_ A ST,_ _-...... u,;, __2_" °eb?'._sr _ !!%_9
i .eronautical F_,.-cjineed_ng Aeronautical Er ineerir i ngAeronautical Engi :al _. Nineerir Aemnautic. l autic-al Aerona
7 ! ACCESSION NUMBER RANGES
Accession numbers cited in this Supplement fall within the following ranges.
STAR (N-10000 Series) N89-10001 -- N89-11688
IAA (A-10000 Series) A89-t0001 A89-12760
This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by RMS AssociaTes. NASA SP-7037(236)
AERONAUTICAL ENGINEERING
A CONTINUING BIBLIOGRAPHY WITH INDEXES
(Supplement 236)
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 January 1989 in
• Scientific and Technical Aerospace Reports (STAR) v • International Aerospace Abstracts (IAA).
Office of Management N_A National Aeronautics and Space Administration Scientific and Technical Information Division
Washington, DC 1989 This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A06. INTRODUCTION
This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 430 reports, journal articles and other documents originally announced in January 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 cummulative index will be published.
Information on the availability of cited publications including addresses of organizations and NTIS price schedules is located at the back of this bibliography.
iii TABLE OF CONTENTS
Page Category 01 Aeronautics (General) 1
Category 02 Aerodynamics 4 Includes aerodynamics of bodies, combinations, wings, rotors, and control sur- faces; and internal flow in ducts and turbomachinery.
Category 03 Air Transportation and Safety 18 Includes passenger and cargo air transport operations; and aircraft accidents.
Category 04 Aircraft Communications and Navigation 23 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 25 Includes aircraft simulation technology.
Category 06 Aircraft Instrumentation 3O Includes cockpit and cabin display devices; and flight instruments.
Category 07 Aircraft Propulsion and Power 33 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 38 Includes aircraft handling qualities; piloting; flight controls; and autopilots.
Category 09 Research and Support Facilities (Air) 41 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.
Category 10 Astronautics 42 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 43 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.
II Category 12 Engineering 43 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 54 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.
Category 14 Life Sciences 57 Includes life sciences (general); aerospace medicine; behavioral sciences; man/system technology and life support; and space biology.
Category 15 Mathematical and Computer Sciences 57 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 59 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 B.A. 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 60
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
NASA SPONSORED
11_-_" ON MICROFICHE
ACCESSION NUMBER N89-10029"# North Carolina State Univ., Raleigh. Dept. of _ CORPORATE SOURCE Mechanical 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: NTIS HC A05/MF A01 _ PRICE CODE COSATI CODE CSCL 01A "_ 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 wing/body 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
NASA SPONSORED
_ _- ON MICRORCHE ACCE_ON NUMBER------_ A89-12562"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. 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),_JOURN/U, 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 numedcal 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 ot a direct solution. Author
v_ AERONAUTICAL
ENGINEERING A Continuing Bibliography (Suppl. 236)
FEBRUARY 1989
01 twin engines, VTOL, the Bell X-l, the Boeing 707, the Boeing 747, the Mercury project, the Mariner spacecraft, the Apollo AERONAUTICS(GENERAL) program, Skylab, and the Space Shuttle. B.J.
A89-10629" National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. UNIQUE RESEARCH CHALLENGES FOR HIGH-SPEED CIVIL A89-10538 TRANSPORTS AIRCRAFT DYNAMIC STABILITY - DEVELOPMENTAL CHARLtE M. JACKSON, JR. and E. K. MORRIS, JR. (NASA, HISTORY ASPECTS [DIE EIGENSTABILITAET VON Langley Research Center, Hampton, VA) IN: International Pacific FLUGZEUGEN - EIN BEITRAG ZUR GESCHICHTLICHEN Air and Space Technology Conference, Melbourne, Australia, Nov. ENTWlCKLUNG] 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive ANDREAS HAFER, GOTTFRIED SACHS (Muenchen, Technische Engineers, Inc., 1988, p. 29-34. Previously announced in STAR as N87-27651. refs Universitaet, Munich, Federal Republic of Germany), and XAVER (SAE PAPER 872400) HAFER (Darmstadt, Technische Hochschule, Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Market growth and technological advances are expected to lead to a generation of long-range transports that cruise at Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 450-459. supersonic or even hypersonic speeds. Current NASA/industry studies wilt define the market windows in terms of time frame, In German. refs (DGLR PAPER 87-057) Mach number, and technology requirements for these aircraft. Initial results indicate that, for the years 2000 to 2020, economically The history of flight-stability analysis in the 19th and early 20th centuries is recalled in an analytical review. Consideration is given attractive vehicles could have a cruise speed up to Mach 6. The to the contributions of Cayley, Penaud, Lanchester, Langley, resulting research challenges are unique. They must be met with Prandtl, Ahlborn, Zahm, Runge, Lilienthal, and the Wright brothers. technologies that will produce commercially successful and environmentally compatible vehicles where none have existed. Diagrams, drawings, graphs, and photographs are provided. T.K. Several important areas of research were identified for the high-speed civil transports. Among these are sonic boom, takeoff A89-10627 noise, thermal management, lightweight structures with long life, INTERNATIONAL PACIFIC AIR AND SPACE TECHNOLOGY unique propulsion concepts, unconventional fuels, and supersonic CONFERENCE, MELBOURNE, AUSTRALIA, NOV. 13-17, 1987, laminar flow. Author PROCEEDINGS Conference sponsored by SAE. Warrendale, PA, Society of A89-10646 Automotive Engineers, Inc. (SAE Proceedings P-208), 1988, 563 MILITARY AEROSPACE TECHNICAL DEVELOPMENT IN p. For individual items see A89-10628 to A89-10673. AUSTRALIA (SAE P-208) I. T. SUTHERLAND (Royal Australian Air Force, Canberra, Papers are presented on such topics as a conceptual study of Australia) IN: International Pacific Air and Space Technology the H-II Orbiting Plane, V/STOL aircraft configurations and Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. opportunities in the Pacific basin, Boeing 7J7 technology and Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. design, space transporation systems for the future, 225-233. refs propulsion-airframe integration for commercial and military aircraft, (SAE PAPER 872426) and X-29A forward-swept-wing flight research. Consideration is also The paper identifies the requirements for and strengths of given to the mission-adaptive wing, large space structures, Australia's military aerospace technologies, with emphasis on the boundary layer control for drag reduction, the interoperability of self-reliance policy of Australian Defence. Particular attention is military and civil air-cargo systems, maintenance and airline safety, given to government policy reviews, current technologies and future forward error correction techniques for mobile satellite support needs, the economic environment, and mechanisms for communications, spacecraft mechanisms technology, modern technological development. Specific reference is made to the techniques for the control of RPVs, and Space Station utilization. F/A-18 Hornet Aircraft Project. B.J. B.J.
A89-10657 A89-10628 A WORLD LEADER IN ENGINEERING AND MAINTENANCE FROM KITTY HAWK TO THE YEAR 2000 W. M. RYAN (Qantas Airways, Ltd., Sydney, Australia) IN: SAMUEL J. SMYTH IN: International Pacific Air and Space International Pacific Air and Space Technology Conference, Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, Proceedings. Warrendale, PA, Society of Automotive Engineers, PA, Society of Automotive Engineers, Inc., 1988, p. 369-373. Inc., 1988, p. 1-21. refs (SAE PAPER 872444) (SAE PAPER 872395) Aspects of the Qantas engineering and maintenance program The evolution of aerospace vehicles is traced from the Wright are discussed. The history of Qantas is briefly reviewed, and the Brother's first flights to a glimpse into the future. Some highlights reasons for the success of the airline are summarized. Its manpower of the discussion are the Fokker T-2, the DC-3, the Lockheed and training programs are described, and its maintenance 01 AERONAUTICS (GENERAL)
philosophy is discussed. Quality control and strategic planning at Aircraft Energy Efficiency program for improving transport aircraft Qantas are addressed. C.D and the Natioanl Aerospace Plane program are examined. NASA research facilities and wind tunnels, and research in materials A89-10689 and structures and aviation safety and automation are discussed. OVER THE RAINBOW R.B. RICHARD G. DESIPIO (U.S. Navy, Naval Air Development Center, Warminster, PA) IN: Aerospace avionics equipment and A89-12401 integration; Proceedings of the Second Conference, Dallas, TX, AUTOMATION APPLICATIONS FOR ROTORCRAFT; Nov. 2-4, 1987. Warrendale, PA, Society of Automotive Engineers, PROCEEDINGS OF THE NATIONAL SPECIALISTS' MEETING, Inc., 1988, p. 139-145. ATLANTA, GA, APR. 4-6, 1988 (SAE PAPER 872499) Meeting sponsored by AHS. Alexandria, VA, American Helicopter The paper addresses advanced avionics architectures as well Society, 1988, 148 p. For individual items see A89-12402 to as a transitionary means of attaining these goals and objectives. A89-12418. An 'Avionics System Index' is presented to define and specify the The present conference on the application of automation to make-up of a partitioned avionics configuration based upon a helicopter systems discusses automatic C31 for target data framework of multiplex data buses, backplane buses, and matrix dissemination, the nonlinear control of a twin-lift helicopter system, switches. It is noted that the standardization of an intraplatform the development of a rule-based demonstration prototype expert network was begun with the introduction and implementation of system for inflight emergencies, automated VTOL RPVs, digital the DOD MIL-STD-1553B and its NATO equivalent STANAG-3838 autopilots for unmanned helicopters, and knowledge-based target bus network; MIL-STD-1553B provided a significant step forward recognition. Also discussed are speech recognition in advanced relative to avionics system integration. K.K. helicopters, a tactics expert for a scout/attack helicopter, novel concepts in helicopter machinery prognostics, a hybrid A89-11450 knowledge-based approach to AH-64 fault isolation, and the TORNADO - THE FIRST EIGHT YEARS implementation of knowledge-based systems for helicopter WILLIAM RICHARDSON (RAF, London, England) Aerospace machinery fault ]orognosis. O.C. (UK) (ISSN 0305-0831), vol. 15, Sept. 1988, p. 6-12. The engineering support necessary to maintain the Tornado A89-12408# aircraft is discussed, focusing on the work in-service. The Torndao NEW CONCEPTS IN HELICOPTER MACHINERY is a day and night, all-weather, ultralow-level attack aircraft capable PROGNOSTICS of using both conventional and nuclear weapons. The development KENNETH PIPE and tAN CHEESEMAN (Stewart Hughes, Ltd., and production program for the aircraft and the organization of Southampton, England) IN: Automation applications for rotorcraft; Tornado engineering support are outlined. Arrangements for the Proceedings of the National Specialists' Meeting, Atlanta, GA, repair and overhaul of Tornado and in- service operation of the Apr. 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, aircraft are examined. Organizational and technical problems which 12p. have occurred in the development process are presented and Technologies that have been developed for rotorhead efforts to overcome these problems are discussed. R.B. transmission and power plant diagnostics are presented. Practical results are discussed for these processing-intensive techniques, A89-12319 as well as the implications for flight safety, maintenance A CANADIAN GOVERNMENT LOOK AT AIRWORTHINESS optimization, and battle damage recovery of the use of this JOHN F. MEW and JAMES A. TORCK (Transport Canada, technology. The hardware required to implement these techniques Ottawa) SAE, Aerospace Vehicle Conference, Annapolis, MD, is noted, both for inboard and carry-onboard systems. Author Apr. 18-20, 1988. 6 p. (SAE PAPER 880935) A89-12409# The paper traces the development of the approach to A HYBRID KNOWLEDGE-BASED APPROACH TO AH-64A airworthiness taken by Canadian government authorities from its FAULT ISOLATION origin through to current practices. It describes the Aerospace BRIAN P. MILLETT and RICHARD K. MABY (McDonnell Douglas industry, the carriers and general aviation in statistical terms, Helicopter Co., Mesa, AZ) IN: Automation applications for indicates the impact of economic regulatory reform and suggests rotorcraft; Proceedings of the National Specialists' Meeting, Atlanta, the way ahead for Canadian and other authorities lies in the attitude GA, Apr. 4-6, 1988. Alexandria, VA, American Helicopter Society, and methodologies practiced by the European authorities in their 1988, 10 p. Army-supported research, refs development of JARs. Author The increasing complexity of state-of-the-art military rotorcraft, in conjunction with greater aircraft availability requirements and A89-12320 the limited pool of skilled maintenance personnel, have prompted EUROPEAN AIRWORTHINESS CONTROL FOR THE 1990S the development of an Intelligent Fault Locator (IFL) expert system J. W. SAULL SAE, Aerospace Vehicle Conference, Annapolis, for AH-64A helicopter fault diagnosis. The IFL combines MD, Apr. 18-20, 1988. 11 p. maintenance data with AI; in order to enhance its operating (SAE PAPER 880936) characteristics and capabilities, a 'shell' has been devised which Key developments and problems in European airworthiness encompasses user-interface and diagnostic modules, as well as a matters for the 1990s are addressed. Efforts being given to the learning module and fuel/flight control subsystem graphics. Fault harmonization of requirements within Europe are reviewed. location downtimes for the AH-64A have been reduced by almost Developments occurring in the control of maintenance standards 47 percent by means of the IFL system. O.C. are examined, and the importance of making the best use of technical resources is stressed. C.D. A89-12412# IMPLEMENTATION OF KNOWLEDGE-BASED SYSTEMS FOR A89-12322" National Aeronautics and Space Administration, HELICOPTER MACHINERY FAULT PROGNOSIS Washington, D.C. IAN CHEESEMAN and KENNETH PIPE (Stewart Hughes, Ltd., THE WINNING EDGE Southampton, England) IN: Automation applications for rotorcraft; CECIL C. ROSEN, III and LOUIS J. WILLIAMS (NASA, Washington, Proceedings of the National Specialists' Meeting, Atlanta, GA, DC) SAE, Aerospace Vehicle Conference, Annapolis, MD, Apr. Apr. 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, 18-20, 1988. 13 p. 8p. (SAE PAPER 880945) Knowledge-based systems have been developed for the Aeronautics research at NASA is reviewed, stressing NASA's automation of helicopter gas turbine powerplant fault-finding leading role in the development of technological advances. The procedures, helicopter transmission system vibration-signature
2 01 AERONAUTICS (GENERAL)
analyses, and rotor head-smoothing tasks. An account is presently the aircraft birdstrike problem and its alleviation. ABU activities given of the development process for these techniques, giving have concentrated in and around airfields, in keeping with the attention to the problems encountered in the extension of these occurrence of nearly 90 percent of birdstrikes at altitudes below diagnostic capabilities into fully prognostic ones. A powerful 900 ft; observations at nocturnal roost sites as much as 50 km interface between the FORTRAN and C languages and either away from major airports have been required, however, for such PROLOG or LISP is an essential feature of the development birdstrike problem-causing species as seagulls. Other ABU activities system. O.C. extend to bird habitat management, bird-scaring, advisory work, and the charting of migratory bird routes in order to facilitate their A89-12537 avoidance by aircraft. O.C. BITING THE BULLET ON AVIATION SAFETY ROBERT L. CRANDALL (American Airlines, Inc., Dallas, TX) Issues in Science and Technology (ISSN 0748-5492), vol. 4, Winter N89-10003# Royal Aerospace Establishment, Farnborough 1988, p. 93-95. (England). It is presently proposed that the U.S. Secretary of Transportation AEROSPACE SYSTEMS AND TECHNOLOGY: THE ROLE OF should constitute a blue-ribbon commitee, headed by the FAA THE RAE and encompassing representatives from all concerned groups, to G. G. POPE Jun. 1988 38 p Presented at RAE Handley conduct a detailed study of the ATC system's current status and Page Memorial Lecture, London, United Kingdom, 21 Apr. 1988 prospects for expansion to handle the increase to 600 million Original contains color illustrations passengers, from the current 415 million passengers, expected by (RAE-TR-88042; RAE-DR/55/07; ETN-88-93140) Avail: NTIS 1992. For the time being, the FAA is noted to be proceeding with HC A03/MF A01; Defence Research Information Centre, 65 the hiring and training of 955 more ATC operators. Difficulties are Brown Street, Glasgow, G2 8EX, United Kingdom likely to emerge from the need to override environmentalist The evolution and role of the U.K. Royal Aerospace concerns and undertake the construction of additional airports, Establishment are reviewed and research in night and all-weather and more runways for existing airports, which will be capable of operations, flight control systems for ASTOVL aircraft, handling expanded future traffic. computational fluid dynamics, airframe materials, weapon aim-point refinement, remote sensing, and systems assessment is A89-12538 summarized. ESA UP IN THE AIR ON AIR TRAFFIC CONTROL GUY V. MOLINARI (U.S. Congress, House Public Works and Transportation Committee, Washington, DC) Issues in Science N89-10830# Politecnico di Torino (Italy). Dipartimento di and Technology (ISSN 0748-5492), vol. 4, Winter 1988, p. 96-99. Ingegneria Aeronautica e Spaziale. refs ORIGIN, OBJECTIVES AND ACTIVITIES OF THE The FAA's answer to currently experienced ATC computer and DEPARTMENT OF AEROSPACE ENGINEERING Annual communications equipment malfunctions and outages _s the Report, 1985 National Airspace System (NAS) plan, which will spend several Nov. 1986 38 p billion dollars in equipment modernization. It is presently noted Avail: NTIS HC A03/MF A01 that in the seven years since the plan was announced, little has The research activities of the Department of Engineering of been accomplished; the plan's costs, moreover, which were the Turin Polytechnic are reported. Department activities are originally envisioned as of the order of $9 billion over a 10-year concerned with both teaching and research. The research is broadly period, have with persistent overruns come to be projected at based and covers all traditional disciplines of aeronautical and $17 billion over a 20-year period. Although the NAS plan originally aerospatial engineering. Allied research themes are also developed, envisioned a reduction of necessary staff due to advanced systems' such as industrial aerodynamics, material science, biofluidynamics, high degree of automation, it is noted to be essential that the laser matter interaction and other topics where one can find new FAA hire additional technician trainees in order to stay even with application fields for the methodologies and the knowledge of attrition. O.C. aerospace disciplines. Brief summaries are given of research activities for 1985. E.R. A89-12716 BIRD HAZARDS IN AVIATION; PROCEEDINGS OF THE SYMPOSIUM, LONDON, ENGLAND, OCT. 14, 1987 N89-10831# Advisory Group for Aerospace Research and London, Royal Aeronautical Society, 1987, 94 p. For individual Development, Neuilly-Sur-Seine (France). Guidance and Control items see A89-12717 to A89-12723. Panel. The present conference discusses such aircraft birdsdstrike COMPUTING SYSTEMS CONFIGURATION FOR HIGHLY effect-related issues as the British civil aviation birdstrike record, INTEGRATED GUIDANCE AND CONTROL SYSTEMS RAF experience with birdstrikes, the design and testing of aircraft Jun. 1988 164 p Lectures held in Bourges, France, 20-21 Jun. engines in order to minimize hazards from birds, and 1988, in Neubiberg, West Germany, 23-24 Jun. 1988, and in Seattle, birdstrike-anticipating design and testing for airframes. Also Wash., 6-7 Jul. 1988 discussed are the design and testing of cockpit windscreens, airline (AGARD-LS-158; ISBN-92-835-0464-X) Avail: NTIS HC A08/MF safety- and economy-related implications of birdstrikes, the A01 responsibility of regulatory authorities for birdstrike effect Modern military air vehicles have to comply with sophisticated minimization, the work of the British Ministry of Agriculture, Fisheries performance requirements. As a result, full advantage must be and Food 'Aviation Bird Unit', and bird control methods applicable taken of the rapid advances in computer hardware/software and beyond the boundaries of airports. O.C. future micro-electronics technologies. New design and development strategies must be implemented in order to obtain the overall A89-12723 performance benefits offered by advanced integrated systems for THE WORK OF THE AVIATION BIRD UNIT guidance and control, avionics, weapon delivery and tactical T. BROUGH (Ministry of Agriculture, Fisheries and Food, performance management. In a two-day program this Lecture Worplesdon Laboratory, Guilford, England) IN: Bird hazards in Series addresses issues which have demonstrated notable and aviation; Proceedings of the Symposium, London, England, Oct. outstanding advances in the field of computing system design, 14, 1987. London, Royal Aeronautical Society, 1987, p. 66-73. design tools and techniques, computers, data buses, and Research supported by Ministry of Defence and Civil Aviation architectures. In particular, the second day's program will show Authority. refs how technological advances have enabled the design of a modern The UK's Aviation Bird Unit (ABU) consists of Ministry of computing system architecture. Future trends and new directions Agriculture biologists specializing in the ornithological aspects of will be subjects for round table discussions.
3 01 AERONAUTICS (GENERAL)
N89-10839# Centre National d'Etudes Spatiales, Toulouse Journal of Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. 612-617. (France). Research supported by the University of Notre Dame. Previously FLIGHT MECHANICS AND AEROTHERMODYNAMIC cited in issue 08, p. 1041, Accession no. A87-22672. refs SOFTWARE (Contract N00014-83-K-0239) J. C. AGNESE, P. SAINTPE, and T. VOIRON 6 Mar. 1988 35 p In FRENCH; ENGLISH summary A89-10108"# PRC Kentron, Inc., Hampton, Va. (CNES-CT/DTI/MS/MN/069; CNES-DLA/SDT/ED/SA; ENGINEERING ANALYSIS OF SLENDER-BODY ETN-88-93094 ) Avail: NTIS HC A03/MF A01 AERODYNAMICS USING SYCHEV SIMILARITY PARAMETERS Aerothermodynamics software for heat flow computation on MICHAEL J. HEMSCH (PRC Kent'ron, Inc., Hampton, VA) Journal an axisymmetric structure, plane sheet, arrow cylinder; wall heating of Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. 625-631. with or without ablation; thrust nozzle free jet computation and its Previously cited in issue 08, p. 1036, Accession no. A87-22522. interaction with a wall (plane or truncated segment); and flight refs mechanics software for Ariane takeoff and booster separation is (Contract NAS1-18000) described. ESA A89-10114# TWO-DIMENSIONAL MODEL FOR AIRFOIL UNSTEADY DRAG BELOW STALL J. G. LEISHMAN (Maryland, University, College Park) Journal of 02 Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. 665, 666. refs A computationally efficient method for computing the unsteady pressure drag on a two-dimensional airfoil undergoing arbitrary AERODYNAMICS motion in compressible flow has been developed. It is shown that the unsteady pressure drag variation on a nonstationary airfoil is Includes aerodynamics of bodies, combinations, wings, rotors, and relatively significant. Inclusion of the method within helicoptor rotor control surfaces; and internal flow in ducts and turbomachinery. aeroelasticity analyses may provide a better definition of higher harmonics of the blade lag excitation and improve prediction of aeroelastic coupling affects. R.R.
A89-10116# A89-10102# THICK AIRFOIL AT LOW REYNOLDS NUMBER AND HIGH INVESTIGATIONS ON HIGH REYNOLDS NUMBER LAMINAR INCIDENCE FLOW AIRFOILS S. RAGHUNATHAN (Belfast, Queen's University, Northern Ireland), G. REDEKER, K. H. HORSTMANN, H. KOESTER, and A. QUAST J. R. HARRISON, and B. D. HAWKINS Journal of Aircraft (ISSN (DFVLR, Institut fuer Aerodynamik, Brunswick, Federal Republic 0021-8669), vol. 25, July 1988, p. 669-671. refs of Germany) (ICAS, Congress, 15th, London, England, Sept. Experimental results on an NACA 0021 airfoil at a blade chord 7-12, 1986, Proceedings. Volume 1, p. 73-85) Journal of Aircraft Reynolds number of 260,000 and over a range of incidence of (ISSN 0021-8669), vol. 25, July 1988, p. 583-590. Previously cited 0-90 deg were obtained in a closed-circuit low-speed wind tunnel. in issue 24, p. 3529, Accession no. A86-48983. refs The results are compared with previous data on other airfoils and with the predictions of momentum theory. At low Reynolds numbers and for symmetric airfoil sections the maximum value of the lift coefficient is between 0.8 and 1.0, the stall angle is between 10 and 15 deg, and after stalling, the lift coefficient decreases with A89-10104"# National Aeronautics and Space Administration. incidence much more rapidly than for thicker airfoils. R.R. Langley Research Center, Hampton, Va. EFFICIENT ALGORITHM FOR SOLUTION OF THE UNSTEADY A89-10160" High Technology Corp., Hampton, Va. TRANSONIC SMALL-DISTURBANCE EQUATION COMPUTATIONAL AND EXPERIMENTAL STUDIES OF LEBUS JOHN T. BATINA (NASA, Langley Research Center, Hampton, AT HIGH DEVICE REYNOLDS NUMBERS VA) Journal of Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. ARILD BERTELRUD (High Technology Corp., Hampton, VA) and 598-605. Previously cited in issue 08, p. 1033, Accession no. R. D. WATSON (NASA, Langley Research Center, Hampton, VA) A87-22420. refs IN: Turbulence management and relaminarisation; Proceedings of the IUTAM Symposium, Bangalore, India, Jan. 13-23, 1987. Berlin and New York, Springer-Verlag, 1988, p. 85-96. refs The present paper summarizes computational and experimental A89-10105"# Texas A&M Univ., College Station. studies for large-eddy breakup devices (LEBUs). LEBU optimization WING LAMINAR BOUNDARY LAYER IN THE PRESENCE OF A (using a computational approach considering compressibility, PROPELLER SLIPSTREAM Reynolds number, and the unsteadiness of the flow) and STAN J. MILEY (Texas A & M University, College Station), experiments with LEBUs at high Reynolds numbers in flight are RICHARD M. HOWARD (U.S. Naval Postgraduate School, discussed. The measurements include streamwise as well as Monterey, CA), and BRUCE J. HOLMES (NASA, Langley Research spanwise distributions of local skin friction. The unsteady flows Center, Hampton, VA) (ICAS, Congress, 15th, London, England, around the LEBU devices and far downstream are characterized Sept. 7-12, 1986, Proceedings. Volume 2, p. 1413-1420) Journal by strain-gage measurements on the devices and hot-wire readings of Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. 606-611. downstream. Computations are made with available time-averaged Previously cited in issue 24, p. 3533, Accession no. A86-49122. and quasi-stationary techniques to find suitable device profiles with refs minimum drag. Author (Contract NAG1-344) A89-10167 THREE-DIMENSIONAL BOUNDARY LAYER TRANSITION ON A CONCAVE-CONVEX CURVED WALL Y. KOHAMA (Tohoku University, Sendal, Japan) IN: Turbulence A89-10106# management and relaminarisation; Proceedings of the IUTAM BOUNDARY-LAYER MEASUREMENTS ON AN AIRFOIL AT Symposium, Bangalore, India, Jan. 13-23, 1987. Berlin and New LOW REYNOLDS NUMBERS York, Springer-Verlag, 1988, p. 215-226. refs M. BRENDEL and T. J. MUELLER (Notre Dame, University, IN) The transition to turbulence over a NASA 998A supercritical 02 AERODYNAMICS
LFC wing is investigated experimentally in the 400 x 400-ram A89-10510 working section of the open-jet wind tunnel at DFVLR Goettingen STUDY OF THE ENGINE INFLUENCE ON WINGS WITH at velocities up to 12 m/see. The results are presented in extensive MODERN HIGH-BYPASS PROPULSION CONCEPTS graphs and flow visualizations and discussed in detail. It is shown [UNTERSUCHUNG DES TRIEBWERKEINFLUSSES AN that the primary destabilizing mechanism in the boundary layer is FLUEGELN MIT MODERNEN a Taylor-Goertler instability in the concave region, resulting in HOCHBYPASS-ANTRIEBSKONZEPTEN ] formation of a counterrotating Taylor-Goertler vortex; this vortex G. SAUER (Berlin, Technische Universitaet, Federal Republic of is transformed to a corotating cross-flow vortex in the convex Germany) and J. SZODRUCH (Messerschmitt-Boelkow-Blohm region at sweep angles greater than 47 deg. T.K. GmbH, Bremen, Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Federal Republic of A89-10171 Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft SUPPRESSION OF UNSTABLE OSCILLATIONS IN A fuer Luft- und Raumfahrt, 1987, p. 171-179. In German. Research BOUNDARY LAYER supported by the Technische Universitaet Berlin, DFG, and A. I. DERZHAVINA, O. S. RYZHOV, and E. D. TERENT'EV (AN BMFT. refs SSSR, Vychislitel'nyi Tsentr, Moscow, USSR) IN: Turbulence (DGLR PAPER 87-063) The use of modern high-bypass engines permits increasing management and relaminarisation; Proceedings of the IUTAM wind tunnel research on capacity optimization of wing-propulsion Symposium, Bangalore, India, Jan. 13-23, 1987. Berlin and New York, Springer-Verlag, 1988, p. 271-284. refs systems. Numerical procedures are needed for the aerodynamic A theoretical study is made of the excitation of preoptimization of configurations of advanced engine concept Tollmien-Schlichting waves by a mechanical vibrator or thermal configurations. To this end, a three-dimensional engine panel source that heats a small part of a surface in subsonic stream. method for flow calculations was developed. The inlet flow and its effects on the flow around a nacelle are shown for the subsonic According to results of most practical concern, it is possible to reduce essentially the amplitude of forced oscillations and even regime and for various engine states. Lift distributions are studied to attain their full attenuation by changing the form of a membrane. using wing panel methods in wing-engine systems with individual The similar effect is reached when the temperature of the heated and twin engines with regard to deviations from undisturbed wing part varies. Hence, a possibility arises to damp traveling lift. The concept of variable wing camber as a potential Tollmien-Schlichting waves using different devices of both compensation for the engine influence on the wing is presented. C.D. mechanical and thermal nature. Author
A89o10192" Boston Univ., Mass. A89-10511 BEM FOR WAVE EQUATION WITH BOUNDARY IN IMPROVEMENT OF A DESIGN CODE FOR AIRFOILS AT ARBITRARY MOTION AND APPLICATIONS TO TRANSONIC REGIME COMPRESSIBLE POTENTIAL AERODYNAMICS OF F. MONGE (Instituto National de Tecnica Aerospacial, Madrid, AIRPLANES AND HELICOPTERS Spain) and H. KOI::STER (DFVLR, institut fuer Entwurf- LUIGI MORINO, BALA K. BHARADVAJ, MARVIN I. FREEDMAN saerodynamik, Brunswick, Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Federal (Boston University, MA), and KADIN TSENG (United Technologies Research Center, East Hartford, CT) IN: Advanced boundary Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche element methods; Proceedings of the IUTAM Symposium, San Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 180-189. refs Antonio, TX, Apr. 13-16, 1987. Berlin and New York, (DGLR PAPER 87-064) Investigations on the design code of McFadden have been Springer-Verlag, 1988, p. 267-277. refs (Contract NAS1-17317; DAAG29-83-K-O050; DAAL03-87-K-0022) carried out in order to improve agreement between the design pressure distribution and the analysis pressure distribution of the The wave equation for an object in arbitrary motion is investigated analytically using a BEM approach, and practical designed airfoil. This has been achieved by modifying the artificial applications to potential flows of compressible fluids around aircraft viscosity term used in the existing McFadden code. The new term wings and helicopter rotors are considered. The treatment accounts has a more realistic meaning, as it is now proportional to the truncation error included in the finite differences scheme used to for arbitrary combined rotational and translational motion of the reference frame and for the wake motion. The numerical solve the full potential equation. In some cases it has also been implementation as a computer algorithm is demonstrated on necessary to carry out a weighted smoothing of the curvature for problems with prescribed and free wakes, the former in modelling with more accuracy the desired pressure distribution. At compressible flows and the latter for incompressible flows; results the same time, the convergence has been accelerated and the are presented graphically and briefly characterized. T.K. arbitrariness of some input parameters avoided. The improved method has been checked on various airfoil designs which are
A89-10509 discussed in the paper. Author AN INVERSE, SUBSONIC TWO-DIMENSIONAL PANEL METHOD FOLLOWING THE METHOD OF SMALLEST A89-10513 QUADRATE FOR THE DESIGN AND MODIFICATION OF PROFILE DEVELOPMENT RESULTS FOR ADVANCED MULTIPLE ELEMENT PROFILES [EIN INVERSES, CIRCULATION-GUIDED ROTOR SYSTEMS IN FAST SUBSONISCHES 2D-PANELVERFAHREN NACH DER HELICOPTERS [ERGEBNISSE DER PROFILENTWlCKLUNG METHODE DER KLEINSTEN QUADRATE ZUM ENTWURF UND FUER FORTSCHRITTLICHE ZlRKULATIONSGESTEUERTE ZUR MODIFIKATION VON MEHRELEMENTPROFILEN] ROTORSYSTEME SCHNELLER HUBSCHRAUBER] H. SCHWARTEN (Messerschmitt-Boelkow-Blohm GmbH, Hamburg, A. WEIGAND (Stuttgart, Universitaet, Federal Republic of Germany) Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, and H. ZIMMER (Dornier GmbH, Friedrichshafen, Federal Republic Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, Raumfahrt, 1987, p. 163-170. In German. refs Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 199-216. In German. refs (DGLR PAPER 87-061) A calculative procedure is presented which, by coupling a (Contract BMFT-T/RF-41/F0013/G2232) computational code with a minimization algorithm, enables a single (DGLR PAPER 87-086) and multielement profile to be designed. The profile is developed Alternative rotor systems designed to achieve greater speed using a special basis function. This method guarantees a flat outline increases for helicopters with smaller blade tip Mach numbers are and permits partial and full outlines, significantly increasing the considered. In particular, a modified calculative procedure involving input flexibility. Five practical examples are used to demonstrate the Coanda effect is used to design improved circulation-guided the quality of the procedure. C.D. rotor (CGR) systems. A CG profile with three interchangeable
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Coanda surfaces was designed, constructed, and tested in a wind FUTATSUDERA Kyushu University, Technology Reports (ISSN tunnel. The theoretical and experimental results demonstrate a 0023-2718), vol. 61, June 1988, p. 287-292. In Japanese, with significant advance over the present state of the art. Further abstract in English. refs research on the flow behavior on a three-dimensional CGR using Separated flows around wing sections are calculated by a a curved lifting line blade element vortex wake method is used to discrete vortex method combined with a panel method. The define a blade form suitable for a fast CGR helicopter. C.D. potential flow around the wing section is expressed by vortex sheets, and separated shear layers are expressed by discrete A89-10542# vortices. In the calculation a s_paration point is determined by A NUMERICAL SOLUTION OF TRANSONIC FLOW USING solving the boundary layer equations. The strength of a shed vortex DISCONTINUOUS SHOCK RELATION is estimated using the local velocity near the separation point. MASAYOSHI NAKAMURA Japan Society for Aeronautical and Modifications for the estimation of pressure coefficients around Space Sciences, Journal (ISSN 0021-4663), vol. 36, no. 414, 1988, the wing section are also proposed. The results show good p. 333-342. In Japanese, with abstract in English. refs agreement with experiments. Author The purpose of this study is to obtain solutions, which contain complete discontinuities of shock waves, of the potential equations A89-10569# for transonic airfoils using numerical techniques. For iterative NUMERICAL EXPERIMENTS FOR SEPARATION FLOWS calculations, the potential equations are transformed into a more AROUND TRAPEZOIDAL CYLINDERS BY A DISCRETE convenient form of simultaneous equations with two variables of VORTEX METHOD velocity potential and Mach number. The solutions with the MASANORI HAYASHI, SHIGERU ASO, and TOMONORI complete discontinuities of shock waves satisfying Prandtle's TAGUCHI Kyushu University, Technology Reports (ISSN relationship are obtained by the iterative calculations without 0023-2718), vol. 61, June 1988, p. 293-300. In Japanese, with divergencies or height frequencies under a grid system in the abstract in English. refs physical plane. Numerical results of the present techniques and Separated flows around several trapezoidal cylinders are of another method for the transonic flow over an airfoil of NACA calculated by a discrete vortex method combined with a panel 0012 with shock wave are used as test cases for comparisons. method. The potential flow around trapezoidal cylinders are Author expressed by vortex sheets and separated shear layers by discrete vortices. In the calculation five types of trapezoidal cylinders whose A89-10544# shape parameter b/h (b is a front body length normal to the AN EXPERIMENTAL STUDY ON AERODYNAMIC freestream and h is rear body length normal to the freestream) PERFORMANCE OF LIPPISCH-TYPE GEW are 0.0, 0.25, 0.5, 0.75, and 1.0, are used. The strength of a FUMIHARU OTAGIRI, SHIGENORI ANDO, TORU NOHISA, shed vortex is estimated using local velocity near a separation HIR©SHI TAKASAKI, and TATSUYA TSUJIMOT© Japan Society point. The strengths of shed vortices are changed remarkably for Aeronautical and Space Sciences, Journal (ISSN 0021-4663), with shape parameters. Those results agree with the previous vol. 36, no. 414, 1988, p. 351-356. In Japanese, with abstract in results that the separation point moves from a rear corner to a English. refs front corner as the shape parameter, b/h, increases. Also Experimental research on some aerodynamic performance of modifications for the estimation of pressure coefficients around Lippisch-type Ground Effect Wing is presented. This type has a wing section are proposed. The results show good agreement with experiments. Author reverse-Delta wing with some cathedral angles (CA) along the leading edge. Based upon the comparison between experiment I A89-10607 (CA - 16.3 deg) and II (CA 8.1 deg), it is concluded that there are some increments of L/D caused from the ground effect A SECOND-ORDER NUMERICAL METHOD FOR THE both in experiment I and I1, but the latter has higher C(L) than the ANALYSIS OF TWO-DIMENSIONAL FLOW OF IDEAL FLUID former, caused by a modification of the model I. Author THROUGH A CASCADE WITH SUPERSONIC INPUT JAROSLAV PELANT Zprava VZLU, no. 2-55, 1988, p. 1-9. A89-10547# A second-order numerical method for modeling flow of an ideal fluid through a cascade in a plane with supersonic imput is ANALYTICAL AND EXPERIMENTAL RESEARCH ON developed assuming the validity of matter, energy, and momentum AERODYNAMICAL EFFECTS OF WIND SHEAR ON AIRCRAFT conservation laws only. The method admits discontinuities in state HARUO KIMURA (Kyushu University, Fukuoka, Japan) and HAMID values and entropy and does not require prior definitions of BASSIRI Kyushu University, Faculty of Engineering, Memoires subsonic and supersonic regions. The numerical procedure, which (ISSN 0023-6160), vol. 48, June 1988, p. 105-124. refs uses a moving net, is described. V.L. The aerodynamical effects of wind shear on aircraft are discussed with both theoretical and experimental viewpoints. In the theoretical section the influence of wind distribution over the A89-10651" National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. aircraft on the pitching moment which had been formulated in a BOUNDARY-LAYER CONTROL FOR DRAG REDUCTION previous paper is reviewed briefly and is followed by a detailed study of the effects of temporal variation of wind. Based on a WILLIAM D HARVEY (NASA, Langley Research Center, Hampton, theory regarding the accelerated motion of an airfoil in a fluid, the VA) IN: International Pacific Air and Space Technology equations for obtaining the acceleration derivatives are derived. It Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. is shown that the influence of these derivatives on the aircraft Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 287-311. refs stability and response is not negligible. In the experimental section (SAE PAPER 872434) the results obtained in a wind shear tunnel on the spatial and temporal effects of wind variation are presented. The tests are Although the number of possible applications of boundary-layer carried out using a two-dimensional wing and tail combination with control is large, a discussion is given only of those that have received the most attention recently at NASA Langley Research the horizontal stabilizer adjustable at different vertical positions, showing the experimental confirmation of the related theories. Center to improve airfoil drag characteristics. This research concerns stabilizing the laminar boundary layer through geometric Author shaping (natural laminar flow, NLF) and active control involving the removal of a portion of the laminar boundary layer (laminar A89-10568# flow control, LFC) either through discrete slots or a perforated A NUMERICAL SIMULATION OF SEPARATED FLOW AROUND surface. At low Reynolds numbers, a combination of shaping and TWO-DIMENSIONAL WING BY A DISCRETE VORTEX forced transition has been used to achieve the desired run of METHOD laminar flow and control of laminar separation. In the design of MASANORI HAYASHI, SHIGERU ASO, and NAOKI both natural laminar flow and laminar flow control airfoils and
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wings, boundary layer stability codes play an important role. A equations has been performed in order to investigate the discussion of some recent stability calculations using both complicated flow patterns or aerodynamic characteristics of the incompressible and compressible codes is given. Author advanced turboprop (ATP) propeller with two types of spinner configuration. The governing equations are written for a rotating A89-10652 Cartesian coordinate system in terms of absolute flow variables. THE FORMATION MECHANISM OF THE ASYMMETRIC The solution algorithm used is an implicit approximate factorization SPATIAL VORTEX OF SLENDER BODIES AT HIGH ANGLE OF method and resultant matrices are efficiently solved by a LUADI A'R'ACK scheme. This solver has been applied to study the effect of ZI-XING WANG (Nanjing Aeronautical Institute, People's Republic interference between highly swept blades and axisymmetrical of China) and DAI SU (East China Institute of Technology, People's spinner on the aerodynamic performance of the ATP propeller. Republic of China) IN: International Pacific Air and Space Numerical results show that the selection of an area-ruled spinner Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, is important for the aerodynamic design of an efficient turboprop. Author Proceedings. Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 313-318. (SAE PAPER 872435) A89-11036# The fluorescent minituft method is used to study the formation FLOW PERFORMANCE OF REVERSED TANDEM CASCADES mechanism of the asymmetric spatial vortex of slender bodies at WITH DOUBLE-CIRCULAR ARC PROFILE FOR COMPRESSOR high angles of attack in a low-speed tunnel without sideslip. When STATOR the width of the lee side (governed by the potential flow) is BIAONAN ZHUANG (Nanjing Aeronautical Institute, People's insufficient for the free development of both side vortices, the Republic of China) Journal of Aerospace Power (ISSN 1000-8055), weak vortex is pushed upward by the strong vortex. Consideration vol. 3, April 1988, p. 153-157, 189. In Chinese, with abstract in is given to the effect of turbulence and adverse pressure. K.K. English. Blowing experiments have been completed on 21 kinds of A89-1e659* National Aeronautics and Space Administration. reversed tandem cascades with different geometrical parameters. Ames Research Center, Moffett Field, Calif. The cascades were designed by the aid of a computer program COMPUTATIONAL FLUID DYNAMICS IN AEROSPACE with reference to the configurations of the tandem cascades of PAUL KUTLER, JOSEPH L. STEGER, and F. R. BAILEY (NASA, Turmo-IIIc, J69 and J85 compressor stators. The main flow Ames Research Center, Moffett Field, CA) IN: International Pacific performances were obtained in the form of a group of curves. Air and Space Technology Conference, Melbourne, Australia, Nov. Three conclusions are drawn as follows: (1) the turning angle of 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive the reversed tandem cascade is larger than that of a single blade Engineers, Inc., 1988, p. 385-400. refs cascade, while the pressure loss coefficient is smaller, (2) the (SAE PAPER 872446) reversed cascades still possess a better performance even if the The status of computational fluid dynamics (CFD) is addressed incident angle is about -13 deg, and (3) the relative displacement in terms of methods, examples of CFD solutions, and computer and the relative axial distance of reversed tandem cascades should technology. The examples are divided into aerospace applications be matched well. Author and fluid physics applications, with the aerospace applications section being further divided into internal and external flows. The A89-11053# role CFD is expected to play in supporting the goals set forth by APPLICATION OF AN ARTIFICIAL DENSITY SCHEME OF the Aeronautical Policy Review Committee established by the Office POTENTIAL STREAM FUNCTION METHOD TO DESIGN OF of Science and Technology Policy is noted. K.K. AIRFOIL BO LIU (Northwestern Polytechnical University, Xian, People's A89-10660 Republic of China) Journal of Aerospace Power (ISSN 1000-8055), UNIFIED COMPUTATION METHOD OF UNSTEADY vol. 3, July 1988, p. 223-226, 282. In Chinese, with abstract in SUPERSONIC/HYPERSONIC FLOW PAST TWO DIMENSIONAL English. FLAT PLATE AND RECTANGULAR WINGS A potential stream-function method is applied to designing JING-SONG CHEN, HAN-MIN YANG, and CAI-WEN ZHANG transonic airfoils. The flowfield is computed by solving the full (Nanjing Aeronautical Institute, People's Republic of China) IN: potential equations with the aid of a relaxation method. An International Pacific Air and Space Technology Conference, artificial-density scheme has been developed to replace the Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, type-related scheme. As compared with the latter, the PA, Society of Automotive Engineers, Inc., 1988, p. 401-414. artificial-density scheme employs an identical scheme in whole refs field and converges steadily. Numerical results show that this (SAE PAPER 872447) method is applicable to the initial design of compressor airfoils Using a perturbation method for the frequency to solve the and provides a better approximation of the actual conditions by two-dimensional unsteady Euler equations, solutions are obtained taking into account the effect of the axial velocity ratio. Author for a flat-plate airfoil in pitching and plunging oscillations which are a set of power series, including up to the sixth-order frequency A89-11056# term. The solutions are valid for low- and higher-frequency cases. TWO-DIMENSIONAL SUBSONIC DIFFUSER FLOW WITH With the aid of that solution and using supersonic linearized theory, UNIFORM SHEAR VELOCITY PROFILE AT INLET the closed approximate expression of unsteady loading distribution XIJUN HUANG, JINZHONG DONG, SHIXIN FAN, and CHENGSHU is given for rectangular wings in pitching and plunging oscillations. SHIO (Beijing Institute of Aeronautics and Astronautics, People's Author Republic of China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, July 1988, p. 235-238, 283. In Chinese, with abstract in A89-10661 English. NUMERICAL APPROACH OF ADVANCED TURBOPROP WITH A prediction method has been developed for average THREE-DIMENSIONAL EULER EQUATIONS parameters of a two-dimensional subsonic diffuser with a uniform SHIGERU SAITO, HIROSHI KOBAYASHt, YASUHIRO WADA shear velocity profile at the inlet. A complete solution of all flow (National Aerospace Laboratory, Tokyo, Japan), and YUICHI parameters can be obtained by interacting the zonal models and MATSUO (Tokyo, University, Japan) IN: International Pacific Air coupling them on common boundaries. The momentum integral and Space Technology Conference, Melbourne, Australia, Nov. and the entrainment equations are used for the boundary-layer 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive zone. The equations are closed by use of Cole's improved Engineers, Inc., 1988, p. 415-424. refs wall-wake velocity profile. Due to different development of the (SAE PAPER 872448) boundary layers on the upper and lower walls of the diffuser under Numerical analysis by solving the three-dimensional Euler conditions of the shear velocity profile in core flow, different
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equations are employed. Three actual diffusers are calculated by The conclusions presented in this paper may be applied to the tip this method and evaluated experimentally. The predictions by this sections of propellers or helicopter rotors for performance method for the streamwise distribution of the pressure coefficient, improvement. Author the velocity of the core flow, and the location of detachment are in good agreement with the test data. Author A89-11073 NUMERICAL SIMULATION OF STEADY TRANSONIC FLOW A89-11059# EXPERIMENTAL STUDY OF ROTATING STALL IN PAST AN 8-PERCENT DCA CASCADE AT A FREESTREAM SINGLE-STAGE AXIAL COMPRESSOR MACH NUMBER OF ABOUT 1 [NUMERICKE MODELOVANI STAClONARNIHO TRANSSONICKEHO OBTEKANI 8 PERCENT WEIYANG QIAO and ZONGYUAN WANG (Northwestern Polytechnical University, Xian, People's Republic of China) Journal DCA MRIZE S FREESTREAM M OF ABOUT 1] of Aerospace Power (ISSN 1000-8055), vol. 3, July 1988, p. KAREL KOZEL and MIROSLAVA VAVRINCOVA Zpravodaj VZLU 253-255, 285. In Chinese, with abstract in English. (ISSN 0044-5355), no. 3, 1988, p. 109-119. In Czech. refs A three-hole dynamic probe is described which can measure Two-dimensional transonic flow past an 8-percent DCA cascade at a freestream Mach number of about 1 was simulated numerically the unsteady flow direction, flow velocity, and total and static pressures of a two-dimensional flow field. Three miniature pressure by solving a two-dimensional system of Euler equations by the transducers are mounted in the probe to detect the pressure finite-volume method using the Mac Cormack explicit difference fluctuation of the unsteady flow. The dynamic pressure signals scheme. Computed and measured results are compared for freestream Mach numbers of 0.91-1.15. B.J. are recorded with a digital data-acquisition system controlled by a microcomputer. The flowfield in the rotating stall regime of a single-stage axial compressor can be studied by means of this probe and the system. Author A89-11080# A FURTHER IMPROVEMENT IN THE NUMERICAL METHOD OF SUPERSONIC INFINITESIMAL HORSESHOE VORTEX A89-11060# DISTRIBUTION" EXPERIMENTAL INVESTIGATION OF CONVERGENT SHOUQIN YU and QINGBING ZHANG (Nanjing Aeronautical EJECTOR NOZZLE/AFTERBODY IN WIND TUNNEL Institute, People's Republic of China) Acta Aerodynamica Sinica RONGHUA ZHANG (Chengdu Aircraft Co., People's Republic of (ISSN 0258-1825), voL 6, Sept. 1988, p, 324-332. In Chinese, China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, with abstract in English. refs July 1988, p. 256-258, 285. In Chinese, with abstract in English. A new smoothing operation is developed in this paper. This The work is aimed at determining the overall performance of a smoothing operation effectively eliminates large oscillations in the convergent ejector nozzle/afterbody with or without fixed auxiliary lifting-pressure coefficient distribution which can occur in numerical inlet doors. The experimental Mach numbers range from 0.6 to computations of supersonic infinitesimal horseshoe vortex 1.2. The nozzle pressure ratio extends from 2.6 to 4.3. The distribution. The lifting-pressure coefficient distribution, as corrected secondary weight flow ratio is 3.5 percent. The testing compared with the analytical results, is satisfactory at various technique presented gives the correlation of the axial momentum freestream Mach numbers. This new operation makes the present tare forces of bellows with the pressure measured in the bellows. numerical method suitable for complex supersonic configurations. The wind-tunnel test data can be revised in timely manner with Author the tare forces computed. The tests show that, due to the effect of the tertiary flow, the nozzle thrust coefficient and efficiency of the ejector nozzle with fixed auxiliary inlet doors increase by 1-1.6 A89-11081# and 1.6-2.8 percent, respectively, compared with a nozzle without INVESTIGATION ON WALL INTERFERENCE OF LOW-SPEED these doors. Author WIND TUNNEL WITH SLOTTED WALLS JIECHUAN FAN and QIUSHENG YANG (Harbin Aerodynamics A89-11061# Research Institute, People's Republic of China) Acta DYNAMIC DISTORTION IN FLOWFIELD DOWNSTREAM OF Aerodynamica Sinica (ISSN 0258-1825), vol. 6, Sept. 1988, p. TRANSONIC SHOCK-BOUNDARY LAYER INTERACTION 333-340. In Chinese, with abstract in English. refs ZHONGWEI HE (Nanjing Aeronautical Institute, People's Republic The paper shows the results of measuring force for calibration of China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, model DBM-01 and measuring wall static pressure in the DFVLR July 1988, p. 259-261, 286. In Chinese, with abstract in English. low-speed wind tunnel with slotted walls and dimensions 3.25 x refs 2.8 m. The effects of the main slot parameters (such as slot The dynamic distortions in a flowfield under transonic- configuration and open area ratio) on wall interference have been shock/turbulent-boundary-layer interactions of different inten- discussed and compared with computation results. It has been sities are investigated in a two-dimensional convergent- concluded that the slotted walls have various effects on reducing divergent duct. The power spectrum and probability-density wall interference. The test section with slotted walls can effectively functions of the total pressure signals are analyzed. A control reduce not only longitudinal but also lateral wall interference; the technique for this dynamic distortion is also presented. real effect of slots is smaller than that predicted theoretically. Author Author
A89-11064# A NEW APPROACH TO IMPROVEMENT OF FANS A89-11082# HANSHOU SU (Beijing Institute of Aeronautics and Astronautics, MEASUREMENTS OF UNSTEADY PRESSURE DISTRIBUTION People's Republic of China) Journal of Aerospace Power (ISSN ON A NACA 0012 PROFILE IN TRANSONIC FLOW 1000-8055), vol. 3, July 1988, p. 271-273, 287. In Chinese, with QIAOSEN WANG and CHUNHUA ZHU (Nanling Aeronautical abstract in English. Institute, People's Republic of China) Acta Aerodynamica Sinica This paper presents experimental results on three-dimensional (ISSN 0258-1825), vol. 6, Sept. 1988, p. 341-349. In Chinese, flowfields in the fan tip region for two actual fans. It is shown that with abstract in English. refs the fan performance can be significantly improved as proplets are Steady and unsteady pressure measurements on a attached to the blade tips. The improvement mechanisms have two-dimensional wing model in the NH-1 transonic wind tunnel of been studied and can be stated as follows: the proplets retain Nanjing Aeronautical Institute are described. The profile of the the tip vortex, and thus the tip-induced loss is reduced remarkably; model is NACA 0012. The model was oscillated in pitch about its additional propulsion moment is gained because the proplets partly 1/4 axis to generate the unsteady aerodynamic pressure. The balance the drag moment due to profile loss in the tip section. measurement system and technology are quite good. Author 02 AERODYNAMICS
A89-11083# are corrected. Several wings with different plane shape are THE VAPOR-SCREEN TECHNIQUE OF FLOW VISUALIZATION calculated. Calculation results are relatively close to the experiment IN THE INTERMITTENT TRANSONIC AND SUPERSONIC WIND results. Author TUNNEL JINSEN HONG (Beijing Institute of Aerodynamics, People's A89-11088# Republic of China) Acta Aerodynamica Sinica (ISSN 0258-1825), FINITE ELEMENT METHOD FOR CALCULATING TRANSONIC vol. 6, Sept. 1988, p. 350-357. In Chinese, with abstract in POTENTIAL FLOW AROUND AIRFOIL FROM PRESSURE English. MINIMUM INTEGRATION Equipment and test results of a vapor-screen flow visualization QI LU, GUOFU ZHANG, and ZUOSHENG YANG (Nanjing method developed for an intermittent transonic and supersonic Aeronautical Institute, People's Republic of China) Acta wind tunnel are discussed. The optimum density of fog in the Aerodynamica Sinica (ISSN 0258-1825), vol. 6, Sept. 1988, p. working section for obtaining high-quality vapor-screen photographs 382-387. In Chinese, with abstract in English. has been determined for the Mach number range 0.6-2.0 at model The transonic flow field around a NACA 0012 airfoil is calculated angles of attack up to 25 deg. Static pressures were obtained using the FEM from pressure-minimum integration of the full along the wall of a Laval nozzle as a function of the absolute potential equation. The artificial viscosity is introduced by way of humidity. Vapor-screen photographs for various flow pattern have using artificial density. The computational mesh is generated been obtained for a typical missile configuration. R.R. automatically in terms of analytical/numerical transformation. SLOR and a pseudotime iterative method are employed for solving the A89-11084# finite-element equation. Several numerical solutions are given. ANALYSIS OF TRANSONIC WINGS INCLUDING VISCOUS Author INTERACTION ZIQIANG ZHU (Beijing Institute of Aeronautics and Astronautics, A89-11105# People's Republic of China) and H. SOBIECZKY (DFVLR, Institut NUMERICAL SIMULATION OF SUPERSONIC FLOW OVER A fuer theoretische Stroemungsmechanik, Goettingen, Federal THREE-DIMENSIONAL CAVITY Republic of Germany) Acta Aerodynamica Sinica (ISSN DONALD P. RIZZETTA (USAF, Wright Aeronautical Laboratories, 0258-1825), vol. 6, Sept. 1988, p. 358-364. In Chinese, with abstract Wright-Patterson AFB, OH) AIAA Journal (ISSN 0001-1452), in English. refs vol. 26, July 1988, p. 799-807. Previously cited in issue 18, p. Transonic flow computations past aerodynamic configuratons 2806, Accession no. A87-42363. refs are complicated by interactions between the outer inviscid flow (usually containing shock waves) and effects created by the viscous A89-11106"# Iowa State Univ. of Science and Technology, flow near the surface and the wake. In an effort to improve Ames. computational tools, some potential-flow methods have been A NEW PNS CODE FOR CHEMICAL NONEQUIMBRIUM coupled with a three-dimensional integral boundary-layer method ":'LOWS for wings. This coupling models a weak interaction between viscous D. K. PRABHU, J. C. TANNEHILL (Iowa State University of Science and inviscid flow; some examples have been calculated and and Technology, Ames), and J. G. MARVIN (NASA, Ames Research compared with experimental data. Author Center, Moffett Field, CA) AIAA Journal (ISSN 0001-1452), vol. 26, July 1988, p. 808-815. Research supported by Iowa State A89-11085# University of Science and Technology. Previously cited in issue NUMERICAL SIMULATION OF COMPACT SCHEMES IN 08, p. 1036, Accession no. A87-22535. refs SUPER-SONIC VISCOUS FLOWS (Contract NAG2-245) YANWEN MA and DEXUN FU (Beijing Institute of Aerodynamics, People's Republic of China) Acta Aerodynamica Sinica (ISSN A89-.11108"# National Aeronautics and Space Administration. 0258-1825), vol. 6, Sept. 1988, p. 365-369. In Chinese, with abstract Langley Research Center, Hampton, Va. in English. refs MULTIGRID SOLUTION OF THE TWO-DIMENSIONAL EULER EQUATIONS ON UNSTRUCTURED TRIANGULAR MESHES Supersonic viscous flow around a sphere-cone is simulated numerically by solving the compressible Navier-Stokes equations. D. J. MAVRIPLIS (NASA, Langley Research Center, Hampton, The viscous part of the equations is treated using a correction VA) AIAA Journal (ISSN 0001-1452), vol. 26, July 1988, p. with operator addition (Fu and Ma, 1984). The normal derivatives 824-831. Previously cited in issue 08, p. 1037, Accession no. of the inviscid part are approximated with central differences. The A87-22577. refs streamwise derivatives are approximated with compact differences. The compact scheme has fourth-order accuracy. Jacobian matrix A89-11109# United Technologies Research Center, East Hartford, splitting and approximate factorization are used for solving the Conn. resulting implicit difference equations. With specially chosen matrix ANALYSIS OF COMPLEX HYPERSONIC FLOWS WITH splitting, the solutions of the implicit difference scheme can be STRONG VISCOUSIINVlSCID INTERACTION expressed explicitly. The scheme used in present paper has the G. D. POWER and T. J. BARBER (United Technologies Research advantages of both implicit and explicit schemes, and the Center, East Hartford, CT) AIAA Journal (ISSN 0001-1452), vol. comparison of the computed results with those obtained by 26, July 1988, p. 832-840. Research supported by the United Srivastava et al. (1978) is satisfactory. Author Technologies Corp., and NASA-DARPA NASP Program Office. Previously cited in issue 18, p. 2803, Accession no. A87-42309. A89-11086# refs RESEARCH ON THE COMPUTATIONAL METHOD OF AERODYNAMIC CHARACTERISTICS OF WING WITH VORTEX A89-11110"# Cornell Univ., Ithaca, N.Y. BREAKDOWN AT HIGH ANGLE OF ATTACK DIAGONAL IMPLICIT MULTIGRID ALGORITHM FOR THE GUOHUA BAO (Northwestern Polytechnical University, Xian, EULER EQUATIONS People's Republic of China) Acta Aerodynamica Sinica (ISSN DAVID A. CAUGHEY (Cornell University, Ithaca, NY) AIAA 0258-1825), vol. 6, Sept. 1988, p. 370-375. In Chinese, with abstract Journal (ISSN 0001-1452), vol. 26, July 1988, p. 841-851. Previously in English. refs cited in issue 08, p. 1037, Accession no. A87-22578. refs The longitudinal and lateral aerodynamic characteristics of a (Contract NAG3-645; NAG2-373) wing with low aspect ratio are calculated, considering the effect of vortex and vortex breakdown. On the basis of the lifting-surface A89-11115# theory of Purvis (1981 and 1982) and the suction simulation method PROPULSIVE VORTICAL SIGNATURE OF PLUNGING AND developed by Polhamus (1966), with reference to Lan's (1982) PITCHING AIRFOILS method, the aerodynamic characteristics at high angle of attack PETER FREYMUTH (Colorado, University, Boulder) AIAA Journal 02 AERODYNAMICS
(ISSN 0001-1452), vol. 26, July 1988, p. 881-883. Previously cited An approximate computational procedure for estimating the in issue 07, p. 932, Accession no. A88-22235. refs friction drag and heating rates on aerodynamic bodies is described (Contract F49620-84-C-0065) in this paper along with its applications to three-dimensional boundary layer flows and transient ablation problems. The A89-11116# procedure is an integral approach, and the basic idea lies in the ON NONLINEAR ASPECTS OF HYPERSONIC use of integral expressions for various aerodynamic quantities on BOUNDARY-LAYER STABILITY the body surface. The approximate solutions are compared with KENNETH F. STETSON (USAF, Wright Aeronautical Laboratories, available exact solutions, and the comparisons are remarkably Wright-Patterson AFB, OH) AIAA Journal (ISSN 0001-1452), vol. favorable. Author 26, July 1988, p. 883-885. refs Experimental results obtained using hot-wire anemometry are A89-11481 used to explore nonlinear effects in the application of linear stability PANEL METHODS IN AERODYNAMICS - SOME HIGHLIGHTS theory to hypersonic problems. The results demonstrate the H. W. M. HOEIJMAKERS (Nationaal Lucht- en presence of high-frequency disturbances (presumably nonlinear Ruimtevaartlaboratorium, Amsterdam, Nethe.rlmnd_) IN" Pmn_l disturbances), and show that the rapidly growincl second-mnd_= me[nods =n fluid mechanics with emphasis on aerodynamics; d;stu,b,=,,_,_ uan acnJeve relatively large amplitudes which may Proceedings of the Third GAMM-Seminar, Kiel, Federal Republic exceed the limits of a small-disturbance assumption. The present of Germany, Jan. 16-18, 1987. Brunswick, Federal Republic of nonlinear theory is not able to predict the measured disturbance Germany, Friedr. Vieweg und Sohn, 1988, p. 1-34. refs growth rates. R.R. A survey is presented of several aspects of the use and further development of panel methods in aerodynamics. Aspects discussed A89-11152" Vigyan Research Associates, Inc., Hampton, Va. include possible types of boundary conditions, low versus NUMERICAL SIMULATION OF THE VORTICAL FLOW OVER A higher-order formulations, simulation of subsonic and supersonic ROUND-EDGED DOUBLE-DELTA WING flow and modeling of wakes as well as of leading-edge vortex C.-H. HSU (Vigyan Research Associates, Inc., Hampton, VA) and separation. Also discussed are computational aspects of panel C. H. LIU (NASA, Langley Research Center, Hampton, VA) IN: methods and possible directions for new developments. The latter Developments in theoretical and applied mechanics. Volume 14; include the extension of the domain of applicability to compressible Proceedings of the Fourteenth Southeastern Conference on flow and the coupling with viscous flow methods, as well as ways Theoretical and Applied Mechanics, Biloxi, MS, Apr. 18, 19, 1988. to improve the efficiency of the panel method. Author University, MS, University of Mississippi, 1988, p. 28-36. refs Simulations of three-dimensional vortical flows over a thin double-delta wing with an aspect ratio of 2.05 have been performed. A89-11484 Steady-state solutions to the unsteady incompressible HISSS - A HIGHER-ORDER PANEL METHOD FOR SUBSONIC Navier-Stokes equations are obtained using a new implicit AND SUPERSONIC ATTACHED FLOW ABOUT ARBITRARY upwind-relaxation finite-difference scheme. The method is CONFIGURATIONS second-order accurate spatially and naturally dissipative. Numerical L. FORNASIER (Messerschmitt-Boekow-Blohm Gmbt4, Munich, results indicate that key features of both vortical interaction and Federal Republic of Germany) IN: Panel methods in fluid vortex breakdown are successfully simulated. The computed lift mechanics with emphasis on aerodynamics; Proceedings of the coefficients and lateral trajectories of the vortical cores are in Third GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. good agreement with the experimental data. Author 16-18, 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg und Sohn, 1988, p. 52-70. refs A89-11153" Old Dominion Univ., Norfolk, Va. A panel method is derived to produce stable results in solving UNSTEADY TRANSONIC AIRFOIL COMPUTATION USING the PrandtI-Glauert equations for supersonic flow. The origin of IMPLICIT EULER SCHEME ON BODY-FIXED GRID the previously encountered inconsistent surface pressure OSAMA A. KANDIL and H. ANDREW CHUANG (Old Dominion fluctuations is discussed. The present method employs higher-order University, Norfolk, VA) IN: Developments in theoretical and surface singularity distributions. A very general boundary value applied mechanics. Volume 14; Proceedings of the Fourteenth specification capability allows either subsonic or supersonic flow Southeastern Conference on Theoretical and Applied Mechanics, problems around geometrically complex three-dimensional Biloxi, MS, Apr. 18, 19, 1988. University, MS, University of configurations to be treated. Results are provided for a Mississippi, 1988, p. 37-46. refs cone-cylinder-cone configuration and a NASA TM 78792 supersonic (Contract NAG1-648) cruise wing-body configuration. R.R. The unsteady Euler equations have been derived for the flow relative motion with respect to a frame of reference that is rigidly A89-11487 attached to the moving airfoil. The grid is generated once by an THE PREDICTION OF TRANSONIC INTERFERENCE FLOW BY elliptic solver without a need for dynamic grid computation. An MEANS OF A HYBRID METHOD implicit factored finite-volume scheme has been developed and H. JAKOB (Messerschmitt-Boelkow-Blohm GmbH, Bremen, Federal implemented through a fully vectorized computer program. Implicit Republic of Germany) IN: Panel methods in fluid mechanics second-order and explicit second and fourth-order dissipations are with emphasis on aerodynamics; Proceedings of the Third added to the scheme. The boundary conditions are explicitly GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. 16-18, satisfied. The scheme is applied to steady and unsteady transonic 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg airfoil flows and the results are in good agreement with the und Sohn, 1988, p. 91-100. experimental data. For forced harmonic airfoil motions, periodic A hybrid method combining a panel method with a finite solutions are achieved within the third cycle of oscillation. difference method has been developed to calculate inviscid Author transonic interference flow in space. An H-type computation grid is established around a wing section profile in order to A89-11157 approximately solve the full potential equation governing transonic APPROXIMATE CALCULATIONS OF VISCOUS DRAG AND spatial flow in a specified wing section. The panel method AERODYNAMIC HEATING determines the cross flow in all nodes, and includes interference T. F. ZIEN (U.S. Navy, Naval Surface Warfare Center, Silver Spring, effects from the fuselage or nacelle. The finite difference method MD) IN: Developments in theoretical and applied mechanics. for planar flow then provides transonic flow results, taking into Volume 14; Proceedings of the Fourteenth Southeastern account oblique shocks on the contours. Appropriate Conference on Theoretical and Applied Mechanics, Biloxi, MS, compressibility corrections and the computation of second Apr. 18, 19, 1988. University, MS, University of Mississippi, 1988, derivatives of the velocity potential are considered. Wing-fuselage p. 79-87. refs results are compared with wind tunnel findings. R.R.
10 02 AERODYNAMICS
A89-11488" Old Dominion Univ., Norfolk, Va. is first obtained. The method involves dividing the lifting surface INTEGRAL EQUATION SOLUTION FOR TRANSONIC AND into panels on which one doublet and one upwash point are located. SUBSONIC AERODYNAMICS A set of linear algebraic equations is derived based on the OSAMA A. KANDIL and HONG HU (Old Dominion University, tangential flow condition at every upwash point and the time Norfolk, VA) IN: Panel methods in fluid mechanics with emphasis dependent strength of the singularity which is represented in a on aerodynamics; Proceedings of the Third GAMM-Seminar, Kiel, Fourier series. A parametric study reveals the influence of Federal Republic of Germany, Jan. 16-18, 1987. Brunswick, Federal discretization. R.R. Republic of Germany, Friedr. Vieweg und Sohn, 1988, p. 101-109. refs A89-11498 CALCULATION OF UNSTEADY TRANSONIC FLOW ABOUT (Contract NAG1-648) Two methods are presented to solve for the subsonic and OSCILLATING WINGS BY A FIELD PANEL METHOD transonic flows around airfoils. The first method is based on the R. VOSS (DFVLR, Institut fuer Aeroelastik, Goettingen, Federal integral solution of the full-potential equation with a shock-capturing Republic of Germany) IN: Panel methods in fluid mechanics technique only or with shock capturing-shock fitting technique. In with emphasis on aerodynamics; Proceedings of the Third the second method, the integral soluton of the full potential equation GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. 16-18, is coupled with an embedded region of Euler equations around 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg the shock location. The second method is a computationally und Sohn, 1988, p. 232-242. refs efficient technique for flows with strong shocks where the entropy A field panel method is described for calculating unsteady increase and vorticity production across the shock are not small. transonic perturbation flows about harmonically oscillating wings. Several numerical examples are presented and compared with The flow is modelled by dipole distributions on the mean wing the experimental data and other computational results. Author and wake surfaces and a source distribution in the flow field to account for the nonhomogeneous compressibility effects in the A89-11489 near field of the wing. The aerodynamic influence coefficients can STEADY AND UNSTEADY POTENTIAL FLOWS AROUND be calculated largely analytically, and the resulting system of AXlSYMMETRIC BODIES AND RING AIRFOILS equations is solved by a quickly converging block iteration. Coupling with finite difference methods can further increase the computation E. KATZER (DFVLR, Institut fuer Aeroelastik, Goettingen, Federal Republic of Germany) IN: Panel methods in fluid mechanics speed. Author with emphasis on aerodynamics; Proceedings of the Third GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. 16-18, A89°11499 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg A VORTEX-LATTICE METHOD FOR THE CALCULATION OF WING-VORTEX INTERACTION IN SUBSONIC FLOW und Sohn, 1988, p. 110-119. refs A higher-order BEM is used to calculate steady and unsteady S. WAGNER, CH. URBAN, and R. BEHR (Muenchen, Universitaet incompressible potential flows around axisymmetric bodies and der Bundeswehr, Neubiberg, Federal Republic of Germany) IN: Panel methods in fluid mechanics with emphasis on aerodynamics; thin ring airfoils. A Fourier decomposition of the flow field reduces the problem by one dimension, resulting in a very efficient algorithm. Proceedings of the Third GAMM-Seminar, Kiel, Federal Republic A stable fast algorithm for determining special elliptic integrals is of Germany, Jan. 16-18, 1987. Brunswick, Federal Republic of described. A quadrature formula for the integration of strong and Germany, Friedr. Vieweg und Sohn, 1988, p. 243-251. refs weak singularities is introduced which is exact for the leading A vortex lattice method based on a time-dependent discrete terms of the expansion. The exclusive representation of the flow procedure with zero-order doublet distributions is proposed for the by a vorticity distribution makes possible a simple implementation study of basic wing-vortex interactions in subsonic flow. A of the Kutta condition. R.R. continuous velocity distribution at the shear layers is obtained by spline functions and a differencing scheme. The method is applied A89-11496 to single or coupled, plane, thin wings with or without vortex ON THE EVALUATION OF AERODYNAMIC INFLUENCE separation at the sharp wing edges. Potential flow effects and their influence on the wing loads and the velocity field are found COEFFICIENTS H. SCHIPPERS (Nationaal Lucht- en Ruimtevaartlaboratorium, to be in good agreement with experimental results. R.R. Amsterdam, Netherlands) IN: Panel methods in fluid mechanics with emphasis on aerodynamics; Proceedings of the Third A89-11500 APPROXIMATION OF FREE AND BOUNDED VORTEX SHEETS GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. 16-18, 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg AT DELTA-WINGS und Sohn, 1988, p. 210-219. refs P. WIEMER, K. HAAG, and J. BALLMANN (Aachen, Rheinisch-Westfaelische Technische Hochschule, Federal Republic A panel method has been developed to solve the boundary integral equation for the vorticity distribution at an airfoil. The of Germany) IN: Panel methods in fluid mechanics with emphasis boundary integral operator is decomposed by splitting the contour on aerodynamics; Proceedings of the Third GAMM-Seminar, Kiel, integration, taking into account the singular behavior of the kernel Federal Republic of Germany, Jan. 16-18, 1987. Brunswick, Federal function near the trailing edge. The decomposition results in a Republic of Germany, Friedr. Vieweg und Sohn, 1988, p. 252-260. compact operator and a contractive operator. The compact refs operator contains a smooth kernel function which is approximated A higher-order panel method is used to investigate the influence by piecewise linear interpolation. It is found that the accuracy of free vortex sheets on the pressure distribution of delta-wings. decreases significantly for a fixed number of panels. R.R. In the present method, the bounded vortex sheets are represented by isoparametric elements in order to obtain a continuous doublet A89-11497 distribution without singular vortex lines for the wing itself. Free A DOUBLET POINT METHOD FOR THE CALCULATION OF vortex layers are represented by panels along the vortex lines UNSTEADY PROPELLER AERODYNAMICS specified by the wing doublet distribution. Employing two independent geometry parameters for each panel, the method is J. SCHOENE (DFVLR, Institut fuer Entwurfsaerodynamik, shown to successfully model the free vortex sheets. R.R. Brunswick, Federal Republic of Germany) IN: Panel methods in fluid mechanics with emphasis on aerodynamics; Proceedings of the Third GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. A89-12130" University Coll. of Swansea (Wales). 16-18, 1987. Brunswick, Federal Republic of Germany, Friedr. FINITE ELEMENT EULER COMPUTATIONS IN THREE Vieweg und Sohn, 1988, p. 220-231. refs DIMENSIONS A lifting surface theory for unsteady flowfields of propellers in JAIME PERAIRE, JOAQUIN PEIRO, LUCA FORMAGGIA, KEN an incompressible medium has been developed. The governing MORGAN, and OLGIERD C. ZIENKIEWICZ (Swansea, University integral equation relating the pressure Ioadings and induced effects College, Wales) International Journal for Numerical Methods in
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Engineering (ISSN 0029-5981), vol. 26, Oct. 1988, p. 2135-2159. A89-12553# Research supported by the Research Corp. refs TRANSONIC COMPUTATIONS ABOUT COMPLEX (Contract NAGW-478) CONFIGURATIONS USING COUPLED INNER AND OUTER A two-step explicit FEM solution algorithm for the FLOW EQUATIONS three-dimensional compressible Euler and Navier-Stokes equations UNO G. NAVERT and YNGVE C-J. SEDIN (Saab-Scania, AB, based on unstructured triangular and tetrahedral grids is described Linkoping, Sweden) (ICAS, Congress, 15th, London, England, and demonstrated. The method represents an extension and Sept. 7-12, 1986, Proceedings. Volume 1, p. 303-312) Journal of refinement of the algorithms presented by Loehner et al. (1984 Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 677-683. and 1985), Peraire et al. (1987), and Morgan et al. (1987). The Previously cited in issue 24, p. 3530, Accession no. A86-49008. formulation and numerical implementation are outlined; the mesh refs generation, data structures, and adaptive remeshing are explained; and results for a two-dimensional airfoil, a three-dimensional engine A89-12554# air intake, a B747 in landing configuration, and a generic fighter NUMERICAL SOLUTIONS OF INDUCED VELOCITIES BY aircraft are presented in extensive graphics and discussed in SEMI-INFINITE TIP VORTEX LINES detail. T.K. YIHWAN DANNY CHIU and DAVID A. PETERS (Georgia Institute of Technology, Atlanta) Journal of Aircraft (ISSN 0021-8669), A89-12135" Purdue Univ., West Lafayette, Ind. vol. 25, Aug. 1988, p. 684-694. refs PREDICTION OF INCIDENCE EFFECTS ON OSCILLATING (Contract DAAG29-83-K-0133; DAAG29-85-K-0228) AIRFOIL AERODYNAMICS BY A LOCALLY ANALYTICAL The method of Rand and Rosen (1984) for improving METHOD convergence on computed axial induced velocity for a helical wake HSIAO-WEI D. CHIANG and SANFORD FLEETER (Purdue is extended to include all velocity components, all points in the University, West Lafayette, IN) International Journal for Numerical wake, and nonhelical vortex lines (contraction). The method is Methods in Engineering (ISSN 0029-5981), vol. 26, Oct. 1988, p. based on finding upper and lower bounds on the truncated integral. 2227-2238. NASA-USAF-supported research, refs Comparisons with other methods show that the present approach A complete mathematical model is formulated to analyze the is efficient and accurate. Further, it avoids the errors associated effects of mean-flow incidence angle on the unsteady aerodynamics with discretization of the vortex lines. Convergence occurs in only of an oscillating airfoil in an incompressible flow field. A velocity three to five revolutions, about 10 percent of the normal potential formulation is utilized. The steady flow is independent of requirement. Author the unsteady flow field but coupled to it through the boundary conditions on the oscillating airfoil. The numerical solution technique A89-12557"# Dayton Univ., Ohio. for both the steady and unsteady flow fields is based on a locally NAVIER-STOKES SOLUTION TO THE FLOWFIELD OVER ICE analytical method. The flow model and solution method are then ACCRETION SHAPES verified through the excellent correlation obtained with the J. N SCOTT, W. L. HANKEY, F. J. GIESSLER, and T. P. GIELDA Theodorsen oscillating-flat-plate and Sears transverse-gust classical solutions. The effects of mean flow incidence on the (Dayton, University, OH) Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 710-716. Previously cited in issue 08, p. steady and oscillating airfoil aerodynamics are then investigated. 1033, Accession no. A87-22414. refs Author (Contract NAG3-665)
A89-12316 A89-12559# AEROTHERMODYNAMICS - THE REQUIRED TOOLS LOW-REYNOLDS-NUMBER AIRFOIL DESIGN FOR THE M.I.To A. J. WAKE (British Aerospace, PLC, London, England) SAE, DAEDALUS PROTOTYPE - A CASE STUDY Aerospace Vehicle Conference, Annapolis, MD, Apr. 18-20, 1988. MARK DRELA (MIT, Cambridge, MA) Journal of Aircraft (ISSN 12 p. refs (SAE PAPER 880928) 0021-8669), vol. 25, Aug. 1988, p. 724-732. Research supported by MIT and Smithsonian Institution. refs HOTOL is a single-stage-to-orbit vehicle which will be marketed An account is given of the design rationale that led to the use as an economic launch system for placing payloads in low earth of three different airfoil profiles in the wing of the Light Eagle orbit at about one-fifth of the cost of an equivalent Space Shuttle human-powered aircraft prototype. The profiles were chosen for launch. This paper discusses how HOTOL will cope with the Re numbers of 500,000, 375,000, and 250,000 using numerical problems of aerodynamic heating and force/moments/control simulation, and optimized in such a way as to both minimize powers. A program of technology development covering theoretical transitional separation bubbles and accommodate structural and methods, wind tunnel experiments, and free-flight models is described. C.D. fabricational constraints. The numerical model employed represents inviscid flow by means of the Euler equations, and viscous flow by means of an integral boundary layer formulation; transitional A89-12551"# Naval Ship Research and Development Center, separation bubbles and their associated losses are calculated by Bethesda, Md. the inclusion of strong viscous-inviscid coupling and an amplification TRANSONIC CHARACTERISTICS OF A HUMPED AIRFOIL transition criterion in the overall equation system. O.C. TSZE C. TAI, GREGORY G. HUSON (David W. Taylor Naval Ship Research and Development Center, Bethesda, MD), RAYMOND A89-12566# M. HICKS (NASA, Ames Research Center, Moffett Field, CA), and GENMAP - COMPUTER CODE FOR MISSION ADAPTIVE GERALD M. GREGOREK (Ohio State University, Columbus) PROFILE GENERATION Journal of Aircraft (ISSN 0021-8669), vot. 25, Aug. 1988, p. 673, 674. Abridged. Previously cited in issue 18, p. 2804, Accession S. C. GUPTA (Institute of Armament Technology, Poona, India) no. A87-42336. Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 766-768. Optimum leading-edge flap (LEF) and trailing-edge flap (TEF) A89-12552"# Vigyan Research Associates, Inc., Hampton, Va. deflections constitute a Mission-Adaptive Profile (MAP) wing INCOMPRESSIBLE NAVIER-STOKES COMPUTATIONS FOR A system. The 'GENMAP' computer code has been developed to ROUND-EDGED DOUBLE-DELTA WING generate minimum-drag MAP deflections of wing LEF and TEF C.-H. HSU, P.-M HARTWICH (Vigyan Research Associates, Inc., for both subsonic and supersonic freestream conditions, as Hampton, VA), and C. H. LIU (NASA, Langley Research Center, functions of both Mach number and angle-of-attack. Drag Hampton, VA) Journal of Aircraft (ISSN 0021-8669), vol. 25, reductions of as much as 55 percent are achievable in the subsonic Aug. 1988, p. 675, 676. Abridged. Previously cited in issue 19, p. regime. Compressibility is noted to deteriorate the optimization 2941, Accession no. A87-44933. refs effort. O.C.
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N89-10004# National Aerospace Lab., Tokyo (Japan). 19 p Presented at the International Powered Life Conference in MEASUREMENT OF AERODYNAMIC CHARACTERISTICS OF Santa Clara, Calif., 7-10 Dec. 1987 A HANG-GMDER-WING BY GROUND RUN TESTS USING A (NASA-TM-100061; A-88072; NAS 1.15:100061) Avail: NTIS HC TEST VEHICLE A03/MF A01 CSCL 01A KOKI HOZUMI, MASAKI KOMODA, TAKATSUGU ONO, and A supersonic STOVL fighter aircraft aerodynamic research YUKICHI TSUKANO 1987 29 p In JAPANESE; ENGLISH program is under way at NASA Ames Research Center. The summary research focuses on technology development for this type of aircraft (NAL-TR-953; ISSN-0389-4010) Avail: NTIS HC A03/MF A01 and includes generating an extensive aerodynamic database and In order to investigate longitudinal force and moment resolving particular aerodynamic uncertainties for various twin- and characteristics of a hang-glider-wing, ground run tests were single-engine aircraft concepts. Highlights of the results from this conducted using a test vehicle. A hang-glider-wing was installed program are presented. The highlights include propulsion-induced on a test vehicle using a six-components-balance for wing tunnel effects on the aircraft drag, prediction capabilities, volume use. Aerodynamic force and moment were measured during the integration for minimizing drag, and wave drag and aerodynamic vehicle run at various constant speeds. Geometrical twist efficiency comparisons. Results indicate that estimated STOVL distribution along the wing span was recorded as well. Measured fighter performance is roughly comparable to the performance of force and moment data were corrected for possible ground effect modem conventional fighters in terms of wave drag and and upwash effect due to movement of the vehicle. The lift curve aerodynamic efficiency. Author slope was about 23 percent smaller than that predicted by theory for a rigid wing of the same geometry. An abrupt increase in the N89-10020"# National Aeronautics and Space Administration. pitching moment was measured as C sub L decreased from positive Langley Research Center, Hampton, Va. to negative. These particular features indicate that aeroelastic WEAK-WAVE ANALYSIS OF SHOCK INTERACTION WITH A deformations affect the aerodynamic characteristics of hang-gliders SLIPSTREAM and/or motor-hang-gliders are mandatory for their flight safety. RAYMOND L. BARGER Nov. 1988 20 p Using the Moriya method, aeroelastic camber variations at typical (NASA-TP-2848; L-16469; NAS 1.60:2848) Avail: NTIS HC spanwise stations were estimated for each combination of dynamic A03/MF A01 CSCL 01A pressure and section angle of attack. Applying the Weissinger A weak wave analysis of shock interaction with a slipstream is method, lift and pitching moment characteristics were analyzed presented. The theory is compared to that for the acoustic case twist distributions. By comparing these analysis with the measured and to the exact nonlinear analysis. Sample calculations indicate data, geometrical deformations of the flexible wing were that the weak wave theory yields a good approximation to the elucidated. Author exact solution when the shock waves are sufficiently weak that the associated entropy increase is negligible. A qualitative N89-10005# Aeronautical Research Labs., Melbourne discussion of the case of counterflowing streams is also included. (Australia). Author A POTENTIAL THEORY FOR THE STEADY SEPARATED FLOW ABOUT AN AEROFOIL SECTION N89-10022"# National Aeronautics and Space Administration. TRAN-CONG TON Feb. 1988 31 p Ames Research Center, Moffett Field, Calif. (ARL-AERO-R-176; AR-004-596) Avail: NTIS HC A03/MF A01 NAVIER-STOKES SIMULATION OF TRANSONIC WING FLOW An incompressible potential flow theory is used to determine FIELDS USING A ZONAL GRID APPROACH the steady separated flow about an airfoil. The theory permits a NEAL M. CHADERJIAN Jan. 1988 26 p continuous variation from fully-attached (Joukowski) flow to (NASA-TM-100039; A-88020; NAS 1.15:100039) Avail: NTIS HC fully-separated (Helmholtz) flow, with the Kutta condition always A03/MF A01 CSCL 01A satisfied at the trailing edge, and with the position of the separation The transonic Navier-Stokes code was used to simulate flow point as an assignable parameter to determine the flow fields about isolated wings for workshop wind-tunnel and free-air configuration. The method is also applicable to other flows such cases using the thin-layer Reynolds-averaged Navier-Stokes as that about a flat plate with a rear free-stream flap. Author equations. An implicit finite-difference scheme based on a diagonal version of the Beam-Warming algorithm was used to integrate the N89-10006# Advisory Group for Aerospace Research and governing equations. A zonal grid approach was used to allow Development, Neuilly-Sur-Seine (France). Propulsion and efficient grid refinement near the wing surface. The flow field was Energetics Panel. sensitive to the turbulent transition model, and flow unsteadiness AGARD MANUAL ON AEROELASTICITY IN AXIAL-FLOW was observed for a wind-tunnel case but not for the corresponding TURBOMACHINES. VOLUME 2: STRUCTURAL DYNAMICS free-air case. The specification of experimental pressure at the AND AEROELASTICITY wind-tunnel exit plane is the primary reason for the difference of MAX F. PLATZER, ed. and FRANKLIN O. CARTA, ed. (United these two numerical solutions. Author Technologies Research Center, East Hartford, Conn.) Jun. 1988 266 p N89-10024"# National Aeronautics and Space Administration. (AGARD-AG-298-VOL-2; ISBN-92-835-0467-4) Avail: NTIS HC Langley Research Center, Hampton, Va. A12/MF A01 VALIDATION OF A PAIR OF COMPUTER CODES FOR An overview of structural dynamics characteristics and analysis ESTIMATION AND OPTIMIZATION OF SUBSONIC methods applicable to single blades and bladed assemblies is AERODYNAMIC PERFORMANCE OF SIMPLE HINGED-FLAP presented. The blade fatigue problem and its assessment methods, SYSTEMS FOR THIN SWEPT WINGS and life-time predictions are considered. Aeroelastic topics covered HARRY W. CARLSON (PRC Systems Services Co., Hampton, Va.) include: the problem of blade-disc shroud aeroelastic coupling, and CHRISTINE M. DARDEN Washington Nov. 1988 118 p formulations and solutions for tuned and mistuned rotors, and (NASA-TP-2828; L-16428; NAS 1.60:2828) Avail: NTIS HC instrumentation on test procedures to perform a fan flutter test. A06/MF A01 CSCL 01A The effect of stagnation temperature and pressure on flutter is Extensive correlations of computer code results with demonstrated and currently available forced vibration and flutter experimental data are employed to illustrate the use of linearized design methodology is reviewed. theory attached flow methods for the estimation and optimization of the aerodynamic performance of simple hinged flap systems. N89-10017"# National Aeronautics and Space Administration. Use of attached flow methods is based on the premise that high Ames Research Center, Moffett Field, Calif. levels of aerodynamic efficiency require a flow that is as nearly WAVE DRAG AND HIGH-SPEED PERFORMANCE OF attached as circumstances permit. A variety of swept wing SUPERSONIC STOVL FIGHTER CONFIGURATION configurations are considered ranging from fighters to supersonic DONALD A. DURSTON and RONALD K. STONUM Jan. 1988 transports, all with leading- and trailing-edge flaps for enhancement
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of subsonic aerodynamic efficiency. The results indicate that Aerodynamics Research Facility. The model incorporated the linearized theory attached flow computer code methods provide a external augmentor concept developed by DHC. Since the first rational basis for the estimation and optimization of flap system test at Ames in 1979, the fuselage augmentor nozzle array has aerodynamic performance at subsonic speeds. The analysis also been redesigned with a larger pitch and notched nozzles instead indicates that vortex flap design is not an opposing approach but of plain slot nozzles. Thrust augmentation of the ejector as is closely related to attached flow design concepts. The successful measured at Ames Research Center was lower than that measured vortex flap design actually suppresses the formation of detached in the DHC laboratory. It is believed that this difference is due to vortices to produce a small vortex which is restricted almost entirely the high temperature of the prir0ary jet flow as compared to the to the leading edge flap itself. Author DHC blown-down rig. An ejector-lift/vectored thrust configuration was also included in the recent tests. This is an arrangement N89-10025"# Pratt and Whitney Aircraft, East Hartford, Conn. where the fuselage augmentor is shortened in the chordwise TURBOFAN FORCED MIXER LOBE FLOW MODELING. PART direction and the extra thrust is generated with a vectorable, ventral 3: APPLICATION TO AUGMENT ENGINES Final Report nozzle. In free air the shortened fuselage augmentor produced T. BARBER, G. C. MOORE, and J. R. BLATT Washington the same augmentation as the long augmentor. In ground proximity, NASA Oct. 1988 32 p at a height of 27 in, and with zero pitch angle, a negative ground (Contract NAS3-23039) effect was measured equal to 6.5 percent of the free-air lift. (NASA-CR-4147; E-4085; NAS 1.26:4147) Avail: NTIS HC Author A03/MF A01 CSCL 01A Military engines frequently need large quantities of thrust for short periods of time. The addition of an augmentor can provide N89-10029"# North Carolina State Univ., Raleigh. Dept. of such thrust increases but with a penalty of increased duct length Mechanical and Aerospace Engineering. and engine weight. The addition of a forced mixer to the augmentor A TRANSONIC INTERACTIVE BOUNDARY-LAYER THEORY improves performance and reduces the penalty, as well as providing FOR LAMINAR AND TURBULENT FLOW OVER SWEPT a method for siting the required flame holders. In this report two WINGS Final Report augmentor concepts are investigated: a swirl-mixer augmentor and SHAWN H. WOODSON and FRED R. DEJARNETTE a mixer-flameholder augmentor. Several designs for each concept Washington Oct. 1988 82 p are included and an experimental assessment of one of the (Contract NCC1-22) swirl-mixer augmentors is presented. Author (NASA-CR-4185; NAS 1.26:4185) Avail: NTIS HC A05/MF A01 CSCL 01A N89-10026# Office National d'Etudes et de Recherches A 3-D laminar and turbulent boundary-layer method is developed Aerospatiales, Paris (France). for compressible flow over swept wings. The governing equations LA RECHERCHE AEROSPATIALE, BIMONTHLY BULLETIN, and curvature terms are derived in detail for a nonorthogonat, NUMBER 1987-4, 239/JULY-AUGUST curvilinear coordinate system. Reynolds shear-stress terms are ESA Jun. 1988 74 p Transl. into ENGLISH of La Recherche modeled by the Cebeci-Smith eddy-viscosity formulation. The Aerospatiale, Bulletin Bimestriel (Paris, France, ONERA), no. governing equations are descretized using the second-order 1987-4, 239/Jul.-Aug., 1987 accurate, predictor-corrector finite-difference technique of Matsuno, (ESA-TT-1088; ETN-88-93051) Avail: NTIS HC A04/MF A01 which has the advantage that the crossflow difference formulas Particle approximation of the two-dimensional Navier-Stokes are formed independent of the sign of the crossflow velocity equations; infrared system evaluation apparatus; strong coupling component. The method is coupled with a full potential wing/body between inviscid fluid and boundary layer for airfoils with sharp inviscid code (FLO-30) and the inviscid-viscous interaction is leading edge (two-dimensional incompressible steady case); performed by updating the original wing surface with the viscous continuum damage mechanics and its applicaton to structural displacement surface calculated by the boundary-layer code. The lifetime predictions; unsteady three-dimensional stall on a number of these global iterations ranged from five to twelve rectangular wing; and Fourier condition in integral methods: depending on Mach number, sweep angle, and angle of attack. application to thin bodies, are discussed. Several test cases are computed by this method and the results are compared with another inviscid-viscous interaction method N89-10027# Office National d'Etudes et de Recherches (TAWFIVE) and with experimental data. Author Aerospatiales, Paris (France). UNSTEADY THREE-DIMENSIONAL STALL ON A RECTANGULAR WING N89-10034"# National Aeronautics and Space Administration. J. J. COSTES /n its La Recherche Aerospatiale, Bimonthly Bulletin, Langley Research Center, Hampton, Va. Number 1987-4, 239/July-August p 55-69 Jun. 1988 Transl. THE PROS AND CONS OF CODE VALIDATION into ENGLISH from La Recherche Aerospatiale, Bimestriel (Paris, PERCY J. BOBBITT Jul. 1988 49 p Presented at the 6th France, ONERA), no. 1987-4, 239/Jul.-Aug., 1987 AIAA Applied Aerodynamic Conference, Williamsburg, Va., 6-8 Jun. Avail: NTIS HC A04/MF A01 1988 Previously announced in IAA as A88-42125 Steady and unsteady stall are studied on a rectangular wing in (NASA-TM- 100657; NAS 1.15:100657; AIAA-PAPER-88-2535) normal flow. The wing is allowed to oscillate in pitch around the Avail: NTIS HC A03/MF A01 CSCL 01A fore quarter chord. Experiments performed at the S 2 wind-tunnel Computational and wind tunnel error sources are examined in Chalais-Meudon with a rectangular wing and a wind velocity of and quantified using specific calculations of experimental data, 95 m/s are in good agreement with the results obtained from the and a substantial comparison of theoretical and experimental theory developed. Author results, or a code validation, is discussed. Wind tunnel error sources considered include wall interference, sting effects, Reynolds N89-10028"# De Havilland Aircraft Co. of Canada Ltd., number effects, flow quality and transition, and instrumentation Downsview (Ontario). such as strain gage balances, electronically scanned pressure PHASE 4 STATIC TESTS OF THE J-97 POWERED, EXTERNAL systems, hot film gages, hot wire anemometers, and laser AUGMENTOR V/STOL MODEL AT THE NASA, AMES velocimeters. Computational error sources include math model RESEARCH CENTER, NOVEMBER 1983 equation sets, the solution algorithm, artificial viscosity/dissipation, D. B. GARLAND Dec. 1985 87 p boundary conditions, the uniqueness of solutions, grid resolution, (Contract NASW-2797) turbulence modeling, and Reynolds number effects. It is concluded (NASA-CR-177395; NAS 1.26:177395) Avail: NTrS HC A05/MF that, although improvements in theory are being made more quickly A01 CSCL 01A than in experiments, wind tunnel research has the advantage of A large-scale, ejector-lift V/STOL Model, powered by a J-97 the more realistic transition process of a right turbulence model in engine, was tested at the NASA Ames Research Center Outdoor a free-transition test. Author
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• m • 02 AERODYNAMICS
N89-10840# Sandia National Labs., Albuquerque, N. Mex. N89-10844"# National Aeronautics and Space Administration. AN APPROXIMATE, MAXIMUM TERMINAL VELOCITY Lewis Research Center, Cleveland, Ohio. DESCENT TO A POINT THREE COMPONENT LASER ANEMOMETER G. RICHARD EISLER and DAVID G. HULL (Texas Univ., Austin.) MEASUREMENTS IN AN ANNULAR CASCADE OF CORE 1987 15 p Presented at the Guidance, Navigation and Control TURBINE VANES WITH CONTOURED END WALL Conference, Minneapolis, Minn., 15 Aug. 1988 LOUIS J. GOLDMAN and RICHARD G. SEASHOLTZ Nov. 1988 (Contract DE-AC04-76DP-00789) 44 p (DE88-000349; SAND-87-3011C; CONF-880818-2) Avail: NTIS (NASA-TP-2846; E-4183; NAS 1.60:2846) Avail: NTIS HC HC A03/MF A01 A03/MF A01 CSCL 20D No closed form control solution exists for maximizing the The three mean velocity components were measured in a terminal velocity of a hypersonic glider at an arbitrary point. As an full-scale annular turbine stator cascade with contoured hub end alternative, this study uses neighboring extremal theory to provide wall using a newly developed laser anemometer system. The a sampled data feedback law to guide the vehicle to a constrained anemometer consists of a standard fringe configuration using ground range and altitude. The guidance algorithm is divided into fluorescent seed particles to measure the axial and tangential two parts: (1) computation of a nominal, approximate, maximum components. The radial component is measured with a scanning terminal velocity trajectory to a constrained final altitude and confocal Fabry-Perot interferometer. These two configurations are computation of the resulting unconstrained groundrange, and (2) combined in a single optical system that can operate simultaneously computation of the neighboring extremal control perturbation at in a backscatter mode through a single optical access port. the sample value of flight path angle to compensate for changes Experimental measurements were obtained both within and in the approximate physical model and enable the vehicle to reach downstream of the stator vane row and compared with calculations the on-board computed groundrangeo The trajectories are from a three-dimensional inviscid computer program. In addition, characterized by glide and dive flight to the target to minimize the detailed calibration procedures are described that were used, prior time spent in the denser parts of the atmosphere. The proposed to the experiment, to accurately determine the laser beam probe on-line scheme successfully brings the final altitude and range volume location relative to the cascade hardware. Author constraints together, as well as compensates for differences in flight model, atmosphere, and aerodynamics at the expense of N89-10847# National Aeronautical Lab., Bangalore (India). guidance update computation time. Comparison with an Aerodynamics Div. independent, parameter optimization solution for the terminal TESTS ON 3 NACA 0012 AIRFOIL MODELS OF DFVLR IN THE velocity is excellent. DOE NAL 0.3 TUNNEL: AN ASSESSMENT OF 2-D WALL INTERFERENCE R. GOPINATH, SANTHA KUMARI, and R. SRtDHARAN Dec. 1987 117 p (TM-AE-8705) Avail: NTIS HC A06/MF A01 N89-10841# Sandia National Labs., Albuquerque, N. Mex. Tests were conducted on three NASA 0012 airfoil models. A AERODYNAMIC DESIGN CONSIDERATIONS FOR A range of Mach numbers from 0.6 to 0.9 and incidence of the FREE-FLYING DUCTED PROPELLER model from 0 degrees to 7 degrees with both free and fixed ROBERT J. WEIR Jan. 1988 32 p Presented at the AIAA transition on the airfoil model, was covered. Flow visualization Atmospheric Flight Mechanics Conference, Minneapolis, Minn., 15 studies were also carried out at a few Mach numbers and incidence. Aug. 1988 Interference corrections were computed from wall pressures (Contract DE-AC04-76DP-00789) measured along the slat on the top and bottom liners of the (DE88-006867; SAND-88-0021C; CONF-880836-1) Avail: NTIS modified test section and the corrected data compared with those HC A03/MF A01 from other tunnels. An analysis of the data on the three models The design philosophy for a free-flying vehicle powered by a of chord lengths 100mm, 150mm and 200mm respectively, from ducted propeller is presented from an aerodynamic viewpoint. the standpoint of interference due to tunnel walls, is presented. Airframe design concentrates on duct inlet lip curvature, diffuser Author angle, and methods of vehicle control. Wind tunnel test results are given to evaluate two inlet designs, two exit designs, and the N89-10849"# National Aeronautics and Space Administration. effect of external appendages such as a camera pod or a forebody. Ames Research Center, Moffett Field, Calif. Finally, a simple, analytic method of ducted propeller blade design THE 1987 GROUND VORTEX WORKSHOP is presented and the results compared with an existing ducted RICHARD J. MARGASON, ed. Feb. 1988 216 p Workshop propeller blade. DOE held at Moffett Field, Calif., 22-23 Apr. 1987 (NASA-CP-10008; A-88008; NAS 1.55:10008) Avail: NTIS HC A10/MF A01 CSCL 01A The purpose of this workshop was to discuss the current N89-10842"# National Aeronautics and Space Administration. understanding of the ground vortex phenomena and their effects Langley Research Center, Hampton, Va. on aircraft, and to establish directions for further research on EXPERIMENTAL RESULTS FOR THE EPPLER 387 AIRFOIL AT advanced, high-performance aircraft designs, particularly those LOW REYNOLDS NUMBERS IN THE LANGLEY concepts utilizing powered-lift systems; e.g., V/STOL. ASTOVL, LOW-TURBULENCE PRESSURE TUNNEL and STOL aircraft. ROBERT J. MCGHEE, BETTY S. WALKER, and BETTY F. MILLARD Oct. 1988 232 p N89-10850"# National Aeronautics and Space Administration. (NASA-TM-4062; L-16430; NAS 1.15:4062) Avail: NTIS HC Ames Research Center, Moffett Field, Calif. A11/MFA01 CSCL01A THE CHARACTERISTICS OF THE GROUND VORTEX AND ITS Experimental results were obtained for an Eppler 387 airfoil in EFFECT ON THE AERODYNAMICS OF THE STOL the Langley Low Turbulence Pressure Tunnel. The tests were CONFIGURATION conducted over a Mach number range from 0.03 to 0.13 and a VEARLE R. STEWART In its The 1987 Ground Vortex Workshop chord Reynolds number range for 60,000 to 460,000. Lift and p 1-38 Feb. 1988 pitching moment data were obtained from airfoil surface pressure Avail: NTIS HC A10/MF A01 CSCL 01A measurements and drag data for wake surveys. Oil flow The interaction of the free stream velocity on the wall jet formed visualization was used to determine laminar separation and by the impingement of deflected engine thrust results in a rolled turbulent reattachment locations. Comparisons of these results with up vortex which exerts sizable forces on a short takeoff (STOL) data on the Eppler 387 airfoil from two other facilities as well as airplane configuration. Some data suggest that the boundary layer the Eppler airfoil code are included. Author under the free stream ahead of the configuration may be important
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in determining the extent of the travel of the wall jet into the general, the steady state results from the VRF matched static oncoming stream. Here, early studies of the ground vortex are results obtained from the wind tunnel once the flow field stabilized examined, and those results are compared to some later data over the flat portion of the ground board. Author obtained with moving a model over a fixed ground board. The effect of the ground vortex on the aerodynamic characteristics N89-10855"# Florida State Univ., Tallahassee. Fluid Mechanics are discussed. Author Research Lab. EFFECTS OF A GROUND VORTEX ON THE AERODYNAMICS N89-10852"# National Aeronautics and Space Administration. OF AN AIRFOIL Ames Research Center, Moffett Field, Calif. A. KROTHAPALLI and D. LEOPOLD (Stanford Univ., Calif.) In GROUND VORTEX FLOW FIELD INVESTIGATION NASA, Ames Research Center, The 1987 Ground Vortex Workshop RICHARD E. KUHN, JOHN H. DELFRATE, and JAMES E. p 147-166 Feb. 1988 ESHLEMAN (Lockheed-California Co., Burbank.) In its The 1987 (Contract NAG2-111; NAG2-198) Ground Vortex Workshop p 61-90 Feb. 1988 Avail: NTIS HC A10/MF A01 CSCL 01A Avail: NTIS HC A10/MF A01 CSCL 01A An experimental investigation was carried out to study the Flow field investigations were conducted at the NASA aerodynamics of an airfoil with a rectangular jet exiting from its Ames-Dryden Flow Visualization Facility (water tunnel) to lower surface at fifty percent of the chord. The airfoil was tested investigate the ground effect produced by the impingement of jets with and without the influence of a ground plane. Surface static from aircraft nozzles on a ground board in a STOL operation. pressures were measured on the airfoil at jet to free stream velocity Effects on the overall flow field with both a stationary and a ratios ranging from 0 to 9. From these pressures, the variation of moving ground board were photographed and compared with similar C sub L with velocity ratio was easily determined. The data found in other references. Nozzle jet impingement angles, measurements indicated significant positive and negative pressure nozzle and inlet interaction, side-by-side nozzles, nozzles in tandem, regions on the lower surface of the airfoil ahead of and after the and nozzles and inlets mounted on a flat plate model were nozzle exit respectively. The presence of a ground plane enhanced investigated. Results show that the wall jet that generates the these pressure ,regions at low velocity ratios, but at a particular ground effect is unsteady and the boundary between the ground ratio for each plane location, a recirculation zone or vortex formed vortex flow field and the free-stream flow is unsteady. Additionally, ahead of the jet resulting in decreased pressures and a drop in C the forward projection of the ground vortex flow field with a moving sub L. Author ground board is one-third less than that measured over a fixed ground board. Results also showed that inlets did not alter the N89-10857"# National Aeronautics and Space Administration. ground vortex flow field. Author Ames Research Center, Moffett Field, Calif. NUMERICAL INVESTIGATION OF A JET IN GROUND EFFECT USING THE FORTIFIED NAVlER-STOKES SCHEME N89-10853"# Air Force Wright Aeronautical Labs., WILLIAM R. VANDALSEM and JOSEPH L. STEGER In its The Wright-Patterson AFB, Ohio. F-15 SMTD LOW SPEED JET EFFECTS WIND TUNNEL TEST 1987 Ground Vortex Workshop p 191-206 Feb. 1988 RESULTS Avail: NTIS HC A10/MF A01 CSCL 01A One of the flows inherent in VSTOL operations, the jet in WILLIAM B. BLAKE In NASA, Ames Research Center, The 1987 Ground Vortex Workshop p 91-119 Feb. 1988 ground effect with a crossflow, is studied using the Fortified Avail: NTIS HC A10/MF A01 CSCL01A Navier-Stokes (FNS) scheme. Through comparison of the simulation results and the experimental data, and through the Key results from low speed wind tunnel testing of the F-15 variation of the flow parameters (in the simulation) a number of STOL and Maneuver Technology Demonstrator (SMDT) with thrust interesting characteristics of the flow have been observed. For reversers are presented. Longitudinally, the largest induced example, it appears that the forward penetration of the ground increments in the stability and control occur at landing gear height. vortex is a strong inverse function of the level of mixing in the These generally reflect an induced lift loss and a nose-up pitching ground vortex. Also, an effort has been made to isolate issues moment, and vary with sideslip. Directional stability is reduced at which require additional work in order to improve the numerical landing gear height with full reverse thrust. Nonlinearities in the simulation of the jet in ground effect flow. The FNS approach horizontal tail effectiveness are found in free air and at landing simplifies the simulation of a single jet in ground effect, but it will gear height. Author be even more effective in applications to more complex topologies. Author N89-10854"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N89-10858"# National Aeronautics and Space Administration. AN ASSESSMENT OF GROUND EFFECTS DETERMINED BY Lewis Research Center, Cleveland, Ohio. STATIC AND DYNAMIC TESTING TECHNIQUES EXPERIMENTAL INVESTIGATION OF THE PERFORMANCE OF JOHN W. PAULSON, JR. and GUY T. KEMMERLY In NASA, A SUPERSONIC COMPRESSOR CASCADE Ames Research Center, The 1987 Ground Vortex Workshop p D. L. TWEEDT, H. A. SCHREIBER, and H. STARKEN (Deutsche 121-146 Feb. 1988 Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Avail: NTIS HC A10/MF A01 CSCL 01A Cologne, West Germany ) Jun. 1988 30 p Presented at the A new testing technique was developed wherein the rate of 33rd International Gas Turbine and Aeroengine Congress and descent can be included as a parameter in ground effects Exposition, Amsterdam, The Netherlands, 5-9 Jun. 1988; sponsored investigations. This technique simulates the rate of descent by by ASME horizontal motion of a model over an inclined ground board in the (NASA-TM-100879; E-4113; NAS 1.15:100879) Avail: NTIS HC Langley Vortex Research Facility (VRF) During initial evaluations A03/MF A01 CSCL 01A of the technique, dynamic ground effects data were obtained over Results are presented from an experimental investigation of a the inclined ground board, steady state ground effects data were linear, supersonic, compressor cascade tested in the supersonic obtained over a flat portion of the ground board, and the results cascade wind tunnel facility at the DFVLR in Cologne, Federal were compared to conventional static wind tunnel ground effect Republic of Germany. The cascade design was derived from the data both with and without a moving belt ground plane simulation. near-tip section of a high-through-flow axial flow compressor rotor Initial testing and analysis led to the following conclusions: the with a design relative inlet Mach number of 1.61. Test data were moving belt ground plane had little effect on static ground effects obtained over a range of inlet Mach numbers from 1.23 to 1.71, for the configurations tested unless thrust reversers were employed; and a range of static pressure ratios and axial-velocity-density in general, rate-of-descent reduced ground effects to the point ratios (AVDR) at the design inlet condition. Flow velocity that for reversed thrust cases an expected loss of lift due to measurements showing the wave pattern in the cascade entrance ground effects was eliminated at approach conditions; and, in region were obtained using a laser transit anemometer. From these
16 02 AERODYNAMICS
measurements,some unique-incidence conditions were deformation of the flow lines downstream. Geometric parameters determined, thus relating the supersonic inlet Mach number to the (sweep, profile incidence) appear to be essential in determining inlet flow direction. The influence of static pressure ratio and AVDR flow tropism in corners. ESA on the blade passage flow and the blade-element performance is described, and an empirical correlation is used to show the N89-10862# Deutsche Forschungs- und Versuchsanstalt fuer influence of these two (independent) parameters on the exit flow Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer angle and total-pressure loss for the design inlet condition. Author Flugmechanik. INVESTIGATION OF WAKE VORTICES OF LANDING AIRCRAFT AT FRANKFURT AIRPORT (FEDERAL REPUBLIC N89-10859# Centre d'Etudes et de Recherches, Toulouse OF GERMANY) (France). Dept. d'Etudes et de Recherches en ROLF ULKEN May 1988 70 p In GERMAN; ENGLISH Aerotherrnodynamique. INVESTIGATION ON OF THE FLOW AROUND A BACKWARD summary (DFVLR-MITT-88-15; ISSN-0176-7739; ETN-88-93183) Avail: FACING STEP WITH SPANWlSE BLOWING Final Report NTIS HC A04/MF A01; DFVLR, VB-PL-DO, 90 60 58, 5000 [ETUDE DE L'ECOULEMENT AUTOUR D'UNE MARCHE DESCENDANTE AVEC SOUFFLAGE TANGENTIEL] Cologne, Federal Republic of Germany, 24.50 deutsche marks X. DESAINT-VICTOR and W. HAJIBRAHIM Jan. 1988 71 p Wake vortices were investigated to see whether and under In FRENCH which meteorological conditions landing aircraft could be endangered by wake vortices generated by leading large transport (Contract AEROSPATIALE-21-003395) aircraft on a parallel glide path. The crosswind shows an evident (CERT-RF-OA-68/2259-AYD; DERAT-52/5004-23; ETN-88-93105) Avail: NTIS HC A04/MF A01 influence on the horizontal motion of a vortex. But its velocity during 56 pct of the time of the main air traffic is so slow that a Spanwise blowing of the boundary layer to eliminate recirculation vortex cannot reach the parallel glide path with dangerous intensity zones downstream of helicopter motor fairings/rotor heads was due to its limited life-span. Within the remaining time the danger analyzed numerically. Flow around a backward facing step with a to a following aircraft depends very strongly on the meteorological slit at riser level for the blowing was studied. Two slit/step height conditions of the vicinity. ESA ratios were chosen and several ratios of blowing velocity to infinite upstream velocity were considered. Results show that the calculation method can predict flows with strong separation, and N89-10864# Centre d'Etudes et de Recherches, Toulouse that spanwise blowing can eliminate recirculation downstream of (France). Dept. d'Etudes et de Recherches en an obstacle. ESA Aerothermedynamique. THREE DIMENSIONAL SHEAR FLOW. ANALYSIS OF THE N89-10860# Office National d'Etudes et de Recherches FLOW IN A DELTA ARROW WING WITH INCIDENCE ANGLE Aerospatiales, Paris (France). Direction de I'Aerodynamique. [ECOULEMENTS CISAILLES TRIDIMENSIONNELS. ANALYSE FLOW AROUND A DELTA WING WITH OR WITHOUT A DE L'ECOULEMENT A L'INTRADOS D'UNE AILE EN FLECHE CANARD (PHI BA = 60 DEC). PART 2: HYDRODYNAMIC ET EN INCIDENCE] VISUALIZATIONS IN UNSTEADY FLOW (PITCHING GUY PAILHAS Mar. 1987 27 p In FRENCH OSCILLATIONS) [ECOULEMENT AUTOUR D'UNE AILE DELTA (Contract STPA-85-95-O04) SANS OU AVEC PLAN CANARD (PHI BA = 60 DEC), (CERT-RTS-OA-25/5025-AYD; DERAT-25/5025-14; DEUXlEME PARTIE: VISUAUSATIONS HYDRODYNAMIQUES ETN-88-93319) Avail: NTIS HC A03/MF A01 EN INSTATIONNAIRE (OSCILLATIONS EN TANGAGE)] Wind tunnel tests were performed on a delta wing to evaluate H. WERLE Feb. 1988 43 p In FRENCH the average velocities and the turbulent fields. A four wire (ONERA-RT-11/2891-AN-PT-2; ETN-88-93111) Avail: NTIS HC anemometer was used. The model was placed at large incidence A03/MF A01 angles and simulated a delta winged aircraft body. The analysis Turbulence phenomena around a thin delta wing were visualized of the turbulence shows that the corner flow is the result of a and measured in a hydrodynamic test facility with a model in conflict between the fluid coming out of the boundary layer below unsteady flow. The model was subjected to harmonic pitching the wing, which could be receptive to the turbulence order imposed oscillations of amplitude + or - 10 deg, around an average by the systems geometry, and the external fluid which forces the incidence of 15 and 20 deg. Vortices at a wing with a canard flow to retake the initial direction. ESA configuration were studied at Reynolds numbers between 20,000 and 100,000 and at frequency K between 0.18 and 0.46. Results show the effectiveness of the canard is greatly reducing bursting. N89-10865"# National Aeronautics and Space Administration. Curves showing the alternating displacement of the vortex axis Lewis Research Center, Cleveland, Ohio. and vortex bursting point, and their evolution as a function of flow EXPERIMENTAL AERODYNAMIC PERFORMANCE OF parameters are obtained. ESA ADVANCED 40 DEC-SWEPT 10-BLADE PROPELLER MODEL AT MACH 0.6 TO 0.85 N89-10861# Centre d'Etudes et de Recherches, Toulouse GLENN A. MITCHELL Sep. 1988 43 p (France). Dept. d'Etudes et de Recherches en (NASA-TM-88969; E-3437; NAS 1.15:88969) Avail: NTIS HC Aerothermedynamique. A03/MF A01 CSCL 01A EXPERIMENTAL INVESTIGATION OF FLOW NEAR A A propeller designated as SR-6, designed with 40 deg of sweep CORNER, PART 2 [ETUDE EXPERIMENTALE D'UN and 10 blades to cruise at Mach 0.8 at an altitude of 10.7 km ECOULEMENT AU VOISlNAGE D'UN COIN (DEUXlEME (35,000 ft), was tested in the NASA Lewis Research Center's 8- PARTIE)] by 6-Foot Wind Tunnel. This propeller was one of a series of GUY PAILHAS Jan. 1988 159 p In FRENCH advanced single rotation propeller models designed and tested as (Contract STPA-85-95-004) part of the NASA Advanced Turboprop Project. Design-point net (CERT-RT-OA-24/5025-AYD; DERAT-24/5025-14; ETN-88-93113) efficiency was almost constant to Mach 0.75 but fell above this Avail: NTIS HC A08/MF A01 speed more rapidly than that of any previously tested advanced Flow in the angle of intersection of two walls was studied propeller. Alternative spinners that further reduced the near-hub using a wind tunnel model to simulate the joint of a highly swept interblade Mach numbers and relieved the observed hub choking (arrow) wing and a fuselage, the wing being at incidence. A hot-wire improved performance above Mach 0.75. One spinner attained anemometer was used to obtain the average flow field and estimated SR-6 Design-point net deficiencies of 80.6 percent at turbulence field in different flow planes. Results show that the Mach 0.75 and 79.2 percent at Mach 0.8, higher than the measured combination of sweep and incidence does not contribute to the performance of any previously tested advanced single-rotation creation of a pressure gradient strong enough to allow an important propeller at these speeds. Author
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N89-10866# Aeronautical Research Labs., Melbourne being researched and developed at a full scale flight experimental (Australia). stage. The main wing itself of the C-1 transport, which is the NON-LINEAR AERODYNAMIC CHARACTERISTICS OBTAINED mother aircraft of the Asuka, was not changed because the main FROM THE ANALYSIS OF FLIGHT-DATA purpose of this research was to establish a upper surface blowing R. A. FEIK Nov. 1987 35 p which will realize a revolutionary STOL performance. Research (AR-004-571; ARL-AERO-TM-390) Avail: NTIS HC A03/MF A01 has also been conducted on the possibility of a rise in aerodynamic A least squares regression analysis program has been performance of the optimum shape of main wings as part of the documented and its advantages and shortcomings when used for research on the practical use of, future STOL aircraft. Tests were analyzing flight data have been summarized. It has been shown conducted in the above research by using a half-cut model with a that the shortcomings can be largely overcome by pre-processing main wing shape designed with a computer aided design system flight measurements via compatibility checking. A particular and are called low speed wind tunnel test. Author advantage of the least squares approach is the ability to partition data into angle of attack subsets. Application to flight data from a delta wing aircraft at Mach 0.65 has been successful in extracting 03 nonlinear features, including a sharp drop in pitch damping at around 4 degrees angle of attack, possibly associated with the development of the leading edge vortex. Comparison with previous AIR TRANSPORTATION AND SAFETY results, internal consistency, and small scatter all confirm the effectiveness of this approach even with moderate quality Includes passenger and cargo air transport operations; and aircraft instrumentation. The methodology described has considerable accidents. potential for application to highly nonlinear flight regimes. Author
N89-10867# General Dynamics/Fort Worth, Tex. A89-10471 UNSTEADY LOW-SPEED WlNDTUNNEL TEST OF A STRAKED QUALIFICATION AND OPERATIONAL ASPECTS OF LIGHT DELTA WING, OSCILLATING IN PITCH. PART 1" GENERAL WEIGHT SKAD (LIGHT WEIGHT SURVIVAL KIT AIR DESCRIPTION AND DISCUSSION OF RESULTS Final Report, DROPPABLE) Jun. 1985 - Aug. 1987 P. D. JOHNSON (Irvin Industries Canada, Ltd., Fort Erie) IN: A. M. CUNNINGHAM, JR., R. G. DENBOER, C. S. DOGGER, E. SAFE Association, Annual Symposium, 25th, Las Vegas, NV, Nov. G. GUERTS, and A. J. PERSOON Apr. 1988 140 p 16-19, 1987, Proceedings. Newhall, CA, SAFE Association, 1987, (Contract F33615-85-C-3013) p. 171-175. lAD-A196456; AFWAL-TR-87-3098-PT-1) Avail: NTIS HC The light weight SKAD, a wing mounted survival kit providing A07/MFA01 CSCL 01A reliable and accurate positioning of two interconnected six man Results of a wind tunnel test of an oscillating straked wing inflatable liferafts and survival equipment, is described. The light indicate unsteady airloads and pressure distributions for a range weight SKAD operational objectives on the CP 121 Tracker aircraft of incidences (-8 to 50 deg) and amplitudes (1 to 16 deg). The were to develop and demonstrate draft loading and unloading wind speed was 80 meters/second, which provided reduced procedures, verify compatibility with the aircraft and weapons risk frequencies up to 0.50 based on root chord. The zeroth and first under typical service conditions, and develop a system drop harmonic as well as the continuous time history of the pressure technique. It is noted that a Ifferaft positional accuracy of +/- 50 and overall loads were measured. Flow visualization was performed ft is estimated for systems released under typical deployment for flow of 30 meters/second using a pulsating laser light sheet. conditions. K.K. This part presents the description of this wind tunnel test and preliminary discussions of results obtained from the test. Details A89-10475 are provided on the model, instrumentation and support system ADVANCED CREW ESCAPE CAPSULE TECHNOLOGIES as well as test program condition/run member cross-reference PROGRAM tables for use with the data base presented in parts 2 through 6 ARUN K. TRIKHA, STEVEN M. WARREN (Boeing Military Airplane of this report. Model geometry and force data processing Co., Seattle, WA), and JAMES M. PETERS (USAF, Wright procedures are presented in the appendices. Also presented in Aeronautical Laboratories, Wright-Patterson AFB, OH) IN: SAFE the appendices are updated values of force data obtained from Association, Annual Symposium, 25th, Las Vegas, NV, Nov. 16-19, the steady tests of the model suspended by a wire balance. 1987, Proceedings. Newhall, CA, SAFE Association, 1987, p. GRA 196-202. refs The use of various advanced technologies such as adaptive N89-11067# Joint Publications Research Service, Arlington, Va. digital control, selectable/controllable thrust, thrust vector control, NUMERICAL SIMULATION OF TRANSONIC FLOW AROUND and retrorockets to improve escape capsule performance is ASUKA discussed. A comparison is made between various alternative SUSUMU TAKANASHI In its JPRS Report: Science and escape capsule configurations, including recoverable and Technology: Japan p 24-25 4 Jun. 1987 Transl. into ENGLISH nonrecoverable hybrid configurations. A recoverable nose capsule from Kogiken Nyusu (Toyko, Japan), Sep. 1986 p 2 configuration was found to be superior to other configurations. It Avail: NTIS HC A05/MF A01 is noted that the development of other technologies, such as Research is being conducted on the numerical simulation of gelled propellants, is important in significantly improving the transonic flow around a low noise short takeoff and landing (STOL) expected weight performance without a high weight penalty. experimental aircraft, Asuka. The purposes of this research are to K.K. evaluate the high speed aerodynamic characteristics of the Asuka, to evaluate the aerodynamic interference between the elements A89-10631" National Aeronautics and Space Administration. and airframe according to the parametric study, and to construct Ames Research Center, Moffett Field, Calif. a numeric data base. Author V/STOL AIRCRAFT CONFIGURATIONS AND OPPORTUNITIES IN THE PACIFIC BASIN N89-11069# Joint Publications Research Service, Arlington, Va. JAMES A. ALBERS and JOHN ZUK (NASA, Ames Research CAD WIND TUNNEL TEST FOR HALF-CUT MODEL OF ASUKA Center, Moffett Field, CA) IN: International Pacific Air and Space In its JPRS Report: Science and Technology: Japan p 29-32 4 Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, Jun. 1987 Transl. into ENGLISH from Kogiken Nyusu (Toyko, Proceedings. Warrendale, PA, Society of Automotive Engineers, Japan), Sep. 1986 p 5-6 Inc., 1988, p. 45-72. Previously announced in STAR as Avail: NTIS HC A05/MF A01 N88-11644. refs A low noise STOL experimental aircraft, Asuka, is presently (SAE PAPER 872403)
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Advanced aircraft configurations offer new transportation on the payroll, increased their engineering staffs, and increased options for the Pacific Basin. Described is a range of vehicles their inventory of spare parts. The FAA reinstituted national work from tow-disk to high-disk loading aircraft, including high-speed program guidelines in October 1985, increased inspector staffing, rotorcraft, subsonic vertical and short takeoff and landing (V/STOL) and initiated a flight standards national aviation inspection aircraft, and subsonic short takeoff and landing (STOL) aircraft. program. K.K. The status and advantages of the various configurations are described. Some of these show promise for satisfying many of A89-10662 the transportation requirements of the Pacific Basin; as such, they AEROELASTICITY PAST, PRESENT AND FUTURE could revolutionize short-haul transportation in that region. DAVlN R. SCOTT (Aerospace Technology of Australia, Australia) Author IN: International Pacific Air and Space Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, A89-10654 PA, Society of Automotive Engineers, Inc., 1988, p. 425-429. INTEROPERABILITY OF MILITARY AND CIVIL AIR-CARGO (SAE PAPER 872449) SYSTEMS This paper describes a study of the oscillatory aeroelastic PAUL D. TUCK (USAF, Office of the Assistant Chief of Staff Studies phenomenon, with special consideration given to the analysis of and Analyses, Washington, DC) IN: International Pacific Air and an air accident case involving an aircraft having a high wing twin Space Technology Conference, Melbourne, Australia, Nov. 13-17, turbopropeller configuration. The aeroelastic analysis was 1987, Proceedings. Warrendale, PA, Society of Automotive developed that made it possible to predict flutter pertinent to the Engineers, Inc., 1988, p. 331-351. refs flight conditions of the aircraft. Finally, a single aeroelasitc analysis (SAE PAPER 821555) system capable of dealing with any previous model was This paper compares military/civil air-cargo systems in terms assembled. I.S. of in-plane hardware, materials-handling equipment (MHE), and unit-load devices (ULDs). A need exists to have available, on short notice, a U.S. airlift system for deployment of cargo/troops to A89-10718 remote points of operation. The DOD recently expressed a FIRE SAFETY AT CIVIL AIRPORTS [OBESPECHENIE requirement for increased interoperability between military and civil POZHARNOI BEZOPASNOSTI NA AERODROMAKH air cargo systems. Interest in interoperability is also indicated by GRAZHDANSKOI AVIATSII] the Advanced Civil/Military Aircraft (ACMA) concept. The ACMA MIKHAIL ABASKULIEVIC DZHAFAROV, NIKOLAI FILLIPOVlCH may be described as an aircraft for fulfilling both U.S. needs for LOZOVOI, VLADIMIR IVANOVlCH LUTSENKO, and VALENTIN strategic airlift and world-wide needs for civil air freight in the KONSTANTINO FEDOROV Moscow, Izdatel'stvo Transport, 1987, mid-1990s and beyond. The advances and development of 264 p. In Russian. refs cargo-capable aircrafrt and their in-plane cargo-handling systems The available data on the fire safety of commercial aircraft, have historically paced development of complementary ground fire fighting methods, and rescue operations are presented in a systems. The military system relies heavily on the 88 x 108-inch systematic manner. In particular, attention is given to the on-board pallet. The civil system relies to a greater extent on intermodal fire safety systems, the use of the fire fighting equipment available containers and the 88 or 96 x 125-inch civil pallets. Author at the airport, and technical characteristics of fire safety equipment. The discussion also covers the organizational and safety A89-10655 engineering aspects of fire fighting. V.L. AEROSPACE TECHNOLOGY - WINDSHEAR FAA: BOEING WlNDSHEAR TRAINING AID PROGRAM A89-10721 CHARLES R. HIGGINS and EDGARS A. KUPCIS (Boeing FUNDAMENTALS OF FLIGHT SAFETY [OSNOVY Commercial Airplane Co., Seattle, WA) IN: International Pacific BEZOPASNOSTI POLETOV] Air and Space Technology Conference, Melbourne, Australia, Nov. BORIS VASIL'EVlCH ZUBKOV and EVGENII ROMANOVICH 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive MINAEV Moscow, Izdatel'stvo Transport, 1987, 144 p. In Engineers, Inc., 1988, p. 353-358. Russian. (SAE PAPER 872441) Various aspects of flight safety are examined on the basis of Severe microburst windshear has been identified as a significant a systems approach to this complex problem. The discussion cause of airline accidents during the takeoff and landing phases covers the principal factors determining flight safety, types of of flight. In 1985 the Federal Aviation Administration contracted malfunctions, analysis of flight safety indices, methods of insuring with an industry team (manufacturers, airline training departments, the reliability of aviation equipment, and factors determining the meteorological experts, pilots groups, other interested parties) to functional efficiency of the flight crew. Attention is also given to develop a windshear training program for transport pilots. This the functions and objectives of traffic control, navigation support, paper treats the organizational structure used to develop industry classification and investigation of flight accidents, and measures consensus on the pilot training issues as well as reports on the designed to prevent flight accidents. V.L. principal elements of the training program developed by this industry team. The paper discusses the tools available to flight crews to recognize and avoid microburst windshear, and failing that, how A89-12539 to recover from an inadvertent encounter. Author AIR SAFETY IN THE AGE OF DEREGULATION LEON N. MOSES and IAN SAVAGE (Northwestern University, A89-10656 Evanston, IL) Issues in Science and Technology (ISSN MAINTENANCE AND AIRLINE SAFETY 0748-5492), vol. 4, Spring 1988, p. 31-36. refs RAYMOND E. RAMAKIS (FAA, Aircraft Maintenance Div., The present discussion of U.S. airlines' behavior following the Washington, DC) IN: International Pacific Air and Space deregulation of this industry in 1978 notes that the development Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, of the hub-and-spoke routing system over the past decade has Proceedings. Warrendale, PA, Society of Automotive Engineers, increased the travel time and uncertainty of passengers while Inc., 1988, p. 359-368. refs increasing the airlines' rate of overbooking. Attention is presently (SAE PAPER 872443) given to the long-term effect of deregulation on such airline Aircraft certification is discussed, as well as airline certification safety-related matters as the upholding of maintenance and training and responsibilities and Federal Aviation Administration regulatory standards under the pressure of reduced profit margins (due to responsibilities. As a result of the continuing inspections of air more intense competition), as well as to the shortfall in FAA carriers and repair stations since 1984, the industry and the FAA resources for airliner inspections and the U.S.'s low rate of such have worked to overcome various negative findings. Among other infrastructural investment as modernized ATC to cope with things, the air carriers have increased the number of mechanics expanded airline operations. O.C.
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A89-12548 England, Oct. 14, 1987. London, Royal Aeronautical Society, 1987, THE ASSURANCE OF FLIGHT SAFETY - A PRIORITY TASK IN p. 61-65. CIVIL AVIATION [DIE GEWAEHRLEISTUNG DER This paper presents the author's viewpoint on the requirement FLUGSICHERHEIT - EINE ERSTRANGIGE LEITUNGSAUFGABE to 'control' birds on a licensed aerodrome in the UK and describes IN DER ZlVILEN LUFTFAHRT] how the Civil Aviation Authority carries out its responsibilities; ALEXANDER RIECHE (Berlin, Humboldt-Universitaet, German discusses the legal liability if a bird strike should occur on an Democratic Republic) Technisch-oekonomische Information der aerodrome; questions whether or not we have reached a plateau zivilen Luftfahrt (ISSN 0232-5012), vol. 24, no. 4, 1988, p. 150, in our knowledge of birds as they effect aircraft close to aerodromes 151, 154. In German. and finally suggests that the bird problem, with our level of The development of greater flight safety in the context of a knowledge, may often be better described as a people problem. socialist society is discussed. The role of cooperation under a Author strong leader is stressed. The leader's main task is the development of flight safety consciousness. The selection of cadres and the formation of strong cooperative bonds among the cadres in order N89-10035# National Transportation Safety Board, Washington, to advance flight safety is emphasized. C.D. D.C. Bureau of Field Operations. AIRCRAFT ACCIDENT REPORTS, BRIEF FORMAT, US CIVIL A89-12717 AND FOREIGN AVIATION, ISSUE NUMBER 10 OF 1987 THE CIVIL AVIATION BIRDSTRIKE RECORD ACCIDENTS JOHN THORPE (Civil Aviation Authority, London, England) IN: 30 Mar. 1988 403 p Bird hazards in aviation; Proceedings of the Symposium, London, (PB88-916905; NTSB/AAB-88/05) Avail: NTIS HC A18/MF A01; England, Oct. 14, 1987. London, Royal Aeronautical Society, 1987, also available on subscription, North American Continent HC p. 1-6. $185.00/year; all others write for quote CSCL 01C An analysis of British civil aviation records on birdstrike events The publication contains selected aircraft accident reports in has determined birdstrike rates for fixed-wing aircraft to currently Brief Format occuring in U.S. civil and foreign aviation operations lie in the 5/10,000-flight range; the helicopter rate is about 1/10,000 during 1987. Approximately 200 General Aviation and Air Carrier hours. Fully 85 percent of birdstrikes occur below 800-ft altitude, accidents presented represent a random selection. The publication and seagulls are the birds most frequently involved. Each year, is issued irregularly, normally 18 times each year. The Brief Format 20 engines are damaged; the approximately 5 cases in which presents the facts, conditions, circumstances and probable causes birds are ingested by more than one engine of a multiengine for each accident. GRA aircraft are considered the most serious ones. It is anticipated that new-generation, intrinsically quieter airliner powerplants may generate a lower aural alert to birds, and thereby increase the N89-10036# National Transportation Safety Board, Washington, probability of birdstrikes. O.C. D.C. Bureau of Field Operations. AIRCRAFT ACCIDENT REPORTS, BRIEF FORMAT, US CIVIL A89-12718 AND FOREIGN AVIATION, ISSUE NUMBER 12 OF 1986 BIRD HAZARDS IN AVIATION - THE RAF VIEW ACCIDENTS C. J. TURNER (RAF, London, England) IN: Bird hazards in 25 Apr, 1988 414 p aviation; Proceedings of the Symposium, London, England, Oct. (PB88-916903; NTSB/AAB-88/03) Avail: NTIS HC A18/MF A01; 14, 1987. London, Royal Aeronautical Society, 1987, p. 7-11. also available on subscription, North American continent HC RAF attitudes to birdstrike problems have significantly changed $185.00/year; all others write for quote CSCL 01C since 1980, when efforts were mounted to reduce the vulnerability Selected aircraft accident reports in Brief Format occuring in of military aircraft and to incorporate greater birdstrike resistance the U.S. civil and foreign aviation operations during 1986 are in aircraft entering the design stage. The last eight years have presented. Approximately 200 General Aviation and Air Carrier also witnessed the RAF's development of Bird Control Units, which accidents presented represent a random selection. The publication actively dissuade birds of all types from the use of airfields for is issued irregularly, normally eighteen times each year. The Brief feeding, nesting, and other social behavior. Outside airfield Format represents the facts, conditions, circumstances and probable causes for each accident. GRA boundaries, a mechanism for the dissemination of local intelligence concerning unusually heavy bird activity has been established. No aircraft have been lost to birdstrike damage in 1986-1988, as a result of these preventive measures. O.C. N89-10450# Office National d'Etudes et de Recherches Aeronautiques, Paris (France). A89-12721 ANALYSIS OF RECENT IN-FLIGHT LIGHTNING MEASUREMENTS ON DIFFERENT AIRCRAFT BIRD HAZARDS IN AVIATION - SAFETY AND ECONOMIC IMPLICATIONS FOR AN AIRLINE J. L. BOULAY, J. P. MOREAU, A. ASSELINEAU, and P. L. RUSTAN (Defense Nuclear Agency, Washington, D.C.) In NOAA, P. OAKE (British Airways, PLC, Houslow, England) IN: Bird hazards International Aerospace and Ground Conference on Lightning and in aviation; Proceedings of the Symposium, London, England, Oct. Static Electricity p 136-144 Apr. 1988 14, 1987. London, Royal Aeronautical Society, 1987, p. 49-60. Avail: NTIS HC A23/MF A01 CSCL 01C The birdstrike incident records of a major British airline presently Two experimental programs have been conducted since 1984 analyzed for the period from 1980 to 1987, over UK, European, and intercontinental routes, encompass cases that resulted in the in order to obtain in-situ measurements on lightning effects on aircraft. These two programs involve the CV-580 aircraft and the malfunction of aircraft control systems, engine or airframe damage, Transall aircraft. Researchers now have a large amount of or the crew's precautionary termination of a flight in anticipation of potentially dangerous consequences from the strike. Attention information concerning typical parameter variations during a direct is given to the primary and secondary aspects of costs due to lightning stroke in flight: currents, electric and magnetic fields in several locations on the aircraft structures. One of the most birdstrike damage, in the course of brief examinations of seven case histories. O.C. important features of these measurements concerns the great similarity between parameter variations for the two experimental programs. After presentation of typical results obtained with the A89-12722 Transall, a comparative analysis is made of CV-580 and Transall BIRD HAZARDS IN AVIATION - THE REGULATORY data on I and H waveforms during the attachment phase of the AUTHORITY'S RESPONSIBILITIES lightning strike. A number of hypotheses aimed at giving physical GORDON SHARP (Civil Aviation Authority, London, England) IN: explanations of the measurements detected in flight are Bird hazards in aviation; Proceedings of the Symposium, London, discussed. Author
20 03 AIR TRANSPORTATION AND SAFETY
N89-10451"# Electro Magnetic Applications, Inc., Lakewood, N89-10455# AIRO, Inc., Colorado Springs, Colo. Colo. A CHRONOLOGY OF IN-CLOUD ELECTRIC FIELD AND LINEAR AND NONLINEAR INTERPRETATION OF CV-580 LIGHTNING STRIKES ON AN INSTRUMENTED RESEARCH LIGHTNING DATA AIRCRAFT POH H. NG, TERENCE H. RUDOLPH, and RODNEY A. PERALA J. WILLIAM BULLOCK and J. J. JONES (New Mexico State Bureau In NOAA, International Aerospace and Ground Conference on of Mines and Mineral Resources, Socorro.) In NOAA, International Lightning and Static Electricity p 145-151 Apr. 1988 Sponsored Aerospace and Ground Conference on Lightning and Static in part by FAA, Atlantic City, N.J. Electricity p 175-180 Apr. 1988 (Contract NASl-17748) Avail: NTIS HC A23/MF A01 CSCL 04B Avail: NTIS HC A23/MF A01 CSCL 01C The two lightning strikes to the aircraft in 1983 were identified. Numerical models developed for the study of lightning strike The strikes occurred when the aircraft was entering or leaving a data acquired by in-flight aircraft are applied to the data measured region of strong vertical electric field. In both cases, the measured on the CV-580. The basic technique used is the three dimensional field subsequent to the strikes was greatly reduced from the time domain finite difference solution of Maxwelrs equations. Both pre-strike value, indicating that the strike removed the nearby linear and nonlinear models are used in the analysis. In the linear charge which was the source of the pre-strike electric field. It model, the lightning channel and the aircraft are assumed to form appears that the aircraft triggered these strikes, and a possible a linear time invariant system. A transfer function technique can triggering mechanism is proposed. The strikes also removed the then be used to study the response of the aircraft to a given pre-strike charge on the aircraft. Since both strikes occurred during lightning strike current. Conversely, the lightning current can be cloud penetrations near zero degree isotherm and depleted a region inferred from the measured response. In the nonlinear model, the of positive charge, it is believed that these were so-called Lower conductivity of air in the vicinity of the aircraft is calculated and Position Charge Centers. Author incorporated into the solution of the Maxwelrs equations. The nonlinear model thus simulates corona formation and air N89-10456"# National Severe Storms Lab., Norman, Okla. breakdown. Results obtained from the models are in reasonable LIGHTNING INITIATION ON AIRCRAFT IN THUNDERSTORMS agreement with the measured data. This study provides another VLADISLAV MAZUR In NOAA, International Aerospace and validation of the models and increases confidence that the models Ground Conference on Lightning and Static Electricity p 181-191 may be used to predict aircraft response to any general lightning Apr. 1988 Previously announced as A88-22289 Sponsored in strike. Author part by NASA Avail: NTIS HC A23/MF A01 CSCL 01C A physical model of the initiation of lightning flashes in N89-10452# Boeing Advanced Systems Co., Seattle, Wash. thunderstorms is presented. The model is based on the LIGHTNING TESTS ON AN ALL-COMPOSITE HELICOPTER bi-directional charged leader concept of Kasemir, and is verified DAVID B. WALEN In NOAA, International Aerospace and Ground with airborne data from lightning strikes to instrumented airplanes Conference on Lightning and Static Electricity p 152-i59 Apr. (NASA F-106B and FAA CV-580). The characteristics of 1988 electromagnetic processes during lightning attachment are Avail: NTIS HC A23/MF A01 CSCL 01C identified by comparison with those studied in natural flashes, those Lightning tests were performed on an all-composite helicopter triggered by wire trailing rockets, and laboratory discharges. A to determine lightning-induced transient effects on the helicopter triggered flash starts with either a negative corona or a positive electrical and electronic systems. Results of the tests were used leader that depends on the ambient electric field vector and the to assess the lightning simulation techniques. The helicopter airplane form factor. The positive leader with continuous current incorporated graphite/epoxy, Kelvar, and fiberglass materials in that increases with time is followed in a few milliseconds by the the structure and skins. Swept continuous wave (CW) transfer negative stepped leader with current pulses of a few kA. The two function measurements and current pulse tests with drive currents leaders develop in space simultaneously and bi-directionally from ranging from 20 kA to 200 kA were used for the lightning tests. the oppositely charged extremities of the airplane. Author Transient voltage and current responses were measured on the helicopter avionics and wiring. The response waveform N89-10457# De Havilland Aircraft Co. of Canada Ltd., Downsview comparisons showed that the transformed transfer functions had (Ontario). similar shapes and amplitudes to the measured pulse responses. LIGHTNING TESTS TO MEASURE THE BULK CURRENT Within constraints of the pulse variations, scaling generally provided LEVELS ASSOCIATED WITH THE ELECTRONIC ENGINE conservative response predictions. Author CONTROL OF A TURBOPROP COMMUTER TRANSPORT PETER BOOTSMA In NOAA, International Aerospace and Ground N89-10454"# Electro Magnetic Applications, Inc., Huntsville, Conference on Lightning and Static Electricity p 192-196 Apr. Ala. 1988 ESTIMATING ELECTRIC FIELD ENHANCEMENT FACTORS ON Avail: NTIS HC A23/MF A01 CSCL 01C AN AIRCRAFT UTILIZING A SMALL SCALE MODEL: A Impulse lightning tests were carried out as part of a development METHOD EVALUATION program to measure the cable current levels associated with the CALVIN C. EASTERBROOK, TERENCE RUDOLPH, and KEVIN electronic engine control (EEC) of a turboprop commuter transport. EASTERBROOK In NOAA, International Aerospace and Ground Described here are two test programs, each utilizing full scale Conference on Lightning and Static Electricity p 171-174 Apr. vehicles to measure the bulk current levels associated with the 1988 engine control cable harness. In the first test program, the tests (Contract NAS1-17748) were performed with the 1200 ampere unipolar test waveform. Avail: NTIS HC A23/MF A01 CSCL 01C The second test program was carried out using a 15 kiloampere A method for obtaining field enhancement factors at specific damped sinusoid test waveform. The latter program was extended points on an aircraft utilizing a small scale model was evaluated for a period of several weeks in order to develop a method of by measuring several canonical shapes. Comparison of the form diverting current from the engine to the surrounding nacelle, and factors obtained by analytical means with measurements indicate improve the shielding of the engine control cable harness. Author that the experimental method has serious flaws. Errors of 200 to 300 percent were found between analytical values and measured values. As a result of the study, the analytical method is not N89-10459# Electro Magnetic Applications, Inc., Lakewood, recommended for calibration of field meters located on aircraft, Colo. and should not be relied upon in any application where the local INTERFERENCE OF PRECIPITATION STATIC DISCHARGES spatial derivatives of the electric field on the model are large over WITH AIRCRAFT NAVIGATIONAL SYSTEMS the dimensions of the sensing probe. Author GREGORY J. RIGDEN In NOAA, International Aerospace and
21 03 AIRTRANSPORTATIONANDSAFETY
Ground Conference on Lightning and Static Electricity p 205-212 fire. The implications of this mishap to aircraft lightning protection Apr. 1988 Sponsored in part by FAA, Atlantic City, N.J.; Lightning and the avoidance of those conditions conducive to lightning strikes and Transients Research Inst., St. Paul, Minn. to aircarft are discussed. Author (Contract DTFA03-84-C-00066) Avail: NTIS HC A23/MF A01 CSCL 01C N89-10483# Saab-Scania, Linkoping (Sweden). The objective was to address p-static problems by determining FINITE DIFFERENCE ANALYSIS OF EXTERNAL AND ways to reduce their effects. The Gates Learjet was used as a INTERNAL LIGHTNING RESPONSE OF THE JAS39 CFC WING model for this study. The small size of the Learjet enabled an BO I. WAHLGREN and JONAS W. ROSEN In NOAA, International accurate numerical investigation utilizing a three dimensional finite Aerospace and Ground Conference on Lightning and Static difference approach to solving Maxwell's equations. The study Electricity p 396-400 Apr. 1988 included an analysis of the possible discharges, where they are Avail: NTIS HC A23/MF A01 CSCL 01C likely to occur and how often, an examination of dischargers to Analysis was carried out on a carbon fiber composite (CFC) determine the dependency of noise levels on discharger design, wing for the JAS39 aircraft, using a 3-D finite difference technique and a look at electromagnetic responses from different types of in the time domain. The wing box was also subjected to extensive dischargers. Author lightning testing which allowed researchers to compare test and analysis results. For both the wing and the wing box, the external N89-10460# New Mexico Inst. of Mining and Technology, configuration as well as the internal installations were modeled Socorro. quite accurately. The model provided for the correct interaction ELECTRIFICATION OF HOVERING HELICOPTERS between external and internal fields. The model is described in C. B. MOORE, MARX BROCK, and CLYDE N. RICHARDS some detail and test results are given. Author (Atmospheric Physics, Inc., Peralta, N. Mex.) In NOAA, International Aerospace and Ground Conference on Lightning and N89-10485# Societe Nationale Industrielle Aerospatiale, Toulouse Static Electricity p 213-217 Apr. 1988 (France). Avail: NTIS HC A23/MF A01 CSCL 01C MODELLING OF COMMON MODE COUPLING BETWEEN AN Helicopters hovering above the earth are often highly charged AIRCRAFT WING TRAVERSED BY A LIGHTNING CURRENT with electricity and this causes operational problems for ground AND WIRING INSTALLED IN THAT WING crew personnel when contact with the aircraft is required. The MICHEL CROKAERT In NOAA, International Aerospace and source of this charge is often attributed to elastic collisions of the Ground Conference on Lightning and Static Electricity p 408-424 rotor blades with dust particles in the surrounding air, but Apr. 1988 researchers found that appreciable charge transfers also occur Avail: NTIS HC A23/MF A01 CSCL 01C through the hot, conductive engine exhaust gases acted on by A code for the calculation of lightning induced common mass local electric fields. Some control of the residue charge on hovering voltage and current in wiring installed in a wing was developed aircraft has been achieved by shielding the exhaust gases from on the basis of the experimental results of the tests on an Airbus electric fields and then varying the voltages applied to electrodes A300 wing subjected to current pulses with very different shapes immersed in the hot gases so as to cause an export of the and amplitudes. The code uses conventional transmission line unwanted charge. Author modelling by quadripote method for both internal and external fields. This model made it possible to explain how magnetic and N89-10461# Naval Research Lab., Washington, D.C. Plasma electric coupling intervenes in time in the voltage and current in Physics Div. wiring. It also makes it possible to account for the loss coefficients MEASUREMENT OF THE ELECTROSTATIC CHARGING ON of the two lines which make up the external and internal fields LARGE HELICOPTERS AND CONTROL OF THE SHOCK and to explain the limitation of certain overvoltages that can HAZARD intervene. This enables researchers to use the similarity existing R. E. PECHACEK, D. P. MURPHY, and J. R. GREIG (G-T Devices, between lines and antennae to extrapolate the results to lightning Inc., Springfield, Va.) In NOAA, International Aerospace and striking an aircraft in flight. Author Ground Conference on Lightning and Static Electricity p 218-227 Apr. 1988 N89-10492# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich Avail: NTIS HC A23/MF A01 CSCL 01C (West Germany). This work was undertaken to ascertain the electrical hazard to INDIRECT EFFECTS ON ELECTRONIC AND MECHANICAL ground personnel attaching cargo to hovering CH-53E helicopters. SYSTEMS INSTALLED IN CARBON FIBRE COMPOUND The hazard is severe, but a solution has been rediscovered. An AIRCRAFT STRUCTURES approximately 10-megohm resister, replacing the stainless wire RAINER STRAUSS In NOAA, International Aerospace and Ground connected along the nylon cable from the helicopter to the cargo Conference on Lightning and Static Electricity p 470-480 Apr. hook allows a man to discharge 200-KV, 1000-pF helicopter through 1988 his body with a barely perceptible shock. The system has been Avail: NTIS HC A23/MF A01 CSCL 01C successfully field tested twice. Author A test program for indirect strike effects on electrical and mechanical systems installed in a carbon fiber compound aircraft N89-10478"# National Aeronautics and Space Administration. structure is described. The test program was carried out on the Langley Research Center, Hampton, Va. front and center of a simulated fuselage of real size, unprotected IMPLICATIONS OF A RECENT LIGHTNING STRIKE TO A and protected with aluminum mesh. The test results showed the NASA JET TRAINER differences of cable shielding standards and also the shielding BRUCE D. FISHER, RALPH J. TAEUBER, and KEITH E. CROUCH effect of the aluminum mesh. Author (Lightning Technologies, Inc., Pittsfield, Mass.) In NOAA, International Aerospace and Ground Conference on Lightning and N89-10868# National Transportation Safety Board, Washington, Static Electricity p 360-369 Apr. 1988 Previously announced in D.C. Bureau of Accident Investigation. IAA as A88-22291 AIRCRAFT ACCIDENT/INCIDENT SUMMARY REPORT, Avail: NTIS HC A23/MF A01 CSCL 01C COPPERHILL, TENNESSEE, FEBRUARY 22, 1986 On February 24, 1987, a NASA To38A airplane experienced a 30 Mar. 1988 9 p lightning strike while approaching the Los Alamitos Army Aviation (PB88-910407; NTSB/AAR-88/02-SUMM) Avail: NTIS HC Facility in California. The airplane was landed safely at Los Alamitos A02/MF A01; also available on subscription, North American with no injury to the crew members. However, the airplane suffered continent HC $70.00/year; all others write for quote CSCL 01C extensive fire damage in the center of the fuselage section. The This report is a summary of an aircraft accident investigated NASA investigation board concluded that the airplane was struck by the National Transportation Safety Board. The accident location by lightning, which resulted in an inflight explosion with subsequent and date is Copperhill, Tennessee, February 22, 1986. GRA
22 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
N89-10_9# Systems Control Technology, Inc., Arlington, Va. 04 AERONAUTICAL DECISION MAKING FOR AIR AMBULANCE HELICOPTER PILOTS: SITUATIONAL AWARENESS AIRCRAFT COMMUNICATIONS AND NAVIGATION EXERCISES Final Report R. J. ADAMS and J. L. THOMPSON Jul. 1988 45 p (Contract DTFA01-87-C-00014) Includes digital and voice communication with aircraft; air navigation (DOT/FAA/DS-88/6) Avail: NTIS HC A03/MF A01 systems (satellite and ground based); and air traffic control. The following materials are based upon actual helicopter air ambulance accidents, which cover four broad accident types most A89-10522 recently associated with aeromedical accidents: night flying, weather, obstacle strikes, and mechanical failures. Three types of AUTOMATED LANDING APPROACH USING MACHINE SEEING information are included for each accident type. These are: [AUTOMATISCHER LANDEANFLUG DURCH MASCHINELLES introductory/background material to provide the historical SEHEN] importance and frequency of each accident type; training E. D. DICKMANNS and G. EBERL (Muenchen, Universitaet der knowledge that should be learned in order to avoid mistakes of Bundeswehr, Neubiberg, Federal Republic of Germany) IN: the past; and decision making exercises. Author Yearbook 1987 1; DGLR, Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 294-300. In German. refs (DGLR PAPER 87-131) The automated landing approach of aircraft using autonomous, N89-10871# National Transportation Safety Board, Washington, on-board evaluation of television images was evaluated by D.C. Bureau of Field Operations. simulation using real-time processing hardware and software in AIRCRAFT ACCIDENT REPORTS, BRIEF FORMAT, US CIVIL the loop. The reuslting image sequence evaluation procedure, AND FOREIGN AVIATION, ISSUE NUMBER 2 OF 1987 based on an integral spatiotemporal model, is described. The ACCIDENTS results, demonstrated with a business jet aircraft, demonstrate that 5Feb. 1988 399p current microprocessors using appropriate data processing are (PB88-916906; NTSB/AAB-88/06) Avail: NTIS HC A17/MF A01; sufficient to solve this class of problems. C.D. also available on subscription, North American continent HC A89-10523 $185.00/year; all others write for quote CSCL 01C PRECONDITIONS FOR G.P.S. INSTALLATION - RECEIVERS IN The publication contains selected aircraft accident reports in DIFFERENTIAL OPERATION FOR LANDING AIRCRAFT IN Brief Format occurring in U.S. civil and foreign aviation operations GENERAL AVIATION [VORAUSSETZUNGEN ZUM EINSATZ during Calendar Year 1987. Approximately 200 General Aviation VON G.P.S. - EMPFAENGERN IN DIFFERENTIAL-BETRIEB and Air Carder accidents contained in the publication represent a ZUR LANDEANFLUGFUEHRUNG VON FLUGZEUGEN DER random selection. The publication is issued irregularly, normally ALLGEMEINEN LUFTFAHRT] eighteen times each year. The Brief Format represents the facts, TH. JACOB (Braunschweig, Technische Universitaet, Brunswick, conditions, circumstances and probable cause(s) for each accident. GRA Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 301-310. In German. refs (Contract BMFT-LFL-8530/7) (DGLR PAPER 87-132) N89-10872"# National Aeronautics and Space Administration. The state of the art in aircraft landing systems and quality Ames Research Center, Moffett Field, Calif. requirements for installation of GPS in landing systems are AVIATION TECHNOLOGY APPLICABLE TO DEVELOPING addressed. The GPS system concept, mode of operation, and REGIONS positional accuracy are discussed, and the room for improvement JOHN ZUK and LARRY R. ALTON Sep. 1988 94 p attainable in GPS by installing differential GPS is examined. A (NASA-TM-89425; A-87093; NAS 1.15:89425) Avail: NTIS HC system concept for installing GPS in aircraft landing systems is AO5/MF A01 CSCL 01C presented, and some experimental flight results using such a This paper is an analysis of aviation technologies useful for system are reported. C.D. formulation of development plans to the year 2000 for emerging nations. The Caribbean Basin was used as a specific application. A89-10524 This development promises to be so explosive over the next 15 RESEARCH ON SATELLITE-TO-AIRCRAFT SIGNAL years as to be virtually unpredictable. Author COMMUNICATION [UNTERSUCHUNG DER NACHRICHTENVERBINDING SATELLIT - FLUGZEUG] ANDREAS NEUL and JOACHIM HAGENAUER (DFVLR, Institut fuer Nachrichtentechnik, Oberpfaffenhofen, Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, N89-10873# National Transportation Safety Board, Washington, Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, D.C. Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 311-313. AIRCRAFT ACCIDENT REPORT: EXECUTIVE AIR CHARTER, In German. INC., DBA AMERICAN EAGLE, FLIGHT 5452, CASA C-212, (DGLR PAPER 87-133) N432CA, MAYAGUEZ, PUERTO RICO, MAY 8, 1987 Technology for communications between satellites and aircraft 2 Aug. 1988 51 p is discussed. The most important technological requirements for (PB88-910409; NTSB/AAR-88/07) Avail: NTIS HC A04/MF A01 maintaining such a communications channel are briefly reviewed, CSCL 01C and a study to determine the most significant physical factors On May 8, 1987, at 0650 local time, flight 5452 of Executive affecting such a communications channel is described. The findings Air Charter, Inc., doing business as Americam Eagle, crashed short concerning the probability distribution of the signal power, the of runway 9 while on a visual approach to the airport at Mayaguez, statistics of fade and connection, and the data transmission are Puerto Rico, in visual meteorological conditions. The safety issues reported. C.D. examined in the accident investigation were pilot performance, air carrier maintenance procedures and practices, bilateral type A89-10580 certification of the airplane, and FAA surveillance of the air CURRENT MILITARY/GOVERNMENT APPLICATIONS FOR carrier. Author SPEECH RECOGNITION
23 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
JAMES W. HICKS, JR. (SCI Technology, Inc., Huntsville, AL) IN: nutzungzentrale, Frankfurt am Main, Federal Republic of Germany) Aerospace Behavioral Engineering Technology Conference, 6th, Ortung und Navigation (ISSN 0474-7550), vol. 29, no. 2, 1988, Long Beach, CA, Oct. 5-8, 1987, Proceedings. Warrendale, PA, p. 284-288. In German. Society of Automotive Engineers, Inc., 1988, p. 37-39. The role of air-traffic flow management (ATFM) in preventing (SAE PAPER 871750) overloads of the European air-safety and ATC systems during This paper presents an overview of several military/government peak traffic periods is reviewed, with a focus on the organizational programs in which SCI Technology has implemented and tested structure and procedures in the FRG. Statistical data on recent its speech recognition technology. Included are the Speckled Trout increases in traffic flow are summarized; the overloads encountered (U.S. Air Force), LHX (Light Helicopter Experimental, U.S. Army), in summer 1987 are described (up to 55 flights/h in sectors with Space Shuttle (NASA), Space Station, AFTI F-16, and ATF a maximum ATC capacity of 35-40 flights/h); and the primary (Advanced Tactical Fighter) programs. Some of the programs tasks of ATFM are identified as (1) strategic planning before peak consist of technology demonstrations, while others involve flight seasons and (2) tactical measures (including early recognition of testing, and one, Speckled Trout, operationally installing and congestion, channeling of major flows, devising alternate routes, utilizing a system on a continual basis. In some cases, the hardware and temporarily increasing ATC capacities). Details of tactical ATFM consists of an SCI Voice Control Unit (VCU-5137) and in others, are discussed, and preliminary predictions for 1988 are a Voice Development System (VDS-7001). Author presented. T.K.
A89-10581 A89-12404" # Aerospace Medical Research Labs., AFTI/F-16 VOICE INTERACTIVE AVIONICS EVALUATION Wright-Patterson AFB, Ohio. F. ALLAN ROSENHOOVER (General Dynamics Corp., Fort Worth, SPEECH RECOGNITION IN ADVANCED ROTORCRAFT - TX) IN: Aerospace Behavioral Engineering Technology USING SPEECH CONTROLS TO REDUCE MANUAL CONTROL Conference, 6th, Long Beach, CA, Oct. 5-8, 1987, Proceedings. OVERLOAD Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. MICHAEL A. VIDULICH (USAF, Aerospace Medical Research 41-48. Laboratory, Wright-Patterson AFB, OH) and MICHAEL R. (SAE PAPER 871751) BORTOLUSSI (Western Aerospace Laboratories, Inc., Moffett Field, This paper describes the structure of the Voice Interactive CA) IN: Automation applications for rotorcraft; Proceedings of Avionics (VIA) system and the results of the AFTI/F-16 flight testing the National Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. of this system. The areas of evaluation during various mission Alexandria, VA, American Helicopter Society, 1988, 10 p. refs profiles, needed for establishing the interactive voice needs for (Contract NCC2-486) mission success are discussed together with problems encountered An experiment has been conducted to ascertain the usefulness during the tests and the lessons learned from incorporating the of helicopter pilot speech controls and their effect on time-sharing VIA technology into the tactical fighter aircraft. The comparison of performance, under the impetus of multiple-resource theories of the data obtained during the voice task scenarios with the same attention which predict that time-sharing should be more efficient scenarios flown strictly by manual operation showed an overall with mixed manual and speech controls than with all-manual ones. reduction in pilot workload when voice tasking was employed. The test simulation involved an advanced, single-pilot scout/attack I.S. helicopter. Performance and subjective workload levels obtained supported the claimed utility of speech recognition-based controls; A89-10642 specifically, time-sharing performance was improved while THE AUSTRALIAN AVIATION SATELLITE SYSTEM preparing a data-burst transmission of information during helicopter DON KNOX (Department of Transport and Communications, hover. O.C. Airways Div., Australia) IN: International Pacific Air and Space Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive Engineers, A89-12414# TACTICAL ROUTE PLANNING Inc., 1988, p. 197-201. JOHN GILMORE, DAN LONG, TOM FRIEDEL, and STEVE TYNOR (SAE PAPER 872420) The Aviation Satellite System carries a significant portion of (Georgia Institute of Technology, Atlanta) IN: Automation aeronautical safety communications throughout Australia. One of applications for rotorcraft; Proceedings of the National Specialists' the benefits of this system is the provision of direct high-quality Meeting, Atlanta, GA, Apr. 4-6, 1988. Alexandria, VA, American aircraft-ground VHF communications to overcome the inherent Helicopter Society, 1988. refs limitations of the high-frequency system. Another benefit is the The dynamic tactical route-planning subsystem designated optimization of air-route structures to allow for direct routing and 'Trek' consists of preprocessing, points-of-interest extraction, optimum flight paths for aircraft. B.J. postprocessing, graph construction, and heuristic search phases. An account is presently given of Trek's application to high-level A89-10722 route planning for a military Autonomous Helicopter System in LASER NAVIGATION EQUIPMENT I LAZERNYE which potential threats that are to be avoided by evasive NAVIGATSIONNYE USTROISTVA ] maneuvering are modeled in terms of threat-exposure time. The model assumes that direct or indirect masking is the only way to VLADIMIR EVSEEVICH ZUEV and VITALII IAKOVLEVICH escape detection by a given radar, so that evasive maneuvering FADEEV Moscow, Izdatel'stvo Radio i Sviaz', 1987, 161 p. In Russian. refs within that radar's envelope has no positive effect. O.C. The physical principles of operation and the general design of laser navigational aids used in the landing and piloting of aircraft A89-12449 are examined. Particular attention is given to methods for AIR NAVIGATION SYSTEMS. I - ASTRONOMICAL calculating and optimizing the performance characteristics of laser NAVIGATION IN THE AIR 1919-1969 navigation equipment with allowance for the effect of the J. E. D. WILLIAMS Journal of Navigation (ISSN 0373-4633), vol. atmosphere on the propagation of laser radiation. Based on the 41, Sept. 1988, p. 375-406. refs results obtained from the operation of experimental laser navigation The history of astronomical navigation in the air is discussed equipment, recommendations concerning the use of such from the first transatlantic flight in 1919 to 1969 when the equipment are made. V.L. development of other systems made astronomical fixing obsolescent. Methods of sight reduction are emphasized. The A89-12152# astronomical position line and the intercept method, methods for AIR-TRAFFIC FLOW MANAGEMENT TODAY solving the PZX triangle, inspection methods, the use of slide [ VERKEHRSFLUSSSTEUERUNG HEUTE I rules and almanacs, astrographic methods, and celestial analogs OLAF RIECKE (Bundesanstalt fuer Flugsicherung, Luftraum- are discussed. R.B.
24 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
N89-10038# Federal Aviation Administration, Washington, D.C. A89-10107# Advanced System Design Service. OPTIMIZATION OF THE CONCEPTUAL DESIGN AND MISSION TERMINAL CONTROL AREA DESIGN AND AIR TRAFFIC PROFILES OF SHORT-HAUL AIRCRAFT LOADINGS Final Report DIMITRI SIMOS and LLOYD R. JENKINSON (Loughborough THOMAS H. HIGGINS Aug. 1988 34 p University of Technology, England) Journal of Aircraft (ISSN (DOT/FAA/DS-88/11) Avail: NTIS HC A03/MF A01 0021-8669), vol. 25, July 1988, p. 618-624. Previously cited in The response probability density function (pdf) technique issue 05, p. 591, Accession no. A87-17933. refs adapted here uses the pdf's of the variables governing both the air traffic Ioadings of stress and the terminal airspace design A89-10109"# PRC Kentron, Inc., Hampton, Va. configurations sensitivty or strengths. This technique is proposed MULTILEVEL DECOMPOSITION APPROACH TO THE as a method which may be used to predict the relative level of PRELIMINARY SIZING OF A TRANSPORT AIRCRAFT WING safety and collision risk for TCA design configurations and air GREGORY A. WRENN and AUGUSTINE R. DOVI (PRC Kentron, traffic Ioadings. For the first time, a strong relationship was found Inc., Hampton, VA) (Structures, Structural Dynamics and Materials between near midair collision reports and midair collisions for Conference, 28th, Monterey, CA, Apr. 6-8, 1987, Technical Papers. annual operations within the fifty states. Operations, airports, and Part 1, p. 856-866) Journal of Aircraft (tSSN 0021-8669), vol. 25, airspace area were found to relate to these cdteda of safety and July 1988, p. 632-638. Previously cited in issue 14, p. 2105, provide useful interactive predictor equations. Author Accession no. A87-33651. refs (Contract NAS1-16794) N89-10885# Arinc Research Corp., Annapolis, Md. IN-SERVICE EVALUATION OF THE TRAFFIC ALERT AND A89-10111# COLLISION AVOIDANCE SYSTEM (TCAS) INDUSTRY CORRELATION AND ANALYSIS FOR SH-2F 101 ROTOR PROTOTYPE FU-SHANG WEI and ROBERT JONES (Kaman Aerospace Corp., DANIEL H. TILLOTSON, LOREN D. BOLSTRIDGE, and GARY P. Bloomfield, CT) (Structures, Structural Dynamics and Materials GAMBARANI May 1988 306 p Conference, 28th, Monterey, CA, Apr. 6-8, 1987 and AIAA Dynamics (Contract DTFA01-80-C-10093) Specialists Conference, Monterey, CA, Apr. 9, 10, 1987, Technical (DOT/FAA/SA-88/2; REPT-3011-01-03-4675) Avail: NTIS HC Papers. Part 2B, p. 743-752) Journal of Aircraft (ISSN 0021-8669), A14/MF A01 vol. 25, July 1988, p. 647-652. Previously cited in issue 14, p. An operational evaluation of the Traffic Alert and Collision 2106, Accession no. A87-33726. refs Avoidance System (TCAS 2) Industry Prototype was conducted to assess the utility of the TCAS to flight crews, to assess the impacts A89-10113# of TCAS on flight crew workload, to assess the impacts of TCAS SIMULATION OF A BIRDSTRIKE IMPACT ON AIRCRAFT on the air traffic control (ATC) system, and to obtain flight crew CANOPY MATERIAL comments on TCAS design parameters and cockpit displays. The evaluation was conducted on one Boeing 727 aircraft operating in T. V. BAUGHN (Southern Methodist University, Dallas, TX) and L. airline revenue service with Piedmont Airlines. Quantitative data W. GRAHAM (General Dynamics Corp., Fort Worth, TX) Journal on TCAS performance were collected to characterize the location of Aircraft (ISSN 0021-8669), voL 25, July 1988, p. 659-664. refs and frequency of TCAS advisories. Quantitative data were collected The simulation of a birdstrike on a material used in aircraft from flight crews and cockpit observers to assess the utility of canopies is performed using the ABAQUS finite-element code. TCAS and to assess the impacts of TCAS on ATC and the flight The results of the simulation are compared to the response of a crews. Minor operational anomalies were identified and changes test coupon struck by a rubber ball with properties that provide a to operational procedures or TCAS logic were recommended. Author load on the coupon comparable to a bird. The displacement-time history of the test coupon is recorded using a high-speed camera. The results of the impact test are compared to the finite-element results. One of the major tasks in developing the simulation was 05 obtaining a load history to apply to the model. The impact load associated with a birdstrike is hydrodynamic, time dependent, and decreases exponentially from the centerline of the impact region. AIRCRAFT DESIGN, TESTING AND The velocity of impact indicates that material properties at PERFORMANCE high-strain rates would be required for the simulation. Published material properties at lower strain rates provided adequate information to demonstrate good correlation for the loads examined. Includes aircraft simulation technology. Good correlation was achieved in comparing the centerline deflection time histories recorded in the impact test and obtained from the finite-element simulation. Author A89-10101"# Air Force Academy, Colo. FLIGHT-TEST DETERMINATION OF AIRCRAFT CRUISE CHARACTERISTICS USING ACCELERATION AND A89-10463 DECELERATION TECHNIQUES AERODYNAMIC CHARACTERISTICS OF THE ACES-II T. R. YECHOUT (U.S. Air Force Academy, Colorado Springs, CO) EJECTION SEAT AT TRANSONIC MACH NUMBERS Journal of Aircraft (ISSN 0021-8669), vol. 25, July 1988, p. DAVID E. A. REICHENAU (Calspan Corp., Arnold AFB, TN) and 577-582. B. J. WHITE (USAF, Wright Aeronautical Laboratories, (Contract NSG-4028) Wright-Patterson AFB, OH) IN: SAFE Association, Annual A flight-test technique has been developed under NASA Dryden Symposium, 25th, Las Vegas, NV, Nov. 16-19, 1987, Proceedings. sponsorship NSG 4028 to predict aircraft cruise performance Newhall, CA, SAFE Association, 1987, p. 113-120. characteristics. The technique used acceleration and deceleration An investigation was carried out in a 16-ft transonic wind tunnel maneuvers to define baseline aerodynamic and propulsion system to determine the full-scale aerodynamic characteristics of the characteristics, which were then input to a performance modeling Advanced Concept Ejection Seat (ACES-tl). It is noted that the prediction program. Conventional stabilized 'speed power' tests, ACES design is the standard ejection seat used in the USAF which are normally used for cruise performance definition, can F-15, F-16, A-10, B-1B, and T-46 aircraft. Particular attention is comprise a large portion of the flight time in a program. A significant given to the effects of Mach Number, dynamic pressure, crew reduction in flight time was estimated using the performance member size, clothing/flight gear, and seat configuration. The modeling approach with associated savings in cost and schedule. aerodynamic characteristics of the ACES II configuration are in A 20-h verification flight-test program was accomplished. Author good agreement with other typical ejection seat configurations.
25 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Adding clothing and flight gear to the manikins had little effect on A89-10517 the model's static stability or performance characteristics. K.K. CONFIGURATION OPTIMIZATION OF COMMERCIAL AIRCRAFT [KONFIGURATIONSOPTIMIERUNG VON VERKEHRSFLUGZEUGEN] A89-10466 CH. HABERLAND, W. FENSKE, and M. GRABERT (Berlin, MULTI-AXIS SEAT EJECTION (MASE) SLED Technische Universitaet, Federal Republic of Germany) IN: HOWARD G. CLARK (USAF, Test Track Div., Holloman AFB, Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Federal Republic NM) IN: SAFE Association, Annual Symposium, 25th, Las Vegas, of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gese_lschaft NV, Nov. 16-19, 1987, Proceedings. Newhall, CA, SAFE fuer Luft- und Raumfahrt, 1987, p. 245-253. In German. refs Association, 1987, p. 136-140. refs (DGLR PAPER 87-081) The MASE sled allows eiection over a range of fixed pitch, The Computer-Augmented Preliminary Design of Aircraft roll, and yaw angles and dynamic rolling conditions. This sled has (CAPDA) system for aircraft configuration development and a pitch range of + or - 30 deg, a yaw range of + or -20 deg, optimization in the design phase is presented. The basic division and a roll range of + or - 90 deg, in addition to the ability to roll into a model-oriented program structure with modular analytical at high rates during the seat ejection. Consideration is given to method part and a separate monitor is described, and the principle the sled fabrication status and the test program planned for FY88. of dynamic variant programming for full computer-based imaging It is noted that the MASE sled will be used as the test bed for of the geometry and performance using fewer configuration the CREST advanced seat development program in conjunction parameters is explained. A preprocessor is used to obtain the with the advanced dynamic anthropomorphic manikin which will empirical-statistical determination of the complete geometries measure seat-man dynamic interactions. K.K. preliminary to design. The use of efficient convergence acceleration methods for the design consolidation is described, and the aims, A89-10478 methods, and limits of the configuration optimization are shown PASSIVE THERMAL PROTECTION SYSTEM using examples. The broad application possibilities offered by the KEVIN T. BETZ (USAF, Aeronautical Systems Div., graphic postwocessors implemented in this system are demonstrated. C.D. Wright-Patterson AFB, OH) IN: SAFE Association, Annual Symposium, 25th, Las Vegas, NV, Nov. 16-19, 1987, Proceedings. Newhall, CA, SAFE Association, 1987, p. 220-223. refs A89-10518 The passive thermal protection system (PTPS), which provides FS 32 - A SPLIT-FOWLER GLIDER PROBLEM PRESENTATION cockpit thermal protection from a nuclear firefalt, consists of AND SOLUTIONS [FS 32 - EIN laminated flat glass panels with integral perimeter frames mounted SPALT-FOWLER-SEGELFLUGZEUG PROBLEMSTELLUNGEN inboard of the aircraft transparencies. The objective of a joint UND LOESUNGEN] B-1B System Program Office/Defense Nuclear Agency effort was JOACHIM FLEINER IN: Yearbook 1987 I; DGLR, Annual Meeting, to develop and qualify PTPS for possible retrofit to the B-1B Berlin, Federal Republic of Germany, Oct. 5-7, 1987, Reports. bomber. It was found that the thermal performance of PTPS Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. required refinement to eliminate increased transmissivity with 254-263. In German. increases in temperature above 120 F. It is noted that a redesigned (DGLR PAPER 87-082) PLZT helmet-mounted goggle is required to fully realize the The fs 32 project to develop a glider with novel, advantages of PTPS. K.K. variable-geometry wings is examined. The relevant technical data and the potential for achieving a significant increase in performance with fs 32 are discussed, and the related constructional and A89-10482 technological problems are addressed. The choice of materials AN INVESTIGATION OF THE PRESSURE IN AN EJECTION and design of the various glider components are discussed in SEAT BAY DUE TO ROCKET JET detail. C.D. PING QIU (China Flight Test Research Center, Xian, People's Republic of China) IN: SAFE Association, Annual Symposium, A89-10520 25th, Las Vegas, NV, Nov. 16-19, 1987, Proceedings. Newhall, DEVELOPMENT OF A HELICOPTER SIMULATION PROGRAM CA, SAFE Association, 1987, p. 249-254. [ENTWlCKLUNG EINES The distribution of pressure in an ejection seat bay due to HUBSCHRAUBERSIMULATIONSPROGRAMMES] rocket jet obtained by simulation test is briefly described in this UWE ARNOLD (Braunschweig, Technische Universitaet, Brunswick, paper. And also the regions likely to experience high pressure Federal Republic of Germany) IN: Yearbook 1987 I; DGLR, and level of high pressure to be expected are given, with the Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, variation of pressure inside seat bay under different seat position 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und and other test conditions. These provide the basis for analyzing Raumfahrt, 1987, p. 275-286. In German. refs and assessing the effect of rocket jet on seat bay structure. (DGLR PAPER 87-123) Author The theoretical bases and structure of a Fortran program for simmulating the rigid body motion of helicopters are presented. A89-10516 The rotor calculation is quasi-stationarily bound to the numerical APPLICATION OF WlNGLETS WITH INTEGRATED, ADJUSTED integration of the differential equations of motion. The steering is TRAILING-EDGE FLAPS IN A GENERAL AVIATION AIRCRAFT governed by a regulator which simulates pilot behavior or a [ANWENDUNG VON WINGLETS MIT INTEGRIERTER, corresponding practical stabilization system. The initial flight state GEREGELTER HINTERKANTENKLAPPE AN EINEM provides a trimming calculation. The discussion is illustrated by FLUGZEUG DER GENERAL AVIATION] examples involving maneuvers. C.D. A. DIEKMANN (Aachen, Rheinisch-Westfaelische Technische Hochschule, Federal Republic of Germany) IN: Yearbook 1987 A89-10526 I; DGLR, Annual Meeting, Berlin, Federal Republic of Germany, SHEAR WIND MEASUREMENTS ABOARD A PIPER PA 18 Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- AND THE DESIGN OF A MODEL GLIDER AIRCRAFT FOR und Raumfahrt, 1987, p. 235-244. In German. DYNAMIC GLIDING FLIGHT [SCHERWlNDMESSUNGEN AN (DGLR PAPER 87-080) BORD EINER PIPER PA 18 UND AUSLEGUNG EINES The use of winglets with adjusted trailing-edge flaps is proposed MODELLSEGELFLUGZEUGES FUER DEN DYNAMISCHEN as a remedy for the flight-mechanical problems caused by rigid SEGELFLUGI winglets. The design and functioning of the flaps and of a simple, O. GOEBEL (Aachen, Rheinisch-Westfaelische Technische linear control is discussed. The concept is illustrated using a general Hochschule, Federal Republic of Germany) IN: Yearbook 1987 aviation aircraft. C,D. I; DGLR, Annual Meeting, Berlin, Federal Republic of Germany,
26 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- A89-10640"# National Aeronautics and Space Administration. und Raumfahrt, 1987, p. 322-328. In German. refs Hugh L Dryden Flight Research Facility, Edwards, Calif. (DGLR PAPER 87-135/1) X-29A FORWARD-SWEPT-WING FLIGHT RESEARCH An aircraft on-board method for measuring shear wind gradients PROGRAM STATUS is presented. The physical principles ot the method are explained, GARY A. TRIPPENSEE and DAVID P. LUX (NASA, Flight Research and the installation of the requisite equipment on a Piper PA 18 Center, Edwards, CA) IN: International Pacific Air and Space is described. Comparisons with other measurements are reported. Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, The optimization of the measurements using a simulative computer Proceedings. Warrendale, PA, Society of Automotive Engineers, program is discussed. C.D. Inc., 1988, p. 181-188. Previously announced in STAR as N88-17644. (SAE PAPER 872418) A89-10527 COMPUTER PROGRAM FOR SIMULATING DYNAMIC GLIDING The X-29A aircraft is a fascinating combination of integrated technologies incorporated into a unique research aircraft. The FLIGHT [EIN RECHNERPROGRAMM ZUR SIMULATION DES X-29A program is a multiple agency program with management DYNAMISCHEN SEGELFLUGS] and other responsibilities divided among NASA, DARPA, the U.S. THORSTEN NOTTEBAUM (Aachen, Rheinisch-Westfaelische Air Force, and the Grumman Corporation. An overview of the Technische Hochschule, Federal Republic of Germany) IN: recently completed X-29A flight research program, objectives Yearbook 1987 I; DGLR, Annual Meeting, Berlin, Federal Republic achieved, and a discussion of its future is presented. Also discussed of Germany, Oct. 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft are the flight test approach expanding the envelope, typical flight fuer Luft- und Raumfahrt, 1987, p. 329-338. In German. refs maneuvers performed, X-29A program accomplishments, lessons (DGLR PAPER 87-135/2) learned for the Number One aircraft, and future plans with the A simple computer program for simulating flight maneuvers Number Two aircraft. A schedule for both aircraft is presented. A with any gliding aircraft under measured shear wind conditions is description of the unique technologies incorporated into the X-29A described. The program can be used to evaluate the possibility of aircraft is given, along with descriptions of the onboard conducting dynamic gliding flight with modern glider aircraft. The instrumentation system. The X-29A aircraft research program has simulated flight maneuvers are described and the equations of proven highly successful. Using high fly rates from a very reliable motion are presented. The determination of the resistance force experimental aircraft, the program has consistently met or exceeded is addressed. The shear wind field and specific total energy are its design and research goals. Author discussed briefly. The program is described and its flight testing is reported. The determination of the minimal requisite wind shear A89-10641 for three glider aircraft is given, and a sample calculation is described. C.D. MISSION-ADAPTIVE WING RONALD W. DECAMP, RICHARD HARDY, and DOUGLAS K. GOULD (Boeing Commercial Airplane Co., Seattle, WA) IN: A89-10632 International Pacific Air and Space Technology Conference, THE BOEING 7J7 - THE EVOLUTION OF TECHNOLOGY AND Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, DESIGN PA, Society of Automotive Engineers, Inc., 1988, p. 189-195. PETER L. SUTCLIFFE (Boeing Commercial Airplane Co., Seattle, (SAE PAPER 872419) WA) IN: International Pacific Air and Space Technology The Mission-Adaptive Wing (MAW) employs composite Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. materials and uses a digital fly-by-wire flight control system to Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. change wing contour to maintain peak aerodynamic efficiency over 73-84. a large flight envelope. Future aircraft will require large subsonic (SAE PAPER 872405) and supersonic lift-to-drag ratios for maximum cruise ranges at The paper describes some of the technologies that are being high and tow altitudes. At the same time, they will require the considered for the 7J7 and shows how those that benefit the ability to pull high lift coefficients for maneuvers. The ultimate bottom line of operating costs are being incorporated. Mission-Adaptive Wing provides these features by deflecting flexible Some of the developments considered are lightweight structural wing surfaces to achieve the wing camber and smooth continuous components constructed of advanced composites and upper surface contour required for peak aerodynamic performance. aluminum-lithium alloys; advanced aerodynamics allowing thicker, The MAW program completed manual control flight testing in lower sweep, higher aspect ratio wings; flat-panel flight deck November 1986 and started automatic control flight testing in the displays to reduce weight, cost, and power requirements; fly-by-wire summer of 1987. During the manual phase of flight testing, surfaces controls; and dramatic improvements in propulsive efficiency from were set in discrete positions. Resulting data confirmed the new engine designs such as the advanced propfan. B.J. aerodynamic potential to achieve all program goals. The automatic control phases will test four modes designed to increase range, A89-10639 maneuverability, and operational flexibility without affecting pilot EVOLUTION OF THE STOL AND MANEUVER TECHNOLOGY workload. Author DEMONSTRATOR J. A. LAUGHREY (USAF, Wright Aeronautical Laboratories, A89-10653 Wright-Patterson AFB, OH) IN: International Pacific Air and Space INTRODUCTION OF THE HORNET - A SUCCESS STORY Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, H. E. COVERT (McDonnell Douglas-Australia, Ltd., Australia), E. Proceedings. Warrendale, PA, Society of Automotive Engineers, H. BORGMEYER, J. M. MARTIN, J. S. MORRISON, and J. M. Inc., 1988, p. 167-180. refs FLYNN (McDonnell Aircraft Co., Saint Louis, MO) IN: International (SAE PAPER 872417) Pacific Air and Space Technology Conference, Melbourne, The STOL and Maneuver Technology Demonstrator Program Australia, Nov. 13-17, 1987, Proceedings. Warrendale, PA, Society is designing and developing, through tests, simulations and of Automotive Engineers, Inc., 1988, p. 319-323. analyses, a new aircraft and propulsion control system that not (SAE PAPER 872436) only better utilizes aerodynamic controls, but also incorporates The F/A-18 Hornet is the U.S. Navy's newest combat aircraft. the propulsive forces of vectoring and reversing, plus braking and It is also in service with the U.S. Marine Corps, the Canadian steering on landing roll out. The new concepts being developed, Armed Forces, the Royal Australian Air Force and the Spanish which include an integrated flight and nozzle control with a Navy. All of these different users have been very successful in two-dimensional nozzle, will be validated through a series of flights integrating the Hornet into their operations with a minimum of exploring takeoff and landing techniques along with cruise and effort and disruption. This is due to the Hornet's design, in which maneuvering flight. Results of this program are being used to a strong emphasis was placed on reliability and maintainability. transition these concepts into future fighter systems. Author The result is a weapon system which is easily learned by the
27 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
personnel who must operate it. Other benefits include a high JEFFREY M. LENOROVITZ Aviation Week and Space Technology readiness rate and a much reduced requirement for support (ISSN 0005-2175), vol. 129, Sept. 26, 1988, p. 40, 41, 43 (3 ff.). personnel and equipment. Author The Soviet Union's Mikoyan MiG-29, a rugged combat aircraft designed primarily for offensive air-to-air missions, is described. The single-seat aircraft has a glass-fiber-wrap nose radome which A89-10663 houses a coherent pulse-Doppler radar; this radar can supposedly A STUDY ON EFFECTS OF AIRCRAFT NOISE ENVIRONMENT detect a fighter-sized target out to a range of 100 km. ON ITS STRUCTURE Soviet-supplied data indicate that°the aircraft has a maximum Mach FU SHIJtAN (Nanchang Aircraft Manufacturing Co., Jiangxi, number above Mach 2.3, and a service ceiling of 17,000 m. K.K. People's Republic of China) IN: International Pacific Air and Space Technology Conference, Melbourne, Australia, Nov. 13-17, A89-12416# 1987, Proceedings (A89-10627 01-01). Warrendale, PA, Society 'THE POINTER', A NEW CONCEPT FOR RPV AIR VEHICLES of Automotive Engineers, Inc., 1988, p. 431-436. Translation. RODNEY TAYLOR (Bell Helicopter Textron, Fort Worth, TX) IN: Previously cited in issue 08, p. 1144, Accession no. A88-23189. Automation applications for rotorcraft; Proceedings of the National (SAE PAPER 872450) Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, 11 p. A89-11447 The tilt-rotor VTOL concept thus far demonstrated by the XV-15 FATIGUE CRACK GROWTH IN AIRCRAFT MAIN LANDING and V-22 aircraft is being used by a small RPV of about 600 Ib GEAR WHEELS gross weight, designated 'Pointer'. Pointer employs a single, ARVIND NAGAR (USAF, Flight Dynamics Laboratory, fuselage-mounted engine whose power is taken by gearbox and Wright-Patterson AFB, OH) IN: Fracture mechanics; Proceedings two driveshafts to the tiltable wingtip nacelles. The VTOL capability of the Nineteenth National Symposium, San Antonio, TX, June of this propulsion system obviates all launch and recovery 30-July 2, 1986. Philadelphia, PA, American Society for Testing equipment without forfeiture of high forward speeds during critical and Materials, 1988, p. 868-882. refs mission segments; in particular, shipboard operations can be readily The fracture behavior of aircraft landing gear wheels of 2014-T6 conducted from small deck areas. O.C. aluminum is analyzed under service-simulated conditions using a variety of fatigue crack growth characterization techniques. Stress A89-12558# intensity factor solutions and material data are applied to perform METHOD TO OPTIMIZE NACELLE SHAPE IN A SUPERSONIC crack growth predictions using a crack growth program, CRKGRO. CRUISE AIRCRAFT With new stress intensity factor subroutines added to the program REINER SUIKAT and SAEED FAROKHI (Kansas, University, library, the analytic predictions of crack growth show good Lawrence) Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. agreement with the measured crack lengths in a full-scale structural 1988, p. 717-723. Previously cited in issue 03, p. 286, Accession test on a cracked wheel. A damage characteristic curve for the no. A88-14254. refs wheel flange is proposed. V.L. A89-12562"# National Aeronautics and Space Administration. A89-11486 Langley Research Center, Hampton, Va. APPLICATION OF AN ADVANCED PANEL METHOD TO EFFICIENT VIBRATION MODE ANALYSIS OF AIRCRAFT WITH AERODYNAMIC PROBLEMS OF AIRCRAFT DESIGN MULTIPLE EXTERNAL STORE CONFIGURATIONS JOHN L. HESS and WALTER O. VALAREZO (Douglas Aircraft M. KARPEL (NASA, Langley Research Center, Hampton, VA; Israel Co., Long Beach, CA) IN: Panel methods in fluid mechanics Aircraft Industries, Ltd., Lod) Journal of Aircraft (ISSN 0021-8669), with emphasis on aerodynamics; Proceedings of the Third vol. 25, Aug. 1988, p. 747-751. refs GAMM-Seminar, Kiel, Federal Republic of Germany, Jan. 16-18, A coupling method for efficient vibration mode analysis of aircraft 1987. Brunswick, Federal Republic of Germany, Friedr. Vieweg with multiple external store configurations is presented. A set of und Sohn, 1988, p. 79-90. refs low-frequency vibration modes, including rigid-body modes, A surface-source panel method for computing general represent the aircraft. Each external store is represented by its geometries and complicated flow situations in aerodynamics is vibration modes with clamped boundary conditions, and by its described. The present higher-order formulation includes an rigid-body inertial properties. The aircraft modes are obtained from improved iterative solver and a propeller capability that predicts a finite-element model loaded by dummy rigid external stores with not only blade performance but also the mutual interference fictitious masses. The coupling procedure unloads the dummy between a propeller and the airframe on which it is mounted. An stores and loads the actual stores instead. The analytical interactive boundary-layer method is also considered. Results are development is presented, the effects of the fictitious mass presented for various propeller flowfields. R.R. magnitudes are discussed, and a numerical example is given for a combat aircraft with external wing stores. Comparison with A89-11491 vibration modes obtained by a direct (full-size) eigensolution shows A SUBSONIC PANEL METHOD FOR DESIGN OF very accurate coupling results. Once the aircraft and stores data 3-DIMENSIONAL COMPLEX CONFIGURATIONS WITH bases are constructed, the computer time for analyzing any external SPECIFIED PRESSURE DISTRIBUTION store configuration is two to three orders of magnitude less than KRZYSZTOF KUBRYNSKI (Instytut Lotnictwa, Warsaw, Poland) that of a direct solution. Author IN: Panel methods in fluid mechanics with emphasis on aerodynamics; Proceedings of the Third GAMM-Seminar, Kiel, A89-12564# Federal Republic of Germany, Jan. 16-18, 1987. Brunswick, Federal PREDICTION OF AIRCRAFT-PROPELLER-INDUCED, Republic of Germany, Friedr. Vieweg und Sohn, 1988, p. 137-146. STRUCTURE-BORNE INTERIOR NOISE refs JAMES F. UNRUH (Southwest Research Institute, San Antonio, A cheap, iterative method for aerodynamic design of complex TX) Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 3-dimensional configurations (such as wing-body combination) with 758-764. Research supported by Southwest Research Institute. prescribed surface pressure distribution is presented. The method Previously cited in issue 07, p. 946, Accession no. A88-22196. is based on the panel method with numerical optimization. In each refs iteration cycle the geometry modifications are modelled by surface transpiration. Some examples of application of this method for A89-12565# wing-body combinations are presented. Author SEAPLANE TAKEOFF PERFORMANCE - USING DELTA RATIO AS A METHOD OF CORRELATION A89-11559 DALE DE REMER (North Dakota, University, Grand Forks) Journal MIG-29 DESIGN MERGES OLD, NEW TECHNOLOGIES of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 765, 766.
28 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
The 'delta ratio', defined as a seaplane's takeoff water-run N89-10041# Lockheed Aeronautical Systems Co., Burbank, distance/total distance over a 50-ft obstacle, allows a pilot to Calif. determine whether a given takeoff can be made irrespective of WHEEL PERFORMANCE EVALUATION. PHASE 1: ANALYSIS lake size, density altitude, engine and propeller condition, or aircraft Final Report weight. Attention is presently given to the effect of aircraft weight P. C. DURUP, T. R. BRUSSAT, and L. BAKOW Sep. 1988 and takeoff technique variations on the assumption of constant 107 p delta ratio. A flap-change technique is identified as effective in (DOT/FAA/CT-88/16) Avail: NTIS HC A06/MF A01 reducing a heavily loaded seaplane's distance over an obstacle. The procedures of analysis and dynamometer testing that may O.C. be used to develop data and supporting technology for improving aircraft wheel performance are described. As related to current wheel standards and in-service inspection procedures, load/test A89-12719 spectra which characterize wheel operating environments DESIGN AND TESTING FOR AIRFRAMES (associated with long, medium, and short haul aircraft) are defined. J. C. GEERING (British Aerospace, PLC, London, England) IN: These spectra may be applied as a basis for effective dynamometer Bird hazards in aviation; Proceedings of the Symposium, London, testing and to the verification of wheel service limits taking into England, Oct. 14, 1987. London, Royal Aeronautical Society, 1987, account stress corrosion and crack growth conditions. Author p. 24-27. An account is given of the criteria that must be satisfied in civil transport aircraft design to reduce vulnerability to birdstrike N89-10042# Technische Hogeschool, Delft (Netherlands). Dept. damage, in a manner consistent with weight and cost penalty minimization. Attention is given to the compromises among of Aerospace Engineering. DESIGN AND EVALUATION OF DYNAMIC FLIGHT TEST strength, function, weight, and cost, that must be achieved in the design of nose radomes, cockpit transparencies, wing leading MANOEUVERES J. A. MULDER Oct. 1986 305 p edges, engine installations, and empennages. Aircraft bird impact tests must be conducted on full-size aircraft components, in order (PB88-210760; LR-497) Avail: NTIS HC A14/MF A01 CSCL to correctly distribute total impact energy. A compressed air gun 01C propels the birdstrike missile at the test specimen, which is usually Analysis of dynamic flight test data, in the sense of estimating the fresh carcass of a chicken. O.C. stability and control derivaties from measurements of the dynamic response of the aircraft to control input signals, can be formulated in the theoretical frame work of maximum likelihood estimation A89-12720 theory. It is shown that, if certain conditions concerning accuracy WINDSCREEN DESIGN AND TESTING and type of the variables measured in flight are met, the original E. S. HINKLEY (Triplex Aircraft and Special Products, Ltd., maximum likelihood estimation problem can be decomposed into Birmingham, England) IN: Bird hazards in aviation; Proceedings two separate estimation problems which are much easier to solve of the Symposium, London, England, Oct. 14, 1987. London, Royal than the original estimation problem. A new technique for the Aeronautical Society, 1987, p. 28-48. calculation of optimal input signals was developed. The technique The paper reviews the problem of bird strikes on windscreens is based on the description of input singals by linear combinations predominantly from the civil aerospace applications, and gives of elements of finite sets of orthonormal functions. A flight test details of the various designs of windscreens used to combat this program was carried out with a DeHaviland DHC-2 Beaver specific threat and the materials that are used. The materials experimental aircraft, equiped with an automatic control system. include glass strengthened to various levels, as cast and stretched The system allowed precise implementation in real time of quite acrylic, polyvinyl butyral and polyurethane interlayers and arbitrary elevator, aileron and rudder control input signals. Also a polycarbonates. The types of design that have emerged over high accuracy flight test measurement system was installed in the approximately 30 years are reviewed, ranging from earlier designs aircraft. Author relying upon the PVB interlayer to the more complex results of recent developments using composite plastic/glass constructions, for instance the EH101 windscreen and Boeing 7J7. Author N89-10887 California Univ., Los Angeles. AEROELASTICITY AND STRUCTURAL OPTIMIZATION OF N89-10040# Materials Research Labs., Melbourne (Australia). HELICOPTER ROTOR BLADES WITH SWEPT TIPS Ph.D. CONTAMINATION OF ENVIRONMENTAL CONTROL SYSTEMS Thesis IN HERCULES AIRCRAFT ROBERTO CELl 1987 507 p A. G. KELSO, J. M CHARLESWORTH, and G. G. MCVEA Apr. Avail: Univ. Microfilms Order No. DA8800601 1988 27 p Structural optimization techniques are used to minimize the (MRL-R-1116; AR-005-230) Avail: NTIS HC A03/MF A01 oscillatory vertical hub shears for a helicopter in forward flight, The assistance of MRL was requested by RAAF in determining subject to aeroelastic stability constraints, blade natural frequency the origins of contamination of trrboprop bleed air used for placement constraints, and autorotation constraints. A special environmental control in Hercules C-130 transport aircraft. Air technique is used to build a sequence of approximate, inexpensive sampling in the interior of affected planes was performed in-flight to solve approximate optimization problems, the solutions of which and on the ground, together with laboratory sampling of vapor converge to the solution of the exact, expensive to solve from all suspect contaminating fluids. Gas chromatographic (GC) optimization problem. Blade configurations with both straight and and GC/mass spectrometric (MS) analysis of collected samples swept tips, and single- and double-cell cross sections are analyzed. confirmed that aviation turbine fuel leakage produces a continuous The results show that the approach used is very efficient, and background of hydrocarbon vapor around 0.1 to 0.5 ppm in affected produces improved designs with a very small number of blade aircraft. Positive indications of turbine oil vapors were found in aeroelastic analyses. A special finite element for the modeling of filter bags taken from the air-duct system of suspect aircraft. Some a swept tip rotor blade is derived. A methodology for the formulation traces of organophosphorus compounds, particularly the tricresyl of the aeroelastic stability and response for helicopter rotor blades phosphate additive in the oil, were found in the air filter bags. is proposed, which reduces considerably the implementation effort, However, at present there is no evidence to support a hypothesis and is applicable to both straight and swept tip blades. The that neurotoxic bicyclophosphorous compounds derived from the methodology is combined with a finite element model of the blade, oil additive are present. It is strongly recommended that in addition and a quasilinear solution technique. As a preliminary to the analysis to normal maintenance of turbine oil seals and fuel nozzles, the of swept tip blades, a study was conducted of the aeroelastic use of charcoal cloth filters in the air ducting system be investigated behavior of rotor blades with noncoincident elastic axis, as a means of absorbing the noxious odors. Author aerodynamic centers, and centers of mass. Dissert. Abstr.
29 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
N89-10889 Southampton Univ. (England). A methodology for analysing aircraft attrition data and THE USE OF THE COMPLEX SUMMATION METHOD FOR establishing the reliability of the results is given. Underlying FORMULATING ALGORITHMS FOR DECOUPLING assumptions include exponentially distributed times between VERTICAL/HORIZONTAL MOTIONS OF ROLLING AIRCRAFT attritions, and a mean that increases with operating experience. Ph.D. Thesis Principal techniques used are Maximum Likelihood Estimation and E. M. BELO 1987 249 p Jackknifing. An example is given drawn from F/A-18 data. GRA Avail: Univ. Microfilms Order No. BRD-80844 Algorithms produced for rolling Aircraft Flight Control Systems to decouple vertical from horizontal motions are assessed. The O'6 aim is to study the use of the Complex Summation Method as a technique to assist the designer in the selection of algorithms choosen to achieve this objective. The benefit of this method for AIRCRAFT INSTRUMENTATION decoupling objective is that the presence of coupling is easily seen by the existence of imaginery coefficients in the complex Includes cockpit and cabin display devices; and flight instruments. system equations. A numerical example is presented and results in terms of time responses are obtained from the application of an algorithms which transforms it into a Similar and A89-10128# Antisymmetrically Coupled (SAC) system with outputs being the COST-EFFECTIVE STRAPDOWN I.N.So DESIGN AND THE acceleration decoupled in Inertial Axes. Dissert. Abstr. NEED FOR STANDARD FLIGHT PROFILES N. F. WATSON and E. A. F. CAMPBELL (Ferranti Defence Systems, N89-10890"# Massachusetts Inst. of Tech., Cambridge. Dept. Ltd., Edinburgh, Scotland) IN: Symposium Gyro Technology 1987; of Aeronautics and Astronautics. Proceedings of the Symposium, Stuttgart, Federal Republic of FLIGHT TEST RESULTS FOR THE DAEDALUS AND LIGHT Germany, Sept. 22, 23, 1987. Stuttgart/Duesseldorf, Universitaet EAGLE HUMAN POWERED AIRCRAFT Stuttgart/Deutsche Gesellschaft fuer Ortung und Navigation, 1987, R. BRYAN SULLIVAN and SIEGFRIED H. ZERWECKH 7 Jun. p. 14.0-14.49. refs 1988 138 p A method is proposed for minimizing INS costs for a given (Contract NAG1-836) performance level. A mathematical error model is first developed (NASA-CR-183305; NAS 1.26:183305) Avail: NTIS HC A07/MF which can be used to predict the statistical properties of INS A01 CSCL 01C position and velocity errors for a given flight profile from the The results of the flight test program of the Daedalus and variance of each significant error source. The model can then be Light Eagle human powered aircraft in the winter of 1987/88 are used to derive a set of limits for the variance of each parameter given. The results from experiments exploring the Light Eagle's which are consistent with the performance requirements of the rigid body and structural dynamics are presented. The interactions specification. Such an 'error budget' can be used to predict the of these dynamics with the autopilot design are investigated. statistical performance of the strapdown INS for any given flight Estimates of the power required to fly the Daedalus aircraft are profile. The introduction of a standard set of flight profiles will detailed. The system of sensors, signal conditioning boards, and make it possible to establish an error budget which meets the data acquisition equipment used to record the flight data is also specified performance requirements for specified flight profiles described. In order to investigate the dynamics of the aircraft, without imposing unrealistic requirements on the components of flight test maneuvers were developed to yield maximum data quality the system. Cost-effective design is achieved partly by deriving from the point of view of estimating lateral and longitudinal stability component specifications which are just sufficient to enable the derivatives. From this data, structural flexibility and unsteady INS to perform adequately (taking into account worst case aerodynamics have been modeled in an ad hoc manner and are conditions). V.L. used to augment the equations of motion with flexibility effects. Results of maneuvers that were flown are compared with the A89-10129# predictions from the flexibility model. To extend the ad hoc flexibility INTEGRATED REDUNDANT REFERENCE SYSTEMS FOR model, a fully flexible aeroelastic model has been developed. The FLIGHT CONTROL AND NAVIGATION WITH SKEWED model is unusual in the approximate equality of many structural SENSOR ARRANGEMENT natural frequencies and the importance of unsteady aerodynamic U. KROGMANN (Bodenseewerk Geraetetechnik GmbH, effects, the Gossamer Albatross. It is hypothesized that this inverse Ueberlingen, Federal Republic of Germany) IN: Symposium Gyro ground effect is caused by turbulence in the Earth's boundary Technology 1987; Proceedings of the Symposium, Stuttgart, layer. The diameters of the largest boundary layer eddies (which Federal Republic of Germany, Sept. 22, 23, 1987. represent most of the turbulent kinetic energy) are proportional to Stuttgart/Duesseldorf, Universitaet Stuttgart/Deutsche Gesell- altitude; thus, closer to the ground, the energy in the boundary schaft fuer Ortung und Navigation, 1987, p. 15.0-15.20. layer becomes concentrated in eddies of smaller and smaller The concept of an integrated redundant reference system for diameter. Eventually the eddies become sufficiently small flight control and navigation is examined, and a prototype of such (approximately 0.5 cm) that they trip the laminar boundary layer a system is briefly described. In the system proposed here, the on the wing. As a result, a greater percentage of the wing area is required performance and flight safety are obtained in the sense covered with turbulent flow. Consequently the aircraft's drag and of a synergistic complement of flight control/stabilization and the pow er required both increase as the aircraft flies closer to navigation by utilizing a minimum number of redundant sensors the ground. The results of the flight test program are examined with sufficient reliability and accuracy and by means of an effective critically, especially with respect to future applications. Maneuvers redundance management technique for failure detection and that allow the observation of stability derivatives for flexible aircraft identification. Skewed sensor orientations are employed in order are detailed. Considerations for the design of autopilots for future to minimize the number of sensors. The sensor layout and the human power aircraft and high-altitude RPV's are discussed. signal processing structure of the prototype system are shown. Techniques useful in estimating the power required to fly aircraft V.L. of very high lift to drag ratio are described. A89-10131# N89-10891# Department of Defence, Canberra (Australia). STATE OF THE ART INERTIAL NAVIGATION - FLIGHT Central Studies Branch. TESTING OF THE HONEYWELL LINS STANDARD SOME STATISTICAL ASPECTS OF ATTRITION STUDIES NAVIGATOR H-423 B. K. MCMILLAN May 1988 27 p D. W. WAGNER (HoneywelI Regelsysteme GmbH, Maintal, Federal (AD-A196665; CSB-MEMO-3; DODA-AR-005-257) Avail: NTIS Republic of Germany) IN: Symposium Gyro Technology 1987; HC A03/MF A01 CSCL t2C Proceedings of the Symposium, Stuttgart, Federal Republic of
30 06 AIRCRAFT INSTRUMENTATION
Germany, Sept. 22, 23, 1987. Stuttgart/Duesseldorf, Universitaet and the PWSS principles are analytically presented. Flight results Stuttgart/Deutsche Gesellschaft fuer Ortung und Navigation, 1987, under inversion weather conditions are given, including wind and p. 17.0-17.26. temperature profiles and vertical shear features. C.D. The hardware and software of the Honeywell Laser Inertial Navigation System (LINS) H-423 are described, and results of the A89-10536 flight testing of the H-423 system conducted on a TORNADO THE HISTORY OF AIRCRAFT ONBOARD EQUIPMENT [ZUR aircraft are reported. An evaluation of the flight test data shows GESCHICHTE DER FLUGZEUG-BORDAUSRUESTUNG] the accuracy of the LINS to be better than 0.3 nm/h, as compared G. W. A. KLEIN IN: Yearbook 1987 I; DGLR, Annual Meeting, to the specified value of 0.8 mn/h. Horizontal velocity errors, which Berlin, Federal Republic of Germany, Oct. 5-7, 1987, Reports. are critical to weapon delivery functions, are less than 2.2 ft/s Bonn, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. rms compared to the specified 2.5 ft/s limit. The results have 436-442. In German. refs been achieved with alignment times of 6 rain versus the specified (DGLR PAPER 87-054) time of 8 min. V.L. The development history of onboard electrical equipment for aircraft is traced, with a focus on flight-control and navigation A89-10364 devices developed in Germany during the 1930s and 1940s. Topics APPLICATIONS OF TIME AND WAVELENGTH DIVISION addressed include generators, gyroscopes, compasses, and inertial MULTIPLEXING TO DIGITAL OPTICAL CODE PLATES navigation. Extensive drawings and diagrams are provided. T.K. D. VARSHNEYA (Teledyne Ryan Electronics, San Diego, CA) and W. L. GLOMB, JR. (United Technologies Research Center, East A89-10582 Hartford, CT) IN: Fiber optic and laser sensors V; Proceedings THE DESIGN EYE REFERENCE POINT of the Meeting, San Diego, CA, Aug. 17-19, 1987. Bellingham, GERALD STONE (Douglas Aircraft Co., Long Beach, CA) IN: WA, Society of Photo-Optical Instrumentation Engineers, 1988, p. Aerospace Behavioral Engineering Technology Conference, 6th, 210-213. refs Long Beach, CA, Oct. 5-8, 1987, Proceedings. Warrendale, PA, The application of pulse time division multiplexing and Society of Automotive Engineers, Inc., 1988, p. 51-57. refs wavelength division multiplexing to reflective digital optical code (SAE PAPER 871763) plates for sensing position on aircraft is discussed, with particular This paper discusses the meaning of the pilot's 'design eye attention given to temperature drifts and component tolerances in reference point' (DERP) concept and examines the difference the optical power budgets. Both approaches are found to be between operational experience and current cockpit design constrained by environmental effects and small power budgets. In procedures relative to the DERP. It is emphasized that, while the addition, the performance of the reflective WDM system is strongly DERP is an effective concept for defining flight deck architecture dependent on the number of connectors used in the interconnect in relation to the pilot interface, it does not adequately express fiber. It is emphasized that the development of either of these operational practice. It is shown that, in practice, failure to place sensor concepts requires careful design and evaluation to resolve the pilot's eye in the proper position will result in a decreased these problems. V.L. visual segment of the ground during approach or the obscuration of vital flight displays, affecting flight safety. A potential design A89-10521 solution that employs a modified automotive 'eyellipse' concept is NAVIGATION OF AIRCRAFT WITH RIGID IMAGE-FORMING proposed as a possible alternative to DERP. The effect of this SENSORS [NAVIGATION VON FLUGGERAETEN MIT new design methodology on existing cockpit geometry is STARREN ABBILDENDEN SENSOREN] demonstrated. I.S. K.-H. KEIL, U. MACKENROTH, R. SCHMIDT, and H. ZINNER (Messerschmitt-Boelkow-Blohm GmbH, Munich, Federal Republic A89-10585 of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, AVIONIC COLOR LIQUID CRYSTAL DISPLAYS - RECENT Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, TRENDS Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 287-293. THOMAS L CREDELLE (GE Corporate Research and In German. BMVg-supported research, refs Development Center, Schenectady, NY) IN: Aerospace Behavioral (DGLR PAPER 87-130) Engineering Technology Conference, 6th, Long Beach, CA, Oct. A system is described which permits an aircraft to be navigated 5-8, 1987, Proceedings. Warrendale, PA, Society of Automotive based only on information fed by an image-forming sensor built Engineers, Inc., 1988, p. 77-82. refs rigidly into the aircraft. The necessary flight parameters are derived (SAE PAPER 871790) by evaluating the spatial and temporal intensity variations in the Flat panel technology, specifically liquid crystal flat panel image plane, and image processing is accomplished using model technology, has made tremendous progress in the past few years assumptions and a Kalman filter. Simulations are used to show and is now poised to challenge the CRTs in avionic applications. that the values resulting from this image processing are complete The operating principles and eiectrooptic characteristics of and accurate enough to permit adequate steering and control of active-matrix-addressed liquid crystal displays are discussed in this the aircraft. C.D. paper. Issues related to performance in the demanding cockpit environment are also presented. Operating characteristics of a A89-10525 1024 x 1024 color LCD is shown. Author THE 'PNEUMATIC WIND SHEAR SENSOR' (PWSS) - AN AID TO FLIGHT PATH REGULATION AND TO DISTURBANCE A89-10617 MAGNITUDE IDENTIFICATION IN SHEAR WIND SITUATIONS THE V-22 VIBRATION, STRUCTURAL LIFE, AND ENGINE [DER 'PNEUMATIC WIND SHEAR SENSOR' (PWSS) - EIN DIAGNOSTIC SYSTEM, VSLED HILFSMITTEL ZUR FLUGBAHNREGELUNG UND ZUR MICHAEL J. AUGUSTIN (Bell Helicopter Textron, Inc., Fort Worth, STOERGROESSENIDENTIFIKATION BEI TX) and JOHN D. PHILLIPS (General Motors Corp., Allison Gas SCHERWlNDSITUATIONEN ] Turbine Div., Indianapolis, IN) IN: Aircraft gas turbine engine S. ZHU, H. NELLES, and R. STAUFENBIEL (Aachen, monitoring systems: An update. Warrendale, PA, Society of Rheinisch-Westfaelische Technische Hochschule, Federal Republic Automotive Engineers, Inc., 1988, p. 67-78. of Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, (SAE 871732) Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, The development of the vibration, structural life, and engine Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 314-321. diagnostic (VSLED) system for the V-22 tiltrotor aircraft is In German. refs discussed. The V-22, its avionic interfaces to VSLED, the VSLED (DGLR PAPER 87-134) hardware, and the concepts used to monitor the V-22 engines Test results on a newly developed, simple Pneumatic Wind are examined. The program schedule for building the VSLED Shear Sensor (PWSS) are reported. The test aircraft is described airborne unit is presented. The functional requirements of the
31 06 AIRCRAFT INSTRUMENTATION
VSLED system are discussed, including the detection of operating System (TCAS) II Industry Prototype installed on a Piedmont limit exceedances, performance degradation trending, fault Airlines' Boeing 727 aircraft. The data presented represents detection and isolation, power assurance checks, post-flight quantitative and qualitative information on the performance of TCAS maintenance data, and parts life usage monitoring. R.B. II in the National Airspace System (NAS) and identifies the impacts of TCAS on Air Traffic Control and the flight crew. The information A89-10647 provided concentrates on the characteristics of the TCAS SURVEILLANCE - HIGH-TECHNOLOGY FIT-OUT FOR THE encounters and the operational use of the system. Author NOMAD AIRCRAFT RICHARD PAGE and BILL BROWN (Government Aircraft Factories, A89-12403"# National Aeronautics and Space Administration. Port Melbourne, Australia) IN: International Pacific Air and Space Ames Research Center, Moffett Field, Calif. Technology Conference, Melbourne, Australia, Nov. 13-17, 1987, SIMULATION AND ANALYSIS OF IMAGE-BASED NAVIGATION Proceedings. Warrendale, PA, Society of Automotive Engineers, SYSTEM FOR ROTORCRAFT LOW-ALTITUDE FLIGHT Inc., 1988, p. 235-242. BANAVAR SRIDHAR (NASA, Ames Research Center, Moffett Field, (SAE PAPER 872428) CA) and ANIL V. PHATAK (Analytical Mechanics Associates, Nomad, a proven low-level marine surveillance aircraft, has Mountain View, CA) IN: Automation applications for rotorcraft; been upgraded to counter illegal drug smuggling. A conceptual Proceedings of the National Specialists' Meeting, Atlanta, GA, Apr. design was formed after providing the latest applicable sensor 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, 11 equipment in a prototype fit-out to the Nomad aircraft. Issues p. refs discussed are the proof of concept, the FLIR installation, the radar The automation of helicopter NOE flight entails the modification installation, the sensor operator work station, avionic systems of nominal trajectories on the basis of the detection and location integration, the navigation system, and the communications and of obstacles by means of onboard sensors. This process is audio system. The final design was firmed after evaluation of the presently studied using a sequence of images from a passive prototype results and in consultation with the future operators. sensor mounted at the helicopter's center of gravity and oriented B.J. with the viewing-axis along the rotorcraft's longitudinal body-axis. Three different Kalman filters are used to estimate the location of A89-10658 an object on the ground during the course of various simulated HEALTH AND USAGE MONITORING - THE INTEGRATED APPROACH helicopter maneuvers; two of the three filters are found to yield good object location estimates. O.C. lAIN ROBERTSON and CLIVE PAGET (Smiths Industries Aerospace and Defence Co., Hampshire, England) IN: International Pacific Air and Space Technology Conference, A89-12411# Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, APPLICATION OF CONSTRAINT SUSPENSION TECHNIQUES PA, Society of Automotive Engineers, Inc., 1988, p. 375-384. TO DIAGNOSIS IN HELICOPTER CAUTION/WARNING (SAE PAPER 872445) SYSTEMS The state-of-the-art health and usage monitoring systems GREG GLENN (McDonnell Douglas Helicopter Co., Mesa, AZ) applied to the propulsion and structural elements of fixed and IN: Automation applications for rotorcraft; Proceedings of the rotary wing civil aircraft are described. A typical system including National Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. an airborne processor and recorder, a data transfer unit, and a Alexandria, VA, American Helicopter Society, 1988, 8 p. ground-based analysis computer is presented. Current work Army-supported research, refs sponsored by the British Civil Aviation Authority is discussed as The U.S. Army's Apache Enhanced Diagnostic System program well as future possibilities. K.K. has accomplished the development of a demonstrator system capable of simulating the multiplex bus traffic of caution/warning- A89-10692 related data, and then invoking a diagnostic module upon detec- CIRCUIT PROTECTION FOR ADVANCED AIRCRAFT - A tion of an abnormal condition. Problem indicators are prioritized FUNCTIONAL AND HISTORICAL PERSPECTIVE on the basis of severity, and displayed on a simulated cockpit FRANCIS A. CANNAVO, JR., ROBERT W. PETERSON, and display and multifunction display. Severe problems are an- CARLTON M COBB (Texas Instruments, Inc., Dallas) IN: nounced aurally by means of digitally-sampled stored messages. Aerospace avionics equipment and integration; Proceedings of the The diagnostic module employs a candidate-generation tech- Second Conference, Dallas, TX, Nov. 2-4, 1987. Warrendale, PA, nique, via 'constraint-suspension', to prune the list of suspected Society of Automotive Engineers, Inc., 1988, p. 167-172. components during failure diagnosis; constraint-suspension is a (SAE PAPER 872502) form of model-based reasoning that allows the diagnosis of faults Aircraft power distribution systems traditionally have been through a modeling of correct system behavior and a comparison controlled by the use of electromechanical devices. Advances in of actual and modeled outputs. O.C. solid state and computer technology now offer the potential for fully automatic control. Solid state power controllers (SSPC) are A89-12415# now emerging to meet this need. By prudent SSPC design, it is DEVELOPMENT OF A RULE-BASED DEMONSTRATION possible to gain the control advantages offered by solid state PROTOTYPE EXPERT SYSTEM FOR INFLIGHT EMERGENCIES technology while at the same time retaining the protection FOR THE UHIH HELICOPTER advantages of traditional circuit breakers. This paper describes JOHNNIE A. HAM (U.S. Army; Georgia Institute of Technology, the key features of circuit breakers in use today that should be Atlanta) IN: Automation applications for rotorcraft; Proceedings considered critical and incorporated into the SSPC specifications of the National Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. for future aircraft as well as describing the special features possible Alexandria, VA, American Helicopter Society, 1988, 8 p. refs with SSPCs. Author An expert system was developed for the UH1H helicopter to identify emergencies using a rule-based control strategy. Once A89-12321 the emergency is correctly identified, the expert then considers OPERATIONAL FINDINGS FROM A TRAFFIC ALERT AND altitude and airspeed and presents the pilot with the procedure to COLLISION AVOIDANCE SYSTEM (TCAS) EVALUATION follow. Judgments can be processed despite incomplete sensor DAN TILLOTSON (Arinc Research Corp., Annapolis, MD) SAE, information, utilizing the 'expert' to determine the most probable Aerospace Vehicle Conference, Annapolis, MD, Apr. 18-20, 1988. failure that had occurred. The engine category of failures was 16p. used for test cases. Software developed was accomplished in (SAE PAPER 880943) LISP using GEST (Generic Expert System Tool). Hardware and This paper provides a summary of the data and findings from implementation issues, as well as automatic response and pilot a ten-month evaluation of the Traffic Alert and Collision Avoidance interaction are also addressed. Four areas need further exploration:
32
L • 07 AIRCRAFT PROPULSION AND POWER
the need for configurable software; the susceptibility of components for Highly Integrated Guidance and Control Systems 15 p Jun. to EMI/EMP interference; and the potentials of parallel processing 1988 and optical computers. Author Avail: NTIS HC A08/MF A01 An avionics architecture exploiting high-speed, high density N89-10834# Air Force Wright Aeronautical Labs., VLSI and VHSIC technology by repartitioning the traditional avionics Wright-Patterson AFB, Ohio. Avionics Lab. suite requires subsystem interconnection via backbone and ADVANCED AVIONICS ARCHITECTURE PAVE PILLAR backplane buses and networks operating at data rates far JOHN C. OSTGAARD In AGARD, Computing Systems exceeding those used for avionics in the past. In fact, the rates Configuration for Highly Integrated Guidance and Control Systems are high enough that fiber optics is the only interconnect technology 8 p Jun. 1988 that does not impose substantial size, weight, and life cycle cost Avail: NTIS HC A08/MF A01 penalties on the overall system. In the Pave Pillar architecture the The increased use of advanced electronics has given modern fiber optic multiplex bus for command and control, block transfer, combat aircraft phenomenal levels of performance, but at a stiff and flight control functions, based on a variation of the IEEE price in initial cost, maintenance workload and aircraft availability. 802.4 and 802.2 token-passing bus protocol for the physical and Hence, aircraft design is shifting to give equal emphasis on data link layers, operates at 50 Mbps. A number of specific performance, affordability, maintainability, and reliability in the implementations have emerged. The parallel internal bus protocol development of avionic systems. The paper discusses the ties users (data processors) together in the backplane and through challenges and benefits of an avionics architecture concept which a bus interface unit to the multiplex bus. Other kinds of networks integrates avionic functions at the system level thereby improving are used to serve subsystems connecting video terminals, sensors, the system's accuracy, increasing its immunity to failure, and signal processors, etc. An overview of the multiplexed high-speed decreasing its reliance on multiple redundant sensors. This design data bus and parallel backplane bus designs and their interface is philosophy, which permits resources to be shared across presented. The implementation details and options for the fiber subsystems, requires a highly coupled system-wide management optic network which supports the interconnection of avionics bus and control program (operating system) supported by a wide-band interface modules in different physical locations are discussed. distribution network, high-speed data and signal processors, and Passive and active star-coupled networks are compared and extensive mass memory. The implementation strategy for this conclusions drawn. The state of the art in packaging of the avionics avionics architecture is the system-wide utilization of common bus interface and related line replaceable modules is illustrated. modular building blocks using advanced microelectronics such as Author VHStC, standard 3/4 ATR modules and integrated racks, all interconnected by fiber optic networks. The generic integration approach and architecture produced by the PAVE PILLAR program 07 is the foundation for avionics development in the next generation aircraft for the U.S. DOD and include such aircraft as the USAF Advanced Tactical Fighter (ATF). Author AIRCRAFT PROPULSION AND POWER
N89-10835# Air Force Wright Aeronautical Labs., Includes prime propulsion systems and systems components, e.g., Wright-Patterson AFB, Ohio. Data and Signal Processing Group. gas turbine engines and compressors; and on-board auxiliary power DATA AND SIGNAL PROCESSING ARCHITECTURES FOR plants for aircraft. FUTURE AVIONICS MARK T. MICHAEL In AGARD, Computing Systems Configuration for Highly Integrated Guidance and Control Systems 12 p Jun. A89-10528 1988 ASPECTS OF INCREASING ECONOMY USING FUTURE Avail: NTIS HC A08/MF A01 LOW-POWER AIRCRAFT PROPULSION SYSTEMS [ASPEKTE Pave Pillar architecture incorporates a Common Signal ZUR WlRTSCHAFTLICHKEITSSTEIGERUNG BEI Processor (CSP) concept as a key building block of a USAF ZUKUENFTIGEN LUFTFAHRTANTRIEBEN KLEINER advanced avionics suite. This concept embodies the use of LEISTUNG] standard internal interfaces, a family of modules, use of the U. DAMMEL and H. RICHTER (KHD Luftfahrttechnik GmbH, programming language Ada to express application program for Oberursel, Federal Republic of Germany) IN: Yearbook 1987 I; the data processors within CSP, and the use of a Graph Notation DGLR, Annual Meeting, Berlin, Federal Republic of Germany, Oct. to represent signal processing functions for the signal processing 5-7, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Lutt- und components of the CSP. The modularity permits upgrading any Raumfahrt, 1987, p. 344-349. In German. hardware or software component with minimal disruption to the (DGLR PAPER 87-100) rest of the design. CSP is an open architecture in that the interfaces Examples are used here to show what steps need to be taken and module specifications are non-proprietary and can be built by to increase the economy of future low-power aircraft propulsion other vendors. The paper will address the system concept, systems. Technologies involving thermodynamics, flow mechanics, hardware architecture, and software philosophy comprising the CSP materials science, construction, mechanical components, and system. It will describe in general terms how the CSP hardware control are considered. A leading concept for the 1990s is works and its expandability. Existing modules will be listed and described. C.D. potential future modules identified. A brief description of the Graph Notation and its advantages will be provided. The CSP Local A89-10613 Operating System capabilities and use will be summarized. AIRCRAFT GAS TURBINE ENGINE MONITORING SYSTEMS: Application studies to determine the suitability of the CSP concept AN UPDATE for different avionic applications such as radar, electronic warfare, Warrendale, PA, Society of Automotive Engineers, Inc. (SAE communications, and electro-optical sensors will be briefly SP-728), 1988, 330 p. For individual items see A89-10614 to summarized. The role of the MIL-STD-1750A processors in CSP A89-10626. and their limitations will be touched on, and future upgrades to (SAE SP-728) 32-bit machines discussed. Author Papers concerning aircraft gas turbine engine monitoring systems are presented, including pocket calculator trend monitoring N89-10836# Harris Corp., Melbourne, Fla. Government for gas turbine engines, the development and testing of inflight Aerospace Systems Div. engine performance monitoring technique for the U.S. Navy P-3C FIBER OPTIC BUSES AND NETWORKS FOR ADVANCED airplane, a guide to temperature monitoring in gas turbine engines, AVIONICS ARCHITECTURES and an overview of airborne vibration monitoring systems. Other R. W. UHLHORN In AGARD, Computing Systems Configuration aspects include the V-22 vibration, structural life, and engine
33 07 AIRCRAFT PROPULSION AND POWER
diagnostic system, an operational engine monitoring system, a An update. Warrendale, PA, Society of Automotive Engineers, Inc., ground based engine monitoring program for general application, 1988, p. 79-84. refs engine monitoring systems for helicopters, and quantitative debris (SAE 871733) monitoring. Oil system monitoring, vibration monitoring systems, Engine monitoring systems have been in use on civil airliners life usage monitoring and parts management for aircraft gas since the late sixties and have developed continuously. This paper monitoring systems are also discussed. R.B. reviews major problems encountered by a typical user and examines current and future developments to determine the extent A89-10614 to which lessons learned in the past have been applied to POCKET CALCULATOR TREND MONITORING FOR GAS development efforts. The view gained is that future systems will TURBINE ENGINES indeed resolve most of the problems encountered. The paper R. HALLIDAY and R. D. JACKSON (Pratt and Whitney Canada, provides existing and potential engine monitoring users with insight Longueil, Canada) IN: Aircraft gas turbine engine monitoring into the main pitfalls of these systems and provides guidelines on systems: An update. Warrendale, PA, Society of Automotive what to look for in an engine monitoring system. Author Engineers, Inc., 1988, p. 1-4. (SAE 841461) A89-10619 The possibility of using a programmable pocket calculator to GAS TURBINE ENGINE MONITORING SYSTEMS - predict the need for engine maintenance by monitoring basic engine HELICOPTER EXPERIENCE parameters at known environmental conditions is discussed. The calculator normalizes the gas generator speed, interturbine JAMES L, PETTIGREW (Howell Instruments, Inc., Fort Worth, TX) temperature, and fuel flow, and corrects for the baseline altitude IN: Aircraft gas turbine engine monitoring systems: An update. and speed. The change between the actual and baseline Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 97-111. refs parameters at the normalized output power are plotted against (SAE 871735) engine running time to give a trend plot. Deviations can be interpreted to determine when engine maintenance is required. A monitoring system for military and civilian helicopters is Thus, hot section inspections scheduling can be based on trend discussed, stressing the use of digital technology engine hardware plots, providing a maintenance cost savings. R.B. to improve the quantity and quality of data available for propulsion system management. The Engine Performance Assurance Monitoring System (EPAMS), which is used in the U.S. Navy's A89-10615 CH-53E, is evaluated and the possible commercial application of DEVELOPMENT AND TESTING OF AN INFLIGHT ENGINE EPAMS is examined. Information provided by the system includes PERFORMANCE MONITORING TECHNIQUE FOR THE U.S. a record of operating time, data for engine trending, maximum NAVY P-3C AIRPLANE temperatures and RPMs for each engine, data for power changes, JOSEPH D. DUPCAK (Lockheed-California Co., Burbank), PAUL hot section factor count, times above selected values, and the DEPPE, and RICH PREVATT (U.S. Navy, Naval Air Test Center, coast-down time at shutdown. R.B. Patuxent River, MD) IN: Aircraft gas turbine engine monitoring systems: An update. Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 5-14. refs A89-10620 (SAE 841462) FIELD EXPERIENCE WITH QUANTITATIVE DEBRIS The development of a low-cost procedure for monitoring engine MONITORING performance for the U.S. Navy P-3C airplane is discussed. The FRANK DIPASQUALE (Aeroquip Corp., Tedeco Div., Glenolden, development program consists of three phases: (1) a flight test PA) IN: Aircraft gas turbine engine monitoring systems: An update. program to obtain engine performance data to determine standards Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. or baselines, (2) the establishment of algorithms and procedures 113-120. refs for implementing inflight engine performance trending, and (3) a (SAE 871736) fleet trial. The proposed engine monitoring system is described Sensor technology for the monitoring of failing engine and preliminary results of the fleet trials are presented. R.B. components has been developed for on-board fluid condition monitoring and to reduce false alarms. The technology, called A89-10616 quantitative debris monitoring (QDM), is described and illustrated, AIR 1900 - GUIDE TO TEMPERATURE MONITORING IN and results are presented from flight and ground based tests. AIRCRAFT GAS TURBINE ENGINES Tests include the use of the QDM system to monitor debris from JERRY L. EDWARDS (Rosemount, Inc., Burnsville, MN) IN: a turbine engine bearing in a load and operational environment Aircraft gas turbine engine monitoring systems: An update. simulating flight conditions, the application of QDM to helicopter Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. gearbox monitoring to detect fretting bearing and bearing race, 15-55. bearing wear detection, and detection of labyrinth seal wear and (SAE 871730) spalled inner race. R.B. This Aerospace Information Report (AIR) is being prepared by the E-32 Committee in recognition of the need to provide the A89-10621 most up-to-date information on temperature measurement for TEXMAS - AN EXPERT SYSTEM FOR GAS TURBINE ENGINE production gas turbine engines. Information on various functions DIAGNOSIS AND MORE for which sensors are used is provided, and the most widely used sensor types are identified. Considerations are made for the entire KENNETH COLLINGE and KENNETH SCHOFF (Textron, Inc., Avco measurement system and not just the sensor itself. Selection Lycoming Textron, Stratford, CT) IN: Aircraft gas turbine engine criteria are discussed and the problem of identifying and quantifying monitoring systems: An update. Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 121-127. error sources is discussed for the purpose of achieving accurate (SAE 871737) measurements. The AIR concludes with a discussion of special problems encountered in temperature measurement. Author The Turbine Engine Expert Maintenance Advisor System (Texmas) is being developed for use with the T53 engine. Texmas
A89-10618 allows for engine performance measurements, the monitoring of trends in measured parameters, event monitoring, low cycle fatigue, LESSONS LEARNED FROM AN OPERATIONAL ENGINE creep rupture, cyclic fatigue life estimation, and fault isolations. MONITORING SYSTEM AND THEIR CORRELATION WITH The expert systems and the system's computer programs are FUTURE DEVELOPMENTS described, and the research projects involved in the development GARY J. WEBB (South African Airways, Johannesburg, Republic of Texmas are discussed. Also, the implementation and of South Africa) IN: Aircraft gas turbine engine monitoring systems: maintenance of Texmas are examined. R.B.
34 07 AIRCRAFT PROPULSION AND POWER
A89-10622 discussed, including low and high cycle fatigue, thermal fatigue GUIDE TO OIL SYSTEM MONITORING IN AIRCRAFT GAS and creep. Engine life prediction and usage measurement, method TURBINE ENGINES validation, and parts life usage data management are examined. IN: Aircraft gas turbine engine monitoring systems: An update. The advantages of engine life usage monitoring and parts Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. management systems are presented, and several of these systems 129-171. refs are described and evaluated. R.B. (SAE AIR 1828) A technical guide for the selection and use of oil system A89-10626 monitoring devices is presented. The benefits of oil system GUIDE TO LIMITED ENGINE MONITORING SYSTEMS FOR monitoring devices are discussed, including reliabiltiy, availability, AIRCRAFT GAS TURBINE ENGINES cost savings, product assurance and verification, and safety. The IN: Aircraft gas turbine engine monitoring systems: An update. monitoring of oil pressure, temperature, quantity, and filter bypass Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. indicator is considered. Established techniques and experimental 303-323. refs devices for oil debris monitoring and techniques for oil condition (SAE AIR 1873) monitoring are discussed. The general requirements for an oil A limited engine monitoring system which can be used by a system monitoring system are given and considerations for debris flight crew or maintenance staff to monitor the health of gas turbine monitoring are presented, including sensor integration into the oil engines in aircraft is discussed. The monitoring of gas path system and oil system layout for optimum prognostic and cost performance and mechanical parameters, low cycle fatigue effectiveness. R.B. counters, and engine history recorders are considered. The benefits, parameters, and architecture of limited engine monitoring A89-10623 systems are examined. Recommendations for the development of A GUIDE TO AIRCRAFT TURBINE ENGINE VIBRATION these systems include unambiguous readings for cockpit displays, MONITORING SYSTEMS manufacturer input into design specification, minimizing the effects IN: Aircraft gas turbine engine monitoring systems: An update. of manual and automated data acquisition on the trend deltas, Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. algorithms for the reduction of measured data which reflect engine 173-196. refs configuration, and supplying complete comprehensive documen- (SAE AIR 1839) tation for system use to manufacturers. R.B. A technical guide for the selection, installation, and use of airborne engine vibration monitoring systems and their elements A89-10635 is presented, with emphasis on system hardware design RB211 DEVELOPMENTS considerations. Aspects of system design which are evaluated D. J. PICKEREL (Rolls-Royce, PLC, London, England) IN: include signal source, mounting surface, interfaces, mounting point, International Pacific Air and Space Technology Conference, displacement and velocity transducers, accelerometers, signal Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, transmission, cable, shielding, grounding, circuit type, connectors, PA, Society of Automotive Engineers, Inc., 1988, p. 105-118. filtering, output formats, and warning functions. Also, tracking filter (SAE PAPER 872409) based systems are examined. The determination of system and This paper examines briefly the growth prospects of long haul performance requirements and the process of system design civil air transportation in the Pacific Basin and the contribution approval and integration are discussed. R.B. made by the RB211-524 in the Boeing 747. The development of the latest committed version of this engine giving over 60,000 Ib A89-10624 static thrust is described as well as the design of the proposed LESSONS LEARNED FROM DEVELOPMENTAL AND 65,000 ib static thrust RB211-524L powerplant. Finally, the OPERATIONAL TURBINE ENGINE MONITORING SYSTEMS prospects for new Ultra High Bypass Ratio cowled turbofans for IN: Aircraft gas turbine engine monitoring systems: An update. long haul operation in the next century are reviewed. Author Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. 197-257. A89-10636 (SAE AIR 1871B) GAS TURBINE ENGINE DEVELOPMENT PARTNERSHIPS The development and operation of several engine monitoring JIM KORN (General Motors Corp., Allison Gas Turbine Div., systems is discussed, pointing out problems in engine operational Indianapolis, IN) IN: International Pacific Air and Space Technology maintenance which can be addressed in the development of future Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. systems. The systems examined include the Condition Monitoring Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. Program for T700-GE-700, the Inflight Engine Condition Monitoring 119-132. System, the Advanced Diagnostic Engine Monitoring System, F/A (SAE PAPER 872410) Inflight Engine Condition Monitoring System, UK Military Engine The structure and progress of the followig major aircraft gas Usage, Condition, and Maintenance Systems, and an operational turbine development programs are examined: (1) the T406-AD-400 engine monitoring system applied to an international airline. turboshaft for the V-22 Osprey; (2) the T800-LHT-800 turboshaft Recommendations for future developments include the engine for LHX; and (3) the Model 578 propfan propulsion system transmission of data from out-stations or inflight to allow effective for transport aircraft. All of these programs contain partnership trouble-shooting away from base, a data base system where data agreements that allow extensive development participation and all is dumped into the airline engineering computer allowing users to rely on a blend of developed hardware with infusion of modem develop their own application programs, and the presentation of technology. It is concluded that the development of gas turbine engine monitoring data on display screens, minimizing paper engines can benefit from the synergistic aspects gained by output. R.B. partnership agreements. B.J.
A89-10625 A89-10637" National Aeronautics and Space Administration. GUIDE TO LIFE USAGE MONITORING AND PARTS Langley Research Center, Hampton, Va. MANAGEMENT FOR AIRCRAFT GAS TURBINE ENGINES PROPULSION-AIRFRAME INTEGRATION FOR COMMERCIAL IN: Aircraft gas turbine engine monitoring systems: An update. AND MILITARY AIRCRAFT Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. WILLIAM P. HENDERSON (NASA, Langley Research Center, 259-301. Hampton, VA) IN: International Pacific Air and Space Technology (SAE AIR 1872) Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Approaches to engine life usage monitoring and parts Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. management are reviewed. Control requirements for these systems 133-144. refs are summarized and failure causes of life-limited parts are (SAE PAPER 872411)
35 07 AIRCRAFT PROPULSION AND POWER
A significant level of research is ongoing at NASA's Langley ZHENGMU WANG (Shenyang Aeroengine Co., People's Republic Research Center on integrating the propulsion system with the of China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, aircraft. This program has included nacelle/pylon/wing integration April 1988, p. 178-180, 192. In Chinese, with abstract in English. for turbofan transports, propeller/nacelle/wing integration for An approach to establishing the optimum regulation law of the turboprop transports, and nozzle/afterbody/empennage integration variable vane for a turbojet engine is presented. The stable for high performance aircraft. The studies included in this paper operating boundary of the engine can be determined according to focus more specifically on pylon shaping and nacelle location matching with effective flight conditions. Author studies for turbofan transports, nacelle and wing contouring and propeller location effects for turboprop transports, and nozzle A89-11051# shaping and empennage effects for high performance aircraft. The APPLICATION OF END-BEND BLADE FOR ENHANCING studies were primarily conducted in NASA Langley's 16-Foot SURGE MARGIN Transonic Tunnel at Mach numbers up to 1.20. Some higher Mach YUNJIN CAI, YULING ZHONG, and LUHONG QIAN (Shenyang number data obtained at NASA's Lewis Research Center is also Aeroengine Co., People's Republic of China) Journal of Aerospace included. Author Power (ISSN 1000-8055), vol. 3, July 1988, p. 215-218, 281. In Chinese, with abstract in English. A89-11026# The blade end-bend technique is applied to the first and second A DYNAMIC CHARACTERISTIC ANALYSIS OF A BLADED stators of the HP compressor of a twin-spool engine to ameliorate DISK ASSEMBLY the flow on the second and third rotors. The tests of the modified DEPING GAO, YISONG ZHANG, and LIYAN YI (Nanjing engine show that its surge margin and efficiency are enhanced Aeronautical Institute, People's Republic of China) Journal of by 7.3 and 4.1 percent, respectively, but the flow and pressure Aerospace Power (ISSN 1000-8055), vol. 3, April 1988, p. 97-100, ratio vary only a little. The flight tests prove that the shutdown of 183. In Chinese, with abstract in English. refs the engine which occurred in flight has been eliminated, so that The dynamic characteristics of a bladed disk assembly are the engine can operate reliably and stably within the overall flight calculated by means of sector elements of thick plates and wave envelope. The performance of the engine and the aircraft has propagation technique of periodical structure. The method saves been improved significantly. Author greatly the computing time and the storage of computer. The vibration characteristics between the bladed disk assembly and A89-11052# the single blade or disk are compared and the influences of the APPROACH TO BLADE END-BEND MECHANISM variation of geometric parameters of the bladed disk assembly on LIXI HUANG, XINGLU WEI, and ZEYAN PENG (Beijing Institute its vibration characteristics are considered. Some conclusions are of Aeronautics and Astronautics, People's Republic of China) drawn which will play an important part in further research on the Journal of Aerospace Power (ISSN 1000-8055), vol. 3, July 1988, vibration control of an aeroengine. A bladed disk assembly of an p. 219-222, 281, 282. In Chinese, with abstract in English. actual compressor is analyzed in this paper, and the results Blade end-bend is a new technique to improve the performance obtained coincide with the experimental data. Therefore, the of compressors. A comprehensive study of two multistage presented method is applicable to practical engineering. Author compressors has been completed with numerical calculation, theoretical analysis, and experimental investigation. It is shown A89-11034# that the end-bend causes redistribution of the whole flowfield, REDUCTION OF EJECTOR NOISE WITH MULTIHOLE NOZZLE and that the changes of characteristics in the main flow region RENSONG FANG and RONGXUE ZHANG (Nanjing Aeronautics may be a factor to improving the engine performance. A comparative study of several end-bend patterns shows that the Institute, People's Republic of China) Journal of Aerospace Power character of redistribution differs among them. It is important to (ISSN 1000-8055), vol. 3, April 1988, p. 145-148, 188. In Chinese, with abstract in English. choose the end-bend pattern suitable for the specific compressor. Author In order to reduce the noise, an ejector with a multihole nozzle is proposed as the primary nozzle, and its design method is A89-11054# presented. For comparison of the aerodynamic performance and the noise characteristics with those of conventional ones in UNSTEADY LOADING NOISE OF COUNTER-ROTATING PROPELLER subsonic and supersonic ejector systems, the sound power levels and the primary and secondary mass flow rates of the ejectors XIOAFENG SUN, ZONGAN HU, and SHENG ZHOU (Beijing were measured, and the static thrusts of the ejectors were Institute of Aeronautics and Astronautics, People's Republic of estimated, based on the measured mass flow rates. The shroud China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, length of the ejector system tested was altered in the experiments July 1988, p. 227-230, 283. In Chinese, with abstract in English. refs so as to study the effect of this parameter on noise and thrust. The experimental results show that the multihole nozzle ejector The unsteady loading noise generated by interaction of a front system not only reduces noise considerably but also gains better rotor wake with an aft rotor in a counterrotating (CR) propeller is aerodynamic performance due to a shorter shroud. The shorter analyzed, and the noise radiation formulas are derived. Numerical the shroud, the more noise reduction and the greater the static predictions of noise for a real CR propeller are completed and thrust increment that can be achieved. Author compared with experimental data. It is concluded that the sound pressure level (SPL) in the axial direction of the rotor is fully determined by the component of unsteady loading noise, but in A89-11040# rotor plane the main contribution to SPL is the component of A JET THRUST MEASUREMENT METHOD WITH GAS steady loading noise, and the effect of the unsteady noise is COMPOSITION ANALYSIS limited to the range of higher harmonics in this case. Author SHIYI PENG (Nanhua Power Plant Research Institute, People's Republic of China) Journal of Aerospace Power (ISSN 1000-8055), A89-11055# vol. 3, April 1988, p. 167, 168, 191. In Chinese, with abstract in PROPFAN DESIGN BY PROPELLER-NACELLE INTERACTION English. ANALYSIS A new method is proposed which uses composition analysis NIANGUO ZHU, MAOZHANG CHEN, and DAOZHI LIU (Beijing of gas from engine for determining jet thrust at a given fuel Institute of Aeronautics and Astronautics, People's Republic of consumption. This method has been verified in JT15D engine testing, and the thrust error is about 6.9 percent. Author China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, July 1988, p. 231-234, 282. In Chinese, with abstract in English. refs A89-11044# A propeller-nacelle interaction analysis has been developed in ESTABLISHMENT OF VARIABLE VANE REGULATION LAW this paper as a kind of lifting-line analysis. It represents the blades
36 07 AIRCRAFT PROPULSION AND POWER
bycurvedliftinglines,takingintoconsiderationthebladesweep continuing development of the technique and its constituent andtheeffect of the nacelle on the propfan flowfield. The wake aerodynamic and structural dynamic components. As shown in model assumes that the vortex filaments occur along stream these two volumes and in the several citations to advanced surfaces. Some corrections have been made to the transonic analyses, current practice has gone well beyond the relatively portion of the blade and the large solid cascade portion at hub. simplistic view of the early paper. The aerodynamic input now Comparison of the results of the design and analysis with those encompasses multiblade systems subjected to compressible flows, obtained previously show that the method is feasible and effective. and structures are modeled to include nonlinearities and mistuning. Aspects of its improvement are also discussed. Author Nevertheless, the paper has served its purpose well. In its original form it set the stage for the continual improvement of engine A89,-11074 flutter prediction methods, and in this manual it provides the reader EXPERIENCE WITH THE DEVELOPMENT OF TURBOPROP with a vehicle for coordinating the separate disciplines which, ENGINES [PERSPEKTIVY DALSlHO VYVOJE together, represent the modern approach to flutter prediction of TURBOVRTULOVYCH MOTORU] turbomachinery blade rows. Author OLDRICH BUNATA Zpravodaj VZLU (ISSN 0044-5355), no. 3, 1988, p. 121-129. In Czech. refs N89-10013# Massachusetts Inst. of Tech., Cambridge. Gas Data on the performance and operational characteristics of Turbine Lab. various turboprop engines are presented. The pros and cons of AEROELASTIC FORMULATION FOR TUNED AND MISTUNED various concepts are examined, and data on the improvement of ROTORS the main parameters of the working cycle and on engine costs EDWARD F. CRAWLEY In AGARD, AGARD Manual on are presented. Particular consideration is given to the advantages Aeroelasticity in Axial-Flow Turbo Machines. Volume 2: Structural and disadvantages of two-stage radial and axial-radial Dynamics and Aeroelasticity 24 p Jun. 1988 compressors. B.J. Avail: NTIS HC A12/MF A01 The topics to be addressed are: the formulation of the A89-11075 aeroelastic problem, including a summary of the relations necessary CONTROL OF THE LOW-CYCLE SERVICE LIFE OF THE to transform various diverse structural and aerodynamic models PRIMARY COMPONENTS OF AIRCRAFT TURBINE ENGINES to a consistent notation; a brief review of the solution techniques ACCORDING TO THE DAMAGE-TOLERANCE CONCEPT applicable; the trends in aeroelastic stability for tuned rotors; and [RIZENI NIZKOCYKLOVE ZlVOTNOSTI PRIMARNICH CASTI the effects of mistuning on stability. Author LETECKYCH TURBINOVYCH MOTORU PODLE KONCEPCE DT] N89-10014# Pratt and Whitney Aircraft, East Hartford, Conn. JIRI STATECNY Zpravodaj VZLU (ISSN 0044-5355), no. 5, 1988, FAN FLUTTER TEST p. 225-234. In Czech. refs HANS STARGARDTER In AGARD, AGARD Manual on The application of the damage-tolerance concept presupposes Aeroelasticity in Axial-Flow Turbo Machines. Volume 2: Structural the close cooperation between the R&D base, the manufacturer, Dynamics and Aeroelasticity 35 p Jun. 1988 the user, and the overhaul shops. This paper examines the Avail: NTIS HC A12/MF A01 establishment of purposeful coordinated activities within this area. The objective is to describe an aeroelastic investigation of fan A strategy is proposed for the Aircraft Research and Test Institute flutter. Discussion includes test procedures for flutter evaluation, 1o ensure the appropriate methodological provisions necessary for data acquisition and reduction, safety, and instrumentation. Some the application of the damage*tolerance concept. B.J. data contents are included, but are not the primary concern. Initially, a complete sequence of preparation, testing, and analysis of an A89-12307" Florida Univ., Gainesville. ideal fan flutter test is presented. This is followed by identification CALCULATIONS OF THE UNSTEADY, THREE-DIMENSIONAL of dangerous blade vibrations, a case history of a NASA/Pratt FLOW FIELD INSIDE A MOTORED WANKEL ENGINE and Whitney Subsonic/Transonic Flutter Study, and a discussion ERLENDUR STEtNTHORSSON, TOM I.-P. SHIH (Florida, and analysis of the program results. Lastly, a summary relating University, Gainesville), HAROLD J. SCHOCK, JR. (Michigan State this test to the overall discussion of fan flutter testing is presented. University, East Lansing), and JAMES STEGEMAN (NASA, Lewis It will be noted that many of the steps in the ideal test situation Research Center, Cleveland, OH) SAE, International Congress were omitted in the actual case history. Most of these differences and Exposition, Detroit, MI, Feb. 29-Mar. 4, 1988. 31 p. refs are in the test preparation area because the case history used a (Contract NAG3°363) previously tested design in which much of the preliminary work (SAE PAPER 880625) and safety screening was already accomplished. Author A computer program (referred to as UF-LRC-3D) was developed for studying the unsteady, three-dimensional flow field inside the N89-10015# Jeffers (James D., Ill), Tampa, Fla. combustion chambers of motored Wankel engines as a function AEROELASTIC THERMAL EFFECTS of engine design and operating parameters. This paper presents JAMES D. JEFFERS, III In AGARD, AGARD Manual on the details of the governing equations and the numerical method Aeroelasticity in Axial-Flow Turbo Machines. Volume 2: Structural used by UF-LRC-3D. Also presented are numerical solutions Dynamics and Aeroelasticity 6 p Jun. 1988 generated by UF-LRC*3D showing the velocity field inside a Avail: NTIS HC A12/MF A01 motored Wankel engine, the mixing of nonhomogeneous fuel-air The adverse effect of increasing temperature on the stability mixtures that enter through the intake port, and the mixing that of turbomachinery airfoils was long recognized but remains today takes place when a gaseous fuel is injected into the combustion one that is not fully understood. The quantitative effect on the chamber during compression. Author reduced frequency parameter, k = omega c/V, which was experimentally and analytically shown to be one of the most N89-10012# United Technologies Research Center, East Hartford, influential stability parameters, is readily calculated. The effects of Conn. increasing temperature on the parameters that comprise reduced AEROELASTIC COUPLING: AN ELEMENTARY APPROACH frequency are well known. Unfortunately, the resulting effect on FRANKLIN O. CARTA In AGARD, AGARD Manual on aeroelastic stability, particularly for stall flutter, is not. This inability Aeroelasticity in Axial-Flow Turbo Machines. Volume 2: Structural to completely assess thermal effects, among others, was Dynamics and Aeroelasticity 16 p Jun. 1988 dramatically underscored by an occurrence of subsonic stall flutter Avail: NTIS HC A12/MF A01 in the first stage fan rotor of the F100 turbofan engine early in It was shown in the original 1967 paper that the energy method, the development program. The severity of the problem prompted using unsteady isolated airfoil theory, and applied to actual an intensive experimental test program and analysis to first multiblade rotors, yielded results that were remarkably accurate. determine a solution and, further, to assess the design techniques This fortuitous agreement was sufficiently encouraging to foster a used to avoid the problem. As a result, a decade of extensive
37 07 AIRCRAFT PROPULSION AND POWER
analytical and experimental research was conducted at the of Queensland implied that it was no longer necessary to focus Government Products Division of Pratt and Whitney Aircraft, the the work of the research group about an annual test series United Technologies Research Center, and the NASA Lewis conducted in the T3 shock tunnel in Canberra. Therefore, it has Research Center. The following is a summary of some of the been possible to organize a group for work to proceed along findings of these investigations. Author lines such that particular personnel are associated with particular project areas. The format of this report consists of a series of N89-10043"# National Aeronautics and Space Administration. reports on specific project areas, with a brief general introduction Lewis Research Center, Cleveland, Ohio. commenting on each report. The introduction is structured by VIBRATION, PERFORMANCE, FLUTTER AND FORCED project areas, with the title of the relevant report stated under the RESPONSE CHARACTERISTICS OF A LARGE-SCALE project area heading. The reports themselves follow in the order PROPFAN AND ITS AEROELASTIC MODEL of the project area headings. Author RICHARD AUGUST (Sverdrup Technology, Inc., Cleveland, Ohio.) and KRISHNA RAO V. KAZA 1988 28 p Presented at the 24th Joint Propulsion Conference, Boston, Mass., 11-13 Jul. 1988; sponsored by AIAA, ASME, SAE and ASEE N89-10892# Naval Air Propulsion Test Center, Trenton, N.J. (NASA-TM-101322; E-4260; NAS 1.15:101322; AIAA-88-3155) STATISTICS ON AIRCRAFT GAS TURBINE ENGINE ROTOR Avail: NTIS HC A03/MF A01 CSCL 21E FAILURES THAT OCCURRED IN US COMMERCIAL AVIATION An investigation of the vibration, performance, flutter, and forced DURING 1982 Final Report response of the large-scale propfan, SR7L, and its aeroelastic R. A. DELUCIA and J. T. SALVINO Jul. 1988 24 p model, SR7A, has been performed by applying available structural (Contract DOT-FA71NA-AP-98) and aeroelastic analytical codes and then correlating measured (DOT/FAA/CT-88/23) Avail: NTIS HC A03/MF A01 and calculated results. Finite element models of the blades were Statistics are presented relating to gas turbine engine rotor used to obtain modal frequencies, displacements, stresses and failures which occurred during 1982 in U.S. commercial aviation strains. These values were then used in conjunction with a 3-D, service use. One-hundred and sixty-one rotor failures occurred in unsteady, lifting surface aerodynamic theory for the subsequent 1982. Rotor fragments were generated in 88 of the failures and, aeroelastic analyses of the blades. The agreement between of these, 16 were uncontained. The predominant failure involved measured and calculated frequencies and mode shapes for both blade fragments. Seven disk failures occurred and all were models is very good. Calculated power coefficients correlate well uncontained. Seventy percent of the 161 failures occurred during with those measured for low advance ratios. Flutter results show the takeoff and climb stages of flight. This service data analysis that both propfans are stable at their respective design points. is prepared on a calendar year basis and published yearly. The There is also good agreement between calculated and measured data support flight safety analysis, proposed regulatory actions, blade vibratory strains due to excitation resulting from yawed flow certification standards, and cost benefit analyses. Author for the SR7A propfan. The similarity of structural and aeroelastic results show that the SR7A propfan simulates the SR7L characteristics. Author N89-10894# Rohr Industries, Inc., Chula Vista, Calif. N89-10044# Air Force Wright Aeronautical Labs., DE-ICING OF AIRCRAFT TURBINE ENGINE INLETS Final Wright-Patterson AFB, Ohio. Report A COMPARATIVE EVALUATION OF RPD (ROTARY PARTICLE H. A. ROSENTHAL, D. O. NELEPOVITZ, and H. M. ROCKHOLT DEPOSITOR) AND FERROGRAPHIC DIAGNOSTIC METHODS Jun. 1988 68 p FOR TURBINE ENGINE LUBRICANT SAMPLES Final Report, (Contract DTFA03-86-C-0050) 12 May - 30 Sep. 1987 (DOT/FAA/CT-87/37) Avail: NTIS HC A04/MF A01 ROBERT L. WRIGHT Mar. 1988 28 p The results of an FAA investigation to determine the effects of (AD-A196207; AFWAL-TR-88-2020) Avail: NTIS HC A03/MF using de-icing, as opposed to anti-icing, in aircraft turbine engine A01 CSCL 11H inlets are given. A literature search was conducted. Ice protection A Rotary Particle Depositor (RPD) was evaluated and compared equipment technology was assessed. The icing/de-icing process, to analytical (AF) and direct reading (DR) ferrographs to ascertain de-ice system operation and performance, ice detector if the RPD is better suited for analysis of wear debris in turbine characteristics, and a method for determining the effects of the engine lubricant samples than the AF and DR. Experimentally, de-icing process on the turbine engine and its associated induction sieved iron particles were added to synthetic turbine engine system are discussed. Author lubricants at various concentrations and analyzed by RPD and ferrographic methods and compared. Also, lubricant samples containing a fine test dust were analyzed by RPD and AF to determine the effectiveness of the RPD's centripetal acceleration and the AF's gravity flow in eliminating non-ferrous contamination from the sample. Finally, actual lubricant samples from a turbine engine simulator were analyzed by RPD and ferrographic methods O8 and compared. For lubricant samples with relatively small amounts of non-ferrous contamination or samples where non-ferrous particles are important in machine health condition assessment, AIRCRAFT STABILITY AND CONTROL the AF and DR ferrographs are equal or superior to RPD for lubricant analyses. GRA Includes aircraft handling qualities; piloting; flight controls; and autopilots. N89-10045"# Queensland Univ., St. Lucia (Australia). Dept. of M.E. SHOCK TUNNEL STUDIES OF SCRAMJET PHENOMENA Final A89-10103"# National Aeronautics and Space Administration. Report Langley Research Center, Hampton, Va. R. G. MORGAN, A. PAULL, R. J. STALKER, P. JACOBS, N. EXPERIMENTAL STUDY OF EFFECTS OF FOREBODY MORRIS, I. STRINGER, andC. BRESCIANINI Sep. 1988 16p GEOMETRY ON HIGH ANGLE-OF-ATTACK STABILITY (Contract NAGW-674) JAY M. BRANDON and LUAT T. NGUYEN (NASA, Langley (NASA-CR-181721; NAS 1.26:181721) Avail: NTIS HCA03/MF Research Center, Hampton, VA) Journal of Aircraft (ISSN A01 CSCL 21E 0021-8669), vol. 25, July 1988, p. 591-597. Previously cited in Commissioning of the new T4 shock tunnel at the University issue 07, p. 849, Accession no. A86-19818. refs
38 08 AIRCRAFT STABILITY AND CONTROL
A89-10515 a high-speed high-altitude jet-powered pilotless TA which is also COMPARISON OF LONGITUDINALLY STABIMZED BEHAVIOR capable of low-altitude flight. The development of the control of IN VERTICAL TURBULENCE BETWEEN A MODERN CANARD the level of automation, flight controller skills, the apportionment CONFIGURATION AND A CONVENTIONAL AIRCRAFT of control, and tracking/navigation is described. Testing confirmed [VERGLEICH DES LAENGSSTABIMTAETSVERHALTENS IN that with the introduction of automatic control techniques fewer VERTIKALER TURBUI FNZ ZWlSCHEN EINEM MODERNEN operators with lesser skill levels can be used for the TA control. ENTENE_URF UND EINEM KONVENTIONELLEN Digital autopilot systems are enabling TA to operate autonomously, FLUGZEUG| with providing a diminishing role for the GCS. I.S. J. FECHER (Gyroflug Ingenieurgesellschaft mbH, Baden-Baden, Federal Republic of Germany) and O. BARTSCH (Messerschmitt-Boelkow-Blohm, Munich, Federal Republic of A89-12402# Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, THE NOE PILOT'S ASSOCIATE - A JOB DESCRIPTION Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, NICK LAPPOS (United Technologies Corp., Sikorsky Aircraft Div., Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 229-234. Stratford, CT) IN- Automation applications for rotorcraft; In German. Proceedings of the National Specialists' Meeting, Atlanta, GA, (DGLR PAPER 87-078) Apr. 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, 8 p. The longitudinal stability behavior in vertical turbulence for The increasing demands of NOE military helicopter operations aircraft with conventional and canard configurations is compared. entail reduced margins-of-error, reduced knowledge of the overall A mathematical model of the canard characteristics is developed. situation, reduced visual and electrooptical event horizons, and The phygoid and angle of attack of the two aircraft types are reduced capability for tactical communication and control. Attention studied, and the frequency curves, power density spectra, and is presently given to emerging possibilities for the automation of effective values are obtained. C.D. helicopter crew burdens in NOE operations, and the consequent expansion of capabilities expected. AI techniques are applied to A89-10519 communications and monitoring tasks, subsystem diagnostics and ASPECTS OF THE CONTROL AND STABILIZATION OF healing, the integration of system controls, and tactical planning SUPERSONIC COMMERCIAL AIRCRAFT |ASPEKTE DER and orientation. O.C. STEUERUNG UND STABIMSlERUNG VON UEBERSCHALLVERKEHRSFLUGZEUGEN | A89-12417# P. MANGOLD and W. ALLES (Dornier GmbH, Friedrichshafen, DIGITAL AUTOPILOTS FOR ROTARY WINGED UNMANNED Federal Republic of Germany) IN: Yearbook 1987 l; DGLR, AERIAL VEHICLES Annual Meeting, Berlin, Federal Republic of Germany, Oct. 5-7, ROBERT C. MICHELSON (Georgia Institute of Technology, 1987, Reports. Bonn, Deutsche Gesellschaft fuer Luft- und Atlanta) IN: Automation applications for rotorcraft; Proceedings Raumfahrt, 1987, p. 264-274. In German. of the National Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. (DGLR PAPER 87-122) Alexandria VA, American Helicopter Society, 1988, 6 p. Recent technological advances have revived the notion of Future rotary-wing RPVs will require high-to-total-authority supersonic and hypersonic aircraft in commerical aviation. For stability augmentation systems, which will require digital aircraft with slender delta wings, questions of control and implementations capable of supplanting both the piloting (inner stabilization are highly significant. In this paper, the demands placed loop control) and navigator (outer loop control) functions. Such on the stabilization system of such an aircraft are considered, digital autopilots are presently noted to yield greater performance and related issues regarding automated flight are examined. The flexibility under a range of anticipated flight regimes, and will be relevant design and realization considerations are addressed. capable of accommodating more complex tasks, as well as of C.D. exhibiting tolerance to high-EMI environments. It is also projected that digital autopilots will be able to sustain substantial physical A89-10668 damage and to perform 'self-healing' to regain full operational THE STUDY OF THE GLOBAL STABILITY OF HIGH effectiveness. O.C. PERFORMANCE AIRCRAFT AT HIGH ANGLES-OF-ATTACK HAO GAO and ZHI-QIANG ZHOU (Northwestern Polytechnical A89-12555# University, Xian, People's Republic of China) IN: International CONTROL OF AUTOROTATIONAL CHARACTERISTICS OF Pacific Air and Space Technology Conference, Melbourne, LIGHT-AIRPLANE FUSELAGES Australia, Nov. 13-17, 1987, Proceedings. Warrendale, PA, Society B. N. PAMADI (Indian Institute of Technology, Bombay, India), V. of Automotive Engineers, Inc., 1988, p. 473-485. refs JAMBUNATHAN, and A. RAHMAN Journal of Aircraft (ISSN (SAE PAPER 872456) 0021-8669), vol. 25, Aug. 1988, p. 695-701. Previously cited in A new approach based on the qualitative theory of ordinary issue 08, p. 1052, Accession no. A87-22574. refs differential equations, bifurcation analysis, and catastrophe theory is proposed to study the global stability of high-performance aircraft A89-12556"# California Univ., Davis. at high angles of attack. The relationship between the stability BOUNDARY-LAYER TRANSITION EFFECTS ON AIRPLANE criteria commonly used in aircraft designs ariel the eigenvalues of STABILITY AND CONTROL linearized matrices at the equilibrium points is studied. Important C. P. VAN DAM (California, University, Davis) and B. J. HOLMES high angle-of-attack flight phenomena such as jump hysteresis, (NASA, Langley Research Center, Hampton, VA) Journal of wing rock, and spin are analyzed using the present approach. Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. 702-709. K.K. Previously cited in issue 23, p. 3415, Accession no. A86-47708. refs A89-10669 MODERN TECHNIQUES FOR THE CONTROL OF RPV'S N89-10046"# Manudyne Systems, Inc., Los Altos, Calif. CHARLES MULHAUSER and JOHN WHITE (Aerospace HELICOPTER ROLL CONTROL EFFECTIVENESS CRITERIA Technologies of Australia, Australia) IN: international Pacific Air PROGRAM SUMMARY Final Contractor Report, Jul. 1983 - and Space Technology Conference, Melbourne, Australia, Nov. Jul. 1987 13-17, 1987, Proceedings. Warrendale, PA, Society of Automotive ROBERT K. HEFFLEY, SIMON M. BOURNE, and MARC A. Engineers, Inc., 1988, p. 487-497. MNICH Apr. 1988 103 p Prepared for Army Research and (SAE PAPER 872457) Technology Labs., Moffett Field, Calif. This paper discusses the techniques used in the control of (Contract NAS2-11665) remotely piloted mid-scale target aircrafts (TAs), with particular (NASA-CR-177477; NAS 1.26:177477; USAAVSCOM-TR-87-A-13) attention given to the control features of the Jindivik TA, which is Avail: NTIS HC A06/MF A01 CSCL 01C
39 08 AIRCRAFTSTABILITYANDCONTROL
A study of helicopter roll control effectiveness is summarized beneficially change helicopter tail boom air loads was suggested for the purpose of defining military helicopter handling qualities in the United States in 1975. The anticipated benefits were a requirements. The study is based on an analysis of pilot-in-the-loop change of tail boom loads to reduce required tail rotor thrust and task performance of several basic maneuvers. This is extended power and improve directional control. High tail boom air loads by a series of piloted simulations using the NASA Ames Vertical experienced by the YAH-64 and described in 1978 led to a wind Motion Simulator and selected flight data. The main results cover tunnel investigation of the usefullness of strakes in altering such roll control power and short-term response characteristics. In loads on the AH-64, UH-60, and UH-1 helicopters. The wind tunnel general the handling qualities requirements recommended are set tests of 2-D cross sections of the tail boom of each demonstrated in conjunction with desired levels of flight task and maneuver that a strake or strakes would be effective. Several limited test response which can be directly observed in actual flight. An programs with the U.S. Army's OH-58A, AH-64, and UH-60A were important aspect of this, however, is that vehicle handling qualities conducted which showed the effects of strakes were modest for need to be set with regard to some quantitative aspect of mission those helicopters. The most recent flight test program, with a Bell performance. Specific examples of how this can be accomplished 204B, disclosed that for the 204B the tail boom strake or strakes include a lateral unmask/remask maneuver in the presence of a would provide more than a modest improvement in directional threat and an air tracking maneuver which recognizes the kill control and reduction in tail rotor power. Author probability enhancement connected with decreasing the range to the target. Conclusions and recommendations address not only the handling qualities recommendations, but also the general use N89-10832# Messerschmitt-Boelkow-BIohm G.m.b.H., Munich of flight simulators and the' dependence of mission performance (West Germany). Aircraft Div. on handling qualities. Author COMPUTING SYSTEM CONFIGURATION FOR FIGHTER AIRCRAFT FLIGHT CONTROL SYSTEMS
N89-10047# National Aerospace Lab., Tokyo (Japan). H. J. KAUL, H. LUEERS, and J. RAUCH In AGARD, Computing FUNCTIONAL MOCK-UP TESTS OF THE FLIGHT CONTROL Systems Configuration for Highly Integrated Guidance Control SYSTEM OF THE NAL QSTOL RESEARCH AIRCRAFT: Systems 32 p Jun. 1988 PLANNING AND MECHANICAL SYSTEM TEST Avail: NTIS HC A08/MF A01 Sep. 1987 56 p In JAPANESE; ENGLISH summary Flight Control Systems (FCS) for present and future Fighter (NAL-TR-944; ISSN-0389-4010) Avail: NTIS HC A04/MF A01 Aircraft developments are based on three basic technologies, The control system of the National Aerospace Laboratory CCV-ACT-digital signal processing. These technologies have Quiet-STOL Research Aircraft has a mechanical control system opened a new degree of freedom for optimizing overall weapon and a triplex digital Stability and Control Augmentation System system performance by extending the requirements to be (SCAS). The mechanical system is responsible for the safety control implemented by the FCS. The computing subsystem of the FCS system, while the digital SCAS system was to be evaluated through is the key element of the FCS by which this performance experiments. Functional mock-up tests were carried out to check optimization can be achieved. Digital FCS for fighter aircraft in safety and performance of the total control system using actual service or under development exhibit a basically common system component hardware and simulating aerodynamic and architecture (static parallel redundancy, centralized heavily mechanical environmental conditions. The mechanical system burdened computing subsystem) which has continuously evolved dynamics test and the total plan for the functional mock-up test since the early days of CCV and ACT activities. The objectives of are described as the fundamental process to ensure minimum the paper are to relate this classical architecture to the advancing safety requirements of the system component matching. The static requirements and the new emerging technologies and to analyze and dynamic characteristics of the mechanical control system its potentials for future developments. Author showed good agreement with the specifications of Japanese Airworthiness Standards (equivalent to FAR25) and MIL. Author N89-10895"# Princeton Univ., N. J. Dept. of Mechanical and Aerospace Engineering. N89-10058"# Lockheed-Georgia Co., Marietta. A STUDY OF HELICOPTER STABILITY AND CONTROL OUADRUPLEX DIGITAL FLIGHT CONTROL SYSTEM INCLUDING BLADE DYNAMICS Final Report, Jul. 1983 - Sep. ASSESSMENT Final Report 1987 D. B. MULCARE, L. E DOWNING, and M. K. SMITH Jul. 1988 XIN ZHAO and H. C. CURTISS, JR. Oct. 1988 169 p 68 p (Contract NAG2-244) (Contract NAS2-11853) (NASA-CR-183245; NAS 1.26:183245) Avail: NTIS HC A08/MF (NASA-CR-182741 ; NAS 1.26:182741 ; DOT/FAA/CT-86/30-REV) A01 CSCL 01C Avail: NTIS HC A04/MF A01 CSCL 01C A linearized model of rotorcraft dynamics has been developed Described are the development and validation of a double through the use of symbolic automatic equation generating fail-operational digital flight control system architecture for critical techniques. The dynamic model has been formulated in a unique pitch axis functions. Architectural tradeoffs are assessed, system way such that it can be used to analyze a variety of rotor/body simulator modifications are described, and demonstration testing coupling problems including a rotor mounted on a flexible shaft results are critiqued. Assessment tools and their application are with a number of modes as well as free-flight stability and control also illustrated. Ultimately, the vital role of system simulation, characteristics. Direct comparison of the time response to tailored to digital mechanization attributes, is shown to be essential longitudinal, lateral and directional control inputs at various trim to validating the airworthiness of full-time critical functions such conditions shows that the linear model yields good to very good as augmented fly-by-wire systems for relaxed static stability correlation with flight test. In particular it is shown that a dynamic airplanes. Author inflow model is essential to obtain good time response correlation, especially for the hover trim condition. It also is shown that the N89-10059"# National Aeronautics and Space Administration. main rotor wake interaction with the tail rotor and fixed tail surfaces Langley Research Center, Hampton, Va. is a significant contributor to the response at translational flight DEVELOPMENT IN HELICOPTER TAIL BOOM STRAKE trim conditions. A relatively simple model for the downwash and APPLICATIONS IN THE US sidewash at the tail surfaces based on flat vortex wake theory is JOHN C. WILSON, HENRY L. KELLEY, CYNTHIA C. DONAHUE, shown to produce good agreement. Then, the influence of rotor and KENNETH R. YENNI Oct. 1988 19 p Prepared for flap and lag dynamics on automatic control systems feedback presentation at the International Conference on Helicopter Handling gain limitations is investigated with the model. It is shown that the Qualities and Control, London, England, 15-17 Nov. 1988 blade dynamics, especially lagging dynamics, can severly limit the (NASA-TM-101496; NAS 1.15:101496; AVSCOM-TM-88-B-014) useable values of the feedback gain for simple feedback control Avail: NTIS HC A03/MF A01 CSCL 01C and that multivariable optimal control theory is a powerful tool to The use of a strake or spoiler on a helicopter tail boom to design high gain augmentation control system. The
4O 09 RESEARCH AND SUPPORT FACILITIES (AIR)
frequency-shapedoptimal control design can offer much better (NASA, Ames Research Center, Moffett Field, CA) AIAA, Applied flight dynamic characteristics and a stable margin for the feedback Aerodynamics Conference, 6th, Williamsburg, VA, June 6-8, 1988. system without need to model the lagging dynamics. Author 10 p. refs (AIAA PAPER 88-2528) N89-10896# George Washington Univ., Washington, D.C. This paper describes the inlet design requirements of the Graduate School of Engineering and Applied Science. National Full-Scale Aerodynamic Complex (NFAC), a closed-loop INVESTIGATION OF THE TUMBLING PHENOMENON USING 4-by-80 foot wind tunnel and indraft 80-by-120 foot wind tunnel. COMPUTER SIMULATION M.S. Thesis The requirements are based upon desired test section flow quality, SCOTT POWELL FEARS Sep. 1985 138 p atmospheric wind isolation, and noise attenuation. An aerodynamic Avail: NTIS HC A07/MF A01 design study of the inlet treatment is described along with the A single degree-of-freedom free-to-pitch simulation of the X-29A analysis method and the small-scale testing program used. was developed and used to investigate the tumble susceptibility Measurements taken in the full-scale facility are presented, and of the X-29A with its controls fixed. Validation of the ability of the the flow quality is summarized. The results are compared with aerodynamic models used in this simulation to accurately describe theoretical predictions and small-scale model results. C.D. tumbling was accomplished by comparing the simulation results to dynamic wind-tunnel test results. The wind-tunnel and simulation A89-12560"# Stanford Univ., Calif. results showed a strong tendency to tumble in the nose-down CONVERGENCE SCHEMES FOR AN ADAPTIVE-WALL WIND direction for the controls-fixed X-29A. A three degree-of-freedom TUNNEL piloted simulation of the X-29A using similar aerodynamic models Z. Z. CELIK (Stanford University, CA) and S. BODAPATI (U.S. was developed and used to test the tumble susceptibility of the Naval Postgraduate School, Monterey, CA) Journal of Aircraft X-29A with its controls active. These tests showed that high initial (ISSN 0021-8669), vol. 25, Aug. 1988, p. 733-739. Previously cited pitch rates are required for tumble entry from trimmed flight. Finally, in issue 18, p. 2818, Accession no. A87-42454. refs a parametric study of the aerodynamic characteristics that affect (Contract NCC2-225) tumble susceptibility was conducted using the single degree-of-freedom simulation and generic aerodynamic data N89-10060"# National Aeronautics and Space Administration. representing the X-29A configuration and a conventional configuration at various static margins. It was shown that an Langley Research Center, Hampton, Va. HIGHLIGHTS OF EXPERIENCE WITH A FLEXIBLE WALLED ordinate direction shift in the static pitching-moment data, TEST SECTION IN THE NASA LANGLEY 0.3-METER differences in the pitching-moment magnitudes or alpha ranges of TRANSONIC CRYOGENIC TUNNEL the positive and negative regions of the static pitching-moment data, reduced static margins, reduced stable pitch damping STEPHEN W. D. WOLF (Vigyan Research Associates, Inc., Hampton, Va.) and EDWARD J. RAY Sep. 1988 12 p Previously magnitudes, and regions of unstable pitch damping will contribute to the tumble susceptibility of a given configuration. Author announced in IAA as A88-37938 (NASA-TM-101491; NAS 1.15:101491) Avail: NTIS HC A03/MF A01 CSCL 14B The unique combination of adaptive wall technology with a 09 contonuous flow cryogenic wind tunnel is described. This powerful combination allows wind tunnel users to carry out 2-D tests at RESEARCH AND SUPPORT FACILITIES (AIR) flight Reynolds numbers with wall interference essentially eliminated. Validation testing was conducted to support this claim using well tested symmetrical and cambered airfoils at transonic Includes airports, hangars and runways; aircraft repair and overhaul speeds and high Reynolds numbers. The test section hardware facilities; wind tunnels; shock tube facilities; and engine test has four solid walls, with the floor and ceiling flexible. The method blocks. of adapting/shaping the floor and ceiling to eliminate top and bottom wall interference at its source is outlined. Data comparisons for different size models tested and others in several sophisticated A89-10115# 2-D wind tunnels are made. In addition, the effects of Reynolds LASER SHEET TECHNIQUE FOR VISUALIZING A PERIODIC number, testing at high lift with associated large flexible walt ROTOR WAKE movements, the uniqueness of the adapted wall shapes, and the A. G. BRAND, N. M. KOMERATH, and H. M MCMAHON (Georgia effects of sidewall boundary layer control are examined. The 0.3-m Institute of Technology, Atlanta) Journal of Aircraft (ISSN TCT is now the most advanced 2-D research facility anywhere. 0021-8669), vol. 25, July 1988, p. 667-669. Previously cited in Author issue 07, p. 955, Accession no. A88-22140. refs
A89-11037# N89-10897"# National Academy of Sciences - National Research A DATA ACQUISITION SYSTEM FOR BLADE VIBRATION Council, Washington, D. C. TEST REVIEW OF AERONAUTICAL WIND TUNNEL FACILITIES CHENGSHENG ZHANG and ZHAOHONG SONG (Beijing Institute 27 Jul. 1988 64 p of Aeronautics and Astronautics, People's Republic of China) (Contract NASW-4003) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, April 1988, (NASA-CR-183057; NAS 1.26:183057) Avail: NTIS HC A04/MF p. 158-160, 190. In Chinese, with abstract in English. refs A01 CSCL 14B A real-time data acquisition system based on IBM-PC for The nation's aeronautical wind tunnel facilities constitute a vibration test is provided. The highest sampling frequency of each valuable technological resource and make a significant contribution channel is 100 kc/s. There are 16 A/D channels and 2 D/A to the global supremacy of U.S. aircraft, both civil and military. At channels in this system. The tests of frequency spectrum analysis the request of NASA, the National Research Council's Aeronautics and vibration stress distribution of blade have been completed and Space Engineering Board organized a commitee to review with this system. Author the state of repair, adequacy, and future needs of major aeronautical wind tunnel facilities in meeting national goals. The A89-12550"# Kansas Univ. Center for Research, Inc., comittee identified three main areas where actions are needed to Lawrence. sustain the capability of NASA's aeronautical wind tunnel facilities INLET DEVELOPMENT FOR THE NFAC 80- BY 120-FOOT to support the national aeronautical research and development INDRAFT WIND TUNNEL activities: tunnel maintenance and upgrading, productivity JOHANNES M. VAN AKEN (University of Kansas Center for enhancement, and accommodation of new requirements Research, Inc., Lawrence), JAMES C. ROSS, and PETER T. ZELL (particularly in hypersonics). Each of these areas are addressed
41 09 RESEARCH AND SUPPORT FACILITIES (AIR)
and the committee recommendations for appropriate actions have guided system development toward easy upgrade at modest presented. Author cost. Results from use and demonstration have been positive, especially in the areas of reliability and ease of use. DOE N89-10898# Sandia National Labs., Albuquerque, N. Vex. SANDIA NATIONAL LABORATORIES FLIGHT SIMULATION FACILITIES 10 T. M. CRIEL and F. V. WYATT May 1988 14 p (Contract DE-AC04-76DP-00789) (DE88-012108; SAND-87-2034) Avail: NTIS HC A03/MF A01 ASTRONAUTICS Flight simulation computer facilities and motion simulator facilities at Sandia National Laboratories include an AD-100 (both Includes astronautics (general); astrodynamics; ground support real-time digital simulation computers), two AD-5s (analog systems and facilities (space); launch vehicles and space vehicles; computers), a VAX 11/780 (a digital mainframe), a PDP 11/60 (a space transportation; spacecraft communications, command and digital computer), and a Carco S-450R-3/R three-axis motion tracking; spacecraft design, testing and performance; spacecraft simulator. This report describes the current equipment. DOE instrumentation; and spacecraft propulsion and power.
N89-10899# Sandia National Labs., Albuquerque, N. Vex. Photometrics and Optical Development Div. A89-10691 SCHLIEREN MEASUREMENTS AT THE 10,000-FOOT SLED GLOBAL POSITIONING SYSTEM (GPS) RECEIVER TRACK INITIALIZATION METHODS FOR MIL-STD-1760A R. A. HILL, R. L. HUGHES, and A. A. SEHMER Jul. 1988 19 p. ROBERT M. KANE (General Dynamics Corp., Convair Div., San (Contract DE-AC04-76DP-00789) Diego, CA) IN: Aerospace avionics equipment and integration; (DE88-012748; SAND-88-0497) Avail: NTIS HC A03/MF A01 Proceedings of the Second Conference, Dallas, TX, Nov. 2-4, 1987. A schlieren technique has been used at the 10,000-foot sled Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. track to record the interaction of the horizontal bow shock produced 155-162. refs by a supersonic sled with the track structure. Under the conditions (SAE PAPER 872501) of these tests, the bow shock reflected from the west retaining The needs of a store that includes GPS are discussed as well wall is observed to interact with the aft portion of the sled; the as methods appropriate for a long-term solution to initialization. bow shock reflected from the east rail passes to the rear of the Alternatives that will reveal the inherent flexibility of GPS and sled. DOE thus permit better short-term compatibilty with existing aircraft are described. Of particular interest are digital initialization, time synchronization, and RF signal delivery. K.K. N89-10900"# California Univ., Davis. Dept. of Mechanical Engineering. DESIGN AND EVALUATION OF A COCKPIT DISPLAY FOR AERODYNAMICA89-11119# DESIGN AND PERFORMANCE OF 'A HOVERING FLIGHT BENT-AXIS GEOMETRY VEHICLE RONALD A. HESS and PETER JAMES GORDER 2 Oct. 1988 W. H. RUTLEDGE, G. F. POLANSKY, and E. L. CLARK (Sandia 39 p National Laboratories, Albuquerque, NM) Journal of Spacecraft (Contract NCC2-383) and Rockets (ISSN 0022-4650), vol. 25, July-Aug. 1988, p. (NASA-CR-183247; NAS 1.26:183247) Avail: NTIS HC A03/MF 257-262. refs A01 CSCL 14B (AIAA PAPER 87-2491) A simulator evaluation of a cockpit display format for hovering Variable bent-axis maneuvering vehicles provide a unique type flight is described. The display format is based on the of control for a variety of supersonic and hypersonic missions. position-velocity-acceleration representation (PVA) similar to that Unfortunately, the large hinge moments often associated with these used in the Pilot Night Vision System in the Army AH-64 helicopter. vehicles have prevented their application. This study examines By only varying the nature of the display law driving the primary the application of both experimental data and computational indicator in the PVA format, i.e., the acceleration symbol, three aerodynamics techniques in the design of such vehicles. A candidate displays are created and evaluated. These range from procedure is presented for the efficient design of a bent-axis a Status display in which the primary indicator provides true geometry given a set of system constraints. In particular, the acceleration information to a Command display, in which the primary selection of vehicle parameters to produce minimum hinge indicator provides flight director information. Simulation results moments for trimmed flight is examined in detail. Finally, the overall indicate that two of the three displays offer performance and performance of the bent-axis geometry is reviewed in terms of handling qualities which make them excellent candidates for future static stability, lift-to-drag ratio, and control effectiveness. Author helicopter cockpit display systems. Author A89-12317 N89-10901# Oak Ridge National Lab., Tenn. HOTOL COMMAND AND CONTROL SYSTEMS PROTOTYPE DATA ACQUISITION AND ANALYSIS SYSTEM J. D. ROWLEY (British Aerospace, PLC, London, England) SAE, FOR NAVY OPERATIONAL FLIGHT SIMULATORS Aerospace Vehicle Conference, Annapolis, MD, Apr. 18-20, 1988. R. C. MULLER, G. O. ALLGOOD, and B. VANHOY 1988 6 p 15p. Presented at the American Institute of Aeronautics and Astronautics (SAE PAPER 880929) Simulation Technology Conference, Atlanta, Ga., 7 Sep. 1988 HOTOL is intended to provide a low cost means of delivering (Contract DE-AC05-84OR-21400) payloads to low earth orbit. The vehicle is thus designed for (DE88-014557; CONF-8809108-1) Avail: NTIS HC A02 unmanned and largely autonomous operations with very limited A problem of flight simulators has been the discomfort contact with a ground station. This paper outlines the Command experienced by some pilots to the point of nausea. Likely and Control Systems studies undertaken to date and proposed explanations are a significant lack of synchronization between sight for future phases. Author and movement as well as motion in the critical frequency magnitude region. A program to examine this problem has been undertaken N89-10111"# National Aeronautics and Space Administration. at Oak Ridge National Laboratory, and the selection of appropriate Lewis Research Center, Cleveland, Ohio. computer hardware and software for analyzing motion and visual FIRE BEHAVIOR AND RISK ANALYSIS IN SPACECRAFT systems in real time is described. While requirements such as ROBERT FRIEDMAN and KURT R. SACKSTEDER 1988 14 p high data acquisition rate and high rates of arithmetic operations Prepared for presentation at the Winter Annual Meeting of the have driven the sections, rapid advances in computer technology American Society of Mechanical Engineers, Chicago, II1., 28 Nov.
42 11 CHEMISTRY AND MATERIALS
-3Dec.1988 aligned and basketweave microstructures in near-alpha alloys used (NASA-TM-100944;E-4232;NAS1.15:100944)Avail:NTISHC in gas turbine engines, with some observations on crack growth A03/MFA01 CSCL22B behavior in IMI834, a new high-temperature titanium alloy. V.L. Practicalriskmanagementforpresentandfuturespacecraft, includingspacestations,involvestheoptimizationofresidualrisks A89-11103# balancedbythespacecraftoperational,technological,and ACTIVE CONTROL OF REHEAT BUZZ economiclimitations.Spacecraftfiresafetyisapproachedthrough A. P. DOWLING, N. HOOPER, P. J. LANGHORNE (Cambridge threestrategies,inorderofrisk:(1)controloffire-causingelements, University, England), and G. J. BLOXSIDGE AIAA Journal (ISSN throughexclusionofflammablematerialsforexample;(2)response 0001-1452), vol. 26, July 1988, p. 783-790. Research supported toincipientfiresthroughdetectionandalarm;and(3)recoveryof by Rolls-Royce, PLC. Previously cited in issue 08, p. 1152, normalconditionsthroughextinguishmentandcleanup.Present Accession no. A87-22628. refs understandingofcombustioninlowgravityisthat,comparedto normalgravitybehavior,firehazardsmaybereducedbythe A89-11214 absenceofbuoyantgasflowsyetatthesametimeincreasedby INFLUENCE OF REGENERATION TREATMENTS ON CREEP ventilationflowsandhotparticleexpulsion.Thispaperdiscusses RUPTURE LIVES OF TURBINE BLADES the applicationof low-gravitycombustionknowledgeand W.-B. BUSCH (Fraunhofer-lnstitut fuer angewandte Materialfor- appropriate aircraft analogies to fire detection, fire fighting, and schung, Bermen, Federal Republic of Germany) and J. fire-safety decisions for eventual fire-risk management and WORTMANN (MTU Motoren- und Turbinen- Union Muenchen optimization in spacecraft. Author GmbH, Munich, Federal Republic of Germany) IN: High temperature alloys: Their exploitable potential. London and New N89-10123"# National Aeronautics and Space Administration. York, Elsevier Applied Science, 1988, p. 337-346. Lewis Research Center, Cleveland, Ohio. Experimental data are presented on the regeneration treatment TECHNOLOGY ISSUES ASSOCIATED WITH FUELING THE of turbine blades of forged Nimonic 108 alloy to show that hot NATIONAL AEROSPACE PLANE WITH SLUSH HYDROGEN isostatic pressing offers the possibility of the complete healing of NED P. HANNUM 1988 9 p Prepared for presentation at the creep voids. Process time and temperatures can be kept sufficiently 7th Joint Intersociety Cryogenic Conference Symposium, Houston, low to suppress undesirable diffusion processes. After the Tex., 22-26 Jan. 1989; sponsored in part by ASME, AIChE and regeneration treatment described here, the life of test specimens, IIR all of which reached the tertiary creep stage, was at least 75 (NASA-TM-101386; E-4445; NAS 1.15:101386) Avail: NTIS HC percent of that of virgin specimens. V.L A02/MF A01 CSCL 21H The National Aerospace Plane is a horizontal takeoff and A89-11216 landing, single stage-to-orbit vehicle using hydrogen fuel. The first THE HIGH TEMPERATURE OXIDATION BEHAVIOR OF THE flights are planned for the mid 1990's. The success of this important SINGLE CRYSTAL NI-BASE ALLOY M002 MOD. WITH AND national program requires advances in virtually every discipline WITHOUT PROTECTIVE COATINGS associated with both airbreathing and space flight. The high heating L. PEtCHL, J. WORTMANN (MTU Motoren- und Turbinen-Union value, cooling capacity, and combustion properties make hydrogen Muenchen GmbH, Munich, Federal Republic of Germany), and H. the fuel of choice, but low density results in a large vehicle. Both -J. RAETZER-SCHEIBE (DFVLR, Cologne, Federal Republic of fuel cooling capacity and density are increased with the use of Germany) IN: High temperature alloys: Their exploitable potential. slush hydrogen and result in significant reductions in vehicle size. London and New York, Elsevier Applied Science, 1988, p. A national program to advance this technology and to find 363-373. refs engineering solutions to the many design issues is now under Cyclic high-temperature oxidation tests were carried out on way. The program uses the expertise of the cryogenics production cylindrical bar (100x8 mm) specimens of the single-crystal Ni-base and services industry, the instrumentation industry, universities and alloy M002 mod. with an AI coating, a PtAI coating, an MCrAIY governments. The program will be discussed to highlight the major coating, and in the uncoated condition. It is found that the oxidation issues and display progress to date. Author of the specimens increases in the following order: uncoated - AI - PtAI - MCrAIY. With all three coatings, cubic and plate-type W-rich phases are found in the base material. Subsurface porosity forms 11 in the uncoated specimens and in specimens with AI and PtAI coatings after the coating has disintegrated. The MCrAIY coating shows extensive porosity at the coating-substrate interface. V.L CHEMISTRY AND MATERIALS A89-12330" National Aeronautics and Space Administration. Includes chemistry and materials (general); composite materials; Lewis Research Center, Cleveland, Ohio. inorganic and physical chemistry; metallic materials; nonmetallic DEPOSITION OF NA2SO4 FROM SALT-SEEDED COMBUSTION materials; and propellants and fuels. GASES OF A HIGH VELOCITY BURNER RIG G. J. SANTORO, F. J. KOHL, C. A. STEARNS (NASA, Lewis Research Center, Cleveland, OH), S. A. GOKOGLU (Analex Corp., A89-10069 Cleveland, OH), and D. A. ROSNER (Yale University, New Haven, MICROSTRUCTURAL OPTIMISATION OF TITANIUM ALLOYS CT) IN: High temperature corrosion in energy systems. FOR DEFECT TOLERANCE IN GAS TURBINE ENGINE Warrendale, PA, Metallurgical Society of AIME, 1985, p. 417-434. COMPONENTS refs M. T. COPE, P. J. POSTANS, and M. A. HICKS (Rolls-Royce, With a view to developing simulation criteria for the laboratory PLC, London, England) IN: Microstructure fracture toughness testing of high-temperature materials for gas turbine engines, the and fatigue crack growth rate in titanium alloys; Proceedings of deposition rates of sodium sulfate from sodium salt-seeded the 1987 TMS-AIME Annual Symposium, Denver, CO, Feb. 24, combustion gases were determined experimentally using a well 25, 1987. Warrendale, PA, Metallurgical Society, Inc., 1987, p. instrumented high-velocity burner. In the experiments, Na2SO4, 137-145. NaCI, NaNO3, and simulated sea salt solutions were injected into The paper is concerned with titanium alloy development for the combustor of the Mach 0.3 burner rig operating at constant high-temperature compressor disc applications, where resistance fuel/air ratios. The deposits formed on an inert rotating collector to low cycle fatigue and creep is of primary importance. Particular were then weighed and analyzed. The experimental results are attention is given to the problem of reducing the microstructural compared to Rosner's vapor diffusion theory. Some additional test unit size while maintaining the tortuous nature of the crack path results, including droplet size distribution of an atomized salt spray, in transformed beta microstructures. Results are presented for are used in interpreting the deposition rate data. V.L.
43 11 CHEMISTRY AND MATERIALS
A89-12759" National Aeronautics and Space Administration. (Contract AF AFOSR-0075-84; AF PROJ. 2306) Langley Research Center, Hampton, Va. (AD-A195489; AFOSR-88-0457TR) Avail: NTIS HC A08/MF A01 THE EFFECTS OF FLUIDS IN THE AIRCRAFT ENVIRONMENT CSCL 11F ON A POLYETHERIMIDE The fatigue of behavior of short cracks was investigated in EDWARD R. LONG, JR. (NASA, Langley Research Center, five wrought nickel-base superalloys currently used for aircraft Cleveland, OH) and WILLIAM D. COLLINS (Old Dominion turbine disks. Cracks were initiated at artificial defects and at University, Norfolk, VA) Polymer Engineering and Science (ISSN persistent slip bands. Test frequencies ranged from 20Hz to 10cpm. 0032-3888), vol. 28, no. 12, June 1988, p. 823-828. refs Fatigue crack growth rates were measured over crack lengths (Contract NCC1-90) ranging from 10 um to lmm. Most of the testing was performed Fluid absorption studies have been made for a polyetherimide in load control with stress ranges approaching the cyclic yield thermoplastic film and a unidirectional composite of the strengths of alloys. Strain controlled tests were performed on IN100 thermoplastic with graphite fibers immersed in water. JP4 jet fuel, under elastic-plastic cycling conditions. GRA ethylene g_ycol, and hydraulic fluid. The changes in the weight, thickness, and tensile properties were measured for the film. The N89-10167# Lawrence Livermore National Lab., Calif. changes in the flexural properties of the composite were measured DIRECTIONAL SPECTRAL EMISSIVITY MEASUREMENTS ON for specimens whose fiber orientation was transverse to their A CERAMIC MOLD MATERIAL length. Only the hydraulic fluid, which caused an erosion or MARK A. HAVSTAD and WILLIAM MCLEAN Apr. 1988 17 p dissolving of the resin at the specimen surface, affected the film's (Contract W-7405-ENG-48) properties. Both the water and the hydraulic fluid affected the (DE88-015407; UCID-21385) Avail: NTIS HC A03/MF A01 flexural properties of the composite, due to capillary absorption This document describes directional spectral emittance along the fiber-resin interface. Author measurements made on a ceramic mold material that is to be used to cast high- temperature turbine rotors. The work was N89-10125"# Clemson Univ., S.C. Dept. of Mechanical performed at approximately 700 K and 5 x 10 to the -9 Torr in an Engineering. emissivity measurement apparatus. The results, which show low FRACTURE CRITERIA FOR DISCONTINUOUSLY REINFORCED scatter and conform to expectations derived from both theoretical METAL MATRIX COMPOSITES Semiannual Report, 16 Feb. - relations and published ceramic data, give a total hemispherical 15 Aug. 1988 emissivity of 0.42 + or - 0.04 when integrated over wavelength H. J. RACK, J. G. GOREE, J. ALBRITTON, and P. and direction at 1000 K. DOE RATNAPARKHI 21 Oct. 1988 152 p (Contract NAG1-724) N89-10175# Federal Aviation Agency, Atlantic City, N.J. (NASA-CR-181175; NAS 1.26:181175) Avail: NTIS HC A08/MF THE PERFORMANCE OF ALTERNATE FUELS IN GENERAL A01 CSCL 11D AVIATION AIRCRAFT Final Report Summarized is the progress achieved during the period AUGUSTO M. FERRARA and RICHARD WARES (liT Research September 16, 1987 to August 15, 1988 on NASA Grant NAG1-724, Inst., Bartlesville, Okla.) Jul. 1988 47 p Fracture Criteria for Discontinuously Reinforced Metal Matrix (DOT/FAA/CT-88/13) Avail: NTIS HC A03/MF A01 Composites. Appended are copies of three manuscripts prepared The results of a study which measured the effects of pressure under NASA funding during the performance period. Author altitude on fuel weathering are described. Samples of unleaded automobile gasoline were exposed to varying pressure altitudes, N89-10156'# National Aeronautics and Space Administration. and the effects of this exposure on aircraft performance and Lewis Research Center, Cleveland, Ohio. volatility were measured. The composition of the fuel, aircraft T55-L-712 TURBINE ENGINE COMPRESSOR HOUSING configuration, and the initial temperature of the fuel when REFURBISHMENT-PLASMA SPRAY PROJECT transferred to the tank were varied to determine the extent these GEORGE W. LEISSLER and JOHN S. YUHAS (Army Aviation variables affected the aircraft performance. Experiments were Systems Command, Cleveland, Ohio.) Oct. 1988 44 p conducted which demonstrated that the use of 100 F fuel during (Contract DA PROJ. 1L1-62209-AH-76) aircraft certification will provide the greatest margin of safety. In (NASA-TM-101310; E-4301; NAS 1.15:101310) Avail: NTIS HC addition, the suitability of methyl-tertiary-butyl ether as an A03/MF A01 CSCL 11F acceptable fuel for use in general aviation aircraft was A study was conducted to assess the feasibility of reclaiming demonstrated. Several different oxygenated fuels (including T55-L-712 turbine engine compressor housings with an 88 wt gasolines containing alcohols) were aged in ground-based tests. percent aluminum to 12 wt percent silicon alloy applied by a plasma The results are presented. Author spray process. Tensile strength testing was conducted on as-sprayed and thermally cycled test specimens which were plasma N89-10179# Federal Aviation Agency, Atlantic City, N.J. sprayed with 0.020 to 0.100 in. coating thicknesses. Satisfactory ALTERNATE FUELS FOR GENERAL AVIATION AIRCRAFT tensile strength values were observed in the as-sprayed tensile WITH SPARK IGNITION ENGINES Final Report specimens. There was essentially no decrease in tensile strength AUGUSTO M. FERRARA Jun. 1988 81 p after thermally cycling the tensile specimens. Furthermore, (DOT/FAA/CT-88/05) Avail: NTIS HC A05/MF A01 compressor housings were plasma sprayed and thermally cycled Described are the results of a study into the behavior of several in a 150-hr engine test and a 200-hr actual flight test during alternate fuels under consideration for use in general aviation which the turbine engine was operated at a variety of loads, speeds aircraft engines. The study consists of a literature search and and torques. The plasma sprayed coating system showed no engine tests using a dynamometer. The literature search identifies evidence of degradation or delamination from the compressor material compatibility problems and possible solutions. For the housings. As a result of these tests, a procedure was designed engine tests, a number of gasoline/alcohol blends were prepared and developed for the application of an aluminum-silicon alloy in using both ethanol and methanol in varying concentrations and order to reclaim T55-L-712 turbine engine compressor housings. the vapor lock behavior was identified. The engine oil was analyzed Author during the study with the intent of detecting accelerated wear. Based on the results of the study, a number of considerations N89-10161# Massachusetts Inst. of Tech., Cambridge. Dept. of pertaining to the use of these alternate fuels in general aviation Materials Science and Engineering. aircraft are identified. Author A STUDY OF THE FATIGUE BEHAVIOR OF SMALL CRACKS IN NICKEL-BASE SUPERALLOYS Final Report, 1 Jan. 1984 - 1 N89-10951"# National Aeronautics and Space Administration. Aug. 1987 Langley Research Center, Hampton, Va. REGIS M. PELLOUX, JUN FENG, and GLENN ROMANOSKI 24 TENSION FATIGUE ANALYSIS AND LIFE PREDICTION FOR Feb. 1988 153 p COMPOSITE LAMINATES
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T. K. OBRIEN, M. RIGAMONTI, and C. ZANOTTI (Costruzioni acceptable values in the case of fatigue and fast fatigue tests, Aeronautiche Giovanni Agusta Sp.A., Gallarate, Italy ) Oct. while the behavior of creep normal specimens is anomalous. The 1988 55 p test conditions are discussed. ESA (NASA-TM-100549; NAS 1.15:100549; AVSCOM-TM°88-B-015) Avail: NTIS HC A04/MF A01 CSCL 11D A tension fatigue life prediction methodology for composite laminates is presented. Tension fatigue tests were conducted on 12 quasi-isotropic and orthotropic glass epoxy, graphite epoxy, and glass/graphite epoxy hybrid laminates. Edge delamination onset ENGINEERING data were used to generate plots of strain energy release rate as a function of cycles to delamination onset. These plots were then Includes engineering (general); communications; electronics and used along with strain energy release rate analyses of electrical engineering; fluid mechanics and heat transfer; delaminations initiating at matrix cracks to predict local delamination instrumentation and photography; lasers and masers; mechanical onset. Stiffness loss was measured experimentally to account for the accumulation of matrix cracks and for delamination growth. engineering; quality assurance and reliability; and structural mechanics. Fatigue failure was predicted by comparing the increase in global strain resulting from stiffness loss to the decrease in laminate failure strain resulting from delaminations forming at matrix cracks A89-10076" National Aeronautics and Space Administration. through the laminate thickness. Good agreement between Langley Research Center, Hampton, Va. measured and predicted lives indicated that the through-thickness ADHESIVELY BONDED JOINTS: TESTING, ANALYSIS, AND damage accumulation model can accurately describe fatigue failure DESIGN; PROCEEDINGS OF THE INTERNATIONAL for laminates where the delamination onset behavior in fatigue is SYMPOSIUM, BALTIMORE, MD, SEPT. 10-12, 1986 well characterized, and stiffness loss can be monitored in real W. S. JOHNSON, ED. (NASA, Langley Research Center, Hampton, time to account for damage growth. Author VA) Symposium supported by ASTM. Philadelphia, PA, American Society for Testing and Materials, 1988, 324 p. For individual items N89-11005# Joint Publications Research Service, Arlington, Va. see A89-10077 to A89-10095. EFFECT OF PROTECTIVE COATINGS ON LIFE OF The papers contained in this volume provide an overview of HEAT-RESISTANT NICKEL STEEL UNDER CYCLIC HEAT the state of the art of testing, analysis, and design of adhesively LOAD Abstract Only bonded joints. The papers are grouped in the following sections: G. N. TRETYACHENKO, G. R. SEMANOV, K. YU. YAKOVCHUK, mechanical testing, stress analysis, failure mechanisms, and design R. I. KURIAT, I. S. MALASHENKO, A. A. RABINOVICH, and N. P. and durability. Specific topics discussed include determination and VASHCHILO In its JPRS Report: Science and Technology. USSR: verification of elastic parameters for adhesives; factors influencing Materials Science p 15 4 Apr. 1988 Transl. into ENGLISH elastic stresses in double cantilever beam specimens; special mixed from Problemy Prochnosti (Kiev, USSR), no. 12, Dec. 1987 p 3-7 finite elements for interracial stress analysis of ahesively bonded Avail: NTIS HC A03/MF A01 joints; debonding characteristics of adhesively bonded woven An experimental study of fireproof coatings on heat-resistant Kevlar composites; and environmental durability of adhesively high-chromium nickel steel for gas-turbine blades was made, its bonded joints. V.L purpose being to evaluate their effect on the fatigue resistance of this steel under cyclic heat load in an atmosphere containing A89-10091" National Aeronautics and Space Administration. products of diesel fuel combustion with up to 0.25 percent sulfur. Langley Research Center, Hampton, Va. Two multimetal coating materials Co-Cr-AI-Y and Ni-Co-Cr-AI-Y as EFFECT OF ADHESIVE DEBOND ON STRESS-INTENSITY well as a double-layer composite material Co-Cr-AI-Y-ZrO sub 2 Y FACTORS IN BONDED COMPOSITE PANELS sub 20 sub 3 (25 to 70 micrometers thick layer of tetragonal + C. A. BIGELOW (NASA, Langley Research Center, Hampton, VA) monoclinic Zr sub 2 stabilized by addition of Y sub 20 sub 3) IN: Adhesively bonded joints: Testing, analysis, and design; were tested, having been deposited on prismatic wedges of that Proceedings of the International Symposium, Baltimore, MD, Sept. steel by the electron-beam vaporization and vacuum condensation 10-12, 1986. Philadelphia, PA, American Society for Testing and process. For comparison, bare wedges were also tested in the Materials, 1988, p. 209-228. refs same manner. Thermal cycling was done in three separate tests, Stress-intensity factors are calculated for a cracked infinite with the maximum temperature 980 C, 1000 C, 1020 C (pressure sheet adhesively bonded to a stringer, and debonding of the 500 MPa) respectively. The life wedges were found to be extended adhesive layer is predicted. The stringer is modeled as a semiinfinite by the coatings in tests with lower maximum temperature. sheet. Adhesive nonlinearity is also included. Both the sheet and Microstructural examination under MIM-7 and Neophot-2 optical stringer are treated as homogeneous, orthotropic materials, a set microscopes, X-ray spectral phase analysis in a Cameca of integral equations is formulated and solved to obtain the adhesive microanalyzer, and microhardness measurements with a PMT-3 shear stresses and crack-tip stress-intensity factors. Adhesive tester under a 50 g load have revealed that the ceramic layer debonding is predicted using a rupture criterion based on the provides high erosion resistance only, while the metal layer provides combined adhesive stresses. A through-the-thickness crack is the fatigue resistance and is where cracks originate at high located in the infinite sheet perpendicular to the edge of the stringer. temperature. Author When the crack is not under the stringer, the debond extends along the edge of the stringer. When the crack tip is beneath the N89-11020# Centre d'Essais Aeronautique Toulouse (France). stringer, the debond extends to the crack tip, then along the edge Section des Essais Mecaniques. of the stringer. Stress levels required for debond initiation decrease CREEP TESTS FOR SLOW AND FAST FATIGUE CONDITIONS as the crack tip is moved beneath the stringer. With a nonlinear ON ALUMINUM ALLOY SPECIMENS [ESSAIS DE FLUAGE DE adhesive, the debond initiates at higher applied stress levels than FATIGUE LENTE ET RAPIDE SUR DES EPROUVETTES EN in linear adhesive cases. Compared with the linear adhesive ALLIAGES D'ALUMINIUM] solution, modeling a nonlinear adhesive causes the stress-intensity 27 Feb. 1987 69 p In FRENCH factor to decrease when debonding is included. Author (Contract STPA-437103/79) (REPT-M0-535200; ETN-88-93321; REPT-437103/79) Avail: NTIS HC A04/MF A01 A89-10093 Tests were performed to evaluate the performance of aluminum STRESS ANALYSIS CONCEPTS FOR ADHESIVE BONDING OF alloys used in supersonic aircraft construction, as well as riveted AIRCRAFT PRIMARY STRUCTURE joints assemblied with titanium alloy rivets. The creep tests were RAYMOND B. KRIEGER, JR. (American Cyanamid Co., Havre de carried out at temperatures from 80 to 120 C. Results show Grace, MD) IN: Adhesively bonded joints: Testing, analysis, and
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design; Proceedings of the International Symposium, Baltimore, improve the fatigue life of the lugs by creating compressive stresses MD, Sept. 10-12, 1986. Philadelphia, PA, American Society for around the hole. The improvement is a factor of 2-2.5 in comparison Testing and Materials, 1988, p. 264-275. refs with nonexpanded reference lugs. The relaxation of residual This paper is a summation of the author's work toward creating stresses due to external loads is investigated by nonlinear finite valid stress analysis of adhesively bonded structure. The context element analysis, and a method is proposed for calculating is airframe construction, specifically metal to metal bonds, and cumulative fatigue damage with allowance for residual stresses. excluding sandwich structure. A model joint is presented as being V.L. a basic representation of the problem. A linear formula is given to calculate the maximum stress on the joint. This is seen to be A89-10121# stiffness driven, hence the adhesive shear stiffness is PACKAGED FIBER OPTIC GYROS WITH HIGH BIAS indispensable. Two extensometers are described as follows: KGR-1 STABILITY for adhesive shear stress versus strain, and KGR-2 for maximum P. GROELLMANN, J. HERTH, M. KEMMLER, K. KEMPF, G. adhesive strain on the model joint. An actual design is discussed, NEUMANN (LITEF GmbH, Litton Technische Werke, Freiburg im including adhesive selection by strain properties and adhesive Breisgau, Federal Republic of Germany) et al. IN: Symposium quality controlboy adhesive stress versus strain data. Author Gyro Technology 1987; Proceedings of the Symposium, Stuttgart, A89-10095 Federal Republic of Germany, Sept. 22, 23, 1987. Stuttgart/Duesseldorf, Universitaet Stuttgart/Deutsche Gesell- ENVIRONMENTAL DURABILITY OF ADHESIVELY BONDED JOINTS schaft fuer Ortung und Navigation, 1987, p. 4.0-4.17. BMFT- supported research, refs LARRY R. PITRONE and STANLEY R. BROWN (U.S. Navy, Naval LITEF is developing a fiber optic gyro of the 0.1 deg/h class Air Development Center, Warminster, PA) IN: Adhesively bonded for strapdown system applications. At the same time, modifications joints: Testing, analysis, and design; Proceedings of the are being performed on the LTR-81 attitude and heading reference International Symposium, Baltimore, MD, Sept. 10-12, 1986. system to allow its use as a fiber gyro testbed. Flight tests are Philadelphia, PA, American Society for Testing and Materials, 1988, scheduled for the end of 1988. This paper gives an overview of p. 289-303. refs the gyro design, its components, and test results achieved. Effective determination of adhesively bonded joint durability is Author crucial for reliable component design and realization of advanced performance. In order to model bond endurance in a manner more consistent with severe service environments, a cyclic stress A89-10154 durability apparatus that achieved constant shear stress without TURBULENCE MANAGEMENT AND RELAMINARISATION; loss due to creep relaxation was designed and implemented for PROCEEDINGS OF THE IUTAM SYMPOSIUM, BANGALORE, accelerated joint durability analysis of two modified epoxy based INDIA, JAN. 19-23, 1987 structural adhesives. Results were compared with those achieved H. W. LIEPMANN, ED. (California Institute of Technology, by sustained stress durability. Thermal analysis of the bulk Pasadena) and R. NARASIMHA, ED. (National Aeronautical adhesives, both before and after hygrothermal exposure, was Laboratory; Indian Institute of Science, Bangalore, India) compared with bonded joint mechanical and durability performance Symposium sponsored by IUTAM, Indian National Science to explore the potential utility of thermal analytical methods in Academy, CSIR, et al. Berlin and New York, Springer-Verlag, 1988, describing adhesive joint properties. Two cure histories for each 530 p. For individual items see A89-10555 to A89-10181. adhesive were investigated to establish bonded joint performance Theoretical, experimental, and applications aspects of and environmental resistance for conventional joint fabrication and turbulence control are examined in reviews and reports of recent potential adhesive/adherend co-curing capabilities. Author investigations. Topics addressed include structures, outer-layer devices, and surface manipulation for wall-bounded flows; dynamics A89-10096 and control of the transition to turbulence; relaminarization; natural SWEDISH SYMPOSIUM ON RESIDUAL STRESSES, SUNNE, laminar flows; free shear flows; and separated flows. Consideration SWEDEN, MAR. 30-APR. 2, 1987, PROCEEDINGS is given to measurements in a synthetic turbulent boundary layer TORSTEN ERICSSON, ED. (Linkoping Institute of Technology, (TBL), TBL modeling and manipulation for zero and adverse Sweden) and JENS BERGSTROM, ED. (Uddeholms AB, Hagfors, pressure gradients, high-Reynolds-number LEBU devices, Sweden) Symposium organized by Linkoping Institute of turbulence management by groove roughness, numerical Technology; Supported by the Uddeholm Research Foundation. simulations of transition in a decelerating boundary layer, Hagfors, Sweden, Uddeholms AB, 1987, 296 p. For individual items xanthan-gum turbulent-drag reduction, the pairing process in an see A89-10097 to A89-10099. excited plane TBL, turbulent mixing in accelerating jets, and the The papers presented in this volume focus on recent theoretical structure and control of a turbulent reattaching flow. T.K. and experimental research in residual stresses, with the areas covered including the mechanisms of residual stress buildup, stress A89-10159 introduction through different processes, residual stress TURBULENT BOUNDARY LAYER MANIPULATION AND measurements, and possible design applications. Papers are MODELLING IN ZERO AND ADVERSE PRESSURE presented on residual stresses due to machining and their influence GRADIENTS on the fatigue properties of steel, residual stresses in coatings, A. M. SAVILL (Cambridge University, England) IN: Turbulence residual stresses and distortion due to welding, and influence of management and relaminarisation; Proceedings of the IUTAM residual stress fields on fatigue crack propagation. V.L. Symposium, Bangalore, India, Jan. 13-23, 1987. Berlin and New York, Springer-Verlag, 1988, p. 69-83. Research supported by A89-10099# Rolls-Royce, PLC. refs FATIGUE LIFE INFLUENCE OF RESIDUAL STRESSES FROM Results are reported from experimental investigations of (1) COLD WORKING AND HIGH SPECTRUM LOADS IN the zero-pressure-gradient boundary layer behind a single flat-plate AIRCRAFT STRUCTURAL DESIGN manipulator and (2) a tandem manipulated layer subjected to a THOMAS JOHANSSON and SVEN-ERIK LARSSON (Saab-Scania strong adverse pressure gradient. Data obtained using hot-wire AB, Linkoping, Sweden) IN: Swedish Symposium on Residual anemometry, sublayer-scale fence skin-friction measurements, and Stresses, Sunne, Sweden, Mar. 30-Apr. 2, 1987, Proceedings. Preston tubes are presented in extensive graphs and discussed Hagfors, Sweden, Uddeholms AB, 1987, p. 246-265. refs in detail, with particular attention to problems of empirical turbulence Experimental data are presented on the residual stresses and modeling. It is found that the reductions in skin friction produced fatigue lives of cold worked attachment lugs of AA7010-T73651 by the manipulator plates result from a combination of direct action aluminum alloy with expanded holes. It is shown that the expansion on the boundary layer, interactions between manipulator wake methods used (split sleeve cold expansion and roller burnishing) vortices and the modified eddy structure, and a shielding action
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of the wake as a new internal layer grows. Good predictive accuracy The fundamental principles of the BEM and specific algorithms, is achieved using the modified ASM model of Leschziner (1986). numerical modeling approaches, and engineering applications are T.K. discussed in reviews and reports. Topics addressed include a hybrid formulation for the Green function in stratified media, advanced A89-10163 BEMs and coupled methods in geomechanics, a dual-reciprocity THE WALL-PRESSURE FLUCTUATIONS OF MODIFIED boundary element for parabolic problems, BEMs for TURBULENT BOUNDARY LAYER WITH RIBLETS three-dimensional optimum design, nonlinear analysis of elastic KWING-SO CHOI (British Maritime Technology, Ltd., Teddington, plates using the BEM, and single-integral equations for scattering England) IN: Turbulence management and relaminarisation; by a penetrable obstacle. Consideration is given to a polar Proceedings of the IUTAM Symposium, Bangalore, India, Jan. coordinate integration scheme with a hierarchical correction 13-23, 1987. Berlin and New York, Springer-Verlag, 1988, p. procedure, cubic interpolation and special elements in 149-160. Research supported by the Department of Trade and two-dimensional potential problems with the BEM, integral-equation Technology of England. refs analysis of elastic shells, and a boundary-integral-equation method An experiment was carried out in a wind tunnel, where the with higher computational accuracy. T.K. wall pressure fluctuations were measured in a modified turbulent boundary layer with riblets, and the results were compared with A89-10261 those without riblets. It was found that the rms intensity was AUTOMATED OPTICAL INSTRUMENT FOR EXTRACTING reduced by 4 percent by the surface modification, most of which WATER DROPLET IMPINGEMENT DATA FROM WIND was the low-frequency component in the energy spectrum. This TUNNEL EXPERIMENTS moderate reduction seemed to be a result of the reduced turbulence G. A. FREUND, JR., F. M. DICKEY, R. ELANGOVAN, M. D. BREER intensity confined within a small volume close to the riblet (Boeing Military Airplane Co., Wichita, KS), and M. PAPADAKIS surface. Author (Wichita State University, KS) IN: Current developments in optical engineering II; Proceedings of the Meeting, San Diego, CA, Aug. A89-10173 18-21, 1987. Bellingham, WA, Society of Photo-Optical ON THE PAIRING PROCESS IN AN EXCITED, PLANE, Instrumentation Engineers, 1987, p. 148-156. Research supported TURBULENT MIXING LAYER by Boeing Co. refs I. WYGNANSKI and I. WEISBROT (Tel Aviv University, Israel) IN: Extraction of empirical water droplet impingement characteristics Turbulence management and relaminarisation; Proceedings of the from records of wind tunnel dye-tracer experiments has been an IUTAM Symposium, Bangalore, india, Jan. 13-23, 1987. Berlin and extremely time consuming process in the past. Described are a New York, Springer-Verlag, 1988, p. 409-422. refs method for extracting impingement data by measuring optical reflectance and a computer controlled laser reflectometer which (Contract AF-AFOSR-86-0323; N00014-85-K-0412) The flow field in a plane turbulent mixing layer which was was designed and built for making these measurements. The disturbed by a small oscillating flap was investigated. Three instrument increases the efficiency of the data extraction process experiments were carried out: one in which the flap oscillated by at least an order of magnitude. The accuracy of the reflectometer sinusoidally at a single frequency; a second in which the flap is discussed and some results obtained with the reflectometer are oscillated at two frequencies, a fundamental and a subharmonic, presented. The results are used to verify three-dimensional particle but the ensuing motion was dominated by the fundamental trajectory computer codes, which may then be used for design perturbation; and a third in which the amplitude of the subharmonic analysis and certification of aircraft antiicing/deicing systems. Author perturbation was increased until a distortion in the mean flow was noticeable. Two velocity components were measured at all phase angles relative to the subharmonic oscillation of the flap at densely A89-10359 spaced intervals. The data were used to map the vorticity fields FIBER-OPTIC SENSOR SYSTEMS FOR AEROSPACE and streak-line patterns, for the purpose of assessing the relevance APPLICATIONS of the latter to the understanding of the dynamical process. E. UDD, R. J. MICHAL, S. E. HIGLEY, J. P. THERIAULT, P. Author LECONG (McDonnell Douglas Astronautics Co., Huntington Beach, CA) et al. IN: Fiber optic and laser sensors V; Proceedings of A89-10181 the Meeting, San Diego, CA, Aug. 17-19, 1987. Bellingham, WA, CONTROL OF SEPARATED FLOW ON A SYMMETRIC Society of Photo-Optical Instrumentation Engineers, 1988, p. AIRFOIL 162-168. CHIANG SHIH, MARIO LEE, and CHIN-MING HO (Southern Advanced aircraft and spacecraft will require fiber-optic sensor California, University, Los Angeles, CA) IN: Turbulence systems to monitor the environment around the platform as well management and relaminarisation; Proceedings of the IUTAM as the structural integrity of the vehicle itself. These sensors when Symposium, Bangalore, India, Jan. 13-23, 1987. Berlin and New embedded in composite or metal matrix material can also be used York, Springer-Verlag, 1988, p. 515-524. refs to monitor the manufacturing process. Thus, this technology (Contract F49620-85-C-0080) provides a means to sense key environmental parameters from On a stationary NACA 0012 airfoil, the separated flow and its the creation of parts, through assembly, test and flight for the life control were examined in an unsteady free stream. The experiment of the platform. Author was carried out in an unsteady water channel. Desired acceleration histories were obtained by controlling the free stream velocity of A89-10512 the channel. The initial separation process and the downstream TRANSITION RECOGNITION IN AIRCRAFT WING PROFILES development were studied in detail. Based upon this information, WITH THE AID OF PIEZOELECTRIC SHEETINGS control devices were placed on the airfoil and significant [TRANSITIONSERKENNUNG AN TRAGFLUEGELPROFILEN modifications on the flow were observed. Author MIT HILFE PIEZO-ELECTRISCHER FOLIEN] P. MIROW (Berlin, Technische Universitaet, Federal Republic of A89-10182 Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, ADVANCED BOUNDARY ELEMENT METHODS; PROCEEDINGS Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, OF THE IUTAM SYMPOSIUM, SAN ANTONIO, TX, APR. 13-16, Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 190-198. 1987 In German. refs T. A. CRUSE, ED. (Southwest Research Institute, San Antonio, (DGLR PAPER 87-065) TX) Symposium sponsored by IUTAM, Southwest Research The structure of a new type of piezoelectrical sheeting Institute, Daimler-Benz AG, and NSF. Berlin and New York, measurement system for recording pressure and shear stress Springer-Verlag, 1988, 506 p. For individual items see A89-10183 variations in bodies surrounded by flow. A series of measurement to A89-10201. results pertaining to transition processes on a 24 dog swept-back
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model aircraft wing is reported. The sheet rms values with wall A89-10671 shear values are compared for the same wing. Details of the FATIGUE TESTING OF FULL-SCALE ALL-COMPOSITE transition and the excitation process are demonstrated using AIRCRAFT WINGS frequency analysis. Sum and difference signals from the sheet N. MILESHKIN, M. L. SCOTT, L. A. WOOD, and D. R. COLLYER sensors show differential changes over the profile depth, allowing (Royal Melbourne Institute of Technology, Australia) IN: the pressure and shear variations to be determined. Coherent International Pacific Air and Space Technology Conference, flow structures are recognizable when the pressure variations are Melbourne, Australia, Nov. 13-17, 1987, Proceedings. Warrendale, normalized, and correlation measurements permit predictions to PA, Society of Automotive I:;ngineers, Inc., 1988, p. 507-512. be made concerning the local signal propagation velocity. C.D. (SAE PAPER 872459) A full scale fatigue test program has been established which A89-10543# will test a sailplane wing set to destruction. A flight loads data FLOW PAST CIRCULAR CYLINDER OF FINITE LENGTH acquisition program using the instrumented high performance PLACED ON GROUND PLANE sailplane owned by the Royal Melbourne Institute of Technology SHIKI OKAMOTO Japan Society for Aeronautical and Space has been conducted to determine the loading cases and spectrum. Sciences, Journal (ISSN 0021-4663), vol. 36, no. 414, 1988, p. The aircraft structure is of glass fiber reinforced polymeric 343-350. In Japanese, with abstract in English. refs composite material construction. One wing was new at the This paper describes an experimental study of the changes of commencement of the fatigue test, while the other is a repaired vortices formation and turbulent wake from a circular cylinder wing salvaged from a damaged sailplane. The test of the repaired placed on a ground plane. The experiment was carried out in a wing will enable the fatigue performance of repair techniques to blow down wind-tunnel having a working section of 500 mm x be evaluated. In parallel with the full scale fatigue test, tests on 5000 mmx 2000 mm in size at Reynolds number 25,000 to 47,000. notched and plain glass fiber specimens will be used to establish material scatter factors which can be employed in safe fatigue life The surface-pressure distributions on the circular cylinder were measured and the drag coefficient was determined from them. estimation. A comprehensive finite element model of the wing is being developed in support of the full scale tests. Author The vortices generated in the flow-field around a circular cylinder have also been observed and the velocity defects and turbulent intensities in the turbulent wake behind the circular cylinder were A89-10676 measured. Consequently, it is found that the flow pattern changes AEROSPACE AVIONICS EQUIPMENT AND INTEGRATION; rapidly from H/D 4, while the shedding vortices change from PROCEEDINGS OF THE SECOND CONFERENCE, DALLAS, arch type to Karman type. Author TX, NOV 2-4, 1987 Conference sponsored by SAE. Warrendale, PA, Society of Automotive Engineers, Inc. (SAE P-205), 1988, 178 p. For individual A89-10573 items see A89-10677 to A89-10692. THE ELECTROCHEMICAL EROSION OF SERVO VALVES BY (SAE P-205) PHOSPHATE ESTER FIRE-RESISTANT HYDRAULIC FLUIDS The conference presents papers on hybrid MIL-STD- W. D. PHILLIPS (Ciba-Geigy Industrial Chemicals, Manchester, 1553B/1773 electrical/optical buses, the use of interrupts on England) (Society of Tribologists and Lubrications Engineers, the IBM PC to generate major and minor frame times, and the Annual Meeting, 42nd, Anaheim, CA, May 11-14, 1987) Lubrication use of the IBM PC for MIL-STD-1553 testing. Other topics include Engineering (ISSN 0024-7154), vol. 44, Sept. 1988, p. 758-767. single-chip solution of MIL-STD-1553A and MIL-STD-1553B data refs communications, a simulation model of the SAE AE-9B high The problem of the electrochemical erosion of servo valves in speed ring bus, and a high performance duel mode synchronous/ hydraulic systems using phosphate ester fire-resistant hydraulic asynchronous parallel bus controller utilizing the PI bus stan- fluids is reviewed with reference to past experience in turbine dard protocol. Consideration is also given to token rotation governor controls and commercial aircraft hydraulics. It is shown timer implementation and global positioning system receiver that the susceptibility of servo valves to electrochemical erosion initialization methods for MIL-STD-1760A. K.K. or pitting corrosion is determined by a variety of factors, such as the pressure drop across the valve or the fluid flow rate through A89-10677 the orifice and the size of the orifice. The zeta potential of the UT1760A RTS - A LOW-COST MONOLITHIC REMOTE fluid also plays an important but, as yet, unquantified role, while TERMINAL STORES INTERFACE FOR MIL-STD-1760A fluid conductivity/resistivity does not appear to be an important JOHN W. PRESSPRICH and MARTIN P. SOQUES (United factor. V.L. Technologies Microelectronics Center, Colorado Springs, CO) IN: Aerospace avionics equipment and integration; Proceedings of the A89-10670 Second Conference, Dallas, TX, Nov. 2-4, 1987. Warrendale, PA, A FREQUENCY DOMAIN MIMO MODAL IDENTIFICATION Society of Automotive Engineers, Inc., 1988, p. 1-5. METHOD WITH APPLICATION IN THE AIRCRAFT GROUND (SAE PAPER 872481) VIBRATION TEST The paper presents a low-cost monolithic remote terminal stores LINGMI ZHANG (Nanjing Aeronautical Institute, People's Republic interface (RTSI) for MIL-STD-1760A applications. The UT1760A of China) IN: International Pacific Air and Space Technology RTS can significantly reduce the cost/space problem associated Conference, Melbourne, Australia, Nov. 13-17, 1987, Proceedings. with applying MIL-STD-1553B within MIL-STD-1760A by integrating Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. a dual redundant remote terminal interface and 16K of memory in 499-505. refs one 68-pin device. The internal architecture of the part relieves (SAE PAPER 872458) the host from most data management tasks associated with This paper presents a frequency-domain MIMO identification MIL-STD-1553B processing by offering a use-defined RAM method. The accuracy, reliability, and ability of handling repeated addressing scheme. K.K. modes are verified by computer simulation and practical structures. The application to an aircraft ground vibration test is given. The A89-10683 results show: (1) that (compared with the traditional multipoint SINGLE-CHIP SOLUTION OF MIL-STD-1553A AND sine-excitation phase-resonance method) operation is simplified, MIL-STD-1553B DATA COMMUNICATIONS testing time is reduced, reliability is improved; and (2) that ROBERT J. BAUER (United Technologies Microelectronics Center, (compared with time-domain MIMO methods developed over the Colorado Springs, CO) IN: Aerospace avionics equipment and past several years) the order of the system (the number of modes) integration; Proceedings of the Second Conference, Dallas, TX, can be identified directly. The calculating time is reduced, and the Nov. 2-4, 1987. Warrendale, PA, Society of Automotive Engineers, need for the user to judge between structural modes and noise Inc., 1988, p. 63-69. modes is avoided. Author (SAE PAPER 872488)
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Several versions of the Avionics Time-Multiplexed 1553 serial determine the relative impact of each on overall bus communication standards are in use. Solutions available for some performance. Author 1553 protocols are often large and complex, and are not designed to be usable for more than one protocol. This paper describes A89-10714 the basic differences among the 1553 protocols, and discusses OPERATING SAFETY OF AUTOMATIC OBJECTS the system and architectural aspects of a single-chip solution that [BEZOPASNOST' FUNKTSIONIROVANIIA meet all requirements for a complete dual-redundant Bus Controller AVTOMATIZIROVANNYKH OB'EKTOV] and Remote Terminal (BCRT) for the following 1553 standards: ANATOLII VLADIMIROVI MAIOROV, GENRIKH KARLOVICH MIL-STD-1553A, MIL-STD-1553B, McDonnell Douglas A3818, MOSKATOV, and GEORGII PETROVlCH SHIBANOV Moscow, McDonnell Douglas A5332, McDonnel Douglas A5690, and Izdatet'stvo Mashinostroenie, 1988, 264 p. In Russian. refs Grumman Aerospace SP-G-151A. Easily integrated into a variety Operating-safety assurance for automatic objects (aircraft, of system architectures and requiring little CPU overhead, the spacecraft, and underwater vehicles) is considered in the framework single-chip device contains all memory management, error logging, of safety-automata theory and automatic-control considerations. and a simple-to-use processor interface. Author The interaction between the operator and the safety-assurance facilities is considered. Methodological recommendations are presented on the specification of reliability requirements for the A89-10686 vehicles considered, as well as on automata synthesis and analysis A CANDIDATE FOR LINEAR TOKEN-PASSING, HIGH-SPEED considerations, test planning, and the analysis of test results. DATA BUS SYSTEMS B.J. JAMES H. NELSON (Northrop Corp., Aircraft Div., Hawthorne, CA), LARRY T. SHAFER (McDonnell Aircraft Co., Saint Louis, MO), A89-10774 DARYLE B. HAMLIN, and JAMES J. HERRMANN (Unisys Corp., A STUDY OF THE ACCURACY OF WING CALCULATIONS Computer Systems Div., Saint Paul, MN) IN: Aerospace avionics BASED ON DIFFERENT SCHEMES [ISSLEDOVANIE equipment and integration; Proceedings of the Second Conference, TOCHNOSTI RASCHETA KRYLA PO RAZLICHNYM Dallas, TX, Nov. 2-4, 1987. Warrendale, PA, Society of Automotive SKHEMAM] Engineers, Inc., 1988, p. 105-120. S. I. PUTILIN and V. T. SAVCHENKO (AN USSR, Institut (SAE PAPER 872494) Gidromekhaniki, Kiev, Ukrainian SSR) Gidromekhanika (ISSN A candidate high-speed data bus protocol has been developed to meet the needs of data bases for distributed real-time 0367-4088), no. 58, 1988, p. 41-47. In Russian. refs Solutions obtained for the same flow problem using different fault-tolerant architectures of the future. Performance charac- vortex and computation point distribution laws are presented. The teristics are described with attention given to token-passing problem considered here is the plane problem for a plate near a protocol, fiber-optics implementation, and host interface. A circular contour, which is relevant to the design of wings with functional block diagram of a dual redundant HSDB network is optimal load distribution and low aspect ratio wings in a bounded provided. K.K. fluid. Ways to improve the accuracy of the results are discussed. V.L. A89-10687 ON HIGH-SPEED DATA BUS PERFORMANCE ANALYSIS A89-11028# M. T. LUDVIGSON (Rockwell International Corp.. Collins AN EXPERIMENTAL iNVESTiGATiON ON THE BISTABLE Government Avionics Div., Cedar Rapids, IA) IN: Aerospace BEHAVIORS OF A FLEXIBLE ROTOR-SQUEEZE FILM avionics equipment and integration; Proceedings of the Second DAMPER SYSTEM Conference, Dallas, TX, Nov. 2-4, 1987. Warrendale, PA, Society CHANGSHENG ZHU, XINHAI FENG (Gas Turbine Establishment, of Automotive Engineers, Inc., 1988, p. 127-131. Jang You, People's Republic of China), and JIANKANG XU (SAE PAPER 872496) (Northwestern Polytechnical University, Xian, People's Republic of The use of average throughput analysis in determining the China) Journal of Aerospace Power (ISSN 1000-8055), vol. 3, relative performance of high-speed data bus networks is examined. April 1988, p. 105-108, 184. In Chinese, with abstract in English. The performance of four different linear bus implementations and refs the SAE ring bus are considered in terms of low to moderate, The bistable behaviors of a resonance type which occurred high, and worst case throughput delays, and theoretical maximum near main resonance speed of the system are investigated, based throughput. It is found that average performance analysis is not a on experiments with a flexible rotor-squeeze film damper system. reliable predictor for bus performance at high levels of randomly The influences of unbalance speed, radial clearance ratio, offered traffic. For linear buses, it was found that preamble, token, centralizing spring stiffness, and acceleration process on the and station response time had a significant effect on average behaviors are considered. It is shown that the squeeze film damper performance. It is suggested that ring buses operating at the same is effective only within a certain unbalance range. If the unbalance data rates will experience significantly longer maximum (worse is large enough, the bistable operation may occur. Author case) delays than linear buses. K.K. A89-11029# A89-10688 THE BISTABLE BEHAVIOR OF A RIGID ROTOR WITH TOKEN ROTATION TIMER IMPLEMENTATION SQUEEZE FILM DAMPER M. T. LUDVIGSON (Rockwell International Corp., Collins LITANG YAN, SHIPING ZHANG, QIHAN LI, and FUAN ZHAO Government Avionics Div., Cedar Rapids, tA) IN: Aerospace (Beijing Institute of Aeronautics and Astronautics, People's Republic avionics equipment and integration; Proceedings of the Second of China) Journal of Aerospace Power (ISSN 1000-8055), voL 3, Conference, Dallas, TX, Nov. 2-4, 1987. Warrendale, PA, Society April 1988, p. 109-112, 184, 185. In Chinese, with abstract in of Automotive Engineers, Inc., 1988, p. 133-138. English. (SAE PAPER 872497) The bistable behaviors of the rigid rotor with centralizing spring Token rotation timers have been shown to be an effective and squeeze film damper are studied by means of calculations means for offering preferential treatment, in terms of message and experiments. The bistable behaviors are characterized by the delays, for certain critical messages in linear (star) high-speed variations of eccentricity, transmissibility and Lagging phase angle. data bus configurations. If a token rotation timer has expired, The results calculated and experimental data are in a good indicating that a prescribed time has transpired during the current agreement. The bistable operation of the rotor can be eliminated token rotation, then a low priority message will not be sent. If all at operating speeds if only the bearing parameters including the messages are not sent on the first available token, then some length and clearance of the film damper, and the stiffness of the degradation in overall message delay performance occurs. Several centralizing spring are chosen properly over a certain unbalance methods of token rotation timer implementation are examined to range of the rotor. Author
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A89-11032# People's Republic of China) Journal of Aerospace Power (ISSN A CIRCULAR CONE SURFACE SHAPING METHOD FOR FAN 1000-8055), vol. 3, July 1988, p. 277, 278, 288. In Chinese, with BLADE abstract in English. MINGHUI HAN and YAJUN LU (Beijing Institute of Aeronautics A node transfer matrix is deduced which considers the angular and Astronautics, People's Republic of China) Journal of stiffness and damping in spline coupling. The steady-state Aerospace Power (ISSN 1000-8055), vol. 3, April 1988, p. 123-126, unbalance responses for a rotor with several spans are obtained 186. In Chinese, with abstract in English. by using the Lund method and the simplified transfer-matrix method. A new method, circular surface shaping method, has been Using a model rotor, the damping ratio, eccentricity, and deflection developed to shape the sheet metal twisted blade. By changing have been measured with the amplitude-frequency characteristic the conical point angle and the location of the blade on the conic method. The steady-state unbalance responses have been surface, this method can satisfy the various radial laws and make obtained from these data. The analytical and experimental results the shaped blade meet the specifications of this aerodynamic are in good agreement. Author design much better. The forwardswept blade shape can be obtained by controlling the blade location on the circular cone surface. As A89-11251 a result, a new design and manufacturing method is provided for COMPOSITES IN SHOCK AND VIBRATION ISOLATION sheet metal twisted blade shaping. The method is of great practical H. RAY (U.S. Army, Materials Technology Laboratory, Watertown, and economic value. Author MA) Journal of Composites Technology and Research (ISSN 0885-6804), vol. 10, Fall 1988, p. 125-128. A89-11033# (Contract F49620-82-C-0035) CALCULATION OF COMPRESSIBLE FLOW AND HEAT This paper is concerned with the contol of force on an armor TRANSFER ON A ROTATING DISK plate of a combat aircraft caused by the central normal impact of DINGYI WU and SONGLING LIU (Northwestern Polytechnical a projectile and transmitted to the supports of plates, where there University, Xian, People's Republic of China) Journal of Aerospace is not enough space for the plate to move normal to the plane of Power (ISSN 1000-8055), vol. 3, April 1988, p. 135-139, 187. In the plate..The analysis requires the use of composite isolators Chinese, with abstract in English. refs which allow the plate to rotate in plane, so that less space is In this paper, the 'BOX' method is extended to swirling required normal to the plane of the plate. In this case, the impact compressible flow on a body of revolution, after the boundary energy is absorbed in the rotational direction in addition to the layer equation is nondimensionalized. The torque coefficients and usual normal to the plane of the plate. To control the force local heat transfer coefficients in the laminar, turbulent, and transmitted to the support, the natural frequency of the system transitional flow regions on the rotating disk are calculated. The must be controlled. The results of the analysis demonstrate the variable air properties are taken into account in the calculation. effects of fiber orientation and the material properties of a The investigation shows that the modified two-layer turbulence composite isolator on the natural frequency of the plate and model is suitable for the calculation of the flow on the rotating composite support system. It is shown that the natural frequency disk. An appropriate analytical formulation of the turbulence model of the plate-support system can be reduced even if the stiffness and relevant constants are also given. Author of the supports is increased. I.S.
A89-11039# A89-11426 A DESIGN METHOD OF 'WIGGLESTRAP' FILM-COOLING FRACTURE MECHANICS; PROCEEDINGS OF THE CONSTRUCTION OF FLAME TUBE NINETEENTH NATIONAL SYMPOSIUM, SAN ANTONIO, TX, CHANGLIN LI (Northwestern Polytechnical University, Xian, JUNE 30-JULY 2, 1986 People's Republic of China) Journal of Aerospace Power (ISSN THOMAS A. CRUSE, ED. (Southwest Research Institute, San 1000-8055), vol. 3, April 1988, p. 164-166, 190. In Chinese, with Antonio, TX) Symposium sponsored by ASTM and Southwest abstract in English. Research Institute. Philadelphia, PA, American Society for Testing This paper presents a calculation method for the design of and Materials, 1988, 950 p. For individual items see A89-11427 to A89-11449. three types of 'wigglestrap' film-cooling construction (i.e., the square, the trapeze, and the double circle arc constructions) which The papers contained in this volume provide an overview of are applied to the flame tube of an aeroengine. When the airflow current theoretical and experimental research in the field of fracture distribution and the corresponding airflow passage section areas mechanics. Topics discussed include three-dimensional issues, are given, all parameters of the construction can be determined. computational and analytical issues, damage tolerance and fatigue, Author elastoplastic fracture, dynamic inelastic fracture, and crack arrest theory and applications. Papers are presented on approximate A89-11046# methods for analysis of dynamic crack growth and arrest, constraint-loss model for the growth of surface fatigue cracks, BEVEL GEAR RESONANCE FAILURES IN CENTRAL GEARING SYSTEM OF AN AEROENGINE fatigue crack growth in aircraft main landing gear wheels, and near-threshold crack growth in nickel-base superalloys. V.L. EJUN XU, SHICHANG LIANG, CHUNJIANG CHANG, and BINGYAN SHEN (Shenyang Aeroengine Research Institute, A89-11860 People's Republic of China) Journal of Aerospace Power (ISSN LASER CONTROL OF VISIBILITY AND CLOUD-BASE HEIGHT 1000-8055), vol. 3, July 1988, p. 193-198, 279. In Chinese, with IN AIRFIELD REGIONS abstract in English. The resonance failures of the bevel gear in the central gearing MAREK PALYS (Institute of Geodesy and Meteorology, Warsaw, system of a specific aircraft engine have been investigated Poland) IN: Laser technology II; Proceedings of the Meeting, experimentally. The features of the resonance failures, the failure Szczecin, Poland, Sept. 7-10, 1987. Bellingham, WA, Society of modes, and the structural dynamic characteristics are summarized, Photo-Optical Instrumentation Engineers, 1988, p. 267-269. refs and the reasons for resonance are clarified. Some preventive A semiconductor-laser-based method for obtaining cloud-base measures against the failures are suggested, and criteria for the height measurements for distances of 50-2000 m and an dynamic-strength design of this type of gear are specified. He-Cd-laser-based method for obtaining visibility measurements Author with a base of order of 1 km are presented, with application to increasing safety in airfield regions. Microstructural changes and thermal fluctuations in the laser beam path are minimized in the A89-11066# case of the height finder by using very short pulses. The study STEADY-STATE UNBALANCE RESPONSES FOR A points out the need for measuring the refraction index structure MULTISPAN ROTOR function along with the standard temperature and wind velocity PINGZHEN REN (Northwestern Polytechnical University, Xian, gradients. R.R
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A89-12151# coefficients in the combustion chamber of an RCE. This was THE OPERATION OF MODERN AIR-SPACE SURVEILLANCE accomplished by making detailed temperature and pressure RADARS [ARBEITSWEISE MODERNER measurements in a direct injection stratified charge (DISC) RCE LUFTRAUM-UEBERWACHUNGSRADARE] under a range of conditions. For each specific measurement point, ALBRECHT LUDLOFF (AEG AG, UIm, Federal Republic of the local gas velocity was assumed equal to the local rotor tip Germany) Ortung und Navigation (ISSN 0474-7550), vol. 29, no. speed. Local physical properties of the fluids were then calculated. 2, 1988, p. 272-282. In German. Two types of correlation equations were derived and are described The operating principles and technological implementation of in this paper. The first correlation expresses the Nusselt number state-of-the-art moving-target-detector (MTD) radar systems for as a function of the Prandtl number, Reynolds number, and ATC and military applications are reviewed and illustrated with characteristic temperature ratio; the second correlation expresses extensive diagrams. The limitations of conventional MTI radars the forced convection heat transfer coefficient as a function of are summarized; the advantages of the ground-clutter-adapted fluid temperature, pressure and velocity. Author Doppler filter set and high-resolution ground-clutter maps of MTD systems are explained; and particular attention is given to the A89-12337" Yale Univ., New Haven, Conn. design and function of the MTD programmable digital signal AERODYNAMICALLY-DRIVEN CONDENSATE LAYER processor, the transmitted signal and block processing, and the THICKNESS DISTRIBUTIONS ON ISOTHERMAL CYLINDRICAL use of center-of-gravity algorithms in the MTD parameter-extraction SURFACES process. T.K. D. E. ROSNER, D. GUNES (Yale University, New Haven, CT), and N. NAZIH-ANOUS Chemical Engineering Communications A89-12252 (ISSN 0098-6445), vol. 24, 1983, p. 275-287. refs HEAT TRANSFER IN THE RECIRCULATING REGION FORMED (Contract NAG3-201) BY A BACKWARD-FACING STEP A simple yet rather general mathematical model is presented E. V. SHISHOV, P. S. ROGANOV, S. I. GRABARNIK, and V. P. for predicting the distribution of condensate layer thickness when ZABOLOTSKY (Moskovskoe Vysshee Tekhnicheskoe Uchilishche, aerodynamic shear is the dominant mechanism of liquid flow along the surface. The Newtonian condensate film is treated using Moscow, USSR) International Journal of Heat and Mass Transfer (ISSN 0017-9310), vo. 31, Aug. 1988, p. 1557-1562. refs well-known thin-layer (lubrication theory) approximations, and condensate supply is taken to be the result of either convective An analysis of experimental data obtained in the present diffusion or inertial impaction. Illustrative calculations for a circular investigation of the vortical structure of a recirculating flow formed by a backward-facing step has allowed the development of an cylinder in a crossflow at Re = 100,000 reveal the consequences of alternate condensate arrival mechanisms and the existence of approximate calculation method for predicting velocity and thicker reverse-flow films behind the position of gas boundary-layer temperature profiles, reattachment length, and local friction and heat-transfer coefficients. An analytical expression for heat transfer separation. The present formulation is readily generalized to include transient liquid layer flows on noncircular objects of variable surface in the reattachment region is derived which correlates experimental heat transfer data for different types of flow with a sudden temperature, as encountered in turbine-blade materials testing or expansion. Author operation. Author
A89-12276" National Aeronautics and Space Administration. A89-12752"# Detroit Diesel Allison, Indianapolis, Ind. MEASUREMENTS OF HEAT TRANSFER DISTRIBUTION OVER Lewis Research Cemer, Cieveiand, Ohio. THE DUAL ELEMENT METHOD OF STRAIN GAUGE THE SURFACES OF HIGHLY LOADED TURBINE NOZZLE TEMPERATURE COMPENSATION GUIDE VANES D. A. NEALY, M S. MIHELC, L. D. HYLTON (General Motors DAVID R. ENGLUND (NASA, Lewis Research Center, Cleveland, OH) IN: SEM, Annual Hostile Environments and High Temperature Corp., Detroit Diesel Allison Div., Indianapolis, IN), and H. J. Measurements Conference, 4th, Windsor Locks, CT, Mar. 24, 25, GLADDEN (NASA, Lewis Research Center, Cleveland, OH) 1987, Proceedings. Bethel, CT, Society for Experimental ASME, Transactions, Journal of Engineering for Gas Turbines and Mechanics, Inc., 1987, p. 40-42. Power (ISSN 0022-0825), vol. 106, Jan. 1984, p. 149-158. The use of a known temperature compensation technique is Previously cited in issue 23, p. 3394, Accession no. A83-47910. refs suggested to reduce the overall temperature sensitivity of a PdCr strain gauge system being developed for turbine engine research. (Contract NAS3-22761 ) The temperature compensation technique proposed for this application uses a resistance thermometer in an adjacent leg of N89-10016# Detroit Diesel Allison, Indianapolis, Ind. the strain gauge bridge circuit to cancel the thermally generated FORCED VIBRATION AND FLUTTER DESIGN METHODOLOGY resistance change of the strain gauge. Equations for calculating LYNN E. SNYDER and DONALD W. BURNS In AGARD, AGARD the required compensation resistor values and the sensitivity of Manual on Aeroelasticity in Axial-Flow Turbo Machines. Volume the resulting strain gauge bridge to both temperature and strain 2: Structural Dynamics and Aeroelasticity 28 p Jun. 1988 are presented. V.L. Avail: NTIS HC A12/MF A01 The aeroelastic principles and considerations of designing A89-12308" National Aeronautics and Space Administration. blades, disks, and vanes to avoid high cycle fatigue failure is covered. Two types of vibration that can cause high cycle fatigue, Lewis Research Center, Cleveland, Ohio. REGRESSED RELATIONS FOR FORCED CONVECTION HEAT flutter, and forced vibration, will first be defined and the basic TRANSFER IN A DIRECT INJECTION STRATIFIED CHARGE governing equations discussed. Next, under forced vibration design ROTARY ENGINE the areas of source definition, types of components, vibratory mode CHI M. LEE (NASA, Lewis Research Center, Cleveland, OH) and shape definitions, and basic steps in design for adequate high HAROLD J. SCHOCK (Michigan State University, East Lansing) cycle fatigue life will be presented. For clarification a forced vibration design example will be shown using a high performance SAE, International Congress and Exposition, Detroit, MI, Feb. turbine blade/disk component. Finally, types of flutter, dominant 29-Mar. 4, 1988. 12 p. Previously announced in STAR as N88-13345. refs flutter parameters, and flutter procedures and design parameters will be discussed. The overall emphasis is on application to initial (SAE PAPER 880626) Currently, the heat transfer equation used in the rotary design of blades, disks, and vanes of aeroelastic criteria to prevent combustion engine (RCE) simulation model is taken from piston high cycle fatigue failures. Author engine studies. These relations have been empirically developed by the experimental input coming from piston engines whose N89-10212# National Aerospace Lab., Amsterdam geometry differs considerably from that of the RCE. The objective (Netherlands). of this work was to derive equations to estimate heat transfer DIGITAL RECORDING OF RADAR DATA IN AN AIRCRAFT
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H. POUWELS 20 Jut. 1987 24 p In DUTCH; ENGLISH N89-10493# Department of National Defence, Ottawa (Ontario). summary Presented at Lecture Course on Digital Signal Processing Quality Engineering Test Establishment. for Realtime Applications, Utrecht, Netherlands, 27 Feb. 1986; ELECTROSTATIC DISCHARGE AND FIELD EFFECTS OF sponsored by NIRIA and KIVI ELECTRONICS SYSTEMS (PB88-209507; NLR-MP-86057-U) Avail: NTIS HC A03/MF A01 L. R. DICKS and G. MORIN In NOAA, International Aerospace CSCL 171 and Ground Conference on Lightning and Static Electricity p In the Netherlands, Side Looking Airborne Radar (SLAT) is 481-486 Apr. 1988 operated with a digital recording of the data. A description is Avail: NTIS HC A23/MF AQ1 CSCL 09C given of the airborne recording chain and of the ground based The effects of static electricity on modern electronics are processing. The airborne electronics for the digitizing, formatting discussed, as well as a comprehensive approach to electrostatic and recording of the radar data are described in detail. The system discharge (ESD) protection measures in all phases of the life cycle setup is tailored to the use of the SLAR as a research tool. of an electronic system. Static electricity has become a potential GRA source of damage to electronic systems used in most applications, including aircraft, ground and shipboard installations. Author N89-10474# Stringfellow and Associates, Atlanta, Ga. LIGHTNING AND SURGE PROTECTION OF LARGE GROUND N89-10497# Westinghouse Electric Corp., Baltimore, Md. FACILITIES SYSTEM PROTECTION FROM ATMOSPHERIC ELECTRICITY MICHAEL F. STRINGFELLOW In NOAA, International Aerospace FOR AEROSTATS WITH CONDUCTING TETHERS and Ground Conference on Lightning and Static Electricity p M. S. WHEELER, G. R. BEACH, P. R. JAKUBOWSKI, and F. A. 328-338 Apr. 1988 FISHER (Lightning Technologies, Inc., Pittstield, Mass.) In NOAA, Avail: NTIS HC A23/MF A01 CSCL 13B International Aerospace and Ground Conference on Lightning and The vulnerability of large ground facilities to direct lightning Static Electricity p 505-511 Apr. 1988 strikes and to lightning-induced overvoltages on the power Avail: NTIS HC A23/MF A01 CSCL 09C distribution, telephone and data communication lines are discussed. Aerostat power tethers have demonstrated survival of lightning Advanced electrogeometric modeling is used for the calculation strikes, IJut they usually have to be reterminated or replaced of direct strikes to overhead power lines, buildings, vehicles and afterward. Two requirements are given for the prevention of objects within the facility. Possible modes of damage, injury and lightning damage to the tether to about 100 kA: installation of a loss are discussed. Some appropriate protection methods for metal-to-metal contact on the outer tether surface to ground the overhead power lines, structures, vehicles and aircraft are tether at the base flying sheave at typical flying positions; and suggested. Methods to mitigate the effects of transients on installation of a shielding band within the outer tether jacket with overhead and underground power systems as well as within a weight of about 0.05 Ib/ft for a half-inch tether. This determination buildings and other structures are recommended. The specification was made in part by high current tests and in part by electrical and location of low-voltage surge suppressors for the protection modeling. Author of vulnerable hardware such as computers, telecommunication equipment and radar installations are considered. The advantages N89-11065# Joint Publications Research Service, Arlington, Va. and disadvantages of commonly used grounding techniques, such CASCADE FLOW ANALYSIS BY NAVIER-STOKES EQUATION as single point, multiple and isolated grounds are compared. An OSAMU NOZAKI In its JPRS Report: Science and Technology: example is given of the expected distribution of lightning flashes Japan p 18-20 4 Jun. 1987 Transl. into ENGLISH from to a large airport, its buildings, structures and facilities, as well as Kogiken Nyusu (Tokyo, Japan), Aug. 1986 p 7-10 to vehicles on the ground. Author Avail: NTIS HC A05/MF A01 As the performance of the large electronic computer has N89-10481# Office National d'Etudes et de Recherches improved, numerical simulation of the flow around the blade of Aeronautiques, Paris (France). the aircraft, for instance, is being actively conducted. In the THE SAFIR LIGHTNING MONITORING AND WARNING compressor and turbine cascades of aircraft engine, multiple blades SYSTEM, APPLICATIONS TO AEROSPACE ACTIVITIES are put side by side closely, and the pressure gradient in the flow P. RICHARD, A. SOULAGE, P. LAROCHE, and J. APPEL /n direction is large. Thus they have more complicated properties NOAA, International Aerospace and Ground Conference on than the independent blade. At present, therefore, it is the Lightning and Static Electricity p 383-390 Apr. 1988 mainstream to use potential, Euler's equation, etc., as the basic Avail: NTIS HC A23/MFA01 CSCL 13B equation but, for knowing the phenomenon caused by the viscosity A real-time lightning monitoring and warning system developed like the interference of shock waves and boundary layers, it is on the bases of recent advances in the field of lightning necessary to solve the Navier-Stokes (N-S) equation. A characterization are described. Applications and perspectives of two-dimensional cascade analysis program was developed by the the system are discussed, particularly applications for the field of N-S equation by expanding the two-dimensional high Reynolds aerospace safety. Author number transonic profile analysis code NSFOIL and the lattice formation program AFMESH for the independent blade, which were N89-10484# United Kingdom Atomic Energy Authority, Culham already developed so as to fit the cascade flow. Author (England). Lightning Studies Unit. A FILAMENTARY METHOD FOR CALCULATING INDUCED N89-11068# Joint Publications Research Service, Arlington, Va. VOLTAGES WITHIN RESISTIVE STRUCTURES IN EITHER THE NEW TRIAL OF VIBRATION TESTING METHOD FREQUENCY OR TIME DOMAIN TETSUHIK© UEDA In its JPRS Report: Science and Technology: C. J. HARDWICK, S. J. HAIGH, and B. J. C. BURROWS In Japan p 26-28 4 Jun. 1987 Transl. into ENGLISH from NOAA, International Aerospace and Ground Conference on Kogiken Nyusu (Toyko, Japan), Sep. 1986 p 3-4 Lightning and Static Electricity p 401-407 Apr. 1988 Avail: NTIS HC A05/MF A01 Avail: NTIS HC A23/MF A01 CSCL 09C A trial of a vibration testing method which will be used in the A program was developed to predict current distributions time domain is discussed. The vibration test is indispensable for resulting from a direct lightning strike to a structure of constant obtaining dynamically elastic characteristics of a structure. In cross section consisting of both metallic and composite conductors. particular, it is necessary to anticipate the flutter phenomenon The structure is represented by a set of filaments which are which will cause structural destruction on the wings of aircraft, assigned va(ues of both resistance and self inductance. The current fins of rockets, turbine blades of engines, etc. Therefore, the can be calculated in either the frequency or time domain; this identification of structural characteristics according to vibration tests current distribution then allows either the transfer impedance of plays an important role in this anticipation. The sine dwell method wires located within the structure or the induced voltage on these and transfer function method can be cited as methods being used wires as a function of time to be calculated. Author widely and presently in such vibration tests. The sine dwell method
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is used to search for resonance points, and the transfer function N89-11184# Centre d'Etudes et de Recherches, Toulouse method is used to process data mathematically in the frequency (France). Dept. d'Etudes et de Recherches en domain by using an fast Fourier transformation analyzer. The Aerothermodynamique. VATREM (vibration analysis in the time domain by the real STUDY OF THREE DIMENSIONAL BOUNDARY LAYERS ON eigenvalue method) is introduced. It is a new trial different from THE FRONT OF A FUSELAGE AND AT AN AIR INTAKE both of the above methods and can be regarded as a kind of [ETUDE DES COUCHES LIMITES TRIDIMENSIONNELLES SUR time domain method. Author POINTE AVANT DE FUSELAGE ET SUR ENTREE D'AIR] C. GLEYZES Dec. 1987 27 p In FRENCH (Contract AEROSPATIALE-11-000639) N89-11077"# Johns Hopkins Univ., Laurel, Md. Applied Physics Lab. (CERT-OA-22/5025-AYD; DERAT-22/5025-16; ETN-88-93107) Avail: NTIS HC A03/MF A01 RESULTS OF 1987 MSS HELICOPTER PROPAGATION EXPERIMENT AT UHF AND L BAND IN CENTRAL MARYLAND Solutions adopted to define grids adapted to calculation of the three-dimensional boundary layer on the nose of the fuselage of JULIUS GOLDHIRSH and WOLFHARD J. VOGEL (Texas Univ., a civil aircraft at low incidence in order to study laminar flow; and Austin.) In JPL, Proceedings of the 12th NASA Propagation at a subsonic air inlet at incidence, are outlined. Examples Experimenters Meeting (NAPEX 12) p 18-26 Aug. 1988 Avail: NTIS HC A09/MF A01 CSCL 20N corresponding to a nose in cryogenic wind tunnel conditions, and a model inlet at high incidence are presented. ESA This effort emphasizes several important results pertaining to a mobile satellite system propagation experiment performed in Central Maryland during June 1987. Fade distributions due to N89-11187# Centre d'Etudes et de Recherches, Toulouse multipath and roadside trees at L Band (1.5 GHz) during a period (France). Dept. d'Etudes et de Recherches en in which the deciduous trees were in full bloom are examined. Aerothermodynamique. The multipath statistics for roadside trees are compared with BOUNDARY LAYER TRANSITION [TRANSITION DE LA previous multipath measurements made in canyon terrain in North COUCHE LIMITE] Central Colorado. Also examined is the repeatability of previous D. ARNAL, J. C. JUILLEN, and F. VIGNAU Feb. 1988 37 p UHF measurements made in Central Maryland and the attenuation In FRENCH effects of foliage on trees at UHF. Fade duration for the multipath (Contract DRET-87-002-018) mode for fade levels of 5 dB and 10 dB is also presented. (CERT-OA-40/5018-AYD; DERAT-40/5018-24; ETN-88-93320) Author Avail: NTIS HC A03/MF A01 A calculation method including the effects of interaction between longitudinal and transversal instabilities on a delta wing is N89-11080"# Ministry of Posts and Telecommunications, Kashima presented. The results of calculations made to qualify the effects (Japan). Communications Research Lab. of wall cooling on a compressible laminar layer are also presented. ETS-V PROPAGATION EXPERIMENTS IN JAPAN The transition processes downstream of a backward facing step SHINGO OHMORI In JPL, Proceedings of the 12th NASA with and without wall aspiration are investigated. ESA Propagation Experimenters Meeting (NAPEX 12) p 47-54 Aug. 1988 Avail: NTIS HC A09/MF A01 CSCL 20N N89-11188# Air Force Inst. of Tech., Wright-Patterson AFB, Propagation experiments on ship, aircraft, and land mobile earth Ohio. stations were carried out using the Engineering Test Sateltite-V A COMPUTATIONAL STUDY OF COHERENT STRUCTURES IN lETS-V), which was launched in August 1987. The propagation THE WAKES OF TWO-DIMENSIONAL BLUFF BODIES M.S. experiments are one of the missions of the Experimental Mobile Thesis Satellite System (EMSS). initial experimental results of JEFFREY ALAN PEARCE Aug. 1988 138 p ETS-V/EMSS on propagation using ship, aircraft, and land mobiles lAD-A196820; AFIT/CI/NR-88-99) Avail: NTIS HC A07/MF A01 with ETS-V are given. Author CSCL 20D The periodic shedding of vortices from bluff bodies was first recognized in the late 1800's. Currently, there is great interest N89-11155"# Sandia National Labs., Albuquerque, N. Mex. Fluid concerning the effect of vortex shedding on structures and on and Thermal Sciences Dept. vehicle stability. In the design of bluff structures which will be CONTINUUM THEORIES FOR FLUID-PARTICLE FLOWS: exposed to a flow, knowledge of the shedding frequency and the SOME ASPECTS OF LIFT FORCES AND TURBULENCE amplitude of the aerodynamic forces is critical. The ability to DAVID F. MCTIGUE, RICHARD C. GIVLER, and JACE W. computationally predict parameters associated with periodic vortex NUNZIATO In NASA, Marshall Space Flight Center, Mixing and shedding is thus a valuable tool. In this study, the periodic shedding Demixing Processes in Multiphase Flows with Application to of vortices from several bluff body geometries is predicted. The Propulsion Systems p 15-31 Jul. 1988 Previously announced as N88-24898 study is conducted with a two-dimensional finite-difference code employed on various grid sizes. The effects of the grid size and (Contract DE-AC04-76DP-00789) time step on the accuracy of the solution are addressed. Strouhal Avail: NTIS HC A09/MF A01 CSCL 20D numbers and aerodynamic force coefficients are computed for all A general framework is outlined for the modeling of fluid particle of the bodies considered and compared with previous experimental flows. The momentum exchange between the constituents results. Results indicate that the finite-difference code is capable embodies both lift and drag forces, constitutive equations for which of predicting periodic vortex shedding for all of the geometries can be made explicit with reference to known single particle tested. Refinement of the finite-difference grid was found to give analysis. Relevant results for lift are reviewed, and invariant little improvement in the prediction; however, the choice of time representations are posed. The fluid and particle velocities and step size was shown to be critical. Predictions of Strouhal numbers the particle volume fraction are then decomposed into mean and were generally accurate, and the calculated aerodynamic forces fluctuating parts to characterize turbulent motions, and the generally exhibited behavior consistentwith previous studies. equations of motion are averaged. In addition to the Reynolds GRA stresses, further correlations between concentration and velocity fluctuations appear. These can be identified with turbulent transport processes such as eddy diffusion of the particles. When the drag N89-11189# Pennsylvania State Univ., University Park. Dept. force is dominant, the classical convection dispersion model for of Mechanical Engineering. turbulent transport of particles is recovered. When other interaction EXPERIMENTAL RESEARCH ON SWEPT SHOCK forces enter, particle segregation effects can arise. This is illustrated WAVE/BOUNDARY LAYER INTERACTIONS Annual Report, 1 qualitatively by consideration of turbulent channel flow with lift Apr. 1987 - 31 Mar. 1988 effects included, Author GARY S. SETTLES 28 Apr. 1988 58 p
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(Contract AF-AFOSR-0082-86; AF PROJ. 2307) crash loads. The airframe test section included a full complement (AD-A196938; PSU-ME-R-87/88-0031 ; AFOSR-88-0637TR) of seats and dummies. Acceleration and load/deflection response Avail: NTIS HC A04/MF A01 CSCL 20D measurements were obtained from the instrumented fuselage, floor This study of swept shock wave interactions with turbulent and seat/dummy installation. Author boundary layers relied entirely on non-intrusive, laser-based optical flow diagnostics. Experiments were carried out to define the N89-11270 Columbia Univ., New York, N.Y. flowfield structure of fin-generated interactions over a Math number RESPONSE OF DISCRETELY STIFFENED STRUCTURES AND range 2.5 to 3.5 using the laser light-screen flow visualization TRANSMISSION OF STRUCTURE-BORNE NOISE Ph.D. Thesis technique. Further experiments resulted in accurate skin friction CONSTANTINOS SOTIRIO LYRINTZIS 1987 81 p measurements in fin-generated swept interactions by way of the Avail: Univ. Microfilms Order No. DA8809385 Laser Interferometer Skin Friction Meter. Techniques were An analytical study is presented to predict the dynamic response perfected for the assessment of flowfield fluctuation levels using and structure-borne noise generation and transmission of complex pulsed-laser holographic interferometry. The results of this research discretely stiffened and interconnected structures under random have given new insight into the fin-interaction flowfield structure, loads. The method is based on transfer matrices for the structural which involves a supersonic jet produced by shock wave refraction response and on modal decomposition for the interior acoustic and impinging on the test surface. High skin friction levels were field. The acoustic enclosure is taken to be rectangular in shape measured in the vicinity of this jet impingement, which compare of which a portion of the boundaries is elastic while the remaining well with computational predictions carried out by others. Finally, surface is acoustically rigid. This formulation can be used for the the observed jet impingement structure is shown to be similar to response and structure-borne noise generation studies in space that of leading-edge shock wave impingement on high-speed flight station and aircraft structures. Numerical results are presented for vehicles. GRA a variety of acousto-structural problems. It is found that this approach permits easy parametric evaluation and that through N89-11192"# General Electric Co., Cincinnati, Ohio. Advanced proper selection of structural parameters, loading conditions and Technology Operation. acoustic characteristics, the vibration response and noise SENSORS FOR CERAMIC COMPONENTS IN ADVANCED transmission can be reduced. Dissert. Abstr. PROPULSION SYSTEMS: SUMMARY OF LITERATURE SURVEY AND CONCEPT ANALYSIS, TASK 3 REPORT N89-11286# Institut de Mecanique des Fluides de Lille (France). W. H. BENNETHUM and L. T. SHERWOOD Aug. 1988 108 p Groupe Mecanique des Structures. (Contract NAS3-25140) AIRCRAFT CRASHES ON THE RUNWAY: DEVELOPMENT OF (NASA-CR-180900; NAS 1.26:180900) Avail: NTIS HC A06/MF A SUPER ELEMENT FOR NONLINEAR ANALYSIS OF A BEAM A01 CSCL 14B [CRASH DES AVIONS SUR PISTE: DEVELOPPEMENT D'UN The results of a literature survey and concept analysis related SUPER-ELEMENT POUR L'ANALYSE NON LINEAIRE D'UNE to sensing techniques for measuring of surface temperature, strain, POUTRE ] and heat flux for (non-specific) ceramic materials exposed to P. GEOFFROY 15 Dec. 1987 35 p In FRENCH elevated temperatures (to 2200 K) are summarized. Concepts (Contract DRET-85-003) capable of functioning in a gas turbine hot section environment (REPT-87/56; ETN-88-93101) Avail: NTIS HC A03/MF A01 are favored but others are reviewed also. Recommendation are A thin shell super finite element was developed to study the made for sensor development in each of the three areas. pre and post elastoplastic buckling behavior of an embedded beam Author subject to a lateral load. The finite element is derived from a local behavior law analogous in its form to the law of the global N89-11196"# Wyle Labs., Inc., Hampton, Va. behavior of the structure. Analysis results and quasi-static and ELECTRICAL NOISE REDUCTION TECHNIQUES dynamic tests on reduced scale models of aircraft structures were CONTRIBUTING TO IMPROVED DATA QUALITY AT THE compared. This element alone cannot be a solution to the response. NATIONAL TRANSONIC FACILITY It is necessary to simultaneously introduce into the finite element J. R. MCPHEE Nov. 1988 38 p model extra degrees of freedom to represent the plastic joints, (Contract NAS1-18304) and to restrain the displacement of the super element nodes to (NASA-CR-4193; NAS 1.26:4193) Avail: NTIS HC A03/MF A01 be representative of the real displacements of the structure. By CSCL 09C replacing a large part of a structure by a large element, specific In initial use, the high-speed digital data acquisition systems at to a given behavior, computation time is considerably reduced. Langley Research Center's National Transonic Facility produced ESA data containing unacceptably high noise levels. Described is a process whereby the contributing noise sources were identified and eliminated. The effects of 60 Hz power, system grounding, 13 EMI/RFI, and other problems are discussed and the corrective action taken is outlined. The overall effort resulted in an improvement of greater than 5:1 in system performance. Although GEOSCIENCES the report describes a system specifically used for wind tunnel data acquisition, the corrective techniques employed are generally Includes geosciences (general); earth resources; energy production applicable to large scale high-speed data systems where signal and conversion; environment pollution; geophysics; meteorology resolution in the low microvolts range is important. Author and climatology; and oceanography.
N89-11265# Federal Aviation Agency, Atlantic City, N.J. LONGITUDINAL IMPACT TEST OF A TRANSPORT AIRFRAME A89-11221 SECTION Final Report, Feb.- Oct, 1987 STRUCTURE AND LIFE CYCLE OF MICROBURST OUTFLOWS BARRY WADE and RICHARD JOHNSON (Transportation Research OBSERVED IN COLORADO Center of Ohio, East Liberty.) Jul. 1988 286 p MARK R. HJELMFELT (National Center for Atmospheric Research, (Contract DTFA03-87-C-00013) Boulder, CO) Journal of Applied Meteorology (ISSN 0894-8763), (DOT/FAA/CT-87/26) Avail: NTIS HC A13/MF A01 vol. 27, Aug. 1988, p. 900-927. Research supported by the National The results of longitudinally impact testing a 10-foot section of Center for Atmospheric Research and NSF. refs a transport airplane at peak acceleration and corresponding velocity (Contract DOT-FA01-82-Y-10513) changes of 7.4 g (22.4 ft/sec) and 14.2 g (36 ft/sec), respectively Observations by Doppler radars and a surface meteorological are reported. The purpose of the tests was to measure the network are used to analyze the morphology of microburst outflows responses of the fuselage and floor structure to simulated dynamic in Colorado. The microburst outflows are classified into individual
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microbursts and microburst lines, and examples of each type are temperature, precipitation, turbulence, and peak and average presented. It is shown that microburst lines have longer lifetimes, electromagnetic values will be available. It is also anticipated that larger areas of divergence, and can create a greater potential for digitized waveforms will be available. Author hazard to aircraft than isolated microburst. Outflow structure was found to resemble features of the laboratory wall jet. Studies of microburst symmetry, as measured across the maximum velocity N89-10438"# Electro Magnetic Applications, Inc., Lakewood, differential, show that the minimum shear is only about 60 percent Colo. of the maximum. R.B. TRIGGERING OF LIGHTNING BY THE ATLAS CENTAUR VEHICLE A89-11554 RODNEY A. PERALA and TERENCE H. RUDOLPH In NOAA, A NUMERICAL ESTIMATION OF THE DEFORESTATION International Aerospace and Ground Conference on Lightning and EFFECTS ON LOCAL CLIMATE IN THE AREA OF THE Static Electricity p 47-57 Apr. 1988 Previously announced in FRANKFURT INTERNATIONAL AIRPORT IAA as A88-22290 Sponsored in part by NASA. Langley Research G. GROSS (Darmstadt, Technische Hochschule, Federal Republic Center Avail: NTIS HC A23/MF A01 CSCL 04B of Germany) Beitraege zur Physik der Atmosphaere (ISSN 0005-8173), vol. 61, Aug. 1988, p. 219-231. refs The triggering of lightning by in-flight vehicles is investigated. Specific attention is placed on the NASA F-106B Thunderstorm Research Aircraft and the Atlas-Centaur vehicle involved in the N89-10429# National Oceanic and Atmospheric Administration, 1987 AC-67 failure. Thunderstorm and vehicle parameters relevant Rockville, Md. to triggered lightning initiation are identified. A numerical simulation INTERNATIONAL AEROSPACE AND GROUND CONFERENCE technique suitable for application to triggered lightning events is ON LIGHTNING AND STATIC ELECTRICITY discussed. Results from this model's use in the F-106B program Apr. 1988 535 p Conference held in Oklahoma City, Okla., are shown and compared to measured data from actual lightning 19-22 Apr. 1988 strikes to the aircraft. Issues unique to the Atlas-Centaur incident (PB88-197439) Avail: NTIS HC A23/MF A01 CSCL 04B are presented. The results consist of currents and current time Various topics related to lightning and static electricity are derivatives on the vehicle as a function of time. Derived ambient discussed. Aircraft strike statistics, lightning propagation models, electric fields at the altitude of the lightning incident are compared aerospace vehicles, simulation, aircraft hazards rocket launch with ground based electric field measurements. Finally, questions hazards, thunderstorms, lightning detection and protection, and still unresolved in the physics of triggered lightning are identified. mapping systems are among the topics covered. Author
N89-10430# Tohoku Univ., Sendal (Japan). Dept. of Electrical Engineering. N89-10443# SRI International Corp., Menlo Park, Calif. STATISTICS OF LIGHTNING INTERACTION WITH AIRCRAFT AN AIRCRAFT-BORNE ELECTRIC FIELD MEASURING IN JAPAN SYSTEM FOR ROCKET LAUNCH SUPPORT YUKtHIRO GOTO and YOSHIHIRO MUROOKA (National Defence JOSEPH E. MANEVICZ, JEFFREY S. THAYER, and HUGH Academy, Yokosuka, Japan ) In NOAA, International Aerospace HERITAGE (Aerospace Corp., Los Angeles, Calif.) /n NOAA, and Ground Conference on Lightning and Static Electricity p 1-7 International Aerospace and Ground Conference on Lightning and Apr. 1988 Static Electricity p 87-93 Apr. 1988 Avail: NTIS HC A23/MF A01 CSCL 04B Avail: NTIS HC A23/MF A01 CSCL 04B A survey of lightning interaction with commercial aircraft in A new field measuring system and associated instrumentation Japan for the past 10 years is given. Aircraft flight conditions installed on a NASA 705 Learjet to be flown into a region of a during lightning strikes and concomitant synoptic weather which rocket launch trajectory to verify meteorological and electric field were reported by flight crews were correlated as a percentage of conditions relative to lightning strike potential are discussed. The the total number of strikes reported in Japan. Author new system is based on an earlier system used for the support of the Apollo/Soyuz and Viking launches. The outputs from a set N89-10431# Chelton (Electrostatics) Ltd., Marlow (England). of four field meters installed in the skin of the vehicle are fed to ISRAEL AIR FORCE (IAF) IN-SERVICE AIRCRAFT LIGHTNING a real-time analog processor that yields the three components of STRIKE AND DAMAGE SURVEY free-space electric field and aircraft potential. The system also ELYA B. JOFFE In NOAA, International Aerospace and Ground records aircraft navigational parameters and time to permit the Conference on Lightning and Static Electricity p 8-12 Apr. 1988 data to be correlated with other measurements. Author Avail: NTIS HC A23/MF A01 CSCL 04B A survey of lightning strikes to aircraft, covering all types of aircraft (tactical fighters, transport aircraft and helicopters), is given. N89-10444# Airborne Research Associates, Weston, Mass. The survey results include descriptive data on each strike and the NEW ELECTRIC FIELD INSTRUMENTATION AND THE effects. A lightning strike in which an F-16 was struck while in EFFECTS OF SPACE CHARGE AT KENNEDY SPACE CENTER flight is discussed. Some basic problems arising from new RALPH MARKSON and BRUCE ANDERSON In NOAA, requirements for lightning protection are discussed. Author International Aerospace and Ground Conference on Lightning and Static Electricity p 94-102 Apr. 1988 N89-10432# Computer Resource Management, Inc., Atlantic Avail: NTIS HC A23/MF A01 CSCL 04B City, N.J. A program is being conducted to develop low power LIGHTNING INFORMATION DATABASE consumption electric field sensors for installation at remote sites, R. L. MCDOWALL and MICHAEL S. GLYNN (Federal Aviation where there is no ac power, in order to expand the aerial coverage Agency, Atlantic City, N.J.) In NOAA, International Aerospace of the lightning warning network. Both radioactive probe and corona and Ground Conference on Lightning and Static Electricity p 13-15 current instruments are being considered. In addition, the layer of Apr. 1988 space charge which develops over land (due to corona) and water Avail: NTIS HC A23/MF A01 CSCL 04B (due to electrode effect) when thundercloud electric fields are The Federal Aviation Administration (FAA) is creating a data present are being investigated since it strongly affects electric base of electromagnetic information on lightning. A number of field measurements made close to the ground. The space charge sources of information have been identified and an attempt to layer is being studied through horizontal and vertical profiles acquire and centrally locate the data is being pursued. The data obtained from an instrumented aircraft as well as an electrosonde will ultimately be available to general researchers. In certain cases which is raised and lowered through the space charge layer by a on-line access to database peripheral information such as altitude, tethered balloon system. Author
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N89-10447# National Research Council of Canada, Ottawa thunderstorms is shown to be a systematic precurser to the (Ontario). Div. of Electrical Engineering. maximum outflow velocity at ground level. The time of peak flash A CASE FOR A UNIFIED LIGHTNING THREAT rate leads the time of maximum differential velocity by 5 to 10 ANDREW S. PODGORSKI In NOAA, International Aerospace minutes. The consistent temporal relationship between the and Ground Conference on Lightning and Static Electricity p electrical phenomenon (lightning rate) and the dynamical 118-122 Apr. 1988 phenomenon (the microburst) is attributed to a common cause - Avail: NTIS HC A23/MF A01 CSCL 04B ice particles aloft. Author For the first time a unified set of lightning parameters that can describe the lightning measured at the ground or on towers or airplanes is proposed. This set of parameters can be used to accurately predict the electromagnetic fields generated by lightning. The new set of lightning parameters was obtained from the lightning current measurements conducted at the CN Tower during the 1986 lightning seasons. The measured currents were compensated for the presence of the tower. Author N89-10499# National Oceanic and Atmospheric Administration, N89-10449# Office National d'Etudes et de Recherches Boulder, Colo. Environmental Sciences Group. Aeronautiques, Paris (France). OKLAHOMA-KANSAS PRELIMINARY REGIONAL SUMMARY OF INFLIGHT DATA ON LIGHTNING CURRENTS EXPERIMENT FOR STORM-CENTRAL (O-K PRE-STORM). AND FIELDS VOLUME 3: AIRCRAFT MISSION SUMMARY J. P. MOREAU, J. M. REAZER, and P. L. RUSTAN (Defense JOSE G. MEITIN, JR. Feb. 1988 112 p Nuclear Agency, Washington, D.C.) In NOAA, International (PB88-205489; NOAA-TM-ERL-ESG-30-VOL-3) Avail: NTIS HC Aerospace and Ground Conference on Lightning and Static A06/MF A01 CSCL 04B Electricity p 129-135 Apr. 1988 Researchers are provided with a synopsis of the flights taken Avail: NTIS HC A23/MF A01 CSCL 04B during May and June of 1985 as part of the Oklahoma-Kansas The peak amplitudes, risetimes and repetition rates of the Preliminary Regional Experiment for STORM-Central (PRE- current and electromagnetic field pulses measured during lightning STORM). This is the final report in a series which describes strikes to a two-engine turbo prop CV-580 aircraft are discussed. the activities and catalogs the data collected during the field phase The .5 Hz to 500 kHz electric field variations recorded in the of the PRE-STORM project. The principal goals of the aircraft aircraft during lightning strikes are summarized. Finally, the current subprogram were to: (1) gather aircraft data in the vicinity of and electric field variations measured in the aircraft are compared developing and mature convective systems in order to better define with those in the MIL-STD-1757A and the newly recommended their structure, evolution, and physical processes, and (2) develop draft advisory circular for the SAE committee AE4L-87-3. Author and test observational strategies for optimal use of long range research aircraft in the mesoscale convective system (MCS) N89-10470# Mississippi Univ., University. Dept. of Physics. environment in order to help define measurement techniques, for THE ELECTRICAL STRUCTURE OF THUNDERSTORM ANVILS example, the use of airborne Doppler radar in coordination with THOMAS C. MARSHALL, W. DAVID RUST, WILLIAM P. WlNN, ground based Doppler radars. Author and KENNETH E. GILBERT (National Center for Physical Acoustics, University, Miss.) In NOAA, International Aerospace and Ground Conference on Lightning and Static Electricity p 303-309 Apr. 1988 Avail: NTIS HC A23/MF A01 CSCL 04B Two electric field soundings through thunderstorm anvil clouds show similar charge structures; negatively charged screening layers on top and bottom surfaces, a layer of positive charge on the interior, and one or two layers of zero charge. Both anvil clouds N89-11356# Federal Aviation Agency, Atlantic City, N.J. were strongly electrified; the peak magnitudes of the electric field EVALUATION OF ENHANCEMENTS TO THE LOW LEVEL in the two storms were 70 and 90 kV/m (so, aircraft penetrating WIND SHEAR ALERT SYSTEM (LLWAS) AT STAPLETON anvil thunderstorms run no risk of triggering lightning flashes). INTERNATIONAL AIRPORT Final Report, Jul. 1987 - Mar. 1988 The non-zero layers had charge densities comparable to those JOHN D. BARAB, RICHARD D. PAGE, BRUCE L. ROSENBURG, found in storm cores, ranging in magnitude from 0.4 to 2.7 nC/m THOMAS E. ZURINSKAS, and GLENN R. SMYTHE (Data cubed. The layers ranged in thickness from 300 to 2000m. The Transformation Corp., Silver Spring, Md.) Aug. 1988 164 p positive charge probably originated in the main positive charge (Contract T12-02Z) region normally found at high altitudes in the core of thunderstorms. (DOT/FAA/PS-88/14; DOT/FAA/CT-88/6) Avail: NTIS HC The removal of the positive charge from the storm's core to the A08/MF A01 anvil may influence the ratio of intra-cloud to cloud-to-ground An operational test and evaluation of enhancements to the lightning flashes and the rate of generation of charge in the core. 11-station Low Level Wind Shear Alert System (LLWAS) at The negatively conducting layers were probably screening layers Stapleton International Airport, Denver, Colorado was conducted resulting from the discontinuity in the electrical conductivity at the during the period August 3 to September 4, 1988. Enhancements cloud boundaries. The lower negative screening layer appeared included a 12th remote station for gathering wind data, a more to be carried toward the storm's core by winds below and at the sophisticated wind shear microburst detection (WSMD) algorithm, lower anvil boundary. Author a Digital Equipment Corporation (DEC) PDP 11-73 computer, a DEC VT-240 Cathode Ray Tube (CRT) Display, and an LLWAS N89-10490# Massachusetts Inst. of Tech., Cambridge. Dept. of message display format, the latter two for local, controller use in Earth, Atmospheric and Planetary Sciences. the air traffic control (ATC) tower cab. Two sets of objectives INTRACLOUD LIGHTNING AS A PRECURSOR TO were associated with this LLWAS evaluation: meteorological and THUNDERSTORM MICROBURSTS human factors objectives. The methodology and dual scientific E. R. WILLIAMS and R. E. ORVILLE (State Univ. of New York, analyses performed were discussed, and detailed results with Albany.) In NOAA, International Aerospace and Ground conclusions and recommendations were provided. Based on the Conference on Lightning and Static Electricity p 454-459 Apr. conclusions, it was recommended that the WSMD algorithm remain 1988 as an operational constituent of the Denver LLWAS and that human Avail: NTIS HC A23/MF A01 CSCL 04B factors considerations be further explored in improving the The intracloud lightning activity of microburst-producing controller LLWAS interface. Author
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14 consists of color graphics image processing hardware and software, as welt as high-resolution display and optical components. The LIFE SCIENCES flexibility and fideity with which CMD images can be simulated permit a wide variety of CMD hardware and information format issues to be addressed. Author Includes life sciences (general); aerospace medicine; behavioral sciences; man/system technology and life support; and planetary A89--11680# biology. MODAL OBSERVABILITY AND CONTROLLABILITY MEASURES FOR FIRST AND SECOND ORDER LINEAR SYSTEMS AND MODEL REDUCTION A89-10589 A. M. A. HAMDAN and A. H. NAYFEH (Virginia Polytechnic Institute TEAS - AN AL BASED THREAT RESPONSE and State University, Blacksburg) IN: Dynamics and control of RECOMMENDATION SYSTEM large structures; Proceedings of the Sixth VPI&SU/AIAA KEITH DRAKE and STEVE ROTHSTEIN (USAF, Wright-Patterson Symposium, Blacksburg, VA, June 29-July 1, 1987. Blacksburg, AFB, OH) IN Aerospace Behavioral Engineering Technology VA, Virginia Polytechnic Institute and State University, 1988, p. Conference, 6th, Long Beach, CA, Oct. 5-8, 1987, Proceedings. 453-475. refs Warrendale, PA, Society of Automotive Engineers, Inc., 1988, p. New measures of modal controllability and observability are 115-120. refs proposed for the linear time-invariant representation of a dynamic (SAE PAPER 871804) system. Gross measures of controllability of a mode from all inputs In the future fighter combat environment, the pilot will be faced and gross measures of observability of a mode in all outputs are with increased workload as he is forced to integrate various also proposed. A closed-form expression relating the norm of the on-board sensor, weapons, and other aircraft systems. Specifically, residue matrix and the proposed gross measures of modal he has less time to react to incoming missiles because of increased controllability and observability is presented, and it is shown that missile and aircraft speeds. The Air Force's Threat Expert Analysis the measures proposed here are directly applicable to second-order System (TEAS) will determine and recommend threat responses models. Possible applications of the measures include large space to the pilot using all available resources. The system will do much structures. V.L. of the data integration for the pilot, thereby reducing his workload. This paper reviews the approach being taken in the TEAS program A89-11748 development. Author THE SYMBOLICS SCOPE SYSTEM AS A PLATFORM FOR ENVIRONMENTAL ANALYSIS A89-10593 BRIAN P. BAUER and THOMAS STANZIONE (Symbolics, Inc., SHOULD TECHNOLOGY ASSIST OR REPLACE THE PILOT? Cambridge, MA) "IN: Digital image processing and visual S. R. LAST (international Federation of Air Line Pilots Associations, communications technologies in meteorology; Proceedings of the Egham, England) IN: Aerospace Behavioral Engineering Meeting, Cambridge, MA, Oct. 27, 28, 1987. Bellingham, WA, Society Technology Conference, 6th, Long Beach, CA, Oct. 5-8, 1987, of Photo-Optical instrumentation Engineers, 1987, p. 135-155. Proceedings. Warrendale, PA, Society of Automotive Engineers, Research supported by Symbolics, Inc. refs Inc., 1988, p. 151-155. The paper describes the design and functionality of the SCOPE (SAE PAPER 880774) system, an image and symbolic computer that manages complexity This paper presents a survey of computer technology and can perform goal-directed processing. SCOPE is an integrated applications in transport aircraft and examines the direction and workstation consisting of a Symbolics Lisp Machine and PIXAR impact of automation on the flight deck. In particular, an attempt Image Computer. The SCOPE system provides a platform for the is made to answer the question of whether or not the automation rapid manipulation and display of meteorological data in the context technology is leading the way for the development of pilotless of a knowledge processing system. As an example, SCOPE is aircraft. It is suggested that, if the human pilot is to remain in currently in operation at an experimental Doppler radar facility for control of aircraft operations, there are some trends in the design the analysis and forecasting of microburst phenomena around an of both hardware and software which need modification and/or airport. The SCOPE system is using an expert system for the reversal. These trends are discussed. I.S. analysis of wind shear and wind-flow information to evaluate the potential for hazards to aviation from microbursts on a real-time basis. B.J. 15 A89-11750 RULE-BASED STRING CODE PROCESSOR MATHEMATICAL AND COMPUTER SCIENCES DAVID CASASENT and SUNG-IL CHIEN (Carnegie-Melton University, Pittsburgh, PA) IN: Intelligent robots and computer Includes mathematical and computer sciences (general); computer vision; Proceedings of the Meeting, Cambridge, MA, Nov. 2-6, operations and hardware; computer programming and software; 1987. Bellingham, WA, Society of Photo-Optical Instrumentation computer systems; cybernetics; numerical analysis; statistics and Engineers, 1988, p. 2-12. USAF-supported research, refs probability; systems analysis; and theoretical mathematics. A new and efficient real-time technique to produce a string code description of the contour of an object, such as an (angle, length) = (phi, s) feature space for the arcs describing the contour, A89-10584 is detailed. The use of such a description for an aircraft identification IMAGE QUALITY AND VISUAL SIMULATION OF COLOR problem case study is demonstrated. The (phi, s) feature space is MATRIX DISPLAYS modified to include a length string code and a convexity string LOUIS D. SILVERSTEIN, ROBERT W. MONTY, JERRY W. HUFF, code. This feature space allows both global and local feature and KEITH L. FROST (Honeywell Systems and Research Center, extraction. The local feature extraction follows human techniques and is thus quite suitable for a rule-based processor. Aircraft have Minneapolis, MN) IN: Aerospace Behavioral Engineering Technology Conference, 6th, Long Beach, CA, Oct. 5-8, 1987, generic parts and thus are quite suitable for the model-based Proceedings. Warrendale, PA, Society of Automotive Engineers, description. Author Inc., 1988, p. 71-76. refs (SAE PAPER 871789) A89-11760 A color matrix display (CMD) image simulation system has been A HIERARCHICAL CONTROL STRATEGY FOR 2-D OBJECT developed to support human factors research leading to design RECOGNITION specifications for CMD visual parameters. The simulation system MARK F. CULLEN (Perkin-Elmer Corp., New Haven, CT),
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CHRISTOPHER L. KUSZMAUL, and TIMOTHY S. RAMSEY IN: A89-12413# Intelligent robots and computer vision; Proceedings of the Meeting, PI - AN AI APPROACH FOR MAINTENANCE AND Cambridge, MA, Nov. 2-6, 1987. Bellingham, WA, Society of DIAGNOSTIC APPLICATIONS Photo-Optical Instrumentation Engineers, 1988, p. 220-224. THOMAS A. DUBOIS, WALTER T. STECKLAIR, and GREGORY A control strategy for two-dimensional object recognition has W. SAUL (Boeing Co., Boeing Computer Services Div., Seattle, been implemented on a hardware configuration which includes a WA) IN: Automation applications for rotorcraft; Proceedings of Symbolics Lisp Machine as a front-end processor to a 16,384 the National Specialists' Meeting, Atlanta, GA, Apr. 4-6, 1988. processor Connection Machine (CM). The goal of this ongoing Alexandria, VA, American Helicopter Society, 1988, 10 p. refs research program is to develop an image analysis system as an The Boeing Pi system is an AI approach for the maintenance aid to human image interpretation experts. Efforts have and diagnosis of complex multicomponent systems. Pi incorporates concentrated on two-dimensional object recognition in aerial maintenance and diagnostic knowledge sources that are common imagery specifically, the detection and identification of aircraft near to applications within this domain. It implements existing AI the Danbury, CT airport. This paper reports on the integration of techniques to minimize the cost of diagnosing complex systems. algorithms on the CM, with a hierarchical control strategy to focus The Pi software architecture is suitable for installation on a and guide the object recognition task to particular objects and man-portable unit for use by maintenance personnel in the field. regions of interest in imagery. It is shown that these techniques Author may be used to manipulate imagery on the order of 2k x 2k pixels in near-real-time. Author N89-10524"# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A89-12176 ON THE DIAGNOSTIC EMULATION TECHNIQUE AND ITS USE COPING WITH LEGACY FACTORS IN THE AIRLAB D. L. BUNDY and J. A. WEISS (McDonnell Aircraft Co., Saint GERARD E. MIGNEAULT Oct. 1988 28 p Louis, MO) Engineering with Computers (ISSN 0177-0667), vol. (NASA-TM-4027; L-16397; NAS 1.15:4027) Avail: NTIS HC 4, no. 1-2, 1988, p. 11-17. A03/MF A01 CSCL 09B Implementers of engineering data base management systems An aid is presented for understanding and judging the relevance inherit a legacy of existing software and data that must be integrated of the diagnostic emulation technique to studies of highly reliable, into the new system with minimum disruption of ongoing activities. digital computing systems for aircraft. A short review is presented Some critical issues addressed here include changes in software of the need for and the use of the technique as well as an engineering practices, impact on user training and procedures, explanation of its principles of operation and implementation. and problems connected with traditional or parochial interests. Details that would be needed for operational control or modification The material covered describes some experiences in coping with of existing versions of the technique are not described. Author these 'legacy factors' during the recent McDonnell Aircraft Company (MCAIR) integrated data base implementation. Author N89-10526"# Lockheed-Georgia Co., Marietta. HARDWARE FAULT INSERTION AND INSTRUMENTATION A89-12405# SYSTEM: EXPERIMENTATION AND RESULTS A TACTICS EXPERT SYSTEM FOR SCOUT/ATTACK J. W. BENSON, D. B. MULCARE, and W. E. LARSON Mar. ROTORCRAFT 1987 80 p Prepared for FAA, Atlantic City, N.J. EDDIE J. TRUJILLO and CHARLES D. HOLLEY (Bell Helicopter (Contract NAS2-11853) Textron, Fort Worth, TX) IN: Automation applications for rotorcraft; (NASA-CR-182746; NAS 1.26:182746; AD-A189863; Proceedings of the National Specialists' Meeting, Atlanta, GA, Apr. DOT/FAA/CT-86/34) Avail: NTIS HC A05/MF A01 CSCL 01D 4-6, 1988. Alexandria, VA, American Helicopter Society, 1988, 10 This report describes the motivation, conduct, and analysis of p. refs some 2500 low-level hardware fault cases applied in automated An examination is conducted of the 'depth' of knowledge and testing at the NASA Ames Reconfigurable Digital Flight Control supporting data required for the automation of military rotorcraft System (RDFCS) Facility. Fault detection was correlated with crew tasks in a sophisticated antiaircraft threat environment; the hardware and software fault monitoring, and in limited cases, with AI and expert system technologies that have been proposed are sensitivity to flight program execution modes. Results obtained charged with the reduction of cockpit workloads while enhancing have been statistically assessed to ascertain system-level reliability mission effectiveness. The expert system software prototype implications based on a model that is described herein. The overall presently developed assists rotorcraft crews with the selection of methodology/facility itself has been critiqued and found to target observation and firing positions. While the overall system constitute a promising enhancement to current practice. GRA executes in C, supporting graphics functions were developed with FORTRAN and DISSPLA graphics software. O.C. N89-10563# National Aerospace Lab., Tokyo (Japan). GENERATION OF A GRID FOR A FINITE DIFFERENCE A89-12410# CALCULATION OF FLOWS AROUND AN AIRCRAFT IN REASONING ABOUT DEVICE BEHAVIOR USING CARTESIAN COORDINATES QUALITATIVE PHYSICS 1987 18 p In JAPANESE; ENGLISH summary T. P. HAMILTON (United Technologies Research Center, East (NAL-TR-956; ISSN-0389-4010) Avail: NTIS HC A03/MF A01 Hartford, CT) and C. JACOBSEN (United Technologies Corp., The generation of a grid for an infinite difference calculation Sikorsky Aircraft Div., Stratford, CT) IN: Automation applications of flows around an aircraft in Cartesian coordinates is examined. for rotorcraft; Proceedings of the National Specialists' Meeting, The main equations governing the generation are plane and line Atlanta, GA, Apr. 4-6, 1988. Alexandria, VA, American Helicopter equations in the three-dimensional field. The external form of the Society, 1988, 16 p. refs aircraft is shaped from a large number of small triangular planes. A computer program has been developed which reasons about The grid is formed by three groups of lines perpendicularly the behavior of devices using qualitative models of their structure intersecting each other. The quantitative relations between the and function. The ultimate goal of this qualitative reasoning system external form of the aircraft and points of tl4e grid are obtained is to provide a general method for representing and reasoning by algebraic treatment of the plane and line equations. In the about behavior throughout a device's life cycle. Current capabilities same manner, views of the aircraft are drawn using these of the system include reasoning about the normal behavior of a equations. Author device, detection of abnormal behavior, and diagnosis of failure without prior knowledge of the device's failure modes. A tool to N89-10565# National Aerospace Lab., Tokyo (Japan). assist in construction of hierarchical qualitative models has also PROGRAMMING TECHNIQUES FOR HIGH-SPEED been developed. Applications of qualitative reasoning under PROCESSING ON THE SUPERCOMPUTER FUJITSU development are described. Author VP-SYSTEM
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MASAHIRO YOSHIDA, KINUYO NAKAMURA, KEIICHIRO UCHIDA, 16 and YOSHIYUKI TANAKURA 1986 78 p In JAPANESE; ENGLISH summary PHYSICS (NAL-TR-915; ISSN-0389-4010) Avail: NTIS HC A05/MF A01 Various methods of effective FORTRAN programming for supercomputers are presented. These programming methods are Includes physics (general); acoustics; atomic and molecular designed to increase vectorization rates and to facilitate high-speed physics; nuclear and high-energy physics; optics; plasma physics; processing of FORTRAN programs. The methods were used to solid-state physics; and thermodynamics and statistical physics. improve the following NAL application software packages: the FVMCAS program for analyzing inviscid compressible flow through three-dimensional cascades and the USTF3 program for unsteady transonic potential flow over oscillating three-dimensional wings. A89-10112"# United Technologies Corp., Windsor Locks, Conn. The vectorized codes are executed on the supercomputer FUJITSU RESULTS OF ACOUSTIC TESTS OF A PROP-FAN MODEL VP-400. Computing times compared with those of the odginal F. B. METZGER and P. C. BROWN (United Technologies Corp., programs show the excellent usefulness of the vectorizing Windsor Locks, CT) Journal of Aircraft (ISSN 0021-8669), vol. methods. Author 25, July 1988, p. 653-658. Previously cited in issue 20, p. 3285, Accession no. A87-45282. (Contract NAS3-24222)
A89-11101# N89-10833# Electronique Serge Dassautt, St. Cloud (France). ACOUSTICS OF TRANSONIC BLADE-VORTEX INTERACTIONS A HIGHLY RELIABLE COMPUTER FOR AIRBORNE A. R GEORGE and A. S. LYRINTZIS (Cornetl University, Ithaca, APPLICATIONS NY) AIAA Journal (ISSN 0001-1452), vol. 26, July 1988, p. MICHEL MUENIER In AGARD, Computing Systems Configuration 769-776. Research supported by the McDonnell Douglas Helicopter for Highly Integrated Guidance and Control Systems 17 p Jun. Co. Previously cited in issue 22, p. 3337, Accession no. 1988 A86-45476. refs Avail: NTIS HC A08/MF A01 The reliability features of the CMF (French Military Computer) AIR embedded computer supporting its operational software are A89-11102# described. This computer was designed to meet the requirements NOISE FIELD OF A PROPELLER WITH ANGULAR INFLOW of the ACE (European Combat Aircraft)/RAFALE D aircraft. R. STUFF (University of Petroleum and Minerals, Dhahran, Saudi Therefore, it has to be highly dependable to satisfy severe physical Arabia) AIAA Journal (ISSN 0001-1452), vol. 26, July 1988, p. requirements (size, weight, power consumption, etc.) and to support 777-782. refs real-time software execution (this software being written in The propeller blade forces are replaced by doublet and high-level languages such as Ada and LTR3, a French Pascal-like quadrupole distributions for the acceleration potential. An essential real-time language). The general structure of the computer is first step in the solution is the derivation of a near-field and a far-field presented, emphasis being placed on the technological choices formula for the pressure due to a point force in arbitrary motion (for example, the use of ASICs: Application Specific Integrated within a uniformly moving acoustic medium. The discrete frequency Circuits). The various protective mechanisms provided at the level spectrum and the three-dimensional directionality of the noise of the machine (hardware and microcode) are then presented: radiated from a propeller with angular inflow are obtained by a data access control and code execution control. Finally, a short conventional Fourier series expansion of the signature. The final presentation of the software production environment is given. In analytical formulas can be evaluated with simplecatculation. conclusion, the compromise made between operational Author dependability and performance characteristics are summarized. Author A89-12561"# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. CRUISE NOISE OF THE 219 SCALE MODEL SR-7A PROPELLER JAMES H. DITTMAR (NASA, Lewis Research Center, Cleveland, N89-10837# Air Force Wright Aeronautical Labs., OH) and DAVID B. STANG (Sverdrup Technology, Inc., Cleveland, Wright-Patterson AFB, Ohio. Avionics Lab. OH) Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, HIGH SPEED PARALLEL PROCESSING NETWORKS FOR p. 740-746. Previously cited in issue 04, p. 570, Accession no. ADVANCED ARCHITECTURES A88-16565. refs D. REED MORGAN In AGARD, Computing Systems Configuration for Highly Integrated Guidance and Control Systems 17 p Jun. 1988 A89-12563"# Southwest Research Inst., San Antonio, Tex. Avail: NTIS HC A08/MF A01 STRUCTURE-BORNE NOISE CONTROL FOR PROPELLER Many force multiplier improvements in vehicle control, situation AIRCRAFT awareness and crew decision aiding will be made possible if JAMES F. UNRUH (Southwest Research Institute, San Antonio, affordable, flyable supercomputers and associated software can TX) Journal of Aircraft (ISSN 0021-8669), vol. 25, Aug. 1988, p. be developed for next-generation military aircraft. New functional 752-757. Previously cited in issue 04, p. 569, Accession no. architectures will emerge because dramatic improvements in A88-16541. refs processing speed can be implemented through tightly coupled (Contract NAS1-17921) networks. Unconstrained system architectures can be developed where the system designer wilt have the capability to fuse together needed logical functions irrespective of previous boundaries. In addition, increased local processing (e.g., smart sensors) will be N89-10601"# Planning Research Corp., Hampton, Va. made possible to improve threat and target classification. Robust ON THE APPROPRIATENESS OF APPLYING CHI-SQUARE use of real-time artificial intelligence at both local, functional and DISTRIBUTION BASED CONFIDENCE INTERVALS TO system levels will be achievable, along with inprovements in fault SPECTRAL ESTIMATES OF HELICOPTER FLYOVER DATA tolerance and system diagnostics. Author CHARLES K. RUTLEDGE Aug. 1988 65 p
59 16 PHYSICS
(Contract NAS1-18000) been responsible for the small-scale and full-scale disagreement. (NASA-CR-181692; NAS 1.26:181692) Avail: NTIS HC A04/MF Author A01 CSCL 20A The validity of applying chi-square based confidence intervals to far-field acoustic flyover spectral estimates was investigated. 19 Simulated data, using a Kendall series and experimental acoustic data from the NASA/McDonnell Douglas 500E acoustics test, were GENERAL analyzed. Statistical significance tests to determine the equality of distributions of the simulated and experimental data relative to theoretical chi-square distributions were performed. Bias and uncertainty errors associated with the spectral estimates were easily identified from the data sets. A model relating the uncertainty and bias errors to the estimates resulted, which aided in determining A89-10537 the appropriateness of the chi-square distribution based confidence THE NONRIGID AIRSHIP OF THE SIEMENS-SCHUCKERT intervals. Such confidence intervals were appropriate for nontonally WORKS [DAS PRALLE LUFTSCHIFF DER associated frequencies of the experimental data but were SIEMENS-SCHUCKERT-WERKE] inappropriate for tonally associated estimate distributions. The H. MOENKE (DGLR, Stein an der Traun, Federal Republic of appropriateness at the tonally associated frequencies was indicated Germany) IN: Yearbook 1987 I; DGLR, Annual Meeting, Berlin, by the presence of bias error and noncomformity of the distributions Federal Republic of Germany, Oct. 5-7, 1987, Reports. Bonn, to the theoretical chi-square distribution. A technique for Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1987, p. 443-449. determining appropriate confidence intervals at the tonally In German. refs associated frequencies was suggested. Author (DGLR PAPER 87-055) The design, construction, and test-flight performance of the large nonrigid airships built by Siemens in the period 1907-1911 N89-10603"# National Aeronautics and Space Administration. are reviewed and illustrated with drawings and photographs. The Lewis Research Center, Cleveland, Ohio. final version of the airship was 118 m long and 13.5 m in diameter THE EFFECT OF FRONT-TO-REAR PROPELLER SPACING ON and had a gas volume of 15,000 cu m, divided into four THE INTERACTION NOISE AT CRUISE CONDITIONS OF A compartments; it was powered by four 125-hp engines and had a MODEL COUNTERROTATION PROPELLER HAVING A maximum speed of 19.8 m/sec. Consideration is given to the REDUCED DIAMETER AFT PROPELLER preliminary tests and design process, the fabrication of the full-scale JAMES H. DITTMAR, ELIOTT B. GORDON (Sverdrup Technology, prototype, test flights in 1911, the rotating hangar (permitting Inc., Cleveland, Ohio.), and ROBERT J. JERACKI Oct. 1988 enclosure or release with the airship facing the wind), and the 30 p reasons why the program was finally abandoned. It is pointed out (NASA-TM-101329; E-4340; NAS 1.15:101329) Avail: NTIS HC that the only airships in operation today employ the same design A03/MF A01 CSCL 20A concept as the Siemens airship. T.K. The effect of forward-to-aft propeller spacing on the interaction noise of a counterrotation propeller with reduced aft diameter was measured at cruise conditions. In general, the tones at 100 percent speed decreased from close to nominal spacing as expected from a wake decay model. However, when the spacing was further increased to the far position, the noise did not decrease as expected and in some cases increased. The behavior at the far spacing was attributed to changing forward propeller performance, which produced larger wakes. The results of this experiment indicate that simple wake decay model is sufficient to describe the behavior of the interaction noise only if the aerodynamic coupling of the two propellers does not change with spacing. If significant coupling occurs such that the loading of the forward propeller is altered, the interaction noise does not necessarily decrease with larger forward-to-aft propeller spacing. Author
N89-10856"# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. NOISE OF THE HARRIER IN VERTICAL LANDING AND TAKEOFF PAUL T. SODERMAN and JOHN D. FOSTER In its The 1987 Ground Vortex Workshop p 167-190 Feb. 1988 Avail: NTIS HC A10/MF A01 CSCL 01A The noise of the Harrier AV8C aircraft in vertical takeoff and landing was measured 100 feet to the side of the aircraft where jet noise dominates. The noise levels were quite high - up to 125 dB overall sound level at 100 feet. The increased noise due to jet impingement on the ground is presented as a function of jet height to diameter ratio. The impingement noise with the aircraft close to the ground was 14 to 17 dB greater than noise from a free jet. Results are compared with small-scale jet impingement data acquired elsewhere. The agreement between small-scale and full-scale noise increase in ground effect is fairly good except with the jet close to the ground. It is proposed that differences in the jet Reynolds numbers and the resultant character of the jets may be partially responsible for the disparity in the full-scale and small-scale jet impingement noise. The difference between single-jet impingement and multiple-jet impingement may also have
6O SUBJECT INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 236) February 1989
Typical Subject Index Listing
Prediction of aircraft-propeller-induced, structure-borne Aeroelasticlty and structural ophmization of helicopter interior noise p 28 A89-12564 rotor blades with swept tips p 29 N89-10887 I SUBJECT HEADING i AEROCAPTURE AERODYNAMIC DRAG Aerodynamic design and performance of a bent-axis Two-dimensional model for airfoil unsteady drag below ! geometry vehicle stall p 4 A89-10114 I AIAA PAPER 87-2491 ] p 42 A89-11119 Boundary-layer control for drag reduction AEROSPACE PLANES AERODYNAMIC CHARACTERISTICS iSAE PAPER 8724341 p 6 A89-10651 Control of separated flow on a symmetric airfoil AERODYNAMIC FORCES p 47 A89-10181 A computational study of coherent structures in the Aerodynamic characteristics of the ACES-II ejection seat wakes of two-dimensional bluff bodies at transomc Mach numbers p 25 A89-10463 IAD-A196820} p 53 N89-11188 An inverse, subsonic two-dimens_onal panel method AERODYNAMIC HEAT TRANSFER following the method of smallest quadrate for the design Navier-Stokes solution to the flowfield over ice accretion and modification of multiple element profiles shapes p 12 A89-12557 IDGLR PAPER 87-061 I p 5 A89-10509 Measurements of heat transfer distribution over the An experimental study on aerodynamic performance ol surfaces of highly loaded turbine nozzle guide vanes Lippisch-type GEW --- Ground Effect Wing p 51 A89-12752 p 6 A89-10544 AERODYNAMIC HEATING Numerical approach of advanced turboprop with Approximate calculations of viscous drag and three-dimensional Euler equations aerodynamic heating p 10 A89-11157 ISAE PAPER 872448] p 7 A89-10661 Aerothermodynamics - The required tools Application of an artificial density scheme of potential The subject heading is a key to the subject content I SAE PAPER 8809281 p 12 A89-12316 stream function method to design of airfoil AERODYNAMIC INTERFERENCE of the document. The title is used to provide a p 7 A89-11053 Wing laminar boundary layer in the presence of a Experimental study of rotating stall in single-stage axial description of the subject matter. When the title is propeller slipstream p 4 A89-10105 compressor p 8 A89-11059 insufficiently descriptive of document content, a Investigation on wall interference of low-speed wind A new approach to _mprovement of fans tunnel with slotted walls p 8 A89-11081 title extension is added, separated from the title p 8 A89-11064 Tests on 3 NACA 0012 airfoil models of DFVLR in the by three hyphens. The (NASA or AIAA) accession Numerical simulation of steady transonic flow past an NAL 03 tunnel: An assessment of 2-D wall interference 8-percent DCA cascade at a freestream Mach number number and the page number are included in each ITM-AE-87051 p 15 N89-10847 of about 1 p 8 A89-11073 AERODYNAMIC NOISE entry to assist the user in locating the abstract in Research on the computational method of aerodynamic Reduction of eiector noise with multihole nozzle the abstract section. If applicable, a report number characteristics of wing with vortex breakdown at high angle p 36 A89-11034 of attack p 9 A89-11086 is also included as an aid in identifying the docu- Noise field of a propeller wLth angular inflow Finite element method for calculating transonic potential ment. Under any one subject heading, the acces- p 59 A89-11102 flow around airfoil from pressure minimum integration Cruise noise of the 2/9 scale model SR-7A propeller sion numbers are arranged in sequence with the p 9 A89-11088 p 59 A89-12561 Measurements of heat transler distnbution over the AIAA accession numbers appearing first. AERODYNAMIC STALLING surfaces of highly loaded turbine nozzle guide vanes Two-dimensional model for airfoil unsteady drag below p 51 A89-12752 stall p 4 A89-10114 Aerodynamic design considerations for a free-flying Unsteady three-dimensional stall on a rectangular ducted propeller wing p 14 N89-10027 A i DE88-006867 [ p 15 N89-10841 AERODYNAMICS The characteristics of the ground vortex and its effect Turbulence management and re_aminarisation; on the aerodynamics of the STOL configuration ABLATION Proceedings of the ]UTAM Symposium, Bangatore. India. p 15 N89-10850 Approximate caiculations of viscous drag and Jan 19-23, 1987 p46 A89-10154 Non-linear aerodynamic characteristics obtained from aerodynamic heating p 10 A89-11157 The formation mechanism of the asymmetric spatial the analysis of flight-data ACCIDENT INVESTIGATION vortex of slender bodies at high angle of attack IAR-004-571 ] p 18 N89-10866 European airworthiness control for the 1990s I SAE PAPER 8724351 p 7 A89-10652 The use of the complex summation method for I SAE PAPER 880936 ) p 2 A89-12320 Panel methods in aerodynamics - Some highlights formulating algorithms for decoupling vertical/horizontal ACOUSTIC MEASUREMENT p 10 A89-11481 motions of rolling aircraft p 30 N89-10889 On the appropriateness of applying chi-square Aerodynamically-driven condensate layer thickness Investigahon of the tumbling phenomenon using distribution based confidence intervals to spectral distributions on isothermal cylindrical surfaces computer simulation p 41 N89-10896 estimates of helicopter flyover data p 51 A89-12337 Numerical simulation of transonic flow around Asuka I NASA-CR-1816921 p 59 N89-10601 Validation of a pair of computer codes for estimation p 18 N89-11067 ACOUSTIC PROPAGATION and optimization o1 subsonic aerodynamic performance AERODYNAMIC COEFFICIENTS of simple hinged-flap systems for thin swept wings Active control of reheat buzz --- Iow-trequency On the evaluation of aerodynamic influence I NASA-TP-28281 p 13 N89-10024 combustion instability of jet aeroengine afterburners coefficients p 11 A89-11496 p 43 A89-11103 An approximate, maximum terminal velocity descent to Experimental aerodynamic performance of advanced 40 ACTIVE CONTROL a point deg-swept 10-blade propeller model at Mach 0,6 to 0.85 Boundary-layer control for drag reduction I DE88-0003491 p 15 N89-10840 INASA-TM-889691 p 17 N89-10865 Schlieren measurements at the 10,000-foot sled track I SAE PAPER 8724341 p 6 A89-10651 AERODYNAMIC CONFIGURATIONS Active control of reheat buzz --- low-frequency [ DE88-012748] p 42 N89-10899 Experimental study of effects of forebody geometry on combushon instability of let aeroengtne afterburners AEROELASTICITY high angle-of-attack stability p 38 A89-10103 p43 A89-11103 Efficient algorithm for solution of the unsteady transonic A circular cone surface shaping method for fan blade ADHESION TESTS small-disturbance equation p 4 A89-10104 p 50 A89-11032 Stress analys_s concepts for adhesive bonding of aircraft Aeroelast_city past, present and future--- with application Application of end_bend blade for enhancing surge pnmary structure p 45 A89-10093 to air accident case margin p 36 A89-11051 ADHESIVE BONDING I SAE PAPER 8724491 p 19 A89-10662 Application of an advanced panel method to AdhesiveLy bonded joints: Testing, analysis, and design_ A data acquisition system lot blade vibration test aerodynamic problems of aircraft design p 41 A89-11037 Proceedings of the International Symposium, Baltimore, p 28 A89-11486 MD, Sept 10-12. 1986 p 45 A89-10076 Measurement of aerodynamic characteristics of a A subsonic panel method for design of 3-dimensional Effect of adhesive debond on stress-intensity factors hang-ghder-wing by ground run tests using a test vehicle complex configurations with specified pressure in bonded composite panels p 45 A89-10091 INAL'TR-9531 p 13 N89-10004 • distribution p 28 A89-11491 Enwronmental durability of adhesively bonded joints AGARD manual on aeroelasticity in axial-flow p 46 A89-10095 A vortex-lattice method for the calculation of wing-vortex turbomachmes. Volume 2: Structural dynamics and AEROACOUSTICS interaction in subsonic flow p 11 A89-11499 aeroelasticdy Results of acoustic tests ol a prop-fan model Transonic computations about complex configurahons IAGARD-AG-298-VOL*21 p 13 N89-10006 p 59 A89-10112 using coupled inner and outer flow equations Aeroelastic coupling: An elementary approach A study on effects of aircraft noise environment on its p 12 A89-12553 p 37 N89-10012 structure Method to optimize nacelle shape in a supersonic cruise Aeroetastlc formulation for tuned and mistuned rotors I SAE PAPER 8724501 p 28 A89-10663 aircraft p 28 A89-12558 p 37 N89-10013
A-1 AERONAUTICALENGINEERING SUBJECT INDEX
Fan flutter test p 37 N89-10014 Surveillance - High-technology fit-out for the Nomad Aircraft crashes on the runway: Development of a super Aeroelastlc thermal effects p 37 N89-10015 aircraft element for nonlinear analysis of a beam Forced vibration and flutter design methodology I SAE PAPER 8724281 p 32 A89-10647 INEPT-87/561 p 54 N89-11286 p 51 N89 10016 Laser nawgation equipment -- Russian book AIRCRAFT COMMUNICATION La Recherche Aerospahale, Bimonthly Bulletin, Number p 24 A89-10722 Research on satellite to-aircraft signal communication 1987-4, 239/July-August The operation of modern air-space surveillance radars I DGLR PAPER 87-1331 p 23 A89-10524 IESA-TT 10881 p 14 N89-10026 p 51 A89-12151 AIRCRAFT COMPARTMENTS The pros and cons of code validation Contamination of environmental control systems in Simulation and analysis of image-based navigation INASA-TM-1006571 p 14 N89-10034 Hercules aircraft system for rotorcraft low-altitude flight Vibration. performance, flutter and forced response IMRL-Rq 1161 p29 N89-10040 p 32 A89-12403 characteristics of a large-scale propfan and its aeroelastic AIRCRAFT CONFIGURATIONS Air navigation systems I Astronomical navigation in model Configuration optimization of commercial aircraft the air 1919-1969 p 24 A89-12449 I NASA-TM-101322] p 38 N89-I0043 IDGLR PAPER 87-081 I p 26 A89-10517 Aeroelastlclty and structural optlmlzahon of hehcopter Interference of precipitation static discharges with Analytical and experimental research on aerodynamical rotor blades with swept tips p 29 N89-10887 aircraft navigational systems p 21 N89-10459 effects of wind shear on aircraft p 6 A89-10547 AERONAUTICAL ENGINEERING AIR POLLUTION Efficient vibration mode analysis of aircraft with multiple International Pacific Air and Space Technology Contamination of environmental control systems in external store configurations p 28 A89-12562 Conference, Melbourne. Australia, Nov. 13 17, 1987, Hercules aircraft GENMAP - Computer code for mission adaptive profile Proceedings IMRL-R-11161 p29 N89-10040 generation p 12 A89-12566 ISAE P-2081 p 1 A89-10627 AIR TRAFFIC AIRCRAFT CONSTRUCTION MATERIALS A world leader in engineering and maintenance Biting the bullet on aviation safety p 3 A89-12537 Simulation of a blrdstnke impact on aircraft canopy ISAE PAPER 8724441 p 1 A89-10657 AIR TRAFFIC CONTROL material p 25 A89-10113 The effects of fluids in the aircraft environment on a Origin, oblecWes and activities of the Department of The Australian Aviation Satellite System Aerospace Engineering p 3 N89 10830 I SAE PAPER 872420 p p 24 A89-10642 polyetberimide p 44 A89-12789 Aviation technology applicable to developing regions Air-traffic flow management today p 24 A89-12152 Indirect effects on electronic and mechanical systems I NASA-TM-894251 p 23 N89-10872 Operational findings from a Traffic Alert and Colhs_on installed in carbon fibre compound aircraft structures AEROSPACE ENGINEERING Avoidance System (TCAS) evaluation p 22 N89 10492 International Pacific Air and Space Technology I SAE PAPER 880943 J p 32 A89-12321 AIRCRAFT CONTROL Conference Melbourne Australia. Nov f 3-17, 1987. Up in the air on air traffic control p 3 A89-12538 Aspects of the control and stabihzahon of supersonic Proceedings Terminal control area design and air traffic Ioadmgs commercial aircraft ISAE P-2081 p 1 A89-10627 IDOT/FAA/DS-88/11 I p 25 N89-10038 I DGLR PAPER 87-1221 p 39 A89-10519 Aerospace systems and technology: The role of the In-service evaluation of the Traffic Alert and Colhsion Lessons learned from developmental and operational RAE Avoidance System (TCAS) industry prototype turbine engine monitoring systems IRAE-TR-880421 p 3 N89-10003 tDOT/FAA/SA-88/21 p 25 N89-10885 ISAE AIR 1871BI p 35 A89-10624 Origin, obiectives and activities of the Department of Evaluation of enhancements to the Low Level Wind Modern techniques for the control of RPV's Aerospace Eng_neenng p 3 N89-10830 Shear Alert System (LLWAS) at Stapleton International I SAE PAPER 8724571 p 39 A89-10669 AEROSPACE ENVIRONMENTS Airport Control of autorotational characteristics of light-airplane Fiber-optic sensor systems for aerospace applications I DOT/FAA/PS-88/141 p56 N89-11356 fuselages p 39 A89-12555 p 47 A89-10359 AIR TRANSPORTATION Boundary-layer transition effects on airplane stablhty and AEROSPACE INDUSTRY V/STOL aircraft configurations and opportunities in the control p 39 A89-12556 Military aerospace techmcal development in Australia Pacific Basin Design and evaluation of dynamic flight test ISAE PAPER 8724261 p I A89-10646 tSAE PAPER 8724031 p 18 A89-10631 manoeuveres The winning edge --- NASA role in US aeronautics AIRBORNE EQUIPMENT IPB88-210760i p 29 N89-10042 industry's competition w_th foreign supphers Digital recording of radar data in an aircraft F-15 SMTD low speed jet effects wind tunnel test I SAE PAPER 8809451 p 2 A89-12322 tPB88-2095071 p 51 N89-10212 results p 16 N89-10853 AEROSPACE PLANES An aircraft-borne electric field measuring system for AIRCRAFT DESIGN Technology issues associated with fueling the national rocket launch support p 55 N89-10443 Optimization of the conceptual design and mission aerospace plane with slush hydrogen Estimating electnc field enhancement factors on an profiles of short-haul aircraft p 25 A89-10107 I NASA-TM-1013861 p 43 N89-10123 aircraft utilizing a small scale model: A method Multilevel decomposihon approach to the preliminary AEROSPACE SYSTEMS evaluahon p 21 N89-10454 sizing el a transport aircraft wing p 25 A89-I0109 Aerospace systems and technology The role of the AIRBORNE/SPACEBORNE COMPUTERS Advanced crew escape capsule technologies program RAE Should technology assist or replace the pilot? p 18 A89-10475 I RAE-TR-880421 p 3 N89-10003 I SAE PAPER 8807741 p 57 A89-10593 improvement of a design code for airfoils at transonic AEROSPACE VEHICLES Lessons learned from developmental and operational regime Computational 6uld dynamics in aerospace turbine engine monitoring systems IDGLR PAPER 87-0641 p 5 A89-10511 tSAE PAPER 8724461 p 7 A89-10659 ISAE AIR 1871BI p 36 A89-10624 Apphcahon of wlnglets wdh _ntegrated, adjusted Triggering of lightning by the Atlas Centaur vehicle On the diagnostic emulation technique and its use pn tralhng-edge flaps in a general av_ahon aircraft p 55 N89-10438 the AIRLAB I DGLR PAPER 87-0801 p 26 A89-10516 AEROTHERMOCHEMISTRY I NASA-TM-40271 p 58 N89-10524 Configuration optimization of commercial aircraft A new PNS code for chemical nonequlllbnum flows A highly reliable computer for airborne applications I DGLR PAPER 87-081 I p 26 A89 10517 p9 A89-f 1106 p 59 N89-10833 fs 32 - A split-Fowler glider problem presentation and AEROTHERMODYNAMICS AIRCRAFT ACCIDENT INVESTIGATION solutions Calculation el compressible flow and heat transfer on Aeroelasticity past. present and future with application I DGLR PAPER 87-0821 p 26 A89-10518 a rotating disk p 50 A89-11033 to air accident case The nonrigid airship of the Siemens-Schuckert Works Aerothermodynamics - The required tools ISAE PAPER 8724491 p 19 A89-10662 I DGLR PAPER 87-0551 p 60 A89-10537 ISAE PAPER 8809281 p 12 A89-12316 Aircraft accident reports, brief format, US civil and foreign The design eye reference point --- for determining Plight mechanics and aerothermodynamic software aviation, issue number 10 of 1987 accidents geometric entities defining cockpit layouts ICNES-CT/DTI/MS/MN/0691 p 4 N89-10839 IPB88-9169051 p 20 N89-10035 ISAE PAPER 8717631 p 31 A89-10582 AFTERBODIES Aircraft accident reports, brief format, US civil and foreign International Pacdic Air and Space Technology Experimental investigation of convergent elector aviahon, issue number 12 of 1986 accidents Conference, Melbourne, Austraha, Nov 13-17, 1987, nozzle/afterbody m wind tunnel p 8 A89-11060 I PB88 9169031 p 20 N89-10036 Proceedings AFTERBURNING Atrcraft accident/incident summary report, Copperhill, ISAE P-2081 p I A89-10627 Active control of reheat buzz --- low-frequency Tennessee, February 22, 1986 From Kitty Hawk to the year 2000 combustion instability of let aeroeng*ne afterburners I PB88-910407 I p 22 N89-10868 ISAE PAPER 8723951 p 1 A89-10628 p43 A89 11103 Aircraft accident reports, brief format, US civi_ and foreign Unique research challenges for htgh-speed civil AH-64 HELICOPTER aviation, issue number 2 of 1987 accidents transports A hybrid knowledge-based approach to AH-64A fault I PB88-9169061 p 23 N89-10871 ISAE PAPER 8724001 p I A89-10629 =solahon p 2 A89-12409 Aircraft accident report: Executive Air Charter, Inc., dba The Boeing 7J7 - The evolution of technology and AIR CARGO American Eagle, Flight 5452, CASA C-212, N432CA, design Interoperabihty of military and civil air-cargo systems Mayaguez, Puerto Rico, May 8, 1987 ISAE PAPER 8724051 p 27 A89-10632 ISAE PAPER 8215551 p 19 A89-10654 I PB88-9104091 p 23 N89-10873 Evolution of the STOL and Maneuver Technology AIR DEFENSE AIRCRAFT ACCIDENTS Demonstrator Military aerospace technical development bn Australia Quahfication and operational aspects of light weight ISAE PAPER 8724171 p 27 A89-10639 ISAE PAPER 8724261 p f A89 10646 SKAD (hght weight survival kit air droppable) Misston-Adaptive Wing AIR LAND INTERACTIONS p 18 A89-10471 I SAE PAPER 8724191 p 27 A89-10641 A numerical eshmahon of the deforestahon effects on European airworthiness control for the 1990s The study of the global stability of high performance local climate in the area of the Frankfurt _nternationat ISAE PAPER 8809361 p 2 A89-12320 aircraft at high angles-of-attack airport p 55 A89-11554 Airclaft accident reports, bdel for mat, US civil and foreign ISAE PAPER 8724561 p 39 A89-10668 AIR NAVIGATION aviation, Issue number 10 of 1987 accidents Over the rmnbow --- Avionics design and systems Integrated redundant reference systems for fhght control I PB88-9169051 p 20 N89-10035 integration and navigahon with skewed sensor arrangement Aircraft accident reports, brief format, US civil and foreign I SAE PAPER 872499 I p 2 A89-10689 p 30 A89-10129 avlahon, issue number 12 of 1986 acctdents A study of the accuracy of wing calculations based on Navigation of aircraft with rigid image-forming sensors IPB88-916903 I p 20 N89-10036 different schemes p 49 A89-10774 IDGLR PAPER 87-130t p 31 A89-10521 Aeronautical decision making for air ambulance Application of an advanced panel method to The Australian Awatton Satellite System helicopter pilots: Situational awareness exercises aerodynamic problems el abrcraft design tSAE PAPER 8724201 p 24 A89-10642 I DOT/FAA/DS-88/61 p 23 N89-10869 p 28 A89-11486
A-2 SUBJECT INDEX AIRCRAFT STABILITY
A subsonic panel method for design of 3-dimensional AIRCRAFT HAZARDS The effect of front-to-rear propeller spacing on the complex configurations with specified pressure Bird hazards in aviation: Proceedings of the Sympostum, interaction noise at Cruise conditions of a model distribution p 28 A89-11491 London. England. Oct 14. 1987 p 3 A89-12716 counterrotat_on propeller having a reduced diimeter aft MIG-29 design merges old, new technologies The work of the Aviation Bird Unit p 3 A89-12723 propeller p 28 A89-11559 Statistics of lightning interaction with aircraft in Japan I NASA-TM*1013291 p 60 N89-10603 Method to optimize nacelle shape m a supersontc cruise p 55 N89-10430 Noise of the Harrier in vertical landing and takeoff aircraft p 28 A89-12558 Israel Air Force (IAF) in-service aircraft lightning strike p 60 N89-10856 and damage survey p 55 N89-10431 AIRCRAFT PERFORMANCE Low-Reynolds-number airfod design for the M.I.T. Lightning information database p 55 N89-10432 Daedalus prototype - A case study p 12 A89-12559 Flight-test determination of aircraft cruise characteristics Triggering of lightning by the Atlas Centaur vehicle using acceleration and deceleration techniques Design and testing for airframes p 29 A89-12719 p 55 N89-10438 p 25 A89-10101 Windscreen design and testing p 29 A89-12720 AIRCRAFT INSTRUMENTS Optimization ot the conceptua; design and mrsslon Wheel performance evaluation Phase 1: Analysis Packaged fiber optic gyros with high bias stabdrty profiles of shorf-haul aircraft p 25 A89-10107 I DOT/FAA/CT-88/161 p 29 N89-10041 p 46 A89-10121 From Kitty Hawk to the year 2000 Generation of a grid for a finite difference calculation State of the art inertial navigation - Fhght testing of the I SAE PAPER 8723951 p 1 A89-10628 of flows around an aircraft in Cartesian coordinates Honeywell LINS Standard Navigator H-423 M*ssion-Adaptive Wing ]NAL-TR-9561 p 58 N89-10563 p 30 A89-10131 ]SAE PAPER 8724191 p 27 A89-10641 Ongm, objectives and actfvihes of the Department of Applications of time and wavelength diwsion multiplexing Introduction of the Hornet - A success story Aerospace Engineering p 3 N89-10830 to digital optical code plates p 31 A89-10364 I SAE PAPER 8724361 p 27 A89-10653 The 'Pneumatic Wind Shear Sensor' (PWSS) - An aid Advanced avionics architecture pave pitlar Seaplane takeoff performance - Using delta ratio as a to flight path regulation and to disturbance magnitude p 33 N89-10834 method of correlation p 28 A89-12565 idenfificatton in shear wind situations Aerodynamic design considerations for a free-flying Wave drag and high-speed performance of supersonic I DGLR PAPER 87-1341 p 31 A89-10525 STOVL fighter configuration ducted propeller Shear wind measurements aboard a Piper PA 18 and I NASA-TM-f00061 1 p 13 N89-10017 IDE88-0068671 p 15 N89-10841 the design of a model glider aircraft for dynamic ghding AIRCRAFT POWER SUPPLIES AIRCRAFT DETECTION flight Circuit protection for advanced aircraft - A functional Rule-based string code processor p 57 A89-11750 I DGLR PAPER 87-135/1 I p 26 A89-10526 and historical perspective AIRCRAFT ENGINES Surveillance - High-technology fit-out for the Nomad I SAE PAPER 8725021 p 32 A89-10692 Aspects of increasing economy using future low-power aircraft AIRCRAFT RELIABILITY aircraft propulsion systems I SAE PAPER 8724281 p 32 A89-10647 Introduction of the Hornet - A success story I DGLR PAPER 87-1001 p 33 A89-10528 Health and usage monitoring - The integrated approach I SAE PAPER 8724361 p 27 A89-10653 Aircraft gas turbine engine monitonng systems: An --- for propulsion and structural elemenfs of fixed and rotary Tornado - The first eight years p 2 A89-11450 update wing civil aircraft A Canadian government look at atrwodhiness I SAE SP-7281 p 33 A89-10613 i SAE PAPER 872445[ p 32 A89-10658 ]SAE PAPER 880935} p 2 A89-12319 Development and testing of an inflighf engine A case for a unified lightning threat European airworthiness control for the 1990s performance monitonng technique for the US Navy P-3C p 56 N89-10447 ISAE PAPER 8809361 p 2 A89-12320 atrplane AIRCRAFT LANDING Functional mock-up tests of the flight control system I SAE 8414621 p 34 A89-10615 Automated landing approach using machine seeing of the NAL QSTOL research aircraft: Planning and AIR 1900 - Guide to temperature mondoring in aircratt I DGLR PAPER 87-131 ] p 23 A89-10522 mechanical system test Preconditions for G.PS. installation - Receivers in gas turbine engines i NAL-TR-9441 p 40 N89-10047 tSAE 8717301 p 34 A89-10616 differential operation for landing aircraft m general Some statistical aspects of attntion studies Lessons learned from an operational engine monitoring aviation I AD-A1966651 p 30 N89-10891 system and their correlation with future developments I DGLR PAPER 87-1321 p 23 A89-10523 AIRCRAFT SAFETY I SAE 8717331 p 34 A89-10618 Invesbgatlon of wake vortices of landing aircraft at Aerospace technology - Windshear FAA: Boeing A guide In aircraft turbine engine vibration mondoring Frankfurt airport (Federal Republic of Germany) W_ndshear Training Aid program systems [DFVLR-MITT-88-151 p 17 N89-10862 ]SAE PAPER 872441 I p 19 A89-10655 I SAE AIR 18391 p 35 A89-10623 AIRCRAFT MAINTENANCE Health and usage monitoring - The integrated approach Guide to life usage monitoring and parts management Pocket Calculator trend mondoring for gas turbine -- for propuls._on and structural elements of fixed and rotary for aircraft gas turbine engines engines wing civil aircraft ISAE AIR 18721 p 35 A89-10625 I SAE 841461 ) p 34 A89-10614 tSAE PAPER 872445l p 32 A89-10658 Gu*de to timited engine monitoring systems for aircraft The V-22 vibration, structural life. and engine diagnostic Operating safety of automatic oblects --- Russian book gas turbine engmes system, VSLED p 49 A89-10714 t SAE AIR 1873l p 35 A89-10626 ISAE 8717321 p 31 A89-10617 The assurance of flight safety - A priority task in civil RB211 developments Texmas - An expert system for gas turbine engine aviation p 20 A89-12548 I SAE PAPER 872409] p 35 A89-10635 diagnosis and more Bird hazards in aviation - Safety and economtc Gas turbine engine development partnerships I SAE 8717371 p 34 A89-10621 implications for an a_dine p 20 A89-12721 {SAE PAPER 8724101 p 35 A89-10636 Lessons learned from developmental and operational Terminal control area design and air traffic Ioadings Propulsion-airframe integrahon for commercial and turbine engine monLtoring systems I DOT/FAA/DS-88/11 I p 25 N89-10038 military aircraft ISAE AIR 1871B1 p 35 A89-10624 International Aerospace and Ground Conference on I SAE PAPER 872411 J p 35 A89-10637 Maintenance and airline safety Lightning and Static Electricity A dynamic characteristic analysis of a bladed disk ISAE PAPER 8724431 p 19 A89-10656 i PB88-1974391 p 55 N89-10429 assembly p 36 A89-11026 A world leader in engmeenng and maintenance Summary of infhght data on lightmng currents and A design method of 'wlgglestrap' film-cooling I SAE PAPER 8724441 p 1 A89-10657 fields p 56 N89-10449 construction of flame tube p 50 A89-11039 Tornado - The first eight years p 2 A89-11450 Analysis of recent in-flight lightning measurements on A let thrust measurement method with gas composition European airworthiness control for the 1990s different aircraft p 20 N89-10450 analysis p 36 A89-11040 tSAE PAPER 880936] p 2 A89-12320 Linear and nonhnear interpretation of CV-580 lightning Bevel gear resonance failures in central gearing system A hybrid knowledge-based approach to AH-64A fault data p 21 N89-10451 of an aeroenglne p 50 A89-11046 isolation p 2 A89-12409 A chronology Of m-cloud electric field and lightning Application of end-bend blade for enhancing surge PI - An AI approach for maintenance and diagnostic strikes on an instrumented research aircraft margin p 36 A89-11051 applications p 58 A89-12413 p 21 N89-10455 Approach to blade end-bend mechanism AIRCRAFT MANEUVERS Lightning imtiation on aircraft m thunderstorms p 36 A89-11052 Evolution of the STOL and Maneuver Technology p 21 N89-10456 Unsteady loading norse of counter-rotating propeller Demonstrator The SAFtR lightning monitoring and warning system, p 36 A89-11054 I SAE PAPER 8724171 p 27 A89-10639 applications to aerospace actrvities p 52 N89-10481 Propfan design by propeller-nacelle interaction Tactical route planning --- for helicopter evasive Modelling of common mode coupling between an aircraft analysis p 36 A89-11055 maneuvering p 24 A89-12414 wing traversed by a lightning current and wibng installed Expenenee with the development of turboprop Transonic characteristics of a humped airfoil in that wing p 22 N89-10485 engines p 37 A89-11074 p 12 A89-12551 Aircraft accident/incident summary report, Copperhill, Tennessee, February 22. 1986 Control of the low-cycle service tile of the primary Design and evaluation of dynamic flight test IPB88-9104071 p 22 N89-10868 components of aircraft turbine engines according to the manoeuveres damage-tolerance concept p 37 A89-11075 IPB88-2107601 p 29 N89-10042 Aircraft accident reports, brief format, US civil and foreign aviation, issue number 2 of 1987 accidents Influence of regenerahon treatments on creep rupture AIRCRAFT MODELS I PB88-916906l p 23 N89-10871 lives of turbine blades p 43 A89-11214 Estimating electnc field enhancement factors on an Statistics on a_rcraft gas turbine engine rotor failures Alternate fuels for General Aviation aircraft with spark aircraft utilizing a small scale model: A method that occurred in US commercial aviation during 1982 ignition engines evatuat*on p 21 N89-10454 I DOT/FAA/CT-88/051 p 44 N89-10179 1DOT/FAA/CT-88/23t . p 38 N89-10892 An assessment of ground effects determined by static AIRCRAFT EQUIPMENT AIRCRAFT SPIN and dynamic testing techniques p 16 N89-10854 The htstory of aircraft onboard equipment Control of autorotational characteristics of tight-airplane AIRCRAFT NOISE I DGLR PAPER 87-054 ] p 31 A89-10536 fuselages p 39 A89-t2555 A study on effects of aircraft noise enwronment on *ts On the diagnostic emulation technique and its use in AIRCRAFT STABILITY the AIRLAB structure Experimental study of effects of forebody geometry on I NASA-TM-40271 p 58 N89-10524 t SAE PAPER 8724501 p 28 A89-10663 htgh angle-of-attack stability p 38 A89-10103 AIRCRAFT FUELS Cruise no*se of the 2/9 scale model SR-7A propeller Comparison of longitudinally stabilized behavior in The performance of alternate fuels in general av*ation p 59 A89-12561 vertical turbulence between a modern canard configuration aircraft Structure-borne noise control for propeller aircraft and a conventional aircraft IDOT/FAA/CT-88/131 p44 N89-10175 p 59 A89-12563 I DGLR PAPER 87-0781 p 39 A89-10515
A-3 AIRCRAFT STRUCTURES SUBJECT INDEX
Aspects of the control and stabihzation of supersonic Effects of a ground vortex on the aerodynamics of an Data and signal processing architectures for future commercial aircraft airfoil p 16 N89-10855 avionics p 33 N89-10835 I DGLR PAPER 87-1221 p 39 A89-10519 AIRFRAMES High speed parallel processing networks for advanced Aircraft dynamic stablhty - Developmental history Design and testing for airframes p 29 A89-12719 architectures p 59 N89-10837 ARROW WINGS aspects Fracture criteria for discontinuously reinforced metal I DGLR PAPER 87-0571 p 1 A89-10538 matrix composites Experimenta_ investigation of flow near a corner, part 2 The study of the global stability of high performance INASA CR-1811751 p44 N89-10125 aircraft at high angles-of-attack AIRLINE OPERATIONS ICERT-RT-OA-24/5025-AYDI p 17 N89-10881 I SAE PAPER 872456J p 39 A89-10668 Three dimensional shear flow. Analysis of the flow in Fundamentals of flight safety --- Russian book Boundarydayer transition effects on airplane stability and a delta arrow wing with incidence angle p 19 A89-10721 control p 39 A89-12556 ICERT-RTS*OA-25/5025-AYDI p 17 N89-10864 Air-traffic flow management today p 24 A89-12152 Design and evaluation of dynamic fhghl test ARTIFICIAL INTELLIGENCE manoeuveres Biting the bullet on aviation safety p 3 A89-12537 Texmas - An expert system for gas turbine engine I PB88-2107601 p 29 N89-10042 Air safety in the age of deregulation diagnosis and more F-15 SMTD low speed let effects wind tunnel test p 19 A89-12539 iSAE 8717371 p 34 A89-10621 results p 16 N89-10853 The assurance of flight safety - A priordy task in civil Pi - An AI approach for maintenance and diagnostic AIRCRAFT STRUCTURES awation p 20 A89-12548 applications p 58 A89-12413 Stress analysis concepts for adhesive bonding of aircraft Bird hazards in awation - Safety and economtc ASTRONAUTS primary structure p 45 A89-10093 implications for an airline p 20 A89-12721 Current military/government applications for speech Fatigue life influence of residual stresses from cold AIRPORT PLANNING recognition working and high spectrum loads in aircraft structural Terminal control area design and air traffic Ioadings ISAE PAPER 8717501 p 23 A89-10580 design p 46 A89-10099 IDOT/FAA/DS-88/11 I p 25 N89-10038 ATMOSPHERIC ENTRY Transition recognition in aircraft wing profiles with the AIRPORTS Aerodynamic design and performance of a bent-axis aid of piezoelectric sheetings International Pacdic Air and Space Technology geometry vehicle I DGLR PAPER 87-0651 p 47 A89-10512 Conference, Melbourne, Austraha, Nov 13-17, 1987, I AIAA PAPER 87-24911 p42 A89-11119 A frequency domain MfMO modal identification method Proceedings ATMOSPHERIC SOUNDING with apphcahon in the aircraft ground vlbrahon test ISAE P-2081 p 1 A89-10627 Structure and life cycle of microburst outflows observed I SAE PAPER 8724581 p 48 A89-10670 Fire safety at civil airports -- Russian book m Colorado p 54 A89-11221 Fracture cntena for discontinuously reinforced metal p 19 A89-10718 ATMOSPHERICS matrix composites A numerical estimation of the deforestation effects on International Aerospace and Ground Conference on I NASA-CR-1811751 p44 N89-10125 local climate in the area of the Frankfurt international Lightning and Static Electncdy Analysis of recent m-fhght lightning measurements on airport p 55 A89-11554 IPB88-1974391 p 55 N89-10429 different aircraft p 20 N89-10450 Bird hazards in aviation - The regulatory authordy's ATTACK AIRCRAFT Lightning tests on an all-composite helicopter responsibilities p 20 A89-12722 A tactics expert system for scout/attack rotorcraft p 21 N89-10452 The work of the Aviation Bird Unit p 3 A89-12723 p 58 A89-12405 A filamentary method for calculating induced voltages Lightning and surge protechon of large ground AUGMENTATION within resistive structures in e_ther the frequency or time faclldles p 52 N89-10474 Turbofan forced mixer lobe flow modeling Part 3: domain p 52 N89-10484 AIRSHIPS Application to augment engines Aircraft crashes on the runway: Development of a super The nonrigid airship of the Siemens-Schuckert Works INASA-CR-41471 p 14 N89-10025 element for nonlinear analysis of a beam IDGt R PAPER 87-0551 p 60 A89 10537 AUTOMATIC CONTROL I REPT 87/561 p54 N89-11286 System protection from atmospheric electncity for Modern techniques for the control of RPV's AIRCRAFT WAKES aerostats with conducting tethers p 52 N89-10497 ISAE PAPER 8724571 p 39 A89-10669 Investigation of wake vortices of landing aircraft at ALTERNATING DIRECTION IMPLICIT METHODS Dghtning tests to measure the bulk current levels Frankfurt airport (Federal Republic of Germany) Diagonal implicit mulhgrid algorithm for the Euler associated with the electronic engine control Of a turboprop IDFVLR-MITT-88-151 p 17 N89-10882 equations p 9 A89-11110 commuter transport p 21 N89-10457 AIRFOIL OSCILLATIONS ALUMINUM AUTOMATIC FLIGHT CONTROL Prediction of incidence effects on oscillating airfoil Indirect effects on electronic and mechanical systems Hardware fault insertion and instrumentation system: aerodynamics by a locally analytical method installed in carbon fibre compound aircraft structures Experimentation and results p 12 A89-12135 p 22 N89-10492 [NASA-CR-1827461 p 58 N89-10526 AIRFOIL PROFILES ALUMINUM ALLOYS AUTOMATIC LANDING CONTROL Thick airfoil at low Reynolds number and high Fatigue crack growth in aircraft mare landing gear Automated landing approach using machine seeing incidence p 4 A89-10116 wheels p 28 A89-11447 I DGLR PAPER 87-131 I p 23 A89-10522 Improvement of a design code for aldOllS at transonic Creep tests for slow and fast tahgue conddions on AUTOMATIC PILOTS regime aluminum alloy specimens Digital autopilots for rotary winged unmanned aerial I DGLR PAPER 87-064 I p5 A89-10511 I REPT-M0-5352001 p 45 N89-11020 vehicles p 39 A89-12417 A numerical solution of transonic flow us*ng ANGLE OF ATTACK Flight test results for the Daedalus and Light Eagle d_scontlnuous shock relation p 6 A89-10542 Experimental study of effects of forebody geometry on human powered aircraft Application of an artificial density scheme of potential high angle-of-attack stability p 38 A89-10103 I NASA-CR-1833051 p30 N89-10890 stream function method to destgn of airfoil The formation mechanism ot the asymmetric spaha_ AUTOMATION p7 A89-11053 vortex of slender bodies at high angle of attack Should technology assist or reptace the pilot? Finite element method for calculating transonic potential I SAE PAPER 872435 I p 7 A89 10652 I SAE PAPER 880774 I p 57 A89-10593 flow around airfoil from pressure m_nlmum integrahon The study of the global stabihty of high performance Operating safety of automatic obiects --- Russian book p9 A89-11088 aircraft at high angles-of-attack p 49 A89-10714 AIRFOILS I SAE PAPER 8724581 p 39 A89-10668 Automahon apphcabons for rotorcraft; Proceedings of Boundary-layer measurements on an airfoil at low Approxlmahon of free and bounded vortex sheets at the Nahonal Specialists' Meeting. Atlanta, CA, Apr 4-8, Reynolds numbers p 4 A89-10106 delta-wings p 11 A89-11500 1988 p 2 A89-12401 Two-dimensional model for airfoil unsteady drag below Inlet development for the NFAC 80- by 120-foot mdrafl AUTOROTATION stall p 4 A89-10114 wind tunnel Control of autorotational characteristics of light-airplane Turbulent boundary layer manipulation and modelhng IAIAA PAPER 88-25281 p 41 A89-12550 fuselages p 39 A89-12555 in zero and adverse pressure gradients ANGULAR DISTRIBUTION AVIONICS p46 A89-10159 Noise field of a propeller with angular inflow AFT I/F-16 votce interactive avionics evaluation Control of separated flow on a symmetric airfoil p89 A89-11102 t SAE PAPER 871751 I p 24 A89-10581 p 47 A89-10161 ANNULAR FLOW Avionic color liquid crystal displays - Recent trends Propulsive vortical signature of plunging and pitching Three component laser anemometer measurements in ISAE PAPER 8717901 p 31 A89-10585 alrfotls p 9 A89-11115 an annular cascade of core turbine vanes with contoured The V-22 vibration, structural life, and engine diagnostic Unsteady transonic airfoil computahon using implicit end wall system, VSLED Euler scheme on body-fixed god p 10 A89-11153 INASA-TP-28461 p 15 N89-10844 ISAE 8717321 p 31 A89-10617 Integral equation solution for transomc and subsonic ANTISUBMARINE WARFARE AIRCRAFT Lessons learned from developmental and operational aerodynamtcs p 11 A89-11488 Development and testing of an mfhght engine Steady and unsteady potential flows around turbine engine monitoring systems performance monitoring technique for the D S Navy P-3C ISAE AIR 1871BI p 35 A89-10624 axlsymmetric bodies and ring a_rfoils p 11 A69-11489 airplane Aerospace avionics equipment and integration: On the evaluation of aerodynamic influence ISAE 8414821 p 34 A89-10615 Proceedings of the Second Conference, Dallas, TX, Nov coefficients p 11 A89-11496 ANVIL CLOUDS 2-4, 1987 Low-Reynolds-number alrfod design for the MIT The electrical structure of thunderstorm anwls ISAE P-2051 p 48 A89-10676 Daedalus prototype - A case study p 12 A89 12559 p 56 N89 10470 UT1760A RTS A low-cost mon_hthlc remote terminal A potential theory for the steady separated flow about ARCHITECTURE stores interlace for MIL STD-1760A an aerofoil section Quadruplex d@tal fhght control system assessment I SAE PAPER 872481 I p 48 A89-10677 IARL-AERO-R-1761 p 13 N89-10005 INASA-CR-1827411 p40 N89 10058 Aeroelashc thermal effects p 37 N89-100 t 5 Advanced avionics architecture pave plltar Smgle-ch_p soluhon of MIL-STD-1553A and Experimental results for the Eppler 387 airfoil at low p 33 N89-10834 MIL-STD-1553B data communications Reynolds numbers m the Langley tow-turbulence pressure ARCHITECTURE (COMPUTERS) I SAE PAPER 8724881 p 48 A89 10683 tunnel Over the rainbow -- Avionics design and systems A candidate for hnear token-passing, high-speed data INASA-TM-40621 p 15 N89-10842 integration bus systems Tests on 3 NACA 0012 airfoil models of DFVLR in the I SAE PAPER 8724991 p 2 A89 10689 I SAE PAPER 8724941 p 49 A89-10686 HAL 0 3 tunnel: An assessment of 2-D wall interference Computing system conhguralion for fighter aircraft flight Token rotation hmer _mplementatlon ITM-AE-87051 p 15 N89-10847 control systems p 40 N89 10832 ISAE PAPER 8724971 p 49 A89-10688
A-4 SUBJECT INDEX CHIPS (ELECTRONICS)
Over the rainbow --- Avionics design and systems BLUFF BODIES BOW WAVES Schlleren measurements at the 10,000-foot sled track integration A computational study Of coherent struclures in the I SAE PAPER 872499j p 2 A89-t0669 wakes of two-dimensional bluff bodies I DE88-0127481 p 42 N89-10899 Circuit protection for advanced aircraft - A functional lAD-A1968201 p 53 N89-11188 BUS CONDUCTORS and historical perspective BLUNT BODIES Fiber optic buses and networks for advanced avionics t SAE PAPER 8725021 p 32 A89-10692 A computattonaf study of coherent structures in the architectures p 33 N89-10836 wakes of two-dimensional bluff bodies Operational findings from a Tra_ic Alert and Collision tAD-A1968201 p 53 N89-11188 Avoidance System (TCAS) evaluation BODY-WING AND TAIL CONFIGURATIONS C I SAE PAPER 8809431 p 32 A89-12321 Analytical and experimental research on aerodynamtcal A highly reliable computer for airborne apphcahons effects of wind shear on aircraft p 6 A89-10547 C-130 AIRCRAFT p 59 N89-10833 BODY-WING CONFIGURATIONS Contamination of environmental control systems in Advanced avionics architecture pave pillar Experimental investigahon of flow near a corner, part Hercules aircraft p 33 N89-10834 2 I MRL-R-1116} p29 N89-10040 Data and signal processing architectures for future tCERT-RT-OA-24/5025-AYDI p 17 N89-10861 CALCULATORS avionics p 33 N89-10835 BOEING AIRCRAFT Pockel calculator trend momforlng for gas turbine Fiber optic buses and networks for advanced avionics The Boeing 7J7 - The evoluhon of technology and engines architectures p 33 N89-10836 design t SAE 841461 I p 34 A89-10614 In-service evaluation of the Traffic Alert and Collision I SAE PAPER 6724051 p 27 A89_10632 CALIBRATING Aerospace technology - Windshear FAA: Boeing Avoidance System (TCAS) industry prototype Convergence schemes for an adaptive-wall wind IDOT/FAA/SA-B8/21 p 25 N89-10885 Windshear Training Aid program tunnel p 41 A69-12560 AXIAL FLOW I SAE PAPER 872441 I p 19 A89-10655 BOEING 727 AIRCRAFT Estimating electric field enhancement factors on an A doublet point method for the calculation of unsteady In-service evaluation of the Traffic Alert and Collision aircraft utilizing a small scale model: A melhod propeller aerodynamics p 11 A89-11497 evaluation p 21 N89-10454 Avoidance System (TCAS) industry prototype Experimental investigabon of the performance of a I DOT/FAA/SA-88/21 p 25 N89-10885 CANARD CONFIGURATIONS supersonic compressor cascade BOEING 747 AIRCRAFT Comparison of longitudinally stablhzed behawor in INASA-TM-1008791 p 16 N89-10858 R8211 developments vertical turbulence between a modern canard configuration AXISYMMETRIC BODIES and a conventional aircraft I SAE PAPER 6724091 p 35 A89-10635 Steady and unsteady potential flows around BOOMS (EQUIPMENT) I DGLR PAPER 87-0781 p 39 A89-10515 a_lsymmetr_c bodies and ring airfoils p 11 A69-11489 Development in helicopter tail boom strake appllcahons Flow around a delta wing with or without a canard (Phi m the US BA 60 deg) Part 2: Hydrodynamic vlsuahzahons m B INASA-TM-1014961 p 40 N89-10059 unsteady flow (pitchtng OSCillations) BOUNDARY ELEMENT METHOD IONERA-RT-11/289t-AN-PT-21 p 17 N89-10860
BACKWARD FACING STEPS Advanced boundary element methodsl Proceedings of CANOPIES Heat transfer in the reclrcu]abng region formed by a the IUTAM Symposium, San Antonio. TX, Apr 13-16, Simulation of a birdstr,ke Impact on aircraft canopy backward-facing step p 51 A69-12252 1987 p 47 A89-10182 materiat p 25 A89-10113 Investigation on of the flow around a backward facing BEM for wave equation with boundary tn arbitrary motion CARBON FIBERS and applications to compressible potential aerodynamics step with spanwise blowing Finite difference analysis Of exteroat and internal ICERT-RF-OA*68/2259_AYDI p 17 N89-10859 of airplanes and helicopters p 5 A89-10192 hghtnlng response of the JAS39 CFC wing BALANCE BOUNDARY INTEGRAL METHOD p 22 N89-10483 Steady-state unbalance responses for a multispan On the evaluation of aerodynamic influence tndlrect effects on e_ectronlc and mechanical systems rotor p 50 A89-11066 coefficients p 11 A89-11496 installed _n carbon fibre compound aircraft structures BELL AIRCRAFT BOUNDARY LAYER CONTROL p 22 N89-10492 Boundary-layer control for drag reduchon The V-22 vibration, structural life, and engine diagnostic CARIBBEAN REGION I SAE PAPER 8724341 p 6 A89-10651 system. VSLED Aviat_on technology applicable to developing regions BOUNDARY LAYER EQUATIONS I SAE 8717321 p 31 A89-10617 I NASA-TM-894251 p 23 N89-10872 A numerical simulation of separated flow around BIRD-AIRCRAFT COLLISIONS CARTESIAN COORDINATES two-dimensional wing by a discrete vortex method Simulahon of a blrdstrlke impact on a_rcraft canopy Generation of a god for a finite difference calculation p 6 A89-10568 material p 25 A89-10113 of flows around an aircraft in Cartesian coordinates Calculation of compressible flow and heat transfer on Bird hazards in awahon; Proceedings of the Sympeslum, 1NAL-TR-9561 p 58 N89-10563 London. England, Oct 14, 1987 p 3 A69-12716 a rotating disk p 50 A89-11033 BOUNDARY LAYER FLOW CASCADE FLOW The ciwl aviation birdstnke record p 20 A89-12717 A second-order numerical method for the analysis Of B_rd hazards m aviation - The RAF wew Dynamic distortion in flowfield downstream of transonic two dimens_ona_ flow of _deal fluid through a cascade w_th p 20 A89-12718 shock-boundary layer mterachon p 8 A89-11061 supersomc input p 6 A89-10607 Design and testing for airframes p 29 A69-12719 Approxtmate calculations of viscous drag and Flow performance of reversed tandem cascades with Windscreen design and teshng p 29 A89-12720 aerodynamic heahng p 10 A89-11157 double-circular arc profile for compressor stator Btrd hazards _n aviation - Safety and economic A transonic interacttve boundary-layer theory for laminar p 7 A89-11036 _mphcations for an airline p 20 A89-12721 and turbulent flow over swept wings Bird hazards in aviation - The regulatory authority's INASA-CR-41851 p 14 N89-10029 Numerical s_mulatlon of steady transonic flow past an responsibilities p 20 A89-12722 Invesbgahon on of the flow around a backward facing B-percent DCA cascade at a freestream Mach number The work of the Awation Bird Und p 3 A89-12723 step with spanwise blowing of about t p 8 A89-t 1073 BLADE SLAP NOISE ICERT-RF-OA-68/2259-AYDI p 17 N89-10859 Three component laser anemometer measurements m ACOUStiCS of transonic blade-vortex interactions Study of three dimensional boundary layers on the front an annular cascade Of core turbine vanes with contoured end wall p59 A89-11101 of a fuselage and at an air intake BLADE TIPS I CERT-OA-22/5025-AYDI p 53 N89-11184 t NASA-TP-28461 p 15 N89-10844 Computational and experimental studies of LEBUs at BOUNDARY LAYER SEPARATION Experimental investigation of the performance of a htgh dewce Reynolds numbers p 4 A89-10160 Boundary-layer measurements on an airfoil at low supersonic compressor cascade Profile development results for advanced Reynolds numbers p 4 A89-10106 {NASA-TM-1008791 p 16 N89o10858 circulation-guided rotor systems in last helicopters Expenmental results for the Eppler 387 airfoil at low Cascade flow analys_s by Navler-Stokes equation IDGLR PAPER 87-086l p 5 A89-10513 Reynolds numbers in the Langley low-turbulence pressure p 52 N89-11065 tunnel CASTING Application of end bend blade for enhancing surge margin p 36 A89-11051 I NASA-TM-40621 p 15 N89-10842 Directional spectral emlsslwty measurements on a Approach to blade end-bend mechanism Experimental research on swept shock wave/boundary ceramic mold matenal p 36 A89-11052 layer interactions IDE88-0154071 p 44 N89-10167 CENSUS A new approach lo improvement of fans lAD-A1969381 p 53 N89-11189 p 8 A89-11064 BOUNDARY LAYER STABILITY Census of US ciwl a_rcraft: Calendar year 1987 BLADE-VORTEX INTERACTION Suppression of unstable oscillations m a boundary j AD-A1966261 p 4 N89 11691 Profile development results for advanced layer p 5 ,_89-10171 CERAMICS On nonlinear aspects of hypersonic boundary-layer circulation-guided rotor systems in fast hehcopters Directional spectral emissivity measurements on a IDGLR PAPER 87 0861 p 5 A89-10513 stability p 10 A89-11116 ceramtc mold matenal Acoustics of transonic blade-vortex interactions Boundary layer transition I DE88-015407 t p44 N89-10167 p 59 A89-11101 ICEBT-OA-40/5018-AYDt p 53 N89-11187 Sensors for ceramic components in advanced BOUNDARY LAYER TRANSITION Prediction of atrcraft-propeller-lnduced, structure-borne propulsion systems: Summary of literature survey and interior noise p 28 A89-12564 Boundary-layer measurements on an airfoil at low concept analysis, task 3 report BLADES Reynolds numbers p 4 A89-10106 INASA-CR-1809001 . p54 N89-11192 Three-dimensional boundary layer transition on a A study of hehcopter stablhty and control including blade CHANNELS (DATA TRANSMISSION) dynamics concave-convex curved wall p 4 A89-10167 A candidate for hnear token-passing, high-speed data I NASA-CR- 1832451 p 40 N89-10895 Boundaryqayer control for drag reducbon bus systems BLOWDOWN WIND TUNNELS I SAE PAPER 8724341 p 6 A89-10651 I SAE PAPER 8724941 p 49 A89-10686 Flow past c_rcular cyhnder of finite length placed on Boundary layer transition effects on airplane stablhty and On h_gh-speed data bus performance analys_s control p 39 A89-12556 ground plane p 48 A89-10543 I SAE PAPER 872496] p 49 A89-10687 BLOWING BOUNDARY LAYERS CHIPS (ELECTRONICS) Flow performance of reversed tandem cascades with The characteristics of the ground vortex and ds effect S_ngle-ch_p soluhon of MIL-STD 1553A and MIL-STD-1553B data communications double-circular arc profile for compressor stator on the aerodynamics of the STOL configuration p 7 A89 11036 p 15 N89-10850 I SAE PAPER 8724881 p 48 A89 10683
A-5 CIRCUIT PROTECTION SUBJECT INDEX
CIRCUIT PROTECTION Turbofan forced mixer lobe flow modeling. Part 3: BEM for wave equation with boundary in arbitrary motion Circuit protection for advanced aircraft - A functional Application to augment engines and applications to compressible potential aerodynamics and historical perspective INASA-CR-41471 p 14 N89-10025 of airplanes and helicopters p 5 A89-t0192 I SAE PAPER 8725021 p 32 A89-10692 COMBUSTION PRODUCTS A numerical solution of transonic flow using International Aerospace and Ground Conference on Deposition of Na2SO4 from salt-seeded combustion discontinuous shock relation p 6 A89-10542 Lightning and Static Electricity gases of a high velocity burner rig p 43 A89-12330 Numerical experiments for separation flows around IPB88-1974391 p 55 N89-10429 COMBUSTION STABILITY trapezoidal cylinders by a discrete vortex method CIRCULAR CONES Active control of reheat buzz --- low-frequency p 8 A89-10569 A circular cone surface shaping method for fan blade combustion instabildy of jet aeroengine afterburners A second-order numerical method for the analysis of p 50 A89-11032 p43 A89-1t 103 two-dimensional flow of ideal fluid through a cascade with CIRCULAR CYLINDERS COMMAND AND CONTROL supersonic input p 6 A89-10607 Flow past circular cylinder of finite length placed on HOTEL Command and Control Systems Computational fluid dynamics in aerospace ground plane p 48 A89-t0543 ISAE PAPER 8809291 p 42 A89-12317 ISAE PAPER 8724461 p 7 A89-10859 Aerodynamically-driven condensate layer thickness Unified computation method of unsteady COMMERCIAL AIRCRAFT distributions on isothermal cylindrical surfaces supersonic/hypersonic flow past two dimensional flat plate Configuration optimization of commercial aircraft p 51 A89 12337 and rectangular wings IDGLR PAPER 87-081 I p 26 A89-10517 CIVIL AVIATION I SAE PAPER 8724471 p 7 A89-10660 Aspects of the control and stabilization of supersonic Lessons learned from an operational engine monitoring Numerical approach of advanced turboprop with commercial aircraft system and their correlation with luture developments three-dimensional Euler equations ISAE 8717331 p34 A89-10618 I DGLR PAPER 87-1221 p 39 A89-10519 I SAE PAPER 8724481 p 7 A89-10661 Interoperablhty of mddary and civil air-cargo systems The Boeing 7J7 - The evolution of technology and A study of the accuracy of wing calculations based on ISAE PAPER 8215551 p 19 A89-t0654 des0gn different schemes p 49 A89-10774 A world leader in engineering and maintenance I SAE PAPER 8724051 p 27 A89-10632 Application of an artificial density scheme of potential I SAE PAPER 872444 I p 1 A89-10657 RB211 developments stream function method to design of airfoil Fire safety at civil airports --- Russian book I SAE PAPER 8724091 p 35 A89-10635 p 7 A89-11053 p 19 A89-10718 European airworthiness control for the 1990s Analysis of transonic wings including viscous Fundamentals of fhght safety --. Russian book ISAE PAPER 8809361 p 2 A89-12320 interachon p 9 A89-11084 p 19 A89-10721 COMMUNICATION CABLES Numerical simulation of compact schemes in Air-traffic flow management today p 24 A89 12152 Lightning tests to measure the bulk current levels super-somc viscous flows p 9 A89-11085 Air navigation systems I - Astronomical navigation in associated with the electromc engine control of a turboprop Finite element method for calculating transonic potential the air 1919-1969 p 24 A89-t2449 commuter transport p 21 N89-10457 flow around airfoil from pressure minimum integration Air safety in the age of deregulation p9 A89-11088 Lightning and surge protection of large ground p 19 A89 12539 Numerical simulation of supersonic flow over a facilities p 52 N89-10474 The assurance of flight safety - A priority task in civil three-dimensional cavity p 9 A89-11105 COMMUNICATION SATELLITES aviation p 20 A89-12548 A new PNS code for chemical nonequilibrium flows The Australian Aviation Satellite System The civil aviation blrdstrike record p 20 A89-12717 p 9 A89-11106 I SAE PAPER 8724201 p 24 A89- t 0642 Design and testing for airframes p 29 A89-12719 Multigrid solution of the two-dimensional Euler equations Results of 1987 MSS helicopter propagation experiment Bird hazards in aviation - The regulatory authordy's on unstructured triangular meshes p 9 A89-11108 responsibilities p 20 A89-12722 at UHF and L band in Central Maryland Diagonal implicit multigrid algorithm for the Euler Census of US civil aircraft: Calendar year 1987 p 53 N89-11077 equations p 9 A89-11110 I AD-A1966261 p4 N89-1169t ETS-V propagation experiments in Japan Numerical simulation of the vortical flow over a CLIMATE CHANGE p 53 N89-11080 round-edged double-delta wing p t 0 A89-11 t 52 A numerical estimation of the deforestation effects on COMPARISON Finite element Euler computahons in three dimensions local chmate in the area of the Frankfurt international Finile difference analysis of external and internal p 11 A89-12130 airport p 55 A89-11554 lightning response of the JAS39 CFC wing Predichon of incidence effects on oscillating airfoil CLOUD HEIGHT INDICATORS p 22 N89-t0483 aerodynamics by a locally analytical method Laser control of visibility and cloud-base height in airfield COMPONENT RELIABILITY p 12 A89-12135 regions p 50 A89-11860 Forced vibration and flutter design methodology Transonic characterishcs of a humped airfoil CLOUDS (METEOROLOGY) p 51 N89-10018 p 12 A89-12551 Intracloud lightning as a precursor to thunderstorm COMPOSITE MATERIALS Incompressible Nawer Stokes computations for a microbursts p 56 N89-10490 Composites in shock and vibration isolation round-edged double-delta wing p 12 A89-12552 COANDA EFFECT p50 A89-1125t Transomc computations about complex conligurations Profile development results for advanced COMPOSITE STRUCTURES using coupled inner and outer flow equations circulation-guided rotor systems tn last helicopters Effect of adhesive debond on stress-intensity factors p 12 A89-12553 IDGLR PAPER 87-0861 p 5 A89 10513 in bonded composite panels p 45 A89-10091 Numerical solutions of induced velocd_es by semHnflnlte COCKPITS Fatigue testing of full-scale all-eomposde aircraft lip vortex lines p 12 A89-12554 Passive thermal protechon system p 26 A89-10478 wings Navler-Stokes solution to the flowfield over ice accretion The design eye reference point --- for determining ISAE PAPER 8724591 p 48 A89-10671 shapes p 12 A89-12557 geometric entdles defining cockpit layouts Lightning tests on an all-composite helicopter The pros and cons of code validation I SAE PAPER 8717631 p 31 A89-10582 p 21 N89-10452 INASA-TM-1006571 p 14 N89 10034 Should technology assist or replace the pilot? Finite difference analysis of external and internal Cascade flow analysis by Navier-Stokes equation I SAE PAPER 8807741 p 57 A89-10593 lightning response of the JAS39 CFC wing p52 N89-11065 Development and testing of an inflight engine p 22 N89-10483 Study of three dimensLonal boundary layers on the Iront performance monitoring technique for the US Navy P-3C Indirect effects on electronic and mechanical systems of a fuselage and at an air intake airplane installed in carbon fibre compound aircraft structures ICERT-OA-22/5025-AYDI p53 N89-11184 ISAE 8414621 p 34 A89-10615 p 22 N89-10492 Boundary layer transition AIR 1900 - Guide to temperature monitoring in aircraft Tension fatigue analysis and hie prediction for composite I CERT-OA-40/5018-AYD I p53 N89-11187 gas turbine engines laminates Experimental research on swept shock wave/boundary ISAE 8717301 p 34 A89-10616 I NASA-TM-1005491 p 44 N89-10951 layer interactions Design and evaluahon of a cockpit display for hovenng COMPRESSIBLE FLOW I AD-A1969381 p53 N89-11189 flight BEM for wave equation with boundary in arbitrary motion COMPUTATIONAL GRIDS INASA-CR-1832471 p 42 N89-10900 and applleahons to compressible potential aerodynamics Diagonal implicit multigrld algorithm for the Euler CODES of airplanes and helicopters p 5 A89-10192 equations p 9 A89-t 1110 Rule-based string code processor p 57 A89-11750 Calculation of compressible flow and heat transfer on The prediction of transonic interference flow by means COLD WORKING a rotating disk p 50 AB9-t t033 of a hybrid method p 10 A89-11487 Fatigue life influence of residual stresses from cold Finite element Euler computations in three dimensions Finite element Euler computations in three dimensions working and high spectrum loads in aircraft structural p 11 A89-12130 p 11 A89 12130 COMPRESSOR BLADES design p 46 A89-10099 Transonic computations about complex configurations COLLISION AVOIDANCE A dynamic characteristic analysis of a bladed disk using coupled inner and outer llow equahons Operational findings from a Traffic Alert and Colhslon assembly p 36 A89-11026 p 12 A89-12553 Flow performance of reversed tandem cascades with Avoidance System (TCAS) evaluation Nawer-Sfokes simulation of transonic wing flow lields double-circular arc profile for compressor slator I SAE PAPER 8809431 p 32 A89-t2321 using a zonal gnd approach p 7 A89-11036 In-service evaluahon of the Traffic Alert and Collision INASA-TM-1000391 p 13 N89-10022 COMPRESSORS Avoidance System (TCAS) industry prototype Generahon of a grid for a fmde 'difference calculahon T55-L-712 turbine engine compressor housing I DOT/FAA/SA-88/2t p 25 N89-10885 of flows around an aircraft in Cartesian coordinates refurbishment-plasma spray proiect COMBAT I NAL-TR-9561 p 58 N89o10563 I NASA-TM-1013101 p44 N89-10158 TEAS - An AI based threat response recommendation COMPUTATIONAL FLUID DYNAMICS Study of three dimensional boundary layers on the front system Turbulence management and relaminarisation; of a fuselage and at an air intake 1SAE PAPER 8718041 p 57 A89-10589 Proceedings of the IUTAM Symposium, Bangalore, India, I CERT-OA-22/5025-AYD I p53 N89-11184 COMBUSTION CHAMBERS Jan 19-23, 1987 p46 A89-t0154 COMPUTER AIDED DESIGN A design method of 'wlgglestrap' film-coohng Computational and expebmental studies of LEBUs at Multilevel decomposdion approach to the preliminary construction of flame tube p 50 A89-11039 high device Reynolds numbers p 4 A89-10160 sizing of a transport aircraft wing p 25 A89-10109 Calculations of the unsteady, three-dimensional flow Advanced boundary element methods; Proceedings of Improvement of a design code for airfoils at transonic field inside a motored Wankel engine the IUTAM Symposium, San Antonio, TX, Apt 13-16, regime I SAE PAPER 8806251 p 37 A89-12307 1987 p 47 A89-10182 I DGLR PAPER 87-064 I p 5 A89-10511
A-6 SUBJECT INDEX DEBRIS
CAD wind tunnel test for half-cut model of Asuka The 1987 Ground Vortex Workshop CRASH LANDING p 18 N89-11069 INASA-CP-100081 p 15 N89-10849 Aircraft accident report: Executive Air Charter. Inc, dba COMPUTER NETWORKS CONFIDENCE Amer,can Eagle. Flight 5452. CASA C-212. N432CA, Fiber optic buses and networks for advanced avionics On the appropriateness of applying chi-square Mayaguez, Puerto R_co, May 8, 1987 architectures p 33 N89-10836 distribution based confidence intervals to spectral I PB88-9104091 p 23 N89-10873 High speed parallel processing networks for advanced estimates of helicopter flyover data Aircraft crashes on the runway: Development of a super architectures p 59 N89-10837 INASA-CR-1816921 p 59 N89-10601 element for nonlinear analysis of a beam COMPUTER PROGRAMMING CONTAMINANTS I REPT-87/56I p 54 NB9-11286 Programming techniques for high-speed processing on Contamination of environmental control systems m CREEP RUPTURE STRENGTH Hercules aircraft the supercomputer FUJITSU VP-system Influence of regeneration treatments on creep rupture iNAL-TR-gt51 p 58 N89-10565 IMRL-R-11161 p 29 N89-10040 lives of turbine blades p 43 A89-11214 CONTAMINATION COMPUTER PROGRAMS CREEP TESTS A comparative evaluation of RPD (Rotary Part,cle Method to optimize nacelle shape ,n a supersonic cruise Creep tests for slow and fast fabgue conditions on Depositor) and ferrographic diagnosbc methods for turbine aircraft p 28 A89-12558 aluminum alloy specimens engine lubricant samples Validation of a pair of computer codes for estimation I REPT-M0-5352001 p 45 N89-11020 and optimization of subsollic aerodynamic performance I AD-A196207] p 38 N89-10044 CRUISING FLIGHT CONTINUUMS of simple hinged-flap systems for thin swept wmgs Flight-test determination of aircraft cruise charactenstics Continuum theories for fluid-particle flows: Some I NASA-TP-28281 p 13 N89-10024 usmg acceleration and deceleration techniques aspects of lift forces and turbulence p 53 N89-11 t 55 A filamentary method for caleulating induced voltages p 25 A8g-10101 within resistive structures in either the frequency or time CONTRAROTATING PROPELLERS Method to optimize nacelle shape in a supersonic cruqse domain p 52 N89-10484 Unsteady loading noise of counter-rotating propeller aircraft p 28 A89-12558 Hardware fault inserf_on and instrumentation system: p 36 A89-11054 The effect of front-to-rear propeller spacing on the Experimentation and results CONTROL SYSTEMS DESIGN interaction noise at cruise conditions of a model I NASA-CR-1827461 p58 N89-10526 C_rcuit protection for advanced aircraft - A functional counterrotation propeller having a reduced diameter aft Programming techniques for high-speed processing on and historical perspective propeller the supercomputer FUJITSU VP-system I SAE PAPER 8725021 p 32 A89-10692 INASA-TM-1013291 p 60 N89-10603 I NAL-TR-9151 p58 N89-10565 Design and evaluation of dynamic flight test CRYOGENIC ROCKET PROPELLANTS Computing Systems Configuration for Highly Integrated manoeuveres Technology issues associated w_th fueling the national Guidance and Control Systems I PB88-2107601 p 29 N89-10042 aerospace plane with slush hydrogen IAGARD-LS-1581 p 3 Nsg-10831 Functional mock-up tests of the flight control system I NASA-TM-1013861 p43 N89-10123 Computing system configuration for fighter aircraft flight of the NAL QSTOL research aircraft: Planning and CRYOGENIC WIND TUNNELS control systems p 40 N89-10832 mechanical system test Highlights of experience with a flexible walled test Some statistical aspects of attrition studies INAL-TR-9441 p 40 N89-10047 section in the NASA Langley 0 3-meter transonic cryogenic I AD-A196665 t p30 N89-10891 tunnel Computing Systems Conhguration for H_ghly Integrated COMPUTER SYSTEMS PROGRAMS I NASA-TM-101491 I p 41 N89-10060 Guidance and Control Systems Flight mechanics and aerothermodynamic software CRYSTAL DEFECTS fAGARD-LS-1581 p 3 N89-10831 ]CNES-CT/DTI/MS/MN/069] p 4 N89-10839 M_crostructural optimisation of titanium alloys for defect COMPUTER VISION Computing system configuration for hghter aircraft flight tolerance in gas turbine engine components control systems p 40 N89-10832 Rule-based string code processor p 57 A89*t 1750 p 43 A89-10069 Advanced avionics archdecture pave pdlar A hierarchical control strategy for 2-D oblect CYCLIC LOADS p 33 N89-10834 recogndlen p 57 A89-11760 Effect of protective coatings on life of heat-resistant COMPUTERIZED SIMULATION CONTROLLABILITY nickel steel under cychc heat load p 45 N89-1 t 005 Development of a helicopter simulation program Modal observability and controllability measures for hrst I DGLR PAPER 87-1231 p 26 A8g-10520 and second order linear systems and model reduction Automated landing approach using machine seeing p 57 A89-11680 D I DGLR PAPER 87-131 I p 23 A89-10522 CONVECTION CURRENTS Computer program for simulating dynamic gliding flight Oklahoma-Kansas preliminary regional experiment for DAMAGE IDGLR PAPER 87-135/21 p27 A89-10527 storm-central (C)-K pre-storm). Volume 3: A,rcraft mission Wheel performance evaluation Phase 1: Analysis Low-Reynolds-number airfoil design for the M.I.T. summary I DOT/FAA/CT-88/161 p 29 N89-10041 Daedalus prototype - A case study p 12 A89-12559 I PB88-2054891 p 56 N89-10499 Israel Air Force OAF) in-service aircraft lightning stnke On the diagnostic emulation technique and its use in CONVERGENCE and damage survey p 55 N89-10431 the AIRLAB DATA ACQUISITION Convergence schemes for an adaptive-wall wind I NASA-TM-40271 p 58 N89-10524 tunnel p 41 A89-12560 Lightning information database p 55 N89-10432 An approximate, maximum terminal velocdy descent to CONVERGENT-DIVERGENT NOZZLES Prototype data acquisition and analysis system for Navy a pont operational flight simulators Dynamic distortion in flowfleld downstream of transonic I DE88-0003491 p 15 N89-10840 I DE88-0145571 p 42 N89-10901 shock-boundary layer interaellon p 8 A89-11061 Investigation of the tumbling phenomenon using Electrical noise reduction lechniques contributing to CORNER FLOW computer simulation p 41 N89-10896 _mproved data quality at the National Transonic Facihty Experimental investigation of flow near a corner, part INASA-CR-41931 p 54 N89-11196 Sandla National Laboratories flight simulation facilities 2 IDE88-0121081 p 42 N89-10898 DATA BASE MANAGEMENT SYSTEMS ICERT-RT-OA-24/5025-AYDI p 17 N89-10861 CONDENSATES Coping with legacy factors --- in data base management COST EFFECTIVENESS Aerodynamically-driven condensate layer thickness systems integrat_on p 5B A89-12176 distributions on isothermal cylindrical surfaces Cost-effective strapdown INS design and the need for DATA BASES p 51 A8g-12337 standard tiight profiles p 30 A89-10128 Lightning information database p 55 N89-10432 CONFERENCES Unique research challenges for high-speed civil DATA CORRELATION Adhesively bonded joints: Testing, analysis, and design: transports StafiSbCS of lightning interaction with aircraft in Japan Proceedings of the International Symposium, Baltimore. I SAE PAPER 8724001 p 1 A89-10629 p 55 N89-10430 MD. Sept. 10-12, 1986 p 45 A89-10076 COST REDUCTION DATA PROCESSING Swedish Symposium on Residual Stresses, Sunne, The Boeing 7J7 - The evoluhon of technology and Linear and nonlinear interpretation of CV-580 lightning Sweden, Mar. 30-Apt 2. 1987, Proceedings design data p 21 N89-10451 p 46 A89-10096 I SAE PAPER 8724051 p 27 A89-10632 Data and signal processmg archdectures for future Turbulence management and relaminarisatidn: COUNTER ROTATION awonics p 33 N89-10835 Proceedings of the IUTAM Symposium. Bangatere, India, The eftect of front-to-rear propeller spacmg on the DATA REDUCTION Jan. 19-23, 1987 p 46 A89-10154 interaction noise at cruise conditions of a model Non-linear aerodynamic characteristics obtained from Advanced boundary element methods: Proceedings of counterrotation propeller hav,ng a reduced diameter aft the analysis of flight-data the IUTAM Symposium, San Antonio. TX. Apr 13-16, propeller tAR-004-571 I p 18 N89-10866 1987 p 47 A89-10182 INASA-TM-1013291 p 60 N89-10603 DATA STRUCTURES Multignd solution of the two-dimensional Euler equations International Pacific Air and Space Technology COUNTERFLOW Conference, Melbourne, Australia, Nov. 13-17, 1987, Weak-wave analys,s of shock interaction with a on unstructured triangular meshes p 9 A89-11108 Proceedings slipstream Symmetric (and generic) algorithms for height balanced trees ISAE P-2081 p I A89-10627 I NASA-TP-28481 p 13 N89-10020 Aerospace awomcs equipment and integration; 10S-8711 I p 59 N89-12332 COUPLINGS Proceedings of the Second Conference, Dallas, TX, Nov DATA TRANSMISSION Aeroelastic coupling: An elementary approach 2-4, 1987 p 37 N89-10012 Single-chip solution of MIL-STD-1553A and I SAE P-2051 p 48 A89-10676 MIL-STD-1553B data communications CRACK PROPAGATION Fracture mechanics; Proceedings Of the Nineteenth I SAE PAPER 8724881 p 48 A8g-10683 Microstructural optimisation of titanium alloys for defect National Symposium, San Antonio, TX, June 30-July 2, DEBRIS tolerance in gas turbme engine components 1986 p 50 A89-11426 F_eld experience with quantdatlve debris monitoring p 43 A89-10069 Automation applications for rotercraff; Proceedings of I SAE 8717361 p 34 A89-10620 the National Specialists' Meeting, Atlanta, GA, Apr. 4-6, Fatigue crack growth in aircraft main landing gear Guide to oil system monitoring in aircraft gas turbine wheels p 28 A89-11447 1988 p 2 A89-12401 englnes Bird hazards in aviation; Proceedings of the Symposium. Wheel performance evaluation Phase t: Analysis ISAE AIR 18281 p 35 A89-I0622 London. England, Oct. 14. 1987 p 3 A89-12716 ( DOT/FAA/CT-88/16t p29 N89-10041 A comparative evaluahon of RPD (Rotary Particle International Aerospace and Ground Conference on A study of the fatigue behavior of small cracks ,n Depositor) and ferrographlc diagnostic methods for turbine Lightnmg and Static Electricity nickel-base superalleys engine lubricant samples IPB88-1974391 p 55 N89-10429 I AD-At954891 p44 N89-10161 IAD-At 962071 p 38 N89-10044
A-7 DECIDUOUSTREES SUBJECT INDEX
DECIDUOUS TREES AIR 1900 - Guide to temperature monitoring in aircraft EFFICIENCY Results of 1987 MSS helicopter propagation experiment gas turbine engines Expenmental aerodynamic performance o1 advanced 40 at UHE and L band in Central Maryland ISAE 8717301 p 34 A89-10616 deg-swept 10-blade propeller model at Mach 06 to 0 85 p53 N89-11077 Design and evaluation of a cockpit display for hovering I NASA-TM-889691 p 17 N89-10865 DECISION MAKING flight EIGENVALUES Aeronautical decision making for air ambulance J NASA-CR-183247 I p 42 N89-10900 New trial of vibration testing method helicopter pi_ots: Situational awareness exercises DISTRIBUTED PROCESSING p52 N89-11068 EJECTION SEATS I DOT/EAA/DS-88/61 p 23 N89-10869 A candidate for linear token-passing, high-speed data DECOUPLING Aerodynamic characteristics of the ACES-II ejection seat bus systems at transonic Mach numbers p 25 A89-10463 The use of the complex summation method for I SAE PAPER 8724941 p 49 A89-10686 formulating algorithms for decoupling vertical/horizontal Multi-axis seat ejection (MASE) sled DISTRIBUTION (PROPERTY} motions of rolhng a_rcraft p 30 N89-10889 p 26 A89-10466 A filamentary method for calculating induced voltages DEFENSE PROGRAM An investigation of the pressure m an ejection seat bay within resistive structures in either the frequency or time Military aerospace technical development in Australia due to rocket jet p 26 A89-10482 domain p 52 N89-10484 ISAE PAPER 8724261 p 1 A89-10646 EJECTORS DOPPLER RADAR DEFORESTATION Reduction of ejector noise with multihole nozzle Intracloud lightmng as a precursor to thunderstorm A numerical estimation of the deforestation effects on p 38 A89-11034 mlcrobursts p 56 N89-10490 local climate in the area of the Frankfurt international Expenmental investigation of convergent ejector DRAG airport p 55 A89-11554 nozzle/afterbody in wind tunnel p 8 A89-11060 DEFORMATION Continuum theories for fluid-parhcle flows: Some ELASTIC PROPERTIES Longitudinal impact test of a transport airframe section aspects of lift forces and turbulence p 53 N89-11155 New trial of vibration testing method I DOT/FAA/CT 87/261 p 54 N89 11265 DRAG REDUCTION p 52 N89-11068 DEICING Investigations on high Reynolds number laminar flow ELECTRIC BRIDGES Automated optical instrument for extracting water droplet airfoils p 4 A89-10102 The dual element method of strain gauge temperature impingement data from wind tunnel experiments Computational and experimental studies of LEBUs at compensation p 51 A89-12276 p 47 A89 10261 high device Reynolds numbers p 4 A89-10160 ELECTRIC CHARGE De-icing of aircraft turbine engine inlets Boundary-layer control for drag reduction A chronology of in-cloud electric field and lightning I DOT/FAA/CT 87/371 p 38 N89-10894 I SAE PAPER 8724341 p 6 A89-10651 strikes on an instrumented research aircraft DELTA WINGS DROPS (LIQUIDS) p 21 N89-10455 Aspects of the control and stabdlzahon 01 supersonic Automated optical instrument for extracting water droplet Lightning initiation on aircraft in thunderstorms commercial aircraft impingement data from wind tunnel experiments p 21 N89-10456 I DGLR PAPER 87 1221 p 39 A89-10519 p 47 A89-10261 ElectrificaPon of hovering helicopters p 22 N89-10460 An experimental study on aerodynamic performance of DURABILITY Lipplsch-type GEW - Ground Effect Wing Measurement of the electrostatic charging on large Environmental durability of adhesively bonded joints p 6 A89-10544 helicopters and control of the shock hazard p 46 A89-10095 Numerical simulation of the vortical flow over a p 22 N89 10461 DUST round-edged double-delta wing p 10 A89-11152 The electrical structure of thunderstorm anvils A comparative evaluation of RPD (Rotary Parhcle Approximation of free and bounded vortex sheets at p 56 N89-10470 Depositor) and ferrographic diagnoshc methods for turbine delta-wings p 11 A89-11500 ELECTRIC CORONA engine lubncant samples Incompressible Navier-Stokes computations for a Lightn.lg initiation on aircraft in thunderstorms lAD-A1962071 p 38 N89-10044 round edged double-delta wing p 12 A89-12552 p 21 N89-10456 Plow around a delta wing with or without a canard (Phi Electrlflcahon of hovenng hehcopters ELECTRIC CURRENT BA 60 deg) Part 2: Hydrodynamic visualizations in p 22 N89-10460 A filamentary method for calculating induced voltages unsteady flow (pitching oscillations) DYNAMIC PRESSURE within resistive structures in either the frequency or time IONERA-RT-11/2891-AN PT 21 p 17 N89-10860 Inlel development for the NFAC 80 by 120-foot indraft domain p 52 N89-10484 Three dimensional shear flow Analysis of the flow in wind tunnel Modelhng of common mode coupling between an aircraft a delta arrow wing with incidence angle IAIAA PAPER 88-25281 p 41 A89-12550 wing traversed by a hghtmng current and wiring installed ICERT-RTS-OA-25/5025AYDI p 17 N89-10864 DYNAMIC RESPONSE in that wing p 22 N89-10485 Unsteady low-speed wlndtunnel test of a straked delta Steady-state unbalance responses for a mulhspan ELECTRIC DISCHARGES wing. oscillating in pitch Part 1 General description and rotor p 50 A89-11066 Electrostatic discharge and field effects of electronics discussion of results Design and evaluahon of dynamic flight test systems p 52 N89-10493 lAD-A1964561 p 18 N89-t0867 manoeuveres ELECTRIC EQUIPMENT DESCENT I PB88-2107601 p 29 N89-10042 The history of aircraft onboard equipment An approximate, maximum terminal velocity descent to Vlbrahon, performance, flutter and forced response I DGLR PAPER 87-054q p 31 A89-10536 ELECTRIC FIELDS a point charactenstics of a large scale propfan and its aeroetastic IDE88-0003491 p 15 N89-10840 model An aircraft-borne electric field measunng system for rocket launch support p 55 N89.10443 An assessment of ground effects determined by static I NASA-TM-1013221 p38 N89- t 0043 New electric field instrumentation and the effects of and dynamic testing techniques p 16 N89-10854 Response of discretely stiffened structures and transmission of structure-borne noise space charge at Kennedy Space Center DESIGN ANALYSIS p 55 N89-10444 Quadruplex d@tal fhght control system assessment p54 N89-11270 Summary of inflight data on lightning currents and DYNAMIC STRUCTURAL ANALYSIS I NASA CR-1827411 p 40 N89-10058 fields p 56 N89-10449 A dynamic characteristic analysis of a bladed disk Design and evaluation of a cockpit display for hovering Estimating electnc field enhancement factors on an fhght assembly p 36 A89-t 1026 aircraft uhhzing a small scale model: A method [NASA-CR-183247 I p 42 N89-10900 Steady-state unbalance responses for a multlspan evaluation p 21 N89-10454 DEVELOPING NATIONS rotor p 50 A89-11066 A chronology of m-cloud electnc field and lightmng Aviation technology applicable to developing regions AGARD manual on aeroelasticity in axial-flow strikes on an instrumented research aircraft I NASA-TM-894251 p 23 N89-10872 turbomachlnes Volume 2 Structural dynamics and p 21 N89 10455 DIFFUSERS aeroelastlclty The electrical structure of thunderstorm anvils Two-dimensional subsonic ddluser flow with uniform IAGARD AG 298 VOL-21 p 13 N89-10006 p 56 N89-10470 shear velocity profile at inlet p 7 A89-11056 Aeroelastic coupling: An elementary approach ELECTRIC POTENTIAL DIGITAL COMPUTERS p 37 N89-10012 A filamentary method for calculating induced voltages Hardware fault insertion and instrumentation system: Aeroelastic formulation for luned and mlstuned rotors within resistive structures in edher the frequency or time Experimentation and results p 37 N89-10013 domain p 52 N89-10484 ELECTRIC POWER TRANSMISSION INASA-CR-1827461 p 58 N89-10526 Flight test results for the Daedalus and Light Eagle DIGITAL DATA human powered aircraft Modelling of common mode coupling between an aircraft wing traversed by a lightning current and wiring installed Digital recording of radar data in an aircraft I NASA-CR-1833051 p 30 N89-10890 in that wing p 22 N89-10485 I PB88-2095071 p 51 N89-102t2 Response of discretely stdlened structures and ELECTRIC WIRE DIGITAL SIMULATION transmission of structure-borne noise Modelhng of cornmon mode coupling between an aircraft Numerical simulation of the vortical flow over a p 54 N89 11270 wing traversed by a lightning current and wiring installed round-edged double-delta wing p 10 A89-11152 Aircraft crashes on the runway: Development of a super in that wing p 22 N89-10485 element for nonhnear analysis of a beam Numerical s=mulatlon of transonic flow around Asuka ELECTRICAL GROUNDING p 18 N89-11067 I REPT-87/561 p 54 N89-11286 Measurement of the electrostatic charging on large DIGITAL SYSTEMS hehcopters and control of the shGck hazard Quadruplex digital fhght control system assessmenl E p 22 N89-10461 INASA-CR-182741 I p 40 N89-10058 Ltghtmng and surge protection of large ground Hardware fault insertion and instrumentation system EARTH ORBITAL ENVIRONMENTS facdlhes p 52 N89-10474 Experimentation and results HOTEL Command and Control Systems System protection from atmospheric olectncity for I NASA-CR-1827461 p 58 N89-10526 I SAE PAPER 8809291 p 42 A89 12317 aerostats with conducting tethers p 52 N89-10497 DISPLAY DEVICES ECONOMIC FACTORS ELECTRICAL MEASUREMENT Image quality and visual simulation of color matrix Bird hazards in aviation - Salety and ecorlomlc International Aerospace and Ground Conference on displays implications for an airhne p 20 A89 12721 Lightning and Static Electricity ISAE PAPER 8717891 p 57 A89-10584 ECONOMIC IMPACT I PB88-1974391 p 55 N89-10429 Avionic color liquid crystal displays - Recent trends A Canadian government look at airworthiness An aircraft-borne electric field measuring system for ISAE PAPER 8717901 p 31 A89-10585 I SAE PAPER 8809351 p 2 A89-12319 rocket launch support p 55 N89-10443
A-8 SUBJECTINDEX FATIGUE LIFE
New eleclnc field instrumentation and the effects of Pocket calculator trend monitoring for gas turbine ESTIMATES space charge at Kennedy Space Center engines Estimating electric field enhancement factors on an p 55 N89-10444 leAF 841461 } p 34 A89-10614 aircraft utilizing a small scale model A method A case for a unified lightning threat Development and test,ng of an inflight engine evaluation p 21 N89-10454 p 56 N89-10447 performance monitoring technique for the U S Navy P-3C EULER EQUATIONS OF MOTION airplane Summary of mflight data on Iighming currents and Numerical approach of advanced turboprop with fields p 56 N89-10449 I SAE 8414621 p 34 A89-10615 three-dlmens,onal Euler equations Anatysts of recent in41ight lightning measurements on AIR 1900 - Guide to temperature monitoring *n aircraft t SAE PAPER 8724481 p 7 A89-10661 different aircraft p 20 N89-10450 gas turbine engines Mulbgnd solution of the two-dimensional E uler equations Estimating electric field enhancement factors on an ISAE 871730J p 34 AB9+10616 on unstructured triangular meshes p 9 A89-11108 aircraft utilizing a small scale model: A method The V-22 vibration, structural hfe. and engine diagnostic Diagonal _mpliclt multigrid algorithm for the Euler evaluation p 21 N89-10454 system, VSLED equations p 9 A89-11110 A chrono{ogy of in-cloud electric field and hghtning I SAE 8717321 p 31 A89-10617 Integral equation solution for transonic and subsonLc strikes on an instrumented research aircraft Lessons learned from an operational engine monitoring aerodynamics p 11 A89-11488 p 21 N89-10455 system and their correlation with future developments Lightning tests to measure the bulk current levels t SAE 8717331 p34 A89-10618 Finite element Euler computahons m three dimensions associated with the electronic engine control of a turboprop Gas turbine engine monitoring systems - Helicopter p 11 A89-12130 commuter transport p 21 N89-10457 expenence EVALUATION Measurement of the electrostatic charging on large ISAE 8717351 p 34 A89-10619 Design and evaluahon of a cockpit display for hovering helicopters and control of the shock hazard Field experience with quantitative debris monitoring flight p 22 N89-10481 I SAE 8717361 p 34 A89-10620 I NASA-CR-t 83247 i p 42 N89-10900 ELECTRICAL RESISTIVITY Texmas - An expert system for gas turbine engine EXHAUST GASES Linear and nonlinear interpretation of CV-580 lightning diagnosis and more Electrification of hovering helicopters data p 21 N89-10451 I SAE 8717371 p 34 A89-10621 p 22 N89-10460 Estimating electric field enhancement factors on an Guide to oil system monitoring in aircraft gas turbine The 1987 Ground Vortex Workshop aircraft uhhzing a small scale model: A method engines tNASA-CP-100081 p 15 N89-10849 evaluation p 21 N89-10454 I SAE AIR 18281 p 35 A89-10622 EXHAUST NOZZLES ELECTROMAGNETIC NOISE A guide 1o aircraft turbine engine vibration monitonng Effects of a ground vortex on the aerodynam,cs of an systems Interference of precipitation static discharges with alrfo_l p 16 N89 10855 I SAE AIR 1839I p 35 A89-10623 aircraft navigational systems p 21 N89-10459 EXPERT SYSTEMS ELECTROMAGNETIC RADIATION Lessons learned from developmental and operational Texmas - An expert System for gas turbine engine interference of precipitation static discharges with turbine engine monitoring systems diagnosis and more I SAE AIR 1871BI p 35 A89-10624 aircraft nawgational systems p 21 N89-10459 ISAE 8717371 p 34 A89-10621 ELECTRONIC EQUIPMENT Guide to life usage monitonng and parts management A taclics expert system for scout/attack rotorcraft E_ectroslahc discharge and field effects of electronics for aircraft gas turbine engines p 58 A89-12408 systems p 52 N89-10493 ISAE AIR 18721 p 35 A89-10625 A hybnd knowledge-based approach to AH-64A fault Hardware fault insertion and instrumentation system: Guide to bruited engine monltormg systems for aircraft isolahon p 2 A89-12409 Experimentation and results gas turbine engines Implementation of knowledge-based systems for l NASA-CR-1827461 p 58 N89-10526 ISAE AIR 18731 p 35 A89-10626 hehcopter machinery fault prognosrs p 2 A89-12412 ELECTROSTATIC CHARGE New concepts m helicopter machinery prognostics Development of a rule-based demonstration prototype Measurement of the electrostatic charging on large p 2 A89-12408 expert system for inflight emergencies for the UH1H helicopters and control of the shock hazard ENGINE NOISE hehcopter p 32 A89-12415 Unsteady loading no_se of counter+rotating propeller p 22 N89-10461 EXTERNAL STORES ELECTROSTATICS p 36 A89-11054 UT1760A RTS - A lOW-COSt monohthic remote terminal ENGINE PARTS Electrostatic discharge and field effects of electronics stores interface for MIL-STD-1760A Microstrucfural optimisation of titanium alloys for defect systems p 52 N89-10493 I SAE PAPER 872481 I p 48 A89-10677 EMERGENCY LIFE SUSTAINING SYSTEMS tolerance in gas turbine engine components Efficient vibration mode analysis of aircraft with multiple p 43 A89-10069 Ouahfication and operational aspects of light weight external store configurations p 28 A89-12562 SKAD (hght weight survival kit air droppabte) Guide to life usage monitoring and parts management p 18 A89-10471 for aircraft gas turbine engines ENGINE AIRFRAME INTEGRATION t SAE AIR 18721 p 35 A89-10625 F Propulsion-airframe integration for commercial and Control of the low-cycle service life of the primary military aircraft components of aircraft turbine engines according to the F-15 AIRCRAFT I SAE PAPER 872411 I p 35 A89-10637 damage-tolerance concept p 37 A89-11075 F-15 SMTD low speed jet effects wind tunnel test ENGINE CONTROL ENGINE TESTS results p 16 N89-10853 Establishment of variable vane regulation law Results of acoustic tests of a prop-fan model F-16 AIRCRAFT p 36 A89-11044 p 59 A89-10112 AFTI/F-16 voice interacbve avionics evaluation Lightmng tests to measure the bulk current levels A let thrust measurement method w_th gas composition ISAE PAPER 871751 I p 24 A89-10581 associated with the electronic engine control of a turboprop analysis p 36 A89-11040 Israel Air Force (IAF) in-service aircraft lightning strike commuter transport p 21 N89-I0457 Aeroelastic thermal effects p 37 N89-10015 and damage survey p 55 N89-10431 ENGINE DESIGN Shock tunnel studies of scramjel phenomena F-18 AIRCRAFT RB211 developments I NASA-CR-181721 I p 38 N89-10045 tntroduchon of the Hornet - A success story dSAE PAPER 8724091 p 35 A89-10635 Alternate fuels for Genera_ Aviation aircraft with spark ISAE PAPER 8724361 p 27 A89-10653 Gas turbine engine development partnerships ignition engines Some statistical aspects of attnhon studies I SAE PAPER 8724101 p 35 A89 10636 I DOT/FAA/CT-88/051 p 44 N89-10179 lAD-A1966651 p 30 N89-10891 Propulsion-airframe integration for commercial and ENVIRONMENT EFFECTS FABRY-PEROT INTERFEROMETERS military aircraft A study on effects of aircraft noise environment On its Three component laser anemometer measurements in I SAE PAPER 872411 I p 35 A89-10637 structure an annular cascade of core turbine vanes with contoured Propfan design by propeller-nacelle interaction I SAE PAPER 8724501 p 28 A89-10663 end wall analys,s p 36 A89-11055 ENVIRONMENTAL MONITORING INASA-TP-28461 p 15 N89-10844 Expenence with the development of turboprop Contamination of environmental control systems m FAILURE ANALYSIS eng,nes p 37 A89-11074 Hercules aircraft Reasoning about device behavior using qualitative Calculations of the unsteady, three-dimensional flow I MRL-R-11161 p29 N89-10040 physics --- helicopter diagnostics p 58 A89-12410 field inside a motored Wankel engine ENVIRONMENTAL TESTS On the diagnoshc emulahon technique and its use in I SAE PAPER 880625 t p 37 A89-12307 Environmental durabihty of adhesively bonded ioints the AIRLAB ENGINE FAILURE p 46 A89-10095 I NASA-TM-40271 p 58 N89-10524 Field experience wdh quantltatwe debris monitoring EPOXY RESINS FAILURE MODES ISAE 871736) p 34 A89-10620 Lightning tests on an aft-composite helicopter Guide to oil system monitoring in aircraft gas turbine Bevel gear resonance failures in central gearing system p 21 N89-10452 engines of an aeroenglne p 50 A89-11046 EQUATIONS OF MOTION t SAE AIR 18281 p 35 A89-10622 Statistics on atrcraft gas turbine engine rotor failures Aerodynamic design considerations for a free-flying Bevel gear resonance failures in central gearing system that Occurred in US commercial aviation during 1982 ducted propeller of an aeroengine p 50 A89-11046 IDOT/FAA/CT-88/23t p 38 N89-10892 IDE88-0068671 p 15 N89-10841 FAN BLADES ENGINE INLETS ERROR ANALYSIS A circular cone surface shaping method for fan blade Study of the engine influence on wings with modern Automated optica_ instrument for extracting water droplet • p 50 A89-11032 h_gh+bypass propulsion concepts impingement data from wind tunnel experiments FANS I DGLR PAPER 87-063t p 5 A89-10510 p 47 A89-I0261 Fan flutter test p 37 N89-10014 De4cing of aircraft turbine engine inlets The pros and cons of code vahdation FATIGUE (MATERIALS) I DOT/FAA/CT-87/371 p 38 N89-10894 iNASA-TM-1006571 p 14 N89-10034 Forced vibration and flutter design methodology Study of three dimensional boundary layers on the front ERRORS p 51 N89-10016 of a fuselage and at an air intake Estimating e_ectnc field enhancement factors on an Wheel performance evaluation Phase 1: Analysis iCERT-OA-22/5025-AYDI p 53 N89-11184 aircraft utilizing a small scale model: A method I DOT/FAA/CT-88/161 p29 N89-10041 ENGINE MONITORING INSTRUMENTS evaluation p 21 N89-10454 FATIGUE LIFE Aircraft gas turbine engine monitoring systems An ESCAPE CAPSULES Fatigue life influence of residual stresses from cold update Advanced crew escape capsule technologies program working and high spectrum loads in aircraft structural I SAE SP-7281 p 33 A89-10613 p 18 A89-10475 design p 46 A89-10099
A-9 SUBJECT INDEX FATIGUE TESTS
Gas turbine engine monitoring systems - Helicopter FIRE FIGHTING Operating safety of automatic objects --- Russian book p 49 A89-10714 experience Fire safety at civil airports --- Russian book Fundamentals of flight safety --- Russian book iSAE 8717351 p 34 A89-10619 p 19 A89-10718 p 19 A89-10721 Guide to life usage monitoring and parts management FIRE PREVENTION Biting the bullet on aviation safety p 3 A89-12537 for aircraft gas turbine engines Fire behavior and risk analysis in spacecraft Air safety in the age of deregulation ISAE AIR 18721 p 35 A89-10625 I NASA-TM-1009441 p 42 N89-10111 p 19 A89-12539 Fatigue crack growth in aircraft main landing gear Aircraft accident report: Executive Air Charter, Inc, dba Seaplane takeoff performance - Using delta ratio as a wheels p 28 A89-11447 American Eagle, Flight 5452, CASA C-212, N432CA, method of correlation p 28 A89-12565 Tension fatigue analysis and life prediction for composite Mayaguez, Puerto Rico, May 8, 1987 Aeronautical decision making for air ambulance laminates IPB88-9104091 p 23 N89-10873 helicopter pilots: Situational awareness exercises I NASA-TM-1005491 p44 N89-10951 FLAME PROPAGATION IDOT/FAA/DS-88/61 p 23 N89-10869 FATIGUE TESTS A design method of 'wiggtestrap' film-cooling Aircraft accident reports, brief format, US civil and foreign Fatigue testing of full-scale all-composite aircraft construction of flame tube p 50 A89-11039 aviation, issue number 2 of 1987 accidents wings FLAME RETARDANTS IPB88-9169061 p 23 N89-10871 I SAE PAPER 8724591 p 48 A89-10671 Aircraft accident report: Executive Air Charter, Inc, dba FLIGHT SIMULATION A study of the fatigue behavior of small cracks in American Eagle, Flight 5452, CASA C-212, N432CA, Mayaguez, Puerto Rico, May 8, 1987 Correlation and analysis for SH-2F 101 rotor nickel-base superalloys p25 A89-10111 I AD-A1954891 p44 N89-10161 IPB88-9104091 p 23 N89-10873 Creep tests for slow and fast fatigue conditions on FLAPPING HINGES Multi-axis seat ejection (MASE) sled p 26 A89-10466 aluminum alloy specimens Validation of a pair of computer codes for estimation I REPT-M0-5352001 p 45 N89-11020 and optimization of subsonic aerodynamic performance An investigation of the pressure in an ejection seat bay due to rocket jet p 26 A89-10482 FAULT TOLERANCE of simple hinged-flap systems for thin swept wings Computer program for simulating dynamic gliding flight Control of the low-cycle service life of the primary INASA-TP-28281 p 13 N89-10024 I DGLR PAPER 87-135/21 p 27 A89-10527 components of aircraft turbine engines according to the FLAT PLATES Image quality and visual simulation of color matrix damage-tolerance concept p 37 A89-11075 Approximate calculations of viscous drag and FEEDBACK CONTROL aerodynamic heating p 10 A89-11157 displays ISAE PAPER 8717891 p 57 A89-10584 Inlet development for the NFAC 80- by 120-foot indraft FLEXIBLE BODIES Simulation and analysis of image-based navigation wind tunnel An experimental investigation on the bistable behaviors system lor rotorcraft low-altitude flight I AIAA PAPER 88-25281 p 41 A89-12550 of a flexible rotor-squeeze film damper system p 32 A89-12403 FERROMAGNETISM p 49 A89-11028 Sandia National Laboratories flight simulation facilities A comparabve evaluation of RPD (Rotary Particle FLIGHT CHARACTERISTICS IDE88-0121081 p 42 N89-10898 Depositor) and ferrographlc diagnostic methods for turbine Navigation of aircraft with rigid image-forming sensors Design and evaluation of a cockpit display for hovering engine lubricant samples I DGLR PAPER 87-1301 p 31 A89-10521 I AD-A1962071 p38 N89-10044 Aircraft dynamic stability - Developmental history flight I NASA-CR-1832471 p 42 N89-10900 FIBER OPTICS aspects FLIGHT SIMULATORS Packaged fiber optic gyros with high bias stability I DGLR PAPER 87-0571 p 1 A89-10538 Prototype data acquisition and analysis system for Navy p 46 A89-10121 FLIGHT CONDITIONS Fiber-ophc sensor systems for aerospace applications Aircraft accident reports, briel format, US civil and foreign operational flight simulators 1 DE88-014557 I p 42 N89-10901 p 47 A89-10359 awation, issue number 10 of 1987 accidents FLIGHT TESTS Fiber optic buses and networks for advanced avionics I PB88-9169051 p20 N89-10035 architectures p 33 N89-10836 Aircraft accident reports, brief format, US civil and foreign Flight-test determination of aircraft cruise characteristics FIGHTER AIRCRAFT aviation, issue number 12 of 1986 accidents using acceleration and deceleration techniques p 25 A89-10101 TEAS - An AI based threat response recommendation IPB88-9189031 p 20 N89-10038 Correlation and analysis for SH-2F 101 rotor FLIGHT CONTROL system p25 A89-10111 I SAE PAPER 8718041 p 57 A89-10589 Integrated redundant reference systems for flight control State of the art inertial navigation - Flight testing el the Evolution of the STOL and Maneuver Technology and navigation with skewed sensor arrangement Demonstrator p 30 A89-10129 Honeywell LINS Standard Navigator H-423 p 30 A89-10131 ISAE PAPER 8724171 p 27 A89-10639 Functional mock-up tests of the flight control system Development and testing of an inflight engine GENMAP - Computer code for mission adaptive profile of the NAL OSTOL research aqrcraft: Planning and performance monLtonng technique for the US Navy P-3C generation p 12 A89-12566 mechanical system test Wave drag and high-speed performance el supersonic I NAL-TR-944 I p 40 N89-10047 airplane ISAE 8414621 p 34 A89-10615 STOVL hghter configuration Ouadruplex digital flight control system assessment I NASA-TM-100061 I p 13 N89-10017 I NASA-CR-182741 I p 40 N89-10058 X-29A forward-swept-wing flight research program Computing system configuration for fighter aircraft flight Computing Systems Configuration for Highly Integrated status control systems p 40 N89-10832 Guidance and Control Systems JSAE PAPER 8724181 p 27 A89-10640 A highly reliable computer Io_ airborne applications IAGARD-LS-1581 p 3 N89-10831 Seaplane takeoff performance - Using delta ratio as a p 59 N89-10833 Computing system configuration for fighter aircraft flight method el correlation p 28 A89-12565 FILM COOLING control systems p 40 N89-10832 Design and evaluation of dynamic flight test A design method of 'wigglestrap' film-cooling The use of the complex summation method lot manoeuveres construction of flame tube p 50 A89-11039 lormulatlng algorithms for decoupling vertical/horizontal IPB88-210760l p 29 N89-10042 FINITE DIFFERENCE THEORY motions el rolling aircraft p 30 N89-10889 Non-linear aerodynamic characteristics obtained from The prediction of transonic interference flow by means FLIGHT CREWS the analysis of flight-data of a hybrid method p 10 A89-11487 Advanced crew escape capsule technologies program IAR-004-5711 p 18 N89-10866 Navier-Stokes solution to the flowfield over ice accretion p 18 A89-10475 Sandia National Laboratories flight simulation facilities Operational findings from a Traffic Alert and Collision shapes p 12 A89-12557 I DE88-012108t p42 N89-10898 Finite difference analysis of external and internal Avoidance System (TCAS) evaluation CAD wind tunnel test for half-cut model of Asuka ISAE PAPER 8809431 p 32 A89-12321 lightning response of the JAS39 CFC wing p 18 N89-11069 p 22 N89-10483 In-service evaluation of the Traffic Alert and Collision FLIGHT TRAINING Generation of a grid lor a finite difference calculahon Avoidance System (TCAS) industry prototype Introduction of the Hornet - A success story of flows around an a_rcraft in Cartesian coordinates IDOT/FAA/SA-88/21 p 25 N89-10885 I SAE PAPER 8724361 p 27 A89-10653 I NAL-TR-956L p 58 N89-10563 FLIGHT HAZARDS A computational study of coherent structures in the Aerospace technology - Windshear FAA: Boeing FLOORS wakes of two-dimensional bluff bodies Windshear Training Aid program Longitudinal impact test of a transport airframe section IAD-A196820i p 53 N89-11188 I SAE PAPER 872441 I p 19 A89-10655 I DOT/FAA/CT-87/261 p 54 N89-11265 FINITE ELEMENT METHOD Bird hazards in aviation - The RAF view FLOW CHARACTERISTICS Finite element method for calculating transonic potential p 20 A89-12718 Flow performance of reversed tandem cascades with flow around airfoil from pressure minimum integration Bird hazards m aviation - Safety and economic double-circular arc profile for compressor starer p 9 A89-11088 implications for an airline p 20 A89-12721 p 7 A89-11036 Finite element Euler computations in three dimensions Bird hazards in aviation - The regulatory authority's FLOW DEFLECTION p 11 A89-12130 responsibilities p 20 A89-12722 Incompressible Nawer-Stokes computations for a Aeroelasticity and structural optimization of helicopter Investigation of wake vortices of landing aircraft at round-edged double-delta wing p 12 A89-12552 rotor blades with swept tips p 29 N89-10887 Frankfurt airport (Federal Repubhc of Germany) FLOW DISTORTION Aircraft crashes on the runway Development of a super IDFVLR-MITT-88-151 p 17 N89-10862 Dynamic dLstortion in tlowfield downstream o! transonic element for nonlinear analysis o1 a beam FLIGHT INSTRUMENTS shock-boundary layer interaction , p 8 A89-11061 International Aerospace and Ground Conference on INEPT-87/561 p 54 N89-11286 Numerical simulation of compact schemes in FINITE VOLUME METHOD Lightning and Stahc Electricity super-sonic viscous flows p 9 A89-11085 I PB88 1974391 p 55 N89-10429 Multlgnd solution of the two-dimensional Eulor equations On nonlinear aspects of hypersonic boundary-layer on unstructured triangular meshes p 9 A89 11108 FLIGHT MECHANICS stability p 10 A89-11118 Diagonal implicd mulhgrid algorithm lor the Euler Fhghl mechanics and aerolhermodynamLc software FLOW DISTRIBUTION equations p 9 A89-11110 ICNES-CT/DTI/MS/MN/0691 p 4 N89-10839 A further improvement in the numerical method of Unsteady transonic airloil compulat_on using _mphctt FLIGHT OPTIMIZATION Euler scheme on body-fixed grid p 10 A89-11153 Tactical route planning --- for hehcopter evasive Supersonic infinitesimal horseshoe vortex distribution p 8 A89-11080 FINS maneuvering p 24 A89-12414 Expenmental research on swept shock wave/boundary FLIGHT SAFETY HISSS - A higher-order panel method lor subsonic and supersonic attached flow about arbitrary configurahons _ayer interactions Maintenance and airline safety p 10 A89-11484 lAD-A1969381 p 53 N89-11189 ISAE PAPER 872443J p 19 A89-10656
A-10 SUBJECT INDEX GROUNDCREWS
Application of an advanced panel method to FLUTTER ANALYSIS Gas turbine engine monitoring systems - Helicopter aerodynamic problems of aircraft desEJn A frequency domain MIMO modal identfficahon method experience p 28 A89-11486 with application in the aircraft ground vibration test I SAE 8717351 p 34 A89-10619 Calculation of unsteady lransonic flow about oscillating I SAE PAPER 8724581 p 48 A89-10670 Field experience w_th quantitative debris momlormg wings by a field panel method p 11 A89-11498 Efficient vibration mode analysis of aircraft with multiple I SAE 871736i p 34 A89-10620 external store configurations p 28 A89-12562 Calculations of the unsteady, three-dimensional flow Texmas - An expert system for gas turbine engine Vibration, performance, flutter and forced response field inside a motored Wankel engine diagnosis and more characteristics of a large-scale propfan and its aeroelastic I SAE PAPER 8806251 p 37 A89-12307 ISAE 871737i p 34 A89-10621 model Guide to oil system monltoMng m a_rcraft gas turbine Aerodynamically-driven condensate layer thickness j NASA-TM-1013221 p38 N89-10043 distributions on isothermal cylindrical surfaces engines New trial of vibration testing method p 51 A89-12337 ISAE AIR 18281 p 35 A89-10622 p 52 N89-11068 Lessons learned from developmental and operabonal Iniel development for the NFAC 80- by 120-foot indraft FLY BY WIRE CONTROL turbine engine monitoring systems wsnd tunnel Mission-Adaptive Wing tSAE AIR 1871BI p 35 A89-10624 I AIAA PAPER 88-25281 p 41 A89-12550 I SAE PAPER 8724191 p 27 A89-10641 Guide to life usage monitoring and parts management Generation of a grid for a finite difference calculation FOLIAGE for aircraft gas turbine engines of flows around an aircraft in Cartesian coordinates Results of 1987 MSS helicopter propagation experiment I SAE AIR 18721 p 35 A89-10625 I NAL-TR-9561 p 58 N89-10563 at UHF and L band in Central Maryland Guide to limited engine monLtoring systems for aircraft Ground vortex flow field investigation p 53 N89-11077 gas turbine engines p 16 N89-10852 FORCED CONVECTION I SAE AIR 18731 p 35 A89-10626 An assessment of ground effects determined by static Regressed relations for forced convection heal transfer Gas turbine engine development partnerships and dynamic testing techniques p 16 N89-10854 in a direct inlection stratified charge rotary engine ISAE PAPER 8724101 p 35 A89-10636 Experimental research on swept shock wave/boundary I SAE PAPER 880626g p 51 A89-12308 Application of end-bend blade for enhancing surge layer interactions FORCED VIBRATION margie p 36 A89-11051 I AD-A1969381 p53 N89-11189 AGARD manual on aeroelasficity in axial-flow Approach to blade end_bend mechanism FLOW EQUATIONS turbomachines. Volume 2: Structural dynamics and p 36 A89-11052 A numerical solution of transonic flow using aeroelasticity Control of the low-cycle service hfe of the primary discontinuous shock relation p 6 A89-10542 I AGARD-AGo298-VOL-21 p 13 N89-10006 components of aircraft turbine engines according to the FLOW GEOMETRY Aeroelastic coupling: An elementary approach damage-tolerance concept p 37 A89-11075 Flow performance of reversed tandem cascades with p 37 N89-10012 Measurements 01 heat transfer distribution over the double-orcular arc profile for compressor stator Forced vibration and flutter design methodology surfaces of highly loaded turbine nozzle guide vanes p 7 A89-11036 p 51 N89-10016 p 51 A89-12752 A design method of "wigglestrap' film*cooling Vibration, performance, flutter and forced response StatlsIics on aircraft gas turbine engine rotor failures construction of flame tube p 50 A89-11039 characteristics of a large-scale propfan and its aeroelastic that occurred m US commercial aviation during 1982 Transonic computations about complex configurations model I DOT/FAA/CT-88/231 p 38 N89-10892 using coupled inner and outer flow equations tNASA-TM-1013221 p 38 N89-10043 GAS TURBINES p 12 A89-12553 FOREBODIES Experimental investigabon of the performance of a FLOW MEASUREMENT Experimental study of effects of forebody geometry on supersonic compressor cascade Boundary-layer measurements on an airfoil at low high angle-of-attack stabihty p 38 A89-10103 INASA-TM-1008791 p 16 N89-10858 Reynolds numbers p 4 A89-10106 FORTRAN GEARS Flow past circular cyhnder of finite length placed on Programming techniques for high-speed processing on Bevel gear resonance failures in central gearing system ground plane p 48 A89-10543 the supercomputer FUJITSU VP-system of an aeroengine p 50 A89-11046 Expenmental study of rotating stall in single-stage axial tNAL-TR-9151 p 58 N89-10565 GENERAL AVIATION AIRCRAFT compressor p 8 A89-11059 FRACTURE MECHANICS Optimization of lhe COnCeptual design and mission Three component laser anemometer measurements in Fracture mechanics; Proceedings of the Nineteenlh profiles of short-haul a_rcraft p 25 A89-10107 an annular cascade of core turbine vanes with contoured National Symposium, San Antonio, TX, June 30-July 2. Apphcation of winglets with integrated, adjusted end wall 1986 p 50 A89-11426 tra_ling-edge flaps tn a general aviation aircraft INASA-TP-28461 p 15 N89-10844 FRACTURE STRENGTH ]DGLR PAPER 87-0801 p 26 A89-10516 FLOW STABILITY Fracture criteria for discontinuously reinforced metal Preeonditions for G PS installation - Recewers in Control of separated flow on a symmetric airfoil matrix composites ddferential operation for landing aircraft in general p 47 A89-10181 I NASA-CR-1811751 p44 N89-10125 aviation Boundary layer transition FREE FLOW I DGLR PAPER 87-1321 p 23 A89-10523 ICERT-OA-40/5018-AYDt p 53 N89-11187 The characteristics of the ground vortex and its effect Alternate fuels for General Aviation aircraft with spark FLOW VELOCITY on the aerodynamics of the STOL configuration tgnLbon engines The characteristics of the ground vortex and its effect p 15 N89-10850 I DOT/FAA/CT-88/05J p 44 N89-10179 on the aerodynamics of the STOL configuration FREQUENCIES Census of US ovil aircraft: Calendar year 1987 p 15 N89-10850 A filamentary method for caleulating induced voltages I AD-A1966261 p4 N89-11691 FLOW VISUALIZATION within resistive structures in eilber the frequency or time GLASS Laser sheet technique for visualizing a periodic rotor domain p 52 N89-10484 Passive thermal protection system p 26 A89-10478 wake p 41 A89-10115 FUEL CONSUMPTION GLIDE PATHS On the pamng process m an excited, plane, turbulent Aspects of increasing economy usieg future low-power fnveshgahon of wake vortices el landing aircraft at mixing layer p 47 A89-10173 aircraft propulsion systems Frankfurt airport (Federal Republic of Germany) The vapor-screen technique of flow visualization in the IDGLR PAPER 87-1001 p 33 A89-10528 I DFVLR-MITT-88-151 p 17 N89-10662 intermittent transonic and supersonic wind tunnel FUEL INJECTION GLIDERS p 9 A89-11083 Regressed relations for forced convection heat transfer fs 32 - A split-Fowler glider problem presentation and Ground vortex flow field investigation in a direct injection stratified charge rotary engine solubons p 16 N89-10852 ISAE PAPER 880626I p 51 A89-12308 I DGLR PAPER 87-0821 p 26 A89-10518 Flow around a delta wing with or without a canard (Phi Turbofan forced mixer lobe flow modeling Part 3: Computer program for simulabng dynamic ghding fhght BA 60 deg). Part 2: Hydrodynamic wsualizations m Apphcation 1o augment engines {DGLR PAPER 87-135/21 p 27 A89-10527 unsteady flow (pitching oscillations) INASA-CR-41471 p 14 N89-10025 Fahgue testing of full-scale all-composite aircraft IONERA-RT-11/2891-AN-PT-21 p 17 N89-10860 FUSELAGES wings Unsteady low-speed windtunnel test of a straked delta Control of autorotational characteristics of tight-airplane t SAE PAPER 8724591 p 48 A99-10671 GLIDING wing, Oscillating in pitch Part 1: General description and fuselages p 39 A89-12555 discussion of results indirect effects on electronic and mechanical systems Computer program for simulating dynamic gilding flight lAD-A1964561 p 18 N89-10867 installed in carbon fibre compound aircraft structures t DGLR PAPER 87-135/2] p 27 A89-10527 GLOBAL POSITIONING SYSTEM FLUID BOUNDARIES p 22 N89-10492 BEM for wave equation with boundary in arbitrary motion Preconditions for G,P,S. installation - Receivers in Longlludinal impact test of a transport airframe section differential operation for landing aircraft in general and apphcations to compressible poteniial aerodynamics l DOT/FAA/CT-67/261 p 54 N89o11265 of a_rplanes and helicopters p 5 A89-10192 aviation FLUID FLOW I DGLR PAPER 87-1321 p 23 A89-10523 Turbofan forced mixer lobe flow modehng Part 3: G Global posihonmg system (GPS) receiver initialization Application to augment engines methods for MIL-STD- 1760A I NASA-CR-4147 t p 14 N89-10025 I SAE PAPER 872501 I p 42 A89-10691 GAS COMPOSITION A comparative evaluation of RPD (Rotary Parhcle GOALS A jet thrust measurement method with gas composition Depositor) and ferrographic diagnoshc methods for turbine Review of aeronautical wind tunnel facilities analysis p 36 A89-11040 engine lubricant samples I NASA-CR-1930571 p 41 N89-10887 GAS TURBINE ENGINES lAD-A1962071 p 38 N89-10044 GOVERNMENT/INDUSTRY RELATIONS FLUTTER Aircraft gas turbine engine monitoring systems: An A Canadian government look at airworthiness AGARD manual on aeroetasticify in axial-flow update t SAE PAPER 8809351 p 2 A89-12319 I SAE SP-7281 p 33 A89-10613 turbomachmes Volume 2 Structural dynamics and GRID GENERATION (MATHEMATICS) aeroelasflolty Pocket calculator trend monitoring for gas turbine Multigrid solution of the two-dlmens_3nal Euler equahons I AGARD-AG-298-VOL-21 p 13 N89-10006 engines on unstructured triangular meshes p 9 A89-11108 Fan flutter test p 37 N89-10014 I SAE 841461 I p 34 A89-10614 GROUND CREWS Aeroelashc thermal effects p 37 N89-10015 AIR 1900 - Guide to temperature monitoring in aircraft Measurement of the electrostatic charging on large Forced vibration and flutter design methodology gas turbine engines hehcopters and control of the shock hazard p 51 N89-10016 I SAE 8717301 p34 A89-10616 p 22 N89-10461
A-11 GROUNDEFFECT(AERODYNAMICS) SUBJECT INDEX
GROUND EFFECT (AERODYNAMICS) Speech recognition in advanced rotorcraft - Using HOT ISOSTATIC PRESSING Flow past circular cylinder of finite length placed on speech controls to reduce manual control overload Influence of regeneration treatments on creep rupture ground plane p 48 A89-10543 p 24 A89-12404 lives of turbine blades p 43 A89-11214 An experimental study on aerodynamic performance of A tactics expert system for scout/attack rotorcraft HOT-WIRE ANEMOMETERS Lippisch-type GEW --- Ground Effect Wing p 58 A89-12405 The pros and cons of code validation INASA-TM-1006571 p 14 N89-10034 p 6 A89-10544 A study of helicopter stability and control including blade HOTOL LAUNCH VEHICLE The 1987 Ground Vortex Workshop dynam0cs Aerothermodynamics - The required tools INASA-CP-100081 p 15 N89-10849 INASA-CR-1832451 p 40 N89-10895 ISAE PAPER 8809281 p 12 A89-12316 The characteristics ot the ground vortex and gs effect HELICOPTER DESIGN on the aerodynamics of the STOL configuration HOUSINGS 'The Pointer', a new concept for RPV air vehicles p 15 N89-10850 T55-L-712 turbine engine compressor housing p 28 A89-12416 Ground vortex flow field investigation refurbishment-plasma spray project Helicopter roll control effectiveness criteria program p 16 N89-10852 INASA-TM-1013101 p 44 N89-10156 summary An assessment of ground effects determined by static HOVERING I NASA-CR-177477 I p 39 N89-10046 and dynamic testing techniques p 16 N89-10854 Measurement of the electrostatic charging on large Effects of a ground vortex on the aerodynamics of an Aeroelasticity and structural optimlzahon of helicopter helicopters and control of the shock hazard airfoil p 16 N89-10855 rotor blades with swept tips p 29 N89-10887 p 22 N89-10461 Numerical mvestigahon of a jet in ground effect using HELICOPTER ENGINES Design and evaluation of a cockpit display for hovering the fortified Navler-Stokes scheme p 16 N89-10857 Gas turbine engine monitoring systems - Helicopter flight GROUND EFFECT MACHINES expenence I NASA-CR-183247i p 42 N89-10900 Aerodynamic design considerahons for a free-flying ISAE 8717351 p 34 A89-10619 HUMAN FACTORS ENGINEERING ducted propeller New concepts in helicopter machinery prognostics The design eye reference point :-- for determining IDE88-0068671 p 15 N89-10841 p 2 A89-12408 geometric entitles defining cockpit layouts GROUND SUPPORT EQUIPMENT Implementahon of knowledge-based systems for ISAE PAPER 8717631 p 31 A89-10582 Up in the air on air traffic control p 3 A89-12538 helicopter machinery fault prognosis p 2 A89-12412 Image quality and visual simulation of color matnx GROUND SUPPORT SYSTEMS HELICOPTER PERFORMANCE displays I SAE PAPER 8717891 p 57 A89-10584 Up in the air on air traffic control p 3 A89-12538 Correlation and analysis for SH-2F 101 rotor GROUND TESTS p25 A89-10111 Evaluation of enhancements to the Low Level Wind A frequency domain MIMe modal identification method Shear Alert System (LLWAS) at Stapleton Internahonal Reasoning about device behavior using quahtatlve with apphcahon in Ihe aircraft ground vibration tesl Airport physics --- helicopter diagnostics p 58 A89-12410 I SAE PAPER 8724581 p 48 A89-10670 IDOT/FAA/PS-88/141 p 56 N89-11356 GUIDANCE SENSORS Apphcahon of constraint suspension techniques to HYDRAULIC FLUIDS diagnosis in helicopter caution/warning systems Integrated redundant reference systems for flight control The electrochemical erosion of serve valves by p32 A89-12411 and navigation with skewed sensor arrangement phosphate ester fire resistant hydraulic tluids p 30 A89 10129 Pi - An AI approach for maintenance and diagnostic p 48 A89-10573 GUIDE VANES applications p 58 A89-12413 HYDROGEN FUELS Measurements of heat transfer distribution over the Tachcal route planning --- for helicopter evasive Technology issues associated with fueling the national surfaces of highly loaded turbine nozzle guide vanes maneuvering p 24 A89-12414 aerospace plane with slush hydrogen p 51 A89-12752 Development of a rule-based demonstration prototype I NASA-TM-1013861 p 43 N89-10123 expert system for intlight emergencies for the UH 1 I{ HYPERSONIC BOUNDARY LAYER H helicopter p 32 A89-12415 On nonlinear aspects of hypersonic boundaryqayer HELICOPTER PROPELLER DRIVE stability p 10 A89-11116 New concepts in helicopter machinery prognostics HYPERSONIC FLOW H-53 HELICOPTER p 2 A89-12408 Engineering analysis of slender-body aerodynamics Measurement of the etectrostatic charging on large HELICOPTER WAKES using Sychev similarity parameters p 4 A89-10108 helicopters and control of the shock hazard Profile development results for advanced Unified computation method of unsteady p 22 N89-10461 circulation-guided rotor systems in fast helicopters supersonic/hypersonic flow past two dimensional flat plate HANG GLIDERS IDGLR PAPER 87-086[ p 5 A89-10513 and rectangular wings Measurement of aerodynamic characteristics of a Numencal soluhons of induced velocities by semi-infinite I SAE PAPER 8724471 p 7 A89-10660 hang-glider-wing by ground run tests using a test vehicle tip vortex lines p 12 A89-12554 A new PNS code lor chemical nonequlSbrium flows INAL-TR-9531 p 13 N89-10004 HELICOPTERS p 9 A89-11106 HARNESSES Development in helicopter tail boom strake apphcahons Analysis el complex hypersomc flows with strong Lightning tests to measure the bulk current levels in the US wscous/inviscid interaction p 9 A89-11109 associated with the electronic engine control of a turboprop INASA-TM-1014961 p 40 N89-10059 HYPERSONIC SPEED commuter transport p 2t N89-10457 Lightning tests on an all composite helicopter Unique research challenges lor high-speed civil HARRIER AIRCRAFT p 21 N89-10452 transports Noise of the Harrier in verhcal landing and takeoff Electrification of hovering helicopters ISAE PAPER 8724001 p 1 A89 10629 p 60 N89-10856 p 22 N89-10460 HAZARDS On the appropriateness of applying chi-square Measurement of the electrostatic charging on large distribution based confidence intervals to spectral helicopters and control of the shock hazard eshmates of helicopter flyover data p 22 N89 10461 ICE INASA-CR-1816921 p 59 N89 10601 Imphcattons of a recent hghtnmg strike to a NASA let Intracloud lightning as a precursor to thunderstorm Investigation on of the flow around a backward facing trainer p 22 N89-10478 m_crobursts p 56 N89-10490 step with spanwise blowing HEAT FLUX ICE FORMATION ICERT-RF-OA-68/2259-AYDI p 17 N89-10859 Sensors for ceramic components in advanced Automated ophcal instrument for extracting water droplet Aeronautical decision making lor air ambulance propulsion systems: Summary of literature survey and helicopter pilots Situational awareness exercises impingement data from wind tunnel experiments concept analysis, task 3 report I DOT/FAA/DS-88/61 p 23 N89-10869 p 47 A89-10261 INASA-CR-1809001 p 54 N89-11192 Navler-Stokes solution to the tlowfleld over _ce accretion Resulls of 1987 MSS helicopter propagahon experiment HEAT RESISTANT ALLOYS at UHF and L band in Central Maryland shapes p 12 A89-12557 A study of the fatigue behawor of small cracks in p53 N89-11077 IDEAL FLUIDS nickel-base superalloys HIGH REYNOLDS NUMBER A second-order numerical method for the analysis of lAD-At954891 p 44 N89-10161 Investlgahons on high Reynolds number laminar flow two-dimensional flow of ideal fluid through a cascade with Effect of protective coatings on life of heat-resistant airfoils p 4 A89-10102 supersonic input p 6 A89-10607 nickel steel under cyclic heat load p 45 N89-11005 Computational and experimental studies of LEBUs at Experience with the development of turboprop HEAT TRANSFER high device Reynolds numbers p 4 A89-10160 engines p 37 A89-11074 Heat transfer in the recirculating region formed by a HIGH SPEED IMAGE ANALYSIS backward-lacing step p 51 A89-12252 High speed parallel processing networks for advanced A hierarchical control strategy for 2-D obiect HEAT TRANSFER COEFFICIENTS architectures p 59 N89-10837 recognihon p 57 A89-11760 Calculation of compressible flow and heat transfer on HIGH TEMPERATURE GASES IMAGE PROCESSING Deposition of Na2SO4 from salt-seeded combustion a rotating disk p 50 A89-11033 The Symbohcs SCOPE system as a platform lor Regressed relations for forced convection heat transfer gases of a high velocity burner ng p 43 A89-12330 environmental analysis p 57 A89-11748 HIGH TEMPERATURE TESTS in a direct miechon strahfied charge rotary engine A hierarchical control strategy for 2-D obiect The dual element method Of strain gauge temperature I SAE PAPER 8806261 p 51 A89-12308 recognition p 57 A89-11760 compensation p 51 A89-12276 HELICOPTER CONTROL HISTORIES IMAGE RESOLUTION Development of a he(icopter slmulahon program The nonrigid airship of the Siemens-Schuckert Works Image quality and wsual simulation el color matnx IDGLR PAPER 87-1231 p 26 A89-10520 I DGLR PAPER 87-0551 p 60 A89-10537 displays Automation apphcahons for rotorcraft; Proceedings of From Kitty Hawk to the year 2000 I SAE PAPER 8717891 p 57 A89-10584 the National Specialists' Meeting. Atlanta, CA, Apr 4 8, ISAE PAPER 8723951 p 1 A89-10628 IMAGE TRANSDUCERS 1988 p 2 A89-12401 HOT CORROSION La Recherche Aerospahale, Bimonthly Bulletin. Number The NeE pilot's associate - A lob descnphon The high temperature oxidation behavior of the single 1987-4, 239/July-August p 39 A89-12402 crystal Hi-base alloy M002 rood. with and without protective IESA-TT-10881 p 14 N89 10026 Simulahon and analysis of image-based nawgallon coatings p 43 A89-11216 IMAGE VELOCITY SENSORS system for rotorcraft low-altitude flighl Deposgion of Na2SO4 from salt-seeded combustion Navigalion of aircratt wdh ng_d _mage-forming sensors p 32 A89 12403 gases of a high velocity burner rig p 43 A89-12330 I DGLR PAPER 87-130i p 31 A89-10521
A-12 SUBJECT INDEX LIGHTNING
IMIDES INTERNAL COMBUSTION ENGINES LAMINATES The effects of fluids in the aircraft environment on a Alternate fuels for General Awation arrcraft with spark Tension fabgue an3tysis and life pred_chon for composite polyetherimlde p 44 A89-12759 ignition engines laminates IMPACT DAMAGE IDOT/FAA/CT-88/051 p44 N89-10179 I NASA-TM- 1005491 p44 N89-10951 S_mulahon of a btrdstnke impact on aircraft canopy INTERVALS LANDING material p 25 A89-10113 On the appropriateness of applying chi-square Noise of the Harrier in vertical landing and takeoff Longitudinal impact test of a transport airframe section distribution based confidence intervals to spectral p 60 N89-10856 tDOT/FAA/CT-87/261 p54 N89-11265 estimates of hehcopter flyover data LANDING GEAR IMPACT LOADS tNASA-CR-1816921 p 59 N89-10601 Fabgue crack growth m a_rcraft main landing gear INVlSCID FLOW Composites in shock and vibration isolabon wheels p 28 A89-11447 Engineering analysis of slender-body aerodynamics p 50 A89-11251 F-15 SMTD low speed let effects wind tunnel test using Sychev slmdarity parameters p 4 A89-10108 IMPACT TESTS results p 16 N89-10853 The prediction of transonic _nterference flow by means S_mulation of a birdstrike impact on aircraft canopy LANDING INSTRUMENTS of a hybrid method p 10 A89-11487 material p 25 A89-10113 Preconditions for G P S installation - Rece*vers in ISOTHERMAL PROCESSES differential operation for landing a_rcraft in general IN-FLIGHT MONITORING Aerodynamically-driven condensate layer thickness aviation Health and usage monitoring - The integrated approach distributions on isothermal cylindrical surfaces I DGLR PAPER 87-1321 p 23 A89-10523 --- for propulsion and structural elements of fixed and rotary p 51 A89-12337 wing civil aircraft LANDING SIMULATION I SAE PAPER 8724451 p 32 A89-10658 Automated landing approach using machine see4ng INCIDENCE J I DGLR PAPER 87-131 ] p 23 A89-10522 Prediction of incidence effects on oscillating airfoil LASER ANEMOMETERS aerodynamics by a locally analyticat method J-97 ENGINE Three component laser anemometer measurements in p 12 A89-12135 Phase 4 static tests ot the J-97 powered, external an annular cascade of core turbine vanes with contoured Expenmental investigation of flow near a corner, part augmentor V/STOL modet at the NASA, Ames Research end wall 2 Center, November 1983 I NASA-TP-2846 I p 15 N89-10844 ICERT-RT-OA-24/5025-AYDI p 17 N89-10861 INASA-CR-1773951 p 14 N89-10028 LASER APPLICATIONS JET ENGINES INCOMPRESSIBLE FLOW Laser sheet technique for VlSUahzing a periodic rotor Active control of reheat buzz --- low-frequency A doublet point method for the calculation of unsteady wake p 41 A89-10115 combustion instability of let aeroenglne afterburners propeller aerodynamtcs p 11 A89-11497 State of the art inertial navigation - Flight testing of the p 43 A89-11103 Honeywell LINS Standard Navigator H-423 Prediction ot incidence effects on Oscillating airfoil JET EXHAUST aerodynamics by a locally analytical method p 30 A89-10131 Ground vortex flow field investigation p 12 A89-12135 Laser control of visibility and cloud-base height m a_rfleld p 16 N89-10852 Incompressible Navier-Stokes computations for a reg*ons p 50 A89-11860 Effects of a ground vortex on the aerodynamics of an LASER GUIDANCE round-edged double-delta wing p 12 A89-12552 airfoil p 16 N89-10855 Laser navigation equipment --- Russian book Continuum theories for fluid-particle flows: Some Numerical investigation of a let In ground effect using p 24 A89-10722 aspects of lift forces and turbulence p 53 N89-11155 the fortified Nawer-Stokes scheme p 16 N89-10857 LATERAL CONTROL INERTIAL NAVIGATION JET IMPINGEMENT Helicopter roll control effectiveness criteria program Cost-effective strapdown I NS design and the need for Noise of the Hamer m vertical Landing and takeoff summary standard flight profiles p 30 A89-10128 p 60 N89-10856 I NASA-CR-1774771 p 39 N89-10046 State of the art inertial navlgahon - Flight testing of the Experimental research on swept shock wave boundary LAUNCH VEHICLES Honeywell LINS Standard Navigator H-423 layer interachons An aircraft-borne etectnc field measuring system for p 30 A89-10131 lAD-A196938] p 53 N89-11189 rocket launch support p 55 N89-10443 Global positioning system (GPS) receiver initialization JET THRUST LEADING EDGES methods for MIL-STD-1760A A let thrust measurement method with gas composition Nur'r_rical simulahon of the vortical flow over a I SAE PAPER 872501 I p 42 A89-10691 analysis p 36 A89-11040 round-edged double-delta wing p 10 A89-11152 INERTIAL REFERENCE SYSTEMS JET VANES LEAR JET AIRCRAFT Integrated redundant reference systems for flight control Establishment of variable vane regulation law Interference of precipitation stahc discharges with and navigation with skewed sensor arrangement p 36 A89-11044 a_rcraft navigational systems p 21 N89-10459 LEAST SQUARES METHOD p 30 A89-10129 JOINTS (JUNCTIONS) INFLUENCE COEFFICIENT An inverse, subsomc two-dimensional panel melhod Adhesively bonded joints: Testing. analysis, and design: Convergence schemes for an adaptive-wall wind following the method of smallest quadrate for the design Proceedings of the International Symposium, Baltimore. tunnel p 41 A89-12560 and modlficahon of multiple element profiles MD, Sept 10-12, 1986 p 45 A89-10076 INFORMATION DISSEMINATION I DGLR PAPER 87-061 I p 5 A89-10509 Environmental durab_hfy of adhesively bonded joints Lightning information database p 55 N89-10432 LIFE (DURABILITY) p 46 A89-10095 INFORMATION MANAGEMENT Unique research challenges for high-speed Civil Lessons learned from an operational engine monitoring transports system and their correlation with future developments K i SAE PAPER 872400[ p 1 A89-10629 ISAE 8717331 p34 A89-10618 LIFT INLET FLOW Continuum theories for fluid-parhcle flows: Some KALMAN FILTERS Study of the engine influence on wings with modern aspects of hft forces and turbulence p 53 N89-11155 h_gh-bypass propulsion concepts Navigahon of aircraft with rigid _mage-formmg sensors LIFT AUGMENTATION ]DGLR PAPER 87-063t p 5 A89-10510 I DGLR PAPER 87-1301 p 31 A89-10521 Phase 4 stahc tests of the J 97 powered, externa_ Two-dtmensionaL subsonic diffuser flow with uniform KARMAN VORTEX STREET augmentor V/STOL model at the NASA, Ames Research shear velocity profile at inlet p 7 A89-11056 Propulsive vorbcal signature of p_unglng and p_tching Center, November 1983 Noise field of a propeller with angular inflow airfoils p 9 A89-11115 I NASA-CR-177395t p 14 N89-10028 p 59 A89-11102 KEVLAR (TRADEMARK) LIFTING BODIES Inlet development for 1he NFAC 80- by 120-foot indraft bghtning tests on an all-composite helicopter A further improvement in the numerical method of wind tunnel p 21 N89-10452 supersonic infinitesimal horseshoe vortex distribution I AIAA PAPER 88-25281 p 41 A89-12550 KITS p 8 A89-11080 INSERTION Qualification and operational aspects of light weight A doublet point method for the calculation of unsteady Hardware fault insertion and instrumentation system: SKAD (light weight survival kit air droppable) propeller aerodynamics p 11 A89-11497 Experimentation and results p 18 A89-10471 LIGHT AIRCRAFT I NASA-CR-1827461 p 58 N89-10526 Control of autorotational charactenstics of hght-airplane INTEGRATED CIRCUITS fuselages p 39 A89-12555 Aerospace avionics equipment and integration_ L LIGHTNING Proceedings of the Second Conference, Dallas, TX, Nov International Aerospace and Ground Conference on 2-4, 1987 LAMINAR BOUNDARY LAYER Lightning and Static Electricity I SAE P-2051 p 48 A89-10676 W_ng laminar boundary layer m the presence of a IP888-1974391 p 55 N89-10429 INTERACTIONAL AERODYNAMICS propeller shpstream p 4 A89-I0105 Statistics of hghtning interaction with a_rcraft in Japan p 55 N89-10430 Propfan design by propeller-nacelle interaction Boundary-layer control for drag reduction analysis p 36 A89-11055 Israel A_r Force (IAF) m-service aircraft lighmmg strike I SAE PAPER 8724341 p 6 A89-10651 Dynamic distortion in flowfield downstream of transomc and damage survey p 55 N89-10431 LAMINAR FLOW shock-boundary layer mteracbon p 8 A89-11061 L_ghtnmg mformat_on database p 55 N89-10432 Turbulence management and relammansatlon; AnaLysts of transonic wings including viscous Triggering of lightning by the Atlas Centaur vehicle Proceedings of the IUTAM Symposium, Bangalore, India, interaction p 9 A89-11084 p 55 N89-10438 Jan 19-23 1987 p 46 A89-10154 Acoustics of transonic blade-vortex interactions An aircraft-borne electric field measuring system for A new PNS code for chemical nonequilibrium flows p59 A89-11101 rocket launch support p 55 N89-10443 p 9 A89-11106 Analysis of complex hypersome flows wdh strong New electric field mstrumentahon and the effects of vlscous/mwscid interachon p 9 A89-11109 A transonic interactive boundary-layer theory for laminar space charge at Kennedy Space Center A vortex-lattice method for the calculation of wing-vortex and turbulent flow over swept wings p 55 N89-10444 _nteract_on m subsonic flow p 11 A89-11499 INASA-CR-41851 p 14 N89-10029 A case for a unified hghtning threat A transonic interactive boundary-layer theory for laminar LAMINAR FLOW AIRFOILS p 56 N89-10447 and turbulent flow over swept wings Investigahons on high Reynolds number laminar flow Summary of inflight data on hghtmng currents and INASA-CR-41851 p 14 N89-10029 aidoils p 4 A89-10102 fields p 56 N89 10449
A-13 LINEAR SYSTEMS SUBJECT INDEX
Analysis of recent in-flight hghtnlng measurements on M METAL MATRIX COMPOSITES different aircraft p 20 N89-10450 Fracture criteria for discontinuously reinforced metal Linear and nonlinear interpretabon of CV-880 hghtnlng MACH NUMBER matrix composites data p 21 N89-10451 Profile development results for advanced I NASA-CRq811751 p44 N89-10125 METAL SHEETS Lightning tests on an all-composite helicopter circulation-guided rotor systems in fast helicopters p 21 N89-10452 IDGLR PAPER 87-0861 p 8 A89-10513 A circular cone surface shaping method for fan blade A chronology of in-cloud electric field and lightning Experimental aerodynamic performance of advanced 40 p 80 A89-11032 strikes on an instrumented research aircraft deg-swept 10-blade propeller model at Mach 06 to 085 METAL-METAL BONDING p 21 N89-10455 INASA-TM-889691 p 17 N89-10865 Stress analysis concepts for adhesive bonding of aircraft pnmary structure p 45 A89-10093 MAGNETIC CIRCUITS Lightning inltlahon on a_rcraft in thunderstorms METEOROLOGICAL PARAMETERS p 21 N89-10456 F_eld expenence with quantitative debris monitoring The Symbolics SCOPE system as a platform for Lightning tests to measure the bulk current tevels ISAE 8717361 p 34 A89-10620 environmental analysis p 57 A89-11748 associated with the electronic engine control of a turboprop Guide to oil system monitoring in aircraft gas turbine METEOROLOGY commuter transport p 21 N89-10457 engines An aircraft-borne electric field measuring system for ISAEAIR 18281 p35 A89-10622 The electrical structure of thunderstorm anvils rocket launch support p 55 N89-10443 p 56 N89-10470 MAINTAINABILITY METHODOLOGY Lightning and surge protection o1 large ground Introduction of the Hornet - A success story Tension fatigue analysis and life prediction for composite faclhtles p 52 N89-10474 I SAE PAPER 8724361 p 27 A89-10653 laminates Imphcahons of a recent hghtnrng strike to a NASA jet Tornado - The first eight years p 2 A89-11450 INASA-TM-1005491 p 44 N89-10951 trainer p 22 N89-10478 MAINTENANCE MICROBURSTS (METEOROLOGY) The SAFIR lightning monitoring and warning system, Review of aeronautical wind tunnel facilities Structure and life cycle of microburst outflows observed apphcatlons 1o aerospace activities p 52 N89-10481 I NASA-CR-1830571 p 41 N89-10897 in Colorado p 54 A89-11221 Evaluation of enhancements to the Low Level Wind Finite difference analysis of external and internal MAN MACHINE SYSTEMS Shear Alert System (LLWAS) at Stapleton International hghtn_ng response of the JAS39 CFC wing Should technology assist or replace the pilot? p 22 N89-10483 I SAE PAPER 8807741 p 57 A89-10593 Airport I DOT/FAA/PS-88/141 p 56 N89-11356 A filamentary method for calculating induced voltages MAN POWERED AIRCRAFT MICROELECTRONICS within reslshve structures _n either the frequency or time Low-Reynolds-number airfoil design for the M IT Advanced avionics architecture pave pillar domain p 52 N89 10484 Daedalus prototype - A case study p 12 A89-12559 p 33 N89-10834 Fhght test results for the Daedalus and Ltgbt Eagle Modelling of common mode coupling between an aircraft MIG AIRCRAFT human powered aircraft wing traversed by a lightning current and wiring instafled MiG-29 design merges old, new technologies I NASA-CR-1833051 p 30 N89-10890 in that wing p 22 N89-10485 p28 A89-11559 MAN-COMPUTER INTERFACE Intracloud hghtnmg as a precursor to thunderstorm MILITARY AIRCRAFT mlcrobursts p 56 N89-10490 Current military/government applications for speech Advanced crew escape capsule technologies program Indirect effects on electronic and mechanical systems recognition p 18 A89-10475 installed in carbon fibre compound aircraft structures I SAE PAPER 8717501 p 23 A89-10580 MILITARY AVIATION AFTI / F- 16 voice *nteractive avionics evaluation p 22 N89 10492 Interoperability of military and civil air-cargo systems System protection from atmospheric electricity for I SAE PAPER 871751 I p 24 A89-10581 ISAE PAPER 8215551 p 19 A89-10654 aerostats with conducting tethers p 52 N89-10497 MARKET RESEARCH MILITARY HELICOPTERS LINEAR SYSTEMS The winning edge --- NASA role in US aeronautics Helicopter roll control effechveness criteria program HISSS - A higher order panel method for subsonic and industry's compehhon with foreign suppliers summary supersonic attached flow about arbitrary conhgufahons I SAE PAPER 8809451 p 2 A89-12322 I NASA-CR-1774771 p39 N89-10046 p 10 A89-11484 MARKETING Destgn and evaluation of a cockpit display for hovering LINEARIZATION Unique research challenges for high-speed civil flight I NASA-CR-183247 I p 42 N89-10900 Modal observabihty and controllability measures for first transports MILITARY OPERATIONS and second order linear systems and model reduchon ISAE PAPER 8724001 p 1 A89-10629 TEAS - An AI based threat response recommendahon p 57 A89-11680 MATERIALS TESTS LIQUID CRYSTALS Windscreen design and teshng p 29 A89-12720 system I SAE PAPER 8718041 p 57 A89-10589 Avionic color liquid crystal displays - Recent trends MATHEMATICAL MODELS MILITARY TECHNOLOGY ISAE PAPER 8717901 p 31 A89-10585 Comparison of Iongdudlnally stabilized behawor in Current mihtary/government applications for speech LOAD DISTRIBUTION (FORCES) vertical turbulence between a modern canard configuration and a conventional aircraft recognition Fatigue hfe influence of residual stresses from cold I SAE PAPER 8717501 p 23 A89-10580 I DGLR PAPER 87-0781 p39 A89-10515 working and high spectrum loads in aircraft structural MiG-29 destgn merges old. new technologies A case for a undied hghtnlng threat design p 46 A89-10099 p 28 A89-11559 p 56 N89-10447 LOADS (FORCES) MISSILE CONTROL Measurement of aerodynamic charactenstlcs ol a Linear and nonlinear interpretation of CV 580 lightning Global positioning system (GPS) receiver inltlahzahon data p 21 N89-10451 hang-ghder-wing by ground run tests usmg a test vehicle methods for MIL-STD-1760A INAL-TR-9531 p 13 N89-10004 Modelling of common mode coupling between an aircraft I SAE PAPER 872501 I p 42 A89-10691 LOW ASPECT RATIO WINGS wing traversed by a lightning current and wiring installed Compubng Systems Configuration for Highly Integrated Research on the computational method of aerodynamic in that wing p 22 N89-10485 Guidance and Control Systems characterlshcs of wing with vortex breakdown at high angle An approximate, maximum terminal velocity descent to IAGARD-LS 1581 p 3 N89-10831 o1 attack p 9 A89-11088 a point MISSION ADAPTIVE WINGS LOW COST IDE88-0003491 p 15 N89-10840 Mission-Adaptive Wing H©TOL Command and Control Systems Aeroelasticity and structural optimization of helicopter I SAE PAPER 8724191 p 27 A89-10641 I SAE PAPER 8809291 p 42 A89-12317 rotor blades with swept tips p 29 N89-10887 GENMAP - Computer code for mission adaptive profile LOW REYNOLDS NUMBER MAXIMUM LIKELIHOOD ESTIMATES gene_'ahon p 12 A89-12566 MIXING Boundary-layer measurements on an airfoil at low Some statistical aspects of attntlon studies Reynolds numbers p 4 A89 10106 tAD-At966651 p 30 N89-10891 Turbofan forced mixer lobe flow modeling Part 3 Thick airfoil at low Reynolds number and high MECHANICAL PROPERTIES Application to augmenl engines incidence p 4 A89-10118 Fracture crilerla for discontinuously reinforced metal INASA-CR-41471 p 14 N89-10025 MIXING LAYERS (FLUIDS) Low-Reynolds-number airfoil design for the MIT matrix composites On the pairing process m an excited, plane, turbulent Daedalus prototype - A case study p 12 A89-12559 I NASA-CR-1811751 p44 N89-10125 Expenmental research on swept shock wave/boundary mixing layer p 47 A89-10173 Experimental results for the Eppler 387 airfoil at low layer interactions MOBILE COMMUNICATION SYSTEMS Reynolds numbers m the Langley low-turbulence pressure Results of 1987 MSS helicopter propagation experiment tunnel lAD-A1969381 p 53 N89-11189 MESH at UHF and L band in Central Maryland INASA-TM-40621 p 15 N89-10842 Indirect effects on electronic and mechanical systems p 53 N89-11077 LOW SPEED installed m carbon fibre compound aircraft structures ETS-V propagallon experiments in Japan Unsteady low-speed windtunnel test of a straked delta p 22 N89-10492 p 53 N89-11080 wing, oscillating in pitch Part 1 General descnphon and MESSAGE PROCESSING MODAL RESPONSE discussion of results Token rotation timer implementation Modal observablhty and controllabtlity measures for first lAD-A1964561 p 18 N89-10867 I SAE PAPER 8724971 p 49 A89-10688 and second order hnear systems and model reducbon LOW SPEED WIND TUNNELS METAL COATINGS ' p57 A89-11680 on Investigation wa_l interference of low-speed wind The high temperature ox*dation behawor of the single Efficient wbrahon mode analysis of a_rcraft with reMit*pie tunnel with slotted walls p 8 A89 11081 crystal Ni-base alloy M002 mod with and without protechve external store configurahons p 28 A89-12562 LUBRICANTS coatings p 43 A89 11216 MODELS A comparative evaLuabon of RPD (Rotary Parhcle METAL FATIGUE Phase 4 static tests of the J 97 powered, external Depositor) and ferrograph_c dlagnoshc methods for turbine Fatigue crack growth m aircraft main landing gear augmenter V/STOL model at the NASA, Ames Research engine lubricant samples wheels p 28 A89-11447 Center, November 1983 lAD-A1962071 p 38 N89-10044 A study of the fatigue behavior of small cracks in INASA-CR-177395t p 14 N89-10028 LUBRICATING OILS nickel-base superalloys Vibration. performance flutter and forced response Guide 1o 0ii system monitoring In aircraft gas turbine lAD-A1954891 p 44 N89-10161 characterlshcs of a large-scale propfan and its aeroelastic engines Effect of protective coatings on hfe of heat-resLstant model ISAEAIR 18281 p35 A89-10622 nickel steel under cyclic heat load p 45 N89-11005 INASA-TM-1013221 p 38 N89-10043
A-14 SUBJECTINDEX PATTERN RECOGNITION
MOLDING MATERIALS A study of the fatigue behavior of small cracks _n OPTICAL GYROSCOPES Packaged fiber optic gyros with high bias stability Direcbonal spectral emissivity measurements on a nickel-base superalloys ceramic mold material j AD-A195489 j p44 N89-10161 p 46 A89-I0!21 I DE88-0154071 p 44 N89-f0167 NIMONIC ALLOYS OPTIMAL CONTROL MOMENTUM TRANSFER InfLuence of regenerabon treatments on creep rupture GENMAP - Computer code for mission adaptive profile Conhnuum theories for fluid-particle flows: Some byes of turbine blades p 43 A89-11214 generation p 12 A89 12566 aspects of lift forces and turbulence p 53 N89-11155 NOISE GENERATORS OPTIMIZATION Response of discretely sbffened structures and MONITORS Multilevel decomposition approach to the prehmmary transmission of structure-borne no_se sizing of a transport aircraft wrng p 25 A89-10109 Health and usage monitoring - The integrated approach p 54 N89-11270 --- for propulsion and structural elements of fixed and rotary Configuration optimization of commercial a_rcraft NOISE MEASUREMENT wing c_vil aircraft I DGLR PAPER 87-081 I p 26 A89-10517 Noise of the Harder m vertical landLng and takeoff i SAE PAPER 8724451 p 32 A89-10658 Vahdabon of a pair of computer codes for estimation p 60 N89-10856 The SAFIR hghtmng monitoring and warning system, and optimization of subsonic aerodynamic performance NOISE PREDICTION (AIRCRAFT) applications to aerospace activities p 52 N89-10481 of simple hinged-flap systems for thin swept w_ngs Unsteady loading noise of counter-rotating propeller I NASA-TP-28281 p 13 N89-10024 MOTION SIMULATORS p 36 A89-11054 Sandia National Laboratories flight simulation facilities Aeroelasflcity and structural optimlzahon of hehcopfer Acoustics of transonic blade-vortex interactions rotor blades with swept tips p 29 N89-10887 I DE88-012108 J p42 H89-10898 p59 A89-11101 Prototype data acquisition and analysis system for Navy Prediction of aircraft-propeller-induced, structure-borne ORBITAL VELOCITY operational fhght simulators interior noise p 28 A89-12564 Technology issues associated with fuehng the national I DE88-014557l p 42 N89-10901 NOISE PROPAGATION aerospace p_ane with slush hydrogen MOVING TARGET INDICATORS Prediction of aircraft-propeller-induced, structure-borne I NASA-TM-1013861 p43 N89-10123 The operation of modern air-space surveillance radars interior noise p 28 A89-f2564 OSCILLATING FLOW p 51 A89-12151 NOISE REDUCTION Numerical s_mulation of supersonic flow over a MRCA AIRCRAFT Reduction of elector noise with multihole nozzle three-dimensional cavity p 9 A89-11105 Tornado - The first eight years p 2 A89-11450 p 36 A89-11034 OSCILLATION DAMPERS MULTIPATH TRANSMISSION Structure-borne noise control for propeller aircraft An experimental _nveshgat_on on the b_stable behawors Results of 1987 MSS helicopter propagation expenment p 59 A89-12563 Of a flexible rotor-squeeze film damper system at UHF and L band in Central Maryland Electrical noise reduction techniques contributing to p 49 A89-11028 p 53 N89-11077 improved data quality at the National Transomc Facility The bistable behavior of a rigid rotor with squeeze film iNASA-CR-41931 p 54 N89-11196 damper p 49 A89-11029 N Response Of discretely stiffened structures and OVERVOLTAGE transmission of structure-borne noise bghtnmg and surge protecbon of large ground NACELLES p 54 N89-11270 faciflhes p 52 N89-10474 NONDESTRUCTIVE TESTS Prop fan design by propeller-nacelle interaction analysis p 36 A89-11055 Wheel performance evaluation Phase 1: Analysis j DOT/FAA/CT-88/161 p29 N89-10041 Method to optimize nacelle shape in a supersonic cruise P aircraft p 28 A89-12558 NONEQUILIBRIUM FLOW A new PNS code for chemical nonequlhbrium flows Lightning tests to measure the bulk current levels PACIFIC OCEAN p9 A89-11106 associated with the electronic engine COntrol of a turboprop VISTOL aircraft configurations and opportunities _n the NONLINEAR EQUATIONS commuter transport p 21 N89-10457 Pacific Basin On nonlinear aspects of hypersonic boundary-layer NAP-OF-THE-EARTH NAVIGATION I SAE PAPER 8724031 p 18 A89-10631 stabildy p 10 A89-11116 The HOE pilot's associate - A job description PANEL METHOD (FLUID DYNAMICS) NONLINEAR SYSTEMS p 39 A89-12402 An _nverse, subsonic two-dimensional panel method Non-hnear aerodynamic characteristLcs obtained from NASA PROGRAMS following the method of smallest quadrate for the design the analysis of fhght-data The winning edge --- NASA role in US aeronautics and modification of mult=pte element profiles IAR-004-571 J p 18 N89-10866 industry's competition with foreign suppliers I DGLR PAPER 87-061 I p 5 A89-10509 NONSTABILIZED OSCILLATION I SAE PAPER 880945j p 2 A89-12322 A numerical simulation of separated flow around NAVfER-STOKES EQUATION Suppression of unstable oscillabons in a boundary layer p 5 A89-10171 two-dimensional wing by a discrete vortex method A new PNS code for chemical nonequilibrium flows p 6 A89-10568 p9 A89-11106 NOSES (FOREBODIES) Numerical experiments for separation flows around Analysis of complex hypersonic flows with strong Study of three dimenslona_ boundary layers on the front trapezoidal cyhnders by a d_screte vortex method wscous/inviscid interaction p 9 A89-11109 of a fuselage and at an air retake p 6 A89-10569 Incompressible Navier-Stokes computations for a I CERT-OA-22/5025-AYD I p53 N89-11184 NOZZLE DESIGN Panel methods in aerodynamics - Some h_ghlights round-edged double-delta wing p 12 A89-12552 Navier-Stokes solution to the flowlieLd over ice accretion Reduction of elector noise with multlhole nozzle p 10 A89-11481 p 36 A89-11034 HISSS - A h_gher-order panel method for subsonic and shapes p 12 A89-12557 NOZZLES supersomc attached flow about arbitrary configurations Navier-Stokes simulation of transonic w_ng flow fields p 10 A89-11484 using a zonal grid approach Experimental investigation of convergent elector Apphcation of an advanced panel method to INASA-TM-t000391 p 13 N89-10022 nozzle/aflerbody in wind funnel p 8 A89-11060 NUCLEAR EXPLOSIONS aerodynamic problems of a_rcraft design La Recherche Aerospatlale, B_monthly Bullebn, Number p 28 A89-11486 1987-4,239/July-August Passive therma_ protection system p 26 A89 10478 NUMERICAL FLOW VISUALIZATION The predichon of transonic interference flow by means I ESA-TT-10881 p 14 N89-10026 A numerical simulation of separated flow around of a hybrid method p 10 A89-11487 Numerical investigation of a jet in ground effect using two-dimensional wing by a discrete vortex method A subsonic panel method for design of 3-dimensional the fortified Navier-Stokes scheme p 16 N89-10857 p 6 A89-10568 complex configurations with specified pressure Cascade flow analysis by Navier-Stokes equation p 52 N89-11065 Numerical experiments for separation flows around distribution p 28 A89-11491 NAVIGATION AIDS trapezoidal cylinders by a discrete vortex method On the eva_uation of aerodynamic influence coefficients p 11 A89-t1496 Packaged hber optic gyros with hLgh bias stability p 6 A89-10569 p 46 A89-10121 Numerical simulation of supersonic flow over a Calculabon of unsteady transonic flow about Oscillating wings by a field panel method p 11 A89-f 1498 Cosf-effecbve strapdown INS design and the need for three-dimensional cavity p 9 A89-11105 Approximation of free and bounded vortex sheets at standard flight profiles p 30 A89-10128 NUMERICAL WEATHER FORECASTING delta-wings p 11 A89-11500 The history of aircraft onboard equipment Structure and hie cycle of microburst outflows observed PANELS I DGLR PAPER 87-0541 p 31 A89-10536 m Colorado p 54 A89-11221 Effect of adhesive debond on stress-intensity factors Laser navigation equipment --- Russian book p 24 A89-10722 in bonded composite panels p 45 A89-1009f PARALLEL PROCESSING (COMPUTERS) The operation of modern air-space surveillance radars O A h_erarch_cal control strategy for 2-D obiect p 51 A89-12151 recognition p 57 A89-11760 NAVIGATION INSTRUMENTS OBSERVABfLITY (SYSTEMS) High speed parallel processing networks for advanced State of the art inertial navigation - Flight testmg of the Modal observability and controllability measures for first architectures p 59 N89-10837 Honeywell LINS Standard Nawgator H-423 and second order linear systems and model reduction PARAMETERIZATION p 30 A89-10131 p 57 A89-11680 Response of discretely stiffened structures and Navigation of aircraft with ng_d image-forming sensors OILS transmission Of structure-borne nolse I DGLR PAPER 87-1301 p 31 A89-10521 Field experience with quanhtabve debns monitoring p 54 N89-11270 Air navigation systems I - Astronomical navigahon in I SAE 8717361 p 34 A89-10620 PARTICLE DIFFUSION the air 1919-1969 p 24 A89-12449 ONBOARD DATA PROCESSING NAVIGATION SATELLITES The high temperature oxidahon behawor of the single S_ngle-chip solution of MIL-STD-1553A and crystal N_-base alloy M002 rood with and without proteclJve The Australian Awabon Satelhte System MIL-STDq 5538 data communlcahons coatmgs p 43 A89-11216 I SAE PAPER 8724201 p 24 A89-10642 I SAE PAPER 8724881 p 48 A89- f 0683 PASSENGER AIRCRAFT NICKEL OPTICAL EQUIPMENT Air safety in the age of deregulation Effect of protective coatings on life of heat-resistant p 19 A89-12539 nickel steel under cychc heat load p 45 N89-11005 Laser navigation equipment **- Russian book PATTERN RECOGNITION NICKEL ALLOYS p 24 A89-10722 RuLe-based string code processor p 57 A89-11750 The high temperature oxidation behavior of the single OPTICAL FIBERS A hierarchical control strategy for 2-D obiect crystal Hi-base alloy M002 rood with and without protective Applications of time and wavelength dwlslon multiplexing recognition p 57 A89-11760 coatings p 43 A89-11216 to digital optical code plates p 31 A89-10364 A-15 PAYLOAD DELIVERY(STS) SUBJECT INDEX
PAYLOAD DELIVERY (STS) Fatigue teshng of full-scale all-composite aircraft PROPELLER DRIVE HOTOL Command and Control Systems wings Structure-borne noise control for propeller aircraft [SAE PAPER 8809291 p 42 A89 12317 I SAE PAPER 8724591 p 48 A89-10671 p 59 A89-12563 PERFORMANCE PREDICTION POLYETHER RESINS PROPELLER FANS On high-speed data bus performance analysis The effects of fluids in the aircraft environment on a Cruise noise of the 2/9 scale mode_ SR-7A propeller ISAE PAPER 8724961 p 49 A89-10687 polyetherimlde p 44 A89 12759 p 59 A89-12561 Seaplane takeoff performance - Using delta ratio as a POROUS WALLS PROPELLER SLIPSTREAMS method el correlation p 28 A89-12565 Investigation on wall interference of low-speed wind Wing laminar boundary layer in the presence of a AGARD manual on aeroeiasticlty in axial-flow tunnel with slotted walls p 8 A89-11081 propeller slipstream p 4 A89-10105 turbomachines Volume 2: Structural dynamics and POSITION SENSING Prediction o1 aircraft-propeller-induced, structure-borne aeroelastlclty Applications of time and wavelength division multiplexing interior no_se p 28 A89-12564 IAGARD-AG-298-VOL-21 p 13 N89-10006 to digital optical code plates p 31 A89-10364 PROPELLERS Computing system conhgurahon for fighter aircraft flight POTENTIAL FLOW Application of an advanced panel method to control systems p 40 N89 10832 8EM for wave equation with boundary in arbitrary motion aerodynamic problems of aircraft design PERFORMANCE TESTS and applications to compressible potential aerodynamics p 28 A89-11486 Flight-test determination o1 aircraft cruise characteristics of airplanes and helicopters p 5 A89-10192 A doublet point method for the calculation of unsteady using acceleration and deceleration techniques A numerical solution of transonic flow using propeller aerodynamics p 11 A89-11497 p 25 A89-10101 discontinuous shock relation p 6 A89-10542 The effect of front-to-rear propeller spacing on the Fan flutter test p 37 N89-10014 Application of an artificial density scheme of potential interaction noise at cruise conditions of a model Vibration. performance, flutter and forced response stream function method to design of airfoil counterrotation propeller having a reduced diameter aft characteristics of a large-scale propfan and its aeroetastic p7 A89-11053 propeller model Finite element method for calculating transonic potential I NASA-TM-1013291 p 60 N89-10603 I NASA-TM-1013221 p 38 N89-10043 flow around airfoil from pressure minimum integration Experimental aerodynamic performance of advanced 40 A comparahve evaluation of RPD (Rotary Particle p9 A89-11088 deg-swept 10-blade propeller model at Mach 0.6 to 085 Depositor) and ferrographic diagnostic methods for turbine Steady and unsteady potential flows around INASA-TM-889691 p 17 N89-10865 engine lubricant samples axlsymmetnc bodies and ring airfoils p 11 A89-11489 PROPULSION SYSTEM CONFIGURATIONS JAD-A196207 I p 38 N89-10044 On the evaluation of aerodynamic influence Study of the engine influence on wings with modern Functional mock-up tests o1 the flight control system coefficients p 11 A89-11496 high-bypass propulsion concepts of the HAL OSTOL research aircraft: Planmng and Unsteady three-dimensional stall on a rectangular I DGLR PAPER 87-0631 p 5 A89-10510 mechanical system test wing p 14 N89-10027 Aspects of increasing economy using future low-power I NAL-TR-944 I p 40 N89-10047 POTENTIAL THEORY aircraft propulsion systems The performance o1 alternate fuels in general aviation A potential theory for the steady separated flow about I DGLR PAPER 87-1001 p 33 A89-10528 arrcraft an aerofoil section PROPULSION SYSTEM PERFORMANCE IDOT/FAA/CT-88/131 p44 N89-10175 IARL*AERO-R-1761 p 13 N89-10005 Health and usage monitoring - The integrated approach Lightning tests on an all-composite hehcopter POWER CONDITIONING --- for propulsion and structural elements of fixed and rotary p 21 N89-10452 Circuit protection for advanced aircraft - A functional wing civil aircraft ETS-V propagation experiments in Japan and historical perspective I SAE PAPER 8724451 p 32 A89-10658 p 53 N89-11080 ISAE PAPER 8725021 p 32 A89-10692 PROPULSIVE EFFICIENCY Longltudina_ impact test of a transport airframe section POWER LINES Propulsive vortical signature of plunging and pitching I DOT/FAA/CT-87/261 p 54 N89-11265 Lightning and surge prc_tection of large ground airfoils p 9 A89-11 115 PERTURBATION THEORY facilities p 52 N89-10474 PROTECTION An approximate, maximum terminal velocity descent to PREDICTION ANALYSIS TECHNIQUES System protection from atmospheric electricity for a point A computational study of coherent structures in the aerostats with conducting tethers p 52 N89-10497 IDE88-0003491 p 15 N89-10840 wakes of two-dimensional bluff bodies PROTECTIVE COATINGS PHOTOGRAPHIC EQUIPMENT tAD*A1968201 p 83 N89-11188 Effect of protective coatings on life of heat-reststant The vapor-screen technique of flow visuahzatlon in the PREDICTIONS nickel steel under cyclic heat load p 45 N89-11005 intermittent transonic and supersonic wind tunnel A filamentary method for calculahng induced voltages PROTOCOL (COMPUTERS) p9 A89-11083 within resistive structures in either the frequency or time Single chip solution of MIL-STD 1553A and PIEZOELECTRICITY domain p 52 N89-10484 MIL-STD 1553B data communications Transition recognition in aircrafl wing profiles with the Tension fahgue analys_s and life predichon for composite I SAE PAPER 8724881 p 48 A89 10683 aid of piezoelectric sheetings laminates A candidate for hnear token-passing, high-speed data I DGLR PAPER 87-0651 p 47 A89-10512 INASA-TM-1005491 p 44 N89-10951 bus systems PILOT PERFORMANCE PRESSURE DISTRIBUTION I SAE PAPER 872494 I p 49 A89-10686 TEAS - An AI based threat response recommendation An investigation of the pressure m an election seat bay Token rotation timer implementation system due to rocket jet p 26 A89-10482 I SAE PAPER 872497 I p 49 A89-10688 ISAE PAPER 8718041 p 57 A89 10589 Measurements of unsteady pressure distribution on a PROTOTYPES The HOE pdots associate A iob descnphon NACA 0012 profile in transonic flow p 8 A89-11082 Prototype data acquisition and analysis system for Navy p 39 A89 12402 A subsonic panel method for design of 3-dimensional operational flight simulators PILOT TRAINING complex configurations with specified pressure I DE88-0145571 p 42 N89-10901 Aerospace technology - Wlndshear FAA: Boeing distribution p 28 A89-11491 PROVING Windshear Training Aid program Calculation of unsteady transonic flow about oscdlahng Quadruplex digital flight control system assessment ISAE PAPER 8724411 p 19 A89-10655 wings by a field panel method p 11 A89-11498 I NASA-CR-182741 I p 40 N89-10058 PILOTLESS AIRCRAFT Unsteady low-speed windtunnel test of a straked delta Digital autopllots Ior rotary winged unmanned aerial wing, oscillating in pitch Part 1 General description and vehicles p 39 A89-12417 discussloe of results Q PILOTS (PERSONNEL) tAD-At964561 p 18 N89-10867 Current mihtary/governmenf applications for speech PRESSURE EFFECTS QUALITY recognition Measurement of aerodynamic characteristics of a Electbcal noise reduction techniques contributing to I SAE PAPER 8717501 p 23 A89-10580 hang-glider-wing by ground run tests using a test vehicle improved data quality at the National Transonic Facihty The design eye reference point --- for determining INAL-TR-9531 p 13 N89-10004 I NASA-CR-41931 p54 N89-11196 geometnc entthes defining cockpit layouts The performance of alternate fuels in general aviation ISAE PAPER 8717631 p 31 A89 10582 aircraft Should technology assist or replace the pilot _ IDOT/FAA/CT-88/131 p44 N89-10175 R I SAE PAPER 8807741 p 57 A89-10593 PRESSURE GRADIENTS PIPE FLOW Turbulent boundary layer manipulation and modelling RADAR DATA A design method of 'wigglestrap' film-cooling in zero and adverse pressure gradients Digital recording of radar data m an aircraft construchon of flame tube p 50 A89-11039 p 46 A89-10159 IPB88-2095071 p 51 N89-10212 PITCHING MOMENTS PRESSURE MEASUREMENT RADAR DETECTION Analytical and experimental research on aerodynamlcal Experimental study of rotating stall in single-stage axial Intracloud lightning as a precursor to thunderstorm effects of wind shear on aircraft p 6 A89-10547 compressor p 8 A89-11059 Propulswe vortical signature of plunging and pdchng PROJECT MANAGEMENT microbursts p 56 N89-10490 RADAR EQUIPMENT airloils p9 A89-11115 Helicopter roll control effecbveness criteria program Measurement of aerodynamic characteristics of a summary The operation of modern air-space surveillance radars p 51 A89-1215t hang-glider-wing by ground run tests using a test vehicle INASA-CR-1774771 p 39 N89-10046 INAL-TR-9531 p 13 N89-t0004 PROP-FAN TECHNOLOGY RADIO FREQUENCY INTERFERENCE Flow around a delta wing with or w_thout a canard (Ph_ Results of acoushc tests of a prop-fao model Electrification of hovering helicopters BA 60 deg) Part 2: Hydrodynamic visualizations in p59 A89-10112 p 22 N89 10460 unsteady flow (p_tchmg oscillations) Propfan design by propeller-nacelle Interaction RADIO RECEIVERS IONERA-RT-11/2891-AN-PT-21 p 17 N89-10860 analysis p 36 A89-11055 Preconditions for G PS mstallahon Receivers in PITTING PROPELLER BLADES differential operation for landing alrcralt in general The electrochemical erosion of serve valves by Noise field of a propeller with angular inflow aviation phosphate ester fire-resistant hydraulic fluids p 59 A89-11102 I DGLR PAPER 87-1321 p 23 A89-10523 p 48 A89-10573 Vibration, performance, flutter and forced response RAFTS PLASTIC AIRCRAFT STRUCTURES characteristics of a large-scale propfan and its aeroelastic Qualdicatlon and operahonal aspects of light weight model Mission*Adaptive Wing SKAD (light weight survival kit air droppable) ISAE PAPER 8724191 p27 A89-10641 I NASA-TM-101322i p 38 N89-10043 p 18 A89-10471
A-16 SUBJECT INDEX SERVICE LIFE
RANDOM LOADS RESONANCE ROTOR BLADES (TURBOMACHINERY) Response of discretely stiffened structures and Bevel gear resonance failures ]n central geanng system AGARD manual on aeroelashcity in axial-flow transmission of structure-borne noise of an aerneng_ne p 50 A89-11046 turbomachmes Volume 2: Structural dynamics and p 54 N89-11270 RESONANT VIBRATION aeroetastioty l AGARD-AG-298-VOL-21 p 13 N89-10006 RATES (PER TIME) An experimental investigation on the b_stable behaviors Intracloud lightning as a precursor tO thunderstorm of a flexible rotor-squeeze film damper system Aeroelastic coupling An elementary approach microbursts p 56 N89-10490 p 49 A89-1 t028 p 37 N89-10012 RESPONSE TIME (COMPUTERS) An assessment of ground effects determined by static Aeroelasbc formulation for tuned and mlstuned rotors On high-speed data bus performance analysis and dynamic teshng techniques p 16 N89-I0854 p 37 N89*10013 I SAE PAPER 8724961 p 49 A89-10687 REAL TIME OPERATION Unsteady three*dimensional stall on a rectangular REYNOLDS NUMBER Automated landing approach using machine seeing" w_ng p 14 N89-10027 Regressed relations for forced convection heat transfer I DGLR PAPER 87-131 I p 23 A89-10522 ROTOR BODY INTERACTIONS in a direct injection stratified charge rotary engine Laser sheet technique for visualizing a periodic rotor REATTACHED FLOW tSAE PAPER 8806261 p 51 A89-12308 wake p 41 A89-10115 HISSS - A higher-order panel method for subsonic and RIBLETS supersonic attached flow about arbitrary configurations The wal_-pressure fluctuations of modified turbulent Investigation on of the flow around a backward lacing step with spanw_se blowing p 10 A89-11484 boundary layer with riblets p 47 A89-10163 }CERT-RF-OA-68/2259-AYDI p 17 N89-10859 Experimental results for the Eppler 387 airfoil at low RIGID ROTORS Reynolds numbers in the Langley low-turbulence pressure The bistable behavior of a rigid rotor with squeeze fitm ROTOR SPEED tunnel damper p 49 A89-11029 An experimental investigation on the b_stable behaviors I NASA-TM-40621 p 15 N89-10842 RING WINGS oI a flexible rotor-squeeze film damper system RECEIVERS Steady and unsteady petent_al flows around p 49 A89-11028 Global positioning system (GPS) receiver initialization axisymmetnc bodies and nng airfoils p 11 A89-11489 ROTORCRAFT AIRCRAFT methods for MIL-STD-1760A RISK Automation applications for rotorcraft: Proceedings of I SAE PAPER 872501 I p 42 A89-10691 Fire behavior and risk analysis m spacecraft the National Speciahsts' Meeting, Atlanta, CA, Apr 4-6, RECIRCULATIVE FLUID FLOW I NASA-TM-100944 I p 42 N89-10111 1988 p 2 A89-12401 Heat transfer in the recirculatlng region formed by a ROCKET LAUNCHING S_mulation and analys_s of _mage-based nawgation backward-facing step p 51 A89-12252 An aircraft-borne electnc fietd measuring system for system for rotorcraft low-altitude flight p Investigation on of the flow around a backward facing rocket launch support 55 N89-10443 p 32 A89-12403 ROCKETS step with spanwise blowing Speech recognihon in advanced rotorcraft - Using ICERT-RF-OA-68/2259-AYDi p 17 N89-10859 An investigation of the pressure in an ejection seat bay speech controls to reduce manual control overload RECLAMATION due to rocket jet p 26 A89-10482 p 24 A89-12404 ROLLING T55-L-712 turbine engine compressor housing A tactics expert system for scout/attack rotorcraft refurbishment-plasma spray prolect The use of the complex summation method for p 58 A89-12405 I NASA-TM-t013101 p44 N89-10156 formulating algonthms for decouphng vertical/honzontal ROTORS RECORDING motions Of rolling aircraft p 30 N89-10889 Steady-state unbalance responses for a multispan ROTARY ENGINES D_glta_ recording of radar data in an aircraft rotor p 50 A89-11066 IP888-2095071 p 51 N89-10212 Regressed relations for forced convection heat transfer RECTANGULAR WINGS m a direct iniection stratified charge rotary engine S Unified computation method of unsteady I SAE PAPER 8606261 p 51 A89-12308 supersonic/hypersonic flow past two dimensional flat plate A comparative evaluation of RPD (Rotary Part_cle SAFETY FACTORS and rectangular wings Depositor) and ferrographJc diagnostic methods for turbine I SAE PAPER 8724471 p 7 A89-10660 engine lubricant samples Operating safety of automatic obiects --- Russian book Unsteady three-dimensional stall on a rectangular lAD-A196207] p 38 N89-10044 p 49 A89-10714 ROTARY STABILITY European a_rworth=ness control for the 1990s wing p 14 N89-10027 REDUCED ORDER FILTERS An expenmental investigation on the bistable behaviors I SAE PAPER 8809361 p 2 A89-12320 Modal observabtlity and controllability measures for first of a flexible rotor-squeeze film damper system The assurance of flight safety - A priority task in civil and second order linear systems and model reduction p 49 A89-11028 aviation p 20 A89-12548 p 57 A89-11680 The bistable behavior of a rigid rotor with squeeze film SAFETY MANAGEMENT REFLECTANCE damper p 49 A89-11029 Maintenance and airline safety Automated optical instrument for extracting water droplet ROTARY WING AIRCRAFT ISAE PAPER 8724431 p 19 A89-10656 impingement data from wind tunnel experiments Helicopter roll control effectiveness criteria program Fire behawor and risk analysis in spacecraft p 47 A89-10261 summary 1NASA-TM-1009441 p 42 N89-10111 REGENERATION (ENGINEERING) I NASA-CR- 1774771 p 39 N89-10046 SATELLITE COMMUNICATION on Influence of regeneration treatments on creep rupture ROTARY WINGS Research satellite-to-aircraft signal communication lives of turbine blades p 43 A89-11214 Profile development results for advanced tDGLR PAPER 87-1331 p 23 A89-10524 REGIONS circulahon-gutded rotor systems m fast helicopters SCALE MODELS V/STOL aircraft configurations and opportunities in the I DGLR PAPER 57-0861 p 5 A89-10513 Cruise noise of the 2/9 scale model SR-TA propeller Pacific Basin Development of a helicopter simulation program p 59 A89-12561 ISAE PAPER 8724031 p 18 A89-10631 I DGLR PAPER 87-123I p 26 A89-10520 Eshmat_ng electnc field enhancement factors on an REGRESSION ANALYSIS Acoustics of transonic blade-vortex interactions aircraft utihzmg a small scale model: A method Regressed relations for forced convection heat transfer p 59 A89-11101 evaluation p 21 N89-10454 in a direct injection stratified charge rotary engine D*gltal autopllots for rotary winged unmanned aerial ,SCHEDULING I SAE PAPER 8806261 p 51 A89-12308 vehicles p 39 A89-12417 Biting the bullet on aviation safety p 3 A89-12537 RELIABILITY ROTATING DISKS SEAPLANES A htghty rehable computer for airborne apphcatlons Calculation of compressible flow and heat transfer on Seaplane takeoff performance - Using delta ratio as a p 59 N89-10833 a rotating disk p 50 A89-11033 method of correlation p 28 A89-12565 RELIABILITY ANALYSIS ROTATING STALLS SENSORS On the d_agnostic emulation technique and its use m Experimental study of rotating stall m single-stage axial Fiber-optic sensor systems for aerospace applications the AIRLAB compressor p 8 A89-11059 p 47 A89-10359 SEPARATED FLOW t NASA-TM-40271 p 58 N89-10524 ROTOR AERODYNAMICS REMOTE SENSING Correlation and analysis for SH-2F 101 rotor Control of separated flow on a symmetric airfoil p 47 A89-10181 Sensors for ceramic components in advanced p25 A89-10111 propulsion systems: Summary of literature survey and Results of acoustic tests of a prop-fan model A numerical s*mulation of separated flow around concept analysis, task 3 report p 59 A89-10112 two-dimensional wing by a discrete vortex method p 6 A89-10568 I NASA-CR- 1809001 p 54 N89-11192 Laser sheet technique for visualizing a perlndic rotor REMOTELY PILOTED VEHICLES wake p 41 A59-10115 Numerical experiments for separation flows around Modern techniques for the control of RPV's Thbck atrfod at low Reynolds number and high trapezoidal cylinders by a discrete vortex method p 6 A89-10569 I SAE PAPER 872457 I p 39 A89-10669 incidence p 4 A89-10116 A potential theory for the steady separated flow about "The Pointer', a new concept for RPV a_r vehicles BEM for wave equation with boundary in arbitrary motton an aerofoil section p 28 A89-12416 and applications to compressible potential aerodynamics IARL-AEBO-R-1761 p 13 N89-10005 REPORTS of airplanes and helicopters p 5 A59-10192 Expenmental research on swept shock wave/boundary Aircraft accident/inodent summary report. Copperhlll. A doublet point method for the calculation of unsteady layer interactions Tennessee, February 22, 1986 propeller aerodynamics p 11 A89-11497 lAD-A1969381 p 53 N89-11189 ] PB88-910407t p 22 N89-t0868 Numerical soluhons of induced velocities by semi-infinite RESEARCH MANAGEMENT SEQUENCING hp vortex hnes p 12 A89-12554 Hardware fault insertion and instrumentation system: ×-29A forward-swept-wing flight research program status A study of hehcopter stability and control including blade Experimentation and results dynamics I NASA-CR-1827461 p 58 N89-10526 [SAE PAPER 8724181 p 27 A89-10640 RESIDUAL STRESS I NASA-CR-183245t p 40 N89-10895 SERVICE LIFE ROTOR BLADES The V-22 vibrat_on, structural life, and engine diagnostic Swedish Symposium on Restdua_ Stresses. Sunne, Sweden, Mar 30-Apr 2, 1987, Proceedings E_ectrification of hovenng hehcopters system, VSLED p 22 N89-10460 ISAE 8717321 p 31 A89-10617 p 46 A89-10096 Guide to hfe usage monitoring and parts management Fatigue hfe influence of residual stresses from cold Statistics on a_rcraft gas turbine engine rotor fadures working and high spectrum loads in aircraft structural that occurred in US commercial aviation during 1982 for aircraft gas turbine engines ISAE AIR 18721 p 35 A89-10625 design p 46 A89-10099 I DOT/FAA/CT-88/231 p 38 N59-10892
A-17 SERVOMECHANISMS SUBJECT INDEX
Guide to limited engine monitoring systems for aircraft Lightning tests on an all-composite helicopter SPARK IGNITION gas turbine engines p 21 N89-10452 Alternate fuels for General Aviation aircraft with spark ISAEAIR 18731 p35 A89-10626 Numerical investigation of a jet in ground effect using ignition engines Controt of the low-cycle service life of the primary the fortified Navier-Stokes scheme p 16 N89-10857 I DOT/FAA/CT-88/051 p44 N89-10179 components of aircraft turbine engines according to the SIMULATORS SPECIMEN GEOMETRY damage-tolerance concept p 37 A89-11075 A comparative evaluation of RPD (Rotary Particle Creep tests for slow and fast fatigue conditions on Reasoning about device behavior using qualitatwe Depositor) and ferrographic diagnostic methods for turbine aluminum alloy specimens physics --- helicopter diagnostics p 58 A89-12410 engine lubncant samples I REPT-M0-5352001 p 45 N89-11020 SERVOMECHANISMS lAD-A1962071 p 38 N89-10044 SPECTRAL EMISSION The electrochemical erosion of serve valves by SINGLE CRYSTALS Directional spectral emissivdy measurements on a phosphate ester fire-resistant hydrauhc fluids The high temperature oxidation behavior of the single ceramic mold material p 48 A89-10573 crystal Hi-base alloy M002 mud with and without protective I DE88-0154071 p 44 N89-10167 SHEAR LAYERS coatings p 43 A89-11216 SPECTRUM ANALYSIS Boundary-layer measurements on an airfoil at low SKIN (STRUCTURAL MEMBER) Interference of precipitation static discharges with Reynolds numbers p 4 A89-10106 Lightning tests on an all-composite helicopter aircraft navigational systems p 21 N89-10459 On the palnng process in an excited, plane, turbulent p 21 N89-10452 On the appropriateness of applying chi-square mixing layer p 47 A89-10173 SKIN FRICTION distribution based confidence intervals to spectral SHEAR STRESS Experimental research on swept shock wave/boundary estimates of helicopter flyover data Effect of adhesive debond on stress-intensity factors layer interactions I NASA-CR-1816921 p 59 N89-10601 in bonded composite panels p 45 A89-10091 I AD-A 196938 t p 53 N89-11189 SPEECH RECOGNITION SHIELDING SLEDS Current military/government applications for speech Lightning tests to measure the bulk current levels Mulh-axis seat ejection (MASE) sled recognition associated with the electronic engine control of a turboprop p 26 A89-10466 ISAE PAPER 8717501 p 23 A89-10580 commuter transport p 21 N89-10457 Schlieren measurements at the 10,000-foot sled track AFTI/F-16 voice interactive avionics evaluation Electrification of hovering helicopters IDE88-012748i p 42 N89-10899 ISAE PAPER 871751 I p 24 A89-10581 p 22 N89-10460 SLENDER BODIES Speech recognition in advanced rotorcraft - Using Indirect effects on electronic and mechanical systems Engineering analysis of slender-body aerodynamics speech controls to reduce manual control overload installed m carbon fibre compound aircraft structures using Sychev similarity parameters p 4 A89-10108 p 24 A89-12404 p 22 N89-10492 The formation mechanism of the asymmetric spatial SQUEEZE FILMS System protection from atmospheric electricity for vortex of slender bodies at high angle of attack An experimental investigation on the bistable behaviors aerostats with conducting tethers p 52 N89-10497 I SAE PAPER 8724351 p 7 A89-10652 of a flexible rotor-squeeze film damper system SHOCK DISCONTINUITY SLENDER WINGS p 49 A89-11028 A numerical solution of transonic flow using Aspects of the control and stabilization of supersonic The bistable behavior of a rigid rotor with squeeze film discontinuous shock relation p 6 A89-10542 commercial aircraft damper p 49 A89-11029 SHOCK TUNNELS I DGLR PAPER 87-1221 p 39 A89-10519 STABILITY Shock tunnel studies of scramjet phenomena SLIPSTREAMS A study of helicopter stability and control including blade I NASA-CR-181721 I p 38 N89-10045 Weak-wave analysis of shock interaction with a dynamics SHOCK WAVE INTERACTION slipstream t NASA-CR-1832451 p 40 N89-10895 Dynamic distortion in flowfield downstream of transonic INASA-TP-28481 p 13 N89-10020 STATIC DISCHARGERS shock-boundary layer interaction p 8 A89-11061 SMALL PERTURBATION FLOW Interference of precipitation static discharges with Weak-wave analysis of shock interaction with a Efficient algorithm for solution of the unsteady transonic aircraft navigational systems p 21 N89-10459 slipstream small-disturbance equation p 4 A89-10104 STATIC ELECTRICITY tNASA-TP-28481 p 13 N89-10020 SODIUM SULFATES International Aerospace and Ground Conference on Experimental research on swept shock wave/boundary Deposition of Na2SO4 from salt-seeded combustion Lightning and Static Electricity layer interactions gases of a high velocity burner ng p 43 A89-12330 I PB88-1974391 p55 N89-10429 lAD-A1969381 p 53 N89-11189 SOUND FIELDS Electrostatic discharge and field effects of electronics SHOCK WAVES Noise field of a propeller with angular inflow systems p 52 N89-10493 Schlieren measurements at the 10,000-foot sled track p 59 A89-11t02 STATIC TESTS IDE88-0127481 p 42 N89-10899 SOUND-SOUND INTERACTIONS Phase 4 static tests of the J-97 powered, exlernal SHORT HAUL AIRCRAFT The effect of front-to-rear propeller spacing on the augmenter V/STOL model at the NASA, Ames Research Optimization of the conceptual design and mission interaction noise at cruise conditions of a model Center, November 1983 profiles of short-haul a_rcraft p 25 A89-10t07 counterrotabon propeller having a reduced diameter aft SHORT TAKEOFF AIRCRAFT tNASA-CR-1773951 p 14 N89-10028 propeller STATISTICAL ANALYSIS V/STOL aircraft configurations and opportunities in the I NASA-TM-101329i p 60 N89-10603 Statistics of lightning interaction with aircraft in Japan Pacific Basin SOUNDING p 55 N89-10430 I SAE PAPER 8724031 p 18 A89-10631 The electncal structure of thunderstorm anwls Statistics on aircraft gas turbine engine rotor lailures Evolution of the STOL and Maneuver Technology p 56 N89-10470 that occurred in US commercial aviation during 1982 Demonstrator SPACE CHARGE I DOT/FAA/CT-88/231 p 38 N89-10892 I SAE PAPER 8724171 p 27 A89-10639 New electric field instrumentation and the effects of STATOR BLADES The 1987 Ground Vortex Workshop space charge at Kennedy Space Center Three component laser anemometer measurements in INASA-CP 100081 p 15 N89-10849 p 55 N89-10444 The characteristics of the ground vortex and its effect SPACE COMMERCIALIZATION an annular cascade of core turbine vanes with contoured end wall on the aerodynamics of the STOL configuration Aerothermodynamics - The required tools INASA-TP-28461 p 15 N89-10844 p 15 N89-10850 ISAE PAPER 8809281 p 12 A89-12316 Ground vortex flow held inveshgahon SPACE MISSIONS STATORS p 16 N89-10852 From Kitty Hawk to the year 2000 Flow performance of reversed tandem cascades with F-t5 SMTD low speed let effects wind tunnel test ISAE PAPER 8723951 p 1 A89-10628 double-circular arc profile for compressor stator results p 16 N89-10853 SPACE TRANSPORTATION p 7 A89-11036 Numerical simulation of transonic flow around Asuka Aerothermodynamics - The required tools STEADY FLOW p 18 N89-11067 ISAE PAPER 880928} p 12 A89-12316 Numerical simulation of steady transonic flow past an CAD wind tunnel test for half-cut model of Asuka SPACECRAFT 8-percent DCA cascade at a freestream Mach number p 18 N89-11069 Operating safety of automatic objects --- Russian book of about 1 p 8 A89-t 1073 SHROUDED PROPELLERS p 49 A89-10714 Unsteady transonic airfoil computabon using implicd Aerodynamic design considerations for a free-flying SPACECRAFT CHARGING Euler scheme on body-fixed grid p 10 A89-11153 ducted propeller Triggering of lightning by the Atlas Centaur vehicle Integral equation solution for transonic and subsonic IDE88-0068671 p 15 N89-10841 p 55 N89-10438 aerodynamics p 11 A89-11488 SIDE-LOOKING RADAR SPACECRAFT DESIGN Steady and unsteady potential flows around Digital recording of radar data in an aircraft International Pacific Air and Space Technology axisymmetric bodies and ring airfoils p t 1 A89-11489 I PB88-2095071 p 51 N89-10212 Conference, Melbourne, Australia, Nov 13-17, 1987, Prediction of incidence effects on oscillating airfoil SIGNAL FADING Proceedings aerodynamics by a locally analytical method ISAE P-2081 p 1 A89-10627 Results of 1987 MSS helicopter propagation experiment p 12 A89-12135 at UHF and L band in Central Maryland From Kitty Hawk to the year 2000 A potential theory for the steady separated flow about ISAE PAPER 8723951 p 1 A89-10628 p 53 N89-t 1077 an aerofoil section SIGNAL PROCESSING Aerodynamic design and performance of a bent-axis geometry vehicle IARL-AERO-R-1761 ' p 13 N89-10005 Data and signal processing architectures for future I AIAA PAPER 87-24911 p42 A89-11119 STEELS avionics p 33 N89-t0835 SPACECRAFT INSTRUMENTS Effect of protective coatings on life of heat-resistant SIMILARITY THEOREM nickel steel under cyclic heat load p 45 N89-11005 Fiber*optic sensor systems for aerospace applications Engineering analysis of slender-body aerodynamics p 47 A89-10359 STIFFNESS using Sychev simllanty parameters p 4 A89-10108 SPACECRAFT SURVIVABILITY Composites in shock and vibration isolation SIMULATION Fire behavior and risk analysis in spacecraft pS0 A89 11251 Navier-Stokes simulation of transonic wing flow fields I NASA-TMo1009441 p 42 N89-1011 t STORMS (METEOROLOGY) using a zonal grid approach SPANWISE BLOWING OMahoma-Kansas preliminary regional experiment for INASA-TM-100039J p 13 N89-10022 Investigation on of the flow around a backward facing storm-central (O-K pre-storm) Volume 3: Aircraft mission Linear and nonhnear interpretabon of CV-580 Iightmng step with spanwise blowing summary data p 21 N89-10451 I CERT-RF-OA-68/2259-AYD t p 17 N89-10859 I PB88-2054891 p 56 N89-10499
A-18 SUBJECT INDEX TECHNOLOGY ASSESSMENT
STRAIN GAGES Validat[on of a pair of computer codes for estimation SURVIVAL EQUIPMENT The dual element method of strain gauge temperature and optimizabon of subsonic aerodynamic pertormance Qualification and operational aspects of light weight compensation p 51 A89-12276 of simple hinged-flap systems for thin swept wings SKAD (light weight survival kit air droppable) STRAIN MEASUREMENT I NASA-TP-2826] p 13 N89-10024 p 18 A89-10471 The dual element method of strain gauge temperature SUPERCOMPUTERS SWEPT FORWARD WINGS compensation p 51 A89-12276 Programming techniques for high-speed processing on X-29A forward-swept-wing flight research program Sensors for ceramic components in advanced the supercornputer FUJITSU VP-system status propulsion systems: Summary of literature survey and I NAL-TR-9151 p58 N89-10565 I SAE PAPER 872418I p 27 A89+10640 SUPERCRITICAL AIRFOILS concept analysis, task 3 report SWEPT WINGS [NASA-CR-1809001 p 54 N89-11192 Muttigrid solution of the two-dimensional Euler equations Validation of a pair of computer codes for eshmation STRAKES on unstructured triangular meshes p 9 A89-11108 and optimlzahon of subsonic aerodynamic performance Transonic characteristics of a humped airfoil Control of eutorotational characteristics of light-airplane of simple hinged-flap systems for thin swept wigs p 12 A89-12551 fuselages p 39 A89-12555 1NASA-TP-28281 p 13 N89-10024 SUPERCRITICAL FLOW Development m helicopter tail boom strake applications A transonic interactive boundary-layer theory for laminar Transonic characteristics of a humped airtoH in the US and turbulent flow over swept wigs p 12 A89-12551 INASA-CR-4185] p 14 N89-10029 j NASA-TM-t014961 p 40 N89-10059 SUPERSONIC AIRCRAFT SWEPTBACK WINGS Unsteady tow-speed windtunnel test of a straked delta Aspects of the control and stabilization o! supersonic wig, oscillating in pitch. Part 1; General description and commercial aircraft Transibon recognition in aircraft wing profiles with the discussion of results aqd of piezoelectric sheetings IDGLR PAPER 87-122l p 39 A89-10519 lAD-A196456] p 18 N89-10867 Method to opbmize naceUe shape in a supersonic cruise IDGLR PAPER 87-0651 p 47 A89-10512 STRAPIX)WN INERTIAL GUIDANCE aircraft p 28 A89-12558 SYMBOLIC PROGRAMMING The Symbelics SCOPE system as a platform for Pacl_aged fiber optic gyros with high bias stability Wave drag and high-speed performance of supersonic p 46 A89-t0121 STOVL fighter configuration environmental analysis p 57 A89-11748 STRATIFIED FLOW I NASA-TM-lO0061 [ p 13 N89-10017 SYMMETRY Regressed relations for forced convection heat transfer SUPERSONIC COMBUSTION RAMJET ENGINES Symmetnc (and generic) algorithms for height balanced in a direct injection stratified charge rotary engine Shock tunnel studies of scramjet phenomena trees tSAE PAPER 8806261 p 51 A89-12308 INASA_;R-181721 I p 38 N89-10045 ICS-8711 _ p 59 N89-12332 STREAM FUNCTIONS (FLUIDS) SUPERSONIC FLOW SYNTHETIC FUELS Application of an artificial density scheme of potential A second-order numerical method for the analysis of Alternate fuels for General Aviation aircraft with spark stream function method to design of airfoil two-dimensional flow of ideal fluid through a cascade with ignibon engmes p 7 A89-11053 supersonic input p 6 A89-10607 IDOT/FAAIC-f-88/05i p 44 N89-10179 STRESS ANALYSIS Computational fluid dynamics =n aerospace SYSTEM FAILURES I SAE PAPER 8724461 p 7 A89-10659 Stress analysis concepts for adhesive bonding Of aircraft Electrostabc discharge and held effects of electronics Unified computation method of unsteady primary structure p 45 A89-10093 systems p 52 N89-10493 supersonic/hypersonic flow past two dimensional flat plate STRESS CYCLES SYSTEMS ANALYSIS and rectangular wings Environmental durability of adheswely bonded jomts Fundamentals of flight safety --- Russian book I SAE PAPER 8724471 p 7 A89-10660 p 46 A89-10095 p 19 A89-10721 A further improvement In the numerical method Of STRESS DISTRIBUTION Quadruptex digital flight control system assessment supersonic infinitesimal horseshoe vortex distribution Swedish Symposium on Residual Stresses, Sunne, I NASA-CR-182741 I p 40 N89-10058 p 8 A89-11080 Sweden, Mar. 30-Apr 2. 1987, Proceedings SYSTEMS ENGINEERING Numerical simulation of compact schemes in p 46 A89-10096 Cost-effectrve strapdown INS des_ln and the need for super-sonic wscous flows p 9 A89-11085 standard flight profiles p 30 A89-10128 STRESS INTENSITY FACTORS Numerical simulation of supersonic flow over a Aerospace avionics equipment and integration: Effect of adhesive debond on stresa-mtensity factors three-dimensional cawty p 9 A89-11105 in bonded composite panels p 45 A89-10091 Proceedings of the Second Conference, Dallas, TX. Nov Panel methods in aerodynamics - Some highlights 2-4, 1987 STRUCTURAL ANALYSIS p 10 A89-11481 I SAE P-2051 p 48 A89-t0676 Advanced boundary element methods; Proceedings Of HISSS - A higher-order panel method for subsOnic and Over the rambow --- Aviomcs design and systems the IUTAM Symposium, San Antonio, TX, Apt 13-16, supersomc attached flow about arbitrary configurations mtegration 1987 p 47 A89-10182 p 10 A89-11484 I SAE PAPER 8724991 p 2 A89-10689 La Recherche Aerospatlale, Bimonthly Bulletm, Number Experimental investigation of the performance of a SYSTEMS INTEGRATION 1987-4. 239/July-August supersonic compressor cascade Aerospace avionics equipment and integration; tESA-TT-10881 p 14 N89-19026 INASA-TM-100879_ p 16 N89-10858 Proceedings of the Second Conference, Dallas, TX. Nov Schlieren measurements at the 10,000-foot sled track Experimental research on swept shock wave/boundary 2-4, 1987 layer interactions I DE88-0127481 p42 N89-10899 I SAE P-2051 p 48 A89-10676 SUPERSONIC SPEED lAD-A196938[ p 53 N89-11189 UT 1760A RTS - A IOW-COSt monolithic remote terminal ClVH Longitudinal impact test of a transport airframe section Unique research challenges for h_gh-speed stores interface for MIL-STD: 1760A IDOT/FAA/CT-87/26t p 54 N89-11265 transports I SAE PAPER 872481 I p 48 A89-10677 STRUCTURAL VIBRATION t SAE PAPER 8724001 p 1 A89-10629 Over the rainbow --- Aviomcs design and systems SUPERSONIC WIND TUNNELS The V-22 vibration, structural life, and engine diagnostic Integration system, VSLED The vapor-screen technique of flow VlSUahzation in the I SAE PAPER 8724991 p 2 A89-10689 tSAE 8717321 p 31 A89-10617 intermittent transomc and supersonic wind tunnel Coping with legacy factors --- in data base management p 9 A89-11083 A guide to aircraft turbme engine vibrahon monitoring systems integration p 58 A89-12176 systems SURFACE CRACKS I SAE AIR 18391 p 35 A89-10623 Fatigue crack growth in aircraft main landmg gear A study on effects of aircraft noise environment on its wheels p 28 A89-11447 T structure SURFACE GEOMETRY I SAE PAPER 8724501 p 28 A89-10663 A circular cone surface shaping method for fan blade T-38 AIRCRAFT A dynamic characteristic analysis of a bladed disk p 50 A89-11032 Imphcations of a recent lightning strike to a NASA iet assembly p 36 A89-11026 SURFACE LAYERS trainer p 22 N89-10478 Efficient vibration mode analysis of alrcraff with multiple Aerodynamically-driven condensate layer thickness TAIL ASSEMBLIES external store configurations p 28 A89-12562 distributions on isothermal cylindrical surfaces Development in helicopter tail boom strake applications SUBMARINES p 51 A89-12337 in the US Operating safety of automabc objects --- Russian book SURFACE TEMPERATURE INASA-TM-1014961 p 40 N89-10059 p 49 A89-10714 Sensors for ceramic components in advanced TAIL ROTORS SUBSONIC FLOW propulsion systems: Summary of literature survey and Development in helicopter tail boom strake applications An inverse, subsonic two-dimensional panel method concept analysis, task 3 report in the US following the method of smallest quadrate for the design I NASA-CR- 1809001 p 54 N89-11192 I NASA-TM-101496J p 40 N89-10059 and modification of multiple element profiles SURGES TAKEOFF I DGLR PAPER 87-061 I p 5 A89-10509 Application of end-bend blade for enhancing surge Seaplane takeoff performance - Using delta ratio as a Computational fluid dynamics m aerospace margin p 36 A89-11051 method of correlation p 28 A89-12565 I SAE PAPER 8724461 p 7 A89-10659 Lighting and surge protection of large ground Noise of the Harner in vertical landing and takeoff Two-dimensional subsonic diffuser flow with uniform facilities p 52 N89-10474 p 60 N89-10856 shear velocity profile at inlet p 7 A89-11056 Modelling of common mode coupling between an aircraft TECHNOLOGICAL FORECASTING Panel methods m aerodynamics - Some highhghts wing traversed by a lightning current and wing installed Avlahon technology applicable to developmg regions p 10 A89-11481 m that wing p 22 N89-10485 I NASA-TM-894251 p 23 N89-10872 HISSS - A higher-order panel method for subsonic and SURVEILLANCE TECHNOLOGY ASSESSMENT supersonic attached flow aboul arbitrary configurations Surveillance - High-technology fit-out tot the Nomad The history of aircraft onboard equipment p 10 A89-11484 aircraft I DGLR PAPER 87-054 I p 31 A89-10536 Integral equation solution for transonic and subsonic I SAE PAPER 8724281 p 32 A89-10647 The nonrigid airship of the Siemens-Schuckert Works aerodynamics p 11 A89-11488 SURVEILLANCE RADAR l DGLR PAPER 87-0551 p 60 A89-10537 A subsonic panel method for design of 3-dimensional The operation of modern air-space surveillance radars Aircraft dynamic stabihty - Developmental history complex configurations with specified pressure p 51 A89-12151 aspects distribution p 28 A89-11491 SURVEYS t DGLR PAPER 87-0571 p 1 A89-10538 A vortex-}atbce method for the calculation of wing-vortex _srael Air Force (IAF) m-service aircraft lightning strike Avionic color _iquid crystal displays - Recent trends interaction in subsonic flow p 11 A89-11499 and damage survey p 55 N89o10431 ISAE PAPER 871790} p 31 A89-10585
A-19 TEMPERATURE COMPENSATION SUBJECT INDEX
Atrcraft gas turbine engJne mondormg systems: An THRUST MEASUREMENT Transonic charactebsbcs of a humped airfoil update A jet thrust measurement method with gas composition p 12 A89-12551 ISAE SP-7281 p 33 A89-10613 analysis p 36 A89-11040 Transonic computations about complex configurations Panel methods in aerodynamics Some highlights THRUST REVERSAL using coupled inner and outer flow equations p 10 A89-11481 F-15 SMTD low speed jet effects wind tunnel test p 12 A89-12553 Air-traffic flow management today p 24 A89-12152 results p 16 N89-10853 Navier-Stokes simulation of transonic wing flow lields The winning edge --- NASA role in US aeronaubcs An assessment of ground effects determined by static usmg a zonal grid approach industry's competition with foreign suppliers and dynamic testing techniques p 16 N89-10854 INASA-TM-1000391 p 13 N89-10022 I SAE PAPER 8809451 p 2 A89-12322 THUNDERSTORMS Numerical simulaboll of transonic flow around Asuka Air navigation systems I - Astronomical navigation in International Aerospace and Ground Conference on p 18 N89-11067 the air 1919-1969 p 24 A89-12449 Lightning and Static Electncity TRANSONIC SPEED TEMPERATURE COMPENSATION IPB88-197439t p 55 N89-10429 A transonic interactive boundary-layer theory for laminar The dual element method of slrafn gauge temperalure Tnggermg of flghtmng by the Atlas Centaur vehicle and turbulent flOW over swept wings compensation p 51 A89-12276 p 55 N89-10438 INASA-CR-41851 p 14 N89-10029 TEMPERATURE CONTROL Lightning initiation on aircraft in thunderstorms TRANSONIC WIND TUNNELS AIR 1900 - Guide to temperature monitoring in aircraft p 21 N89-10456 The vapor-screen technique of flow visualization m the gas turbine engines The electncal structure Of thunderstorm anvils intermittent transonic and supersomc wind tunnel ISAE 8717301 p 34 A89-10616 p 56 N89-10470 p 9 A89-11083 TEMPERATURE EFFECTS Intracloud hghtnmg as a precursor to thunderstorm Highhghts of experience with a flexible walled test Aeroelastic thermal effects p 37 N89-10015 microbursts p 56 N89-10490 section in the NASA Langley 03 meter transonic cryogenic tunnel TEMPERATURE MEASUREMENT TILT ROTOR AIRCRAFT INASA-TM-t014911 p 41 N89-I0060 AIR 1900 - Guide to temperature monitoring in aircraft The V-22 wbrahon, structural life. and engine diagnosbc Electrical noise reduction techniques contributing to gas turbine engines system. VSLEO ISAE 8717301 p 34 A89-10616 I SAE 8717321 p 31 A89-10617 improved data quahty at the National Transonlc Facility Sensors for ceramic components in advanced 'The Pointer'. a new concept for RPV air vehicles INASA-CR-41931 p54 NSg-1f f96 propulsion systems: Summary of hterature survey and p 28 A89-12416 TRANSPORT AIRCRAFT concept analysis, task 3 report TIME Invest=gatlons on high Reynolds number laminar flow INASA-CR.1809001 p 54 N89-11192 A filamentary method for calculating induced voltages airfoils p 4 A89-10102 TENSILE TESTS within resistive structures in either the frequency or time Multilevel decomposition approach to the prefimlnary Tension latlgue analysis and life prediction for composite domain p 52 N89 10484 sizing o1 a transport aircraft wing p 25 A89-10109 laminates New tnal of vibration testing method Unique research challenges for high-speed civil INASA-TM-1005491 p 44 N89-10951 p 52 N89-11068 transports TERMINAL FACILITIES TIME DIVISION MULTIPLEXING ISAE PAPER 8724001 p 1 A89-10629 Terminal control area design and air traffic Ioadings Applications of time and wavelength division multiplexing Propulsion-airframe integration for commercial and I DOT/FAA/DS-88/11 I p 25 N89-10038 to digital optical code plates p 31 A89-10364 mildary aircraft TERMINAL VELOCITY TIP SPEED ISAE PAPER 872411 I p 35 A89-10637 An approximate, maximum terminal velocity descent to Cruise noise of the 2/9 scale model SR-7A propeller Contamination of environmental control systems in a point p 59 A89-12561 Hercules aircraft IDE88-0003491 p 15 N89-10840 TITANIUM ALLOYS IMRL-R-11161 p 29 NR9-10040 TEST FACILITIES Microstructural optimisation o1 titanium alloys for defect TRAPEZOIDAL WINGS Multi-axis seat ejection (MASE) sled tolerance m gas turbine engine components Numerical experiments for separation flows around p 26 A89-10466 p 43 A89 10069 trapezoidal cylinders by a discrete vortex method TETHERING TOLLMEIN-SCHLICHTING WAVES p 6 A89-10569 System protection from atmospheric electricity for Suppression of unstable oscillations *n a boundary TREES (MATHEMATICS) aerostats with conducting tethers p 52 N89 10497 layer p 5 A89-10171 Symmetric (and generic) algorithms for hetght balanced THERMAL ENVIRONMENTS TOWERS trees Effect of protective coatings on life of heat-resistant A case for a unified lightning threat ICS-87111 p59 N89-12332 mckel steel under cyclic heat load p 45 N89-11005 p 56 N89.10447 TRENDS THERMAL PROTECTION TRACKING FILTERS Review of aeronautical wind tunnel facilities Passive thermal protection system p 26 A89-10478 A guide to aircraft turbine engine vibration monitoring I NASA-CR-1830571 p41 N89-10897 THERMAL STRESSES systems TUMBLING MOTION Effec_ Ot proIecbve coat}rigs on hfe of heat-resistant I SAE AIR 18391 p 35 A89-10623 Investigabon Of the lumbhng phenomenon using nickel steel under cyclic heat load p 45 N89-11005 TRAILING EDGE FLAPS computer slmulahon p 41 N89-10896 THERMOMETERS Apphcatlon of winglets with integrated adjusted TUNING The dual element method of strain gauge temperature traihng-edge flaps m a genera1 aviahon aircraft Aoroelastlc formulation for tuned and mlstuned rotors compensabon p 51 A89-12276 I DGLR PAPER 87-080[ p 26 A89-10516 p 37 N89-10013 THERMOPLASTIC FILMS TRAJECTORY OPTIMIZATION TURBINE BLADES The effects of fluids in the aircraft enwronment on a An approximate, maximum terminal velocity descent to A data acquisition system for blade vibration test polyethenmlde p 44 A89-12759 a point p41 A89-11037 THREE DIMENSIONAL BOUNDARY LAYER IDE88-000349t p 15 N89-10840 Influence of regeneration treatments on creep rupture Three-dimensional boundary layer transdlon on a TRANSITION FLOW lives of turhme blades p 43 A89-11214 concave-convex curved wall p 4 A89-10167 Boundary layer transd_on The high temperature ox_dahon behawor of the single Approximate calculations of viscous drag and I CERT-OA-40/5018 AYDI p53 N89-11187 crystal Hi-base alloy M002 mud with and without protechve aerodynamic heating p 10 A89-11157 TRANSONIC FLOW coatings p 43 A89-11216 Study of three dimensional boundary layers on the front Efficient algorithm for sotuhon of the unsteady transomc Deposlhon of Na2SO4 from salt-seeded combustion of a fuselage and at an air intake small-disturbance equation p 4 A89-10104 I CERT-OA-22/5025-AYD I p 53 N89-11184 Aerodynamic characteristics of the ACES-II election seat gases of a high velocity burner ng p 43 A89-12330 THREE DIMENSIONAL FLOW at transonic Mach numbers p 25 A89-10463 Aerodynamic design constderatlons for a tree.flying Numerical approach of advanced turboprop with Improvement of a design code for airfoils at transonic ducted propeller three-dimensional Euler equations regime iDE88-0068671 p 15 N89 10841 ISAE PAPER 8724481 p 7 A89-10661 I DGLR PAPER 87-064 I p5 A89-10511 Effect of protechve coatings on life of heat-resistant A new approach to improvement of fans A numerical solution of transonic flow using nickel steel under cyclic heat load p 45 N89-11005 p8 A89-11064 discontinuous shock relahon p 6 A89-10542 TURBINE ENGINES Numerical simulation of supersonic flow over a Apphcahon of an artdlcla_ density scheme of potential A guide to a_rcraft turbine engine vlbrahon monitoring three-dimensional cavity p 9 A89-11105 stream function method to design of airfoil systems Numerioal slmulahon of the vortical flow over a p 7 A89-11053 I SAE AIR 18391 p 35 A89-10623 round-edgeddouble-deltawing p 10 A89-11152 Numencal simulabon of steady traesomc flow past an A comparahve evaluahon of RPD (Rotary Parbcle Application of an advanced panel method to 8-percent DCA cascade at a freestream Mach number Depositor) and ferrographic diagnostic methods for turbtne aerodynamic probJems of mrcrafl design of about 1 p 8 A89-11073 engine lubricant samples p 28 A89 11486 Measurements of unsteady pressure distribution on a [ADA1962071 p38 N89 10044 NACA 0012 profile in transomc flow p 8 A89-11082 A subsonic panel method for design of 3-dimensional T55 L-712 turbine engine compressor housing Analysis of transonic wings including viscous complex conhguratlons with specified pressure refurbishment-plasma spray prelect distribution p 28 A89-11491 interaction p 9 A89-11084 I NASA-TM. I0131Oi p44 N89.10156 Finite element method for calculating transonic potential Fmde element Euler computations in three dlmens,ons TURBINE WHEELS flow around alrloiI from pressure minimum integration p 11 A89-12130 Statistics on aircraft gas turbine engine rotor failures p 9 A89-11086 that occurred m US commercial awahon during 1982 Calculations of the unsteady, three-dimensional flow Diagonal imphcd mulhgnd algorithm Ior the Euler {DOT/FAA/CT-88/231 p 38 N89-10892 field reside a motored Wankel engine equahons p 9 A89-11110 TURBOCOMPRESSORS ISAE PAPER 8806251 p 37 A89-12307 Unsteady transonic airfoil computation using imphcd Approach to blade end-bend mechanism Three dimensional shear flow Analysis of the flow m Euler scheme on body fixed gnd p 10 A89-t 1153 p 36 A89 11052 a delta arrow wing with incidence angle The predichon of transonic mtederence flow by means ICERT-RTS*OA-25/5025-AYDI p 17 N89-10864 of a hybrid method p 10 A89-11487 Experimental study of rotahng stall in single-stage axial THRUST Integral equation solution for transomc and subsomc compressor p 8 A89-11059 Turbofan forced m_xer lobe flow modeling. Part 3: aerodynamics p 11 A89-11488 Experimenta_ investigation ol the performance of a Application to augment engines Calculation of unsteady transonic flow about oscillating supersonic compressor cascade INASA-CR-41471 p 14 N89-10025 wings by a field panel method p 11 A89-11498 INASA-TM 1008791 p 16 N89-10858
A-20 SUBJECT INDEX VORTEX SHEETS
TURBOFAN ENGINES Highlights of experience with a flexible walled test VAPOR DEPOSITION Turbofan forced mixer lobe flow modehng Part 3: sechon in the NASA Langley 0 3-meter transonic cryogenic Deposition of Na2SO4 from salt seeded combushon Apphcatlen to augment engmes tunnel gases of a high velocity burner rig p 43 A89-12330 INASA-CR-41471 p 14 N89-10025 I NASA-TM-t01491 I p 41 N89-10060 VARIABLE GEOMETRY STRUCTURES TWO DIMENSIONAL MODELS TURBOFANS fs 32 - A spht-Fowler girder problem presentabon and A new approach to improvement of fans Two-dimensional model for airfoil unsteady drag below solutions p8 A89-11064 stall p 4 A89-10114 I DGLR PAPER 87-082t p 26 A89-10518 TURBOJET ENGINES TWO PHASE FLOW VATOL AIRCRAFT Establishment of variable vane regulation law Navler-Stokes solution to the flowfield over ice accrehon The 1987 Ground Vortex Workshop p 36 A89-11044 shapes p 12 A89-12557 INASA-CP*100081 p 15 N89-10849 De-icing of aircraft turbine engine inlets VECTORS (MATHEMATICS) I DOT/FAA/CT-87/371 p 38 N89-10894 U Programmmg techniques for high-speed processmg on TURBOMACHINERY the supercomputer FUJITSU VP-sysfem Forced vibration and flutter design methodology INAL-TR-9151 p 58 N89-f0565 UH-1 HELICOPTER p 51 N89-10016 VELOCITY MEASUREMENT Development of a rule-based demonstration prototype TURBOPROP ENGINES Three component laser anemometer measurements fn expert system for inflight emergencies for the UH1H Development and testing of an inflight engine an annular cascade of core turbine vanes with contoured performance monitoring techmque for the U.S Navy P-3C helicopter p 32 A89-12415 end wall ULTRAHIGH FREOUENCIES airplane I NASA-TP-2846 ) p 15 NBg-10844 {SAE 841462) p 34 A89-10615 Results of 1987 MSS hehcopter propagation experiment VERTICAL TAKEOFF AIRCRAFT at UHF and L band in Central Maryland Guide to limited engine monitoring systems for aircraft Wave drag and high-speed performance of supersonic p 53 N89-1f077 gas turbine engines STOVL fighter configuration ULTRALIGHT AIRCRAFT I SAE AIR 18731 p 35 A89-10626 INASA-TM-t000611 p 13 N89-10017 Low-Reynolds-number airfoil design for the M.I.T Numerical approach of advanced turboprop with The t987 Ground Vortex Workshop Daedalus prototype - A case study p 12 A89-12559 three-dimensional Euler equat_)ns tNASA-CP-10008t p 15 N89-10849 Flight test results for the Daedalus and Light Eagle I SAE PAPER 8724481 p 7 A89-10661 Numencal investigation of a jet in ground effect using human powered aircraft Experience with the development of turboprop the fortified Navler-Stokes scheme p 16 N89-I0857 ]NASA-CR-1833051 p 30 N89-10890 engmes p 37 A89-11074 VERY LARGE SCALE INTEGRATION UNITED STATES Experimental aerodynamic performance of advanced 40 UT 1760A RTS - A low-cost monolithtc remote terminal Development in hehcopter tail boom strake applications deg-swept 10-blade propeller model at Mach 0.6 to 0.85 stores interface for MIL-STD-1760A in the US i NASA-TM-889691 p 17 N89-10865 I SAE PAPER 872481 I p 48 A89-10677 tNASA-TM-1014961 p 40 N89-10059 TURBOSHAFTS VIBRATION DAMPING UNSTEADY AERODYNAMICS Guide to limded engine monitoring systems for aircraft The bistable behavior of a rigtd rotor with squeeze film Efficient algorithm for solution of the unsteady transonic gas turbine engtnes damper p 49 A89-11029 ]SAE AIR 18731 p 35 A89-10626 small-disturbance equation p 4 A89-10104 VIBRATION ISOLATORS Unified computation method of unsteady TURBULENCE Composites _n shock and vibrahon tsolahon supersonic/hypersenic flow past two dimensional fiat plate Turbulence management and relaminarisation; p 50 A89-1f251 and rectangular wings Proceedings of the IUTAM Symposium, Bangalore. India. VIBRATION MODE ISAE PAPER 8724471 p 7 A89+10660 Jan 19-23, 1987 p 46 A89-10154 A frequency domain MIMO medal identlficatron method Unsteady leading noise of counter-rotating propeller TURBULENCE MODELS with apphcation in the a_rcrafl ground vibration test p 36 A89-11054 Comparison Of Iongitudmalty stabilized behavtor in I SAE PAPER 872458I p 48 A89-10670 Measurements of unsteady pressure distributlen on a vertical turbulence between a modern canard configuration VIBRATION TESTS NACA 0012 profile m transonic flow p 8 A89-11082 and a conventional aircraft A frequ_Ftncy domain MIMO modal identihcation method A doublet point method for the calculation of unsteady IDGLR PAPER 87-078i p39 A89-10515 with application in the aircraft ground vlbrahon test propeller aerodynamics p 11 A89-11497 Calculation of compressible flow and heat transfer on j SAE PAPER 872458i p 48 A89-10670 Prediction of incidence effects on oseiltatmg a_rfoil a rotating disk p 50 A89-11033 A data acquisition system for blade vibration test aerodynamics by a locally analytical method TURBULENT BOUNDARY LAYER p41 A89-11037 p 12 A89-12135 Turbulent boundary layer mampulation and modelling New trial of vibration testing method AGARD manual on aeroelasticity in axial-flew in zero and adverse pressure gradients p 52 N89-f 1068 turbomachines Volume 2: Structural dynamics and p 46 A89-10159 VIBRATIONAL STRESS aeroeiast=city The wall-pressure fluctuations of modified turbulent A data acquisition system for blade vibration test IAGARD-AG-2g8-VOL-21 p 13 N89-10006 boundary layer with r_blets p 47 A89-10163 p 41 A89-11037 Aeroelastlc formulation for tuned and mistuned rotors Experimental research on swept shock wave/boundary VISCOSITY p 37 N89-10013 layer interactions Cascade flow analysis by Nawer-Stokes equation Fan flutter test p 37 N89-10014 IAD-A1969381 p 53 N89-11189 p 52 N89-11065 UNSTEADY FLOW TURBULENT DIFFUSION VISCOUS DRAG Two-dimensional model for airfoil unsteady drag below Confmuum theories for fluid-particle flows: Some Approximate calculabons of viscous drag and stall p 4 A89-10114 aspects of hft forces and turbulence p 53 N89-11155 aerodynamic heating p 10 A89-11157 TURBULENT FLOW A second-order numencal method for the analysis of VISCOUS FLOW two-dimensional flow of ideal fluid through a cascade with AnalysEs of complex hypersomc flows with strong Analysis of transonic wings including viscous supersonic mput p 6 A89-10607 wscous/Inviscld mteraction p 9 A89-11109 interaction p 9 A89-11084 A transonic interactive boundary-layer theory for laminar Undied computation method of unsteady Numerical stmulatlon of compact schemes in and turbulent flow over swept wings supersonic/hypersonic flow past two dimensional fiat plate super-son_c wscous flows p 9 A89-11085 INASA-CR-41851 p 14 N89-10029 and rectangular wmgs Analysis of complex hypersonic flows with strong Flow around a delta wing w_th or without a canard (Phi I SAE PAPER 8724471 p 7 A89-10660 wscous/mviscid interaction p 9 A89-1f f09 BA 60 deg) Part 2: Hydredynamlc vlsualizatlens m Unsteady transonic aidoll computation using implicit Panel methods in aerodynamics - Some highhghts unsteady flow (pitching oscitlabons) Euler scheme on body-fixed grid p 10 A89-11153 p 10 A89-1148f I ONERA-RT-11/2891-AN-PT-21 p 17 N89-10860 Steady and unsteady potential flows around VISUAL PERCEPTION TURBULENT MIXING axisymmetric bodies and ring airfods p 11 A89-11489 The design eye reference pont --- for determinmg On the pairing process m an excded, plane, turbulent Calculation of unsteady transonic flow about oscillatmg geometric entities defining cockpit layouts m_xlng layer p 47 A89-10173 wings by a field panel method p f 1 A89-11498 iSAE PAPER 8717631 p 31 A89-10582 TURBULENT WAKES VOICE CONTROL Calculations of the unsteady, three-dimensional flow Flew past circular cyttnder of finite length placed on field inside a motored WankeL engine Speech recOgnition in advanced rotorcraft - Using ground plane p 48 A89-10543 !SAE PAPER 8806251 p 37 A89-12307 speech controls to reduce manual control overload Inveshgation of wake vortices of landing aircraft at p 24 A89-12404 Unsteady three-dimensional stall on a rectangular Frankfurt airport (Federal Republic of Germany) VORTEX BREAKDOWN wmg p 14 N89-10027 iDFVLR-MtTT-88-15f p 17 N89-10862 Research on the computational method of aerodynamic TWO DIMENSIONAL BODIES characteristics ot wing w_th vortex breakdown at high angle A computational study of coherent structures in the V of attack p 9 A89-11086 wakes of two-dimensional bluff bodies VORTEX GENERATORS I AD-A1968201 p53 N8g-t 1188 Inveshgahon of wake vortices of landing aircraft at VISTOL AIRCRAFT TWO DIMENSIONAL FLOW Frankfurt airport (Federal Repubhc of Germany) V/STOL aircraft configurations and opportunities in the An reverse, subsonic two-dlmenstonal panel method t DFVLR-MITT-88-151 p 17 N89-10862 Pacdic Basin following the method of smallest quadrate for the design VORTEX SHEDDING I SAE PAPER 8724031 p 18 A89-f0631 and modification of multiple element profiles A computational study of coherent structures in the i DGLR PAPER 87-061 I p 5 A89-10509 Wave drag and high-speed performance of supersonic wakes of two-dimensional bluff bodies A numerical sJmulahon of separated llow around STOVL fighter configuration I AD-Af 96820 [ p53 N89-11188 two-dimensional wmg by a discrete vortex method i NASA-TM-100061 } p f3 N89-10017 VORTEX SHEETS p 6 A89-10568 Phase 4 static tests of the J-g7 powered, external A numerical simulahon of separated flow around A second-order numencal method for the analysis of augmentor V/STOL model at the NASA. Ames Research two-dimensional wing by a discrete vortex method fwo-dimens_onal flow of ideal ftuld through a cascade with Center, November 1983 p 6 A89-10568 supersemc mpuf p 6 A89-10607 INASA-CR-1773951 p 14 N89-10028 Numerical experiments for separation flows around Two-dimensional subsenLc diffuser flow with uniform VALVES trapezoidal cylinders by a discrete vortex method shear velocity profile at inlet p 7 A8g-11056 The electrochemLcal erosion of serve valves by p 6 A89-10569 Integral equation solution for transonic and subsonic phosphate ester fire-resistant hydrauhc fluids A vortex-lattice method for the calculation of wing-vortex aerodynamics p 11 A89-11488 p 48 A89-10573 interaction in subsonic flow p 11 A89-1 t499
A-21 VORTICES SUBJECT INDEX
Approximation of free and bounded vortex sheets at WEATHER Measurement of aerodynamic characteristics of a delta-wings p 11 A89-11500 Aircraft accident reports, brief format, US civil and foreign hang-glider-wing by ground run tests using a test vehicle VORTICES aviation, issue number 10 of 1987 accidents INAL-TR-9531 p 13 N89-10004 Computational and experimental studies of LEBUs at {PB88-9169051 p 20 N89-10035 The pros and cons of code validation high device Reynolds numbers p 4 A89-10160 Aircraft accident reports, brief format, US civil and foreign INASA-TM-1006571 p 14 N89-10034 Flow past circular cylinder of finite length placed on aviation, issue number 12 of 1986 accidents Shock tunnel studies of scramjet phenomena ground plane p 48 A89-10543 I PB88-9169031 p 20 N89-10036 I NASA-CR-181721 I p 38 N89-10045 The formation mechanism of the asymmetric spatial Statistics of lightning interaction with aircraft in Japan Highlights of experience with a flexible walled test vortex of slender bodies at high angle of attack p 55 N89-10430 section in the NASA Langley 0 3-meter transonic cryogenic I SAE PAPER 8724351 p 7 A89-10652 tunnel WEATHER FORECASTING A study of the accuracy of wing calculehons based on I NASA-TM-t01491 I p 41 N89-10060 Oklahoma-Kansas preliminary regional experiment for different schemes p 49 A89-10774 Aerodynamic design considerations for a free-flying storm-central (O-K pre-storm). Volume 3: Aircraft mission A further improvement in the numerical method of ducted propeller summary supersonic infinitesimal horseshoe vortex distribution IDE88-0068671 p 15 N89-10841 I PB88-2054891 p 56 N89-10499 p8 A89-11080 Experimental results for the Eppler 387 airfoil at low WEATHER RECONNAISSANCE AIRCRAFT Propulsive vortical signature el plunging and pitching Reynolds numbers in the Langley low-turbulence pressure Oklahoma-Kansas preliminary regional experiment for airfoils p9 A89-11115 tunnel Numerical simulation of the vortical flow over a storm-central (O-K pre-storm) Volume 3: Aircraft mission INASA-TM-40621 p 15 N89-10842 round-edged double-delta wing p 10 A89-11152 summary Tests on 3 NACA 0012 airfoil models of DFVLR in the I PB88-2054891 p 56 N89-10499 Heat transfer in the recirculating region formed by a NAL 0.3 tunnel: An assessment of 2-O wall interference backward-facing step p 51 A89-12252 WEATHER STATIONS ITM-AE*87051 p 15 N89-10847 Incompressible Navier-Stokes computations for a Evaluation of enhancements to the Low Level Wind F-t5 SMTD low speed jet effects wind tunnel test round-edged double-delta wing p 12 A89-12552 Shear Alert System (LLWAS) at Stapleton International results p 16 N89-10853 Structure-borne noise control for propeller aircraft Airport Experimental investigation of flow near a corner, part p 59 A89-12563 I DOT/FAA/PS-88/14 I p 56 N89-11356 2 The 1987 Ground Vortex Workshop WEATHERING ICERT-RT-OA-24/5025-AYDI p 17 N89-10861 INASA-CP-100081 p 15 N89-10849 The performance of alternate fuels in general aviation Three dimensional shear flow Analysis of the flow m The characteristics of the ground vortex and its effect aircraft a delta arrow wing with incidence angle on the aerodynamics of the STOL configuration t DOT/FAA/CT-88/131 p44 N89-I0175 ICERT-RTS-OA-25/5025-AYDI p 17 N89-10864 p 15 N89-10850 WHEELS Unsteady low-speed windtunnel test of a straked delta Ground vortex flow field investigation Wheel performance evaluation Phase 1: Analysis wing, oscillating in pitch Part 1: General description and p 16 N89-10852 I DOT/FAA/CT-88/161 p 29 N89-10041 discussion of results An assessment of ground effects determined by static WIND (METEOROLOGY) lAD-A1964561 p 18 N89o10867 and dynamic testing techniques p 16 N89-10854 Oklahoma-Kansas prehminary regional experiment for Investigation o1 the tumbhng phenomenon using Effects of a ground vortex on the aerodynamics of an storm-central (O-K pre-storm). Volume 3: Aircraft mission computer simulation p 41 N89-10896 airfoil p 16 N89-10855 summary Review of aeronautical wind tunnel facildies Numerical investigation of a jet _n ground effect using t PB88-2054891 p 56 N89-10499 I NASA-CR-183057) p 41 N89-10897 the fortified Navier-Stokes scheme p 16 N89-10857 WIND EFFECTS CAD wind tunnel test for half-cut model of Asuka VORTIClTY Analytical and experimental research on aerodynamical p 18 N89-11069 On the evaluation of aerodynamic influence effects of wind shear on aircraft p 6 A89-10547 Electrical noise reduction techniques contributing to coefficients p 11 A89-11496 WIND MEASUREMENT improved data quality at the National Transonic Facility Shear wind measurements aboard a Piper PA 18 and I NASA-CR-41931 p54 N89-11196 the design of a model ghder aircraft for dynamic gliding WIND TUNNEL WALLS W flight Three-dimensional boundary layer transition on a I DGLR PAPER 87-135/1 I p 26 A89-10526 concave-convex curved wall p 4 A89-10167 WAKES WIND SHEAR Investigation on wall interference of low-speed wind Laser sheet technique for visualizing a periodic rotor The 'Pneumatic Wind Shear Sensor' (PWSS) - An aid tunnel with slotted walls p 8 A89-11081 wake p41 A89-10115 to fhght path regulation and to disturbance magnitude Convergence schemes for an adaptive-wall wind A computational study of coherent structures in the identification m shear wind situations tunnel p 41 A89-12560 wakes of two-dimensional bluff bodies I DGLR PAPER 87-1341 p 31 A89-10525 Highlights of experience wdh a flexible walled test I AD-A1968201 p53 N89-11188 Shear wind measurements aboard a Piper PA 18 and section in the NASA Langley 0 3-meter transonic cryogenic tunne_ WALL PRESSURE the design el a model glider aircraft for dynamic gliding The wall-pressure fluctuations of modified turbulent flight I NASA-TM-101491 I p 41 N89-1006Q WIND TUNNELS boundary layer with nblets p 47 A89-10163 I DGLR PAPER 87-135/1 I p 26 A89-10526 Review of aeronautica_ wind tunnel faclhtles Tests on 3 NACA 0012 airfoil models of DFVLR in the Analyhcal and experimental research on aerodynamical I NASA-CR-t 83057 I p41 N89-10897 NAL 03 tunnel: An assessment of 2-D wall interference effects of wind shear on aircraft p 6 A89-10547 Aerospace technology - Windehear FAA: Boeing WIND TURBINES ITM-AE-87051 p 15 N89-10847 Windshear Training Aid program Thick airfoil at low Reynolds number and high WANKEL ENGINES I SAE PAPER 872441 I p 19 A89-10655 incidence p 4 A89-10116 Calculations of the unsteady, three-dimensional flow Structure and life cycle Of microburst outflows observed WIND VELOCITY field inside a motored Wankel engine in Colorado p 54 A89-11221 Unsteady low-speed wlndtunnel test of a straked delta ISAE PAPER 8806251 p 37 A89-12307 Evaluation of enhancements to the Low Level Wind wing, oscdlatmg in pitch Part 1: General doscbption and WARNING SYSTEMS Shear Alert System (LLWAS) at Stapteton International discussion of results Application of constraint suspension techniques to Airport lAD-A1964561 p 18 N89-10867 diagnosis in helicopter caution/warning systems I DOT/FAA/PS-88/141 p 56 N89-11356 WINDSHIELDS p 32 A89-12411 WIND TUNNEL TESTS Windscreen design and testing p 29 A89-12720 New electric field instrumentation and the effects of Experimental study of effects of forebody geometry on WING FLOW METHOD TESTS space charge at Kennedy Space Center high angle-of-attack stabihty p 38 A89-10103 An experimental study on aerodynamic performance of p 55 N89-10444 Laser sheet technique for visualizing a periodic rotor Lippisch-type GEW - - Ground Effect Wing The SAFIR lightning monitoring and warning system, wake p 41 A89-10115 p 6 A89-10544 apphcahons to aerospace activihes p 52 N89-10481 Thick airfoil at low Reynolds number and high WING LOADING In-serwce evaluahon of the Traffic Alert and Colhslon incidence p 4 A89-10116 A vortex-lattice method for the caiculahon of wing-vortex Avoidance System (TCAS) industry prototype Automated optical instrument for extracting water droplet interaction in subsonic flow p 11 A89-11499 I DOT/EAA/SA-88/21 p 25 N89-10885 impingement data from wind tunnel experiments Approximation of free and bounded vortex sheets at Evaluahon of enhancements to the Low Level Wind p 47 A89-10261 delta-wings p 11 A89-11500 Shear Alert System (LLWAS) at Stapteton International Aerodynamic characteristics of the ACES-II election seat WING NACELLE CONFIGURATIONS Airport at transonic Math numbers p 25 A89-10463 Wing laminar boundary layer in the presence of a IDOT/FAA/PS-88/141 p 56 N89-11356 Study of the engine influence on wings with modern propeller slipstream p 4 A89-10105 WAVE DRAG high-bypass propulsion concepts Propulsion-airframe integrahon for commercial and Wave drag and high-speed performance of supersonic I DGLR PAPER 87-0631 p 5 A89-10510 military aircraft STOVL fighter eonhgurahon An experimental study on aerodynamic performance of I SAE PAPER 872411 I p 35 A89-10637 INASA-TM-100061 I p 13 N89-10017 Lippisch-type GEW --- Ground Effect Wing WING OSCILLATIONS p 6 A89-10544 WAVE EQUATIONS Efliclent algorithm for solution of the unsteady traneomc Experimental investigation of convergent ejector BEM for wave equahon with boundary m arbitrary motion small-disturbance equation , p 4 A89-10104 nozzle/afterbody in wind tunnel p 8 A89-11060 and applications to compressible potential aerodynamics Unsteady transonic airfoil computahon using imphcit Propulsive vortical signature of plunging and pdchmg of airplanes and helicopters p 5 A89-10192 Euler scheme on body-fixed gnd p 10 A89-11153 airfoils p 9 A89-11115 WAVE PROPAGATION Calculation of unsteady transonic flow about osclllahng Aerothermodynamics - The required tools Results of 1987 MSS hehcopter propagation experiment ISAE PAPER 8809281 p 12 A89-12316 wings by a held panel method p 11 A89-11498 at UHF and L band m Central Maryland Inlet development for the NFAC 80- by 120-foot indraft WING PANELS p 53 N89 11077 wind tunnel Study of the engine influence on wings with modern ETS-V propagation expenments m Japan I AIAA PAPER 88-25281 p 41 A89-12550 high-bypass propulsion concepts p53 N89-11080 Transonic characteristics of a bumped air|oil IDGLR PAPER 87-0631 p 5 A89-10510 WAVELENGTH DIVISION MULTIPLEXING p 12 A89-12551 WING PROFILES Applications of time and wavelength division multiplexing Cruise noise of the 2/9 scale model SR-YA propeller Multilevel decomposd_on approach to the prehmmary to digital optical code plates p 31 A89-10364 p 59 A89-12561 s_zing of a transport aircraft wing p 25 A89-10109
A-22 SUBJECT INDEX X-29 AIRCRAFT
T[ansitlon recogn_tien In aircraft wing profiles with the aid of piezoelectric sheetings I DGLR PAPER 87-065 J p 47 A89-10512 fs 32 - A split-Fowler glider problem presentation and solutions I DGLR PAPER 87-0821 p 26 A89-10518 A numerical simulation of separated flow around two-dimensional wing by a discrete vortex method p 6 A89-10568 Measurements of unsteady pressure distribution on a NACA 0012 profile in transonic flow p 8 A89-11082 The prediction of transonic interference flow by means of a hybnd method p 10 A89-11487 GENMAP - Computer code for mission adaptive profile generation p 12 A89-12566 WING TIP VORTICES ACOUStiCS of transonic blade-vortex interactions p 59 A89-11101 Numerical solutions of induced velocities by semi-infinite tip vortex lines p 12 A89-12554 WINGLETS Application of wingiets with integrated, adjusted trailing*edge flaps in a general awatien aircraft I DGLR PAPER 87-0801 p 26 A89-10516 WINGS Fatigue testing of fulL-scale all-composite aircraft wings ] SAE PAPER 872459] p 48 A89-10671 A study of the accuracy of wing calculations based on different schemes p 49 A89-10774 Analysis of transonic wings including viscous interaction p 9 A89-11084 Structure-borne noise control for propeller aircraft p 59 A89-12563 Nawer-Stokes simulation of transonic wing flow fields using a zonal grid approach 1NASA-TM-1000391 p 13 N89-10022 Finite difference analysis of external and internal lightning response Of the JAS39 CFC wing p 22 N89-10483 Modelling of common mode coupling between an aircraft wing traversed by a lightning current and wiring installed in that wing p 22 N89-10485 WORKLOADS (PSYCHOPHYSlOLOGY) TEAS - An AI based threat response recommendation system I SAE PAPER 871804 f p 57 A89-10589 X
X-29 AIRCRAFT X-29A forward-swept-wing flight research program status I SAE PAPER 8724181 p 27 A89-10640 investigation of the tumbling phenomenon using computer simulahon p 41 N89-10896
A-23 PERSONAL AUTHOR INDEX
AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 236) February 1989
lypical Personal Author Index Listing
ASO, SHIGERU BELO, E. M. A numerical simulation of separated flow around The use of the complex summation method for two-dtmensionat wing by a discrete vortex method formulating algonthms for decoupling vertical/horizontal p 6 A89-10568 motions of rolhng aircraft p 30 N89-10889 _ PERSONAL AUTHOR I Numerical experiments for separation flows around BENNETHUM, W. H. 'BOURNE, SIMON M. trapezoidal cylinders by a discrete vortex method Sensors for ceramic components in advanced p 6 A89-10569 propulsion systems: Summary of hterature survey and r._s Hehcopter roll control effectiveness criteria program ummary ASSELINEAU, A. concept analysis, task 3 report Analysis of recent in-fhght hghtning measurements on I NASA-CR-t 809001 p54 N89-11 t92 different aircraft p 20 N89-10450 BEN.SON, J. W. AUGUST, RICHARD Hardware fault mserbon and instrumentation system: Experimentation and results Vibration, performance, flutter and forced response I NASA-CR-1827461 p 58 N89-10526 characteristics of a large-scale propfan and its aeroelastic BERGSTROM, JENS ___Ac_INASACR-177477 I p 39 N89-tO046 model Swedish Symposium on Residual Stresses. Sunne. I NASA-TM-1013221 p 38 N89-10043 Sweden, Mar 30-Apr. 2, 1987, Proceedings AUGUSTIN, MICHAEL J. p 46 A89-10096 The V-22 wbration, structural life, and engBne diagnosttc BERTELRUD, ARILD system. VSLED Computational and expenmental studies of LEBUs at ISAE 6717321 p 31 A89-10617 h_gh dewce Reynolds numbers p 4 A89-10160 Listings in this index are arranged alphabetically BETZ, KEVIN T. by personal author. The title of the document pro- B Passwe thermal protection system p 28 A89-10478 vides the user with a brief description of the sub- BHARADVAJ, BALA K.
ject matter. The report_numher helps to indicate BEM for wave equation with boundary in arbitrary motion BAILEY, F. R. and applications to compressible potential aerodynamics the type of document listed (e.g., NASA report, Computational fluid dynamics m aerospace of airplanes and helicopters p 5 A89-10192 translation, NASA contractor report). The page I SAE PAPER 8724461 p 7 A89-10659 BIGELOW, C. A. and accession numbers are located beneath and BAKOW, L Effect of adhesive debond on stress-intensity factors Wheel performance evaluation Phase 1: Analysis to the right of the title. Under any one author's in bonded composde panels p 45 A89-10091 I DOT/FAA/CT-88/161 p 29 N89-10041 BLAKE, WILLIAM B. name the access=on numbers are arranged in se- BALLMANN, J. F-15 SMTD low speed let effects wind tunnel test quence with the AIAA accession numbers appear- Approximation of free and bounded vortex sheets at results p 16 N89-t0853 ing first• delta-wings p 11 A89-11500 BLATr, J. R. BAO, GUOHUA Turbofan forced mixer lobe flow modeling. Part 3: Research on the computational method of aerodynamic Application to augment engines A characterist*cs of wing with vortex breakdown at high angle I NASA-CR-41471 p 14 N89-10025 of attack p 9 A89-11086 BLOXSIDGE, G. J. ADAMS, R. J. BARAB, JOHN D. Actwe control of reheat buzz p 43 A89-t 1103 BOBBITr, PERCY J. Aeronaubeal decision making for air ambulance Evaluation of enhancements to the Low Level Wind helicopter pilots: SJtuahonal awareness exercises Shear Alert System (LLWAS) at Stapleton International The pros and cons of code validation I DOT/FAA/DS-88/61 p 23 N89-10869 Airport tNASA-TM-100657I p 14 N89-10034 BODAPATI, S. AGNESE, J. C. 1DOT/FAA/PS-88/141 p 56 N89-11356 Convergence schemes tot an adaptive-wall wind BARBER, T. Flight mechanics and aerothermodynamic software tunnel p 41 A89-12560 ICNES-CT/DTI/MS/MN/0691 p 4 N89-10839 Turbofan forced mixer lobe flow modeling Part 3 BOLSTRIDGE, LOREN D. Application to augment engines ALBERS, JAMES A. In-service evaluation of the Traffic Alert and Collision INASA-CR-41471 p 14 N89-10025 V/STOL a_rcraft configurations and opportunlhes in the Avoidance System (TCAS) industry prototype BARBER, T. J. Pacific Basin I DOT/FAA/SA-88/21 p 25 N89-10885 Analysis of complex hypersonic flows with strong I SAE PAPER 8724031 p 18 A89-1063t BOOTSMA, PETER viscous/invIscid _nterachon p 9 A8g-11109 ALBRITrON, J. bghtning tests to measure the bulk current levels BARGER, RAYMOND L Fracture criterJa for discontinuously reinforced meta_ associated with the electronic engine control of a turboprop Weak-wave analysis of shock interaction with a matrix composites commuter transport p 21 N89-10457 slipstream I NASA-CR-1811751 p44 N89-10125 BORGMEYER, E. H. tNASA-TP-28481 p 13 N89-10020 Introduchon of the Hornet - A success story ALLES, W. BARTSCH, O. I SAE PAPER 8724361 p 27 A89-10653 Aspects of the Control and stablhzation of supersonic Compartson of longitudinally stab=hzed behavior in BORTOLUSSl, MICHAEL R. commercial aircraft vertical turbulence between a modern canard configuration Speech recognit*on in advanced rotorcraft - Using I DGLR PAPER 87-1221 p 39 A89-t0519 and a conventional atrcraft speech controls to reduce manual control overload ALLGOOD, G. O. IDGLR PAPER 87-0781 p 39 A89-10515 p 24 A89-12404 Prototype data acquisition and analysis system for Navy BASSIRI, RAMID BOULAY, J. L operational flight simulators Analyhcal and expenmental research on aerodynamical Analys_s of recent in-flight lightning measurements on IDE88-0145571 p 42 N89-10901 effects of wind shear on aircraft p 6 A89-10547 different aircraft p 20 N89-t0450 ALTON, LARRY R. BATINA, JOHN T. BOURNE, SIMON M. Aviation technology apphcable 1o developing regions Efficient algorithm for solutton of the unsteady transonic Hehcopter roll control effectiveness criteria program INASA-TM-e94251 p 23 N89-10872 small-disturbance equation p 4 A89-10104 summary ANDERSON, BRUCE BAUER, BRIAN P. ] NASA-CR-t 77477 t p39 N89-10046 New electric field _nstrumentatlon and the effects of The Symbolics SCOPE system as a platform for BRAND, A. G. Laser sheet technique for visualizing a periodic rotor space charge at Kennedy Space Center environmental analysis p 57 A89-11748 wake p 41 A89-10115 p 55 N89-10444 BAUER, ROBERT J. BRANDON, JAY M. ANDO, SHIGENORI Single-chip solution of MiL-STD-1553A and Experimental study of effects, of forebody geometry on An experimental study on aerodynamic performance of MIL-STD-1553B data communications high angle*of-attack stabdity p 38 A89-10103 bppisch-type GEW p 6 A89-10544 I SAE PAPER 8724881 p 48 A89-t0683 BREER, M. D. APPEL, J. BAUGHN, T. V. Automated optical instrument for extracting water _roplet S_mulation of a birdstrike tmpact on aircraft canopy The SAFIR lightning monltonng and warmng system, impingement data from wind tunnel experiments applications to aerospace actwities p 52 N89-10481 material p 25 A89-10113 p 47 A89-10261 ARNAL, D. BEACH, G. R. BRENDEL, M. Boundary layer transition System protection from atmospheric electricity for Boundary-layer measurements on an airfoil at low ICERT-OA-40/5018-AYDI p 53 N89-11187 aerostats with conducting tethers p 52 N89-10497 Reynolds numbers p 4 A89-10106 ARNOLD, UWE BEHR, R. BRESCIANINI, C. Development of a helicopter simulation program A vortex-lattice method for the Calculation of wing-vortex Shock tunnel studies of scramjet phenomena I DGLR PAPER 87-1231 p 26 A89-10520 interaction in subsonic flow p 11 A89-11499 {NASA-CR-181721 [ p 3E N89-10045
B-1 BROCK, MARX PERSONAL AUTHOR INDEX
BROCK, MARX CHEN, JING-SONG D Electrification of hovering helicopters Unified computation method of unsteady p 22 N89-10460 supersonic hypersonic flow past two dimensiona_ flat plate DAMMEL, U. BRON, COEN and rectangular wings Aspects of increasing economy using future low-power Symmetric (and generic) algorithms for height balanced I SAE PAPER 872447 I p 7 A89-10660 aircraft propulsion systems trees CHEN, MAOZHANG I DGLR PAPER 87-1001 p 33 A89-10528 ICS-8711 I p 59 N89-12332 Propfan design by propeller-nacelle interaction DARDEN, CHRISTINE M. BROUGH, T. analysis p 36 A89-11055 Validation of a pair of computer codes for estimation The work of the Aviation Bird Unit p 3 A89-12723 CHIANG, HSlAO-WEI D. and optimization of subsonic aerodynamic performance BROWN, BILL Prediction of incidence effects on oscillating airfoil of simple hinged-flap systems for thin swept wings Surveillance - High-technology fit-out for the Nomad aerodynamics by a locally analytical method INASA-TP-28281 p 13 N89-10024 aircraft p 12 A89-12135 DE REMER, DALE I SAE PAPER 8724281 p 32 A89-10647 CHIEN, SUNG-fL Seaplane takeoff performance - Using delta ratio as a BROWN, P. C. method of correlation p 28 A89-12565 Rule-based string code processor p 57 A89-11750 Results of acoustic tests of a prop-fan model CHIU, YIHWAN DANNY DECAMP, RONALD W. p 59 A89-10112 Mission-Adaptive Wing Numerical solutions of induced velocities by semi-infinite BROWN, STANLEY R. ISAE PAPER 8724191 p 27 A89-10641 Environmental durability of adhesivety bonded iomts tip vortex lines p 12 A89-12554 DEJARNETTE, FRED R. p 46 A89-10095 CHOI, KWING-SO A transonic interactive boundary-layer theory for laminar BRUSSAT, T. R. The wall-pressure fluctuations of modified turbulent and turbulent flow over swept wings Wheel performance evaluation Phase 1: Analysis boundary layer with riblets p 47 A89-10163 INASA-CR-41851 p 14 N89-10029 I DOT/FAA/CT-88/161 p 29 N89-10041 CHUANG, H. ANDREW DELFRATE, JOHN H. BULLOCK, J. WILLIAM Unsteady transonic airfoil computation using implicit Ground vortex flow field investigation A chronology of m-cloud electric field and lightning Euler scheme on body-fixed grid p 10 A89-11153 p 16 N89-10852 strikes on an instrumented research aircraft CLARK, E. L DELUCfA, R. A. p 21 N89-10455 Aerodynamic design and performance of a bent-axis BUNATA, OLDRICH geometry vehicle Statistics on aircraft gas turbine engine rotor failures that occurred in US commercial aviation during 1982 Experience with the development of turboprop I AIAA PAPER 87-2491 I p 42 A89-11 t 19 I DOT/FAA/CT-88/231 p 38 N89-10892 engines p 37 A89-11074 CLARK, HOWARD G. DENBOER, R. G. BUNDY, D. L. Multi-axis seat ejection (MASE) sled Unsteady low-speed wiedtunnel test of a straked delta Coping with legacy factors p 58 A89-12176 p 28 A89-10466 BURNS, DONALD W. wing, oscillating in pitch, Part 1: General description and COBB, CARLTON M. discussion of results Forced vibration and flutter design methodology Crrcuit protection for advanced aircraft - A functional p 51 N89-10016 lAD-At964561 p 18 N89-10867 and historical perspective BURROWS, B. J. C. DEPPE, PAUL ISAE PAPER 8725021 p 32 A89-10692 A filamentary method for calculating induced voltages Development and testing of an inflight engine COLLfNGE, KENNETH within resistive structures in either the frequency or time performance monitoring technique for the US Navy P-3C Texmas - An expert system for gas turbine engine domain p 52 N89-10484 airplane diagnosis and more BUSCH, W.-B. ISAE 8414621 p 34 A89-10615 ISAE 8717371 p 34 A89-10621 Influence of regeneration treatments on creep rupture DERZHAVINA, A. I. COLLINS, WILLIAM D. lives of turbine blades p 43 A89-11214 Suppression of unstable oscillations in a boundary The effects of fluids in the aircraft environment on a layer p 5 A89-10171 polyetherlmide p 44 A89-12759 DESAfNT-VICTOR, X. C COLLYER, D. R. Investigation on of the flow around a backward facing Fatigue testing of full-scale all-composite aircraft step with spanwlse blowing wings CAI, YUNJIN ICERT-RF*OA-68/2259-AYDI p 17 N89-I0859 I SAE PAPER 8724591 p 48 A89-10671 Application of end-bend blade for enhancing surge DESIPfO, RICHARD G. COPE, M. T. margin p 36 A89-11051 Over the rainbow Microstructural optimisation of tdamum alloys for defect CAMPBELL, E. A. F. ISAE PAPER 8724991 p 2 A89-10689 tolerance in gas turbine engine components Cost-effective slrapdown I N S design and the need for DICKEY, F. M. p 43 A89-10069 standard flight profiles p 30 A89-10128 Automated optical instrument for extrachng water droplet COSTES, J. J. CANNAVO, FRANCIS A., JR. impingement data from wind tunnel experiments Unsteady three-dimensional stall on a rectangular Circuit protection for advanced aircraft - A functional p 47 A89-10261 wing p 14 N89-10027 and historical perspective DICKMANNS, E. D. {SAE PAPER 8725021 p 32 A89-10692 COVERT, H. E. Automated landing approach using machine seeing Introduchon of the Hornet - A success story CARLSON, HARRY W. I DGLR PAPER 87-131 I p 23 A89-10522 I SAE PAPER 8724361 p 27 A89-10653 Vahdatlon of a pair of computer codes for estimation DICKS, L. R. CRANDALL, ROBERT L. and optimization of subsonic aerodynamic performance Electrostatic discharge and field effects of electronics E}iting the bullet on aviation safety p 3 A89-12537 of simple hinged-flap systems for thin swept wings systems p 52 N89-t0493 INASA-TP-28281 p 13 N89-10024 CRAWLEY, EDWARD F. DIEKMANN, A. Aeroelastic formulation for tuned and mlstuned rotors CARTA, FRANKLIN O. Application of winglets with inlegrated, adjusted p 37 N89-10013 AGARD manual on aeroelasticity in axial-flow trailing-edge flaps in a general aviation aircraft turbomachmes Volume 2: Structural dynamics and CREDELLE, THOMAS L. I DGLR PAPER 87-0801 p 26 A89-10516 aeroelashcity Avionic color liquid crystal displays - Recent trends DIPASQUALE, FRANK I AGARD-AG-298-VOL-21 p 13 N89-10008 ISAE PAPER 8717901 p 31 A89-10585 Field expenence with quantitative debris monitoring CRIEL, T. M. Aeroelastic coupling: An elementary approach I SAE 8717361 p 34 A89-10620 p 37 N89-10012 Sandia National Laboratories flight simulation facildleS DITTMAR, JAMES H. IDE88-0121081 p 42 N89-10898 CASASENT, DAVID Cruise noise of the 2/9 scale model SR-7A propeller CROKAERT, MICHEL Rule-based string code processor p 57 A89-11750 p 59 A89 12561 Modelhng of common mode coupling between an aircraft CAUGHEY, DAVID A. The effect of front-to-rear propeller spacing on the Diagonal implicit multigrid algorithm for the Euler wing traversed by a lightning current and wiring installed interaction noise at cruise conditiooe of a model in that wing p 22 N89-10485 equations p 9 A89-1 t 110 counterrotahon propeller having a reduced diameter aft CELl, ROBERTO CROUCH, KEITH E. propeller Imphcahons of a recent lightning strike to a NASA let Aeroelasticdy and structural optimization of helicopter I NASA-TM-1013291 p 60 N89-10603 trainer p 22 N89-10478 rotor blades with swept tips p 29 N89-10887 DOGGER, C. S. CRUSE, T. A. CELIK, Z. Z. Unsteady low-speed windtunnel test of a straked delta Convergence schemes for an adaptive-wall wind Advanced boundary element methods; Proceedings of wing. oscillating in pitch Part 1: General description and tunnel p 41 A89-12560 the IUTAM Symposium, San Antonio, TX, Apr 13-16, dISCUSSIOn of results CHADERJIAN, NEAL M. 1987 p 47 A89-10182 lAD-A1964581 p 18 N89-10867 CRUSE, THOMAS A. Navier-Stokes simulation of transonic wing flow fields DONAHUE, CYNTHIA C. Fracture mechanics; Proceedings of the Nineteenth using a zonal grid approach Development in helicopter tail boom strake applications INASA-TM-t000391 p 13 N89-10022 National Symposium, San Antonio, TX, June 30-July 2, m the US 1988 p 50 A89-11428 CHANG, CHUNJIANG I NASA-TM-f014961 p 40 N89-10059 CULLEN, MARK F. Bevel gear resonance failures in central gearing system DONG, JfNZHONG A hierarchical control strategy for 2-D object of an aeroenglne p 50 A89-11046 Two-dimensional subsonic diffuser flow with umform recogndlon p 57 A89-11760 CHARLESWORTH, J. M. CUNNINGHAM, A. M., JR. shear velocity profile at inlet p 7 A89-11056 Contamination of environmental control systems in Unsteady low-speed wlndlunnel test of a straked delta DOVI, AUGUSTINE R. Hercules aircraft wing, oscillating in pitch Part 1: General description and Multilevel decomposition approach to the preliminary IMRL-R-11161 p 29 N89 10040 discussion of results sizing of a transport aircraft wing p 25 A89-10109 CHEESEMAN, IAN fAD-A1964561 p 18 N89-10887 DOWLING, A. P. New concepts in helicopter machinery prognostics CURTISS, H. C., JR. Achve control of reheat buzz p 43 A89-11103 p 2 A89-12408 A study of helicopter stability and control including blade DOWNING, L. E. Implementation of knowledge-based systems for dynamics Ouadruplex digital flight control system assessment helicopter machinery fault prognosis p 2 A89-12412 I NASA-CR-1832451 p 40 N89-10895 I NASA-CR-182741 I p 40 N89-10058
B-2 PERSONAL AUTHOR INDEX GREIG, J. R.
DRAKE, KEITH FENG, JUN GEOIFFROY, P, TEAS - An AI based threat response recommendation A study of the fatigue behavior of small cracks m Aircraft crashes on the runway: Development of a super system nlckel-basa superalleys element for nenhnear analysis of a beam I SAE PAPER 871804 I p 57 A89-10589 I AD-A1954891 p 44 N89-10161 I REPT-87/561 p 54 N89-11286 DRELA, MARK FENG, XINHAI GEORGE, A. R. Low-Reynolds-number airfoil design for the MI.T An experimental investlgation on the bistable behawors ACOUStiCS Of transonic blade-vortex interactions Daedalus prototype - A case study p 12 A89-12559 of a flexible rotor-squeeze film damper system p59 A89-11101 DUBOIS, THOMAS A. p 49 A89-11028 GIELDA, T. P. FENSKE, W. PI - An AI approach tot maintenance and diagnostic Navier-Stokes solution to the flowfield over _ce accretfon Configuration optimizabon of commercial aircraft applications p 58 A89-12413 shapes p 12 A89-12557 DUPCAK, JOSEPH D. I DGLR PAPER 87-081 I p 26 A89-10517 FERRARA, AUGUSTO M. GIESSLER, F. a. Development and testing of an inflight engine Navier-Stokes solution to the flowfield over ice accrehon The performance of alternate fuels in general aviation performance monitonng technique for the US. Navy P-3C shapes p 12 A89-12557 airplane aircraft GILBERT, KENNETH E. ]SAE 841462] p 34 A89-10615 l DOT/FAA/CT-88/131 p 44 N89-10175 The electrical structure of thunderstorm anvils DURSTON, DONALD A. Alternate luels for General Aviation aircraft with spark ignition engines p 56 N89-10470 Wave drag and high-speed performance of supersonic I DOT/FAA/CT-88/051 p 44 N89-10179 GILMORE, JOHN STOVL fighter configuration FISHER, BRUCE D. Tactical route planning p 24 A89-12414 I NASA-TM-100061 I p 13 N89-10017 Implications of a recent lightning strike to a NASA jet GIVLER, RICHARD C. DURUP, P. C. trainer p 22 N89-10478 Continuum theones for fluld-parhcle flows: Some Wheel performance evaluation. Phase 1 : Analysis FISHER, F. ,ill aspects of lift forces and turbulence p 53 N89-11155 IDOT/FAA/CT-88/16] p 29 N89-10041 System protection from atmospheric electricity for GLADDEN, H. J. DZHAFAROV, MIKHAIL ABASKULIEVICH aerostats with conducting tethers p 52 N89-10497 Measurements of heat transler distribution over the Fire safety at civil a_rports p 19 A89-107t8 FLEETER, SANFORO surfaces of highly loaded turbine nozzle guide vanes Prediction of incidence effects on oscdfating airfod p 51 A89-12752 E aerodynamics by a locally analytical method GLENN, GREG p 12 A89-12135 Apphcation of constraint suspension techniques to FLEINER, JOACHIM diagnosis in helicopter cautton/warmng systems EASTERBROOK, CALVIN C. - fs 32 A split-Fowler glider problem presentation and p 32 A89-12411 Estlmahng electric field enhancement factors on an solutions GLEYZES, C. aircraft utilizing a small scale model: A method IDGLR PAPER 87-0821 p 26 A89-10518 Study of three dimensional boundary layers on the front evaluation p 21 N89-10454 FLYNN, J. M. of a fuselage and at an air _ntake EASTERBROOK, KEVIN Introduction of the Hornet - A success story I CERT-OA-22/5025-AYD I p 53 N89-11184 Eshmating electric field enhancement factors on an I SAE PAPER 8724361 p 27 A89-10653 GLOMB, W. L., JR. aircraft utdizing a small scale model: A method FORMAGGIA, LUCA Applicattons of time and wavelength dlwsion multiplexing evaluation p 21 N89-10454 Finite element Euler computations m three dimensions to digital optical code plates p 31 A89-10364 EBERL G. p 11 A89-12130 GLYNN, MICHAEL S. Automated landing approach using machine seeing FORNASIER, L. bghtnmg information database p 55 N89-10432 I DGLR PAPER 87-131 I p 23 A89-10522 HISSS - A higher-order panel method for subsonic and GOEBEL O. EDWARDS, JERRY L. supersonic attached flow about arbitrary configurations Shear wind measurements aboard a Piper PA 18 and A_R 1900 - Guide to temperature monitoring in aircraft p 10 A89-11484 the design of a model glider aircraft for dynamic gliding gas turbine engines FOSTER, JOHN D. flight I SAE 8717301 p34 A89-10616 Noise of the Harrier in vertical landing and takeoff I DGLR PAPER 87-135/1 I p 26 A89-10526 EISLER, G. RICHARD p 60 N89-10856 GOKOGLU, S. A. An approximate, maximum terminal velocity descent to FREEDMAN, MARVIN I. Deposition of Na2SO4 from salt-seeded combustion a point BEM for wave equation with boundary in arbitrary motion gases of a h*gh velocity burner ng p 43 A89-12330 I DE88-0003491 p 15 N89-10840 and applications to compressible potential aerodynamics GOLDHIRSH, JULIUS ELANGOVAN, R. of airplanes and helicopters p 5 A89-10192 Results of 1987 MSS helicopter propagation experiment Automated ophcal instrument for extractingwater droplet FREUND, G. A., JR. at UHF and L bancl in Central Maryland impingement data from wincl tunnel experiments Automated optical instrument for extracting water droplet p 53 N89-11077 GOLDMAN, LOUIS J. p 47 A89-10261 impingement data from wind tunnel experiments ENGLUND, DAVID R. p 47 A89-10261 Three component laser anemometer measurements m an annular cascade of core turbine vanes with contoured The dual element method of strain gauge temperature FREYMUTH, PETER end wall compensation p 51 A89-12276 Propulsive vortical signature of plunging and pitching tNASA-TP-2846f p 15 N89-10844 ERICSSON, TORSTEN airfoils p 9 A89-11115 GOPINATH, R. Swedish Symposium on Residual Stresses. Sunne, FRIEDEL TOM Tests on 3 NACA 0012 airfoit models of DFVLR m the Sweden, Mar. 30-Apt 2, 1987. Proceedings Tactical route planning p 24 A89-12414 NAL 0.3 tunnel: An assessment of 2-D wall interference p 46 A89-10096 FRIEDMAN, ROBERT ITM-AE-8705] p 15 N89-10847 ESHLEMAN, JAMES E. Fire behawor and risk analysis in spacecraft GORDER, PETER JAMES [ NASA-TM-100944 I p 42 N89-10111 Ground vortex flow field investigation Design and evaluation of a cockpit display for hovering p 16 N89-10852 FROST, KEITH L flight Image quality and wsual simulation of color matrix I NASA-CR-t 832471 p42 N89-10900 F displays GORDON, ELIOTT B, ISAE PAPER 8717891 p 57 A89-10584 The effect of front-to-rear propeller spacing on the FU, DEXUN interaction noise at cruise conditions of a model FADEEV, VITALII IAKOVLEVICH Numerical simulation of compact schemes irl counterrotation propeller having a reduced diameter aft Laser navigation equipment p 24 A89-10722 super-sonic viscous flows p 9 A89-11085 propeller FAN, JIECHUAN FUTATSUDERA, NAOKI I NASA*TM-1013291 p60 N89-10603 Investigation on wall interference of low-speed wind A numerical sqmulabon of separated flow around GOREE, J. G. tunnel with slotted walls p 8 A89-11081 two-dimensional wing by a discrete vortex method Fracture criteria for discontinuously reinforced metal FAN, SHIXIN p 6 A89-10568 matrix composites Two-dimensional subsonic diffuser flow with uniform I NASA-CR-1811751 p44 N89-10125 shear velocity profile at inlet p 7 A89-11056 GOTO, YUKIHIRO FANG, RENSONG G Statistics of lightning interaction with aircraft in Japan Reduction of ejector noise with mult_hole nozzle p 55 N89-10430 GOULD, DOUGLAS K. p 36 A89-11034 GAMBARANI, GARY P. Mission-Adaptive Wing FAROKHI, SAEED In-service evaluation oi the Traffic Alert and Collision I SAE PAPER 8724191 p 27 A89-10641 Method to optimize nacelle shape in a supersonic cruise Avoidance System (TCAS) industry prototype GRABARNIK, S. I. aircraft p 28 A89-12558 I DOT/FAA/SA-88/21 p 25 N89-10885 Heat transfer in the reclrculatlng region formed by a FEARS, SCOTT POWELL GAD, DEPING backward-facing step p 51 A89-12252 A dynambc characterlshc analysis of a bladed disk Investigation of the tumbling phenomenon using GRABERT, M. assembly p 36 A89-11026 computer slmulat_on p 41 N89-10896 Configuration optimization of commercial aircraft FECHER, J. GAD, HAD I DGLR PAPER 87-0811 p 26 A89-10517 Comparison of longitudinally stabilized behavior in The study of the global stabdity of high performance GRAHAM, L. W. aircraft at high angles-of-attack vertical turbulence between a modern canard configuration Simulation of a birdstrlke impact on aircraft canopy and a conventional aircraft I SAE PAPER 8724561 p 39 A89-10668 material p 25 A89-10113 I DGLR PAPER 87-0781 p 39 A89-10515 GARLAND, D. B. GREGOREK, GERALD M. FEDOROV, VALENTIN KONSTANTINOVICH Phase 4 static tests of the J-97 powered, external Transonic characteristics of a humped airfoil augmentor V/STOL model at the NASA. Ames Research Fire safety at clwt airports p 19 A89-10718 p 12 A89-12551 FEIK, R. A. Center, November 1983 GREIG, J. R. Non-hnear aerodynamic characteristics obtained from INASA-CR-1773951 p 14 N89-10028 Measurement of the electrostatic charging on large the analysis of flight-data GEERING, J. C. helicopters and control of the shock hazard IAR-004-571 I p 18 N89-10866 Design and teshng for airframes p 29 A89-12719 p 22 N89-10461
B-3 GROELLMANN, P. PERSONAL AUTHOR INDEX
GROELLMANN, P. HAVSTAD, MARK A. HORSTMANN, K. H. Packaged fiber optic gyros with h_gh bias stability Directional spectral emissivity measurements on a Investigations on high Reynolds number laminar flow p 46 A89-10121 ceramic mold material airfoils p 4 A89-10102 GROSS, G. J DE88-015407 j p44 N89-10167 HOWARD, RICHARD M. A numerical estimation of the deforestation effects on HAWKINS, B. B. Wing laminar boundary layer in the presence of a local climate in the area of the Frankfurt international Thick airfoil at low Reynolds number and high propeller slipstream p 4 A89-10105 airport p 55 A89-11554 incidence p 4 A89-10116 HOZUMf, KOKI GUERTS, E. G. HAYASHI, MASANORI Measurement of aerodynamic characteristics of a Unsteady low-speed windtunnel test of a stroked delta A numerical simulation of separated flow around hang-glider-wing by ground run tests using a test vehicle wing. oscillating in pitch Part 1 General description and two-dimensional wing by a discrete vortex method INAL-TR-9531 p 13 N89-10004 discussion of results p 6 A89-10868 HSU, C.-H. lAD-A1964561 p 18 N89-10867 Numerical experiments for separation flows around Numerical simulation of the vortical flow over a GUNES, D. trapezoidal cylinders by a discrete vortex method round-edged double-delta wing p 10 A89-11152 Aerodynamically-driven condensate layer thickness p 6 A89-10569 Incompressible Navier-Stokes computations for a distributions on isothermal cylindrical surfaces HE, ZHONGWEI round-edged double-deRa wing p 12 A89-12552 p 51 A89-12337 Dynamic distortion in flowfield downstream of transomc HU, HONG GUPTA, S. C. shock-boundary layer interaction p 8 A89-11061 Integral equation solution for transonic and subsonic aerodynamics p 11 A89-11488 GENMAP - Computer code for mission adaptive profile HEFFLEY, ROBERT K. generation p 12 A89-12566 Helicopter roll control effectiveness criteria program HU, ZONGAN summary Unsteady loading noise of counter-rotating propeller I NASA-CR-1774771 p39 N89-10046 p 36 A89-11054 H HEMSCH, MICHAEL J. HUANG, LlXf Engineering analysis of slender-body aerodynamics Approach to blade end-bend mechanism p 36 A89-11052 HAAG, K. using Sychev similanty parameters p 4 A89-10108 HUANG, XfJUN Approximation of free and bounded vortex sheets a{ HENDERSON, WILLIAM P. Two-dimensional subsonic diffuser flow with uniform delta-wings p 11 A89-11500 Propulsion-airframe integration for commercial and mihtary aircraft shear velocity profile at inlet p 7 A89-11056 HABERLANO, CH. I SAE PAPER 872411 { p 35 A89-10637 HUFF, JERRY W. Configuration optimlzahon of commercial aircraft HERITAGE, HUGH Image quality and visuat simulation of color matrix IDGLR PAPER 87-0811 p 26 A89-10517 An aircraft-borne electnc field measuring system for displays HAFER, ANDREAS rocket launch support p 55 N89-10443 ISAE PAPER 8717891 p 57 A89-10584 Aircraft dynamic stability - Developmental history HERRMANN, JAMES J. HUGHES, R. L. aspects A candidate for linear token-passing, high-speed data Schlieren measurements at the 10,000-foot sled track LOGLR PAPER 87-0571 p 1 A89-10538 bus systems I DE88-0127481 p 42 N89-10899 HAFER, XAVER I SAE PAPER 8724941 p 49 A89-10686 HULL, DAVID G. A)rcraft dynamJc stabfldy - Developmenta} history HERTH, J. An approximate, maximum terminal velocdy descent to aspects Packaged fiber optic gyros with high bias stability a point IOGLR PAPER 87-0571 p 1 A89-10538 p 48 A89-10121 IDE88-000349i p 15 N89-10840 HAGENAUER, JOACHIM HESS, JOHN L. HUSON, GREGORY G. Research on sateltite-lo-alrcraft signal communication Application of an advanced pane1 method to Transonic characteristics of a humped airfoil I OGLR PAPER 87-1331 p 23 A89 10524 aerodynamic problems of a*rcraft design p 12 A89-12551 HAIGH, S. J. p 28 A89-11486 HYLTON, L. D. A filamentary method for calculating induced voltages HESS, RONALD A. Measurements of heat transfer distnbution over the within reslsbve structures in either the frequency or time Design and evaluation of a cockpit display for hovering surfaces of h_ghly loaded turbine nozzle guide vanes domain p 52 N89-10484 flight p 51 A89-12752 HAJfBRAHIM, W. I NASA-CR-1832471 p 42 N89-10900 Investigation on of the flow around a backward facing HICKS, JAMES W., JR. J step with spanwise blowing Current military/government applications for speech ICERT.RF.OA-68/2259-AYD I p 17 N89-10859 recognition JACKSON, CHARLIE M., JR. HALLIDAY, R. ISAE PAPER 8717501 p 23 A89 t0580 HICKS, M. A. Unique research challenges for high-speed civil Pocket calculator trend monitoring for gas turbine transports Microstructural oplimisation of titanium alloys for defect engines ISAE PAPER 8724001 p I A89-10629 tolerance in gas turbine engine components {SAE 841461 { p 34 A89 10614 JACKSON, R. O. p 43 A89 10069 HAM, JOHNNIE A. Pocket calculator trend monitoring for gas turbine HICKS, RAYMOND M. Development el a rule-based demonstrabon prototype engines Transoolc characteristics of a humped airfoil expert system for mfhght emergencies for the UH1H I SAE 841461 I p 34 A89-10614 p 12 A89 12551 helicopter p 32 A89-12415 JACOB, TH. HIGGINS, CHARLES R. HAMDAN, A. M. A. Preconditions for GP.S. installation - Recewers m Aerospace technology - Windshear FAA: Boeing Modal observabitity and controllability measures for first differential operation for landing aircraft in general Wmdshear Training Aid program and second order hnear systems and model reduction aviation ISAE PAPER 872441 I p 19 A89-10655 I DGLR PAPER 87-1321 p 23 A89-10523 p57 A89-11680 HIGGINS, THOMAS H. HAMILTON, T. P. JACOBS, P. Terminal control area design and aLr traffic Ioadings Reasoning about device behavior using qualitative IDOT/FAA/DS-88111 I p 25 N89-10038 Shock tunnel studies of scramiet phenomena physics p 58 A89-12410 HIGLEY, S. E. INASA-CR 181721 i p 38 N89-10045 HAMLIN, DARYLE B. Fiber-optic sensor systems for aerospace applications JACOBSEN, C. A candidate for linear token-passing, high-speed data p 47 A89-10359 Reasoning about device behavior using qualitative bus systems HILL, R. A. physics p 58 A89-12410 I SAE PAPER 8724941 p 49 A89-10686 Schheren measurements at the lO,000-foot sled track JAKOB, H. HAN, MINGHUI I DE88-0127481 p42 N89-10899 The prediction of transonic *nterference hOW by means A circular cone surface shaping method for fan blade HINKLEY, E. S. of a hybnd method p 10 A89-11487 p 50 A89-11032 Windscreen design and testing p 29 A89-12720 JAKUBOWSKI, P. R. HANKEY, W. L. HJELMFELT, MARK R. System protection from atmospheric electricity for Navler-Stokes solution to the flowfleld over ice accretion Structure and _ife cycle of microburst outflows observed aerostafs with conducting tethers p 52 N89-10497 shapes p 12 A89-12557 m Colorado p 54 A89-11221 JAMBUNATHAN, V. HANNUM, NED P. He, CHIN-MING Control of autorotational charactenstlcs of hght-airp_ane Technology issues associated with lueling the national Control of separated flow on a symmetric airfoil fuselages p 39 A89-12555 p 47 A89-10181 aerospace plane with Slush hydrogen JEFFERS, JAMES D., Ill HOEIJMAKERS, H. W. M. I NASA-TM-1013881 p43 N89-10123 Aeroelastic thermal effects p 37 N89-10015 Panel methods in aerodynamics - Some highlights HARDWlCK, C. J. JENKINSON, LLOYD R. p 10 A89-11461 A filamentary method for calculating Induced voltages HOLLEY, CHARLES O. OpttmlzatJon el the conceptual design and mlss/on within resistive structures in either the frequency or time profiles of short-haul aircraft p 25 A89-10107 A tachcs expert System for scout/attack rotorcraft domain p 52 N89 10484 p 58 A89-12405 JERACKI, ROBERT J. HARDY, RICHARD HOLMES, B. J. The effect of front-to-rear propeller spacing on the Mtsslon-Adapbve Wing interaction noise at cruise conditions of a model Boundary-layer translhon effects on aLrplane stability and ISAE PAPER 8724191 p 27 A89-10641 Control p 39 A89-12556 counterrotatlon propeller hawng a reduced diameter aft HARRISON, J. R. HOLMES, BRUCE J. propeller Thick airfoil at low Reynolds number and h_gh Wing laminar boundary layer in the presence 01 a {NASA-TM-tOt329} pG0 N89-10603 incidence p 4 A89-10116 propeller slipstream p 4 A89-10105 JOFFE, ELYA B. HARTWICH, P.-M, HONG, JINSEN Israel Air Force OAF) m-service aircraft hghming stoke Incompressible Navler-Stokes computations for a Fhe vapor-screen technique of flow visualization in the and damage survey p 55 N89 10431 round-edged double-delta wing p 12 A89-12552 intermittent transonic and Supersonic wind tunnel JOHANSSON, THOMAS HARVEY, WILLIAM D. p9 A89-11083 Fatigue life influence of residual stresses from cold Boundary-layer control for drag reduction HOOPER, N. working and h_gh spectrum loads in aircraft structural [SAE PAPER 872434{ p 6 A89-I0651 Active conlrot of reheat buzz p 43 A89-11103 design p 46 A89-10099
B-4 PERSONAL AUTHOR INDEX MARGASON, RICHARD J.
JOHNSON, P. D. KOMODA, MASAKI LI, CHANGLIN Quahfleat_on and operational aspects of light weight Measurement of aerodynamic characteristics of a A design method of "wlgglestrap _ fl_m-coohng SKAD (light weight survival kit air droppable) hang-glider-wing by ground run tests using a test vehicle construction of flame tube p 50 A89-11039 p 18 A89-10471 INAL-TR-953L p 13 N89-10004 LI, QIHAN JOHNSON, RICHARD KOBN, JIM The bistable behavior of a rigid rotor with squeeze film Longitudinal lmpacl test of a transport airframe section Gas turbine engine developmenl partnerships damper p 49 A89-11029 I DOT/FAA/CT-87/261 p 54 N69-11265 } SAE PAPER 8724101 p 35 A89-10636 LIANG, SHICHANG JOHNSON, W. S. KOZEL KAREL Bevel gear resonance failures in central gearing system Numerical simulation of steady transonic flow past an Adhesively bonded ioints: Testing, analysis, and design; of an aeroengine p 50 A89-11046 8-percent DCA cascade at a freestream Mach number Proceedings of the leternational Symposium, BaltCmore, LIEPMANN, H. W. MD, Sept 10-12, 1966 p 45 A89-10076 of about 1 p 8 A89-11073 Turbulence management and retammansahon: JONES, J. J. KRIEGER, RAYMOND B., JR. Proceedings o1 the IUTAM SymposJum, Bangatore. India, Stress analysis concepts for adhesive bonding of aircraft A chronology of in-cloud electric field and lightning Jan. 19-23. 1987 p 46 A89-10154 strikes on an instrumented research aircraft primary structure p 45 A89-10093 KROGMANN, U. LIU, BO p 21 N89-10455 Apphcation of an artificial densdy scheme of potenhal JONES, ROBERT Integrated redundant reference systems for flight control stream function method to design of airfoil Correlation and analysis for SH-2F 101 rotor and nawgahon with skewed sensor arrangement p 7 A89-11053 p25 A89-10111 p 30 A89-10129 LIU, C. H. JUILLEN, J. C. KROTHAPALLI, A. Numerical simulation of the vortical flow over a Boundary layer transition Effects of a ground vortex on the aerodynamics of an ICERT-OA-40/5018-AYD[ p 53 N89-11187 airfoil p 16 N89-10855 round-edged double-delta wing p 10 A89-11152 KUBRYNSKI, KRZYSZTOF Incompressible Navier-Stokes computations for a A subsonic panel method for design of 3-dimensional round-edged double-della wing p 12 A89-12552 K complex configurations with specified pressure LIU, DAOZHI distnbufion p 28 A89-11491 Propfan design by propeller-nacelle mterachon KANDIL OSAMA A. KUHN, RICHARD E. analysis p 36 A89-11055 Unsteady transonic a_rfoll computation using implicit Ground vortex flow field Investigation LIU. SONGLING Euler scheme on body-fixed grid p 10 A89-11153 p 16 N89-10852 Calculation of compressible flew and heat transfer on Integral equation solution for transonic and subsonic KUMARI, SANTHA a rotating disk p 50 A89-11033 aerodynamics p 11 A89-11488 Tests on 3 NACA 0012 alrfoit models of DFVLR in the LONG, DAN KANE, ROBERT M. NAL 03 tunnel: An assessment of 2-D wall interference Tactical route planning p 24 A89-12414 Global poslhonmg system (GPS) receiver initialization ]TM-AE-87051 p 15 N89-10847 LONG, EDWARD R., JR. methods for MIL-STD-1760A KUPCIS, EDGARS A. The effects of fluids in the aircraft environment on a I SAE PAPER 872501 t p 42 A89-10691 Aerospace technology - Windshear FAA: Boeing polyetherimlde p 44 A89-12759 KARPEL M. Windshear Training Aid program LOZOVOI, NIKOLAI FILLIPOVICH Efficient vibration mode analysis of aircraft with multiple I SAE PAPER 872441 I p 19 A89-10655 Fire safety at cwil a_rports p 19 A89-10718 external store configurahons p 28 A69-12562 KURIAT, R. I. LU, QI KATZER, E. Effect of protective coatings on life of heat-resistant Finite element method for calculating transonic potenha{ Steady and unsteady potential flows around nickel steel under cyclic heat load p 45 N89-11005 flow around a_rfoil from pressure mlmmum integration axtsymmetric bodies and nng a_rfods p 11 A89-11489 KUSZMAUL CHRISTOPHER L. p 9 A89-11088 KAUL, H, J. A hierarchical control strategy for 2-D object LU, YAJUN Computing system configuration for fighter aircraft flight recognition p 57 A89-11760 A c_rcutar cone surface shaping method for fan blade control systems p 40 N89-10832 KUTLER, PAUL p 50 A89-11032 KAZA, KRISHNA HAD V. Computational fluid dynamics m aerospace LUDLOFF, ALBRECHT Vibration, performance, flutter and forced response I SAE PAPER 8724461 p 7 A89-10659 The operation of modern air-space surveillance radars characteristics of a large-scale propfan and its aeroelastic model p 51 A89-12151 L LUDVIGSON, M. T. I NASA-TM-101322] p 38 N89-10043 KEIL K.-H. On high-speed data bus performance analysis LANGHORNE, P. J. I SAE PAPER 8724961 p 49 A89-10687 Navigation of aircraft with rigid image-forming sensors Token rotation timer implementalion I DGLR PAPER 87-1301 p 31 A89-10521 Active control of reheat buzz p 43 A89-11103 KELLEY, HENRY L LAPPOS, NICK I SAE PAPER 872497 I p 49 A89-10688 The NOE pilot's associate - A job descnphon LUEERS, H. Development m helicopter tad boom strake apphcations in the US p 39 A89-12402 Computing system configuration for fighter aircraft flight control systems p 40 N89-10832 I NASA-TM-1014961 p 40 N89-10059 LAROCHE, P. LUTSENKO, VLADIMIR IVANOVICH KELSO, A. G. The SAFIR Jightning rnomtoring and warning system, applications to aerospace activities p 52 N89-10481 Fire safety at cwil airports p 19 A89-10718 Contamination of environmental control systems m LUX, DAVID P. Hercules aircraft LARSON, W. E. Hardware fau_t insertion and instrumentation system: X-29A forward-swept-wing flight research program IMRL-R-11161 p 29 N89-10040 status KEMMERLY, GUY T. Expenmentation and results I NASA-CR- 1827461 p 58 N89-10526 t SAE PAPER 8724181 p 27 A89-10640 An assessment of ground effects determined by stahc LYRINTZIS, A. S. and dynamic teshng techniques p 16 N89-10854 LARSSON, SVEN-ERIK KEMMLER, M. Fahgue life influence of residual stresses from cold ACOUStics of transonic blade-vortex interactions p59 A89-11101 Packaged fiber optic gyros with high b_as stability working and high spectrum loads in aLrcraft structural LYRINTZIS, CONSTANTINOS SOTIRIOS p 46 A89-10121 design p 46 A89-10099 Response of discretely stiffened structures and KEMPF, K. LAST, S. R. transmission of structure-borne noise Packaged fiber optic gyros with high bias stability Should technology assist or replace the pilot? p 46 A89-10121 I SAE PAPER 8807741 p 57 A89-10593 p 54 N89-11270 KIMURA, HARUO LAUGHREY, J. A. Analytical and expenmental research on aerodynamical Evolution of the STOL and Maneuver Technology M effects of wind shear on aircrafl p 6 A89-10547 Demonstrator KLEIN, G. W. A. tSAE PAPER 872417l p 27 A89-10639 MA, YANWEN The history of aircraft onboard equipment LECONG, P. Numerical simulation of compact schemes in t DGLR PAPER 87-0541 p 31 A89-10536 Fiber-optic sensor systems for aerospace applications super-sonic viscous flows p 9 A89-11085 KNOX, DON p 47 A89-10359 MABY, RICHARD K. The Australian Aviation Satellite System LEE, CHI M. A hybrid knowledge-based approach to AH-64A fault I SAE PAPER 8724201 p 24 A89-10642 Regressed relations for forced convection heat transfer isolation p 2 A89-12409 KOBAYASHI, HIROSHI m a direct injection stratified charge rotary engine MACKENROTH, U. Numerical approach of advanced turboprop with i SAE PAPER 8806261 p 51 A69-12308 Navigation of aircraft with rigid image-forming sensors three-dimensional Euler equahons LEE, MARIO iDGLR PAPER 87-1301 p 31 A89-10521 I SAE PAPER 8724481 p 7 A89-10661 MAIOROV, ANATOLII VLADIMIROVICH KOESTER, H. Control of separated flow on a symmetric airfoil p 47 A89-10181 Operating safety of automatic obiects Inveshgahons on h_gh Reynolds number laminar flow p 49 A89-10714 LEISHMAN, J. G. airfoils p 4 A89-10102 MALASHENKO, I. S. Two-dimensional model for airtol_ unsteady drag below Improvement of a design code for airfoils at transonic Effect of protective coatings on life of heat-resistant stall p 4 A89-10114 regime n_ckel steel under cyclic heat load • p 45 N89-11005 LEISSLER, GEORGE W. I DGLR PAPER 87-064 I p 5 A89-10511 MANEVICZ, JOSEPH E. KOHAMA, Y. T55-L-712 turbine engine compressor housing An aircraft-borne electric field measunng system for refurbishment-plasma spray prolect Three-dimensional boundary layer transition on a rocket launch support p 55 N89-10443 concave-convex curved wall p 4 A89-10167 I NASA-TM-1013101 p44 N89-10156 MANGOLD, P. KOHL, F. J. LENOROVITZ, JEFFREY M. Aspects of the control and stabilization of supersomc Deposition of Na2SO4 from salt-seeded combushon MiG-29 design merges old, new technologies commercLal aircraft gases o1 a high velocity burner ng p 43 A89_12330 p 28 A89-11559 I DGLR PAPER 87-1221 p 39 A89-10519 KOMERATH, N. M. LEOPOLD, D. MARGASON, RICHARD J. Laser sheet techmque for visualizing a periodic rotor Effects of a ground vortex on the aerodynamics of an The 1987 Ground Vortex Workshop wake p 41 A89-10115 airfoil p 16 N89-10855 INASA-CP-100081 p 15 N89-10849
B-5 PERSONAL AUTHOR INDEX MARKSON, RALPH
MARKSON, RALPH MIROW, P. MURPHY, D. P. New electric field instrumentation and the effects of Transition recognition in aircraft wing profiles with the Measurement of the electrostatic charging on large space charge at Kennedy Space Center aid of piezoelectric sheetings helicopters and control of the shock hazard p 22 N89-10461 p 55 N89-10444 I DGLR PAPER 87-0651 p 47 A89-10512 MARSHALL, THOMAS C. MITCHELL, GLENN A. The electrical structure of thunderstorm anvils Experimental aerodynamic performance of advanced 40 N p 56 N89-10470 deg-swept 10-blade propeller model at Mach 0.6 to 085 INASA-TM-889691 p 17 N89-10865 MARTIN, J. M. NAGAR, ARVIND Introduction of the Hornet - A success story MNICH, MARC A. Fatigue crack growth in aircraft main landing gear I SAE PAPER 8724361 p 27 A89-10653 Helicopter roll control effectiveness criteria program wheels p 28 A89q 1447 MARVIN, J. G. summary NAKAMURA, KINUYO A new PNS code for chemical nonequdlbnum flows I NASA-CR-1774771 p39 N89-10046 Programming techniques for high-speed processing on p9 A89q 1106 MOENKE, H. the supercomputer FUJITSU VP-system MATSUO, YUICHI The nonrigid airship of the Siemens-Schuckert Works I NAL-TR-9151 p58 N89-10565 Numerical approach of advanced turboprop with I DGLR PAPER 87-0551 p 60 A89-10537 NAKAMURA, MASAYOSHI three-d_mensional Euler equations MOLINARI, GUY V. A numerical solution of transonic flow using ISAE PAPER 8724481 p 7 A89-10661 Up in the air on air traffic control p 3 A89-12538 discontinuous shock relation p 6 A89-10542 MAVRIPLIS, O. J. MONGE, F. NARASIMHA, R. Multigrid solution of the two-dimensional Euler equations Improvement of a design code for airfoils at transonic Turbulence management and relaminarisation: on unstructured triangular meshes p 9 A89-11108 Proceedings of the IUTAM Symposium, Bangalore, India, MAZUR, MLADISLAV regime IDGLR PAPER 87-0641 p 5 A89-10511 Jan. 19-23, 1987 p46 A89-10154 Lightning initiation on aircraft in thunderstorms NAMERT, UNO G. p 21 N89-10456 MONTY, ROBERT W. Transonic computations about complex configurations MCDOWALL R. L. Image quahty and visual simulation of color matrix using coupled inner and outer flow equations Lightning information database p 55 N89-10432 displays p 12 A89-12553 MCGHEE, ROBERT J. ISAE PAPER 8717891 p 57 A89-10584 NAYFEH, A. H. MOORE, C. B. Experimental results for the Epp_er 387 airfoil at low Modal observability and controllability measures for first Electnfication of hovering helicopters Reynolds numbers in the Langley low-turbulence pressure and second order linear systems and model reduction p 22 N89-10460 tLmnel p 57 A89-11680 INASA TM-40621 p 15 N89-10842 MOORE, G. C. NAZlH-ANOUS, N. MCLEAN, WILLIAM Turbofan forced mixer lobe flow modehng Part 3: Aerodynamically-driven condensate tayer thickness Directional spectral emissivity measurements on a ApplicaPon to augment engines distributions on isothermal cylindrical surfaces ceramic mold material INASA-CR-41471 p 14 N89-10025 p 51 A89-12337 MOREAU, J. P. i DE88-015407 I p44 N89-10167 NEALY, D. A. MCMAHON, H. M. Summary of inflight data on lightning currents and Measurements of heat transfer distribution over the Laser sheet technique for visualizing a periodic rotor fields p 56 N89-10449 surfaces of highly loaded turbine nozzle guide vanes wake p 41 A89-10115 Analysis of recent in-flight lightning measurements on p 51 A89-12752 different aircraft p 20 N89-10450 MCMILLAN, B. K. NELEPOVITZ, D. O. Some stabstical aspects of attrition studies MORGAN, D. REED De-icing of aircrag turbine engine inlets tAD-A1966651 p 30 N89 10891 High speed paralle_ processing networks for advanced I DOT/FAA/CT-87/37 I p 38 N89-10894 MCPHEE, J. R. architectures p 59 N89-10837 NELLES, H. Electrical noise reduction techniques conlributmg to MORGAN, KEN The 'Pneumahc Wind Shear Sensor' (PWSS) - An aid Finite element Euler computations in three dimensions improved data quality at the Natlonat Transon*c Faclhty to flight path regulation and to disturbance magnitude INASA-CR*41931 p 54 N89-11196 p 11 A89-12130 identification in shear wind situations MCTIGUE, DAVID F. MORGAN, R. G. I DGLR PAPER 87-1341 p31 A89-10525 Continuum theories for fluid-particle flows: Some Shock tunnel studies of scramiet phenomena NELSON, JAMES H. aspects of lift forces and turbulence p 53 N89 11155 I NASA-CR-181721 I p 38 N89-10045 A candidate for linear token-passing, high-speed data MCVEA, G. G. MORIN, G. bus systems Contamination of environmental control systems in Electrostabc dLscharge and field effects of electronics I SAE PAPER 872494 I p 49 A89-10686 Hercules aircraft systems p 52 N89-10493 NEUL, ANDREAS IMRL-R-11161 p29 N89-10040 MERINO, LUIGI Research on satefllte-to-alrcraft signal commuelcatlon MEITIN, JOSE G., JR. BEM for wave equation with boundary in arbitrary motion I DGLR PAPER 87-1331 p 23 A89-10524 Oklahoma-Kansas prehmlnary regional experiment for and applications to compressible potential aerodynamics NEUMANN, G. storm-central (O-K pre-storm) Volume 3: Aircraft mlsston of airplanes and helicopters p 5 A89-10192 Packaged fiber optic gyros with high bias stabdlly summary MORRIS, E. K., JR. p46 A89-10121 I PB88-2054891 p 56 N89 10499 Unique research challenges for high-speed civil NG, POH H. METZGER, F. B. transports Linear and nonlinear interpretahon of CV-580 hghtnmg Results of acoushc tests of a prop-fan model I SAE PAPER 8724001 p 1 A89-10629 data p 21 N89-10451 p59 A89-10112 MORRIS, N. NGUYEN, LUAT T. MEW, JOHN F. Shock tunnel studies of scramlet phenomena Experimental study o1 effects o1 forebody geometry on A Canadian government look at airworthiness INASA-CR-1817211 p 38 N89-10045 high angle-of-attack stability p 38 A89 10103 I SAE PAPER 8809351 p 2 A89-12319 MORRISON, J. S. NOHISA, TORU MICHAEL, MARK T. Introduction of the Hornet A success story An experimental study on aerodynamic performance of Data and signal processing archdecfures for luture ISAE PAPER 8724361 p 27 A89-10653 Lippisch-type GEW p 6 A89-10544 avionics p 33 N89-10835 MOSES, LEON N. MICHAL, R. J. Air safety in the age of deregulation NOTTEBAUM, THORSTEN Fiber optic sensor systems for aerospace applications p 19 A89-12539 Computer program for simulating dynamic gliding fhght p 47 A89-10359 MOSKATOV, GENRIKH KARLOVICH I DGLR PAPER 87-135/21 p 27 A89-10527 MICHELSON, ROBERT C. Operating safety of automahc obiects NOZAKI, OSAMU Digital autopilots for rotary winged unmanned aenal p 49 A89-10714 Cascade ltow analysts by Navier-Stokes equation vehicles p 39 A89-12417 MUELLER, T. J. p 52 N89-11065 MIGNEAULT, GERARD E. Boundary-layer measurements on an a_rfoll at low NUNZIATO, JACE W. On the diagnostic emulation technique and its use m Reynolds numbers p 4 A89-10106 Continuum theones for fluid-particle flows: Some the AIRLAB MUENIER, MICHEL aspects of hft forces and turbulence p 53 N89-11155 INASA-TM-40271 p 58 N89-10524 A highly reliable computer for airborne applications MIHELC, M. S. p 59 N89-10833 Measurements of heat transfer distribuhon over the MULCARE, D. B. O surfaces of highly loaded turbine nozzle guide vanes Quadruplex digital fhght control system assessment
p 51 A89-12752 I NASA-CR-182741 I p 40 N89-10058 OAKE, P. Hardware fault insertion and mstrumentahon system MILESHKIN, N. Bird hazards m awatlon - Safety and econom0c Fatigue testing of full-scale all-composite a_rcraft Experimentation and results tmphcatlons for an airhne p 20 A89-12721 I NASA-CR-1827461 p 58 N89-10526 wings OBRIEN, T. K. ISAE PAPER 8724591 p 48 A89-10671 MULDER, J. A. Tension lahgue analysis and life pro, diction for composite MILEY, STAN J. Design and evaluahon of dynamic fhght test laminates Wing laminar boundary layer in the presence of a manoeuveres I NASA TM.1005491 p 44 N89-10951 propeller shpstream p 4 A89.10105 I PB88-2107601 p29 N89.10042 OHMORI, SHINED MILLARD, BETTY F. MULHAUSER, CHARLES ETS-V propagahon experiments in Japan Experimental results for the Eppler 387 airfoil at low Modern techniques for the control of RPV's p53 N89-11080 Reynolds numbers in the Langley low-turbulence pressure I SAE PAPER 8724571 p 39 A89 10669 OKAMOTO, SHIKI tunnel MULLER, R. C. Flow past circular cylinder of finite _ength placed on INASA-TM-40621 p 15 N89-10842 Prototype data acqulsdlon and analysis system for Navy MILLETT, BRIAN P. operattonal lhght stmulators ground plane p 48 A89-10543 A hybnd knowledge-based approach to AH 64A fault I DE88-014557f p 42 N89-10901 ONe, TAKATSUGU isolation p 2 A89 12409 MUROOKA, YOSHIHIRO Measurement of aerodynamic characteristics of a
MINAEV, EVGENII ROMANOVICH Statisbcs of lightning interaction with aircraft in Japan hang-ghder-wing by ground run tests using a test vehicle INAL-TR-9531 p 13 N89_10004 Fundamentals of flight safety p 19 A89-10721 p 55 N89-10430
B-6 PERSONAL AUTHOR INDEX ROSEN, CECIL C., IU
ORVILLE. R. E. PETERS, JAMES M. R Intracloud lightning as a precursor to thunderstorm Advanced crew escape capsule technologies program microbursts p 56 N89-10490 p 18 A89-10475 RABINOVICH, A. A. OSTGAARD, JOHN C. PETER.SON, ROBERT W. Effect of protective coatings on life of heat-resistant Advanced avionics architecture pave pillar Circuit protection for advanced mrcraff - A functional nickel steel under cychc heat load p 45 N89-11005 p 33 N89-10834 and historical perspective RACK, H. J. OTAGIRI, FUMIHARU I SAE PAPER 8725021 p 32 A89-10692 Fracture criteria for discontinuously reinforced metal An experimental study on aerodynamic performance of PE'FI'tGREW, JAMES L matrix composites INASA-CR-1811751 p 44 N89-10125 Lippisch-type GEW p 6 A89-10544 Gas turbine engine monitoring systems - Helicopter RAETZER-SCHEIBE, H. -J. experience I SAE 8717351 p 34 A89-10619 The high temperature oxidation behavior of the single crystal Hi-base alloy M002 rood with and wfthout protective P PHATAK, ANIL V. coatings p 43 A89-11216 Simulation and analysLs of image-based navigation RAGHUNATHAN, S. PAGE, RICHARD system for rotorcraft Iow-alhtude flight Thick airfoil at low Reynolds number and high SurveBlance - High-technology tit-out for the Nomad p 32 A89-12403 _ncidence p 4 A89-101t6 aircraft PHILLIPS, JOHN D. RAHMAN, A. I SAE PAPER 8724281 p 32 A89-10647 The V-22 vibration, structural life, and engine diagnostic Control of autorotational characteristics Ot light-airplane system, VSLED PAGE, RICHARD D. luselages p 39 A89-12555 Evaluation of enhancements to the Low Level Wind I SAE 871732i p 31 A89-10617 RAMAKIS, RAYMOND E. 5:; Shear Alert System (LLWAS) at Stapleton International PHILLIPS, W. D. Maintenance and airline safety The electrochemical erosion of servo valves by AirpOrt I SAE PAPER 8724431 p 19 A89-10656 I DOT/FAA/PS-88/141 p 56 N89-11356 phosphate ester fire-resistant hydraulic fluids RAMSEY, TIMOTHY S. p 48 A89-10573 PAGET, CLIVE A hierarchical control strategy for 2-D obiect Health and usage monitoring - The integrated PICKEREL D. J. recOgnition p 57 A89-11760 approach RB211 developments RATNAPARKHI, P. t SAE PAPER 8724451 p 32 A89-10658 I SAE PAPER 8724091 p 35 A89-10635 Fracture Criteria for discontinuously reinforced metal PAILHAS, GUY PIPE, KENNETH matrix composites Experimental investigation ot flow near a corner, part New concepts in helicopter machinery prognoshcs I NASA-CR-1811751 p44 N89-10125 2 p 2 A89-12408 RAUCH, J. rCERT-RT-OA-24/5025-AYDI p 17 N89-10861 Implementation of knowledge-based systems for Computing system configuration for fighter aircraft flight Three dimensional shear flow Analysis of the flow in helicopter machinery fault prognosis p 2 A89-12412 control systems p 40 N89-10832 a delta arrow wing with incidence angle PITRONE, LARRY R. RAY, EDWARD J. ICERT*RTS-OA-25/5025-AYDI p 17 N89-10864 Environmental durability of adhesively bonded ioints Highlights of experience with a flexible walled test PALYS, MAREK p 46 A89-10095 section in the NASA Langley 0 3-meter transonic cryogenic tunnel Laser control of visibility and cloud*base height in airfield PLATZER, MAX F. regions p 50 A89-11860 AGARD manual on aeroelasticity in axial-flow I NASA-TM-101491 I p 41 N89-10060 PAMADI, B. N. turbomachines. Volume 2: Structural dynamics and RAY, H. Composites in shock and vibration isolation Control of autorotatlonal characteristics of light-airplane aeroelasticity p 50 A89-11251 fuselages p 39 A89-12555 [AGARD-AG*298-VOL-21 p 13 N89-10006 REAZER, J. M. PAPADAKIS, M. PODGORSKI, ANDREW S. Summary of infhght data on lightning currents and Automated optical instrument for extracting water droplet A case for a unified lightning threat fields p 56 N89-10449 impingement data from wind tunnel experiments p 56 N89-10447 REDEKER, G. p 47 A89-10261 POLANSKY, G. F. Investigations on h_gh Reynolds number laminar flow PAULL, A. Aerodynamic design and performance of a bent-axis a_rfoils p 4 A89-10102 Shock tunnel studies of scramlet phenomena geometry vehicle REICHENAU, DAVID E. A. t NASA-CR-181721 I p 38 N89-10045 LAIAA PAPER 87-2491 I p 42 A89-11119 Aerodynamic characteristics of the ACES-II ejection seat PAULSON, JOHN W., JR. POPE, G. G. at transonic Mach numbers p 25 A89-10463 An assessment Of ground effects determined by static Aerospace systems and technology: The role of the BEN, PINGZHEN and dynamic testing techniques p 16 N89-10854 RAE Steady_state unbalance responses for a multispan PEARCE, JEFFREY ALAN tRAE-TR-880421 p 3 N89-10003 rotor p 50 A89-11066 A computational study Of coherent structures in the POSTANS, P. a. RICHARD, P. wakes of two-dimensional bluff bodies Microstructural optrmisation of titanium alloys for defect The SAFIR lightning monitonng and warning system, ] AD-A1968201 p53 N89-11188 tolerance in gas turbine engine components applications to aerospace actwities p 52 N89-10481 PECHACEK, R. E. p 43 A89-10069 RICHARDS, CLYDE N. Measurement of the electrostatic charging on large POUWELS, H. Electrlhcatlon of hovenng helicopters helicopters and control of the shock hazard Digital recording of radar data in an aircraft p 22 N89-10460 RICHARDSON, WILLIAM p 22 N89-10461 I P888-209507 t p51 N89-10212 PEICHL L Tornado - The first eight years p 2 A89-11450 POWER, G. D. RICHTER, H. The high temperature oxidation behavior of the single Analysis of complex hypersomc flows with strong Aspects of increasing economy using future low-power crystal Hi-base alloy M002 rood. with and without protective wecous/inviscid interaction p 9 A89-11109 coatings p 43 A89-11216 aircraft propulsion systems PEIRO, JOAOUIN PRABHU, D. K. I DGLR PAPER 87-1001 p 33 A89-10528 A new PNS code for chemical nonequilibnum flows RIECHE, ALEXANDER Finite element Euler computahons in three dimensions p9 A89-11106 p 11 A89-12130 The assurance of flight safety - A priority task in CWd PELANT, JAROSLAV PRESSPRICH, JOHN w. aviation p 20 A89-12548 A second-order numerical method for the analysis of UT1760A RTS - A low-cost monolithic remote terminal RIECKE, OLAF two-dimensional flow of ideal fluid through a cascade with stores interface for MIL-STD-1760A Air-traffic flow management today p 24 A89-12152 supersonic input p 6 A89-10607 ]SAE PAPER 872481 I p 48 A89-10677 RIGAMONTI, M. Tension fatigue analysis and life prediction for composite PELLOUX, REGIS M. PREVA'rr, RICH laminates A study of the fatigue behavior of small cracks in DeveLopment and teshng of an mfhght engine I NASA-TM-1005491 p 44 N89-10951 nickel-base superalloys performance monitoring technique for the U.S. Navy P-3C RIGDEN, GREGORY J. I AD-A1954891 p44 N89-10161 airplane Interference of precipitation stahc discharges with PENG, SHIYI I SAE 8414621 p 34 A89-10615 A jet thrust measurement method with gas composlhon a_reraft navigational systems p 21 N89-10459 PUTILIN, S. I. RIZZETTA, DONALD P. analysis p 36 A89-11040 A study of the accuracy of wing calculations based on PENG, ZEYAN Numerical simulation of supersonic flow over a different schemes p 49 A89-10774 three-dimensional cavity p 9 A89-11105 Approach to blade end-bend mechanism ROBERTSON, IAIN p 36 A89-11052 Health and usage monitoring - The integrated PERAIRE, JAIME Q Finite element Euler computahons in three dimensions approach I SAE PAPER 872445 t p 32 A89-10658 p 11 A89-12130 ROCKHOLT, H. M. PERALA, RODNEY A. QIAN, LUHONG Tnggermg of lightning by the Atlas Centaur vehicle Application of end-bend blade for enhancing surge De-icing of aircraft turbine engine inlets I DOT/FAA/CT -87/371 p 38 N89-10894 p 55 N89-10438 margin p 36 A89-11051 ROGANOV, P. S. Linear and nonlinear interpretahon of CV-580 hghmmg QIAO, WEIYANG Heat transfer in the reclrculating region formed by a data p 21 N89-10451 Experimental study of rotahng stall in single-stage axial PERSOON, A. J. backward-facing step p 51 A89-12252 compressor p 8 A89-11059 ROMANOSKI, GLENN Unsteady low-speed wmdtunnel test of a straked delta elU, PING A study of the fatigue behavior of small cracks In wing. oscdlahng in pitch Part 1: General description and discussion of results An investigation of the pressure _n an ejection seat bay nickel-base superalloys tAD-A1964561 p 18 N89-10867 due to rocket jet p 26 A89-10482 lAD-At954891 p 44 N89-10161 PETERS, DAVID A. QUAST, A. ROSEN, CECIL C., III Numerical solutions of induced velocities by semHnfinlte Inveshgations on high Reynolds number laminar flow The winning edge tip vortex lines p 12 A89-12554 airfoils p 4 A89-10102 I SAE PAPER 8809451 p 2 A89-12322
B-7 ROSEN, JONAS W. PERSONAL AUTHOR INDEX
ROSEN, JONAS W. SAUL, GREGORY W. SHIH, TOM I.-P. Finite difference analysis of external and internal Pi - An AI approach for maintenance and diagnostic Calculations of the unsteady, three-dimensional flow lightning response of the JAS39 CFC wing applications p 58 A89-12413 field inside a motored Wankel engine p 22 N89-10483 SAULL, J. W. I SAE PAPER 880625 t p 37 A89-12307 ROSENBURG, BRUCE L European airworthiness control for the 1990s SHIJIAN, FU Evaluation of enhancements to the Low Level Wind I SAE PAPER 8809361 p 2 A89-12320 A study on effects of aircraft noise environment on its Shear Alert System (LLWAS) at Stapleton International SAVAGE, IAN structure Airport Air safety in the age of deregulation I SAE PAPER 8724501 p 28 A89-10663 I DOT/FAA/PS-88/141 p 56 N89-11356 p 19 A89-12539 SHIO, CHENGSHU ROSENHOOVER, F. ALLAN SAVCHENKO, V. T. Two-dimensional subsonic diffuser flow with uniform AFTI/F-16 voice interactive avionics evaluation A study of the accuracy of wing calculations based on shear velocity profile at inlet p 7 A89-11056 I SAE PAPER 8717511 p 24 A89-10581 different schemes p 49 A89-10774 SHISHOV, E. V. ROSENTHAL, H. A. SAVILL, A. M. Heat transfer in the recirculating region formed by a De-icing of aircraft turbine engine inlets Turbulent boundary layer manipulation and modelling backward-facing step p 51 A89-12252 IDOT/FAA/CT-87/371 p 38 N89-10894 in zero and adverse pressure gradients SILVERSTEIN, LOUIS D. ROSNER, O. A. p 46 A89-10159 Image quality and visual simulation of color matrix Deposition of Na2SO4 from salt-seeded combustion SCHIPPERS, H. displays gases of a high velocity burner rig p 43 A89-12330 On the evaluation of aerodynamic influence ISAE PAPER 8717891 p 57 A89-10584 ROSNER, O. E. coefficients p 11 A89-11496 SIMOS, DIMITRI Aerodynamically-driven condensate layer thickness SCHMIDT, R. Optimization of the conceptual design and mission distributions on isothermal cylindrical surfaces Navigation of aircraft with rigid image-forming sensors profiles of short-haul aircraft p 25 A89-10107 p 51 A89-12337 I DGLR PAPER 87-1301 p31 A89-10521 SMITH, M. K. ROSS, JAMES C. SCHOCK, HAROLD J. Quadruplex digital flight control system assessment Inlet development for the NFAC 80- by 120 foot indraft Regressed relations for forced convection heat transfer I NASA-CR-182741 I p 40 N89-10056 wind tunnel in a direct injection stratified charge rotary engine SMYTH, SAMUEL J. IAIAA PAPER 88-25281 p 41 A89-12550 tSAE PAPER 8806261 p 51 A89-12308 From Kitty Hawk to the year 2000 ROTHSTEIN, STEVE SCHOCK, HAROLD J., JR. ISAE PAPER 872395i p 1 A89-10628 TEAS - An AI based threat response recommendation Calculations of the unsteady, three-dimensional flow SMYTHE, GLENN R. system field inside a motored Wankel engine Evaluation of enhancements to the Low Level Wind I SAE PAPER 8718041 p 57 A89-10589 I SAE PAPER 8806251 p 37 A89 12307 Shear Alert System (LLWAS) at Stapleton International ROWLEY, J. D. SCHOENE, J. Airport HOTEL Command and Control Systems A doublet point method for the calculation of unsteady I DOT/FAA/PS-88/14 I p 56 N89-t 1356 I SAE PAPER 8809291 p 42 A89-12317 propeller aerodynamics p 11 A89-11497 SNYDER, LYNN E. RUDOLPH, TERENCE SCHOFF, KENNETH Forced vibration and flutter design methodology Estimating electric field enhancement factors on an Texmas - An expert system for gas turbine engine p 51 N89-10016 aircraft utilizing a small scale model: A method diagnosis and more SOBIECZKY, H. evaluation p 21 N89-10454 I SAE 8717371 p34 A89-10621 Analysis of transonic wings including viscous RUDOLPH, TERENCE H. SCHREIBER, R. A. interaction p 9 A89-11084 Triggering of hghtning by the Atlas Centaur vehicle Experimental investigation of the performance of a SODERMAN, PAUL T. p 55 N89-10438 supersonic compressor cascade Noise Of the Harrier in vertical landing and takeoff Linear and nonlinear interpretation of CV-580 lightning tNASA-TM-f008791 p 16 N89-10858 p 60 N89-10856 data p 21 N89-I0451 SCHWARTEN, H. SONG, ZHAOHONG RUST, W. DAVID An inverse, subsonic two-dimensional panel method A data acquisition system for blade vibration test The electrical structure of thunderstorm anvils following the method of smallest quadrate for the design p41 A69-11037 p 56 N89-10470 and modification of multiple element profiles SOQUES, MARTIN P. RUSTAN, P. L. I DGLR PAPER 87-061 I p 5 A89-10509 UT1760A FiTS - A low-cost monolithic remote terminal stores interface for M IL-STD-1760A Summary of inflight data on lightning currents and SCOTT, DAVIN R. fields p 56 N89-10449 Aeroelashcity past, present and future t SAE PAPER 872481 I p 48 A89-10677 SOULAGE, A. Analysts of recent tn-fhght lightning measurements on ISAE PAPER 8724491 p 19 A89-10662 different aircraft p 20 N89-10450 SCOTT, J. N. The SAFIR lightning monitoring and warning system, Navler-Stokes solution to the flowfield over ice accretion applications to aerospace activities p 52 N89-10481 RUTLEDGE, CHARLES K. shapes p 12 A89-12557 SRIDHAR, BANAVAR On the appropriateness of applying chi-square SCOTT, M. L. Simulation and analysis of image-based navigation distribution based confidence intervals to spectral Fatigue testing of full-scale all-composite aircraft system for rotorcraft low-altitude flight estimates of helicopter flyover data wings p 32 A89-12403 I NASA-CFI-1816921 p 59 N89-10601 I SAE PAPER 8724591 p 48 A89-10671 SRIDHARAN, R. RUTLEDGE, W. H. SEASHOLTZ, RICHARD G. Tests on 3 NACA 0012 airfoil models of DFVLR in the Aerodynamic design and performance of a bent axis Three component laser anemometer measurements in NAL 03 tunnel: An assessment of 2-D wall interference geometry vehicle an annular cascade of core turbine vanes with contoured ITM-AE-87051 p 15 N89-10847 IAIAA PAPER 87-24911 p 42 A89-11119 end wall STALKER, R. J. RYAN, W. M. INASA-TP-28461 p 15 N89-10844 Shock tunnel studies of scramjet phenomena A world leader in engineering and maintenance SEDIN, YNGVE C-J. I NASA-CR-181721 I p 38 N89-10045 ISAE PAPER 8724441 p t A89-10657 Transonic computations about complex configurations STANG, DAVID B. RYZHOV, O. S. using coupled inner and outer flow equations Cruise noise el the 2/9 scale model SFI-7A propeller Suppression of unstable oscillations in a boundary p 12 A89-12553 p 59 A89-12561 layer p 5 A89-10171 SEHMER, A. A. STANZIONE, THOMAS Schlieren measurements at the tO,O00-foot sled track The Symbolics SCOPE system as a platform for I DE88-0127481 p 42 N89-10899 environmental analysis p 57 A89-11748 S SEMANOV, G. R. STARGARDTER, HANS Effect of protechve coahngs on life of heat-resistant Fan flutter test p 37 N89-10014 SACHS, GOTTFRIED nickel steel under cyclic heat load p 45 N89-11005 STARKEN, H. Aircraft dynamic stability - Developmental history SETTLES, GARY S. Experimental investigation of the performance of a aspects Experimental research on swept shock wave/boundary supersonic compressor cascade IDGLR PAPER 87-0571 p 1 A89-10538 layer interactions INASA-TM-1008791 p 16 N89-10858 SACKSTEDER, KURT R. I AD-A1969381 p53 N89-1 t 189 STATECNY, JIRI Fire behavior and risk analysis m spacecraft SHARER, LARRY T. Control of the low-cycle service life of the primary J NASA-TM-t00944 t p 42 N89-1011 t A candidate for hnear token-passing, high-speed data components of aircraft turbine engines according to the SAINTPE, P. bus systems damage-tolerance concept p 37 A89-11075 Flight mechanics and aerothermodynamlc software I SAE PAPER 8724941 p 49 A89-10686 STAUFENBIEL, R. SHARP, GORDON I CNES-CT/DTI/MS/MN/0691 p4 N89-10839 The 'Pneumatic Wind Shear Sensor' (PWSS) - An aid Bird hazards in aviation - The regulatory authordy's to flight path regulation and to disturbance magnitude SAITO, SHIGERU responsibddles p 20 A89-12722 identification m shear wind situations Numerical approach of advanced turboprop with SHEN, BINGYAN I DGLR PAPER 87-1341 p 31 A89-10525 three-dimensional Euler equations Bevel gear resonance failures in central gearing system STEARNS, C. A. I SAE PAPER 8724481 p 7 A89-10661 of an aeroenglne p 50 A89-11046 Deposihon of Na2SO4 from salt-_eeded combustion SALVINO, J. T. SHERWOOD, L. T. gases of a high velooty burner rig p 43 A89-12330 Statistics on aircraft gas turbine engine rotor failures Sensors for ceramic components In advanced STECKLAIR, WALTER T. that occurred in US commercial aviation during 1982 propulsion systems Summary of htP, rature survey and Pi - An AI approach for maintenance and diagnostic I DOT/FAA/CT-88/231 p 38 N89-10892 concept analysis, task 3 report apphcahons p 58 A89-12413 SANTORO, G. J. INASA-CFI-1809001 p 54 N89-11192 STEGEMAN, JAMES Deposition of Na2SO4 from salt seeded combustion SHIBANOV, GEORGlt PETROVICH Calculations of the unsteady, three dimensional flow gases of a high velocity burner rig p 43 A89-12330 Operating safety of automatic objects field inside a motored Wankel engine SAUER, G. p 49 A89-10714 ISAE PAPER 8806251 p 37 A89-12307 Study of the engine influence on wings with modern SHIH, CHIANG STEGER, JOSEPH L. high-bypass propulsion concepts Control of separated flow on a symmetric airfoil Computational fluid dynamics =n aerospace I DGLFI PAPER 87-0631 p 5 A89-10510 p 47 A89-10181 ISAE PAPER 8724461 p 7 A89-10659
B-8 PERSONAL AUTHOR INDEX WANG, ZONGYUAN
Numerical investigation of a jet in ground effect using THAYER, JEFFREY S. V the fortified Navler-Stokes scheme p 16 N89-10857 An aircraft-borne electric f,e_d measuring system for STEINTHORSSON, ERLENDUR rocket launch support p 55 N89-10443 VALAREZO, WALTER O. Calculations of the unsteady, three-dimensional flow THERIAULT, J. P. Apphcafion of an advanced panel method to field reside a motored Wankei engine Fiber-optic sensor systems for aerospace applications aerodynamic problems of aircraft design ESAE PAPER 8806251 p 37 A89-12307 p 47 A89-10359 p 28 A89-11486 STETSON, KENNETH F. THOMPSON, J. L VAN AKEN, JOHANNES M. On nonlinear aspects of hypersonic boundary-layer Aeronautical decision making for air ambulance Inlet development for the NFAC 80- by 120-toot indraff stability p 10 A89-11116 helicopter pilots: Situational awareness exercises wind tunnel STEWART, VEARLE R. IDOT/FAA/DS-88/61 p 23 N89-10869 I AIAA PAPER 88-25281 p 41 AB9-12550 The characteristics of the ground vortex and its effect THORPE, JOHN VAN DAM, C. P. on 1he aerodynamics of the STOL configuration The civil aviation birdstrike record p 20 A89-12717 Boundary-layer transition effects on airplane stability and p 15 N89-10850 TILLOTSON, DAN control p 39 A89-12556 STONE, GERALD Operational findings from a Traffic Alert and Collispon VANDALSEM, WILLIAM R. The design eye reference point Avoidance System (TCAS) evaluation Numerical investlgatqon of a jet in ground effect using I BAE PAPER 871763l p 31 A89-10582 ISAE PAPER 8809431 p 32 A89-12321 the fortified Navier-Stokes scheme p 16 N89-10857 STONUM, RONALD K. TILLOTSON, DANIEL H. VANHOY, B. Wave drag and high-speed pedormanoe of supersonic In-serwce evaluation of the Traffic Alert and Colhsion Prototype data acquisition and analysis system for Navy STOVL tighter configuration Avoidance System (TCAS) industry prototype operational flight sqmulators INASA-TM-100061 I p 13 N89-10017 I DOT/FAA/SA-88/21 p 25 N89-10885 IDE88-0145571 p 42 N8g-10901 STRAUSS, RAINER TON, TRAN4:OMG VARSNNEYA, D. Indirect effects on electronic and mechanical systems A potential theory for the steady separated flow about Applications of time and wavelength division multiplexing installed in carbon fibre compound aircraft structures an aerofoil seebon to digital optical code plates p 31 A89-10364 p 22 N89-10492 IARL-AERO-R-1761 p 13 N89-10005 VASHCHILO, N. P. STRINGER, I. TORCK, JAMES A. Effect of protecltve coabngs on hfe of heat-resistant Shock tunnel studies of scramjet phenomena A Canadian government look at airworthiness nickel stee_ under cyclic heat load p 45 N89-11005 tNASA-CR-181721 I p 38 N89-10045 ISAE PAPER 8809351 p 2 A89-12319 VAVRINCOVA, MIROSLAVA STRINGFELLOW, MICHAEL F. TRETYACHENKO, G. N. Numencal simutahon of steady transomc flow past an Lightning and surge protection of large ground Effect of protective coatings on hfe of heat-resistant B-percent DCA cascade at a freestream Mach number facilities p 52 N89-10474 nickel steel under cyclic heat load p 45 N89-11005 of about 1 p 8 A89-11073 STUFF, R. TRIKHA, ARUN K. VIDULICH, MICHAEL A. Noise tle}d of a propeller w_th angular inflow Advanced crew escape capsule technologies program Speech recognlbon in advanced rotorcraft - Using p59 A89-11102 p 18 A89-10475 speech controls to reduce manual control overload SU, DAI TRIPPENSEE, GARY A. p 24 A89-12404 The formation mechanism O1 the asymmetric spatial X-29A forward-swept-wing flight research program VIGNAU, F. vortex of slender bodies at high angle of attack status Boundary layer transition {SAE PAPER 8724351 p 7 A89-10652 I SAE PAPER 8724181 p 27 A89-10640 ICERT-OA-40/5018-AYDI p 53 N8g-11187 SU, HANSHOU TRUJILLO, EDDIE J. VOGEL, WOLFHARD J. A new approach to _mprovement of fans A tactics expert system for scout/attack rotorcraft Results of 1987 MSS hehcopter propagation experiment p8 A89-11064 p 58 A89-12405 at UHF and L band in Central Maryland SUIKAT, REINER TSENG, KADIN p 53 N89-11077 Method to optimize nacelle shape in a supersonic cruise BEM for wave equation with boundary in arbitrary motion VOIRON, T. aircraft p 28 A89-12558 and applications to compressible potential aerodynamics Flight mechanics and aerothermodynamic software SULLIVAN, R. BRYAN of airplanes and hehcopters p 5 A89-10192 ICNES-CT/DTI/MS/MN/0691 p 4 N89-10839 Flight test results for the Daedalus and Light Eagle TSUJIMOTO, TATSUYA VOSS, R. human bowered aircraft An expenmental study on aerodynamic performance of Calculation of unsteady transonic flow about oscillating I NASA-CR-1833051 p 30 N89-10890 Lippisch-type GEW p 6 A89-10544 wings by a field panel method p 11 A89-11498 SUN, XlOAFENG TSUKANO, YUKICHI Unsteady loading noise of counter-rotating propeller Measurement of aerodynamic characteristics of a W p 36 A89-11054 hang-glider-wing by ground run tests using a test vehicle SUTCLIFFE, PETER L I NAL-TR-9531 p 13 N89-10004 The Boeing 7J7 - The evolution of technology and TUCK, PAUL D. WADA, YASUHIRO design Interoperability of military and civil air-cargo systems Numerical approach of advanced turboprop with tSAE PAPER 8724051 p 27 A89-10632 tSAE PAPER 8215551 p 19 A89-10654 three-dimensional Euler equations SUTHERLAND, I. T. TURNER, C. J. I SAE PAPER 8724481 p 7 A89-10661 Md_tary aerospace technical development in Australia Bird hazards in aviation - The RAF view WADE, BARRY I SAE PAPER 8724261 p 1 A89-10646 p 20 A89-12718 Longitudinal impact test of a transport airframe section SZODRUCH, J. TWEEDT, D. L. I DOT/FAA/CT-87/26] p 54 N89-11265 Study of the engine influence on wings with modern Experimental invest_gahon of the performance of a WAGNER, D. W. high-bypass propulsion concepts supersonic compressor cascade State of the art inertial navigation - Fhght testing of the iDGLR PAPER 87-0631 p 5 A89-10510 tNASA-TM-t008791 p 16 N89-10858 Honeywell LINS Standard Navigator H-423 p 30 A89-10131 TYNOR, STEVE Tactical route planning p 24 A89-12414 WAGNER, S. T A vortex-lattice method for the calculation of wing-vortex mteracbon in subsonic flow p 11 A89-11499 TAEUBER, RALPH J. U WAHLGREN, BO I. Implications of a recent lightning strike to a NASA jet Fimte difference analysis of external and internal trainer p 22 N89-10478 UCHIDA, KEIICHIRO lightning response of the JAS39 CFC wing TAGUCHI, TOMONORI Programming techniques for high-speed processing on p 22 N89-10483 Numerical experiments for separation flows around the supercomputer FUJITSU VP-system WAKE, A. J. trapezoidal cylinders by a discrete vortex method I NAL-TR-915 [ p 58 N89-10565 Aerothermodynamics - The required tools p 6 A89-10569 I SAE PAPER 8809281 p 12 A89-12316 TAI, TSZE C. UDD, E. WALEN, DAVID B. Transonic characteristics of a humped airfoil Fiber-optic sensor systems for aerospace applications on p 12 A89-12551 p 47 A8g-t0359 Lightning tests an all-composite helicopter p 21 N89-10452 TAKANASHI, SUSUMU UEDA, TETSUHIKO Numencal simulation of transonic flow around Asuka New trial of vibration testing method WALKER, BE'trY S. p 18 N89-11067 p 52 N89-11068 Experimental results for the EppFer 387 atrfod at low TAKASAKI, HIROSHI UHLHORN, R. W. Reynolds numbers in the Langley low-turbulence pressure An experimental study on aerodynamic performance of Fiber Optic buses and networks for advanced avionics tunnel Lippisch-type GEW p 6 A89-10544 architectures p 33 N89-10836 tNASA-TM-40621 p 15 N89-10842 TANAKURA, YOSHIYUKI ULKEN, ROLE WANG, QIAOSEN Programming techniques for high-speed processing on Investigahon of wake vorbces of landing aircraft at Measurements of unsteady pressure distribution on a the supercomputer FUJITSU VP-system Frankfurt airport (Federal Republic of Germany) NACA 0012 profile in transonic flow" p 8 A89-11082 1NAL-TR-9151 p 58 N89-10565 I DFVLR-MITT-88-151 p 17 N89-10862 WANG, ZHENGMU TANNEHILL, J. C. Establishment of variable vane regulation law UNRUH. JAMES F. A new PNS code for chemicat nonequihbrium flows p 36 A89-11044 Structure-borne noise control for propeller aircraft WANG, ZI-XING p9 A89-11106 p 59 A89-12563 TAYLOR, RODNEY The formation mechanism of the asymmetric spatial Predicbon of aircraft-propeller-reduced, structure-borne 'The Pointer', a new concept for RPV air vehicles vortex of slender bodies at high angle of attack mtenor noise p 28 A89-12564 p 28 A89-12416 I SAE PAPER 8724351 p 7 A89-10652 TERENT'EV, E. D. URBAN, CH. WANG, ZONGYUAN Suppression of unstable oscillations in a boundary A vortex4attice method for the calculation of wing-vortex Experimental study of rotating stall in single-stage axial layer p 5 A89-10171 interaction in subsonic flow p 11 A89-11499 compressor p 8 A89-11059
B-9 WARES, RICHARD PERSONAL AUTHOR INDEX
WARES, RICHARD WU, DINGYI ZHANG, LINGMI The performance of alternate fuels in general aviation Calculation of compressible flow and heat transfer on A frequency domain MIMe modal identification method aircraft a rotating disk p 50 A89-11033 with application in the aircraft ground vibration test IDOT/FAA/CT-88/131 p 44 N89-10175 WYATT, F. V. I SAE PAPER 8724581 p 48 A89-10670 WARREN, STEVEN M. Sandia National Laboratories flight simulation facilities ZHANG, QINGBING Advanced crew escape capsule technologies program I DE88-0121081 p 42 N89-10898 A further improvement in the numerical method of p 18 A89-10475 WYGNANSKI, I. supersonic infinitesimal horseshoe vortex distribution WATSON, N. F. On the pairing process in an excited, plane, turbulent p8 A89-11080 Cost-effechve strapdown INS. design and the need for mixing layer p 47 A89-10173 ZHANG, RONGHUA standard flight profiles p 30 A89-10128 Experimental investigation of convergent ejector WATSON, R. D. nozzle/afterbody in wind tunnel p 8 A89-11060 Computational and experimental studies of LEBUs at X ZHANG, RONGXUE high device Reynolds numbers p 4 A89 10160 Reduction of elector noise with multihole nozzle WEBB, GARY J. XU, EJUN p36 A89-11034 Lessons learned from an operational engine monitoring ZHANG, SHIPING Bevel gear resonance failures in central gearing system system and their correlation with future developments of an aeroengine p 50 A89-11046 The bistable behavior of a rigid rotor with squeeze film ISAE 871733q p 34 A89-10618 XU, JIANKANG damper p 49 A89-11029 WEI, FU-SHANG ZHANG, YISONG An experimental investigation on the bistable behaviors Correlation and analysis for SH-2F 101 rotor A dynamic characteristic analysis of a bladed disk of a flexible rotor-squeeze film damper system p25 A89-10111 assembly p 36 A89-11026 p 49 A89-11028 WEI, XINGLU ZHAO, FUAN Approach 10 blade end-bend mechanism The bistable behavior of a rigid rotor with squeeze film p 36 A89-11052 Y damper p 49 A89-11029 WEIGAND, A. ZHAO, XIN Profile development results for advanced A study of helicopter stabihty and control including blade YAKOVCHUK, K. YU. circulation-guided rotor systems in fast helicopters dynamics Effect of protective coatings on life of heat-resistant I DGLR PAPER 87-0861 p 5 A89-10513 I NASA-CR-1832451 p 40 N89-10895 nickel sleel under cyclic heat load p 45 N89-11005 WEIR, ROBERT J. YAH, LITANG ZHONG, YULING Aerodynamic design conslderahons for a free-flying Application of end-bend blade for enhancing surge The bistable behavior of a rigid rotor w_th squeeze film ducted propeller margin p 36 A89-11051 damper p 49 A89-11029 IDE88-0068671 p 15 N89-10841 YANG, HAN-MIN ZHOU, SHENG WEISBROT, I. Unsteady loading noise of counter-rotating propeller Unified computation method of unsteady On the pairing process in an excited, plane, turbulent p36 A89-11054 supersonic/hypersonic flow past two dimensional flat plate m_xlng layer p 47 A89-10173 ZHOU, ZHI-QIANG and rectangular wings WEISS, J. A. The study of the global stability of high performance I SAE PAPER 8724471 p 7 A89-10660 Coping with legacy factors p 58 A89-12178 YANG, QIUSHENG aircraft at high angles-of-attack WERLE, H. ISAE PAPER 8724561 p 39 A89-10668 Investigation on wall interference of low-speed wind Flow around a delta wing with or without a canard (Phi ZHU, CHANGSHENG tunnel with slotted walls p 8 A89-11081 BA 60 deg). Part 2: Hydrodynamic visuahzations in An experimental mvestigahon on the bistable behaviors YANG, ZUOSHENG unsteady flow (pitching Oscillations) ot a flexible rotor-squeeze film damper system Finite element method for calculating transonic potential IONERA-RT-11/2891-AN-PT-21 p 17 N89-10860 p 49 A89 11028 flow around airfoil from pressure minimum integration WHEELER, M. S. ZHU, CHUNHUA p 9 A89-11088 System protechon from atmospheric electricity for Measurements of unsteady pressure distribution on a YECHOUT, T. R. aerostats with conducting tethers p 52 N89-10497 NACA 0012 profile in transonic flow p 8 A89-11082 Flight-test determination of aircraft cruise characteristics WHITE, B. J. ZHU, NIANGUO using acceleration and deceleration techniques Aerodynamic characteristics of the ACES-II ejection seat Propfan design by propeller-nacelle interaction p 25 A89-10101 at transonic Mach numbers p 25 A89-10463 analysis p 36 A89-11055 YENNI, KENNETH R. WHITE, JOHN ZHU, S. Development in hehcopter tail boom strake applications Modern techniques for the control of RPV's In the US The 'Pneumahc Wind Shear Sensor' (PWSS) - An aid I SAE PAPER 8724571 p 39 A89-10669 to flight path regulation and to disturbance magnitude I NASA-TM-1014961 p 40 N89-10059 WIEMER, P. identification in shear wind situations YI, LIYAN Approximation of free and bounded vortex sheets at IDGLR PAPER 87-1341 p 31 A89-I0525 A dynamic characteristic analysis of a bladed disk delta-wings p 11 A89-11500 ZHU, ZIQIANG assembly p 36 A89-11026 WILLIAMS, E. R. YOSHIDA, MASAHIRO Analysis of transonic wings including viscous Intracloud lightning as a precursor to thunderstorm interaction p 9 A89-11084 Programming techniques for high-speed processing on microbursts p 56 N89-10490 ZHUANG, BIAONAN the supercomputer FUJITSU VP-system WILLIAMS, J. E. D. Flow performance of reversed tandem cascades with INAL-TR-9tSl p 58 N89-10565 Air navigation systems I - Astronomical navigation in double-circular arc profile for compressor staler YU, SHOUQIN the air 1919-1969 p 24 A89-12449 p 7 A89-11036 A further improvement in the numerical method of WILLIAMS, LOUIS J. ZlEN, T. F. supersonic infinitesimal horseshoe vortex distribution The winning edge p8 A89-11080 Approximate calculations of wscous drag and I SAE PAPER 8809451 p 2 A89-12322 YUHAS, JOHN S. aerodynamic heating p 10 A89-11157 WILSON, JOHN C. ZIENKIEWICZ, OLGIERD C. T55-L-712 turbine engine compressor housing Development in helicopter tail boom strake applications Finite element Euler computations in three dimensions refurbishment-plasma spray prelect in the US p 11 A89-12130 I NASA-TM-1013101 p44 N89-10156 I NASA-TM-1014961 p 40 N89-10059 ZlMMER, H. WINN, WILLIAM P. Profile development results for advanced The electrical structure of thunderstorm anvils Z circulation-guided rotor systems in fast helicopters p 56 N89-10470 IDGLR PAPER 87-0861 p 5 A89-10513 WOLF, STEPHEN W. D. ZABOLOTSKY, V. P. ZINNER, H. Highlights of expeoeece with a flexible walled test Heat transfer in the recirculating region formed by a Navigation of aircraft with rigid image-forming sensors section in the NASA Langley O 3-meter transonic cryogenic backward-facing step p 51 A89-12252 IDGLR PAPER 87-1301 p 31 A89-10521 tunnel ZANOTTI, C. ZUBKOV. BORIS VASIL'EVICH I NASA-TM-101491 I p 41 N89-10060 Tension fahgue analysis and life prediction for composite Fundamentals of flight safety p 19 A89-10721 WOOD, L. A. laminates ZUEV, VLADIMIR EVSEEVICH Fatigue testing of full-scale all-composde aircraft I NASA-TM-1005491 p 44 N89-10951 Laser navigation equipment p 24 A89-10722 wings ZELL, PETER T. ZUK, JOHN I SAE PAPER 8724591 p 48 A89-10671 Inlet development for the NFAC 80 by 120-foot mdraft V/STOL aircraft configurahons and opportunities in the WOODSON, SHAWN H. wind tunnel Pacific Basin A transonic interactive boundary-layer theory for laminar IAIAA PAPER 88-25281 p 41 A89-12550 ISAE PAPER 8724031 p 18 A89-10631 and turbulent flow over swept wings ZERWECKH, SIEGFRIED H. Aviahon technology apphcable to developing regions INASA-CR-41851 p 14 N89-10029 Flight test results for the Daedalus and Light Eagle I NASA-TM-894251 p 23 N89-10872 WORTMANN, J. human powered aircraft ZURINSKAS, THOMAS E. Influence of regeneration treatments on creep rupture I NASA-CR-1833051 p 30 N89-10890 Evaluahon of enhancements to the Low Level Wind lives of turbine blades p 43 A89-11214 ZHANG, CAI-WEN Shear Alert System (LLWAS) at Sta'pleton International The high temperature oxidation behavior el lhe single Unified computation method el unsteady Airport crystal Hi-base alloy M002 mod with and without protective supersonic/hypersonic flow past two d_menslonal flat plate IDOT/FAA/PS-88/141 p56 N89-11356 coatings p 43 A89-11216 and rectangular wings WRENN, GREGORY A. ISAE PAPER 8724471 p 7 A89-10660 Multilevel decomposition approach to the preliminary ZHANG, CHENGSHENG sizing of a transport aircraft wing p 25 A89-10109 A data acquisition system for blade vibration test WRIGHT, ROBERT L. p41 A89 11037 A comparative evaluation of RPD (Rotary Particle ZHANG, GUOFU Depositor) and ferrographic dlagnosbc methods for turbine Finite element method for calculating transonic potential engine lubncant samples flow around airfoil from pressure minimum integrahon lAD-A1962071 p 38 N89-10044 p9 A89-11088
B-10 CORPORATE SOURCE INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 236) February 1989
Typical Corporate Source Index Listing High speed parallel processing networks for advanced Columbia Univ., New York, N.Y. architectures p 59 N89-10837 Response Of discretely stiffened structures and F-15 SMTD low speed jet effects wind tunnel test transmission Of structure-borne noise results p 16 N89-10853 p 54 N89-11270 Airborne Research Associates, Weston, Mass. Computer Resource Management, Inc., Atlantic City, ICORPORATE SOURCE! New electric field instrumentation and the effects of N.J. space charge at Kennedy Space Center Lightning reformation database p 55 N89-10432 p 55 N89-10444 Cornell Univ., Ithaca, N.Y. I AIRO, Inc., Colorado Springs, Colo. Diagonal implicit multigrid algorithm tot the Euler A chronology of in-cloud electric held and hghtning equations p 9 A89-11110 Federal Aviation Administration, Atlantic City. N.J. strikes on an instrumented research aircraft p 21 N89-10455 D Analex Corp., Cleveland, Ohio.
Deposition of Na2SO4 from salt-seeded combustion Dayton Univ., Ohio. gases of a high velocity burner rig p 43 A8@-12330 Navier-Stokes soluhon to the flowfield over =ce accrehon Analytical Mechanics Associates, Inc., Mountain View, shapes p 12 A89-12557 Calif. De Ravilland Aircraft Co. of Canada Ltd., Downsview Simulation and analysis of image-based navigation (Ontario). system for rolorcratt Iow-alhtude flight Phase 4 stahc tests of the J-97 powered, externa_ p 32 A89-12403 augmentor V/STOL model at the NASA, Ames Research Arinc Research Corp., Annapolis, Md. Center. November 1983 tn-service evaluahon of the Traffic Alert and Co[liston INASA-CR-1773951 p 14 N89-10028 Avoidance System (TCAS) industry prototype Lightning tests to measure the bulk current levels I DOT/FAA/SA-88/21 p 25 N89-10885 associated with the electronic engine control of a turboprop Army Research and Technology Labs., Moffett Field, commuter transport p 21 N89-10457 Calif. Department of Defence, Canberra (Australia). Hehcopter roll control effectiveness criteria program Some statishcal aspects oi attrition studies Listings in this index are arranged alphabetically summary I AD-At 966651 p30 N89-10891 by corporate source. The title of the document is I NASA-CR-1774771 p 39 N89-10046 Department of National Defence, Ottawa (Ontario). used to provide a brief description of the subject Electrostatic discharge and field effects of electronics systems p 52 N89-10493 matter The page number and the accession B Detroit Diesel Allison, Indianapolis, Ind. number are included in each entry to assist the Measurements of heat transfer distnbutlon over the
user in locating the abstract in the abstract sec- Boeing Advanced Systems Co., Seattle, Wash. surfaces of highly loaded turbine nozzle guide vanes tion If applicable, a report number is also included Lightning tests on an all-composite hehcopter p 51 A89-12752 p 21 Nsg-t0452 Forced vibration and flutter design methodology as an aid in identifying the document. Boston Univ., Mass. p 51 N89-10016 BEM for wave equation with boundary m arbitrary motion Deutsche Forschungs- und Versuchsanstalt fuer Luft- and applications to compressible potential aerodynamIcs und Raumtahrt, Brunswick (West Germany). of airplanes and helicopters p 5 A89-10192 Investigation of wake vortices of landing aircraft at A Frankfurt airport (Federal Republic of Germany) C IDFVLR-MITT-88-151 p 17 N89-10862 Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seine (France). E AGARD manual on aeroelasticity in a_,al-flow California Univ., Davis. turbomachines Volume 2: Structural dynamics and _oundary-tayer transition effects on airplane stablhty and Electro Magnetic Applications, Inc., Huntsville, Ala. aeroeiashcity control p 39 A89-12556 Esbmating electric field enhancement factors on an tAGARD-AG-298+VOL-21 p 13 N89 10006 Design and evaluation of a cockpit display for hovering aircraft utilizing a small scale model: A method Computing Systems Configuration for Highly Integrated ihght evaluation p 21 N89-1045Zl Guidance and Control Systems t NASA-CR-183247I p 42 N89-10900 IAGARD-LS-158t p 3 N89.10831 California Univ., Los Angeles. Electro Magnetic Applications, Inc., Lakewood, Colo. Aeronautical Research Labs., Melbourne(Australia). Aeroelasticity and structural optlmlzahon of hehcopter Tnggenng of hghtnlng by the Atlas Centaur vehicle p 55 N89-10438 A potenhal theory for the steady separated flow about rotor blades with swept tips p 29 N89-10887 an aerofod section Centre d'Essais Aeronautique Toulouse (France). Linear and nonlinear interpretation of CV-580 lightning data p 21 N89-10451 IARL-AERO-R-1761 p 13 N89-10005 Creep tests for slow and fast fatigue condihons on Non-hnear aerodynamic characteristics obtained from aluminum alloy specimens Interference of prec_pitahon static discharges with the analysis of flight-data I REPT-M0-535200t p 45 N89-11020 aircraft navigational systems p 21 N89-10459 IAR-004-571 I p 18 N89-10866 Centre d'Etudes et de Recherches, Toulouse (France). Electronique Serge Bassault, St. Cloud (France). A highly reliable computer for airborne applications Aerospace Medical Research Labs., Wright-Patterson Investigation on of the flow around a backward facing AFB, Ohio. step with spanwise blowing p 59 N89-10833 Speech recognition m advanced rotorcraft - Using I CERT-RF-OA-68/2259-AYD I p 17 N89-10859 speech Controls to reduce manual control overload Experimental investigation of flow near a corner, part F 2 p 24 A89-12404 ICERT-RT-OA-24/5025*AYDI p 17 N89-10861 Air Force Academy, Colo. Federal Aviation Administration, Atlantic City, N.J. Three dimensional shear flow. Analysis Of the flow in Flight-test determination of a_rcraft cruise characteristics Hardware fault Insertton and instrumentation system: a delta arrow wing with incidence angle using acceleration and deceleration techniques Experimentation and results ICERT-RTS-OA-25/5025-AYDI p 17 N89-10864 p 25 A89-10101 INASA-CR-182746i p 58 N89-10526 Study of three dimensional boundary layers on the front Air Force Inst. of Tech., Wright-Patterson AFB, Ohio. Federal Aviation Administration, Washington, D.C. of a fuselage and at an air intake A computational study of coherent structures in the Terminal control area design and air traffic Ioadings t CERT-OA-22/5025-AYD I p 53 N89-11184 wakes of two-dimensional bluff bodies t DOT/FAA/DS-88/11 I p 25 N89-10038 Boundary layer transition I AD-A1968201 p 53 N89-11188 Census of US civil aircraft: Calendar year 1987 ICERT-OA-40/5018-AYDI p 53 N89-11187 lAD-A1966261 p 4 N89-11691 Air Force Wright Aeronautical Labs., Wright-Patterson Centre National d'Etudes Spatiales, Toulouse (France). AFB, Ohio. Flight mechanics and aerothermodynamic software Federal Aviation Agency, Atlantic City, N.J. A comparative evaluation of RPD (Rotary Particle ICNES-CT/DTI/MS/MN/069I p 4 N89-10839 The performance of alternate fuels =n general aviation aircraft Depositor) and ferrographlc diagnostIc methods for turbine Chelton (Electrostatics) Ltd., Marlow (England). engine [ubncant samples Israel Air Force lIAr) m-servzce aircraft lightning strike IDOT/FAA/CT-88/131 p44 N89-10175 lAD-A196207 I p 38 N89-10044 and damage Survey p 55 N89-10431 Alternate fuels for General Aviation aircraft with spark Advanced avionics archLtecture pave pillar Clemson Univ., S.C. ignition engines p 33 N89-10834 Fracture criteria for discontinuously reinforced metal I DOT/FAA/CT-88/051 p44 N89-10179 Data and signal processing architectures for future matrix composftes Longitudinal impact test of a transport a_rframe section awomcs p 33 N89-10835 I NASA-CR-181175{ p 44 N89-10125 I DOT/FAA/CT-87/261 p 54 NB9-11265
C-1 Florida State Univ., Tallahassee. CORPORA TE SOURCE
Evaluation of enhancements to the Low Level Wind Lockheed-Georgia Co., Marietta. Noise of the Harrier in vertical landing and takeoff Shear Alert System (LLWAS) at Stapleton International Quadruplex digital flight control system assessment p 60 N89-10856 Airport I NASA-CR-182741 I p 40 N89-10058 Numerical investigation of a let m ground effect using iDOT/FAA/PS-88/141 p 56 N89-11356 Hardware fault Insertion and instrumentation system: the fortified Navier-Stokes scheme p 16 N89-10857 Florida State Univ., Tallahassee. Experimentation and results Aviation technology applicable to developing regions Effects of a ground vortex on the aerodynamics of an INASA-CR-1827461 p 58 N89-10526 I NASA-TM-894251 p 23 N89-10872 a_rfoil p 16 N89-10855 National Aeronautics and Space Administration. Hugh Florida Univ., Gainesville. M L. Dryden Flight Research Facility, Edwards, Calif. Calculations of the unsteady, three-dimensional flow X-29A forward-swept-wing flight research program field inside a motored Wankel engine status Manudyne Systems, Inc., Los Altos, Calif. I SAE PAPER 8806251 p 37 A89 12307 Helicopter roll control effectiveness criteria program ISAE PAPER 8724181 p 27 A89 10640 summary National Aeronautics and Space Administration. 13 I NASA-CR-1774771 p 39 N89-10046 Langley Research Center, Hampton, Va. Massachusetts Inst. of Tech,, Cambridge. Adhesively bonded joints: Testing, analysis, and design; Aeroelasttc formulation for tuned and misfuned rotors Proceedings of the International Symposium, Balhmore, General Dynamics/Fort Worth, Tex. p 37 N89-10013 MD, Sept 10-12, 1986 p 45 A89-10076 Unsteady low-speed windtunneI test of a straked delta A study of the fatigue behavior of small cracks in Effect of adhesive debond on stress-intensity factors wing, oscillating in pitch Part 1: General description and nickel-base superalloys in bonded composde panels p 45 A89-10091 discussion of results lAD-At954891 p 44 N89-10161 Expenmental study of effects of forebody geometry on lAD-A1964561 p 18 N89-10867 Intracloud lightning as a precursor 1o thunderstorm high angle-of-attack stability p 38 A89-10103 General Electric Co., Cincinnati, Ohio. microbursts p 56 N89-10490 Efficient algorithm for solution of the unsteady transonic Sensors for ceramic components in advanced Flight test results for the Daedalus and Light Eagle small-disturbance equation p 4 A89-10104 propulsion systems: Summary of literature survey and human powered aircraft Wing laminar boundary layer in the presence of a concept analysis, task 3 report I NASA-CR-1833051 p 30 N89-10890 propeller slipstream p 4 A89-10105 INASA-CR-f809001 p 54 N89-11192 Materials Research Labs., Melbourne (Australia). Computational and experimental sludles of LEBUs at George Washington Univ., Washington, D.C. Contamination of environmental control systems in high device Reynolds numbers p 4 A89-10160 Investigatton of the tumbling phenomenon using Hercules aircraft computer simulation p 41 N89 10896 I MRL-R-11161 p29 N89-10040 Unique research challenges for high-speed civil transports Groningen Rijksuniversdett (Netherlands). Measerschmitt-Boelkow-Blohm G.m.b.H., Munich (West ISAE PAPER 8724001 p 1 A89-10629 Symmetric (and generic) algorithms for height balanced Germany). trees Indirect effects on electronic and mechanical systems Propulsion-airframe integration for commercial and ICS-8711 I p 59 N89-12332 installed in carbon fibre compound aircraft structures military aircraft p 22 N89-10492 I SAE PAPER 8724111 p 35 A89-10637 Computing system configuration for fighter aircraft fhght Boundary-layer control for drag reducbon H control systems p 40 N89-10832 I SAE PAPER 8724341 p 6 A89-10651 Michigan State Univ., East Lansing. Multigrid solution of the two-dimensional Euler equations Harris Corp., Melbourne, Fla. Calculations of the unsteady, three-dimensional flow on unstructured tnangular meshes p 9 A8g 11108 Fiber opttc buses and networks for advanced av*ontcs field reside a motored Wankel engine Numerical simulation of the vortical flow over a I SAE PAPER 880625 J p 37 A89-12307 architectures p 33 N89-10836 round-edged doubl_-delta wing p 10 A89-11152 Reglessed relations for forced convection heat transfer High Technology Corp., Hampton, Va. Incompressible Navier-Stokes computations for a m a direct miechon stratified charge rotary engine Computabonal and experimenta_ studies of LEBUs at round-edged double-delta w_ng p 12 A89-12552 I SAE PAPER 8806261 p 51 A89-12308 high dewce Reynolds numbers p 4 A89 10160 Ministry of Posts and Telecommunications, Kashima Boundary-layer translhon effects on airplane stability and control p 39 A89-12556 (Japan). I ETS-V propagation experiments in Japan Effictent vibration mode analysis of aircraft with multiple p83 N89-11080 external store configurations p 28 A89-12562 The effects of fluids in the aircraft environment on a Institut de Mecanique des Fluides de Lille (France). Mississippi Univ., University. The electrical structure of thunderstorm anvils polyethenmide p 44 A89-12759 Aircraft crashes on the runway Development of a super element for nonlinear analysis of a beam p 56 N89-10470 Weak-wave analysis of shock interaction with a INEPT-87/561 p 54 N89-11286 slipstream Iowa State Univ. of Science and Technology, Ames. N INASA TP-28481 p 13 N89-10020 A new PNS code for chemical nonequihbnum flows Vahdahon of a pair of computer codes for esfimahon p9 A89-11106 and optimization of subsonic aerodynamic performance National Academy of Sciences - National Research Israel Aircraft Industries Ltd., Led. of simple htnged flap systems for thin swept wings Council, Washington, D. C. Efficient vibration mode analysis of aircraft with mulhple I NASA TP-2828 I p 13 N89 10024 Review of aeronautical wind tunnel faclhtles external store configurahons p 28 A89-12562 The pros and cons of code vahdation I NASA-CR-1830571 p41 N89-10897 INASA-TM-1006571 p 14 N89-10034 National Aeronautical Lab., Bangalore (India). J Tests on 3 NACA 0012 airfoil models of DEVLR m the Development in helicopter tail boom strake applications HAL 0.3 tunnel An assessment of 2-D wall *nterference in the US I NASA-TM-1014961 p 40 N89-1005g Jeffers (James D., III), Tampa, Fla. ITM-AE-87051 p 15 N89-10847 Highhghts of experience with a flexible walled test Aeroelastic thermal effects p 37 N8g-10015 National Aeronautics and Space Administration, section in the NASA Langley 0 3-meter transonic cryogenic Johns Hopkins Univ., Laurel, Md. Washington, D.C. tunnel Results of 1987 MSS helicopter propagahon expenment The winning edge I NASA-TM-101491 I p 41 N89-10060 at UHF and L band in Central Maryland [ SAE PAPER 880945 I p 2 A89-12322 Imphcations of a recent lightning strike to a NASA let p 53 N89-11077 National Aeronautics and Space Administration. Ames trainer p 22 N89-10478 Joint Publications Research Service, Arlington, Va. Research Center, Moffett Field, Calif. On the diagnostic emulahon technique and its use in Effect of protectwe coatings on hfe of heat-resistant V/STOL aircraft configurations and opportunities m the the AIRLAB nickel steel under cychc heat load p 45 N89-11005 Pacific Basm I NASA-TM-40271 p 58 N89-10524 Cascade flow analysis by Nawer-Stokes equahon tSAE PAPER 8724031 p 18 A89-10631 Experimental results for the Eppler 387 airfoil at low p 52 N89-11065 Computational fluid dynamics m aerospace Numerical simulation of transonic flow around Asuka I SAE PAPER 8724461 p 7 A89 10659 Reynolds numbers in the Langley low-turbulence pressure tunnel p 18 N89-11067 A new PNS code for chemical nonequdibnum flows INASA-TM-40621 p 15 N89-10842 New trial of wbration testing method p9 A89-11106 An assessment of ground effects determined by static p 52 N89q 1068 Simulation and analys_s of image-based navigation CAD wind tunnel test for halt cut model of Asuka system for rotorcraft Iow-altdude fhght and dynamic testing techniques p 16 N89-10854 Tension fahgue analysis and life prediction for composite p 18 N89-11069 p 32 A89-12403 Inlet development for the NFAC 80- by 120-foot indraft laminates wind tunnel I NASA-TM-1005491 p44 N89-10951 K I AIAA PAPER 88-25281 p 41 A89-12550 National Aeronautics and Space Administration. Lewis Transonic characterishcs of a humped airfoil Research Center, Cleveland, Ohio. Kanaas Univ. Center for Research, Inc., Lawrence. p 12 A89-12551 The dual e_ement method of strain gauge temperature Inlet development Ior the NFAC 80- by 120-foo1 Indrall compensation p 51 A8g-12276 Wave drag and htgh-speed performance of supersomc wind tunnel STOVL fighter configuration Calculations of the unsteady, fhree-dtmenslonal flow I AIAA PAPER 88 25281 p 41 A89 12550 INASA-TM-f000611 p 13 N89-10017 field inside a motored Wankel engine I SAE PAPER 8806251 p 37 A89-12307 Nawer-Stokes slmulahon of transonic wing flow fields Regressed relations for forced convechon heat transfer L using a zonal grid approach In a direct injection stratdied charge rolary engine INASA-TM-t000391 p 13 N89-10022 I SAE PAPER 8806261 p 51 A89 12308 The 1987 Ground Vortex Workshop Lawrence Livermore National Lab., Calif. Deposition of Na2SO4 from salt-seeded combushon INASACP-t00081 p 15 N89-10849 DLrectlonal spectral emlsstvlty measurements on a gases of a htgh velocity burner ng p 43 A89 12330 ceramic mold matenal The charactenstlcs of the ground vortex and its effect Cruise noise of the 2/9 scale model SR-7A propeller IDE88-0154071 p 44 N89-10167 on the aerodynamics of the STOL configuration p 59 A89-12561 Lockheed Aeronautical Systems Co., Burbank, Calif. p 15 N89-10850 Measurements of heat transfer distribution over the Wheel performance evaluation Phase f: Analysis Ground vortex flow field investigation surfaces of highly loaded turbine nozzle guide vanes IDOT/FAA/CT-88/161 p 29 N89-10041 p 16 N89-10852 p 51 A89-12752
C-2 CORPORA TE SOURCE University Coll. of Swansea (Wales).
V_brabon. performance, flutter and forced response Naval Ship Research and Development Center, Royal Aerospace Establishment, Farnborough charactenshcs of a large-scale propfan and its aeroelastic Bethesda, Md. (England). model Transonic characteristics of a humped airfod Aerospace systems and technology The role of the I NASA-TM-1013221 p38 N89-10043 p 12 A89-12551 RAE F_re behavior and risk analysis _n spacecraft New Mexico Inst. of Mining and Technology, Socorro. I RAE-TR-88042t p 3 N89-I0003 ] NASA-TM-100944 J p42 N89-10111 Electrihcation of hovering helicopters Technology Issues associated with fueling the national p 22 N89-10460 aerospace plane with slush hydrogen North Carolina State Univ., Raleigh. S j NASA-TM-t013861 p43 N89-10123 A transonic interactive boundary-layer theory for laminar T55-L-712 turbine engine compressor housing and turbulent flow over swept wings Saab-Scanla, Linkoping (Sweden). refurbishment-plasma spray project tNASA-CR-41851 p 14 N89-10029 Flmte ddterence analysis of external and internal ! NASA-TM-1013101 p44 N89-10166 lightning response of the JAS39 CFC wing The effect of front-to-rear propeller spacing on the p 22 N89-10483 Interaction noise at cruise conditions of a model O Sandla National Labs., Albuquerque, N. Mex. counterrotation propeller having a reduced diameter aft An approximate, maximum terminal velocity descent to propeller Oak Ridge National Lab., Tenn. a point I NASA-TM-1013291 p 60 N89-10603 Prototype data acquisition and analysis system for Navy t DE88-0003491 p 15 N89-10840 Three component laser anemometer measurements in operational flight s_mulators Aerodynamic design considerations for a tree-flying an annular cascade of core turbine vanes with contoured [ DE88-0145571 p 42 N89-10901 ducted propeller end wail Office National d'Etudes el de Recherches lDE88-006667] p 15 N89-10841 INASA-TP-28461 p 15 N89-10844 Aeronautiques, Paris (France). Sandia National Laboratories fhght simulation facilihes Experimental investigation of the performance of a Summary of inflight data on lightning currents and IDE88-012108] p 42 N89-10898 sugersonlc compressor cascade fluids p 56 N89-10449 Schheren measurements at the 10,000-foot sled track INASA-TM-1008791 p 16 N89-10668 Analysis of recent in-fhght lightning measurements on I DE88-0127481 p 42 N89-10899 Experimental aerodynamic performance of advanced 40 different aircraft p 20 N89-10450 Continuum theories for fluid-particle flows: Some dog-swept 10-blade propeller model at Mach 0 6 to 085 The SAFIR lightning monitoring and warning system, aspects of lift forces and turbulence p 53 N89-1 t 155 LNASA-TM-889691 p 17 N89-10865 applications to aerospace activities p 52 N89-10481 Societe Nationale Industrielle Aerospetiale, Toulouse National Aerospace Lab., Amsterdam (Netherlands). Office National d'Etudes et de Recherches (France). Digital recording of radar data in an aircraft Aerospattales, Paris (France). Modelling of common mode coupling between an aircraft i P688-2095071 p 51 N69-10212 La Recherche AerospahaJe, Bimonthly Bullehn. Number wing traversed by a hghtmng current and wiring installed National Aerospace Lab., Tokyo (Japan). 1987-4, 239/July-August m that wing p 22 N89-10465 Measurement of aerodynamic characteristics of a IESA-TT-10681 p 14 N89-10026 Southampton Univ. (England). hang-glider-wing by ground run tests using a test vehicle Unsteady three-dimensional stall on a rectangular The use of the complex summation method for J NAL-TR-953 i p 13 N89-10004 wing p 14 N89-10027 formulating algorithms for decouphng vert_cal/honzontal Functional mock-up tests of the flight control system Flow around a delta wing with or without a canard (Phi motions of rolhng aircraft p 30 N89-10889 of the HAL OSTOL research aircraft: Planning and BA 60 dog) Part 2: Hydrodynamic visuahzations m Southwest Research Inst., San Antonio, Tes. mechanical system test unsteady flow (pitching OSClllahons) Structure-bOrne noise control for propeller aircraft INAL-TR-944J p 40 N89-10047 IONERA-RT-11/2891-AN-PT-21 p 17 N89-10860 p 59 A89-12563 Generation of a grid for a flnde difference calculation Ohio State Univ., Columbus. SRI International Corp., Menlo Park, Calif. of flows around an aircraft in Cartesian coordinates Transonic charactenshcs of a humped airfoil An a;rcraft-borr_ electric held measuring system for I NAL-TR-956I p 58 N89-10563 p 12 A89-12551 rocket launch support p 55 N89-10443 Old Dominion Univ., Norfolk, Va. Programming techniques for high-speed processing on Stanford Univ., Calif. Unsteady transonic aldoll computation using implicit the supercompuler FUJITSU VP-system Convergence schemes for an adaptwe-watl wind i NAL-TR+9151 p 58 N89-10565 Euler scheme on body-fixed grid p 10 A89-11153 tunnel p 41 A89-12560 National Oceanic and Atmospheric Administration, Integral equation solution for transonic and subsonic Stringfellow and Associates, Atlanta, Ca. Boulder, Colo. aerodynamqcs p t t A89-11488 The effects of fluids in the aircraft environment on a Lightning and surge protectnon of large ground Oklahoma-Kansas preliminary regional experiment for facllilies p 52 N69-10474 storm-central (O-K pro-storm) Volume 3: Aircraft mission polyethebmide p 44 A89-12759 Sverdrup Technology, Inc., Cleveland, Ohio. summary Cruise noise of the 2/9 scale model SR-7A propeller I PB88-2054891 p 56 N89-10499 P p 59 A89-12561 National Oceanic and Atmospheric Administration, Rockville, Md. Systems Control Technology, Inc., Arlington, Va. Pennsylvania State Univ., University Park. Aeronautical decision making for air ambulance Internabonal Aerospace and Ground Conference on Experimental research on swept shock wave/boundary helicopter pilots: Situational awareness exercises Lightning and Static Electricity layer interactions I DOT/FAA/DS-88/61 p 23 N89-10869 I P688-1974391 p 55 N89-10429 IAD-A196936t p 53 N89-11189 National Research Council of Canada, Ottawa Planning Research Corp., Hampton, Va. (Ontario). On the appropriateness el applying ch_-square T A case for a unified hghtning threat distribution based confidence intervals to spectral p 56 N89-10447 estnmates of hehcopter flyover data Technische Hogeschool, Delft (Netherlands). National Severe Storms Lab., Norman, Okla. INASA-CR-1816921 p 59 N69-I0601 Design and evaluation of dynamic flight test Politecnico di Todno (Italy). Lightning initiation on aircraft in thunderstorms manoeuveres p 21 N89-10456 Origin, obiectlves and activities of the Department of IPB88-210760J p 29 N89-10042 National Transportation Safety Board, Washington, D. Aerospace Engineering p 3 N89-10830 Texas A&M Univ., College Station. C. Pratt and Whitney Aircraft, East Hartford, Conn. Wing laminar boundary layer in the presence of a Aircraft accident reports, brief format, US civil and foreign Fan flutter test p 37 N89-10014 propeller slipstream p 4 A89-10105 aviation, issue number 10 of 1987 accidents Turbofan forced mixer lobe flow modeling Part 3: Tohoku Univ., Sendal (Japan). I PB88-9169051 p 20 N89-10035 Application to augment engines iNASA-CR-4147i p 14 N89-10025 Statistics of hghtmng interaction with aircraft in Japan A_rcraft accident reports, brief format, US civil and foreign p 55 N89-10430 awation, issue number 12 of 1986 accidents PRC Kentron, Inc., Hampton, Va. Engineering analysis of slender-body aerodynamics I P688-9169031 p 20 N89-10036 usiog Sychev simdarity parameters p 4 A89-10108 Aircraft accident/incident summary report, Copperhill, Multilevel decomposition approach to the preliminary U Tennessee, February 22. 1986 sizing of a transport aircraft wing p 25 A89-10109 l PB88-910407 t p 22 N89-10868 Princeton Univ., N. J. United Kingdom Atomic Energy Authority, Culham Aircraft accident reports, brief format, US ovil and foreign A study of helicopter stability and control including blade (England). aviation, issue number 2 of 1987 accidents dynamics A filamentary method for calculating _nduced voltages IPB88-9169061 p 23 N89 10871 i NASA-CR- 1832451 p 40 N89-10895 within reslshve structures in either the frequency or time Aircraft accident report: Executive Air Charter. Inc, dba Purdue Univ., West Lafayette, Ind. domain p 52 N89-10484 American Eagle. Flight 5452. CASA C-212. N432CA. Prediction of incidence effects on OSCillating a_doil United Technologies Corp., Windsor Locks, Conn. Mayaguez, Puerto Rico, May 8. 1987 aerodynamics by a locally analytical method Results of acoustic tests of a prop-fan model IP688-9104091 p 23 N89-10873 p 12 A89-12135 p69 A89-10112 Naval Air Propulsion Test Center, Trenton, N.J. Statistics on aircraft gas turbine engine rotor failures United Technologies Research Center, East Hartford, Conn. that occurred m US commercial awation during 1962 Q I DOT/FAA/CT-88/23 t p 38 N69-10892 HEM for wave equation with boundary in arbitrary motion Queensland Univ., St. Lucia (Australia). and apphcabons to compressible potential aerodynamics Naval Postgraduate School, Monterey, Calif. Shock tunnel studies Of scramiet phenomena of airplanes and helicopters p 5 A89-10192 Wing lamrnar boundary layer in the presence of a I NASA-CR-181721 I p 38 N89-10045 propeller shpstream p 4 A89-10105 Analys_s of complex hypersonic flows with strong Convergence schemes for an adaptive-wall wind viscous/mviscid interaction p 9 A89-11109 tunnel p 41 A89-12560 R Aeroelastlc couphng: An elementary approach Naval Research Lab., Washington, D.C. p 37 N89-10012 Measurement of the electrostatic charging on large Rohr Industries, Inc., Chula Vista, Calif. University CoU. of Swansea (Wales). hehcopters and control of the shock hazard De-icing of aqrcraft turbine engine inlets Finite element Euler computations _n three dimensions p 22 N89-10461 IDOT/FAA/CT-87/371 p 38 N89-10894 p 11 A89-12130
C-3 Vigyan Research Associates, Inc., Hampton, Va. CORPORA TE SOURCE V
Vigyan Research Associates, Inc., Hampton, Va. Numerical slmulahon of the vortical flow over a round-edged double-delta wing p 10 A89-11152 Incompressible Navler-Stokes computations for a round-edged double-delta wing p 12 A89-12552 W
Western Aerospace Labs., Inc., Monte Serene, Calif. Speech recognition tn advanced rotorcraft - Using speech controls to reduce manual control overload p 24 A89-12404 Westinghouse Electric Corp., Baltimore, Md. System protection from atmospheric electrlCdy for aerostats wtth conductrng tethers p 52 N89 10497 Wyle Labs., Inc., Hampton, Va. Electrical noise reduction techniques contributing tO improved data quality at the National Transonic Facility INASA-CR-41931 p 54 N89-fft96 Y
Yale Univ., New Haven, Conn. Deposthon of Na2SO4 from salt seeded combustion gases of a high v¢,loclty burner ng p 43 A89 12330 Aerodynamically-driven condensate layer thickness distributions on isothermal cylindrical surfaces p 51 A89-12337
C-4 FOREIGN TECHNOLOGY INDEX
AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 236) February 1989
Typical Foreign Technology Index Listing C Expenmental investigation of convergent elector nozzle/atterbody Jn wind tunnel p 8 A89-11060 CANADA Dynamic dlstorbon in flowfield downstream ot transonic Qualification and operational aspects of light weight shock-boundary layer interaction p 8 A89-11061 SKAD (light weight survival kit air droppable) A new approach to improvement of fans p 18 A89-10471 p8 A89-11064 Pocket calculator trend momtoring for gas turbine Steady state unbalance responses for a multrspan engines rotor p 50 A89-11066 ISAE 841461 ] p 34 A89-10614 INTELLECTUAL I A further improvement in the numerical method of A Canadian government _ook at airworthiness supersonic infinitesimal horseshoe vortex distribution ORIGIN I ISAE PAPER 880935j p 2 A89-12319 p 8 A89-11080 ___ COUNTRY OF I Phase 4 static tests of the J-97 powered, external augmentor V/STOL model at the NASA. Ames Research Investigation on wall interference of low-speed wind tunnel with slotted walls p 8 A89-11081 CANADA Center. November 1983 INASA-CR-1773951 p 14 N89-10028 Measurements of unsteady pressure distribution on a _Quaht,cahon and operabonal aspecls of hghl welghl A case for a unified hghtning threat NACA 0012 profile m transonic flow p 8 A89-11082 SKAD(.g.,*o,g,ts..... a,.,1a,,d,opp_b_) p 58 N89-t0447 The vapor-screen techmque of flow vlsuahzatlon m the Lightning tests to measure the bulk current levels intermittent transonic and supersonic wind tunnel associated with the electronic engine control of a turboprop p9 A89-11083 commuter transport p 21 N89-10457 Analys_s of transonic wLngs including viscous Etectrostahc discharge and field effects of electronics interaction p 9 A89-11084 systems p 52 N89-10493 Numerical simulation of corrl3act schemes in CHINA, PEOPLE'S REPUBLIC OF super-sonic viscous flows p 9 A89-11085 An _nvestigatlon of the pressure m an ejection seat bay Research on the computational method ol aerodynamic due to rocket jet p 26 A89-10482 characteristics of wing with vortex breakdown at high angle UMBER I The formation mechanism of the asymmetric spahal of attack p 9 A89-11086 vortex of slender bodies at high angle of attack Finite element method for calculahng transonic potential I SAE PAPER 872435l p 7 A89-10652 flow around airfoil from pressure minimum integration Unified computation method of unsteady p 9 A89-11088 Listings in this index are arranged alphabetically supersomc/hypersomc flow past two dimensional flat plate CZECHOSLOVAKIA and rectangular w{ngs by country of intellectual origin. The title of the A second-order numenca_ method for the analysis of I SAE PAPER 8724471 p 7 A89-10660 document is used to provide a brief description of two-dimensional flow of ideal fluid through a A study on effects of a_rcraft noise environment on its the subject matter. The page number and the ac- structure supersonsc input p 6 Numerical simulahon of steady transonic flow cession number are included in each entry to as- I SAE PAPER 8724501 p 28 A89-t0663 The study of the global stability of high performance 8-percent DCA cascade at a freestream Mach sist the user in locating the citation in the abstract of about I p 8 A89-11073 a_rcraft at high angles-or-attack section. If applicable, a report number is also in- ISAE PAPER 8724561 p 39 A89-10668 Expenence with the development of cluded as an aid in identifying the document. A frequency domain MIMO modal identification method engines p 37 A89-11074 with application in the aircraft ground vibralion test Control of the low-cycle service life of the I SAE PAPER 8724581 p 48 A89-10670 components of aircraft turbine engines according to A dynamic characteristic analysts of a bladed disk damage-tolerance concept p 37 A assembly p 36 A89-11026 An experimental investigation on the bistable behaviors of a flexible rotor-squeeze film damper system F AUSTRALIA p 49 A89-11028 The Australian Aviation Satellite System The bistable behavior of a rigid rotor w_th squeeze film FRANCE [SAE PAPER 8724201 p 24 A89-10642 damper p 49 A89-11029 AGARD manual on aeroelashcity in axial-flow MiNary aerospace technical development in Austraha A circular cone surface shaping method for fan blade turbomachmes Volume 2 Structural dynamics and !SAE PAPER 8724261 p I A89-10646 p 50 A89-11032 aeroelastlcfty Calculahon'bf compressible flow and heat transter on l AGARD-AG-298-VOL-21 p 13 N89-10006 Surveillance - H_gh-technology fit-out for the Nomad a rotating disk p 50 A89-11033 La Recherche Aerospatiale, Bimonthly Bulletin, Number aircraft Reduction of ejector noise with multihole nozzle 1987-4, 239/July-August I SAE PAPER 8724281 p 32 A89-10647 p 38 A89-11034 IESA-TT-t0881 p 14 N89-10026 Flow performance of reversed tandem cascades with Introduction of the Hornet - A success story Unsteady three-dimensional sial[ on a rectangular double-circular arc profile for compressor stator l SAE PAPER 8724361 p 27 A89-10653 wing p 14 N89-10027 p 7 A89-11036 Summary of mfhght data on lightning currents and A world leader in engineering and maintenance A data acquisition system for blade vlbrabon test fields p 56 N89-10449 ISAE PAPER 8724441 p 1 A89-10657 p 41 A89-11037 Analysis of recent in-flight lightning measurements on A design method Of 'wigglestrap' film-coohng Aeroelastlclty past, present and future different aircraft p 20 N89-10450 construction of flame tube p 50 A89-11039 ISAE PAPER 8724491 p 19 A89-10662 The SAFIR lightning monitoring and warning system, A jet thrust measurement method with gas composition apphcations to aerospace activities p 52 N89-10481 analysis p 36 A89-11040 Modern techmques for the control of RPV's Modelhng of common mode coupling between an aircraft Establishment of vanable vane regulation law I SAE PAPER 8724571 p 39 A89-10669 wing traversed by a lightning current and wiring installed p 36 A89-11044 Fatigue testing of full-scale all-composite aircraft _n that wing p 22 N89-10485 Bevel gear resonance failures in central gearing system wings Computing Systems Configuration for Highly Integrated ot an aeroengme p 50 A89-11046 I SAE PAPER 8724591 p 48 A89-10671 Guidance and Control Systems Applicahon of end-bend blade for enhancing surge [ AGARD-LS-1581 p3 N89-10831 A potential theory for the steady separated flow about margin p 36 A89-11051 A highly reliable computer for airborne applications an aerofoil section Approach to blade end-bend mechanism p 59 N89-10833 I ARL-AERO-R-t76t p 13 N89-t0005 p 36 A89-11052 Fhght mechanics and aerothermodynamic software Applicahon ot an artificial density scheme of potential Contamination of environmental control systems in I CNES-CT/DTi/MS/MN/0691 p 4 N89-10839 stream function method to desLgn of airfoil Hercules aircraft Invest_gation on of the flow around a backward facing p 7 A89-11053 !MRL-R-11161 p 29 N89-10040 step w_th spanwtse blowing Unsteady loading noise of Counter-rotating propeller ICERT-RF-OA-68/2259-AYDI p 17 N89-108;59 Shock tunnel studies of scramlet phenomena p 36 A89-11054 Flow around a delta wing with or without a canard (Phi iNASA-CR-181721 I p 38 N89-10045 Proptan design by propeller-nacelle interaction BA 60 deg) Part 2: Hydrodynamic visualizations =n Non-linear aerodynamic charactenstlcs obtained from analysis p 36 A89-11055 unsteady flow (pdchmg oscdlabons) the analysis of Bight-data Two-dimensional subsonic diffuser flow with uniform iONERA-BT-11/2891-AN-PT-2i p 17 N89-10860 IAR-004-5711 p 18 N89-10866 shear velocity prohle at inlet p 7 A89-11056 Experimental investigation of flow near a corner, part 2 Some stahshcal aspects of attrition studies Experimental study of rotating stall m single-stage axial I AD-A196665 I p 30 N89-10891 compressor p 8 A89-11059 I CERT-RT-OA-24/5025-AYD I p 17 N89-10861
D-1 GERMANY DEMOCRATIC REPUBLIC FOREIGN TECHNOL OG Y INDEX
Three d*mensional shear flow. Analysis of the flow in The high temperature oxidation behavior of the single New trial of vibration testing method a delta arrow wing with incidence angte crystal Ni-base alloy M002 rood wdh and without protective p 52 N89 11068 ICERT-RTS-OA-25/5025-AYDI p 17 N89-10864 coatings p 43 A89-11216 CAD wind tunnel test for half-cut model of Asuka Creep tests for slow and fast fatigue conddlOnS on HISSS - A higher-order panel method for subsonic and p 18 N89-11069 aluminum alloy specimens supersonic attached flow about arbdrary configurations ETS-V propagation experiments in Japan JREPT-M0-5352001 p 45 N89-11020 p 10 A89-11484 p 53 N89-11080 Study of three dimensional boundary layers on the front The prediction of transonic interference flow by means of a fuselage and at an air retake of a hybrid method p 10 A89-11487 ICERT-OA-22/5028-AYDI p 53 N89-11184 N Boundary layer transition Steady and unsteady potenhal flows around ICERT-OA-40/5018-AYDI p 53 N89-11187 axisymmetric bodies and ring airfoils p 11 A89-11489 NETHERLANDS Aircraft crashes on the runway: Development of a super A doublet point method for the calculation of unsteady Panel methods in aerodynamics - Some highlights element for nonlinear analysis of a beam propeller aerodynamics p 11 A89-11497 p 10 A89-1148t IREPT-87/561 p 54 N89-11286 Calculation of unsteady transonic flow about oscillating On the evaluation of aerodynamic influence wings by a field panel method p 11 A89-t 1498 coefficients p 11 A89-11496 A vortex-latt_ce method for the calculation of wing-vortex Design and evaluation of dynamic flight test G interaction in subsonic flow p 11 A89-11499 manoeuveres Approximation of free and bounded vortex sheets at IPB88-2107601 p 29 N89-10042 GERMANY DEMOCRATIC REPUBLIC delta-wings p 11 A89-11500 Digital recording of radar data in an aircraft The assurance of flight safety - A priority task in Civil A numencal estimation of the deforestation effects on I PB88-2095071 p51 N89-10212 aviation p 20 A89-12548 local climate in the area of the Frankfurt international Symmetric (and genenc) algorithms for height balanced GERMANY,FEDERAL REPUBLIC OF airport p 55 A89-t 1554 trees Investigations on high Reynolds number laminar flow The operation of modern air-space surveillance radars ICS-8711 i p59 N89-12332 airfoils p 4 A89-10102 p 51 A89-12151 Packaged fiber ophc gyros with high bias stability A_r-traffic flow management today p 24 A89-12152 p 46 A89-10121 Indirect effects on electronic and mechanical systems P Integrated redundant reference systems for flight control installed in carbon fibre compound aircraft structures and navigation wtth skewed sensor arrangement p 22 N89-10492 POLAND p 30 A89-10129 Computing system configuration for fighter aircraft flight A subsonic panel method for design of 3-dimensional State of the art inertial navigation - Flight teshng of the control systems p 40 N89-10832 complex configurations with specified pressure Honeywell LINS Standard Navigator H-423 Investigation of wake vortices of landing alrcrafl at distribution p 28 A89 11491 p 30 A89 10131 Frankfurt airport (Federal Republic of Germany) Laser conlrol of VlSiblhty and cloud-base height in airfield An reverse, subsonic two-dimensional panel method IDFVLR-MITT-88-151 p 17 N89-10862 regions p 50 A89-11860 following the method of smallest quadrafe for the design and moddicafion o( multiple element profiles S I DGLR PAPER 87-061 I p 5 A89 10509 I Study of the engine influence on wings with modern SAUDI ARABIA high-bypass propulsion concepts INDIA I DGLR PAPER 87 0631 p 5 A89-10510 Control of autorotational characteristics of light-airplane Noise field of a propeller with angular inflow Transition recognition _n a_rcraft wing profiles with the fuselages p 39 A89-12555 p59 A89-11102 SOUTH AFRICA, REPUBLIC OF aid of piezoelectric sheetings GENMAP - Computer code for mission adaptive profile I DGLR PAPER 87-0651 p 47 A89-10512 generation p 12 A89-12566 Lessons learned from an operational engine monitoring Profile development results for advanced Tests on 3 NACA 0012 airfoil models of DFVLR in the system and their correlation with future developments clrculahon-gu*ded rotor systems in fast helicopters NAL 03 tunnel: An assessment of 2-D wall interference ISAE 8717331 p34 A89-10618 SPAIN IDGLR PAPER 87-0861 p 5 A89-10513 tTM-AE-87051 p 15 N89-10847 Improvement of a design code for airfoils at transonic Comparison of longitudinally stabilized behavior in INTERNATIONAL ORGANIZATION vertical turbulence between a modern canard configuration Should technology assist or replace the pilot'_ regime and a conventional aircraft I SAE PAPER 8807741 p 57 A89-10593 I DGLR PAPER 87-064 I p 5 A89-1051 t SWEDEN IDGLR PAPER 87-0781 p 39 A89-10515 ISRAEL Swedish Symposium on Residual Stresses, Sunne, Application of winglets wdh integrated, adjusted On the pamng process in an excited, plane, turbulenf Sweden, Mar 30*Apr 2, 1987, Proceedings trailing-edge flaps m a general aviation aircraft mixing layer p 47 A89-10173 ITALY p 46 A89-10096 I DGLR PAPER 87-080l p 26 A89-10516 Origin, obiecfives and achvlhes of the Department of Fatigue life influence of residual stresses from cold Configuration optimization of commercial aircraft Aerospace Engineenng p 3 N89-10830 working and high spectrum loads in aircraft structural I DGLR PAPER 87-081 I p 26 A89-10517 design p 46 A89-10099 fs 32 A spht-Fowler ghder problem presentahon and Transonic computations about complex configurations solutions J using coupled inner and outer flow equations I DGLR PAPER 87-0821 p 26 A89-10518 p 12 A89-12553 Aspects of the control and stabilization of supersonic JAPAN Finite difference analysis of external and internal commercial aircraft Three-dimensional boundary layer transition on a hghtning response of the JAS39 CFC wing IDGLR PAPER 87 1221 p 39 A89 f0519 concave-convex curved wall p 4 A89-10167 p 22 N89 1O483 Development of a helicopter slmulahon program A numerical solution of transonic flow using I DGLR PAPER 87-1231 p 26 A89-10520 discontinuous shock relation p 6 A89-10542 U Navigation of aircraft with rigid image-forming sensors Flow past circular cyhnder of finite length placed on I DGLR PAPER 87-130i p 31 A89-10521 ground plane p 48 A89-10543 An experimental study on aerodynamic performance of U,S.S.R. Automated landing approach using machine seeing Lippisch-type GEW p 6 A89-10544 Suppression of unstable oscdlations in a boundary I DGLR PAPER 87-131 I p 23 A89-10522 Analytical and experimental research on aerodynam,cal layer p 5 A89-10171 Preconditions for G PS mslallahon - Receivers in effects of w_nd shear on a_rcraft p 6 A89-10547 Operating safety of automatic obiects differential operation for landing mrcraft in general A numerical simulahon of separated flow around p 49 A89-10714 aviation two-dimensional wing by a discrete vortex method Fire safety at ciwl airports p 19 A89-10718 I DGLR PAPER 87-1321 p 23 A89-10523 p 6 A89 10568 Fundamentals of flight safety p 19 A89-I0721 Research on satellite-to-mrcraft srgnal communication Numerlca_ experiments for separalion flows around Laser nawgahon equipment p 24 A89-10722 I DGLR PAPER 87-1331 p 23 A89-10524 trapezoidal cylinders by a discrete vorlex method A study of the accuracy of wing calculations based on The 'Pneumatic Wind Shear Sensor' (PWSS) - An aid p 6 A89-10569 ddferent schemes p 49 A89-10774 to flight path regulation and to disturbance magnitude Numerical approach of advanced turboprop with Heat transfer in the recirculating region formed by a identification in shear wind situations three-dimensional Euler equations backward4acmg step p 51 A89-12282 I DGLR PAPER 87-1341 p 31 A89-10525 I SAE PAPER 8724481 p 7 A89-I0661 Effect of protechve coahngs on life of heat-resistant Shear wind measurements aboard a Piper PA 18 and Measurement of aerodynamic characteristics of a nickel steel under cyclic heat load p 45 N89-11005 UNITED KINGDOM the design of a model glider aircraft for dynamic gliding hang-ghder-w,ng by ground run tests using a test vehicle flight INAL-TR-9531 p 13 N89-10004 M_crostructural optimisation of titanium alloys for defect I DGLR PAPER 87-135/11 p 26 A89-10526 Funchonal mock-up tests of the fhght control system tolerance in gas turbine engine components Computer program for simulating dynamic gliding flight of the NAL QSTOL research aircraft: Planning and p 43 A89-10069 IDGLR PAPER 87-135/21 p 27 A89-10527 mechanical system test Ophmizahon of the conceptual design and mission profiles of short-haul aircraft p 25 A89-10107 Aspects of increasing economy uslrlg future low power I NAL TR-944 I p40 N89-10047 Thick alrlod at low Reynolds 'number and high a,rcraft propulsion systems Stahshcs of hghlnmg interachon with a_rcraft in Japan incidence p 4 A89-10116 I DGLR PAPER 87-1001 p 33 A89 10528 p 55 N89-10430 Generahon of a grid for a finite ddference calculation Cost-effechve strapdown INS design and the need for The history of aircraft onboard equipment of flows around an aircraft ,n Cartesian coordinates standard fhght profiles p 30 A89-10128 I DGLR PAPER 87-054 I p31 A89 10536 INAL TR 9561 p 58 N89-10863 Turbulent boundary layer manipulation and modelling The nonngid airship of the Siemens-Schuckert Works Programming lechniques for high-speed processing on in zero and adverse pressure gradients I DGLR PAPER 87-0551 p 60 A89-10537 the supercomputer FUJITSU VP-system p 46 A89-10159 Aircraft dynamic stablhty - Developmental history INAL-TR-9151 p 58 N89-10568 The wall pressure fluctuations of modified turbulent aspects Cascade flow analysis by Nawer-Stokes equahon boundary layer with nblets p 47 A89 10163 I DGLR PAPER 87-0571 p 1 A89-10538 p52 N89-11065 The electrochemical erosion of serve valves by Influence of regeneration treatments on creep rupture Numerical simulation of transonic flow around Asuka phosphate ester fire-resistant hydraulic fluids lives of turbine blades p 43 A89-11214 p 18 N89-11067 p 48 A89-10573
D-2 FOREIGN TECHNOLOG Y INDEX UNITED KINGDOM
RB211 developments /SAE PAPER 8724091 p 35 A89-10635 Health and usage monitoring - The integrated approach !SAE PAPER 8724451 p 32 A89-10658 Active control of reheat buzz p 43 A89-11103 Tornado - The first eight years p 2 A89-11450 Finite element Eule_ computations in three dimensions p 11 A89-12130 4 Aerothermodynamlcs - The required tools I SAE PAPER 8809281 p 12 A89-12316 HOTOL Command and Control Systems I SAE PAPER 8809291 p 42 A89-12317 New concepts in hehcopter machinery prognostics p 2 A89-12408 Implementation of knowledge-based systems for helicopter machinery fault prognosis p 2 A89-12412 Air navigation systems. I - Astronomical navigation in the air 1919-1969 p 24 A89-12449 Bird hazards in awation; Proceedings of the Symposium, London. England, Oct 14, 1987 p 3 A89-12716 The civil aviation birdstrike record p 20 A89-12717 Bird hazards in aviation - The RAF view p 20 A89-12718 Design and testing for aarframes p 29 A89-12719 Windscreen design and testing p 29 A89-12720 Bird hazards in aviation - Safety and economic Fmplications for an alrhne p 20 A89-12721 Bird hazards m aviation - The regulatory authoritys responsibilities p 20 A89-12722 The work of the Aviation Bird Unit p 3 A89-12723 Aerospace systems and technology: The rote of the RAE I RAE-TR-880421 p 3 N89-10003 _srael Air Force (IAF) in-service aircraft lightning strike and damage survey p 55 N89-10431 A filamentary method for calculating induced voltages within resistive structures in elther the frequency or tirne domain p 52 N89-10484 The use of the complex summation method for formulating algorithms for decoupling vertical/honzontal motions of rolling aircraft p 30 N89-10889
D-3 CONTRACT NUMBER INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 236) February 1989
Typical Contract Number Index Listing
NAS1-16794 ...... p 25 A69-10109 NAS1-17317 ...... p 5 A89-10192 NAG 1-724 p 44 N89-I0125 NAS1-17748 ...... p 21 N89-10451 p 21 N89-10454 NAS1-17921 ...... p 59 A89-12563 NASl-18000 ...... p 4 A89-10108 p 59 N89-10601 NASl-18304 ...... p 54 N89-11196 NAS2-11665 ...... p 39 N89-10046 NAS2-11853 ...... p 40 N89-10058 p 58 N89-10526 NAS3-22761 ...... p 51 A89-t2752 NAS3-23039 ...... p 14 N89-10025 NAS3-24222 ...... p 59 A89-10112 NAS3-25140 ...... p 54 N89-11192 NCC1-22 ...... p 14 N89-10029 Listings in this index are arranged alpha-numeri- NCC1-90 ...... p ,44 A89-12759
cally by contract number. Under each contract NCC2-225 ...... p 41 A89-12560 NCC2-383 ...... p 42 N89-10900 number, the accession numbers denoting docu- NCC2-486 ...... p 24 A89-12404 ments that have been produced as a result of NSG-4028 ...... p 25 A89-10101 research done under the contract are arranged in N00014-83-K-0239 ...... p 4 A89-10106 N00014-85-K-0412 ...... p 47 A89-10173 ascending order with the AIAA accession numbers STPA-437103/79 ...... p 45 N89-11020 appearing first. The accession number denotes STPA-85-95-004 ...... p 17 N89-10861 the number by which the citation is identified in p 17 N89-10864
the abstract section. Preceding the accession T12-02Z ...... p 56 N89-11356 W-7405-ENG-48 ...... p 44 N89-10167 number is the page number on which the citation 323-53-6X ...... p 42 N89-10111 may be found. 505-01-51 ...... p 23 N89-10872 505-43-01 ...... p 14 N89-10028 505-60-01-02 ...... p 13 N89-10020 AEROSPATIALE- 11-000639 ...... p53 N89-11184 505-60-21-01 ...... p 15 N89-10842 AEROSPATIALE-21-003395 ...... p 17 N89-10859 505-60-21-02 ...... p 14 N89-10029 AF AFOSR-0075=84 ...... p 44 N89-10161 505-61-01-01 ...... p 14 N89-10034 p 54 N89-11196 AF PROJ 2306 ...... p 44 N89-10161 505-61-01-02 ...... p 41 N89-10060 AF PROJ. 2307 ...... p 53 N89-1t189 505-61-51-10 ...... p 40 N89-10059 AF-AFOSR-0082-86 ...... p 53 N89-11189 505-61-71-05 ...... p 13 N89-10024 AF-AFOSR-86-0323 ...... p 47 A89-10173 505-61-71 ...... p 13 N89-10017 BMFT-LFL-8530/7 ...... p 23 A89-10523 p 15 N89-10849 BMFT-T/RF-41/FOO13/G2232 .... p 5 A89-10513 505-62-OK ...... p 44 N89-10156 DA PROJ 1L1-62209-AH-76 ...... p 44 N89-10156 505-62-21 ...... p 14 N89-10025 DAAG29-83-K-0050 ...... p 5 A89-10192 p 15 N89-10844 DAAG29-83-K-0133 ...... p 12 A89-12554 505-62-61 ...... p 16 N89-10858 DAAG29-85-K-0228 ...... p 12 A89-12554 505-62-81-61 ...... p 38 N89-10045 DAAL03-67-K-0022 ...... p 5 A89-10192 505-63-01-05 ...... p 44 N89-10951 DE-AC04-76DP-00789 ...... p 15 N89-10840 505-63-16 ...... p 38 N89-10043 p 15 N89-10841 505-63-51-07 ...... p 59 N89-10601 p 42 N89-10898 505-66-21-03 ...... p 58 N89-10524 p 42 N89-10899 535-03-01 ...... p 60 N89-10603 p 53 N89-11155 p 17 N89-10865 DE-AC05-84OR-21400 ...... p 42 N89-10901 763-01-21 ...... p 43 N89-10123 DOT-FA01-82-Y-10513 ..... p 54 A89-11221 DOT-FA71NA-AP-98 ...... p 38 N89-10892 DRET-85-003 ...... p 54 N89-11286 DRET-87-002-018 ...... p 53 N89-11187 DTFA01*80-C-10093 ...... p 25 N89-10885 DTFA01-87-C-00014 ...... p 23 N89-10869 DTFA03-84-C-00066 ...... p 21 N89-10459 DTFA03-86-C-0050 ...... p 38 N89-10894 DTFA03-87-C-00013 ...... p 54 N89-11265 F33615-85-C-3013 ...... p 18 N89-10867 F49620-82-C-0035 ...... p 50 A89-11251 F49620-84-C-0065 .... p 9 A89-11115 F49620-85-C-0080 ...... p 47 A89-10181 NAGW-478 ...... p 11 A89-12130 NAGW-674 ...... p 38 N89-10045 NAG1-344 ...... p 4 A89-10105 NAG1-648 ...... p 10 A89-11153 p 11 A89-11488 NAG1-724 ...... p 44 N89-10125 NAG 1-836 ...... p 30 N89-10890 NAG2-111 ...... p 16 N69-10855 NAG2-198 ...... p 16 N89-10855 NAG2-244 ...... p 40 N89-10895 NAG2-245 ...... p 9 A89-11106 NAG2-373 ...... p9 A89-11110 NAG3-201 ...... p 51 A89-12337 NAG3-363 ...... p 37 A89-12307 NAG3-645 ...... p 9 A89-11110 NAG3-665 ...... p 12 A89-12557 NASW-2797 ...... p 14 N89-10D28 NASW-4003 ...... p 41 N89-10897 IE-1 REPORT NUMBER INDEX
II
AERONAUTICAL ENGINEERING/A Continuing Bibliography (Supplement 236) February 1989
• /pical Report Number Index Listing CNES-DLA/SDT/ED/SA ...... p 4 N89-10839 # ETN-88-93107 ...... p 53 N89-11184 # ETN-88-93111 ...... p 17 N89-10860 # ETN-S8-93113 ...... p 17 N89-10861 # CONF-860818-2 ...... p 15 N89-10840 # ETN-88-93140 ...... p 3 N89-10003 # CONF-860836-1 ...... p 15 N89-10841 # ETN-88-93183 ...... p 17 N89-10862 # N89-10901 # ACCESSION I ON E CONF-8809108-1 ...... p 42 ETN-88-93319 ...... p 17 N89-10864 # ETN-88-93320 ...... p 53 N89-11187 # N89-12332 # ,,,,, ICS-8711 ...... p59 ETN-88-93321 ...... p 45 N89-11020 # ETN-88-93356 ...... p 59 N89-12332 # N89-I0891 # NASA-CR 163247 CSB-MEMO-3 ...... p 30 FAA-AMS-420 ...... p 4 N89-11691 # DERAT*22/5025-16 ...... p 53 N89-11184 # N89-10861 # DERAT-24/5025-14 ...... p 17 IS8N-92-835-0464- X ...... p 3 N89 10831 # N89-10864 # .89.1o,ooi, DERAT-25/5025-14 ...... p 17 ISBN-92-835-0467-4 ...... p 13 N89 10006 # DERAT-40/5018-24 ...... p 53 N69-11187 # N89-10859 # DERAT-52(5004-23 ...... p 17 ISSN-0176-7739 ...... p 17 N89-10862 # ISSN-0369-4010 ...... p 13 N89-10004 # N89-10840 # DE88-000349 ...... p 15 ISSN-0389-4010 ...... p 40 N89-10047 # Listings in this index are arranged alpha-numeri- N89-10841 # DE88-006867 ...... p 15 ISSN-0389-4010 ...... p 58 N89-10563 # N89-10898 # cally by report number. The page number indicates DE88-012108 ...... p 42 ISSN-0389-4010 ...... p 58 N89-10565 # the page on which the citation is located. The DE88-012748 ...... p 42 N89-10899 # N69-10901 # accession number denotes the number by which DE88-014557 ...... p 42 L-16397 ..... p 58 N89-10524 " # DE68-015407 ...... p 44 N89-10167 # N89-10024 ° # the citation is identified. An asterisk (*) indicates L- 16428 ...... p 13 L-16430 ...... p 15 N89-10842 * # N89-10862 # that the item is a NASA report. A pound sign (#) DFVLR-MITT-88-15 ...... p 17 L-16469 ...... p 13 N89-10020 " # indicates that the item is available on microfiche. DGLR PAPER 87-054 ..... p 31 A89-10536 LR-497 ...... p 29 N89-10042 # DGLR PAPER 67-055 ...... p 60 A89-10537 DGLR PAPER 87-057 ...... p 1 A89-I0538 A-87093 ...... p 23 N89-10872 " # MRL-R-1116 ...... p29 N89-10040 # DGLR PAPER 87-061 ..... p 5 A89-10509 A-88008 ...... p 15 N89-10849 " # A89-10510 A-88020 ...... p 13 N89-10022 " # DGLR PAPER 87-063 ...... p 5 NAL-TR-915 ...... p 58 N69-10565 # DGLR PAPER 67-064 ...... p 5 A89-10511 A-88072 ...... p 13 N69-I0017 * # NAL-TR-944 ...... p 40 N89-10047 # A89-10512 DGLR PAPER 67-065 ...... p 47 NAL-TR-953 ...... p 13 N89-10004 # DGLR PAPER 87-078 ...... p 39 A89-10515 AD-A189863 ...... p 58 N89-10526 * # NAL-TR-956 ...... p 58 N89-10563 # DGLR PAPER 87-080 ...... p 26 A89-10516 AD-A195489 ...... p 44 N89-10161 # DGLR PAPER 87-08t ...... p 26 A89-10517 AD-A196207 ...... p 38 N89-10044 # NAS 115:100039 ...... p 13 N89-10022 * # DGLR PAPER 87-082 ...... p 26 A89-10518 AD-A196456 ...... p 18 N89-10867 # NAS 1 15:100061 ...... p 13 N89-10017 * # DGLR PAPER 87-086 .... p 5 A89-10513 AD-A196626 ...... p 4 N89-11691 # NAS 1 15:100549 ...... p 44 N89-10951 * # DGLR PAPER 87-100 ...... p 33 A89-10528 AD-A196665 ...... p 30 N89-10891 # NAS 1.15:100657 ...... p 14 N89-10034 * # DGLR PAPER 87-122 ..... p 39 A89-10519 AD-A196820 ...... p 53 N89-11188 # NAS 1 15:100879 ...... p 16 N89-10858 " # DGLR PAPER 87-123 ...... p 26 A89-10520 AD-A196938 ...... p 53 N89-11189 # NAS 1 15:100944 . p 42 N89-I0111 # A89-10521 DGLR PAPER 87-130 ..... p 31 NAS 1 15101310 ...... p 44 N89-10156 # DGLR PAPER 87-131 ...... p 23 A89-10522 AFiT/CI/NR-88-99 ...... p53 N89,-11186 # NAS 1 15101322 .... p 36 N69-10043 # A89-10523 DGLR PAPER 87-132 ...... p 23 NAS 1 15101329 ...... p 60 N89-10603 # DGLR PAPER 87-133 ...... p 23 A89-10524 AFOSR-88-0457TR p 44 N89-10161 # NAS 1 15:101386 ...... p43 N89-10123 # DGLR PAPER 87-134 ...... p 31 A89-10525 AFOSR-88-0637'TR ..... p 53 N89-11189 # NAS 1 15101491 ...... p 41 N89-10060 # DGLR PAPER 87-138/1 ...... p 26 A89-10526 NAS 1 18101496 p 40 N89-10059 # DGLR PAPER 87-135/2 .... p 27 A89-10527 AFWAL-TR-87-3098-PT- 1 p 18 N89-10867 # NAS 1 15:4027 ...... p 58 N89-10524 # AFWAL-TR-88-2020 . p 38 N89-10044 # NAS 1 15:4062 ...... p 15 N89-10842 * # DODA-AR-005-257 ...... p 30 N89-10891 # NAS 1.15:88969 ...... p 17 N89-10865 * #
AGARD-AG*298-VOL-2 ..... p 13 N69-10006 # NAS 1 15:89425 ...... p 23 N89-10872 " # DOT/FAA/CT-86/30-REV . p 40 N89-10058 * # NAS 126:177395 ...... p 14 N89-10028 * # DOT/FAA/CT-86/34 p 58 N89-10526 * # NAS 126:177477 ..... p 39 N89-10046 * # AGARD-LS- 158 ...... p 3 N89-10831 # N89-11265 # OOTIFAAICT-87/26 .... p 54 NAS 1.26:180900 ...... p 54 N89-11192 * # DOT/FAA/CT-87/37 .... p 38 N89-10894 # AIAA PAPER 87-2491 ...... p 42 A89-11119 # NAS 126:181175 ...... p 44 N89-10125 * # DQT/FAA/CT.66/05 ...... p 44 N89-10179 # AIAA PAPER 88-2528 ...... p 41 A89-12550 * # NAS 1 26:181692 ...... p 59 N89-10601 " # DOT/FAA/CT*6B/13 ...... p 44 N89-10175 # NAS 126:181721 ...... p 38 N89-10045 ° # DOT/FAA/CT-88/16 ...... p 29 N89-10041 # N89-10058 * # AIAA-PAPER-88-2535 p 14 N89-10034 * # NAS 126:182741 ...... p 40 DOT/FAA/CT-88/23 ...... p 38 N89-10892 # NAS 1.26:162746 ...... p 58 N89-10526 * # DOT/FAA/CT-88/6 ...... p 56 N89-11356 # AIAA-88-3155 ...... p 38 N89-10043 * # NAS 1.26:163057 ...... p 41 N89-10897 " # NAS 1 26:183245 ...... p 40 N89-10895 * # DOT/FAA/DS-88/11 ...... p 25 N89-10038 # AR-004-571 ...... p 18 N88-10866 # NAS 1.26:183247 ...... p 42 N89-10900 * # DOT/FAA/DS-88/6 . . p 23 N89-10869 # AR-004-596 ...... p 13 N89-10005 # NAS 1 26:183305 ...... p 30 N89-10890 ° # N89-10025 * # AR-005-230 ...... p 29 N89-10040 # NAS 1.26:4147 ...... p 14 DOT IFAAI PS-88114 ...... p 56 N89-11356 # NAS 1 26:4185 ...... p 14 N89-10029 ° # N89-11196 * # ARL-AERO-R-176 ...... p 13 N89-I0005 # NAS 1 26:4193 ...... p 54 ...... N89-10885 # DOTIFAA/SA-88/2 p 25 NAS 155:10008 ...... p 15 N89-10849 * # N89-10024 ° # ARL AERO-TM-390 ...... p 18 N89-10866 # NAS 160:2828 ...... p 13 E-3437 ...... p 17 N89-10865 * # NAS 1.60:2846 ...... p 15 N89-10844 " # E-4085 ...... p 14 N89-10025 ° # N89-10020 " # AVSCOM-_M-88-B-014 ..... p 40 N89-10059 " # NAS 1 60:2648 ...... p 13 E-4113 ...... p16 N89-10858 # AVSCOM-TM-88-B-015 ...... 13 44 N89-10951 " # N89-10844 # E-4183 ...... p 15 NASA-CP- 10008 ...... p 15 N89-10849 * # E-4232 ...... p 42 N69-I0111 # N89-10043 # CERT-OA-22/5025-AYD .... p 53 N89-11184 # E-4260 ...... p 38 NASA-CR-177395 ...... p'14 N89-10028 " # N89-10156 # CERT-OA-40/5018-AYD ...... p 53 N89-11187 # E-4301 ...... p 44 NASA-CR-177477 ...... p 39 N89-10046 * # N89-10603 # E-4340 ...... p 60 NASA-CR-180900 ...... p 54 N89-11192 ? # E-4445 ...... p 43 N89-10123 " # CERT-RF-OA-68/2259-AYD ...... p 17 N89-10859 # NASA-CR-181175 ...... p 44 N89-10125 ° # NASA-CR- 181692 ...... p 59 N89-10601 * # N89-10026 # ESA-TT-1088 ...... p 14 NASA-CR-161721 ...... p 38 N89-10045 " # CERT-RT-OA-24/5025-AYD ...... p 17 N89-10861 # NASA-CR-182741 ...... p 40 N89-10058 * # ETN-88-93051 ...... p 14 N89-10026 # NASA-CR- 182746 ...... p 58 N89-10526 " # CERT-RTS-OA-25/SO25-AYD p 17 N89-10864 # ETN-88-93094 ...... p 4 N89-10839 # N89-10897 * # ETN-88-93101 ...... p 54 N89-11286 # NASA-CR-183057 ...... p 41 N69-10859 # NASA-CR-163245 ...... p 40 N69-10895 * # CNES-CT/DTI/MS/MN/069 ..... p 4 N89-10839 # ETN-68-93105 ...... p 17
F-1 • NASA-OR-183247 REPORT NUMBER INDEX
NASA CR-183247 ..... p 42 N89-10900 • # SAE PAPER 872444 ...... p 1 A89-10657 NASA CR.183308 p 30 N89 10890 • # SAE PAPER 872445 .... p 32 A89-10658 NASA CR-4147 p 14 N89-10025 • # SAE PAPER 872448 p 7 A89-10659 " NASA CR 4185 .... p 14 N89-10029 • # SAE PAPER 872447 . p 7 A89q0660 NASA-CR-4193 ...... p84 N89-11196 • # SAE PAPER 872448 ...... p 7 A89-10661 SAE PAPER 872449 ...... p 19 A89-10662 NASA-TM-100039 p 13 N89-10022 # SAE PAPER 872450 ...... p 28 A89-10663 NASA TM-100061 p 13 N89-10017 # SAE PAPER 872456 ...... p 39 A89-10668 NASA-TM 100549 ...... p 44 N89-10951 # SAE PAPER 872457 ...... p 39 A89-10669 NASA TM 100657 .... p 14 N89-10034 # SAE PAPER 872458 ...... p 48 ,A89 10670 NASA-TM-100879 ..... p 16 N89-10858 # SAE PAPER 872459 ...... p 48 A89-10671 NASA-TM- 100944 p42 N89-10111 # SAE PAPER 872481 ...... p 48 A89-10677 NASA-TM-101310 p44 N89-10156 # SAE PAPER 872488 ...... p 48 A89-10683 NASA TM.101322 p 38 N89-10043 # SAE PAPER 872494 ...... p 49 A89-10686 NASA TM-101329 p 60 N89-10603 # SAE PAPER 872496 ...... p 49 A89-10687 NASA TM-101386 p 43 N89-10123 # SAE PAPER 872497 ...... p 49 A89-10688 NASA TM-101491 p 41 N89-10060 # SAE PAPER 872499 ...... p 2 A89-10689 NASA-TM 101496 .... p40 N89-10059 # SAE PAPER 872501 ...... p 42 A89-10691 NASA-TM 4027 ...... p 58 N89-10524 # SAE PAPER 872502 ...... p 32 A89-10692 NASA-TM-4062 ...... p 15 N89-10842 # SAE PAPER 880625 ...... p 37 A89-12307 * NASA-TM-88969 ...... p 17 N89-10865 # SAE PAPER 880626 p 51 A89-12308 * NASA-TM-89425 ...... p 23 N89-10872 # SAE PAPER 880774 ...... p 57 A89-10593 SAE PAPER 880928 p 12 A89-12316
NASA-TP-2828 p 13 N89 10024 • # SAE PAPER 880929 ...... p 42 A89-12317 NASA TP-2846 p 15 N89-10844 • # SAE PAPER 880935 ..... p 2 A89-12319 NASA TP 2848 ...... p 13 N89-10020 • # SAE PAPER 880936 ...... p 2 A89-12320 SAE PAPER 880943 .... p 32 A89-12321 NLR MP 86057.U p 51 N89 10212 # SAE PAPER 880945 p 2 A89-12322 "
NOAA TM-ERL-ESG-30-VOL 3 p 56 N89-10499 # SAE SP-728 .... p 33 A89-10613
NTSB/AAB.88/03 ...... p20 N89 10036 # SAE 841461 ...... p 34 A89 1O614 NTSB/AAB 88/05 ...... p 20 N89-10035 # SAE 841462 ...... p 34 A89-10615 NTSB/AAB-88/06 p23 N89-10871 # SAE 871730 .... p 34 A89-10616 SAE 871732 ...... p 31 A89-10617 NTSB/AAR 88/02 SUMM ..... p 22 N89-10868 # SAE 871733 ...... p 34 A89-10618 NTSB/AAR 88/07 ...... p 23 N89-10873 # SAE 871735 ...... p 34 A89-10619 SAE 871736 ...... p 34 A89-10620 ONERA RT 11/2891-AN PT-2 ..... p 17 N89-10860 # SAE 871737 ...... p 34 A89-10621
PB88 197439 ...... p55 N89-10429 # SAND-87-2034 ...... p 42 N89-10898 # PB88 205489 p 56 N89-10499 # SAND.87-3011C ...... p 15 N89-10840 # PB88-209507 ...... p 51 N89-10212 # SAND-88-0021C ...... p 15 N89-10841 # PB88 210760 p 29 N89.10042 # SAND-88.0497 ...... p 42 N89-10899 # PB88 910407 p22 N89-10868 # PB88-910409 p23 N89-10873 # TM-AE-8705 ...... p 15 N89-10847 # PB88 916903 ...... p 20 N89-10036 # PB88 916908 p 20 N89-10035 # UCID.21385 ...... p 44 N89.10167 # PB88-916906 p 23 N8!)-10871 # USAAVSCOM.TR-8/.A-13 p 39 N89-10046 " # PSU ME R 87/88 0031 p53 N89-11189 #
RAE DR/55/07 ...... p 3 N89-10003 #
RAE TR RR042 ...... p 3 N89.10003 #
REPT M0 535200 p 45 N89 11020 #
REPT 3011 01 03 4675 p 25 N89-10885 # REPT-437103/79 p 45 N89-11020 # REPT-87/56 p 54 N89-11286 #
SAE AIR 1528 p 35 A89 10622 SAE AIR 1839 ...... p 35 A89-10623 SAE AIR 1871B p 35 A89-10624 SAE AIR 1872 ...... p35 A89-10628 SAE AIR 1873 p 35 A89-10626
SAE P-205 ..... p 48 A89-10676 RAE P-208 ...... p 1 A89-10627
SAE PAPER 821555 p 19 A89-10684 SAE PAPER 871750 p 23 A89-10880 SAE PAPER 871751 p 24 A89-10581 SAE PAPER 871763 p 31 A89 10882 SAE PAPER 871789 p 57 A89 10584 SAE PAPER 871790 p 31 A89-10885 SAE PAPER 871804 p 57 A89.10589 SAE PAPER 872395 p 1 A89.10628 SAE PAPER 872400 p 1 A89 10629 SAE PAPER 872403 p 18 A89 10631 SAE PAPER 872405 p 27 A89 10632 SAE PAPER 872409 p 35 A89 10635 SAE PAPER 872410 p 35 A89 10636 SAE PAPER 872411 ..... p 35 A89 10637 SAE PAPER 872417 p 27 A89 10639 SAE PAPER 872418 ...... p 27 A89 10640 • # SAE PAPER 872419 p 27 A89 10641 SAE PAPER 872420 .... p 24 A89 10642 SAE PAPER 872426 .... p 1 A89 10646 SAE PAPER 872428 p 32 A89 10647 SAE PAPER 872434 ..... p 6 A89 10651 SAE PAPER 872435 ...... p 7 A89 10682 SAE PAPER 872436 ...... p 27 A89-10653 SAE PAPER 872441 ...... p 19 A89-16655 SAE PAPER 872443 ...... p 19 A89-10656
F-2 ACCESSION NUMBER INDEX
AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 236) February 1989
Typical Accession Number Index Listing A89÷10651 * p 6 A89-11426 p 50 A89-12723 p 3 A89-10652 p 7 A89-11447 p 28 A89-12752 * # p 51 A89-12759 * p 44 A89-10653 p 27 A89-11450 p 2 A89-10654 p 19 A89-11481 p 10 N89-10003 # p 3 A89-10655 p 19 A89-11484 p 10 N89-10004 # p 13 N89-10844 * # p 15 A89-10656 p 19 A89-11486 p 28 N89-10005 # p 13 A89-10657 p 1 A89-11467 p 10 N89-10006 # p 13 A89-10658 p 32 A89-11488 " p 11 -E_-I- N89-10012 # p 37 A89-10659 * p 7 A89-11489 p 11 N89-I0013 # p 37 A89-10660 p 7 A89-11491 p 28 N89-10014 # p 37 , ?1 A89-10661 p 7 A89-11496 p 11 N89-10015 # p 37 A89-10662 p 19 A89-11497 p 11 N89-10016 # p 51 A89-10663 p 28 A89-11498 p 11 N89-10017 * # p 13 A89-10668 p 39 A89-11499 p 11 N89-10020 * # p 13 A89-10669 p 39 A89-11500 p 11 N89-10022 * # p 13 A89-10670 p 48 A89-11554 p 55 N89-10024 " # p 13 A89-10671 p 48 A89-11559 p 28 N89-10025 * # p 14 Listings is this index are arranged alpha-numeri- A89-10676 p 48 A89-11680 # p 57 N89-10026 # p 14 cally by accession number. The page number A89-10677 p 48 A89-11748 p 57 N89-10027 # p 14 A89-10683 p 48 A89-11750 p 57 listed to the right indicates the page on which the N89q0028 * # p 14 A89-10686 p 49 A89-11760 p 57 citation is located. An asterisk (°) indicates that N89-10029 " # p 14 A89-10687 p 49 A89-11860 p 50 N89-10034 ° # p 14 the item is a NASA report. A pound sign (#) indi- A89-10668 p 49 A89-12130 * p 11 N89-10035 # p 20 cates that the item is available on microfiche. A89-10689 p 2 A89-12135 " p 12 N89 10036 # p 20 A89-10691 p 42 A89-12151 # p 51 N89-10038 # p 25 A89-10692 p 32 A89-12152 # p 24 N89-10040 # p 29 A89-10714 p 49 A89-12176 p 58 N89-10041 # p 29 A89-10718 p 19 A89-12252 p 51 N89-10042 # p 29 A89-10069 p 43 A89-t0520 p 26 A89-10721 p 19 A89-12276 * p 51 N89-10043 * # p 38 A89-10076 * p 45 A89-10521 p 31 A89-10722 p 24 A89-12307 * p 37 N89-10044 # p 38 A89-10091 " p 45 A89-10522 p 23 A89-10774 p 49 A89-12308 * p 51 A89-11026 # p 36 N89-10045 * # p 38 A89q0093 p 45 A89-10523 p 23 A89-12316 p 12 N89o10046 ° # p 39 A89-11028 # p 49 A89-12317 p 42 A89-10095 p 46 A89-10524 p 23 N89-100a7 # p 40 A89-10096 p 46 A89-11029 # p 49 A89-12319 p 2 N89-10058 " # p 40 A89-10099 # p 46 A89-10525 p 31 A89-11032 # p 50 A89-12320 p 2 N89-10059 " # p 40 A89-10101 * # p 25 A89-10526 p 26 A89-11033 # p 50 A89-12321 p 32 N89-10060 " # p 4_ A89-10102 # p 4 A89-I0527 p 27 A89-11034 # p 36 A89-12322 * p 2 N89-10111 "# p42 A89-10103 * # p 38 A89-10528 p 33 A89-11036 # p 7 A89-12330 * p 43 N89-10123 " # p 43 A89-10104 * # p 4 A89-10536 p 31 A89-11037 # p 41 A89-12337 * p 51 N89-10125 " _' p 44 A89-10105 * # p 4 A89-t0537 p 60 A89-11039 # p 50 A89-12401 p 2 N89-10156 " # p 44 A89-10106 # p 4 A89-10538 p 1 A89 11040 # p 36 A89-12402 # p 39 N89-10161 c p 44 A89-10107 # p 25 A89-10542 # p 6 A89-11044 # p 36 A89-12403 " # p 32 A89÷10108 ° # p 4 A89-10543 # p 45 N89-10167 _" p 44 A89+11046 # p 50 A89-12404 * # p 24 N89-10175 # p44 A89 10109 * # p 25 A89-10544 # p 6 A89q 1051 # p 36 A89q2405 # p 58 N89-10179 # p 44 A89-10111 # p 25 A89-10547 # p 6 A89-11052 # p 36 A89-12408 # p 2 N89-10212 # p 51 A89-10112 * # p 59 A89-t0568 # p 6 A89-11053 # p 7 A89-12409 # p 2 N89-10429 # :) 55 A89 10113 # p 25 A89-10569 # p 6 A89-11054 # p 36 A89-12410 # p 58 N89-10430 # :) 55 A89-10114 # p 4 A89-10573 p 48 A89-11055 # p 36 A89-12411 # p 32 N89-10431 ,_ _ 55 A89-10115 # p 41 A89-10580 p 23 A89-11056 # p 7 A89-12412 # p 2 N89-10432 _' t' 55 A89-10116 # p 4 A89-10581 p 24 A89-11059 # p 8 A89-12413 # p 55 N89-10438 " # # 55 A89-I0121 # p 46 A89-10582 p 31 A89-11060 # p 8 A89-12414 # p 24 N89-10443 _' p 55 A89-10128 # p 30 A89-10564 p 57 A89-11061 # p 8 A89-12415 # p 32 N89-10444 # p t 5 A89-10129 # p 30 A89-10585 p 31 A89-11064 # p 8 A89-12416 # p 28 N89-10447 # p 56 A89-10131 # p 30 A89-10589 p 57 A89-11066 # p 50 A89-12417 # p 39 N89-10449 # p 56 A89-10154 p 46 A89-t0593 p 57 A89-11073 p 8 A89-12449 p 24 A89-10607 p 6 N89-10450 # p 20 A89-10159 p 46 A89-1t074 p 37 A89-12537 p 3 A89-10613 p 33 N89-10451 * # p 21 A89-10160 * p 4 A89-11075 p 37 A89-12538 p 3 A89-10614 p 34 A89-10163 p 47 A89-11080 # p 8 A89-12539 p 19 N89-10452 # p 21 j A89-10615 p 34 A89-10167 p 4 A89-1108t # p 8 A89-12548 p 20 N89-10454 * # p 21 A89-10616 p 34 N89-10455 # p 21 A89-10171 p 5 A89-11082 # p 8 A89-12550 * # p 41 N89-10456 * # p 21 A89-10173 p 47 A89-10617 p 31 A89-11083 # p 9 A89-12551 * # p 12 N89-10457 # p 21 A89-10181 p 47 A89-10618 p 34 A89-11084 # p 9 A89-12552 * # p 12 N89-10459 # p 21 A89-10182 p 47 A89-10619 p 34 A89-11085 # p 9 A89-12553 # p 12 N89-10460 # p 22 A89-10192 * p 5 A89-10620 p 34 A89-11086 # p 9 A89-12554 # p 12 N89-10461 # p 22 A89-10261 p 47 A89-10621 p 34 A89-11088 # p 9 A89-12555 # p 39 N89-10470 # p 56 A89-10359 p 47 A89-10622 p 35 A89-11101 # p 59 A89-12556 * # p 39 N89-10474 # p 52 A89-10364 p 31 A89-10623 p 35 A89-11102 # p 59 A89-12557 * # p 12 N89-10478 * # p 22 A89-10463 p 25 A89-10624 p 35 A89-11103 # p 43 A89-12558 # p 28 N89-10481 # p 52 A89q0466 p 26 A89-10625 p 35 A89-11105 # p 9 A89-12559 # p 12 N89-10483 # p 22 A89-10471 p 18 A89_10626 p 35 A89-11106 *# p9 A89-12560 *# p41 A89-t0627 p 1 N89-10484 # p 52 A89-10475 p 18 A89-11108 * # p 9 A89-12561 * # p 59 N89-10485 # p 22 A89-10478 p 26 A89-10628 p 1 A89_11109 # p 9 A89-12562 * # p 28 N89-10490 # p 56 A89-10482 p 26 A89-10629 * p 1 A89-11110 * # p 9 A89-12563 * # p 59 A89-10631 * p 18 N89 10492 # p 22 A89-11115 # p9 A89-12564 # p28 A89-10509 p 5 A89-10632 p 27 N89-10493 # p 52 A89-11116 # p 10 A89-12565 # p 28 A89-10510 p 5 A89-10635 p 35 N89-10497 # p 52 A89-11119 # p42 A89-12566 # p12 A89-10511 p 5 A89-10636 p 35 N89-10499 # p 56 A89-10512 p 47 A89 11152 * p 10 A89-12716 p 3 N89-10524 * # p 58 A89_10513 p 5 A89-10637 * p 35 A89÷11153 ° p 10 A89-12717 p 20 A89-10639 p 27 N89-10526 * # p 58 A89-11157 p 10 A89-12718 p 20 A89-10515 p 39 A89-10640 * # p 27 N89-10563 # p 58 A89-11214 p 43 A89-12719 p 29 A89-10516 p 26 A89-10641 p 27 N89-10565 # p 58 A89-10517 p 26 A89-10642 p 24 A89-11216 p 43 A89-12720 p 29 A89-11221 p 54 A89-12721 p 20 N89-10601 * # p 59 A89-10518 p 26 A89-10646 p 1 N89-10603 * # p 60 A89-10519 p 39 A89-10647 p 32 A89q 1251 p 50 A89-12722 p 20
G..1 N89-10830 ACCESSION NUMBER INDEX
N89-10830 # p 3 N89-10831 # p 3 N89-10832 # p 40 N89-10833 # p 59 N89-10834 # p 33 N89-10835 # p 33 N89-10836 # p 33 N89-10837 # p 59 N89-10839 # p 4 N89-10840 # p 15 N89-10841 # p 15 N89-10842 *# p 15 N89-10844 " # p 15 N89-10847 # p 15 N89-10849 * # p 15 N89-10850 * # 15 N89-10852 * # 16 N89-10853 *# 16 N89-10854 * # 16 N89-10855 *# 16 N89-10856 ° # 60 N89-10857 *# 16 N89-10858 "# 16 N89-10859 # 17 N89-10860 # 17 N89-10861 # 17 N89-10862 # 17 N89-10864 # 17 N89-10865 * # 17 N89-10866 # 18 N89-10867 # 18 N89-10868 # )22 N89-10869 # p 23 N89-10871 # p 23 N89-10872 * # p 23 N89-10873 # p 23 N89-10885 # p 25 N89-10887 p 29 N89-10889 p 30 N89-10890 * # p 30 N89-10891 # p 30 N89-10892 # p 38 N89-10894 # p 38 N89-10895 * # p 40 N89-10896 # p 41 N89-10897 *# p 41 N89-10898 # p 42 N89-10899 # p 42 N89-10900 * # p 42 N89-10901 # p 42 N89-10951 * # D 44 N89-11005 # 3 45 N89-11020 # 3 45 N89-11065 # 3 52 N89-11067 # 3 18 N89-11068 # 3 52 N89-11069 # 3 18 N89-11077 * # 3 53 N89-11080 ° # 3 53 N89-11155 *# 3 53 N89-11184 # 3 53 N89-11187 # 3 53 N89-11188 # 3 53 N89-11189 # 353 N89-11192 *# 354 N89-11196 *# 354 N89-11265 # 54 N89-11270 54 N89-11286 # 54 N89-11356 # 3 56
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NOTE: Each additional delivery address on an order requires a separate shipping and handling charge. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (236)
4. Title and Subtitle 5. Report Date Aeronautical Engineering February 1989
A Continuing Bibliography (Supplement 236) 6. Performing Organization Code
7. Author(s) 8. Performing Organization Report No.
10. Work Unit No. 9. Performing Organization Name and Address
National Aeronautics and Space Administration 11. Contract or Grant No. Washington, DC 20546
13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address
14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
This bibliography lists 430 reports, articles and other documents introduced into the NASA scientific and technical information system in January, 1989.
17. Key Words (Suggested by Authors(s)) 18. Distribution Statement Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies
19. security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price * Unclassified Unclassified 122 A06/HC
• For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1989 FEDERAL REGION, AL DEPOSITORY UBRARIES
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