AERONAUTICAL ENGINEERING
A CONTINUING BIBLIOGRAPHY WITH INDEXES
(Supplement 242)
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 July 1989 in
Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA).
National Aeronautics and Space Administration Office of Management NASA Scientific and Technical Information Division Washington. DC 1989 This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A07. INTRODUCTION
This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 466 reports, journal articles and other documents originally announced in July 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 inckde the xiginal accessio:: 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 NTlS price schedules is located at the back of this bibliography.
iii TABLE OF CONTENTS
Page Category 01 Aeronautics (General) 437
Category 02 Aerodynamics 439 Includes aerodynamics of bodies, combinations, wings, rotors, and control sur- faces; and internal flow in ducts and turbomachinery.
Category 03 Air Transportation and Safety 460 includes passenger and cargo air transport operations; and aircraft accidents.
Category 04 Aircraft Communications and Navigation 465 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 467 Includes aircraft simulation technology.
Category 06 Aircraft Instrumentation 475 Includes cockpit and cabin display devices; and flight instruments.
Category 07 Aircraft Propulsion and Power 477 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 481 Includes aircraft handling qualities; piloting; flight controls; and autopilots.
Category 09 Research and Support Facilities (Air) 484 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tubes; and aircraft engine test stands.
Category 10 Astronautics N.A. 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 487 includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; propellants and fuels; and materials processing.
V Category 12 Engineering 490 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 499 Includes geosciences (general); earth resources and remote sensing; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography.
Category 14 Life Sciences N.A. Includes life sciences (general); aerospace medicine; behavioral sciences; rnan/system technology and life support; and space biology.
Category 15 Mathematical and Computer Sciences 499 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 501 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 N.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 N.A.
Subject Index ...... A-1 Personal Author Index ...... B-1 Corporate Source Index ...... C-1 Foreign Technology Index ...... D-1 Contract Number Index ...... E-1 Report Number Index ...... F-1 Accession Number Index ...... G-1 TYPICAL REPORT CITATION AND ABSTRACT
NASA SPONSORED 1 1- 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 264185) Avail NTlS HC A05/MF A01 -PRICE CODE COSATI CODE -CSCL 0 1 A x 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 winglbody 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 1 ON MICROFICHE ACCESSION NUMBER -A89-12562'# National Aeronautics and Space Administration. Langley Research Center, Hampton. Va. TITLE -EFFICIENT VIBRATION MODE ANALYSIS OF AIRCRAFT WITH MULTIPLE EXTERNAL STORE CONFIGURATIONS AUTHOR -M. KARPEL (NASA, Langley Research Center, Hampton, VA; Israel Aircraft Industries. Ltd.. Lod) Journal of Aircraft (ISSN 0021 -8669).-JOURNAL TITLE vol. 25, Aug. 1988, p. 747-751. refs A coupling method for efficient vibration mode analysis of aircraft with multiple external store configurations is presented. A set of low-frequency vibration modes, including rigid-body modes, represent the aircraft. Each external store is represented by its vibration modes with clamped boundary conditions. and by its rigid-body inertial properties. The aircraft modes are obtained from a finite-element model loaded by dummy rigid external stores with fictitious masses. The coupling procedure unloads the dummy stores and loads the actual stores instead. The analytical development is presented, the effects of the fictitious mass magnitudes are discussed, and a numerical example is given for a combat aircraft with external wing stores. Comparison with vibration modes obtained by a direct (full-size) eigensolution shows very accurate coupling results. Once the aircraft and stores data bases are constructed, the computer time for analyzing any external store configuration is two to three orders of magnitude less than that of a direct solution. Author
vii AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 242)
AUGUST 1989
01 A8933559 FALCONET TARGET RPV OPERATIONS SIMON F. DICKINSON (Flight Refuelling, Ltd., Wimborne, AERONAUTICS (GENERAL) England) IN: Remotely piloted vehicles; International Conference, 7th, Bristol, England, Sept. 12-14, 1988, Proceedings. Bristol, England, Univeisit-i of Biistol, !988, p. 9.: -3.1 1. Falconet is a British target-practice RPV employed at the Royal Artillery Range in the Hebrides, Scotland. The air vehicle is a A8932775 conventional low-wing monoplane with a single podded-installation DFVLR, ANNUAL REPORT 1987 [DFVLR, JAHRESBERICHT turbojet beneath the fuselage. The ground control system for 19871 Falconet has been designed to integrate the operation of the Cologne, DFVLR, 1988, 100 p. In German. No individual items target with existing tracking radars of the Royal Artillery Range. are abstracted in this volume. Both carousel and zero-length (rocket-assisted) takeoff systems The activities of the FRG aerospace research organization are available. Controllers that may be used encompass those for DFVLR in aeronautics, astronautics, and energy technology during the launch area, recovery area, visually-guided flight and 1987 are surveyed. Topics addressed include the computer-based radar-guided flight. The Falconet air vehicle’s structural components ATC planning and decision tool COMPAS, wind-tunnel tests on a are of modular type for ease of maintenance and repair. O.C. delta wing as part of the International Vortex Flow Experiment, mesoscale remote sensing of the atmosphere for meteorological A89-33560 applications, wind-tunnel testing of reentry bodies in the hypersonic CIVILIAN RPVS - EYE IN THE SKY OR PIE IN THE SKY? regime, renewable energy sources, and the organizational and A.M. CUDMORE, K. S. GIBSON, D. M. LUMBROSO, A. J. STOCKS, financial status of DFVLR. Extensive photographs, drawings, and and 1. D. TINSON (Southampton, University, England) IN: Remotely diagrams are provided, and an English summary is given for each piloted vehicles; International Conference, 7th, Bristol, England, section. T.K. Sept. 12-14, 1988, Proceedings. Bristol, England, University of Bristol, 1988, p. 11.1-11.10. A feasibility study has been conducted for a civilian-applications A8932982 observational sensor-platform RPV, designated the Southampton MATHEMATICAL RESEARCH AT THE AERONAUTICAL University Remotely Piloted Airborne Surveillance System RESEARCH LABORATORIES 19391960 (SURPASS), operating beyond visual range with a real-time video D. G. HURLEY (Western Australia, University, Nedlands, camera. This RPV for UK use would be designed to ensure that Australia) Australian Mathematical Society, Journal, Series B - the complex interactions inherent in any remote system are taken Applied Mathematics (ISSN 0334-2700), vol. 30. April 1989, p. fully into account. The SURPASS flight control system would be 389-413. refs similar to those of military RPVs, using ground radar tracking of A review of mathematical studies undertaken to support the vehicle and a combination of autopilot and ground-piloting on experimental work at the Australian Aeronautical Research the basis of telemetered sensor data. O.C. Laboratories during the first 20 years of their operation is presented. Topics addressed include wind-tunnel design and corrections, wood in aircraft construction, boundary-layer flow and turbulence, heat A8934448 GENERAL AVIATION transfer at low Reynolds numbers, stalling of thin wings, transonic MALCOLM L. RITCHIE (Ritchie, Inc., Dayton, OH) IN: Human airfoils, supersonics, vibrations, fatigue, and mathematical methods. factors in aviation. San Diego, CA, Academic Press, Inc., 1988, p. Diagrams, graphs, and typical flow visualizations are provided. 561-589. refs T.K. Human-factors analysis techniques are applied to characterize the general-aviation (GA) pilot, aircraft, and operational A8933555 environment. The focus is on the nonprofessional end of the GA THE U.S. NAVY UNMANNED AIR VEHICLE PROGRAM spectrum. Consideration is given to pilot skill level and skill EDWARD E. DAVIS (US. Navy, Naval Air Systems Command, maintenance, equipment costs, human performance in GA, the Washington, DC) IN: Remotely piloted vehicles; International GA cockpit (instrument flight capabilities, controls, and displays), Conference, 7th, Bristol, England, Sept. 12-14, 1988, Proceedings. GA performance variables (manipulative skills, information Bristol, England, University of Bristol, 1988, p. 1.1 -1.1 1. acquisition and processing, decision processes, input processes, The U.S. Navy’s progress to date in RPV development is and emergency operations), systems management (propulsion, discussed with a view to remaining problems in at-sea and shore communication, and cruise), in-flight correction of malfunctions, operations and the Navy’s role as part of the DoD Joint Service navigation tasks, and ATC-related tasks. Possible improvements RPV baseline design-development program, which is to result in in GA avionics based on personal computers and smart data links competitive procurement in 1990. Attention is given to the system are described. T.K. components of the already-operational Pioneer RPV, the installation of Pioneer RPVs aboard battleships, the status of the Amber A8934450 high-altitude/long-endurance RPV, the design requirements AIR TRAFFIC CONTROL formulated to date for the baseline midrange RPV concept, and V. DAVID HOPKIN (RAF, Institute of Aviation Medicine, the NATO ships-compatible Small Ship RPV development effort. Farnborough, England) IN: Human factors in aviation. San Diego, O.C. CA, Academic Press, Inc., 1988, p. 639-663. refs
437 01 AERONAUTICS (GENERAL)
The application of human-factors (HF) analysis techniques to A89-35377 the ATC task, equipment, and operational environment is discussed THE FUTURE OF THE CIVIL AVIATION INDUSTRY [LES in an introductory review. The evolution of HF research since the ENJEUX DE LA CONSTRUCTION AERONAUTIQUE CIVILE] 1950s is briefly recalled; the typical ATC tasks are listed and G. DELALANDE (Direction Generale de I'Aviation Civile, Paris, characterized; the problems of workstation design are outlined; France) L'Aeronautique et I'Astronautique (ISSN 0001-9275), typical controller selection and training procedures are described; no. 134, 1989, p. 19-23. In French. and particular attention is given to the factors leading to human The future character of the civil aviation industry is predicted error, the effects of workstation design on controller health, the based on current market trends and recent technological advances. problems of stress and boredom, the measurement of controller Areas of improvement for civil transport aircraft, regional transport workload and performance. and the impact of automation. It is aircraft, business aircraft, and helicopters are listed in order of pointed out that many changes in ATC technology are neither priority. Technological advances considered include improved motivated by HF concerns nor necessarily beneficial in the HF engine fuel consumption, improved modeling of engine sense. T.K. aerodynamics, the development of advanced materials, and flight control systems. R.R.
A89-34896# A89-35378 FAST, IN-SITU REPAIR OF AIRCRAFT PANEL COMPONENTS CIVIL-TRANSPORT AIRCRAFT AT AEROSPATIALE [LES S. DEHM and D. WURZEL (DFVLR, Stuttgart, Federal Republic of AVIONS DE TRANSPORT CIVIL A L'AEROSPATIALE] Germany) (ICAS, Congress, 15th, London, England, Sept. 7-12, C. TERRAZZONI (Aerospatiale, Division Avions, Toulouse, 1986, Proceedings. Volume 2, p. 836-843) Journal of Aircraft (ISSN France) L'Aeronautique et I'Astronautique (ISSN 0001-9275). 0021-8669). vol. 26, May 1989, p. 476-481. Previously cited in no. 134, 1989, p. 24-31. In French. issue 24, p. 3524, Accession no. A86-49066. The status and future of the Airbus and ATR civil aircraft programs are considered. Recent Airbus developments include an A8935100 increased flight range and the ability to carry more passengers. 8-2 - THE END OF THE LONG ROAD TOWARD A 'STEALTH Finite element calculations for studying linear and nonlinear BOMBER [E2 - EL FINAL DEL LARGO CAMINO HAClA EL phenomena and structural optimization problems are discussed. 'BOMBARDERO FURTIVO] Other topics reviewed include the reduction of maintenance costs, JOSE ANTONIO MARTINEZ CABEZA lngenieria Aeronautica y performance improvements, the application of the propfan. and Astronautica (ISSN 0020-1006). Feb. 1989, p. 13-25. In Spanish. the development of supersonic and hypersonic vehicles. R.R. A development history is presented for the USAF 8-2 'stealth bomber', with a view to competing strategic aircraft alternatives A89-35379 considered during the 1970s and the debt owed by the B-2's BUSINESS AVIATION AND NEW TECHNOLOGIES [AVIATION configuration designers to the experience gained by the Northrop D'AFFAIRES ET TECHNOLOGIES NOUVELLES] 'flying wing' aircraft XB-35, and the YB-49 of the 1950s. The B-2 J. MAESTRATI (Avions Marcel Dassault Breguet Aviation, is noted to have been produced almost entirely via totally integrated Merignac, France) L'Aeronautique et I'Astronautique (ISSN CAD/CAM facilities requiring the investment of some $1 billion by 0001-9275), no. 134, 1989, p. 32-34. In French. the primary contractor. The proposed production run of 132 8-2 New technologies for business aircraft are discussed, with aircraft is estimated to cost $70 billion. The first 8-2 to be completed special attention given to the application of laminar flow techniques. was unveiled on November 22, 1988. O.C. It is predicted that the maximization of laminar flow will result in a 15 percent increase in flight range. Wind tunnel and flight test results for laminar flow obtained with the Falcon 50 aircraft have A8935125 confirmed theoretical predictions. The possibility of a supersonic LIFE WITH THE OLDER AIRCRAFT business aircraft using extended laminarity and having a 7500-km BILL SWEETMAN lnteravia (ISSN 0020-5168). vol. 44, March flight radius is considered. R.R. 1989, p. 250-252, 254. Maintenance costs for older airliners are 2-3 times higher than those for more recent types; these costs are expected to further N89-20086'# National Aeronautics and Space Administration, increase as regulatory responses to recent fuselage fatigue- and Washington, DC. corrosion-instigated accidents opt for more conservative PERFORMANCE AND TEST SECTION FLOW assumptions about fatigue resistance in light AI-alloy structures CHARACTERISTICS OF THE NATIONAL FULL-SCALE subjected to thousands of pressurization/depressurization cycles. AERODYNAMICS COMPLEX 40- BY 80-FOOT WIND TUNNEL Attention is presently given to a tabulation of data concerning the PETER T. ZELL and KAREN FLACK Feb. 1989 81 p number of aircraft, economic design service life objective, and (NASA-TM-101065; A-89028; NAS 1.15101065) Avail: NTlS HC number of aircraft that have operated beyond the 75-percent and A05/MF A01 CSCL 01A 100-percent points of that service life objective, for 8-707, 8-720, Results from the performance and test section flow calibration 8-727, 6-737, and 8-747 airliner types. O.C. of the 40-by 80-Foot Wind Tunnel are presented. A flow calibration test was conducted in May and June 1987. The goal of the flow calibration test was to determine detailed spatial variations in the A8935376 40-by 80-ft test section flow quality throughout the tunnel ONERA RESEARCH ON CIVIL AIRCRAFT [RECHERCHES DE operational envelope. Data were collected for test section speeds L'ONERA SUR LES AVIONS CIVILS] up to 300 knots and for air exchange rates of 0, 5, and 10 percent. J.-P. MAREC (ONERA. Chatillon-sous-Bagneux, France) The tunnel performance was also calibrated during the detailed L'Aeronautique et I'Astronautique (ISSN 0001-9275), no. 134, 1989, mapping of the test section flow field. Experimental results p. 3-17; Comments, p. 17, 18. In French. refs presented indicate that the flow quality in the test section, with Civil-aircraft research conducted at ONERA concerning the exception of temperature, is relatively insensitive to the level airframes, propulsion, and safety is reviewed. Airframe studies are of dynamic pressure and the air exchange rate. The dynamic performed on drag reduction, aeroelasticity, flight mechanics, the pressure variation in the test section is within + or - 0.5 deg at buckling of composite structures, and the strength of all test section velocities. Cross-stream temperature gradients in aluminum-lithium alloys. Propulsion research discussed includes the test section caused by the air exchange system were such topics as combustion, high-temperatureturbine-blade fatigue, documented, and a correction method was established. Streamwise propfan engines, and propulsion/airframe integration. Safety static pressure variation on the centerline is about 1 percent of regulations concerning lightning strikes and the effects of icing test section dynamic pressure over 30 ft of the test section are also considered. R.R. length. Author
438 02 AERODYNAMICS
N8920087# National Aerospace Lab., Amsterdam (Netherlands). A89-33249’# National Aeronautics and Space Administration. Structures and Materials Div. Lewis Research Center, Cleveland, OH. ENVIRONMENT-ASSISTED AEROSPACE FATIGUE PROBLEMS HOT GAS INGESTION TESTING OF AN ADVANCED STOVL IN THE NETHERLANDS CONCEPT IN THE NASA LEWIS 9- BY 15-FOOT LOW SPEED R. J. H. WANHILL 2 Feb. 1988 24 p Presented at the WIND TUNNEL WITH FLOW VISUALIZATION Environmentally Assisted Fatigue Symposium, Sheff ield, England, ALBERT L. JOHNS (NASA, Lewis Research Center, Cleveland, Apr. 1988 OH), JOSEPH D. FLOOD, THOMAS W. STROCK, and KURT C. (NLR-MP-880044; ETN-89-94053) Avail: NTlS HC AO3/MF AMUEDO (McDonnell Aircraft Co., Saint Louis, MO) AIAA. ASME, A01 SAE, and ASEE, Joint Propulsion Conference, 24th, Boston, MA, Corrosion and environment-assisted fatigue problems in aircraft, July 11-13, 1988. 26 p. Previously announced in STAR as and the measures taken to alleviate them are reviewed. Landing N89-15078. gear, airframes, flying controls, propellers and rotor blades, and (AIAA PAPER 88-3025) engines are discussed. ESA Advanced Short Takeoff /Vertical Landing (STOVL) aircraft capable of operating from remote sites, damaged runways, and small air capable ships are being pursued for deployment around the turn of the century. To achieve this goal, it is important that 02 the technologies critical to this unique class of aircraft be developed. Recognizing this need, NASA Lewis Research Center, AERODYNAMICS McDonnell Douglas Aircraft, and DARPA defined a cooperative program for testing in the NASA Lewis 9- by 15-foot Low Speed Includes aerodynamics of bodies, combinations, wings, rotors, and Wind Tunnel (LSWT) to establish a database for hot gas ingestion, control surfaces; and internal flow in ducts and turbomachinery. one of the technologies critical to STOVL. Results from a test program are presented along with a discussion of the facility modifications allowing this type of testing at modal scale. These A88331OO# modifications to the tunnel include a novel ground plane, an ON A METHOD FOR SOLVING INTEGRAL EQUATIONS OF elaborate model support which included 4 degrees of freedom, LIFTING-SURFACE THEORY FOR OSCILLATING HIGH-SPEED heated high pressure air for nozzle flow, a suction system exhaust PROPELLERS for inlet flow, and tunnel sidewall modifications. Several flow TERUO ICHIKAWA Japan Society for Aeronautical and Space visualization techniques were employed including water mist in Sciences, Journal (ISSN 0021-4663), vol. 37, no. 420, 1989, p. the nozzle flows and tufts on the ground plane. Headwind 47-51. refs (free-stream) velocity was varied from 8 to 23 knots. Author A lifting-surface theory of oscillating high-speed propellers has been formulated earlier by the author in a form of integral equations. A89-33383# In this paper, a method for solution of these integral equations is SINGLE AND MULTI-ELEMENT AIRFOILS IN AN ISOTROPIC proposed. An adjoint variational principle, equivalent to the integral TURBULENT OUTER FLOW equations for direct and reverse flows, as well as to the Kutta GEORGE D. CATALANO, C. MIKE FREMAUX (Louisiana State conditions in both the flows, is derived. It is shown that the University, Baton Rouge), and ERIC 8. ZIMMERMAN (U.S. Military generalized aerodynamic forces acting on the propeller blades Academy, West Point, NY) IN: International Symposium on will be computed advantageously by applying a Rayleigh-Ritz type Applications of Laser Anemometry to Fluid Mechanics, 4th, Lisbon, method to the variational principle. Author Portugal, July 11-14, 1988, Proceedings. Lisbon, lnstituto Superior Tecnico, 1988, p. 3.12 (5 p.). refs A8933140 It is shown that allowance should be made for the magnitude A STUDY OF THE ROTOR WAKE IN NAP-OF-THE-EARTH of the free-stream turbulent intensity in estimates of the lift and CHENGJAN HE and ZHENG GAO (Nanjing Aeronautical Institute, pitching moment coefficients for both single and multielement People’s Republic of China) Chinese Journal of Aeronautics airfoils. At a given angle of attack, the lifting efficiency of the (ISSN 1000-9361), vol. 1, July 1988, p. 71-78. refs airfoil decreases with increasing turbulence intensity. A simple An investigation of the ground vortex, the most significant perturbation-analysis-based prediction model is developed which aerodynamic phenomenon in rotor aerodynamics during yields results in close agreement with the experimental data nap-of-the-earth flight, is carried out. Based on the analysis of the obtained. K.K. rotor wake near the ground, a theoretical method has been established which can be used for calculating the ground vortex, A89-33385# its longitudinal position, and its strength. The computational results HELICOPTER ROTOR WAKE INVESTIGATION USING A are compared with available experimental data and found to be in LASER DOPPLER ANEMOMETRY TECHNIQUE good agreement. Author M. NSI MBA, D. FAVIER, C. MARESCA, and P. CRESPI (Institut de Mecanique des Fluides, Marseille, France) IN: International A8833142 Symposium on Applications of Laser Anemometry to Fluid A DIGITAL SIMULATION TECHNIQUE FOR DRYDEN Mechanics, 4th, Lisbon, Portugal, July 11-14, 1988, Proceedings. ATMOSPHERIC TURBULENCE MODEL Lisbon, lnstituto Superior Tecnico, 1988, p. 5.12 (7 p.). refs ZHENYAN ZHAO, YELUN XIAO, and YlJlAN SHI (Beijing University (Contract DRET-87-095) of Aeronautics and Astronautics, People’s Republic of China) The aim of the present research is to provide an accurate Chinese Journal of Aeronautics (ISSN 1000-9361), vol. 1, July description of the flowfield generated by helicopter rotors operating 1988, p. 87-97. refs in hover and forward flight regimes. A two-dimensional laser The Dryden model is usually used in studying the response of velocimeter is implemented for instantaneous velocity mea- a flight vehicle to atmospheric turbulence. For a modern flight surements either in the wake or around the blades. The mea- simulator, it is necessary to generate random winds (in the Dryden surements performed near the blades then lead to determine model or sometimes in others) with a digital computer. In this the distribution of circulation along the blade span which is used Paper, a theoretically strict new method to meet this purpose is to validate the predictions of rotor aerodynamics codes based on proposed. By this method, a three-dimensional atmospheric a free wake analysis calculation. Author turbulence is obtained which contains three components of the wind velocity and three components of the wind-velocity gradient. A89-33410 The reliability of this method is checked by comparing the MEASUREMENTS OF MEAN-FLOW AND TURBULENCE autocorrelation value obtained with the theoretical one. A numerical CHARACTERISTICS IN A TURBOJET EXHAUST USING A example has shown a satisfactory result. Author LASER VELOCIMETER
439 02 AERODYNAMICS
HANS J. SCHAEFER (Saint-Louis, lnstitut Franco-Allemand de A8933426 Recherches, France) IN: Symposium on Turbulence, 11th, Rolla, MEAN AND TURBULENT VELOCITY MEASUREMENTS OF MO, Oct. 17-19, 1988, Preprints. Rolla, MO, University of SUPERSONIC MIXING LAYERS Missouri-Rolla, 1988, p. A1 3-1 to A1 3-9. refs S. G. GOEBEL, J. C. DUTTON, H. KRIER, and J. P. RENlE (Illinois, Mean-flow and turbulence characteristics have been measured University, Urbana) IN: Symposium on Turbulence, 11th, Rolla, in a high-temperature axisymmetric jet exhausting from an MO, OCt. 17-19, 1988, Preprints. Rolla, MO, University of aero-engine and the effects of exit Mach number and temperature Missouri-Rolla, 1988, p. A34-1 to A34-10. refs on the jet flow field were studied. A laser Doppler velocimeter (Contract NO0014-86-K-0434) was used to map the flow characteristics over a range of Mach The behavior of supersonic mixing layers under three conditions numbers from 0.46 to 0.84. Radial distributions of the mean axial has been examined by schlieren photography and laser Doppler velocity and the rms of the corresponding fluctuations were velocimetry. It was found that higher levels of secondary freestream obtained at different axial stations in the flow. The various turbulence did not increase the peak turbulence intensity observed distributions are found to collapse when plotted in appropriate within the mixing layer, but slightly increased the growth rate. coordinates and the collapsed data can be approximated by a Higher levels of freestream turbulence also reduced the axial universal profile. These experimental findings are in good distance required for development of the mean velocity. At higher agreement with previous measurements in isothermal jets. convective Mach numbers, the mixing layer growth rate was found Author to be smaller than that of an incompressible mixing layer at the same velocity and freestream density ratio. The increase in A89-33423' Pennsylvania State Univ., University Park. convective Mach number also caused a decrease in the turbulence MEASUREMENTS OF A SUPERSONIC TURBULENT VORTEX intensity. Author 0. M. METWALLY and G. S. SETTLES (Pennsylvania State University, University Park) IN: Symposium on Turbulence, 11 th, A89-33627# Rolla, MO, Oct. 17-19, 1988, Preprints. Rolla, MO, University of COMPUTATION OF FLOW FIELDS FOR HYPERSONIC FLIGHT Missouri-Rolla, 1988, p. A31-1 to A31-5. refs AT HIGH ALTITUDES (Contract NCA2-235) J. N. MOSS University of Texas, U.S. Air Force Academy, and Mean-flow measurements of a supersonic turbulent streamwise GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, 2nd, vortex are presented. This vortex was produced by the injection U.S. Air Force Academy, Colorado Springs, CO, Jan. 16-20, 1989, of a swirling flow along the centerline of a supersonic airstream Paper. 46 p. refs at Mach 3. Directional Mach number distributions, obtained via a Data on the nature of the flow and aerodynamic characteristics five-hole flow-angularity probe, reveal vortex characteristics similar of different reentry configurations under transitional-flow conditions to those of the incompressible case, even though rotational Mach are discussed. The important physical phenomena that occur under numbers up to 0.8 were obtained. This work is the first step of a hypersonic low-density conditions are described. Direct simulation study of the supersonic vortex breakdown phenomenon. Author Monte Carlo calculations provide a means of establishing the limits on the valid application of continuum methods for hypersonic A8933424 low-density flows. K.K. INSTANTANEOUS PROFILES AND TURBULENCE STATISTICS OF SUPERSONIC FREE SHEAR LAYERS BY RAMAN A8933634'# Stanford Univ., CA. EXCITATION + LASER-INDUCED ELECTRONIC A NUMERICAL METHOD FOR PREDICTING HYPERSONIC FLUORESCENCE (RELIEF) VELOCITY TAGGING OF OXYGEN FLOWFIELDS R. B. MILES, J. J. CONNORS, E. C. MARKOVITZ, P. J. HOWARD, ROBERT W. MACCORMACK and GRAHAM V. CANDLER and G. J. ROTH (Princeton University, NJ) IN: Symposium on (Stanford University, CA) University of Texas, U.S. Air Force Turbulence, 11th, Rolla, MO, Oct. 17-19, 1988, Preprints. Rolla, Academy, and GAMNI-SMAI, Joint Europe/U.S. Short Course in MO, University of Missouri-Rolla, 1988, p. A32-1 to A32-9. refs Hypersonics, 2nd. U.S. Air Force Academy, Colorado Springs, CO. (Contract AF-AFOSR-86-0191) Jan. 16-20, 1989, Paper. 8 p. Research supported by SDIO. A new method of flow tagging based on the vibrational excitation refs of oxygen is applied to both supersonic and high-speed subsonic (Contract DAA103-86-K-0139; NAGW-965; F33615-86-C-3015) air flows to generate instantaneous velocity profiles and turbulence The flow about a body traveling at hypersonic speed is energetic statistics across the free shear layer. By simultaneously tagging enough to cause the atmospheric gases to chemically react and two lines, both transverse and streamwise velocity correlations reach states in thermal nonequilibrium. The prediction of hypersonic are found. Rayleigh scattering can also be imaged, so this flow flowfields requires a numerical method capable of solving the diagnostic technique has the capability of instantaneously recording conservation equations of fluid flow, the chemical rate equations density cross section and velocity profiles. Author for specie formation and dissociation, and the transfer of energy relations between translational and vibrational temperature states. A8933425 Because the number of equations to be solved is large, the A COMPARISON OF THE TURBULENCE STRUCTURE OF numerical method should also be as efficient as possible. The SUBSONIC AND SUPERSONIC BOUNDARY LAYERS proposed paper presents a fully implicit method that fully couples A. J. SMITS, A. E. ALVING, R. W. SMITH, E. F. SPINA, E. M. the solution of the fluid flow equations with the gas physics and FERNANDO (Princeton University, NJ) et al. IN: Symposium on chemistry relations. The method flux splits the inviscid flow terms, Turbulence, 11 th, Rolla, MO, Oct. 17-19, 1988, Preprints. Rolla, central differences of the viscous terms, preserves element MO, University of Missouri-Rolla, 1988, p. A33-1 to A33-10. refs conservation in the strong chemistry source terms, and solves (Contract AF-AFOSR-88-0120) the resulting block matrix equation by Gauss Seidel line A comparison of the turbulence structure of subsonic and relaxation. Author supersonic boundary layers reveals that, despite broad similarities, significant differences exist. The length scales derived from A89-33637# space-time correlations indicate that the spanwise scales are THE FLOW ON THE LEE-SIDE OF A DELTA WING AT almost identical but that the streamwise scales in the supersonic MACH 7 flow are about half the size of those in subsonic flow. The M. LINDE (Flygtekniska Forsoksanstalten, Bromma, Sweden) large-scale structures in the subsonic boundary layer appear to University of Texas, US. Air Force Academy, and GAMNI-SMAI, move slightly slower, and lean more toward the wall, than those Joint Europe/U.S. Short Course in Hypersonics, 2nd, U.S. Air Force observed in supersonic flows, and their shear stress content is Academy, Colorado Springs, CO, Jan. 16-20, 1989, Paper. 14 p. distributed differently among the four quadrants. These refs observations should have a strong impact on deriving turbulence The structure of the flow field on the lee-side of a 70-deg models for supersonic flows. Author delta wing with flat upper surface and rounded leading edge at M
440 02 AERODYNAMICS
= 7 and at a high angle of attack is studied. A conical five-hole discussed with attention given to three-dimensional flows. The pressure probe is used to study the flow. Surface oil flow is also ideal-gas continuum flow is simulated using an explicit/implicit used for the visualization of the flow close to the surface. K.K. finite-difference method for the thin-layer approximation of the time-dependent Navier-Stokes equations. In the two dimensional A89-33638# case, real-gas effects are implemented using curve-fitting routines EXPERIMENTAL METHODS FOR HYPERSONICS - for the air properties in chemical equilibrium. K.K. CAPABILITIES AND LIMITATIONS RICHARD D. NEUMANN University of Texas, U.S. Air Force A89-33645# Academy, and GAMNI-SMAI. Joint Europe/U.S. Short Course in LAMINAR-TURBULENT TRANSITION PROBLEMS AT HIGH Hypersonics, 2nd, U.S. Air Force Academy, Colorado Springs, CO, SPEEDS Jan. 16-20, 1989, Paper. 31 p. refs DANIEL ARNAL (ONERA, Centre d’Etudes et de Recherches de Experimentation is a necessary element in understanding Toulouse, France) University of Texas, US. Air Force Academy, hypersonic flows, and must be engaged in more intensively in and GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, order to: (1) formulate models for inclusion in numerical design 2nd, U.S. Air Force Academy, Colorado Springs, CO, Jan. 16-20, tools; (2) validate assembled CFD tools for accuracy; and (3) 1989, Paper. 39 p. refs generate design data. It is presently noted that insufficient This paper is devoted to a description of some theoretical and interaction exists IsetJveen numerical and experimental methods experimental problems related with boundary layer transition at at present, as illustrated by the literature’s stress on numerics at high speeds, in a two-dimensionai mean iiow. On the theoretical the expense of critical experimentation for the validation of point of view, emphasis is given on linear stability theory, which theoretical methods’ capabilities. There is felt to be insufficient describes the first stages of the transition process. In test hardware and instrumentation. O.C. incompressible flow, it is often associated with the e(n) method for predicting transition onset. The extension of this method to A89-33640# compressible flows will be discussed. Another problem is to model COMPUTATIONAL METHODS FOR HYPERSONIC FLOWS - the transition region, the extent of which becomes very large in SPECIAL TECHNIQUES AND REAL GAS EFFECTS hypersonic conditions,. This can be done by using an intermittency H. HOLLANDERS, L. MARRAFFA, J. L. MONTAGNE, PH. MORICE, method. Some comparisons with experimental results are and H. VlVlAND University of Texas, U.S. Air Force Academy, presented. In the last part of the paper, the problem of boundary and GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, layer tripping by isolated, three-dimensional roughness elements 2nd, US. Air Force Academy, Colorado Springs, CO, Jan. 16-20, is discussed. Author 1989, Paper. 68 p. refs Some aspects of computational methods for hypersonic flows A89-33646# are discussed. The general equations governing frozen or HYPERSONIC BOUNDARY-LAYER TRANSITION equilibrium gas flows are reviewed and examples of methods based K. F. STETSON University of Texas, U.S. Air Force Academy, on explicit and implicit schemes developed to solve the and GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics. time-dependent Navier-Stokes equations for perfect gas are 2nd, U.S. Air Force Academy, Colorado Springs, CO, Jan. 16-20, presented. Computational techniques for the treatment of stiff 1989, Paper. 100 p. refs source terms are described. K.K. Hypersonic boundary-layer instability phenomena are described as well as parameteric trends. Attention is given to the effect of A89-33641’# National Aeronautics and Space Administration. Mach number, nosetip bluntness, crossflow, unit Reynolds number, Ames Research Center, Moffett Field, CA. environment, wall temperature, surface roughness, mass transfer, TURBULENCE MODELING FOR HYPERSONIC FLOWS and vibration. Prediction methods and prediction methodology are J. G. MARVIN and T. J. COAKLEY (NASA, Ames Research Center, discussed as well. K.K. Moffett Field, CA) University of Texas, U.S. Air Force Academy, and GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, A89-33735*# United Technologies Corp., Windsor Locks, CT. 2nd, US. Air Force Academy, Colorado Springs, CO, Jan. 16-20, NEAR WAKES OF ADVANCED TURBOPROPELLERS 1989, Paper. 48 p. refs D. 6. HANSON (United Technologies Corp., Hamilton Standard Turbulence modeling for high speed compressible flows is Div., Windsor Locks, CT) and W. P. PATRICK (United Technologies described and discussed. Starting with the compressible Research Center, East Hartford, CT) AIAA, Aeroacoustics Navier-Stokes equations, methods of statistical averaging are Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 13 p. described by means of which the Reynolds-averagedNavier-Stokes Research supported by United Technologies Corp. refs equations are developed. Unknown averages in these equations (Contract NAS3-23720) are approximated using various closure concepts. Zero-, one-, and (AIAA PAPER 89-1095) two-equation eddy viscosity models, algebraic stress models and The flow in the wake of a model single rotation Prop-Fan rotor Reynolds stress transport models are discussed. Computations of operating in a wind tunnel was traversed with a hot-wire supersonic and hypersonic flows obtained using several of the anemometer system designed to determine the 3 periodic velocity models are discussed and compared with experimental results. components. Special data acquisition and data reduction methods Specific examples include attached boundary layer flows, shock were required to deal with the high data frequency, narrow wakes, wave boundary layer interactions and compressible shear layers. and large fluctuating air angles in the tip vortex region. The model From these examples, conclusions regarding the status of modeling tip helical Mach number was 1.17, simulating the cruise condition. and recommendations for future studies are discussed. Author Although the flow field is complex, flow features such as viscous velocity defects, vortex sheets, tip vortices, and propagating A89-33644# acoustic pulses are clearly identified with the aid of a simple NUMERICAL SIMULATION OF THREE-DIMENSIONAL analytical wake theory. Author HYPERSONIC VISCOUS FLOWS W. KORDULLA, B. MUELLER, S. RIEDELBAUCH, W. WETZEL, A89-33758# and G. BRENNER (DFVLR, Goettingen, Federal Republic of EXPERIMENTAL VALIDATION OF A LIFTING SURFACE Germany) University of Texas, U.S. Air Force Academy, and MODEL FOR ROTOR WAKE-STATOR INTERACTION GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, 2nd, J. 6.H. M. SCHULTEN (Nationaal Lucht- en Ruimtevaartlabora- US. Air Force Academy, Colorado Springs, CO, Jan. 16-20, 1989, torium, Amsterdam, Netherlands) AIAA, Aeroacoustics Confer- Paper. 49 p. refs ence, 12th, San Antonio, TX, Apr. 10-12, 1989. 8 p. Research (Contract DFG-RU-334/1 -6) supported by the Nederlands lnstituut vOOr Vliegtuigontwikkeling Numerical approaches to the simulation of viscous hypersonic en Ruimtevaart. refs flows in the continuum- as well as the gaskinetic-flow regimes are (AIAA PAPER 89-1125)
44 1 02 AERODYNAMICS
In most current turbofan engines, the interaction between fan The analytical results are found to generally agree with experimental wakes and the outlet guide vanes in the by-pass duct or the inlet data to within 10-15 percent. V.L. guide vanes of the core engine, is the major noise-generating mechanism. A set of complet and clean experimental data on A89-34151 rotor/stator interaction has become available, which adds ANALYSIS OF SEPARATED FLOW PAST A THIN PROFILE IN significanctly to the existing material. In the present paper these THE CASE OF TRANSLATIONAL OSCILLATIONS [RASCHET data are used for a detailed comparison with results of a lifting OTRYVNOGO OBTEKANIIA TONKOGO PROFILIA PRI surface method. Despite an unsteady normal velocity up to 20 POSTUPATEL'NYKH KOLEBANIIAKH] percent of the main velocity, a good agreement between measured 0. IU. KOROTKOV and G. M. SHUMSKll Aviatsionnaia Tekhnika and computed vane pressures is found. Author (ISSN 0579-2975), no. 4, 1988, p. 92-94. In Russian. refs The paper is concerned with the translational oscillations of a A8933783 thin rectilinear profile (a plate) in the path of separated flow of an NONLINEAR KINK MODES FOR SUPERSONIC VORTEX ideal incompressible fluid. In particular, the effect of the amplitude SHEETS and frequency of the forced oscillations of the profile on its aerodynamic characteristics is investigated by means of a numerical MIGUEL.. ~ ~~~ ARTOLA and ANDREW J. MAJDA (Princeton University, NJ) Physics of Fluids A (ISSN 0899-8213), vol. 1. March 1989, experiment. Vortex formation processes typical of such flows are p. 583-596. refs examined. V.L. (Contract NSF DMS-87-02864; DAAL03-86-K-0003; NOOOl 4-85-K-0507; NOOOl 4-86-K-07591 A89-34152 Both recent large-scale numerical simulations and time- OPTIMAL PROFILE SELECTION IN THE DESIGN OF A dependent asymptotic nonlinear wave theories reveal the SUBSONIC TURBINE CASCADE [K VYBORU OPTIMAL'NOGO prominence of kink modes in the nonlinear instability of supersonic PROFILIA V PROEKTIRUEMOI DOZVUKOVOI RESHETKE vortex sheets. These kink modes are nonlinear traveling waves TURBINY1 that move along the vortex sheet at various speeds and have a 6. I. MAMAEV and T. I. SHUVEROVA Aviatsionnaia Tekhnika wave structure consisting of a kink in the slip stream bracketed (ISSN 0579-2975), no. 4, 1988, p. 94-96. In Russian. by shocks and rarefactions emanating from each side of the kink. An analytical/experimental study has been conducted to Here an explicit construction is developed for calculating all the investigate the possibility of optimizing the performance nonlinear kink modes that bifurcate from a given unperturbed characteristics of subsonic turbine cascades by varying their contact discontinuity. This construction is applied at small geometry. In particular, pressure distributions over cascade profiles amplitudes to provide a completely independent confirmation of are determined for different geometric parameters of the profiles. the asymptotic nonlinear wave theories through a static bifurcation The pressure distribution characteristics are explained in terms of analysis. For the unperturbed vortex sheet, bifurcation diagrams curvature distribution over the profile. V.L. at large amplitudes are also computed for several interesting density ratios and Mach numbers. These results are applied at A89-34427*# Sterling Software, Palo Alto, CA. large amplitude to explain some of the phenomena observed in numerical simulations. Author ADVANCES IN THE COMPUTATION OF TRANSONIC SEPARATED FLOWS OVER FINITE WINGS UNVER KAYNAK (Sterling Software, Inc., Palo Alto, CA) and A8934 114 JOLEN FLORES (NASA, Ames Research Center, Moffett Field, VISCOSITY EFFECTS IN THE GENERATION OF THE LIFTING CA) Computers and Fluids (ISSN 0045-7930), vol. 17, no. 2, FORCE OF AERODYNAMIC WING PROFILES [VIAZKOSTNYE 1989, p. 31 3-332. refs EFFEKTY PRI FORMlROVANll POD'EMNOI SlLY (Contract NCA2-OR-745-309; NAS2-11555) AERODINAMICHESKIKH PROFILE1 KRYL'EVI Problems encountered in numerical simulations of transonic L. F. KOZLOV and V. A. KOCHIN (AN USSR, lnstitut wind-tunnel experiments with low-aspect-ratio wings are surveyed Gidromekhaniki, Kiev, Ukrainian SSR) Bionika (ISSN 0374-6569), and illustrated. The focus is on the zonal EulerINavier-Stokes no. 22, 1988, p. 1-12. In Russian. refs program developed by Holst et al. (1985) and its application to A generalized Zhukovski-Chaplygin postulate is formulated shock-induced separation. The physical basis and numerical which corresponds in particular cases to the Taylor-Howarth and implementation of the method are reviewed, and results are other criteria. It is shown that the classical Zhukovski-Chaplygin presented from studies of the effects of artificial dissipation, postulate, based on qualitative results of flow visualization, boundary conditions, grid refinement, the turbulence model, and approximately reflects the actual situation in the case of stationary geometry representation on the simulation accuracy. Extensive flow past wing profiles with a sharp trailing edge. For profiles with graphs and diagrams and typical flow visualizations are provided. a rounded trailing edge and nonstationary flow past aerodynamic T.K. profiles, the generalized Zhukovski-Chaplygin postulate should be used which allows for viscosity effects in the generation of the A89-34461 V.L. lifting force of aerodynamic wing profiles. LARGE-EDDY SIMULATIONS OF EXCITATION EFFECTS ON A VTOL UPWASH FOUNTAIN A8934149 MAGDI H. RlZK and SURESH MENON (Flow Research Co., Kent, NUMERICAL MODELING OF TRANSONIC FLOW OF A WA) Physics of Fluids A (ISSN 0899-8213), VOI.1, April 1989, p. VISCOUS GAS IN A PLANE CHANNEL WITH A SUDDEN 732-740. refs EXPANSION [CHISLENNOE MODELIROVANIE (Contract F49620-85-C-0084) TRANSZVUKOVOGO TECHENllA VIAZKOGO GAZA V In the present investigation of a VTOL aircraftlike propulsion PLOSKOM KANALE PRI VNEZAPNOM RASSHIRENII] system upwash fountain's response to various azimuthal and V. K. BULGAKOV, A. M. LIPANOV, A. M. ROSLOV, and 0. A. axisymmetric excitations, kinematic considerations are used to TIMOFEEV Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 4, ascertain the interactions of large-scale structures in the fountain, 1988, p. 89-91. In Russian. refs as well as the effects of these interactions on fountain Flow of a viscous gas in a suddenly expanding channel is characteristics. The flow is assumed to be governed by the investigated in the transonic velocity region using a system of full time-dependent, incompressible Navier-Stokes equations. Distinct Navier-Stokes equations. The system of equations with the fountain characteristics are found to be shared among the cases corresponding boundary conditions is solved numerically using an in which azimuthal perturbations are applied at both jet exits. A implicit splitting scheme. The results obtain indicate that the strong resemblance also exists for the cases of azimuthal and Reynolds number affects the length of the separation zone but axisymmetric forcings in opposite directions at the two jet exits. has practically no effect on the base pressure beyond the step. O.C.
442 02 AERODYNAMICS
A8834621 applications or domain decomposition methods to turbomachinery A NEW LOOK AT THEODORSEN'S METHOD IN AEROFOIL forces, patched-grid computations of high-speed inlet flows, THEORY turbulent flow computations in an angled duct with a step, RAJENDRA K. BERA (National Aeronautical Laboratory, Bangalore, Navier-Stokes calculations of scramjet-afterbody flowfields, India) International Journal for Numerical Methods in Fluids (ISSN incompressible cascade calculations using an upwind differenced 0271-2091). vol. 9, March 1989, p. 251-262. refs TVD scheme, Euler solver for 3D inverse problems, iterative Theodorsen's (1931) method for calculating the incompressible acceleration and physically based dissipation for Euler equations potential flow past an aerofoil is reviewed. It is found that some of gasdynamics, and noniterative solution for pressure in parabolic simple modifications to the computational process make the flows. Also addressed are: higher order scheme for convective computations relatively faster, easier, and more accurate. The new flows, use of modified finite element method for CFD applications, modifications are applicable to the analysis of conventional airfoils Navier-Stokes calculations of transonic flows past open and with up to moderate thickness and camber ratio. Several examples transitional cavities, Navier-Stokes simulation of unsteady are presented to show the effectiveness of the modifications. three-dimensional blade-vortex interactions, and stream function Author formulation for natural convection in a multiply connected enclosure. C.D. A8934627 VISCOUS-INVISCID !NTERACTION AND COMPUTATION IN A89-34728' National Aeronautics and Space Administration. AERODYNAMICS Langley Research Center, Hampton, VA. J. C. LE BALLEUR (ONERA, Chatillon-sous-Bagneux, France) IN: PATCHED-GRID COMPUTATIONS OF HIGH-SPEED INLET BAIL V; Proceedings of the Fifth International Conference on FLOWS Boundary and Interior Layers - Computational and Asymptotic J. L. THOMAS, D. H. RUDY (NASA, Langley Research Center, Methods, Shanghai, People's Republic of China, June 20-24, 1988. Hampton, VA), S. R. CHAKRAVARTHY (Rockwell International Dublin, Ireland, Boole Press, Ltd., 1988, p. 30-41. refs Science Center, Thousand Oaks, CA), and R. W. WALTERS (ONERA, TP NO. 1988-116) (Virginia Polytechnic Institute and State University, Blacksburg) IN: A short survey of progress in viscous-inviscid formulation and Advances and applications in computational fluid dynamics; numerical coupling algorithms is given, for computation in high Proceedings of the Symposium, ASME Winter Annual Meeting, Reynolds number aerodynamics. The 'defect formulation' is shown Chicago, IL, Nov. 27-Dec. 2, 1988. New York. American Society to provide a unified development, both for boundary-layerlike and of Mechanical Engineers, 1988, p. 11-22. refs Navier-Stokes solvers. Thin-layer solvers are efficiently developed Two implicit algorithms for the compressible Navier-Stokes with interacted integral equations, closed with a velocity profile equations are applied to the computation of high-speed inlet flows modeling and a two-half-equation turbulence model. The original typical of those which are encountered on propulsion systems of semiinverse coupling method is suggested in steady flows, and a advanced hypersonic vehicles. A patched grid formulation is used time-consistent semiimplicit method in unsteady flows. With these, to treat accurately the blunt cowl interaction with the forebody the viscous-inviscid numerical technique is now capable to compute compression field and efficiently treat variations in inlet geometry without limitations the complex separation processes. Results are downstream of the inlet entrance. Results from the two algorithms, shown for computation of massive separation and stall, of each based on an upwind-biased spatial differencing approach for shock-boundary layer interactions, and of unsteady separation with the convective and pressure terms within a flux-difference-splitting transonic buffet. Author framework, are compared with experimental results for both inlets, and reasonable agreement is found. C.D. A89-34646' National Aeronautics and Space Administration. Ames Research Center, Moffett Field, CA. A89-34730' Florida Univ., Gainesville. HIGH-RESOLUTION SHOCK-CAPTURING SCHEMES FOR A SELF-ADAPTIVE COMPUTATIONAL METHOD FOR INVISCID AND VISCOUS HYPERSONIC FLOWS TRANSONIC TURBULENT FLOW PAST A REAL PROJECTILE H. C. YEE (NASA, Ames Research Center, Moffett Field, CA), G. C.-C. HSU, N.-H. SHIAU (Florida, University, Gainesville), and W.-J. H. KLOPFER (Nielsen Engineering and Research, Inc., Mountain CHYU (NASA, Ames Research Center, Moffett Field, CA) IN: View, CA), and J.-L. MONTAGNE (NASA, Ames Research Center, Advances and applications in computational fluid dynamics; Moffett Field, CA; ONERA, Chatillon-sous-Bagneux, France) IN: Proceedings of the Symposium, ASME Winter Annual Meeting, BAIL V; Proceedings of the Fifth International Conference on Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American Society Boundary and Interior Layers - Computational and Asymptotic of Mechanical Engineers, 1988, p. 33-41. refs Methods, Shanghai, People's Republic of China, June 20-24, 1988. (Contract NAG2-2473) Dublin, Ireland, Boole Press, Ltd., 1988, p. 417-423. refs An attempt to develop an effective solution-adaptive The development of robust, accurate, and efficient implicit computational method for complex unsteady flow problems is shock-capturing schemes for multidimensional compressible reported. The adaptive grid generation technique is critically Navier-Stokes equations in the hypersonic and real gas flow examined to understand its application to self-adaptive regimes is presently undertaken by extending a class of implicit computational procedures. A complex flow problem involving an total variation-diminishing (TVD) schemes suitable for transonic impulsive Mach 0.96 transonic turbulent flow past a real and supersonic, multidimensional Euler and Navier-Stokes secant-ogive-cylinder-boattail projectile, including the base flow equations to hypersonic computations. Numerical aspects of TVD region at zero angle of attack, is considered. The coupling of the schemes are identified which affect the convergence rate for grid generation code to the unsteady Navier-Stokes code makes hypersonic Mach numbers and real gas flows, but which have a it possible to generate a new grid network adaptive to the computed negligible effect on low Mach number or perfect gas flows. O.C. solution at every time step. C.D.
A8934726 A89-34732' Old Dominion Univ., Norfolk, VA. ADVANCES AND APPLICATIONS IN COMPUTATIONAL FLUID NAVIER-STOKES CALCULATIONS OF DYNAMICS; PROCEEDINGS OF THE SYMPOSIUM, ASME SCRAMJET-AFTERBODY FLOWFIELDS WINTER ANNUAL MEETING, CHICAGO, IL, NOV. 27-DEC. 2, 0. BAYSAL, W. C. ENGELUND (Old Dominion University, Norfolk, 1988 VA), and K. E. TATUM (NASA, Langley Research Center, Hampton, OKTAY BAYSAL, ED. (Old Dominion University, Norfolk, VA) VA) IN: Advances and applications in computational fluid Symposium sponsored by ASME, Fluid Engineering Division. New dynamics; Proceedings of the Symposium, ASME Winter Annual York, American Society of Mechanical Engineers, 1988, 217 p. Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American For individual items see A89-34727 to A89-34747. Society of Mechanical Engineers, 1988, p. 49-59. refs Various papers on advances and applications in computational (Contract NAG1-811) fluid dynamics are presented. Individual topics considered include: Scramjet simulant-gas exhaust flows are computed using
443 two-dimensional Navier-Stokes (NS) equations. The NS equations A89-34740' are solved using an implicit, upwind, finite-volume scheme, and SECOND ORDER ACCURATE FINITE DIFFERENCE the Reynolds stresses are modeled algebraically. The solutions APPROXIMATIONS FOR THE TRANSONIC SMALL are compared with experimental data where the freestream and DISTURBANCE EQUATION AND THE FULL POTENTIAL the nozzle exhaust fluids are air. The NS equations for the flow, EQUATION where the scramjet exhaust simulant gas is a mixture of Freon-12 M. M. MOSTREL (Bell Communications Research, Inc., Piscataway, and argon, are solved by an explicit, finite difference scheme. NJ) IN: Advances and applications in computational fluid dynamics; The results are compared with experimental data, and certain Proceedings of the Symposium, ASME Winter Annual Meeting, discrepancies are explained. C.D. Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American Society of Mechanical Engineers, 1988, p. 129-143. refs (Contract NO001 4-86-K-0691; NAG2-70) A8934733 New shock-capturingfinite difference approximations for solving INCOMPRESSIBLE CASCADE CALCULATION USING AN two scalar conservation law nonlinear partial differential equations UPWIND DIFFERENCED TVD SCHEME describing inviscid, isentropic, compressible flows of aerodynamics J. J. GORSKI (U.S. Navy, David W. Taylor Naval Ship Research at transonic speeds are presented. A global linear stability theorem and Development Center, Bethesda, MD) IN: Advances and is applied to these schemes in order to derive a necessary and applications in computational fluid dynamics; Proceedings of the sufficient condition for the finite element method. A technique is Symposium, ASME Winter Annual Meeting, Chicago, IL, Nov. proposed to render the described approximations total 27-Dec. 2, 1988. New York, American Society of Mechanical variation-stable by applying the flux limiters to the nonlinear terms Engineers, 1988, p. 61-69. refs of the difference equation dimension by dimension. An entropy (Contract N00024-86-WR-10432) theorem applying to the approximations is proved, and an implicit, A reliable and robust method has been developed for solving forward Euler-type time discretization of the approximation is the incompressible flow Navier-Stokes equations in two dimensions. presented. Results of some numerical experiments using the The method is based on an upwind differenced TVD scheme which approximations are reported. C.D. requires no numerical parameters to be changed for the different calculations. Comparisons with data for three different cascades A89-34744' Old Dominion Univ., Norfolk, VA. demonstrate the accuracy of the method for ideal and flat plate NAVIER-STOKES CALCULATIONS OF TRANSONIC FLOWS cascades. C.D. PAST OPEN AND TRANSITIONAL CAVITIES S. SRINIVASAN, 0. BAYSAL (Old Dominion University, Norfolk, VA), and E. B. PLENTOVICH (NASA, Langley Research Center, A8934736 INVISCID PREDICTION OF TRANSONIC FLOWS IN Hampton, VA) IN: Advances and applications in computational TURBOMACHINES USING A RUNGE-KUlTA INTEGRATION fluid dynamics; Proceedings of the Symposium, ASME Winter SCHEME Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, A. ARNONE and S. S. STECCO (Firenze, Universita, Florence, American Society of Mechanical Engineers, 1988, p. 169-179. Italy) IN: Advances and applications in computational fluid refs dynamics; Proceedings of the Symposium, ASME Winter Annual (Contract NCCl-121) Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American Computational simulations of deep and transitional cavities at Society of Mechanical Engineers, 1988, p. 93-100. refs transonic regimes were performed. The three-dimensional unsteady A computer code for solving the Euler equations has been separation on the cavity floor was analyzed, and computational developed and applied on H-grids for turbomachinery flowfield flow visualization inside the cavity was done. A parametric study prediction. The integration in time is based on an explicit four-stage was performed to investigate the effects of varying Mach number Runge-Kutta scheme. Linear interpolations are used for spatial and the ratio delta/D, where delta is the instantaneous boundary discretizationand care was taken in maintaining global conservation layer thickness at the upstream lip and D is the depth. Both and the smoothing character of the dissipative terms. Comparison time-averaged and instantaneous solutions were obtained. with inviscid theoretical solutions and with experimental data shows Comparison of the solutions with experimental data were generally that the method is an accurate inviscid solver and can be applied favorable; some discrepancies are explained. C.D. to turbomachinery to yield a good blade-to-blade prediction. Author A89-34745' JAI Associates, Mountain View, CA. NAVIER-STOKES SIMULATION OF UNSTEADY THREE-DIMENSIONAL BLADE-VORTEX INTERACTIONS A89-34737 G. R. SRINIVASAN (JAI Associates, Inc., Mountain View, CA) and COMPUTATIONAL STUDY OF THE EFFECT OF CASCADE W. J. MCCROSKEY (NASA, Ames Research Center; U.S. Army, PARAMETERS ON STALL PROPAGATION IN AXIAL Aeroflightdynamics Directorate, Moffett Field, CA) IN: Advances COMPRESSORS and applications in computational fluid dynamics; Proceedings of F. SISTO, S. JONNAVITHULA, and S. THANGAM (Stevens Institute the Symposium, ASME Winter Annual Meeting, Chicago, IL, Nov. of Technology, Hoboken, NJ) IN: Advances and applications in 27-Dec. 2, 1988. New York. American Society of Mechanical computational fluid dynamics; Proceedings of the Symposium, Engineers, 1988, p. 181-186. refs ASME Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. (Contract DAAL03-88-C-0006) New York, American Society of Mechanical Engineers, 1988, p. The unsteady, viscous, three-dimensional flow field of a 101-107. refs helicopter rotor blade encountering a passing vortex is calculated (Contract NO0014-86-K-0315; N62271-87-M-0204) by solving the thin layer Navier-Stokes equations by a Propagating stall in a linear cascade of airfoils is simulated finite-difference numerical procedure. A prescribed vortex method using a vortex tracking method. The imposed periodicity of the is adopted to preserve the structure of the interacting concentrated vortex arrays is shown to constrain the occurrence of stable vortex. The test cases considered correspond to the experimental propagating stall to a limited range of flow and geometric model rotor test conditions of Caradonna et al. Author parameters. Within this stable range, the method is insensitive to the nonphysical parameters, and hence is quite robust. The role A89-34746 of a vortex merging algorithm in the method is examined in detail, A LINEAR COMPUTER CODE TO DETERMINE AEROELASTIC and recent improvements are discussed. A systematic parametric STABILITY IN AIRFOIL CASCADES AT UNSTEADY FLOW study is conducted within the stable ranges to extend the available CONDITIONS results, and conclusions are drawn concerning the key parameter S. S. STECCO and L. MARCHI (Firenze, Universita, Florence, of interblade phase angle or its surrogate the stall patch wavelength Italy) IN: Advances and applications in computational fluid at a specified frequency. C.D. dynamics; Proceedings of the Symposium, ASME Winter Annual
444 02 AERODYNAMICS
Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American has been so structured as to allow especially careful examination Society of Mechanical Engineers, 1988, p. 187-193. Research of the relationship between the growth of the separated region supported by the Comitato Nazionale per la Ricerca e per lo and transition. O.C. Sviluppo dell’Energia Nucleare e delle Energie Alternative and CNR. refs A89-34883# The aerodynamic behavior of an oscillating elastic cascade in MODEL FOR INVESTIGATION OF HELICOPTER FUSELAGE nonuniform subsonic flow is investigated analytically, applying the INFLUENCE ON ROTOR FLOWFIELDS potential solution obtained by Marchi (1987) to define the blade OMRl RAND and ALFRED GESSOW (Maryland, University, College pressure distributions which bound the overall linearized problem. Park) Journal of Aircraft (ISSN 002143669), vol. 26, May 1989, The derivation of the model equations is outlined; the solution p. 401, 402. Research supported by the U.S. Army. refs procedure is explained; and numerical results from simulations of The paper presents an efficient analytical model for analyzing torsional vibrations and gusts in different flat-plate and curved-plate helicopter fuselage effects on main rotor flowfields in various flight configurations are presented in extensive graphs and characterized conditions. The fuselage shapes are obtained by a discrete in detail, including the effects of interblade vibrational phase angle, distribution of point and line sources/sinks along their axes which, stagger angle, pitch/cord ratio, reduced vibration frequency, and together with the freestream velocity, create bodies with two planes flow Mach number. The behavior of flat- and curved-plate cascades of symmetry. It is shown that the method enables the description is found to be identical, suggesting the use of flat-plate cascades of a large family of helicopter-like shapes with very few sources. as a reference in unsteady design analyses. T.K. Small tiiselage yaw angles are in!ro&ced by slender body theory. The paper also includes an explicit slender-body approximation A89-34749 for taking into account an arbitrary distribution of main rotor THIN AEROFOILS WITH HIGH-INCIDENCE FLAPS OR BLUNT downwash over the fuselage surface. The model is used for TRAILING EDGES parametric investigation of the fuselage influence for a variety of J. A. MORIARTY and E. 0. TUCK (Adelaide, University, Australia) shapes, flight conditions, and rotor/fuselage relative positions. Aeronautical Journal (ISSN 0001-9240), vol. 93, March 1989, p. Author 93-99. refs The method of matched asymptotic expansions is used to A89-34884*# National Aeronautics and Space Administration. calculate the lift for a class of thin aerofoils with high-incidence Langley Research Center, Hampton, VA. flaps or blunt trailing edges. The analysis is based on smallness WIND-TUNNEL WALL EFFECTS ON DELTA WINGS of the ratio between the flap length (or trailing-edge thickness) NEAL T. FRlNK (NASA, Langley Research Center, Hampton, VA) and the chord of the main foil. Results are compared with exact Journal of Aircraft (ISSN 0021-8669), vol. 26, May 1989, p. 403, solutions for bent plates and for triangular and quadrilateral bodies. 404. Abridged. Previously cited in issue 21, p. 3338, Accession A procedure for extension to general trailingedge configurations, no. A87-49089. including detached flaps, is outlined. Author A89-34886# A89-34807# EFFECT OF WING TIP STRAKES ON WING LIFT-DRAG RATIO EVALUATION OF ALGEBRAIC TURBULENCE MODELS FOR EN-CHUN MA (Beijing Institute of Aeronautics and Astronautics, PNS PREDICTIONS OF SUPERSONIC FLOW PAST A People’s Republic of China) Journal of Aircraft (ISSN 0021-8669), SPHEREGONE vol. 26, May 1989, p. 410-416. SIAMACK A. SHlRAZl and C. RANDALL TRUMAN (New Mexico, The objective is to increase the wing lift-drag ratio by vortex University, Albuquerque) AlAA Journal (ISSN 0001-1452), vol. induction method generated with wing tip strakes. Experimental 27, May 1989, p. 560-568. Research supported by Sandia National results for a rectangular wing of aspect ratio 5 equipped with Laboratories. Previously cited in issue 08, p. 1043, Accession no. wing tip strakes indicated that the flat-plate strake was worse A87-22696. refs than a strake with dihedral angle and thickness for increasing the wing lift-drag ratio. Strakes cut off at 45 deg were the best at A89-34809’# Virginia Univ., Charlottesville. increasing the wing lift-drag ratio, while strakes with delta = 0 LASER-INDUCED IODINE FLUORESCENCE TECHNIQUE FOR deg were the best at improving the ratio. Author QUANTITATIVE MEASUREMENT IN A NONREACTING SUPERSONIC COMBUSTOR A89-34887# D. G. FLETCHER and J. C. MCDANIEL (Virginia, University, NUMERICAL SOLUTIONS FOR THE FLOWFIELD AROUND A Charlottesville) AlAA Journal (ISSN 0001 -1452), vol. 27, May COUNTER-ROTATING PROPELLER 1989, p. 575-580. Previously cited in issue 09, p. 1191, Accession MAKOTO KOBAYAKAWA (Kyoto University, Japan) and no. A87-24916. refs MASAHIRO NAKAO (Mitsubishi Heavy Industries, Ltd., Nagoya, (Contract NAG1-373) Japan) Journal of Aircraft (ISSN 0021-8669), vol. 26, May 1989, p. 417-422. refs A893481 1# Three-dimensional Euler equations are used to investigate the TRANSITIONAL FLOW ON AXIAL TURBOMACHINE BLADING flowfield around a counter-rotating propeller in flight at a Mach G. J. WALKER (US. Naval Postgraduate School, Monterey, CA) 0.8. Two volumes including front and rear blades are solved AlAA Journal (ISSN 0001-1452), vol. 27, May 1989, p. 595-602. separately. The interaction between both blades is included in the Previously cited in issue 08, p. 1032, Accession no. A87-22356. calculation by the connecting surfaces. The non-iterative implicit refs AD1 (alternating direction implicit) scheme is used in order to solve the Euler equations. The periodic steady solution is obtained. This A8934819# simulates the relative motion of the blades exactly. Numerical NUMERICAL INSTABILITIES IN THE CALCULATION OF calculations are performed for a counter-rotating propfan with SR-3 LAMINAR SEPARATION BUBBLES AND THEIR IMPLICATIONS blade configurations. The results show that the propeller efficiency TUNCER CEBECI (Douglas Aircraft Co., Long Beach, CA) AlAA is superior to that of a single-rotating propfan with the same number Journal (ISSN 0001-1452), vol. 27, May 1989, p. 656-658. refs of blades. Author (Contract F49620-84-C-0007) The prediction of separation bubbles on airfoils is presently A89-34892’# National Aeronautics and Space Administration. undertaken by using both linear stability theory and the e exp n Langley Research Center, Hampton, VA. method to ascertain transitions based on calculated velocity EULER AND NAVIER-STOKES LEESIDE FLOWS OVER profiles. An examination is then conducted of the leading-edge SUPERSONIC DELTA WINGS separation bubble on a thin airfoil as a function of angle-of-attack S. N. MCMILLIN, J. L. THOMAS (NASA, Langley Research Center, and for Reynolds numbers of up to 100,000. This systematic study Hampton, VA), and E. M. MURMAN (MIT, Cambridge, MA) Journal
445 02 AERODYNAMICS of Aircraft (ISSN 0021-8669), VOI.26, May 1989, p. 452-458. An experimental study has been conducted to ascertain the previously cited in issue 21, p. 3335, Accession no. A87-49053. aerodynamic characteristics of three-dimensional flow through a refs linear cascade of turbine vanes; the results obtained are compared (Con?ract NO0014-86-K-0288) with those for a duct whose shape is similar to that of the cascade passage. While the qualities of these two viscous flows are very A8934893# similar (except in the leading-edge region), the secondary flow is TRANSONIC...... - - BUFFET OF A SUPERCRITICAL AIRFOIL WITH stronger in the duct passage than in the vane cascade passage. TRAILING-EDGE FLAP The effect on cascade passage flow of a horseshoe vortex B. H. K. LEE and F. C. TANG (National Research Council of generated around the leading edge of each vane is noted to be Canada, High Speed Aerodynamics Laboratory, Ottawa) Journal limited to the leading edgelendwall-junction region. O.C. of Aircraft (ISSN 0021-8669), vol. 26, May 1989, p. 459-464. refs A89-35053'# San Diego State Univ., CA. A supercritical airfoil with a trailing-edge flap was tested at the EFFECT OF 90 DEGREE FLAP ON THE AERODYNAMICS OF High Reynolds Number Two-Dimensional Test Facility of the A TWO-ELEMENT AIRFOIL National Aeronautical Establishment. Buffet boundaries at various J. KATZ (San Diego State University, CA) and R. LARGMAN flap angles were determined from the divergence of the indicated ASME, Transactions, Journal of Fluids Engineering (ISSN normal-force fluctuations. The test was performed quite deep into 0098-2202), vol. 111, March 1989, p. 93, 94. refs the buffet regime of the airfoil, and spectral analyses of the (Contract NCC2-458) unsteady normal force showed shock-wave oscillations of The aerodynamic performance of a two-element airfoil with a approximately 50-80 Hz for Mach numbers between 0.612 and 90-deg trailing edge flap was experimentally investigated. The 5 0.792. The drag of the airfoil was measured from wake probes, percent-chord long flap, significantly increased the lift of the and the drag penalties for the large flap angles were quite baseline airfoil, throughout a wide range of angles of attack. The significant. This study illustrates the use of trailing-edge flaps for maximum lift coefficient of the flapped wing increased too, whereas buffet alleviation at transonic conditions. Author the liftldrag ratio decreased. Author A89-34895'# Johnson Aeronautics, Palo Alto, CA. CALCULATION OF BLADE-VORTEX INTERACTION AIRLOADS A89-35 168 ON HELICOPTER ROTORS CALCULATION OF COMPRESSION SHOCK SURFACES IN WAYNE JOHNSON (Johnson Aeronautics, Palo Alto, CA) Journal THREE-DIMENSIONAL, STEADY SUPERSONIC FLOWS USING of Aircraft (ISSN 0021-8669), vol. 26, May 1989, p. 470-475. A BICHARACTERISTIC METHOD [BERECHNUNG VON Research sponsored by the US. Army. refs VERDICHTUNGSSTOSSFLAECHEN IN RAEUMLICHEN, (Contract NAS2-12767) STATIONAEREN UEBERSCHALLSTROEMUNGEN MIT ElNEM Two alternative approaches area developed to calculate BICHARAKTERISTIKENVERFAHREN] blade-vortex interaction airloads on helicopter rotors, second-order W. JULING and J. BALLMMANN (Aachen, Rheinisch-Westfaelische lifting-line theory and a lifting-surface theory correction. The Technische Hochschule, Federal Republic of Germany) Zeitschrift common approach of using a larger vortex core radius to account fuer Flugwissenschaften und Weltraumforschung (ISSN for lifting-surface effects is quantified. The second-order lifting-line 0342-068X), vol. 12, Sept.-Dec. 1988, p. 313-322. In German. theory also improves the modeling of low aspect-ratio blades yawed refs flow, and swept tips. Calculated results are compared with This paper presents a numerical algorithm of second-order wind-tunnel measurements of lateral flapping, and with flight test accuracy for use on shock surfaces in three-dimensionalsupersonic measurements of blade section lift on SA34912 and H-34 helicopter flowfields. The algorithm is based on the steady-state rotors. The tip vortex core radius required for good correlation three-dimensional method of characteristics. The method used for with the flight test data is about a 20-percent chord, which is the shock uses a local grid made up of four bicharacteristics on within the range of measured viscous core sizes for helicopter the streamline before the shock, five bicharacteristics behind the rotors. Author shock, and one shock surface-generating line. The scheme is an iterative predictor-corrector algorithm where two of the unknown A89-34898# flow variables behind the shock are used as control variables. It INDUCED DRAG AND THE IDEAL WAKE OF A LIFTING WING is shown that pressure is unsuitable for this purpose. Computed C. W. MCCUTCHEN (NIH, National Institute of Diabetes and solutions in which a shock surface present in the three-dimensional Digestive and Kidney Diseases, Bethesda, MD) Journal of Aircraft flowfields is either included or ignored illustrate the capabilities of (ISSN 0021-8669), vol. 26, May 1989, p. 489-493. refs the method. C.D. The wake of a lifting wing in inviscid flow is a pair of downward-sloping vortices with distributed vorticity in which the A89-35172 vortex lines are approximately helical. Suction in the vortex cores INVESTIGATION OF FLOW SEPARATION IN A counterbalances the negative momentum drag, and the difference THREE-DIMENSIONAL DIFFUSER USING A COUPLED EULER between the two is the induced drag, which is presently AND BOUNDARY-LAYER METHOD characterized as the integral over any transverse plane behind H. W. STOCK, S. LECHER, and W. SEIBERT (Dornier GmbH, the wing of the difference between the energies of lateral and Friedrichshafen, Federal Republic of Germany) Zeitschrift fuer longitudinal motion per unit length. The drag contribution of the Flugwissenschaftenund Weltraumforschung(ISSN 0342-068X). vol. portion of the wing lying between any two transverse planes is 12, Sept.-Dec. 1988, p. 347-357. Research supported by BMFT. equal to the growth of this integral between the forward and the refs rear planes. O.C. The causes of flow separation in an empty, small-scale model of the European Transonic Wind Tunnel (ETWT) diffuser are A8934934 numerically investigated. The three-dimensional nature of the flow, A COMPARISON OF SECONDARY FLOW IN A VANE its generation mechanism, and is influence on flow separation are CASCADE AND A CURVED DUCT studied. The inviscid flow is calculated by a three-dimensional M. T. BOYLE, M. SIMONDS (Maine, University, Orono), and K. finite volume method for the solution of the Euler equations, and POON (Textron Lycoming, Stratford. CT) IN: Heat transfer in the viscous flow on the diffuser wall is evaluated by a gas turbine engines and three-dimensional flows; Proceedings of boundary-layer method for three-dimensional, compressible the Symposium, ASME Winter Annual Meeting, Chicago, IL, Nov. turbulent flow. The boundary-layer information is transferred as a 27-Dec. 2, 1988. New York, American Society of Mechanical boundary condition to the inviscid method via the outflow concept. Engineers, 1988, p. 85-93. Research supported by Textron It is shown that the diffuser geometry is responsible for the flow Lycoming. refs separation. Agreement is found between experimental results
446 02 AERODYNAMICS obtained in a small-scale ETWT test rig diffuser and the numerical Performance issues such as turnover and wake recontact may be ones. C.D. strongly influenced by velocities induced by the wake of the delivering aircraft, especially if the aircraft is maneuvering at the A89-35195# time of parachute deployment. Author THREE-DIMENSIONAL BOUNDARY-LAYER TRANSITION STUDY A89-35218# Y. KOHAMA (Tohoku University, Sendai, Japan) Aeronautical PREDICTION OF PARACHUTE COLLAPSE DUE TO WAKE Society of India, Journal (ISSN 0001-9267), vOI. 40, Aug. 1988, p. RECONTACT 145-157. refs J. W. OLER (Texas Tech University, Lubbock) IN: AlAA This paper deals with brief survey of three-dimensional (3-D) Aerodynamic Decelerator Systems Technology Conference, 1Oth, boundary-layer transition in axisymmetric spinning bodies, curved Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, walls (concave, convex walls, swept bodies) and flat plate with DC, American Institute of Aeronautics and Astronautics, 1989, p. pressure gradient which being the fundamental study for LFC wing. 104-109. Particular attention is made to clarify the transition process and (AIAA PAPER 89-0901) coherent structure in 3-D boundary-layer transition is suggested. The wake behind a decelerating parachute and payload may, Author in some instances, overtake and collapse the parachute. This paper presents an analytical model of the parachute and payload A89-35214# deceleration process inciudiny ihe wake developmen!. Ca!cul&.!ion A PRELIMINARY CHARACTERIZATION OF PARACHUTE results include the deceleration history, wake velocity distribution, WAKE RECONTACT and an indication of the occurrence of wake recontact. Author JAMES H. STRICKLAND and J. MICHAEL MACHA (Sandia National Laboratories, Albuquerque, NM) IN: AlAA Aerodynamic A89-35241# Decelerator Systems Technology Conference, 10th. Cocoa Beach, ANALYSIS OF DECELERATORS IN MOTION USING FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American COMPUTATIONAL FLUID DYNAMICS Institute of Aeronautics and Astronautics, 1989, p. 78-85. refs EARL C. STEEVES (U.S. Army, Research, Development and (Contract DE-AC04-76DP-00789) Engineering Center, Natick, MA) IN: AlAA Aerodynamic (AIAA PAPER 89-0897) Decelerator Systems Technology Conference, 1Oth, Cocoa Beach, A series of tests was conducted on a 10-ft-diameter ringslot FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American parachute with a geometric porosity of 20 percent to establish Institute of Aeronautics and Astronautics, 1989, p. 269-278. refs the conditions under which wake recontact occurs. The vertical (AIAA PAPER 89-0931) helicopter drop tests covered a range of mass ratios from 0.5 to This paper presents results of work on the use of computational 3.0 and a range of Froude numbers from 70 to 400. Data consisted fluid dynamics to predict the behavior of aerodynamic decelerators. of velocity time histories obtained using a laser tracker and diameter This investigation includes flow about stationary decelerators and time histones obtained from photometric data. A collapse parameter a procedure to treat problems involving coupling between the based on the ratio of the maximum parachute diameter to the decelerator motion and fluid motion, such as the terminal velocity subsequent minimum diameter was correlated with the mass ratio problem. Computational results are presented for a flat, circular and the Froude number or equivalently with the initial to final disk and include normal flow about a stationary disk, terminal velocity ratio. Author velocity of a free-falling disk, a disk moving through a fluid with uniform acceleration and uniform velocity. These results show the A8%35215# numerical techniques to be reasonably successful in predicting FLOW VISUALIZATION STUDIES OF WAKE BEHIND the drag performance and terminal velocity. Author AXISYMMETRIC BLUFF BODIES INCLUDING PARACHUTE CANOPY MODELS HlROSHl HlGUCHl (Minnesota, University, Minneapolis) IN: AlAA A89-35243# Aerodynamic Decelerator Systems Technology Conference, 1Oth, A COUPLING APPARENT MASS FOR PARACHUTE Cocoa Beach, FL. Apr. 18-20, 1989, Technical Papers. Washington, INFLATION EQUATIONS DC, American Institute of Aeronautics and Astronautics, 1989, p. D. F. WOLF (Sandia National Laboratories, Albuquerque, NM) IN: 86-90. refs AlAA Aerodynamic Decelerator Systems Technology Conference, (AIAA PAPER 89-0898) loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Flow visualization study was conducted for various Washington, DC, American Institute of Aeronautics and configurations of axisymmetric bluff body geometries including Astronautics, 1989. p. 286-292. refs those of solid and ribbon parachute canopy models. The structures (Contract DE-AC04-76DP-00789) of the unsteady wake patterns were documented and analyzed. (AIAA PAPER 89-0933) In addition, the effect of rapid model acceleration and deceleration A parachute inflation model based on a conservation of on the wake was visualized. The results from photos and video momentum equation was originally proposed to provide a predictive are discussed. Author capability for new parachute designs. The original model predicted faster inflations and larger loads than those observed in test data. A8%35216# The differences were most significant for parachute systems which AN APPROXIMATE METHOD FOR CALCULATING AIRCRAFT experienced large decelerations during the inflation process. A DOWNWASH ON PARACHUTE TRAJECTORIES coupling apparent mass effect was proposed which reduces the JAMES H. STRICKLAND (Sandia National Laboratories, inflation rates and loads. The effect is similar in form to the classical Albuquerque, NM) IN: AlAA Aerodynamic Decelerator Systems hydrodynamics description of coupling between degrees of freedom Technology Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, for an asymmetric body. An approximate value of 1 to 1.3 for the Technical Papers. Washington, DC, American Institute of coupling apparent mass coefficient is estimated based on Aeronautics and Astronautics, 1989, p. 91-96. refs comparison with flight data for ribbon parachutes. Author (Contract DE-AC04-76DP-00789) (AIAA PAPER 89-0899) A89-35244# An approximate method for calculating velocities induced by AN EXPERIMENTAL INVESTIGATION OF THE AERODYNAMIC aircraft on parachute trajectories is presented herein. A simple LOADS ON CAMBERED PLATES system of quadrilateral vortex panels is used to model the aircraft J. H. LAWRENCE, J. W. OLER, and D. T. ADAMSON (Texas wing and its wake. The purpose of this work is to provide a Tech University, Lubbock) IN: AlAA Aerodynamic Decelerator simple analytical tool which can be used to approximate the effect Systems Technology Conference, loth, Cocoa Beach, FL, Apr. of aircraft-induced velocities on parachute performance. 18-20, 1989, Technical Papers. Washington, DC, American Institute
447 of Aeronautics and Astronautics, 1989, p. 293-296. refs Mechanical Engineers, Journal (ISSN 0257-9731), vol. 9, Aug. 1988, (AIM PAPER 89-0935) p. 229-240. refs If the parachute deceleration of a payload results in a large A finite difference method is presented which solves numerically momentum transfer to the surrounding fluid over a relatively short the flow field about a cascade of two-dimensional airfoils. The distance, the resulting wake velocities may be large enough for method is a strongly conservative discretization of the full potential the wake to overtake and collapse the parachute. This paper equation, with an artificial viscosity added in supersonic regions describes an experimental test program aimed at investigating the to ensure the stability and the capture of shock waves. All aerodynamic interaction between the parachute and fluid during a computations are performed on a C-type, body-fitted grid which is wake recontact process. Author generated by a sequence of conformal and shear transformations. The concept of artificial time is applied for the development of a convergent successive line over-relaxation (SLOR) scheme. Results A8435250# of using NACA0012 airfoils as cascade blades are illustrated and UNSTEADY AERODYNAMICS ON SINGLE THE EFFECTS OF compared with data from other sources. The agreement is in PARACHUTE SYSTEM AND CLUSTERED general quite satisfactory. Author DONALD E. WAYE and DONALD W. JOHNSON (Sandia National Laboratories, Albuquerque, NM) AIAA, Aerodynamic Decelerator Systems Technology Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989. 8 p. A89-35430 (Contract DE-AC04-76DP-00789) A COMBINED METHOD FOR CALCULATING SUPERSONIC (AIAA PAPER 89-0934) FLOW OF AN IDEAL GAS PAST A WING WITH A A study was performed to evaluate the performance of SUPERSONIC BLUNT LEADING EDGE [KOMBINIROVANNYI equivalent drag area single parachute systems and cluster METOD RASCHETA SVERKHZVUKOVOGO OBTEKANIIA parachute systems during the early inflation and initial deceleration KRYLA SO SVERKHZVUKOVOI ZATUPLENNOI PEREDNEI phase. Analytical work showed that the cluster system could exhibit KROMKOI IDEAL'NYM GAZOM] better performance during this unsteady aerodynamic phase, due N. V. VOEVODENKO and 1. M. PANTELEEV Akademiia Nauk to a significant decrease in the apparent mass of air influenced SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), by the parachutes. Two test programs have been performed in Jan.-Feb. 1989, p. 159-164. In Russian. refs support of these assumptions. Author A combined numerical method based on the consecutive calculation of flows near the blunt leading edge of a wing and at its center is proposed for calculating supersonic flow of an ideal A8935381 gas past a wing with a supersonic blunt leading edge. Flow EXPERIMENTAL WIND TUNNEL STUDY OF A parameters near the center of the wing are calculated on the MILITARY-AIRCRAFT AIR INTAKE - COMPARISON WITH basis of the plane flow law. Equations of motion for both regions FLIGHT [ETUDE EXPERIMENTALE DUNE ENTREE D'AIR are integrated numerically using Godunov's method. The results D'AVION MlLlTAlRE EN SOUFFLERIE - COMPARAISON AVEC obtained are analyzed to evaluate the applicability of the combined LE VOL] method. V.L. M. BOURASSEAU and M. RAPUC (Avions Marcel Dassault Breguet Aviation, Saint Cloud, France) (Colloque d'Aerodynamique Appliquee. 25th, Talence, France, Oct. 12-14, 1988) L'Aeronautique et I'Astronautique (ISSN 0001-9275), no. 134, 1989, p. 46-53. In A8935433 French. EFFECT OF THE ASYMMETRY OF BOUNDARY CONDITIONS Wind tunnel techniques for evaluating the performance of ON BOUNDARY LAYER FLOW NEAR A CONE AT ANGLE OF military-aircraft air intakes in the subsonic and supersonic regimes AlTACK [O VLllANll NESlMMETRll GRANICHNYKH USLOVll are discussed. Wind-tunnel measurements for steady and unsteady NA TECHENIE V POGRANICHNOM SLOE OKOLO KONUSA flows are obtained and are numerically analyzed in real time. Spatial POD UGLOM ATAKI] and temporal distortion of the internal flow is shown to result in a E. S. KORNIENKO and V. M. SHUCHINOV Akademiia Nauk degradation of compressor performance. Wind-tunnel results for SSSR, Izvestiia. Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), refs various Mach numbers, angles of incidence, and sideslip angles Jan.-Feb. 1989, p. 173-176. In Russian. The effect of the asymmetry of viscous flow past a cone is agree well with flight test data. R.R. investigated for various values of the phase shift. Three-dimensional flow past a cone at angle of attack is calculated on the basis of A89-35393# the finite difference solution of the boundary layer equation. It is THE CORRELATION BETWEEN REYNOLDS STRESS AND found that the presence of phase shifts may lead to the TURBULENT KINETIC ENERGY IN THE NEAR WAKE OF A nonsymmetric distribution of enthalpy and injection and also to SYMMETRIC AIRFOIL the hysteresis of the heat flux and friction force. Examples of KEMlN HE and XING TU (Northwestern Polytechnical University, calculations of laminar flow past a cone are presented. V.L. Xian, People's Republic of China) Northwestern Polytechnical University, Journal (ISSN 1000-2758), vol. 7, April 1989, p. 138-146. In Chinese, with abstract in English. refs A89-35434 This paper describes the turbulent flow field in the trailing edge TURBULIZATION OF A HIGH-VELOCITY BOUNDARY LAYER boundary layer and near wake of a NASA 63-012 symmetric airfoil BY A PROJECTION [TURBULIZATSIIA in a low-speed wind tunnel and investigates the correlation between VYSOKOSKOROSTNOGO POGRANICHNOGO SLOlA Reynolds stress and turbulent kinetic energy in near wake of the VYSTUPOM] airfoil. It is shown that the distributions of the Reynolds stress V. IA. KISELEV and V. I. LYSENKO Akademiia Nauk SSSR, and turbulent kinetic energy were similar for about 80 percent of Izvestiia, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), Jan.-Feb. the wake width, except for the region near the center line. Equations 1989, p. 176-179. In Russian. relating the Reynold stress and turbulent kinetic energy for the The turbulization of a boundary layer by a projection is outer region of the wake and for the center region of the near investigated experimentally at Mach numbers greater than 5 using wake are given. IS. a nitrogen wind tunnel. It is found that even a high-velocity (very stable) boundary layer on a plate can be turbulized by means of A8935417# a projection. As the height of the projection is increased, the A NUMERICAL INVESTIGATION OF STEADY TRANSONIC position of the laminar-turbulent transition approaches that of the CASCADE FLOW IN TURBOMACHINERY turbulizer. A further increase in the projection height leads to KUEN-CHUAN WU and PONG-JEU LU (National Cheng Kung nonviscous boundary layer separation and to a noticeable flow University, Tainan, Republic of China) Chinese Society of restructuring. V.L.
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A8935435 V. J. MODI, F. MOKHTARIAN (British Columbia, University, THIN AXISYMMETRIC CAVERNS IN SUPERSONIC FLOW Vancouver, Canada), T. YOKOMIZO, G. OHTA, and T. OINUMA [TONKIE OSESIMMETRICHNYE KAVERNY V (Kanto Gakuin University, Yokohama, Japan) (IUTAM, Science SVERKHZVUKOVOM POTOKE] Council of Japan, Architectural Institute of Japan, et al., Symposium A. D. VASIN Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti on Fundamental Aspects of Vortex Motion, Tokyo, Japan, Aug. i Gaza (ISSN 0568-5281). Jan.-Feb. 1989, p. 179-181. In Russian. 31-Sept. 4, 1987) Fluid Dynamics Research (ISSN 0169-5983), refs vol. 3, no. 1-4, Sept. 1988, p. 225-230. An integro-differential equation for the profile of a cavern in (Contract NSERC-A-2181) supersonic flow is obtained in the context of thin body theory. An The fluid dynamics of airfoils with rotating cylinder boundary analytical expression is obtained which relates cavern elongation layer control is studied using a numerical surface singularity to the cavitation and Mach numbers. As the cavitation number approach incorporating separated flow and wall confinement decreases, the effect of compressibility on cavern elongation effects. A finite-difference boundary layer scheme is used to becomes insignificant. V.L. account for viscous corrections. A comparison is made between numerical and experimental data on the pressure distribution and A8935450 associated lift characteristics. K.K. A METHOD FOR CALCULATING POTENTIAL TRANSONIC FLOWS IN TURBOMACHINERY CASCADES CMETOD A89-35999 RASCHETA POTENTSIAL'NYKH TRANSZVUKOVYKH VORTEX BREAKDOWN AND ITS CONTROL ON DELTA TECHENll V RESHETKAKH TURBOMASHINI WINGS P. M. BYVAL'TSEV and M. IA. IVANOV Zhurnal Vychislitel'noi A. SCHMUECKER and K. GERSTEN (Bochum, Ruhr-Universitaet, Matematiki i Matematicheskoi Fiziki (ISSN 0044-4669), vol. 29, Federal Republic of Germany) (IUTAM, Science Council of Japan, March 1989, p. 447-459. In Russian. refs Architectural Institute of Japan, et al., Symposium on Fundamental A fast method has been developed for calculating stationary Aspects of Vortex Motion, Tokyo, Japan, Aug. 31-Sept. 4, 1987) subsonic, transonic, and supersonic potential flows in plane Fluid Dynamics Research (ISSN 0169-5983). vol. 3, no. 1-4, Sept. cascades and in cascades located on a rotation surface in a 1988, p. 268-272. variable-thickness layer. The method implements a version of the In order to investigate the breakdown of vortices generated by approximate factorization method which retains second-order the leading edge of delta wings, LDA-measurements have been accuracy in the supersonic regions of the flow. The method is performed in the flow on the suction side of a delta wing of based on the numerical integration of the complete equation for aspect ratio Lambda = 2. The measurements describe the growth the velocity potential written in divergent form in arbitrary curvilinear of the vortex along the leading edge and reveal a certain radial coordinates. The advantages of this approach over the commonly structure upstream of the breakdown point. Moreover, they shed used versions of the approach that uses the method of artificial light on the mechanism responsible for the onset of vortex compressibility in the supersonic regions are demonstrated. V.L. breakdown on the suction side of a wing. The occurrence of the breakdown phenomenon on a delta wing may be prevented or at A8435481 least retarded by the use of spanwise blowing jets. The interaction SUPERSONIC FLOW PAST CARET WINGS AND ELEMENTS of vortex and jets giving rise to these effects is discussed with OF STAR-SHAPED BODIES AT ANGLES OF ATTACK AND the help of measured velocity profiles. Author BANK [SVERKHZVUKOVOE OBTEKANIE LAMBDA-KRYL'EV I ELEMENTOV ZVEZDOOBRAZNYKH TEL PRI UGLAKH ATAKI I A8936006 KRENA] SOUND GENERATION AND FLOW INTERACTION OF 0. N. IVANOV and A. I. SHVETS PMTF - Zhurnal Prikladnoi VORTICES WITH AN AIRFOIL AND A FLAT PLATE IN Mekhaniki i Tekhnicheskoi Fiziki (ISSN 0044-4626), Jan.-Feb. 1989, TRANSONIC FLOW p. 81-87. In Russian. refs G. E. A. MEIER, H.-M. LENT, and K. F. LOEHR (Max-Planck-lnstitut Experimental results are reported on supersonic flow past caret fuer Stroemungsforschung, Goettingen, Federal Republic of wings at angles of attack and bank. The results cover flow Germany) (IUTAM, Science Council of Japan, Architectural characteristics for a wide range of anhedral angles (the caret Institute of Japan, et al., Symposium on Fundamental Aspects of angle between the windward planes of the wing), with both a Vortex Motion, Tokyo, Japan, Aug. 31 -Sept. 4, 1987) Fluid Dynamics curved shock wave and a system of shocks between the wings, Research (ISSN 0169-5983), vol. 3, no. 1-4. Sept. 1988, p. corresponding to Mach and regular interactions. For large anhedral 344-348. refs angles (150-180 deg), the flow schemes studied correspond to The mechanisms of sound generation and the kind of interaction nonsymmetric flow past aircraft with caret wings; for small anhedral of vortices with airfoils in an airflow are investigated. Experiments angles (less than 90 deg), they correspond to flow past an element have been performed in stationary flow with vortices of a Karman of a star-shaped body. V.L. vortex street and in a shock tube flow with a starting vortex of a lifting airfoil. Depending on the dimensions of vortices and airfoils, A8935495 their distance, and the flow Mach numbers, different kinds and POTENTIAL MODELS OF TRANSONIC FLOWS [O amplitudes of upstream propagating steep sound waves occur. POTENTSIAL'NYKH MODELIAKH TRANSZVUKOVYKH Author TECHENIII IU. B. LlFSHlTS and A. A. SHAGAEV (Tsentral'nyi Aerogid- A89-36012 rodinamicheskii Institut, Moscow, USSR) Akademiia Nauk DETAILED MEASUREMENTS IN THE TRANSONIC VORTICAL SSSR, Doklady (ISSN 0002-3264), vol. 304, no. 6, 1989, p. FLOW OVER A DELTA WING 1315-1319. In Russian. refs H. HORNUNG (DFVLR, lnstitut fuer experimentelle Stroe- The paper considers the development of potential models for mungsmechanik, Goettingen, Federal Republic of Germany) transonic flows, where the Zhukovskii-Chaplygin condition and A. ELSENAAR (Nationaal Lucht- en Ruimtevaartlaboratorium, guarantees uniqueness of the solution. The proposed method is Amsterdam, Netherlands) (IUTAM, Science Council of Japan, used to calculate transonic flow past wing profiles. In particular, Architectural Institute of Japan, et al., Symposium on Fundamental the pressure-coefficient distribution is shown for the NACA 0012 Aspects of Vortex Motion, Tokyo, Japan, Aug. 31-Sept. 4, 1987) profile at a freestream Mach number of 0.8 and an angle of attack Fluid Dynamics Research (ISSN 0169-5983), vol. 3, no. 1-4, Sept. of 1.25 deg. B.J. 1988, p. 381-386. refs Experimental results obtained in the Joint International Vortex A8935994 Flow Experiment for Euler Code Validation are presented, which BOUND VORTEX BOUNDARY LAYER CONTROL WITH document surface and field information on compressible flow over APPLICATION TO V/STOL AIRPLANES a delta wing, with particular emphasis on the vortical flow on the
449 02 AERODYNAMICS
lee side. The results show that dissipative effects in Euler error has no significant Mach number sensitivity in the medium to computations are concentrated at the wall, in the vortex sheet, in high subsonic range. The uncertainty or the largest expected error shock waves, and in the vortex core. They lead to significant total in the Sabreliner static pressure measurement after correction for pressure losses that are almost independent of the numerical position error is + or - 0.39mb. Author details of the method and of the same order as experimentally observed values. The validity of using Euler computations for such N89-20093'# Boeing Commercial Airplane Co., Seattle, WA. flows is discussed. IS. DEVELOPMENT AND APPLICATION OF A PROGRAM TO CALCULATE TRANSONIC FLOW AROUND AN OSCILLATING A89-36013 THREE-DIMENSIONAL WING USING FINITE DIFFERENCE SOME CONSIDERATIONS ON LEADING EDGE VORTICES ON PROCEDURES Final Report WINGS IN SUPERSONIC FLOW WARREN H. WEATHERILL and F. EDWARD EHLERS Feb. ADRIANA NASTASE (Aachen, Rheinisch-WestfaelischeTech- 1989 91 p nische Hochschule, Federal Republic of Germany) (IUTAM, (Contract NASl-17977) Science Council of Japan, Architectural Institute of Japan, et ai., (NASA-CR-181744; NAS 1.26:181744; D6-54693) Avail: NTlS Symposium on Fundamental Aspects of Vortex Motion, Tokyo, HC A05/MF A01 CSCL 01A Japan, Aug. 31-Sept. 4, 1987) Fluid Dynamics Research (ISSN A finite difference method for solving the unsteady transonic 0169-5983), vol. 3, no. 1-4, Sept. 1988, p. 387-391. refs flow about harmonically oscillating wings is investigated. The This paper considers the determination of the shape, position, procedure is based on separating the velocity potential into steady and intensity of leading-edge vortices on the lee side of the and unsteady parts and linearizing the resulting unsteady differential following wing models: a wedged delta wing fitted with fuselage, equation for small disturbances. The differential equation for the a double-wedged wing, and a wedged delta wing. These parameters unsteady potential is linear with spatially varying coefficients and are obtained by interpretation of skin friction lines and by exploration with the time variable eliminated by assuming harmonic motion. of the theoretical and experimental pressure coefficients on the Difference equations are derived for harmonic transonic flow to surface of the these wing models in supersonic flow. It is shown include a coordinate transformation for swept and tapered that leading edge vortices have a great influence on the pressure planforms. A pilot program is developed for three-dimensional distribution on the lee side of the wing surface in the vicinity of planar lifting surface configurations (including thickness) for the the leading edge of the wing, but have no influence on the lift CRAY-XMP at Boeing Commercial Airplanes and for the CYBER and pitching moment coefficients of these wings on the pressure VPS-32 at the NASA Langley Research Center. An investigation distribution on the wind side of the wing and on the central part is made of the effect of the location of the outer boundaries on of the lee side of the wing. IS. accuracy for very small reduced frequencies. Finally, the pilot program is applied to the flutter analysis of a rectangular wing. A89-36022# Author NUMERICAL ANALYSIS OF THREE-DIMENSIONAL NON RIGID WINGS N89-20094'# National Aeronautics and Space Administration. THOMAS CHATZIKONSTANTINOU (Software und Beratung fuer Langley Research Center, Hampton, VA. die Segel- und Drachenkonstruktion, Berlin, Federal Republic of SOME LOW-SPEED FLUlTER CHARACTERISTICS OF SIMPLE Germany) AIAA. Aerodynamic Decelerator Systems Technology LOW-ASPECT-RATIO DELTA WING MODELS Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989. 20 p. ROBERT V. DOGGETT, JR. and DAVID L. SOISTMANN (Planning (AIAA PAPER 89-0907) Research Corp., Hampton, VA.) Jan. 1989 11 p Presented This paper presents a numerical method for predicting the at the 30th AIAA/ASME/AHS/ASC Structures, Structural Dynamics behavior of an elastic membrane wing under aerodynamic loading. and Materials Conference, Mobile, AL, 3-4 Apr. 1989 Its shape cannot be found unless the pressure distribution is known (NASA-TM-101547; NAS 1.15:101547; AIAA-89-1325) Avail: and the pressure cannot be found unless the shape is known. It NTIS HC AO3/MF A01 CSCL 01A follows that both the aerodynamic and structural problems have Some results from a combined experimental and analytical study to be solved simultaneously. Mathematically this leads to an of the low-speed flutter characteristics of low-aspect-ratio delta integrodifferential equation. The equation can be solved numerically wings are presented. Data are presented which show the effects with a combined iterative finite-elementlintegral-equation method. of sweep angle on the flutter characteristics of some simple plate The pressure is calculated using a vortex-lattice simulation of the models of constant planform area. The range of sweep angles steady potential flow and the shape is determined using a finite studied was from 30 to 72 degrees. In addition, flutter results are element representation of the structure. A sophisticated model for presented for two 30 deg-sweep clipped-delta wing models. Further, the numerical analysis of ram air wings is presented, measured results are presented that show the effects of root clamping values are compared to calculated values for one ram air wing. (percentage length of the root chord that is cantilevered) for a 45 Author deg-sweep delta wing. The experimental data are compared with analytical results obtained by using kernel function and doublet N89-20092# National Center for Atmospheric Research, Boulder, lattice subsonic unsteady lifting surface theories. Author CO. Atmospheric Technology Div. POSITION ERROR CALIBRATION OF A PRESSURE SURVEY N89-20096 Leicester Univ. (England). AIRCRAFT USING A TRAILING CONE HIGH REYNOLDS NUMBER INCOMPRESSIBLE FLOW EDWARD N. BROWN Jul. 1988 37 p SIMULATION ABOUT PARACHUTE CANOPIES AND SIMILAR (Contract NSF ATM-87-09659) BLUFF BODIES Ph.D. Thesis (PB88-250733; NCAR/TN-313-STR) Avail: NTlS HC A03/MF YAACOV I. FRUCHT 1987 219 p A01 CSCL01A Avail: Univ. Microfilms Order No. BRD-82605 A review is presented of the trailing cone development and A model for the flow around bluff bodies was developed. It is testing, application procedures and the results of position error applied to an investigation of parachute canopy aerodynamic evaluation over a wide speed and altitude range. The position characteristics. The model assumes an axisymmetric incom- error of the NCAR Sabreliner determined by the trailing cone pressible high Reynolds number flow, applicable to the calcu- method is different from the error determined from earlier tower lation of aerodynamic characteristics at zero angle of attack. flights. Independent comparisons with pacer aircraft confirm the The flow is assumed to separate from the canopy at its hemline. static pressure differences between the two position error functions. The vorticity is carried downstream, forming a free shear layer. In D-values during deceleration maneuvers at the pressure survey the flow field vorticity is confined to the shear layer, outside it the altitudes indicate the coefficients of the dynamic pressure terms flow is irrotational. A velocity potential can be defined in the fluid of either correction function are valid and the versatility of the field. The canopy surface is replaced by a vortex ring panel lattice. trailing cone method provides sufficient data to indicate the position Each panel contains a circular bound vortex ring which is located
450 02 AERODYNAMICS at one quarter panel length. For each panel the flow boundary neither predicts accurately the aerodynamic characteristics of conditions on the canopy surface are fulfilled along a control circle helicopter hub fairings nor was cost effective. Author at three quarters of the panel length. In the vortex modelling of the separated wake a number of elements were introduced: N89-20099'# National Aeronautics and Space Administration. improvement of the near wake simulation by accounting for the Langley Research Center, Hampton, VA. standing eddy on the canopy under surface; a simple method of GEOMETRICAL AND STRUCTURAL PROPERTIES OF AN calculating the newly created vortex ring strength and location; AEROELASTIC RESEARCH WING (ARW-2) and reduction of the free parameters from two, the time step and MAYNARD C. SANDFORD, DAVID A. SEIDEL, CLINTON V. the number of panels representing the canopy surface to one, ECKSTROM, and CHARLES V. SPAIN (PRC Kentron, Inc.. i.e., the number of panels. Further model validation and Hampton, VA.) Washington Apr. 1989 40 p implementation were suggested. Methods of model development (NASA-TM-4110; L-16545; NAS 1.15:4110) Avail: NTlS HC for asymmetric canopy representation were discussed. A03lMF A01 CSCL 01A Dissert. Abstr. Transonic steady and unsteady pressure tests were conducted on a large elastic wing known as the DAST ARW-2 wing. The wing has a supercritical airfoil, an aspect ratio of 10.3, a leading N89-20097 Old Dominion Univ., Norfolk, VA. edge sweepback angle of 28.8 deg and is equipped with two VISCOUS SHOCK LAYER ANALYSIS OF HYPERSONIC inboard and one outboard trailing edge control surfaces. The FLOWS OVER LONG SLENDER VEHICLES Ph.D. Thesis geomeiricai and structurai characteristics are presented of this KAM-PUI LEE 1988 222 p elastic wing, using a combination of measured and calculated data, Avail: Univ. Microfilms Order No. DA8823955 to permit future analyst to compare the experimental surface A method for solving the viscous shock layer equations for pressure data with theoretical predictions. Author hypersonic flows over long slender bodies is presented. The governing equations are solved by employing a spatial marching N89-20100*# National Aeronautics and Space Administration. implicit finite difference technique. The two first order equations, Ames Research Center, Moffett Field, CA. continuity and normal momentum, are solved simultaneously as a DOCUMENTATION OF TWO- AND THREE-DIMENSIONAL coupled set. This method yields a simple and computationally HYPERSONIC SHOCK WAVE/TURBULENT BOUNDARY efficient technique. Flows past hyperboloids and sphere cones LAYER INTERACTION FLOWS with body half angles of 5 to 35 deg are considered. The flow MARVIN 1. KUSSOY (Eloret Corp., Sunnyvale, CA.) and CLIFFORD conditions included are from high Reynolds numbers at low altitudes C. HORSTMAN Jan. 1989 26 p to low Reynolds numbers at high altitudes. Detailed comparisons (Contract NCC2-452) were made with other predictions and experimental data for slender (NASA-TM-101075; A-89048; NAS 1.15:101075) Avail: NTlS HC body flows. The results show that the coupling between the AO31MF A01 CSCL 01A continuity and normal momentum equations is essential and Experimental data for a series of two- and three-dimensional adequate to obtain stable and accurate solutions past long slender shock wavelturbulent boundary layer interaction flows at Mach 7 bodies. Both the Cebeci-Smith and Baldwin-Lomax turbulence are presented. Test bodies, composed of simple geometric shapes, models are found to be adequate for application to long slender were designed to generate flows with varying degrees of pressure bodies. Using the corrected slip models, the viscous shock layer gradient, boundary-layer separation, and turning angle. The data predictions compare favorably with experimental data. Under include surface-pressure and heat-transfer distributions as well as chemical nonequilibrium conditions, the surface catalytic effects limited mean-flow-field surveys in both the undisturbed and the can influence the heat transfer. Dissert. Abstr. interaction regimes. The data are presented in a convenient form for use in validating existing or future computational models of N89-20098'# National Aeronautics and Space Administration. these generic hypersonic flows. Author Ames Research Center, Moffett Field, CA. EVALUATION OF VSAERO IN PREDICTION OF N89-20101'# National Aeronautics and Space Administration. AERODYNAMIC CHARACTERISTICS OF HELICOPTER HUB Langley Research Center, Hampton, VA. FA1R INGS A CELL-VERTEX MULTIGRID METHOD FOR THE ALEXANDER LOUIE Feb. 1989 36 p NAVIER-STOKES EQUATIONS (NASA-TM-101048; A-88320; NAS 1.15:101048) Avail: NTlS HC R. RADESPIEL Jan. 1989 41 p AO31MF A01 CSCL 01A (NASA-TM-101557; NAS 1.1 5:101557) Avail: NTlS HC AO31MF A low-order panel code, VSAERO, was used to predict the A01 CSCL01A aerodynamic characteristics of helicopter hub fairings. Since the A cell-vertex scheme for the Navier-Stokes equations, which is simulation of this kind of bluff body by VSAERO was not based on central difference approximations and Runge-Kutta time documented before, the VSAERO solutions were correlated with stepping, is described. Using local time stepping, implicit residual experimental data to establish their validity. The validation process smoothing, a multigrid method, and carefully controlled artificial revealed that simulation of the aerodynamic environment around dissipative terms, very good convergence rates are obtained for a a hub fairing was sensitive to several modeling parameters. Some wide range of two- and three-dimensional flows over airfoils and of these parameters are body and wake panels arrangement, wings. The accuracy of the code is examined by grid refinement streamwise and spanwise separation location, and the most studies and comparison with experimental data. For an accurate prominent one-the wake modeling. Three wake models were used: prediction of turbulent flows with strong separations, a modified regular wake, separated wake, and jet model. The regular wake version of the nonequilibrium turbulence model of Johnson and is a wake with negligible thickness (thin wake). It is represented King is introduced, which is well suited for an implementation into by a single vortex sheet. The separated wake and the jet model three-dimensional Navier-Stokes codes. It is shown that the in the present application are wakes with finite thickness (thick solutions for three-dimensional flows with strong separations can wake). They consist of a vortex sheet enclosing a region of be dramatically improved, when a nonequilibrium model of low-energy flow. The results obtained with the reqular wake were turbulence is used. Author marginally acceptable for sharp-edged hub fairings. For all other cases under consideration, the jet model results correlated slightly N89-20102# National Aerospace Lab., Amsterdam (Netherlands). better. The separated wake, which seemed to be the most Flight Dynamics Div. appropriate model, caused the solution to diverge. While the regular OBSERVED REYNOLDS NUMBER EFFECTS ON AIRFOILS wake was straight-forward to apply in SiNIUlatiOnS, the jet model AND HIGH ASPECT RATIO WINGS AT TRANSONIC FLOW was not. It requires the user to provide information about the CONDITIONS doublet strength gradient on wake panels by guessing the efflux A. ELSENAAR 1 Feb. 1988 49 p Presented at the AGARD velocities at the wake shedding location. In summary, VSAERO Special Course on Boundary Layer Simulation Methodology in
45 1 Transonic Wind Tunnel Testing, Brussels, Belgium and Tullahoma, AlAA 1988 (NASA-TM-101946; E-4595; NAS 1.151 01 946; AIAA-89-0993) (NLR-MP-88006-U; ETN-89-94055) Avail: NTlS HC A03/MF Avail: NTlS HC A03/MF A01 CSCL 01A A0 1 A circular jet was excited simultaneously by two different Variation of airfoil and high aspect ratio wing aerodynamic harmonically related tones. Data for three pairs of Strouhal numbers characteristics (lift, pitching moment, drag, drag divergence, and (St(D) = f'D/U (sub j) = 0.2 and 0.4, 0.3 and 0.6, 0.4 and 0.8). buffet boundaries) as a function of Reynolds number is discussed. For each case the initial phase difference between the two waves Examples related to drag, maximum lift, and pitching moment show was varied in steps of 45 deg, for one full cycle and the level of that tests with free transition behave qualitatively different from the fundamental and subharmonic forcing were varied flows with mostly turbulent boundary layer development (whether independently over the range of 0.1 to 7 percent of the jet exit caused by natural transition close to the leading edge or by artificial velocity. Our initial findings concurred with published findings, such means such as fixation). Free transition results can even be very as a critical level of the fundamental is required for subharmonic misleading for flight conditions. For Reynolds number effects augmentation, the initial phase difference is critical in determining observed on configurations with fully turbulent boundary layer flow, whether the subharmonic is augmented or suppressed. The detailed a distinction between direct Reynolds number effects (resulting documentation of several aspects of this phenomenon all measured from changes in boundary layer development) and indirect Reynolds in one and the same experimental facility in a controlled manner, number effects (that appear as changes in pressure distribution) bring out several important points that eluded previous researchers: is made. The question of how relevant two-dimensional flows are (1) At high amplitudes of the fundamental and subharmonic forcing to high aspect ratio wings is addressed. It is argued that certain levels the subharmonic augmentation is independent of the initial conditions must be met before one can speak of a good phase difference. (2) Contrary to the earlier belief that stable pairing correspondence between two- and three-dimensional flows. The could be produced only with an initial laminar boundary layer, the utility of wind tunnel tests for flight prediction is reviewed. ESA present work shows that by the two-frequency excitation method this phenomenon can be induced over a range of conditions for a jet with an initially turbulent boundary layer. (3) It is seen that N89-20103# lnstitut Franco-Allemand de Recherches, Saint-Louis two-frequency excitation is indeed more effective than single (France). frequency excitation in jet mixing enhancement. Higher spreading BASE FLOW INVESTIGATION BEHIND AXI-AND rates seem to go along with higher subharmonic levels. Author NON-AXISYMMETRIC BLUNT BODIES C. BERNER 10 Dec. 1987 13 p Presented at ICALEO '87 - 6th International Congress on Application of Lasers and N89-20921'# Sverdrup Technology, Inc., Cleveland, OH. Electro-Optics. San Diego, CA, 8-12 Nov., 1987 COMPARISON OF 3D COMPUTATION AND EXPERIMENT FOR (ISL-CO-246/87; ETN-89-94112) Avail: NTlS HC A03/MF A01 NON-AXISYMMETRIC NOZZLES Final Report Experimental investigations of the flow field in the near-wake H. LA1 and E. NELSON Feb. 1989 12 p Presented at the of blunt afterbodies are presented. Measurements were performed 27th Aerospace Sciences Meeting, Reno, NV, 9-12 Jan. 1989; by a two- or three-dimensional frequency shifted laser Doppler sponsored in part by AlAA velocimeter. Experiments were conducted in a blowdown type (Contract NAS3-24105; NAS3-25266) annular nozzle whose Mach number variation ranged between 0.2 (NASA-CR-182245; E-4574; NAS 1.26: 182245; AIAA-89-0007) and 0.9. Models consist of a cylindrical afterbody, and a conical Avail: NTlS HC AO3/MF A01 CSCL 01A and a triangular boattail. Results include mean velocities and the Three dimensional solutions of a single expansion ramp nozzle corresponding mean square velocity fluctuations. They show are computed with the existing PARC computer code by solving interesting features of the mean flow field and give accurate the full Navier-Stokes equations. The computations are performed information about afterbody flows like local flow direction, size to simulate the non-axisymmetric nozzle flowfield in both the and shape of the recirculating regions, rear stagnation point internal/external expansion regions and the exhaust plume in a location, and the differences in flow structure. ESA quiescent ambient environment. Two different configurations of the nozzle at a pressure ratio NPR = 10 are examined. Numerical results of laminar flows are presented, and the wall pressure N89-20105# Minnesota Univ., Minneapolis. Dept. of Aerospace distributions are compared with the experimental data. Author Engineering and Mechanics. AERODYNAMICS OF TWO-DIMENSIONAL SLOlTED BLUFF N89-20922'# Boeing Advanced Systems Co., Seattle, WA. BODIES ADDITIONAL DEVELOPMENT OF THE XTRAN3S COMPUTER F. TAKAHASHI and H. HlGUCHl 30 Apr. 1988 131 p Prepared PROGRAM Final Report for Sandia National Labs., Albuquerque, NM C. J. BORLAND Jan. 1989 98 p (Contract DE-AC04-76DP-00789) (Contract NASl-17864) (DE89-007288; SAND-88-7151) Avail: NTlS HC A07/MF A01 (NASA-CR-181743; NAS 1.26:181743) Avail: NTlS HC A05/MF Aerodynamic characteristics of two-dimensional, slotted bluff A01 CSCL 01A bodies were experimentally investigated. Flow visualizations, base Additional developments and enhancements to the XTRANBS pressure measurements, mean velocity vector measurements, and computer program, a code for calculation of steady and unsteady drag force measurements were conducted to analyze effects of aerodynamics, and associated aeroelastic solutions, for 3-D wings spacing ratio (i.e., porosity), curvature, and vent. Low porosity model in the transonic flow regime are described. Algorithm improvements configurations produced stable near-wake patterns with enhanced for the XTRAN3S program were provided including an implicit finite vortex sheddings of overall wake formations. Model curvature difference scheme to enhance the allowable time step and reduced drag forces and weakened the vortex sheddings. vectorization for improved computational efficiency. The code was Stabilizing effect of curvature on the near-wake patterns was also modified to treat configurations with a fuselage, multiple found. A vent combined with large model curvature was found to stores/nacelles/pylons, and winglets. Computer program changes control drag force effectively, as well as suppressing vortex (updates) for error corrections and updates for version control are sheddings. DOE provided. Author
N89-20920'# Sverdrup Technology, Inc., Cleveland, OH. N89-20923 California Univ., Los Angeles. SUBHARMONIC AND FUNDAMENTAL HIGH AMPLITUDE TRANSVERSE JETS IN COMPRESSIBLE CROSSFLOWS Ph.D. EXCITATION OF AN AXISYMMETRIC JET Thesis GANESH RAMAN and EDWARD J. RICE (National Aeronautics STEPHEN DOUGLAS HEISTER 1988 211 p and Space Administration. Lewis Research Center, Cleveland, Avail: Univ. Microfilms Order No. DA8826010 OH.) Mar. 1989 28 p Presented at the 2nd Shear Flow The deflection and mixing of both gaseous and liquid jets in Conference. Tempe, AZ, 13-16 Mar. 1989; sponsored in part by compressible crossflows are discussed. For gaseous jets, the jet
452 02 AERODYNAMICS cross-section is modeled as a compressible vortex pair which can reduce the aircraft cruise drag through improved integration results from viscous forces at the periphery of the jet. The behavior as well as increase aircraft maneuverability through the application of the vortex pair is then combined with mass and momentum of thrust vectoring. Some of the primary integration problems for balances along the axis of the jet to form a model which describes twin-engine aircraft at transonic speeds are identified, and several the trajectory and mixing of the injected fluid. In the case of a methods are demonstrated for reducing or eliminating the supersonic crossflow, a numerical technique is used to solve the undersirable characteristics, while enhancing configuration inviscid outer flow and the position of the bow shock which effectiveness. Author envelopes the jet. This solution was combined with a liquid jet model developed by T.T. Nguyen to calculate liquid jet trajectories N89-20927*# National Aeronautics and Space Administration. and the location of jet breakup. The solution was also combined Hugh L. Dryden Flight Research Facility, Edwards, CA. with the compressible vortex pair of solution to generate trajectories FLIGHT RESEARCH AND TESTING of gaseous jets in supersonic crossflows. Dissert. Abstr. TERRILL W. PUTNAM and THEODORE G. AYERS In NASA, Langley Research Center, Transonic Symposium: Theory, N89-20924 Stanford Univ., CA. Application, and Experiment, Volume 1, Part 1 p 33-59 Mar. NUMERICAL SIMULATION OF THE FLOW FIELD OVER 1989 Previously announced as N88-26361 DELTA WINGS WITH LEADING EDGE BLOWING Ph.D. Thesis Avail: NTlS HC A18/MF A01 CSCL 01A DAVIDT. YEH 1988 131 p Flight research and testing form a critical link in the aeronautic Avail: Univ. Microfilms Order No. DA8826271 research and development chain. Briiiiant concepts, elegant The vortical flow over a delta wing contributes an important theories, and even sophisticated ground tests of flight vehicles part of the lift - the so-called nonlinear vortex lift. Controlling this are not sufficient to prove beyond a doubt that an unproven vortical flow with its favorable influence would enhance the aeronautical concept will actually perform as predicted. Flight maneuverability and control of the aircraft. Several experiments research and testing provide the ultimate proof that an idea or have revealed that span-wise and tangential leading edge blowing concept performs as expected. Ever since the Wright brothers, can be applied as a means of controlling the position and strength flight research and testing were the crucible in which aeronautical of the leading edge vortices. The present research studies these concepts were advanced and proven to the point that engineers effects by numerical solution of the three-dimensional and companies are willing to stake their future to produce and Navier-Stokes equations. The leading edge jet is simulated by design aircraft. This is still true today, as shown by the development defining a permeable boundary, corresponding to the jet slot, where of the experimental X-30 aerospace plane. The Dryden Flight suitable boundary conditions are implemented. Numerical results Research Center (Ames-Dryden) continues to be involved in a are shown to compare favorably with experimental measurements. number of flight research programs that require understanding and It is found that the use of spanwise leading edge blowing at characterization of the total airplane in all the aeronautical moderate angle of attack magnifies the size and strength of the disciplines, for example the X-29. Other programs such as the leading edge vortices, and moves the vortex cores outboard and F-14 variable-sweep transition flight experiment have focused on upward. The increase in lift primarily comes from the greater a single concept or discipline. Ames-Dryden also continues to nonlinear vortex lift. However, spanwise blowing causes earlier conduct flight and ground based experiments to improve and vortex breakdown, thus decreasing the stall angle. The effects of expand the ability to test and evaluate advanced aeronautical tangential blowing at low to moderate angles of attack tend to concepts. A review of significant aeronautical flight research reduce the pressure peaks associated with leading edge vortices programs and experiments is presented to illustrate both the and to increase the suction peak around the leading edge. progress being made and the challenges to come. Author Dissert. Abstr.
N89-20925'# National Aeronautics and Space Administration. N89-20928*# High Technology Corp., Hampton, VA. Langley Research Center, Hampton, VA. SHOCK-BOUNDARY-LAYER INTERACTION IN FLIGHT TRANSONIC SYMPOSIUM: THEORY, APPLICATION, AND ARILD BERTELRUD ln NASA, Langley Research Center, EXPERIMENT, VOLUME 1, PART 1 Transonic Symposium: Theory, Application, and Experiment, JEROME T. FOUGHNER, JR., comp. Mar. 1989 416 p Volume 1, Part 1 p 61-77 Mar. 1989 Symposium held in Hampton. VA, 19-21 Apr. 1988; sponsored by Avail: NTlS HC A18/MF A01 CSCL 01A NASA, Washington Original contains color illustrations A brief survey is given on the study of transonic shock/boundary (NASA-CP-3020-VOL-1-PT-1; L-16501-VOL-l-PT-l; NAS layer effects in flight. Then the possibility of alleviating the adverse 1.55:3020-VOL-l-PT-l) Avail: NTlS HC A18/MF A01 CSCL shock effects through passive shock control is discussed. A 01 A Swedish flight experiment on a swept wing attack aircraft is used Topics addressed include: wind tunnel and flight experiments; to demonstrate how it is possible to reduce the extent of separated computational fluid dynamics (CFD) applications, industry flow and increase the drag-rise Mach number significantly using a overviews; and inviscid methods and grid generations. moderate amount of perforation of the surface. Author
N89-20926'# National Aeronautics and Space Administration. N89-20929*# Boeing Commercial Airplane Co., Seattle, WA. Langley Research Center, Hampton, VA. Computational Fluid Dynamics Lab. AIRFRAME/PROPULSION INTEGRATION CHARACTERISTICS TRANSONIC CFD APPLICATIONS AT BOEING AT TRANSONIC SPEEDS E. N. TINOCO In NASA, Langley Research Center, Transonic WILLIAM P. HENDERSON and BOBBY L. BERRIER ln its Symposium: Theory, Application, and Experiment, Volume 1, Part Transonic Symposium: Theory, Application, and Experiment, 1 p 79-107 Mar. 1989 Volume 1, Part 1 p 1-31 Mar. 1989 Avail: NTlS HC A18/MF A01 CSCL 01A Avail: NTlS HC A18/MF A01 CSCL 01A The use of computational methods for three dimensional The aerodynamic characteristics for both single and twin-engine transonic flow design and analysis at the Boeing Company is high-performance aircraft are significantly affected by shock presented. A range of computational tools consisting of production induced flow interactions as well as other local flow interference tools for every day use by project engineers, expert user tools for effects which usually occur at transonic speeds. These adverse special applications by computational researchers, and an emerging interactions can not only cause high drag, but also cause unusual tool which may see considerable use in the near future are aerodynamic loadings and/or severe stability and control problems. described. These methods include full potential and Euler solvers, Many programs are under way to not only develop method for some coupled to three dimensional boundary layer analysis reducing the adverse effects, but also to develop an understanding methods, for transonic flow analysis about nacelle, wing-body, of the basic flow conditions which are the primary contributors. It wing-body-strut-nacelle, and complete aircraft configurations. As is anticipated that these programs will result in technologies which the examples presented show, such a toolbox of codes is necessary
453 02 AERODYNAMICS for the variety of applications typical of an industrial environment. GEORGE D. SHREWSBURY, JOSEPH VADYAK, DAVID M. Such a toolbox of codes makes possible aerodynamic advances SCHUSTER, and MARILYN J. SMITH ln NASA, Langley Research not previously achievable in a timely manner, if at all. Author Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1 p 175-194 Mar. 1989 Original N89-20930'# General Dynamics Corp.. Fort Worth, TX. document contains color illustrations THE APPLICATION OF CFD FOR MILITARY AIRCRAFT Avail: NTlS HC A18/MF A01 CSCL 01A DESIGN AT TRANSONIC SPEEDS A computer analysis was developed for calculating steady (or C. W. SMITH, W. W. BRAYMEN, I. C. BHATELEY, and W. K. unsteady) three-dimensional aircraft component flow fields. This LONDENBERG In NASA, Langley Research Center, Transonic algorithm, called ENSBD, can compute the flow field for the Symposium: Theory, Application, and Experiment, Volume 1, Part following configurations: diffuser ductlthrust nozzle, isolated wing, 1 p 109-132 Mar. 1989 isolated fuselage, wing/fuselage with or without integrated inlet Avail: NTlS HC A18/MF A01 CSCL 01A and exhaust, nacelle/inlet, nacelle (fuselage) afterbody/exhaust Numerous computational fluid dynamics (CFD) codes are jet, complete transport engine installation, and multicomponent available that solve any of several variations of the transonic flow configurations using zonal grid generation technique. Solutions can equations from small disturbance to full Navier-Stokes. The design be obtained for subsonic, transonic, or hypersonic freestream philosophy at General Dynamics Fort Worth Division involves use speeds. The algorithm can solve either the Euler equations for of all these levels of codes, depending on the stage of configuration inviscid flow, the thin shear layer Navier-Stokes equations for development. Throughout this process, drag calculation is a central viscous flow, or the full Navier-Stokes equations for viscous flow. issue. An overview is provided for several transonic codes and The flow field solution is determined on a body-fitted computational representative test-to-theory comparisons for fighter-type grid. A fully-implicit alternating direction implicit method is employed configurations are presented. Correlations are shown for lift, drag, for the solution of the finite difference equations. For viscous pitching moment, and pressure distributions. The future of applied computations, either a two layer eddy-viscosity turbulence model CFD is also discussed, including the important task of code or the k-epsilon two equation transport model can be used to validation. With the progress being made in code development achieve mathematical closure. Author and the continued evolution in computer hardware, the routine application of these codes for increasingly more complex N89-20934'# Rockwell International Corp., Los Angeles, CA. geometries and flow conditions seems apparent. Author Aircraft Operations. TRANSONIC AERODYNAMIC DESIGN EXPERIENCE N89-20931'# Grumman Aerospace Corp., Bethpage, NY. Aircraft E. BONNER ln NASA, Langley Research Center, Transonic Systems. Symposium: Theory, Application, and Experiment, Volume 1, Part APPLIED TRANSONICS AT GRUMMAN 1 p 195-216 Mar. 1989 W. H. DAVIS In NASA, Langley Research Center, Transonic Avail: NTlS HC A18/MF A01 CSCL 01A Symposium: Theory, Application, and Experiment, Volume 1, Part Advancements have occurred in transonic numerical simulation 1 p 133-152 Mar. 1989 that place aerodynamic performance design into a relatively well Avail: NTlS HC A18/MF A01 CSCL 01A developed status. Efficient broad band operating characteristics A review of several applications of Computational Fluid can be reliably developed at the conceptual design level. Recent Dynamics (CFD) to various aspects of aerodynamic design recently aeroelastic and separated flow simulation results indicate that carried out at Grumman is presented. The emphasis is placed on systematic consideration of an increased range of design problems project-oriented applications where the ease of use of the methods appears promising. This emerging capability addresses static and and short start-to-completiontimes are required. Applications cover dynamic structuraVaerodynamic coupling and nonlinearities transonic wing design/optimization, wing mounted stores load associated with viscous dominated flows. Author prediction, transonic buffet alleviation, fuselage loads estimation, and compact offset diffuser design for advanced aircraft N89-20935'# Michigan Univ., Ann Arbor. configurations. Computational methods employed include extended EULER SOLVERS FOR TRANSONIC APPLICATIONS transonic small disturbance (automatic grid embedding) formulation BRAM VANLEER In NASA, Langley Research Center, Transonic for analysis/design/optimization and a thin layer Navier-Stokes Symposium: Theory, Application, and Experiment, Volume 1, Part formulation for both external and internal flow analyses. Author 1 p 217-230 Mar. 1989 Avail: NTlS HC A18/MF A01 CSCL 01A N89-20932'# Lockheed Aeronautical Systems Co., Burbank, The 1980s may well be called the Euler era of applied CA. aerodynamics. Computer codes based on discrete approximations TRANSONICS AND FIGHTER AIRCRAFT: CHALLENGES AND of the Euler equations are now routinely used to obtain solutions OPPORTUNITIES FOR CFD of transonic flow problems in which the effects of entropy and LUIS R. MIRANDA In NASA, Langley Research Center, Transonic vorticity production are significant. Such codes can even predict Symposium: Theory, Application, and Experiment, Volume 1, Part separation from a sharp edge, owing to the inclusion of artificial 1 p 153-173 Mar. 1989 Original document contains color dissipation, intended to lend numerical stability to the calculation illustrations but at the same time enforcing the Kutta condition. One effect Avail: NTlS HC A18/MF A01 CSCL 01A not correctly predictable by Euler codes is the separation from a The application of computational fluid dynamics (CFD) to fighter smooth surface, and neither is viscous drag; for these some form aircraft design and development is discussed. Methodology of the Navier-Stokes equation is needed. It, therefore, comes as requirements for the aerodynamic design of fighter aircraft are no surprise to observe that the Navier-Stokes has already begun briefly reviewed. The state-of-the-artof computational methods for before Euler solutions were fully exploited. Moreover, most transonic flows in the light of these requirements is assessed and numerical developments for the Euler equations are now the techniques found most adequate for the subject application constrained by the requirement that the techniques introduced, are identified. Highlights from some proof-of-feasibility Euler and notably artificial dissipation, must not interfere with the new physics Navier-Stokes computations about a complete fighter aircraft added when going from an Euler to a full Navier-Stokes configuration are presented. Finally, critical issues and opportunities approximation. In order to appreciate the contributions of Euler for design application of CFD are discussed. Author solvers to the understanding of transonic aerodynamics, it is useful to review the components of these computational tools. Space N89-20933'# Lockheed Aeronautical Systems Co., Marietta, GA. discretization, time- or pseudo-time marching and boundary Advanced Flight Sciences Dept. procedures, the essential constituents are discussed. The subject COMPUTATION OF AIRCRAFT COMPONENT FLOW FIELDS of grid generation and grid adaptation to the solution are touched AT TRANSONIC MACH NUMBERS USING A upon only where relevant. A list of unanswered questions and an THREE-DIMENSIONAL NAVIER-STOKES ALGORITHM outlook for the future are covered. Author
454 02 AERODYNAMICS
N89-20936'# Michigan Univ., Ann Arbor. Dept. of Aerospace M. HAFEZ In NASA, Langley Research Center, Transonic Engineering. Symposium: Theory, Application, and Experiment, Volume 1, Part AN EMBEDDED MESH PROCEDURE FOR LEADING-EDGE 1 p 309-339 Mar. 1989 VORTEX FLOWS Avail: NTlS HC A18/MF A01 CSCL 01A KENNETH G. POWELL and EARLL M. MURMAN (Massachusetts Vector potential and related methods, for the simulation of Inst. of Tech., Cambridge.) ln NASA, Langley Research Center, both inviscid and viscous flows over aerodynamic configurations, Transonic Symposium: Theory, Application, and Experiment, are briefly reviewed. The advantages and disadvantages of several Volume 1, Part 1 p 231-259 Mar. 1989 formulations are discussed and alternate strategies are Avail: NTlS HC A18/MF A01 CSCL 01A recommended. Scalar potential, modified potential, alternate A cell-vertex scheme is outlined for solving the flow about a formulations of Euler equations, least-squares formulation, delta wing with M (sub infinity) is greater than 1. Embedded regions variational principles, iterative techniques and related methods, and of mesh refinement allow solutions to be obtained which have viscous flow simulation are discussed. Author much higher resolution than those achieved to date. Effects of mesh refinement and artificial viscosity on the solutions are studied, N89-20940'# Princeton Univ., NJ. to determine at what point leading-edge vortex solutions are DEVELOPMENTS AND TRENDS IN THREE-DIMENSIONAL grid-converged. A macroscale and a microscale for the size of MESH GENERATION the vortex are defined, and it is shown that the macroscale (which TIMOTHY J. BAKER ln NASA, Langley Research Center, includes tne wing suriace ptopeiiiesj is converge:! or! ?. mnderate!y I_^I ~ans~iiic Symposium: Thesry, P.pp!ica?inn, and Experiment, refined grid, while the microscale is very sensitive to grid spacing. Volume 1, Part 1 p 341-376 Mar. 1989 Original document The level of numerical diffusion in the core of the vortex is found contains color illustrations to be substantial. Comparisons with the experiment are made for Avail: NTlS HC A18/MF A01 CSCL 01A two cases which have transonic cross-flow velocities. Author An intense research effort over the last few years has produced several competing and apparently diverse methods for generating N89-20937'# Michigan Univ., Ann Arbor. meshes. Recent progress is reviewed and the central themes are ASYMPTOTIC METHODS FOR INTERNAL TRANSONIC FLOWS emphasized which form a solid foundation for future developments T. C. ADAMSON, JR. and A. F. MESSITER In NASA, Langley in mesh generation. Author Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1 p 261 -291 Mar. 1989 Avail: NTlS HC A18/MF A01 CSCL 01A N89-20941'# National Aeronautics and Space Administration. For many internal transonic flows of practical interest, some Langley Research Center, Hampton, VA. of the relevant nondimensional parameters typically are small GENERATION OF UNSTRUCTURED GRIDS AND EULER enough that a perturbation scheme can be expected to give a SOLUTIONS FOR COMPLEX GEOMETRIES useful level of numerical accuracy. A variety of steady and unsteady RAINALD LOEHNER, PARESH PARIKH (Vigyan Research transonic channel and cascade flows is studied with the help of Associates, Inc., Hampton, VA.), and MANUEL D. SALAS ln its systematic perturbation methods which take advantage of this fact. Transonic Symposium: Theory, Application, and Experiment, Asymptotic representations are constructed for small changes in Volume 1, Part 1 p 377-408 Mar. 1989 Prepared in cooperation channel cross-section area, small flow deflection angles, small with Naval Research Lab., Washington, DC differences between the flow velocity and the sound speed, small Avail: NTlS HC A18/MF A01 CSCL 01A amplitudes of imposed oscillations, and small reduced frequencies. Algorithms are described for the generation and adaptation of Inside a channel the flow is nearly one-dimensional except in thin unstructured grids in two and three dimensions, as well as Euler regions immediately downstream of a shock wave, at the channel solvers for unstructured grids. The main purpose is to demonstrate entrance and exit, and near the channel throat. A study of how unstructured grids may be employed advantageously for the two-dimensional cascade flow is extended to include a description economic simulation of both geometrically as well as physically of three-dimensional compressor-rotorflow which leads to analytical complex flow fields. Author results except in thin edge regions which require numerical solution. For unsteady flow the qualitative nature of the shock-wave motion N89-20942*# National Aeronautics and Space Administration. in a channel depends strongly on the orders of magnitude of the Langley Research Center, Hampton, VA. frequency and amplitude of impressed wall oscillations or TRANSONIC SYMPOSIUM: THEORY, APPLICATION, AND fluctuations in back pressure. One example of supersonic flow is EXPERIMENT, VOLUME 1, PART 2 considered, for a channel with length large compared to its width, JEROME T. FOUGHNER, JR., comp. Mar. 1989 511 p including the effect of separation bubbles and the possibility of Symposium held in Hampton, VA, 19-21 Apr.1988; sponsored by self-sustained oscillations. The effect of viscosity on a weak shock NASA, Washington Original contains color illustrations wave in a channel is discussed. Author (NASA-CP-3020-VOL-1-PT-2; L-16501-VOL-l-PT-2; NAS 1.55:302O-VOL-l-PT-2) Avail: NTlS HC A22/MF A01 CSCL N89-20938'# Rensselaer Polytechnic Inst.. Troy, NY. 01A WAVE DRAG DUE TO LIFT FOR TRANSONIC AIRPLANES In order to assess the state of the art in transonic flow disciplines JULIAN D. COLE and NORMAN D. MALMUTH ln NASA, Langley and to glimpse at future directions, NASA-Langley held a Transonic Research Center, Transonic Symposium: Theory, Application, and Symposium. Emphasis was placed on steady, three dimensional Experiment, Volume 1, Part 1 p 293-308 Mar. 1989 Sponsored external, transonic flow and its simulation, both numerically and in part by Rockwell North American Aircraft experimentally. The symposium included technical sessions on wind (Contract AF-AFOSR-0037-88) tunnel and flight experiments; computational fluid dynamic Avail: NTlS HC A18/MF A01 CSCL 01A applications; inviscid methods and grid generation; viscous methods Lift dominated pointed aircraft configurations are considered in and boundary layer stability; and wind tunnel techniques and wall the transonic range. These are treated as lifting wings of zero interference. This, being volume 1, is unclassified. thickness with an aspect ratio of order one. An inner expansion which starts as Jones' theory is matched to a nonlinear outer N89-20944'# National Aeronautics and Space Administration. transonic theory as in Barnwell's earlier work. Expressions for the Ames Research Center, Moffett Field, CA. wave drag due to the equivalent body are derived. Some examples AERODYNAMIC ANALYSIS OF THREE ADVANCED of numerical calculations for different configurations are CONFIGURATIONS USING THE TRANAIR FULL-POTENTIAL presented. Author CODE M. D. MADSON, R. L. CARMICHAEL, and J. P. MENDOZA ln N89-20939'# California Univ., Davis. NASA, Langley Research Center, Transonic Symposium: Theory, VECTOR POTENTIAL METHODS Application, and Experiment, Volume 1, Part 2 p 437-452 Mar.
455 02 AERODYNAMICS
1989 N89-20952'# Iowa State Univ. of Science and Technology, Avail: NTlS HC A22/MF A01 CSCL 21E Ames. Dept. of Aerospace Engineering. Computational results are presented for three advanced TURBULENT EDDY VISCOSITY MODELING IN TRANSONIC configurations: the F-16A with wing tip missiles and under wing SHOCK/BOUNDARY-LAYER INTERACTIONS fuel tanks, the Oblique Wing Research Aircraft, and an Advanced G. R. INGER In NASA, Langley Research Center, Transonic Turboprop research model. These results were generated by the Symposium: Theory, Application, and Experiment, Volume 1, Part latest version of the TranAir full potential code, which solves for 2 p 611-627 Mar. 1989 Previously announced in IAA as transonic flow over complex configurations. TranAir embeds a A88-40758 surface paneled geometry definition in a uniform rectangular flow Avail: NTlS HC A22/MF A01 CSCL 01A field grid, thus avoiding the use of surface conforming grids, and The treatment of turbulence effects on transonic shock/ decoupling the grid generation process from the definition of the turbulent boundary layer interaction is addressed within the configuration. The new version of the code locally refines the context of a triple deck approach valid for arbitrary practical uniform grid near the surface of the geometry, based on local Reynolds numbers between 1000 and 10 billion. The modeling of panel size and/or user input. This method distributes the flow the eddy viscosity and basic turbulent boundary profile effects in field grid points much more efficiently than the previous version each deck is examined in detail using Law-of-the-WalVLaw-of-the- of the code, which solved for a grid that was uniform everywhere Wake concepts as the foundation. Results of parametric studies in the flow field. TranAir results are presented for the three showing how each of these turbulence model aspects influences configurations and are compared with wind tunnel data. Author typical interaction zone property distributions (wall pressure, dis- placement thickness and local skin friction) are presented and dis- cussed. Author
N89-20948'# McDonnell-Douglas Research Labs., Saint Louis, N89-20953'# Virginia Polytechnic Inst. and State Univ., MO. Blacksburg. Dept. of Engineering Science and Mechanics. EULEWNAVIER-STOKES CALCULATIONS OF TRANSONIC STABILITY OF COMPRESSIBLE BOUNDARY LAYERS FLOW PAST FIXED- AND ROTARY-WING AIRCRAFT ALI H. NAYFEH In NASA, Langley Research Center, Transonic CONFIGURATIONS Symposium: Theory, Application, and Experiment, Volume 1, Part J. E. DEESE and R. K. AGARWAL In NASA, Langley Research 2 p 629-689 Mar. 1989 Center, Transonic Symposium: Theory, Application, and Avail: NTlS HC A22/MF A01 CSCL 01A Experiment, Volume 1, Part 2 p 521-545 Mar. 1989 Original The stability of compressible 2-D and 3-D boundary layers is document contains color illustrations reviewed. The stability of 2-D compressible flows differs from that Avail: NTlS HC A22/MF A01 CSCL 01A of incompressible flows in two important features: There is more Computational fluid dynamics has an increasingly important than one mode of instability contributing to the growth of role in the design and analysis of aircraft as computer hardware disturbances in supersonic laminar boundary layers and the most becomes faster and algorithms become more efficient. Progress unstable first mode wave is 3-D. Whereas viscosity has a is being made in two directions: more complex and realistic destabilizing effect on incompressible flows, it is stabilizing for configurations are being treated and algorithms based on higher high supersonic Mach numbers. Whereas cooling stabilizes first approximations to the complete Navier-Stokes equations are being mode waves, it destabilizes second mode waves. However, second developed. The literature indicates that linear panel methods can order waves can be stabilized by suction and favorable pressure model detailed, realistic aircraft geometries in flow regimes where gradients. The influence of the nonparallelism on the spatial growth this approximation is valid. As algorithms including higher rate of disturbances is evaluated. The growth rate depends on approximations to the Navier-Stokes equations are developed, the flow variable as well as the distance from the body. Floquet computer resource requirements increase rapidly. Generation of theory is used to investigate the subharmonic secondary suitable grids become more difficult and the number of grid points instability. Author required to resolve flow features of interest increases. Recently, the development of large vector computers has enabled N89-20954*# Old Dominion Univ., Norfolk, VA. Dept. of researchers to attempt more complex geometries with Euler and Mechanical Engineering and Mechanics. Navier-Stokes algorithms. The results of calculations for transonic SECONDARY THREE-DIMENSIONAL INSTABILITY IN flow about a typical transport and fighter wing-body configuration COMPRESSIBLE BOUNDARY LAYERS using thin layer Navier-Stokes equations are described along with NABIL M. EL-HADY In NASA, Langley Research Center, Transonic flow about helicopter rotor blades using both EulerINavier-Stokes Symposium: Theory, Application, and Experiment, Volume 1, Part equations. Author 2 p 691-704 Mar. 1989 Avail: NTlS HC A22/MF A01 CSCL 01A Three dimensional linear secondary instability theory is extended for compressible boundary layers on a flat plate in the presence N89-20951'# National Aeronautics and Space Administration. of finite amplitude Tollmien-Schlichting waves. The focus is on Ames Research Center, Moffett Field, CA. principal parametric resonance responsible for strong growth of TURBULENCE AND MODELING IN TRANSONIC FLOW subharmonics in low disturbance environment. Author MORRIS W. RUBESIN and JOHN R. VIEGAS In NASA, Langley Research Center, Transonic Symposium: Theory, Application, and N89-20956'# National Aeronautics and Space Administration. Experiment, Volume 1, Part 2 p 581-610 Mar. 1989 Lewis Research Center, Cleveland, OH. Avail: NTlS HC A22/MF A01 CSCL 01A AN LDA (LASER-DOPPLER ANEMOMETRY) INVESTIGATION A review is made of the performance of a variety of turbulence OF THREE-DIMENSIONAL NORMAL SHOCK WAVE models in the evaluation of a particular well documented transonic BOUNDARY-LAYER INTERACTIONS flow. This is done to supplement a previous attempt to calibrate R. M. CHRISS. W. R. HINGST, A. J. STRAZISAR, and T. G. and verify transonic airfoil codes by including many more turbulence KEITH, JR. (Toledo Univ., OH.) In NASA, Langley Research models than used in the earlier work and applying the calculations Center, Transonic symposium: Theory, Application, and to an experiment that did not suffer from uncertainties in angle of Experiment, Volume 1, Part 2 p 741-764 Mar. 1989 attack and was free of wind tunnel interference. It is found from Avail: NTlS HC A22/MF A01 CSCL 01A this work, as well as in the earlier study, that the Johnson-King Nonintrusive measurements were made of a normal shock turbulence model is superior for transonic flows over simple wave/boundary layer interaction. TWOdimensional measurements aerodynamic surfaces, including moderate separation. It is also were made throughout the interaction region while 3-D shown that some field equation models with wall function boundary measurements were made in the vicinity of the shock wave. The conditions can be competitive with it. Author measurements were made in the corner of the test section of a
456 02 AERODYNAMICS continuous supersonic wind tunnel in which a normal shock wave CONTROL had been stabilized. Laser Doppler Anemometry, surface pressure VENKATRAMAN RAGHAVAN Dec. 1987 182 p measurement and flow visualization techniques were employed (UMAERO-87-37) Avail: NTlS HC AO9/MF A01 for two freestream Mach number test cases: 1.6 and 1.3. The A numerical method is developed to study the unsteady former contained separated flow regions and a system of shock circulation control aerodynamics of two-dimensional airfoils. Two waves. The latter was found to be far less complicated. The results cases of unsteadiness in flow are considered. The first case is define the flow field structure in detail for each case. Author the unsteadiness arising from an unsteady, periodic freestream and the second is the unsteadiness due to unsteady blowing N89-20958'# National Aeronautics and Space Administration. momentum. A simple solution for the potential flow is obtained using conformal mapping. The changes due to the presence of Langley Research Center, Hampton, VA. the separated wake region behind the airfoil is calculated by WALL INTERFERENCE ASSESSMENT AND CORRECTIONS distributing a set of source panels in the wake region along the P. A. NEWMAN, W. B. KEMP, JR., and J. A. GARRIZ (Vigyan Research Associates, Inc., Hampton, VA.) In its Transonic surface. The source strengths are determined by using the condition of constant pressure at the control points and that the velocity at Symposium: Theory, Application, and Experiment, Volume 1, Part the separation points must be zero. The unsteady potential flow 2 p 817-851 Mar. 1989 Avail: NTlS HC A22/MF A01 CSCL 01A is assumed to be a periodic variation of the steady potential flow, in phase with the periodic freestream. The boundary layer flow is Wind tunnel wall interference assessment ana correction jWlACj calculated by solving the unsteady boundary layer equaiions using concepts, applications, and typical results are discussed in terms an implicit finite difference method. The flow due to the wall jet is of several nonlinear transonic codes and one panel method code calculated from quasi one-dimensional flow upto the slot on the developed for and being implemented at NASA-Langley. Contrasts between 2-D and 3-D transonic testing factors which affect WlAC surface and further downstream the mixing shear layer is computed numerically as part of the boundary layer solution. The finite procedures are illustrated using airfoil data from the 0.3 m Transonic Cryogenic Tunnel and Pathfinder 1 data from the National Transonic difference method uses backward differences whenever reverse Facility. Initial results from the 3-D WlAC codes are encouraging; flow is encountered. The potential flow and the boundary layer research on and implementation of WlAC concepts continue. and wall jet calculations are combined in an iterative procedure to Author get a converged solution for the entire flow field. The solution provides the velocity and pressure fields which is used to determined the lift and drag forces under given freestream and N89-20959'# Calspan Field Services, Inc., Arnold AFS, TN. jet momentum conditions. The pressure distribution obtained from TWO-MEASURED VARIABLE METHOD FOR WALL the potential flow is used to calcualte the lift and pressure drag INTERFERENCE ASSESSMENTKORRECTION forces. The wall shear data obtained from the boundary layer C. F. LO and W. L. SICKLES In NASA, Langley Research Center, flow gives the skin friction drag.Satisfactory correlation of predicted Transonic Symposium: Theory, Application, and Experiment, results with experimental data is achieved for steady lift over circular Volume 1, Part 2 p 853-866 Mar. 1989 cylinders as well as elliptic airfoils. Author Avail: NTlS HC A22/MF A01 CSCL 01A An iterative method for wall interference assessment and/or N89-20963'# Kansas Univ. Center for Research, Inc., correction is presented for transonic flow conditions in wind tunnels Lawrence. equipped with two component velocity measurements on a single INVESTIGATION OF A FREE-TIP ROTOR CONFIGURATION interface. The iterative method does not require modeling of the FOR RESEARCH ON SPANWISE LIFE DISTRIBUTIONS AND test article and tunnel wall boundary conditions. Analytical proof WAKE VELOCITY SURVEYS OF A SEMI-SPAN WING WITH A for the convergence and stability of the iterative method is shown DISCONTINUOUS TWIST Final Report in the subsonic flow regime. The numerical solutions are given for PAUL FORTIN and HlROYUKl KUMAGAI Apr. 1989 209 p both 2-D and axisymmetrical cases at transonic speeds with the (Contract NCC2-175) application of global Mach number correction. Author (NASA-CR-184948; NAS 1.26:184948) Avail: NTlS HC AlO/MF A01 CSCL01A N89-20960'# National Aeronautics and Space Administration. A wind tunnel test was conducted in the NASA Ames 7 x 10 Langley Research Center, Hampton, VA. Foot Wind Tunnel to investigate the lift distribution on a semi-span COMPARISON OF AIRFOIL RESULTS FROM AN ADAPTIVE wing with a discontinuous change in spanwise twist. The semi-span WALL TEST SECTION AND A POROUS WALL TEST SECTION wing had a tip with an adjustable pitch angle independent on the RAYMOND E. MINECK In its Transonic Symposium: Theory, inboard section pitch angle simulating the free-tip rotor blade when Application, and Experiment, Volume 1, Part 2 p 867-890 Mar. its free-tip is at a deflected position. The spanwise lift distribution 1989 over the wing and the tip were measured and three component Avail: NTlS HC A22/MF A01 CSCL 01A velocity surveys behind the wing were obtained with a three Two wind tunnel investigations were conducted to assess two dimensional laser Doppler velocimeter (LV) with the wing at one different wall interference alleviation/correction techniques: angle of attack and the tip deflected at different pitch angles. A adaptive test section walls and classical analytical corrections. six component internal strain gage balance was also used to The same airfoil model has been tested in the adaptive wall test measure total forces and moments on the tip. The three section of the NASA-Langley 0.3 m Transonic Cryogenic Tunnel dimensional lift was computed from the two dimensional life (TCT) and in the National Aeronautical Establishment (NAE) High distributions obtained from the LV and from the strain gage balance. Reynolds Number 2-D facility. The model has a 9 in. chord and a The results from both experimental methods are shown to be in CAST 10-2IDOA 2 airfoil section. The 0.3 m TCT adaptive Wall agreement with predictions made by a steady, three dimensional test section has four solid walls with flexible top and bottom walls. panel code, VSAERO. Author The NAE test section has porous top and bottom walls and solid side walls. The aerodynamic results corrected for top and bottom N89-20964'# National Aeronautics and Space Administration. wall interference at Mach numbers from 0.3 to 0.8 at a Reynolds Ames Research Center, Moffett Field, CA. number of 10 by 1,000,000. Movement of the adaptive Walls was THREE-DIMENSIONAL SINGULAR POINTS IN used to alleviate the top and bottom wall interference in the test AERODYNAMICS results from the NASA tunnel. Author AYNUR UNAL Jan. 1988 19 p Prepared in cooperation with Army Aviation System s Command, Saint Louis, MO Submitted N89-20962# Maryland Univ., College Park. Dept. of Aerospace for publication Engineering. (NASA-TM-100045; A-88029; NAS 1.1 5:100045; AD-A197978; UNSTEADY FORCE CALCULATIONS ON CIRCULAR USAAVSCOM-TR-87-A-14) Avail: NTlS HC A03/MF A01 CSCL CYLINDERS AND ELLIPTICAL AIRFOILS WITH CIRCULATION 01A
457 02 AERODYNAMICS
When three-dimensionalseparation occurs on a body immersed unit Reynolds number of 1.0-million per foot. The test equipment, in a flow governed by the incompressible Navier-Stokes equations, test techniques, and the data acquisition and reduction procedures the geometrical surfaces formed by the three vector fields (velocity, are described. Analysis of the hot wire anemometer data is beyond vorticity and the skin-friction) and a scalar field (pressure) become the scope of this report. GRA interrelated through topological maps containing their respective singular points and extrema1 points. A mathematically consistent N89-20967# Air Force Inst. of Tech., Wright-Patterson AFB, description of these singular points becomes inevitable when we OH. School of Engineering. want to study the geometry of the separation. A separated stream EFFECT OF RIBLETS UPON FLOW SEPARATION IN A surface requires, for example, the existence of a saddle-type SUBSONIC DIFFUSER Y.S. Thesis singular point on the skin-friction surface. This singular point is NATHAN W. MARTENS Dec. 1988 102 p actually, in the proper language of mathematics, a saddle of index (AD-A2031 78; AFIT/GAE/AA/88D-23) Avail: NTlS HC AO6/MF two. The index is a measure of the dimension of the outset (set A01 CSCL20D leaving the singular point). Hence, when a saddle of index two is This thesis investigates the effect of riblets upon flow separation specified, a two dimensional surface that becomes separated from in a two-dimensional straight-walled subsonic diffuser. Riblets are the osculating plane of the saddle is implied. The three-dimensional small flow-aligned grooves which can be attached to an singular point is interpreted mathematically and the most common aerodynamic body. Studies involving the application of riblets to aerodynamical singular points are discussed through this turbulent flow over a flat plate have consistently shown a decrease perspective. Author in viscous drag as compared to the same surface without riblets. The purpose of this investigation was to determine the effect N8920965# Air Force Armament Lab., Eglin AFB, FL. applying riblets to the walls of a subsonic diffuser would have Aerodynamics Branch. upon flow separation in the fluid handling device. For this A STUDY OF TRANSONIC DRAG REDUCTION OF A BLUNT investigation, it was found separation was indeed delayed in a CYLINDER BY A CYLINDER PROBE Flnal Report, 18 Oct. diffuser employing riblets as compared to a geometrically identical 1985 - 1 Jul. 1988 M.S. Thesis - Mlssisslppl State Unlv., MS - plain diffuser. For the smaller throat widths, this delay was Aug.1987 significant, being as high as 250 percent due to riblets. As the DAVID H. BRIDGES Aug. 1988 69 p diffuser throat width increased, the delay in flow separation due (AD-A202557; AFATL-TR-88-95) Avail: NTlS HC A04/MF A01 to riblets decreased. Also evident in the investigation was the CSCL 20D strong dependence of flow separation upon throat velocity for the This thesis examines the reduction of the drag of a blunt diffuser with riblets. GRA cylinder by a cylindrical probe in the transonic regime, and determines characteristics of the flowfield from the experimental N89-20968# National Aeronautical Establishment, Ottawa drag coefficient data. The experiment was conducted in the (Ontario). NASA-Ames Research Center 6 x 6 ft supersonic wind tunnel. AN EXPERIMENTAL STUDY OF TRANSONIC BUFFET OF A The model consisted of a blunt cylinder with diameter d2 and SUPERCRITICAL AIRFOIL WITH TRAILING EDGE FLAP several extendable cylindrical probes, yielding probe-to-cylinder B. H. LEE and F. C. TANG Sep. 1988 85 p diameter ratios dl/d2 of 0.248, 0.368, an 0.45, an probe (AD-A203189; NAE-AN-54) Avail: NTlS HC A05/MF A01 length-to-cylinder diameter ratios l/d2 up to 2.0 (3.0 for the CSCL 01A smallest probe). These configurations were tested at Mach numbers A supercritical airfoil with a trailing edge flap has been the between 0.8 and 1.5. C sub D decreased as both 1/d2 and dl/d2 subject of aerodynamic investigation in the National Aeronautical increased, due to the fact that the cylinder face was immersed in Establishment’s High Reynolds Number 2-D Test Facility. The a wake of reduced stagnation pressure created by the probe. effects of flap deflection on buffet intensities and delay of buffet After reaching a minimum, C sub D increased as l/d2 increased, onset at transonic speeds were studied. Buffet boundaries for indicating a transition of the flow over the probe from a lower-drag various flap angles were determined from the divergence of the open cavity mode to a higher-drag open cavity mode to a fluctuating balance normal force measurements (C prime sub N). higher-drag closed cavity mode. This change was rather abrupt, The onset of buffet was obtained from plots of C prime sub N and there was also hysteresis in the supersonic tests in agreement versus C sub L at values of C sub L where the slope was 0.1. with previous experiments. C sub D also reached a minimum and This value for the slope was arbitrarily chosen, but was found to increased as dl/d2 approached 1. C sub D usually increased give consistent results which agreed well with values computed with Mach number due to the increase in stagnation pressure from the criterion using the trailing edge pressure divergence for with M. For a particular range of length and diameter ratios, C those cases where buffet onset is primarily due to trailing edge sub D decreased with increasing M for 0.8 is less than M is less separation. For given flow conditions the deflection of the trailing than 0.95. This was attributed to the transition of the flow over edge flap altered the circulation and hence the position of the the probe from the high-drag closed mode to the low-drag open shock wave and its strength. The variations of these two quantities mode as M increased. GRA with flap angles were determined from pressure measurements carried out on the airfoil surface. The test was performed quite N89-20966# Calspan Field Services, Inc., Arnold AFS, TN. deep inside the buffet regime and shock wave oscillations were INVESTIGATION OF THE DEVELOPMENT OF LAMINAR investigated from spectral analyses of the balance outputs. BOUNDARY-LAYER INSTABILITIES ALONG A COOLED-WALL Fluctuations in the shock motion of approximately 70 Hz were CONE IN HYPERSONIC FLOWS Final Report, 20 - 24 Jun. detected. The drag of the airfoil was computed from the wake 1988 stagnation pressure deficit and the drag penalties for large flap J. C. DONALDSON and M. G. HATCHER Dec. 1988 51 p angles were quite significant. GRA Prepared in cooperation with Arnold Engineering D evelopment Center, Arnold AFS, TN N89-20969# Air Force Inst. of Tech.. Wright-Patterson AFB, (AD-A202587; AEDC-TSR-88-V32) Avail: NTlS HC AO4/MF A01 OH. School of Engineering. CSCL 01A NUMERICAL SIMULATION OF FLOW OVER ICED AIRFOILS Measurements of fluctuating flow and mean flow parameters M.S. Thesls were made in the boundary layer on a cooled wall, sharp 7-deg LARRY A. COLEMAN Dec. 1988 145 p (half-angle) cone in an investigation of wall temperature effects (AD-A203291; AFIT/GAE/AA/88D-4) Avail: NTlS HC A07/MF on the stability of laminar boundary layers in hypersonic flow. The A01 CSCL01A flow fluctuation measurements were made using constant-current This thesis evaluates the performance of an iced NACA 0012 hot-wire anemometry techniques. Boundary-layer profiles and cone airfoil numerically. The full Navier-Stokes equations are solved surface conditions were measured to supplement the hot-wire data. using the Beam-Warming algorithm. Steady-state solutions are Testing was done at Mach numbers 8 and 6 with a free-stream obtained at a Mach number of 0.12 and a Reynolds number based
458 02 AERODYNAMICS
on chord of 1.41 million, for angles of attack from 2 to 8 deg. Lift the treatment of the eddy viscosity development through the shock, and drag curves obtained from the numerical solutions were in the separated regions over the airfoil and in the near wake. compared to experimental data and other numerical results. This This work was critical for obtaining a successful solution on the comparison showed that the Beam-Warming algorithm provides a very difficult test case chosen. GRA good estimate of the lift and drag at angles of attack below stall. Computed lift coefficientswere within 11.5 percent of experimental data. These results were in excellent agreement with other numerical solutions. After stall, however, the code did not predict the expected decrease in lift and the calculated drag coefficient was much lower than the experimental data. Comparison of two local flowfield characteristics with the experimental data was less encouraging. A computed velocity profile was compared to the N89-20972# George Washington Univ., Washington, DC. experimental profile for a station in the separated region on the METHODOLOGY FOR USING STEADY EXPERIMENTAL upper surface. This comparison showed that the computed AERODYNAMIC DATA TO IMPROVE STEADY AND separation bubble is approximately one half the thickness of the UNSTEADY AERODYNAMIC ANALYSIS M.S. Thesis bubble measured experimentally. Flow reattachment location is CAROL DANIELLE WIESEMAN Feb. 1989 110 p another measure of the predictive accuracy of the numerical Avail: NTlS HC AOG/MF A01 scheme. GRA Cmrection factor methodologies were developed which use steady experimental or accurate analytical pressure or force data to correct steady and unsteady aerodynamic calculations obtained OH. School of Engineering. by simpler methods. Three methods of calculating these factors THIN-LAYER NAVIER-STOKES SOLUTIONS FOR A CRANKED were developed to match steady lifting pressure distributions, airfoil DELTA WING M.S. Thesis section properties (lift and moment derivatives) and total force FRANCIS R. SMITH Dec. 1988 100 p and moment derivaties with respect to angle of attack and control (AD-A203292; AFIT/GAE/AA/88D-34) Avail: NTlS HC AO5/MF surface deflection. A rectangular supercritical wing previously tested I A01 CSCL20D in the NASA-Langley Transonic Dynamics Tunnel was used as a For thin, highly swept wings operating at moderate to high test case for the methodology. The reasons for choosing this angles of attack. flow over the wing is dominated by formation of wing as a test case were that an abundance of pressure data leading edge vortices. These vortices produce a minimum pressure were available, both steady and unsteady, at Mach numbers ranging which results in an additional liincrement. The lift increment is from subsonic and transonic, for a range of reduced frequencies. This test case was a severe test for the methodology. Correction factors were calculated to match distributions of lifting pressure derivatives or to match section lift and moment derivatives obtained by the doublet lattice method to the corresponding steady state experimental values. These factors were then applied to steady and unsteady aerodynamic calculations. Author
N8420973'# Continuum Dynamics, Inc., Princeton, NJ. PERFORMANCE OPTIMIZATION FOR ROTORS IN HOVER AND AXIAL FLIGHT T. R. QUACKENBUSH, D. A. WACHSPRESS. A. E. KAUFMAN, and D. B. BLISS (Duke Univ., Durham, NC.) Apr. 1989 41 p (Contract NAS2-12789) (NASA-CR-177524; NAS 1.26:177524) Avail: NTlS HC AOS/MF A01 CSCL01A Performance optimization for rotors in hover and axial flight is 1987 - Jan. 1988 a topic of continuing importance to rotorcraft designers. The aim DON W. KINSEY Nov. 1988 73 p of this Phase 1 effort has been to demonstrate that a linear (AD-A203331; AFWAL-TR-88-3085) Avail: NTlS HC A04/MF optimization algorithm could be coupled to an existing influence A01 CSCL20D coefficient hover performance code. This code, dubbed EHPIC This report describes a numerical solution of the Navier-Stokes (Evaluation of Hover Performance using Influence Coefficients), equations for transonic flow over a thick supercritical airfoil with uses a quasi-linear wake relaxation to solve for the rotor strong shock-induced separation on both the upper and lower performance. The coupling was accomplished by expanding of surfaces. The separated flow region extends from the shock the matrix of linearized influence coefficients in EHPIC to (approximately 50 percent chord) to the trailing edge on both accommodate design variables and deriving new coefficients for surfaces. The report first reviews the processes involved in linearized equations governing perturbations in power and thrust. producing a computational solution of the Navier-Stokes equations These coefficients formed the input to a linear optimization analysis, for a two-dimensional airfoil in a perfect gas. A brief development which used the flow tangency conditions on the blade and in the of the Navier-Stokes equations is provided. The solution algorithm wake to impose equality constraints on the expanded system of used (an explicit predictor-corrector method) is developed and equations; user-specified inequality contraints were also employed described. An algebraic turbulence model used to model the to bound the changes in the design. It was found that this locally turbulent Reynolds stresses is described and the need for such a linearized analysis could be invoked to predict a design change model is discussed. A hyperbolic, two-dimensional procedure for that would produce a reduction in the power required by the rotor producing a computational grid (mesh) is also described. The at constant thrust. Thus, an efficient search for improved versions boundary conditions imposed at the outer regions of the of the baseline design can be carried out while retaining the computational domain (farfield) and at the airfoil Surface are accuracy inherent in a free wakellifting surface performance discussed and described. The second part of the report discusses analysis. Author
459 03 AIR TRANSPORTATION AND SAFETY
03 T. YAVUZ (Karadeniz Technical University, Trabzon, Turkey) Journal of Aircraft (ISSN 0021-8669), vol. 26, May 1989. p. 432-437. refs AIR TRANSPORTATION AND SAFETY The concept of virtual mass is described, and experiments are outlined in which virtual mass and virtual inertia components for a Includes passenger and cargo air transport operations; and aircraft parachute canopy were determined. Results show that these accidents. components depend on the canopy shape and its attitude relative to the airflow; they also depend on the dimensionless acceleration, or acceleration number, of the parachute. Except at high values A89-33825 of acceleration number, these virtual inertia terms are of greater PREDICTING THE EFFECTS OF AIRCRAFT ICING magnitude than corresponding values determined by potential flow Aerospace Engineering (ISSN 0736-2536), vol. 9, March 1989, P. methods, and this is characteristic of unsteady bluff-body flows. 23-26. Their significance is indicated in dynamic behavior prediction for The type and quantity of ice that accumulates on an aircraft the descending fully deployed parachute canopy. Author external component's leading edge depends on the physical properties of the icing cloud, the geometry of the aircraft A89-34891# component, local aerodynamic conditions, and the duration of the MODELING OF PARACHUTE OPENING - AN EXPERIMENTAL water droplet/surface encounter. Aircraft components with relatively INVESTIGATION high radii of curvature have been found to deflect a greater portion CALVIN K. LEE (US. Army, Research, Development, and of the smaller droplets, thereby avoiding severe icing; the greatest Engineering Center, Natick, MA) Journal of Aircraft (ISSN danger accordingly lies with components having smaller radii of 002143669), vol. 26, May 1989, p. 444-451. refs curvature, as found in many general aviation aircraft. Attention is Scaling parameters for the peak opening force and opening given to the results of efforts to determine the effects of surface time of solid cloth parachutes are investigated using the physical icing on flying qualities. O.C. modeling technique. Using Froude number and mass ratio as the two scaling parameters, the correlation of the nondimensionalpeak A89-34444' Miami Univ., Coral Gables, FL. opening force and opening time between the full-scale and the COCKPIT AUTOMATION model parachutes made from the Same 1.1 oz/sq yd ripstop nylon EARL L. WIENER (Miami, University, Coral Gables, FL) IN: Human was not entirely satisfactory. Nylon fabrics with areal densities up factors in aviation. San Diego, CA, Academic Press, Inc., 1988, p. to 14 oz/sq yd were then used to construct full-scale parachutes 433-461. refs so that the 1.1 oz/sq yd model parachute would have a lighter (Contract NCC2-377) fabric. This improved the correlation between the full-scale The aims and methods of aircraft cockpit automation are parachutes and the model parachute, and established the reviewed from a human-factors perspective. Consideration is given importance of scaling canopy fabric as well as Froude number to the mixed pilot reception of increased automation, government and mass ratio for modeling parachute opening. Author concern with the safety and reliability of highly automated aircraft, the formal definition of automation, and the ground-proximity A89-35158'# National Severe Storms Lab., Norman, OK. warning system and accidents involving controlled flight into terrain. TRIGGERED LIGHTNING STRIKES TO AIRCRAFT AND The factors motivating automation include technology availability; NATURAL INTRACLOUD DISCHARGES safety; economy, reliability, and maintenance; workload reduction VLADISLAV MAZUR (NOAA, National Severe Storms Laboratory, and two-pilot certification; more accurate maneuvering and Norman, OK) Journal of Geophysical Research (ISSN 0148-0227), navigation; display flexibility; economy of cockpit space; and military vol. 94, March 20, 1989, p. 3311-3325. Research supported by requirements. T.K. NASA. refs The physical model of Mazur (1989) for triggering lightning A89-34885# strikes by aircraft was used to interpret the initiation of intracloud EXPERIMENTAL INVESTIGATION OF ELECTROSTATIC FIRE flashes observed by the French UHF-VHF interferometric system. ACCIDENTS AFTER AIRCRAFT LANDING AND PREVENTIVE It is shown that both the intracloud discharges and MEASURES airplane-triggered lightning strikes were initiated by simultaneous HANSHENG LUO (Air Force, Institute, Beijing, People's Republic bidirectional development of the negative stepped leader and the of China) Journal of Aircraft (ISSN 0021-8669), vol. 26, May positive leader-continous current process. However, the negative 1989, p. 405-409. stepped leader phase in triggered flashes is of shorter duration This work is an experimental investigation to determine the (tens of milliseconds), than that in intracloud flashes (usually cause of electrostatic fire accidents after aircraft landing and to hundreds of milliseconds). This is considered to be due to the clarify the effects of various factors on the cause. This research fact that, on the aircraft there is a single initiation process, versus work has conducted a series of ground simulation tests and actual the numerous initiation processes that occur inside the cloud. flight tests under the fire and explosion environment conditions. IS. The test results have indicated that the process of an aircraft landing run is the fundamental process of electrostatic charges A89-35200# generating in fuel tanks. After an aircraft comes to a stop, there ADVANCED TECHNIQUES USED IN KANISHKA AIRCRAFT is also a process of accumulation of electrostatic charges, while ACCIDENT INVESTIGATION fuel charged with higher energy remains for a considerably long H. S. KHOLA (Directorate General of Civil Aviation, New Delhi, period, unable to dissipate. All kinds of unbonded conductors in India) Aeronautical Society of India. Journal (ISSN 0001-9267), the tank are electrodes for dangerous spark discharges. When an VOI. 40, Aug. 1988, p. 215-220. aircraft using RP-2 fuel flies in hot weather, the concentration of This paper discusses methods used in the investigation of the flammable vapor produced in the space above the fuel surface June 23, 1985 accident involving an Air India aircraft, Kanishka, inside of the tank will, under certain conditions, come close to its which left no survivals or witnesses and only 3-5 percent of aircraft chemical equivalent, thus possessing the condition of combustibles wreckage, mostly nonstructural parts, floating on water, close to under which an electrostatic spark can cause fires and explosions. the position in the Atlantic Ocean where the aircraft disappeared Some principles that should be followed in aircraft fuel system from the radar screan. Data available included the cockpit voice design are discussed. Author recorder tapes; microscopic examinations of the forward cargo compartment skin and the fuselage skin around the 2R door; A89-34889# examination of bodies recovered; and cornpailsons of observations DETERMINING AND ACCOUNTING FOR A PARACHUTE on the wreckage remains with fractures produced in experimental VIRTUAL MASS explosion in skin panels, stringers, and tubes. Data led to the
460 03 AIR TRANSPORTATION AND SAFETY conclusion that the cause of the accident was a bomb explosion. A89-35211# Evidence is presented that connects the Kanishka explosion with HIGH ALTITUDE PARACHUTE AND ITS MILITARY a bomb explosion at the Narita airport. I.S. APPLICATIONS M. L. CHAURASIA and RAJESH KUMAR (Aerial Delivery Research and Development Establishment, Agra, India) IN: AlAA A89-35201 Aerodynamic Decelerator Systems Technology Conference, 1Oth, AlAA AERODYNAMIC DECELERATOR SYSTEMS Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, TECHNOLOGY CONFERENCE, lOTH, COCOA BEACH, FL, DC, American Institute of Aeronautics and Astronautics, 1989, p. APR. 18-20, 1989, TECHNICAL PAPERS 60-63. refs Conference sponsored by AIAA. Washington, DC, American (AIAA PAPER 89-0893) Institute of Aeronautics and Astronautics, 1989,326 p. For individual The high altitude parachute (HAP) design presently discussed items see A89-35202 to A89-35247. was first projected as a military requirement in light of the The present conference on advanced aerodynamic decelerator inadequacies and hazards associated with parachuting at high technologies discusses prospective US. Army airdrop technology altitudes. The design proceeds from the environmental requirements, future aircraft escape capsules, high-altitude characteristics of low air density, atmospheric pressure variations, decelerator systems, pilot ejection from a prone flying position, an etc. A three-stage HAP deployment scheme addresses the hazards in!!ataD!e triangular accelerator. a novel recovery parachute system associated with emergence from a high-speed aircraft at extreme for the F-111 crew-escape module, the prediction of parachute diitiides; a ny!m fabric o! u!!ra!ow porosity has been developed collapse due to wake recontact, the tethered parafoil test technique, and incorporated into the design to preclude an initially excessively and a piloted cargo-delivery system employing ram-air parachutes. swift descent. O.C. Also discussed are a 10,000-lb capacity ram-air parachute, the numerical analysis of three-dimensional nonrigid wings, innovative A89-35212# parachute materials, lightweight Kevlar parachute fabrics, aging THE DEVELOPMENT OF THE PANEL STABILIZED effects on nylon parachutes, a low-altitude tactical assault SLOTTED-SQUARE PARACHUTE parachute, a national data bank on parachute textile materials, a CARL T. CALIANNO (U.S. Navy, Naval Air Development Center, vortex-panel analysis of circular-arc bluff -bodies in unsteady flow, Warminster, PA) IN: AlAA Aerodynamic Decelerator Systems a seat-mounted combined harness, and a ’whirltower’ test facility. O.C. Technology Conference, 1Oth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American Institute of Aeronautics and Astronautics, 1989, p. 64-70. (AIAA PAPER 89-0894) A89-35207# Stabilization panels have been incorporated by a slotted square AERIAL DELIVERY OF PERSONNEL IN GROUND PROXIMITY parachute. Wind tunnel tests have been conducted to ascertain HENRY J. HUNTER (Douglas Aircraft Co., Long Beach, CA) and how various stabilizing panel configurations affect the drag and MICHAEL J. WUEST (USAF. Flight Test Center, Edwards AFB, stability performance of this parachute configuration; the CA) IN: AlAA Aerodynamic Decelerator Systems Technology configurations extended to ribless-guide surface, conical, and cross Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical parachutes. These parachutes have furnished reference-points for Papers. Washington, DC, American Institute of Aeronautics and the determination of wind tunnel test technique accuracy and the Astronautics, 1989. p. 38-43. comparison of novel design performance characteristics with those (AIAA PAPER 89-0887) of existing parachute types. Flight testing was then conducted to The long-used low-altitude parachute extraction system (LAPES) verify wind tunnel results. It is found that simple stabilizing panels by which heavy equipment and supplies can be offloaded from an will yield twice the stabilizing moment as ribless parachute aircraft flying just above ground level is presently extended to configurations. O.C. deliver military personnel capsules that will preclude the wide dispersion and great vulnerability of parachute drops. Attention is given to the limits of human tolerance to the decelerations A89-35213# associated with this type of LAPES application; the means of A REVISION OF THE ADDED MASS CONCEPT AS APPLIED controlling or limiting these deceleration forces are analyzed, and TO PARACHUTE MOTION the results from earlier tests using a ground proximity extraction D. J. COCKRELL, Y. I. FRUCHT, and R. J. HARWOOD (Leicester, system are compared with those for a LAPES. Basic design University, England) IN: AlAA Aerodynamic Decelerator Systems concepts for a LAPES personnel capsule are presented. O.C. Technology Conference, 1Oth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American Institute of Aeronautics and Astronautics, 1989, p. 71-77. Research supported A89-35210# by the Ministry of Defence Procurement Executive. refs A CONTROL CANOPY RELEASE METHOD FOR IMPROVED (AIAA PAPER 89-0895) OPENING OF CLUSTERED PARACHUTES A parachute canopy is an immersed body for which the rate CALVIN K. LEE and JAMES E. SADECK (U.S. Army, Research, of change of momentum of the air in which it is immersed is of Development and Engineering Center, Natick, MA) IN: AlAA the order of that of the canopy and hence the equations of motion Aerodynamic Decelerator Systems Technology Conference, 10th. for the latter must also include the former. This rate of change of Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, momentum of the air is allowed for by added mass components, DC, American Institute of Aeronautics and Astronautics, 1989, p. the magnitudes of which must be determined experimentally. In 53-59. refs general, unsteady motion through fluids of bluff bodies like (AIAA PAPER 89-0892) parachute canopies is very complex and the coefficients of these This paper presents a concept and a method for achieving added mass components can be shown to be dependent on the simultaneous opening of clustered parachutes. The concept is to immersed body shape and attitude, the flow Reynolds number inflate the parachutes in a cluster as though they were one large and on either the instantaneous acceleration number or the parachute. The method involves partial reefing of the parachutes, oscillation’s Keulegan-Carpenter number. However, at the connecting them together during opening, and releasing them at Keulegan-Carpenter numbers normally encountered by the almost full inflation. This method, called control canopy rehSe oscillatory pitching motion of fully-inflated parachute canopies the method, was tested with two-G12 (64-foot-diameter, flat-circular relevant added mass coefficient are of negligible magnitudes and cargo parachutes), three-Gl2, and three-C9 (28-foot-diameter, need not be considered further in the relevant equations of motion. flat-circular, personnel parachutes) clusters. Their opening was The effects of neglecting these added mass coefficients are significantly improved when compared to the opening of the Clusters considered by reference to the root-locus diagram which follows without using this method. Author from their linearization. Author
46 1 03 AIR TRANSPORTATION AND SAFETY
A89352 19# low weight throughout the flat, tubular, and transition sections. A TETHERED PARAFOIL TEST TECHNIQUE tubular section strength of 535 Ibs at a weight of 0.044 oz/yd GLEN J. BROWN (Vertigo, Inc., Lake Elsinore, CA) IN: AlAA was achieved. This reduces suspension line weight by 8 percent Aerodynamic Decelerator Systems Technology Conference, 1Oth, compared with that of the most efficient braid which has a strength Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, of 470 Ibs and weighs 0.048 oz/yd. Length measuring procedures DC, American Institute of Aeronautics and Astronautics, 1989, p. for production control and inspection were developed. Using these 110-113. Research supported by the Developmental Sciences procedures it was possible to produce alternating weave fabric cop with less than 1 percent variation in length in the tubular (AIAA PAPER 89-0903) sections. Author A test technique has been developed and is now in use that is effective in measuring the performance of full scale Parafoils. A8935227# The method involves tethering the Parafoil under test to an INVESTIGATION OF THE SERVICE AND AGE LIVES OF U.S. instrumented test rig on a truck. Measurements of airspeed, tether ARMY PERSONNEL PARACHUTES tension and tether angle are used to determine the Parafoil’s LID ROBERT J. COSKREN (Albany International Research Co., and lift coefficient. For development testing a device is added Mansfield, MA) and ERWIN A. WUESTER (US. Army, Research, that allows trim and camber changes to be made while running. Development and Engineering Center, Natick, MA) IN: AlAA The test rig has been used with Parafoils from 18 q ft to 800 Sq Aerodynamic Decelerator Systems Technology Conference, 1Oth, ft. Data reduction techniques and examples of results are Cocoa Beach, FL, Apr. 18-20. 1989. Technical Papers. Washington, presented. Author DC, American Institute of Aeronautics and Astronautics, 1989, p. 159-165. refs A8935220# (AIAA PAPER 89-0915) THE DEVELOPMENT OF A 10,000 LB CAPACITY RAM AIR The suspension lines from 30 US. Army and 32 U.S. Forestry PARACHUTE Service parachutes were studied to determine the effect of age E. PUSKAS (Para-Flite, Inc., Pennsauken, NJ) IN: AlAA and/or service on their tensile behavior. The data showed a gradual Aerodynamic Decelerator Systems Technology Conference, 1Oth, loss of line strength with age and/or service of the U.S. Forestry Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, Service parachutes studied. The controlled deployment of four DC, American Institute of Aeronautics and Astronautics, 1989, p. parachutes at the Yuma Proving Ground and the Naval Weapons 114-120. Research supported by Para-Flite, Inc. Center indicated that the deployment of a parachute under severe (AIAA PAPER 89-0904) conditions of load or velocity can result in seriously weakened The design and development of a 3,000 sq ft, 10.000 Ib capacity. suspension lines. This may be due to the development of structural ram air parachute is described. Design philosophy structural and imbalance between the core and sheath of the line. K.K. aerodynamic considerations of the design, manufacturing and testing are outlined and discussed. Because large ram air A89-35228# parachutes carrying thousands of pounds become unguided PERSONNEL PARACHUTE AGE/SERVICE LIFE CRITERIA missiles during testing, it was necessary to develop a means of ROBERT W. RODIER, ERWIN A. WUESTER, and JAMES E. HALL controlling and guiding the parachute during the test phase. The (U.S. Army, Research, Development and Engineering Center, means of guidance developed for this purpose is also covered, Natick, MA) IN: AlAA Aerodynamic Decelerator Systems although briefly. Author Technology Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American Institute of A8935221# Aeronautics and Astronautics, 1989, p. 166-171. refs EVOLUTION OF THE MANTA-RAY PARACHUTE (AIAA PAPER 89-0916) M. J. RAVNITZKY (Irvin Industries, Inc., Santa Ana, CA) IN: A simple dynamic test technique is developed for laboratory AlAA Aerodynamic Decelerator Systems Technology Conference, testing of Army personnel parachute suspension lines in order to loth, Cocoa Beach, FL. Apr. 18-20, 1989, Technical Papers. provide insight into their degradation mechanisms. Cyclic loading Washington, DC, American Institute of Aeronautics and tests of MIL-C-5040 Type \I nylon cord are performed using a 10 Astronautics, 1989, p. 121-1 24. refs minute relaxation period between loadings on clean lines and lines (AIAA PAPER 89-0906) contaminated with sand and grit particles. It is found that the The ’manta-ray’ parachute configuration, which can be primary source of suspension line strength degradation is the characterized as a ring-sail parachute with ram air-inflated leading incidental inclusion of sand and grit particles during parachute edge, has demonstrated LID values as high as 2.17 in extensive retrieval. Most strength loss occurs during the first 30-50 cycles ground and aerial testing. Technical concerns to which attention or uses. The number of uses and geographical differences in was given during developmental testing encompassed reefing, sand particles are found to be far more important in establishing leading-edge collapse, LID modulation, and turn control. A the service life than is date of manufacture. S.A.V. comparison of test results with ram-air parachute performance suggests a continuum between the characteristics of inflated airfoil A8935231# parachutes and those of ballistic parachutes incorporating a glide THE DEVELOPMENT AND TESTING OF THE HISAC capability. The data obtained on various parachute parameters PARACHUTE RECOVERY SYSTEM may be applicable to ram-air parachute optimization. O.C. VANCE L. BEHR (Sandia National Laboratories, Albuquerque, NM) IN: AlAA Aerodynamic Decelerator Systems Technology A8935223# Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical DEVELOPMENT OF AN ALTERNATING FLAT TO TUBULAR Papers. Washington, DC, American Institute of Aeronautics and KEVLAR PARACHUTE TAPE Astronautics, 1989, p. 187-192. Research sponsored by the U.S. R. H. ERICKSEN (Sandia National Laboratories, Albuquerque, NM) Army. refs and R. KOCH (Bally Ribbon Mills, PA) IN: AlAA Aerodynamic (Contract DE-AC04-76DP-00789) Decelerator Systems Technology Conference, 1Oth, Cocoa Beach, (AIAA PAPER 89-0921) FL, Apr. 18-20, 1989, Technical Papers. Washington, DC,. American Through the use of analyses and airdrop and ground tests, a Institute of Aeronautics and Astronautics, 1989, p. 133-142. high performance parachute recovery system has been developed Research supported by USAF. for the High Speed Airdrop Container (HISAC) program. Airdrop (AIAA PAPER 89-0910) and ground test results indicate that the use of a reefed and An alternating flat to tubular Kevlar tape was developed to staged drogue in conjunction with a cluster of three standard replace braided suspension lines and woven tape radials on the unreefed T-10 personnel parachutes provides the best combined new crew escape module parachute system for the F-11 1 aircraft. turnover and impact velocity characteristics. Initial deployment of Weaves were developed which had high strength efficiency and the drogue parachute is produced by an aerodynamically deployed
462 03 AIR TRANSPORTATION AND SAFETY tailplate which produces no appreciable carriage drag. Ground test conventional open-type ejection seat (S4S) and highlighting the results indicate that reliable deployment of the tailplate is achieved effectiveness and relevance of ongoing Navy 6.2 and 6.3 programs through the use of aerodynamic drag surfaces which are deployed as they relate to the conduct and evaluation of test programs shortly after the HlSAC is released from the carriage aircraft. demonstrating improved life support equipment. This demonstration S.A.V. verified the operation of the IH-1 restraint harness, a U.S. Navy developed instrumentation system incorporated into a modified A8935233# Biofidelic Manikin (which closely emulates the elasticity and rigidity MEASUREMENTS OF INDIVIDUAL PARACHUTE LOADS IN A of the human spine), and stabilization fins which had previously CLUSTERED PARACHUTE SYSTEM been developed for the S4S ejection seat. Author VANCE L. BEHR (Sandia National Laboratories, Albuquerque, NM) IN: AlAA Aerodynamic Decelerator Systems Technology A89-35845 Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical A PRONATED ESCAPE SYSTEM FOR FIGHTER AIRCRAFT Papers. Washington, DC, American Institute of Aeronautics and JEFF OLINGER, JEFF NICHOLSON (USAF, Kirtland AFB, NM), Astronautics, 1989, p. 202-205. Research supported by USAF. and STUART KRAMER (USAF, Institute of Technology, (Contract DE-AC04-76DP-00789) Wright-Patterson AFB, OH) SAFE Journal, vol. 19, Spring 1989, (AIAA PAPER 89-0923) p. 50-55. refs .A small rugged load sensor which can be installed in the riser A forward-leaning (pronated) seat design is proposed which of a parachute system to directly measure parachute loads has meets the requirements of providing adequate support for the pilot been developed. The load sensor consists of a clevis, a spool, during high-acceleration maneuvers, as well as the means of and an instrumented clevis pin. Multiple sensors can be installed escaping the aircraft in an emergency over a wide range of speeds, in each riser of a clustered parachute system to measure the altitudes, and attitudes. The predicted performance of the pronated loads developed by each parachute. The results are presented escape system (PRESS) was estimated for three injury risk levels. from preliminary tests of the load sensor. R.B. It was shown that the PRESS seat with a seat front angle of 35 deg offers increased g-tolerance over conventional upright seats A89-35234# and the same g-tolerance as a 65-deg reclined seat. Compared SMALL PARACHUTE FLIGHT DATA ACQUISITION SYSTEM with existing ejection capsules, the seat is very light, and yet D. E. RYERSON and G. C. HAUSER (Sandia National Laboratories, offers better protection than capsules. I.S. Albuquerque, NM) IN: AlAA Aerodynamic Decelerator Systems Technology Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, A89-36019# Technical Papers. Washington, DC, American Institute of PARACHUTES - YESTERDAY, TODAY, AND TOMORROW Aeronautics and Astronautics, 1989, p. 206-210. T. W. KNACKE AIAA, Aerodynamic Decelerator Systems (AIAA PAPER 89-0924) Technology Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989. A small data acquisition system for parachute design and testing 8 p. refs is examined. The system consists of a microprocessor-controlled (AIAA PAPER 89-0880) unit which digitizes data from up to eight analog gauge inputs and A brief historical overview of parachute development is stores the digitized data. The system specifications are listed and presented, citing their use from 1930 to the use of drogue chutes mechanical, electrical, and software descriptions of the system for Space Shuttle SRB recovery. Figures presented show the are given. The use of the system in parachute and water entry growth of parachute deployment velocity from the 1940s to the tests is discussed. R.B. 1990s and the growth in parachute fabric fiber strength from 1930 to 1980. Future requirements for parachutes in the field of air A89-35245# vehicle recovery are cited, including high-strength materials, A SEAT-MOUNTED COMBINED HARNESS high-drag parachute canopies, and low total parachute forces, in J. P. MURRAY (Grumrnan Corp., Aircraft Systems Div., Bethpage, order for parachute assemblies to have minimum weight and NY) IN: AlAA Aerodynamic Decelerator Systems Technology compartment volume. The need for a new whirl tower with Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical performance matching current requirements is mentioned. S.A.V. Papers. Washington, DC, American Institute of Aeronautics and Astronautics, 1989, p. 297-301. (Contract N62269-83-C-0233) A89-36020# (AIAA PAPER 89-0937) RADIUS-TIPPED TRIANGULAR INFLATABLE DECELERATOR The preliminary development of a seat-mounted combined DESIGN AS AFFECTED BY harness and survival undergarment for the U.S. Navy that meets PRODUCEABlLITY/SURVIVABlLlTY CONSTRAINTS the criteria of flight restraint, ejection, parachuting, and crash PATRICK J. CANNON and MARK A. KOCH (Raven Industries, conditions is discussed. This effort was part of an attempt to Inc., Sioux Falls, SD) AIAA, Aerodynamic Decelerator Systems develop and qualify a number of specific point designs for retrofitting Technology Conference, 10th. Cocoa Beach, FL, Apr. 18-20, 1989. improved restraint equipment into various operational escape 9 P. systems. Harnesses were manufactured to conduct ejection tower (AIAA PAPER 89-0888) testing, windblast tests, water drag tests, negative 'g' tests, cockpit A concept for a sewn fabric decelerator/stabilizer is presented compatibility tests, and live parachute jumps over land and water. and discussed. General requirements for the device are presented K.K. and strengths and limitations of various competing concepts are contrasted and discussed. The conflict between the need for A8935841 simple, low cost design for high volume produceability and more TRANSONIC/SUPERSONIC (720 KEAS 1.2 MACH) EJECTION complex designs and usage of expensive materials in order to DEMONSTRATION TEST OF AN S4S BlOFlDELlTY MANIKIN ensure survivability is discussed. A proprietary Raven Industries (BFM1) design is presented which addresses this conflict by using flat-panel LAWRENCE E. KINKER, ROBERT MCCONNELL, GEORGE construction to create a decelerator which develops an effective FRISCH (U.S. Navy, Naval Air Development Center, Warminster, three dimensional shape when inflated. Conceptual sketches of PA), and DONALD E. MCCAULEY (Universal Propulsion Co., Inc., decelerator designs are provided. Author Phoenix, AZ) SAFE Journal, vol. 19, Spring 1989, p. 8-13. In September 1988 a 725 KEAS ejection demonstration test N89-20108# National Transportation Safety Board, Washington, was conducted at Hurricane Mesa, Utah, using an S4S ejection DC. Bureau of Safety Programs. seat and Navy configured Biofidelic Manikin. The conduct of this AIRCRAFT ACCIDENT DATA, US GENERAL AVIATION, test was specifically geared toward demonstrating the feasibilty of CALENDAR YEAR 1986 Annual Review Report aircrew recovery at transonic/supersonic air speed with a 25 Oct. 1988 166 p
463 03 AIR TRANSPORTATION AND SAFETY
(PB89-121453; NTSB/ARG-88/01) Avail: NTlS HC AO8/MF A01 27 Sep. 1988 97 p CSCL 01c (PB88-910411; NTSB/AAR-88/09) Avail: NTlS HC A05/MF The report presents a statistical compilation and review of A01; also available on subscription, North American Continent HC general aviation accidents which occurred in 1986 in the United $70.00/year; all others write for quote CSCL 01 C States, its territories and possessions, and in international waters. The National Transportation Safety Board decided that the The accidents reported are all those involving U.S. registered probable cause of the accident was the captain's failure to have aircraft not conducting operations under 14 CFR 121, 14 CFR the aircraft deiced a second time after a delay before takeoff that 125, 14 CFR 127, or 14 CFR 135. The report is divided into five led to upper wing surface contamination and a loss of control sections: All Accidents; Fatal Accidents; Serious Injury Accidents; during rapid takeoff rotation by the first officer. Contributing to the Property Damage Accidents and Midair Collision Accidents. Several accident were the absence of regulatory or management controls tables present accident parameters for 1986 accidents only, and governing operations by newly qualified flight crew members and each section includes tabulations which present comparative the confusion that existed between the flight crew and the air statistics for 1986 and for the five-year period 1981 to 1985. traffic controllers that led to the delay in departure. Author GRA N89-20974# General Accounting Office, Washington, DC. N89-20109# National Transportation Safety Board, Washington, AVIATION SAFETY: MEASURING HOW SAFELY INDIVIDUAL DC. Bureau of Field Operations. AIRLINES OPERATE AIRCRAFT ACCIDENT REPORTS BRIEF FORMAT, US CIVIL Mar. 1988 40 p AND FOREIGN AVIATION, ISSUE NUMBER 12 OF 1986 (GAO/RCED-88-61) Avail: NTlS HC AO3/MF A01 ACCIDENTS The deregulation of airline fares and schedules in 1978 led to 30 Mar. 1988 427 p rapid growth and change in the airline industry, placing increased fPB88-916902: NTSB/AAB-88/02) Avail: NTlS HC A1 9/MF A01; burdens on FAA's airline inspection program. Because of growing also available on subscription, North American Continent HC concern that airlines may be operating less safely under $1 85.00/year; all others write for quote CSCL 01C deregulation, improved ways to measure how safely individual The publication contains selected aircraft accident reports in airlines operate are sought. Information was provided on the Brief Format occurring in US. civil and foreign aviation operations feasibility of developing and publishing for air travelers indicators during Calendar Year 1986. Approximately 200 General Aviation that compare how safely individual airlines operate. The focus and Air Carrier accidents contained in the publication represent a was on identifying: areas of airline performance recognized as random selection. The publication is issued irregularly, normally important to airline safety, the availability and quality of data in eighteen times each year. The Brief Format represents the facts, these areas, and ongoing research on measuring individual airline conditions, circumstances, and probable cause(s) for each safety. Author accident. GRA N89-20975# Naval Environmental Prediction Research Facilitv, N89-20110# National Transportation Safety Board, Washington, Monterey, CA.
DC. Bureau of Field Operations. ICING CONSIDERATIONS~~ ~~~ FOR HALE (HIGH ALTITUDE. LONG AIRCRAFT ACCIDENT REPORTS, BRIEF FORMAT, US CIVIL ENDURANCE) AIRCRAFT Final Technical Report AND FOREIGN AVIATION, ISSUE NUMBER 14 OF 1986 GERARD N. VOGEL Nov. 1988 54 p ACCIDENTS (AD-A202584; NEPRF-TR-88-11) Avail: NTlS HC A04/MF A01 11 Aug. 1988 347 p CSCL 048 (PB88-916904; NTSB/AAB-88/04) Avail: NTlS HC A1 5/MF A01 ; Although a low probability event, ice accretion does present a also available on subscription, North American Continent HC major obstacle to safe aircraft operations. In this report, the $185.00/year; all others write for quote CSCL 01C character of the aircraft icing environment is explored in terms of The publication contains selected aircraft accident reports in key meteorological and aerodynamic factors as related to the HALE Brief Format occurring in U.S. civil and foreign aviation operations (High Altitude, Long Endurance) aircraft. The distribution of icing during Calendar Year 1986. Approximately 200 General Aviation in the atmosphere, mainly a function of temperature and cloud and Air Carrier accidents contained in the publication represent a structure, is presented. Ice forecasting techniques and icing random selection. The publication is issued irregularly, normally instrumentation are discussed as viable approaches for minimizing eighteen times each year. The Brief Format represents the facts, potential aircraft icing hazards. It is concluded that an onboard conditions, circumstances and probable cause(s) for each ice accumulation detector in combination with ground-basedremote accident. GRA sensing instrumentation would provide the best capability icing forecasting program, which is often both effort- and time-efficient, N89-20111'# Sierra Nevada Corp., Reno. is recommended. GRA ANALYSIS OF DOPPLER RADAR WINDSHEAR DATA Final Report N89-20976# Air Force Flight Dynamics Lab., Wright-Patterson F. WILLIAMS, P. MCKINNEY, and F. OZMEN Jan. 1989 AFB, OH. 189 p IN-FLIGHT LIGHTNING CHARACTERIZATION PROGRAM ON (Contract NAS1-18598) A CV-580 AIRCRAFT Final Report, Oct. 1983 - Sep. 1987 (NASA-CR-181762; NAS 1.26~181762;DOT/FAA/PS-88/19) HAROLD D. BURKET, LAWRENCE C. WALKO, JEAN S. REAZER, Avail: NTlS HC AO9/MF A01 CSCL 01C and ARTURO V. SERRANO Jun. 1988 185 p The objective of this analysis is to process Lincoln Laboratory (AD-A203954; AFWAL-TR-88-3024) Avail: NTlS HC AO9/MF Doppler radar data obtained during FLOWS testing at Huntsville, A01 CSCLO4B Alabama, in the summer of 1986, to characterize windshear events. A CV-580 aircraft was instrumented with external displacement The processing includes plotting velocity and F-factor profiles, current density sensors, surface current density sensors, current histogram analysis to summarize statistics, and correlation analysis shunts, and static electric field mill sensors and was flown in to demonstrate any correlation between different data fields. active thunderstorms in central Florida during the summer of 1984 Author and 1985. Electromagnetic data were collected and analyzed for 52 direct lightning strikes to the aircraft flying at altitudes between N89-20112# National Transportation Safety Board, Washington, 2,000 and 18,000 ft. The data consisted of analog records with DC. Bureau of Accident Investigation. dc to 2-MHz bandwidth and 10-us windows of digital samples AIRCRAFT ACCIDENT REPORT CONTINENTAL AIRLINES, taken at 5-ns intervals. The data show the physical mechanism of INC., FLIGHT 1713, MCDONNELL DOUGLAS DC-9-14, N626TX, lightning attachment to aircraft and suggest comparison of aircraft STAPLETON INTERNATIONAL AIRPORT, DENVER, responses to lightning and simulated NEMP is also provided. COLORADO, NOVEMBER 15,1987 GRA
464 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
04 The results of comparing four different frequency estimation schemes in the presence of high dynamics and low carrier-to-noise ratios are given. The comparison is based on measured data from AIRCRAFT COMMUNICATIONS AND NAVIGATION a hardware demonstration. The tested algorithms include a digital phase-locked loop, a cross-product automatic frequency tracking Includes digital and voice communication with aircraft; air navigation loop, and extended Kalman filter, and finally, a fast Fourier systems (satellite and ground based); and air traffic control. transformation-aided cross-product frequency tracking loop. The tracking algorithms are compared on their frequency error performance and their ability to maintain lock during severe A8933567 maneuvers at various carrier-to-noise ratios. The measured results DATA LINKS FOR VIDEO AND IR SURVEILLANCE are shown to agree with simulation results carried out and reported JOHN R. SHARMAN (STC Defence Systems, PLC, Radio and previously. Author Microwave Div., Paignton, England) IN: Remotely piloted vehicles; International Conference, 7th, Bristol, England, Sept. 12-14, 1988, Proceedings. Bristol, England, University of Bristol, 1988, p. 21 .l-21.12. Research supported by the Ministry of Defence. N89-20114# Royal Signals and Radar Establishment, Malvern Four data link types for robotic surveillance aircraft applications (England). are presented whose architectures are moauiar and reconfigurabie THE APPLICATION OF SOFTWARE FAULT TOLERANCE TO to meet a wide variety of requirements with minimum time and AIR TRAFFIC CONTROL: STUDY CONTRACT OVERVIEW cost. QPSK and TDM are employed in the RF communications L. N. SIMCOX Jun. 1988 21 p system design to permit tuning over a wide band, and both low-GHz (BR108567; RSRE-MEMO-4114) Avail: NTlS HC AO3/MF A01 and multi-GHz RF architectures can be implemented using a An overview of research done on the application of software common modem and channelization architecture. Spread-spectrum fault tolerance to air traffic control (ATC) systems is provided. A coding may be added to the downlink in order to protect the requirements analysis of the London Air Traffic Control Centre telemetry and sensor timing. The high level of antijamming (LATCC) was developed using the CORE method with automated performance thus achieved furnishes further gains in flexibility. support. This was then taken as the basis for a MASCOT design O.C. of the LATCC Radar Data Processing subsystem. This design was converted into one with the software fault tolerant features A8933572 of Recovery Blocks in a MASCOT-like environment. Author DEVELOPMENT OF A LOW COST TRACKING/RANGING SYSTEM H. CUCKSON IN: Remotely piloted vehicles; International Conference, 7th, Bristol, England, Sept. 12-14, 1988, N89-20115# National Aerospace Lab., Amsterdam (Netherlands). Supplementary Papers. Bristol, England, University of Bristol, 1988, Flight Div. p. 20.1 -20.5. THE APPLICATION OF TRAJECTORY PREDICTION An account is given of the Skytrack low cost tracker for ALGORITHMS FOR PLANNING PURPOSES IN THE unmanned aircraft (UMA) operations, which in addition to NETHERLANDS AIR TRAFFIC CONTROL (ATC) SYSTEM location-finding furnishes all the up/downlinks required by J. N. P. BEERS, T. B. DALM, J. M. TENHAVE, and H. VISSCHER surveillance and target-practice UMAs. A phase-comparison 29 Oct. 1986 15 p Submitted for publication interferometer system was chosen for the tracker, since it can (NLR-MP-87031-U; ETN-89-94034) Avail: NTlS HC A03/MF furnish high accuracy and resolution with antennas that are of A0 1 only modest gain. The transmitter is of conventional, 0-band The Netherlands ATC-environment, the basic set-up of the telemetry type, with a stabilized oscillator. The system is highly trajectory prediction module, improvements realized, and the portable, and can be set up by a single person. The development performance figures are presented. Applications of the trajectory capability for a covert, ECM-resistant system is also offered. prediction results in the system are listed, including data distribution O.C. rules, presentation of estimated times of arrival, boundary estimates, and, in particular, long-term detection of conflicts for A89-33573 overflying aircraft, planning in inbound traffic for Schiphol airport, SOME CONSEQUENCES OF REDUCED FRAME RATE FOR and planning of departure times for an efficient engine start-up OPERATOR PERFORMANCE procedure. ESA MICHAEL H. REJMAN (Army Personnel Research Establishment, Farnborough, England) IN: Remotely piloted vehicles; International Conference, 7th, Bristol, England, Sept. 12-14, 1988. Supplementary Papers. Bristol, England, University of Bristol, 1988, N89-20117# National Aerospace Lab., Amsterdam (Netherlands). p. 22.1-22.7. refs Flight Div. Results we presented from an experiment which examined CONTINUOUS-DISCRETE FILTERING FOR SYSTEMS WITH the effect of reduced frame-rate TV transmission from RPVs, in MARKOVIAN SWITCHING COEFFICIENTS order to reduce bandwidth requirements while retaining the H. A. P. BLOM 30 Oct. 1987 20 p Presented at the 21st real-time Surveillance capabilities required in terrain feature- Asilomar Conference on Signals, Systems and Computers, Pacific following flying tasks. Attention was also given in this study Grove, CA, 2-4 Nov. 1987 to the effects of such image manipulation on the secondary task (NLR-MP-87076-U; ETN-89-94046) Avail: NTlS HC AOS/MF of target-detection. The results obtained demonstrate that A01 frame-rate reduction can have serious deleterious effects on the The classical continuous-time linear system with Markovian conduct of such tasks. The implications of these results for the switching coefficients is extended, to incorporate jumps in R sup operation of RPVs are discussed, with emphasis on the importance n which occur simultaneously with coefficient switching. This system of human factors considerations. O.C. is defined by a stochastic differential equation in a hybrid space, which is driven by a Brownian motion and a Poisson random N8920113'# Jet Propulsion Lab., California Inst. of Tech., measure with a randomly time-changed mean measure. The exact Pasadena. continuous-discrete filter for such a system is approximated by a HIGH-DYNAMIC GPS TRACKING Final Report numerical algorithm, which is in its most simple form the interacting S. HlNEDl and J. 1. STATMAN 15 Dec. 1988 95 p multiple model algorithm. For application to the problem of tracking (Contract NAS7-918) a maneuvering aircraft, given measurements of uncertain origin, (NASA-CR-184868; JPL-PUBL-88-35; NAS 1.26:184868) Avail: the obtained methods can easily be combined with probabilistic NTlS HC AO5/MF A01 CSCL 17G data association. ESA
465 04 AIRCRAFT COMMUNICATIONS AND NAVIGATION
N89-20119# Sandia National Labs., Albuquerque, NM. baselines show rms daily repeatability of 0.3 to 2 parts in 10 to Exploratory Systems Development Div. the 8th power and agree with very long base interferometry (VLBI) TRAJECTORY SCORING IN RECTANGULAR COORDINATES solutions at the level of 1.5 parts in 10 to the 8th power. This USING TRANSPONDER-INTERROGATOR RANGE AND RANGE GPS demonstration provides an opportunity to test different RATE DATA techniques for high-accuracy orbit determination for high Earth JEFF HOLLOWELL Jan. 1989 247 p orbiters. The best GPS orbit strategies included data arcs of at (Contract DE-AC04-76DP-00789) least 1 week, process noise models for tropospheric fluctuations, IDE89-007005: SAND-87-1850) Avail: NTlS HC A1 1/MF A01 estimation of GPS solar pressure coefficients, and combine \---- - Range and range rate measurements taken from a processing of GPS carrier phase and pseudorange data. For data transponder-interrogator ranging system are processed via an arc of 2 weeks, constrained process noise models for GPS dynamic extended Kalman filter and an extended Kalman smoother to parameters significantly improved the situation. Author provide an accurate time-position history of a vehicle's trajectory by estimating the errors in the vehicle's inertial navigation system. N89-20977# General Accounting Office, Washington, DC. The necessary equations are derived in rectangular coordinates. MICROWAVE LANDING SYSTEMS ADDITIONAL SYSTEMS As such, they are only valid for low altitude flights over a small SHOULD NOT BE PROCURED UNLESS BENEFITS PROVEN geographic area. The equations are implemented in a FORTRAN May 1988 74 p program which is used to process flight data gathered at Edgewood, (GAO/RCED-88-118) Avail: NTlS HC A04/MF A01 NM. DOE Important parts of the national airspace system (NAS) are the precision landing systems which allow aircraft equipped with the N8420330'# Jet Propulsion Lab., California Inst. of Tech., necessary electronic hardware (avionics) to land in conditions of Pasadena. limited visibility, thereby increasing the time an airport can operate DERIVING A GEOCENTRIC REFERENCE FRAME FOR during poor weather. The current precision landing system, the SATELLITE POSITIONING AND NAVIGATION instrument landing system (ILS), is scheduled to be replaced with R. P. MALM (Sterling Software, Pasadena, CA.) and S.-C. WU the microwave landing system (MLS) as part of the Federal Aviation ln its The Telecommunications and Data Acquisition Report p 1-13 Administration's (FAA) effort to modernize the nation's air traffic 15 Nov. 1988 control system-known as the NAS plan. The MLS program was Avail: NTlS HC A12/MF A01 CSCL 17G reviewed, addressing the following objectives: assess the With the advent of Earth-orbiting geodetic satellites, justification and requirements for a new precision landing system nongeocentric datums or reference frames have become things to replace ILS and determine and analyze ILS improvements since of the past. Accurate geocentric three-dimensional positioning is MLS was justified, determine whether FAA has adequately now possible and is of great importance for various geodetic and demonstrated MLS' potential operational and economic benefits, oceanographic applications. While relative positioning accuracy of and determine the reasonableness of FANS MLS siting strategy. a few centimeters has become a reality using very long baseline Author interferometry (VLBI). the uncertainty in the offset of the adopted coordinate system origin from the geocenter is still believed to be N89-20978*# National Aeronautics and Space Administration. on the order of 1 meter. Satellite laser ranging (SLR), however, is Ames Research Center, Moffett Field, CA. capable of determining this offset to better than 10 cm. but this is AH-1S COMMUNICATION SWITCH INTEGRATION PROGRAM possible only after years of measurements. Global Positioning LORAN HAWORTH, ZOLTAN SZOBOSZLAY, ROBERT SHIVELY, System (GPS) measurements provide a powerful tool for an and FRANK J. BlCK (Army Aviation Systems Command, Saint accurate determination of this origin off set. Two strategies are Louis, MO.) Mar. 1989 62 p discussed. The first strategy utilizes the precise relative positions (NASA-TM-101053; A-89005; NAS 1.15:101053; that were predetermined by VLBI to fix the frame orientation and USAAVSCOM-TR-88-A-009) Avail: NTlS HC A04/MF A01 the absolute scaling, while the offset from the geocenter is CSCL 17G determined from GPS measurements. Three different cases are The C-6533IARC communication system as installed on the presented under this strategy. The reference frame thus adopted test AH-1 E Cobra helicopter was modified to allow discrete radio will be consistent with the VLBl coordinate system. The second selection of all aircraft radios at the cyclic radio/intercommunication strategy establishes a reference frame by holding only the longitude system switch. The current Cobra-fleet use of the C-6533 system of one of the tracking sites fixed. The absolute scaling is determined 'is cumbersome, particularly during low-altitude operations. by the adopted gravitational constant (GM) of the Earth; and the Operationally, the current system C-6533 configuration and design latitude is inferred from the time signature of the Earth rotation in requires the pilot to estimate when he can safely remove his the GPS measurements. The coordinate system thus defined will hand from an active flight control to select radios during low-altitude be a geocentric Earth-fixed coordinate system. Author flight. The pilot must then physically remove his hand from the flight control, look inside the cockpit to select and verify the radio N89-20331*# Jet Propulsion Lab., California Inst. of Tech., selection and then effect the selected radio transmission by Pasadena. activating the radio/lCS switch on the cyclic. This condition is DETERMINATION OF GPS ORBITS TO SUBMETER potentially hazardous, especially during low-level flight at night in ACCURACY degraded weather. To improve pilot performance, communications W. 1. BERTIGER, S. M. LICHTEN. and E. C. KATSlGRlS ln its effectiveness, and safety, manprint principles were utilized in the The Telecommunications and Data Acquisition Report p 14-27 selection of a design modification. The modified C-6533 design 15 Nov. 1988 was kept as basic as possible for potential Cobra-fleet modification. Avail: NTlS HC A12/MF A01 CSCL 17G The communications system was modified and the design was Orbits for satellites of the Global Positioning System (GPS) subsequently flight-tested by the US. Army Aeroflightdynamics were determined with submeter accuracy. Tests used to assess Directorate and NASA at the NASA Ames Research Center, orbital accuracy include orbit comparisons from independent data Mountain View, California. The design modification enables the sets, orbit prediction, ground baseline determination, and formal Cobra pilot to maintain hands-on flight controls while selecting errors. One satellite tracked 8 hours each day shows rms error radios during nap-of-the-Earth (NOE) flight without looking inside below 1 m even when predicted more than 3 days outside of a the cockpit which resulted in reduced pilot workload ratings, better 1-week data arc. Differential tracking of the GPS satellites in high pilot handling quality ratings and increased flight safety for the Earth orbit provides a powerful relative positioning capability, even NOE flight environment. Author when a relatively small continental US. fiducial tracking network is used with less than one-third of the full GPS constellation. To N89-20980# Air Force Inst. of Tech., Wright-Patterson AFB, demonstrate this capability, baselines of up to 2000 km in North OH. School of Engineering. America were also determined with the GPS orbits. The 2000 km AIRCRAFT TRACKING WITH DUAL TACAN M.S. Thesis
466 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
CHRISTOPHER J. MCCORMACK Dec. 1988 71 p for small-unit missions, the role of UAVs in the modern battlefield, (AD-A202647; AD-E900870; AFIT/GE/ENG/88D-28) Avail: NTlS the Sentinel and Sea Sentinel rotary-wing RPVs, the Skyeye and HC A04/MF A01 CSCL 17G Phoenix complementary RPVs, the Falconet target RPV, civilian This thesis addresses the problem of determining aircraft observation-platform applications of RPVs, and the Norton P37 position during flight given noisy and biased measurements from rotary RPV engine. Also discussed are a computer-controlled a barometric altimeter and two tactical air navigation (TACAN) system for multidrone flights, the development of a preliminary transceivers. A Kalman smoother is developed to perform post-flight sizing method for UAVs, low cost avionics for UAVs, a low cost data processingon the measurement data. The smoother estimates trackinglranging system, RPV data links for video and IR aircraft position, velocity, and acceleration as well as biases in surveillance, and aspects of the design of a naval RPV recovery the measurements. Since actual flight test data is not available, system. O.C. computer simulations examine the performance of this tracking technique. The simulated flight includes low and high-speed turns, A89-33556 constant rate ascents, descents, and accelerations. The tracking CANADAIR SENTINEL/SEA SENTINEL ROTARY WING RPV. algorithm tracked the aircraft inertial navigation system used by IV the 4950th Test Wing in another flight test program that showed R. J. ATKINS and S. N. NASRY (Canadair, Inc., Montreal, a position error growth rate of 2000 meters per hour. GRA Canada) IN: Remotely piloted vehicles; International Conference, ?!h, Bris?~!,Eogland, Sept. 12-14. 1988. Proceedings. Bristol, England, University of Bristol, 1988, p. 5.1 -5.1 5. refs 05 An evaluation is presented of the results obtained to date in the full-scale engineering development program of the CL-227 rotary-wing RPV, which in addition to the land-warfare applications AIRCRAFT DESIGN, TESTING AND for which it was originally conceived, and designated ’Sentinel’, PERFORMANCE has been chosen as a candidate for naval development, to be designated ‘Sea Sentinel’. The most recent development efforts Includes aircraft simulation technology. have concentrated on the incorporation of a FLlR sensor, changes in ground control station design, and advanced methods for the display and manipulation of FLlR imagery. Attention is given to A89-33139 the problem posed by shipboard operations that must take into APPLICATION OF HARMONIC ANALYSIS METHOD TO account ship motion and ship aerodynamic wake factors. O.C. RESEARCH ON ROTOR AIRLOADS ZHENHAN QIU. ZHENGZHONG XUE, and YUJIAN DUAN (Chinese A89-33557 Helicopter Research and Development Institute, People’s Republic SOME ASPECTS OF THE DEVELOPMENT AND OPERATIONAL of China) Chinese Journal of Aeronautics (ISSN 1000-9361), TESTING OF THE SPRITE SYSTEM VOI.1. July 1988, p. 63-70. R. G. AUSTIN and C. C. PUGH (ML Aviation Co., Ltd., Maidenhead, Following rotor-vortex theory, the rotor circulation and the England) IN: Remotely piloted vehicles; International Conference, rotor-induced velocity are developed into Fourier series. The 7th, Bristol, England, Sept. 12-14, 1988, Proceedings. Bristol, circulation distribution along the blade (spanwise) is expressed in England, University of Bristol, 1988. p. 7.1-7.15. terms of segment-by-segment linear functions, and the The Sprite military RPV is of helicopterlike, VTOL-capable induced-velocity equations and the circulation equations are configuration employing contrarotating coaxial main rotor blades derived. The induced velocity and its harmonic components are and involving, in addition to the flight vehicle, a control console, a obtained to provide a quantitative basis for the vortex model. For communications station, a terrestrial transport vehicle, and flight calculating each harmonic component of the induced velocity a vehicle ground support equipment. After 8 years of development, simplified method is put forward which saves computer time and is of significant benefit. Author Sprite has proven itself capable of fulfilling such varied requirements as those of the U.S. Army and Marine Corps for a close-range A8933146 RPV, the RAF and USAF Damaged Airfield Information Reporting THE RELIABILITY ANALYSIS OF AIRCRAFT STRUCTURES System, and the U.S. Navy’s small naval vessel-deployable RPV DEPEI ZHU (Northwestern Polytechnical University, Xian, People’s system. The structural and mechanical components of the Sprite RPV are highly modular for ease of field maintenance and repair. Republic of China) Chinese Journal of Aeronautics (ISSN 1000-9361), vol. 1, July 1988. p. 117-122. refs O.C. This paper presents a set of fundamental equations for reliability analysis of single-critical-pointaircraft structures. The mathematical A89-33558 model is formulated by considering the following factors: the static COMPLEMENTARY MINIS - SKYEYE AND PHOENIX, AN strength of the structure; initial cracks, the initiation, propagation, OVERVIEW OF THEIR MULTI-MISSION COVERAGE and instability of fatigue cracks; the residual strength of the R. W. DENNIS (GEC Avionics, Ltd., Flight Controls Div., Rochester, structure; the statistical distribution of the load; the periods of England), G. R. SEEMANN, G. L. HARRIS, and J. MAHON overhaul; accidental damage; the communication of damage among (DevelopmentalSciences Corp., Ontario, CA) IN: Remotely piloted fleets; etc. Based on this mathematical model, the influence of vehicles; International Conference, 7th, Bristol, England, Sept. these factors on the reliability can be quantitatively analyzed, and 12-14, 1988, Proceedings. Bristol, England, University of Bristol, various criteria for fatigue design of aircraft structures can be 1988, p. 8.1-8.10. Research supported by the Ministry of Defence evaluated from the aspect of reliability. Author Procurement Executive, DOD, and US. Army. Despite their independent development, the Skyeye and Phoenix A89-33554 RPVs have been noted to share great commonality of approach REMOTELY PILOTED VEHICLES; INTERNATIONAL to launch and recovery operations, flight control, and navigation. CONFERENCE, 7TH, BRISTOL, ENGLAND, SEPT. 12-14, 1988, Attention is presently given to the prospects for simultaneous, PROCEEDINGS AND SUPPLEMENTARY PAPERS coordinated, and complementary operations of the two systems Conference sponsored by the Royal Aeronautical Society and from a common launcher and under the control of a common University of Bristol. Bristol, England, University of Bristol, 1988, ground station. Phoenix is envisioned to operate in its primary p. Proceedings, 173 p.; Supplementary Papers, 83 p. For individual role using Skyeye’s cueing facility while flying at higher altitude items see A89-33555 to A89-33576. with a SAR payload, or perhaps as a communications-relay The present conference on the development status and platform. Skyeye is also expected to benefit from incorporation of development prospects for RPVs discusses the U.S. Navy’s such Phoenix subsystems as its thermal imager and digital map unmanned air vehicle (UAV) program, U.S. Marine Corps RPVS unit. O.C.
467 A8433561 tradeoff and optimization studies comparing various major THE THETA BETA - DESIGN OF A SYSTEM alternative configurational types are presented. O.C. P. A. EUSTACE (Theta Analysis and Systems, Ltd., Aldershot, England) IN: Remotely piloted vehicles; International Conference, A89-33705# 7th. Bristol, England, Sept. 12-14, 1988, Proceedings. Bristol, PREDICTION OF STRUCTURAL-ACOUSTIC RESPONSE OF AN England, University of Bristol, 1988, p. 12.1-12.8. AIRCRAFT FUSELAGE MODELED AS A PERIODIC Theta Beta is a prototype civil-applicationsunmanned air vehicle STRUCTURE of modular design that can furnish a highly stable sensor platform HAMID JAMSHIDIAT and GAUTAM SENGUPTA (Boeing with largely off-the-shelf technology. The modularity of the structure Commercial Airplanes, Seattle, WA) AIAA, Aeroacoustics allows alternative configurations of the wing/buggy/payload to be Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 14 p. refs chosen in order to best match a given application. The structure (AIAA PAPER 89-1045) is transportable in two very compact parts; a permanently deployed An FEM scheme for predicting the natural modes of an aircraft 'quadricycle' undercarriage obviates ground-launch equipment. fuselage immersed in an acoustic medium is developed and Both ground-based and autopilot control may be employed as demonstrated. The complexity of the FEM model (and hence the required. Speed minimum and maximum are, respectively, 30 and computational cost) is reduced by applying the theory of periodic 60 kts. O.C. structures (PS) to large portions of the fuselage; the theoretical basis of this PS-FEM procedure is discussed in detail and illustrated A8433562 with diagrams. Results for 15-bay steel cylinders with and without FLIGHT TEST OF XRAE-1 TO ESTABLISH AERODYNAMIC frame stiffeners are then presented in extensive tables and graphs DATA and shown to be in good agreement with analytical solutions and D. J. DYER (Cranfield Institute of Technology, England) IN: full (non-PS) FEM predictions. The CPU time required for a typical Remotely piloted vehicles; International Conference, 7th, Bristol, computation is 9.59 sec with the PS-FEM, as compared to 269.5 England, Sept. 12-14, 1988, Proceedings. Bristol, England, sec with the full FEM. T.K. University of Bristol. 1988, p. 13.1-13.8. Research supported by the Ministry of Defence Procurement Executive. A89-33706# Flight test results are presented for the small unmanned aircraft IN-FLIGHT EXPERIMENTS ON THE ACTIVE CONTROL OF designated XRAE-1, outfitted with two different wings, one of which PROPELLER-INDUCED CABIN NOISE was of conventional airfoil profile while the other employed a S. J. ELLIOTT, P. A. NELSON, I. M. STOTHERS, C. C. BOUCHER Wortmann FX63-137 profile. Attention was given to climb rate for (Southampton, University, England), J. F. EVERS (British a given airspeed, coefficient of lift for a given angle-of-attack, and Aerospace, PLC, Manchester, England) et al. AIAA, Aeroacoustics coefficient of drag for the coefficient of lift achieved. Flight test Conference, 12th, San Antonio, TX. Apr. 10-12, 1989. 6 p. Research and analysis methods employed are discussed, as are comparisons supported by the Department of Trade and Industry of England. conducted between flight test results and those obtained for the refs two wings in wind tunnel tests. Good correlation was obtained. (AIAA PAPER 89-1047) O.C. Results are presented on flight trials of an experimental system for the active control of the harmonic sound field in the passenger A8433564 cabin of a B.Ae. 748 twin turboprop aircraft with engines running THE DEVELOPMENT OF A PRELIMINARY SIZING METHOD at 14,200 rpm. The control system could adjust the output signals FOR UNMANNED AIR VEHICLES fed to up to 16 loudspeakers, placed at various positions within A. TURNBULL and J. P. FIELDING (Cranfield Institute of the cabin, to minimize the sum of the squares of the outputs of Technology, England) IN: Remotely piloted vehicles; International up to 32 microphones. The system was able to control the first Conference, 7th. Bristol, England, Sept. 12-14, 1988, Proceedings. three harmonics of the blade passage frequency simultaneously. Bristol, England, University of Bristol, 1988, p. 15.1-15.7. refs The reductions achieved by the control system were found to be The present multivariate optimization package-based sizing close to the optimum reductions achievable, as calculated using method for a wide variety of unmanned air vehicle configurations the measured primary pressures and transfer responses. IS. employs simple mass and drag estimation formulas for such airframe and systems components as the engine, fuselage, wing, A89-33717*# Southwest Research Inst., San Antonio, TX. electrical power and recovery systems. The total vehicle mass is INSTALLATION EFFECTS ON PROPELLER WAKENORTEX then optimized with respect to the specific configurationalvariables INDUCED STRUCTURE-BORNE NOISE TRANSMISSION of wing area and span, fuselage diameter, and engine thrust. The J. F. UNRUH (Southwest Research Institute, San Antonio, TX) final results yield the vehicle's optimized mass. The baseline AIAA, Aeroacoustics Conference, 12th. San Antonio, TX, Apr. configuration mounts the turbojet powerplant beneath the fuselage, 10-12, 1989. 8 p. refs and employs conventional wings and empennage. O.C. (Contract NASl-17921) (AIAA PAPER 89-1072) A89-33626# A laboratory-based test apparatus was employed to investigate TECHNOLOGY REQUIREMENTS FOR HYPERSONIC the effects of power-plant placement, enginelnacelle mass AIRBREATHING AIRCRAFT installation, and wing-to-fuselage attachment methods on D. DWOYER University of Texas, US. Air Force Academy, and propeller-induced structure-borne noise (SBN) transmission levels GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, 2nd, and their effects on noise-control measures. Data are presented U.S. Air Force Academy, Colorado Springs, CO, Jan. 16-20, 1989, showing SBN transmission is insensitive to propeller spanwise Paper. 59 p. refs placement, however some sensitivity is seen in propeller-to-wing A comprehensive evaluation is made of the technology spacing. Installation of an enginelnacelle mass and variation in development status, development requirements, and technology wing-to-fuselage attachments have measurable influences on SBN integration problems associated with prospective hypersonic transmission and control measures. Author airbreathing aircraft design and construction efforts. Attention is given to the performance criteria that must be met by the A89-33719# variable-cycle powerplants under consideration and the primacy FULL-SCALE DEMONSTRATION TESTS OF CABIN NOISE of scramjet propulsion, as well as to the intrinsic difficulties REDUCTION USING ACTIVE VIBRATION CONTROL encountered in the integration of LH2 fuel's cryotankage M. A. SIMPSON, T. M. LUONG (Douglas Aircraft Co., Long Beach, requirements with a highly aerothermodynamically stressed vehicle CA), C. R. FULLER (Virginia Polytechnic Institute and State primary structure. Both hypersonic-cruise and airbreathing University, Blacksburg), and J. D. JONES (Purdue University, West spacecraft launch vehicle projects are considered. Results from Lafayette, IN) AIAA, Aeroacoustics conference, 12th, San Antonio, ~~
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
TX, Apr. 10-12, 1989. 7 p. resistance at reduced weight and to suppress structural vibration (AIAA PAPER 89-1074) within aircraft equipment bays. The approach is to incorporate The results of tests conducted to demonstrate the effectiveness constrained layer damping into the fuselage and equipment racks of active vibration control techniques in reducing structure-borne as an integral part of their design, rather than to use less effective aircraft cabin noise are reported. A prototype active vibration control add-on damping treatment after the structure has been system is tested in a fuselage acoustic research facility using a manufactured. The aft equipment bay of the B-1B aircraft was 50-foot aft section of a DC-9 aircraft as the test article. Shakers selected as the baseline component with which to compare and attached to the engine pylon are used to simulate structure-borne demonstrate the technology developed in this program. Author vibrations which cause noise in the cabin. Active control forces are applied with shakers located in the aircraft interior and A89-33743# connected to the fuselage structure. The level and phase of the IDENTIFYING SONIC FATIGUE PRONE STRUCTURES ON A control forces are set by a PC-based control system, which is HYPERSONIC TRANSATMOSPHERIC VEHICLE (TAV) designed to minimize the average acoustic energy measured at P. J. POZEFSKY (McDonnell Douglas Corp., Saint Louis, MO) selected locations in the aircraft cabin. The tests show good global AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. reduction of interior noise levels and represent the benefits of 10-12, 1989. 6 p. refs active vibration control in full-sized aircraft. S.A.V. (AIAA PAPER 89-1103) A procedure was developed to identify areas of a large, A89-33720# hypersonic transatmospheric vehicle (TAV) that wiil be critical in ADAPTIVE ACTIVE CONTROL OF ENCLOSED SOUND FIELDS sonic fatigue. This preliminary screening involved the application IN ELASTIC CYLINDERS VIA VIBRATIONAL INPUTS of simplified techniques to predict the acoustic loads and resulting D. S. MANDIC and J. D. JONES (Purdue University, West Lafayette, local dynamic structural response on several areas of a typical IN) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, TAV. The predicted responses were evaluated relative to basic Apr. 10-12. 1989. 12 p. refs high cycle fatigue data to determine susceptibility to the acoustic (Contract NSF MSM-88-10384) environment. Structures in several key areas show high acoustic (AIAA PAPER 89-1075) response and warrant further investigation. Author An active noise control system is evaluated using a simplified model of an aircraft fuselage. Horn drivers are used to simulate A89-33754'# Lockheed Aeronautical Systems Co., Burbank, propeller-induced cabin noise while a mini-shaker attached CA. pointwise to the shell wall is used as the control source. A single INTERIOR NOISE IN THE UNTREATED GULFSTREAM II input/single output control system based on the filtered-x version PROPFAN TEST ASSESSMENT (PTA) AIRCRAFT of the least mean squares algorithm is used to optimize the signal H. L. KUNTZ and R. A. PRYDZ (Lockheed Aeronautical Systems of the control shaker. Control at three discrete frequencies corresponding to dominant acoustic cavity modes of the test shell Co., Kelly Johnson Research and Development Center, Burbank, is demonstrated, as well as control of two modes simultaneously. CA) AIAA. Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 9 p. Global reductions as high as 28 dB of the interior acoustic field, with minimal increases in shell vibrations, are achieved. V.L. (Contract NAS3-24339) (AIAA PAPER 89-11 19) Interior noise on the Gulfstream II Propfan Test Assessment A89-3372 1# (PTA) aircraft was measured using 19 wing, 22 fuselage, and 32 MODEL SIZE REQUIREMENTS FOR FINITE ELEMENT cabininterior microphones to determine the sources of the cabin PREDICTION OF LOW-FREQUENCY CABIN NOISE AND noise. Results from ground and flight test acoustic and vibration VIBRATION measurements and analyses show that the major source of cabin A. E. LANDMANN and H. F. TILLEMA (Boeing Commercial noise was the airborne propfan blade passage frequency tones. Airplanes, Seattle, WA) AIAA, Aeroacoustics Conference, 12th, The radiated sound pressure levels and the richness of the San Antonio, TX, Apr. 10-12, 1989. 6 p. refs harmonic content of the propfan increased with increasing altitude. (AIAA PAPER 89-1076) The acoustic output of the propfan also depended on the shaft Engine vibration transmitted with little attenuation through the power, helical Mach number, and blade passage frequency. IS. airplane structure is a major source of LF cabin noise and vibration in advanced propeller aircraft. In order to design aircraft with lower interior noise and vibration levels, the use of the FEM to predict A89-33755'# Douglas Aircraft Co.. Inc.. Long Beach, CA. the dynamics characteristics of engine/airframe/acoustic-cavity CABIN NOISE CONTROL GROUND TESTS FOR UHB systems has been studied. In this paper, the effort to define the AIRCRAFT required level of airframe structural modeling detail for acceptable MYLES A. SIMPSON (Douglas Aircraft Co., Long Beach, CA) AIAA, predictions is discussed. The work presented covers the Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, assumptions made in several model-size reduction schemes and 1989. 11 p. a comparison of test data to the reduced model predictions. The (Contract NASl-18037) reduced models studied include dynamic reduction of the (AIAA PAPER 89-1121) empennage and vertical tail substrctures. representation of the Measurement and analysis procedures for cabin noise control shell structure aft of the rear spar with beams, and modeling of ground tests conducted on a DC-9 aircraft test section are only the passenger cabin and strut-to-fuselage connections. presented along with a summary of test results. These tests were Author designed to analyze the effectiveness of selected noise control treatments in reducing passenger cabin noise on aircraft with A89-33742# aft-mounted, advanced turboprop engines. The performance of SONIC FATIGUE-RESISTANT DAMPED LAMINATED various structural and cabin sidewall treatments is assessed, based STRUCTURES on measurements of the resulting interior noise levels and fuselage CARL L. RUPERT (USAF, Flight Dynamics Laboratory, acceleration levels under simulated advanced turboprop Wright-Patterson AFB, OH) and RALPH E. TATE (LTV Corp., LTV excitation. Author Aircraft Products Group, Dallas, TX) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 8 p. A89-33757"# National Aeronautics and Space Administration. (AIAA PAPER 89-1102) Langley Research Center, Hampton. VA. The sound pressure levels generated by aircraft jet engines PROPELLER MODELLING EFFECTS ON INTERIOR NOISE IN can result in sonic fatigue of structure and damage to Sensitive, CYLINDRICAL CAVITIES WITH APPLICATION TO ACTIVE on-board electronic gear. The program objective is to develop the CONTROL passive damping technology required to achieve sonic fatigue R. J. SlLCOX and H. C. LESTER (NASA, Langley Research Center,
469 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Hampton, VA) AIAA, Aeroacoustics Conference, 12th. San M. KARPEL and Z. SHEENA (Israel Aircraft Industries, Ltd., Lod) Antonio, TX, Apr. 10-12, 1989. 13 p. refs Journal of Aircraft (ISSN 002143669), vol. 26, May 1989, p. (AIM PAPER 89-1123) 493-495. refs The coupling of a vibrating finite elastic cylinder and its interior A wing structural optimization process such as that presently cavity, closed with rigid end caps, is examined. Results are discussed attempts to achieve the targeted degree of structural presented for several types of excitation including a point force, a effectiveness with minimum weight increase. A NASTRAN run for single external acoustic monopole, and an array of external vibration modes which also creates a data base of element monopoles. Modal spectra are examined for a frequency range contributions to the generalized stiffness matrix is first performed; typical of the harmonic noise produced by advanced turbo-props. the major optimization cycle is divided into secondary cycles with The effect of frequency and source distribution on modal content intermediate targets. A preliminary version of the Lavi wing has is presented. Significant interface modal filtering, which would have been used to demonstrate the method, using antisymmetric a beneficial impact on an active system for reducing interior noise, boundary conditions. O.C. was found to occur for all cases. Some preliminary experimental data for a stiffened, composite cylinder are presented and A89-35196# discussed. Author SPIN TESTING METHODS IN FLIGHT J. P. DUVAL (Avions Marcel Dassault-Breguet Aviation, Istres, A89-33771’# McDonnell-Douglas Helicopter Co.. Mesa, AZ. France) (National Seminar on Flight Research, Test and IMPORTANCE OF ENGINE AS A SOURCE OF HELICOPTER Development, Bangalore, India, Sept. 2, 3, 1987) Aeronautical EXTERNAL NOISE Society of India, Journal (ISSN 0001-9267), vol. 40, Aug. 1988, p. R. D. JANAKIRAM, M. J. SMITH, and H. TADGHlGHl (McDonnell 159-166. Translation. Douglas Helicopter Co., Mesa, AZ) AIAA, Aeroacoustics The principles of a spin test method are described together Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 14 p. refs with the techniques involved and the individual steps of a field (Contract NASl-17145) test of spin. Particular attention is given to the preliminary study (AIM PAPER 89-1147) in wind tunnel, the instrumentation of the aircraft in flight and on A turboshaft engine’s importance as a source of helicopter the ground, and the pilot’s equipment. Results are presented on external noise is presently evaluated experimentally and analytically spin tests carried out on an Alpha Jet aircraft. IS. on the basis of test data from an MD500E helicopter, with and without engine muffler, during level flyovers and climbing flight. A A89-35197# strong engine noise component is noted for helicopter positions DESIGNING WITH ADVANCED FIBROUS COMPOSITES nearly overhead and beyond observed position, especially in the J. HART-SMITH (Douglas Aircraft Co., Long Beach, CA) 200-1000 Hz range; its strong rearward directivity suggests the (Workshop on New Materials and Process for Mechanical Design, noise source to be the broadband exhaust or combustion noise Brisbane, Australia, May 1988) Aeronautical Society of India, radiated from the exhaust duct. The engine muffler furnished Journal (ISSN 0001-9267), vol. 40, Aug. 1988, p. 167-199. refs estimated perceived noise level reductions of 2-3 dB for the The characteristics of advanced fibrous composites (carbon, centerline. O.C. boron, aramid, or glass in organic matrices) used by the aircraft industry in the U.S and Western Europe are discussed. Compared A89-34509 to metal alloys, fibrous composites have lower densities, higher TRANSIENT DYNAMICS OF AIRCRAFT PROPELLERS DURING specific strengths, lower manufacturingcosts, virtually no corrosion, TOUCH-DOWN IMPACT an improved surface finish, and the ability to make lower drag Y. A. KHULIEF and H. T. CHlU (Alabama, University, Birmingham) shapes more easily. In addition, fibrous composites make it possible Computers and Structures (ISSN 0045-7949), vol. 31, no. 3, 1989, to tailor laminate patterns for achieving desired stiffness and to p. 413-419. refs manufacture dimensionally stable components with zero coefficient The vibrational response of a rotating flexible structure to of expansion. Structural details of two ’all-composite’ aircraft, the impulsive excitation is investigated analytically, applying a numerical de Havilland Mosquito and the Lear Fan transport aircraft are dynamic-analysis scheme based on a multibody-system formulation. discussed. Also discussed are some popular malpractices in The generalized elastodynamic model and its realization for an advanced composite structures, the effects of joints on the design aircraft propeller (modeled as a flexible beam) undergoing of composite structures, and the use of honeycomb sandwich touchdown impact are derived, and results from a simulation of type construction. I.S. an entire light-aircraft/propeller configuration are presented in extensive graphs. The model is found to account for changes in A89-35198# blade response due to rotation-induced stiffness and the blade DEVELOPMENT OF EXPERIMENTAL TECHNIQUES FOR orientation at impact. T.K. HELICOPTER ROTOR PERFORMANCE STUDIES S. R. PATIL (National Aeronautical Laboratory, Bangalore, India) A89-34808# and M. A. RAMASWAMY (Indian Institute of Science, Bangalore, SURFACEPRESSUREMEASUREMENTSONABODY India) Aeronautical Society of India, Journal (ISSN 0001-9267), SUBJECT TO VORTEX WAKE INTERACTION vol. 40, Aug. 1988, p. 201-209. Research sponsored by the A. G. BRAND, H. M. MCMAHON, and N. M. KOMERATH (Georgia Aeronautical Research and Development Board. refs Institute of Technology, Atlanta) AIAA Journal (ISSN 0001-1 452), The details of teetering rotor model and the associated strain VOI.27, May 1989, p. 569-574. refs gauge balance and calibration fixtures have been presented. (Contract DAAG29-82-K-0094) Hovering results for 1.22 m diameter teetering rotor model Wind-tunnel experiments were conducted to examine the evaluated experimentally have been compared with the simple interaction effects between a rotor and idealized airframe in forward blade element-momentum theory. Author flight. Mean and unsteady pressures were measured on the airframe surface for various flight speeds. Strong rotor-wake interactions A89-35202# with the airframe create large excursions in the mean pressure HIGH PERFORMANCE ESCAPE CAPSULES distribution. Extreme fluctuations in the unsteady component of WILLIAM G. PICKL (USAF, Wright Research and Development pressure are also observed. The flowfield features that cause these Center, Wright-Patterson AFB, OH) IN: AlAA Aerodynamic effects are identified and discussed. It is essential that a Decelerator Systems Technology Conference, 1Oth, Cocoa Beach, comprehensive aerodynamic interaction be obtained. Author FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American Institute of Aeronautics and Astronautics, 1989, p. 1-6. refs A89-34899# (AIAA PAPER 89-0878) STRUCTURAL OPTIMIZATION FOR AEROELASTIC CONTROL The extreme dynamic pressure environments of future EFFECTIVENESS supersonic and hypersonic Cruise aircraft call for crew-escape
470 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
capsules of low weight and high performance. Improved design can simultaneously alleviate gust-induced wing bending loads and techniques and variable-geometry drogue chute stabilization control the aircraft in the pitch plane. Digital simulation results of subsystems are presently employed to reduce escape capsule a simple pitch-plane maneuver are presented to illustrate the weight, while gaining an active attitude-control capability and the tracking capabilities of the contoller. I.S. possibility of ground-avoidance maneuvers. Retrorocket-firing is noted to be a promising method for the attenuation of A89-35825 landing-impact loads. Hypersonic drogue decelerator technologies NEW WINGS, NEW WAYS are available that may be capable of initial operation at speeds of Flight International (ISSN 0015-3710), vol. 135, March 18, 1989, up to Mach 20. O.C. p. 26-29. The USSR's most recently revised unified airworthiness A89-35205# standards, to which such new aircraft as the four-engined, PILOT EJECTION FROM A PRONATED FLYING POSITION wide-body 11-96-300 airliner must adhere, follow the European ALLEN D. DISSELKOEN, KEITH H. HEISE (USAF, Aeronautical safety-assessment practices developed over a decade ago. The Systems Div., Wright-PattersonAFB, OH), ROBERT F. GARGIULO maximum allowable probabilities of various poten?ially hazardous (USAF, Electronic Systems Div., Hanscom AFB, MA), and CURTIS situations are determined for the aircraft as a whole, and acceptable H. SPENNY (USAF, Institute of Technology, Wright-Patterson AFB, probabilities are then derived for the failures of individual aircraft OH) !N: ,A!&& .Aemdynamic Decelerator Systems Technology systems. Each system is, finally, assessed as a number of separate Conference, loth, Cocoa Beach, FL, Apr. 18-20, 1989, Technical components. Efforts are also beifig made to reduce msjor Papers. Washington, DC, American Institute of Aeronautics and maintenance for new aircraft in order to reduce the staffing levels Astronautics, 1989, p. 24-33. refs required in heavy maintenance tasks. O.C. (AIAA PAPER 89-0885) Aerodynamic and biomechanic analyses are presented for a A89-35842 fighter seat and escape system. A semi-enclosedseat configuration CONTROLLING SEVERED HELICOPTER BLADES DURING is described that provides pilot protection for ejections at a dynamic EMERGENCY ESCAPE pressure of 2,000 psf, well beyond the capability of existing GARY L. JARVIS and WILLIAM E. MCELRATH (Delta Technology open-seat ejection systems. Increased ejection performance is Systems, Warminster, PA) SAFE Journal, voi. 19. Spring 1989, achieved by taking advantage of a pronated (forward-leaning) seat p. 26-33. refs configuration to: (1) increase pilot protection from windstream This paper presents a methodology for controlling the deceleration forces and (2) provide stability in the windstream prior trajectories of the severed helicopter blades, thus reducing the I to deployment of the drogue chute. These enhancements, in hazard to other aircraft in close proximity, using the AH-1 Cobra conjunction with the increased pilot g-tolerance during flight as a model for the preliminary design of a blade deceleration (described herein), make the concept of a pronated fighter seat system. Design concepts are presented for a modular very attractive. A computer model of pressure distribution on panels self-contained fabric aerodynamic decelerator device mounted on was used to predict aerodynamic forces and moments. Computer each blade, which can be deployed by a simple mechanical action, simulation of ejection dynamics was used to predict dynamic The results of a trajectory study demonstrated that the use of this stability. Author deceleration device results in a significant reduction in the flight. IS. A89-35209# TESTING OF A NEW RECOVERY PARACHUTE SYSTEM FOR A89-35843 THE Flll AIRCRAFT CREW ESCAPE MODULE - AN UPDATE ADVANCED RECOVERYSEQUENCER(ARS) DONALD W. JOHNSON (Sandia National Laboratories, JAMES SCHOEN (Douglas Aircraft Co., Long Beach, CA) and KIT Albuquerque, NM) IN: AIAA Aerodynamic Decelerator Systems Q. BOYD (USAF, Wright-Patterson AFB, OH) SAFE Journal, vol. Technology Conference, 1Oth, Cocoa Beach, FL, Apr. 18-20, 1989, 19. Spring 1989, p. 34-41. Technical Papers. Washington, DC, American Institute of An Advanced Recovery Sequencer (ARS) has been developed Aeronautics and Astronautics, 1989, p. 47-52. refs for the ACES II ejection seat. The ARS uses digital microcontroller (Contract AF PROJECT SM-MMK-87-10-324; technology and solid state pressure transducers to optimize escape DE-AC04-76DP-00789) sequence timing. This is achieved by means of a continuously (AIAA PAPER 89-0891) variable time delay for recovery parachute deployment under A new recovery parachute system has been designed for the moderate-to-high-speedconditions.This is in contrast to the fixed F111 crew escape module (CEM). The system includes a cluster delay provided by the current analog sequencer. The ARS will of three 49-ft-dia ringslot-solid parachutes, a Kevlar deployment provide enhanced system reliability and maintainability through the bag, and an explosively fired drogue gun to deploy the pilot use of built-in test capability. The ARS has completed subsystem parachute. Tests have been conducted that indicate the parachute qualification testing and is ready for system qualification testing. system will meet the rate of descent requirement of 25 ftlsec at This paper presents an overview of the ARS program from 5000 ft pressure altitude. To control the drag load developed by conception through qualification. Author the parachutes, a new central reefingldisreefing system has been developed. Since the recovery parachute system is normally N89-20121'# Illinois Univ., Urbana-Champaign. Dept. of deployed crosswind from the CEM, line sail of the suspension Aeronautical and Astronautical Engineering. lines during early tests was a problem but has been minimized by AEROSPACE VEHICLE DESIGN, SPACECRAFT SECTION a dual pilot parachute system. Author FINAL PROJECT REPORTS May 1988 344 p A8935299 (Contract NGT-21-002-080) LOAD ALLEVIATION ON TRANSPORT AIRCRAFT USING (NASA-CR-184741; NAS 1.26:184741; AAE-241-VOL-1) Avail: ACCELERATION FEEDBACK NTlS HC A15lMF A01 CSCL 01C A. BRADSHAW, T. RAHULAN, and M. A. WOODHEAD (Salford, The objective was to create a manned Martian aircraft which University, England) IN: International Conference on Control 88, can perform: scientific surveys of particular sites distant from the Oxford, England, Apr. 13-15, 1988, Proceedings. London, Institution base; a deployment of scientific instrument packages by air drop of Electrical Engineers, 1988, p. 701-706. refs that land rovers cannot accomplish; and rescue operations. A theoretical concept for a flight controller was developed, Designing the airfoil requires a wing which can operate within the which incorporates feedback of the rates of change of the state low Reynolds numbers apparent on Mars. The airfoil, NASA and output, making it possible to achieve gust-load alleviation on NLF(1)-1015 was chosen. The design of the aircraft is comparable a transport aircraft. Noninteracting control equations were to a P-38 military aircraft. The aircraft uses fuel cells to power the developed that yielded an integrated flight control system which two propellers. A rocket-assisted takeoff is necessary to enable
47 1 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Romulus to liftoff. Although the design and creation of Romulus demonstrate the relationship between the Matched Filter Theory would be an expensive adventure, such a vehicle could be most approach to the calculation of time-correlated gust loads and useful in evaluating the Mars surface and in creating a habitat for Phased Design Load Analysis in common use in the aerospace mankind. B.G. industry. The relationship depends upon the duality between Matched Filter Theory and Random Process Theory and upon the N89-20122'# Illinois Univ., Urbana-Champaign. Dept. of fact that Random Process Theory is used in Phased Design Loads Aeronautical and Astronautical Engineering. Analysis in determining an equiprobable loads design ellipse. AEROSPACE VEHICLE DESIGN, SPACECRAFT SECTION Extensive background information describing the relevant points FINAL PROJECT REPORTS of Phased Design Loads Analysis, calculating time-correlated gust May 1988 354 p loads with Matched Filter Theory, and the duality between Matched (Contract NGT-21-002-080) Filter Theory and Random Process Theory is given. It is then (NASA-CR-184742; NAS 1.26:184742; AAE-241 -VOL-2) Avail: shown that the time histories of two time-correlated gust load NTlS HC Al6/MF A01 CSCL 01c responses, determined using the Matched Filter Theory approach, The next major step in the evolution of the space program is can be plotted as parametric functions of time and that the resulting the exploration of the planet Mars. In preparation for this, much plot, when superposed upon the design ellipse corresponding to research is needed on the problem of surveying the planet surface. the two loads, is tangent to the ellipse. The question is raised of An aircraft appears to be a viable solution because it can carry whether or not it is possible for a parametric load plot to extend men and equipment large distances in a short period of time as outside the associated design ellipse. If it is possible, then the compared with ground transportation. The problems and design use of the equiprobable loads design ellipse will not be a of an aircraft which would be able to survey the planet Mars are conservative design practice in some circumstances. Author examined. Author N89-20126# National Aerospace Lab., Amsterdam (Netherlands). N89-20123*# Illinois Univ., Urbana-Champaign. Dept. of Structures and Material Dept. Aeronautical and Astronautical Engineering. MATCHING POWER SPECTRA DENSITY (PSD)-DESIGN LOAD AEROSPACE VEHICLE DESIGN, SPACECRAFT SECTION R. NOBACK 18 Aug. 1987 16 p Presented at the 65th May 1988 703 p AGARD Structures and Materials Panel and Flight of Flexible (Contract NGT-21-002-060) Aircraft in Turbulence Workshop, Cesme, Turkey, 4-9 Oct. 1987 (NASA-CR-184743; NAS 1.26:184743; AAE-241-VOL-3) Avail: Sponsored by The Netherlands Agency for Aerospace Programs, NTIS HC A99/MF E03 CSCL 01C Delft, The Netherlands Research results are presented for the following groups: Project (NLR-MP-870594; ETN-89-94040) Avail: NTlS HC AO3/MF Mars Airplane Vehicle and Reconnaissance Instrument Carrier A01 (MAVRIC), ACME, ARES, Project ACRONYM, Mars Aircraft It is shown that it is possible to generate equal probability Recepticle with Technical Instruments, Aerobraking, and Navigation design load conditions using power spectral density-design loads (MARTIAN), and NOMADS. Each project is described by the obtained with the design envelope criterion, and the correlation following areas of focus: mission planning and costs; aerobraking coefficients between these loads. The correlation coefficients can systems; structures and thermal control systems; attitude and be calculated easily together with the A-values. The matrix of articulation control systems; comman and data control systems; correlation coefficients can be used to define an N-dimensional science instrumentation; and power and propulsion systems. surface. For the two-dimensional case this surface reduces to an B.G. ellipse. Each point on the surface defines an equal probability design load condition. It can be shown that such a condition is in N89-20124'# National Aeronautics and Space Administration. equilibrium. Each design load condition can be used to calculate Ames Research Center, Moffett Field, CA. an estimate for the stress in a point of the structure. The method HUB AND BLADE STRUCTURAL LOADS MEASUREMENTS OF also can be used to generate design load conditions for the AN SA34912 HELICOPTER complete structure, for example the wing. A problem arises if GLORIA K. YAMAUCHI, RUTH M. HEFFERNAN, and MICHEL stresses have to be calculated for a section of the structure for GAUBERT (Societe Nationale lndustrielle Aerospatiale, Marignane, which the design values of the loads and the correlation coefficients France ) Dec. 1988 136 p were not calculated. It then seems logical to interpolate within a (NASA-TM-101040; A-88300; NAS 1.15101 040) Avail: NTlS HC design load condition. This however leads to inconsistent Values A07/MF A01 CSCL OlC of both loads and stresses in that section. The same problem Data from 23 flight conditions, including level flights ranging arises in a discrete gust analysis if the design load conditions are from advance ratio mu = 0.14 to 0.37 and steady turning flights defined as the loads occurring at the same time. A possible solution from advance ratio mu = 0.26 to 0.35, are presented for an is to interpolate between the corresponding design loads and Aerospatiale SA34912 Gazelle helicopter. The data include hub correlation coefficients of the adjoining sections. ESA loads data (for 6 of the 23 conditions), blade structural data at eleven different blade radial stations, and fuselage structural data. N89-20127# Rockwell International Corp., Columbus, OH. North All dynamic data are presented as harmonic analysis coefficients American Aircraft Operations. (ten harmonics per rotor revolution). The data acquisition and POWER EFFICIENT HYDRAULIC SYSTEMS. VOLUME 1: reduction procedures are also documented. Blade structural and STUDY PHASE Final Report, Oct. 1985 - Jul. 1988 inertial properties are provided in addition to control system RICHARD V. HUPP and ROBERT K. HANING Jul. 1988 239 p geometry and properties. Author (Contract N62269-85-C-0259) (AD-A203899; NA-88-0001-VOL-l; NADC-88066-60-VOL-1) N89-20125'# Planning Research Corp., Hampton, VA. Aerospace Avail: NTlS HC A11/MF A01 CSCL 13G Technologies Div. Energy saving concepts for aircraft hydraulic systems were ON THE RELATIONSHIP BETWEEN MATCHED FILTER studied in a two-phase program. Task 1 was an investigation of THEORY AS APPLIED TO GUST LOADS AND PHASED methods and techniques to reduce overall hydraulic system power DESIGN LOADS ANALYSIS requirements by lowering system demands and increasing THOMAS A. ZEILER and ANTHONY S. POTOTZKY Apr. 1989 component efficiencies. Task 2 involved hardware demonstration 27 p Presented at the Gust Specialists Meeting, Mobile, AL, 6 test on selected concepts. Task 1: Study Phase. A baseline Apr. 1989 hydraulic system for an advanced aircraft design was established. (Contract NAS1-18000) Twenty energy saving techniques were studied as candidates for (NASA-CR-181802; NAS 1.26:181802) Avail: NTlS HC A03/MF application to the baseline vehicle. A global systems analysis A01 CSCLOlC approach was employed. The candidates were compared on the A theoretical basis and example calculations are given that basis of total fuel consumption and six qualitative factors. Nine of
472 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE the most promising techniques were applied to a Target System . solution of the unsteady transonic small disturbance potential The target system had a 28 percent reduction in energy equation. An overview is given of the CAP-TSD code development consumption and an 868 Ib weight reduction over the baseline effort along with recent algorithm modifications which are listed aircraft. GRA and discussed. Calculations are presented for several configurations including the General Dynamics 119th scale F-16C N89-20128# Rockwell International Corp., Columbus, OH. North aircraft model to evaluate the algorithm and hence the reliability American Aircraft Operations. of the CAP-TSD code in general. Calculations are also presented POWER EFFICIENT HYDRAULIC SYSTEMS. VOLUME 2 for a flutter analysis of a 45 deg sweptback wing which agree HARDWARE DEMONSTRATION PHASE Final Report, Oct. well with the experimental data. Descriptions are presented of the 1985 - JuI. 1988 CAP-TSD code and algorithm details along with results and RICHARD V. HUPP and ROBERT K. HANING Jul. 1988 204 p comparisons which demonstrate the stability, accuracy, efficiency, (Contract N62269-85-C-0259) and utility of CAP-TSD. Author (AD-A203900; NA-88-0001-VOL-2; NADC-88066-60-VOL-2) Avail: NTIS HC AlO/MF A01 CSCL 13G N89-20947'# National Aeronautics and Space Administration. Energy saving concepts for aircraft hydraulic systems were Langley Research Center, Hampton, VA. studied in a two-phase program. Task 1 was an investigation of INVERSE WING DESIGN IN TRANSONIC FLOW INCLUDING methods and techniques to reduce overaii nydrauiic system powe: WSCOUS lNTERACTlON requirements by lowering system demands and increasing LELAND A. CARLSON, ROBERT R. RATCLIFF, THOMAS A. component efficiencies. Task 2 involved hardware demonstration GALLY (Texas A&M Univ., College Station.), and RICHARD L. tests on selected concepts. Hardware demonstration phase. Two CAMPBELL In its Transonic Symposium: Theory, Application, techniques demonstrated for energy savings were control valves and Experiment, Volume 1, Part 2 p 497-51 9 Mar. 1989 with overlap and dual pressure level systems. Tests were conducted (Contract NSG-1619) on control valves, a servo actuator, dual pressure pumps, and a Avail: NTlS HC A22/MF A01 CSCL 01C lightweight hydraulic system simulator. Valves with 0.002 in. overlap Several inverse methods were compared and initial results reduced system energy consumption 18 percent compared to using indicate that differences in results are primarily due to coordinate valves with zero lap. Operation at 4000 psi reduced system energy systems and fuselage representations and not to design consumption 53 percent compared to operation at 8000 psi. procedures. Further, results from a direct-inverse method that Pressure level switching was accomplished with good results. includes 3-D wing boundary layer effects, wake curvature, and GRA wake displacement are represented. These results show that boundary layer displacements must be included in the design N89-20945'# Grumman Aerospace Corp., Bethpage, NY. Aircraft process for accurate results. Author Systems Div. METHOD TO PREDICT EXTERNAL STORE CARRIAGE LOADS N89-20981'# California Univ., Los Angeles. School of AT TRANSONIC SPEEDS Engineering and Applied Science. BRUCE S. ROSEN In NASA, Langley Research Center, Transonic HYPERSONIC DRONE DESIGN A MULTIDISCIPLINARY Symposium: Theory, Application, and Experiment, Volume 1, Part EXPERIENCE 2 p 453-465 Mar. 1989 Previously announced in IAA as Jun. 1988 302 p A88-22003 (Contract NGT-21-002-080) (Contract NASl-18105) (NASA-CR-184740; NAS 1.26:184740) Avail: NTlS HC A1 4/MF Avail: NTIS HC A22/MF A01 CSCL 01C A01 CSCLOlC A computational method for prediction of external store carriage Efforts were focused on design problems of an unmanned loads at transonic speeds is described. The geometric flexibility hypersonic vehicle. It is felt that a scaled hypersonic drone is required for treatment of isolated and underwing, pylon mounted necessary to bridge the gap between present theory on hypersonics stores is achieved by computing solutions on a five level embedded and the future reality of the National Aerospace Plane (NASP) for grid arrangement. A completely automated grid generation two reasons: to fulfill a need for experimental data in the hypersonic procedure facilitates applications. Store modeling capability regime, and to provide a testbed for the scramjet engine which is consists of bodies of revolution with multiple fore and aft fins. A to be the primary mode of propulsion for the NASP. Three areas body conforming grid improves the accuracy of the computed store of great concern to NASP design were examined: propulsion, body flow field. A nonlinear finite difference relaxation scheme, thermal management, and flight systems. Problem solving in these developed specifically for modified transonic small disturbance flow areas was directed towards design of the drone with the idea that equations, enhances numerical stability and accuracy. As a result, the same design techniques could be applied to the NASP. A more accurate treatment of low aspect ratio, highly swept and seventy degree swept double delta wing configuration, developed tapered wing planforms is possible. A limited supersonic freestream in the 70's at NASA Langley, was chosen as the aerodynamic capability is also provided. Pressure, load distribution, force and and geometric model for the drone. This vehicle would be moment correlation show good agreement for several test cases. air-launched from a B-1 at Mach 0.8 and 48,000 feet, rocket Author boosted by two internal engines to Mach 10 and 100,000 feet, and allowed to cruise under power of the scramjet engine until N89-20946'# National Aeronautics and Space Administration. burnout. It would then return to base for an unpowered landing. Langley Research Center, Hampton, VA. Preliminary energy calculations based upon the flight requirements STEADY AND UNSTEADY TRANSONIC SMALL DISTURBANCE give the drone a gross launch weight of 134,000 Ib. and an overall ANALYSIS OF REALISTIC AIRCRAFT CONFIGURATIONS length of 85 feet. Author JOHN T. BATINA, DAVID A. SEIDEL, ROBERT M. BENNETT, HERBERT J. CUNNINGHAM, and SAMUEL R. BLAND ln its N89-20982*# National Aeronautics and Space Administration. Transonic Symposium: Theory, Application, and Experiment, Langley Research Center, Hampton. VA. Volume 1, Part 2 p 467-496 Mar. 1989 INTEGRATED AERODYNAMIC/DYNAMIC OPTIMIZATION OF Avail: NTIS HC A22/MF A01 CSCL 01C HELICOPTER ROTOR BLADES A transonic unsteady aerodynamic and aeroelastic code called ADIT1 CHATTOPADHYAY, JOANNE L. WALSH. and MICHAEL F. CAP-TSD (Computational Aeroelasticity Program - Transonic Small RILEY (Planning Research Corp., Hampton, VA.) Feb. 1989 Disturbance) was developed for application to realistic aircraft 15 p Presented at the 30th AIAA/ASME/ASCE/AHS/ASC configurations. It permits the calculation of steady and unsteady Structures, Structural Dynamics and Materials Conference, Mobile, flows about complete aircraft configurations for aeroelastic analysis AL, 3-5 Apr. 1989 of the flutter critical transonic speed range. The CAP-TSD code (NASA-TM-101553; NAS 1.15:101553; AIAA-89-1269) Avail: uses a time accurate approximate factorization algorithm for NTlS HC AO3/MF A01 CSCL 01C
473 05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE
An integrated aerodynamic/dynamic optimization procedure is several audio world terminals on that network. The simulation model used to minimize blade weight and 4 per rev vertical hub shear used the mean token rotation time (TRT) in combination with a for a rotor blade in forward flight. The coupling of aerodynamics specified target TRT (TTRT) as the performance parameter of and dynamics is accomplished through the inclusion of airloads interest. The TRT responses of FDDl were observed for cases which vary with the design variables during the optimization where all terminals used 16-bit PCM, 5-bit ADPCM, CVSD, or process. Both single and multiple objective functions are used in LPC (packetized to 4096, 16384, or 35904 bits; for 50, 100, 130, the optimization formulation. The Global Criteria Approach is used and 150 stations) with or without silence suppression to the audio to formulate the multiple objective optimization and results are signals begin transmitted. The simulation results (the TRT compared with those obtained by using single objective function responses) revealed that FDDl can support 130 audio terminals formulations. Constraints are imposed on natural frequencies, using 16-bit PCM; however, it cannot support 150 audio terminals. autorotational inertia, and centrifugal stress. The program CAMRAD When silence suppression is applied, FDDl is able to support the is used for the blade aerodynamic and dynamic analyses, and the same 150 terminals with less than a 2 percent probability that an program CONMIN is used for the optimization. Since the spanwise audio packet would be late for play out on a receiving audio and the azimuthal variations of loading are responsible for most terminal. The simulation results also showed that at least 150 rotor vibration and noise, the vertical airload distributions on the terminals using 5-bit ADPCM, CVSD, or LPC with or without silence blade, before and after optimization, are compared. The total power suppression could be accommodated by FDDI. GRA required by the rotor to produce the same amount of thrust for a given area is also calculated before and after optimization. Results indicate that integrated optimization can significantly reduce the N89-20986# Air War Coll., Maxwell AFB, AL. blade weight, the hub shear and the amplitude of the vertical INCORPORATING FIVE NATIONS OPERATIONAL airload distributions on the blade and the total power required by the rotor. Author REQUIREMENTS INTO A SINGLE AIRCRAFT: THE F-16 MULTINATIONAL FIGHTER PROGRAM VIEWED FROM THE OPERATIONAL SIDE N89-20983'# National Aeronautics and Space Administration. ElNAR SMEDSVIG Apr. 1988 62 p Ames Research Center, Moffett Field, CA. (AD-A202552) Avail: NTlS HC A04/MF A01 CSCL 05A SIMULATION AT DRYDEN FLIGHT RESEARCH FACILITY Remarks on the background for the F-16 multinational program FROM 1957 TO 1982 introduce a detailed discussion of the operational facets of the JOHN P. SMITH, LAWRENCE J. SCHILLING, and CHARLES A. total program. A description of the operational organizations follows WAGNER Feb. 1989 14 p Presented at the SES/SFTE to complete the background for the author's views on the Simulation-AircraftTest and Evaluation Symposium, Patuxent River, importance of the international participation in the F-16 program. MD, 16-17 Mar. 1982 After a discussion of how the international participation improved (NASA-TM-101695; H-1530; NAS 1.15:101695) Avail: NTlS HC the F-16 operational dialogue has improved interoperability and AO3/MF A01 CSCL 01C cooperation beyond the original F-16 program. Lessons learned The Dryden Flight Research Facility has been a leader in and potential future applications are discussed. GRA developing simulation as an integral part of flight test research. The history of that effort is reviewed, starting in 1957 and continuing to the present time. The contributions of the major program activities conducted at Dryden during this 25-year period to the N89-20987# Air Force Inst. of Tech., Wright-Patterson AFB, development of a simulation philosophy and capability is OH. School of Engineering. explained. Author PRELIMINARY DESIGN OF A MODULAR UNMANNED RESEARCH VEHICLE. VOLUME 1: SYSTEM DESIGN N89-20984# Air Force Occupational and Environmental Health DOCUMENT M.S. Thesis Lab., Brooks AFB, TX. CHRISTOPHER D. HALL, RICHARD L. JOHNSON, PETER J. CONTAMINATION OF THE EXTERIOR OF A C-130E LAMATSCH, DOUGLAS A. MCCABE, PAUL J. MUELLER, 111, AIRCRAFT USED FOR AERIAL SPRAY, 907 TAG, MICHAEL E. PAUL, and LETITIA M. POHL Dec. 1988 215 p RICKENBACKER ANGB, OH Final Report (ADA202765; AFIT/GSE/AA/88D-2-VOL-l) Avail: NTlS HC THOMAS H. LILLIE Sep. 1988 14 p AlO/MF A01 CSCL 01C (AD-A202430; USAFOEHL-88-137EQ01IOJEF) Avail: NTlS HC This thesis presents the analysis and development of a modular AO3/MF A01 CSCL 15F unmanned research vehicle (MURV) to support aeronautical Contamination of the exterior of a C-l30E aircraft was evaluated research for AFIT. The MURV is proposed as a test vehicle to during flight tests of a new modular aerial spray system at Dobbins permit experimental efforts beyond the restrictions of pure analytical AFB, GA and Avon Park AFR, FL. Oil sensitive cards and paper and wind tunnel research, yet less costly and more accessible index cards were taped to 50 sites on the exterior of the aircraft than full-scale flight tests. A classical systems approach was applied to monitor deposition of Dibrom, Malathion, soybean oil, and water in concert with a conventional aircraft design process which during aerial spray operations. Light contamination of the aileron emphasized system level needs and objectives in the design of occurred when the wing booms were used and heavy contamination MURV subsystems. The primary design drivers were the need for of the cargo door and horizontal stabilizer occurred when the adequate data acquisition for anticipated experiments, structural fuselage booms were used. GRA and functional modularity to permit simple reconfiguration, and focus on a set of unique experiments relating to fighter-like N89-20985# Air Force Inst. of Tech., Wright-Patterson AFB, supermaneuverability. The supermaneuverability experiments OH. School of Engineering. dictated that the general arrangement of the MURV baseline design PERFORMANCE ANALYSIS OF THE FIBER DISTRIBUTED would resemble a typical modern fighter aircraft configuration, the DATA INTERFACE IN THE SUPER COCKPIT AUDIO WORLD recommended baseline being a turbojet-powered delta wing design M.S. Thesis with canards, single vertical tail, and control-configured ventral JUANCHO E. FORLANDA Dec. 1988 288 p fins. Modularity implications resulted in the design of a flexible, (ADA202535; AFIT/GCS/ENG/88D-6) Avail: NTlS HC A1 3/MF digital flight control system with primary functions distributed A01 CSCL 12G between the vehicle and a remote pilot/control ground station, The purpose of this thesis was to determine if the Fiber and a fuselage design which allows for relocation and replacement Distributed Data Interface (FDDI) network, a 100 Mbps fiber optic of wings and tails or canards. The data acquisition system is fully ring network, could satisfy the networking requirement (to support integrated with the flight control system and the remote ground up to 130 terminals) of the Super Cockpit Audio World. To help station. The MURV is capable of flight speeds approaching 260 make this determination a computer sirnulation was created to knots for altitudes up to 20,000 feet, and has fuel to fly for well model the FDDl network and the load that may be created by over 30 minutes. GRA
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N89-20988# Air Force Inst. of Tech., Wright-Patterson- AFB, to identify the regimes of helicopters operation that can support OH. School of Engineering. limit cycling and the range of excitations the system can withstand A WIND TUNNEL AND COMPUTER INVESTIGATION OF THE before entering a limit cycle. GRA Low SPEED AERODYNAMIC CHARACTERISTICS OF THE PRONE ESCAPE SYSTEM (PRESS) M.S. Thesis N89-20991'# National Aeronautics and Space Administration. LONNIE R. DILLON Dec. 1988 104 p Langley Research Center, Hampton. VA. (AD-A202768; AFIT/GAE/AA/88D-09) Avail: NTlS HC AO6/MF AEROELASTIC MODELING FOR THE FIT TEAM F/A-18 A01 CSCL 01A SIMULATION Due to new design technology, future jet fighters will fly at THOMAS A. ZEILER and CAROL D. WIESEMAN Mar. 1989 higher g levels than before. A previous preliminary design study 19 p Presented at the 2nd NASAIAF Symposium on Recent was conducted to develop an ejection seat providing higher Advances in Multidisciplinary Analysis and Optimization, Hampton, g-tolerance for the crewmember during maneuvering as well as VA, Sep. 1988 improved windblast protection during ejection. This seat used the (NASA-TM-101569; NAS 1.15:101569) Avail: NTlS HC AO3/MF crewmember in a prone, or leaning forward, position. The Prone A01 CSCL 01C Ejection System was computer simulated at supersonic conditions Some details of the aeroelastic modeling of the F/A-18 aircraft in the earlier report and found satisfactory. It was the purpose of done for the Functional Integration Technology (FIT) team's !his present rose~rch!o perform an experimental low speed study research in integrated dynamics modeling and how these are of the aerodynamic characteristics of the PRESS. Wind tunnel combined with the FIT team's integrated dynamics model are testing was performedto determine the static stability of the PRESS described. Also described are mean axis corrections to elastic and measure pressures over the seat. It was determined that modes, the addition of nonlinear inertial coupling terms into the static pitch stability did not occur at the desired angle of attack, equations of motion, and the calculation of internal loads time but could be easily corrected with aerodynamic fins and/or a shift histories using the integrated dynamics model in a batch simulation in the center of gravity. Directional stability was also confirmed. program. A video tape made of a loads time history animation An analytical experiment was also performed to determine whether was included as a part of the oral presentation. Also discussed is a potential paneling code could be modified to predict flow work done in one of the areas of unsteady aerodynamic modeling conditions about the PRESS. An apparent body was constructed identified as needing improvement, specifically, in correction factor by including the regions of flow separation as part of the seat methodologies for improving the accuracy of stability derivatives itself. Water tunnel flow visualization was used to determine the calculated with a doublet lattice code. Author shape of the apparent body. The computer analysis showed that a paneling code could accurately predict the pressure coefficients on the cowling. GRA 06 N89-20989# Air Force Inst. of Tech., Wright-Patterson AFB, OH. School of Engineering. AIRCRAFT INSTRUMENTATION RESPONSE EQUIVOCATION ANALYSIS FOR THE SMART STICK CONTROLLER M.S. Thesis JOHN M. PRACHER Nov. 1988 148 p Includes cockpit and cabin display devices; and flight instruments. (AD-A203146; AFIT/GE/ENG/88D-38) Avail: NTlS HC A07/MF A01 CSCLOlD This thesis provides an analysis of response equivocation (lost A89-33148 information) for subjects who use the smart stick controller -- an DESIGN OF AN AIRBORNE OPTIC FIBER DATA BUS SYSTEM aircraft stick controller designed by the Armstrong Aerospace RENZHOU FAN, GONGHAO WANG, and RUILIN CHEN (Beijing Medical Research Laboratory (AAMRL) to improve a pilot's tracking University of Aeronautics and Astronautics, People's Republic of performance. First, a control theory model of a compensatory China) Chinese Journal of Aeronautics (ISSN 1000-9361), vol. 1. tracking task is developed and analyzed. Then, using an information July 1988, p. 128-137. refs theory model of the pilot, the results are used to develop The development, application, communication protocol, and expressions for information theory parameters (input entropy, system structure of an airborne data-bus system are discussed. transinformation, and equivocation). Six subjects were tested using The emphasis is on the design of the hardware, software, and the smart stick controller and experimental an apparatus developed fiber-optic transmission system of the bus controller and remote by the AAMRL. Each subject was tested twice: first in the passive terminal. Some experiments and their results are also given. stick mode (normal stick operation), and again in the active stick Author mode. In the active stick mode, the smart stick actively exerts a force in the direction opposite to the desired stick motion. Power A89-33571 spectral densities of the display error and the operator response LOW COST AVIONIC SYSTEM FOR UMA were used to calculate the information theory parameters. GRA S. E. UWINS (Skyleader Radio Control, Ltd., Croydon, England) and D. W. ALLEN IN: Remotely piloted vehicles; International N89-20990# Georgia Inst. of Tech., Atlanta. School of Mechanical Conference, 7th, Bristol, England, Sept. 12-14, 1988, Engineering. Supplementary Papers. Bristol, England, University of Bristol, 1988, NONLINEAR ROTORCRAFT ANALYSIS-EXPERIMENTAL AND p. 19.1-1 9.4. ANALYTICAL Final Report, 15 Sep. 1985 - 14 Jan. 1989 The desirable features and capabilities of avionics suites BENSON H. TONGUE 13 Nov. 1988 8 p applicable to both civil and military reconnaissance unmanned (Contract DAAG29-85-K-0207) aircraft (UMA) are discussed. The XRAEl UMA test vehicle was (AD-A203967; ARO-22557.5-EG) Avail: NTlS HC AO2/MF A01 initially outfitted with a commercial anemometer-based airspeed CSCL 01c sensor and an angle-of-attack sensor, for comparative testing; in A parallel effort involving both analytical and experimental work order to furnish additional damping in pitch, an angular rate gyro was performed to allow a deeper understanding of the limit Cycle was incorporated. The result was the Skyleader 8409 low cost behavior of rotorcraft and of the implication of this behavior for UMA avionics system, whose capacity for further development is the safe operation of such rotorcraft. The theoretical development presently related. O.C. encompassed articulated and hingeless rotors with a great enough number of included degrees of freedom to allow accurate A89-33574 predictions of a simplified rotorcraft's responses. The experimental LINESCAN 2000 - TOMORROWS SENSOR TODAY model allowed the simulation of both hingeless and articulated T. M. STEPHENS (British Aerospace, PLC, Hatfield, England) IN: rotors in ground resonance. The purpose of the above work was Remotely piloted vehicles; International Conference, 7th, Bristol.
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England, Sept. 12-14, 1988, Supplementary Papers. Bristol, The Netherlands. 2 Oct. 1987 Previously announced in IAA as England, University of Bristol, 1988, p. 23.1-23.4. A8841465 The range of considerations pertinent to the design of a payload (NLR-MP-870474; ETN-89-94036) Avail. NTlS HC AO3/MF for reconnaissance RPV applications is illustrated by the case of A0 1 the ’Linescan 2000’ IR imaging system’s design constraints, which The data acquisition system for the Fokker 100 test aircraft encompass high reliability and maintainability, modularity, and the (capability, electrical lay-out, real time presentation facilities, and minimization of scheduled servicing. Linescan 2000, which occupies performance parameters) is described. The take-off and landing an RPV payload volume of only 0.02 cu m, achieves high resolution performance measuring system and the automatic noise measuring and a wide field-of-view with a configuration that entails a minimum system are highlighted. It was decided to keep the data acquisition of onboard signal processing. Proven modular components are systems for both test aircraft identical. The savings on the design employed, significantly reducing development costs. O.C. costs and the possibility of using each aircraft for most of the flight tests counterbalance the extra cost in instrumentation. The A8934443 data acquisition systems perform to specification. ESA AVIATION DISPLAYS ALAN F. STOKES (Illinois, University, Savoy) and CHRISTOPHER N89-20993# Air Force Inst. of Tech., Wright-Patterson AFB, D. WICKENS (Illinois, University, Champaign) IN: Human factors OH. School of Engineering. in aviation. San Diego, CA, Academic Press, Inc., 1988, p. 387-431. REAL-TIME DISPLAY OF TIME DEPENDENT DATA USING A Research supported by General Motors Corp. refs HEAD-MOUNTED DISPLAY M.S. Thesis The design principles and characteristics of state-of-the-art GARY K. LORIMOR Dec. 1988 64 p cockpit displays are reviewed from the perspective of (AD-A203051; AFIT/GE/ENG/88D-22) Avail: NTlS HC A04/MF human-factors engineering. Topics addressed include flight-path A01 CSCL25C displays (quickening and predictive displays), navigational displays, The purpose of this investigation was the development of a display organization and configuration, the visual overload problem, software system to integrate time-dependent data with a head-up displays, peripheral displays, speech and nonspeech three-dimensional virtual environment. Red Flag data tapes were auditory displays, color displays, advanced cockpits, and display used as a source of time-dependent data. To project this into a automation (decluttering and reconfiguration). Drawings, diagrams, virtual environment a head-mounted display was used. The software and photographs of typical displays are provided. T.K. development was done on a Silicon Graphics Iris 3130 workstation. The design of the software system allows the user to be free of A8434446 the keyboard for most situations. The position of the user’s head COCKPIT-CREW SYSTEMS DESIGN AND INTEGRATION was determined using a Polhemus 3-space tracker. The user could GEORGE A. SEXTON (Lockheed-Georgia Co., Advanced Design exercise basic control of the system with input from mouse buttons. Dept., Marietta) IN: Human factors in aviation. San Diego, CA, The user was allowed to move to any position in the environment Academic Press, Inc., 1988, p. 495-526. refs by looking in the direction of desired travel. The user was also Recent advances in transport-aircraft cockpit design are given the option to ride in any cockpit which was in the environment. reviewed from the perspective of human-factors engineering. The This allowed the user to see the environment from a pilots early evolution of the cockpit is recalled; the relationship between perspective at a specific point and time in the display sequence. design and crew workload is explored; and the design philosophies Minimal machine dependent routines were used in the development and actual display and control systems of state-of-the-art cockpits of the software system. The software system was developed using are discussed in detail and illustrated with extensive photographs. the C programming language. The results of this effort were Particular attention is given to computerization, head-down and encouraging. There appears to be further possibilities of use for a head-up displays, fly-by-wire systems, control technology, data system of this type in the training arena. The update rate of this links, lighting, the crew-systems design process itself (mission system is about 10 frames per second. There appears to be several analysis and mission scenarios, hardware design, mockup studies, open questions concerning the benefits of such a system in the and testing by experienced aircrews), and system integration. The training environment. GRA impact of new designs on physical and cognitive workloads, aircraft certification, and personnel policies is briefly characterized. T.K. N89-20994# Air Force Inst. of Tech., Wright-Patterson AFB, OH. School of Engineering. N89-20129# National Aerospace Lab., Amsterdam (Netherlands). A HELMET-MOUNTED VIRTUAL ENVIRONMENT DISPLAY Hoofdafdeling: Vliegtuigen. SYSTEM M.S. Thesis ELECTRONICS IN CIVIL AVIATION ROBERT KEITH REBO Dec. 1988 87 p F. J. ABBINK 5 Nov. 1987 20 p In DUTCH; ENGLISH (AD-A203055; AFIT/GCS/ENG/88D-17) Avail: NTlS HC summary Presented at the KIVI-NIRIA Symposium on Electronics A05/MF A01 CSCL 25C in Aerospace, Utrecht, The Netherlands, 5 Nov. 1987 This effort researches existing Helmet Mounted Display (HMD) (NLR-MP-87009-U; ETN-89-94031) Avail: NTlS HC AO3/MF systems and presents a prototype design of a color A01 Helmet-MountedVirtual Environment Display System. Many existing The development of the electronic systems which are used in systems are discussed, including systems currently in use by the airliners for communication, navigation, identification, flight control, US. Navy, Air Force, and Army. Several differing designs are engine control, for the acquisition and presentation of flight and presented and evaluated. The Air Force Institute of Technology System data, as well as for air traffic control is reviewed. The Helmet Mounted Virtual Environment Display System places the development of these systems was made possible by developments user in a visual situation that is generated by a computer. This in microelectronics, computer technology, and display technology. HMD system could easily be adapted for use with a video camera. Developments in electronics systems in civil aviation, as fly-by-wire, This paper presents an inexpensive system design that incorporates full authority digital engine control, satellite navigation, satellite the benefits of other efforts. The cost trade offs are evaluated communication, and the microwave landing system, and their and the best design for the lowest cost is presented. The optics, implications on future air traffic control are considered. ESA three dimensional considerations, the mounting platform and display technologies are also discussed. The final HMD system N89-20130# National Aerospace Lab., Amsterdam (Netherlands). design is described in detail and presented so that any reader Flight Div. could build a similar system for minimal cost. This system uses THE DATA ACQUISITION SYSTEM FOR THE FOKKER 100 color Liquid Crystal Displays (LCD) mounted directly before the TEST AIRCRAFT eyes of the user. Specially designed optics were developed to S. STORM VANLEEUWEN and A. VOSKES (Fokker B.V., enable the user to focus on the image Only inches away. The Amsterdam, Netherlands ) 28 Jul. 1987 15 p Presented at positional information of the user is determined by a sensitive the 18th Annual Flight Test Engineers Symposium, Amsterdam, electromagnetic device developed by Polhemus Navigational
476 07 AIRCRAFT PROPULSION AND POWER
Sciences. This system is very accurate but has a limited effective A89-33570 range. Predictive tracking is discussed and implemented using a EVOLUTION OF A SMALL TURBINE ENGINE FAMILY FOR simple Kalman filter equation. GRA UNMANNED AERIAL VEHICLES J. POWELL (Williams International, Walled Lake, MI) IN: Remotely piloted vehicles; International Conference, 7th, Bristol. England, Sept. 12-14, 1988, Supplementary Papers. Bristol, England, 07 University of Bristol. 1988, p. 17.1-1 7.6. An account is given of the development history for a family of small, flightweight, expendable gas turbine engines applicable to AIRCRAFT PROPULSION AND POWER many typical unmanned air vehicles' turboshaft requirements, including those of the CL-227 VTOL Sentinel contrarotating Includes prime propulsion systems and systems components, e.g., rotary-wing propulsion system. An exhaust heat recuperator may gas turbine engines and compressors; and on-board auxiliary power be incorporated in order to improve fuel consumption by as much plants for aircraft. as 45 percent and to reduce exhaust IR emissions, as required to improve tactical survivability. One engine family member is also applicable to turboshaft primary power unit requirements. O.C. AW-333~ 3-D LDA-MEASUREMENTS IN THE JET OF A BYPASS-ENGINE A89-33769# D. PALLEK, K.-H. SAUERLAND, K. A. BUETEFISH (DFVLR, lnstitut ACOUSTIC CHARACTERISTICS OF COUNTERROTATING fuer experimentelle Stroemungsmechanik, Goettingen, Federal FANS FROM MODEL SCALE TESTS Republic of Germany), H.-J. ROSCHER, and H. HOHEISEL B. A. JANARDAN and P. R. GLIEBE (General Electric Co., (DFVLR, lnstitut fuer Entwurfsaerodynamik, Brunswick, Federal Cincinnati, OH) AIAA, Aeroacoustics Conference, 12th, San Republic of Germany) IN: International Symposium on Applications Antonio, TX, Apr. 10-12, 1989. 14 p. refs of Laser Anemometry to Fluid Mechanics, 4th. Lisbon, Portugal, (AIAA PAPER 89-1142) . July 11-14, 1988, Proceedings. Lisbon, lnstituto Superior Tecnico, The noise characteristics of contrarotating UDF engine rotor 1988, p. 4.13 (6 p.). refs configurations were studied in an anechoic facility with a 1/Bscale The present contribution describes measurements obtained with rotor model. Tests were conducted at simulated takeoff and cutback a three-component LDA (focal length 2.3 m) within the propulsive conditions to determine the effects of such configurational jet of a real fan engine (RR M45 H) in an engine test bed. The variations as front and back blade row blade-numbers, tip speeds, aerodynamic data obtained at the fan exit, at the turbine nozzle and rotor-to-rotor spacings. Significant overall acoustic improve- exit, and downstream of the nozzle plug give insight into the ments result with increasing blade numbers. Steady-loading noise, propulsive jet behavior without external flow for an off-design as represented by noise levels at the blade passing frequencies, condition. The velocity components in the specified positions for decreased with reduced tip speed for a given thrust. Standard- all three coordinate directions are discussed, allowing the diameter and clipped-diameter aft fan blade effects were also evaluation of the radial distributions and the swirl components. In tested. O.C. addition, the important parameters of the turbulence in the jet are presented. Author A09-34139 A89-33405 SOME ASPECTS OF THE NUMERICAL MODELING OF THE METALLIC LIMITATIONS IN AIRCRAFT ENGINES - THE NONSTATIONARY HEAT CONDUCTIVITY OF GAS TURBINE RATIONAL RETURN TO THE STONE AGE COMPONENTS [ NEKOTORYE VOPROSY CHISLENNOGO G. W. MEETHAM (Rolls Royce, PLC, Derby, England) IN: MODELlROVANllA NESTATSIONARNOI TEPLOPROVODNOSTI International Conference on PM Aerospace Materials, Lucerne, DETALEI GAZOVYKH TURBIN] Switzerland, Nov. 2-4, 1987, Proceedings. Shrewsbury, England, V. G. KADYSHEV and V. A. STRUNKIN Aviatsionnaia Tekhnika MPR Publishing Services, Ltd., 1988, p. 38.1 -38.6. (ISSN 0579-2975), no. 4, 1988, p. 55-59. In Russian. refs The current development status of materials for high-tem- Some problems associated with the implementation of the finite perature applications in advanced gas-turbine engines is sur- element method in calculations of the thermal state of gas turbine veyed. Topics discussed include Ni-based superalloys for turbine components are discussed. In particular, methods are described airfoils, corrosion-resistant coatings, directional solidification, which make it possible to reduce the computational effort by a single-crystal technology, mechanical alloys, and blade cooling factor of 4-5. This is achieved by using a modified numerical scheme methods. Consideration is given to film cooling techniques for and through an optimum combination of the integration step and combustors, oxidation-resistant superalloys for combustors, and of the upper relaxation parameter in solving systems of algebraic the future potential of Sic and Si3N4 components (assuming that equations. V.L. their reliability can be demonstrated). T.K.
AW-33565 A09-34140 THE NORTON P73 ROTARY RPV ENGINE EFFECT OF THE DESIGN OF A TWO-ROW NOZZLE RING ON C. J. BIDDULPH (Norton Motors, Ltd., Lichfield, England) IN: THE EFFICIENCY OF A TURBINE STAGE OF MEDIUM ROTOR Remotely piloted vehicles; International Conference, 7th, Bristol, SOLIDITY [VLIIANIE KONSTRUKTSH DVUKHRIADNOGO England, Sept. 12-14, 1988, Proceedings. Bristol, England, SOPLOVOGO APPARATA NA EFFEKTIVNOST' TURBlNNOl University of Bristol. 1988, p. 16.1 -16.8. STUPENI SREDNEI VEERNOSTI] The development history, design features and performance IU. L. KORZUNOV, S. S. KOSTIUCHENKO, IU. I. MITIUSHKIN, V. capabilities of the P73 RPV engine are presented. The P73 is a D. RONZIN, and V. M. CHERNYSH Aviatsionnaia Tekhnika (ISSN Wankel-type rotary engine based on extensive experience with 0579-2975), no. 4, 1988, p. 59-64. In Russian. refs motorcycle motors, but incorporating ram air cooling and A study is made of the effect of the tangential tilt of back-twisted ultralightweight structural design to meet the performance blades and of the profiling of the outer boundary surface of a requirements of target-drone RPVs. The use of ram-air cooling two-row nozzle ring on the efficiency of a medium-solidity turbine has obviated intercoolers and exhaust ejectors. The engine is able cascade. It is shown that the two-row nozzle ring design proposed to produce 26 bhp despite a weight of only 22 Ibs, and has met here reduces the thrust ratio gradient over the blade height and all requirements of the Joint Air Regulations 22.1849, which is the increases the efficiency of the turbine stage. The increase in turbine European test standard for motor-glider and sailplane engines. efficiency resulting from the substitution of a two-row nozzle ring O.C. for a single-row ring is estimated at 0.8 percent. V.L.
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A8934141 numerical scheme was also performed. The effects of the AN ANALYTICAL-EXPERIMENTALSTUDY OF RING GAP parameters on the rotating stall performance are investigated. The LOSSES IN SMALL AXIAL-FLOW TURBINES effects of inlet guide vane loss on rotating stall performance were [ RASCHETNO-EKSPERIMENTAL‘NOE ISSLEDOVANIE POTER’ also discussed. An evaluation is made of the h prime = -g OT RADIAL’NOGO ZAZORA V OSEVYKH MALORAZMERNYKH approximation, and a spectral analysis of the rotating stall cell TURBlNAKHl determined from the full model suggests why this breaks down. E. A. KRYLOV and S. A. GUSAROV Aviatsionnaia Tekhnika Dissert. Abstr. (ISSN 0579-2975), no. 4, 1988, p. 64-68. In Russian. refs Ring gap losses in small axial-flow turbines are investigated N89-20132’# Pratt and Whitney Aircraft, East Hartford, CT. analytically and experimentally using advanced experimental design Commercial Engineering Dept. methods. A generalized expression is obtained which provides a STRUCTURAL TAILORING OF ADVANCED TURBOPROPS way to accurately account for the effect of ring gap losses in this (STAT) PROGRAMMER’S MANUAL class of turbines. It is shown that ring gap losses have a noticeable K. W. BROWN and P. R. HARVEY Mar. 1989 53 p effect on turbine efficiency. V.L. (Contract NAS3-23941) (NASA-CR-182164; NAS 1.26:182164; PWA-5967-51) Avail: A8934150 NTlS HC A04/MF A01 CSCL 21E NOISE LEVELS OF A COMBINED BYPASS-PROPFAN ENGINE The Structural Tailoring of Advanced Turboprops (STAT) IN THE FAR SONIC FIELD [UROVNI SHUMA DVIGATELIA computer program was developed to perform numerical KOMBINIROVANNOI SKHEMY TRDD-TVVD V DAL‘NEM optimizations on highly swept propfan blades. This manual ZVUKOVOM POLE] describes the functionality of the STAT system from a programmer’s I. S. ZAGUZOV Aviatsionnaia Tekhnika (ISSN 0579-2975), no. viewpoint. It provides a top-down description of module intent and 4. 1988, p. 91, 92. In Russian. interaction. The purpose of this manual is to familiarize the The acoustic characteristics of a combined bypass-propfan programmer with the STAT system should he/she wish to enhance engine with counterrotating coaxial propellers are investigated or verify the program’s function. Author analytically in the far sonic field. Calculations are carried out for standard propellers with straight blades. Noise matrices of the N89-20133’# National Aeronautics and Space Administration. principal sources are obtained for different operating regimes and Lewis Research Center, Cleveland, OH. then used for estimating environmental noise levels produced by EXPERIMENTAL INVESTIGATION OF TRANSONIC aircraft equipped by such engines. Possible ways of reducing the OSCILLATING CASCADE AERODYNAMICS engine noise level are briefly discussed. V.L. DANIEL H. BUFFUM and SANFORD FLEETER (Purdue Univ., West Lafayette, IN.) Jan. 1989 15 p Presented at the 27th Aerospace A89-34409# Sciences Meeting, Reno, NV, 9-12 Jan. 1989; sponsored in part A NEW METHOD FOR THE THERMODYNAMIC CALCULATION by AlAA Previously announced in IAA as A89-26369 OF COMBUSTION CHAMBERS (Contract NAG3-656) TIANYU ZHU (Air Force PR China, Aeronautic Repair Research (NASA-TM-101993; E-4697; NAS 1.15:101993) Avail: NTlS HC Institute, People’s Republic of China) and FUQUN CHEN A03/MF A01 CSCL 21E (Northwestern Polytechnical University, Xian, People’s Republic of Fundamental experiments are performed in the NASA Lewis China) Journal of Propulsion Technology (ISSN 1001-4055). Feb. Transonic Oscillating Cascade Facility to investigate the subsonic 1989, p. 27-30, 73. In Chinese, with abstract in English. and transonic aerodynamics of cascaded airfoils executing torsion For the thermodynamic calculation of the gas turbine mode oscillations at realistic values of reduced frequency. In combustion chamber, there are two methods to be selected, the particular, an unsteady aerodynamic influence coefficient technique noniterative precise method (NIPM) and the isothermal enthalpy is developed and utilized. In this technique, only one airfoil in the difference method (IEDM). According to the principle of NIPM, a cascade is oscillated at a time, with the resulting airfoil surface general solution of the energy equilibrium equation for the main unsteady pressure distribution measured on one dynamically combustion chamber, the reheat combustor, and the exhaust-fired instrumented reference airfoil. The unsteady aerodynamics of an burners in the gas turbine and steam turbine combined cycle, equivalent cascade with all airfoils oscillating at any specified using gas or liquid fuel, is developed in this paper. It is shown interblade phase angle are then determined through a vector that IEDM is the linear approximation of NIPM, and the fuel-air summation of these data. These influence coefficient determined ratio calculated by the former is slightly less than that by the oscillating cascade data were correlated with: (1) data obtained in latter, but their relative difference will not exceed 0.5 percent. this cascade with all airfoils oscillating at several interblade phase The general solution provided in this paper can also be applied to angle values; and (2) predictions from a classical linearized the thermodynamic calculation of all kinds of engine combustion unsteady cascade model. Author chamber using gas or liquid fuel in aerospace. Author N89-20134’# Cornell Univ., Ithaca, NY. N89-20131 Cornell Univ., Ithaca. NY. PROPULSION OVER A WIDE MACH NUMBER RANGE Final AN ANALYTICAL AND NUMERICAL STUDY OF AXIAL FLOW Report M.S. Thesis COMPRESSOR INSTABILITY Ph.D. Thesis EDWIN L. RESLER, JR. and BARRY M. GREENBERG Mar. FRANCES ELIZABETH MCCAUGHAN 1988 192 p 1989 71 p Avail: Univ. Microfilms Order No. DA8821176 (Contract NAG3-803) An axial-flow compressor is an important component of the (NASA-CR-182267; NAS 1.26:182267) Avail: NTlS HC A04/MF turbo-jet engine. It is of great interest to characterize the possible A01 CSCL 21E modes of response of this system with respect to variations in Criteria is presented to assess the relative merits of different the values of the governing parameters. A mathematical model of propulsion systems. Previous references focus mainly on subsonic an idealized axial-flow compression system was developed by or low supersonic flight speeds. The main focus here is on a Moore and Greitzer. The properties of this model, which consists higher range, from low supersonic to orbital velocities. Air breathing of a set of partial differential equations, were investigated by both propulsion systems for hypersonic flight persent the engine designer analytical and numerical means. A single-harmonic truncation of with circumstances that differ in important fundamental ways from the full model was investigated by means of modern dynamical those encountered in engines designed for operation at subsonic systems theory. A thorough investigation is made of the stability or low supersonic speeds. This analysis highlights the importance of the equilibria and periodic solutions, revealing period-doubling of various features of hypersonic engine design. Since the bifurcations which lead to apparently chaotic behavior. Using performance of hypersonic engines are energy limited, unlike low Cornell’s supercomputing facilities, an extensive study of the full speed engines which are stagnation pressure limited, the efficient set of partial differential equations using a pseudo-spectral use of the energy of the fuel used is critical to minimize the
478 07 AIRCRAFT PROPULSION AND POWER
take-off fuel mass fraction of the vehicle. Furthermore, since the N89-20138'# National Aeronautics and Space Administration. required energy increase of a vehicle per incremental speed change Lewis Research Center, Cleveland, OH. increases with speed, the engine must be designed to operate ASSESSMENT, DEVELOPMENT, AND APPLICATION OF efficiently at high speed. An analysis of engine performance in COMBUSTOR AEROTHERMAL MODELS terms of entropy changes of the flow passing through the engine J. D. HOLDEMAN, H. C. MONGIA, and E. J. MULARZ (Army allows comparison of various engine designs as well as a Aviation Systems Command, Cleveland, OH.) In its Toward convenient method to determine the effect of individual engine Improved Durability in Advanced Aircraft Engine Hot Sections p component efficiencies on overall engine performance. Author 23-37 Apr. 1989 Previously announced in IAA as A88-54140 Avail: NTlS HC AOGIMF A01 CSCL 21E The gas turbine combustion system design and development N89-20135*# National Aeronautics and Space Administration. effort is an engineering exercise to obtain an acceptable solution Lewis Research Center, Cleveland, OH. to the conflicting design trade-offs between combustion efficiency, TOWARD IMPROVED DURABILITY IN ADVANCED AIRCRAFT gaseous emissions, smoke, ignition, restart, lean blowout, burner ENGINE HOT SECTIONS exit temperature quality, structural durability, and life cycle cost. DANIEL E. SOKOLOWSKI, ed. Washington Apr. 1989 121 p For many years, these combustor design trade-offs have been Proceedings of the 3rd ASME International Gas Turbine and carried out with the help of fundamental reasoning and extensive Aeroengine Congress and Exposition, Amsterdam, Netherlands, component and bench testing, backed by empirical and experience 5-9 Jun. 1986 PreviGUslj afinoiinced in !.lA as P.89-54137 (NASA-TM-4087; E-4468; NAS 1.15:4087) Avail: NTlS HC correiaiions. Recent edvances ifi :he capaSi!ity c! ccmpe!a!iona! fluid dynamics codes have led to their application to complex 3-D AOGIMF A01 CSCL 21 E flows such as those in the gas turbine combustor. A number of The conference on durability improvement methods for U.S. Government and industry sponsored programs have made advanced aircraft gas turbine hot-section components discussed NASA's Hot Section Technology (HOST) project, advanced significant contributions to the formulation, development, and verification of an analytical combustor design methodology which high-temperature instrumentation for hot-section research, the will better define the aerothermal loads in a combustor, and be a development and application of combustor aerothermal models, valuable tool for design of future combustion systems. The and the evaluation of a data base and numerical model for turbine contributions made by NASA Hot Section Technology (HOST) heat transfer. Also discussed are structural analysis methods for sponsored Aerothermal Modeling and supporting programs are gas turbine hot section components, fatigue life-prediction modeling for turbine hot section materials, and the service life modeling of described. Author thermal barrier coatings for aircraft gas turbine engines. N89-20139'# National Aeronautics and Space Administration. N89-20136'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. Lewis Research Center, Cleveland, OH. REVIEW AND ASSESSMENT OF THE DATABASE AND NASA HOST PROJECT OVERVIEW NUMERICAL MODELING FOR TURBINE HEAT TRANSFER DANIEL E. SOKOLOWSKI In its Toward Improved Durability in H. J. GLADDEN and R. J. SIMONEAU In its Toward Improved Advanced Aircraft Engine Hot Sections p 1-4 Apr. 1989 Durability in Advanced Aircraft Engine Hot Sections p 39-55 Apr. Previously announced in IAA as A88-54138 1989 Previously announced in IAA as A8864141 Avail: NTlS HC AOG/MF A01 CSCL 21 E Avail: NTlS HC AO6/MF A01 CSCL 21E NASA's Hot Section Technology (HOST) program has The objectives of the NASA Hot Section Technology (HOST) developed improved analytical models for the aerothermal Turbine Heat Transfer subproject were to obtain a better environment, thermomechanical loading, material behavior, understanding of the physics of the aerothermodynamic structural response, and service life of aircraft gas turbine engines' phenomena and to assess and improve the analytical methods hot section components. These models, in conjunction with used to predict the flow and heat transfer in high-temperaturegas sophisticated computer codes, can be used in design analyses of turbines. At the time the HOST project was initiated, an critical combustor and turbine elements. Toward these ends, efforts across-the-board improvement in turbine design technology was were undertaken in instrumentation, combustion, turbine heat needed. A building-block approach was utilized and the research transfer, structural analysis, fatigue-fracture, and surface protection. ranged from the study of fundamental phenomena and modeling Attention is presently given to the organization of HOST activities to experiments in simulated real engine environments. Experimental and their specific subject matter. Author research accounted for approximately 75 percent of the funding while the analytical efforts were approximately 25 percent. A healthy government/industry/university partnership, with industry providing N89-20137'# National Aeronautics and Space Administration. almost half of the research, was created to advance the turbine Lewis Research Center, Cleveland, OH. heat transfer design technology base. Author ADVANCED HIGH TEMPERATURE INSTRUMENT FOR HOT SECTION RESEARCH APPLICATIONS D. R. ENGLUND and R. G. SEASHOLTZ In its Toward Improved N89-20140'# National Aeronautics and Space Administration. Durability in Advanced Aircraft Engine Hot Sections p 5-21 Apr. Lewis Research Center, Cleveland, OH. 1989 Previously announced in IAA as A88-54139 STRUCTURAL ANALYSIS METHODS DEVELOPMENT FOR Avail: NTlS HC AOG/MF A01 CSCL 21E TURBINE HOT SECTION COMPONENTS Programs to develop research instrumentationfor use in turbine R. L. THOMPSON In its Toward Improved Durability in Advanced engine hot sections are described. These programs were initiated Aircraft Engine Hot Sections p 57-82 Apr. 1989 Previously to provide improved measurements capability as support for a announced in IAA as A8844142 multidisciplinary effort to establish technology leading to improved Avail: NTlS HC AOGIMF A01 CSCL 21E hot section durability. Specific measurement systems described The structural analysis technologies and activities of the NASA here include heat flux sensors, a dynamic gas temperature Lewis Research Center's gas turbine engine HOT Section measuring system, laser anemometry for hot section applications, Technoloogy (HOST) Program are summarized. The technologies an optical system for viewing the interior of a combustor during synergistically developed and validated include: time-varying operation, thin film sensors for surface temperature and strain thermal/mechanical load models; component-specific automated measurements, and high temperature strain measuring systems. geometric modeling and solution strategy capabilities; advanced The state of development of these sensors and measuring systems inelastic analysis methods; inelastic constitutive models; is described, and, in some cases, examples of measurements high-temperature experimental techniques and experiments; and made with these instruments are shown. Work done at the NASA nonlinear structural analysis codes. Features of the program that Lewis Research Center and at various contract and grant facilities incorporate the new technologies and their application to hot is covered. Author section component analysis and design are described. Improved
479 07 AIRCRAFT PROPULSION AND POWER and, in some cases, first-time 3-D nonlinear structural analyses of N89-20144*# National Aeronautics and Space Administration. hot section components of isotropic and anisotropic nickel-base Lewis Research Center, Cleveland, OH. superalloys are presented. Author VIEWS ON THE IMPACT OF HOST J. B. ESGAR (Sverdrup Technology, Inc., Cleveland, OH.) and DANIEL E. SOKOLOWSKI In its Toward Improved Durability in N89-20141'# General Electric Co., Cincinnati, OH. Advanced Aircraft Engine Hot Sections p 117-123 Apr. 1989 STRUCTURAL ANALYSIS APPLICATIONS Previously announced in IAA as A8844146 R. L. MCKNIGHT In NASA, Lewis Research Center, Toward Avail: NTlS HC AO6/MF A01 CSCL 21E Improved Durability in Advanced Aircraft Engine Hot Sections p The Hot Section Technology (HOST) Project, which was 83-95 Apr. 1989 Previously announced in IAA as A8844143 initiated by NASA Lewis Research Center in 1980 and concluded Avail: NTlS HC AO6/MF A01 CSCL 21E in 1987, was aimed at improving advanced aircraft engine hot An account is given of the application of computer codes for section durability through better technical understanding and more the efficient conduct of three-dimensional inelastic analyses to accurate design analysis capability. The project was a aircraft gas turbine combustor, turbine blade, and turbine stator multidisciplinary, multiorganizational, focused research effort that vane components. The synergetic consequences of the program's involved 21 organizations and 70 research and technology activities activities are illustrated by an evaluation of the computer analyses and generated approximately 250 research reports. No major of thermal barrier coatings and of the Space Shuttle Main Engine's hardware was developed. To evaluate whether HOST had a High Pressure Fuel Turbopump turbine blading. This software, in significant impact on the overall aircraft engine industry in the conjunction with state-of-the-art supercomputers, can significantly development of new engines, interviews were conducted with 41 reduce design-task burdens. Author participants in the project to obtain their views. The summarized results of these interviews are presented. Emphasis is placed on results relative to three-dimensional inelastic structural analysis, N8920142'# National Aeronautics and Space Administration. thermomechanical fatigue testing, constitutive modeling, combustor Lewis Research Center, Cleveland, OH. aerothermal modeling, turbine heat transfer, protective coatings, FATIGUE LIFE PREDICTION MODELING FOR TURBINE HOT computer codes, improved engine design capability, reduced engine SECTION MATERIALS development costs, and the impacts on technology transfer and G. R. HALFORD, T. G. MEYER, R. S. NELSON, D. M. NISSLEY, the industry-governmentpartnership. Author and G. A. SWANSON In its Toward Improved Durability in Advanced Aircraft Engine Hot Sections p 97-107 Apr. 1989 N89-20145# Army Aviation Engineering Flight Activity, Edwards Previously announced in IAA as A88-54144 Prepared in AFB, CA. cooperation with Pratt and Whitney Aircraft, East Hartford, CT AIRWORTHINESS AND FLIGHT CHARACTERISTICS CSCL 21 E Avail: NTlS HC AO6/MF A01 EVALUATION OF AN IMPROVED ENGINE AIR FILTRATION A major objective of the fatigue and fracture efforts under the SYSTEM ON THE UH-1H HELICOPTER Final Report, 16 Sep. NASA Hot Section Technology (HOST) program was to significantly 1987 29 Mar. 1988 improve the analytic life prediction tools used by the aeronautical - JAMES D. BROWN, JOHN S. LAWRENCE, PAUL W. LOSIER, gas turbine engine industry. This was achieved in the areas of CHARLES E. CASSIL, and MATHEW S. GRAHAM May 1988 high-temperature thermal and mechanical fatigue of bare and 160 p coated high-temperature superalloys. The cyclic crack initiation and (AD-A203446; USAAEFA-86-16) Avail: NTlS HC A08/MF A01 propagation resistance of nominally isotropic polycrystalline and CSCL 21 E highly anisotropic single crystal alloys were addressed. Life The U.S. Army Aviation Engineering Flight Activity conducted prediction modeling efforts were devoted to creep-fatigue an Airworthiness and Flight Characteristics evaluation of the UH-1H interaction, oxidation, coatings interactions, multiaxiality of aircraft with an Improved Engine Air Filtration System (IEAFS) stress-strain states, mean stress effects, cumulative damage, and thermomechanical fatigue. The fatigue crack initiation life models installed and with the standard filter installed between 16 September 1987 and 29 February 1988. Aircraft performance and developed to date include the Cyclic Damage Accumulation (CDA) handling qualities, engine-air induction system compatibility, and and the Total Strain Version of Strainrange Partitioning (TS-SRP) engine performance with the IEAFS installed were evaluated. This for nominally isotropic materials, and the Tensile Hysteretic Energy evaluation was conducted at Edwards AFB, California. Twenty-five Model for anisotropic superalloys. A fatigue model is being flights were conducted for a total of 20.1 productive flight hours. developed based upon the concepts of Path-Independent Integrals The aircraft performance and handling qualities, engine vibrations, (PII) for describing cyclic crack growth under complex nonlinear and inlet temperature characteristics with the IEAFS installed are response at the crack tip due to thermomechanical loading not significantly different from those of the standard UH-1H. The conditions. A micromechanistic oxidation crack extension model inlet pressure distortion and engine installation losses with the was derived. The models are described and discussed. Author IEAFS installed are less than those of the standard UH-1H. One deficiency, the poor reliability of the IEAFS latch rivets, was N8920143'# National Aeronautics and Space Administration. identified. One shortcoming, the poor reliability of the latch lever Lewis Research Center, Cleveland, OH. locking device, was identified. Both the deficiency and the LIFE MODELING OF THERMAL BARRIER COATINGS FOR shortcoming should be corrected before production. GRA AIRCRAFT GAS TURBINE ENGINES R. A. MILLER In its Toward Improved Durability in Advanced N89-20146*# Oklahoma Univ., Norman. School of Aerospace Aircraft Engine Hot Sections p 109-115 Apr. 1989 Previously and Mechanical Engineering. announced in IAA as A88-54145 A FIRST SCRAMJET STUDY Avail: NTlS HC AO6/MF A01 CSCL 21 E GEORGE EMANUEL Apr. 1989 55 p Thermal barrier coating life models developed under the NASA (Contract NAG1-886) Lewis Research Center's Hot Section Technology (HOST) Program (NASA-CR-184965; NAS 1.26:184965) Avail: NTlS HC A04/MF are summarized. An initial laboratory model and three A01 CSCL 21E design-capable models are discussed. Current understanding of A variety of related scramjet engine topics are examined. The coating failure mechanisms are also summarized. The materials flow is assumed to be 1-D, the gas is thermally and calorically and structural aspects of thermal barrier coatings have been perfect, and focus is on low hypersonic Mach numbers. The thrust successfully integrated under the HOST program to produce models and lift of an exposed half nozzle, which is used on the aerospace which may now or in the near future be used in design. Efforts plane, is evaluated as well as a fully confined nozzle. A rough on this program continue at Pratt and Whitney Aircraft where their estimate of the drag of an aerospace plane is provided. Thermal model is being extended to the life prediction of physical vapor effects and shock waves are next discussed. A parametric scramjet deposited thermal barrier coatings. Author model is then presented based on the influence coefficient method,
480 08 AIRCRAFT STABILITY AND CONTROL which evaluates the dominant scramjet processes. The independent parameters are the ratio of specific heats, a nondimensional heat addition parameter, and four Mach numbers. The total thrust AIRCRAFT STABILITY AND CONTROL generated by the combustor and nozzle is shown to be independent of the heat release distribution and the combustor exit Mach number, providing thermal choking is avoided. An operating Includes aircraft handling qualities; piloting; flight controls; and condition for the combustor is found that maximizes the thrust. autopilots. An alternative condition is explored when this optimum is no longer realistic. This condition provides a favorable pressure gradient and a reasonable area ratio for the combustor. Parametric results based A89-32725' Rice Univ., Houston, TX. on the model is provided. Author ABORT LANDING GUIDANCE TRAJECTORIES IN THE PRESENCE OF WINDSHEAR A. MIELE, T. WANG, C. Y. TZENG (Rice University, Houston, TX), and W. W. MELVIN (Air Line Pilots Association, Washington. N8920943*# McDonnell Aircraft Co., Saint Louis, MO. DC) Franklin Institute, Journal (ISSN 0016-0032). vo!. 326, no. Computation Fluid Dynamics. 2, 1989, p. 185-220. Research supported by Boeing Commercial TRANSONIC PROPULSION SYSTEM INTEGRATION ANALYSIS Airplane Co. and Air Line Pilots Association. refs AT MCDONNELL AiRCRAFT COMPANY (Con!:ac! NAG! -516) RAYMOND R. COSNER In NASA, Langley Research Center, The flight trajectory of abort landing in the presence of Transonic Symposium: Theory, Application, and Experiment, windshear is examined with reference to flight in a vertical plane. Volume 1, Part 2 p 409-436 Mar. 1989 It is assumed that the only control is the angle of attack. Inequality Avail: NTlS HC A22/MF A01 CSCL 21 E constraints are imposed on both the angle of attack and its time The technology of Computational Fluid Dynamics (CFD) is derivative. Numerical results are obtained for several combinations becoming an important tool in the development of aircraft of windshear intensities and initial altitudes. Guidance trajectories propulsion systems. Two of the most valuable features of CFD are considered, approximating the optimal trajectories and using * are: (1) quick acquisition of flow field data; and (2) complete local information on the state of the aircraft, the initial altitude, description of flow fields, allowing detailed investigation of and the total wind velocity difference. Results are presented for interactions. Current analysis methods complement wind tunnel optimal trajectories, guidance trajectories, simplified guidance testing in several ways. Herein, the discussion is focused on CFD trajectories, constant pitch trajectories, and maximum angle of methods. However, aircraft design studies need data from both attack trajectories. R.B. CFD and wind tunnel testing. Each approach complements the other. Author A89-33563 DEVELOPMENT AND IMPLEMENTATION OF FLIGHT CONTROL SYSTEM FOR A RESEARCH DROP MODEL N89-20995'# National Aeronautics and Space Administration. M. A. NASEEM (British Aerospace, PLC, Military Aircraft Div., Lewis Research Center, Cleveland, OH. Brough, England) and A. JEAN ROSS (Royal Aerospace A REAL-TIME SIMULATOR OF A TURBOFAN ENGINE Establishment, Farnborough, England) IN: Remotely piloted JONATHAN S. LlTT (Army Aviation Research and Development vehicles; International Conference, 7th. Bristol, England, Sept. Command, Cleveland, OH.), JOHN C. DEIAAT, and WALTER C. 12-14, 1988, Proceedings. Bristol, England, University of Bristol. MERRILL Mar. 1989 32 p 1988, p. 14.1-14.14. Research supported by the Ministry of Defence (NASA-TM-100869; E-4578; NAS 1.1 5:100869; Procurement Executive. refs AVSCOM-TR-89-C-001) Avail: NTlS HC AO3/MF A01 CSCL An account is given of the design, implementaticn, and testing 21 E of the flight control systems employed by two, slightly different A real-time digital simulator of a Pratt and Whitney FlOO engine High Incidence Research Model (HIRM) unmanned vehicle has been developed for real-time code verification and for actuator configurations used in free-flight tests of aircraft control methods diagnosis during full-scale engine testing. This self-contained unit at angles-of-attack up to, and beyond, departure. These can operate in an open-loop stand-alone mode or as part of configurations are both of tailless, canardldelta lifting surface type. closed-loop control system. It can also be used for control system Flight record samples are presented to illustrate the successes design and development. Tests conducted in conjunction with the achieved and the difficulties encountered. Although the two HIRM NASA Advanced Detection, Isolation, and Accommodation program vehicles are not RPVs, much that was learned during their flight show that the simulator is a valuable tool for real-time code testing is applicable to RPV control system design. O.C. verification and as a real-time actuator simulator for actuator fault diagnosis. Although currently a small perturbation model, advances A89-33566 in microprocessor hardware should allow the simulator to evolve THE COMPUTER CONTROLLED SYSTEM FOR MULTI-DRONE into a real-time, full-envelope, full engine simulation. Author PERFORMING FORMATION FLIGHT IN A SAME AERIAL ZONE BAIRONG YU (Vu He Machinery Factory, Nanjing, People's Republic of China) IN: Remotely piloted vehicles; International N89-20996'# National Aeronautics and Space Administration. Conference, 7th, Bristol, England, Sept. 12-14, 1988. Proceedings. Lewis Research Center, Cleveland, OH. Bristol, England, University of Bristol, 1988, p. 18.1-18.9. refs A COMPENDIUM OF CONTROLLED DIFFUSION BLADES A microcomputer-controlled FM radio remote-control system GENERATED BY AN AUTOMATED INVERSE DESIGN has been designed to accomplish multiple RPV piloting tasks within PROCEDURE a given aerial zone. Attention is given to the performance criteria JOSE M. SANZ Mar. 1989 204 p to which the communication encoder and control software have (NASA-TM-101968; E-4665; NAS 1.15:101968) Avail: NTlS HC been designed to ensure system stability, reliability, and resistance AlO/MF A01 CSCL 21E to interference. The principal use of this remote control system is A set of sample cases was produced to test an automated in the collective, formation-flying control of target drones. Block design procedure developed at the NASA Lewis Research Center diagrams are presented for the various hardware and software for the design of controlled diffusion blades. The range of components of the system. O.C. application of the automated design procedure is documented. The results presented include characteristic compressor and turbine A89-34130 blade sections produced with the automated design code as Well A MATHEMATICAL MODEL OF AIRCRAFT SPIN AND as various other airfoils produced with the base design method RESULTS OF ITS COMPUTER INTEGRATION Prior to the incorporation of the automated procedure. Author [MATEMATICHESKAIA MODEL' SHTOPORA SAMOLETA I
48 1 08 AIRCRAFT STABILITY AND CONTROL
REZUL’TATY INTEGRIROVANIIA EE NA EVMJ on Control 88, Oxford, England, Apr. 13-15, 1988, Proceedings. V. F. NATUSHKIN Aviatsionnaia Tekhnika (ISSN 0579-2975), London, Institution of Electrical Engineers, 1988, p. 689-694. no. 4, 1988, p. 18-22. In Russian. Research supported by SERC. refs Aircraft spin dynamics is examined on the basis of a new Control laws for hover flight conditions of a typical battlefield mathematical model which treats the spin as a complex helicopter are developed. The loop shaping procedure for designing phenomenon accompanied by a strong manifestation of inertial, the control laws using H-infinity optimization is presented. The aerodynamic, kinematic, and gyroscopic cross constraints. Criteria procedure is analyzed with respect to the singular values of the determining conditions for the onset and cessation of the spinning sensitivity and complementary sensitivity functions, using a nominal motion are obtained, as are optimal spin control laws. The model of the helicopter trimmed about the hover. Results of predictions of the model proposed here are found to be in good nonlinear time simulations demonstrated that the design was agreement with experimental data. V.L. robustly stable to the unmodeled rotor and actuator dynamics and to the unmodeled dynamics due to changes in the flight A8934897*# National Aeronautics and Space Administration. envelope. I.S. Langley Research Center, Hampton, VA. AEROELASTIC DEFORMATION EFFECTS ON THE A89-35300 STOPPED-ROTOR DYNAMICS OF AN X-WING AIRCRAFT VARIABLE STRUCTURE MODEL-FOLLOWING CONTROL OF MICHAEL G. GILBERT (NASA, Langley Research Center, FLIGHT DYNAMICS Hampton, VA) and WALTER A. SILVA (Planning Research Corp., A. S. I. ZINOBER, M. K. YEW (Sheffield, University, England), Hampton, VA) Journal of Aircraft (ISSN 0021-8669), vol. 26, and R. J. PATTON (York, University, England) IN: International May 1989, p. 482-488. Previously cited in issue 22, p. 3538, Conference on Control 88, Oxford, England, Apr. 13-15, 1988, Accession no. A87-49613. refs Proceedings. London, Institution of Electrical Engineers, 1988, p. 707-712. refs A89-35045’# National Aeronautics and Space Administration. (Contract SERC-GR/D/55436) Langley Research Center, Hampton, VA. This paper discusses the design of a control system which ACTIVE CONTROL LAW SYNTHESIS FOR FLEXIBLE would force the aircraft dynamics to follow the dynamics of an AIRCRAFT ideal problem. The model-following problem is considered using V. MUKHOPADHYAY (NASA, Langley Research Center; PRC the variable structure control approach of Young (1978) and Zinober Kentron, Inc., Hampton, VA) IN: Recent advances in control of (1984) and a CAD design package VASSYD with a robust nonlinear and distributed parameter systems, robust control, and eigenstructure algorithm; the objective of the control design is to aerospace control applications; Proceedings of the Symposium, force the error between the model and the plant to zero as time ASME Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2. 1988. tends to infinity. The simulation results, obtained for flight conditions New York, American Society of Mechanical Engineers, 1988, p. different from the nominal model on which the control design was 183-188. refs based, indicated clearly that the plant response follows the model (Contract NAS1-18000) trajectory, and the error between the two responses is rapidly An application of an active control law synthesis procedure is eliminated. I.S. presented, to meet multiple design requirements for a flexible aircraft modeled by a large order state space system. In this A89-35301 synthesis procedure, a linear quadratic Gaussian type cost function MULTIVARIABLE DESIGN OF A BANK-TO-TURN AUTOPILOT is minimized by updating the free parameters of the control law, FOR COMMAND GUIDANCE while satisfying a set of constraints on the design loads, responses G. MCCONNELL (Short Brothers, PLC, London, England) and G. and stability margins. Analytical expressions for gradients of the W. IRWIN (Belfast, Queen’s University, Northern Ireland) IN: cost function and the constraints, with respect to the control law International Conference on Control 88, Oxford, England, Apr. design variables are used to facilitate rapid numerical convergence. 13-15, 1988, Proceedings. London, Institution of Electrical These gradients can also be used for sensitivity study. A stable Engineers, 1988, p. 713-718. refs classical control law as well as an estimator-based full or reduced This paper describes a design of a bank-to-turn autopilot for order control law can be modified, in order to meet individual command guidance. A multivariable approach was used, which root-mean-square response limitations as well as minimum singular assumes that the roll rate is a constant at each design point and value restrictions. Both analog and digital control laws can be determines a steady-state control law for this fixed value. The full optimized. Low order, robust control laws were synthesized for autopilot controller is then implemented by scheduling the resulting flutter suppression of a flexible aircraft. Author steady-state controllers. The results demonstrate an improvement in performance by the gain scheduled controllers. Two multivariable A8935286 design methodologies, namely, the frequency domain characteris- VARIABLE STRUCTURE CONTROL LAWS FOR AIRCRAFT tics locus method and the time domain linear quadratic optimal MANOEUVRES control method, are described. IS. S. K. MUDGE and R. J. PATTON (York, University, England) IN: International Conference on Control 88, Oxford, England, Apr. A89-35302 13-15, 1988, Proceedings. London, Institution of Electrical IMPLEMENTATION OF A TRANSPUTER-BASED FLIGHT Engineers, 1988, p. 564-568. refs CONTROLLER The design procedure for a variable structure control system P. J. FLEMING, D. F. GARCIA NOCETTI, and H. A. THOMPSON (VSCS) for aircraft maneuvers is formulated, and the technique is (North Wales, University College, Bangor, Wales) IN: International illustrated using a pitch-pointing/vertical translation maneuver Conference on Control 88, Oxford, England, Apr. 13-15, 1988, developed for a combat aircraft by Sobel and Shapiro (1985) and Proceedings. London, Institution of Electrical Engineers, 1988, p. Andry et al. (1983). The performance of the VSCS controller is 719-724. Research supported by the Royal Aircraft assessed using a fully nonlinear simulation which incorporates wind Establishment. turbulence in the form of a Dryden spectrum. The performance of This paper describes the software and hardware aspects of a the VSCS is compared with that of the purely linear control used pilot study carried out with the goal of mapping an existing aircraft to define the model dynamics. I.S. flight control law for the Versatile Autopilot (VAP) onto a parallel processing system. The potential of the INMOS transputer and its A89-35297 associated programming language OCCAM for the implementation DESIGN OF ROBUST MULTIVARIABLE HELICOPTER of this control law was investigated. The paper describes methods cotifioi LAWS-FOR HANDLING QUALITIES used to generate the concurrent realization of the height-hold mode, ENHANCEMENT the most complex mode operated by the VAP control law, using A. YUE (Oxford University, England) IN: International Conference two alternative approaches, parallel branches and heuristic. The
482 08 AIRCRAFT STABILITY AND CONTROL adaptability and extendability of both approaches, as well as the blade torsional flexibility, unsteady aero-dynamics, forward flight, execution speed and the ease of programming, are evaluated. periodic terms, and trim solution is shown. The model is then IS. used with linear optimal control theory to investigate the influence of these effects on the closed loop damping. In the second study, N89-20147 Virginia Polytechnic Inst. and State Univ., the feasibility of designing simple implemetable controllers to Blacksburg. suppress air resonance throughout a wide range of operating ROBUST STABILIZATION OF LINEAR TIME-INVARIANT conditions is demonstrated. The control design method is also UNCERTAIN SYSTEMS VIA LYAPUNOV THEORY Ph.D. Thesis applied to a different configuration experiencing a fuselage induced CHIEN-HSIANG CHAO 1988 114 P flap-lag instability. Dissert. Abstr. Avail: Univ. Microfilms Order No. DA8817401 The problem of synthesizing a robust stabilizing feedback N89-20150 Massachusetts Inst. of Tech., Cambridge. controller for linear time-invariant systems with constant ON-BOARD AUTOMATIC AID AND ADVISORY FOR PILOTS uncertainties that are not required to satisfy matching conditions OF CONTROL-IMPAIRED AIRCRAFT Ph.D. Thesis is considered. Only the bounds on the uncertainties are required ELAINE ANN WAGNER 1988 261 p and no statistical property of the uncertainties is assumed. The Avail: Univ. Microfilms Order No. DA8821885 systems under consideration are described by linear state equations The consideration of the problem of aircraft control failures with uncertainties. Lyapunov theory is exploited to establish the from a broader, more meaningful viewpoint than with control loop conditions for stabilizability of the ciosea ioop system. Linear reconfiguration or redesign is presented. The additional controller design is also investigated. Under the same assumptions considerations involved in making full recoveries from control for the existence of a stabilizing discontinuous controller, it is failures are first categorized. Performance and operating constraints shown that a linear robust stabilizing controller always exists. Three that are best taken into account explicitly are presented, and there examples are included to illustrate the design procedures for robust is a discussion of the sometimes very important role of explicit controllers. Dissert. Abstr. post-failure retrim of the aircraft. Because it can be expected that pilots, if unaided, may continue often to be unable to recover N89-20148 Purdue Univ., West Lafayette, IN. aircraft after control failure, these considerations were cast in the MODAL COST ANALYSIS OF FLEXIBLE STRUCTURES form of knowledge and capabilities that an automatic aid and MODELING FLEXIBLE STRUCTURES FOR CONTROL DESIGN pilot advisory system should have. Because automatic emergency Ph.D. Thesis control is seen to be a very significant part of the proposed system, ANREN HU 1987 200 p a rule-based expert-type system to find a successful control strategy Avail: Univ. Microfilms Order No. DA8814487 was developed for elevator failures on the C-130. This system The integration issues of structural modeling and control design directs pre-simulation of the control strategy, changing it on the for large flexible structures are very important for developing sound basis of empirical guidelines concerning simple, objective features models in a closed loop environment. Consideration of these issues of the aircraft response to the strategy. The advisory function of leads one to conclude that the modeling problem and control the recovery-aiding system is also described. The issues of pilot problem are not independent. The connection between these two interface are discussed, as well as what to calculate to support problems must be understood to develop reliable control algorithms the advisory during various flight phases. Dissert. Abstr. and reduce the cost of extensive laboratory and flight testing. It is this input-output type phenomenon which must be reflected in N89-20998 Purdue Univ., West Lafayette, IN. structural modeling. The modal costs represent the contribution of ACTUATION CONSTRAINTS IN MULTIVARIABLE FLIGHT a vibration mode in the system response for given input and output CONTROL SYSTEMS Ph.D. Thesis locations. A complete modal cost analysis is provided for certain MARK RONALD ANDERSON 1988 202 p distributed parameter systems and shows that structural modeling Avail: Univ. Microfilm Oder No. DA8825502 and model reduction methods should be influenced by the specific This research deals with stability and performance robustness control objectives. The analysis proceeds via the following steps: of non-linear multivariable feedback control systems. The systems Convergence properties of modal costs are discussed for vibration considered include linear as well as non-linear idealizations, where of various simple continua. Open loop model cost analysis is applied non-linear models are used to represent practical limitations to finite element models of beam-like structures. Finite element (limiting) in the physical devices. A robustness analysis models are used to develop Linear Quadratic Gaussian control methodology, intended for use early in the control-law synthesis, laws while exact models are used to evaluate performance of is developed to evaluate stability and performance with respect to the resulting closed loop systems. A comprehensive modal cost control surface deflection and rate limits specifically. The analysis is presented for simple continua and discusses its methodology consists of three steps. First, a linear actuator signal implications in subsequent control system design. Dissert. Abstr. approximation is chosen based on a priori bounds, developed herein, between the time response of the linear signal N89-20149 California Univ., Los Angeles. approximation and the actual actuator signal. Second, the peak ACTIVE CONTROL HELICOPTER AEROMECHANICAL AND magnitude of the linear signal approximation is used to define a AEROELASTIC INSTABILITIES Ph.D. Thesis quasi-linear representation of the deflection and rate limit saturation MARC D. TAKAHASHI 1988 367 p elements using either describing function or sector methods. Third, Avail: Univ. Microfilms Order No. DA8822168 stability and performance robustness with respect to the The active control of three helicopter rotor instabilities is quasi-linear saturation models may then be evaluated using investigated using a coupled rotor/fuselage helicopter analysis. matrix-singular-value or eigenvalue techniques. The analysis The mathematical model is derived to capture air resonance and methodology is used to evaluate the stability robustness of two includes important features such as blade torsional flexibility, high-authority, multivariable flight control laws for two different pilot unsteady aerodynamics, and forward flight, which are effects that stick force inputs to a generic foward-swept-wing aircraft. were ignored in the few previous studies on air resonance control. Dissert. Abstr. Because of these modeling features, two other aeroelastic instabilities can also be simulated with the model and a brief N89-20999'# Systems Technology, Inc., Hawthorne, CA. investigation into the active control of these instabilities is made. TAILLESS AIRCRAFT PERFORMANCE IMPROVEMENTS WITH The first of these is a flap-lag-torsion instability inforward flight RELAXED STATIC STABILITY and the second is a flap-lag instability that is induced by the IRVING L. ASHKENAS and DAVID H. KLYDE Mar. 1989 presence of the fuselage degrees of freedom. A realistic helicopter 145 p configuration experiencing an air resonance instability is then (Contract NASl -18524) selected and it is used in two active control studies. In the first (NASA-CR-181806; NAS 1.26:181806; STI-TR-1252-1) Avail: Study, open loop damping data is presented and the effect Of NTlS HC A07/MF A01 CSCL 01C
483 08 AIRCRAFT STABILITY AND CONTROL
The purpose is to determine the tailless aircraft performance altitude. The controllers and prefilters are transformed to the z improvements gained from relaxed static stability, to quantify this plane for simulation purposes. The design is simulated with healthy potential in terms of range-payload improvements, and to identify plant and 24 combinations of surface failures. GRA other possible operational and handling benefits or problems. Two configurations were chosen for the study: a modern high aspect ratio, short-chord wing proposed as a high-altitude long endurance (HALE) remotely piloted vehicle; a wider, lower aspect ratio, high volume wing suitable for internal stowage of all fuel and payload 09 required for a manned long-range reconnaissance mission. Flying at best cruise altitude, both unstable configurations were found to RESEARCH AND SUPPORT FACILITIES (AIR) have a 14 percent improvement in range and a 7 to 9 percent improvement in maximum endurance compared to the stable configurations. The unstable manned configuration also shows a Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tube facilities; and engine test 15 percent improvement in the 50 ft takeoff obstacle distance and an improved height response to elevator control. However, it blocks. is generally more deficient in control power due to its larger adverse aileron yaw and its higher takeoff and landing lift coefficient C(sub L), both due to the downward trimmed (vs. upward trimmed for A89-33384*# National Aeronautics and Space Administration. stable configurations) trailing edge surfaces. Author Langley Research Center, Hampton, VA. ANALYSIS OF THE DEDICATED LASER VELOCIMETER SYSTEMS AT NASA - LANGLEY RESEARCH CENTER N89-21000# Air Force Inst. of Tech., Wright-Patterson AFB, JAMES F. MEYERS (NASA, Langley Research Center, Hampton, OH. School of Engineering. VA) IN: International Symposium on Applications of Laser FLIGHT CONTROLLER DESIGN WITH NONLINEAR Anemometry to Fluid Mechanics, 4th, Lisbon, Portugal, July 11-14, AERODYNAMICS, LARGE PARAMETER UNCERTAINTY AND 1988, Proceedings. Lisbon, lnstituto Superior Tecnico, 1988, p. PILOT COMPENSATION M.S. Thesis 4.12 (10 p.). refs THOMAS J. KOBYLARZ Dec. 1988 115 p Three representative laser velocimeter systems used at NASA (AD-A202727; AFIT/GE/ENG/88D-19) Avail: NTlS HC AOG/MF - Langley Research Center are described and analyzed. They range A01 CSCLOlD from a small orthogonal three component system used for detailed Nonlinear Quantitative Feedback Theory (QFT), developed by aerodynamic investigations to a large two component system used Dr. Isaac Horowitz, is used to design a flight control system for for investigations of complicated helicopter rotor flow fields. The the YF-16 aircraft. Upon completing this stability augmentation components used in each system are described and analyzed for system (SAS) additional compensation is added to reduce pilot their contributions to the measurement uncertainty. Example flow workload while improving handling qualities. The YF-16 uncertain field measurements are presented to illustrate the capabilities of plant is simulated with C (a blend of normal acceleration at pilot station and pitch rate) as the controlled output. The simulation these systems. Author includes the full six degree of freedom nonlinear dynamic equations of motion and aerodynamic data throughout the entire subsonic A89-33568 flight envelope. A technique is presented which enables the DESIGN ASPECTS OF A NAVAL RPV RECOVERY SYSTEM uncertain nonlinear YF-16 to be represented as a set of linear D. R. TAYLOR (GEC Avionics, Ltd., Rochester, England) IN: timer invariant plants which is equivalent to the nonlinear plant Remotely piloted vehicles; International Conference, 7th, Bristol, with respect to the set of acceptable outputs. Once this set of England, Sept. 12-14, 1988, Proceedings. Bristol, England, plants is obtained, a linear OFT controller is synthesized yielding University of Bristol, 1988, p. 25.1-25.15. fixed compensation which is extremely insensitive to varying flight The full potential of RPVs in naval operations cannot be realized conditions. Simulations in the time and frequency domains until the performance advantages of fixed-wing air vehicles are demonstrate that the desired performance is attained. Further work combined with a reliable recovery system that can be accomodated with real-time man-in-the-loop simulations should be accomplished by vessels no larger than frigates. Attention is presently given to to expand the area of pilot compensation. GRA the guidance-, capture-, retardation-, and restraint-phase problems of returning RPV shipboard recovery, given the ship environment’s N89-21001# Air Force Inst. of Tech., Wright-Patterson AFB. hydrodynamic motions, aerodynamic turbulence, and restricted OH. School of Engineering. space. Net and hook-and-wire methods are examined, and a A DIGITAL RATE CONTROLLER FOR THE CONTROL version of the latter which employs a long, overboard-extending RECONFIGURABLE COMBAT AIRCRAFT DESIGNED USING boom for parachute-decelerated RPV recovery is proposed. O.C. QUANTITATIVE FEEDBACK THEORY M.S. Thesis KURT NYLE NEUMANN Dec. 1988 149 p (AD-A203050; AFIT/GE/ENG/88D-33) Avail: NTlS HC A07/MF A89-33569 A01 CSCL01D LAUNCH, RECOVERY AND HANDLING SYSTEMS FOR The objective of this thesis is to develop a digital controller VERTICAL TAKE-OFF AND LANDING UAVS OPERATING using Quantitative Feedback Theory for a fighter aircraft with FROM SMALL SHIPS unstable, nonminimum phase dynamics that meets performance JAY J. DOYLE (Indal Technologies, Inc., Mississauga, Canada) specifications despite surface failures. Aircraft design trends for IN: Remotely piloted vehicles; International Conference, 7th, Bristol, highly maneuverable fighter aircraft are relaxing stability England, Sept. 12-14, 1988, Supplementary Papers. Bristol, requirements in order to increase performance in the transonic England, University of Bristol, 1988, p. 6.1-6.7. refs and supersonic regions. However, as a result, the aircraft is Launch and recovery systems are proposed for shipboard statically unstable in the subsonic region which makes the flight operations of naval reconnaissance VTOL unmanned air vehicles, control system critical to flight safety. The conventional approach such as the CL-227 Sea Sentinel, in the case of ships as small to the flight safety problem is to provide multiple redundancy as 4000-ton destroyers. These Operations must remain possible throughout the fight control system. However, QFT provides an at sea state 5, which in the destroyer’s case can generate rolling alternative to excessive hardware. The three controlled states are motions of up to +/- 25 deg. The system presently defined the pitch, roll, and yaw rates. A weighting matrix is derived which furnishes complete postlanding Security of the CL-227 during deck linearly combines the nine control surfaces into three control inputs. rolling motions as great as 31 deg. Self-activating probes The plant is converted to a certain plane using the Hoffman incorporated into each of the landing gear legs of the CL-227 algorithm. Three constant gain controllers and three prefilters are release spring-loaded fingers that open under the landing grid to designed for a single flight condition of 0.9 Mach and 30000 ft prevent upward or lateral motion. O.C. 09 RESEARCH AND SUPPORT FACILITIES (AIR)
A8933575 A89-33802 INTEGRATED MODULAR RPV GROUND STATION WITH FULL-SCALE FATIGUE TESTING OF AIRCRAFT STRUCTURES P. ~REFERENCE TO~ ~ THE 'RAVEN' PROJECT R. EDWARDS (PP Data, Ltd., England) IN: Full-scale fatigue R. WlLLlS and S. M. HUDSON (Flight Refuelling, Ltd., Wimborne, testing of components and structures. London and Stoneham, MA, England) IN: Remotely piloted vehicles; International Conference, Buttenvorths, 1988, p. 16-43. refs 7th, Bristol, England, Sept. 12-14, 1988, Supplementary Papers. The history of full-scale fatigue testing of aircraft structures is Bristol, England, University of Bristol, 1988, p. 24.1 -24.1 1. Research reviewed, and the design philosophy and justification of such testing supported by the Ministry of Defence Procurement Executive. are discussed. A detailed case study is given for the fatigue testing The performance requirements, development history, design of the Concorde. It is concluded that it is possible to justify full-scale features, and accomplishments to date of the RPV flight control testing of aircraft structures on the basis of safety or economics, ground station initially developed for the XRAE1, XRAE2, and whether or not such tests are required for certification. For small Raven RPVs. The beyond-visual-rangeflight requirement for the military aircraft the safety case is particularly strong because of controller led to the use of a radar-tracking system in conjunction the difficulty in making designs fail-safe. The case study with a ground station desktop computer for outer-loop control. An demonstrates that intelligently conducted tests can help in greatly MVME 110 single-board computer was chosen as the basis of extending the life of a fleet. C.D. the dedicated system due to its flexibility, availability, and large capacity for future development. O.C. A89-33803 FATIGUE EVALUATION OF HELICOPTER ROTOR HEADS R. L. C. GREAVES (Westland Helicopters, Ltd., Yeovil, England) A8933630# IN: Full-scale fatigue testing of components and structures. London HIGH ENTHALPY TESTING IN HYPERSONIC SHOCK and Stoneham, MA, Butterworths, 1988, p. 77-97. TUNNELS Methods of testing and evaluating the life of specific types of E. ESSER, H. GROENIG, and H. OLlVlER (Aachen, helicopter rotor heads are described. The nature of the loads on Rheinisch-WestfaelischeTechnische Hochschule, Federal Republic a rotor and the types of rotors considered are reviewed, and the of Germany) University of Texas, U.S. Air Force Academy, and flight measurement and analysis of the loads are addressed. The GAMNI-SMAI, Joint Europe/U.S. Short Course in Hypersonics, 2nd, derivation of test loads is summarized, and fatigue test programs U.S. Air Force Academy, Colorado Springs, CO, Jan. 16-20, 1989, are discussed. The development of a universal rotor head test Paper. 93 p. refs facility is described. C.D. High-enthalpy hypersonic ground test facilities, such as shock tunnels, free piston shock tunnels, and gun tunnels are described. The performance of the Aachen tunnel is addressed with attention A89-33804 given to some shock tube data for equilibrium air. Simulation of FATIGUE TESTING OF GAS TURBINE COMPONENTS flight conditions in shock tunnels is detailed. K.K. G. ASQUITH and A. C. PICKARD (Rolls-Royce, PLC, Derby, Eng!snd! IN: Full-scale fatigue testing of components and structures. London and Stoneham, MA, Buttenvorths, 1988, p. A89-33760# 210-234. refs NEW STATIC ENGINE NOISE TEST TECHNIQUES WHICH Aspects of the fatigue testing of gas turbine components are REDUCE TEST TIME SIGNIFICANTLY discussed. Component life prediction and design requirements are Y. ATVARS and D. M. LANE (Boeing Commercial Airplanes, Seattle, summarized, and the determination of safe predicted total life and WA) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, of safe crack propagation life are examined in detail, The full-scale Apr. 10-12, 1989. 15 p. refs component testing of gas turbine components is addressed. It is (AIAA PAPER 89-1127) shown that a large number of variables can affect the lives of This paper examines the applicability of static-noise gas turbine components, and that full-scale component testing ~~.t?-?~~>icitir\nmethnric that can sinnificnntly rndiica total test nffnrr; a means of ensurina that the most sianificant of these are time, compared to current industry practices, without compromising taken into account in the procedure for safe-life estimation. C.D. data quantity or quality. Two methods are considered in which noise levels are recorded continuously as the engine power is A89-34890# advanced either smoothly or in steps through the operational power RESULTS FROM LASER SHEET VISUALIZATION OF A range, unlike in the common approach, where the engine power PERIODIC ROTOR WAKE setting is arbitrarily stabilized for two minutes or more prior to A. BRAND, N. KOMERATH, and H. MCMAHON (Georgia Institute steady-state noise recording. Test results are presented on engines of Technology, Atlanta) Journal of Aircraft (ISSN 0021-8669), from three different engine manufacturers and test facilities, in vol. 26, May 1989, p. 438-443. Previously cited in issue 07, p. which the method of smooth continuous acceleration was used. 955, Accession no. A88-22140. refs The method in which the engine power is advanced in steps was (Contract DAAG29-82-K-0084) also tried and was found to be very effective. Both methods reduce test time significantly and yield excellent quality data. IS. A89-35217# WALL-INTERFERENCE CORRECTIONS FOR PARACHUTES IN A8933801 A CLOSED WIND TUNNEL FULL-SCALE FATIGUE TESTING OF COMPONENTS AND J. MICHAEL MACHA and ROBERT J. BUFFINGTON (Sandia STRUCTURES National Laboratories, Albuquerque, NM) IN: AIAA Aerodynamic KENNETH JAMES MARSH, ED. (National Engineering Laboratory, Decelerator Systems Technology Conference, 1Oth, Cocoa Beach, East Kilbride, Scotland) London and Stoneham, MA, Butterworths, FL, Apr. 18-20, 1989, Technical Papers. Washington, DC, American 1988, 344 p. For individual items see A89-33802 to A89-33804. Institute of Aeronautics and Astronautics, 1989, p. 97-103. refs The development and practice of full-scale fatigue testing in (Contract DE-AC04-76DP-00789) industrial design and development are discussed. The industries (AIAA PAPER 89-0900) involved in aircraft structures, automotive components and systems, An extensive test program was conducted to gather information railway components, helicopter rotor heads, artillery gun structures, on wall-interference effects for parachutes in closed wind tunnels. offshore structures and components, bridge components, military Drag area and base pressure measurements were made for a set bridges, nuclear engineering, gas turbine components, mobile crane of ribbon parachutes of 7, 15, and 30 percent geometric porosity components and structures, ropes, and general mechanical in six different wind tunnels, covering a geometric blockages from engineering components are considered. The service operating 2-35 percent. The resulting data have been used to formulate environment, the design and operation of the Strongfloor Structural and validate approximate blockage correction equations based on Testing Laboratory at NEL are also addressed. C.D. the theory of Maskell (1963). The corrections are applicable to
485 09 RESEARCH AND SUPPORT FACILITIES (AIR) single parachutes and clusters of two and three parachutes. N89-21002'# National Aeronautics and Space Administration. Author Lewis Research Center, Cleveland, OH. FLOWFIELD MEASUREMENTS IN THE NASA LEWIS RESEARCH CENTER 9- BY 15-FOOT LOW-SPEED WIND National Aeronautics and Space Administration. TUNNEL N8920955'# CHRISTOPHER E. HUGHES Mar. 1989 78 p Langley Research Center, Hampton, VA. (NASA-TM-100883; E-4116; NAS 1.15:100883) Avail: NTlS HC TEST TECHNIQUES: A SURVEY PAPER ON CRYOGENIC A05/MF A01 CSCL 148 TUNNELS, ADAPTIVE WALL TEST SECTIONS, AND An experimental investigation was conducted in the NASA MAGNETIC SUSPENSION AND BALANCE SYSTEMS Lewis 9- by 15-Foot Low-Speed Wind Tunnel to determine the ROBERT A. KILGORE, DAVID A. DRESS, STEPHEN W. D. WOLF, flow characteristics in the test section during wind tunnel operation. and COLIN P. BRITCHER (Old Dominion Univ., Norfolk, VA.) lfl In the investigation, a 20-probe horizontally-mounted Pitot-static its Transonic Symposium: Theory, Application, and Experiment, flow survey rake was used to obtain cross-sectional total and Mar. 1989 Volume 1, Part 2 p 705-740 static pressure surveys at four axial locations in the test section. CSCL 148 Avail: NTlS HC A22/MF A01 At each axial location, the cross-sectional flowfield surveys were The ability to get good experimental data in wind tunnels is made by repositioning the Pitot-static flow survey rake vertically. often compromised by things seemingly beyond our control. In addition, a calibration of the new wind tunnel rake Inadequate Reynolds number, wall interference, and support instrumentation, used to determine the wind tunnel operating interference are three of the major problems in wind tunnel testing. conditions, was performed. Boundary laser surveys were made at Techniques for solving these problems are available. Cryogenic three axial locations in the test section. The investigation was wind tunnels solve the problem of low Reynolds number. Adaptive conducted at tunnel Mach numbers 0.20, 0.15, 0.10, and 0.05. wall test sections can go a long way toward eliminating wall The test section profile results from the investigation indicate that interference. A magnetic suspension and balance system (MSBS) fairly uniform total pressure profiles (outside the test section completely eliminates support interference. Cryogenic tunnels, boundary layer) and fairly uniform static pressure and Mach number adaptive wall test sections, and MSBS are surveyed. A brief profiles (away from the test section walls and downstream of the historical overview is given and the present state of development and application in each area is described. Author test section entrance) exist throughout in the wind tunnel test section. Author
N89-21003# Systems Control Technology, Inc., Arlington, VA. N89-20957*# National Aeronautics and Space Administration. HELIPORT SYSTEM PLANNING GUIDELINES Langley Research Center, Hampton, VA. DEBORAH PEISEN Apr. 1988 113 p INSTRUMENTATION ADVANCES FOR TRANSONIC TESTING (Contract DTFAOl-87-C-00014) PERCY J. BOBBITT ln its Transonic Symposium: Theory, (AD-A199081; DOT/FAA/PM-87/33; DOT/FAA/PP-88/3) Avail: Application, and Experiment, Volume 1. Part 2 p 765-816 Mar. NTlS HC AO6/MF A01 CSCL 01E 1989 State and city governments generally realize that continued Avail: NTlS HC A22/MF A01 CSCL 148 vitality depends on a steady expansion of industry and services New and improved instrumentation, like new and improved wind as a function of planned growth. The helicopter is a proven catalyst tunnels, provide capabilities which stimulate innovative research for enhancement of those desired growth patterns. However, and discovery. During the past few years there have been a number without the necessary support infrastructure, this positive of instrumentation developments which have aided and abetted contribution of the helicopter cannot be realized. Determining the the acquisition of more accurate aerodynamic data and have led need for such a support system can be achieved through an to new physical insights as well. Some of these advances are understanding of local helicopter activities and the metropolitan reviewed, particularly in the area of thin film gages, hot wire or state-wide socioeconomic dynamics in which they occur. This anemometry, and laser instrumentation. A description is given of allows for data base development, including a fleet inventory, and the instruments and/or techniques and some sample results are analysis to provide a foundation for determining current, and shown. Author forecasting future, helicopter activity and support facility requirements. Heliport planning is a relatively new field. Previous efforts, although based on proven fixed-wing airport methods, have N89-20961'# National Aeronautics and Space Administration. produced a series of uncoordinated and nonstandardized products Langley Research Center, Hampton, VA. from many various individual planners and organizations. CAPABILITIES OF WIND TUNNELS WITH TWO-ADAPTIVE Consequently, the data collected and the analytical processes used WALLS TO MINIMIZE BOUNDARY INTERFERENCE IN 3-D have not been consistent or directly comparable. Fundamental MODEL TESTING planning criteria by which urban area heliport requirements may RAINER REBSTOCK and EDWIN E. LEE, JR. ln its Transonic be assessed at any jurisdictional level are given Author Symposium: Theory, Application, and Experiment, Volume 1, Part 2 p 891-910 Mar. 1989 Sponsored in part by National Research N8921004*# Vigyan Research Associates, Inc., Hampton, VA. Council PERFORMANCE OF THE ACTIVE SIDEWALL Avail: NTlS HC A22/MF A01 CSCL 148 BOUNDARY-LAYER REMOVAL SYSTEM FOR THE LANGLEY An initial wind tunnel test was made to validate a new wall 0.3-METER TRANSONIC CRYOGENIC TUNNEL adaptation method for 3-D models in test sections with two adaptive S. BALAKRISHNA, W. ALLEN KILGORE, and A. V. MURTHY Feb. walls. First part of the adaptation strategy is an on-line assessment 1989 26 p of wall interference at the model position. The wall induced (Contract NAS1-17919) blockage was very small at all test conditions. Lift interference (NASA-CR-181793; NAS 1.26181793) Avail: NTlS HC AO3/MF occurred at higher angles of attack with the walls set A01 CSCL14B aerodynamically straight. The adaptation of the top and bottom A performance evaluation of an active sidewall boundary-layer tunnel walls is aimed at achieving a correctable flow condition. removal system for the Langley 0.3-m Transonic Cryogenic Tunnel The blockage was virtually zero throughout the wing planform after (TCT) was evaluated in 1988. This system uses a compressor the wall adjustment. The lift curve measured with the walls adapted and two throttling digital valves to control the boundary-layer mass agreed very well with interferencefree data for Mach 0.7, regardless flow removal from the tunnel. The compressor operates near the of the vertical position of the wing in the test section. The 2-D maximum pressure ratio for all conditions. The system uses a wall adaptation can significantly improve the correctability of 3-D surge prevention and flow recirculation scheme. A microprocessor model data. Nevertheless, residual spanwise variations of wall based controller is used to provide the necessary mass flow and interference are inevitable. Author compressor pressure ratio control. Initial tests on the system
486 11 CHEMISTRY AND MATERIALS
indicated problems in realizing smooth mass flow control while modification of the P/M IN792 alloy, designated APK-6, which in running the compressor at high speed and high pressure ratios. addition to exhibiting creep rupture strength levels superior to cast An alternate method has been conceived to realize boundary-layer IN792 at 650-750 C possesses the fatigue resistance of IN738LC mass flow control which avoids the recirculation of the compressor at 600 C. This level of fatigue resistance is comparable to that of mass flow and operation near the compressor surge point. This Nimonic 90. Two preferred compaction routes have been defined scheme is based on varying the speed of the compressor for a for the new alloy: HIP at 1160 C, followed by 1100 C extrusion, sufficient pressure ratio to provide needed mass flow removal. and direct extrusion of the loose powder at 1120 C. The system has a mass flow removal capability of about 10 percent Directionally-recrystallizedAPK-6 yields a stress-rupture strength of test section flow at M = 0.3 and 4 percent at M = 0.8. The comparable to that of dispersion-strengthened Mar.M.002, for system performance has been evaluated in the form of the service lives of about 1000 hr at 980 C. O.C. compressor map, and compressor tunnel interface characteristics covering most of the 0.3-m TCT operational envelope. Author A89-33456 ADVANCED MICROSTRUCTURALOBSERVATIONSOFGAS N89-21005# Naval Civil Engineering Lab., Port Hueneme, CA. TURBINE P/M MATERIALS EXPERIMENTAL EXAMINATION OF THE AEROTHERMAL M. JEANDIN, J. D. BARTOUT, and F. GRILLON (Paris, Ecole PERFORMANCE OF THE T-10 TEST CELL AT NAS (NAVAL Nationale Superieure des Mines, Evry, France) IN: International AIR STATION), CUB1 POINT Report, Oct. 1986 - Sep. 1987 Conference on PM Aerospace Materials, Lucerne, Switzerland, Nov. C. A. KODRES, E. E. COOPER, and P. L. STONE Sep. 1988 2-4, 1987, Proceedings. Shrewsbury, England, MPR Publishing 140 p Services, Ltd., 1988, p. 6.1-6.13. refs (AD-A203887; NCEL-TN-1788) Avail: NTlS HC A07/MF A01 In situ SEM observations at temperatures of up to 1500 C CSCL 148 have been performed on high-performance P/M alloys, in This report presents results of aerodynamic and thermodynamic conjunction with TEM, in order to investigate such thermally- tests conducted on the first standard Navy air-cooled T-10 test activated phenomena as: (1) the densification kinetics and cell. Objectives of the tests were to: (1) Determine if aerodynamic microstructural modification of particles during the sintering of and thermodynamic design objectives for the standard T-10 test Ni-base superalloy powders; (2) the location, size and shape of cells were met; (2) Obtain data for comparing analytical predictions recrystallized zones and the kinetics of recrystallization for Ni-base and validating analytical modeling techniques, and (3) Obtain superalloys; and (3) the thermomechanical behavior of thermal baseline data of cell performance for use in case of future changes barrier coatings deposited on a Ni-base superalloy and their in design or operations. GRA microstructural features’ evolution vs time and temperature. The principal sources of instrumentation errors were the need to operate under vacuum and to use thermal etching. A laser-heating system 11 is recommended for future investigations. O.C. A89-33463 CHEMISTRY AND MATERIALS ‘ SPRAY FORMED WASPALOY FOR DISC FORGINGS H. PUSCHNIK, H. JAEGER, and F. HEINEMANN (Vereinigte Includes chemistry and materials (general); composite materials; Edelstahlwerke AG, Kapfenberg, Austria) IN: International inorganic and physical chemistry; metallic materials; nonmetallic Conference on PM Aerospace Materials, Lucerne, Switzerland, Nov. materials; and propellants and fuels. 2-4, 1987, Proceedings. Shrewsbury, England, MPR Publishing Services, Ltd., 1988, p. 14.1-14.7. refs In the ’Osprey’ spray-forming process, liquid metal is subjected A89-32948 to spray atomization by means of a high velocity inert gas jet and FIRE EXTINGUISHING AGENTS FOR OXYGEN-ENRICHED directed onto a circular plate. The disklike preform thus created ATMUSPHtHtS car1 ua dirwiiy iuryau iriiu a yas iuruiria uisi. Se~uiiuarypilase DENNIS M. ZALLEN and EDWARD T. MOREHOUSE, JR. (USAF, particles and nonmetallic inclusions are finely dispersed in a fashion Engineering and Services Center, Tyndall AFB, FL) IN: analogous to P/M materials; the preforms are also characterized Flammability and sensitivity of materials in oxygen-enriched by very low gas content. Tensile test results show the atmospheres; Proceedings of the Symposium, Cambridge, England, Osprey-produced disks to have, in addition to a tensile strength Apr. 6-8, 1987. Volume 3. Philadelphia, PA, American Society for that is competitive with P/M and forged disks, both suitably high Testing and Materials, 1988, p. 391-412. refs ductility and toughness values. O.C. Fire suppression agent requirements for extinguishing fires in oxygen-enriched atmospheres were determined by employing A8933465 small-, medium-, large-, and full-scale test apparatus. The small- TITANIUM PM AlTRlBUTES AND POTENTIAL FOR AIRCRAFT and medium-scale tests showed that a doubling of the oxygen ENGINE APPLICATIONS concentration required five times more Halon to be extinguished. G. E. WASIELEWSKI and A. M. JOHNSON (General Electric Co., This trend agrees with Halon’s chemical interference in the chain Aircraft Engine Business Group, Cincinnati, OH) IN: International reaction of the combustion process and the increase in the flame Conference on PM Aerospace Materials, Lucerne, Switzerland, Nov. radical pool caused by increased oxygen. For fires of similar size 2-4, 1987, Proceedings. Shrewsbury, England, MPR Publishing and intensity, the effect of oxygen enrichment of the cabin volume Services, Ltd., 1988, p. 18.1-18.12. refs in the HC-131A was not as great as in the smaller compartments The need of high-temperature, high-strength titanium alloys as of the 8-52, which presented a higher damage scenario. The lighter weight substitutes for nickel-base superalloys in aircraft full-scale tests showed that damage to the airframe was as engines has spurred interest in rapidly solidified (RS) titanium. important a factor in extinguishment as oxygen enrichment was. The limitations of titanium ingot metallurgy and the potential of Author RS metallurgy are described. A review of the major RS powder-making processes evaluates the resultant powder attributes A89-33454 and significance relative to aircraft engine applications. The features PM SUPERALLOY TURBINE BLADES of gas atomized and substrate quenched powder are described S. W. K. SHAW (Inco Engineered Products, Ltd., Birmingham, and the cooling rate effects analyzed. Consolidation methods aimed England) IN: International Conference on PM Aerospace Materials, at preserving the RS powder features are reviewed and examples Lucerne, Switzerland, Nov. 2-4, 1987, Proceedings. Shrewsbury. of properly improvements are shown. Concerns and sources for England, MPR Publishing Services, Ltd., 1988, p. 3.1-3.22. powder contamination and their potential effects on properties are A development history and performance capability evaluation given. Aircraft engine payoffs and the need for lower cost high are presented for a large, forged gas turbine blade based on a quality powder are discussed. Author
487 11 CHEMISTRY AND MATERIALS
A89-33474 which describes the process of benz(a)pyrene formation. It is RAPIDLY SOLIDIFIED ALUMINUM ALLOYS FOR HIGH shown, in particular, that the total content of benz(a)pyrene in the TEMPERATURE/HIGH STIFFNESS APPLICATIONS combustion products depends to a large degree on the efficiency PAUL S. GILMAN and SANTOSH K. DAS (Allied-Signal Metals of the afterburning process in the secondary zone of the Combustion and Ceramics Laboratory, Morristown, NJ) IN: International chamber. V.L. Conference on PM Aerospace Materials, Lucerne, Switzerland, Nov. 2-4, 1987, Proceedings. Shrewsbury, England, MPR Publishing A89-34120 Services, Ltd., 1988, p. 27.1-27.12. refs SOME CHARACTERISTICS OF THE FORMATION OF Rapid solidification and consolidation technologies have been CONTAMINANTS DURING THE COMBUSTION OF used to develop thermally stable intermetallic compounds in HYDROCARBON FUELS IN THE COMBUSTION CHAMBERS structural parts fabricated from quarternary, AI-Fe-V-Si alloys OF GAS TURBINE ENGINES [O NEKOTORYKH applicable to turbine engines, aircraft and missile structures, and OSOBENNOSTIAKH OBRAZOVANIIA ZAGRlAZNlAlUSHCHlKH similar elevated service temperature/corrosion resistance/elastic VESHCHESTV PRI SZHlGANll UGLEVODORODNYKHTOPLIV modulus-critical elements. The rapidly solidified alloys were V KAMERAKH SGORANllA GAZOTURBINNYKH DVIGATELEI] produced by planar flow casting of the melt, followed by V. P. SVINUKHOV Fizika Goreniia i Vzryva (ISSN 0430-6228). comminution of the ribbon thus obtained; they are characterized vol. 24, Nov.-Dec. 1988, p. 37-42. In Russian. refs by the high volume fractions of silicides dispersed in the AI matrix. High tensile moduli and excellent corrosion resistance are A8434121 obtained. O.C. A SIMPLE ONE-DIMENSIONAL MODEL FOR THE EFFECT OF AIR POLLUTION ON SUPERSONIC COMBUSTION [PROSTAIA A8433490 ODNOMERNAIA MODEL' VLllANllA ZAGRIAZNENNOSTI POTENTIAL APPLICATIONS FOR ADVANCED STRUCTURAL VOZDUKHA NA SVERKHZVUKOVOE GORENIIE] CERAMICS IN AERO GAS TURBINE ENGINES S. I. BARANOVSKII, A. S. NADVORSKII, and D. D. S. NEWSAM (Rolls-Royce, PLC, Derby, England) IN: International ROMASHKOVA Fizika Goreniia i Vzryva (ISSN 0430-6228), vol. Conference on PM Aerospace Materials, Lucerne, Switzerland, Nov. 24, Nov.-Dec. 1988, p. 42-51. In Russian. refs 2-4, 1987, Proceedings. Shrewsbury, England, MPR Publishing An attempt is made to develop a numerical model describing Services, Ltd., 1988, p. 43.1-43.18. refs the effect of the type of heating on the combustion of a hydrogen-air Structural engineering ceramics offer the promise of good high mixture in supersonic flow. It is shown, in particular that the temperature mechanical properties, combined with low density, enrichment of the mixture with oxygen is a necessary but not high temperature corrosion and oxidation resistance and in sufficient condition for the correct modeling of supersonic composite form a degree of toughness. This paper discusses the combustion using flame heating. Flame heating using a hydrocarbon potential applications of ceramics in aero gas turbines and the fuel is shown to be preferable to heating with a hydrogen fuel. engineering requirements which must be satisfied before the unique V.L. properties of this class of materials can be exploited and fully utilized in the gas turbine field. In addition the advantages and A89-34122 disadvantages of monolithic and reinforced ceramics are discussed EFFECT OF TURBULENCE ON THE COMBUSTION OF AN and potential systems and major problem areas highlighted. ATOMIZED LIQUID FUEL [VLIIANIE TURBULENTNOSTI NA Author GORENIE RASPYLENNOGO ZHIDKOGO TOPLIVA] V. R. KUZNETSOV Fizika Goreniia i Vzryva (ISSN 0430-6228), A8434080 vol. 24. Nov.-Dec. 1988, p. 51-57. In Russian. refs CERAMICS IN HIGH-TEMPERATUREGAS TURBINES The combustion of an atomized liquid fuel in turbulent flow is (REVIEW) [KERAMIKA V VYSOKOTEMPERATURNYKH GTU investigated analytically. First, the combustion of an individual fuel /OBZOR/ ] droplet completely entrained by the flow is analyzed with allowance 1.1. KIRILLOV, A. V. SUDAREV, and A. G. REZNIKOV (Leningradskii for the effects of evaporation processes and free convection. The Metallicheskii Zavod, VTUZ, Leningrad, USSR) Promyshlennaia combustion process typical of the idling mode of aviation gas Teplotekhnika (ISSN 0204-3602). vol. 10, no. 6, 1988, p. 67-87. turbine engines is then examined with emphasis on the effect of In Russian. refs the air excess ratio. It is shown, in particular, that as the air The possibilities afforded by the use of ceramic materials in excess ratio decreases from infinity to 1, the combustion efficiency gas turbines are examined. In particular, it is shown that high may change nonmonotonically. V.L. thermal efficiency can be achieved in high-temperature ceramic turbines as a result of the almost complete elimination of air cooling A89-34894# requirements. General principles for designing gas turbine FUEL HOLDUP AND COMPONENT DlFFUSlVlTY IN A COOLED components in ceramic materials are formulated. The CYLINDRICAL TANK design-related characteristics of ceramic components and the ERNST VON MEERWALL (Akron, University, OH), DALE possibilities of combining ceramic and metal components are SCHRUBEN (Texas A & M University, Kingsville), ANTHONY LEO, discussed. The current status of ceramic gas turbines and future RICK BRUNO, and JOHN JOSHUA Journal of Aircraft (ISSN prospects are briefly reviewed. V.L. 0021 -8669), vol. 26, May 1989. p. 465-469. The precipitation of solid waxes from aircraft jet fuels in A89-34119 cylindrical tanks (pod wing tanks) at the low temperatures CHARACTERISTICS OF THE FORMATION OF encountered in high-altitude flight has been experimentally BENZ(A)PYRENE IN THE COMBUSTION CHAMBERS OF modeled. The techniques used were a direct measurement of AVIATION GAS TURBINE ENGINES [OB OSOBENNOSTIAKH optical opacity and holdup in a simulated wing tank, ultrasound OBRAZOVANIIA BENZ/A/PIRENA V KAMERAKH SGORANllA imaging, and diffusion measurements based on nuclear magnetic AVIATSIONNYKH GTD] resonance. The work is intended to show the applicability of these IU. A. KNYSH, A. A. GORBATKO. A. V. IVLIEV, S. V. LUKACHEV, techniques to the study of holdup in realistic systems, and to and V. G. ROZNO Fizika Goreniia i Vzryva (ISSN 0430-6228), attempt qualitative correlation between their results. The vol. 24, Nov.-Dec. 1988, p. 33-37. In Russian. refs morphology of the fuel precipitate and its permeability to the liquid The carcinogenic properties of the combustion products of fuel component are found to depend on cooling rate as well as aviation fuels are largely determined by the presence of the on the final temperature. Author incompletely burned hydrocarbon or polynuclear compounds such as benz(a)pyrene. Here experimental data are presented on the A89-34933 formation of benz(a)pyrene in the combustion chambers of aviation EXPERIMENTAL INVESTIGATION OF THE THERMAL gas turbine engines, and a phenomenological scheme is proposed CONDUCTIVITY OF DISPERSED CERAMIC MATERIALS
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G. P. PETERSON and L. S. FLETCHER (Texas A & M University, using compact tension specimens were performed in order to study College Station) IN: Heat transfer in gas turbine engines and the effects of stress ratio and temperature on the near-threshold three-dimensional flows; Proceedings of the Symposium, ASME fatigue crack growth characteristics of Ti-8AI-1Mo-1 V. Crack closure Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New and the effective stress intensity range could account for the effects York, American Society of Mechanical Engineers, 1988, p. 77-84. of stress ratio at constant temperature. It is noted that crack Research supported by AGlE Corp. refs closure could not account for the effects of temperature at a Several analytical methods are presented by means of which fixed stress ratio cf 0.1. R.9. the effective thermal conductivities of prospective, extreme service-temperature gas turbine blade materials incorporating N89-20205'# Norfolk State Coll., VA. Dept. of Chemistry and ceramic dispersions can be ascertained. The character and results Physics. of an experimental investigationof the effective thermal conductivity A (13)C NMR ANALYSIS OF THE EFFECTS OF ELECTRON of four such materials are also presented; the materials are tungsten RADIATION ON GRAPHITE/POLYETHERIMIDE COMPOSITES carbide-cobalt, tungsten-copper, silicon nitride, and titanium Final Report diboride, and mean effective thermal conductivities and their MILTON W. FERGUSON 29 Mar. 1989 9 p temperature dependences are defined in light of 300-900 K (Contract NCCl-115) measurements. Analytical method results are compared with (NASA-CR-182818; NAS 1.26:182818) Avail: NTlS HC A02/MF experimental ones. O.C. A01 CSCL 11D Initial investigations have been made into ine use of high A89-35224# resolution nuclear magnetic resonance (NMR) for the NEW LIGHTWEIGHT PARACHUTE FABRICS OF KEVLAR characterization of radiation effects in graphite and Kevlar fibers, ARAMID FIBER polymers, and the fiberlrnatrix interface in graphite/polyetherimide STEVEN D. BEARE (Du Pont de Nemours and Co., Wilmington, composites. Sample preparation techniques were refined. Essential DE) IN: AlAA Aerodynamic Decelerator Systems Technology equipment has been procured. A new NMR probe was constructed Conference, 1Oth, Cocoa Beach, FL. Apr. 18-20, 1989, Technical to increase the proton signal-to-noise ratio. Problem areas have Papers. Washington, DC, American Institute of Aeronautics and been identified and plans developed to resolve them. Author Astronautics, 1989, p. 143-147. refs (AIM PAPER 89.0911) The 55-denier Kevlar fiber-based 'Style 172' parachute fabric, N89-20231# National Aerospace Lab., Amsterdam (Netherlands). which weighs 1.1 oz/sq yd, yields 3 times the strength of nylon Structures and Materials Div. at the same weight and has the additional advantage of being QUENCH SENSITIVITY OF AIRFRAME ALUMINUM ALLOYS nonmelting. The fabric's air permeability can be adjusted from 50 H. J. KOLKMAN, W. G. J. THART, and L. SCHRA 29 Jan. 1988 to 150 CFM/sq ft, depending on the application intended; attention 10 p Presented at the 8th International Conference on the is given to a primary ejection-system parachute application for Strength of Metals and Alloys, Tampere, Finland, 22-26 Aug. USAF and US Navy aircraft that will reduce the probability of 1988 death and injury in 'fireball' situations. Additional decelerator (NLR-MP-88003-U; ETN-89-94052) Avail: NTlS HC A02/MF applications under development for this fabric are weapons-delivery A0 1 systems and aerospace payload-recovery systems in which The quench sensitivity of six precipitation hardened aluminum strengthlweight values are critical. O.C. alloys for aerospace applications was investigated and explained by means of transmission electron microscopy. The quench A89-35235# sensitivity is mainly caused by the solute depletion associated A CRITICAL REVIEW OF THE STATE OF THE ART FOR with heterogeneous precipitation at dispersoids for low quench MEASUREMENT OF STRESS IN PARACHUTE FABRICS rates. ESA EUGENE E. NIEMI, JR. (Lowell, University, MA) IN: AlAA Aerodynamic Decelerator Systems Technology Conference, 1Oth, N89-21051*# National Aeronautics and Space Administration. Cocoa Beach, FL, Apr. 18-20, 1989, Technical Papers. Washington, Lewis Research Center, Cleveland, OH. DC, American Institute of Aeronautics and Astronautics, 1989, p. FUEL-RICH CATALYTIC COMBUSTION OF JET-A 211-221. refs FUEL-EQUIVALENCE RATIOS 5.0 TO 8.0 (AIAA PAPER 89-0925) THEODORE A. BRABBS and CARMEN M. GRACIA-SALCEDO This paper presents a summary of the state of the art for (Army Aviation Research and Development Command, Cleveland, measuring stresses in parachute fabrics. It reviews fabric properties OH.) May 1989 10 p Prepared for presentation at the and the relationships between stress and strain. The use of Central States Meeting of the Combustion Inst., Dearborn, MI, 30 pressure measurements together with a known canopy gore shape Apr. - 3 May 1989 to determine stresses is discussed. The most commonly used (NASA-TM-101975; E-4675; AVSCOM-TR-89-C-001; NAS stress measuring device, the Omega sensor, is reviewed in detail, 1.15:101975) Avail: NTlS HC AO2IMF A01 CSCL 218 and some problems associated with its use are explained. Other Fuel-rich catalytic combustion (E.R. greater than 5.0) is a types of Stress or strain measuring transducers that have been unique technique for preheating a hydrocarbonfuel to temperatures used with parachutes, or that show potential for use with much higher than those obtained by conventional heat exchangers. parachutes, are reviewed and principles of operation are explained. In addition to producing very reactive molecules, the process Recommendations are made for additional studies that should be upgrades the structure of the fuel by the formation of hydrogen conducted to obtain more information on parachute fabric and smaller hydrocarbons and produces a cleaner burning fuel by stresses. Author removing some of the fuel carbon from the soot formation chain. With fuel-rich catalytic combustion as the first stage of a two A89-35722 stage combustion system, enhanced fuel properties can be utilized THE EFFECT OF STRESS RATIO ON THE NEAR-THRESHOLD by both high speed engines, where time for ignition and complete FATIGUE CRACK GROWTH BEHAVIOR OF TIIAL-1MO-1V AT combustion is limited, and engines where emission of thermal NO ELEVATED TEMPERATURE sub x is critical. Two-stage combustion (rich-lean) has been shown G. C. SALIVAR, J. E. HEINE (Florida Atlantic University, Boca to be effective for NO sub x reduction in stationary burners where Raton), and F. K. HAAKE (United Technologies Corp.. Government residence times are long enough to burn-up the soot formed in Products Div., West Palm Beach, FL) Engineering Fracture the first stage. Such residence times are not available in aircraft Mechanics (ISSN 0013-7944), vol. 32, no. 5, 1989, p. 807-817. engines. Thus, the soot-free nature of the present process is critical Research supported by the United Technologies Corp. refs for high speed engines. The successful application of fuel-rich (Contract F33615-85-C-5050) catalytic combustion to Jet-A, a multicomponent fuel used in gas Computer-controlled decreasing stress intensity range tests turbine combustors, is discusssed. Author
489 11 CHEMISTRY AND MATERIALS
N89-21071# Princeton Univ., NJ. Dept. of Mechanical and resonance lines in jet fuels. The 2-D inadequate method was shown Aerospace Engineering. to be a particularly useful experiment for determining carbon-carbon FUELS COMBUSTION RESEARCH Final Technlcal Report, 1 connectivities. A combination of the heteronuclear correlation, Oct. 1985 - 30 Sep. 1988 J-coupled, and INADEQUATE 2-D experiments proved to be a IRVIN GLASSMAN, FREDERICK L. DRYER, and FORMAN A. very powerful combination of techniques for identifying all of the WILLIAMS 30 Nov. 1988 47 p major structural types of fragments in the JP-4, JP5, and MIG-25 (Contract F49620-86-C-0006) fuels. GRA (AD-A204161; AFOSR-89-0087TR) Avail: NTlS HC A03/MF A01 CSCL 21D Studies of near and slightly sooting inverse and normal co-flow diffusion flames determined aromatics as the key intermediates to soot formation. The extent of aromatic formation was correlated 12 with the earlier Princeton smoke height test results. The effect of oxygen addition to tightly bound fuels (ethene, ethyne and benzene) ENGINEERING in diffusion flames was found to accelerate the pyrolysis and thus the soothing tendency, but not to affect other fuels in the Includes engineering (general); communications; electronics and temperature range of soot formation. Flow reactor experiments electrical engineering; fluid mechanics and heat transfer; determined oxidation kinetic results for the mono and dialkylated instrumentation and photography; lasers and masers; mechanical aromatic components of jet fuels. Succinctly, it was found that engineering; quality assurance and reliability; and structural the alkyl chains are attached initially and in the case of dialkylated mechanics. compounds not simultaneously. Mechanisms have been presented. Results on boron slurry droplet combustion were obtained and provided a basis for calculating when droplet disruption would A89-33354# occur. Questions with respect to boron cloud combustion addressed THE INFLUENCE OF A RADIAL SWIRL GENERATOR ON THE mechanisms of ignition and combustion in the regime of chemical FLOW FIELD FROM A FUEL NOZZLE MODEL kinetic control. GRA CH. HASSA, E. BLUEMCKE, M. RACHNER, and H. EICKHOFF (DFVLR, lnstitut fuer Antriebstechnik, Cologne, Federal Republic N8921125# Detroit Diesel Allison. Indianapolis, IN. of Germany) IN: International Symposium on Applications of HIGH DENSITY FUEL EFFECTS Final Report, Sep. 1985 - Apr. Laser Anemometry to Fluid Mechanics, 4th. Lisbon, Portugal, July 1988 11-1 4, 1988, Proceedings. Lisbon, lnstituto Superior Tecnico, 1988, N. K. RIZK, V. L. OECHSIE, P. T. ROSS, and H. C. MONGIA 18 p. 4.1 (6 p.). Research supported by TECFIAM. refs Aug. 1988 174 p In the present investigation outlet velocity profiles of a radial (Contract F33615-86-C-2604) swirl generator in a fuel nozzle model have been measured. The (AD-A202426 DDA-EDR-13471; AFWAL-TR-88-2046) Avail: goal was to remove uncertainties concerning the prescription of NTIS HC AO8/MF A01 CSCL 210 inlet conditions for the numerical prediction of gas turbine The purpose of this program was to determine, by combustor combustor flows. It was found that the amount of swirl produced rig tests and data evaluation, the effects of the high density fuel from the generator was greater than expected from calculation properties on the performance and durability of the Allison T56-A-15 based on cascade theory. Two- and three-dimensional calculations combustion system. Four high density fuels in addition to baseline of the flow from the fuel nozzle model incorporating the measured JP4 were evaluated in the effort. The rig test program included: inlet velocity profiles are compared with measurements. Author nozzle flow bench testing, aerothermal performance and wall temperature, flame stability and ignition, injector coking and plugging, and flow transient effect. The data evaluation effort A893338 1# involved the utilization of empirical correlations in addition to COMPARISON OF LDA AND LTA APPLICATION FOR analytical multidimensional tools to analyze the performance of PROPELLER TESTS IN WIND TUNNELS the combustor. The modifications required to optimize the J. H. M. GOODEN and J. W. KOOl (Nationaal Lucht- en performance with high density fuels were suggested and the Ruimtevaartlaboratorium, Emmeloord, Netherlands) IN: expected improvement in performance was evaluated. GRA International Symposium on Applications of Laser Anemometry to Fluid Mechanics, 4th, Lisbon, Portugal, July 11-14, 1988, Proceedings. Lisbon, lnstituto Superior Tecnico, 1988, p. 4.1 1 (6 N89-21130# Utah Univ., Salt Lake City. Dept. of Chemistry. p.). Research supported by the Nederlands lnstituut voor MODERN MULTIPLE-PULSE, HIGH FIELD NMR STUDIES OF Vliegtuigontwikkeling en Ruimtevaart. refs HIGH DENSITY JET FUELS Final Report A two-component laser Doppler (LDA) and laser transit (LTA) DONALD W. ALDERMAN, JANET C. CURTIS, DAVID M. GRANT, anemometer have been compared under industrial testing CHARLES L. MAYNE, and RONALD J. PUGMIRE Aug. 1988 conditions in the flow field of a propeller. Free-stream flow speed 54P (Contract F33615-864-2643) was 40 m/s. The propeller, diameter 0.73 m, was operated at 3500 and 6000 rpm. Axial and tangential velocities were measured (AD-A203320; AFWAL-TR-88-2049) Avail: NTlS HC A04/MF A01 CSCL21D in front of, between, and behind the propeller blades. Author Modern high field nuclear magnetic resonance (NMR) spectroscopic techniques have been evaluated in order to assess A89-33388# the capabilities of such techniques for the study of jet fuels and PARTICLE IMAGE DISPLACEMENT VELOCIMETRY APPLIED related materials. The utility and quantitative aspects of spectral IN HIGH SPEED FLOWS editing techniques were evaluated. The field of 2-dimensional NMR C. S. MORAITIS and M. L. RIETHMULLER (Institut von Karman spectroscopy is growing rapidly and several existing 2-D techniques de Dynamique des Fluides, Rhode-Saint-Genese, Belgium) IN: are quite attractive for jet fuel studies. The protonhomonuclear International Symposium on Applications of Laser Anemometry to correlation experiment is shown to provide useful information even Fluid Mechanics, 4th, Lisbon, Portugal, July 11-14, 1988, in complex fuels. The heteronuclear correlation (1 H-l3C) Proceedings. Lisbon, lnstituto Superior Tecnico, 1988, p. 7.14 (5 experiment permits one to sort out overlapping lines in both the P.). refs proton and carbon frequency domains. The Jcoupled 2-D An experiment that demonstrated the applicability of experiment is very useful for characterizing the nature of the carbon particle-image-displacementvelocimetry (PIDV) to high-speed flows resonances as C, CH, CH2 and CH3 groups in jet fuels. A is reported. The problems encountered, Pertinent to seeding and Combination of heteronuclear correlation and J-coupled 2-D laser sheet illumination, are highlighted, and the solutions given experiments allow one to sort and identify the hundreds of are described in detail. Author
490 12 ENGINEERING
A8933402 and the selection of coating materials are considered together SYMPOSIUM ON TURBULENCE, llTH, UNIVERSITY OF with some production-proven applications of the technology taken MISSOURY-ROLLA. ROLLA. OCT. 17-19, 1988, PREPRINTS from the hot parts of a number of different gas turbines. The use Symposium sponsored by the University of Missouri-Rolla. Rolla, of the argon shrouded plasma spray process in conjunction with MO, University of Missouri-Rolla, 1988, 605 p. For individual items MCrAlY alloys (where M is Ni, Co, or Fe) and oxide ceramics to see A89-33403 to A89-33437. produce high temperature thermal barrier systems is highlighed. Topics discussed include turbulence structure in wake and jet Author flows, and turbulence structure in confined flows. Papers are also presented on laser-Doppler anemometry methods, developments A8933580# in measuring techniques, flows in complex geometries, and HEAT TRANSFER IN GAS TURBINE COMBUSTORS transonic and supersonic flows. B.J. MARIA DA GRACA CARVALHO and PEDRO JORGE COELHO (Lisboa. Universidade Tecnica, Lisbon, Portugal) Journal of A89-33435' Missouri Univ., Rolla. Thermophysics and Heat Transfer (ISSN 0887-8722), vol. 3, April NASA LIDAR VELOCIMETRY MEASUREMENTS 1989. p. 123-131. Research supported by the lnstituto Nacional RICHARD ANDERSON (Missouri-Rolla, University, Rolla) and de lnvestigacao Cientifica and Calouste Gulbenkian Foundation. JAMES BILBRO (NASA, Marshall Space Flight Center, Huntsville, refs AL) IN: Symposium on Turbulence, llth, Rolla, MO, Oct. 17-19, The present paper is concerned with the prediction of the 1988, %eprin!s. Rolla, Me, hiversity d Missouri-Rolla, !088, p. !oca! !!ow, hss!-?rane!nr, and ccmbustion prxesses inside a 11-1 to 11-6. refs three-dimensional can combustor chamber of a gas turbine. A A large number of turbulence experiments performed at the three-dimensional numerical solution technique is used to solve Marshall Space Flight Center are reviewed. These experiments the governing time-averaged partial differential equations and the include measurements of clear air turbulence, aircraft landing physical modeling for turbulence, combustion, and thermal wakes, wind shear, and severe storm turbulence. Also discussed radiation. Heat-transfer modeling is emphasized in this paper. A is a plan to orbit a lidar on a satellite in a north-south orbit to method to calculate the distribution of temperature, radiative heat make daily worldwide wind measurements. B.J. flux, and total heat flux of the liner is described. The implications of neglecting radiative heat transfer in gas turbine combustion A8933448 chamber calculations are discussed. The influence of working AIR FORCE TRIBOLOGY PROGRAMS pressure on radiative heat transfer is investigated, comparing the B. D. MCCONNELL (USAF, Wright Aeronautical Laboratories, radiative heat flux and temperature distribution of the liner for Wright-Patterson AFB, OH) IN: Engineered materials for advanced three different working pressures: 5, 15, and 25 bar. Both radiative friction and wear applications; Proceedings of the International and convective fluxes increase with pressure, mainly because of Conference, Gaithersburg, MD, Mar. 1-3, 1988. Metals Park, OH, the increase of inlet air temperature and gas emissivity. The ratio ASM International, 1988, p. 187-190. Research supported by of the fluxes to the energy supplied to the combustor is very USAF. refs small. However, the accurate assessment of the flux distribution The organizational structure, aims, and current status of USAF is an essential prerequisite for the prediction of the liner temperature tribology research programs are surveyed. The DARPA fundamental distribution and liner life. Author research program on solid-lubricated ceramics includes studies of adhesion problems, atomic-level friction, molecular dynamics, A89-33621 diamond films, lubricious oxides, and advanced tribological test FABRICATION OF SINTERED ALPHA-SIC TURBINE ENGINE equipment. The efforts of the Air Force Office of Scientific Research COMPONENTS focus on the characterization of thin films using advanced analytical R. W. OHNSORG and M. 0. TEN EYCK (Standard Oil Engineered techniques, whereas research for space applications includes work Materials Co., Niagara Falls, NY) IN: Silicon carbide '87; on the deposition of thin ultralow-friction films, surface coatings Proceedings of the Symposium, Columbus, OH, Aug. 2-5, 1987. for lightweight high-strength gears and bearings, ion implantation Westerville, OH, American Ceramic Society, Inc., 1989, p. methods, and the use of AES for in situ monitoring of surfaces 367-386. refs during friction and wear tests. T.K. Sintered alpha-Sic turbine engine components have been fabricated using three primary forming procedures: wet-bag isostatic A8433461 pressing followed by green machining, slip casting, and injection STRUCTURE AND PROPERTIES OF FORGED ODS molding. A closed loop fabrication approach is presented which NICKEL-BASE SUPERALLOYS takes each of these three paths into account. Additional process E. GRUNDY (Doncasters Monk Bridge, Ltd., Leeds, England) IN: iterations are discussed, which can be related to one of the three International Conference on PM Aerospace Materials, Lucerne, paths. The format enables the part designer and manufacturer to Switzerland, Nov. 2-4, 1987, Proceedings. Shrewsbury, England, interact and determine which path is most suitable based on MPR Publishing Services, Ltd., 1988, p. 12.1-12.10. refs economic and performance considerations. R.B. The forging of critical gas turbine parts from oxide dispersion strengthened (ODS), mechanically alloyed bar feedstock provides A89-33731'# AeroChem Research Labs., Inc., Princeton, NJ. an extremely cost-effective means of component production. SIMULTANEOUS COMPUTATION OF JET TURBULENCE AND Additionally, there exists the flexibility to control the structural and NOISE property response of these thermomechanically processing- C. H. BERMAN (AeroChem Research Laboratories. Inc., Princeton, sensitive alloys. Preselection of processing parameters com- NJ) and J. 1. RAMOS (Carnegie-Mellon University, Pittsburgh, PA) bined with postworking recrystallization treatments are used AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. to develop longitudinal crystal structures of variable grain size 10-12, 1989. 12 p. Research supported by NASA and New Jersey and aspect ratios in the MA 754 stator vane alloy and the MA Commission on Science and Technology. refs 6000 rotor blade alloy. Author (AIAA PAPER 89-1091) The existing flow computation methods, wave computation A8933487 techniques, and theories based on noise source models are ARGON SHROUDED PLASMA COATINGS FOR GAS TURBINE reviewed in order to assess the capabilities of numerical techniques APPLICATIONS to compute jet turbulence noise and understand the physical B. J. GILL (Union Carbide UK, Ltd., Swindon, England) IN: mechanisms governing it over a range of subsonic and supersonic International Conference on PM Aerospace Materials, Lucerne, nozzle exit conditions. In particular, attention is given to (1) methods Switzerland, Nov. 2-4, 1987, Proceedings. Shrewsbury, England, for extrapolating near field information, obtained from flow MPR Publishing Services, Ltd., 1988, p. 40.1-40.18. refs computations, to the acoustic far field and (2) the numerical solution In this paper, the principles of argon shrouded plasma spraying of the time-dependent Lilley equation. V.L.
49 1 12 ENGINEERING
A89-33741# A89-34 136 SONIC FATIGUE AND NONLINEAR RESPONSE OF AN EXPERIMENTAL STUDY OF THE RATE STIFFENED PANELS CHARACTERISTICS OF BRUSH SEALS IN COMPARISON RIMAS VAlCAlTlS (Columbia University, NY) and SIU-TONG CHOl WITH LABYRINTH SEALS [EKSPERIMENTAL'NOE (Weidlinger Associates, New York) AIAA, Aeroacoustics ISSLEDOVANIE RASKHODNYKH KHARAKTERISTIK Conference. 12th, San Antonio, TX. Apr. 10-12, 1989. 10 p. refs SHCHETOCHNOGO UPLOTNENIIA I SRAVNENIE S (AIAA PAPER 89-1101) LABIRINTNYY UPLOTNENIEM] A theoretical study on nonlinear response of discretely stiffened G. M. GORELOV, V. E. REZNIK, and V. I. TSlBlZOV Aviatsionnaia panels to random pressures and thermal loads is presented in Tekhnika (ISSN 0579-2975), no. 4, 1988, p. 43-46. In Russian. this paper. The random input pressures are simulated in time-space The effect of the geometrical parameters of brush seals on domain and the nonlinear equations of motion are solved the flow rate characteristic is investigated experimentally, and the numerically by a Monte Carlo type approach. In addition, preliminary results are compared with the rate characteristic of a known estimates of sonic fatigue based on the nonlinear stress distribution labyrinth seal. It is shown that the efficiency of brush seals is of response peaks and fatigue data from constant amplitude tests higher than that of labyrinth seals. A study of the thermal state of are given. The numerical results include deflection and stress brush seals indicates that, despite the lower flow rate of air, response time histories, spectral densities, root mean square sufficient cooling of the brush wires is achieved. V.L. values, crossing rates, probability distribution, peak distribution and fatigue damage. Author A89-34144 ADAPTIVE CONTROL OF THE GRINDING OF LARGE GAS TURBINE BLADES [ADAPTIVNOE UPRAVLENIE SHLIFOVANIEM PERA KRUPNOGABARITNYKH LOPATOK A89-34126 GTD] NATURAL VIBRATIONS OF CYLINDRICAL SHELLS WITH A L. T. MOISEEVA, F. S. IUNUSOV, and A. N. LUNEV Aviatsionnaia RECTANGULAR CUTOUT [SOBSTVENNYE KOLEBANIIA Tekhnika (ISSN 0579-2975). no. 4, 1988, p. 77-80. In Russian. TSlLlNDRlCHESKlKH OBOLOCHEK S PRIAMOUGOL'NYM A fully automated process for the dimensional grinding of large VYREZOM] gas turbine blades has been developed, with the shaping of the V. N. BAKULIN and S. L. SNESAREV Aviatsionnaia Tekhnika blades controlled adaptively based on deformations in excess of (ISSN 0579-2975), no. 4, 1988, p. 3-6. In Russian. refs the allowance and based on allowance fluctuations. Formulas are The effect of the dimensions of rectangular cutouts on the presented for determining and predicting deformations from the parameters of the natural vibrations of cylindrical shells is cutting forces. A model is developed and used in a series of investigated numerically using the finite element method. The simulations aimed at the evaluation and optimization of different results are compared with experimental data and an analytical system operation modes. V.L. solution using an orthotropic cylindrical shell with Navier-type boundary conditions as an example. It is found that, for the shell A89-34154 considered here, an increase in the cutout dimensions has only a ASSESSMENT OF THE ADEQUACY OF BEARING slight effect on the natural vibration of the shell. V.L. LUBRICATION IN A GAS TURBINE ENGINE THROUGH OPENINGS IN THE ROTATING SHAFT [OTSENKA DOSTATOCHNOSTI SMAZKI PODSHIPNIKA GTD CHEREZ OTVERSTllA VO VRASHCHAIUSHCHEMSIA VALU] A8934128 V. N. OSlPOV Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 4, THE LOAPBEARING CAPACITY OF CLOSED-PROFILE 1988, p. 98-100. In Russian. OBLONG CYLINDRICAL SHELLS MADE OF A A lubrication system for the rotor transmission bearings of gas METALIPOLYMER COMPOSITE LAMINATE [NESUSHCHAIA turbines whereby the lubricant is supplied to the bearings through SPOSOBNOST' DLINNYKH TSlLlNDRlCHESKlKH OBOLOCHEK openings in the rotating shaft is examined as a promising substitute ZAMKNUTOGO PROFILIA, IZGOTOVLENNYKH I2 SLOISTOGO for the presently used spray lubrication system. Here, calculations METALLOPOLIMERNOGO KOMPOZITA] are made to determine the adequacy of lubricant supply to the I. G. TEREGULOV and E. S. SIBGATULLIN Aviatsionnaia Tekhnika bearings in such a system. It is shown that the lubrication system (ISSN 0579-2975). no. 4, 1988, p. 9-13. In Russian. proposed here provides for a more complete utilization of the oil The limiting state of thin multilayer shells of arbitrary profile is in comparison with spray lubrication, which results in lower bearing investigated analytically. The shell considered here is made of temperatures V.L. alternating layers of an aluminum alloy and a polymer composite; the external load acting on the shell is reduced to an axial force A89-34155 and a torque. The results obtained are presented in the form of EFFECT OF THE BLADE HEIGHT AT THE EXIT OF THE tables and graphs. V.L. SHROUDED ROTOR OF A RADIAL-FLOW CENTRIPETAL MICROTURBINE ON THE TURBINE EFFICIENCY [VLIIANIE VYSOTY LOPATKI NA VYKHODE I2 OBANDAZHENNOGO RABOCHEGO KOLESA RADIAL'NOI TSENTROSTREMITEL'NOI A89-34 129 MIKROTURBINY NA EE KPD] FORMULATION AND SOLUTION OF AXISYMMETRIC N. T. TIKHONOV and V. N. MATVEEV Aviatsionnaia Tekhnika PROBLEMS IN THE STATICS OF MULTILAYER SHELLS OF (ISSN 0579-2975), no. 4, 1988, p. 100, 101. In Russian. REVOLUTION WITH CONTACT INTERACTION BETWEEN LAYERS [POSTANOVKA I RESHENIE OSESIMMETRICHNYKH A89-34159 ZADACH STATlKl MNOGOSLOINYKH OBOLOCHEK ENSURING THE QUALITY OF THE COVERING SURFACE IN VRASHCHENIIA PRI KONTAKTNOM VZAlMODElSTVll SLOEV] THE CASE OF RIVETED JOINTS WITH HIGH RADIAL V. A. FIRSOV Aviatsionnaia Tekhnika (ISSN 0579-2975), no. 4, INTERFERENCE [OBESPECHENIE KACHESTVA 1988, p. 13-17. In Russian. refs POVERKHNOSTI OBSHlVKl PRI VYPOLNENll The mechanics of the static deformation of multilayer shells of ZAKLEPOCHNYKH SOEDlNENll s VYSOKIM RADIAL'NYM revolution is analyzed from the standpoint of contact problems. NATIAGOM] An axisymmetric boundary value problem is stated for the mean A. 1. IARKOVETS, V. A. ZVIAGINTSEV, and V. Z. KONDRASHOV relative layer thickness and a linear approximation of displacement Aviatsionnaia Tekhnika (ISSN 0579-2975). no. 4. 1988, p. 108-110. vectors over the thickness of each layer. Calculations are carried In Russian. for a real structure to demonstrate the approach proposed here. The objective of the study was to determine the conditions V.L. under which the residual stresses produced by the interference fit
492 12 ENGINEERING have a favorable effect on the life of the structure without causing to Nelson's (1984). Predictions of the analysis are compared to any undesirable distortions of the airframe covering surface experimental results for a smooth-stator/smooth-rotor seal and geometry. By using the superposition principle and treating a riveted three honeycomb-stator/smooth-rotor seals. The model predicts a joint as a certain inhomogeneity producing the stress-strain state leakage and direct damping well. The model overpredicts the in a solid plate, an expression is obtained for displacements in a dependence of cross-coupled stiffness on fluid prerotation. The plate with a system of m+l joints; an expression for determining model predicts direct stiffness poorly. Author the critical values of the equivalent radial interference is then derived. The method is tested for the case of single joints in D16T panels made with 4-mm rivets of V65 alloy. V.L. A89-34867# ON THE DESIGN OF BIAXIALLY STIFFENED COMPOSITE A8934738 PLATES APPLICATIONS OF R GENERALIZED PRESSURE F. H. HO (BFGoodrich Co., Aerospace Div., Brecksville, OH) IN: CORRECTION ALGORITHM FOR FLOWS IN COMPLICATED Advanced composites and processing technology; Proceedings of GEOMETRIES the Symposium, ASME Winter Annual Meeting, Chicago, IL, Nov. W. SHYY (Florida, University, Gainesville) and M. E. BRAATEN (GE Research and Development Center, Schenectady, NY) IN: 27-Dec. 2, 1988. New York, American Society of Mechanical Engineers, 1988, p. 51-54. refs Advances and applications in computational fluid dynamics; The development of an integrally fabricated, biaxially stiffened Proceedings of Ihe ~YITI~GS~~~E,ASME Wln!e: Amua! Mee!ing, composite airframe primary structure entails thesolution of the Chicago, IL. Nov. 27-Dec. 2, 1988. New York, American Society problem posed by the discontinuity of the tensile load path at the of Mechanical Engineers, 1988, p. 109-119. refs stiffener intersections. The present treatment of the problem An overview is given of recent progress in developing a unified increases the web height of the secondary stiffener at cross-over numerical algorithm capable of solving flow over a wide range of sections. It is stressed that the added stiffener height should be Mach and Reynolds numbers in complex geometries. The algorithm just sufficient to satisfy strength requirements at the cutout. The is based on the pressure correction method, combined treatment overall advantage of the quasi-isotropic lamination has been of the Cartesian and contravariant velocity components on arbitrary demonstrated for the case of the design merit index employed. coordinates, and second-order accurate discretization. A number O.C. of two- and three-dimensional flow problems including the effects of electric currents, turbulence, combustion, multiple phases, and compressibility are presented to demonstrate the capability of the present algorithm. Some related technical issues, such as the A89-34909 skewness of the grid distribution and the promise of parallel DIRECT NUMERICAL SIMULATION OF A computation. are also addressed. Author THREE-DIMENSIONAL TURBULENT BOUNDARY LAYER P. MOIN, S. SHIH, 0. SENDSTAD, and D. DRIVER (Stanford A8934794'# Texas A&M Univ., College Station. University, CA) IN: Recent developments in computational fluid ANNULAR HONEYCOMB SEALS: TEST RESULTS FOR dynamics; Proceedings of the Symposium, ASME Winter Annual LEAKAGE AND ROTORDYNAMIC COEFFICIENTS - Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American COMPARISONS TO LABYRINTH AND SMOOTH Society of Mechanical Engineers, 1988, p. 139-145. refs CONFIGURATIONS (Contract AF-AFOSR-87-0285) D. CHILDS, D. ELROD, and K. HALE (Texas A & M University, The effect of a suddenly imposed transverse pressure gradient College Station) ASME, Transactions, Journal of Tribology (ISSN on a fully developed planar two-dimensional channel flow at Re 0742-4787), vol. 111, April 1989, p. 293-300; Discussion, p. 300, = 3300 is investigated by means of numerical simulations. The 301. refs spectrum method of Kim et al. (1987) is implemented on a 128 x (Contract NAG3-181; F49620-82-K-0033) 128 x 128 grid capable of resolving all turbulent scales; no subgrid (ASME PAPER 88-TRIB-35) or turbulence models are required. Ensemble-averaged results from Test results are presented for leakage and rotordynamic 14 simulation runs are presented in graphs and briefly coefficients for seven honeycomb seals. All seals have the same characterized. Good agreement with published experimental data radius, length, and clearance; however, the cell depths and is demonstrated. T.K. diameters are varied. Rotordynamic data, which are presented, consist of the direct and cross-coupled stiffness coefficients and the direct damping coefficients. The rotordynamic-coefficient data show a considerable sensitivity to changes in cell dimensions; A89-34912' Scientific Research Associates, Inc., Glastonbury, however, no clear trends are identifiable. Comparisons of test data CT. for the honeycomb seals with labyrinth and smooth annular seals BIPOLAR COORDINATES FOR COMPUTATION OF shows the honeycomb seal had the best sealing (minimum leakage) TRANSITION DUCT FLOWS performance, followed in order by the labyrinth and smooth seals. R. K. MADABHUSHI and R. LEVY (Scientific Research Associates, For prerotated fluids entering the seal, in the direction of shaft Inc., Glastonbury, CT) IN: Recent developments in computational rotation, the honeycomb seal has the best rotordynamic stability fluid dynamics; Proceedings of the Symposium, ASME Winter followed in order by the labyrinth and smooth. For no prerotation, Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York. or fluid prerotation against shaft rotation, the labyrinth seal has American Society of Mechanical Engineers, 1988. p. 185-192. the best rotordynamic stability followed in order by the smooth refs and honeycomb seals. Author (Contract NAS3-24224) Numerical simulation techniques for flows in jet-engine transition A8434798*# Texas A&M Univ.. College Station. ducts with changing cross sections are developed and AN ENTRANCE REGION FRICTION FACTOR MODEL APPLIED demonstrated. The boundary-conforming grids required are TO ANNULAR SEAL ANALYSIS - THEORY VERSUS generated using bipolar coordinates, and the singularities arising EXPERIMENT FOR SMOOTH AND HONEYCOMB SEALS at the no-slip boundaries are treated as described by de Vahl D. ELROD. C. NELSON, and D. CHILDS (Texas A & M University, Davis (1979) and Tsai and Levy (1987). Grids for several typical College Station) ASME. Transactions, Journal of Tribology (ISSN configurations are employed in computations with the 0742-4787), vol. 111, April 1989, p. 337-343. refs three-dimensional laminar/turbulent viscous-flow solver of Levy et (Contract NAG3-181) al. (1983), and the results are presented graphically. The scheme (ASME PAPER 88-TRIB-41) used to deal with singularities is shown to be robust, suggesting A friction factor model is developed for the entrance-region of that the bipolar grids may be applicable to Navier-Stokes a duct. The model is used in an annular gas seal analysis similar computations. T.K.
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A89-34926' General Electric Co., Fairfield, CT. A8934931 HEAT TRANSFER IN GAS TURBINE ENGINES AND PREDICTION OF HEAT TRANSFER CHARACTERISTICS OF THREE-DIMENSIONAL FLOWS; PROCEEDINGS OF THE DISCRETE HOLE FILM COOLING - ONE ROW OF INJECTION SYMPOSIUM, ASME WINTER ANNUAL MEETING, CHICAGO, INTO A TURBULENT BOUNDARY LAYER IL, NOV. 27-DEC. 2,1988 S. YAVUZKURT (Pennsylvania State University, University Park) E. ELOVIC, ED. (General Electric Co., Fairfield, CT), J. E. OBRIEN, and D. K. TAFTl IN: Heat transfer in gas turbine engines and ED. (NASA, Lewis Research Center. Cleveland, OH), and D. W. three-dimensional flows; Proceedings of the Symposium, ASME PEPPER, ED. (Marquardt co., Van Nuys, CA) Meeting sponsored Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New by ASME, Heat Transfer Division. New York, American Society of York, American Society of Mechanical Engineers, 1988, p. 45-52. Mechanical Engineers, 1988, 127 p. For individual items see Research supported by Textron Lycoming. refs A89-34927 to A89-34935. Predictions of spanwise averaged effectiveness and The present conference on heat transfer characteristics of heat-transfer coefficients are presently made on the basis of a gas turbines and three-dimensional flows discusses velocity- two-dimensional injection model for the discrete-hole injection temperature fluctuation correlations at the flow stagnation process that is incorporated in a two-dimensional boundary layer flow of a circular cylinder in turbulent flow, heat transfer across code using the low Reynolds number version of the k-epsilon turbulent boundary layers with pressure gradients, the effect of jet model of turbulence. Attention is given to the case of one row of grid turbulence on boundary layer heat transfer, and heat transfer injection into a turbulent boundary layer. Two constants derived characteristics predictions for discrete-hole film cooling. Also from experimental data are employed: the aerodynamic drag discussed are local heat transfer in internally cooled turbine airfoil coefficient, controlling the jet penetration into the boundary layer, leading edges, secondary flows in vane cascades and curved ducts, and the entrainment fraction, which simulates the effect of three-dimensional numerical modeling in gas turbine coal three-dimensional entrainment on the temperature profile. Velocity combustor design, numerical and experimental results for tube-fin and temperature profiles are in good agreement with experimental heat exchanger airflow and heating characteristics, and the data. O.C. computation of external hypersonic three-dimensional flow field and heat transfer characteristics. O.C. A8934932 LOCAL HEAT TRANSFER IN INTERNALLY COOLED TURBINE AIRFOIL LEADING EDGE REGIONS. I - IMPINGEMENT COOLING WITHOUT FILM COOLANT EXTRACTION. II - A89-34928' National Aeronautics and Space Administration. IMPINGEMENT COOLING WITH FILM COOLANT EXTRACTION Lewis Research Center, Cleveland, OH. R. S. BUNKER and D. E. METZGER (Arizona State University, EFFECTS OF WAKE PASSING ON STAGNATION REGION Tempe) IN: Heat transfer in gas turbine engines and HEAT TRANSFER three-dimensional flows; Proceedings of the Symposium, ASME J. E. OBRIEN (NASA, Lewis Research Center, Cleveland, OH) Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New IN: Heat transfer in gas turbine engines and three-dimensional York, American Society of Mechanical Engineers, 1988, p. 53-63. flows; Proceedings of the Symposium, ASME Winter Annual refs Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American The highly localized internal heat transfer characteristics of Society of Mechanical Engineers, 1988, p. 17-28. refs large-scale models of impingement-cooled turbine blade leading In the present experimental study, an annular-flow wind tunnel edge regions presently studied derives its cooling from a single fitted with a spoked-wheel wake generator was used to ascertain line of equally-spaced multiple jets aimed at the leading-edge apex, both time-averaged and time-resolved effects of wake passing in and exiting the leading-edge region in the opposite or chordwise a cylinder stagnation region; the cylindrical spokes generated wakes direction. Detailed two-dimensional local surface Nusselt number simulating those of a turbine inlet guide vanes. The time-averaged distributions have been obtained with temperature-indicating heat transfer results obtained indicate an asymmetric heat-transfer coatings. Results indicate generally increasing heat transfer with coefficient distribution about the stagnation line, with higher the 0.6 power of jet Reynolds number. In the second part of this heat-transfer coefficients on the side corresponding to the suction study, in which the same cooling process is used in conjunction side of the turbine blade. Spectra of the hot-film records indicate with the extraction of the coolant fluid, the results obtained indicate that vortex-shedding is a major contributor to the unsteady buffeting that heat transfer is primarily dependent on jet Reynolds number, of the testcylinder boundary layer at circumferential stations with smaller influences from the flow-extraction rate. O.C. located at both + and -60 deg from the stagnation line, despite making only a minor contribution to the stagnation line itself. O.C. A8934935 COMPUTATION OF EXTERNAL, HYPERSONIC, THREE-DIMENSIONAL FLOWFIELD AND HEAT TRANSFER A. BAIAKRISHNAN (MCAT Institute, San Jose, CA) IN: Heat A8434930 transfer in gas turbine engines and three-dimensional flows; EFFECT OF JET GRID TURBULENCE ON TURBULENT Proceedings of the Symposium, ASME Winter Annual Meeting, , BOUNDARY LAYER HEAT TRANSFER Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American Society C. D. YOUNG and J. C. HAN (Texas A 8 M University, College of Mechanical Engineers, 1988. p. 115-122. refs Station) IN: Heat transfer in gas turbine engines and Hypersonic and equilibrium flowfields and heat-transfer rates three-dimensional flows; Proceedings of the Symposium, ASME around a blunt-nosed configuration are calculated by solving the Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New Euler equations and thin-layer Navier-Stokes equations. The York, American Society of Mechanical Engineers, 1988, p. 37-44. equilibrium thermodynamic and transport properties of the gas refs mixture are introduced into the numerical procedure by way of (Contract F33615-86-C-2723) tables. Shock stand-off distances, normalized pressures, densities, A wind tunnel with a biplanar, square-mesh round-tube grid for and temperatures around a sphere, for Mach numbers of 10, 15, uniform, controllable-flow rate jet injection in either coflow or and 20, and at altitudes ranging from 20 to 80 km, are presented counterflow fashion is presently used to ascertain the effect of for inviscid flow. Laminar heat-transfer rates for several Mach high freestream turbulence on turbulent boundary layer heat numbers are computed. Computed stagnation-point heat-transfer transfer. A flat plate section instrumented with foil-thermocouples results compare well with an engineering correlation and also with is located behind the jet grid. The surface Stanton numbers with a viscous shock-layer solution. Computed heat-transfer distributions the counterflow and coflow injections are, respectively, about 45 around the body compare well with experimental data. Author and 25 percent higher than the zero turbulence correlation in the fully turbulent region. The effects of length-scale and low Reynolds A89-35004 number on the surface Stanton number are discussed. O.C. COMPRESSIBLE FLOW LOSSES IN BRANCHED DUCTS
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N. I. ABOU-HAIDAR and S. L. DIXON (Liverpool, University, in the macro- and micro-mechanics of composite materials England) IN: Collected papers in heat transfer 1988; Proceedings structures; Proceedings of the Symposium, ASME Winter Annual of the ASME Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. 2, Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American 1988. Volume 2. New York, American Society of Mechanical Society of Mechanical Engineers, 1988, p. 169-175. refs Engineers, 1988, p. 17-23. refs Divergence instability of a simply supported orthotropic Investigation of the additional total pressure losses occurring composite shell reinforced in both axial and circumferential at the junction of various branched ducts has been made both directions is considered. The shell is subject to an axial static analytically and experimentally. Experimental results are presented load and to an action of an outside supersonic gas flow in the for five different dividing flow geometries of a lateral branch off a direction parallel to the shell axis. Two variants of the solution straight duct. All duct intersections tested were sharp-edged. Dry considered in the paper include discrete widely spaced stiffeners air was the working fluid. Analysis of the results confirms the and closely spaced stiffeners; the latter case can be treated using expected strong and increasingly adverse influence of a smeared stiffeners technique. It is proven that divergence compressibility at values of Mach number higher than 0.6. instability of shells treated by smeared stiffeners technique can Author occur only if they are subject to axial compressive loads exceeding the static buckling value. Author A8935074 QUANTITATIVE FRACTOGRAPHY - POSSIBILITIES AND A8435237# APPLICATIONS IN AIRCRAFT RESEARCH PARACHUTE DRAWING STANDARDS CURRENTLY IN USE 1. NEDBAL, J. KUNZ, and J. SlEGL (Ceske Vysoke Uceni AT SANDIA NATIONAL LABORATORIES Technicke, Prague, Czechoslovakia) IN: Basic mechanisms in KENNETH L. RONQUILLO (Sandia National Laboratories, fatigue of metals; Proceedings of the International Colloquium, Albuquerque, NM) IN: AlAA Aerodynamic Decelerator Systems Brno, Czechoslovakia, Apr. 12-14, 1988. Amsterdam, Elsevier, Technology Conference. loth, Cocoa Beach, FL, Apr. 18-20, 1989, 1988, p. 393-403. refs Technical Papers. Washington, DC, American Institute of The paper reviews methods of fatigue failure fractography Aeronautics and Astronautics, 1989, p. 233-241. developed for reconstitution of fatigue crack kinetics. Some results (Contract DE-AC04-76DP-00789) of fractographic analysis of failured aircraft structures are (AIAA PAPER 89-0927) presented. It points out the importance of relation between macro- A method of making comprehensive parachute drawings has and microscopic fatigue crack propagation. The unacceptability of been established at Sandia National Laboratories. This method the assumption of macroscopic crack growth rate and striation uses some of the basic, standardized and conventional drawing spacing equality is illustrated by experimental data acquired on practices used in making mechanical drawings. This method also AICu4Mgl (type 2024) sheet specimens. with the application in introduces new drafting techniques unique to parachute drawings. case study of the aircraft fuselage skin part failure. Author Author
A8935081 A8935247# MICRO RADIOGRAPHY AND TOMOGRAPHY FOR HIGH AN EXPRESSION FOR DYNAMIC STRAIN IN A 'WEAK LINK RESOLUTION NDT OF ADVANCED MATERIALS AND GEORGE A. BARNARD IN: AlAA Aerodynamic Decelerator MICROSTRUCTURAL COMPONENTS Systems Technology Conference, 10th. Cocoa Beach, FL, Apr. M. MAISL, H. REITER, and P. HOELLER (Fraunhofer-lnstitut fuer 18-20, 1989, Technical Papers. Washington, DC, American Institute zerstoerungsfreie Pruefverfahren; Saarland, Universitaet, of Aeronautics and Astronautics, 1989, p. 310-318. Saarbruecken, Federal Republic of Germany) IN: New directions (AIAA PAPER 89-0942) in the nondestructive evaluation of advanced materials; A 'weak link' is represented by a break cord or a lanyard used Proceedings of the Symposium, ASME Winter Annual Meeting, to control a sequence of events during deployment of a parachute. Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American Society In this paper, a closed-form analytical solution is presented for of Mechanical Engineers, 1988, p. 29-33. the asymptotic strain state of a weak link between stronger The application of microradiography and microcomputed bounding members. The convergence interval and convergence tomography for the NDT of high strength ceramics and time are defined. For typical properties of materials used in fiber-reinforced composites is discussed. Radiography with high-speed parachutes, the strain state of such a link is accurately microfocal X-ray tubes provides high-resolution radiographs using represented by its asymptotic value because of the rapid the direct projection technique. Tomography produces high-contrast convergence of the solution. A sample calculation is presented to images of sections of an object, and results are presented using demonstrate the use of the analysis in designing break links and a tomographic unit with a resolution of the order of magnitude of pull cords for fast-moving systems. Author 20 microns. R.R. A8935654 A8935097# PROSPECTS FOR THE APPLICATION OF HOLOGRAPHIC AEROELASTIC DIVERGENCE OF FRONT-FREE-AFT-FIXED INTERFEROMETRY TO THE STUDY OF THE RESONANT ELASTIC STRIP PARALLEL TO UNIFORM FLOW VIBRATIONS OF COMPLEX SYSTEMS [O PERSPEKTIVAKH YUZO YAMAMOTO (Gifu National College of Technology, Japan) PRlMENENllA METODA GOLOGRAFICHESKOI Japan Society for Aeronautical and Space Sciences, Transactions INTERFEROMETRII K ISSLEDOVANIIU REZONANSNYKH (ISSN 0549-3811), vol. 31, Feb. 1989, p. 188-194. refs KOLEBANll SLOZHNYKH SISTEM] The static instability of a slender free-fixed elastic strip in a I. F. OBRAZTSOV and V. A. SMIRNOV Raschety na Prochnost', uniform air stream whose free end is the leading edge is studied. no. 28, 1988, p. 134-151. In Russian. The analysis is performed using slender body aerodynamic theory Results of holographic interferometry studies of the behavior and beam theory. Both the static aeroelastic divergence speed of plates, shells, and complex three-dimensional models of and the divergence mode are derived. Low speed wind tunnel mechanical systems subjected to periodic dynamic loading are tests for the present problem were done. The strips used in these reported. Examples are presented to demonstrate the possibility tests were thin copper plates and thin aluminum plates. It is shown of the vibration of different parts of the same structure at different that the divergence speed based on linear lift is higher than the frequencies. Photographs of holograms are presented. V.L. one based on nonlinear lift. Author N89-20355'# Ohio State Univ., Columbus. ElectroScience Lab. A8935146 ELECTROMAGNETIC PROPERTIES OF ICE COATED DIVERGENCE INSTABILITY OF REINFORCED COMPOSITE SURFACES Semiannual Report CYLINDRICAL SHELLS A. DOMINICK, E. WALTON, N. WANG, and L. BEARD Feb. v. BIRMAN (New Orleans, University, LA) IN: Recent advances 1989 19 p
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(Contract NSG-3913) with Interacted Viscous Effects (TAWFIVE) was improved by the (NASA-CR-184780; NAS 1.26:184780; ESL-720964-2) Avail: incorporation of multigrid and a method to specify lift coefficient NTlS HC AO3/MF A01 CSCL 20N rather than angle-of-attack. A finite volume full potential multigrid The electromagnetic scattering from ice coated structures is method is used to model the outer inviscid flow field. First order examined. The influence of ice is shown from a measurement viscous effects are modeled by a 3-D integral boundary layer standpoint and related to a simple analytical model. A hardware method. Both turbulent and laminar boundary layers are treated. system for the realistic measurement of ice coated structures is Wake thickness effects are modeled using a 2-D strip method. A also being developed to use in an existing NASA Lewis icing brief discussion of the engineering aspects of the program is given. tunnel. Presently, initial measurements have been performed with The input, output, and use of the program are covered in detail. a simulated tunnel to aid in the development. Author Sample results are given showing the effects of boundary layer corrections and the capability of the lift specification method. N89-20363*# Ohio State Univ., Columbus. ElectroScience Lab. Author IMPROVED COMPUTER SIMULATION OF THE TCAS 3 CIRCULAR ARRAY MOUNTED ON AN AIRCRAFT N89-20422# Von Karman Inst. for Fluid Dynamics, R. G. ROJAS. Y. C. CHEN, and WALTER D. BURNSIDE Mar. Rhode-Saint-Genese(Belgium). 1989 191 p A CALCULATION METHOD FOR COMPRESSIBLE THREE (Contract NSG-1498) DIMENSIONAL TURBULENT BOUNDARY LAYER FLOWS (NASA-CR-184907; NAS 1.261184907; ELS-TR-716199-12) L. J. JOHNSTON Jul. 1988 82 p Avail: NTlS HC AO9/MF A01 CSCL 20N (VKI-TN-167; ETN-89-94121) Avail: NTlS HC A05/MF A01 The Traffic advisory and Collision Avoidance System (TCAS) A calculation method for compressible 3D boundary layers is is being developed by the Federal Aviation Administration (FAA) described. The method involves a finite difference discretization to assist aircraft pilots in mid-air collision avoidance. This report of the governing mean flow equations. The differencing scheme concentrates on the computer simulation of the enchanced TCAS used to discretize spanwise derivatives adapts automatically to 2 systems mounted on a Boeing 727. First, the moment method the sign of the local crossflow within the boundary layer. A is used to obtain an accurate model for the enhanced TCAS 2 plane-by-planesolution procedure in the spanwise direction enables antenna array. Then, the OSU Aircraft Code is used to generate second-order accuracy to be maintained throughout the whole flow theoretical radiation patterns of this model mounted on a simulated field. A normal coordinate scaling with the local total momentum Boeing 727 model. Scattering error curves obtained from these thickness removes most of the boundary layer growth in patterns can be used to evaluate the performance of this system computational space. The method is applied to a range of in determining the angular position of another aircraft with respect experimental flows, including compressible subsonic and to the TCAS-equipped aircraft. Finally, the tracking of another supersonic free stream conditions. The Cebeci-Smith algebraic aircraft is simulated when the TCAS-equipped aircraft follows a turbulence model is used for the initial validation of the calculation prescribed escape curve. In short, the computer models developed method. A simple modification to this model is tested, involving in this report have generality, completeness and yield reasonable an explicit dependence of the outer eddy viscosity on the crossflow results. Author within the boundary layer. A significantly improved prediction of an infinite swept wing flow experiment is obtained. ESA N89-20386'# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, CA. N89-20426# Calspan Corp., Buffalo, NY. AN AIRFOIL PITCH APPARATUS-MODELING AND CONTROL TRANSMISSION AND REFLECTION ON PRESSURE WAVES DESIGN BY COMPRESSOR AND TURBINE STAGES, BASED ON AN DANIEL R. ANDREWS Mar. 1989 13 p Prepared for ACTUATOR-DISK MODEL Technical Report, 1 Jun. 1986 - 1 presentation at the 35th Instrument Society of America Sep. 1987 InstrumentationSymposium, Orlando, FL, 1-4 May 1989 Submitted W. J. RAE, P. F. BATCHO, and M. G. DUNN 1 Feb. 1988 for publication 49 P (NASA-TM-101076; A-89051; NAS 1.15:101076) Avail: NTlS HC (Contract DNA001-834-01 82; DNA PROJ. N99-QMXA) AOWMF A01 CSCL 09C (AD-A203513; CALSPAN-7170-7; DNA-TR-88-58) Avail: NTlS The study of dynamic stall of rapidly pitching airfoils is being HC AOWMF A01 CSCL 20D conducted at NASA Ames Research Center. Understanding this The amplitudes of the pressure waves transmitted and reflected physical phenomenon will aid in improving the maneuverability of by an actuator disk due to the impingement of an incident pressure fighter aircraft as well as civilian aircraft. A wind tunnel device wave calculated. Analytic expressions for the wave amplitudes which can linearly pitch and control an airfoil with rapid dynamic are derived for the limit where the incident pressure rise is small response is needed for such tests. To develop a mechanism and these formulas, as well as direct calculations, are used to capable of high accelerations, an accurate model and control estimate the effect of multiple wave reflections from a pair of system is created. The model contains mathematical actuator disks. These predictions help to explain a number of representations of the mechanical system, including mass, spring, phenomena that have been observed in measurements made when and damping characteristics for each structural element, as well shock-tube generated overpressure waves were sent into an as coulomb friction and servovalve saturation. Electrical operating engine. GRA components, both digital and analog, linear and nonlinear, are simulated. The implementation of such a high-performancesystem N89-20468# Battelle Columbus Labs., OH. requires detailed control design as well as state-of-the-art DEVELOPMENTOFAROTARYVALUEFORPULSE components. This paper describes the system model, states the COMBUSTION APPLICATIONS Final Report, Jun. 1986 - Mar. system requirements, and presents results of its theoretical 1988 performance which maximizes the structural and hydraulic aspects PAUL E. GEORGE and JOHN M. CORLISS 31 Oct. 1988 of this system. Author 63 P (Contract GRI-5086-234-1280) N89-20409'# National Aeronautics and Space Administration. (PB89-131114; GRI-88/0185) Avail: NTlS HC A04/MF A01 Langley Research Center, Hampton, VA. CSCL 131 UPDATED USERS GUIDE FOR TAWFIVE WITH MULTIGRID Research demonstrated the technical feasibility of a N. DUANE MELSON and CRAIG L. STREElT Washington May computer-controlled inlet-air rotary valve for pulse combustion 1989 68 p applications. The results show that a Schimdt pulse combustor (NASA-TM-4109; L-16543; NAS 1.154109) Avail: NTlS HC operated with a rotary valve provides similar performance in terms AO4/MF A01 CSCL 20D of heat transfer, pressure boost and turndown ratio to that of A program for the Transonic Analysis of a Wing and Fuselage aero-valved and flapper-valved pulse combustors. The benefits of
496 12 ENGINEERING scale-up ease, design flexibility and tolerance of adverse conditions analytical formulation of rotor dynamics equations, fuselage do not justify the added cost of the valve, motor and control dynamic equations. coupling between the rotor and fuselage, and systems for most industrial applications. GRA solutions to the total system of equations in C81 are included. Analytical predictions of hub shears for main rotor harmonics 2p, N89-20472'# Mechanical Technology, Inc., Latham, NY. 4p, and 6p generated by C81 are used in conjunction with 2p HIGH SPEED BALANCING APPLIED TO THE T700 ENGINE OLS measured control loads and a 2p lateral tail rotor gearbox Final Report force, representing downwash impingement on the vertical fin, to J. WALTON, C. LEE, and M. MARTIN Mar. 1989 110 p Prepared excite the NASTRAN model. NASTRAN is then used to correlate in cooperation with Army Aviation Systems Command, Cleveland, with measured OLS flight test vibrations. Blade load comparisons OH predicted by C81 showed good agreement. In general, the fuselage (Contract NAS3-23929; NAS3-24633; DA PROJ. vibration correlations show good agreement between anslysis and 1L1-62209-AH-76) test in vibration response through 15 to 20 Hz. Author (NASA-CR-180899; NAS 1.26:180899; MTI-87TR56; AVSCOM-TR-88-C-007) Avail: NTlS HC AO6/MF A01 CSCL N89-20519# National Aerospace Lab., Amsterdam (Netherlands). 131 Structures and Materials Div. The work performed under Contracts NAS3-23929 and BULGING CRACKS IN PRESSURIZED FUSELAGES A NAS3-24633 is presented. MTI evaluated the feasibility of NUMERICAL STUDY high-speed balancing for both the T700 power turbine i0:G and E. R!KS 17 Nov. 1987 33 p the compressor rotor. Modifications were designed for the existing (Contract NIVR-06404N) Corpus Christi Army Depot (CCAD) T53/T55 high-speed balancing (NLR-MP-87058-U; ETN-89-94039) Avail: NTlS HC AO3/MF system for balancing T700 power turbine rotors. Tests conducted A0 1 under these contracts included a high-speed balancing evaluation The possibility to obtain useful results by means of commercially for T700 power turbines in the Army/NASA drivetrain facility at available nonlinear finite element techniques in analyses of MTI. The high-speed balancing tests demonstrated the reduction pressurized, stiffened, thin walled shells cylindrical shells was of vibration amplitudes at operating speed for both low-speed studied. Unstiffened as well as stiffened configurations based on balanced and non-low-speed balanced T700 power turbines. In actual fuselage designs were considered. It is shown that the addition, vibration data from acceptance tests of T53, T55, and nonlinear effect is large for large aspect ratios of the cracks and T700 engines were analyzed and a vibration diagnostic procedure that stiffeners have, in general, a considerable effect on the stress developed. Author intensity factors. ESA
N89-20498# Air Force Systems Command, Wright-Patterson AFB. N89-20520# National Aerospace Lab., Amsterdam (Netherlands). OH. Structures and Materials Div. STRUCTURAL MECHANICS CONTEMPORARY STATE AND ANALYSIS OF CRACK OPENING BEHAVIOR BY PROSPECTS FOR DEVELOPMENT (SELECTED PORTIONS) APPLICATION OF A DISCRETIZED STRIP YIELD MODEL V. V. BOLOTIN, 1. I. GOLDENBLAT, and A. F. SMIRNOV 19 A. U. DEKONING and G. LlEFTlNG (Technische Hogeschool Aug. 1988 83 p Transl. into ENGLISH from Stroitelnaya Twente, Enschede. Netherlands ) 1 Mar. 1986 41 p Presented Mekhanika (Moscow, USSR), 1972 p 3, 65-98, 190-191 at the International Symposium on Fatigue Crack Closure, (AD-A198766; FrD-ID(RS)-T-O438-88) Avail: NTlS HC A05/MF Charleston, WV, May 1986 A01 CSCL20K (Contract NIVR-1823/01702-N) In recent years, many works have been published on structural (NLR-MP-87065-U; ETN-89-94043) Avail: NTlS HC A03/MF mechanics and its application to calculation of structures, aircraft, A0 1 ships and machines. However, among these investigations are The crack opening behavior of a fatigue crack in a centrally still insufficient works of survey character, which give cracked panel was studied using a discretized version of the respresentation about the level of the interesting U.S. field of Dugdale and Barenblatt model. The effect of crack growth was science as a whole. Survey/coverage in no way pretends to also included. Results obtained for constant amplitude loading completeness; authors paid attention to those works which were agree with data in the literature. The effect of application of single close to their scientific interests. Examined in detail are sections overload-underload combinations and of simple block loading dealing the theory of the elastoplastic calculation of constructions, programs on the crack opening behavior were analyzed. The results statistical dynamics and the theory of the reliability of constructions, were compared with predictions based on an empirical model and mechanics of construction with the composite materials. A (CORPUS). The criteria used in the CORPUS model to select special chapter is dedicated to the application of electronic significant load excursions in the applied load sequence were computers to structural mechanics. GRA checked. Both models were used to predict crack growth under a simplified landing gear load sequence. The predicted crack opening N89-20512*# Textron Bell Helicopter, Fort Worth, TX. loads and the crack growth agree with experimental data. ESA COUPLED ROTORIFUSELAGE DYNAMIC ANALYSIS OF THE AH-1G HELICOPTER AND CORRELATION WITH FLIGHT N89-20521# National Aerospace Lab., Amsterdam VIBRATIONS DATA Final Report (Netherlands). J. C. CORRIGAN, J. D. CRONKHITE, R. V. DOMPKA, K. S. PERRY, CURRENT STATUS OF FLIGHT SIMULATION FATIGUE J. P. ROGERS, and S. G. SADLER Jan. 1989 144 p CRACK GROWTH CONCEPTS (Contract NASl-17496) R. J. H. WANHILL and J. SCHIJVE 15 Jan. 1988 19 p Presented (NASA-CR-181723; NAS 1.26:181723) Avail: NTlS HC A07/MF at the 3rd French MetallurgicalSociety International Spring Meeting, A01 CSCL20K Paris, France, Jun. 1988 Under a research program designated Design Analysis Methods (NLR-MP-88001-U; ETN-89-94051) Avail: NTlS HC AO3/MF for VlBrationS (DAMVIBS), existing analytical methods are used A01 for calculating coupled rotor-fuselage vibrations of the AH-1G Crack growth models and methods of crack growth prediction helicopter for correlation with flight test data from an AH-1G are compared with respect to applicability and limitations. Research Operational Load Survey (OLS) test program. The analytical areas for improvement of crack growth prediction are specified. representation of the fuselage structure is based on a NASTRAN Fatigue crack growth predictions should be considered acceptable finite element model (FEM), which has been developed, extensively if within a factor of 2 of test results, and if they show the correct documented, and correlated with ground vibration test. One trends for variations of spectrum and test parameters. Although procedure that was used for predicting coupled rotor-fuselage the choice of crack growth model depends on particular vibrations using the advanced Rotorcraft Flight Simulation Program circumstances, it is preferable, certainly in the long term, to (281 and NASTRAN is summarized. Detailed descriptions of the concentrate on improving and using crack opening models.
497 12 ENGINEERING
Improvement of crack opening models, in particular their ability to Two oblique shocks, typical of those formed at the trailing edge deal with plane strainlplane stress conditions and more of a transonic rotor blade, are captured. These shocks are smeared complicated crack geometries, requires developments in analytical over several grid points, as expected with a shock capturing and experimental determinations of near-tip crack opening and scheme, but their influence on the blade loading diagram is the compilation of flight simulation fatigue test data banks. Usable evident. GRA models and methods for predicting short crack growth are years away. Their applicability will probably be restricted to damage N89-21270# Air Force Inst. of Tech., Wright-Patterson AFB, tolerance of engine disks and blades and durability analysis of OH. School of Engineering. airframes. A better description of constant amplitude fatigue crack APPLICATION OF THE BOUNDARY ELEMENT METHOD TO growth is needed, especially at low and high stress intensity levels FATIGUE CRACK GROWTH ANALYSIS M.S. Thesis and high stress ratios. More understanding is required of the TIMOTHY C. KELLEY Sep. 1988 142 p interrelations between microstructure, fracture mechanisms, (AD-A202565; AFIT/GAE/AA/88S-l) Avail: NTlS HC A07/MF fracture topography, threshold, crack growth curve transition points, A01 CSCL20K and crack opening behavior. ESA This investigation analyzes a crack emanating from one hole, and approaching a second hole, in a two hole tension strip with N89-20525# Aeronautical Research Inst. of Sweden, Stockholm. finite boundaries using the Boundary Element Method. The study Structures Dept. included the effects of varying the hole diameter, hole separation ESTIMATION OF THE EQUIVALENT INITIAL FLOW SIZE and the length of the geometric correction factor beta, which can (EIFS) DISTRIBUTION AND PREDICTION OF FAILURE be presented as a family of curves. An example damage tolerance PROBABILITIES FOR DIFFERENT PARAMETER VARIATIONS analysis is presented with the beta curves being incorporated into LARS MORAEUS Oct. 1987 30 p Sponsored by the Swedish a beta look-up table as used in the NASA/FLAGRO fatigue crack Board for Technical Development growth program. This technique is acceptable in most fatigue crack (FFA-TN-1987-35; ETN-89-94123) Avail: NTlS HC A03/MF A01 growth programs now used in the aircraft industry to ensure aircraft The prediction of the probability of failure due to excessive structural integrity. Several classic fracture mechanics problems cracking in aircraft structures was studied. Equivalent initial flaw are analyzed, and computational efficiency as compared to size (EIFS) distribution for an aluminum alloy (2024-T3) was conventional finite element techniques is investigated. Agreement determined using experimental crack growth data for small cracks. with analytic solutions as well as other numerical methods (finite The results show that the statistical basis for the EIFS determination element) is excellent. The computation efficiency was shown to must be considerably larger in order to draw any conclusions an improvement over existing methods. GRA regarding the generic properties of the EIFS-distribution. Parameter influences on the probability of failure are investigated by using a hypothetical aircraft structure. Results show that the effect of N89-21282# Air Force Inst. of Tech., Wright-Patterson AFB, varying the standard deviation of the extreme loads and the crack OH. School of Engineering. growth rate correlation time is almost negligible. ESA MACROCRACK-MULTIPLE DEFECT INTERACTION CONSIDERING ELASTIC, PLASTIC AND VISCOPLASTIC N89-20950'# National Aeronautics and Space Administration. EFFECTS M.S. Thesis Langley Research Center, Hampton, VA. LEROY K. SMITH Dec. 1988 129 p THE 3-D EULER AND NAVIER-STOKES CALCULATIONS FOR (AD-A203186; AFIT/GAE/AA/88D-35) Avail: NTlS ,HC A07/MF AIRCRAFT COMPONENTS A01 CSCL20K VEER N. VATSA, BRUCE W. WEDAN, and ELI TURKEL (Institute A finite element investigation was conducted to analyze an for Computer Applications in Science and Engineering, Hampton, axial tension specimen with collinear defects placed symmetrically VA.) In its Transonic Symposium: Theory, Application, and about a center crack. The material modeled was IN-718, a Experiment, Volume 1, Part 2 p 571-579 Mar. 1989 nickel-based superalloy used in jet engines. The effects of Avail: NTlS HC A22/MF A01 CSCL 20D crackldefect interaction were compared using elastic, elastic An explicit multistage Runge-Kuttatype of time-stepping scheme plastic, and viscoplastic constitutive models. A 2-D nonlinear finite is used for solving transonic flow past a transport type element code called SNAP was used. This program has the winglfuselage configuration. Solutions for both Euler and capability to simulate crack growth and closure by releasing or Navier-Stokes equations are obtained for quantitative assessment closing nodes along the crack plane. Elastic stress intensity of boundary layer interaction effects. The viscous solutions are solutions were developed for two different finite width specimens. obtained on both a medium resolution grid of approximately 270,000 The stress intensity versus crack length plots compared well with points and a find grid of 460,000 points to assess the effects of infinite theory. Results show that the defect can partially shield grid density on the solution. Computed pressure distributions are the crack from finite width effects. A critical spacing was also compared with the experimental data. Author noted where the stress intensity of the crack exceeded the stress intensity for the combined length of the crack and defect. The N89-21248# Air Force Inst. of Tech., Wright-Patterson AFB, defect has a prominent influence range equal to approximately OH. School of Engineering. one defect length for all constitutive models. The presence of a DEVELOPMENT OF A SHOCK CAPTURING CODE FOR USE defect increases the magnitude of the crack opening and AS A TOOL IN DESIGNING HIGH-WORK LOW ASPECT RATIO stresslstrain fields in front of the crack tip. GRA TURBINES M.S. Thesis MARK A. DRIVER Dec. 1988 76 p N89-21759'# Auburn Univ.. AL. Dept. of Algebra, Combinatorics (AD-A202706 AFIT/GAE/AA/88D-10) Avail: NTlS HC A05/MF and Analysis. A01 CSCL01A ROTORDYNAMIC ANALYSIS OF A BEARING TESTER A numerical algorithm is developed with the capability of RICHARD A. ZALIK In Alabama Univ., Research Reports: 1988 capturing shocks in the internal blade passages of a modern gas NASA/ASEE Summer Faculty Fellowship Program 25 p Dec. turbine. The algorithm uses MacCormack's explicit finite difference 1988 scheme to solve the two-dimensional form of the Euler equations. Avail: NTlS HC A99/MF E03 CSCL 131 Inlet and exit boundary conditions are developed that allow The properties of the solutions of a system of four coupled disturbances to propagate out of the computational domain without nonlinear differential equations that model the behavior of the reflection. Periodic boundary conditions are applied such that an rotating shaft of a bearing tester are studied. In particular, it is infinite cascade is modeled. The computed steady state solution shown how the bounds for the rotations of these equations can is compared with experimental data for a high-work low aspect be obtained from bounds for the solutions of the linearized ratio turbine. The ability to obtain a reasonably accurate blade equations. By studying the behavior of the Fourier transforms of loading diagram within a practical execution time is demonstrated. the solution, the approach to the stability boundary can also be 15 MATHEMATICAL AND COMPUTER SCIENCES predicted. These conclusions are verified by means of numerical graphics in atmospheric dispersion modeling, and pollution from solutions of the equations, and of power spectrum density (PSD) motor vehicles and aircraft at Stapleton International Airport are plots. Author discussed. Atmospheric Dispersion Modeling; Pollution from Motor Vehicles and Aircraft at Stapleton International Airport (Abbreviated Report). (FR) GRA
13 N89-21417'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. GEOSCIENCES GAS TURBINE ALTERNATIVE FUELS COMBUSTION CHARACTERISTICS Final Report Includes geosciences (general); earth resources; energy production R. JAMES ROLLBUHLER Feb. 1989 27 p and conversion; environment pollution; geophysics; meteorology (Contract DE-AI01-85CE-50111) and climatology; and oceanography. (NASA-TM-101470; E-4584; DOE/NASA/50111-3; NAS 1.15:101470) Avail: NTIS HC A03/MF A01 CSCL 21D An experimental investigation was conducted to obtain A8434028 combustion performance and exhaust pollutant concentrations for A PHYSICAL-STATISTICAL METHOD FOR THE PREDICTION specific synthetic hydrocarbon fuels. Baseline comparison fuels OF VERTICAL WIND SHEAR IN THE LOWER PART OF THE used were gasoline and diesel fuel number two. Testing was done ATMOSPHERIC BOUNDARY LAYER over a range of fuel to air mass ratios, total mass flow rates, and [FIZIKO-STATISTICHESKII SPOSOB PROGNOZA input combustion air temperatures in a flame-tube-type gas turbine VERTIKAL'NOGO SDVIGA VETRA V NlZHNEl CHASTI combustor. Test results were obtained in terms of released heat POGRANICHNOGO SLOIA ATMOSFERYI and combustion gas emission values. The results were comparable T. V. DAVIDOVICH IN: Problems of weather forecasting and to those obtained with the base fuels with variations being obtained diagnostics. Moscow, Gidrometeoizdat, 1988, p. 31 -41. In with changing operating conditions. The release of carbon particles Russian. refs during the tests was minimal. Author
A89-34359 WIND DAMAGE TO AIRPORTS - LESSONS LEARNED HENRY LIU and FARIBORZ NATEGHI (Missouri-Columbia, 15 University, Columbia) Journal of Aerospace Engineering (ISSN 0893-1321), vol. 1, April 1988, p. 105-116. refs MATHEMATICAL AND COMPUTER SCIENCES (Contract NSF CEE-83-05014) A postdisaster investigation of !he June 17, 1985 windstorm-induced damage to the Columbia Regional Airport in Includes mathematical and computer sciences (general); computer Missouri reveals that the storm was a microburst, rather than a operations and hardware; computer programming and software; tornado as originally thought; the private-aircraft tiedown system computer systems; cybernetics; numerical analysis; statistics and was seriously flawed, and road-surfacing gravel was the primary probability; systems analysis; and theoretical mathematics. source of damage to automobiles parked at the airport terminal. The gust factor of this type of wind event is much higher than normally assumed in structural design. The atmospheric pressure A89-33664 of the storm measured was greatly affected by the wind-generated MULTISPECTRAL TERRAIN BACKGROUND SIMULATION pressure of the building in which the barometer was housed. The TECHNIQUES FOR USE IN AIRBORNE SENSOR EVALUATION lessons to he learned frnm these data in enrjnenrinn nractica are MICHAEL WEINBERG, RONALD WOHLERS, JOHN CONANT, and discussed. O.C. EDWARD PUWERS (Aerodyne Research, Inc.. Billerica, MA) IN: Multispectral image processing and enhancement; Proceedings of A89-34888# the Meeting, Orlando, FL. Apr. 6-8, 1988. Bellingham, WA, Society THUNDERSTORM-GENERATED SOLITARY WAVES - A WIND of Photo-Optical Instrumentation Engineers, 1988, p. 243-252. SHEAR HAZARD A background simulation code called Aerie is discussed. Aerie R. J. DOVIAK (NOAA, National Severe Storms Laboratory. Norman, is designed to reflect the major sources of IR background clutter OK) and D. R. CHRISTIE (Australian National University, Canberra, that are of concern for the staring and scanning sensors being Australia) Journal of Aircraft (ISSN 0021-8669), vol. 26, May considered for various aircraft threat warning sensors. The Aerie 1989, p. 423-431. Previously cited in issue 07, p. 1060, Accession characteristics are summarized, and the three-dimensional earth no. A88-22520. refs simulation procedures and the scene data base preparation Aerie (Contract DOT-FA01-80-Y-10524; AF-AFOSR-83-0045) uses are described. Some sample scenes generated by Aerie are shown. C.D. N89-20557# Federal Aviation Administration, Washington, DC. Office of Environment and Energy. A89-33751"# Virginia Polytechnic Inst. and State Univ., A MICROCOMPUTER POLLUTION MODEL FOR CIVILIAN Blacksburg. AIRPORTS AND AIR FORCE BASES. MODEL APPLICATION A SMART PAlTERN RECOGNITION SYSTEM FOR THE ANDBACKGROUND AUTOMATIC IDENTIFICATION OF AEROSPACE ACOUSTIC H. M. SEGAL Aug. 1988 94 p Sponsored in part by AFESC, SOURCES Tyndall AFB, FL R. H. CABELL and C. R. FULLER (Virginia Polytechnic Institute (AD-A199794; FAA-EE-88-5; AFESC/ESL-TR-88-55) Avail: NTIS and State University, Blacksburg) AIAA, Aeroacoustics HC AO5/MF A01 CSCL 24A Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 10 p. refs This is the last of three reports describing the Emissions and (Contract NAG1-762) Dispersion Modeling System (EDMS). It consists of an accumulation (AIAA PAPER 89-111 4) of five key documents describing the development and use of the An intelligent air-noise recognition system is described that uses EDMS model. This report is prepared in accordance with pattern recognition techniques to distinguish noise signatures of discussions with the EPA and requirements outlined in the March five different types of acoustic sources, including jet planes, 27, 1980 Federal Register for submitting air quality models to the propeller planes, a helicopter, train, and wind turbine. Information EPA. Model development and use, the influence of aircraft for classification is calculated using the power spectral density operations on air quality at airports, the Simplex A (a simplified and autocorrelation taken from the output of a single microphone. atmospheric dispersion Model for airport use), microcomputer Using this system, as many as 90 percent of test recordings were
499 15 MATHEMATICAL AND COMPUTER SCIENCES correctly identified, indicating that the linear discriminant functions and aerodynamic grid points are derived; the transformation matrix developed can be used for aerospace source identification. I.S. furnishes a general two-dimensional interpolation scheme that is also applicable to pressure, temperature, or strains. O.C. A89-33765*# Planning Research Corp., Hampton, VA. A89-35044'# Pennsylvania State Univ., University Park. PREDICTION OF FULL SYSTEM HELICOPTER NOISE FOR A OBSERVER DESIGN FOR COMPENSATION OF MDHC 500E HELICOPTER USING THE ROTONET PROGRAM NETWORK-INDUCED DELAYS IN INTEGRATED D. S. WEIR, L. E. BECKER, and C. K. RUTLEDGE (Planning Research Corp., Hampton, VA) AIAA, Aeroacoustics Conference, COMMUNICATION AND CONTROL SYSTEMS R. LUCK and A. RAY (Pennsylvania State University, University 12th. San Antonio, TX, Apr. 10-12, 1989. 16 p. refs Park) IN: Recent advances in control of nonlinear and distributed (Contract NASl-18000) parameter systems, robust control, and aerospace control (AIAA PAPER 89-1135) applications; Proceedings of the Symposium, ASME Winter Annual The long-term goal of the NASA/U.S. helicopter industry Meeting, Chicago, IL, Nov. 27-Dec. 2, 1988. New York, American program designated 'Rotonet' is the achievement of a helicopter Society of Mechanical Engineers, 1988, p. 175-182. refs noise signature-prediction capability on the basis of helicopter (Contract NAG3-823; NSF DMC-87-07648) geometry and operating condition data. A prediction-validation data A method for compensating the effects of network-induced base is being compiled through flight testing of an MDHC 500E delays in integrated communication and control systems (ICCS) is helicopter; the data base will encompass acoustic spectra, proposed, and a finite-dimensional time-invariant ICCS model is noise-level time histories, and effective perceived noise levels developed. The problem of analyzing systems with time-varying incorporating actual meteorological conditions and helicopter and stochastic delays is circumvented by the application of a dynamics. An evaluation is made of the Rotonet system as currently deterministic observer. For the case of controller-to-actuator delays, defined, with a view to prospective developments. O.C. the observed design must rely on an extended model which represents the delays as additional states. R.R. A89-34132 STABILITY ANALYSIS OF THE MULTIPLE DISCRETE A89-35261 STABILIZATION SYSTEM OF AN ELASTIC FLIGHT VEHICLE FREQUENCY DOMAIN TECHNIQUES APPLIED TO THE [ANALIZ USTOlCHlVOSTl MNOGOKRATNOI DISKRETNOI IDENTIFICATION OF HELICOPTER DYNAMICS SISTEMY STABlLlZATSll UPRUGOGO LETATELNOGO P. YOUNG and R. J. PATTON (York, University, England) IN: APPARATA] International Conference on Control 88, Oxford, England, Apr. E. I. SOMOV and E. A. BONDARENKO Aviatsionnaia Tekhnika 13-15, 1988, Proceedings. London, Institution of Electrical (ISSN 0579-2975), no. 4, 1988, p. 26-30. In Russian. refs Engineers, 1988, p. 153-158. Research supported by SERC and A mathematical model is presented which describes, in state Royal Aircraft Establishment. refs space, a linear discrete flight vehicle stabilization system of the The application of frequency domain techniques to the multiple type with delay. The approach proposed here has been identification of helicopter dynamics using a scale-model helicopter used to analyze the stability of the closed-loop linear as a test system is described. Simulations of the helicopter using continuous/discrete gyroscopic stabilization system of a large flight linear models of longitudinal and lateral motion are detailed. A vehicle in the case of the practically complete absence of the comparison is made between the performances of two input signals natural damping of elastic vibrations of the structure. V.L. in identifying the transfer functions of the models. K.K.
A89-34569' Virginia Polytechnic Inst. and State Univ., A89-35283 Blacksburg. QUANTITATIVE DESIGN FOR SYSTEMS WITH UNCERTAINTY EFFICIENT OPTIMIZATION OF INTEGRATED AND CONTROL FAILURES AERODYNAMIC-STRUCTURAL DESIGN I. HOROWITZ, S. WANG (California, University, Davis), and C. R. T. HAFTKA, B. GROSSMAN, W. M. EPPARD, P. J. KAO, and HOUPIS (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, D. M. POLEN (Virginia Polytechnic Institute and State University, OH) IN: International Conference on Control 88, Oxford, England, Blacksburg) International Journal for Numerical Methods in Apr. 13-15, 1988, Proceedings. London, Institution of Electrical Engineering (ISSN 0029-5981), vol. 28, March 1989, p. 593-607. Engineers, 1988, p. 547-552. refs refs (Contract NSF ECS-86-08875) (Contract NAGl -505; NAGl -603) The application of quantitative feedback theory (OFT) to flight Techniques for reducing the computational complexity of control systems in which the uncertainty consists of varying flight multidisciplinary design optimization (DO) of aerodynamic structures conditions and possible failures of effectors is discussed. The are described and demonstrated. The basic principles of design procedure is discussed as well as application to flight control aerodynamic and structural DO are reviewed; the formulation of with effector failures. It was possible to obtain highly satisfactory the combined DO problem is outlined; and particular attention is designs because of the simple, direct, logical, and transparent given to (1) the application of perturbation methods to nature of QFT MlMO design. K.K. cross-sensitivity computations and (2) numerical approximation procedures. Trial DOs of a simple sailplane design are presented N89-20683'# Draper (Charles Stark) Lab., Inc., Cambridge, MA. in tables and graphs and discussed in detail. The IBM 3090 CPU RELIABILITY AND PERFORMANCE EVALUATION OF time for the entire integrated DO was reduced from an estimated SYSTEMS CONTAINING EMBEDDED RULE-BASED EXPERT 10 h to about 6 min. T.K. SYSTEMS Final Report ROBERT M. BEATON, MILTON E. ADAMS, and JAMES V. A. A89-34900# HARRISON Feb. 1989 35 p FINITE-SURFACE SPLINE (Contract NAS9-17560) KARl APPA (Northrop Corp., Aircraft Div., Hawthorne, CA) Journal (NASA-CR-181769; NAS 1.26:181769) Avail: NTlS HC A03/MF of Aircraft (ISSN 0021-8669), vol. 26, May 1989, p. 495, 496. A01 CSCLO9B refs A method for evaluating the reliability of real-time systems The present method employs uniform plate elements to containing embedded rule-based expert systems is proposed and represent a given platform by means of a number of quadrilateral investigated. It is a three stage technique that addresses the impact or triangular bending elements. A set of constraint conditions using of knowledge-base uncertainties on the performance of expert shape functions that are employed in the determination of the systems. In the first stage, a Markov reliability model of the system stiffness matrix of the plate element are established, in such a is developed which identifies the key performance parameters of way that the deformed plate passes through the given data points. the expert system. In the second stage, the evaluation method is Subsequently, a mapping matrix relating displacements at structural used to determine the values of the expert system's key
500 16 PHYSICS performance parameters. The performance parameters can be the interior of the cylinder was predicted on a mode-per-mode evaluated directly by using a probabilistic model of uncertainties basis. B.J. in the knowledge-base or by using sensitivity analyses. In the third and final state, the performance parameters of the expert A09-33712# system are combined with performance parameters for other ACOUSTIC FORCING OF THREE DIMENSIONAL SHEAR system components and subsystems to evaluate the reliability and LAYERS performance of the complete system. The evaluation method is MARTIN V. LOWSON (Bristoi, University, England) A!AA, demonstrated in the context of a simple expert system used to Aeroacoustics Conference, 12th. San Antonio, TX, Apr. 10-12, supervise the performances of an FDI algorithm associated with 1989. 13 p. refs an aircraft longitudinal flight-control system. Author (AIAA PAPER 89-1063) The response to acoustic forcing of the separated vortex flow over delta wings at low speeds has been experimentally N89-21592# Air Force Inst. of Tech., Wright-Patterson AFB, investigated in the 5000-50,000 Reynolds number range. Two OH. School of Engineering. distinct modes of instability were found for the shear layer, one SELECTION OF A FREQUENCY SENSITIVE QFT analagous to the classic Kelvin-Helmholtz response of the (QUANTITATIVE FEEDBACK THEORY) WEIGHTING MATRIX two-dimensional shear layer, and the other a streamwise instability USING THE METHOD OF SPECIFIED OUTPUTS M.S. Thesis which may correspond to the theory of Lin and Corcos (1984). At WILLIAM D. PHILLIPS Dec. 1988 112 p sufficiently high sound levels, the iiow was shown :G be en!ire!y (ADA202692; AFIT/GAE/ENG/88D-O1) Avail: NTlS HC AOG/MF A01 CSCL 01D disrupted. R.R. Use of Quantitative Feedback Theory (QFT) on a multiple input multiple output control system requires certain mathematical A89-33715'# National Aeronautics and Space Administration. properties of the plant matrix of transfer functions. In general, the Langley Research Center, Hampton, VA. plant matrix P(s) does not possess the necessary or desired AIRFOIL PROFILE DRAG INCREASE DUE TO ACOUSTIC mathematical properties for the QFT design to proceed. A EXCITATION frequency sensitive weighting matrix Delta(s) is used to transform JOHN G. SHEARIN (NASA, Langley Research Center, Hampton, the plant matrix P(s) into the equivalent plant matrix Pe(s) that VA) and MICHAEL G. JONES (Planning Research Corp., Hampton, does satisfy OFT requirements. In matrix notation, the relationship VA) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, between the equivalent plant, plant, and weighting matrix is Apr. 10-12, 1989. 7 p. refs Pe(s)=P(s) Delta(s). This thesis identifies the necessary and (AIAA PAPER 89-1069) desired characteristics of the equivalent plant Pe(s) for the QFT A two-dimensional airfoil (NACA-0009) is subjected to high process, explains the use of the Method of Specified Outputs intensity pure-tone sound over a 1-5 kHz frequency range while which generates the frequency sensitive weighting matrix Delta(s), immersed in a flow with 240 ft/sec velocity in a quiet flow facility and calculates several weighting matrices for a 3-input 2-output with a Reynolds number of 3 million. Wake dynamic pressures lateral-directional model of the F-16 aircraft. For several control are determined, and the momentum deficit is used to calculate a system failures, the mathematical structure of the failed equivalent two-dimensional drag coefficient. Significant increases in drag are plant matrices Pef(s) is examined for compliance with OFT observed when the airfoil is subjected to high-intensity sound at requirements. A weighting matrix Delta(s) is found that produces critical frequencies. The increased drag is accompanied by acceptable equivalent plant matrices for failures of down to 0.01 movement of the natural transition location. When the transition is percent of available control surface deflections. GRA fixed by roughness at 10 percent chord, no further transition movement is observed in response to an acoustic Tollmien-Schlichting disturbance. However, a 4 percent increase in the sectional drag coefficient is noted. It is believed to be due to the sound exciting the flow near the airfoil surface (shear layer), 16 thus causing the existing turbulence to become more intense, possess a higher mixing rate (momentum), and increase the skin PHYSICS friction. S.A.V.
Includes physics (general); acoustics; atomic and molecular A89-33716# physics; nuclear and high-energy physics; optics; plasma physics; ON SOUND GENERATION BY A JET FLOW PASSING A solid-state physics; and thermodynamics and statistical physics. SEMI-INFINITE AEROFOIL Y. P. GUO (Cambridge University, England) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 11 p. refs A89-33708'# National Aeronautics and Space Administration. (AIAA PAPER 89-1070) Langley Research Center, Hampton, VA. This paper studies the sound generated when a steadily NOISE REDUCTION OF A COMPOSITE CYLINDER convected jet flow impinges upon a fixed semi-infinite aerofoil. SUBJECTED TO RANDOM ACOUSTIC EXCITATION Far field sound pressures and the unsteady load experienced by FERDINAND W. GROSVELD and T. BEYER (NASA, Langley the aerofoil are analytically examined for both subsonic and Research Center; Planning Research Corp., Hampton, VA) AIAA, supersonic mean flows. Energetics is considered according to Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, definitions usually used in acoustics of moving flows. Author 1989. 12 p. refs (Contract NASI -18000) A89-33722'# Joint Inst. for Advancement of Flight Sciences, (AIAA PAPER 89-1049) Hampton, VA. Interior and exterior noise measurements were conducted on ASYMPTOTIC/NUMERICAL ANALYSIS OF SUPERSONIC a stiffened composite floor-equipped cylinder, with and without an PROPELLER NOISE interior trim installed. Noise reduction was obtained for the case M. K. MYERS and R. WYDEVEN (Joint Institute for Advancement of random acoustic excitation in a diffuse field; the frequency of Flight Sciences, Hampton, VA) AIAA, Aeroacoustics range of interest was 100-800-Hz one-third octave bands. The Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 11 p. refs measured data were compared with noise reduciion predictions (Contract NCCl-14) from the Propeller Aircraft Interior Noise (PAIN) program and from (AIAA PAPER 89-1078) a statistical energy analysis. Structural model parameters were An asymptotic analysis based on the Mach surface structure not predicted well by the PAIN program for the given input of the field of a supersonic helical source distribution is applied to parameters; this resulted in incorrect noise reduction predictions predict thickness and loading noise radiated by high speed propeller for the lower one-third octave bands where the power flow into blades. The theory utilizes an integral representation of the
50 1 16 PHYSICS
Ffowcs-Williams Hawkings equation in a fully linearized form. The 10-12, 1989. 16 p. refs asymptotic results are used for chordwise strips of the blade, (Contract NAG1-421) while required spanwise integrations are performed numerically. (AIAA PAPER 89-1088) The form of the analysis enables predicted waveforms to be The stochastic model theory of TAM (1987, 1989) for broadband interpreted in terms of Mach surface propagation. A computer shock associated noise was extended to include the effects of code developed to implement the theory is described and found forward flight. The theory was applied to the forward flight simulation to yield results in close agreement with more exact computations. experiments of Norum and Shearin (1984, 1986, and 1988). Good Author agreement is found between calculated and measured far-field noise spectra over the flight Mach number range of 0.0 to 0.4. A8933723# K.K. A LIFTING LINE MODEL FOR PROPELLER NOISE H. H. BROUWER (Nationaal Lucht- en Ruimtevaartlaboratorium, A89-33733# Amsterdam, Netherlands) AIAA, Aeroacoustics Conference, 12th. INTERACTION NOISE MECHANISMS FOR AN ADVANCED San Antonio, TX, Apr. 10-12, 1989. 9 p. refs PROPELLER - EXPERIMENTAL RESULTS (AIAA PAPER 89-1079) J. C. SIMONICH, D. C. MCCORMICK, and P. L. LAVRICH (United The possibility of calculating the sound field of a propeller Technologies Research Center, East Hartford, CT) AIAA, from knowledge of the spanwise lift distribution, is investigated. Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, An expression for the sound pressure is derived within a first-order 1989. 16 p. Research supported by United Technologies Corp. approximation for blades of high aspect ratio. In this approximation refs the propeller is described by a system of rotating lifting lines. (AIAA PAPER 89-1093) Numerical results for a six-bladed model propeller are compared The interaction mechanisms associated with wakes incident with experimental data and the results of a theory based on a upon rotating propfan blades are presently studied experimentally detailed description of the propeller geometry. It appears that for in order to generate a database for the improvement of a high-aspect-ratio propeller, the agreement is satisfactory. noise-prediction methodology components and achieve a deeper Author understanding of interaction-noise generation. A single, stationary, swept fan blade representative of a state-of-the-art profan was A8933724*# United Technologies Corp., Windsor Locks, CT. used to generate a wake upstream of a single-rotating propfan SOUND POWER SPECTRUM AND WAVE DRAG OF A and gather interaction noise measurements. A potentially dominant PROPELLER IN FLIGHT interaction noise-source mechanism, related to a velocity defect D. B. HANSON (United Technologies Corp., Hamilton Standard associated with the leading edge vortex of the swept blade, was Div., Windsor Locks, CT) AIAA, Aeroacoustics Conference, 12th, identified. This vortex defectlblade interaction generated significant San Antonio, TX, Apr. 10-12, 1989. 17 p. Research supported by blade surface pressure fluctuations. O.C. United Technologies Corp. refs (Contract NAS3-23720) (AIAA PAPER 89-1081) A89-33734# Theory is presented for the sound power and sound power INTERACTION NOISE MECHANISMS FOR ADVANCED spectrum of a single rotation propeller in forward flight. Calculations PROPELLERS - ANALYTICAL EVALUATION are based on the linear wave equation with sources distributed D. J. PARZYCH (United Technologies Corp., Hamilton Standard over helicoidal surfaces to represent effects of blade thickness Div., Windsor Locks, CT) and P. L. LAVRICH (United Technologies and steady loading. Sound power is distributed continuously over Research Center, East Hartford, CT) AIAA, Aeroacoustics frequecy, as would be expected from Doppler effects, rather than Conference, 12th. San Antonio, TX, Apr. 10-12, 1989. 8 p. in discrete harmonics. The theory is applied to study effects of (AIAA PAPER 89-1094) sweep and Mach number in propfans. An acoustic efficiency is Theoretical lift response and unsteady noise radiation models defined as the ratio of radiated sound power to shaft input power. were evaluated by comparing predictions with test results of a This value is the linear estimate of the effect of wave drag due to model three bladed Prop-Fan located downstream of stationary the supersonic blade section speeds. It is shown that the acoustic swept and unswept vanes. The wakes shed by the upstream vane efficiency is somewhat less than 1 percent for a well designed were measured and used as input to the theories, therefore propfan. Author eliminating the ambiguity of unsteady air angles at the downstream rotor. The vane wake interaction noise was isolated by subtracting A8933726# the measured rotor-alone noise from the measured total noise. It FINITE ELEMENT MODELLING OF SHEARED FLOW EFFECTS was found that the lift response and noise radiation model evaluated ON THE RADIATION CHARACTERISTICS OF ACOUSTIC showed good agreement with the measured results. Author SOURCES IN A CIRCULAR DUCT JAMES EDWARD STECK and WALTER EVERSMAN A8933736# (Missouri-Rolla, University, Rolla) AIAA, Aeroacoustics NEAR-FIELD NOISE OF A PUSHER PROPELLER Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 12 p. refs P. L. SPENCE, M. B. TRACY, and M. A. TAKALLU (Planning (AIAA PAPER 89-1085) Research Corp., Hampton, VA) AIAA, Aeroacoustics Conference, A mixed finite element method is proposed for solving a 12th, San Antonio, TX, Apr. 10-12, 1989. 13 p. refs third-order partial differential equation governing the acoustic (AIAA PAPER 89-1096) pressure field in a duct containing radially sheared subsonic flow. A theoretical/computational code is used to predict the near The approach used here is to treat this equation as a coupled field noise generated by a propeller in a pusher configuration. pair of differential equations, one a second-order equation in terms The wake due to the pylon upstream of the Propeller is generated of acoustic density and the other a first-order equation in terms using a similarity formulation. Unsteady loads on the propeller are of an artificial variable representing the effects of the sheared determined by implementing a time-dependent variation of the flow. The finite element code is refined using numerical sectional angles of attack and Mach numbers along with the experiments, and results are presented for a specific propeller periodic circulation due to shed vortices from the propeller's trailing and duct geometry. V.L. edge. Using this unsteady loading, noise predictions are performed and compared, along with steady loading noise predictions, to A8933729'# Florida State Univ., Tallahassee. existing flight test measurements. The measured data were FORWARD FLIGHT EFFECTS ON BROADBAND SHOCK obtained from earlier flight tests of a general aviation aircraft with ASSOCIATED NOISE OF SUPERSONIC JETS engines installed in pusher configurations. The predicted results CHRISTOPHER K. W. TAM (Florida State University, Tallahassee) show that the unsteady loading effects are more pronounced out AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. of the plane of the propeller disk. The steady loading is not sufficient
502 16 PHYSICS to account for the level of measured data and the unsteady loading different propeller configurations with the annoyance of noise must be included in the prediction. Author conventional turboprop and jet aircraft flyover noise. It was found that advanced turboprops with single-rotating propellers were, on A8933737'# Missouri Univ., Rolla. average, slightly less annoying than the other aircraft. Fundamental THE EFFECT OF THE WIND TUNNEL WALL BOUNDARY frequency and tone-to-broadband noise ratio affected annoyance LAYER ON THE ACOUSTIC TESTING OF PROPELLERS response to advanced turboprops but the effects varied with WALTER EVERSMAN (Missouri-Rolla, University, Rolla) AIM, propeller configuration and noise metric. The addition of duration Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, corrections and corrections for tones above 500 Hz to the noise 1989. 10 p. Research supported by NASA. refs measurement procedures improved prediction ability. Author (AIAA PAPER 89-1097) An approximation based on the representation of the boundary AW-3376~ layer by lamina of uniform flow with suitable interlayer boundary AN ANALYTICAL MODEL FOR THE PREDICTION OF MR/TR conditions is shown to be accurate, efficient, and compatible with INTERACTION NOISE finite element formulations. The approximation has been HORMOZ TADGHlGHl (McDonnell Douglas Helicopter Co., Mesa, implemented using existing codes to produce a model for assessing AZ) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, the suitability of the acoustic environment in a wind tunnel for the Apr. 10-12, 1989. 15 p. refs acoustic testing of propellers. It is found that, witin suitable acotis:ic (Aim ?APER 89-! !SO) treatment and with measurements made near the propeller and A detailed analytical study of helicopter tail rotor (TR) noise well removed from the walls, the free field directivity and level due to interactions with the main rotor (MR) tip vortices is can be reproduced with good fidelity. V.L. presented. The airloads due to MR/TR vortex interaction are modeled assuming an airfoil of infinite span cutting through a A89-33738# moving vortex. The investigation included the use of rotor free FUSELAGE BOUNDARY LAYER EFFECTS ON SOUND wake analysis to accurately define the geometry of the interacting PROPAGATION AND SCATTERING discrete tip vortices from the main rotor. A comparison of the H. Y. LU (Boeing Commercial Airplanes, Seattle, WA) AIAA, airloads and acoustic predictions with measurements is given. In Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, particular, the predictions of waveform features and peak amplitude 1989. 10 p. refs for the interactions inboard of the blade tip compared favorably (AIAA PAPER 89-1098) with measured data. B.J. The effects of a fuselage and its boundary layer on sound propagation to the fuselage surface and on sound scattering in A89-33763# the farfield were analyzed. A hard-wall infinite cylinder with a INTEGRATING THE ACOUSTIC ANALOGY FOR SUPERSONIC boundary layer of both velocity and temperature variations was ROTATING SURFACES modeled to simulate the fuselage of an aircraft in flight. Examples VALANA L. WELLS (Arizona State University, Tempe) AIAA, for a monopole noise source outside the boundary layer showed Aeroacoustics Conference, 12th, San Antonio, TX. Apr. 10-12, considerable noise attenuation on the cylindrical surface forward 1989. 16 p. refs of the source and much less effect on the downstream side. Data (AIAA PAPER 89-1133) from a transonic wind tunnel test showed the same trends. For This paper discusses the analytical characteristics of waveforms enroute and airport community noise, the boundary layer alters produced by rotating surface sources with tip Mach number the interference pattern caused by the fuselage. Author greather than 1. The analysis covers both monopole and quadrupole sources which have the greatest importance for A8433759# prediction of high-speed rotor noise. By using idealized source EXPERIMENTAL INVESTIGATION OF ROTOR WAKEBTATOR distributions over the rectangular surfaces, the results show that INTERACTION NOISE GENERATION BY ACOUSTIC MODE the Lighthill/Curle analogy with time derivatives taken outside the MEASUREMENTS integrals poses no additional difficulty attributable to numerical T. ZANDBERGEN (Nationaal Lucht- en Ruimtevaartlaboratorium, error. Author Amsterdam, Netherlands) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, 1989. 10 p. Research supported by the Nederlands lnstituut voor Vliegtuigontwikkeling en A89-33764'# Florida Atlantic Univ., Boca Raton. Ruimtevaart. refs THE PREDICTION OF BLADE WAKE INTERACTION NOISE (AIAA PAPER 89-1126) BASED ON A TURBULENT VORTEX MODEL The rotor wakelstator interaction noise generation was STEWART A. L. GLEGG (Florida Atlantic University, Boca Raton) investigated using acoustic measurements in a low-speed wind AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, Apr. tunnel, downstream of a rotor/stator combination; some acoustic 10-12, 1989. 9 p. refs measurements were also carried out in the intake duct of the (Contract NAG1-71 5) wind tunnel model and outside the model. The blade passing (AIAA PAPER 89-1134) fEclUf?ncy harmonics were found to be dominated by the regular Blade wake interaction is defined as the broadband noise rotor/stator interaction modes. In addition, cut-off rotor/stator generated by the interaction of helicopter rotor blades with their interaction modes were observed; the origin of these is considered own wake. Experimental observations have shown that this is a to be in the highly nonuniform flow downstream of the rotor/stator. strong function of advance ratio and tip path plane angle. This An additinal noise source occurred due to the lock-in of rotor paper describes how this noise source can be associated with vortex shedding and acoustic spinning modes. I.S. the blade vortex interactions in the forward sector of the rotor. Measured levels of turbulence in the vortex core are used to A8433761'# National Aeronautics and Space Administration. predict the broadband noise levels with some success. However, Langley Research Center, Hampton, VA. more detailed information on the turbulence spectrum and the ADVANCED TURBOPROP AIRCRAFT FLYOVER NOISE trajectory of the shed vortices is required before more accurate ANNOYANCE - COMPARISON OF DIFFERENT PROPELLER noise predictions can be made. Author CONFIGURATIONS DAVID A. MCCURDY (NASA, Langley Research Center, Hampton, A89-33766# VA) AIAA, Aeroacoustics Conference, 12th, San Antonio, TX, NOISE AND INSTABILITY WAVES IN SUPERSONIC JETS IN Apr. 10-12, 1989. 12 p. refs THE PROXIMITY OF FLAT AND CYLINDRICAL WALLS (AIAA PAPER 89-1128) K. K. AHUJA, J. A. MCCAULLEY, and C. K. W. TAM (Lockheed A laboratory experiment was conducted to compare the Aeronautical Systems Co., Marietta, GA) AIAA, Aeroacoustics annoyance of flyover noise from advanced turboprop aircraft having Conference. 12th, San Antonio, TX, Apr. 10-12, 1989. 12 p,
503 16 PHYSICS
Research supported by Lockheed Internal Research and can account for the fundamental and first harmonics of the blade Development Program. refs frequencies. It is suggested that higher frequences may be due to (AIAA PAPER 89-1136) the absorption of atmospheric turbulence. R.R. The effect of the proximity of fuselage on the noise radiated from a model supersonic unheated round jet exhausting parallel A89-35388 to the fuselage wall was investigated using acoustic measurements, PREDICTION OF WAKE-INTERACTION NOISE IN complemented by phase-locked measurements of the instability AXIAL-FLOW MACHINES - APPLICATION TO HELICOPTER waves in the jet, in a flow visualization facility. Results showed FENESTRON [PREDICTION DU BRUIT D’INTERACTION DE that, as the jet is brought close to the fuselage surface, drastic SILLAGES DANS LES MACHINES TOURNANTES - changes in the noise occur only after the nozzle to fuselage APPLICATION AU FENESTRON DHELICOPTERE] distance becomes about one jet exit diameter or less. The effect FRANCElTE FOURNIER and MICHEL ROGER (Lyon, Ecole of the fuselage curvature (investigated using a flat and a cylindrical Centrale, Ecully, France) Academie des Sciences (Paris), Comptes fuselage) on the radiated noise was found to be insignificant. Rendus, Serie II - Mecanique, Physique, Chimie, Sciences de I.S. I’Univers, Sciences de la Terre (ISSN 0249-6305), vol. 308, no. 9, March 2, 1989, p. 831-834. In French. refs A wake model based on experimental measurements is used A89-33768# to determine the noise generated by rotor-stator interactions in an TWINJET SCREECH SUPPRESSION axial-flow machine. Application of the model to the tail rotor of a L. L. SHAW (USAF, Flight Dynamics Laboratory, Wright-Patterson helicopter shows that the 3rd to 9th harmonics of the blade passing AFB. OH) AIAA, Aeroacoustics Conference, 12th, San Antonio, frequency can be attributed to this noise source. Neither the first TX, Apr. 10-12, 1989. 12 p. refs two harmonics nor the large-band noise are attributed to wake (AIAA PAPER 89-1140) interactions. R.R. Results are reported from an experimental investigation of screech noise in twin jet-engine configurations and of methods N89-20776*# Sverdrup Technology, Inc., Cleveland, OH. for suppressing this noise. The acoustic mechanisms of screech generation and amplification are reviewed; the experimental setup NOISE GENERATED BY A FLIGHT WEIGHT, AIR FLOW (in which acoustic and phase-averagedschlieren data are obtained CONTROL VALVE IN A VERTICAL TAKEOFF AND LANDING on a 4.7-percent scale model of an F-15 aircraft equipped with AIRCRAFT THRUST VECTORING SYSTEM Final Report axisymmetric nozzles) is described; and the results are presented RONALD G. HUFF Feb. 1989 55 p Prepared in cooperation with Huff (Ronald G.) and Associates, North Olmsted, OH in extensive graphs and flow visualizations. Screech tones with amplitudes up to 163 dB are measured, with amplification by up (Contract NAS3-25266) to 20 dB due to interplume coupling. Suppression by active noise (NASA-(33-182232; E-4556; NAS 1.16:182232) Avail: NTlS HC cancellation and by shifting the nozzle exit planes is found to be A04/MF A01 CSCL 20A ineffective; small tabs mounted in the exit plane are very effective Tests were conducted in the NASA Lewis Research Center’s in suppressing screech from both single and twin jets, while a Powered Lift Facility to experimentally evaluate the noise generated small secondary jet is effective for single-jet screech. T.K. by a flight weight, 12 in. butterfly valve installed in a proposed vertical takeoff and landing thrust vectoring system. Fluctuating pressure measurements were made in the circular duct upstream A89-33770# and downstream of the valve. This data report presents the results HUB TO TIP VARIATIONS OF COUNTER ROTATING of these tests. The maximum overall sound pressure level is PROPELLER INTERACTION NOISE generated in the duct downstream of the valve and reached a H. V. L. PATRICK (Tennessee, University, Knoxville) and R. T. value of 180 dB at a valve pressure ratio of 2.8. At the higher NAGEL (North Carolina State University, Raleigh) AIAA, valve pressure ratios the spectra downstream of the valve is broad Aeroacoustics Conference, 12th, San Antonio, TX, Apr. 10-12, banded with its maximum at 1000 Hz. Author 1989. 12 p. refs (AIAA PAPER 89-1145) N89-20777’# National Aeronautics and Space Administration. Axial and circumferential flow velocity components were Langley Research Center, Hampton, VA. measured at discretepoints between hobby-craft model ACOUSTIC TEST OF A MODEL ROTOR AND TAIL ROTOR: counter-rotating propellers using a single sensor hot-film RESULTS FOR THE ISOLATED ROTORS AND COMBINED anemometer. Coherence analysis was used to determine CONFIGURATION characteristics of the relationship between the far-field radiated R. M. MARTIN, C. L. BURLEY, and J. W. ELLIOTT Feb. 1989 noise and the measured flow velocity components at the primary 73 P aerodynamics interaction tones. Tests were performed in an (NASA-TM-101550; NAS 1.15:101550) Avail: NTlS HC A04/MF open-jet anechoic wind tunnel at a free-stream speed of 0.08 A01 CSCL20A Mach number with a 3 x 4 CRP configuration. It was determined Acoustic data from a model scale main rotor and tail rotor that the degree of linearity in the flow-noise relation varied radially experiment in the NASA Langley 14 by 22 Foot Subsonic Tunnel 1 along the propeller blade span. Author are presented for the main rotor and trail rotor in isolation and for the two rotors operating together. Results for the isolated main A89-35385 rotor show the importance of the rotor flapping conditions on PREDICTION OF POTENTIAL NOISE INTERACTIONS IN mid-frequency noise content. High levels of main rotor retreating AXIAL-FLOW MACHINES - APPLICATION TO THE side blade-vortex interaction noise are shown to radiate HELICOPTER FENESTRON [PREDICTION DU BRUIT downstream of the model. The isolated tail rotor noise results D’INTERACTIONS POTENTIELLES DANS LES MACHINES show the dominance of harmonic noise in the thrusting direction. TOURNANTES - APPLICATION AU FENESTRON The occurrence of tail rotor broadband noise is seen by the DHELICOPTERE] broadening of the tail rotor harmonics and is attributed to fuselage FRANCElTE FOURNIER and MICHEL ROGER (Lyon, Ecole wake turbulence. The combined main and tail rotor data are Centrale, Ecully, France) Academie des Sciences (Paris), Comptes presented to show the dominance of each rotor’s different noise Rendus, Serie 11 - Mecanique, Physique, Chimie, Sciences de sources at different directivity locations. Author I’Univers, Sciences de la Terre (ISSN 0249-6305), vol. 308, no. 8, Feb. 23, 1989, p. 703-706. In French. N89-20779’# National Aeronautics and Space Administration. A method for predicting the far-field noise created in a rotor Lewis Research Center, Cleveland, OH. by the flow around cylindrical obstacles (such as support arms) UNSTEADYBLADEPRESSUREMEASUREMENTSONA placed downstream of the rotor is proposed. Application of the MODEL COUNTERROTATION PROPELLER method to helicopter rotor blades shows that this noise source LAURENCE J. HEIDELBERG and RICHARD P. WOODWARD Apr.
504 16 PHYSICS
1989 22 p Presented at the 12th Aerocoustics Conference, of fundamental research into methods to quiet explosive noise San Antonio, TX, 10-12 Apr. 1989; sponsored inpart by AlAA and materials used to reduce the noise from explosions. This (NASA-TM-102002; E-4684; NAS 1.1511 02002; AIAA-89-1144) report reproduces journal articles regarding this USA-CERL Avail: NTlS HC A03/MF A01 CSCL 20A research in chronoiogical order. GRA In an exploratory effort an advanced counterrotation propeller instrumented with blade-mountedpressure transducers was tested in the NASA Lewis 9- by 15-Foot Anechoic Wind Tunnel at a simulated takeoff and landing speed of Mach 0.20. The propeller's aft diameter was reduced to investigate possible noise reductions resulting from reduced blade row interaction with the tip vortex. The propeller was tested at three blade row spacings at fixed blade setting angles, at themaximum blade row spacing at higher blade setting angles and at propeller axis angles attack to the flow up to + or - 16 deg. A limited number of unsteady blade surface pressure measurements were made on both rotors of the model counterrotation propeller. Emphasis was placed on determining the effects of rotor-rotor interactions on the blade surface pressures. A unique method of processing the pressure signals was developed that enables even weak interaction waveforms and spectra to be separated from the total signal. The interaction on the aft rotor was many times stronger than thaton the forward rotor. The fundamental rotor interaction tone exhibited complicated behavior but generally increased with rotational speed and blade setting angle and decreased with rotor spacing. With the propeller axis at an angle to the flow, the phase response of the aft rotor appeared to be significantly affected by the presence of the forward rotor. Author
N89-21628'# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, OH. COMPARISON OF PROPELLER CRUISE NOISE DATA TAKEN IN THE NASA LEWIS 8- BY 6-FOOT WIND TUNNEL WITH OTHER TUNNEL AND FLIGHT DATA JAMES H. DllTMAR Apr. 1989 23 p Presented at the 12th Aeroacoustics Conference, San Antonio, TX, 10-12 Apr. 1989; sponsored in part by AlAA (NASA-TM-101976; E-4676; NAS 1.151 01 976; AIAA-89-1059) Avail: NTlS HC A03/MF A01 CSCL 20A The noise of advanced high speed propeller models measured in the NASA 8- by 6-foot wind tunnel has been compared with model propeller noise measured in another tunnel and with full-scale propeller noise measured in flight. Good agreement was obtained for the noise of a model counterrotation propeller tested in the 8- by 6-foot wind tunnel and in the acoustically treated test section of the Boeing Transonic Wind Tunnel. This good agreement indicates the relative validity of taking cruise noise data on a plate in the 8- by 6-foot wind tunnel compared with the free-field method in the Boeing tunnel. Good agreement was also obtained for both single rotation and counter-rotation model noise comparisons with full-scale propeller noise in flight. The good scale model to full-scale comparisons indicate both the validity of the 8- by 6-foot wind tunnel data and the ability to scale to full size. Boundary layer refraction on the plate provides a limitation to the measurement of forward arc noise in the 8- by 6-foot wind tunnel at the higher harmonics of the blade passing tone. The use of a validated boundary layer refraction model to adjust the data could remove this limitation. Author
N89-21632# Army Construction Engineering Research Lab., Champaign, IL. ATTENUATION OF BLAST WAVES USING FOAM AND OTHER MATERIALS Final Report RICHARD RASPET, S. K. GRIFFITHS, JOSEPH M. POWERS, HERMAN KRIER, and TIMOTHY D. PANCZAK Nov. 1988 72 P (AD-A203148; CERL-TM-N-89/01) Avail: NTlS HC A04/MF A01 CSCL 191 Noise is a problem everywhere the Army trains or tests with large weapons or helicopters. Noise and hazardous waste have been listed as the major problems facing the Army into the 21st century. Research at the US. Army Construction Engineering Research Laboratory (USA-CERL) is aimed at solving the total noise problem for the Army. This report documents several years
505 SUBJECT INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
Typical Subject Index Listing
ACOUSTIC MEASUREMENT Near wakes of advanced turbopropellers Acoustic test of a model rotor and tail rotor: Results [AIAA PAPER 89-10951 p 441 A89-33735 for the isolated rotors and combined configuration Near-fieldnoise of a pusher propeller SUBJECT HEADING [NASA-TM-101550] p 504 N89-20777 [AIM PAPER 89-10961 p 502 A89-33736 ACOUSTIC PROPAGATION The effect of the wind tunnel wall boundary layer on On sound generationby a jet flow passing a semi-infinite the acoustic testing of propellers aerofoil [AIAA PAPER 89-10971 p 503 A89-33737 I'r' [AlAA PAPER 89-10701 p 501 A8943716 An analytical model for the prediction of MRITR AEROSPACE PLANES ACOUSTIC PROPERTIES interaction noise --- main rotorltail rotor Tecnnoiogy issues asSirCi6ied iiiili fieling :he na:iSca! kcuustic ihaiactaiis:ics a! coi;n:c::z!a!ina fans !vm model scale tests jAiAA PAPER ae-ii3Gj p 503 A89-33752 [NASA-TM-101386] p 43 N89-10123 [AIAA PAPER 89-11421 p 477 A89-33769 Integrating the acoustic analogy for supersonic rotating ACOUSTICS surfaces Comparison 01 propeller cruisa noise data taken in the [AIAA PAPER 89-11331 p 503 A89-33763 7-1 NASA Lewis 8- by 6-loot wind tunnel with other tunnel The prediction of blade wake interaction noise based and flight data on a turbulent vortex model [ NASA-TM-101976] p 505 N89-21628 [AIAA PAPER 89-11341 p 503 A8943764 ACTIVE CONTROL Noise and instability waves in supersonic jets in the In-flight experiments on the active control of proximity of flat and cylindrical walls propeller-inducedcabin noise [AIAA PAPER 89-1 1361 p 503 A89-33766 [AIAA PAPER 89-10471 p468 A89-33706 Hub to ti variations of counter rotating propeller Full-scale demonstration tests of cabin noise reduction interaction noise The subject heading ISa key to the subject content using actie vibration control [AIM PAPER 89-11451 p 504 A89-33770 01 the document The title is used to provide a [AIAA PAPER 89-10741 p 468 A89-33719 Noise levels of a combined bypass-proplan engine in Adaptive active control of enclosed sound fields in elastic description of the subject matter When Ihe title IS the far sonic field p 478 A89-34150 cylinders via vibrational inputs --- noise attenuation AERODYNAMIC BALANCE insufficiently descriptive of document content, a research for advanced turboprop aircraft An experimental study of transonic buffet of a title extension IS added, separated from the tltle [AIAA PAPER 89-10751 p 469 A89-33720 supercritical airfoil with trailing edge flap Propeller modellingeffects on interbr noise in cylindrical by three hyphens The (NASA or AIAA) accession [ AD-AZO31891 p458 N89-20968 cavities with application to active control AERODYNAMIC BRAKES number and the page number are included in each [AIAA PAPER 89-11231 p 469 A8933757 Analysis of decelerators in motion using computational entry to assist the user in locating the abstract In Active Conrrol law synthesis for flexible aircraft fluid dynamics p 482 A89-35045 the abstract section If applicable. a report number [AIAA PAPER 89-09311 p 447 A89-35241 is also included as an aid in identilying the docu- Load alleviation on transport aircraft using acceleration feedback p 471 A89-35299 AERODYNAMIC CHARACTERISTICS ment Under any one subject headmg. the acces- Active conIrol helicopter aeromechanical and Flight test of XRAE-1 to establish aerodynamic data sion numbers are arranged in sequence with the aeroelastic instabilities p 483 N89-20149 p468 A89-33562 Viscosity effects in the generation of the litting force AlAA accession numbers appearing lirsl ACTUATOR DISKS Transmission and reflection on pressure waves by of aerodynamic wing profiles p 442 A89-34114 compressor and turbine stages, based on an actuator-disk Numerical modeling of transonic flow of a viscous gas model in a plane channel with a sudden expansion [AD-A2035131 p 496 N89-20426 p 442 A89-34149 A ACTUATORS Analysis of separated flow past a thin profile in the case Actuation constraints in multivariable flight control of translational oscillations p 442 A89-34151 ABORT TRAJECTORIES systems p 483 N89-20998 Numerical solutions for the flowiietd around a Abort landing guidance trajectories in the presence of ADAPTIVE CONTROL counter-rotating propeller p 445 A89-34887 windshear p 481 A89-32725 Adaptive active control of enclosed sound fields in elastic Transonic buffet of a supercriticalairfoil with trailing-edge cylinders via vibrational inputs --- noise attenuation flap p 446 A89-34893 ABSORBERS (MATERIALS) research advanced turboprop aircraft for A comparison of secondary flow in a vane cascade and Attenuation of blast waves using foam and other [AIAA PAPER 89-10751 p 469 A89-33720 a curved duct p 446 A89-34934 materials Adaptive control of the grinding of large gas turbine [AD-A203148] p 505 N89-21632 blades p 492 A89-34144 Effect of 90 degree flap on the aerodynamics of a twoglement airfoil p 446 A89-35053 ACCELERATION TOLERANCE ADAPTIVE FILTERS A preliminary characterization of parachute wake Aerial delivery 01 personnel in ground proximity A self-adaptive computational method for transonic turbulent flow past a real projectile p 443 A89-34730 recontact [AIM PAPER 89-06871 p 461 A89-35207 [AIAA PAPER 89-08971 p 447 A89-35214 ACOUSTIC ATTENUATION AERIAL RECONNAISSANCE Complementary minis- Skyeyeand Phoenix, anovekw Prediction of parachute collapse due to wake Twin-jet screech suppression of their multi-mission coverage p 467 A89-33558 recontact [AIM PAPER 89-11401 p 504 A89-33768 Linescan 2000 - Tomorrow's sensor today [AIM PAPER 89-0901I p 447 A89-35218 ACOUSTIC EMISSION p 475 A89-33574 A combined method for calculating supersonic flow of Prediction of wake-interaction noise in axial-flow AEROACOUSTICS an ideal gas past a wing with a supersonic blunt leading machines - Application to helicopter lenestron Acoustic forcing of three dimensional shear layers edge p 448 A89-35430 p 504 A89-35388 [AIAA PAPER 89-10631 p 501 A89-33712 Effect of the asymmetry of boundary conditions on ACOUSTIC EXCITATION On sound generationby a jet flow passing a semi-infinite boundary layer flow near a cone at angle of attack Noise reduction of a composite cylinder subjected to aerofoil p 448 A89-35433 random acoustic excitation [AIM PAPER 89-10701 p 501 A89-33716 Thin axisymmetric caverns in supersonic flow p 449 A89-35435 [AIAA PAPER 89-10491 p 501 A89-33708 Asymptoticlnumerical analysis of supersonic propeller High Reynolds number incompressible flow simulation Airfoil profile drag increase due to acoustic excitation noise [AIAA PAPER 89-10781 p 501 A89-33722 about parachute canopies and similar bluff bodies [AIM PAPER 89-10691 p 501 A69-33715 p450 N89-20096 Sound power spectrum and wave drag of a propeller Sonic fatigue and nonlinear response of stiffened Evaluation 01 VSAERO in prediction of aerodynamic in flight panels characteristics of helicopter hub fairings [AIM PAPER 89-10811 p 502 A89-33724 [AIAA PAPER 89-11011 p 492 A89733741 [ NASA-TM-1010481 p 451 N89-20098 Finite element modelling of sheared flow effects on the Aerodynamics of two-dimensional slotted bluff bodies ACOUSTIC FATIGUE radiation characteristics of acoustic sources in a circular Sonic fatigue and nonlinear response of stiffened [ DE89-0072881 p 452 N89-20105 duct Airframelpropulsion integration characteristics at panels [AIAA PAPER 69-10851 p 502 A89-33726 [AIAA PAPER 89-11011 p 492 A89-33741 transonic speeds p 453 N89-20926 Forward flight effects on broadband shock associated A study of transonic drag reduction of a blunt cylinder Sonic fatigue-resistant damped laminated structures noise of supersonic jets by a cylinder probe [AIAA PAPER 89-11021 p 469 A89-33742 [AIAA PAPER 89-10881 p 502 A89-33729 [ AD-A202557] p 458 N89-20965 Identifyingsonic fatigue prone structureson a hypersonic Interactionnoise mechanisms for an advanced propeller AERODYNAMIC CONFIGURATIONS
Transatmospheric Vehicle (TAW ~ Experimental results The development of a preliminary sizing method for [AIAA PAPER 89-1103] p 469 A89-33743 [AIM PAPER 89-10931 p 502 A8943733 unmanned air vehiiles p 460 A89-33564 AERODYNAMIC DRAG SUBJECT INDEX
~ffectof the design of a two-row nozzle ring on the AERODYNAMIC STALLING efficiency of a turbine stage of medium rotor solidity Computational study of the effect of cascade parameters p 477 A89-34140 on stall propagation in axial compressors Evolution of the manta-ray parachute p 444 A89-34737 [AIAA PAPER 89-09061 p 462 A89-35221 AERODYNAMICS Supersonic flow past caret wings and elements of Business aviation and new technologies star-shaped bodies at angles of attack and bank p 438 A89-35379 p 449 A89-35481 Two-dimensional Navier-Stokes solution of the flow over bumentation of two- and three-dimensional a thick supercritical airfoil with strong shock-induced hypersonic shock wavelturbulent boundary layer separation interaction flows [ADA203331 I p 459 N89-20971 [ NASA-TM.1010751 p 451 N89-20100 Icing considerations for HALE (High Altitude. Long Transonic CFD applications at Boeing Endurance) aircraft p 453 N89-20929 [ AD-A2025841 p 464 N89-20975 Applied transonics at Grumman p 454 N89-20931 Integrated aerodynamicldynamic optimization of Vector potential methods p 455 N89-20939 helicopter rotor blades AERODYNAMIC DRAG [NASA-TM-I01 553 1 p 473 N89-20982 Airfoil profile drag increase due lo aCOuStiC eXCitatiOn [AIAA PAPER 89-10691 p 501 A89-33715 AEROELASTICITY Stability analysis of the multiple discrete stabilization Induced drag and the ideal wake of a lifting wing p 446 A89-34898 system of an elastic flight vehicle p 500 A89-34132 Parachutes .Yesterday. today. and tornorrow A linear computer code to determine aeroelastic stability [AIM PAPER 89-08801 p 463 A89-36019 in airfoil cascades at unsteady flow conditions p 444 A89-34746 Effect of riblets upon flow separation in a subsonic diffuser Aeroelastic deformation effects on the stopped-rotor [AD-A2031781 p 458 N89-20967 dynamics of an X-wing aircraft p 482 A89-34897 Numerical simulation of flow over iced airfoils Structural optimization for aermlastic control [AD-A203291I p 458 N89-20969 effectiveness p 470 A89-34899 AERODYNAMIC FORCES Finite-surface spline p 500 A89-34900 Modeling of parachute opening - An experimental Aeroelastic divergence of front-free-aft-fixedelastic strip investigation p 460 A89-34891 parallel to uniform flow p 495 A89-35097 AERODYNAMIC HEAT TRANSFER Some low-speed flutter characteristics of simple Local heat transfer in internally cooled turbine airfoil low-aspect-ratio delta wing models leading edge regions. I - Impingement cooling without film [NASA-TM-1015471 p 450 N89-20094 coolant extraction. II . Impingement cooling with film Active control helicopter aeromechanical and coolant extraction p 494 A89-34932 aeroelastic instabilities p 483 N89-20149 Computation of external. hypersonic. three-dimensional Additional development of the XTRAN3S computer flowfield and heat transfer p 494 A89-34935 program AERODYNAMIC INTERFERENCE [NASA-CR-l817d3] p 452 N83-20922 Wall-interference corrections for parachutes in a closed Aeroelaslic modeling for the FIT team FIA-18 wind tunnel simulation [AlAA PAPER 89-09001 p 485 A89-35217 [NASA-TM-1015691 p 475 N89-20991 Turbulence and modeling in transonic flow AERONAUTICAL ENGINEERING p 456 N89-20951 Flight research and testing p 453 N89-20927 Wall interference assessment and corrections Preliminary design of a modular unmanned research p 457 N89-20958 vehicle. Volume 1: System design document Two-measured variable method for wall interference [AD-A202765] p 474 N89-20987 assessmentlcorrection p 457 N89-20959 AERONAUTICS Comparison of airfoil results from an adaptive wall test Mathematical research at the Aeronautical Research section and a porous wall test section Laboratories 1939.1960 p 437 A89-32982 p 457 N89-20960 AEROSPACE ENGINEERING Capabilibes of wind tunnels with two-adaptive walls to DFVLR. Annual Report 1987 p 437 A89-32775 minimize boundary interference in 3-D model testing AEROSPACE PLANES p 486 N89-20961 Technology requirements for hypersonic airbreathing AERODYNAMIC LOADS aircraft p 468 A89-33626 Application of harmonic analysis method lo research AEROSPACE VEHICLES on rotor airloads p 467 A89-33139 Sonic fatigue and nonlinear response of stiffened panels Calculation of blade-vortex interaction airloads on helicopter rotors p 446 A89-34895 [AIAA PAPER 89-1101 ] p 492 A89-33741 AEROTHERMOCHEMISTRY Measurements of individual parachute loads in a Computalional methods for hypersonic flows - Special clustered parachute system techniques and real gas effects p 441 A89-33640 [AIAA PAPER 89-09231 p 463 A89-35233 Numerical Simulation of three-dimensional hypersonic An experimental investigationof the aerodynamic loads viscous flows p 441 A89-33644 on cambered plates AEROTHERMODYNAMICS [AIAA PAPER 89.09351 p 447 A89-35244 A numerical method for predicting hypersonic Numerical analysis of three-dimensional non rigid flowfields p 440 A89-33634 wings Toward improved durability in advanced aircraft engine [AIAA PAPER 89-09071 p 450 A89-36022 hot sections Hub and blade structural loads measurements of an [NASA-TM-4087] p 479 N89-20135 aircraft SA34912 helicopter NASA HOST project overview p 479 N89-20136 [NLR-MP-87047-U1 p 476 N89-20130 [ NASA-TM-1010401 p 472 N89-20124 Assessment. development, and application of AIRCRAFT Method to predict external store carriage loads at combustor aerothermal models p 479 N89-20138 Aerospace vehicle design. Spacecraft Section final transonic speeds p 473 N89-20945 Review and assessment of the database and numerical project reports Integrated aerodynamic/dynamic optimization of modeling for turbine heat transfer p 479 N89-20139 [NASA-CR-184741] p 471 N89-20121 helicopter rotor blades Views on the impact of HOST p 480 N89-20144 AIRCRAFT ACCIDENT INVESTIGATION [NASA-TM-101553] p 473 N89-20982 Experimental examination of the aerothermal Experimental investigationof electrostaticfire accidents AERODYNAMIC NOISE performanceoftheT-lOtestcellatNAS(NavalAirStation), after aircraft landing and preventive measures Cubi Point Interaction noise mechanismsfor an advanced propeller p 460 A89-34885 ! - Experimental results [AD-A203887] p 487 N89-21005 Advanced techniques used in Kanishka aircraft accident High density fuel effects [AIM PAPER 89.10931 p 502 A89-33733 investigation p 460 A89-35200 [ AD-A202426] p 490 N89-21125 Sound generation and flow interaction of vortices with AFTERBODIES Aircraft accident data. US general aviation. calendar year an airfoil and a flat plate in transonic flow Navier-Stokes calculations of scramjet-afterbody p 449 A89-36006 flowfields p 443 A89-34732 AERODYNAMIC STABILITY Base flow investigation behind axi-andnon-axisymmetric The develooment of the oanel stabilized sloned-sauare blunt bodies parachute [ ISL-CO-246/87] p 452 N89-20103 [AIAA PAPER 89-08941 p 461 A89-35212 AGING (MATERIALS) A mnd tunnel and computer investigation of the low Investigation of the service and age lives of U.S. Army speed aerodynamic characteristics of the prone escape personnel parachutes system (PRESS) [AIAA PAPER 89-09151 p 462 A89-35227 [AD-A202768] p 475 N89-20988 AH-10 HELICOPTER Flight controller design with nonlinear aerodynamics. Coupled rotorlfuselage dynamic analysis of the AH-1G large parameter uncertainty and pilot compensation helicopter and correlation with flight vibrations data [AD-A2027271 p 484 N89-21000 [NASA-CR-I81 7231 P 497 N89-20512
A-2 SUBJECT INDEX AIRCRAFT NOISE
AIRCRAFT ACCIDENTS Efficient optimization of inlegrated Life modeling of thermal barrier coatings for aircraft gas Aircraft accident data. US general aviation, calendar year aerodynamic-structuraldesign p 500 A89-34569 turbine engines p 480 N89-20143 1986 Structural optimization for aeroelastic control Views on the impact of HOST p 480 N89-20144 [ PB89-1214531 p 463 N89-20108 effectiveness p 470 A89-34899 AIRCRAFT GUIDANCE Aircraft accident reports: Brief format, US civil and 8-2 - The end of the long road toward a 'stealth Abort landing guidance trajectories in the presence of foreign aviation, issue number 12 of 1986 accidents bomber' p 438 A89-35100 windshear p 481 A8942725 Designing with advanced fibrous composites [ PB88-9169021 p 464 N89-20109 Design aspects of a naval RPV recovery system Aircrafi accident reports. brief format, US civil and foreign p 470 A89-35197 High performance escape capsules p 484 A89-33568 aviation. issue number 14 of 1986 accidents AIRCRAFT HAZARDS [PB88-916904] p 464 N89-20110 [AIAA PAPER 89-08781 p 470 A89-35202 Thunderstorm-generated solitary waves - A wind shear Aircrafi acddenl report: Continental Airlines, Inc., Flight ONERA research on civil aircraft p 438 A89-35376 hazard p 499 A89-34888 1713, McDonnell Douglas DC-9-14, N626TX. Stapleton The future of the civil aviation industry International Airport, Denver, Colorado, November 15, p 438 A89-35377 Controlling severed helicopter blades during emergency 1987 Aerospace vehicle design, Spacecraft Section final escape p 471 A89-35842 [PB88-910411] p 464 N89-20112 project reports Icing considerations for HALE (High Altitude, Long AIRCRAFT COMMUNICATION [ NASA-CR-I847421 p 472 N89-20122 Endurance) aircraft Improved computer simulation of the TCAS 3 circular Aerospace vehicle design. Spacecraft Section [AD-A202584] p 464 N89-20975 array mounted on an aircraft [NASA-CR-I847431 p 472 N89-20123 AIRCRAFT HYDRAULIC SYSTEMS [NASA-CR-184907] p 496 N89-20363 Power efficient hydraulic systems. Volume 1: Study Power efficient hydraulic systems. Volume 1 : Study AIRCRAFT COMPARTMENTS phase phase In-flight experiments on the active control Of [AD-A2038991 p 472 N89-20127 [AD-A2038991 p 472 N89-20127 propeller-induced cabin noise Power efficient hydraulic systems. Volume 2: Hardware Power efficient hydraulic systems. Volume 2 Hardware [AIM PAPER 89-10471 p 468 A89-33706 demonstration phase demonstration phase Full-scale demonstration tests of cabin noise reduction [AD-A2039001 p 473 N89-20128 [AD-A203900] p 473 N89-20128 using active vibration control Transonic Symposium: Theory, Application, and AIRCRAFT INSTRUMENTS [AIM PAPER 89-10741 p 468 A89-33719 Experiment, Volume 1, Part 1 Design of an airborne optic fiber data bus system [NASA-CP-3020-VOL-I-PT-l] p 453 N89-20925 Model size requirements for finite element prediction p 475 A89-33148 Airframelpropulsion integration characteristics at of low-frequency cabin noise and vibration Aviation displays p 476 A89-34443 [AIAA PAPER 89-10761 p 469 A89-33721 transonic speeds p 453 N89-20926 AIRCRAFT LANDING Interior noise in the untreated Gulfstream II PropfanTest Flight research and testing p 453 N89-20927 Abort landing guidance trajectories in the presence of Assessment (PTA) aircraft Shock-boundary-layerinteraction in flight windshear p 481 A89-32725 [AIM PAPER 89-11191 p 469 A89-33754 p 453 N89-20928 Cabin noise control ground tests for UHB aircraft Transonic CFD applications at Boeing Transient dynamics of aircraft propellers during [AIM PAPER 89-11211 p 469 A89-33755 p 453 N89-20929 touch-down impact p 470 A89-34509 AIRCRAFT CONFIGURATIONS The application of CFD for military aircraft design at Experimental investigation of electrostaticfire accidents Ttm US. Navy unmanned air vehicle program transonic speeds p 454 N89-20930 after aircraft landing and preventive measures p 437 A89-33555 Applied transonics at Grumman p 454 N89-20931 p 460 A89-34885 The Theta Beta - Design of a system -.-remotely piloted Transonics and fighter aircraft: Challenges and AIRCRAFT MAINTENANCE civil aircraft p 468 A89-33561 opportunities for CFD p 454 N89-20932 Full-scalefatigue testing of aircraft structures Aerodynamic analysis of three advanced configurations Computation of aircraft component flow fields at p 485 A89-33802 using the TranAir full-potentialcode p 455 N89-20944 transonic Mach numbers using a three-dimensional Fast, in-situ repair of aircraft panel components Steady and unsteady transonic small disturbance Navier-Stokes algorithm p 454 N89-20933 p 438 A89-34896 analyss of realistic aircraft configurations Transonic aerodynamic design experience Life with the older aircraft p 438 A89-35125 p 473 N89-20946 p 454 N8Y-20934 Environment-assisted aerospace fatigue problems in EulerlNavier-Stokescalculations of transonic flow past Wave drag due to lift for transonic airplanes The Netherlands fixed- and rotary-wing aircraft configurations p 455 N89-20938 [ NLR-MP-8800441 p 439 N89-20087 p456 N89-20948 Transonic propulsion system integration analysis at AIRCRAFT MANEUVERS Preliminary dean of a modular unmanned research McDonnell Aircraft Company p 481 N89-20943 Design aspects of a naval RPV recovery system vehicle. Volume 1: System design document Performance optimization for rotors in hover and axial p 484 A89-33568 [AD-A202765] p 474 N89-20987 flight Variable structure control laws for aircraft manoeuvres Tailless aircrafi performance improvementswith relaxed [NASA-CR-1775241 p 459 N89-20973 p 482 A89-35286 static stability Hypersonic drone design: A multidisciplinary Continuous-discrete filtering for systems with Markovian [NASA-CR-I81 8061 p 483 N89-20999 experience switching coefficients AIRCRAFT CONSTRUCTION MATERIALS [ NASA-CR-1847401 p 473 N89-20981 [ NLR-MP-87076-UI p 465 N89-20117 Air Force tribology programs p 491 A89-33448 AIRCRAFT DETECTION Numerical simulation of the flow field over delta wings Metallic limitations in aircraft engines - The rational return Aircraft tracking with dual TACAN with leading edge blowing p 453 N89-20924 to the stone age p 477 A8943485 LAU-AZUZM/ 1 p 400 IYUY-LUYUU AIRCRAFl MODELS Noise reduction of a composite cylinder subjected to AIRCRAFT ENGINES A mathematical model of aircraft spin and results of random acoustic excitation Titanium PM attributes and potential for aircraft engine its computer integration p 481 A89-34130 [AIM PAPER 89-10491 p 501 A89-33708 applications p 487 A89-33465 Transient dynamics of aircraft propellers during Structural mechanics: Contemporary state and Metallic limitations in aircraflengines - The rationalreturn touch-down impact p 470 A89-34509 prospects for development (selected portions) to the stone age p 477 A89-33485 AIRCRAFT NOISE [ AD-AI 987661 p 497 N89-20498 Evolution of a small turbine engine family for unmanned In-flight experiments on the active control of AIRCRAFT CONTROL aerial vehicles p 477 A8943570 propeller-induced cabin noise Stability analysis of the multiple discrete stabilization Acoustic characteristics of counterrotating fans from [AIAA PAPER 89-10471 p 468 A89-33706 System of an elastic flight vehicle p 500 A89-34132 model scale tests Installation effects on propeller wakelvortex induced Cockpit automation p 460 A89-34444 [AIAA PAPER 89-11421 p 477 A89-33769 structure-borne noise transmission Active control law synthesis for flexible aircraft Fatigue testing of gas turbine components [AIAA PAPER 89-10721 p 468 A89-33717 p 482 A89-35045 p 485 A89-33804 Full-scaledemonstration tests of cabin noise reduction Power efficient hydraulic systems. Volume 2 Hardware Characteristics of the lormation of benz(a)pyrene in the using active vibration control demonstration phase combustion chambers of aviation gas turbine engines [AIM PAPER 89-10741 p 468 A89-33719 [ AD-A203900] p 473 N89-20128 p 488 A89-34119 Adaptive active controlof enclosedsound fields in elastic On-board automatic aid and advisory for pilots of An experimentalstudy of the rate characteristicsof brush cylinders via vibrational inputs --- noise attenuation control-impaired aircraft p 483 N89-20150 seals in comparison with labyrinth seals research for advanced turboprop aircraft Numerical simulation of the flow field over delta wings p 492 A89-34136 [AIAA PAPER 89-10751 p 469 A89-33720 with leading edge blowing p 453 N89-20924 Some aspects of the numerical modeling of the Model size requirements for finite element prediction Tailless aircraft performance improvementswith relaxed nonstationary heat conductivity of gas turbine of low-frequency cabin noise and vibration static stability components p 477 A89-34139 [AlAA PAPER 89-10761 p 469 A89-33721 [ NASA-CR-1818061 p 483 N89-20999 Effect of the design of a two-row nozzle ring on the Asymptoticlnumerical analysis of supersonic propeller AIRCRAFT DESIGN efficiency of a turbine stage of medium rotor solidity noise Canadair SentinellSaa Sentinel rotary wing RPV. IV p 477 A89-34140 [AIAA PAPER 89-10781 p 501 A89-33722 p 467 A89-33556 An analytical-experimentalstudy of ring gap losses in A lifting line model for propeller noise Some aspects of the development and operational small axial-flow turbines p 478 A89-34141 [AIAA PAPER 89-10791 p502 A8933723 testing of the Sprite system p 467 A89-33557 Adaptive control of the gnnding of large gas turbine Finite element modelling of sheared flow effects on the Complementaryminis - Skyeye and Phoenix, an overview blades p 492 A89-34144 radiation characteristics of acoustic sources in a circular of their multi-mission coverage p 467 A89-33558 Noise levels of a combined bypass-propfan engine in duct The Theta Beta - Design of a system --.remotely piloted the far sonic field p 478 A89-34150 [AlAA PAPER 89-10851 p 502 A89-33726 civil aircraft p 468 A89-33561 8-2 - The end of the long road toward a 'stealth Forward flight effects on broadband shock associated The computer controlled system for multi-drone bomber' p 438 A89-35100 noise of supersonic jets performingformation flight in a same aerial zone Toward improved durability in advanced aircraft engine [AIAA PAPER 89-10881 p 502 A89-33729 p 481 A89-33566 hot sections Fuselage boundary layer effects on sound propagation Model size requirements for finite element prediction [NASA-TM-40871 p 479 N89-20135 and scattering Of low-frequencycabin noise and vibralion NASA HOST project overview p 479 N89-20136 [AlAA PAPER 89-10981 p 503 A89-33738 [AIM PAPER 89-10761 p 469 A89-33721 Review and assessment of the database and numerical A smart pattern recognition system for the automatic Cockpit-crew systems design and integration modeling for turbine heat transfer p 479 N89-20139 identificationof aerospace acoustic sources p 476 A89-34446 Structural analysis applications p 480 N89-20141 [AlAA PAPER 89-11141 P 499 A8943751
A-3 SUBJECT INDEX
Interior noise in the untreated Gulfstream II Propfan Test Matching Power Spectra Density (PSD)-design load --- Quench sensitivity of airframe aluminum alloys Assessment (PTA) aircraft aircraft structures [ NLR-MP-88003-UI p 489 N89-20231 [AIAA PAPER 89-11191 p 469 A8943754 [ NLR-MP-87059-Ul p 472 N89-20126 AIRFRAMES Cabin noise control ground tests for UHB aircraft A (13)C NMR analysis of the effectsof electron radiation Some aspects of the development and operational [AIM PAPER 89-1121 1 p 469 A89-33755 on graphitelpolyetherimide composites testing of the Sprite system p 467 A8943557 Propeller modellingeffects on interior noise in cylindrical [ NASA-CR-1828181 p 489 N89-20205 Load alleviation on transport aircraft using acceleration cavities with application to active COntrOl Electromagnetic properties of ice coated surfaces feedback p 471 A8945299 [AIM PAPER 89-11231 p 469 A8943757 [ NASA-CR-1847801 p 495 N89-20355 AIRLINE OPERATIONS Advanced turboprop aircraft flyover noise annoyance - Structural mechanics: Contemporary state and Life with the older aircraft p 438 A8935125 Comparison of different propeller configurations prospects for development (selected portions) Aviation safety: Measuring how safely individual airlines [AIM PAPER 89-1128) p A89-33761 503 [AD-A198766] p 497 N89-20498 operate Twin-jet screech suppression Current status of flight simulation fatigue crack growth [GAOlRCED-88-61] p 464 N89-20974 [AIAA PAPER 89-11401 p 504 A89-33768 AIRPORT PLANNING concepts Hub to tip variations of counter rotating propeller Heliport system planning guidelines [ NLR-MP-88001-U ] p 497 N89-20521 interaction noise [AD-A199081 ] p 486 N89-21003 [AIM PAPER 89-11451 p 504 A89-33770 Estimation of the Equivalent Initial Flow Size (EIFS) AIRPORTS Importance of engine as a source of helicopter external distribution and prediction of failure probabilities for Wind damage to airports - Lessons learned different parameter variations noise p 499 A89-34359 [AlAA PAPER 89-11471 p 470 A89-33771 [ FFA-TN-1987-351 p 498 N89-20525 A microcomputerpollution model for civilian airports and Prediction of wake-interaction noise in axial-flow AIRCRAFT WAKES Air Force bases. Model application and background machines - Application to helicopter fenestron Installation effects on propeller wakelvoctex induced [AD-A1997941 p 499 N89-20557 p 504 A8945388 structure-borne noise transmission AIRSPEED Noise generated by a flght weight, air flow control valve [AIM PAPER 89.10721 p 468 A8933717 The development of a preliminary sizing method for in a vertical takeoff and landing aircraft thrust vectoring Interactin noise mechanisms for advanced propellers unmanned air vehicles p 468 A89-33564 system - Analytical evaluation The Norton P73 rotary RPV engine [NASA-CR-1822321 p 504 N89-20776 [AIAA PAPER 89-10941 p 502 A8943734 p 477 A89-33565 Attenuation of blast waves using foam and other Prediction of parachute collapse due to wake ALGORITHMS materiels recontact Computation of aircraft component flow fields at [ ADA2031481 p 505 N89-21632 [AIM PAPER 89.0901 ] p 447 A89-35218 transonic Mach numbers using a three-dimensional AIRCRAFT PERFORMANCE AIRDROPS Navier-Stokes algorithm p 454 N89-20933 Predicting the effects of aircraft icing The development and testing of the HISAC parachute Generation of unstructuredgrids and Euler solutions for p 460 A89-33825 recovery system complex geometries p 455 N89-20941 Load alleviation on transport aircraft using acceleration [AIAA PAPER 89-09211 p 462 A89-35231 A digital rate controller for the control reconfigurable feedback p 471 A89-35299 AIRFOIL OSCILLATIONS combat aircraft designed using quantitative feedback Tailless aircraft performance improvements with relaxed On a method for solving integral equations of theory static stability lifting-surface theory for oscillating high-speed propellers [AD-A203050] p 484 N89-21001 [NASA-CR-181 8061 p 483 N89-20999 p 439 A89-33100 Development of a shock capturing code for use as a AIRCRAFT PRODUCTION Analysis of separated flow past a thin profile in the case tool in designing high-work low aspect ratio turbines New wings, new ways p 471 A89-35825 of translational ascillatims p 442 A89-34151 [AD-A202706] p 498 N89-21248 AIRCRAFT RELIABILITY Experimental investigation of transonic oscillating ALUMINUM ALLOYS The reliability analysis of aircraft structures cascade aerodynamics Rapidly solidified aluminum alloys for high p 467 A89-33146 [ NASA-TM-1019931 p 478 N89-20133 temperaturelhighstiffness applications Civilian RPVs - Eye in the sky or pie in the sky? AIRFOIL PROFILES p 488 A8943474 p 437 A89-33560 Single and multi-elementairfoils in an isotropic turbulent Quench sensitivity of airframe aluminum alloys Life with the older aircraft p 438 A89-35125 outer flow p 439 A89-33383 [ NLR-MP-88003-Ul p 489 N89-20231 Aimocthiness and flght characteristics evaluation of an Airfoil profile drag increase due to acoustic excitation AMPLITUDES improved engine air filtration system on the UH-1H [AIM PAPER 89-10691 p 501 A8943715 Subharmonic and fundamentalhigh amplitudeexcitation helitM Optimal profile selection in the design of a subsonic of an axisymmetric jet [AD42034461 p 480 N89-20145 turbine cascade p 442 A89-34152 [ NASA-TM-1019461 p 452 N89-20920 Awlication of the boundary element method to fatigue Effect of jet grid turbulence on turbulent boundary layer ANGLE OF AlTACK crack growth analysis heat transfer p 494 A8944930 Numerical instabilities in the calculation of laminar [AD42025651 p 498 N89-21270 Local heat transfer in internally cooled turbine airfoil separation bubbles and their implications AIRCRAFT SAFETY leading edge regions. I - Impingement cooling without film p 445 A89-34819 We with the older aircraft p 438 A89-35125 cwlanl extraction. II . Impingement cooling with film Effect of 90 degree flap on the aerodynamics of a Controlling severed helicopter blades dunng emergency coolant extraction p 494 A8934932 two-element airfoil p 446 A89-35053 -Cape p 471 A89-35842 Effect of 90 degree flap on the aerodynamics of a ANNULI Advanced Recovery Sequencer (ARS) --- for ejection two-element airfoil p 446 A8945053 An entrance region friction factor model applied to seats p 471 A89-35843 The correlation between Reynolds stress and turbulent annular seal analysis - Theory versus experiment for A pfonated escape system for fighter aircraft kinetic energy in the near wake of a symmetric airfoil smooth and honeycomb seals p 463 A8945845 p 448 A89-35393 [ASME PAPER 88-TRIB-41] p 493 A8934798 Aviation safety: Measuring how safely individual airlines A numerical investigation of steady transonic cascade APPLICATIONS OF MATHEMATICS operate flow in turbomachinery p 448 A89-35417 Mathematical research at the Aeronautical Research [GAOlRCED-88-61] p 464 N89-20974 An airfoil pitch apparatus-modelingand control design Laboratories 1939-1960 p 437 A89-32982 A digital rate controller for the control reconfigurable [NASA-TM-101 0761 p 496 N89-20386 ARGON combat aircraft designed using quantitative feedback Wall interference assessment and corrections Argon shrouded plasma coatings for gas tubine theory p 457 N89-20958 applications p 491 A89-33487 [AD-A203050] p484 N89-21001 Comparison of airfoil results from an adaptive wall test ASCENT TRAJECTORIES AIRCRAFT SPECIFICATIONS section and a porous wall test section Aircraft tracking with dual TACAN The US. Navy unmanned air vehicle program p457 N89-20960 [AD-A202647] p466 N89-2U980 p 437 A8943555 Numerical simulation of flow over iced airfoils.. ASYMPTOTIC METHODS AIRCRAFT SPIN [AD-A203291] p 458 N89-20969 Asymptoticlnumerical analysis of supersonic propeller Spin testing methods in flight p 470 A89-35196 AIRFOILS noise AIRCRAFT STRUCTURES Flight test of XRAE-1 to establish aerodvnamic data [AIAA PAPER 89-10781 p 501 A8943722 The reliability analysis of aircraft structures p 468 A89-33562 Asymptotic methods for internal transonic flows p 467 A89-33146 On sound generation by a jet flow passing a semi-infinite p 455 N89-20937 The Theta Beta - Design of a system --- remotely piloted aerofoil Wave drag due to lift for transonic airplanes civil aircraft p468 A89-33561 [AIAA PAPER 89-10701 p 501 A89-33716 p 455 N89-20938 Full-scale fatigue testing of components and structures A new look at Theodorsen’s method in aerofal theory ATMOSPHERIC CIRCULATION -- Book p 485 A8943801 p 443 A89-34621 A physical-statisticalmethod for the predictionof vertical Full-scale fatigue testing of aircraft structures Tethered parafoil test technique wind shear in the lower part of the atmospheric boundary p 485 A89-33802 [AIAA PAPER 89-09031 p 462 A89-35219 layer p 499 A8944028 Natural vibrations of cylindricalshells with a rectangular Bound vortex boundary layer control with application ATMOSPHERIC ELECTRICITY wtout p 492 A8934126 to V/STOL airplanes p 449 A8945994 Triggered lightning strikes to aircraft and natural Formulation and solution of axisymmetric problems in Sound generation and flow interaction of vortices mth intracloud discharges p 460 A89-35158 the statics of multilayer shells of revolution with contact en airfoil and a flat plate in transonic flow ATMOSPHERIC TURBULENCE interaction between layers p 492 A8944129 p 449 A89-36006 A digital simulation technique for Dryden atmospheric Developments and trends in three-dimensional mesh turbulence model Ensuring the quality of the covering surface in the case p 439 A8943142 Thunderstorm-generatedsolitary waves ~ A wind shear of riveted joints with high radial interference generatwn p 455 N89-20940 Unsteady force calculations on circular cylinders and p 492 A89-34159 hazard p 499 A89-34888 elliptical airfoils with circulation control AlTACK AIRCRAFT Fuel holdup and component diffusivity in a cooled [UMAERO-87-37] p 457 N89-20962 Shock-boundary-layerinteraction in flight cylindrical tank p 488 A89-34694 Numencal Simulation of flow over iced airfoils P 453 N89-20928 Fast, in-situ repair of aircraft panel components [AD-A203291] p 458 N89-20969 AUDIO FREQUENCIES p 438 A8944896 AIRFRAME MATERIALS Performance analysis of the fiber distributed data Quantitativefractography - Possibilitiesand applications On the design of biaxially stiffened composite plates interface in the super cockpit audio world in aircraft research p 495 A89-35074 p 493 A89-34867 [AD-A202535] p 474 N89-20985 A-4 SUBJECT INDEX CARRIER TO NOISE RATIOS
AUGMENTATION High Reynolds number incompressible flow simulation Two-dimensionalNavier-Stokes solution of the flow over Design of robust multivariable helicopter control laws about parachute canopies and similar bluff bodies a thick supercntical airfoil with strong shock-induced for handling qualities enhancement p 482 A8945297 p 450 N89-20096 separation AUTOMATIC CONTROL Aerodynamics of two-dimensional slotted bluff bodies [AD-A203331] p 459 N89-20971 Cockpit automation p 460 A8944444 [ DE89-0072881 p 452 N89-20105 BOUNDARY LAYER STABILITY BLUNT BODIES On-board automatic aid and advisory for pilots of Hypersonic boundary-layer transition control-impairedaircraft p 483 N89-20150 Thin aerofoils with high-incidence flaps or blunt trailing p 441 A89-33646 edges p 445 A8944749 AUTOMATIC PILOTS Three-dimensionalboundary-layer transition study Base flow investigationbehind axi-and non-axisymnetric p 447 A89-35195 Multivariable design of a bank-to-turn autopilot for blunt bodies command guidance p 482 A89-35301 Stability of compressible boundary layers [ ISLGo-246/87] p 452 N89-20103 p 456 N89-20953 Implementationof a transputer-basedflight controller A study of transonic drag reduction of a blunt cylinder Secondary three-dimensionalinstability in compressible p 482 A8945302 by a cylinder probe AUTOMOBILES boundary layers p 456 N89-20954 [AD-A2025571 p 458 N89-20965 Investigation of the development of laminar Full-scale fatigue testing of components and StruCtureS BLUNT LEADING EDGES -.-Book p 485 A89-33801 boundary-layer instabilities along a cooled-wall cone in A combined method for calculating supersonic flow of hypersonic flows an ideal gas past a wing with a supersonic blunt leading AVIATION METEOROLOGY [AD-A202587] p 458 N89-20966 A physical-statisticalmethod for the predictionof vertical edge p 448 A89-35430 BOUNDARY LAYER TRANSITION wind shear in the lower part of the atmospheric boundary BODY-WING CONFIGURATIONS Laminar-turbulenttransition problems at high speeds layer p 499 A89-34028 Model for investigation of helicopter fuselage influence p 441 A89-33645 on rotor flowfields p 445 A89-34883 AVIONICS Hypersonic boundary-layer transition Applied transonics at Grumman p 454 N89-20931 Desipn o! 5." airborne optic fiber data bus system p 441 A89-33646 p 475 A8943148 Computation of ai;c:aE cozpcnen! !!cw fields at Xi%;! p:o!ile &ss increase dun to acoustic excitation Complementary minis- Skyeye and Phoenix, an overview transonic Mach numbers using a three-dimensional [AIAA PAPER 89-10691 p 501 A8943715 Navier-Stokesalgorithm p 454 N89-20933 of their multi-missioncoverage p 467 A89-33558 Numerical instabilities in the calculation of laminar Transonic aerodynamic design experience Falconet target RPV operations p 437 A89-33559 separation bubbles and their implications p 454 N89-20934 p 445 A89-34819 Low cost avionic system for UMA --- unmanned Wave drag due to lift for transonic airplanes aircraft p 475 A89-33571 Three-dimensionalboundary-layer transition study p 455 N89-20938 p 447 A8945195 Electronics in civil aviation Method lo predict external store carriage loads at [NLR-MP-87009-U] p 476 N89-20129 Turbulization of a high-velocity boundary layer by a transonic speeds p 473 N89-20945 AXIAL FLOW projection p 448 A8945434 Euler/Navier-Stokescalculations of transonic flow past BOUNDARY LAYERS An analytical and numerical study of axial flow fixed- and rotary-wingaircraft configurations compressor instability p 478 N89-20131 Shock-boundary-layer interaction in flight p 456 N89-20948 AXIAL FLOW TURBINES p 453 N89-20928 BOEING 747 AIRCRAFT Transitional flow on axial turbomachine blading BRAKES (FOR ARRESTING MOTION) Advanced techniques used in Kanishka aircraft accident p 445 A89-34811 Analysis of decelerators in motion using computational investigation p 460 A89-35200 Prediction of wake-interaction noise in axialflow fluid dynamics BOMBER AIRCRAFT machines - Application lo helicopter fenestron [AIAA PAPER 89-0931 1 p 447 A89-35241 8-2 The end of the long road toward a 'stealth p504 A89-35388 . BROADBAND bomber' p 438 A8945100 AXISYMMETRIC FLOW Forward flight effects on broadband shock associated BOMBS Subharmonic and fundamental high amplitude excitation noise of supersonic jets Advanced techniques used in Kanishka aircraft accident of an axisymmetric jet [AIAA PAPER 89-10881 p 502 A8943729 investigation p460 A89-35200 [NASA-TM-101946] p 452 N89-20920 BUFFETING BOUNDARYELEMENTMETHOD Comparison of 3D computation and experiment for Transonic bunet of a supercriticalairfoil with trailingedge Application of the boundary element method to fatigue non-axisymmetric noales flap p 446 A89-34893 [NASA-CR-182245] p 452 N89-20921 crack growth analysis An experimental study of transonic buffet of a [AD-A202565] p 498 N89-21270 supercritical airfoil with trailing edge flap BOUNDARYLAYERCONTROL [ AD-AZO31891 p 458 N89-20968 B Bwnd vortex boundary layer control with application BUTTERFLYVALVES to V/STOL airplanes p 449 A8945994 Noise generated by a flight weight. air flow control valve E1AIRCRAFT Effect of riblets upon flow separation in a subsonic in a vertical takeoff and landing aircraft thrust vectoring 8-2 . The end of the long road toward a 'stealth diffuser system bomber' p 438 A89-35100 [AD-A203178] p 458 N89-20967 [NASA-CR-l82232] p 504 N89-20776 BALANCING Performance of the active sidewall boundary-layer BYPASS RATIO High speed balancing applied to the T700 engine removal system for the Langley 0.3-meter Transonic 3-D LDA-measurements in the jet of a bypass-engine [NASA-CR-180899] p 497 N89-20472 Cryogenic Tunnel p 477 A89-33386 BALLISTICS [NASA-CR-181793] p 486 N89-21004 Base flow investgationbehind axi-andnon-axisymmetric BOUNDARYLAYEREOUATIONS blunt bodies Viscous-inviscid interaction and computation in C [ ISL-CO-246/87] p 452 N89-20103 aerodynamics BAROTROPIC FLOW [ONERA, TP NO. 1988-1161 p 443 A8944627 CABIN ATMOSPHERES Analysis of Doppler radar windshear data Unsteady force calculations on circular cylinders and Fire extinguishing agents for oxygen-ennched [NASA-CR-l81762] p 464 N89-20111 elliptical airfoils with circulation control atmospheres p 487 A89-32948 BASE FLOW [UMAERO-87-37] p 457 N89-20962 CALIBRATING Base flow investigationbehind mi-and non-axisymmetric BOUNDARY LAYER FLOW Position error calibration of a pressure survey aircraft blunt bodies The enect of the wind tunnel wall boundary layer on using a trailing cone [ISL-c0-246/87] p 452 N89-20103 the acoustic testing of propellers [ PB88-2507331 p 450 N89-20092 BEARINGS [AIM PAPER 89-10971 p 503 A8943737 CAMBER Assessment of the adequacy of bearing lubrication in Effect of the asymmetry of boundary conditions on An expenmental invesbgationof the aerodynamic loads a gas turbine engine through openings in the rotating boundary layer flow near a cone at angle of anack on cambered plates shaft p 492 A8934154 p 448 A89-35433 [AIAA PAPER 89-0935) p 447 A8945244 Rotordynamic analysis of a bearing tester A calculationmethod for compressiblethree dimensional CANARD CONFIGURATIONS p 498 N89-21759 turbulent boundary layer flows Development and implementation of flight control BEHAVIOR [VKI-TN-167] p 496 N89-20422 system for a research drop model p 481 A89-33563 Rotordynamic analysis of a bearing tester Turbulence and modeling in transonic flow CANOPIES p 498 N89-21759 p 456 N89-20951 A control canopy release method for improved opening BIAS Turbulent eddy viscosity modeling in transonic of clustered parachutes Aircraft tracking with dual TACAN shock/boundary-layer interactions p 456 N89-20952 [AIAA PAPER 89-08921 p 461 A89-35210 [AD-A202647] p 466 N89-20980 Capabilities of wind tunnels with two-adaptive walls to A revision of the added mass concept as applied to BIODYNAMICS minimize boundary interference in 3-D model testing parachute motion Transoniclsupersonic (720 KEAS 1.2 Mach) ejection p 486 N89-20961 [AIAA PAPER 89-08951 p 461 A89-35213 demonstration test of an S4S Biofidelity Manikin (BFMl) BOUNDARY LAYER SEPARATION High Reynolds number incompressible flow %mulation p 463 A8945841 Numerical instabilities in the calculation of laminar about parachute canopies and similar bluff bodies BLADE-VORTEX INTERACTION separation bubbles and their implications p450 N89-20096 Application of harmonic analysis method lo research p 445 A89-34819 CARBON MONOXIDE on rotor airloads p 467 A89-33139 Investigation of flow Separation in a three-dimensional Some charactenstics of the formallon of Contaminants Navier-Stokessimulation of unsteady three-dimensional diffuser using a coupled Euler and boundary-layer during the combustion of hydrocarbon fuels in the blade-vortex interactions p 444 A8944745 method p 446 A89-35172 combustion chambers of gas turbine engines Surface pressure measurements on a body subject lo An LDA (Laser-Doppler Anemometry) investigation of p 488 ABS-34120 vortex wake interaction p 470 A89-34808 three-dimensional normal shock wave boundary-layer CARET WINGS Calculation of blade-vortex interaction airloads on interactions p 456 N89-20956 Supersonic flow past caret wmgs and elements of helicopter rotors p 446 A89-34895 Effect of riblets upon flow separation in a subsonic star-shaped bodies a1 angles of anack and bank BLUFF BODIES diffuser p 449 A89-35481 Flow visualization studies of wake behind axisymmetric [AD-A2031781 p 458 N89-20967 CARRIER TO NOISE RATIOS bluff bodies including parachute canopy models Numerical Simulation of flow over iced airfoils High-dynamic GPS tracking [AIM PAPER 8948981 p 447 A8945215 IAD-A203291I p 458 N89-20969 [NASA-CR-184868] p 465 N89-20113
A-5 CARTESIAN COORDINATES SUBJECT INDEX
CARTESIAN COORDINATES CLOUD PHYSICS Comparison of propeller cruise noise data taken in the Trajectory scoring in rectangular coordinates using Icing considerations for HALE (High Altitude, Long NASA Lewis 8- by 6-foot wind tunnel with other tunnel transponder-interrogator range and range rate data Endurance) aircraft and flight data [ DE89-0070051 p 466 N89-20119 [AD-A202584] p 464 N89-20975 [ NASA-TM-101976] p 505 N89-21628 CASCADE FLOW CLUlTER COMPENSATORY TRACKING Optimal profile selection in the design of a subsonic Multispectral terrain background simulation techniques Response equivocation analysis for the smart stick turbine cascade p 442 A89-34152 for use in airborne sensor evaluation controller Incompressible cascade calculation using an upwind p 499 A89-33664 [ AD-A2031461 p 475 N89-20989 differenced NDscheme p 444 A8944733 COCKPITS COMPOSITE MATERIALS Cnmoutational_. studv of the effect of cascade parameters Cockpit automation p 460 A89-34444 Experimental investigation of the thermal conductivity on stall propagation in axial compressors Cockpit-crew systems design and integration of dispersed ceramic materials p 488 A89-34933 p 444 A89-34737 p 476 A89-34446 A (13)C NMR analysis of the effects of electron radiation on graphite/polyetherimidecomposites A linear comDuter code to determine aeroelastic stability Performance analysis of the fiber distributed data [NASA-CR-I8281 81 p 489 N89-20205 in airfoil cascades at unsteady flow conditions interface in the super cockpit audio world p 444 A89-34746 COMPOSITE STRUCTURES [ AD42025351 p 474 N89-20985 A comparison of secondary flow in a vane cascade and Noise reduction of a composite cylinder subjected to a curved duct p 446 A8944934 COLLAPSE random acoustic excitation Prediction of parachute collapse due to wake A numerical investigation of steady transonic cascade [AIAA PAPER 89-10491 p 501 A89-33708 flow in turbomachinery p 448 A89-35417 recontact On the design of biaxially stiffened composite plates [AIAA PAPER 89-09011 p 447 A89-35218 A method for calculating potential transonic flows in p 493 A89-34867 turbomachinery cascades p 449 A8945450 COLLISION AVOIDANCE COMPRESSIBLE BOUNDARY LAYER Experimental investigation of transonic oscillating Civilian RPVs - Eye in the sky or pie in the sky? A calculation method for compressible three dimensional cascade aerodynamics p 437 A89-33560 turbulent boundary layer flows [ NASA-TM-IO19931 p 478 N89-20133 Improved computer simulation of the TCAS 3 circular [VKI-TN-167] p 496 N89-20422 Asymptotic methods for internal transonic flows array mounted on an aircraft Secondary three-dimensional instability in compressible p 455 N89-20937 [ NASA-CR-1849071 p 496 N89-20363 boundary layers p 456 N89-20954 CATALYTIC ACTIVITY COLOR COMPRESSIBLE FLOW Fuel-rich catalytic combustion of Jet-A fuel-equivalence A helmet-mounted virtual environment display system Turbulence modeling for hypersonic flows ratios 5.0 to 8.0 [ AD-A203055I p 476 N89-20994 p 441 A8943641 [ NASA-TM-I019751 p 489 N89-21051 COMBUSTIBLE FLOW Patched-grid computations of high-speed inlet flows CAVITATION FLOW High density fuel effects p 443 A8944728 Thin axisymmetric caverns in supersonic flow [AD-A202426] p 490 N89-21125 Laser-induced iodine fluorescence technique for p 449 A89-35435 COMBUSTION CHAMBERS quantitative measurement in a nonreacting supersonic CAVITIES The influence of a radial swirl generator on the flow combustor p 445 A89-34809 Navier-Stokes calculations of transonic flows past open field from a fuel nozzle model p 490 A89-33354 Compressible flow losses in branched ducts and transitional cavities p 444 A89-34744 p 494 A89-35004 Heat transfer in gas turbine combustors CERAMIC COATINGS Transverse jets in compressible crossflows p 491 A89-33580 Argon shrouded plasma coatings for gas turbine p 452 N89-20923 applications p 491 A89-33487 A new method ior the thermodynamic calculation of Stability of compressible boundary layers CERAMIC MATRIX COMPOSITES combustion chambers p 478 A89-34409 p 456 N89-20953 Micro radiography and tomography for high resolution Laser-induced iodine fluorescence technique for Experimental examination of the aerothermal NDT of advanced materials and microstructural quantitative measurement in a nonreacting supersonic performanceof the T-I0 test cell at NAS (Naval Air Station). components p 495 A89-35081 combustor p 445 A89-34809 Cubi Point CERAMICS Assessment, development, and application of [AD-A203887] p 487 N89-21005 Potential applications for advanced structural ceramics combustor aerothermal models p 479 N89-20138 COMPRESSORS in aero gas turbine engines p 488 A89-33490 Structural analysis applications p 480 N89-20141 An analytical and numerical study of axial flow Fabrication of sintered alpha-Sic turbine engine Development of a rotary value for pulse combustion compressor instability p 478 N89-20131 components p 491 A89-33621 applications Transmission and reflection on pressure waves by Ceramics in high-temperature gas turbines (Review) [ PB89-I31 1141 p 496 N89-20468 compressor and turbine stages, based on an actuator-disk p 488 A89-34080 model High density fuel effects Experimental investigation of the thermal conductivity [AD-A203513] p 496 N89-20426 [ AD-A202426 I p 490 N89-21125 of dispersed ceramic materials p 488 A89-34933 Performance of the active sidewall boundary-layer Life modeling of thermal barrier coatings for aircraft gas COMBUSTION CONTROL removal system for the Langley 0.3-meter Transonic Fuels combustion research turbine engines p 480 N89-20143 Cryogenic Tunnel [AD-A204161] p 490 N89-21071 CHANNEL FLOW [NASA-CR-181793] p 486 N89-21004 Numerical modeling of transonic flow of a viscous gas COMBUSTION EFFICIENCY COMPUTATIONAL FLUID DYNAMICS in a plane channel with a sudden expansion Assessment, development, and application of Symposium on Turbulence. 11th. University of p 442 A89-34149 combustor aerothermal models p 479 N89-20138 Missoury-Rolla. Rolla. Oct. 17-19, 1988. Preprints Asymptotic methods lor internal transonic flows COMBUSTION PHYSICS p 491 A89-33402 p 455 N89-20937 A simple one-dimensional model for the effect of air A comparison of the turbulence structure of subsonic CHANNELS (DATA TRANSMISSION) pollution on supersonic combustion p 488 A89-34121 and supersonic boundary layers p 440 A89-33425 Design of an airborne optic fiber data bus system Fuels combustion research Computation of flow fields for hypersonic flight at high p 475 A89-33148 [AD-A204161] p 490 N89-21071 altitudes p 440 A89-33627 CHARACTERIZATION COMBUSTION PRODUCTS High enthalpy testing in hypersonic shock tunnels In-flight lightning characterizationprogram on a CV-580 Characteristics of the formation of benz(a)pyrene in the p 485 A89-33630 aircraft combustion chambers of aviation gas turbine engines A numerical method for predicting hypersonic [AD-A203954] p 464 N89-20976 p 488 A89-34119 flowfields p 440 A89-33634 CHEMICAL REACTIONS Some characteristics of the formation of contaminants Computational methods for hypersonic flows - Special Fuels combustion research during the combustion of hydrocarbon fuels in the techniques and real gas effects p 441 A8943640 [AD-A204161] p 490 N89-21071 combustion chambers of gas turbine engines Nonlinear kink modes for supersonic vortex sheets CIRCULAR CYLINDERS p 488 A89-34120 p 442 A8943783 I Unsteady force calculations on circular cylinders and COMBUSTION TEMPERATURE Viscosity effects in the generation of the lifting force I elliptical airfoils with circulation control Gas turbine alternative fuels combustion of aerodynamic wing profiles p 442 A8944114 [UMAERO-87-37] p 457 N89-20962 characteristics Advances in the cornputation of transonic separated CIVIL AVIATION [NASA-TM-I01470] p 499 N89-21417 flows over finite wings p 442 A8944427 Civilian RPVs ~ Eye in the sky or pie in the sky? COMMAND AND CONTROL A new look at Theodorsen's method in aerofoil theory p 437 A89-33560 Low cost avionic system for UMA --- unmanned p 443 A89-34621 The Theta Beta - Design of a system --- remotely piloted aircraft p 475 A89-33571 Viscous-inviscid interaction and computation in I civil aircraft p 468 A89-33561 Multivariable design of a bank-to-turn autopilot for aerodynamics Data links for video and IR surveillance command guidance p 482 A89-35301 [ONERA, TP NO. 1988-1161 p 443 A89-34627 p 465 A89-33567 COMMAND GUIDANCE High-resolution shock-capturing schemes for inviscid Multivariable design of a bank-to-turn autopilot for General aviation p 437 A89-34448 and viscous hypersonic flows p 443 A89-34646 command guidance p 482 A89-35301 ONERA research on civil aircraft p 438 A89-35376 Advances and applications in computational fluid The future of the civil aviation industry COMMERCIAL AIRCRA- Business aviation and new technologies dynamics; Proceedings of the Symposium, ASME Winter p 438 A89-35377 Annual Meeting, Chicago. IL. Nov. 27-Dec. 2. 1988 Civil-transport aircraft at Aerospatiale p 438 A89-35379 COMMUNICATION EQUIPMENT p 443 A89-34726 p 438 A89-35378 AH-IS communication switch integration program Inviscid prediction of transonic flows in turbomachines Aircraft accident reports: Brief format, US civil and [NASA-TM-101053] p 466 N89-20978 using a Runge-Kuttaintegration scheme foreign aviation, issue number 12 of 1986 accidents COMMUNICATION NETWORKS p 444 A89-34736 [ PB88-916902I p 464 N89-20109 Performance analysis of the fiber distributed data Computational study of the effect of cascade parameters Aircraft accident reports. brief format, US civil and foreign interlace in the super cockpit audio world on stall propagation in axial compressors aviation, issue number 14 of 1986 accidents [AD-A202535] p 474 N89-20985 p 444 A89-34737 [PB88-916904] p 464 N89-20110 COMPARISON Applications of a generalized pressure correction Electronics in civil aviation High-dynamic GPS tracking algonthm for flows in complicated geometries [ NLR-MP-87009-U1 p 476 N89-20129 [ NASA-CR-1848681 p 465 N89-20113 p 493 A89-34738 A-6 SUBJECT INDEX CONTROL SYSTEMS DESIGN
Second order accurate finite difference approximations COMPUTER AIDED DESIGN A wind tunnel and computer investigation of the low for the transonic small disturbance equation and the full Experimental methods lor hypersonics- Capabilitiesand speed aerodynamic characteristics of the prone escape potential equation p 444 A8934740 limitations p 441 A89-33638 system (PRESS) Navier-Stokescalculations of transonic flows past open Efficient optimization of integrated [ AD-A202768 I p 475 N89-20988 and transitional cavities p 444 A8934744 aerodynamic-structuraldesign p 500 A89-34569 CONES Navier-Stokessimulation of unsteady three-dimensional B-2 - The end of the long road toward a 'stealth Position error calibration of a pressure survey aircraft blade-vortex interactions p 444 A8944745 bomber' p 438 A89-35100 using a trailing cone A linear computer code to determine aeroelastic stability Structural analysis applications p 480 N89-20141 [ PB88-2507331 p 450 N89-20092 Transonic propulsion system integration analysis at in airfoil cascades at unsteady flow conditions CONFERENCES McDonnell Aircraft Company p 481 N89-20943 p 444 A8944746 Symposium on Turbulence. 1Ith, University of EulerlNavier-Stokes calculations of transonic flow past Evaluation of algebraic turbulence models lor PNS Missoury-Rolla. Rolla, Oct. 17-19. 1988, Preprints fixed- and rotary-wingaircraft conligurations predictions of supersonic flow past a sphere-cone p 491 A89-33402 p 445 A89-34807 p 456 N89-20948 Performanceoptimization for rotors in hover and axial Remotely piloted vehicles; International Conference. Wind-tunnel wall effects on delta wings 7th. Bristol, England, Sept. 12-14, 1988, Proceedingsand p 445 A89-34884 flight Supplementary Papers p 467 A89-33554 Euler and Naw-Stokes leeside flows over supersonic [ NASA-CR-1775241 p 459 N89-20973 delta wings p 445 A89-34892 A compendium of controlled diffusion blades generated Advances and applications in computational fluid dynamics; Proceedings of the Symposium, ASME Winter Direct numerical simulation of a three-dimensional by an automated inverse design procedure turnlent boundary layer p 493 A89-34909 [ NASA-TM-I01 9681 p 481 N89-20996 Annual Meeting. Chicago, IL. Nov. 27-Dec. 2. 1988 Bipolar coordinates for computation of transition duct COMPUTER AIDED TOMOGRAPHY p 443 A89-34726 flows p 493 A89-34912 Micro radiography and tomography for high resolution Heat transfer in gas turbine engines and Calculation of compression shock surfaces in NDT of advanced materials and microstructural three-dimensional flows; Proceedings 01 the Symposium, three-dimensional, steady supersonic :lows usinp B components p 495 A89-35081 ASME Winter Annual Meeting, Chicago, IL. Nov. 27-Dec. bicharacteristic method p 446 A89-35168 COMPUTER GRAPHICS 2.1988 p 494 A89-34926 Investigation of flow separation in a threedimensional Multispectral terrain background simulation techniques AlAA Aerodynamic Decelerator Systems Tecnnoiogy diffuser using a coupled Euler and boundary-layer lor use in airborne sensor evaluation Conference. 10th. Cocoa Beach, FL. Apr. 18-20. 1989. method p 446 A89-35172 p 499 A89-33664 Technical Papers p 461 A8945201 Analysis of decelerators in motion using computational COMPUTER PROGRAMS Toward improved durability in advanced aircraft engine fluid dynamics Prediction of full system helicopter noise for a MDHC hot sections [AIM PAPER 89-09311 p 447 A8935241 500E helicopter using the Rotonet program [NASA-TM-4087] p 479 N89-20135 A numerical investigation of steady transonic cascade [AlAA PAPER 89-11351 p 500 A89-33765 Transonic Symposium: Theory. Application, and flow in turbomachinery p 448 A89-35417 Development and application of a program to calculate Experiment, Volume 1, Part 1 A method for calculating potential transonic flows in transonic !low around an oscillatingthree-dimensional wing [NASA-CP-3020-VOL-I-PT-I 1 p 453 N89-20925 turbomachinery cascades p 449 A89-35450 using finite difference procedures CONFORMAL MAPPING Potential models of transonic flows [ NASA-CR-1817441 p 450 N89-20093 Patched-grid computations of high-speed inlet flows p 449 A89-35495 Evaluation of VSAERO in prediction of aerodynamic p 443 A8944728 Development and application of a program to calculate characteristics of helicopter hub fairings A self-adaptive computational method for transonic transonic flow around an oscillatingthree-dimensional wing [ NASA-TM-I01 0481 p 451 N89-20098 turbulent flow past a real projectile p 443 A8944730 using finite difference procedures Updated users' guide for TAWFIVE with multigrid CONGRESSIONAL REPORTS [NASA-CR-I81 7441 p450 N89-20093 [NASA-TM-4109] p 496 N89-20409 Aviation safety: Measuring how safely individual airlines A cell-vertex multigrid method for the Navier-Stokes Additional development of the XTRAN3S computer operate equations program [ GAO/RCED-88-61] p 464 N89-20974 [ NASA-TM-I01 5571 p 451 N89-20101 [NASA-CR-I81 7431 p 452 N89-20922 Microwave landing systems: Additional systems should Assessment. development. and application of The application of CFD for military aircraft design at not be procured unless benefits proven combustor aerothermal models p 479 N89-20138 transonic speeds p 454 N89-20930 [GAOIRCED-88-1181 p 466 N89-20977 Comparison 01 3D computation and experiment for Applied transonics at Grumman p 454 N89-20931 CONICAL BODIES non-axisymmetric nozzles Aerodynamic analysis of three advanced configurations Investigation of the development 01 laminar [ NASA-CR-1822451 p 452 N89-20921 using the TranAw full-potential code p 455 N89-20944 boundary-layer instabilities along a cooled-wall cone in Transonic Symposium: Theory. Application. and Selection of a frequency sensitive QFT (Quantitative hypersonic flows Experiment. Volume 1, Part 1 Feedback Theory) weighting matrix using the method of [ AD-A2025871 p 458 N89-20966 [NASA-CP-3020-VOL-I-PT-I ] p 453 N89-20925 specified outputs CONICAL FLOW Airframelpropulsion integration characteristics at [AD-A202692] p 501 N89-21592 Evaluation of algebraic turbulence models for PNS transonic speeds p 453 N89-20926 COMPUTER SYSTEMS DESIGN predictions of supersonic flow past a sphere-cone Transonic CFD applications at Boeing A helmet--mountedvirtual environment display system p 445 A89-34807 p 453 N89-20929 [AD-A203055] p 476 N89-20994 Effect of the asymmetry of boundary conditions on The application 01 CFD for military aircraft design at COMPLITER SYSTEMS PROGRAMS boundary layer flow near a cone at angle 01 attack transonic speeds p454 N89-20930 The applitlon 01 software fault tolerance lo air traffic p 448 A89-35433 Applied transonics at Grumman p 454 N89-20931 control: Study contract overview CONTACT LOADS Transonics and fighter aircralt Challenges and [ BRIO85671 p 465 N89-20114 Formulation and solution of axisymmetric problems in opportunities for CFD p 454 N89-20932 Real-time display of time dependent data using a the statics of multilayer shells 01 revolution with contact Computation of aircraft component flow fields at head-mounted display interaction between layers p 492 A89-34129 transonic Mach numbers using a three-dimensional [ADA2030511 p 476 N89-20993 CONTAMINATION Navier-Stokes algorithm P 454 N89-20933 COMPUTER TECHNIQUES Contaminationof the exterior of a C-130E aircraft used Transonic aerodynamic design experience The computer controlled system for multi-drone for aerial spray, 907 TAG, Rickenbacker ANGB, OH p 454 N89-20934 performing formation flight in a same aerial zone [AD-A202430] P 474 N89-20984 Euler solvers for transonic applitions p 481 A89-33566 CONTRAROTATING PROPELLERS P 454 N89-20935 Structural analysis applications p 480 N89-20141 Hub to tip variations of counter rotating propeller An embedded mesh procedure for leading-edge vortex COMPUTERIZED SIMULATION interaction noise flows p 455 N89-20936 [AIM PAPER 89-11451 p 504 A8943770 Asymptotic methods lor internal transonic flows Experimental methods for hypersonics. Capabilities and limitations p 441 A89-33638 Unsteady blade pressure measurements on a model p 455 N89-20937 counterrotation propeller Numerical simulation of three-dimensional hypersonic Vector potential methods p 455 N89-20939 [ NASA-TM-102002] viscous flows p 441 A89-33644 p 504 N89-20779 Developments and trends in three-dimensional mesh CONTROL CONFIGURED VEHICLES generation p 455 N89.20940 Advances in the computation 01 transonic separated Structural optimization lor aeroelastic control flows over tinite wings p 442 A89-34427 Generation of unstructured grids and Euler solutions for effectiveness p 470 A8944899 complex geometries p 455 N89-20941 Direct numerical simulation of a three-dimensional CONTROL STICKS Transonic Symposium: Theory. Application. and turbulent boundary layer p 493 A89-34909 Response equivocation analysis for the smart stick Experiment, volume 1, part 2 Bipolar coordinates for computation of transition duct controller [NASA-CP-3020-VOL-I-PT-21 p 455 N89-20942 flows p 493 A8944912 [AD-A203146] p 475 N89-20989 Thin-layer Navier-Stokes solutions lor a cranked delta Numerical simulation of the flow field over delta wings CONTROL SURFACES wing with leading edge blowing p 453 N89-20924 Actuation constraints in multivariable flight control [AD-A203292] p 459 N89-20970 Transonic aerodynamic design experience systems p 483 N89-20998 COMPUTATIONAL GRIDS p 454 N89-20934 Selection of a frequency sensitive QFT (Ouantitative Patched-gridcomputations of high-speed inlet flows Vector potential methods P 455 N89-20939 Feedback Theory) weighting matrix using the method of p 443 A8944728 specified outputs Applications of a generalized pressure correction Developments and trends in three-dimensional mesh generation p 455 N89-20940 [ AD-A202692I p 501 N89-21592 algorithm for flows in complicated geometries CONTROL SYSTEMS DESIGN p 493 A8944738 Transonic Symposium: Theory. Application, and Low cost avionic system for UMA --- unmanned Experiment, volume 1, part 2 Generation of unstructured grids and Euler solutions for aircraft p 475 A89-33571 complex geometries p 455 N89-20941 [ NASA-CP-3020-VOL-i-PT.2] p 455 N89-20942 Aviation displays p 476 A89-34443 Aerodynamic analysis of three advanced configurations Simulation at Dlyden Flight Research Facility from 1957 Cockpit automation p 460 A8944444 using the TranAir full-potentialcode p 455 N89-20944 to 1982 Observer design for compensation of network-induced Two-dimensionalNavier-Stokes solution of the flow over [ NASA-TM-101695] p 474 N89-20983 delays in integrated communication and control systems a thick supercritical airfoil with strong shock-induced Performance analysis of the fiber distributed data p 500 A89-35044 separation interface in the super cockpit audio world Active control law synthesis for flexible aircraft [AD-A203331] p 459 N89-20971 [AD-A2025351 p 474 N89-20985 P 482 A89-35045
A-7 CONTROL THEORY SUBJECT INDEX
Frequency domain techniques applied to the Estimation of the Equivalent Initial Flow Size (EIFS) DATA LINKS identificationof helicwter dynamics .P 500 A89-35261 distribution and prediction of failure probabilities for The U S Navy unmanned air vehicle program Quantitative design for systems with uncertainty and different parameter variations p 437 A89-33555 control failures p 500 A89-35283 [ FFA-TN-1987.351 p 498 N89-20525 Data links for video and IR surveillance Variable structure control laws for aircraft manoeuvres CRACK PROPAGATION p 465 A89-33567 p 482 A89-35286 The effect of stress ratio on the near-threshold fatigue Some consequpnces nf reduced frame rate for operator Design of robust multivariable helicopter control laws crack growth behavior of Ti-8AI-1Mo-IV at elevated performance p 465 A89-33573 for handling qualities enhancement P 482 A89-35297 temperature p 489 A89-35722 DATASYSTEMS Load alleviation on transport aircraft using acceleration Fatigue life prediction modeling for turbine hot section Design of an airborne optic fiber data bus system feedback p 471 A89-35299 materials p 480 N89-20142 p 475 A89-33148 DE HAVILLAND AIRCRAFT Variable structure model-following COntrOl Of flight Analysis of crack opening behavior by application of a Designing with advanced fibrous composites dynamics p 482 A89-35300 discretized strip yield model Multivariable design of a bank-to-turn autopilot for [NLR-MP-87065-U I p 497 N89-20520 p 470 A89-35197 command guidance p 482 A89-35301 DECELERATION Current status of flight simulation fatigue crack growth implementation of a transputer-based flight controller AlAA Aerodynamic Decelerator Systems Technology concepts p 482 A89-35302 Conference, loth, Cocoa Beach, FL, Apr 18-20, 1989. [ NLR-MP-88001-U] p 497 N89-20521 Modal cost analysis of flexible structures: Modeling Technical Papers p 461 A89-35201 Application of the boundary element method to fatigue flexible structures for control deslgn p 483 N89-20148 Prediction of oarachute collaose due to wake crack growlh analysis recontact Development of a rotary value for pulse combustion [AD-A2025651 p 498 N89-21270 applications [AIAA PAPER 89-09011 p 447 A89-35218 [PB89-1311141 p 496 N89-20468 Macrocrack-multiple defect interaction considering Analvsis of decelerators in motion usinq-. ComDutational Flight controller design with nonlinear aerodynamics, elastic, plastic and viscoplastic effects fluid dynamics large parameter uncertainty and pilot compensation [ AD-A2031861 p 498 N89-21262 [AIAA PAPER 89.09311 p 447 A89-35241 [AD-A2027271 p 484 N89-21000 CRACKING (FRACTURING) Radius-tippedtriangular inflatable decelerator design as A digital rate controller for the control reconfigurable Bulging cracks in pressurized fuselages: A numerical affected by produceabilitylsurvivability constraints combat aircraft designed using quantitative feedback study [AIAA PAPER 69-08881 p 463 A89-36020 theory [ NLR-MP-87058-Ul p 497 N89-20519 DEEP SPACE NETWORK [AD-A2030501 p 484 N89-21001 Estimation of the Equivalent Initial Flow Size (EIFS) Determination of GPS orbits to submeter accuracy CONTROL THEORY distribution and prediction of failure probabilities for p 466 N89-20331 Aviation displays p 476 A89-34443 different parameter variations DEFECTS Active control helicopter aeromechanical and [ FFA-TN-1987.351 p 498 N89-20525 Macrocrack-multiple defect interaction considering aeroelastic instabilities p 483 N89-20149 CRACKS elastic. plastic and viscoplastic effects Response equivocation analysis for the Smart stick Macrocrack-multiple defect interaction considering [AD-A203186] p 498 N89-21282 controller elastic, plastic and viscoplastic effects DEGRADATION [AD-A203146] p 475 N89-20989 [AD-A2031861 p 498 N89-21282 Personnel parachute agelsewice life criteria [AIAA PAPER 89-09161 Actuation constraints in multivariable flight control CROSS FLOW p 462 A89-35228 DEICING systems p 483 N89-20998 Transverse jets in compressible crossflows Aircraft accident report: Continental Airlines, Inc.. Flight A dgital rate controller for the control reconfigurable p 452 N89-20923 combat aircraft designed using quantitative feedback 1713, McDonnell Douglas DC-9-14, N626TX. Stapleton CRYOGENIC WIND TUNNELS theory International Airport. Denver, Colorado, November 15, Test techniques: survey paper cryogenic tunnels. [AD-A203050) p 484 N89-21001 A on 1987 adaptive wall test sections. and magnetic suspension and Selection of a frequency sensitive OFT (Quantitative [PB88-9104111 p 464 N89-20112 balance systems p 486 N89-20955 Feedback Theory) weighting matrix using the method of DELTA WINGS specified outputs Performance of the active sidewall boundary-layer The flow on the lee-side of a delta wing at Mach 7 [AD-A202692] p 501 N89-21592 removal system for the Langley 0.3-meter Transonic p 440 A89-33637 CONTROL VALVES Cryogenic Tunnel Acoustic forcing of three dimensional shear layers Power efficient hydraulic systems. Volume 2 Hardware [ NASA-CR-1817931 p 486 N89-21004 [AIM PAPER 89.10631 p 501 A89-33712 demonstration phase CYCLIC HYDROCARBONS Wind-tunnel wall effects on delta wings [AD-A203900] p 473 N89-20128 Characteristicsof the formation of benz(a)pyrene in the p 445 A89-34864 CONTROLLED ATMOSPHERES combustion chambers of aviation gas turbine engines Euler and Navier-Stokes leeside flows over supersonic Fire extinguishing agents for oxygen-enriched p 488 A89-34119 delta wings p 445 A89-34892 atmospheres p 487 A89-32948 CYLINDERS Vortex breakdown and its control on delta wings CONTROLLERS Noise reduction of a composite cylinder subjected to p 449 A89-35999 Response equivocation analysis for the smart Stick random acoustic excitation Detailed measurements in the transonic vortical flow controller [AIAA PAPER 89.10491 p 501 A89-33708 over a delta wing p 449 A89-36012 [AD-A203146] p 475 N89-20989 Propeller modellingeffects on interior noise In cylindrical Some considerationson leading edge vortices on wings A dgital rate controller lor the control reconfigurable cavities with application to active control in supersonic flow p 450 A89-36013 combat aircraft designed using quantitative feedback [AIAA PAPER 89.11231 p 469 A89-33757 Some low-speed flutter characteristics of simple theory CYLINDRICAL BODIES [ AD-A203050 I p 484 N89-21001 low-aspect-ratiodelta wing models A study of transonic drag reduction of a blunt cylinder [ NASA-TM-I01 5471 p 450 N89-20094 COOLING by a cylinder probe Investigation of the development of laminar Numerical simulation of the flow field over delta wings [AD-A2025571 p 458 N89-20965 with leading edge blowing p 453 N89-20924 boundary-layer instabilities along a cooled-wall cone in CYLINDRICAL SHELLS hypersonic flows An embedded mesh procedure for leading-edge vortex Natural vibrations of cylindrical shells with a rectangular flows p 455 N89-20936 [AD-A202587] p 458 N89-20966 cutout p 492 A89-34126 CORROSION PREVENTION The load-bearing capacity of closed-profile oblong Thin-layer Navier-Stokes solutions for a cranked delta Environment-assistedaerospace fatigue problems in cylindrical shells made of a metallpolymer composite wing The Netherlands laminate p 492 A89-34128 [AD-A2032921 p 459 N89-20970 (NLR-MP-88004-UI p 439 N89-20087 Divergence instabilityof reinforced composite cylindrical DENSITY (MASSIVOLUME) CORROSION RESISTANCE shells p 495 A89-35146 High density fuel effects Ceramics in high-temperaturegas turbines (Review) Bulging Cracks in pressurized fuselages: A numerical [AD-A2024261 p 490 N89-21125 p 488 A89-34080 study DEPLOYMENT COST ANALYSIS [NLR-MP-87058-U] p 497 N89-20519 Modeling of parachute opening ~ An experimental Modal cost analysis of flexible structures: Modeling CYLINDRICAL TANKS investigation p 460 A89-34891 flexible structures for control design p 483 N89-20148 Fuel holdup and component diffusivity in a cooled A control canopy release method for improved opening COUNTER ROTATION cylindrical tank p 488 A89-34894 of clustered parachutes Acoustic characteristics of counterrotating fans from [AlAA PAPER 89-08921 p 461 A8945210 model scale tests An expression for dynamic strain in a 'weak link' [AIAA PAPER 89.11421 p 477 A89-33769 D [AIAA PAPER 89-09421 p 495 A89-35247 Numerical solutions for the flowfield around a DAMAGE ASSESSMENT DEPOSITION counter-rotating propeller p 445 A89-34887 Wind damage to airports - Lessons learned Contamination of the exterior of a C-130E aircraft used Comparison of propeller cruise noise data taken in the for aerial spray, 907 TAG, Rickenbacker ANGB, OH P 499 A89-34359 NASA Lewis 8- by 6-loot wind tunnel with other tunnel DAST PROGRAM [AD-A2024301 p 474 N89-20984 and flight data Geometrical and structural properties of an Aeroelastic DESCENT TRAJECTORIES [ NASA-TM-1019761 p 505 N89-21628 Research Wing (ARW-2) An approximate method for calculating aircraft CRACKCLOSURE [NASA-TM-41IO] p 451 N89-20099 downwash on parachute trajectories The effect of stress ratii on the near-thresholdfatigue DATA ACOUISITION [AlAA PAPER 89-08991 p 447 A89-35216 crack growth behavior of Ti-8AI-1Mo-1V at elevated Small parachute flight data acquisition system DESIGN temperature p 489 A8945722 [AIAA PAPER 89-09241 P 463 A89-35234 Aerospace vehicle design, Spacecraft Section final CRACK INITIATION The data acquisition system for the Fokker 100 test project reports Fatigue life prediction modeling for turbine hot section aircraft [NASA-CR-1847411 p 471 N89-20121 materials p 480 N89-20142 [ NLR-MP-87047-U] P 476 N89-20130 DESIGN ANALYSIS Analysis of crack opening behavior by application of a DATA BASES The development and testing of the HISAC parachute discretized strip yield model Review and assessment of the database and numerical recovery system [NLR-MP-87065-U] p 497 N89-20520 modeling for turbine heat transfer P 479 N89-20139 [AlAA PAPER 89-0921] p 462 A89-35231 SUBJECT INDEX EQUILIBRIUM FLOW
Measurements of individual parachute loads in a DUCTED FLOW Controlling severed helicopter blades during emergency clustered parachute system Finite element modelling of sheared flow effects on the escape p 471 A89-35842 [AIAA PAPER 89-09231 p 463 A89-35233 radiation characteristics of acoustic sources in a circular ENERGY CONSUMPTION duct Power efficient hydraulic systems Volume 1 Study Parachutes ~ Yesterday, today, and tomorrow [AIAA PAPER 89-08801 p 463 A89-36019 [AlAA PAPER 89-10851 p 502 A89-33726 phase Bipolar coordinates for computation of transition duct Aerospace vehicle design, Spacecraft Section final [AD-A203899] p 472 N89-20127 flows p 493 A89-34912 ENERGY DISSIPATION project reports A comparison of secondary flow in a vane cascade and [NASA-CR-184741I p 47: N89-20121 An analytical experimental study of ring gap losses in a Curved duct p 446 A89-34934 mall axial flow turbines p 478 A89 34141 Aerospace vehicle design. Spacecraft Section final Compressible flow losses in branched ducts ENGINE DESIGN project reports p 494 A89-35004 Metallic limitationsin aircraft engines -The rational return [NASA-CR-1847421 p 472 N89-20122 DUMMIES lo the stone age p 477 A89-33485 Aerospace vehicle design, Spacecraft Section Transonic/supersonic (720 KEAS 1.2 Mach) ejection Potential applications for advanced structural ceramics [NASA-CR-1847431 p 472 N89-20123 demonstrationtest of an S4S Biofidelity Manikin (BFMI) in aero gas turbine engines p 488 A89-33490 DIFFERENTIALEQUATIONS p 463 A89-35841 The Norton P73 rotary RPV engine Rotordynamic analysis of a bearing tester DYNAMIC CONTROL p 477 A89-33565 p 498 N89-21759 Frequency domain techniques applied lo the Evolution of a small turbine engine family for unmanned DIFFUSERS identification of helicopter dynamics p 500 A89-35261 aerial vehicles p 477 A89-33570 Investigation of flow separation in a three-dimensional DYNAMIC MODELS Acoustic characteristics of counterrotating fans from diffuser using a coupled Euler and boundary-layer Transient dynamics of aircraft propellers during model scale tests method p 446 A89-35172 touch-down impact p 470 A89-34509 [AIAA PAPER 89.11421 p 477 A89-33769 DIFFUSION DYNAMIC RESPONSE Assessment of the adequacy of bearing lubrication in A compendium of controlled diffusion blades generated An eirfoii pitch appa:a!ds~mde!ing n-c! ccn!rcl design a gas turbine engine through openings in the rotating by an automated inverse design procedure [ NASA-TM-101076] p 496 N89-20386 shaft p 492 A89-34154 [ NASA-TM-1019681 p 481 N89-20996 DYNAMIC STRUCTURAL ANALYSIS Propulsion over a wide Mach number range Prospects for the application of holographic DIFFUSION FLAMES [ NASA-CR-1822671 p 478 N89-20134 Fuels combustion research interferometry to the study of the resonant vibrations of Assessment, development, and application of [AD-A204161] p 490 N89-21071 complex systems p 495 A89-35654 combustor aerothermal models p 479 N89-20138 Coupled rotorlfuselage dynamic analysis of the AH-IG DIGITAL SIMULATION Review and assessment of the database and numerical helicopter and correlation with flight vibrations data modeling for turbine heat transfer p 479 N89-20139 A digital simulation technique for Dryden atmospheric [ NASA-CR-1817231 p 497 N89-20512 turbulence model p 439 A89-33142 Structural analysis methods development for turbine hot section components p 479 N89-20140 A real-time simulator of a turbofan engine Structural analysis applications p 480 N89-20141 [NASA-TM-I00869] p 481 N89-20995 E Views on the impact of HOST p 480 N89-20144 DIGITAL SYSTEMS ENGINE MONITORING INSTRUMENTS In-flight lightning characterizationprogram on a CV-580 EARTH ORBITAL ENVIRONMENTS 3-D LDA-measurementsin the let of a bypass-engine aircraft Technology requirements for hypersonic airbreathing p 477 A89-33386 [ AD-A2039541 p 464 N89-20976 aircraft p 468 A89-33626 ENGINE NOISE A digital rate controller for the control reconfigurable EDDY VISCOSITY Model size requirements for finite element prediction combat aircraft designed using quantitative feedback Turbulent eddy viscosity modeling in transonic of low-frequencycabin noise and vibration shock/boundary-layer interactions p 456 N89-20952 theory [AIAA PAPER 89-10761 p 469 A89-33721 [AD-A203050] p 484 N89-21001 EFFECTIVE PERCEIVED NOISE LEVELS Near-field noise of a pusher propeller DISCRETE FUNCTIONS Noise levels of a combined bypass-propfan engine in [AIAA PAPER 89.10961 p 502 A89-33736 Stability analysis of the multiple discrete stabilization the far sonic field p 478 A89-34150 Experimental investigation of rotor wakelstator system 01 an elastic flight vehicle p 500 A89-34132 EIGENVALUES interaction noise generation by acoustic mode Actuation constraints in multivariable flight control DISPLAY DEVICES measurements systems p 483 N89-20998 Aviation displays p 476 A89-34443 [AIAA PAPER 89-11261 p 503 A89-33759 EJECTION SEATS New static engine noise test techniques which reduce DISTANCE Pilot ejection from a pronated flying position Trajectory scoring in rectangular coordinates using test time significantly [AIAA PAPER 89-08851 p 471 A89-35205 [AIAA PAPER 89-11271 p 485 A89-33760 transponder-interrogator range and range rate data New lightweight parachute fabrics of Kevlar aramid [ DE89-0070051 p 466 N89-20119 Importance of engine as a source of helicopter external fiber noise DIVERGENCE [AIAA PAPER 89.091 11 p 489 A89-35224 Divergence instabilityof reinforced composite cylindrical [AIAA PAPER 89-11471 p 470 A89-33771 A seat-mounted combined harness Noise levels of a combined bypass-propfan engine in shells p 495 A89-35146 [AIAA PAPER 89.09371 p 463 A89-35245 DOPPLER RADAR the far sonic field p 478 A89-34150 Transonic/supersonic (720 KEAS 1.2 Mach) ejection ENGINE PARTS Analysis of Doppler radar windshear data demonstration test of an S4S Biofidelity Manikin (BFMI) Fabrication of sintered alpha-SIC turbine engine [ NASA-CR-1817621 p 464 N89-20111 p 463 A89-35841 components p 491 A89-33621 DOWNWASH Advanced Recovery Sequencer (ARS) --- for ejection Fatigue testing of gas turbine components An approximate method for calculating aircraft seats p 471 A89-35843 p 485 A89-33804 downwash on parachute trajectories A pronated escape system for fighter aircraft Ceramics in high-temperature gas turbines (Review) [AIAA PAPER 89-08991 p 447 A89-35216 p 463 A89-35845 p 488 A89-34080 DRAG A wind tunnel and computer investigation of the low Structural analysis methods development for turbine hot Wave drag due to lift for transonic airplanes speed aerodynamic characteristics of the prone escape section components p 479 N89-20140 p 455 N89-20938 system (PRESS) Structural analysis applications p 480 N89-20141 DRAGCHUTES [AD-A202768] p 475 N89-20988 ENGINE TESTS Radius-tippedtriangular inflatable decelerator design as ELASTIC DAMPING New static enaine noise test techniaues which reduce affected by produceability/survivabilityconstraints A linear computer code to determine aeroelastic stability test time significantly [AIAA PAPER 89-08881 p 463 A89-36020 in airfoil cascades at unsteady flow conditions [AIM PAPER 89-11271 p 485 A89-33760 p 444 A89-34746 DRAG FORCE ANEMOMETERS An experimentalstudv of the rate characteristicsof brush Aerodynamics of two-dimensional slotted bluff bodies ELASTIC DEFORMATION seals in comparison with labyrinth seals Aeroelastic deformation effects on the stopped-rotor [ DE89-0072883 p 452 N89-20105 p 492 A89-34136 dynamics of an X-wing aircraft p 482 A8944897 DRAG REDUCTION Advanced high temperature instrument for hot section ELASTIC PROPERTIES research applications p 479 N89-20137 A study of transonic drag reduction of a blunt cylinder Macrocrack-multiple defect interaction considering by a cylinder probe A real-time simulator of a turbofan engine elastic. plastic and viscoplastic effects [ NASA-TM-1008691 p 481 N89-20995 [AD-A2025571 p 458 N89-20965 [AD-A2031861 p 498 N89-21282 Expenmental examination of the aerothermal DRONE AIRCRAFT ELASTIC WAVES The computer controlled system for multi-drone performanceoftheT-10 test cellat NAS(Nava1Air Station), Transmission and reflection on pressure waves by Cubi Point performing formation flight in a same aerial zone compressor and turbine stages, based on an actuator-disk p 481 A89-33566 [AD-A203887] p 487 N89-21005 model ENGINEERINGDRAWINGS Hypersonic drone design: A multidisciplinary [ AD-A203513] p 496 N89-20426 Parachute drawing standards currently in use at Sandia experience ELECTRO-OPTICS National Laboratories NASA-CR-1847401 p 473 N89-20981 I Design of an airborne optic fiber data bus system [AIAA PAPER 89.09271 p 495 A89-35237 DROP TESTS p 475 A89-33148 ENVIRONMENTMODELS Development and implementation of flight control ELECTROMAGNETIC PULSES A microcomputer pollution model for civilian airports and System for a research drop model p 481 A89-33563 In-flight lightning characterization program on a CV-580 Air Force bases Model application and background A preliminary characterization of parachute wake aircraft [AD-A1997941 p 499 N89-20557 recontact [AD-A2039541 p 464 N89-20976 EQUATIONS OF MOTION [AIAA PAPER 89-08971 p 447 A89-35214 ELECTROSTATICS On a method for solving integral equations of The development of a 10,000 Ib capacity ram air Experimental investigation01 electrostatic fire accidents Iifting-surfacetheory for oscillating high-speed propellers parachute after aircraft landing and preventive measures p 439 A89-33100 [AIAA PAPER 89-09041 p 462 A89-35220 p 460 A89-34885 EQUILIBRIUM FLOW DUCT GEOMETRY EMERGENCIES Thin-layer Navier-Stokes solutions for a cranked delta Bipolar coordinates for cornputation of transition duct High performance escape capsules wing flows D 493 A89-34912 [AIAA PAPER 89-08781 p 470 A89-35202 [ AD-A203292] p 459 N89-20970
A-9 EQUIPMENT SPECIFICATIONS SUBJECT INDEX
EQUIPMENT SPECIFICATIONS FAILURE ANALYSIS Selection of a frequency sensitive QFT (Quantitative Parachute drawing standards currently in use at Sandia Full-scale fatigue testing of aircraft structures Feedback Theory) weighting matrix using the method of National Laboratories p 485 A89-33802 specified outputs rAlAA PAPER 89-09271 p 495 A8945237 Fatigue testing 01 gas turbine components [AD-A2026921 p 501 N89-21592 E~CAPE p 485 A89-33804 FINITE DIFFERENCE THEORY Controlling severed helicopter blades during emergency Quantitative lractography .Possibilities and applications Incompressible cascade calculation using an upwind uscam p 47 t A8945842 in aircraft research p 495 A8945074 differenced NDscheme p 444 A89-34733 ESCAPE CAPSULES On-board automatic aid and advisory for pilots of Second order accurate linite difference approximations High performance escape capsules control-impaired aircraft p 483 N89-20150 for the transonic small disturbance equationp 444 andA8944740 the full [AlAA PAPER 89-08781 p 470 A8935202 potential equation Estimation of the Equivalent Initial Flow Size (EIFS) Development and application of a program to calculate Testing of a new recovery parachute system lor the distribution and prediction of failure probabilities for transonic flow around an oscillating three-dimensionalwing Flll aircraft crew escape module - An update different parameter variations [AIAA PAPER 89.0891 I p 471 A89-35209 using linite diflerence procedures [FFA-TN-t987-351 p 498 N89-20525 Develooment of an alternating flat to tubular Kevlar [ NASA-CR-1817441 p 450 N89-20093 FAILURE MODES parachute tape A calculation method for compressiblethree dimensional [AIAA PAPER 89-09101 p 462 A8945223 Quantitative design for systems with uncertainty and turbulent boundary layer flows control failures p 500 A8945283 ESCAPE SYSTEMS [VKI-TN-167] p 496 N89-20422 Pilot ejection from a pronated flying position FAIRINGS FINITE ELEMENT METHOD [AIM PAPER 89-08851 p 471 A89-35205 Evaluation of VSAERO in prediction of aerodynamic Finite-surface spline p 500 A89-34900 Advanced Recovery Sequencer (ARS) _-- for ejection characteristics 01 helicopter hub fairings Structural Tailoring 01 Advanced Turboprops (STAT) seats D 471 A89-35843 [ NASA-TM-1010481 p 451 N89-20098 programmer’s manual A pronated escape system for lighter aircraft FAR FIELDS [ NASA-CR-1821641 p 478 N89-20132 o 463 A89-35845 Noise levels of a combined bypass-propfan engine in Bulging cracks in pressurized fuselages: A numerical A wind tunnel and computer investigation of the low the far sonic field p 478 A8944150 study speed aerodynamic characteristics of the prone escape FATIGUE (MATERIALS) [NLR-MP-87058-U] p 497 N89-20519 system (PRESS) Environment-assistedaerosDace fatiaue-. Droblems in Application of the boundary element method to fatigue [AD-A2027681 p 475 N89-20988 The Netherlands crack growth analysis ESTIMATES [NLR-MP-88004-V] p 439 N89-20087 [AD-A202565] p 498 N89-21270 High-dynamic GPS tracking FATIGUE LIFE Macrocrack-multiple defect interaction considering [NASA-CR-184868] p 465 N89-20113 Fatigue life prediction modeling for turbine hot section elastic, ptasti and viscoplasti effects EULER EQUATIONS OF MOTION materials p 480 N89-20142 [AD-A2031861 p 498 N89-21282 Euler and Navier-Stokesleeside flows over supersonic Current status of flight simulation fatigue crack growth FINITE VOLUME METHOD delta wings p 445 A89-34892 concepts Navier-Stokes calculations 01 scramjet-afterbody Computation 01 aircraft component flow fields at [NLR-MP-88001-U I p 497 N89-20521 flowfields p 443 A8944732 transonic Mach numbers using a three-dimensional FATIGUE TESTS FIRE EXTINGUISHERS Navier-Stokesalgonthm p 454 N89-20933 Full-scale fatigue testing 01 components and structures Fire extinguishing agents for oxygen-enriched Euler solvers for transonic applications --- Book p 485 A89-33801 atmospheres p 487 A89-32948 p 454 N89-20935 Full-scale fatigue testing of aircraft structures FIRE PREVENTION Generation of UnStNCtUred gnds and Euler solutions lor p 485 A89-33802 Experimentaltnves:igation of electrostatic fire accidents complex geometries p 455 N89-20941 Fatigue evaluation of helicopter rotor heads after aircraft landing and preventive measures EulerlNavier-Stokes calculations of transonic flow past p 485 A89-33803 p 460 A89-34885 lixed- and rotary-wing aircraft configurations Fatigue testing of gas turbine components FLAPS (CONTROL SURFACES) p 456 N89-20948 p 485 A89-33804 Thin aerofoils with high-incidence flaps or blunt trailing The 3-D Euler and Navier-Stokescalculations lor aircraft Personnel parachute agelservice life criteria edges p 445 A8944749 components p 498 N89-20950 [AIAA PAPER 89.09161 p 462 A89-35228 Effect of 90 degree flap on the aerodynamics of a EUROPEAN AIRBUS FAULT TOLERANCE two-element airfoil p 446 A89-35053 Civil-transport aircraft at Aerospatiale The application of software fault tolerance to air traffic FLAT PLATES p 438 A89-35378 control: Study contract overview Effect of riblets upon flow separation in a subsonic EXCITATION lBR1085671 p 465 N89-20114 diffuser Subharmonic and fundamentalhigh amplitude excitation FEEDBACK [AD-A203178] p 458 N89-20967 of an axisymmetric jet A digital rate controller lor the control reconfigurable FLEXIBLE BODIES [NASA-TM-101946) p 452 N89-20920 combat aircraft designed using quantitative feedback Transient dynamics of aircraft propellers during EXHAUST EMISSION theory touch-down impact p 470 A89-34509 Gas turbine alternative fuels combustion [AD-A2030501 p 484 N89-21001 Active control law synthesis lor flexible aircraft characteristics Selection 01 a frequency sensitive OFT (Quantitative p 482 A89-35045 [ NASA-TM-l01470] p 499 N89-21417 Feedback Theory) weighting matrix using the method of Modal cost analysis of flexible structures: Modeling EXHAUST FLOW SIMULATION specified outputs flexible structures for control design p 483 N89-20148 Navier-Stokes calculations of scramjet-afterbody AD-A202692 ] p 501 N89-21592 FLEXING llowfields p 443 A89-34732 FEEDBACKCONTROL Comparison of airfoil results from an adaptive wall test EXHAUST GASES Quantitative design lor systems with uncertainty and section and a porous wall test section Hot gas ingestion testing of an advanced STOVL control failures p 500 A8945283 p 457 N89-20960 concept in the NASA Lewis 9- by 15-lootLow Speed Wind Variable structure model-following control of flight FLIGHT CHARACTERISTICS Tunnel with flow visualization dynamtcs p 482 A89-35300 A mathematical model of aircraft spin and results of [AIAA PAPER 88-30251 p 439 A89-33249 Modal cost analysis of flexible structures: Modeling its computer integration p 481 A89-34130 Measurements of mean-llow and turbulence flexible structures for control design p 483 N89-20148 Airworthiness and flight characteristics evaluation of an characteristics in a turbojet exhaust using a laser Actuation constraints in multivariable flight control improved engine air filtration system on the UH-1H velocimeter p 439 A89-33410 systems p 483 N89-20998 helicopter EXPERIMENT DESIGN Flight controller design with nonlinear aerodynamics, [ADA2034461 p 480 N89-20145 Experimental methods for hypersonics -Capabilitiesand large parameter uncertainty and pilot compensation FLIGHT CONDITIONS limitatlons p 441 A8943638 [AD-A202727] p 484 N89-21000 A coupling apparent mass lor parachute inflation ONERA research on civil aircraft p 438 A893376 FIBER COMPOSITES equations EXPERT SYSTEMS Micro radiography and tomography for high resolution [AIAA PAPER 89.09331 p 447 A89-35243 On-board automatic aid and advisory for pilots 01 NOT of advanced materials and microstructural FLIGHT CONTROL control-impaired aircraft p 483 N89-20150 components p 495 A89-35081 Some aspects of the development and operational Reliability and performance evaluation of systems Designing with advanced fibrous composites testing of the Sprite system p 467 A89-33557 containing embedded rule-based expert systems p 470 A8945197 Complementary minis - Skyeye and Phoenix, an overview [ NASA-CR-1817691 p 500 N89-20683 FIBER OPTICS of their multi-mission coverage p 467 A89-33558 EXTERNAL STORES Design of an airborne optic fiber data bus system Falconet target RPV operations p 437 A8943559 Method to predict external store carriage loads at p 475 A89-33148 Civilian RPVS - Eye in the sky or pie in the sky? transonic speeds p 473 N89-20945 Performance analysis of the fiber distributed data p 437 A89-33560 interface in the super cockpit audio world Flight test of XRAE-1 to establish aerodynamic data F [AD-A202535] P 474 N89-20985 p 468 A89-33562 FIGHTER AIRCRAFT Development and implementation of flight control Pilot ejection from a pronated flying position F-1 11 AIRCRAFT system lor a research drop model p 481 A89-33563 [AIAA PAPER 89-08851 P 471 A89-35205 The computer controlled system lor multi-drone Testing of a new recovery parachute system for the A pronated escape system for lighter aircraft Flll aircraft crew escape module An update performing formation llight in a same aerial zone - P 463 A8945845 [AIM PAPER 89-08911 p 471 A8945209 Transonics and fighter aircraft Challenges and P 481 A89-33566 Quantitative design lor systems with uncertainty and F-16 AIRCRAFT opportunities lor CFD p 454 N89-20932 Incorporatingfive nations’ operational requirements into Aeroelastic modeling for the FIT team FIA-18 control failures P 500 A89-35283 a single aircraft The F-16 multinational fighter program simulation Variable structure model-following control of flight viewed from the operational side [NASA-TM-1015691 P 475 N89-20991 dynamics p 482 A89-35300 [AD-A202552] p 474 N89-20986 A digital rate controller lor the control reconfigurable Implementation of a transputer-based llight controller FABRICATION combat aircraft designed using quantitative feedback p 482 A89-35302 Fabrication of sintered alpha-Sic turbine engine theory AH-IS communication switch integration program components p 491 A89-33621 [AD-A203050] P 484 N89-21001 [ NASA-TM-1010531 p 466 N89-20978 SUBJECT INDEX FREE FLIGHT
Preliminary design of a modular unmanned research Gmpanson of propeller cruise noise data taken in the Measurements of mean-flow and turbulence vehicle. Volume 1: System design document NASA Lewis 8- by 6-foot wind tunnel with other tunnel characteristics in a turbojet exhaust using a laser [ AD-A2027651 p 474 N89-20987 and flight data velocimeter p 439 A8943410 Flight controller design with nonlinear aerodynamics, [ NASA-TM-101976] p 505 N89-21628 Measurements of a supersonic turbulent vortex large parameter uncertainty and pilot compensation FLIGHT VEHICLES p 440 A89-33423 [AD-A202727] p 484 N89-21000 Prospects for the application of holographic Instantaneous profiles and turbulence statistics of Selection of a frequency sensitive QFT (Quantitative interferometry to the study of the resonant vibrations of supersonic free shear layers by Raman excitation + complex systems p 495 A89-35654 Feedback Theory) weighting matrix using :he inethod Of laser-induced electronic fluorescence (relief) velocity specified outputs FLOW CHARACTERISTICS tagging of oxygen p 440 A89-33424 Supersonic flow past caret wings and elements of [ AD-A202692I p 501 N89-21592 Laser-induced iodine fluorescence technique for star-shaped bodies at angles of attack and bank quantitative measurement in a nonreacting supersonic FLIGHT CREWS p 449 A89-35481 combustor p 445 A89-34809 Cockpit-crew systems design and integration FLOW DEFLECTION p 476 A89-34446 Turbulization of a high-velocity boundary layer by a Detailed measurements in the transonic vortical flow FLIGHT HAZARDS projection p 448 A89-35434 over a delta wing p 449 A89-36012 In-flightlightning characterizationprogram on a CV-580 An expenmental study of transonic buffet of a Base flow investigationbehind axi-and non-axisymmetric aircratt supercritical airfoil with trailing edge flap blunt bodies [AD-A2039541 p 464 N89-20976 LAD-AZ031891 p 458 N89-20968 [ ISL-CO-246l871 p 452 N89-20103 FLIGHT PATHS FLOW DISTRIBUTION FLOW STABILITY An approximate method for calculating aircraft The influence of a radial swirl generator on the flow An analytical and numerical study of axial flow downwash on parachute trajectories field from a fuel nozzle model p 490 A89-33354 compressor instability p 478 N89-20131 [AIM PAPER 89-08991 p 447 A89-35216 Comparison of LDA and LTA application for propeller FLOW THEORY The application of trajectory prediction algorithms ior tests in wind irrnnsls p A90 A.89-33381 A new look at Theodorsen's method in aerofoil theory planning purposes in the Netherlands Air Traffic Control A numerical method for predicting hypersonic p 443 A63-3462: [ATC) system flowfields p 440 A89-33634 FLOW VELOCITY [NLR-MP-87031-U] p 465 N89-20115 The flow on the lee-side of a delta wing at Mach 7 The influence of a radial swirl generator on the flow FLIGHT SAFETY p 440 A89-33637 field from a fuel nozzle model p 490 A89-33354 Improved computer simulation of the TCAS 3 circular Interactionnoise mechanismsfor an advanced ..DroDeller Particle image displacementvelocimetry applied in high array mounted on an aircraft ~ Experimental results speed flows p 490 A89-33388 [NASA-CR-184907] p 496 N89-20363 [AIM PAPER 89-10931 p 502 A8943733 FLOW VISUALIZATION Navier-Stokes calculations of scramiet-afterbodv Simulation at Dryden Flight Research Facilityfrom 1957 Hot gas ingestion testing of an advanced STOVL flowfields p 443 A89-34732 to 1982 concept in the NASA Lewis 9- by 15-foot Low Speed Wind Model for investigation of helicopter fuselage influence [ NASA-TM-1016951 p 474 N89-20983 Tunnel with flow visualization on rotor flowfields p 445 A89-34883 FLIGHT SIMULATION [AIAA PAPER 88.30251 p 439 A89-33249 Numerical solutions for the flowfield around a A digital simulation technique for Dryden atmospheric Results from laser sheet visualization of a periodic rotor turbulence model p 439 A89-33142 counter-rotating propeller p 445 A89-34887 Computation of external. hypersonic, three-dimensional wake p 485 A89-34890 Aircraft tracking with dual TACAN flowfield and heat transfer p 494 A8944935 Flow visualization studies of wake behind axisymmetric [AD-A202647] p 466 N89-20980 Performance and test section flow characteristics of the bluff bodies including parachute canopy models Simulation at Dryden Flight Research Facility from 1957 National Full-ScaleAerodynamics Complex 40- by 80-foot [AlAA PAPER 89-08981 p 447 A89-35215 to 1982 wind tunnel FLUID INJECTION [NASA-TM-1Ol695l p 474 N89-20983 [NASA-TM-101065 1 p 438 N89-20086 Predictlon of heat transfer characteristics of discrete FLIGHT TEST INSTRUMENTS Viscous shock layer analysis of hypersonic flows over hole film cooling - One row of injection into a turbulent The data acquisition system for the Fokker 100 test long slender vehicles p 451 N89-20097 boundary layer p 494 A89-34931 aircraft Updated users' guide for TAWFIVE with multigrid FLUID JETS [NLR-MP-87047-U] p 476 N89-20130 [ NASA-TM-41091 p 496 N89-20409 Transverse jets in compressible crossflows FLIGHT TEST VEHICLES Additional development of the XTRAN3S computer p 452 N89-20923 Preliminary design of a modular unmanned research program FLUlTER ANALYSIS vehicle. Volume 1: System design document [NASA-CR-1817431 p 452 N89-20922 Development and application of a program lo calculate [AD-A202765] p 474 N89-20987 Numerical simulation of the flow field over delta wings transonic flow around an oscillating three-dimensionalwing FLIGHT TESTS with leading edge blowing p 453 N89-20924 using finite difference procedures Canadair SentinellSea Sentinel rotary wing RPV. IV Computation of aircraft component flow fields at [ NASA-CR-181744] p 450 N89-20093 p 467 A89-33556 transonic Mach numbers using a three-dimensional Some low-speed flutter characteristics of simple Flight test of XRAE-1 to establish aerodynamic data Navier-Stokesalgorithm p 454 N89-20933 low-aspect-ratiodelta wing models p 468 A89-33562 An embedded mesh procedure for leading-edge vortex [NASA-TM-101547] p 450 N89-20094 The Norton P73 rotary RPV engine flows p 455 N89-20936 Additional development of the XTRAN3S computer p 477 A89-33565 Generation of unstructuredgrids and Euler soIutions for program Experimental methods for hyparsonics - Capabilitiesand complex geometries p 455 N89-20941 [NASA-CR-181743] p 452 N89-20922 limitations p 441 A89-33638 Aerodynamic analysis of three advanced configurations FOAMS 6-2- The end of the long road toward a 'stealth using the TranAir full-potential code p 455 N89-20944 Attenuation of blast waves using foam and other bomber' p 438 A89-35100 Steady and unsteady transonic small disturbance materials Spin testing methods in flight p 470 A8935196 analysis of realistic aircraft configurations [AD-A203148] p 505 N89-21632 The development of the panel stabilized slotted-square p 473 N89-20946 FOKKER AIRCRAFT parachute Instrumentationadvances for transonic testing The data acquisition system for the Fokker 100 test [AIAA PAPER 89-08941 p 461 A89-35212 p 486 N89-20957 aircraft Small parachute flight data acquisition system Comparison of airfoil results from an adaptive wall test [ NLR-MP-87047-Ul p 476 N89-20130 [AIAA PAPER 89.09241 p 463 A89-35234 section and a porous wall test section FORCE DISTRIBUTION A coupling apparent mass for parachute inflation p 457 N89-20960 Modeling of parachute opening - An experimental equations A study of transonic drag reduction of a blunt cylinder investigation p 460 A89-34891 [AIAA PAPER 89-09331 p 447 A89-35243 by a cylinder probe FORECASTING The effects of unsteady aerodynamics on single and [ AD-A2025571 p 458 N89-20965 Icing considerations for HALE (High Altitude. Long clustered parachute system Numerical simulation Of flow over iced airfoils Endurance) aircratt [AIAA PAPER 89.09341 p 448 A89-35250 [AD-A203291I p 458 N89-20969 [AD-A202584] p 464 N89-20975 Experimental wind tunnel study of a militaly-aircraft air Flowfield measurements in the NASA Lewis Research FORGING intake - Cornparison with flight p 448 A89-35381 Center 9- by 15-fmt low-speed wind tunnel Structure and properties of forged ODS nickel-base Hub and blade structural loads measurements of an [ NASA-TM-1008831 p 486 N89-21002 superalloys p 491 A89-33461 SA34912 helicopter FLOW EQUATIONS Spray formed Waspaloy for disc forgings [NASA-TM-101040] p 472 N89-20124 Viscous shock layer analysis of hypersonic flows over p 487 A89-33463 Aiworthiness and flight characteristics evaluation of an long slender vehicles p 451 N89-20097 FRACTOGRAPHY improved engine air filtration system on the UH-1H FLOW GEOMETRY Quantitative fractography- Possibilitiesand applications helicopter Numerical modeling of transonic flow of a viscous gas in aircraft research p 495 A89-35074 [AD-A203446] p 480 N89-20145 in a plane channel with a sudden expansion FRACTURE MECHANICS Coupled rotorlfuselage dynamic analysis of the AH-IG p 442 A89-34149 Fatigue life prediction modeling for turbine hot section helicopter and correlation with flight vibrations data Applications of a generalized pressure correction materials p 480 N89-20142 [ NASA-CR-I81 7231 p 497 N89-20512 algorithm for flows in complicated geometries Analysis of crack opening behavior by application of a Transonic Symposium: Theory. Application. and p 493 A89-34738 discretized strip yield model Experiment. Volume 1, Part I Navier-Stokes calculations of transonic flows past open [ NLR-MP-87065-Vl p 497 N89-20520 LNASA-CP-3020-VOL-1-PT-I] p 453 N89-20925 and transitional cavities p 444 A89-34744 Current status of flight simulation fatigue crack growth Flight research and testing p 453 N89-20927 Compressible flow losses in branched ducts concepts AH-IS communication switch integration program p 494 A89-35004 INLR-MP-88001 -U] p 497 N89-20521 [ NASA-TM-101053] p 466 N89-20978 A cell-vertex multigrid method for the Navier-Stokes Application of the boundary element method lo fatigue Aircraft tracking with dual TACAN equations crack growth analysis [ADA2026471 p 466 N89-20980 [ NASA-TM-IO15571 p 451 N89-20101 [AD-A202565] p 498 N89-21270 Contaminationof the exterior of a C-130E aircraft used FLOW MEASUREMENT FREE FLIGHT for aerial spray, 907 TAG, Rickenbacker ANGB. OH Analysis of the dedicated laser velocimeter systems at Development and implementation of flight control [AD-A202430] p 474 N89-20984 NASA - Langley Research Center p 484 A89-33384 system for a research drop model p 481 A89-33563
A-1 1 SUBJECT INDEX
FREE FLOW Structure and properties of forged ODS nickel-base GOVERNMENTPROCUREMENT Laser-induced adine fluorescence technique for superalloys p 491 A89-33461 Incorporatingfive nations' operational requirements into quantitative measurement in a nonreacting supersonic Metalliclimitations in aircraftengines - The rational return a single aircraft The F-16 multinational fighter program combustor p 445 A89-34809 lo the stone age p 477 A89-33485 viewed from the operational side Effect of jet grid turbulence on IUrbuknt boundary layer Potential applications for advanced structural ceramics [AD-A207552] p 474 N89-20986 heat transfer p 494 A89-34930 in aero gas turbine engines p 488 A89-33490 GRAPHITE-EPOXY COMPOSITES FREE MOLECULAR FLOW Evolutionof a small turbine engine family for unmanned Divergence instability of reinforcedcomposite cylindrical Computation of flow fields for hypersonic flight at hlgh aerial vehicles p 477 A89-33570 shells p 495 A89-35146 altitudes p 440 A89-33627 Heat transfer in gas turbine combustors GRAVITY WAVES FREQUENCIES p 491 A89-33580 Thunderstorm-generated solitary waves - A wind shear High-dynamic GPS tracking Fabrication of sintered alpha-Sic turbine engine hazard p 499 A89-34888 [NASA-CR-1848681 p 465 N89-20113 components p 491 A89-33621 GRID GENERATION (MATHEMATICS) FREOUENCY SHIFT KEYING Fatigue testing of gas turbine components A self-adaptive computational method for transonic Data links for video and IR surveillance p 485 A89-33804 turbulent flow past a real projectile p 443 A89-34730 p 465 A89-33567 Ceramics in high-temperature gas turbines (Review) Applications of a generalized pressure correction FRICTION FACTOR p 488 A89-34080 algorithm for flows in complicated geometries An entrance region friction factor model applied lo Characteristics of the formation of benz(a)pyrene in the p 493 A89-34738 annular seal analysis - Theory versus experiment for cornbustion chambers of aviation gas turbine engines Transonic Symposium: Theory, Application, and smooth and honeycomb seals p 488 A89-34119 Experiment. Volume 1. Part 1 [ASME PAPER 88-TRIB-41I p 493 A89-34798 Some characteristics of the formation of contaminants [NASA-CP-3020-VOL-t-PT-I I p 453 N89-20925 FUEL COMBUSTION during the combustion of hydrocarbon fuels in the Euler solvers for transonic applications Some characteristics of the formation of Contaminants cornbustion chambers of gas turbine engines p 454 N89-20935 during the combustion of hydrocarbon fuels in the p 488 A89-34120 Developments and trends in three-dimensional mesh combustion chambers of gas turbine engines An experimental study of the rate characteristics of brush generation p 455 N89-20940 p 488 A89-34120 seals in comparison with labyrinth seals Generation of unstructured grids and Euler solutions for A simple one-dimensional model for the effect of air p 492 A89-34136 complex geometries p 455 N89-20941 pollution on supersonic combustion p 488 A89-34121 Some aspects of the numerical modeling of the Transonic Symposium: Theory, Application, and Effect of turbulence on the combustion of an atomized nonstationary heat conductivity of gas turbine Experiment, volume 1, part 2 liquid fuel p 488 A89-34122 components p 477 A89-34139 [NASA-CP-3020-VOL-I-PT-2] p 455 N89-20942 Fuel-richcatalytic combustion of Jet-A fuel-equivalence An analytical-experimental study of ring gap losses in Transonic propulsion system integration analysis at ratios 5.0 to 8.0 small axial-flow turbines p 478 A89-34141 McDonnell Aircraft Company p 481 N89-20943 [ NASA.TM-I 019751 p 489 N89-21051 Adaptive control of the grinding of large gas turbine Method to predict external store carriage loads at Fuels combuslion research blades p 492 A89-34144 transonic speeds p 473 N89-20945 [AD-A2041611 p 490 N89-21071 Noise levels of a combined bypass-propfan engine in GROUNDBASEDCONTROL Gas turbine alternative fuels combustion the far sonic field p 478 A89-34150 Canadair SentinelISea Sentinel rotary wing RPV. IV characteristics Assessment of the adequacy of bearing lubrication in p 467 A89-33556 [NASA-TM-101470] p 499 N89-21417 a gas turbine engine through openings in the rotating GROUND EFFECT (AERODYNAMICS) FUEL CONTAMINATION shaft p 492 A89-34154 A study of the rotor wake in nap-of-the-eanh Some charactenstics of the formation of contaminants A new metnod for the thermodynamic calculation of p 439 A89-33140 dunng the combustion of hydrocarbon fuels in the combustion chambers p 478 A89-34409 GROUNDRESONANCE combustion chambers of gas turbine engines Heat transfer in gas turbine engines and Nonlinear rotorcraft analysis-experimental and p 488 A89-34120 three-dimensional flows; Proceedings of the Symposium, analytical FUELSPRAYS ASME Winter Annual Meeting, Chicago, IL. Nov. 27-Dec. [ADA203967 1 p 475 N89-20990 Effect of turbulence on the combustion of an atomized 2. 1988 p 494 A89-34926 GROUND STATIONS liquid fuel p 488 A89-34122 Effects of wake passing on stagnation region heat Integrated modular RPV ground station with reference FUEL TANKS transfer p 494 A8944928 to the 'Raven' project p 485 A8943575 Fuel holdup and component diffusivity in a cooled Local heat transfer in internally cooled turbine airfoil GROUND TESTS cylindrical tank p 488 A89-34894 leading edge regions. I - Impingement cooling without film Cabin noise control ground tests for UHB aircraft FULLSCALETESTS coolant extraction. II - Impingement cooling with film [AIAA PAPER 89-1121 ] p 469 A89-33755 Full-scale demonstration tests of cabin noise reduction coolant extraction p 494 A89-34932 GUIDE VANES using actie vibration control Experimental investigation of the thermal conductivity Effects of wake passing on stagnation region heat [AIAA PAPER 89-10741 p 468 A89-33719 of dispersed ceramic materials p 488 A89-34933 transfer p 494 A89-34928 Full-scale fatigue testing of aircraft structures Toward improved durability in advanced aircraft engine A comparison of secondary flow in a vane cascade and p 485 A8943802 hot sections a CUNed duct p 446 A89-34934 FUNCTIONAL DESIGN SPECIFICATIONS [NASA-TM-4087] p 479 N89-20135 GUST LOADS Linescan 2000 - Tomorrow's sensor today NASA HOST project overview p 479 N89-20136 On the relationship between matched filter theory as p 475 A89-33574 Assessment, development, and application of applied lo gust loads and phased design loads analysis FUSELAGES combustor aerothermal models p 479 N89-20138 [ NASA-CR-I81 8021 p 472 N89-20125 Prediction of structural-acousticresponse of an aircraft Review and assessment of the database and numerical fuselage modeled as a periodic structure modeling for turbine heat transfer p 479 N89-20139 [AIAA PAPER 89.1045) p 468 A89-33705 Structural analysis methods development for turbine hot H Adaptive actie controlof enclosed sound fields in elastic section components p 479 N89-20140 cylinders via vibrational inputs ... noise attenuation Structural analysis applications p 480 N89-20141 HARMONIC ANALYSIS research for advanced turboprop aircraft Fatigue life prediction modeling for turbine hot section Application of harmonic analysis method lo research [AIM PAPER 89-10751 p 469 A89-33720 materials p 480 N89-20142 on rotor airloads p 467 A89-33139 Fuselage boundary layer effects on sound propagation Life modeling of thermal barrier coatings for aircraft gas HARMONIC OSCILLATION and scattering turbine engines p 480 N89-20143 Development and application of a program to calculate [AIAA PAPER 89-1098] p 503 A8943738 Views on the impact of HOST p 480 N89-20144 transonic flow around an oscillatingthree-dimensional wing Noise and instability waves in supersonic jets in the High speed balancing applied lo the T700 engine using finite difference procedures proximity of flat and cylindrical walls [NASA-CR-180899] p 497 N89-20472 [NASACR-1817441 p 450 N89-20093 [AlAA PAPER 89-1 1361 p 503 A8943766 Fuel-rich catalytic combustion of Jet-A fuel-equivalence HARMONICS Model for investigation of helicopter fuselage influence ratios 5.0 to 8.0 Subharmonic and fundamental high amplitude excitation on rotor flowfields p 445 A89-34883 [NASA-TM-101975] p 489 N89-21051 of an axisymmetric jet Bulging cracks in pressurized fuselages: A numerical High density fuel effects [NASA-TM-101946] p 452 N89-20920 HARNESSES study [AD-A202426] p 490 N89-21125 A seat-mounted combined harness [ NLR-MP-87058-Ul p 497 N89-20519 Gas turbine alternative fuels combustion characteristics [AIAA PAPER 89-09371 p 463 A8945245 [ NASA-TM-101470] p 499 N89-21417 HAZARDS GAS TURBINES AH-I S communication switch integration program G Argon shrouded plasma coatings for gas turbine [NASA-TM-101053] p 466 N89-20978 Contamination of the exterior of a C-130E aircraft used applications p 491 A8943487 GAPS for aenal spray, 907 TAG, Rickenbacker ANGB. OH An analytical-experimental study of ring gap losses in Development of a shock capturing code for use as a tool in designing high-work low aspect ratio turbines [AD-A202430] p 474 N89-20984 small axial-flow turbines p 478 A89-34141 HEAT RESISTANT ALLOYS GAS EXPANSION [ADA2027061 P 498 N89-21248 GENERAL AVIATION AIRCRAFT PM superalloy turbine blades p 487 A89-33454 Numerical modeling of transonic flow of a viscous gas Advanced microstructural observations of gas turbine in a plane channel with a sudden expansion General aviation P 437 A89-34448 Aircraft accident reports, brief format, US civil and foreign P/M materials p 487 A89-33456 p 442 A8944149 aviation, issue number 14 of 1986 accidents Structure and properties of forged ODS nickel-base GAS JETS [PB88-916904] P 464 N89-20110 superalloys p 491 A89-33461 Transverse jets in compressible crossflows GLOBAL POSITIONING SYSTEM Structural analysis methods development for turbine hot p 452 N89-20923 High-dynamic GPS tracking section components p 479 N89-20140 GAS TURBINE ENGINES [ NASA-CR-184868l P 465 N89-20113 Fatigue life prediction modeling for turbine hot section The influence of a radial swirl generator on the flow Deriving a geocentric reference frame for satellite materials p 480 N89-20142 field from a fuel nozzle model p 490 A8943354 positioning and navigation P 466 N69-20330 Macrocrack-multiple defect interacton considering Advanced microstructural observations of gas turbine Determination of GPS orbits to submeter accuracy elastic. plastic and viscoplastic elfects P/M materials p 487 A89-33456 P 466 N89-20331 [AD-A203186] p 498 N89-21282
A-12 SUBJECT INDEX INERTIAL NAVIGATION
HEATTRANSFER HELIPORTS HYPERSONIC AIRCRAFT Heat transfer in gas turbine combustors Heliport System planning guidelines Technology requirements for hypersonic airbreathing p 491 A89-33580 [ AD-A199081 J p 486 N89-21003 aircraft p 468 A89-33626 Heat transfer in gas turbine engines and HELMET MOUNTED DISPLAYS High performance escape capsules three-dimensional flows; Proceedings of the Symposium, Real-time display of time dependent data using a [AIM PAPER 89-08781 p 470 A89-35202 ASME Winter Annual Meeting. Chicago, IL. Nov. 27-Dec. head-mounted display HYPERSONICBOUNDARYLAYER 2.1988 p 494 A89-34926 [AD-A203051] p 476 N89-20993 Hypersonic boundary-layertransition A helmet-mounted virtual environment display system ~ffectsof wake passing an s!agnation region heat p 441 A89-33646 [AD-A203055] p 475 N89-20994 transfer p 494 A89-34928 invesiigation of !he development of laminar HIGH ALTITUDE boundary-layer instabilities along a cooled-wall cone in Documentation of two- and threedimensional High altitude parachute and its military applications hypersonic Shock wavefturbulent boundary layer hypersonic flows [AlAA PAPER 89.08931 p 461 A89-35211 interaction flows HIGH ALTITUDE ENVIRONMENTS [AD-A202587] p 458 N89-20966 [ NASA-TM-1010751 p 451 N89-20100 HYPERSONIC FLIGHT Icing considerations for HALE (High Altitude. Long The flow on the lee-side of a delta wing at Mach 7 Review and assessment of the database and numerical Endurance) aircraft modeling for turbine heat transfer p 479 N89-20139 p 440 A89-33637 [AD-A202584] p 464 NB9-20975 Experimental methods for hypersonics Capabilitiesand HEAT TRANSFER COEFFICIENTS HIGH SPEED . limitations p 441 A89-33638 Prediitwn of heat transfer characteristics of discrete Turbulization of a high-velocity boundary layer by a Propulsion over a wide Mach number range hole film cooling - One row of injection into a turbulent projection p 448 A89-35434 [ NASA-CR-1822671 p 478 N89-20134 boundary layer p 494 A89-34931 High speed balancing applied to the T700 engine HYPERSONIC FLOW Local heat transfer in internally cooled turbine airfoil [ NASA-CR-1808991 p 497 N89-20472 Computation of flow fields for hypersonic flight at high leading edge regions. I - Impingement cooling without film HIGH TEMPERATURE altitudes p 440 A89-33627 coolant extraction. II lmpingemenr cooiing with film Rapid!y solidi!ied a!&nini.im alloys for high - A nmerical method for predicting hypersonic coolant extraction p 494 A89-34932 temperaturelhigh stiffness applications flowfields p 440 A89-33634 p 488 A89-33474 HELICOPTER CONTROL Computational methods for hypersonic flows - Special HIGH TEMPERATURE ENVIRONMENTS Frequency domain techniques applied to the techniques and real gas effects p 441 A89-33640 Experimental investigation of the thermal conductivity identificationof helicopter dynamics p 500 A89-35261 Turbulence modeling for hypersonic flows of dispersed ceramic materials p 488 A89-34933 Design of robust multivariable helicopter COntrd laws p 441 A89-33641 Views on the impact of HOST p 480 N89-20144 for handling qualities enhancement p 482 A89-35297 Numerical simulation of three-dimensional hypersonic HIGH TEMPERATURE FLUIDS HELICOPTER DESIGN viscous flows p 441 A89-33644 Fuel-richcatalytic combustion of Jet-A fuel-equivalence Fatigue evaluation of helicopter rotor heads Laminar-turbulenttransition problems at high speeds ratios to p 485 A89-33803 5.0 8.0 p 441 A89-33645 [NASA-TM-I01 9751 p 489 N89-21051 Active control helicopter aeromechanical and High-resolution shock-capturing schemes for inviscid HIGH TEMPERATURE GASES aeroelastic instabilities p 483 N89-20149 and viscous hypersonic flows p 443 A89-34646 Hot gas ingestion testing of an advanced STOVL HELICOPTER ENGINES Patched-gridcomputations of high-speed inlet flows concept in the NASA Lewis 9- by 15-fOOt Low Speed Wind Importance of engine as a source of helicopter external p 443 A89-34728 Tunnel with flow visualization noise Computation of external, hypersonic,three-dimensional [AIAA PAPER 88.30251 p 439 A89-33249 [AlAA PAPER 89.11471 p 470 A89-33771 flowfield and heat transfer p 494 A89-34935 HIGH TEMPERATURE RESEARCH HELICOPTER PERFORMANCE Viscous shock layer analysis of hypersonic flows over Toward improved durabiiiiy in advanced aircraft engine Development of experimental techniques for helicopter long slender vehicles p 451 N89-20097 rotor performance studies p 470 A89-35198 hot sections HYPERSONIC SPEED Hub and blade structural loads measurements of an [ NASA-TM-40871 p 479 N89-20135 A first scramjet study Advanced high temperature instrument for hot section SA34912 helicopter [NASA-CR-184965) p 480 N89-20146 [ NASA-TM-I01040] p 472 N89-20124 research applications p 479 N89-20137 HYPERSONIC VEHICLES Structural analysis methods development for turbine hot Nonlinear rotorcraft analysis-experimental and Mean and turbulent velocity measurements of section components p 479 N89-20140 analytical supersonic mixing layers p 440 A89-33426 [AD-A203967] p475 N89-Zo990 HIGH TEMPERATURE TESTS Identifyingsonic fatigue prone structureson a hypersonic The effect of stress ratio on the near-threshold fatigue HELICOPTER TAIL ROTORS Transatmospheric Vehicle (TAV) crack growth behavior of Ti-8AI-IMo-1V at elevated An analytical model for the prediction of MRlTR [AIM PAPER 89-11031 p 469 A89-33743 temperature p 489 A89-35722 interaction noise __.main rotorltail rotor Hypersonic drone design: A multidisciplinary [AIAA PAPER 89-11301 p 503 A89-33762 HOLOGRAPHIC INTERFEROMETRY experience Prediction of potential noise interactions in axial-flow Prospects for the application of holographic [NASA-CR-I847401 p 473 N89-20981 machines - Application to the helicopter fenestron interferometry to the study of the resonant vibrations of HYPERSONIC WIND TUNNELS p 504 A89-35385 complex systems p 495 A89-35654 High enthalpy testing in hypersonic shock tunnels Prediction of wake-interaction noise in axial-flow HONEYCOMB STRUCTURES p 485 A89-33630 machines - Application to helicopter fenestron Annular honeycomb seals: Test results for leakage and p 504 A89-35388 rotordynamic coefficients . Comparisons to labyrinth and HELICOPTER WAKES smooth configurations I A study of the rotor wake in nap-of-the-earth [ASME PAPER 88-TRIB-351 p 493 A89-34794 p 439 A89-33140 HORIZONTAL TAIL SURFACES ICE Helicopter rotor wake investigation using a laser Doppler Development and implementation of flight control Numerical simulation of flow over iced airfoils anemometry technique p 439 A89-33385 system for a research drop model p 481 A89-33563 [AD A203291 ] p 458 N89-20969 The prediction of blade wake interaction noise based HOTSURFACES ICE CLOUDS on a turbulent vortex model Structural analysis methods development for turbine hot Predicting the effects of aircraft icing [AIAA PAPER 89-11341 p 503 A89-33764 section components p 479 N89-20140 p 460 A89-33825 Surface pressure measurements on a body subject to HOVERING ICE FORMATION vortex wake interaction p 470 A89-34808 Performance optimization for rotors in hover and axial Predicting the effects of aircraft icing Prediction 01 wake-interaction noise in axial-flow flight p 460 A89-33825 machines - Application to helicopter fenestron [NASA-CR-1775241 p 459 N89-20973 Electromagnetic properties of ice coated surfaces p504 A89-35388 HUBS [ NASA-CR-1847801 p 495 N89-20355 Evaluation of VSAERO in prediction of aerodynamic Evaluation of VSAERO in prediction of aerodynamic Icing considerations for HALE (High Altitude, Long characten'stics of helicopter hub fairings characteristics of heliwpter hub fairings Endurance) aircraft [NASA-TM-101048] p 451 N89-20098 [ NASA-TM-1010481 p 451 N89-20098 [ADA2025841 p 464 N89-20975 Performance optimization for rotors in hover and axial Hub and blade structural loads measurements of an IDENTIFYING flight SA349l2 helicopter Modern multiple-pulse, high field NMR studies of high [NASA-CR-1775241 p 459 N89-20973 [ NASA-TM-1010401 p 472 N89-20124 density let fuels HELICOPTERS Integrated aerodynamicfdynamic optimization of [AD-A203320] p 490 N89-21130 Analysis of the dedicated laser velocimeter systems at helicopter rotor blades IMAGE PROCESSING NASA - Langley Research Center p 484 A89-33384 [NASA-TM-1015531 p 473 N89-20982 Some consequencesof reduced frame rate for operator performance p 465 A89-33573 Prediction of full system helicopter noise for a MDHC HUMAN FACTORS ENGINEERING 5OOE helicopter using the Rotonet program General aviation p 437 A89-34448 IMPACT LOADS [AIAA PAPER 89.11351 p 500 A89-33765 Transient dynamics of aircraft propellers during Air traffic control p 437 A89-34450 Model for investigation of helicopter fuselage influence touch-down impact p 470 A89-34509 on rotor flowfields p 445 A89-34883 HYDROCARBON FUELS IN-FLIGHT MONITORING Calculation of blade-vortex interaction airloads on Some characteristics of the formation of contaminants In-flight lightning characterization program on a CV-580 helicopter rotors p 446 A89-34895 during the combustion of hydrocarbon fuels in the aircraft Controlling severed helicopter blades during emergency cornbustion chambers of gas turbine engines [AD-A203954] p 464 N89-20976 escape p 471 A89-35842 p 488 A89-34120 INCOMPRESSIBLE FLOW Performance optimization for rotors in hover and axial HYDROCARBONS A new look at Theodorsen's method in aerofoil theory flight Gas turbine alternative fuels combustion p 443 A89-34621 [NASA-CR-177524] p 459 N89-20973 characteristics Incompressible cascade calculation using an upwind Integrated aerodynamic/dynamic optimization of [ NASA-TM-101470) p 499 N89-21417 differenced NOscheme p 444 A89-34733 helicopter rotor blades HYDRODYNAMIC RAM EFFECT INERTIAL NAVIGATION [NASA-TM-101553] p 473 N89-20982 The development of a 10,000 Ib capacity ram air Trajectory scoring in rectangular coordinates using Heliport system planning guidelines parachute transponder interrogator range and range rate data [AD-A19908l] p 486 N89-21003 [AIAA PAPER 89-09041 p 462 A89-35220 [DE89-0070051 p 466 N89-20119
A-13 INFLATABLE STRUCTURES SUBJECT INDEX
Aircraft tracking with dual TACAN Updated users' guide for TAWFIVE with multigrid KNOWLEDGE BASES (ARTIFICIAL INTELLIGENCE) ( AD-A2026471 p 466 N89-20980 [ NASA-TM-41091 p 496 N89-20409 Reliability and performance evaluation of SyStemS INFLATABLE STRUCTURES Vector potential methods p 455 N89-20939 containing embedded rule-based expert systems A coupling apparent mass for parachute inflation ISOTROPIC TURBULENCE [ NASA-CR-1817691 p 500 N89-20683 equations Single and multi-elementairfoils in an isotropic turbulent [AIAA PAPER 89-09331 p 447 A89-35243 outer flow p 439 A8943383 Radius-tipped triangular inflatable decelerator design as ITERATIVE SOLUTION L affected by produceabilily/suNivabilily constraints Two-measured variable method for wall interference [AIAA PAPER 89-08881 p 463 A89-36020 assessmentlcorreclion p 457 N89-20959 INFORMATION THEORY Response equivocation analysis for the smart stick controller [ AD-AZ031461 p 475 N89-20989 J INFRARED IMAGERY JET AIRCRAFT NOISE Multispectral terrain background Simulation techniques Simultaneous computation of jet turbulence and noise for use in airborne sensor evaluation [AIAA PAPER 89-10911 p 491 A8943731 p 499 A89-33664 INFRARED SCANNERS Sonic fatigue-resistant damped laminated structures Linescan 2000 - Tomorrow's sensor today [AIM PAPER 89-11021 p 469 A8943742 p 475 A89-33574 New static engine noise test techniques which reduce INLET FLOW test time significantly Patched-grid computations of high-swed inlet flows [AIAA PAPER 89-11271 p 485 A8943760 p 443 A89-34728 Noise and instability waves in supersonic jets in the INPUTlOUTPUT ROUTINES proximity of flat and cylindrical walls Thin-layer Navier-Stokes solutions for a cranked delta [AIAA PAPER 89-11361 p 503 A89-33766 wing JET ENGINE FUELS [AD-A2032921 p 459 N89-20970 Fuel-rich catalytic combustion of Jet-A fuel-equivalence INSPECTION ratios 5.0 lo 8.0 Aviation safety: Measuring how safely individual airlines [NASA-TM-101 9751 p 489 N89-21051 operate Fuels combustion research [GAO/RCED-88-61] p 464 N89-20974 [AD-A2041611 p 490 N89-21071 INTAKE SYSTEMS Modern multiple-pulse, high field NMR studies of high Hot gas ingestion testing of an advanced STOVL density jet fuels concept in the NASA Lewis 9- by 15-foot Low Speed Wind [AD-A2033201 p 490 N89-21130 Tunnel with flow visualization JET ENGINES [AIAA PAPER 88-30251 p 439 A89-33249 INTERACTIONALAERODYNAMICS 3-0 LDA-measurements in the jet of a bypass-engine Application of harmonic anaiysts method to research p 477 A89-33386 on rotor airloads p 467 A8943139 PM superalloy turbine blades p 487 A89-33454 On sound generationby a jet flow passinga semi-infinite Spray formed Waspaloy for disc forgings aerofoil p 487 A89-33463 [AIAA PAPER 89-10701 p 501 A89-33716 The development of a preliminary sizing method for Interactionnoise mechanismsforan advanced propeller unmanned air vehicles p 468 A8943564 - Experimental results Assessment of the adequacy of bearing lubrication in [AIAA PAPER 89-10931 p 502 A89-33733 a gas turbine engine through openings in the rotating Expenmental validationof a lining surface model for rotor shaft p 492 A89-34154 wake-slator interaction Expenmental examination of the aerothermal [AIAA PAPER 89-11251 p 441 A89-33758 performanceoftheT-1Otestcellat NAS(Nava1AirStation). An analytical model for the prediction of MR/TR Cubi Point interaction noise --- main rotorltail rotor [AD-A2038871 p 487 N89-21005 [AIAA PAPER 89-11301 p 503 A8943762 JET EXHAUST Large-eddy simulations of excitation effects on a VTOL Simultaneous computation of jet turbulence and noise upwash fountain p 442 A89-34461 Viscous-inviscid interaction and computation in [AIM PAPER 89-1091 1 p 491 A89-33731 aerodynamics Experimental examination of the aerothermal [ONERA, TP NO. 1988-1161 p 443 A89-34627 performance01 the T-10 test cell at NAS (Naval Air Station). Calculation of blade-vortex interaction airloads on Cubi Point helicopter rotors p 446 A8944895 [AD-A2038871 p 487 N89-21005 An experimental investgationof the aerodynamic loads JET FLOW on cambered plates Twin-jet screech suppression [AIAA PAPER 89-09351 p 447 A89-35244 [AIAA PAPER 89-11401 p 504 A89-33768 Prediction of potential noise interactions in axial-flow Subharmonic and fundamental high amplitude excitation machines - Application to the helicopter fenestron of an axisymmetric jet p 504 A89-35385 [NASA-TM-101 9461 p 452 N89-20920 Updated users' guide for TAWFIVE with multigrid JET IMPINGEMENT [NASA-TM-4109] p 496 N89-20409 On sound generation by a jet flow passing a semi-infinite Transonic Symposium: Theory. Application, and aerofoil Experiment, volume 1. part 2 [AIAA PAPER 89-10701 p 501 A8943716 [NASA-CP-3020-VOL-l-PT-2] p 455 N89-20942 Large-eddy simulations of excitation effects on a VTOL Inverse wing design in transonic flow including viscous upwash fountain p 442 A8944461 interaction p 473 N89-20947 Local heat transfer in internally cooled turbine airfoil Turbulent eddy viscosity modeling in transonic leading edge regions. I - Impingement cooling without film Instantaneous profiles and turbulence statistics of shocklbundary-layer interactions p 456 N89-20952 coolant extraction. II - Impingement cooling with film An LDA (Laser-Doppler Anemometry) investigation of supersonic free shear layers by Raman excitation + coolant extraction p 494 A8944932 three-dimensional normal shock wave boundary-layer laser-induced electronic fluorescence (relief) velocity JP-4 JET FUEL interactions p 456 N89-20956 tagging of oxygen p 440 A89-33424 High density fuel effects INTERFACES Laser-induced iodine fluorescence technique for 1 Performance analysis of the fiber distributed data [AD-A2024261 P 490 N89-21125 interface in the super cockpit audio world [AD-A202535] p 474 N89-20985 K INTERPROCESSOR COMMUNICATION Observer design for compensation of network-induced KALMAN FILTERS delays in integrated communication and control systems Trajectory scoring in rectangular coordinates using p 500 A89-35044 transponder-interrogatorrange and range rate data INVARIANCE [ DE89-0070051 P 466 N89-20119 Robust stabilization of linear time-invariant uncertain KEVLAR (TRADEMARK) systems via Lyapunov theory p 483 N89-20147 Development of an alternating flat to tubular Kevlar INVISCID FLOW parachute tape Viscous-inviscid interaction and computation in [AIM PAPER 89-09101 p 462 A89-35223 aerodynamics New lightweight parachute fabrics of Kevlar aramid [ONERA. TP NO. 1988-1161 p 443 A89-34627 fiber High-resolution shock-capturing schemes for inviscid [AIAA PAPER 89-09111 p 489 A89-35224 and viscous hypersonic flows p 443 A89-34646 KINETIC ENERGY Inviscid prediction of transonic flows in turbomachines The correlation between Reynolds stress and turbulent using a Runge-Kuna integration scheme kinetic energy in the near wake of a symmetric airfoil p 444 A89-34736 p 448 A8945393
A-14 SUBJECT INDEX MILITARY AIRCRAFT
Some considerations on leading edge vortices on wings Investigation of a free-tiprotor configuration for research MASS FLOW in supersonic flow p 450 A8946013 on spanwise life distributions and wake velocity surveys Performance of the active sidewall boundary-layer Numerical simulation of the flow field over delta wings of a semi-span wing with a discontinuous twist removal system for the Langley 0.3-meter Transonic with leading edge blowing p 453 N89-20924 [ NASA-CR-1849481 p 457 N89-20963 Cryogenic Tunnel An embedded mesh procedure for leading-edge vortex LOADING MOMENTS [NASA-CR-181793] p 486 N89-21004 flows p 455 N89-20936 Load alleviation on transport aircraft using acceleration MATCHED FILTERS feedback p 471 A89-35299 Thin-layer Navier-Stokes solutions for a cranked delta On the relationship between matched filter theory as LOADS (FORCES) wing applied to gust loads and phased design loads analysis [ AD-A2032921 p 459 N89-20970 Unsteady force calculations on circular cylinders and INASA-CR-1818021 p 472 N89-20125 elliptical airfoils with circulation control MATERIALS TESTS LEAKAGE [UMAERO-87-37] p 457 N89-20962 Annular honeycomb seals: Test results for leakage and Air Force tribology programs p 491 A8943448 LONGITUDINALSTABILITY MATHEMATICAL MODELS rotordynamic coefficients - Comparisons to labyrinth and An airfoil pitch apparatus-modelingand control design High Reynolds number incompressible flow simulation smooth configurations [ NASA-TM-101076l p 496 N89-20366 [ASME PAPER 88-TRIB-351 p 493 A8944794 about parachute canopies and similar bluff bodies LOW ASPECT RATIO p 450 N89-20096 An entrance region friction factor model applied to Development of a shock capturing code for use as a Geometrical and structural properties of an Aeroelastic annular seal analysis - Theory versus experiment for tool in designing high-work low aspect ratio turbines Research Wing (AAW-2) smwth and honeycomb seals [AD-A202706] p 496 N89-21248 [ NASA-TM-41IO] p 451 N89-20099 [ASME PAPER 88-TRIB-411 p 493 A89-34798 LOW ASPECT RATIO WINGS On the relationship between matched filter theory as LEE WAVES Advances in the ComDutation of transonic SeDarated applied to gust loads and phased design loads analysis The flow on the lee-side of a delta wing at Mach 7 flows over finite wings p 442 A89-34427 [ NASA-CR-1818021 p 472 N89-20125 p 440 A89-33637 LOW COST An analytical and numerical study of axial flow LIAPUNOV FUNCTIONS Low cost avionic system for UMA --- unmanned compressor instability p 478 N89-20131 Robust stabilization of linear time-invariant uncertain aircraft p 475 A89-33571 Review ana assessmeni oi tie database and ntimeiica! systems via Lyapunov theory p 483 N89-20147 LOW SPEED modeling for turbine heat transfer p 479 N89-20139 LIFE (DURABILITV) Some low-speed fluner characteristics of simple Fatigue life prediction modeling for turbine hot section Toward improved durability in advanced aircraft engine low-aspect-raho delta mng models materials p 480 N89-20142 hot sections [ NASA-TM-1015471 p 450 N89-20094 Modal cost analysis of flexible structures: Modeling [ NASA-TM-40871 p 479 N89-20135 LOW SPEED WIND TUNNELS flexible structures for control design p 483 N89-20148 Life modeling of thermal barrier coatings for aircraft gas Flowiield measurements in the NASA Lewis Research Active control helicopter aeromechanical and turbine engines p 480 N89-20143 Center 9- by 15-foot low-speed wind tunnel aeroelastic instabilities p 483 N89-20149 [ NASA-TM-l00883] p 486 N89-21002 LIFT Transmission and reflection on pressure waves by LOW TEMPERATURE TESTS Interaction noise mechanisms for advanced propellers compressor and turbine stages. based on an actuator-disk Investigation of the development of laminar - Analytical evaluation model boundary-layer instabilities along a cooled-wall cone in [AIAA PAPER 89-10941 p 502 A89-33734 [AD-A203513] p496 N89-20426 hypersonic flows Viscosity effects in the generation of the lifting force Analysis of crack opening behavior by application of a [AD-A202587] p 458 N89-20966 of aerodynamic wing profiles p 442 A89-34114 discretized strip yield model LUBRICATING OILS [ NLR-MP-87065-UI p 497 N89-20520 A first scramjet study Assessment of the adequacy of bearing lubrication in Transverse jets in compressible crossflows [ NASA-CR-1849651 p 480 N89-20146 a gas turbine engine through openings in the rotating p 452 N89-20923 Wave drag due to lifor transonic airplanes shaft p 492 A8944154 Performance analysis of the fiber distributed data p 455 N89-20938 interface in the super cockpit audio world Investigation of a free-tip rotor configuration for research [AD-A202535] p 474 N89-20985 on spanwise life distributions and wake velocity SUN~S M Aeroelastic modeling for the FIT team F/A-18 of a semi-span dng with a discontinuous twist simulation MAGNETIC SUSPENSION [ NASA-CR-1849481 p 457 N89-20963 [NASA-TM-I01 5691 p 475 N89-20991 Test techniques A survey paper on cryogenic tunnels. Numerical simulation of flow over iced airfoils Rotordynamic analysis of a bearing tester adaptive wall test sections. and magnetic suspension and IAD-AZ03291] p458 N89-20969 p 498 N69-21759 Thin-layer Navier-Stokes solutions for a cranked delta balance systems p 486 N89-20955 MATHEMATICS MAINTENANCE wing Mathematical research at the Aeronautical Research Contamination of the extenor of a C-l30E aircraft used [AD-A203292] p 459 N89-20970 Laboratories 1939-1960 p 437 A8942982 Methodologyfor using steady experimental aerodynamic for aerial spray, 907 TAG, Rickenbacker ANGB. OH MATRICES (MATHEMATICS) [AD-A202430] p 474 N89-20984 data to improve steady and unsteady aerodynamic Selection of a frequency sensitive QFT (Quantitative MAN MACHINE SYSTEMS analysis p 459 N89-20972 Feedback Theory) weighting matrix using the method of Aviation displays p 476 A8944443 LIFT DRAG RATIO specified outputs Cockpit automation p 460 A89-34444 Effect of wing tip strakes on wing liftdrag ratio [AD-A202692] p 501 N89-21592 p 445 A89-34886 Cockpit-crew systems design and integration MATRIX METHODS p 476 A89-34446 Induced drag and the ideal wake of a ling wing Selection of a frequency sensitive QFT (Quanhtative Air traffic control p 437 A8944450 p 446 A89-34898 Feedback Theory) weighting matrix using the method of A seat-mounted combined harness Effect of 90 degree flap on the aerodynamics of a specified outputs [AIM PAPER 89-09371 p 463 A89-35245 two-element airfoil p 446 A89-35053 [AD-A202692] p 501 N89-21592 LIFTING BODIES Flight controller design with nonlinear aerodynamics. MEMBRANE STRUCTURES On a method for solving integral equations of large parameter uncertainty and pilot compensation Numerical analysis of three-dimensional non rigid Iifting-SUrfaCetheory for oscillating high-speed propellers [ AD-AZO2727 1 p 484 N89-21000 wings p 439 A89-33100 MANIFOLDS [AIAA PAPER 89-09071 p 450 A69-36022 Experimentalvalidation of a lifting surface model for rotor Vanable structure control laws for aircraft manoeuvres METAL FATIGUE waksstator interaction p 482 A89-35286 Ouantitative fractography - Possibilities and applications [AIAA PAPER 89-11251 p 441 A8943758 MANNED SPACECRAFT in aircraft research p 495 A8945074 LIGHTNING AerosDace vehicle design.-. SDacecraft. Section final Fatigue life prediction modeling for turbine hot section Triggered lightning strikes to aircraft and natural project reports materials p 480 N89-20142 intracloud discharges p460 A89-35158 [NASA-CR-184741I p 471 N89-20121 METAL PLATES In-flight lightning characterization program on a CV-580 MARKOV PROCESSES Aeroelastic divergence of front-free-aft-fixedelastic strip aircraft Continuousdiscretefiltering -. for svstems with Markovian parallel to uniform flow p 495 A8945097 [AD-A203954] p 464 N89-20976 switching coefficients METALS LINE OF SIGHT COMMUNICATION INLR-MP-87076-U 1 0 465 N89-20117 Metallic limitations in aircraftengines - The rationalreturn Data links for video and IR surveillance Reliability and performance evaluation of systems to the stone age p 477 A8943485 p 465 A8933567 containing embedded rule-based expert systems MICROBURSTS (METEOROLOGY) LINEAR QUADRATIC GAUSSIAN CONTROL [NASA-CR-t81769] p 500 N89-20683 Analysis of Doppler radar windshear data Active control law svnthesis for flexible aircraft MARS (PLANET) [ NASA-CR-l81762] p 464 N89-20111 p 482 A6935045 Aerospace vehicle design. Spacecraft Section MICROSTRUCTURE LINEAR SYSTEMS [NASA-CR-1847431 p 472 N89-20123 Advanced microstructural ObSeNatiOnS of gas turbine Robust stabilization of linear time-invariant uncertain P/M malerials p 487 A89-33456 MARS SURFACE Systems via Lyapunov theory p 483 N89-20147 MICROWAVE LANDING SYSTEMS Aerospace vehicle design, Spacecraft Section final LIQUID CRYSTALS Microwave landing systems: Additional systems should A helmet-mounted virtual environment display system project reports not be procured unless benefits proven [NASA-CR-184741I p 471 N89-20121 [AD-A203055] p 476 N89-20994 [GAO/RCED88-118] p 466 N89-20977 LIQUID FUELS Aerospace vehicle design. Spacecraft Section final MIDAIR COLLISIONS Effect of turbulence on the combustion of an atomized project reports Aircraft accident data, US general aviation, calendar year liquid fuel p 468 A89-34122 [ NASA-CR-1847421 p 472 N89-20122 1986 LOAD DISTRIBUTION (FORCES) MASS [PB89-121453] p 463 N69-20106 Measurements of individual parachute loads in a Determining and accounting for a parachute virtual MILITARY AIR FACILITIES clustered parachute system mass p 460 A8944889 A microcomputer pollution model for civilian airportsand [AIAA PAPER 89-09231 p 463 A89-35233 MASS DISTRIBUTION Air Force bases. Model application and background On the relationship between matched filter theory as A revision of the added mass conced as aDDlied to [AD-A1997941 p 499 N89-20557 applied to gust loads and phased design loads analysis parachute motion MILITARY AIRCRAFT [NASA-CR-181 8021 p 472 N89-20125 [AIAA PAPER 89-08951 p 461 A89-35213 Air Force tribology programs p 491 A89-33448
A-15 MILITARY HELICOPTERS SUBJECT INDEX
The application of CFD for military aircraft design at Euler/Navier-Stokescalculations of transonic flow past NOISE PROPAGATION transonic speeds p 454 N89-20930 fixed- and rotary-wing aircraft configurations Installation effects on propeller wakelvortex induced MILITARY HELICOPTERS p 456 N89-20948 structure-borne noise transmission Some aspects of the development and operational The 3-D Euler and Navier-Stokes calculations for aircraft [AIAA PAPER 89-10721 p 468 A89-33717 testing of the Sprite system p 467 A89-33557 components p 498 N89-20950 NOISE REDUCTION MILITARY OPERATIONS Three-dimensional singular points in aerodynamics Prediction of structural-acoustic response of an aircraft Aerial delivery 01 personnel in ground proximity [ NASA-TM-1000451 p 457 N89-20964 fuselage modeled as a periodic structure [AIM PAPER 89-08871 p 461 A89-35207 Thin-layer Navier-Stokes solutions for a cranked delta [AlAA PAPER 89.10451 p 4613 A89-33705 MILITARY TECHNOLOGY wing In-flight experiments on the active control of Testing of a new recovery parachute system for the [AD-A203292] p 459 N89-20970 propeller-induced cabin noise F111 aircraft crew escape module - An update Two-dimensional Navier-Stokessolution of the flow over [AIAA PAPER 89-10471 p 468 A89-33706 [AIAA PAPER 89-08911 p 471 A89-35209 a thick supercritical airfoil with strong shock-induced Noise reduction of a composite cylinder subjected to High altitude parachute and its military applications separation random acoustic excitation [AIAA PAPER 89-08931 p 461 A89-35211 [ADA203331 ] p 459 N89-20971 [AIAA PAPER 89-10491 p 501 A89-33708 Radius-tipped triangular inflatabledecelerator design as NAVIGATION Full-scale demonstration tests of cabin noise reduction affected by produceabilitylsurvlvability constraints Trajectory scoring in rectangular coordinates using using active vibration control [AIM PAPER 89-08881 p 463 A89-36020 transponder-interrogator range and range rate data [AIAA PAPER 89.10741 p 468 A89-33719 [DE89-0070051 p 466 N89-20119 MISSION PLANNING Adaptive active control of enclosedsound fields in elastic NEAR WAKES Aerospace vehicle design, Spacecraft Section cylinders via vibrational inputs --- noise attenuation [ NASA-CR-1847431 p 472 N89-20123 Near wakes of advanced turbopropellers [AIAA PAPER 89.10951 p 441 A89-33735 research for advanced turboprop aircraft MIXING LAYERS (FLUIDS) [AIAA PAPER 89-10751 p 469 A89-33720 Mean and turbulent velocity measurements Of The correlation between Reynolds stress and turbulent supersonic mixing layers p 440 A89-33426 kinetic energy in the near wake of a symmetric airfoil Cabin noise control ground tests for UHB aircraft MODEL REFERENCE ADAPTIVE CONTROL p 448 A89-35393 [AIAA PAPER 89-1 1211 p 469 A89-33755 Variable structure model-following control of flight NICKEL ALLOYS Propeller modelling effects on interior noise in cylindrical dynamics p 482 A89-35300 Structure and properties of forged ODS nickel-base cavities with application to active control MODELS superalloys p 491 A89-33461 [AIAA PAPER 89-11231 p 469 A89-33757 Investigation of the development of laminar NOISE (SOUND) Twin-jet screech suppression boundary-layer instabilities along a cooled-wall cone in Comparison of propeller cruise noise data taken in the [AIAA PAPER 89-11401 p 504 A89-33768 hypersonic flows NASA Lewis 8- by 6-foot wind tunnel with other tunnel Attenuation of blast waves using foam and other [AD-A202587] p 458 N89-20966 and flight data materials MODULES [ NASA-TM-1019761 p 505 N89-21628 [ADA203148 I p 505 N89-21632 Preliminary design of a modular unmanned research NOISE GENERATORS NONDESTRUCTIVE TESTS vehicle. Volume 1: System design document Acoustic forcing of three dimensional shear layers Micro radiography and tomography for high resolution [AD-A202765] p 474 N89-20987 [AIM PAPER 89.10631 p 501 A89-33712 NDT of advanced materials and microstructural MOLECULAR STRUCTURE Finite element modelling of sheared flow effects on the components p 495 A89-35081 A (13)C NMR analysis of the effects of electron radiation radiation characteristics of acoustic sources in a circular NONLINEAR FEEDBACK on graphite/polyetherimide composites duct Flight controller design with noniinear aerodynamics. [ NASA-CR-I8281 p 489 N89-20205 81 [AIAA PAPER 89.10651 p 502 A89-33726 large parameter uncertainty and pilot compensation MONOPLANES A smart pattern recognition system for the automatic [AD-A202727] p 484 N89-21000 Falconet target RPV operations p 437 A89-33559 identificationof aerospace acoustic sources NONLINEAR FILTERS MULTIPROCESSING (COMPUTERS) [AIM PAPER 89-1 1141 p 499 A89-33751 Continuous-discretefiltering for systems with Markovian Implementation of a transputer-based flight controller Experimental investigation of rotor wakelstator switching coefficients p 482 A89-35302 interaction noise generation by acoustic mode [ NLR-MP-87076-UI p 465 N89-20117 MULTISPECTRAL BAND SCANNERS measurements Multispectral terrain background simulation techniques [AIAA PAPER 89-11261 p 503 A89-33759 NORMAL SHOCK WAVES for use in airborne sensor evaluation Sound generation and flow interaction of vortices with An LDA (Laser-Doppler Anemometry) investigation of p 499 A89-33664 an airfoil and a flat plate in transonic flow three-dimensional normal shock wave boundary-layer MULTIVARIATE STATISTICAL ANALYSIS p 449 A89-36006 interactions p 456 N89-20956 A digital rate controller for the control reconfigurable NOISE MEASUREMENT NOZZLE DESIGN combat aircraft designed using quantitative feedback Interior noise in the untreated Gulfstream II Propfan Test Effect of the design of a two-row nozzle rihg on the theory Assessment (PTA) aircraft efficiency of a turbine stage of medium rotor solidity [AD-A20305Ol p 484 N89-21001 [AIAA PAPER 89-11191 p 469 A89-33754 p 477 A89-34140 NOISE POLLUTION Comparison of 3D computation and experiment for Fuselage boundary layer effects on sound propagation non-axisymmetrie nozzles N and scattering [NASA-CR-1822451 p 452 N89-20921 [AIAA PAPER 89-10981 p 503 A89-33738 NAP-OF-THE-EARTH NAVIGATION Effect of riblets upon flow separation in a subsonic Advanced turboprop aircraft flyover noise annoyance - diffuser A study of the rotor wake in napof-the-earth Comparison of different propeller configurations [AD-A203178] p 458 N89-20967 p 439 A89-33140 [AIAA PAPER 89-11281 p 503 A89-33761 NOZZLE FLOW AH-I S communication switch integration program NOISE PREDICTION [ NASA-TM-1010531 p 466 N89-20978 The influence of a radial swirl generator on the flow Prediction of wake-interaction noise in axial-flow field from a fuel nozzle model p 490 A89-33354 NASA PROGRAMS machines - Application to helicopter fenestron NASA HOST project overview p 479 N89-20136 Simultaneous computation of jet turbulence and noise p 504 A89-35388 [AIAA PAPER 89-10911 p 491 A89-33731 Views on the impact of HOST p 480 N89-20144 NOISE PREDICTION (AlRCRAFTl Twin-jet screech suppression NASTRAN Prediction of structural-acoustic response of an aircraft Coupled rotorlluselage dynamic analysis of the AH-1G [AIAA PAPER 89-11401 p 504 A89-33768 fuselage modeled as a periodic structure helicopter and correlation with flight vibrations data [AIAA PAPER 89-10451 p 468 A89-33705 A first scramjet study [NASA-CR-1817231 p 497 N89-20512 Model size requirements for finite element prediction [NASA-CR-1849651 p 480 N89-20146 NATIONAL AIRSPACE SYSTEM of low-frequency cabin noise and vibration NUCLEAR MAGNETIC RESONANCE Microwave landing systems: Additional systems should [AIAA PAPER 89-10761 p 469 A89-33721 A (13)C NMR analysis of the effects of electron radiation not be procured unless benefits proven Asymptoticlnumericalanalysis of supersonic propeller on graphitelpolyetherimidecomposites [GAO/RCED-88-118] p 466 N89-20977 noise [ NASA-CR-1828181 p 489 N89-20205 NAVIER-STOKES EQUATION [AIAA PAPER 89-10781 p 501 A89-33722 Modern multiple-pulse, high field NMR studies of high Navier-Stokes calculations of scramjet-afterbody Simultaneous computation of jet turbulence and noise density jet fuels flowfields p 443 A89-34732 [AIM PAPER 89.10911 p 491 A89-33731 [AD-A203320] p 490 N89-21130 Navier-Stokes calculations 01 transonic flows past open Interaction noise mechanisms for advanced propellers NUMERICAL ANALYSIS and transitional cavities p 444 A89-34744 - Analytical evaluation An analytical and numerical study of axial flow Navier-Stokes simulation of unsteady three-dimensional [AIAA PAPER 89-10941 p 502 A89-33734 compressor instability p 478 N89-20131 blade-vortex interactions p 444 A89-34745 Near-field noise of a pusher propeller Evaluation of algebraic turbulence models for PNS Wave drag due to lift for transonic airplanes [AIAA PAPER 89.10961 p 502 A89-33736 p 455 N89-20938 predictions of supersonic llow past a sphere-cone An analytical model for the prediction of MRlTR Application 01 the boundary element method to fatigue p 445 A89-34807 interaction noise --- main rotorltail rotor Euler and Navier-Stokes leeside flows over supersonic crack growth analysis [AIM PAPER 89-11301 p 503 A89-33762 [ADA2025651 p 498 N89-21270 delta wings p 445 A89-34892 Integrating the acoustic analogy for supersonoc rotating A cell-vertex multigrid method lor the Navier-Stokes surfaces NUMERICAL FLOW VISUALIZATION equations Numerical simulation of three-dimensional hypersonic [AIM PAPER 89-11331 p 503 A89-33763 [ NASA-TM-1015571 p 451 N89-20101 The prediction of blade wake interaction noise based viscous flows p 441 A89-33644 Comparison of 3D computation and experiment for on a turbulent vortex model Direct numerical simulation 01 a three-dimensional non-axisymmetric nozzles [AIAA PAPER 89.11341 p 503 A89-33764 turbulent boundary layer p 493 A89-34909 [ NASA-CR-1822451 p 452 N89-20921 Prediction of full system helicopter noise for a MDHC Bipolar coordinates for computation of transition duct Computation of aircraft component flow fields at 500E helicopter using the Rotonet program flows p 493 A89-34912 transonic Mach numbers using a three-dimensional [AlAA PAPER 89-11351 P 500 A89-33765 NUMERICAL STABILITY Navier-Stokes algorithm p 454 N89-20933 Prediction of potential noise interactions in axial-flow Numerical instabilities in the calculation of laminar Euler solvers for transonic applications machines .Application to the helicopter fenestron separation bubbles and their implications p 454 N89-20935 p 504 A89-35385 p 445 A89-34819
A-16 SUBJECT INDEX PREDICTION ANALYSIS TECHNIQUES
0 A control canopy release method for improved opening AH-IS communication switch integration program of clustered parachutes [ NASA-TM-1010531 p 466 N89-20978 OBSERVABILITY (SYSTEMS) [AIM PAPER 89-08921 p 461 A89-35210 Response equivocation analysis for the smart stick Observer design for compensation of network-induced High altitude parachute and its military applications controller delays in integrated communication and control systems [AIAA PAPER 89-08931 p 461 A89-35211 [AD-A203146] p 475 N89-20989 p 500 A89-35044 The development of the panel stabilized slotted-square PILOTLESS AIRCRAFT parachute ONBOARD DATA PROCESSING The US. Navy unmanned air vehicle program Electronics in civil aviation lAlAA PAPER 69-08941 p 461 A89-35212 p 437 A89-33555 A revision of the added mass concept as applied to [ NLR-MP-87009-Ul p 476 N89-20129 Flight test of XRAE-1 to establish aerodynamic data parachute motion p 468 A89-33562 OPERATINGTEMPERATURE [AIM PAPER 89-08951 p 461 A89-35213 Assessment of the adequacy of bearing lubncation in A preliminary characterization of parachute wake The development of a preliminary sizing method for a gas turbine engine through openings in the rotating recontact unmanned air vehicles p 468 A89-33564 shaft p 492 A89-34154 [AIAA PAPER 89-08971 p 447 A89-35214 The computer controlled system for multi-drone OPERATOR PERFORMANCE Flow visualization studies of wake behind axisymmetric performing formation flight in a same aerial zone Some consequences of reduced frame rate for operator bluff bodies including parachute canopy models p 481 A89-33566 performance p 465 A89-33573 [AIAA PAPER 89-08981 p 447 A89-35215 Evolution of a small turbine engine family for unmanned OPTICAL RADAR Prediction of parachute collapse due to wake aerial vehicles p 477 A89-33570 NASA lidar velocimetry measurements recontact p 491 A89-33435 Low cost avionic system for UMA --- unmanned [AIAA PAPER 89-0901 I p 447 A89-35218 aircraft p 475 A89-33571 OPTIMIZATION Tethered parafoil test technique PILOTS (PERSONNEL) The development of a preliminary sizing method for [AIM PAPER 89-09031 p 462 A89-35219 unmanned air vehicles ~4%A69-33564 Pilot ejection from a pronated flying position The developmeni oi a iO.000 I: iapaci?j :a- Bir [A!.M PAPER AR-0885j p 471 A89-35205 Optimal profile selection in the design of a subsonic parachute turbine cascade p 442 A89-34152 PITCH (INCLINATION) [AIAA PAPER 89-09041 p 462 A89-35220 An airfoil pitch apparatus-modeling and control design Efficient optimization of integrated Evolution of the manta-ray parachute aerodynamic-structuraldesign p 500 A89-34569 [NASA-TM-101 0761 p 496 N89-20386 [AIAA PAPER 8949061 p 462 A89-35221 PLANETARYBOUNDARYLAYER Performance Optimization for rotors in hover and axial Investigation of the service and age lives of US. Army flight A physical-statisticalmethod for the predictionof vertical personnel parachutes [NASA-CR-1775241 p 459 N89-20973 wind shear in the lower part of the atmospheric boundary [AIAA PAPER 89-09151 p 462 A89-35227 Integrated aerodynamicldynamic optimization of layer p 499 A89-34028 Personnel parachute agelservice life criteria helicopter rotor blades PLASMA SPRAYING [AIAA PAPER 89-09161 p 462 A89-35228 [NASA-TM-1015531 p 473 N89-20982 Argon shrouded plasma coatings for gas turbine Measurements of individual parachute loads in a ORBITAL POSITION ESTIMATION applications p 491 A89-33487 clustered parachute system Determination of GPS orbits to submeter accuracy PLASTIC AIRCRAFT STRUCTURES [AIM PAPER 89-09231 p 463 A89-35233 p 466 N89-20331 Designing with advanced fibrous composites Small parachute flight data acquisition system OSCILLATING FLOW p 470 A89-35197 [AIAA PAPER 89-09241 p 463 A89-35234 Experimental investigation of transonic oscillating PLATES (STRUCTURAL MEMBERS) Parachute drawing standards currently in use at Sandia cascade aerodynamics An experimental investigation of the aerodynamic loads National Laboratories [ NASA-TM-1019931 p 478 N89-20133 on cambered plates [AIM PAPER 89-09271 p 495 A89-35237 OXYGEN [AIM PAPER 89-09351 p 447 A89-35244 Parachutes Yesterday, today, and tomorrow Fire extinguishing agents for oxygen-enriched - POLISHING p 463 A89-36019 atmospheres p 487 A89-32948 [AIAA PAPER 89-08801 Adaptive control of the grinding of large gas turbine High Reynolds number incompressible flow simulation blades p 492 A89-34144 about parachute canopies and similar bluff bodies POLYMER MATRIX COMPOSITES P p 450 N89-20096 The load-bearing capacity of closed-profile oblong PARALLEL PROCESSING (COMPUTERS) cylindrical shells made of a metallpolymer composite PACKINGS (SEALS) Implementation of a transputer-basedflight controller laminate p 492 A89-34128 An experimentalstudy of the rate characteristics of brush p 482 A89-35302 A (1 3)C NMR analysis of the effects of electron radiation seals in comparison with labyrinth seals PASSENGER AIRCRAFT on graphitelpolyetherimidecomposites p 492 A89-34136 New wings. new ways p 471 A89-35825 [ NASA-CR-1828181 p 489 N89-20205 PANEL METHOD (FLUID DYNAMICS) PATERN RECOGNITION POROSITY Investigation of a free-tip rotor configuration for research A smart panern recognition system for the automatic Comparison of airfoil results from an adaptlve wall test on spanwise life distributions and wake velocity surveys identificationof aerospace acoustic sources section and a porous wall test section of a semi-span wing with a discontinuous twist [AlAA PAPER 89-11141 p 499 A89-33751 p 457 N89-20960 [NASA-CR-184948] p 457 N89-20963 Modern multiple-pulse, high field NMR studies of high POSITION ERRORS PANELS density jet fuels Position error calibration of a pressure survey aircraft Sonic fatigue and nonlinear response of stiffened [AD-A203320] p 490 N89-21130 using a trailing cone panels PAYLOADS [ PB88-2507331 p 450 N89-20092 [AIAA PAPER 89-llOl] p 492 A89-33741 Linescan 2000 - Tomorrow's sensor today POTENTIAL FLOW Fast, in-situ repair of aircraft panel components p 475 A89-33574 Second order accurate finite difference approximations p 438 A89-34896 PERFORATEDSHELLS for the transonic small disturbance equation and the lull The development of the panel stabilized slotted-square Natural vibrations of cylindrical shells with a rectangular potential equation p 444 A89-34740 parachute cutout p 492 A89-34126 Potential models of transonic flows [AIM PAPER 8948941 p 461 A89-35212 PERFORMANCE PREDICTION p 449 A89-35495 PARACHUTEDESCENT Evaluation of VSAERO in prediction of aerodynamic POTENTIAL THEORY An approximate method for calculating aircraft characteristics of helicopter hub fairings Vector potential methods p 455 N89-20939 downwash on parachute trajectories [ NASA-TM-1010481 p 451 N89-20098 POWDER METALLURGY [AIAA PAPER 89-08991 p 447 A8935216 Views on the impact of HOST p 480 N89-20144 PM superalloy turbine blades p 487 A89-33454 An experimental investigationof the aerodynamic loads Performance optimization for rotors in hover and axial Advanced microstructural observations 01 gas turbine on cambered plates flight PIM materials p 487 A89-33456 [AIAA PAPER 89-09351 p 447 A89-35244 [NASA-CR-117524] p 459 N89-20973 Spray formed Waspaloy for disc forgings An expression for dynamic strain in a 'weak link' Nonlinear rotorcraft analysis-experimental and p 487 A89-33463 [AIAA PAPER 89-09421 p 495 A89-35247 analytical Titanium PM anributes and potential for aircraft engine PARACHUTE FABRICS [AD-A203967] p 475 N89-20990 applications p 487 A89-33465 Testing of a new recovery parachute system for the Rotordynamic analysis of a bearing tester POWER EFFICIENCY F111 aircraft crew escape module - An update p 498 N89-21759 An analytical-experimental study of ring gap losses in [AIAA PAPER 8!3-0891] p 471 A89-35209 PERFORMANCE TESTS small axial-flow turbines p478 A8934141 Development of an alternating flat to tubular Kevlar Development of experimental techniques for helicopter Effect of the blade height at the exit of the shrouded parachute tape rotor performance studies p 470 A89-35198 rotor of a radial-flowcentripetal microturbineon the turbine [AIAA PAPER 89-09lOl p 462 A89-35223 Transoniclsupersonic (720 KEAS 1.2 Mach) ejection efficiency p 492 A89-34155 New lightweight parachute fabrics of Kevlar aramid demonstration test of an S4S Biofidelity Manikin (BFMI) Power efficient hydraulic systems. Volume 1: Study fiber p 463 A89-35841 phase [AIAA PAPER 89-091 1 ] p 489 A89-35224 A study Of transonic drag reduction of a blunt cylinder [ AD-A203899] p 472 N89-20127 A critical review of the state of the art for measurement by a cylinder probe POWER SPECTRA Of stress in parachute fabrics [ADA2025571 p 458 N89-20965 Sound power spectrum and wave drag 01 a propeller [AIAA PAPER 89-09251 p 489 A89-35235 High density fuel effects in flight PARACHUTES [AD-A202426] p 490 N89-21125 [AIM PAPER 89-10811 p 502 A89-33724 Determining and accounting ior a parachute VirtUal Rotordynamic analysis of a bearing tester Matching Power Spectra Density (PSD)-design load --- mass p 460 A89-34889 p 498 N89-21759 aircraft structures Modeling of parachute opening . An experimental PILOT PERFORMANCE [NLR-MP-87059-U1 p 472 N89-20126 investigation p 460 A89-34891 General aviation p 437 A89-34448 PREDICTION ANALYSIS TECHNIQUES AIAA Aerodynamic Decelerator Systems Technology Aircraft accident report: Continental Airlines, Inc.. Flight Evaluation of algebraic turbulence models for PNS Conference. loth, Cocoa Beach. FL. Apr. 18-20, 1989. 1713, McDonnell Douglas DC-9-14. N628TX. Stapleton predictions of supersonic flow past a sphere-cone Technical Papers p 461 A8935201 International Airport, Denver, Colorado, November 15, p 445 A89-34807 Aerial delivery of personnel in ground proximity 1987 Fatigue life prediction modeling for turbine hot section [AIAA PAPER 89-08871 p 461 A89-35207 [PB88-910411] p 464 N89-20112 materials p 480 N89-20142
A-17 PRESSURE DISTRIBUTION SUBJECT INDEX
Current status of flight simulation fatigue crack growth Acoustic characteristics of counterrotating fans from R concepts model scale tests [ NLR-MP-88001-U] p 497 N89-20521 [AIAA PAPER 89-11421 p 477 A89-33769 RADAR CROSS SECTIONS Estimation of the Equivalent Initial Flow Size (EIFS) Civil-transport aircraft at Aerospatiale Electromagnetic properties of ice coated surfaces distnbution.~ and prediction Of failure probabilities for p 438 A89-35378 [ NASA-CR-I847801 p 495 N89-20355 RADAR DETECTION different parameter Variations PROPELLER BLADES [ FFA-TN-1987-351 p 498 N89-20525 Electromagnetic properties of ice coated surfaces Structural Tailoring of Advanced Turboprops (STAT) Investigation of a free-tiprotor configurationfor research [NASA-CR-184780] p 495 N89-20355 programmer’s manual RADAR ECHOES on spanwise life distributions and wake velocity Surveys [NASA-CR-I821 641 p 478 N89-20132 of a semi-span wing with a discontinuous twist Electromagnetic properties of ice coated surfaces [ NASA-CR-1849481 p 457 N69-20963 Unsteady blade pressure measurements on a model [ NASA-CR-1847801 p 495 N89-20355 Two-dimensionalNavier-Stokes Solution of the flow Over counterrotation propeller RADAR SIGNATURES a thick supercritical airfoil with strong shock-induced [ NASA-TM-1020021 p 504 N89-20779 Analysis of Doppler radar windshear data separation PROPELLER DRIVE [ NASA-CR-181762] p 464 N89-20111 [AD-A2033311 p 459 N89-20971 Prediction of structural-acoustic response of an aircraft RADIO CONTROL PRESSURE DISTRIBUTION fuselage modeled as a periodic structure Data links for video and IR surveillance Applications of a generalized pressure correction [AIAA PAPER 89-10451 p 468 A89-33705 p 465 A89-33567 RADIOGRAPHY algorithm for flows in Complicated geometries In-flight experiments on the active control Of Micro radiography and tomography for high resolution p 493 A89-34738 propeller-induced cabin noise Surface pressure measurements on a body subject to [AIAA PAPER 89-10471 p 468 A89-33706 NOT of advanced materials and microstructural vortex wake interaction p 470 A89-34608 components p 495 A89-35081 PROPELLER EFFICIENCY Inverse wing design in transonic flow including viscous RAMAN LASERS interaction p 473 N89-20947 Sound power spectrum and wave drag of a propeller Instantaneous profiles and turbulence statistics of in flight Methodologyfor using steady experimental aerodynamic supersonic free shear layers by Raman excitation + [AlAA PAPER 89-1081 p 502 A89-33724 data to improve steady and unsteady aerodynamic I laser-induced electronic fluorescence (relief) velocity analysis p 459 N89-20972 Structural Tailoring of Advanced Turboprops (STAT) tagging of oxygen p 440 A89-33424 PRESSURE DROP programmer’s manual RANDOMPROCESSES Compressible flow losses in branched ducts [NASA-CR-I82164] p 478 N89-20132 On the relationship between matched filter theory as p 494 A89-35004 PROPELLER FANS applied to gust loads and phased design loads analysis PRESSURE EFFECTS Interaction noise mechanisms for advanced propellers [ NASA-CR-1818021 p 472 N89-20125 Geometrical and structural properties of an Aeroelastic - Analytical evaluation RANGEFINDING Research Wing (ARW-2) [AIM PAPER 89-10941 p 502 A89-33734 Development of a low cost trackinglranging system [NASA-TM-41101 p 451 N89-20099 p 465 A89-33572 PROPELLERS PRESSURE GRADIENTS RAPID QUENCHING (METALLURGY) Comparison of LOA and LTA application for propeller Transitional flow on axial turbomachine blading Rapidly solidified aluminum alloys for high tests in wind tunnels p 490 A89-33381 p 445 A89-34811 temperaturelhigh stiffness applications Stability of compressible boundary layers Installation effects on propeller wakelvortex induced p 488 A89-33474 p 456 N89-20953 structure-borne noise transmission RAREFIED GAS DYNAMICS PRESSUREMEASUREMENT [AIAA PAPER 89-10721 p 468 A89-33717 Computation of flow fields for hypersonic flight at high Unsteady blade pressure measurements on a model Asymptoticlnumerical analysis of supersonic propeller altitudes p 440 A89-33627 counterrotation propeller noise RATES (PER TIME) [ NASA-TM-1020021 p 504 N89-20779 [AIAA PAPER 89-10781 p 501 A89-33722 Trajectory scoring in rectangular coordinates using PRESSURESENSORS A lilting line model for propeller noise transponder-interrogator range and range rate data Unsteady blade pressure measurements on a model [AIAA PAPER 89-10791 p 502 A89-33723 [ DE89-0070051 p 466 N89-20119 counterrotation propeller Finite element modelling of sheared flow effects on the REACTION KINETICS [ NASA-TM-1020021 p 504 N89-20779 radiation characteristics of acoustic sources in a circular Fuels combustion research PRESSURE SWITCHES duct [AD-A204161] p 490 N89-21071 Power efficient hydraulic systems. Volume 2: Hardware [AIAA PAPER 89-10851 p 502 A89-33726 REAL GASES demonstration phase Near-field noise of a pusher propeller Computational methods for hypersonic flows - Special [ AD-A203W01 p 473 N89-20128 [AIAA PAPER 89-10961 p 502 A89-33736 techniques and real gas effects p 441 A89-33640 PROBABILITY DENSITY FUNCTIONS The effect of the wind tunnel wall boundary layer on REAL TIME OPERATION Real-time display of time dependent data using a Matching Power Spectra Density (PSD)-design load --- the acoustic testing of propellers aircraft structures [AlAA PAPER 89-10971 p 503 A89-33737 head-mounted display [ NLR-MP-87059-UI p 472 N89-20126 [AD-A203051I p 476 N89-20993 PROBABILITY THEORY Propeller modelling effects on interior noise in cylindrical RECEIVERS Icing consrderatbns for HALE (High Altitude, Long cavities with application to active control High-dynamic GPS tracking [AIAA PAPER 89-11231 p 469 A89-33757 Endurance) aircraft [NASA-CR-184868] p 465 N89-20113 [ AD-A2025841 p 464 N89-20975 Transient dynamics of aircraft propellers during RECOVERY PROBLEM SOLVING touch-down impact p 470 A89-34509 Launch, recovery and handling systems for vertical Reliability and performance evaluation of systems Numencal solutions for the flowfield around a take-off and landing UAVs operating from small ships containing embedded rule-based expert systems counter-rotating propeller p 445 A89-34887 p 484 A89-33569 [NASA-CR-181 7691 p 500 N89-20683 Companson of propeller cruise noise data taken in the RECOVERY PARACHUTES Hypersonic drone design: A multidisciplinary NASA Lewis 8- by 6-foot wind tunnel with other tunnel Testing of a new recovery parachute system for the experience and flight data F111 aircraft crew escape module - An update [NASA-CR-1847401 p 473 N89-20981 [NASA-TM-101976] p 505 N89-21628 [AIAA PAPER 89-0891 I p 471 A89-35209 PRODUCTDEVELOPMENT PROPULSION SYSTEM CONFIGURATIONS The development and testing of the HlSAC parachute New wings, new ways p 471 A89-35825 Aerospace vehicle design, Spacecraft Section final recovery system Assessment. development. and application of project reports [AIAA PAPER 89-0921I p 462 A89-35231 combustor aerothermal models p 479 N89-20138 [NASA-CR-184741] p 471 N89-20121 A seat-mounted combined harness PRODUCTION ENGINEERING PROPULSION SYSTEM PERFORMANCE [AIAA PAPER 89-09371 p 463 A89-35245 Incorporating five nations’ operational requirements into Propulsion over a wide Mach number range The effects of unsteady aerodynamics on single and a single aircraft: The F-16 multinational fighter program [ NASA-CR-1822671 p 478 N89-20134 clustered parachute system viewed from the operational side Transonic propulsion system integration analysis at [AIAA PAPER 89-09341 p 448 A89-35250 [AD-A202552] p 474 N89-20986 McDonnell Aircraft Company p 481 N89-20943 RECOVERY VEHICLES Design aspects of a naval RPV recovery system PROGRAM VERIFICATION (COMPUTERS) PROPULSIVE EFFICIENCY p 484 A89-33568 Transonics and fighter aircraft: Challenges and Propulsion over a wide Mach number range RECTANGULAR WINGS opportunities for CFD p 454 N89-20932 [NASA-CR-1822671 p 478 N89-20134 PROJECTILES Development and applicatmn of a program to calculate PROTECTIVE COATINGS transonic flow around an oscillatingthree-dimensional wing A self-adaptive computational method for transonic Argon shrouded plasma coatings for gas turbine turbulent flow past a real projectile p 443 A89-34730 using finite difference procedures applications P 491 A89-33487 [ NASA-CR-1817441 p 450 N89-20093 PRONE POSITION PYRENES REDUNDANCY Pilot ejection from a pronated flying position Characteristics of the formation of benz(a)pyrene in the The application of sollware fault tolerance to air traffic [AIAA PAPER 89-08851 p 471 A89-35205 combustion chambers of aviation gas turbine engines control: Study contract overview PROP-FAN TECHNOLOGY P 488 A89-34119 [ BRIO85671 p 465 N89-20114 Sound power spectrum and wave drag of a propeller REENTRY VEHICLES in flight Cornputation of flow fields for hypersonic flight at high [AIAA PAPER 89-10811 p 502 A89-33724 Q altitudes p 440 A89-33627 Interactionnoise mechanismsfor an advanced propeller REFLECTION - Experimental results QUALITY CONTROL Transmission and reflection on pressure waves by [AIM PAPER 89-10931 p 502 A89-33733 Ensuring the quality of the covering surface in the case compressor and turbine stages, based on an actuator-disk Near wakes of advanced turbopropellers of riveted joints with high radial interference model [AIAA PAPER 89-10951 p 441 A89-33735 P 492 A89-34159 [AD-A203513] p 496 N89-20426 Interior noise in the untreated Gullstream II Propfan Test QUENCHING (COOLING) REFRACTORY COATINGS Assessment (PTA) aircraft Quench sensitivity of airframe aluminum alloys Life modeling of thermal barrier coatings for aircraft gas [AlAA PAPER 89-11191 p 469 A89-33754 [NLR-MP-88003-U] P 469 N89-20231 turbine engines p 480 N89-20143
A-18 SUBJECT INDEX ROTORS
REGULATIONS Incorporating five nations' operational requirements into Helicopter rotor wake investigation using a laser Doppler Aviation safety: Measuring how safely individual airlines a single aircran: The F-16 multinational fighter program anemometry technique p 439 A89-33385 operate viewed from the operational side An analytical model for the prediction of MRfTR [GAO/RCED-88-611 p 464 N89-20974 [ AD-A202552 I p 474 N89-20986 interaction noise --- main rotorftail rotor REINFORCED PLASTICS RESEARCH [AIAA PAPER 89-1 1301 p 503 A89-33762 Efficient optimization of integrated Attenuation of blast waves using foam and other Integrating the acoustic analogy for supersonic rotating aerodynamic-structuraldesign p 500 A89-34569 materials surfaces Divergenceinstability of reinforcedcomposite cylindrical [AD-A203148] p 505 N89-21632 [AiAA PAPER 89-1 133 I p 503 A89-33763 RESEARCH AIRCRAFT shells p 495 A89-35146 Fatigue evaluation of helicopter rotor heads Triggered lightning strlkes to aircraft and natural REINFORCED SHELLS p 485 A89-33803 intracloud discharges p 460 A89-35158 The load-bearing capacity of closed-profile oblong ONERA research on civil aircraft p 438 A89-35376 The load-bearing capacity of closed-profile oblong cylindrical shells made of a metalfpolymer composite Simulation at Dryden Flight Research Facility from 1957 cylindrical shells made of a metalfpolymer composite laminate p 492 A89-34128 to 1982 laminate p 492 A89-34128 REINFORCEMENT (STRUCTURES) [ NASA-TM-1016951 p 474 N89-20983 Model for investigation of helicopter fuselage influence On the design of biaxially stiffened composite plates Preliminary design of a modular unmanned research on rotor flowfields p 445 A89-34883 p 493 A89-34867 vehicle. Volume 1. System design document Development of experimental techniques for helicopter RELIABILITY [AD-A202765] p 474 N89-20987 rotor performance studies p 470 A89-35198 The application of software fault tolerance to air traffic RESEARCHANDDEVELOPMENT Acoustic test of a model rotor and tail rotor: Results control: Study contract overview DFVLR, Annual Repolf 1987 p 437 A89-32775 for the isolated rotors and combined configuration [ BR1085671 p 465 N89-20114 RESEARCH FACILITIES [ NASA-TM-101550I p 504 N89-20777 RELIABILITY ANALYSIS L"!hematical research at the Aeronautical Research Integrated aerodynamtc/dynamic optimization of The reliability analysis of aircraft structures Laboratories 1939-1960 p 437 A89-32982 helicopter rotor blaaes p 467 A89-33146 RESEARCH MANAGEMENT [ NASA-TM-101553] p 473 N89-20982 Reliability and performance evaluation of systems Flight research and testing p 453 N89-20927 ROTATING DISKS containing embedded rule-based expert systems RESEARCH VEHICLES Development of a rotary value for pulse combustion [NASA-CR-1817691 p 500 N89-20683 Preliminary design of a modular unmanned research applications RELIABILITY ENGINEERING vehicle. Volume 1: System design document [PB89-131114] p 496 N89-20468 Toward improved durability in advanced aircraft engine [ AD-A202765] p 474 N89-20987 ROTATING SHAFTS RESONANT FREQUENCIES hot sections Rotordynamic analysis of a bearing tester Prediction of structural-acousticresponse of an aircraft [ NASA-TM-40871 p 479 N89-20135 p 498 N89-21759 Airworthiness and flight characteristics evaluation of an fuselage modeled as a periodic structure [AIAA PAPER 89-10451 p 468 A89-33705 ROTATING STALLS improved engine air filtration system on the UH-1H Computational study of the effect of cascade parameters helicopter Prospects for the application of holographic interferometry to the study of the resonant vibrations of on stall propagation in axial compressors [AD-A203446] p 480 N89-20145 p 444 A89-34737 REMOTE CONTROL complex systems p 495 A89-35654 RESONANT VIBRATION ROTOR AERODYNAMICS The computer controlled system for multi-drone Acoustic test of a model rotor and tail rotor: Results On a method for solving integral equations of performing formation flight in a same aerial zone lifting-surfacetheory for oscillating high-speed propellers p 481 A89-33566 for the isolated rotors and combined configuration [ NASA-TM-101550] p 504 N89-20777 p 439 A89-33100 REMOTE SENSORS REYNOLDS NUMBER Application of harmonic analysis method to research Multispectral terrain background simulation techniques Observed Reynolds number effects on airfoils and high on rotor airloads p 467 A89-33139 for use in airborne sensor evaluation aspect ratio wings at transonic flow conditions A study of the rotor wake in nap-of-the-earth p499 A89-33664 [NLR-MP-88W-U] p 451 N89-20102 p 439 A89-33140 REMOTELY PILOTED VEHICLES REYNOLDS STRESS Analysis of the dedicated laser velocimeter systems at Remotely piloted vehicles; International Conference, The correlation between Reynolds stress and turbulent NASA - Langley Research Center p 484 A89-33384 7th. Bristol. England, Sept. 12-14, 1988, Proceedings and kinetic energy in the near wake of a symmetric airfoil Supplementary Papers p 467 A89-33554 Experimentalvalidation of a liftingsurface modelfor rotor p 448 A89-35393 wake-stator interaction The US. Navy unmanned air vehicle program RIBBON PARACHUTES [AIAA PAPER 89-11251 p 441 A89-33758 p 437 A8833555 Wall-interference corrections for parachutes in a closed Acoustic characteristics of counterrotating fans from Canadair SentineIlSea Sentinel rotary wing RPV. IV wind tunnel model scale tests p 467 A89-33556 [AIAA PAPER 89-09001 p 485 A89-35217 [AIAA PAPER 89-11421 p 477 A89-33769 Some aspects of the development and operational A coupling apparent mass for parachute inflation Navier-Stokes simulation of unsteady three-dimensional testing the Sprite system p 467 A8933557 equations of blade-vortex interactions p 444 A89-34745 Complementary minis - Skyeye and Phoenix. an overview [AIAA PAPER 89-09331 p 447 A89-35243 of their multi-mission coverage p 467 A89-33558 The effects of unsteady aerodynamics on single and Surface pressure measurements on a body subject to Falconet target RPV operations p 437 A89-33559 clustered parachute system vortex wake interaction p 470 A89-34808 Civilian RPVs - Eye in the sky or pie in the sky? [AIM PAPER 89.09341 p 448 A89-35250 Results from laser sheet visualization of a periodic rotor p 437 A89-33560 RIBLETS wake p 485 A89-34890 The Theta Beta - Design of a system --.remotely piloted Effect of riblets upon flow separation in a subsonic Calculation of blade-vortex interaction airloads on civil aircraft p 468 A89-33561 diffuser helicopter rotors p 446 A89-34895 The development of a preliminary sizing method for [ AD-MO31781 p 458 N89-20967 Aeroelastic deformation effects on the stopped-rotor unmanned air vehicles p468 A89-33564 RIGID ROTORS dynamics of an X-wing aircraft p 482 A89-34897 The Norton P73 rotary RPV engine Nonlinear rotorcraft analysis-experimental and Hub and blade structural loads measurements of an p 477 A89-33565 analytical SA34912 helicopter Data links lor video and IR surveillance [AD-A203967l p 475 N89-20990 [ NASA-TM-101040] p 472 N89-20124 p 465 A89-33567 RIVETED JOINTS Unsteady blade pressure measurements on a model Design aspects of a naval RPV recovery system Ensuring the quality of the covering surface in the case counterrotationpropeller p 484 A89-33568 of riveted joints with high radial interference [ NASA-TM-1020021 p 504 N89-20779 Launch. recovery and handling Systems for vertical p 492 A89-34159 Rotordynamic analysis of a bearing tester take-off and landing UAVs operating from small ships ROBUSTNESS (MATHEMATICS) p 498 N89-21759 p 484 A89-33569 Active control law synthesis for flexible aircraft ROTORBLADES Evolution of a small turbine engine family for unmanned p 482 A89-35045 The prediction of blade wake interaction noise based aerial vehicles p 477 A89-33570 Robust stabilization of linear time-invariant uncertain on a turbulent vortex model Low cost avionic system for UMA --- unmanned systems via Lyapunov theory p 483 N89-20147 [AIAA PAPER 89-11341 p 503 A89-33764 aircraft p 475 A89-33571 Actuation constraints in multivariable flight control Fatigue evaluation of helicopter rotor heads Development of a low cost trackinglranging system systems p 483 N89-20998 p 485 A89-33803 p 465 A89-33572 ROTARY ENGINES Controllina severed helicooter blades durina emeraencv Some consequences of reduced frame rate for operator The Norton P73 rotary RPV engine escape p 471 " A89.<584; performance p 465 A89-33573 p 477 A89-33565 ROTOR BLADES (TURBOMACHINERY) Linescan 2000 - Tomorrow's sensor today ROTARY WING AIRCRAFT Hiah speed balancina- applied.. to the T700 enaine p 475 A89-33574 Canadair SentinellSea Sentinel rotary wing RPV. IV [NASA-GR-l808991 p 497 N89-20472 Integrated modular RPV ground station with reference p 467 A89-33556 ROTOR BODY INTERACTIONS to the 'Raven' project p 485 A89-33575 Some aspects of the development and operational Model for investigation of helicopter fuselage influence Tailless aircraft performanceimprovements with relaxed testing of the Sprite system p 467 A89-33557 on rotor flowfields p 445 A89-34883 static stability Aeroelastic deformation effects on the stopped-rotor Hub and blade structural loads measurements of an [ NASA-CR-I81 8061 p 483 N89-20999 dynamics of an X-wing aircraft p 482 A89-34897 SA3490 helicopter REMOVAL Nonlinear rotorcraft analysis-experimental and [ NASA-TM-101040] p 472 N89-20124 Performance of the active sidewall boundary-layer analytical Coupled rotorffuselage dynamic analysis of the AH-1G removal system for the Langley 0.3-meter Transonic [AD-A203967] p 475 N89-20990 helicopter and correlation with flight vibrations data Cryogenic Tunnel ROTARY WINGS [ NASA-CR-1817231 P 497 N89-20512 [ NASA-CR-1817931 p 486 N89-21004 On a method for solving integral equations of ROTORS REOUIREMENTS lifting-surfacetheory for oscillating high-speed propellers Experimental investigation of rotor wakefstator Aerospace vehicle design, Spacecraft Section final p 439 A89-33100 interaction noise generation by acoustic mode project reports Analysis of the dedicated laser velocimeter systems at measurements [ NASA-CR-1847421 p 472 N89-20122 NASA - Langley Research Center p 484 A89-33384 [AlAA PAPER 89-11261 p 503 A89-33759 RUNGE-KUlTA METHOD SUBJECT INDEX
Annular honeycomb seals: Test results for leakage and SERVICE LIFE SIMULATORS rotordynamic coefficients - Comparisons to labyrinth and Investigation of the service and age lives of U.S. Army A real-time simulator of a turbofan engine smooth configurations personnel parachutes [ NASA-TM-I008691 p 481 N89-20995 [ASME PAPER 88-TRIB-351 p 493 A89-34794 [AIAA PAPER 89-09151 p 462 A89-35227 SINGULARITY (MATHEMATICS) An entrance region friction factor model applied to Personnel parachute agelservice life criterie Three-dimensional singular points in aerodynamics annular seal analysis - Theory versus experiment for [AIAA PAPER 89.09161 p 462 A89-35228 [NASA-TM-100045] p 457 N89-20964 smooth and honeycomb Seals Environment-assisted aerospace fatigue problems in SLENDER BODIES [ASME PAPER 88-TRIB-411 p 493 A89-34798 The Netherlands Viscous shock layer analysis of hypersonic flows over Perlormance optimization for rotors in hover and axial I NLR-MP-88004-Ul p 439 N89-20087 long slender vehicles p 451 N89-20097 SLENDER WINGS flight SERVOMECHANISMS Observed Reynolds number effects on airfoils and high [ NASA-CR-1775241 p 459 N89-20973 Power efficient hydraulic systems. Volume 2: Hardware aspect ratio wings at transonic flow conditions RUNGE-KUlTA METHOD demonstration phase [ NLR-MP-88006-Ul p 451 N89-20102 Inviscid prediction of transonic flows in turbomachines ADA203900 I p 473 N89-20128 SMALL PERTURBATION FLOW using a Runge-Kuna integration scheme SHEAR FLOW p 444 A89-34736 Second order accurate finite difference approximations Finite element modelling of sheared flow effects on the A cell-vertex multigrid method for the Navier-Stokes for the transonic small disturbance equation and the full radiation characteristics of acoustic sources in a circular potential equation p 444 A89-34740 equations duct [NASA-TM-1015571 p 451 N89-20101 Steady and unsteady transonic small disturbance [AlAA PAPER 89-10851 p 502 A89-33726 The 3-13Euler and Navier-Stokescalculations for aircraft analysis of realistic aircraft configurations components p 498 N89-20950 SHEARLAYERS p 473 N89-20946 Instantaneous profiles and turbulence statistics of SOFTWARE TOOLS supersonic free shear layers by Raman excitation + Reliability and performance evaluation of systems S laser-induced electronic fluorescence (relien velocity containing embedded Nle-baSed expert systems tagging of oxygen p 440 A89-33424 [NASA-CR-I 81 7691 p 500 N89-20683 SADDLE POINTS Acoustic forcing of three dimensional shear layers SOOT Three-dimensional singular pints in aerodynamics [AIAA PAPER 89-10631 p 501 A8943712 Fuels combustion research [ NASA-TM-1000451 p 457 N89-20964 Subharmonic and fundamental high amplitude excitation [AD-A204161 ] p 490 N89-21071 SAFETY of an axisymmetric jet SOUND FIELDS Nonlinear rotorcraft analysisexperimental and [ NASA-TM-I01 9461 p 452 N89-20920 A lifting line model for propeller noise ana l yt lca l SHEAR PROPERTIES [AlAA PAPER 89.10791 p 502 A89-33723 [AD-A2039671 p 475 N89-20990 Integrated aerodynamicldynamic optimization of SOUND PROPAGATION SAFETY FACTORS helicopter rotor blades Fuselage boundary layer effects on sound propagation General aviation p 437 A89-34448 [NASA-TM-1015531 p 473 N89-20982 and scattering SAMPLING SHEATHS [AIAA PAPER 89-10981 p 503 A89-33738 In-flight lightning charactenzationprogram on a CV-580 Ensuring the quality of the covering surface in the case SOUND TRANSMISSION aircraft of riveted joints with high radial interference Installation effects on propeller wakelvortex induced [AD-A203954] p 464 N89-20976 p 492 A89-34159 structure-borne noise transmission SATELLITE TRACKING SHELL STABILITY [AIM PAPER 89-1072) p 468 A89-33717 Denving a geocentric reference frame for satellita SPACE EXPLORATION The load-bearing capacity of closed-profile oblong posltoning and navigation p 466 N89-20330 Aerospace vehicle design, Spacecraft Section final Determination of GPS orbits to submeter accuracy cylindrical shells made of a metallpolymer composite laminate p 492 A89-34128 project reports p 466 N89-20331 [ NASA-CR-1847421 p 472 N89-20122 SCALE MODELS Formulation and solution of axisymmetric problems in SPACECRAFT CONFIGURATIONS Acoustic characteristics of counterrotating fans from the statics of multilayer shells of revolution with contact Technology requirements for hypersonic airbreathing interaction between layers p 492 A89-34129 model scale tests aircraft p 468 A89-33626 [AIAA PAPER 89.11421 p 477 A89-33769 SHIPS SPACECRAFT DESIGN SCATTERING Design aspects of a naval RPV recovery system Technology requirements for hypersonic airbreathing A microcomputerpollution model for civilian airports and p 484 A89-33568 aircraft p 468 A89-33626 Air Force bases. Model application and background SHOCK DISCONTINUITY SPECTROSCOPY [ AD-A1997941 p 499 N89-20557 High-resolution shock-capturing schemes for inviscid Modern multiple-pulse, high field NMR studies of high SCORING and viscous hypersonic flows p 443 A89-34646 density jet fuels Trajectory scoring in rectangular coordinates using SHOCK LAYERS [ AD-A203320] p 490 N89-21130 transponder-interrogator range and range rate data Viscous shock layer analysis of hypersonic flows over SPIN DYNAMICS [ DE89-0070051 p 466 N89-20119 long slender vehicles p 451 N89-20097 A mathematical model of aircraft spin and results of SEALS (STOPPERS) Shock-boundary-layerinteraction in flight its computer integration p 481 A89-34130 Annular honeycomb seals. Test results for leakage and p 453 N89-20928 Spin testing methods in flight p 470 A89-35196 rotordynamic coefficients - Comparisons to labyrinth and SHOCK LOADS SPLINE FUNCTIONS smooth configurations Development of a shock capturing code for use as a Finite-surfacespline p 500 A89-34900 [ASME PAPER 88-TRIB-351 p 493 A89-34794 tool in designing high-work low aspect ratio turbines SPRAYED COATINGS An entrance region friction factor model applied to [ AD-A2027061 p 498 N89-21248 Argon shrouded plasma coatings for gas turbine annular seal analysis Theory versus experiment for - SHOCK TUNNELS SPRAYERSapplications p 491 A8943487 smooth and honeycomb seals High enthalpy testing in hypersonic shock tunnels [ASME PAPER 88-TRIB-41I p 493 A89-34798 p 485 A89-33630 Contamination of the exterior of a C-I 30E aircraft used SECONDARY FLOW SHOCK WAVE INTERACTION for aerial spray, 907 TAG, Rickenbacker ANGB, OH A comparison of secondary flow in a vane cascade and Turbulent eddy viscosity modeling in transonic [ AD-A202430] p 474 N89-20984 a curved duct p 446 A89-34934 shocklboundary-layer interactions p 456 N89-20952 SPRAYING Secondary three-dimensional instability in compressible An LDA (Laser-Doppler Anemometry) investigation of Spray formed Waspaloy for disc forgings boundary layers p 456 N89-20954 three-dimensional normal shock wave boundary-layer p 487 A89-33463 SELF OSCILLATION interactions p 456 N89-20956 STABILITY Natural vibrations of cylindrical shells with a rectangular SHOCK WAVES Actuation constraints in multivariable flight control cutout p 492 A89-34126 Forward flight effects on broadband shock associated systems p 483 N89-20998 SENSORS noise of supersonic jets STABILITY DERIVATIVES Linescan 2M)o - Tomorrow’s sensor today [AIAA PAPER 89-10881 p 502 A89-33729 Methodology lor using steady experimental aerodynamic p 475 A89-33574 Calculation of compression shock surfaces in data to improve steady and unsteady aerodynamic SEPARATED FLOW three-dimensional, steady supersonic flows using a analysis p 459 N89-20972 Acoustic forcing of three dimensional shear layers bicharacteristic method p 446 A89-35168 Aeroelastic modeling lor the FIT team FIA-18 [AIAA PAPER 89.10631 p 501 A89-33712 Documentation of two- and three-dimensional simulation Analysis of separated flow past a thin profile in the case hypersonic shock wavelturbulent boundary layer [NASA-TM-l01569] p 475 N89-20991 of translational oscillations p 442 A8944151 interaction flows STABILITY TESTS Advances in the computation of transonic separated [NASA-TM-IOI075] P 451 N89-20100 Investigation of the development of laminar flows over finite wings p 442 A8944427 SIGNAL DETECTORS boundary-layer instabilities along a cooled-wall cone in hypersonic flows Investigation of flow separation in a three-dimensional Improved computer simulation of the TCAS 3 circular diffuser using a coupled Euler and boundary-layer array mounted on an aircraft p 458 N89-20966 STAGNATION[AD-A2025871 FLOW method p 446 A8945172 [NASA-CR-184907] p 496 N89-20363 SIGNAL TRANSMISSION Effects of wake passing on stagnation region heat Three-dimensional singular points in aerodynamics Some consequences of reduced frame rate for operator transfer p 494 A89-34928 [NASA-TM-100045] p 457 N89-20964 performance P 465 A89-33573 STALLING Effect of riblets upon flow separation in a subsonic High-dynamic GPS tracking An analytical and numerical study of axial flow diffuser [ NASA-CR-I848681 P 465 N89-20113 compressor instability p 478 N89-20131 [AD-A2031781 p 458 N89-20967 SILICON CARBIDES STANDARDS Numerical simulation of flow over iced airfoils Fabrication of sintered alpha-Sic turbine engine High speed balancing applied to the T700 engine [AD-A203291] p 458 N89-20969 components p 491 A89-33621 [ NASA-CR-I808991 p 497 N89-20472 Two-dimensional Navier-Stokessolution of the flow over SIMULATION STATIC DEFORMATION a thick supercritical airfoil with strong shock-induced High Reynolds number incompressible flow simulation Formulatin and solution Of axisymrnetrii problems in separation about parachute canopies and similar bluff bodies the statics of multilayer shells of revolution with contact [AD-A203331] p 459 N89-20971 p 450 N89-20096 interaction between layers p 492 A89-34129
A-20 SUBJECT INDEX SYNTHETIC FUELS
STATIC PRESSURE Analysis of crack opening behavior by application of a SUPERSONIC FLOW Position error calibration of a pressure survey aircraft discretized strip yield model Particle image displacement velocimetry applied in high using a trailing cone [ NLR-MP-87065-Ul p 497 N89-20520 speed flows p 490 A89-33388 [PB88-2507331 p 450 N89-20092 STRUCTURAL DESIGN Measurements of a supersonic turbulent vortex Flowfield measurements in the NASA Lewis Research Efficient optimization of integrated p 440 A89-33423 Center 9. by 15-foot low-speed wind tunnel aerodynamic-structuraldesign p 500 A89-34569 Mean and turbulent velocity measurements of [NASA-TM-1008831 p 486 N89-21002 Designing with advanced fibrous composites supersonic mixing layers p 440 A89-33426 STATIC STABILITY p 470 A89-35197 Laminar-turbulent transition problems at high speeds A wind tunnel and computer investigation of the low Aerospace vehicle design, Spacecraft Section final p 441 A89-33645 project reports speed aerodynamic characteristics 01 the prone escape Evaluation of algebraic turbulence models for PNS system (PRESS) [NASA-CR-1847421 p 472 N89-20122 Aerospace vehicle design, Spacecraft Section predictions of supersonic flow past a sphere-cone [AD-A202768] p 475 N89-20988 p 445 A89-34807 Tailless aircraft performance improvementswith relaxed [ NASA-CR-I847431 p 472 N89-20123 STRUCTURAL DESIGN CRITERIA Euler and Navier-Stokes leeside flows over supersonic static stability delta wings p 445 A89-34892 [ NASA-CR-I81 8061 p 483 N89-20999 Metallic limitations in aircralt engines - The rational return to the stone age p 477 A8943485 Calculation of compression shock surfaces in STATIC TESTS three-dimensional, steady supersonic flows using a New static engine noise test techniques which reduce Matching Power Spectra Density (PSD)-design load --- bicharacteristic method p 446 A89-35168 test time significantly aircraft structures [AIAA PAPER 89-11271 p 485 A89-33760 [NLR-MP-87059-U] p 472 N89-20126 A combined method lor calculating supersonic flow of STATOR BLADES STRUCTURAL ENGINEERING an ideal gas past a wing with a supersonic blunt leading Experimental investigation of rotor wakelstator Potential applications for advanced structural ceramics edge p 448 A89-35430 interaction noise generation by aioiis:ic mode in aero gas turbine engines p 488 A89-33490 Thin axisymmetnc caverns in supersonic flow measurements STRUCTURAL FAILURE p 449 .4.89-35435 [AIAA PAPER 89-11261 p 503 A89-33759 Estimation of the Equivalent Initial Flow Size (EIFS) Supersonic flow past caret wings and elements of STATORS distribution and prediction of failure probabilities for star-shaped bodies at angles of attack and bank Experimentalvalidation of a liftingsurface model lor rotor different parameter variations p 449 A89-35481 wake-stator interaction [ FFA-TN-1987.351 p 498 N89-20525 Some considerations on leading edge vortices on wings [AIAA PAPER 89-11251 p 441 A89-33758 STRUCTURAL RELIABILITY in supersonic flow p 450 A89-36013 The reliability analysis of aircraft Structures STEADY FLOW Comparison of 3D computation and experiment lor p 467 A89-33146 A numerical investigation of steady transonic cascade non-axisymmetric nozzles Full-scale fatigue testing 01 components and structures flow in turbomachinery p 448 A89-35417 (NASA-CR-182245I D 452 N89-20921 Steady and unsteady transonic small disturbance --- Book p 485 A89-33801 STRUCTURAL STABILITY Transverse jets in compressible crossflows analysis of realistic aircraft configurations P 452 N89-20923 p 473 N89-20946 Divergenceinstability of reinforced composite cylindrical SUPERSONIC JET FLOW Methodologylor using steady experimentalaerodynamic shells p 495 A89-35146 Fonvard flight effects on broadband shock associated data to improve steady and unsteady aerodynamic STRUCTURAL VIBRATION analysis p 459 N89-20972 Full-scaledemonstration tests of cabin noise reduction noise of supersonic jets [AIAA PAPER 89.10881 p 502 A8943729 STIFFENING using active vibration control On the design 01 biaxially stiffened composite plates [AIAA PAPER 89-10741 p 468 A8943719 Noise and instability waves in supersonic jets in the p 493 A89-34867 Sonic fatigue-resistant damped laminated structures proximity of flat and cylindrical walls STIFFNESS [AIAA PAPER 89-11021 p 469 A89-33742 [AIAA PAPER 89-11361 p 503 A89-33766 Rapidly solidified aluminum alloys for high Natural vibrations of cylindncal shells with a rectangular SUPERSONIC SPEED temperaturelhighstiffness applications cutout p 492 A8944126 Integrating the acoustic analogy for supersonic rotating p 488 A89-33474 Structural optimization for aeroelastic control surfaces STOCHASTIC PROCESSES effectiveness p 470 A89-34899 [AIAA PAPER 89-11331 p 503 A89-33763 Observer design for Compensation of network-induced Prospects lor the application of holographic Transonic/supersonic (720 KEAS 1.2 Mach) ejection delays in integrated communication and control systems interferometry to the study of the resonant vibrations of demonstration test of an S4S Biofidelity Manikin (BFM1) p 500 A89-35044 complex systems p 495 A89-35654 p 463 A89-35841 Quantitative design for systems with uncertainty and SUBSONIC FLOW SUPERSONIC WIND TUNNELS control failures p 500 A89-35283 A comparison of the turbulence structure of subsonic A studv of transonic draa reduction of a blunt cvlinder STRAIN DISTRIBUTION and supersonic boundary layers p 440 A8943425 by a cylinder probe An expression for dynamic strain in a 'weak iirii' C!p!ima! profile selection in the design of a subsonic [AD-A202557] p 458 N89-20965 [AIAA PAPER 89-os471 P 495 A8945247 turbine cascade p 442 A89-34152 SUPERSONICS STRAIN GAGES Wind-tunnel wall effects on delta wings Nonlinear kink modes for supersonic vortex sheets Advanced high temperature instrument for hot section p 445 A89-34884 p 442 A89-33783 SUPPORT INTERFERENCE research applications p 479 N89-20137 Effect of riblets upon flow separation in a subsonic STRAIN MEASUREMENT difluser Test techniques: A survey paper on cryogenic tunnels, Advanced high temperature instrument for hot section [AD-A203178] p 458 N89-20967 adaptive wall test sections. and magnetic suspension and research applications p 479 N89-20137 balance systems p 486 N89-20955 Numerical simulation of flow over iced airfoils SURFACE FINISHING STRAKES [AD-A203291] p 458 N89-20969 Effect of wing tip strakes on wing lift-drag ratio Adaptive control of the grinding of large gas turbine p 445 A89-34886 SUPERCRITICALAIRFOILS blades p 492 A89-34144 STRESS ANALYSIS Transonic buffet of a supercriticalairfoil with trailing-edge SURFACE PROPERTIES flap p 446 A8944893 A critical review of the state 01 the art for measurement Ensuring the quality of the covering surface in the case of stress in parachute fabrics Geometrical and structural properties of an Aeroelastic of riveted joints with high radial interference [AIAA PAPER 89-09251 p 489 A89-35235 Research Wing (ARW-2) p 492 A89-34159 An expression lor dynamic strain in a 'weak link' [ NASA-TM-41101 p 451 N89-20099 SURFACETEMPERATURE [AIAA PAPER 89.09421 p 495 A8945247 An experimental study of transonic buffet of a Advanced high temperature instrument for hot section STRESS CORROSION CRACKING supercritical airfoil with trailing edge flap research applications p 479 N89-20137 Environment-assisted aerospace fatigue problems in [AD-A2031891 p 458 N89-20968 SURFACE VEHICLES The Netherlands Two-dimensionalNavier-Stokes solution of the flow over A microcomputer pollution model for civilian airports and [ NLR-MP-88004-UI p 439 N89-20087 a thick supercritical airfoil with strong shock-induced Air Force bases. Model application and background STRESSMEASUREMENT separation [ AD-A1997941 p 499 N89-20557 A critical review of the state of the art for measurement [AD-A20333t I p 459 N89-20971 SURVEYS of Stress in parachute fabrics SUPERSONIC AIRCRAFT Position error calibration of a pressure survey aircraft [AIM PAPER 89.09251 p 489 A89-35235 Twin-jet screech suppression using a trailing cone STRESS RATIO [AIAA PAPER 89-11401 p 504 A89-33768 [ PB88-2507331 p 450 N89-20092 The efleCt of stress ratio on the near-threshold fatigue SUPERSONIC AIRFOILS Views on the impact of HOST p 480 N89-20144 crack growth behavior of Ti-8AI-1Mo-1V at elevated Asymptoticlnumerical analysis of supersonic propeller Structural mechanics: Contemporary state and prospects for development (selected portions) temperature p 489 A89-35722 noise STRESSTRAIN RELATIONSHIPS [AIAA PAPER 89-10781 p 501 A89-33722 [AD-A198766] p 497 N89-20498 Macrocrack-rnultipledefect interaction considering SWEPT WINGS SUPERSONIC BOUNDARY LAYERS Development and application of a program to calculate elastic, plastic and viscoplastic effects A comparison of the turbulence structure of subsonic transonic flow around an oscillatingthree-dimensional wing [AD-A203186] p 498 N89-21282 and supersonic boundary layers p 440 A89-33425 STRUCTURAL ANALYSIS using finite difference procedures SUPERSONIC COMBUSTION [NASA-CR-l81744] p 450 N89-20093 Sonic fatigue and nonlinear response of stiffened A simple one-dimensional model for the effect of air panels SWIRLING pollution on supersonic combustion p 488 A89-34121 [AIAA PAPER 89-llOl] p 492 A89-33741 The influence 01 a radial swirl generator on the flow ONERA research on civil aircraft p 438 A89-35376 SUPERSONIC COMBUSTION RAMJET ENGINES field from a fuel nozzle model p 490 A89-33354 Navier-Stokes calculations of scramjet-afterbody Structural analysis methods development for turbine hot SWITCHES flowfields p 443 A89-34732 section components p 479 N89-20140 AH-1S communication switch integration program Structural analysis applications p 480 N89-20141 Laser-induced iodine fluorescence technique for [ NASA-TM-l01053] p 466 N89-20978 Views on the impact of HOST p 480 N89-20144 quantitative measurement in a nonreacting supersonic SYNTHETIC FUELS Structural mechanics: Contemporary state and combustor p 445 A89-34809 Gas turbine alternative fuels combustion prospects for development (selected portions) A first scramjet study characteristics [ ADA1987661 p 497 N89-20498 [ NASA-CR-1849651 p 480 N89-20146 [ NASA-TM-I01470] P 499 N89-21417 A-21 SYSTEM IDENTIFICATION SUBJECT INDEX
SYSTEM IDENTIFICATION Simulation at Dryden Flight Research Facility from 1957 Investigation of flow separation in a three-dimensional Frequency domain techniques applied to the to 1982 diffuser using a coupled Euler and boundary-layer identification of helicopter dynamics p 500 A8945261 [ NASA-TM-1016951 p 474 N89-20983 method p 446 A89-35172 SYSTEMS ANALYSIS A real-time simulator of a turbofan engine A cell-vertex multigrid method for the Navier-Stokes General aviation p 437 A89-34448 [NASA-TM-100869] p 481 N89-20995 equations Power efficient nydraulic systems Volume 1 Study TETHERING [NASA-TM-101557] p 451 N89-20101 phase Canadair SentinellSea Sentinel rotary wing RPV. IV The 3-0 Euler and Navier-Stokescalculations for aircraft [APA2038991 p 472 N89-20127 p 467 A89-33556 components p 498 N89-20950 SYSTEMS ENGINEERING Tethered parafoil test technique Stability of compressible boundary layers The Theta Beta - Design of a system ---remotelypiloted [AIM PAPER 89-09031 p 462 A89-35219 p 456 N89-20953 civil aircraft p 468 A8943561 - _.- THERMAL ANALYSIS THREE DIMENSIONAL MODELS SYSTEMS INTEGRATION Heat transfer in gas turbine combustors Comparison of 3D computation and experiment for Cockpit-crew systems design and integration p 491 A89-33580 non-axisymmetricnozzles p 476 A8944446 Structural analysis methods development for turbine hot [NASA-CR-1822451 p 452 N89-20921 Transonic propulsion system integration analysis at section components p 479 N89-20140 Capabilities of wind tunnels with two-adaptive walls to McDonnell Aircraft Company p 481 N89-20943 THERMAL CONDUCTIVITY minimize boundary interference in 3-D model testing Aeroelastic modeling for the FIT team FIA-18 p 486 N89-20961 simulatm Some aspects of the numerical modeling of the [NASA-TM-1015691 p 475 N89-20991 nonstationary heat conductivity of gas turbine Three-dimensional singular points in aerodynamics [NASA-TM-l000451 p 457 N89-20964 SYSTEMS STABILITY components p 477 A8934139 Stability analysis of the multiple discrete stabilization Experimental investigation of the thermal conductivity THRUST system of an elastic flight vehicle p 500 A8944132 of dispersed ceramic materials p 488 A89-34933 A first Scramjet study THERMAL FATIGUE [ NASA-CR-1849651 p 480 N89-20146 The effect of stress ratio on the near-thresholdfatigue THRUSTVECTORCONTROL T crack growth behavior of Ti-BAI-1Mo-1V at elevated Noise generated by a flight weight, air flow control valve temperature p 489 A89-35722 in a vertical takeoff and landing aircraft thrust vectoring T-39 AIRCRAFT Fatigue life prediction modeling for turbine hot section system Position error calibration of a pressure survey aircraft materials p 480 N89-20142 [NASA-CR-l82232] p 504 N89-20776 using a trailing cone THERMAL INSULATION THUNDERSTORMS [PB88-250733] p 450 N89-20092 Life modeling of thermal barrier coatings for aircraft gas Thunderstorm-generatedsolitary waves - A wind shear TACAN turbine engines p 480 N89-20143 hazard p 499 A89-34888 Aircraft tracking mth dual TACAN THERMAL PROTECTION [ AD-A202647I p 466 N89-20980 TIME Life modeling of thermal barrier coatings for aircraft gas Robust stabilization of linear time-invariant uncertain TAIL ASSEMBLIES turbine engines p 480 N89-20143 systems via Lyapunov theory p 483 N89-20147 Tailless aircraft performance improvementswith relaxed THERMAL STABILITY static stability TIME DEPENDENCE Ceramics in high-temperaturegas turbines (Review) Real-time display of time dependent data using a [ NASAGR-1818061 p 483 N89-20999 p 488 A89-34080 TAIL ROTORS head-mounted display Experimental investigation of :he thermal conductivity [AD-A203051I p 476 N89-20993 Acoustic test of a model rolor and tail rotor: Results of dispersed ceramic materials p 488 A89-34933 TIME DIVISION MULTIPLEXING for the isolated rotors and combined configuration THERMODYNAMIC PROPERTIES Observer design for compensation of network-induced [ NASA-TM-1015501 p 504 N89-20777 A new method for the thermodynamic calculation of delays in integrated communication and control systems TAPES combustion chambers p 478 A8944409 p 500 A89-35044 Development of an alternating flat to tubular Kevlar THIN AIRFOILS parachute tape Analysis of separated flow past a thin profile in the case TIME LAG [AIAA PAPER 89-09101 p 462 A8945223 of translational oscillations p 442 A89-34151 Observer design for compensation of network-induced TECHNOLOGICAL FORECASTING Thin aerofoils with high-incidence flaps or blunt trailing delays in integrated communication and control systems AIAA Aerodynamic Decelerator Systems Technology edges p 445 A89-34749 p 500 A8945044 Conference, 10th. Cocoa Beach, FL. Apr. 18-20. 1989, Numerical instabilities in the calculation of laminar TIME MARCHING Technical Papers p 461 A8945201 separation bubbles and their implications Euler solvers for transonic applications Implementationof a transputer-based flight controller p 445 A89-34819 p 454 N89-20935 p 482 A89-35302 THIN BODIES TITANIUM ALLOYS TECHNOLOGY ASSESSMENT Thin axisymmetric caverns in supersonic flow Titanium PM attributes and potential for aircrall engine Assessment, development. and application of p 449 A8945435 applications p 487 A89-33465 combustor aerothermal models p 479 N89-20138 THIN PLATES The effect of stress ratio on the near-threshold fatigue Review and assessment of the database and numerical Aeroelastic divergence of front-free-aft-fixedelastic strip crack growth behavior of Ti-BAI-1Mo-1V at elevated modeling for turbine heat transfer p 479 N89-20139 parallel to uniform flow p 495 A89-35097 temperature p 489 A89-35722 TECHNOLOGY UTILIZATION THIN WALLED SHELLS Designing with advanced fibrous composites TRACKING (POSITION) Bulging cracks in pressunzed fuselages: A numerical p 470 A8945197 Development of a low cost trackinglrangingsystem study p 465 A89-33572 High altitude parachute and its military applications [ NLR-MP-8705841 p 497 N89-20519 [AIAA PAPER 89-08931 p 461 A89-35211 High-dynamic GPS tracking THREE DIMENSIONAL BODIES [ NASA-CR-I848681 p 465 N89-20113 TEMPERATURE EFFECTS Numerical analysis of three-dimensional non rigid Aircraft tracking with dual TACAN A first scramjet study wings [AD-A202647] p 466 N89-20980 [ NASA-CR-1 84965 I p 480 N89-20146 [AIAA PAPER 89-0907) p 450 A89-36022 TEMPERATURE GRADIENTS THREE DIMENSIONAL BOUNDARY LAYER TRACKING FILTERS Performance and test section flow characteristicsof the Direct numerical simulation of a three-dimensional Continuous-discretefiltering for systems with Markovian National Full-scaleAerodynamics Complex 40- by 80-foot turbulent boundary layer p 493 A89-34909 switching coefficients wind tunnel Three-dimensional boundary-layertransition study [ NLR-MP-87076-UI p 465 N89-20117 [ NASA-TM-1010651 p 438 N89-20086 p 447 A8945195 TRAILING EDGE FLAPS TEMPERATUREMEASUREMENT A calculationmethod for compressiblethree dimensional Transonic buffet of a supercriticalairfoil with trailingedge Advanced high temperature instrument for hot section turbulent boundary layer flows flap p 446 A8934893 research applications p 479 N89-20137 [VKI-TN-167] p 496 N89-20422 An experimental study of transonic buffet of a TENSILE STRENGTH Transonic CFD applications at Boeing supercritical airfoil with trailing edge flap Investigation of the service and age lives of US. Army p 453 N89-20929 [AD-A203189] p 458 N89-20968 personnel parachutes Secondary three-dimensionalinstability in compressible TRAILING EDGES [AIAA PAPER 89-09151 p 462 A89-35227 boundary layers p 456 N89-20954 Thin aerofoils with high-incidence flaps or blunt trailing TENSILE TESTS THREE DIMENSIONAL FLOW edges p 445 A8944749 Investigation of the service and age lives of U.S. Army 3-D LDA-measurements in the jet of a bypass-engine Effect of 90 degree flap on the aerodynamics of a personnel parachutes p 477 A89-33386 two-element airfoil p 446 A8945053 [AIM PAPER 89-09151 p 462 A89-35227 Heat transfer in gas turbine combustors TRAINING DEVICES p 491 A89-33580 Real-time display of time dependent data using a TERRAIN ANALYSIS Numerical simulation of three-dimensional hypersonic Multispectral terrain background simulation techniques head-mounted display viscous flows p 441 A8943644 [AD-A203051] p 476 N89-20993 for use in airborne sensor evaluation Acoustic forcing of three dimensional shear layers p 499 A89-33664 TRAJECTORIES [AIAA PAPER 89-10631 p 501 A8943712 TEST CHAMBERS Navier-Stokessimulation of unsteady three-dimensional Trajectory scoring in rectangular coordinates using transponder-interrogator range and range rate data Perfwmance and test section flow characteristicsof the blade-vortex interactions P 444 A8944745 [DE89-0070051 p 466 N89-20119 National Full-ScaleAerodynamics Complex 40- by 80-loot Heat transfer in gas turbine engines and wind tunnel three-dimensionalflows: Proceedings of the Symposium, TRAJECTORY ANALYSIS [ NASA-TM-101065] p 438 N89-20086 ASME Winter Annual Meeting, Chicago, IL. Nov. 27-Dec. An approximate method for calculating aircraft TEST FACILITIES 2,1988 P 494 A8944926 downwash on parachute trajectories New static engine noise test techniques which reduce Computation of external. hypersonic, three-dimensional [AIAA PAPER 89-08991 p 447 A8945216 test time significantly flowfield and heat transfer p 494 A89-34935 The application of trajectory prediction algorithms for [AIAA PAPER 89-11271 p 485 A89-33760 Calculation of compression shock surfaces in planning purposes in the Netherlands Air Traffic Control Development of experimental techniques for helicopter three-dimensional. steady supersonic flows using a (ATC) system rotor performance studies p 470 A8945198 bicharacteristic method P 446 A89-35168 [NLR-MP-8703I-U] p 465 N89-20115
A-22 SUBJECT INDEX TURBULENT BOUNDARY LAYER
TRAJECTORY CONTROL Aerodynamic analysis of three advanced configurations Prediction of potential noise interactions in axial-flow The application of trajectory prediction algorithms for using the TranAir full-potentialcode p 455 N89-20944 machines - Application to the helicopter fenestron planning purposes in the Netherlands Air Traffic Control Steady and unsteady transonic small disturbance p 504 A8945385 (ATC) system analysis of realistic aircraft configurations TURBOFAN ENGINES [ NLR-MP-87031-U] p 465 N89-20115 p 473 N89-20946 Experimental investigation of rotor wakelstator TRAJECTORY OPTIMIZATION Inverse wing design in transonic flow including viscous interaction noise generation by acoustic mode Abort landing guidance trajectories in the presence of interaction p 473 N89-20947 measurements windshear p 481 A89-32725 EulerlNavier-Stokescalculations of transonic flow past [AIM PAPER 89.11261 p 503 A8933759 TRANSATMOSPHERIC VEHICLES fixed- and rotary-wingaircraft configurations New static engine noise test techniques which reduce Identifyingsonic fatigue prone structureson a hypersonic p 456 N89-20848 test lime significantly The 3-D Euler and Navier-Stokescalculations for aircraft Transatmospheric Vehicle (TAW [AIAA PAPER 89-11271 p 485 A89-33760 components p 498 N89-20950 [AIAA PAPER 89-11031 p 469 A8943743 A real-time simulator of a turbofan engine Turbulence and modeling in transonic flow TRANSITION FLOW [ NASA-TM-l00869] p 481 N89-20995 p 456 N89-20951 Computation of flow fields for hypersonic flight at high TURBOJET ENGINES altitudes p 440 A89-33627 Turbulent eddy viscosity modeling in transonic shock/boundary-layerinteractions p 456 N89-20952 Measurements of mean-flow and turbulence Laminar-turbulent transition problems at high speeds characteristics in a turbojet exhaust using a laser p 441 A89-33645 Wall interference assessment and corrections velocimeter p 439 A89-33410 Transitional flow on axial turbomechine blading p 457 N89-20958 p 445 A89-34811 Two-measured vanable method for wall inter!erence Falconet target RPV operations p 437 A89-33559 Bipolar coordinates for computation of transition duct assessmentlcorrection p 457 N89-20959 TURBOMACHINE BLADES flows p 493 A89-34912 A study of transonic drag reduction of a blunt cylinder Some aspects of the numerical modeling of the Three-dimensional boundary-layer transition study by a cylinder probe nonstationary heat conductivity of gas turbine p 447 A89-35195 [AD-A202557] p 458 N89-20965 components p 477 A8944139 A study 01 transonic drag reduction of a blunt cylinder An experimentai study Of :i~iisoiilc StUe! o! B Effect 9f the design of a two-row nozzle ring on the by a cylinder probe supercritical airfoil with trailing edge flap efficiency of a turbine stage of medium rotor solidity [AD-A202557] p 458 N89-20965 [ ADA2031891 p 458 N89-20968 p 477 A89-34140 TRANSONIC FLOW Two-dimensionalNavier-Stokes solution of the flow over Effect of the blade height at the exit of the shrouded Numerical modeling of transonic flow of a viscous gas a thick supercritical airfoil with strong shock-induced rotor of a radial-flow centripetal microturbineon the turbine in a plane channel with a sudden expansion separation efficiency p 492 A89-34155 p 442 A89-34149 [AD-A203331] p 459 N89-20971 TURBOMACHINERY Advances in the Computation of transonic separated Development of a shock capturing code for use as a Inviscid prediction of transonic flows in turbomachines flows over finite wings p 442 A89-34427 tool in designing high-work low aspect ratio turbines using a Runge-Kuna integration scheme A self-adaptive computational method for transonic [ AD-A202706I p 498 N89-21248 p 444 A89-34736 turbulent flow past a real projectile p 443 A89-34730 TRANSONIC SPEED A numerical investigation of steady transonic cascade Inviscid prediction of transonic llows in turbomachines Transonic/supersonic (720 KEAS 1.2 Mach) ejection flow in turbomachinery p 448 A89-35417 using a Runge-Kuna integration scheme demonstration test of an 545 Biofidelity Manikin (BFM1) A method for calculating potential transonic flows in p 444 A8944736 p 463 A89-35841 turbomachinery cascades p 449 A8945450 Second order accurate finite difference approximations The application of CFD for military aircraft design at TURBOPROP AIRCRAFT for the transonic small disturbance equation and the full transonic speeds p 454 N89-20930 Adaptive active control of enclosed sound fields in elastic potential equation p 444 A89-34740 Method to predict external store carriage loads at cylinders via vibrational inputs --- noise attenuation Navier-Stokescalculations of transonic flows past open transonic speeds p 473 N89-20945 research for advanced turboprop aircrafl and transitional cavities p 444 A8944744 Two-measured variable method for wall interference [AIAA PAPER 89-10751 p 469 A89-33720 Transonic buffet of a supercriticalairfoil withtrailing-edge assessmentlcorrection p 457 N89-20959 Near-fieldnoise of a pusher propeller flap p 446 A89-34893 TRANSONIC WIND TUNNELS [AIAA PAPER 89.10961 p 502 A89-33736 A numerical investigation of steady transonic cascade Investigation of flow separation in a three-dimensional Propeller modelling effects on interior noise in cylindrical flow in turtmrnachinery p 448 A8945417 diffuser using a coupled Euler and boundary-layer cavities with application lo active control A method for calculating potential transonic flows in method p 446 A89-35172 [AIM PAPER 89-11231 p 469 A8943757 turtmmachinery cascades p 449 A89-35450 Instrumentationadvances for transonic testing Advanced turboprop aircraft flyover noise annoyance - Potential models of transonic flows p 486 N89-20957 Comparison of different propeller configurations p 449 A89-35495 Performance of the active sidewall boundary-layer [AIM PAPER 89-11281 p 503 A89-33761 Sound generation and flow interaction of vortices with removal system lor the Langley 0.3-meter Transonic TURBOPROP ENGINES an airfoil and a flat plate in transonic llow Cryogenic Tunnel Near wakes of advanced turbopropellers 449 A89-36006 [NASA-CR-I81 7931 p 486 N89-21004 [AIAA PAPER 89-10951 p 441 A8943735 Detailed measurements in the transonic vortical flow TRANSPORT AIRCRAFT Catin n~iseco~::o! oroexj !es!r !or IJHU eircrati over a delta wng p 449 A69-36012 Load alleviation on transoort aircraft using acceleration [AIAA PAPER 89-11211 p 469 A8943755 Development and application of a program to calculate feedback p 471 A89-35299 Structural Tailoring 01 Advanced Turboprops (STAT) transonic llow around an oscillating three-dimensional wing The future of the civil aviation industry programmer's manual using finite difference procedures p 438 A89-35377 [ NASA-CR-1821641 p 478 N89-20132 [NASA-CR-181744] p 450 N89-20093 Civil-transport aircraft at Aerospatiale TURBULENCE Geometrical and structural properties 01 an Aeroelastic p 438 A89-35378 Symposium on Turbulence, 1lth. University of Research Wing (ARW-2) New wings, new ways p 471 A89-35825 Missoury-Rolla. Rolla. Oct. 17-19. 1988, Preprints [NASA-TM-41lo] p 451 N89-20099 TRAVELING WAVES p 491 A89-33402 Observed Reynolds number effects on airfoils and high Nonlinear kink desfor supersonic vortex sheets TURBULENCE EFFECTS aspect ratio wings at transonic flow conditions p 442 A89-33783 Single and multi-elementairfoils in an isotropic turbulent [NLR-MP-88006-U] p 451 N89-20102 TRIBOLOGY outer flow p 439 A89-33383 Experimental investigation of transonic oscillating Air Force tribology programs p 491 A89-33448 Measurements 01 mean-flow and turbulence cascade aerodynamics TURBINE BLADES characteristics in a turbojet exhaust using a laser [NASA-TM-101 9931 p 478 N89-20133 PM superalloy turbine blades p 487 A8943454 velocimeter p 439 A89-33410 Updated users' guide for TAWFIVE with multigrid Adaptive control of the grinding of large gas turbine Instantaneous profiles and turbulence statistics of [ NASA-TM-41091 p 496 N89-20409 blades p 492 A89-34144 supersonic free shear layers by Raman excitation + Additional development of the XTRANBS computer Optimal profile selection in the design 01 a subsonic laser-induced electronic fluorescence (relief) velocity program turbine cascade p 442 A89-34152 tagging of oxygen p 440 A89-33424 [NASA-CR-181 7431 p 452 N89-20922 Transitional flow on axial turbomachine blading NASA lidar velocimetry measurements Airframelpropulsion integration characteristics at p 445 A89-34811 p 491 A89-33435 transonic speeds p 453 N89-20926 Life modeling of thermal barrier coatings for aircraft gas Effect of turbulence on the combustion of an atomized Shock-boundary-layerinteraction in flight turbine engines p 480 N89-20143 liquid fuel p 488 A89-34122 p 453 N89-20928 A compendium 01 controlled diffusionblades generated Effect of jet grid turbulence on turbulent boundary layer Transonic CFD applications at Boeing by an automated inverse design procedure heat transler p 494 A89-34930 p 453 N89-20929 [ NASA-TM-101968l p 481 N89-20996 TURBULENCE MODELS Transonics and fighter aircrafl Challenges and A digital simulation technique for Dryden atmospheric TURBINE ENGINES Opportunities for CFD p 454 N89-20932 turbulence model p 439 A89-33142 Advanced high temperature instrument for hot section Transonic aerodynamic design experience Turbulence modeling for hypersonic flows research applications p 479 N89-20137 p454 N89-20934 p 441 A89-33641 Euler solvers for transonic applications TURBINE WHEELS Evaluation of algebraic turbulence models for PNS p 454 N89-20935 Effect of the blade height at the exit of the shrouded predictions of supersonic flow past a sphere-cone Asymptotic methods for internal transonic flows rotor of a radial-flowcentripetal microturbineon the turbine p 445 A8944807 p 455 N89-20937 efficiency p 492 A89-34155 The correlation between Reynolds stress and turbulent Wave drag due to lift for transonic airplanes TURBINES kinetic energy in the near wake of a symmetric airtoil p 455 N89-20938 Transmission and reflection on pressure waves by p 448 A89-35393 Developments and trends in three-dimensional mesh compressor and turbine stages, based on an actuator-disk Turbulence and modeling in transonic flow generation p 455 N89-20940 model p 456 N89-20951 Transonic Symposium: Theory. Application, and [ AD-A2035131 p 496 N89-20426 TURBULENTBOUNDARYLAYER Experiment, volume 1, part 2 TURBOCOMPRESSORS A comparison of the turbulence structure of subsonic [NASA-CP-3020-VOL-l-PT-2] p 455 N89-20942 Computational study of the effect of cascade parameters and supersonic boundary layers p 440 A89-33425 Transonic propulsion system integration analysis at on stall propagation in axial compressors Direct numerical simulation of a three-dimensional McDonnell Aircraft Company p 481 N89-20943 p 444 A8944737 turbulent boundary layer p 493 A89-34909
A-23 TURBULENT FLOW SUBJECT INDEX
Effect 01 jet grid turbulence on turbulent boundary layer Unsteady force Calculations on circular cylinders and VIBRATION MODE heat transfer p 494 A89-34930 elliptical airfoils with circulation control Structural optimization for aerwlastic control Prediction 01 heat transfer characteristics of discrete [ UMAERO-87-37] p 457 N89-20962 effectiveness p 470 A89-34899 hole film cooling . One row of injection into a turbulent Methodologyfor using steady experimentalaerodynamic VIBRATION TESTS boundary layer p 494 A89-34931 data to improve steady and unsteady aerodynamic Structural Tailoring of Advanced Turboprops (STAT) Turbuliation of a high-velocity boundary layer by a analysis p 459 N89-20972 programmer’s manual projection p 448 A89-35434 Aeroelastic modeling lor the FIT team FIA-18 LNASA-CR-1821641 p 478 N89-20132 Documentation 01 two- and three-dimensional simulation Coupled rotor/fuselage dynamic analysis of the AH-1G hyp”9nic shock wave/turbulent boundary layer [NASA-TM-1015691 p 475 N89-20991 helicopter and correlation with lliht vibrations data interachon flows UNSTEADY FLOW [NASA-CR-l81723] p 497 N89-20512 VIDEO EQUIPMENT [ NASA-TM-1010751 p451 N89-20100 Navier-Stokessimulation of unsteady three-dimensional Civilian RPVs Eye in the sky pie in the sky? I A calculationmethod for compressiblethree dimensional blade-vortex interactions p 444 A89-34745 - or turbulent boundary layer flows p 437 A89-33560 I [VKI-TN-167] p496 N89-20422 Development and application of a program to calculate VIRTUAL MEMORY SYSTEMS transonic flow around an oscillating three-dimensionalwing A helmet-mounted virtual environment display syslem TURBULENT FLOW using finite difference procedures [ADA2030551 p 476 N89-20994 Measwements of a supersonic turbulent vortex [NASA-CR-181744] p 450 N89-20093 D 440 A89-33423 VIRTUAL PROPERTIES Steady and unsteady transonic small disturbance Mean and turbulent velocity measurements of Determining and accounting for a parachute virtual supersonic mixing layers p 440 A89-33426 analysis of realistic aircraft configurations mass p 460 A89-34889 p 473 N89-20946 Heat transfer in gas turbine combustors VISCOPLASTICITY p491 A89-33580 UPSTREAM Macrocrack-multipledefect interaction considering Simultaneous computation of jet turbulence and noise Incompressible cascade calculation using an upwind elastic, plastic and viscoplastic effects [AIM PAPER 89-10911 p 491 A89-33731 differenced TVD scheme p 444 A89-34733 [AD-A203186] p 498 N89-21282 A self-adaptive computational method lor transonic UPWASH VISCOSITY turbulent flow past a real projectile p 443 A89-34730 Large-eddy simulations of excitation effects on a VTOL Viscosity effects in the generation of the lifting force Direct numerical simulation of a three-dimensional upwash fountain p442 A89-34461 01 aerodynamic wing profiles p 442 A89-34114 turbulent boundary layer p 493 A89-34909 USER MANUALS (COMPUTER PROGRAMS) VISCOUS DRAG Perfumanceand test section flow Characteristicsof the Updated users’ guide for TAWFIVE with multigrid Viscous shock layer analysis of hypersonic flows over I National Full-ScaleAerodynamics Complex 40- by 80-foot [ NASA-TM-41091 p496 N89-20409 long slender vehicles p 451 N89-20097 wind tunnel USER REQUIREMENTS VISCOUS FLOW [NASA-TM-101065] p 438 N89-20086 The future of the civil aviation industry Numerical simulation of three-dimensional hypersonic Tuhlent eddy viscosity modeling in transonic p 438 A89-35377 viscous flows p 441 A89-33644 shocklboundary-layer interactions p 456 N89-20952 Microwave landing systems: Additional systems should Numerical modeling of transonic flow of a viscous gas i Effect of riblets upon flow separation in a subsonic rot be procured unless benefits proven in a plane channel with a sudden expansion diftuser [GAO/RCED-88-118] p 466 N89-20977 p 442 A89-34149 [ADA2031781 p458 N89-20967 Visuws-inviscid interaction and computation in TURBULENT HEAT TRANSFER aerodynamics Effect of jet grid turbulence on turbulent boundary layer [ONERA. TP NO. 1988-1161 p 443 A89-34627 heat transfer p 494 A89-34930 v High-resolution shockcapturing schemes for inviscid Prediin heat transfer characteristics of discrete and viscous hypersonic flows p 443 A89-34646 ot V/STOL AIRCRAFT hole film cooling - One row of injection into a turbulent Transitional flow on axial turbomachine blading boundary layer p 494 A89-34931 Hot gas ingestion testing of an advanced STOVL p 445 A89-34811 concept in the NASA Lewis 9- by 15-foot Low Speed Wind A comparison of secondary flow in a vane cascade and TURBULENT JETS Tunnel with flow visualization , Experimental examination of the aerothermal a curved duct p 446 A89-34934 [AIM PAPER 88-30251 p 439 A89-33249 pertofmanceol theT-1Otestcell at NAS (Naval Air Station). Updated users’ guide for TAWFIVE with multigrid Bound vortex boundary layer control with application Cubi Point [NASA-TM-4109] p496 N89-20409 V/STOL airplanes p 449 A89-35994 [AD-A2038871 p 487 N89-21005 to Vector potential methods p 455 N89-20939 VALVES TURBULENT WAKES Inverse wing design in transonic flow including viscous Acoustic test of a model rotor and tail rotor: Results Development of a rotary value lor pulse combustion interaction p 473 N89-20947 applications lor the isolated rotors and combined configuration VORTEX ALLEVIATION 1NASA-TM-1015501 p 504 N89-20777 [PB89-131114] p496 N89-20468 Effect of wing tip strakes on wing lft-drag ratio TWO DIMENSIONAL BODIES VARIABLE GEOMETRY STRUCTURES p445 A89-34886 Aerodynamics of two-dimensional slotted blutf bodii Variable structure model-following control of flight Vortex breakdown and its control on delta wings IDE894072881 p452 N89-20105 dynamics p482 A8835300 p 449 A89-35999 TWO DIMENSIONAL FLOW VECTORS (MATHEMATICS) VORTEX BREAKDOWN Laminar-turbulent transition problems at high speeds Vector potential methods p 455 N89-20939 Vortex breakdown and its control on delta wings p441 A8833645 Three-dimensional singular points in aercdynamics p 449 A89-35999 [ NASA-TM-1oOO451 p457 N89-20964 Numerical simulation of the flow field over delta wings Asymptotic memods for internal transonic Rows VELOCITY MEASUREMENT p 455 N89-20937 with leading edge blowing p 453 N89-20924 Particle image displacementvelocimetry applied in hgh Stability of compressible boundary layers VORTEX SHEDDING speed flows p 490 A89-33388 Aerodynamics of two-dimensional slotted bluff bodies p456 N89-20953 Mean and turbulent velocity measurements of [ DE89407288] p 452 N89-20105 TwodimensionalNavier-Stokes solution of the flow over supersonic mixing layers p440 A89-33426 a thick supercritical airfoil with strong shock-induced NASA lidar velocimetry measurements VORTEX SHEETS separation p 491 A89-33435 Nonlinear kink modes for supersonic vortex sheets [AD-A203331I p 459 N89-20971 VERTICAL LANDING p 442 A89-33783 TWO DIMENSIONALMODELS Launch, recovery and handling systems for vertical VORTICES Prediction of heat transfer characteristics of discrete takeoff and landing UAVs operating from small ships Measurements 01 a supersonic turbulent vortex hole film cding - One row of injection into a turbulent 13484 A89-33569 p 440 A89-33423 boundary layer p494 A8934931 Noise generated by a flight weight. air flow control valve Induced drag and the ideal wake of a lilting wing in a vertical takeoff and landing aircraft thrust vectoring p 446 A89-34898 system Bound vortex boundary layer control with application U [NASA-CR-182232] p504 N89-20776 lo V/STOL airplanes p 449 A89-35994 VERTICAL MOTION Sound generation and flow interaction of vortices with UNIFORM FLOW A physical-statisticalmethod for the prediinof vertical an airfoil and a flat plate in transonic flow Aeroelasti divergenceof lront-free-aft-fixedelastic strip wind shear in the lower part 01 the atmospheric boundary p449 A89-36006 parallel to uniform flow p495 A89-35097 layer p 499 A89-34028 Detailed measurements in the transonic vortical flow UNSTEADY AERODYNAMICS VERTICAL TAKEOFF over a delta wing p 449 A89-36012 Launch, recovery and handling systems lor vertical A linear computer code to determineaeroelastic stability Some considerationson leading dge voltices wings takeoff and landing UAVs operating from small ships on in airfoil cascades at unsteady flow conditions in supersonic flow p 450 A89-36013 p 484 A89-33569 p 444 A89-34746 Numerical simulation of the flow fmld over delta wings A revision of the added mass concept as applied to Noise generated by a flight weight, air flow control valve in a vertical takeoff and landing aircraft thrust vectoring with leading edge blowing p 453 N89-20924 parachute motion An embedded mesh procedure for leadingedge vortex [AIAA PAPER 89-08951 p 461 A89-35213 system [NASA-CR-l82232] p504 N89-20776 flows p455 N89-20936 The effects of unsteady aerodynamics on single and VERTICAL TAKEOFF AIRCRAFT Thin-layer Navier-Stokes solutions lor a cranked delta clustered parachute system Large-eddy simulationsof excitation effects on a VTOL wing [AIM PAPER 89.09341 p 448 A89-35250 upwash fountain p 442 A89-34461 [ AD-AZ032921 p 459 N89-20970 Expenmental wind tunnel study of a military-aircraftair VERY LONG BASE INTERFEROMETRY intake - Comparison with flight p 448 A89-35381 Deriving a geocentric reference frame lor satellite Experimental investigation of transonic oscillating positioning and navigation p 466 N89-20330 W cascade aerodynamics Determination 01 GPS orbits to subrneter accuracy [NASA-TM-101993] p 478 N89-20133 p466 N89-20331 WAKES Addiinal development of the XTRAN3S computer VIBRATION DAMPING Experimentalvalidation of a lfting surface model for rotor program Sonic fat!gue-resistant damped laminated structures wake-stator interaction [ NASA-CR-1817431 p452 N89-20922 [AIAA PAPER 89-1 1021 p 469 A89-33742 [AIM PAPER 89-11251 p 441 A8833758
A-24 SUBJECT INDEX X WING ROTORS
Experimental investigation of rotor wakelstator Comparison Of LDA and LTA application for propeller Performance of the active sidewall boundary-layer interaction noise generation by acoustic mode tests in wind tunnels p 490 A89-33381 removal system for the Langley 0.3-meter Transonic measurements Single and multislement airfoils in an isotropic turbulent Cryogenic Tunnel [AIAA PAPER 89-11261 p 503 A89-33759 outer flow p 439 A89-33383 [ NASA-CR-1817931 p 486 N89-21004 Results from laser sheet visualiti of a periodic rotor Particle image displacement velocimetty applied in high WING CAMBER wake p485 A89-34890 speed flows p490 A89-33388 A new look at Theodorsen's method in aerofoil theory Induced drag and the ideal wake of a lingwing Flght test of XRAE-1 to establish aerodynamic data p 443 A89-34621 p446 A89-34898 p 468 A89-33562 WING FLOW METHOD TESTS Effects of wake passing on stagnation region heat Development and implementation of flight control Advances in the computation of transonic separated transfer p 494 A89-34928 system for a research drop model p 481 A89-33563 flows over finite wings p 442 A89-34427 A preliminary characterization of parachute wake Hgh enthalpy testing in hypersonic shock tunnels WING LOADING recontact p 485 A89-33630 Numerical analysis of three-dimensional non rigid [AIM PAPER 8948971 p 447 A8935214 The flow on the lee-side of a deita wing at Mach 7 wings Flow visualization studies of wake behind adsymmebic p440 A89-33637 [AIAA PAPER 8949071 p 450 A89-36022 Muff bodies including parachute campy models~ Near wakes of advanced turbopropellers WING NACELLE CONFIGURATIONS [AIAA PAPER 8W983 p 447 A89-35215 [AIAA PAPER 89-10951 p 441 A89-33735 The 3-D Euler and Navier-Stokescalculations for aircraft WALL FLOW The effect of the wind tunnel wall boundary layer on components p 498 N89-20950 The effect of the wind tunnel wall boundary layer on the acwstic testing of propellers WING PANELS the acwstic testing of propellers [AIAA PAPER 89-10971 p 503 A89-33737 Geometrical and structural properties of an Aeroelastic [AIAA PAPER 89-10971 p 503 A89-33737 Surface pressure measurements on a body subject to Research Wing (ARW-2) Noise and instability waves in supersonic jets in the vortex wake interaction p 470 A89-34808 [NASA-TM-41lo] p 451 N89-20099 proximity of flat and cylindrical walls Results from laser sheet visualization of a periodic rotor WING PLANFORMS [AIM PAPER 89-11361 p503 A89-33766 wake p 485 A89-34890 Development and application of a program to calculate Wind-tunnel wall effects on delta wings Tethered parafoil test technique transonic flow around an oscillating three-dimensionalwing p445 A89-34884 [AIAA PAPER 8909031 p 462 A8835219 using finite difference procedures Wall-interferenceconections for Darachutes in a closed Experimentalwind tunnel study of a military-aircraft air [NASA-CR-l81744] p 450 N89-20093 wind tunnel intake - Comparison with flight p 448 A89-35381 WING PROFILES [AIM PAPER 8809001 p 485 A89-35217 An airfoil pitch apparatus-modeling and control design Viscosity effects in the generation of the lining force WALL JETS [ NASA-TM-1010761 p496 N89-20386 of aerodynamic wing profiles p 442 A89-34114 Large- simulations of excitation effects on a VTOL Acoustic test of a model rotor and tail rotor: Results A combined method for calculating supersonic flow of upwash fountain p442 A89-34461 for the isolated rotors and combined confguration an ideal gas past a wing with a supersonic blunt leading WALL PRESSURE [NASA-TM-t01550] p 504 N89-20777 edse p 448 A89-35430 Wall interference assessment and wrrections Unsteady blade pressure measurements on a model Some low-speed flutter characteristics of simple p457 N89-20958 counterrotation propeller low-aspect-ratio delta wing models WAVE DRAG [ NASA-TM-lOXX)P] p 504 N89-20779 [NASA-TM-101547] p 450 N89-20094 Sound pawer spectrum and wave drag of a propeller Transonic Symposium: Theciy, Application. and Additional development of the XTRAN3S computer in Rght Experiment Volume 1, Part 1 program [AIM PAPER 89-1081] p502 A8933724 [NASACP-3020-VOL-1-P-l] p 453 N89-20925 [NASA-CR-161743] p 452 N89-20922 WAVE INTERACTION Inverse wing design in transonic flow including viscous Airframelpropulsion integration characteristics at Documentation of two- and three-dimensional interaction p 473 N89-20947 transonic p 453 N89-20926 hypersonic shock wave/turbulent boundary layer speeds Turbulence and modeling in transonic flow Transonic Symposium: Theory. Application. and interactioo Rows p 456 N89-20951 1NASA-TM-1010751 p451 N89-20100 Ex**men!, Volume 1, pa!! 2 'wiNG TIP VORTiCES WAVEFORYS [NASA-CP302@VOL-l-PT-2] p 455 N89-20942 The prediction of blade wake interaction mise based Integrating the acoustic anakgy for supersonic rotating Test tebmiques: A survey paper on cryogenic tunnels. on a turbulent vortex model surfaces adaptive wall teet sectiomr,ard magnetic suspension and [AIAA PAPER 89-11341 p 503 A89-33764 [AIAA PAPER 89-11331 p503 A89-33783 balance systems p486 N89-2Q955 WING TIPS WAXES An LDA (Laser-Doppler Anemometry) investigation of Effect of wing tip strakes on wing lift-drag ratio Fuel holdup and component diffusivity in a cooled three-dimemrional normal shock wave boundary-layer p 445 A89-34886 cylindrical tank p4BB A89-34894 interactions p456 N89-20956 WINGS WEIGHT REDUCTION Instrumentationadvances for transonic testing Induced drag and the ideal wake of a lifting wing Integrated aerodynamicldynamic optimizatiw, of p 486 N89-20957 p 446 A89-34898 heliter rotor blades Wall interference assessment and corrections Investigationof a free-tip rotor configurationfor research [ NASA-TM-1015531 p473 N89-20982 p457 N89-20958 on spanwise life distributions and wake velocity SUN~~S WEIGHTING N"S mmoa-n nl akfnil rasliltr, frnm an adaotii~wall test of a semi-span wing with a discontinuous twist aeiecwn of a nequency sensmve WI (ouanmatnre section and a porous wall test section i~nan-bn-IWJWJ P 451 NOY-LULIOJ Feedbeck Theay) weighting mabix using the method of p 457 N89-20960 WROUGHT ALLOYS specified outputs Structure and propertiis of forged ODS nickel-base Capabilities of wind tunnels with two-adaptive walls to [ADA2026921 p 501 N89-21592 superalloys p 491 A89-33461 WEST GERMANY minimize boundary interference in 3-D m&l testing DFVLR. Annual Report 1987 p 437 A89-32775 p 486 N89-20961 WIND EFFECTS InvestiMnof a free-tip rotor configurationfor research X Wind damage to airpwts - Lessons learned on spanwise life distributions and wake velocity surveys p 499 A89-34359 of a semi-span wing with a discontinuous twist X RAY INSPECTION WIND SHEAR [NASACR-t84948] p457 N89-20963 Micro radiography and tomography for high resolution Abort landing guidance trajectories in the presence of A wind tunnel and complter investigation of the low NDT of advanced matenals and microstructural windshear p 481 A8932725 speed aerodynamic characteristics of the prone escape components p495 A89-35081 A physccal-statisticalmethod for the predictiof vertical system (PRESS) X WING ROTORS wind shear in the lower part of the atmospheric boundary [AD-A202768] p 475 N89-20988 Aeroelastic deformation effects on the stopped-rotor layer p499 A89-34028 Flowfield measurements in the NASA Lewis Research dynamics of an X-wing aucraft p 482 A89-34897 Thurderstorm-generated solitary waves - A wind shear Center 9- by 15-foot low-speed wind tunnel hazard p499 A89-34888 [ NASA-TM-1008831 p 486 N89-21002 Analysis of Doppler radar windshear data Comparison of propeller mise noise data taken in the [NASACR-181762] p464 N89-20111 NASA Lewis 8- by &foot wind tunnel with other tunnel WINDTUNNELAPPARATUS and flight data Instrumentation advances for transonic testing [ NASA-TM-1019761 p 505 N89-21628 p486 N89-20957 WIND TUNNEL WALLS WIND TUNNEL CALIBRATIOW Wind-tunnel wall effects on delta wings Performance and test section flow characteristicsof the p445 A89-34884 National Full-Scale Aerodynamics Complex 40- by 80-foot Wall-interferencecorrecfions for parachutes in a closed wind tunnel wind tunnel [NASA-TM-101065] p438 N89-20086 [AIM PAPER 89-09001 p 485 A89-35217 Flowfield measurements in the NASA Lewis Research Test techniques: A swvey paper on cryogenic tunnels. Center 9- by 15-foot low-speed wind tunnel adaptive wall test sections. and magnetic suspensionand [NASA-TM-100883] p486 N89-21002 WIND TUNNEL MODELS balance systems p486 N89-20955 Active control law synthesis for flexible aircraft Wall interference assessment and corrections p457 N89-20958 p482 A89-35045 Capabilies of wind tunnels with twc-adaptive walls to Two-measured variable method for wall interference minimize boundary interference in 3-D model testing assessmentlconection p 457 N89-20959 p486 N89-20961 Comparison of airfoil results from an adaptive wall test WIND TUNNEL TESTS section and a porous wall test section Hot gas ingestion testing of an advanced STOVL D457 N89-20960 concept in the NASA Lewis 9- by 15-1001 Low Speed Wind Capabilities of wind tunnels with two-adaptive walls to Tunnel with Row visualition minimize bourn interference in 3-D model testing [AIAA PAPER 8830251 p 439 A89-33249 11486 N89-20961
A-25 PERSONAL AUTHOR INDEX
AERONAUTICAL ENGINEER1NG /A Continuing Bibliography (Supplement 242) August 1989
vpical Personal Author Index Listing
ANDERSON, RICHARD BAYSAl, OKTAY NASA lidar velocimetly measurements Advances and applications in computational fluid p 491 A89-33435 dynamics, Proceedings of the Symposium. ASME Winter ANDREWS, DANIEL R. Annual Meeting, Chicago. IL, Nov 27-Dec 2, 1988 An airfoil pitch apparatus-modeting and control design p 443 A89-34726 [NASA-TM-1010761 p 496 N89-20386 BEARD. L. BOURNE, SIMON M. APPA. KARl Electromagneticproperties of ice coated surfaces 7Helicopter roli control effectiveness criteria program Finite-surfacespline p 500 A89-34900 [ NASA-CR-1847801 p 495 N89-20355 summary ARNAL, DANIEL BEARE, STEVEN D. I INASA-CR-1774771I o 39 N89-10046 Laminar-turbulenttransition problems at high speeds New lightweight paracnute fabrics oi neviar drarnnd p 441 A89-33645 fiber ARNONE, A. [AIM PAPER 89-091 11 p 489 A89-35224 Inviscid prediction of transonic flows in turbomachines BEATON, ROBERT M. using a Runge-Kuna integration scheme Reliability and performance evaluation of systems p 444 A89-34736 containing embedded rule-based expert systems ARTOLA, MIGUEL [ NASA-CR-1817691 p 500 N89-20683 Nonlinear kink modes for supersonic vortex sheets BECKER, L. E. p 442 A89-33783 Prediction of full system helicopter noise for a MDHC ASHKENAS, IRVING L. 500E helicopter using the Rotonet program Tailless aircraft performanceimprovements with relaxed [AIAA PAPER 89.11351 p 500 A89-33765 Listings in this index are arranged alphabetically static stability BEERS, J. N. P. by personal author The title of the document pro- [NASA-CR-181 8061 p 483 N89-20999 The application of trajectory prediction algorithms for vides the user with a brief description of the sub- ASQUITH, G. planning purposes in the Netherlands Air Traffic Control Fatigue testing of gas turbine components (ATC) system ject matter The report number helps to indicate p 485 A89-33804 INLR-MP-87031-Ul p 465 N89-20115 the type of document listed (e g , NASA report. ATKINS, R. J. BEHR, VANCE L. translation. NASA contractor report) The page Canadair SentinellSea Sentinel rotary wing RPV. IV The develoDment and testino of the HISAC DaraChUte p 467 A89-33556 recovery system and accession numbers are located beneath and ANARS, Y. [ AlAA PAPER 89-0921 ] p 462 A89-35231 to the right of the title Under any one author's New static engine noise test techniques which reduce Measurements of individual parachute loads in a name the accession numbers are arranged in se- test time significantly clustered parachute system quence with the AlAA accession numbers appear- [AIAA PAPER 89-1 1271 p 485 A89-33760 [AlAA PAPER 89-09231 p 463 A8945233 AUSTIN, R. 0. BENNETT, ROBERT M. ing first Some aspects of the development and operational Steady and unsteady transonic small disturbance testing of the Sprite system p 467 A8943557 analysis of realistic aircraft configurations A AYERS, THEODORE G. p 473 N89-20946 Flight research and testing p 453 N89-20927 BERA, RAJENDRA K. ABBINY, F. A new look at Theodorsen's method in aerofoil theory .!. p 443 A89-34621 Electronics in civil aviation BERMAN, C. H. [NLR-MP-87009-U] p 476 N89-20129 a e:mu!!aneous computation of jet turbulence and noise ABOU-HAIDAR, N. 1. BAKER, TIMOTHY J. [AIAA PAPER 89-1091] p 491 A89-33731 Compressible flow losses in branched ducts Developments and trends in three-dimensional mesh BERNER, C. p 494 A89-35004 generation p 455 N89-20940 Base flow investigationbehind axi-and non-axisymmetric ADAMS, MILTON 8. BAKULIN, V. N. blunt bodies Reliability and performance evaluation of systems Natural vibrations of cylindrical shells with a rectangular [ ISL-C0-246/871 p 452 N89-20103 containing embedded rule-based expert systems cutout p 492 A89-34126 BERRIER, BOBBY L. [ NASA-CR-1817691 p 500 N89-20683 BALAKRISHNA, S. Airframe/propulsion integration characteristics at Performance of the active sidewall boundary-layer ADAMSON, D. T. transonic speeds p 453 N89-20926 removal system lor the Langley 0.3-meter Transonic An experimental investigation the aerodynamic loads BERTELRUD, ARlLD of Cryogenic Tunnel on cambered plates Shock-boundary-layerinteraction in flight [NASA-CR-1817931 p 486 N89-21004 [AIAA PAPER 89-09351 p 447 A89-35244 p 453 N89-20928 BALAKRISHNAN, A. BERTIGER, W. 1. ADAMSON, T. C., JR. Computation of external, hypersonic, three-dimensional Determinationof GPS orbits to submeter accuracy Asymptotic methods for internal transonic flows flowfield and heat transfer p 494 A89-34935 p 466 N89-20331 p 455 N89-20937 BALLMMANN, J. BEYER, T. AGARWAL, R. K. Calculation of compression shock surfaces in Noise reduction of a composite cylinder subjected to EulerlNavier-Stokes calculations of transonic flow past three-dimensional, steady supersonic flows using a random acoustic excitation fixed- and rotary-wing aircraft configurations bicharacteristic method p 446 A89-35168 [AIAA PAPER 89-10491 p 501 A89-33708 p 456 N89-20948 BARANOVSKII. S. 1. BHATELEY. I. C. AHUJA, K. K. A simple one-dimensional model for the effect of air The application of CFD for military aircraft design at pollution on supersonic combustion p 488 A89-34121 Noise and instability waves in supersonic jets in the transonic speeds p 454 N89-20930 proximity of flat and cylindrical walls BARNARD, GEORGE A. BICK, FRANK J. An expression for dynamic strain in a 'weak link [AIAA PAPER 89-11361 p 503 A89-33766 AH-I S communicationswitch integration program [AIAA PAPER 89-09421 p 495 A89-35247 [ NASA-TM-101053] p 466 N89-20978 ALDERMAN, DONALD W. BARTOUT. J. D. BIDDULPH. C. J. Modern multiple-pulse, high field NMR studies of high Advanced microstructural observations of gas turbine The Norton P73 rotary RPV engine density jet fuels PIM materials p 487 A89-33456 p 477 A89-33565 [AD-A203320] p 490 N89-21130 BATCHO, P. F. BILBRO, JAMES ALLEN, D. W. Transmission and reflection on pressure waves by NASA lidar velocimetry measurements Low cost avionic system for UMA p 475 A89-33571 compressor and turbine stages. based on an actuator-disk p 491 A89-33435 ALVING, A. E. model BIRMAN, V. A comparison of the turbulence structure of subsonic [ADA2035131 p 496 N89-20426 Divergence instabilityof reinforced composite cylindrical and supersonic boundary layers p 440 A8933425 BATINA, JOHN T. shells p 495 A8945146 AMUEDO, KURT C. Steady and unsteady transonic small disturbance BLAND, SAMUEL R. Hot gas ingestion testing of an advanced STOVL analysis of realistic aircraft configurations Steady and unsteady transonic small disturbance concept in the NASA Lewis 9- by 15-1001 Low Speed Wind p 473 N89-20946 analysis of realistic aircraft configurations Tunnel with flow visualization BAYSAL, 0. p 473 N89-20946 [AIAA PAPER 88.30251 p 439 A89-33249 Navier-Stokes calculations of scramjet-afterbody BLISS, D. B. ANDERSON, MARK RONALD flowfields p 443 A89-34732 Performance optimization for rotors in hover and axial Actuation constraints in multivariable flight control Navier-Stokes calculations of transonic flows past open flight systems p 483 N89-20998 and transitional cavities p 444 A89-34744 [ NASA-CR-1775241 P 459 N89-20973
B- 1 BLOM, H. A. P. PERSONAL AUTHOR INDEX
BLOY, H. A. P. BUFFINGTON. ROBERT J. CHEN. Y. C. Continuous-discretefiltering for systems with Markovian Wall-interferencecweclions for parachutesin a closed Improved computer simulation of the TCAS 3 circular switching coefficients wind tunnel array mounted on an aircraft [ NLR-MP-87076-Ul p 465 N89-20117 [AIAA PAPER 89-09001 p 485 A89-35217 [NASA-CR-184907] p496 N89-20363 BLUEYCKE, E. BUFFUY, DANIEL H. CHERNYSH. V. Y. The influence of a radial swirl generator on the flow Experimental investigation of transonic oscillating Eflwt of the design of a two-row male ring on the field from a fuel nozzle model p 490 A89-33354 cascade aerodynamics efflclency of a turbine stage of medium rotor sdiity BOBBITI, PERCY J. [NASA-TM-101993] p 478 N89-20133 p 477 A89-34140 Instrumentationadvances for transonic testing BULGAKOV, V. K. CHI- D. p 486 N89-20957 Numerical modeling of transonic flow of a viscous gas Annular honeycomb seals: Test results for leakage and
BOLOTIN, V. V. in a plane channel with a sudden expansion rOtMdynamk coefficients ~ Comparisons to labyrinth and Structural mechanics: Contempotary State and p 442 A8934149 smooth configurations prospects for development (selected portions) BUNKER, R. S. [ASME PAPER 88-TRIB-351 p 493 A89-34794 [ADA1987661 p 497 N89-20498 Local heat transfer in internally cooled twbine airfoil An entrance region friction factor model applied to BONDARENKO, E. A. leading edge regions. I - Impingement mlingwithout film annular seal analysis . Theory versus experiment for Stability analysis of the multiple discrete stabilization smooth and honeycomb seals coolant extraction. II ~ Impingement cooling with film system of an elastic flight vehicle p 500 A89-34132 coolant extraction p 494 A8944932 [ASME PAPER 88-TRIB-411 p 493 A89-34798 CHIU, H. T. BONNER, E. BURKET, HAROLD D. Transient dynamics of aircraft propellers during Transonic aerodynamic design experience In-flightlightning characterization program on a CV-580 p454 N89-20934 aircraft touch-dorm impact p470 A89-34509 CHOI, SIU-TONG BORUND, C. J. [AD-A203954] p464 N89-23976 Additional development of the XTRANBS computer Sonic fawue and nonlinear response of stiffened BURLEY, C. L panels program Acoustic test of a model rotor and tail rotor: Results [NASA-CR-181 7431 p 452 N89-20922 [AIAA PAPER 89.1101 ] p 492 A8943741 for the isolated rotors and combined configuration CHRIS, R. Y. BWCHER, C. C. [NASA-TM-1015501 p504 N89-20777 In-flight experiments on the active control of An LDA (Laser-Doppler Anemometry) investigation of BURNSIDE, WALTER D. three-dimensional normal shock wave boundary-layer propellerinducedcabin noise Improved computer simulation of the TCAS 3 circular [AIAA PAPER 89-10471 p468 A8943706 interactions p458 N89-20956 array mounted on an aircraft CHRISTIE, D. R. BOURASSEAU, Y. [NASA-CR-1849071 p496 N89-20363 Thunderstorm-generatedsolitary waves - A wind shear Experimental wind tunnel study of a military-aircraftair BYVALISEV, P. Y. intake. Comparison with flight p 448 A89-35381 hazard p499 A89-34888 A method for calculating potential transonic flows in CHYU, W.J. BOYD, KIT 0. turbomachinery cascades p 449 A8935450 A sell-adaptive computational method for transonic Advanced Recovery Sequencer (ARS) turbulent flow past a real projectile p 443 A8934730 p 471 A89-35843 COAKLEY. T. J. BOYLE, Y. T. C Turbulence modeling lor hypemic flows A comparison of secondary flow in a vane cascade and p 441 A89-33641 a Curved duct p 446 A89-34934 CABELL, R. H. COCKRELL, D. J. BRMTEN. M. E. A smart pattern recognihon system for the automatc A revision of the added mass concept as applied to Applications of a generalized pressure correction Idenbfiitwn of aerospace amsksources parachute motion algorithm for flows in complicated geometries [AIM PAPER 89-11141 p 499 A8943751 [AIM PAPER 8948951 p 461 A8935213 p 493 A8944738 CALIANNO, CARL T. COELHO, PEDRO JORGE BRABBS. THEOWRE A. The development of the panel stabilized slotted-square Heat transfer in gas turbine combustors Fuel-rich catalyiic combustion of Jet-A fuel-equivalence parachute p 491 A89-33580 ratios 5.0 to 8.0 [AIAA PAPER 89-08941 p 461 A89-35212 COLE, JUUAN D. [NASA-TM-101975] p 489 N89-21051 CAMPBELL, RICHARD L Wave drag due to lift for transonic airplanes BRADSHAW. A. Inverse mng descgn in trensonc flow including vtscous p455 N8920938 Load alleviation on transpoct aircraft using acceleration interaction p 473 N89-20947 COLEMAN, LARRY A. feedback p 471 A89-35299 CANDLER, GRAHAM V. Numerical sirnulation of flow wer iced airfoils BRAND, A. A numencal method for predictlng hypersonic [ADA2032911 p458 N89-20969 Resuns from laser sheet visualization 01 a periodic rotor flavflelds p 440 A89-33634 CONANT,JOHN wake p485 A89-34890 CANNON, PATRICK J. Multispectral terrain background simulation techniques BRAND, A. 0. Radius-tippedtnangular inflatable decelerator design as for use in airborne Sensor evaluation Surface pressure measurements on a body subject to affected by produceablitylswvwabilityconstraints p499 A89-33664 vortex wake interaction p 470 A8944808 [AIAA PAPER 8948881 p 463 ABS-36020 CONNORS, J. J. BRAYYEN, W. W. CARLSON, LELAND A. Instantaneous profiles and turbulence statistics of The application 01 CFD lor military aircraft design at Inverse mng-- desian in transontc flow includina viscous supersonic free shear layers by Raman excitation + interaction p473 N89-20947 laser-induced electronic fluorescence (relii9 velocity transonic speeds p454 N89-20930 CARYICHAEL, R. L tagging of oxygen p440 A8933424 BRENNER, 0. Aerodynamic analysis of three advanced configurations -PER, E. E. Numerical simulation of three-dimensimal hypersonic using the TranAir full-potentialcode p 455 N89-20944 Experimental examination of the aerothermal viscous flom p441 A89-33644 CASSIL, CHARLES E. perfcfmanceoftheT-tOtestcellalNAS(NavalAir Station). BRIDGES, DAVID H. Aimorlhiness and flight characteristics evaluation of an Cubi Point A study of transonic drag reduction of a blunt cylinder improved engine air filtration system on the UH-1H [AD-A203887] p 487 N89-21005 by a cylinder probe heliter CORLIS, JOHN Y. [AD-A202557] p458 N89-20965 [AD-A203446] p 480 N89-20145 Development of a rotary value for pulse combustion BRITCHER, COLIN P. CATALANO, GEORGE D. appiitions Test techniques: A survey paper on cryogenic tunnels. Single and muiti-element airfoils in an isotropic turbulent [PB89-131114] p496 N89-20468 adaptive wall test sections. and magnetic suspension and outer flow p439 A89-33383 CORRIGAN, J. C. balance systems p486 N89-20955 CEBECI, TUNCER Coupled rotorlfuselage dynamic analysis of the AH-1G BRWWER, H. H. Numerical instabilies in the calculation of laminar helicopter and conelation with flight Vibrations data A lifting line model for propeller noise separation bubbles and their implitions [NASACR-181723] p 497 N89-20512 [AIM PAPER 89-1079) p502 A8933723 P 445 A8934819 COSKREN, ROBERT J. BROWN, EDWARD N. CHAKRAVARTHY, S. R. Investigation of the service and age lives of US. Amry Position error calibration of a pressure survey aircraft Patched-gridcomputations Of high-speed inlet flows personnel parachutes using a trailing cone P443 A89-34728 [AIAA PAPER 8949151 p462 A8935227 1PB88-250733) p450 N89-20092 CHAO, CHIEN-HSIANG COSNER. RAYMOND R. BROWN, GLEN J. Robust stabilization of linear time-invariant uncertain Transonic propulsion system integration analysis at Tethered paraloil test technique systems via Lyapunov theory P 483 N89-20147 McDonnell Aircraft Company p481 N89-20943 [AIAA PAPER 89-09031 p 462 A89-35219 CHATIOPADHYAY, ADlTl CREW, P. BROWN, JAMES D. Integrated aercdynamicldynamic optimization of Heliter rotor wake investigationusing a laser Doppler heliter rotor blades Airworthiness and flight Characteristics evaluation of an anemometry technique p439 A89-33385 improved engine air filtration system on the UH-1H [NASA-TM-101553] P 473 N89-20982 CRONKHITE, J. D. CHATZIKONSTANTINOU,THOMAS Coupled rotorlfuselage dynamc analysis of the AH-1G helicopter Numerical analysis of three-dimensional non rigid heliter and conelation with flight vibrations data [ADA2034461 p 480 N89-20145 WiuiMa [NASA-CR-181 7231 p 497 N89-20512 BROWN. K. W. [AiGPAPER 89-09071 P450 A89-36022 CUCKSON. H. Structural Tailoring of Advanced Turboprops (STAT) CHAURASIA. M. L Development of a low cost trackinglrangingsystem programmer's manual High altitude parachute and its military applications P465 A8943572 [NASA-CR-182164] p 478 N89-20132 [AIAA PAPER 89-08931 P 461 A89-35211 CUDMORE. A. Y. BRUNO, RICK CHEN. FUOUN Civilian RPVs - Eye in the sky or pie in the sky? Fuel holdup and component diffusivity in a cooled A new method for the thermodynamic calculation of p437 A8943560 cylindrical tank p 488 A89-34894 combustion chambers P 478 A89-34409 CUNNINGHAY, HERBERT J. BUETEFISH, K. A. CHEN, RUlLlN Steady and unsteady transonic small disturbance 3-D LDA-measurements in the bt of a bypass-engine Design of an airborne opt! fiber data bus system analysis of realistic aircraft configurations p 477 A89-33386 P 475 A89-33148 p473 N89-20946 8-2 PERSONAL AUTHOR INDEX FOURNIER, FRANCElTE
CURTIS, JANET C. DRIVER, D. ESGAR, J. B. Modern multiplepulse, high field NMR studies of hgh Direct numerical simulation of a three-dimensional Views on the impact of HOST p 480 N89-20144 density jet fuels turbulent boundary layer p 493 A8934909 ESSER, B. [AD-A2033201 p 490 N89-21130 DRIVER, MARK A. Hgh enthalpy testing in hypersonic shock tunnels Development of a shock capturing code for use as a p485 A89-33630 tool in designing hgh-work low aspect ratio tutbines EUSTACE. P. A. [AD-A202706] p 498 N89-21248 D The Theta Beta ~ Design of a system DRYER, FREDERICK L p468 A8943561 Fuels combusti research DA GRACA CARVALHO, MARIA EVERS, J. F. Heat transfer in gas turbine combustors [ ADA204161 ] p 490 N89-21071 In-flight experiments on the active contrd of WAN, YUAN p 491 A89-33580 prqmller-inducedcabin noise Application of harmonic analysis method to research DAM, T. 8. [AIAA PAPER 89-10471 p468 A89-33706 on rotor airloads p 467 A89-33139 The application of trajectory prediction algorithms for EVERSMAN. WALTER planning purposes in the Netherlands Air Traffic Contrd DUNN, m. G. Transmission and reflection on pressure waves by Finite element modelling of sheared flow effects on the (ATC) system radiation characteristics of acoustic sources in a circular [ NLR-MP-87031-Ul p 465 N89-20115 Compressor and turbine stages, based on an actuatordisk model duct DAS, SANTDSH K. [AD-A2035131 p496 N89-20426 [AIAA PAPER 89-10651 p 502 A89-33726 Rap4dly soli aluminum alloys for high DUTTON, J. C. The effect of the wind tunnel wall boundary layer on temperaturelhigh stiffness applications Mean and turbulent velocity measurements of the acoustic testing of propellers p 488 A89-33474 supersonic mixii layers p 440 A6943426 [AIAA PAPER 6410971 p 503 A89-33737 DAVIDOVICH, T. V. WVAL, J. P. A phj:yshl-:?atistk.s! mekd!or me pdkthd vertical t6sti13mekds i:: fligh! p 470 A@9-35!W wind shear in the lower part of the atmospheric boundary DWOYER. D. F layer p499 A89-34028 Technology requirements for hypersonic airbreathing DAVIS, EDWARD E. aircraft p 468 A8943626 FAN, RENZHOU The U.S. Navy unmanned air vehicle program DYER, D. J. Design of an airborne optic fiber data bus system p 437 A8943555 Flittest of XRAE-t to establish aerodynamic data p 475 A6933148 DAVIS, W. H. p 468 A89-33562 FAVIER, D. Appld transonics at Grumman p 454 N89-20931 Helicopter rotor wake invesligationusing a laser mler DEESE, J. E. anemometry technique p 439 A8943385 EulerlNavierStokescalculations of transonic flow past E FERGUSON. MILTON W. fixed- and rotary-wingaircraft conhgurations A (13)C NMR analysis of the effects of electronradiation p456 N89-20948 ECKSTROM, CLINTON V. on graphtte/polyetherimi& CMmpOsites Geometrical and structural properlies of an Aeroelastic MHM, S. [ NASA-CR-1828181 p 489 N69-20205 Research Wing (ARW-2) Fast. in-situ repair of aircraft panel components FERNANDO, E. M. p438 A89-34896 [NASA-TM-41101 p 451 N89-20099 EDWARDS, P. R. A comparison of the turbulence structure of subsonic MKONING, A. U. Full-scale fatigue testing of aircraft structures and supersonic boundary layers p 440 A8943425 Analysis of crack opening behavior by application of a p485 A69-33802 FIELDING, J. P. discretized stnp yield model EHLERS, F. EDWARD The deve!opmnt of a preliminary %zing method lor [NLR-MP-87065-U] p497 N89-20520 Development and application of a program to calculate unmanned air vehicles p468 A89-33564 DELAAT, JOHN C. transonicflow around an oscillating threedimensionalwing FIRSOV, V. A. A real-time simulator of a turbofan engine using finite dfterence procedures Formulation and solution of axisymmetric problems in [NASA-TM-100869] p481 N89-20995 [NASA-CR-181744] p 450 N89-20093 the statics of multilayer shells of revolution with contact DELALANDE. 0. EICKHOFF, H. interaction between layers p 492 A89-34129 The future of the civil aviation industry The influence of a radial swirl generator on the fbw FLACK, KAREN p438 A89-35377 field from a fuel nozzle model p 490 A89-33354 Performanceand test Section flow characteristics of the DENNIS, R. W. EL-HADY, NABIL M. National Full-ScaleAerodynamics Complex 40- by 80-foot Complementary minis - Skyeye and phoenix, an overview Secondary three-dimensional instability in compressible wind tunnel Of their multi-mission coverage p 467 A6933558 boundary layers p 456 N69-20954 [ NASA-TM-l01065] p 438 N89-20066 DICKINSON. SIMON-r: ELLIOTT, J. W. FLEETER, SANFORD Falconet target nrv operations p 437 ASS-33553 .."*""..*I---=Hr *mi.--I -.nf mnrlal mtw and tail rotor: Results Exprirnental investisation of transonic oscillating n!LLON, LONNIE R. for the isdated rotors and cinnbined confyluratin cascade aerodynamics A wind tunnel and computer investition of the low [ NASA-TM-1015501 p 504 N89-20777 i NASA-TM-iOi 9931 p 478 N89-20133 speed aerodynamic characteristics of the prone escape ELLIOTT, S. J. FLEMING, P. J. system (PRESS) In-flight experiments on the active control of Implementation of a transputer-basedflight controller [ADA2027881 p475 N89-20988 propellerinducedcabin wise p 482 A8935302 DISSELKOEN. ALLEN D. [AIAA PAPER 69-10471 p46J3 A89-33706 FLETCHER, D. G. Pilot ejection from a pronated flying position ELOVIC, E. Laser-induced iodine fluorescence technique for [AIM PAPER 89-08651 p 471 A89-35205 Heat transfer in gas turbine engines and quantitatie measurement in a nonreacting supersonic DIWAR, JAMES H. threedimensional flows; Proceedings of the Symposium, combustor p 445 A89-34809 Comparison of propeller cruise noise data taken in the ASME Winter Annual Meeting. Chicago. IL. Nov. 27-Dec. FLETCHER, L S. NASA Lewis 6- by 6-1001 wind tunnel with other tunnel 2.1988 p 494 A89-34926 Experimental investigation of the thermal conductivity and fliht data ELROD, D. of dispersed ceramic materials p 488 A8934933 [NASA-TM-1019761 p 505 N89-21628 Annular honeycomb seals: Test results for leakage and FLOOD, JOSEPH D. DIXON, S. L rotordymm coefficients. Comparisons to labyrinth and Hot gas ingestion testing of an advanced STOVL Compressible flow losses in branched ducts smooth configurations concept in the NASA Lewis 9- by 15-1001 Low Speed Wind p494 A6935004 [ASME PAPER 88-TRIM51 p 493 A89-34794 Tunnel with Row visualization MHiGElT, ROBERT V., JR. An entrance region friction factor model applied to [AIAA PAPER 88-30251 p 439 A89-33249 Some low-speed flutter characteristics of simple annular seal analysis - Tlmcny versus experiment for FLORES, JOLEN low-aspect-rati delta wing models smooth and honeywmb seals Advances in the computation of transonic separated [NASA-TM-101547] p450 N89-20094 [ASME PAPER 8STRIB411 p493 A89-34798 flows over finite wings p442 A89-34427 DOMINICK, A. ELSENMR. A. FORLANDA, JUANCHO E. Electromagneticproperties of ice coated surfaces Detailed measurements in the transonic vortical flow Performance analysis of the fiber distributed data [NASA-CR-184780] p 495 N89-20355 over a delta wing p 449 A89-36012 interface in the super cockpit audio world DOMPKA, R. V. Observed Reynolds number effects on airfoils and high [AD42025351 p474 N89-20985 Coupled rotorlfuselage dynamic analysis of the AH-1G aspect ratio wings at transonic flow condifins FORTIN, PAUL helicopter and correlation with fliht vibrations data [NLR-MP-88CCE-U] p 451 N89-20102 lnvestjgationof a free-tip rotor conhgurationfor research on spanwise life distributins and wake velocity sulveys [NASA-CR-181723] p 497 N89-20512 EMANUEL, GEORGE of a semi-span wing with a discontinuous twist DONALDSON. J. C. A first scramjet stus, [NASA-CR-184946] p457 N89-20963 lnvestiation of the development of laminar [NASA-CR-t84965] p 460 N89-20146 boundary-layer instabilities along a cooled-wall cone in FOUGHNER, JEROME T., JR. hypersonic flows ENGELUND, W. C. Transonic Symposium: Theory, Apphcati, and Navier-Stokes calculations of scramjet-aftehdy Experiment, Volume 1, Part 1 [ADA2025871 p458 N89-20966 p 443 A89-34732 DOVIAK, R. J. flowfields [NASA-CP-3020-VOL-1-PT-l] p 453 N89-20925 Thunderstorm-generatedsolitary waves .A wind shear ENGLUND, D. R. Transonic Symposium: Theory, Application. and hazard p499 A89-34888 Advanced high temperature instrument for hot section Experiment volume 1. parl2 DOYLE, JAY J. research applications p 479 N89-20137 [NASA-CP-302O-VOL-l-PT-2] p 455 N89-20942 Launch, recovery and handling systems for vertical EPPARD, W. M. FOURNIER, FRANCElTE take-off and landing UAVs operating from small ships Efficient optimization of integrated Prediction of potential noise interactions in axial-flow p484 A89-33569 aerodynamic-structural design p 500 A89-34569 machines - Application to the helicopter fenestron DRESS, DAVID A. ERICKSEN, R. H. p 504 A69-35385 Test techniques: A SUNW paper on cryogenic tunnels. Development of an alternating flat to tubular Kevlar Prediction of wake-interaction noise in axial-flow adaptive wall test sections. and magnetic suspension and parachute tape machines - Application to helicopter fenestron balance systems p 486 N89-20955 [AIM PAPER 6949101 p 462 A89-35223 D 504 A8945388
8-3 FREMAUX, C. MIKE PERSONAL AUTHOR INDEX
FREMAUX, C. MIKE GORBATKO, A. A. HANSON, D. B. Single and multi-elementairfoils in an isotropic turbulent Characteristicsof the formation of benz(a)pyrene in the Sound power spectrum and wave drag of a propeller outer flow p 439 A89-33383 combustion chambers 01 aviation gas turbine engines in flight FRINK. NEAL 1. p 488 A89-34119 [AIAA PAPER 89-10811 p 502 A89-33724 Wind-tunnel wall effects on delta wings GORELOV, G. M. Near wakes of advanced turbopropellers p 445 A89-34884 An experimentalstudy of the rate characteristics01 brush [AIAA PAPER 89-10951 p 441 A89-33735 FRISCH, GEORGE seals in comparison with labyrinth seals HARRIS, G. L. Transoniclsupersonic (720 KEAS 1.2 Mach) ejection p 492 A8934136 Complementary minis - Skyeye and Phoenix, an overview demonstration test of an S4S Biofidelity Manikin (BFMl) GORSKI, J. J. of their multi-mission coverage p 467 A89-33558 p 463 A89-35841 Incompressible cascade calculation using an upwind HARRISON, JAMES V. A. FRUCHT, Y. 1. differenced NDscheme p 444 A8944733 Reliability and performance evaluation of systems A revision of the added mass concept as applied to GRACIA-SALCEDO, CARMEN M. containing embedded rule-based expert systems [NASA-CR-181 7691 parachute motion Fuel-rich catalytic combustion of Jet-A fuel-equivalence p500 N89-20683 HART-SMITH, J. [AIAA PAPER 89-08951 p 461 A89-35213 ratios 5.0 to 8.0 Designing with advanced fibrous composites FRUCHT. YAACOV 1. [ NASA-TM-1019751 p 489 N89-21051 High’Reynolds number incompressible flow simulation p 470 A89-35197 GRAHAM, MAlTHEW S. HARVEY, P. R. about parachute canopies and Slmilar bluff bodies Airworthiness and flight characteristics evaluation of an p 450 N89-20096 Structural Tailoring of Advanced Turboprops (STAT) improved engine air filtration system on the UH-1H FULLER, C. R. programmer’s manual helicopter [NASA-CR-1821641 p 478 N89-20132 Full-scale demonstrationtests of cabin noise reduction [ADA2034461 p 480 N89-20145 using active vibration control HARWOOD, R. J. [AIAA PAPER 89.10741 p 468 A89-33719 GRANT, DAVID M. A revision of the added mass concept as applied to Modern multiple-pulse, high field NMR studies of high A smart pattern recognition system for the automatic parachute motion density jet fuels identification of aerospace acoustic sources [AIM PAPER 89-08951 p 461 A8945213 [AIAA PAPER 89-11141 p 499 A89-33751 [ AD-A203320 I p 490 N89-21130 HASSA, CH. GREAVES, R. L. C. The influence of a radial swirl generator on the flow Fatigue evaluation of helicopter rotor heads field from a fuel nozzle model p 490 A8943354 G p 485 A8943803 HATCHER, M. 0. GREENBERG, BARRY M. Investigation of the development of laminar GALLY, THOMAS A. Propulsion over a wide Mach number range boundary-layer instabilities along a cooled-wall wne in Inverse wing design in transonic flow including viscous [NASA-CR-182267] p 478 N89-20134 hypersonic flows interaction p 473 N89-20947 GRIFFITHS, S. K. [AD-A2025871 p458 N89-20966 GAO, ZHENG Attenuation of blast waves using foam and other HAUSER, 0. C. A study of the rotor wake in nap-of-the-earth materials Small parachute flight data acquisition system p 439 A89-33140 [AD-A203148] p 505 N89-21632 [AIAA PAPER 89-09241 p 463 A89-35234 GARCIA NOCElTI, D. F. GRILLON, F. HAWORTH. LORAN Implementationof a transputer-based flight controller Advanced microstructural observations of gas turbine AH-IS communication switch integration program p 482 A8945302 PlM materials p 487 A89-33458 [NASA-TM-101053I p 466 N89-20976 GARGIULO, ROBERT F. GROENIG, H. HE, CHENGJAN Pilot ejection from a pronated flying position A study of the rotor wake nap-of-the-earth High enthalpy testing in hypersonic shock tunnels in [AIM PAPER 89-08851 p 471 A89-35205 p 439 A89-33140 p 485 A89-33630 GARRIZ, J. A. HE, KEMlN GROSSMAN, E. Wall interference assessment and corrections The correlation between Reynolds stress and turbulent Efficient optimization of integrated p 457 N89-20958 kinetic energy in the near wake of a symmetric airfoil aerodynamic-structuraldesign p 500 A89-34569 GAUBERT, MICHEL p 448 A8945393 GROSVELD, FERDINAND W. Hub and blade strwlural loads measurements of an HEFFERNAN, RUTH Noise reduction of a composite cylinder subjected to M. SA349l2 helicopter Hub and blade structural loads measurements of an random acoustic excitation [ NASA-TM-1010401 p 472 N89-20124 SA34912 helicopter GEORGE, PAUL E. [AIAA PAPER 89-10491 p 501 A89-33708 GRUNDY, E. [ NASA-TM-1010401 p 472 N89-20124 Development of a rotary value for pulse combustion HEIDELBERG, LAURENCE J. Structure and properties of forged ODS nickel-base applications Unsteady blade pressure measurements on a model [PB89-1311141 p 496 N89-20468 superalloys p 491 A89-33461 GUO, Y. P. counterrotation propeller GERSTEN. K. [ NASA-TM-1020021 p 504 N89-20779 Vortex breakdown and its control on delta wings On sound generationby a jet flow passing a semi-infinite aerofoil HEINE, J. E. p 449 A89-35999 The effect 01 stress ratio on the near-threshold fatigue GESSOW, ALFRED [AIAA PAPER 89-10701 p 501 A89-33716 GUSAROV, S. A. crack growth behavior 01 Ti-8AI-1 Mo-1 V at elevated Model for investigationof helicopter fuselage influence temperature p 489 A8945722 An analytical-experimentalstudy of ring gap losses in on rotor flowfields p 445 A89-34883 HEINEMANN, F. small axial-flow turbines p 478 A89-34141 GIBSON, K. S. Spray formed Waspaloy for disc forgings Civilian RPVs - Eye in the sky or pie in the sky? p 487 A89-33463 p 437 A89-33560 H HEISE. KEITH H. GILBERT, MICHAEL G. Pilot ejection from a pronated flying position Aeroelastic deformation effects on the stopped-rotor HAAKE, F. K. [AIM PAPER 89-08851 p 471 A89-35205 dynamics of an X-wing aircratt p 482 A89-34897 The effect of stress ratio on the near-threshold fatigue HEISTER, STEPHEN DOUGLAS GILL, B. J. crack growth behavior of Ti-8AI-1 Mo-1V at elevated Transverse jets in compressible crossflows Argon shrouded plasma coatings for gas turbine temperature p 489 A8945722 p 452 N89-20923 applications p 491 A89-33487 HAFEZ M. HENDERSON, WILLIAM P. OILMAN, PAUL S. Vector potential methods p 455 N89-20939 Airframelpropulsion integration characteristics at Rapidly solidified aluminum alloys for high HAFTKA, R. T. transonic speeds p 453 N89-20926 temperaturelhighstiffness applications Efficient optimization of integrated HIGUCHI, H. p 488 A89-33474 aerodynamic-structuraldesign p 500 A8944569 Aerodynamics of two-dimensional sloned bluff bodies GLADDEN, H. J. HALE, K. [DE89-007288] p 452 N89-20105 Review and assessment of the database and numerical Annular honeycomb seals: Test results for leakage and HIGUCHI, HlROSHl modeling for turbine heat transfer p 479 N89-20139 rotordynamic coefficients . Comparisons to labyrinth and Flow visualization studies of wake behind axisymmetric GLASSMAN, IRVlN smooth configurations bluff bodies including parachute canopy models Fuels combustion research [ASME PAPER 88-TRIB-351 p 493 A8944794 [AIAA PAPER 89-08981 p 447 A89-35215 [AD-A204161] p 490 N89-21071 HALFORD, G. R. HINEDI, S. High-dynamic GPS tracking GLEGG, STEWART A. L. Fatigue life prediction modeling for turbine hot section [NASA-CR-184868] p 465 N89-20113 The prediction 01 blade wake interaction noise based materials P 480 N89-20142 HINGST, W. R. on a turbulent vortex model HALL, CHRISTOPHER 0. Preliminary design of a modular unmanned research An LDA (Laser-Doppler Anemometry) investigation of [AIAA PAPER 89-11341 p 503 A8943764 vehicle. Volume 1: System design document three-dimensional normal shock wave boundary-layer GLIEBE, P. R. [AD-A202765] P 474 N89-20987 interactions p 456 N89-20956 Acoustic characteristics of counterrotating fans from HALL, JAMES E. HO, F. H. model scale tests Personnel parachute agelservice life criteria On the design of biaxially stiffened composite plates [AIAA PAPER 89-11421 p 477 A8943769 [AIAA PAPER 89-09161 P 462 A89-35228 p 493 A89-34867 GOEBEL, S. G. HAN, J. C. HOELLER, P. Mean and turbulent velocity measurements of Effect of jet grid turbulence on turbulent boundary layer Micro radiography and tomography for high resolution supersonic mixing layers p 440 A89-33426 heat transfer P 494 A8944930 NOT 01 advanced materials and microstructural GOLDENBLAT, 1.1. HANING, ROBERT K. components p 495 A89-35081 Structural mechanics: Contemporary state and Power efficient hydraulic systems. Volume 1: Study HOHEISEL, H. prospects for development (selected portions) phase 3-D LDA-measurementsin the jet of a bypass-engine [AD-A198766] p 497 N89-20498 [AD-A203899] P 472 N89-20127 p 477 A89-33386 GOODEN, J. H. M. Power efficient hydraulic systems. Volume 2: Hardware HOLDEMAN. J. 0. Comparison of LOA and LTA application for propeller demonstration phase Assessment, development, and application of tests in wind tunnels D 490 A89-33381 [ AD-AZ03900] P 473 N89-20128 combustor aerothermal models p 479 N89-20138
8-4 PERSONAL AUTHOR INDEX KOMERATH. N. M.
HOLLANDERS, H. J KAYNAK, UNVER Computational methods for hypersonic flows - Special Advances in the computation of transonic separated techniques and real gas effects p 441 A89-33640 JAEGER, H. flows over finite wings p 442 A8944427 HOLLOWELL, JEFF Spray formed Waspaloy for disc forgings KEITH, T. G., JR. Trajectory scoring in rectangular coordinates using p 487 A89-33463 An LDA (Laser-Doppler Anemometry) investigation of transponder-interrogatorrange and range rate data JAMSHIDIAT, HAMlD three-dimensional normal shock wave boundary-layer [ DE89-0070051 p 466 N89-20119 Prediction of structural-acoustic response of an aircraft interactions p 456 N89-20956 fuselage modeled as a periodic structure KELLEY, TIMOTHY C. HOPKIN, V. DAVID [AIAA PAPER 89-10451 p 466 A89-33705 Air traffic conhol p 437 A69-34450 Application of the boundary element method lo fatigue JANAKIRAY, R. D. crack growth analysis HORNUNG, H. Importanceof engine as a source of helicopter external [ AD-A202565] p 498 N89-21270 Detailed measurements in the transonic vortical flow noise KEMP. W. B., JR. over a delta wing p 449 A89-36012 [AIM PAPER 89-11471 p 470 A8943771 Wall interference assessment and corrections JANARDAN, B. A. HOROWITZ, 1. p 457 N89-20958 Acoustic characteristics of counterrotating fans from Quantitative design for systems with uncertainty and KHOLA, H. S. conhol failures p 500 A89-35283 model scale tests [AIAA PAPER 89-11421 p 477 ABS-33769 Advanced techniques used in Kanishka aircraft accident HORSTMAN, CLIFFORD C. JARVIS, GARY L investigation p460 A6945200 Documentation of two- and three-dimensional Controlling severed helicopter blades during emergency KHULIEF, Y. A. hypersonic shock wavelturbulent boundary layer escape p 471 A89-35842 Transient dynamics of aircraft propellers during interaction flows JEANDIN, touch-down impact p 470 A89-34509 [ NASA-TM-1010751 p 451 N89-20100 m. Advanced microstructural ObSeNatiOnS of gas turbine KILGORE, ROBERT A. HOUPIS, C. PIM materials p 487 A8933456 Test techniques: A survey paper on cryogenic tunnels. Quantitatnre deqn for systems with uncertainty and JOHNS, ALBERT L adaptive wall test sections. and magnetic suspension and conhol failures p500 A89-35283 Hot gas ingestion testing of an advanced STOVL balance systems p 486 N89-20955 HOWARD, P. J. concept in the NASA Lewis 9- by 15-foot Low Sped Wind KILGORE, W. ALLEN Instantaneous profiles and turbulence statistics of Tunnel with flow visualization Performance of the active sidewall boundary-layer supersonic free shear layers by Raman excitation + [AIM PAPER 88-30251 p 439 A89-33249 removal system for the Langley 0.3-meter Transonic laser-induced electronic fluorescence (relief) velocity JOHNSON, A. m. Cryogenic Tunnel tagging of oxygen p 440 A8943424 Titanium PM attributes and potential for aircraft engine [ NASA-CR-1817931 p 486 N89-21004 HSU, C.C. applications p 487 A8943465 KINKER, LAWRENCE E. A self-adaptive computational method for transonic JOHNSON. DONALD W. Transoniclsupersonic (720 KEAS 1.2 Mach) ejection turbulent Rav past a real projectile p 443 A89-34730 Testing of a new recovery parachute system lor the demonstration test of an S4S Biofidelity Manikin (BFM1) F11 1 aircraft crew escape module - An update p 463 A8945841 HU. ANREN [AIM PAPER 89-08911 p 471 ABS-35209 KINSEY, DON W. Modal cost analysis of flexible structures: Modeling The effects of unsteady aerodynamics on single and flexible structures for control design p 483 N89-20148 Two-dimensionalNavier-Stokes solution of the flow over clustered parachute system a thick supercritical airfoil with strong shock-induced HUDSON, S. M. [AIAA PAPER 89-09341 p 448 A8935250 separation Integrated modular RPV ground station with reference JOHNSON, RICHARD L [AD-A203331I p 459 N89-20971 to the 'Raven' pmiect p 485 A8943575 Preliminary design 01 a modular unmanned research KIRILLOV, 1. 1. HUFF, RONALD 0. vehicle. Volume 1: System design document Ceramics in high-temperaturegas turbines (Review) Noise generated by a flight weight. air flow control valve [AD-A202765] p 474 N89-20987 p 488 A89-34080 in a vertical takeoff and landing aircraft thrust vectoring JOHNSON, WAYNE KISELEV, V. IA. system Caicuiation oi biade-vortex inieiaeiion airloads on Turbulization of a hign-veiocity boundary iayer by a [NASA-CR-l82232] p 504 N89-20776 helicopter rotors p 446 A8944895 projection p 448 A89-35434 HUGHES, CHRISTOPHER E. JOHNSTON, L J. KLOPFER, G. H. Flowfield measurements in the NASA Lewis Research A calculationmethod forcompressiblethree dimensional High-resolution shock-capturing schemes for inviscid Center 9- by 15-fool low-speed wind tunnel turbulent boundary layer flows and viscous hypersonic flows p 443 A8944646 [ NASA-TM-1008831 p 486 N89-21002 [VKI-TN-167] p 496 N89-20422 KLYDE, DAVID H. HUNTER, HENRY J. JONES, J. D. Tailless aircraft performanceimprovements with relaxed Aerial delivery of personnel in ground proximity Full-scale demonstrationtests of cabin noise reduction static stability [AIAA PAPER 8948871 p 461 A89-35207 using active vibration control [NASA-CR-181806] p 483 N89-20999 HUPP, RICHARD V. [AIAA PAPER 69-10741 p 468 A89-33719 KNACKE, T. W. Power effiient hydraulic systems. Volume 1: Study Adaptive active control olenclosed sound fields in elastic Parachutes - Yesterday. today. and tomorrow phase cylinders via vibrational inprts [AIAA PAPER 89-08801 p 463 A89-36019 IAD-A2038991 o 472 N89-20127 lAlAA PAPER 89.10751 p 469 A89-33720 .YUVP". . . . -. .. 111.-. .A .. Power efficient hydraulic systems. Volume 2: Hardware JONES, MICHAEL G. Characteristics of the formation of benz(a)pyrene in the demonshation phase Airfoil profile drag increase due lo acoustic excitation combustion chambers of aviation gas turbine engines [AD-A203900] p 473 N89-20128 [AIAA PAPER 89-10691 p 501 A89-33715 p 488 ~89-34119 HURLEY, D. 0. JONNAVITHULA, S. KOBAYAKAWA, MAKOTO Mathematical research at the Aeronautical Research Computational study of theeffectof cascade parameters Numerical solutions lor the flowfield around a Laboratories 1939-1960 p 437 A89-32902 on stall propagation in axial compressors counter-rotating propeller p 445 A89-34887 p 444 A89-34737 KOBYLARZ. THOMAS J. JOSHUA. JOHN Flight controller design with nonlinear aerodynamics. I Fuel holdup and component diffusivity in a cooled large parameter uncertainty and pilot compensation cylindrical tank p 488 A8944894 [ AD-A2027271 p 484 N89-21000 IARKOVETS, A. 1. JULING, W. KOCH. MARK A. Ensuring the quality of the covering surface in the case Calculation of compression shock surfaces in Radius-tippedtriangular inflatable decelerator design as Of riveted joints with high radial interlereme three-dimensional, steady supersonic flows using a affected by produceabilitylsurvivability constraints p 492 A8944159 bicharacteristic method p 446 A89-35168 [AIAA PAPER 89-08881 p463 A89-36020 ICHIKAWA, TERUO KOCH, R. On a method for solving integral equations of Development of an alternating flat to tubular Kevlar lifting-surface theory for oscillating high-speed propellers K parachute tape p 439 A89-33100 [AIAA PAPER 89-09101 p 462 A89-35223 INGER, G. R. KADYSHEV. V. 0. KOCHIN, V. A. Turbulent eddy viscosity modeling in transonic Some aspects of the numerical modeling 01 the Viscosity effects in the generation of the lilting force shocklboundary-layer interactions p 456 N89-20952 nonstationary heat conductivity of gas turbine of aerodynamic wing profiles p 442 A8944114 components p 477 A8934139 IRWIN, 0. W. KODRES, C. A. Multivariable design of a bank-to-turn autopilot for KAO. P. J. Experimental examination of the aerothermal command guidance p 482 A89-35301 Efficient optimization of integrated performanceof theT-lOtestcellatNAS(NavalAirStation), IUNUSOV, F. S. aerodynamic-structuraldesign p 500 A89-34569 Cubi Point Adaptive control of the grinding of large gas turbine KARPEL, M. [AD-A203887] p 487 N89-21005 blades p 492 A89-34144 Structural optimization for aeroelastic control KOHAMA. Y. IVANOV, M. IA. effectiveness p 470 A8944899 Three-dimensionalboundary-layer transition study A method for calculating potential transonic flows in KATSIGRIS. E. C. p 447 A89-35195 turbomachinery cascades p 449 A8945450 Determinationof GPS orbits lo submeter accuracy KOLKMAN, H. J. IVANOV, 0. N. p 466 N89-20331 Quench sensitivity of airframe aluminum alloys Supersonic flow past caret wings and elements of KATZ. J. [NLR-MP-88003-U] p 489 N89-20231 star-shaped bodies at angles of anack and bank Effect 01 90 degree flap on the aerodynamics of a KOMERATH, N. p 449 A8935481 twoslement airfoil p 446 A8935053 Results from laser sheet visualization of a periodic rotor IVLIEV, A v. KAUFMAN, A. E. wake p 485 A8944890 Characteristicsof the formation of benz(a)pyrene in the Performance optimization for rotors in hover and axial KOMERATH, N. M. combustion chambers of aviation gas turbine engines flight Surface pressure measurements on a bcdy subject to p 488 A89-34119 [NASA-CR-1775241 p 459 N89-20973 vortex wake interaction P 470 A89-34808
B-5 KONDRASHOV, V. 2. PERSONAL AUTHOR INDEX
KONDRASHOV, V. 2. LAWRENCE, J. H. LORIMOR, GARY K. Ensuring the quality of the covering surface in the case An experimental investigationof the aerodynamic loads Real-time display of time dependent data using a of nveted joints with high radial interference on cambered plates head-mounted display p 492 A89-34159 [AIM PAPER 89-09351 p 447 A89-35244 [AD-A203051] p 476 N89-20993 K001, J. W. LAWRENCE, JOHN S. LOSIER, PAUL W. Comparison of LDA and LTA application for propeller Airworthiness and flight characteristics evaluation of an Airworthiness and flight characteristics evaluation of an tests in wind tunnels p 490 A89-33381 improved engine air filtration system on the UH-1H improved engine air filtration system on the UH-1H KOROULLA, W. helicopter helicopter Numerical simulation of three-dimensional hypersonic [AD-A203446] p 480 N89-20145 [AD-A203446] p 480 N89-20145 viscous flows p 441 A89-33644 LE BALLEUR. J. C. LOUIE, ALEXANDER KORNIENKO, E. S. Viscous-inviscid interaction and computation in Evaluation of VSAERO in prediction of aerodynamic Effect of the asymmetry of boundary conditions on aerodynamics characteristics of helicopter hub fairings boundary layer flow near a cone at angle of anack [ONERA. TP NO. 1988-1161 p 443 A89-34627 [NASA-TM-101 0481 p 451 N89-20098 p 448 A89-35433 LEE, 8. H. LOWSON, MARTIN V. KOROTKOV. 0. IU. An experimental study of transonic buffet of a Acoustic forcing of three dimensional shear layers Analysis of separated flow past a thin profile in the case supercritical airfoil with trailing edge flap [AIM PAPER 89.10631 p 501 A89-33712 of translational oscillations p 442 A89-34151 [AD-A203189] p 458 N89-20968 LU, H. Y. KORZUNOV, IU. L. LEE, E. H. K. Fuselage boundary layer effects on sound propagation Effect of the design of a two-row nozzle ring on the Transonic buffetof a supercriticalairfoil with trailing-edge and scanering efficiency of a turbine stage of medium rotor solidity p 446 A89-34893 [AIAA PAPER 89.10981 p 503 A89-33738 D 477 A89-34140 flap LEE, C. LU, PONGJEU KOSTIUCHENKO, S. S. High speed balancing applied the T700 engine A numerical investigation of steady transonic cascade Effect of the design of a two-row nozzle nng on the to [NASA-CR-I808991 p 497 N89-20472 flow in turbomachinery p 448 A89-35417 efficiency of a turbine stage of medium rotor solidity LEE, CALVIN K. LUCK, R. p 477 A89-34140 Observer design for compensation of network-induced KOZLOV, L F. Modeling of parachute opening - An experimental investigation p 460 A89-34891 delays in integrated communication and control systems Viscosity effects in the generation of the lifting force p 500 A89-35044 of aerodynamic wing profiles p 442 A89-34114 A control canopy release method for improved opening LUKACHEV, S. V. KRAMER. STUART of clustered parachutes Characteristicsof the formation of benz(a)pyrenein the A pronated escape system for fighter aircraft [AIAA PAPER 89-08921 p 461 A89-35210 combustion chambers of aviation gas turbine engines p 463 A89-35845 LEE, EDWIN E., JR. p 488 A89-34119 KRIER, H. Capabilities of wind tunnels with two-adaptive walls to Mean and turbulent velocity measurements of minimize boundary interference in 3-D model testing LUMBROSO, 0. M. supersonic mixing layers p 440 A89-33426 p 486 N89-20961 Civilian RPVs - Eye in the sky or pie in the sky? KRIER, HERMAN LEE, KAY-PUI p 437 A89-33560 Attenuation of blast waves usina foam and other Viscous shock layer analysis of hypersonic flows over LUNEV, A. N. malerials long slender vehicles p 451 N89-20097 Adaptive control of the grinding of large gas turbine blades p 492 A89-34144 [ ADA2031481 p 505 N89-21632 LECHER, S. KRYLOV, B. A. Investigation of flow separation in a three-dimensionai LUO, HANSHENG An analyhcalexpenmental study of ring gap losses in diffuser using a coupled Euler and boundary-layer Expenmental investigationof electrostatic fire accidents small axial-flow turbines p 478 A89-34141 method p 446 A89-35172 after aircraft landing and preventive measures p 460 A89-34885 KUMAGAI. HlROYUKl LENT, H.-M. Investgatton of a free-bp rotor configuration for research Sound generation and flow interaction of vortices with LUONG, T. M. on spanwlse life distnbutions and wake velocity surveys an airfoil and a flat plate in transonic flow Full-scale demonstration tests of cabin noise reduction using active vibration control of a semi-span mng with a discontinuous twlst p 449 A89-36006 [AlAA PAPER 89-10741 p 468 A89-33719 [ NASA-CR-1849481 p 457 N89-20963 LEO, ANTHONY KUMAR, RAJESH Fuel holdup and component diffusivity in a cooled LYSENKO, V. 1. High altitude parachute and its milttary applications cylindrical tank p 488 A89-34894 Turbulization of a high-velocity boundary layer by a projection p 448 A89-35434 [AlAA PAPER 89-08931 p 461 A89-35211 LESTER, H. C. KUNTZ. H. L Propeller modellingeffects on interior noise in cylindrical lntenor noise in the untreated Gulfstream II Propfan Test cavities with application to active control AsSesmenl (PTA) aircraft [AIM PAPER 89-11231 p 469 A89-33757 M [AIAA PAPER 89-11191 p 469 A89-33754 LEVY, R. MA, ENCHUN KUNZ, J. Bipolar coordinates for computation of transition duct Effect of wing lip strakes on wing lifldrag ratio Quanbtabve fractography Possibilities and applications flows p 493 A89-34912 p 445 A89-34886 in aircraft research p 495 A89-35074 LICHTEN, S. M. MACCORMACK, ROBERT W. KUSSOY. MARVIN 1. Determinationof GPS orbits lo submeter accuracy Documentation of two- and three-dimensional A numerical method for predicting hypersonic p 466 N89-20331 flowfields p 440 A89-33634 hypersonic shock wave/turbulent boundary layer LIEFTING, 0. interachon flows Analysis of crack opening behavior by application of a MACHA, J. MICHAEL [ NASA-TM-1010751 p 451 N89-20100 discretized strip yield model A preliminary characterization of parachute wake KUZNETSOV, V. R. [ NLR-MP-87065-UI p 497 N89-20520 recontact Effect of turbulence on the combustion of an atomized LIFSHITS. IU. B. [AIM PAPER 89-08971 p 447 A89-35214 liquid fuel p 488 A89-34122 Potential models of transonic flows Wall-interference corrections for parachutes in a closed p 449 A89-35495 wind tunnel LILLIE, THOMAS H. [AIAA PAPER 89-09001 p 485 A89-35217 L Contaminationof the exlerior of a C-130E aircraft used MAOABHUSHI. R. K. lor aerial spray, 907 TAG, Rickenbacker ANGB, OH Bipolar coordinates for computation of transition duct LAI, H. [AD-A202430] p 474 N89-20984 .flows p 493 A89-34912 Comparison of 3D computation and experiment for LINDE, M. MADSON, M. D. non-axisymmetric nozzles The flow on the lee-side of a delta wing at Mach 7 Aerodynamic analysis of three advanced configurations [NASA-CR-182245] p 452 N89-20921 p 440 A89-33637 using the TranAir full-potential code p 455 N89-20944 LAMATSCH, PETER J. LIPANOV, A. M. MAESTRATI, J. Preliminary design of a modular unmanned research Numerical modeling of transonic flow of a viscous gas Business aviation and new technologies vehicle. Volume 1: System design document in a plane channel with a sudden expansion p 438 A89-35379 [ AD-A202765] p 474 N89-20987 p 442 A89-34149 MAHON, J. LANDMANN, A. E. LIlT. JONATHAN S. Complementary minis - Skyeye and Phoenix, an overview Model size requirements for finite element prediction A real-time simulator of a turbofan engine of their multi-mission coverage p 467 A89-33558 of low-frequencycabin noise and vibration [NASA-TM-I008691 p 481 N89-20995 LIU, HENRY MAISL, M. [AIAA PAPER 89-10761 p 469 A89-33721 Micro radiography and tomography for high resolution Wind damage to airports - Lessons learned LANE, D. M. NDT of advanced materials and microstructural New static engine noise lest techniques which reduce P 499 A89-34359 LO, C. F. components p 495 A89-35081 test lime significantly Two-measured variable method for wall interference MAJDA, ANDREW J. [AIAA PAPER 89-11271 p 485 A89-33760 assessment/correction P 457 N89-20959 Nonlinear kink modes for supersonic vortex sheets LARGMAN, R. LOEHNER, RAINALD p 442 A89-33783 Effect of 90 degree flap on the aerodynamics of a Generation of unstructuredgrids and Euler solutions for MALM, R. P. two-element airfoil p 446 A89-35053 complex geometries P 455 N89-20941 Deriving a geocentric reference frame for satellite LAVRICH. P. L. LOEHR, K. F. positioning and navigation p 466 N89-20330 Interaction noise mechanisms for an advanced propeller Sound generation and flow interaction of vortices with MALMUTH, NORMAN D.
~ Experimental results an airfoil and a flat plate in transonic flow Wave drag due lo lift lor transonic airplanes [AIM PAPER 89-10931 p 502 A89-33733 p449 A89-36006 p 455 N89-20938 Interaction noise mechanisms for advanced propellers LONDENBERG, W. K. MAMAEV, B. 1. - Analytical evaluation The application of CFD for militaly aircraft design at Optimal profile Selection in the design of a subsonic [AIAA PAPER 89.10941 p 502 A89-33734 transonic speeds p 454 N89-20930 turbine cascade p 442 A89-34152 PERSONAL AUTHOR INDEX NATEGHI, FARIBORZ
MANDIC, D. S. MCDANIEL, J. C. MONGIA,H.C. Adaptive active control of enclosed sound fields in elastlc Laser-induced iodine fluorescence technique for Assessment, development, and application of cylinders via vibrational inputs quantitative measurement in a nonreacting supersonic combustor aerothermal models p 479 N89-20138 [AIAA PAPER 89-10751 p 469 A89-33720 combustor p 445 A89-34809 High density fuel effects MARCHI, L MCELRATH, WILLIAM E. [AD-A202426] p 490 N89-21125 A linear computer code to determineaeroelastic stability Controllingsevered helicopter blades during emergency MONTAGNE, J. L. in airfoil cascades at unsteady flow conditions escape p 471 A89-35842 Computational methods for hypersonic flows Special MCKINNEY, P. - p 444 A89-34746 techniques and real gas effects p 441 A8943640 Analysis of Doppler radar windshear data MAREC, J.-P. MONTAGNE, J.-L ONERA research on civil aircraft p 438 A89-35376 [ NASA-CR-I81 7621 p 464 N89-20111 MCKNIGHT, R. L. High-resolution shock-capturing schemes for inviscid MARESCA, C. Structural analysis applications p 480 N89-20141 and viscous hypersonic flows p 443 A89-34846 Helicopterrotor wake investigationusing a laser Doppler MORAEUS, LARS anemometry technique p 439 A89-33385 MCMAHON, H. Results from laser sheet visualization of a periodic rotor Estimation of the Equivalent Initial Flow Size (EIFS) MARKOVITZ, E. C. wake p 485 A89-34890 distribution and prediction of failure probabilities for Instantaneous profiles and turbulence StatiStiCS Of MCMAHON, H. M. different parameter variations supersonic free shear layers by Raman excitation + Surface pressure measurements on a body subject to [FFA-TN-1987-35] p 498 N89-20525 laser-induced electronic fluorescence (relief) Velocity vortex wake interaclion p 470 A89-34808 MORAITIS, C. S. tagging 01 oxygen p 440 A8943424 MCMILLIN, S. N. Particle image displacement velocirnetry applied in high MARRAFFA, L Euler and Navier-Stokesleeside flows over supersonic speed flows p 490 A89-33388 Computational methods for hypersonic flows - Special delta wngs p 445 A8944892 MOREHOUSE, EDWARD T., JR. techniques and real gas effects p 441 A89-33640 MEETHAM, 0. W. Fire extinguishing agents for oxygen-enriched MARSH, KENNEW JAMES Metallic limitationsin aircraftengines - The rational return atmospheres p 487 A89-32948 Full-scale fatigue testing of components and to the stone age p 477 A89-33485 MORIARN, J. A. structures p 485 A89-33801 MEIER, 0. E. A. Thin aerofoils with high-incidence flaps or blunt trailing MARTENS, NATHAN W. Sound generation and flow interaction of vortices with edges p 445 A89-34749 Effect of riblets upon flow separation in a subsonic an airfoil and a flat plate in transonic flow MORICE, PH. diffuser p449 A89-36006 Computational methods for hypersonic flows - Special [AD-A203178] p 458 N89-20967 MELSON. N. DUANE techniques and real gas effects p 441 A8943640 MARTIN, M. Updated users' guide for TAWFIVE with multigrid MOSS, J. N. High speed balancing applied lo the T700 engine [NASA-TM-4109] p 496 N89-20409 Computation of flow fields for hypersonic flight at high MELVIN, W. W. [ NASA-CR-180899I p 497 N89-20472 altitudes p 440 A89-33627 Abort landing guidance trajectories in the presence of MARTIN, R. M. MOSTREL, M. M. Acwstic test of a model rotor and tail rotor: Results windshear p 481 A8942725 MENDOZA, J. P. Second order accurate finite difference approximations for the isolated rotors and combined configuration for the transonic small disturbance equation and the full Aerodynamic analysis of three advanced configurations [ NASA-TM-1015501 p 504 N89-20777 potential equation using the TranAir full-potential code p 455 N89-20944 p 444 A89-34740 MARTINEZ CABEZA, JOSE ANTONIO MUDOE. S. K. MENON, SURESH 8-2 - The end of the long road toward a 'stealth Variable structure control laws for aircraft manoeuvres Large-eddy simulations of excitation effects on a VTOL bomber' p 438 A89-35100 p 482 A89-35286 MARVIN, J. 0. upwash fountain p 442 A8944461 MUELLER, B. MERRILL, WALTER C. Turbulence modeling for hypersonic Row Numerical simulation of three-dimensional hypersonic A real-time simulator of a turbofan engine p441 A89-33641 viscous flows p 441 A89-33644 [ NASA-TM-1008691 p 481 N89-20995 MATVEEV. V. N. MUELLER, PAUL J., 111 MESSITER, A. F. Effect of the blade height at the exit of the shrouded Preliminary design of a modular unmanned research Asymptotic methods for internal transonic flows rotor of a radial-flow centripetal microturbineon the turbine vehicle. Volume 1: System design document p 455 N89-20937 efl i c i e n cy p 492 A8944155 [AD-A202765] p 474 N89-20987 METWALLY, 0. M. MAYNE, CHARLES L MUKHOPADHYAY,V. Measurements of a supersonic turbulent vortex Modern multiple-pulse, high field NMR studies of high Active control law synthesis for flexible aircraft density jet fuels p 440 A8943423 p 482 A89-35045 [AD-A203320] p 490 N89-21130 METZGER, 0. E. MULARZ, E. J. MAZUR, VLADISLAV Local heat transfer in internally cooled turbine airfoil Assessment, development. and application of li______l leading edge regions I - Impingement cooling without film combustor aerothermal models p 479 N89-20138 IIWC"CNli$:ning ~Wkes 0 ai:c:z!! acd c=!Gr=! cooiant exiraciion. ii - inipiiiyiiiefii cooling ivith :i!m !.?"RUAr., E. intracloud discharges p 460 A8945158 1. coolant extraction p 494 A89-34932 Euler and Navier-Stokes leeside flows over supersonic MCCABE. DOUGLAS A. MEYER, T. 0. delta wings p 445 A69-34892 Preliminary design of a modular unmanned research MURMAN, EARLL M. vehicle. Volume 1: System design document Fatigue life prediction modeling for turbine hot section materials p 480 N89-20142 An embedded mesh procedure for leading-edge vortex IAD-AZ027651 p 474 N89-20987 flows p 455 N89-20936 MCCAUGHAN, FRANCES ELIZABETH MEYERS, JAMES F. Analysis the dedicated laser velocimeter systems at MURRAY, J. P. An analytical and numerical study of axial flow of NASA - Langley Research Center p 484 A89-33384 A seat-mounted combined harness compressor instability p 478 N89-20131 MIELE. A. [AIAA PAPER 89-09371 p 463 A8945245 MCCAULEY, DONALD E. MURTHY. A. V. Transoniclsupersonic (720 KEAS 1.2 Mach) ejection Abort landing guidance trajectories in the presence of windshear p 481 A89-32725 Performance of the active sidewall boundary-layer demonstration test of an S4S Biofidelity Manikin (BFMI) removal system for the Langley 0.3-meter Transonlc MILES, R. B. p 463 A8945841 Cryogenic Tunnel MCCAULLEY, J. A. Instantaneous profiles and turbulence statistics of supersonic free shear layers by Raman excitation [ NASA-CR-1817931 p 486 N89-21004 Noise and instability waves in supersonic jets in the + MYERS, M. K. laser-induced electronic fluorescence (relief) velocity proximity of flat and cylindrical walls Asymptotic/numerical analysis of supersonic propeller tagging of oxygen p 440 A89-33424 [AIAA PAPER 89.11361 p 503 A89-33766 noise MILLER, A. MCCONNELL, 6.0. R. [AIAA PAPER 89.10781 p 501 A89-33722 Air Force tribology programs p 491 A8943448 Life modeling 01 thermal barrier coatings for aircraft gas turbine engines p 480 N89-20143 MCCONNELL, 0. Multivariable design of a bank-to-turn autopilot for MINECK, RAYMOND E. N Comparison of airfoil results from an adaptive wall test command guidance p 482 A89-35301 section and a porws wall test section NADVORSKII. A. S. MCCONNELLROBERT p 457 N89-20960 A simple one-dimensional model for the effect of air Transoniclsupersonic (720 KEAS 1.2 Mach) ejection MIRANDA, LUIS R. pollution on supersonic combustion p 488 A8944121 demonstration test of an S4S Biofidelity Manikin (BFMI) Transonics and fighter aircraft Challenges and NAGEL, R. T. p 463 A8945841 Opportunities for CFD p 454 N89-20932 Hub to tip variations of counter rotating propeller MCCORMACK. CHRISTOPHER J. MITIUSHKIN, IU. 1. interaction noise Aircraft tracking with dual TACAN Effect of the desgn of a two-row nozzle ring on the [AIAA PAPER 89.11451 p 504 A8933770 [AD-A202647] p 466 N89-20980 efficiency of a turbine stage of medium rotor solidity NAKAO, MASAHIRO MCCORMICK, 0. C. p 477 A8944140 Numerical solutions for the flowfield around a Interaction noise mechanisms for an advanced propeller MODI, V. J. counter-rotating propeller p 445 A89-34887 - Experimental results NASEEY. M. A. Bound vortex boundary layer control with application [AIM PAPER 89-10931 p 502 A8943733 Development and implementation of flight control to V/STOL airplanes p 449 A89-35994 MCCROSKEY, W. J. System for a research drop model p 481 A89-33563 Navier-Stokessimulation of unsteady three-dimensional MOIN, P. NASRY, S. N. blade-vortex interactions p 444 A89-34745 Direct numerical simulation of a three-dimensional Canadair SentinellSea Sentinel rotary wing RPV. IV MCCURDY, DAVID A. turbulent boundary layer p 493 A89-34909 p 467 A8943556 Advanced turboprop aircraft flyover noise annoyance . MOISEEVA. L T. NASTASE, ADRIANA Cornparison of different propeller configurations Adaptive control of the grinding of large gas turbine Some considerations on leading edge vortices on wings [AIM PAPER 89-11281 p 503 A89-33761 blades p 492 A8944144 in supersonic flow p 450 A8946013 MCCUTCHEN, C. W. MOKHTARIAN,F. NATEGHI, FARIBORZ Induced drag and the ideal wake of a lifting wing Bound vortex boundary layer control with application Wind damage to airports - Lessons learned p 446 A89-34898 to V/STOL airplanes p 449 A8945994 p 499 A8944359
8-7 NATUSHKIN, V. F. PERSONAL AUTHOR INDEX
NATUSHKIN, V. F. OSIPOV, V. N. POWELL, KENNETH 0. A mathematical model Of aircraft spin and results Of Assessment of the adequacy of bearing lubrication in An embedded mesh procedure for leadingedge Vortex its comwter integration p 481 A8944130 a gas turbine engine through openings in the rotating flows p 455 N89-20936 NAYFEH,'ALI H. shaft p 492 A89-34154 POWERS, EDWARD Stability of compressible boundary layers OZMEN, F. Multispectral terrain background simulation techniques p 456 N89-20953 Analysis of Doppler radar windshear data for use in airborrre sensor evaluation NEDBAL, 1. [ NASA-CR-1817621 p 464 N69-20111 p 499 A89-33664 Quantitativefractography - Possibilitiesand applications POWERS, JOSEPH M. in aircraft research p 495 A8945074 Attenuation of blast waves using foam and other NELSON, C. P matenals An entrance region friction factor model applied to [ AD-AZO31481 p 505 N69-21632 annular seal analysis - Theoly versus experiment for PALLEK. 0. POZEFSKY, P. J. smooth and honeycomb seals 3-D LDA-measurements in the jet of a bypass-engine Identifyingsonic fatigue prone structures on a hypersonic [ASME PAPER 68-TRIB-411 p 493 A8944796 p 477 A69-33366 Transatmospheric Vehicle (TAV) NELSON, E. PANCZAK, TIMOTHY 0. [AIAA PAPER 89-11031 p 469 A89-33743 Comparison of 30 computation and experiment for Attenuation of blast waves using foam and other PRACHER, JOHN M. non-axisymmetric nozzles matenals Response equivocation analysis for the smart stick [ NASA-CR-1822451 p 452 N89-20921 [AD-A203148] p 505 N89-21632 controller NELSON, P. A. PANTELEEV. 1. M. [ AD-A2031461 p 475 N89-20989 In-flight experiments on the active control Of A combined method for calculating supersonic flow of PRYDZ. R. A. propeller-inducedcabin noise an ideal gas past a wing with a supersonic blunt leading Interior noise in the untreated Gulfstream II PropfanTest [AIM PAPER 89-10471 p 468 A6943706 edge p 448 A69-35430 Assessment (PTA) aircraft NELSON, R. S. PARIKH. PARESH [AIAA PAPER 89-11191 p 469 A89-33754 Fatgue life prediction modeling for turbine hot section Generation of unstructuredgrids and Euler solutions lor PUGH, C. C. materials p 480 N89-20142 complex geometries p 455 N69-20941 Some aspects of the development and operational NEUMANN, KURT NYLE PARZYCH, 0. J. testing of the Spnte system p 467 A89-33557 A dgital rate controller for the control reconfigurable Interaction noise mechanisms for advanced propellers PUGMIRE, RONALD J. combat aircraft designed uslng quantitative feedback - Analflical evaluation Modern multiple-pulse. high field NMR studies of high theory [AIAA PAPER 89-10941 p 502 A69-33734 density jet fuels [AD-A203050] p 484 N89-21001 PATIL, S. R. [AD-A203320] p 490 N89-21130 NEUMANN, RICHARD 0. Development of experimental techniques for helicopter PUSCHNIK, H. Experimental methods for hypersonics- Capabilities and rotor performance studies p 470 A89-35198 Spray formed Waspaloy for disc forgings limitations p 441 A89-33638 PATRICK, H. V. L p 487 A89-33463 NEWMAN. P. A. Hub to tip variations of counter rotating propeller PUSKAS, E. Wall interference assessment and corrections interaction noise The development of a 10,000 Ib capacity ram air p 457 N89-20958 [AIAA PAPER 89-11451 p 504 A8943770 parachute NEWSAM. S. PATRICK, W. P. [AIAA PAPER 89-09041 p 462 A89-35220 Potential applicabons for advanced structural ceramics Near wakes of advanced turbopropellers PUTNAM, TERRILL W. in aero gas turbne engines p 488 A69-33490 [AIAA PAPER 89-10951 p 441 A89-33735 Flight research and testing p 453 N89-20927 NICHOLSON. JEFF PAlTON, R. J. A pronated escape system for fghter aircraft Frequency domain techniques applied lo the p 463 A89-35845 identification of helicopter dynamics p 500 A89-35261 Q NIEMI, EUGENE E., JR. Variable structure control laws for aircraft manoeuvres QIU, ZHENHAN A cnttcal revlew of the state of the art for measurement p 482 A89-35266 Application of harmonic analysis method to research 01 stress in parachute labncs Variable structure model-following control of flight rotor airloads p 467 A89-33139 [AIAA PAPER 89-09251 p 489 A89-35235 dynamics p 482 A89-35300 on QUACKENBUSH. T. R. NISSLEY, 0. M. PAUL, MICHAEL E. Performance optimization for rotors in hover and axial Fatigue life prediction modeling for turbine hot section Preliminary design of a modular unmanned research flight matenals p 480 N89-20142 vehicle. Volume 1: System design document [NASA-CR-177524] p 459 N89-20973 NOBACK. R. [AD-A202765] p 474 N69-20967 Matching Power Spectra Density (PSD)design load PEISEN, DEBORAH [ NLR-MP-87059-UI p 472 N89-20126 Heliport system planning guidelines R NSI MBA. M. [AD-A1990811 p 486 N89-21003 Helicopter rotor wake investigation using a laser Doppler PEPPER, 0. W. RACHNER, M. anemometry technique p 439 A89-33385 Heat transfer in gas turbine engines and The influence of a radial swirl generator on the flow three-dimensionalflows; Proceedings of the Symposium, field from a fuel nozzle model p 490 A8933354 ASME Winter Annual Meeting, Chicago. IL. Nov. 27-Dec. RADESPIEL, R. 0 2, 1988 p 494 A6944926 A cell-vertex multignd method for the Navier-Stokes PERRY, K. S. OBRIEN, J. E. equations Coupled rotor/fuselage dynamic analysis of the AH-1G [ NASA-TM-1015571 p 451 N89-20101 Heat transfer in gas turbine engines and helicopter and correlation with flight vibrations data threedimensbnal flows; Proceedings of the Symposium. RAE, W. J. [ NASA-CR-1817231 p 497 N89-20512 Transmission and reflection on pressure waves by ASME Winter Annual Meeting, Chicago, IL. Nov. 27-Dec. PETERSON, 0. 2,1988 p 494 A89-34926 P. compressor and turbine stages, based on an actuator-disk Experimental investigation of the thermal conductivity model Effects 01 wake passing on stagnation region heat of dispersed ceramic materials p 488 A89-34933 [ AD-AZ035131 p 496 N69-20426 transfer p 494 A89-34928 PHILLIPS, WILLIAM 0. RAGHAVAN, VENKATRAMAN OBRAZTSOV, 1. F. Selection of a frequency sensitive OFT (Quantitative Unsteady force calculations on circular cylinders and Prospects lor the application of holographic Feedback Theory) weighting matrix using the method of elliptical airfoils with circulation control interlerometry to the study of the resonant vibrations of specified outputs [UMAERO-87-37] p 457 N89-20962 complex systems p 495 A6945654 [AD-A202692] p 501 N89-21592 RAHULAN, T. OECHSIE, V. L PICKARD. A. C. Load alleviation on transport aircraft using acceleration High density fuel effects Fatigue testing of gas turbine components feedback p 471 A89-35299 [AD-A202426] p 490 N69-21125 p 485 A89-33804 RAMAN, GANESH OHNSORG, R. W. PICKL, WILLIAM 0. Subharmonic and fundamentalhigh amplitude excitation Fabrication of sintered alpha-Sic turbine engine High performance escape capsules 01 an axisyrnmetric jet Components p 491 A6943621 [AIAA PAPER 69-08781 p 470 A69-35202 [ NASA-TM-1019461 p 452 N89-20920 OHTA, 0. PLENTOVICH, E. 8. RAMASWAMY, M. A. Bound vortex boundary layer control with application Navier-Stokescalculations of transonic flows past open Development 01 experimental techniques for helicopter to V/STOL airplanes p 449 A89-35994 and transitional cavities p 444 A89-34744 rotor performance studies p 470 A69-35198 OINUMA, T. POHL, LETITIA M. RAMOS. J. 1. Preliminary design of a modular unmanned research Bound vortex boundary layer control with application Simultaneous computation 01 jet turbulence and noise vehicle. Volume 1: System desgn document to V/STOL airplanes p 449 A8945994 [AIM PAPER 89-10911 p 491 A89-33731 [ AD-A202765I p 474 N89-20987 OLER. J. W. POLEN, 0. M. RAND. OMRl Model for investigation of helicopter fuselage influence Prediction of parachute collapse due to wake Efficient optimization of integrated rotor flowfields p 445 A8944863 rec 0 n la c t aerodynamic-structuraldesign p 500 A69-34569 on [AIAA PAPER 69-09011 p 447 A89-35218 POON, K. RAPUC. Y. An exmrirnental investiaation of the aerodvnamic loads A comparison of secondary flow in a vane cascade and Experimental wind tunnel study of a military-aircraft air intake Comparison with flight p 448 A89-35381 on cambered plates - a CUN~duct p 446 A89-34934 - IAIAA PAPER 89-09351 D 447 A89-35244 POTOTZKY, ANTHONY S. RASPET, RICHARD OLINGER, JEFF On the relationship between matched filter theory as Attenuation of blast waves using foam and other A pronated escape system for fighter aircraft applied to gust loads and phased design loads analysis materials p 463 A8945645 [ NASA-CR-1618021 P 472 N89-20125 [ AD-AZ031481 p 505 N89-21632 OLIVIER, H. POWELL, J. RATCLIFF, ROBERT R. High enthalpy testing in hypersonic shock tunnels Evolution of a small turbine engine family for unmanned Inverse wing design in transonic flow including viscous p 485 A89-33630 aerial vehicles p 477 A8933570 interaction p 473 N89-20947
8-8 PERSONAL AUTHOR INDEX SHUVEROVA, 1.1.
RAVNITZKY, M. J. RONZIN, V. D. SCHRUBEN, DALE Evolution of the manta-ray parachute Effect of the design of a two-row nozzle ring on the Fuel holdup and component diffusivity in a cooled [AIAA PAPER 89-09061 p 462 A89-35221 efficiency of a turbine stage of medium rotor solidity cylindrical tank p 488 A89-34894 RAY, A. p 477 A89-34140 SCHULTEN, J. B. H. M. Observer design for compensation of network-induced ROSCHER, H.J. Experimental validation of a lifting surface model for rotor delays in integrated communication and control systems 3-D LDA-measurements in the jet of a bypass-engine wake-stator interaction p 500 A89-35044 p 477 A89-33386 [AIM PAPER 89-11251 p 441 A89-33758 ROSEN, BRUCE S. REAZER, JEAN S. SCHUSTER, DAVID M. In-flightlightning characterizationprogram on a CV-580 Method to predict external store carriage loads at Computation of aircraft component flow fields at aircran transonic speeds p 473 N89-20945 transonic Mach numbers using a three-dimensional [ AD-A2039541 p 464 N89-20976 ROSLOV, A. M. Navier-Stokes algorithm p 454 N89-20933 Numerical modeling of transonic flow of a viscous gas SEASHOLTZ. R. 0. REBO, ROBERT KEITH in a plane channel with a sudden expansion A helmet-mounted virtual environment display system Advanced high temperature instrument for hot section p 442 A89-34149 [AD-A203055] p 476 N89-20994 research applications p 479 N89-20137 ROSS, A. JEAN SEEMANN, 0. R. REBSTOCK, RAINER Development and implementation of flight control Complementary minis - Skyeye and Phoenix, an overview Capabilities of wind tunnels wth two-adaptive walk to system for a research drop model p 481 A8933563 of their multi-mission coverage p 467 A8943558 minimize boundary interference in 3-D model testing ROSS, P. T. p 486 N89-20961 SEGAL, H. M. Hgh density fuel effects A microcomputerpollution model for civilian airports and REITER, H. [AD-A202426] p 490 N89-21125 Air Force bases. Model application and background Micro radiography and tomography for high resolution ROTH, G. J. [AD-A1997941 p 499 N89-20557 NDT of advanced materials and microstructural Instantaneous profiles and turbulence statistics of SEIBERT, W. components p 495 4.89-15081 aupe:s=nic !:e% sheer !lye!$ by R8man excitation + Investigation of flow separation in a three-dimensional REJMAN, MICHAEL H. laser-induced electronic fluorescence (relie0 velocity diffuser using a coupled Euler and boundary-layer Some consequences of reduced frame rate for operator tagging of oxygen p 440 A89-33424 method p 446 A89-35172 performance p 465 A8933573 ROZNO. V. 0. SEIDEL, DAVID A. RENIE, J. P. Characteristicsof the formation of benz(a)pyrene in the Geometrical and structural properties of an Aeroelastic Mean and turbulent velocity measurements of combustion chambers of aviation gas turbine engines Research Wing (ARW-2) supersonic mixing layers p 440 A89-33426 p 488 A89-34119 [ NASA-TM-41101 p 451 N89-20099 RESLER. EDWIN L, JR. RUBESIN, MORRIS W. Steady and unsteady transonic small disturbance Propulsion over a wide Mach number range Turbulence and modeling in transonic flow analysis of realistic aircraft configurations [ NASA-CR-182267I p 478 N89-20134 p 456 N89-20951 p 473 N89-20946 REZNIK, V. E. RUDY, D. H. SENDSTAD, 0. An experimental study of the rate characteristicsof brush Patched-gridcomputations of high-speed inlet flows Direct numerical simulation of a three-dimensional seals in comparison with labyrinth seals p 443 A89-34728 turbulent boundary layer p 493 A89-34909 p 492 A89-34136 RUPERT, CARL L. SENGUPTA, GAUTAM Sonic fatigue-resistant damped laminated structures RUNIKOV, A. 0. Prediction of structural-acousticresponse of an aircraft [AlAA PAPER 89-11021 p 489 A8943742 Ceramics in high-temperaturegas turbines (Review) fuselage modeled as a periodic structure RUTLEDGE, C. K. p 488 A89-34080 [AIAA PAPER 89-10451 p 468 A89-33705 Prediction of full system helicopter noise for a MDHC RICE, EDWARD J. SERRANO, ARTURO V. 5M)E helicopter using the Rotonet program In-flight lightning characterization program on a CV-580 Subharmonic and fundamental high amplitude excitation [AIAA PAPER 89-11351 p 500 A89-33765 aircraft of an axisymmelric jet RYERSON, D. E. [AD-A203954] p 464 N89-20976 [NASA-TM-1019461 p452 N89-2-3920 Small parachute flight data acquisition system SETTLES, 0. S. RIEDELBAUCH, S. [AIAA PAPER 89-09241 p 483 A89-35234 Measurements of a supersonic turbulent vortex Numerical simulation of three-dimensional hypersonic p 440 A89-33423 viscous flows p441 A8943644 SEXTON, GEORGE A. RIETHMULLER, M. L S Cockpit-crew systems design and integration Particle image displacementvelocimetry applied in high p 476 A8944446 sped flows p 490 A89-33388 SADECK, JAMES E. SHAGAEV, A. A. RIKS, E. A control canopy release method for improved opening Potential models of transonic flows Bulging cracks in pressurized fuselages: A numerical of clustered parachutes p 449 A8945495 [A!.AA PAPER R9-0892! p 461 A89-35210 study SH.ARM&Ni JOHN R. [NLR-MP-87058-U] p 497 N89-20519 SADLER, S. 0. Data links for video and IR surveillance RILEY, MICHAEL F. Coupled rotor/fuselaga dynamic analysis of the AH-!G p 455 A89-33567 Integrated aerodynamicldynamic optimization of helicopter and correlation with flight vibrations data SHAW, L. L. helicopter rotor blades [ NASA-CR-1817231 p 497 N89-20512 Twin-jet screech suppression [NASA-TM-101 5531 p 473 N89-20982 SALAS. MANUEL D. [AlAA PAPER 89-11401 p 504 A89-33768 Generation of unstructured grids and Euler solutions for RITCHIE. MALCOLM L SHAW, S. W. K. complex geometries p 455 N89-20941 PM superalloy turbine blades p 487 A89-33454 General aviation p 437 A8934448 SALIVAR, G. C. RIZK, MAGDI H. SHEARIN. JOHN 0. The effect of stress ratio on the near-thresholdfatigue Airfoil profile drag increase due to acoustic excitation Large-eddy simulations of excitation effects on a VTOL crack growth behavior of Ti-8AI-1Mo-1V at elevated upwash fountain p 442 A89-34461 [AIM PAPER 89-10691 p 501 A89-33715 temperature p 489 A8945722 SHEENA, 2. RIZK, N. K. SANDFORD, MAYNARD C. High density fuel effects Structural optimization for aermlastic control Geometrical and structural properties of an Aeroelastic effectiveness p 470 A89-34899 [AD-A202426] p 490 N89-21125 Research Wing (ARW-2) SHI, YlJlAN RODIER, ROBERT W. [ NASA-TM-41101 p 451 N89-20099 A digital simulation technique for Dryden atmospheric Personnel parachute agelsewice life criteria SANZ, JOSE M. turbulence model p 439 A89-33142 [AlAA PAPER 89-09161 p 462 A8945228 A compendium of controlled diffusion blades generated SHIAU, N.-H. ROGER, MICHEL by an automated inverse design procedure A self-adaptive computational method for transonic Prediction of potential noise interactions in axial-flow [ NASA-TM-1019681 p 481 N89-20996 turbulent flow past a real projectile p 443 A8934730 machines - Application to the helicopter fenestron SAUERLAND, K.-H. SHIH, S. p 504 A8935385 3-D LDA-measurements in the jet of a bypass-engine Direct numerical simulation of a three-dimensional Predictin of wake-interaction noise in axial-flow p 477 A89-33386 turbulent boundary layer p 493 A89-34909 machines - Application to helicopter fenestron SCHAEFER, HANS J. SHIRAZI, SIAMACK A. p 504 A89-35388 Measurements of mean-flow and turbulence Evaluation of algebraic turbulence models for PNS ROGERS, J. P. characteristics in a turbojet exhaust using a laser predictions of supersonic flow past a sphere-cone p 439 A89-33410 h~pledrotor/fuselage dynamic analysis of the AH-IG velocimeter p 445 A89-34807 helicopter and correlation with flight vibrations data SCHIJVE, J. SHIVELY, ROBERT Current status of flight simulation fatigue crack growth [ NASA-CR-1817231 p 497 N89-20512 AH-1S communication switch integration program ROJAS, R. 0. concepts [ NASA-TM-1010531 p 466 N89-20978 [ NLR-MP-88001-Ul p 497 N89-20521 Improved computer simulation of the TCAS 3 circular SHREWSBURY, GEORGE D. array mounted on an aircran SCHILLING, LAWRENCE J. Computation of aircraft component flow fields at Simulation at Dryden Flight Research Facility from 1957 [NASA-CR-184907] p 496 N89-20363 transonic Mach numbers using a three-dimensional ROLLBUHLER, R. JAMES to 1982 Navier-Stokes algorithm p 454 N89-20933 [NASA-TM-101695] p 474 N89-20983 Gas turbine alternative fuels combustion SHUCHINOV. V. M. characteristics SCHMUECKER, A. Effect of the asymmetry of boundary conditions on [ NASA-TM-101470] p 499 N89-21417 Vortex breakdown and its control on delta wings boundary layer flow near a cone a1 angle of attack ROMASHKOVA, D. D. p 449 A89-35999 p 448 A8935433 A simple one-dimensional model for the effect of air SCHOEN. JAMES SHUMSKII, 0. M. pollution on supersonic combustion p 488 A89-34121 Advanced Recovery Sequencer (ARS) Analysis of separated flow past a thin profile in the case RONOUILLO, KENNETH L p 471 A89-35843 of translational oscillations p 442 A8944151 Parachute drawing standards currently in use at Sandia SCHRA, L. SHUVEROVA, T. 1. National Labwatories Quench sensitivity of airframe aluminum alloys Optimal profile selection in the design of a subsonic [AIM PAPER 89-09271 p 495 A8945237 [NLR-MP-88003-U] p 489 N89-20231 turbine cascade p 442 A8944152
B-9 SHVETS. A. I. PERSONAL AUTHOR INDEX
SHVETS, A. 1. SOISTMANN, DAVID L. STRUNKIN, V. A. Supersonic flow past caret wings and elements of Some low-speed flutter characteristics of simple Some aspects of the numerical modeling of the star-shaped bodies at angles of attack and bank low-aspect-ratio delta wing models nonstationaw heat conductivitv of aas turbine p 449 A8945481 [ NASA-TM-1015471 p 450 N89-20094 components. . p 477- A89-34139 SHYY. W. SOKOLOWSKI, DANIEL E. SUDAREV. A. V. Applications of a generalized pressure correction Toward improved durability in advanced aircraft engine Ceramics in high-temperaturegas turbines (Review) algorithm for flows in complicated geometries hot sections p 488 A89-34080 D 493 A89-34738 [NASA-TM-40871 p 479 N89-20135 SVINUKHOV, V. P. SIBGATULLIN, E. S. NASA HOST prolect overview p 479 N89-20136 Some characteristics of the formation of contaminants The load-bearing capacity of closed-profile oblong Views on the impact of HOST p 480 N89-20144 during the combustion of hydrocarbon fuels in the cornbustion chambers of gas turbine engines cylindrical shells made of a metallpolymer composite SOMOV, E. 1. laminate p 492 A8944128 p 488 A89-34120 Stability analysis of the multiple discrete stabilization SWANSON, 0. A. SICKLES, W. L. system of an elastic flight vehicle p 500 A8944132 Two-measured variable method for wall interference Fatigue life prediction modeling for turbine hot section assessmentlconection p 457 N89-20959 SPAIN, CHARLES V. matenals p 480 N89-20142 Geometrical and structural properties of an Aeroelastic SIEGL. J. SWEETMAN, BILL Research Wing (ARW-2) Quantitative fractography - Possibilitiesand applications Life with the older aircraft p 438 A89-35125 in aircraft research p 495 A8945074 [NASA-TM-41101 p 451 NE9 20099 SZOBOSZLAY, ZOLTAN SILCOX. R. J. SPENCE. P. L. AH-1S communication switch integration program Propeller modelling effects on interior noise in cylindrical Near-field noise of a pusher propeller [ NASA-TM-I01 0531 p 466 N89-20978 [AIAA PAPER 89-10961 p 502 A8943736 cavities with application to active control [AIAA PAPER 89-11231 p 469 A89-33757 SPENNY, CURTIS H. SILVA, WALTER A. Pilot election from a pronated flying position T [AIAA PAPER 89-08851 p 471 A8945205 Aeroelastic deformation effects on the stopped-rotor TADGHIGHI, H. dynamics of an X-wing aircraft p 482 A8944897 SPINA, E. F. Importance of engine as a source of helicopter external SIMCOX, L. N. A comparison of the turbulence structure of subsonic noise The application of software fault tolerance to air traffic and supersonic boundary layers p 440 A8943425 [AIAA PAPER 89-11471 p 470 A89-33771 control Study contract overview SRINIVASAN, G. R. [ BR1085671 p 465 N89-20114 TADGHIGHI. HORMOZ Navier-Stokessimulation of unsteady three-dimensional An analytical model for the prediction of MRITR SIMONDS, M. blade-vortex interactions p 444 A8944745 interaction noise A comparison of secondary flow in a vane cascade and SRINIVASAN, S. a CUNed duct p 446 A8944934 [AIAA PAPER 89-11301 p 503 A89-33762 Navier-Stokescalculations of transonic flows past open TAFTI. D. K. SIMONEAU, R. J. and transitional cavities p 444 A8944744 Review and assessment of the database and numerical Prediction of heat transfer characteristics of discrete STATMAN, J. I. modeling for turbine heat transfer p 479 N89-20139 hole film cooling - One row of injection into a turbulent High dynamic GPS tracking SIMONICH, J. C. boundary layer p 494 A89-34931 [ NASA-CR-I848681 p 465 N89-20113 Interaction noise mechanismsfor an advanced propeller TAKAHASHI, F. - Experimental results STECCO, S. S. Aerodynamics of two-dimensional slotted bluff bodies [AIM PAPER 89-10931 p 502 A89-33733 Inviscid prediction of transonic flows in turbomachines [ DE89-0072881 p 452 N89-20105 SIMPSON, M. A. using a Runge-Kutta integration scheme TAKAHASHI, MARC D. Full-scale demonstrationtests of cabin noise reduction p 444 A89-34736 Active control helicopter aeromechanical and using active vibration control A linear computer code to determine aeroelastic stability aeroelastic instabilities p 483 N89-20149 [AIAA PAPER 89-10741 p 468 A89-33719 in airfoil cascades at unsteady flow conditions TAKALLU, M. A. SIMPSON, MYLES A. p 444 A89-34746 Near-field noise of a pusher propeller Cabin nase control ground tesls for UHB aircraft STECK. JAMES EDWARD [AIAA PAPER 89-1096) p 502 A8943736 [AIM PAPER 89-1 121I p 469 A8943755 Finite element modelling of sheared flow effects on the TAM, C. K. W. SISTO, F. radiation charactenstics of acoustic sources in a circular Noise and instability waves in supersonic jets in the Computational study of the effectof cascade parameters duct proximity of flat and cylindrical walls on stall propagaton in axial compressors [AIM PAPER 89 10851 p 502 A89 33726 [AIM PAPER 89-11361 p 503 A89-33766 P 444 A8944737 STEEVES, EARL C. TAM, CHRISTOPHER K. W. Forward flight effects on broadband shock aksociated SMEDSVIG, ElNAR Analvsis of decelerators in motion usina comDutational ~. noise of supersonic jets Incorporatingfive nations' operational requirements into fluid dynamics [AIAA PAPER 89-10881 p 502 A8943729 a single aircraft The F-16 multinational fighter program [AIAA PAPER 89-0931 I p 447 A8935241 viewed from the operational side STEPHENS, T. M. TANG, F. C. Transonic buffetof a supercriticalairfoil with trailing-edge LAD-AZ025521 p 474 N89-20986 Linescan 2000 - Tomorrow's sensor today p 446 A89-34893 SMIRNOV, A. F. p 475 A89-33574 flap Structural mechanics: Contemporary state and STETSON, K. F. An experimental study of transonic buffet of a supercritical airfoil with trailing edge flap prospects for development (selected portions) Hypersonic boundary-layer transition [AD-A2031891 p 458 N89-20968 [ AD-AI 987661 p 497 N89-20498 p 441 A89-33646 SMIRNOV, V. A. STOCK, H. W. TATE, RALPH E. Sonic fatigue-resistant damped laminated structures Prospects for the application of holographic Investigation of flow separation in a three-dimensional [AlAA PAPER 89-11021 p 469 A89-33742 interferometry to the study of the resonant vibrations of diffuser using a coupled Euler and boundary-layer complex systems p 495 A89-35654 method p 446 A89-35172 TATUM. K. E. SMITH, C. W. STOCKS, A. J. Navier-Stokes calculations of scramjet-afterbody The application of CFD for military aircraft deslgn at Civilian RPVS - Eye in the sky or pie in the sky? flowfields p 443 A89-34732 transonic speeds p 454 N89-20930 p 437 A89-33560 TAYLOR, D. R. SMITH, FRANCIS R. STOKES, ALAN F. Design aspects of a naval RPV recovery system Thin-layer Navier-Stokes solutions for a cranked delta Aviation displays p 476 A89-34443 p 484 A89-33568 wing STONE, P. L TEN EYCK, M. 0. [AD-A203292] p 459 N89-20970 Experimental examination Of the aerothermal Fabrication of sintered alpha-Sic turbine engine SMITH, JOHN P. performanceof theT-lOtestcellatNAS(Naval Air Station), components p 491 A89-33621 Simulation at Dryden Flight Research Facility from 1957 Cubi Point TENHAVE, J. M. to 1982 [AD-A203887] p 487 N89-21005 The application of trajectory prediction algorithms for [ NASA-TM-101695l p 474 N89-20983 STOTHERS, I. M. planning purposes in the Netherlands Air Traffic Control SMITH, LEROY K. In-flight experiments on the active control of (ATC) system Macrocrack-multiple defect interaction considering propeller-inducedcabin noise [NLR-MP-87031-Ul p 465 N89-20115 elastic. plastic and viscoplastic effects [AlAA PAPER 89-10471 p 468 A89-33706 TEREGULOV, 1.0. [AD-A2031861 p 498 N89-21282 STRAZISAR, A. J. The load-bearing capacity of closed-profile oblong SMITH, M. J. An LDA (Laser-Doppler Anemometry) investigation of cylindrical shells made of a metallpolymer composite Importance of engine as a source of helicopter external three-dimensional normal shock wave boundary-layer laminate p 492 A8944128 noise interactions p 456 N89-20956 TERRAZZONI, C. STREElT, CRAIG L. [AIAA PAPER 89-11471 p 470 A89-33771 Civil-transport aircraft at Aerospatiale Updated users' guide for TAWFIVE with multigrid SMITH, MARILYN J. p 438 A8945378 [ NASA-TM-41 091 P 496 N89-20409 Computation of aircraft component flow fields at STRICKLAND, JAMES H. THANGAM. S. transonic Mach numbers using a three-dimensional A preliminary characterization of parachute wake Computationalstudy of the effect of cascade parameters Navier-Stokesalgorithm p 454 N89-20933 recontact on stall propagation in axial compressors p 444 A8944737 SMITH, R. W. [AIAA PAPER 89-08971 P 447 A89-35214 A comparison of the turbulence structure of subsonic An approximate method for calculating aircraft THART, W. 0. J. and supersonic boundary layers p 440 A89-33425 downwash on parachute trajectories Quench sensitivity of airframe aluminum alloys SMITS. A. J. [AIAA PAPER 89-08991 P 447 A89-35216 [NLR-MP-88003-U1 p 489 N89-20231 A comparison of the turbulence structure of subsonic STROCK, THOMAS W. THOMAS, J. L. and supersonic boundary layers p 440 A89-33425 Hot gas ingestion testing of an advanced STOVL Patched-grid computations of high-speed inlet flows SNESAREV, S. L. concept in the NASA Lewis 9- by 15-foot Low Speed Wind p 443 A8944728 Natural vibrations of cylindrical shells with a rectangular Tunnel with flow visualization Euler and Navier-Stokes leeside flows over supersonic cutout p 492 A8944126 [AlAA PAPER 88.30251 P 439 A89-33249 delta wings p 445 A89-34892
B-10 PERSONAL AUTHOR INDEX VAMAUCHI, GLORIA K.
THOMPSON, H. A. VISSCHER, H. WEIR, D. S. Implementation of a transputer-based flight controller The application of trajectory prediction algorithms lor Prediction of full system helicopter noise for a MDHC p 482 A8945302 planning purposes in the Netherlands Air Traffic Control 500E helicopter using the Rotonet program THOMPSON, R. L (ATC) system [AIAA PAPER 89-11351 p 500 A89-33765 Structural analysis methods development for turbine hot [NLR-MP-87031-U] p 465 N89-20115 WELLS, VALANA L. section components p 479 N89-20140 VIVIAND, H. Integrating the acoustic analogy for supersontc rotating TIKHONOV. N. T. Computational methods for hypersonic flows - Special surfaces Effect of the blade height at the exit of the shrouded techniques and real gas effects p 441 A89-33640 [AIAA PAPER 89-11331 p 503 A89-33763 roto( of a radial-flow centripetal microturbine on the turbine VOEVODENKO, N. V. WETZEL, W. A combined method for calculating supersonic flow of efficiency p 492 A8944155 Numerical simulation of three-dimensional hypersonic an ideal gas past a wing with a supersonic blunt leading TILLEMA. H. F. viscous flows p 441 A89-33644 Model size requirements for finite element prediction edge p 446 A89-35430 VOGEL, GERARD N. WICKENS, CHRISTOPHER D. of low-lrequency cabin noise and vibration Icing considerations for HALE (High Altitude, Long Aviation displays p 476 A89-34443 [AIM PAPER 89-10761 p 469 A8943721 Endurance) aircraft WIENER, EARL L. TIMOFEEV, 0. A. [ AD-A202584] p 464 N89-20975 Cockpit automation p 460 A8944444 Numerical modeling of transonic flow 01 a viscous gas VON MEERWALL ERNST WIESEMAN, CAROL D. in a plane channel with a sudden expansion Fuel holdup and component diffusivity in a cooled Aeroelastic modeling lor the FIT team FIA-18 p 442 A8944149 cylindrical tank p 488 A89-34894 simulation TINOCO, E. N. VOSKES, A. [NASA-TM-101569] p 475 N89-20991 Transonic CFD applications at Boeing The data acquisition system lor the Fokker 100 test WIESEMAN, CAROL DANIELLE p 453 N89-20929 aircraft Methodologyfor using steady expertmental aerodynamic TINSON. !. D. :?!LR-M?-9704?-Uj p 476 NA9-20!?0 data to improve steady and unsteady aerodvnamic Civilian RPVs - Eye in the sky or pie in the sky? analysis p 459 N89-20972 p 437 A89-33560 WILLIAMS, F. TONGUE, BENSON H. W Analysis 01 Doppler radar windshear data Nonlinear rotorcraft analysis-experimental and [NASA-CR-181762] p 464 N89-20111 analytical WACHSPRESS. D. A. WILLIAMS, FORMAN A. [AD-A203967] p 475 N89-20990 Performance optimization for rotors in hover and axial Fuels combustion research TRACY, M. B. flight [AD-A204161] p 490 N89-21071 Near-fieldnoise 01 a pusher propeller [ NASA-CR-1775241 p 459 N89-20973 [AIAA PAPER 8S-lOSSl p 502 A89-33736 WAGNER, CHARLES A. WILLIS. R. TRUMAN, C. RANDALL Simulation at Dryden Flight Research Facility from 1957 Integrated modular RPV ground station with reference Evaluation of algebraic turbulence models lor PNS to 1982 to the 'Raven' project p 485 A89-33575 predictions of supersonic flow past a sphere-cone [ NASA-TM-I01 6951 p 474 N89-20983 WOHLERS, RONALD p 445 A89-34807 WAGNER, ELAINE ANN Multispectral terrain background simulation techniques TSIBIZOV. V. 1. On-board automatic aid and advisory for pilots of for use in airborne sensor evaluation An experimentalstudy of the rate characteristics of brush control-impaired aircraft p 483 N89-20150 p 499 A89-33664 seals in comparison with labyrinth seals WALKER, G. J. WOLF, D. F. p 492 A89-34136 Transitional flow on axial turbomachine blading A coupling apparent mass lor parachute inflation TU, XING p 445 A89-34811 equations The correlation between Reynolds stress and turbulent WALKO, LAWRENCE C. [AIAA PAPER 89.0933) p 447 A8945243 kinetic energy in the near wake of a symmetric airfoil In-flightlightning characterization program on a CV-580 WOLF, STEPHEN W. D. p 448 A8945393 aircraft Test techniques: A survey paper on cryogenic tunnels, TUCK, E. 0. [AD-A203954] p 464 N89-20976 adaptive wall test sections. and magnetic suspension and Thin aerofoils with high-incidence flaps or blunt trailino WALSH, JOANNE L. balance systems p 486 N89-20955 edges p 445 Integrated aerodynamicldynamic optimization of WOODHEAD, 1. A. TURKEL, ELI helicopter rotor blades Load alleviation on transport aircraft using acceleration The 3-D Euler and Navier-Stokescalculations for aircraft [NASA-TM-101553] p 473 N89-20982 feedback p 471 A89-35299 components p 498 N89-20950 WALTERS, R. W. WOODWARD, RICHARD P. TURNBULL A. Patched-grid computations of high-speed inlet flows Unsteady blade pressure measurements on a model The development of a vreliminaw sizina method for p 443 A89-34728 counterrotation propeller WALTON, E: [?!hS+?L"? 02002) 7 504 Nn9-20779 Electromagnetic properties of ice coated surfaces WU. KUENCHUAN Abort lanaing guidance trajectories in the presence oi NASA-CR-1847801 p 455 N89-20355 i A numerical investigation of steady transonic cascade windshear p 481 A89-32725 WALTON, J. flow in turbomachinery p 448 A89-35417 High speed balancing applied to the T700 engine INASA-CR-1808991 p 497 N89-20472 wu, S.C. U WANG, GONGHAO Deriving a geocentric reference frame lor satellite Design of an airborne optic fiber data bus system positioning and navigation p 466 N89-20330 UNAL, AYNUR p 475 A8943148 WUEST. MICHAEL J. Threedimensional singular points in aerodynamics WANG, N. Aerial delivery of personnel in ground proximity [ NASA-TM-1000451 p457 N89-20964 Electromagnetic properties of ice coated surfaces [AlAA PAPER 89-08871 p 461 A8945207 UNRUH, J. F. [NASA-CR-184780] p 495 N89-20355 WUESTER, ERWIN A. Installation effects on propeller wakelvortex induced WANG, S. Investigation of the service and age lives 01 US. Army
structure-borne noise transmission~~ Quanbtatwe design lor systems with uncertainty and personnel parachutes [AIAA PAPER 89-10721 p 468 A89-33717 control failures p 500 A89-35283 LAlAA PAPER 89-09151 p 462 A89-35227 UWINS. S. E. WANG, T. Personnel parachute agelservice life criteria Low cost avionic system for UMA p 475 A89-33571 Abort landing guidance trajectories in the presence 01 [AIAA PAPER 89-09161 p 462 A89-35228 windshear p 481 A8942725 WURZEL, D. WANHILL, R. J. H. Fast, in-situ repair of aircraft panel components v Environment-assisted aerospace fatigue problems in p 438 A89-34896 VADYAK, JOSEPH The Netherlands WYDEVEN, R. Computation of aircraft component flow fields at [NLR-MP-88004-U1 p 439 N89-20087 Asymptoticlnumerical analysis 01 supersonic propeller transonic Mach numbers using a three-dimensional Current status of flight simulation fatigue crack growth noise Navier-Stokes algorithm p 454 N89-20933 concepts [AIAA PAPER 89-10781 p 501 A8943722 VAICAITIS, RIMAS [NLR-MP-88001-U] p 497 N89-20521 Sonic fatigue and nonlinear response of stiffened WASIELEWSKI, G. E. panels Titanium PM attributes and potential lor aircraft engine X applications p 487 A89-33465 [AIM PAPER 89-llOl] p 492 A89-33741 XIAO, YELUN VANLEER, BRAM WAYE, DONALD E. A digital simulation technique for Dryden atmospheric Euler solvers for transonic applications The effects 01 unsteady aerodynamics on single and turbulence model p 439 A89-33142 p 454 N89-20935 clustered parachute system [AIAA PAPER 89-09341 p 448 A8945250 XUE, ZHENGZHONG VANLEEUWEN, S. STORM Application of harmonic analysis method to research The data acquisition system for the Fokker 100 test WEATHERILL, WARREN H. on rotor airloads p 467 A8943139 aircraft Development and application of a program to calculate [ NLR-MP-87047-UI p 476 N89-20130 transonic flow around an oscillatingthree-dimensional wing VASIN. A. D. using finite difference procedures Y Thin axisymmetric caverns in supersonic flow [NASA-CR-181744] p 450 N89-20093 p 449 A89-35435 WEDAN, BRUCE W. YAMAMOTO, YUZO VATSA, VEER N. The 3-D Euler and Navier-Stokescalculations for aircraft Aeroelastic divergence 01 front-free-aft-fixedelastic strip The 3-D Euler and Navier-Stokescalculations for aircraft components p 498 N89-20950 parallel to uniform flow p 495 A8935097 components p 498 N89-20950 WEINBERG, MICHAEL YAMAUCHI, GLORIA K. VIEGAS, JOHN R. Multispectral terrain background simulation techniques Hub and blade structural loads measurements of an Turbulence and modeling in transonic flow for use in airborne sensor evaluation SA34912 helicopter p 456 N89-20951 p 499 A89-33664 [ NASA-TM-101040] p 472 N89-20124
B-11 YAVUZ, 1. PERSONAL AUTHOR INDEX
YAVUZ, T. Determining and accounting for a parachute virtual mass p 460 A89-34889 YAVUZKURT, S. Prediction of heat transfer characteristics of discrete hole film cooling - One row of injection into a turbulent boundary layer p 494 A89-34931 YEE, H. C. High-resolution shock-capturing schemes for inviscid and viscous hypersonic flows p 443 A89-34646 YEH. DAVID T. Numerical simulation of the flow field over delta wings with leading edge blowing p 453 N89-20924 YEW, M. K. Variable structure model-following control of flight dynamics p 482 A89-35300 YOKOYIZO, T. Bound vortex boundary layer control with application to V/STOL airplanes p 449 A89-35994 YOUNG. C. 0. Effect of jet grid turbulence on turbulent boundary layer heat transfer p 494 A89-34930 YOUNG, P. Frequency domain techniques applied to the identification 01 helicopter dynamics p 500 A89-35261 YU, BAIRONG The computer controlled system for multi-drone performing formation flight in a same aerial zone p 481 A89-33566 VUE, A. Design of robust multivariable helicopter control laws for handling qualities enhancement p 482 A89-35297
UGUZOV, 1. S. Noise levels of a combined bypass-propfan engine In the far mnic field p 478 A89-34150 ULIK, RICHARD A. Rotordynamic analysis of a beanng tester p 498 N89-21759 ZALLEN. DENNIS Y. Fire extinguishing agents for oxygen-enriched atmospheres p 487 A89-32948 ZANDBERGEN, T. Experimental investigation of rotor wakelstator interaction noise generation by acoustic mode measurements [AlAA PAPER 89-11261 p 503 A89-33759 ZEILER. THOMAS A. On the relationship between matched tiller theory as applied to gust loads and phased design loads analysis [NASA-CR-181802] p 472 N89-20125 Aeroelastic modeling for the FIT team FIA-18 simulation [NASA-TM-1015691 p 475 N89-20991 ZELL, PETER T. Performance and test section flow characteristicsof the National Full-ScaleAerodynamics Complex 40- by 80-foot wind tunnel [ NASA-TM-1010651 p438 N89-20086 ZHAO, ZHENYAN A digital simulation technique for Dryden atmospheric turbulence model p 439 A89-33142 ZHU, DEPEI The reliability analysis of aircraft structures p 467 A89-33146 znu, TIANYU A new method for the thermodynamic calculation of combustion chambers p 478 A89-34409 ZIMYERMAN, ERIC 8. Single and multi-elementairfoils in an isotropic turbulent wter flow p 439 A89-33383 ZINOBER, A. S. I. Variable structure model-following control of flight dynamics p 482 A89-35300 NIAGINTSEV, V. A. Ensuring the quality of the covering surface in the case of riveted joints with high radial interference p 492 A89-34159
8-12 CORPORATE SOURCE INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
vpical Corporate Source A wind tunnel and computer investigation of the low B Index Listing speed aerodynamic characteristics of the prone escape system (PRESS) Battelle Columbus Labs.. OH. [AD-A202768] p 475 N89-20988 Development of a rotary value for pulse combustion Response equivocation analysis for the smart stick applications controller [ PB89-131114] p496 N89-20468 CORPORATE SOURCE [ AD-AZ031461 p 475 N89-20969 Boelng Advanced Systems Co., Seattle, WA. Real-time display of time dependent data using a Additional development of the XTRAN3S computer head-mounteddisplay program [AD-AZJ~O~Ij p 476 iis3-29993 [NASA-CR-l817431 p 452 N89-20922 Commercial Alrplane Co.. WA. A helmet-mounted virtual environment display system Boelng Seattle, FederalI Admlnlstratlon, Atlsntlc Clty, N.J. Development and application of a program to calculate [ AD-A203055I p 476 N69-20994 Hardware fault insertion and instrumentation system transonic flow around an oscillatingthree-dimensional wing Flight controller design with nonlinear aerodynamics. using finite difference procedures large parameter uncertainty and pilot compensation [NASA-CR-182746] 758N89,10526 [NASA-CR-161 7441 p 450 N89-20093 [ AD-A202727I p 484 N89-21000 Transonic CFD applications at Boeing A digital rate controller for the control reconfigurable p 453 N89-20929 , combat airwaft deslgned using quantitative feedback theory [AD-A203050] p464 N89-21001 C Development of a shock capturing code for use as a tool in designing high-work low aspect ratio turbines Calllornla Unlv., Davls. [AD-A202706] p 496 N89-21246 Vector potential methods p 455 N89-20939 Application of the boundary element method to fatigue Callfornla Unlv.. Loa Angdea. crack growth analysis Active control helicopter aeromechanical and [AD-A202565] p 498 N89-21270 aeroelastic instabilities p 483 N69-20149 Transverse jets in compressible crossflows Macrocrack-multiple defect interaction considering p 452 N69-20923 elastic. plastic and viscoplastic effects Listings in this index are arranged alphabetically [AD-A2031861 p 498 N89-21282 Hypersonic drone design: A multidisciplinary experience by corporate source The title of the document is Selection of a frequency sensitive OFT (Quantitative [NASA-CR-184740] p 473 N89-20981 used to provide a brief description of the subject Feedback Theory) weighting matrix using the method of specified outputs Calspan Corp., Buffalo, NY. matter The page number and the accession [AD-A202692] p 501 N89-21592 Transmission and reflection on pressure waves by compressor and turbine stages. based on an actuator-disk number are included in each entry to assist the Air Force Occupatlonal and Environmental Health Lab., model user in locating the abstract in the abstract sec- Brooks AFB, TX. [ AD-A203513 1 p496 N89-20426 tion Ifapplicable. a report number is also included Contaminationof the exterior of a C-130E aircraft used for aerial spray, 907 TAG, Rickenbacker ANGB, OH Calapan Fleld Services, Inc.. Arnold AFS, TN. as an aid in identifying !he document [AD-A202430] p 474 N89-20984 Two-measured variable method for wall interference assessmentlcorrection p 457 N89-20959 A!r FQIW Symterns Command. Wright-Patterson AFB, on. iiii-es:iga:ion c! !he des!e!opmon! of laminar A Structural mechanics: Contemporary State and boundavlayer instabilities along a cooled-wall cone in prospects for development (selected portions) hypersonic flows U [ AD-A198766) p 497 N89-20498 [AD-A202587] p458 N89-20966 AeroChem Research Labs., Inc., Prlnceton, NJ. Air Line Pilot. Auoclatlon, International, Waahlngton, Carnaglo-Mellon Unlv., Pittsburgh, PA. Sirnultanews computation of jet turbulence and noise Simultaneous computation of jet turbulence and noise [AIAA PAPER 89-1091 1 p 491 A89-33731 Dc. Abort landing guidance trajectories in the presence of [AIM PAPER 89-10911 p 491 A89.33731 Aeronautical Research inst of Swaden.Stockhdm. windshear p 481 A89-32725 Contlnuum Dynamlca, Inc., Prlnceton. NJ. Estimation of the Equivalent Initial Flow Size (EIFS) Alr War Coll., Maxwell AFB. AI- Performance optimization for rotors in hover and axial dislribution and prediction of failure probabilities for Incorporatingfive nations' operational requirements into flight different parameter variations a single aircralt The F-16 multinationel fighter program [ NASA-CR-1775241 p 459 N89-20973 [ FFA-TN-1987-351 p 498 N89-20525 viewed horn the operational side Cornell Unlv., Itham, NY. Alr Fone Armament Lab., Eglin AFB, FL [AD-A202552] p 474 "(89.20986 An analytical and numerical study of axial flow A study of transonic drag reduction of a blunt cylinder Army Avla.vl.tlonEnglwrlng Flight Actlvlty, Edwards compressor instability p 478 N89-20131 by a cylinder probe AFB, CA. Propulsion over a wide Mach number range [AD-A202557] p 458 N89-20965 Aimorthiness and flight characteristics evaluation of an [NASA-CR-1822671 p 478 N89-20134 Alr FomFlbht DyMmks Lab., Wrlght-Patt- AFB, improved engine air filtration system on the UH-1H on. helicopter In-flight lightning characterization program on a CV-580 [AD-A203446] p480 N89-20145 D aircraft Army Avlatlon Research and Development Commend, [AD-A203954] p 464 N89-20976 Moffett Fldd, CA. Deholt Dbwl Allison, IndlaMpollS, IN. Alr Force Inrt. of Tech., Wrlght-Patterson AFB, OH. Navier-Stokessimulation of unsteady three-dimensional High density fuel effects Effect of riblets upon flow separation in a subsonic blade-vortex interactions p 444 A89-34745 [AD-A202426] p 490 N89-21125 diffuser Army Avlatlon Systems Command, Cleveland, OH. Douglas Aircraft Co., Inc., Long Beach, CA. High balancing applied to the T700 engine [AD-A203178] p458 N89-20967 speed Cabin noise control ground tests for UHB aircraft [ NASA-CR-1808991 p 497 N89-20472 Numerical sirnulation of flow over iced airfoils [AIAA PAPER 89-1121 I p 469 A89-33755 Army Avlatlon Syrtems Command, Salnt Louls, MO. [AD-A203291] p 456 N89-20969 Draper (Charles Stark) Lab., Inc., Cambrldge, MA. Thin-layer Navier-Stokes solutions for a cranked delta Three-dimensional singular points in aerodynamics [NASA-TM-100045] p457 N89-20964 Reliability and performance evaluation of systems wing containing embedded rule-based expert systems IAD-A203292] p 459 N89-20970 Army Construction Englneerlng Research Lab., Champalgn, [NASA-CR-181 7691 p500 N89-20683 Two-dimensionalNavier-Stokes solution of the flow over IL Attenuation of blast waves using foam and other a thick supercritical airfoil with strong shock-induced materials separation [AD-A203148] p 505 N89-21632 F [AD-A203331] p 459 N89-20971 Arnold Englneerlng Development Center, Arnold Alr Aircraft tracking with dual TACAN Force Station, TN. Federal Avlatlon Admlnlatratlon, Washlngton, Dc. IAD-AZ026471 p 466 N89-20960 Investigation of the development of laminar A microcomputerpollution model for civilian airports and Performance analysis of the fiber distributed data boundary-layer instabilities along a cooled-wall cone in Air Force bases. Model application and background interface in the super cockpit audio world hypersonic flows [ AD-A1997941 p 499 N89-20557 [AD-A202535] p474 N69-20985 [AD-A202587] p458 N89-20966 Florida Atiantlc Unh.. Boca Raton. Preliminary design of a modular unmanned research Auburn Unlv., AL The prediction of blade wake interaction noise based vehicle. Volume 1: System design document Rotordynamic analysis of a bearing teSter on a turbulent vortex model [ADA2027651 p 474 N89-20987 p 498 N89-21759 [AIAA PAPER 89-11341 p 503 A89-33764 c-1 Florida State Univ. CORPORA TE SOURCE
Florida State Unlv., Tallahassee. K Advances in the computation of transonic separated Forwsrd flight effects on broadband shock associated flows over finite wings p 442 A89-34427 noise of supersonic jets Kansas Unlv. Center for Research, Inc., Lawrence. High-resolution shock-capturing schemes for inviscid [AIM PAPER 89-10881 p 502 A89-33729 Investigation of a free-tip rotor configurationfor research and viscous hypersonic flows p 443 A89-34646 Florlda Unlv., Galnesvllle. on spanwise life distributions and wake velocity surveys A self-adaptive computational method for transonic A self-adaptive computational method for transonic of a semi-span wing with a discontinuous twist turbulent flow pas1 a real proiecriie p 443 A89-34730 [ NASA-CR-184948) p457 N89-20963 turbulent flow past a real projectile p 443 A89-34730 Navier-Stokes simulation of unsteady three-dimensional blade-vortex interactions p 444 A89-34745 L Evaluation of VSAERO in prediction of aerodynamic G characteristics of helicopter hub fairings Leicester Unlv. (England). [ NASA-TM-I01 0481 p 451 N89-20098 General Accountlng Offlce. Washlngton, DC. Hgh Reynolds number incompressible flow %mulation Documentation of two- and three-dimensional Aviation safety Measunng how Safely individual airlineS about parachute canopies and similar bluff bodies hypersonic shock wave/turbulent boundary layer operate p 450 N89-20096 interaction flows [GAOIRCED-8861 1 p 464 N89-20974 Lockheed Aeronautlcal Systems Co., Burbank, CA. [ NASA-TM-1010751 p 451 N89-20100 Microwave landing systems Additional systems should Interior noise in the untreated Gulfstream II PropfanTest Hub and blade structural loads measurements of an not be procured unless benefits proven Assessment (PTA) aircraft SA34912 helicopter [GAOIRCED-88-tt8l p466 NE920977 [AIAA PAPER 89 11191 p 469 A89-33754 [ NASA-TM-101040] p 472 N89-20124 General Oynamlcs Corp., Fort Worth, TX. Transonics and fighter aircraft Challenges and An airfoil pitch apparatus-modeling and control design The application of CFD for military aircraft design at opportunities for CFD p 454 N89-20932 [NASA-TM-101076] p 496 N89-20386 transonic speeds p 454 N89-20930 Lockheed Aeronautlcal Systems Co., Marletta, GA. Aerodynamic analysis of three advanced configurations General Ektrlc Co.. Clnclnnatl, OH. Computation of aircraft component flow fields at using the TranAir full-potentialcode p 455 N89-20944 transonic Mach numbers using a three-dimensional Structural analysis applications p 480 N89-20141 Turbulence and modeling in transonic flow Navier-Stokes algorithm p 454 N89-20933 General Ektrlc Co., Faldleld, CT. p 456 N89-20951 Heat transfer in gas turbine engines and Three-dimensional singular points in aerodynamics three-dimensonal flows. Proceedings of the Symposium, M [ NASA-TM-1000451 p 457 N89-20964 ASME Winter Annual Meeting. Chicago, IL. Nov 27-Dec AH-I communication switch integration program 2, I988 p 494 A89-34926 S Marquardt Corp., Van Nuys, CA. [ NASA-TM-I01 0531 p 466 N89-20978 George Waehlngton Unlv., Washlngton. DC. Heat transfer in gas turbine engines and Simulation at Dryden Flight Research Facilityfrom 1957 Methodologyfor using steady experimentalaerodynamic three-dimensional flows; Proceedings of the Symposium, to 1982 data lo improve steady and unsteady aerodynamic ASME Winter Annual Meeting, Chicago, IL, Nov. 27-Dec. analysis p 459 N89-20972 [NASA-TM-I01 6951 p 474 N89-20983 2,1988 p 494 A89-34926 National Aeronautics and Space Adminlstration. Hugh GeorgL. Inst. of Tech.. Atlanta. Maryland Unlv., College Park. Nonlinear rotorcraft analysis-expenmental and L Dryden Flight Research Facility. Edwards, CA. Unsteady force calculations on circular cylinders and Flight research and testing p 453 N89-20927 analytical elliptical airfoils with circulation control Natlonal Aeronautlcs and Space Adminlstratlon. [AD-A203967] p 475 NE9 20990 [ UMAERO-87-37] p 457 N89-20962 Langley Research Center, Hampton, VA. Grumman Aerospace Corp., Bethpage, NY. Massachusetts Inst. of Tech., Cambridge. Analysis of the dedicated lase: velocimeter systems ai Appiled transonss at Grumman p 454 N89-20931 Euler and Navier-Stokes ieeside flows over supersonic NASA Langley Research Center p 484 A89-33384 Method to predict external store carriage loads at delta wings p 445 A89-34892 - transonic speeds p 473 N89 20945 On-baard automatic aid and advisory for pilots of Noise reduction of a composite cylinder subjected to control-impaired aircraft p 483 N89-20150 random acoustic excitation H MccDonnell AIrcraft Co., Saint Louis. MO. [AIM PAPER 89-10491 p 501 A89-33708 Hot gas ingestion testing of an advanced STOVL Airfoil profile drag increase due to acoustic excitation concept in the NASA Lewis 9- by 15-foot Low Speed Wind [AIAA PAPER 89.10691 p 501 A89-33715 Hlgh Technology Corp.. Hampton, VA. Propeller modelling effects on intenor noise in cylindrical Shock-boundary-layerinteraction in flight Tunnel with flow visualization [AIAA PAPER 88-30251 p 439 A89-33249 cavities with application to active control p 453 N89-20928 [AIAA PAPER 89-11231 p 469 A89-33757 Huff (Ronald G.) and Aasaclates, North Olmsted, OH. Transonic propulsion system integration analysis at McDonnell Aircraft Company p 481 N89-20943 Advanced turboprop aircraft flyover noise annoyance - Noise generated by a flight weight. air flow control valve Companson of different propeller configurations in a vertical takeoff and landing aircraft thrust vectonng McDonnell-DouglasHelicopter Co., Mesa, Az. Importance of engine as a source of helicopter external [AIAA PAPER 89-1 I281 p 503 A89-33761 system Patched-grid computations of high-speed inlet flows [ NASA-CR-1822321 p 504 N89-20776 noise [AIM PAPER 89-11471 p 470 A89-33771 p 443 A89-34728 McDonnell-Douglas Reaearch Labs., Saint Louls, MO. Navier-Stokes calculations of scramjet-afterbody I EulerlNavier-Stokescalculations of transonic flow past flowfields p 443 A89-34732 fixed- and rotary-wing aircraft configurations Navier-Stokes calculations of transonic flows past open llllnots Univ.. UrbanaChampalgn. p 456 N89-20948 and transitional cavities p 444 A89-34744 Aerospace vehicle design, Spacecraft Section final Mechanlcal Technology, Inc., Latham, NY. Wind-tunnel wall effects on delta wings project reports High speed balancing applied to the T700 engine p 445 A89-34884 [ NASA-CR 184741] p 471 N89-20121 [ NASA-CR-1808991 p 497 N89-20472 Euier and Navier-Stokes ieeside flows over supersonic Aerospace vehicle design. Spacecraft Section final Mlaml Unlv., Coral Gablea, FL delta wings p 445 A89-34892 prolect reports Cockpit automation p 460 A89-34444 Aeroelastic deformation effects on the stopped-rotor [ NASA-CR-1847421 p 472 N89-20122 Mlchlgan Unlv.. Ann Arbor. dynamics of an X-wing aircraft p 482 A89-34897 Aerospace vehicle design. Spacecraft Section Euler solvers for transonic applications Active control law synthesis for flexible aircraft [NASA-CR-184743] p 472 N89-20123 p 454 N89-20935 p 482 A89-35045 lnstltut Franco-Allamand de Recherchea, Saint-Louls An embedded mesh procedure for leading-edge vortex Some low-speed flutter characteristics of simple (France). flows p 455 N89-20936 low-aspect-ratiodelta wing models Base flow investigation behind axi-andnon-axisymmetnc Asymptotic methods for internal transonic flows [NASA-TM-101547] p 450 N89-20094 blunt bodles p 455 N89-20937 Geometrical and structural properties of an Aeroelastic [lSL-CO-246/87] p 452 N89-20103 Mhnesota Unlv., Mlnneapolls. Research Wing (ARW-2) Iowa State Unlv. of Sclencs and Technology, Ames. Aerodynamics Of two-dimensional slotted bluff bodies [NASA-TM-41101 p 451 N89-20099 Turbulent eddy viscosity modeling in transonic r DEW-0072881 D 452 N89-20105 A cell-vertex multigrid method for the Navier-Stokes 1 shocklboucdary-layerinteractms p 456 N89-20952 Missouri Univ., Rotla. equations I NASA lidar velocimetry measurements [ NASA-TM-1015571 p 451 N89-20101 p 491 A89-33435 Updated users' guide for TAWFIVE with multigrid J The effect of the wind tunnel wall boundary layer on [ NASA-TM-41091 p 496 N89-20409 the acoustic testing of propellers Acoustic test of a model rotor and tail rotw: Results JAl Associates, Mountaln Vlew, CA. [AIAA PAPER 89-10971 p 503 A89-33737 for the isolated rotors and combined configuration Navier-Stokes simulation of unsteady three-dimensional [ NASA-TM-1015501 p 504 N89-20777 i blade-vortex interactions p 444 A89-34745 Transonic Symposium: Theory, Application, and Jet Propulslon Lab., Calltornla Inst. of Tsch., N Experiment. Volume 1, Part 1 Pasadena. [ NASA-CP-3020-VOL-1-PT-1I p 453 N89-20925 Hgh-dynamic GPS tracking Natlonal Aeronautlcal Establishment, Ottawa (Ontarlo). Airframelpropulsion integration characteristics at INASA-CR-l84868] p 465 N89-20113 An experimental study of transonic buffet of a transonic speeds p 453 N89-20926 Deriving a geocentric reference frame for satellite supercnlical airfoil wth trailing edge flap Generation of unstructured gnds and Euler solutions for positioning and navigation p 466 N89-20330 [ADA2031891 P 458 N89-20968 complex geometries P 455 N89-20941 Determination of GPS orbits to submeter accuracy National Aeronautics and Space Adminlstration, Transonic Symposium: Theory. Application. and p 466 N89-20331 Washlngton, DC. Experiment, volume 1, part 2 Johnson Aeronautlcs, Palo Alto, CA. Performance and test Section flow characteristics of the [ NASA-CP-3020-VOL-1-PT-21 p 455 N89-20942 Calculation of blade-vortex interaction airloads on National Full-scale Aerodynamics Complex 40- by 8o-fmt Steady and unsteady transonic small disturbance helicopter rotors p 446 A89-34895 wind tunnel analysis of realistic aircraft configurations Jdnt Inst. for Advancement of Fllght Sclences. [ NASA-TM-I01 0651 p 438 N89-20086 p 473 N89-20946 Hampton, VA. Natlonal Aeronautlcs and Space Admlnlstration. Ames Inverse wing design in transonic flow including viscous Asymptotklnumerical analysis of supersonic propeller Reaearch Center, Moffett Fleld, CA. interaction p 473 N89-20947 noise Turbulence modeling for hypersonic flows The 3-D Euler and Navier-Stokes calculalionsfor aircraft [AIAA PAPER 89-10781 p 501 A89-33722 D 441 A89-33641 components p 498 N89-20950
c-2 CORPORA TE SOURCE Sterling Software
Test techniques: A survey paper on cryogenic tunnels, Electronics in civil aviation Observer design for Compensation of network-induced adaptive wall test sections, and magnetic suspension and [NLR-MP-87009-U] p 476 N89-20129 delays in integrated communication and control systems balance systems p 486 N89-20955 The data acquisition system for the Fokker 100 test p 500 A8945044 Instrumentationadvances for transonic testing aircraft Plannlng Research Corp., Hampton, VA. P 486 N89-20957 INLR-MP-6704741 0 476 N89-20130 Noise reduction of a composite cylinder subiected to Wall interference assessment and corrections Quench sensitivity of airlrame aluminum alloys random acoustic excitation p 457 N89-20958 [ NLR-MP-88003-U] p 489 N89-20231 [AIM PAPER 89-10491 p 501 A89-33708 Comparison of airfoil results from an adaptive wall test Bulging cracks in pressurized fuselages: A numerical Airfoil profile drag increase due to acoustic excitation section and a porous wall test Section study [AIAA PAPER 89.10691 p 501 A89-33715 p 457 N89-20960 Prediction of full system helicopter noise for a MDHC [ NLR-MP-87056-UJ p 497 N89-20519 500E helicopter using the Rotonet program Capabilities of wind tunnels with two-adaptive walk to Analysis of crack opening behavior by application of a [AIM PAPER 89-11351 p 500 A89-33765 minimize boundary interference in 3-D model testing discretized strip yield model p 486 N89-20961 Aeroelastic deformation effects on the stopped-rotor [ NLR-MP-87065-Ul p 497 N89-20520 Integrated aerodynamicldynamic optimization Of dynamics of an X-wing aircraft p 482 A89-34897 Current status of flight simulation fatigue crack growth helicopter rotor blades On the relationship between matched filter theory as [ NASA-TM-1015531 p 473 N69-20982 concepts applied to gust loads and phased design loads analysis [ NLR-MP-88001-UI p 497 N89-20521 Aeroelastic modeling for the FIT team FIA-16 [ NASA-CR-1818021 p 472 N89-20125 simulation National Center for Atmospheric Research, Boulder, Pran and Whltney Alrcraft, East Hartford, CT. [NASA-TM-1015691 p 475 N89-20991 co. Structural Tailoring of Advanced Turboprops (STAT) Natlonal Aeronautics and Smce Admlnlstratlon. Lewis Position error calibration of a pressure survey aircraft programmer's manual Ressarch Center, Cleveland, OH. using a trailing cone [ NASA-CR-1621641 p 478 N89-20132 Hot gas ingestion testing of an advanced STOVL [ PB88-2507331 p 450 N89-20092 Fatigue life prediction modeling for turbine hot section concept in the NASA Lewis 9- by 15-foot Low Speed Wind National Severe Storms Lab., Norman, OK. materials p 480 N89-20142 iurlilei with fiow visiis.liiB:ion Triggered lightning strikes to aircraft and natural PRC Kentron, Inc.. Hampton, VA. [AIAA PAPER 88-30251 p 439 A89-33249 intracloud discharges p 460 A89-35158 Active control law synthesis for flexible aircraft Heat transfer in gas turbine engines and National Tranaportatlon Safety Board, Washlngton, p 482 A89-35045 three-dimensionalflows; Proceedings of the Symposium, Dc. Princeton Unlv., NJ. ASME Winter Annual Meeting. Chicago, IL. Nov. 27-Dec. Aircraft accident data, USgeneral aviation. calendaryear Developments and trends in three-dimensional mesh 2,1988 p 494 A89-34926 1986 generation p 455 N89-20940 Effects of wake passing on stagnation region heat [ PB89-1214531 p 463 N89-20108 Fuels combustion research transfer p 494 A89-34928 Aircraft accident reports: Bnef format. US civil and [AD-A204161] p 490 N89-21071 Experimental investigation of transonic oscillating foreign aviation, issue number 12 of 1986 accidents Purdue Unlv., West Lafayette, IN. cascade aerodynamics [PB88-916902] p 464 N89-20109 Modal cost analysis of flexible structures: Modeling flexible structures for control design p 463 N89-20148 [ NASA-TM-1019931 p 478 N89-20133 Aircraft accident reports. brief format, US civil and foreign Actuation constraints in multivariable flight control Toward improved durability in advanced aircraft engine aviation, issue number 14 of 1986 accidents hot sections [PB88-9169041 p 464 N89-20110 systems p 463 N89-20998 [ NASA-TM-40871 p 479 N89-20135 Aircraft accident report: Continental Airlines. Inc.. Flight NASA HOST project overview p 479 N89-20136 1713, McDonnell Douglas DC-9-14, N626TX. Stapleton Advanced high temperature instrument for hot section R International Airport. Denver, Colorado. November 15, research applications p 479 N89-20137 1967 Assessment, development. and application Rensselaer Polytechnic Inst., Troy, NY. of [PB88-910411] p 464 N89-20112 combustor aerothermal models p 479 N89-20138 Wave drag due to lift for transonic airplanes Review and assessment of the database and numerical Naval Clvll Engineering Lab., Port Hueneme. CA. p 455 N89-20938 modeling for turbine heat transfer p 479 N89-20139 Experimental examination of the aerothermal Rice Unlv., Houston, TX. Structural analysis methods development for turbine hot performanceof the T-10 test cell at NAS (Naval Air Station). Abort landing guidance trajectories in the presence of section components p 479 N89-20140 Cubi Point windshear p 461 A89-32725 Fatigue life prediction modeling for turbine hot section [ AD-A2038871 p 487 N89-21005 Rockwell lnternatlonal Corp., Columbus, OH. materials p480 N89-20142 Naval Environmental Prediction Research Faclllty, Power efficient hydraulic systems. Volume 1: Study Life modeling of thermal barrier coatings for aircraft gas Monterey, CA. phase turbine engines p 480 N89-20143 Icing considerations for HALE (High Altitude, Long t AD-A203899 I p 472 N89-20127 Views on the impact of HOST p 480 N89-20144 Endurance) aircraft Power efficient hydraulic systems. Volume 2: Hardware Unsteady blade pressure measurements on a model [AD-A202584] p 464 N89-20975 demonstration phase counterrotation prcpeller Naval Reaearch Lab., Washlngton, DC. [ AD-A203900] p 473 N89-20128 r.. I. T.. rnnnnn. Rockwell International Corp.. Los Angeles, CA. LlVM=M-I. M-IVLWLJ p 53' ?!89-E779 Gener=!ion e! .ns!p~!crd grids snd Fiuler snlutions for An LDA (Laser-Doppler Anemometry) investigation of complex geometries p 455 N89-20941 Transonic aerodynamic design experience p 454 N89-20934 three-dimensional normal shock wave tmundary-layer Nlelsen Englneerlng and Research, Inc., Mountain Rockwell International Sclence Center, Thousand interactions p 456 N89-20956 Vlew, CA. Oaks, CA. A real-time simulator of a turbofan engine High-resolution shockcapturing schemes for inviscid Patched-grid computations of high-speed inlet flows [NASA-TM-100869] p 481 N89-20995 and wscous hypersonic flows p 443 A8944646 A compendium of controlled diffusion blades generated p 443 A8944728 Norfolk State Coll., VA. Royal Slgnals and Radar Establlshment. Malvarn by an automated inverse design procedure A (13)C NMR analysis of the effects of electron radiation [NASA-TM-lOl%El p481 N89-20996 (England). on graphitelpolyetherim!& composites The application of software fault tolerance to air traffic Flowfield measurements in the NASA Lewis Research [ NASA-CR-1828181 p 489 N89-20205 Center 9- by 15-foot low-speed wind tunnel control: Study contract overview [ NASA-TM-1008831 p 486 N89-21002 [ BR1085671 p 465 N89-20114 Fuel-rich catalytic combustion of Jet-A fuel-equivalence 0 ratios 5.0 to 8.0 S [NASA-TM-101 9751 p 489 N89-21051 Offlce National d'Etudes et de Recherches Gas turbine alternative fuels combustion Aerospatlales, Leclerc (France). San Dlego State Unlv., CA. characteristics High-resolution shock-capturing schemes for inviscid Effect of 90 degree flap on the aerodynamics of a INASA-TM-1014701 p 499 N89-21417 and viscous hypersonic flows p 443 A8944646 two-element airfoil p 446 A89-35053 Comparison of propeller cruise noise data taken in the Ohio state univ., Columbus. Sandla Natlonal Labs., Albuquerque, NM. NASA Lewis 8- by 6-foot wind tunnel with other tunnel Electromagneticproperlies of ice coated surfaces Aerodynamics of two-dimensional slotted bluff bodies and flight data [NASA-CR-1847801 p 495 N89-20355 [ DE89-007286] p 452 ~89-20105 [NASA-TM-101976] p 505 N89-21628 Improved computer simulation of the TCAS 3 circular Trajectory scoring in rectangular coordinates using Natlonal Aeronautics and Space Admlnlstratlon. array mounted on an aircraft transponder-interrogatorrange and range rate data Marshall Space Fllght Center, Huntavllle, AL. [NASAGR-1849071 p 496 N89-20363 [ DE89-0070051 p 466 N89-20119 NASA lidar velocimetry measurements Oklahoma Unlv., Norman. Sclentlflc Research Assoclates, Inc., Glastonbury, CT. p 491 A8943435 A first scramjet Study Bipolar cmrdinates for computation of transition duct National Aerospace Lab., Amsterdam (Netherlands). [NASA-CR-1849651 p 480 N89-20146 flows p 493 A69 3491 2 Environment-assisted aerospace fatigue problems in Old Domlnlon Unlv., Norfolk, VA. Sierra Nevada Corp.. Reno. The Netherlands Navier-Stokes calculations of scramjet-afterbody Analysis of Doppler radar windshear data [NLR-MP-88004-U] p 439 N89-20087 flowfields p 443 A89-34732 [ NASA-CR-1817621 p 464 N89-20111 Observed Reynolds number effects on airfoils and high Navier-Stokes calculations of transonic flows past open Southwest Research Inst., San Antonlo, TX. aspect ratio wings at transonic flow conditions and transitional cavities p 444 A8934744 Installation effects on propeller wakelvortex induced [NLR-MP-88006-U] p 451 N89-20102 Viscous shock layer analysis of hypersonic flows over structure-borne noise transmission long slender vehicles p 451 N89-20097 The application of trajectory prediction algorithms for [AIAA PAPER 69-10721 p 468 A8943717 Secondary three-dimensionalinstability in compressible Stanford Unlv., CA. planning purposes in the Netherlands Air Traffic Control boundary layers p 456 N69-20954 (ATC) system A numerical method for predicting hypersonic [NLR-MP-87031-U] p 465 N89-20115 flowfields p 440 A8943634 Continuous-discretefiltering for systems with Markovian P Numerical simulation of the flow field over delta wings switching coefficients with leading edge blowing p 453 N89-20924 [ NLR-MP-87076U1 p 465 N69-20117 Pennsylvanla State Unlv.. Unlverslty Park. Sterllng Software, Palo Alto, CA. Matching Power Spectra Density (PSD)-design load Measurements of a supersonic turbulent vortex Advances in the computation of transonic separated [NLR-MP-67059-U] p 472 N89-20126 p 440 A89-33423 flows over finite wngs p 442 A89-34427
c-3 Sverdrup Technology, Inc. CORPORA TE SOURCE
SverdNp Technology, InC., Cleveland, OH. e'oise generated by a flight welght, air flow control valve in a vertical takeoff and landing aircraft thrust vectoring system [ NASA-CR-1822321 p 504 N89-20776 Subharmonic and fundamental high amplitude excitation of an axisymmetric jet [ NASA-TM-1019461 p 452 N89-20920 Comparison of 3D computation and expenment for non-axisymmetric nozzles [ NASA-CR-182245) p 452 N89-20921 Systems Control Technology, Inc., Arllngton, VI. HelipOrt system planning guidelines IAD-Al990811 p 486 N89-21003 Systma Technology, Inc., Hawthorne, CA. Tailless aircraft performanceimprovements with relaxed static stability [NASA-CR-1818061 p 483 N89-20999 T
Texas A6Y Unlv., College Station. Annular honeycomb seals: Test results for leakage and rotordynamic coefficients - Comparisons to labyrinth and smooth configurations [ASME PAPER 88-TR16-351 p 493 A89-34794 An entrance region friction factor model applied to annular seal analysis - Theory versus experiment for smooth and honeycomb seals [ASME PAPER 88-TRIB-41I p 493 A89-34798 Textron Bell Hellcopter. Fort Worth, TX. Coupled rotorlfuselagedynamic analysis of the AH-1G heliter and correlatiin mth fllght vibrations data [ NASA-CR-1817231 p 497 N89-20512 U Unltod Technologles Corp., Windsor Locks, CT. Sound power spectrum and wave drag of a propeller in fliht [AIM PAPER 89.1081 ] p 502 A8943724 Near wakes of advanced turbopropellers [AIM PAPER 89-10951 p 441 A89-33735 Unltod Tschnologles Resoarch Center, East Hartford, CT. Near wakes of advanced turbopropellers [AIAA PAPER 89-10951 p 441 A8943735 Utah Unlv., Salt Lake Clty. Modern multiple-pulse, high field NMR studies of high density jet fuels [AD-A203320] p 490 N89-21130
Vlgyan Research A~lates,Im., Hampton, VA. Performance of the active sidewall boundary-layer removal system for the Langley 0.3-meter Transonic Cryogenic Tunnel [ NASACR-I81 7931 p486 N89-21004 Vlrglnla Polytechnic Inst. and State Unlv., Blacksburg. A smart pattern recognition system for the automatic identiticatin of aerospace acoustic sources [AIAA PAPER 89.11141 p 499 A8943751 Efficient optimization of integrated aerodynamic-structuraldesign p 500 A8944569 Patched-gridcomputations of high-speed inlet flows p 443 A8944728 Robust stabilization of linear time-invariant uncertain SYStems via Lyapunov theory p 483 N89-20147 Stability of compressible boundary layers p 456 N89-20953 Vlwinla Univ., Charlottesvllle. Laser-induced iodine fluorescence technique for quantitative measurement in a nonreacting supersonic combustor p 445 A8944809 Von Karman Inst. for Fluld Dynamks, Rhodo-SaintGeneso (Belgium). A calculationmethod for compressible three dimensional turbulent boundary layer flows [ VKI-TN-1671 p 496 N89-20422
c-4 FOREIGN TECHNOLOGY INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
Typical Foreign Technology A digital simulation technique for Dryden atmospheric Investigation of flow separation in a three-dimensional turbulence model p 439 A8943142 diffuser using a coupled Euler and boundary-layer Index Listing The reliability analysis of aircraft structures method p 446 A8945172 p 467 A8943146 Vortex breakdown and its control on delta wings Design of an airborne optic fiber data bus system p 449 A8945999 p 475 A8943148 Sound generation and flow interaction of vortices with The cornpuler controlled system for multi-drone an airfoil and a flat plate in transonic flow performing formation flight in a same aerial zone p449 A89-36006 p 481 A8943566 Detailed measurements in the transonic vortical flow A zew me!hob !~r!he !hormc+amic ca!cu!a!ioc of over a deita wing p 449 A83-323372 combustion chambers p 478 A8944409 Experimental investigation of electrostatic fire accidents Some considerationson leading edge vortices on wings after aircraft landing and preventive measures in supersonic flow p 450 A8936013 Numerical analysis of three-dimensional non rigid ~~ p 460 A8944885 CANADA Effect of wing tip strakes on wing lift-dragratio wings - Qualification and operational aspects of light weight p 445 A89-34886 [AIM PAPER 89-09071 p 450 A89-36022 SKAD (light weight survival kit air droppable) The correlation between Reynolds stress and turbulent o 18 A89-10471 kinetic energy in the near wake of a symmetric airfoil p 448 A89-35393 I CZECHOSLOVAKIA Quantitative fractography - Possibilitiesand applications INDIA in aircraft research p 495 A89-35074 A new look at Theodorsen's method in aerofoil theocy p 443 A89-34621 Development of experimental techniques for helicopter F rotor performance studies p 470 A8945198 Advanced techniques used in Kanishka aircraft accident FRANCE investigation p 460 A89-35200 Helicopterrotor wake investigation using a laser Doppler anemometry technique p 439 A89-33385 High altitude parachute and its military applications Measurements of mean-flow and turbulence [AIAA PAPER 89-0893) p 461 A8945211 INTERNATIONAL ORGANIZATION Listings in lhis index are arranged alphabetically characteristics in a turbojet exhaust using a laser velocimeter p 439 A89-33410 Particle image displacement velocimetry applied in high by country of intelleclual origin The title of the Advanced microstructural ObSeNationS of gas turbine speed flows p 490 A89-33388 documenl is used lo provide a brief descriplion of P/M materials p 487 A89-33456 ISRAEL the subject matter The page number and the ac- Computational methods for hypersonic flows - Special Structural optimization for aeroelastic control effectiveness p 470 A89-34899 Cession number are tncluaed in each enlry to as. techniques and real gas effects p 441 A8943640 Laminar-turbulent transition problems at high speeds ITALY sist Ihe user in locating the ctlafion in Ihe abstract p 441 A8943645 Inviscid prediction of transonic flows in turbomachines seclion If appltcable. a reporl number IS also in- Viscous-inviscid interaction and computation in using a Runge-Kutta integration scheme ciuded as an am in ideniiiying iine documeni --.OPrn&".rniPE __,. . p 444 A8944736 [ONERA. TP NO. 1988-1161 p 443 A89-34627 A linear computer code lo determineaeroelastic stability Spin testing methods in flight p 470 A8945796 in airfoil Cascades at unstaady flow condi:ions A ONERA research on civil aircraft p 438 A8945376 D 444 A89-34748 The future of the civil aviation industry AUSTRALIA p 438 A8945377 Mathematical research at the Aeronautical Research Civil-transport aircraft at Aerospatiale J Laboratories 1939-1960 p 437 A89-32982 D 438 A89-35378 Business aviation and new technol&ies Thin aerofoils with high-incidence flaps or blunt trailing JAPAN p 438 A8945379 On a method for solving integral equations of edges p 445 A89-34749 Experimental wind tunnel study of a militaty-aircraft air lifting-surface theory for oscillating high-speed propellers AUSTRIA intake - Comparison with flight p 448 A89-35381 p 439 A89-33100 Spray formed Waspaloy for disc forgings Prediction of potential noise interactions in axial-flow Numerical solution^ for the flowfield around a p 487 A8943463 machines - Application lo the helicopter fenestron counter-rotating propeller p 445 A89-34887 p 504 A89-35385 Aeroelastic divergence of front-free-aft-fixedelastic slnp Prediction of wake-interaction noise in axial-flow parallel to uniform flow p 495 A8945097 B machines - Application to helicopter fenestron Three-dimensionalboundary-layer transition study p 504 A89-35388 p 447 A89-35195 BELGIUM Base flow investigationbehind axi-andnon-axisymmetric A calculation method for compressible three dimensional blunt bodies turbulent boundary layer flows [ ISL-C0-246/871 p 452 N89-20103 N [VKI-TN-167] p 496 N89-20422 NETHERLANDS G Comparison of LDA and LTA application for propeller C tests in wind tunnels p 490 A8943381 GERMANY,FEDERAL REPUBLIC OF A lifting line model for propeller mise CANADA DNLR. Annual Report 1987 p 437 A8942775 [AIAA PAPER 89-10791 p 502 A89-33723 Canadair SentineVSea Sentinel rotary wing RPV. IV The influence of a radial swirl generator on the flow Experimentalvalidation of a liftingsurface model for rotor p 467 A8933556 field from a luel nozzle model p 490 A8943354 wake-stator interaction Launch. recovery and handling systems for vertical 3-D LDA-measurementsin the jet of a bypass-engine [AIAA PAPER 89-11251 p 441 A8943758 take-off and landing UAVs operating from small ships D 477 A89-33386 Experimental investigation of rotor wakelstator interaction noise generation by acoustic mode p 484 A89-33569 High enthalpy testing in hypersonic shock tunnels Transonic buffet of a supercriticalairfoil with trailing-edge measurements D 485 A89-33630 flap p 446 A89-34893 [AlAA PAPER 89-1126) p 503 A89-33759 Numerical simulation of three-dimensional hypersonic Bound vortex boundary layer control with application Environment-assisted aerospace fatigue problems in viscous flows p 441 A8943644 to V/STOL airplanes p 449 A8935994 The Netherlands An experimental study of transonic buffet of a Fast. in-situ repair of aircraft panel components [ NLR-MP-88004-Ul p 439 N89-20087 supercritical airfoil with trailing edge flap p 438 A8944896 Observed Reynolds number effects on airfoils and high [AD-A203189] p 458 N89-20968 Micro radiography and tomography for high resolution aspect ratio wings at transonic flow conditions CHINA, PEOPLES REPUBLIC OF NDT of advanced materiels and microstructural [NLR-MP-88006-U] p 451 N89-20102 Application of harmonic analysis method to research components p 495 A89-35081 The application of trajectory prediction algorithms for on rotor airloads p 467 A89-33139 Calculation of compression shock surfaces in planning purposes in the Netherlands Air Traffic Control A study of the rotor wake in nap-of-the-earth three-dimensional. steady supersonic flows using a (ATC) system p 439 A89-33140 bicharacteristic method p 446 A8945168 [NLR-MP-87031-U] p 465 N89-20115
D- 1 PORTUGAL FOREIGN TECHNOLOGY INDEX
Continuous-discretefiltering for systems with Markovian Effect of the design of a two-row nozzle ring on the On Sound generation by a jet flow passinga semi-infinite smtching coefficients efficiency of a turbine stage of medium rotor solidity aerofoil [ NLR-MP-67076-U] p 465 N89-20117 p 477 A89-34140 [AIL PAPER 89.10701 p 501 A89-33716 Matching Power Spectra Density (PSD)-design load An analytical-experimentalstudy of ring gap losses in Full-scale fatigue testing of components and [NLR-MP-87059-U] p 472 N89-20126 small axial-flow turbines p 478 A89-34141 structures p 485 A89-33801 Electronics in civil aviation Adaptive control of the grinding of large gas turbine Full-scale fatigue testing of aircraft structures [ NLR-MP-87009-Ul p 476 N89-20129 blades p 492 A8944144 p 485 A89-33802 The data acquisition system for the Fokker 100 test Numerical modeling of transonic flow of a viscous gas Fatigue evaluation of helicopter rotor heads aircraft in a plane channel with a sudden expansion p 485 A89-33803 [ NLR-MP-87047-Ul p 476 N89-20130 p 442 A89-34149 Fatigue testing of gas turbine components Quench sensitivity of airframe aluminum alloys Noise levels of a combined bypass-propfan engine in p 485 A89-33804 I NLR-MP-88003-U1 p 489 N89-20231 the far sonic field p 470 A89-34150 Air traffic control p 437 A89-34450 Bulging cracks in pressunzed fuselages: A numerical Analysis of separated flow past a thin profile in the case Compressible flow losses in branched ducts study of translational oscillations p 442 A89-34151 p 494 A89-35004 [NLR-MP-87058-U1 p 497 N89-20519 Optimal profile selection in the design of a subsonic A revision of the added mass concept as applied to Analysis of crack opening behavior by application of a turbine cascade p 442 A89-34152 parachute motion discretized stnp yield model Assessment of the adequacy of bearing lubrication in [AIAA PAPER 89-08951 p 461 A89-35213 [NLR-MP-87065-UI p 497 N89-20520 a gas turbine engine through openings in the rotating Frequency domain techniques applied to the Current status of flaht simulation fatigue crack growth shaft p 492 A8944154 identification of helicopter dynamics p 500 A8935261 concepts Effect of the blade height at the exit of the shrouded Variable structure control laws for aircraft manoeuvres [NLR-MP-88001-U I p 497 N89-20521 rotor of a radial-flowcentripetal microturbineon the turbine p 482 A89-35286 efficiency p 492 A8944155 Design of robust multivariable helicopter control laws Ensuring the quality of the covering surface in the case for handling qualities enhancement p 482 A89-35297 P of riveted joints with high radial interference Load alleviation on transport aircraft using acceleration p 492 A89-34159 feedback p 471 A8945299 PORTUGAL A combined method for calculating supersonic flow of Variable structure model-following control of flight Heat transfer in gas turbine combustors an ideal gas past a wing with a supersonic blunt leading dynamics p 482 A89-35300 p 491 A89-33580 edge p 448 A8945430 Multivariable design of a bank-to-turn autopilot for Effect of the asymmetry of boundary conditions on command guidance p 482 A89-35301 boundary layer flow near a cone at angle of anack Implementationof a transputer-basedflight controller S p 448 A8945433 p 482 A89-35302 SPAIN Turbulization of a high-velocity boundary layer by a New wings, new ways p 471 A89-35825 High Reynolds number incompressible flow simulation 8-2 - The end of the long road toward a 'stealth projection p 448 A8945434 bomber' p 438 A89-35100 Thin axisymmetric caverns in supersonic flow about parachute canopies and similar bluff bodies SWEDEN p 449 A89-35435 p 450 N69-20096 The flow on the lee-side of a delta wing at Mach 7 A method for calculating potential transonic flows in The application of software fault tolerance to air traffic p 440 A89-33637 turbomachinery cascades p 449 A6945450 control: Study contract overview Estimation of the Equivalen! Initial Flow Size (EIFS) Supersonic flow past caret wings and elements of [ BRIO85671 p 465 N89-20114 distribution and prediction of failure probabrlittes for star-shaped bodies at angles of attack and bank different parameter vanations p 449 A89-35481 [ FFA-TN-1987.35) p 498 N89-20525 Potential models of transonic flows SWITZERLAND p 449 A89-35495 Life with the older aircraft p 438 A8945125 Prospects for the application of holographic interferometry to the study of the resonant vibrations of complex systems p 495 A89-35654 T Structural mechanics. Contemporary state and prospects for development (selected portions) TAIWAN rAD-AI987661 p 497 N89-20498 A numencal investigation of steady transonic cascade UNITED KINGDOM flow in turbomachinery p 448 A8945417 PM superalloy turbine blades p 487 A89-33454 TURKEY Structure and properties of forged ODS nickel-base Determining and accounting for a parachute virtual superalloys p 491 A89-33461 mass p 460 A89-34889 Metallic limitationsin aircraflengines - The rational return to the stone age p 477 A89-33485 Argon shrouded plasma coatings for gas turbine U applications p 491 A89-33487 Potential applications for advanced structural ceramics U.S.S.R. in aero gas turbine engines p 488 A89-33490 A physical-statisticalmethod for the predictionof vertical Remotely piloted vehicles; International Conference. wind shear in the lower part of the atmospheric boundary 7th. Bristol. England, Sept. 12-14. 1988. Proceedings and layer p 499 A89-34028 Supplementary Papers p 467 A89-33554 Csramics in high-temperaturegas turbines (Review) Some aspects of the development and operational p 488 A89-34080 testing of the Sprite system p 467 A69-33557 Viscosity effects in the generation of the lifting force Complementary minis- Skyeyeand Phoenix, an overview of aerodynamic wing profiles p 442 A8944114 of their multi-mission coverage p 467 A89-33558 Falconet target RPV operations p 437 A89-33559 Charactenstics of the formation of benz(a)pyrene in the Civilian RPVS Eye in the sky or pie in the sky? combustion chambers of aviation gas turbine engines - P 437 A89-33560 p 488 A89-34119 The Theta Beta .Design of a system Some characteristics of the formation of contaminants p 468 A8943561 during the combustion of hydrocarbon fuels in the Flight test of XRAE-1 to establish aerodynamic data combustion chambers of gas turbine engines P 468 A89-33562 p 488 A89-34120 Development and implementation of flight control A simple one-dimensional model for the effect of air system for a research drop model p 461 A69-33563 pollution on supersonic combustion p 488 A89-34121 The development of a preliminary sizing method for Effect of turbulence on the combustion of an atomized unmanned air vehicles P 468 A69-33564 liquid fuel p 488 A8934122 The Norton P73 rotary RPV engine Natural vibrations of cylindrical shells with a rectangular P 477 A89-33565 cutout p 492 A89-34126 Data links for video and IR surveillance The load-bearing capacity of closed-profile oblong P 465 A8943567 cylindrical shells made of a metallpolymer composite Design aspects of a naval RPV recovery system laminate p 492 A89-34126 P 484 A8943568 Formulation and solution of axisymmetric problems in Low cost avionic system for UMA p 475 A69-33571 the slatics of multilayer shells of revolution with contact Development of a low cost trackinglranging system interaction between layers p 492 A69-34129 P 465 A89-33572 Some consequences of reduced frame rate for operator A mathematical model of aircraft spin and results of its computer integration p 481 A89-34130 perf or ma n c e P 465 A89-33573 Linescan ZOO0 - Tomorrow's sensor today Stability analysis of the multiple discrete stabilization p 475 A8943574 system of an elastic flight vehicle p 500 A8944132 Integrated modular RPV ground station with reference An experimental study of the rate characteristics of brush to the 'Raven' project P 485 A89-33575 seals in Comparison with labyrinth seals In-flight experiments on the active control of p 492 A8944136 propeller-inducedcabin noise Some aspects of the numerical modeling of the [AIAA PAPER 89-10471 P 468 A89-33706 nonstationary heat conductivity of gas turbine Acoustic forcing of three dimensional shear layers components p 477 A69-34139 [AIAA PAPER 69-10631 P 501 A89-33712 CONTRACT NUMBER INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
Typical Contract Number Index Listing
NAG2-2473 ...... p 443 A89-34730 p459 N89-20973 NAG2-70 ...... p 444 A89-34740 p466 N89-20978 NAG1-724 D 44 N89-10125 NAG3-181 ...... p 493 A89-34794 505-62-OK ...... p497 N89-20472 p 493 A89-34798 505-62-01 ...... p481 N89-20995 NAG3-656 ...... p 478 N89-20133 505-62-21 ...... p452 N89-20920 p452 N89-20921 NAG3403 ...... p 478 N89-20134 p481 N89-20996 NAG3-823 ...... p A89-35044 500 p489 N89-21051 NAS1-17145 ...... p 470 A89-33771 505-62-61 ...... p478 N89-20133 NAS1-17496 ...... p 497 N89-20512 CONTRACTNL'L'BEFI I 505-62-71 ...... p504 N89-20776 NAS1-17864 ...... p 452 N89-20922 . 505-63-18 ...... D 479 N89-20135 h NASI-I7919 ...... p 486 N89-21004 505-63-21-01 ...... p452 N89-20922 NASI-17921 ...... p 468 A89-33717 505-63-21-02 ...... p450 N89-20094 NASl -17977 ...... p 450 N89-20093 NAS1-18000 ...... p 501 A89-33708 505-63-21-04 ...... p472p 451 N89-20099N89-20125 p 500 A89-33765 p 475 N89-20991 p 482 A89-35045 Listings in this index are arranged alpha-numerl- 505-63-51-01 ...... p497 N89-20512 p 472 N89-20125 cally by contract number Under each contract 505-63-51 ...... p504 N89-20777 NAS1-18037 ...... p 469 A89-33755 505-66-01-02 ...... p483 N89-20999 number. the accession numbers denoting docu- NAS1-I8105 p 473 N89-20945 ...... 505-66-21-02 ...... p500 N89-20683 ments that have been produced as a result of NASI-18524 p 483 N89-20999 ...... 505-67-41-51 ...... p 464 N89-20111 NAS1-18598 ...... p 464 N89-20111 research done under the contract are arranged in 505-68-27 ...... p474 N89-20983 NASP-I 1555 ...... p 442 A89-34427 ascending order with the AlAA accession numbers 505-80-11 ...... p451 N89-20100 NAS2-12767 ...... p 446 A89-34895 535-03-01 ...... p504 N89-20779 appearing first The accession number denotes NAS2-12789 ...... p 459 N89-20973 p486 N89-21002 the number by which the citation IS identilied In NAS3-23720 ...... p 502 A89-33724 p505 N89-21628 the abstract section Preceding the accession p 441 A89-33735 535-05-01 ...... p478 N89-20134 NAS3-23929 ...... p 497 N89-20472 number is the page number on which the cltation 778-32-11 ...... p499 N89-21417 NAS3-23941 ...... p 478 N89-20132 992-21-01 ...... p457 N89-20964 may be found NAS3-24105 ...... p 452 N89-20921 NAS3-24224 ...... p 493 A89-34912 NAS3-24339 ...... p 469 A89-33754 AF PROJECT SM-MMK-87-10-324 .... p 471 A89-35209 NAS3-24633 ...... p 497 N89-20472 AF-AFOSR-0037-88 ...... p 455 N89-20938 NAS3-25266 ...... p 504 N89-20776 AF-AFOSR-83-0045 ...... p 499 A89-34888 p 452 N89-20921 ...... p 440 A89-33424 NAS7-918 ...... p 465 N89-20113 AF-AFOSR-87-0285 ...... p 493 A89-34909 NAS9-17560 ...... p 500 N89-20683 AF-AFOSR-88-0120 ...... p 440 A89-33425 NCA2-OR-745-309 ...... p 442 A89-34427 DA PROJ. 1L1-62209-AH-76 ...... p 497 N89-20472 NCA2-235 ...... p 440 A89-33423 DAAG29-82-K-0084 ...... p 485 A89-34890 NCCl-115 ...... p 489 N89-20205 r.. ,.nn "l I, nnn YM"LJ-OL-R-WI*...... p 670 A80-34'08 NCC1-121 ...... p 444 A89-34744 DAAG29-85-K-0207 ...... p 475 N89-20990 NCCl-14 ...... p 501 A89-33722 DAA103-86-K-0139 ...... p 440 A89-33634 NCC2-175 ...... p 457 b!'89-20963 DAAL03-86-K-0003 ...... p 442 A89-33783 NCC2-377 ...... p 460 A89-34444 DAAL03-88-C-0006 ...... p 444 A89-34745 NCC2-452 ...... p 451 N89-20100 DE-AG04-76DP-00789 ...... p 471 A89-35209 NCC2-458 ...... p 446 A89-35053 p 447 A89-35214 NGT-21-002-080 ...... p 471 N89-20121 p 447 A89-35216 p 472 N89-20122 p 485 A89-35217 p 472 N89-20123 p 462 A89-35231 p 473 N89-20981 p 463 A89-35233 NIVR-06404N ...... p 497 N89-20519 p 495 A89-35237 NIVR-1823/01702-N ...... p 497 N89-20520 p 447 A89-35243 NSERC-A-2181 ...... p 449 A89-35994 p 448 A89-35250 NSF ATM-87-09659 ...... p 450 N89-20092 p 452 N89-20105 NSF CEE-83-05014 ...... p 499 A89-34359 p 466 N89-20119 NSF DMC-87-07648 ...... DE-A101-85CE-50111 ...... p 499 N89-21417 NSF DMS-87-02864 ...... p 442 A89-33783 DFG-RU-334/1-6 ...... p 441 A89-33644 NSF ECS-86-08875 ...... p 500 A89-35283 DNA PROJ. N99-QMXA ...... p 496 N89-20426 NSF MSM-88-10384 ...... p 469 A89-33720 DNA001-83-GO182 ...... p 496 N89-20426 ...... p 496 N89-20363 4 ...... p 499 A89-34888 ...... p 439 A89-33385 NSG-3913 ...... p 495 N89-20355 ...... p 486 N89-21003 N00014-85-K-0507 ...... p 442 A89-33783 F33615-85-C-5050 ...... p 489 A89-35722 N00014-86-K-0288 ...... p 445 A89-34892 F33615-86-C-2604 ...... p 490 N89-21125 ...... p444 A89-34737 F33615-86-C-2643 ...... p 490 N89-21130 ...... p440 A89-33426 F33615-86-C-2723 ...... p 494 A89-34930 N00014-86-K-0691 ...... p 444 A89-34740 F33615-86-C-3015 ...... p 440 A89-33634 N00014-86-K-0759 ...... p 442 A89-33783 F49620-82-K-0033 ...... p 493 A89-34794 N00024-86-WR-10432 ...... p 444 A89-34733 F49620-84-C-0007 ...... p 445 A89-34819 ...... p 463 A89-35245 F49620-85-C-0084 ...... p 442 A89-34461 ...... p 472 N89-20127 F49620-86-C-0006 ...... p 490 N89-21071 p 473 N89-20128 GRI-5086-234-1280 ...... p 496 N89-20468 N62271-87-M-0204 ...... p 444 A89-34737 ...... p 440 A89-33634 SERC-GRID155436 ...... p 445 A89-34809 505-60-01-01 ...... NAG1-421 ...... p 496 N89-20409 NAGI-505 ...... 505-60-11-01 ...... p 453 N89-20925 NAGI-516 ...... p 481 A89-32725 p 455 N89-20942 505-61-01-09 ...... p 486 N89-21004 NAG1-603 ...... p 500 A89-34569 505-61-28 ...... p 438 N89-20086 NAGl -715 ...... p 503 A89-33764 505-61-51-10 ...... p 473 N89-20982 NAG1-762 ...... p 499 A89-33751 505-61-51 ...... p 451 N89-20098 NAGl-811 ...... p 443 A89-34732 p 472 N89-20124 NAG1-886 ...... p 480 N89-20146 p 496 N89-20386
E- 1 REPORT NUMBER INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
Vpical Report Number Index Listing ...... p 458 N89-20965 # AlAA PAPER 89-1093 ...... p 502 A89-33733 # AlAA PAPER 89-1094 ...... p 502 A89-33734 # AFESCIESL-TR-88-55 ...... p 499 N89-20557 # AlAA PAPER 89-1095 .. p 441 A89-33735 # AIM PAPER 89-1097 ...... p 503 A89-33737 * # n AFtTIGAElAAl88D-09 ...... p 475 N89-20988 # AlAA PAPER 89-1098 ...... p 503 A89-33738 # AFITIGAElAAl88D-10 ...... p 498 N89-21248 # AlAA PAPER 89-1 101 ...... p 492 A89-33741 X AFITIGAElAAl88D-23 ...... p 458 N89-20967 # AlAA PAPER 89-1102 _. p469 A89-33742 # AFITIGAE/AA/88D34 ...... p 459 N89-20970 # AFITIGAEIAAl88D35 ...... p 498 N89-21282 # AlAA PAPER 89-1114 ...... p 499 A89-33751 * # NASA-CR-163247 ...... AFITIGAE/AA/88D4 ...... p 458 N89-20969 # AlAA PAPER 89-1119 ...... p 469 A89-33754 W AFIT/GAEIAA/88S-l ...... p 498 N89-21270 # AlAA PAPER 89-1121 ...... p 469 A89-33755 * # AIM PAPER 89.1123 _._._ p 469 A89-33757 * # AFITlGAElENGl88D-01 ...... p 501 N89-21592 # NUMBER SPONSORED AlAA PAPER 89-1126 ...... p 503 A89-33759 # AFIT/GCS/ENG/88D-17 ...... p 476 N89-20994 X AlAA PAPER 89-1127 ...... p 485 A89-33760 # ww AFITIGCSlENGI88D-6 p 474 N89-20985 # ...... AlAA PAPER 89-1128 ...... p 503 A89733761 # Listings in this index are arranged alpha-numeri. AlAA PAPER 89-1130 ...... p 503 A8943762 # AFIT/GEIENG/88Dl9 ...... p 484 N89-21000 # cally by report number The page number indicates AlAA PAPER 89-1 133 ...... p 503 A89-33763 # AFIT/GE/ENG/88D22 p476 N89-20993 # AlAA PAPER 89-1134 ...... p 503 A89-33764 * X the page on which the citation IS localed The AlAA PAPER 89-1135 ...... p 5M) A89-33765 * X accession number denotes the number by which AFITIGEIENGI88D33 ...... p 484 N89-21001 # AIM PAPER 89-1136 _._._. p503 A89-33766 # AFITIGEIENGl88D38 p 475 N89-20989 # the citation is identlfied An asterlsk (*) Indicates ...... AlAA PAPER 89-1140 _._._. that the item IS a NASA report A pound slgn (#) AlAA PAPER 89-1142 ...... p 477 A89-33769 # AFITlGSElAAl88D-2-VOL-1 ...... p 474 N89-20987 # AlAA PAPER 89-1145 ...... p 504 A89-33770 # indicates thal the item is available on microfiche AlAA PAPER 89-1147 ...... p 470 A89-33771 * X AFOSR-89-0087TR ...... p 490 N89-21071 # AIAA-89-0007 ...... p 452 N89-20921 # Age028 ...... p 457 N89-20964 * # AFWAL-TR-88-2046 ...... p 490 N89-21125 # AIM-89-0993 ...... p 452 N89-20920 * # Age300 ...... AIM-89-1059 ...... p 505 N89-21628 # A-88320 ...... p 451 N89-20098 * # AFWAL-TR-88-3024 ...... p 464 N89-20976 # AIAA-89-1144 ...... A89005 ...... p 466 N89-20978 * # AFWAL-TR-88-3085 ...... p 459 N89-20971 # AIAA-89-1269 ...... A-89028 ...... p 438 N89-20086 * # AIAA-89-1325 ...... p 451 N89-20100 * # AIM PAPER 88-3025 ...... p 439 A89-33249 * X AIM PAPER 89-0878 ...... p 470 A89-35202 # ARO-22557.5-EG ...... p 475 N89-20990 X AIMPAPER 89-0880 ...... p 463 A89-36019 # p 471 A89-35205 # ME-241-VOL-1 ...... p 471 N89-20121 * # AlAA PAPER 89-0885 ...... ASME PAPER 88-TRIB-35 p 493 A89-34794 * # ME-241-VOL-2 ...... p 472 N89-20122 * X AIM PAPER 89-0887 . p461 A89-35207 # ASME PAPER 88-TRIB-41 p 493 A89-34798 # ME-241-VOL-3 ...... p 472 N89-20123 * X AlAA PAPER 89-0888 . p463 A89-36020 # AIM PAPER 89-0891 . p471 A89-35209 # AVSCOM-TR-88-C-007 ...... p 497 N89-20472 * # AD-A197978 ...... p 457 N89-20964 * # AIM PAPER 89-0892 ...... P 461 A89-35210 # AVSCOM-TR-89-'2-001 ...... p 481 N89-20995 * # AlAA PAPER 89-0893 p 461 A89-35211 # AD-Al W766 .. p487 NR8-304RA W ...... AVSCnM.TR.RQ-C.001 - - -...... p 4R8 NR9.21051 * ;y AD-A199081 ...... p 486 N89-21003 # AIMPAPER 89-0894 ...... p 461 A89-35212 X AIAA PAPER 89-0895 ...... p 461 A89-35213 d BR108567 . p465 Fi89-20114 # AIMPAPER 890897 p 447 A89-35214 p 490 N89-21125 X ...... X p474 N89-20984 # AlAA PAPER 89-0898 ...... p 447 A89-35215 # CALSPAN-7170-7 ...... P 496 N89-20426 # ...... p 474 N89-20985 # AlAA PAPER 890899 ...... p 447 A89-35216 # ...... p 485 A89-35217 # CERL-TM-N-89/01 ...... p 505 N89-21632 # AD-A202557 ...... p 458 N89-20965 X ...... p 447 A89-35218 # p462 A89-35219 # ADA202565 ...... p 498 N89-21270 # ...... DDA-EDR-13471 ...... p 490 N89-21125 W ...... p 464 N89-20975 X AIM PAPER 89-0904 ...... p 462 A89-35220 # ...... p 458 N89-20966 # AlAA PAPER 89-0906 ...... P 462 A8945221 X DEBS-007005 ...... p 486 N89-20119 x ...... p 466 N89-20980 X AIM PAPER 89-0907 ...... P 450 A89-36022 X DE89-007288 ...... p 452 N89-20105 # AD-A202692 ...... p 501 N89-21592 # AIM PAPER 894910 ...... p 462 A89-35223 X AlAA PAPER 894911 p489 A89-35224 AD-A202706 ...... p 498 N89-21248 # # DNA-TR-88-58 ...... P 496 N89-20426 x AD-A202727 ...... p 484 N89-21000 # p 462 A89-35228 X AIM PAPER 894916 ...... DOE/NASAI50111-3 ...... p 499 N89-21417 'X AlAA PAPER 89-0921 ...... p 462 A89-35231 X AlAA PAPER 894923 ...... p 463 A89-35233 # DOTIFAAIPM-87/33 ...... p 486 N89-21003 x DOTIFAAIPP-8813 ...... p 486 N89-21003 x
AlAA PAPER 89-0931 ...... p 447 A89-35241 X DOTlFAAlPS-881lS ...... p 464 N89-20111 'X AlAA PAPER 89-0933 ...... P 447 A89-35243 # p 448 A89-35250 # p498 N89-21282 # AlAA PAPER 89-0934 ...... D6-54693 ...... p 450 N89-20093 'X AIM PAPER 89-0935 ...... p 447 A89-35244 # AD-AZO3189 ...... p 458 N89-20968 # AIM PAPER 89-0937 p 463 A89-35245 X ADA203281 p 458 N89-20969 # ...... E-4116 ...... P 4% N89-21002 'X ...... AlAA PAPER 89-0942 p 495 A89-35247 # ...... E4468 ...... D 479 N89-20135 'X AIM PAPER 89-1045 ...... p 468 A89-33705 # E4556 p 504 N89-20776 * # AlAA PAPER 89-1047 ...... p 468 A89-33706 X E-4574 p 452 N89-20921 * # AIM PAPER 89-1049 ._.._p 501 A89-33708 * # E-4578 ...... p 481 N89-20995 * # AIM PAPER 89-1063 p 501 A8943712 # ..... E-4584 p 499 N89-21417 * # AIM PAPER 89-1069 ...... p 501 A89-33715 * X ...... AlAA PAPER 89-1070 ...... p 501 A89-33716 # E-4595 . p 452 N89-20920 * # AlAA PAPER 89-1072 ...... p 468 A8943717 * # E-4665 . p 481 N89-20996 * # AIM PAPER 89-1074 ...... p 468 A89-33719 X E4675 . p 489 N89-21051 .# AlAA PAPER 89-1075 ...... p 469 A89-33720 X E-4676 ...... p 505 N89-21628 * # AlAA PAPER 89-1076 ...... p 469 A89-33721 X E-4684 ...... p 504 N89-20779 * # AlAA PAPER 89-1078 ._.._ p 501 A89-33722 * # E-4697 ...... AD-AZ04161 ...... p 490 N89-21071 # AlAA PAPER 89-1079 ..... p502 A89-33723 X AIM PAPER 89-1081 ...... p 502 A89-33724 * # ADE900870 ...... AIM PAPER 89-1085 ...... p 502 A89-33726 # ELS-TR-716199-12 ...... p 496 N89-20363 ' # AIM PAPER 89-1088 ...... p 502 A89-33729 * # AEDC-TSR-88-V32 ...... p 458 N89-20966 X AIM PAPER 89-1091 ...... p 491 A89-33731 * # ESL-720964-2 ...... p 495 N89-20355 * # F- 1 ETN-89-94031 REPORT NUMBER INDEX
ETN-89.94031 ...... p 476 N89-20129 # NAS 1.55:30x)-VOL-l-PT-l ...... p 453 N89-20925 * # SAND-88-7151 ...... p 452 N89-20105 # ETN-89.94034 ...... p 465 N89-20115 # NAS 1.55:302O-VOL-l-PT-2 ...... p 455 N89-20942 * # ETN-89.94036 ...... p 476 N89-20130 # STI-TR-1252-1 ...... p 483 N89-20999 * # ETN-89-94039 ...... P 497 N89-20519 # NASA-CP-3020-VOL-1-PT-l ...... p 453 N89-20925 * # ETN-89-94040 ...... P 472 N89-20126 # NASA-CP-3020-VOL-1-PT-2 ...... p 455 N89-20942 * # UMAERO-87-37 ...... p 457 N89-20962 # ETN-89-94043 ...... P 497 N89-20520 # ETN-89.94046 ...... p 465 N89-20117 # NASA-CR-177524 ...... p 459 N89-20973 * # USAAEFA-66-16 ...... p 480 N89-20145 # ETN-89.94051 ...... P 497 N89-20521 # NASA-CR-180899 ...... p 497 N89-20472 * # ETN-89-94052 ...... P 489 N89-20231 # NASA-CR-181723 ...... p 497 N89-20512 * # USAAVSCOM-TR-87-A-14 ...... p 457 N89-20964 * # ETN-89-94053 ...... p 439 N89-20087 # NASA-CR-181743 ...... p 452 N89-20922 * # USAAVSCOM-TR-88-A-009 ...... p 466 N89-20978 * # ETN-89-94055 ...... P 451 N89-20102 # NASA-CR-181744 ...... p 450 N89-20093 * # ETN-89-94112 ...... p 452 N89-20103 # NASA-CR-181762 ...... p 464 N89-20111 * # USAFOEHL-88-137EQ01lOJEF ... p 474 N89-20984 # ETN-89-94121 ...... p 496 N89-20422 # NASA-CR-181769 ...... p 500 N89-20683 * # ETN-89-94123 ...... p 498 N89-20525 # NASA-CR-181793 ...... p 486 N89-21004 * # VKI-TN-167 ...... D 496 N89-20422 # NASA-CR-181802 ...... p 472 N89-20125 ' # FAA-EE-88-5 ...... p 499 N89-20557 # NASA-CR-181806 ...... p 483 N89-20999 * # NASA-CR-182164 ...... P 478 N89-20132 * # FFA-TN-1987-35 ...... p 498 N89-20525 # NASA-CR-182232 ...... p 504 N89-20776 * # NASA-CR-182245 ...... p 452 N89-20921 * # FTD-ID(RS)-T-0438-88 ...... p 497 N89-20498 # NASA-CR-182267 ...... p 478 N89-20134 * # NASA-CR-182818 ...... p 489 N89-20205 * # GAO/RCED-88-118 ...... p 466 N89-20977 # NASA-CR-184740 ...... p 473 N89-20981 * # GAOIRCED-88-61 ...... p 464 N89-20974 # NASA-CR-184741 ...... p 471 N89-20121 * # NASA-CR-184742 ...... p 472 N89-20122 * # GRI-8810185 ...... p 496 N89-20468 # NASA-CR-184743 ...... p 472 N89-20123 * # NASA-CR-184780 ...... p 495 N89-20355 * # H-1530 ...... p 474 N89-20983 * # NASA-CR-184868 ...... P 465 N89-20113 * # NASA-CR-184907 ...... p 496 N89-20363 * # ISL-CO-246/87 ...... p 452 N89-20103 # NASA-CR-184948 ...... p 457 N8Y-20963 * # NASA-CR-184965 ...... p 480 N89-20146 * # JPL-PUBL-88-35 ...... p 465 N89-20113 * # NASA-TM-100045 ...... p 457 N89-20964 * # L-16501-VOL-1-PT-1...... p 453 N89-20925 * # NASA-TM-100869 ...... p 481 N89-20995 * # L-16501-VOL-1-PT-2...... p 455 N89-20942 * # NASA-TM-100883 ...... p 486 N89-21002 * # L-16543 ...... p 496 N89-20409 * # NASA-TM-101040 ...... p 472 N89-20124 * # L-16545 ...... P 451 N89-20099 * # NASA-TM-101048 ...... p 451 N89-20098 * # NASA-TM-101053 ...... p 466 N89-20978 * # MTI-87TR56 ...... p 497 N89-20472 * # NASA-TM-101065 ...... p 438 N89-20086 * # NASA-TM-101075 ...... p 451 N89-20100 * # NA88-0001-VOL-1 ...... P 472 N89-20127 # NASA-TM-101076 ...... p 496 N89-20386 * # NA88-0001-VOL-2 ...... P 473 N89-20128 # NASA-TM-101470 ...... p 499 N89-21417 * # NASA-TM-101547 ...... p 450 N89-20094 * # NADC-88066-60-VOL-1 ...... p 472 N89-20127 # NASA-TM-101550 ...... p 504 N89-20777 * # NADC-88066-60-VOL-2 ...... p 473 N89-20128 # NASA-TM-101553 ...... p 473 N89-20982 * # NASA-TM-101557 ...... p 451 N89-20101 * # NAE-AN-54 ...... p 458 N89-20968 # NASA-TM-101569 ...... p 475 N89-20991 * # NASA-TM-101695 ...... p 474 N89-20983 * # NAS 1.15:100045 ...... p 457 N89-20964 * # NASA-TM-101946 ...... p 452 N89-20920 * # NAS 1.15:100869 ...... p 481 N89-20995 * # NASA-TM-101968 ...... p 481 N89-20996 * # NAS 1.15:100883 ...... p 486 N89-21002 ' # NASA-TM-101975 ...... p 489 N89-21051 * # NAS 1.15101040 ...... P 472 N89-20124 * # NASA-TM-101976 ...... p 505 N89-21628 * # NAS 1.15:101048 ...... p 451 N89-20098 * # NASA-TM-101993 ...... p 478 N89-20133 * # NAS 1.15:101053 ...... p 466 N89-20978 * # NASA-TM-102002 ...... p 504 N89-20779 * # NAS 1.15:101065 ...... p 438 N89-20086 * # NASA-TM-4087 ...... p 479 N89-20135 * # NAS 1.15:101075 ...... p 451 N89-20100 * # NASA-TM-4109 ...... p 496 N89-20409 * # NAS 1.15101076 ...... p 496 N89-20386 * # NASA-TM-4110 ...... p 451 N89-20099 * # NAS 1.15101470 ...... p 499 N89-21417 * # NAS 1.15:101547 ...... p 450 N89-20094 * # NCAR/TN-SlB-STR ...... p 450 N89-20092 # NAS 1.15:101550 ...... p504 N89-20777 * # NAS 1.15:101553 ...... p 473 N89-20982 * # NCEL-TN-1788 ...... p 487 N89-21005 # NAS 1.15:101557 ...... p 451 N89-20101 * # NAS 1.15:101569 ...... p 475 N89-20991 * # NEPRF-TR-88-11 ...... p 464 N89-20975 # NAS 1.15:101695 ...... p 474 N89-20983 * # NAS 1.15:101946 ...... p 452 N89-20920 * # NLR-MP-87009-U ...... p 476 N89-20129 # NAS 1.15101968 ...... p 481 N89-20996 * # NLR-MP-87031-U ...... p 465 N89-20115 # NAS 1.15:101975 ...... p 489 N89-21051 * # NLR-MP-870474 ...... p 476 N89-20130 # NAS 1.15:101976 ...... p 505 N89-21628 * # NLR-MP-87058-U ...... p 497 N89-20519 # NAS 1.15101993 ...... p 478 N89-20133 * # NLR-MP-870594 ...... p 472 N89-20126 # NAS 1.15102002 ...... p 504 N89-20779 * # NLR-MP-87065-U ...... p 497 N89-20520 # NAS 1.15:4087 ...... p 479 N89-20135 * # NLR-MP-870764 ...... p 465 N89-20117 # ...... p 496 N89-20409 * # NLR-MP-88001-U ...... p 497 N89-20521 # ...... p 451 N89-20099 * # NLR-MP-88003-U ...... p 489 N89-20231 # 182232 ...... p 504 N89-20776 * # NLR-MP-88004-U ...... p 439 N89-20087 # 177524 ...... p 459 N89-20973 * # NLR-MP-88006-U ...... p 451 N89-20102 # 180899 ...... p 497 N89-20472 * # ...... p 497 N89-20512 * # NTSB/AAB-88/02 ...... p 464 N89-20109 # NAS 1.26:181743 ...... p 452 N89-20922 * # NTSB/AAB-88/04 ...... p 464 N89-20110 # NAS 1.26181744 ...... p 450 N89-20093 * # NAS 1.26:181762 ...... p 464 N89-20111 * # NTSB/AAR-88/09 ...... p 464 N89-20112 # NAS 1.26:181769 ...... p 500 N89-20683 ' # NAS 1.26:181793 ...... p 486 N89-21004 * # NTSB/ARG-88/01 ...... p 463 N89-20108 # NAS 1.26181802 ...... p 472 N89-20125 * # NAS 1.26:181806 ...... p 483 N89-20999 * # ONERA, TP NO. 1988-116 ...... p 443 A89-34627 NAS 1.26:182164 ...... p 478 N89-20132 * # NAS 1.26182245 ...... p 452 N89-20921 * # PB88-250733 ...... p 450 N89-20092 # NAS 1.26182267 ...... p 478 N89-20134 * # PB88-910411 ...... p 464 N89-20112 # NAS 1.26182818 ...... p 489 N89-20205 * # PE88-916902 ...... P 464 N89-ml09 # NAS 1.26184740 ...... P 473 N89-20981 * # PEW-916904 ...... p 464 N89-20110 # NAS 1.26:184741 ...... P 471 N89-20121 ' # PB89-121453 ...... P 463 N89-20108 # NAS 1.26:184742 ...... p 472 N89-20122 * # PB89-131114 ...... p 496 Nag-20468 # NAS 1.26:184743 ...... P 472 N89-20123 * # NAS 1.26184780 ...... P 495 N89-20355 * # PWA-5967-51 ...... p 478 ~89-20132* # NAS 1.26184868 ...... p 465 N89-20113 * # NAS 1.26184907 ...... P 496 N89-20363 ' # P465 N89-20114 # NAS 1.26:184948 ...... p 457 N89-20963 * # NAS 1.26184965 ...... p 480 N89-20146 * # SAND-87-1850 ...... p 466 ~89-20119 #
F-2 ACCESSION NUMBER INDEX
AERONAUTICAL ENGINEERING /A Continuing Bibliography (Supplement 242) August 1989
Typical Accession Number Index Listing A8943769 # p477 A89-34898 # P 446 A8945435 p 449 A8943770 # p 504 A89-34899 # p470 A8935450 P 449 A89-33771 * # p 470 A89-34900 # p 500 A89-35481 p 449 A89-34909 p 493 A89-33783 p 442 A8945495 p 449 A8944912 * p 493 A8945654 p 495 A69-33801 p 485 A89-34926 * p 494 N89-10844 '# D 15 A8945722 p 489 A89-33802 p 485 A89-34928 p 494 * A69-35825 p 471 A89-33803 p 485 A89-34930 p 494 A89-33804 p 485 A89-35841 p 463 A8944931 p 494 A8945842 p 471 A89-33825 p 460 A8944932 p 494 A8944028 p 499 A89-35643 p 471 A89-34933 p 488 A8945645 p 463 A8944080 p 488 A89-34934 p 446 AB9 31?14 p 442 ~a9-35994 p 449 A8944935 F 494 A8945999 p 449 A8944119 p 488 A89-35004 p 494 A8944120 p 488 A89-36006 p 449 A89-35044 * # p 500 A89-36012 p 449 A8944121 p 488 A8945045 * # p 482 A6946013 p 450 A89-34122 p 468 A89-35053 # p 446 ' A8946019 # p463 A89-34126 p 492 A8945074 p 495 Listings is this index are arranged alpha-numeri- A89-34128 p 492 A89-36020 # p 463 A8945081 p 495 A89-36022 # p450 cally by accession number The page number A89-34129 p 492 A8945097 # p495 A89-34130 p 481 listed to the right indicates the page on which the A8945100 p 438 N89-20086 ' # p 438 A8944132 p 500 A8945125 p 438 citation is located An asterisk (') indicates that N89-20067 # p439 A8944136 p 492 A89-35146 p 495 N89-20092 # p450 the item is a NASA report A pound sign (X)rndi- A89-34139 p 477 A89-35158 * # p 460 N89-20093 * # p 450 cates that the item is available on microfiche A89-34140 p 477 A89-35168 p 446 N89-20094 * # p 450 A89-34141 p 478 A89-35172 p 446 A89-34144 p 492 N89-20096 p 450 A89-35195 # p447 N89-20097 p 451 A6944149 p 442 A89-35196 # p470 A89-34150 p 478 N89-20096 * # p 451 A69-33574 P 475 A8945197 # p470 A8942725 * p 481 A8944151 p 442 N89-20099 * # p 451 A8943575 P 485 A89-35196 # p470 A89-32775 p 437 A8944152 p 442 N89-20100 ' # p 451 A89-33580 # P 491 A69-35200 # P460 A8942948 p 487 A8944154 p 492 N89-20101 * # p 451 A89-33621 P 491 A89-35201 p 461 N89-20102 # p451 A89-32982 p 437 A8944155 p 492 A89-35202 # p470 A8943626 # P468 A89-34159 p 492 N89-20103 # p452 A89-33100 # p439 A8943627 # p440 A6945205 # p471 A8944359 p 499 N89-20105 # p452 A89-33139 p 467 A89-33630 # P485 A89-35207 # p461 A89-34409 # p478 N89-20108 # p 463 A89-33140 p 439 A89-33634 * # P 440 A89-35209 # p471 A8944427 * # p 442 N89-20109 # p 464 A89-33142 p 439 A8943637 # P440 A8945210 # p461 N89-20110 # p464 A89-33146 p 467 A89-33638 # p 441 A89-34443 p 476 A89-35211 # p 461 A89-34444 * p 460 N89-20111 * # p 464 A89-33148 p 475 A89-33640 # P441 A89-35212 # p461 A8944446 p 476 N89-20112 # p464 A89-33249 * # p 439 A89-33641 * # P 441 A8945213 # p461 A8944446 p 437 N89-20113 * # p 465 A89-33354 # p490 A89-33644 # P441 A89-35214 # P447 A89-34450 p 437 N89-20114 # p 465 A89-33381 # P490 A89-33645 # P441 A8945215 # p 447 ..^^IYOY-LUI^^. .-13 B p 465 fiOJ.54.10"" " , I p 442 ,409-33393 # p439 A8943646 # P441 . .^. A8945216 # p447 N89-20117 # P465 A8944509 p 470 ,nna,rlr7 ""L 8, p4g5 A89-33384 * # p 484 A89-30664 9499 \.," # A8944569 ' p 500 N89-20119 # p466 A89-33385 # p439 A89-33705 p468 A89-35218 # p447 # A8944621 p 443 N89-20121 '# p 471 A89-33386 # p477 A89-33706 # P468 A8945219 # p462 A89-34627 p 443 N89-20122 * # p 472 A89-33388 # p490 A89-33708 * # P 501 A89-35220 # p462 A89-34646 * p 443 N89-20123 * # p 472 A89-33402 p 491 A89-33712 # p501 A6945221 # p462 A89-34726 p 443 N89-20124 ' # p 472 A89-33410 p 439 A8943715 * # p 501 A69-35223 # p462 A8944728 * p 443 N89-20125 * # p 472 A8943423 P 440 A89-33716 # p501 A89-35224 # p489 A8944730 * p 443 N89-20126 # p472 A89-33424 p 440 A89-33717 * # p 468 A89-35227 # p462 N89-20127 # p472 A8943425 p 440 A8944732 * p 443 A89-35228 # p462 A89-33719 # P468 A89-34733 P 444 N89-20128 # p473 A8943426 p 440 A89-33720 # P 469 A8945231 # p462 A8944736 p 444 N89-20129 # p478 A8933435 ' p 491 A89-33721 # p 469 A8945233 # p463 A89-34737 p 444 N89-20130 # p476 A8943448 p 491 A8943722 * # p 501 A89-35234 # p463 A8944738 p 493 N89-20131 p 478 A8943454 p 487 A89-33723 # p502 A89-35235 # p489 A8944740 * p 444 N89-20132 ' # D 478 A89-33456 p 487 A8933724 * # p 502 A89-35237 # p495 A89-34744 * p 444 N89-20133 '# p 478 A89-33461 p 491 A8943726 # P 502 A89-35241 # p447 A8944745 * p 444 N89-20134 '# p 478 A8933463 p 487 A8943729 * # P 502 A89-35243 # p447 A8944746 p 444 N69-20135 '# p 479 A89-33465 p 487 A8943731 '# p 491 A8945244 # p447 A8944749 p 445 N89-20136 '# p 479 A8943474 p 488 A8943733 # p 502 A89-35245 # p463 A89-34794 * # p 493 N89-20137 '# p 479 A8943485 p 477 A89-33734 # p502 A8945247 # p495 A8944798 * # p 493 N89-20138 '# p 479 A8943487 p 491 A89-33735 * # p 441 A8945250 # p448 A89-34807 # p 445 N89-20139 '# p 479 A89-33490 p 488 A89-33736 # P502 A8945261 p 500 A89-34808 # p 470 N89-20140 *# p 479 A8943554 p 467 A8943737 * # P 503 A89-35283 p 500 N89-20141 '# p 480 A6943555 p 437 A8934809 * # p 445 A89-35286 p 462 A89-33738 # P503 A89-34811 # p 445 N89-20142 '# p 480 A89-33556 p 467 A69-33741 P 492 A89-35297 p 482 # A89-34819 # p445 N89-20143 '# p 480 A8943557 p 467 A89-33742 # p469 A89-35299 p 471 A89-34867 # p493 N89-20144 '# p 480 A89-33558 p 467 A89-33743 P469 A8945300 p 482 # A89-34883 # p445 N89-20145 # p 480 A89-33559 p 437 A89-33751 * # p 499 A6945301 p 482 A89-34884 * # p 445 N89-20146 '# p 480 A89-33560 p 437 A8943754 * # p 469 A69-35302 p 482 A89-34885 # p 460 N89-20147 p 483 A6d-33561 p 468 A89-33755 * # P 469 A89-35376 p 438 A89-34886 # p 445 N89-20148 p 483 A89-33562 p 468 A6943757 * P 469 A89-35377 p 438 # A89-34887 # p445 N89-20149 D 483 A8943563 p 481 A89-33758 P441 A89-35378 p 438 # A89-34888 # p499 N89-20150 b 483 A89-33564 p 468 A89-33759 P503 A8945379 p 438 # A8944889 # p460 N89-20205 * # p 489 A89-33565 p 477 A89-33760 P485 A6945381 p 448 # A8944890 # p 485 N89-20231 # p 489 A6943566 p 481 A8943761 '# P 503 A89-35385 p 504 A8944891 p 460 N89-20330 * # p 466 A89-33567 p 465 # A8935388 p 504 A89-33762 # P503 A89-34892 * # p 445 N89-20331 '# p 466 A89-33568 p 484 A8945393 # p448 A8943763 # p 503 A69-34893 # p446 N89-20355 * # p 495 A8943569 p 484 A8945417 # p 448 A8933764 * # P 503 A8944894 # p468 N89-20363 * # p 496 A8943570 p 477 A69-35430 p 448 A8943765 * # p 500 A8944895 * # p 446 N89-20386 * # p 496 A89-33571 p 475 A89-34896 # p438 A69-35433 p 448 N89-20409 * # p 496 A8943572 p 465 A8943766 # P 503 A89-34897 * # p 482 A89-35434 p 448 N89-20422 # p 496 A89-33573 p 465 A8943769 # P504 G-1 N89-20426 ACCESSION NUMBER INDEX
N89-20426 # P496 N89-21051 '# p 489 N89-20468 # P496 N89-21071 # p490 N89-20472 * # P 497 N89-21125 # p490 N89-20498 # P497 N89-21130 # p490 N89-20512 * # P 497 N89-21248 # p498 N89-20519 X P497 N89-21270 # p498 N89-20520 # P497 N89-21282 # p 498 N89-20521 # P497 N89-21417 '# p 499 N89-20525 X P498 N89-21592 # p501 N89-20557 # P499 N89-21628 * # P 505 N89-20683 * x P 500 N89-21632 # p 505 N89-20776 * # P 504 N89-21759 * # D 498 N89-20777 * # P 504 N89-20779 * X p 504 N89-20920 X P 452 N89-20921 ' X P 452 N89-20922 * # P 452 N89-20923 p 452 N89-20924 p 453 N89-20925 * X p 453 N89-20926 * # p 453 N89-20927 * # p 453 N89-20928 * # p 453 N89-20929 * X p 453 N89-20930'# p454 N89-20931 * X p 454 N89-20932 * # p 454 N89-20933 * X p 454 N89-20934 * # p 454 N89-20935 * X P 454 N89-20936 * X p 455 N89-20937 ' X p 455 N89-20938 # P 455 N89-20939 * # p 455 N89-20940 * # P 455 N89-20941 ' X p 455 N89-20942 * X p 455 N89-20943 ' # p 481 N89-20944 * # p 455 N89-20945 * X p 473 N89-20946 * X p 473 N89-20947 * # p 473 N89-20948 * X p 456 N89-20950 * X p 498 N89-20951 * # p 456 N89-20952 * # p 456 N89-20953 * X p 456 N89-20954 * X p 456 N89-20955 * # p 486 N89-20956 * W p 456 N89-20957 ' # p 486 N89-20958 ' # p 457 N89-20959 * X p 457 N89-20960 * X p 457 N89-20961 * # p 486 N89-20962 # p457 N89-20963 * X p 457 N89-20964'X p457 N89-20965 # p458 N89-20966 # p458 N89-20967 # p458 N89-20968 # p458 N89-20969 # p458 N89-20970 # p 459 N89-20971 # p459 N89-20972 # p459 N89-20973 * X p 459 N89-20974 X p464 N89-20975 X p464 N89-20976 # p464 N89-20977 # p 466 N89-20978 * # p 466 N89-20980 # p466 N89-20981 * # p 473 N89-20982 * X p 473 N89-20983 * X p 474 N89-20984 # p 474 N89-20985 # p 474 N89-20986 # p 474 N69-20987 # p474 N89-20988 # p475 N89-20989 # p475 N89-20990 X p475 N89-20991 '# p 475 N89-20993 # p 476 N89-20994 # p 476 N89-20995 * # p 481 N89-20996 * # p 481 N89-20998 p483 N89-20999 * X p 463 N89-21000 # p 484 N89-21001 # p484 N89-21002 * # p 486 N89-21003 # p 486 N89-21004 * # p 486 N89-21005 # p487
6-2 AVAILABILITY OF CITED PUBLICATIONS
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7. Author@) 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 466 reports, articles and other documents introduced into the NASA scientific and technical information system in July, 1989.
17. Key Words (Suggested by Authors(s)) I 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 134 A07lHC
*For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1989 FEDERAL REGIONAL DEPOSITORY LIBRARIES
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