995; ISSN-0389-4010) Avail: NTlS HC A04/MF A01 averaging oscillations. The fast dynamics (path angle/attitude/ A longitudinal nonlinear aerodynamic model form for USB-STOL throttlellift coefficient) is modeled in terms of periodic solutions aircraft was prepared. The static and dynamic parts of the model in a boundary-layer-like motion which does not die out but form were drawn separately. The static model form was then moves along with the progression of the slow state en- verified by fitting it to wind tunnel test data of the NAL-STOL ergy. This is shown not to help the situation. A better approx- experimental airplane ASUKA. For the dynamic form, three types imation in terms of relaxation oscillations is proposed. Unlike of model form were proposed as candidates. The candidates differ earlier models, the energy is allowed to vary. However, the net from each other in the method of modeling the lag of downwash: change in energy per cycle is zero. Fast, constant-energy climbs In the first model the lag is simulated precisely, in the second and descents and slow energy transitions are spliced together in model it is approximated from the first lag, and in the third model, zeroth order approximation to obtain the periodic solutions. The the lag is neglected. A comparison of the results of dynamic flight energies in question are determined as part of the problem. This simulation with these three models comes to the conclusion that technique is shown to produce a more practical solution, but still the second model is the most appropriate for parameter needs improvement for practical application. GRA identification from flight test data. Author N89-25997# Naval Ship Research and Development Center, N89-25991 Department of the Air Force, Washington. DC. Bethesda, MD. Aviation Dept. AIRCRAFT ENGINE OUTER DUCT MOUNTING DEVICE Patent TIPJET VTOL UAV (VERTICAL TAKEOFF AND RONALD E. QUINN, inventor (to Air Force) 13 Dec. 1988 4 p LANDINGNNMANNED AERIAL VEHICLE) SUMMARY. Filed 17 Jul. 1987 VOLUME 1: A 1200 POUND TIPJET VTOL UNMANNED (AD-DO13988; US-PATENT-4,790,137; AERIAL VEHICLE. PART 1 : CONCEPTUAL DESIGN STUDY OF US-PATENT-APPL-SN-074802) Avail: US Patent and Trademark A 1200-POUND VEHICLE Interim Report, Apr. - Dec. 1988 Office CSCL 21 /5 KENNETH R. READER, JANE S. ABRAMSON, ALAN W. The invention comprises a mounting assembly for supporting SCHWARTZ, and JAMES C. BIGGERS Jan. 1989 80 p
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(AD-A206738; DTRC/AD-89/01) Avail: NTlS HC A05/MF A01 incorporates basic features and capabilities that are considered CSCL 01 /3 as representative for computer aided engineering applications in A new concept is developed for an Unmanned Aerial Vehicle industrial practice. Although an acceptable, optimum design (UAV) configured with a tip-jet driven, two-bladed, stoppable rotor configuration is obtained, verification and validation remains difficult. and circulation control airfoils. The conceptual design of the Tipjet This is inherent to the use of conceptual design methods. The Vertical Takeoff and Landing (VTOL) UAV is presented, and vehicle analysis methods currently implemented in the program library are performance is evaluated for three mid-range UAV Navy missions: generally referred to as class 1 methods. They are usually based Tactical Reconnaissance, Over-the-HorizonTargeting, and Combat on statisticaVempirica1 considerations and are generally quite Support Reconnaissance. Vehicle performance predictions are suitable for obtaining absolute answers with very little input presented for hover and low-speed, rotary-wing flight, for information. However, caution must be taken when using these conversion between rotary-wing and fixed-wing flight, and for methods in automated design. ESA fixed-wing flight. Requirements for shipboard support of the vehicle are outlined. Mission specific equipment is described including size, weight, and power requirements. Standard design methods are applied to conduct a detailed mission performance analysis for the conceptual design. The analysis results indicate that the 1200-lb Tipjet VTOL UAV is a viable candidate vehicle for the AIRCRAFT INSTRUMENTATION specified missions. Moreover, the concept is directly applicable to much larger UAVs that will greatly enhance naval warfare Includes cockpit and cabin display devices; and flight instruments. capabilities. Part 1 of Volume 1 presents the conceptual design for the Tipjet VTOL UAV along with vehicle performance analysis for the designed missions. GRA A89-44645# STEALTH TECHNOLOGY FOR REDUCING AIRCRAFT N89-25998# General Accounting Office, Washington, DC. RECOGNITION National Security and International Affairs Div. KAY W. DlURlCH and JOACHIM GRASHOF Dornier Post (ISSN STRATEGIC BOMBERS: B-18 COST AND PERFORMANCE 0012-5563), no. 2, 1989, p. 77-80. REMAIN UNCERTAIN Techniques used in developing stealth technology for reducing 3 Feb. 1989 60 p aircraft recognition are reviewed. The calculation of radar signature (AD-A206751; GAOINSIAD-89-55) Avail: NTlS HC A04/MF A01 by approximation methods and by exact numeric methods is CSCL 0113 addressed, taking into account the physical optics approximation Early in 1987 The General Accounting Office testified on the method and the finite volume method for Maxwell equations. The B-1B bomber program before the House and Senate Committees main types of radar-camouflaging construction are examined, and on Armed Services. It identified B-1B development deficiencies the measurement of radar backscatter is discussed. C.D. during the testimonies, and the Chairmen requested that GAO continue to monitor the program. This report updates and assesses A89-45105 the progress of the B-1B program since 1987 and presents other EXPERIMENTAL LOCALIZED RADAR CROSS SECTIONS OF related issues. On October 2, 1981, the President announced his AIRCRAFT decision to develop and deploy 100 B-1Bs. In selecting the B-lB, BERNARD D. STEINBERG, DONALD L. CARLSON, and DOD believed that the technology, cost, and schedule risks would WOOSUNG LEE (Pennsylvania, University, Philadelphia) IEEE, be low because of the experience gained from the canceled B-1A Proceedings (ISSN 0018-9219), vol. 77, May 1989, p. 663-669. program. On January 18, 1982, the President certified to the refs Congress that the B-1B would have an initial operational capability (Contract DAAG29-85-K-0247) during 1986 and that the development and acquisition baseline Localized radar cross section (RCS) measurements. are cost of B-1B fleet would not exceed $20.5 billion ($27.8 billion presented for the Boeing 727 and the Lockheed L-1011 aircraft. escalated dollars). However, to field the B-1B in just 5 years, the The measurements were made at X band from a few degrees aft program would feature highly concurrent full-scale development, of broadside. The elevation angle was approximately 30 deg. Four production, and testing schedules. GRA data sets, each of 128 pulses, were obtained from each airplane examined. The data presented are composites of measurements N89-26000# Federal Aviation Administration, Washington, DC. of five Boeing 727s and three L-101Is. The data exhibit the large Advanced System Design Service. variations in observed RCS reported elsewhere. I.E. FAA ROTORCRAFT RESEARCH, ENGINEERING AND DEVELOPMENT BIBLIOGRAPHY, 1962-1988 SUPPLEMENT A89-45107' Northwestern Univ., Evanston, IL. ROBERT D. SMITH Mar. 1989 103 p REVIEW OF FD-TD NUMERICAL MODELING OF (AD-A207162; AD-E501097; DOT/FAA/DS-89/03) Avail: NTlS ELECTROMAGNETIC WAVE SCAlTERlNG AND RADAR HC AO6/MF A01 CSCL 01/3 CROSS SECTION This bibliography of FAA rotorcraft reports published from 1962 ALLEN TAFLOVE (Northwestern University, Evanston, IL) and to 1988 is a supplement to an earlier bibliography. Both KORADA R. UMASHANKAR (Illinois, University, Chicago) IEEE, bibliographies are limited to documents in which the research, Proceedings (ISSN 0018-9219), vol. 77, May 1989, p. 682-699. engineering, and development elements of the FAA were involved refs as sponsors, participants, or authors. This bibliography contains (Contract F30602-79-C-0039;F19628-82-C-0140; NAG3-635; NSF abstracts on 53 technical reports. The indexes in this document ECS-85-15777) address these 53 reports as well as the 133 reports in the earlier Applications of the finite-difference time-domain (FD-TD) bibliography (FAA/PM-86/47). GRA method for numerical modeling of electromagnetic wave interactions with structures are reviewed, concentrating on N89-26001 Technische Univ., Delft (Netherlands). scattering and radar cross section (RCS). A number of two- and DEVELOPMENT AND APPLICATION OF A COMPUTER-BASED three-dimensional examples of FD-TD modeling of scattering and SYSTEM FOR CONCEPTUAL AIRCRAFT DESIGN Ph.D. Thesis penetration are provided. The objects modeled range in nature CORNELIS BIL 1988 267 p from simple geometric shapes to extremely complex aerospace (ETN-89-94886) Avail: Delft Univ. Press, Stevinweg 1, 2628 CN and biological systems. Rigorous analytical or experimental Delft, Netherlands validatons are provided for the canonical shapes, and it is shown A system for computer aided conceptual aircraft design was that FD-TD predictive data for near fields and RCS are in excellent developed and implemented. Although this system is intended for agreement with the benchmark data. It is concluded that with design education and research in a university environment, it continuing advances in FD-TD modeling theory for target features
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relevant to the RCS problems and in vector and concurrent propulsion system and for the identification of recovery procedures supercomputer technology, it is likely that FD-TD numerical for the F404 engine. The aim of the development program is to modeling will occupy an important place in RCS technology in the provide enhanced flight safety and to reduce the duties of the 1990s and beyond. I.E. propulsion engineers. As telemetry data is received, the results are continually displayed in a number of different color graphical A89-45111 formats. The system makes possible the monitoring of the engine RADAR CROSS SECTION OF ARBITRARILY SHAPED BODIES state and the individual parameters. Anomaly information is OF REVOLUTION immediately displayed to the engineer. R.R. TE-KAO WU (Hughes Aircraft Go., El Segundo, CA) IEEE, Proceedings (ISSN 0018-9219). vol. 77, May 1989, p. 735-740. refs The radar cross section (RCS) of an arbitrarily shaped, 07 homogeneous dielectric body of revolution (BOR) is evaluated by the surface integral equation (SIE) formulation and the method of AIRCRAFT PROPULSION AND POWER moments. Method accuracy is verified by the good agreement with the exact solutions for the RCS of a dielectric sphere. To Includes prime propulsion systems and systems components, e.g., demonstrate the advantages of this method, the RCS for a complex gas turbine engines and compressors; and on-board auxiliary power BOR model of human torso is computed with a nonaxially incident plants for aircraft. plane wave. Seven Fourier modes are considered in the computation. The SIE and approximate integral equation (AIE) formulations are then given for the RCS evaluation of a composite A8943885 dielectric and conducting BOR. For the cases considered, both PROP-FAN TESTED FOR STRUCTURAL AND ACOUSTIC formulations give the same surface currents and RCS results. DATA However, significant savings in computer storage and CPU time Aerospace Engineering (ISSN 0736-2536), vol. 9, June 1989, p. are realized for the AIE approach, since only one current (electric 27-29. or magnetic) need be determined for RCS evaluation. I.E. A primary objective of NASA’s Propfan Test Assessment (PTA) program was the acquisition of structural and acoustic baseline A89-45329 data during flight, using a modified Gulfstream II aircraft, in order AN EXPLORATORY STUDY OF THE USE OF to understand the propfan concept on the scale of the 9-ft diameter MOVEMENT-CORRELATEDCUES IN AN AUDITORY HEAD-UP SR-7L propfan mated to a 6000-hp engine and modified T56 DISPLAY gearbox. A total of 30 strain gages were mounted on the propfan ROBERT D. SORKIN, GREG C. ELVERS (Florida, University, in order to conduct the structural tests; vibratory response data Gainesville), FREDERIC L. WIGHTMAN, and DORIS S. KISTLER were acquired over the entire test envelope. After strain-gage data (Wisconsin, University, Madison) Human Factors (ISSN from the flight tests were reduced to a data sample average of 0018-7208), vol. 31, April 1989, p. 161-166. refs total vibratory strain at a stabilized flight condition, selected data (Contract F33657-86-C-2221) points were analyzed harmonically to sort out the amplitude and The ability of observers to localize targets with an auditory frequency content of the response. O.C. head-up display under different movement conditions is assessed. The observer had to indicate the target’s location after listening A89-44108# to a sequence of three signals. The following different conditions EFFICIENT COMPUTATIONAL TOOL FOR RAMJET relating the observer’s head movement to the target’s spatial COMBUSTOR RESEARCH position were tested: (1) a target fixed in physical space, (2) no P. VANKA, J. L. KRAZlNSKl (Argonne National Laboratory, IL), head movement allowed, and (3) a target fixed in position relative S. to the observer’s head. K.K. and A. S. NEJAD (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) Journal of Propulsion and Power (ISSN 0748-4658), vol. 5, July-Aug. 1989, p. 431-437. Research A89-46298# supported by USAF. refs THEANALYSISANDMEASUREMENTSOFRADARCROSS (AIAA PAPER 88-0060) SECTION (RCS) OF SOME WING STRUCTURE MODELS A multigrid-based calculation procedure is presented for the JINGZUO YANG. XIONGOING YU (Nanjing Aeronautical Institute. efficient solution of the time-averaged equations of a turbulent, People’s Republic of China), and JlANXlNG YANG (Shanghai elliptic-reacting flow. The equations are solved on a nonorthogonal Xinhua Radio Factory, People’s Republic of China) Acta curvilinear coordinate system. The physical models currently Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 10. April incorporated are a two-equation k-epsilon turbulence model, a 1989, p. 8196-6199. In Chinese, with abstract in English. four-step chemical kinetics mechanism, and a Lagrangian Three glass fiber composite and aluminum wing structure particle-trackingprocedure applicable to dilute sprays. Demonstration models, and the measurements of RCS of these models are given. calculations are presented to illustrate the performance of the calcu- Based upon the results of the measurements, the conceptual lation procedurefor a ramjet dump combustor configuration. Author analysis of the electromagnetic properties of these wing structure models are discussed. The purposes of this paper are to develop wing structural concepts of low RCS and to select the structural concept to assess the application of advanced materials such as ~a9-44113# glass fiber and carbon fiber composites for aircraft. Author IMPROVED COMPRESSOR PERFORMANCE USING RECESSED CLEARANCE (TRENCHES) A89-46910’# PRC Systems Services Co., Edwards, CA. D. C. WISLER and B. F. BEACHER (General Electric Co., Cincinnati, PRELIMINARY DEVELOPMENT OF AN INTELLIGENT OH) Journal of Propulsion and Power (ISSN 0748-4658), vol. 5, COMPUTER ASSISTANT FOR ENGINE MONITORING July-Aug. 1989, p. 469-475. Previously cited in issue 20. p. 2922, JAMES D. DISBROW (PRC Systems Services, Inc., Aerospace Accession no. A86-42823. refs Technologies Div., Edwards, CA), EUGENE L. DUKE, and RONALD (Contract F33615-81-C-2030) J. RAY (NASA, Flight Research Center, Edwards, CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, A89-44115’# Analatom, Inc., San Jose, CA. Monterey, CA, July 10-13, 1989. 10 p. refs NUMERICAL SIMULATIONS OF OBLIQUE DETONATIONS IN (AIAA PAPER 89-2539) SUPERSONIC COMBUSTION CHAMBERS As part of the F-18 high-angle-of-attack vehicle program, an JEAN-LUC CAMBIER (Analatom, Inc., San Jose, CA), HENRY G. AI method has been developed for the real-time monitoring of the ADELMAN, and GENE P. MENEES (NASA, Ames Research Center,
674 07 AIRCRAFT PROPULSION AND POWER
Moffett Field, CA) Journal of Propulsion and Power (ISSN Republic of China) Journal of Aerospace Power (ISSN 1000-8055), 0748-4658), vol. 5, July-Aug. 1989, p. 482-491. Previously cited in vol. 4, April 1989, p. 130-132, 199. In Chinese, with abstract in issue 07, p. 950, Accession no. A88-22043. refs English. Mixture of cold air flow from annular pass-through holes with A0944117# main flow (cold or hot stream) has been researched experimentally. ADVANCED TURBOFAN ENGINE COMBUSTION SYSTEM The momentum exchange for annular pass air flow through plain DESIGN AND TEST VERIFICATION or plunging circular holes into main flow has been studied J. W. SANBORN, J. E. LENERTZ, and J. D. JOHNSON (Garrett experimentally on a rectangular test section in a simulated Turbine Engine Co., Phoenix, AZ) Journal of Propulsion and combustion chamber. The momentum exchange increases the Power (ISSN 0748-4658), vol. 5, July-Aug. 1989, p. 502-509. pressure loss of the main air stream near the jet holes. The results Previously cited in issue 20, p. 31 54, Accession no. A87-45231. show that the mixture pressure loss of combustor with plunging circular holes is 1 to 1.5 times as large as that of the combustor with plain circular holes. Therefore, the combustor with plunging A0944362 circular holes is favorable to combustion, and may reduce the DYNAMIC STRESS ANALYSIS OF ROTATING length of the combustor. Author TURBO-MACHINERY BLADED-DISK SYSTEMS V. OMPRAKASH and V. RAMAMURTI (Indian Institute of Technology, Madras, India) Computers and Structures (ISSN A09-45557# 0045-7949), vol. 32, no. 2, 1989, p. 477-488. refs COLD FLOW MEASUREMENTS FOR A DOUBLE SWIRLER The steady state dynamic stress and deformation analysis of COMBUSTOR high pressure stage turbomachinery bladed-disks is carried out QINGFAN ZHANG, QlNGPlNG ZHENG, YlMlNG SAO, and taking into account all the geometric complexities involved. The XlAOMEl ZANG (Nanjing Aeronautical Institute, People’s Republic contributions due to initial stress and membrane behavior are of China) Journal of Aerospace Power (ISSN 1000-8055), vol. 4, included. Only one substructure is used for finite element modeling April 1989, p. 133, 134. 199. In Chinese, with abstract in English. qnd analysis, taking advantage of rotational periodicity. A triangular refs shell element with six degrees of freedom per node is employed THe cold flow patterns in a double swiller combustor have for this purpose. The blade and disk attachment is established by been measured by using a six-orientation hot-wire probe technique. a set of constraint equations obtained by the Love-Kirchhoff The results show that the central recirculation zone for hypothesis. The final set of equations are solved by an out of counterrotating swirling is different from that of corotating swirling. core submatrices elimination method. The influence of different A better pattern in the central recirculation zone for combustion levels of approximations and various geometric parameters on will be obtained if the swiller angles of both the outer swirler and the stresses and deformations is discussed. Author the center swirler are chosen reasonably. Author
A8945031 A09-45550# CIVIL SUPERSONICS - PROPULSION IS THE KEY EXPERIMENTAL RESEARCH ON SWIRLING COMBUSTION ’ JULIAN MOXON Flight International (ISSN 0015-3710). vol. 135, EFFICIENCY , June 10, 1989, p. 116, 117, 119, 122. XlANJlAN HUANG, HAOYUAN TAN, and WE1 CUI (Nanjing Of the three most important environmental problems facing next- Aeronautical Institute, People’s Republic of China) Journal of generation SST designers, including sonic boom overpres- Aerospace Power (ISSN 1000-8055), vol. 4, April 1989, p. 135, sures. NOx pollution of the stratosphere, and airport noise, 136, 199. In Chinese, with abstract in English. the latter two are directly addressable by propulsion system design This paper describes the experiments of combustion efforts. Attention is presently given to the variable-cycle engine performances in two kinds of swirling augmentor models. The (VCE) efforts of three major aircraft propulsion system combustion efficiencies and stabilizing limits have been measured. manufacturers in the US. and Britain; their VCE configurations The length of flame have been observed. The experiments of address the aforementioned problems by varying the amount of swirling combustion under small swirl angles have been completed, turbofan-bypass air from a high flow rate at subsonic speeds to a in which the flame could not be stabilized in recirculation zone. low one in supersonic cruise. Cooler combustion temperatures Results show that the efficiency of swirling combustion increases reduce NOx, and lower exhaust velocities associated with approximately 20 percent in comparison with that of V-flameholder high-bypass subsonic flow reduce takeoff and landing and the length of flame is obviously shortened. Author noise-generating exhaust stream velocities. O.C. A89-45559# A8945042 A DYNAMIC DIGITAL MODEL FOR THE TURBOJET WITH EUROPEAN GAS TURBINE ENGINES [LES TURBOMOTEURS PULSE-MONITORED FUELER EUROPEENS] DlYl TANG and YUANHU CAI (Northwestern Polytechnical JEAN BERNARD COCHETEUX L’Aeronautique et I’Astronautique University, Xian, People’s Republic of China) Journal of Aerospace (ISSN 0001-9275). no. 136-137, 1989, p. 79-88. In French. Power (ISSN 1000-8055). vol. 4, April 1989, p. 137-140, 194. In The European-made RTM 322 and MTR 390 helicopter Chinese, with abstract in English. turboshaft engines are described. The RTM 322, employed in the The ingestion of the hot gas from armanent firing or recirculation EH101, “90, and Sikorsky H60 helicopters, uses a compressor of exhaust gas from VTOL- and STOL-type aircraft will bring engine composed of three axial stages and one centrifugal stage, a into unstable and cause troubles for flight. It is good practice to high-efficiency two-stage turbine generator, and a light combustion use a pulse-monitored fueler for improving the engine stability. A chamber. The MTR 390, employed in the Westland Lynx and digital model for this purpose is presented, which consists of a PAH2-HAC/HAP helicopters, uses a double-centrifuge compressor, first-order fuel-feed model, a components volume model, and a an inverse-flux combustion chamber, and a cooled single-stage rotor-dynamic model. The steady-state performance and transient turbine generator. The introduction of new techologies has resulted behavior of a double spool turbojet are predicted on the basis of in gains in mass, size, performance, flexibility, and specific fuel this model. Then, the steady-state performance is compared with consumption for the MTR 390 over previous helicopter engines. the sea-level acceptance curve to check the validity of the model R.R. in specific case of steady state. The transient behaviors, such as the time histories of the secondary fuel line pressure, the speeds A89-45556# of two spools and the thrust, are also calculated and compared AN EXPERIMENTAL RESEARCH ON MIXTURE PRESSURE with the experimental curves of the same behaviors of another LOSS IN COMBUSTOR engine. The results indicate that the simulation effect of this model LlXlAO MO (Gas Turbine Establishment, Sichuan. People’s is satisfactory. Author
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A89-45567# calculations for evaluating the performance of engine with desired EXPERIMENTAL INVESTIGATION ON CHARACTERISTICS OF control laws. The second part uses complete numerical codes for SINGLE AND TANDEM BLADE CASCADES WITH simulating the transient operations of engines. Both iterative and DOUBLEGIRCULAR ARC PROFILE volume methods are used. Moreover the secondary transient BIAONAN ZHUANG and BINGHENG GUO (Nanjing Aeronautical effects may be taken into account. Author Institute, People’s Republic of China) Journal of Aerospace Power (ISSN 1000-8055), vol. 4, April 1989, p. 169-172, 197. In Chinese, A8946751# with abstract in English. ENVIRONMENTAL ICING TEST OF T800 HELICOPTER A single cascade and a tandem cascade with double-circular ENGINE WITH INTEGRAL INLET PARTICLE SEPARATOR arc profile have been designed and investigated, which have same WILLIAM R. STIEFEL (General Motors Corp., Allison Gas Turbine total cord, total camber, constructional inlet and exit angles, and Div., Indianapolis, IN) AIAA, ASME, SAE, and ASEE, Joint solidity, as the reference tandem compressor stator blade of an Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. existing gas turbine engine. The inlet Mach number is 0.3. The 10 p. characteristics of both single and tandem cascades, such as the (AIM PAPER 89-2324) dependence of turning angle Delta-beta and coefficient of total An environmental icing test was conducted during the pressure loss omega on incidence angle i have been obtained. Preliminary Flight Rating phase of the LHTEC T800 development The experimental data are compared and analyzed. The tandem program. This 1200 shp class turboshaft engine features an integral cascade features large fluid turning angle and small loss coefficient. inlet particle separator which challenges the task of anti-icing For incidence angle from -6.5 to +3.5 deg, Detla-beta of the because of the large surface area to be protected, particularly in tandem cascade is larger than Delta-beta of the single cascade light of the stringent limits on the allowable performance decrement 2-5 dBg, and omega the tandem cascade is smaller than omega associated with anti-icing system operation. Further, the inlet of the single cascade. For example, when i = 1 deg, for the particle separator configuration denies line-of-sight visual access tandem cascade Delta-beta = 55.4 deg, omega = 0.04, for the to most of the ice-sensitive flow path, thereby complicating single cascade Delta-beta = 49.6, omega = 0.076. Author evaluation of anti-icing system functional performance. This paper describes the engine and anti-icing system and discusses the A89-46025# selection of an icing test facility, the configuring and calibration of THE INVESTIGATION OF JET ENGINE STARTING an icing simulation system, and the optical/video techniques used HONGMIN WANG (Beijing University of Aeronautics and for on-line visual access to the internal flow-path surfaces of the Astronautics, People’s Republic of China) Journal of Propulsion inlet particle separator for monitoring potential ice formations. Technology (ISSN 1001-4055), June 1989, p. 70-74. In Chinese, Author with abstract in English. refs The process of starting a jet engine requires that the engine A89-46752# rotates up to idle reliably and satisfactorily. The starting VALIDATION OF A FREEJET TECHNIQUE FOR EVALUATING performance is modified based on the test of a flight evaluation INLET-ENGINE COMPATIBILITY schedule of a sample engine. The measurement and the data D. K. BEALE (Sverdrup Technology, Inc., Arnold AFB, TN) and M. acquisition for a small single-spool engine are conducted on a S. COLLIER (USAF, Arnold Engineering Development Center, sea-level test bench first. It is shown that, as main fuel is ignited, Arnold AFB, TN) AIAA, ASME, SAE. and ASEE, Joint Propulsion flame with temperature above 1250 C occurs at blade tips, while Conference, 25th, Monterey, CA, July 10-13, 1989. 19 p. the average exhaust gas temperature is 400 to about 500 C. The (AIAA PAPER 89-2325) mechanism and the criteria for overheating turbine blades during A free-jet test technique for the assessment of inlet-engine starting are presented in this paper. By using heat releasing ratio compatibility has undergone validation tests based on comparisons as the criteria to measure the overheating, the effects of FAR, between the free-jet results and wind tunnel test results obtained fuel droplet size, fuel evaporation constant, and air density on it with a 16.29-percent scale F-15 fighter inlet model. Free-jet are discussed. Author measurements have been found to be in good agreement with wind tunnel test results, indicating that the freestream reference A89-46600# plane flow-field characteristics can be simulated in a free-jet facility. PERFORMANCE ANALYSIS OF SCRAMJET ENGINES In addition, a short forebody simulator can be used to simulate YOSHIHARU TSUJIKAWA (Osaka Prefecture, University, Sakai, inlet influences on inlet flow. and inlet reference plane flow-field Japan), YUJIRO TSUKAMOTO (Mitsubishi Heavy Industries, Ltd., measurements can be used to determine free-jet settings required Komaki. Japan), and SHOlCHl FUJI1 (National Aerospace for the simulation. O.C. Laboratory, Chofu, Japan) Osaka Prefecture, University, Bulletin, Series A - Engineering and Natural Sciences (ISSN 0474-7844), A89-46770# vol. 37, no. 1, 1988, p. 1-13. refs PRELIMINARY ASSESSMENT OF EXHAUST SYSTEMS FOR The quasi-one-dimensional model for the flow through a HIGH MACH (4 TO 6) FIGHTER AIRCRAFT scramjet engine is proposed, and the performance of the A. P. KUCHAR and J. P. WOLF (GE Aircraft Engines, Cincinnati, components is analyzed thermodynamically. In the analysis, there OH) AIM, ASME, SAE, and ASEE, Joint Propulsion Conference, are severe difficulties in the combustor due to problems such as 25th. Monterey, CA, July 10-13, 1989. 13 p. turbulent diffusion and mixing at supersonic speed. For the (AIAA PAPER 89-2356) combustion reaction, a global hydrogen-air combustion model with While current-technology supersonic aircraft operate with two-step reaction schemes is introduced. Author maximum nozzle pressure ratios (NPRs) in the 15-20 range, NPRs of nearly 100 for Mach 4 and over 600 for Mach 6 are anticipated; A89-46704# these far higher values require commensurately higher nozzle NUMERICAL CODES FOR UNSTEADY SIMULATION OF expansion ratios, resulting in substantially higher nozzle sizes and TURBOJET, TURBOFAN AND TURBOPROP ENGINES FOR weights relative to current systems. Conventional axisymmetric TRAINING PURPOSES nozzles. two-dimensional convergent-divergent nozzles, and single G. TORELLA (Accademia Aeronautica, Naples, Italy) AIAA, ASME, expansion-ramp nozzles have been investigated: the latter two SAE, and ASEE, Joint Propulsion Conference, 25th. Monterey, types are found to achieve the requisite levels of performance at CA, July 10-13, 1989. 11 p. refs the expense of considerable size and weight, while the (AIM PAPER 89-2259) axisymmetric nozzle has geometric constraints that limit its An integrated package for simulating the transient behavior of Performance capability. O.C. jet engine with different configurations is presented. The package is divided in two parts. The first is based on suitable codes for A89-46774# managing large DATABASE and uses the results of available RE-ENGINING STAGE TWO AIRCRAFT WITH THE TAY
676 07 AIRCRAFT PROPULSION AND POWER
J. B. HODSON (Rolls-Royce, Inc., Sherman Oaks, CA) and V. M. thruster, which suggest a promising path towards practical SZEWCZYK (Rolls-Royce, PLC, Derby, England) AIAA, ASME, propulsion systems having variable thrust levels which are not SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, only controllable but scalable. A numerical-simulationcode suitable CA, July 10-13, 1989. 7 p. for the design, analysis, and evaluation of self-aspirating detonation (AIAA PAPER 89-2361) engines has been developed; candidate detonation chamber flow The Tay 670 variant of the Tay family of high-bypass turbofan properties verify the total dominance of unsteady gasdynamics. engines is of 18,000-lb takeoff thrust class, and is undergoing O.C. development as a replacement powerplant for the 8737-200, 8727-200, and DC-9 airliners, with a view to the significant airport A89-46838# community noise reductions thus obtainable. It is also noted that SEMI-CONSTANT VOLUME PULSE COMBUSTION FOR GAS 'hushkits' currently comtemplated for the JTBD low-bypass turbofan TURBINE ENGINE STARTING engines powering the aforementioned aircraft will result in only a R. B. BLACKBURN and J. L. MOULTON (Sunstrand Corp., marginal meeting of new noise requirements while involving Sunstrand Advanced Technology Group, Rockford, IL) AIAA, significant performance degradation by comparison with the ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, reengining that can be achieved with the Tay 670. O.C. Monterey, CA, July 10-13, 1989. 10 p. refs (AIAA PAPER 89-2449) A89-46776# Conventional external start power systems make up THE CHALLENGE OF REDUCING SUPERSONIC CIVIL approximately 40 to 50 percent of the installed weight and volume TRANSPORT PROPULSION NOISE of small gas turbine engines. A self-start concept based on A. M. STERN and A. A. PERACCHIO (United Technologies Corp., nonresonant pulse combustion could eliminate all or most of any Pratt and Whitney Group, East Hartford, CT) AIAA, ASME, SAE, external start power system. A case is made for a self-starting and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July engine using electronic fuel injection and unique flapper valving in 10-13, 1989. 6 p. refs the diffuser of the engine compressor. Preliminary analysis indicates (AIAA PAPER 89-2363) net rotor acceleration occurs when using low speed performance Achievement of FAR 36 Stage 3 noise levels presents a of an actual compressor and turbine. A functional flapper valve challenge. Techniques such as, for example, the use of inverted demonstrator and timed fuel injection pulses constitute 'a priori' velocity profile jet exhausts, suppressor/ejectors, thermo-acoustic feasibility. Author shields, are shown to provide significant suppression, but not enough to meet Stage 3. Additional suppression is required and A89-46851# achievement is suggested through the use of devices that increase ENGINE LIFE MATURATION PROCESS exhaust flow, aircraft operational techniques and engine/airframe F. M. CASSIDY, S. I. VUKELICH (USAF, Wright-Patterson AFB, integration. Needed additional experimental programs on noise OH), and J. SAMMONS (United Technologies Corp., Pratt and suppression and analytical studies are identified. Author Whitney Group, West Palm Beach, FL) AIAA, ASME, SAE, and ASEE, Joint PropulsionConference, 25th. Monterey, CA, July 10-13, A89-46777"# National Aeronautics and Space Administration. 1989. 10 p. Hugh L. Dryden Flight Research Center, Edwards, CA. (AIAA PAPER 89-2464) MEASUREMENT EFFECTS ON THE CALCULATIOPN OF Aircraft engine structural safety, increased service readiness, IN-FLIGHT THRUST FOR AN F404 TURBOFAN ENGINE and reduced life-cycle costs, are the factors addressed by the TIMOTHY R. CONNERS (NASA, Flight Research Center, Edwards, Engine Life Maturation Process (ELMP) methodology encom- CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, passing such engines' design, development, production, and 25th, Monterey, CA, July 10-13, 1989. 22 p. refs deployment. ELMP attempts to achieve early engine maturation (AIAA PAPER 89-2364) by developing initial maintenance-planning factors in the initial A study has been performed that investigates parameter design stages, in conjunction with active data-gathering and measurement effects on calculated in-flight thrust for the General updates of the planning factors throughout the engine system's Electric F404-GE-400 afterburning turbofan engine which powered service life. A controlled methodology for progressively increasing the X-29A forward-swept wing research aircraft. Net-thrust inspection intervals until the ultimate engine design life is achieved uncertainty and influence coefficients were calculated and are is the result of ELMP, as presently illustrated for the case of the presented. Six flight conditions were analyzed at five engine power variants of the F1OO fighter aircraft turbofan. O.C. settings each. Results were obtained using the mass flow-temperature and area-pressure thrust calculation methods, A09-46054# both based on the commonly used gas generator technique. Thrust ROLE OF DYNAMIC SIMULATION IN FIGHTER ENGINE uncertainty was determined using a common procedure based on DESIGN AND DEVELOPMENT the use of measurement uncertainty and influence coefficients. S. J. KHALID (United Technologies Corp., Pratt and Whitney Group, The effects of data nonlinearity on the uncertainty calculation West Palm Beach, FL) AIAA, ASME, SAE, and ASEE, Joint procedure were studied and results are presented. The advantages Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 12 and disadvantages of using this particular uncertainty procedure p. refs are discussed. A brief description of the thrust-calculation technique (AIAA PAPER 89-2467) along with the uncertainty calculation procedure is included. Representative engine models have been developed which can Author accurately account for off-design and dynamic effects very early in aircraft engine configuration and control design phases, ensuring A89-46837# favorable component matching. Attention is presently given to the A REVIEW OF PROPULSION APPLICATIONS OF THE PULSED use of such models in the case of specific flowpath design DETONATION ENGINE CONCEPT considerations in a fast-response twin-spool afterburning turbofan, S. EIDELMAN, W. GROSSMANN, and I. LOTTATI (Science the F100-PW-229. In addition to flowpath design, simulation tradeoff Applications International Corp., McLean, VA) AIAA, ASME, SAE, studies are used to optimize the control system; novel control and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July modes can be analytically evaluated across the operational 10-13, 1989. 12 p. Research supported by DARPA. refs spectrum with appropriate activation criteria that are readily (Contract N66001-88-D-0088) implementable in digital-control logic. O.C. (AIAA PAPER 89-2446) The present evaluation of the development status of pulsed A89-46861# detonation propulsion concepts gives attention to the results of ADVANCED PROPULSION SYSTEMS FOR LARGE SUBSONIC experiments performed at the US. Naval Postgraduate School, TRANSPORTS using a self-aspirating mode of operation for a pulsed detonation N. J. PEACOCK and J. H. R. SADLER (Rolls-Royce, PLC, Derby,
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England) AIAA, ASME, SAE, and ASEE, Joint Propulsion compared on the basis of power transmission and speed reduction Conference, 25th, Monterey. CA, July 10-13, 1989. 10 p. capabilities, weight and size, design complexity, efficiency and (AIAA PAPER 89-2477) reliability. Suitable gearbox air-to-oil cooler concepts were This paper will examine the parameters that influence the design developed and optimized for highly compact incorporation within of new engines for large transport aircraft. The search for the the propfan hub. Cooling performance is analyzed relative to the lowest installed specific fuel consumption has produced a variety flight mission including hot day effects. The detrimental impact of of proposals under the label of Ultra High Bypass engines. A cooling air extraction on engine performance is also examined. number of these designs are examined and the factors controlling The results presented are typical for both single and counterrotating their installed performance are reviewed. Weight and cost effects gearbox heat rejection problems. Author are also considered. The technology necessary to achieve a competitive product is identified. This is then related to the current new engine proposals which are largely derivative with little change A89-46868# in bypass ratio from current products. Author ENSURING SURGE-FREE ENGINE OPERATION ON TODAY'S TURBOFAN POWERED BUSINESS JETS A89-46862# F. NAWROCKI (Gulfstream Aerospace Corp., Savannah, GA) DUCTED ULTRA-HIGH BYPASS ENGINE CONFIGURATION AIAA, ASME, SAE. and ASEE, Joint Propulsion Conference, 25th, DEFINITION Monterey, CA, July 10-13, 1989. 22 p. H. A. GEIDEL (MTU Motoren- und Turbinen-Union Muenchen (AIAA PAPER 89-2487) GmbH, Munich, Federal Republic of Germany) and D. E. GRAY Surge-free operation in accordance with FAA requirements has (United Technologies Corp., Pratt and Whitney Group, East been addressed in the course of flight tests for the Gulfstream G Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion IV business aircraft with respect to ten distinct engine operational Conference, 25th, Monterey, CA. July 10-13, 1989. 11 p. factors. The engine in question is the Tay Mk 610-8 turbofan; the (AIAA PAPER 89-2478) factors addressed were engine service deterioration; the worst In the course of the 1980s. as fuel costs declined from their combinations of compressor and/or turbine matching, rigging exorbitant 1970s levels, the overall economics of prospective tolerances, and slew rates, respectively; Mach number; heavy passenger aircraft engine designs rather than the reduction of rainfall ingestion; runway water ingestion; snow and ice slug their specific fuel consumption became the primary factor in ingestion; altitude-dependent Reynolds number effects; and inlet evaluating comparative merit. Attention is presently given to the distortion effects. O.C. justification of Advanced Ducted Engine (ADE) designs on the basis of such a direct operating cost-oriented comparative study. ADEs possess performance characteristics intermediate between A89-46869# conventional turbofans and 'unducted fan' configurations, but THE ROLLS ROYCE ALLISON RB580 TURBOFAN - achieve overall economic superiority on the basis of their essential MATCHING THE MARKET REQUIREMENT FOR REGIONAL simplicity of design and construction. O.C. TRANSPORT J. H. R. SADLER, N. J. PEACOCK (Rolls-Royce, PLC, Derby, A89-46863# England), and L. SNYDER (General Motors Corp., Allison Gas TECHNOLOGY READINESS FOR ADVANCED DUCTED Turbine Div., Indianapolis, IN) AIAA, ASME. SAE, and ASEE, ENGINES Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. D. ECKARDT (MTU Motoren- und Turbinen-Union Muenchen 7 P. GmbH, Munich, Federal Republic of Germany) and G. L. BRINES (AIAA PAPER 89-2488) (United Technologies Corp., Pratt and Whitney Group, East The RB580 high bypass turbofan engine has a thrust growth Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion capability to 10.000 Ib and has been optimized for efficient operation Conference, 25th. Monterey, CA, July 10-13, 1989. 10 p. refs in regional markets involving 50-70 seat airliners with (AIAA PAPER 89-2479) higher-than-turboprop cruise speeds. The two-spool engine The Advanced Ducted Engines (ADEs) currently undergoing configuration achieves an overall pressure ratio of 24 and features development for next-generation passenger aircraft typically a single-stage wide-chord fan for high efficiency/low noise possess bypass ratios of the order of 12-25 and specific fuel operation. The highly modular design of the configuration facilitates consumption figures 12-17 percent lower than current advanced maintenance and repair; a dual-redundant full-authority digital turbofans. An extensive technology-readiness program has been electronic control system is incorporated. An SFC reduction of mounted on behalf of ADE design definition over the last two the order of 10 percent at cruise thrust is achieved, relative to years, encompassing among its concerns aircraft/engine- current engines of comparable thrust class. O.C. installation interference, low pressure-ratio fan aerodynamics, fanhacelle interactions (including windmilling and thrust- reversal), acoustic characteristics, transonic-drive turbines, A89-46898'# National Aeronautics and Space Administration. and slender nacelle aerodynamic and mechanical design. Both Langley Research Center, Hampton, VA. turbine-driven and geared ADE fans, which may be of single-rotating EVALUATION OF PARALLEL INJECTOR CONFIGURATIONS or contrarotating type, are discussed. O.C. FOR SUPERSONIC COMBUSTION G. BURTON NORTHAM (NASA, Langley Research Center, A89-46865# Hampton, VA), 1. GREENBERG, and C. S. BYINGTON (Joint HIGH PERFORMANCE GEAR SYSTEMS AND HEAT Institute for Advancement of Flight Sciences, Hampton, VA) AIAA, MANAGEMENT FOR ADVANCED DUCTED SYSTEMS ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, K. RUED, H. A. GEIDEL, A. ROHRA, and K. BRIT2 (MTU Motoren- Monterey, CA, July 10-13, 1989. 15 p. refs und Turbinen-Union Muenchen GmbH, Munich, Federal Republic (AIAA PAPER 89-2525) of Germany) AIM, ASME, SAE, and ASEE, Joint Propulsion Techniques for the enhancement of mixing in a scramjet Conference, 25th, Monterey, CA, July 10-13, 1989. 8 p. combustor are presently investigated experimentally with (AIAA PAPER 89-2482) wall-mounted parallel injector ramps that are speculated to prove Recent design studies on gear systems and corresponding useful at high speeds in the extraction of thrust from engine- or gearbox cooling concepts are presented. Investigations are based airframe-coolant hydrogen. The injector ramps were designed to on MTU's Advanced Ducted Engine concept CRISP (Counter generate a reflected shock wave from the duct top wall which will Rotating Integrated Shrouded Propfan) which develops shaft pass just downstream of the fuel injectors' barrel shock; fuel injector powers up to 17 MW for a short/medium range twin aircraft. Three Mach number is 1.7, in virtue of which an underexpanded fuel different in-line gear arrangements, i.e. differential planetary, split flow is generated. Shadowgraph and UV-TV flow visualizations star/planetary and compound star, have been evaluated and were conducted for three duct configurations. O.C.
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A89-46926# surfaces as a cohesive system, and facilitates the evaluation of A NUMERICAL INVESTIGATION OF SCRAMJET potential changes to an individual surface contour during the design COMBUSTORS process. This evaluation encompasses not only flow property H. H. KLEIN and P. C. CHAN (JAYCOR, San Diego, CA) IAA, changes around the component being modified, but also around ASME, SAE, and ASEE, Joint Propulsion Conference, !5th, all upstream and downstream components in the complete turbine Monterey, CA, July 10-13, 1989. 15 p. Research supported by system. Illustrative examples of this system's application to JAYCOR. refs advanced turbines for airbreathing and rocket-propellant turbines (AIAA PAPER 89-2561) are presented. O.C. The propulsion system for hypersonic vehicles will rely heavily on computational fluid dynamics for its design. JAYCOR has A89-46938# developed the EITACC code to solve the Navier-Stokes Equations TESTING OF THE 578-DX PROPFAN PROPULSION SYSTEM over a wide range of flow conditions. The code has successfully D. C. CHAPMAN (General Motors Corp., Allison Gas Turbine Div., modeled the types of flows found in scramjet engines, including: Indianapolis, IN), R. E. FLEURY (United Technologies Corp., Pratt supersonic flow with imbedded subsonic regions, complex shock and Whitney Group, East Hartford, CT), and D. E. SMITH (United and expansion fields, turbulent mixing and transport, flow separation Technologies Corp., Hamilton Standard Div., Windsor Locks, CT) and reattachment, and combustion. In this paper the EITACC code AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, is described and the results of flow in a generic scramjet combustor Monterey, CA, July 10-13, 1989. 9 p. are presented. Author (AIAA PAPER 89-2581) The 578-DX Propfan Demonstrator Propulsion System, whose A89-46927# flight testing on an MD-80 airliner testbed was recently completed, EFFECTIVENESS OF PLASMA TORCHES FOR IGNITION AND has a powerplant encompassing a gas generator developed from FLAMEHOLDING IN SCRAMJET engines currently used in marine and industrial applications, a YUKlNORl SATO, MASAMI SAYAMA, KATSURA OHWAKI novel compressor, a reduction-gear system developed under NASA (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan), auspices, a contrarotating propfan. a specialized nacelle, and a GORO MASUYA, TOMOYUKI KOMURO (National Aerospace full-authority digital electronic control system. The flight test Laboratory, Chofu, Japan) et al. AIAA, ASME, SAE, and ASEE, program has yielded data on (1) near- and far-field acoustic data Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. to assess FAR36 Stage 111 conditions compliance; (2) data useful 9 p. refs in the resolution of aircraftlengine integration problems; and (3) (AIAA PAPER 89-2564) data suitable for guiding future geared propfan propulsion system A plasma torch with a feed stock of air or oxygen was studied development decisions. O.C. experimentally to determine its effect on ignition and flameholding in a scramjet combustor. Consideration was given to fuel injection from one orifice, from four orifices on one wall, and from all nine A89-46939# orifices on both walls. This plasma torch was capable of stable UHB DEMONSTRATOR FLIGHT TEST PROGRAM - PHASE 2 operation without any support gas. In the case of single wall JOHN E. DONELSON, WILLIAM T. LEWERENZ, and ROGER T. injection, the plasma torch ignited the fuel jet located directly DURBIN (Douglas Aircraft Co., Long Beach, CA) AIAA, ASME, downstream and the flame formed ignited adjacent fuel jets. In SAE, and ASEE, Joint Propulsion Conference, 25th. Monterey, double wall injection, ignition of the fuel injected from the wall CA, July 10-13, 1989. 9 p. opposite the plasma torch was unsuccessful. K.K. (AIAA PAPER 89-2582) The second phase of the MD-80 airliner testbed-based Ultrahigh A89-46932# Bypass (UHB) demonstrator flight-test program has expanded TURBINE ENGINE STRUCTURAL EFFICIENCY technical knowledge in the areas of passenger comfort, airport DETERMINATION community noise, airframe structural design, engine operability, and A. F. STORACE (GE Aircraft Engines, Cincinnati, OH) AIAA, aircraftlengine integration. This deeper technical understanding of ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, gearedlcontrarotating rotor noise and vibration characteristics will Monterey, CA, July 10-13, 1989. 11 p. refs be applied to the design of UHB-incorporating MD-91 and -92 (Contract F33615-87-C-2843) aircraft, in order to achieve passenger cabin noise and airport (AIAA PAPER 89-2571) vicinity noise levels comparable to those of current-generation high Studies performed for advanced turbine engine concepts show bypass turbofan powered airliners. O.C. that major increases in thrust/weight performance and structural efficiency can be obtained by adapting structural geometry to take A89-46940# full advantage of material characteristics. This paper focuses on ESTIMATING IN-FLIGHT ENGINE PERFORMANCE analytical methods and design concepts developed to enhance VARIATIONS USING KALMAN FILTER CONCEPTS the structural efficiency of turbine engines. Turbine engine structural R. H. LUPPOLD, J. R. ROMAN (United Technologies Optics and efficiency is quantified through the improvements obtainable in Applied Technology Laboratory, West Palm Beach, FL), G. W. engine system vibration, turbomachinery clearance closures, and GALLOPS, and L. J. KERR (United Technologies Corp., Pratt and specific strength. Author Whitney Group, West Palm Beach, FL) AIAA, ASME, SAE, and ASEE, Joint PropulsionConference, 25th, Monterey, CA, July 10-13, A89-46936# Pratt and Whitney Aircraft Group, West Palm Beach, 1989. 10 p. refs FL. (AIAA PAPER 89-2584) APPLICATION OF A MULTI-STAGE 3-0 EULER SOLVER TO This paper describes an algorithm for estimating both the cause THE DESIGN OF TURBINES FOR ADVANCED PROPULSION and level of off-nominal engine performance. A state variable model SYSTEMS for an advanced tactical turbofan engine configuration was F. W. HUBER (United Technologies Corp., Pratt and Whitney Group, developed which models explicitly the effects of engine West Palm Beach, FL) and R. R. NI (United Technologies Corp., performance variations. A Kalman filter algorithm based on this Pratt and Whitney Group, East Hartford, CT) AIAA, ASME, SAE, model is used to estimate five engine factors that fully charac- and ASEE, Joint Propulsion Conference, 25th. Monterey, CA, July terize off-nominal performance. The Kalman filter inputs are 10-13, 1989. 6 p. Research supported by USAF, US. Army, NASA, measurements from a standard engine control instrumentation General Dynamics Corp., and United Technologies Corp. suite. Proof-of-concept tests using nonlinear engine simulation data (AIAA PAPER 89-2578) as well as actual data are presented. Potential applications of this The present three-dimensional Euler solver for iterative design concept include in-flight and maintenance diagnostics, in-flight of multistage gas turbine aerodynamic contours allows the aircraft/engine performance. integration, and adaptive engine optimization of turbine airfoil, endwall, inlet, and exit flow passage control laws. Author
679 07 AIRCRAFT PROPULSION AND POWER
~a+46941# pressure, or the fuel injection to air dynamic pressure are high, DIAGNOSTIC EXPERT SYSTEMS FOR GAS TURBINE Le., when the fuel injector manifold pressure is high. Of the four ENGINES - STATUS AND PROSPECTS cycles, the coolant-bleed cycle shows the most well-balanced DAVID L. DOEL (GE Aircraft Engines, Evendale, OH) and LEE R. performance. Author LAPIERRE (GE Aircraft Engines, Lynn, MA) AIAA, ASME. SAE, and ASEE, Joint Propulsion Conference, 25th. Monterey, CA, July 10-13, 1989. 8 p. refs ~a9-4701~ (AIAA PAPER 89-2585) SUPERSONIC TURBOMACHINE ROTOR FLUlTER CONTROL The status of condition monitoring algorithm development is BY AERODYNAMIC DETUNING discussed with attention given to recent work with artificial KAREN M. SPARA and SANFORD FLEETER (Purdue University, intelligence. The use of expert systems for gas path analysis and West Lafayette, IN) AIAA, ASME, SAE, and ASEE, Joint Propulsion for on-wing fan trim balance is discussed. It is noted that tools Conference, 25th, Monterey, CA, July 10-13, 1989. 11 p. refs like GEN-X address the need to eliminate the knowledge (AIAA PAPER 89-2685) engineer. K.K. A mathematical model is developed to analyze the flutter stability characteristics of an aerodynamically detuned rotor ~a9-46942# operating in a supersonic inlet flow field with a supersonic axial LOW COST CONTROL SYSTEM FOR EXPENDABLE TURBINE component. Alternate blade aerodynamic detuning is considered, ENGINES accomplished by alternating the circumferential spacing of adjacent K. BILL SWONGER Ueledvne CAE. Toledo. OHI and MARTIN F. rotor blades. The unsteady aerodynamics are determined by HUFFMAN -(USAF, ‘Aero’ Propulsion and Power Laboratory, developing an influence coefficient technique which is appropriate Wright-Patterson AFB, OH) AIAA, ASME, SAE. and ASEE, Joint for both aerodynamically tuned and detuned rotor configurations. Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. The effects of this detuning on the flutter stability characteristics 21. p. of supersonic axial flow rotors are then demonstrated by applying (AIAA PAPER 89-2586) this model to baseline twelve bladed rotors. Results show that, The design and development of a new low cost control system dependent on the specific blade row and flow field geometry, for nonman-rated engines are discussed. Consideration is given alternate blade aerodynamic detuning is a viable flutter control to control mode selection, fuel pump and metering device mechanism for supersonic throughflow rotors. Author evaluation, fuel pump evaluation, engine shaft integrated liquid ring pump, fuel metering device evaluation, engine sensor ~a+47019# evaluation, reliability analysis, and electronic hardware fabrication. DYNAMIC TURBINE BLADE TEMPERATURE MEASUREMENTS The engine tests demonstrated N-dot control law operation/stability, WILLIAM J. BECKER, RICHARD J. ROW. WALTER F. O’BRIEN digital engine control hardware operation, and compatibility with the (Virginia Polytechnic Institute and State University, Blacksburg), liquid ring pump engine system. K.K. and GERALD K. BENSING (Rosemount, Inc., Aerospace Div., Eagan, MN) AIAA, ASME, SAE, and ASEE, Joint Propulsion ~a9-46944# Conference, 25th, Monterey, CA, July 10-13, 1989. 14 p. Research EVALUATION OF A FAULT TOLERANT DIGITAL ENGINE supported by Rosemount, Inc. refs CONTROLLER (AIAA PAPER 89-2689) WILLIAM E. WRIGHT, JAMES C. HALL (GE Aircraft Engines, Turbine blade surface measurements were obtained during Cincinnati, OH), JOHN J. DEYST, JR., and RICHARD E. HARPER transient operation of a turbofan engine test rig. A single-fiber (Charles Stark Draper Laboratory, Inc., Cambridge, MA) AIM, radiation pyrometer was employed to image the suction side of ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, the blades from about 60 percent axial chord to the trailing edge Monterey, CA, July 10-13, 1989. 14 p. refs at an average radial location of 70 percent blade height. During (Contract F33657-82-C-2265;F33657-85-C-2131; the starting and acceleration transients, the blade surface was NO01 40-83-C-9046) shown to reverse, with large temperature gradients appearing during (AIAA PAPER 89-2589) starting. During the deceleration transients, the trailing edge cooled Two programs initiated by the USAF (INTERFACE I and ILL) more rapidly than the 60-percent chord location, resulting in larger to address aircraft engine control reliability and redundancy issues temperature gradients than were noted in steady operation. The associated with advanced aircraft are described. INTERFACE I observed temperature gradients and profile inversions indicate a incorporated a military standard 1750A 16-bit processor architecture cycling of thermally-induced stresses which may contribute to low programmed in Jovial and INTERFACE ILL utilizes military standard cycle fatigue damage. A simple one-dimensional heat transfer 1815 Ada in combination with a 32-bit processor. After evaluating model is proposed to explain the different heating rates found these types of engine control, the results of studies on fault-tolerant during the transients. R.R. parallel processing for engine controls are presented. K.K.
~a9-47006# ~a9-4702~ A COMPARISON OF SCRAMJET ENGINE PERFORMANCES ADVANCED MATERIAL APPLICATIONS FOR TURBINE OF VARIOUS CYCLES AIRFOILS TAKESHI KANDA, GORO MASUYA, YOSHIO WAKAMATSU, F. 0. SOECHTING (United Technologies Corp., Pratt and Whitney, NOBUO CHINZEI, and AKlO KANMURI (National Aerospace Group, West Palm Beach, FL) AIAA, ASME, SAE, and ASEE, Laboratory, Kakuda, Japan) AIAA, ASME, SAE, and ASEE, Joint Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 10 5 P. p. refs (AIAA PAPER 89-2693) (AIAA PAPER 89-2676) A comparative study has been conducted to ascertain the An airframe-integrated hydrogen fueled scramjet engine is strength requirementsof 20 monolithic ceramic materials applicable assumed in order to compare engine performances of various to high-temperature turbine airfoils in both cooled and uncooled engine cycles: an expander cycle, a staged-combustion cycle, a operating environments. Fused silica, TIN, TiB2, AIN, Zr02, Sic, coolant-bleed cycle, and a gas-generator cycle. Each engine was BeO, Si3N4, and Hf02 were among the materials studied. The regeneratively cooled by liquid hydrogen. Effects of flight Mach amount of cooling that may be required by each of the materials number, flight dynamic pressure, and fuel injection-to-air dynamic is determined, and it is found that maximum tensile stress levels pressure ratio were examined as related to propellant feed-line are enhanced when a turbine airfoil material is cooled. High thermal power balance. The system pressure of the closed loop cycle conductivity materials are desirable due to their minimization of becomes high, while the specific impulse of the open loop cycle thermal stresses in uncooled applications and of coolant flow becomes low, when the flight Mach number, the flight dynamic requirements in cooled applications. O.C.
680 07 AIRCRAFT PROPULSION AND POWER
A89-47024# NASA Langley Research Center to develop a supersonic PREDICTION OF PERIODIC LOADINGS ON SINGLE combustion ramjet (scramjet) capable of propelling a vehicle at ROTATION PROPFAN WITH OFF-AXIS INFLOW hypersonic speeds in the atmosphere or beyond. Recently, that SHIH H. CHEN (Rockwell International Corp., Rocketdyne Div., research has been directed toward the optimization of the scramjet Canoga Park, CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion combustor, and in particular the efficiency of fuel-air mixing and Conference, 25th, Monterey, CA, July 10-13, 1989. 11 p. refs reaction in the engine. This paper describes a numerical study of (AIAA PAPER 89-2694) fuel-air mixing and reaction in a supersonic combustor, and A 3D Green's function potential paneling method is used to discusses the analysis of a technique that was used to enhance predict the propfan unsteady load in a yawed flow condition when the mixing processes and overall combustion efficiency in the flow. the axis of blade rotation is inclined to the free stream. Unsteady Based on the results of that study, conclusions are drawn regarding response is predicted in a frequency domain with proper the applicability of the technique to enhance mixing in a scramjet predetermined interblade phase angle. The method is shown to combustor. Author be accurate and efficient in computation comparing to a time domain calculation. Single rotation propfan blade SR2 is used to A8947091# demonstrate the capability. The effects of shaft angle of attack, NUMERICAL STUDY OF REACTIVE RAMJET DUMP advance ratio, number of blades, and Mach number on the COMBUSTOR FLOWFIELDS WITH A PRESSURE BASED CFD response due to the off-axis inflow are studied. The results indicate METHOD that the shaft angle of attack has a major effect on the unsteady TEN-SEE WANG, YEN-SEN CHEN, and RICHARD C. FARMER blade loading. Author (SECA, Inc., Huntsville, AL) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 12 A89-47061# p. refs A PROPULSION DEVELOPMENT STRATEGY FOR THE (AIAA PAPER 89-2798) NATIONAL AERO-SPACE PLANE The formulation and verification of a numerical model for RAYMOND H. MOSZEE and CURTIS D. SNYDER (USAF, National simulating reactive dump combustor flowfields by solving the Aero-Space Plane Joint Program Office, Wright-Patterson AFB, Navier-Stokes equations are presented. A pressure-based solution OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, algorithm which uses time-centered, time-marching, central spatial 25th, Monterey, CA, July 10-13, 1989. 11 p. discretization, and adaptive dissipation was developed for this (AIAA PAPER 89-2751) analysis. A one-step reversible finite rate hydrogenloxygen The National Aero-Space Plane (NASP) Program, which is a chemical kinetics model and a point implicit method were used to joint DOD-NASA effort to develop and demonstrate technologies evaluate the reaction source terms in the species equations. The applicable to a new generation of transatmospheric vehicles, is temperature dependency of the dissipation rate on the combustion described. In connection with the vehicle engine design, process is studied. Author consideration is given to several propulsion related issues, concerns, and a risk reduction approach that incorporates rocket augmentation. As part of the NASP Program, an experimental A89-47092# aircraft called the X-30 has been constructed. Through the use of RAMJET COMBUSTOR MODELING FOR ENGINEERING this facility, propulsive concepts have been proven at speeds up DESIGN to Mach 25. K.K. L. S. CARETTO and A. K. RUNCHAL (Analytic and Computational Research, Inc., Los Angeles, CA) AIAA, ASME, SAE, and ASEE, A89-47084# Joint Propulsion Conference, 25th. Monterey, CA, July 10-13, 1989. COMBUSTION ENHANCEMENT IN SUPERSONIC COAXIAL 10 p. refs FLOWS (Contract F33615-84-C-2440) E. GUTMARK, K. J. WILSON, K. C. SCHADOW, T. P. PARR, and (AIAA PAPER 89-2799) D. M. HANSON-PARR (U.S. Navy, Naval Weapons Center, China A mathematical model was used as an integral part of the Lake, CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion design process for a ramjet dump combustor. The model solved Conference, 25th, Monterey, CA, July 10-13, 1989. 15 p. refs the two-dimensional, axisymmetric Navier-Stokes equations and (AIAA PAPER 89-2788) differential equations for swirl, fuel mass fraction, and turbulence Mixing enhancement of supersonic combusting jets was quantities. It was used for initial studies of cold flow modeling and obtained by using noncircular and multistep nozzles. The tests comparisons of combustion tests. The trends predicted by the were performed with free and coaxial supersonic jets in a wide model compared favorably with those found in the experimental range of parameters, including convective Mach numbers (0.25 to program and provided useful information for the design process. 2.25), temperature variation, velocity and density ratios and design The computer model represented the important details of the and off-design conditions. The measurements included total combustion process, but was kept simple so that all computer pressure in nonreacting flows, temperature and radiance using runs could be made on an IBM PC/AT. Author infrared imaging, and combustion zone mapping using planar laser induced fluorescence. The tests showed increased spreading rate A89-47094# of rectangular jets relative to a circular jet. This improvement was IMPROVING THE DEVELOPMENT PROCESS FOR MAIN dependent on the nozzle inner design and outer flow conditions. COMBUSTOR EXIT TEMPERATURE DISTRIBUTION Interaction of shock and shear layer instabilities at off-design STANLEY K. WIDENER (GE Aircraft Engines, Cincinnati, OH) conditions further enhanced mixing in the absence of coaxial flow. AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, The multistep nozzle increased small-scale mixing, thus enhancing Monterey, CA, July 10-13, 1989. 10 p. refs heat release and improved the flameholding characteristics of the (AIAA PAPER 89-2804) combustion. Author The development and treatment of the gas temperature distribution exiting a gas turbine main combustor is aided by the A89-47088'# National Aeronautics and Space Administration. application of available data for dilution jet penetration and mixing Langley Research Center, Hampton, VA. characteristics. This paper presents a method for predicting the MIXING ENHANCEMENT IN A SUPERSONIC COMBUSTOR results of changes in dilution features, and provides examples of J. PHILIP DRUMMOND, MARK H. CARPENTER, DAVID W. application of this method. The method applies laws of mass and RIGGINS, and MARY S. ADAMS (NASA, Langley Research Center, energy conservation to determine local changes in temperature Hampton, VA) AIAA, ASME, SAE, and ASEE, Joint Propulsion resulting from changes in stoichiometry as the dilution jets mix Conference, 25th, Monterey, CA, July 10-13, 1989. 16 p. refs with the main stream. Predictions are compared with measurements (AIAA PAPER 89-2794) taken during a typical combustor development program. This Research has been conducted for a number of years at the approach has been shown to effectively reduce the number of
68 1 07 AIRCRAFT PROPULSION AND POWER
test iterations required to achieve a satisfactory temperature A89-47 103# distribution. Author DEVELOPMENT TESTING OF THE 578 PROPFAN GEAR SYSTEM A8947098'# National Aeronautics and Space Administration. N. E. ANDERSON and D. A. WAGNER (General Motors Corp., Langley Research Center, Hampton, VA. Allison Gas Turbine Div., Indianapolis. IN) AIAA, ASME, SAE, PARAMETRIC STUDY OF A SIMULTANEOUS PITCH/YAW and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July THRUST VECTORING SINGLE EXPANSION RAMP NOZZLE 10-13. 1989. 7 p. ALBERT0 W. SCHIRMER (NASA, Langley Research Center; (AIAA PAPER 89-2817) George Washington University, Hampton. VA) and FRANCIS J. Development testing of the first high-power counterrotating gear CAPONE (NASA, Langley Research Center, Hampton, VA) AIAA, system for use in propfan propulsion systems is described in this ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, paper. In preparation for flight tests aboard a McDonnell Douglas Monterey, CA, July 10-13, 1989. 12 p. refs MD-80 aircraft, extensive rig and propulsion system integration (AIAA PAPER 89-2812) tests were conducted. This discussion focuses on the development In the course of the last eleven years, the concept of thrust testing leading to the highly successful flight tests. Author vectoring has emerged as a promising method of enhancing aircraft control capabilities in post-stall flight incursions during combat. In A89-47106# order to study the application of simultaneous pitch and yaw DESIGN OF A GEAR DRIVE FOR COUNTER-ROTATING FAN vectoring to single expansion ramp nozzles, a static test was ROTORS conducted in the NASA-Langley 16 foot transonic tunnel. This D. C. HOWE and A. H. MCKlBBlN (United Technologies Corp., investigation was based on internal performance data provided by Pratt and Whitney Group, East Hartford, CT) AIAA, ASME, SAE, force, mass flow and internal pressure measurements at nozzle and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July pressure ratios up to 8. The internal performance characteristics 10-13, 1989. 12 p. of the nozzle were studied for several combinations of six different (AIAA PAPER 89-2820) parameters: yaw vectoring angle, pitch vectoring angle, upper ramp Improved gearbox efficiency, durability, and structural weight cutout, sidewall hinge location, hinge inclination angle and sidewall are sought in the development of advanced-technology design containment. Results indicated a 2-to- 3-percent decrease in features for in-line, differential planetary gear drive systems for resultant thrust ratio with vectoring in either pitch or yaw. Losses contrarotating propfan rotors. Attention is presently given to a were mostly associated with the turning of supersonic flow. 12,000 SHP nominal-rating gearbox of this type that is projected Resultant thrust ratios were also decreased by sideways expansion to possess a growth margin extending to 15,000 SHP, in conjunction of the jet. The effects of cutback corners in the upper ramp and with a durability goal of 30,000 hr (mean-time between unplanned lower flap on performance were small. Maximum resultant yaw removals) and an efficiency goal of 99 percent at cruise power; vector angles, about half of the flap angle, were achieved for the also discussed is the fully automated gearbox-testing facility configuration with the most forward hinge location. Author enployed, whose capabilities encompass simulated fan rotor torque, thrust, and side loads, as well as simulated aircraft attitudes. A89-47100# O.C. ADVANCED COOLING CONCEPTS FOR MULTI-FUNCTION NOZZLE DURABILITY A89-47107# STEPHEN A. PAUL (United Technologies Corp., Pratt and Whitney DESIGN CRITERIA AND ANALYSIS OF DYNAMIC STRESSES Group, West Palm Beach, FL) and ALEX J. GIESE (USAF, Wright OF A PROPELLER GEAR SYSTEM Research and Development Center, Wright-Patterson AFB, OH) KAYAALP BUYUKATAMAN (GE Aircraft Engines, Lynn, MA) AIAA, AIAA, ASME, SAE. and ASEE, Joint Propulsion Conference, 25th. ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 12 p. refs Monterey, CA, July 10-13, 1989. 13 p. refs (AIAA PAPER 89-2814) (AIAA PAPER 89-2822) Advanced cooling techniques, and such improved refractory The turboprop engine gearbox design effort that has been materials as a Ni-based superalloy and carbodcarbon composites, undertaken for the USN's Long-Range Air ASW-Capable Aircraft have been used to maximize the projected performance and has emphasized the use of advanced gear-design methods, durability levels of a baseline vectoring/reversing single-expansion including the employment of a computer model incorporating most ramp nozzle (SERN) for year-2000 fighter aircraft. Impingement knowledge accumulated in the field of gear manufacturing and cooling is identified as the optimal cooling technique for both system simulation to date. The theoretical basis of the simulation metallic and carbon-composite materials, yielding significant cooling model assumes that the system consists of a series of springs, airflow reductions without durability reduction. SERN-type nozzles and that it responds to input data through time-dependent variable incorporating the improvements presently discussed do not entail and nonlinear spring rates. Gear impact locations, temperature significant increases in aircraft takeoff gross weight. O.C. distributions, dynamic surface stresses and bending stresses, lubricant film thicknesses, gear profile errors, and operating speeds, A8947102# are among the factors addressed. O.C. ADVANCED THRUST VECTORING NOZZLES FOR SUPERCRUISE FIGHTER AIRCRAFT A89-47125# J. MACE, P. SMERECZNIAK, G. KREKELER (McDonnell Aircraft TRANSFERRING JET ENGINE DIAGNOSTIC AND CONTROL Co., Saint Louis, MO), D. BOWERS (USAF, Wright Research and TECHNOLOGY TO LIQUID PROPELLANT ROCKET ENGINES Development Center, Wright-Patterson AFB, OH), M. MACLEAN JOSEPH F. ALCOCK and STEVEN K. HAGAR (United (GE Aircraft Engines, Cincinnati, OH) et al. AIAA, ASME, SAE, Technologies Corp., Pratt and Whitney Group, West Palm BeaCh, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July FL) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 10-13, 1989. 10 p. refs 25th, Monterey, CA, July 10-13, 1989. 15 p. (AIAA PAPER 89-2816) (AIAA PAPER 89-2851) The role of advanced pitchlyaw thrust vectoring nozzles in This paper presents the methodology for developing a expanding the performance envelope of future fighter aircraft has diagnostic and control system for a current, operational jet engine. been examined. Two nozzle concepts were designed and integrated A description is given of each development stage, the system into a supercruise aircraft and their static performance quantified. components and the technologies which could be transferred to Analytical and experimental data bases were developed and used liquid propellant rocket engines. Finally, the operational impact is to identify payoffs and penalties associated with using these described in terms of cost and maintenance based on actual jet advanced nozzles. Advanced nozzles having combined pitch and engine experience. Efforts are continuing to develop new diagnostic yaw thrust deflection capability are shown to provide significant techniques under IR&D for application on the advanced technical maneuver benefits for future supercruise fighters. Author fighter. Already improved techniques and application methods are
682 07 AIRCRAFT PROPULSION AND POWER becoming available. This technology is being evaluated and may The measurement methods and calculations of the flow and also be transferred to rocket engine diagnostic and control system the combustion characteristics of the jet-engine-combustor flame development. Author are described for experiments conducted in an actual combustion chamber of a jet engine, and the results of calculations, which A89-47150# were made using a two-equation turbulence model, were compared THE INFLUENCE OF SWIRL AND FUEL COMPOSITION OF with the measuremets. The flame structure inside the combustor BORON-CONTAINING FUELS ON COMBUSTION IN A SOLID and the effects of the air/fuel ratio on the flame properties were FUEL RAMJET COMBUSTION CHAMBER determined using measurements of temperature and species R. PEIN and F. VlNNEMElER (DLR, lnstitut fuer chemische Antriebe concentration of C02, CO, and 02 at four different air-to-fuel und Verfahrenstechnik, Hardthausen am Kocher, Federal Republic ratios. It was found that the calculated temperature and species of Germany) AIAA, ASME, SAE, and ASEE, Joint Propulsion concentrations were predicted reasonably well, particularly at the Conference, 25th, Monterey, CA, July 10-13, 1989. 10 p. refs downstream locations and away from the centerline region, where (AIAA PAPER 89-2885) the temperature and the C02 concentration were overpredicted Investigations in the field of boron combustion were carried and the oxygen concentration was underpredicted. IS. out at the ramjet test facility. A solid fuel ramjet combustor was used which was directly connected with an air heater and an air A89-47162# supply. The experiments were conducted with and without inlet NUMERICAL INVESTIGATION OF THRUST-REVERSING flow swirl. HTPB fuels containing boron or boron carbide in varying NOZZLE USING AN IMPLICIT TVD SCHEME compositions were applied. The effects of swirl flow and fuel S. M. LIANG (National Cheng Kung University, Tainan, Republic composition on boron combustion efficiency, fuel regression and of China) and C. L. HU AIAA, ASME, SAE, and ASEE, Joint thrust were measured. An exhaust particle sampling technique in Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 12 connection with a chemical analysis method was developed in p. Sponsorship: National Science Council of the Republic of order to measure the composition of the condensed combustion China. refs products. Author (Contract NSC-77-0401-E006-33) (AIAA PAPER 89-2899) A89-47151# A compressible Navier-Stokes solver using an implicit TVD EFFECTS OF BYPASS AIR ON THE COMBUSTION OF BORON scheme has been developed to study the performance and internal PARTICLES IN A SOLID FUEL RAMJET flowfield of a two-dimensional thrust-reversing nozzle. It is noted B. NATAN and A. GANY (Technion - Israel Institute of Technology, that the present TVD scheme overcomes numerical instablity error Haifa) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, created near the corners and satisfies the entropy condition so 25th, Monterey, CA, July 10-13, 1989. 5 p. refs that no expansion shock is captured. Results for the reverse thrusts, (AIAA PAPER 89-2886) discharge coefficients, and pressure distributions along the flap The research deals with a theoretical prediction of the and the blocker at different nozzle pressure ratios are found to combustion behavior of individual boron particles in a solid fuel agree well with experimental data. It is shown that a supersonic ramjet (SFRJ) motor. The results indicate that boron particles can bubble terminated by a weak shock and an induced separated not complete their burning inside the main combustor. The idea flow exist near the corners, and that there are high and low of using an after-burner, where bypass air is added, as a possible temperature regions on the flap and a low temperature region on solution to achieve better combustion efficiencies has been the blocker. R.R. examined. The results reveal that most of the particles can burn efficiently in a 0.5 m length after-burner. Author A89-47170# A TECHNIQUE FOR THE MEASUREMENT OF BLADE TIP A89-47153# A 3-D ANALYSIS OF GAS TURBINE COMBUSTORS CLEARANCE IN A GAS TURBINE J. W. H. CHIVERS (Rolls-Royce, PLC, Derby, England) AIAA, N. K. RlZK and H. C. MONGIA (General Motors Corp., Allison ASME, SAE, and ASEE. Joint Propulsion Conference, 25th. Gas Turbine Div., Indianapolis, IN) AIAA, ASME, SAE, and ASEE, Monterey, CA, July 10-13, 1989. 13 p. refs Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 11 p. refs (AIAA PAPER 89-2916) A technique for measuring the steady and the transient blade-tip (AIAA PAPER 89-2888) clearances in a gas turbine was developed. Problems associated In order to achieve the required performance goals and with obtaining such a measurement in a gas turbine environment structural durability of gas-turbine combustion systems, a design approach was formulated to guide the development effort of the are discussed, and a measurement specification is derived which is applicable to sea-level bench engine testing. Results are combustor. The approach combines the capabilities of the analytical tools with well established empirical correlations. By this means, presented on the performance of a prototype clearance system, which was evaluated in the laboratory, and then was used on an the impact of systematic modification to the details of the burner engine turbine. IS. is easily determined. The validation effort of the developed model included the utilization of the data obtained for a number of production combustors that significantly varied in design and A89-47178# concept. Fuels used in these combustors included typical aviation SUPERSONIC NOZZLE MIXER EJECTOR fuels such as JP-4 and DF-2 as well as specially prepared high T. G. TILLMAN, R. W. PATERSON (United Technologies Research density fuels. Model validation also involved the application of the Center, East Hartford, CT), and W. M. PRESZ, JR. (Western New model in the development phases of an annular combustor. Several England College, Springfield, MA) AIAA, ASME, SAE, and ASEE, modifications to the dome and primary zone features were proposed Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. in this effort. The predictions of the combustor performance and 10 p. Research supported by United Technologies Corp., refs wall temperatures made using the present approach were found (AIM PAPER 89-2925) to be in good agreement with the measurements. Author Experimental results are presented for the performance of a supersonic nozzle mixer-ejector representative of candidate devices A89-47155# for commercial SST noise attenuation during takeoff and landing. COMBUSTION CHARACTERISTICS OF GASEOUS FLAMES IN In this mixer-ejector configuration, an array of large-scale, A GAS TURBINE COMBUSTOR low-intensity streamwise vortices is introduced into the downstream A. M. ATTYA, M. A. HABIB, and M. R. TAHA (Cairo University, mixing duct; these enhance mixing through an inviscid-mixing Giza, Egypt) AIAA, ASME, SAE, and ASEE, Joint Propulsion process yielding enhanced ejector pumping. A convergent/ Conference, 25th, Monterey, CA, July 10-13, 1989. 10 p. refs divergent, suitably lobed mi.xer nozzle was tested and its re- (AIAA PAPER 89-2892) sults compared with those for a conventional slot-nozzle
683 07 AIRCRAFT PROPULSION AND POWER ejector. The lobed nozzle is able to increase ejector pumping England) AIAA, ASME, SAE, and ASEE, Joint Propulsion performance by 75 percent over the conventional nozzle. O.C. Conference, 25th, Monterey. CA, July 10-13, 1989. 10 p. refs (AIAA PAPER 89-2944) A89-47179# An evaluation has been conducted of the ignition characteristics EXPENDABLE SUPERSONIC EXHAUST NOZZLE CONCEPTS of a novel plasma jet igniter and a conventional surface-discharge V. D. BAKER, 0. KWON, B. V. R. VITTAL, and T. F. MCKAIN igniter, at both atmospheric and subatmospheric pressures, for (General Motors Corp.. Allison Gas Turbine Div., Indianapolis, IN) turbulence levels representative of gas turbine combustion AIAA, ASME, SAE. and ASEE, Joint Propulsion Conference, 25th, chambers; an isooctane-fueled combustion bomb was employed Monterey, CA, July 10-13,1989. 10 p. refs in these comparative performance tests. Observed lean ignition (AIAA PAPER 89-2927) limits at different turbulence levels were found to be less restrictive The minimization of propulsion system size, weight, cooling in the case of the plasma jet igniter. Quench-regime ignitions have requirements, and cornplexitylcost for a supersonic unmanned been obtained with the plasma jet, due to chemically-enhanced aircraft is presently undertaken in the specific case of the flame propagation. A subsequent evaluation of both igniters in a expendable nozzle employed by the powerplant. A series of kerosene-fueled gas turbine engine’s turboannular combustor has supersonic nozzle scale model configurations was designed with verified the combustion-bomb’s finding of considerably enhanced a view to eventual wind-tunnel testing; attention is given to the altitude-relight capability with the plasma jet. O.C. results of detailed analyses of their complex internal and external flow fields using a fully viscous compressible code. The code is A89-47191# shown to be capable of predicting the complex interaction between COMPRESSOR EXIT TEMPERATURE ANALYSIS external and internal flows. O.C. PAUL D. NELSON, NORMAN D. POTI, and JEFFREY M. STRICKER (USAF. Aero Propulsion and Power Laboratory, A89-47180’# General Electric Co., Cincinnati, OH. Wright-Patterson AFB, OH) AIAA, ASME. SAE, and ASEE, Joint A STATIC INVESTIGATION OF SEVERAL STOVL EXHAUST Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. SYSTEM CONCEPTS 7 P. B. M. ROMINE, JR., B. E. MEYER (GE Aircraft Engines, Cincinnati, (AIAA PAPER 89-2947) OH), and R. J. RE (NASA, Langley Research Center, Hampton, An analytical study has been performed to ascertain the effect VA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, of compressor exit temperature or pressure ratio, turbine inlet 25th, Monterey, CA, July 10-13, 1989. 10 p. temperature, and turbine blade and vane structure temperatures (AIAA PAPER 89-2928) will have on the takeoff gross weight of a Mach-3, 50,000-ft ceiling A static cold flow scale model test was performed in order to dry turbojet-powered interceptor. Engine performance data were determine the internal performance characteristics of various integrated with a projected mission profile having realistic STOVL exhaust systems. All of the concepts considered included anticipated constraints. The results obtained indicate that these a vectorable cruise nozzle and a separate vectorable vertical thrust mission constraints play an important role in the determination of ventral nozzle mounted on the tailpipe. The two ventral nozzle optimum design points; in addition, inlet flow matching has a configurations tested featured vectorable constant thickness substantial effect on the acceleration rate. Compressor exit cascade vanes for area control and improved performance during temperature must be of the order of 1400-1500 F, with a transition and vertical lift flight. The best transition performance corresponding pressure ratio in the 20-30 range. O.C. was achieved using a butterfly door type ventral nozzle and a pitch vectoring 2DCD or axisymmetric cruise nozzle. The clamshell ~a+47198# blocker type of ventral nozzle had reduced transition performance DISTORTION TEST CAPABILITIES FOR FUTURE FIGHTER due to the choking of the tailpipe flow upstream of the cruise AIRCRAFT ENGINES nozzle. R.R. MARK H. AMUNDSON (USAF, Arnold Engineering Development Center, Arnold AFB, TN) and RAYMOND G. HOLM (GE Aircraft A89-47186*# National Aeronautics and Space Administration. Engines, Cincinnati, OH) AIAA, ASME, SAE, and ASEE, Joint Lewis Research Center, Cleveland, OH. Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 12 INVESTIGATION OF LOW NOX STAGED COMBUSTOR p. refs CONCEPT IN HIGH-SPEED CIVIL TRANSPORT ENGINES (AIAA PAPER 89-2956) HUNG LEE NGUYEN, DAVID A. BITTKER, and RICHARD W. Limitations currently exist in the ability of fighter aircraft engine NlEDZWlECKl (NASA, Lewis Research Center, Cleveland, OH) test facilities to simulate inlet pressure-distortion fields due to AIAA, ASME, SAE. and ASEE, Joint Propulsion Conference, 25th, maneuvering and inlet temperature-distortion fields due to the Monterey, CA, July 10-13, 1989. 14 p. Previously announced in ingestion of plumes from missile firings. The suitability of the STAR as N89-22606. refs Aeropropulsion Systems Test Facility Test Cell C-1 for engineering (AIAA PAPER 89-2942) evaluations of pressure and temperature distortion simulations has Levels of exhaust emissions due to high temperatures in the been evaluated in conjunction with the Airjet Distortion Generator main combustor of high-speed civil transport (HSCT) engines during employed by this test facility. Attention was also given to the supersonic cruise are predicted. These predictions are based on facility’s ability to produce time-dependent inlet pressure and a new combustor design approach: a rich burnlquick quenchllean temperature distortions. O.C. burn combustor. A two-stage stirred reactor model is used to calculate the combustion efficiency and exhaust emissions of this A89-47199# novel combustor. A propane-air chemical kinetics model is used NORMAL IMPINGING JET IN CROSSFLOW - A PARAMETRIC to simulate the fuel-rich combustion of jet fuel. Predicted engine INVESTIGATION exhaust emissions are compared with available experimental test D. BRAY and K. KNOWLES (Royal Military College of Science, data. The effect of HSCT engine operating conditions on the levels Shrivenham, England) AIAA, ASME, SAE, and ASEE, Joint of exhaust emissions is also presented. The work described in Propulsion Conference, 25th, Monterey, CA. July 10-13, 1989. 9 this paper is a part of the NASA Lewis Research Center High-speed p. refs Civil Transport Low NO(x) Combustor program. Author (AIAA PAPER 89-2957) The flowfield of a single round impinging jet in crossflow has ~89-4718a# been experimentally studied, with special attention given to EVALUATION OF NOVEL IGNITERS IN A TURBULENT BOMB parametric effects on ground vortex penetration. It is found that FACILITY AND A TURBO-ANNULAR GAS TURBINE application of a moving ground plane decreased penetration by COMBUSTOR about 20 percent, and that increased nozzle height increased wall H. C. LOW, C. W. WILSON (Rolls-Royce, PLC, Bristol, England), jet momentum and ground vortex penetration. For the case of the R. G. ABDEL-GAYED, and D. BRADLEY (Leeds, University, nozzle height being above the vortex height, deflection of the jet
684 07 AIRCRAFT PROPULSION AND POWER axis is found to occur, moving back the impingement point and N89-26004'# Sverdrup Technology, Inc., Cleveland, OH. leading to reductions in penetration (as measured from the nozzle TURBOFAN ENGINE CONTROL SYSTEM DESIGN USING THE centerline). R.R. LQG/LTR METHODOLOGY Flnal Report SANJAY GARG Jun. 1989 24 p Presented at the American Control Conference, Pittsburgh, PA, 21 -23 Jun. 1989; sponsored N89-25165'# National Aeronautics and Space Administration. by American Automatic Control Council Lewis Research Center, Cleveland, OH. (Contract NAS3-25266) STRUCTURAL TAILORING OF COUNTER ROTATION (NASA-CR-182303; E-4765; NAS 1.26:182303) Avail: NTlS HC PROPFANS AOWMF A01 CSCL 21 /5 KENNETH W. BROWN (Pratt and Whitney Aircraft, East Hartford, Application of the Linear-Quadratic-Gaussian with Loop- CT.) and D. A. HOPKINS /n NASA. Langley Research Center, Transfer-Recovery methodology to design of a control system Recent Advances in Multidisciplinary Analysis and Optimization, for a simplified turbofan engine model is considered. The Part 1 p 389-402 Apr. 1989 importance of properly scaling the plant to achieve the desired (Contract NAS3-23941) Target-Feedback-Loop is emphasized. The steps involved in the Avail: NTlS HC A23/MF A01 CSCL 21 15 application of the methodology are discussed via an example, The STAT program was designed for the optimization of single and evaluation results are presented for a reduced-order rotation, tractor propfan designs. New propfan designs, however, compensator. The effect of scaling the plant on the stability generally consist of two counter rotating propfan rotors. STAT is robustness evaluation of the closed-loop system is studied in constructed to contain two levels of analysis. An interior loop, detail. Author consisting of accurate, efficient approximate analyses, is used to perform the primary propfan optimization. Once an optimum design N89-26005# United Technologies Research Center, East Hartford, has been obtained, a series of refined analyses are conducted. CT. These analyses, while too computer time expensive for the THREE DIMENSIONAL FLOW AND TEMPERATURE PROFILE optimization loop, are of sufficient accuracy to validate the ATTENUATION IN AN AXIAL FLOW TURBINE Final Report, 15 optimized design. Should the design prove to be unacceptable, Dec. 1985 - 15 Mar. 1989 provisions are made for recalibration of the approximate analyses, DAVID H. JOSLYN and ROBERT P. DRlNG 15 Mar. 1989 for subsequent reoptimization. Author 136 p (Contract F49620-86-C-0020) (AD-A206736; AFOSR-89-0439TR) Avail: NTlS HC A07/MF A01 N89-25207'# Textron Lycoming, Stratford, CT. CSCL 21/5 PROCEDURES FOR SHAPE OPTIMIZATION OF GAS TURBINE While strongly three dimensional and highly unsteady nature DISKS of the flow in axial turbines has, until recently, defied in-depth TSU-CHIEN CHEU ln NASA. Langley Research Center, Recent analysis, the benefits that can be realized from an improved Advances in Multidisciplinary Analysis and Optimization, Part 3 p capability to predict the aerodynamics and heat transfer in turbines 1097-1108 Apr. 1989 are numerous. These benefits include improved performance Avail: NTlS HC A22/MF A01 CSCL 2115 through higher efficiency, higher thrust-to-weight ratio through Two procedures, the feasible direction method and sequential higher turbine inlet temperature, and improved durability through linear programming, for shape optimization of gas turbine disks more precise predictions of local heat load. This program was are presented. The objective of these procedures is to obtain particularly interested in the aerodynamic mechanisms affecting optimal designs of turbine disks with geometric and stress attenuation of a radial temperature profile in the flow as it passed constraints. The coordinates of the selected points on the disk through the turbine. The radial temperature profile in the flow contours are used as the design variables. Structural weight, stress exiting a combustor and entering a turbine can range from and their derivatives with respect to the design variables are compressor exit temperature (approx = 1100 F) near the. hub calculated by an efficient finite element method for design senitivity and tip end walls to a maximum (as high as 3200 F) in the analysis. Numerical examples of the optimal designs of a disk midspan region. The heat load at any location on the turbine subjected to thermo-mechanical loadings are presented to illustrate airfoils or end walls depends strongly on the local gas temperature and compare the effectiveness of these two procedures. Author at that location; hence the mixing, or attenuation, of the inlet temperature profile is of critical importance. This program has N89-25238'# National Aeronautics and Space Administration. advanced the state-of-the-art by providing: (1) an exhaustive Lewis Research Center, Cleveland, OH. aerodynamic data base for the three dimensional flow in a large FUEL PROPERTIES EFFECT ON THE PERFORMANCE OF A scale axial turbine; (2) an exhaustive data base documenting the SMALL HIGH TEMPERATURE RISE COMBUSTOR mixing of a simulated combustor exit temperature profile as it WALDO A. ACOSTA and STEPHEN A. BECKEL (Pratt and Whitney passed through the turbine; and (3) an assessment of state of Aircraft, West Palm Beach, FL.) Jul. 1989 12 p Presented at the art three dimensional time accurate, Navier-Stokes prediction the 25th Joint Propulsion Conference, Monterey, CA. 10-12 Jul. of the flow in the turbine stage. GRA 1989; sponsored in part by AIAA, ASME, SAE, and ASEE (Contract N00140-83-C-8899) N8926006# Air Force Wright Aeronautical Labs., (NASA-TM-102096; AVSCOM-TR-89-C-004; E-4857; NAS Wright-Patterson AFB, OH. Turbine Engine Div. 1.15:102096 AIAA-89-2901) Avail: NTlS HC AO3/MF A01 TWO AXIAL COMPRESSOR DESIGNS FOR A STAGE CSCL 21 /5 MATCHING INVESTIGATION Final lnterlm Report, 1 Jan. - 30 The performance of an advanced small high temperature rise Sep. 1988 combustor was experimentally determined at NASA-Lewis. The C. HERBERT LAW Mar. 1989 281 p combustor was designed to meet the requirements of advanced (AD-A206951; AFWAL-TR-89-2005) Avail: NTlS HC A1 3/MF high temperature, high pressure ratio turboshaft engines. The A01 CSCL 13/11 combustor featured an advanced fuel injector and an advanced The design of two single-stage axial-flow compressors for a segmented liner design. The full size combustor was evaluated at stage matching investigation are described. The purpose of the power conditions ranging from idle to maximum power. The effect investigation is to develop a data base and design techniques of broad fuel properties was studied by evaluating the combustor necessary to match supersonic blade rows in turbomachinery with three different fuels. The fuels used were JP-5, a blend of compression systems. Two compressor designs are required to Diesel Fuel Marine/Home Heating Oil, and a blend of Suntec investigate both fan-type and core-type compression systems, since C/Home Heating Oil. The fuel properties effect on the performance each configuration has unique aerodynamic and performance of the combustion in terms of pattern factor, liner temperatures, characteristics. The latest state-of-the-art aerodynamic and and exhaust emissions are documented. Author mechanical design techniques were used to design two supersonic
685 07 AIRCRAFT PROPULSION AND POWER stages to be tested in an environment typical of the second-stage on variable-structure system theory, a discontinuous control of an advanced military fan and an advanced military core law is derived that accomplishes asymptotic decoupled output compressor. This report presents the results of the detailed trajectory-following in the presence of uncertainty in the system. aerodynamic design of the two compressor stages. GRA In the closed-loop system, the trajectories are attracted toward a chosen hypersurface in the state space and then slide along it. N8926008'# National Aeronautics and Space Administration. During the sliding phase the motion is insensitive to parameter Lewis Research Center, Cleveland, OH. variations. Based on this result, a control law for asymptotically AERONAUTICAL APPLICATIONS OF HIGH-TEMPERATURE decoupled control of roll angle, angle of attack, and sideslip in SUPERCONDUCTORS rapid, nonlinear maneuvers is derived. Simulation results are GEORGE E. TURNEY, ROGER W. LUIDENS. KENNETH UHERKA, presented to show that large, simultaneous lateral and longitudinal and JOHN HULL (Argonne National Lab., IL.) Aug. 1989 15 p maneuvers can be performed in spite of uncertainty in the stability Presented at the Aircraft Design, Systems and Operations derivatives. I.E. Conference, Seattle, WA, 31 Jul. - 2 Aug. 1989; sponsored in part by AIAA, AHS, and ASEE A89-45151 (NASA-TM-102311; E-4951; NAS 1.15102311) Avail: NTlS HC 1988 REPORT TO THE AEROSPACE PROFESSION: SOCIETY A03/MF A01 CSCL 21/5 OF EXPERIMENTAL TEST PILOTS, SYMPOSIUM, 32ND, The successful development of high-temperature BEVERLY HILLS, CA, OCT. 13-15, 1988, PROCEEDINGS superconductors (HTS) could have a major impact on future Symposium sponsored by the Society of Experimental Test Pilots. aeronautical propulsion and aeronautical flight vehicle systems. A Lancaster, CA, Society of Experimental Test Pilots, 1988, 371 p. preliminary examination of the potential application of HTS for For individual items see A89-45152 to A89-45168. aeronautics indicates that significant benefits may be realized Various papers on aerospace topics are presented. The subjects through the development and implementation of these newly addressed include: testing for agility, F-14/F-110 high angle of discovered materials. Applications of high-temperature super- attack flight tests, results and lessons learned from X-29A conductors (currently substantiated at 95 K) were envisioned performance flight test, F-18 Hornet-LEX Fence flight test results, for several classes of aeronautical systems, including subsonic progress on the ATF, initial flight test results of F-15 and supersonic transports, hypersonic aircraft, V/STOL aircraft, STOL/Maneuvering Technology Demonstrator, F/A 18 Digital Flight rotorcraft, and solar, microwave and laser powered aircraft. Control System degraded modes flight evaluation, and methodology Introduced and described are the particular applications and of FAA handling qualities assessment. Also discussed are: digital potential benefits of high-temperature superconductors as related flight and inlet control in the SR-71, aspects of the development to aeronautics and/or aeronautical systems. Author of the longitudinal control system of the Fokker 100, 8-1B high AOA testing, model 360 development, requirements and testing of manual CAT llla with A HUD, tactical significance of helicopter aerobatic flight, B-1B development testing, Space Shuttle crew escape, supersonic cruise fighter design, and X-15 pilot-in-the-loop and redundantlemergency systems evaluation. C.D. AIRCRAFT STABILITY AND CONTROL A8945152 Includes aircraft handling qualities; piloting; flight controls; and TESTING FOR AGILITY - A PROGRESS REPORT autopilots. ALAN D. HOOVER (USAF, Research Projects Office, Edwards AFB, CA) IN: 1988 report to the aerospace profession; Society of Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, A8945048 Oct. 13-15, 1988, Proceedings. Lancaster, CA, Society of SIMULATION METHODOLOGY FOR HELICOPTER Experimental Test Pilots, 1988, p. 3-22. AUTOMATIC FLIGHT CONTROL SYSTEMS [METHODOLOGIE Progress made to date in defining metrics for aircraft agility is DE SIMULATION DES SYSTEMES DE COMMANDES reviewed. Simplified comparisons are made between aircraft. A AUTOMATIQUES DE VOL DUN HELICOPTERE] case study in agility design is examined. C.D. MARC ACHACHE (Aerospatiale, Division Helicopteres, Marignane, France) (Ecole Nationale Superieure de I'Aeronautique et de A89451 53 I'Espace, Colloque International sur la Simulation - INFAUTOM F-l4/F110 HIGH ANGLE OF ATTACK FLIGHT TESTS 89, 5th, Toulouse, France, Mar. 2, 1989) L'Aeronautique et JOE EDWARDS (US. Navy, Naval Air Test Center, Patuxent River, I'Astronautique (ISSN 0001-9275), no. 136-137, 1989, p. 128-134. MD) IN: 1988 report to the aerospace profession; Society of In French. Experimental Test Pilots, Symposium, 32nd. Beverly Hills, CA, Oct. The application of different types of simulators for studying the 13-15. 1988, Proceedings. Lancaster, CA, Society of Experimental various phases of the development and testing of helicoptor Test Pilots, 1988, p. 23-49. automatic FCSs is considered, and three simulator tools are The F-14 Tomcat has been plagued throughout its service life described in detail. The Rebeca tool treats the frequential aspects by a series of engine operability and reliability problems, particularly of the automatic FCS, and it is used to derive the helicopter in the high angle of attack (AOA) flight regime. This paper reports control laws. The delayed-time simulation tool Smash was flight tests results for the F110-GE-400 engine which will be developed for such helicopters as Dauphin, HAP, and "90. Smash incorporated into the F-14D in 1990. The present version of the performs closed-loop simulations which are capable of integrating F-14, called the F-l4A(PLUS), the flight control system, and the different helicopter, sensor, or actuator models. The Sisyphe tool test aircraft are reviewed, and the scope of the tests is examined. simulates the real-time functioning of automatic FCS software. The AOA flight characteristics exhibited by the F-14 are described, R.R. including directional stability, dihedral effect, kinematic coupling, stores effect, stalls, and spins. Departures that occurred during A8945064 AOA tests, including lateral control-induced departures, rudder and ASYMPTOTICALLY DECOUPLED DISCONTINUOUS CONTROL cross control-induced departures, asymmetric thrust-induced OF SYSTEMS AND NONLINEAR AIRCRAFT MANEUVER departures, vertical stalls, and inertia-coupled departures are SAHJENDRA N. SlNGH (Nevada, University, Las Vegas) IEEE addressed, Engine performance during the tests and recovery from Transactions on Aerospace and Electronic Systems (ISSN departures are discussed. C.D. 0018-9251), vol. 25, May 1989, p. 380-391. refs (Contract DAAL03-87-G-0004) A8945154 The question of control of a class of nonlinear systems that X-29A PERFORMANCE FLIGHT TESTS - RESULTS AND can be decoupled by state-variable feedback is considered. Based LESSONS LEARNED
686 08 AIRCRAFT STABILITY AND CONTROL
HARRY C. WALKER, 111 (USAF, Flight Test Center, Edwards AFB, modes. This paper discusses the flight test techniques and mission CA) IN: 1988 report to the aerospace profession; Society of tasks utilized to evaluate the F/A-18 degraded digital FCS and Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. highlights some of the results obtained. C.D. 13-15, 1988, Proceedings. Lancaster, CA, Society of Experimental Test Pilots, 1988, p. 50-71. refs A89-45 159 The X-29 was developed to perform flight tests of advances in FAA HANDLING QUALITIES ASSESSMENT - METHODOLOGY aerodynamics that are thought to hold promise for increasing IN TRANSITION performance. The major resources used to such flight tests are COLLET E. MCELROY (FAA, Seattle Aircraft Certification Office, summarized, and the objectives, techniques, and data reduction WA) IN: 1988 report to the aerospace profession; Society of used in performance testing are discussed. Results of X-29 Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. performance testing with regard to the effects of variable camber 13-15, 1988, Proceedings. Lancaster, CA, Society of Experimental control, maneuver dynamic effects, and other effects on Test Pilots, 1988, p. 149-166. performance are examined, and a comparison is made between Changes in FAA methodology for handling qualities assessment the forward swept wings of the X-29 and conventional aft-swept called for by the introduction of maneuver demandlfly-by-wire wing fighter aircraft. Engineering disciplines related to performance technology into civil air transport are discussed. The new FAA that were tested during the course of the X-29 flight test are handling qualities rating method (HQRM) and a new ratings considered. C.D. methodology that has been developed are discussed. Operational considerations are addressed. C.D. A89-45155 F-18 HORNET - LEX FENCE FLIGHT TEST RESULTS A89-45161 F. ALAN FRAZIER (McDonnell Aircraft Co., Saint Louis, MO) IN: FOKKER 100, SOME ASPECTS OF THE DEVELOPMENT OF 1988 report to the aerospace profession; Society of Experimental THE LONGITUDINAL CONTROL SYSTEM Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, WIM J. HUSON (Fokker Aircraft, Amsterdam, Netherlands) IN: Proceedings. Lancaster, CA, Society of Experimental Test Pilots, 1988 report to the aerospace profession; Society of Experimental 1988, p. 72-89. refs Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, The F/A-18 Hornet in operational service has exhibited Proceedings. Lancaster, CA, Society of Experimental Test Pilots, extraordinary high angle of attack performance. The severe penalty 1988, p. 182-197. paid for this often-used capability is the high dynamic load Some of the problem areas that were encountered during the environment experienced by the empennage during high speed development and certification process for the longitudinal control high angle of attack maneuvering. In 1985, flight testing was in the Fokker 100 aircraft are reviewed. It is shown that predictions completed that initially defined the dynamic load environment and made at the first flight were not completely correct for low-speed qualified an interim structural modification of the vertical tail stall and for ground effect. Certification issues are discussed. structure. Subsequent engineering investigations and wind tunnel C.D. testing have identified an aerodynamic solution, the LEX Fence, which alters the high energy vortex shed from the Leading Edge A89-45162 Extension (LEX) prior to its impingement on the vertical tail surfaces. B-1B HIGH AOA TESTING Conclusion of the LEX Fence flight test program has since resulted ADDISON S. THOMPSON (Rockwell International Corp., Pittsburgh, in NAVAIR approval of the LEX Fence modification of all F/A-18 PA) IN: 1988 report to the aerospace profession; Society of aircraft. This paper reports in detail the conduct and results of Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. this flight test program. Author 13-15, 1988, Proceedings. Lancaster, CA, Society of Experimental Test Pilots, 1988, p. 198-204. A8945157 Changes made in the B-1B aircraft resulted in performance F-15 STOL/MANEUVERING TECHNOLOGY DEMONSTRATOR - being constrained by angle of attack (AOA) limits during some INITIAL FLIGHT TEST RESULTS mission phases. Since B-1A testing had shown that there was LAURENCE A. WALKER (McDonnell Aircraft Co., Saint Louis, MO) more lift available if it could be utilized, a flight control system and WILLIAM R. NEELY (USAF, Wright-Patterson AFB, OH) IN: modification called Stall Inhibitor System (SIS) was developed to 1988 report to the aerospace profession; Society of Experimental enable the envelope to be more fully realized. The flight control Test Pilots, Symposium, 32nd, Beverly Hills, CA. Oct. 13-15, 1988, system with the SIS is described here, and some flight test methods Proceedings. Lancaster, CA. Society of Experimental Test Pilots, and results with the SIS are reported. C.D. 1988, p. 110-127. The technologies and testing involved in the development of A89-45164 the F-15 STOLIManeuvering Technolgoy Demonstrator are MANUAL CAT IllA WITH A HUD - REQUIREMENTS AND examined. Four key technologies are described: the two- TESTING dimensional thrust vectoring and reversing nozzle, the inte- HOWARD B. GREENE (FAA, Seattle, WA) IN: 1988 report to grated flightlpropulsion control system, the rough field landing the aerospace profession; Society of Experimental Test Pilots, gear, and the plot-vehicle interface. The role of simulation is the Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, Proceedings. system development and the flight test program status are Lancaster, CA, Society of Experimental Test Pilots, 1988, p. summarized, and initial flight test results are discussed. C.D. 223-238. Test requirements have been developed and used to A89-45158 demonstrate the HUD/aircraft/human pilot system capability to F/A-lIA DIGITAL FLIGHT CONTROL SYSTEM DEGRADED perform reliably the manual landing task in low-visibility conditions. MODES FLIGHT EVALUATION The use of a HUD in the manual CAT llla landing task is discussed TERRY M. HOFFART and MARC G. STEVENS (US. Navy, Naval in detail. Performance test results are reviewed, and visual and Air Test Center, Patuxent River, MD) IN: 1988 report to the fixation lessons learned from the tests are addressed. C.D. aerospace profession; Society of Experimental Test Pilots, Symposium, 32nd, Beverly Hills, CA, Oct. 13-15, 1988, Proceedings. A89-45165 Lancaster, CA, Society of Experimental Test Pilots, 1988. p. 8-1B DEVELOPMENT TESTING 130-148. DAVID J. EICHHORN and HAROLD R. GASTON (USAF, The F/A-18 aircraft utilizes a four-channel digital fly-by-wire Washington, DC) IN: 1988 report to the aerospace profession; flight control system (FCS) with a control augmentation system as Society of Experimental Test Pilots, Symposium, 32nd, Beverly its primary FCS mode. Backup or degraded FCS modes are Hills, CA, Oct. 13-15, 1988, Proceedings. Lancaster, CA, Society provided in the event of specific system failures to the FCS and of Experimental Test Pilots, 1988, p. 255-277. include the direct electrical linkage and the mechanical backup The flight test results of the B-1B Terrain following (TF) System
687 08 AIRCRAFT STABILITY AND CONTROL and the 6-16 Weapons Certification Program are discussed. The provide the integrated control communication paths and the TF system and the certification program are described along with simulation feedback data. In piloted tests, the use of pitch vectoring, the test objectives and methods. Typical weapon separations are yaw vectoring, and reversing nozzles as primary control effectors shown. C.D. at low air speeds, in combination with the robust control laws and control selector, resulted in greatly enhanced aircraft agility A89-45179# throughout the entire flight envelope. R.R. THE INFLUENCE OF ALTITUDE AND SPEED VARIATIONS ON THE AEROPLANES LOAD COMPONENTS IN LONGITUDINAL A89-47030’# Boeing Co., Seattle, WA. NONLINEAR MANOEUVRES EXPERIENCES WITH A PREVALIDATION METHODOLOGY I. TEPOSU (Institutul National pentru Creatie Stiintifica si Tehnica, FOR DESIGNING INTEGRATED/PROPULSION CONTROL Bucharest, Rumania) Revue Roumaine des Sciences Techniques, SYSTEM ARCHITECTURES Serie de Mecanique Appliquee (ISSN 0035-4074), vol. 34, Mar.-Apr. GERALD C. COHEN, CHARLES W. LEE, MICHAEL J. 1989, p. 131-149. refs STRICKLAND (Boeing Co., Boeing Advanced Systems, Seattle, The aerodynamic and inertial load components in the xyz WA), and DANIEL L. PALUMBO (NASA, Langley Research Center, reference system are determined for the case of longitudinal Hampton. VA) AIAA, ASME, SAE, and ASEE, Joint Propulsion maneuvers with large variations of incidence angle, altitude, and Conference, 25th, Monterey, CA, July 10-13, 1989. 11 p. refs speed. It is shown that maneuvers with incidence changes up to (Contract NASl-18099) the stall point and about 1,500-m altitude variations can be (AIM PAPER 89-2703) described with a precision of 2-3 percent in the load estimation. This paper describes a validation methodology and supporting The results may be used in the determination of the nonlinear analytical tools developed to provide system designers with a response of an aircraft and the maneuvering loads on an aircraft‘s capability of selecting, in the early stages of development, components. R.B. candidate architectures for an integrated airframe/propulsion control system and of predicting their reliability and performance. A89-45294# The results of an application of this methodology to an integrated A PILOT’S VIEW OF INTELLIGENT SYSTEMS flight and propulsion control system demonstrated that firm system DOUGLAS M. HOSMER (Lockheed Aeronautical Systems Co., requirements are being established early in the system life cycle Burbank, CA) Aerospace America (ISSN 0740-722X). vol. 27, and that an early evaluation exposes missing and conflicting July 1989, p. 32, 33. specifications. It is shown that fundamental improvements and The current trend toward single-seat combat aircraft and the refinements can be made early in the concept life cycle when the accompanying evolution of avionics and complex subsystems have potential for increased performance is high and the cost and increased pilot workloads to a degree that is unacceptable in schedule impacts from changes are relatively low. The application combat. An interactive/cooperative real-time expert system of this methodology reduces technical risks associated with functioning as ’pilot’s associate’ is therefore proposed which can integrated system concepts incorporating new technologies. IS. alternatively either assess a situation and advise the pilot as to possible courses of action or, in the event of the pilot’s delegation A8947031 ’# National Aeronautics and Space Administration, of the requisite authority, take appropriate action. The greatest Washington, DC. anticipated payoff from a pilot’s associate system lies in the sorting, INTEGRATED CONTROLS PAY-OFF filtering, and fusing of information destined for the pilot’s attention TERRILL W. PUTNAM and RICHARD S. CHRISTIANSEN (NASA, and decisionmaking. O.C. Washington, DC) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 6 p. A8946546 (AIAA PAPER 89-2704) MODELING OF CONTROLLED FLIGHT DYNAMICS USING It is shown that the integration of the propulsion and flight IN-FLIGHT SIMULATORS [MODELIROVANIE DlNAMlKl control systems for high performance aircraft can help reduce UPRAVLIAEMOGO POLETA NA LETAIUSHCHIKH pilot workload while simultaneously increasing overall aircraft LABORATORIIAKH] performance. Results of the Highly Integrated Digital Electronic LEONID M. BERESTOV and VADlM V. GORlN Moscow, Control (HiDEC) flight research program are presented to Izdatel’stvo Mashinostroenie, 1988, 112 p. In Russian. refs demonstrate the emerging payoffs of controls integration. Ways in The fundamentals of flight dynamic modeling using in-flight which the performance of fighter aircraft can be improved through simulators, the principles of base flight vehicle and control system the use of propulsion for primary aircraft control are discussed. selection, and the use of in-flight simulation for modeling the stability Research being conducted by NASA with the F-18 High Angle-of and controllability characteristics of prospective flight vehicles are Attack Research Vehicle is described. K.K. reviewed. The discussion covers the theory of in-flight simulation, the structure of control systems for in-flight simulators, A89-47032# simulator-flight vehicle similarity criteria, principles of the design THE EVOLUTION - IFPC TO VMS of in-flight simulators, and the use of in-flight simulators for pilot R. E. MATTES and W. A. YONKE (McDonnell Aircraft Co., Saint training. V.L. Louis, MO) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey. CA, July 10-13, 1989. 10 p. A8947029# (AIAA PAPER 89-2705) THE PURSUIT OF INTEGRATED CONTROL - A REALTIME The gains demonstrated in the Highly Integrated Digital Engine AIRCRAFT SYSTEM DEMONSTRATION Control Program are summarized. Gains expected from the KENNETH D. TILLMAN. TIMOTHY J. IKELER (United Technologies extension of this vehicle management system functional integration Corp., Pratt and Whitney Group, West Palm Beach, FL), and philosophy to the utility systems are predicted. Integrated RUSSELL A. PURTELL (Northrop Corp., Aircraft Div., Hawthorne, flight/propulsion control has revealed major benefits in engine CA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, performance which can be obtained through integrated control. 25th, Monterey, CA, July 10-13. 1989. 8 p. K.K. (AIM PAPER 89-2701) Digital flight control and digital engine control hardware were A89-47166’# National Aeronautics and Space Administration. combined with cockpit control hardware and computer simulations Lewis Research Center, Cleveland, OH. of aircraft and engines in order to develop a real-time closed-loop INTEGRATED FLIGHT/PROPULSIO.NCONTROL STUDY FOR piloted integrated flight and propulsion control system. Integrated STOVL APPLICATIONS control laws have been obtained to provide optimal blending of JAMES R. MIHALOEW (NASA, Lewis Research Center, Cleveland, vectored thrust and aerodynamic control surfaces. MIL-STD-15536 OH) and CARL WEISS (United Technologies Corp., Pratt and and high speed optic token passing data busses are employed to Whitney Group, West Palm Beach, FL) AIAA, ASME, SAE. and
688 08 AIRCRAFT STABILITY AND CONTROL
ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, requirements. A subset of the available eigenvector freedoms was 1989. 7 p. employed. The eigenvector freedoms associated with a particular (AIAA PAPER 89-2908) closed-loop eigenvalue are coefficients of basis vectors which span The STOVL Integrated Flight Propulsion Controls (IFPC) the subspace in which that closed-loop vector must lie. Design Program, initiated by NASA Lewis and NASA Ames to develop requirements are included as a vector of inequality constraints. the necessary technologies for integrating the flight and propulsion The procedure was successfully applied to develop an unscheduled controls of a future STOVL aircraft, is described. A major element controller which stabilizes symmetric flutter of an aeroelastic vehicle of the STOVL IFPC Program is the STOVL Controls Integration to a dynamic pressure 44 percent above the open-loop flutter Program (SCIP), which focuses on the development of an integrated point. The design process proceeded from full-state feedback to flight propulsion control for the advanced vectored thrust STOVL the inclusion of a full-order observer to the selection of an concept. The SClP has progressed to the point of generating top eighth-order controller which preserved the full-state sensitivity level control requirements. K.K. characteristics. Only a subset of the design freedoms was utilized (i.e., assuming full-state feedback only four out of 26 eigenvectors N89-25141# Technische Hochschule, Aachen (Germany, F.R.). were used, and no variations were made in the closed-loop FLIGHT-MECHANICAL INVESTIGATIONS OF THE LATERAL eigenvalues). Utilization of additional eigensystem freedoms could MOTION OF CONFIGURATIONS WITH WINGLETS further improve the controller. Author [FLUGMECHANISCHE UNTERSUCHUNGEN ZUR SEITENBEWEGUNG VON KONFIGURATIONEN MIT WING LETS] A. DIEKMANN and A. JOSTEN In its Vortex Flows in Flying N89-25193'# Planning Research Corp., Hampton, VA. Technique p 339-371 1988 In GERMAN DIGITAL ROBUST CONTROL LAW SYNTHESIS USING Avail: NTlS HC A17/MF A01 CONSTRAINED OPTIMIZATION The effect of an aerodynamically optimized winglet with trailing VIVEKANANDA MUKHOPADHYAY ln NASA. Langley Research edge flap, on the flight characteristics was investigated, using the Center, Recent Advances in Multidisciplinary Analysis and Rallye Morane aircraft. The static forces and moments, as well as Optimization, Part 2 p 879-895 Apr. 1989 the effect of the winglet on roll damping were determined in wind (C,ontract NASI -8000) tunnel tests. The dynamic behavior and winglet action during Avail: NTlS HC A22/MF A01 CSCL 0113 spinning were determined during flight tests. The calculation of Development of digital robust control laws for active control the dynamic behavior of the aircraft with tip strips or winglets is of high performance flexible aircraft and large space structures is based on the measured static force and moment coefficients as a research area of significant practical importance. The flexible well as on the estimated dynamic derivatives. The effect of the system is typically modeled by a large order state space system winglet on the coupling between longitudinal and lateral motion of equations in order to accurately represent the dynamics. The was calculated. Nonlinear effects for large angles of attack and active control law must satisy multiple conflicting design sideslip angles were taken into account. ESA requirements and maintain certain stability margins, yet should be simple enough to be implementableon an onboard digital computer. N89-25189'# Purdue Univ., West Lafayette, IN. Described here is an application of a generic digital control law AEROSERVOELASTIC TAILORING FOR LATERAL CONTROL synthesis procedure for such a system, using optimal control theory ENHANCEMENT and constrained optimization technique. A linear quadratic Gaussian TERRENCE A. WEISSHAAR and NAM CHANGHO In NASA. type cost function is minimized by updating the free parameters Langley Research Center, Recent Advances in Multidisciplinary of the digital control law, while trying to satisfy a set of constraints Analysis and Optimization, Part 2 p 803-814 Apr. 1989 on the design loads, responses and stability margins. Analytical Avail: NTlS HC A22/MF A01 CSCL 0113 expressions for the gradients of the cost function and the The need for effective aileron power for aircraft lateral control constraints with respect to the control law design variables are and turning maneuvers dates back to the Wright Brothers and used to facilitate rapid numerical convergence. These gradients their wing warping concept for active stabilization of their aircraft. can be used for sensitivity study and may be integrated into a Early researchers in Great Britain, Japan, Germany and the United simultaneous structure and control optimization scheme. Author States explored ways to increase the effectiveness of control aileron to generate a roll moment. The basic problem of aileron effectiveness and the interrelationship between structural distortion and the loads applied by the control surface is illustrated. A rigid N89-25195'# National Aeronautics and Space Administration. wing/aileron surface will develop the capability to generate Hugh L. Dryden Flight Research Facility, Edwards, CA. increased roll rates as airspeed increases. A flexible surface will CONTROL SURFACE SPANWISE PLACEMENT IN ACTIVE become less effective as airspeed increases because of the twisting FLUTTER SUPPRESSION SYSTEMS distortion created by the aft-mountedcontrol surface. This tendency E. NlSSlM and J. J. BURKEN In NASA. Langley Research is further worsened by bending distortion of an aft swept wing. Center, Recent Advances in Multidisciplinary Analysis and This study focuses its attention on the ability of a combined effort Optimization, Part 2 p 919-934 Apr. 1989 Prepared in between structural redesign of a wing and sizing and placement cooperation with Technion-Israel Inst. of Technology, Haifa of a control surface to create specified roll performance with a Avail: NTlS HC A22/MF A01 CSCL 0113 minimum hinge moment. This design optimization problem indicates All flutter suppression systems require sensors to detect the the advantages of simultaneous consideration of structural design movement of the lifting surface and to activate a control surface and control design. Author according to a synthesized control law. Most of the work performed to date relates to the development of control laws based on N89-25191"# National Aeronautics and Space Administration. predetermined locations of sensors and control surfaces. These Langley Research Center, Hampton, VA. locations of sensors and control surfaces are determined either FLUTTER SUPPRESSION USING EIGENSPACE FREEDOMS TO arbitrarily, or by means of a trial and error procedure. The MEET REQUIREMENTS aerodynamic energy concept indicates that the sensors should be WILLIAM M. ADAMS, JR., ROBERT E. FENNELL, and DAVID M. located within the activated strip. Furthermore, the best chordwise CHRlSTHlLF (Planning Research Corp., Hampton, VA.) ln its location of a sensor activating a T.E. control surface is around Recent Advances in Multidisciplinary Analysis and Optimization, the 65 percent chord location. The best chordwise location for a Part 2 p 837-859 Apr. 1989 sensor activating a L.E. surface is shown to lie upstream of the Avail: NTlS HC A22/MF A01 CSCL 01 /3 wing (around 20 percent upstream of the leading edge), or A constrained optimization methodology has been developed alternatively, two sensors located along the same chord should which allows specific use of eigensystem freedoms to meet design be used. Author
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N89-25239'# National Aeronautics and Space Administration. The Active Flexible Wing Project is a collaborative effort Langley Research Center, Hampton, VA. between the NASA Langley Research Center and Rockwell AN ANALYTICAL SENSITIVITY METHOD FOR USE IN International. The objectives are the validation of methodologies INTEGRATED AEROSERVOELASTIC AIRCRAFT DESIGN associated with mathematical modeling, flutter suppression control MICHAEL G. GILBERT May 1989 12 p Presented at the law development and digital implementation of the control system European Forum on Aeroelasticity and Structural Dynamics, for application to flexible aircraft. A flutter suppression control law Aachen. Fed. Republic of Germany, 17-19 Apr. 1989 synthesis for this project is described. The state-space (NASA-TM-101583; NAS 1.15:101583) Avail: NTlS HC A031MF mathematical model used for the synthesis included ten flexible A01 CSCL 0113 modes, four control surface modes and rational function Interdisciplinary analysis capabilities have been developed for approximation of the doublet-lattice unsteady aerodynamics. The aerosewoelastic aircraft and large flexible spacecraft, but the design steps involved developing the full-order optimal control laws, requisite integrated design methods are only beginning to be reducing the order of the control law, and optimizing the developed. One integrated design method which has received reduced-order control law in both the continuous and the discrete attention is based on hierarchal problem decompositions, domains to minimize stochastic response. System robustness was optimization, and design sensitivity analyses. This paper highlights improved using singular value constraints. An 8th order robust a design sensitivity analysis method for Linear Quadratic Gaussian control law was designed to increase the symmetric flutter dynamic (LOG) optimal control laws, enabling the use of LQG techniques pressure by 100 percent. Preliminary results are provided and in the hierarchal design methodology. The LQG sensitivity analysis experiences gained are discussed. Author method calculates the change in the optimal control law and resulting controlled system responses due to changes in fixed N8%26011'# Boeing Commercial Airplane Co., Seattle, WA. design integration parameters using analytical sensitivity equations. DESCENT STRATEGY COMPARISONS FOR TNAV-EQUIPPED Numerical results of a LQG design sensitivity analysis for a realistic AIRCRAFT UNDER AIRPLANE-PREFERRED OPERATING aerosewoelastic aircraft example are presented. In this example, CONDITIONS Final Report the sensitivity of the optimal control law and aircraft response for K. H. IZUMl Washington Aug. 1989 41 p various parameters such as wing bending natural frequency is (Contract NAS1-18027) determined. The sensitivity results computed from the analytical (NASA-CR-4248; NAS 1.26:4248) Avail: NTlS HC A031MF A01 expressions are used to estimate changes in response resulting CSCL 0113 from changes in the parameters. Comparisons of the estimates Three 4-D descent strategies were evaluated which were with exact calculated responses show they are reasonably accurate employed by TNAV-equipped aircrafl in an advanced metering air for + or - 15 percent changes in the parameters. Evaluation of traffic control environment. The Flow Management Evaluation the analytical expressions is computationally faster than equivalent Model (FMEM) was used to assess performance using three criteria finite difference calculations. Author when traffic enters the simulation under preferred cruise operating conditions (altitude and speed): throughput, fuel usage, and conflict N89-26009'# National Aeronautics and Space Administration. probability. In comparison to an evaluation previously performed Lewis Research Center, Cleveland, OH. under NASA contract, the current analysis indicates that the optimal INTEGRATED FLIGHT/PROPULSION CONTROL SYSTEM descent strategy is preferred over the clean-idle and constant DESIGN BASED ON A CENTRALIZED APPROACH descent angle (CFPA) strategies when all three criteria are SANJAY GARG, DUANE L. MATTERN (Sverdrup Technology, Inc., considered. Author Cleveland, OH.), and RANDY E. BULLARD 1989 41 p Presented at the Guidance, Navigation and Control Conference, N89-26012# Virginia Polytechnic Inst. and State Univ., Blacksburg. Boston, MA, 14-16 Aug. 1989; sponsored by the AlAA Interdisciplinary Center for Applied Mathematics. (NASA-TM-102137; E-4860; NAS 1.1511 02137; AIAA-89-3520) STATE SPACE MODELS FOR AEROELASTIC AND Avail: NTlS HC A03/MF A01 CSCL 0113 VISCOELASTIC SYSTEMS Technical Report, 1 Jan. - 31 Dec. An integrated flight/propulsion control system design is 1988 presented for the piloted longitudinal landing task with a modern, T. L. HERDMAN 15 Feb. 1989 5 p statically unstable, fighter aircraft. A centralized compensator based (Contract AF-AFOSR-0074-88; AF PROJ. 2304) on the Linear Quadratic Gaussian/Loop Transfer Recovery (AD-A207092; AFOSR-89-0380TR) Avail: NTlS HC A021MF A01 methodology is first obtained to satisfy the feedback loop CSCL 0111 performance and robustness specificiations. This high-order Dynamic modeling of various aeroelastic control systems require centralized compensator is then partitioned into airframe and engine at some point in the derivation of the model an application of sub-controllers based on modal controllability1observability for the Soehngen's inversion formula for finite Hilbert transforms to obtain compensator modes. The order of the sub-controllers is then a desired representation for the solution of the airfoil equation. reduced using internally-balanced realization techniques and the Conditions on initial data to guarantee well-posedness of the sub-controllers are simplified by neglecting the insignificant resulting model equations must be matched with those needed to feedbacks. These sub-controllers have the advantage that they justify the validity of the inversion formula. It is shown that this can be implemented as separate controllers on the airframe and compatibility can be achieved by assuming that the circulation the engine while still retaining the important performance and history belongs to a weighted L2 space. The resulting state space stability characteristics of the full-order centralized compensator. formulation provides a suitable setting for control design for the Command prefilters are then designed for the closed-loop system aeroelastic system. GRA with the simplified sub-controllers to obtain the desired system response to airframe and engine command inputs, and the overall N89-26013'# Systems Technology, Inc., Hawthorne, CA. system performance evaluation results are presented. Author ADVANCED PILOTED AIRCRAFT FLIGHT CONTROL SYSTEM DESIGN METHODOLOGY. VOLUME 1: KNOWLEDGE BASE N89-26010'# National Aeronautics and Space Administration. Final Report Langley Research Center, Hampton, VA. DUANE T. MCRUER and THOMAS T. MYERS Oct. 1988 FLUlTER SUPPRESSION CONTROL LAW SYNTHESIS FOR 285 p THE ACTIVE FLEXIBLE WING MODEL (Contract NASl-17987) VIVEK MUKHOPADHYAY (Planning Research Corp., Hampton, (NASA-CR-181726-VOL-1; NAS 1.26:181726-VOL-1; VA.), BOYD PERRY, 111, and THOMAS E. NOLL May 1989 9 p STI-TR-1228-1) Avail: NTlS HC A131MF A01 CSCL 0113 Presented at the European Forum on Aeroelasticity and Structural The development of a comprehensive and electric methodology Dynamics, Aachen, Fed. Republic of Germany, 17-19 Apr. 1989 for conceptual and preliminary design of flight control systems is (NASA-TM-101584; NAS 1.1 5101584) Avail: NTlS HC AO21MF presented and illustrated. The methodology is focused on the A01 CSCL 0113 design stages starting with the layout of system requirements and
690 09 RESEARCH AND SUPPORT FACILITIES (AIR)
ending when some viable competing system architectures aircraft weighing more than 5669 kg to be established either by (feedback control structures) are defined. The approach is centered model testing or by analysis and extrapolation, in a way that gives on the human pilot and the aircraft as both the sources of, and due consideration to the effects of inlets, control surfaces, the keys to the solution of, many flight control problems. The projecting structures, and any other factor likely to affect the methodology relies heavily on computational procedures which are hydrodynamic characteristics of the aircraft. Airframe energy- highly interactive with the design engineer. To maximize absorption characteristics must also be considered. Helicopter effectiveness, these techniques, as selected and modified to be ditching-and-flotation characteristics are also expected to become used together in the methodology, form a cadre of computational increasingly important. O.C. tools specifically tailored for integrated flight control system preliminary design purposes. While theory and associated A89-45036 Computational means are an important aspect of the design FRENCH AEROSPACE RESEARCH IN THE INTERNATIONAL methodology, the lore, knowledge and experience elements, which CONTEXT [LA RECHERCHE AEROSPATIALE FRANCAISE guide and govern applications are critical features. This material DANS LE CONTEXTE INTERNATIONAL] is presented as summary tables, outlines, recipes, empirical data, JEAN CARPENTIER (ONERA, Chatillon-sous-Bagneux, France) lists, etc., which encapsulate a great deal of expert knowledge. L‘Aeronautique et I’Astronautique (ISSN 0001-9275), no. 136-137, Much of this is presented in topical knowledge summaries which 1989, p. 23-27. In French. are attached as Supplements. The composite of the supplements The French contribution to the fields of aerodynamics, solid and the main body elements constitutes a first cut at a a Mark 1 mechanics, advanced materials, aerodynamic structures, and Knowledge Base for manned-aircraft flight control. Author optoelectonics is reviewed. The multidisciplinary approach employed by ONERA is illustrated by the validation of A320 flow N89-26014’# Systems Technology, Inc., Hawthorne, CA. calculations via experimental tests performed in the S1 wind tunnel. ADVANCED PILOTED AIRCRAFT FLIGHT CONTROL SYSTEM In the field of propulsion research, numerical simulation results of DESIGN METHODOLOGY. VOLUME 2 THE FCX FLIGHT the unsteady viscous three-dimensional flow in a gas turbine engine CONTROL DESIGN EXPERT SYSTEM Final Report are validated using experimental data obtained by laser velocimetry THOMAS T. MYERS and DUANE T. MCRUER Oct. 1988 and CARS. Experimental acoustic and thermal data for Ariane 5 190 p are obtained using a reduced-scale model. R.R. (Contract NASl -17987) (NASA-CR-181726-VOL-2;NAS 1.26181 726-VOL-2; A89-45047 STI-TR-1228-1) Avail: NTlS HC AOS/MF A01 CSCL 0113 ECONOMIC ASPECTS OF SIMULATION IN AIR The development of a comprehensive and electric methodology TRANSPORTATION [ASPECTS ECONOMIQUES DE LA for conceptual and preliminary design of flight control systems is SIMULATION DANS LE DOMAINE DU TRANSPORT AERIEN] presented and illustrated. The methodology is focused on the JEAN PINET (Academie Nationale de I’Air et de I’Espace, Toulouse, design states starting with the layout of system requirements and France) L‘Aeronautique et I’Astronautique (ISSN 0001-9275), ending when some viable competing system architectures no. 136-137, 1989, p. 123-127. In French. (feedback control structures) are defined. The approach is centered Economic aspects of the application of flight simulators to flight on the human pilot and the aircraft as both the sources of, and training are considered. The flight hour/simulator hour cost price the keys to the solution of, many flight control problems. The ratio for the A300 is 10 and for the Concord is 15. The aircraft methodology relies heavily on computational procedures which are price/FFS phase II simulator price ratio is found to be 6 for A300, highly interactive with the design engineer. To maximize to be 5 for A310, to be 3 for the A320, and to be 1 for the effectiveness, these techniques, as selected and modified to be ATR42. It is noted that Airbus-type phase II simulators cost between used together in the methodology, form a cadre of computational 12 and 15 million dollars. The recent imposition of stricter safety tools specifically tailored for integrated flight control system standards (particularly for take-offs and landings) and the ability preliminary design purposes. The FCX expert system as presently of flight simulators to adequately simulate complicated situations developed is only a limited prototype capable of supporting basic (that can easily be repeated) have made it more economical to lateral-directional FCS design activities related to the design use fewer flight training hours and more simulator training hours. example used. FCX presently supports design of only one FCS R.R. architecture (yaw damper plus roll damper) and the rules are largely focused on Class IV (highly maneuverable) aircraft. Despite this A89-45130 limited scope, the major elements which appear necessary for CONCEPT FOR AN AIRCRAFT MULTI-COMPONENT THRUST application of knowledge-based software concepts to flight control MEASUREMENT FACILITY design were assembled and thus FCX represents a prototype which RONALD M. DAVINO and ALLAN W. F. STANLEY (USAF, Flight can be tested, critiqued and evolved in an ongoing process of Test Center, Edwards AFB, CA) IN: Society of Flight Test development. Author Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, 1988, p. 11-2.1 to 11-2.13. refs The configuration and capabilities of a multicomponent thrust measurement facility for full-scale tactical aircraft are presented. The thrust measurement capabilities along the axial, vertical, and RESEARCH AND SUPPORT FACILITIES (AIR) lateral axes are discussed, along with the required accuracies. The ground effect can be evaluated by varying the aircraft height Includes airports, hangars and runways; aircraft repair and overhaul in the test facility. Means of managing exhaust gas flows, and of facilities; wind tunnels; shock tube facilities; and engine test measuring the velocity, pressure, temperature, and acoustic fields blocks. of the test aircraft, are assessed. It is noted that the present facility will provide a decreased risk to the test vehicle and will decrease the number of required test hours. R.R. A89-43890 IN THE DRINK A89-45248. Vigyan Research Associates, Inc., Hampton, VA. IAN DORMER Flight International (ISSN 0015-3710). vol. 135, A HIGH SPEED DATA ACQUISITION SYSTEM FOR THE May 20, 1989, p. 87-90. ANALYSIS OF VELOCITY, DENSITY, AND TOTAL The increasing use of twin-engined airliners for over-water TEMPERATURE FLUCTUATIONS AT TRANSONIC SPEEDS operations has renewed interest in the scale model testing of STEVEN J. CLUKEY (Vigyan Research Associates, Inc., Hampton, their emergency water-landing, or ’ditching’ characteristics. The VA), GREGORY S. JONES (NASA, Langley Research Center, U.S. FAA and the U.K. CAA require the ditching ability of all Hampton, VA), and P. CALVIN STAINBACK (Compfere, Inc.,
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Hampton, VA) SAE, Aerospace Technology Conference and A89-46755# Exposition, Anaheim, CA, Oct. 3-6, 1988. 10 p. refs AN EXPERIMENTAL TECHNIQUE FOR THE MEASUREMENT (SAE PAPER 881451) OF MASS FLOW OF SCRAMJET INLETS TESTED IN The use of a high-speed Dynamic Data Acquisition System HYPERSONIC PULSE FACILITIES (DDAS) to measure simultaneously velocity, density, and total D. M. VAN WIE, G. P. CORPENING, L. A. MATTES, D. A. temperature fluctuations is described. The DDAS is used to CARPENTER (Johns Hopkins University, Laurel, MD), S. MOLDER automate the acquisition of hot-wire calibration data. The data (Ryerson Polytechnical Institute, Toronto, Canada) et al. AIAA. acquisition, data handling, and data reporting techiques used by ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, DDAS are described. Sample data are used to compare results Monterey, CA, July 10-13, 1989. 30 p. refs obtained with the DDAS with those obtained from the FM tape (AIAA PAPER 89-2331) and post-test digitization method. C.D. An experimental technique for the measurement of inlet mass flow in hypersonic pulse facilities has been investigated. The technique utilizes the rate of pressure rise in a plenum attached A89-45249' National Aeronautics and Space Administration. to the aft end of an inlet to infer the mass flow into the plenum. Langley Research Center, Hampton, VA. The technique has been investigated in two experiments. In the A NEW LOOK AT WIND TUNNEL FLOW QUALITY FOR first test, an inlet was simulated using the exhaust from a calibrated TRANSONIC FLOWS sonic nozzle, and pulse flow conditions were generated using a GREGORY S. JONES (NASA, Langley Research Center, Hampton, Ludwieg tube. In this test series, the feasibility of the technique VA) and P. CALVIN STAINBACK (Complere, Inc., Hampton, VA) was demonstrated. The accuracy of the technique was estimated SAE, Aerospace Technology Conference and Exposition, Anaheim, to be or 5 percent with the potential to increase the accuracy CA, Oct. 3-6, 1988. 22 p. refs + - to or 2 percent. In the second experiment, a Busemann inlet (SAE PAPER 881452) + - was tested in the RyersonAJniversity of Toronto Mach 8.3 gun The implementation of several transonic hot wire anemometry tunnel. The plenum filling technique operated as designed in this techniques for obtaining fluctuating data related to wind tunnel test series, although an estimate of the accuracy of the technique flow quality has been evaluated. An overview of the theoretical could not be obtained due to uncertainties in the tunnel operating considerations, calibration techniques, and related assumptions are conditions. Author discussed for the data presented from the LaRC 8' Transonic Pressure Tunnel. The impact of incorrect assumptions related to hot wire sensitivities are highlighted. Velocity, density, total A89-46849'# Virginia Univ., Charlottesville. temperature, and mass flow results from three-element, INITIAL SUPERSONIC COMBUSTION FACILITY two-element, and single-element probes are presented in rms and MEASUREMENTS spectral formats. Based on these comparisons, great caution should ROLAND H. KRAUSS, R. BRADFORD WHITEHURST, 111, JOHN be used when relying on flow quality information obtained utilizing D. ABITT, 111, CORlN SEGAL, and JAMES C. MCDANIEL (Virginia, hot wire techniques other than the three-element technique. University, Charlottesville) AIAA, ASME, SAE, and ASEE, Joint Author Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 6 p. refs (Contract NGT-50142; NAGl-795) A89-46258# (AIAA PAPER 89-2462) THE RESEARCH OF 2-D FLEXIBLE WALL SELF-CORRECTING A combustion test tunnel designed for continuous operation to WIND TUNNEL 2000 K was assembled. Flow quality of a Mach 2 nozzle for use PEICHU ZUO, JIAJU HE, HUAXING LI, and MEN XU (Northwestern with this tunnel was examined using an array of impact probes. Polytechnical University, Xian, People's Republic of China) Acta The performance of gas shields used to protect optical windows Aerodynamica Sinica (ISSN 0258-1825), vol. 7, no. 2, 1989, p. was examined using both shadowgraphs and planar laser induced 208-214. In Chinese, with abstract in English. refs iodine fluorescence. High speed videography was used to aid in The results of studies on a two-dimensional flexible wall design of pressure relief panels related to hydrogen combustion self-correcting wind tunnel are presented. The parameter choice testing safety. Author for this wind tunnel is discussed as well as the iterative test method. Recommendations are made with regard to areas of further research. K.K. A89-46905'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. NEW HYPERSONIC FACILITY CAPABILITY AT NASA LEWIS A89-46696# RESEARCH CENTER GUST GENERATION IN A WINDTUNNEL AND ESTIMATION JEFFREY HAAS, ROGER CHAMBERLIN, and JOHN H. DlCUS OF THE MODEL (NASA, Lewis Research Center, Cleveland, OH) HlROBUMl OHTA. TAKAFUMI MONJI. ATSUSHI FUJIMORI, and AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, ATSUSHI HAlTOkl Japan Society for Aeronautical and Space CA, July 10-13, 1989. 9 p. Previously announced in STAR as Sciences, Journal (ISSN 0021-4663), vol. 37, no. 424, 1989, p. N89-22617. refs 247-252. In Japanese, with abstract in English. (AIAA PAPER 89-2534) Three types of gust generators are tested in a wind-tunnel to Four facility activities are underway at NASA Lewis Research examine their characteristics. The generators which were Center to develop new hypersonic propulsion test capability. Two investigated are the flag method, turbulent-flow-glid method and of these efforts consist of upgrades to existing operational facilities. their combined method. The gust velocities generated by these The other two activities will reactivate facilities that have been in methods are measured using a hot wire anemometer of X type, a standby condition for over 15 years. These four activities are and the characteristics of the power spectra are examined for discussed and the new test facilities NASA Lewis will have in several parameters such as wind velocity, the size and thickness place to support evolving high speed research programs are of a flag. To estimate a gust model for controller designs, discrete described. Author models based on an ARMA process are first identified by the AIC method. A continuous model with a lower dimension is then derived by selecting the coefficients of a rational function. These selections A89-46908# are based on the quasi-Newton method which minimizes the square FREEJET TEST CAPABILITY FOR THE AEROPROPULSION sum of errors at some discrete frequencies. It is found that the SYSTEMS TEST FACILITY gust generators considered here can furnish one with a convenient D. A. DUESTERHAUS (USAF, Directorate of Propulsion Test, mean for wind-tunnel experiments. In particular, the estimated gust Arnold AFB, TN) and P. V. MAYWALD (Sverdrup Technology, model may be expected to provide a simple mathematical model Inc., Arnold AFB, TN) AIAA, ASME, SAE, and ASEE, Joint for designing controllers. Author Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 11
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p. refs Force Base (AFB), Selfridge Air Guard Base (AGE), and El Tor0 (AIAA PAPER 89-2537) Marine Corps Air Station (MCAS) was investigated. Considered The Arnold Engineering Development Center (AEDC) is installing were the airfield, terminal, access issues, and any previous studies into the Aeropropulsion Systems Test Facility (ASTF) a free-jet conducted by Federal, State, regional, or local authorities that test capability for ground determination in a simulated flight evaluated the short and long term importance of using these environment of turbine engine and aircraft inlet compatibility utilizing facilities to alleviate the shortage of civil airport and air space full-scale inlets and engines as test articles. The details of the capacity. Author design, installation, and projected testing capability are described for a 57-sq ft supersonic nozzle and a 77-sq ft subsonic nozzle. N89-25242’ National Aeronautics and Space Administration. Support systems for mechanically pitching and yawing the free-jet Marshall Space Flight Center, Huntsville, AL. nozzles are also reported, as well as the test cell hardware for WARM FOG DISSIPATION USING LARGE VOLUME WATER capturing the free-jet nozzle flow. The plans for demonstrating SPRAYS Patent the free-jet capability prior to its initial operational date are VERNON W. KELLER, inventor (to NASA) 1 Nov. 1988 10 p explained. Author Filed 23 Jul. 1984 Supersedes N84-32398 (22-22, p 3538) (NASA-CASE-MFS-25962-1; US-PATENT-4,781,326; A89-47020# US-PATENT-APPL-SN-633180; US-PATENT-CLASS-239-2.1; TURBINE AERODYNAMIC PERFORMANCE MEASUREMENTS US-PATENT-CLASS-239-14.1) Avail: US. Patent and Trademark IN SHORT DURATION FACILITIES Off ice CSCL 1412 G. R. GUENETTE, A. H. EPSTEIN, and E. IT0 (MIT, Cambridge, To accomplish the removal of warm fog about an area such MA) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, as an airport runway, a plurality of nozzles along a line adjacent 25th, Monterey, CA, July 10-13, 1989. 14 p. refs the area propelled water jets through the fog to heights of (Contract F33615-87-C-2729) approximately twenty-five meters. Each water jet breaks up forming (AIAA PAPER 89-2690) a water drop size distribution that falls through the fog overtaking, Short duration, blowdown-type turbomachinery test facilities colliding, and coalescing with individual fog droplets and thereby offer the potential for very low cost, high accuracy testing of axial removes the fog. A water retrieval system is used to collect the flow turbines and have been used extensively to generate heat water and return it to reservoirs for pumping it to the nozzles transfer data. This paper addresses the use of these facilities for once again. turbine aerodynamic performance testing for research and Official Gazette of the US. Patent and Trademark Office development in place of conventional rigs. Differences between the quasi-isothermal testing of short duration rigs and adiabatic N89-25243# Deutsche Forschungs- und Versuchsanstalt fuer testing in steady state rigs are explored and shown to be of the Luft- und Raumfahrt, Brunswick (Germany, F.R.). Hauptabteilung order of 1 percent in turbine adiabatic efficiency. Procedures for Windkanaele. minimizing this difference during testing and/or correcting for the PRESSURE MEASUREMENT TECHNIQUE OF WT-WK Status difference during post-test data analysis are discussed. The errors Report, 1988 associated with this correction are shown to be below those from RUEDIGER SIEBERT Sep. 1988 49 p In GERMAN; ENGLISH other sources in the turbine measurement processes. Accuracy summary Report will also be announced as translation requirements for pressure, temperature, torque, and heat transfer (ESA-TT-1145) instrumentation in short duration rigs are presented along with (DFVLR-MITT-88-11; ISSN-0176-7739;ESA-7-1145; examples of current practice. It is shown that no new ETN-89-94643) Avail: NTlS HC AO3/MF A01; DFVLR, instrumentation development is required for these facilities, so that VB-PL-DO, Postfach 90 60 58, 5000 Cologne, Federal Republic overall they represent little technical risk. Author of Germany, 19.50 deutsche marks Information for users of the wind tunnels of DFVLR (Deutsche N89-25240# National Aeronautical Lab., Bangalore (India). Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt) in Structures Div. Braunschweig, Gottingen, and Koln is presented. The principal ON THE STRESS PROBLEM OF THE PEBBLE BED HEAT arrangement, details, and status of the pressure measurement EXCHANGER IN A HYPERSONIC WIND TUNNEL technique are described. For quick information, the data of all M. N. BAPURAO and ASHOK KAMATH Jul. 1987 78 p available pressure transducers and pressure measurement systems (NAL-TM-ST-8705) Avail: NTlS HC AOWMF A01 are presented in tables. ESA The stress problem associated with the pebble bed heat exchanger in the hypersonic wind tunnel at IISc, Bongalore, is N89-26015# National Aerospace Lab., Tokyo (Japan). investigated. The investigation is carried out in two stages: the THE SCHLIEREN OBSERVATION SYSTEM INSTALLED IN THE first stage deals with the problem encountered during the NAL TWO-DIMENSIONAL HIGH-REYNOLDS NUMBER preheating of pebble bed, while in the second stage pressure TRANSONIC WIND TUNNEL AND ATTEMPTS TO IMPROVE IT loading arising from tunnel blowdowns is considered. The heat YASUO OGUNI, MAMORU SATO, HlROSHl KANDA, SElZO transfer and the associated thermal stress problems of stage one SAKAKIBARA, and HlTOSHl MlWA Mar. 1988 23 p and also the problem of pressure loading in the presence of (NAL-TR-964; ISSN-0389-4010) Avail: NTlS HC A03/MF A01 temperature occurring in stage two are analyzed using the finite For years attempts were made to improve the resolution of a element method with the aid of the NASTRAN and ASKA software colored Schlieren system used in the NAL2DHi-Re transonic wind packages. The results obtained indicate the presence of stress tunnel. Experience was gained as to the relative advantages concentration in the disc-flange region at the entry section and in between the two colored Schlieren systems: the prism method the ellipsoidal cap near the exit section of the pebble bed heat and the color-filter method. The change of color is continuous for exchanger. The significance of finite element results presented change of fluid density gradient with the former method while with the aid of the FEMVIEW interactive graphic processor is discontinuous with the latter. However, the latter method is less discussed in detail. Author susceptible to disturbances due to density fluctuations in the plenum chamber through which the rays travel before being N89-25241# Federal Aviation Administration, Washington, DC. recorded, and is more appropriate when displaying qualitative Office of Airport Planning and Programming. pictures of the flow field. Firstly an attempt was made to cope REPORT TO CONGRESS TECHNICAL FEASIBILITY OF JOINT with the plenum chamber noises by using a system with a cylindrical USE AT SCOTT AFB, SELFRIDGE AGB AND EL TOR0 MCAS channel to isolate the ray paths from the disturbing plenum LAURENCE KIERNAN May 1988 46 p environment. Secondly to get better resolution for quantifying (AD-A194597; APP-86-51; DOT/FAA/PP-88/5) Avail: NTlS HC density gradients, a filter with a fine array of colors was successfully AO3/MF A01 CSCL 01/51 tried; the array consists of 47 stripes, each containing seven colors The technical feasibility of joint civil/military use of Scott Air alternately from red to purple. The density gradients along the
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model surface were estimated from the Schlieren record, and were VA favorably compared with those obtained from the surface pressure (Contract DTFAOl-87-2-02015) distribution data. While it was observed that more improvement of (AD-A207159; WES/TR/GL-89-3; ESL-TR-88-52; the resolution is needed for accurate determination of the density DOT/FAA/DS-88/03) Avail: NTlS HC A15/MF A01 CSCL field, the results so far show the merit of further exploring the 14/2 procedure for deriving a density gradient field from two Schlieren This study evaluates seven nondestructive testing devices for records by using filters with the stripes of colors perpendicular to use on airfield pavements. Four falling weight deflectometers and each other. Author three vibrators weFe evaluated for accuracy, repeatability, and reliability. Deflection data were collected on 12 pavements N89-26018# Army Armament Research and Development consisting of thick and thin asphalt concrete, portland cement Command, Dover, NJ. Development and Engineering Center. concrete, and composite (asphalt concrete over portland cement AIRCRAFT JET ENGINE EXHAUST BLAST EFFECTS ON concrete) pavements over fine and coarse grain subgrades. This PAR-56 RUNWAY THRESHOLD LAMP FIXTURES Final Report report describes the test program, presents results of accuracy JACOB K. STRUCK and ANTHONY J. BARILE (Federal Aviation and repeatability tests, and presents the deflection data collected Administration, Atlantic City, NJ.) Jun. 1989 79 p on the 12 pavements. GRA (Contract DTFA03-84-A-40020) (DOT/FAA/CT-89/4) Avail: NTlS HC AO5/MF A01 The effects of jet engine exhaust blast on PAR-56 lamps located at the runway threshold were measured. Sensors were 10 placed on and near the lamp assemblies which measured blast velocity and temperature, bulb face temperature, lamp fixture ASTRONAUTICS acceleration and sound pressure level. These sensors were coupled to a computer controlled instrumentation system housed in a van Includes astronautics (general); astrodynamics; ground support located near the threshold of runway 13 at La Guardia Airport. systems and facilities (space); launch vehicles and space vehicles; Data were acquired during the engine runup and takeoff roll of space transportation; spacecraft communications, command and some 162 aircraft during the measurement phase. The data were tracking; spacecraft design, testing and performance; spacecraft recorded on digital magnetic tape and video tape to form a instrumentation; and spacecraft propulsion and power. permanent record of the raw data. The data were later plotted and analyzed, both manually and using a computer in order to extract the worst case environmental parameters encountered during the measurement phase. A prediction algorithm was A89-43869 THE 'NERVE CENTER' OF ESA TASKS AND PROCEDURES developed to allow prediction of key environmental effects on the - OF THE ESOC IN DARMSTADT [DAS 'NERVENZENTRUM' PAR-56 lamps caused by new aircraft or aircraft not measured. DER ESA AUFGABEN UND ARBEITSWEISEN DES ESOC IN The algorithm was developed by correlating the acquired data - DARMSTADT] against the manufacturers' published jet exhaust blast velocity and REIMAR LUEST (ESA, Paris, France) Astronautik (ISSN temperature contours. A protective shroud was devised and 0004-6221), vol. 26, Jan.-Mar. 1989, p. 5-7. In German. installed on one of the instrumented lamp assemblies during the The design and activities of the European Space Operations last portion of data collection. The data suggest a beneficial Center (ESOC) in Darmstadt (FRG) are reviewed. Topics addressed reduction of the hostile jet blast effects measured on the shrouded include the ESOC organizational structure, the role of the ESOC lamp versus the unshrouded lamp. Author in ESA operations, activities from launch preparation to the mission proper, the ESOC approach to space-flight control, telemetry and N89-260 19# Army Engineer Waterways Experiment Station, telecomrnand procedures, satellite monitoring, and man-machine Vicksburg, MS. Geotechnical Lab. interfaces. Diagrams and photographs are provided. T.K. DESIGN CRITERIA FOR AGGREGATE-SURFACED ROADS AND AIRFIELDS Final Report, 1986 - 1988 YU T. CHOU Apr. 1989 113 p A89-43892 (Contract DA PROJ. 4A1-62719-AT-40) CIVIL SATELLITE NAVIGATION AND LOCATION SYSTEMS (AD-A207059; WES/TR/GL-89-5) Avail: NTlS HC AO6/MF A01 W. F. BLANCHARD Journal of Navigation (ISSN 0373-4633). CSCL 0115 vol. 42, May 1989, p. 202-222. refs Failure criteria for aggregate-surfaced pavements subject to The use of satellites for civil navigation and location, including vehicular and aircraft loadings are developed. The criteria determine satellites not necessarily launched for that purpose, is reviewed. the required thickness making use of the layered elastic design In particular, attention is given to differences between civil and procedure. A literature study was conducted to determine existing military satellites; civil use of military systems and the associated design procedures that might be applicable. Types of distresses commercial considerations and regulatory issues; the use of in aggregate pavements were identified. Those basic parameters communication satellites; and radiodetermination satellite service that influence performance were defined. Efforts were made to based on geostationary satellites. The discussion also covers compare the existing design procedures using hypothetical design integration with ground-based radio-navigation systems; existing conditions. and the differences between the procedures were radio-navigation satellite systems; and the Starfix, Geostar/Locstar, discussed. The technique of reliability analysis was applied on the Starfind, Navsat, and Rexstar systems. V.L. design procedures. It was found that the reliabilities of some procedures were very low. Field tests on subgrade soils covered A89-46016# with high strength aggregates are recommended. The tests are THE ATR/RJ ENGINE PERFORMANCE AT CONSTANT necessary for the verification of developed failure criteria. GRA DYNAMIC PRESSURE AND THE CONSIDERATION OF TRANSITION CONDITION N89-26020# Army Engineer Waterways Experiment Station, SHAOQING WANG (The 31st Research Laboratory, People's Vicksburg, MS. Geotechnical Lab. Republic of China) and QlNG HUA (The 606th Research Institute, EVALUATION OF NONDESTRUCTIVE TEST EQUIPMENT FOR People's Republic of China) Journal of Propulsion Technology AIRFIELD PAVEMENTS. PHASE 1: CALIBRATION TEST (ISSN 1001-4055), June 1989, p. 20-24. In Chinese, with abstract RESULTS AND FIELD DATA COLLECTION Final Report, Feb. in English. 1986 - Jun. 1988 The ATR/RJ combined engine performance at constant
ROSS__~ A. BENTSEN.~~ ALBERT J. BUSH. 111. and J. A. HARRISON dynamic pressure is analyzed. Based on the data, the transition Jan. 1989 331 p Sponsored in part by Department of the Air condition is considered and calculated. Also, the static temperature, Force, Tyndall AFB, FL and Department of the Navy, Alexandria, static pressure in combustor, airflow rate, and thrust under the
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condition of various dynamic pressure are compared. All the through viscous flow losses as sound waves pass through the performance parameters presented in the paper are useful for the tortuous pore structure of the material. Exhaust gas noise design of the air-turborockethamjet combined engine. Author attenuation requirements are reviewed. Their selection process for higher performance materials is discussed. A new FELTMETAL A89-47005*# Oklahoma Univ., Norman. fiber metal acoustic material has been designed for use in gas INTEGRATION OF SCRAMJETS WITH WAVERIDER turbine auxiliary power unit exhaust environments without CONFIGURATIONS supplemental cooling. The physical and acoustic properties of mesh M. L. RASMUSSEN (Oklahoma, University, Norman) and C. E. supported fiber metal acoustic medium FM 827 are discussed. SOARES AIAA, ASME, SAE, and ASEE, Joint Propulsion Exposure testing was conducted under conditions which simulated Conference, 25th, Monterey, CA, July 10-13, 1989. 9 p. refs auxiliary power unit operation. Weight gain and tensile strength (Contract NAG1-886) data as a function of time of exposure at 650 C (1202 F) are (AIAA PAPER 89-2675) reported. Fabrication of components with fiber metal acoustic This paper presents a parametric study of a scramjet propulsion materials is easily accomplished using standard roll forming and system integrated into a waverider lifting-body configuration. The gas tungsten arc welding practices. Author analysis explores the effect of inlet geometry, internal cross-section-area distribution of the combustor section, the distribution of the heat release of the reacting mixture, the heat A8944577 transfer, and the friction on the performance of the propulsion A STUDY OF AL-LI ALLOYS USING SMALL ANGLE NEUTRON system. The Mach number, temperature, and pressure distributions SCAlTERlNG within the scramjet model are studied parametrically, and the effects B. C. PIKE, S. MESSOLORAS, and R. J. STEWART (Reading, on the thrust are obtained. The results provide insight on the University, England) Scripta Metallurgica (ISSN 0036-9748). vol. design concepts and problems that might arise for a given 23, June 1989, p. 983-988. Research supported by SERC. refs internal-flow configuration. Author The present study follows the growth of the delta-prime precipitates in AI-Li alloys as a function of aging time for bulk samples at various temperatures; attention is given to the results obtained with small-angle neutron scattering for the effects of small 11 additions of Cu or Zr on precipitation in samples of two binary alloy, a ternary Al-Li-Zr alloy, and two commercial alloys with CHEMISTRY AND MATERIALS different Cu contents. All the precipitate sizes determined for the different aging times and temperatures are parameterized on a single linear plot for all alloys studied. On the basis of the growth Includes chemistry and materials (general); composite materials; of the delta-prime precipitates, the energy of fusion and the inorganic and physical chemistry; metallic materials; nonmetallic interfacial tension are determined. O.C. materials; and propellants and fuels.
~89-45330 ~a9-44103# HOT DUCTILITY RESPONSE OF AL-MG AND AL-MG-LI DEVELOPMENT AND APPLICATION OF A SURROGATE ALLOYS DISTILLATE FUEL J. P. BALAGUER (Raytheon Co., Microwave Tube Div., Waltham, C. P. WOOD, V. G. MCDONELL, R. A. SMITH, and G. S. MA Rensselaer Polytechnic Institute, Troy, NY) and D. W. WALSH SAMUELSEN (California; University, Irvine) Journal of Propulsion (California State Polytechnic University, San Luis Obispo) Welding and Power (ISSN 0748-4658), vol. 5, July-Aug. 1989, p. 399-405. Journal, Research Supplement (ISSN 0043-2296), vol. 68, July refs 1989, p. 253-s to 261-s. Research supported by ASM (Contract FO8635-83-C-0052; N00014-83-C-9151) International. refs A surrogate fuel comprised of 14 pure hydrocarbons is The effect of Li addition on the heat-affected zone (HAZ) formulated based on the distillation curve and compound class hot-cracking susceptibility of aluminum alloys was investigated by composition of a petroleum-derived JP-4. The goal is to establish comparing the hot-ductility behavior of a commercial AI-4Mg alloy a fuel of controlled composition for modeling, and for the study of (alloy 5083) with that of an AI-4Mg-2Li alloy. Hot-ductility profiles fuel property and chemical composition effects in the combustion for the two alloys were developed for two thermal cycles designed of JP-4 fuels. Spatially resolved interferometric measurements of to simulate the weld HAZ. The results of on-heating and on-cooling droplet size and droplet velocity are obtained and compared for tests were compared on the basis of the strength ratio and the both the petroleum and surrogate JP-4 in a nonreacting spray ductility ratio between the two, as a function of homologous strain chamber. Measurements are also obtained for a high aromatic temperature. Also compared were the results of micrography and JP-5 of purposefully disparate properties. The performance of these SEM fractography of the two alloys tested on heating and on three fuels is then compared in a swirl-stabilized, spray-atomized cooling. It was found that the HAZ cracking susceptibility of model laboratory combustor where in-flame measurements of AI-4Mg-21i alloy was similar to that of AI-4Mg alloy. I.S. velocity and temperature are acquired and compared. The nonreacting measurements of atomization quality establish that the atomization characteristics of the petroleum and surrogate JP-4 A89-45554# are identical, whereas the atomization performance of the JP-5 is EFFECTS OF FUEL CHEMICAL PROPERTIES ON EXHAUST significantly different. Under reacting conditions, substantial SMOKE FROM GAS TURBINE COMBUSTOR differences between the JP-4 and JP-5 are observed in both the RUSHAN JIN (Beijing University of Aeronautics and Astronautics, velocity and thermal fields, whereas the surrogate, in contrast, People’s Republic of China) and A. H. LEFEBVRE (Purdue yields an identical velocity and thermal field to that of the petroleum University, West Lafayette, IN) Journal of Aerospace Power (ISSN JP-4. Author 1000-8055), vol. 4, April 1989, p. 121-126, 194. In Chinese, with abstract in English. refs ~89-44400 The state-of-the-art of the study on soot formation and exhaust FIBER METAL ACOUSTIC MATERIAL FOR GAS TURBINE smoke from gas turbine combustor has been reviewed with stress EXHAUST ENVIRONMENTS on the effects of fuel chemical properties. Based on a great amount MICHAEL S. BEATON (Brunswick Corp., Technetics Div., DeLand, of experimental data obtained on a variety of gas turbine FL) Journal of Materials Engineering (ISSN 0931-7058), vol. 11, combustors, the best correlation parameter representing the fuel June 1989, p. 149-157. refs effect has been determined as SP exp -0.92(100 - N) exp-0.4, FELTMETAL fiber metal acoustic materials function as broad where SP is smoke point, and N is the naphthalene content (in band acoustic absorbers. Their acoustic energy absorbance occurs percentage) of the fuel. Author
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A89-45927 SAMPE Metals and Metals Processing conference, Dayton, OH, SPACE AGE METALS TECHNOLOGY; PROCEEDINGS OF THE Aug. 2-4, 1988. Covina, CA, Society for the Advancement of SECOND INTERNATIONAL SAMPE METALS AND METALS Material and Process Engineering, 1988, p. 166-176. refs PROCESSING CONFERENCE, DAYTON, OH, AUG. 2-4, 1988 Proprietary AI-Li alloy development efforts aimed at aircraft F. H. FROES, ED. (USAF, Materials Laboratory, Wright-Patterson primary structure applications have led to the successful fabrication AFB, OH) and RAY A. CULL, ED. Conference sponsored by and testing of upper aft wing skins for an F-15 fighter. In the SAMPE. Covina, CA, Society for the Advancement of Material wake of such efforts, it has emerged that significant differences and Process Engineering (International SAMPE Metals and Metals exist in response to commonly employed forming and processing Processing Conference Series. Volume 2), 1988, 542 p. For operations between AI-Li alloys and conventional AI alloys. The individual items see A89-45928 to A89-45959. applicability of AI-Li alloys is enhanced by their superplastic The present conference discusses advancements in Ti alloy formability; they have also been found to be more corrosion-resistant casting methods, NiAl-based alloys for high temperature than conventional alloys. The segregation of AI-Li scrap from that of applications, electron-beam cold hearth melting of metals, AI-Li conventional alloys is, however, necessary prior to recycling. O.C. alloys for fighter aircraft applications, mechanically-alloyed high-modulus/elevated temperature AI-Ti alloys, the stress-induced hot corrosion of Rene 90, the high temperature oxidation behavior A89-45944 of Ti3AI alloys, and Ti requirements for current and future military TITANIUM REQUIREMENTS FOR CURRENT AND FUTURE gas turbine engines. Also discussed are the fatigue behavior of MILITARY GAS TURBINE ENGINES P/M Ti-6AI-4V, hydrogen in advanced aerospace materials, E. S. HURON and J. A. MILLER (United Technologies Corp., Pratt beryllides for very high temperature service, rapidly solidified P/M and Whitney Group, West Palm Beach, FL) IN: Space age metals Al-Fe-Ce alloys, advanced Mg alloys for aerospace applications, technology; Proceedings of the Second International SAMPE adaptive gas tungsten arc-welding, development trends in Metals and Metals Processing Conference, Dayton, OH, Aug. 2-4, electrodeposition, the fractography of titanium aluminide metal-matrix 1988. Covina, CA, Society for the Advancement of Material and composites, and ingot-metallurgy metal-matrix composites. O.C. Process Engineering, 1988, p. 271 -285. refs The substitution of titanium for nickel in gas turbine engine components would result in significant weight savings. Currently A89-45929 the use of titanium is limited by the possibility of catastrophic MICROSTRUCTURE-PROPERTY RELATIONSHIPS IN titanium fires and by elevated temperature properties, including ADVANCED NICKEL BASE SUPERALLOY AIRFOIL CASTINGS creep and damage tolerance. With careful design, the fire problem ALAN D. CETEL and DAVID N. DUHL (United Technologies Corp., can be controlled, but mechanical properties must be improved. Pratt and Whitney Group, Hartford, CT) IN: Space age metals In this paper, some of the key current and projected requirements technology; Proceedings of the Second International SAMPE for titanium are outlined, and compared with the results of recent Metals and Metals Processing Conference, Dayton, OH, Aug. 2-4, alloy developments and future alloy design philosophy. Author 1988. Covina. CA, Society for the Advancement of Material and Process Engineering, 1988, p. 37-48. refs A89-45948 The present assessment of the current understanding of A REVIEW OF BERYLLIDES FOR VERY HIGH TEMPERATURE microstructure-property relationships in both polycrystal Ii n e and SERVICE single-crystal superalloys gives attention to the behavior of J. M. MARDER and A. J. STONEHOUSE (Brush Welman, Inc., advanced, high-strength single-crystal turbine airfoil casting alloys Elmore, OH) IN: Space age metals technology; Proceedings of containing high volume fractions of the ordered intermetallic N13AI the Second International SAMPE Metals and Metals Processing gamma-prime phase. Heat treatment after casting can strongly Conference, Dayton, OH, Aug. 2-4, 1988. Covina, CA, Society for influence the size and distribution of the gamma-prime the Advancement of Material and Process Engineering, 1988, p. strengthening particles, which in turn affect creep and tensile 357-367. refs strength characteristics. Such secondary microstructural features With the renewed emphasis on very high operating temperatures as shrinkage porosity and carbides also significantly affect fatigue of aircraft and engine structural materials, the potential application life. O.C. of beryllide intermetallic compounds is undergoing serious evaluation. The beryllides, as a group, present a unique combination A8945931 of high temperature strength and low density, which may be CONTINUAL OPPORTUNITIES FOR SUPERALLOY translatable into significant improvements in high speed aircraft DEVELOPMENT performance. The objective of this paper is to review the current KEH-MINN CHANG (GE Corporate Research and Development state of beryllide technology. Binary intermetallic compounds of Center, Schenectady, NY) IN: Space age metals technology; beryllium are fabricated, under laboratory conditions, as powder Proceedings of the Second International SAMPE Metals and Metals metallurgy products. The typical fabrication processes used for Processing Conference, Dayton, OH, Aug. 2-4, 1988. Covina, CA, these materials are reviewed with an emphasis upon the Society for the Advancement of Material and Process Engineering, characteristics of the consolidated compounds, including density, 1988, p. 76-90. refs microstructure, high temperature strength and oxidation resistance. Two recent developments in the field of gas turbine superalloys, Directions for future development are suggested. Author a crack growth-resistant alloy and a weldable casting alloy, are judged to be indicative of remaining horizons for further superalloy A89-47149# advancements. The path to crack growth resistance for P/M COMBUSTION BEHAVIOR OF BORON-BASED BAMO/NMMO superalloys is heat-treatment above their precipitate solvus, to yield FUEL-RICH SOLID PROPELLANTS a large recrystallized grain structure. Based on the criterion of WEN-HSIN HSIEH, ARlE PERETZ, KENNETH K. KUO precipitation reaction, the novel weldable casting alloy Rene 220C (Pennsylvania State University, University Park), and I-TE HUANG has been demonstrated in gas turbine engine hardware trials to AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, offer an at least 50 C advantage in peak service temperature Monterey, CA, July 10-13, 1989. 10 p. refs over the 718 superalloy. O.C. (Contract NO0014-86-K-0468) (AIAA PAPER 89-2884) A89-45937 Combustion characteristics of boron/poly (BAMO/NMMO) ALUMINUM-LITHIUM ALLOYS FOR FIGHTER AIRCRAFT fuel-rich solid propellants have been studied due to their potential APPLICATIONS application to solid-fuel ramjets (SFRJ). For the same boron V. M. VASEY-GLANDON, E. A. WALKER-HECKMAN, and K. K. content, BAMO/NMMO copolymer-based fuels are superior to SANKARAN (McDonnell Aircraft Co., Saint Louis, MO) IN: Space conventional HTPB fuels due to their vigorous pyrolysis age metals technology; Proceedings of the Second International characteristic for dispersing boron particles into the main reaction
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zone. However, their specific impulses are generally lower than and High Temperature Measurements Conference, 5th, Costa that of HTPB, in spite of high positive heats of formation. Formation Mesa, CA, Mar. 22, 23, 1988, Proceedings. Bethel, CT, Society of hexagonal crystalline boron nitride (BN) has been found in the for Experimental Mechanics, Inc., 1988, p. 1-3. combustion of this family of propellants studied. Favorable The nature of high-temperature structural measurement conditions for the formation of BN have been identified. BN also requirements is discussed. While attention is focused on airframe has a significant effect on the theoretical performance for high structural applications, the discussion is valid for the propulsion equivalence ratio conditions. The burning rate was found to depend area as well. The requirements are outlined by considering the strongly upon pressure and nonmonotonically on boron content. following areas: large-scale structures, structural components, and An ’energy sink’ hypothesis is proposed to explain this observation. small specimens. K.K. Fine-wire thermocouple measurements support this hypothesis. Author A8943843 EMBEDDED TEMPERATURE MEASUREMENTS IN A A89-47213 CARBON-CARBON WING LEADING EDGE HOT STRUCTURE MECHANICAL PROPERTIES OF HIGH-TEMPERATURE F. J. SZAFRANSKI (General Dynamics Corp., Convair Div., San BERYLLIUM INTERMETALLIC COMPOUNDS Diego, CA) IN: Annual Hostile Environmentsand High Temperature R. L. FLEISCHER and R. J. ZABALA (GE Corporate Research Measurements Conference, 5th, Costa Mesa, CA, Mar. 22, 23, and Development Center, Schenectady, NY) Metallurgical 1988, Proceedings. Bethel, CT, Society for Experimental Transactions A - Physical Metallurgy and Materials Science (ISSN Mechanics, Inc., 1988, p. 12-26. refs 0360-2133), vol. 20A, July 1989, p. 1279-1282. refs Technology development efforts related to the measurement (Contract F33615-86-C-5055) of subsurface temperatures in a two-dimensional carbon-carbon For such high-temperature mechanical uses as high wing leading edge test sample are described. The feasibility of thrustlweight advanced gas turbine engine hot section using microminiature fine-wire temperature probes for making components, beryllium intermetallic compounds possess high subsurface in situ temperature measurements in a carbon-carbon elastic stiffness, low specific gravity, and relatively high melting hot structure is demonstrated. The detection of thermal gradients temperatures. Their strength and tendency toward brittleness has and the accurate measurement of in situ temperature in the been evaluated by conducting microhardness tests to 1150 or carbon-carbon test article along with the airfoil X (fore-aft) and Y 1300 C, examining the specimens’ indentations for cracks at each (lateral) axes is successfully demonstrated. K.K. temperature. Results are presented for the beryllium intermetallics Bel7Nb2, Bel2Ti, Bel3Zr, and highly anisotropic Bel2Nb; A8943844 performance comparisons are made with high-performance APPARENT STRAIN CHARACTERISTICS OF STRAIN GAUGES nonberyllium intermetallics. O.C. UNDER HIGH TEMPERATURE ENVIRONMENT H. AONO, T. CHIKATA, and R. SAT0 (Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan) IN: Annual Hostile N89-261 IIT Research Inst., Bartlesville, OK. National Inst. lo# Environments and High Temperature Measurements Conference, for Petroleum and Energy Research. 5th, Costa Mesa, CA, Mar. 22, 23, 1988, Proceedings. Bethel, CT, COMPARISONS BETWEEN UNLEADED AUTOMOBILE Society for Experimental Mechanics, Inc., 1988, p. 27-30. GASOLINE AND AVIATION GASOLINE ON VALVE SEAT Results of an experimental study on the behavior of a RECESSION IN LIGHT AIRCRAFT ENGINES Final Report high-temperature strain gage are used to develop a method for JERRY R. ALLSUP May 1989 19 p estimating the apparent strain with allowance for scatter. The (Contract DTFA03-88-A-00016) histogram of the apparent strain which was obtained exerimentally (NIPER-409; DOT/FAA/CT-TN89/33) Avail: NTlS HC AO3/MF for a titanium specimen at 100 C is presented. A scatter factor of A0 1 + or - 0.23 was suggested for use in the theoretical formula Testing was conducted to determine the potential for excessive proposed by Bapu Rao, et ai. K.K. valve seat recession in light aircraft engines using unleaded automobile gasoline (autogas) fuel. Two 10320 Lycoming engines were operated on a test stand for a 150 hr duration; one engine A8943876 used 1OOLL aviation gasoline (avgas) and the other used unleaded THE LINKS IN THE CHAIN - THE INMARSAT SYSTEM premium autogas. New original equipment manufacture (OEM) JOHN WILLIAMSON (International Maritime Satellite Organization, valve seats (hardness Rockwell HRB 40) were installed at the London, England) British Interplanetary Society, Journal (ISSN beginning of the test and recession was measured at 16 hr intervals. 0007-084X), vol. 42, June 1989, p. 267-276. The air-fuel mixture was precisely controlled by monitoring exhaust The components of the lnmarsat system are examined. The gas composition. Results show valve seat recession using unleaded locations and status of the various lnmarsat spacecraft are listed autogas fuel was not significantly different from lOOLL avgas. and the characteristics of the spacecraft are discussed. The Author Standard-A, Standard-C, land-mobile, and aeronautical terminals of the lnmarsat system and the functions of the coast earth stations, the network coordination stations for the different ocean regions, and the operation control center are described. In addition, consideration is given to the telex and telephony processes, and 12 the process of obtaining approval to operate a ship earth station. R.B. ENGINEERING ~a9-4463s Includes engineering (general); communications; electronics and RECENT DEVELOPMENTS IN CALCULATION METHODS FOR electrical engineering; fluid mechanics and heat transfer; TURBOMACHINES [ DEVELOPPEMENTS RECENTS DES instrumentation and photography; lasers and masers; mechanical METHODES DE CALCULS DANS LES TURBOMACHINESI engineering; quality assurance and reliability; and structural CH. HIRSCH (Brussel, Vrije Universiteit; Bruxelles, Universite Libre, mechanics. Brussels, Belgium) Revue Francaise de Mecanique (ISSN 0373-6601), no. 4, 1988, p. 5-10. In French. refs A quasi-three-dimensional approach to the modeling of ~89-43840 multistage turbomachines is presented which is based on the OPTICAL RESEARCH NEEDED TO SUPPORT THE TESTING superposition of two-dimensional flows. Recent developments in OF HYPERSONIC VEHICLE STRUCTURES these methods include a more precise and rigorous definition of GENE E. MADDUX (USAF, Wright Aeronautical Laboratories, the averaged parameters, the introduction of contributions due to Wright-Patterson AFB, OH) IN: Annual Hostile Environments the nonaxisymmetric and unsteady flow components, and the
697 12 ENGINEERING introduction of secondary flow effects (such as turbulent diffusion) the real picture are discussed. The present method is shown to on the radial mixing. Meridianal flow models which take into account be capable of performing such flight-test photo-evaluation tasks the coupling effects of the wall boundary layers are also as flight path determination, calibration of side-slip and angle of discussed. R.R. attack, and terrain following control. R.R.
A8944636 A8945142 PRESENT STATE OF THE THEORY OF SECONDARY FLOWS THE MEASUREMENT OF LINEAR AND ANGULAR AND EXPERIMENTAL VERIFICATIONS [ETAT ACTUEL DE LA DISPLACEMENTS IN PROTOTYPE AIRCRAFT - THEORIE DES ECOULEMENTS SECONDAIRES ET INSTRUMENTATION, CALIBRATION AND OPERATIONAL VERIFICATIONS EXPERIMENTALES] ACCURACY I. TREBINJAC, F. LEBOEUF, A. VOUILLARMET (Lyon, Ecole SAM STORM VAN LEEUWEN (Nationaal Lucht- en Centrale, Ecully, France), and G. BOIS (Metraflu, Ecully, France) Ruimtevaartlaboratorium, Amsterdam, Netherlands) IN: Society Revue Francaise de Mecanique (ISSN 0373-6601), no. 4, 1988, of Flight Test Engineers, Annual Symposium, 19th, Arlington, TX, p. 35-46. In French. refs Aug. 14-18, 1988, Proceedings, Lancaster, CA, Society of Flight Secondary flow theories based on coherent models of the Test Engineers, 1988, p. V-3.1 to V-3.10. refs averaged flow allow the three-dimensional effects encountered in The design and development of angular displacement industrial flows to be simulated. Secondary flow models for transducers for flight test instrumentation systems are considered. turbomachines include the effects of flow injection on the walls of Calibration tools, developed to meet the accuracy requirements, the motor hub and housing, along with the effects of static pressure allowed in situ calibration with short turn around times. The design on the mean flow. It is suggested that the pressure losses near of the control surface deflection measurement channels for the the walls, the three-dimensionaltransport of the secondary vorticity, Fokker 100 prototype aircraft is discussed in detail. It is and the clearance between the blade tip and the compressor demonstrated that a bellows coupling provides accurate results, housing are not adequately modeled using present techniques. and that the levers and push-pull rod drive mechanisms perform R.R. well. The results suggest that a complex mechanical drive mechanism reduces the system accuracy. R.R. A8444663 CRACK SHAPE IDENTIFICATION AS AN INVERSE A8945144 BOUNDARY VALUE PROBLEM [ RlSSFORMlDENTlFlKATlON RESEARCH AND APPLICATION OF A NEW KIND OF ALS INVERSES RANDWERTPROBLEM] MEASUREMENT TECHNOLOGY OF TAKE-OFF AND LANDING DIRK F. HARTMANN (Hannover, Universitaet, Hanover, Federal PERFORMANCE Republic of Germany) (Gesellschaft fuer angewandte Mathematik YANG CHUNBAO (Harbin Aircraft Factory, People's Republic of und Mechanik, Wissenschaftliche Jahrestagung, Vienna, Austria, China) IN: Society of Flight Test Engineers, Annual Symposium, Apr. 5-9, 1988) Zeitschrift fuer angewandte Mathematik und 19th, Arlington, TX, Aug. 14-18, 1988, Proceedings. Lancaster, Mechanik (ISSN 0044-2267), vol. 69, no. 4, 1989, p. T 166, T CA, Society of Flight Test Engineers, 1988. p. VI-2.1 to VI-2.5. 167. In German. A video-based take-off and landing performance measurement Rotor damage frequently involves transverse cracks in the shaft. system has been developed to aid in certification of the Y-12 This paper presents a nondestructive way to determine the shape aircraft. The system has high accuracy and is adaptable to of such cracks. The resulting predictions are shown to be in good computer analysis. Employing dual channel audio inputs, and the agreement with observation. C.D. video system is capable of coordinating such synchronous signals as RIG B time code and voice with flight data obtained using an A89-45136' airborne data acquisition system. Applications of the system include EXPERTVISION - A VIDEO-BASED NON-CONTACT SYSTEM searching for the best take-off and landing flight path, the FOR MOTION MEASUREMENT establishment of helicopter hovering capacity, and fly-over noise JAMES S. WALTON (Motion Analysis Corp.. Santa Rosa, CA) evaluation. R.R. IN: Society of Flight Test Engineers, Annual Symposium, 19th, Arlington, TX, Aug. 14-18, 1988, Proceedings, Lancaster, CA. Society of Flight Test Engineers, 1988, p. IV-1.1 to IV-1.6. Research A89-45177# supported by NASA. refs REINFORCING SOLUTIONS FOR A PANEL CUT-OUT A system known as Expertvision for obtaining noncontact R. VlSlNESCU (Institutul National pentru Creatie Stiintifica si kinematic measurements using standard video signals is described. Tehnica, Bucharest, Rumania) Revue Roumaine des Sciences In the system, a video processor extracts edge information from Techniques, Serie de Mecanique Appliquee (ISSN 0035-4074), vol. video images using a proprietary thresholding technique. Images 34. Jan.-Feb. 1989, p. 33-41. can be examined in real time at up to 200 fields/s, and as many Reinforcing solutions are presented for the cut-out of the skin as four synchronized inputs can be treated simultaneously by and two stringers in an aircraft structure such as a wing or fuselage. buffering the edge coordinates for each view in dedicated RAM It is assumed that the perturbation functions form a self-balanced memory. Mechanical applications for Expertvision include the study system of forces which will minimize the strain energy of an imposed of simple impacts, ballistics, wing flutter, the kinematics of helicopter area of structure. The Cauchy problem for the Euler-type differential rotor blades, and fluid and gas flow problems. R.R. equations system, representing the condition required to minimize the strain energy, is solved. R.B.
A8945137 A894188# LOW COST EQUIPMENT FOR FLIGHT TEST FILM AND VIDEO STUDY OF FLOW AND HEAT TRANSFER IN ROTATING EVALUATION CAVITIES V. M. STORCH and F. J. ENZINGER (Messerschmitt-Boelkow-Blohm J. GUIDEZ, M. IZARD, P. J. MICHARD, and J. PERRUCHlNl GmbH, Munich, Federal Republic of Germany) IN: Society of Flight (ONERA, Chatillon-sous-Bagneux, France) ONERA, TP no. Test Engineers,Annual Symposium, 19th, Arlington, TX, Aug. 14-18, 1989-33, 1989, 24 p. Research sponsored by DRET, SNECMA, 1988, Proceedings. Lancaster, CA, Society of Flight Test Engineers, and Turbomeca. refs 1988, p. IV-2.1 to IV-2.6. (ONERA, TP NO. 1989-33) A low-cost method for the precise measurement of lateral Two experimental rigs contructed at ONERA to study flow and movements of aircraft and missiles is discussed in which video heat transfer in rotating cavities are described. The MERCI test images are processed by a computer. In the method, the filmed rig is used to study the influence of rotation on the heat transfer object is compared with a computer simulated picture, and various coefficient inside a channel rotating in an orthogonal mode. The procedures for bringing the computed picture into coincidence with thermal analysis was performed with thermocouples located on
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the rotating channel and IR pyrometry at high spatial and temporal discussed in reviews and reports. Topics addressed include CFD resolutions. The CRETE test rig was used to study the flow between models in plasma dynamics, parallel computation for simulation two disks which represent the turbine disks. K.K. studies, CFD for hypersonic airbreathing aircraft, multigrid methods for the steady incompressible Navier-Stokes equations, upwind A89-45191# differencing techniques, TV stable schemes for shock-interacting INFRARED AND MILLIMETER WAVE ACQUISITION SYSTEM flows, Euler models of hypersonic vortex flows, parallel multilevel [STATION DE MESURES MlLLlMETRlQUE ET INFRAROUGE] adaptive methods, and vortex methods for slightly viscous B. VAIZAN (ONERA, Chatillon-sous-Bagneux, France) (Colloque three-dimensional flows. Consideration is given to the accuracy of International sur le Radar, Paris, France, Apr. 24-28, 1989) ONERA, node-based solutions on irregular meshes, multigrid calculations TP no. 1989-36, 1989, 5 p. In French. for cascades, a finite-volume-element method for planar cavity flow, (ONERA, TP NO. 1989-36) parallel heterogeneous mesh refinement for advection-diffusion equa- The purpose of this paper is, at first, to describe a system tions, the convergence of the spectral-viscosity mehtod for nonlinear devoted to signatures acquisition at 35 GHz and 94 GHz and in conservation laws, and numerical simulations of Taylor vortices in a two infrared bands around 3 and 10 microns, simultaneously. This spherical gap. T.K. system, installed aboard a helicopter in a side-looking position, collects data on clutters; producing maps of the observed areas. A89-45352' National Aeronautics and Space Administration. In the following, various application studies are mentioned: among Langley Research Center, Hampton, VA. them, a multispectral signatures analysis of various extended COMPUTATIONAL FLUID DYNAMICS - A PERSONAL VIEW targets which may be applied to navigation updating, and also M. Y. HUSSAINI (NASA, Langley Research Center; Institute for performance studies of dual-mode sensors using different kinds Computer Applications in Science and Engineering, Hampton, VA) of fusion techniques. Author IN: International Conference on Numerical Methods in Fluid Dynamics, llth, Williamsburg, VA, June 27-July 1, 1988, A89-45208 Proceedings. Berlin and New York, Springer-Verlag, 1989, p. ISOPARAMETRIC SHEAR SPRING ELEMENT APPLIED TO 3-12. refs CRACK PATCHING AND INSTABILITY This paper provides a personal view of computational fluid R. C. CHU and T. C. KO (Aeronautical Industry Development dynamics. The main theme is divided into two categories - one Center, Taichung, Republic of China) Theoretical and Applied dealing with algorithms and engineering applications and the other Fracture Mechanics (ISSN 0167-8442), vol. 11, May 1989, p. with scientific investigations. The former category may be termed 93-102. refs computational aerodynamics, with the objective of providing reliable The effect of an adhesive-bonded rectangular patch on the aerodynamic or engineering predictions. The latter category is stress and energy states of a center-cracked panel is investigated essentially basic research, where the algorithmic tools are used analytically, applying an FEM approach based on a novel to unravel and elucidate fluid-dynamic phenomena hard to obtain isoparametric shear-spring element. The formulation of the element in a laboratory. A critique of the numerical solution techniques for and the construction of the FEM model are explained, and both compressible and incompressible flows is included. The numerical results for aircraft-type panels reinforced with discussion on scientific investigations deals in particular with unidirectional BFRP laminate patches are presented in extensive transition and turbulence. Author tables and graphs. The distance I between the points of local and global maxima of the minimum strain-energy density function is A89-45453 identified as a critical parameter affecting panel stability; it is shown THE INSTABILITY AND ACOUSTIC WAVE MODES OF that, if the patch thickness is increased sufficiently to contain I SUPERSONIC MIXING LAYERS INSIDE A RECTANGULAR within the patch, failure can be kept localized. T.K. CHANNEL CHRISTOPHER K. W. TAM and FANG Q. HU (Florida State A89-45210 University, Tallahassee) Journal of Fluid Mechanics (ISSN FATIGUE FAILURE INITIATION ANALYSIS OF 0022-1120), vol. 203, June 1989, p. 51-76. refs WING/FUSELAGE BOLT ASSEMBLY (Contract N00014-87-J-1130) G. C. SIH and C. K. CHAO (Lehigh University, Bethlehem, PA) A thin unconfined two-dimensional shear layer in a rectangular Theoretical and Applied Fracture Mechanics (ISSN 0167-8442), channel is considered, and the coupling between the motion of vol. 11, May 1989, p. 109-120. refs the shear layer and the acoustic modes of the channel is shown This work is concerned with predicting the fatigue failure to produce new two-dimensional instability waves. An analysis of initiation of a wing/fuselage bolt assembly. Accounted for in the the normal modes of a supersonic shear layer inside a rectangular analysis are both the influence of energy dissipation and damage channel indicates that, in addition to the unstable waves, there accumulation as the structure is subjected to repeated cyclic are basically two other families of neutral acoustic waves. The loading. Results involving the location and number of cycles to new instabiity waves are the dominant instabilities of a confined initiate a fatigue crack of 0.01 inches are obtained. They agree mixing layer at high supersonic convective Mach numbers, and both qualitatively and quantitatively with the experimental findings. they are relevant to the study of the supersonic mixing and Also discussed is the influence of pretorque in the bolt, which combustion process inside a ramjet engine combustion chamber. tends to decrease the number of cycles to fatigue-crack initiation. R.R. Fatigue life may be extended by altering the load path so as to decrease the accumulation of energy near the site of failure A89-45535' National Aeronautics and Space Administration. initiation. Author Ames Research Center, Moffett Field, CA. THE SPATIALLY NON-UNIFORM CONVERGENCE OF THE A89-45351 National Aeronautics and Space Administration. NUMERICAL SOLUTIONS OF FLOWS Langley Research Center, Hampton, VA. ARGYRIS G. PANARAS (NASA, Ames Research Center. Moffett INTERNATIONAL CONFERENCE ON NUMERICAL METHODS Field, CA) Journal of Computational Physics (ISSN 0021-9991), IN FLUID DYNAMICS, llTH, WILLIAMSBURG, VA, JUNE vol. 82, June 1989, p. 429-453. Previously announced in STAR as 27-JULY 1, 1988, PROCEEDINGS N88-11429. refs D. L. DWOYER, ED., M. Y. HUSSAINI, ED., and R. G. VOIGT, The spatial distribution of the numerical disturbances that are ED. (NASA, Langley Research Center; Institute for Computer .generated during the numerical solution of a flow is examined. It Applications in Science and Engineering, Hampton, VA) is shown that the distribution of the disturbances is not uniform. Conference sponsored by NASA. Berlin and New York, In regions where the structure of a flow is simple, the magnitudes Springer-Verlag (Lecture Notes in Physics. Volume 323), 1989, of the generated disturbances is small and their decay is fast. 634 p. For individual items see A89-45352 to A89-45434. However, in complex flow regions, as in separation and vortical Recent advances in computational fluid dynamics (CFD) are areas, large magnitude disturbances appear and their decay may
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be very slow. The observed nonuniformity of the numerical A89-45570# disturbances makes possible the reduction of the calculation time EXPERIMENTAL INVESTIGATION OF AEROENGINE by application of what may be called the partial-grid calculation HIGH-SPEED ROLLER BEARING technique, in which a major part of the calculation procedure is YANGYUAN FENG. JlAXlNG SHAO, and MINGXUE ZHAN applied in selective subregions, where the velocity disturbances (Shenyang Aeroengine Research Institute, People’s Republic of are large, and not within the whole grid. This technique is expected China) Journal of Aerospace Power (ISSN 100043055), vol. 4, to prove beneficial in large-scale calculations such as the flow April 1989, p. 183, 184, 200. In Chinese, with abstract in English. about complete aircraft configurations at high angle of attack. Also, A research work for developing aircraft engine high-speed roller it has been shown that if the Navier-Stokes equations are written bearings with 2.5 x 10 to the 6th DN has been completed. At in a generalized coordinate system, then in regions in which the first, a front roller bearing of a turbine rotor on an existing engine grid is fine, such as near solid boundaries, the norms become was tested to expose its defects as its DN was increased. Then, infinitesimally small, because in these regions the Jacobian has a new bearing was designed to eliminate these defects, and very large values. Thus, the norms, unless they are unscaled by comparative tests have been carried out. The results show that the Jacobians, reflect only the changes that happen at the outer the new bearing can meet the requirements of the roller bearing boundaries of the computation domain, where the value of the working at 2.5 x 10 to the 6th DN, when its design parameter are Jacobian approaches unity, and not in the whole flow field. chosen reasonably. Author Author A89-45950 A89-45552# MACHINE VISION FOR CONTROL OF GAS TUNGSTEN ARC APPLICATION OF THE BOUNDARY ELEMENT METHOD TO WELDING UNSTEADY HEAT TRANSFER PROBLEMS ROBERT A. ANDERSON (GE Aircraft Engines, Cincinnati, OH) JlNG DING (Northwestern Institute of Architectural Engineering, IN: Space age metals technology; Proceedings of the Second People’s Republic of China) Journal of Aerospace Power (ISSN International SAMPE Metals and Metals Processing Conference, 1000-8055), vol. 4, April 1989, p. 110-114, 193. In Chinese, with Dayton, OH, Aug. 2-4, 1988. Covina, CA, Society for the abstract in English. Advancement of Material and Process Engineering, 1988, p. The boundary element method is applied to analyzing 393-406. refs temperature field transient distribution on aircraft engine turbine A gas tungsten arc welding robot system using machine vision blades. It is possible to calculate the thermal stresses and life control to weld aircraft engine components is described. The span of the blade and to check the blade strength according to equipment, capabilities, and operational theory of the system are the temperature field determined by this method. The temperature discussed. Both vision controlled robot motion for weld joint tracking distributions on a set of different sections in a turbine blade at and vision-based weld process control are used to overcome typical several instants have been calculated. Author production conditions such as nonrepeatable joint locations, joint width variations, and part thickness variations. This state of the A89-45561# art robotic system is currently being used to weld aircraft engine MEASUREMENT OF THREE-DIMENSIONAL FLOW IN hardware in a production environment. Improvements in productivity TURBOMACHINERY WITH A SINGLE SLANTED HOT-WIRE and quality have been realized. Author YUCHUN LI and HAOKANG JIANG (Beijing University of Aeronautics and Astronautics, People’s Republic of China) Journal A89-46218 of Aerospace Power (ISSN 1000-8055), vol. 4, April 1989, p. INERTIAL GUIDANCE TEST FACILITY USING THE EARTH 145-149, 195. In Chinese, with abstract in English. refs ENVIRONMENT An improvement to measuring three-dimensionalmean flow field ALLEN DEITCH (General Electric Co., Fairfield. CT) IN: Institute in turbomachinery with a single slanted hot-wire is presented. The of Environmental Sciences, Annual Technical Meeting, 34th, King method features high accuracy and broad angular measuring range. of Prussia, PA, May 3-5, 1988, Proceedings. Mount Prospect, IL, In order to obtain the three-dimensionalflow field, the single slanted Institute of Environmental Sciences, 1988, p. 188-192. wire is set in several positions around the probe axis. The data A facility for the calibration and simulated flight testing of high are sampled with the help of a high-speed data acquisition system accuracy inertial guidance systems is discussed. The facility is and the phase-locked ensemble averaging technique. Then, the located below ground in the interior of a six-story building and three-dimensional mean flow field is calculated by means of a utilizes the motion of the earth and precisely established geodetic data processing program previously developed. A periodic references. To establish a highly accurate North reference, a Polaris three-dimensional flow field at the exit of an axial-flow compressor sighting pier is placed outside of the facility so that Polaris is rotor is successfully measured. A proof calculation against the visible at a vertically angled line of sight into the below-grade test calibration data shows that the errors in velocity measurement area. The desired precision is obtained by applying a collimator are less than 1 percent of the mean velocity, and the errors in for the transfer of azimuth from a different elevation. The optical the flow direction are less than 1 degree. Author window, azimuth survey, alignment mirror, and theodolite are described. The total facility error, based on the root sum squared A89-45568# method is found to be 6 sec, which is satisfactory for a 10-arcsec STUDY OF NONLINEAR DUFFING CHARACTERISTICS OF test facility. R.B. FLEXIBLE ROTOR WITH SFDB GUANG MENG and ZHONGQING XUE (Northwestern A89-46221 Polytechnical University, Xian, People’s Republic of China) Journal MECHANICAL STRESSES DURING AIR TRANSPORT AND of Aerospace Power (ISSN 1000-8055), vol. 4, April 1989, p. GROUND OPERATIONS 173-178, 197. In Chinese, with abstract in English. refs THOMAS TROST (Swedish Packaging Research Institute, Nonlinear characteristics comparable with those of the one-DOF Sweden) IN: Institute of EnvironmentalSciences, Annual Technical Duffing equation are theoretically and numerically predicted for a Meeting, 34th King of Prussia, PA, May 3-5, 1988, Proceedings. flexible rotor-centralized squeeze-film damper bearing. It is Mount Prospect, IL, Institute of Environmental Sciences, 1988, p. established that the number of intersection points of the bone 21 3-217. refs curve with the amplitude-limit curve determine the nonlinear form Data on the mechanical hazards in the air transport environment of system response, and that the amplitude-timit curve is tangential were obtained with a unit load device on the main deck of a to the amplitude-frequencyresponse curve at the intersection point. Boeing 747 aircraft. Vertical, transverse, and longitudinal While the squeeze-film force will not change the rigid critical speed accelerations and vibrations during different flight modes and of the original system, it will deflect the amplitude-frequency ground operations were measured for a flight on the route response curve; this deflection has the characteristics of a hard Stockholm-Oslo-New York-Stockholm. The data are analyzed in spring. O.C. both time and frequency domains. Consideration is given to the
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application of the results for simulating vibration tests and for the A0946474 design and testing of products and packages to optimize securing A COROLLARY TO - DUANE‘S POSTULATE ON RELIABILITY equipment and improve loading routines. R.B. GROWTH DANIEL G. FRANK (Litton Industries, Guidance and Control A09-46202# Systems Div., Woodland Hills, CA) IN: Annual Reliability and THE SOLUTION OF 3-0 TEMPERATURE DISTRIBUTION IN A Maintainability Symposium, Atlanta, GA, Jan. 24-26, 1989, CYCLING OIL COOLED AIRCRAFT AC GENERATOR BY Proceedings. New York, Institute of Electrical and Electronics NETWORK TOPOLOGY METHOD Engineers, Inc., 1989, p. 167-170. XINFU ZHUANG and HOAZHI CHEN (Nanjing Aeronautical Results are presented of an investigation into reliability Institute, People’s Republic of China) Acta Aeronautica et characteristics demonstrated by selected avionic equipments over Astronautica Sinica (ISSN 1000-6893). vol. 10, March 1989, p. the major portion of their expected service life. It was found that A143-Al50. In Chinese, with abstract in English. refs avionics equipment items of various types demonstrate remarkably similar trends of a gradual decline in reliability during prolonged service. The data provide a basis for modification on Duane’s A09-46462 (1964) learning curve approach by extending its applicability to ADINTS - MOVING TOWARD STANDARDIZATION OF project a reliability profile over an equipment‘s planned service AUTOMATIC TEST EQUIPMENT life. The revised equations are then used to predict changes in LINDA M. SYLVESTRE (Kearfott Guidance and Navigation Corp., equipment reliability and availability, thus providing a capability to Little Falls, NJ) IN: Annual Reliability and Maintainability more accurately estimate life-cycle support resource requirements Symposium, Atlanta, GA, Jan. 24-26, 1989, Proceedings. New York, and costs. I.E. Institute of Electrical and Electronics Engineers, Inc., 1989, p. 82-85. In a move towards standardization of automatic test equipment A09-46470 (ATE), the US Air Force is enforcing utilization of modular ATE A PERFORMANCE MEASURE FOR A VHSIC AVIONIC (MATE) guides in the development of test systems for both current SYSTEM - MISSION DEPENDENT AVAILABILITY and future avionics programs. The author discusses the design SEUNG C. CHAY (Westinghouse Research and Development and production of thirteen automatic depot inertial navigation test Center, Pittsburgh, PA) and JOSEPH G. HENDERSON systems (ADINTS), using the MATE guides. ADINTS is designed (Westinghouse Electric Corp., Hunt Valley, MD) IN: Annual with accessible interfaces, large computer memory, reserved rack Reliability and Maintainability Symposium, Atlanta, GA, Jan. 24-26, space and test table flexibility, all of which make it adaptable to 1989, Proceedings. New York, Institute of Electrical and Electronics many kinds of units under test. Of particular importance in testing Engineers, Inc., 1989, p. 191-196. refs inertial products, a real-time-controlled interface is available. The A VHSlC (very-high-speed integrated circuit) avionic system is bus architecture complies with the MIL-STD-1553 A/B designed to carry out multiple missions, and the determination of requirements. When coupled with the benefits to a depot of whether the system is in the operable state or in the failed state standardization, commonality of spare parts, and shorter run times, depends on what particular mission the system is to perform at ADINTS has the potential to provide support to other military any given moment. Moreover, a VHSlC system contains an services and some commercial users of inertial products both in important feature, which allows extensive built-in-test capabilities this country and overseas, as well as the US Air Force. LE. with LRM (line replaceable module) modularity, which in turn gives a reconfiguration capability. For this type of system, the conventional reliability measures are not adequate. The authors A09-46460 introduce a performance and reliability measure, which they call MECHANICAL DURABILITY PREDICTION METHODS hission-dependent availability,’ to be used for a VHSlC type of RONALD G. LAMBERT (General Electric Co., Utica, NY) IN: system. The measure is used to determine the logistics Annual Reliability and Maintainability Symposium, Atlanta, GA, Jan. requirements and also to carry out tradeoff studies involving 24-26, 1989, Proceedings. New York, Institute of Electrical and redundancies, built-in-test capabilities, maintenance actions, and Electronics Engineers, Inc., 1989, p. 119-1 27. refs the extent of reconfiguration capability. LE. Simple closed-form analytical expressions are derived to accurately predict the durability (i.e., failure-free operating period or fatigue life) of avionic equipment structural elements as part of A09-46400 the US Air Force Avionics Integrity Program (AVIP) requirements. RIM THROUGH AVIONICS/ELECTRONICS INTEGRITY These expressions are functions of both the quantity of PROGRAM like-structural elements per assembly and quantity of identical WILBUR W. BHAGAT (USAF, Wright-Patterson AFB, OH) IN: assemblies per system for thermal cycling and random vibration Annual Reliability and Maintainability Symposium, Atlanta, GA, Jan. environments. Analytical predictions are compared with empirical 24-26, 1989, Proceedings. New York, Institute of Electrical and results for cantilever beams for solder joints on multilayer Electronics Engineers, Inc., 1989, p. 216-220. refs assemblies containing leadless chip carriers (LCCs). LE. The author addresses the importance of designing reliability and maintainability (R&M) into electronic equipment in the early A09-46472 stages of its development. He describes an approach called the A TOP-DOWN SFP ANALYSIS OF A COMPLEX SYSTEM Avionics/Electronics Integrity Program (AVIP), which emphasizes OWEN R. GREEN (Boeing Aerospace, Mountain View, CA) IN: early attention to design criteria and analysis, and dictates a Annual Reliability and Maintainability Symposium, Atlanta, GA, Jan. process which strikes a balance between analysis and test. He 24-26, 1989, Proceedings. New York, Institute of Electrical and outlines some of the problems and limitatons that have been Electronics Engineers, Inc., 1989, p. 154-156. observed using the traditional reliability approach (MIL-STD-785 The single-failure points (SFPs) in a system can be found by process) and discusses how the AVIP approach will overcome either bottom-up or top-down analysis, since each SFP must cause these problems and limitations. AVlP retains and incorporates the a significant system-level failure effect. For a large complex system, proven and useful elements of the traditional reliability approach, top-down analysis can be more efficient. The authors present, as such as failure modes; effects and criticality analysis (FMECA); an example, a high-pressure air heater and its pressure controller, failure reporting analysis and corrective action system (FRACAS); which are part of a hypersonic wind tunnel. The failure effect of and environmental stress screening (ESS). LE. concern is heater overpressurization. At least one failure in the pressure controller and one or more in the application safety A09-46403 features would be required for overpressure to occur. It is therefore A NONTRADITIONAL APPROACH TO RELIABILITY concluded that there are not SFPs for heater overpressurization WILSON D. YATES, 111 (McDonnell Aircraft Co., Saint Louis, MO) in this wind tunnel. LE. IN: Annual Reliability and Maintainability Symposium, Atlanta, GA,
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Jan. 24-26, 1989, Proceedings. New York, Institute of Electrical A89-46748# and Electronics Engineers, Inc., 1989, p. 239-241. A MODEL FOR AIRBLAST ATOMIZATION The author suggests tha 85 percent of the reliability factors N. K. RlZK and H. C. MONGIA (General Motors Corp., Allison that influence the customer's cost of ownership are established Gas Turbine Div., Indianapolis, IN) AIAA, ASME, SAE, and ASEE, prior to full-scale development; therefore, reliability needs to be Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. considered before that point. To that end, the author has prototyped 9 p. refs an expert system which recommends a prioritized list of design (AIAA PAPER 89-2321) alternatives to improve the reliability of the system under study. The objective of fuel injection modeling activities is generally When faced with a design problem, the designer can use the to give support to the atomizer design effort to achieve improved expert system to derive a thorough list of preassessed design spray quality. in gas turbine combustors, enhanced atomization is alternatives. LE. essential for satisfactory performance, since droplet sizes can have direct impact on almost all key aspects of combustion. A model A89-46493 that includes the integration of the submodels of air flow, fuel SPAREL - A MODEL FOR RELIABILITY AND SPARING IN THE injection and atomization, and droplets turbulent dispersion has WORLD OF REDUNDANCIES been formulated. The model was applied to an airblast atomizer ARNE NORDIN and FRITZ F. MAlER (Ericsson Radar Electronics, that incorporated a short prefilming device. The predictions were AB, Stockholm, Sweden) IN: Annual Reliability and Maintainability validated against two-component phase Doppler interferometry data Symposium, Atlanta, GA, Jan. 24-26, 1989, Proceedings. New York, of that atomizer. The results of the present investigation Institute of Electrical and Electronics Engineers, Inc., 1989, p. demonstrate the capability of the developed model to predict 313-320. refs satisfactorily the air flow field and spray characteristics. They A description is given of a state-of-the-artcomputerized model indicate the need for detailed measurements in the near field of which is developed to handle reliability and sparing problems for atomizer in order to quantitatively verify the modeling of the initial systems with complex redundancies. The model is used in the atomization processes in this region. Author daily work when doing different kinds of system reliability analysis. The main applications of SPAREL are discussed. A detailed model A89-46750# description including equipment and maintenance support modeling SPRAY PATTERNATION AT HIGH PRESSURE is given. The mathematical assumptions and the calculation J. M. COHEN and T. J. ROSFJORD (United Technologies Research methods are examined. Some program facilities are mentioned, Center, East Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint and some examples are presented for a fictitious sample case. Propulsion Conference, 25th, Monterey, CA, July 10-13, 1989. 9 SPAREL is a very useful tool since it considers availability, p. refs redundancies with complex structures and logistic support as an (Contract F33615-85-C-2515) entity. I.E. (AIAA PAPER 89-2323) The spatial distribution of the fuel spray created by a gas A89-46503' National Aeronautics and Space Administration. turbine fuel injector has been measured at high pressure and Langley Research Center, Hampton, VA. temperature. A patternation system for measuring fuel spray mass TESTING OF RELIABILITY - ANALYSIS TOOLS flux distributions at high power conditions has been designed and KELLY J. HAYHURST (NASA, Langley Research Center, Hampton, operated. The facility has been designed to simulate the VA) IN: Annual Reliability and Maintainability Symposium, Atlanta, environment inside a gas turbine combustor as closely as possible. GA, Jan. 24-26, 1989, Proceedings. New York, Institute of Electrical Results for a full scale gas turbine fuel injector have been obtained and Electronics Engineers, Inc., 1989, p. 487-490. refs at high levels of pressure, temperature and liquid flowrate and An outline is presented of issues raised in verifying the accuracy compared with visual observations. Author of reliability analysis tools. State-of-the-art reliability analysis tools implement various decomposition, aggregation, and estimation A89-46778# techniques to compute the reliability of a diversity of complex COMPUTATIONAL FLUID DYNAMICS USING CATIA CREATED fault-tolerant computer systems. However, no formal methodology GEOMETRY has been formulated for validating the reliability estimates produced JEANNE E. GENGLER (Boeing Commercial Airplanes, Seattle, by these tools. The author presents three states of testing that WA) AIM, ASME, SAE, and ASEE, Joint Propulsion Conference, can be performed on most reliability analysis tools to effectively 25th, Monterey, CA, July 10-13, 1989. 5 p. increase confidence in a tool. These testing stages were applied (AIAA PAPER 89-2368) to the SURE (semi-Markov Unreliability Range Evaluator) reliability A method has been developed to link the geometry definition analysis tool, and the results of the testing are discussed. LE. residing on a CAD/CAM system with a computational fluid dynamics (CFD) tool needed to evaluate aerodynamic designs and requiring A89-46697'# National Aeronautics and Space Administration. the memory capacity of a supercomputer. Requirements for Lewis Research Center, Cleveland, OH. surfaces suitable for CFD analysis are discussed. Techniques for CERAMIC BEARINGS FOR USE IN GAS TURBINE ENGINES developing surfaces and verifying their smoothness are compared, E. V. ZARETSKY (NASA, Lewis Research Center, Cleveland, OH) showing the capability of the CAD/CAM system. The utilization of ASME, Transactions, Journal of Engineering for Gas Turbines and a CAD/CAM system to create a computational mesh is explained, Power (ISSN 0022-0825), vol. 111, Jan. 1989, p. 146-154; and the mesh interaction with the geometry and input file Discussion, p.154. 155; Author's Closure, p. 156, 157. Previously preparation for the CFD analysis is discussed. C.D. announced in STAR as N88-18007. refs Three decades of research by US. industry and government A89-46841'# Textron Lycoming, Stratford, CT. laboratories have produced a vast body of data related to the THREE-DIMENSIONAL MULTIGRID NAVIER-STOKES use of ceramic rolling element bearings and bearing components COMPUTATIONS FOR TURBOMACHINERY APPLICATIONS for aircraft gas turbine engines. Materials such as alumina, silicon S. V. SUBRAMANIAN (Textron, Inc.. Textron Lycoming, Stratford, carbide, titanium carbide, silicon nitride, and a crystallized glass CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, ceramic have been investigated. Rolling-element endurance tests 25th, Monterey, CA, July 10-13, 1989. 10 p. Research supported and analysis of full-complement bearings have been performed. by the Textron Lycoming Independent Research and Development Materials and bearing design methods have continuously improved Program and NASA. refs over the years. This paper reviews a wide range of data and (AIAA PAPER 89-2453) analyses with emphasis on how early NASA contributions as well The fully three-dimensional, time-dependent compressible as more recent data can enable the engineer or metallurgist to Navier-Stokes equations in cylindrical coordinates are presently determine just where ceramic bearings are most applicable for used, in conjunction with the multistage Runge-Kutta numerical gas turbines. Author integration scheme for solution of the governing flow equations,
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to simulate complex flowfields within turbomechanical components Div., Rockford, IL) and JIM BIRDSALL (United Technologies Corp., whose pertinent effects encompass those of viscosity, Pratt and Whitney Group, West Palm Beach, FL) AIAA, ASME, compressibility, blade rotation, and tip clearance. Computed results SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, are presented for selected cascades, emphasizing the code's CA, July 10-13, 1989. 5 p. capabilities in the accurate prediction of such features as airfoil (AIAA PAPER 89-2587) loadings, exit flow angles, shocks, and secondary flows. The paper discusses the use of a single high speed centrifugal Computations for several test cases have been performed on a fuel pump as the only pump in a gas turbine engine fuel system. Cray-YMP, using nearly 90,000 grid points. O.C. The characteristics and requirements of the high speed centrifugal fuel pump system are compared with a more traditional fuel pump A89-46846# system. The application of composite technology to the high speed A CONCENTRATION PROBE FOR THE STUDY OF MIXING IN centrifugal pump concept is also reviewed. Author SUPERSONIC SHEAR FLOWS W. F. NG, F. T. KWOK, and T. A. NINNEMANN (Virginia Polytechnic A89-47025'# Toledo Univ., OH. Institute and State University, Blacksburg) AIAA, ASME, SAE, AEROELASTIC ANALYSIS OF PROP FAN BLADES WITH A and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July SEMIEMPIRICAL DYNAMIC STALL MODEL 10-13, 1989. 7 p. Research supported by Johns Hopkins University T. S. R. REDDY (Toledo, University, OH) and ORAL MEHMED and United Technologies Corp. refs (NASA, Lewis Research Center, Cleveland, OH) AIAA, ASME, (AIAA PAPER 89-2459) SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, An aspirating hot-film probe is developed to measure local CA, July 10-13, 1989. 20 p. refs mean gas composition in supersonic flows. The probe consists of (AIAA PAPER 89-2695) a constant temperature hot-film sensor operating in a channel The time-history response of a propfan wind-tunnel model with a choked exit. Thus, the flow over the hot film is influenced with dynamic stall was studied analytically. The response obtained only by total temperature, total pressure, and gas concentration. from the analysis was compared with available experimental data. The probe has a spatial resolution of 0.011 inches. It is easily The governing equations of motion were formulated in terms of calibrated and shows acceptable sensitivity to flow angularity. The blade normal modes calculated using the COSMIC-NASTRAN probe is applied in the study of a supersonic air/helium mixing computer code. The response analysis considered the blade layer in the VPI&SU 23 cm x 23 cm Supersonic Wind Tunnel. plunging and pitching motions. The lift, drag, and moment Data are presented in raw form and after reduction to concentration coefficients for angles of attack below the static stall angle were and mean flow quantities. Author obtained from a quasi-steady theory. For angles above static stall angles, a semiempirical dynamic stall model based on a correction A89-46858# to the angle of attack was used to obtain lift, drag, and moment ADVANTAGES OF CERAMIC, SOLID LUBRICATED BEARINGS coefficients. Using these coefficients, the aerodynamic forces were FOR SMALL GAS TURBINE ENGINES calculated at a selected number of strips, and integrated to obtain J. T. EXLEY and J. LAW (Teledyne CAE, Toledo, OH) AIAA, the total generalized forces. The combined momentum-blade ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, element theory was used to calculate the induced velocity. The Monterey, CA, July 10-13, 1989. 11 p. semiempirical stall model predicted a limit cycle oscillation near (AIAA PAPER 89-2472) the setting angle at which large vibratory stresses were observed The engine and system benefits development from solid in an experiment. The predicted mode and frequency of oscillation lubricated, ceramic bearings are numerous. These benefits include also agreed with those measured in the experiment near this setting simpler mechanical subsystems, enhanced survivability and mission angle. The results also correlated well with the other published completion probability, greater engine design/configurational data that used a semiempirical dynamic stall model based on a freedom, increased 'wooden round' storage capability, reduced synthesized procedure. Author weight, increased engine performance and reduced engine life cycle cost. Ceramic, solid lubricated bearings were demonstrated A89-47083# in various projects involving rig and engine testing for unmanned REVIEW OF PASSIVE SHEAR-FLOW CONTROL RESEARCH air vehicle applications. Bearing design features are discussed for FOR IMPROVED SUBSONIC AND SUPERSONIC COMBUSTION future engine benefits. Author K. C. SCHADOW and E. GUTMARK (US. Navy, Naval Weapons Center, China Lake, CA) AIAA, ASME, SAE, and ASEE, Joint A89-46928'# Virginia Univ., Charlottesville. Propulsion Conference, 25th. Monterey, CA. July 10-13. 1989. 17 QUANTITATIVE CHARACTERIZATIONOF A NONREACTING, p. refs SUPERSONIC COMBUSTOR FLOWFIELD USING UNIFIED, (AIAA PAPER 89-2786) LASER-INDUCED IODINE FLUORESCENCE Shear-flow investigations have been conducted in the high-Re, D. G. FLETCHER and J. C. MCDANIEL (Virginia, University, turbulent initial-condition combustion regime representative of flow Charlottesville) AIAA, ASME, SAE, and ASEE, Joint Propulsion configurations encountered in ramjets and in supersonic plumes. Conference, 25th. Monterey, CA, July 10-13, 1989. 34 p. refs Large-scale vortical structures were identified and characterized (Contract NAG1-373) in both nonreacting and combustion-reaction experimental (AIAA PAPER 89-2565) conditions; attention was given to these structures' role in mixing, A calibrated, nonintrusive optical technique, laser-induced iodine and their breakup into fine-scale turbulence. Shear-flow/combustion fluorescence (LIIF) was used to quantify the steady, compressible control was obtained by actively enlisting duct acoustics and flowfield of a nonreacting, supersonic combustor. The combustor passively employing noncircular flow cross-sections. The was configured with single and staged, transverse-air injection into investigations were extended to supersonic shear flows, yielding a supersonic-air freestream behind a rearward-facing step. improved mixing for supersonic combustion. O.C. Pressure, temperature, two-velocity components, and injectant mole fraction were measured with high spatial resolution in the A89-47104# three-dimensional flowfields. These experimental results provide a TECHNOLOGY DEVELOPMENT REQUIRED BY PROPFAN benchmark set of data for validation of computational fluid dynamic POWER REDUCTION GEARBOXES (CFD) codes being developed to model supersonic combustor L. BATTEZZATO and R. PlAS (Fiat Aviazione S.p.A., Turin, Italy) flowfields. Author AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th. Monterey, CA, July 10-13, 1989. 6 p. A89-46943# (AIAA PAPER 89-2818) LIGHT WEIGHT GAS TURBINE ENGINE FUEL PUMPING The design requirements for the propfan transmission are TECHNOLOGY discussed, with respect to the power-turbine and the fan speed JOHN M. KASSEL (Sundstrand Corp., Aerospace Fluid Systems ranges required for advanced aircraft, and the weight, reliability,
703 12 ENGINEERING maintenance, safety, and quietness aspects. Particular attention is Cleveland, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion given to the mechanical characteristics of the materials and the Conference, 25th, Monterey, CA, July 10-13, 1989. 9 p. Previously configuration of the planet gear and carrier and the ring gear. announced in STAR as N89-22925. refs The design of the oil system is also considered. I.S. (AIAA PAPER 89-2919) A method to estimate the frequency of transmission overhauls A89-47 163# is presented. This method is based on the two-parameter Weibull TIME DEPENDENT PROBABILISTIC FAILURE OF COATED statistical distribution for component life. A second method is COMPONENTS presented to estimate the number of replacement components BRICE N. CASSENTI (United Technologies Research Center, East needed to support the transmission overhaul pattern. The second Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion method is based on renewal theory. Confidence statistics are Conference, 25th, Monterey, CA, July 10-13, 1989. 11 p. refs applied with both methods to improve the statistical estimate of (AIAA PAPER 89-2900) sample behavior. A transmission example is also presented to A probabilistic time dependent failure model has been illustrate the use of the methods. Transmission overhaul frequency developed for the failure of materials. The model is an extension and component replacement calculations are included in the of a previously developed theory for static probabilistic failure that example. Author includes fatigue and creep rupture failure. The model has been applied to coatings and ceramic matrix composites. It has been A89-47181# shown to accurately predict the segment size in coatings and the BRAYTON CYCLE ENGINES WITH RECIPROCATING WORK statistical failure locations in brittle tensile specimens. Many of COMPONENTS the features of the model can be illustrated using one-dimensional R. DECHER (Washington. University, Seattle) AIAA, ASME, SAE, (Le., .through thickness) analyses of layered materials. Such and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July analyses have direct applications to coated components. The model 10-13, 1989. 8 p. refs has been incorporated in a computer program that processes output (AIAA PAPER 89-2933) from a finite element model, and hence allows the application in This paper is a description of a family of novel engine concepts structural analyses in any number of dimensions, with arbitrary which utilize displacement work components in the Brayton cycle. loading. Author The performance characteristics of these engines are described in detail in the cited references and summarized here. The A89-47168# implications of these characteristics on configuration possibilities OPTICAL FIBER SENSOR DEVELOPMENT FOR TURBINE are discussed. It is shown that low cost, steady flow engines with APPLICATIONS their high potential for low emissions are practical for small to JAMES R. DUNPHY and GERALD MELTZ (United Technologies medium power output. Author Research Center, East Hartford, CT) AIAA, ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey, CA, July 10-13, A89-47189'# Virginia Polytechnic Inst. and State Univ., 1989. 8 p. Blacksburg. (Contract F33615-80-C-2044; F33615-83-C-2330) IMPROVED PLASMA TORCH FOR IGNITION AND FLAME (AIAA PAPER 89-2914) HOLDING IN SUPERSONIC COMBUSTION A twin-core optical fiber sensor is being developed for W. F. OBRIEN, R. J. ROBY (Virginia Polytechnic Institute and application to turbine engine diagnostics. It promises advantages State University, Blacksburg), and S. D. STOUFFER AIAA, ASME, of small, nonintrusive dimensions, inherent immunity to EMI, high SAE, and ASEE, Joint Propulsion Conference, 25th, Monterey. temperature durability, and the capability to perform static strain CA, July 10-13, 1989. 12 p. Research supported by NASA. refs and temperature measurements simultaneously. This paper (AIAA PAPER 89-2945) summarizes the sensor concept, nonrotating risk reduction A plasma torch system designed for ignition and flame-holding experiments, and rotating demonstration tests. During these in supersonic combustion studies has been modified, in order to experiments, the optical fiber sensors were attached to modified decrease electrode wear and increase stability, through the FlOO turbine disks and operated in extreme conditions with incorporation of a flow swirler in the gas inlet that adds temperatures higher than 1200 F, strains approaching 3000 vortex-stabilization to the arc. The torch body was redesigned in microstrain, and spin rates greater than 7000 rpm. Author order to achieve superior alignment of the electrodes; the electrode gap was made continuously adjustable, thereby allowing fine tuning A89-47172# during torch operation. Table operation of the improved torch has THREE DIMENSIONAL FINITE ELEMENT STRESS been demonstrated in pure nitrogen, eliminating the requirement PREDICTIONS OF SPUR GEARS COMPARED TO GEAR of argon gas for arc stabilization. O.C. FATIGUE RIG MEASUREMENTS MARTIN OZKUL (Pratt and Whitney Canada, Mississauga) AIAA, A89-47250' National Aeronautics and Space Administration. ASME, SAE, and ASEE, Joint Propulsion Conference, 25th, Lewis Research Center, Cleveland, OH. Monterey. CA, July 10-13, 1989. 7 p. SELECTION OF ROLLING-ELEMENT BEARING STEELS FOR (AIAA PAPER 89-2918) LONG-LIFE APPLICATIONS A three dimensional finite element analysis technique has been ERWIN V. ZARETSKY (NASA, Lewis Research Center, Cleveland, developed for evaluating the gear tooth contact and fillet bending OH) IN: ASTM International Symposium on the Effect of Steel stresses. The method is based on an isoparametric formulation Manufacturing Processes on the Quality of Bearing Steels, Phoenix, using 20-noded solid elements and the sub-structure approach to AZ, Nov. 4-6, 1986, Proceedings. Philadelphia, PA, American minimize computer core usage. The analysis has been applied to Society for Testing and Materials, 1989, p. 5-43. Previously a test case of LCR spur gears specifically designed for pitting announced in STAR as N87-11993. refs endurance testing on a gear fatigue rig. The analysis results are Nearly four decades of research in bearing steel metallurgy compared with strain gauge results obtained from gear fatigue rig and processing have resulted in improvements in bearing life by a to determine allowables for gear tooth stressing. They are finally factor of 100 over that obtained in the early 1940s. For critical compared to the tooth stresses obtained using a gear teeth dynamic applications such as aircraft, these improvements have resulted model for further substantiation. Author in longer lived, more reliable commercial aircraft engines. Material factors such as hardness, retained austenite, grain size and carbide A89-47173'# Akron Univ., OH. size, number, and area can influence rolling-element fatigue life. TRANSMISSION OVERHAUL AND REPLACEMENT Bearing steel processing such as double vacuum melting can have PREDICTIONS USING WEIBULL AND RENEWAL THEORY a greater effect on bearing life than material chemistry. The M. SAVAGE (Akron, University, OH) and D. G. LEWlCKl (NASA, selection and specification of a bearing steel is dependent on the Lewis Research Center; U.S. Army, Propulsion Directorate, integration of all these considerations into the bearing design and
704 12 ENGINEERING application. The paper reviews rolling-element fatigue data and Langley Research Center, Recent Advances in Multidisciplinary analysis which can enable the engineer or metallurgist to select a Analysis and Optimization, Part 2 p 581-599 Apr. 1989 rolling-element bearing steel for critical applications where long Avail: NTlS HC A22/MF A01 CSCL 2011 1 life is required. Author Structural optimization has been available to the structural analysis community as a tool for many years. The popular use of N89-25164'# LTV Aerospace and Defense Co., Dallas, TX. displacement method finite-element techniques to analyze linearly Military Aircraft Div. elastic structures has resulted in an ability to calculate the weight THE DESIGNER OF THE 90's A LIVE DEMONSTRATION and constraint gradients inexpensively for numerical optimization TOMMY L. GREEN, BASIL M. JORDAN, JR., and TIMOTHY L. of structures. Here, recent experiences in the investigation and OGLESBY ln NASA. Langley Research Center, Recent Advances use of structural optimization are discussed. In particular, in Multidisciplinary Analysis and Optimization, Part 1 p 373-385 experience with the commercially available ADWNASOPT code is Apr. 1989 addressed. An overview of the ADWNASOPT procedure and how Avail: NTlS HC A23/MF A01 CSCL 13/2 it was implemented is given. Two example problems are also A survey of design tools to be used by the aircraft designer is discussed. Author given. Structural reliability, maintainability, cost and predictability, and acoustics expert systems are discussed, as well as scheduling, drawing, engineering systems, sizing functions, and standard parts and materials data bases. R.J.F. N89-25187*# Worcester Polytechnic Inst., MA. Dept. of Mechanical Engineering. TREATMENT OF BODY FORCES IN BOUNDARY ELEMENT N89-25166*# Lockheed Aeronautical Systems Co., Burbank, DESIGN SENSITIVITY ANALYSIS CA. SUNIL SAIGAL, JAMES H. KANE, R. AITHAL, and JlZU CHENG COMPOSITE SIZING AND PLY ORIENTATION FOR STIFFNESS ln NASA. Langley Research Center, Recent Advances in REQUIREMENTS USING A LARGE FINITE ELEMENT Multidisciplhary Analysis and Optimization, Part 2 p 759-776 Apr. STRUCTURAL MODEL 1989 N. A. RADOVCICH and D. P. GENTILE In NASA. Langley (Contract NSF MSM-87-0742) Research Center, Recent Advances in Multidisciplinary Analysis Avail: NTlS HC A22/MF A01 CSCL 20/11 and Optimization, Part 1 p 403-429 Apr. 1989 The inclusion of body forces has received a good deal of Avail: NTlS HC A23/MF A01 CSCL 2011 1 attention in boundary element research. The consideration of such A NASTRAN bulk dataset preprocessor was developed to forces is essential in the desgin of high performance components facilitate the integration of filamentary composite laminate such as fan and turbine disks in a gas turbine engine. Due to properties into composite structural resizing for stiff ness their critical performance requirements, optimal shapes are often requirements. The NASCOMP system generates delta stiffness desired for these components. The boundary element method and delta mass matrices for input to the flutter derivative program. (BEM) offers the possibility of being an efficient method for such The flutter baseline analysis, derivative calculations, and stiff ness iterative analysis as shape optimization. The implicit-differentiation and mass matrix updates are controlled by engineer defined of the boundary integral equations is performed to obtain the processes under an operating system called CBUS. A multi-layered sensitivity equations. The body forces are accounted for by either design variable grid system permits high fidelity resizing without the particular integrals for uniform body forces or by a surface excessive computer cost. The NASCOMP system uses ply layup integration for non-uniform body forces. The corresponding drawings for basic input. The aeroelastic resizing for stiffness sensitivity equations for both these cases are presented. The capability was used during an actual design exercise. Author validity of present formulations is established through a close agreement with exact analytical results. Author N89-25174'# Northrop Corp., Hawthorne, CA. Aircraft Div. ASTROS: A MULTIDISCIPLINARY AUTOMATED STRUCTURAL DESIGN TOOL D. J. NEILL In NASA. Langley Research Center, Recent Advances N89-25196*# Air Force Wright Aeronautical Labs., in Multidisciplinary Analysis and Optimization, Part 2 p 529-543 Wright-Patterson AFB, OH. Apr. 1989 AN APPROXIMATION FUNCTION FOR FREQUENCY Avail: NTlS HC A22/MF A01 CSCL 2011 1 CONSTRAINED STRUCTURAL OPTIMIZATION ASTROS (Automated Structural Optimization System) is a R. A. CANFIELD In NASA. Langley Research Center, Recent finite-element-based multidisciplinary structural optimization Advances in Multidisciplinary Analysis and Optimization, Part 2 p procedure developed under Air Force sponsorship to perform 937-953 Apr. 1989 automated preliminary structural design. The design task is the Avail: NTlS HC A22/MF A01 CSCL 20/11 determination of the structural sizes that provide an optimal The purpose is to examine a function for approximating natural structure while satisfying numerous constraints from many frequency constraints during structural optimization. The disciplines. In addition to its automated design features, ASTROS nonlinearity of frequencies has posed a barrier to constructing provides a general transient and frequency response capability, approximations for frequency constraints of high enough quality as well as a special feature to perform a transient analysis of a to facilitate efficient solutions. A new function to represent vehicle subjected to a nuclear blast. The motivation for the frequency constraints, called the Rayleigh Quotient Approximation development of a single multidisciplinary design tool is that such (RQA), is presented. Its ability to represent the actual frequency a tool can provide improved structural designs in less time than is constraint results in stable convergence with effectively no move currently needed. The role of such a tool is even more apparent limits. The objective of the optimization problem is to minimize as modern materials come into widespread use. Balancing structural weight subject to some minimum (or maximum) allowable conflicting requirements for the structure's strength and stiffness frequency and perhaps subject to other constraints such as stress, while exploiting the benefits of material anistropy is perhaps an displacement, and gage size, as well. A reason for constraining impossible task without assistance from an automated design tool. natural frequencies during design might be to avoid potential Finally, the use of a single tool can bring the design task into resonant frequencies due to machinery or actuators on the better focus among design team members, thereby improving their structure. Another reason might be to satisy requirements of an insight into the overall task. Author aircraft or spacecraft's control law. Whatever the structure supports may be sensitive to a frequency band that must be avoided. Any N89-25177*# General Dynamics Corp., Fort Worth, TX. of these situations or others may require the designer to insure RECENT EXPERIENCES USING FINITE-ELEMENT-BASED the satisfaction of frequency constraints. A further motivation for STRUCTURAL OPTIMIZATION considering accurate approximations of natural frequencies is that B. K. PAUL, J. C. MCCONNELL, and MIKE H. LOVE In NASA. they are fundamental to dynamic response constraints. Author
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N89-25 197*# Air Force Wright Aeronautical Labs., high temperatures. In this system there will be an unknown tradeoff Wright-PattersonAFB, OH. between frequency response, cost, and accuracy. The exact STRUCTURAL OPTIMIZATION OF FRAMED STRUCTURES tradeoff can only be estimated. It appears that for USING GENERALIZED OPTlMALlTY CRITERIA thermomechanical tests with cycle times on the order of minutes R. M. KOLONAY, VIPPERLA B. VENKAYYA, V. A. TISCHLER, a very reasonable system may be feasible. The intended and R. A. CANFIELD In NASA. Langley Research Center, Recent applications involve very high temperatures in both materials testing Advances in Multidisciplinary Analysis and Optimization, Part 2 p and monitoring component testing. Gas turbine engines, rocket 955-969 Apr. 1989 engines, and hypersonic vehicles (NASP) all involve measurement Avail: NTlS HC A22/MF A01 CSCL 20/11 needs that could partially be met by the proposed technology. The application of a generalized optimality criteria to framed Author structures is presented. The optimality conditions, Lagrangian multipliers, resizing algorithm, and scaling procedures are all N89-25443*# National Aeronautics and Space Administration. represented as a function of the objective and constraint functions Langley Research Center, Hampton, VA. along with their respective gradients. The optimization of two plane AUTOMATED THERMAL MAPPING TECHNIQUES USING frames under multiple loading conditions subject to stress, CHROMATIC IMAGE ANALYSIS displacement, generalized stiffness, and side constraints is GREGORY M. BUCK Apr. 1989 17 p presented. These results are compared to those found by optimizing (NASA-TM-101554; NAS 1.15101554) Avail: NTlS HC A03/MF the frames using a nonlinear mathematical programming A01 CSCL 14/2 technique. Author Thermal imaging techniques are introduced using a chromatic image analysis system and temperature sensitive coatings. These N89-25231'# Air Force Wright Aeronautical Labs., techniques are used for thermal mapping and surface heat transfer Wright-PattersonAFB, OH. measurements on aerothermodynamic test models in hypersonic RECENT DEVELOPMENTSIN LARGE-SCALE STRUCTURAL wind tunnels. Measurements are made on complex vehicle OPTIMIZATION configurations in a timely manner and at minimal expense. The VIPPERLA B. VENKAYYA In NASA. Langley Research Center, image analysis system uses separate wavelength filtered images Recent Advances in Multidisciplinary Analysis and Optimization, to analyze surface spectral intensity data. The system was initially Part 3 p 1521-1540 Apr. 1989 developed for quantitative surface temperature mapping using Avail: NTlS HC A22/MF A01 CSCL 2011 1 two-color thermographic phosphors but was found useful in A brief discussion is given of mathematical optimization and interpreting phase change paint and liquid crystal data as well. the motivation for the development of more recent numerical search Author procedures. A review of recent developments and issues in multidisciplinary optimization is also presented. These N89-25464'# Bently Rotor Dynamics Research Corp., Minden, developments are discussed in the context of the preliminary design NV. of aircraft structures. A capability description of programs FASTOP, INFLUENCE OF RUBBING ON ROTOR DYNAMICS, PART 2 TSO, STARS, LAGRANGE, ELFIN1 and ASTROS is included. Final Report Author AGNES MUSZYNSKA, DONALD E. BENTLY, WESLEY D. FRANKLIN, ROBERT D. HAYASHIDA, LORI M. KINGSLEY, and N89-25358# Deutsche Forschungs- und Versuchsanstalt fuer ARTHUR E. CURRY Mar. 1989 202 p Luft- und Raumfahrt, Stuttgart (Germany, F.R.). Structures and (Contract NAS8-36719) Materials Dept. (NASA-CR-183649-PT-2; NAS 1.26:183649-PT-2) Avail: NTlS MATERIALS AND STRUCTURES FOR 2000 AND BEYOND AN HC AlO/MF A01 CSCL 1319 AlTEMPTED FORECAST Rotor dynamic behavior depends considerably on how much CARL-JOCHEN WINTER and MARTIN MAILAENDER Feb. the specific physical phenomena accompanying rotor rubbing 1989 86 p In GERMAN; ENGLISH summary against the stator is involved. The experimental results of (DNLR-MIn-89-02; ISSN-01 76-7739; ETN-89-94648) Avail: rotor-to-stator rubbing contact are analyzed. The computer code NTlS HC A05/MFA01; DNLR, VB-PL-DO, Postfach 90 60 58, is described for obtaining numerical calculations of rotor-to-stator 5000 Cologne, Federal Republic of Germany, 51 deutsche marks rubbing system dynamic responses. Computer generated results Developments in aerospace materials and structures, and are provided. The reduced dynamic data from High Pressure Fuel research needed to meet the challenges imposed by these Turbo Pump (HPFTP) hot fire test are given. The results provide developments were discussed. ESA some significant conclusions. Information is provided on the electronic instrumentation used in the experimental testing. B.G. N89-25432'# Connecticut Univ., Storrs. Dept. of Mechanical Engineering and Physics. N89-25479'# National Aeronautics and Space Administration. X-RAY BASED EXTENSOMETRY Final Report, 15 Dec. 1987 - Ames Research Center, Moffett Field, CA. 15 Dec. 1988 FLAP-LAG STABILITY DATA FOR A SMALL-SCALE E. H. JORDAN and D. M. PEASE Dec. 1988 26 p ISOLATED HINGELESS ROTOR IN FORWARD FLIGHT (Contract NAG3-854) MICHAEL J. MCNULTY Apr. 1989 121 p (NASA-CR-185058; NAS 1.26:185058) Avail: NTlS HC A03/MF (NASA-TM-102189; A-89124; NAS 1.15:102189; A01 CSCL 1412 USAAVSCOM-TR-89-A-003) Avail: NTlS HC AO6/MF A01 A totally new method of extensometry using an X-ray beam CSCL 20/11 was proposed. The intent of the method is to provide a An isolated, hingeless rotor with discrete flap and lead-lag non-contacting technique that is immune to problems associated flexures and relatively rigid blades was tested in the with density variations in gaseous environments that plague optical Aeroflightdynamics Directorate's 7- by 10-Foot Wind Tunnel. The methods. X-rays are virtually unrefractable even by solids. The lead-lag stability of a structurally simple rotor configuration in new method utilizes X-ray induced X-ray fluorescence or X-ray fonvard flight was determined. The model tested had no cyclic induced optical fluorescence of targets that have melting pitch control, and was therefore operated untrimmed at several temperatures of over 3000 F. Many different variations of the collective pitch angles, at shaft angles from 0 deg to -20 deg, basic approaches are possible. In the year completed, preliminary and at advance ratios as high as 0.55. Two inplane natural experiments were completed which strongly suggest that the frequencies, 0.61 /rev and 0.72/rev, were tested for configuration method is feasible. The X-ray induced optical fluorescence method both with and without structural flap lag coupling. Concomitant appears to be limited to temperatures below roughly 1600 F hover testing of the model was also conducted. Representative because of the overwhelming thermal optical radiation. The X-ray plots of the frequency and damping data are presented to show induced X-ray fluorescence scheme appears feasible up to very general trends, and complete tabular data and model properties
706 12 ENGINEERING information are included for use in detailed correlation exercises. (ATC) ports of the Mode S sensor. A requirements document was The most prominent feature of the forward flight data is an abrupt necessary since there were no specifications given for the CID in increase in damping with advance ratio at certain high-speed, high the Mode S specifications. Note that this document lists the shaft-angle conditions, with high flapping loads. The hover data functional requirements for the CID and is not a detailed are consistent with previous experimental and theoretical results specification. Author for hingeless rotors without kinematic couplings. Overall, the data quality is very good and the data are expected to be useful in the N89-26123# Federal Aviation Administration, Atlantic City, NJ. development and validation of rotor aeroelastic stability analyses. Technical Center. Author COMMUNICATIONS INTERFACE DRIVER (CID) SYSTEM USER’S MANUAL N89-25480’# Boeing Helicopter Co., Philadelphia, PA. TOM BRATTON, CHARLES DUDAS, MARK SCHOENTHAL, JIM PLAN, FORMULATE, DISCUSS AND CORRELATE A NASTRAN DAVIS, ANDREW LEONE, and JEFFREY LIVINGS Jun. 1989 FINITE ELEMENT VIBRATIONS MODEL OF THE BOEING 71 P MODEL 360 HELICOPTER AIRFRAME (DOT/FAA/CT-TN89/36) Avail: NTlS HC A04/MF A01 R. GABEL, P. F. LANG, L. A. SMITH, and D. A. REED Apr. This user’s manual for the Communications Interface Driver 1989 296 p (CID) systems is used to describe the operating procedures of (Contract NAS1-17497) the CID. The CID system is a test tool intended to supply or (NASA-CR-181787; NAS 1.26:181787) Avail: NTlS HC A13/MF receive a capacity level of communications messages to and from A01 CSCL 2011 1 the air traffic control (ATC) and non-ATC ports of the Mode Select Boeing Helicopter, together with other United States helicopter (Mode S) sensor. The primary intent of the CID user’s manual is manufacturers, participated in a finite element applications program to guide the user through the operating procedures of the X.25 to emplace in the United States a superior capability to utilize communications diagnostic (COMMDIAG) and Time-of-Year (TOY) finite element analysis models in support of helicopter airframe diagnostic programs, the scenario generator and CID initialization design. The activities relating to planning and creating a finite (CIDINIT) data base off-line support programs, the CID real-time element vibrations model of the Boeing Model 36-0 composite program and the scenario list (SCLIST) and extraction list (EXLIST) airframe are summarized, along with the subsequent analytical data analysis programs. The manual also includes the procedures correlation with ground shake test data. Author to boot the CID system and to handle the required cabling and baud rate switch setup. Author N89-26120# Electroimpact, Inc., Seattle, WA. ELECTROMAGNETIC EMISSIONS FROM A MODULAR LOW VOLTAGE ELECTRO-IMPULSE DE-ICING SYSTEM Final N89-26127# Federal Aviation Administration, Atlantic City, NJ. Report Technical Center. PETER ZIEVE, BRENT HUFFER, and JAMES NG Mar. 1989 MODE S PERFORMANCE TEST PLAN CHARLES BAXTER Jul. 1989 67 p 44 P (DOT/FAA/CT-88/31) Avail: NTlS HC AO3/MF A01 (DOT/FAA/CT-TN89/24) Avail: NTlS HC A04/MF A01 An important consideration in the certification of electro-impulse The Mode S Performance Tests to be conducted by t he Federal deicing (EIDI) systems for aircraft ice protection is electromagnetic Aviation Administration Technical Center is described. The Mode interference (EMI). When the capacitor bank in an ElDl system S Performance Tests will provide a performance baseline and discharges, a large pulse of current travels down a transmission site:adaptation optimization effort for each Mode S configuration line to the coil. Subsequent radiation by the transmission line and (terminal, en route, and multi-sensor). System level accuracy and the coil produces EMI. The low voltage electro-impulse deicing resolution tests will be conducted using live test aircraft and system (LVEIDI) is unique in that the capacitor bank is mounted precision trackers. These tests have not been previously adjacent to the coil thereby eliminating most of the cables. accomplished due to the lack of multiple sensors and precision Electromagnetic emissions from this system would then be primarily trackers at the contractor’s facility. A stress test effort will also be from the coil. The performed tests investigate the EM1 environment conducted to characterize the performance of the Mode S sensor inside and outside of both a composite and an aluminum wing. beyond its specified requirements. This plan addresses the National Due to the absence of the shielding effect of aluminum, the problem Airspace System requirements and test objective as outlined in of electromagnetic emissions is particularly severe when the wing the Mode S Master Test Plan. This plan also identifies the is constructed of composite materials. Measurements of the organizational responsibilities, resources, coordination efforts, and radiated electric field indicate that emissions from the aluminum success criteria necessary to develop a set of test procedures to wing were well within the standards. Some tests with the composite accomplish the above tests. Author wing were within standards while others were not. It was found that the composite wing could be brought back into compliance N89-26133# Federal Aviation Administration, Atlantic City, NJ. through the addition of thin metallic shielding. Conducted emissions SATELLITE LOW RATE VOICE DEMONSTRATION TEST PLAN on the LVElDl power feed cable were brought within standards Test Plan Jan. 1988 - Mar. 1989 with the addition of a line filter. An unshielded connection cable JOAN GRELIS Dec. 1988 18 p for a compass flux valve was run through the wing just behind (AD-A206710; DOT/FAA/CT-TN88/39) Avail: NTlS HC A03/MF the LVElDl module. Discharge of the capacitor bank had no A01 CSCL25/4 discernible effect on operation of the compass flux valve. No This test plan describes the design of the demonstration of a problems were observed in other tests of the wing internal low data rate voice Codec communications link via satellite. The environment. Author demonstration will include the use of 4.8 kbps voice Codec equipment interfaced with a mobile satellite (MSAT) N89-26121# Federal Aviation Administration, Atlantic City, NJ. communications terminal installed in the Federal Aviation FUNCTIONAL REQUIREMENTS OF THE COMMUNICATIONS Administration’s (FAA’s) B- 727 (N-40) aircraft and similar INTERFACE DRIVER (CID) equipment at the COMSAT ground earth station in Southbury, JEFFREY LIVINGS, JAMES DAVIS, CHARLES DUDAS, and MARK Connecticut. This configuration, used in conjunction with SCHOENTHAL Jun. 1989 23 p INMARSAT satellite capability, completes an aircraft-to- (Contract T-1007-A) satellite-to-ground facility circuit that provides a communi- (DOT/FAA/CT-TN87/41-REV) Avail: NTlS HC A03/MF A01 cations quality voice link between the pilot and the ground. The functional requirements that the Communications Interface In addition to a demonstration, techniques will be developed for Driver (CID) was built to and tested against are listed. The CID is evaluating voice Codecs for air traffic control (ATC) applications. a test tool whose purpose is to supply and receive a capacity Controllers from the FAA will be used in the evaluation. A Codec level of communications messages to and from the air traffic control Test Bed Facility will be developed to conduct stress testing in a
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laboratory controlled environment. This project will allow critical an important role in the desigdanalysis of specific configurations evaluation of digital voice satellite communications technology in within this complex machine. In order to do this, a plan is being a simulated ATC environment. GRA developed to ensure the timely impact of CFD on IHPTET. The developing philosphy of CFD in the context of IHPTET is discussed. N89-26168# National Aerospace Lab., Tokyo (Japan). The key elements in the developing plan and specific examples MECHANISMS OF ENDWALL LEAKAGE FLOWS AND THE of state-of-the-art CFD efforts which are IHPTET turbine engine ASSOCIATED LOSSES IN A LINEAR TURBINE ROTOR relevant are discussed. Author CASCADE WITH BLADE TIPGLEARANCE ATSUMASA YAMAMOTO and KATSUYOSHI KABA Jun. 1988 N89-26176'# High Technology Corp., Hampton, VA. 23 P HOMAR: A COMPUTER CODE FOR GENERATING (NAL-TR-985T; ISSN-0389-4010) Avail: NTlS HC AO3/MF A01 HOMOTOPIC GRIDS USING ALGEBRAIC RELATIONS: USER'S The mechanisms of three-dimensional flows and of the MANUAL associated losses occurring in the tip endwall region of a linear ANUTOSH MOITRA Washington NASA Jul. 1989 79 p turbine cascade with tip-clearance are discussed. The clearance (Contract NASI -18240) gap sizes and the cascade incidences were chosen as the most (NASA-CR-4243; NAS 1.26:4243) Avail: NTlS HC AO5/MF A01 important variables affecting the mechanisms. Flows close to the CSCL 20/4 endwall and inside the clearance were surveyed in great detail A computer code for fast automatic generation of using a micro five-hole Pitot tube of 0.6 mm head size. The results quasi-three-dimensionalgrid systems for aerospace configurations gave very detailed information on the mechanisms, such as leakage is described. The code employs a homotopic method to flow vectors and pressure distributions throughout the clearance. algebraically generate two-dimensional grids in cross-sectional Interaction of leakage flow with the endwall flow and their planes, which are stacked to produce a three-dimensional grid associated separation lines, effects of gap size and inlet flow system. Implementation of the algebraic equivalents of the angle on loss generation, and skewness of the three-dimensional homotopic relations for generating body geometries and grids are endwall flows are also discussed. Author explained. Procedures for controlling grid orthogonality and distortion are described. Test cases with description and N89-26172'# Cornell Univ., Ithaca, NY. School of Mechanical specification of inputs are presented in detail. The FORTRAN and Aerospace Engineering. computer program and notes on implementation and use are MULTIGRID CALCULATION OF THREE-DIMENSIONAL included. Author TURBOMACHINERY FLOWS Final Report, 1 Sep. 1985 - 30 Jan. 1989 N89-26196# Manchester Univ. (England). Dept. of Engineering. DAVID A. CAUGHEY Jun. 1989 28 p Sponsored by NSF; A PRELIMINARY INVESTIGATION INTO EULER METHODS IBM and Corporate Research Inst. FOR APPLICATION TO MULTI-ELEMENT AEROFOILS FOR (Contract NAG3-645) HIGH LIFT Ph.D. Thesis (NASA-CR-I85332; NAS 1.261 85332; FDA-89-07) Avail: NTlS MICHAEL L. BARBER Nov. 1987 116 p HC AO3/MF A01 CSCL 2014 (AERO-REPT-8710; ETN-89-94950) Avail: NTlS HC AO6/MF Research was performed in the general area of computational A0 1 aerodynamics, with particular emphasis on the development of The full potential equation is solved for flow past a circular efficient techniques for the solution of the Euler and Navier-Stokes cylinder and the results obtained are compared with the benchmark equations for transonic flows through the complex blade passages solution of Rayleigh and Janzen. Euler's equations of motion are associated with turbomachines. In particular, multigrid methods derived in a Cartesian coordinate system. A general form of the were developed, using both explicit and implicit time-stepping equations for orthogonal curvilinear coordinate systems is also schemes as smoothing algorithms. The specific accomplishments given. The equations in Cartesian coordinates are discretized. The of the research have included: (1) the development of an explicit main methods are those or Lax, MacCormack, and Hall. The first multigrid method to solve the Euler equations for three-dimensional order finite difference technique and first and second order turbomachinery flows based upon the multigrid implementation of cell-vertex integral method are applied to the problem of a 10 Jameson's explicit Runge-Kutta scheme (Jameson 1983); (2) the percent symmetric thin airfoil in subsonic freestream. The results development of an implicit multigrid scheme for the are compared to those or the linearized model. A flow solution three-dimensional Euler equations based upon lower-upper over a circular cylinder is treated. The Euler equations are factorization; (3) the development of a multigrid scheme using a developed in inverted cylindrical polar coordinates. The inverse diagonalized alternating direction implicit (ADI) algorithm; (4) the conformal mapping is used to map the exterior region of the circle extension of the diagonalized AD1 multigrid method to solve the onto the internal region. A subsonic freestream flow is considered Euler equations of inviscid flow for three-dimensional for a leading quarter of the circle using the second order finite turbomachinery flows; and also (5)the extension of the diagonalized difference technique and the second order cell-vertex method. AD1 multigrid scheme to solve the Reynolds-averaged Results are compared with those obtained using the full-potential Navier-Stokes equations for two-dimensional turbomachinery model. For a half-circle, results for a slightly supercritical freestream flows. K.C.D. are given. ESA
N89-26174'# National Aeronautics and Space Administration. N89-26207'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. Ames Research Center, Moffett Field, CA. CFD IN THE CONTEXT OF IHPTET: THE INTEGRATED HIGH A LONG-RANGE LASER VELOCIMETER FOR THE NATIONAL PERFORMANCE TURBINE TECHNOLOGY PROGRAM FULL-SCALE AERODYNAMICS COMPLEX: NEW ROBERT J. SIMONEAU and DALE A. HUDSON (Air Force Wright DEVELOPMENTS AND EXPERIMENTAL APPLICATION Research and Development Center, Wright-Patterson AFB, OH.) MICHAEL S. REINATH Jun. 1989 44 p Presented at the 1989 17 p Presented at the 25th Joint Propulsion Conference, 13th International Congress on Instrumentation in Aerospace Monterey, CA, 10-12 Jul. 1989; cosponsored by the AIAA, ASME, Facilities, Gottingen, Fed. Republic of Germany, 18-21 SeD. 1989 SAE, and ASEE (NASA-TM-101081; A-89070;-NAS 1.15101 08i) Avail: NTlS HC (NASA-TM-102132; E-4868; NAS 1.15:102132; AIAA-89-2904) A03/MF A01 CSCL 14/2 Avail: NTlS HC AO3/MF A01 CSCL 2014 A long-range laser velocimeter (LV) developed for remote The Integrated High Performance Turbine Engine Technology operation from within the flow fields of the large wind tunnels of (IHPTET) Program is an integrated DOD/NASA technology program the National Full-Scale Aerodynamics Complex is described. designed to double the performance capability of today's most Emphasis is placed on recent improvements in optical hardware advanced military turbine engines as we enter the twenty-first as well as recent additions to data acquisition and processing century. Computational Fluid Dynamics (CFD) is expected to play techniques. The system has been upgraded from a dual-beam,
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single-color LV with focal range to 10 m, to a dual-beam, two-color (AD-A207090; AFWAL-TR-88-3101) Avail: NTlS HC A1 9/MF LV with focal range to 20 m. At the new extended measurement A01 CSCL 1215 range (between 10 and 20 m), signals are photon-resolved, and a The ASTROS (Automated Structural Optimization System) photon correlation technique is applied to acquire and process procedure provides multidisciplinary analysis and design capability the LV signals. This technique permits recovery of the velocity for aerospace structures. The engineering analysis capabilities in probability distributions at a particular measurement location from the system include structural analysis (static and dynamic), which the mean components of velocity and the corresponding aeroelastic analysis (static and dynamic) and automated design. normal stress components of turbulence are obtained. The method A specifically designed data base and executive system were used for data reduction is outlined in detail, and a discussion of implemented to maximize the system's efficiency, flexibility, and measurement accuracy is made. To study the performance of the maintainability. The charts used in the ASTROS User Training LV and verify the measurement accuracy, laboratory measurements Workshop, conducted by the Air Force and Northrop are presented were made in the flow field of a 10 cm-diameter, 30-m/sec in this report. GRA axisymmetric jet. A discussion of the requirements and techniques used to seed the flow is made, and boundary-layer surveys of N89-26273'# National Aeronautics and Space Administration. mean velocity and turbulence intensity of the streamwise Langley Research Center, Hampton, VA. component and the component normal to the surface are LANGLEY ROTORCRAFT STRUCTURAL DYNAMICS presented. Author PROGRAM BACKGROUND, STATUS, ACCOMPLISHMENTS, PLANS N89-26240 Department of the Air Force, Washington, DC. RAYMOND G. KVATERNIK Jun. 1989 22 p SUPERCONDUCTING ROTOR COOLING SYSTEM Patent (NASA-TM-101618; NAS 1.15:101618) Avail: NTlS HC AO3/MF PHILLIP W. ECKELS, inventor (to Air Force) 18 Oct. 1988 4 p A01 CSCL 20111 Filed 13 Oct. 1987 Excessive vibration is the most common technical problem to (AD-D014020; US-PATENT-4,779,017; arise as a show stopper in the development of a new rotorcraft. US-PATENT-APPL-SN-107197; US-PATENT-CLASS-310-52) Vibration predictions have not been relied on by the industry during Avail: US Patent and Trademark Office CSCL 13/1 design because of deficiencies in finite element dynamic analyses. A superconducting rotor cooling system for an electrical A rotorcraft structural dynamics program aimed at meeting the generator includes a free vortex type pump which is located within industry's long-term needs in this key technical area was and forms an integral part of the rotor assembly. The free vortex implemented at Langley in 1984. The subject program is a pump takes advantage of the centrifugal force of rotation of the cooperative effort involving NASA, the Army, academia, and the cooling fluid to help the rotor winding compartment to remain in a helicopter industry in a series of generic research activities directed superfluid helium state. Improved cooling results from combined at establishing the critical elements of the technology base needed natural convection (which occurs in a conventional rotor) and the for development of a superior finite element dynamics design superfluid heat transport (which occurs at the velocity of sound). analysis capability in the US. helicopter industry. An executive GRA overview of the background, status, accomplishments, and future direction of this program is presented. Author N8926259'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. COMPUTATIONAL STRUCTURAL MECHANICS FOR ENGINE STRUCTURES 13 C. C. CHAMIS 1989 12 p Presented at the 30th Structures, Structural Dynamics and Materials (SDM) Conference, Mobile, AL, GEOSCIENCES 3-5 Apr. 1989; cosponsored by the AIAA, ASME, ASCE, AHS, and ACS Includes geosciences (general); earth resources; energy production (NASA-TM-102119; E-4898; NAS 1.151021 19) Avail: NTlS HC and conversion; environment pollution; geophysics; meteorology AO3/MF A01 CSCL 2011 1 and climatology; and oceanography. The computational structural mechanics (CSM) program at Lewis encompasses: (1) fundamental aspects for formulating and solving structural mechanics problems, and (2) development of A89-44016 integrated software systems to cornputationally simulate the LOW-TEMPERATURE PERFORMANCE OF A POWER-PACK performance/durability/life of engine structures. It is structured to FOR A 2-WATT ELT mainly supplement, complement, and whenever possible replace, FRASER WALSH and RADEK FUKSA (Energy Conversion Corp., costly experimental efforts which are unavoidable during Somerville, MA) IN: International Power Sources Symposium, engineering research and development programs. Specific 33rd, Cherry Hill, NJ, June 13-16, 1988, Proceedings. Pennington, objectives include: investigate unique advantages of parallel and NJ, Electrochemical Society, Inc., 1988, p. 633-638. multiprocesses for: reformulating/solving structural mechanics and The performance characteristics of two power packs for an formulating/solving multidisciplinary mechanics and develop airborne emergency locator transmitter (ELT) are described. One integrated structural system computational simulators for: predicting of these power packs is based on the use of 12 C-size alkaline structural performances, evaluating newly developed methods, and cells; the other, on the use of four Li/SOC12 cells. The performance for identifying and prioritizing improved/missing methods needed. under load of the two power packs was tested as a function of Herein the CSM program is summarized with emphasis on the operating temperature. In these tests, the ELT with power pack Engine Structures Computational Simulator (ESCS). Typical results was held in a cold chamber at the desired temperature for 24 h obtained using ESCS are described to illustrate its versatility. or longer prior to turning on the ELT; at this point, the load voltage Author across both the continuous drain and the pulse load circuits was monitored. It was found that, at temperatures lower than -10 C, N89-26267# Northrop Corp., Hawthorne, CA. Aircraft Div. only the Li/SOCIP-based power pack was capable of meeting both AUTOMATED STRUCTURAL OPTIMIZATION SYSTEM the desired discharge lifetime and power output requirements. (ASTROS): USER TRAINING WORKSHOP Final Report, Jul. IS. 1983 - Jun. 1988 E. H. JOHNSON, D. J. NEILL, D. L. HERENDEEN, and R. A. A89-45131 CANFIELD (Department of the Air Force, Wright-Patterson AFB, 'FLIGHT TESTING' A MULTI-MEGAWATT WIND TURBINE OH.) Mar. 1989 427 p M. G. REES (Boeing Aerospace, Seattle, WA) IN: Society of (Contract F33615-83-C-3232) Flight Test Engineers, Annual Symposium, 19th, Arlington, TX, Aug.
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14-18, 1988, Proceedings. Lancaster, CA, Society of Flight Test due to maneuvering helicopters, and to obtain pilot perceptions Engineers, 1988, p. 11-3.1 to 11-3.10. refs and observations concerning maneuvering and parking separation The field test program for the Moddb, a 3.2 megawatt horizontal criteria. Ten wind vector transmitters were situated at various axis wind turbine, is described. The test results showed the locations around the helicopter in order to gather information to structural stresses to be significantly below the allowable describe the rotorwash induced wind speed and direction changes. fatigue-related values. The variable speed generator employed is Pilot interviews were also conducted at these heliports. Volume 1 characterized by improved energy capture, reduced power swings of this report documents the results of this activity. It describes at rated power, and reduced structural loads with respect to a the data collection and analysis methodology and addresses previous synchronous generator. A good fit is found between the technical as well as operational issues. It provides graphical control law assumptions and experimental results for aerodynamic descriptions of the heliport environment and of wind speed changes torque. Design, assembly, and equipment reliability problems are due to rotorwash from maneuvering helicopters, along with analysis identified. R.R. of pilot responses. The results of this study will be considered in future modifications of the Federal Aviation Administration Heliport A89-46775# Design Advisory Circular 150/390-2. GRA NOISE ISSUES - AN FAA PERSPECTIVE ON TRANSPORT NOISE N89-26323# Massachusetts Jnst. of Tech., Lexington. Lincoln NICHOLAS P. KRULL (FAA, Office of Environment and Energy, Lab. Washington. DC) AIAA, ASME, SAE, and ASEE, Joint Propulsion SELECTED WIND SHEAR EVENTS OBSERVED DURING THE Conference, 25th, Monterey. CA, July 10-13, 1989. 7 p. 1987 EVALUATION OF ENHANCEMENTS TO THE FAA (AIAA PAPER 89-2362) (FEDERAL AVIATION ADMINISTRATION) LOW LEVEL WIND The history of noise regulation in the United States is traced SHEAR ALERT SYSTEM AT STAPLETON INTERNATIONAL and the current status of noise regulations is presented for several AIRPORT types of aircraft and propulsion systems. Consideration is given to MICHAEL F. DONOVAN and MARILYN M. WOLFSON 15 Feb. helicopters, tiltrotors, conventional turbojet and turbofan powered 1989 118 p transports, advanced turboprop or unducted fan powered (Contract DTFAO1-80-Y-10546; F19628-85-C-0002) transports, and high-speed civil transports. Some international (AD-A20671 1; ATC-158; DOT/FAA/PS-88/9) Avail: NTlS HC developments which may influence the US. aviation industry and AO61MF A01 CSCL 04/2 US. noise regulations are addresed as well. It is believed that, in The FAA Technical Center (FAATC) conducted a test of the time, Stage 2 aircraft will be eliminated, either through local access enhancements to the FAA Low Level Wind Shear Alert System restrictions or by Federal regulations. K.K. (LLWAS) at Denver Stapleton International Airport from 3 Aug. to 4 Sep. 1987. Upon completion of the test, the performance of the N89-25530# Lawrence Livermore National Lab., CA. LLWAS during selected microburst and gust front test cases was PREVENTING DEPLETION OF STRATOSPHERIC OZONE: investigated in detail. Additional sources of true wind shear IMPLICATIONS ON FUTURE AIRCRAFT EMISSIONS information were sought to help evaluate the performance of the DOUGLAS E. KlNNlSON and DONALD J. WUEBBLES Apr. LLWAS. In support of these efforts, Lincoln Laboratory supplied 1989 17 p Presented at the 82nd Air and Waste Management complete data sets, including single Doppler radar data from the Association Annual Meeting and Exhibition, Anaheim, CA, 25-30 Lincoln network of 30 automatic weather stations in the vicinity of Jun. 1989 Stapleton, and LLWAS data to the FAATC. This report summarizes (Contract W-7405-ENG-48) salient features for a number of FAATC selected wind shear events (DE89-009964; UCRL-99926; CONF-890692-4) Avail: NTlS HC which occurred during the evaluation of the enhanced LLWAS, A03IMF A01 and documents the data that Lincoln Laboratory has provided to There is much renewed interest in the development of faster the FAA as part of its project responsibilities. GRA aircraft for intercontinental passenger flights. Such aircraft would likely spend a large fraction of their flight time in the stratosphere, at altitudes as high as 35 km. It is important, in order to present 15 the problems with the proposed supersonic-transportthat occurred in the early 1970’s. that the aircraft industry work together with the atmospheric science community to insure that future aircraft MATHEMATICAL AND COMPUTER SCIENCES emissions will not deplete stratospheric ozone. In this study, we have used our two-dimensional model of the troposphere and Includes mathematical and computer sciences (general); computer stratosphere to examine the sensitivity of stratospheric ozone to operations and hardware; computer programming and software; such emissions. Initial results indicate, for commercial fleets as computer systems; cybernetics; numerical analysis; statistics and large as proposed for the origina! SST and depending on the probability; systems analysis; and theoretical mathematics. odd-nitrogen emissions per engine, that substantial decreases in stratospheric ozone could result. The decrease in ozone is sensitive to the altitude and latitude in the emissions. Effects on ozone, for A8944423 the same emission rate, tend to be larger as altitude increases, IN SEARCH OF EFFECTIVE DIVERSITY - A SIX-LANGUAGE until a maximum effect is reached near 30 kin. DOE STUDY OF FAULT-TOLERANT FLIGHT CONTROL SOFTWARE ALGIRDAS AVIZIENIS, MICHAEL R. LYU, and WERNER SCHUTZ N89-26294# Federal Aviation Administration, Atlantic City, NJ. (California, University, Los Angeles) IN: FTCS-18; International ANALYSIS OF HELICOPTER ENVIRONMENTAL DATA Symposium on Fault-Tolerant Computing, lath, Tokyo, Japan, June INDIANAPOLIS DOWNTOWN HELIPORT, WALL STREET 27-30, 1988, Digest of Papers. Washington, DC, Computer Society HELIPORT. VOLUME 1: SUMMARY Technical Note for Period Press, 1988, p. 15-22. Research supported by Honeywell, Inc. Ending May 1988 and California Microelectronics Innovation and Computer Research ROSANNE M. WEISS, JOHN G. MORROW, DONALD Opportunities Program. refs GALLAGHER, MARK DIMEO. and SCOTT ERLICHMAN Oct. The techniques used in the design of multiversion flight-control 1988 61 p software are investigated experimentally. Software for the (ADA206708; DOT/FAA/CT-TN87/54-VOL-l) Avail: NTlS HC computer-controlled landing of commercial transport aircraft was A04lMF A01 CSCL 01 I5 developed in six computer languages (C, PASCAL, Ada, Modula-2, During the summer of 1987 heliport environmental data were PROLOG, and T) by independent, isolated teams of programmers, collected at the Indianapolis Downtown Heliport and at New York’s with three formal reviews and careful error reporting incorporated Wall Street Heliport. The purpose of this data collection activity into the design process. The resulting programs were subjected was to obtain measures of rotorwash in the heliport environment to unit, integration, acceptance, and flight-simulation tests and
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evaluated in detail. Recommendations are given to maximize the permits the reconstruction of global covariance information from potential for diversity in the software design process while assuring local observation data without significant loss of accuracy. The the identification and elimination of duplicate faults. T.K. data computation is significantly reduced in comparison to methods requiring the inversion of potentially large matrices. K.K. A89-45293# EXPERT SYSTEMS ROLE BROADENS A8946244 DAVID M. SMITH (Lockheed Aeronautical Systems Co., Burbank, LOCAL ANALYTICAL METHODS FOR DIGITAL SIMULATION CA) Aerospace America (ISSN 0740-722X). vol. 27, July 1989, OF DYNAMICAL CONTROL SYSTEM p. 26-28. J ING-GAO FEI (Beijing Institute of Computer Applications and Expert-system technologies are under development for such Simulation Technology, People’s Republic of China) Science in aerospace applications as the scheduling of complex, China, Series A - Mathematics, Physics, Astronomy and resource-limited processes, composite materials’ fabrication, and Technological Sciences (ISSN 0253-5831), vol. 32, March 1989, the intelligent, real-time-interactive assistance of flight crews in p. 361-373. high-stresslhigh-workload situations. All such real-time cooperative Local analytical methods for digital simulation of the dynamical expert systems involve (1) the capture of expertise from multiple control system are presented to overcome the difficulties due to sources; (2) the creation of an adequate interface between the the stiffness, the oscillation with high frequency, and the user and the system; and (3) the creation of a suitable interface discontinuity. The idea of computation of the analog computer is between the system and the process or vehicle to be managed. introduced into the computation of digital simulation, the system The most challenging of these system-definition tasks has been is decomposed into some subsystems, each of which can run found to be the first, since contributions from specialists in many independently, and, with the approximated input information, the fields must be integrated. O.C. local analytical expressions for the solutions of these subsystems are constructed. Finally, a simple analysis about the accuracy A8946144 estimate and the stability of the algorithms is given. The CONTROL AND DYNAMIC SYSTEMS. VOLUME 29 - computational results show that the CPU time expended on the ADVANCES IN ALGORITHMS AND COMPUTATIONAL digital simulation of a flying control system is only 1/20 of that TECHNIQUES IN DYNAMIC SYSTEMS CONTROL. PART 2 needed by the traditional numerical methods. Author C. T. LEONDES, ED. (California, University, Los Angeles) San Diego, CA, Academic Press, Inc., 1988, 324 p. For individual items A8946551 see A89-46145 to A89-46148. METHODS FOR THE MATHEMATICAL MODELING OF FLIGHT Recent advances in the theory of numerical control for VEHICLE ENGINES [METODY MATEMATICHESKOGO dynamical systems are discussed in reviews and reports contributed MODELlROVANllA DVIGATELEI LETATEL‘NYKH by leading experts. Topics examined include the numerical reliability APPARATOV] of Kalman-filter schemes, algorithms for system fault detection ROSTISLAV K. CHUIAN Moscow, Izdatel’stvo Mashinostroenie, through modeling and estimation techniques, computer 1988, 288 p. In Russian. refs architectures set up to generate higher-performance controllers, Methods for modeling and optimizing flight vehicle engines and and angle-only-tracking filtering. Consideration is given to their components using state-of-the-art digital and analog gradient-projection methods for systems-optimization problems; computers are reviewed. In particular, attention is given to the optimal control, estimation, and compensation of linear classification of mathematical models, hierarchical principles of the discrete-time systems with stochastic parameters; an algorithm for development of mathematical models, statistical testing of models, the approximation of multivariable linear systems; and algorithms and digital and analog models of flight vehicle engines. The for discrete-time adaptive control of rapidly time-varying systems. discussion also covers engine identification models and methods T.K. and optimal design of flight vehicle engines. V.L.
A89-46147’ National Aeronautics and Space Administration. N89-25162*# Georgia Inst. of Tech., Atlanta. Ames Research Center, Moffett Field, CA. TRUSS AN INTELLIGENT DESIGN SYSTEM FOR AIRCRAFT ARRANGING COMPUTER ARCHITECTURES TO CREATE WINGS HIGHER-PERFORMANCE CONTROLLERS PRESTON R. BATES and DANIEL P. SCHRAGE ln NASA. Langley STEPHEN A. JACKLIN (NASA, Ames Research Center, Moffett Research Center, Recent Advances in Multidisciplinary Analysis Field, CA) IN: Control and dynamic systems. Volume 29. Part 2. and Optimization, Part 1 p 333-355 Apr. 1989 San Diego, CA, Academic Press, Inc., 1988, p. 67-99. refs Avail: NTlS HC A23/MF A01 CSCL 09/2 Techniques for integrating microprocessors, array processors, Competitive leadership in the international marketplace, and other intelligent devices in control systems are reviewed, with superiority in national defense, excellence in productivity, and safety an emphasis on the (re)arrangement of components to form of both private and public systems are all national defense goals distributed or parallel processing systems. Consideration is given which are dependent on superior engineering design. In recent to the selection of the host microprocessor, increasing the power years, it has become more evident that early design decisions are and/or memory capacity of the host, multitasking software for the critical, and when only based on performance often result in host, array processors to reduce computation time, the allocation products which are too expensive, hard to manufacture, or of real-time and non-real-time events to different computer unsupportable. Better use of computer-aided design tools and subsystems, intelligent devices to share the computational burden information-basedtechnologies is required to produce better quality for real-time events, and intelligent interfaces to increase United States products. A program is outlined here to explore the communication speeds. The case of a helicopter vibration- use of knowledge based expert systems coupled with numerical suppression and stabilization controller is analyzed as an example, optimization, database management techniques, and designer and significant improvements in computation and throughput rates interface methods in a networked design environment to improve are demonstrated. T.K. and assess design changes due to changing emphasis or requirements. The initial structural design of a tiltrotor aircraft wing A8946150 is used as a representative example to demonstrate the approach GAIN TRANSFER - AN ALGORITHM FOR DECENTRALIZED being followed. Author HIERARCHICAL ESTIMATION WILLIAM T. GARDNER (Hughes Aircraft Co., Los Angeles, CA) N89-25179’# Northrop Corp., Hawthorne, CA. Aircraft Div. IN: Control and dynamic systems. Volume 30. Part 3. San Diego, ROBUST COMPUTER-AIDED SYNTHESIS AND OPTIMIZATION CA, Academic Press, Inc., 1989, p. 19-64. refs OF LINEAR MULTIVARIABLE CONTROL SYSTEMS WITH The development of the gain transfer algorithm for application VARYING PLANT DYNAMICS VIA AUTOCON to a decentralized hierarchical estimator is studied. This technique C. P. LEFKOWITZ, J. A. TEKAWY, P. K. PUJARA, and M. G.
71 1 15 MATHEMATICAL AND COMPUTER SCIENCES
SAFONOV (University of Southern California, Los Angeles.) ln N89-26606*# National Aeronautics and Space Administration. NASA. Langley Research Center, Recent Advances in Lyndon B. Johnson Space Center, Houston, TX. MultidisciplinaryAnalysis and Optimization, Part 2 p 621-638 Apr. APPLICATIONS OF FUZZY SETS TO RULE-BASED EXPERT 1989 SYSTEM DEVELOPMENT Avail: NTlS HC A22/MF A01 CSCL 0912 ROBERT N. LEA ln NASA. Goddard Space Flight Center, The AUTOCON is an automated computer-aided design tool for 1989 Goddard Conference on Space Applications of Artificial the synthesis and optimization of linear multivariable control Intelligence p 385-388 Apr. 1989 systems based upon user-defined control parameter optimization. Avail: NTlS HC A17/MF A01 CSCL 12/1 Violations in stability and performance requirements are computed Problems of implementingrule-based expert systems using fuzzy from constraints on Single Input/Single Output (SISO) open- and sets are considered. A fuzzy logic software development shell is closed-loop transfer function frequency responses, and from used that allows inclusion of both crisp and fuzzy rules in decision constraints on the singular-value frequency responses of Multiple making and process control problems. Results are given that Input/Multiple Output (MIMO) transfer functions, for all critical plant compare this type of expert system to a human expert in some variations. Optimum nonlinear programming algorithms are used specific applications. Advantages and disadvantages of such in the search for local constrained solutions in which violations in systems are discussed. Author stability and performance are caused either to vanish or be minimized for a proper selection of the control parameters. Classical N89-26610*# Massachusetts Inst. of Tech., Cambridge. Lab. control system stability and performance design can, in this way, for Information and Decision Systems. be combined with modern multivariable robustness methods to NONLINEAR AND ADAPTIVE CONTROL Final Report, 1 Jun. offer general frequency response loop-shaping via a 1984 - 31 Jan. 1989 computer-aided design tool. Complete Nichols, Nyquist, Bode, MICHAEL ATHANS Jul. 1989 24 p singular-value Bode magnitude and transient response plots are (Contract NAG2-297) produced, including user-defined boundary responses. AUTOCON (NASA-CR-180088; NAS 1.26180088; LIDS-FR-1891; is used to synthesize and optimize the IateraVdirectional flight MIT-OSP-95178) Avail: NTlS HC AO3/MF A01 CSCL 09/2 control system for a typical high-performance aircraft. Author The primary thrust of the research was to conduct fundamental research in the theories and methodologies for designing complex high-performance multivariable feedback control systems; and to N89-25180'# McDonnell-DouglasHelicopter Co., Mesa, AZ. conduct feasibiltiy studies in application areas of interest to NASA COMPUTERIZED DESIGN SYNTHESIS (CDS), A sponsors that point out advantages and shortcomings of available DATABASE-DRIVEN MULTIDISCIPLINARY DESIGN TOOL control system design methodologies. Author D. M. ANDERSON and A. 0. BOLUKBASI ln NASA. Langley Research Center, Recent Advances in Multidisciplinary Analysis N89-26623'# National Aeronautics and Space Administration. and Optimization, Part 2 p 639-650 Apr. 1989 Langley Research Center, Hampton, VA. Avail: NTlS HC A22/MF A01 CSCL 09/2 INTEGRATED STRUCTURE/CONTROL LAW DESIGN BY The Computerized Design Synthesis (CDS) system under MULTILEVEL OPTIMIZATION development at McDonnell Douglas Helicopter Company (MDHC) MICHAEL G. GILBERT and DAVID K. SCHMIDT Jun. 1989 is targeted to make revolutionary improvements in both response 12 p Presented at the AlAA Guidance, Navigation and Control time and resource efficiency in the conceptual and preliminary Conference, Boston, MA. 14-16 Aug. 1989 design of rotorcraft systems. It makes the accumulated design (NASA-TM-101623; NAS 1.15:101623) Avail: NTlS HC A03/MF database and supporting technology analysis results readily A01 CSCL 09/2 available to designers and analysts of technology, systems, and A new approach to integrated structure/control law design production, and makes powerful design synthesis software available based on multilevel optimization is presented. This new approach in a user friendly format. Author is applicable to aircraft and spacecraft and allows for the independent design of the structure and control law. Integration N89-25220'# Georgia Inst. of Tech., Atlanta. School of of the designs is achieved through use of an upper level Aerospace Engineering. coordination problem formulation within the multilevel optimization THE ROLE OF OPTIMIZATION IN THE NEXT GENERATION OF framework. The method requires the use of structure and control COMPUTER-BASED DESIGN TOOLS law design sensitivity information. A general multilevel J. EDWARD ROGAN ln NASA. Langley Research Center, Recent structure/control law design problem formulation is given, and the Advances in Multidisciplinary Analysis and Optimization, Part 3 p use of Linear Quadratic Gaussian (LQG) control law design and 1335-1357 Apr. 1989 design sensitivity methods within the formulation is illustrated. Avail: NTlS HC A22/MF A01 CSCL 0912 Results of three simple integrated structure/control law design There is a close relationship between design optimization and examples are presented. These results show the capability of the emerging new generation of computer-based tools for structure and control law design tradeoffs to improve controlled engineering design. With some notable exceptions, the system performance within the multilevel approach. Author development of these new tools has not taken full advantage of recent advances in numerical design optimization theory and practice. Recent work in the field of design process architecture 16 has included an assessment of the impact of next-generation computer-based design tools on the design process. These results are summarized, and insights into the role of optimization in a PHYSICS design process based on these next-generation tools are presented. An example problem has been worked out to illustrate Includes physics (general); acoustics; atomic and molecular the application of this technique. The example problem - layout of physics; nuclear and high-energy physics; optics; plasma physics; an aircraft main landing gear - is one that is simple enough to be solid-state physics; and thermodynamics and statistical physics. solved by many other techniques. Although the mathematical relationships describing the objective function and constraints for the landing gear layout problem can be written explicitly and are A89-46772'# National Aeronautics and Space Administration. quite straightforward, an approximation technique has been used Langley Research Center, Hampton, VA. in the solution of this problem that can just as easily be applied SUPERSONIC JET NOISE AND THE HIGH SPEED CIVIL to integrate supportability or producibility assessments using theory TRANSPORT of measurement techniques into the design decision-making JOHN M. SEINER (NASA, Langley Research Center, Hampton, process. Author VA) and EUGENE A. KREJSA (NASA, Lewis Research Center,
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Cleveland, OH) AIAA, ASME, SAE, and ASEE, Joint Propulsion coefficient, helical tip Mach number and advance ratio, and Conference, 25th, Monterey, CA, July 10-13, 1989. 24 p. refs propeller direction of rotation. Results show a dependence of the (AIAA PAPER 89-2358) level and directivity of the tones on the angle of attack and on An evaluation is made of the comparative advantages of the sideslip angle with the propeller direction of rotation, which is prospective SST engine noise-suppression systems, with a view similar to results obtained in wind tunnel tests with advanced to their effectiveness in meeting the federally-mandated community propeller designs. The level of the tones at each microphone noise standards of FAR 36 Stage 111. A noise-suppression system increases with increasing angle of attack for inboard-down propeller must be capable of removing at least 4 EPNdB of noise percent rotation and decreases for inboard-up rotation. The level also thrust loss at takeoff. While none of the suppressors presently increases with increasing slideslip angle for both propeller directions discussed is capable of meeting this goal, the inverted velocity of rotation. Increasing the power coefficient results in a slight profile/annular convergent-divergent plug/acoustically-treated increase in the level of the tones. A strong shock wave is generated ejector suppressor combination of configurational elements appears by the propeller blades even at relatively low helical tip Mach to represent the most efficient noise-control apparatus. Noncircular numbers resulting in high harmonic levels. As the helical tip Mach cross-section nozzle geometries also furnish a general noise number and the advance ratio are increased, the level of the reduction advantage over circular ones. O.C. higher harmonics increases much faster than the level of the blade passage frequency. Author N89-25140# Technische Hochschule, Aachen (Germany, F.R.). STRUCTURAL LOADING AND NOISE DISTURBANCE OF N89-25676# Technische Univ., Berlin (Germany, F.R.). HELICOPTERS [STRUKTURBEANSPRUCHUNGUND Fachgebeit Flugfuehrung und Luftverkehr. LAERMBELAESTIGUNG BElN HUBSCHRAUBERI REDUCTION OF AIRCRAFT NOISE IN CIVIL AIR TRANSPORT R. MUELLER In its Vortex Flows in Flying Technique p 313-337 BY OPTIMIZATION OF FLIGHT TRACKS AND TAKEOFF AND 1988 In GERMAN APPROACH PROCEDURES Final Report, 31 Mar. 1988 Avail: NTlS HC A17/MF A01 UWE ROTTMANN Aug. 1988 229 p In GERMAN; ENGLISH Test experiments were performed and calculation methods were summary developed to study the structural loading of helicopter rotor blades (Contract BMUNR-FB-88-105-05-501) and the resulting noise emission which can strongly reduce (ILR-MITT-200; ETN-89-94560) Avail: NTlS HC A1 1/MF A01 operational conditions of a helicopter. An optimized winglet was Noise optimized design of operational flight procedures for constructed which reduced rotor blade loading and rotor noise effective noise pollution reduction is analyzed. Power cutback emission by changing position and structure of the wing tip vortices. during certain stages of approach and takeoff, extension of distance The use of such winglets is especially advantageous in case of between sound source and sound receiver, as well as diminution fast descent. In fast forward flight the flow at the winglet can of sound impact time are optimized for specific flight procedures become a problem due to the high angles of attack at the winglet; and routings. Five takeoff and three landing procedures are however, no separation phenomena at the winglet were analyzed in acoustic effects. Sound immission is computed by observed. ESA NOlSlMSlS (NOISe IMpact Slmulation System), a simulation system especially created for this task, under consideration of aircraft N89-25673'# National Aeronautics and Space Administration. type specified sound emission characteristics and performance data Langley Research Center, Hampton, VA. as well as different meteorological conditions. The investigations AIRFOIL SELF-NOISE AND PREDICTION for the example of Frankfurt airport result in formulating a planning THOMAS F. BROOKS, D. STUART POPE (PRC Kentron, Inc., guideline with notes and impulses for activities in operational noise Hampton, VA.), and MICHAEL A. MARCOLlNl Jul. 1989 145 p abatement. ESA (NASA-RP-1218; L-16528; NAS 1.61 :1218) Avail: NTlS HC A07/MF A01 CSCL 2011 N89-25697# Deutsche Forschungs- und Versuchsanstalt fuer A prediction method is developed for the self-generated noise Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Abteilung of an airfoil blade encountering smooth flow. The prediction Lasertechnik. methods for the individual self-noise mechanisms are semiempirical PROTOTYPE OF A SLANT VISUAL RANGE MEASURING and are based on previous theoretical studies and data obtained DEVICE from tests of two- and three-dimensional airfoil blade sections. JUERGEN STREICHER, CHRISTIAN WERNER, UWE BERGHAUS, The self-noise mechanisms are due to specific boundary-layer HARALD GATZ, EBERHARD GELBKE, ANDREAS LISIUS, and phenomena, that is, the boundary-layer turbulence passing the CHRISTOPH MUENKEL (Impulsphysik G.m.b.H., Hamburg, trailing edge, separated-boundary-layer and stalled flow over an Germany, F.R. ) Aug. 1988 81 p In GERMAN; ENGLISH airfoil, vortex shedding due to laminar boundary layer instabilities, summary vortex shedding from blunt trailing edges, and the turbulent vortex (DFVLR-FB-88-42; ISSN-0171-1342; ETN-89-94632) Avail: NTlS flow existing near the tip of lifting blades. The predictions are HC A05fMF A01; DFVLR, VB-PL-DO, Postfach 90 60 58, 5000 compared successfully with published data from three self-noise Cologne, Fed. Republic of Germany, DM 25.50 studies of different airfoil shapes. An application of the prediction A prototype an eye-safe slant visual range measuring device method is reported for a large scale-model helicopter rotor, and consisting of a modified eye-safe cloud ceilograph is described. the predictions compared well with experimental broadband noise The system concept with a fast data system and a complex data measurements. A computer code of the method is given. Author handling program is presented. It is intended for airports. ESA
N89-25675'# National Aeronautics and Space Administration. N89-26679'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. Langley Research Center, Hampton, VA. IN-FLIGHT MEASUREMENT OF PROPELLER NOISE ON THE A NEW CLASS OF RANDOM PROCESSES WITH FUSELAGE OF AN AIRPLANE APPLICATION TO HELICOPTER NOISE Annual Report No. 2 FREDERIC G. PLA (Sverdrup Technology, Inc., Cleveland, OH.), JAY C. HARDIN and A. G. MIAMEE (Hampton Inst., VA.) 1989 RICHARD RANAUDO, and RICHARD P. WOODWARD Jul. 25 P 1989 58 p (Contract NAG1-768) (Contract NAS3-24105) (NASA-CR-185037; NAS 1.26:185037) Avail: NTlS HC AO3/MF (NASA-TM-102285; E-4952; NAS 1.15102285) Avail: NTlS HC A01 CSCL20/1 A04/MF A01 CSCL 2011 The concept of dividing random processes into classes (e.g., In-flight measurements of propeller noise on the fuselage of stationary, locally stationary, periodically correlated, and an OV-1OA aircraft were obtained using a horizontal and a vertical harmonizable) has long been employed. A new class of random microphone array. A wide range of flight conditions were tested processes is introduced which. includes many of these processes including changes in angle of attack, sideslip angle, power as well as other interesting processes which fall into none of the
713 16 PHYSICS
above classes. Such random processes are denoted as linearly Canada) Montreal, McGill University, 1988, 429 p. In English correlated. This class is shown to include the familiar stationary and French. No individual items are abstracted in this volume. and periodically correlated processes as well as many other, both Papers are presented on the obsolescence of bilateral air harmonizable and non-harmonizable, nonstationary processes. transport agreements, air transport deregulation in jurisdictions When a process is linearly correlated for all t and harmonizable, other than the U.S., the role of the ICAO in the suppression of its two-dimensional power spectral density S(x)(omega 1, omega drug trafficking, and aircraft accidents in Japan. Also considered 2) is shown to take a particularly simple form, being non-zero are legal aspects of space conquest, liability for damage caused only on lines such that omega 1 to omega 2 = + or - r(k) where in outer space by space refuse, international organizations for the r(k's) are (not necessarily equally spaced) roots of a space regulation, and key judical decisions related to space law. characteristic function. The relationship of such processes to the Other topics include space surveillance for arms control and class of stationary processes is examined. In addition, the verification, the extraterritorial application of US. antitrust laws, application of such processes in the analysis of typical helicopter ESA resolutions on participation in the Space Station program, noise signals is described. Author and an international agreement on the establishment of tariffs for intra-European scheduled air services. R.R. N89-26683'# United Technologies Research Center, East - A89-46835# Hartford, CT. ECONOMIC ANALYSIS OF A BEAM-POWERED, NOISE PRODUCED BY TURBULENT FLOW INTO A ROTOR PERSONALIZED GLOBALAEROSPACETRANSPORTATION THEORY MANUAL FOR NOISE CALCULATION Final Report SYSTEM R. K. AMlET Jun. 1989 36 p GEORGE LIST, LElK MYRABO (Rennselaer Polytechnic Institute, (Contract NAS1-17763) Troy, NY), and DAVID WALTON AIAA, ASME, SAE, and ASEE, (NASA-CR-181788; NAS 1.26:181788) Avail: NTlS HC A03/MF Joint Propulsion Conference, 25th, Monterey, CA. July 10-13, 1989. A01 CSCL 2011 An analysis is presented for the calculation of noise produced 7 P. (AIAA PAPER 89-2443) by turbulent flow into a helicopter rotor. The method is based on This paper presents an economic analysis of a revolutionary the analysis of Amiet for the sound produced by an airfoil moving transport technology intended for high-speed world travel. The in rectilinear motion through a turbulent flow field. The rectilinear Apollo lightcraft technology will make possible door-to-door travel motion results are used in a quasi-steady manner to calculate the half-way around the globe in 45 minutes; an unmanned instantaneous spectrum of the rotor noise at any given rotor experimental launch of a laser-boosted demonstration is due within position; the overall spectrum is then found by averaging the five years. Estimates are presented of vehicle size; ridership; instantaneous spectrum over all rotor azimuth angles. Account is revenues; fleet size; capital, operating and maintenance cost; and taken of the fact that the rotor spends different amounts of retarded time at different rotor positions. Blade to blade correlation is expected profitability. On a net present value basis. over a 20-year time span, the system should have costs 20 percent below included in the analysis, leading to harmonics of blade passing revenues, implying not only an ability to be economically profitable frequency. The spectrum of the turbulence entering the rotor is but, as the reader will probably agree, a potential market calculated by applying rapid distortion theory to an isotropic penetrability which goes well beyond the conservative assumptions turbulence spectrum, assuming that the turbulence is stretched as made in the analyses. Author it is pulled into the rotor. The inputs to the program are obtained from the atmospheric turbulence model and mean flow distortion N89-25764*# National Aeronautics and Space Administration. calculation, described in another volume of this set of reports. Marshall Space Flight Center, Huntsville, AL. The analytical basis is provided for a module which was FEDERAL INCENTIVES FOR INDUSTRIAL MODERNIZATION: incorporated in NASA's ROTONET helicopter noise prediction HISTORICAL REVIEW AND FUTURE OPPORTUNITIES program. Author SANDRA C. COLEMAN and ROBERT G. BATSON (Alabama Univ., Tuscaloosa.) Aug. 1987 37 p Submitted for publication (NASA-TM-101785; NAS 1.15:101785) Avail: NTlS HC AO3/MF A01 CSCL 0511 17 Concerns over the aging of the U.S. aerospace industrial base led DOD to introduce first its Technology Modernization (Tech SOCIAL SCIENCES Mod) Program, and more recently the Industrial Modernization Incentive Program (IMIP). These incentives include productivity Includes social sciences (general); administration and management; shared savings rewards, contractor investment protection to allow documentation and information science; economics and cost for amortization of plant and equipment, and subcontractor/vendor analysis; law and political science; and urban technology and participation. The purpose here is to review DOD IMlP and to transportation. evaluate whether a similar program is feasible for NASA and other non-DOD agencies. The IMlP methodology is of interest to industrial engineers because it provides a structured, disciplined approach A89-45039 to identifying productivity improvement opportunities and AIRBUS INDUSTRIE, LESSONS FROM EXPERIENCE [AIRBUS documenting their expected benefit. However, it is shown that INDUSTRIE, LECONS D'UNE EXPERIENCE] more research on predicting and validating cost avoidance is ROGER BETEILLE (Airbus Industrie. Blagnac, France) needed. Author L'Aeronautique et I'Astronautique (ISSN 0001 -9275), no. 136-137, 1989. p. 60-68. In French. The Airbus program, a cooperative venture of France, England, Germany, Spain, the Netherlands, and Belgium, is discussed in detail. The problems encountered during the design, fabrication, and marketing of the Airbus aircraft are reviewed. It is emphasized that cooperation among the various countries requires the standardization of computer languages, technical terms, and scientific parameters. R.R.
A8945175 ANNALS OF AIR AND SPACE LAW. VOLUME 13 NICOLAS MATEESCO MATTE, ED. (McGill University, Montreal,
714 SUBJECT INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245) November 1989
Typical Subject Index Listing AERODYNAMIC CHARACTERISTICS Predictionof periodic loadings on single rotationpropfan Multi-stage compressor airfoil aerodynamics. I . Airfoil with off-axis inflow potential flow analysis p 639 A89-44112 [AIAA PAPER 89-26941 p 681 A89-47024 Prediction of the stability limit of multistage axial Reduction of 1-P aerodynamic loads on tractor aircraft compressors p 640 A89-44637 engine installations Experimental study on aerodynamic characteristics of [AIAA PAPER 89-29241 p 651 A89-47177 hypersonic transport configuration p 640 A89-44972 Performance and loads data from an outdoor hover test Numerical modelling of flight dynamics and flight test of a Lynx tail rotor data identification of a jet trainer airplane [NASA-TM-101 0571 p 656 N89-25958 AEROSPACEPLANES p 663 A89-45139 AERODYNAMIC NOISE Technology issues associatedwith fueling the national Effects of axial velocity density ratio on cascade Airfoil self-noiseand prediction aerospace plane with slush hydrogen performances p 645 A89-45565 [NASA-RP-t2181 p 713 N89-25673 Experimental study of vortex and aerodynamic [NASA-TM-101386] p 43 N89-10123 The acoustics of a small-scale helicopter rotor in characteristics of stack wings with sideslip hover 7 -7 p 646 A89-46259 r [ NASA-TM-101058l p 655 N89-25954 Performance and flow field of a ducted propeller [AIAA PAPER 89.26731 p 649 A89-47003 A new class of random processes with application to helicopter noise Turbine aerodynamic performance measurements in [ NASA-CR-1850371 p 713 N89-26679 short duration facilities Noise produced by turbulent flow into a rotor: Theory [AIAA PAPER 89.26901 p 693 A89-47020 Viscous aerodynamic analysis of an oscillating flat-plate manual for noise calculation [NASA-CR- 18 17881 714 N89-26683 airfoil p 652 A89-47356 p AERODYNAMIC STALLING The subject heading is a key to the subject content Steady-state and transitional aerodynamic natural low-frequency oscillation of the flow over an of the document. The title is used to provide a characteristics of a wing in simulated heavy rain A [ NASA-TP-29321 p 655 N89-25951 airfoil near stalling conditions p 645 A89-45437 description of the subject matter. When the title is Computational and experimental study of stall insufficiently descriptive of document content, a Two axial compressor designs for a stage matching investigation propagation in axial compressors [AIAA PAPER 89-24541 p 647 A89-46842 title extension is added, separated from the title [AD-A2069511 p 685 N89-26006 by three hyphens. The (NASA or AIAA) accession AERODYNAMIC CONFIGURATIONS Steady-state and transitional aerodynamic characteristics of a wing in simulated heavy rain number and the page number are included in each Hypersonic vehicle propulsion - A computational fluid dynamics application case study p 639 A89-44116 [ NASA-TP-29321 p 655 N89-25951 entry to assist the user in locating the abstract in Studies of vortex flow aerodynamics using CFD flow AERODYNAMICS the abstract section. If applicable, a report number visualizations p 641 A89-45260 International Conference on Numerical Methods in Fluid Transonic analysis of arbitrary configurations using Dynamics. llth, Williamsburg, VA, June 27-July 1. 1988. is also included as an aid in identifying the docu- Proceedings p 699 A89-45351 locally refined grids p 644 A89-45419 ment. Under any one subject heading, the acces- Computational fluid dynamics A personal view Aerodynamic design and testing of Fokker 50 nacelle - p 699 A89-45352 sion numbers are arranged in sequence with the and intake ducts AIAA accession numbers appearing first. [AIAA PAPER 89-24831 p 665 A89-46866 A high resolution finite volume scheme for steady external transonic flow p 642 A89-45369 Design and testing of a common engine and nacelle for the Fokker 100 and Gulfstream GIV airplanes Difference methods for initial-boundary-valueproblems [AIAA PAPER 89.24861 p 666 A89-46867 and flow around bodies (Revised edition) --- Book p 646 A89-46198 Aerodynamics of high-lift, low-aspect-ratio unswept wings p 652 A89-47372 Modeling of controlled flight dynamics using in-flight A simulators Russian book p 688 A89-46546 The conceptual design of a Mach 2 Oblique Flying Wing --- Structural optimization of rotor blades with integrated supersonic transport ACGENERATORS dynamics and aerodynamics p 668 N89-25156 The solution of 3-D temperature distribution in a cycling [NASA-CR-177529] p 671 N89-25233 Integrated aerodynamic-structural design 01 a oil cooled aircraft ac generator by network topology Experimentaland computational flow-field results for an forward-swept transport wing p 669 N89-25168 method p 701 A89-46282 all-body hypersonic aircraft Effects of nonlinear aerodynamics and static [NASA-CR-185347] p 655 N89-25953 ACCIDENT PREVENTION aeroelasticity on mission performance calculations for a Airline operations and the contaminated runway Development and application of a computer-based fighter aircraft p 669 N89-25170 [SA€ PAPER 8814601 p 658 A89-47339 system for conceptual aircraft design Optimum design of swept-forward high-aspect-ration ACOUSTIC INSTABILITY [ETN-89-948661 p 673 N89-26001 graphite-epoxy wings p 669 N89-25172 The instability and acoustic wave modes of supersonic HOMAR: A computer code for generating homotopic Control surface spanwise placement in active flutter mixing layers inside a rectangular channel grids using algebraic relations: User's manual suppression systems p 689 N89-25195 p 699 A89-45453 [ NASA-CR-42431 p 708 N89-26176 Meeting the challenges with the Douglas Aircraft F-16 inlet stability investigation AERODYNAMIC DRAG Company Aeroelastic Design Optimization Program [AIAA PAPER 89.24651 p 665 A89-46852 Wind-tunnel investigations of wings with serrated sharp (ADOP) p 671 N89-25222 ACOUSTICS trailing edges p641 A89-45262 The acoustics of a small-scale helicopter rotor in In-flight measurement of propeller noise on the fuselage Computational modeling of axisymmetric propeller-hull hover of an airplane interaction in slender low drag bodies [ NASA-TM-1010581 p 655 N89-25954 [NASA-TM-102285] p 713 N89-25675 [AIAA PAPER 89-26741 p 649 A89-47004 AEROELASTICITY ACTIVE CONTROL An experimental investigation of high llfthgh rate Aeroelastic analysis of prop fan blades with a Digital robust control law synthesis using constrained aerodynamics of an unsteady airfoil semiempirical dynamic stall model optimization p 689 N89-25193 [ AD-A206964I p 856 N89-25964 [AIAA PAPER 89-26951 p 703 A89-47025 Structural optimization of rotor blades with straight and An integratedapproach to the optimum design of actively AERODYNAMIC HEATING swept tips subject to aeroelastic constraints controlled composite wings p 670 N89-25194 Finite element flow-thermal-structural analysis of p 667 N89-25152 aerodynamically heated leading edges ACTUATORS Optimization of rotor blades for combined structural. p 855 N89-25198 Flap system for short takeoff and landing aircraft performance. and aeroelastic characteristics [AD-D013981] p 671 N89-25234 An introduction to the problem of aerodynamic heating p 667 N89-25153 ADAPTIVE CONTROL [AERO-REPT-8901] ' p 656 N89-25970 Efficient sensitivity analysis and optimization of a Nonlinear and adaptive control AERODYNAMIC INTERFERENCE helicopter rotor p668 N89-25155 [NASA-CR- 180088l p 712 N89-26610 Nacellelpylon interference study on a t117th-scale, Composite sizing and ply orientation for stiffness AERIAL PHOTOGRAPHY twin-engine. low-wing transport model requirements using a large finite element structural An air photo analysis of an airplane crash [AIAA PAPER 89-24801 p 665 A89-46864 model p 705 N89-25166 p 657 A89-45337 Vortices and pressure waves at plates. cylinders and Aerolastic tailoring and integrated wing design AEROACOUSTICS wind profiles p 668 N89-25167 Airfoil self-noise and prediction [ISL-R-102/88] p 656 N89-25966 Effects of nonlinear aerodynamics and static [ NASA-RP-12181 p 71 3 N89-25673 AERODYNAMIC LOADS aeroelasticity on mission performance calculations for a AERODYNAMIC BALANCE The influence of altitude and speed variations on the fighter aircraft p 669 N89-25170 Efficient sensitivity analysis and optimization of a aeroplane's load components in longitudinal nonlinear Results of including geometric nonlinearities in an helicopter rotor p 668 N89-25155 manoeuvres p 688 A89-45179 aeroelastic model of an F/A-t 8 p 669 N89-25190
A- 1 AEROSPACE ENGINEERING SUBJECT INDEX
An ove~~ewof the Douglas Aircraft Company AGING (METALLURGY) AIR TRANSPORTATION Aeroelasbc Deslgn Optimizabon Program (ADOP) A study of AI-Li alloys using small angle neutron Annals of air and space law. Volume 13 --- Book p 671 N89-25221 scattenng p 695 A89-44577 p 714 A89-45175 Meeting the challenges with the Douglas Aircraft AILERONS The EEC supports air transport research Company Aeroelastic Design Optimization Program AerOSeNoelaStiC tailonng for lateral control p 638 A89-46078 (ADOW p 671 N89-25222 enhancement p 689 N89-25189 Mechanical stresses during air transport and ground An analytcal sensitivity method for use in integrated AIR BREATHING ENGINES operations p 700 A89-46221 aeroservoelastic aircraft design A simple theory of aerospaceplane Economic analysis of a beam-powered, personalized [ NASA-TM-1015831 p 690 N89-25239 p 662 A89-44975 global aerospace transportation system Flap-lagstability data for a small-scaleisolated hingeless CFD for hypersonic airbreathing aircraft [AIAA PAPER 89-24431 p 714 A89-46835 rotor in forward flight p 641 A89-45355 FAA statistical handbook of aviation: Calendar year [ NASA-TM-1021891 p 706 N89-25479 A review of propulsion applications of the pulsed 1987 Influence of thekness and camber on the aeroelastic detonabon engine concept [AD-A2009171 p 638 N89-25113 stability of supersonic throughflow fans An engineenng [AlAA PAPER 89-24461 p 677 A89-46837 FAA (federal Aviation Administratmn) aviatmn forecasts: approach Numencal and expenmental investigation of Fiscal years 1989-2000 [ NASA-TM 1019491 p 656 N89-25957 airframe-integratedinlet for high velocities [ ADA2067161 p 638 N89-25948 Flutter suppression control law synthesis for the Active [AIAA PAPER 89-26791 p649 A89-47009 AlRBORNElSPACEBORNECOMPUTERS Flexible Wing model Combustion enhancement in supersonic coaxial flows Preliminary development of an intelligent computer [ NASA-TM-101584I p 690 N89-26010 [AlAA PAPER 89-27881 p 681 A89-47084 assistant for engine monitoring State space models for aeroelastic and viscoelastic AIR CONDITIONING [AIAA PAPER 89-25391 p 674 A89-46910 systems Airplane tests of enhanced emergency smoke venting AIRCRAFT ACCIDENT INVESTIGATION [ AD-A207092] p 690 N89-26012 [D218N3011 p 658 N89-25976 An air photo analysis of an airplane crash Automated structural opbmization system (ASTROS) AIR COOLING p 657 A89-45337 User training workshop Hgh performance gear systems and heat management AIRCRAFT ACCIDENTS [ AD-A207090] p 709 N89-26267 for advanced ducted systems In the drink --- ditch landing capability of aircraft AEROSPACE ENGINEERING [AIAA PAPER 89.24821 p 678 A89-46865 p 691 A89-43890 1988 report to the aerospace profession, Society of AIR FLOW FAA statistical handbook of aviation: Calendar year Expenmental Test Pilots, Symposium, 32nd Beverly Hills. Reducbon of 1-P aerodynamic loads on tractor aircraft 1987 CA. Oct 13-15, 1988. Proceedings p 686 A89-45151 engine installatmns [AD-A200917] p 638 N89-25113 Federal incentwes for industnal modernization Histoncal [AIAA PAPER 89-29241 p 651 A89-47177 General aviation accidents involving visual flight rules review and future opportunities EC-lBB/Boeing 707 Smoke Venting flight test flight into instrument meteorological conditions [ NASA-TM-1017851 p 714 N89-25764 [AD-A206601I p 659 N89-25979 [ PB89-9170011 p 658 N89-25974 AEROSPACE INDUSTRY AIR INTAKES Fuel containment system concept to reduce spillage Aerospatiale's short-term and intermediate-term place Flow charactenstics in an S-shaped rectangular-round [ DOT/FAA/CT-TN89/22] p 672 N89-25994 in the international scene p 637 A89-45032 diffuser at high incidence p 646 A89-46260 AIRCRAFT APPROACH SPACING Dassault, leader in European military and business Aerodynamic deslgn and tesbng of Fokker 50 nacelle Controller evaluationsof the descent advisor automation aircraft p 637 A89-45033 and intake ducts aid The SNECMA group today and tomorrow [AlAA PAPER 89-24831 p 665 A89-46866 [ NASA-TM-1021971 p 659 N89-25981 p 637 A89-45034 AIR LAW AIRCRAFT COMMUNICATION French aerospace research in the internabonal Annals of air and Space law Volume 13 --- Book Radio Technical Commission for Aeronautics. Annual context D 691 A89-45036 p 714 A89-45175 Assembly Meebng and Technical Symposium, Aeronautical research in the European future AIR NAVIGATION Washington. DC. Nov. 28-30. 1988. Proceedings p 638 A89-45037 Civil satellite navigatton and locabon systems p 660 A89-45875 AEROSPACEPLANES p 694 A89-43892 Functional requirements of the Communications Ootical research needed to SUDW~~.. the testing of AIR POLLUTION Interface Driver (CID) hyp&sonic vehicle structures p 697 A89-4<840 Preventing deplebon of stratospheric ozone [DOT/FAA/CT-TN87/41-REVl p 707 N89-26121 A simple theory of aerospaceplane Implications on future srcraft emissions AIRCRAFT COMPARTMENTS p 662 A89-44975 [ DE89-0099641 p 710 N89-25530 EC-lBB/Boeing 707 Smoke Venting flight test Economic analysis of a beam-powered, personalized AIR TRAFFIC [AD-A206601] p 659 N89-25979 global aerospace transportation system FAA (FederalAviation Administrabon) aviationforecasts AIRCRAFT CONFIGURATIONS [AIM PAPER 89.24431 p 714 A69-46835 Fiscal years 1989 2000 Reinforcing solutions for a panel cut-out Rapid methodology for design and performance [AD-A20s716] p 638 N89-25948 p 698 A89-45177 prediction of integrated scramjetlhypersonic vehicle Descent strategy comparisons for TNAV-equipped Configuration studies for a regional airliner using [AIAA PAPER 89-26821 p666 A89-47012 aircraft under airplane-preferred operating conditions open-rotor ultra-high-bypass-ratioengines A propulsion development strategy for the National [ NASA-CR-42481 p 690 N89-26011 [AlAA PAPER 89-25601 p666 A89-46937 Aero-Space Plane AIR TRAFFIC CONTROL Aeroelastic modeling for the FIT (Functional Integration [AIAA PAPER 89-2751I p 681 A89-47061 A knowledge-based en route monitor for air traffic Technology) team F/A-t 8 simulation Hypersonic airbreathing vehicle conceptual design control p660 A89-45065 p 670 N89-25192 (focus on aero-space plane) p 670 N89-25210 Air traffic control - No easy solutions in a complex Hypersonic airbreathing vehicle conceptual design AEROSPACE SYSTEMS terminal environment (focus on aero-space plane) p 670 N89-25210 Applications 01 integrated design/analysis systems in [SAE PAPER 8814691 p 661 A89-47335 The conceptual design of a Mach 2 Oblique Flying Wing aerospace structural design p 666 N89-25147 Research in automabon for air traffic control - United supersonic transport AEROSPACETECHNOLOGYTRANSFER Kingdom work and associated European projects [ NASA-CR-1775291 p 671 N89-25233 Transferringjet engine diagnostic and control technology [SAE PAPER 8814701 p 661 A89-47336 Development and application of a computer-based to liquid propellant rocket engines Notice to Airmen (NOTAM)., svstem oDerational system for conceptual aircraft design [AIM PAPER 89-28511 p 682 A89-47125 concept [ETN-89-94886] p 673 N89-26001 AEROSPACE VEHICLES [ DOT/FAA/CT-TN89/10] p 658 N89-25142 HOMAR: A computer code for generating homotopic Automated structural optimization system (ASTROS): FAA (FederalAviabon Administratian)aviation forecasts: grids using algebraic relations: User's manual User training workshop Fiscal years 1989-2000 [NASA-CR-4243] p 708 N89-26176 [AD-A207090] p 709 N89-26267 [ AD-A206716] p 638 N89-25948 AIRCRAFT CONSTRUCTION MATERIALS AEROTHERMODYNAMICS Controller evaluabons of the descent advisor automation Space age metals technology; Proceedings of the Experimental study on aerodynamic characteristics of aid Second International SAMPE Metals and Metals hypersonic transport configuration p 640 A89-44972 [ NASA-TM-1021971 p 659 N89-25981 Processing Conference, Dayton, OH, Aug. 2-4. 1988 Model predictions of fan response to inlet temperature Evaluationof a promonalgonthm for the stereographic p 696 A89-45927 transients and spatial temperature distortion representation of aircraft in an air traffic control system Aluminum-lithium alloys for fighter aircraft applications [AIAA PAPER 89-26861 p 650 A89-47016 [DOT/fAA/CT-TN89/20] p 661 N89-25985 p 696 A89-45937 Dynamic turbine blade temperature measurements Controller evaluabon of lnibal Data Link air traffic control A review of beryllides for very high temperature [AIM PAPER 89-26891 p 680 A89-47019 services Volume 2 Mini Study 2 service p 696 A89-45948 finite element flow-thermal-structural analysis of [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 Advanced material applications for turbine airfoils aerodynamically heated leading edges Descent strategy Comparisons for TNAV-equipped [AIAA PAPER 89.26931 p 680 A89-47023 p 655 N89-25198 aircraft under airplane-preferred operating conditions Multi-objective/loading optimization for rotating AFTERBODIES [ NASA-CR-42481 p 690 N89-26011 composite flexbeams p 668 N89-25157 Experimentaland computational flow-field results for an Funcbonal requirements of the Communications Integrated aerodynamic-structural design of a all-body hypersonic aircraft Interlace Dnver (CID) forward-swept transport wing p 669 N89-25168 [ NASA-CR-1853471 p 655 N89-25953 [DOT/FAA/CT-TN87/41 REV] p 707 N89-26121 Probabiliste damage tolerance methods for metallic AFTERBURNING Mode S performance test @an aerospace structures p 672 N89-25237 Measurement effects on the calculatiopn of in-flight [DOT/FAA/CT TN89/24] p 707 N89.26127 Materials and structures for 2000 and beyond An thrust for an F404 turbofan engine Satellite low rate voice demonstration test plan attempted forecast [AIAA PAPER 89-23641 p 677 A89-46777 [AD-A206710] p 707 N89-26133 [ DFVLR-MITT-89-02] p 706 N89-25358 Effects of bypass air on the combustion of boron AIR TRAFFIC CONTROLLERS(PERSONNEL) AIRCRAFT CONTROL particles in a solid fuel ramjet Controller evaluabons of the descent advisor automation Asymptotically decoupled discontinuous control of [AIAA PAPER 89-28861 p 683 A89-47151 aid systems and nonlinear aircraft maneuver AGGREGATES [ NASA-TM-1021971 p 659 N89-25981 p 686 A89-45064 Design criteria for aggregate-surfaced roads and Controller evaluabon of Initial Data Link air traffic control 1988 report to the aerospace profession: Society of airfields services Volume 2 Mini Study 2 ExperimentalTest Pilots, Symposium. 32nd, Beverly Hills, [AD-A207059] p 694 N89-26019 [DOT/FAAICT~9/14-VOL-2] p 661 N89-25986 CA, Oct. 13-15, 1988, Proceedings p 686 A89-45151
A-2 SUBJECT INDEX AIRCRAFT FUELS
8-16 high AOA testing p 687 A89745162 Optimum structural design with static aeroelastic Experimental investigation on characteristics of single Manual CAT llla with a HUD - Requirements and testing constraints p 669 N89-25171 and tandem blade cascades with double-circular arc --.FAA instrument approach category Optimum design of swept-forward high-aspect-ration profile p 676 A89-45567 p 687 A89-45164 graphite-epoxy wings p 669 N89-25172 Experimental investigation of aeroengine high-speed Expert systems' role broadens p 711 A89-45293 Recent Advances in Multidisciplinary Analysis and roller bearing p 700 A89-45570 Local analytical methods for digital simulation of Optimization. part 2 Continual opportunities for superalloy development dynamical control system p 71 1 A89-46244 [ NASA-CP-3031-PT-2] p 669 N89-25173 p 696 A89-45931 ASTROS A multidisciplinary automated structural The pursuit of integrated control - A realtime aircraft The ATRlRJ engine performance at constant dynamic design tool p 705 N69-25174 system demonstration pressure and the consideration of transition condition Recent experiences using finite-element-based [AIAA PAPER 89-27011 p 668 A69-47029 p 694 A69-46016 The evolution - IFPC to VMS integrated structural optimization p 705 N89-25177 ... The investigation 01 jet engine starting flightlpropulsion control for Vehicle Management Computerized Design Synthesis (COS). A p 676 A89-46025 System databasedriven multidisciplinarydesign tool [AIAA PAPER 89-27051 p 688 A89-47032 p 712 N89-25160 Performance analysis of scramjet engines Parametric study of a simultaneous pitchlyew thrust Aeroservoelastic tailoring for lateral control 0676 A89-46600 vectoring single expansion ramp nozzle enhancement p 689 N89-25189 Ceramic bearings for use in gas turbine engines [AIAA PAPER 89-28121 p 682 A89-47098 Results of including geometric nonlinearities in an D 702 A89-46697 Integrated flight/propuJsion control study for STOVL aeroelastic model of an F/A-18 p 669 N89-25190 Numerical codes lor unsteady simulation of turbojet, applications Flutter suppression using eigenspace freedoms to meet turbofan and turboprop engines lor training purposes [AIAA PAPER 69-29081 p 688 A89-47166 requirements p 689 N89-25191 [AIAA PAPER 89.22591 p 676 A89-46704 Contributionsto the improvement 01 flight safety in wind Aeroelastic modeling for the FIT (Functional Integration Re-engining stage two aircraft with the Tay shear Technology) team FIA-18 simulation [AIAA PAPER 89-2361I p 676 A89-46774 [ DFVLR-FB-88-49] p 656 N89-25144 p 670 N89-25192 Engine life maturation process Aeroservoelastic tailoring for lateral control An integratedapproach to the optimum design of actively [AIAA PAPER 69.24641 p 677 A89-46851 controlled composite wings p 670 N89-25194 enhancement p 689 N89-25189 T-4 inletlengine compatibility flight test results Control surface spanwise placement in active flutter Applications of fuzzy sets to rule-based expert system [AIAA PAPER 89.24661 p 665 A89746853 development p 712 N69-26606 suppression systems p 689 N89-25195 Role of dynamic simulation in lighter engine design and Nonlinear and adaptive control An approximation function for frequency constrained development [ NASA-CR-1800861 p 712 N89-26610 structural optimization p 705 N89-25196 [AIAA PAPER 69-24671 p 677 A89-46854 AIRCRAFT DESIGN Structural optimization of framed structures using Tupolev's new twin p 662 A89-43887 generalized optimality criteria p 706 N89-25197 Advanced propulsion systems for large subsonic Rafale - Dassault's new dawn p 662 A69-45030 Recent Advances in Multidisciplinary Analysis and transports . Aeronautical research in the European future Optimization. part 3 [AIAA PAPER 89.24771 p 677 A89-46861 p 638 A89-45037 [ NASA-CP-3031-PT-31 p 670 N89-25201 Ducted ultra-high bypass engine configuration The ACE/Rafale p 662 A69-45041 Hypersonic airbreathing vehicle.conceptual design definition Airbus - The new families p 662 A69-45043 (focus on aero-space plane) p 670 N89-25210 [AIAA PAPER 69-24761 p 678 A89-46662 The systems of the future Airbus A330 and A340 Optimizing conceptual aircraft designs for minimum life Design and testing of a common engine and nacelle aircraft p 662 A89-45044 cycle cost p 670 N69-25211 for the Fokker 100 and Gullstream GIV airplanes
Testing for agility ~ A progress report Aircraft design optimization with multidisciplinary [AIAA PAPER 89-24861 p 666 A89-46867 p 686 A89-45152 performance criteria p 671 N89-25212 Free-jet test capability for the aeropropulsion systems X-29A performance flight tests - Results and lessons An overview of the Douglas Aircraft Company test facility learned p 686 A89-45154 Aeroelastic Design Optimization Program (ADOP) [AIAA PAPER 89-25371 p 692 A89-46906 The ATF is on its way p 664 A89-45156 p 671 N69-25221 Preliminary development of an intelligent computer F-15 STOLlManeuvering Technology Demonstrator - Recent developments in large-scale structural assistant for engine monitoring Initial flight test results p 687 A89-45157 optimization p 706 N89-25231 [AIAA PAPER 89-25391 p 674 A89-46910 Time-correlated gust loads using Matched-Filter Theory A supersonic cruise fighter design Turbine engine structural efficiency determination and Random-Process Theory: A new way of looking at p 664 A89-45167 [AIAA PAPER 89-2571I p 679 A89-46932 Flow characteristics in an S-shaped rectangular-round things Configuration studies for a regional airliner using diffuser at high incidence p 646 A89-46260 [NASA-TM-101573] p 671 N89-25232 open-rotor ultra-high-bypass-ratioengines Easy method of matching fighter engine to airframe for The conceptual design of a Mach 2 Oblique Flying Wing [AIM PAPER 89-25801 p 666 A89-46937 use in aircraft engine design courses supersonic transport [AIAA PAPER 69-22601 p 665 A89-46705 [ NASA-CR-1775291 p 671 N89-25233 UHB demonstrator flight test program - Phase 2 -._ Large-scale wind tunnel tests 01 an ejector-lift STOVL An economic model for evaluating high-speed aircraft ultra-high bypass engine technology aircraft model designs [AIM PAPER 89.25821 p 679 A89-46939 [AIAA PAPER 89-29051 p666 A89-47165 [NASA-CR-177530] p 671 N89-25235 Evaluation of a fault tolerant digital engine controller Damping of wing tip vortex systems by the modification An analytical sensitivity method for use in integrated [AIAA PAPER 69-25891 p 680 A89-46944 of the wing tips p 654 N89-25138 aeroservoelastic aircraft design Model predictions for improved recoverability 01 a Recent Advances in Multidisciplinary Analysis and [NASA-TM-I01 5831 p 690 N89-25239 multistage axial-flow cornpressor Optimization. part 1 Longitudinal nonlinear aerodynamic model form for [AIAA PAPER 89-26871 p 650 A89-47017 [NASA-CP-3031-PT-I] p666 N89-25146 USB-STOL aircraft Dynamic turbine blade temperature measurements Applications 01 integrated designlanalysis systems in [NAL-TR-9951 p 672 N69-25990 [AIAA PAPER 89-26891 p 680 A8947019 aerospace structural design p 666 N89-25147 Development and application of a computer-based Advanced material applications for turbine airfoils Overview of Dynamics Integration Research (DIR) system lor conceptual aircraft design [AIM PAPER 89-26931 p 660 A89-47023 program at Langley Research Center [ ETN-89-946861 p 673 N89-26001 A propulsion development strategy lor the National p 667 N89-25150 Aeronautical applications of high-temperature Aero-Space Plane Structural optimization of rotor blades with straight and superconductors [AIAA PAPER 69-27511 D 681 A89-47061 swept tips subject to aeroelastic constraints [NASA-TM-102311] p686 N89-2MX)B Advanced cooling wncepts for multi-function nozzle p 667 N89-25152 AIRCRAFT DETECTION durability Optimization of rotor blades for combined structural. [AIM PAPER 892814) pE82 A89-47100 Low-temperature performance of a power-pack lor a performance, and aeroelastic characteristics Design 01 a gear drive for counter-rotating fan rotors %watt ELT p 709 A89-44016 p 667 N69-25153 [AIAA PAPER 89-28201 p 682 A89-47106 Transonic airfoil design for helicopter rotor Stealth technology for reducing aircraft recognition A technique fw the measurement 01 blade tip clearance p673 A80-44645 applications p 667 N89-25154 in a gas turbine Efficient sensitivity analysis and optimization of a Experimental localized radar cross sections of aircraft [AIAA PAPER 89.29161 p 683 A89-47170 helicopter rotor p 668 N89-25155 p 673 A8945105 Reduction of 1-P aerodynamic loads on tractor aircraft Multi-objectielloading optimization lor rotating The analysis and measurements of radar cross section engim installations composite flexbeams p 668 N69-25157 (RCS) of some wing structure models [AlAA PAPER 89-29241 p 651 A89-47177 Development of a microcomputer based integrated p 674 A8946296 Distortion test capabilities lor future fighter aircraft design system for high altitude long endurance aircraft AIRCRAFT ENGINES engines p664 N89-25159 Apparent strain characteristics of strain gauges under [AIM PAPER 89-29561 p 684 A89-47198 TRUSS An intelligent design system for aircraft wings high temperature environment p 697 A8943844 Aircraft engine outer duct mounting device p 711 N89-25162 Powered lift aircraft take off climb performance with one [AD-W13988] p 672 N89-25991 The designer of the 90's: A live demonstration engine inoperative p 663 A89-45127 Two axial compressor designs lor a stage matching p 705 N89-25164 F-l4/F110 high angle 01 attack flight tests investigation Structural tailoring 01 counter rotation proplans p 686 A89451 53 [AD-A206951I p 685 N89-26006 p 665 N89-25165 Application of the boundary element method to unsteady AIRCRAFT EQUIPMENT Composite sizing and ply orientation for stiffness heat transfer problems p 700 A8945552 Nondestructive qualification of UH-1 replacement parts: requirements using a large finite element structural Completin enhancement An experimental research mixture pressure in model p 705 N89-25166 on loss [AD-A206674] p 672 N89-25995 Aerolastic tailoring and integrated wing design combustor p 675 A8945556 AIRCRAFT FUELS p 668 N89-25167 Cold flow measurements for a double swirler Fuel containment system concept to reduce spillage Integrated aerodynamic-structural design of a combustor p 675 A69-45557 [DOTlFAA/CT-TN89122] p 672 N69-25994 forward-swept transport wing p669 N89-25168 Experimental research on swirling combustion Comparisons between unleaded automobile gasoline Effects of nonlinear aerodynamics and static efficiency p 675 A89-45558 and aviation aasoline on valve seat recession in liaht aeroelasticity on mission performance calculations for a A dynamic digital model for the turbojet with aircraft engines fighter aircraft p 669 N89-25170 pulse-monitoredfueler p 675 A89-45559 [NIPER-4091 p 697 N89-26110
A-3 AIRCRAFT GUIDANCE SUBJECT INDEX
AIRCRAFT GUIDANCE Integrated controls pay-off -.-for flightlpropulsion Inverse method for the determination of transonic blade Controllerevaluations of the descent advisor automation aircraft systems profiles of turbomachineries p 643 A89-45404 ad [AIAA PAPER 89-2704) p 688 A89-47031 Simulation of unsteady flow past sharp shoulders on [ NASA-TM-1021971 p 659 N89-25981 Fighter aircraft affordability. survwability, and semi-infinite bodies p 644 A89-45415 AIRCRAFT INDUSTRY effectiveness through multi-function nozzles Analysis of low Reynolds number separation bubbles Airbus - The new families p 662 A89-45043 [AIM PAPER 89-28151 p 666 A89-47101 using semiempirical methods p 652 A89-47351 An economic model for evaluating high-speed aircraft Compressor exit temperature analysis Airfoil self-noise and prediction designs [AlAA PAPER 89.29471 p 684 A89-47191 [NASA-RP-l218] p 713 N89-25673 [ NASA-CR-1775301 p 671 N89-25235 An initial assessment of the imDact of bOundaN laver AIRFOILS Federalincentives for industrial modernization: Historical .. control on SST Multi-stage compressor airfoil aerodynamics. I . Airfoil rmew and future opportunibes [AERO-REPT-8802] p 656 N89-25969 potential flow analysis p 639 A89-44112 [ NASA-TM-101785] p 714 N89-25764 Computation of viscous unsteady compressible flow Feasibility of predicting performance degradation of AIRCRAFT LANDING about airfoils p 642 A89-45378 airfoils in heavy rain Navigation aids to aircraft all-weather landing Microstructure-propertyrelationships in advanced nickel [NASA-CR-181842] p 657 N89-25973 p 659 A89-43891 base superalloy airfoil castings p 696 A89-45929 In search of effective diversity - A six-language study Strategic bombers: E-1B cost and performance remain Design and analysis of airfoils in transonic viscous of faun-tolerant flight control software uncertain flow p 648 A89-46262 p 710 A89-44423 [AD-A206751] p 673 N89-25998 The computed results of airfoil near the freestream Mach Researchand applmlmn of a new kind of measurement AIRCRAFT PILOTS number one p 646 A89-46266 technology of takeoff and landing performance Expert systems' role broadens p 71 1 A89-45293 Unsteady transonic airfoil computation using implicit p 698 A89-45144 Automation in transport aircraft - Current and future Euler scheme on body-fixed grid p 652 A89-47358 Manual CAT llla with a HUD - Requirements and testing trends Numerical analysis of supersonic flow through oscillating --.FAA instrument approach category [SAE PAPER 8814681 p 657 A89-47334 cascade Sections by using a deforming grid p687 A89-45164 AIRCRAFT POWER SUPPLIES [ NASA-TM-102053] p 653 N89-25119 Airline operations and the contaminated runway The solution of 3-D temperature distribution in a cycling Two-dimensional elliptic grid generation for airfoils and [SAE PAPER 8814601 p 658 A89-47339 oil cooled aircraft ac generator by network topology cascades Reduction of aircraft noise in civil air transport by method p 701 A89-46282 [ DFVLR-FB-88-52] p 653 N89-25125 operrization of flight tracks and takeoff and approach AIRCRAFT PRODUCTION Design Optimization of axisymmetric bodies in procedures The EEC supports air transport research nonuniform transonic flow p 670 N89-25206 [ ILR-MITT-2001 p 713 N89-25676 p 638 A89-46078 Airfoil self-noiseand prediction Integratedflightlpropulsion control system design based AIRCRAFT RELIABILITY [ NASA-RP-12181 p 713 N89-25673 on a centralized approach Damage tolerance analysis and structural integrity in Air A numerical solution of transonic flow using [ NASA-TM-1021371 pa90 N89-26009 Force aircraft p 661 A89-43884 discontinuous shock wave relationship AIRCRAFT MAINTENANCE C-130 Hercules outer mng residual strength tests [NAL-TR-997] p 655 N89-25950 Aging aircraft p 657 A89-45296 p 663 A89-45132 Steady-state and transitional aerodynamic Hornet maintenance p 638 A89-46496 Aircraft development lest and evaluation - An Office of characteristics of a wing in simulated heavy rain Aircraft sustainability model version 1.5: Users manual the Secretary of Defense perspecbve [NASA-TP-2932] p 655 N89-25951 [AD-A2070151 p 638 N89-25949 p 638 A89-45143 Flow characteristics about a trailing edge Nondestructivequalification of UH-1 replacement parts: Aging aircraft p 657 A89-45296 [UTIAS-TN-270] p 655 N89-25952 Completion enhancement Hornet maintenance p638 A8946496 Influence of thickness and camber on the aeroelastic [AD-A206674] p 672 N89-25995 AIRCRAFT SAFETY stability of supersonic throughflow fans: An engineering AIRCRAFT MANEUVERS In the dnnk --- ditch landing capability of aircraft approach Asymptotically decoupled discontinuous control of p 691 A89-43890 [ NASA-TM-1019491 p 656 N89-25957 systems and nonlinear aircraft maneuver C-130 Hercules outer wing residual strength tests An experimental investigation of high liftlhigh rate p 686 A89-45064 p 663 A89-45132 aerodynamics of an unsteady airfoil
Testing for agility ~ A progress report Aging aircraft p 657 A89-45296 [ AD-A2069641 p 656 N89-25964 p 686 A89-45152 AIRCRAFT STABILITY Feasibility of predicting performance degradation of F-I5 STOLlManeuvenng Technology Demonstrator - A new flight flutler excitation system airfoils in heavy rain Initial flight test results p 687 A8945157 p 663 A89-45140 [ NASA-CR-1818421 p 657 N89-25973 The influence of altitude and speed variations on the The measurement of linear and angular displacements A preliminary investigation into Euler methods for aeroplane's load components in longitudinal nonlinear in prototype aircraft - Instrumentation, calibration and application to multi-e1ement aerofoilsfor high lift manoeuvres p 688 A89-45179 operational accuracy p 698 A89-45142 [ AERO-REPT-87101 p 708 N89-26196 AIRCRAFT MODELS Aeroservoelasbc tailonng for lateral control A IR F R A Y ES Meeting the challenges with the Douglas Aircraft enhancement p 689 N89-25189 Opbcal research needed to support the testing of Company Aeroelastic Design Optimization Program Integrated structurelcontrol law design by multilevel hypersonic vehicle structures p 697 A89-43840 (Amp) p 671 N89-25222 optimization Full scale fatigue crack growth test of advanced jet AIRCRAFT NOISE [ NASA-TM-101 623 ] p 712 N89-26623 trainer AT-3 p 664 A89-45207 Noise considerations for tiltrotor AIRCRAFT STRUCTURES Probabilistic damage tolerance methods for metallic [AIAA PAPER 89-23591 p 665 A89-46773 Damage tolerance analysis and structural integrity in Air aerospace structures p 672 N89-25237 Noise issues - An FAA perspective on transport noise Force aircraft p 661 A89-43884 Plan, formulate,discuss and correlate a NASTRAN finite [AIAA PAPER 89-23621 p 710 A89-46775 Technology of structures maintains high standards element vibrations model of the Boeing Model 360 Structural loading and noise disturbance of helicopters p 637 A89-44642 helicopter airframe p 713 N89-25140 Probabilistic analysis of aircraft structure [NASA-CR-l81787] p 707 N89-25480 Reduction of aircraft noise in civil air transport by p 665 A89-46470 AIRLINE OPERATIONS optimization of flight tracks and takeoff and approach Aerolastic tailoring and integrated wing design Airline operations and the conlaminated runway procedures p 668 N89-25167 [SAE PAPER 8814601 p 658 A89-47339 [ ILR-MITT-2001 p 713 N89-25676 Recent developments in largescale structural AIRPORT BEACONS A new class of random processes mth application to optimization p 706 N89-25231 Heliport identification beacon helicopter noise Time-correlatedgust loads using Matched-FilterTheory [DCTlFAA/CT-TN89/31] p 661 N89-25984 [ NASA-CR-1850371 p 713 N89-26679 and Random-Process Theory: A new way of looking at Mode S performance test plan AIRCRAFT PARTS things [ DOTlFAAlCT-TN89/24] p 707 N89-26127 lsoparametnc shear spring element applied to crack [NASA-TM-101573] p 671 N89-25232 AIRPORT SURFACE DETECTION EQUIPMENT patching and instability p 699 A89-45208 Probabilistic damage tolerance methods for metallic Prototype of a slant visual range measuring device AIRCRAFT PERFORMANCE aerospace structures p 672 N89-25237 [ DFVLR-FB-88-42] p 713 N89-25697 Dornier's role in the 'European Fighter Aircraft' EFA Materials and structures for 2Mx) and beyond: An Evaluationof a projection algorithm for the stereographic program p 637 A89-44643 atlempted forecast representation of aircraft in an air traffic control system [DFVLR-MITT-8902] p 706 N89-25359 Society of Flight Test Engineers, Annual Symposium, [DOTIFAAlCT-TN89/20] p 661 N89-25985 19th. Arlington, TX, Aug. 14-18. 1988. Proceedings Integrated structurelcontrol law design by multilevel AIRPORTS p A89-45126 opbmization 662 Air traffic control No easy solutions in a complex [NASA-TM-101623) p 712 N89-26623 - Powered lift aircraft take off climb performance with one terminal environment engine inoperative p A89-45127 AIRCRAFT SURVIVABILITY 663 [SAE PAPER 8814691 p 661 A89-47335 Numerical modelling of flight dynamics and flight test Fighter aircraft affordability, survivability. and effectiveness through multi-function nozzles FAA statistical handbook of aviation: Calendar year data identification of a jet trainer airplane 1987 p 663 A89-45139 [AIAA PAPER 89-28151 p666 A89-47101 AIRFOIL FENCES [ AD-A2009171 p 838 N89-25113 Research and application of a new kind of measurement F-18 Hornet LEX Fence flight test results Design criteria for aggregate-surfaced roads and technology of lake-off and landing performance . p 687 A89-45155 airfields p 698 A89-45144 AIRFOIL OSCILLATIONS [AD-A2070591 p 694 N89-26019 X-29A performance flight tests - Results and lessons A natural low-frequency oscillation of the flow over an Evaluation of nondestructive test equipment for airfield learned p 686 A89-45154 airfoil near stalling conditions p645 A89-45431 pavements. Phase 1: Calibrationlest results and field data F-18 Hornet - LEX Fence flight test results Viscous aerodynamic analysis of an oscillating flat-plate collection p 687 A89-45155 airfoil p 652 A89-47356 [AD-A207159] p 694 N89-26020 FlA-18A digital flight control system degraded modes AIRFOIL PROFILES ALGORITHMS flight evaluation p 687 A89-45158 A flow-field solver using overlying and embedded Evaluationof a projection algorithm for the stereographic FAA handling qualities assessment - Methodology in meshes together with a novel compact Euler algorithm representation of aircraft in an air traffic control system transition p 687 A89-45159 p 641 A89-45359 [ DOT/FAA/CT-TN89/20] p 661 N89-25985
A-4 SUBJECT INDEX BORON
ALL-WEATHER LANDING SYSTEMS ATMOSPHERIC CHEMISTRY 6 Navigation aids to aircraft all-weather landing Preventing depletion of stratospheric ozone: p 659 A89-43891 Implications on future aircraft emissions 51AIRCRAFT ALTERNATING DIRECTION IMPLICIT METHODS [DE89-009964] p 710 N89-25530 6-16 high AOA testing p 687 A89-45162 Solution of the incompressible Navier-Stokesequations ATOMIZING 6-1B development testing p 687 A89-45165 A model for airblast atomization using artificial compressibility methods Strategic bombers: 6-1 cost and performance remain [AIAA PAPER 89-2321 ] p 702 A89-46748 6 p 641 A89-45366 uncertain Multigrid calculation of three-dimensional AlTACK AIRCRAFT [AD42067511 p 673 N89-25998 The ACE/Rafale p 662 A89-45041 turbomachinery flows BACKWARD FACING STEPS [ NASA-CR-1853321 p 708 N89-26172 Free-jet test capability for the aeropropulsion systems Evaluation of Darallel injector confiaurations for ALTITUDE TESTS test facility supersonic combustion Distortion test capabilities for future fighter aircraft [AIAA PAPER 89.25371 p 692 A89-46908 [AIAA PAPER 89-25251 p 678 A89-46898 engines AUDITORY STIMULI BALL BEARINGS [AIAA PAPER 89-29561 p 684 A89-47198 An exploratory study of the use of movement-correlated Advantaaes of ceramic. solid lubricated bearinas for ALUMINUM ALLOYS cues in an auditory head-up display p 674 A89-45329 small gas turbine engines A study of AI-Li alloys using small angle neutron AUSTENITIC STAINLESS STEELS [AIM PAPER 89-24721 p 703 A89-46858 scattering p 695 A89-44577 Fiber metal acoustic material for gas turbine exhaust BALLOON FLIGHT Hot ductility response of AI-Mg and AI-Mg-Li alloys environments p 695 A89-44400 Long duration balloon technology survey, phase 1 p 695 A89-45330 AUTOCORRELATION [AD-A206975] p 656 N89-25965 Aluminum-lithium alloys for fighter aircraft applications A new class of random processes with application to BEAMS (SUPPORTS) p 696 A89-45937 helicopter noise Multiobiectielloading optimization for rotating ANALOG COMPUTERS [NASA-CR-1850371 p 713 N89-26679 composite flexbeams p 668 N89-25157 Local analytical methods for digital simulation of AUTOMATED EN ROUTE ATC BEARING ALLOYS dynamical control system p 71 1 A89-46244 A knowledge-based en route monitor for air traffic Selection of rolling-element bearing steels for long-life ANGLE OF ATTACK control p 660 A89-45065 applications p 704 A89-47250 F-l4/F110 high angle of attack flight tests AUTOMATIC CONTROL BEARINGS p 686 A89-45153 Controller evaluationof Initial Data Link air traffic control Study of nonlinear Duffing characteristicsof flexible rotor X-29A performance flight tests . Results and lessons services. Volume 2 Mini Study 2 with SFDB ... squeeze film damper bearings learned p 686 A69-45154 [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 p 700 A89-45568 F-18 Hornet - LEX Fence flight test results AUTOMATIC FLIGHT CONTROL BEDS (PROCESS ENGINEERING) p 687 A89-45155 Simulation methodology for helicopter automatic flight On the stress problem of the pebble bed heat exchanger 6-16 high AOA testing p 687 A89-45162 control systems p 686 A89-45048 in a hypersonic wind tunnel Wind-tunnel investigations of wings with serrated sharp Digital flight and inlet control in the SR-71 [ NAL-TM-ST-87051 p 693 N89-25240 trailing edges p 641 A89-45262 ' p 664 A89-45160 BENDING FATIGUE Bow shock matching with viscous effects on hypersonic A look at the Model 360 development Three dimensional finite element stress predictions of forebodies p 664 A89-45163 spur gears compared to gear fatigue rig measurements [AIAA PAPER 89-26781 p 649 A89-47008 AUTOMATIC LANDING CONTROL [AIAA PAPER 89-29181 p 704 A89-47172 Low-speed wind tunnel performance of high-speed Navigation aids to aircraft all-weather landing BERYLLIUM ALLOYS counterrotation propellers at angle-of-attack p 659 A89-43891 A review of beryllides for very high temperature [NASA-TM-102292] p 653 N89-25121 AUTOMATIC TEST EQUIPMENT service p 696 A89-45948 ANTARCTIC REGIONS ADINTS - Moving toward standardization of automatic BERYLLIUM COMPOUNDS Omega navigation in the shadow of Antarctica test equipment p 701 A89-46462 Mechanical properties of high-temperature beryllium p 660 A89-43893 AUTOMATIC WEATHER STATIONS intermetallic compounds p 697 A89-47213 ANTIFRICTION BEARINGS Selected wind shear events observed during the 1987 BIBLIOGRAPHIES Selection of rollingelement bearing steels for long-life evaluation of enhancements to the FAA (Federal Aviation FAA rotorcraft research. engineering and development applications p 704 A89-47250 Administration) low level wind shear alert system at bibliography, 1962-1988: Supplement Stapleton International Airport APPLICATIONS PROGRAMS (COMPUTERS) [ AD-A207 1621 p 673 N89-26000 [AD-A206711] p 710 N89-26323 Plan, formulate. discuss and correlate a NASTRAN finite BLADE TIPS element vibrations model of the Boeing Model 360 AUTOMATION Design of vane tips improving axial compressor helicopter airframe Automation in transport aircraft . Current and future perfor ma n c e p 640 A89-44640 [NASA-CR-1817871 p 707 N89-25480 trends The investigation of jet engine starting [SAE PAPER 8814681 p 657 A89-47334 HOMAR: A computer code for generating homotopic p 676 A89-46025 grids using algebraic relations: User's manual AUTOMOBILE FUELS A technique for the measurement of blade tip clearance [ NASA-CR-42431 p 708 N89-26176 Comparisons between unleaded automobile gasoline in a gas turbine and aviation gasoline on valve seat recession in light [AIAA PAPER 89-29161 p 683 A8Q-47170 APPROACH CONTROL aircraft engines BLADE-VORTEX INTERACTION Microwave landina system instrumentation A Dilol's -. - [ NIPER-4091 p 697 N89-26110 Airfoil self-noise and prediction viewpoint [NASA-RP-1218] p 713 N89-25673 [SAE PAPER 8814611 p 661 A89-47340 AVIONICS Development and verificationof software for flight safety BLOWDOWN WIND TUNNELS Controller evaluationsof the descent advisor automation critical strapdown systems p 659 A89-43827 Experimental study of spreading rate enhancement of aid high Mach number turbulent shear layers [ NASA-TM-1021971 p 659 N89-25981 From avionics technology to architectural concepts p 637 A89-45035 [AlAA PAPER 89.24581 p 648 A89-46845 APPROXIMATION The ATF is on its way p 664 A89-45156 BLUNT BODIES An approximation function for frequency constrained Interaction of an oblique shock wave with supersonic X-15 pilot-in-the-loop and redundant/emergency structural optimization p 705 N89-25196 turbulent blunt body flows p 644 A89-45405 The role of optimization in the next generation of systems evaluation p 664 A89-45168 Pressure fluctuations on an oscillating trailing edge computer-baseddesign tools p 712 N89-25220 Radio Technical Commission for Aeronautics, Annual p 645 A89-45458 Relaxation oscillations in aircraft cruise-dash Assembly Meeting and Technical Symposium, BODIES OF REVOLUTION optimization Washington, Dc. Nov. 28-30.1988. Proceedings Radar cross section of arbitrarily shaped bodies of [AD-A206722] p 672 N89-25996 p 660 A89-45875 revolution p 674 A89-45111 ARCHITECTURE (COMPUTERS) ADINTS . Moving toward standardization of automatic BODY-WING CONFIGURATIONS From avionics technology to architectural concepts test equipment p 701 A89-46462 Development of a highly efficient and accurate 3D Euler p 637 A89-45035 Mechanical durability prediction methods flow solver p 642 A89-45370 Arranging computer architectures to create p 701 A89-46468 HOMAR: A computer code for generating homotopic higher-performancecontrollers p 71 1 A89-46147 A corollary to - Duane's postulate on reliability growth grids using algebraic relations: User's manual ARRIVALS p 701 A89-46474 [ NASA-CR-42431 p 708 N89-26176 Controller evaluationsof the descent advisor automation A performance measure for a VHSIC avionic system - BOEING AIRCRAFT aid Mission dependent availability p 701 A89-46478 A look at the Model 360 development [ NASA-TM-1021971 p 659 N89-25981 R8M through Avionics/Electronics Integrity Program p 664 A89-45163 ARTIFICIAL INTELLIGENCE p 701 A89-46480 BOEING 727 AIRCRAFT Establishing artificial intelligence technology in a flight Experimental localized radar cross sections of aircraft test environment p 663 A89-45135 AXIAL FLOW p 673 A89-45105 Prediction of the stability limit of multistage axial Recent Advances in Multidisciplinary Analysis and BOLTED JOINTS Optimization, part 2 compressors p 640 A89-44637 Fatigue failure initiation analysis of wing/fuselage bolt [ NASA-CP-3031 -PT-2 I p 669 N89-25173 Model predictions of fan response to inlet temperature assembly p 699 A89-45210 ASPHALT transients and spatial temperature distortion BOMBS Evaluation of nondestructive test equipment for airfield [AIM PAPER 89-26861 p 650 A89-47016 Cost-effective approach to flight testing the 'Casmu pavements. Phase 1: Calibration test results and field data AXIAL FLOW TURBINES Skyshark' a stand-off weapon dispenser collection Three dimensional flow and temperature profile p 663 A89-45128 [AD-A207159] p 694 N89-26020 attenuation in an axial flow turbine BORON ASYMPTOTIC METHODS [AD-A206736] p 685 N89-26005 The influence of swirl and fuel composition of Asymptotically decoupled discontinuous control of AXISYMMETRIC BODIES boron-containingfuels on combustion in a solid fuel ramjet systems and nonlinear aircraft maneuver Design optimization of axisymmetric bodies in combustion chamber D 686 A89-45064 nonuniform transonic flow p 670 N89-25206 [AIAA PAPER 89-28851 p 683 A89-47150
A-5 BORON NITRIDES SUBJECT INDEX
Effects of bypass air on the combustion of boron CAMBER CHANNEL FLOW particles in a solid fuel ramjet Influence of thickness and camber on the aeroelastic Modeling of turbulence tor compression corner flows [AIAA PAPER 89-28861 p 683 A89-47151 stability of supersonic throughflow fans: An engineering and internal flows BORON NITRIDES approach [AIM PAPER 89-23441 p 647 A89-46763 Combustion behavior of boron-based BAMOINMMO [NASA-TM-101949] p 656 N89-25957 CHEMICAL COMPOSITION fuel-rich solid propellants CAMOUFLAGE Development and application of a surrogate distillate [AlAA PAPER 89-28841 p 696 A89-47149 Stealth technology for reducing aircraft recognition fuel p 695 A89-44103 BOUNDARVELEMENTMETHOD p 673 A89-44645 The inf!uence of swirl and fuel composition of Applicabon of the boundary element method to unsteady CANTILEVER BEAMS boron-containingfuels on combustion in a solid fuel ramjet heat transfer problems p 700 A89-45552 Mechanical durability prediction methods combustion chamber Treatment of body forces in boundary element design p 701 A89-46468 [AIAA PAPER 89.28851 p 683 A89-47150 sensitivrty analysis p 705 N89-25187 CARBONCARBON COMPOSITES CHEMICAL PROPERTIES BOUNDARYLAYERCONTROL Embedded temperature measurements in a Effects of fuel chemical properties on exhaust smoke Survey and assessment of validation data base for carbon-carbon wing leading edge hot structure from gas turbine combustor p 695 A89-45554 shockwave boundary layer interactions in supersonic p 697 A89-43843 CIRCUIT RELIABILITY inlets CASCADE FLOW A performance measure for a VHSlC avionic system - [AIM PAPER 89-29391 p 651 A89-47183 Transonic cascade flow solved by the combined Mission dependent availability p 701 A89-46478 An initial assessment of the impact of boundary layer shock-capturing and shock-fittingmethod CIRCULAR CYLINDERS control on SST p 639 A89-44114 Review of FD-TD numericalmodeling of electromagnetic [AERO-REPT-8802] p 656 N89-25969 Multigrid calculations for cascades wave scattering and radar cross section BOUNDARY LAYER EOUATIONS p 643 A89-45391 p 673 A89-45107 Analysis of low Reynolds number separation bubbles Effects of axial velocity density ratio on cascade Behavior of vortex street in the wake behind a circular using semiempincal methods p 652 A89-47351 performances p 645 A89-45565 cylinder under controlled excitation p 646 A89-46694 BOUNDARY LAYER FLOW Expenmental investigation on characteristics of single A preliminary investigation into Euler methods for Computer scmulation of some typss of ROWS arising at and tandem Made cascades with double-circular arc applicabon to multi-element aerofoils for high Itft interactions between a supersonic flow and a boundary profile p 676 A89-45567 [AERO-REPT-8710] p 708 N89-26196 layer p 642 A89-45381 A validation of a Navier-Stokes2D solver for transonic CIRCULATION CONTROL AIRFOILS Investigation on unsteady flow field and endwall turbine cascade flows Tipjet VTOL UAV (Vertical Takeoff and boundary layer in axial flow compressor with hot-wire [AIAA PAPER 89-2451I p 647 A89-46839 LandingIUnmanned Aerial Vehicle) summary. Volume 1: anemometer p 645 A89-45560 Two-dimensional computations of multi-stage A 1200 pound tipjet VTOL unmanned aerial vehicle. Part Survey and assessment of validation data base for compressoc flows using a zonal approach 1:Co nceptual design study of a 1200-pound vehicle shockwave boundary layer interactions in supersonic [AIM PAPER 89.24521 p 647 A89-46840 [ADA2067381 p 672 N89-25997 inlets Application of simple wave theory to the radiative CIVIL AVIATION [AIAA PAPER 89-29391 p 651 A89-47183 boundary conditions required for an internal flow Euler Civil satellite navigation and location systems BOUNDARY LAVER SEPARATION solver p 694 A89-43892 Analysis of low Reynolds number separation bubbles [AIAA PAPER 89-25771 p 648 A89-46935 Civil supersonics - Propulsion is the key using semiempincal methods p 652 A89-47351 Steady-state and time-dependent aerodynamics in an p 675 A89-45031 Airfoil self-noise and prediction annular turbine cascade operating at high subsonic Mach FAA handling qualities assessment - Methodology in [ NASA-RP-12181 p 713 N89-25673 numbers transition p 687 A89-45159 BOUNDARY LAVER TRANSITION [AIAA PAPER 89-29411 p 651 A89-47185 Supersonic jet noise and the high speed civil transport Unsteady transition lxation p 652 A89-47376 Numericalanalysis of supersonic flow through oscillating [AIAA PAPER 89.23581 p 712 A89-46772 BOUNDARVUVERS cascade sections by using a deforming grid The challenge of reducing supersonic civil transport Airfoil self-noise and prediction [NASA-TM-102053] p 653 N89-25119 propulsion noise [ NASA-RP-12181 p 713 N89-25673 Twodimensional elliptic gnd generation for airfoils and [AIAA PAPER 89.23631 p 677 A89-46776 BOUNDARVVALUEPROBLEMS cascades FAA statistical handbook of aviation: Calendar year Crack shape identification as an inverse boundary value [DFVLR-FB-88-52] p 653 N89-25125 1987 problem p 698 A89-44663 Influence of thickness and camber on the aeroelastic [AD-A2009171 p 638 N89-25113 Differencemethods for initial-boundary-valueproblems stability of supersonic throughflow fans: An engineering UK airmisses involving commercial air transport and flow around bodies (Revised edition) --- Book approach [CAA-3188] p 658 N89-25143 Report to Congress: Technical feasibility of joint use p 646 A89-46198 [ NASA-TM-1019491 p 656 N89-25957 Mechanisms of Endwall leakage flows and the at Scott AFB, Selfridge AGB and El Tor0 MCAS BOW WAVES associated losses in a linear turbine rotor cascade with [ AD-A1 94597 1 p 693 N89-25241 Compressibility and shock wave interaction effects on blade tipclearance FAA (Federal Aviation Administration)aviation forecasts: free shear layers [ NAL-TR-985TI p 708 N89-26168 Fiscal years 1989-2000 [AlAA PAPER 89-24601 p 648 A89-46847 CAST ALLOYS [AD-A206716] p 638 N89-25948 Bow shock matching with viscous effects on hypersonic Microstructure-propertyrelationships in advanced nickel General aviation accidents involving visual flight rules forebodies base superalloy airfoil castings p 696 A89-45929 flight into instrument meteorological conditions [AIAA PAPER 89-26781 p 649 A89-47008 CAUCHVPROBLEM [PB89-917001J p 658 N89-25974 BRAVTONCVCLE Generalization01 the Roe Scheme for computing flows Heliport identiication beacon Brayton cycle engines wlth reciprocating work of mixed gases with variable concentrations IDOT/FAA/CT-TN89/31] p 661 N89-25984 components p 639 A89-44322 CLEAR AIR TURBULENCE [AIAA PAPER 89-29331 p 704 A89-47181 CEMENTS Analysis of severe atmosphericdisturbances from airline BUBBLES Evaluation of nondestructive test equipment for airfield flight records Analysis of low Reynolds number separation bubbles pavements. Phase 1: Calibrationtest results and field data [ NASA-TM-1021861 p 658 N89-25977 using semiempirical methods p 652 A89-47351 collection CLEARANCES BYPASS RATIO [ ADA207159 J p 694 N89-26020 Improved compressor performance using recessed Advanced propulsion systems for large subsonic CENTRIFUGAL COMPRESSORS clearance (trenches) p 674 A89-44113 transports Prediction of turbomachinery performance - Application Controller evaluations of the descent advisor automalion [AIM PAPER 89-24771 p 677 A89-46861 to a centrifugal pump, a centrifugal compressor, and a aid Ducted ultra-high bypass engine configuration radial inflow turbine p 640 A89-44638 INASA-TM-1021971 p 659 N89-25981 definition L2F 8 LDV velocimetry measurement and analysis of CLOUD HEIGHT INDICATORS [AIAA PAPER 89-24781 p 678 A89-46862 the 3-D flow field in a centnfugal compressor Prototype of a slant visual range measuring device Technology readiness for advanced ducted engines [AIAA PAPER 89-25721 p 648 A89-46933 [ DFVLR-FB-88-42] p 713 N89-25697 [AIAA PAPER 89-24791 p 678 A89-46863 CENTRlFUGAL PUMPS COAXIAL FLOW Prediction of turbomachinery performance Application Configuration studies for a regional airliner using - Combustion enhancement in supersonic coaxial flows to a centnfugal pump, a centnfugal compressor, and a open-rotor ultra-high-bypass-ratioengines [AIM PAPER 89-27881 p 681 A89-47084 [AIAA PAPER 89-25801 p 666 A89-46937 radial inflow turbine p 640 A89-44638 COCKPIT SIMULATORS Light weight gas turbine engine fuel pumping BYPASSES An exploratory study of the use of movement-correlated technology cues in an auditory head-up display p 674 A89-45329 Effects 01 bypass air on the combustion of boron [AIM PAPER 89-25871 p 703 A89-46943 COCKPITS particles in a solid fuel ramjet CERAMIC MATRIX COMPOSITES [AIAA PAPER 89-2886) p 683 A89-47151 Expert systems' role broadens p 71 1 A89-45293 Time dependent probabilistic failure of coated components COLD FLOW TESTS [AIAA PAPER 89-29001 p 704 A89-47163 Cold flow measurements for a double swirler C CERAMICS combustor p 675 A89-45557 Ceramic bearings for use in gas turbine engines A static investigation 01 several STOVL exhaust system C-130 AIRCRAFT p 702 A89-46697 concepts C-130 Hercules outer wing residual strength tests Advantages of ceramic, solid lubricated bearings for [AIAA PAPER 89.29281 p 684 A89-47180 p 663 A89-45132 small gas turbine engines COLOR CALIBRATING [AIAA PAPER 89-24721 p 703 A89-46858 The Schlieren Observation System installedin the NAL Inertial guidance test facility using the earth Advanced material applications for turbine airfoils two-dimensional high-Reynolds number transonic wind environment p 700 A89-46218 [AIAA PAPER 89-26931 p 680 A89-47023 tunnel and attempts to improve it Evaluation of nondestructive test equipment for airfield CHANNEL CAPACITY [NAL-TR-9641 p 693 N89-26015 pavements. Phase 1: Calibrationtest results and field data Communications Interface Driver (CID) system user's COMBAT collection manual Testing for agility - A progress report [ADA2071 591 p 694 N89-26020 [DOTlFAA/CT-TN89/36] p 707 N89-26123 p 686 A89-45152 SUBJECT INDEX COMPUTATIONAL FLUID DYNAMICS
COMBUSTIBLE FLOW COMPLEX SYSTEMS Numerical study of the 3D separating flow about Efficient computational tool for ramjet combustor SPAREL - A model for reliability and sparing in the world obstacles with sharp corners p 641 A89-45363 research of redundancies p 702 A89-46493 Computetion of hypersonic vortex flows with an Euler [AIAA PAPER 88-00601 p 674 A89-44108 COMPONENT RELIABILITY model p 642 A89-45368 Review of passive shear-flow control research for R8M through AvionicslElectronicsIntegrity Program Low-storageimplicit upwind-FEM schemes for the Euler improved subsonic and supersonic combustion p 701 A89-46480 equations p 642 A89-45375 [AIAA PAPER 89-27861 p 703 A89-47083 Transmission overhaul and replacement predictions Computation of viscous unsteady compressible flow Mixing enhancement in a supersonic combustor using Weibull and renewal theory about airfoils p 642 A89-45378 [AIAA PAPER 89-27941 p 681 A89-47088 [AIAA PAPER 89-29191 p 704 A89-47173 COMPOSITE MATERIALS Computer simulation of some lypes of flows arising at COMBUSTION CHAMBERS interactions between a supersonic flow and a boundary Integrated aerodynamic-structural design of a Advanced turbofan engine combustion system design layer p 642 A89-45381 and test verification p 675 A89-44117 forward-swept transport wing p 669 N89-25168 COMPOSITE STRUCTURES Accurate simulation of vortical flows The instability and acoustic wave modes of supersonic The analysis and measurements of radar cross section p 643 A89-45384 mixing layers inside a rectangular channel (RCS) of some wing structure models Multigrid calculations for cascades p 699 A89-45453 p 674 A89-46298 p 643 A89-45391 Effects of fuel chemical properties on exhaust smoke Multi-objectivelloading optimization for rotating RNS solutions for three-dimensional steady from gas turbine combustor p 695 A89-45554 composite flexbeams p 668 N89-25157 incompressible flows p 643 A89-45393 An experimental research on mixture pressure loss in Optimum design of swept-forward high-aspect-ration Numerical study of unsteady viscous hypersonic blunt combustor p 675 A89-45556 graphite-epoxy wings p 669 N89-25172 body flows with an impinging shock p 643 A89-45394 Cold flow measurements for a double swirfer COMPRESSIBILITY EFFECTS lnvmmethod for the determination of transonic blade combustor p 675 A89-45557 Compressibility and shock wave interaction effects on profiles of turbomachineries p 643 A89-45404 Evaluation of parallel injector configurations for free shear layers Interaction of an oblique shock wave with supersonic supersonic combustion [AIM PAPER 89-24601 p 648 A89-46847 turbulent blunt body flows p 644 A89-45405 [AIAA PAPER 89-25251 p 678 A89-46898 COMPRESSIBLE FLOW Simulation of inviscid hypersonic real gas flows A numerical investigation of Scramjet combustors Multidimensionaladaptive Euler solver p 644 A89-45414 [AIAA PAPER 89-25611 p 679 A89-46926 p 641 A89-45360 Simulation of unsteady flow past sharp shoulders on Mixing enhancement in a supersonic combustor Solution of the incompressible Navier-Stokesequations semi-infinite bodies p 644 A89.45415 [AIAA PAPER 89-27941 p 681 A89-47088 using artificial compressibility methods Transonic analysis of arbitrary configurations using Improvingthe development process for main combustor p 641 A89-45366 locally refined grids p 644 A89-45419 exit temperature distribution An implicit time-marching method for solving the 3-D Navier-Stokes simulation of transonic flow about wings [AIAA PAPER 89-28041 p 681 A89-47094 compressible Navier-Stokes equations using a block structured approach p 644 A89.45422 ' A 3-D analysis of gas turbine combustors p 642 A89-45374 Inviscid and viscous flow simulations around the [AIAA PAPER 89-28881 p 683 A89-47153 Computation of viscous unsteady compressible flow Onera-M6 by NDschemes p 644 A89-45425 Combustion characteristics of gaseous flames in a gas about airfoils ' p642 A89-45378 Transonic flow solutions on general 3D regions using turbine combustor Modeling of turbulence for compression corner flows composite-block grids p 644 A89-45428 [AIM PAPER 89-28921 p 683 A89-47155 and internal flows A natural low-frequency oscillation of the flow over an Investigation of low NOx staged combustor concept in [AIAA PAPER 89-23441 p 647 A89-46763 airfoil near stalling conditions p 645 A89-45437 high-speed civil transport engines Computational analysis of turbomachinery flows using A Newionlupwindmethod and numerical study of shock [AIAA PAPER 89-29421 p 684 A89-47186 FLOFIVE wave/boundary layer interactions p 645 A89-45468 Evaluation of novel igniters in a turbulent bomb facility [AIAA PAPER 89-25591 p 648 A89-46924 The spatially non-uniform convergence of the numerical and a turbo-annular gas turbine combustor Quantitative characterization of a nonreacting. solutions of flows p 699 A89-45535 [AIAA PAPER 89-29441 p 684 A89-47188 supersonic combustor flowfield using unified, laser-induced Difference methods for initial-boundary-valueproblems Fuel properties effect on the performance of a small iodine fluorescence and flow around bodies (Revised edition) --- Book high temperature rise combustor [AIAA PAPER 89-25651 p 703 A89-46928 p 646 A89-46198 [ NASA-TM-1020961 p 685 N89-25238 Numericalanalysis of supersonic flow through oscillating An integrated design computational method for the wing COMBUSTION EFFICIENCY cascade sections by using a deforming grid optimization camber and twist at subsonic and supersonic Experimental research on swirling combustion [NASA-TM-102053] p 653 N89-25119 flow p 646 A89-46256 efficiency p 675 A89-45558 COMPRESSOR BLADES The computed results of airfoil near the freestream Mach Combustion enhancement in supersonic coaxial flows Computational and experimental study of stall number one p 646 A89-46266 [AIAA PAPER 89-27881 p 681 A89-47084 propagation in axial compressors Mach 5 inlet CFD and experimental results The influence of swirl and fuel composition of [AIAA PAPER 89-24541 p 647 A89-46842 [AIAA PAPER 89-23551 p 647 A89-46769 boron-containingfuels on combustion in a solid fuel ramjet COMPRESSOR EFFICIENCY Computational fluid dynamics using CATlA created combustion chamber Improved compressor performance using recessed geometry [AIAA PAPER 89-28851 p 683 A89-47150 clearance (trenches) p 674 A89-44113 [AIAA PAPER 89-23681 p 702 A89-46778 Effects of bypass air on the combustion of boron Design of vane tips improving axial compressor A validation of a Navier-Stokes 2D solver for transonic particles in a solid fuel ramjet performance p 640 A89-44640 turbine cascade flows [AIAA PAPER 89-28861 p 683 A89-47151 COMPRESSOR ROTORS [AIAA PAPER 89-24511 p 647 A89-46839 Investigation of low NOx staged combustor concept in Multi-stage compressor airfoil aerodynamics. I - Airfoil Two-dimensional computations of multi-stage high-speed civil transport engines potential flow analysis p 639 A89-44112 compressor flows using a zonal approach [AIAA PAPER 89-29421 p 684 A89-47186 COMPUTATIONAL FLUID DYNAMICS [AlAA PAPER 89-24521 p 647 A89-46840 COMBUSTION PHYSICS LOPAN . A low-order panel method for subsonic and Threedimensional multigrid Navier-Stokes Combustion behavior of boron-based BAMOINMMO supersonic flows p 639 A89-43724 computations for turbomachinery applications fuel-rich solid propellants Transonic cascade flow solved by the combined [AIAA PAPER 89-24531 p 702 A89-46841 [AIAA PAPER 89-28841 p 696 A89-47149 shock-capturingand shock-fitting method Computational analysis of turbomachineiy flows using COMBUSTION TEMPERATURE p 639 A89441 14 FLOFIVE Fuel properties effect on the performance of a small Hypersonic vehicle propulsion . A computational fluid [AIAA PAPER 89-25591 p 646 A89-46924 high temperature rise combustor dynamics application case study p 639 A89-44116 A numerical investigation of scramjet combustors [ NASA-TM-1020961 p 685 N89-25238 Generalizationof the Roe scheme for computing flows [AIAA PAPER 89-25611 p 679 A89-46926 COMBUSTION WIND TUNNELS of mixed gases with variable concentrations Quantitative characterization of a nonreacting. Initial supersonic combustion facility measurements p639 A894322 supersonic combustorflowfield using unified.laser-induced [AIAA PAPER 89-24621 p 692 A89-46849 Inviscid transonic flow over a wavy wall decaying iodine fluorescence COMMERCIAL AIRCRAFT downstream p639 A894390 [AIAA PAPER 89.25651 p 703 A89-46928 Jet or prop required for future regional transports? Recent developments in calculation methods for Application of simple wave theory to the radiative p 637 A89-44641 turbomachines p697 A8944635 boundary conditions required for an internal flow Euler Dassault. leader in European military and business Present state of the theory of secondary flows and solver aircratt p 637 A89-45033 experimental verifications p698 A894636 [AIAA PAPER 89.25771 p 648 A89-46935 Airbus - The new families p 662 A89-45043 Prediction of turbomachinery performance - Application Applicationof a multi-stage3-D Euler solver to the design Supersonic jet noise and the high speed civil transport to a centrifugal pump, a centrifugal compressor. and a of turbines for advanced propulsion systems [AIAA PAPER 89-23581 p 712 A89-46772 radial inflow turbine p640 A89-44838 [AIAA PAPER 89-25781 p 679 A89-46936 The challenge of reducing supersonic civil transport Theoretical and experimental study of turbine Compulational modeling of axisymmetric propeller-hull propulsion noise aerodynamics p 640 A89-44639 interaction in slender low drag bodies [AIAA PAPER 89-26741 p 649 A89-47004 [AlAA PAPER 89-23631 p 677 A89-46776 A new variational method for the generation of hm and Large scale advanced propeller blade pressure Ensuring surge-free engine operation on today's three-dimensional adapted grids in computational fluid distributions Prediction and data turbofan powered business jets dynamics - [AIAA PAPER 89-26961 p 650 A89-47026 [AIAA PAPER 89-24871 p 678 A89-46868 [ONERA. TP NO. 1989-311 p 641 A8945187 Supersonic nozzle mixer ejector Navier-Stokes simulations around a propfan using Studies of vortex flow aerodynamics using CFO flow [AIM PAPER 89.29251 p 683 A89-47178 higher-order upwind schemes visualizations p641 A8945260 UK airmisses involving commercial air transport [AIAA PAPER 89-26991 p 650 A89-47028 [CAA-3188] p 658 N89-25143 International Conference on Numerical Methods in Fluid Rarefied gas flow through two-dimensional nozzles COMMUNICATION NETWORKS Dynamics. 11th. Williamsburg. VA, June 27July 1. 1988. [AIAA PAPER 89-28931 p 650 A89-47156 The links in the chain - The lnmarsat system -_-lo permit Proceedings p 699 A89-45351 The applicationof 3D marchingscheme for the prediction mobile communications to and from any point on Earth Computational fluid dynamics - A personal view of supersonic free jets p 697 A89-43876 p 699 A89-45352 [AIAA PAPER 89.28971 p 651 A89-47160 Satellite low rate voice demonstration test plan CFD for hypersonic airbreathing aircraft Investigation of the flow structure around a rapidly [ AD-A2067101 p 707 N89-26133 D 641 A89-45355 pitching airfoil p 652 A89-47360
A-7 COMPUTATIONAL GEOMETRY SUBJECT INDEX
Numerical analysis of supersonic flow through oscillating TRUSS An intelligent design system for aircraft wings Computational structural mechanics for engine cascade sections by using a deforming grid p 71 1 N89-25162 structures [ NASA-TM-1020531 p 653 N89-25119 The designer of the 90's: A live demonstration [NASA-TM-102119] p 709 N89-26259 Twc-dimensional elliptic grid generation for airfoils and p 705 N69-25164 COMPUTER SYSTEMS PROGRAMS cascades Structural tailoring of counter rotation propfans HOMAR. A computer code for generating homotopic [ DFVLR-FB-88-52] p 653 N89-25125 p 685 N89-25165 grids using algebraic relations User's manual Recent Advances in Multidisciplinary Analysis and Composite sizing and ply orientation for stiffness [ NASA-CR-42431 p 708 N89-26176 Opbmization. part 1 requirements using a large finite element structural COMPUTER TECHNIQUES [ NASA-CP-3031-PT-1I p666 N89-25146 model p 705 N89-25166 Multilevel decomposition of complete vehicle Effects of nonlinear aerodynamics and static Aerolastic tailoring and integrated wing design configuration in a parallel computing environment aeroelasticity on mission performance calculations for a p668 N89-25167 p 670 N89-25205 fighter aircraft p 669 N89-25170 Integrated aerodynamic-structural design of a COMPUTER VISION A numerical solution of transonic flow using forward-swept transport wing p 669 N69-25168 Machine vision for control of gas tungsten arc welding discontinuous shock wave relationship Effects of nonlinear aerodynamics and static p 700 A89-45950 [NAL-TR-997] p 655 N89-25950 aeroelasticlty on mission performance calculations for a COMPUTERIZED SIMULATION Experimental and computationalflow-field results for an fighter aircraft p 669 N89-25170 Evaluating ILS and MLS sites without flight tests all-body hypersonic aircraft Optimum structural design with static aeroelastic p 660 A89-43894 [ NASA-CR-1853471 p 655 N89-25953 constraints p 669 N89-25171 Numerical simulations of oblique detonations in Multigrid calculation of three-dimensional Recent Advances in Multidisciplinary Analysis and supersonic combustion chambers p 674 A89-44115 turbomachinery flows Optimization. part 2 French aerospace research in the international [ NASA-CR-1853321 p 708 N69-26172 [ NASA-CP-3031-PT-21 p 669 N89-25173 context p 691 A89-45036 CFD in the context of IHPTET The Integrated High ASTROS A multidisciplinary automated structural Some aspects of interference on Loran-C Performance Turbine Technology Program design tool p 705 N89-25174 p 660 A89-45221 [ NASA-TM-1021321 p 708 N89-26174 Recent experiences using finite-element-based Computer simulation of some types of flows arising at A preliminary investigation into Euler methods for structural Optimization p 705 N89-25177 interactions between a supersonic flow and a boundary application to multi-element aerofoils for high lift Robust computer-aided synthesis and optimization of layer p 642 A69-45361 [AERO-REPT-8710] p 708 N89-26196 linear multivariable control systems with varying plant Numerical codes for unsteady simulation of turbojet, COMPUTATIONAL GEOMETRY dynamics via AUTOCON p 711 N89-25179 turbofan and turboprop engines for training purposes HOMAR: A computer code for generating homotopic Computenzed Design Synthesis (CDS). A [AIM PAPER 89-22591 p 676 A89-46704 gnds using algebraic relations: User's manual databasednven multidisciplinarydesign tool Recent Advances in Multidisciplinary Analysis and [ NASA-CR-42431 p 708 N89-26176 p 712 N69-25160 Optimization. part 3 COMPUTATIONAL GRIDS Digital robust control law synthesis using constrained [ NASA-CP-3031-PT-3] p 670 N89-25201 Efficient computational tool for ramjet combustor optimization p 689 N69-25193 Influence of rubbing on rotor dynamics, part 2 research An integratedapproach to the optimum design of actively [NASA-CR-163649-PT-2] p 706 N89-25464 [AIM PAPER 88-00601 p 674 A89-44108 controlled composite wings p 670 N69-25194 Reduction of aircraft noise in civil air transport by A flow-field solver using overlying and embedded Recent Advances in Multidisciplinary Analysis and optimization of flight tracks and takeoff and approach meshes together with a novel compact Euler algorithm Optimization. part 3 procedures p 641 A89-45359 [ NASA-CP-3031-PT-31 p 670 N89-25201 [ILR-MITTT-200] p 713 N89-25676 Multidimensionaladaptive Euler solver Multilevel decomposition of complete vehicle CONCRETES p 641 A89-45360 configuration in a parallel computing environment Evaluation of nondestructive test equipment for airfield Development of a highly efficientand accurate 3D Euler p 670 N89-25205 pavements. Phase 1: Calibrationtest results and field data flow solver p 642 A89-45370 Design optimization of axisymmetric bodies in collection Low-storageimplicit upwind-FEM schemes for the Euler nonuniform transonic flow p 670 N89-25206 [AD-A2071591 p 694 N89-26020 equations p 642 A69-45375 Procedures for shape optimization of gas turbine disks CONDUCTIVE HEAT TRANSFER Adaptive numerical solutions of the Euler equations in p 685 N89-25207 Study of flow and heat transfer in rotating cavities 3D using finite elements p 644 A69-45413 The role of optimization in the next generation of [ONERA, TP NO. 1989-331 p 698 A89-45186 Transonic analysis of arbitraty configurations using computer-based design tools p 712 N89-25220 CONFERENCES locally refined grids p 644 A89-45419 An overview of the Douglas Aircraft Company Society of Flight Test Engineers, Annual Symposium, Transonic flow solutions on general 3D regions using Aeroelastic Design Optimizationbrogram(ADOP) 19th. Arlington, TX. Aug. 14-18, 1968. Proceedings composite-block grids p 644 A89-45428 D 671 N89-25221 p 662 A69-45126 Computationalanalysts of turbomachinery flows using Meeting the challenges with the Douglas Aircraft 1988 report to the aerospace profession; Society of FLOFIVE Company Aeroelastic Design Optimization Program ExperimentalTest Pilots, Symposium, 2nd. Beverly Hills, [AIAA PAPER 89.25591 p 648 A89-46924 (Amp) p 671 N89-25222 CA. Oct. 13-15, 1966, Proceedings p 686 A89-45151 Block-structured solution of transonic flows around Recent developments in large-scale structural InternationalConference on Numerical Methods in Fluid mngf pylon/ nacelle configurations optimization p 706 N89-25231 Dynamics, 11th. Williamsburg. VA, June 27-July 1. 1988, [AIAA PAPER 89-29401 p 651 A69-47184 Development and application of a computer-based Proceedings p 699 A89-45351 Numericalanalysis of supersonic flow through oscillating system for conceptual aircraft destgn cascade sections by using a deforming grid [ ETN-69-948861 p 673 N89-26001 Radio Technical Commission for Aeronautics, Annual Assembly Meeting and Technical Symposium, [ NASA-TM-1020531 p 653 N89-25119 Automated sbvctural Optimization system (ASTROS) Washington, DC. Nov. 1968, Proceedings Two-dimensional elliDtic and oeneration for airfoils and User training workshop 28-30. cascades [ AD-AZ07090) p 709 N89-26267 p 660 A89-45875 [ DFVLR-FB-88-52] p 653 N89-25125 COMPUTER GRAPHICS Space age metals technology; Proceedings of the Procedures for sham.. ODtimization of aas turbine disks Applications of integrated designlanalysis Systems in Second International SAMPE Metals and Metals p 685 N89-25207 aerospace structural dewgn p666 N89-25147 Processing Conference, Dayton, OH, Aug. 2-4. 1988 A numerical solution of transonic flow using An overview of the Douglas Aircraft Company p 696 A89-45927 discontinuous shock wave relationship Aeroelasbc Dewgn Optimization Program (ADOP) Aerospace Behavioral Technology Conference and [ NAL-TR-9971 p 655 N89-25950 p 671 N89-25221 Exposition, 7th. Anaheim, CA, Oct. 3-6. 1988. Multigrid calculation of three-dimensional Meeting the challenges with the Douglas Aircraft Proceedings turbomachinery flows Company Aeroelastic Design Optimization Program [SAE P-2161 p 638 A89-47326 [NASA-CR-1853321 p 708 N89-26172 (Amp) p 671 N89-25222 Recent Advances in Multidisciplinary Analysis and HOMAR: A computer code for generating homotopic COMPUTER PROGRAMMING Optimization, part 1 grids using algebraic relations: User's manual Muhlevel decompostbon of complete vehicle [NASA-CP-3031-PT-l] p 666 N89-25146 [ NASA-CR-42431 p 708 N89-26176 configuration in a parallel computing environment Recent Advances in Multidisciplinary Analysis and COMPUTER AIDED DESIGN p 670 N89-25205 Optimization, part 2 French aerospace research in the international Influence of ~bb~ngon rotor dynamics. part 2 [NASA-CP-3031-PT-2] p 669 N89-25173 context p 691 A6945036 [NASA-CR-l83649-PT-2] p 706 N89-25464 Recent Advances in Multidisciplinary Analysis and A nontraditional approach to reliability Automated structural optimization system (ASTROS) Optimization, part 3 p 701 A89-46483 User traning workshop [NASA-CP-3031-PT-3] p 670 N89-25201 Computational fluid dynamics using CATlA created [AD-A207090] p 709 N89-26267 CONFORMAL MAPPING COMPUTER PROGRAMS geometry Solution of Euler equations by a finite element method ASTROS A multidisciplinary automated structural [AIAA PAPER 89-23681 p 702 A69-46776 application to supersonic flows p 639 A89-44319 design tool p 705 N89-25174 Aerodynamic design and testing of Fokker 50 nacelle Robust computer-ad& synthesis and optimization of Three-dimensional multigrid Navier-Stokes and intake ducts linear mUltNanable control systems with varying plant Computations for turbomachinery applications [AIM PAPER 89-2483) p665 A89-46866 dynamics via AUTOCON p 71 1 N89 25179 [AIAA PAPER 89-24531 p 702 A89-46841 Application 01 a multi-stage3-D Euler solver to the design An overview of the Douglas Aircraft Company CONGRESSIONAL REPORTS 01 turbines for advanced propulsion systems Aeroelastic Deslgn Optimizabon Program (ADOP) Report to Congress: Technical feasibility of joint use [AIAA PAPER 89-25781 p 679 A69-46936 p 671 N89-25221 at Scott AFB. Selfridge AGB and El Tor0 MCAS Recent Advances in Multidisciplinary Analysis and Meeting the challenges with the Douglas Aircraft [ ADA1 945971 p 693 N89-25241 Optimization. part 1 Company Aeroelastic Design Optimization Program CONICAL BODIES [NASA-CPJO31-PT-1 I p666 N89-25146 (ADOW p 671 N89-25222 Radiative characteristics of hypersonic cone wake Applications of integrated designfanalysis systems in Recent developments in large-scale structural p 646 A69-46263 aerospace slructural design p666 N89-25147 optimization p 706 N89-25231 CONTACT LOADS Development of a microcomputer based integrated Feasibility of predicttng performance degradation of Three dimensional finite element stress predictions of design system for high altitude long endurance aircraft airfoils in heavy rain spur gears compared to gear fatigue rig measurements p 668 N89-25159 [NASA-CR-l81&I21 p 657 N89-25973 [AIAA PAPER 89.29181 p 704 A89-47172 SUBJECT INDEX DEPLETION
CONTAINMENT An integratedapproach to the optimum design of actively CROSS FLOW Fuel containment system concept to reduce spillage controlled composite wings p 670 N89-25194 Normal impinging jet in crossflow ~ A parametric [ DOT/FAA/CT-TN89/22] p 672 N89-25994 Control surface spanwise placement in active flutter investigation CONTRAROTATING PROPELLERS suppression systems p 689 N89-25195 CRUISE[AIAA PAPERMISSILES 89-29571 p 684 A89-47199 Average-passage simulation of counter-rotating propfan Recent Advances in Multidisciplinary Analysis and propulsion systems as applied to cruise missiles Optimization, part 3 Average-passage simulation of counter-rotating propfan [AIAA PAPER 89-29431 p 651 A89-47187 [ NASA-CP-3031-PT-31 p 670 N89-25201 propulsion systems as applied to cruise missiles Low-speed wind tunnel performance of high-speed Flutter suppression control law synthesis for the Active [AIM PAPER 89-29431 p 651 A89-47187 counterrotation propellers at angle-of-attack Flexible Wing model CRUISING FLIGHT [ NASA-TM-1022921 p 653 N89-25121 [ NASA-TM-1015841 p 690 N89-26010 A supersonic cruise fighter design Nonlinear and adaptive control p 664 A89-45167 CONTROL SIMULATION [ NASA-CR-1800881 p 712 N89-26610 Simulation methodology for helicopter automatic flight Advancedthrust vectoring nozzlesforsupercruise fighter Integrated structure/control law design by multilevel control systems p 686 A89-45048 aircraft optimization [AIM PAPER 89-28161 p 682 A89-47102 CONTROL STABILITY [ NASA-TM-I01 6231 p 712 N89-26623 Nonlinear and adaptive control CUES CONTROLLABILITY An exploratory study of the use of movement-correlated [ NASA-CR-1800881 p 712 N89-26610 FAA handling qualities assessment Methodology in - cues in an auditory head-up display p 674 A89-45329 CONTROL SURFACES transition p 687 A89-45159 Control surface spanwise placement in active flutter Aircraft design optimization with multidisciplinary suppression systems p 689 N89-25195 performance criteria p 671 N89-25212 CONTROL SYSTEMS DESIGN CONTROLLERS D F/A-I8A digital flight control system degraded modes Robust computer-aided synthesis and optimization of flight evaluation p 687 A89-45158 linear multivariable control systems with varying plant DAMPERS Study of nonlinear Duffing characteristics of flexible rotor Fokker 100, some aspects of the development of the dynamics via AUTOCON p 711 N89-25179 with SFDB squeeze film damper bearings longitudinal control system p 687 A89-45161 Flutter suppression using eigenspace freedoms to meet --- p 700 A89-45568 Control and dynamic systems. Volume 29 Advances requirements p 689 N89-25191 - DAMPING in algorithms and computational techniques in dynamic CONVECTION Damping of wing tip vortex systems by the modification systems control. Part 2 Book p 71 1 A89-46144 Superconductingrotor cooling system --- of the wing tips p 654 N89-25138 Arranging computer architectures to create [AD-DO140201 p 709 N89-26240 higher-performancecontrollers p 71 1 A89-46147 CONVECTIVE HEAT TRANSFER Flap-lag stability data for a small-scaleisolated hingeless Ensuring surge-free engine operation on today's An introduction to the problem of aerodynamic heating rotor in fomard flight p 706 N89-25479 turbofan powered business jets [AERO-REPT-8901I p 656 N89-25970 [ NASA-TM-1021891 . [AIAA PAPER 89-24871 p 678 A89-46868 CONVERGENCE DASSAULT AIRCRAFT Estimating in-flightengine perlormance variations using The spatially non-uniformconvergence of the numerical Rafale - Dassault's new dawn p 662 A89-45030 Kalman filter concepts solutions of flows . p699 A89-45535 Dassault. leader in European military and business [AlAA PAPER 89-25841 p 679 A89-46940 COOLING SYSTEMS aircraft p 637 A89-45033 Evaluation of a fault tolerant digital engine controller Superconductingrotor cooling system DATA ACQUISITION [AIAA PAPER 89-25891 p 680 A89-46944 [AD-W140201 p 709 N89-26240 The System 500, a real-time flight test telemetry The pursuit of integrated control - A realtime aircraft CORNER FLOW system p 660 A89-45134 system demonstration Modeling of turbulence for compression corner flows Notice to Airmen (NOTAM) system operational [AIM PAPER 89-2701I p 688 A89-47029 and internal flows concept Experiences with a prevalidation methodology for [AIAA PAPER 89-23441 p 647 A89-46763 [ DOT/FAA/CT-TN89/10] p 658 N89-25142 designing integrated/propulsion control System COST ANALYSIS A long-range laser velocimeter for the National architectures Fighter aircraft affordability. survivability. and Full-Scale Aerodynamics Complex: New developments [AIAA PAPER 89-27031 p 688 A89-47030 effectivenessthrough multi-function nozzles and experimental application Integrated controls pay-off -.-for flight/propulsion [AIAA PAPER 89-28151 p 666 A89-47101 [NASA-TM-101081I p 708 N89-26207 aircraft systems An economic model for evaluating high-speed aircraft DATABASEMANAGEMENTSYSTEMS [AIAA PAPER 89-27041 p 688 A89-47031 designs TRUSS: An intelligent design system for aircraft wings The evolution . IFPC to VMS ... integrated [NASA-CR-1775301 p 671 N89-25235 p 711 N89-25162 flight/propulsion control for Vehicle Management COST REDUCTION DATA BASES System Economic aspects of simulation in air transportation Computerized Design Synthesis (CDS), A [AIAA PAPER 89-27051 p 688 A89-47032 p 691 A89-45047 database-driven multidisciplinarydesign tool Transferringjet engine diagnosticand control technology Low cost control system for expendable turbine p 712 N89-25180 to liquid propellant rocket engines engines DATA LINKS [AIAA PAPER 89-28511 p 682 A89-47125 [AIAA PAPER 89.25861 p 680 A89-46942 Controller evaluation of Initial Data Link air traffic control Integrated flight/propulsion control study for STOVL Optimizing conceptual aircraft designs for minimum life services. Volume 2 Mini Study 2 applications cycle cost p 670 N89-25211 [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 [AIAA PAPER 89.29081 p 688 A89-47166 DATA PROCESSING COSTS The System a real-time flight test telemetry Research in automation for air traffic control - United FAA (FederalAviation Administration) aviation forecasts: 500, system p 660 A89-45134 Kingdom work and associated European projects Fiscal years 1989-2000 A long-range laser velocimeter for the National [SAE PAPER 8814701 p 661 A89-47336 [ AD-A2067161 p 638 N89-25948 Contributions to the improvement of flight safety in wind Full-Scale Aerodynamics Complex: New developments COUNTER ROTATION shear and experimental application Design of a gear drive for counter-rotating fan rotors [NASA-TM-101081I p 708 N89-26207 [ DFVLR-FB-86-49] p 658 N89-25144 [AIAA PAPER 89-28201 p 682 A89-47106 Robust compuler-aided synthesis and optimization of DE HAVILUND AIRCRAFT linear multivariable control systems with varying plant Structural tailoring of counter rotation propfans The military Dash 8 flight test program dynamics via AUTOCON p 711 N89-25179 p 685 N89-25165 p664 A89-45145 Digital robust control law synthesis using constrained COUNTER-ROTATINGWHEELS DECISION MAKING optimization p 689 N89-25193 UHB demonstrator flight test program - Phase 2 .-_ The role of optimization in the next generation of An analytical sensitivity method for use in integrated ultra-high bypass engine technology computer-based design tools p 712 N89-25220 aeroservoelastic aircraft design [AIAA PAPER 89-25821 p 679 A89-46939 DECOUPLING [NASA-TM-101583] p 690 N89-25239 COVERINGS Asymptotically decoupled discontinuous control of Turbofan engine control system design using the Aircraft jet engine exhaust blast effects on Par-56runway systems and nonlinear aircraft maneuver LQG/LTR methodology threshold lamp fixtures p 686 A89-45064 [ NASA-CR-1823031 p 685 N89-26004 [ DOT/FAA/CT-89/4] p 694 N89-26018 DEFENSE PROGRAM Integratedflight/propulsion control system design based CRACK GEOMETRY The ATF is on its way p 664 A89-45156 on a centralized approach Crack shape identification as an inverse boundary value DEICERS [ NASA-TM-1021371 p 690 N89-26009 problem p 698 A89-44663 Electromagneticemissions from a modular Low Voltage Advanced piloted aircraft flight control system design CRACK INITIATION Electro-Impulse De-icing system p 707 N89-26120 methodology. Volume 1: Knowledge base Fatigue failure initiation analysis of winglfuselage bolt [DOT/FAA/CT-88/31] [NASA-CR-181726-VOL-l] p 690 N89-26013 assembly p 699 A89-45210 DELTA WINGS Experimental study on aerodynamic characteristics of Advanced piloted aircraft flight control system design CRACK PROPAGATION hypersonic transport configuration p A89-44972 methodology. Volume 2: The FCX flight control design Full scale fatigue crack growth test of advanced jet €40 Unsteady phenomena on delta wings with partially expert system trainer AT-3 p 664 A89-45207 [ NASA-CR-181726-VOL-21 p 691 N89-26014 broken-down vortex regions p 654 N89-25129 lsoparametric shear spring element applied to crack DENSITY MEASUREMENT Nonlinear and adaptive control patching and instability p 699 A89-45208 [ NASA-CR-1800881 p 712 N89-26610 A high speed data acquisition system for the analysis Integrated structure/control law design by multilevel Probabilistic damage tolerance methods for metallic of velocity, density, and total temperature fluctuations at optimization aerospace structures p 672 N89-25237 transonic speeds [ NASA-TM-1016231 p 71 2 N89-26623 CRASH LANDING [SAE PAPER 8814511 p 691 A89-45248 CONTROL THEORY An air photo analysis of an airplane crash X-ray based extensometry Estimating in-flightengine performance variations using p 657 A89-45337 [NASA-CR-185058] p 706 N89-25432 Kalman filter concepts CREEPRUPTURESTRENGTH DEPLETION [AIAA PAPER 89-25841 p 679 A89-46940 Time dependent probabilistic failure of coated Preventing depletion of stratospheric ozone: Digital robust control law synthesis using constrained components Implications on future aircraft emissions optimization p 689 N89-25193 [AIAA PAPER 89-29001 p 704 A89-47163 [DE89-0099641 p 710 N89-25530 A-9 DESCENT SUBJECT INDEX
DESCENT DITCHING Flap-lagstability data lor a small-scaleisolated hingeless Controller evaluabons of the descent advisor automation In the dnnk --- ditch landing capability of aircraft rotor in forward flight ad p 691 A89-43890 [ NASA-TM-1021891 p 706 N89-25479 [NASA-TM-102197] p 659 N89-25981 DIVERGENCE DYNAMIC STRUCTURAL ANALYSIS DESCENT TRAJECTORIES Current flight test experience related to structural Dynamic stress analysis of rotating turbo-machinery Descent strategy comparisons lor TNAV-equipped dwergence of forward-swept wings p 663 A89-45141 bladeddisk systems p 675 A89-44362 arcraft under arplanepreferred operabng conditms DOPPLER RADAR Current flight test experience related to structural [NASA-CR-4248] p690 N89-26011 Selected wind shear events observed dunng the 1987 divergence of forward-swept wings p 663 A89-45141 DESIGN ANALYSIS evaluation of enhancements to the FAA (Federal Aviation Reinforcing solutions for a panel cut-out Effects of nonlinear aerodynamics and static Administration) low level wind shear alert system at p 698 A89-45177 aeroelasticlty on mission performance calculations for a Stapleton International Airport Effect of winglets on loading mechanics and wing fighter aircraft p 669 N89-25170 [AD-A206711I p 710 N89-26323 assembly reactions p 654 N89-25137 Recent Advances in Multidisciplinary Analysis and DOWNWASH Structural optimization 01 rotor blades with integrated Cpbmaalon. part 2 Analysls of hellcopter enwonmental data Indianapolis dynamics and aerodynamics p 668 N89-25156 [ NASA-CP-3031-PT-2] p 669 N89-25173 downtown heliport. Wall Street heliport Volume 1 Multi-objecke/loading optimization for rotating Treatment of forces in boundary element design body Summary composite flexbeams p 668 N89-25157 sensttwity analysts p 705 N89-25187 [ AD-A206708] p 710 N89-26294 Computational structural mechanics for engine Recent Advances in MUltidiSCiDlinaN Analvsis and structures ... DRAG REDUCTION Optimizamn. part 3 [NASA-TM-l02t19] p 709 N89-26259 Spanmse Ifl distnbubons and wake velocity surveys of [ NASA-CP-3031-PT-3] p 670 N89-25201 Langley rotorcraft structural dynamics program: a semi-span mng wth a disconbnuous twist Deston mbmmbon of axisymmetnc bodies in Background. status, accomplishments, plans [NASA-CR-1775321 p 653 N89-25122 nonuniorm transonic flow p 670 N89-25206 [ NASA-TM-1016181 p 709 N89-26273 The conceptual desgn of a Mach 2 Oblique Fiymg Wing An inibal assessment of the imoact of boundarv,. laver DYNAMICAL SYSTEMS wpersonlc transport control on SST Control and dynamic systems. Volume 29 . Advances [ NASA-CR-t775291 p 671 N89-25233 [AERO-REPT-8802] p656 N89-25969 in algorithms and computational techniques in dynamic An analflcal sensitmty method for use in integrated DUCT GEOMETRY systems control. Part 2 --- Bwk p 71 1 A89-46144 aerosewoelasbc arcraft desgn Further experiments on supersonic turbulent flow Gain transfer - An algorithm for decentralized [ NASA-TM-1015831 p 690 N89-25239 development in a square duct p 652 A89-47357 hierarchical estimation p 71 1 A89-46150 Tiplet VTOL UAV (VertJcal Takeoff and DUCTED FAN ENGINES LandingIUnmanned Aenal Vehicle) summary Volume 1 Ducted ultra-hylh bypass engine configurabon A 1200 pound bplet VTOL unmanned aenal vehicle Part definibon E 1 Co nceptual desrgn study of a 1200-poundvehicle [AIAA PAPER 89-24781 p 678 A89-46862 [AD-A206738] p 672 N89-25997 Technology readiness lor advanced ducted engines EARTH ENVIRONMENT Strategic bombers 6-1B cost and performance remain [AIAA PAPER 89-24791 p 678 A89-46863 Inertial guidance test facility using the earth uncertain Hah perlormance gear systems and heat management environment p 700 A89-46218 [AD-A206751] p 673 N89-25998 for advanced ducted systems ECONOMIC ANALYSIS Design criteria for aggregate-surfaced roads and [AIAA PAPER 89-24821 p 678 A89-46865 Economic analysis of a beam-powered, personalized airfields DUCTED FLOW global aerospace transportation system [ADA2070591 p 694 N89-26019 Further experiments on supersonic turbulent flow [AIAA PAPER 89.24431 p 714 A89-46835 Langley rotorcraft structural dynamlcs program development in a square duct p 652 A89-47357 Federal incentwesfor industrial modernization:Historical Background. status. accomplishments.plans DUCTlLlTV review and future opportunities [ NASA-TM-1016181 p 709 N89-26273 Hot ductility response of AI-Mg and AI Mg-Li alloys [ NASA-TM-1017851 p 714 N89-25764 DESIGN TO COST p 695 A89-45330 ECONOMIC FACTORS The Rolls Royce Allison RB580 turbofan - Matching the DUCTS Economic aspects 01 simulation in air transportation market requirement lor regional transport Aircraft engine outer duct mounting device p 691 A89-45047 [AIAA PAPER 89-24881 p 678 A89-46869 [AD-l3Jl3988] p 672 N89-25991 ECONOMICS DETONATION WAVES DUMP COMBUSTORS An economic model for evaluating high-speed aircraft designs Numencal stmulabons of oblique detonations in Efficient computational tool lor ramjet combustor supersonic combustion chambers p 674 A89-44115 research [NASA-CR-177530] p 671 N89-25235 FAA (FederalAviation Administration)aviation forecasts: DIELECTRICS~ [AIAA PAPER 88-00601 p 674 A89-44108 Radar cross section 01 arbitrarily shaped bodies of Numencal study of reactwe ramjet dump combustor Fiscal years 1989-2ooO revolution p 674 A89-45111 flowfields mth a pressure based CFD method [AD-A206716] p 638 N89-25948 DIFFERENCE EQUATIONS [AIAA PAPER 89-27981 p 681 A89-47091 EDUCATION Difference methods for initial-boundary-valueproblems Ramjet cornbustor modeling lor engineering design Easy method of matching fighter engine to airframe for and flow around bodies (Revised edition) --- Book [AIAA PAPER 89-27991 p 681 A89-47092 use in aircraft engine design courses p 646 A89-46198 DURABILITY [AIAA PAPER 89-22601 p 665 A89-46705 DIFFUSERS Advanced cooling concepts for multi-funcbon nozzle EIGENVALUES Flow characteristics in an S-shaped rectangular-round durabillty Fluller suppression using egenspace freedoms to meet diftuser at high incidence p646 A89-46260 [AIAA PAPER 89-28141 p682 A89-47100 requirements p 689 N89-25191 DIGITAL SIMULATION DYNAMIC CHARACTERISTICS EIGENVECTORS Numerical simulation of the flow about a wing with Longitudinal nonlinear aerodynamic model form for Flutter suppression using egenspace freedoms to meet leading-edgevortex flow p 643 A89-45390 USE-STOL aircraft requirements p 689 N89-25191 Local analytical methods for digital simulation of [ NAL-TR-9951 p 672 N89-25990 EJECTORS dynamical control system p 71 1 A89-46244 Relaxabon oscrllabons in arcraft cruise-dash Large-scale wind tunnel tests of an ejector-lift STOVL DIGITAL SYSTEMS opbmizabon aircraft model F/A-l8A dylital flight control system degraded modes [ AD-A206722 I p 672 N89-25996 [AIAA PAPER 89.29051 p 666 A89-47165 flight evaluation p 687 A89-45158 DYNAMIC CONTROL Supersonic nozzle mixer ejector Digital fliiht and inlet control in the SR-71 Local analytical methods for digital simulation of [AIM PAPER 89.29251 p 683 A89-47178 p 664 A89-45160 dynamical control system p 71 1 A89-46244 ELASTIC DAMPING Low cost control system for expendable turbine Nonlinear and adaptwe control Study of nonlinear Duffingcharacteristics of flexiblerotor engines [ NASA-CR-180088 ] p 712 N89-26610 with SFDB --- squeeze film damper bearings [AIM PAPER 89-25861 p 680 A89-46942 DYNAMIC MODELS p 700 A89-45568 DIGITAL TECHNIQUES A dynamic digltal model for the turbojet with ELECTRIC BATTERIES Evaluation of a fault tolerant digital engine controller pulse-monltoredfwler p 675 A89-45559 Low-temperature performance of a power-pack for a [AIAA PAPER 89-25891 p680 A894944 Role of dynamlc slmulabon in fighter engine design and 2-watt ELT p 709 A89-44016 DIHEDRAL ANGLE development ELECTRIC CONDUCTORS Effect of milling machine roughness and wing dihedral [AlAA PAPER 89-24671 p 677 A89-46854 Radar cross section of arbitranly shaped bodies of on the supersonic aerodynamic characteristics of a highly Lorgtudtnal nonlinear aerodynamic model form for revolution p 674 A89-45111 USE-STOL aircraft swept wing ELECTRIC GENERATORS [ NAL-TR-9951 p 672 N89-25990 [NASA-TP-2918] p 652 N89-25117 Superconductingrotor cooling system State space models for aeroelasbc and viscoelastic [AD-M)14020] DISKS (SHAPES) systems p 709 N89-26240 Procedures for shape Optimizabon of gas turbine disks [AD-A207092] p690 N89-26012 ELECTROMAGNETICINTERFERENCE p 685 N89-25207 DYNAMIC PRESSURE Some aspects 01 interlerenceon Loran-C DISPLACEMENT MEASUREMENT The ATR/RJ engine performance at constant dynamic p 660 A89-45221 The measurement of linear and angular displacements pressure and the conslderabon of transibon condibon Electromagneticemissions from a modular Low Voltage in prototype aircraft . Instrumentation. calibration and p 694 A89-460 16 Electro-Impulse De-icing system operational accuracy p 698 A89-45142 DYNAMIC RESPONSE [DOT/FAA/CT48/31] p 707 N89-26120 DISPLAY DEVICES Aircraft design opbmizatlon with multidisciplinary ELECTROMAGNETICPULSES Aerospace Behavioral Technology Conference and perlormance cntena p 671 N89-25212 Electromagneticemissions from a modular Low Voltage Exposition, 7th. Anaheim, CA. Oct. 3-6. 1988, State space models for aeroelastic and viscoelastic Electro-Impulse De-icing system Proceedings systems [DOT/FAA/CT-88/31] p 707 N89-26120 [SAE P-2161 p638 A8947326 [ADA2070921 p690 N89-26012 ELECTROMAGNETICSCATTERING DISSIPATION DYNAMIC STABILITY Review of FD-TO numencal modelingof electromagnetic Warm log dissipation using large volume water sways Optimizabon dewgn for suppressing 'ground resonance. wave scattering and radar cross section [NASA-CASE-MFS25962-1I p 693 N89-25242 01 helicopters p664 A89-46278 p 673 A89-45107
A-10 SUBJECT INDEX EULER EQUATIONS OF MOTION
ELECTROMAGNETIC SHIELDING Role of dynamic simulation in fighter engine design and Treatment of body forces in boundary element design Electromagneticemissions from a modular Low Voltage development sensitivity analysis p 705 N89-25187 Electro-ImpulseDe-icing system [AIAA PAPER 89.24671 p 677 A89-46854 Aircraft engine outer duct mounting device [DOT/FAA/CT-BB/Bl] p 707 N89-26120 Advanced propulsion systems for large subsonic [AD-WI39881 p 672 N89-25991 ELECTRONIC CONTROL transports Computational structural mechanics for engine Low cost control system lor expendable turbine [AlAA PAPER 89-24771 p 677 A89-46861 structures engines Ducted ultra-high bypass engine configuration [NASA-TM-1021191 p 709 N89-26259 definition [AIAA PAPER 89-25861 p680 A89-46942 ENGINE STARTERS [AIM PAPER 89-24781 p 678 A89-46862 Evaluation of a fault tolerant digital engine controller The investigation of jet engine starting Technology readiness for advanced ducted engines [AIAA PAPER 89-25891 p 680 A89-46944 p 676 A89-46025 ELECTRONIC EQUIPMENT [AIAA PAPER 89.24791 p 678 A89-46863 Nacelle/pylon interference study on a 1/17th-~caIe, Semiconstant volume pulse combustion for gas turbine R8M through Avionics/Electronics Integrity Program engine starting p 701 A89-46480 twin-engine, low-wing transport model [AIAA PAPER 89-24801 p 665 A89-46864 [AIAA PAPER 89-24491 p 677 A89-46838 EMERGENCYLOCATORTRANSMllTERS Design and testing of a common engine and nacelle ENGINE TESTS Low-temperature performance of a power-pack for a for the Fokker 100 and Gulfstream GIV airplanes Advanced turbofan engine combustion system design 2-watt ELT p 709 A89-44016 [AIAA PAPER 89-24861 p 666 A89-46867 and test verification p 675 A89-44117 ENERGY CONSERVATION The Rolls Royce Allison RB580 turbofan - Matching the Prediction of turbomachinery performance ~ Application Relaxation oscillations in aircraft cruise-dash market requirement for regional transport to a centrifugal pump, a centrifugal compressor. and a optimization [AIAA PAPER 89-24881 p 678 A89-46869 radial inflow turbine p 640 A89-44638 [AD-A206722] p 672 N89-25996 Turbine engine structural efficiency determination Experimental investigation on characteristics of single ENGINE AIRFRAME INTEGRATION [AIM PAPER 89-25711 p 679 A89-46932 and tandem blade cascades with double-circular arc Prop-fan tested for structural and acoustic data Configuration studies lor a regional airliner using profile p 676 A89-45567 p 674 A89-43885 open-rotor ultra-high-bypass-ratioengines The ATR/RJ engine performance at constant dynamic Easy method of matching lighter engine to airframe for [AIM PAPER 89-25801 p 666 A89-46937 pressure and the consideration of transition condition use in aircraft engine design courses UHB demonstrator flight test program - Phase 2 --- p 694 ABS-46016 [AIAA PAPER 89-22603 p 665 A89-46705 ultra-high bypass engine technology The investigation of jet engine starting Design and testing of a common engine and nacelle [AIAA PAPER 89-25821 p 679 A89-46939 p 676 A89-46025 Rapid methodology for design and performance for the Fokker 100 and Gulfstream GIV airplanes An experimentaltechnique for the measurement of mass prediction of integrated scramjetlhypersonic vehicle [AIAA PAPER 89-24861 p666 A89-46867 flow of scramjet inlets tested in hypersonic pulse [AIAA PAPER 89-26821 p A89-47012 Bow shock matching with viscous effects on hypersonic 666 facilities forebodies A propulsion development strategy for the National [AIAA PAPER 89-2331I p 692 A89-46755 [AIAA PAPER 89-26781 p 649 A89-47008 Aero-Space Plane Design and testing a common engine and nacelle Numerical and experimental investigation of [AIAA PAPER 89-27511 p 681 A89-47061 01 for the Fokker and Gulfstream GIV airplanes airlrame-integrated inlet for high velocities Ramjet combustor modeling for engineering design 100 [AIAA PAPER 89-24861 p 666 ABS-46867 [AIAA PAPER 89-26791 p 649 A89-47009 [AlAA PAPER 89-27991 p 681 A89-47092 Rapid methodology for design and performance Advanced cooling concepts for multi-function nozzle Ensuring surge-free engine operation on today's prediction of integrated scramjetlhypersonic vehicle durability turbofan powered business jets [AIAA PAPER 89-26821 p 666 A89-47012 [AIAA PAPER 89-28141 p 682 A89-47100 [AIAA PAPER 89-24871 p 678 A89-46868 Experiences with a prevalidation methodology for Brayton cycle engines with reciprocating work Free-jet test capability for the aeropropulsion systems designing integrated/propulsion control system components test facility architectures [AIAA PAPER 89-29331 p 704 A89-47181 [AIAA PAPER 89-25371 p 692 A89-46908 [AIAA PAPER 89-27031 p 688 A89-47030 Treatment of body forces in boundary element design A comparison of scramjet engine performances of Integrated flight/propulsion control study lor STOVL sensitivity analysis p 705 N89-25187 various cycles applications Influenceof rubbing on rotor dynamics, part 2 [AIAA PAPER 89-2676) p 680 A8947006 [AIAA PAPER 89-29081 p 688 A89-47166 [ NASA-CR-183649-PT-21 p 706 N89-25464 Mach 4 testing of scramjet inlet models Average-passage Simulation of counter-rotatingpropfan CFD in the context of IHPTET The Integrated High [AlAA PAPER 89-26801 p 649 A89-47010 propulsion systems as applied to cruise missiles Performance Turbine Technology Program Turbine aerodynamic performance measurements in [AIAA PAPER 89-29431 p 651 A89-47187 [ NASA-TM-102132] p 708 N89-26174 short duration facilities ENGINE CONTROL Computational structural mechanics for engine [AIAA PAPER 89-26901 p 693 A89-47020 structures Estimating in-flight engine performance variations using Development testing of the 578 propfan gear system [NASA-TM-102119] p 709 N89-26259 Kalman filter concepts [AIM PAPER 89-28171 p 682 A89-47103 [AlAA PAPER 89.25841 . p 679 A89-46940 ENGINE FAILURE Distortion test capabilities for future fighter aircraft Evaluation of a fault tolerant digital engine controller Powered lift aircraft lake off climb performance with one engines [AIAA PAPER 89.25891 p 680 A89-46944 engine inoperative p 663 A89-45127 The pursuit of integrated control - A realtime aircraft ENGINE INLETS [AIM PAPER 89-29561 p 684 ABS-47198 system demonstration Digital flight and inlet control in the SR-71 ENVIRONMENT EFFECTS [AIAA PAPER 89-2701] p 688 A89-47029 p664 A89-45160 Analysis of helicopter environmental data: Indianapolis Integrated controls pay-off --- for flight/propulsion Environmental icing test of T800 helicopter engine with downtown helimrt. Wall Street helioort. Volume 1: aircraft systems integral inlet particle separator Summary [AIAA PAPER 89-27041 p 688 A89-47031 [AIAA PAPER 89-23241 p 676 A89-46751 [AD-A206708] p 710 N89-26294 The evolution - IFPC to VMS -_- integrated Validation of a free-jet technique for evaluating ENVIRONMENT SIMULATION flightlpropulsion control for Vehicle Management inlet-engine compatibility Mechanical stresses during air transport and ground System [AlAA PAPER 89.23251 p 676 A89-46752 operations p 700 A89-46221 [AIAA PAPER 89-27051 p 688 A89-47032 An experimentaltechnique for the measurement 01 mass ENVIRONMENTAL CONTROL Transferringjet engine diagnostic and control technology flow of scramjet inlets tested in hypersonic pulse Airplane tests of enhanced emergency smoke venting to liquid propellant rocket engines facilities [D218N301] p 658 N89-25976 [Alh PAPER 89.28511 - p 682 A89-47125 [AIAA PAPEfl 89-2331] p 692 A8946755 ERROR ANALYSIS ENGINE COOLANTS T-4 inlet/engine compatibility flight test results Gain transfer - An algorithm for decentralized Advanced material applications for turbine airfoils [AIM PAPER 89-24661 p665 A8946853 hierarchical estimation p 71 1 A89-46150 IAlAA PAPER 89.2693) p 680 A89-47023 Free-jet test capability for the aeropropulsion systems Evaluationof a projectionalgorithm for the stereographic ENGINE DESIGN test facility representation of aircraft in an air traffic control system Numerical simulations of oblique detonations in [AIAA PAPER 89-25371 p 692 A89-46908 [ DOT/FAA/CT-TN89/20] p 661 N89-25985 supersonic combustion chambers p 674 A89-44115 Mach 4 testing of scramjet inlet models ESCAPE SYSTEMS Advanced turbofan engine combustion system design [AIAA PAPER 89-26801 p 649 A89-47010 Sled testing of US. Air Force escape systems and test verification p 675 A89-44117 ENGINE MONITORING INSTRUMENTS p 657 A89-45129 Recent developments in calculation methods for Preliminary development 01 an intelligent computer EULER EQUATIONS OF MOTION turbomachines p 697 A89-44635 assistant for engine monitoring Solution of Euler equations by a finite element method Theoretical and experimental study of turbine [AlAA PAPER 89-25391 p 674 A89-46910 application to supersonic flows p 639 A89-44319 aerodynamics p640 A8844639 Diagnostic expert systems for gas turbine engines - A flow-field solver using overlying and embedded Design of vane tips improving axial compressor Status and prospects meshes together with a novel compact Euler algorithm performance p 640 A89-44640 [AIAA PAPER 89-25851 p 680 A89-46941 p 641 A89-45359 Methods lor the mathematical modeling of flight vehicle Transferringjet engine diagnostic and controltechnology Multidimensionaladaptive Euler solver ' engines --- Russian book p 711 A89-46551 to liquid propellant rocket engines p 641 A89-45380 Performance analysis of scramjet engines [AIAA PAPER 89-28511 ' p 682 A89-47125 Computation 01 hypersonic vortex flows with an Euler p 676 A89-46600 Optical fiber sensor development for turbine model p 642 A89-45368 Numerical codes for unsteady simulation of turbojet, applications A high resolution finite volume scheme for steady turbofan and turboprop engines for training purposes [AIAA PAPER 89-29141 p 704 A89-47168 external transonic flow p 642 A89-45369 [AlAA PAPER 89-22591 p 676 A89-46704 ENGINE NOISE Development of a highly eflicient and accurate 30 Euler Easy method of matching fighter engine to airframe for Re-engining stage two aircraft'with the Tay flow solver p 642 A89-45370 use in aircraft engine design courses [AIAA PAPER 89-2361] p 676 A89-46774 Low-storageimplicit upwind-FEM schemes for the Euler [AIAA PAPER 89-22601 p 665 A89-46705 ENGINE PARTS equations p 642 A89-45375 Re-engining stage two aircraft with the Tay Experimental investigation of aeroengine high-speed Multigrid calculations for cascades [AIAA PAPER 89-2361I p 676 A89-46774 roller bearing p 700 A89-45570 p 643 A89-45391 Engine life maturation process Ceramic bearings for use in gas turbine engines Adaptive numerical solutions of the Euler equations in [AIM PAPER 89-24641 p 677 A89-46851 p 702 A89-46697 30 using finite elements p 644 A89-45413
A-1 1 EUROPE SUBJECT INDEX
Application of simple wave theory to the radiative Diagnostic expert systems for gas turbine engines - Transmission overhaul and replacement predictions boundary conditions required for an internal flow Euler Status and prospects using Weibull and renewal theory solver [AlAA PAPER 89-25851 p 680 A89-46941 [AIAA PAPER 89.29191 p 704 A89-47173 [AlAA PAPER 89.25771 p 648 A89-46935 Recent Advances in Multidisciplinary Analysis and FAULT TOLERANCE Application of a multi stage 3-D Euler solver to the design Optimization. part 1 Damage tolerance analysis and structural integrity in Air of turbines for advanced propulsion systems [ NASA-CP-3031-PT-I] p 666 N89-25146 Force aircraft p 661 A89-43884 [AIAA PAPER 89-25781 p 679 A89-46936 TRUSS. An intelligent design system for aircraft wings In search of effective diversity - A six-language study Multigrid calculation of three-dimensional p 711 N89-25162 of fault-tolerant flight control software turbomachinery flows The designer of the 90's: A live demonstration p 710 A89-44423 [ NASA-CR 1853321 p 708 N89-26172 p 705 N89-25164 Testing of reliability - Analysis tools A preliminary investigation into Euler methods for Advanced piloted aircraft flight control system design p 702 A89-46503 application to multi-element aerofoils for high lift methodology. Volume 1: Knowledge base Evaluation of a fault tolerant digital engine controller [AERO-REPT-8710] p 708 N89-26196 [NASA-CR-I81726-VOL-lI p 690 N89-26013 [AIAA PAPER 89-25891 p 680 A89-46944 EUROPE Advanced piloted aircraft flight control system design The pursuit of integrated control - A realtime aircraft Dornier's role in the 'European Fighter Aircraft' EFA methodology. Volume 2: The FCX flight control design system demonstration program p 637 A89-44643 expert system [AIAA PAPER 89 2701 I p 688 A89-47029 The phased establishment of support matunty for the [ NASA-CR-181726-VOL-21 p 691 N89-26014 FAULT TREES European Fighter Aircraft (EFA) p 637 A89-44644 Applications of funy sets to rule-based expert system Probabilistic analysis of aircraft structure EUROPEAN AIRBUS development p 712 N89-26606 p 665 A89-46470 Airbus lndustne lessons from experience EXTENSOMETERS FEASIBILITY ANALYSIS p 714 A89-45039 The ConceDtual desian of a Mach 2 Obliaue Flvina Wina X-ray based extensometry ._ I Airbus The new families p662 A8945043 - [ NASA-CR-1850581 p 706 N89-25432 supersonic transport The systems of the future Airbus A330 and A340 [NASA-CR-177529] p 671 N89-25233 aircraft p 662 A89-45044 Rewrt to Conaress Technical feasibilitv of ioint use EUROPEANSPACE AGENCY F at Scott AFB. Seliridge AGB and El Tor0 MCAS. The 'nerve center' of ESA - Tasks and procedures of [AD-A194597] p 693 N89-25241 the ESOC in Darmstadt p 694 A89-43869 F-1 11 AIRCRAFT FEEDBACKCONTROL EVACUATING (VACUUM) Fast brake --.F-111 high-performanceparachute system Asymptotically decoupled discontinuous control of Airplane tests of enhanced emergency smoke venting development p 657 A89-46593 systems and nonlinear aircraft maneuver [D218N301] p 658 N89-25976 F-14 AIRCRAFT p 686 A89-45064 EXHAUST EMISSION F-l4/F110 high angle of attack flight tests Turbofan engine control system design using the Effects of fuel chemical properties on exhaust smoke p 686 A89-45153 LQGILTR methodology from gas turbine combustor p 695 A89-45554 F-15 AIRCRAFT [ NASA-CR-1823031 p 685 N89-26004 Investigation of low NOx staged combustor concept in F-15 STOL/Maneuvering Technology Demonstrator - Applications of fuzzy sets to rule-based expert system high-speed civil transport engines Initial flight test results p 687 A89-45157 development p 712 N89-26606 [AlAA PAPER 89-29421 p 684 A89-47186 Integrated controls pay-off --- for flight/propulsion Nonlinear and adaptive control Fuel properties effect on the performance of a small aircraft systems [ NASA-CR-1800881 p 712 N89-26610 high temperature rise combustor [AlAA PAPER 89-27041 p 688 A89-47031 FIBER COMPOSITES [ NASA-TM-1020961 p 685 N89-25238 F-16 AIRCRAFT lsoparametric shear spring element applied to crack Aircraft let engine exhaust blast effects on Par-56runway F-16 inlet stability investigation patching and instability p 699 A89-45208 threshold lamp fixtures IAIAA PAPER 89.24651 p 665 A89-46852 FIGHTER AIRCRAFT [ M)T/FAA/CT-89/4] p 694 N89 26018 F-18 AIRCRAFT Dornier's role in the 'European Fighter Aircran' EFA Comparisons between unleaded automobile gasoline Service suitability testing of the FIA-18A for use by the program p 637 A89-44643 and aviation gasoline on valve seat recession in light Blue Angels Navy Flight Demonstration Team The phased establishment of support matunty for the aircraft engines p 664 A89-45146 European Fighter Aircraft (EFA) p 637 A89-44644 [ NIPER-4091 p 697 N89-26110 F-18 Hornet - LEX Fence flight test results Rafale - Dassault's new dawn p 662 A89-45030 EXHAUST GASES p 687 A89-45155 1988 report to the aerospace profession; Society of Fiber metal acoustic matenal for gas turbine exhaust FIA-18A digital flight control system degraded modes Experimental Test Pilots, Symposium, 32nd. Beverly Hills, environments p 695 A89-44400 flight evaluation p 687 A89-45158 CA, Oct. 13-15. 1988, Proceedings p 686 A89-45151 A dynamic digital model for the turbojet with Hornet maintenance p 638 A89-46496 Testing for agility - A progress report pulse-monitoredfueler p 675 A89-45559 FAIL-SAFE SYSTEMS p 686 A89-45152 Improving the development processfor main combustor Probabilistic damage tolerance methods for metallic The ATF is on its way p 664 A89-45156 exit temperature distnbution aerospace structures p 672 N89-25237 A supersonic cruise fighter design [AIAA PAPER 89-28041 p 681 A89-47094 FAILURE p 664 A89-45167 EXHAUST NOZZLES Design criteria for aggregate-surfaced roads and A pilot's view of intelligent systems Prelrminary assessment of exhaust systems for high airfields p 688 A89-45294 Mach (4 to 6) fighter aircraft [AD-A2070591 p 694 N89-26019 Aluminum-lithium alloys for fighter aircratt applications [AlAA PAPER 89.23561 p 676 A89-46770 FAILURE ANALYSIS p 696 A89-45937 Rectangular nozzle plume velocity modeling for use in Fatigue failure initiation analysis of wing/fuselage bolt A nontraditional approach to reliability jet noise prediction assembly p 699 A89-45210 p 701 A89-46483 [AIAA PAPER 89-23571 p647 A8946771 ADINTS - Moving toward standardization of automatic Advanced cooling concepts for multi-function nozzle test equipment p 701 A89-46462 Easy method of matching fighter engine to airframe for durability Probabilistic analysis of aircraft structure use in aircraft engine design courses [AIAA PAPER 89-28141 p 682 A89 47100 p 665 A89-46470 [AIAA PAPER 89-22601 p 665 A89-46705 Fighter aircraft affordability. survivability. and A top-down SFP analysis of a complex system --- single Preliminary assessment of exhaust systems for high effectiveness through multi-functionnozzles failure points p701 A8946472 Mach (4 to 6) fighter aircraft [AIAA PAPER 89-28151 p666 A89-47101 A corollary to - Duane's postulate on reliability growth [AlAA PAPER 89.23561 p 676 A89-46770 Expendable supersonic exhaust nozzle concepts p 701 A89-46474 Role of dynamic simulation in fighter engine design and [ AlAA PAPER 89-29271 p 684 A89-47179 RBM through AvionicslElectronics Integrity Program development EXHAUST SYSTEMS p 701 A89-46480 [AIM PAPER 89-24671 p 677 A89-46854 Preliminary assessment of exhaust systems for high Time dependent probabilistic failure of coated Fighter aircraft affordability, survivability, and Mach (4 to 6) fighter aircraft components effectiveness through multi-functionnozzles [AIM PAPER 89-23561 p 676 A89-46770 [AIAA PAPER 89-29001 p 704 A89-47163 [AIAA PAPER 89-28151 p 666 A89-47101 A static investigationof several STOVL exhaust system Probabilisbc damage tolerance methods for metallic Advanced thrust vectoring nozzles for supercruise fighter concepts aerospace structures p 672 N89-25237 aircraft [AlAA PAPER 89-29281 p 684 A89-47180 FAN BLADES [AlAA PAPER 89-28161 p 682 A89-47102 EC-18BIBoeing 707 Smoke Venting flight test Model predictions of fan response to inlet temperature Large-scale wind tunnel tests of an ejector-lift STOVL [AD-A2066011 p 659 N89 25979 transients and spatial temperature distortion aircraft model EXHAUST VELOCITY [AIAA PAPER 89-26861 p 650 A89-47016 [AIAA PAPER 89.29051 p 666 A89-471.65 FANS Rectangular nozzle plume velocity modeling for use in Distortion test capabilities for future fighter aircraft Design of a gear drive for counter-rotating fan rotors let noise prediction engines [AlAA PAPER 89.28201 p 682 A89-47106 [AIAA PAPER 89.23571 p 647 A89-46771 [AlAA PAPER 89.29561 p 684 A89-47198 EXPERT SYSTEMS Influence of thickness and camber on the aeroelastic stability of supersonic throughflow fans: An engineering Effects of nonlinear aerodynamics and static Establishing artificial intelligence technology in a flight aeroelasticity on mission performance calculations for a test environment p 663 A89-45135 approach [ NASA-TM-1019491 p 656 N89-25957 bghrer aircraft p 669 N89-25170 ExpertVision - A video-based non-contact System for FINITE DIFFERENCE THEORY mobon measurement p 698 A89-45136 FATIGUE (MATERIALS) Probabilistic damage tolerance methods for metallic Review of FD-TD numerical modeling of electromagnetic Expert systems' role broadens p 71 1 A89-45293 aerospace structures p 672 N89-25237 wave scattering and radar cross section A pilot's view of intelligent systems FATIGUE LIFE p 673 A89-45107 p 688 A89-45294 Full scale fatigue crack growth test of advanced jet An implicit time-marching method for solving the 3-D A nontradibonal approach to reliability trainer AT-3 p664 A89-45207 compressible Navier-Stokes equations p 701 A89-46483 Fatigue falure initiation analysis of winglfuselage bolt p 642 A89-45374 Preliminary development of an intelligent computer assembly p 699 A89-45210 Numerical analysis of supersonic flow through oscillating assstant for engine monitoring Mechanical durability prediction methods cascade sections by using a deforming grid [AlAA PAPER 89-25391 p 674 A89-46910 D 701 A89-46468 [NASA-TM-102053] p 653 N89-25119
A-12 SUBJECT INDEX FLIGHT TESTS
FINITE ELEMENT METHOD 1988 report to the aerospace profession; Society of FLIGHT SIMULATION Solution of Euler equations by a finite element method Experimental Test Pilots, Symposium, 32nd, Beverly Hills, In search of effective diversity - A six-language study application to supersonic flows p 639 A89-44319 CA. Oct. 13-15. 1988, Proceedings p 686 A89-45151 of fault-tolerant flight control software Dynamic stress analysis of rotating turbo-machinery F-l4/F110 high angle of attack flight tests p 710 A69-44423 bladed-disk systems p 675 A89-44362 p 686 A89-45153 Economic aspects of simulation in air transportation lsoparametric shear spring element applied to crack Digital flight and inlet control in the SR-71 p 691 A89-45047 patching and instability p 699 A89-45208 p 664 A89-45160 Simulation methodology for helicopter automatic flight Computation of hypersonic vortex flows with an Euler Fokker 100, some aspects of the development of the control systems p 666 A89-45048 longitudinal control system p 687 A89-45161 model p 642 A89-45368 Longitudinal nonlinear aerodynamic model form for X-15 pilot-in-the-loop and redundant/emergency Low-storage implicit upwind-FEM schemes for the Euler USB-STOL aircraft systems evaluation p 664 A89-45168 equations p 642 A89-45375 [NAL-TR-995] p 672 N89-25990 Modeling of controlled flight dynamics using in-flight Adaptive numerical solutions of the Euler equations in simulators --- Russian book p 688 A89-46546 Descent strategy comparisons for TNAV-equipped 3D using finite elements p 644 A89-45413 aircraft under airplane-preferred operating conditions The pursuit of integrated control ~ A realtirne aircraft Applications of integrated design/analysis systems in system demonstration [NASA-CR-4248] p 690 N89-26011 aerospace structural design p 666 N89-25147 [AIAA PAPER 89-2701] p 688 A89-47029 FLIGHT SIMULATORS ASTROS: A multidisciplinary automated structural Experiences with a prevalidation methodology for Economic aspects of simulation in air transportation design tool p 705 N89-25174 designing integratedlpropulsion control system p 691 A89-45047 Recent experiences using finite-element-based architectures Inertial guidance test facility using the earth structural optimization p 705 N69-25177 [AIAA PAPER 89-27031 p 688 A89-47030 environment p 700 A89-46218 Finite element flow-thermal-structural analysis of Integrated controls pay-off --- for flight/propulsion Modeling of controlled flight dynamics using in-flight aerodynamically heated leading edges aircraft systems simulators ..-Russian book p 688 A89-46546 p 655 N89-25198 [AIAA PAPER 89-27041 p 688 A89-47031 FLIGHT TESTS Procedures for shape optimization of gas turbine disks The evolution - IFPC to VMS --- integrated llyushin goes the distance p 662 A89-43888 p 685 N89-25207 flight/propulsion control for Vehicle Management Society of Flight Test Engineers, Annual Symposium, On the stress problem of the pebble bed heat exchanger System 19th, Arlington, TX. Aug. 14-18, 1988. Proceedings in a hypersonic wind tunnel [AIAA PAPER 89.27051 p 688 A89-47032 p 662 A89-45126 [ NAL-TM-ST-87051 p 693 N89-25240 Integrated flight/propulsion control study for STOVL Cost-effective approach to flight testing the 'Casmu Plan, formulate. discuss and correlate a NASTRAN finite applications Skyshark' a stand-off weapon dispenser element vibrations model of the Boeing Model 360 [AIAA PAPER 89.29081 p 688 A89-47166 p 663 A89-45128 helicopter airframe Integrated flight/propulsioncontrol system design based Sled testing of U.S. Air Force escape systems [ NASA-CR-1817871 p 707 N89-25480 on a centralized approach p 657 A89-45129 Langley rotorcraft structural dynamics program: [NASA-TM-102137] p 690 N89-26009 'Flight testing' a multi-megawatt wind turbine Background, status, accomplishments, plans Advanced piloted aircraft flight control system design p 709 A89-45131 [ NASA-TM-1016181 p 709 N89-26273 methodology. Volume 1: Knowledge base The System 500, a real-time flight test telemetry FINITE VOLUME METHOD [NASA-CR-181726-VOL-lI p 690 N89-26013 system p 660 A89-45134 A high resolution finite volume scheme for steady Advanced piloted aircraft flight control system design Establishing artificial intelligence technology in a flight external transonic flow p 642 A89-45369 methodology. Volume 2: The FCX flight control design test environment p 663 A89-45135 Unsteady and turbulent flow using adaptation methods expert system Low cost equipment for flight test film and video p 643 A89-45392 [NASA-CR-181726-VOL-2] p 691 N69-26014 evaluation p 698 A89-45137 Navier-Stokes simulation of transonic flow about wings FLIGHT CREWS A simple low-cost telemetry system for those of modest using a block structured approach p 644 A89-45422 Aerospace Behavioral Technology Conference and means p 660 A89-45136 Numerical study of reactive ramjet dump combustor Exposition, 7th, Anaheim, CA, Oct. 3-6, 1988, Numerical modelling of flight dynamics and flight test flowfields with a pressure based CFD method Proceedings data identificationof a jet trainer airplane [AIAA PAPER 89.27981 p 681 A89-47091 [SAE P-2161 p 638 A89-47326 p 663 A89-45139 Unsteady transonic airfoil computation using implicit FLIGHT ENVELOPES A new flight flutter excitation system Euler scheme on body-fixed grid p 652 A89-47358 Current flight test experience related to structural p 663 A89-45140 FIRES divergence of forward-swept wings p 663 A89-45141 Current flight test experience related to structural Airplane tests of enhanced emergency smoke venting Advanced thrust vectoring nozzles for supercruise fighter divergence of forward-swept wings p 663 A89-45141 [ D21EN301 ] p 658 N89-25976 aircraft The measurement of linear and angular displacements FIXED WINGS [AIM PAPER 89-26161 p 682 A89-47102 in prototype aircraft - Instrumentation. calibration and Results of including geometric nonlinearities in an FLIGHT HAZARDS operational accuracy p 698 A89-45142 aerwlastic model of an F/A-18 p 669 N89-25190 Airline operations and the contaminated runway Aircraft development test and evaluation - An Office of FLAME HOLDERS [SAE PAPER 8814601 p 656 A69-47339 the Secretary of Defense perspective Effectiveness of plasma torches for ignition and UK airmisses involving commercial air transport p 638 A89-45143 flameholding in scramjet [CAA-3/88] p 658 N69-25143 Research and applicationof a new kind of measurement [AIM PAPER 89-25641 p 679 A89-46927 FLIGHT MANAGEMENT SYSTEMS technology of take-off and landing performance Improved plasma torch for ignition and flame holding The evolution - IFPC to VMS --- integrated p 698 A89-45144 in supersonic combustion flight/propulsion control for Vehicle Management The military Dash 8 flight test program [AIM PAPER 89-29451 p 704 A69-47169 System p 664 A89-45145 FLAME PROPAGATION [AIM PAPER 89.27051 p 688 A89-47032 Service Suitability testing of the F/A-lBA for use by the Combustion characteristics of gaseous flames in a gas FLIGHT MECHANICS Blue Angels Navy Flight Demonstration Team turbine combustor ExpertVision - A video-based non-contact system for p 664 A89-45146 [AIAA PAPER 89-28921 p 683 A89-47155 motion measurement p 698 A89-45136 1988 report to the aerospace profession; Society of FLAPS (CONTROL SURFACES) Numerical modelling of flight dynamics and flight test Experimental Test Pilots. Symposium, 32nd. Beverly Hills, Flap system for short takeoff and landing aircraft data identificationof a jet trainer airplane CA, Oct. 13-15, 1988, Proceedings p 686 A89-45151 [AD-W13981] p 671 N89-25234 p 663 A89-45139 F-l4/F110 high angle of attack flight tests FLAT PLATES Flight-mechanicalinvestigations of the lateral motion of p 686 A89-45153 Viscous aerodynamic analysis of an oscillating flat-plate configurationswith winglets p 689 N89-25141 X-29A performance flight tests - Results and lessons airfoil p 652 A89-47356 FLIGHT PATHS learned p 686 A89-45154 FLEXIBLE BODIES Gain transfer - An algorithm for decentralized F-16 Hornet - LEX Fence flight test results Study of nonlinear Duffing characteristicsof flexible rotor hierarchical estimation p 71 1 A89-46150 p 687 A89-45155 with SFDB -.-squeeze film damper bearings Controller evaluations of the descent advisor automation F-15 STOL/Maneuvering Technology Demonstrator - p 700 A89-45568 aid Initial flight test results p 687 A89-45157 The research of 2-0 llexible wall self-correcting wind [ NASA-TM-1021971 p 659 N89-25981 F/A-l8A digital flight control system degraded modes tunnel p 692 A89-46258 Relaxation oscillations in aircraft cruise-dash flight evaluation p 667 A89-45156 Digital robust control law synthesis using constrained optimization Fokker 100, some aspects of the development of the optimization p 669 N89-25193 [ AD-A206722] p 672 N89-25996 longitudinal control system p 667 A89-45161 FLEXIBLE SPACECRAFT FLIGHT SAFETY Manual CAT llla with a HUD - Requirements and testing Recent Advances in Multidisciplinary Analysis and Development and venficationof software for flight safety .--FAA instrument approach category Optimization. part 3 critical strapdown systems p 659 A69-43827 p 687 A89-45164 [NASA-CP-3031-PT-3] p 670 N89-25201 8-1B development testing p 687 A89-45165 Air traffic control No easy solutions in a complex FLEXIBLE WINGS - terminal environment X-15 pilot-in-the-loop and redundanVemergency Flutter suppression control law synthesis for the Active systems evaluation p 664 A89-45168 [SAE PAPER 8814691 p 661 A69-47335 Flexible Wing model Inertial guidance test facility using the earth [NASA-TM-l01584] p 690 N89-26010 Notice to Airmen (NOTAM) system operational environment p 700 A89-46216 FLIGHT ALTITUDE concept Environmental icing test of T800 helicopter engine with The influence of altitude and speed variations on the [DOT/FAA/CT-TN89/10] p 658 N89-25142 integral inlet particle separator aeroplane's load components in longitudinal nonlinear UK airmisses involving commercial air transport [AlAA PAPER 89-23241 p 676 A89-46751 manoeuvres p 686 A89-45179 [CAA-3/88] p 658 N89-25143 F-I6 inlet Stability investigation FLIGHT CHARACTERISTICS Contributions to the improvement of flight safety in wind [AIAA PAPER 89-24651 p 665 A89-46652 The ACEIRafale p 662 A89-45041 shear T-4 inletlengine compatibility flight test results FLIGHT CONTROL [ DFVLR-FB-88-49] p 656 N69-25144 [AIAA PAPER 89-24661 p 665 A69-46853
In search of eflective diversity ~ A six-language study Analysis of severe atmospheric disturbances from airline Ensuring surge-free engine operation on today's of fault-tolerant flight control software flight records turbofan powered business jets p 710 A89-44423 [ NASA-TM-lO2186l p 658 N89-25977 [AIAA PAPER 89-24871 p 678 A89-46868
A-13 FLIGHT VEHICLES SUBJECT INDEX
Tesbng of the 578-DX propfan propulsion system FLOW THEORY Free-jet test capability for the aeropropulsion systems [AIM PAPER 89-2581I p 679 A69-46938 Present stale of the theory of secondary flows and test facility UHB demonstrator flight test program - Phase 2 --- experimental verifications p 698 A89-44636 [AlAA PAPER 89.25371 p 692 A89-46908 ultra-high bypass engine technology FLOW VELOCITY The applicationof 3D marching scheme for the prediction [AIAA PAPER 89-25821 p 679 A89-46939 Computer simulation of some types of flows arising at of supersonic free jets FLIGHT VEHICLES interactions between a supersonic flow and a boundary [AIAA PAPER 89-28971 p 651 A89-47160 Methods for the mathematical modeling of flight vehicle layer p 642 A89-45381 FRICTION engines -- Russian book p 71 1 A69-46551 Measurement of three-dimensional flow in Influence of rubbing on rotor dynamics, part 2 FLOW CHARACTERISTICS turbomachinery with a wngle slanted hot-wire [NASA-CR-I83649-PT-21 p 706 N69-25464 Flow charactenslcs in an Sshapd rectangular-round p 700 A69-45561 FUEL COMBUSTION Semi-constantvolume pulse combustion for gas turbine diffuser at high incldence p646 A89-46260 Effects of axial velocity density ratio on cascade engine starting Applicabon of simple wave theory to the radiative performances p 645 A89-45565 boundary conditions required for an internal flow Euler [AIM PAPER 89-24491 p 677 A89-46838 Hot wire measurements downstream of a prop-fan solver Initial supersonic combustion facility measurements [AIAA PAPER 89-26981 p 650 A89-47027 [AIAA PAPER 89-25771 p 648 A89-46935 [ AIAA PAPER 89-24621 p 692 A69-46849 Flow charactenstics about a trailing edge FLOW VISUALIZATION FUEL CONSUMPTION [ UTIASTN-2701 p 655 N89-25952 Compressibility and shock wave interaction effects on Ducted ultra-high bypass engine configuration FLOW COEFFICIENTS free shear layers definition Flow characteristics in an S-shaped rectangular-round [AIAA PAPER 69-24601 p 648 A89-46847 [AIM PAPER 89-24781 p 678 A69-46862 diffuser at high incidence p646 A89-46260 FLUID FLOW Technology readiness for advanced ducted engines FLOW DISTRIBUTION Effects of nonlinear aerodynamics and static [AIM PAPER 89.24791 p 676 A69-46663 CFD for hypersonic airbrealhing aircraft aeroelasticity on mission performance calculations for a Testing of the 578-DX propfan propulsion system p 641 A69-45355 fighter aircraft p 669 N89-25170 [AIAA PAPER 89-2581] p 679 A89-46938 A Row-field solver using overlying and embedded FLUTTER UHB demonstrator flight test program - Phase 2 __. meshes together with a novel compact Euler algorithm Supersonic turbomachine rotor flutter control by ultra-high bGass engine technology p 641 A89-45359 aerodynamic detuning [AIAA PAPER 89-25621 p 679 A89-46939 The spatially non-uniformconvergence of the numencal [AIAA PAPER 89-26851 p 680 A89-47015 Relaxation oscillations in aircraft cruise-dash solulms of flows p 699 A89-45535 Flutter suppression using eigenspace freedoms to meet optimization Spray patternabon at high pressure requirements p 689 N69-25191 [AD-A206722] p 672 N69-25996 [AlAA PAPER 89-23231 p 702 A89-46750 Control surface spanwise placement in active flutter FUEL CONTROL Computational and expenmental study of stall suppression systems p 689 N89-25195 Numerical codes for unsteady simulation of turbojet. turbofan and turboprop engines for training purposes propagation in axial compressors FLUTTER ANALYSIS [AIM PAPER 69-22591 p 676 A69-46704 [AIAA PAPER 89-24541 p 647 A89-46842 A new flight flutter excitation system An experimental study of the effect of streamwise p 663 A89-45140 FUEL INJECTION vorticity on supersonic mixing enhancement A model for airblast atomization Aeroelastic analysis of prop fan blades with a [AIM PAPER 89-24561 p648 A69-46843 [AIAA PAPER 89-2321] p 702 A89-46748 semiempirical dynamic stall model L2F 8 LDV velocimetry measurement and analysis of Low angle inlection into a supersonic flow [AIAA PAPER 89-26951 p 703 A69-47025 the 3-D flow field in a cenlrifugal compressor [AIAA PAPER 69-2461] p 648 A89-46848 [AIAA PAPER 89-25721 p 646 A89-46933 Flutter suppression control law synthesis for the Active Evaluation of parallel injector configurations for Performance and flow field of a ducted propeller Flexible Wing model supersonic combustion [AIAA PAPER 89-26731 p 649 A89-47003 [ NASA-TM-1015641 p 690 N89-26010 IAlAA PAPER 89-25251 p 678 A89-46898 Numencal study 01 reactive ramjet dump combustor FLY BY WIRE CONTROL Fuel properties eflect on the perlormance of a small flowfields with a pressure based CFD method FIA-18A digital flight control system degraded modes high temperature rise combustor [AIAA PAPER 89-27981 p 681 A69-47091 flight evaluation p 687 A89-45158 [ NASA-TM-1020961 p 685 N69-25238 Numerical investigation of thrust-reversing nozzle using FAA handling qualities assessment - Methodology in FUEL PUMPS an implicit NDscheme transition p 687 A89-45159 Light weight gas turbine engine fuel pumping [AlAA PAPER 89-28991 p 683 A89-47162 FOAMS technology Average-passage simulation of counter-rotating propfan Fuel containment system concept lo reduce spillage [AIAA PAPER 89.25871 p 703 A89-46943 propulslon systems as applied to cruise missiles [ DOTIFAA/CT-TN89/22] p 672 N69-25994 FUEL SPRAYS [AIAA PAPER 89-29431 p 651 A89-47187 FOG A model for airblast atomization Normal impinging jet in crossflow - A parametric Warm fog dissipation using large volume water sprays [ AlAA PAPER 89-2321] p 702 A89-46748 investigation [NASA-CASE-MFS25962-1] p 693 N89-25242 Spray patternation at high pressure [AIAA PAPER 89-29571 p 684 A89-47199 FOKKER AIRCRAFT [AIM PAPER 89-23231 p 702 A69-46750 Investigation of the flow structure around a rapidly The measurement of linear and angular displacements FUEL SYSTEMS pitching airfoil p 652 A89-47360 in prototype aircraft - Instrumentation. calibration and A dynamic digital model for the turbojet with Experimentaland computational flow-field results for an operational accuracy p 696 A69-45142 pulse-monitoredfueler p 675 A89-45559 all-body hypersonic aircraft Fokker 100, some aspects of the development of the Light weight gas turbine engine fuel pumping [NASA-CR-1853471 p 655 N89-25953 longitudinal control system p 687 A69-45161 technology Vortices and pressure waves at plates, cylinders and Aerodynamic design and testing of Fokker 50 nacelle [AIAA PAPER 89-25871 p 703 A89-46943 wind profiles and intake ducts FUEL TANKS [ ISL-R-1021881 p 656 N89-25966 [AIAA PAPER 89-24631 p 665 A69-46666 Fuel containment system concept lo reduce spillage A long-range laser velocimeter for the National Design and testing of a common engine and nacelle [ DOTIFAA/CT-TN69/22] p 672 N89-25994 Full-Scale Aerodynamics Complex: New developments for the Fokker 100 and Gulfstream GIV airplanes FUELVALVES and expenmental application [AlAA PAPER 89-24861 ~€66A89-46867 Compansons between unleaded automobile gasoline [NASA-TM-101081I p 708 N69-26207 FORCE DISTRIBUTION and aviation gasoline on valve seal recession in light FLOW GEOMETRY Spanwse lift distributions and wake velocity surveys of aircraft engines Numerical study of the 3D separating flow about a semi-span wing with a discontinuous twist (NIPER-4091 p 697 N89-26110 obstacles with sharp corners p 641 A89-45363 [NASA-CR-l775321 p 653 N89-25122 FUEL-AIR RATIO Computational fluid dynamics using CATlA created FOREBODIES Initial supersonic combustion facility measurements geometry Bow shock matching with viscous effects on hypersonic [AIAA PAPER 89-24621 p 692 A89-46849 [AIAA PAPER 89-23681 p 702 A89-46776 forebodies Compansons between unleaded automobile gasoline Two-dimensional computations of multi-stage [AIAA PAPER 89-26781 p649 A89-47008 and aviation gasoline on valve seal recession in light compressor flows using a zonal approach Expenmental and computational flow-field results for an aircraft engines [AIAA PAPER 89-24521 p 647 A89-46840 all-body hypersonic aircraft [NIPER-409] p 697 N69-26110 Mach 4 testing of scramjet inlet models [ NASA-CR-1853471 p 655 N89-25953 FULL SCALE TESTS [AIM PAPER 89-26801 p 649 A89-47010 FORECASTING Full scale fatigue crack growth test of advanced jet FAA (FederalAviation Administration) aviation forecasts: Flow structure and scaling laws in lateral wing-tip trainer AT-3 p 664 A89-45207 blowing p 652 A89-47352 Fiscal years 1989-ZOO0 [AD-A206716] p 638 N89-25946 FUSELAGES FLOW MEASUREMENT In-flightmeasurement of propeller noise on the fuselage A new look at wind tunnel flow quality for transonic FRACTURE MECHANICS Crack shape identifcabon as an inverse boundary value of an airplane flows [NASA TM-1022851 p 71 3 N89-25675 [SAE PAPER 6814521 p 692 A69-45249 problem p 698 A89-44663 FRACTURES (MATERIALS) FUZY SETS Cold flow measurements for a double Swirler Probabilistic damage tolerance methods for metallic Applications of fuzzy sets to rule-based expert system combustor p 675 A89-45557 aerospace slructures p 672 N89-25237 development p 71 2 N89-26606 Hot wire measurements downstream of a propfan FRAMES [AIM PAPER 89-26981 p 650 A89-47027 Structural optimization of framed structures using FLOW STABlLlN generalized optimality criteria p 706 N89-25197 G Prediction of the stability limit of multistage axial FREE FLOW compressors p 640 A89-44637 An experimental study of the effect of streamwise GAS COMPOSITION Numerical study of the 3D separating flow about vorticity on supersonic mixing enhancement A concentration probe for the study of mixing in obstacles with sharp corners p 641 A89-45363 [AIAA PAPER 89-24561 p 648 A89-46843 supersonic shear flows Influence of thickness and camber on the aeroelastic FREE JETS [AIAA PAPER 89.24591 p 703 A69-46846 stability 01 supersonic throughflow fans: An engineering Validation of a free-jet technique for evaluating GAS FLOW approach inlet-engine compatibility Simulation of inviscid hypersonic real gas flows [ NASA-TM-I019491 p 656 N69-25957 [AIM PAPER 89-23251 p 676 A89-46752 p 644 A69-45414
A-14 SUBJECT INDEX HELICOPTERS
Rarefied gas flow through two-dimensionalnozzles Improving the development process for main combustor H [AIM PAPER 89-28931 p 650 A89-47156 exit temperature distribution GAS JETS [AIAA PAPER 89-28041 p 681 A89-47094 HANDBOOKS Low angle injection into a supersonic flow Evaluation of novel igniters in a turbulent bomb facility FAA statistical handbook of aviation: Calendar year [AIAA PAPER 89-2461 1 p 648 A89-46848 and a turbo-annular gas turbine combustor 1987 GAS MIXTURES [AIAA PAPER 89.29441 p 684 A89-47188 [AD-A200917] p 638 N89-25113 Generalization of the Roe scheme for computing flows Two axial compressor designs for a stage matching HARMONIC FUNCTIONS of mixed gases with variable concentrations investigation A new class of random processes with application to p 639 A89-44322 [AD-A206951] p685 N89-26006 helicopter noise An experimental research on mixture pressure loss in GAS-SOLID INTERFACES [ NASA-CR-1850371 p 713 N89-26679 combustor p 675 A89-45556 Diffuser performance of two-stream supersonic wind HEAD-UP DISPLAYS GAS TEMPERATURE tunnels p 652 A89-47373 Manual CAT llla with a HUD - Requirementsand testing The investigation of jet engine starting GEAR TEETH --- FAA instrument approach category p 687 A89-45164 p 676 A89-46025 Three dimensional finite element stress predictions of An exploratory study of the use of movement-correlated Improving the development process for main combustor spur gears compared to gear fatigue rig measurements [AIM PAPER 89.29181 p 704 A89-47172 cues in an auditory head-up display p 674 A89-45329 exit temperature distribution HEAT EXCHANGERS [AIM PAPER 89-28041 p 681 A89-47094 GEARS On the stress problem of the pebble bed heat exchanger GAS TUNGSTEN ARC WELDING High performance gear systems and heat management in a hypersonic wind tunnel Machine vision for control of gas tungsten arc welding for advanced ducted systems [ NAL-TM-ST-87051 p 693 N89-25240 p 700 A89-45950 [AIM PAPER 89-24821 p 678 A89-46865 HEAT RESISTANT ALLOYS GAS TURBINE ENGINES Development testing of the 578 propfan gear system Microstructure-propertyrelationships in advanced nickel Fiber metal acoustic material for gas turbine exhaust [AIAA PAPER 89-28171 p 682 A89-47103 base superalloy airfoil castings p 696 A89-45929 environments p 695 A89-44400 Technology development required by propfan power Continual opportunities for superalloy development European gas turbine engines p 675 A89-45042 reduction gearboxes p 696 A89-45931 Study of flow and heat transfer in rotating cavities [AIAA PAPER 89.28181 p 703 A89-47104 A review of beryllides for very high temperature [ONERA. TP NO. 1989-331 p 698 A89-45188 Design of a gear drive for counter-rotating fan rotors service p 696 A89-45948 Application of the boundary element method to unsteady [AIAA PAPER 89-28201 p 682 A89-47106 HEAT TRANSFER heat transfer problems p 700 A89-45552 Design criteria and analysis of dynamic stresses of a Application of the boundary element method to unsteady Effects of fuel chemical properties on exhaust smoke propeller gear system heat transfer problems p 700 A89-45552 from gas turbine combustor p 695 A89-45554 [AIAA PAPER 89-28221 p 682 A89-47107 Turbine aerodynamic performance measurements in Experimental investigation on characteristics of single GEODESY short duration facilities and tandem blade cascades with double-circular arc New Kalman filter algorithms for hybrid navigation. [AIM PAPER 89.26901 p 693 A89-47020 profile p 676 A89-45567 flightpath Computation and inertial geodesy On the stress problem of the pebble bed heat exchanger Experimental investigation of aerwngine high-speed p 659 A89-43828 in a hypersonic wind tunnel roller bearing p 700 A89-45570 GOVERNMENTllNDUSTRY RELATIONS [ NAL-TM-ST-87051 p 693 N89-25240 Continual opportunities for superalloy development Federal incentivesfor industrialmodernization: Historical Long duration balloon technology survey, phase 1 p 696 A89-45931 review and future opportunities [ AD-A2069751 p 656 N89-25965 Titanium requirementsfor current and future military gas [NASA-TM-1017851 p 714 N89-25764 Three dimensional flow and temperature profile turbine engines p 696 A89-45944 attenuation in an axial flow turbine GRAPHITE-EPOXY COMPOSITES Ceramic bearings for use in gas turbine engines [ADA2067361 p 685 N89-26005 Optimum design swept-fomard high-aspect-ration p 702 A89-46697 of Superconducting rotor cooling system graphite-epoxy wings p 669 N89-25172 Numerical codes for unsteady Simulation of turbojet. [ AD-Wl40201 p 709 N89-26240 turbofan and turboprop engines for training purposes GRID GENERATION (MATHEMATICS) HEATING EQUIPMENT [AIAA PAPER 89-22591 p 676 A89-46704 Efficient computational tool for ramjet combustor A top-down SFP analysis of a complex system --- single A model for airblast atomization research failure points p 701 A89-46472 [AIAA PAPER 89-23211 p 702 A89-46748 [AIAA PAPER 88-00601 p 674 A89-44108 On the stress problem of the pebble bed heat exchanger Spray panernation at high pressure Solution of Euler equations by a finite element method in a hypersonic wind tunnel [AIM PAPER 89-23231 p 702 A89-46750 application to supersonic flows p 639 A89-44319 [ NAL-TM-ST-87051 p 693 N89-25240 Semi-constantvolume pulse combustion for gas turbine A new variational method for the generation of two- and HELICOPTER CONTROL engine starting three-dimensional adapted grids in computational fluid Simulation methodology for helicopter automatic flight [AIAA PAPER 89-24491 p 677 A89-46838 dynamics control systems p 686 A89-45048 Three-dimensional multigrid Navier-Stokes [ONERA. TP NO. 1989.311 p 641 A89-45187 Arranging computer architectures to create cornputations for turbomachinery applications A flow-field solver using overlying and embedded higher-performancecontrollers p 71 1 A89-46147 [AIAA PAPER 89-24531 p 702 A89-46841 meshes together with a novel compact Euler algorithm HELICOPTER DESIGN Engine life maturation process p 641 A89-45359 Helicopter blades p 640 A89-45045 [AIAA PAPER 89-24641 p 677 A89-46851 ComDutational fluid dvnamics usina CATlA created Optimization design for suppressing 'ground resonance' Advantages of ceramic, solid lubricated bearings for geometry of helicopters p 664 A89-46278 small gas turbine engines [AIAA PAPER 89-23681 p 702 A89-46778 HELICOPTER ENGINES [AIAA PAPER 89-24721 p 703 A89-46858 Three-dimensional multigrid Navier-Stokes European gas turbine engines p 675 A89-45042 Diagnostic expert systems for gas turbine engines Environmental icing test T800 helicopter engine with . computations for turbomachinery applications of integral inlet particle separator Status and prospects [AlAA PAPER 89-24531 p 702 A89-46841 [AIAA PAPER 89-25851 p 680 A89-46941 [AIAA PAPER 89-23241 p 676 A89-46751 HOMAR: A computer code for generating homotopic Light weight gas turbine engine fuel pumping HELICOPTER PERFORMANCE grids using algebraic relations: User's manual technology A look at the Model 360 development [NASA-CR-42431 p 708 N89-26176 [AIAA PAPER 89.25871 p 703 A89-46943 p 664 A89-45163 Model predictions of fan response to inlet temperature GROUND EFFECT (COMMUNICATIONS) Performance and loads data from an outdoor hover test transients and spatial temperature distortion Evaluating ILS and MLS sites without flight tests of a Lynx tail rotor [AIAA PAPER 89.26861 p 650 A89-47016 p 660 A89-43894 [ NASA-TM-1010571 p 656 N89-25958 Advanced material applications for turbine airfoils GROUNDRESONANCE Analysis of helicopter environmental data: Indianapolis [AIAA PAPER 89.26931 p 680 A89-47023 Optimization design for suppressing 'ground resonance' downtown heliport, Wall Street heliport. Volume 1: A 3-D analysis of gas turbine combustors of helicopters p 664 A89-46278 Summary [AlAA PAPER 89-28881 p 683 A89-47153 GROUND SUPPORT SYSTEMS [AD-A206708] p 710 N89-26294 Combustion charactenstics of gaseous flames in a gas The 'nerve center' of ESA - Tasks and procedures of HELICOPTER TAIL ROTORS turbine combustor the ESOC in Darmstadt p 694 A89-43869 Mechanical reaction of wings moving through a vortex [AIAA PAPER 89.28921 p 683 A89-47155 GROUND TESTS region p 654 N89-25139 A technique for the measurement of blade tip clearance Society of Flight Test Engineers, Annual Symposium, Performance and loads data from an outdoor hover test in a gas turbine 19th, Arlington. TX. Aug. 14-18, 1988. Proceedings of a Lynx tail rotor [AIAA PAPER 89-29161 p 683 A89-47170 p 662 A89-45126 [ NASA-TM-1010571 p 656 N89-25958 Mechanical properties of high-temperature beryllium Concept for an aircraft multi-component thrust HELICOPTERS intermetallic compounds p 697 A89-47213 measurement facility p 691 A89-45130 The induced power based on leading edge suction for Treatment of body forces in boundary element design GUIDE VANES a helicopter in hovering p 646 A89-46267 Structural loading and noise disturbance ot helicopters sensitivity analysis p 705 N89-25187 Average-passage simulation of counter-rotating propfan p 713 N89-25140 Procedures for shape optimization of gas turbine disks propulsion systems as applied to cruise missiles p 685 N89-25207 [AIM PAPER 89.29431 p 651 A89-47187 An initiative in multidisciplinary optimization of Fuel properties effect on the performance of a small rotorcraft p 667 N89-25151 high temperature rise combustor GUST ALLEVIATORS Structural optimaation of rotor blades with straight and Gust generation in a wind-tunnel and estimation of the [NASA-TM-102096] p 685 N89-25238 swept tips subject to aeroelastic constraints model p 692 A89-46696 Aircraft engine outer duct mounting device p 667 N89-25152 [AD-D013988] p 672 N89-25991 GUST LOADS Optimization of rotor blades for combined structural, GAS TURBINES Gust generation in a wind-tunnel and estimation of the performance, and aeroelastic characteristics Application of a multi-stage3-D Euler solver to the design model p692 A89-46696 p 667 N89-25153 of turbines for advanced propulsion systems Time-correlated gust loads using Matched-Filter Theory Transonic airfoil design for helicopter rotor [AIAA PAPER 89-25781 p 679 A89-46936 and Random-Process Theory: A new way of looking at applications p 667 N89-25154 Surge and rotating stall in axial compressors things Efficient sensitivity analysis and optimization of a [AIAA PAPER 89-26831 p 649 A89-47013 [NASA-TM-101573] p 671 N89-25232 helicopter rotor p 668 N89-25155
A-15 HELIPORTS SUBJECT INDEX
Structural optimization of rotor blades with integrated Hot wire measurements downstream of a prop-fan Bow shock matching with viscous effects on hypersonic dynamics and aerodynamics p 668 N89-25156 [AIAA PAPER 89-26981 p 650 A89-47027 forebodies Computerized Design Synthesis (COS). A HOVERING [AIM PAPER 89.26781 p 649 A89-47008 database-driven multidisciplinary design tool The induced power based on leading edge suction for Rapid methodology for design and performance p 712 N89-25180 a helicopter in hovering p 646 A89-46267 prediction of integrated scramjetIhypersonicvehicle Plan, formulate. discuss and correlate a NASTRAN finite Flap-lagstability data for a small-scaleisolated hingeless [AIAA PAPER 89.26821 p 866 A89-47012 element vibrations model of the Boeing Model 360 rotor in forward flight Mixing enhancement in a supersonic combustor helicopter airframe INASA-TM- 1021 89 1 p 706 N89-25479 [AlAA PAPER 89.2794) p 681 A89-47088 I NASA-CR-181787l p 707 N89-25480 The acoustics of a small-scale helicopter rotor in Finite element flow thermal-structural analysis of FAA rotorcraft research, engineenng and development hover aerodynamically heated leading edges bibliography, 1962-1988: Supplement lNASA-TM-101058] p 655 N89-25954 p 655 N89-25198 [AD-A207162] p 673 N89-26000 Performance and loads data from an outdoor hover test HYPERSONIC WAKES A new class of random processes with application to of a Lynx tail rotor Radiative characteristics of hypersonic cone wake helicopter noise [ NASA-TM-l01057] p 656 N89-25958 p 646 A89-46263 [ NASA-CR-1850371 p 713 N89-26679 Analysis of helicopter environmental data: Indianapolis HYPERSONIC WIND TUNNELS HELIPORTS downtown heliport, Wall Street heliport. Volume I: A top-down SFP analysis of a complex system --- single Heliport identificationbeacon Summary failure points p 701 A89-46472 [ DOTIFAA/CT-TN89/31] p 661 N89-25984 [AD-A206708] p 710 N89-26294 New hypersonic facility capability at NASA Lewis Analysis of helicopter environmental data: Indianapolis HUBS Research Center downtown heliport. Wall Street heliport. Volume 1: Efficient sensitivity analysis and optimization of a [AIAA PAPER 89-25341 p 692 A89-46905 Summary helicopter rotor p 668 N89-25155 On the stress problem of the pebble bed heat exchanger [ AD-A206708] p 710 N89-26294 HULLS (STRUCTURES) in a hypersonic wind tunnel HEURISTIC METHODS Computational modeling of axisymmetric propeller-hull [ NAL-TM-ST-8705] p 693 N89-25240 A nontraditional approach to reliability interaction in slender low drag bodies p 701 A89-46483 [AlAA PAPER 89-26741 p 649 A89-47004 Applications of fuzzy sets to rule-based expert system HUMAN FACTORS ENGINEERING I development p 712 N89-26606 X-I 5 pilot-in-the-loop and redundantlemergency HIGH ASPECT RATIO systems evaluation p664 A89-45168 ICE FORMATION Optimum design of swept-forward high-aspect-ration Aerospace Behavioral Technology Conference and Environmental icing test of T8OO helicopter engine with graphite-epoxy wings p 669 N89-25172 Exposition, 7th. Anaheim, CA. Oct. 3-6. 1988. integral inlet particle separator [AIAA PAPER 89 23241 HIGH PRESSURE Proceedings p 676 A89 46751 Spray patternation at high pressure [SAE P-2161 p 638 A89-47326 ICE PREVENTION [AIAA PAPER 89-23231 p 702 A89-46750 Automation in transport aircrafl - Current and future Electromagnetic emissons from a modular Low Voltage Electro-Impulse De-icing system HIGH REYNOLDS NUMBER trends Sirnulabon of unsteady flow past sharp shoulders on [SAE PAPER 881468l p 657 A89-47334 [DOTIFAAICT 88/31] p 707 N89-26120 semi-infinite bodies p 644 A89-45415 Research in automation for air traffic control - United IGNITERS Experimental study of spreading rate enhancement of Kingdom work and associated European projects Evaluation of novel igniters in a turbulent bomb facility high Mach number turbulent shear layers [SAE PAPER 8814701 p 661 A89-47336 and a turbo-annular gas turbine combustor [ AIAA PAPER 89.24581 p 648 A89-46845 HYBRID NAVIGATION SYSTEMS [AIMPAPER 89-29441 p 684 A89-47188 HIGH STRENGTH ALLOYS New Kalman filter algorithms for hybrid navigation. Improved plasma torch for ignition and flame holding Aluminum-lithium alloys for lighter aircraft applications flightpath computation and inertial geodesy in supersonic combusbon p 696 A89-45937 p 659 A89-43828 [AIAA PAPER 89 2945) p 704 A89-47189 A review 01 beryllides for very high temperature HYDRAULIC JETS IGNITION service p 696 A89-45948 Warm fog dissipation using large volume water sprays Effectiveness 01 plasma torches for ignition and flameholding in scramlet HIGH TEMPERATURE [ NASA-CASE-MFS-25962-1] p 693 N89-25242 Mechanical properties of high-temperature beryllium HYDROCARBON FUELS IAIAA PAPER 89.25641 p 679 A89-46927 intermetallic compounds p 697 A89-47213 Development and application of a surrogate distillate ILYUSHIN AIRCRAFT X-ray based eaensometry fuel p 695 A89-44103 llyushin goes the distance p 662 A89-43888 [NASA-CR-I850581 p 706 N89-25432 HYPERSONIC AIRCRAFT Ilyushin's new workhorse p 662 A89-44375 HIGH TEMPERATURE AIR Experimental study on aerodynamic characteristics of IMAGE ANALYSIS A top-down SFP analysis 01 a complex system --- single hypersonic transport configuration p 640 A89-44972 Automated thermal mawina.. - techniaues using chromatic failure points p 701 A89-46472 CFD for hypersonic airbreathing aircraft image analysis HIGH TEMPERATURE ENVIRONMENTS p 641 A89-45355 [ NASA-TM-1015541 p 706 N89-25443 Optical research needed to support the testing of Mach 5 inlet CFD and experimental results IMAGE PROCESSING hypersonic vehicle structures p 697 A89-43840 IAlAA PAPER 89-23551 p 647 A89-46769 Low cost equipment for flight test film and video Apparent strain characteristics of strain gauges under Experimental and computational flow-field results for an evaluation p 698 A89-45137 high temperature environment p 697 A89-43844 all-body hypersonic aircraft IMAGING TECHNIQUES HIGH TEMPERATURE GASES NASA-CR-I853471 p 655 N89-25953 Evaluationof a prolectionalgorithm for the stereographic A dynamic digital model for the turbojet with HYPERSONIC FLIGHT representation of aircraft in an air traffic control system pulsemonitored fueler p 675 A89-45559 New hypersonic facility capability at NASA Lewis IDOTIFAAICT-TN89/20] p 661 N89-25985 Continual opportunities for superalloy development Research Center IMPACT LOADS Feasibility of predicting performance degradation of p 696 A89-45931 [AIAA PAPER ~9.25341 p 692 A89-46905 HIGHTEMPERATURESUPERCONDUCTORS Hypersonic airbreathing vehicle conceptual design airfoils in heavy rain Aeronautical applications of high-temperature (focus on aero-space plane) p 670 N89-25210 [NASA CR-1818421 p 657 N89-25973 superconductors HYPERSONIC FLOW IMPROVEMENT [NASA-TM-10231I] p686 N89-26008 CFD for hypersonic airbreathing aircraft A long-range laser velocimeter for the National HIGH TEMPERATURE TESTS p 641 A89-45355 Full-Scale Aerodynamics Complex New developments Titanium requirements for current and future military gas Computation of hypersonic vortex flows with an Euler and expenmental application turbine engines p 696 A89-45944 model p 642 A89-45368 [NASA-TM 101081 1 p 708 N89-26207 IN-FLIGHT MONITORING A review of beryllides for very high temperature Numerical study of unsteady viscous hypersonic blunt Measurement effects on the calculatiopn of in-flight service p 696 A89-45948 body flows with an impinging shock p 643 A89-45394 Simulation of inviscid hypersonic real gas flows thrust for an F404 turbofan engine HILBERT SPACE [AIAA PAPER 89-23641 p 677 A89-46777 State space models for aeroelastic and viscoelastic p 644 A89-45414 HYPERSONIC INLETS Preliminary development of an intelligent computer systems assistant for engine monitonng [AD-A2070921 p 690 N89-26012 Mach 5 inlet CFD and experimental results [AIAA PAPER 89-23551 p 647 A89-46769 [AIAA PAPER 89 25391 p 674 A89-48910 HOMOTOPY THEORY Numerical and expenmental investigation of In-flight measurement of propeller noise on the fuselage HOMAR: A computer code for generating homotopic airframe-integrated inlet for high velocities of an airplane gnds using algebraic relations User's manual [AIM PAPER 89-26791 p 649 A89-47009 [NASA-TM 1022851 p 713 N89-25675 [NASA-CR-42431 D 708 N89-26176 HYPERSONIC TEST APPARATUS INCENTIVES HORIZONTAL FLIGHT An experimentaltechnique for the measurementof mass Federal incentivesfor industnal modernization Historical Flap-lagstability data for a small-scale isolated hingeless flow of scramjet inlets tested in hypecsonrc pulse review and future opportunities rotor in forward flight facilities [NASA-TM-I01785] p 714 N89-25764 [ NASA-TM-1021891 p 706 N89-25479 1 AIM PAPER 89-2331 I p 692 A89-46755 INCOMPRESSIBLE FLOW HORSESHOE VORTICES HYPERSONIC VEHICLES Solution of the incompressible Navier-Stokesequations Normal impinging let in crossflow - A parametnc Optical research needed to support the testing of using artificial compressibility methods investigation hypersonic vehicle structures p 697 A89-43840 p 641 A89-45366 [AIAA PAPER 89-29571 p 684 A89-47199 Hypersonic vehicle propulsion - A computational fluid RNS solutions for three-dimensional steady HOT WORKING dynamics application case study p 639 A89-44116 incompressible flows p 643 A89-45393 Hot ducblity response of AI-Mg and AI-Mg-Li alloys New hypersonic facility capability at NASA Lewis A lifting surface method for the calculation of steady p 695 A89-45330 Research Center and unsteady, incompressible propeller aerodynamics HOT-WIRE ANEMOMETERS [AIM PAPER 89-25341 p 692 A69-46905 1 DFVLR-FB-89-04J p 657 N69-25972 A high speed data acquisition system for the analysis A numerical investigation of scramjet combustors INDUSTRIAL PLANTS of velocity, density. and total temperature fluctuations at [AIAA PAPER 89-2561 I p 679 A89-46926 Federal incentivesfor industrialmodernization Historical transonic speeds Integration of scramjets with waverider configurations review and future opportunities [ SAE PAPER 881451 ] p 691 A89-45248 [AIAA PAPER 89-26751 p 695 A89-47005 [ NASA-TM-101 7851 p 714 N89 25764
A-16 SUBJECT INDEX LASER DOPPLER VELOCIMETERS
INERTIAL GUIDANCE Annals of air and space law. Volume 13 --- Book JET IMPINGEMENT Inertial guidance test facility using the earth p 714 A89-45175 Normal impinging jet in crossflow - A parametric environment p 700 A89-46218 INTERPROCESSOR COMMUNICATION investigation INERTIAL REFERENCE SYSTEMS Arranging computer architectures to create [AIAA PAPER 89-29571 p 684 A89-47199 Development and verification 01 software for flight safety higher-performance controllers p 71 1 A89-46147 JET MIXING FLOW critical strapdown systems p 659 A89-43827 INVENTORYMANAGEMENT Three dimensional flow and temperature profile INFORMATION DISSEMINATION Aircraft sustainability model version 1.5 Users manual attenuation in an axial flow turbine Notice to Airmen (NOTAM) system operational [AD-A207015] p 638 N89-25949 [ AD-A206736] p 685 N89-26005 concept INVERSIONS JET PROPULSION [DOT/FAA/CT-TN89/10] p 658 N89-25142 State space models for aeroelastic and viscoelastic Jet or prop required lor future regional transports? systems INFRARED RADAR p 637 A69-44641 [AD-A207092] p 690 N89-26012 Infrared and millimeter wave acquisition system Civil supersonics - Propulsion is the key INVESTMENT [ONERA. TP NO. 1989.361 p 699 A89-45191 p 675 A89-45031 Federal incentives for industrialmodernization: Historical A review of propulsion applications of the pulsed INFRARED RADIATION review and future opportunities detonation engine concept Radiative characteristics of hypersonic cone wake [NASA-TM-101785] p 714 N89-25764 [AlAA PAPER 89-24461 p 677 A89.46837 p 646 A89-46263 INVISCID FLOW INFRARED SIGNATURES Inviscid transonic flow over a wavy wall decaying JP-4 JET FUEL Infrared and millimeter wave acquisition system downstream p 639 A89-44390 Development and application of a surrogate distillate p 695 A89-44103 [ONERA. TP NO. 1989-361 p 699 A89-45191 Multidimensional adaptive Euler solver fuel INLET AIRFRAME CONFIGURATIONS p 641 A89-45360 Numerical and experimental investigation of Simulation of inviscid hypersonic real gas flows airframe-integrated inlet for high velocities p 644 A89-45414 K [AIAA PAPER 89-26791 p 649 A89-47009 Inviscid and viscous flow simulations around the INLET FLOW Onera-MG by TVD schemes p 644 A89-45425 KALMAN FILTERS Validation of a free-jet technique for evaluating Bow shock matching with viscous effects on hypersonic New Kalman filter algorithms lor hybrid navigation. flightpath Computation and inertial geodesy inlet-enginecompatibility forebodies [AIAA PAPER 89-23251 p 676 A89-46752 [AIAA PAPER 89.26781 p 649 A89-47008 p 659 A89-43828 F-16 inlet stability investigation Inviscid analysis of a dual mode scramjet inlet Gain transfer - An algorithm for decentralized hierarchical estimation p 71 1 A89-46150 [AIAA PAPER 89-24651 p 665 A89-46852 [AIAA PAPER 89-26811 p 649 A89-47011 Inviscid analysis of a dual mode scramjet inlet Numerical analysis of supersonic flow through oscillating Estimating in flight engine performance variations using [AIAA PAPER 89-26811 p 649 A89-47011 cascade sections by using a deforming grid Kalman filter concepts Supersonic turbomachine rotor flutter control by [ NASA-TM-1020531 p 653 N89-25119 [AIAA PAPER 89.25841 p 679 A89-46940 aerodynamic detuning Multigrid calculation of three-dimensional KELVIN-HELMHOLTZ INSTABILITY [AIAA PAPER 89-26851 p 680 A89-47015 turbomachinery flows The instability and acoustic wave modes of supersonic INLET TEMPERATURE [NASA-CR-1853321 p 708 N89-26172 mixing layers inside a rectangular channel Model predictions of fan response to inlet temperalure p 699 A89-45453 ISENTROPIC PROCESSES transients and spatial temperature distortion Nonisentropic potential calculation for 2-D and 3-D KINEMATICS [AIAA PAPER 89-26861 p 650 A89-47016 transonic flow p 645 A89-45434 Expertvision - A video-based non-contact system for Three dimensional flow and temperature profile motion measurement p 698 A89-45136 ISOPARAMETRIC FINITE ELEMENTS attenuation in an axial flow turbine KNOWLEDGE BASES (ARTIFICIAL INTELLIGENCE) [AD-A206736] p 685 N89-26005 lsoparametric shear spring element applied to crack patching and instability p 699 A89-45208 A knowledge-based en route monitor for air traffic INPUTlOUTPUTROUTINES control p 660 A89 45065 Three dimensional finite element stress predictions of Aircraft sustainability model version 1.5: Users manual Advanced piloted aircraft flight control system design [AD-A2070151 p 638 N89-25949 spur gears compared to gear fatigue rig measurements [AIAA PAPER 89-29181 p 704 A89-47172 methodology Volume 1 Knowledge base INSTRUMENT APPROACH [ NASA-CR-181728-VOL-l] p 690 N89-26013 Manual CAT llla with a HUD Requirements and testing - Advanced piloted aircraft flight control system design FAA instrument approach category -.- methodology Volume 2 The FCX flight control design p 687 A89-45164 J expert system Microwave landing system instrumentation A pilot's . [ NASA-CR-181726-VOL-21 p 691 N89-26014 viewpoint JET AIRCRAFT [SAE PAPER 8814611 p 661 A89-47340 Numerical modelling of flight dynamics and flight test INSTRUMENT LANDING SYSTEMS data identificationof a jet trainer airplane Evaluating ILS and MLS sites without flight tests p 663 A89-45139 L p 660 A89-43894 The Rolls Royce Allison RB580 turbofan - Matching the INTAKE SYSTEMS market requirement for regional transport LAMINAR BOUNDARY LAYER F-16 inlet stability investigation [AIAA PAPER 89-24881 p 678 A89-46869 A Newtonlupwind method and numerical study of shock wave/boundary layer interactions p 645 A89-45468 [AIAA PAPER 89-24651 p 665 A89-46852 Overview of Dynamics Integration Research (DIR) INTEGRAL ROCKET RAMJETS program at Langley Research Center An initial assessment of the impact of boundary layer Efficient computational tool for ramjet combustor p 667 N89-25150 control on SST [AERO-REPT-8802] p 656 N89-25969 research Results of including geometric nonlinearities in an [AIAA PAPER 88-00601 p 674 A89-44108 aeroelastic model of an F/A-I8 p 669 N89-25190 LAMINAR FLOW AIRFOILS INTERACTIONAL AERODYNAMICS Investigation of the flow structure around a rapidly Aeroelastic modeling for the FIT (Functional Integration Interaction of an oscillating vortex with a turbulent pitching airfoil p 652 A89-47360 Technology) team F/A-18 simulation boundary layer p 645 A89-45906 p 670 N89-25192 LAMINATES Rapid methodology for design and performance Composite sizing and ply orientation for stiffness An economic model for evaluating high-speed aircraft prediction of integrated scramjellhypersonic vehicle requirements using a large finite element structural designs [AIAA PAPER 89-26821 p 666 A89-47012 model p 705 N89-25166 [NASA-CR-1775301 p 671 N89-25235 Average-passagesimulation of counter-rotatingpropfan LANDING INSTRUMENTS propulsion systems as applied to cruise missiles JET AIRCRAFT NOISE Microwave landing system instrumentation ~ A pilot's [AIAA PAPER 89-29431 p 651 A89-47187 Rectangular nozzle plume velocity modeling for use in viewpoint Investigation of the flow structure around a rapidly jet noise prediction [SAE PAPER 8814611 p 661 A89-47340 [AIAA PAPER 89-23571 p 647 A89-46771 pitching airfoil p 652 A89-47360 LANDING LOADS Supersonic jet noise and the high speed civil transport INTERMETALLICS Mechanical stresses during air transport and ground Mechanical properties of high-temperature beryllium [AIAA PAPER 89-23581 p 712 A89-46772 operations p 700 A89-46221 intermetallic compounds p 697 A89-47213 The challenge of reducing supersonic civil transport LARGE SPACE STRUCTURES INTERNATIONAL COOPERATION propulsion noise Digital robust control law synthesis using constrained Dornier's role in the 'European Fighter Aircraft' EFA [AIAA PAPER 89-23631 p 677 A89-46776 optimization p 689 N89-25193 program p 637 A89-44643 JETBLASTEFFECTS Recent Advances in Multidisciplinary Analysis and The phased establishment of support maturity for the Aircraft jet engine exhaust blast effects on Par-56 runway European Fighter Aircraft (EFA) p 637 A89-44644 Optimization. part 3 threshold lamp fixtures [ NASA-CP-3031-PT-31 p 670 N89-25201 Aerospatiale's short-term and intermediate-term place [ DOT/FAA/CT-89/4] p 694 N89-26018 Integrated structurelcontrol law design by multilevel in the international scene p 637 A89-45032 JET ENGINES optimization The SNECMA group today and tomorrow Prediction of the stability limit of multistage axial [ NASA-TM-1016231 p 712 N89-26623 p 637 A89-45034 compressors p 640 A89-44637 Airbus Industrie. lessons from experience LASER APPLICATIONS Theoretical and expenmental study of turbine p 714 A89-45039 Optical research needed to support the testing of aerodynamics p 640 A89-44639 INTERNATIONAL RELATIONS hypersonic vehicle structures p 697 A89-43840 Aerospatiale's short-term and intermediate-termplace Full scale fatigue crack growth test of advanced jet LASER DOPPLER VELOCIMETERS in the international scene p 637 A89-45032 trainer AT-3 p 664 A89-45207 L2F a LDV velocimetry measurement and analysis of Dassault, leader in European military and business Transferringjet engine diagnostic and control technology the 3-D flow field in a centrifugal compressor aircraft p 637 A89-45033 to liquid propellant rocket engines [AIAA PAPER 89-25721 p 648 A89-46933 The SNECMA group today and tomorrow [AIM PAPER 89-2851 ] p 682 A89-47125 A long-range laser velocimeter for the National p 637 A89-45034 Aircraft jet engine exhaust blast effects on Par-56 runway Full-scale Aerodynamics Complex: New developments French aerospace research in the international threshold lamp fixtures and experimental application context p 691 A89-45036 [ DOTIFAA/CT-89/4] p 694 N89-26018 [NASA-TM-101081I p 708 N89-26207 A-17 LASER INDUCED FLUORESCENCE SUBJECT INDEX
LASERINDUCEDFLUORESCENCE LINEAR QUADRATIC REGULATOR MANAGEMENTMETHODS Ouanmabve characterization of a nonreacting, Fluner suppression using eigenspace freedoms to meet Relaxation oscillations in aircraft cruise-dash supersonic combustor flowfield uslng unified laser-induced requirements p 689 N89-25191 optimization iodine fluorescence LININGS [AD-A206722] p 672 N89-25996 [AIM PAPER 89-25651 p 703 A89-46928 Fuel properties effect on the performance of a small MANEUVERABILITY LASER PROPULSION high temperature rise combustor Testing for agility - A progress report Economic analysis of a beam-powered. personalized [ NASA-TM-1020961 p 685 N89-25238 p 686 A89-45152 global aerospace transportation system LIQUID COOLING F-15 STOLlManeuvering Technology Demonstrator - [AIAA PAPER 89-24431 p 714 A89-46835 The solution of 3-D temperature distribution in a cycling Initial flight lest results p 687 A89-45157 LATERAL CONTROL oil cooled aircraft ac generator by nelwork topology An expenmental investigation of high liftlhigh rate Aeroservoelasw tailonng for lateral control method p 701 A89-46282 aerodynamics of an unsteady airfoil enhancement p 689 N89-25189 High performance gear systems and heal management [AD-A206964] p 656 N89-25964 LATERAL STABILITY for advanced ducted systems MANUAL CONTROL Asyrnmetnc separated flows about sharp cones in a [AIAA PAPER 89.24821 p 678 A89-46865 Manual CAT llla with a HUD - Requirementsand testing supersonic stream p A89-45402 643 Superconducting rotor cooling system -..FAA instrument approach category Flight-mechanicalinvestigations of the lateral motion of [ AD-DO140201 p 709 N89-26240 p 687 A89-45164 configurations mth winglets p 689 N89-25141 LIQUID CRYSTALS LEADING EDGES MARITIME SATELLITES Automated thermal mapping techniques using chromatic The links in the chain. The Inmarsat system permit Embedded temperature measurements in a --- lo image analysis mobile communications to and from any point on Earth carboncarbon mng leading edge hot structure [ NASA-TM-1015541 p7W N89-25443 p 697 A89-43843 p 697 A89-43876 LiauiD HELIUM MARKETING Soluaon of the incompressibleNaner-Stokes equations Superconducting rotor cooling system using arlthcial compressibility methods Aerospatiale's short-term and intermediate-term place [AD-DO14020] p 709 N89-26240 in the international scene p 637 A89-45032 p 641 A89-45366 Liaum PROPELLANTROCKET ENGINES MASS FLOW Numerical simulabon 01 the flow about a wing wlth Transferringjet engine diagnostic and control technology An experimental technique for the measurement of mass leading-edge vortex flow p643 A89-45390 to liquid propellant rocket engines flow of scramjet inlets tested in hypersonic pulse The induced power based on leading edge suction for [AIM PAPER 89-28511 p 682 A69-47125 facilities a helicopter in hovenng p 646 A89-46267 LITHIUM ALLOYS [AIAA PAPER 89-2331) p 692 A89-46755 Finite element flow-thermal-structural analysis of A study of AI-Li alloys using small angle neutron aerodynamlcally healed leading edges scanering p 695 A89-44577 MATCHED FILTERS p 655 N89-25198 Hot ductility response of AI-Mg and AI-Mg-Li alloys Time-correlatedgust loads using Matched-Filter Theory Flow charactensticsabout a trailing edge p 695 A89-45330 and Random-Process Theory: A new way of looking at [ UTIAS-TN-2701 p 655 N89-25952 Aluminum-lithium alloys for fighter aircraft applications things LEAKAGE p 696 A89-45937 [ NASA-TM-1015731 p 671 N89-25232 Mechanisms of Endwall leakage flows and the LOAD DISTRIBUTION (FORCES) MATCHING associated losses in a linear turbine rotor cascade with The influence 01 altitude and speed variations on the Two axial compressor designs for a stage matching blade bp-clearance aeroplane's load components in longitudinal nonlinear investigation [NAL-TR-985T] p 708 N89-26168 manoeuvres p 688 A89-45179 [AD-A206951I p 685 N89-26006 LIFE (DURABILITY) Three dimensional finite element stress predictions of MATHEMATICAL MODELS Selection of rolling-element beanng steels for longlife spur gears compared to gear fatigue ng measurements Methods for the mathematical modeling of flight vehicle applications p 704 A89-47250 [AIM PAPER 89.29181 p 704 A69-47172 engines --- Russian book p 71 1 A89-46551 LIFE CYCLE COSTS On the Stress problem of the pebble bed heal exchanger Rectangular noale plume velocity modeling for use in A corollaly to - Duane's postulate on reliability growth in a hypersonic wind tunnel jet noise prediction p 701 A89-46474 [ NAL-TM-ST-87051 p 693 N89-25240 [AIAA PAPER 89-23571 p 647 A89-46771 R8M through AvionicslElectronicslntegnty Program LOADS (FORCES) p 701 A89-46480 Ramjet combustor modeling for engineering design Multi-objeclwelloading optimization for rotating [AlAA PAPER 89-27991 p 681 A89-47092 A nontraditional approach to reliability composite flexbeams p 668 N89-25157 p 701 A89-46483 Plan, formulate. discuss and correlate a NASTRAN finite LOCKHEED AIRCRAFT element vibrations model of the Boeing Model 360 Hornet maintenance p 638 A89-46496 Experimental localized radar cross sections of aircraft Opbmizing conceptual aircraft designs for minimum life helicopter airframe p 673 A89-45105 [ NASA-CR-1817871 p 707 N89-25480 cycle cost p 670 N89-25211 LONGITUDINAL CONTROL Aircraft sustainability model version 1.5: Users manual LIFT Fokker 100. some aspects of the development of the [AD-A207015] p 638 N89-25949 Aerodynamics of high-lift. low-aspect-ratio UnSwept longitudinal control system p 687 A89-45161 wings p 652 A89-47372 LORAN C Long duration balloon technology survey, phase 1 Spanwise lift distnbutions and wake velocity surveys of Some aspects of interference on Loran-C [AD-A2W975] p 656 N89-25965 a semi-span wing with a discontinuous twist D660 A89-45221 Analysis of severe atmospheric disturbancesfrom airline [ NASA-CR-1775321 p 653 N8g-25122 LOW ASPECT RATIO flight records An experimental investigation of high Iift/high rate Aerodynamics 01 high-lift. low-aspect-ratio unswept [ NASA-TM-1021861 p 658 N89-25977 aerodynamics of an unsteady airfoil wings p 652 A89-47372 Langley rotorcraft structural dynamics program: [AD-A206964] p 656 N89-25964 LOW WEIGHT Background. status. accomplishments. plans Long duration balloon technology survey, phase 1 Light weight gas turbine engine fuel pumping [ NASA-TM-10161 81 p 709 N89-26273 [AD-A206975] p 656 N89-25965 technology MATHEMATICAL PROGRAMMING A preliminary investigation into Euler methods for [AIAA PAPER 89-25871 p 703 A89-46943 Robust computer-aided synthesis and optimization 01 application to multi-element aerofoils for high lift linear multivariable control systems with varying plant [ AERO-REPT-87101 p 708 N89-26196 dynamics via AUTOCON p 71 1 N89-25179 LIFT AUGMENTATION M Powered lift arcraft take off climb performance with one MECHANICAL OSCILLATORS Evaluation of nOndeSlNClNe test equipment for airfield engine inoperative p 663 A89-45127 MACHNUMBER pavements. Phase 1: Calibration test results and field data Preliminary assessment of exhaust systems for high Flow structure and scaling laws in lateral wing-tip collection blowing p 652 A89-47352 Mach (4 to 6) fighter aircraft [AD-A207159] p 694 N89-26020 [AIAA PAPER 89.23561 p 676 A89-46770 LIFT DEVICES MECHANICAL PROPERTIES Flap system for short takeoff and landing aircraft Expenmental study of spreading rate enhancement of Advanced material applications for turbine airfoils [AD-W13981] p 671 N89-25234 high Mach number turbulent shear layers [AIAA PAPER 89-24581 p648 A89-46845 [AIAA PAPER 89-26931 p 680 A89-47023 LIFT DRAG RATIO Mechanical properties 01 high-temperature beryllium Effect of milling machine roughness and wing dihedral MAGNESIUM ALLOYS intermetallic compounds p 697 A89-47213 on the supersonic aerodynamic charactenstics of a highly Hot ducblily response of AI-Mg and AI-Mg-Li alloys MELTING POINTS swept wing p 695 A89-45330 [ NASA-TP-29181 p 652 N89-25117 MAINTAINABILITY Continual opportunities for superalloy development ADINTS - Moving toward standardization 01 automatic p 696 A89-45931 LIFTING BODIES test equipment p 701 A89-46462 A lifting surface method for the calculation of steady MESSAGE PROCESSING R8M through AvionicslEIecIronics lntegnty Program Communications Interface Driver (CID) system user's and unsteady, incompessible propeller aerodynamics p 701 A89-46480 [ DFVLR-FB-89-041 p 657 N89-25972 manual MAINTENANCE [ DOT/FAA/CT-TN89/36] p 707 N89-26123 LINEAR PROGRAMMING Transmission overhaul and replacement predictions Procedures for shape optimization of gas turbine disks METAL FIBERS using Weibull and renewal theory Fiber metal acoustic material for gas turbine exhaust p 685 N89-25207 [ AIAA PAPER 89-29191 p 704 A89-47173 environments p 695 A89-44400 LINEAR QUADRATIC GAUSSIAN CONTROL MAN MACHINE SYSTEMS An analylcal senslwity method for use in integrated A knowledge-based en route monitor for air traffic METALS aerosewoelasbc aircraft design control p660 A89-45065 Space age metals technology; Proceedings of the [NASA-TM-1015831 p 690 N89-25239 Expert systems' role broadens p 71 1 A89-45293 Second lnternational SAMPE Metals and Metals Turbofan engine control system design using the A pilot's view of intellgent systems Processing Conference. Dayton, OH, Aug. 2-4. 1988 LQGlLTR methodology p 688 A8945294 p 696 A89-45927 [NASA-CR 1823031 p685 NE926004 Aerospace Behavioral Technology Conference and METEOROLOGICAL INSTRUMENTS Integratedflightlpropulsion control system design based Exposition, 7th. Anaheim. CA, Oct 3-6. 1988. General aviation accidents involving visual flight rules on a centralized approach Proceedings flight into instrument meteorological conditions [ NASA-TM-1021371 p690 N89-26009 [SAE P-2161 p 638 A89-47326 [ PB89-9170011 p 658 N89-25974 SUBJECT INDEX NOZZLE DESIGN
METEOROLOGICAL RADAR MTBF NEUTRON SCATTERING
Selected wind shear events ObSeNed during the 1987 A performance measure for a VHSlC avionic system ~ A study of AI-Li alloys using small angle neutron evaluation of enhancements to the FAA (Federal Aviation Mission dependent availability p 701 A89-46478 scattering p 695 A89-44577 Administration) low level wind shear alert system at NEWTON METHODS Stapleton International Airport A Newton/upwind method and numerical study of shock [AD-A206711I p 710 N89-26323 N wave/boundary layer interactions p 645 A89-45468 METHOD MOMENTS NICKEL ALLOYS OF NACELLES Radar cross section of arbitrarily shaped bodies of Microstructure-propertyrelationships in advanced nickel Aerodynamic design and testing of Fokker 50 nacelle revolution p 674 A89-45111 base superalloy airfoil castings p 696 A89-45929 and intake ducts NITROGEN OXIDES MICROBURSTS (METEOROLOGY) [AIAA PAPER 89-24831 p665 A89-46866 Analysis of severe atmosphericdisturbances from airline Investigation of low NOx staged combustor concept in NASTRAN high-speed civil transport engines flight records Composite sizing and ply orientation for stiffness [ NASA-TM-1021861 p 658 N89-25977 [AIM PAPER 89-29421 p 684 A89-47186 requirements using a large finite element structural Preventing depletion of stratospheric ozone: MICROCOMPUTERS model p 705 N89-25166 Development of a microcomputer based integrated Implications on future aircraft emissions Recent experiences using finite-element-based [DE89-009964] p 710 N89-25530 design system for high altitude long endurance aircraft structural optimization p 705 N89-25177 p 668 N89-25159 NOISE INTENSITY Plan, formulate, discuss and correlate a NASTRAN finite Re-engining stage two aircraft with the Tay MICROPROCESSORS element vibrations model of the Boeina Model 360 [AIM PAPER 89-2361I p 676 A89-46774 Low cost control system for expendable turbine helicopter airframe NOISE MEASUREMENT engines [NASA-CR-161787] p 707 N89-25480 The acoustics of a small-scale helicopter rotor in [AIAA PAPER 89-25861 p 680 A89-46942 NATIONAL AIRSPACE SYSTEM hover MICROSTRUCTURE FAA statistical handbook of aviation: Calendar year [ NASA-TM-l01058] p 655 N89-25954 Microstructure-propertyrelationships in advanced nickel 1987 Noise produced by turbulent flow into a rotor: Theory base superalloy airfoil castings p 696 A89-45929 [AD-A200917] p 638 N89-25113 manual for noise calculation MICROWAVE LANDING SYSTEMS Notice to Airmen (NOTAM) system operational [ NASA-CR-1817881 p 714 N89-26683 Evaluating ILS and MLS sites without flight tests concept NOISE POLLUTION p 660 A89-43894 [DOT/FAA/CT-TN89/10] p 658 N89-25142 Supersonic jet noise and the high speed civil transport Microwave landing system instrumentation - A pilot's Mode S performance test plan [AIAA PAPER 89-23581 p 712 A89-46772 viewpoint [DOT/FAA/CT-TN89/24] p 707 N89-26127 Noise considerations for tiltrotor [SAE PAPER 8814611 p 661 A89-47340 NATURAL LANGUAGE (COMPUTERS) [AIAA PAPER 89-23591 p 665 A89-46773 Advanced piloted aircraft flight control system design MILITARY AIR FACILITIES Noise issues - An FAA perspective on transport noise methodology. Volume 1: Knowledge base ' Report to Congress: Technical feasibility of joint use [AIAA PAPER 89-23621 p 710 A89-46775 [NASA-CR-l81726-VOL-lI p 690 N89-26013 at Scott AFB. Selfridge AGE and El Tor0 MCAS Structural loading and noise disturbance of helicopters Advanced piloted aircraft flight control system design [AD-A1945971 p 693 N69-25241 p 713 N89-25140 methodology. Volume 2 The FCX flight control design MILITARY AIRCRAFT NOISE PREDICTION (AIRCRAPT) expert system Damage tolerance analysis and structural integrity in Air Rectangular nozzle plume velocity modeling for use in [ NASA-CR-181726-VOL-21 p 691 N89-26014 Force aircraft p 661 A89-43884 jet noise prediction NAVIER-STOKES EQUATION Stealth technology for reducing aircraft recognition [AIAA PAPER 89-23571 p 647 A89-46771 Computationalfluid dynamics personal view p 673 A89-44645 - A Airfoil self-noise and prediction D 699 A89-45352 Cost-effective approach to flight testing the 'Casmu [NASA-RP-1218] p 713 N89-25673 Solution of the incompressible Navier-Stokesequations Skyshark' a stand-off weapon dispenser NOISE REDUCTION using artificialcompressibility methods p 663 A89-45128 Fiber metal acoustic material for gas turbine exhaust p 641 A69-45366 Sled testing of US. Air Force escape systems environments p 695 A89-44400 An implicit time-marching method {or solving the 3-0 p 657 A89-45129 Supersonic jet noise and the high speed civil transport compressible Navier-Stokes equations Establishing artificial intelligence technology in a flight [AIM PAPER 89-23581 p 712 A89-46772 p A89-45374 test environment p A89-45135 642 Re-engining stage two aircraft with the Tay 663 Accurate simulation of vortical flows Aircraft development test and evaluation An Office of [AIAA PAPER 89-2361] p 676 A89-46774 - p 643 A89-45384 the Secretary of Defense perspective The challenge of reducing supersonic civil transport Unsteady and turbulent flow using adaptation methods p 638 A89-45143 propulsion noise p 643 A69-45392 The military Dash flight test program [AIM PAPER 89.23631 p 677 A89-46776 8 RNS solutions for three-dimensional steady p664 A89-45145 Reduction of aircraft noise in civil air transport by incompressible flows p 643 A69-45393 T-4 inletlengine compatibility flight test results ODtimization of fliaht tracks and takeoff and aDDrOaCh Navier-Stokes simulation of transonic flow about wings [AIAA PAPER 89-24661 p 665 A89-46653 piocedures using a block structured approach p 644 A89-45422 Experiences with a prevalidation methodology for [ ILR-MITT-2001 p 713 N89-25676 A Newton/upwind method and numericalstudy of shock designing integratedlpropulsion control system NOISE SPECTRA wave/boundary layer interactions p 645 A69-45468 architectures The acoustics of a small-scale helicopter rotor in Modeling of turbulence for compression corner flows [AIM PAPER 89-27031 p A89-47030 hover 688 and internal flows Compressor exit temperature analysis [ NASA-TM-1010581 p 655 N89-25954 [AIM PAPER 89-23441 p 647 A89-46763 [AIAA PAPER 89-29471 p 684 A89-47191 Noise produced by turbulent flow into a rotor: Theory A validation of a Navier-Stokes2D solver for transonic MILITARY TECHNOLOGY manual for noise calculation turbine cascade flows Titanium requirementsfor current and future military gas [NASA-CR-181788] p 714 N89-26683 [AIAA PAPER 89-2451] p 647 A89-46839 turbine engines p 696 A89-45944 NONDESTRUCTIVETESTS Three-dimensional multigrid Navier-Stokes MILLIMETER WAVES Nondestructive qualification of UH-1 replacement parts: computations for turbomachinery applications Completion enhancement Infrared and millimeter wave acquisition system [AIAA PAPER 69.24531 p 702 ~89-46a41 [ONERA. TP NO. i~a9-361 p 699 A89-45191 [ AD-AZ066741 p 672 ~89-25995 MILLING (MACHINING) Computational analysis of turbomachinery flows using Evaluation of nondestructive test equipment for airfield Effect of milling machine roughness and wing dihedral FLOFIVE pavements. Phase 1: Calibration test results and field data on the supersonic aerodynamic characteristics of a highly [AIAA PAPER 89-25591 p 648 A89-46924 collection swept wing Performance and flow field of a ducted propeller [AD-A2071591 p 894 N89-26020 [ NASA-TP-29181 p 652 N89-25117 [AIAA PAPER 89.26731 p 649 A89-47003 NONLINEAR EQUATIONS MISSILE CONFIGURATIONS Computational modeling of axisymmetric propeller-hull Longitudinal nonlinear aerodynamic model form for Average-passage simulation of counter-rotating propfan interaction in slender low drag bodies USB-STOL aircraft propulsion systems as applied to cruise missiles [AIAA PAPER 89-26741 p 649 A89-47004 [NAL-TR-995] p 672 N89-25990 [AIM PAPER 89-29431 p 651 A89747187 Navier-Stokes simulations around a propfan using NONLINEAR SYSTEMS MISSILE CONTROL higher-order upwind schemes Asymptotically decoupled discontinuous control of Infrared and millimeter wave acquisition system [AIAA PAPER 89-26991 p 650 A89-47028 systems and nonlinear aircraft maneuver [ONERA. TP NO. 1989.361 p 699 A89-45191 Numerical study of reactive ramjet dump combustor p 686 A89-45064 MIXING LAYERS (FLUIDS) flowfieldswith a pressure based CFD method Nonlinear and adaptive control The instability and acoustic wave modes of supersonic [AIAA PAPER 89-27981 p 681 A89-47091 [NASA-CR-180088] p 712 N89-26610 NONLINEARITY mixing layers inside a rectangular channel Numerical investigation of thrust-reversing noale using Results of including geometric nonlinearities in an p 699 A89-45453 an implicit TVD scheme aeroelastic model of an F/A-18 p 669 N89-25190 Diffuser performance of two-stream supersonic wind [AIAA PAPER 89-28991 p 683 A89-47162 tunnels p 652 A89-47373 Nonlinear and adaptive control Three dimensional flow and temperature profile MOBILE COMMUNICATION SYSTEMS [NASA-CR-1800881 p 712 N89-26610 attenuation in an axial flow turbine The links in the chain -The lnmarsat system ---to permit NONUNIFORM FLOW [AD-A206736] p 685 N89-26005 mobile communications to and from any point on Earth The spatially non-uniform convergence of the numerical p 697 A89-43876 Multigrid calculation of three-dimensional solutions of flows p 699 A89-45535 MOTION SIMULATION turbomachinery flows Design optimization of axisymmetric bodies in An exploratory study of the use of movement-correlated [NAM-CR-185332] p 708 N89-26172 nonuniform transonic flow p 670 N89-25206 cues in an auditory head-up display p 674 A89-45329 NAVIGATION AIDS NOSE TIPS MOUNTING Navigation aids to aircraft all-weather landing Unsteady transition location p 652 A89-47376 Flap system for short takeoff and landing aircraft p 659 A89-43891 NOZZLE DESIGN [AD-M)13981] p 671 N89-25234 NAVIGATION SATELLITES Preliminary assessment of exhaust systems for high Aircraft engine outer duct mounting device Civil satellite navigation and location systems Mach (4 to 6) fighter aircraft [ AD-Wl39881 p 672 N89-25991 p 694 A89-43892 [AIAA PAPER 89-23561 p 676 A89-46770
A-19 NOZZLE FLOW SUBJECT INDEX
Parametric study of a simultaneous pitchlyaw thrust An initiative in multidisciplinary optimization of P vectonng single expansion ramp nozzle rotorcraft p 667 N89-25151 [AIM PAPER 89.28121 p 682 A89-47098 Structural optimization of rotor blades with straight and PANEL METHOD (FLUID DYNAMICS) Supersonic nozzle mixer ejector swept tips subject to aeroelastic constraints LOPAN - A low-order panel method for subsonic and [AIAA PAPER 89-29251 p 683 A89-47178 p 667 N89-25152 supersonic flows p 639 A89-43724 Expendable supersonic exhaust nozzle concepts Optimization of rotor blades for combined structural, Transonic analysis of arbitrary configurations using [AIM PAPER 89-29271 p 684 A89-47179 performance, and aeroelastic characteristics locally refined grids p 644 A89-45419 NOZZLE FLOW p 687 N89-25153 A lifting surface method for the calculation of steady and unsteady, incompressible propeller aerodynamics Rectangular nozzle plume velocity modeling for use in Efficient sensitivity analysis and optimization of a [DFVLR-FB-89-04] p 657 N89-25972 jet noise prediction helicopter rotor p 668 N89-25155 [AIAA PAPER 89-23571 p 647 A89-46771 PANELS Structural opbmization of rotor blades with integrated Initial supersonic combustion facility measurements Reinforcing solutions for a panel cut-out dynamics and aerodynamics p 668 N89-25156 [AIAA PAPER 89-24621 p 692 A89-46849 p 698 A89-45177 Combustion enhancement in supersonic coaxial flows Multi-objectivelloading optimization for rotating PARACHUTEDESCENT [AIAA PAPER 89-27881 p 681 A89-47084 composite flexbeams p 668 N89-25157 Fast brake- F-111 high-performance parachute system Rarefied gas flow through two-dimensional nozzles Structural tailoring of counter rotation propfans development p 657 A89-46593 [AIAA PAPER 89-28931 p 650 A89-47156 p 685 N89-25165 PARALLEL PROCESSING (COMPUTERS) NOZZLE GEOMETRY Aerolastic tailoring and integrated wing design Multilevel decomposition of complete vehicle Advanced thrust vectonng nozzlesfor supercruise fighter p 668 N89-25167 configuration in a parallel computing environment aircraft Optimum structural design with static aeroelastic p 670 N89-25205 [AIAA PAPER 89-28161 p 682 A89-47102 constraints p 669 N89-25171 PARTIAL DIFFERENTIAL EQUATIONS Numerical investigation of thrust-reversing nozzle using Optimum design of swept-forward high-aspect-ration Crack shape identificationas an inverse boundary value an implicit NDscheme graphite-epoxy wings p 669 N89-25172 problem p 698 A89-44663 PASSENGER AIRCRAFT [AIAA PAPER 89-28991 p 683 A89-47162 Recent Advances in Multidisciplinary Analysis and Tupolev's new twin p 662 A89-43887 Normal impinging jet in crossflow - A parametric Optimization, part 2 llyushin goes the distance p 662 A89-43888 investigabon [ NASA-CP-3031-PT-21 p 669 N89-25173 [AI4A PAPER 89-29571 p 684 A89-47199 In the drink --- ditch landing capability of aircraft ASTROS: A multidisciplinary automated Structural p 691 A89-43890 NUMERICAL ANALYSIS design tool p 705 N89-25174 The spatially non-uniform convergence of the numerical Ilyushin's new workhorse p 662 A89-44375 solutions of flows p 699 A89-45535 Recent experiences using finite-element-based Jet or prop required for future regional transports? structural optimization p 705 N89-25177 NUMERICAL FLOW VISUALIZATION p 637 A89-44641 Numerical simulations of oblique detonabons in Robust computer-aided synthesis and optimization Of PATCH TESTS supersonic combustion chambers p 674 A89-44115 linear mulbvanable control systems with varying plant lsoparametric shear spring element applied to crack Studies of vortex flow aerodynamics using CFD flow dynamics via AUTOCON p 71 1 N89-25179 patching and instability p 699 A89-45208 visualizations p 641 A89-45260 Treatment of body forces in boundary element design PAVEMENTS Computation of hypersonic vortex flows with an Euler sensitivity analysis p 705 N89-25187 Design criteria for aggregate-surfaced roads and model p 642 A89-45368 Digital robust cnntrol law synthesis using constrained airfields NUMERICAL INTEGRATION optimization p 689 N89-25193 [AD-A207059] p 694 N89-26019 A flow-field solver using overlying and embedded An integrated approach to the optimum design of actively Evaluation of nondestructivetest equipment for airfield meshes together with a novel compact Euler algorithm controlled composite wings p 670 N89-25194 pavements. Phase I:Calibration test results and field data collection p 641 A89-45359 An approximation function for frequency constrained structural optimization p 705 N89-25196 [AD-A2071591 p 694 N89-26020 PERFORATEDPLATES 0 Structural optimization of framed structures using Reinforcing solutions for a panel cut-out generalized optimality criteria p 706 N89-25197 p 698 A89-45177 OBLIQUE SHOCK WAVES Recent Advances in Multidisciplinary Analysis and PERFORMANCE PREDICTION Numerical simulations of oblique detonations in Optimization. part 3 Prediction of turbomachinery performance - Application supersonic combustion chambers p 674 A89-44115 [NASA-CP-3031-PT-31 p 670 N89-25201 to a centrifugal pump, a centrifugal compressor. and a Interaction of an oblique shock wave with supersonic Multilevel decomposition of complete vehicle radial inflow turbine p 640 A89-44638 turbulent blunt body flows p 644 A89-45405 configurationin a parallel computing environment Performance analysis of scramjet engines OBLIQUE WINGS p 670 N89-25205 p 676 A89-46600 Control surface spanwise placement in active flutter Design opbmization of axlsymmetric bodies in Theapplicationof3D marching scheme forthe prediction suppression systems p 689 N89-25195 nonuniform transonic flow p 670 N89-25206 of supersonic free jets The conceptual design of a Mach 2 Oblique Flying Wing Procedures for shape optimization of gas turbine disks [AIAA PAPER 89-28971 p 651 A89-47160 supersonic transport p 685 N89-25207 Reduction of I-P aerodynamic loads on tractor aircraft [NASA-CR-I775291 p 671 N89-25233 Optimizing conceptual aircraft designs for minimum life engine installations OMEGA NAVIGATION SYSTEM cycle cost p 670 N89-25211 [AIAA PAPER 89-29241 p 651 A89-47177 Omega navigation in the shadow of Antarctica Aircraft design optimization with multidisciplinary Brayton cycle engines with reciprocating work p 660 A89-43893 performance criteria p 671 N89-25212 components ONBOARD EQUIPMENT The role of optimization in the next generation of [AIAA PAPER 89-29331 p 704 A89-47181 The measurement of linear and angular displacements computer-based desrgn tools p 712 N89-25220 Feasibility of predicting performance degradation of in prototype aircraft - Instrumentation, calibration and An overview of the Douglas Aircraft Company airfoils in heavy rain operational accuracy p 698 A89-45142 Aeroelastic Design Optimization Program (ADOP) [ NASA-CR-1818421 p 657 N89-25973 OPENINGS p 671 N89-25221 Tipjet VTOL UAV (Vertical Takeofi and Reinforcing solutions for a panel cut-out Meeting the challenges with the Douglas Aircraft LandinglUnmanned Aerial Vehicle) summary. Volume 1: p 698 A89-45177 Company Aeroelastic Design Optimization Program A 1200 pound tipjet VTOL unmanned aerial vehicle. Part OPTICAL FIBERS (ADOPI p 671 N89-25222 I:& nceptual design study of a 1200-pound vehicle Optical fiber sensor development for turbine Recent developments in large-scale structural [AD-A206738] p 672 N89-25997 applications optimization p 706 N89-25231 PERFORMANCE TESTS [AIAA PAPER 89-29141 p 704 A89-47168 Relaxation oscillations in aircraft cruise-dash 'Flight testing' a multi-megawatt wind turbine OPTICAL RADAR optimization p 709 A89-45131 Prototype of a slant visual range measuring device [AD-A206722] p 672 N89-25996 A performance measure for a VHSlC avionic system - [ DFVLR-FB-86-42] p 713 N89-25697 Integrated structurelcontrol law design by multilevel Mission dependent availability p 701 A89-46478 OPTICAL RANGE FINDERS optimization Turbine aerodynamic performance measurements in Prototype of a slant visual range measunng device [ NASA-TM-1016231 p 712 N89-26623 short duration facilities [DFVLR-FB-88-42] p 713 N89-25697 ORGANIZATIONS [AIAA PAPER 89.26901 p 693 A89-47020 OPTIMAL CONTROL The 'nerve center' of ESA - Tasks and procedures of Mode performance test plan Flutter suppression control law synthesis for the Active S the ESOC in Darmstadt p 694 A89-43869 [ DOT/FAA/CT-TN89/24] p 707 N89-26127 Flexible Wing model OSCILLATING FLOW [NASA-TM-1015841 p690 N89-26010 Satellite low rate voice demonstration test plan A natural low-frequency oscillation of the flow over an [AD-A2067101 p 707 N89-26133 Nonlinear and adaptive control airfoil near stalling conditions p 645 A89-45437 Selected wind shear events observed during the 1987 [NASA-CR-1800881 p 712 N89-26610 Pressure fluctuations on an oscillating trailing edge OPTIMIZATION p 645 A89-45458 evaluation of enhancements to the FAA (Federal Aviation Administration) low level wind shear alert system at An integrateddesign computationalmethod for the wing Interaction of an oscillating vortex with a turbulent Stapleton InternationalAirport optimization camber and twist at subsonic and supersonic boundary layer p 645 A89-45906 flow p 646 A89-46256 Numericalanalysis of supersonic flow through oscillating [AD-A206711] p 71 0 N89-26323 Optimization design for suppressing 'ground resonance' cascade sections by using a deforming gnd PHOSPHORS of helicopters p664 A89-46278 [ NASA-TM-1020531 p 653 N89-25119 Automated thermal mapping techniques using chromatic Recent Advances in Mllltidisciplinary Analysis and OSCILLATIONS image analysis Optimization, part 1 Relaxation oscillations in aircraft cruise-dash [ NASA-TM-1015541 p 706 N89-25443 [ NASA-CP-3031-PT-1I p666 N89-25146 opbmization PHOTOINTERPRETATION Applications of integrated design/analysis systems in [ AD42067221 p 672 N89-25996 An air photo analysis of an airplane crash aerospace structural design p666 N89-25147 OZONE p 657 A89-45337 Overview of Dynamics Integration Research (DIR) Preventing depletion of stratospheric ozone: PILOT PERFORMANCE program at Langley Research Center Implications on future aircraft emissions A pilot's view of intelligent systems p 667 N89-25150 [ DE89-009964I p 710 N89-25530 p 688 A89-45294
A-20 SUBJECT INDEX PYLONS
Advanced piloted aircraft flight control system design PRESSUREMEASUREMENT PROPELLER EFFICIENCY methodology. Volume 1: Knowledge base Pressure measurement technique of WT-WK _-- wind Low-speed wind tunnel performance of high-speed [NASA-CR-181726-VOL-lI p 690 N89-26013 tunnels counterrotation propellers at angle-ol-attack Advanced piloted aircraft flight control system design [DFVLR-MIlT-88-11] p 693 N89-25243 [NASA-TM-102292] p 653 N89-25121 methodology. Volume 2: The FCX flight control design PRESSURE OSCILLATIONS PROPELLER FANS expert system Pressure lluctuations on an oscillating trailing edge Predictionof periodic loadings on single rotation propfan [NASA-CR-l81726-VOL-21 p 691 N89-26014 p 645 A89-45458 with off-axis inflow Applications of fuzzy sets to rule-based expert system PRESSURE REDUCTION [AIAA PAPER 89-26941 p 681 A89-47024 development p 712 N69-26606 An experimental research on mixture pressure loss in Aeroelastic analysis 01 prop fan blades with a combustor p 675 A89-45556 PILOT TRAINING semiempirical dynamic stall model PRESSURE REGULATORS Economic aspects of Simulation in air transportation [AIAA PAPER 89-26951 p 703 A89-47025 A top-down SFP analysis of a complex system single p 691 A89-45047 --- Technology development required by propfan power failure points p 701 A89-46472 PITCH (INCLINATION) reduction gearboxes PROBABILITY THEORY [AIAA PAPER 89-28181 p 703 A89-47104 Parametric study of a simultaneous pitchlyaw thrust Probabilistic analysis of aircraft structure Average-passage simulation of counter-rotating propfan vectoring single expansion ramp nozzle p 665 A89-46470 [AIAA PAPER 89-28121 p 682 A89-47098 propulsion systems as applied to cruise missiles Time dependent probabilistic failure of coated [AIAA PAPER 89-29431 p 651 A89-47187 An experimental investigation of high liftlhigh rate components aerodynamics of an unsteady airfoil [AIAA PAPER 69-29001 p 704 A89-47163 PROPELLER NOISE [ AD-A206964] p 656 N89-25964 Probabilistic damage tolerance methods for metallic In-flight measurement of propeller noise on the fuselage PITCHING MOMENTS aerospace structures p 672 N89-25237 of an airplane Investigation of the flow structure around a rapidly PROCESS CONTROL (INDUSTRY) [NASA-TM-102285] p 713 N89-25675 pitching airfoil p 652 A89-47360 Machine vision for control 01 gas tungsten arc welding PROPELLERS PLASMA JETS p 700 A89-45950 A lifting surface method for the calculation of steady Evaluation of novel igniters in a turbulent bomb facility PRODUCTDEVELOPMENT and unsteady, incompressible propeller aerodynamics p 657 N89-25972 and a turbo-annular gas turbine combustor Aeronautical research in the European future [ DFVLR-FB-89-04] [AIAA PAPER 89-29441 p 684 A89-47166 p 638 A89-45037 PROPULSION SYSTEM CONFIGURATIONS PLASMA TORCHES European gas turbine engines p 675 A89-45042 Advanced propulsion systems for large subsonic Effectiveness of plasma torches for ignition and Airbus - The new families p 662 A89-45043 transports flameholding in scramjet FAA rotorcraft research, engineering and development [AIAA PAPER 89-24771 p 677 A89-46861 [AIAA PAPER 69-25641 p 679 A89-46927 bibliography, 1962-1988: Supplement Testing of the 576-DX propfan propulsion system Improved plasma torch lor ignition and flame holding [AD-A207162] p 673 N89-26000 [AIM PAPER 89-2581I p 679 A69-46938 ’ in supersonic combustion PRODUCTION COSTS Integration of scramjets with waverider configurations [AIAA PAPER 89-29451 p 704 A89-47189 Strategic bombers: 8-1B cost and performance remain [AIAA PAPER 89-26751 p 695 A89-47005 PLUMES uncertain Numerical investigation of thrust-reversingnozzle using Rectangular nozzle plume velocity modeling for use in [AD-A206751] p 673 N89-25998 an implicit NDscheme jet noise prediction PROGRAMMING LANGUAGES [AIAA PAPER 89-28991 p 683 A89-47162 [AIAA PAPER 89-23571 p 647 A89-46771 In search of effective diversity - A six-language study Integrated flight/propulsion control study for STOVL POLARIZATION (WAVES) of fault-tolerant llight control software applications Review 01 FD-TD numericalmodeling of electromagnetic p 710 A89-44423 [AIAA PAPER 89-29081 p 688 A89-47166 wave scattering and radar cross section Development of a microcomputer based integrated A static investigation of several STOVL exhaust system p 673 A89-45107 design system for high altitude long endurance aircraft concepts POLYMERIC FILMS p 668 N89-25159 [AIAA PAPER 69-29281 p 684 A89-47180 Long duration balloon technology survey, phase 1 PROLOG (PROGRAMMING LANGUAGE) Average-passage simulation of counter-rotating proplan [AD-A206975] p 656 N89-25965 A knowledge-based en route monitor for air traffic propulsion systems as applied to cruise missiles POLYMERS control p 660 A89-45065 [AIM PAPER 89-29431 p 651 A89-47187 Combustion behavior of boron-based BAMO/NMMO PROP-FAN TECHNOLOGY Aeronautical applications of high-temperature fuel-rich solid propellants Prop-fan tested for structural and acoustic data superconductors [AIAA PAPER 89-26641 p 696 A89-47149 p 674 A89-43885 [NASA-TM-102311] p 686 N89-26008 POSITIONING Testing of the 578-DX propfan propulsion system PROPULSION SYSTEM PERFORMANCE Control surface spanwise placement in active flutter [AIM PAPER 89-25811 p 679 A89-46938 New hypersonic facility capability at NASA Lewis suppression systems p 689 N89-25195 Predictionof periodic loadingson single rotation propfan Research Center POTENTIAL FLOW with off-axis inflow [AIAA PAPER 89-25341 p 692 A89-46905 Multi-stage compressor airfoil aerodynamics. I - Airfoil [AIAA PAPER 89-26941 p 681 A89-47024 A numerical investigation of scramjet combustors potential flow analysis p 639 A89-44112 Aeroelastic analysis of prop fan blades with a [AIAA PAPER 89-2561] p 679 A89-46926 Multigrid calculations for cascades semiempirical dynamic stall model Application of a multi-stage3-D Euler solver to the design p 643 A89-45391 [AIAA PAPER 89-26951 p 703 A89-47025 of turbines for advanced propulsion systems Nonisentropic potential calculation for 2-D and 3-D Large scale advanced propeller blade pressure [AIAA PAPER 89.25781 p 679 A89-46936 transonic flow p 645 A89-45434 distributions - Prediction and data Estimating in-flight engine performance variations using POWER SPECTRA [AIAA PAPER 69-26961 p 650 A69-47026 Kalman filter concepts A new class of random processes with application to Hot wire measurements downstream of a propfan [AIAA PAPER 89-25841 p 679 A89-46940 helicopter noise [AIM PAPER 89-26981 p 650 A89-47027 A comparison of scramjet engine performances 01 [ NASA-CR-1850371 p 713 N69-26679 Navier-Stokes simulations around a propfan using various cycles PREDICTION ANALYSIS TECHNIOUES higher-order upwind schemes [AIM PAPER 89.26761 p 680 A89-47006 Model predictions lor improved recoverability of a [AIAA PAPER 89-26991 p 650 A69-47028 A propulsion development strategy for the National multistage axial-flow compressor Development testing of the 578 propfan gear system Aero-Space Plane [AIAA PAPER 89-26871 p 650 A89-47017 [AIAA PAPER 89.28171 p 682 A89-47103 [AIAA PAPER 89-2751I p 681 A89-47061 FAA (FederalAviation Administration)aviation forecasts: Technology development required by proplan power Development testing of the 578 propfan gear system Fiscal years 1989-2000 reduction gearboxes [AIAA PAPER 89.28171 p 682 A89-47103 [AD-A206716] p 638 N89-25948 [AIM PAPER 89-28181 p 703 A89-47104 Expendable supersonic exhaust nozzle concepts PREPROCESSING Average-passage simulation of counter-rotating proplan [AIAA PAPER 89-29271 p 684 A89-47179 Composite sizing and ply orientation for stiffness propulsion systems as applied to cruise missiles Integratedflight/propulsion control system design based requirements using a large finite element structural [AIAA PAPER 89-29431 p 651 A89-47187 on a centralized approach model p 705 N89-25166 Structural tailoring of counter rotation proplans [NASA-TM-102137] p 690 N89-26009 PRESSURE DISTRIBUTION p 685 N89-25165 PROTECTIVE COATINQS Large scale advanced propeller blade pressure PROPELLANT CHEMISTRY Time dependent probabilistic failure of coated distributions - Prediction and data Development and application of a surrogate distillate components [AIAA PAPER 69-26961 p 650 A89-47026 fuel p 695 A89-44103 [AIAA PAPER 89-29001 p 704 A89-47163 On the stress problem 01 the pebble bed heat exchanger PROPELLER BLADES PROTOTYPES in a hypersonic wind tunnel Helicopter blades p 640 A89-45045 The measurement 01 linear and angular displacements [ NAL-TM-ST-87051 p 693 N89-25240 Large scale advanced propeller blade pressure in prototype aircraft . Instrumentation. calibration and Experimental and computational flow-fieldresults lor an distributions - Prediction and data operational accuracy p 698 A89-45142 all-body hypersonic aircraft [AIAA PAPER 89-26961 p 650 A89-47026 PULSED JET ENGINES [NASA-CR-185347] p 655 N89-25953 Navier-Stokes simulations around a proplan using A review of propulsion applications of the pulsed The Schlieren Observation System installed in the NAL higher-order upwind schemes detonation engine concept two-dimensional high-Reynolds number transonic wind [AIM PAPER 89-26991 p 650 A89-47028 [AIAA PAPER 89-24461 p 677 A89-46837 tunnel and attempts to improve it Reduction of 1-P aerodynamic loads on tractor aircraft PUMPS [ NAL-TR-9641 p 693 N89-26015 engine installations Superconductingrotor cooling system PRESSUREDROP [AIAA PAPER 89.29241 p 651 A89-47177 [ AD-Wl40201 p 709 N89-26240 Calculation of the total pressure loss coefficient with Low-speed wind tunnel performance of high-speed PYLONS three models for four supersonic axial-flow compressors counterrotation propellers at angle-of-attack Nacelle/pylon interference study on a 1/17th-sca1e, p 640 A89-44898 [NASA-TM-102292] p 653 N89-25121 twin-engine, low-wing transport model PRESSUREEFFECTS PROPELLER DRIVE [AIAA PAPER 89-24801 p 665 A89-46864 Aircraft jet engine exhaust blast effectson Par-56 runway Design criteria and analysis of dynamic stresses of a Block-structured solution of transonic flows around threshold lamp lixtures propeller gear system wing/pylon/nacelle configurations [ DOT/FAA/CT-89/4] p 694 N89-26018 [AIM PAPER 69-28221 p 682 A89-47107 [AIAA PAPER 89-29401 p 651 A89-47184
A-2 1 RADAR BEACONS SUBJECT INDEX
R Arranging computer architectures lo create Ceramic bearings for use in gas turbine engines higher-performancecontrollers p 71 1 A89-46147 p 702 A89-46697 RADARBEACONS Gain transfer - An algonthm for decentralized Advantages of ceramic, solid lubricated bearings for Functmal requirements of the Communications hrerarchlcal estimator8 p 711 A89-46150 small gas turbine engines Interface Dnver (CID) RECIRCULATIVE FLUID FLOW [AIAA PAPER 89-24721 p 703 A89-46858 [DOT/FAA/CT-TN87/41-REV] p 707 N89-26121 Cold flow measurements for a double swirler Selection of rolling-element bearing steels for long-life Mode S performance test plan combustor p 675 A89-45557 applications p 704 A89-47250 [ DOT/FAA/CT-TN89/24 I p 707 N89-26127 RECONNAISSANCE AIRCRAFT ROLLING MOMENTS Aeroservcelastic tailoring for lateral control RADAR CROSS SECTIONS Digital flight and inlet control in the SR-71 Experimental localized radar cross sections of aircraft p 664 A89-45160 enhancement p 689 N69-25189 p 673 A89-45105 ROTARY WING AIRCRAFT RECOVERABILITY Review of FD-TD numerical modelingof electromagnetic Langley rotorcraft structural dynamics program: Model predictions for improved recoverability of a wave scanenng and radar cross section Background. status, accomplishments. plans multistage axial-flow compressor p 673 A89-45107 [ NASA-TM-1016181 p 709 N89-26273 [AIAA PAPER 89-26871 p 650 A89-47017 Radar cross secbon of arbitranly shaped bodies of ROTARY WINGS revolution p 674 A89-45111 REDUNDANCY Helicopter blades p 640 A89-45045 The analysis and measurements of radar cross section X-15 pilot-in-the-loop and redundant/emergency Vortex flows in flying technique (RCS) of some mng structure models systems evaluation p 664 A89-45168 [ ETN-89.944281 p 653 N89-25126 p 674 A89-46298 SPAREL - A model for reliability and sparing in the world Strongly unsteady vortex fields at elastic helicopter rotor RADAR DETECTION of redundancies p 702 A89-46493 blades p 654 N89-25131 Stealth technology for reducing aircraft recognibon REGULATIONS Mechanical reaction of wings moving through a vortex p 673 A89-44645 Noise issues - An FAA perspective on transport noise region p 654 N89-25139 RADARTARGETS [AIM PAPER 89-23621 p 710 A89-46775 An initialive in multidisciplinary optimization of Experimental localized radar cross sections of aircraft REINFORCEMENT (STRUCTURES) rotorcraft p 667 N89-25151 p 673 A89-45105 Reinforcing solutions for a panel CUI-out Structural optimization of rotor blades with straight and The analysis and measurements of radar cross Section p 698 A89-45177 swept lips sutqect to aeroelastic constraints (RCS) of some wing structure models RELIABILITY ANALYSIS p 667 N89-25152 p 674 A89-46298 A corollary lo - Duane's postulate on reliability growth Optimization of rotor blades for combined structural, RADIAL FLOW p 701 A89-46474 performance, and aeroelastic characteristics Prediction of turbomachinery performance .Applicabon SPAREL - A model for reliability and sparing in the world p 667 N89-25153 to a centnfugal pump, a centrifugal compressor, and a of redundancies p 702 A89-46493 Transonic airfoil design for helicopter rotor radial inflow turbme p 640 A89-44638 Testing of reliability - Analysis tools applications p 667 N89-25154 RADIATIVE HEAT TRANSFER p 702 A89-46503 Efficient sensitivity analysis and optimization of a Application of simple wave theory lo the radiative Transmission overhaul and replacement predictions helicopter rotor p 668 N89-25155 boundary conditions required for an internal flow Euler using Weibull and renewal theory Multi-objectivelloading optimization for rotating solver [AIAA PAPER 89-29191 p 704 A89-47173 composite flexbeams p 668 N89-25157 [AlAA PAPER 89-25771 p 648 A89-46935 RELIABILITY ENGINEERING TRUSS An intelligent design system for aircraft wings RADIO NAVIGATION A nontraditional apptoach to reliability p 711 N89-25162 C~ilsatellite navigation and location systems p 701 A89-46483 Flaplag stability data for a small-scaleisolated hingeless p 694 A89-43892 The designer of the 90's: A hedemonstration rotor in forward flight Omega navigation in the shadow of Antarctica p 705 N89-25164 [ NASA-TM-1021891 p 706 N89-25479 p 660 A89-43893 REMOTELY PILOTED VEHICLES The acoustics of a small-scale helicopter rotor in Some aspects of interference on Loran-C Tipjet VTOL UAV (Vertical Takeoff and hover p 660 A89-45221 Landing/Unmanned Aerial Vehicle) summary. Volume 1: [NASA-TM-I01 058) p 655 N89-25954 RAIN A 1200 pound tiplet VTOL unmanned aerial vehicle. Part ROTATING DISKS Steady-state and transitional aerodynamic 1:Co nceptual destgn study of a 1200-pound vehicle Dvnamic stress analvsis of rotatina turbo-machinerv characteristics of a wing in simulated heavy rain [AD-A206738] p 672 N89-25997 bladeddisk systems . 6675 A89-44362 [ NASA-TP-29321 p 655 N89-25951 REOUIREMENTS ROTATING FLUIDS Feasibility of predicting performance degradation of Report to Congress: Technical feasibility of joint use Study of flow and heal transfer in rotating cavities airfoils in heavy rain at Scon AFB, Selfridge AGB and El Tor0 MCAS [ONERA, TP NO 1989-331 p 698 A89-45188 [NASA-CR-1818421 p 657 N89-25973 [ AD-A1945971 p 693 N89-25241 ROTATING STALLS RAMJET ENGINES Functional requirements of the Communications Investigation on unsteady flow field and endwall The ATR/RJ engine performance at constant dynamic Interface Diver (CIO) boundary layer in axial flow compressor with hot-wire pressure and the consideration of transition condition [DoT/FAA/CT-TN87/41-REV] p 707 N89-26121 anemometer p 645 A89-45560 p694 A8946016 RESEARCH Surge and rotating stall in axial compressors Review of passive shear-flow control research for The EEC supports air tranwrf research [AIAA PAPER 89-26831 p 649 A89-47013 improved subsonic and supersonic combustion p 638 A89-46078 Rotating stall performance and recoverability of a [AIAA PAPER 89-27861 p 703 A89-47083 RESEARCH AIRCRAFT high-speed IO-stage axial-flow compressor Numerical study of reactive ramjet dump combustor A look at the Model 360 development [AIAA PAPER 89-28841 p 650 A89-47014 flowfields with a pressure based CFD method p 664 A89-45163 Aeroelastic analysis of prop fan blades with a [AIAA PAPER 89-27981 p 681 A89-47091 RESEARCH ANDDEVELOPMENT semiempirical dynamic stall model Ramjet combustor modeling for engineenng design Aeronautical research in the European future [AIAA PAPER 89-26951 p 703 A89-47025 [AIAA PAPER 89-27991 p 681 A89-47092 p 638 A89-45037 ROTATION Combustion behavior of boron-based BAMOlNMMO RESEARCH FACILITIES In-fltght measurement of propeller noise on the fuselage fuel-nch solid propellants Overview of Dynamics Integration Research (DIR) of an airplane [AIAA PAPER 89-28841 p 696 A89-47149 program at Langley Research Center [ NASA-TM-1022851 p 713 N89-25675 The influence of swirl and fuel composition of p 667 N89-25150 ROTOR AERODYNAMICS boroncontainingfuels on combustion in a solid fuel ramjet RESIDUAL STRENGTH Multi-stage compressor airfoil aerodynamics I - Airfoil combuslii chamber C-I30 Hercules Outer wing residual strength tests potential flow analysis p 639 A89-44112 [AIM PAPER 89-28851 p683 A8947150 p 663 A89-45132 Theorebcal and expenmental study of turbine Effects of bypass air on the combustion of boron RESONANT FREOUENCIES aerodynamics p 640 A89-44639 particles in a solid fuel ramjet A natural low-frequency oscillation of the flow over an Helicopter blades p 640 A89-45045 [AIAA PAPER 89-28861 p 683 A89-47151 airfoil near stalling conditions p 645 A89-45437 Configuration studies for a regional airliner using RANDOM ACCESS MEMORY An approximation function for frequency constrained open-rotor ultra-high-bypass-ratioengines Arranging computer architectures lo create structural optimization p 705 N89-25196 [AIAA PAPER 89-25801 p 666 A89-46937 higher-performancecontrollers p 71 1 A89-46147 REYNOLDS NUMBER Hot wire measurements downstream of a proplan RANDOM PROCESSES Analysis of low Reynolds number separation bubbles [AlAA PAPER 89-26981 p 650 A89-47027 Timeconelated gust loads using Matched-FilterTheory using semiempincal methods p 652 A89-47351 Noise produced by turbulent flow into a rotor Theory and Random-Process Theory: A new way 01 looking at RIBBON PARACHUTES manual for noise calculation things Fast brake --F- 111 high-performanceparachute system [NASA-CR-1817881 p 714 N89-26683 1 NASA-TM-1015731 p 671 N89-25232 development p 657 A89-46593 ROTOR BLADES (TURBOMACHINERY) A new class of random processes with applicabon 10 RIGID ROTORS Inverse method for the determination of transonic blade helicopter noise Flaplagstability data for a small-scaleisolated hingeless profiles of turbomachinenes p 643 A89-45404 [ NASA-CR-1850371 p 713 N89-26679 rotor in forward flight Supersonic turbomachine rotor flutter control by RANDOM VIBRATION I NASA-TM-1021891 p 708 N89-25479 aerodynamic detuning Mechanical durability prediction methods ROADS [AIM PAPER 89 26851 p 680 A89-47015 p 701 A89-46468 Design criteria for aggregate-surfaced roads and Numencal analysis of supersonic flow through oscillating RAREFIED GAS DYNAMICS airfields cascade secmns by using a deforming grid Rarefied gas flow through two-dimensional nOnles [AD-A207059] p 694 N89-26019 [ NASA-TM-1020531 p 653 N89-25119 [AIM PAPER 89-28931 p 650 A89-47156 ROCKET ENGINE DESIGN Multignd calculation of three-dimensional REAL GASES The ATRlRJ engine performance at constant dynamic turbomachinery flows Simulation of inviscid hypersonic real gas flows pressure and the consideration of transition condition [ NASA-CR-1853321 p 708 N89-26172 p 644 A89-45414 p 694 A89-46016 ROTOR BODY INTERACTIONS REAL TIME OPERATION ROLLER BEARINGS Computational modeling of axisymmetric propeller-hull The System 500, a real-lime flight test telemetry Experimental investigation of aeroengine high-speed interaction in slender low drag bodies system p660 A89-45134 roller bearing p 700 A89-45570 [AIAA PAPER 89-2674) p 649 A89-47004
A-22 SUBJECT INDEX SPACECRAFT STRUCTURES
ROTOR DYNAMICS SEPARATED FLOW SHROUDED PROPELLERS Study of nonlinear Duffingcharacteristics of flexible rotor Numerical study of the 3D separating flow about Performance and flow field of a ducted propeller with SFDB -.-squeeze film damper bearings obstacles with sharp corners p 641 A89-45363 [AIAA PAPER 89-26731 p649 A8947003 p700 A89-45568 Numerical simulation of the flow about a wing with SIDE-LOOKING RADAR Influence of rubbing on rotor dynamics, part 2 leading-edge vortex flow p 643 A89-45390 Infrared and millimeter wave acquisition system [NASA-CR-183649-PT-2] p 706 N89-25464 Asymmetric separated flows about sharp cones in a [ONERA, TP NO. 1989.361 p 699 A89-45191 Flap-lagstability data for a small-scaleisolated hingeless supersonic stream p 643 A89-45402 SIDESLIP rotor in forward flight Simulation of unsteady flow past sharp shoulders on Experimental study of vortex and aerodynamic [NASA-TM-102189] p 706 N89-25479 semi-infinite bodies p 644 A89-45415 characteristics of stack wings with sideslip ROTORS Inviscid and viscous flow simulations around the p 646 A89-46259 Onera46 by TVD schemes p 644 A89-45425 Improved compressor performance using recessed SIMULATION SERVICE LIFE clearance (trenches) p 674 A89-44113 Aeroelastic modeling for the FIT (Functional Integration C-130 Hercules outer wing residual strength tests Design of a gear drive for counter-rotating fan rotors Technology) team FIA-18 simulation p 663 A89-45132 [AIAA PAPER 89-28201 p 682 A89-47106 p 670 N89-25192 Aging aircraft p 657 A89-45296 Influence of rubbing on rotor dynamics, part 2 SLENDER BODIES [ NASA-CR-183649-PT-21 p 706 N89-25464 A corollary to - Duane's postulate on reliability growth p 701 A89-46474 Computational modeling of axisymmetric propeller-hull Mechanisms of Endwall leakage flows and the interaction in slender low drag bodies associated losses in a linear turbine rotor cascade with Engine life maturation process [AIAA PAPER 89-24641 p 677 A89-46851 [AIM PAPER 89.26741 p 649 A89-47004 blade tip-clearance SLENDER CONES [ NAL-TR-985Tl p 708 N89-26168 Transmission overhaul and replacement predictions using Weibull and renewal theory Asymmetric separated flows about sharp cones in a Superconductingrotor cooling system supersonic stream p 643 A89-45402 [AD-D014020] p 709 N89-26240 [AIAA PAPER 89.29191 p 704 A89-47173 SMOKE RUNWAY ALIGNMENT Three dimensional flow and temperature profile Effects of fuel chemical properties on exhaust smoke Microwave landing system instrumentation - A pilot's attenuation in an axial flow turbine from gas turbine combustor p 695 A89-45554 viewpoint [AD-A206736] p 685 N89-26005 [SAE PAPER 8814611 p 661 A89-47340 SHADOWGRAPH PHOTOGRAPHY EC-lBB/Boeing 707 Smoke Venting flight test RUNWAY CONDITIONS Initial supersonic combustion facility measurements [AD-A206601I p 659 N89-25979 Airline operations and the contaminated runway [AIAA PAPER 89-24621 p 692 A89-46849 SMOKE ABATEMENT [SAE PAPER 8814601 p 658 A89-47339 SHAPES Airplane tests 01 enhanced emergency smoke venting Warm fog dissipation using large volume water sprays Radar cross section of arbitrarily shaped bodies of [D218N301] p 658 N89-25976 [NASA-CASE-MFS-25962-1] p 693 N89-25242 revolution p 674 A89-45111 SOFTWARE TOOLS RUNWAY LIGHTS Treatment of body forces in boundary element design In search of effective diversity - A six-language study . Aircraft jet engine exhaust blast effects on Par-56runway sensitivity analysis p 705 N89-25187 of fault-tolerant flight control software threshold lamp fixtures Procedures for shape optimization of gas turbine disks p 710 A89-44423 p685 N89-25207 [ DOT/FAA/CT-89/4] p 694 N89-26018 . A knowledge-based en route monitor for air traffic SHEAR FLOW RUNWAYS control p 660 A89-45065 Numerical study of the 3D separating flow about Warm fog dissipation using large volume water sprays Robust computer-aided synthesis and optimization of [NASA-CASE-MFS-25962-1] p 693 N89-25242 obstacles with sharp corners p 641 A89-45363 A concentration probe for the study of mixing in linear multivariable control systems with varying plant Design criteria for aggregate-surfaced roads and dynamics via AUTOCON p 71 1 N89-25179 airfields supersonic shear flows [AIM PAPER 89-24591 p 703 A89-46846 The role of optimization in the next generation of [AD-A207059] p 894 N89-26019 computer-based design tools p 712 N89-25220 Evaluation of nondestructive test equipment for airfield Review of passive shear-flow control research for SOLDERED JOINTS pavements. Phase 1: Calibration test results and field data improved subsonic and supersonic combustion Mechanical durability prediction methods collection [AIAA PAPER 89.27861 p 703 A89-47083 p 701 A89-46468 [ AD-A2071591 p 694 N89-26020 SHEARLAYERS Experimental study of spreading rate enhancement of SOLID LUBRICANTS high Mach number turbulent shear layers Advantages of ceramic, solid lubricated bearings for S [AIM PAPER 89-24581 p 648 A89-46845 small gas turbine engines A concentration probe for the study of mixing in [AIM PAPER 89-24721 p 703 A89-46858 SAFETY FACTORS supersonic shear flows SOLID PROPELLANT COMBUSTION Sled testing of US. Air Force escape systems [AIAA PAPER 89.24591 p 703 A89-46846 Combustion behavior of boron-based BAMOlNMMO p 857 A89-45129 Compressibility and shock wave interaction effects on fuel-rich solid propellants SATELLITE INSTRUMENTS free shear layers [AIAA PAPER 89-28841 p 696 A89-47149 Low-temperature performance of a power-pack for a [AIAA PAPER 89-24601 p 648 A89-46847 The influence of swirl and fuel composition of %watt ELT p 709 A69-44016 SHOCK DISCONTINUITY boron-containingfuels on combustion in a solid fuel ramjet SCALE MODELS Multidimensionaladaptive Euler solver combustion chamber Nacellelpylon interference study on a 1/17th-scale. p 641 A89-45380 [AIAA PAPER 89-28851 p 683 A89147150 twin-engine. low-wing transport model SHOCK TUBES SOLID PROPELLANT ROCKET ENGINES [AIAA PAPER 89-24801 p 665 A89-46864 Vortices and pressure waves at plates, cylinders and Effects of bypass air on the combustion of boron Mach 4 testing of scramjet inlet models wind profiles particles in a solid fuel ramjet [AIAA PAPER 89-26801 p 649 A89-47010 [ISL-R-102/88] p 656 N89-25966 [AIAA PAPER 89-28861 p 683 A89-47151 SCALING LAWS SHOCK WAVE ATTENUATION SPACE LAW Flow structure and scaling laws in lateral wing-tip Transonic cascade flow solved by the combined Annals of air and space law. Volume 13 --- Book blowing p 652 A89-47352 shock-capturing and shock-fitting method p 714 A89-45175 SCHLIEREN PHOTOGRAPHY p 639 A89-44114 SPACE TRANSPORTATION The Schlieren Observation System installed in the NAL SHOCK WAVE INTERACTION Economic analysis of a beam-powered, personalized two-dimensional high-Reynolds number transonic wind Numerical study of unsteady viscous hypersonic blunt global aerospace transportation system tunnel and attempts to improve it body flows with an impinging shock p 643 A89-45394 [AIAA PAPER 89.24431 p 714 A89-46835 [NAL-TR-964] p 693 N89-26015 Interaction of an oblique shock wave with supersonic SPACECRAFT CONSTRUCTION MATERIALS SEALS (STOPPERS) turbulent blunt body flows p 644 A89-45405 Space age metals technology; Proceedings of the Comparisons between unleaded automobile gasoline A Newtonlupwindmethod and numerical study of shock Second International SAMPE Metals and Metals and aviation gasoline on valve seat recession in light wave/boundary layer interactions p 645 A89-45468 Processing Conference. Dayton, OH. Aug. 2-4, 1988 aircraft engines Compressibility and shock wave interaction eftects on p 696 A89-45927 [NIPER-409] p 697 N89-28110 free shear layers Materials and structures for 2000 and bevond: An SECONDARY FLOW [AIAA PAPER 89-24601 p 648 A89-46847 attempted forecast Recent developments in calculation methods for Survey and assessment of validation data base for [ DNLR-MITT-89-02] p 706 N89-25358 turbomachines p 697 A89-44635 shockwave boundary layer interactions in supersonic Aeronautical applications of high-temperature Present state 01 the theory of secondary flows and inlets superconductors experimental verifications p 698 A89-44636 [AIAA PAPER 89-29391 p651 A8947183 [NASA-TM-102311] p686 N89-26008 Design of vane tips improving axial compressor A numerical solution of transonic flow using SPACECRAFT DESIGN performance p 640 A89-44640 discontinuous shock wave relationship Recent Advances in Multidisciplinary Analysis and SELECTION [ NAL-TR-9971 p 655 N89-25950 Optimization, part 3 Selection of rolling-element bearing steels for longlife SHOCK WAVES [NASA-CP-3031-PT-3] p 670 N89-25201 applications p 704 A89-47250 A numerical solution of transonic flow using Aeronautical applications of high-temperature SEMIEMPIRICAL EQUATIONS discontinuous shock wave relationship superconductors AerOelastic analysis 01 prop fan blades with a [ NAL-TR-9971 p 655 N89-25950 [NASA-TM-102311] p 686 N89-26008 semiempirical dynamic stall model SHORT TAKEOFF AIRCRAFT SPACECRAFT STABILITY [AIAA PAPER 89.26951 p 703 A89-47025 Concept for an aircraft multi-component thrust Integrated structurelconlrol law design by multilevel SENSITIVITY measurement facility p 691 A89-45130 optimization
An analytical sensitivity method for use in integrated F-15 STOLIManeuvering Technology Demonstrator ~ [ NASA-TM-101623] p 712 N89-26623 aeroservoelastic aircraft design Initial flight test results p 687 A89-45157 SPACECRAFTSTRUCTURES [ NASA-TM-101583I p 690 N89-25239 A static investigation of several STOVL exhaust system Technology of structures maintains high standards SENSORS concepts p 637 A89-44642 Optical fiber sensor development for turbine [AIAA PAPER 89-29281 p 684 A89-47180 Materials and structures for 2000 and beyond An applications Flap system for short takeoff and landing aircraft attempted forecast [AIAA PAPER 89-29141 p 704 A89-47168 [AD-D013981] p 671 N89-25234 [ DFVLR-MITT-89-02] p 706 N89-25358
A-23 SUBJECT INDEX
SPANWISE BLOWING Mechanical stresses during air transport and ground STRUCTURAL DESIGN CRITERIA Flow structure and scaling laws in lateral wing-tip operations p 700 A89-46221 Design criteria and analysis of dynamic stresses of a Mowing p 652 A89-47352 Probabilistic analysis of aircraft structure propeller gear system Spanmse lift distnbutions and wake velocity surveys of p665 A89-46470 [AIAA PAPER 89-28221 p 682 A89-47107 a semi-span wng with a discontinuous twist Design critena and analyus of dynamic stresses of a STRUCTURAL ENGINEERING [NASA-CR-1775321 p 653 N89-25122 propeller gear system Turbine engine structural efficiency determination SPAREPARTS [AIAA PAPER 89-28221 p 682 A89-47107 [AIAA PAPER 89-25711 p 679 A89-46932 Aircraft sustainability model version 1.5: Users manual Computenzed Design Synthesis [COS). A Recent Advances in Multidisciplinary Analysis and (AD-A207015] p 638 N89-25949 databasedriven multidisuplinary design tool Optimization, part 1 NondestructNequalification of UH-1 replacement parts: p 712 N89-25180 [NASA-CP-3031-PT-t] p 666 N89-25146 Complebon enhancement X-ray based extensometry TRUSS An intelligent design system !or aircraft wings [AD-A206674] p 672 N89-25995 (NASA-CR-l85058] p 706 N89-25432 p 71 1 N89-25162 SPATIAL MARCHING Computational structural mechanics for engine Recent Advances in Multidisciplinary Analysis and The applicationof 3D marching scheme for the prediction structures Optimization. part 3 of supersonic free jets [NASA-TM-102 1 191 p 709 N89-26259 [ NASA-CP-3031-PT-31 p 670 N89-25201 (AIAA PAPER 89-28971 p 651 A89-47160 STRESS DISTRIBUTION Multilevel decomposition of complete vehicle SPECTRAL CORRELATION Three dimensional finite element stress predictions of configuration in a parallel computing environment A new class of random processes with application to spur gears compared to gear fatigue rig measurements p 670 N89-25205 heliipter nase [AIAA PAPER 89-29181 p 704 A89-47172 STRUCTURAL FAILURE [ NASA-CR-1850371 p 71 3 N89-26679 On the stress problem of the pebble bed heat exchanger Probabilistic damage tolerance methods for metallic SPILLING in a hypersonic wind tunnel aerospace structures p 672 N89-25237 Fuel containment system concept to reduce spillage [ NAL-TM-ST-87051 p 693 N89-25240 STRUCTURALRELIABILITY [DOT/FAAICT-TN89/221 p 672 N89-25994 STRUCTURALANALYSIS Damage tolerance analysis and structural integrity in Air SPOILERS Turbine engine structural efficiency determination Force aircraft p 661 A89-43884 Flap system for short takeoff and landing aircraft [AIAA PAPER 89-2571I p 679 A89-46932 Probabilistic analysis of aircraft structure [AD-W13981] p 671 N89-25234 Applications of integrated designlanalysis systems in p 665 A89-46470 SPRAY CHARACTERISTICS aerospace structural design p 666 N89-25147 STRUCTURAL VIBRATION Spray patternation at high pressure Optimum structural design with static aeroelastic A new flight flutter excitation system [AIAA PAPER 89-23231 p 702 A89-46750 constraints p 669 N89-25171 p 663 A89-45140 SPRAYERS Optimum design of swept-fomard high-aspect-ration Mechanical stresses dunng air transport and ground Warm fog dissipation using large volume water sprays graphite-epoxy wings p 669 N89-25172 operations p 700 A89-46221 [ NASACASE-MFS-25962-1] p 693 N89-25242 Recent Advances in Multidisciplinary Analysis and Structural loading and noise disturbance of helicopters SQUEEZE FILMS Optimization. part 2 p 713 N89-25140 Study of nonlinear Duffing characteristicsof flexible rotor [NASA-CP-3031-PT-2] p 669 N89-25173 Efficient sensitivity analysis and optimization of a mth SFOB --.squeeze frlm damper bearings ASTROS: A multidisciplinary automated structural helicopter rotor p 668 N89-25155 p 700 A89-45568 design tool p 705 N89-25174 Plan, formulate,discuss and correlate a NASTRAN finite STANDARDIZATION Recent experiences using finite-element-based element vibrations model of the Boeing Model 360
ADINTS ~ Moving toward standardization of automatic structural opbmization p 705 N89-25177 helicopter airframe test equipment p 701 A89-46462 Results of including geometric nonlinearities in an [ NASA-CR-1817871 p 707 N89-25480 STANDARDS aeroelasbc model of an F/A-18 p 669 N89-25190 Langley rotorcraft structural dynamics pogram: HelipOR identification beacon An integrated approach to the optimumdesign of actively Background, status, accomplishments, plans [ DOT/FAAICT-TN89/31I p 661 N89-25984 controlled composite wings p 670 N89-25194 [ NASA-TM-l01616] p 709 N89-26273 STATE ESTIMATION Finite element flOW-thermal-StNCtUral analysis of SUBSONIC AIRCRAFT Gain transfer - An algorithm lor decentralized aercdynamically heated leading edges Advanced propulsion systems for large subsonic hierarchical estimation p 71 1 A89-46150 p 655 N89-25198 transports STATIC CHARACTERISTICS An overview of the Douglas Aircraft Company [AlAA PAPER 89.24771 p 677 A69-46861 Longitudinal nonlinear aerodynamic model form for Aeroelastic Desgn Optimizabon Program (ADOP) SUBSONIC FLOW USB-STOL aircraft p 671 N89-25221 LOPAN - A low-order panel method for subsonic and [ NAL-TR-9951 p 672 N89-25990 Recent developments in large-scale structural supersonic flows p 639 A89-43724 STATISTICAL ANALYSIS Optimization p 706 N89-25231 An integrated design computational method for the wing FAA statistical handbook of aviation: Calendar year Automated structural Optimization system (ASTROS): optimization camber and twist at subsonic and supersonic 1987 User training workshop flow p 646 A89-46256 [AD-A2009171 p 638 N89-25113 [AO-A207090] p 709 N89-26267 Review of passive shear-flow control research for STATORS STRUCTURAL DESIGN improved subsonic and supersonic combustion Influence of rubbing on rotor dynamics, part 2 Technology of structures maintains high standards [AIM PAPER 89-27861 p 703 A89-47083 [NASA-CR-183649-PT-2] p 706 N89-25464 p 637 A89-44642 Steady-state and lime-dependent aerodynamics in an STEADY FLOW Light weight gas turbine engine fuel pumping annular turbine cascade operating at high subsonic Mach A high resolution finite volume scheme for steady technology numbers external transonic flow p 642 A89-45369 [AIAA PAPER 89-25871 p 703 A69-46943 [AIM PAPER 89-29411 p 651 A89-47185 RNS solutions for three-dimensional steady Technoloov develoDment' rewired bv.. DroDfan , . Dower SUCTION incompressible flows p 643 A89-45393 reduction gearboxes ' The induced power based on leading edge suction for Unsteady transonic airfoil computation using implicit [AIAA PAPER 89.28181 p 703 A89-47104 a helicopter in hovering p 646 A89-46267 Euler scheme on body-fixed grid p 652 A89-47358 ADDlicationS of integrated desianlanalvsis svstems in SUPERCONDUCTORS A lifting surface method for the calculation of steady aerospace structural d&gn - p 666 N89-25147 Superconducting rotor cooling system and unsteady, incompressible propeller aerodynamics Structural tailonng of counter rotation proplans [AD-W14020] p 709 N89-26240 [DFVLR-FB-89-04] p 657 N89-25972 p685 NE925165 SUPERFLUIDITY STEADY STATE Optimum structural design with static aeroelastic Superconducting rotor cooling system Steady-state and transitional aerodynamic constraints p 669 N89-25171 [AO-W14020] p 709 N89-26240 characteristics of a wing in simulated heavy rain Recent Advances in Multidisciplinary Analysis and SUPERSONIC AIRCRAFT [NASA-TP-29321 p 655 N89-25951 Optimization, part 2 Civil supersonics - Propulsion is the key STEAM TURBINES [NASA-CP-3031-PT-2] p 669 N89-25173 p 675 A89-45031 Steady-state and timedependent aerodynamics in an Computenzed Design Synthesis (CDS). A Digital flight and inlet control in the SR-71 annular turbine cascade operating at high subsonic Mach databasednven multidisciplinarydesign tool p 664 A89-45160 numbers p 712 N89-25180 A supersonic cruise fighter design [AIAA PAPER 89-2941] p 651 A89-47185 Treatment of body forces in boundary element design p 664 A89-45167 STEELS sensibvw analysis p 705 N89-25187 Expendable supersonic exhaust nozzle concepts Selecbon of rolling-element bearing steels for long-life AerOelasbc modeling for the FIT (Functional Integration [AIAA PAPER 89-29271 p 684 A89-47179 appliicabons p 704 A89-47250 Technology) team FIA-18 simulation Compressor exit temperature analysis p 670 N89-25192 STEREOSCOPY (AIM PAPER 89-29471 p 684 A89-47191 An approximabon Iuncbon for frequency constrained Evaluationof a projection algorithm for the stereographic SUPERSONICBOUNDARYLAYERS structural opbmizabon p 705 N89-25196 representation 01 aircraft in an illr traffic control system The instability and acoustic wave modes of supersonic Structural optimization 01 framed structures uung [WT/FAA/CT-TN89/201 p 661 N89-25985 mixing layers inside a rectangular channel generalized opbmallty cntena p 706 N89-25197 p 699 A89-45453 STRAIN GAGES Recent Advances in Multidisciplinary Analysis and Apparent strain characteristics of strain gauges under Opt~mization.part 3 SUPERSONIC COMBUSTION high temperature environment p 697 A89-43844 [NASA-CP-3031-PT-3] p 670 N89-25201 Numerical simulations of oblique detonations in STRAIN MEASUREMENT The role of optimization in the next generation of supersonic combustion chambers p 674 A89-44115 Apparent strain charactenstics of strain gauges under computer-baseddesrgn tools p 712 N89-25220 Quantitative characterization of a nonreacting, high temperature environment p 697 A89-43844 An overview of the Douglas Aircraft Company Supersoniccombustor flowiieldusing unified, laser-induced STRATOSPHERE Aeroelasbc Design Opbmization Program (ADOP) iodine fluorescence Preventing depletion of stratospheric ozone: p 671 N89-25221 [AIAA PAPER 89-2565) p 703 A89-46928 Implications on future aircraft emissions Recent developments in large-scale structural Review of passive shear-flow control research for DE890099641 p 710 N89-25530 optimization p 706 N89-25231 improved subsonic and supersonic combustion STRESS ANALYSIS Integrated structurelcontrol law design by multilevel [AIAA PAPER 89-27861 p 703 A89-47083 Dynamic stress analysis of rotating turbo-machinery optimization Combustion enhancement in supersonic coaxial flows bladeddisk Systems p 675 A89-44362 [ NASA-TM-1016231 p 712 N89-26623 [AIAA PAPER 89.27881 p 681 A89-47084
A-24 SUBJECT INDEX TECHNOLOGY ASSESSMENT
Improved plasma torch for ignition and flame holding SUPERSONIC INLETS The influence of swirl and fuel Composition of in supersonic combustion Inviscid analysis of a dual mode scramjet inlet boron-containingfuels on combustionin a solid fuel ramjet [AlAA PAPER 89-29451 p 704 A89-47189 [AIAA PAPER 89-2681I p 649 A89-47011 combustion chamber SUPERSONIC COMBUSTION RAMJET ENGINES Survey and assessment of validation data base for [AlAA PAPER 89-28851 p 683 A89-47150 A simple theory of aerospaceplane shockwave boundary layer interactions in supersonic SYNTHETICAPERTURERADAR p 662 A89-44975 inlets Experimental localized radar cross sections of aircraft Performance analysis of scramjet engines [AIAA PAPER 89-29391 p 651 A89-47183 p 673 A89-45105 p 676 A89-46600 SUPERSONIC JET FLOW SYSTEMS COMPATIBILITY Anexperimental technique for the measurementof mass Generalization of the Roe scheme for computing flows Validation of a free-jet technique for evaluating flow of scramjet inlets tested in hypersonic pulse of mixed gases with variable concentrations inlet-engine compatibility facilities p 639 A89-44322 [AIAA PAPER 89-23251 p 676 A89-46752 [AlAA PAPER 89.23311 p 692 A89-46755 Theapplication0f3D marching scheme for the prediction T-4 inlet/engine compatibility flight test results of supersonic free jets Experimental study of spreading rate enhancement of [AIAA PAPER 89.24661 p 665 A89-46853 [AIAA PAPER 89-28971 p 651 A89-47160 high Mach number turbulent shear layers SUPERSONIC NOZZLES SYSTEMS ENGINEERING [AIAA PAPER 89-24581 p 648 A89-46845 Supersonic nozzle mixer ejector From avionics technology to architectural concepts p 637 A89-45035 Initial supersonic combustion facility measurements [AIAA PAPER 89-29251 p 683 A89-47178 [AIAA PAPER 89-24621 p 692 A89-46849 Expendable supersonic exhaust nozzle concepts SPAREL ~ A model for reliabilityand sparing in the world Evaluation of parallel injector configurations for [AIAA PAPER 89.29271 p 684 A89-47179 of redundancies p 702 A89-46493 supersonic cornbustion SUPERSONIC SPEED Methods for the mathematical modeling of flight vehicle [AIAA PAPER 89-25251 p 678 A89-46898 Investigation of low NOx staged combustor concept in engines --_ Russian book p 71 1 A89-48551 A numerical investigationof scramjet combustors high-speed civil transport engines Computerized Design Synthesis (COS), A [AIAA PAPER 89-2561 ] p 679 A89-46926 [AIM PAPER 89-29421 p 684 A89-47186 database-driven multidisciplinary design tool Effectiveness of plasma torches for ignition and Effect of milling machine roughness and wing dihedral p 712 N89-25180 flameholding in scramjet on the supersonic aerodynamic characteristics of a highly Recent Advances in MultidisciDlinaw.. Analvsis . and [AIAA PAPER 89-25641 p 679 A89-46927 swept wing Optimization, part 3 Integration of scramjets with waverider configurations [ NASA-TP-29181 p 652 N89-25117 [NASA-CP-3031-PT-3] p 670 N89-25201 [AIAA PAPER 89-26751 p 695 A89-47005 SUPERSONIC TRANSPORTS Hypersonic airbreathing vehicle conceptual design A comparison of scramjet engine performances of Supersonic jet noise and the high speed civil transport (focus on aero-space plane) p 670 N89-25210 various cycles [AIAA PAPER 89.23581 p 712 A89-46772 SYSTEMS INTEGRATION [AIAA PAPER 89.26761 p 680 A89-47006 The challenge of reducing supersonic civil transport Integration of scramjets with waverider configurations Mach 4 testing of scramjet inlet models propulsion noise [AIM PAPER 89-26751 p 695 A89-47005 ’ [AIAA PAPER 89-26801 p 649 A89-47010 [AIAA PAPER 89-23631 p 677 A89-46776 The pursuit of integrated control - A realtime aircraft Inviscid analysis of a dual mode scramjet inlet The conceptual design of a Mach 2 Oblique Flying Wing system demonstration [AIAA PAPER 89-26811 p 649 A89-47011 supersonic transport [AIAA PAPER 89-27011 p 688 A89-47029 [NASA-CR-l77529] p 671 N89-25233 lntearated controls Dav-off for fliahtlDrODulsion Rapid methodology for design and performance .. -.. - .. aircrafisystems prediction of integrated scramjetlhypersonic vehicle Preventing depletion of stratospheric ozone: [AIAA PAPER 89-27041 p 688 A89-47031 [AlAA PAPER 89.26821 p 666 A89-47012 Implications on future aircraft emissions [DE89-009964] p 710 N89-25530 The evolution - IFPC to VMS -.- intearated A propulsion development strategy for the National An initial assessment of the impact of boundary layer flightlpropulsion control for Vehicle Management Aero-Space Plane System [AIAA PAPER 89-27511 p 681 A89-47061 control on SST [AERO-REPT-8802] p 656 N89-25969 [AIM PAPER 89-27051 p 688 A89-47032 Mixing enhancement in a supersonic combustor SUPERSONIC TURBINES Applications of integrated designlanalysis systems in [AIAA PAPER 89-27941 p 681 A89-47088 aerospace structural design p 666 N89-25147 Two axial compressor designs for a stage matching SUPERSONIC COMPRESSORS Overview of Dynamics Integration Research (DIR) Calculation of the total pressure loss coefficient with investigation [AD-A206951] p 685 N89-26006 program at Langley Research Center three models for four supersonic axial-flow compressors p 667 N89-25150 p 640 A89-44898 SUPERSONIC WIND TUNNELS Aeroelastic modelinq for the FIT (Functional Integration Two axial compressor designs for a stage matching A concentration probe for the study of mixing in Technology) team Fln-18 simulation supersonic shear flows investigation D 670 N89-25192 [ AD-AZ06951] p 685 N89-26006 [AIM PAPER 89-24591 p 703 A89-46846 Hypersonic airbreathing vehicle conceptual design SUPERSONIC DIFFUSERS New hypersonic facility capability at NASA Lewis (focus on aero-space plane) p 670 N89-25210 Diffuser performance of two-stream supersonic wind Research Center An analytical sensitivity method for use in integrated tunnels p 652 A89-47373 [AIAA PAPER 89-25341 p 692 A89-46905 aeroservoelastic aircraft design SUPERSONIC FLIGHT Diffuser performance of two-stream supersonic wind [NASA-TM-101583] p 690 N89-25239 An introduction to the problem of aerodynamic heating tunnels p 652 A89-47373 lntearatedfliaht/DrODUlSiOn control svstem desianbased [AERO-REPT-8901I p 656 N89-25970 SUPPORT SYSTEMS on a &ntralize;d approach SUPERSONIC FLOW The phased establishment of support maturity for the [ NASA-TM-1021371 p 690 N89-26009 LOPAN - A low-order panel method for subsonic and European Fighter Aircratt (EFA) p 637 A89-44644 supersonic flows p 639 A89-43724 SUPPORTS Solution of Euler equations by a finite element method Aircraft engine outer duct mounting device T application lo supersonic flows p 639 A89-44319 [AD-D013988] p 672 N89-25991 Multidimensional adaptive Euler solver TAILLESS AIRCRAFT p 641 A89-45360 SURFACE ROUGHNESS EFFECTS The conceptualdesign of a Mach 2 Oblique Flying Wing Computer Simulation of some types of flows arising at Effect 01 milling machine roughness and wing dihedral supersonic transport interactions between a supersonic flow and a boundary on the supersonic aerodynamic characteristics of a highly [NASA-CR-1775291 p 671 N89-25233 swept wing layer p 642 A89-45381 TAKEOFF Asymmetric separated flows about sharp cones in a [NASA-TP-2918] p 652 N89-25117 Research and applicationof a new kind of measurement supersonic stream p 643 A89-45402 SURFACETEMPERATURE technology of take-off and landing performance Interaction of an oblique shock wave with supersonic Dynamic turbine blade temperature measurements p 698 A89-45144 turbulent blunt body flows p 644 A89-45405 [AIAA PAPER 89-26891 p 680 A89-47019 Reduction of aircraft noise in civil air transport by An integrated design computational method for the wing SURGES optimization of flight tracks and takeoff and approach optimization camber and twist at subsonic and supersonic Surge and rotating stall in axial compressors procedures flow p 646 A89-46256 [AIAA PAPER 89.26831 p 649 A89-47013 [ ILR-MITT-2001 p 713 N89-25676 An experimental study of the effect of streamwise SWEPT FORWARD WINGS TAKEOFF RUNS vorticity on supersonic mixing enhancement Current flight test experience related to structural Powered lift aircraft take off climb performance with one [AIAA PAPER 89-24561 p 648 A89-46843 divergence of forward-swept wings p 663 A89-45141 engine inoperative p 663 A89-45127 A concentration probe for the study of mixing in Integrated aerodynamic-structural design of a TARGET ACQUISITION supersonic shear flows forward-swept transport wing p 669 N89-25168 An exploratory study of the use of movement-correlated [AIAA PAPER 89-24591 p 703 A89-46846 Optimum design of swept-forward high-aspect-ration cues in an auditory head-up display p 674 A89-45329 Low angle injection into a supersonic flow graphite-epoxy wings p 669 N89-25172 TAYLOR SERIES [AIAA PAPER 89-24611 p 648 A89-46848 SWEPT WINGS An approximation function for frequency constrained structural optimization p 705 N89-25196 Supersonic turbomachine rotor flutter control by Numerical simulation of the flow about a wing with aerodynamic detuning TECHNOLOGICAL FORECASTING leading-edge vortex flow p 643 A89-45390 [AIAA PAPER 89.26851 p 680 A89-47015 Jet or prop required for future regional transports? Mixing enhancement in a supersonic combustor Effect of milling machine roughness and wing dihedral p 637 A89-44641 [AIAA PAPER 89.27941 p 681 A89-47088 on the supersonic aerodynamic characteristics of a highly The systems of the future Airbus A330 and A340 Further experiments on supersonic turbulent flow swept wing aircraft p 662 A89-45044 development in a square duct p 652 A89-47357 [NASA-TP-2918] p 652 N89-25117 Titanium requirements for current and future military gas Numerical analysis of supersonic flow through oscillating Optimum structural design with static aeroelastic turbine engines p 696 A89-45944 cascade sections by using a deforming grid constraints p 669 N89-25171 Materials and structures for 2000 and beyond An [ NASA-TM-1020531 p 653 N89-25119 Aeroservoelastic tailoring for lateral control attempted forecast Influence of thickness and camber on the aeroelastic enhancement p 689 N89-25189 [DFVLR-MITT-89-02] p 706 N89-25358 stability of supersonic throughflow fans: An engineering SWIRLING TECHNOLOGYASSESSMENT approach Experimental research on swirling cornbustion Technology of structures maintains high standards [ NASA-TM-1019491 p 656 N89-25957 efficiency p 675 A89-45558 D 637 A89-44642
A-25 TECHNOLOGY UTILIZATION SUEUECT INDEX
Stealth technology for reducing aircraft recognition Numerical study of the 30 separating flow about TOPOLOGY p 673 A89-44645 obstacles with sharp corners p 641 A89-45363 The solution of 3-0 temperature distribution in a cycling Technology readiness for advanced ducted engines Development of a highly efficient and accurate 30 Euler oil cooled aircraft ac generator by network topology [AIAA PAPER 89-24791 p 678 A89-46863 flow solver p 642 A89-45370 method p 701 A89-46282 Automatwn in transport aircraft . Current and future An implint time-marching method for soking the 3-0 TRAILING EDGES trends compressible Navier-Stokes equations Wind-tunnel investigations of wings with serrated sharp [SAE PAPER 8814681 p 857 A89-47334 p 642 A89-45374 trailing edges p641 A8945282 TECHNOLOGY UTILIZATION Low-storageimplicit upwind-FEM schemes for the Euler Pressure fluctuations on an oscillating trailing edge ExpertViwon - A ndeo-based noncontact system for equations p 642 A89-45375 p 645 A89-45458 nwtwn measurement p 898 A89-45136 RNS solutions for three-dimensional steady Flow about trailing edges in unsteady flow TELEMETRY incompressibleflows p 643 A89-45393 p 654 N89-25135 The System 500, a real-time flight test telemetry Adaptive numerical solutwns of the Euler equations in TRAINING AIRCRAFT system p660 A89-45134 30 using finite elements p 644 A89-45413 Numerical modelling of flight dynamics and flight test A wmple lowcost telemetry system for those of modest Transonic flow solubons on general 30 regions using data identification of a jet trainer airplane means p660 A89-45138 composite-block grids p 644 A89-45428 p 663 A89-45139 TEMPERATURE DISTRIBUTION Nonisentropic potential calculation for 2-0 and 3-0 Full scale fatigue crack growth test of advanced jet The solumn of 3-D temperature dishbution in a cycling transonic flow p 645 A89-45434 trainer AT-3 p664 A89-45207 oil cooled aircraft ac generator by network topology Measurement of three-dimensional flow in TRANSIENT RESPONSE method p 701 A89-46282 turbomachinery with a single slanted hot-wire Steady-state and transitional aerodynamic TEMPERATURE EFFECTS p 700 A89-45561 characteristics of a wing in simulated heavy rain Low-temperature performance of a power-pack for a Three-dimensional multigrid Navier-Stokes [ NASA-TP-29321 p 655 N89-25951 2-wan ELT p 709 A89-44016 computations for turbomachinery applications TRANSITION FLOW krcraftpt engine exhaust blast effectson Par-56runway [AIAA PAPER 89-24531 p702 A89-46841 A new look at wind tunnel flow quality for transonic threshold lamp fixtures Computabonal analysis of turbomachinery flows using flows [DOT/FM/CT89/41 p 694 N89-26018 FLOFIVE [SAE PAPER 8814521 p 692 A89-45249 TEMPERATURE MEASUREMENT [AIAA PAPER 89-25591 p 648 A89-46924 TRANSMISSIONS (MACHINE ELEMENTS) Optical research needed to support the tesbng of L2F B LDV velocimetry measurement and analysis of Transmission overhaul and replacement predictions hypersonic vehicle structures p 697 A89-43840 the 3-0 flow field in a centrifugal compressor using Weibull and renewal theory Embedded temperature measurements in a [AIAA PAPER 89-25721 p 648 A89-46933 [AIAA PAPER 89.29191 p 704 A89-47173 carbonarbon wing leading edge hot structure Applicabon of a multi-stage3-13 Euler solver to the design TRANSONIC FLOW D 897 A89-43843 of turbines for advanced propulsion systems Transonic cascade flow solved by the combined A hgh speed data acquisition system for the analysis [AIAA PAPER 89-25781 p 679 A89-48936 shock-capturing and shock-fining method of velocity, density, and total temperature fluctuations at The applicationof 3D marching scheme for the prediction p 639 A89-44114 transonic speeds of supersonic free jets Inviscid transonic flow over a wavy wall decaying [SAE PAPER 8814511 p 691 A89-45248 [AIAA PAPER 89-28971 p651 A8947160 downstream p 839 A89-44390 Dynamic twbine Made temperature measurements Three dimensional flow and temperature profile A hgh speed data acquisition system for the analysis [AIAA PAPER 89-26891 p 680 A89-47019 attenuation in an axial flow turbine of velocity, density, and total temperature fluctuations at TEMPERATURE PROFILES [ADA2067361 p 685 N89-26005 transonic speeds Three dimensional flow and temperature profile Mechanisms of Endwall leakage flows and the [SAE PAPER 8814511 p 691 A89-45248 attenuation in an axial flow turbine associated losses in a linear turbine rotor cascade with A new look at wind tunnel flow quality for transonic [AD-A2067361 p685 N89-26005 blade tipclearance flows TERNARYALLOYS [NAL-TR-985T] p 708 N89-26168 [SAE PAPER 8814521 p 692 A89-45249 A study of AI-Li alloys using small angle neutron Multigrid calculation of three-dimensional A high resolution finite volume scheme for steady scatteting p 695 A89-44577 turbomachinery flows external transonic flow p 642 A89-45369 TERRAIN FOLLOWING AIRCRAFT [NASAGR-185332] p 708 N89-28172 Inverse method for the determinationof transonic blade 6-1B development testing p 687 A89-45165 THREE DIMENSIONAL MODELS profiles of turbomachinenes p 643 A89-45404 TEST EQUIPMENT A new variational method for the generation of two- and Transonic analysis of arbitrary configurations using Study of flow and heat transfer in rotating cavities threedimensional adapted grids in computational fluid locally refined grids p 644 A89-45419 [ONERA. TP NO. 1989-331 p 698 A89-45168 dynamics Navier-Stokessimulation of transonic flow about wings Functional requirements of the Communications [ONERA, TP NO. 1989-31I p 641 A89-45187 using a block structured approach p 644 A89-45422 Interface Driver (CID) THRUSTMEASUREMENT Transonic flow solutions on general 3D regions using [MIT/FAA/CT-TN87/41-REV] p 707 N89-26121 Concept for an aircraft multicomponent thNSt compositeblock gnds p 644 A89-45428 TEST FACILITIES measurement facility p 691 A89-45130 Nonisentropic potential calculation for 2-0 and 3-0 Concept for an aircraft multicomponent thrust Measurement effects on the calculatiopn of in-flight transonic flow p 645 A89-45434 measurement facility p 891 A89-45130 thrust for an F404 turbofan engine Design and analysis of arfoils in transonic viscous Inertial guidance test facility using the earth [AIAA PAPER 89-23641 p 677 A89-46777 flow p 646 A89-46262 environment p 700 A89-46218 THRUST REVERSAL The computed results of airfoil near the freestream Mach Free-jet test capability for the aeropropulsion systems Numerical investigabonof thrust-reversing nozzle using number one p 646 A89-46266 test facility an implicit NOscheme A validation of a Navier-Stokes 2D solver for transonic [AIM PAPER 89-25371 p 892 A89-46908 [AIAA PAPER 89-28991 p 683 A89-47182 turbine cascade flows Turbine aerodynamic performance measurements in THRUSTVECTORCONTROL [AIAA PAPER 89-24511 p 647 A89-46839 short duration facilities Parametric study of a simultaneous pitchlyaw thrust Navier-Stokes simulations around a propfan using [AIM PAPER 89-26801 p 693 A89-47020 vectoring single expanslon ramp noale higherorder upwind schemes Satellite low rate voice demonstration test plan [AIAA PAPER 89-28121 p 682 A89-47098 [AIAA PAPER 89-26991 p 650 A89-47028 [ AD-A2067101 p 707 N89-26133 Advancedthrustvectoring noalesfor supercruise fighter Block-structured solubon of transonic flows around THERMAL ANALYSIS aircraft winglpylonlnacelle configurations High performance gear systems and heat management [AIAA PAPER 89-28161 p 882 A89-47102 [AIAA PAPER 89.29401 p 651 A89-47184 for advanced ducted systems THRUST-WEIGKT RATIO Unsteady transonic airfoil computation using implicit [AIM PAPER 89.24821 p 678 A89-46885 Long duration balloon technology survey, phase 1 Euler scheme on body-fixed grid p 652 A89-47358 THERMAL CYCLING TESTS [AD-A206975] p 856 N89-25965 Vortex structures in the wake of transonic flow about Mechanical durability prediction methods TILT ROTOR AIRCRAFT profiles p 654 N89-25134 p701 A8946468 FMrotorcraft research, engineering and development Transonic airfoil design for helicopter rotor THERMAL MAPPING bibliography, 1962-1988: Supplement applications p 667 N89-25154 Automated thermal mamirw.. - techniauesusing chromatic [AD-A207162] p673 N89-2MHX) Design optimizatm of axisymmetric bodies in image analysis TILT ROTOR RESEARCH AIRCRAFT PROGRAM nonuniform transonic flow p 670 N89-25206 [NASA-TM-1015541 p 706 N89-25443 Noise considerations for tiltrotor A numerical solution of transonic flow using THERMAL STRESSES [AIAA PAPER 89-23591 p 665 A89-48773 discontinuous shock wave relationship On the stress problem of the pebble bed heat exchanger TIME MARCHING [ NAL-TR-9971 p 655 N89-25950 in a hypersonic wind tunnel An implicit time-marching method for solving the 3-0 Multigrid calculation of three-dimensional [NAL-TM-ST-8705] p 693 N89-25240 Compressible Navier-Stokesequations turbomachinery flows THERMOCOUPLES p 642 A89-45374 [NASA-CR-185332] p 708 N89-26172 Embedded temperature measurements in a TIP DRIVEN ROTORS carboncarbon wing leading edge hot structure Tipjet VTOL UAV (Vertical Takeoff and TRANSONIC WIND TUNNELS p 897 A89-43843 LandinglUnmanned Aerial Vehicle) summary. Volume 1: A new look at wind tunnel flow quality for transonic THERMOGRAPHY A 1200 pound tipjet VTOL unmanned aerial vehicle. Part flows Automated thermal mappingtechniques usingchromatic 1:Co nceptual design study of a 1200-poundvehicle [SAE PAPER 8814521 p 692 A89-45249 image analysis [AD-A206738] p 672 N89-25997 Parametric study of a simultaneous pitch/yaw thrust [ NASA-TM-1015541 p706 N89-25443 TITANIUM ALLOYS vectoring single expansion ramp noale THICKNESS Titanium requirementsfor current and future military gas [AIAA PAPER 89.28121 p 682 A89-47098 Influence of thickness and camber on the aermlastic turbine engines p696 A89-45944 The Schlieren Observation System installed in the NAL stability of supersonic throughflow fans: An engineering TOLERANCES (MECHANICS) two-dimensional high-Reynolds number transonic wnd appcoach Probabilistic damage tolerance methods for metallic tunnel and attempts to improve it [ NASA-TM-I019491 p 656 N89-25957 aerospace structures p 672 N89-25237 [NAL-TR-964] p 693 N89-26015 THREE DIMENSIONAL FLOW TOOLS TRANSPORT AIRCRAFT Recent developments in calculation methods for Testing of reliability - Analysis tools Jet or prop required for future regional transports? tubmachines p 897 A89-44635 p 702 A89-46503 p 637 A89-44641
A-26 SUBJECT INDEX UNSTEADY AERODYNAMICS
Experimental study on aerodynamic characteristics of TURBOFAN ENGINES TURBULENTBOUNDARYLAYER hypersonic transport configuration p 640 A89-44972 Advanced turbofan engine combustion system design The mixing of three-dimensional turbulent wakes in FAA handling qualities assessment . Methodology in and test verification p 675 A89-44117 boundary layers p 639 A89-43722 transition p 687 A89-45159 Measurement effects on the calculatiopn of in-flight Pressure fluctuations on an oscillating trailing edge The EEC supports air transport research thrust for an F404 turbofan engine p 645 A89-45458 p 638 A89-46078 [AIAA PAPER 89-23641 p 677 A89-46777 Interaction of an oscillating vortex with a turbulent Advanced propulsion systems for large subsonic T-4 inletlengine compatibility flight test results boundary layer p645 A89-45906 [AIAA PAPER 89.24661 p 665 A89-46853 transports TURBULENT FLOW Nacellelpylon interference study on a lf17th-scale. [AlAA PAPER 89.24771 p 677 A89-46861 Efficient computational tool for ramjet combustor twin-engine, low-wing transport model Nacellefpylon interference study on a 1f17th-scale. research [AIAA PAPER 89-24801 p A89-46864 twin-engine, low-wing transport model 665 [AIAA PAPER 88-00601 p 674 A89-44108 [AlAA PAPER 89-24801 p A89-46864 Ensuring surge-free engine operation on today's 665 A new variational method for the generation of two- and UHB demonstrator flight test program - Phase 2 --_ turbofan powered business jets three-dimensional adapted grids in computational fluid ultra-high bypass engine technology [AIAA PAPER 89.24871 p 678 A89-46868 dynamics [AIAA PAPER 89-25821 p 679 A89-46939 The Rolls Royce Allison FIB580 turbofan - Matching the [ONERA. TP NO. 1989-31I p 641 A89-45187 Investigation of low NOx staged combustor concept in market requirement for regional transport high-speed civil transport engines [AlAA PAPER 89.24881 p 678 A89-46869 Unsteady and turbulent flow using adaptationp 643 A89-45392 methods [AIAA PAPER 89-29421 p 684 A89-47186 Estimating in-flight engine performance variations using Automation in transport aircraft - Current and future Kalman filter concepts Interaction of an oblique shock wave with supersonic trends [AIAA PAPER 89-25841 p 679 A89-46940 turbulent blunt body flows p 644 A89-45405 [SAE PAPER 8814881 p 657 A89-47334 Dynamic turbine blade temperature measurements Modeling of turbulence for cornpression corner flows An economic model for evaluating high-speed aircraft [AIAA PAPER 89-26891 p 680 A89-47019 and internal flows designs Advanced cooling concepts for multi-function nozzle [AIAA PAPER 89-23441 p 647 A89-46763 [NASA-CR-177530] p 671 N89-25235 durability Two-dimensional cornputations of multi-stage TREES (MATHEMATICS) [AIAA PAPER 89.28141 p 682 A89-47100 compressor flows using a zonal approach Multilevel decomposition of complete vehicle Turbofan engine control system design using the [AIAA PAPER 89-24521 p 647 A89-46840 configuration in a parallel computing environment LOGfLTR methodology Experimental study of spreading rate enhancement of p 670 N89-25205 [ NASA-CR-1823031 p 685 N89-26004 high Mach number turbulent shear layers TRUSSES CFD in the context of IHPTET The Integrated High [AlAA PAPER 89-24581 p 648 A89-46845 Performance Turbine Technology Program Integrated structurelcontrol law design by multilevel Low angle injection into a supersonic flow [NASA-TM-102132] p 708 N89-26174 optimization [AIAA PAPER 89-2461I p 648 A89-46848 TURBOJET ENGINE CONTROL [ NASA-TM-1016231 p 712 N89-26623 Further experiments on supersonic turbulent flow Diagnostic expert systems for gas turbine engines TUPOLEV AIRCRAFT - development in a square duct p 652 A89-47357 Status and prospects Tupolev's new twin p 682 A89-43887 Noise produced by turbulent flow into a rotor: Theory [AIAA PAPER 89-25851 p A89-46941 TURBINE BLADES 680 manual for noise calculation Low cost control system for expendable turbine Theoretical and experimental study of turbine [NASA-CR-181788] p 714 N89-26683 aerodynamics p 640 A89-44639 engines TURBULENT MIXING [AIAA PAPER 89-25861 p 680 A89-46942 A validation of a Navier-Stokes 2D solver for transonic The mixing of three-dimensional turbulent wakes in Turbofan engine control system design using the turbine cascade flows boundary layers p 639 A89-43722 LQGILTR methodology [AIAA PAPER 89-24511 p647 A89-46839 An experimental study of the effect of streamwise [NASA-CR-182303] p 685 N89-26004 Dynamic turbine blade temperature measurements vorticity on supersonic mixing enhancement TURBOJET ENGINES [AIAA PAPER 89-26891 p 680 A89-47019 [AIAA PAPER 89.24561 p 648 A89.46843 A dynamic digital model for the turbojet with A technique for the measurement of blade tip clearance A concentration probe for the study of mixing in pulse-monitoredfueler p 675 A89-45559 in a gas turbine supersonic shear flows The investigation of jet engine Starting [AIAA PAPER 89-29163 p 683 A89-47170 [AIAA PAPER 89-24591 p 703 A89-46846 p 676 A89-46025 Steady-state and time-dependent aerodynamics in an TURBULENT WAKES Compressor exit temperature analysis annular turbine cascade operating at high subsonic Mach The mixing of three-dimensional turbulent wakes in [AlAA PAPER 89-29471 p 684 A89-47191 numbers boundary layers p 639 A89-43722 TURBOMACHINE BLADES [AIAA PAPER 89-29411 p 651 A89-47185 Vortex structures in the wake of transonic flow about Dynamic stress analysis of rotating turbo-machinery Procedures for shape optimization of gas turbine disks profiles p 654 N89-25134 bladed-disk systems p 675 A89-44362 p 685 N89-25207 Flow characteristics about a trailing edge Two axial compressor designs for a stage matching TURBINE ENGINES [ UTIAS-TN-2701 p 855 N89-25952 Theoretical and experimental study of turbine investigation TWISTING [AD-A206951 p 685 N89-26006 aerodynamics p 640 A89-44639 1 An integrated design computational method for the wing Multirid calculation of three-dimensional Turbine engine structural efficiency determinatin Optimization camber and twist at subsonic and supersonic turbomachinery flows [AIM PAPER 89-25711 p 679 A89-46932 flow p 646 A89-46256 [ NASA-CR-1853321 p 708 N89-26172 Turbine aerodynamic performance measurements in TWO DIMENSIONAL FLOW TURBOMACHINERY short duration facilities Nonisentropic potential calculation for 2-D and 3-D Recent developments in calculation methods for [AlAA PAPER 89-26901 p 693 A89-47020 transonic flow p 645 A89-45434 turbomachines p 697 A89-44635 ODtical fiber sensor develooment for turbine Computational and experimental study of stall Present state of the theory of secondary flows and appiications propagation in axial compressors experimental venfications p 698 A89-44636 [AIAA PAPER 89-29141 p 704 A89-47168 [AIAA PAPER 89.24541 p 647 A89-46842 Prediction of turbomachinery perlormance Application TURBINES . Multigrid calculation of three-dimensional a centrifugal pump, a centrifugal compressor, and a Mechanisms of Endwall leakage flows and the to turbomachinery flows radial inflow turbine p 640 A89-44638 associated losses in a linear turbine rotor cascade with [NASA-CR-I p N89-26172 Measurement of three-dimensional flow in 853321 708 blade tip-clearance TWO DIMENSIONAL MODELS turbomachinery with a single slanted hot-wire [NAL-TR-985Tl p 708 N89-26168 Rarefied gas flow through two-dimensional nozzles p 700 A89-45561 TURBOCOMPRESSORS [AIAA PAPER 89-28931 p 650 A89-47156 Multi-stage compressor airfoil aerodynamics. I - Airfoil Effects of axial velocity density ratio on cascade potential flow analysis p 639 A89-44112 performances p 645 A89-45565 Prediction of the stability limit of multistage axial Computational analysis of turbomachinery flows using U compressors p 640 A89-44637 FLOFIVE Design of vane tips improving axial compressor [AIAA PAPER 89.25591 p 648 A89-46924 UH-1 HELICOPTER performance p 640 A89-44640 Multigrid calculation of three-dimensional Nondestructive qualification of UH-1 replacement parts Calculation of the total pressure loss coefficient with turbomachinery flows Completion enhancement three models for four supersonic axial-flow compressors [ NASA-CR-1853321 p 708 N89-26172 [AD-A206674] p 672 N89-25995 p 640 A89-44898 TURBOPROP AIRCRAFT UNIFORM FLOW Investigation on unsteady flow field and endwall Ilyushin's new workhorse p 662 A89-44375 Design optimization of axisymmetric bodies in boundary layer in axial flow compressor with hot-wire nonuniform transonic flow p 670 N89-25206 Jet or prop required for future regional transports? anemometer p 645 A89-45560 p 637 A89-44641 UNITED KINGDOM Two-dimensional computations of multi-stage UK airmisses involving commercial air transport compressor flows using a zonal approach Design criteria and analysis of dynamic stresses of a [CAA-3/88] p 658 N89-25143 propeller gear system [AIAA PAPER 89-24521 p 647 A89-46840 UNSTEADY AERODYNAMICS [AIAA PAPER 89-28221 p 682 A89-47107 Computational and experimental study of stall Investigation on unsteady flow field and endwall propagation in axial Compressors TURBOPROP ENGINES . boundary layer in axial flow compressor with hot-wire [AIM PAPER 89-24541 p647 A89-46842 Technology development required by propfan power anemometer p 645 A89-45560 Surge and rotating stall in axial Compressors reduction gearboxes Supersonic turbomachine rotor flutter control by [AIAA PAPER 89-28831 p 649 A89-47013 [AIAA PAPER 89-28181 p 703 A89-47104 aerodynamic detuning Rotating stall performance and recoverability of a TURBOROCKET ENGINES [AIAA PAPER 89-26851 p 680 A89-47015 high-speed 10-stage axial-flow compressor The ATRIRJ engine performance at constant dynamic Mechanical reaction of wings moving through a vortex [AIAA PAPER 89-26841 p 650 A89-47014 pressure and the consideration of transition condition region p 654 N89-25139 Model predictions for improved recoverability of a p 694 A89-46016 Aeroelastic modeling for the FIT (Functional Integration multistage axial-flow compressor TURBULENCE MODELS Technology) team F/A-18 simulation [AIAA PAPER 89-26871 p 650 A89-47017 Modeling of turbulence for compression corner flows p 670 N89-25192 Compressor exit temperature analysis and internal flows An integratedapproach to the optimum design of actively [AIAA PAPER 89.29471 p 684 A89-47191 [AIAA PAPER 89.23441 p 647 A89-46763 controlled composite wings p 670 N89-25194
A-27 UNSTEADY FLOW SUBJECT INDEX
Influence of thickness and camber on the aeroelastic Measurement of three-dimensional flow in VORTEX SHEDDING stability of supersonic throughflow fans An engineering turbomachinery with a single slanted hot-wire Evaluation of parallel inlector configurations for approach p 700 A89-45561 supersonic combustion [ NASA-TM-1019491 p 656 N89-25957 VENT ING [AIM PAPER 89-25251 p 678 A89-46898 An experimental investigation of high liftlhigh rate Airplane tests of enhanced emergency smoke venting Airfoil self-noise and prediction aerodynamics of an unsteady airfoil [D218N301] p 658 N89 25976 [NASA RP-1.2181 p 7 13 N89-25673 [AD-A206964] p 656 N89-25964 EC-18BIBoeing707 Smoke Venting flight test VORTEX SHEETS UNSTEADY FLOW [AD-A206601] p 659 N89-25979 Computation of hypersonic vortex flows with an Euler model p 642 A89-45368 Recent developments in calculation methods for VENTS turbomachines p 697 A89-44635 VORTEX STREETS EC-18BlBoeing 707 Smoke Venting flight test Computation of viscous unsteady compressible flow [ADA206601J p 659 N89-25979 Behavior of vortex street in the wake behind a circular about airfoils p 642 A89-45378 cylinder under controlled excitation p 646 A89-46694 VERTICAL LANDING Unsteady and turbulent flow using adaptation methods VORTICES A static investigation of several STOVL exhaust system p 643 A89-45392 Studies of vortex flow aerodynamics using CFD flow concepts Numerical study of unsteady viscous hypersonic blunt visualizations p 641 A89-45260 [AIAA PAPER 89-29281 p 684 A89-47180 body flows wth an impinging shock p 643 A89-45394 Accurate simulation of vortical flows Simulabon of unsteady flow past sharp shoulders on VERTICAL TAKEOFF AIRCRAFT p 643 A89-45384 semi-infinite bodies p 644 A89-45415 Tiplet VTOL UAV (vertical Takeoff and Expenmental study of vortex and aerodynamic Investigation on unsteady flow field and endwall LandinglUnmanned Aenal Vehicle) summary Volume I charactenstics of stack wings with sideslip boundary layer in axial flow compressor with hot-wire A 1200 pound tipjet VTOL unmanned aerial vehicle Part p 646 A89-46259 anemometer p 645 A89-45560 1 Co nceptual design study of a 1200-pound vehicle Strongly unsteady vortex fields at elastic helicopter rotor Numerical des for unsteady simulation of turbojet, [AD-A206738] p 672 N89-25997 blades p 654 N89-25131 turbofan and turboprop engines for training purposes FAA rotorcraft research engineering and development Mechanical reaction of wings moving through a vortex [ AIAA PAPER 89 22591 p 676 A89-46704 bibliography, 1962-1988 Supplement region p 654 N89-25139 Two-dimensional computations of multi-stage [AD A2071621 p 673 NE9 26000 VORTICITY compressor flows using a zonal approach VERY LOW FREQUENCIES Present state of the theory of secondary flows and [AlAA PAPER 89-24521 p 647 A89-46840 Omega navigation in the shadow of Antarctica experimental verifications p 698 A89-44636 Unsteady transonic airfoil computation using implicit p 660 A89-43893 An expenmental study of the effect of streamwise Euler scheme on body-fixed gnd p 652 A89-47358 VHSlC (CIRCUITS) vorticity on supersonic mixing enhancement Unsteady transition location p 652 A89-47376 A performance measure for a VHSlC avionic system - [AIAA PAPER 89-24561 p 648 A89-46843 Numerical analysis of supersonic flow through oscillating Mission dependent availability p 701 A89-46478 cascade sections by using a deforming grid VIBRATION DAMPING [ NASA-TM-1020531 p 653 N89-25119 Flutter suppression control law synthesis for the Active W Vortex flows in flyng technique Flexible Wing model WAKES [ETN-89-94428I p 653 N89-25126 [ NASA-TM-101 5841 p 690 N89-26010 Behavior of vortex street in the wake behind a circular Unsteady phenomena on delta wings with partially VIDEO EQUIPMENT broken-down vortex regions p 654 N89-25129 cylinder under controlled excitation p 646 A89-46694 ExpertVision - A video-based non-contact system for WALL FLOW Strongly unsteady vortex fields at elastic helicopter rotor motion measurement p 698 A89 451 36 blades p N89 25131 Inviscid transonic flow over a wavy wall decaying 654 Low cost equipment for flight test film and vnieo Flow about trailing edges in unsteady flow downstream p 639 A89-44390 evaluation p 698 A89-45137 p 654 N89-25135 Mechanisms of Endwall leakage flows and the A lifting suriace method for the calculatmn of steady Research and application of a new kind of measurement associated losses in a linear turbine rotor cascade with and unsteady, incompressible propeller aerodynamics technology of take-off and landing performance blade tip-clearance [ DFVLR-FB-69-04] p 657 N89-25972 p 698 A89 45144 [NAL-TR 985TI p 708 N89 26168 UNSWEPT WINGS VISCOELASTICITY WALL JETS Aerodynamics of high-lift. low-aspect-ratio unswept State space models for aeroelastic and viscoelastic Normal impinging let in crossflow A parametnc wings p 652 A89-47372 systems investigation USER MANUALS (COMPUTER PROGRAMS) [AD-A2070921 p 690 N89 26012 [AIAA PAPER 89-29571 p 684 A89-47199 Aircraft sustainability model version 1 5 Users manual VISCOUS FLOW WALLS [AD A2070151 p 638 N89-25949 Present state of the theory of secondary flows and Mechanisms of Endwall leakage flows and the Communications Interface Dnver (CID) system user's expenmental Verifications p 698 A89 44636 associated losses in a linear turbine rotor cascade with blade tip-clearance manual Computation of viscous unsteady compressible flow [ NAL-TR-985Tl p 708 N89-26168 [WTIFAAICT-TN891361 p 707 N89-26123 about airfoils p 642 A89-45378 USER REQUIREMENTS Computer simulation of some types of flows arising at WARNING SYSTEMS Selected wind shear events observed during the 1987 Automated structural optimization system (ASTROS) interactions between a supersonic flow and a boundary evaluation of enhancements to the FAA (Federal Aviation User training workshop layer p 642 A89-45381 Administration) low level wind shear alert system at [AD-A2070901 p 709 N89-26267 Unsteady and turbulent flow using adaptation methods p 643 A89 45392 Stapleton International Airport [AD-A206711] p 710 N89-26323 Numencal study of unsteady viscous hypersonic blunt WATER LANDING V body flows with an impinging shock p 643 A89-45394 In the dnnk ditch landing capability of aircraft Inviscid and viscous flow simulations around the --- V/STOL AIRCRAFT Onera-M6 by TVD Schemes p644 A8945425 p 691 A89-43890 WAVE SCATTERING Concept for an aircraft multi-component thrust Design and analysis of airfoils in transonic viscous measurement facility p 691 A89-45130 flow p646 A8946262 Review of FD-TD numerical modeling of electromagnetic wave scattering and radar cross section Large-Scale wind tunnel tests of an elector-lift STOVL Navier-Stokes simulations around a propfan using aircraft model higher order upwind Schemes p 673 A89-45107 (AIM PAPER 89-29051 p 666 A89-47165 (AIAA PAPER 89-2699) p 650 A89 47028 WAVERIDERS Integration of Scramlets wth wavender conftgurations Integrated flightlpropulslon control study for STOVL Viscous aerodynamic analysis of an oscillating flat-plate applications airfoil p 652 A89-47356 [AIAA PAPER 89.26751 p 695 A89 47005 WEAPON SYSTEMS [AIAA PAPER 89-2908) p 688 A89-47166 Flow charactenstics about a trailing edge VALVES [UTlAS TN-2701 p 655 N89-25952 The phased establishment of support maturity for the European Fighter Aircraft (EFA) p 637 A89-44644 EC-18BlBoeing 707 Smoke Venting flight test VISUAL FLIGHT RULES [AD-A206601I p 659 N89-25979 General aviation accidents involving visual flight rules The ACElRafale p 662 A89-45041 Cost-effective approach to flight testing the 'Casmu VARIABLE CYCLE ENGINES flight into instrument meteorological conditions Civil supersonics - Propulsion is the key IPB89-917001I p 658 NE9 25974 Skyshark' a stand-off weapon dispenser p 675 A89-45031 VOICE COMMUNICATION p 663 A89-45128 A comDarison of scramlet. enaine-. Derformances of Satellite low rate voice demonstration test plan ADINTS Moving toward standardization of automatic various cicles [AD-A206710] p 707 N89-26133 test equipment p 701 A89-46462 [AIAA PAPER 89-26761 p 680 A89-47006 VORTEX BREAKDOWN Hornet maintenance p 638 A89-46496 Distortion test capabilities for future fighter aircraft VARIATIONAL PRINCIPLES Vortex flows in flying technique A new vanational method for the generation of two- and [ ETN-89-944281 p 653 N89-25126 engines three-dimensional adapted grids in computational fluid Unsteady phenomena on delta wings with partially [AIM PAPER 89-29561 p 684 A89-47198 dynamics broken-downvortex regions p 654 N89-25129 WEAPONS DELIVERY B-1B development testing [ONERA, TP NO 1989-311 p 641 A89-45187 VORTEXGENERATORS p 687 A89-45165 WEAR VELOCITY DISTRIBUTION Asymmetric Separated flows about sharp cones in a The influence of altitude and speed variations on the supersonic stream p 643 A89-45402 Influence of rubbing on rotor dynamics. part 2 aeroplane's load components in longitudinal nonlinear Interaction of an oscillating vortex with a turbulent [NASA-CR 183649-PT 2) p 706 N89-25464 manoeuvres p 688 A89-45179 boundary layer p 645 A89-45906 WEIBULL DENSITY FUNCTIONS VELOCITY MEASUREMENT VORTEX INJECTORS Transmission overhaul and replacement predictions A high speed data acquisition system for the analysis An expenmental study of the effect of Streamwise using Weibull and renewal theory of velocity. density. and total temperature fluctuations at vorticity on supersonic mixing enhancement [AIAA PAPER 89 29191 p 704 A89 471 73 transonic speeds [AIAA PAPER 89-24561 p 648 A89-46843 WEIGHT REDUCTION [ SAE PAPER 881451 1 p 691 A89-45248 VORTEX RINGS An approximation function for frequency constrained Investigation on unsteady flow field and endwall Analysis of severe atmospheric disturbances from airline structural optimization p 705 N89 25196 boundary layer in axial flow compressor with hot-wire flight records Structural optimization of framed structures using anemometer p 645 A89-45560 [ NASA-TM-1021861 p 658 N89-25977 generalized optimality criteria p 706 N89 25197
A-28 SUBJECT INDEX X-29 AIRCRAFT WIND EFFECTS Mechanical reaction of wings moving through a vortex X Contributionsto the improvement of flight safety in wind region p 654 N89-25139 shear WING NACELLE CONFIGURATIONS XRAYFLUORESCENCE [DFVLR-FB-86-49] p 658 N89-25144 Nacelle/pylon interference study on a l/l7th-scale, X-ray based extensometry WIND SHEAR twin-engine, low-wing transport model [ NASA-CR-1850581 p 706 N89-25432 Contributionsto the improvement of flight safety in wind [AIAA PAPER 89-24801 p 665 A89-46864 X-15 AIRCRAFT shear Block-structured solution of transonic flows around X-15 pilot-in-the-loop and redundant/emergency [DFVLR-FB-88-49] p 658 N89-25144 wing/pylon/nacelle configurations systems evaluation p 664 A89-45168 Analysis of severe atmospheric disturbancesfrom airline [AIAA PAPER 89.29401 p 651 A89-47184 X-29 AIRCRAFT flight records WING OSCILLATIONS X-29A performance flight tests - Results and lessons [ NASA-TM-1021861 p 658 N89-25977 A new flight fluner excitation system learned p 686 A89-45154 Selected wind shear events Observed during the 1987 p 663 A89-45140 evaluation of enhancements lo the FAA (Federal Aviation Unsteady transonic airfoil computation using implicit Administration) low level wind shear alert system at Euler scheme on body-fixed grid p 652 A89-47358 Stapleton International Airport WING PROFILES [AD-A206711] p 710 N89-26323 Wind-tunnel investigations of wings with serrated sharp WINDTUNNELAPPARATUS trailing edges p 641 A89-45262 A top-down SFP analysis of a complex system --- single Vortex structures in the wake of transonic flow about failure points p 701 A89-46472 profiles p 654 N89-25134 On the stress problem of the pebble bed heat exchanger Flow about trailing edges in unsteady flow in a hypersonic wind tunnel p 654 N89-25135 [ NAL-TM-ST-87051 p 693 N89-25240 Vortices and pressure waves at plates, cylinders and WIND TUNNEL MODELS wind profiles Aeroelastic analysis of prop fan blades with a IISL-R-102/88] p 656 N89-25966 semiempirical dynamic stall model WING SPAN [AIAA PAPER 89-26951 p 703 A89-47025 Spanwise lift distributions and wake velocity surveys of Experimentaland computational flow-fieldresults for an a semi-span wing with a discontinuous twist all-body hypersonic aircraft [NASA-CR-177532] p 653 N89-25122 [NASA-CR-185347] p 655 N89-25953 WING TIP VORTICES WIND TUNNEL TESTS Numerical simulation of the flow about a wing with A new look at wind tunnel flow quality for transonic leading-edge vortex flow p 643 A89-45390 flows Inviscid and viscous flow simulations around the [SAE PAPER 8814521 p 692 A89-45249 Onera-MG by TVD schemes p 644 A89-45425 Wind-tunnel investigations of wings with serrated sharp Flow structure and scaling laws in lateral wing-tip trailing edges p 641 A69-45262 blowing p 652 A89-47352 A natural low-frequency oscillation of the flow over an Vortex flows in flying technique airfoil near stalling conditions p 645 A89-45437 [ETN-89-94428] p 653 N89-25126 Gust generation in a wind-tunnel and estimation of the Unsteady phenomena on delta wings with partially model p 692 A89-46696 broken-down vortex regions p 654 N89-25129 Validation of a free-jet technique for evaluating inlet-engine compatibility Vortex structures in the wake of transonic flow about profiles p 654 N89-25134 [AIM PAPER 89-23251 p 676 A89-46752 Mach 5 inlet CFD and experimental results Damping of wing tip vortex systems by the modification [AIAA PAPER 89.23551 p 647 A89-46769 of the wing tips p 654 N89-25138 Compressibility and shock wave interaction effects on Vortices and pressure waves at plates. cylinders and free shear layers wind profiles [AIAA PAPER 89-24601 p 648 A89-46847 [ISL-R-l02/88] p 656 N89-25966 F-16 inlet stability investigation WING TIPS [AIAA PAPER 89-24851 p665 A89-46852 Damping of wing lip vortex systems by the modification Mach 4 testing of scramjet inlet models of the wing tips p 654 N89-25138 [AIAA PAPER 89-26801 p 649 A89-47010 Structural optimization of rotor blades with straight and Parametric study of a simultaneous pitch/yaw thrust swept tips subject to aeroelastic constraints vectoring single expansion ramp nozzle p 667 N89-25152 [AIAA PAPER 89-28121 p 682 A89-47098 WING-FUSELAGE STORES Large-scale wind tunnel tests of an ejector-lift STOVL Fatigue failure initiation analysis of wing/fuselage boll aircraft model assembly p 699 A69-45210 [AIAA PAPER 89-29051 p 666 A89-47165 WINGLETS Low-speed wind tunnel performance of high-speed Vortex flows in flying technique counterrotation propellers at angle-of-anack [ETN-89-94428] p 653 N89-25126 [ NASA-TM-1022921 p 653 N89-25121 Effect of winglets loading mechanics and wing Spanwise lift distributions and wake velocity surveys of on a semi-span wing with a discontinuous twist assembly reactions p 654 N89-25137 [NASA-CR-177532] p 653 N89-25122 Flight-mechanicalinvestigations of the lateral motion of Flow characteristics about a trailing edge configurations with winglets p 689 N89-25141 [UTIAS-TN-270] p 655 N89-25952 WINGS Performance and loads data from an outdoor hover test Embedded temperature measurements in a of a Lynx tail rotor carbon-carbon wing leading edge hot structure [NASA-TM-101057] p 656 N89-25958 p 697 A89-43843 The Schlieren Observation System installed in the NAL Navier-Stokes simulation of transonic flow about wings two-dimensional high-Reynolds number transonic wind using a block structured approach p 644 A8945422 tunnel and attempts to improve it An integrated design computational method for the wing [NAL-TR-964] p 693 N89-26015 optimization camber and twist at subsonic and aupenronic WIND TUNNEL WALLS flow p 646 A89-46256 The research of 2-0 flexible wall self-correcting wind Experimental study 01 vortex and aerodynamic tunnel p 692 A89-46258 characteristics of stack wings with sideslip WIND TUNNELS p646 A8946259 Pressure measurement technique of WT-WK -..wind The analysis and measurements of radar cross section tunnels (RCS) of some wing structure models [DFVLR-MITT-BB-ll] p 693 N89-25243 p874 A89-46298 A long-range laser velocimeter for the National Full-Scale Aerodynamics Complex: New developments Aerolastic tailoring and integrated wing design and experimental application pBBB N89-25167 [NASA-TM-101081] p 708 N89-26207 An integrated approach lo the optimumdesign of actively WIND TURBINES controlled composite wings p 670 N89-25194 'Flight testing' a multi-megawan wind turbine Steady-state and transitional aerodynamic p 709 A89-45131 characteristics of a wing in simulated heavy rain WING CAMBER [ NASA-TP-29321 p 655 N89-25951 An integrated design computational method for the wing Electromagneticemissions from a modular Low Voltage optimizationcamber and twist at subsonic and supersonic Electro-Impulse De-icing system flow p 646 A89-46256 [ DOT/FAA/CT-88/31] p 707 N89-26120 WING LOADING WORKLOADS (PSYCHOPHYSIOLOGY) C-130 Hercules outer wing residual strength tests Aerospace Behavioral Technology Conference and p 663 A89-45132 Exposition. 7th. Anaheim. CA. Oct. 3-6, 1988. Effect of winglets on loading mechanics and wing Proceedings assembly reactions p 654 N89-25137 [SAE P-2161 p 638 A89-47326
A-29 PERSONAL AUTHOR INDEX
AERO NA UTlCAL ENGINEE R ING /A Continuing Sibliography (Supplement 245) November 1989
Typical Personal Author Index Listing
ADAMS, WILLIAM M., JR. ATHANS, MICHAEL Flutter suppression using eigenspace freedoms to meet Nonlinear and adaptive control I PERSONALAUTHOR I requirements p 689 N89-25191 [NASA-CR-1800881 p 712 N89-26610 ADELMAN, HENRY G. ATTYA, A. M. Numerical simulations of oblique detonations in Combustion characteristicsof gaseous flames in a gas supersonic combustion chambers p 674 A89-44115 turbine combustor ADELMAN, HOWARD M. [AIAA PAPER 89-28921 p 683 A89-47155 BOURNE, SIMON M. An initiative in multidisciplinary optimization of - Helicopter roll control effectiveness criteria program AVIZIENIS. ALGIRDAS rotorcraft p 667 N89-25151 In search of effective diversity - A six-language study summary ADOLPH, CHARLES E. [NASA-CR-17747711 P 39 N89-10046 of fault-tolerant flight control software Aircraft development test and evaluation - An Office of p 710 A89-44423 7 -7 the Secretary of Defense perspective p 638 A89-45143 AFZALI, HOSSEIN B Development and verificationof software for flight safety critical strapdown systems p 659 A89-43827 BABA, NOBUHIRO 41HARA. YASUHIKO Numerical study of the 3D separating flow about Experimental study on aerodynamic characteristics of obstacles with sharp corners p 641 A89-45363 hypersonic transport configuration p 640 A89-44972 BACH, R. E., JR. Listings in this index are arranged alphabetically AITHAL, R. Treatment of body forces in boundary element design Analysis of severe atmospheric disturbances from airline by personal author. The title of the document pro- sensitivity analysis p 705 N89-25187 flight records vides the user with a brief description of the subject AKAGI, MASAHIRO [ NASA-TM-1021861 p 658 N89-25977 matter. The report number helps to indicate the T-4 inletlengine compatibility flight test results BADESHA, S. S. [AIAA PAPER 89.24661 p 665 A89-46853 Block-structured solution of transonic flows around type of document listed (e.g., NASA report, trans- AKIBA, RVOJIRO winglpylonlnacelle configurations lation, NASA contractor report). The page and ac- A simple theory of aerospaceplane [AIAA PAPER 89-29401 p 651 A89-47184 cession numbers are located beneath and to the p 662 A89-44975 BAl, XUE-SONG right of the title. Under any one author’s name the ALBONE, C. M. Nonisentropic potential calculation for 2-D and 3-D A flow-field solver using overlying and embedded transonic flow p 645 A89-45434 accession numbers are arranged in sequence with meshes together with a novel compact Euler algorithm BAKER, V. D. the AIAA accession numbers appearing first. p 641 A89-45359 Expendable supersonic exhaust nozzle concepts ALCOCK, JOSEPH F. [AIM PAPER 89-29271 p 684 A89-47179 Transferringjet engine diagnostic and control technology BALAGUER, J. P. to liquid propellant rocket engines Hot ductility response of AI-Mg and AI-Mg-Li alloys A [AIAA PAPER 89-28511 p 682 A89-47125 p 695 A89-45330 ALEKSANDROVICH, E. V. BAO, GUOHUA ABDELGAYED, R. G. Numerical and experimental investigation of Experimental study of vortex and aerodynamic Evaluation of novel igniters in a turbulent bomb facility airframe-integrated inlet for high velocities characteristicsof Stack wings with sideslip and a turbo-annular gas turbine cornbustor [AIAA PAPER 89.26791 p 649 A89-47009 p 646 A89-46259 [AIAA PAPER 89.29441 p 684 A89-47188 ALLSUP, JERRY R. BAPURAO, M. N. Comparisons between unleaded automobile gasoline On the stress problem of the pebble bed heat exchanger ABDOL-HAMID, KHALED S. and aviation gasoline on valve seat recession in light in a hypersonic wind tunnel The applicationof 3D marching scheme forthe prediction aircraft engines [NAL-TM-ST-8705] p 693 N89-25240 of supersonic free jets [NIPER-409] p 697 N89-26110 BARBER. MICHAEL L [AIAA PAPER 89-28971 p 651 A89-47160 AMIET, R. K. A preliminary investigation into Euler methods for ABEL, IRVING Noise produced by turbulent flow into a rotor: Theory application to multi-element aerofoils for high lift Overview of Dynamics Integration Research (DIR) manual for noise calculation [AERO-REPT-8710] p 708 N89-26196 program at Langley Research Center [ NASA-CR-1817881 p 714 N89-26683 BARBER, THOMAS J. p 667 N89-25150 AMUNDSON, MARK H. Hypersonic vehicle propulsion . A computational fluid ABGRALL, REMI Distortion test capabilities for future fighter aircraft dynamics application case study p 639 A89-44116 Generalization of the Roe scheme for computing flows engines BARILE. ANTHONY J. of mixed gases with variable concentrations [AIAA PAPER 89.29561 p 684 A89-47198 Aircraft jet engine exhaust blast effects on Par-56 runway p 639 A89-44322 ANDERSON, D. M. threshold lamp fixtures Computerized Design Synthesis (CDS). A [DOT/FAAICT-89/41 p 694 N89-26018 ABIlT, JOHN D., 111 database-driven multidisciplinary design tool BARON, JUDSON R. Initial supersonic combustion facility measurements p 712 N89-25180 Unsteady and turbulent flow using adaptation methods [AIAA PAPER 89-24621 p 692 A89-46849 ANDERSON, N. E. p 643 A89-45392 ABRAMSON, JANE S. Development testing of the 578 propfan gear system BARR, R. Tipjet VTOL UAV (Vertical Takeoff and [AIM PAPER 89-28171 p 682 A89-47103 Omega navigation in the shadow of Antarctica LandinglUnmannedAerial Vehicle) summary. Volume 1: ANDERSON, ROBERT A. p 660 A89-43893 A 1200 pound tipjet VTOL unmanned aerial vehicle. Part Machine vision for control of gas tungsten arc welding BARTHELEMY, JEAN-FRANCOIS M. 1:Co nceptual design study of a 1200-poundvehicle p 700 A89-45950 Recent Advances in Multidisciplinary Analysis and [ AD-A2067381 p 672 N89-25997 ANFINDSEN, KNUT Optimization, pall 1 ACHACHE. MARC Airline operations and the contaminated runway [NASA-CP-3031-PT-l] p666 N89-25146 Simulation methodology for helicopter automatic flight [SAE PAPER 8814601 p 858 A89-47339 Recent Advances in Multidisciplinary Analysis and control systems p 686 A89-45048 AONO, H. Optimization. part 2 ACOSTA, WALDO A. Apparent strain characteristics of strain gauges under [NASA-CP-3031-PT-2] p 669 N89-25173 Fuel properties effect on the performance of a small high temperature environment p 697 A89-43844 Recent Advances in Multidisciplinary Analysis and high temperature rise combustor ARAKAWA, CHUlCHl Optimization, part 3 [ NASA-TM-1020961 p 685 N89-25238 Navier-Stokes simulatiohs around a propfan using [ NASA-CP-3031-PT-31 p 670 N89-25201 higher-order upwind schemes BATES, PRESTON R. ADAMCZYK, JOHN J. [AIAA PAPER 89.26991 p 650 A89-47028 TRUSS: An intelligent design system for aircraft wings Average-passagesimulation of counter-rotatingpropfan ARINA. RENZO p 711 N89-25162 propulsion systems as applied to cruiSe missiles Multidimensional adaptive Euler solver BATSON, ROBERT 0. [AIAA PAPER 89-29431 p 651 A89-47187 p 641 A89-45360 Federal incentivesfor industrialmodernization: Historical ADAMS, MARY S. ARNOLD, JAMES R. review and future opwrtunities Mixing enhancement in a supersonic combustor Powered lift aircraft take off climb performance with one [NASA-TM-1017851 p 714 N89-25764 [AIAA PAPER 89.27941 p 681 A89-47088 engine inoperative p 663 A89-45127 BATTEUATO. L. ADAMS, PAUL F. W. ARTLEV, MARGERY E. Technology development required by propfan power The military Dash 8 flight test program Probabilistic damage tolerance methods for metallic reduction gearboxes p 664 A89-45145 aerospace structures p 672 N89-25237 [AIAA PAPER 89-28181 p 703 A89-47104
B- 1 BAXTER, CHARLES PERSONAL AUTHOR INDEX
BAXTER. CHARLES BOBER, L J. BUSHNELL, DAVID 8. Mode S performance test plan Large scale advanced propeller blade pressure A simple low-cost telemetry system for those of modest [DOT/FAA/CT-TN89/241 p 707 N89-26127 distributions - Prediction and data means p 660 A89-45138 BEACHER. B. F. [AIAA PAPER 89-26961 p 650 A8947026 BUSSOLETTI, JOHN E. Improved compressor performance using recessed BOERSTOEL, J. W. Transonic analysis of arbitrary configurations using clearance (trenches) p 674 A89-44113 Numerical simulation of the flow about a wing with locally refined gnds p 644 A89-45419 BEALE, D. K. leading-edge vortex flow p 643 A89-45390 BUTT, GRAHAM Validation of a free-jet technique for evaluating BOHLMANN, JON Effect of winglets on loading mechanics and wing inlet-enginecompatibility Aerolastic tailoring and integrated wing design assembly reactions p 654 N89-25137 [AIAA PAPER 89-23251 p 676 A89-46752 p668 N89-25167 BUTTRILL, CAREY S. BEASLEY, JOSEPH N. BOIS, G. Results of including geometric nonlinearities in an Establishing artificial intelligence technology in a flight Present state of the theory of secondary flows and aeroelastic model of an F/A-18 p 669 N89-25190 test environment p 663 A89-45135 experimental venfications p 698 A89-44836 BUYUKATAMAN. KAYAALP BEATON, MICHAEL S. BOLUKBASI. A. 0. Design criteria and analysis of dynamic stresses of a Fiber metal acoustic material for gas turbine exhaust Computenzed Design Synthesis (CDS). A propeller gear system environments p 695 A89-44400 database-driven multidisciplinary design tool [AIAA PAPER 89-28221 p 682 A89-47107 BECKEL, STEPHEN A. p 712 N69-25160 BYINGTON, C. S. Fuel properbes effect on the performance of a small BOWERS. D. Evaluation of parallel injector configurations for high temperature nse combustor Advanced thrust vectoring nozzles for supercruise fighter supersonic combustion [ NASA-TM-I020961 p 685 N89-25238 aircraft [AlAA PAPER 89-25251 p 678 A89-46898 BECKER, WILLIAM J. [AIM PAPER 89-28161 p 682 A89-47102 Dynamic turbine blade temperature measurements BOWMAN. KEITH B [AIAA PAPER 89-26891 p 680 A89-47019 Optimum structural design with static aeroelastic C BENNETT. JOHN constraints p 669 N89-25171 Air traffic control - No easy solutions in a complex BOYER, KEITH M. CABELLO, JEAN terminal environment Model predictions of fan response to inlet temperature A new variational method for the generation of two-and [SAE PAPER 8814691 p 661 A89-47335 transients and spatial temperature distortion three-dimensional adapted grids in computational fluid BENSING, GERALD K. [AIAA PAPER 89-26861 p 650 A89-47016 dynamics Dynamic turbine blade temperature measurements Model predictions for improved recoverability of a [ONERA. TP NO. 1989-311 p 641 A89-45187 [AIAA PAPER 89-26891 p 680 A89-47019 multistage axial-flow compressor CAI. YUANHU BENTLY, DONALD E. [AIM PAPER 89.26871 p 650 A89-47017 A dynamic digital model for the turbojet with Influence of rubbing on rotor dynamics. part 2 BRADLEY, D. pulse-monitoredfueler p 675 A89-45559 [ NASA-CR-I83649-PT-21 p 706 N89-25464 Evaluation of novel igniters in a turbulent bomb facility CAMBIER, JEAN-LUC BENTSEN, ROSS A. and a turbo-annular gas turbine combustor Numerical simulations of oblique detonations in Evaluation of nondestructive test equipment for airfield [AIAA PAPER 89.29441 p 684 A89-47188 supersonic combustion chambers p 674 A89-44115 pavements. Phase 1: Calibration test results and field data BRATTON, TOM collection Communications Interface Driver (CID) system user's CAMPBELL, BRYAN A. [AD-A207159] p 694 N89-26020 manual Steady-state and transitional aerodynamic characteristics of a mng in simulated heavy rain BERESTOV, LEONID M. [DOT/FAAICT-TN89/361 p 707 N89-26123 [NASA-TP-2932] p 655 N89-25951 Modeling of controlled flight dynamics using in-flight BRAY, D. simulators p 688 A89-46546 Normal impinging jet in crossflow - A parametric CAMPBELL, R. L Optimum design of swept-fonvard high-aspect-ration BERGHAUS, UWE investigation graphite-epoxy wings p 669 N89-25172 Prototype of a slant visual range measuring device [AIAA PAPER 89-29571 p 684 A89-47199 [ DFVLR-FB-86-42] p 713 N89-25697 BREZINSKY, RICHARD H. CANFIELD, R. A. An approximation function for frequency constrained BESSEY, ROGER Long duration balloon technology survey. phase 1 L structural optimization p 705 N89-25196 Nondestructive qualificationof UH-1 replacement parts: [ ADA206975 I p 656 N89-25965 Completion enhancement BRILEY. W. R. Structural optimization of framed structures using [AD-A2066741 p 672 N89-25995 Solution of the incompressible Navier-Stokes equations generalized optimality cnteria p 706 N89-25197 using artificial compressibility methods Automated structural optimization system (ASTROS): BETEILLE. ROGER p 641 A89-45366 Airbus Industrie. lessons from experience User training workshop p 714 A89-45039 BRINE, GERALD T. [ADA2070901 p 709 N89-26267 Flap system for short takeoff and landing aircraft CAPILLON, BERNARD BEZOS, GAUDY M. [AD-D013981] p 671 N89-25234 Steady-state and transitional aerodynamic The SNECMA group today and tomorrow BRINES, G. L p 637 A89-45034 characteristics of a wing in simulated heavy rain Technology readiness for advanced ducted engines CAPONE, FRANCIS J. [ NASA-TP-2932I p 655 N89-25951 [AIAA PAPER 89-24791 p 678 A89-46863 Parametric study of a simultaneous pitchlyaw thrust BHAGAT, WILBUR W. K. BRITZ, vectoring single expansion ramp nozzle R8M through Avionics/Electronics Integrity Program High performance gear systems and heat management [AIAA PAPER 89.28121 p 682 A89-47098 p 701 A89-46480 for advanced ducted systems BHATT, VINAY [AIAA PAPER 89-24821 p 678 A89-46865 CARETTO, L S. Mulblevel decomposibon of complete vehicle BROOKS. THOMAS F. Ramjet combustor modeling for engineering design configurationin a parallel computing environment Airfoil self-noise and prediction [AlAA PAPER 89-27991 p 681 A89-47092 p 670 N89-25205 [ NASA-RP-I2181 p 71 3 N89-25673 CARLSON, DONALD L. BIGGERS. JAMES C. BROWN, KENNETH W. Experimental localized radar cross sections of aircraft Tipjet VTOL UAV (Verbcal Takeoff and Structural tailonng of cwnter rotation propfans p 673 A89-45105 Landing/Unmanned Aerial Vehicle) summary. Volume 1: p 685 N89-25165 CARPENTER, D. A. A 1200 pound tipjet VTOL unmanned aerial vehicle. Part BRUNEAU, CHARLESHENRI An experimental technique for the measurement of mass 1:Co nceptual design study of a 1200-pound vehicle Computation of hypersonic vortex flows with an Euler flow of scramjet inlets tested in hypersonic pulse [ AD-A2067361 p 672 N89-25997 model p 642 A89-45368 facilities BIL, CORNELIS BRY, P. [AIAA PAPER 89-2331I p 692 A89-46755 Development and application of a computer-based Theoretical and expenmental study of turbine CARPENTER, MARK H. system for conceptual aircraft design aerodynamics p 640 A89-44639 Mixing enhancement in a supersonic combustor [ ETN-89-948861 p 673 N89-26001 BUCK. GREGORY M. [AIM PAPER 89-27941 p 681 A89-47088 BILANIN, A. J. Automated thermal mapping techniques using chromatic CARPENTIER, JEAN image analysis Feasibility of predicting performance degradation Of French aerospace research in the international [NASA-TM-101554] p 706 N89-25443 airfoils in heavy rain context p 691 A89-45036 [ NASA-CR-1818421 p 657 N89-25973 BUGGELN, R. C. CARROLL, MARK A. Solution of the incompressible Navier-Stokes equations Computational analysis of turbomachinery flows using BIRDSALL, JIM using artificial compressibility methods Light weight gas turbine engine fuel pumping FL 0 FIVE p 641 A89-45366 [AIAA PAPER 89.25591 p 648 A89-46924 technology BULLARD. RANDY E. [AlAA PAPER 89-25871 p 703 A89-46943 CARSTENS, VOLKER Integrated flight/propubon control system design based Two-dimensional elliptic grid generation for airfoils and BITTKER. DAVID A. on a centralized approach cascades Investigation of low NOx staged combustor concept in [ NASA-TM-1021371 p 690 N89-26009 [ DFVLR-FB-88-52] p 653 N89-25125 high-speed civil transport engines BUNTING, S. R. [ AlAA PAPER 89-29421 p 684 A89-47186 An initial assessment of the impact of boundary layer CASSENTI, BRICE N. BLACK, RICHARD T. control on SST Time demndent Drobabilistic failure of coated Establishing artificial intelligence technology in a flight [AERO-REPT-W02] p 656 N89-25969 components test environment p 663 A89-45135 BURKEN, J. J. [AIAA PAPER 89-2900) p 704 A89-47163 BLACKBURN, R. B. Control surface spanwise placement in active flutter CASSIDY, F. M. Semi-constant volume pulse combustion for gas turbine suppression systems p 689 N89-25195 Engine life maturation process engine starting BUSH, ALBERT J.. 111 [AIAA PAPER 89.24641 p 677 A89-46851 [AIM PAPER 89-24491 p 677 A89-46838 Evaluation of nondestructive test equipment for airfield CATTAFESTA, L N. BLANCHARD, W. F. pavements. Phase 1: Calibration test results and field data An experimental study of the effect of streamwise Civil satellite navigation and lmtion systems collection vorticity on supersonic mixing enhancement p 694 A89-43892 [ AD-A207159] p 694 N89-26020 [AIAA PAPER 89-24561 p 648 A69-46643
6-2 PERSONAL AUTHOR INDEX DICUS, JOHN H.
CAUGHEY, DAVID A. CHIKATA, T. CORSIGLIA, VICTOR Multigrid calculation of three-dimensional Apparent strain characteristics of strain gauges under Large-scalewind tunnel tests of an elector-lift STOVL turbomachinery flows high temperature environment p 697 A89-43844 aircraft model [NASA-CR-185332] p 708 N89-26172 CHINZEI, NOBUO [AIAA PAPER 89-29051 p 666 A89-47165 CAUSON, D. M. A comDarison of scramiet. engine-. performances of COX, G. B.. JR. A high resolution finite volume scheme lor steady various cycles Hypersonic vehicle propulsion - A computational fluid external transonic flow p 642 A89-45369 [AIM PAPER 89-26761 p 680 A89-47006 dynamics application case study p 639 A89-44116 CELI, ROBERTO CHIVERS. J. W. H. CRATCH, PRESTON Structural optimization of rotor blades with straight and A technique for the measurement of blade tip clearance Controller evaluation of Initial Data Link air traffic control swept tips subject to aeroelastic constraints in a gas turbine services Volume 2 Mini Study 2 p 667 N89-25152 [AIAA PAPER 89-29161 p 683 A89-47170 [ DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 CETEL, ALAN D. CHOPRA, INDERJIT CUI, WE1 Efficient sensitivity analysis and optimization of a Microstructure-property relationships in advanced nickel Experimental research on swirling combustion helicopter rotor p 668 N89-25155 base superalloy airfoil castings p 696 A89-45929 efficiency p 675 A89-45558 CHOU, YU T. CHAMBERLIN, ROGER Design criteria lor aggregate-surfaced roads and CULL, RAY A. Space age metals technology, Proceedings 01 the New hvoersonic lacilitv.. caoabilitv . at NASA Lewis airfields Second International SAMPE Metals and Metals ResearchCenter [AD-A2070591 p 694 N89-26019 [AIAA PAPER 89.2534) p 692 A89-46905 CHRISTHILF. DAVID M. Processing Conference, Dayton. OH, Aug 2-4, 1988 p 696 A89-45927 CHAMIS, C. C. Flutter suppression using eigenspace freedoms to meet Comoutational structural mechanics lor enaine requirements p 689 N89-25191 CURRY, ARTHUR E. structures CHRISTIANSEN, RICHARD S. Influence of rubbing on rotor dynamics, part 2 [ NASA-TM-1021191 p 709 N89-26259 Integrated controls pay-off [ NASA-CR-183649-PT-21 p 706 N89-25464 CHAMPNEY, J. M. [AIAA PAPER 89-27041 p 688 A89-47031 Modeling of turbulence for compression corner llows CHU, R. C. and internal flows Full scale fatigue crack growth test of advanced jet D [AIAA PAPER 89-23441 p 647 A89-46763 trainer AT-3 p 664 A89-45207 CHAN, P. C. lsoparametric shear spring element applied to crack DAFNIS, ATHANASSIOS A numerical investigation of scramjet combustors patching and instability p 699 A89-45208 Effect 01 winglets on loading mechanics and wing [AIAA PAPER 89-25611 p 679 A89-46926 CHUANG, H. ANDREW assembly reactions p 654 N89-25137 CHANG, KEH-MINN Unsteady transonic airfoil computation using implicit DAIGUJI. HlSAAKl Continual opportunities lor superalloy development Euler scheme on body-fixed grid p 652 A89-47358 An implicit time-marching method for solving the 3-0 p 696 A89-45931 CHUIAN, ROSTISLAV K. compressible Navier-Stokes equations CHANG, KEUN-SHIK Methods for the mathematical modeling of flight vehicle p 642 A89-45374 Inviscid transonic flow over a wavy wall decaying engines p 71 1 A89-46551 DARDEN, CHRISTINE M. downstream p 639 A89-44390 CHUNBAO, YANG Effect of milling machine roughness and wing dihedral Research and application of a new kind of measurement CHANGHO, NAM on the supersonic aerodynamic characteristics of a highly technology 01 take-off and landing performance AerOSeNOelaStiC tailoring for lateral control swept wing enhancement p 689 N89-25189 p 698 A89-45144 [ NASA-TP-29181 p 652 N89-25117 CHUNG, CHAN-HONG CHAO, C. K. DASSAULT, SERGE Rarefied gas flow through two-dimensional nozzles Dassault. leader in European military and business Fatigue failure initiation analysis of wing/fuselage bolt [AIAA PAPER 89-28931 p 650 A89-47156 assembly p 699 A89-45210 aircraft p 637 A89-45033 CLEARY, JOSEPH W. DAVINO, RONALD M. CHAO, GUOYING Experimental and computational flow-field results for an Radiative characteristics of hypersonic cone wake Concept lor an aircraft multi-component thrust all-body hypersonic aircraft measurement facility p 691 A89-45130 p 646 A89-46263 [ NASA-CR-1853471 p 655 N89-25953 CHAPMAN, D. C. CLIFF, E. M. DAVIS, D. 0. Further experiments on supersonic turbulent flow Testing of the 578-OX propfan propulsion system Relaxation oscillations in aircraft cruise-dash development in a square duct p 652 A89-47357 [AIAA PAPER 89-2581 I p 679 A89-46938 optimization CHARNLEY, JOHN [AD-A206722] p 672 N89-25996 DAVIS, JAMES Navigation aids to aircraft all-weather landing CLUKEY, STEVEN J. Functional requirements 01 the Communications p 659 A89-43891 A high speed data acquisition system for the analysis Interface Driver (CID) [DOT/FAA/CT-TN87/41-REV] p 707 N89-26121 CHASE, HERBERT A. of velocity. density, and total temperature fluctuations at Hornet maintenance p 638 A89-46496 transonic speeds DAVIS, JIM CHAlTOPADHYAY, ADIT1 [SAE PAPER 8814511 p 691 A89-45248 Communications Interface Driver (CID) system user's Structural optimization of rotor blades with integrated COCHETEUX, JEAN BERNARD manual dynamics and aerodynamics p 668 N89-25156 European gas turbine engines p 675 A89-45042 [DOT/FAA/CT-TN89/36] p 707 N89-26123 CHAlTOT, JEAN-JACOUES COHEN, GERALD C. DE HAIJ, L. Computation of hypersonic vortex flows with an Euler Experiences with a prevalidation methodology for Design and testing of a common engine and nacelle model p 642 A89-45368 designing integratedlpropulsion control system for the Fokker 100 and Gulfstream GIV airplanes CHAY, SEUNG C. architectures [AIAA PAPER 89-24861 p 666 A89-46867 A performance measure lor a VHSlC avionic system - [AIAA PAPER 89-27031 p 688 A89-47030 DE WITT, KENNETH J. Mission dependent availability p 701 A89-46478 COHEN, J. M. Rarefied gas flow through two-dimensional nozzles CHEN, BING-MU Spray patternation at high pressure [AIAA PAPER 89.28931 p 650 A89-47156 Difference methods lor initial-boundary-value problems [AIAA PAPER 89-23231 p 702 A89-46750 DECHAUMPHAI, PRAMOTE and flow around bodies (Revised edition) COLANTUONI, S. Finite element flow-thermal-structural analysis 01 p 646 A89-46198 A validation of a Navier-Stokes 20 solver lor transonic aerodynamically heated leading edges CHEN, H. C. turbine cascade flows p 655 N89-25198 Development of a highly efficient and accurate 30 Euler [AlAA PAPER 89-2451 1 p647 A89-46839 DECHER, R. flow solver p 642 A89-45370 COLE, J. D. Computational modeling 01 axisymmetric propeller-hull CHEN, HOAZHI The military Dash 8 llight test program interaction in slender low drag bodies The solution of 3-0 temperature distribution in a cycling p664 A89-45145 [AIAA PAf'ER 89-26741 p 649 A89-47004 oil cooled aircraft ac generator by network topology COLEMAN, SANDRA C. Brayton cycle engines with reciprocating work method p 701 A89-46282 Federal incentives lor industrialmodernization: Historical components CHEN, SHIH H. review and future opportunities [AIAA PAPER 89.29331 p 704 A89-47181 Prediction of periodic loadings on single rotation proplan [ NASA-TM-1017851 p 714 N89-25764 DEITCH, ALLEN with off-axis inflow COLLIER, M. S. Inertial guidance test facility using the earth [AIAA PAPER 89-26941 p 681 A89-47024 Validation of a free-jet technique lor evaluating environment p 700 A89-46218 CHEN, YEN-SEN inlet-engine compatibility DEL VECCHIO, J. J. Numerical study 01 reactive ramjet dump combustor [AIAA PAPER 89-23251 p 676 A8946752 An air photo analysis of an airplane crash llowfields with a pressure based CFD method CONNERS. TIMOTHY R. p 657 A89-45337 [AIAA PAPER 89-27981 p 681 A89-47091 Measurement effects on the calwlatiopn of in-flight DEMEIS. RICHARD CHENG, JlZU thrust for an F404 turbofan engine Aging aircraft p 657 ' A89-45296 Treatment of body forces in boundary element design [AIAA PAPER 89-23641 , p 677 A8946777 DERRE, ANDRE sensitivity analysis p 705 N89-25187 COPENHAVER, W. W. From avionics technology to architectural concepts CHENG, Y. P. Rotating stall performance and recoverability of a p 637 A89-45035 Optimization of rotor blades lor combined structural. high-speed IO-stage axial-flow compressor DERVIEUX. A. performance, and aeroelastic characteristics [AlAA PAPER 89-26841 p 650 A8947014 Low-storage implicit upwind-FEM schemes for the Euler p 667 N89-25153 CORNING, MICHELLE M. equations p 642 A89-45375 CHETVERUSHKIN, B. N. Powered lift aircraft take off climb performancewithone DEYST, JOHN J., JR. Computer simulation of some types of flows arising at engine inoperative p 663 A8945127 Evaluation of a fault tolerant digital engine controller interactions between a supersonic flow and a boundary CORPENING, G. P. [AIM PAPER 89-25891 p 680 A89-46944 layer p 642 A89-45381 An experimental technique for the measurementof mass DICUS, JOHN H. CHEU, TSUCHIEN flow of scramjet inlets tested in hypersonic pulse New hypersonic facility capability at NASA Lewis Procedures for shape optimization of gas turbine disks facilities Research Center p 685 N89-25207 [AlAA PAPER 89-2331 ] p 692 A89-46755 [AIAA PAPER 89-25341 p 692 A89-46905
B-3 DIEKMANN, A. PERSONAL AUTHOR INDEX
DIEKMANN, A. DUNSFORD, N. J. F Flight-mechanical investigabons of the lateral motion of Microwave landing system instrumentation - A pilot's configurabons with winglets p 689 N89-25141 viewpoint FAGAN. JOHN R., JR. DIMEO, MARK [SAE PAPER 881461 I p 661 A89-47340 L2F 8 LDV velocimetry measurement and analysis of Analysis of helicopter environmental data Indianapolis DURANTI, P. the 3-D flow field in a centrifugal compressor downtown heliport, Wall Street heliport Volume 1 Cost-effectwe approach to flight testing the 'Casmu [AIM PAPER 89.25721 p 648 A89-46933 Summary Skyshark' a stand-off weapon dispenser FALATO, BETTY K. [ AD-AZ06708) p 710 N89-26294 p 663 A89-45128 Notice to Airmen (NOTAM) System operational DING, JlNG concept DURBIN, ROGER T. Application of the boundary element method to unsteady [DOT/FAA/CT-TN89/10] p 658 N89-25142 heat transfer problems p 700 A89-45552 UHB demonstrator flight test program - Phase 2 FARBRIDGE, JOSEPH [AIAA PAPER 89-25821 p 679 A89-46939 DISBROW, JAMES 0. Large-scale wind tunnel tests of an ejector-lift STOVL Preliminary development of an intelligent computer DWOVER, D. L. aircraft model assstant for engine monitoring International Conference on Numencal Methods in Fluid [AIAA PAPER 89.29051 p 666 A89-47165 [AIAA PAPER 89.25391 p 674 A89-46910 Dynamics. llth, Williamsburg. VA, June 27-July 1. 1988. FARMER, RICHARD C. DITTRICH, KAV W. Proceedings p 699 A89-45351 Numerical shrdy of reaclive ramjet dump combustor Stealth technology for reducing aircraft recognition DZVGADLO, ZBlGNlEW flowfields with a pressure based CFD method p 673 A89-44645 Numencal modelling of flight dynamics and flight test [AIAA PAPER 89-27981 p 681 A89-47091 DODO, ALAN J data identificationof a let trainer airplane FAVINI, BERNARDO An overview of the Douglas Aircraft Company D 663 A89-45139 Multidimensional adaptive Euler solver Aeroelastic Design Optimization Program (ADOP) p MI A89-45360 p 671 N89-25221 FEI, JING-GAO DOEL, DAVID L Local analytical methods for digital simulation of Diagnostic expert systems for gas turbine engines - E dynamical control system p 71 1 A89-46244 Status and prospects FENG, VANGVUAN [AIAA PAPER 89 25851 p 680 A89-46941 EASTEP, F. E. Experimental investigation of aeroengine high-speed DOLLING, D. S. Optimum structural design with static aeroelastic roller bearing p 700 A89-45570 Expenmental study of spreading rate enhancement of constraints p 669 N89-25171 FENNELL, ROBERT E. high Mach number turbulent shear layers ECER, A. Fluner suppression using eigenspace freedoms to meet [AIAA PAPER 89-24581 p 648 A89-46845 Block-structured solution of transonic flows around requirements p 689 N89-25191 DONELSON, JOHN E. wing/pylon/nacelle confgurabons FEO, A. UHB demonstrator flight lest program - Phase 2 [AIAA PAPER 89-29401 p 651 A89-47184 Feasibility of predicting performance degradation of [AIM PAPER 89-25821 p 679 A89-46939 ECKARDT, D. airfoils in heavy rain DONOVAN. MICHAEL F. Technology readiness for advanced ducted engines [ NASA-CR-1818421 p 657 N89-25973 Selected wind shear events observed dunng the 1987 [AIAA PAPER 89-24791 p 678 A89-46863 FERRElTI, G. evaluation of enhancements to the FAA (Federal Aviation Cost-effective approach to flight testing the 'Casmu ECKELS, PHILLIP W. Administration) low level wind shear alert system at Skyshark' a stand-off weapon dispenser Superconducting rotor cooling system Stapleton International Airport p 663 A89-45128 [ADA206711 ] p 710 N89-26323 [ACJ-D014020] p 709 N89-26240 FEZOUI, L DORMER, IAN EDWARDS, 0. Low-storage implicit upwind-FEM schemes for the Euler In the dnnk p 691 A89-43890 An air photo analysls of an airplane crash equations p 642 A89-45375 DORTYANN. K. p 657 A89-45337 FISCHER, B. Computation of viscous unsteady compressible flow EDWARDS, JOE Configuration studies for a regional airliner using about airfoils p 642 A89-45378 F-l4/F110 high angle of attack flight tests open-rotor ultra-high-bypass-ratio engines Flow abut trailing edges in unsteady flow p 686 A89-45153 [AIM PAPER 89-25801 p 666 A89-46937 p 654 N89-25135 EICHHORN, DAVID J. FLEETER, SANFORD WWLER, CONSTANCE A. B-1B development testing p 687 A89-45165 L2F 8 LDV velocimetry measurement and analysis of Model predictions of fan response lo inlet temperature EICHORN. FRANK L the 3-D flow field in a centrifugal compressor transients and spatial temperature distortion Aircraft sustainability model version 1 5 Users manual [AIM PAPER 89-25721 p 648 A89-46933 [AIAA PAPER 89-26861 p 650 A89-47016 [AD-A207015] p 638 N89-25949 Supersonic turbomachine rotor flutter control by DRING, R. P. EIDELMAN, S. aerodynamic detuning Multi-stage compressor airfoil aerodynamics I - Airfoil A review of propulsion applications of the pulsed [AIAA PAPER 89.26851 p 680 A89-47015 potential flow analyss p 639 A89-44112 detonation engine concept Viscous aerodynamic analysis of an oscillating flat-plate DRING, ROBERT P. [AIAA PAPER 89-24461 p 677 A89-46837 airfoil p 652 A89-47356 Two-dimensional computabons of multi-stage ELIZAROVA, T. G. FLEISCHER, R. L compressor flows using a zonal approach Computer smulabon of some types of flows ansing at Mechanical propertles of high-temperature beryllium [AIAA PAPER 89-24521 p 647 A89-46840 interactions between a supersonic flow and a boundary intermetallic compounds p 697 A89-47213 Three dimensional flow and temperature profile layer p 642 A89 45381 FLETCHER, 0. G. attenuation in an axial flow turbine ELLIOlT, G. S. Quantitative charactenzation of a nonreacting, [AD-A206736] p685 N89-26005 Compressbility and shock wave interaction effects on supersonic combustor flowfieldusing unified, laser-induced DRIVER, MARK A. free shear layers iodine fluorescence Application of simple wave theory to the radiative [AIAA PAPER 89-24601 p 648 A89-46847 [AIAA PAPER 89-25651 p 703 A89-46928 boundary conditions required for an internal flow Euler ELVERS, GREG C. FLEURV, R. E. solver An exploratory study of the use of movement-correlated Testing of the 578-DX proplan propulsion system [AlAA PAPER 89-25771 p 648 A89-46935 cues in an auditory head-up display p 674 A89-45329 [AlAA PAPER 89-25811 p 679 A89-46938 DRUMMOND. J. PHILIP ENZINGER, F. J. FORMAGGIA, L Mixing enhancement in a supersonic combustor Low cost equipment for flight test film and video Adaptive numerical solutions of the Euler equations in [AlAA PAPER 89-27941 p681 A8947088 evaluation p 698 A89-45137 3D using finite elements p 644 A89-45413 DUDAS, CHARLES EPSTEIN, A. H. FOSS, WILLARD E., JR. Functional requirements of the Communications Turbine aerodynamic performance measurements in Effects of nonlinear aerodynamics and static Interface Dwer (CID) short duration facilities aeroelasticity on mission performance calculations for a [DOT/FAA/CT-TN87/41-REV] p 707 N89-26121 [AIM PAPER 89-26901 p 693 A89-47020 fighter aircraft p 669 N89-25170 Communications Interface Dnver (CID) system user's ERLICHMAN, SCOlT FRANK, DANIEL 0. manual Analysis of helicopter environmental data Indianapolis A corollary lo - Duane's postulate on reliability growth [ DOT/FAA/CT-TN89/36] p 707 N89-26123 downtown heliport. Wall Street heliport Volume 1 p 701 A89-46474 DUDLEY, MICHAEL Summary FRANKLIN, WESLEY 0. Large-scale wind tunnel tests of an ejector-lift STOVL [AD A2067081 p 710 N89-26294 Influence of rubbing on rotor dynamics, part 2 aircraft model ERWIN, 0. E. [ NASA-CR-I83649-PT-21 p 706 N89-25464 [AIAA PAPER 89-29051 p666 A89-47165 Compressiblity and shock wave interaction effects on FRANSSON, T. H. DUESTERHAUS, 0. A. free shear layers Steady-state and time-dependent aerodynamics in an Free-jet test capability for the aeropropulsion systems [AlAA PAPER 89-24601 p 648 A89-46847 annular turbine cascade operating at high subsonic Mach test facility ERZBERGER. HEINZ numbers [AIAA PAPER 89-25371 p 692 A89-46908 Controller evaluations of the descent advisor automation [AIAA PAPER 89-2941 ] p 651 A89-47185 DUHL, DAVID N. aid FRASER, EUGENE J. Microstructure-property relationships in advanced nickel [NASA-TM-102197] p 659 N89-25981 Service suitability testing of the FIA-18A for use by the base superalloy airfoil castings p 696 A89-45929 EXLEV, J. T. Blue Angels Navy Flight Demonstration Team DUKE, EUGENE L Advantages of ceramic. solid lubncated bearings for p 664 A89-45146 Preliminary development of an intelligent computer small gas turbine engines FRAZIER, F. ALAN assistant for engine monitoring [AIAA PAPER 89.24721 p 703 A89-46858 F-18 Hornet - LEX Fence flight test results [AlAA PAPER 89.25391 p 674 A89-46910 EUAT, A. p 687 A89-45155 DUNPHV, JAMES R. Steady-state and bmedependent aerodynamics in an FRELIN, M. Opltcal fiber sensor development for turbine annular turbine cascade operating at high subsonic Mach Prediction of turbomachinery performance. Application appllcations numbers to a centrifugal pump, a centrifugal compressor, and a [AIAA PAPER 89-29141 p 704 A89-47168 [AIAA PAPER 89 2941 I p 651 A89-47185 radial inflow turbine p 640 A89-44638
8-4 PERSONAL AUTHOR INDEX HARTMANN, DIRK F.
FRIBERG, M. GEORGE, A. GU, ZHONGWAN Predictionof turbomachinery performance - Application Vortices and pressure waves at plates, cylinders and Optimizationdesign for suppressing 'ground resonance' to a centrifugal pump, a centrifugal compressor, and a wind profiles of helicopters p 664 A89-46278 radial inflow turbine p 640 A89-44638 [ISL-R-102188] p 656 N89-25966 GUENE'ITE, 0. R. FRIEDMAN, PAUL J. GESSNER, F. 8. Turbine aerodynamic performance measurements in The System 500, a real-time flight test telemetry Further experiments on supersonic turbulent flow short duration facilities system p 660 A89-45134 development in a square duct p 652 A89-47357 [AIAA PAPER 89-26901 p 693 A89-47020 FRIEDMANN. PERETZ P. OHIA, K. N. GUIDEZ, J. Structural optimization of rotor blades with straight and Simulation of unsteady flow past sharp shoulders on Study of flow and heat transfer in rotating cavities swept tips subject to aeroelastic constraints semi-infinite bodies p 644 A89-45415 [ONERA. TP NO. 1989-331 p 698 A89-45188 OHIA, U. p 667 N89-25152 GUNDY-BURLET, KAREN L. Simulation of unsteady flow past sharp shoulders on FROES, F. H. Twodimensional computations of multi-stage semi-infinite bodies p 644 A89-45415 Space age metals technology; Proceedings of the compressor flows using a zonal approach GIESE, ALEX J. Second International SAMPE Metals and Metals [AIAA PAPER 89-24521 p 647 A89-46840 Processing Conference, Dayton. OH, Aug. 2-4. 1988 Advanced cooling concepts for multi-function nozzle durability GUO, BINGHENG p 696 A89-45927 Experimental investigation on characteristics of single FUJII, KOZO [AIAA PAPER 89.28141 p 682 A89-47100 GILBERT, MICHAEL G. and tandem blade cascades with double-circular arc Accurate simulation of vortical flows profile p 676 A89-45567 p 643 A89-45384 An analytical sensitivity method for use in integrated aerosewoelastic aircraft design GUO, NINGFANG FUJII, SHOlCHl Investigation on unsteady flow field and endwall Performance analysis of scramjet engines [ NASA-TM-1015831 p 690 N89-25239 Integrated structurelcontrol law design by multilevel boundary layer in axial flow compressor with hot-wire p 676 A89-46600 anemometer p 645 A89-45560 FUJIMORI, ATSUSHI optimization GUO, RONGWEI Gust generation in a wind-tunnel and estimation of the [ NASA-TM-1016231 p 712 N89-26623 Flow characteristics in an S-shaped rectangular-round model p 692 A89-46696 GILES, GARY L FUKSA. RADEK Effects of nonlinear aerodynamics and static diffuser at high incidence p 646 A89-46260 Low-temperature performance of a power-pack for a aeroelasticity on mission performance calculations for a GUTMARK, E. 2-watt ELT p 709 A89-44016 fighter aircraft p 669 N89-25170 Review of passive shear-flow control research for GILLANT, P. improved subsonic and supersonic combustion Prediction of the stability limit of multistage axial [AIAA PAPER 89.27861 p 703 A89-47083 G compressors p 640 A89-44637 Combustion enhancement in supersonic coaxial flows GOLUB, ROBERT A. [AIAA PAPER 89-27881 p 681 A89-47084 GABEL, R. Noise considerations for tiltrotor Plan. formulate, discuss and correlate a NASTRAN finite [AIAA PAPER 89.23591 p 665 A89-46773 element vibrations model of the Boeing Model 360 GORIN, VADlM V. H helicopter airframe Modeling of controlled flight dynamics using in-flight [ NASA-CR-1817871 p 707 N89-25480 simulators p 688 A89-46546 HAAS, JEFFREY GAINES, MIKE GOUTINES, MARIUS New hypersonic facility capability at NASA Lewis Rafale - Dassault's new dawn p 662 A89-45030 Design of vane tips improving axial compressor Research Center GALLAGHER, DONALD performance p 640 A89-44640 [AIAA PAPER 89-25341 p 692 A89-46905 Analysis of helicopter environmental data: Indianapolis GRAGG, C. D. HABIB, M. A. downtown heliport, Wall Street heliport. Volume 1: Sled testing of US. Air Force escape systems Combustion characteristics of aaseous flames in a oas Summary p 657 A89-45129 turbine combustor [AD-A206708] p 710 N89-26294 GRAHAM, 0. M. [AIAA PAPER 89-28921 p 683 A89-47155 GALLOPS, G. W. An experimental investigation of high liftlhigh rate HAFTKA. RAPHAEL 1. Estimating in-flightengine performance variations using aerodynamics of an unsteady airfoil Integrated aerodynamic-structural design of a Kalman filter concepts [AD-A206964] p 656 N89-25964 forward-swept transport wing p 669 N89-25188 [AIAA PAPER 89.25841 p 679 A89-46940 GRANDHI. RAMANA V. Optimum design of swept-forward high-aspect-ration GANY, A. Optimum structural design with static aeroelastic graphite-epoxy wings p 669 N89-25172 Effects of bypass air on the cornbustion of boron constraints p 669 N89-25171 HAGAR, STEVEN K. particles in a solid fuel ramjet GRASHOF. JOACHIM Transferringjet engine diagnostic and control technology [AIAA PAPER 89-28861 p 683 A89-47151 Stealth technology for reducing aircraft recognition to liquid propellant rocket engines GARDNER, WILLIAM T. p 673 A89-44645 [AIAA PAPER 89-28511 p 682 A89-47125
Gain transfer ~ An algorithm for decentralized GRASSO, F. HAGEN, MARTIN J. hierarchical estimation p 71 1 A89-46150 A validation of a Navier-Stokes2D solver for transonic Performanceand loads data from an outdoor hover test GARG, SANJAY turbine cascade flows of a Lynx tail rotor Turbofan engine control system design using the [AIAA PAPER 89-24511 p 647 A89-46839 [NASA-TM-101057] p 656 N89-25958 LQGILTR methodology GRAY, D. E. HALL, DAVID W. [NASA-CR-1823031 p 685 N89-26004 Ducted ultra-high bypass engine configuration Development of a microcomputer based integrated Integratedflightlpropulsion control system design based definition design system for high altitude long endurance aircraft on a centralized approach [AIAA PAPER 89-24781 p 678 A89-46862 p 668 N89-25159 [ NASA-TM-1021371 p 690 N89-26009 GRAY, ROBERT E. HALL, JAMES C. GARSTANG, J. H. Application of simple wave theory to the radiative Evaluation of a fault tolerant digital engine controller An air photo analysis of an airplane crash boundary conditions required for an internal flow Euler [AIM PAPER 89-25891 p 680 A89-46944 p 657 A89-45337 solver HAMADA. TADAYUKI GASTON, HAROLD R. [AIAA PAPER 89-25771 p 648 A89-46935 T-4 inletlengine compatibility flight test results 6-1B development testing p 687 A89-45165 GREEN, OWEN R. [AIAA PAPER 89-24661 p 665 A89-46853 GATES, F. L A top-down SFP analysis of a complex system HAMED. A. Reduction of 1-P aerodynamic loads on tractor aircraft p 701 A89-46472 Survey and assessment of validation data base for engine installations GREEN, TOMMY L shockwave boundary layer interactions in supersonic [AIAA PAPER 89-29241 p 651 A89-47177 The designer of the 90's: A live demonstration inlets GATZ, HARALD p 705 N89-25164 [AIM PAPER 89-29391 p 651 A89-47183 Prototype of a Slant visual range measuring device GREENBERG, 1. HAMILTON, BRIAN K. [DFVLR-FB-88-42] p 713 N89-25697 Evaluation of parallel injector configurations for Multi-objectivelloading optimization for rotating GAZZANIGA, JOHN A. supersonic combustion composite flexbeams p 668 N89-25157 Low-speed wind tunnel performance of high-speed [AIM PAPER 8925251 p 678 A89-46898 HANSEN, ALFRED 0. counterrotation propellers at angle-of-attack GREENE, HOWARD 8. Damage tolerance analysis and structural integrity in Air [NASA-TM-102292] p 653 N89-25121 Manual CAT llla with a HUD - Requirements and Force aircraft p 661 A89-43884 GEIDEL, H. A. testing p 687 A89-45164 HANSON-PARR, D. M. Ducted ultra-high bypass engine configuration GRELIS, JOAN Combustion enhancement in supersonic coaxial flows definition Satellite low rate voice demonstration test plan [AIAA PAPER 89-27881 p 681 A89-47084 [AIAA PAPER 89-24781 p 678 A89-46862 [ AD-A2067101 p 707 N89-26133 HARDIN, JAY C. High performance gear systems and heat management A new class of random processes with application to GROSS, BEN for advanced ducted systems helicopter noise [AIAA PAPER 89-24821 p 678 A89-46865 Inviscid analysis of a dual mode scramjet inlet [ NASA-CR-1850371 p 713 N89-26679 GELBKE, EBERHARD [AIAA PAPER 89-2681] p 649 A89-47011 HARPER, RICHARD E. Prototype of a slant visual range measuring device GROSSMAN, BERNARD Evaluation of a fault tolerant digital engine controller [DFVLR-FB-88-42] p 713 N89-25697 Integrated aerodynamic-structural design of a [AIAA PAPER 89-25891 p 680 A89-46944 GENGLER, JEANNE E. forward-swept transport wing p 669 N89-25168 HARRISON, J. A. Comwtational fluid dvnamics usina CATlA created GROSSMANN, W. Evaluation of nondestructive test equipment for airfield geomeiry A review of propulsion applications of the pulsed pavements. Phase 1: Calibrationtest results and field data [AIM PAPER 89.23681 p 702 A89-46778 detonation engine concept collection GENTILE, D. P. [AIM PAPER 89-24461 p 677 A89-46837 [AD-A207159] p 694 N89-26020 Composite sizing and ply orientation for stiffness GRUENSPAHN, K. HARTMANN, DIRK F. requirements using a large finite element structural Strongly unsteady vortex fields at elastic helicopter rotor Crack shape identificationas an inverse boundaty value model D 705 N89-25166 blades p 654 N89-25131 problem p 698 A89-44663
8-5 HARTMANN, G. PERSONAL AUTHOR INDEX
HARTMANN, G. HOTOP, H.J. I Simulatlon of inviscid hypersonic real gas flows New Kalman filter algonthms for hybrid navigation. p 644 A89-45414 flightpath computation and inertial geodesy IKAWA, HIDE0 HARTWICH. PA. p 659 A89-43828 Rapid methodology for design and performance Studies of vortex flow aerodynamics using CFD flow HOWARD, F. G. prediction of integrated scramlett hypersonic vehicle visualizations p 641 A89-45260 Wind-tunnel investigations of wings with serrated sharp [AIAA PAPER 89-26821 p 666 A89-47012 HASSAN. AHMED A. trailing edges p 641 A89-45262 IKELER, TIMOTHY J. Transonic airfoil design for helicopter rotor The pursuit of integrated control - A realtime aircraft applications p 667 N89-25154 HOWE, D. C. system demonstration Design of a gear drive for counter-rotating fan rotors [AlAA PAPER 89 27011 p 688 A89 47029 HASSENPFLUG. WOLFGANG [AlAA PAPER 89-28201 p 682 A89-47106 Development and venfication of sottware for flight safety INGRALDI, ANTHONY M. cwcal strapdown systems p 659 A89-43827 HOZUMI, KOlCHl Nacellelpylon interference study on a 1/17th-scale, HASTINGS, DANIEL E. Experimental study on aerodynamic characteristics of twin-engine. low-wing transport model Bow shock matching wth viscous effects on hypersonic hypersonic transport configuration p 640 A89-44972 [AIAA PAPER 89-24801 p665 A89-46864 forebodies HSIA. Y.C. ISHIGURO, TOMIKO [AIAA PAPER 89-26781 p 649 A89-47008 Inviscid analysis of a dual mode SCramjet inlet Inviscid and viscous flow simulations around the HATTORI, ATSUSHI [AIAA PAPER 89-26811 p 649 A89-47011 Onera-M6 by TVD schemes p 644 A89 45425 Gust generation in a wnd-tunnel and estimation of the HSIEH, WEN-HSIN ISHII, H. model p 692 A89-46696 Combustion behavior of boron-based BAMOlNMMO Surge and rotating stall in axial compressors HAYASHIDA. ROBERT D. fuel-nch solid propellants [AIAA PAPER 89-26831 p 649 A89-47013 Influence of rubbing on rotor dynamics. part 2 [AIAA PAPER 89-28841 p 696 A89-47149 ITO, E. Turbine aerodynamic performance measurements in [ NASA-CR-183649-PT-21 p 706 N89-25464 HSU, C.-H. short duration facilities HAYHURST, KELLY J. Studies of vortex flow aerodynamics using CFD flow [AIM PAPER 89.26901 Tesbng of reliability - Analysis tools visualizations p641 A89-45260 p 693 A89-47020 p 702 A89-46503 IZARD, M. HU. C. L Study of flow and heat transfer in rotating cavities HE, JIAJU Numerical investigation of thrust-reversingnozzle using The research of 2-D flexible wall self-correcting wind [ONERA. TP NO 1989-331 p 698 A89-45188 an implicit TYD scheme tunnel p 692 A89-46258 IZUMI, K. H. [AIAA PAPER 89-28991 p 683 A89-47162 HE, LONGDE Descent strategy comparisons for TNAV-equipped The computed results of airfal near the freestream Mach HU, FANG 0. aircraft under airplane-preferred operating conditions number one p 646 A89-46266 The instability and acoustic wave modes of supersonic [ NASA-CR-42481 p 690 N89-26011 mixing layers inside a rectangular channel HENDERSON, JOSEPH 0. p 699 A89-45453 A performance measure for a VHSlC avionic system - Mission dependent availability p 701 A89-46478 HUA, QlNG J HERDMAN, T. L. The ATRtRJ engine performance at constant dynamic JABOUR, JAY State soace models for aeroelastic and viscoelastic pressure and the consideration of transition condition The ATF is on its way p 664 A89-45156 systems p 694 A89-46016 JACKLIN, STEPHEN A. [ AD-A207092 I p 690 N89-26012 HUANG, CHANGYOU Arranging computer architectures to create HERENDEEN. D. L. An integrated design computational method for the wing higher-performancecontrollers p 71 1 A89-46147 Automated structural optimization system (ASTROS): optimization camber and twist at subsonic and supersonic JACKSON, B. User training workshop flow p646 A8946256 Transonic airfoil desion for helicooter rotor [AD-A207090] p 709 N89-26267 HUANG, I-TE applications p 667 "89-25154 HERMANSON, J. C. Combustion behavior of boron-based BAMO/NMMO JACOBS. J. M. J. W. Computational modeling of axisymmetric propeller-hull fuel-rich solid propellants Numerical simulabon of the flow about a wing with interactionin slender low drag bodies [AIAA PAPER 89-28841 p 696 A89-47149 [AIAA PAPER 89-26741 p 649 A89-47004 leading-edgevortex flow p 643 A89-45390 HUANG, XlANJlAN JACQUOTTE, OLIVIER-PIERRE HERRICK. PAUL W. Experimental research on swirling combustion A new variational method for the generation of two- and Fighter aircraft affordability, survivability. and efficiency p 675 A89-45558 three-dimensional adaoted.~ onds in comoutational fluid effectivenessthrough multi-function noales HUBER. F. W. dynamics [AIAA PAPER 89-28151 p 666 A89-47101 Applicationof a multi-stage3-D Euler solver to the design JAGO.[ONERA. JOANN TP NO.C. 1989-31I p 641 A89-45187 HIMANSU, A. of turbines for advanced propulsion systems RNS solutions for three-dimensional steady [AIAA PAPER 89-25781 p 679 A89-46936 Radio Technical Commission for Aeronautics. Annual incompressible flows p643 A8945393 HUDSON, DALE A. Assembly Meebng and Technical Symposium. HIRSCH, CH. CFD in the context of IHPTET The Integrated High Washington, E€. Nov. 28-30. 1988. Proceedings Recent developments in calculation methods for Performance Turbine Technology Program p 660 A89-45875 turbomachines p 697 A89-44635 [NASA-TM-1021321 p 708 N89-26174 JAMESON, ANTONY HO, P. Y. HUFF, DENNIS L. Multigrid calculations for cascades Computational modeling of axisymmetric propeller-hull Numencal analysis of supersonic flow through oscillating p 643 A89-45391 interaction in slender low drag bodies cascade sections by using a deforming grid JENG, DUEN-REN [AIM PAPER 89-26741 p649 A89-47004 [NASA-TM-1020531 p 653 N89-25119 Rarefied gas flow through twodimensional nozzles HODSON, J. B. HUFFER, BRENT [AMPAPER 89-28931 p 650 A89-47156 Re-engining stage two aircraft with the Tay Electromagnetcemissions from a modular Low Voltage JIANG, HAOKANG [AIAA PAPER 89-23611 p 676 A89-46774 Electro-Impulse De-icing system Measurement of three-dimensional flow in HOEIJMAKERS, H. W. M. IWT/FAAICT-88/31I p 707 N89-26120 turbomachinery with a single slanted hot-wire Numerical simulation 01 the flow about a wing with HUFFMAN, MARTIN F. p 700 A89-45561 leading-edge vortex flow p 643 A89-45390 Low cost control system for expendable turbine JIN, RUSHAN HOFFART. TERRY M. engines Effects of fuel chemical properties on exhaust smoke FIA-I8A digital flight control system degraded modes [AIAA PAPER 89-25861 p 680 A89-46942 from gas turbine combustor p 695 A89-45554 flight evaluation p 687 A89-45158 HUGHES, CHRISTOPHER E. JOHNSON, E. H. HOLM, RAYMOND 0. Low-speed wind tunnel performance of high-speed Automated structural optimization system (ASTROS): Distortion test capabilities lor future fighter aircraft counterrotation propellers at angle-of-attack User training workshop engines [NASA-TM-1022921 p 653 N89-25121 [AD-A207090] p 709 N89-26267 [AIAA PAPER 89.29561 p 684 A89-47198 HULL, JOHN JOHNSON, FORRESTER T. HOLMES, B. J. Aeronautical applications of high-temperature Transonic analysis of arbitrary configurations using Wind-tunnel investigations of wings with serrated sharp superconductors locally refined grids p 644 A89-45419 trailing edges p 641 A89-45262 [NASA-TM-102311I p 686 N89-26008 JOHNSON, J. D. HOLT. MAURICE HUNT, JAMES L. Advanced turbofan engine combustion system design Interaction of an oblique shock wave with supersonic Hypersonic airbreathing vehicle conceptual design and test verification p 675 A89-44117 turbulent blunt body flows p 644 A89-45405 (focus on aero-space plane) p 670 N89-25210 JOHNSON, VICKI S. HOUDEPPE, DIETER HURON, E. S. Optimizing conceptual aircraft designs for minimum life Mechanical reaction of wings moving through a vortex Titanium requirementsfor current and future military gas cycle cost p 670 N89-25211 region p 654 N89-25139 turbine engines p 696 A89-45944 JOLLES, F. HONG. M. C. HUSON, WIM J. Steady-state an0 timedependent aerodynamics in an A knowledge-based en route monitor for air traffic Fokker 100. some aspects of the development of the annular turbine cascade operating at high subsonic Mach control p660 A89-45065 longitudinal control system p 687 A89-45161 numbers HOOVER. ALAN D. HUSSAINI, M. Y. [AIAA PAPER 89.29411 p 651 A89-47185 Testing for agility - A progress report InternationalConference on Numerical Methods in Fluid JONES, GREGORY S. p 686 A89-45152 Dynamics, 11th. Williamsburg, VA. June 27-July 1. 1988, A high speed data acquisition system for the analysis HOPKINS, 0. A. Proceedings p 699 A89-45351 of velocity. density, and total temperature fluctuations at Structural tailoring of counter rotation propfans Computational fluid dynamics - A personal view transonic speeds p 685 N89-25165 p 699 A89-45352 [SAE PAPER 8814511 p 691 A89-45248 HOMER. DOUGLAS M. HUSTON, ROBERT J. A new look at wind tunnel flow quality for transonic A pilot's view of intelligent systems Noise considerations for bltrotor flows p 688 A89-45294 [AlAA PAPER 89-23591 p 665 A89-46773 [SAE PAPER 8814521 p 692 A89-45249
B-6 PERSONAL AUTHOR INDEX LENERTZ, J. E.
JONES, PAUL H. KELLER. VERNON W. KRULL. NICHOLAS P. Heliport identification beacon Warm fog dissipation using large volume water sprays Noise issues . An FAA perspective on transport noise [ DOT/FAA/CT-TN89/31] p 661 N89-25984 [NASA-CASE-MFS-25962-1] p 693 N89-25242 [AIM PAPER 89-23621 p 710 A89-46775 JONNAVITHULA,S. KELLEY, n. J. KUCHAR, A. P. Computational and experimental study of stall Relaxation oscillations in aircraft cruise-dash Preliminary assessment of exhaust systems for high propagation in axial compressors optimization Mach (4 to 6) fighter aircraft [AIAA PAPER 89-24541 p 647 A89-46842 [AD-A2067221 p 672 N89-25996 [AIAA PAPER 89-23561 p 676 A89-46770 JORDAN, BASIL M., JR. KERNS, KAROL KUDO, KENJI The designer of the 90's A live demonstration Controller evaluation of Initial Data Link air traffic control Mach 4 testing of scramjet inlet models p 705 N89-25164 services. Volume 2: Mini Study 2 [AIAA PAPER 89-26801 p 649 A89-47010 [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 JORDAN, E. H. KUMAGAI, HlROYUKl KERR, L J. Spanwise lift distributions and wake velocity surveys of X-ray based extensometry Estimatingin-flight engine performance variations using [ NASA-CR-1850581 p 706 N89-25432 a semi-span wing with a discontinuous twist Kalman filter concepts [ NASA-CR-1775321 p 653 N89-25122 JOSLYN. DAVID H. [AIM PAPER 89.25841 p 679 A89-46940 KUMAR, AJAY Three dimensional flow and temperature profile KHALID, S. J. attenuation in an axial flow turbine CFD for hypersonic airbreathing aircraft Role of dynamic simulation in fighter engine design and p 641 A89-45355 [AD-A2067361 p 685 N89-26005 development JOSLYN, H. D. [AIM PAPER 89-24871 p 677 A89-46854 KUO, KENNETH K. Combustion behavior of boron-based BAMO/NMMO Multi-stage compressor airfoil aerodynamics I . Airfoil KHOSLA, P. K. potential flow analysis p 639 A89-44112 RNS solutions for three-dimensional steady fuel-rich solid propellants p 696 A89-47149 JOSTEN, A. incompressible flows p 643 A89-45393 [AIM PAPER 89-28841 Flight-mechanicalinvestigations of the lateral mOtiOn of KIERNAN, LAURENCE KUTLER, P. configurations with winglets p 689 N89-25141 Reporr to Congress: Technical feasibility of joint use Numerical study of unsteady viscous hypersonic blunt body flows with an impinging shock p 643 A89-45394 JOYCE, GAYNOR at Scott AFB. Selfridge AGB and El Tor0 MCAS A flow-field solver using overlying and embedded [ AD-A1945971 p 693 N89-25241 KVATERNIK, RAYMOND 0. meshes together with a novel compact Euler algorithm KINGSLEY, LORI M. Langley rotorcraft structural dynamics program: p 641 A89-45359 Influence of rubbing on rotor dynamics, part 2 Background. status, accomplishments. plans [NASA-CR-183649-PT-2] p 706 N89-25464 [ NASA-TM-101 61 81 p 709 N89-26273 KINNISON, DOUGLAS E. KWOK, F. T. K Preventing depletion of stratospheric ozone: A concentration probe for the study of mixing in Implications on future aircraft emissions supersonic shear flows KABA, KATSUYOSHI [ DE89-0099643 p 710 N89-25530 [AIM PAPER 89-24591 p 703 A89-46846 Mechanisms of Endwall leakage flows and the KISTLER, DORIS S. KWON, 0. associated losses in a linear turbine rotor cascade with An exploratory study of the use otmovement-correlated Expendable supersonic exhaust nozzle concepts blade tipclearance cues in an auditory head-up display p 674 A89-45329 [AIM PAPER 89-29271 p 684 A89-47179 [ NAL-TR-985Tl p 708 N89-26168 KITAPLIOGLU, CAHlT KALFON, DANIEL The acoustics of a small-scale helicopter rotor in Solution of Euler equations by a finite element method hover L [ NASA-TM-1010581 p 655 N89-25954 application to supersonic flows p 639 A89-44319 KLEIN, H. H. LABORIE. JEAN-PIERRE KALLINDERIS, JOHN 0. A numerical investigation of scramjet combustors The systems of the future Airbus A330 and A340 Unsteady and turbulent flow using adaptation methods [AIAA PAPER 89-25611 p 679 A89-46926 aircraft p 662 A89-45044 p 643 A89-45392 KLOPFER, G. H. LAMBERT, RONALD 0. KAMATH, ASHOK Numerical study of unsteady viscous hypersonic blunt Mechanical durability prediction methods On the stress problem of the pebble bed heat exchanger bcdy flows with an impinging shock p 643 A89-45394 p 701 A89-46468 in a hypersonic wind tunnel LAMINIE, JACQUES [ NAL-TM-ST-87051 p 693 N89-25240 KLUG, H. G. Configuration studies for a regional airliner using Computation of hypersonic vortex flows with an Euler KANDA, HlROSHl open-rotor ultra-high-bypass-ratioengines model p 642 A89-45368 The Schlieren Observation System installed in the NAL [AIAA PAPER 89-25801 p 666 A89-46937 LAN, C. EDWARD two-dimensional high-Reynolds number transonic wind KNOWLES, K. Design optimization of axisymmetric bodies in tunnel and attempts to improve it nonuniform transonic flow p 670 N89-25206 Normal impinging jet in crossflow . A parametric [ NAL-TR-9641 p 693 N89-26015 LANG, P. F. investigation KANDA, TAKESHI [AIAA PAPER 89-29571 p 684 A89-47199 Plan, formulate, discuss and correlate a NASTRAN finite A comparison of scramjet engine performances of element vibrations model of the Boeing Model 360 various cycles KO, T. C. helicopter airframe [AIAA PAPER 89-26761 p 680 A89-47006 Isoparametric shear spring element applied to crack [NASA-CR-181787] p 707 NE§-25480 patching and instability p 699 A89-45208 Mach 4 testing of scramjet inlet models LAPIERRE, LEE R. [AIAA PAPER 89-26801 p 649 A89-47010 KOBAYASHI, HlROSHl Diagnostic expert systems for gas turbine engines - Navier-Stokes simulations around a propfan using KANDIL, OSAMA A. Status and prospects higher-order upwind schemes [AIAA PAPER 89-25851 p 680 A89-46941 Unsteady transonic airfoil computation using implicit [AIAA PAPER 89-26991 p 650 A89-47028 Euler scheme on bcdy-fixed grid p 652 A89-47358 LAW, C. HERBERT KANE, JAMES H. KOENIG, REINHARD Two axial compressor designs for a stage matching Treatment of body forces in boundaly element design Contributionsto the improvement of flight safety in wind investigation sensitivity analysis p 705 N89-25187 shear [ABM06951 1 p 685 N89-26006 p658 NE925144 KANMURI, AKIO [DNLR-FB-88-49] LAW, J. A comparison of scramjet engine performances of KOLONAY, R. M. Advantages of ceramic, solid lubricated bearings for various cycles Structural optimization of framed structures using small gas turbine engines [AIM PAPER 89.26761 p680 A89-47006 generalized optimality criteria p 706 N89-25197 [AIM PAPER 89-24721 p 703 A89-46858 KAO, PI-JEN KOMURO, TOMOYUKI LEA, ROBERT N. Integrated aerodynamic-structural design of a Effectiveness of plasma torches for ignition and Applications of fuzzy sets to rule-based expert system forward-swept transport wing p 669 N89-25168 flameholding in scramjet development p 712 N89-26606 KAPLAN, BRUCE A. [AIAA PAPER 89-25641 p 679 A89-46927 LEBOEUF. F. Service suitability testing of the FIA-18A for use by the Mach 4 testing of scramjet inlet models Present state of the theory of secondary flows and Blue Angels Navy Flight Demonstration Team [AIAA PAPER 89-26801 p 649 A8947010 experimental verifications p 698 A89-44636 p 664 A89-45146 KRAUSS, ROLAND H. LEE, C. S. Flow structure and scaling laws in lateral wing-tip KARIYA, TlMMY T. Initial supersonic combustion facility measurements p 652 A89-47352 Nacellelpylon interference study on a 1/17th-scale, [AIAA PAPER 89-24621 p692 A89-46849 blowing LEE, CHARLES W. twin-engine, low-wing transport model KRAWCZAK, JUERGEN [AIAA PAPER 89.24801 p 665 A89-46864 Experiences with a prevalidation methodology for The phased establishment of support maturity for the designing integrated/propulsion control system KASHIWABARA, Y. European Fighter Aircraft (EFA) p 637 A8944644 Surge and rotating stall in axial compressors architectures KRAZINSKI, J. L [AIAA PAPER 89.26831 p 649 A89-47013 [AIAA PAPER 89-27031 p 688 A89-47030 Efficient computational tool for ramjet combustor KASSEL, JOHN M. LEE, WOOSUNG research Light weight gas turbine engine fuel pumping Experimental localized radar cross sections of aircraft [AIAA PAPER 88-00601 p 674 A89-44108 technology p 673 A89-45105 [AIAA PAPER 89-25871 p 703 A89-46943 KREJSA, EUGENE A. LEFEBVRE. A. n. KATZ, JOSEPH Supersonic jet noise and the high speed cMl bansport Effects of fuel chemical properties on exhaust smoke [AIAA PAPER 89-23581 p 712 A89-46772 Aerodynamics of high-lift, low-aspect-ratio unswept from gas turbine combustor p 695 A89-45554 wings p 652 A89-47372 KREKELER. 0. LEFKOWITZ, C. P. KEITH, THE0 G., JR. Advanced thrust vectoring nonles for supercruise fighter Robust computer-aided synthesis and optimization of Rarefied gas flow through two-dimensional nozzles aircraft linear multivariable control systems with varying plant [AIAA PAPER 89-28931 p 650 A89-47156 [AIAA PAPER 89.28161 p 682 A89-47102 dynamics via AUTOCON p 711 N89-25179 KELLER, HERBERT KROO, ILAN LENERTZ, J. E. Technology of structures maintains high standards Aircraft design optimization with multidisciplinary Advanced turbofan engine combustion system design p 637 A89-44642 performance criteria p 671 N89-25212 and test verification p 675 A89-44117 8-7 LEONDES, C. T. PERSONAL AUTHOR INDEX
LEONDES, C. T. LIVINGS, JEFFREY MARVNIAK, JERZV Control and dynamic systems Volume 29 Advances Functional requirements of the Communications Numerical modelling of flight dynamics and flight test in algonthms and computational techniques in dynamic Interface Dnver (CID) data identificationof a jet trainer airplane systems control Part 2 p 711 A89-46144 [DOT/FAAICT TN87/41-REV] p 707 N89-26121 p 663 A89-45139 LEONE, ANDREW Communications Interface Driver (CID) system user’s MASON, PHILIP Communicatms Interface Dnver (CID) system user’s manual Applications of integrated designlanalysis systems in manual [ WT/FAA/CT-TN89/361 p 707 N89-26123 aerospace structural design p 666 N89-25147 [ DOT/FAA/CT-TN89/361 p 707 N89-26123 LIVNE, E. MASUVA, GORO LERNER, EDWlN An integrated approach to the optimum design of actively Effectiveness of plasma torches for ignition and Applications of integrated dewgn/analysis systems in controlled composite wings p 670 N89-25194 flameholding in scramjet aerospace structural design p 666 N89-25147 LOKOS, WILLIAM A. [AIAA PAPER 89.25641 p 679 A89-46927 LEW, THOMAS M. Current flight test experience related to structural A comparison of scramlet engine performances of Long duratlon balloon technology survey phase 1 divergence of forward-swept wings p 663 A89-45141 various cycles [AD-A206975] p 656 N89-25965 [AIAA PAPER 89-26761 p 680 A89-47006 LOTTATI, I. LEWERENZ, WILLIAM T. Mach 4 testing of scramjet inlet models A review of propulsion applications of the pulsed UHB demonstrator flight test program - Phase 2 [AIM PAPER 89.26801 p 649 A89-47010 [AIAA PAPER 89-25821 p 679 A89-46939 detonation engine concept [AIAA PAPER 89-24461 p 677 A89-46837 MATSUI, TATSUVA LEWICKI. D. G. Behavior of vortex street in the wake behind a circular LOVE, MIKE Transmission overhaul and replacement predictions H. cylinder under controlled excitation p 646 A89-46694 Aerolastic tailonng and integrated wing design using Weibull and renewal theory p 668 N89-25167 MATSUO, VUlCHl [AlAA PAPER 89.29191 p 704 A89-47173 Navier-Stokes simulations around a propfan using Recent expenences using finite-element-based LEWIS, MARK J. higher-order upwind schemes structural optimization p 705 N89-25177 Bow shock matching with viscous effects on hypersonic [AIAA PAPER 89.26991 p 650 A89-47028 LOW, H. C. forebcdies MATTE, NICOLAS MATEESCO Evaluation of novel gniters in a turbulent bomb facility [AIM PAPER 89-26781 p 649 A89-47008 Annals of air and space law. Volume 13 and a turbo-annular gas turbine combustor LI, HUAXING p 714 A89-45175 [AIAA PAPER 89-29441 p684 A8947188 The research of 2-D flexible wall self-correcting wind MATTERN, DUANE L tunnel p 692 A89-46258 LUEST, REIMAR Integrated flight/propulsioncontrol system design based The ’nerve center’ of ESA Tasks and procedures of LI, VAPING - on a centralized approach the ESOC in Darmstadt p 694 A89-43869 Investigation on unsteady flow field and andwall [ NASA-TM-102137] p 690 N89-26009 boundary layer in axial flow compressor mth hot-wire LUIDENS, ROGER W. MATTES, L A. Aeronautical applications of high-temperature anemometer p 645 A89-45560 An experimental technique for the measurement of mass superconductors LI. VUCHUN flow of scramjet inlets tested in hypersonic pulse [NASA-TM-102311I p 686 N89 26008 Measurement of three-dimensional flow in facilities tuhmachinery with a single slanted hot-wire LUO, SHIJUN [AIAA PAPER 89-2331 I p 692 A89-46755 p 700 A89-45561 Design and analysis of arfoils in transonic viscous MATTES, R. E. flow p 646 A89-46262 LI. VUPU The evolution - IFPC to VMS LUPPOLD, An integrateddesign computational method for the wing R. H. [AIAA PAPER 89-27051 p 688 A89-47032 Estimating in-flight engine performance variations using optimization camber and twist at subsonic and supersonic Kalman filter concepts MAmNGLV, JACK D. flow p 646 A89-46256 [AIAA PAPER 89-25841 p 679 A89-46940 Easy method of matching fighter engine to airframe for LI, ZHENHAO LVU. MICHAEL R use in aircraft engine design courses The induced power based on leading edge suction for In search of effecbve dNersity - A six-language study [AlAA PAPER 89-22601 p 665 A89-46705 a helicopter in hovenng p 646 A89-46267 of fault-tolerantflight control software MAVLOR, ELLIOTT L LIANG, S. M. p 710 A89-44423 Airplane tests of enhanced emergency smoke venting Numerical investgatmn 01 thrust-reversng nozzle using [ D218N301I p 658 N69-25976 an implicit NDscheme MAYS, R. B. [AIAA PAPER 89-28991 p 683 A89-47162 M Low angle injection into a supersonic flow LIDDLE, A. 0. [AIAA PAPER 89-2461 1 p 648 A89-46848 MACE, J. Automation in transport aircraft ~ Current and future MAVWALD, P. V. trends Advanced thrust vectonng nozzles for supercruise fighter Free-jet test capability for the aeropropulsion systems [SAE PAPER 8814681 p 657 A89-47334 aircraft test facility LIM, JOON W. [AIAA PAPER 89-28161 p 682 A89-47102 [AIAA PAPER 89.25371 p 692 A89-46908 MACLEAN. M. Efficient sensitivity analysis and optimization of a MCCALLUM. B. N. helicopter rotor p 668 N89-25155 Advanced thNSt vectoring nozzles for supercruise fighter F-16 inlet stability investigation aircraft LIN. CHIN E. [AIAA PAPER 89-24651 p 665 A89-46852 [AlAA PAPER 89-28161 p 682 A89-47102 A knowledge-based en route monitor for air traffic MCCONNELL, J. C. control p 660 A89-45065 MADDUX, GENE E. Optical research needed to support the testing of Recent experiences using finite-element-based LIN. ai hypersonic vehicle structures p 697 A89-43840 structural optimization p 705 N89-25177 Flow characteristics in an S-shaped rectangular-round MAHAPATRA, P. R. MCDANIEL, J. C. diffuser at high incidence p 646 A89-46260 Evaluating ILS and MLS sites without flight tests Quantitative characterization of a nonreacting. LIN, alXUN p 660 A89-43894 supersonic combustor flowfield using unified, laser-induced Investigation on unsteady flow field and endwall MAHIEDDINE, M. iodine fluorescence boundary layer in axial flow compressor with hot-wire Prediction of turbomachinery performance Application (AlAA PAPER 89.25651 p 703 A89-46928 anemometer p645 A8945560 to a centnfugal pump a centnfugal compressor and a MCDANIEL, JAMES C. LINDERT, HANSWERNER radial inflow turbine p 640 A89-44638 Initial supersonic combustion facility measurements Mechanical reaction of wings moving through a vortex MAIER, FRITZ F. [AIM PAPER 89-24621 p 692 A89-46849 region p 654 N89-25139 SPAREL - A model for reliabilrty and sparing in the world MCDONALD, H. LIO. DEHUA of redundancies p 702 A89-46493 Solution of the incompressible Navier-Stokesequations An integrated design computational method for the wing MAILAENDER, MARTIN using artificial compressibility methods opbmization camber and twist at subsonic and supersonic Materials and structures for 2MH) and beyond An p 641 A89-45366 flow p 646 A89-46256 attempted forecast MCWNELL, V. G. LIOU, MENGSING [ DFVLR-MITT-89-02] p 706 N89-25358 Development and application of a surrogate distillate A Newton/upwindmethod and numencal study of shock MANTAV, WAYNE R. fuel p 695 A89-44103 wavelboundary layer interactions p 645 A89-45468 An initiattve in multidisciplinary optimization of MCELROV, COLLET E. LISIUS, ANDREAS rotorcraft p 667 N89-25151 FAA handling qualities assessment - Methodology in Prototype of a slant visual range measunng devlce MARCOLINI, MICHAEL A. transition p 687 A89-45159 Airfoil self-noise and prediction [DFVLA-FB-88-42] p 71 3 N89-25697 MCKAIN, T. F. [NASA-RP-l218] p 71 3 N89-25673 LIST, GEORGE Expendable supersonic exhaust nozzle concepts MARCONI, F. Economic analyss of a beam-powered, personalized [AlAA PAPER 89-29271 p 684 A89-47179 Asymmetnc separated flows abut sharp cones in a global aerospace transportation system MCKIBBIN, A. H. [AIM PAPER 89-24431 p 71 4 A89-46835 supersonic stream p 643 A89-45402 MARDER, J. M. Design of a gear drive for counter-rotating fan rotors LIU. C. H. A review of beryllides for very high temperature [AlAA PAPER 89-28201 p 682 A89-47106 Studies 01 vortex flow aerodynamics using CFD flow service p 696 A89 45948 MCKINZIE, D. J. visualizations p 641 A89-45260 MAREK. HENRY R. A natural low-frequency oscillation of the flow over an LIU, FENG Controller evaluation of lnibal Data Link air traffic control airfoil near stalling conditions p 645 A89-45437 Multignd calculations for cascades services Volume 2 Mini Study 2 MCNULTV. MICHAEL J. p 643 A89-45391 [ DOT/FAA/CT-89/14 VOL-21 p 661 N89-25986 Flaplag stability data for a small-scale isolated hingeless LIU, PING MARTIN, JOHN G. rotor in forward flight Design and analysis of airfoils in transonic viscous Hypersonic airbreathing vehicle conceptual design [ NASA-TM-102189] p 706 N89-25479 flow p 646 A89-46262 (focus on aero-space plane) p 670 N89-25210 MCRUER. DUANE T. LIU. QlANZHl MARTRE. HENRl Advanced piloted aircraft flight control system design Effects of axial velocity density ratio on cascade Aerospatiale’s short-term and intermediate-term place methodology. Volume 1: Knowledge base performances p 645 A89-45565 in the international scene p 637 A89-45032 [NASA-CR-181726-VOL-l] p 690 N89-26013 PERSONAL AUTHOR INDEX OHWAKI, KATSURA
Advanced piloted aircraft flight control system design MORROW, JOHN G. NEILL, D. J. methodology. Volume 2: The FCX flight control design Analysis of helicopter environmental data: Indianapolis ASTROS: A multidisciDlinarv.. automated structural expert system downtown heliport, Wall Street heliport. Volume 1: design tool p 705 N89-25174 [ NASA-CR-I81 726-VOL-21 p 691 N89-26014 Summary Automated structural optimization system (ASTROS): MECKLIN, RON [ AD-A2067081 p 710 N89-26294 User training workshop A look at the Model 360 development MOSZEE, RAYMOND H. [AD-A207090] p 709 N89-26267 p 664 A89-45163 A propulsion development strategy for the National NEJAD, A. S. MEWED, ORAL Aero-Space Plane Efficient computational tool for ramjet combustor Aeroelastic analysis of prop fan blades with a [AIAA PAPER 89-2751 ] p 681 A89-47061 research semiempirical dynamic stall model MOUILLE, RENE [AIAA PAPER 88-00601 p 674 A89-44108 [AIAA PAPER 89.26951 p 703 A89-47025 Helicopter blades p 640 A89-45045 NELSON, PAUL D. MEHTA, R. D. MOULTON, J. L. Compressor exit temperature analysis Interaction of an oscillating vortex with a turbulent Semi-constant volume pulse cornbustion for gas turbine [AIM PAPER 89-29471 p 684 A89-47191 boundary layer p 645 A89-45906 engine starting NEWMAN, DON [AIAA PAPER 89-24491 p 677 A89-46838 MELTZ, GERALD The ATF is on its way p 664 A89-45156 Optical fiber sensor development for turbine MOXON, JULIAN Civil supersonics - Propulsion is the key NG, JAMES applications Electromagnetic emissions from a modular Low Voltage [AIAA PAPER 89-29141 p 704 A89-47168 p 675 A89-45031 MUELLER, R. Electro-Impulse De-icing system MELVIN, ROBIN 0. [ DOT/FAA/CT-88/31] p 707 N89-26120 Transonic analysis of arbitrary configurations using Structural loading and noise disturbance of helicopters NG, W. F. locally refined grids p 644 A89-45419 p 713 N89-25140 A concentration probe for the study of mixing in MENEES, GENE P. MUELLER, THOMAS J. supersonic shear flows Numerical simulations of oblique detonations in Analysis of low Reynolds number separation bubbles [AIAA PAPER 89-24591 p 703 A89-46846 supersonic combustion chambers p 674 A89-44115 using semiempirical methods p 652 A89-47351 MENG, GUANG MUENKEL, CHRISTOPH NGUYEN, HUNG LEE Study of nonlinear Duffing characteristics of flexible rotor Prototype of a slant visual range measuring device Investigationof low NOx staged combustor concept in with SFDB p 700 A89-45568 [ DFVLR-FB-88-42] p 713 N89-25697 high-speed civil transport engines p 684 A89-47186 MESSOLORAS, S. MUKHOPADHYAY, VIVEK [AIAA PAPER 89-29421 A study of AI-Li alloys using small angle neutron Flutter suppression control law synthesis for the Active NI, R. R. scattering p 695 A89-44577 Flexible Wing model Application of a multi-stage 3-D Euler solver lothe design MEYER, 6. E. [ NASA-TM-1015841 p 690 N89-26010 of turbines for advanced propulsion systems A static investigation of several STOVL exhaust system MUKHOPADHYAY, VIVEKANANDA [AIAA PAPER 89-25781 p 679 A89-46936 . concepts Digital robust control law synthesis using constrained NI, WENYAN [AIAA PAPER 89.29281 p 684 A89-47180 optimization p 689 N89-25193 Transonic cascade flow solved by the combined MIAMEE, A. G. MULAC, RICHARD A. shock-capturing and shock-fitting method A new class of random processes with application lo Average-passage simulation of counter-rotatingpropfan p 639 A89-44114 helicopter noise propulsion systems as applied to cruise missiles NIEDZWIECKI, RICHARD W. [ NASA-CR-1850371 p 71 3 N89-26679 [AIAA PAPER 89-29431 p 651 A89-47187 Investigation of low NOx staged combustor concept in MICHARD, P. J. MULHOLLAND, ROBERT G. high-speed civil transport engines Study of flow and heat transfer in rotating cavities Evaluation of a projectionalgorithm for the stereographic [AIAA PAPER 89-29421 p 684 A89-47186 [ONERA. TP NO. 1989-331 p 698 A89-45188 representation of aircraft in an air traffic control system NINNEMANN, T. A. MICHAUX, B. [ DOT/FAA/CT-TN89/20] p 661 N89-25985 A concentration probe for the study of mixing in Inverse method for the determinationof transonic blade MURAKAMI, AKIRA supersonic shear flows profiles of turbomachineries p 643 A89-45404 Experimental study on aerodynamic characteristics of [AIAA PAPER 89-24591 p 703 A89-46846 MIHALOEW, JAMES R. hypersonic transport configuration p 640 A89-44972 NISSIM, E. Intearated fliaht/DroDuIsion control study for STOVL MURAKAMI, ATSUO Control surface spanwise placement in active flutter applications Mach 4 testing of scramjet inlet models suppression systems p 689 N89-25195 [AIAA PAPER 89.29081 p 688 A89-47166 [AIAA PAPER 89-26801 p 649 A89-47010 NOLL, THOMAS E. MILLER. J. A. MUSZYNSKA, AGNES Flutter suppression control law synthesis lor the Active Titanium requirements for current and future military gas Influence of rubbing on rotor dynamics, part 2 Flexible Wing model turbine engines p 696 A89-45944 [NASA-TM-101584] p 690 N89-26010 [ NASA-CR-183649-PT-21 p 706 N89-25464 MIWA, HlTOSHl NOMURA, SHlGEAKl The Schlieren ObseNation System installed in the NAL MYERS, THOMAS T. Experimental study on aerodynamic characteristics of Advanced piloted aircrafl flight control system design two-dimensional high-Reynolds number transonic wind hypersonic transport configuration p 640 A89-44972 methodology. Volume 1: Knowledge base tunnel and attempts to improve it NORDIN, ARNE [ NASA-CR-181726-VOL-1I p 690 N89-26013 [ NAL-TR-9641 p 693 N89-26015 SPAREL - A model for reliability and sparing in the world MIYATA, HlDEAKl Advanced piloted aircrafl flight control system design of redundancies p 702 A89-46493 Numerical study of the 30 separating flow about methodology. Volume 2: The FCX flight control design NORTHAM, G. BURTON obstacles with sharp corners p 641 A89-45363 expert system Evaluation of parallel injector conligurations for MO, LlXlAO [ NASA-CR-181726-VOL-21 p 691 N89-26014 supersonic combustion An experimental research on mixture pressure loss in MYRABO, LElK [AIAA PAPER 89.25251 p 678 A89-46898 combustor p 675 A89-45556 Economic analysis of a beam-powered, personalized MOGHADAM, A. global aerospace transportation system The mixing of three-dimensional turbulent wakes in [AIAA PAPER 89-24431 p 714 A89-46835 0 boundary layers p 639 A89-43722 MOITRA, ANUTOSH OBRIEN, W. F. HOMAR: A computer code for generating homotopic N Improved plasma torch for ignition and flame holding grids using algebraic relations: User's manual in supersonic combustion [NASA-CR-4243] p 708 N89-26176 NAKAMURA, MASAYOSHI [AIAA PAPER 89-29451 p 704 A89-47189 MOKRIS, DANIEL J. A numerical solution of transonic flow using O'BRIEN, WALTER F. EC-lBB/Boeing 707 Smoke Venting flight test discontinuous shock wave relationship Model predictions for improved recoverability of a [AD-A206601] p 659 N89-25979 [NAL-TR-997] p 655 N89-25950 multistage axial flow compressor p 650 A89-47017 MOLDER, S. NALLASAMY, M. [AIAA PAPER 89-26871 An experimental technique for the measurementof mass Large scale advanced propeller blade pressure Dynamic turbine blade temperature measurements p 680 A89-47019 flow of scramjet inlets tested in hypersonic pulse distributions .Prediction and data [AIAA PAPER 89-26891 facilities [AIM PAPER 89-26961 p 650 A89-47026 OGAWA, SATORU [AIAA PAPER 89-23311 p 692 A89-46755 Inviscid and viscous flow simulations around the NATAN, B. Onera46 by NOschemes p 644 A89-45425 MONGIA, H. C. Effects of bypass air on the combustion of boron OGLESBY, TIMOTHY L. A model for airblast atomization particles in a solid fuel ramjet The designer of the 90s A live demonstration [AIAA PAPER 89-2321] p 702 A89-46748 [AIAA PAPER 89-28861 p 683 A89-47151 A 3-D analysis of gas turbine combustors p 705 N89-25164 NAUGHTON, J. W. [AIAA PAPER 89-28881 p 683 A89-47153 OGUNI, YASUO An experimental study of the effect of streamwise MONJI, TAKAFUMI The Schlieren Observation System installed in the NAL vorticity on supersonic mixing enhancement Gust generation in a wind-tunnel and estimation of the two-dimensional high-Reynolds number transonic wind [AIAA PAPER 89-24561 p 648 A89-46843 model p 692 A89-46696 tunnel and attempts to improve it MOON, YOUNG J. NAWROCKI, F. [ NAL-TR-9641 p 693 N89-26015 Interaction of an oblique shock wave with supersonic Ensuring surge-free engine operation on today's OHMOMO, MITSUHARU turbulent blunt body flows p 644 A89-45405 turbofan powered business jets T-4 inlet/engine compatibility flight lest results MORGAN, K. [AIAA PAPER 89.24871 p 678 A89-46868 [AIAA PAPER 89-24661 p 665 A89-46853 Adaptive numerical solutions of the Euler equations in NAWROCKI, H. OHTA. HlROBUMl 3D using finite elements p 644 A89-45413 Design and testing of a common engine and nacelle Gust generation in a wind-tunnel and estimation of the MORISSET, JACQUES for the Fokker 100 and Gulfstream GIV airplanes model p 692 A89-46696 Airbus - The new families p 662 A89-45043 [AIAA PAPER 89.24861 p 666 A89-46867 OHWAKI, KATSURA MORRIS, STEPHEN NEELY, WILLIAM R. Effectiveness of plasma torches for ignition and Aircraft design optimization with multidisciplinary F-15 STOL/Maneuvering Technology Demonstrator - flameholdingin scramjet performance criteria p 671 N89-25212 Initial flight test results p 687 A89-45157 [AIAA PAPER 89-25641 p 679 A89-46927 B-9 OKIISHI, 1. H. PERSONAL AUTHOR INDEX
OKIISHI, T. H. PERRY, BOYD, 111 R Rotabng stall performance and recoverability of a Time-correlatedgust loads using Matched-Filter Theory high-speed 10-stage axial-flow compressor and Random-Process Theory: A new way of looking at RADOVCICH, N. A. [AIAA PAPER 89-26841 p 650 A89-47014 things Composite sizing and ply orientation for stiffness OKUDE, MUNESHIGE [ NASA-TM-1015731 p 671 N89-25232 requirements using a large finite element structural Eehawor of vortex street in the wake behind a circular Flutter suppression control law synthesis for the Active model p 705 N89-25166 cylinder under controlled excitation p 646 A89-46694 Flexible Wing model RAGSDELL, K. M. OMPRAKASH, V. [NASA-TM-101584J p690 N89-26010 Mulblevel decomposltion of complete vehicle Dynamic stress analysis of rotating tubamachinery configuration in a parallel computing environment PETERS, DAVID A. bladeddisk systems p 675 A89-44362 p 670 N89-25205 ORTWERTH, J. PAUL Optimization of rotor blades for combined structural. RAI, MAN MOHAN performance, and aeroelastic characteristics lnviscd analyws of a dual mode scramlet inlet Two-dimensronal computations of multi-stage p 667 N89-25153 [AIAA PAPER 89-2681I p 649 A89-47011 compressor flows using a zonal approach OZKUL, MARTIN PETERS, JAMES R. [AIM PAPER 89-24521 p 647 A89-46840 Three dimensronal finlte element stress predictions of Multi-objectwe/loading optimization for rotating RAJAGOPALAN, R. GANESH spur gears compared to gear fabgue rig measurements composite flexbeams p 668 N89-25157 Performance and flow field of a ducted propeller [AIAA PAPER 89-29181 p 704 A89-47172 PFITZNER. M. [AIAA PAPER 89-26731 p 649 A89-47003 Simulation of inviscd hypersonic real gas flows RAMAMURTI, R. p 644 A89-45414 Simulation of unsteady flow past sharp shoulders on P PIAS. R. semi-infinite bodies p 644 A89-45415 Technology development required by propfan power RAMAMURTI, V. PAGE, JAKE reduction gearboxes Dynamic stress analysis of rotating turbo-machinery Fast brake p 657 A89-46593 [AIAA PAPER 89.28181 p 703 A89-47104 bladed-disk systems p 675 A89-44362 PALUMBO, DANIEL L PIKE, 8. C. RAMSEY, JOHN K. Expenences with a prevalidation methodology for A study of AI-Li alloys using small angle neutron Influence of thickness and camber on the aercelastic dewgning integrated/propulsron control system scattering p 695 A89-44577 stability of supersonic throughflow fans: An engineering architectures approach [AIAA PAPER 89-27031 p 688 A89-47030 PINET, JEAN Economic aspects of simulation in air transportation [ NASA-TM-1019491 p 656 N89-25957 PANARAS, ARGYRIS G. p 691 A8945047 RANAUDO, RICHARD The spabally non-uniformconvergence of the numencal In-flight measurement of propeller noise on the fuselage PLA, FREDERIC G. solutions of flows p 699 A89-45535 of an airplane In-flight measurement of propeller noise on the fuselage PANDEY, AJAY K. [NASA-TM-102285) p 713 N89-25675 Fmite element flow-thermal structural analysis of of an airplane [ NASA-TM-1022851 p 713 N89-25675 RAND, JAMES L aerodynamically heated leading edges Long duration balloon technology survey, phase 1 p 655 N89-25198 POISSONQUINTON, PH. [AD-A206975] p 656 N89-25965 Aeronautical research in the European future PAPAMOSCHOU, DlMlTRl RASMUSSEN, M. L p 638 A89-45037 Diffuser performance of two-stream supersonic mnd Integration of scramjets with waverider configurations tunnels p 652 A8947373 POLEN, DAVID M. [AIAA PAPER 89-26751 p 695 A89-47005 PARK, JEONG-JOO Integrated aerodynamic-structural design of a RAY, RONALD J. Inviscid transonic flow over a wavy wall decaying forward-swept transport wing p 669 N89-25168 Preliminary development of an intelligent computer downstream p 639 A89-44390 POLL, D. 1. A. assistant for engine monitonng PARR, T. P. An inibal assessment of the impact of boundary layer [AIAA PAPER 89-25391 p 674 A89-46910 Combuston enhancement in supersonic coaxial flows control on SST RE, R. J. [AIAA PAPER 89-27881 p 681 A89-47084 [AERO-REPT-8802I p 656 N89-25969 A static investigation of several STOVL exhaust system PATERSON, R. W. An introduction to the problem of aerodynamic heating concepts Supersonic nozzle mixer ejector [AERO-REPT-8901I p 656 N89-25970 [AIAA PAPER 89-29281 p 684 A89-47180 [AIAA PAPER 89.29251 p 683 A89-47178 POPE, D. STUART RE, RICHARD J. PAUL, B. K. Airfoil self-noise and prediction Nacelle/pylon interference study on a 1117th-scale. Recent experiences using finite-element-based [ NASA-RP-12181 p 71 3 N89-25673 twin-engine, low-wing transport model structural optimization p 705 N89-25177 POSTLETHWAITE,ALAN [AIAA PAPER 89-24801 p 665 A89-46864 PAUL, STEPHEN A. Tupolev's new twin p 662 A89-43887 READER, KENNETH R. Advanced cooling concepts fcf multi-function noale llyushin goes the distance p 662 A89-43888 Tipjet VTOL UAV (Vertical Takeoff and durability Ilyushin's new workhorse p 662 A89-44375 LandinglUnmanned Aerial Vehicle) summary. Volume 1: [AIM PAPER 89-28141 p 682 A89-47100 POTI, NORMAN A 1200 pound tipjet VTOL unmanned aenal vehicle. Part PEACOCK, N. J. Model predictions of fan response to inlet temperature 1:Co nceptual design study of a 1200-poundvehicle Advanced propulsion systems for large subsonic transients and spatial temperature distortion [AD-A206738] p 672 N89-25997 transports [AlAA PAPER 89-26861 p 650 A89-47016 REDDY, D. R. [AIAA PAPER 89-24771 p 677 A89-46861 POTI, NORMAN D. Mach 5 inlet CFD and experimental results The Rolls Royce Allison RE580 turbofan - Matching the Compressor exit temperature analysis [AIAA PAPER 89-23551 p 647 A89-46769 market requirement for regional transport [AIAA PAPER 89-29471 p 684 A89-47191 REDDY. T. S. R. [AIM PAPER 89-24881 p 678 A89-46869 POTOTZKY. ANTHONY S. Aercelastic analysis of prop fan blades with a PEASE, D. M. Time-correlated gust loads using Matched-FilterTheory semiempirical dynamic stall model X-ray based extensometry and Random-Process Theory: A new way of looking at [AIAA PAPER 89-26951 p 703 A89-47025 [NASA-CR-l8W58] p706 N89-25432 things Numencal analysis of supersonic flow through oscillating PEIN, R. [NASA-TM-101573] p 671 N89-25232 cascade sections by using a deforming grid The influence of swirl and fuel composition of POULOSE, M. M. [ NASA-TM-1020531 p 653 N89-25119 boroncontainingfuels on combustion in a solid fuel ramjet Evaluating ILS and MLS srtes without flight tests REED, D. A. combustion chamber p660 A89-43894 Plan, formulate. discuss and correlate a NASTRAN finite [AIAA PAPER 89-28851 p683 A89-47150 PRES& W. M.. JR. element vibrations model of the Eoeing Model 360 PEIRO. J. Supersonic nozzle mixer ejector helicopter airframe Adaptwe nurnencal solutons of the Euler equatIOnS m [AIM PAPER 89-29251 p683 A8947178 [NASA-CR-l81787] p 707 N89-25480 3D using finite elements p 644 A89-45413 PUJARA. P. K. REED. WILMER H., 111 PENDERGRAFT, ODlS C., JR. Robust computer-aided synthesis and opbmization of A new flight flutter excitation system Nacellelpylon interference study on a 1/17th-scale, linear multivariable control systems with varying plant p 663 A89-45140 twin-engine, low-wing transport model dynamics via AUTOCON p 71 1 N89-25179 REES, M. G. [AIAA PAPER 89-24801 p665 A89-46864 PURTELL, RUSSELL A. 'Flight testing' a multi-megawatt wind turbine PERACCHIO, A. A. The pursuit of integrated control - A realtime aircraft p 709 A89-45131 The challenge of reducing supersonic Clvil transport system demonstration REINATH, MICHAEL S. propulsion nase [AIM PAPER 89-27011 p 686 A89-47029 A long-range laser velocimeter for the National [AIM PAPER 89-23631 p 677 A89-46776 PUTNAM. TERRILL W. Full-scale Aerodynamics Complex: New developments PERAIRE, J. Integrated controls pay-off and expenmental application Adaptwe numencal solubons of the Euler equations in [AIAA PAPER 89-27041 p 688 A89-47031 [ NASA-TM-101081] p 708 N89-26207 3D uwng finite elements p 644 A89-45413 REMMERSWAAL,L P. PERETZ. ARIE Some aspects of interference on Loran-C Combustion behavior of boron-based BAMO/NMMO Q p 660 A89-45221 fuel-nch sold propellants REVELLIN-FALCOZ,BRUNO [AIM PAPER 89-28841 p 696 A89-47149 QUACKENBUSH. T. R. The ACEIRafale p €62 A89-45041 PERIAUX, J. Feasibility of predictmg performance degradation of RICCIONI, EVEREST E. Low-storageimplicit upmnd-FEM Schemes for the Euler airfoils in heavy rain A supersonic cruise fighter design equamns p 642 A89-45375 [ NASA-CR-1818421 p 657 N89-25973 p664 A89-45167 PERRUCHINI, J. QUI". RONALD E. RIGGINS, DAVID W. Study of flow and heat transfer in rotabng cawties Aircraft engine Outer duct mounting dence Mixing enhancement in a supersonic combustor [ONERA. TP NO 1989-331 p 698 A89-45188 [AD-W13988] p 672 N89-25991 [AIAA PAPER 89-27941 p 681 A89-47088
B-10 PERSONAL AUTHOR INDEX SHUART, MARK J.
RINK. LINDA M. SAHM, KARL FRIEDRICH SCHOENE, JUERGEN Computational analysis of turbomachinery flows using Technology of Structures maintains high Standards A lifting surface method for the calculation of Steady FLOFIVE p 637 A89-44642 and unsteady, incompressible propeller aerodynamics [AIAA PAPER 89.25591 p 648 A89-46924 SAIGAL, SUNlL [DNLR-FB-89-04] p 657 N89-25972 RINKER, J. N. Treatment 01 body forces in boundary element design SCHOENTHAL, MARK An air photo analysis of an airplane crash sensitivity analysis p 705 N89-25187 Funcbnal requirements of the Communications p 657 A89-45337 SAITO, SHIGERU Interface Driver (CID) RIZK, N. K. Navier-Stokes simulations around a propfan using [DOT/FAA/CT-TN87/41-REV] p 707 N89-26121 A model for airblast atomization higher-order upwind schemes Communications Interface Driver (CID) system user's [AIAA PAPER 89-2321] p 702 A89-46748 [AlAA PAPER 89-26991 p 650 A89-47028 manual A 3-D analysis of gas turbine combustors SAKAKIBARA, SEI20 [DOTIFAAICT-TN89/361 p 707 N89-26123 [AIAA PAPER 139-2888] p 683 A89-47153 The Schlieren Observation System installed in the NAL SCHRAGE, DANIEL P. two-dimensional high-Reynolds number transonic wind ROBERTS, L. TRUSS An intelligent design system for aircraft wings Flow structure and scalinq laws in lateral wina-tip tunnel and attempts to improve it p 71 1 N89-25162 [ NAL-TR-964 I p 693 N89-26015 blowing p652 A89-47352 SCHROEDER, HANS-WOLFGANG ROBY. R. J. SALMON, ROBERT F. Fuel containment system concept to reduce spillage Technology of structures maintains high standards Improved plasma torch for ignition and flame holding p 637 A89-44642 in supersonic combustion [ DOT/FAA/CT-TN89/22] p 672 N89-25994 SAMANT, SATISH S. SCHROEDER, LINDA M. [AIAA PAPER 89-29451 p 704 A89-47189 Viscous aerodynamic analysis of an oscillating flat-plate ROBY, RICHARD J. Transonic analysis of arbitrary configurations using locally refined grids p 644 A89-45419 airfoil p 652 A89-47356 Dynamic turbine blade temperature measurements SCHULTZ, T. A. [AIAA PAPER 89.26891 p 680 A89-47019 SAMIMY, M. Analysis of severe atmospheric disturbanceslrom airline ROCKWELL, DONALD Compressibility and shock wave interaction effects on flight records Pressure fluctuations on an oscillating trailing edge free shear layers [AIAA PAPER 89-24601 p 648 A89-46847 [NASA-TM-102188] p 658 N89-25977 p 645 A89-45458 ROGAN, J. EDWARD SAMMONS, J. SCHUSTER, LAWRENCE S. Development of a microcomputer based integrated Engine life maturation process Current llight test experience related lo structural design system for high altitude long endurance aircraft [AIAA PAPER 89.24641 p 677 A89-46851 divergence of forward-swept wings p 663 A89-45141 p 668 N89-25159 SAMUELSEN, G. S. SCHUR. WERNER The role of optimization in the next generation of Development and application of a surrogate distillate In search of effective diversity . A six-language study computer-based design tools p 712 N89-25220 fuel p 695 A89-44103 of fault-tolerant flight control software ROHRA, A. SANEORN, J. W. p 710 A89-44423 ' High performance gear systems and heat management Advanced turbofan engine combustion system design SCHWAMEORN. 0. for advanced ducted systems and test verilication p 675 A89-44117 Navier-Stokes simulation of transonic flow about wings [AIAA PAPER 89.24821 p 678 A89-46865 SANKARAN, K. K. using a block structured approach p 644 A89-45422 ROMAN, J. R. Aluminum-lithium alloys for fighter aircraft applications SCHWARTZ, ALAN W. Estimating in-flight engine performance vanations using p 696 A89-45937 Tipjet VTOL UAV (Vertical Takeoft and Kalman filter concepts SAO, YlMlNG LandinglUnmanned Aerial Vehicle) summary. Volume 1: [AIAA PAPER 89.25841 p 679 A89-46940 Cold flow measurements for a double swirler A 1200 pound tipjet VTOL unmanned aerial vehicle. Part ROMBERG, H.-J. combustor p 675 A89-45557 1:Co nceptual design study of a 1200-pound vehicle Vortex structures in the wake of transonic flow about SATO, MAMORU [ AD-A208738 1 p 672 N89-25997 profiles p 654 N89-25134 The Schlieren Observation System installed in the NAL SCHWEIKHARD, WILLIAM 0. ROMINE, E. M., JR. two-dimensional high-Reynolds number transonic wind A simple low-cost telemetry system for those of modest A static investigation of several STOVL exhaust system tunnel and attempts to improve it means p 660 A89-45138 concepts [NAL-TR-964J p 693 N89-26015 SCHWEITZER, B. [AIAA PAPER 89.29281 p 684 A89-47180 SATO, R. Flow about trailing edges in unsteady flow ROMMEL, BRUCE A. Apparent strain characteristics of strain gauges under p 654 N89-25135 Meeting the challenges with the Douglas Aircraft high temperature environment p 697 A89-43844 SCOTT, PAMELA G. Company Aeroelastic Design Optimization Program SATO, YUKlNORl Long duration balloon technology survey, phase 1 (ADOP) p 671 N89-25222 Effectiveness of plasma torches for ianition and [AD-A206975] p 656 N89-25965 ROSFJORD, T. J. flameholding in scramjet SEGAL, CORlN Spray panernation at high pressure [AIAA PAPER 89-25641 p 679 A89-46927 Initial supersonic combustion facility measurements [AIAA PAPER 89-24621 [AIAA PAPER 89-23231 p 702 A89-48750 SAVAGE, M. p 692 A89-46849 ROTTMANN, UWE Transmission overhaul and replacement predictions SEILER, F. Vortices and pressure waves at plates. cylinders and Reduction of aircraft noise in civil air transport by using Weibull and renewal theory optimization of flight tracks and takeoff and approach [AIAA PAPER 89-29191 p 704 A89-47173 wind profiles [ISL-R-102/88] p 656 N89-25966 procedures SAYAMA, MASAMI [ ILR-MITT-200] p 713 N89-25676 SEINER, JOHN M. Effectiveness of plasma torches for ignition and Supersonic jet noise and the high speed civil transport ROUT, R. K. flameholding in scramlet Block-structured solution of transonic flows around [AIAA PAPER 89-23581 p 712 A89-46772 [AIAA PAPER 89-25641 p 679 A89-46927 SETTLES, G. S. wing/pylon/nacelle configurations SCHADOW, K. C. [AlAA PAPER 89-29401 p 651 A89-47184 An experimental study of the effect of streamwise Review of passive shear-flow control research for RUEIN, S. G. vorticity on supersonic mixing enhancement improved subsonic and supersonic combustion RNS solutions for three-dimensional steady [AIAA PAPER 89-24561 p 648 A89-46843 [AIAA PAPER 89-27861 p 703 A89 47083 incompressible flows p 643 A89-45393 SHANG. J. S. RUEIN, T. 0. Combustion enhancement in supersonic coaxial flows Survey and assessment 01 validation data base for [AIAA PAPER 89-27881 p 681 A89-47084 LOPAN - A low-order panel method for subsonic and shockwave boundary layer interactions in supersonic supersonic flows p 639 A89-43724 SCHERER, T. inlets RUED, K. Damping of wing tip vortex systems by the modification [AIAA PAPER 89-29391 p 651 A89-47183 High performance gear systems and heat management of the wing tips p 854 "25138 Investigation of the flow structure around a rapidly lor advanced ducted systems SCHER, J. A. pitching airfoil p 652 A89-47360 [AIAA PAPER 89.24821 p 678 A89-46865 Low angle injection into a supersonic flow SHANKAR, U. J. RUMSEY, C. L. [AIAA PAPER 89-24611 p 648 A89-46848 Relaxation oscillations in aircraft cruise-dash A natural low-frequency oscillation of the flow over an SCHINSTOCK. WILLIAM C. optimization airfoil near stalling conditions p 645 A89-45437 A simple low-cost telemetry system lor those of modest [ AD-A206722] p 672 N89-25996 RUNCHAL, A. K. means p 660 A8g-45138 SHAO, JlAXlNG Experimental investigation of aeroengine high-speed Ramjet combustor modeling for engineering design SCHIPHOLT, G. J. roller bearing p 700 A89-45570 [AlAA PAPER 89.27991 p 681 A89-47092 Aerodynamic design and testing of Fokker 50 nacelle SHAU, Y. R. RUPP, GEORGE 0. and intake ducts Mach 5 inlet CFD and experimental resulls [AIAA PAPER 89-24831 p665 A89-46866 Experimental study 01 spreading rate enhancement of [AIAA PAPER 89-23551 p 647 A89-46769 high Mach number turbulent shear layers SCHIRMER, ALBERT0 W. [AIM PAPER 89-24581 p 648 A89-46845 Parametric study of a simultaneous pitchlyaw thrust SHE, GUANGMING S vectoring single expansion ramp nozzle An integrated design computational method lor the wing [AIAA PAPER 89-28121 p 682 A8947098 optimization camber and twist at subsonic and supersonic SADLER, J. H. R. SCHMIDT, DAVID K. flow p 646 A89-46256 Advanced propulsion systems for large subsonic lntearated structure/control law design"~ bv multilevel SHIMAZAKI, HlROSHl transports 0ptimi;ation T-4 inlet/engine compatibility flight test results [AIAA PAPER 89-24771 p 677 A89-46861 [NASA-TM-101623] p 712 N89-28823 [AIAA PAPER 89-24661 p 665 A89-46853 The Rolls Royce Allison RB580 turbofan - Matching the SCHMIDT, GORDON S. SHINGLEDECKER, CLARK market requirement lor regional transport Analysis of low Reynolds number separation bubbles Controller evaluation of Initial Data Link air traffic control [AIAA PAPER 89-24881 p 678 A89-46869 using semiempirical methods p 652 A89-47351 services. Volume 2: Mini Study 2 SAFONOV. M. 0. SCHNEIDER. JON C. [ DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 Robust computer-aided synthesis and optimization of Average-passage simulationof counter-rotatingpropfan SHUART, MARK J. linear multivariable control systems with varying plant propulsion systems as applied to cruise missiles Oplimum design of swept-forward high-aspect-ration dynamics via AUTOCON p 711 N89-25179 [AIAA PAPER 89.29431 p 651 A89-47187 graphite-epoxy wings p 669 N89-25172
6-11 SIEBERT, RUEDIGER PERSONAL AUTHOR INDEX
SIEBERT, RUEDIGER SPARA, KAREN M. STRUCK, JACOB K. Pressure measurement technique of WT-WK Supersonic turbomachine rotor flutter control by Aircraft jet engine exhaust blast effects on Par-56runway [DFVLR-MITT-88-11I p 693 N89-25243 aerodynamic detuning threshold lamp fixtures SIGNOR, DAVID 8. [AIAA PAPER 89-26851 p 680 A89-47015 [ DOT/FAA/CT-69/4] p 694 N89-26018 Performance and loads data from an outdoor hover test SPYROPOULOS, J. T. SUBRAMANIAN, S. V. of a Lynx tail rotor Block-structured solubon of transonic flows around Three-dimensional multignd Navier-Stokes [ NASA-TM-1010571 p 656 N89-25958 wing/pylonlnacelle configurations computations for turbomachinery applications SlH, 0. C. [AIM PAPER 89-29401 p 651 A89-47184 [AIAA PAPER 89.24531 p 702 A89-46641 Fatlgue fatlure initiation analysis of wng/fuselage bolt SOUIRE, L C. SUDANI. NORIKAZU assembly p 699 A89-45210 The mixing of three-dimensional turbulent wakes in Expenmental study on aerodynamic characteristics of SIMMERL. JOSEPH boundary layers p 639 A89-43722 hypersonic transport configuration p 640 A89-44972 Jet or prop required for future regional transports? SRUUJES, J. SWONGER, K. BILL p 637 A89-44641 Vortices and pressure waves at plates, cylinders and Low cost control system for expendable turbine SIMONEAU, ROBERT J. wind profiles engines CFD in the context of IHPTET The Integrated High (ISL-R-t02/88] p 656 N89-25966 [AIM PAPER 89-25861 p 680 A89-46942 PerformanceTurbine Technology Program SYLVESTRE, LINDA M. STAINBACK, P. CALVIN [ NASA-TM-102132J p 708 N89-26174 ADINTS - Moving toward standardization of automatic A high speed data acquisition system for the analysis SIMONICH, J. C. test equipment p 701 A89-46462 of velocity. density. and total temperature fluctuations at Hot wre measurements downstream of a prop-fan SZAFRANSKI, F. J. transonic speeds [AIAA PAPER 89-26981 p 650 A89-47027 Embedded temperature measurements in a [SAE PAPER 8814511 p 691 A89-45248 SINGH. SAHJENDRA N. carbon-carbon wing leading edge hot structure Asymptotically decoupled discontinuous control of A new look at wind tunnel flow quality for transonic p 697 A89-43643 systems and nonlinear atrcratt maneuver flows SZEWCZYK, V. M. p686 A89-45064 [SAE PAPER 8814521 p 692 A89-45249 Reengining stage two aircraft with the Tay SISTO. F. STANLEY, ALLAN W. F. [AIAA PAPER 89-23611 p 676 A89-46774 Computational and expenmental study of stall Concept for an aircraft multi-component thrust propagaton in axial compressots measurement facility p 691 A89-45130 [AIAAPAPER 89-24541 p647 A89-46842 STAUBLI, THOMAS T SLIWA, STEVEN M. Pressure fluctuations on an oscillating trailing edge Overview of Dynamics Integration Research (DIR) p 645 A89-45458 TAFLOVE. ALLEN program at Langley Research Center STECKEMETZ, BERN0 Review of FD-TD numericalmodeling of electromagnetic p 667 N89-25150 Unsteady phenomena on delta wings with partially wave scanenng and radar cross section SMAILYS. A. A. broken-down vortex regions p 654 N89-25129 p 673 A89-45107 TAHA, M. R. Rsduction of t-P aerodynamic loads on tractor aircraft STEINBERG. BERNARD 0. Combustion charactenstics of gaseous flames in a gas engine installations Experimental localized radar cross sections of aircraft turbine combustor [AIAA PAPER 89-29241 p 651 A89-47177 p 673 A89-45105 [AIM PAPER 89 28921 p 683 A89-47155 SMERECZNIAK. P. STEPANOV, V. A. Advanced thrust vectonng nozzles for supercruise fighter TAKAKURA, YOKO Numencal and experimental investigation of Inviscid and viscous flow simulations around the atrcraft airframe-integratedinlet for high velocities [AIM PAPER 89-28161 p 682 A89-47102 Onera-M6 by TVD schemes p 644 A89-45425 [AIAA PAPER 89-26791 p 649 A89-47009 SMITH, BRIAN TALOlTA, NICHOLAS J. Large-scale wnd tunnel tests of an ejector-lifl STOVL STERN, A. M. Controller evaluation01 Initial Data Link air traffic control The challenge of reducing supersonic civil transport aircraft model services Volume 2 Mini Study 2 propulsion noise [AIM PAPER 89-29051 p 666 A89-47165 [DOT/FAA/CT-89114-VOL-21 p 661 N89-25986 [AIM PAPER 89-23631 p 677 A89-46776 SMITH, CHARLES A. TAM, CHRISTOPHER K. W. Performanceand loads data from an outdoor hover test STETSON, KENNETH F. The instabiltty and acoustic wave modes of supersonic Unsteady transition location p 652 A89-47376 of a Lynx tail rotor mixing layers inside a rectangular channel [ NASA-TM-1010571 p 656 N89-25958 STEVE, H. p 699 A89-45453 Low-storageimplicit upwnd-FEM schemes for the Euler TAN, HAOYUAN SMITH, D. E. Expenmental research on swriing combustion Testing of the 578-DX propfan propulsion system equations p 642 A89-45375 efficiency p 675 A89-45558 [AIAA PAPER 89-25811 p 679 A89-46938 STEVENS, MARC 0. F/A-lBA digital flight control system degraded modes TANG, DlYl SMITH, DAVID M. A dynamic digital model for the turbojet with Expen systems' role broadens p 71 1 A89-45293 flight evaluation p 687 A89-45158 STEWART, R. J. pulse-monitoredfueler p 675 A89-45559 SMITH, DWAYNE S. TATUM. KENNETH E. Flow charactenstics about a trailing edge A study of AI-Li alloys using small angle neutron scattering p 695 A89-44577 Effects of nonlinear aerodynamics and static [UTIAS-TN-270] p 655 N89-25952 aeroelasticity on mission performance calculations for a STIEFEL, WILLIAM R. SMITH, L. A. fighter aircraft p 669 N69-25170 Environmental icing test of TBOO helicopter engine with Plan, formulate. discuss and correlate a NASTRAN finite TAVELLA, 0. integral inlet pamcle separator element vibrations model of the Boeing Model 360 Flow structure and scalrng laws lateral wmq-tip [AIM PAPER 89.23241 p 676 A89-46751 m helicopter airframe blowing p 652 A89-47352 [NASA-CR-1817871 p 707 N89-25480 STOFF, HORST TEKAWY, J. A. SMITH, R. A. Calculation of the total pressure loss coefficient with Robust computer-aided synthesis and optimization of three models for four supersonic axial-flow compressors Development and applicatlon of a surrogate distillate linear multivariable control systems with varying plant fuel p 695 A89-44103 p 640 A89-44898 dynamics via AUTOCON p 71 1 N89-25179 SMITH, RICHARD E. STONEHOUSE. A. J. TEPOSU, 1. X-15 pilot-in-the-loop and redundantlemergency A review of beryllides for very high temperature The influence of altitude and speed variations on the systems evaluation p 664 A89-45168 service p 696 A89-45948 aeroplane's load components in longitudinal nonlinear SMITH, ROBERT 0. STORACE, A. F. manoeuvres p 688 A89-45179 Turbine engine structural efficiency determination FAA rotorcraft research, engineering and development TERLIZZI, A. bibliography, 1962-1988 Supplement [AlAA PAPER 89-2571I p 679 A89-46932 A validation of a Navier-Stokes 2D solver for transonic [AD-A207162] p 673 N89-260M) STORCH, V. M. turbine cascade flows [AIM PAPER 89-24511 SNYDER, CURTIS 0. Low cost equipment lor flight test film and video p 647 A89-46839 evaluation p 698 A89-45137 THANGAM, S. A propulsion development strategy for the National Computational and experimental study of stall Aero-Space Plane STORM VAN LEEUWEN. SAM propagation in axial compressors [AIM PAPER 89-2751] p681 A89-47061 The measurement of linear and angular displacements in prototype aircraft - Instrumentation. calibration and [AIAA PAPER 89-24541 p 647 A89-46842 SNYDER. L THOMAS, R. H. The Rolls Royce Allison FIB580 turbofan - Matching the operational accuracy p 698 A89-45142 STOUFFER, S. 0. Low angle injection into a supersonic flow market requKement for regonal transport [AIAA PAPER 89-24611 p 648 A89-46846 [AIM PAPER 89-24881 p 678 A89-46869 Improved plasma tcfch for ignition and flame holding in supersonic combustion THOMPSON, ADDISON S. WARES. C. E. [AIAA PAPER 89-29451 p 704 A89-47189 6-16 high AOA testing p 687 A89-45162 Integration of scramlets wth wavender configurations THOMPSON, JOE F. [AIAA PAPER 89-26751 p 695 A89-47005 STOUFFLET, B. Low-storageimplicit upwind-FEM schemes for the Euler Transonic flow solutions on general 3D regions using SOBEL, LAWRENCE equations p 642 A89-45375 composite-block grids p 644 A89-45428 Applications of integrated designlanalysis systems in STREICHER, JUERGEN THORNING, ARTHUR 0. aerospace structural design p 666 N89-25147 Prototype of a slant nsual range measuring device Research in automation for air traffic control - United SOBIESZCUNSKI-SOBIESKI,JAROSLAW [ DFVLR-FB-88-42] p 713 N89-25697 Kingdom work and associated European projects Integrated aerodynamic-structural deslgn of a STRICKER, JEFFREY M. ISAE PAPER 8814701 p 661 A89-47336 forward-swept transport wing p 669 N89-25168 Compressor exit temperature analysis TILDEN, THOMAS V. SOECHTING, F. 0. [ AlAA PAPER 89-29471 p 684 A89-47191 Digital flight and inlet control in the SR-71 Advanced matenal applicabons for turbine airfoils STRICKLAND, MICHAEL J. p 664 A89-45160 [AIM PAPER 89-26931 p 680 A89-47023 Experiences with a prevalidation methodology for TILLMAN. KENNETH 0. SORKIN, ROBERT 0. designing integrated/propulsion control system The pursuit of integrated control - A realtime aircraft An exploratory study of the use of movement-correlated architectures system demonstration cues in an auditory head-up display p 674 A89-45329 [AIAA PAPER 89-27031 p 688 A89-47030 [AlAA PAPER 89-2701] p 688 A89-47029
8-12 PERSONAL AUTHOR INDEX WISLER, D. C.
TILLMAN, T. 0. Recent developments in large-scale structural WALTON, JAMES S. Hot wire measurements downstream of a prop-fan optimization p 706 N89-25231 Expertvision - A video-based non-contact system for [AIAA PAPER 89.26981 p 650 A89-47027 VIJGEN, P. M. H. W. motion measurement p 698 A89-45136 Supersonic nozzle mixer ejector Wind-tunnel investigations of wings with serrated sharp WANG, HONGMIN [AIAA PAPER 89-29253 p 683 A89-47178 trailing edges p 641 A89-45262 The investigationof jet engine starting TISCHLER, V. A. VINNEMEIER, F. p 676 A89-46025 Structural optimization of framed structures using The influence of swirl and fuel composition of WANG, S. S. generalized optimality criteria p 706 N89-25197 boron-containingfuels on combustion in a solid fuel ramjet Full scale fatigue crack growth test of advanced jet Combustion chamber TOBIAS. LEONARD trainer AT-3 p 664 A89-45207 [AIM PAPER 89-28851 p A89-47150 Controller evaluations of the descent advisor automation 683 WANG, SHAOQING VINOGRAWV, V. A. aid The ATR/RJ engine performance at constant dynamic Numerical and experimental investigation of [NASA-TM 1021971 p 659 N89-25981 pressure and the consideration of transition condition airframe-integrated inlet for high velocities p 694 A89-46016 TODA, DAISUKE [AIAA PAPER 89.26791 p 649 A89-47009 WANG, TEN-SEE T-4 inletlengine compatibility flight test results VISBAL, MIGUEL R. Numerical study of reactive ramjet dump combustor [AIAA PAPER 89.24661 p 665 A89-46853 Investigation of the flow structure around a rapidly flowfields with a pressure based CFD method TORELLA, G. pitching airfoil p 652 A89-47360 [AIM PAPER 89-27981 p 681 A89-47091 Numerical codes for unsteady simulation of turbojet. VISINESCU, R. turbofan and turboprop engines for training purposes Reinforcing solutions for a panel cut-out WARSI, S. [AIAA PAPER 89-22591 p 676 A89-46704 p 698 A89-45177 Large scale advanced propeller blade pressure TOUSSAINT, M. VITTAL, B. V. R. distributions - Prediction and data Prediction of turbomachinery performance - Application Expendable supersonic exhaust nozzle concepts [AIAA PAPER 89-26961 p 650 A89-47026 to a centrifugal pump, a centrifugal compressor, and a [AIAA PAPER 89-29271 p 684 A89-47179 WEILAND, C. radial inflow turbine p 640 A89-44638 VITTING, T. Simulation of inviscid hypersonic real gas flows TREBINJAC, I. Damping of wing tip vortex systems by the modification p 644 A89-45414 Present state of the theory of secondary flows and of the wing tips p 854 N89-25138 WEIR, LOIS J. experimental verifications p 698 A89 44636 VOIGT, R. 0. Mach 5 inlet CFD and experimental results TROST, THOMAS InternationalConference on Numerical Methods in Fluid [AIAA PAPER 89-23551 p 647 A89-46769 Mechanical stresses during air transport and ground Dynamics, 11th. Williamsburg, VA. June 27-July 1. 1988, WEISS, CARL operations p 700 A89-46221 Proceedings p 699 A89-45351 Integrated flight/propulsion control study for STOVL TSUJIKAWA, YOSHIHARU VOLCKERS, UWE applications Performance analysis of scramlet engines Controller evaluations of the descent advisor automation [AIAA PAPER 89-29081 p 688 A89-47166 p 676 A89-46600 aid WEISS, ROSANNE M. TSUKAMOTO, YUJIRO [NASA-TM-102197] p 659 N89-25981 Analysis of helicopter environmental data: Indianapolis Performance analysis of scramjet engines VOLPERT. DOMlNlOUE downtown heliport, Wall Street heliport. Volume 1: p 676 A89-46600 Solution of Euler equations by a finite element method Summary TURNEY, GEORGE E. application to supersonic flows p 639 A89-44319 [AD-A206708] p 710 N89-26294 Aeronautical applications of high-temperature VON GLAHN, U. H. WEISSHAAR, TERRENCE A. superconductors Rectangular nozzle plume velocity modeling for use in [NASA-TM-102311] p686 N89-26008 AeroseNoelastic tailoring for lateral control jet noise prediction enhancement p 689 N89-25189 [AIAA PAPER 89-23571 p 647 A89-46771 WERNER, CHRISTIAN U VON WELCK, STEPHAN Prototype of a slant visual range measuring device The EEC supports air transport research [DFVLR-FB-88-421 p 71 3 N89-25697 p 638 A89-46078 UHERKA, KENNETH WESTPHAL, R. V. Aeronautical applications of high-temperature VOOGT, N. Interaction of an oscillating vortex with a turbulent superconductors Aerodynamic design and testing of Fokker 50 nacelle boundary layer p 645 A89-45906 and intake ducts [NASA-TM-10231I] p 686 N89-26008 WHITEHURST, R. BRADFORD, 111 [AIAA PAPER 89-24831 p 665 A89-46866 UMASHANKAR,KORADA R. Initial supersonic combustion facility measurements Review of FD-TD numerical modeling of electromagnetic VOUILLARMET, A. [AIAA PAPER 89.2462) p 692 A89-46849 Present state of the theory of secondary flows and wave scattering and radar cross section WHITFIELD, DAVID L. p 673 A89-45107 experimental verifications p 698 A89-44636 Transonic flow solutions on general 3D regions using VUKELICH, S. 1. composite-blockgrids p 644 A89-45428 Engine life maturation process WIDENER, STANLEY K. v [AIAA PAPER 89-24641 p 677 A89-46851 Improving the development process for main combustor VAIUN, 8. exit temperature distribution Infrared and millimeter wave acquisition system W [AIM PAPER 89.28041 p 681 A89-47094 [ONERA, TP NO 1989-361 p 699 A89-45191 WIESEMAN, CAROL D. VAN DAM, C. P. Aeroelastic modeling for the FIT (Functional Integration WAELCHLI, RENE Wind-tunnel investigationsof wings with serrated sharp Technology) team F/A-18 simulation Calculation of the total pressure loss coefficient with trailing edges p 641 A89 45262 p 670 N89-25192 three models for four supersonic axial-flow compressors VAN DEN BERG, J. I. p 640 A89-44898 WIETING, ALLAN R. Numerical simulation of the flow about a wing with Finite element flow-thermal-structural analysis of WAGNER, D. A. leading-edge vortex flow p 643 A89-45390 aerodynamically heated leading edges Development testing 01 the 578 propfan gear system VAN HENGST, J. p 655 N89-25198 [AIM PAPER 89.28171 p 682 A89-47103 Aerodynamic design and testing of Fokker 50 nacelle WIGHTMAN, FREDERIC L. WAGNER, J. H. and intake ducts An exploratory study of the use of movement-correlated Hot wire measurements downstream of a prop-fan [AIAA PAPER 89-24831 p 665 A89-46866 cues in an auditory head-up display p 674 A89-45329 [AIAA PAPER 89-26981 p 650 A89-47027 Design and testing of a common engine and nacelle WILBECK, JAMES S. for the Fokker and Gulfstream GIV airplanes WAKAMATSU, YOSHIO 100 Long duration balloon technology survey, phase 1 [AIAA PAPER 89-24861 p 666 A89-46867 A comparison of Scrarnjet engine performances of [AD-A206975] p 656 N89-25965 VAN WIE, D. M. various cycles An experimental technique for the measurement of mass [AIAA PAPER 89-26761 p 680 A89-47006 WILLIAMSON, GALE L. The System 500, a real-time flight test telemetry flow of scramlet inlets tested in hypersonic pulse WALKER-HECKMAN, E. A. system p 660 A89-45134 facilities Aluminum-lithium alloys for fighter aircraft applications [AIAA PAPER 89-23311 p 692 A89-46755 p 696 A89-45937 WILLIAMSON, JOHN VAN WILLIGEN, D. The links in the chain - The lnmarsat system WALKER, HARRY C., 111 p 697 A89-43876 Some aspects of interference on Loran-C X-29A performance flight tests - Results and lessons p 660 A89-45221 learned p 688 A89-45154 WILSON, C. W. Evaluation of novel igniters in a turbulent bomb facility VANDERVELDEN, ALEXANDER J. M. WALKER, LAURENCE A. and a turbo-annular gas turbine combustor The conceptual design of a Mach 2 Oblique Flying Wing F-I5 STOL/Maneuvering Technology Demonstrator - [AIAA PAPER 89-29441 p 684 A89-47188 supersonic transport Initial flight test results p 687 A89-45157 [ NASA-CR-1775291 p 671 N89-25233 WILSON, K. J. WALSH, D. W. An economic model for evaluatina hiah-soeed aircraft Combustion enhancement in supersonic doaxial flows 1. Hot ductility response of AI-Mg and AI-MgLi alloys designs [AlAA PAPER 89-27881 p 681 A89-47084 p 695 A89-45330 [ NASA-CR-1775301 p 671 N89-25235 WINGROVE, R. C. VANKA. S. P. WALSH, FRASER Analysis of severe atmospheric disturbances from airline Efficient computational tool for ramjet combustor Low-temperature performance of a power-pack for a flight records research 2-watt ELT p 709 A89-44016 [ NASA-TM-1021861 p 658 N89-25977 [AIAA PAPER 88-00601 p 674 A89-44108 WALSH, JOANNE L. WINTER, CARL-JOCHEN VASEY-GLANDON, V. M. Structural optimization of rotor blades with integrated Materials and structures for 2000 and beyond: An Aluminum-lithium alloys for fighter aircraft applications dynamics and aerodynamics p 668 N89-25156 attempted forecast p 696 A89-45937 WALTON, DAVID [DFVLR-MITT-89-02] p 706 N89-25358 VENKAYYA, VIPPERLA B. Economic analysis of a beam-powered, personalized WISLER, D. C. Structural optimization of framed structures using global aerospace transportation system Improved compressor performance using recessed generalized optimality criteria p 706 N89-25197 [AIAA PAPER 89-24431 p 714 A89-46835 clearance (trenches) p 674 A89-44113
B-13 WOLF, J. P. PERSONAL AUTHOR INDEX
WOLF, J. P. YU, JAMES C. ZURINSKAS. THOMAS Preliminary asssssment of exhaust systems for high Noise considerabons for tiltrotor Controller evaluationof Initial Data Link air traffic control Mach (4 to 6) fighter aircrafl [AlAA PAPER 89.23591 p 665 A89-46773 sewices Volume 2 Mini Study 2 [AIAA PAPER 89-23561 p 676 A89-46770 YU, N. J. [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 WOLFSON, MARILYN M. Development of a highly efficientand accurate 3D Euler Selected wind shear events ObSeNed dunng the 1987 flow solver p 642 A89-45370 evaluaton 01 enhancements to the FAA (Federal Aviation YU, XIONGOING Administration) low level wind shear alert system at The analysis and measurements of radar cross section Stapleton lnternabonal Airport (RCS) of some wing structure models [AD-A206711] p 710 N89-26323 p 674 A8946298 WOOD, c. P. Development and application of a surrogate distillate fuel p 695 A89 44103 WOOD. N. J. z Flow structure and scaling laws in lateral wing-tip ZABALA, R. J. blowing p 652 A89-47352 Mechanical properbes of high-temperature beryllium WOODWARD, RICHARD P. intermetallic compounds p 697 A89-47213 In-flightmeasurement of propeller noise on the fuselage of an airplane ZAMAN, K. 8. M. 0. [ NASA-TM-1022851 p 713 N89 25675 A natural low-hequency oscillation of the flow over an WRIGHT, WILLIAM E. airloil near stalling conditions p 645 A89-45437 Evaluabon of a fault tolerant digital engine controller ZANG, XlAOMEl [AIM PAPER 89-25891 p 680 A89-46944 Cold flow measurements for a double smrler WU, TE-KAO combustor p 675 A89-45557 Radar cross section of arbitrarily shaped bodies of ZANNElTI, LUCA revolulton p 674 A89 451 11 Multidimensionaladaptrve Euler solver WUEBBLES, DONALD J. p641 A89-45360 Prevenbng depletion of stratospheric ozone ZARETSKY. E. V. Implications on future aircraft emissions Ceramic beanngs for use in gas turbme engines [DE89-009964I p 710 N89-255’30 p702 A8946697 ZARETSKY, ERWIN V. Selection of rollingelement beanng steels for long-life X applications p 704 A89-47250 ZEILER, THOMAS A. XIAO, NINGFANG Aeroelastic modeling for the FIT [Functional Integration Investigabon on unsteady flow field and endwall Technology) team F/A-18 slmulation boundary layer in axial flow compressor with hot-wire p 670 N89-25192 anemometer p 645 A89-45560 Timecorrelated gust loads uslng Matched-FilterTheory XU, JIANZHONG and Random-Process Theory A new way of looking at Transonic cascade flow solved by the combined things shock-capturingand shock-fitting method [NASA TM-1015731 p 671 NE9 25232 p 639 A89 44114 ZHAN, MINGXUE XU, MEN Expenmental investigation of aeroengine high-speed The research of 2-D flexible wall self-correcting wind roller beanng p 700 A89-45570 tunnel p 692 A89-46258 ZHANG, QINGFAN XUE, ZHONGQING Cold flow measurements lor a double swirler Study of nonlinear Duff ing charactenstics of flexible rotor combustor p 675 A89-45557 with SFDB p 700 A89-45568 ZHANG. ZHAOXING Performance and flow heM of a ducted propeller Y [AlAA PAPER 89-26731 p 649 A89-47003 ZHANG, ZUO-MIN Difference methods for inibal-boundary-valueproblems YAMAMOTO, ATSUMASA and flow around bodies (Revised edition) Mechanisms of Endwall leakage flows and the p 646 A89 461 98 associated losses in a linear turbine rotor cascade with ZHENG, QlNGPlNG blade tipclearance [ NAL-TR-985Tl p 708 N89-26168 Cold flow measurements for a double swirler combustor p 675 A89-45557 YAMAMOTO, 0. ZHONG, XICHANG Large scale advanced propeller blade pressure Differencemethods for initial-boundary-valueproblems distnbubons - Prediction and data and flow around bodies (Rewsed edition) [AIAA PAPER 89.26961 p 650 A89-47026 p 646 A89-46198 YAMAMOTO. SATORU ZHOU, XUEHUA An implicit time-marching method for solving the 3-D Radiative charactenstics of hypersonic cone wake compressrble Navier-Stokes equations p 646 A89-46263 p 642 A89-45374 ZHU, GOLlN YAMAUCHI, GLORIA K. An integrated deslgn computational method lor the wing Performance and loads data from an outdoor hover test optimization camber and twist at subsonic and supersonic of a Lynx tail rotor flow p646 A89-46256 [ NASA-TM-101057) p 656 N89-25958 ZHU, YOU-LAN YAN, RUQUN Difference methods for initial-boundary-valueproblems Effects of axial velocity density ratio on cascade and flow around bodies (Revised edibon) performances p 645 A89-45565 p 646 A89-46198 YANG, JlANXlNG ZHU, ZlQlANG The analysis and measurements of radar cross Section Nonisentropic potential calculation for 2-D and 3-13 (RCS) of some wing structure models transonic flow p 645 A89-45434 p 674 A89-46298 ZHUANG, BIAONAN YANG, JINGZUO Expenmental investigation on charactenstics of single The analysls and measurements of radar cross section and tandem blade cascades with double-circular arc (RCS) of some wing structure models profile p 676 A89-45567 p 674 A89-46298 ZHUANG, XlNFU YATES. WILSON D., 111 The solubon of 3-0 temperature distribution in a cycling oil cooled aircraft ac generator by network topology A nontraditional approach to reliability p 701 A89-46483 method p 701 A89-46282 ZIELINSKI, PAUL A. YEE, H. C. Probabilisbc analysis of arcrafi structure Numencal study of unsteady viscous hypersonic blunt p665 A8946470 body flows with an impmging shock p 643 A89-45394 ZIEVE. PETER YONKE, W. A. Electromagneticemissions from a modular Low Voltage The evolution . IFPC to VMS Electro-Impulse De icing system [AIAA PAPER 89-27051 p 688 A89-47032 [ DOT/FAA/CT-88/31] p 707 N89-26120 YOUNG, DAVID P. ZIMMERMAN, ANDREW T. Transonic analysis of arbitrary configurations using C-I 30 Hercules outer mng residual strength tests locally refined grids p 644 A89-45419 p 663 A89-45132 YOUNG, K. B. ZUO, PEICHU Omega navigation in the shadow 01 Antarctica The research of 2-D flexible wall self-correcting wind p 660 A89-43893 tunnel p 692 A89-46258
6-14 CORPORATE SOURCE INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245) November 1989
Army Engineer Watamays Experlment Statlon, Department of the Alr Force, Washington, DC. Vlcksburg, MS. Flap system for short takeoff and landing aircraft Design criteria lor aggregate-surfaced roads and [AD-D013981I p 671 N89-25234 Typical Corporate Source airfields Aircraft engine outer duct mounting device Index Listing [AD-A207059] p 694 N89-26019 [AD-W13988] p 672 N89-25991 Evaluation of nondestructive test equipment lor airfield Superconducting rotor cooling system pavements. Phase 1: Calibrationtest results and lield data [ AD-DO140201 p 709 N89-26240 collection Deutache Forachungs- und Versuchaanstalt fuer Luft- [AD-A207159] p 694 N89-26020 und Raumfahrt, Brunawlck (Germany, F.R.). I CORPORATESOURCE I Contributions lo the improvement of flight safety in wind shear B [DFVLR-FB-88-49] p 658 N89-25144 Pressure measurement technique of WT-WK Federal Admlnlstratlon, Atlantlc Clty, N.J. Bently Rotor Dynamics Raurarch Corp., Mlnden, NV. [DFVLR-MlTT-88-11] p 693 N89-25243 Hardware fault insertion and instrumentation system Influence 01 rubbing on rotor dynamics, part 2 A lifting surface method for the calculation of steady [ NASA-CR-183649-PT-21 p 706 N89-25464 and unsteady, incompressible propeller aerodynamics [NASA-CR-182746] P 58 N89-10526 Boelng Co., Seattle, WA. [DFVLR-FB-89-04] p 657 N89-25972 Experiences with a prevalidation methodology for Deutscha Forschungs- und Versuchsanstalt fuer Luft- 7-T- desianina intearated/DrODulSiOn- .. control svstem und Raumfahrt, Goettlngen (Germany, F.R.). architectures Two-dimensionalelliptic grid generation lor airfoils and [AIAA PAPER 89-27031 p 688 A89-47030 cascades Airplane tests of enhanced emergency smoke venting [DFVLR-FB-88-52] p 653 N89-25125 [D218N301] - p 658 N89-25976 Deutache Forschungs- und Versuchaanstalt fuer Luft- Boelng Commerclal Airplane Co., Seattle, WA. und Raumfahrt, Oberpfaffenhofen (Weat Germany). Descent strategy comparisons lor TNAV-equipped Prototype of a slant visual range measuring device aircraft under airplane-preferred operating conditions [DFVLR-FB-88-42] p 713 N89-25697 Listings in this index are arranged alphabetically [ NASA-CR-42481 p 690 N89-26011 Deutsche Forschungs- und Varsuchaanstalt fuer Luft- by corporate source. The title of the document is Boelng Hellcopter Co., Phlladelphla, PA. und Raumfahrt, Stuttgart (Germany, F.R.). Plan, formulate, discuss and correlate a NASTRAN finite Materials and structures lor 2000 and beyond An used to provide a brief description of the subject element vibrations model of the Boeing Model 360 attempted forecast matter. The page number and the accession helicopter airframe [ DFVLR-MITT-89-02] p 706 N89-25358 number are included in each entry to assist the [NASA-CR-1817871 p 707 N89-25480 user in locating the abstract in the abstract section. E If applicable, a report number is also included as C an aid in identifying the document. Electrolmpact, Inc., Seattle, WA. Calltornla Unlv., Berkeley. Electromagneticemissions from a modular Low Voltage The conceptual design of a Mach 2 Oblique Flying Wing Electro-Impulse De-icing system supersonic transport [DOT/FAA/CT-88/31] p 707 N89-26120 [NASA-CR-177529] p 671 N89-25233 Eloret Corp., Sunnyvale, CA. An economic model for evaluating high-speed aircraft Experimentaland computational flow-fieldresults for an A designs all-body hypersonic aircraft [ NASA-CR-1775301 p 671 N89-25235 [ NASA-CR-1853471 p 655 N89-25953 Alr Force Wright Aeronautical Labs., Wright-Patterwn Calltornla Unlv., Davis. AFB, OH. Wind-tunnel investigationsof wings with serrated sharp m Optimum structural design with static aeroelastic trailing edges p 641 A89-45262 F constraints p 669 N89-25171 Calltornla Unlv., Lo8 Angeles. Structural optimization of rotor blades with straight and Federal Avlatlon Admlnlstratlon. Atlantic Clty, NJ. An approximation function for frequency constrained Notice lo Airmen [NOTAM) system operational structural optimization p 705 N89-25196 swept lips subject to aeroelastic constraints p 667 N89-25152 concept Structural optimization of framed structures using [ DOT/FAAICT-TNBS/ 101 p 658 N89-25142 generalized optirnality criteria p 706 N89-25197 An integrated approach to the optimumdesign of actively controlled composite wings p 670 N89-25194 Heliport identificationbeacon Recent developments in large-scale structural Clvll Avlatlon Authority, London (England). [DOT/FAA/CT-TN89/31I p 661 N89-25984 optimization p 706 N89-25231 UK airmisses involving commercial air transport Evaluationof a projection algorithm for the stereographic Two axial compressor designs for a stage matching [CAA-3/88] p 658 N89-25143 representation of aircraft in an air traffic control system investigation Complere, Inc., Hampton, VI. [ DOT/FAA/CT-TN89/20] p 661 N89-25985 [AD-A206951] p685 N89-2W A high speed data acquisition system lor the analysis Controller evaluation of Initial Data Link air traffic control Services Volume 2 Mini Study 2 Akron Unlv., OH. of velocity. density, and total temperature fluctuations at [DOT/FAA/CT-89/14-VOL-2] p 661 N89-25986 Transmission overhaul and replacement predictions transonic speeds using Weibull and renewal theory [SAE PAPER 8814511 p 691 A89-45248 Fuel containment system concept to reduce spillage [ DOT/FAA/CT-TN89/22] p 672 N89-25994 [AIAA PAPER 89-29191 p 704 A89-47173 A new look at wind tunnel flow quality for transonic Functional requirements of the Communications Analatom, Inc.. San Jour, CA. flows [SAE PAPER 8814521 p 692 A89-45249 Interface Driver (CID) Numerical simulations of oblique detonations in Conneclcut Unlv., Storm. [DOT/FAA/CT-TN87/41-REV] p 707 N89-26121 supersonic combustion chambers p 674 A89-44115 X-ray based extensometry Communications Interface Driver (CID). .. svstem user's Analytlcal Services and Materials, Inc., Hamplon, VI. [ NASA-CR-1850581 p 706 N89-25432 manual Theapplicationof3D marchingscheme forthe prediction Contlnuum Dynamics, Inc., Prhceton, NJ. [ DOT/FAA/CT-TN89/36] p 707 N89-26123 of supersonic free jets Feasibility 01 predicting performance degradation of Mode S performance lest plan [AIAA PAPER 89-2897) p 651 A89-47160 airfoils in heavy rain IDOT/FAA/CT-TN89/241 o 707 N89-26127 Applled and Theoretlcal Mechanics, Inc., Oakland, CA. [ NASA-CR-1818421 p 657 N89-25973 Satellite low rate voice demonstration test plan Modeling of turbulence for compression corner flows Cornell Unlv., Ithaca, NY. IAD-A2067101 D 707 N89-26133 and internal llows Multigrid calculation of three-dimensional Analysis 01 helicopter environmental data: Indianapolis turbomachinery flows [AIAA PAPER 89.23441 p 647 A89-46763 downtown heliport, Wall Street heliport. Volume 1: [ NASA-CR-1853321 p 708 N89-26172 Army Armament Reurarch and Development Summary Command, Dover, MI. [ AD-A206708 I p 710 N89-26294 Aircraft jet engine exhaust blast effectson Par-56runway D Federal Avlatlon Admlnlstratlon, Washington, DC. threshold lamp fixtures FAA statistical handbook of aviation: Calendar year [DOT/FAA/CT-89/4] p 694 N89-26018 De Hsvllland Alrcraft Co. of Canada Ltd., Downsvlew 1987 Army Avlatlon Systems Command, Cleveland, OH. (Ontario). [AD-A2009171 p 638 N89-25113 Transmission overhaul and replacement predictions Large-scale wind tunnel tests of an ejector-lift STOVL Report to Congress: Technical feasibility 01 joint use using Weibull and renewal theory aircraft model at Scott AFB. Selfridge AGB and El Tor0 MCAS [AIAA PAPER 89-29191 p 704 A89-47173 [AIM PAPER 89-29051 p 666 A89-47165 [ AD-A1945971 p 693 N89-25241
c-1 General Accounting Office CORPORA TE SOURCE
FAA (Federal Aviation Administration)aviation forecasts Kansas Univ. Center for Research, Inc.. Lawrence. The spatially non-uniformconvergence of the numerical Fiscal years 1989-2000 Spanwise lift distnbutions and wake velocity surveys of solutions of flows p 699 A89-45535 [AO-A2067161 p 638 N89-25948 a semi-span wing with a disconbnuous twist Interaction of an oscillating vortex with a turbulent FAA rotorcraft research, engineering and development [ NASA-CR-1775321 p 653 N89-25122 boundary layer p 645 A89-45906 bibliography. 1962-1988 Supplement Arranging computer architectures to create [ADA2071621 p 673 N89-26000 higher-performancecontrollers p 71 1 A89-46147 L Two-dimensional computations of multi-stage Lawrence Livermore National Lab., CA. compressor flows using a zonal approach G Preventing depletion of stratospheric ozone: [AIAA PAPER 89.24521 p 647 A89-46840 implications on future aircraft emissions Large-scale wind tunnel tests of an ejector-lift STOVL General Accounting Office, Washington, DC. [ DE89-009964] p 710 N89-25530 aircraft model Strategic bombers 6-16 cost and performance remain Lockheed Aeronautical Systems Co.. Burbank, CA. [AIAA PAPER 89-29051 p 666 A89-47165 uncertain Composite sizing and ply orientation for stiffness Flap-lagstability datalor a small-scaleisolated hingeless [ AD-A2067511 p 673 N89-25998 requirements using a large finite element structural rotor in forward flight General Dynamics Corp., Fort Worth, TX. model p 705 N89-25166 [ NASA-TM-1021891 p 706 N89-25479 Aerolastic tailoring and integrated wing design Logistics Management Inst., Betheada, MD. The acoustics of a small-scale helicopter rotor in p 668 N89-25167 Aircraft sustainability model version 1.5: Users manual hover Recent experiences using finite-element-based [AD-A207015] p 638 N89-25949 [NASA-TM-l010581 p 655 N89-25954 structural optimization p 705 N89-25177 Loral Defense Systems, Akron, OH. Performanceand loads data from an outdoor hover test General Electric Co., Cincinnati, OH. Analysis of low Reynolds number separation bubbles of a Lynx tail rotor A static investigation of several STOVL exhaust system using semiempincal methods p 652 A89-47351 [ NASA-TM-1010571 p 656 N89-25958 LTV Aerospace and Defense Co.. Dailaa, TX. conc e p 1 s Analysis of severe atmospheric disturbancesfrom airline [AIAA PAPER 89-29281 p 684 A89-47180 The designer the 90s: A live demonstration of flight records p 705 N89-25164 George Washington Univ., Hampton, VA. [ NASA-TM-I021 861 p 658 N89-25977 Parametnc study of a simultaneous pitchlyaw thrust Controller evaluations of the descent advisor automation vectonng single expansion ramp nozzle M aid (AIAA PAPER 89-28121 p 682 A89-47098 [NASA-TM-1021971 p 659 N89-25981 George washington Univ., Washington, DC. Manchester Univ. (England). A long-range laser velocimeter for the National Probabilistic damage tolerance methods for metallic An initial assessment of the impact of boundary layer Full-Scale Aerodynamics Complex: New developments aerospace structures p 672 N89-25237 control on SST and experimental application Georgia Inst. of Tech., Atlanta. [ AERO-REPT-88021 p 656 N89-25969 [NASA-TM-I01081] p 708 N89-26207 Optimization of rotor blades for combined structural, An introduction to the problem of aerodynamic heating National Aeronautics and Space Administration. Flight performance, and aeroelastic characteristics [AERO-REPT-8901I p 656 N89-25970 Research Center, Edwards, CA. p 667 N89-25153 A preliminary investigation into Euler methods for Current flight test experience related to structural TRUSS An intelligent design system for aircraft wings application to multielement aerofoils for high lift divergence of forward-swept wings p 663 A89-45141 p 711 N89-25162 [AERO-REPT-87101 p 708 N89-26196 National Aeronautics and Space Administration. Hugh The role of optimization in the next generation of Maryland Univ., College Park. L. Dryden Flight Research Center, Edwards, CA. computer-baseddesign tools p 712 N89-25220 Efficient sensitivity analysis and optimization of a Measurement effects on the calculatiopn of in-flight Grumman Aerospace Corp.. Bethpage, NY. helicopter rotor p 668 N89-25155 thrust for an F404 turbofan engine Applications of integrated designlanalysis systems in Massachusetts inst. of Tech., Cambridge. [AIAA PAPER 89-23641 p 677 A89-46777 aerospace structural design p 666 N89-25147 Nonlinear and adaphve control National Aeronautics and Space Administration. Hugh [ NASA-CR-1800881 p 712 N89-26610 L. Dryden Flight Research Facility, Edwards, CA. Massachusetts Inst. of Tech., Lexington. Preliminary development of an intelligent computer H Selected wind shear events Observed during the 1987 assstanl for engine monitoring evaluation of enhancements to the FAA (Federal Aviation [AIAA PAPER 89.25391 p 674 A89-46910 Administration) low level wind shear alert system at Hall (David) Conauitlng, Sunnyvale, CA. Control surface spanwise placement in active fluner Development of a microcomputer based integrated Stapleton International Airport [AD-A206711] p 710 N89-26323 suppression systems p 689 N89-25195 design system for high altitude long endurance aircraft National Aeronautics and Space Administration. p 668 N89-25159 McDonneil-Douglas Astronautics Co., Saint Louis, MO. Average-passage smulation of counter-rotating propfan Lyndon B. Johnson Space Center, Houston, TX. High Technology Corp., Hampton, VA. propulsion systems as applied to cruise missiles Applications of fuzzy sets to rule-based expert system Wind-tunnel investigations of wngs wth serrated sharp [ AlAA PAPER 89-2943 p 651 A89-47187 development p 712 N89-26606 trailing edges p 641 A89-45262 1 McDonnell-Douglas Corp., Long Beach, CA. National Aeronautics and Space Administration. HOMAR A computer code for generating homotopic An overview 01 the Douglas Aircraft Company Langley Research Center, Hampton, VA. gnds uslng algebraic relations User's manual Aeroelastic Design Optimization Program (ADOP) A high speed data acquisition system for the analysis [ NASA-CR-42431 p 708 N89-26176 p 671 N89-25221 of velocity. density. and total temperature fluctuations at Meeting the challenges with the Douglas Aircraft transonic speeds Company Aeroelastic Design Optimization Program [SAE PAPER 8814511 p 691 A89-45248 I (ADOP) p 671 N89-25222 A new look at wind tunnel flow quality for transonic McDonnell-Douglas Helicopter Co., Mesa, AZ. flows IIT Research Inat., Bartiesvlile, OK. Transonic airfoil design for helicopter rotor [SA€ PAPER 8814521 p 692 A89-45249 Comparisons between unleaded automobile gasoline applications p 667 Nag-25154 Studies of vortex flow aerodynamics using CFD flow and aviation gasoline on valve seat recession in light Multi-obiecttvelloading optimization for rotating visualizations p 641 A89-45260 aircraft engines composite flexbeams p 668 N89-25157 Wind-tunnel investigations of wings with serrated sharp [NIPER-409] p 697 N89-26110 Computerized Design Synthesis (CDS). A trailing edges p 641 A89-45262 iilinoia Univ., Chicago. database-drivenmultidisciplinary design tool international Conference on Numerical Methods in Fluid Review of FD-TD numerical modelingof electromagnetic p 712 N89-25180 Dynamics. 1Ith. Williamsburg, VA. June 27-July 1. 1988, wave scattering and radar cross Section Mississippi State Univ., Mississippi State. Proceedings p 699 A89-45351 p 673 A89-45107 Transonic flow solutions on general 3D regions using Computational fluid dynamics - A personal view Institut Franc-Allemand de Recherches, Saint-Louis composite-block grids p 644 A89-45428 p 699 A89-45352 (France). Missouri Univ., Columbia. CFD for hypersonic airbreathing aircraft Vortices and pressure waves at plates, cylinders and Multilevel decomposition of complete vehicle p 641 A89-45355 mnd profiles configuration in a parallel computing environment A natural low-frequency Oscillation of the flow over an [ ISL-R-1021881 p 656 N89-25966 p 870 N89-25205 airfoil near stalling conditions p 645 A89-45437 Testing of reliability . Analysis tools Institute for Computer Applications in Science and p 702 A89-46503 Engineering, Hampton, VA. Supersonic jel noise and the high speed civil transport International Conference on Numerical Methods in Fluid N IAIAA PAPER 89-2358) p 712 A89-46772 Dynamics, 1lth, Williamsburg. VA. June 27-July 1, 1988, Proceedings p 699 A89-45351 National Aeronautical Lab., Bangalore (India). Noise considerations for tiltrotor On the stress problem of the pebble bed heat exchanger [AlAA PAPER 89.23591 p 665 A89-46773 in a hypersonic wind tunnel Nacellelpylon interference study on a 1117th-scale. twin-engine, low-wing transport model J [ NAL-TM-ST-87051 p 693 N89-25240 [AIAA PAPER 89-24801 p 665 A89-46864 National Aeronautics and Space Administration, Joint inst. for Advancement of Flight Sciences, Evaluation of parallel injector configurations for Washington, DC. supersonic cornbustion Hampton, VA. Integrated controls pay-off [AiAA PAPER 89-25251 p 678 A89-46898 Evaluation of parallel iniector configurations for [AlAA PAPER 89-27041 p 688 A89-47031 Experiences with a prevalidation methodology for supersonic combustion National Aeronautics and Space Administration. Ames (AIAA PAPER 89-25251 p 678 A89-46898 designing integratedlpropulsion control system Research Center, Moffett Field, CA. architectures Numerical simulations of oblique detonations in [AIAA PAPER 89.27031 p 688 A89-47030 K supersonic combustion chambers p 674 A89-44115 Mixing enhancement in a supersonic combustor Accurate simulation of vortical flows [AIM PAPER 89.27941 p 681 A89-47088 Kansas Univ., Lawrence. p 643 A89-45384 Parametric study of a simultaneous pitchlyaw thrust Design optimization of axisymmetrlc bodies in Numerical study of unsteady viscous hypersonic blunt vectoring single expansion ramp nozzle nonuniform transonic flow p 670 N89-25206 body flows with an impinging shock p 643 A89-45394 [AIAA PAPER 89-28121 p 682 A89-47098 c-2 CORPORA TE SOURCE Technische Hochschule
A static investigation of several STOVL exhaust system Integrated flightlpropulsion control study for STOVL Notre Dame Univ., IN. concepts applications Analysis of low Reynolds number separation bubbles [AIAA PAPER 89-29281 p 684 A89-47180 [AIAA PAPER 89-29081 p 688 A89-47166 using semiempirical methods p 652 A69-47351 Effect of milling machine roughness and wing dihedral Transmission overhaul and replacement predictions on the supersonic aerodynamic characteristicsof a highly using Weibull and renewal theory swept wing [AIAA PAPER 89-29191 p 704 A89-47173 0 [ NASA-TP-29181 p 652 N89-25117 Investigation of low NOx staged combustor concept in Ohio State Univ., COlumbU8. Recent Advances in Multidisciplinary Analysis and high-speed civil transport engines Compressibility and shock wave interaction effects on Optimization. part 1 [AIAA PAPER 89-29421 p 684 A69-47186 free shear layers [NASA-CP-3031-PT-1] p 666 N89-25146 Average-passagesimulation of counter-rotatingpropfan [AIAA PAPER 89-24601 p 648 A89-46647 Overview of Dynamics Integration Research (DIR) propulsion systems as applied to cruise missiles Ohlo Unlv., Athens. program at Langley Research Center [AIAA PAPER 89-29431 p 651 A89-47187 An experimental investigation of high Iiftlhigh rate p 667 N89-25150 Selection of rolling-element bearing steels for long-life aerodynamics of an unsteady airfoil An initiative in multidisciplinary optimization of applications p 704 A89-47250 [ADA2069641 p 656 N69-25964 rotorcraft p 667 N89-25151 Numerical analysis of supersonic flow through oscillating Oklahoma Unlv.. Norman. Structural optimization of rotor blades with integrated cascade sections by using a deforming grid Integration of scramjets with waverider configurations dynamics and aerodynamics p 668 N89-25156 p 653 N89-25119 [ NASA-TM-I020531 [AIAA PAPER 89-26751 p 695 A69-47005 Integrated aerodynamic-structural design of a Low-speed wind tunnel performance of high-speed Old Domlnion Unlv., Norfolk, VA. forward-swept transport wing p 669 N89-25168 counterrotationpropellers at angle-of-attack Unsteady transonic airfoil computation using implicit Effects of nonlinear aerodynamics and static [ NASA-TM-1022921 p 653 N89-25121 Euler scheme on body-fixedgrid p 652 A89-47358 aeroelasticity on mission performance calculations for a Structural tailoring of counter rotation propfans fighter aircraft p 669 N69-25170 p 685 N89-25165 Optimum design of swept-forward high-aspect-ration Fuel properties effect on the performance of a Small P graphite-epoxy wings p 669 N89-25172 high temperature rise combustor Recent Advances in Multidisciplinary Analysis and [ NASA-TM-1020961 p 685 N89-25238 Pennsylvania State Unlv., Unlverslty Park. Optimization, part 2 In-flight measurement of propeller noise on the fuselage An expenmental study of the effect of streamwise [ NASA-CP-3031-PT-21 p 669 N89-25173 of an airplane vorticity on supersonic mixing enhancement Results of including geometric nonlinearities in an [ NASA-TM-1022851 p 713 N89-25675 [AIAA PAPER 89-24561 p 648 A89-46643 aeroelastic model of an FIA-I8 p 669 N89-25190 Influence of thickness and camber on the aeroelastic Plannlng Research Corp., Hampton, VA. Flutter suppression using eigenspace freedoms to meet stability of supersonic throughflow fans: An engineering Digital robust control law synthesis using constrained requirements p 689 N89-25191 approach optimization p 689 N89-25193 Aeroelastic modeling for the FIT (Functional Integration [ NASA-TM-1019491 p 656 N69-25957 Pratt and Whltney Aircraft Group, East Hartford, CT. Technology) team FIA-18 simulation Aeronautical applications of high-temperature Application of a multi-stage3-D Euler solver to the design p 670 N89-25192 superconductors of turbines for advanced propulsion systems Finite element flow-thermal-structural analysis of [NASA-TM-10231I] p 686 N89-26008 [AIAA PAPER 89-25781 p 679 A89-46936 aerodynamically heated leading edges Integrated flightlpropulsioncontrol system design based Pratt and Whltney Aircraft Group, Weat Palm Beach, p 655 N89-25198 on a centralized approach FL. Recent Advances in Multidisciplinary Analysis and [NASA-TM-1021371 p 690 N89-26009 Application of a multi-stage3-D Euler solver to the design Optimization. part 3 CFD in the context of IHPTET The Integrated High of turbines for advanced propulsion systems [ NASA-CP-3031-PT-31 p 670 N89-25201 Performance Turbine Technology Program [AIAA PAPER 89-25781 p 679 A89-46936 Hypersonic airbreathing vehicle conceptual design [NASA-TM-102132] p 708 N89-26174 PRC Systems Servlces Co., Edwards, CA. (focus on aero-space plane) p 670 N89-25210 Computational structural mechanics for engine Preliminary development of an intelligent computer Optimizing conceptual aircraft designs for minimum life structures assistant for engine monitoring cycle cost p 670 N89-25211 [NASA-TM-1021191 p 709 N89-26259 [AIAA PAPER 89-25391 p 674 A89-46910 Time-correlatedgust loads using Matched-FilterTheory National Aeronautics and Space Administration. Purdue Univ., West Lafayette, IN. and Random-Process Theory: A new way of looking at Marahall Space Flight Center, Huntsville, AL. L2F 8 LDV velocimetry measurement and analysis of things Warm fog dissipation using large volume water sprays the 3-D flow field in a centrifugal compressor [NASA-TM-101573] p 671 N89-25232 [ NASA-CASE-MFS-25962-1I p 693 N89-25242 [AIAA PAPER 89-25721 p 648 A89-46933 An analytical sensitivity method for use in integrated Federal incentives for industrial modernization: Historical AeroseNoelastic tailoring for lateral control aerosewoelastic aircraft design review and future opportunities enhancement p 689 N89-25189 [NASA-TM-101583] p 690 N89-25239 [NASA-TM-1017851 p 714 N89-25764 Automated thermal mapping techniques using chromatic National Aerospace Lab., Tokyo (Japan). image analysis A numerical solution of transonic flow using S [ NASA-TM-1015541 p 706 N89-25443 discontinuous shock wave relationship Airfoil self-noise and prediction [ NAL-TR-9971 p 655 N89-25950 San Dlego State Univ., CA. [NASA-RP-12181 p 713 N69-25673 Longitudinal nonlinear aerodynamic model form for Aerodynamics of high-lift, low-aspect-ratio unswept Steady-state and transitional aerodynamic USE-STOL aircraft wings p 652 A89-47372 characteristicsof a wing in simulated heavy rain [ NAL-TR-9951 p 672 N69-25990 Xlentlflc Research Associates, Inc., Glastonbury, CT. [ NASA-TP-2932I p 655 N89-25951 The Schlieren Observation System installed in the NAL Solution of the incompressible Navier-Stokesequations Flutter suppression control law synthesis for the Active two-dimensional high-Reynolds number transonic wind using artificial compressibility methods Flexible Wing model tunnel and attempts to improve it p 641 A89-45366 [NASA-TM-1015841 p 690 N89-26010 [ NAL-TR-9641 p 693 N89-26015 Stanford Univ., CA. Langley rotorcraft structural dynamics program: Mechanisms of Endwall leakage flows and the Interaction of an oscillating vortex with a turbulent Background, status, accomplishments, plans associated losses in a linear turbine rotor cascade with boundary layer p 645 A89-45906 INASA-TM-1016161 p 709 N89-26273 blade tip-clearance Aircraft design Optimization with multidisciplinary Integrated structurelconlrol law design by multilevel [ NAL-TR-SBBT] p 708 N89-26168 performance criteria p 671 N89-25212 optimization National Transportation Safety Board, Washington, Sverdrup Technology, Inc., Cleveland, OH. [NASA-TM-101623] p 712 N89-26623 DC. Mach 5 inlet CFD and experimental results A new class of random processes with application lo General aviation accidents involving visual flight rules [AIAA PAPER 89-23551 p 647 A89-46769 helicopter noise flight into instrument meteorological conditions Large scale advanced propeller blade pressure [ NASA-CR-1850371 p 713 N89-26679 [PB89-917001] p 658 N89-25974 distributions - Prediction and data National Aeronautics and Space Administration. Lewis Naval Ship Research and Development Center, [AIAA PAPER 89-26961 p 650 A89-47026 Research Center, Cleveland. OH. Bethesda, MD. Average-passage simulation of counter-rotating propfan A natural lowfrequency oscillation of the flow over an Tipjet VTOL UAV (Vertical Takeoff and propulsion systems as applied to cruise missiles airfoil near stalling conditions p 645 A89-45437 LandingIUnmannedAerial Vehicle) summary. Volume 1: [AIAA PAPER 89-29431 p 651 A89-47167 A Newtonlupwind method and numerical study of shock A 1200 pound tipjet VTOL unmanned aerial vehicle. Part Turbofan engine control system design using the wavelboundary layer interactions p 645 A89-45468 1:Co nceptual design study of a 1200-pound vehicle LQGILTR methodology [NASA-CR-182303] p 685 N89-26004 Ceramic bearings for use in gas turbine engines [ ADA206738 I p 672 N89-25997 p 702 A89-46697 Nondestructive Testing Information Analysis Center, Systems Technology, Inc., Hawthorne, CA. Advanced piloted aircraft flight control system design Mach 5 inlet CFD and experimental results San Antonio, TX. methodology, Volume 1: Knowledge base [AIAA PAPER 89-23551 p 647 A89-46769 Nondestructive qualificationof UH-1 replacement parts: Completion enhancement [ NASA-CR-I81 726-VOL-11 p 690 N89-26013 Rectangular nozzle plume velocity modeling for use in [AD-A2066741 p 672 N89-25995 Advanced piloted aircraft flight control system design jet noise prediction Northrop Corp., Hawthorne, CA. methodology, Volume 2: The FCX flight control design [AIAA PAPER 89-23571 p 647 A89-46771 ASTROS A multidiscipllnary automated structural expert system Supersonic jet noise and the high speed civil transport design tool p 705 N89-25174 [ NASA-CR-161726-VOL-21 p 691 N89-26014 [AIAA PAPER 89.23581 p 712 A89-46772 Robust computer-aided Synthesis and optimization of New hypersonic facility capability at NASA Lewis linear multivariable control systems with varying plant Research Center dynamics via AUTOCON p 71 1 N89-25179 T [AIAA PAPER 89-25341 p 692 A89-46905 Automated structural optimization system (ASTROS): Aeroelastic analysis of prop fan blades with a User training workshop Technlon - Israel inst. of Tech., Haif8. semiempirical dynamic stall model [AD-A207090] p 709 N89-26267 Control surface spanwise placement in active flutter [AIAA PAPER 69-26951 p 703 A89-47025 Northwestern Univ.. Ev8ndOt1, IL. suppression systems p 689 N89-25195 Large scale advanced propeller blade pressure Review of FD-TD numerical modeling of electromagnetic Technlsche Hochschule, Aachen (Germany, F.R.). distributions - Prediction and data wave scattering and radar cross section Vortex flows in flying technique [AIAA PAPER 69-26961 p 650 A89-47026 p 673 A89-45107 [ ETN-89.944281 p 653 N89-25126 c-3 Technische Univ. CORPORA TE SOURCE
Unsteady phenomena on delta wings with partially Ouantitatlve charactenzahon of a nonreacting. broken-down vortex regions p 654 N89-25129 supersonic combustor flowfield using unified. laser-induced Strongly unsteady vortex fields a1 elastic helicopter rotor iodine fluorescence blades p 654 N89-25131 [AIM PAPER 89-25651 p 703 A89-46928 Vortex structures in the wake of transonic flow about profiles p 654 N89-25134 W Flow about trailing edges in unsteady flow p 654 N89-25135 Washington Unlv.. Seattle. Effect of mnglets on loading mechanics and wing Further experiments on supersonic turbulent flow assembly reactions p 654 N89-25137 development in a square duct p 652 A89-47357 Damping of wing tip vortex systems by the modification Wlnzen Internatlonal, Inc., San Antonio, TX. of the mng tips p 654 N89-25138 Long duration balloon technology survey, phase 1 Mechanical reachon of wings moving through a vortex [AD-A206975] p 656 N89-25965 region p 654 N89-25139 Worcester Polytechnic Inst.. MA. Structural loading and noise disturbance of helicopters Treatment of body forces in boundary element design p 713 N89-25140 sensitivity analysis p 705 N89-25187 Flight-mechanicalinvestigations of the lateral motion of configuraeons mlh winglets p E89 N89-25141 Technlsche Unlv.. Berlin (Germany, F.R.). Reduction of aircraft noise in civil air transport by opbmization of flight tracks and takeoff and approach procedures [ ILR-MITT-2001 p 71 3 N89-25676 Technische Univ.. Delfl (Netherlands). Development and application of a computer-based system for conceptual aircraft design (ETN-89 948861 p 673 N89-26001 Test Wing (4950th). Wright-Patterson AFB, OH. EC18BlBoeing 707 Smoke Venting flight test [ AD-AZWl] p 659 N89-25979 Textron Lycoming, Stratford, CT. Threedimensional multigrid Naner-Stokes computations for turbomachinery applications [AIAA PAPER 89.24531 p 702 A89-46841 Procedures for shape optimization of gas turbine disks p 685 N89-25207 Tokdo Univ., OH. Aeroelastic analysis of prop fan blades mth a semiempirical dynamic stall model [AIAA PAPER 89-26951 p 703 A89-47025 Rarefied gas flow through twodimensional nozzles [AIM PAPER 89.28931 p 650 A89-47156 Toronto Unlv., Downsview (Ontarlo). Flow characteristics about a trailing edge [UTIASTN-270] p 655 N89-25952 U United Technologles Corp., West Palm Beach, FL Integrated flightlpropulsion control study for STOVL applications [AIAA PAPER 89-29081 p 688 A89-47166 United Technologles Research Center, East Hartford, CT. Two-dimensional computations of multi-stage compressor flows using a zonal approach [AIAA PAPER 89.24521 p 647 A89-46840 Three dimensional flow and temperature profile anenuation in an axial flow turbine [AD-A206736] p685 N89-26005 Noise produced by turbulent flow into a rotor Theory manual for noise calculation [NASA-CR 1817881 p714 N8926683 Unlverslty Coll. of Swansea (Wales). Adaptwe numerical solutions of the Euler equations in 3D using finite elements p 644 A89-45413 v Vlgyan Research Associates. Inc., Hampton, VA. A high speed data acquisition system for the analysis of velocity. density. and total temperature fluctuations at transonic speeds [SAE PAPER 881451I p 691 A89-45248 Studies of vortex flow aerodynamics using CFD flow visualizations p 641 A89-45260 Nacellelpylon interference study on a 1Il7th-scale hn-engine. low-wing transport model [AlAA PAPER 89-24801 p 665 A89-46864 Virginla Polytechnic Inst. and State Unlv., Blacksburg. Low angle injection into a supersonic flow [AIM PAPER 89-24611 p648 A89-46848 Improved plasma torch for ignition and flame holding in supersonic combustion [AIAA PAPER 89-29451 p 704 A89-47189 Relaxation oscillations in aircralt cruise-dash optimization [AD A2067221 p 672 N89-25996 State space models for aeroelastic and viscoelastic systems [AD-A207092] p690 N89-26012 Virginia Unlv.. Charlottesvilk. Initial supersonic combustion facility measurements [AIAA PAPER 89-24621 p 692 A89-46849 c-4 FOREIGN TECHNOLOGY INDEX I I AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245) November 1989
Experimental research on swirling combustion Dassault, leader in European military and business efficiency p 675 A89-45558 aircraft p 637 A89-45033 Typical Foreign Technology A dynamic digital model for the turbojet with The SNECMA group today and tomorrow Index Listing pulse-monitoredfueler p 675 A89-45559 p 637 A89-45034 Investigation on unsteady flow field and endwall From avionics technology to architectural concepts boundary layer in axial flow compressor with hot-wire p 637 A89-45035 anemometer p 645 A89-45560 French aerospace research in the international Measurement of three-dimensional flow in context p 691 A89-45036 turbomachinery with a single slanted hot-wire Aeronautical research in the European future INTELLECTUAL p 700 A89-45561 p 638 A89-45037 Effects of axial velocity density ratio on cascade The ACE/Rafale p 662 A89-45041 performances p 645 A89-45565 European gas turbine engines p 675 A89-45042 Experimental investigation on characteristics of single Airbus .The new families p 662 A89-45043 CANADA and tandem blade cascades with double-circular arc The systems of the future Airbus A330 and A340 Qualification and operational aspects of light weight profile p 676 A89-45567 aircraft p 662 A89-45044 SKAD (light weight survival kit airdroppable) Study of nonlinear Duffing characteristicsdf flexible rotor Helicopter blades p 640 A89-45045 D 18 A89-10471 with SFDB p 700 A89-45568 Economic aspects of simulation in air transportation r p 691 A69-45047 Experimental investigation of aeroengine high-speed I roller bearing p 700 A89-45570 Simulation methodology for helicopter automatic flight /-rThe ATR/RJ engine performance at constant dynamic control systems p 686 A89-45048 pressure and the consideration of transition condition A new variational method for the generation of two- and p 694 A89-46016 three-dimensional adapted grids in computational fluid The investigation of jet engine starting dynamics p 676 A89-46025 (ONERA, TP NO 1989-31I p 641 A69-45187 Differencemethods for initial-boundary-valueproblems Study of flow and heat transfer in rotating cavrties and flow around bodies (Revised edition) [ONERA. TP NO 1989.331 p 698 A89-45188 Listings in this index are arranged alphabetically p 646 A89-46198 Infrared and millimeter wave acquisition system by country of intellectual origin. The title of the Local analytical methods for digital simulation of [ONERA, TP NO 1989-361 p 699 A89-45191 document is used to provide a brief description of dynamical control system p 71 1 A89-46244 Computation of hypersonic vortex flows with an Euler An integrated design computational method for the wing model p 642 A89-45368 the subject matter. The page number and the ac- optimization camber and twist at subsonic and supersonic Low-storage implicit upwind FEM schemes for the Euler cession number are included in each entry to assist flow p 646 A89-46256 equations p 642 A89-45375 the user in locating the citation in the abstract sec- The research of 2-D flexible wall self-correcting wind Vortices and pressure waves at plates, cylinders and wind profiles tion. If applicable, a report number is also included tunnel p 692 A89-46258 Experimental study of vortex and aerodynamic [ ISL-R-l02/88] p 656 N89-25966 as an aid in identifying the document. characteristics of stack wings with sideslip p 646 A89-46259 Flow characteristics in an S-shaped rectangular-round G diffuser at high incidence p646 A89-46260 Design and analysis of airfoils in transonic viscous GERMANY,FEDERAL REPUBLIC OF flow p 646 A89-46262 Developmentand verification of software for flight safely critical strapdown systems p 659 A89-43827 Radiative characteristics Of hypersonic cone wake B p 646 A89-46263 New Kalman filter algorithms for hybrid navigation, The computed results of airfoil near the freestream Mach flightpath computation and inertial geodesy BELGIUM number one p 646 A89-46266 p 659 A89-43828 Recent developments in calculation methods for The induced power based on leading edge suction for Jet or prop required for future regional transports? turbomachines p 697 A89-44635 a helicopter in hovering p 646 A89-46267 p 637 A89-44641 Optimizationdesign for suppressing 'ground resonance' Technology of Structures maintains high standards of helicopters p 664 A89-46278 p 637 A89-44642 C The solutmn of 3-0 temperature distribution in a cycling Dornier's role in the 'European Fighter Aircraft' EFA oil cooled aircraft ac generator by network topology program p 637 A89-44643 CANADA method p 701 A89-46282 The phased establishment of support maturity for the The military Dash 8 flight test program The analysis and measurements of radar cross section European Fighter Aircraft (EFA) p 637 A89-44644 p 664 A89-45145 (RCS) of some wing structure models Stealth technology for reducing aircraft recognition p 673 A89-44645 Annals of air and space law. Volume 13 p 674 A89-46298 p 714 A89-45175 Crack shape identificationas an inverse boundary value problem p 698 A89-44663 Three dimensional finite element stress predictions of Low cost equipment for flight test film and video spur gears compared to gear fatigue rig measurements E evaluation p 698 A89-45137 [AIAA PAPER 89.29181 p 704 A89-47172 EGYPT Computation of viscous unsteady compressible flow Reduction of 1-P aerodynamic loads on tractor aircraft Combustion characteristics of gaseous flames in a gas about airfoils p 642 A89-45378 engine installations turbine combustor Simulation of inviscid hypersonic real gas flows [AlAA PAPER 89.29241 p 651 A89-47177 [AIAA PAPER 89-28921 p683 A8947155 p 644 A89-45414 Flow characteristics about a trailing edge Navier-Stokes Simulation of transonic flow about wings [ UTIAS-TN-2701 p 655 N89-25952 using a block structured approach p 644 A89-45422 CHINA, PEOPLES REPUBLIC OF F The EEC supports air transport research Transonic cascade flow solved by the combined p 638 A89-46078 shock-capturing and shock-fittingmethod FRANCE Ducted ultra-high bypass engine configuration Solution of Euler e uations by a finite element method p 639 A89-44114 definition application to supersonic flows p 639 A89-44319 Research and application of a new kind of measurement [AIAA PAPER 89.24781 p 67.8 A89-46862 Present state of the theory of secondary flows and technology of take-off and landing performance Technology readiness for advanced ducted engines expenmental venfications p 698 A89-44636 p 698 A89-45144 p 678 A89-46863 Prediction of the stability limit of multistage axial [AIM PAPER 89-24791 Nonisentropic potential calculation for 2-D and 3-0 High performance gear systems and heat management transonic flow p 645 A89-45434 compressors p 640 A89-44637 Prediction of turbomachinery performance - Application for advanced ducted systems Application of the boundary element method to unsteady to a centnfugal pump, a centnfugal compressor, and a [AIM PAPER 89-24821 p 678 A89-46865 heat transfer problems p 700 A89-45552 radial inflow turbine p 640 A89-44638 Configuration studies for a regional airliner using Effects of fuel chemical properties on exhaust smoke Theoretical and expenmental study of turbine open-rotor ultra-high-bypass-ratioengines from gas turbine combustor p 695 A89-45554 aerodynamics p 640 A89-44639 [AIAA PAPER 89-25801 p 666 A89-46937 An experimental research on mixture pressure loss in Design of vane tips improving axial compressor The influence of Swirl and fuel composition of combustor p 675 A89-45556 performance p 640 A89-44640 boron-containingfuels on combustion in a solid fuel ramjet Cold flow measurements for a double swirler Aerospatiale's short-term and intermediate-term place combustion chamber combustor p 675 A89-45557 in the international scene D 637 A89-45032 [AIAA PAPER 89-28851 p 683 A89-47150
D- 1 INDIA FOREIGN TECHNOLOGY INDEX
Two-dimensional elliptic grid generation for airfoils and Accurate simulation of vortical flows SWITZERLAND cascades p 643 A89-45384 Calculation of the total pressure loss coefficient with [ DFVLR-FB-88-52] p 653 N89-25125 Inviscid and viscous flow simulations around the three models for four supersonic axial-flow compressors Vortex flows in flying technique Onera-M6 by NDschemes p 644 A89-45425 p 640 A89-44898 1 ETN-89-944281 p 653 N89-25126 Performance analysis of scramlet engines Steady-state and time-dependent aerodynamics in an Unsteady phenomena on delta wings with partially p 676 A89-46600 annular turbine cascade operating at high subsonic Mach broken-down vortex regions p 654 N89-25129 Behavior of vortex street in the wake behind a circular numbers cylinder under controlled excitation p 646 A89-46694 Strongly unsteady vortex fields at elastic helicopter rotor [AIAA PAPER 89-29411 p 651 A89-47185 Gust generation in a wind-tunnel and estimation of the blades p 654 N89-25131 model p 692 A89-46696 Vortex structures in the wake of transonic flow about T-4 inlet/engine compatibility flight test results T profiles p 654 N89-25134 [AIAA PAPER 89.24661 p 665 A89-46853 Flow about trailing edges in unsteady flow Effectiveness of plasma torches for ignition and TAIWAN p 654 N89-25135 flameholding in scramlet A knowledge-based en route monitor for air traffic Effect of winglets on loading mechanics and wing [AIM PAPER 89-25641 p 679 A89-46927 control p 660 A89-45065 assembly reactions p 654 N89-25137 A comparison of scramlet engine performances of Full scale fatigue crack growth test of advanced jet Damping of wing tip vortex systems by the modification various cycles trainer AT-3 p 664 A89-45207 of the wing tips p 654 N89-25138 [AIAA PAPER 89.26761 p A89-47006 680 Isoparametnc shear spring element applied to crack Mechanical reaction of wings moving through a vortex Mach 4 testing of scramlet inlet models patching and instability p 699 A89-45208 region p 654 N89-25139 (AIM PAPER 89-26801 p649 A8947010 Structural loading and noise disturbance Of helicopters Numerical investigation of thrust-reversing nozzle using Surge and rotating stall in axial compressors an implicit NDscheme p 713 N89-25140 [AIMPAPER 89.26831 p 649 A89-47013 [AIAA PAPER 89-28991 p 683 A89-47162 Flight-mechanicalinvestigatlons of the lateral motion of Navier-Stokes simulations around a propfan using configurations with winglets p 689 N89-25141 higher-order upwind schemes Contnbutionsto the improvement of flight safety in wind [AIAA PAPER 89-26991 p 650 A89-47028 u shear A numerical solution of transonic flow using [ DFVLR-FB-88-49] p 658 N89-25144 discontinuous shock wave relationship U.S.S.R. Pressure measurement technique of WT-WK [ NAL-TR-9971 p 655 N89-25950 Computer Simulation of some types of flows arising at (DFVLR-MITT-88-111 p 693 N89-25243 Longitudinal nonlinear aerodynamic model form for interactions between a supersonic flow and a boundary Matenals and structures for 2000 and beyond An USE-STOL aircraft layer p 642 A89-45381 attempted forecast [ NAL-TR-9951 p 672 N89-25990 Modeling of controlled flight dynamics using in-flight [ DFVLR-MITT-89-02] p 706 N89-25358 The Schlieren Observation System installed in the NAL Simulators p 688 A89-46546 Reduction of aircraft noise in civil air transport by two-dimensional high-Reynolds number transonic wind Methods for the mathematical modeling of flight vehicle optimization of flight tracks and takeoff and approach tunnel and attempts to improve it engines p 71 1 A89-46551 procedures [NAL-TR-9641 p 693 N89-26015 Numencal and expenmental investigation of [ ILR-MITT-2001 p 713 N89-25676 Mechanisms of Endwall leakage flows and the airframe-integratedinlet for high velocities Prototype of a slant visual range measuring device associated losses in a linear turbine rotor cascade with [AlAA PAPER 89.26791 p 649 A89-47009 [ DFVLR-FB-88-42] p 713 N89-25697 blade tip-clearance UNITED KINGDOM A lifting surface method for the calculation of steady [ NAL-TR-985TI p 708 N89-26168 The mixing of three-dimensional turbulent wakes in and unsteady, incompressible propeller aerodynamics boundary layers p 639 A8943722 [ DFVLR-FB-89-04] p 657 N89-25972 Tupolev's new twin p 662 A89-43887 K llyushin goes the distance p 662 A89-43888 I In the drink p 691 A89-43890 KOREAWUTH) Navigation aids to aircraft all-weather landing Inviscid transonic flow over a wavy wall decaying p 659 A89-43891 INDIA downstream p 639 A89-44390 Evaluating ILS and MLS sites without flight tests Civil satellite navigation and location systems p 660 A89-43894 p 694 A69-43892 Dynamic stress analysis of rotating turbo-machinery N Ilyushin's new workhorse p 662 A89-44375 bladed-disk systems p 675 A89-44362 A study of AI-Li alloys using small angle neutron On the stress problem of the pebble bed heat exchanger NETHERLANDS scattering p 695 A89-44577 in a hypersonic wind tunnel The measurement of linear and angular displacements Rafale - Dassault's new dawn p 662 A89-45030 [ NAL-TM-ST-87051 p 693 N89-25240 in prototype aircraft - Instrumentation. calibration and Civil supersonics - Propulsion is the key INTERNATIONAL ORGANIZATION operational accuracy p 698 A89-45142 p 675 A89-45031 The 'nerve center' of ESA - Tasks and procedures of Fokker 100, some aspects of the development of the A flow-field solver using overlying and embedded the €SO€ in Darmstadt p 694 A89-43869 longitudinal control system p 687 A89-45161 meshes together with a novel compact Euler algorithm The links in the chain - The lnmarsat system Some aspects of interference on Loran-C p 641 A89-45359 p 697 A89-43876 p 660 A89-45221 A high resolution finite volume scheme for steady Airbus Industrie. lessons from experience Numerical Simulation of the flow about a wing with external transonic flow p 642 A89-45369 p 71 4 A89-45039 leading-edgevortex flow p 643 A89-45390 Adaptive numerical solutions of the Euler equations in ISRAEL Aerodynamic design and testing of Fokker 50 nacelle 3D using finite elements p 644 A89-45413 LOPAN - A low-order panel method for subsonic and and intake ducts Advanced propulsion systems for large subsonic supersonic flows p 639 A89-43724 [AIM PAPER 89-24831 p 665 A89-46866 transports Effects of bypass air on the combustion of boron Development and application of a computer-based [AIAA PAPER 89.2477) p 677 A89-46861 particles in a solid fuel ramjet system for conceptual aircraft design The Rolls Royce Allison RB580 turbofan - Matching the [AlAA PAPER 89-28861 p 683 A89-47151 [ ETN-89-948861 p 673 N89-26001 market requirement for regional transport ITALY NEW ZEALAND [AIAA PAPER 89.24881 p 678 A89-46869 Cost-effective approach to flight testing the 'Casmu Omega navigation in the shadow of Antarctica A technique for the measurementof blade tip clearance Skyshark a stand-off weapon dispenser D 660 A89-43893 in a gas turbine p 663 A89-45128 [AIAA PAPER 89.29161 p 683 A89-47170 Multidimensionaladaptive Euler solver Evaluation of novel igniters in a turbulent bomb facility p MI A89-45360 P and a tubannular gas turbine combustor Numerical codes for unsteady simulation of turbolet. [AIAA PAPER 89-29441 p 684 A89-47188 turbofan and turboprop engines for training purposes POLAND Normal impinging jet in crossflow - A parametric [AIAA PAPER 89-22591 p 676 A89-46704 Numerical modelling of flight dynamics and flight test investigation A validation of a Navier-Stokes 2D solver for transonic data identification of a jet trainer airplane [AIM PAPER 89-29571 p 684 A89-47199 turbine cascade flows p 663 A89-45139 Automation in transport aircraft - Current and future [AIAA PAPER 89-2451I p 647 A89-46839 trends Technology development required by propfan power [SAE PAPER 8814681 p 657 A89-47334 reduction gearboxes R Air traffic control - No easy solutions in a complex [AlAA PAPER 89-28181 p 703 A89-47104 terminal environment [SAE PAPER 8814691 p 661 A89-47335 ROMANIA (RUMANIA) Research in automation for air traffic control - United Reinforcing solutions for a panel cut-out Kingdom work and associated European projects J p 698 A89-45177 [SAE PAPER 8814701 p 661 A89-47336 JAPAN The influence of altitude and speed variations on the Airline operations and the contaminated runway Apparent strain charactenstics of strain gauges under aeroplane's load components in longitudinal nonlinear [SAE PAPER 8814601 p 658 A89-47339 high temperature environment p 697 A89-43844 manoeuvres p688 A8945179 Microwave landing system instrumentation - A pilot's Expenmental study on aerodynamic characteristics of viewpoint hypersonic transport configuration p 640 A89-44972 [SAE PAPER 8814611 p 661 A89-47340 A simple theory of aerospaceplane S UK airmisses involving commercial air transport p 662 A89-44975 [ CAA-3/88] p 658 N89-25143 Numerical study of the 3D separating flow about SWEDEN An initial assessment of the impact of boundary layer obstacles with sharp corners p MI A89-45363 Mechanical stresses dunng air transport and ground control on SST An implicit time-marching method for solving the 3-D operations p 700 A89-46221 [AERO-REPT-8802] p 656 N89-25969 compresslble Navier-Stokesequations SPAREL - A model for reliability and spanng in the world An introduction to the problem of aerodynamic heating p 642 A89-45374 of redundancies p 702 A89-46493 [AERO-REPT-89011 p 656 N89-25970
D-2 FOREIGN TECHNOLOGY INDEX UNITED KINGDOM
I A preliminary investigation into Euler methods for application to multi-element aerofoils for high lift [AERO-REPT-67101 p 708 N89-26196
D-3 CONTRACT NUMBER INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245) November 1989
Typical Contract Number Index Listing NAG1-886 ...... p695 A89-47005 506-43-41-01 ...... p666 N89-25146 ...... p712 N89-26610 p 669 N89-25173 NAG2-471 ...... p671 N89-25233 p 670 N89-25201 p 671 N89-25235 535-03-01 ...... p653 N89-25119 NAG3-577 ...... p650 A89-47156 p 713 N69-25675 NAG1-724 ...... p 44 N89-10125 NAG3-635 ...... 673 A8g-45107 535-05-01 ...... P685 N89-25238 992-21-01 ...... P706 Nag-25479 NAG3-645 ...... p708 N8g-26172 -I- /--I- ...... p648 A89-46847 ...... p644 A89-45428 ...... p706 N89-25432 NUMBER NUMBER NUMBER NAS1-17497 ...... p707 N89-25480 NAS1-17763 ...... NAS1-17987 ...... p 691 N89-26014 NAS1-18027 ...... p690 N89-26011 Listings in this index are arranged alphanumeri- cally by contract number. Under each contract number. the accession numbers denoting docu- ments that have been produced as a result of re- search done under the contract are arranged in ascending order with the AlAA accession numbers appearing first . The accession number denotes the number by which the citation is identified in the abstract section . Preceding the accession number is the page number on which the citation may be found .
AF PROJ. 2304 ...... p 690 N89-26012 AF PROJ. 2307 ...... p 656 N89-25964
AF-AFOSR-0312-87 ...... p 656 N89-25964 AF-AFOSR-87-0074 ...... p 644 A89-45415 ...... p652 A89-47351 p 643 A89-45404 N00014-81-K-0095 ...... p 649 A89-47004 N00014-83-C-9151 ...... p695 A89-44103 BMUNR-FB-88-105-05-501 ...... p 713 N89-25676 N00014-84-C-0354 ...... p639 A89-44112 DA PROJ. 4A1-62719-AT-40 ...... p 694 N89-26019 N00014-85-K-0646 ...... p652 A89-47373 N00014-86-K-0315 ...... p647 A89-46842 N00014-86-K-0468 ...... DAAL03-87-G-0004 ...... p 686 A89-45064 N00014-87-J-1130 ...... DLA900-84-C-0910 ...... p 672 N89-25995 N00014-87-K-0169 ...... p648 A89-46847 DRET-80-098 ...... p 640 A89-44637 N00014-89-J-1221 ...... p648 A89-46845 ...... p685 N89-25238 ...... p680 A89-46944 ...... p647 A69-46842 DTFA01-87-Z-02015 ...... p 694 N89-26020 N66001-88-D-0088 ...... p677 A89-46837 DTFA03-84-A-40020 ...... p 694 N89-26018 ...... p644 A89-45413 ...... p672 N89-25995 T-1007-A ...... p707 N89-26121 FO8635-83-C-0052 ...... p 695 A89-44103 W-7405-ENG-48 ...... p710 N89-25530 F08635-86-K-0390 ...... p 672 N89-25996 505-60 ...... p671 N89-25233 P 671 N89-25235 F19628-85-C-0002 ...... p 710 N89-26323 505-61-01 ...... p708 N89-26207 F30602-79-C-0039 ...... p 673 A89-45107 505-61-51 ...... p 704 A89-47168 p655 N89-25954 ...... p 674 A89-44113 p656 N89-25958 505-62-01 ...... p690 N89-26009 505-62-21 ...... p708 N89-26174 505-63-16 ...... p656 N89-25957 ...... p709 N89-26259 505-63-21-04 ...... p671 N89-25232 p 690 N89-25239 p690 N89-26010 p 712 N89-26623 505-63-51-01 ...... p707 N89-25480 p 709 N89-26273 505-63-51-06 ...... p713 N89-25673 505-63-51 ...... D714 N89-26683 505-66-01-02 ...... p690 N89-26013 p 691 N89-26014 N89-25961 505-66-41-01 ...... p690 N89-26011 505-66-41 ...... p658 N69-25977 N89-25951 N89-25973 505-69-01-01 ...... p652 N89-25117 NAGl -768 ...... p 713 N89-26679 505-69-61 ...... N89-26008 ...... p 692 A89-46849 505-80-11-05 ...... p708 N89-26176 ...... p 648 A89-46843 506-40-41-02 ...... p706 N89-25443
E- 1 REPORT NUMBER INDEX
I AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245) November 1989
Typical Report Number Index Listing AlAA PAPER 89-2331 ...... p 692 A89-46755 # AlAA PAPER 89-2704 ...... P 688 A89-47031 * # AlAA PAPER 89-2344 ...... p 647 A89-46763 * # AlAA PAPER 89-2705 ...... p 688 A89-47032 # AlAA PAPER 89-2355 ...... p 647 A89-46769 * # AlAA PAPER 89-2751 ...... p 681 A89-47061 # AIAA PAPER 89-2356 ...... p 676 A89-46770 # AlAA PAPER 89-2786 ...... p 703 A89-47083 # AlAA PAPER 89-2788 ...... p 681 A89-47084 # NUMBER AlAA PAPER 89-2357 ...... p 647 A89-46771 * # NUMBER AlAA PAPER 89-2794 ...... p 681 A89-47088 * # AlAA PAPER 89-2358 ...... p 712 A89-46772 * # AlAA PAPER 89-2798 ...... p 681 A89-47091 # AlAA PAPER 89-2359 ...... p 665 A89-46773 * # AIAA PAPER 89-2799 ...... p 681 A89-47092 # AlAA PAPER 89-2361 ...... p 676 A89-46774 # NASA-CR-183247 ...... P 42 N89-10900 ' # AlAA PAPER 89-2804 ...... p 681 A89-47094 # AIM PAPER 89-2362 ...... p 710 A89-46775 # AlAA PAPER 89-2812 ...... p 682 A89-47098 * # AlAA PAPER 89-2363 ...... p 677 A89-46776 # AlAA PAPER 89-2814 ...... p 682 A89-47100 # AlAA PAPER 89-2364 p 677 A89-46777 * # ...... AlAA PAPER 89-2815 ...... p 666 A89-47101 # AlAA PAPER 89-2368 ...... p 702 A89-46778 # AlAA PAPER 89-2816 ...... p 682 A89-47102 # NUMBER SPONSORED AlAA PAPER 89-2443 p 714 A89-46835 # ...... AlAA PAPER 89-2817 ...... p 682 A89-47103 # AlAA PAPER 89-2446 p 677 A89-46837 ...... # AlAA PAPER 89-2818 ...... p 703 A89-47104 # AlAA PAPER 89-2449 ...... p 677 A89-46838 # AlAA PAPER 89-2820 ...... p 682 A89-47106 # AlAA PAPER 89-2451 ...... p 647 A89-46839 # AlAA PAPER 89-2822 ...... p 682 A89-47107 # AlAA PAPER 89-2452 p 647 A89-46840 * # Listings in this index are arranged alphanumeri- ...... AlAA PAPER 89-2851 ...... p 682 A89-47125 # AlAA PAPER 89-2453 ...... p 702 A89-46841 * # AlAA PAPER 89-2884 ...... p 696 A89-47149 # cally by report number. The page number indicates AlAA PAPER 89-2454 p 647 A89-46842 ...... # AlAA PAPER 89-2885 ...... p 683 A89-47150 # !he page on which the citation is located. The ac- AlAA PAPER 89-2456 ...... p 648 A89-46843 * # AlAA PAPER 89-2886 ...... p 683 A89-47151 # cession number denotes the number by which the AlAA PAPER 89-2458 ...... p 648 A89-46845 # AlAA PAPER 89-2888 ...... p 683 A89-47153 # AlAA PAPER 89-2459 p, 703 A89-46846 ...... # AlAA PAPER 89-2892 ...... p 683 A89-47155 # citation is identified. An asterisk (') indicates that AlAA PAPER 89-2460 ...... p 648 A89-46847 * # AIAA PAPER 89-2893 ...... p 650 A89-47156 * # the item is a NASA report. A pound sign (#) indi- AlAA PAPER 89-2461 p 648 A89-46848 * ...... # A89-47160 * # cates that the item is available on microfiche. AlAA PAPER 89-2462 ...... A89-47162 # AlAA PAPER 89-2464 ...... p 677 A89-46851 # AlAA PAPER 89.2900 ...... p 704 A89-47163 # AlAA PAPER 89-2465 p 665 A89-46852 # ...... AlAA PAPER 89-2905 ...... p 666 A89-47165 * # AlAA PAPER 89-2466 ...... p 665 A89-46853 # A-89014 ...... p 656 N89-25958 * # AlAA PAPER 89-2908 ...... p 688 A89-47166 * # ...... p 655 N89-25954 * # AlAA PAPER 89-2467 ...... p 677 A89-46854 # AlAA PAPER 89-2914 ...... p 704 A89-47168 # ...... p 708 N89-26207 * # AlAA PAPER 89-2472 ...... p 703 A89-46858 # AlAA PAPER 89-2916 ...... p 683 A89-47170 # A-89111 ...... p 658 N89-25977 * # AlAA PAPER 89-2477 ...... p 677 A89-46861 # AlAA PAPER 89-2918 ...... p 704 A89-47172 # ...... p 706 N89-25479 * # AlAA PAPER 89-2478 ...... p 678 A89-46862 # AlAA PAPER 89-2919 ...... p 704 A89-47173 * # AlAA PAPER 89-2479 p 678 A89-46863 # ...... p 659 N89-25981 * # ...... AlAA PAPER 89-2924 ...... p 651 A89-47177 # AlAA PAPER 89-2480 p A89-46864 * # ...... 665 AlAA PAPER 89-2925 ...... p 683 A89-47178 # AlAA PAPER 89-2482 p 678 A89-46865 # AD-AI 94597 ...... p 693 N89-25241 # ...... AlAA PAPER 89-2927 ...... p 684 A89-47179 # AD-A20091 7 ...... p 638 N89-25113 # AlAA PAPER 89-2483 ...... p 665 A89-46866 # AlAA PAPER 89-2928 ...... p 684 A89-47180 * # AD-A206601 ...... p 659 N89-25979 # AlAA PAPER 89-2486 ...... p 666 A89-46867 # AlAA PAPER 89-2933 ...... p 704 A89-47181 # ...... p672 N89-25995 # AlAA PAPER 89-2487 ...... p 678 A89-46868 # AlAA PAPER 89-2939 ...... p 651 A89-47183 # ...... p 710 N89-26294 # AlAA PAPER 89-2488 ...... p 678 A89-46869 # AlAA PAPER 89-2940 ...... p 651 A89-47184 # AlAA PAPER 89-2525 p 678 A89-46898 * AD-A206710 ...... p 707 N89-26133 # ...... # AlAA PAPER 89-2941 ...... p 651 A89-47185 # AD-A206711 ...... P 710 N89-26323 # AlAA PAPER 89-2534 ...... p 692 A89-46905 ' # AlAA PAPER 89-2942 ...... p 684 A89-47186 * # AlAA PAPER 89-2537 p 692 A89-46908 AD-A206716 ...... P 638 N89-25948 # ...... # AlAA PAPER 89-2943 ...... p 651 A89-47187 * # AD-A206722 ...... P 672 N89-25996 # AlAA PAPER 89-2539 ...... p 674 A89-46910 * # AlAA PAPER 89-2944 ...... p 684 A89-47188 # AlAA PAPER 89-2559 ...... p 648 A89-46924 # AD-A206736 ...... p 685 N69-26005 # AlAA PAPER 89-2945 ...... p 704 A89-47189 * # AD-A206738 ...... p 672 N89-25997 # AlAA PAPER 89-2561 ...... p 679 A89-46926 # AlAA PAPER 89-2947 ...... p 684 A89-47191 # ...... p 673 N89-25998 # AlAA PAPER 89-2564 ...... p 679 A89-46927 # AlAA PAPER 89-2956 ...... p 684 A89-47198 # AlAA PAPER 89-2565 p 703 A89-46928 # ...... p 685 N89-26006 # ...... ' AlAA PAPER 89-2957 ...... p 684 A89-47199 # AD-A206964 ...... p 656 N89-25964 # AIM PAPER 89-2571 ...... p 679 A89-46932 # AD-A206975 ...... p 656 N89-25965 # AIMPAPER 89-2572 ...... p 648 A89-46933 * # AIAA-89-2583 ...... p 653 "39-25121 * # AlAA PAPER 89-2577 ...... p 648 A89-46935 # AD-A207015 ...... p 638 N89-25949 # AIAA-89-2805 ...... p 653 N89-25119 * # AD-A207059 ...... p 694 N89-26019 # AlAA PAPER 89-2578 ...... p 679 A89-46936 # AIAA-89-2901 ...... p 685 N89-25238 * # AlAA PAPER 89-2580 p 666 A89-46937 # AD-AZO7090 ...... AIAA-89-2904 ...... p 708 N89-26174 * # AlAA PAPER 89-2581 679 A89-46938 # AD-A207092 ...... p AIAA-89-3520 ...... p 690 N89-26009 * # ...... p 694 N89-26020 # AlAA PAPER 89-2582 ...... p 679 A89-46939 # ...... p 673 N89-26000 # AlAA PAPER 89-2584 ...... p 679 A89-46940 # APP-88-5 ...... p 693 N89-25241 # AlAA PAPER 89-2585 ...... p 680 A89-46941 # AD-DO13981 ...... p 671 N89-25234 AlAA PAPER 89-2586 ...... p 680 A8946942 # ATC-158 ...... p 710 AD-DO13988 ...... p 672 N89-25991 AlAA PAPER 89-2587 ...... p 703 A89-46943 # AD-DO14020 ...... p 709 N89-26240 AlAA PAPER 89-2589 ...... p 680 A89-46944 # AVSCOM-TR-89-12.004 ...... p 685 AlAA PAPER 89-2673 ...... p 649 A89-47003 # AD-E501097 ...... p 673 N89-26000 # AlAA PAPER 89-2674 ...... p 649 A89-47004 # CAA-3/88 ...... p 658 N89-25143 AlAA PAPER 89-2675 ...... p 695 A89-47005 * # AERO-REPT-8710 ...... p 708 N89-26196 # AlAA PAPER 89-2676 ...... p 680 A89-47006 # CDI-89-04 ...... p 657 N89-25973 * # AERO-REPT-8802 ...... p 656 N89-25969 # AlAA PAPER 89-2678 ...... p 649 A89-47008 # AERO-REPT-8901 ...... p 656 N89-25970 # AlAA PAPER 139-2679 ...... p 649 A89-47009 # CONF-890692-4 ...... p 710 N89-25530 # AlAA PAPER 89-2680 ...... p 649 A8947010 # AFATL-TP-89-03 ...... p 672 N89-25996 # AlAA PAPER 89-2681 ...... p 649 A89-47011 # N89-25530 # AlAA PAPER 89-2682 ...... p 666 A89-47012 # AFOSR-89-0380TR ...... p 690 N89-26012 # AlAA PAPER 89-2683 ...... p 649 A89-47013 # DFVLR-FB-88-42 ...... p 713 N89-25697 # ...... p 656 N89-25964 # AlAA PAPER 89-2684 ...... p 650 A89-47014 # DFVLR-FB-88-49 ...... p 658 N89-25144 # ...... p 685 N89-26005 # AlAA PAPER 89-2685 ...... p 680 A89-47015 # DFVLR-FB-88-52 ...... p 653 N89-25125 # AlAA PAPER 89-2686 .....,...... p 650 A89-47016 # DFVLR-FB-89-04 ...... p 657 N89-25972 # AFWAL-TR-88-3101 ...... p 709 N89-26267 # AlAA PAPER 89-2687 ...... p 650 A89-47017 # AFWAL-TR-89-2005 ...... p 685 N89-26006 # AlAA PAPER 89-2689 ...... p 680 A89-47019 # DFVLR-MITT-88-11 ...... p 693 N89-25243 # AlAA PAPER 89-2690 ...... p 693 A89-47020 # DFVLR-MITT-89-02 ...... p 706 "39-25358 # AlAA PAPER 88-0060 ...... p 674 A89-44108 # AlAA PAPER 89-2693 ...... p 680 A89-47023 # AlAA PAPER 89-2259 ...... p 676 A89-46704 # AlAA PAPER 89-2694 ...... p 681 A89-47024 # DOT/FAA/CT-TN87/41-REV ...... p 707 N89-26121 # AlAA PAPER 89-2260 ...... p 665 A89-46705 # AlAA PAPER 89-2695 ...... p 703 A89-47025 * # DOT/FAA/CT-TN87/54-VOL-l .... p 710 N89-26294 # AlAA PAPER 89-2696 ...... p 650 A89-47026 * # AlAA PAPER 89-2321 ...... p 702 A89-46748 # DOT/FAA/CT-TN88/39 ...... p 707 N89-26133 # AlAA PAPER 89-2698 ...... p 650 A89-47027 # AlAA PAPER 89-2323 ...... p 702 A89-46750 # AlAA PAPER 89-2699 ...... p 650 A89-47028 # DOT/FAA/CT-TN89/10 ...... p 658 N89-25142 # AlAA PAPER 89-2324 ...... p 676 A89-46751 # AlAA PAPER 89-2701 ...... p 688 A89-47029 # DOT/FAA/CT-TN89/20 ...... p 661 N89-25985 # AlAA PAPER 89-2325 ...... p 676 A89-46752 # AlAA PAPER 89-2703 ...... p 688 A89-47030 * # DOT/FAA/CT-TN89/22 ...... p 672 N89-25994 #
I F- 1 DOT/FAA/CT-TNII)/ 24 REPORT NUMBER INDEX
WT/FAA/CT-TN89/24 ...... p 707 N89-26127 # NAS 1.15:101058 ...... p 655 N89-25954 * # NIPER-409 ...... p 697 N89-26110 # WT/FAA/CT-TN89/31 ...... p 661 N89-25984 # NAS 1.15:101081 ...... p 708 N89-26207 * # WT/FAA/CT-TN89/33 ...... p 697 N89-26110 # NAS 1.15:101554 ...... p 706 N89-25443 * # NTSB/SR-89/01 ...... p 658 N89-25974 # WT/FAA/CT-TN89/36 ...... p 707 N89-26123 # NAS 1.15:101573 ...... p 671 N89-25232 ' # NAS 1.15:101583 ...... p 690 N89-25239 * # ONERA. TP NO. 1989-31 ...... p 641 A89-45187 # DOT/FAA/CT-88/31 ...... p 707 N89-26120 # NAS 1.15:101584 ...... p 690 N89-26010 * # ONERA. TP NO. 1989-33 ...... p 698 A89-45188 # WTIFAAICT-89114-VOL-2 ...... p 661 N89-25986 # NAS 1.15:101618 ...... p 709 N89-26273 * # ONERA. TP NO. 1989-36 ...... p 699 A89-45191 # WT/FAA/CT-89/4 ...... p 694 N89-26018 # NAS 1.15:101623 ...... p 712 N89-26623 * # WT/FAA/CT-89/9 ...... p 658 N89-25976 # NAS 1.15:101785 ...... p 714 N89-25764 * # PB89-917001 ...... p 658 N89-25974 # ...... p 656 N69-25957 * # WT/FAA/DS88/03 ...... p 694 N89-26020 # ...... p 653 N69-25119 * # REPT-4950/FTR-86-05-03 ...... p 659 N89-25979 # WT/FAA/DS-89/03 ...... p 673 N89-26000 # NAS 1.15:102096 ...... p 685 N89-25238 # WT/FAA/DS-89/05 ...... p 658 N89-25142 # NAS 1.15:102119 ...... p 709 N89-26259 * # SA€ P-216 ...... p 638 A89-47326 NAS 1.15:102132 ...... p 708 N89-26174 * # WT/FAA/PP-W/5 ...... p 693 N89-25241 # NAS 1.15:102137 ...... p 690 N89-26009 * # SAE PAPER 861451 ...... p 691 A89-45248 * NAS 1.15:102186 ...... p 658 N89-25977 * # SAE PAPER 861452 ...... p 692 A89-45249 * WTIFAA/PS88/9 ...... p 710 N89-26323 # NAS 1.15:102189 ...... p 706 N89-25479 * # SAE PAPER 881460 ...... p 658 A89-47339 NAS 1.15:102197 ...... p 659 N89-25981 * # SA€ PAPER 881461 ...... p 661 A69-47340 DTRCIAD-89/01 ...... p 672 N89-25997 # NAS 1.15:102285 ...... p 713 N89-25675 * # SAE PAPER 881468 ...... p 657 A89-47334 NAS 1.15:102292 ...... p 653 N89-25121 .# SA€ PAPER 881469 ...... p 661 A89-47335 D218N301 ...... p 658 N89-25976 # NAS 1.15:102311 ...... p 686 N89-26008 * # SA€ PAPER 881470 ...... p 661 A89-47336 NAS 1.26:177529 ...... p 671 N89-25233 * # E4642 ...... p 656 N89-25957 * # NAS 1.26:177530 ...... p 671 N89-25235 * # STI-TR-1228-1 ...... p 690 N89-26013 * # E4765 ...... p 685 N89-26004 * # NAS 1.26:177532 ...... p 653 N89-25122 * # STI-TR-1228-1 ...... p 691 N89-26014 * # €4805 ...... p 653 N89-25119 * # NAS 1.26180088 ...... p 712 N89-26610 * # E4857 ...... p 685 N89-25238 * # NAS 1.26:181726VOL-l ...... p 690 N89-26013 * # UCRL-99926 ...... p 710 N89-25530 # E4860 ...... p 690 N89-26009 * # NAS 1.26:181726-VOL-2 ...... p 691 N69-26014 * # E4868 ...... p 708 N89-26174 * # NAS 1.26:181787 ...... p 707 N89-25480 * # US-PATENT-APPL-SN-074802 ..... p 672 N89-25991 E4883 ...... p 653 N89-25121 * # NAS 1.26:181788 ...... p 714 N89-26683 * # US-PATENT-APPL-SN-107197 .._..p 709 N89-26240 E4898 ...... p 709 N89-26259 * # NAS 1.26:181842 ...... p 657 N89-25973 * # USPATENT-APPL-SN-633180 ..... p 693 N89-25242 * E4951 ...... p 686 N89-26008 * # NAS 1.26:182303 ...... p 685 N89-26004 * # US-PATENT-APPL-SN-928350 ..... p 671 N89-25234 E4952 ...... p 713 N89-25675 * # NAS 1.26:183649-PT-2 ...... p 706 N89-25464 * # NAS 1.26:185037 ...... p 713 N89-26679 * # USPATENT-CLASS-239-14.1 .._._.p 693 N89-25242 * ESA-TT-1145 ...... p 693 N89-25243 # NAS 1.26:185058 ...... p 706 N89-25432 * # US-PATENT-CLASS-239-2.1 ...... p 693 N89-25242 * NAS 1.26:185332 ...... p 708 N89-26172 * # USPATENT-CLASS-310-52 ...... p 709 N89-26240 ESL-TR-88-52 ...... p 694 N89-26020 # NAS 1.26:185347 ...... p 655 N89-25953 * # NAS 1.26:4243 ...... p 708 N89-26176 * # US-PATENT-4.779.017 ...... p 709 N89-26240 ETN-89-94326 ...... p 658 N89-25143 ...... p 690 N89-26011 * # US-PATENT4.761.326 ...... p 693 N89-25242 ' ETN-89-94428 ...... p 653 N89-25126 # ...... p 666 N89-25146 * # US-PATENT-4,784,355 ...... p 671 N89-25234 ETN-89-94560 ...... p 713 N89-25676 # NAS 1.55:3031-PT-2 ...... p 669 N89-25173 * # US-PATENT-4,790.137 ...... p 672 N89-25991 ETN-89-94632 ...... p 713 N89-25697 # NAS 1.55:3031-PT-3 ...... p 670 N89-25201 * # ETN-89-94635 ...... p 658 N89-25144 # NAS 1.60:2918 ...... p 652 N89-25117 * # USAAVSCOM-TR-89-A-M)3 ...... p 706 N89-25479 * # ETN-89-94638 ...... p 653 N89-25125 # NAS 1.60:2932 ...... o 655 N89-25951 * # ETN-89-94643 ...... p 693 N89-25243 # NAS 1.61:1218 ...... p 713 N89-25673 * # ...... p655 N89-25952 # ETN-89-94648 ...... p 706 N89-25358 # ETN-89-94853 ...... p 656 N89-25966 # NASA-CASE-MFS25962-1 ...... p 693 N89-25242 * WES/TR/GL-89-3 ...... p 694 N89-26020 # ETN-89-94886 ...... p 673 N89-26001 WES/TR/GL-89-5 ...... p 694 N89-26019 # ETN-89-94950 ...... p 708 N89-26196 # NASA-CP-3031-PT-1 ...... p 666 N89-25146 * # ETN-89-94953 ...... p 656 N89-25969 # NASA-CP-3031-PT-2 ...... p 669 N89-25173 * # Wll-9942-01-TR-01 ...... p 656 N89-25965 # ETN-89-94956 ...... p 656 N89-25970 # NASAGP-3031-PT-3 ...... p 670 N89-25201 * # ETN-89-94980 ...... p 657 N89-25972 # NASA-CR-177529 ...... p 671 N89-25233 * # FAA-APO-89-1 ...... p 638 N89-25948 # NASA-CR-177530 ...... p 671 N89-25235 * # NASA-CR-177532 ...... p 653 N89-25122 * # FDA-89-07 ...... p 708 N89-26172 * # NASA-CR-180088 ...... p 712 N89-26610 * # NASA-CR-181726VOL-1 ...... p 690 N89-26013 * # GAO/NSIAD-89-55 ...... p 673 N89-25998 # NASA-CR-181726VOL-2 ...... p 691 N89-26014 * # NASA-CR-181787 ...... p 707 N89-25480 * # ILR-MITT-200 ...... p 713 N89-25676 # NASA-CR-181788 ...... p 714 N89-26683 * # NASA-CR-181842 ...... p 657 N89-25973 * # ISL-R-102/88 ...... p 656 N89-25966 # NASA-CR-182303 ...... p 685 N89-26004 * # NASA-CR-183649-PT-2 ...... p 706 N89-25464 * # ISSN-0082-5263 ...... p 655 N89-25952 # NASA-CR-185037 ...... p 713 N89-26679 * # ISSN-0171-1342 ...... p 653 N89-25125 # NASA-CR-185058 ...... p 706 N89-25432 * # ISSN-0171-1342 ...... p 658 N89-25144 # NASAGR-185332 ...... p 708 N89-26172 * # ISSN-0171-1342 ...... p 713 N89-25697 # NASA-CR-185347 ...... p 655 N89-25953 * # ISSN-0171-1342 ...... p 657 N89-25972 # NASA-'3-4243 ...... p 708 N89-26176 * # ISSN-0176-7739 ...... p 693 N89-25243 # NASA-CR4248 ...... p 690 N89-26011 * # ISSN-01767739 ...... p 706 N89-25358 # ISSN-0389-4010 ...... p 655 N89-25950 # NASA-RP-1218 ...... p 713 N89-25673 * # ISSN-0389-4010 ...... p 672 N89-25990 # ISSN-0389-4010 ...... p 693 N89-26015 # NASA-TM-101057 ...... p 656 N89-25958 * # ISSN-0389-4010 ...... p 708 N89-26168 # NASA-TM-101058 ...... p 655 N89-25954 * # ISSN-0951-6301 ...... p 658 N89-25143 NASA-TM-101081 ...... p 708 N89-26207 ' # NASA-TM-101554 ...... p 706 N89-25443 * # L-16528 ...... p 713 N89-25673 * # NASA-TM-101573 ...... p 671 N89-25232 * # L-16546 ...... p 652 N89-25117 * # NASA-TM-101583 ...... p 690 N89-25239 * # L-16568-PT-1 ...... p 666 N89-25146 * # NASA-TM-101584 ...... p 690 N89-26010 * # L-16568-PT-2 ...... p 669 N89-25173 * # NASA-TM-101618 ...... p 709 N89-26273 * # L-16568-PT-3 ...... p 670 N89-25201 * # NASA-TM-101623 ...... p 712 N89-26623 * # L-16576 ...... p 655 N89-25951 * # NASA-TM-101785 ...... p 714 N89-25764 * # NASA-TM-101949 ...... p 656 N89-25957 * # LIDS-FR-1891 ...... p 712 N89-26610 * # NASA-TM-102053 ...... p 653 N89-25119 * # NASA-TM-102096 ...... p 685 N89-25238 * # LMCAFBOl RZ ...... p 638 N89-25949 # NASA-TM-102119 ...... p 709 N89-26259 * # NASA-TM-102132 ...... p 708 N89-26174 * # MIT-OSP-95178 ...... p 712 N89-26610 * # NASA-TM-102137 ...... p 690 N89-26009 * # NASA-TM-102186 ...... p 658 N89-25977 * # NAL-TM-ST-8705 ...... p 693 N89-25240 # NASA-TM-102189 ...... p 706 N89-25479 * # NASA-TM-102197 ...... p 659 N89-25981 * # NAL-TR-964 ...... p 693 N89-26015 # NASA-TM-102285 ...... p 713 N89-25675 * # NAL-TR-985T ...... p 708 N89-26168 # NASA-TM-102292 ...... p 653 N89-25121 * # NAL-TR-995 ...... p 672 N89-25990 # NASA-TM-102311 ...... p 686 N69-26008 * # NAL-TR-997 ...... p 655 N89-25950 # NASA-TP-2918 ...... p 652 N89.251 17 * # NAS 1.15:101057 ...... p 656 N89-25958 * # NASA-TP-2932 ...... p 655 N89-25951 * # ACCESSION NUMBER INDEX
November 1989 AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 245)
A89-45179 # p 688 A89-46221 p 700 A89-46928 ' # p 703 Typical Accession Number A89-45187 # p641 A89-46244 p 71 1 A69-46932 # p679 A89-46256 # p646 Index Listing A89-45188 # p698 A89-46933 * # p 648 A89-46258 # p692 A69-46935 # 11648 A89-45191 # p 699 A89-46259 # p646 A89-46936 # P679 A89-45207 p 664 A89-46260 # p646 A89-46937 # P666 A69-45208 p 699 A89-46262 # p 646 N89-7j A89-45210 p 699 A89-46938 # P679 , , A89-46263 # p646 A89-46939 # P679 A89-45221 p 660 A89-46266 # p646 A89-46940 # P679 A89-45248 * p 691 A89-46267 # p 646 A89-46941 # p680 A89-45249 * p 692 A89-46278 # p664 A89-46942 # P680 A89-45260 * # p 641 A69-46282 # p 701 A89-46943 # p 703 SPONSORED MICROFICHE NUMBER A89-45262 * # p 641 A69-46298 # p674 IN*SIIIpiq-qTq A89-45293 # p711 A89-46944 # p680 A89-46462 p 701 A89-47003 # p649 A89-45294 # p688 p 701 A89-46468 A89-47004 # p 649 A69-45296 # p657 A89-46470 p 665 A89-47005 * # p 695 A89-45329 p 674 A89-46472 p 701 A89-47006 # p680 A89-45330 p 695 p 701 A89-46474 A89-47008 # p 649 Listings in this index are arranged alphanumeri- A89-45337 p 657 p 701 A89-46478 A89-47009 # p649 cally by accession number. The page number listed A89-45351 * p699 A89-46460, p 701 A89-45352 * p 699 A89-47010 # p649 to the right indicates the page on which the citation A89-46483 p 701 A89-47011 # p649 A89-45355 ' p 641 A89-46493 p 702 is located. An asterisk (*) indicates that the item A89-45359 p 641 A89-47012 # p666 A89-46496 p 638 A89-47013 # p 649 is a NASA report. A pound sign (X) indicates that A89-45360 ' p641 p 702 A89-46503 * A89-47014 # p650 the item is available on microfiche. A89-45363 p 641 A89-46546 p 688 A89-45366 * p 641 A89-47015 # p680 A89-46551 p 71 1 A89-47016 # p650 A89-45368 p 642 A89-46593 p 657 A89-45369 p 642 A89-47017 # p 650 A89-46600 # p676 A89-47019 # p 680 A89-45370 p 642 A89-46694 p646 A89-43722 p 639 A89-45035 p 637 # A89-47020 # P693 A89-45036 p 691 A89-45374 p 642 A89-46696 # p692 A89-43724 p 639 A89-45375 p 642 A89-47023 # p680 A89-45037 p 638 A89-46697 * # p 702 A89-43827 # p 659 A89-45378 p 642 A89-47024 # p681 A69-45039 p 714 A89-46704 # p676 A89-43828 # p659 A89-45381 p 642 A89-47025 * # p 703 A89-45041 p 662 A69-46705 # p 665 A89-43840 p 697 A89-45384 * p 643 A89-47026 * # p 650 A89-45042 p 675 A89-46748 # p702 A89-47027 # p650 p 697 A89-45390 p 643 A89-43843 A89-45043 p 662 A89-46750 # p702 A89-47028 # p650 p 697 A89-45391 p 643 A89-43844 A89-45044 p 662 A89-46751 # p676 A89-47029 # p688 A89-43869 p 694 A89-45392 p 643 A89-46752 # p676 . 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A89-47198 # p684 N89-25243 # p693 A89-47199 # P684 N89-25358 # p 706 A8947213 p 697 N89-25432 * # p 706 A89-47250 * p 704 N89-25443 * # P 706 A89-47326 p 638 N89-25464 * # p 706 A89-47334 p 657 N89-25479 * # p 706 A89-47335 p 661 N69-25480 * # p 707 A89-47336 p 661 N89-25530 # p 710 A89-47339 p 658 N89-25673 * # p 713 A8947340 p661 N89-25675 * # p 713 A89-47351 * # p 652 N89-25676 # p713 A89-47352 # p652 N89-25697 # p 713 A89-47356 # p652 N89-25764 ' # p 714 A89-47357 * # P 652 N89-25946 # p 638 A89-47358 * # P 652 N89-25949 # p 638 A89-47360 # p652 N89-25950 # p 655 A89-47372 * # p 652 N89-25951 * # p 655 A89-47373 # P652 N89-25952 # p655 A89-47376 # P652 N89-25953 * # p 655 N89-25954 * # p 655 N89-25113 # P 638 N89-25957 * # P 656 N69-25117 * # P 652 N89-25958 * # p 656 N89-25119 * # P 653 N89-25964 # P656 N89-25121 * # P 653 N89-25965 # p656 N89-25122 * # p 653 N69-25966 # 11656 N89-25125 # P653 N89-25969 # P656 N89-25126 # p653 N89-25970 # p 656 N89-25129 # P 654 N89-25972 # p657 N89-25131 # P654 N89-25973 * # p 657 N89-25134 # p654 N89-25974 # p 658 N89-25135 # p654 N89-25976 # p 658 N89-25137 # P654 N89-25977 * # p 658 N89-25138 # p 654 N89-25979 # p659 N89-25139 # p654 N89-25981 * # p 659 N89-25140 # P713 N89-25984 # p661 N89-25141 # P 689 N89-25985 # p661 N89-25142 # p 658 N89-25986 # p 661 N89-25143 p 658 N89-25990 # p672 N89-25144 # P658 N89-25991 p 672 N89-25146 * # P 666 N89-25994 # p 672 N89-25147 '# P 666 N89-25995 # p672 N89-25150 * # P 667 N89-25996 # p 672 N89-25151 * # p 667 N89-25997 # p 672 N89-25152 * # P 667 N89-25998 # p673 N89-25153 * # p 667 N89-26000 # P673 N69-25154 * # P 667 N89-26001 p 673 N89-25155 * # P 668 N89-26004 * # p 685 N89-25156 * # p 668 N89-26005 # p685 N89-25157 * # P 668 N89-26006 # p685 N89-25159 '# P 668 N89-26008 * # p 686 N89-25162 '# P 711 N89-26009 * # p 690 N89-25164 * # p 705 N89-26010 * # p 690 N89-25165 * # p 685 N69-26011 * # p 690 N89-25166 * # P 705 N89-26012 # p690 N89-25167 * # P 668 N89-26013 * # p 690 N89-25168 * # P 669 N89-26014 * # p 691 N89-25170 * # p 669 N89-26015 # p693 N89-25171 * # p 669 N89-26018 # P694 N89-25172 * # P 669 N89-26019 # p694 N89-25173 * # p 669 N89-26020 # p 694 N89-25174 * # P 705 N89-26110 # p697 N89-25177 '# p 705 N89-26120 # p707 N89-25179 *# P 711 N89-26121 # p707 N89-25180 '# p 712 N89-26123 # p707 N89-25187 * # p 705 N89-26127 # p 707 N89-25189 ' # P 689 N89-26133 # p 707 N89-25190 ' # P 669 N89-26168 # p708 N89-25191 * # p 689 N89-26172 * # p 708 N89-25192 * # P 670 N69-26174 * # p 708 N89-25193 * # P 669 N89-26176 * # p 708 N89-25194 * # P 670 N89-26196 # p 708 N89-25195 * # P 689 N89-26207 * # p 708 N89-25196 '# p 705 N89-26240 p 709 N89-25197 * # P 706 N89-26259 * # p 709 N89-25198 * # P 655 N89-26267 # p709 N89-25201 * # p 670 N89-26273 # p 709 N89-25205 * # P 670 N89-26294 # p710 N89-25206 * # P 670 N89-26323 # p 710 N89-25207 * # P 685 N89-26606 * # p 712 N89-25210 * # p 670 N89-26610 '# p 712 N89-25211 '# P 670 N89-26623 '# p 712 N89-25212 * # P 671 N89-26679 * # p 713 N89-25220 '# p 712 N89-26683 ' # p 714 N89-25221 * # P 671 N89-25222 * # p 671 N89-25231 * # p 706 N89-25232 ' # P 671 N89-25233 * # P 671 N89-25234 P 671 N89-25235 * # P 671 N89-25237 P 672 N89-25238 * # P 685 N89-25239 * # P 690 N89-25240 # P693 N89-25241 # P 693 N89-25242 * D 693 AVAILABILITY OF CITED PUBLICATIONS
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