https://ntrs.nasa.gov/search.jsp?R=19860015852 2018-01-30T11:37:31+00:00Z NASA Aeronautical . NASA SP-7037(200) Engineering May 1986 A Continuing Bibliography with Indexes National Aeronautics and Space Administration . .1 I2v,,/) ) AEECNAU1ICAL BIGIIEEBIIG: A cCMINUING iIbLICGfiAPHY WITH INDEXES {SOPPIiMEl-I 2CC) (Ndticnai Duties and Space Adiitistrdtion} 136 p Unclas [fie AQ7 cocL 01A 00/01 43555 Aeronautical Engineering Aeror 3ring Aeronautical Engineering igineering Aeronautical Engine sal Engineering Aeronautical E nautical Engineering Aeronaut Aeronautical Engineering Aero sring Aeronautical Engineering igineering Aeronautical Engine sal Engineering Aeronautical E nautical Engineering Aeronaut! Aeronautical Engineering Aero sring Aeronautical Engineering ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges. STAR (N-10000 Series) N86-16186 - N86-18283 IAA (A-10000 Series) A86-19291 - A86-22713 This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by RMS Associates. NASA SP-7037(200) AERONAUTICAL ENGINEERING A CONTINUING BIBLIOGRAPHY WITH INDEXES (Supplement 200) 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 April 1986 in Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAA). Scientific and Technical Information Branch 1986 National Aeronautics and Space Administration Washington, DC This supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, price code A06. INTRODUCTION This issue of Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 484 reports, journal articles, and other documents originally announced in April 1986 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged by the first nine STAR specific categories and the remaining STAR major categories. This arrangement offers the user the most advantageous breakdown for individual objectives. The citations include the original accession numbers from the respective announcement journals. The IAA items will precede the STAR items within each category. Seven indexes -- subject, personal author, corporate source, foreign technology, contract number, report number, and accession number -- are included. An annual cumulative index will be published. TABLE OF CONTENTS Page Category 01 Aeronautics (General) 197 Category 02 Aerodynamics 198 Includes aerodynamics of bodies, combinations, wings, rotors, and control surfaces; and internal flow in ducts and turbomachinery. Category 03 Air Transportation and Safety 212 Includes passenger and cargo air transport operations; and aircraft accidents. Category 04 Aircraft Communications and Navigation 215 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 217 Includes aircraft simulation technology. Category 06 Aircraft Instrumentation 228 Includes cockpit and cabin display devices; and flight instruments. Category 07 Aircraft Propulsion and Power 232 Includes prime propulsion systems and systems components, e.g., gas turbine engines and compressors; and on-board auxiliary power plants for aircraft. Category 08 Aircraft Stability and Control 237 Includes aircraft handling qualities; piloting; flight controls; and autopilots. Category 09 Research and Support Facilities (Air) 240 Includes airports, hangars and runways; aircraft repair and overhaul facilities; wind tunnels; shock tube facilities; and engine test blocks. Category 10 Astronautics 243 Includes astronautics (general); astrodynamics; ground support systems and facilities (space); launch vehicles and space vehicles; space transportation; spacecraft communications, command and tracking; spacecraft design, testing and performance; spacecraft instrumentation; and spacecraft propulsion and power. Category 11 Chemistry and Materials 243 Includes chemistry and materials (general); composite materials; inorganic and physical chemistry; metallic materials; nonmetallic materials; and propellants and fuels. Preceding Page Blank Category 12 Engineering 248 Includes engineering (general); communications; 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 259 Includes geosciences (general); earth resources; energy production and conversion; environment pollution; geophysics; meteorology and climatology; and oceanography. Category 14 Life Sciences 260 Includes sciences (general); aerospace medicine; behavioral sciences; man/ system technology and life support; and planetary biology. Category 15 Mathematics and Computer Sciences 262 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 264 Includes physics (general); acoustics; atomic and molecular physics; nuclear and high-energy physics; optics; plasma physics; solid-state physics; and thermodynamics and statistical physics. Category 17 Social Sciences 266 Includes social sciences (general); administration and management; documentation and information science; economics and cost analysis; law and political science; and urban technology and transportation. Category 18 Space Sciences N.A. Includes space sciences (general); astronomy; astrophysics; lunar and planetary exploration; solar physics; and space radiation. Category 19 General 267 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 AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 200) MAY 1986 01 F-15 fighter airframe bulkheads, reducing the current 25-hr process in which 1100 measurements are conducted to a 2.5-hr one. Also noted is the robotic assembly of a microswitch from 17 parts that AERONAUTICS (GENERAL) have been positioned randomly on a tray. Also sponsored are two programs on flexible assembly subsystems that are developing the technologies required by an Automated Assembly Center, such as flexible fixturing, part-location sensing, and temporary/permanent fastening of parts. O.C. A86-2105S AVIATION MAINTENANCE MANAGEMENT E. H. KING (Southern Illinois University, Carbondale, IL) A86-22128 Carbondale, IL, Southern Illinois University Press, 1986. 221 p. EVOLUTION OF AIRCRAFT/AEROSPACE STRUCTURES AND refs MATERIALS SYMPOSIUM, DAYTON, OH, APRIL 24, 25, 1985, The maintenance management concerns that confront the PROCEEDINGS various levels of aviation supervision are discussed. The topics Symposium sponsored by AIAA. Dayton, OH, American Institute addressed include: the FAA's organizational structure, FAA of Aeronautics and Astronautics, 1985, 137 p. For individual items publications pertaining to maintenance, aviation maintenance see A86-22129 to A86-22144. procedures, the application of aviation maintenance concepts, and Various papers on the evolution of aircraft and aerospace budgeting, cost controls, and cost reduction. Also considered are: structures and materials are presented. The topics addressed training and professional development in aviation maintenance, include: XB-70 structures and materials advances, structural safety and maintenance, electronic data processing, and aviation evolution from B-58 to F-16, advanced composites in construction maintenance management problem areas. C.D. of the Beech Starship, structural and material considerations for advanced fighters, the evolution of reciprocating engines at Lycoming, aircraft design from the myth of make-do to Mach 3, A86-21325 and the Wright Brothers' experience in the evolution of aircraft GENERAL AVIATION AND REGIONAL AIR TRAFFIC - design, structures and materials. Also considered are: evolution of COMPONENTS OF THE TRAFFIC SYSTEM, SYMPOSIUM, the turbofan aircraft engine, X-15 high-temperature advanced FRIEDRICHSHAFEN, WEST GERMANY, MARCH 28, 29, 1985, structure, X-20 structures overview, ASSET program for technology REPORTS [DIE ALLGEMEINE LUFTFAHRT UNO development. Shuttle Orbiter airframe, airframe design to achieve REGIONALLUFTVERKEHR BESTANDTEILE DES •minimum cost, superplastically formed-diffusion bonded titanium VERKEHRSSYSTEMS, SYMPOSIUM, FRIEDRICHSHAFEN, technology transition case study, transition of advanced materials WEST GERMANY, MARCH 28, 29, 1985, VORTRAEGE] and structures in single crystal blades, and composites technology Symposium sponsored by DGLR, DGON, and BMFT. Bonn, transfer and transition. C.D. Deutsche Gesellschaft fuer Luft- und Raumfahrt, 1985, 196 p. In German. No individual items are abstracted in this volume. The airport system in the Federal Republic of Germany is N86-16187*# National Aeronautics and Space Administration. considered, taking into account 11 international airports, 30 smaller Langley Research Center, Hampton, Va. airports, air traffic requirements, the importance of general aviation VORTEX WAKE ALLEVIATION STUDIES WITH A VARIABLE and regional air traffic for the economy, and the significance of TWIST WING smaller airlines that can provide cost-effective air transportation G. T. HOLBROOK, D. M. DUNHAM, and G. C. GREENE Nov. for regions and cities which cannot be profitably serviced by the 1985 117p refs big airliners of the large airlines. Attention is given to the role of (NASA-TP-2442; L-15870; NAS 1.60:2442) Avail: NTIS HC the Lufthansa in the regional air traffic of West Germany, the A06/MFA01 CSCL01B regional air traffic from the point of view of the European Regional Vortex wake alleviation studies were conducted in a wind tunnel Airlines Organization (ERA), observations made in connection with and a water towing tank using a multisegmented wing model which regional air traffic, the effect of regional air traffic on the region in provided controlled and measured variations in span load. Fourteen which the airport is located, observations made in an airport with model configurations are tested at a Reynolds number of one respect to air traffic control, and requirements related to runways million and a lift coefficient of 0.6 in the Langley 4- by 7-Meter in case of instrument flight operations at regional airports. The Tunnel and the Hydronautics Ship Model Basin water tank at political and economic significance of air traffic involving business Hydronautics, Inc., Laurel, Md. Detailed measurements of span aircraft is considered along with the availability of the Global load and wake velocities at one semispan downstream correlate Positioning System. G.R. well with each other, with inviscid predictions of span load and wake roll up, and with peak trailing-wing rolling moments measured A86-21894# in the far wake. Average trailing-wing rolling moments are found TOWARD AUTOMATED AIRFRAME ASSEMBLY to be an unreliable indicator of vortex wake intensity because W. H. REIMANN (USAF, Manufacturing Technology Div., vortex meander does not scale between test facilities and free-air Wright-Patterson AFB, OH) Aerospace America (ISSN 0740-722X), conditions. A tapered-span-load configuration, which exhibits little vol. 24, Jan. 1986, p. 44-46, 48. or no drag penalty, is shown to offer significant downstream wake The U.S. Air Force has been supporting research on flexible alleviation to a small trailing wing. The greater downstream wake automated systems for airframe assembly over the course of alleviation achieved with the addition of spoilers to a flapped-wing several years. Attention is given to the use of two robots to inspect configuration is shown to result directly from the high incremental 197 01 AERONAUTICS (GENERAL) drag and turbulence associated with the spoilers and not from rates. In each case, the motion began at 0 deg angle-of-attack, the span load alteration they cause. Author and terminated when the airfoil reached 90 deg angle-of-attack. It was found that lift and drag coefficient data could be correlated N86-16188# Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn using simple trigonometric functions. These correlations in turn (West Germany). allow one to estimate lift and drag coefficients over the entire AIR AND SPACE FLIGHT. DREAM AND FACTS [LUFT- UNO range of motion for any nondimensional pitching rate. Author RAUMFAHRT. TRAUM UND WIRKLICHKEIT] L BOELKOW, K. VONGERSDORFF, and H. J. EBERT 1985 32 p In GERMAN Presented at the opening of the Air and A86-19633*# Informatics General Corp., Palo Alto, Calif. Space Travel Hall of the Deutsches Museum, Munich, West UNSTEADY TRANSONICS OF A WING WITH TIP STORE Germany, 6 May 1984 and at Bayerischer Verdienstorden, 20 Jul. G. P. GURUSWAMY (Informatics General Corp., Palo Alto, CA), 1984 P. M. GOORJIAN (NASA, Ames Research Center, Moffett Field, (MBB-FILM-382) Avail: NTIS HC A03/MF A01 CA), and E. L. TU AIAA, Aerospace Sciences Meeting, 24th, The history of man's conquest of the air and space with hot Reno, NV, Jan. 6-9, 1986. 14 p. USAF-supported research, refs air balloons, subsonic and hypersonic aircraft, helicopters and (AIAA PAPER 86-0010) gliders as well as rockets, space shuttles, and manned space The presence of tip stores influences both the aerodynamic flights is reviewed. Progress in aircraft and space technology is and the aeroelastic performance of wings. Such effects are more discussed. Author (ESA) pronounced in the transonic regime. In this study, a theoretical method is developed, for the first time, to compute unsteady N86-16189# Rijksluchtvaartdienst, The Hague (Netherlands). transonics of oscillating wings with tip stores. The method is based ACTIVITIES REPORT IN AERONAUTICS Annual Report, 1984 on the small-disturbance, aerodynamic equations of motion from [JAARVERSLAG 1984] the potential-flow theory. To validate the method, subsonic and 1984 62 p In DUTCH transonic aerodynamic computations are made for a Avail: NTIS HC A04/MF A01 lower-aspect-ratio wing, and they are compared with the available The activities of the Dutch Civil Aeronautics Board (CAB) are experimental data. Comparisons are favorable. The strong effects reviewed. Air traffic control, airfields, air transportation, aviation of the tip store on the transonic aerodynamics of the wing are security, aviation school, national aeronautics and astronautics also illustrated. The method developed in this steady can be used museum, and national aeronautics and astronautics laboratory are for transonic, aeroelastic computations of wings with tip stores. presented. Regional services in Europe; an aviation accident law; Author Maastricht airport; and recognition of industries by the CAB are discussed. Author (ESA) A86-19635# N86-16190# Societe Nationale Industrielle Aerospatiale, Suresnes OSCILLATING HOT-WIRE MEASUREMENTS ABOVE AN (France). Lab. Central. FX63-137 AIRFOIL PROBLEMS FOUND WHEN INTRODUCING NEW MATERIALS W. S. SARIC (Arizona State University, Tempe) and J. D. [PROBLEMES POSES PAR L'INTRODUCTION DES MATERIAUX CROUCH AIAA, Aerospace Sciences Meeting, 24th, Reno, NV, NOUVEAUX] Jan. 6-9, 1986. 13 p. refs G. HILAIRE 29 Apr. 1985 34 p In FRENCH Presented at (Contract N00014-84-K-0093; N00014-85-K-0527) Journees de la Technologie 1984, Jonville, France, 5-6 Dec. (AIAA PAPER 86-0012) 1984 A system is developed to allow measurement of both the mean (SNIAS-852-551-101; C-47-652-AC/GH-AT) Avail: NTIS HC and disturbance flow velocities in separated regions. An oscillation A03/MF A01 arm assembly is developed which provides a directional bias to Aircraft specifications and design problems are discussed. The the hot-wire probe, along with a linear step assembly, which steps parameters guiding the choice of new materials are analyzed. the probe through the boundary layer. A series of velocity profiles Organic matrix composite materials, carbon or glass, aluminum are measured on the FX63-137 airfoil in the chord Reynolds number lithium alloys, titanium alloys and metallic matrix composites are range of 150,000 to 300,000, at angles of attack of alpha = 12 examined. The effect of a new material on the aircraft life and deg and alpha =14 deg. Data are presented on the size of the maintenance and operation cost is discussed. Fatigue problems separation bubble and on the location of transition to turbulence. and lithium alloys are studied. Author (ESA) Author 02 A86-19676*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. NUMERICAL MODELING OF ROTOR FLOWS WITH A AERODYNAMICS CONSERVATIVE FORM OF THE FULL-POTENTIAL EQUATIONS Includes aerodynamics of bodies, combinations, wings, rotors, and R. C. STRAWN (NASA, Ames Research Center, Moffett Field, control surfaces; and internal flow in ducts and turbomachinery. CA) and F. X. CARADONNA (NASA, Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field, CA) AIAA, Aerospace Sciences Meeting, 24th, Reno, NV, Jan. 6-9, 1986. 9 A86-19631# p. refs AN EXPERIMENTAL INVESTIGATION OF AN AIRFOIL (AIAA PAPER 86-0079) PITCHING AT MODERATE TO HIGH RATES TO LARGE ANGLES A computer program has been developed to solve a OF ATTACK three-dimensional conservative formulation of the full-potential G. M. GRAHAM and J. H. STRICKLAND (Texas Tech University, equation. Its ability to solve transonic, unsteady rotor flows is Lubbock) AIAA, Aerospace Sciences Meeting, 24th, Reno, NV, demonstrated by comparison to forward flight non-lifting pressure Jan. 6-9, 1986. 7 p. Research supported by the Sandia National data at low to moderate advance ratios. A 'split potential' Laboratory, refs formulation has been added to the code which incorporates known (Contract F49620-82-C-0035) vorticity fields into the full-potential calculation. Using this (AIAA PAPER 86-0008) methodology, rotor wake contributions have been incorporated into Flow visualization data, surface pressure distributions, and load the computer code. Pressure results are presented for lifting rotors cell data were obtained from a NACA 0015 airfoil undergoing in hover. These results are compared to experimental data as constant pitch motions over a wide range of nondimensional pitch well as to other predictions. Author 198 02 AERODYNAMICS A86-19693*# National Aeronautics and Space Administration. event in the case of an airfoil which pitches at a constant rate. A Ames Research Center, Moffett Field, Calif. total of 100 dynamic-stall data runs were made at five tunnel THE COMPUTATION OF STEADY 3-D SEPARATED FLOWS speeds in the range of flow velocities from 26 to 48 ft/s. At each OVER AERODYNAMIC BODIES AT INCIDENCE AND YAW tunnel speed four pitch rates were used. Attention is given to T. H. PULLIAM (NASA, Ames Research Center, Moffett Field, details regarding the experimental approach, the obtained results, Stanford, CA) and D. PAN AIAA, Aerospace Sciences Meeting, lift-curve characteristics, preseparation characteristics, drag and 24th, Reno, NV. Jan. 6-9, 1986. 12 p. refs moment characteristics, and general comments. It is believed that (Contract NCA2-IR-745-404) the results reported provide insight into the mechanisms at work (AIAA PAPER 86-0109) in the dynamic-stall process. It is emphasized that different This paper describes the implementation of a general purpose mechanisms are at work at different points in the dynamic-stall 3-D NS code and its application to simulated 3-0 separated vortical event. G.R. flows over aerodynamic bodies. The thin-layer Reynolds-averaged NS equations are solved by an implicit approximate factorization A86-19699# scheme. The pencil data structure enables the code to run on VORTICES PRODUCED BY AIR PULSE INJECTION FROM THE very fine grids using only limited incore memories. Solutions of a SURFACE OF AN OSCILLATING AIRFOIL low subsonic flow over an inclined ellipsoid are compared with M. C. ROBINSON and M. W. LUTTGES (Colorado, University, experimental data to validate the code. Transonic flows over a Boulder) AIAA, Aerospace Sciences Meeting, 24th, Reno, NV, yawed elliptical wing at incidence are computed and separations Jan. 6-9, 1986. 14 p. refs occurred at different yaw angles are discussed. Author (Contract AF-AFOSR-81-0037) (AIAA PAPER 86-0118) A86-19696# High rates of vortex production are not consistent with the INFLUENCE OF EXCITATION ON COHERENT STRUCTURES airfoil oscillation rates needed to match realistic, higher Reynolds IN REATTACHING TURBULENT SHEAR LAYERS numbers. Thus, alternative mechanisms must be evolved for the F. W. ROOS and J. T. KEGELMAN (McDonnell Douglas Research control and generation of large scale vortices which can yield Laboratories, St. Louis, MO) AIAA, Aerospace Sciences Meeting, significant amounts of lift enhancement. The present study is 24th, Reno, NV, Jan. 6-9, 1986. 10 p. Research supported by concerned with a noval means for producing large scale vortices McDonnell Douglas Corp. refs over a dynamically pitching airfoil. A pulse of air is delivered during (AIAA PAPER 86-0112) each cycle of the sinusoidal pitch oscillation. The pulse produces A series of experiments was performed in the reattaching a brief stream of air arising from a span oriented slot located at turbulent shear layer produced by flow over a backward-facing, 0.1c parallel to the leading edge. Experiments were conducted on two-dimensional step. Gentle excitation of the shear layer by an an NACA 0015 airfoil with six inch chord in a subsonic, low oscillating flap at the step lip proved to be highly effective in turbulence wind tunnel. Attention is given to experimental details, regularizing and enhancing the formation and development of unsteady flow visualization, the development of pulse vortices, vortical structures in the reattaching flow. Effects of variations in and hot wire anemometry of flow with and without air pulse excitation amplitude and frequency were defined. An injection. G.R. excitation-frequency-sensitive reduction in reattachment length was identified with the process of vortical-structure coalescence in the A86-19700# shear layer upstream of reattachment. Shear-layer excitation was FLUID DYNAMICS OF CYLINDER RESPONSE TO KARMAN shown to increase the intensity of reattachment-wall pressure VORTEX SHEDDING fluctuations in all cases, regardless of the reattachment-length L E. ERICSSON (Lockheed Missiles and Space Co., Inc., effect. Subharmonic phase-modulation of the shear-layer excitation Sunnyvale, CA) AIAA, Aerospace Sciences Meeting, 24th, Reno, was demonstrated to be effective in regularizing the vortex-merging NV, Jan. 6-9, 1986. 11 p. refs process in the reattaching shear layer. Author (AIAA PAPER 86-0119) The fluid mechanics of cylinder response to Karman vortex A86-19697# shedding are composed of three district flow phenomena: (1) the COMPUTATION OF DYNAMIC STALL OF NACA0012 AIRFOIL vortex wake formation, (2) the coupling between flow separation BY BLOCK PENTADIAGONAL MATRIX SCHEME and body motion, and (3) the interaction between shed vortices Y. SHIDA, H. TAKAMI, K. KUWAHARA (Tokyo, University, Japan), and the body cross-section. Analysis of available experimental and K. ONO (Nihon University, Tokyo, Japan) AIAA, Aerospace results for circular and rectangular cross-section cylinders shows Sciences Meeting, 24th, Reno, NV, Jan. 6-9, 1986. 11 p. refs that, for small amplitudes, (1) is the dominating flow mechanism, (AIAA PAPER 86-0116) and the cylinder response is of the resonant type. However, when The flow field around an oscillating NACA0012 airfoil in pitch the amplitude exceeds a few percent of the cylinder crossflow at 0.25 chord is analyzed by solving the two-dimensional dimension, the dominating flow mechanism is (2), and the cylinder compressible Navier-Stokes equations. A block pentadiagonal response changes from the resonant to the self-excited type typical matrix scheme based on the approximate factorization method is for systems with nonlinear negative damping. Flow mechanism (3) adopted. Two kinds of mesh, 161 x 40 and 321 x 80, are used. appears only to be important if the cross-section has a suitable In the case of coarse mesh, lift stall is captured. In the case of chordwise extent, as in the case of the rectangular fine mesh, not 'only lift stall but also restoration process of the lift cross-sections. Author coefficient in the downstroke is captured. The process of the beginning of separation at stall stage is intensively studied. A86-19702# Author STEADY AND UNSTEADY FULL POTENTIAL CALCULATION FOR LARGE AND SMALL ASPECT RATIO SUPERCRITICAL A86-19698# WINGS LIFT-CURVE CHARACTERISTICS FOR AN AIRFOIL PITCHING S. Y. RUO, J. B. MALONE (Lockheed Georgia Co., Marietta, GA), AT CONSTANT RATE and L N. SANKAR (Georgia Institute of Technology, Atlanta) AIAA, E. J. JUMPER (USAF, Institute of Technology, Wright-Patterson Aerospace Sciences Meeting, 24th, Reno, NV, Jan. 6-9, 1986. 12 AFB, OH), S. J. SCHRECK (USAF, Aeronautical Systems Div., p. refs Wright-Patterson AFB, OH), and R. L DIMMICK AIAA, Aerospace (AIAA PAPER 86-0122) Sciences Meeting, 24th, Reno, NV, Jan. 6-9, 1986. 11 p. refs A numerical method which solves the three-dimensional (AIAA PAPER 86-0117) full-potential equation by a strongly implicit, approximate Daley and Jumper (1984) have conducted an experimental study factorization algorithm is used to analyze the flow over a high of dynamic stall for an airfoil pitching at constant rates. The present and a low aspect ratio wing. Steady and unsteady flow analyses paper provides a report on a systematic study of the dynamic-stall are respectively obtained by relaxation and time-accurate marching. 199