Aeronautical NASA SP-7037 (134) NASA Engineering April 1981
SHUTTLE LAUNCH Aeronautical Engineering Aei ering Aeronautical Engineerjr igineering Aeronautical Engin ^^ • ••• • ^^ • JL • • ^^ • •
- ••"""•"'^pj.H«HHSbio...,?-.^ Iul/U1 °^r>nau xajucai engineering Aer ^ring Aeronautical Engineerim gineer jng Aeronautical Engirt ^al Engineering Aeronautical E lautical Engineering Aeronaut Aeronautical Engineering Aert ring Aeronautical Engineerinc MBKR RAN(
-10000
prepared by the and Teehnic AERONAUTICAL ENGINEERING A Continuing Bibliography Supplement 134 A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in March 1981 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA). Scientific and Technical Information Branch 1 981 National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB/141/093 from the National Technical Information Service (NTIS), Springfield. Virginia 22161 at the price of $5.00 domestic: $10.00 foreign. INTRODUCTION Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements have been issued. This supplement to Aeronautical Engineering - A Continuing Bibliography (NASA SP-7037) lists 387 reports, journal articles, and other documents originally announced in March 1981 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (I A A). 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 in two major sections, IA A Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number -- are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS IAA ENTRIES (A81-10000 Series) All publications abstracted in this Section are available from the Technical Information Service. American Institute of Aeronautics and Astronautics. Inc. (AIAA), as follows: Paper copies of accessions are available at S7.00 per document up to a maximum of 40 pages. The charge for each additional page is $0.25. Microfiche of documents announced in IAA are available at the rate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standing orders for all IAA microfiche. The price for the IAA microfiche by category is available at the rate of $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 per microfiche. Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped on payment of pro-forma invoices. All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications. STAR ENTRIES (N81 10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line. Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page viii. Documents on microfiche are designated by a pound sign (ft) following the accession number. The pound sign is used without regard to the source or quality of the microfiche. Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section. Springfield. Va. 22161. NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the U S-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD. PB. or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification. Avail: SOD (or GPO). Sold by the Superintendent of Documents. U.S. Government Printing Office, in hard copy. The current price and order number are given following the availability line. (NTIS will fill microfiche requests, at the standard S3.50 price, for those documents identified by a jf symbol.) (1) A microfiche is a transparent sheet of film. 105 by 148 mm in size, containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26:1 reduction). Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration. Public Documents Room (Room 126). 600 Independence Ave.. S.W.. Washington. D.C. 20546. or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory. Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports, usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet. DOE Technical Information Center - Its Functions and Services (TID-4660). which may be obtained without charge from the DOE Technical Information Center. Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation. Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction. The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction. Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House, Inc. (PHI). Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI. Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa. Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.) Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie, Physik, Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany, at the price shown in deutschmarks (DM). Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks. U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line. GENERAL AVAILABILITY All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover. SUBSCRIPTION AVAILABILITY This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements is $50.00 domestic; $100.00 foreign. All questions relating to the subscriptions should be referred to NTIS. Ann: Subscrip- tions. 5285 Port Royal Road. Springfield Virginia 22161. VI ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics National Technical Information Service and Astronautics 5285 Port Royal Road Technical Information Service Springfield. Virginia 22161 555 West 57th Street. 1 2th Floor New York. New York 10019 Pendragon House. Inc. British Library Lending Division, 899 Broadway Avenue Boston Spa. Wetherby, Yorkshire, Redwood City. California 94063 England Commissioner of Patents and Superintendent of Documents Trademarks U.S. Government Printing Office U.S. Patent and Trademark Office Washington, D.C. 20402 Washington. D.C. 20231 Department of Energy University Microfilms Technical Information Center A Xerox Company P.O. Box 62 300 North Zeeb Road Oak Ridge. Tennessee 37830 Ann Arbor, Michigan 48106 ESA-lnformation Retrieval Service ESRIN Via Galileo Galilei University Microfilms, Ltd. 00044 Frascati (Rome) Italy Tylers Green London. England Fachinformationszentrum Energie, Physik, Mathematik GMBH U.S. Geological Survey 7514 Eggenstein Leopoldshafen 1033 General Services Administration Federal Republic of Germany Building Washington. D.C. 20242 Her Majesty's Stationery Office P.O. Box 569. S.E. 1 London, England U.S. Geological Survey 601 E. Cedar Avenue NASA Scientific and Technical Information Flagstaff, Arizona 86002 Facility P.O. Box 8757 U.S. Geological Survey B. W. I. Airport, Maryland 21240 345 Middlefield Road Menlo Park, California 94025 National Aeronautics and Space Administration Scientific and Technical Information U.S. Geological Survey Branch (NST-41) Bldg. 25, Denver Federal Center Washington, D.C. 20546 Denver, Colorado 80225 NTIS PRICE SCHEDULES Schedule A STANDARD PAPER COPY PRICE SCHEDULE (Effectrve Jonu«ry 1. 19811 Prie» Peg. Mane North American Cod* Pric* AOI Microfiche $ 350 $ 7 00 A02 OO1-025 500 10OO A03 026-050 6.50 1300 ACM 051 075 800 1600 A05 076 100 950 1900 A06 101-125 11.00 2200 A07 126-150 1250 2500 A08 151-175 1400 2800 A 09 176-200 1550 31 00 A10 201-225 17.00 3400 All 226-250 1850 3700 A12 251-275 2000 4000 A13 276 300 21 50 4300 A14 301-325 23.00 4600 A15 326 350 2450 4900 A16 351-375 2600 5200 A17 376-400 2750 5500 A18 401 425 2900 5800 A19 426-450 3050 61 00 A20 451-475 32.00 6400 A21 476 500 33.50 6700 A22 501 525 3500 7000 A23 526-550 36.50 7300 A24 551-575 3800 76OO A25 576 600 3950 7900 601 -up A99 - Write for quote I/ Add $1.50 for each additional 25 page increment or ponion thereof for 601 pages up. 2/ Add $3.00 for each additional 25 page increment or ponion thereof for 601 pages and more. Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche Price Cod* E01 S 5.50 1150 E02 650 13.50 E03 8.50 17.50 E04 1050 21 SO EOS 12.50 2550 E06 1450 2950 E07 16.50 33 50 EOS 18 50 3750 E09 2050 41 50 E10 22.50 4550 Ell 24.50 4950 E12 27.50 55.50 E13 30.50 61 50 E14 33.50 6750 E15 3650 73.50 E16 39.50 7950 E17 42.50 85.50 EI8 45.50 91 5O E19 5050 100.50 E20 6050 121 50 E99 - Write for quote N01 TABLE OF CONTENTS IAA Entries 99 STAR Entries 125 Subject Index .-. A-1 Personal Author Index B-1 Contract Number Index C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT - AVAILABLE ON MICROFICHE -» N81-1063«*# FWG Associates. Inc.. Tullahoma. Tenn.-.- NASA ACCESSION PILOT-AIRCRAFT SYSTEM REPONSE TO WIND SHEAR NUMBER r Interim Report Barry S. Turkel and Walter Frost Washington NASA Nov.- -CORPORATE 1980 98 p refs SOURCE TITLE- (Contract NAS8-33458) _, (NASA-CR-3342) Avail: NTIS^ HC A05/MF A01 CSCL04B* The nonlinear aircraft motion and automatic control model is expanded to incorporate the human pilot into simulations of -PUBLICATION AUTHORS- aircraft response to wind to wind shear. The human pilot is DATE described by a constant gains lag filter. Two runs are carried out using pilot transfer functions. Fixed-stick, autopilot, and manned computer simulations are made with an aircraft having CONTRACT -AVAILABILITY characteristics of a small commuter type aircraft flown through OR GRANT- SOURCE longitudinal winds measured by a Doppler radar beamed along the glide slope. Simulations are also made flying an aircraft through sinusoidal head wind and tail wind shears at the phugoid REPORT frequency to evaluate the response of manned aircraft in -COSATI NUMBER- thunderstorm wind environments. S.F. CODE TYPICAL CITATION AND ABSTRACT FROM IAA ~AVAILABLE ON I MICROFICHE AIAA ACCESSION ' A81-10474 tt ^The design of blowing-cooled aircraft electrical NUMBER machines (Voprosy konstruktsii produvaemykh aviatsionnykh elek- tricheskikh mashin). V. I. Naumenko, O. G. Klochkov, and V. V. . 'AUTHORS Bandurin (Akademiia Nauk Ukrainskoi SSR, Institut Elektrodina- TITLE- miki, Kiev, Ukrainian SSR). Tekbnicheskaia Elektrodinamika, July- Aug. 1980, p. 81-87. In Prussian. AUTHOR'S The current status of air-cooled aircraft electrical machines is AFFILIATION reviewed. The possibility of reducing the weight and size of TITLE OF air-cooled machines is discussed, with particular emphasis on the PERIODICAL- design of cooling systems for synchronous ac-generators. B.J. -PUBLICATION DATE Page intentionally left blank Page intentionally left blank V- f AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 134) APRIL 1981 Technical Review, vol. 15, no. 2, 1980, p. 47-58. IAA ENTRIES The Advanced Attack Helicopter (YAH-64) is designed primari- ly as an antiarmor helicopter capable of operating day or night in the nap-of-the-earth environment. This paper provides an aircraft descrip- A81-16551 ff Steady flow past a rectangular wing with tion, and gives attention to the status of test vehicles, flight test circulation that is variable along the span (Statsionarnoe obtekanie results, and ordnance testing. B.J. priamougol'nogo kryla s tsirkuliatsiei peremennoi po razmakhu). N. N. Poliakhov and Z. N. Shesternina. Leningradskii Universitet, Vestnik, Matematika, Mekhanika, Astronomiia, July 1980, p. 85-92. A81-16581 * Shipboard trials of the Quiet Snort-Haul Re- In Russian. search Aircraft /QSRA/. J. L. Martin (NASA, Ames Research Center, A method is proposed for solving the problem of the steady Moffett Field, Calif.) and P. B. Strickland (U.S. Navy, Naval Air Test flow past a plane rectangular wing at low angle of attack with an Center, Patuxent River, Md.). (Society of Experimental Test Pilots, arbitrary distribution of circulation along the span. The spanwise Symposium, 24th, Beverly Hills, Calif., Sept. 24-27, J980.1 Society distribution of density of attached vortices is prescribed in the form of Experimental Test Pilots, Technical Review, vol. 15, no. 2, 1980, of a power series with indefinite coefficients; this makes it possible p. 59-74. 6 refs. to carry out integration along the span in quadratures and to The feasibility of the application of advanced state-of-the-art determine series coefficients from the condition that circulation at high lift STOL aircraft in the aircraft carrier environment was the ends of the wing is equal to zero. Series coefficients are solutions evaluated using the NASA Quiet Short-Haul Research Aircraft (QSRA). The QSRA made repeated unarrested landings and free of a system of Fredholm equations of the second kind. B.J. deck takeoffs from the USS Kitty Hawk while being flown by three pilots of significant different backgrounds. The exercise demonstrat- A81-16578 The implications of current flight control ed that the USB propulsive lift technology presents no unusual research and development. R. C. Ettinger (USAF, Flight Dynamics problems in the aircraft carrier environment. Optimum parameters Laboratory, Wright-Patterson AFB, Ohio). (Society of Experimental for landing the QSRA were determined from the shore-based Test Pilots, Symposium, 24th, Beverly Hills, Calif., Sept. 24-27, program; these proved satisfactory during operations aboard ship. 1980.) Society of Experimental Test Pilots, Technical Review, vol. Correlation of shipboard experience with shore-based data indicates 15, no. 2, 1980, p. 18-37. that both free deck takeoffs and unarrested landings could be The impact of current flight control research and development conducted with zero to 35 knots of wind across the deck of an on present and future aircraft is considered. Attention is given to the development of such systems as fly-by-wire, tactical weapons aircraft carrier the size of the USS Kitty Hawk. B.J. delivery, DIGITAC, control configured vehicle, integrated flight fire A81-16582 Head-Up-Display flight tests. S. J. Monagan control, mission adaptive wing, and wing-in-ground effect. B.J. and R. E. Smith (Calspan Advanced Technology Center, Buffalo, N.Y.). (Society of Experimental Test Pilots, Symposium, 24th, A81-16579 F/A-18 full scale development test. W. H. Beverly Hills, Calif., Sept. 24-27, 1980.) Society of Experimental Brinks (McDonnell Douglas Corp., St. Louis, Mo.). (Society of Test Pilots, Technical Review, vol. 15, no. 2, 1980, p. 75-87. Experimental Test Pilots, Symposium, 24th, Beverly Hills, Calif., HUD flight tests conducted for the United States Navy and Air Sept. 24-27, 1980.) Society of Experimental Test Pilots, Technical Force by the Flight Research Branch of the Calspan Advanced Review, vol. 15, no. 2, 1980, p. 38-46. Technology Center are described. The HUD flight test system The flight envelope of the F/A-18 in the fighter escort includes the NT-33A variable fly-by-wire research aircraft, a program- configuration (two AIM-7s, two AIM-9s, and a 20-mm gun) has been mable HUD, and a workload assessment device. The integration of expanded to 1.9 Mach number in flutter testing, and to zero airspeed the Display Evaluation Flight Test System and the workload during high angle of attack maneuvers. Flutter testing has been assessment device with the NT-33 in-flight simulation aircraft has completed for the fighter escort configuration with the required 15% resulted in an advanced systems research aircraft for USAF and USN or better flutter margin and damping at the most critical flight flight research. This aircraft has proved to be a powerful tool for condition. During high angle of attack testing the aircraft has been investigating the relationships between displays, flying qualities, and flown in dynamic maneuvers to over 90-deg angle of attack and pilot performance and workload. B.J. 35-deg of sideslip with no departure tendencies in the fighter escort configuration. The load factor envelope has been expanded to a A81-16583 Air traffic management enhancement through negative 2.8 gs and a positive 7.6 gs at various speeds and altitudes. new avionics /4-D/. D. A. Moor (Lockheed Corp., Burbank, Calif.). B.J. (Society of Experimental Test Pilots, Symposium, 24th, Beverly Hills, Calif., Sept. 24-27, 1980.) Society of Experimental Test Pilots, A81-16580 Advanced Attack Helicopter /YAH-64/ - Sta- Technical Review, vol. 15, no. 2, 1980, p. 90-93. tus report. J. W. Groulx (Hughes Helicopters, Culver City, Calif.). The first phase of a NASA/Lockheed program for the 1980s is (Society of Experimental Test Pilots, Symposium, 24th, Beverly to expand the current L-1011 Flight Management System descent Hills, Calif., Sept. 24-27, 1980.) Society of Experimental Test Pilots, mode to include the fourth dimension, time. This would enable an 99 A81-16584 L-1011 to make a completely automatic descent (4-D) from cruise A81-16588 * The XV-15 tilt rotor research aircraft. D. C. altitude to arrive at a metering fix within a few seconds of a time Dugan (NASA, Ames Research Center, Moffett Field, Calif.), R. G. allocated by ATC. The initial 4-D descent flight tests of the Erhart (Bell Helicopter Textron, Fort Worth, Tex.), and L. G. prototype system were such that a 2sigma arrival time error Schroers (U.S. Army, Aeromechanics Laboratory, Moffett Field, disposition of 8 sec is believed to be an attainable goal. B.J. Calif.). (Society of Experimental Test Pilots, Symposium, 24th, Beverly Hills, Calif., Sept. 24-27, 1980.) Society of Experimental Test Pilots, Technical Review, vol. 15, no. 2, 1980, p. 168-185. A81-16584 757/767 design considerations for improved The XV-15 tilt rotor has shown good handling qualities in all productivity. T. E. Twiggs (Boeing Commercial Airplane Co., Seattle, modes of flight; in the helicopter mode it allows precision hover and Wash.). (Society of Experimental Test Pilots, Symposium, 24th, agility with low pilot workload. Vibration and noise levels are low; Beverly Hills, Calif., Sept. 24-27, 1980.1 Society of Experimental the conversion procedure is easy, with satisfactory acceleration or Test Pilots, Technical Review, vol. 15, no. 2, 1980, p. 94-113. 7 refs. deceleration. The XV-15 handling demonstrated its potential for In the fall of 1981 and the spring of 1982, flight testing is many civil and military applications. A.T. scheduled to begin on a new series of technology transports, the 757 and the 767. Productivity improvement will be extracted from A81-16684 Sarsat - A rescue system for ships and aircraft various disciplines of the aircraft design; among the technologies (SARSAT • ein Rettungssystem fur Schiffe und Flugzeuge). J. Nauck contributing are weight savings, aerodynamic efficiency, digital (Erno Raumfahrttechnik GmbH, Bremen, West Germany). Nach- electronic reliability and adaptability, and improved cockpit environ- richten Elektronik, vol. 34, Oct. 1980, p. 362-364. In German. ment. These factors are reviewed along with pilot workload The Sarsat satellite is discussed along with alternative orbit plans modification, descent strategies, and ATC compatibility. B.J. for ocean and general emergence services. Emphasis is placed on designing an economical system. A system of satellites in geostation- A81-16585 A cockpit view of advanced airline avionics. R. ary orbit employs 3 satellites and covers 94% of the earth surface. A F. Hanna (American Airlines, Inc., Dallas, Tex.). (Society of system of 8 satellites in polar orbits provides 100% coverage of the Experimental Test Pilots, Symposium, 24th, Beverly Hi/Is,,Calif., earth. A system of satellites in geostationary and polar orbits is also Sept. 24-27, 1980.1 Society of Experimental Test Pilots, Technical examined which overcomes the advantages of the individual system. Review, vol. 15, no. 2. 1980, p. 114-134. A proposal using quasi-polar orbits recommended by IMCO (Inter- Several current and proposed future developments in advanced governmental Maritime Consultative Organization) is illustrated and airline avionics are described. Particular-consideration is given to the compared to a plan with a 57 degree orbit. R.C. ARINC Communications Addressing and Reporting System, the Electronic Flight Instrument System, and the Engine Indicating and A81 -16688 A new system for the study of visual informa- Crew Alerting System. It is suggested that advanced airline avionics tion presentation in aeronautics - GIBI (Un nouveau systeme d'etude will provide: (1) enhanced safety by reducing head downtime and by de la presentation d'informations visuelles en aeronautique - Le providing more timely crew alerting, (2) increased passenger comfort GIBI). J. P. Menu, G. F. Santucci, and C. L. Valot. Medecine by providing better enroute weather update for optimum route Aeronautique et Spatiale, Medecine Subaquatique et Hyperbare, vol. selection, (3) better on-time performance through maintenance 19, 3rd Quarter, 1980, p. 185-187. In French. monitoring for corrective action and dispatch, and (4) improved fuel The GIBI (French acronym for interactive binary image genera- efficiency by displaying real-time performance and navigation data tor) system to be used in the development of electronic cockpit for more effective management. B.J. displays as well as in fundamental research on visual perception is presented. The system makes use of cathode ray tube images A81-16586 The future ATC system as influenced by generated by a calculator-based information system operating in real advanced avionics, S. I. Rothschild (FAA, Washington, D.C.). time through either a shadow mask or a penetration rider scanning (Society of Experimental Test Pilots, Symposium, 24th, Beverly graphics processor, and is capable of reacting to subject responses. It Hills, Calif., Sept. 24-27, 1980.1 Society of Experimental Test Pilots, may be used in flight simulations to determine the essential Technical Review, vol. 15, no. 2, 1980, p. 135-145. parameters for piloting at each stage of the flight and a useful The paper describes current FAA activities underway to attempt symbology in which this information may appear. A.L.W. to determine how the future ATC system should evolve and how the features provided by that future system should tie into near-term developments. Attention is given to activities dealing with national A81-16689 Helicopter alarms - The use of ALAT incident flow planning, the terminal area, navigation, air-ground communica- and accident record cards (Les alarmes en helicopters - Exploitation tions, human factors, and weather. B.J. des fiches d'incidents et d'accidents de I'A.L.A.T.). J. P. Papin and B. Gangloff. Me'decine Aeronautique et Spatiale, Medecine Sub- aquatique et Hyperbare, vol. 19, 3rd Quarter, 1980, p. 188-190. In A81-16587 Development and certification of the Gulf- French. stream III. R. K. Smyth (Grumman Aerospace Corp., Bethpage, Records of helicopter accidents and incidents kept by ALAT are N.Y.). (Society of Experimental Test Pilots, Symposium, 24th, analyzed in order to determine the roles played by on-board alarms. Beverly Hills, Calif., Sept. 24-27, 1980.) Society of Experimental The causes, diagnostic procedures, and crew reactions to 262 Test Pilots, Technical Review, vol. 15, no. 2, 1980, p. 155-167. incidents on various types of helicopters over several years are The paper discusses the development and certification testing of examined. It is pointed out that diagnosis is more often immediate Grumman's new business jet, the Gulfstream III. The G-lll represents when the cause is mechanical and when an alarm is functioning, and an improved version over its predecessor, the G-ll, with a longer that when the diagnosis is immediate, the action taken is most often fuselage, a modern recontoured nose, and a new wing to which has adequate. It is concluded that an improvement in the presentation of been added NASA winglets to control wing-tip airflow and reduce alarms may increase flight safety, particularly as regards the drag due to lift. These new features give the G-lll a 4600 Ib increase determination of the cause of the situation and the utilization of in fuel capacity and increase its range to 3600 nautical miles. During signals. A.L.W. preliminary test flights a phenomenon known as 'aileron tug' occurred as a function of Mach number and lift coefficient causing the need for installation of a row of vortex generators forward of the A81-16712 Sound radiation from a finite length unflanged ailerons. On its first transoceanic flight from Savannah to Hannover, circular duct with uniform axial flow. I - Theoretical analysis. II - the G-lll exhibited no problems and in subsequent tests including Computed radiation characteristics. G. W. Johnston and K. Ogimoto minimum unstick speed and high speed upset maneuvers, met (Toronto, University, Toronto, Canada). Acoustical Society of certification requirements. B.R.K. America, Journal, vol. 68, Dec. 1980, p. 1858-1883. 23 refs. Natural 100 A81-17044 Sciences and Engineering Research Council of Canada Grant No. English Channel, respectively, are discussed as an example of an A-7945. individual entrepreneurial approach to aircraft design. The objectives An analysis of sound radiation from a finite length, unflanged, and guiding principles of the design program are outlined, and the hard wall circular duct with uniform axial flow using the Wiener- sequence of project events is traced from the time of the first Hopf method is presented. The acoustic model simulates the noise conception of a low-velocity man-powered aircraft in 1976 to the radiation from a turbojet aircraft engine in flight at low and medium cross-channel flight of the Gossamer Albatross in June, 1979. thrust levels as in landing or steady cruise flights. It includes the Aircraft performance and aerodynamic design are examined, with diffraction of sound at both ends and its mean convection by the attention given to the available and required power, and the duct and external flow fields; the refraction effects resulting from evolution of aircraft stability and control. Aircraft structures and nonuniform exterior flow fields at the inlet and exhaust under high instrumentation are discussed, and the way in which all the necessary thrust conditions are not included. The finite duct effects are developments came together in the successful flight of the Gossamer quantitatively presented for the case of plane-excitation; the finite Albatross despite turbulence and headwinds is related. A.L.W. duct radiation has length resonance which produces standing waves on either side of the source plane. The diffracted sound waves A81-16939 ;/' Renewal function for any arbitrary period - A interfere in the farfield resulting in a modified radiation directivity Bayesian way. D. D. Bhattacharya (Ministry of Defence, Directorate relative to the semi-infinite duct radiation. AT. of Scientific Evaluation, New Delhi, India). Defence Science Journal, vol. 30, Jan. 1980, p. 17-20. 6 refs. A81-16717 il A case study in aircraft design: The de The usual format on which the consumption data and activity Havilland family of STOL commuter aircraft. R. D. Hiscocks. New for spare parts of a system are available, makes it difficult for the York, American Institute of Aeronautics and Astronautics, Inc., evaluation of the renewal function on the procedure as laid down by 1980. 129 p. 19refs.$15. Cox (1967). The author has, therefore, discussed in this paper a The development of de Havilland STOL commuter aircraft from model through Bayesian Approach as to how in such cases the DHC-1 Chipmunk through the DHC-6 Twin Otter is described. renewal function could be obtained for any period of activity, Special attention is then given to the development of the DHC-7; provided the past experiences are available in the form of a sample preliminary design considerations, aircraft weight, noise, structural information. For a Beta-Prior density for the mean demand rate of philosophy, construction materials, qualification testing, the power- the Poisson demand distribution, the renewal function in its plant, engine mounts, propulsion control, and lateral control, are analytical and asymptotic forms are obtained. (Author) described. Finally, attention is given to the current market for STOL commuter aircraft, and to plans for the DHC-8. B.J. A81-16968 H Inverse problems of controlled flight dynamics - Longitudinal motion (Obratnye zadachi dinamiki upravliaemogo A81-16718 ii Concorde aerodynamics and associated sys- poleta - Prodol'noe dvizhenie). B. N. Petrov and P. D. Krut'ko tems development. J. Rech (Societe Nationale Industrielle Aero- (Moskovskoe Vysshee Tekhnicheskoe Uchilishche, Moscow, USSR). spatiale, Toulouse, France) and C. S. Leyman (British Aerospace, Akademiia Nauk SSSR, Doklady, vol. 255, no. 1, 1980, p. 43-47. In Bristol, England). New York, American Institute of Aeronautics and Russian. Astronautics, Inc., 1980. 104 p. S15. The paper deals with the development of a new approach to the A case study on the innovative aspects of Concorde aerodynam- construction of aircraft control algorithms. The approach is based ics is presented. Attention is given to design objectives, aircraft essentially on the concept of inverse problems of dynamics, aerodynamic layout, flying qualities, performance and noise, and introduced by Petrov, Krut'ko, and Popov (1979). The basic aspects powerplant aerodynamics. B.J. of automatic aircraft control are analyzed on the basis of a nonlinear mathematical model whose equations are written in a system of A81-16719 ;/' A case study on the F-16 fly-by-wire flight velocity coordinates. V.P. control system. C. S. Droste and J. E. Walker. New York, American Institute of Aeronautics and Astronautics, Inc., 1980. 120 p. $15. A81 -16969 # The method of superelements in the dynamics The implementation of the F-16 fly-by-wire system is described of complex structures (Metod superelementov v dinamike slozhnykh with emphasis on the electrical-to-mechanical interface (i.e., the struktur). I. F. Obraztsov, A. S. Vol'mir, and V. N. Terskikh YF-16 control surface actuation system), redundancy, and lightning (Voenno-Vozdushnaia Inzhenernaia Akademiia, Moscow, USSR). protection. The unique flight control system functional features are Akademiia Nauk SSSR, Doklady, vol. 255, no. 1, 1980, p. 59-61. In then discussed, with attention given to AOA/g limiting, high-AOA Russian. roll coordination, roll rate limiter, rudder fadeout, yaw rate limiter, The paper deals with the superelement method, as an extension and manual pitch override. B.J. of the finite element method, capable of treating complex systems with very high computer speed and memory requirements. The A81-16720 ;/' The Grumman Aerospace and Gulfstream coupling of superelements of different orders is demonstrated, using American Gulfstream III case study in aircraft design. L. M. Mead a delta wing configuration as an example. The normal mode vibration (Grumman Aerospace Corp., Bethpage, N.Y.), Ch. Coppi (Gulfstream frequencies of the fuselage and four wing sections are plotted and American Corp., Van Nuys, Calif.), and J. Strakosch (Grumman compared with the experiment. V.P. Aerospace Corp., Bethpage, N.Y.). New York, American Institute of Aeronautics and Astronautics, Inc., 1980. 115 p. S15. A81-17044 H Airline flight departure procedures • Choosing A design evaluation of the Gulfstream III executive jet is between noise abatement, minimum fuel consumption and minimum presented. Attention is given to the ancestry of Gulfstream III and cost. R. E. Jones. Canadian Aeronautics and Space Journal, vol. 26, requirements definition, preliminary design studies and the evolution 3rd Quarter, 1980, p. 181-199. 13 refs. of the Gulfstream III design, and a design description and the A performance computer program was developed to analyze development program of Gulfstream III. B.J. reduced noise takeoff procedures for the B-737 and B-747 aircraft. The I ATA procedure was quieter by 5 dB within 10 nm of the A81 -16721 II The Gossamer Condor and Albatross: A case airport (where noise levels are highest) than the more fuel efficient study in aircraft design. J. D. Burke (AeroVironment, Inc., Pasadena, ATA method which uses 80 Ib less of fuel in a B-737 and 450 Ib less Calif.). New York, American Institute of Aeronautics and Astro- in the B-747. The operational cost of a B-747 using the ATA method nautics, Inc., 1980. 66 p. 20 refs. (AV-R-80/540) S15. for full-power takeoff is higher because of greater maintenance The design and testing of the Gossamer Condor and the charges; a decision basis is proposed for the B-747 which uses IATA Gossamer Albatross, the first human-powered aircraft to complete procedures for heavyweight takeoffs and ATA recommendations for the figure-eight course required for the Kremer prize and to cross the lightweight takeoffs. A.T. 101 A81 17045 A81-17045 H Productivity - The challenge of aircraft and Mach number range of 0.98-1.10. Below this range, the shock is too engine maintenance. P. E. Benham (CP Air, Richmond, British weak to affect the drag; at subsonic flows above this Mach range, the Columbia, Canada). (Canadian Aeronautics and Space Institute, flow over a slender body is described up to the first order by the Annual General Meeting, Vancouver, Canada, May 13, 1980.) linear supersonic theory, achieving the minimal wave drag body of Canadian Aeronautics and Space Journal, vol. 26, 3rd Quarter, 1980, Sears-Haack. It was concluded that axisymmetric bodies with p. 201-208. 7 refs. minimal wave drag at near-sonic speeds can be designed by numerical Several methods of improving maintenance in aircraft operations optimization techniques using a finite difference code for the flow which should produce the most reliable components at lowest costs field computation. At subsonic Mach numbers, the optimum body are explored. The aims of aircraft maintenance include serviceable has a blunt nose and an almost shockless condition. A.T. equipment, on-time flight departures, and higher scheduled aircraft utilization; these goals are limited by high maintenance costs, A81-17049 # Application of fracture mechanics in designing requirements for low fuel consumption, and limited ground support lower wing skin of transport aircraft. V. G. Nanduri (De Havilland capital investment. A successful productivity manufacturing contract Aircraft of Canada, Ltd., Downsview, Ontario, Canada). Canadian negotiated by Canadair and the Internal Association of Machinists Aeronautics and Space Journal, vol. 26, 3rd Quarter, 1980, p. and Aerospace Workers was based on relating work compensation 235-238. and bonuses to schedule improvements and production planning; this An application finite element method of using fracture mechan- method is difficult to apply in airline maintenance because of ics in the design of test panels similar to the lower surface of a unexpected failures and nonroutine types of repair. A computer transport aircraft wing is discussed. The cracked stiffened panel is system for engine planning was developed which comprises a file of assumed to be a composite material with the skin and stiffeners component specifications, an on-line video terminal which displays representing the matrix and fibers; an expression is derived for the all repairs required, and a computer terminal which reviews the net section stress to produce total panel failure. The expression is schedule and priorities. A.T. based on the law of mixtures equation, the notch strength analysis of Kuhn (1967), and the proportional limit of the stress-strain curve as A81-17046 // Today and the future in aircraft wheel and the limiting stress for the stiffeners. Detail designs of a wing bottom brake development. J. P. Ruppe (Bendix Corp., Aircraft Brake and surface and of the narrow 7- and 6-stringer panels are presented; the Strut Div., South Bend, Ind.). (Canadian Aeronautics and Space failure of a 7-stringer panel during a residual strength test is Institute, Annual General Meeting, Vancouver, Canada, May 13, photographically depicted. A.T. 1980.) Canadian Aeronautics and Space Journal, vol. 26, 3rd Quarter, 1980, p. 209-216. A81-17067 Periodically stiffened fluid-loaded plates. I - A review of developments in aircraft wheel and brake design for Response to convected harmonic pressure and free wave propagation. commercial aviation which emphasizes low weight, longer life, and II - Response to line and point forces. B. R. Mace (Southampton, safety is presented. Modern wheels designed by computer models University, Southampton, England). Journal of Sound and Vibration, which simulate stresses from tire contact forces, deflections, and vol. 73, Dec. 22, 1980, p. 473-504. 17 refs. Research supported by strains are discussed, along with thermal analyses of the wheel and the Ministry of Defence (Procurement Executive). brake assemblies. Wheel materials are usually 2014-T6 or T61 forged A formulation for the vibration and sound radiation of aluminum, but Ti, composites, and powder metallurgy Al alloys are fluid-loaded plates periodically stiffened by line supports is presented being considered as alternates. An aircraft brake was also designed by for line and point force excitations. The response to a convected computer simulation to produce a lightweight failure-resistant harmonic pressure is determined by Fourier transforms; at low component; the most significant advance in brake design was frequencies, where the separation of the stiffeners is less than application of steel/ceramet antifriction compositions with increased one-third of the plate wavelength, the stiffened plate behaves like an brake life. It is concluded that future aircraft brakes will be made of equivalent orthotropic plate. At higher frequencies, the input carbon composites of greater wear resistance, high heat storage mobility shows peaks at specific frequencies which can be identified capacity, and strength maintained at elevated temperatures. A.T. with the bounding frequencies of zero propagation zones, and standing waves can be set up on the plate. With further increases in A81-17047 # Optimum selection of main parameters for the frequency, the mobility approaches a value determined by the reverse design of a supersonic military aircraft. T. S. Patel (Indian properties of the structure at the point of excitation. A.T. Institute of Technology, Bombay, India) and C. S. Dixit (Air India, Bombay, India). Canadian Aeronautics and Space Journal, vol. 26, A81-17143 /?' Fuel conservation in the air transportation 3rd Quarter, 1980, p. 218-229. 8 refs. industry - General and operational aspects (II contenimento del Reverse design problem of developing supersonic military consume di carburante nell'industria del trasporto aereo - Aspetti aircraft around a given engine has been dealt with in the present generali ed operativi). A. Schiavo. Ingegneria, Sept.-Oct. 1980, p. paper. Optimum selection of the main parameters has been carried 257-266. 8 refs. In Italian. out for the airplane performing specified mission requirements. Two variants are worked out using two different criteria of evaluation; (1) minimum fuel requirements; and (2) maximum payload capacity. A81-17146 H Aerodynamic design of a ducted propeller - The feasible direction method of M. J. Box for nonlinear constrained Optimization of efficiency (II progetto aerodinamico di un'elica optimization has been used in preparing computer software. The intubata - Ottimizzazione del rendimento). S. de Ponte and A. Baron program developed can be easily modified to incorporate changes in (Milano, Politecnico, Milan, Italy). Ingegneria, Sept.-Oct. 1980, p. constraints, addition of constraints or changes in objective function. 273-278. In Italian. The final results obtained are compared with the geometry of a typical military airplane of the same type and power plant. (Author) A81-17166 H Rolls-Royce engines status report. Aircraft Engineering, vol. 52, Dec. 1980, p. 2-7. A81-17048 # Transonic axisymmetric bodies with minimal The article presents a survey of various Rolls-Royce engines wave drag. Y. Y. Chan, D. J. Jones (National Research Council, High including RB211 Turbofan, Pegasus Vectored-Thrust Turbofan, Speed Aerodynamics Laboratory, Ottawa, Canada), and D. L. Olympus 593 Turbojet, Dart Turboprop, RB 401 Demonstrator and Mundie. Canadian Aeronautics and Space Journal, vol. 26, 3rd Business Jet Engine, Viper Turbojet, Tyne Turboprop, Conway Quarter, 1980, p. 231-234. 10 refs. Turbofan, Gnome Turboshaft Engine, and Turmo III C4. All of the An optimization technique was applied in the design of area engines have undergone extensive testing and are reviewed for their distributions of transport aircraft with minimum wave drag at high individual features. The RB211 Turbofan models have a take-off transonic speeds. The minimal drag bodies were calculated for the thrust of about 50,000 Ib and improved fuel consumption and have 102 A81-17453 been used in the Lockheed L. 1011-1 Tristar, and the Boeing 747. A81-17372 ;/' Formation of solid phase during the heating of The RB211-535, being developed for the new Boeing 757 twinjet jet fuels (Osobennosti obrazovaniia tverdoi fazy pri nagreve reaktiv- airliner is discussed together with the Adour Turbofan model which nykh topliv). V. V. Malyshev and V. A. Astaf'ev. Khimiia i powers the Anglo-French Jaguar supersonic strike/trainer aircraft. Tekhnologiia Topliv i Masel, no. 12, 1980, p. 25-27. 10 refs. In The latter has a take-off thrust of 5,115 Ib. for the Adour Mk. 102 Russian. and of 5,700 Ib for the Adour -56. The major feature of these The mechanisms of tar and sludge formation during thermal engines is a significant increase in reheat thrust. The Olympus 593 oxidation of jet fuels have been investigated under static and Turbo-jet has a take-off thrust of 38,000 Ib and is the most dynamic conditions in the temperature range 120-200 C. It is found extensively tested commercial engine. The Dart Turboprop is a that tar deposits consist of high-molecular compounds whose long-serving commercial gas turbine noted for its fuel economy and solubility and adsorption properties change with increasing tempera- low noise levels. Finally the Gem Turboshaft Engine which powers ture by nonoxidation mechanisms. These compounds are thought to the twin engine Westland Lynx helicopter has a fuel consumption cause the coagulation of the solid phase. Under static conditions, significantly better than similar engines in service. B.R.K. sludge formation is largely determined by the surface oxidation of the fuel. V.L. A81-17167 ,*' Coatings in the aero gas turbine. R. H. Wedge and A. V. Eaves (Rolls-Royce, Ltd., Aero Div., Bristol, England). A81-17373 H Composition of sludge formed in B-3V oil Aircraft Engineering, vol. 52, Dec. 1980, p. 25-29. (Sostav osadkov, obrazuiushchikhsia v masle B-3V). E. A. Kunina, V. The paper discusses sprayed coatings for gas turbine engines, the G. Kuznetsov, G. T. Novosartov, and L. V. Boiko. Khimiia i different problems associated with different parts of the engine, and Tekhnologiia Topliv i Masel, no. 12, 1980, p. 27-29. In Russian. future developments in the use of sprayed coatings and their likely The composition of sludge which precipitates from B-3V oil and impact on cost effectiveness within the gas turbine industry. The is deposited on oil filters and other components of the lubricating traditional metallic coatings such as 'hard' chrome to produce wear systems of gas turbine engines has been investigated by chemical and resistance, copper and tin as soft metals associated with bearings, IR spectral analyses. It is found that filter deposits are formed by cadmium plating for corrosion resistance, and silver plating for Altax, an oxidation product of the antiscoring additive Captax, while anti-seize/anti-fret application are supplemented by 'sprayed' coat- the deposits formed on the hottest components of the system consist ings. The major problems which can arise in gas turbine engines are mostly of additive oxidation products and oxides of the metals of hammer wear (combatted by chromium plating or various plasma the structural components. To reduce the deposits, it is recommend- sprayed carbide coatings), fretting and rubbing wear (combatted by ed to increase the thermal oxidation stability of B-3V oil by means copper-nickel-indium, copper-nickel, aluminum bronze, and alumi- of more effective antioxidation additives. V.L. num bronze-polyester}, rotating seal problems (combatted by sprayed alumina), and high temperatures (combatted by various nickel-chromium alloy sprays). A table is given which shows the A81-17375 tt Joint-laboratory qualification testing of oils various sprayed coatings and their cost effectiveness. Future develop- for gas turbine engines (Mezhlaboratornye ispytaniia masel dlia GTD ments are anticipated in the method of application and components po metodam kvalifikatsionnoi otsenki). R. R. Bureeva, S. E. Krein, of the various sprayed coatings. B.R.K. and G. T. Novosartov. Khimiia i Tekhnologiia Topliv i Masel, no. 12, 1980, p. 41-43. 12 refs. In Russian. Data on the kinematic viscosity, lubricating properties, and A81-17324 # Turbopropeller engine P2L-10S. W. Kordzin- thermal oxidation stability of several aviation oils based on test ski. Technika Lotnicza i Astronautyczna, vol. 35, May 1980, p. 10, results from five different laboratories have been statistically 11. In English and Polish. evaluated for convergence and repeatability using the method of The paper deals with the design, specifications, and performance dispersion analysis. Indices of convergence and repeatability are of a version of the Soviet TWD-10 turboprop engine currently shown to be useful tools for evaluating the accuracy of test methods manufactured in Poland on the basis of a license agreement. The used. V.L. engine is intended for the An-28 STOL aircraft and the PZL Sokol helicopter. Modern time and labor saving methods used in the production of the engine are noted. V.P. A81-17453 Captive carry and free flight rain erosion considerations for reinforced ablative fluorocarbon radome materials. G. F. Schmitt, Jr. (USAF, Materials Laboratory, Wright-Patterson A81-17325 /' The PZL-Sokol - New Polish helicopter. T. AFB, Ohio). SAMPE Journal, vol. 16, Nov.-Dec. 1980, p. 12-16. 6 Chwalczyk. Technika Lotnicza i Astronautyczna, vol. 35, May 1980, refs. p. 33-37. In English and Polish. Experiments were conducted to assess the rain erosion behavior The medium-weight-class helicopter under consideration fits during captive carry and free flight of reinforced ablative plastics between the Soviet helicopters, Mi-2 and Mi-8, as a substitution of used in missile radomes. Forty-eight specimens were mounted on the Mi-4, whose production has been terminated. In the passenger both the left and right sides of a supersonic rain erosion wedge with version of the helicopter, 12 (removable) seats are arranged in a 12 each at the following angles: 13.5, 30, 45, 60 deg and then tested 1.4-m high 3.2 x 1.56 m cabin. The design characteristics and on a Holloman rocket sled track 50,000 feet long with 18,000 feet specifications of the helicopter are examined. V.P. equipped with nozzles for rain simulation at speeds up to Mach 4.0 (4200 fps). The principal materials variables investigated were types of polymer (polytetrafluoroethylene, fluorinated ethylene propyl- A81-17371 ;! Comparative evaluation of the quality of jet ene, polyfluoroalcohol, ethyltetrafluoroethylene), type of reinforce- fuels (Sravnitel'naia otsenka urovnia kachestva reaktivnykh topliv). ment (S-glass, E-glass, AB-312 aluminum borosilicate), amount of A. F. Gorenkov. Khimiia i Tekhnologiia Topliv i Masel, no. 12, 1980, fiber loading (10 to 40 percent by weight), and orientation of fibers p. 21-25. 5 refs. In Russian. (perpendicular to surface, parallel to surface, random). Some of the A methodology is presented for comprehensive evaluation of conclusions show that the fiber reinforced fluorocarbon plastics fuel products which involves (1) selection of the base values of which exhibited the lowest mean-depth-of-penetration at 60 deg quality indices, (2) determination of the relative values of quality were also the best at the 13.5 deg angle; the polytetrafluoroethylene indices by establishing a functional relationship between the actual and polyfluoroalcohol fluorocarbon polymers provide the best and the base value of each index, (3) determination of the weights erosion resistance; and the aerodynamic heating of supersonic free for each of the relative quality indices, and (4) calculation of the flight in combination with erosion conditions at Mach 4.0 change the combined quality index. Evaluation results are given for several fuel rankings of ablative fluorocarbons compared to erosion resistance at grades. V.L. subsonic velocities. B.R.K. 103 A81-17467 A81-17467 Problems of flight mechanics involved in all- The meeting focused on engine technology, drive systems, weather helicopter operation (Flugmechanische Probleme bei der propulsion system operations, and propulsion systems integration. Realisierung des Allwettereinsatzes von Hubschraubern). P. Hamel Papers were presented on contingency ratings, digital control for and B. Gmelin (Deutsche Forschungs- und Versuchsanstalt fiir Luft- helicopter powerplants, the T700 booster stage, advanced transmis- und Raumfahrt, Institut fiir Flugmechanik, Braunschweig, West sion component development and test program, safety considerations Germany). Zeitschrift fur Flugwissenschaften und Weltraum- for drive train design, survey of propulsion system failures resulting forschung, vol. 4, Nov.-Dec. 1980, p. 335-345. 12 refs. In German. in mishaps, failure indication and corrective action for turboshaft In view of the inferior flight mechanical behavior of the engines, and an infrared suppressor for the Black .Hawk helicopter. helicopter, in particular, with respect to military all-weather require- A.T. ments, some major factors influencing the flight mechanical behavior of the pilot/helicopter system are examined. Flight mechanical A81-17502 The impact of contingency ratings on ad- problem areas are elucidated, and the basic flight properties of the vanced turboshaft engine design. A. Brooks (General Electric Co., helicopter that would enable all-weather operation are discussed. Lynn, Mass.). In: Specialists' Meeting on Helicopter Propulsion Methods of optimizing basic helicopter flight characteristics are Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. proposed. V.P. Washington, D.C., American Helicopter Society, 1980. 7 p. A81-17471 The effect of aerodynamic coupling on the An aircraft engine designer's consideration of contingency dynamics of aircraft in fast rolling motion (Einfluss der aerodyna- power ratings of advanced turboshaft engines is presented. It was mischen Kopplung auf die Flugzeugdynamik bei schnellen Roll shown that one engine inoperative requires methods of achieving bewegungen). G. Sachs and W. Fohrer (Miinchen, Hochschule der short time horsepower (SHP) increments of 10-20%; large increases Bundeswehr, Neubiberg, West Germany). Zeitschrift fur Flugwissen- in SHP (above 20%) for contingency power will be limited by schaften und Weltraumforschung, vol. 4, Nov.-Dec. 1980, p. compressor capability and local high temperatures leading to hot 379-388. 28 refs. In German. section hardware failures. A.T. The paper deals with the effects of coupling of longitudinal and lateral aerodynamic characteristics on the dynamics of rolling A81-17503 A simple combustor system for a small gas aircraft. The aerodynamic coupling considered is caused by unsym- turbine engine. G. Opdyke, Jr. and B. C. Forbes (Avco Corp., Avco metric flow conditions resulting from sideslipping where rolling Lycoming Stratford Div., Stratford, Conn.). In: Specialists' Meeting moments due to angle-of-attack and pitching moments due to angle on Helicopter Propulsion Systems, Williamsburg, Va., November 6-8, of sideslip are of particular significance for the problem addressed. It 1979, Technical Papers. Washington, D.C., Amer- is shown that the attainable rate of roll is significantly influenced and ican Helicopter Society, 1980. 9 p. 12 refs. that marked effects on stability are possible. Furthermore, it is The design of a simple, low cost annular combustor, based on a shown that aerodynamic coupling can cause au tor o tat ion (i.e., a unique aerodynamic mixing concept, is described in terms of its rolling motion without aileron forcing moments). The results are mechanical simplicity, versatility in the use of different fuel injection derived using simplified relations and complete six-degree-of-freedom systems, and its demonstrated performance characteristics. The calculations. (Author) design, called a circumferentially stirred combustor, incorporates a primary zone flame stabilization method which results in an inexpensive shape for the combustor liner and a reduction of the A81-17472 A wall interference analysis (Zur Ermittlung number of fuel injectors to about one half that normally used for a von Wandinterferenzen). J. Barche. Zeitschrift fur Flugwissenschaf- swirl stabilized annular primary zone design. This circumferentially •ten und Weltraumforschung, vol. 4, Nov.-Dec. 1980, p. 389-396. 6 stirred combustor design has been applied to helicopter engine refs. In German. models and to advanced shaft and fan engines. (Author) In the present paper, an attempt is made to apply theoretical experience to the problem of correcting for the wall effect in wind A81-17504 Digital control for helicopter powerplants. D. tunnels. A method based on Green's theorem is proposed, in which A. Caine (Lucas Industries, Inc., Lucas Aerospace Div., Englewood, correction for the wall effect is made from the interference signals N.J.) and S. Janik (Avco Corp., Avco Lycoming Stratford Div., generated by a body situated in the proximity of the wall. Because of Stratford, Conn.). In: Specialists' Meeting on Helicopter Propulsion this location, the body itself does not figure in the calculations. The Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. only requirement of the method is that the flow be attached at the Washington, D.C., American Helicopter Society, wall (i.e., that the interference field may be described by potential 1980. 16 p. theory). V.P. Full-authority electronic control of helicopter engines using digital large scale integration technology is described. The control A81-17488 The effect of cyclic loading on the apparent uses a 12-bit complementary metal-oxide semiconductor micro- cleavage fracture toughness of 1Cr-Mo-V rotor steel. I. Roman, K. processor as a compromise between the 8-bit and 16-bit systems, Ono (California. University, Los Angeles, Calif.), and A. S. Tetelman. requiring low electrical power consumption. The software logic, the Engineering Fracture Mechanics, vol. 14, no. 1, 1981, p. 155-159, interfacing of the digital system with the powerplant and the 161-163. 19 refs. Research supported by the Electric Power Research airframe by optical serial links, and self-diagnostics methods are Institute. discussed. A.T. A significant increase in the cleavage fracture toughness of 1Cr-Mo-V rotor steel due to cyclic loading was observed. A new A81-17505 The digital control system as part of an model that is capable of predicting and explaining the observation is integrated accessory fit for future engines. M. P. Perks and T. G. proposed. The model combines macroscopic fracture criteria with Morton (Rolls-Royce, Ltd., Aero Div., Leavesden, Herts., England). the assumption that transient flow properties of a material in the In: Specialists' Meeting on Helicopter Propulsion Systems, Williams- cyclic plastic zone can be represented by those of the material burg, Va., November 6-8, 1979, Technical Papers. subjected to macroscopic low cycle fatigue under fully reversed Washington, D.C., American Helicopter Society, 1980. 12 p. strain control. (Author) The paper suggests that the traditional approach of designing the control system in isolation from the other accessories on a gas A81-17501 Specialists' Meeting on Helicopter Propulsion turbine engine may not provide the most cost effective total solution Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. for an engine having a digital control system. It is considered that the Meeting sponsored by the American Helicopter Society. Washington, integrity of the digital control can be maintained while providing D.C., American Helicopter Society, 1980. 239 p. $18. additional functions not associated with its prime control task. This 104 A81-17514 could allow the development of advanced monitoring systems to tion with the gear tests, three rolling bearing materials, AMS 6444 minimize life cycle costs and achieve maximum aircraft utilization. (CEVM 52100), AMS 6491 (DVM M-50), and silicon nitride will be The application of these principles to helicopter engines is discussed compared. Additionally, an input spiral bevel pinion with integral and an arrangement proposed which could provide substantial ball bearing inner races and a minilube system will be evaluated. benefits both to the helicopter pilot and to the ground crew. Pilot (Author) workload would be substantially reduced by advising him of engine or aircraft management factors on a 'need to know' basis. Operators A81-17510 Safety considerations for helicopter drive would benefit from regular information on the operational status of systems of the 1980s. H. Ferris (FAA, Los Angeles, Calif.). In: the engines. (Author) Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. A81-17506 The T700 booster engine. A. Brooks (General Washington, D.C., American Helicopter Society, 1980. 8 p. Electric Co., Lynn, Mass.). In: Specialists' Meeting on Helicopter The impact of helicopter drive systems on safety is reviewed. Propulsion Systems, Williamsburg, Va., November 6-8, 1979, Techni- Problems included the inability to estimate drive system loads, cal Papers. Washington, D.C., American Helicop- incorrect dynamic analysis for fatigue, failure to design for fatigue by ter Society, 1980. 7 p. minimizing stress raisers, and inadequate lubrication and cooling. The T700 booster engine which provides greater horsepower by Recommendations are made for manufacturing and testing of gears, using a high tip speed transonic axial compressor combined with a bearings, seals, fasteners, housings, couplings, and driveshafts. A.T. moderate pressure ratio centrifugal compressor resulting in high ratio and engine efficiency is described. The engine RDT&E costs were A81-17511 Helicopter propulsion system development low; the problem of matching the discharge flow of the constant rpm and qualification. V. R. Edwards (U.S. Army, Propulsion and Power booster stage with the variable flow requirement of the core engine Div., St. Louis, Mo.). In: Specialists' Meeting on Helicopter Propul- compressor is discussed. AT. sion Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. Washington, D.C., American Helicopter A81-17507 Advanced transmission component develop- Society, 1980. 8 p. 5 refs. ment and test program. P. C. FitzGerald and G. F. Gardner (United The U.S. Army programs for developing helicopter propulsion Technologies Corp., Sikorsky Aircraft Div., Stratford, Conn.). In: systems and relating them to the total aircraft weapon arrangement Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg, are described. Turbine engines provided large reductions in weight Va., November 6-8, 1979, Technical Papers. and their turboshaft systems reduced fuel consumption; a new Washington, D.C., American Helicopter Society, 1980. 14 p. specification included requirements for polar moments of inertia, The Advanced Transmission Components Investigation Program torsional spring constants, sand and dust ingestion, and provisions for for future helicopters is analyzing stainless steel fabricated main low cycle fatigue and stress rupture. The airframe design handbook transmission housings, advanced thrust carrying cylindrical roller specifies engine circumferential design limits, rotor blades, and bearings, and a high contact ratio buttress tooth form gear made of a fast-acting control devices for rapid aircraft maneuvers. A.T. new CBS 600 low alloy steel. High temperature gearbox operation will be designed to eliminate the oil cooler; a finite element model was used to determine stainless steel housing thicknesses and the rib A81-17512 Development and operational flight test of the structure for the crash load design criteria. A.T. model 250-C28B gas turbine engine. F. J. Schweibold (General Motors Corp., Detroit Diesel Allison Div., Indianapolis, Ind.). In: A81-17508 Drive system development for the 1980's. J. Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg, W. Lenski, Jr. and J. C. Mack (Boeing Vertol Co., Philadelphia, Pa.). Va., November 6-8, 1979, Technical Papers. In: Specialists' Meeting on Helicopter Propulsion Systems, Williams- Washington, D.C., American Helicopter Society, 1980. 8 p. burg, Va., November 6-8, 1979, Technical Papers. The development and flight testing of the 250-C28B gas turbine Washington, D.C., American Helicopter Society, 1980. 12 p. 9 engine installed in a 206L1 helicopter are described. The tests were refs. Army-sponsored research. made for initial engine/drive train stability, response characteristics, The design and testing of advanced helicopter transmission compressor surge margins, water/snow ingestion capabilities, and components including high-speed tapered roller bearings, integrated relight system operation. Mission endurance profiles were established bearings and gears, high-speed seals, and high-modulus composite along with requirements for air bleeds, ground and air starts, and gear housings are described. Integral-shaft inner races are being full-authority electronic fuel controls. A.T. developed for high speed bearings, and means of improving internal oil flow for greater tolerance to oil interruption are designed. The assembly weight, number of bearings, faying surfaces, oil flow rates, A81-17513 A survey of propulsion systems' malfunc- and equipment test life are compared for current and advanced tions/failures resulting in helicopter mishaps. L. T. Burrows (U.S. transmission systems. A.T. Army, Applied Technology Laboratory, Fort Eustis, Va.). In: Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg, A81-17509 Development of helicopter transmission com- Va., November 6-8, 1979, Technical Papers. ponents for the 1980s. R. A. Battles (Bell Helicopter Textron, Fort Washington, D.C., American Helicopter Society, 1980. 6 p. Worth, Tex.). In: Specialists' Meeting on Helicopter Propulsion A survey of propulsion systems malfunctions/failures (M/F) was Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. based on the record of four Army helicopter models during Washington, D.C., American Helicopter Society, 1971-1978. The analysis included power plants, power transmissions, 1980. 8 p. 9 refs. Army-supported research. lubrication, fuel, and instrumentation; the tail rotor gearbox, the New components and materials are being evaluated for applica- intermediate/combiner gearbox, and drive shafting were evaluated in tion to the next generation of helicopter transmissions. Three types the power train subsystems. Component M/F histories relating to of involute gears • standard spur, high contact ratio (HCR) spur, and helicopter mishaps are presented, noting that relatively insignificant double-helical (D-H) - are to be evaluated in direct comparison tests. components have been a continuing cause of mishaps. M/F occur- These tests will evaluate the following parameters: noise, efficiency, rence can be reduced by proper design and manufacturing practices, scoring, pitting, bending, and loss-of-lubricant operation. The test together with adequate maintenance during the life of the helicopter. program is not to be concluded until early 1981; however, calculated A.T. test results are discussed. All three types of gears are made of Carpenter EX-00053, a new, high-temper-resistant, air-hardening, A81-17514 Issues regarding Army turboshaft engines carburizing steel. The double-helical sun and planet gears are made in diagnostics and condition monitoring. G. W. Hogg (U.S. Army, one piece by shaping, shaving, carburizing, and honing. In conjunc- Applied Technology Laboratory, Fort Eustis, Va.). In: Specialists' 105 A81-17515 Meeting on Helicopter Propulsion Systems, Williamsburg, Va., dynamic simulation based on steady state matching deck perfor- November 6-8, 1979, Technical Papers. Washing- mance for analyzing specific interface problems, including transient ton, D.C., American Helicopter Society, 1980. 15 p. loss in compressor surge margin, is demonstrated. (Author) A review of Army helicopter diagnostic methods, condition monitoring equipment, and turboshaft engine maintenance is A81-17518 Is the engine helicopter-worthy. A. G. Attridge presented. Engine maintenance by modules detects malfunctions, (Bell Helicopter Textron, Power Plant Design Group, Fort Worth, providing leadtime for repair and reducing secondary damage; it Tex.). In: Specialists' Meeting on Helicopter Propulsion Systems, produces data for life-limited hardware tracking, determines opera- Williamsburg, Va., November 6-8, 1979, Technical Papers. tional readiness, and enhances safety. Technological improvements Washington, D.C., American Helicopter Society, 1980. have been utilized in engine gas path determinations, oil monitoring, 9 p. vibration signature analysis, and application of electronic micro- Is the engine helicopter-worthy is a question posed most miniaturization for analyzing and displaying diagnostic data. A.T. frequently at the beginning of every new design program. This paper discusses some of the difficulties encountered in the installation of A81-17515 Failure Indication and Corrective Action for the engine in terms of effects on airframe hardware. The Bell turboshaft engines. A. D. Pisano (General Electric Co., Aircraft Helicopter Textron Models 214A and 214ST are used as examples of Engine Group, Lynn, Mass.). In: Specialists' Meeting on Helicopter current single- and twin-engine technology. (Author) Propulsion Systems, Williamsburg, Va., November 6-8, 1979, Techni- cal Papers. Washington, D.C., American Helicop- A81-17519 Advanced technology turboshaft IR suppres- ter Society, 1980. 10 p. sion. F. Husted (U.S. Navy, Naval Air Propulsion Center, Trenton, In order to prevent loss of power modulation capability in the N.J.), J. F. Hurley, and J. N. Dale (Avco Corp., Avco Lycoming event of a failed engine control sensor, an automatic in-flight Failure Stratford Div., Stratford, Conn.). In: Specialists' Meeting on Helicop- Indication and Corrective Action (PICA) strategy is developed for ter Propulsion Systems, Williamsburg, Va., November 6-8, 1979, advanced turboshaft helicopter applications. PICA provides for both Technical Papers. Washington, D.C., American the detection of a failed sensor and the generation of the best Helicopter Society, 1980. 8 p. estimate of the failed signal which can then be used to provide The development and testing of a passive IR suppression system continuity of stable engine control. The technical basis of PICA is a for an advanced technology turboshaft engine are described. The constant gain extended Kalman filter. The PICA structure consists of exhaust plume gas radiation and exhaust ducting hot metal radiation a nonlinear model of the turboshaft engine along with update logic were analyzed for all aspect and zenith angles; engine power losses to force the model to track the actual engine behavior. Utilizing the were minimized by a suppressor feature which permits full power results of extensive computer simulations with an advanced turbo- recovery in permissive flight zones. The suppressor utilizes turbine shaft engine, the T700-GE-700, it is shown that stable engine control exhaust gas energy to pump plume dilution and wall cooling air; a can be maintained in the presence of multiple sensor failures. maximum plume and hot metal radiation suppression is provided (Author) with a minimum power loss by a rectangular vane-vane configuration. Power loss data are presented in terms of increased back pressure on A81-17516 Review of engine/airframe/drive train dynamic the engine, and metal skin temperatures are given in the form of interface development problems. W. J. Twomey (United Tech- metal cooling effectiveness. A.T. nologies Corp., Sikorsky Aircraft Div., Stratford, Conn.). In: Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg, Va., November 6-8, 1979, Technical Papers. A81-17520 General Electric infrared suppressors for the Washington, D.C., American Helicopter Society, 1980. 11 p. 6 refs. Black Hawk helicopter. M. C. Harrold (General Electric Co., Aircraft Grant No. DAAJ02-77-C-0037. Engine Group, Lynn, Mass.). In: Specialists' Meeting on Helicopter The coupled interaction between two or more helicopter Propulsion Systems, Williamsburg, Va., November 6-8, 1979, Tech- subsystems has often been the source of vibration problems. This nical Papers. Washington, D.C., American Heli- paper gives a review of Sikorsky experience with such problems over copter Society, 1980. 14 p. the past twenty years of developing gas turbine powered helicopters. A cruise operation infrared (IR) suppressor has been used in This review is part of an overall Government effort to accumulate Black Hawk helicopter propulsion systems to counter heat-seeking data which will eventually lead to solutions of generic problems of missiles. The design includes suppressor core, transition duct, nacelle this type. The problems presented include forced vibration problems, ram inlet, rear seals, and inlet particle ducting system; they operate self-excited vibrations, and a transient response problem. Eighteen on ram pressure in forward IR signature for a cruise velocity of 4000 problems are sumarized and grouped according to type. Five of the ft altitude, 95 F ambient temperature, with a 9-hp maximum problems are described in some detail. Recent trends in problems are horsepower loss per engine over an unsuppressed engine configura- discussed. Recommendations are made for future analytical/testing tion. . A.T. efforts to achieve an improved understanding of interfacing dynamic problems and potential solutions. (Author) A81-17521 Exhaust gas reingestion measurements. B. Turczeniuk (Boeing Vertol Co., Philadelphia, Pa.). In: Specialists' A81-17517 Engine-airframe transient compatibility - Meeting on Helicopter Propulsion Systems, Williamsburg, Va., Analysis and test. J. R. Alwang (Boeing Vertol Co., Philadelphia, November 6-8, 1979, Technical Papers. Washing- Pa.). In: Specialists' Meeting on Helicopter Propulsion Systems, ton, D.C., American Helicopter Society, 1980. 12 p. Williamsburg, Va., November 6-8, 1979, Technical Papers. Results of flight tests to measure the magnitude and effects of Washington, D.C., American Helicopter Society, 1980. engine exhaust gas reingestion and inlet pressure distortion are 9 P. presented. The tandem rotor CH-47 and single rotor YUH-61A This paper discusses dynamic analysis and test requirements helicopters were flown with instrumented engine inlets using related to engine-airframe compatibility in two areas: drive system fast-response probes. A wide range of flight maneuvers were torsional stability and transient response. Prediction of stability evaluated, including operating in and out of ground effect, flares, characteristics using linear techniques and correlation with experi- hovering turns, lateral and rearward flight. The dynamic inlet air mental data are reviewed. Control testing, leading to determination temperature and pressure patterns, time histories, and variation of of worst-case conditions, is presented with an aircraft flight test basic engine parameters during exhaust reingestion are provided. The procedure for providing an accurate evaluation of propulsion system effect of instrumentation time constant on the maximum inlet stability. The importance of developing a nonlinear component-by- temperature rise is discussed. Also shown is the effect of an inlet component engine simulation for optimizing control functional screen on pressure distortion. Conclusions are drawn as to the use of configurations and transient schedules is emphasized. Use of a this data to establish turbine engine compressor stall margin 106 A81-17802 requirements needed to avoid experiencing problems with the A81-17656 Laminar boundary layer on swept-back wings engine/helicopter integration. (Author) of infinite span at an angle of attack. I. G. Brykina, E. A. Gershbein, and S. V. Peigin. (Akademiia Nauk SSSR, Izvestiia, Mekhanika A81-17522 ft The supercritical profile of the supercritical Zhidkosti i Gaza, May-June 1980, p. 27-39.) Fluid Dynamics, vol. wing (Superkritische Profile - Superkritische Fliigel). O. Wagner 15, no. 3, Nov. 1980, p. 344-354. 24 refs. Translation. (Miinchen, Technische Universitat, Munich, West Germany). Luft- In the present paper, the compressible boundary layer flow on und Raumfahrt, vol. 1, 4th Quarter, 1980, p. 105, 106, 108, 109. 10 swept wings of infinite span is studied for various angles of attack refs. In German. under the assumption of an impermeable or BLC wing surface. A This paper discusses the profile wing design for supercritical first-approximation analytical solution is obtained (also for axisym- structures. Emphasis is placed on the flow of air surrounding the metric flow) by an integral method of successive approximations. wing and variations in flow fields are examined. Modifications to the Asymptotic solutions of the boundary layer equations are obtained profile for flight below transonic levels are presented that increase for large values of the BLC parameter. V.P. the uplift pressure and permit the achievement of critical Mach numbers on the order of 0.85. The uplift pressure along the upper A81-17735 ,4 Experimental investigations on shock- side of the profile is compared for a classical and a Peaky profile. A associated noise. D. Ma, P. Li, G. Dai, and H. Wang (Academia Sinica, comparison of classical and supercritical wing cross sections indicates Acoustics Institute, Peking, Communist China). Sc/entia Sinica, vol. a flatter upper side, a larger nose radius, and a thicker profile to the 23, Oct. 1980, p. 1237-1246. 13 refs. supercritical wing. R.C. Shock-associated noise from a choked airjet produces sound fields and spectra which vary widely with different nozzles and pressure ratios between 2 and 8. The overall sound pressure levels in A81-17525 ti Aerial surveying of small areas from a small the direction perpendicular to the jet show deviations of the sound remotely controlled drone (Aerofotos'emka malykh uchastkov s pressure level from turbulent noise at the ratio of 2, rising to 20 dB distantsionno upravliaemogo bespilotnogo mini-nositelia). A. G. at ratios above 3, and then remaining constant up to the ratio of 8.5. Vanin. Geodeziia i Kartografiia, Nov. 1980, p. 55-58. In Russian. Expressions are derived for screech frequency and peak frequency of Some aspects of the automation of aerial surveying are wide-band shock-associated noise which agree with experimental discussed. Data obtained in West Germany with radio-controlled data; significant dips are observed in the frequency spectra of a model aircraft and helicopter, using a 6 by 6 cm photogrammetric composite jet noise at a specific pressure ratio which results from an camera are examined. V.P. interference effect between wide-band and turbulent noises. A.T. A81-17741 ft Variational principles and generalized varia- A81-17548 ft One-dimensional considerations concerning tional principles for the hybrid aerodynamic problem of airfoil the stability behavior of inlet diffusers for supersonic aircraft cascades on an arbitrary stream sheet of revolution. G. Liu (Shanghai (Eindimensionale Betrachtungen zum Stabilitatsverhalten von Ein- Institute of Mechanical Engineering, Shanghai, Communist China). laufdiffusoren fur Qberschall-Flugantriebe). H.-L. Weinreich. Darm- Sc/entia Sinica, vol. 23, Oct. 1980, p. 1339-1347. 5 refs. stadt, Technische Hochschule, Fachbereich Maschinenbau, Dr.-Ing. In this paper a hybrid aerodynamic problem of airfoil cascades is Dissertation, 1979. 192 p. 77 refs. In German. suggested and formulated, being a unification as well as a generaliza- The thesis deals essentially with the nonlinear interaction tion of the conventional direct and inverse problems, so as to meet between inlet and diffuser in the case of frictionless flow in a long various requirements of turbomachinery blade design. A new connecting channel. Under the assumption that the inlet length is universal function - the moment function - is also introduced. Then, much smaller than the total length, it is shown that isolated buzz two families of variational principles and generalized variational cycles can appear even below the stability boundary if throttling is principles are established for the hybrid problem of type A, in which too nonuniform, while regular (normal) pulsations set in when a along some part of the airfoil contour velocity distribution is certain throttle level is exceeded. The transient process leads swiftly prescribed, while along remainder contour geometry is given. In to a well-established cycle. Throttling just above the stable inter- order to facilitate the treatment of a variety of boundary conditions action boundary gives rise to vigorous pulsations. V.P. all of them have been converted into natural ones, and use is made of the artificial interfaces. This paper is primarily aimed at providing a broader and rigorous theoretical basis for introducing the finite A81-17577 If Principle for the design of hybrid control element method and other variational methods into computational systems for passenger transport systems (Printeip postroeniia gibrid- aerodynamics of turbomachinery. (Author) nykh sistem upravleniia passazhirsko-transportnykh samoletov). I. A. Mikhalev and B. N. Okoemov. Priborostroenie, vol. 23, Oct. 1980, p. 45-50. In Russian. A81-17801 Recent selected papers of Northwestern Poly- Methods for the design of onboard hybrid control and process- technical University. Parts 1 & 2. Xian, Shaanxi, People's Republic of ing systems for passenger aircraft are described. The hybrid automat- China, Northwestern Polytechnical University, 1979. Pt. 1, 203 p.; ic control system is designed as a quasi-continuous system whose pt. 2, 243 p. In English and Chinese. characteristics are close to those of an initial optimal continuous system. The aircraft control algorithm is constructed on the basis of Papers are presented on such topics as the finite difference a law for the control of continuous systems, which are synthesized computation of steady transonic potential flow past aircraft, the by a method of optimal continuous linear systems. P.T.H. design of subcritical airfoils, the synthesis of array antennas of high directivity and low sidelobe, the calculation of the integral-type flexure hinge assembly of dynamically tuned gyroscopes, the A81-17622 Stationary displacement of a body by a shock structural analysis of fuselages with cutouts, and the solidification wave. E. I. Zababakhin and IM. E. Zababakhin. (PMTF - Zhurnal characteristics of superalloys. Also considered are the matrix analysis Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, Mar.-Apr. 1980, p. of wings, pulsed spray transfer arc welding, color discrimination by a 135-137.) Journal of Applied Mechanics and Technical Physics, vol. color-picture reader, the response of a turbojet engine to inlet 21, no. 2, Sept. 1980, p. 269, 270. Translation. pressure distortion, and the acoustic instability of solid propellant The conditions where a streamlined body will travel together rocket engines. B.J. with a shock front, on which it floats like a cork in water, are examined. It is shown that the requirements concerning the A81-17802 ft Finite difference computation of the steady aerodynamic quality of the body's configuration are not difficult to transonic potential flow around airplanes. S. Luo, Y. Zhen, H. Qian, meet. V P and D. Wang. In: Recent selected papers of Northwestern Polytechni- 107 A81-17803 cal University. Part 1. Xian, Shaanxi, People's A procedure is described for the design of total-temperature Republic of China, Northwestern Polytechnical University, 1979, p. thermocouple probes for the investigation of turbojet exhaust gas; 1-14. 5 refs. In Chinese, with abstract in English. the aim of the design is to achieve a minimum steady-state error The velocity potential equation for steady transonic flow past under given operating conditions. The gas velocity in the sheath, i.e., . an aircraft is solved by mixed finite difference schemes. The finite the optimum internal flow velocity, is determined on the principle difference equations for the velocity potential are solved by the line that the sum of the radiation error, the conduction error, and the relaxation method. The influence of the wing on the horizontal tail is velocity error is a minimum under give'n operating conditions. By computed taking into account the deflection of the wing wake using the optimum internal flow velocity, the diameter of the vortices. Two numerical examples are considered and results agree exhaust hole is determined and the layout of the probe is designed. fairly well with wind tunnel test results: (1) a wing-fuselage- Verification tests have shown that the error of the thermocouple horizontal tail-vertical tail configuration at freestream Mach numbers probe reaches a minimum when the diameter of the exhaust hole is of 0.25 and 0.95; and (2) a wing-fuselage configuration at a 1.4mm. B.J. freestream Mach number of 1.05 and an angle of attack of 2.2 deg. B.J. A81-17815 H The automatic matrix force method and tech- niques for handling more complex computations with given comput- A81-17803 H Second order approximation theory of an er capacity. Q. Yang. In: Recent selected papers of Northwestern arbitrary aerofoil in incompressible potential flow. C. Lin. In: Recent Polytechnical University. Part 1. Xian, Shaanxi, selected papers of Northwestern Polytechnical University. Part 1. People's Republic of China, Northwestern Polytechnical University, Xian, Shaanxi, People's Republic of China, 1979, p. 177-188. 10 refs. In Chinese, with abstract in English. Northwestern Polytechnical University, 1979, p. 15-25. 11 refs. In A detailed description is given of the automatic matrix force Chinese, with abstract in English. method, a numerical method of aircraft structural analysis. It is A novel method for calculating incompressible potential flow shown that the method can be applied to complex structures with a around an airfoil is presented. The region outside an arbitary airfoil is high degree of redundancy. B.J. conformally transformed into the region outside a unit circle. The transformation functions are expanded into ascending power series, and only those terms up to and including the second order are A81-17816 H Structural analysis of fuselages with cutouts retained. The method gives second-order perturbation solutions by finite element method. S. Ge, C. Sun, X. Tang, and T. Ye. In: which are uniformly valid throughout the flow field. Analytical Recent selected papers of Northwestern Polytechnical University. formulas are given. B.J. Part 1. Xian, Shaanxi, People's Republic of China, Northwestern Polytechnical University, 1979, p. 189-200. 6 A81-17804 fi Aerodynamic calculations and design of sub- refs. In Chinese, with abstract in English. critical aerofoils. C. Lin. In: Recent selected papers of Northwestern A finite element procedure is developed for the structural Polytechnical University. Part 1. Xian, Shaanxi, analysis of fuselages with cutouts. It is shown that, when the elastic People's Republic of China, Northwestern Polytechnical University, behavior of the bulkhead is considered, the normal stresses exhibit a 1979, p. 27-35. 20 refs. In Chinese, with abstract in English. three-wave circumferential variation. Calculated displacements along Methods are developed for the analysis of the direct problem the length of the fuselage are in agreement with full-scale test data. and inverse problem of airfoils in subcritical potential flow. The B.J. direct problem (i.e., the prediction of pressure distribution for a given airfoil at a given angle of attack) is treated on the basis of a A81-17818 H The matrix analysis of wings. Y. Xu, R. Zhu, compressibility correction in the second-order approximation theory. J. Jiang, and Y. Cai. In: Recent selected papers of Northwestern It is shown that formulas obtained for the direct problem can be Polytechnical University. Part 2. Xian, Shaanxi, combined with the Newton iteration method to treat the inverse problem, i.e., the determination of airfoil geometry and angle of People's Republic of China, Northwestern Polytechnical University, attack for a given pressure distribution. B.J. 1979, p. 41-62. In Chinese, with abstract in English. A matrix analysis is presented in which plate-beam wing structures are simplified either as plane stress or plate bending A81-17805 " An aerodynamic design method for transonic models. In addition to applying the element stiffness matrix of plane axial flow compressor stage. F. Zhu, X. Zhou, S. Liu, and F. Fan. In. stress, the paper introduces a triangular element matrix for laminated Recent selected papers of Northwestern Polytechnical University. plates and an element stiffness matrix for beams of axially variable Part 1. Xian, Shaanxi, People's Republic of rectangular cross section. Two general computer programs are China, Northwestern Polytechnical University, 1979, p. 37-49. 9 refs. presented, and numerical results are given for the deflections and In Chinese, with abstract in English. stresses of a wing consisting of plates and beams, a honeycomb-core A three-dimensional aerodynamic design method for the tran- wing, and a solid wing. B.J. sonic axial flow compressor stage is described. The method consists of three main parts: (1) the mean S2 streamsurface calculation, (2) the approximate calculation of the SI streamsurface of revolution, A81-17824 j A preliminary experimental investigation of and (3) the definition of the blade element on the conical surface the response of a turbojet engine to inlet pressure distortion. F. and the stacking of blade airfoil sections. The method is unusual in Chen, D. Tang, Z. Hu, W. Li, J. Yu, X. Wu, J. Zhao, Q. Lin, Z. Wang, that the stations for calculating the S2 streamsurface are curves, and and S. Liu. In: Recent selected papers of Northwestern Polytechnical particularly in that the airfoil parameters of the blade are calculated University. Part 2. Xian, Shaanxi, People's on a plane tangent to the approximate streamsurface of revolution. Republic of China, Northwestern Polytechnical University, 1979, p. On this tangential plane, two-dimensional flow is used as the basic 169-185. 8 refs. In Chinese, with abstract in English. model to calculate the Mach wave system on the suction surface of Preliminary results are presented concerning the influence of the cascade entrance region. B.J. inlet pressure distortion on the characteristics and instability of the axial compressor of a turbojet engine. Experiments were performed on the test bed of a turbojet engine with a 9-stage compressor whose A81-17807 H An optimum design procedure of total- first stage is transonic. It is found that the inlet pressure distortion temperature thermocouple probes. C. Liu and J. Zhao. In: Recent affects not only the stall line but also the shape and position of selected papers of Northwestern Polytechnical University. Part 1. constant speed lines of the compressor. Inlet pressure distortion Xian, Shaanxi, People's Republic of China, shifts the speed lines toward the left and flattens them. The effect of Northwestern Polytechnical University, 1979, p. 65-74. 11 refs. In the decrease in the first stage nozzle exit area is similar to that of Chinese, with abstract in English. inlet pressure distortion. B.J. 108 A81-17954 A81-17825 H The measurement and analysis of station 23-mm Gatling-style rotary cannon and nine weapons stations parameters of a turbojet engine. Q. Dong, J. Zhao, S. Liu, X. Wu, Z. containing a total of 16 1,102-lb bombs. The Su-24 is capable of Hu, M. Cong, Q. Lin, Z. Wang, S. You, and L. Zheng. In: Recent interdiction missions far beyond the PLOT (Front Line of Troops) selected papers of Northwestern Polytechnical University. Part 2. and is most effective in a HI-LO-HI profile from its Soviet bases. Xian, Shaanxi, People's Republic of China, Fencer is being delivered at a production rate of 8-9 monthly, and Northwestern Polytechnical University, 1979, p. 187-201. 11 refs. In represents an important advance in Soviet attack capability. B.R.K. Chinese, with abstract in English. The flow field parameters at characteristic stations of a turbojet A81-17841 # An experimental study on kerosene-hydrogen engine were measured under design operating conditions. These data were used to calculate the gasdynamic parameters of the characteris- hybrid combustion in a gas turbine combustor. H. Hiroyasu, M. Arai, tic stations, the main process parameters, the component loss T. Kadota (Hiroshima, University, Hiroshima, Japan), and J. Yoso coefficients, and the engine performance. The parameters of the (Japanese National Railways, Tokyo, Japan). JSME, Bulletin, vol. 23, engine under various throttle conditions were recorded for different Oct. 1980, p. 1655-1662. 7 refs. speeds, different nozzle areas, and with and without compressor Kerosene-hydrogen hybrid combustion was studied in a swirler bleeding. Attention is also given to the rational selection of probe type combustor. Kerosene was atomized by an air blast atomizer, locations to take due consideration of flow field characteristics, and and gaseous hydrogen was supplied to a kerosene spray through an to the selection of the proper method of data processing for annular slit in the atomizer. Blow out limit of the flame shifts to the obtaining accurate average station parameters of the engine. B.J. lean side of the air-fuel mixture in the hybrid combustion, which results in a slight decrease in NOx emission and a decrease in soot emission. When the hybrid ratio is under 10%, the flame stability is A81-17826 S! An experimental investigation of the rotating improved by hybrid combustion; increasing the hybrid ratio from 10 stall, surge, and wake behind the rotor for a single stage axial to 50% produces an increased combustion efficiency and reductions compressor. W. Zhang, Z. Liu, C. Zhang, and J. Liu. In: Recent of soot and NOx. (Author) selected papers of Northwestern Polytechnical University. Part 2. Xian, Shaanxi, People's Republic of China, Northwestern Polytechnical University, 1979, p. 203-215. 8 refs. In A81-17952* # Inlet flow distortion in turbomachinery. B. S. Seidel, M. D. Matwey (Delaware, University, Newark, Del.), and J. J. Chinese, with abstract in English. Adamczyk (NASA, Lewis Research Center, Cleveland, Ohio). Ameri- Dynamic measurements were used to study the rotor, rotating stall, and surge of a single-stage axial compressor (design speed of can Society of Mechanical Engineers, Gas Turbine Conference and 15,000 rpm). The rotating stall is found to be related to the total Products Show, New Orleans, La., Mar. 10-13, 1980, Paper turbulence caused by the wake of the rotor. It is shown that before 80-GT-20. 6 p. 12 refs. Members,.$1.50; nonmembers, $3.00. Grant rotating stall occurs, the wake range of the rotor widens, the shape of No. NsG-3189. A single stage axial compressor with distorted inflow is studied. the wake changes significantly, and the total turbulence caused by The inflow distortion occurs far upstream and may be a distortion in the wake increases sharply. It is also shown that surge occurs as a stagnation temperature, stagnation pressure or both. The blade rows result of continuous expansion of the rotating stall cell. As soon as surge occurs, distinct reverse flow appears; the flow pulse frequency are modeled as semi-actuator disks. Losses, quasi-steady deviation of surge is far less than that of rotating stall. B.J. angles, and reference incidence correlations are included in the analysis. Both subsonic and transonic relative Mach numbers are considered. A parameter study is made to determine the influence of A81-17827 It A vaporizing combustor with double combus- such variables as Mach number and swirl angle on the attenuation of tion spaces. M. Tang, H. Zhu, and Q. Du. In: Recent selected papers the distortion. (Author) of Northwestern Polytechnical University. Part 2. Xian, Shaanxi, People's Republic of China, Northwestern A81-17953 * # Comparison of experimental and computation- Polytechnical University, 1979, p. 217-228. 5 refs. In Chinese, with al shock structure in a transonic compressor rotor. G. Haymann- abstract in English. Haber (General Electric Corp., Lyman, Mass.) and W. T. Thompkins, A tubular combustor is described that has a novel type of Jr. (MIT, Cambridge, Mass.). American Society of Mechanical prevaporizing tube, which is of annular cross section. The dome of Engineers, Gas Turbine Conference and Products Show, New the combustor is divided into two combustion spaces; fuel is injected Orleans, La., Mar. 10-13, 1980, Paper 80-GT-81. 11 p. 17 refs. under moderate pressure into the annular space of the prevaporizing Members, $1.50; nonmembers, $3.00. Grant No. NGL-22-009-383. tube through the orifices on the two fueled-distribution rings. The Measurement of passage shock strength in a transonic compres- injected fuel forms oil films on the two walls. The combustor is sor rotor using a gas fluorescent technique revealed an unexpected designed to be used as an air heater for a high-temperature wind variation in shock strength in the radial direction. An axisymmetric tunnel. It is required that the combustor provide a steady uniform idealization would normally predict that the passage shock strength hot gas stream at a temperature of 400-1100 C, and that the flame would gradually weaken when moving radially inward until disap- not extend beyond the exit of the flame tube. B.J. pearing at the sonic radius. However, the measurements indicated a sharp peak in strength at the nominal sonic radius. Blade boundary layer separation originating at this point accounts for about one half A81-17832 Sukhoi's pivotal interdictor. Air International, of the total rotor losses. A numerical computation of the three- vol. 20, Jan. 1981, p. 6-10. dimensional inviscid flow, using time-marching techniques, has The article covers the development, design, and operation of the accurately predicted in general the radial and tangential variations in Soviet Su-24 aircraft, NATO code name 'Fencer'. The Su-24 is passage shock strength and in particular the sharp pressure peak at configurationally similar to its USAF counterpart, the F-111, the nominal sonic radius. The overall shock strength was somewhat although scaled down both dimensionally and in weight (empty overpredicted, but this overprediction may be the result of boundary equipped weight of 41,890 Ib rising to a maximum weight of 87,080 layer separation in the experiment. This paper presents comparisons Ib). It has a combat radius of 1700 km and can attain speeds of 2445 between the optical density measurements and computational results km/hr (M = 2.3) above 36,000 ft and 1470 km/hr (M = 1.2) at sea and in addition a short analytical discussion which demonstrates that level. The aircraft is powered by a pair of Tumansky R-29B the sharp shock strength rise may occur in many transonic turbofans (42% more unreheated thrust than the TF30-P-9 of the compressor rotors. • (Author) F-111), with five LP and six HP compressor stages and a maximum unreheated thrust of 17,636 Ib. The Su-24 is equipped with a radar of the pulse-Doppler type for navigation, terrain-following, and A81-17954 * H Structure and decay characteristics of tur- all-weather weapons delivery, and its armament is comprised of a bulence in the near- and far-wake of a moderately loaded compressor 109 A81-17976 rotor-blade. A. Ravindranath and B. Lakshminarayana (Pennsylvania 20%; and the nozzle entrance Reynolds number attained a value of State University, University Park, Pa.). American Society of Mechani- about 10-million. For three different loading cases the free-stream cal Engineers, Gas Turbine Conference and Products Show, New turbulence intensity and fluctuation along the nozzle axial length are Orleans, La., Mar. 10-13, 1980, Paper 80-GT-95. 10 p. 9 refs. determined together with the local Stanton number. For low Members, S1.50; nonmembers, S3.00. Grant No. NsG-3012. Reynolds number (less than one-million) no clear change of heat The wake of a turbomachinery rotor-blade is turbulent, highly transfer is observed; for Re exceeding one-million, a weak and nearly three-dimensional, and nonisotropic with appreciable curvature in linear dependence of Stanton number on free-stream turbulence the trailing-edge and near-wake regions. The characteristics of the intensity is shown. B.J. turbulence vary considerably with radius, blade loading, free-stream turbulence, Reynolds number, and the rotor-blade geometry. This A81-17997 Vector and scalar characteristics of opposing paper is concerned with the turbulence properties of a moderately jets discharging normally into a cross-stream. Z. A. Khan and J. H. loaded compressor blade, particularly near the blade trailing-edge. Whitelaw (Imperial College of Science and Technology, London, The tangential variation of the axial, tangential and radial intensities England). International Journal of Heat and Mass Transfer, vol. 23, and stresses across the wake, as well as their decay characteristics Dec. 1980, p. 1673-1680. 10 refs. Research supported by the Science were measured with a tri-axial hot-wire probe in the rotor frame of Research Council. reference. The decay of intensities and stresses were found to be very Measurements of mean velocity and a passive scalar (helium rapid in the trailing-edge and near-wake regions and slow in the tracer) have been obtained for two rows of opposing jets discharging far-wake region. The effects of inlet-guide-vane and the hub-wall normally into a cross-flowing stream and simulate an important boundary layers on the rotor wake turbulence spectra are also aspect of gas-turbine combustor practice. Results are presented for a discussed. Similarity rules for the three components of intensity are downstream distance of 6 jet diameters from the jet center lines and also derived and presented in this paper. (Author) for a jet-to-mainstream velocity ratio of 2.25. The influence of the nonuniform pitch and pitch-to-diameter ratio is quantified with the opposing jets separated by 4D. For a pitch to diameter ratio of 2, a A81-17976 History of flight testing the L-1011 Tristar jet slight geometrical asymmetry of the central jet for one row of holes transport. I - The L-1011-1. R. J. Gatineau (Lockheed-California Co., Engineering Flight Test Div., Palmdale, Calif.). Lockheed Horizons, results in a severe asymmetry of the velocity field. This effect is not, however, propagated to the opposing side. The scalar flux measure- Winter 1980-1981, p. 3-17. The article highlights the flight testing and development of the ments show the nearest adjacent jet aiding the displaced jet to regain L-1011 Tristar jet transport. The L-1011 has a take-off gross weight symmetry and the counteraction to this of the opposing jet. With a of 430,000 to 504,000 Ib, a range of up to 5000 nautical miles, and pitch-to-diameter ratio of 4, the scalar measurements indicate can carry 300 to 345 passengers at a nominal cruise speed of Mach 'slipping' between the opposed jets. Furthermore, symmetrical 0.83. The L-1011 is currently available in four basic models arrangement of the jets with this higher pitch-to-diameter ratio leads (L-1011-1, L-1011-100, L-1011-200, L-1011-500), each model hav- to impingement of the opposing jets with the jets bifurcating ing differences in design, range, fuel capacity, and passenger capacity. asymmetrically, and geometrical asymmetry no longer results in The aircraft were intensively tested overa a period of two years for severe asymmetry of the velocity field. (Author) take-off and landing, noise levels, load capacity, strucural defects, A81-18022 # Effects of axisymmetric sonic nozzle geometry aircraft system and and component performance, and flight perfor- on Mach disk characteristics. A. L. Addy (Illinois, University, mance in a series of tests designed to meet the flight demonstration requirements necessary for certification, which was received from the Urbana, III.). AIAA Journal, vol. 19, Jan. 1981, p. 121, 122. 13 refs. Results are presented on the effects of axisymmetric sonic FAAin1972. B.R.K. nozzle geometry on the onset, diameter, and location of the Mach disk in moderately underexpanded freejet flows. A contoured A81-17977 Autonomous navigation using passively sensed converging nozzle, four conically converging sharp-edged nozzles and terrain images. O. Firschein and M. J. Hannah (Lockheed Signal a sharp-edged orifice are examined. The mass flow rate and choking Processing Laboratory, Palo Alto, Calif.). Lockheed Horizons, Winter characteristics of the six sonic nozzles are investigated over the 1980-1981, p. 26-34. stagnation to back pressure ratio range greater than 1 and less than The possibility of using passively sensed terrain images as the 10. R.C. basis for an autonomous navigation system in subsonic vehicles flying at low altitudes is of interest for unmanned flight applications. Through a TV camera or mosaic of light-sensitive semiconductor A81-18024 # A study of multiple jets. S. Raghunathan and devices, the image scene is converted into a number which is stored I. M. Reid (Belfast, Queen's University, Belfast, Northern Ireland). in a computer and can then be used by the 'Navigation Expert' (a AIAA Journal, vol. 19, Jan. 1981, p. 124-127. computer program being developed at Lockheed's Signal Processing This paper investigates the reduction of noise level through a Laboratory) to make decisions and control the vehicle's flight. The multiple jet array. Nozzles are equally spaced around a circle with a Navigation Expert coordinates several subsystems including the radius of 5 mm from the axis of the central nozzle, and operate at a Instruments Subsystem (IS), a Dead Reckoning System (DRS), a supply pressure of 0.3-0.5 MPa (3-5 bar). A noise spectra peak Ground Velocity Subsystem (GVS), a Visual Bootstrapping Sub- corresponding to f = 20 KHz is found. Noise reduction is observed system (VBS), and a Landmarks Subsystem (LS). Further research is without significant reduction in the momentum of the jet. R.C. necessary before an automatic navigation system based on images can become operational. B.R.K. A81 18051 International Air Transportation Conference, New Orleans, La., April 30-May 3, 1979, Proceedings. Volumes 1 & A81-17994 Influence of free-stream turbulence intensity 2. Conference sponsored by ASCE, SAE, AIAA, ICE, ATRIF, and on heat transfer in the two-dimensional turbulent boundary layer of Transportation Research Board. New York, American Society of an accelerated compressible flow. K. Bauer, J. Straub, and U. Grigull Civil Engineers, 1979. Vol. 1, 485 p.; vol. 2, 343 p. Price of two (Miinchen, Technische Universitat, Munich, West Germany). Interna- volumes, $59. tional Journal of Heat and Mass Transfer, vol. 23, Dec. 1980, p. The conference included papers on airspace analysis in airport 1635-1642. 10 refs. Research sponsored by the Bundesministerium system planning, performance of flexible highway pavements, micro- der Verteidigung. wave landing systems, civic-electrical engineering interface, hedging The effect of free-stream turbulence on heat transfer in the against errors in airport forecasting, a computer program for slabs turbulent boundary layer is investigated experimentally for accelerat- with discontinuities, and flight instrumentation for all-weather ed compressible flow in a two-dimensional convergent-divergent approach and landing. Also discussed were air service for small nozzle. The turbulence intensity varied from nearly zero to about communities, helicopters for all-weather terminals, NOT techniques, 110 A81 18062 airline deregulation, runway configuration management systems, and The rationale, operations, and expected benefits are described the role of aircraft separation assurance in the cockpit. A.T. for the implementation of fifty passenger DeHavilland Dash-7 aircraft in the Alleghany commuter fleet of Ransome Airlines. The A81-18052 Airspace analysis in airport system planning. inovative use of STOL aircraft, 30 RNAV, and stub ends of runways G. W. Antis, W. J. Dunlay, Jr., H. Fan (Peat, (Warwick, Mitchell and is argued to have large potential effects on intercity air transporta- Co., San Francisco, Calif.), and C. Brittle (Metropolitan Transpor- tion. T.M. tation Commission, Berkeley, Calif.). In: International Air Trans- portation Conference, New Orleans, La., April 30-May 3, 1979, A81-18058 Testing model rotorcraft for overwater opera- Proceedings. Volume 1. New York, American tions. W. A. Crago and D. L. Williams (British Hovercraft Corp., Ltd., Society of Civil Engineers, 1979, p. 1-15. Experimental and Electronic Laboratories, East Cowes, Isle of Wight, An airspace capacity model was used to estimate the capacity of England). In: International Air Transportation Conference, New the San Francisco Bay Area airspace under a variety of different Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. operating conditions. The results were compared with alternative New York, American Society of Civil Engineers, forecasts of aviation demand in 1997. The comparisons of demand 1979, p. 137-152. with airspace capacity led to conclusions on: (1) the extent to which This paper presents a brief historical review of some of the the Bay Area airspace will be able to accommodate future aviation problems associated with the ditching and flotation of helicopters. It activity, and (2) the locations of critical capacity constraints and also discusses the sea conditions likely to be met and shows how the airspace interactions. T.M. various phenomena involved can be investigated by means of model experiments. (Author) A81-18054 Introduction to a rigid pavement design proce- dure. W. R. Barker (U.S. Army, Geotechnical Laboratory, Vicksburg, A81-18059 Flight instrumentation requirements for all- Miss.). In: International Air Transportation Conference, New Or- weather approach and landing. J. L. DeCelles and G. Terhune (Air leans, La., April 30-May 3, 1979, Proceedings. Volume 1. Line Pilots Association, Kansas City, Mo.). In: International Air New York, American Society of Civil Engineers, 1979, Transportation Conference, New Orleans, La., April 30-May 3, 1979, p. 33-48. 16refs. Proceedings. Volume 1. New York, American Description of a new mechanistic procedure for the structural Society of Civil Engineers, 1979, p. 153-164. 5 refs. design of rigid airport pavements to carry the design traffic under The official position and rationale of the Air Line Pilots field conditions. The technique involves three major elements: (1) Association (ALPA) is given regarding instrumentation requirements material characterization, (2) computation of load response param- for air carrier approach and landing. The argument is made that the eters, and (3) correlation of the load response parameters to cost of continuing the status quo is greater (in terms of safety, pavement performance. One limitation of the procedure is that it reliability and economy) than the expense of providing the necessary must be restricted to standard jointed Portland cement concrete improvements. The paper expounds the inadequacy of conventional pavements. T.M. instrumentation for operating to present and future visibility minima, and it presents the rationale for ALPA's contention that A81 -18055 Micro-wave landing system - An operational these inadequacies can be overcome only by head-up display (HUD) point of view. A. J. Beatty (International Federation of Air Line of suitable information to the pilot. (Author) Pilots Association, Egham, Surrey, England). In: International Air Transportation Conference, New Orleans, La., April 30-May 3, 1979, A81-18060 New major U.S. airports - Capacity considera- Proceedings. Volume 1. New York, American tions. V. J. Drago (Battelle Columbus Laboratories, Columbus, Society of Civil Engineers, 1979, p. 49-53. Ohio). In: International Air Transportation Conference, New Or- The official position of the International Federation of Air Line leans, La., April 30-May 3, 1979, Proceedings. Volume 1. Pilots Association (IFALPA) is given regarding the need for a new New York, American Society of Civil Engineers, 1979, nonvisual approach and landing guidance system. The argument is p. 165-178. 9 refs. made that early implementation of the micro-wave landing system A methodology is developed to investigate the need for major (MLS) will enhance the safety, reliability and economy of interna- new airports at 21 U.S. hubs through the year 2000. This tional civil air operations. The paper does not attempt to investigate methodology is based on calculating average runway delays for in detail the mechanisms of MLS and the theory of its signal various airport activity and operational scenarios. Cost estimates are propagation. It does, however, investigate its use by the line pilot given for the required new facilities. (Author) from the operational point of view, including its effect on commer- cial air transport. (Author) A81-18061 An overview - 1980 generation avionic devel- A81-18056 RNAV benefits today - Today and future opments. T. A. Ellison (United Air Lines, Inc., Chicago, III.). In: requirements. R. A. Berube (National Airlines, Inc., Clifton, N.J.). International Air Transportation Conference, New Orleans, La., April In: International Air Transportation Conference, New Orleans, La., 30-May 3, 1979, Proceedings. Volume 1. .New April 30-May 3, 1979, Proceedings. Volume 1. York, American Society of Civil Engineers, 1979, p. 179-186. The 1980 generation air transports now under development will New York, American Society of Civil Engineers, 1979, p. 54-71. 37 incorporate a completely new generation of avionics devices and refs. Presently experienced and expected future benefits of area interfaces, briefly described. The major changes in 1980 avionics will bring new benefits and new problems to the operator. Integration of navigation systems are reviewed as they relate to the economy, information through improved computation and display facilities will safety, and workload of flight operations. Minimum system charac- better optimize aircraft operation. Some of the benefits can be teristics and functional requirements are tabulated on the basis of personal experience, simulations, tests, and postulated aspects of the forecast from data recorded in current aircraft operations. Means are RNAV environment. T.M. suggested to utilize and maintain new avionics capabilities effectively in the transition environment of the 1980's. (Author) A81-18057 The introduction of STOL and RNAV to large A81 -18062 Non-destructive pavement evaluation. M. E. commercial operations. C. J. Blaydon (Ransome Airlines, Bensalem, Harr (Purdue University, Lafayette, Ind.). In: International Air Pa.). In: International Air Transportation Conference, New Orleans, Transportation Conference, New Orleans, La., April 30-May 3, 1979, La., April 30-May 3, 1979, Proceedings. Volume 1. Proceedings. Volume 1. New York, American New York, American Society of Civil Engineers, 1979, p. 85-94. Society of Civil Engineers, 1979, p. 213-219. 9 refs. 111 A81-18063 A81-18063 Prestressed concrete airfield pavements. R. Respondents to a comprehensive survey concerning the aviation Heinen (Dyckerhoff and Widmann, Inc.; Dywidag Canada, Ltd., industry are generally optimistic but watchful about the prospects Canada). In: International Air Transportation Conference, New for the growth in the 1980s. Identifying factors most likely to Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. influence air transportation demand was a major purpose of the New York, American Society of Civil Engineers, October 1978 survey of 120 forecasters, planners, and researchers, 1979, p. 220-235. who came from four different global -regions and six different industry sectors. The survey results presented in this paper show A81-18064 Automating airborne company communica- changes in real air fares and real economic growth to be the tions. R. E. Johnson (United Air Lines, Inc., San Francisco, Calif.). respondent's chief bellwethers, followed closely by jet fuel availabil- In: International Air Transportation Conference, New Orleans, La., ity and price, and government regulation. Also considered in the April 30-May 3, 1979, Proceedings. Volume 1. survey are modifiers that would be most disruptive to the industry; New York, American Society of Civil Engineers, 1979, p. 236-242. here, a prolonged OPEC embargo, a major recession, and further As industry matures, the authority to accomplish changes large cuts in air fare discounts topped the list. Base-line values for without financial controls is reduced. This paper will outline how the certain assumptions are also provided. Comparisons are made among Air Transport Industry finally launched a major change in communi- respondents in different regions and industry sectors. (Author) cations with their aircraft after years of development. In order to meet financial goals, the scope of the programs were reduced and A81-18069 A new perspective in aviation systems plan- technology advances were utilized to provide answers not previously ning. M. J. Ryan, Jr. (Metropolitan Council of the Twin Cities, St. available. (Author) Paul, Minn.). In: International Air Transportation Conference, New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. New York, American Society of Civil Engineers, A81-18065 Helicopters - Help for the all weather terminal. 1979, p. 283-291. J. C. Kettles (Petroleum Helicopters, Inc., Lafayette, La.). In: New and increased emphasis on maximizing the use of existing Internationa! Air Transportation Conference, New Orleans, La., April aviation facilities, particularly in large urban areas, has placed 30-May 3, 1979, Proceedings. Volume 1. New considerably more responsibility on the metropolitan aviation system York, American Society of Civil Engineers, 1979, p. 243-247. planners. As part of the process of maintaining a system plan responsive to the area's air transportation needs, the systems planner A81 -18066 Runway rehabilitation, Washington National is the key to protecting and preserving the continued viability of the Airport. F. Moavenzadeh and M. J. Markow (MIT, Cambridge, metropolitan areas' airport system, including both air carrier and Mass.). In: International Air Transportation Conference, New general aviation airports. Given that few, if any, new air carrier Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. airports will be built prior to the end of the century, the aviation New York, American Society of Civil Engineers, system planners' role must be centered on coordinating airport plans 1979, p. 249-264. with community comprehensive plans. This is especially true with The structural condition of a runway flexible pavement at respect to the airport/land use compatibility planning currently Washington National Airport was evaluated. Since its last overlay in underway at some airports around the nation, including the Twin 1972, the runway has exhibited horizontal and vertical permanent Cities. (Author) deformations or distortions, including lateral distortions of surface paint and groove patterns, vertical heaves and troughs, and localized A81-18070 * Avionics and displays in a future airspace depressions. Pavement and soils investigations carried out to identify system. S. Salmirs (NASA, Langley Research Center, Hampton, Va.). the causes of these distress mechanisms indicated that observed In: International Air Transportation Conference, New Orleans, La., pavement damage was related more to materials properties and April 30-May 3, 1979, Proceedings. Volume 1. perhaps construction practices, rather than to structural adequacy. New York, American Society of Civil Engineers, 1979, p. 292-309. Recommendations included: (1) removal of severely distressed material, either by cold-planing or other means; (2) replacement of 10 refs. The terminal configured vehicle (TCV) program was conceived damaged material with a stiff, high-tensile-strength asphalt concrete to address the problems of (1) operation in the crowded terminal base; and (3) overlay of entire pavement surface with an epoxy area airspace, and (2) integration of airborne avionics systems asphalt layer to resist horizontal stresses induced by braking and necessary to improve the efficiency of these operations. The program turning aircraft and to retard cracking. (Author) and its interaction with industry task groups are summarized, including elements of research and data collection. New technology A81-18067 Community participation in airport planning. is discussed which may be useful in implementing some defined B. D. Myers (Missouri, Aviation Dept., Kansas City, Mo.). In: avionics and display requirements. T.M. International Air Transportation Conference, New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. New A81-18071 The problems of helicopter ditching. J. Scan- York. American Society of Civil Engineers, 1979, p. 265-274. Ion (Civil Aviation Authority, London, England). In: International Several principles and techniques for community and citizen Air Transportation Conference, New Orleans, La., April 30-May 3, participation were exercised during the Kansas City International 1979, Proceedings. Volume 1. New York, Ameri- Airport Master Plan and Environs Area Plan update. These proce- can Society of Civil Engineers, 1979, p. 310-324. dures include establishing advisory and policy committees, a project Technical reasons for the occurrence of emergency helicopter information center, the conducting of public information meetings, ditchings are reviewed in an attempt to survey current approaches to and various other methods of providing information on the plan for this problem. Existing legislation affecting overwater operations and the publics consideration. Advice from the community assisted in airworthiness is examined, and problems of survivability are consid- shaping the final airport and environs plan. The public must be ered, ranging from evacuation of the helicopter to the search and represented in the continuous planning process. (Author) rescue facilities. T.M. A81-18068 Aviation assumptions in the eighties. D. E. A81 -18072 Canada's national aviation forecasting models. Raphael (Transportation Research Board, Washington, D.C.; SRI W. T. Tucker (Canadian Air Transportation Administration, Ottawa, International, Menlo Park, Calif.). In: International Air Transporta- Canada). In: International Air Transportation Conference, New tion Conference, New Orleans, La., April 30-May 3, 1979, Proceed- Orleans, La., April 30-May 3, 1979, Proceedings. Volume 1. ings. Volume 1. New York, American Society of New York, American Society of Civil Engineers, Civil Engineers, 1979, p. 276-282. 1979, p. 343-357. 112 A81-18080 This paper outlines the role of the Canadian Department of and flexible pavement construction. The depth of construction Transport in airport planning and site-specific forecasting. It then required by individual aircraft using their unique landing gear provides an overview of the national system of aviation forecasting configurations is established over a range of subgrade support values models currently being developed and describes the progress to date. from weak to strong. Pavements are classified by establishing the Two of these models, viz., the Air Passenger Origin and Destination relationship between actual construction on their assessed subgrade Model (PODM) and the Passenger Traffic Allocation Model (PTAM), support value to an equivalent depth of reference construction by were recently completed and these are described in some detail. the use of equivalency factors. The problem of limited weight and Finally, a brief summary is given of other forecasting methods and overload aircraft operations are considered. (Author) models with specific reference to planning peak period forecasts. (Author) A81 -18077 Omega - An economic Loran A replacement. A81-18073 The federal role in airport noise control L. L. James (Trans World Airlines, Inc., Kansas City, Mo.). In: planning. J. E. Wesler (FAA, Washington, D.C.). In: International Air International Air Transportation Conference, New Orleans, La., April Transportation Conference, New Orleans, La., April 30-May 3, 1979, 30-May 3, 1979, Proceedings. Volume 1. New Proceedings. Volume 1. New York, American York, American Society of Civil Engineers, 1979, p. 439-452. 7 refs. Society of Civil Engineers, 1979, p. 375-382. Since receiving statutory authority in 1968, the FAA has developed and followed a step-by-step, deliberate program to impose A81-18078 Recent developments in NOT techniques. G. noise limits on all aircraft. Noise reduction at the source cannot solve T. Baird and J. P. Nielsen (New Mexico, University, Albuquerque, N. the aviation noise problem, however, since aircraft can never be Mex.). In: International Air Transportation Conference, New Or- silent. Recognizing this, the Department of Transportation leans, La., April 30-May 3, 1979, Proceedings. Volume 2. (DOTI/FAA Aviation Noise Abatement Policy of November 18, New York, American Society of Civil Engineers, 1979, 1976, spells out the shared responsibilities among all elements of the p. 481-493. aviation community for aviation noise abatement. This paper reviews The Civil Engineering Research Facility developed three non- briefly these shared responsibilities for aviation noise abatement, and destructive pavement testing methods starting with Thumper I which describes those functions which the Federal government is fulfilling. used a steady-state vibrator to determine the wave propagation (Author) properties of the pavement. This system's shortcomings included a non-air-transportable van and complex electronics requiring highly trained personnel. The Thumper II excluded these problems by A81-18074 L-1011 Flight Management System design utilizing a drop weight impact source and basic recording equipment, considerations. F. F. Wright and R. J. Oliver (Lockheed-California but needed a computer center to digitize and process the recorded Co., Burbank, Calif.). In: International Air Transportation Con- signals. The Thumper III is the most modern system which combines ference, New Orleans, La., April 30-May 3, 1979, Proceedings. air-transportability with the on-board minicomputer resulting in Volume 1. New York, American Society of Civil quick and reliable airfield testing. A.T. Engineers, 1979, p. 383-398. This paper describes some of the design considerations related to A81-18079 Investment decision-making in international the fuel and cost savings aspects of the L-1011 Flight Management airports. P. H. Beinhaker (IBI Group, Toronto; Beinhaker/lrwin System. Reductions in fuel and cost are achieved by optimizing the Associates; InterBase, Inc.; Beinhaker Planning and Development thrust and speed in the climb, cruise and descent regimes of flight. Services, Ltd., Canada). In: International Air Transportation Confer- The system mechanization, operation and design problems to ence, New Orleans, La., April 30-May 3, 1979, Proceedings. Volume accomplish this optimization are discussed. (Author) 2. New York, American Society of Civil Engi- neers, 1979, p. 494-503. A81-18075 Fully bonded concrete overlay for an airport The paper discusses the maximization of the initial land resource runway. E. J. Barenberg (Illinois, University, Urbana, III.) and B. L. for airport facilities and the insurance of the protection of airport Ratterree (Crawford, Murphy and Tilly, Inc., Springfield, III.). In: land and investments by insuring compatible land development on International Air Transportation Conference, New Orleans, La., April adjacent lands. The location of airport facilities in the close 30-May 3, 1979, Proceedings. Volume 1. New proximity of the airfield with adequate provisions for the expansion York, American Society of Civil Engineers, 1979, p. 399-416. 6 refs. of passenger and ground access facilities is discussed. The maximum Fully bonded concrete overlays are a viable method for productivity in land use can be provided by charging land rents in rehabilitating concrete pavements. Use of this procedure for upgrad- accordance with the accessibility to the airfield; environmental ing concrete pavements has been limited by the expensive and factors should be accounted for by relating the costs of mitigation to environmenatlly objectional procedure of acid etching the existing the operations and/or facilities causing the problem and recovering pavement surface. With the newly developed machinery capable of the costs through charges. A.T. milling off a thin layer of the existing concrete, acid etching of the surface is no longer required, making this approach more economical- ly and environmentally attractive. This paper describes the design A81-18080 Increasing capacity with computer-assisted de- analyses leading to the selection of a fully bonded concrete overlay cision making. R. G. Dear (California State University, Fullerton, to rehabilitate and upgrade an existing concrete runway, and the Calif.). In: International Air Transportation Conference, New Or- construction procedures used to assure full bonding of the overlay to leans, La., April 30-May 3, 1979, Proceedings. Volume 2. the pavement. (Author) New York, American Society of Civil Engineers, 1979, p. 519-538. A81-18076 UK pavement design and evaluation - A new Computer use in the high density terminal areas is discussed approach. R. M. Hutson (Department of the Environment, Direc- with the aim of increasing airport capacity, decreasing delays, and torate of Civil Engineering Services, Croydon, Surrey, England). In: aiding sequencing and scheduling performed by controllers. A International Air Transportation Conference, New Orleans, La., April method of Constrained Position Shifting (CPS) was developed which 30-May 3, 1979, Proceedings. Volume 1. New is based on resequencing on the first-come, first-serve order with York, American Society of Civil Engineers, 1979, p. 417-426. 8 refs. respect to arrival on the runway; simulation is presented for one The features of an aircraft pavement classification system are simple CPS strategy which limits each aircraft to a maximum shift of reviewed and a new approach to matching aircraft and pavements is four positions from its first position (forward or rearward). It was outlined. The system is based on the use of reference construction shown that significant improvements in system performance can be materials with defined mechanical properties representative of rigid attained along with potential savings. A.T. 113 A81-18081 A81-18081 Helicopter survivability in overwater situa- balance with other components of the airport planning program. The tions. M. J. Evans (British Airways Helicopters, Ltd., Aberdeen, ASM-3 system includes a highly modular structure so that individual Scotland). In: International Air Transportation Conference, New routines, such as runway assignment rules, can be easily recorded and Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. replaced without changing the balance of the program; the space New York, American Society of Civil Engineers, simulation model is comprised of a number of computer algorithms 1979, p. 539-552, which approximate the flight planning and plan-executing functions of the pilot and air traffic controller. An example of airspace simulation is given which analyzes the time of flight of each aircraft A81 -18082 Computer generated displays and pilot effec- arrival/departure, the aircraft energy consumption, noise and air tiveness. D. M. Fadden and E. F. Weener (Boeing Commercial pollution, and the costs of air traffic control required for sale Airplane Co., Seattle, Wash.). In: International Air Transportation operation. A.T. Conference, New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. New^York, American Society of Civil A81-18087 The importance of 'Interim Standard Micro- Engineers, 1979, p. 553-561. wave Landing System' for small community airports. L. E. McCabe On-board digital computers and electronic display equipment (Minnesota, Dept. of Transportation, St. Paul, Minn.). In: Interna- for 757 and 767 aircraft permit almost any reasonable format or tional Air Transportation Conference, New Orleans, La., April presentation and computation of flight parameters previously un- 30-May 3, 1979, Proceedings. Volume 2. New available for display. Previous computer display programs have York, American Society of Civil Engineers, 1979, p. 618-621. indicated the necessity of dynamic simulation to maximize display effectiveness; optimization in the format of information displays can reduce the mental calculations by the pilot, allowing more time for A81-18088 Airport/environs plan making - Managing the managing the flight. The pilot panel mockup, pilot adaptation planning process. R. R. Platzek (Williams, Platzek and Mocine, enhancement, and the duties of the pilot as the flight manager are Sausalito, Calif.) and R. H. Doyle (Peak, Marwick, Mitchell and Co., outlined, concluding that the new computer displays will allow the San Mateo, Calif.). In: International Air Transportation Conference, pilot to operate more accurately and efficiently. AT. New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. New York, American Society of Civil Engineers, 1979, p. 649-659. A81 -18083 Airport visual approach, guidance and landing Airport/environs planning should provide for the joint airport/ systems - Airline pilots viewpoint. J. A. Forgas (Air Line Pilots environs institutional system, acceptable work program, adequate Association, Washington, D.C.). In: International Air Transportation financing, public involvement, and a coordinated technical team. It Conference, New Orleans, La., April 30-May 3, 1979, Proceedings. was shown that a linear analytic approach to airport planning will Volume 2. New York, American Society of Civil involve only staff technicians who wiil recommend a final proposal; Engineers, 1979, p. 562-567. this is an in-house effort, which may make it possible to manage airport/environs planning even if the participants do not agree on the A81-18084 Design of the new Tehran International Air- final selected plan. The cyclic or iterative method determines port. R. J. Hodge (Tippetts-Abbett-McCarthy-Stratton, Washington, whether a consensus exists, and repeats the process through a D.C.). In: International Air Transportation Conference, New Orleans, number of cycles until the technicians, the public, and the La., April 30-May 3, 1979, Proceedings. Volume 2. decision-makers agree on one feasible plan. The cyclic approach is New York, American Society of Civil Engineers, 1979, more applicable to situations involving low mutual thrust, requiring p. 572-585. all participants to be familiar with all potential tradeoffs. A.T. This paper covers the design concepts, considerations and parameters for a new major international airport in the Middle East. Included are discussions on the airfield, the terminal complex, air A81-18089 Runway Configuration Management System cargo facilities, aircraft support facilities and airport service facilities. concepts. A. N. Sinha and R. L. Fain (Mitre Corp., Air Transporta- (Author) tion Systems Div., McLean, Va.). In: International Air Transporta- tion Conference, New Orleans, La., April 30-May 3, 1979. Proceedings. Volume 2. New York, American A81 -18085 Modeling of the terminal area Air Traffic Society of Civil Engineers, 1979, p. 668-683. U.S. Department of Management and Control. C.-C. Hsin (Mitre Corp., Metrek Div., Transportation Contract No. FA79WA-4184. McLean, Va.). In: International Air Transportation Conference, New The Configuration Management System was based on three Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. concepts representing a wide range of static and dynamic selection New York, American Society of Civil Engineers, processes. The basic model updates operational conditions such as 1979, p. 586-605. 5 refs. wind and weather, checks on the availability of runways, and A study of the advanced terminal area Air Traffic Management analyzes feasible remaining available runways. The model output and Control (ATM/C) system included the basic structures and provides an ordered list of available runway configurations in control elements, and the design of advanced automation methods. It decreasing order of capacity for a specific set of operating condi- was shown that the terminal area ATM/C is stochastic and can be tions; the intermediate model identifies feasible pairs of configura- effectively measured; the problem is complex due to numerous tions (for current conditions and expected changes), and the subsystems and various control functions. Both the generation and advanced model produces configurations for the extended period. the transmission of information should be emphasized to improve The model testing at Chicago's O'Hare airport should result in the ATM/C; continuous improvements of the surveillance, communi- enhancement such as interactions with vortex advisory systems, cation and tracking capabilities are required to accomodate the generation of equipment logs, and identification of relationships advanced automation functions. A.T. between dual and triple arrival configurations to assist in transition between them. A.T. A81-18086 Airspace simulation in airport system plan- ning. E. S. Joline (Aviation Simulations International, Inc., Hunting- A81 -18090 Traffic forecasting for the NRIA. M. A. ton, N.Y.). In: International Air Transportation Conference, New Thomet and S. M. Sultan (Bechtel. Inc., San Francisco, Calif.). In: Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. International Air Transportation Conference, New Orleans. La., April New York, American Society of Civil Engineers, 30-May 3, 1979, Proceedings. Volume 2. New 1979, p. 606-617. York, American Society of Civil Engineers, 1979, p. 684-708. The ASM-3 airport simulation model has been designed for easy A traffic forecasting method for the New Riyadh International adaptation to various applications to maintain analysis costs in Airport was based on an econometric model which uses the value of 114 A81 18410 imports of goods and services as a variable for predicting air traffic. Consideration is given to exact and approximate theories, computer The variable is projected by estimating petroleum revenues and the experiments, temporal and spatial normal-mode response, nonparallel ratio of imports to exports; the forecasts were made for 1983, 1990, flows, and nonlinear effects. Other concepts discussed include and 2000. Historical statistics for passenger, air freight, and airmail secondary instability, coupling, and advanced perturbation methods. are presented for the Saudi Arabia airports; it is noted that the VV.L. econometric model forecasts are under review and do not represent the present basis of planning. A.T. A81-18122 Three-dimensional boundary layer transition via the mechanisms of 'attachment line contamination' and 'cross A81-18091 Environmental aspects of airport planning. R. flow instability'. D. I. A. Poll (Cranfield Institute of Technology, A. Waller (Atkins Research and Development, Epsom, Surrey, Cranfield, Beds., England). In: Laminar-turbulent transition; Pro- England). In: International Air Transportation Conference, New ceedings of the Symposium, Stuttgart, West Germany, September Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. 16-22, 1979. Berlin, Springer- Verlag, 1980, p. New York, American Society of Civil Engineers, 253-262. 8 refs. 1979, p. 713-730. 25 refs. Transition via the mechanisms of attachment line contamination The planning of airports around London is used to illustrate and cross flow instability has been studied experimentally by using a U.K. policy relating to the effects of airports on the environment. highly swept wing with a large leading edge radius. Although the The background of legislation is described. Approaches to decision- principal objective was to determine the conditions necessary for the making where environmental factors are important are compared, onset of turbulence, particular consideration has been given to the with particular reference to social-cost-benefit analysis. Possible identification of the forms of disturbance which occur in the laminar trends in environmental concern and in the environmental treatment boundary layer before the turbulent spots appear. (Author) of airports are put forward for discussion. (Author) A81-18318 Aeronautical-Maritime Engineering Satellite AS1-18092 The role of aircraft separation assurance in the /AMES/ program of Japan. S. Miura, H. Morikawa (Ministry of Posts cockpit. F. C. White (Air Transport Association of America, and Telecommunications, Radio Research Laboratories, Koganei, Washington, D.C.). In: International Air Transportation Conference, Tokyo, Japan), Y. Watanabe (Ministry of Transport, Electronic New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2. Navigation Research Institute, Mitaka, Tokyo, Japan), and S. New York, American Society of Civil Engineers, Morimoto (National Space Development Agency of Japan, Tokyo, 1979, p. 743-751. 8 refs. Japan). International Astronautical Federation, International Astro- The application of an aircraft separation assurance display in the nautical Congress, 31st, Tokyo, Japan, Sept. 22-28, 1980, Paper cockpit of a passenger aircraft is discussed. The principal method of 80-D-171. 11 p. aircraft separation assurance will be provided by the ground air A spin-stabijized geosynchronous satellite to be positioned over traffic control (ATC) systems; the Discrete Address Beacon System the Pacific Ocean between 160 deg E long and 180 deg E long, and the Air Traffic Advisory and Resolution Service (DABS/ATARS) AMES (Aeronautical Maintenance Engineering Satellite) is scheduled will supply a backup to the ATC in areas with an aircraft traffic for a 1986 launch by Japan. Developed by the National Space density above 0.02 aircraft/sq mi. The Active BCAS which uses Development Agency (NASDA), the cylindrical satellite 2 m in altitude reporting air traffic control transponders will provide backup length and 2 m in diameter weighs 350 kg BOL and carries an L-band aircraft separation for the balance of the world airspace. The cockpit multiple spot beam antenna to operate in the 5 GHz-5.25 GHz range display of airciaft separation is under investigation, but optimum as well as a global-beam C-band horn antenna transmitting at 1.5 cockpit display information has not yet been developed for installing GHz/1.6 GHz. With an expected lifetime of 1.5 years, AMES will this system. A.T. conduct navigation and communications studies within the joint AEROSAT program. Possible applications will be in the ATC and A81-18093 Saudi Arabia's new Gateway Airports. J. Hoyt small fishing vessels communications domain. R.S. and R. Campbell (Ralph M. Parsons Co., Pasadena, Calif.). In: International Air Transportation Conference, New Orleans, La., April A81-18371 A study of air breathing rockets - Subsonic 30-May 3, 1979, Proceedings. Volume 2. New mode combustion. G. Masuya, N. Chinzei, and S. Ishii (National York, American Society of Civil Engineers, 1979, p. 768-795. Aerospace Laboratory, Kakuda, Miyagi, Japan). International Astro- nautical Federation, International Astronautical Congress, 31st, Tokyo, Japan, Sept. 22-28, 1980, Paper 80-F-270. 1 5 p. 6 refs. A81-18100 */? Geometric dilution of precision in Global A study of subsonic mode combustion in cylindrical secondary Positioning System navigation. B. T. Fang (Computer Sciences Corp., combustors of air-breathing rockets determined the effects of the System Sciences Div., Silver Spring, Md.). Journal of Guidance and oxidizer-fuel ratio of the primary rocket, mass flow ratio of Control, vol. 4, Jan.-Feb. 1981, p. 92-94. Contract No. NAS5-24300. The evaluation of the GPS navigation performance is essentially secondary air to primary rocket propellants, and the length of equivalent to the computation of the diagonal terms of the geometric secondary combustors. Gaseous hydrogen and oxygen were the dilution of precision (GDOP) matrix. Certain theoretical results primary rocket propellants and room temperature compressed air concerning the general properties of the GDOP matrix are obtained. was used as secondary air. Combustion efficiency and air inlet An efficient algorithm for the computation of the GDOP matrix and pressure were related to the ratio of experimental to theoretical exit the navigation performance index is given; and applications of the pressure using a one-dimensional model which assumes incomplete results are illustrated by numerical examples. B.J. combustion. A.T. A81-18105 Dialogue on bridging some gaps in stability A81-18410 Satellites to aid flight safety. C. Rosetti (ESA, and transition research. T. Herbert (Stuttgart, Universitat, Stuttgart, Paris, France). International Astronautical Federation, International West Germany) and M. V. Morkovin (Illinois Institute of Tech- Astronautical Congress, 31st, Tokyo, Japan, Sept. 22-28, 1980, nology, Chicago, III.). In: Laminar-turbulent transition; Proceedings Paper80-1AA-17. 13 p. of the Symposium, Stuttgart, West Germany, September 16-22, A satellite-based system of communications for civil aviation is 1979. Berlin, Springer-Verlag, 1980, p. 47-72. 43 discussed. Changes in the present system are felt to be necessary; (1) refs. Research supported by the Alexander von Humboldt-Stiftung; because voice communication wastes the frequency spectrum; and Contract No. F49620-77-C-013. (2) because many areas of the earth are not covered by radar. The Typical applied problems in stability and transition in external, need is stressed for an integrated system based on terrestrial internal, and free-shear layer through-flow systems are reviewed. infrastructures over developed continental areas, and on satellites in 115 A81-18497 ocean and desert areas for communication as well as for global crane, (3) vibration control in helicopters, and (4) a system with navigation. Link budgets are given for a satellite-aircraft link having a truncated modes. (Author) transmission speed of 2400 bit/sec. The functions that could be performed by an integrated L-band satellite system are enumerated. A81-18599 # Radio navigation for aircraft: Handbook The simplifications that such a system would make possible are (Aviatsionnaia radionavigatsiia: Spravochnik). A. A. Sosnovskii and I. discussed, as are the resulting improvements in safety. C.R. A. Khaimovich. Moscow, Izdatel'stvo Transport, 1980. 256 p. 36 refs. In Russian. A81-18497 ft Elimination of vibrations in aircraft piping The basic principles of air navigation instruments and systems systems (Ustranenie kolebanii v aviatsionnykh truboprovodakh). V. are described. Attention is given to loran, satellite navigation P. Shorin. Moscow, Izdatel'stvo Mashinostroenie, 1980. 160 p. 42 systems, shoran, beacon landing systems (meter and centimeter refs. In Russian. wavelengths), radio altimeters, and Doppler velocity meters. B.J. The book examines problems of designing acoustic dampers for preventing vibrations in aircraft piping systems. Methods of com- A81-18600 # Practical aerodynamics of the helicopter Mi- puting damper effectiveness, design optimization, and experimental 6A (Prakticheskaia aerodinamika vertoleta Mi-6A). K. N. Laletin and testing are presented. Simple designs of jet type, low frequency L. T. Artamonov. Moscow, Izdatel'stvo Transport, 1980. 168 p. 14 acoustic filters, and resonating devices which prevent pipe and valve refs. In Russian. vibrations are described. AT. The book deals with some characteristic features of the rotor and airframe of the Mi-6A helicopter. The balancing, stability, and A81-18576 ft Cruise-missile-carrier navigation requirements. controllability of the helicopter in unsteady and some special modes G. T. Schmidt and R. H. Setterlund (Charles Stark Draper Laborato- of flight are examined. Attention is given to the behavior of the ry, Inc., Cambridge, Mass.). Journal of Guidance and Control, vol. 3, helicopter in flights with a suspended load and in emergency IMov.-Dec. 1980, p. 487-493. 6 refs. Contracts No. situations, such as failure of one of the two engines, failure of the tail F33657-78-C-0473; No. F33615-78-C-1563. rotor, etc. V.P. This paper addresses the modeling, simulation, and performance predictions used in determining aircraft avionics and transfer- A81 -18639 ft Turbine blade technology - Present and future. alignment requirements for a generic aircraft that would launch R. E. Allen and J. E. Sidenstick (General Electric Co., Aircraft cruise missiles over water, a considerable distance from a first Engine Group, San Francisco, Calif.). American Society of Mechani- TERCOM (terrain comparison) update area. Such would be the case cal Engineers, Century 2 Aerospace Conference, San Francisco, for an undefended wide-body aircraft that must remain far away Calif., Aug. 13-15. 1980,Paper80-C2/Aero-10. 7 p. Members, $1.50; from an opponent's air defense system. This long standoff range nonmembers, $3.00. presents some unique requirements that are not present in a mission Research being done on turbine blades and on the cooling where cruise missiles are launched 'close' to the first fix point, as systems used in turbines is surveyed. Attention is given to the from a penetrating bomber. The methodology used and the system advances that have been made in the CF6 turbine blade with the requirements' results are described. (Author) shaped gill holes used on recent CF6 designs and film cooling cited as examples of cooling improvements. Attention is also given to the cast A81-18577 H Model-following system with assignable error cored design for blades. The benefits (among 'them corrosion dynamics and its application to aircraft. N. Kawahata (National resistance) offered by the alloy Rene' 80 are enumerated, and the Aerospace Laboratory, Chofu, Tokyo, Japan). Journal of Guidance greater repairability of blades made possible by General Electric's and Control, vol. 3, Nov.-Dec. 1980, p. 508-516. 19 refs. CODEP coating is discussed. The use of Hot Isostatic Pressing (HIP) A main objective of this paper is to propose a practical tool for to eliminate micro shrink is analyzed (the improvement in the CF6 designing a model-following system. Successive differentiations of blade from this type of pressing being equivalent to a metal output errors between a linear time-invariant system (a plant) and a temperature increase of approximately 25 F). Directional solidifica- model yield controllable output error dynamics in a block-decoupled tion is also discussed and the characteristics of new alloys (DS Rene' companion form. Such a particular form of the error dynamics 80H, Rene' 150, DS Eutectics) are presented. C.R. makes it easy to determine a model-following control law such that the output error dynamics have arbitrarily assigned stability charac- A81-18640 I: Water content of helicopter gear oils. H. A. teristics. Assigning asymptotic stability to the output error dynamics Spikes (Imperial College of Science and Technology, London, alone does not guarantee system stability. The transmission zeros England) and P. B. Macpherson (Westland Helicopters, Ltd., Yeovil, which are inherent to the input-output relations must be in the Somerset, England). American Society of Mechanical Engineers, left-hand half-plane for internal system stability. The approach has Century 2 International Power Transmissions and Gearing Confer- been applied to a variable stability and response aircraft under ence, San Francisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-12. development. An example of the longitudinal model-following 8 p. 13 refs. Members, $1.50; nonmembers, S3.00. system on this aircraft is shown to demonstrate the proposed The dissolved water contents of a number of gearbox lubricants method. (Author) have been measured in laboratory experiments, fatigue test rigs and helicopter test and service gearboxes. The effect of temperature and A81-18578 H Frequency-shaped cost functional - Extension humidity on water content has been determined. It is concluded that of linear-quadratic-Gaussian design methods. N. K. Gupta (Integrated the water levels present in test and service gearboxes may be Systems, Inc., Palo Alto, Calif.). Journal of Guidance and Control, sufficient to reduce rolling fatigue lives. A comparison of water vol. 3, Nov.-Dec. 1980, p. 529-535. 6 refs. Contract No. content in fatigue test rigs and service gearboxes shows that N00014-77-C-0247. differences exist between the two which may impair correlations of The linear-quadratic-Gaussian method for feedback control fatigue lives. (Author) design is extended to include frequency-shaped weighting matrices in the quadratic cost functional. This extension provides a means to A81-18642 ff A low height 2300 kW helicopter transmission meet classical design requirements with automated computational with an enclosed planetary gear. G. White (Transmission Research, procedures of modern control theory. A design algorithm to Inc., Cleveland, Ohio). American Society of Mechanical Engineers, optimize frequency-shaped cost functionals requires definition of Century 2 International Power Transmissions and Gearing Confer- new states and the solution of a modified linear-quadratic-Gaussian ence. San Francisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-17. problem. Four examples are presented to demonstrate frequency 6 p. Members, S1.50; nonmembers, S3.00. shaping methodology: (1) aircraft in lateral wind, (2) an industrial A helicopter main rotor transmission with inputs from two 116 A81-18683 1150-kW engines can be arranged to have the exceptionally low A81-18668 * *' Calculated and experimental data for a height of 32 cm. This low height, and consequent 10 percent 118-mm bore roller bearing to 3 million DN. H. H. Coe and F. T. reduction in weight, is made possible by the novel feature of Schuller (NASA, Lewis Research Center, Cleveland, Ohio). American enclosing the final-stage planetary gear within the support walls and Society of Mechanical Engineers and American Society of Lubrica- bearings of a large diameter spur gear. The three drive stages provide tion Engineers, Century 2 International Lubrication Conference, San an overall speed-reduction ratio of 81:1 at a main gearbox efficiency Francisco, Calif.. Aug. 18-21, 1930, ASME Paper 80-C2/Lub-14. 8 p. of 97.5 percent. Additionally, the number of critical bearings in the 16 refs. Members, SI .50; nonmembers, S3.00. main gearbox is reduced by 24 percent in comparison with Operating characteristics for a 118-mm bore cylindrical roller production transmissions of similar rating. (Author) bearing were calculated using the computer program CYBEAN. The predicted results of inner and outer-race temperatures and heat transferred to the lubricant generally compared well with experimen- A81-18646 ft Approximation of gear transmission error by tal data for shaft speeds to 3 million DN (25,500 rpm), radial loads standard gear errors. A. Toda and G. V. Tordion (Universite Laval, to 8900 N (2000 Ib), and total lubricant flow rates to 0.0102 cu Quebec, Canada). American Society of Mechanical Engineers, Centu- m/min (2.7 gal/min). (Author) ry 2 International Power Transmissions and Gearing Conference. San Francisco, Calif., Aug. 18-21, 1980. Paper 80-C2/DET-71. 6 p. 5 refs. A81 -18671 II On the steady state and dynamic performance Members, S1.50; nonmembers, S3.00. Research supported by the characteristics of floating ring bearings. C.-H. Li and S. M. Rohde National Research Council of Canada. (GM Research Laboratories, Warren, Mich.). American Society of The standard errors such as profile error, pitch error, etc. are Mechanical Engineers and American Society of Lubrication Engi- commonly measured through the existing gear testing machines. neers, Century 2 International Lubrication Conference, San Francis- However, the gear transmission error is not measured as such, co, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-17. 9 p. 13 although it is a total error of the gear system and is a principal refs. Members, $1.50; nonmembers, S3.00. contributor to the gearbox vibration. An attempt was made to relate An analysis of the steady state and dynamic characteristics of these individual errors to this important transmission error using floating ring journal bearings has been performed. The stability automotive and gas turbine gears. The results show that the characteristics of the bearing, based on linear theory, are given. The combined pitch and profile error may be approximated as the transient problem, in which the equations of motion for the bearing transmission error. (Author) system are integrated in real time was studied. The effect of using finite bearing theory rather than the short bearing assumption was A81-18648 tj Experience with advanced high performance examined. Among the significant findings of this study is the gear steel. S. Binder and J. C. Mack (Boeing Vertol Co., Philadelphia, existence of limit cycles in the regions of instability predicted by Pa.). American Society of Mechanical Engineers, Century 2 Interna- linear theory. Such results explain the superior stability characteris- tional Power Transmissions and Gearing Conference, San Francisco, tics of the floating ring bearing in high speed applications. An Calif., Aug. 18-21, 1980, Paper 80-C2/DET-77. 7 p. 7 refs. Members, understanding of this nonlinear behavior, serves as the basis for new and rational criteria for the design of floating ring bearings. (Author) $1.50; nonmembers, S3.00. A material development program is described that led to an A81-18672 * # Performance of computer-optimized tapered- advanced, high-hot-hardness gear steel with improved load-carrying roller bearings to 2.4 million DN. R. J. Parker (NASA, Lewis capacity at elevated temperatures and under marginal lubrication. Research Center, Cleveland, Ohio), S. I. Pinel, and H. R. Signer Development tasks included definition of scoring, bending fatigue (Industrial Tectonics, Inc., Compton, Calif.). American Society of strength, and tooth contact capacities and fracture mechanics Mechanical Engineers and American Society of Lubrication Engi- properties. Gears were load-run in test rigs and in endurance neers, Century 2 International Lubrication Conference, San Francis- gearboxes. Since the gear steel is also used for bearing surfaces, co, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-18. 8 p. 5 refs. rolling-contact fatigue tests were conducted. It has been found that Members, $1.50; nonmembers, $3.00. melting practice has direct effects on fracture toughness and fatigue The temperature distribution and bearing heat generation of threshold properties. Improved properties have been obtained by 120.65 mm bore high-speed tapered roller bearings was determined double-vacuum melting both the advanced steel and AISI 9310. To at shaft speeds of 20,000 rpm under simultaneous thrust and radial date, over 100 tons of the advanced steel have been processed into loads. The temperatures and thermal outputs were computed as helicopter drive components. Approximately 27,000 hr of develop- functions of shaft speed, loading lubricant flow rates, and lubricant ment, reliability and flight testing have been accomplished. The inlet temperatures. Bearing temperatures and heat generation were material was selected for the gear train of the modernized U.S. Army considerably lower than in standard bearings; cup cooling was CH-47D (Chinook) helicopter, for which qualification testing is now effective in lowering cup temperatures to levels of cone tempera- complete. Improved characteristics will reduce maintenance and tures. A.T. provide increased reliability for this helicopter. (Author) A81-18683 * ii Dynamic characteristics of a high-speed rotor A81-18654 H The rigidity and performance of a simple spiral with radial and axial foil-bearing supports. L. Licht, W. J. Anderson bevel helicopter gearbox. M. M. A. Taha, C. M. M. Ettles, and P. B. (NASA, Lewis Research Center, Cleveland, Ohio), and S. W. Doroff Macpherson (Imperial College of Science and Technology, London, (U.S. Navy, Office of Naval Research, Arlington, Va.). American England). American Society of Mechanical Engineers, Century 2 Society of Mechanical Engineers and American Society of Lubrica- International Power Transmission and Gearing Conference, San tion Engineers, Century 2 International Lubrication Conference, San Francisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-103. 10 p. 5 Francisco, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-35. 10 refs. Members, $1.50; nonmembers, $3.00. Research supported by p. 15 refs. Members, S1.50; nonmembers, $3.00. NASA-Navy- the Ministry of Defence (Procurement Executive). sponsored research. The analysis of Taha et al (1978) on the performance of a An asymmetric rotor (19N; 4.3 Ib), supported radially and helicopter gearbox with a cantilevered housing and two taper roller axially by compliant bearings is subjected to severe excitation by bearings is extended to include a complete gearbox. The deflections rotating unbalance in the 'pitching' mode at speeds to 50,000 rpm. at the tooth contact points must be determined precisely to provide The resilient, air-lubricated bearings provide very effective damping, an even operation of spiral bevel gears; these deflections are a so that regions of resonance and instability can be traversed with function of the transmitted torque, bearing preloads, rigidity of the amplitudes and limit-trajectories within acceptable bounds. A novel casings and shafts, bearing spacings, and bearing alignment. Finally, journal bearing is introduced, in which a resilient support is furnished the effects of misalignment between the bearing races, shaft and by the outer turn of the coiled foil-element bent to form an open casing, and spacer deformations are discussed. AT. polygon. The experimental apparatus and procedure are described. 117 A81-18738 and the response of the rotor and flexible support system are decision making, and observational control in the detection of documented by oscilloscope records of motion. (Author) unexpectedly appearing objects and measurement of their parame- ters. Such situations may arise in astronomy, laser, sonar, and lidar A81-18738 * ,-f Lubrication of rolling element bearings. R. J. observations, recording of microparticles, etc. The analysis is carried Parker (NASA, Lewis Research Center, Cleveland, Ohio). American out within the framework of the theory of statistical solutions. Society of Mechanical Engineers and American Society of Lubrica- Attention is given to practical aspects and to the effectiveness of the tion Engineers, Century 2 International Lubrication Conference, San optimal and suboptimal algorithms proposed for information pro- Francisco, Calif., Aug. 18-21, 1980, Paper. 24 p. 47 refs. cessing and observation control. V.P. This paper is a broad survey of the lubrication of rolling-element bearings. Emphasis is on the critical design aspects related to speed, A81-18777 Prediction methods for fatigue crack growth in temperature, and ambient pressure environment. Types of lubrica- aircraft material. J. Schijve (Delft, Technische Hogeschool, Delft, tion including grease, jets, mist, wick, and through-the-race are Netherlands). In: Fracture mechanics; Proceedings of the Twelfth discussed. The paper covers the historical development, present state National Symposium, Washington University, St. Louis, Mo., May of technology, and the future problems of rolling-element bearing 21-23, 1979. Philadelphia, Pa., American Society lubrication. (Author) for Testing and Materials, 1980, p. 3-34. 41 refs. The present state of knowledge of fatigue crack growth and A81-18748 Surface analysis of bearing steels after solvent qualitative and quantitative understanding of predictions are re- treatments. II - Lubricant-coated bearing surfaces. M. K. Barnett viewed with reference to the developments in experimental tech- (U.S. Navy, Naval Research Laboratory, Washington, D.C-). Ameri- niques and indications obtained from fatigue of aircraft structures. can Society of Lubrication Engineers and American Society of Results of recent work on the prediction of fatigue crack growth in Mechanical Engineers, International Lubrication Conference, San aluminum alloys are reported, including (1) crack growth under Francisco, Calif., Aug. 18-21, 1980, ASLE Preprint 80-LC-8A-6. 7 p. flight-simulation loading with crack closure measurements, (2) crack 15 refs. Navy-sponsored research. growth predictions for flight-simulation loading based on a constant In order to evaluate the effectiveness of standard cleaning crack opening stress level, and (3) crack growth under random procedures and individual solvents, reference surfaces of 440C loading to explore the usefulness of the root mean square K-value bearing steel were coated with thin films of a formulated synthetic and to observe effects of irregularity and crest factor. V.L. hydrocarbon or a formulated polyol ester instrument lubricant and exposed to the solvent cleaning process. The surfaces were then A81-19296 ft A fault tolerant multiprocessor system with analyzed by wettability, Auger electron and X-ray photoelectron reconfiguration suitable for multiaxial flight stabilization and trim- spectroscopies, and by Fourier transform infrared spectroscopy. ming (Fehlertolerantes, rekonfigurierbares Mehrrechnersystem, geeig- Results are discussed in terms of cleaning efficiency, recontamina- net zur mehrachsigen Flugstabilisierung und -trimmung). D. Schmidt tion, and types of random contamination. V.L. (Litton Technische Werke der Hellige GmbH, Freiburg im Breisgau, West Germany). Bundesministerium fur Forschung und Technologie, A81 -18758 The wear of PTFE-containing dry bearing Statusseminar zur Luftfahrtforschung und Luftfahrttechnologie, liners contaminated by fluids. R. W. Bramham, R. B. King, and J. K. Garmisch-Partenkirchen, West Germany, Oct. 8, 9, 1980, Paper. 12 Lancaster (Royal Aircraft Establishment, Farnborough, Hants., p. In German. Research supported by the Bundesministerium fur England). American Society of Lubrication Engineers and American Forschung und Technologie. Society of Mechanical Engineers, International Lubrication Confer- This paper investigates a redundant processor system for time ence, San Francisco, Calif., Aug. 18-21, 1980, ASLE Preprint critical process control with high reliability, fault tolerant proce- 80-LC-6B-3.9p. 15 refs. dures, and soft-wave control reconfiguration. Redundancy in the The influence of fluid contamination on the wear of aircraft dry assemblies and the bus system of the hardware is discussed and the bearing liners has been examined using an accelerated test procedure. structure of the computer system is presented for n identical and It is shown that fluids generally increase wear to an extent depending autonomous processors coupled with m serial bus connections. A on the level of stress, the type of fluid and the structure and cross coupler consisting of several multiplexers is examined in composition of the liner material. Water is deleterious, but at low relation to configuration of the central processing units and the stresses mineral and diester oils can sometimes reduce the wear rate storage units. A model for the software system which is subdivided below that obtained in dry conditions. Explanations for the trends into a central unit and parallel operating functions is illustrated. R.C. observed are deduced from an examination of worn surfaces by X-ray photoelectron spectroscopy and scanning electron microscopy. (Author) A81-19297 H Automatization of the adhesion process for supporting airframe pans in light contour systems (Automatisierter A81-18759 Ferrography as a health monitor and a design Klebeprozess fur tragende Flugzeug-Zellenbauteile in leichten aid for the development of helicopter gearboxes. G. Pocock and S. J. Kontursystemen). H.-J. Rieckhof (Messerschmitt-Bolkow-Blohm Courtney (Admiralty Marine Technology Establishment, Poole, GmbH, Hamburg, West Germany). Bundesministerium fur Forschung Dorset, England). American Society of Lubrication Engineers and und Technologie, Statusseminar zur Luftfahrtforschung und Luft- American Society of Mechanical Engineers, International Lubrication fahrttechnologie, Garmisch-Partenkirchen, West Germany, Oct. 8, 9, Conference, San Francisco, Calif., Aug. 18-21, 1980, ASLE Preprint 1980, Paper. 19 p. In German. 80-LC-6B-4. 6 p. 9 refs. This paper examines a simpler fixture along with automatic The use of ferrography to monitor the health of helicopter procedures for a more economical construction of airframes. The gearboxes undergoing fatigue substantiation trials is described. The fixture consists of a light profile airframe and several milled or cast results illustrate the sensitivity of ferrography in detecting the onset mounting parts. The mass of the fixture is 190 kg compared to 700 of gear fatigue and indicate that the fatigue was initiated by kg for previous fixtures and better pressure ratios in the adhesion micropitting. This suggests that the gears were not properly joints are obtained. An automatic quality control procedure based on lubricated under the fatigue loads. (Author) the Squirter inspection principle is also discussed. R.C. A81-18773 # Detection of moving objects (Obnaruzhenie A81 19298 ,7 A summary of proposals for airflight research dvizhushehikhsia ob'ektov). P. A. Bakut, lu. V. Zhulina, and N. A. by the BMFT (Uberblick iiber die Fdrderung der Luftfahrtforschung Ivanchuk. Moscow, Izdatel'stvo Sovetskoe Radio, 1980. 288 p. 59 durch das BMFT). H. Hertrich (Bundesministerium fiir Forschung refs. In Russian. und Technologie, Bonn, West Germany). Bundesministerium fiir The book deals with the optimization of information processing. Forschung und Technologie, Statusseminar zur Luftfahrtforschung 118 A81 19346 und Luftfahrnechnologie, Garmisch-Partenkirchen, West Germany, krylo-korpus, raspolozhennoi pod uglom ataki k nabegaiushchemu Oct. 8, 9, 1980, Paper. 30 p. In German. sverkhzvukovomu potoku). S. I. Kusakin. Akademiia Nauk SSSR, This paper examines the aims and distribution of government Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1980, p. 136-148.8 grants by the Federal Department for Research and Technology refs. In Russian. (BMFT) for airflight research. Projects include investigations into A theoretical study of the velocity field formed near a interference phenomena related to airfoil and lift, and carbon fiber wing-body combination in supersonic flow is presented;-the charac- technology for civilian aircraft construction. Research into better teristics of the field related to the effects of the body (i.e., the handling of increased air traffic and cooperation in projects with fuselage) are emphasized. Attention is given to the general form of other European countries and the U.S. are also discussed. Statistics the singular term of the asymptotic expansion of the solution of the on financial support for airflight research are reported for 1979 to linear equation in the vicinity of the Mach cone that starts at the 1982. R.C. intersection of the leading edge of the wing and the surface of the body. A uniformly exact solution is obtained for the nonlinear A81 -19299 jf Stress measurements on landing gear for the differential equation of additional velocity potential. The position Airbus A-300 B2 (Beanspruchungsmessungen am Fahrwerk des and location of the shock on the upper surface of the wing are determined. B.J. Airbus A-300 B2). O. Buxbaum (Fraunhofer-lnstitut fur Betriebs- festigkeit, Darmstadt, West Germany). Bundesministerium fiir Forschung und Technologie, Statusseminar zur Luftfahrtforschung A81 -19338 ;/' Propagation of three-dimensional acoustic per- und Luftfahrnechnologie, Garmisch-Partenkirchen, West Germany, turbations in channels of variable cross-sectional area at frequencies Oct. 8, 9, 1980, Paper. 20 p. 12 refs. In German. dose to cutoff frequency (Rasprostranenie trekhmernykh akusti- This paper investigates operational characteristics of landing gear cheskikh vozmushchenii v kanalakh peremennoi ploshchadi pope- in relation to changes in aircraft design. The distinction between fail rechnogo secheniia pri chastotakh, blizkikh v chastote otsechki). A. safe and safe line landing parts is discussed and preliminary results A. Osipov. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i with an Airbus A-300 82 aircraft are presented. Measurement of Gaza, Nov.-Dec. 1980, p. 149-159. 8 refs. In Russian. spring deflection of the landing gear stabilizer is discussed along with The paper presents a theoretical study of the propagation of determination of the steering force on the nose end landing gear. The three-dimensional acoustic disturbances in a two-dimensional gas effect of increased rolling time on landing gear design is examined flow in axisymmetric channels of variable cross-sectional area at along with the torsion moment during the banking roll. R.C. frequencies close to the cutoff frequency. Attention is given to slow changes of cross-sectional area along the channel. The application of A81-19300 // Hingeless tailrotor in fiber composite construc- the WKB approximation to the present problem is considered, and a tion and vibration-isolation systems /ARIS, AS IS/ for helicopters method is developed for calculating the reflection coefficient of the (Gelenkloser Heckrotor in Faserverbund-Bauweise und Schwingungs- acoustic disturbances. The present study may be applicable to the Isolationssysteme /ARIS, AS IS/ fiir Hubschrauber). G. Reichert investigation of noise emission from jet engines. B.J. (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany). Bundesministerium fiir Forschung und Technologie, Statusseminar zur Luftfahrtforschung und Luftfahrnechnologie, Garmisch- A81-19342 SNIAS helicopters (Les helicopteres de la SNIAS). G. Bruner. L'Aeronautique et I'Astronautique, no. 84, Partenkirchen, West Germany, Oct. 8, 9, 1980, Paper. 35 p. 8 refs. In 1980, p. 21-30. 34 refs. In French. German. (MBB-UD-311-80-0) The design of tailrotors and vibration isolation systems for The helicopters manufactured by the French firm SNIAS (the helicopters is discussed. Elastic bend-torsion elements are examined Aerospatiale National Industrial Company) are reviewed. Specifica- in place of the hinge and bearings of the tail rotor, which provide a tions, model types and brief commercial histories are presented for reduction in weight, cost, and waiting time for operation. Emphasis the Alouette III, Super Frelon, Puma, Gazelle, Lama, Dauphin, is placed on determining the aerodynamic stability of the system for Ecureuil and Super Puma. SNIAS facilities for helicopter production full operation. The reduction of rotor induced cell vibration through and means employed for the fabrication of composite blades are also rotor isolation is also investigated. Passive units without additional pointed out. A.L.W. energy input and active units with disturbance variable compensation are considered. R.C. A81-19344 The design-to-cost of aircraft (La conception a couts objectifs des avions). M. Tassinari (Societe Nationale Industri- A81-19325 - Some aspects of optimizing the aerodynamics elle Aerospatiale, Paris, France). L'Aeronautique et I'Astronautique, of turbine stages (Problemy optymalizacji aerodynamicznej stopnia no. 84, 1980, p. 37, 38. In French. turbiny). R. Puzyrewski (Polska Akademia Nauk, Instytut Maszyn The application of the design-to-cost approach to the manufac- Przeplywowych, Gdansk, Poland). Instytut Maszyn Przeplywowych, ture and design of aircraft is examined. The various costs involved in Prace, no. 78, 1980, p. 101-108. In Polish. the production and utilization of an aircraft are reviewed, with The principal factors which define the efficient operation of a attention given to development, industrialization, production and turbine stage are discussed, and the characteristic areas of kinetic indirect costs borne by the manufacturer, the acquisition, utilization, energy dissipation are identified. A method of matching the guide maintenance and Hie cycle costs borne by the user, and the global wave and rotor blade systems for maximal stage efficiency is cost borne by all involved, and advantages of the design-to-cost proposed. V.P. approach in controlling global production costs while ensuring product quality are pointed out. The development of design-to-cost in the United States as a means of controlling Defense Department A81-19335 ft Determination of the effect of transverse cost overruns is then traced, and the use of a proposal procedure cutouts on the hydrodynamic characteristics of a finite-span wing in based on minimal technical specifications and an imposed production the case of steady and unsteady motion near a wall (K otsenke cost is emphasized. A.L.W. vliianiia poperechnykh vyrezov na gidrodinamicheskic koeffitsienty kryla konechnogo razmakha pri statsionarnom i nestatsionarnom dvizhenii vblizi steoki). K. V. Rozhdestvenskii. Akademiia Nauk A81-19346 Aircraft engine programs employing cost ob- SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1980, p. jectives (Programmes de moteurs d'avions a objectifs de cout). C. 122-128. In Russian. Foure. L'Aeronautique et I'Astronautique, no.. 84, 1980, p. 41, 43-48. In French. A81 -19337 :; Characteristics of the velocity field near a Consideration is given to the procedures to be followed in a wing-body combination located at an angle of attack to an oncoming program of aircraft engine development, production and utilization supersonic flow (Osobennosti polia skorostei vblizi kombinatsii in which cost objectives are accorded the same importance as 119 A81-19347 technical objectives. The practice of value analysis, which includes decrease in drag is obtained with pneumatic turbulators that blow the identification and ordering of user requirements, the identifica- ram air out of 0.6 mm pilot tubes at a distance of 16 mm. The tion of functions to be provided and the prediction of production pneumatic models can be implemented at various positions and are costs, is discussed and illustrated for the case of the cycle definition also found to be effective after the position of separation. R.C. and scaling stage of engine airflow using the technique of mass estimation. The roles of studies of technical and technological A81-19393 j Drag reduction through formation flight progress, reliability and lifetimes, and maintenance requirements in (Widerstandersparnis durch Formationsflug). D. Hummel and K.-W. engine development are considered, and measures which can be taken Bock (Braunschweig, Technische Universitat, Braunschweig, West following the initial design stage to reduce life cycle costs are pointed Germany). Deutsche Gesellschaft fur Luft- und Raumfahrt, Sym- out. Finally, organizational structures developed for the carrying out posium iiber Aerodynamischen Widerstand, Cologne, West Germany, of engine programs with cost objectives are examined. A.L.W. Nov. 25, 26. 1980, Paper 80-106. 53 p. 12 refs. In German. Improved performance through formation flying is examined A81-19347 Design to cost and new technologies (Design with an estimation procedure. Reductions up to 20% of the to cost et technologies nouvelles). F. Cordie (Avions Marcel-Dassault- performance in solo flight are obtained. Total performance is shown Breguet Aviation, Direction Generale Technique, Saint-Cloud, Hauts- to be dependent on the number and lateral distance of the aircraft de-Seine, France). L'Aeronautique et I'Astronautique, no. 84, 1980, and independent of the arrangement. The greatest reduction is found p. 49-55. In French. towards the center of the formation, and the optimal flight speed of The impact of the advent of new aircraft production technolo- a formation of similar aircraft is less than that for a solo flight. The gies on the design to cost process is discussed. The process of reciprocal induction field with gliders at close distances is also determining the mass-cost relationship of a new construction investigated. R.C. technology representing an improvement in aircraft weight and a reduction in cost is considered, and design consequences of a weight reduction are pointed out. Consideration is then given to the A81-19395 # Calculation of the lift dependent drag polar of development of composite material technology for military aircraft, cambered fighter plane configurations with deflected maneuver flaps and it is pointed out that the use of composites, which currently in the subsonic region by means of a modified procedure according represent 35 to 40 percent of the mass of an advanced combat to Lamar (Berechnung der auftriebsabhangigen Widerstandspolaren aircraft, has lead to reductions in both aircraft mass and cost, von verwolbten Kampflugzeugkonfigurationen mit ausgeschlagenen particularly when the technology is considered in the design stage in Manoverklappen im Unterschall an Hand eines modifizierten Verfah- the design to cost process. A.L.W. rens nach Lamar). G. Wedekind (Dornier GmbH, Friedrichshafen, West Germany). Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium iiber Aerodynamischen Widerstand, Cologne, West Ger- A81-19348 Pyrotechnics serving safety (La pyrotechnic au many, Nov. 25,26, 1980, Paper 80-109. 15 p. In German. service de la securite). S. Morlan (Societe Nationale Industrielle A procedure to calculate lift and camber dependent drag is Aerospatiale, Division Systemes Balistiques et Spatiaux, Ues examined in relation to the suction force analogy of Polhamus Mureaux, Yvelines, France). L'Aeronautique et I'Astronautique, no. (1971) and a method by Lamar (1975, 1974) in which the suction 84, 1980, p. 57, 59-61. 63-66. In French. forces at the wing leading edge and side edge are calculated directly Possible applications of pyrotechnics technology capable of and rotated vertical to the wing plane. The effects of a rounded-off improving aircraft safety in the air and on the ground are examined. nose and wing camber are also taken into account. A correction Consideration is given to the use of pyrotechnics in military aviation method is derived for the polars of an uncambered wing-fuselage automatic canopy jettisoning systems and pyrotechnic logic circuits, combination along with modification for variations in the width of in civil aviation in the in-flight evacuation and protection system of the nose region. In the case of cambered wings, the suction force is the Corvette prototype aircraft, and in possible ground escape rotated vertical to the wing plane regardless of the nose camber for systems for civil and commercial aircraft that have crashed. A.L.W. calculating leading edge turbulence. R.C. A81 -19375 System considerations in the implementation A81-19396 H Procedures for optimal drag design of camber of digital control. K. C. Daly (Charles Stark Draper Laboratory, Inc., and flap deflection in supersonic regions with consideration to Cambridge, Mass.). In: Guidance and control 1980; Proceedings of geometric limits (Verfahren zum widerstandsoptimalen Entwurf der the Annual Rocky Mountain Conference, Keystone, Colo., February Wolbung und Klappenausschlage im Uberschall unter Beruck- 17-21, 1980. San Diego, Calif., Univelt, Inc., sichtigung geometrischer Einschrankungen). G. Wedekind (Dornier 1980, p. 651-664. 16 refs. (AAS 80-032) GmbH, Friedrichshafen, West Germany). Deutsche Gesellschaft fiir The intent of this paper is to address several of the most Luft- und Raumfahrt, Symposium iiber Aerodynamischen Wider- significant system requirements for digital controllers and to deter- stand, Cologne, West Germany, Nov. 25, 26, 1980, Paper 80-110. 17 mine how the processing system organization and performance p. In German. affects these criteria. Special emphasis is given to control require- This paper examines procedures for the optimization of camber ments resulting from system configurations designed to produce high in wing design of fighter planes. The method of Lagrange multipliers integrity controllers. The resulting interaction between reliability and is presented for the camber optimization algorithm in the supersonic performance considerations is also discussed. (Author) region along with calculations for the determination of pressure distribution and drag. An optimally cambered delta wing is illus- A81-19392 H Reduction of profile drag by blowing out trated and the induced drag is compared to drag with and without through peg holes in areas of streamline separation bubbles (Verrin- suction force. A method for combining individual wings with similar gerung des Profilwiderstandes durch Ausblasen aus Lochreihen im design but different camber is also examined. R.C. Bereich laminarer Abloseblasen). K. H. Horstmann and A. Quast (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, A81-19397 # Experimental investigation of a right angle Institut fiir Entwurfs-Aerodynamik, Braunschweig, West Germany). wing with partially separated flow with and without ground effects Deutsche Gesellschaft fur Luft- und Raumfahrt. Symposium iiber (Experimentelle Untersuchung eines Rechteckfliigels bei teilweise Aerodynamischen Widerstand, Cologne, West Germany, Nov. 25, 26, abgeloster Strbmung ohne und mit Bodeneinfluss). H. Bippes, M. 1980, Paper 80-103. 18 p. In German. Turk, and K. Jacob (Deutsche Forschungs- und Versuchsanstalt fiir This paper investigates the problem of streamline separation Luft- und Raumfahrt, Gottingen, West Germany). Deutsche Gesell- bubbles on aircraft profiles and fuselages. The additional drag is schaft fiir Luft- und Raumfahrt, Symposium iiber Aerodynamischen examined in relation to increased angle of incidence and unusually Widerstand, Cologne', West Germany, Nov. 25. 26, 1980, Paper high wall shear stress. A reduction in the separation bubble and a 80-111. 19 p. 6 refs. In German. 120 A81-19444 This paper investigates ground effects on flight performance functions performed by ATC. The structure of a real-time system with partially separated flow. Tests are carried out with a NACA proposed for channel management is described; the major surveil- 4415 profile with an aspect ratio from 1.5 to 6.2. At smaller lance functions are developed, and a number of design criteria to distances higher pressure along the total wing chord is found in the reduce the associated computational effort are presented. Finally, an middle section of the pressure side of the wing with an increase in evaluation of interrogation-reply scheduling techniques is presented. the collection point of the suction side leading to an increase in lift. B.J. A net performance gain is registered despite an increase in the profile drag. A secondary flow of low intensity is observed in the region A81 -19425 Characteristics of NAVSTAR user stations between the separated and adjoining flow. B.C. (Particularity des stations d'utilisateur du systeme NAVSTAR). G. David and J. P. Van Uffelen (Telecommunications Radio-Electriques ASM9398 H The practical application of the Wake Blocking et Telephoniques, Le Plessis-Robinson, Hauts-de-Seine, France). Corrections according to Maskell (Die praktische Anwendung der L'Onde Electrique, vol. 60, Dec. 1980, p. 23-29. 7 refs. In French. Wake Blocking-Korrekturen nach Maskell). H. Kamber (Eidge- The characteristics of the NAVSTAR/GPS satellite navigation nossisches Flugzeugwerk, Emmen, Switzerland). Deutsche Gesell- system are examined in relation to the operational requirements for a schaft fur Luft- und Raumfahrt, Symposium fiber Aerodynamischen user station. Following a brief review of the NAVSTAR system and Widerstand, Cologne, West Germany, Nov. 25, 26, 1980, Paper its advantages over previous navigation systems, consideration is 80-112. 30 p. I n German. (FO-1533) given to the types of signals emitted by the 18 satellites in the With the construction of larger wind channel models, wall system, their modulation and the C/A (clear acquisition) and P effects play a greater role. This paper examines uncertainties found (protected) codes used for distance measurements. The synchroniza- in the Wake Blocking Correction method, particularly in reference to tion of a local code with the received signal in the decoding of the larger models. Difficulties arise in the selection of the profile transmitted signal and the acquisition of time measurements by the resistance and in the determination of the induced resistance which synchronization acquisition and tracking components of the receiver cannot be obtained satisfactorily through measurement. A modifica- is discussed, and the functions and components of the user station, tion for calculating the profile resistance is presented along with including antenna and preamplifier, receiver, and signal processor, are various methods for determining the induced resistance. R.C. examined. It is pointed out that the GPS offers users moving at high speeds the possibility of determining their position with greater A81-19399 # Drag estimations for stream-line and cylin- accuracy than any other existing system of long-range navigation. drical contour distortions on aircraft fuselages and train cars A.L.W. (Widerstandsabschatzung fur stromlinienformige und zylindrische Konturstorungen an Rugzeugriimpfen und Eisenbahnwaggons). H. A81-19441 « Experimental investigation of orographic Neppert (Messerschmitt-Bolkow-Blohm GmbH, Hamburg, West Ger- waves and vertical motions in the Krasnovodsk airport area (Eksperi- many). Deutsche Gesel/schaft fur Luft- und Raumfahrt, Symposium mental'nye issledovaniia orograficheskikh voln i vertikal'nykh dvizhe- iiber Aerodynamischen Widerstand, Cologne, West Germany, Nov. nii v raione Aeroporta Krasnovodsk). 0. A. Liapina and E. I. Sofiev 25, 26, 1980, Paper 80-116. 17 p. 21 refs. In German. (Sredneaziatskii Regional'nyi Nauchno-lssledovatel'skii Institut, This paper discusses drag estimations for cylindrical and USSR). Meteoro/ogiia i Gidrologiia, Nov. 1980, p. 49-53. In Russian. aerodynamically stream-line bodies such as warning lights on aircraft The difficult conditions for aircraft approach for landing in fuselages and trains. Compressibility measurements in wind channels strong northerly winds were investigated. Orographic waves were are examined in relation to drag estimations. Cylindrical and studied using constant level balloons tracked by double-theodolite stream-line warning light casings are compared for drag reduction and observations; vertical motions were determined by conventional fuel conservation. The effect of the length of the boundary layer on pilot-balloon measurements. Wave parameters, their origins, and their drag is investigated with casings on train wagons. R.C. effects on aircraft landing approach conditions are presented. A.T. A81-19400 ff The determination of the induced drag on slim wings with high lift systems in the transonic region (Zur Ermittlung A81 -19442 ti Conditions of generation and methods of des induzierten Widerstandes an schlanken Fliigeln mit Hochauf- damping the inlet vortex of a turbojet engine (Warunki generowania i triebssystemen im transsonischen Bereich). W. Sonnleitner metody tlumienia wiru wlotowego turbinowego silnika odrzutowe- (Messerschmitt-Bolkow-Blohm GmbH, Ottobrunn, West Germany). go). T. Gajewski (Wuzsza Oficerska Szkola Lotnicza, Deblin, Poland). Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium iiber Technika Lotnicza i Astronautyczna, vol. 35, Nov. 1980, p. 5-8. 19 Aerodynamischen Widerstand, Cologne, West Germany, Nov. 25, 26, refs. In Polish. 1980, Paper. 27 p. 28 refs. In German. (MBB-FE122) An aeromechanical analysis of the generation of an inlet vortex This paper investigates the effect of aircraft flaps with emphasis in a turbojet engine is presented. Methods for the prevention of on trail edge flaps. Potential theoretical methods for the calculation vortex generation and methods of vortex damping are described. B.J. of flap effects are compared with semi-empirical handbook methods. A Gaussian least squares method is presented for approximation of polars near the crown and a formula for calculating the suction A81-19443 # Map-type displays (Wskazniki mapowe). Z. power explicitly is presented. The discrepancy between the calculat- Mrotek (Instytut Lotnictwa, Warsaw, Poland). Technika Lotnicza i ed K-values for the induced drag and experimental results is discussed Astronautyczna, vol. 35, Nov. 1980, p. 11-16. 5 refs. In Polish. along with empirical correction functions. R.C. The basic characteristics of map-type displays are described in order to compile a classification of such devices. Particular attention is given to the Decca Automatic Chart Display, the Decca Flight Log, A81-19417 Performance evaluation of an interrogation- the ACA Horizontal Situation Indicator, and the Ferranti Combined reply scheduling technique for a discrete address beacon system. G. Map and Electronic Display. B.J. Bucci (CNR, Centre di Studio per I'lnterazione Operatore- Calcolatore, Bologna, Italy) and D. Maio (Bologna, Universita, Bologna, Italy). In: Digital signal processing. A81-19444 />' Calculation of propeller efficiency for an ideal London and New York, Academic Press, 1980, p. 239-250. 8 refs. propeller (Obliczenie sprawnosci smigla idealnego). Technika Lotnic- Research supported by the Consiglio Nazionale delle Ricerche. za i Astronautyczna, vol. 35, Nov. 1980, p. 25, 26. In Polish. Some results of a study carried out as part of an ATC project In the initial design of aircraft power plants, use is made of an sponsored by the Italian CNR are presented. The main objectives 'estimated' propeller characteristic which reflects correctly the were to implement the ATC system on mini or microcomputers; to influence of changes in such parameters as the propeller diameter, air give an account of the maximum supported target load; and to density, etc. In the present paper, a method of deriving such a achieve the greatest reliability of the surveillance and communication characteristic is proposed. The solution obtained yields the upper 121 A81 19445 bounds of the theoretical potentialities of propeller-type aircraft A joint supersonic V/STOL fighter development and flight power plants. V.P. demonstration program is being proposed by McDonnell Douglas and Rolls-Royce. The proposed flight demonstration aircraft is based on the use of a modified Marine/British Aerospace AV-8A airframe and A81-19445 ft Collisions between aircraft and birds (Zderze- the Rolls-Royce Pegasus 11 engine to increase overall engine thrust nia samolotow z ptakami). S. Tujaka (Przemyslowy Instytut Tele- by 50%. The four-to-five year development and flight demonstration komunikacji, Gdansk, Poland). Technika Lotnicza i Astronautyczna, program would produce an aircraft capable of flight in the Mach 1.6 vol. 35, Nov. 1980, p. 27, 28. In Polish. region and would cost 300-500 million dollars. By using the STOL The danger that birds pose for aircraft is described. Attention is capability, USAF aircraft could be airborne in approximately 1200 given to the flight altitudes of various species of birds, types of bird ft, carrying a full load of ordnance. Mission capabilities include close flight, and methods of preventing collisions between aircraft and air support and interdiction. P.T.H. birds in the vicinity of airfields. B.J. A81-19491 Solid-state power system use expands. P. J. A81-19469 Circulation Control Wing /CCW/ flight tests. C. Klass. Aviation Week and Space Technology, vol. 114, Jan. 12, 1981, Sewell (Grumman Aerospace Corp., Bethpage, N.Y.). Society of p. 70, 71, 73. Experimental Test Pilots, Technical Review, vol. 15, no. 1, 1980, p. Variable-speed constant-frequency (VSCF) systems for supply- 6-20. ing aircraft electric power are challenging more traditional hydro- The Circulation Control Wing (CCW) design, based on the mechanical constant-speed type systems for military applications Coanda effect, involves the conversion of the trailing edge of the after nearly two decades of development. The potential appeal of airfoil into an enlarged rounded surface to which a jet of air adheres VSCF is the reduction of moving parts, which holds promise of when blown tangentially from the upper surface. The resulting high higher reliability and reduced maintenance. It also offers more augmentation of circulation lift reduces landing approach and precise control of frequency and voltage, and responds more quickly takeoff velocities and distances, and offers options for increased to large electric load changes to minimize voltage and frequency aircraft payload and wing loading. The aerodynamic technology for transients. The operational payoff in terms of increased avionics the CCW program was developed by the NSRDC. A contract for the reliability is difficult to measure, however. This paper examines design and modification of an A-6A aircraft to the CCW configura- applications of VSCF, with particular attention given to the 40-kva tion and subsequent flight testing was awarded to Grumman in 1977. system that Westinghouse will supply for the F-5G (the system is Flight testing began Jan. 29, 1979 and was completed Mar. 1, 1979 expected to be scaled-up version of its 20-kva dc link system in 16 flights for a total of 25 hours. P.T.H. designed for the AV-8B). P.T.H. A81-1947Q Planning for and evaluating the potential of a land based aircraft for carrier operations. P. S. Norton (Lockheed- A81-19497 Fighters for the 1990s. M. Lambert. Interavia, California Co., Burbank, Calif.). (Society of Experimental Test vol. 36, Jan. 1981, p. 19-26. Pilots, European Symposium, 11th, Bristol, England, Apr. 1979.1 Programs under way in the U.S., Britain, West Germany, and Society of Experimental Test Pilots, Technical Review, vol. 15, no. France to design fighter aircraft for the 1990's are surveyed noting 1,1980, p. 21-35. that the principles of survivability, lethality, and affordability are The role of the test pilot in performing a compressed and fairly paramount. The stealth concept is illustrated through a diagram of complicated shore-based carrier suitability evaluation of a land-based the Tactical High Altitude Penetrator. Various concepts that will aircraft is considered. Particular attention is given to an evaluation figure in fighter design are presented, among them the supercruiser, which Lockheed conducted with the Dassault/Dornier Alpha Jet at forward sweep, and the Advanced Fighter Technology Integrator Istres, France; the evaluation is examined through the test pilot's AFTI/F-16 (offering six-degree-of-freedom flight). The AFTI/F-111 viewpoint, with emphasis on the test pilot's personal role and Mission Adaptive Wing, with flexible plastic skin on the upper wing contribution to the overall effort. The evaluation is relatively unique surface and special internal control linkages, is discussed, as is the because it has served to measure the potential of a land-based aircraft HiMAT Highly Maneuverable Aircraft Technology demonstrator for carrier operations without operation from an actual aircraft (performance design point, Mach 0.9 at 30,000 ft; maximum speed, carrier. Several primary facilities, such as a mirror landing system, more than Mach 1.5; able to pull 6G at Mach 1.2 at 30,000 ft). adjustable angle of attack system, and telemetry, were required. Attention is also given to runway dependence, integrated avionic P.T.H. control, and propulsion to Integrated Flight/Fire Control. C.R. A81-19471 * A status report on NASA general aviation A81-19498 Primary training of military pilots - Changing stall/spin flight testing. J. M. Patton, Jr. (NASA, Langley Research theories and new trainers. M. Grangier. Interavia, vol. 36, Jan. 1981, Center, Hampton, Va.). Society of Experimental Test Pilots, Tech- p. 29-33. nical Review, vol. 15, no. 1, 1980, p. 36-49. 9 refs. The need to choose between propeller, turboprop, and jet The NASA Langley Research Center has undertaken a compre- aircraft for the primary training of military pilots is discussed with hensive program involving spin tunnel, static and rotary balance wind high fuel costs cited as one of the factors limiting flight training. It is tunnel, full-scale wind tunnel, free flight radio control model, flight noted that turboprops seem to be growing in favor since they make it simulation, and full-scale testing. Work underway includes aero- possible to give pilots more advanced training. They can be used not dynamic definition of various configurations at high angles of attack, only to train pilots in the classical missions of primary training (basic testing of stall and spin prevention concepts, definition of spin and training, conversion) but also to give them experience in instrument spin recovery characteristics, and development of test techniques and flying, navigation with IFR equipment for day/night observation, emergency spin recovery systems. This paper presents some interest- aerobatics, and formation flying. Training aircraft under develop- ing results to date for the first aircraft (low-wing, single-engine) in ment in various countries are discussed, including the Aerospatiale the program, in the areas of tail design, wing leading edge design, Epsilon, the Caproni Vizzola C-22J, the Embraer EMB-312, the mass distribution, center of gravity location, and small airframe Gulfstream American Peregrine 600, and the SIAI-Marchetti S.211 changes, with associated pilot observations. The design philosophy of and SF.260TP. C.R. the spin recovery parachute system is discussed in addition to test techniques. P.T.H. A81-19499 Visual systems at Lufthansa's simulator centre. J. Gegerle. Interavia, vol. 36, Jan. 1981, p. 42, 43. ASM9490 Industry proposes supersonic V/STOL. C. A. The high cost of in-flight pilot training has spurred the Robinson, Jr. Aviation Week and Space Technology, vol. 114, Jan. development of simulators in civil aviation. Lufthansa's experience 12, 1981, p. 36-39, 42. with simulators is discussed, with attention given to recent improve- 122 A81 19636 ments. Redifon's Daynite, a daylight Computer Generated Imagery for the determination of the optimal distribution of the wing system, is analyzed, as is the newer IMovoview SP2 system. The latter cambers for subsonic and transonic flight velocities. A.Y. can offer night scenes having as many as 5,000 light points and daylight scenes having a large number of surfaces. Economic A81-19631 The coordinate-deformation method in the incentives will ensure the continued development of simulators: problem of a supersonic gas flow over an airfoil. S. I. Kusakin and M. Lufthansa estimates that it costs $12,360 for one flight hour on a F. Pritulo. (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu 747, compared with $515 for the same time in a simulator. C.R. so dnia rozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p. 32-39.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, A81-19500 The flying hologram - Latest in head-up p. 20-26. Translation. display systems. D. Boyle. Interavia, vol. 36, Jan. 1981, p. 44, 45. The essentially three-dimensional flow field at a delta wing The holographic or diffractive optics head-up display (D-HUD) situated in a supersonic gas flow is examined. It is shown that a is analyzed. This new equipment uses holographic principles to singularity generated by the breaking point on the leading edge arises provide a head-up display with a wider field of view and improved in the pressure gradient of the wing surface. The general form of this brightness for the symbols that are presented to the pilot super- singularity is determined. The method of deformed coordinates is imposed on his view of the outside world. The different types of used to obtain an exact solution of the differential equation for the optical path for the D-HUD system are presented diagramatically. additional velocity potential. A.Y. With holographically produced lenses, symbol brightness is improved from 1,600 to 5,000 ft-Lamberts and raster presentation brightness is raised from 400 to 1,200 ft-Lamberts. The use of the D-HUD in the A81-19632 Hypersonic gas flow over a delta wing. A. I. Golubinskii and A. I. Shchedrin. (Aeromekhanika. Sbornik statei U.S. Air Force's Low Altitude Navigation Targeting Infra-Red for Night (LANTIRN) program is discussed. C.R. posviashchaetsia 60-letiiu so dnia rozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p. 39-45.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p. 27-32. 9 refs. Translation. A81-19552 H Model vibrations beyond low-speed stall The problem of a plane delta wing of moderate aspect ratio in a (Vibrations de maquettes au-dela du decrochage a basse vitesse). X. hypersonic gas flow, whose freestream Mach number tends to Vaucheret (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, infinity as the adiabatic index tends to zero is examined. The analysis France). La Recherche Aerospatiale, Nov.-Dec. 1980, p. 387-397. 5 is carried out for small angles of attack. An asymptotic expression refs. In French. for the pressure at the center of the Mach cone is derived. A.Y. Vibrations of a string-mounted model beyond stall are analyzed by using the nonlinear equation of motion established for moderate amplitudes around high angle of attack according to a time/angle of A81 -19633 Some characteristics of subsonic flow over the attack cycle. The nonlinear solution yields frequency and damping root area of a sweptback wing. M. N. Nekrasova. (Aeromekhanika. variations versus amplitude and amplitude history beyond stall. A Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi- parametric study shows that the effects of maximum angle of attack ka Vladimira Vasil'evicha Struminskogo, p. 46-55.) Fluid Mechanics - and the duration of the step at this angle are decisive. For hard stall, Soviet Research, vol. 9, Mar.-Apr. 1980, p. 33-40 5 refs. Translation. the operator can perform the tests from indications that are aimed at Flows past peaked profiles at the root of a swept wing and at avoiding amplitude divergences at nonzero frequency. B.J. the sections of a straight wing are studied by visualization tech- niques, and the pressure distribution is determined. Two types of A81 -19629 Nonlinear aerodynamic characteristics of a flow were observed: flow with an almost complete isentropic thin airfoil of arbitrary plane configuration. S. M. Belotserkovskii compression of the supersonic flow along the surface of a swept and M. I. Nisht. (Aeromekhanika. Sbornik statei posviashchaetsia transonic wing; and flow with partially isentropic compression, with 60-letiiu so dnia rozhdeniia akademika Vladimira Vasil'evicha a shock-wave at the wing root. A.Y. Struminskogo, p. 9-24.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p. 1-13. 26 refs. Translation. General approaches to the schematization of separated inviscid A81-19634 Plane vortex gas flows. A. A. Nikol'skii. incompressible flows are reviewed, along with numerical methods of (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dnia solving the flow equations. Nonlinear and nonstationary problems rozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p. concerning separated flows are described on the basis of the 55-66.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p. three-dimensional Laplace equation, the conditions at wing surface 41-50. 5 refs. Translation. and the vortex sheet, and the initial conditions. The behavior of the The two-dimensional turbulent gas flow equations are studied wakes in space and time is determined from differential equations by expressing them in a convenient form. Two dual laws are resulting from the condition that the vortex sheet must move along established for subsonic flows: (1) under constant pressure, the angle the trajectory of the fluid particles. The mechanical load over the of inclination of the velocity vector varies monotonously along the wing is computed by means of the Cauchy-Lagrange integral. A pressure line; (2) with constant inclination of the velocity vector, the method of discrete vortices is used to implement the scheme on a pressure varies monotonously along the velocity vector line. These computer, and an example is considered in which the vortex laws are used to investigate the uniqueness of the location of the structures and nonlinear aerodynamic coefficients of rectangular and shock-waves in supersonic flows of two-dimensional tapered bodies delta wings are determined for separated and nonseparated flows. with angles of inclination not exceeding a critical value. A.Y. A.Y. A81-19636 The sonic boom from an aircraft flying along A81-19630 Thin minimum-drag airfoils. V. N. Zhigulev. an arbitrary path in a stratified atmosphere in the presence of a (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dnia three-component wind. lu. L. Zhilin. (Aeromekhanika. Sbornik statei rozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p. posviashchaetsia 60-letiiu so dnia rozhdeniia akademika Vladimira 24-31.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p. Vasil'evicha Struminskogo, p. 73-86.) Fluid Mechanics • Soviet 14-19. Translation. Research, vol. 9, Mar.-Apr. 1980, p. 57-68. 19 refs. Translation. The variational problem of 'returned' suction force on a General theory of acoustic shock is applied to the study of the cambered slender wing is analyzed and solved for a class of infinite acoustic shock from an aircraft flying in a layered atmosphere with a slender wings of arbitrary planform in a gas flow at small angles of three-component wind, all the parameters of which depend only on incidence in nonlinear regime. The requirement that the leading edge the altitude above the earth's surface. Calculation of attenuation of the wing be shock-free is shown to be necessary for a complete factors is reduced to four quadratures. It is shown that for a given implementation of the suction force. Various methods are proposed state of the atmosphere the attenuation factors depend on only five 123 A81-19643 similarity parameters, characterizing the flight regime and the position of the observer perceiving the acoustic shock relative to the flight path. P.T.H. A81-19643 The influence of flow disturbances on the laminar-turbulent transition in a supersonic boundary layer. A. M. Kharitonov (Akademiia Nauk SSSR. Institut Teoreticheskoi i Prikladnoi Mekhaniki, Novosibirsk, USSR). (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi- ka Vladimira Vasil'evicha Struminskogo, p. 153-164.) Fluid Mechan- ics - Soviet Research, vol. 9, Man-Apr. 1980, p. 125-134. 18 refs. Translation. Results of experimental studies on the effect of various factors on the transition of a supersonic boundary layer are discussed. It is shown that in supersonic wind tunnels, a significant effect on the transition of the boundary layer on a model is exerted by the scale of acoustic perturbations, which is proportional to the boundary layer displacement thickness of the working section. Experimental data obtained over a wide range of variation of flow parameters in aerodynamically similar test installations with different dimensions of the working section are generalized by means of a correlation parameter based on the disolacement thickness. P.T.H. A81 -19644 Wall cooling and the laminar-turbulent bound- ary layer transition at supersonic flow velocities. M. A. Alekseev, V. A. Kuz'minskii, N. F. Ragulin, and lu. G. Shvalev. (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi- ka Vladimira Vasil'evicha Struminskogo, p. 164-170.) Fluid Mechan- ics - Soviet Research, vol. 9. Mar.-Apr. 1980, p. 135-139. Translation. Results of an experimental investigation of the effect of cooling the surface on the transition of a boundary layer from a turbulent to a laminar to a turbulent one on straight wing models and bodies of revolution with ogive nose in a supersonic wind tunnel are discussed. The flow velocities corresponded to Mach numbers of 3, 3.5, and 4, and the Reynolds number ranged from 18 million to 40 million. The phenomenon of reversal is seen to be characteristic of turbulent transition under these conditions. P.T.H. A81-19657 Nondestructive dynamic testing. E. M. Uygur (Middle East Technical University, Ankara, Turkey). In: Research techniques in nondestructive testing. Volume 4. London, Academic Press, 1980, p. 205-244. 117 refs. Recent advances in nondestructive dynamic testing based on damping and resonant frequency measurements are reviewed with reference to the underlying theory, applications, and instrumenta- tion. Examples which illustrate the application of dynamic testing techniques to the study and detection of both macroscopic and microscopic defects and properties are given. It is shown that in most cases the same arrangement and instrumentation can be employed for both micro- and macro-scale work. V.L. 124 N81-13925 (Contract NAS1-15534) (NASA-CR-3352: D6-41840-2) Avail: NTIS HC A06/MF A01 CSCL01C The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics were included in the system to display or edit input and to permit monitoring and readout of STAR ENTRIES program results. T.M N81 13921*# National Aeronautics and Space Administration Langley Research Center. Hampton, Va. A COMPUTER PROGRAM FOR THE DESIGN AND ANALY- N81-13916# Southern California Association of Governments. SIS OF LOW-SPEED AIRFOILS. SUPPLEMENT Los Angeles Richard Eppler (Stuttgart Univ.) and Dan M Somers Dec. 1980 SOUTHERN CALIFORNIA AVIATION SYSTEM STUDY 30 p refs Technical Report. 1978 - 1980 (NASA-TM-81862) Avail: NTIS HC A03/MF A01 CSCL Lawrance H. Goldman, J. Timothy Merwin. Lisa D. Murphy, and 01A Walter E. Gillfillan Jul. 1980 237 p refs Three new options were incorporated into an existing (PB80-215544) Avail: NTIS HCA11/MFA01 CSCL 13B computer program for the design and analysis of low speed Southern California's 1995 air travel needs are examined. airfoils. These options permit the analysis of airfoils having variable Existing and planned air carrier airports are restricted by policy chord (variable geometry), a boundary layer displacement iteration, constraints and cannot accommodate the air travel demand and the analysis of the effect of single roughness elements. All forecast for 1995. Seven overall strategies, joint civilian/ military three options are described in detail and are included in the use of an existing military facility, removal or revision of the FORTRAN IV computer program. Author policy constraints, a new air carrier airport are described. Alternative airport sites are evaluated for market attractiveness, N81-13922*# National Aeronautics and Space Administration. noise impacts, airspace workability, financial feasibility, etc. GRA Langley Research Center. Hampton. Va. PASSIVE CONTROL OF WING/STORE FLUTTER N81-13917*# New Mexico Univ.. Albuquerque. Technology Wilmer H. Reed. III. F. W. Cazier. Jr.. and Jerome T. Foughner. Application Center. Jr. Dec. 1980 19 p refs Presented at the 5th Joint Tech. AIRCRAFT MAINTENANCE. CITATIONS FROM THE Coordinating Group Aircraft Stores Compatibility Symp.. St. Louis. INTERNATIONAL AEROSPACE ABSTRACTS DATA BASE 9-11 Sep. 1980 Progress Report. 1974 - Jul. 1980 (NASA-TM-81865: L-14010) Avail: NTIS HC A02/MF A01 Gerald F. Zollars Sep. 1980 84 p Supersedes NTIS/PS-79/ CSCL 01A 0859/3 Sponsored in cooperation with NASA and NTIS Results are presented for a passive flutter suppression (NASA-CR-163837; PB80-815905: NTIS/PS-79/0859/3) approach known as the decoupler pylon. The decoupler pylon Avail: NTIS HC S30.00/MF $30.00 CSCL 018 dynamically isolates the wing from store pitch inertia effects by These citations from the international literature concern means of soft spring/damper elements assisted by a low frequency various aspects of aircraft maintenance. Both military and civil feedback control system which minimizes static pitch deflections aviation experience are included. Articles cited concern airline of the store because of maneuvers and changing flight conditions. operations, engine and avionics reliability, the use of automatic Wind tunnel tests and analyses show that this relatively simple test equipment, maintenance scheduling, and reliability engineer- pylon suspension system provides substantial increases in flutter ing. This updated bibliography contains 347 citations, 85 of which speed and reduces the sensitivity of flutter to changes in store are new additions to the previous edition. GRA inertia and center of gravity. Flutter characteristics of F-16 and YF-17 flutter models equipped with decoupler pylon mounted stores are presented and compared with results obtained on the N81-13918*|f National Aeronautics and Space Administration. same model configuration with active flutter suppression systems. Langley Research Center. Hampton. Va. These studies show both passive and active concepts to be WIND-TUNNEL TEST OF AN ARTICULATED HELICOPTER effective in suppressing wing/store flutter. Also presented are ROTOR MODEL WITH SEVERAL TIP SHAPES data showing the influence of pylon stiffness nonlinearities on John D. Berry and Raymond E. Mineck Dec. 1980 95 p refs wing/store flutter. Author Prepared in cooperation with Army Aviation Research and Development Command. Hampton. Va. N81-13923*# Bihrle Applied Research. Inc., Jericho. N. Y. (NASA-TM-80080: L-12774: AVRADCOM-TR-79-49) Avail: ROTARY BALANCE DATA FOR A SINGLE-ENGINE NTIS HC A05/MF A01 CSCL 01A AGRICULTURAL AIRPLANE CONFIGURATION FOR AN Six interchangeable tip shapes were tested: a square (baseline) ANGLE-OF-ATTACK RANGE OF 8 DEG TO 90 DEC Final tip. an ogee tip. a subwing tip. a swept tip. a winglet tip. and a Report short ogee tip. In hover at the lower rotational speeds the swept, William Mulcay and Julio Chu Washington NASA Dec. 1980 ogee, and short ogee tips had about the same torque coefficient, 243 p refs and the subwing and winglet tips had a larger torque coefficient (Contract NAS1-14849) than the baseline square tip blades. The ogee and swept tip (NASA-CR-3311) Avail: NTIS HCA11/MFA01 CSCL 01A blades required less torque coefficient at lower rotational speeds Aerodynamic characteristics obtained in a helical flow and roughly equivalent torque coefficient at higher rotational environment utilizing a rotary balance located in the Langley speeds compared with the baseline square tip blades in forward spin tunnel are presented in plotted form for a 1/10 scale single flight. The short ogee tip required higher torque coefficient at engine agricultural airplane model. The configurations tested higher lift coefficients than the baseline square tip blade in the include the basic airplane, various wing leading edge and wing forward flight test condition. Author tip devices, elevator, aileron, and rudder control settings, and other modifications. Data are presented without analysis for an angle of attack range of 8 deg to 90 deg. and clockwise and counter-clockwise rotations covering a spin coefficient range from N81-13920*# Boeing Commercial Airplane Co.. Seattle. Wash. 0 to .9. Author A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSIS OF SUPERSONIC AIRCRAFT. PART 2: USER'S MANUAL N81-13925$ Aeronautical Research Inst. of Sweden. Stockholm. Final Contractor Report. Sep. 1978 - Aug. 1980 Aerodynamics Dept. W D. Middleton. J. L. Lundry, and R G. Coleman Washington DOWNWASH CALCULATION AT CLOSE RANGE BEHIND Dec. 1980 124 p refs A TRAPEZOIDAL WING IN SUPERSONIC FLOW 125 N81-13926 Anders Hasselrot 1980 37 p refs N81-13931# ARO. Inc.. Arnold Air Force Station. Tenn. (Contract FMV-F-K-80123-78-017-21-001) AN EVALUATION OF WIND TUNNEL TEST TECHNIQUES (FFA-TN-AU-1661: ISSN-SW-0081-5640) Avail: NTIS FOR AIRCRAFT NOZZLE AFTERBODY TESTING AT HC A03/MF A01 TRANSONIC MACH NUMBERS Final Report. 1 Oct. The results were determined as a function of values at the 1977-1 Jan. 1979 wing trailing edge and at the Trefftz-plane. A correction for off T. L Kennedy AEDC Nov. 1980 184 p refs the wing plane points is given. A description of the method, a (AD-A091775: AEDC-TR-80-8) Avail: NTIS FORTRAN listing of the coded method and results to be compared HC A09/MF A01 CSCL 20/4 with theoretical and experimental values of downwash are The results of many experiments to develop and verify wind presented. T.M. tunnel test techniques for determining engine exhaust effects on aircraft performance at transonic Mach numbers are N81-13926# Deutsche Forschungs- und Versuchsanstalt fuer summarized. The influence of model support interference, exhaust Luft- und Raumfahrt. Brunswick (West Germany). Abt. jet simulation techniques, wind tunnel calibration flow quality and operating conditions, model geometric effects, and measure- Rettungs-und Bergungssysteme. ment techniques in afterbody aerodynamic forces are discussed. A CONTRIBUTION TO STABILIZATION OF FLIGHT VEHICLE Recommendations are given for reducing or eliminating adverse PARACHUTE SYSTEMS Christos Saliaris and Dieter Muenscher Apr. 1980 34 p refs interference effects on wind tunnel test data. GRA In GERMAN: ENGLISH summary Report will also be announced as translation (ESA-TT-679) N81-13932# ARO. Inc.. Arnold Air Force Station. Tenn. (DFVLR-Mitt-80-05) Avail: NTIS HC A03/MF A01: OFVLR. EVALUATION OF WIND TUNNEL NOZZLE AFTERBODY Cologne DM 8.30 TEST TECHNIQUES UTILIZING A MODERN TWIN ENGINE The dynamic behavior of the two dimensional motion of a FIGHTER GEOMETRY AT MACH NUMBERS FROM 0.6 TO parachute load system was considered. For a mathematical model, 1.2 Final Report. Oct. 1975 - Sep. 1979 the system of nonlinear differential equations was numerically Ernest J. Lucas AEDC Oct. 1980 122 p refs integrated without linearization. For a number of examples with (AD-A091545: AEDC-TR-79-63) Avail: NTIS a modified guide surface parachute, the influence of the canopy HC A06/MF A01 CSCL 01/3 size, the distance between the attachment point and the Analyses of surface pressure data from wind tunnel tests canopy, and the distance between the attachment point and the conducted in the Propulsion Wind Tunnel (16T) on the 0.1- and center of gravity of the load on the oscillation of the flight 0.2-scale models of the YF-17 aircraft and flight tests conducted vehicle was studied. T.M. at the NASA Dryden Flight Research Center with the prototype YF-17 were conducted to substantiate the effectiveness of the subscale wind tunnel test techniques currently used at AEDC to N81-13929# Deutsche Forschungs- und Versuchsanstalt fuer provide data to evaluate throttle-dependent effects. The data Luft- und Raumfahrt. Goettingen (West Germany). Abt. were obtained at Mach numbers 0.6. 0.9. and 1.2 at characteristic Instationaere Aerodynamik. Reynolds numbers based on fuselage length from 14 million to ANALYSIS OF UNSTEADY PRESSURE MEASUREMENTS 250 million. The data obtained at Mach numbers 0.6 and 0.9 ON AN AEROFOIL SECTION WITH AN HARMONICALLY indicate that valid techniques are available to obtain subscale OSCILLATING. SLOTTED FLAP wind tunnel data that are directly applicable to aft-end throttle- Karl Kienappel and David F. Round (MBB. Hamburg) Apr. 1980 dependent flight performance prediction. The wind tunnel plume 66 p ref simulation techniques, however, do not provide data for directly (DFVLR-FB-80-22) Avail: NTIS HC A04/MF A01: DFVLR. predicting the flight vehicle, aft-end. calculated loads at Mach Cologne DM 14.20 number 1.2. Additional corrections must be applied to the data An analysis is made of unsteady pressure distribution and to compensate for temperature effects associated with afterburning aerodynamic coefficients measured for an airfoil and harmonically operations, such as that encountered at Mach 1.2. GRA oscillating slotted control surface in a low speed wind tunnel. The influences on the pressure distribution and aerodynamic N81-13933# Committee on Public Works and Transportation coefficients are examined: frequency of oscillation: flap steady (U. S. House). deflection: section incidence: flow velocity and slot geometry, AVIATION SAFETY: INTERIOR COMPARTMENT MATERI- i.e. whether the slot is open or closed. There is a carry over ALS between steady and unsteady pressure distributions, which Washington GPO 1979 373 p Hearings before the Subcomm. although small at low incidence and flap deflections, becomes on Oversight and Rev. of the Comm. on Public Works and more important at higher values, particularly when separation Transportation, 96th Congr.. 1st Sess.. 25-26 Apr. 1979 related effects begin to affect the overall flow behavior. Author (GPO 50-388) Avail: Subcommittee on Oversight and Review Safety efforts are divided into two aspects: accident prevention N81-13930# Office National d Etudes et de Recherches and accident survivability, or crashworthiness. The hearings focus Aerospatiales. Paris (France) on the frequent occurence of postcrash fire in survivable air REVIEW OF THEORETICAL AND EXPERIMENTAL RESULTS carrier accidents and on the effect that fire has on the materials ON THREE DIMENSIONAL TURBULENT WAKES AND which surround the passengers in the aircraft cabin. BOUNDARY LAYERS J. Cousteix. B. Aupoix. and G. Pailhas 1980 54 p refs In FRENCH: ENGLISH summary Report will also be announced N81-13934# Committee on Public Works and Transportation as translation (ESA-TT-678) (U. S. House). (ONERA-NT-1980-4: ISSN-0078-3781) Avail: NTIS TESTIMONY OF ELWOOD T. DRIVER. VICE CHAIRMAN. HC A04/MF A01 NATIONAL TRANSPORTATION SAFETY BOARD, AC- Various turbulence models were analyzed for boundary layer COMPANIED BY GERRIT J. WALKOUT. CHIEF. HUMAN predictions: mixing length, transport equations for the components FACTORS DIVISION. AND MATTHEW M. MCCORMICK. of the shear stress. The influence of the shear stress direction SENIOR AIR SAFETY INVESTIGATOR. HUMAN FACTORS was studied. Various solutions are discussed for taking into account DIVISION the nonalignment between the shear stress and the velocity In its Aviation Safety: Interior Compartment Mater. 1979 p 4-64 derivative normal to the wall. Such a nonalignment was also introduced in an integral method. The results of an experiment Avail: Subcommittee on Oversight and Review in a wake which is initially strongly dissymmetric and three The importance of fuel ignition prevention, and when this dimensional are discussed. They were obtained by detailed measure fails, the control of fire propagation inside the aircraft. measurements of mean velocities and of the six components of is discussed. Two air carrier accidents investigated by the Safety the Reynolds stress tensor. Attempts of prediction are dis- Board are described. It is recommended by the Board that the cussed. T.M. FAA conduct research in four specific areas affecting the severity 126 N81-13942 of injuries of aircraft occupants. These are: (1) containment of improvements in flame resistance of aircraft interior construction flammable fluids, including the fuel. oil. hydraulic fluid, etc.: material in all categories and an order of magnitude reduction (2) control of flammable fluids through chemical alteration or in smoke emission of materials. In other words, the smoke emission the inerting of fuel systems: (3) the reduction or elimination of was reduced by an order of 10 times in the last few years. the toxic effects of burning materials: and (4) improved escape E.D.K. methodology and passenger education. E.D.K. N81-13938# Naval Weapons Center. China Lake. Calif. N81-13935# Committee on Public Works and Transportation AN INVESTIGATION OF SAFETY HAZARDS AND RELIABIL- (U. S. House). ITY PROBLEMS IN AERIAL REFUELING STORES Final TESTIMONY OF JAMES J. KRAMER. ASSOCIATE ADMIN- Report. Mar. - Jul. 1980 Leo D. Budd Aug. 1980 70 p refs ISTRATOR FOR AERONAUTICS AND SPACE TECHNOL- OGY. NATIONAL AERONAUTICS AND SPACE ADMINIS- (AD-A091788: AD-E900014: NWC-TP-6218) Avail: NTIS TRATION. ACCOMPANIED BY JOHN H. ENDERS. PROJECT HC A04/MF A01 CSCL 01/2 MANAGER. AVIATION SAFETY TECHNOLOGY OFFICE. An investigation was conducted to identify sources of safety JOHN A. PARKER, CHEMICAL RESEARCH PROJECTS hazards and reliability problems in model D-704 aerial refueling OFFICE. NASA-AMES RESEARCH CENTER. AND stores. A failure modes and effects analysis was performed on DEMITRIUS A. KOURTIDES. CHEMICAL RESEARCH the D-704. Mishap data, safety UR (unsatisfactory report) data. PROJECTS OFFICE. NASA AMES RESEARCH CENTER and 3-M (maintenance and material management) data were In its Aviation Safety: Interior Compartment Mater. 1979 analyzed to identify historical problems. Comparisons of model p 65-158 31-300 failure statistics to model D-704 failure statistics is Avail: Subcommittee on Oversight and Review CSCL 01C included. GRA The materials system development program FIREMEN (Fire Resistant Materials Engineering) is described. The program is N81-13940# Boeing Military Airplane Development, Seattle, carried out through contracts witrr the major aircraft manufacturers Wash. Aircrew Escape Group. whereby they are funded to test and evaluate these advanced ADVANCED EJECTION SEAT FOR HIGH DYNAMIC material systems under the real constraints of state of the art PRESSURE ESCAPE. WIND TUNNEL TEST Final Report. manufacturing processes, production schedules, costs, weight, 15 Aug. 1979 - 20 May 1980 and so forth. E.O.K. John 0. Bull. David T. Ther. and Roger F. Yurczyk Aug. 1980 139 p refs N81-13936# Committee on Public Works and Transportation (Contract F3361 5-79-C-3406: AF Proj. 2402) (U. S. House). (AD-A091810: AFWAL-TR-80-3084) Avail: NTIS TESTIMONY OF RICHARD W. TAYLOR. VICE PRESIDENT HC A07/MF A01 CSCL 01/3 AND SPECIAL ASSISTANT TO THE PRESIDENT. AND Wind tunnel tests were conducted to evaluate new high EUGENE A. BARA. CHIEF ENGINEER. PAYLOAOS SYS- dynamic pressure protective devices incorporated into a conven- TEMS. BOEING COMMERCIAL AIRPLANE COMPANY tional ejection seat. These tests are part of a development program In its Aviation Safety: Interior Compartment Mater. 1979 'Advanced Ejection Seat for High Dynamic Pressure Escape'. p 159-297 The objectives of this program are to develop an ejection seat Avail: Subcommittee on Oversight and Review design which will provide safe escape during emergency A brief review of the Boeing aircraft interior materials and conditions encountered throughout the performance envelope of fire test methods development programs is given. This activity an aircraft with speed capability to 687 KEAS. Preliminary phases has gone on for many years and contributed to the AIA of this program have resulted in selection and definition of a crashworthiness program in 1968. As a result of these activities, windbiast shield, an aft body drag reduction boom, a horizontal the 747 was designed and built using the latest available stabilizer and a flow diverter. These devices were incorporated technology, thereby establishing the requirements for wide body into a one-half scale ejection seat/crewmember model and jet transports. Boeing's program in interior materials has continued were tested in the AEDC PWT 16-T transonic tunnel. Aerodynamic and the highlights of the last five years are reviewed. E.D.K. data derived from these tests are being used in six-degree-of- freedom computer simulations for performance assessments of N81-13937# Committee on Public Works and Transportation the ejection seat configurations. GRA (U. S. House). N81-13941*# Quinby (Gilbert F.). Fort Washington, Pa. TESTIMONY OF A PANEL CONSISTING OF: LLOYD E. AN ASSESSMENT OF GENERAL AVIATION UTILIZATION FRISBEE. VICE PRESIDENT. ENGINEERING AND OPERA- OF ADVANCED AVIONICS TECHNOLOGY Final Report TIONS. LOCKHEED CALIFORNIA COMPANY; LYLE A. Gilbert F. Quinby Dec. 1980 38 p WRIGHT. DIRECTOR. POWERPLANT ENGINEERING, (NASA Order L- 11 593) DOUGLAS AIRCRAFT COMPANY. ACCOMPANIED BY (NASA-CR-159328) Avail: NTIS HC A03/MF A01 CSCL DOCTOR H. C. SCHJELDERUP. CHIEF TECHNOLOGY 17G ENGINEER, MATERIALS AND PROCESS ENGINEERING. Needs of the general aviation industry for services and facilities AND F. E. DUSKIN, SENIOR DESIGN ENGINEER, INTERI- which might be supplied by NASA were examined. In the data ORS ENGINEERING, DOUGLAS AIRCRAFT COMPANY collection phase, twenty-one individuals from nine manufacturing In its Aviation and Safety: Interior Compartment Mater. 1979 companies in general aviation were interviewed against a carefully p 298-370 prepared meeting format. General aviation avionics manufacturers Avail: Subcommittee on Oversight and Review were credited with a high degree of technology transfer from Lockheed has conducted programs to improve aircraft material the forcing industries such as television, automotive, and flame resistance and develop advanced techniques for firesafety computers and a demonstrated ability to apply advanced testing in coordinated programs with other airframe companies, technology such as large scale integration and microprocessors materials suppliers, and NASA. During this time, Lockheed has to avionics functions in an innovative and cost effective manner. had active, continuous liaison with governmental agencies to The industry's traditional resistance to any unnecessary regimenta- develop firesafety testing techniques, study the feasibility and tion or standardization was confirmed. Industry's self sufficiency trade offs for advanced aircraft fire management systems, and in applying advanced technology to avionics product development seek meaningful and productive areas of research and development was amply demonstrated. NASA research capability could be in aircraft fire safety. Active support and participation was also supportive in areas of basic mechanics of turbulence in weather maintained in technical committee work such as ASTM-F7 and alternative means for its sensing. Author Committee on Aerospace Test Methods to standardize on flammability. smoke, and other combustion byproducts test techniques and to perform inter-laboratory comparison testing N81- 13942$ Deutsche Forschungs- und Versuchsanstalt fuer of flammability and smoke emission methods. Improved flam- Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). mability and smoke test techniques have contributed to substantial Abteilung Regelungssysteme. 127 N81-13944 THE COLLISION COURSE: CONDITIONS. GUIDANCE signal propagation, and cost analysis. This updated bibliography LAWS AND PROPERTIES contains 100 abstracts. 11 of which are new entries to the Winfried Hofmann Jan. 1980 108 p refs In GERMAN: previous edition. GRA ENGLISH summary (DFVLR-FB-80-06) Avail: NTIS HC A06/MF A01: DFVLR. N81-13948# National Technical Information Service. Springfield. Cologne DM 18.40 Va. An evaluation of the influence of distinct missile properties MICROWAVE LANDING SYSTEMS. CITATIONS FROM THE (acceleration phase, lead single constraints and maneuverability) NTIS DATA BASE Progress Report. 1964 - Jun. 1980 and real world disturbances on the properties and requirements William E. Reed Sep. 1980 205 p Supersedes NTIS/PS-79/ of collision course guidance is presented. For proportion navigation 0777: NTIS/PS-78/0731 guidance, comprehensive diagrams are presented to evaluate the (PB80-814635: NTIS/PS-79/0777: NTIS/PS-78/0731) Avail: terminal miss behavior, the requirements on the missile and NTIS HC S30.00/MF $30.00 CSCL 17G on a line of sight angular rate measuring sensor. Missile dynamics, Federally sponsored research on the planning, development, initial alignment errors, target maneuvers and target aspect-angle and operation of aircraft microwave landing systems, is presented. caused measurement errors were considered as real world Studies include feasibility, systems engineering, equipment, signal disturbances. Author propagation, and cost analysis. This updated bibliography contains 181 abstracts, 35 of which are new entries to the previous N81-13944# Deutsche Forschungs- und Versuchsanstalt fuer edition. GRA Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Flugmechanik. N81-13949$ Automation Industries, Inc., Silver Spring. Md. MIDAIR AND NEAR MIDAIR COLLISIONS ON TWO- AND Vitro Labs. THREE-DIMENSIONAL CURVILINEAR FLIGHT PATHS WIND SHEAR SYSTEMS INTEGRATION PLAN. VICON Otto Weber Mar. 1980 108 p refs In GERMAN: ENGLISH (VISUAL CONFIRMATION) RELIABILITY ANALYSIS Final summary Report will also be announced as translation Report (ESA-TT-685) Charles W. Hamby and James R. DeMattio Feb. 1980 74 p (DFVLR-FB-80-13) Avail: NTIS HC A06/MF A01: DFVLR. (Contract DOT-FA79WA-4279) Cologne DM 21 IPB80-2 18233: VITRO/JOB-03021-03540: FAA-RD-80-61) Collision avoidance by means of the 'see and avoid' concept, Avail: NTIS HC A04/MF A01 CSCL 17G advanced secondary radar systems on the ground, and independent The reliability of a visual confirmation system which visually electronic systems onboard is discussed. For two- and three- confirmed that an aircraft awaiting takeoff has been verbally dimensional stationary turns, basic geometrical and physical cleared for takeoff by the airport controller is examined. It is aspects of conflict detection were derived and details given on found that the predicted availability of the VICON system as the apparent size and motion of the other airplane on the installed at Bradley International Airport is 99.94% for the seven windshield. For conflict warning by means of electronic systems month test period. It is also found that the number of spare on the ground or onboard, a linear track model was used. T.M. parts to provide a 99% assurance that there will be no degradation of VICON system performance due to a lack of spare parts over 6 months is predicted to be sixty-three total spares covering N81-13945# Federal Aviation Administration, Atlantic City. N.J. twenty-seven different component types. Thirty percent of the FLIGHT TEST INVESTIGATION OF LORAN-C FOR EN spares are required for the controller's operating switches. GRA ROUTE NAVIGATION IN THE GULF OF MEXICO Final Report Robert Pursel Sep. 1980 102 p N81-13950# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- (FAA Proj. 045-390-130) brunn (West Germany). Theorgtische Aerodynamik. (AD-A091637: FAA-CT-80-18: FAA-RD-80-47) Avail: NTIS COMPUTATIONAL AERODYNAMIC DESIGN TOOLS AND HC A06/MF A01 CSCL 17/7 TECHNIQUES USED AT FIGHTER DEVELOPMENT Flight tests of a long range navigation (LORAN-C) airborne P. Sacher. W. Kraus. and R. Kunz 6 Sep. 1979 54 p refs navigator were conducted in the Gulf of Mexico oil exploration Presented at Meeting SMP of AGARD., Neubiberg. Germany, and production area. Two systems were installed in a CV-580 3-6 Sep 1979 aircraft to examine simultaneously the performance from two (MBB-FE-122/S/PUB/13) Avail: NTIS HC A04/MF A01 different LORAN-C triads. Four separate test loutes were flown Configuration optimization, component design, and experimen- over a period of 3 days. These routes covered the eastern, central, tal proof in fighter design are summarized. Requirements for and western test areas, and an overland route from Houston. supersonic performance, including supersonic drag reduction and Texas, to Lafayette. Louisiana. An inertial navigation system (INS) canard tail design, were reviewed. The main aerodynamic principles was used as a position reference standard. The INS data were in use throughout the aircraft industry are described. T.M. updated to correct for drift. Accuracy of trie position reference from the corrected INS data was - or - 0.3 nautical miles (nmi). The flight test data collected indicated that both the Malone, N81-13951# Technische Hogeschool. Delft (Netherlands). Dept. Raymondville. Jupiter and the Malone. Raymondville. Grangevrlle of Aerospace Engineering. triads provided en route LORAN-C navigation capability which FUNDAMENTALS OF CONCEPTUAL DESIGN OPTIMIZA- met Federal Aviation Administration (FAA) Advisory Circular TION OF SUBSONIC TRANSPORT AIRCRAFT AC-90-45A accuracy requirements except when operating near E. Torenbeek Aug. 1980 173 p refs the baseline extension of the Malone Grangeville baseline when (VTH-LR-292) Avail: NTIS HC A04/MF A01 using the Malone. Raymondville. Grangeville triad. GRA Various merit functions and feasible design program structures are discussed and program elements common to most design exercises were analyzed. Criteria for optimum cruise conditions N81-13947# National Technical Information Service. Springfield. are presented for aircraft with or without Mach number dependent Va. drag polars and arbitrary propulsion systems. Constrained and MICROWAVE LANDING SYSTEMS. CITATIONS FROM THE unconstrained optima for design cruise speed and altitude, engine ENGINEERING INDEX DATA BASE Progress Report. thrust, wing loading, aspect ratio and lift coefficient are presented 1970 - Jun. 1980 in the form of generalized analytical expressions. Different criteria Willliam E. Reed Sep. 1980 105 p Supersedes NTIS/PS-79/ were found when engines were sized for optimum cruising flight 0778: NTIS/PS-78/0732 or for specified low speed performance. A generalized cruise (PB80-814643: NTIS/PS-79/0778: NTIS/PS-78/0732) Avail: performance analysis is presented for modern turbofan and NTIS HC S30.00/MF $30.00 CSCL 17G propeller aircraft, resulting in new criteria for optimum flight The bibliography cites reports from worldwide research on conditions. A detailed account of the aircraft mass breakdown the planning development, and operation of microwave landing sensitivity to parametric variations, derivations for the payload systems, including feasibility, systems engineering, equipment. fraction, and partial (constrained) and global optima were derived. 128 N81-13960 Some opportunities for improvements and extended applicatiioni s (NASA-CR-163833: PB80-815970. NTIS/PS-79/1017) Avail: to non-conventional and advanced designs are discussed briieflye . NTIS HC S30.00/MF $30.00 CSCL01C TT.M. Technological forecasts of aircraft design are discussed in N81-13952# Deutsche Forschungs- und Versuchsanstalt fuer approximately 162 citations. Forecasts dealing with the configura- Luft- und Raumfahrt. Brunswick (West Germany). Abt. tion of both civil and military aircraft are included. Specific topics Entwurfsaerodynamik. stressed are fuel consumption, avionics, and cost and noise reduction. GRA LAMINAR-AIRFOILS FOR TRANSPORT AIRCRAFT Armin Quasi Mar. 1980 34 p refs In GERMAN: ENGLISH summary Report will also be announced as translation N81-13958*# National Aeronautics and Space Administration. (ESA-TT-680) Langley Research Center. Hampton. Va. (DFVLR-Mitt-80-07; ESA-TT-680) Avail. NTIS EVALUATION OF A COMPUTER-GENERATED PERSPEC- HC A03/MF A01: DFVLR. Cologne DM 8.30 TIVE TUNNEL DISPLAY FOR FLIGHT PATH FOLLOWING Wing sections with laminar flow and their effects on fuel Arthur J. Grunwald. James B. Robertson, and Jack J. Hatfield consumption are discussed. It was shown that lammanzation by Dec. 1980 100 p refs section shape is possible at certain Reynolds numbers and at (NASA-TP-1736: 1-13253) Avail: NTIS HC A06/MF A01 reduced Mach numbers. T.M. CSCL 01 D The display was evaluated by monitoring pilot performance in a fixed base simulator with the vehicle dynamics of a CH-47 N81-13955# Texas Univ. at Austin. Dept. of Aerospace tandem rotor helicopter. Superposition of the predicted future Engineering and Engineering Mechanics. vehicle position on the tunnel image was also investigated to THE EFFECTS OF WARHEAD-INDUCED DAMAGE ON THE determine whether, and to what extent, it contributes to better AEROELASTIC CHARACTERISTICS OF LIFTING SUR- system performance (the best predicted future vehicle position FACES. VOLUME 1: AEROELASTIC EFFECTS Final Report. was sought). Three types of simulator experiments were 1 Feb. 1979 - 31 Jan. 1980 conducted: following a desired trajectory in the presence of J. H. Chang and R. 0. Stearman Jul. 1980 122 p refs disturbances: entering the trajectory from a random position, (Grant AF-AFOSR-3569-78; AF Proj. 2301) outside the trajectory: detecting and correcting failures in (AD-A091674; AFOSR-80-1039TR) Avail: NTIS automatic flight. The tunnel display with superimposed predictor/ HC A06/MF A01 CSCL 01/3 director symbols was shown to be a very successful combination, An investigation is being conducted to determine whether which outperformed the other two displays in all three experiments. ballistic damage can seriously degrade the aeroelastic integrity A prediction time of 4 to 7 sec. was found to optimize trajectory of lifting surfaces on aircraft. A potential aeroelastic failure mode tracking for the given vehicle dynamics and flight condition. that was identified in the first year's study has been investigated Pilot acceptance of the tunnel plus predictor/director display here over a larger range of parameters. This failure mechanism was found to be favorable and the time the pilot needed for results from the localized steady drag generated when a lifting familiarization with the display was found to be relatively short. surface encounters damage to its aerodynamic shape. Its modeling Author has been extended in this study to swept wing configurations and to possible multiple and distributed damage sites. In addition, N81-13959*# National Aeronautics and Space Administration. a larger range of single damage site locations has also been Langley Research Center, Hampton. Va considered to assess the possible tradeoffs between the influence DEVELOPMENT OF A COMPUTER PROGRAM DATA BASE of both structural and aerodynamic damage locations. A check OF A NAVIGATION AID ENVIRONMENT FOR SIMULATED on the validity of the strip theory aerodynamic modeling employed IFR FLIGHT AND LANDING STUDIES in this study has also been made by comparing these results Hugh P. Bergeron. Alix T. Haynie (Georgia Inst. of Tech.), and with those obtained from a lifting surface theory modeling. Finally, James B. McDede (Embry-Riddle Aeronautical Inst.) Nov. 1980 an additional failure mechanism is identified that results from 35 p refs any unsteady but periodic fluctuating aerodynamic drag loads (NASA-TM-80064) Avail: NTIS HC A03/MF A01 CSCL that are generated by the damage. A parametric and oscillatory 17G instability can be induced by relatively low level drag loads in A general aviation single pilot instrument flight rule simula- this case if they happened to be appropriately tuned to the tion capability was developed. Problems experienced by single structural frequencies of the wing. GRA pilots flying in IFR conditions were investigated. The simulation required a three dimensional spatial navaid environment of a N81-13956# Federal Aviation Administration, Oklahoma City, flight navigational area. A computer simulation of all the Okla. Standards Development Branch. navigational aids plus 12 selected airports located in the CURRENT AIRCRAFT SURVEY (APPROACH SPEEDS. Washington/Norfolk area was developed. All programmed GROSS WEIGHTS. AND DIMENSIONS) locations in the list were referenced to a Cartesian coordinate Frank Parr Jul. 1980 36 p system with the origin located at a specified airport's reference (Proj. AFS-560-79-17) point. All navigational aids with their associated frequencies, call (PB80-225691: FAA-AFO-500-20) Avail: NTIS letters, locations, and orientations plus runways and true headings HC A03/MF A01 CSCL01B are included in the data base. The simulation included a TV A survey of current aircraft was conducted to determine displayed out-the-window visual scene of country and suburban the effect of a revision to FAR 97.3. The revision deleted the terrain and a scaled model runway complex. Any of the use of gross weight in categorization of aircraft for instrument programmed runways, with all its associated navaids, can be approach minimums. Of 237 aircraft types and models of 22 referenced to a runway on the airport in this visual scene. This nations surveyed. 180 were not affected by the rule change. Of allows a simulation of a full mission scenario including breakout the affected aircraft, 31 changed from Category D to C, one and landing. R.C.T. from D to B, one from D to A. 17 to C to B, three from C to A. and four from B to A. Ten aircraft types have series which N81-13960# Deutsche Forschungs- und Versuchsanstalt fuer fall into two categories. GRA Luft- und Raumfahrt. Brunswick (West Germany). Abteilung Flugsimulation. N81-13957*# New Mexico Univ.. Albuquerque. Technology EQUIPMENT FOR TESTING AND MEASURING A 'HELMET Application Center. MOUNTED SIGHT AND DISPLAY1 SYSTEM WITH A TECHNOLOGICAL FORECASTING-AIR CRAFT DESIGN. COUPLED MOVABLE TELEVISION CAMERA IN THE CITATIONS FROM THE INTERNATIONAL AEROSPACE FLIGHT-SIMULATOR FOR RESEARCH OF THE DFVLR ABSTRACTS DATA BASE Progress Report. 1974 - Aug. 1980 R. Dierke. Friedrich Erdmann. E. Biertuempel. R. Ehlers. and H. Gerald F. Zollars and Mary K. Gallagher Sep. 1980 45 p Loehr Jan. 1980 81 p refs In GERMAN: ENGLISH summary Supersedes NTIS/PS-79/1017 Sponsored in part by NASA Report will also be announced as translation (ESA-TT-675) and NTIS (DFVLR-Mitt-80-04) Avail: NTIS HC A05/MF A01 129 N81-13963 Equipment for testing a helmet mounted sight and display Direct constrained parameter optimization was used to system (HMS/D) in a flight simulator is described. After defining optimally size a medium range transport for minimum direct the values to be measured and the corresponding reference values, operating cost. Several stability and control constraints were varied the software and hardware of the testing equipment is described, to study the sensitivity of the configuration to specifying the as well as the control program of the equipment and the methods unaugmented flying qualities of transports designed to take of data recording. Special aspects of the mathematical background maximum advantage of relaxed static stability augmentation and measurement of static errors of a HMS/D System (Honeywell) systems. Additionally, a number of handling qualities related design are given in the appendices. E.D.K. constants were studied with respect to their impact on the design. Author N81-13963*# Teledyne Continental Motors. Mobile. Ala. Aircraft Products Div. N81-13969*# Calspan Advanced Technology Center. Buffalo, ADVANCED TECHNOLOGY SPARK-IGNITION AIRCRAFT N.Y. PISTON ENGINE DESIGN STUDY Final Report LANDING FLYING QUALITIES EVALUATION CRITERIA FOR Kenneth J. Stuckas Nov. 1980 127 p refs x AUGMENTED AIRCRAFT Final Report (Contract NAS3-21272) Robert C. Radford. Roger Smith, and Randall Bailey Jun. 1980 (NASA-CR-165162) Avail: NTIS HC A07/MF A01 CSCL 99 p refs 21G (Contract NAS4-2534) The advanced technology, spark ignition, aircraft piston engine (NASA-CR-163097: CALSPAN-6339-F-3) Avail: NTIS design study was conducted to determine the improvements that HC A05/MF A01 CSCL 01C could be made by taking advantage of technology that could The criteria evaluated were: Calspan Neal-Smith: Onstott reasonably be expected to be made available for an engine (Northrop Time Domain); McDonnell-Douglas Equivalent System intended for production by January 1, 1990. Two engines were Approach: R. H. Smith Criterion. Each criterion was applied to proposed to account for levels of technology considered to be the same set of longitudinal approach and landing flying qualities moderate risk and high risk. The moderate risk technology engine data. A revised version of the Neal-Smith criterion which is is a homogeneous charge engine operating on avgas and offers applicable to the landing task was developed and tested against a 40% improvement in transportation efficiency over present other landing flying qualities data. Results indicated that both designs. The high risk technology engine, with a stratified charge the revised Neal-Smith criterion and the Equivalent System combustion system using kerosene-based jet fuel, projects a 65% Approach are good discriminators of pitch landing flying qualities: improvement in transportation efficiency. Technology enablement Neal-Smith has particular merit as a design guide, while the program plans are proposed herein to set a timetable for the Equivalent System Approach is well suited for development of successful integration of each item of required advanced appropriate military specification requirements applicable to highly technology into the engine design. , Author augmented aircraft. Author N81-13964| Rolls-Royce Ltd.. Derby (England). THE FUTURE OF CIVIL TURBO-FAN ENGINES N81-13970# Deutsche Forschungs- und Versuchsanstalt fuer A. G. Newton and J. F. Coplin 1980 41 p Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. (PNR-90034) Avail: NTIS HC A03/MF A01 fuer Dynamik der Flugsysteme. The scarcity of fuel and rapidly increasing fuel prices means APPLICATION OF VECTOR PERFORMANCE OPTIMIZA- that there will be ever increasing pressure to reduce the fuel TION TO A ROBUST CONTROL LOOP DESIGN FOR A consumption of commercial aeroengines. The present generation FIGHTER AIRCRAFT of large fan engines has consolidated significant improvements Gerhard Kreisselmeier and Reinhold Steinhauser Apr. 1980 in this respect compared with the engines it replaced. The fuel 70 p refs In GERMAN: ENGLISH summary consumption of this class of engines can be greatly reduced (by (DFVLR-FB-80-14) Avail: NTIS HC A05/MF A01: DFVLR. amount 12-15 percent) by adopting a derivative approach and. Cologne DM 13.20 in the longer term, by a further 10 percent by more radical For a McDonnell-Douglas F-4C aircraft a robust, fixed gain changes. The methods by which the current performance was controller is designed, which provides satisfying handling qualities achieved are described. Author of the longitudinal motion of the aircraft over the complete flight range without gain scheduling. Robustness is achieved in the sense of covering large parameter variations and providing good gain and phase margins. Only low control rates and low feedback N81-13966# School of Aerospace Medicine. Brooks AFB, Tex. gains are involved. The results are obtained by application of a Aerospace Medical Div. performance vector optimization design method which permits a ORGANIC COMPOUNDS IN THE EXHAUST OF A J8S-S great many different design objectives simultaneously and in a TURBINE ENGINE Interim Report. Jan. - Sep. 1978 highly systematic fashion. Two different designs are presented James P. Conkle. William W. Lackey. Charles L Martin, and placing emphasis on pitch rate control and normal acceleration Andrew Richardson, III Sep. 1980 35 p refs control. E.D.K. (AF Proj. 7930) (AD-A091712: SAM-TR-80-29) Avail: NTIS HC A03/MF A01 CSCL 21/2 Information related to exhaust hydrocarbons associated with a J85-5 turbine engine is presented. A comparison of two sampling N81-13971# Deutsche Forschungs- und Versuchsanstalt fuer techniques (cryogenic trapping and sorption tube) is discussed. Luft- und Raumfahrt. Brunswick (West Germany). Abt. The collected samples were analyzed by coupled gas chromato- Flaechenflugzeuge. graph-mass spectrometer-data system. The number of com- SYSTEM IDENTIFICATION OF THE LONGITUDINAL pounds identified in the samples was 231. with equivalent results MOTION OF THE DFVLR HFB 320 RESEARCH AIRCRAFT from the two sampling techniques. Less than half of the WITH PARTICULAR CONSIDERATION OF CONTROL compounds identified were aromatic and oxygenated species. SURFACE EFFECTIVENESS GRA Ohad Rix Jul. 1979 58 p ref In GERMAN: ENGLISH summary Report will also be announced as translation (ESA-TT-666) N81-13968*# National Aeronautics and Space Administration. (DFVLR-Min-79-16) Avail: NTIS HCA04/MFA01 Langley Research Center. Hampton, Va. The identification of the longitudinal motion of the DFVLR ECONOMIC EVALUATION OF FLYING-QUALITIES DESIGN HFB 320 research aircraft using a maximum likelihood method CRITERIA FOR A TRANSPORT CONFIGURED WITH is described. The main emphasis is on the identification of control RELAXED STATIC STABILITY surface effectiveness of separately or simultaneously deflected Steven M. Sliwa Dec. 1980 30 p refs DLC flaps and spoilers. The flight test technique and the influence (NASA-TP-1760: L-13944) Avail: NTIS HC A03/MF A01 of different model approaches on the results are discussed. CSCL 01C E.D.K 130 N81-14061 N81-13972# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- determined parameters are the necessary phase compensation brunn (West Germany). Airplane Div. and gain adaption which the pilot must perform and also the ACTIVE FLUTTER SUPPRESSION ON AN F-4F AIRCRAFT closed loop resonance. The influence of DLC gain factor, spoiler WITH EXTERNAL STORES USING ALREADY EXISTING actuator rate and spoiler deflection wash-out time constant on CONTROL SURFACES pilot workload, is presented. Simulated time histories of pitch 0. Sensburg. H. Hoenlinger. and T. E. Moll (AFFDU 25 Mar. rate and normal acceleration response due to step type control 1980 9 p refs Presented at AIAA 21st Struct.. Struct. Dyn. inputs show the corresponding reactions of the various DLC and Mater. Conf, Seattle. 12-14 May. 1980 configurations which are essential for pitch control and flight (MBB-FE-17/S/PUB/24) Avail: NTIS HC A02/MF A01 path control. Author The flutter suppression system was flight tested using classical flight flutter tests, open loop tests, and closed loop tests. The N81-139770 Calspan Corp., Buffalo. N. Y. control law was found by applying optimal control theory thus FURTHER INVESTIGATIONS OF ADAPTIVE-WALL WIND minimizing the control surface motion due to disturbances and TUNNELS Final Report. Aug. 1978 - Dec. 1979 providing the required stability margins. The selection of the J. C. Erickson. Jr.. C. E. Wittliff. and D. C. Daughtery Oct. wing mounted store configuration is described. T.M. 1980 72 p refs (Contract F40600-78-C-0003) N81-13973# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- (AD-A091774: CALSPAN-6374-A-1: AEDC-TR-80-34) Avail: brunn (West Germany). Airplane Div. NTIS HC A04/MF A01 CSCL 20/4 ACTIVE CONTROL OF AN EXPLOSIVE WING-STORE The objective of this investigation was to continue the FLUTTER CASE assessment of the Calspan perforated-wall, segmented-plenum H. Hoenlinger. 0. Sensburg. M. Kuehn, and H. Goedel 8 Apr. adaptive-wall wind tunnel for flows in which the tunnel walls 1980 9 p refs Presented at 50th Meeting Struct, and Mater. are supercritical. An important aspect of the investigation was Panel of AGARD. Athens. 13-18 Apr. 1980 the development of a static pipe measuring technique for (MBB-FE-17/S/PUB/25) Avail: NTIS HC A02/MF A01 determining the normal velocity distributions. This technique Control laws were calculated, using optimal control theory, was developed to overcome the limitations on the number of to suppress an explosive wing store flutter case on a YF- flow angle probe measurements that could be made in the Calspan 17 dynamically scaled model. The trailing edge flap was used tunnel The flow about a static pipe in the presence of model/wall for flutter suppression because usually hydraulically driven ailerons induced disturbances was analyzed within the framework of are available in modern fighters. The design aim of 15 times slender body theory to give the relationship between differential the flutter dynamic pressure could be demonstrated during the pressure measurements across the pipe and the steam wise wind tunnel test. It should be emphasized that no changes to derivative of the normal velocity at the pipe centerline. GRA the analytically developed control law were necessary in the test which proves that theory has well advanced during the last years. E.D.K. N81-14004# Rolls-Royce Ltd.. Derby (England). Plastics and Composite Materials Lab. N81-13974$ Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- A RESIN INJECTION TECHNIQUE FOR THE FABRICATION brunn (West Germany). Airplane Div. OF AERO ENGINE COMPOSITE COMPONENTS EFFECTS OF NONLINEARITIES ON WING STORE FLUT- W. R. Jones and J. W. Johnson 1980 10 p TER (PNR-90024) Avail: NTIS HC A02/MF A01 G. DeFerrari. L Chesta. 0. Sensburg. and A. Lotze 9 Apr. A method for the manufacture of high quality composite 1980 16 p refs Presented at 50th Meeting Struct, and Mater. aero engine components, free from voids and having a high Panel of AGARD.. Athens. 13-18 Apr.. 1980 Prepared jointly degree of dimensional reproducibility is described. A porous fiber with Agritalia. Turin preform held in the component shape by the use of a thermoplastic (MBB-FE-17/S/PUB/27) Avail: NTIS HC A02/MF A01 binder is employed. The preform is then infiltrated with epoxy The effects of structural nonlinearities, in particular friction resin in a closed die using a vacuum assisted high pressure and backlash, on the dynamic behavior of airplanes can be injection method. It is possible to include inserts or third dimension very important for flutter. Larger nonlinearities do exist on reinforcement in components, and reference is made to the sweepable wing airplanes with sweepable wing mounted stores production of a carbon fiber fan blade and a nose spinner. S.F. because a considerable amount of joints (with possible play) and bearings (with play and friction) is necessary but the problem is also present for fired wing airplanes. A major problem is the N81-14O06# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- interpretation of linear ground resonance and flight flutter tests brunn (West Germany). Aircraft Div. and their comparison with analytical predictions. Findings from CONSTANT-AMPLITUDE AND FLIGHT-BY FLIGHT TESTS ground resonance tests and flight flutter tests are presented ON CERP SPECIMENS and an explanation for these test results is given. Calculations F. J. Arendts. K. 0. Sippel. and D. Weisgerber 9 Apr. 1980 with linear assumptions (parameter variations) were made and 13 p refs Presented at 50th Meeting Struct, and Mater. Panel the method of harmonic balance for finding these parameters of AGARD, Athens, 13-18 Apr., 1980 Supported by FRG Min. was applied. It is shown certain levels of excitation must be of Defense reached in order to make flight flutter tests reliable for establishing (MBB-FE-2/S/PUB-26) Avail: NTIS HC A02/MF 01 flutter clearance speeds. Author Constant-amplitude and flight-by-flight tests with five different load spectra were done with unnotched carbon fiber reinforced points specimens. Also the influence of overloads was investigated. N81-13975# Deutsche Forschungs- und Versuchsanstalt fuer The test results were compared with fatigue life predictions based Luft- und Raumfahrt. Brunswick (West Germany). Abteilung on 'Miner's Rule' applied for different conditions. The results Flaechenflugzeuge. show that overloads in all cases cause a significant reduction of THEORETICAL INVESTIGATION OF THE INFLUENCE OF the fatigue life. It turned out that fatigue life estimations based SPOILER DYNAMICS ON THE HANDLING QUALITIES OF on 'Miner's Rule' are on the unsafe side in some cases by AN AIRCRAFT WITH DIRECT LIFT CONTROL more than a factor 10. getting a big scatter among the cases Dieter Schafranek Nov. 1979 72 p refs In GERMAN: ENGLISH investigated. Author summary Report will also be announced as translation (ESA-TT-68D (DFVLR-FB-80-07) Avail: NTIS HC A04/MF A01: DFVLR. N81-14061# Systems Research Labs.. Inc.. Dayton. Ohio. Cologne DM 14.70 Research Applications Div. Parameters describing the pilots workload during pitch tracking THE STRESS BEHAVIOR OF THREE ADVANCED NICKEL and flight path tracking tasks on a transport aircraft equipped BASE SUPERALLOYS DURING HIGH TEMPERATURE LOW with spoiler direct lift control (DLC) were determined. The CYCLE FATIGUE Technical Report. Jan. 1977 - Aug. 1978 131 N81 14064 Henry L. Bernstein Jun. 1980 243 p refs N81-14082*# General Electric Co.. Philadelphia. Pa. Advanced (Contract F33615-76-C-5191: AF Proj. 7351) Energy Programs Dept. (AD-A091694; SRL-9799: AFWAL-TR-80-4075) Avail: NTIS IMPROVED CERAMIC HEAT EXCHANGER MATERIALS HC A11/MF A01 CSCL 11/6 Final Report This report is a compilation of data on stress behavior as a Harry W. Rauch Dec. 1980 39 p refs function of cycles obtained during high temperature, low cycle (Contracts NAS3-19698 EC-77-A-31-101 1: fatigue tests on three advanced Ni-base superalloys--Rene 95. DE-AI01-77CS-51040) AF-115. and AF2-1DA. The data are presented in both tabular (NASA-CR-159678: DOE/NASA/9698-2) Avail: NTIS and graphical formats. The materials studied are those used for HC A03/MF A01 CSCL 07C jet engine turbine disks, and the fatigue tests were conducted The development and evaluation .of materials for potential at their operating temperatures. The purpose of this report is to application as heat exchanger structures in automotive gas turbine make the test data available to the technical community. No engines is discussed. Test specimens in the form of small discussion is presented on an analysis or an understanding of monolithic bars were evaluated for thermal expansion and the data, although some observations are included. GRA dimensional stability before and after exposure to sea salt and sulfuric acid, followed by short and long term cycling at temperatures up to 1200 C. The material finally selected. GE-7808. consists of the oxides. 2rO2-MgO-AI2O3-S102. and is described N81-14O64# Massachusetts Inst. of Tech.. Cambridge. Lab. generically as ZrMAS. The original version was based on a for Manufacturing and Productivity. commercially available cordierite (MAS) frit. However, a clay/talc PREVENTION OF SPUNE WEAR BY SOFT METALLIC mixture was demonstrated to be a satisfactory very low cost COATINGS Final Report. 1 Jan. 1977 - 30 Jun. 1979 source of the cordierite (MAS) phase. Several full size honeycomb Nannaji Saka. Hyo Choi Sin. and Nam P. Suh Jul. 1980 71 p regenerator cores, about 10.2 cm thick and 55 cm diameter refs were fabricated from both the frit and mineral versions of GE-7808. (Contract N00014-76-C-0068) The honeycomb cells in these cores had rectangular dimensions (ADA091861: MIT/LMP/TRB-80-2) Avail: NTIS of about 0.5 mm x 2.5 mm and a wall thickness of approximately HC A04/MF A01 CSCL 01/3 0.2 mm. The test data show that GE-7808 is significantly more The purpose of this cooperative program between MIT. Naval stable at 1100 C in the presence of sodium than the aluminosilicate Air Development Center (NAOC) and Foxboro-Analytical is to reference materials. In addition, thermal exposure up to 1100 C, study the mechanism of wear and increase the wear resistance with and without sodium present, results in essentially no change of aircraft splines. In addition to testing a much larger number in thermal expansion of GE-7808. M.G. of splines under a variety of conditions than has been done so far. optical microscopy, scanning electron microscopy and ferrography have been extensively used to identify the wear N81-14084# Naval Weapons Center. China Lake. Calif. mechanism. Test specimens of aircraft splines were coated with VANADIUM TRINEODECANOATE PROMOTER FOR Au. Ni. Ag and Cd with various thicknesses (0.1 - 10 micron FIBERGLASS-POLYESTER SOIL SURFACINGS Final Report. m) and tested in the SwRI spline wear tester with and without Apr. 1979 - Mar. 1980 grease. The gold coated splines exhibited induction periods of Alan L. Woodman. Ronald A. Henry, Arnold Adicoff. and Dwight 250 hours, which is four times that exhibited by the uncoated A. Fine Jun. 1980 30 p refs splines. Ni. Ag and Cd failed to increase the induction period. (AD-A091785: AD-E900008: NWC-TP-6184) Avail: NTIS Unluhncated splines wore exactly at the same rate as the HC A03/MF A01 CSCL 11/2 post-induction wear rates of the grease lubricated splines. Optical A Marine Corps chemical formulation developed for the and scanning electron microscopy results indicate that the mode construction of fiberglass-reinforced plastic surfaces for soils of wear is by subsurface deformation, crack nucleation and growth consists of a polyester resin, cumene hydroperoxide catalyst and processes (i.e.. by the delamination mechanism) both in the a promoter solution containing a vanadium salt and N.N-dimethyl- induction and the post-induction periods. Analysis of the splines p-toluidine. A new. relatively simple method for preparing the by the energy dispersive X-ray analysis showed that the metallic vanadium trineodecanoate (VND) solution has been devised to coatings did not react with grease. This and other evidence replace the previously used commercial salt solution which is indicates that the costing/substrate bond strength is an important no longer being manufactured. This preparation is now ready to factor in the wear of splines. Methods for improving the bond be scaled-up to pilot plant size. Reactivity and accelerated aging strength and reducing the cost of the coatings are suggested. studies indicate that the VND solution functions at least as well GRA as the commercial salt. Laminates made under either dry or wet conditions with the VND displayed significantly higher flexural strengths than those made with the commercial material. GRA N81-14077* National Aeronautics and Space Administration. Lyndon B. Johnson Space Center, Houston. Tex. SURFACE FINISHING Patent N81-14182| Transportation Research Board. Washington. D.C. Jack A. Kinzler. James T. Hefferman. Leroy G. Fehrenkamp. and SEALING JOINTS AND CRACKS. THIN RESURFACING. William S. Lee. inventors (to NASA) Issued 30 Sep. 1980 AND LOCATING VOIDS UNDER CONCRETE SLABS 8 p Filed 25 Jan. 1979 Supersedes N79-21183 (17-12. Wouter Gulden. Gordon K. Ray. I. Minkarah, J. P. Cook, and J. p 1540) Continuation of abandoned US Patent Appl. SN-785279. B. Thornton 1980 38 p refs filed 6 Apr. 1977 which is a division of US Patent Appl. (PB80-215635: TRB/TRR-752: ISBN-0-309-03062-5: SN-568541. US Patent-4. 032. 089. filed 16 Apr. 1975 LC-80-23303) Avail: NTIS HC A03/MF A01 CSCL 13B (NASA-Case-MSC-12631-3: US-Patent-4.225.372: The six papers in this report deal with the following areas: US-Patent-Appl-SN-006952: US-Patent-Class-156-154: effect of defective joint seals on pavement performance: pavement US-Patent-Class-156-160: US-Patent-Class-156-163: design features and their effect on joint seal performance: US-Patent-Class-156:212: US-Patent-Class-156-267: pavement restoration measures to precede joint resealing: and US-Patent-Class-156-295: US-Patent-Class-156-323: US-Paient-Class-156-331: US-Patent-Appl-SN-785279: conditions and operations for joint and crack resealing of airfield US-Patent-Appl-SN-568541: US-Patent-4.032.089) Avail: US pavement. The use of a very thin overlay to reestablish the skid Patent and Trademark Office CSCL 11A resistance of a concrete pavement and applicability of radar subsurface profiling in estimating sidewalk undermining are also A surface of an article adapted for relative motion with a discussed. GRA fluid environment is finished by coating the surface with a fluid adhesive, covering the adhesive with a sheet of flexible film material under tension on the film material whereby the tensioned N81-14195# Deutsche Forschungs- und Versuchsanstalt fuer film material is bonded to the surface by the adhesive. Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. Official Gazette of the U.S. Patent and Trademark Office fuer Hochfrequenztechnik. 132 N81 14318 VOLUMETRIC PATTERN PREDICTION OF ANTENNAS ON decay associated with the full-flow conditioning system and its AIRCRAFT USING THE GEOMETRICAL THEORY OF individual components possesses initial period of decay character- DIFFRACTION Ph.D. Thesis - Kaiserslautern Univ. istics throughout the 600 cm decay length investigated. It is Thomas Jank Nov. 1979 178 p refs In GERMAN: ENGLISH concluded that these decay characteristics are due to the large summary Report will also be announced as translation scale of turbulence incoming and exiting the flow conditioning (ESA-TT-677) system of the Compressor Research Facility. GRA (DFVLR-FB-80-01: TT-677) Avail: NTIS HC A09/MF A01 The patterns of small dipoles or slot antennas mounted on N81-14289# Deutsche Forschungs- und Versuchsanstalt fuer the fuselage of an aircraft are computed in the high frequency Luft- und Raumfahrt, Goettingen (West Germany). Inst. fuer case. For the computation of the field the geometrical theory of Experimentelle Stroemungsmechanik. diffraction is used. A very versatile and realistic mathematical A COMPUTER-BASED LASER DOPPLER VELOCIMETER aircraft mode is developed. The construction of all rays which Jens-Carsten Petersen Jun. 1979 64 p refs In GERMAN: contribute considerably to the total field is a complicated numerical ENGLISH summary problem. Via the solution of this ray tracing problem it is possible (DFVLR-Mitt-79-14) Avail: NTIS HC A04/MF A01: DFVLR. to obtain arbitrary pattern cuts. Author Cologne DM 11.50 A Laser-Doppler-Velocimeter is described which is specially designed for windtunnel applications. Facing other Velocimeters N81-14265*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. the data analysis is here performed digitally by use of a computer. The control of the testing procedure is also done by EXPERIMENTAL STUDY OF SUPERSONIC VISCOUS the computer, while a remote control is installed between LEESIDE FLOW OVER A SLENDER DELTA WING computer and positioning control for the optical part of the Joachim Szodruch Dec. 1980 62 p refs Velocimeter. built up on two three-axis-travers mechanisms. This (NASA-TM-81248: A-8408) Avail: NTIS HC A04/MF A01 CSCL 200 remote control generates or improves all signals necessary for control procedures. In addition to the description of the An investigation was conducted to study in detail the vortical system's functions, necessary and desirable improvements are flow over the leeward side of a 70 deg swept delta wing having briefly discussed. Author subsonic and supersonic leading edges. Two types of flow were encountered and studied, namely leading edge separation and separation with a shock. Especially for the latter type. Reynolds number plays an important role and unexpected strong stream- N81-14292# Institut Franco-Allemand de Recherches, St. Louis wise vortices were observed. An optical method is described to (France). obtain a first aproximation of shear stress values in the streamwise THE DALEMBERTOMETER direction across the wing span. Author P. Smigieiski and P. G. Sava 20 Nov. 1979 9 p refs Presented at 2nd European Congr. on Opt. Appl. to Metrology (OPIEM 79). Strasburg. Nov. 1979 N81-14275# ARO. Inc.. Arnold Air Force Station. Tenn. (ISL-CO-220/79) Avail: NTIS HC A02/MF A01 LASER-RAMAN/RAYLEIGH FLOW DIAGNOSTIC TECH- A new device is presented utilizing a He-Ne 5 mW laser as NIQUES APPLIED TO SUBSONIC FLOW Final Report. a light source, and including a Mach-Zehnder interferometer 13 Apr. 1977 - 14 Mar. 1978 coupled with schlieren systems with defocalized phase plates W. D. Williams. D. W. Sinclair, and L L Price AEDC Oct. permitting the measurement of the dalembertian of the optical 1980 57 p refs Sponsored by Air Force path along a trajectory of the laser beam in a transparent medium. (AD-A091695: AEDC-TR-80-20) Avail: NTIS This device which required a long development, as much optically HC A04/MF A01 CSCL 20/4 as electronically, is used for the study of noise sources in the The feasibility of performing laser-Raman/Rayleigh scattering air jets. The particularities of the system are described and its measurements in subsonic flows was demonstrated in the 6 in. performances are illustrated by applications in aerodynamics. Acoustic Research Tunnel (ARTI of the Propulsion Wind Tunnel Author facility at AEDC. The ART is an open-circuit, atmospheric inbleed tunnel that operates on the Plenum Evacuation System of the 16 ft transonic Propulsion Wind Tunnel (16T). Laser-Raman/ N81-14300# Institut Franco-Allemand de Recherches. St. Louis Rayleigh scattering techniques were used to measure air number (France). density, H20 number density, and static temperature and to CONTROLS OF AERONAUTICAL STRUCTURES UNDER detect the onset of water vapor condensation. Measurements FATIGUE TESTING BY HOLOGRAPHIC PULSED LASERS were made near the tunnel axial centerline over the Mach number INTERFEROMETRY range from 0.10 to 0.80. Measurements were also made in the H. Fagot. F. Albe. P. Smigieiski. A. Stimpfling. and J. L. Arnaud turbulent boundary layer on the wall of the test section at Mach (SNIAS) 20 Nov. 1979 11 p refs Presented at 2nd European numbers 0.50 to 0.80. GRA Congr. on Opt. Appl. to Metrology (OPIEM 79), Strasburg. Nov. 1979 Sponsored in part by Direction des Recherches, Etudes et Techniques (ISL-CO-218/79) Avail: NTIS HC A02/MF A01 N81-14276/JI Air Force Wright Aeronautical Labs., Wright- A compact and mobile holographic camera is described which Patterson AFB, Ohio. is capable of recording holograms by double exposure. The time EFFECTS OF DOWNSTREAM DISTANCE ON TURBULENCE lapse between the 2 laser impulses (duration 20 ns, energy DECAY FOR THE COMPRESSOR RESEARCH FACILITY LOW 100 mj approx.) is adjustable from 0.1 micron to infinity. The CONDITIONING SYSTEM Final Report. 1 Feb. 1978 - 1 Jul. successful 'in situ' experimentation of this device took place 1979 while bars of aeronautical structures were being tested for Douglas C. Rabe Mar. 1980 72 p refs fatigue (periodical tensile stress). The holograms were recorded (AF Pro). 3066) without interrupting the fatigue testings which lasted several (AD-A091543: AFWAL-TR-80-2023) Avail: NTIS hours. The testbars being used were chosen because their HC A04/MF A01 CSCL 14/2 characteristics demonstrate problems typically met in aeronau- The turbulence decay of the 304.8 cm (120 in) diameter tics. A.R.H. flow conditioning system for the Air Force Aero Propulsion Laboratory's Compressor Research Facility was investigated in a 25.4 cm (10 in) diameter channel to predict turbulence levels N81-14318* National Aeronautics and Space Administration. that can be expected at the entrance to compressors being Pasadena Office. Calif. tested in the facility. Results of this experimentation show that POWER CONTROL FOR HOT GAS ENGINES Patent the flow conditioning system will meet the design goal of reducing William F. MacGlashan. inventor (to NASA) (JPL) Issued 21 Oct. the expected imcoming turbulence level of 30-40% to less than 1980 10 p Filed 19 May 1978 Supersedes N78-25430 1% at the entrance to a test compressor. Further, the turbulence (16 - 16, p 2122) Sponsored by NASA 133 N81-14324 (NASA-Case-NPO-14220-1: US-Patenl-4.228.656: COMPRESSOR CONFIGURATION AND DESIGN OPTIMIZA- US-Patent-Appl-SN-907421: US-Patent-Class-60-518: TION FOR THE HIGH RELIABILITY GAS TURBINE Final US-Patent-Class-74-417) Avail: US Patent and Trademark Report Office CSCL 131 Diana L. Day and Fred H. Boenig Apr. 1980 54 p Prepared A hot gas engine in which the expander piston of the engine in cooperation with Pratt and Whitney Aircraft. West Palm Beach. is connected to an expander crankshaft. A displacer piston of Fla. the engine is connected to a separate displacer crankshaft which (Contract DE-AC03-79ET-15425) may or may not be coaxial with the expander crankshaft. A (DOE/ET-15425/T1: GTR-2136) Avail: NTIS phase angle control mechanism used as a power control for HC A04/MF A01 changing the phase angle between the expander and displacer The compressor and diffuser preliminary designs were complet- crankshaft is located between the two crankshafts. The phase ed to define size and performance characteristics. The compressor angle control mechanism comprises a differential type mechanism has 9 stages and a predicted adiabatic efficiency of 8835%. comprised of a pair of gears, as for example, bevel gears, one The diffuser selected is a conventional straight wall configura- of which is connected to one end of the expander crankshaft tion with an equivalent conical angle of 8 degrees. An alternate and the other of which is connected to the opposite end of the diffuser configuration was recommended because of its excellent displacer crankshaft. A mating bevel gear is disposed in meshing performance potential in high Mach number applications. The engagement with the first two level gears to provide a phase HTF compressor configuration appears to offer equivalent COE angle control between the two crankshafts. Other forms of and reliability as compared to the Baseline Reliable Engine differential mechanisms may be used including conventional spur configuration, but at more conservative aerodynamic loading gears connected in a differential type arrangement. levels. J.M.S. Official Gazette of the U.S. Patent and Trademark Office N81-14324# Lord Kinematics. Erie. Pa. N81-14329# Detroit Diesel Allison. Indianapolis. Ind. SERVICE LIFE DETERMINATION FOR THE UH-60-A GAS TURBINE ENGINES AND TRANSMISSIONS FOR BUS (UTTAS) HELICOPTER ELASTOMERIC BEARINGS Final DEMONSTRATION PROGRAMS Technical Status Report. Report. Aug. 1978 - Apr. 1980 31 Jan. - 30 Apr. 1980 Ernest P. Gaudette Apr. 1980 86 p D. N. Nigro May 1980 7 p (Contract DAAG46-78-C-0030) (Contract DE-AC02-78CS-54867) (AD-A091756; APE-79-021: USAAVRADCOM-TR-80-F-9: (COO-4867-07) Avail: NTIS HC A02/MF A01 AMMRC-TR-80-25) Avail: NTIS HC A05/MF A01 CSCL Activities related to the procurement and delivery of 1 1 gas 01/3 turbine engines, 11 automatic transmissions, and software items A method for predicting the endurance life of the elastomeric such as cost reports, drawings and parts lists for the bus bearings on the UTTAS helicopter rotor is presented. The critical demonstration program are reported. DOE layers, based on elastomer strain, are determined analytically for these two bearings. Representative standard laboratory test specimens bonded with the specified elastomers are subjected N81-14332# General Electric Co.. Schenectady. N. Y. Gas to the same static and typical dynamic strains, and tested to Turbine Div. failure. Two resulting S-N curves are reported, one for each of DEVELOPMENT OF H IG H-TEM PER ATU R E TURBINE the two rotor elastomeiic bearings. A short verification of SUBSYSTEM TECHNOLOGY TO A TECHNOLOGY READI- Miner's cumulative damage theory is also conducted and NESS STATUS. PHASE 2 Quarterly Report. Jul. - Sep. reported. GRA 1979 M. W. Horner Oct. 1979 172 p (Contract EX-76-C-01-1806) (FE-1806-72) Avail: NTIS HC A08/MF A01 N81-14325# Pratt and Whitney Aircraft Group, West Palm The program was divided into three phases: Program and Beach. Fla. Government Products Div. System Definition, Technology Testing and Test Support Studies, IMPROVED CAPABILITIES TO DETECT INCIPIENT BEAR- and Technology Readiness Verification Test Program. The work ING FAILURES Final Report. 1 May 1978 - 31 Mar. 1980 scope for the overall three phases of the program encompasses J. A. Alcorta. J. H. Mohn, and L L. Packer Jul. 1980 86 p the design, development, manufacture, and test of a GE-TRV refs turbine subsystem to be tested at a DOE facility. The objectives (Contract F33615-78-C-2008: AF Pro). 3048) of Phase 2 are to: perform component design and technology (AD-A091687: PWA-FR-13036A: AFWAL-TR-80-2057) Avail: testing in critical areas: perform system design and tradeoff NTIS HC A05/MF A01 CSCL 13/9 analyses in sufficient depth to support the component design A methodology using safe, low level radiation technique for and test tasks: and update the Phase 1 combined cycle studies the detection of wear in gas turbine engine mainshaft bearings to evaluate the commercial viability of GE-TRV turbine system. has been developed and evaluated in a simulated gas turbine DOE engine bearing environment. In conjunction with spectrometric analyses of engine oil samples, the radioactive tag will detect low levels of wear and will simultaneously indicate whether the N81-14347*# California Univ., Los Angeles. Dept. of Mechanics tagged bearing is the source of the wear, lron-55 is employed and Structures. as the active tag owing to its low radiation levels, long half-life, DUAL METHODS AND APPROXIMATION CONCEPTS IN and homogeneity of the isotope in the bearing rollers. The low STRUCTURAL SYNTHESIS Final Report. Feb. 1978 - Aug. levels of radiation existent in the tagged wear particles requires 1979 the separation of wear debris from the oil. Test results showed Claude Fleury and Lucien A. Schmit. Jr. Washington NASA that the tagging method would provide a means of identifying Dec. 1980 223 p refs the tagged rollers experiencing abnormal wear at the -f or - (Grant NsG-1490) 0.5 part per million iron level. Safe, low-level radioactive (NASA-CR-3226) Avail: NTIS HC A10/MF A01 CSCL 20K bearing roller tagging was achieved by waiting six months after Approximation concepts and dual method algorithms are neutron irradiation for the decay of the iron-59 and the combined to create a method for minimum weight design of chromium-51 gamma emitting radioisotopes. Wear measurements structural systems. Approximation concepts convert the basic are conducted using the long half-life, low energy emitting X-rays mathematical programming statement of the structural synthesis from iron-55. The technique used for tagging, debris concentration, problem into a sequence of explicit primal problems of separable debris measurement, and bearing testing is given. GRA form. These problems are solved by constructing explicit dual functions, which are maximized subject to nonnegativity con- straints on the dual variables. It is shown that the joining together N81-14327# United Technologies Corp.. South Windsor, Conn. of approximation concepts and dual methods can be viewed as Power Systems Div. a generalized optimality criteria approach. The dual method is 134 N81 14560 successfully extended to deal with pure discrete and mixed N81-14555*# National Aeronautics and Space Administration. continuous-discrete design variable problems. The power of the Marshall Space Flight Center. Huntsville. Ala. method presented is illustrated with numerical results for example PROCEEDINGS: FOURTH ANNUAL WORKSHOP ON problems, including a metallic swept wing and a thin delta wing METEOROLOGICAL AND ENVIRONMENTAL INPUTS TO with fiber composite skins. Author AVIATION SYSTEMS Walter Frost, ed. and Dennis W. Camp. ed. Mar. 1980 287 p refs Workshop held in Tullahoma, Tenn.. 25-27 Mar^ 1980: N81-14363# Pennsylvania Univ.. Philadelphia. Dept. of Materials sponsored in part by FAA and NOAA Prepared in cooperation Science and Engineering. with Tennessee Univ. Space Inst. MECHANISMS OF DAMAGE ACCUMULATION IN TIME- (Contract NAS8-32692) DEPENDENT CYCLIC DEFORMATION Progress Report. (NASA-CP-2139: FAA-RD-80-67) Avail: NTIS 1 Jan. - 31 Dec. 1980 HC A13/MF A01 CSCL 04B Campbell Laird Aug. 1980 15 p refs Various aspects of the interaction of the atmosphere with (Contract DE-AC02-80ER-10570) aviation systems are discussed. The topics for discussion addressed (DOE/ER-10570/1) Avail: NTIS HC A02/MF A01 the following: winds and wind shear: turbulence: icing and frost: Two kinds of damage produced in cyclic creep were fog. visibility, and ceiling: and atmospheric electricity and lightning. investigated. The change in dislocation density and arrangement in copper and damage phenomena involving precipitates in Cr-Mo-V rotor steel. In copper tested at low temperatures, N81-14556*# National Aeronautics and Space Administration. strain bursts were recognized for the first time in polycrystals of Marshall Space Flight Center. Huntsville, Ala. a pure metal in both cyclic and static creep. The stress regime SURVEY OF WORKSHOPS ON METEOROLOGICAL AND for producing bursts was defined and the dislocation structures ENVIRONMENTAL INPUTS TO AVIATION SYSTEMS associated with them studied. Interpretation based on instabilities Walter Frost (Tennessee Univ. Space Inst.) and Dennis W. Camp associated with the persistent slip bands which form in regular In its Proc: Fourth Ann. Workshop on Meteorol. and Environ. fatigue is being explored. For the study of rotor steel, three Inputs to Aviation Systems Mar. 1980 p 23-39 batches of material were obtained and characterized and a new high temperature apparatus built to do tests. A literature review Avail: NTIS HC A13/MF A01 CSCL 04B justifying the choice of steels and tests is provided. HOE Various aspects of aviation meteorology are discussed with respect to their relative effects on aircraft terminal operations. Existing data on turbulence and wind shear from aircraft and N81-14525$ National Technical Information Service. Springfield. towers are summarized. The significance of obtaining more real Va. time wind and temperature information is emphasized. The MANEUVERING AIRCRAFT: NOISE POLLUTION AND application and testing of various radiometer devices are also CONTROL. CITATIONS FROM THE NTIS DATA BASE described. Airborne methods to indicate wind differences at flight Progress Report, 1976 - Aug. 1980 altitude and at touchdown are reported. R.C.T. Guy E. Habercom. Jr. Sep. 1980 189 p Supersedes NTIS/PS-79/0973 and NTIS/PS-78/0930 N81-14557*# National Aeronautics and Space Administration. (PB80-815566; NTIS/PS-79/0973: NTIS/PS-78/0930) Avail: Marshall Space Flight Center, Huntsville. Ala. NTIS HC S30.00/MF S30.00 CSCL 13B AVIATION METEOROLOGY RESEARCH AND DEVELOP- Methods for alleviating noise created by maneuvering aircraft MENT: A STATUS REPORT are cited. Flyby. turning flight, takeoffs. and landings are the John Enders In its Proc: Fourth Ann. Workshop on Meteorol. maneuvers investigated. This updated bibliography contains and Environ. Inputs to Aviation Systems Mar 1980 p 40-44 184 citations. 25 of which are new entries to the previous edition. GRA Avail: NTIS HC A13/MF A01 CSCL 048 The dynamic and rapid growth of technology in the area of aviation meteorology research and development are described with emphasis on the measurement of hazardous weather N81 14550# Los Alamos Scientific Lab.. N. Mex. phenomena. Aspects of both onboard instrumentation and ground based facilities are evaluated in terms of their effectiveness STATISTICAL RELATIONSHIP BETWEEN MEDIAN VISIBIL of in avoiding hazards due to atmospheric electricity and lightning. ITY AND CONDITIONS OF WORSTCASE MANMADE IMPACT ON VISIBILITY Methods of alleviating terminal are hazards such as fog. low John D. Gins (Technology Service Corp.. Santa Monica. Calif.), visibility and ceilings are also described. R.C.T. David Nochumson. and John Trijonis (Santa Fe Research Corp.. N. Mex.) 1980 16 p refs Presented at the Symp. on Plumes N81-14558*# National Aeronautics and Space Administration. and Visibility. Grand Canyon. Ariz. 10-14 Nov. 1980 Marshall Space Flight Center. Huntsville.-Ala. (Contract W-7405-eng-36) FEDERAL AVIATION ADMINISTRATION AND NATIONAL (LA-UR-80-2485: CONF-801114-1) Avail: NTIS WEATHER SERVICE AVIATION RESEARCH AND DEVELOP- HCA02/MF A01 MENT The data base for the study consisted of midday visibility John W. Connolly In its Proc: Fourth Ann. Workshop on Meteorol. recordings for the years 1974 to 1976 at 28 suburban/nonurban and Environ. Inputs to Aviation Systems Mar. 1980 p 45-48 airports throughout the United States. The visibility recordings were converted to estimates of extinction coefficients with the Avail: NTIS HC A13/MF A01 CSCL 04B use of the Koschmeider formula. The data were sorted according An overview is given of the developmental status of aviation to meteorology in order to eliminate days that were obviously weather services. Particular attention is given to justifying the dominated by natural causes of poor visibility. Three approaches need for better, more reliable service. The accomplishments of were used for relating worst-case extinction to median extinction. several automatic weather stations are discussed. R.C.T. The first approach was based upon frequency distribution functions. The second used observed ratios of upper percentile to median extinction. The third employed regression techniques. N81-14560*# Army Test and Evaluation Command. Aberdeen All ot the relationships were formulated and evaluated with the Proving Ground. Md. 1974 to 1976 data on a national/annual basis as well as AIRCRAFT ICING INSTRUMENTATION: UNFILLED regional/quarterly basis. Performance tests were run against 1954 NEEDS to 1956 data at 11 of the 28 sites. Simple ratio relationships Phyllis F. Kitchens In NASA. Marshall Space Flight Center are recommended for use in translating median visibility impacts Proc: Fourth Ann. Worksnop on Meteorol. and Environ. Inputs into worst-case impacts. The errors associated with these ratio to Aviation Systems Mar 1980 p 61-65 models are approximately 30%. DOE Avail: NTIS HC A13/MF A01 CSCL 04B 135 N81 14561 A list of icing instrumentation requirements are presented. William W. Vaughan In its Proc.: Fourth Ann. Workshop on Because of the Army's helicopter orientation, many of the Meteorol and Environ. Inputs to Aviation Systems Mar. 1980 suggestions are specific to rotary wing aircraft: however, some p 140-160 of the instrumentation are also suitable for'general aviation Avail: NTIS HC A13/MF A01 CSCL 048 aircraft. R.C.T. The phenomenology of lightning and lightning measurement techniques are briefly examined with a particular reference to N81-14561*# Lockheed Aircraft Service Co.. Pasadena. Calif. aeronautics. Developments made in airborne and satellite detection TURBULENCE: FROM A PILOT'S VIEWPOINT methods are reported. NASA research efforts are outlined which Charles L. Pocock In NASA. Marshall Space Flight Center cover topics including in-situ measurements, design factors and Proc: Fourth Ann. Workshop on Meteorol. and Environ. Inputs protection, remote optical and radio frequency measurements, to Aviation Systems Mar. 1980 p 66-70 and space vehicle design. M.G. Avail: NTIS HC A13/MF A01 CSCL 04B N81-14568*# Federal Aviation Administration. Washington. D.C. The measurement of atmospheric turbulence is discussed in Systems Research and Development Service. terms of a pilots viewpoint. Two areas of measurement are MEASURING WEATHER FOR AVIATION SAFETY IN THE considered: frequency and severity of turbulence. Suggestions 1980'S are given for helping the pilot solve the turbulence problem. Robert W. Wedan In NASA. Marshall Space Flight Center R.C.T. Proc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputs to Aviation Systems Mar. 1980 p 162-167 N81-14562*# National Aeronautics and Space Administration. Hugh L. Dryden Flight Research Center. Edwards. Calif. Avail: NTIS HCA13/MFA01 CSCL 04B CLEAR AIR TURBULENCE: HISTORICAL COMMENTS Requirements for an improved aviation weather system are L. J. Ehernberger In NASA. Marshall Space Flight Center defined and specifically include the need for (1) weather Proc: Fourth Ann. Workshop on Meterol. and Environ. Inputs observations at all airports with instrument approaches, to Aviation Systems Mar. 1980 p 71-81 refs (2) more accurate and timely radar detection of weather elements hazardous to aviation, and (3) better methods of timely distribution Avail: NTIS HC A13/MF A01 CSCL 04B of both pilot reports arhd ground weather data. The development The basic reference material for gust design criteria are cited. of the discrete address beacon system data link, Doppler weather The status of clear air turbulence meteorology (forecasting and radar network, and various information processing techniques detection) is discussed. The directions of further research are described. M.G. technology is indicated. R.C.T. N81-14563*# Federal Aviation Administration, Atlantic City, N81-14571*j{/ National Oceanic and Atmospheric Administration, N.J, Boulder. Colo. Environmental Research Labs. WINDS AND WIND SHEAR IN-SITU SENSORS THE MICROBURST: COMMON FACTOR IN RECENT R. Craig Goff In NASA. Marshall Space Flight Center Proc: AIRCRAFT ACCIDENTS Fourth Ann. Workshop on Meteorol. and Environ. Inputs to Aviation Fernando Caracena In NASA. Marshall Space Flight Center Systems Mar. 1980 p 82-108 Proc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputs to Aviation Systems Mar. 1980 p 186-200 refs Avail: NTIS HC A13/MF A01 CSCL 04B The problem of development of instrumentation for providing Avail: NTIS HC A13/MF A01 CSCL 04B wind speed and direction information directly or indirectly to a The phenomenology of one class of strong thunderstorm pilot in the cockpit is considered. The pilots need for horizontal downdrafts, microbursts, is described. Several aircraft accidents wind information at various stages of flight {i.e., at liftoff, in are analyzed in which a microburst was involved and a concept approach and departure corridors, and even in flight outside the for an early warning wind shear sensor is presented. M.G. terminal area) are emphasized. R.C.T. N81-14572*# National Center for Atmospheric Research. Boulder. Colo. DOCTOR FUJITA'S MICROBURST ANALYSIS AT CHICAGO N81-14566*# Aeronautical Systems Div., Wright-Patterson AFB, Ohio. John McCarthy In NASA. Marshall Space Flight Center Proc.: OBSERVING LIGHTNING FROM GROUND-BASED AND Fourth Ann. Workshop on Meteorol. and Environ. Inputs to Aviation AIRBORNE STATIONS Systems Mar. 1980 p 201-202 John C. Corbin. Jr. In NASA. Marshall Space Flight Center Proc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputs Avail: NTIS HC A13/MF A01 CSCL 046 to Aviation Systems Mar. 1980 p 130-139 refs Doppler radar measurements of an intense wind shear occurance are discussed. The data suggest the presence of an Avail: NTIS HC A13/MF A01 CSCL 048 incredibly strong low level jet outflow component of the microburst The operational designs and performance capabilities of event, reaching 60 knots only 50 meters above the surface. ground-based and airborne lightning detection systems are Evidence also suggests that microbursts more typically occur in reviewed. The airborne Stormscope system is described and very weak thunderstorms that have hardly reached thunderstorm compared with onboard radar and the lightning detection and stage. M.G. ranging system (LDAR). Two examples of difference-in-time-of- arrival systems for detecting spherics from discharges in electrified clouds are described: (1) The LDAR system and (2) Taylor's N81-14575# Weapons Systems Research Lab.. Adelaide lightning mapping system. Next, an interferometric system (Australia). adapted to lightning location is discussed. Finally, systems that LOW-SPEED WIND-TUNNEL TESTS OF TWO WEATHER- are based upon crossed-loop magnetic direction finding principles COCKING SENSORS but which have been refined and improved to accurately locate D. P. Brown and R. I. Macleod Aug. 1980 29 p refs lightning discharges to ground are reviewed. M.G. (WSRL-0171-TM: AR-002-036) Avail: NTIS HC A03/MF A01 N81-14567*# National Aeronautics and Space Administration. Two blunt-nosed weathercocking wind direction sensors, one Marshall Space Flight Center, Huntsville. Ala. stabilized by a ring tail and the other by swept cruciform fins, AERONAUTICAL CONCERNS AND NATIONAL AERONAU- were tested in a low-speed wind tunnel to investigate possible TICS AND SPACE ADMINISTRATION ATMOSPHERIC aerodynamic interference between these wind direction sensors ELECTRICITY PROJECTS and the vehicles in front of which they were to be mounted. In 136 N81-14789 these low speed tests, sensor support shaft diameter and vehicle N81-14714*)Sf Boeing Co.. Seattle. Wash. nose tip geometry both caused significant errors in the ring-tailed GRID GENERATION FOR GENERAL THREE-DIMENSIONAL sensor's alignment to the free stream when the vehicle was at CONFIGURATIONS angle of attack. A disk baffle placed on the shaft behind the K. D. Lee. M. Huang. N. J. Yu, and P. E. Rubbert In NASA. sensor base was found to reduce sensor misalignment significantly Langley Research Center Numerical Grid Generation Tech. 1980 at small angles of attack. Alignment errors for the cruciform p 355-366 sensor were much smaller than those of the ring-tailed sensor Avail: NTIS HC A24/MF A01 CSCL 12A at small angles of attack, and these smaller errors were further A suitable grid system for complex three dimensional reduced when a baffle was placed on the shaft. Author configurations such as wing/body/nacelle shape for the solution of nonlinear transonic flow problems was constructed. Two approaches were explored based on Thompson's body fitted N81-14601*# EG and G Washington Analytical Services Center. coordinate concept. The most general approach was to divide Inc.. Pocomoke City. Md. the computational domain into multiple rectangular blocks where CATALOG OF SEA STATE AND WIND SPEED IN THE the configuration itself was also represented by a set of blocks SOUTH ATLANTIC BIGHT whose structure follows the natural lines of the configuration. J. D. McMillan Jan. 1980 134 p refs The block structured grid system was adaptable to complex (Contract NAS6-2639) configurations and gives good grid quality near physical corners. (NASA-CR-156872) Avail: NTIS HC A07/MF A01 CSCL However, it introduced algorithm issues for the flow solution 08C concerning the treatment of nonanalytic grid block boundaries The GEOS 3 significant waveheight and ground wind speed and nonstandard grid cells. These issues were explored in relation estimation algorithms are derived and then applied to all GEOS to the grid generation. A more limited approach treats a wing/body 3 data in the South Atlantic Bight. The investigation area is configuration with only a single rectangular block in computational divided into five geographical sectors and significant waveheight space. The issues involving nonstandard cells were avoided, but and wind speed histograms are presented in each sector by other limitations on grid resolution appear. Both a linear and a month and by season. In the discussion of the histograms, definite nonlinear system of grid generation equations were developed seasonal trends are identified and examined. Author including methods of grid control. R.C.T. N81-14788*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N81-14697*# Lockheed-Georgia Co.. Marietta. ASSESSMENT OF GROUND EFFECTS ON THE PROPAGA- COMPONENT-ADAPTIVE GRID EMBEDDING TION OF AIRCRAFT NOISE: THE T-38A FLIGHT EXPERI- E. H. Atta In NASA. Langley Research Center Numerical MENT Grid Generation Tech. 1980 p 157-174 ref William L Willshire, Jr. Dec. 1980 128 p refs (NASA-TP-1747: L-13765) Avail: NTIS HC A07/MF A01 Avail: NTIS HC A24/MF A01 CSCL 12A CSCL 20A One of the major problems related to transonic flow A flight experiment was conducted to investigate air to ground prediction about realistic aircraft configuration is the generation propagation of sound at gazing angles of incidence. A turbojet of a suitable grid which encompasses such configurations. In powered ariplane was flown at altitudes ranging from 10 to general, each aircraft component (wing, fuselage, nacelle) requires 160 m over a 20-microphone array positioned over grass and a grid system that is usually incompatible with the grid systems concrete. The dependence of ground effects on frequency, of the other components: thus, the implementation of finite- incidence angle, and slant range was determined using two difference methods for such geometrically-complex configurations analysis methods. In one method, a microphone close to the is a difficult task. An approach was developed to treat such a flight path is compared to down range microphones. In the problem. The basic idea is to generate different grid systems, other method, comparisons are made between two microphones each suited for a particular component. Thus, the flow field domain which were equidistant from the flight path but positioned over is divided into overlapping subdomains of different topology. These the two surfaces. In both methods, source directivity angle was grid systems are then interfaced with each other in such a way the criterion by which portions of the microphone signals were that stability, convergence speed and accuracy are maintained. compared. The ground effects were largest in the frequency Author range of 200 to 400 Hz and were found to be dependent on incidence angle and slant range. Ground effects measured for angles of incidence greater than 10 deg to 15 deg were near N81-14708*/? Aircraft Research Association Ltd. Bedford zero. Measured attenuation increased with increasing slant range (England). for slant ranges less than 750 m. Theoretical predictions were AN INVESTIGATION INTO GRID PATCHING TECH- found to be in good agreement with the major details of the NIQUES measured results. Author C. R. Forsey, M. G. Edwards, and M. P. Carr In NASA. Langley Research Center Numerical Grid Generation Tech. 1980 N81-14789*# Georgia Inst. of Tech., Atlanta. School of p 265-294 Sponsored in part by the Ministry of Defence, England Aerospace Engineering. PREDICTION OF SOUND RADIATED FROM DIFFERENT Avail: NTIS HC A24/MF A01 CSCL 12A PRACTICAL JET ENGINE INLETS Semiannual Status Report. In the past decade significant advances were made using 2 Jun. - 30 Nov. 1980 flow field methods in the calculation of external transonic flows B. T. Zinn and W. L Meyer 1980 41 p refs over aerodynamic configurations. It is now possible to calculate (Grant NAG3-67: Contract F49620-77-C-0066) inviscid transonic flow over three dimensional configurations by (NASA-CR-163824) Avail: NTIS HC A03/MF A01 CSCL solving the potential equation. However, with the exception of 20A the transonic small disturbance methods which have the advantage Existing computer codes for calculating the far field radiation of a simple cartesian grid, the configurations over which it is patterns surrounding various practical jet engine inlet configura- possible to calculate such flows are relatively simple. The major tions under different excitation conditions were upgraded. The reason for this is the difficulty of producing compatibility between, computer codes were refined and expanded so that they are grid generation and flow equation solutions The main programs now more efficient computationally by a factor of about three in use. use essentially analytic transformations for prescribed and they are now capable of producing accurate results up to configurations and, as such, are not easy to extend. While there nondimensional wave numbers of twenty. Computer programs is work in progress to extend this type of system to a limited were also developed to help generate accurate geometrical extent, the long term effort is directed towards a more general representations of the inlets to be investigated. This data is approach. This approach should not be restricted to producing required as input for the computer programs which calculate grid systems in isolation but rather a consideration of the overall the sound fields. This new geometry generating computer program problem of flow field solution. E.D.K. considerably reduces the time required to generate the input 137 N81-14792 data which was one of the most time consuming steps in the considerations are made, for which classes of fans noise standards process. The results of sample runs using the NASA-Lewis QCSEE can be defined to characterize the noise emission of the various inlet are presented and comparison of run times and accuracy fan types. M.G. are made between the old and upgraded computer codes. The overall accuracy of the computations is determined by comparison N81-14962*# National Aeronautics and Space Administration. of the results of the computations with simple source solutions. A.R.H. Washington. 0. C. BIRD FLIGHT AND AIRPLANE FLIGHT A. Magnan Dec. 1980 424 p refs Transl. into ENGLISH N81-14792$ National Physical Lab.. Teddington (England). from Serv. Tech. de I'Aeron. (Paris), bull. 74. Jun. 1931 p 5-307 Transl. by Kanner (Leo) Associates. Redwood City. Calif. Acoustics Unit. THE RATING OF HELICOPTER NOISE: DEVELOPMENT (Contract NASw-3199) OF A PROPOSED IMPULSE CORRECTION (NASA-TM-75777) Avail: NTIS HC A18/MF A01 CSCL B. F. Berry. H. C. Fuller. A. J. John, and D. W. Robinson Dec. 01B Research was based on a series of mechanical, electrical, 1979 45 p refs (NPL-AC-93; ISSN-0143-7143) Avail: NTIS and cinematographic instruments developed to measure various features of air current behavior as well as bird and airplane HC A03/MF A01 Efforts to the scale of effective perceived noise level (EPNL) flight. Investigation of rising obstruction and thermal currents to account for the subjective effects of impulsive helicopter noise led to a theory of bird flight, especially of the gliding and are reported. Psychoacoustical studies of the annoyance of soaring types. It was shown how a knowledge of bird flight can recorded and simulated helicopter noises are described and an be applied to glider and ultimately motorized aircraft construction. objective descriptor of impulsiveness is developed. This descriptor The instruments and methods used in studying stress in airplanes forms the basis of a draft standard for an impulse correction to and in comparing the lift to drag ratios of airplanes and birds EPNL M.G. are described. T.M. N81-14793# Rolls-Royce Ltd.. Derby (England). EXHAUST NOISE IN FLIGHT: THE ROLE OF ACOUSTIC N81-14964 Air Force Inst. of Tech.. Wright-Patterson AFB, Ohio. INSTALLATION EFFECTS I. S. Southern Apr. 1980 14 p refs TIME DEPENDENT NAVIER-STOKES SOLUTION OF A (PNR-90029) Avail: NTIS HC A02/MF A01 TURBULENT GAS JET EJECTED FROM A RECTANGULAR The acoustic installation effect on engine exhaust noise due ORIFICE INTO A HIGH-SUBSONIC CROSSFLOW to the presence of a wing or high tailplane is discussed for Ph.D. Thesis both the static and flight cases. A simple theoretical model for William Charles Golbitz 1980 187 p reflection and edge diffraction using ray theory is introduced Avail: Univ. Microfilms Order No. 8028555 and compared with experimental results. The model is used to The high temperature (1500K) exhaust gases from an predict full scale installation effects where, due to the low airborne chemical laser being forcibly ejected downwards at a directivity of engine noise, reflection is dominant and the effect jet to freestream dynamic pressure ratio (Q) of 0.15 from an generally less than 3 dB. This suggests that the so called static aspect ratio 1.75 rectangular diffuser orifice aligned with the to flight anomaly cannot be explained in terms of acoustic major axis parallel to the mach 0.7 ambient crossflow at the installation effects. Some alternative possibilities are reviewed. tropopause was successfully simulated using a modified donor-cell Author ICE (Implicit Continuous fluid Eulerian) algorithm formulated in primitive variables. The complete set of time dependent, three-dimensional Navier-Stokes equations and a species conservation equation were numerically solved for every cell in N81-14795# Rolls-Royce Ltd.. Derby (England). the computational domain. The diffusive flux effects caused by THE MEASUREMENT OF AERO GAS TURBINE NOISE concentration gradients (Fick's Law) as well as variable transport L. R. Bentley 29 Jan. 1980 44 p refs and thermodynamic properties of the gas mixture were incorpor- (PNR-90032) Avail: NTIS HC A03/MF A01 ated into the numerical model Turbulence closure was achieved Equipment used in noise certification tests for gas turbine by employing a locally varying velocity defect eddy viscosity aircraft engines includes: (1) a microphone system, calibrated model. Chemical reactions between the exhaust gases and the amplifier and tape recorder: (2) a means of relating aircraft ambient crossflow were proscribed. Dissert. Abstr. position and the noise: and (3) an apparatus for determining the temperature and humidity conditions in the propagation space N81-14966 Wichita State Univ.. Kans. for the calculation of atmospheric attenuation. Techniques for AN ANALYTIC MODEL OF SUBSONIC FLOW AROUND AN obtaining flyover and static test bed measurements are examined AIRFLOW WITH A SPOILER Ph.D. Thesis and assessed. Future developments are considered with emphasis Neal Jay Pfeiffer 1980 103 p on the acquisition of digital data. A.R.H. Avail: Univ Microfilms Order No. 8028606 A computer model was developed to simulate low speed N81-14796# Deutsche Forschungs- und Versuchsanstalt fuer two dimensional flow past the airfoil Flow visualization and wind Luft- und Raumfahrt. Goettingen (West Germany). Inst. fuer tunnel measurements provided insight into the basic physical Experimentelle Stroemungsmechanik. features of this flow. The basis of the method was the matching NOISE AND NOISE ABATEMENT IN FANS AND BLOWERS: of solutions for outer and inner regions. Once the inner and A REVIEW outer solutions were compatible, surface pressures were integrated Wolfgang Neise Mar. 1980 148 p refs In GERMAN: ENGLISH to give values of lift. drag, pitching moment and spoiler hinge summary moment coefficients. Corrections for skin friction were included. (DFVLR-FB-80-16) Avail: NTIS HC A07/MF A01: DFVLR. Computations were made for two low speed airfoils for which Cologne DM 22.50 detailed data exist for flow with spoilers. The comparisons covered Noise generation and its reduction industrial fans (ventilators) ranges of spoiler deflection angles up to 60 deg and angles of is addressed. A review is given of the fan types commonly in attack from zero to full stall. T.M. use and their practical applications, the mechanisms of the aerodynamic noise generation in fans, theoretical and empirical N81-14967* National Aeronautics and Space Administration. prediction methods for fan noise, acoustic similarity laws, and John F. Kennedy Space Center, Cocoa Beach. Fla. noise reduction methods by means of the fan construction and SYSTEM FOR REFURBISHING AND PROCESSING PARA- fan operation. Measurement procedures are discussed with respect CHUTES Patent to the noise radiated from different parts of a fan. e.g.. from the Russell T. Crowell. inventor (to NASA) Issued 30 Sep. 1980 fan inlet or outlet, from the fan casing, from the fan as a whole, 8 p Filed 21 Dec. 1977 Supersedes N78-22026 (16 - 13. and to the noise radiated into ducts connected to the fan. Finally. p 1654) 138 N81-14974 (NASA-Case-KSC-11042-1; US-Patent-4,224.810: with linearized theory for calculation of aerodynamic force US-Patent-Appl-SN-862878: US-Patent-Class-68-3R) Avail: US coefficients. R.C.T. Patent and Trademark Office CSCL 13H A method for refurbishing and processing parachutes is disclosed including an overhead monorail conveyor system on N81-14971*# Boeing Commercial Airplane Co.. Seattle. Wash. which the parachute is suspended for horizontal conveyance. A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSIS The parachute is first suspended in partially open tented OF SUPERSONIC AIRCRAFT. PART 3: COMPUTER configuration wherein open inspection of the canopy is permitted. PROGRAM DESCRIPTION Final Report. Sep. 1978 - Aug. The parachute is transported by the monorail conveyor to a 1980 washing and drying station. Following drying of the parachute, W. D. Middleton, J. L. Lundry, and R. G. Coleman Washington the parachute is conveyed into an interior space where it is NASA Dec. 1980 122 p refs finally inspected and removed from the monorail conveyor and (Contract NAS1-15534) laid upon a table for folding. Following folding operations, the (NASA-CR-3353: D6-41840-3) Avail: NTIS parachute is once again mounted on the conveyor in an elongated HC A06/MF A01 CSCL 01A horizontal configuration and conveyed to a packing area for The computer program documentation for the design and stowing the parachute in a deployment bag. analysis of supersonic configurations is presented. Schematics Official Gazette of the U.S Patent and Trademark Office and block diagrams of the major program structure, together with subroutine descriptions for each module are included.R.C.T. N81-14968* National Aeronautics and Space Administration. Langley Research Center, Hampton. Va. N81-14972*# National Aeronautics and Space Administration. AERODYNAMIC SIDE-FORCE ALLEVIATOR MEANS Langley Research Center. Hampton. Va. Patent INVESTIGATION OF CONVERGENT-DIVERGENT NOZZLES Dhanvada M. Rao. inventor (Old Dominion Univ.) Issued 30 Sep APPLICABLE TO REDUCED-POWER SUPERSONIC CRUISE 1980 7 p Filed 12 Mar 1979 Supersedes N79-17813 (17 - AIRCRAFT 09. p 1072) Sponsored by NASA Bobby L. Berrier and Richard J. Re Dec. 1980 218 p refs (NASA-Case-LAR-12326-1; US-Patent-4,225.102; (NASA-TP-1766: L-13974) Avail: NTIS HC A10/MF A01 US-Patent-Appl-SN-019541; US-Patem-Class-244-130; CSCL 01A US-Patent-Class-102-56R: US-Patent-Class-102-92.1; An investigation was conducted of isolated convergent- US-Patent-Class-244-119) Avail: US Patent and Trademark divergent nozzles to determine the effect of several design Office CSCL 01A parameters on nozzle performance. Tests were conducted using An apparatus for alleviating high angle of attack side force high pressure air for propulsion simulation at Mach numbers on slender pointed cylindrical forebodies such as fighter aircraft, from 0 60 to 2.86 at an angle of attack of 0 deg and at nozzle missiles and the like is described. A symmetrical pair of helical pressure ratios from jet off to 460. Three power settings (dry. separation trips was employed to disrupt the leeside vortices partial afterburning, and maximum afterburning), three nozzle normally attained. The symmetrical pair of trips starts at either lengths, and nozzle expansion ratios from 1.22 to 2.24 were a common point or at space points on the upper surface of the investigated. In addition, the effects of nozzle throat radius and forebody and extends along separate helical paths along the a cusp in the external boattail geometry were studied. The results circumference of the forebody. of this study indicate that, for nozzles operating near design Official Gazette of the US Patent and Trademark Office conditions, increasing nozzle length increases nozzle thrust-minus- drag performance. Nozzle throat radius and an external boattail N81-14969$ National Aerospace Lab.. Amsterdam (Netherlands). cusp had negligible effects on nozzle drag or internal perfor- TRANSONIC WIND TUNNEL TESTS ON AN OSCILLATING mance. Author WING WITH EXTERNAL STORE. PART 4: THE WING WITH UNDERWING: STORE Final Report, Feb. 1977 - N81-14973*# National Aeronautics and Space Administration. Sep. 1979 Langley Research Center. Hampton. Va. H. Tijdeman, J. W. G vanNunen, A. N. Draan, A. J. Persoon, R. BIBLIOGRAPHY OF SUPERSONIC CRUISE RESEARCH Poestkoke, R. Roos, P. Schnippers. and C M Siebert Wright- (SCR) PROGRAM FROM 1977 TO MID-1980 Parterson AFB. Ohio AFFDL Sep. 1979 178 p refs Sherwood Hoffman Dec. 1980 106 p (Grant AF-AFOSR-3233-77) (NASA-RP-1063; L-13764) Avail: NTIS HC A06/MF A01 (AD-A077370: AFFD L-TR-78-194-PI-4; NLR-TR-78106-U) CSCL 01A Avail: NTIS HCA09/MFA01 CSCL01A The supersonic cruise research (SCR) program, initiated in Detailed steady and unsteady pressure distributions were July 1972, includes system studies and the following disciplines: obtained over the wing, while on the store total aerodynamic propulsion, stratospheric emission impact, structures and materials, loads were measured. The tests covered the Mach number range aerodynamic performance, and stability and control. In a between Ma = 0.6 and Ma = 1.35, and reduced frequencies coordinated effort to provide a sound basis for any future ranging up to k = 0.4 at Ma = 0.6 and to k = 02 at Ma = consideration that may be given by the United States to the 1.35. Emphasis was put on the influence of the pylon and store development of an acceptable commercial supersonic transport, on the wing loading and further on the loads acting on the integration of the technical disciplines was undertaken, analytical pylon and store itself. A comparison is presented of experimen- tools were developed, and wind tunnel, flight, and laboratory tal data and theoretical results obtained with the unsteady NLRI investigations were conducted. The present bibliography covers and Doublet Lattice methods. T.M. the time period from 1977 to mid-1980. It is arranged according to system studies and the above five SCR disciplines. There are N81-14970*# Boeing Commercial Airplane Co., Seattle, Wash. 306 NASA reports and 135 articles, meeting papers, and company A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSIS reports cited. E.D.K. OF SUPERSONIC AIRCRAFT. PART 1: GENERAL DESCRIPTION AND THEORETICAL DEVELOPMENT Final N81-14974*# National Aeronautics and Space Administration. Report. Sep. 1978 - Aug. 1980 Langley Research Center. Hampton, Va. W. D. Middleton and J. L. Lundry Washington NASA Dec. LEADING-EDGE DEFLECTION OPTIMIZATION FOR A 1980 101 p refs HIGHLY SWEPT ARROW WING CONFIGURATION (Contract NAS1-15534) Paul L. Coe, Jr.. Jarrett K. Huffman, and James W. Fenbert (NASA-CR-3351; 06-41840-1) Avail: NTIS Dec. 1980 59 p refs HC A06/MF A01 CSCL 01A (NASA-TP-1777; L-13820) Avail: NTIS HC A04/MF A01 An integrated system of computer programs was developed CSCL 01A for the design and analysis of supersonic configurations. The Tests were also conducted to determine the sensitivity of system uses linearized theory methods for the calculation of the lateral stability derivative C sub I sub beta to geometric surface pressures and supersonic area rule concepts in combination anhedral. The optimized leading edge deflection was developed 139 N81-14975 by aligning the leading edge with the incoming flow along the J J. Adamczyk. W. Stevens, and R. Jutras (GE Co.. Evendale. entire span. Owing to the spanwise variation of upwash, the Ohio) 1981 15 p refs Proposed for presentation at 26th resulting optimized leading edge was a smooth, continuously Ann. Intern. Gas Turbine Conf.. Houston, 8-12 Mar. 1981: warped surface. For the particular configuration studied, levels sponsored by Am. Soc. of Mech. Engr. of leading edge suction on the order of 90 percent were achieved (NASA-TM-81613: E-612) Avail: NTIS HC A02/MF A01 CSCL with the smooth, continuously warped leading edge contour. The 01A results of tests conducted to determine the sensitivity of C sub An analytical model is developed.for predicting the onset of I sub beta to geometric anhedral indicate values of delta C sub supersonic stall bending flutter in axial flow compressors. The I sub beta/delta T which are in reasonable agreement with analysis is based on a modified two dimensional, compressible, estimates provided by simple vortex lattice theories. T.M. unsteady actuator disk theory. It is applied to a rotor blade row by considering a cascade of airfoils whose geometry and dynamic N81-14975*# National Aeronautics and Space Administration. response coincide with those of a rotor blade element at Langley Research Center. Hampton. Va. 85 percent of the span height (measured from the hub). The WIND-TUNNEL MEASUREMENTS AND COMPARISON rotor blades are assumed to be unshrouded (i.e., free standing) WITH FLIGHT OF THE BOUNDARY LAYER AND HEAT and to vibrate in thejr first flexural mode. The effects of shock TRANSFER ON A HOLLOW CYLINDER AT MACH 3 waves and flow separation are included in the model through Robert L. Stallings. Jr.. and Milton Lamb Dec. 1980 48 p quasi-steady, empirical, rotor total-pressure-loss and deviation- refs angle correlations. The actuator disk model predicts the unsteady (NASA-TP-1789; L-14044) Avail: NTIS HC A03/MF A01 aerodynamic force acting on the cascade blading as a function CSCL 01A of the steady flow field entering the. cascade and the geometry The wind tunnel tests were conducted both with and without and dynamic response of the cascade. Calculations show that boundary layer trips at Mach 3 and nominal free stream Reynolds the present model predicts the existence of a bending flutter numbers per meter ranging from 3.3 x 10 the 6th power. mode at supersonic inlet Mach numbers. This flutter mode is Instrumentation consisted of pressure orifices, thermocouples, a suppressed by increasing the reduced frequency of the system boundary layer pilot pressure rake, and a floating element skin or by reducing the steady state aerodynamic loading on the friction balance. Measurements from both wind tunnel and flight cascade. The validity of the model for predicting flutter is were compared with existing engineering prediction methods. demonstrated by correlating the measured flutter boundary of a T.M. high speed fan stage with its predicted boundary. This correlation uses a level of damping for the blade row (i.e.. the log decrement of the rotor system) that is estimated from the experimental N81-14976*# Detroit Diesel Allison. Indianapolis. Ind. flutter data. The predicted flutter boundary is shown to be in EXPERIMENTAL DETERMINATION OF UNSTEADY BLADE good agreement with the measured boundary. Author ELEMENT AERODYNAMICS IN CASCADES. VOLUME 2: TRANSLATION MODE CASCADE Final Report R. E. Riffel and M. D. Rothrock Dec. 1980 183 p refs N81-14979*# National Aeronautics and Space Administration. (Contract NAS3-20055) Lewis Research Center. Cleveland. Ohio. (NASA-CR-165166: EDR-10361-Vol-2) Avail: NTIS SOLUTION OF PLANE CASCADE FLOW USING IMPROVED HC A09/MF A01 CSCL 01A SURFACE SINGULARITY METHODS A two dimensional cascade of harmonically oscillating airfoils Eric R. McFarland 1981 14 p refs Presented for presentation was designed to model a near tip section from a rotor which at 26th Ann. Intern. Gas Turbine Conf., Houston 8-12 Mar. was known to have experienced supersonic translational model 1981: sponsored by Am. Soc. of Mech. Engr. flutter. This five bladed cascade had a solidity of 1.52 and a (NASA-TM-81589: E-568) Avail: NTIS HC A02/MF A01 CSCL setting angle of 0.90 rad. Unique graphite epoxy airfoils were 01A fabricated to achieve the realistic high reduced frequency level A solution method was developed for calculating compressible of 0.15. The cascade was tested over a range of static pressure inviscid flow through a linear cascade of arbitrary blade shapes. ratios approximating the blade element operating conditions of The method uses advanced surface singularity formulations which were adapted from those in current external flow analyses. The the rotor along a constant speed line which penetrated the flutter resulting solution technique provides a fast flexible calculation boundary. The time steady and time unsteady flow field for flows through turbomachinery blade rows. The solution method surrounding the center cascade airfoil were investigated. Author and some examples of the method's capabilities are presented. Author N81-14977*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland. Ohio. N81-14980*# National Aeronautics and Space Administration. FINITE ELEMENT ANALYSIS OF INVISCID SUBSONIC Lewis Research Center. Cleveland. Ohio. BOATTAIL FLOW FULL POTENTIAL SOLUTION OF TRANSONIC QUASI 3D R. V. Chima and P. M. Gerhart (Akron Univ.. Ohio) 1981 16 p FLOW THROUGH A CASCADE USING ARTIFICIAL refs Presented at the Nineteenth Aerospace Sci. Meeting. COMPRESSABILITY St. Louis. 12-15 Jan. 1981: sponsored by Am. Inst. of Aeronautics C. Farrell and J. Adamczyk 1981 40 p refs Presented at and Astronautics 26th Ann. Intern. Gas Turbine Conf.. Houston. Tex.. 8-12 Mar. (NASA-TM-81650: E-651) Avail: NTIS HC A02/MF A01 CSCL 1981: sponsored by ASME 01A (NASA-TM-81637: E-574) Avail: NTIS HC A03/MF A01 CSCL A finite element code for analysis of inviscid subsonic flows 01A over arbitrary nonlifting planar or axisymmetric bodies is described. The three-dimensional flow in a turbomachinery blade row The code solves a novel primitive variable formulation of the was approximated by correcting for streamtube convergence and coupled irrotationality and compressible continuity equations. radius change in the throughflow direction. The method is a Results for now over a cylinder, a sphere, and a NACA 0012 airfoil fully conservative solution of the full potential equation incorpora- verify the code. Computed subcritical flows over an axisymmetric ting the finite volume technique on body fitted periodic mesh, boattailed afterbody compare well with finite difference results with an artificial density imposed in the transonic region to insure and experimental data. Interative coupling with an integral stability and the capture of shock waves. Comparison of results turbulent boundary layer code shows strong viscous effects on for several supercritical blades shows good agreement with their the inviscid flow. Improvements in code efficiency and exten- hodograph solutions. Other calculations for these profiles as well sions to transonic flows are discussed. Author as standard NACA blade sections indicate that this is a useful scheme analyzing both the design and off-design performance of turbomachinery blading. T.M. N81-14978*$ National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. N81-14981*# National Aeronautics and Space Administration. SUPERSONIC STALL FLUTTER OF HIGH SPEED FANS Ames Research Center. Moffett Field, Calif 140 N81-14989 EXPERIMENTAL AERODYNAMIC CHARACTERISTICS OF Bo C. A. Johansson 17 Sep. 1980 51 p refs TWO V/STOL FIGHTER/ATTACK AIRCRAFT CONFIGURA- (Contract NE-5061-013) TIONS AT MACH NUMBERS FROM 0.4 TO 1.4 (FFA-TN-HU-2189-pt-3: ISSN-0081-5640: FFA-133) Avail: Walter P. Nelms. Donald A. Durston. and J. R. Lummus (General NTIS HC A04/MF A01 Dynamics. Fort Worth. Tex.) Dec. 1980 529 p refs The turbine was approximated by a disk area of continuous (NASA-TM-81234: A-8338) Avail: NTIS HC A23/MF A01 distributions of thrust and force parallel to the disk plane. Its CSCL 01A wake was represented by a semi-infinite cylinder of distributed A wind tunnel test was conducted to measure the aerodynamic vorticity. A numerical example was calculated. The theory is characteristics of two horizontal attitude takeoff and landing based upon assumptions strictly valid only for small perturbations V/STOL fighter/attack aircraft concepts. In one concept, a jet of the undisturbed flow. However, the results may have a wider diffuser ejector was used for the vertical lift system: the other range of applicability. T.M. used a remote augmentation lift system (RALS). Wind tunnel tests to investigate the aerodynamic uncertainties and to establish a data base for these types of concepts were conducted over a Mach number range from 0.2 to 2.0. The present report covers N81-14986# Flow Research. Inc.. Los Angeles, Calif. tests, conducted in the 1 1 foot transonic wind tunnel, for Mach DEVELOPMENT OF FINITE-VOLUME METHODS FOR numbers from 0.4 to 1.4. Detailed effects of varying the angle THREE-DIMENSIONAL TRANSONIC FLOWS of attack (up to 27 deg). angle of sideslip (-4 deg to +8 deg). John E. Mercer. Wen-Huei Jou. David A. Caughey. Anthony Mach number. Reynolds number, and configuration buildup were Jameson, and David Nixon Aug. 1980 110 p refs investigated. In addition, the effects of wing trailing edge flap (Contract N00014-78-C-0079) deflections, canard incidence, and vertical tail deflections were (AD-A090829: FLOW-RR-166) Avail: NTIS explored. Variable canard longitudinal location and different shapes HC A06/MF A01 CSCL 20/4 of the inboard nacelle body strakes were also investigated. This report covers the Phase II progress in a two phase E.D.K. effort to develop the full potential finite volume algorithm for transonic flow over wing-body configurations. The work in- N81-14983# National Aerospace Lab. Tokyo (Japan). cluded investigations of grid-generation schemes, extension of A METHOD FOR OBTAINING SHOCKLESS TRANSONIC the wing-body code to more complex configurations, and the FLOWS PAST AIRFOILS. PARTIALLY MODIFIED FROM A effects of vortex wake modeling. The wing-body code was used GIVEN ARBITRARY AIRFOIL to analyze a computer designed military aircraft wing which had Masayoshi Nakamura Aug. 1980 25 p refs been wind tunnel tested. Computed results agree quite well with (NAL-TR-602T) Avail: NTIS HC A02/MF A01 the experimental data. A second test case was also run for a A method for obtaining shockless transonic flows past two business jet aircraft. Unfortunately, experimental data for the dimensional airfoils is described. The methods of calculations of test case were not available for comparison. GRA transonic flows are roughly classified into two groups: the direct method, which yields the transonic flows past given arbitrary N81-14987# National Transportation Safety Board. Washington, airfoils: and the inverse method, which determines shapes of D. C. Bureau of Technology. airfoils. In the former method, tne shock waves normally exist BRIEFS OF ACCIDENTS INVOLVING COMMUTER AIR in the region of transonic flows, and some numerical methods CARRIERS AND ON-DEMAND AIR TAXI OPERATIONS. U.S. are already known. In the latter, transonic flows with given pressure GENERAL AVIATION 1978 distribution are calculated, and several analytical methods also 5 Aug. 1980 193 p exist. The method described is a combination of the direct (PB81-101701: NTSB-AMM-80-11) Avail: NTIS method yield, the shockless transonic flows past airfoils which HC A09/MF A01 CSCL 01B are partially modified from a given arbitrary airfoil. If one puts Included are 55 commuter air carrier and 216 on demand an arbitrary airfoil into a region of free stream flows with a air taxi accident briefs. The brief format presents the facts, comparatively large free stream Mach number, the shock waves conditions, circumstances and probable cause(s) for each accident. generally exist. R.C.T. Additional statistical information is tabulated by type of operation, N81-14984# National Aerospace Lab., Tokyo (Japan). injuries, aircraft weight, and causes(s) and related factor(s). T.M. AN INVESTIGATION OF SUPPORT-INTERFERENCE EFFECTS N81-14988# National Transportation Safety Board, Washington, Noboru Hashimoto, Koichi Hozumi, Tadao Koyama, Akira D. C. Bureau of Accident Investigation. Yoshizawa, and Takashi Matsuzaki Aug. 1980 28 p refs In COMMUTER AIRLINE SAFETY Special Study. 1970 - ENGLISH and JAPANESE 1979 (NAL-TR-622) Avail: NTIS HC A03/MF A01 22 Jul. 1980 53 p refs Base pressure and pressure distribution on the sting surface (PB81-104267: NTSB-AAS-80-1) Avail: NTIS in the flow having a free stream Mach number of 7.1 and a HC A04/MF A01 CSCL 01 B free stream Reynolds number based on the unit length from A review of the predominant safety issues which effect the 0.2 x 10 to the 5th power to 2.0 to x 10 to the 5th power/cm commuter airline industry and a review of the relationship of were measured. The oil flow observation on the sting surface the Federal regulations to the commuter airlines are presented. was made at the same time. Avoiding the strong base pressure The Safety Board developed the basis of the study from its rise caused by the effect of strut, the sting flare corner effect 1972 special study of air taxis, the Board's accident statistics, was investigated. The experimental results showed that the base and accident investigation experience and from an extensive field pressure depends upon the Reynolds number and is affected by survey. The operational maintenance, training, and regulatory areas the interaction of the base recirculating flow and the separated of the industry are discussed and safety deficiencies are analyzed. flow around the sting flare corner. This effect of the sting flare A number of safety recommendations to the FAA designed to corner becomes smaller as the length of the sting increases enhance the commuter airline industry are presented. T.M. and the standard length of a sting which has a sufficiently minimal effect on the base pressure was obtained. In order to predict N81-14989*# Ohio Univ.. Athens. Avionics Engineering the base pressure of the sting mounted models, the correlation Center. of the base pressure with local flow properties, immediately DC-TO-DC POWER SUPPLY FOR LIGHT AIRCRAFT FLIGHT preceding the base, is discussed for those cases where there is TESTING little effect from the sting flare and strut. T.M. Stephen R. Yost Dec. 1980 7 p ref (Grant NGR-39-009-017) N81-14985# Aeronautical Research Inst. of Sweden. Stockholm. (NASA-CR-163850: TM-76) Avail: NTIS HC A02/MF A01 Structures Dept. CSCL 17G THE VELOCITY INDUCED BY THE WAKE OF A WIND The power supply unit was developed to serve as the power TURBINE IN A SHEAR LAYER. INCLUDING GROUND source for a Loran-C receiver.The power supply can be connected EFFECT directly to the aircraft's electrical system, and is compatible with 141 N81-14991 either 14 or 28 volt electrical systems. Design specifications N81-14994*# Lockheed-Georgia Co.. Marietta. are presented for the unit along with a description of the circuit ADVANCED FLIGHT DECK/CREW STATION SIMULATOR design. T.M. FUNCTIONAL REQUIREMENTS Final Report. Oct. 1979 - Feb. 1980 R. L. Wall. J. L. Tate, and M. J. Moss Dec. 1980 145 p N81-14991*# California Polytechnic State Univ.. San Luis refs Obispo. (Contract NAS1-15546) FLIGHT EVALUATION OF THE TERMINAL GUIDANCE (NASA-CR-159331: LG80ER0035) Avail: NTIS SYSTEM HC A07/MF A01 CSCL 01C Doral R. Sandlin 1981 65 p refs This report documents a study of flight deck/crew system (Grant NsG-4022) research facility requirements for investigating issues involved (NASA-CR-163859) Avail: NTIS HC A04/MF A01 CSCL with developing systems, and procedures for interfacing transport 17G aircraft with air traffic control systems planned for 1985 to 2000. The terminal guidance system (TGS) is avionic equipment Crew system needs of NASA, the U.S. Air Force, and industry which gives guidance along a curved descending flight path to were investigated and reported. A matrix of these is included, a landing. A Cessna 182 was used as the test aircraft and the as are recommended functional requirements and design criteria TGS was installed and connected to the altimeter. DME. RMI. for simulation facilities in which to conduct this research. Methods and gyro compass. Approaches were flown by three different of exploiting the commonality and similarity in facilities are pilots. When the aircraft arrives at the termination point, it is identified, and plans for exploiting this in order to reduce set up on final approach for a landing. The TGS provides guidance implementation costs and allow efficient transfer of experiments for curved descending approaches with guideslopes of 6 deg from one facility to another are presented. Author which required, for experienced pilots, workloads that are approximately the same as for an ILS. The glideslope is difficult N81-14995# Oak Ridge Y-12 Plant. Tenn. to track within 1/2 n.m. of the VOR/DME station. The system F-111 WINDSCREEN MACHINING Final Report permits, for experienced pilots, satisfactory approaches with a H. L. Gerth and R. J. Brown 22 Sep. 1980 22 p refs turn radius as low as 1/2 n.m. and a glideslope of 6 deg. Turn (Contract W-7405-eng-26) angles have little relation to pilot workload for curved approaches. (Y-2232) Avail: NTIS HC A02/MF A01 Pilot experience is a factor for curved approaches. Pilots with The feasibility of improving the optical image transmitted low instrument time have difficulty flying steep approaches with through a military aircraft windscreen by using single-point small turn radius. Turbulence increases the pilot workload for diamond turning is studied. Reduced warpage (waviness) of the curved approaches. The TGS does not correct to a given flight windscreen surfaces ensures that a more accurate optical image path over the ground nor does it adequately compensate for is presented to the aircraft pilot. Machining the acrylic surface wind drift. E.D.K. was accomplished with slightly impared image transmissibility. The use of this technique as a potential production process is discussed. DOE N81-14992# Deutsche Forschungs- und Versuchsanstalt flier Luft- und Raumfahrt. Brunswick (West Germany). Abteilung N81-14996*# New Mexico Univ.. Albuquerque. Technology Flugzeugsteuerung und -Regelung. Application Center APPLICATEO TECHNIQUES FOR THE CONTROL OF REMOTELY PILOTED VEHICLES. CITATIONS FROM THE APPROACH TRAFFIC INTERNATIONAL AEROSPACE ABSTRACTS DATA BASE Albrecht Seyfried (Tech. Univ.. Brunswick), Manfred Schubert. Progress Report, 1974 - Jul. 1980 and Uwe Voelckers (Tech. Univ.. Brunswick) Oct. 1979 31 p Samuel C. Mauk Sep. 1980 59 p Supersedes NTIS/PS-79/ refs In GERMAN; ENGLISH summary Report will also be 0875/9 Sponsored in part by NASA and NTIS announced as translation (ESA-TT-668) (NASA-CR-163864; NTIS/PS-79/0875/9: PB80-815921) (DFVLR-Mitt-79-20) Avail: NTIS HC A02/MF A01 Avail: NTIS HC S30.00/MF $30.00 CSCL01C The achievement of a regular distributed aircraft arrival rate These citations from the international literature cover various at the TM borders and the smooth integration of different flows aspects of remotely piloted vehicles. Included are articles of traffic are the main objects of flow control in the approach concerning aircraft design, flight tests, aircraft control, cost area. With respect to these goals some fundamental flow control effectiveness, automatic flight control, automatic pilots, and data measures normally being applied in a selected near terminal links. Civil aviation applications are included, although military area were investigated by the analysis of real traffic recordings uses of remotely piloted vehicles are stressed. This updated as well as by controller interviews. The effects of certain flow bibliography contains 224 citations. 43 of which are new additions control principles on the entry and exit distribution and on the to the previous edition. GRA further evolution of traffic within the TMA are explained. Finally it is discussed to which degree such different flow control techniques should be considered in a future computer assisted N81-14997*# National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. ATC system. Author SIMULATOR STUDY OF CONVENTIONAL GENERAL AVIATION INSTRUMENT DISPLAYS IN PATH-FOLLOWING TASKS WITH EMPHASIS ON PILOT-INDUCED OSCILLA- N81-14993*# Lockheed-Georgia Co.. Marietta. TIONS A SURVEY OF NEW TECHNOLOGY FOR COCKPIT APPLICA- James J. Adams Dec. 1980 55 p refs TION TO 1990'S TRANSPORT AIRCRAFT SIMULATORS (NASA-TP-1776: L-13785) Avail: NTIS HC A04/MF A01 Final Report. Jul. 1979 - Jan. 1980 CSCL 01D A. P. Holt. Jr.. D. 0. Noneaker. and L Walthour Dec. 1980 A study of the use of conventional general aviation instruments 118 p refs by general aviation pilots in a six degree of freedom, fixed base (Contract NAS1-15546) simulator was conducted. The tasks performed were tracking a (NASA-CR-159330: LG81ER0074) Avail: NTIS VOR radial and making an ILS approach to landing. A special HC A06/MF A01 CSCL 01C feature of the tests was that the sensitivity of the displacement Two problems were investigated: inter-equipment data indicating instruments (the RMI. CDI. and HSI) was kept transfer, both on board the aircraft and between air and ground: constant at values corresponding to 5 n. mi. and 1.25 n. mi. and crew equipment communication via the cockpit displays and from the station. Both statistical and pilot model analyses of controls. Inter-equipment data transfer is discussed in terms of the data were made. The results show that performance in path data bus and data link requirements. Crew equipment communica- following improved with increases in display sensitivity up to tion is discussed regarding the availability of CRT display systems the highest sensitivity tested. At this maximum test sensitivity, for use in research simulators to represent flat panel displays of which corresponds to the sensitivity existing at 1.25 n. mi. for the future, and of software controllable touch panels. T.M. the ILS glide slope transmitter, tracking accuracy was no better 142 N81-15005 than it was at 5 n. mi. from the station and the pilot aircraft N81 15001*# Purdue Univ.. Lafayette. Ind. School of system exhibited a marked reduction in damping. In some cases, Mechanical Engineering. a pilot induced, long period unstable oscillation occurred. Author APPLICATION OF THE MNA DESIGN METHOD TO A NONLINEAR TURBOFAN ENGINE Final Report Gary Leininger Jan. 1981 107 p ref-; N81-14998* Beam Engineering. Inc.. Sunnyvale. Calif. (Grant NsG-3171) STATIC SOURCE LOCATIONS FOR FOUR NOZZLES (NASA-CR-163855) Avail: NTIS HC A06/MF A01 CSCL MOUNTED ON A J 85 ENGINE Final Report 21E Leif E. Hoglund Jan. 1979 236 p refs Using nonlinear digital simulation as a representative model (Contract NAS2-9399) of the dynamic operation of the QCSEE turbofan engine, a feedback (NASA-CR-152401) Avail: NASA. Ames Research Center control system is designed by variable frequency design tech- CSCL 21E niques. Transfer functions are generated for each of five power The test nozzles included a round 17.5 in. diameter variable level settings covering the range of operation from approach flap ejector (VFE) nozzle, a round 'stovepipe' nozzle, and a power to full throttle (62.5% to 100% full power). These transfer 104 tube suppressor nozzle operated both with and without an functions are then used by an interactive control system design ejector shroud. The velocities tested ranged from 600 to 1600 synthesis program to provide a closed loop feedback control fps at an approximate total temperature of 1400 R. The axial using the multivariable Nyquist array and extensions to multivari- position of the noise sources during static operation was able Bode diagrams and Nichols charts. A.R.H. determined by jet velocity. Strouhal number, and direction of propagation. The velocity dependence was more evident for the 104 tube suppressor nozzle than for the conical nozzles tested. N81-15003*# Spectron Development Labs.. Inc.. Costa Mesa. The results for both the VFE conical nozzle and the stovepipe Calif. conical nozzle indicate source locations to be much closer to FUEL INJECTOR CHARACTERIZATION STUDIES Final the jet exit plane than expected. Corrections for near field effects Report were found to differ slightly for each nozzle tested. The corrections Michael J. Houser and William D. Bachalo Oct. 1980 54 p presented are simply the differences between the measured refs near field levels and the required near field levels if spherics! (Contract NAS3-21288) spreading is assumed from source to far field. Author (NASA-CR-165200; SDL-80-2122-13F) Avail: NTIS HC A04/MF A01 CSCL 21E N81-14999* National Aeronautics and Space Administration. The atomization of several general aviation piston engine Lewis Research Center. Cleveland, Ohio. manifold port fuel injectors was investigated The injectors were CURVED CENTERLINE AIR INTAKE FOR A GAS TURBINE installed in a test rig and operated under simulated conditions. ENGINE Patent Laser interferometric techniques were used to optically probe William C. Ruehr (GE. Cincinnati). James L Younghans (GE. the spray droplet fields for droplet size and velocity at numerous Cincinnati), and Edwin B. Smilh. inventors (to NASA) (GE. spatial locations throughout the field. R.C.T. Cincinnati) Issued 2 Sep. 1980 6 p Filed 14 May 1979 Sponsored by NASA N81-150O4*# General Electric Co.. Cincinnati. Ohio. Aircraft (NASA-Case-LEW-13201-1; US-Patent-4.220.171; Engine Group US-Patent-Appl-SN-038980; US-Patent-Class-137-15.1: AERODYNAMIC STABILITY ANALYSIS OF NASA J85-13/ US-Patent-Class-181-214) Avail: US Patent and Trademark PLANAR PRESSURE PULSE GENERATOR INSTALLATION Office CSCL 21E K Chung. W. M. Hosny. and W. G Steenken Nov. 1980 An inlet for a gas turbine engine was disposed about a 168 p refs curved centerline for the purpose of accepting intake air that is (Contract NAS3-21259) flowing at an angle to engine centerline and progressively turning (NASA-CR-165141; R80AEG429) Avail: NTIS that intake airflow along a curved path into alignment with the HC A08/MF A01 CSCL 21E engine. This curved inlet is intended for use in under the wing A digital computer simulation model for the J85-13/Planar locations and similar regions where airflow direction is altered Pressure Pulse Generator (P3 G) test installation was developed by aerodynamic characteristics of the airplane. By curving the by modifying an existing General Electric compression system inlet, aerodynamic loss and acoustic generation and emission model. This modification included the incorporation of a novel are decreased. method for describing the unsteady blade lift force This approach Official Gazette of the U.S. Patent and Trademark Office significantly enhanced the capability of the model to handle unsteady flows. In addition, the frequency response characteristics of the J85-13/P3G test installation were analyzed in support of selecting instrumentation locations to avoid standing wave nodes N81-150OO*# National Aeronautics and Space Administration within the test apparatus and thus, low signal levels. The feasibility Hugh L. Dryden Flight Research Center, Edwards, Calif. of employing explicit analytical expression for surge prediction FLIGHT EVALUATION OF A SIMPLIFIED GROSS THRUST was also studied. J.M.S. CALCULATION TECHNIQUE USING AN FIDO TURBOFAN ENGINE IN AN F 15 AIRPLANE Frank J. Kurtenbach and Frank W. Burcham. Jr. Jan. 1981 N81-150O5*# General Electric Co.. Cincinnati. Ohio. Aircraft 21 p refs Engine Group. (NASA-TP-1782: H-1118) Avail: NTIS HC A02/MF A01 CSCL TF34 ENGINE COMPRESSION SYSTEM COMPUTER 21E STUDY A simplified gross thrust calculation technique was evaluated W. M. Hosny and W. G. Steenken Jun. 1979 93 p refs in flight tests on an F-15 aircraft using prototype F100-PW-100 (Contract NAS3-20599) engines. The technique relies on afterburner duct pressure (NASA-CR-159889: R78AEG612) Avail: NTIS measurements and empirical corrections to an ideal one- HC A05/MF A01 CSCL 21E dimensional analysis to determine thrust. In-flight gross thrust The stability of the fan and the compressor components calculated by the simplified method is compared to gross thrust was examined individually using linearized and time dependent, calculated by the engine manufacturer's gas generator model. one dimensional stability analysis techniques. The stability of The evaluation was conducted at Mach numbers from 0.6 to the fan core integrated compression system was investigated 1.5 and at altitudes from 6000 meters to 13.700 meters. The using a two dimensional compression system model. The flight evaluation shows that the simplified gross thrust method analytical equations on which this model was based satisfied and the gas generator method agreed within plus or minus the mass, axial momentum, radial momentum, and energy 3 percent. The discrepancies between the data generally fell conservation equations for flow through a finite control volume. within an uncertainty band derived from instrumentation errors The results gave an accurate simulation of the flow through the and recording system resolution. A.R.H. compression system. The speed lines of the components were 143 N81-15006 reproduced: the points of instability were accurately predicted: G. Dallemagne Paris 16 Sep. 1980 18 p refs In FRENCH the locations where the instability was initiated in the fan and Presented at 4eme Journees du Vieillissement des Polymeres, the core were indicated: and the variation of the bypass ratio Station de Bandol, 19 Sep. 1980 during flow throttling was calculated. The validity of the (SNIAS-801-551-107) Avail: NTIS HC A02/MF A01 analytical techniques was then established by comparing these Various paints, pigments, and varnishes were studied to results with test data and with results obtained from the steady determine their effectiveness in protecting JPI/H20 against state cycle deck. J.M.S. biocontamination by Cladiosporium resinae. In order of decreasing resistance, they were found to be: (1) PU: a varnish polymerized at 60 C and promers inhibited by ZnCr04 and SrCr04: (2) a N81-15OO6*# Pratt and Whitney Aircraft Group. East Hartford. cured epoxy/amine primer, inhibited by BaCrO4: and Conn. Commercial Products Div. (3) epoxide/amide and epoxide/amme-amide primers inhibited COST/BENEFIT ANALYSIS OF ADVANCED MATERIALS by SrCr04. Of the systems examined, it is advisable not to use TECHNOLOGIES FOR FUTURE AIRCRAFT TURBINE NBR varnish, with and without inhibitors, and epoxide/amine- ENGINES Final Report amide primers inhibited by BaCr04 in biodeteriorating milieu. G. E. Stephens Aug. 1980 49 p refs Transl. by A.R.H. (Contract NAS3-20072) (NASA-CR-165225: PWA-5755) Avail: NTIS N81-15148# Mason and Hanger-Silas Mason Co., Inc.. Amarillo. HC A03/MF A01 CSCL 21E Tex. Development Div. The materials technologies studied included thermal barrier TOOL FORCE EVALUATION OF LATHE MACHINED HIGH coatings for turbine airfoils, turbine disks, cases, turbine vanes EXPLOSIVES and engine and nacelle composite materials. The cost/benefit of Gary L. Flowers Apr. 1980 44 p each technology was determined in terms of Relative Value defined (Contract DE-AC04-76DP-00487) as change in return on investment times probability of success (MHSMP-80-20: Endeavor-302) Avail: NTIS divided by development cost. A recommended final ranking of HC A03/MF A01 technologies was based primarily on consideration of Relative A procedure to determine the effects of machining properties Values with secondary consideration given to changes in other upon tool forces encountered during lathe machining of high economic parameters. Technologies showing the most promising explosives is evaluated. Transducers fit between the tool holder cost/benefits were thermal barrier coated temperature nacelle/ and the tool post and interface to existing signal conditioners. engine system composites. T.M. All forces on the cutter were evaluated during machining of two types of high explosives at four cutter radii, four feed rates, N81-150O7# Texas Univ. at Arlington.. Dept. of Aerospace three depths of cut. and two cutting speeds Findings indicate Engineering. that the transducer design is inadequate to allow accurate force A PURE DIRECT FORCE/MOMENT CONTROL FOR vector separation at all reasonable attack angles. Problems COAXIAL COUNTERROTATING ROTORS concerning instrument drift, tool chatter, and detection levels Aspi Rustom Wadia (AiResearch Mfg. Co.. Phoenix. Ariz.) and ate also found. M G Jack E. Fairchild [1980] 19 p refs Avail: NTIS HC A02/MF A01 A simple first harmonic analysis using Fourier series is N81-15156# Toronto Univ.. Downsview (Ontario). Inst. for presented for the control of rigid coaxial and counterrotating Aerospace Studies. helicopter rotors in hover. It it shown that by a particular HEAVE INSTABILITIES OF AMPHIBIOUS AIR CUSHION combination of cyclic controls on each rotor, pure moments or SUSPENSION SYSTEMS forces can be generated in any direction. Such controls could M. J. Hinchey Nov. 1980 135 p refs Sponsored by Transport give the helicopter maneuvering capabilities not possible in Canada Research and Development Centre and National Research conventional machines. An elementary cockpit control configura- Council of Canada tion is suggested to implement the control strategy. E.D.K. (UTIAS-246: ISSN-0082-5255) Avail: NTIS HC A07/MF A01 Attempts to ascertain the accuracy with which analytical N81-15009$ Royal Aircraft Establishment. Farnborough (England). Structures Dept. models can be used to predict the onset of heave instabilities THE RESONANCE FREQUENCIES OF VENTILATED WIND are described with emphasis on relatively simple configurations TUNNELS in which important effects are uncoupled. For the basic element 0. G. Ma bey London Apr. 1978 52 p refs Supersedes of multicell systems, even relatively short supply ducting can RAE-TR-78038: ARC-37974 have a very large effect, especially at low flows or hover-gaps (ARC-R/M-3841: BR73233: RAE-TR-78038: ARC-37974) where the duct-cushion system tends to behave as a Helmholtz Avail: NTIS HC A04/MF A01: HMSO £8 PHI resonator. For loop and segment systems, it is concluded that Experiments suggest that the theory widely used to predict duct effects would be small. Internal flow effects associated the transverse resonance frequencies in slotted tunnels is in error with jets and vortices within the basic cushion volume are shown in the Mach number range from 0 to 0.5. One reason for the to be relatively unimportant at practical flow rates, although error is that the theory is based on an unrepresentative wall they are important at very high flow rates. Nonlinear phenomena, boundary condition. Moreover, the theory implies that the plenum and procedures for controlling or quenching limit cycle amplitudes chamber surrounding the working section is large, whereas the are explored. Suggestions for future work are included. A.R.H. plenum chamber depth is generally less than twice the tunnel height. An improved theory was developed, which shows that N81-15310# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- the resonance frequencies of ventilated tunnels are influenced Genese (Belgium). Dept. of Computational Fluid Dynamics. by the depth of the plenum chamber for Mach numbers up to COMPUTATIONAL FLUID DYNAMICS. VOLUME 2 about M = 0.6. Although the theory is approximate, it agrees 1980 380 p refs Lecture held in Rhode-Saint-Genese. Belgium. well with experiments for slotted and perforated walls (with both 24-28 Mar. 1980 2 Vol. normal and 60 deg inclined holes). The results are consistent (VKI-LS-1980-5-Vol-2) Avail: NTIS HC A17/MF A01 with other experiments which show that plenum chamber design Several aspects of computational fluid dynamics are discussed. can influence the flow unsteadiness within the working section Theoretical methods are developed for computing the aerodynamic of a ventilated tunnel. Author flow of aircraft configurations. N81-15072$ Societe Nationale Industrielle Aerospatiale, Suresnes (France). Lab. Centrale. N81-15311# Jenkins (Gwilym) and Partners Ltd.. Lancaster THE RESISTANCE OF TANK PROTECTIVE MEASURES TO (England). MICROORGANISMS [RESISTANCE DES PROTECTIONS AN ECONOMIC AND VERSATILE PANEL METHOD FOR DE FONDS DE RESERVOIRS AUX MICROORGANISMES] AIRCRAFT AND AIRCRAFT/STORE CONFIGURATIONS. 144 N81-15467 AN OUTLINE OF THE PRINCIPAL FEATURES OF THE Experimental transonic flutter results are presented for a MATHEMATICAL MODELING AND NUMERICAL IMPLE- simplified 1/50 size, aspect ratio 1.77. wind tunnel model of MENTATION OF THE BRITISH AEROSPACE (WARTON) an arrow wing design Flutter results are presented for two MK II PANEL METHOD configurations: namely, one with and one without a ventral fin W. G. Semple In Von Kacman Inst. for Fluid Dyn. Computational mounted at the 0.694 semispan station. Results are presented Fluid Dyn.. Vol. 2 1980 70 p refs Prepared in cooperation for both configurations trimmed to zero lift and in a lifting condition with British Aerospace Aircraft Group. Preston, England at angles of attack up to 4 deg. The results show that the flutter characteristics of both configurations are similar to those Avail: NTIS HC A17/MF A01 usually observed. Increasing angle of attack reduces the flutter The principal features of the mathematical modeling and dynamic pressure by a small amount (about 13 percent maximum) numerical implication of the MK 11 panel method are outlined. for both configurations. The addition of the fin to the basic The geometric structure, conventions and terminology of MK11 wing increases the flutter dynamic pressure. Calculated results are given. The method of solution of the linear equations for for both configurations in the nonlifting condition obtained by the source and doublet weights are described. A brief review of using subsonic doublet lattice unsteady aerodynamic theory results from the method is given and the possible avenues of correlate reasonably well with the experimental results. Calculated future development are summarized. R.CT. results for the basic wing obtained by using subsonic kernal function unsteady aerodynamic theory did not agree as well with the experimental data Author N81-15313*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. VORTEX METHODS FOR TWO- AND THREE-DIMENSIONAL N81-15401# Instituut TNO voor Werktuigkundige Constructies. FLOW SIMULATIONS Delft (Netherlands). A. Leonard In Von Karman Inst. for Fluid Dyn. Computational EXPERIMENTAL ANALYSIS AND METHODS TO DETER- Fluid Dyn.. Vol. 2 1980 52 p refs MINE THE DYNAMIC BEHAVIOR OF PROPULSION SHAFTING SYSTEMS Avail: NTIS HC A17/MF A01 L. J. Wevers In Ned. Akoestisch Genootschap Vibration Tech. The point vortex and vortex blob methods for two dimensional Jan. 1980 p 13-35 refs In DUTCH: ENGLISH summary flows are presented. Several results are discussed concerning the numerical analysis of the latter scheme, e.g.. the preservation Avail: NTIS HC A03/Mt- A01 of globally conserved quantities and the analysis of the spatial The dynamic bending properties of propeller shaftings were discretization error resulting from the convection of fixed blobs investigated. Measurements were taken at a full size laboratory of vorticity. An application to the two dimensional mixing layer facility and onboard ships. The aim of the measurements was is briefly described. The contour dynamics method is also to verify the results of a numerical calculation method with a discussed. The simulation of three dimensional flows with vortex finite element program developed to face lateral vibration methods is discussed. A natural way to represent the vorticity problems in an early stage of the design of a ship's propulsion is in the form of closed tubes of filaments of vorticity, although system. R.C.T. other schemes are examined. Applications to aircraft trailing vortices and to a turbulent spot in a laminar boundary layer are presented. Hybrid schemes that use an Eulerian mesh to solve N81-15414# Westinghouse Electric Corp., Concordville, Pa. the Poisson equation for the velocity field are discussed. The Combustion Turbine Systems Div. goal of these schemes is to avoid the high cost of the Biot-Savart COMPRESSOR CONFIGURATION AND DESIGN OPTIMIZA- integration if many vortex elements are used while enjoying most TION FOR THE HIGH RELIABILITY GAS TURBINE Final of the advantages of pure Lagrangian schemes. R.CT. Report R. E. Strong Sep. 1980 128 p refs (Contract DE-AC03-79ET-15332) N81-15362 Texas A&M Univ.. College Station. (OOE/ET-15332/T1) Avail. NTIS HC A07/MF A01 PROBABILISTIC ANALYSIS OF FOUNDATION FORCES FOR An advanced compressor for use in the high reliability A CLASS OF UNBALANCED ROTATING MACHINES combustion turbine engine was investigated. Advanced design Ph.D. Thesis concepts based on low aspect ratio aircraft engine compressor Lola Boyce 1980 105 p technology were utilized to define three compressor configurations Avail: Univ. Microfilms Order No. 8101577 with 11. 13 and 15 stages. The results were applied to The rotor-housing is modeled as a three degree-of-freedom compressors with 14:1 pressure ratio. 800 Ibs/sec (360 kg/sec) system wherein the principal modes of vibration are a vertical airflow and operating at 3600 rpm to match the requirements translation in the direction of the machine supports and a rolling of heavy duty power generation combustion turbine engines. and pitching motion of the rotor. The equations of motion for Typical, front, middle and last stages of these three compressors the system are derived using analytical methods, solved, and were studied to evaluate their aerodynamic and mechanical related to the foundation force. For a selected machine class, feasibility and to determine the influence of the number of stages, all parameters are constant except for rotor mass eccentricity. and stage loadings on their overall efficiency. The 11 stage the distance from the center of mass of the rotating mass to compressor was selected for further mechanical analysis to verify the bearing axis. The deterministic analysis requires the selection its structural constraints and define in greater detail its mechani- of some representative value of eccentricity from the data available cal configuration. Cost of this compressor was estimated for for a number of rotors. The corresponding foundation force is comparison with the present 19 stage high reliability reference calculated. No measure of the error associated with the foundation compressor derived from the Westinghouse W-501 engine. force is available. The probabilistic analysis requires the calculation R.C.T. of the mean value of the foundation force and includes some N81-15467# Stuttgart Univ. (West Germany). Inst. fuer Statik measure for its error. The classical probabilistic method accounts und Dynamik. for foundation force error by employing the propagation of errors ROTOR MODEL FOR VERIFICATION OF COMPUTATION formula to calculate variance. Dissert. Abstr. METHODS [ROTORMODELL ZUR VERIFIZIERUNG VON RECHENVERFAHREN] N81-15397*# National Aeronautics and Space Administration. J. H. Argyris. W. Aicher, F. Karl. W. Kuemmerle. and M. Mueller Langley Research Center. Hampton. Va. 1979 58 p refs In GERMAN: ENGLISH summary EFFECTS OF ANGLE OF ATTACK AND VENTRAL FIN ON (Contract BMFT-ET-4086-A) TRANSONIC FLUTTER CHARACTERISTICS OF AN ARROW- (ISD-262: ISSN-0170-6071) Avail: NTIS HC A04/MF A01 WING CONFIGURATION In order to prove the quality of idealization and the validity Robert V. Doggett and Rodney A. Ricketts Dec. 1980 29 p of computation for windmills, a driven model of a windmill with (NASA-TM-81914: L-14114) Avail: NTIS HC A03/MF A01 a 7.4 m diameter rotor was constructed. New data acquisition CSCL 20K and data transmission systems with 16 channels and digitization 145 N81-15579 in the rotating system were developed and tested. The dynamic (NASA-CR-163863. PB80-815889; NTIS/PS-79/0858/5) response of the rotor blades to the cyclic loading of gravity was Avail: NTIS HC S30.00/MF $30.00 CSCL 04B taken to compare measurements and computations. For the These citations from the international literature describe all measurements and evaluation which were performed by a aspects of clear air turbulence (CAT). Articles covering research measurement system and a computer, the necessary software and analysis, theories and experiments, detection and measure- was built. T.M. ment equipment, simulation modeling, and CAT accidents involving aircraft are included. This updated bibliography contains N81-15579*# National Aeronautics and Space Administration, 237 citations. 116 of which are new additions to the previous Washington. D. C. edition. GRA THE ANNOYANCE CAUSED BY NOISE AROUND AIRPORTS Final Report Josse Jul. 1980 114 p refs Transl. into ENGLISH of "la N81-16702*# Duke Univ.. Durham. N. C. Dept. of Computer Gene causee par le Bruit Autour des Aeroports" Rept. Sciences. D.G.R.S.T/C.S.T.B.-63-FR-138 Centre Sci. et Tech. du Batiment. VALIDATION METHODS RESEARCH FOR FAULT- Paris. 1 Mar. 1968 p 1-219 Transl. by Scientific Translation TOLERANT AVIONICS AND CONTROL SYSTEMS SUB- Service, Santa Barbara. Calif. WORKING GROUP MEETING. CARE 3 PEER REVIEW (Contract NASw-3198) Kishor S. Trivedi. ed. and James B. Clary, ed. (Research Triangle (NASA-TM-75784; DGRST/CSTB-63-FR-1 38) Avail: NTIS Inst.. Research Triangle Park. N.C.) Dec. 1980 30 p refs HC A06/MF A01 CSCL 13B Meeting held at Research Triangle Park. N.C.. 15-16 Sep. 1980 A comprehensive study of noise around selected airports in (Grant NAG 1-70) France was performed. By use of questionnaires, the degree of (NASA-CP-2167: L-14215) Avail: NTIS HC A03/MF A01 annoyance caused by aircraft noise was determined. Three CSCL 12A approaches used in the study were: (1) analytical study on the A computer aided reliability estimation procedure (CARE 3). influence of noise on sleep: (2) sociological study on the developed to model the behavior of ultrareliable systems required satisfaction of occupants of buildings which conform to laws by flight-critical avionics and control systems, is evaluated. The which are supposed to guarantee sufficient comfort; and mathematical models, numerical method, and fault-tolerant (3) statistical study of correlations between external noises and architecture modeling requirements are examined, and the testing psychological and pathological disturbances in residences. E.O.K. and characterization procedures are discussed. Recommendations aimed at enhancing CARE 3 are presented: in particular, the N81 15580# Toronto Univ., Downsview (Ontario). Inst. for need tor a better exposition of the method and the user interface Aerospace Studies. is emphasized. M.G. AIRCRAFT ANNOYANCE EVALUATIONS USING FIELD AND LABORATORY SIMULATION TECHNIQUES G. W Johnston and A. A. Haasz Dec. 1980 60 p refs N81-16729| Computer Sciences Corp.. Orlando. Fla. Sponsored in part by Transport Canada COMPUTER GENERATED IMAGERY (CGI) CURRENT (UTIAS-248: ISSN-0082-5255) Avail: NTIS TECHNOLOGY AND COST MEASURES FEASIBILITY STUDY HC A04/MF A01 Final Technical Report. 22 Apr. - 26 Sep. 1980 A series of aircraft noise annoyance evaluation tests were Leonard T. Suminski, Jr. and Paul H. Hulin 26 Sep. 1980 performed under controlled conditions in a laboratory. Jurors 189 p refs drawn from nominal 30-35 NEF zones were exposed to aircraft (Contract N61339-79-D-0008) noise events previously recorded near their homes in the vicinity (AD-A091636: CSC/TR-80/6008: PM-TRADE-RE-0012) Avail. of the Toronto International and Oshawa General Aviation Airports. NTIS HC A09/MF A01 CSCL 09/2 Comparison of test results indicates that under optimum simulation The primary purpose of this report is to determine the conditions both Toronto and Oshawa observers consistently rate feasibility of developing a cost/performance, cost estimating model the International Airport noise exposure as considerably more for CGI visual systems. In doing so. vendor surveys were made disturbing/ annoying than that at the General Aviation Airport and an analysis of current and future technology/techniques was sites. The laboratory test results were also compared with conducted. The report makes recommendations for some costing conventional field interview annoyance data obtained for the same efforts to be conducted by PMTRADE. along with recommenda- group of jurors in a previous study conducted by McMaster tions for other efforts. GRA University. Author N81-15768*# National Aeronautics and Space Administration. N81-16648*# New Mexico Univ.. Albuquerque. Technology Lewis Research Center. Cleveland. Ohio. Application Center. ANALYSIS OF PRESSURE SPECTRA MEASUREMENTS IN LIGHTNING. CITATIONS FROM THE INTERNATIONAL A DUCTED COMBUSTION SYSTEM Ph.D. Thesis - Toledo AEROSPACE ABSTRACTS DATA BASE Progress Report, Univ. 1974 - Jul. 1980 Jeffrey Hilton Miles Nov. 1980 138 p refs Samuel C. Mauk Sep. 1980 73 p Supersedes NTIS/PS-79/ (NASA-TM-81583: E-558) Avail. NTIS HC A07/MF A01 CSCL 0832/0 Sponsored in part by NASA and NTIS 20A (NASA-CR-163857: PB80-815947) Copyright. Avail: NTIS Combustion noise propagation in an operating ducted liquid HC S30.00/MF $30.00 CSCL 048 fuel combustion system is studied in relation to the development These citations from the international literature concern of combustion noise prediction and suppression techniques. The various aspects of lightning. Articles covering aircraft hazards, presence of combustor emissions in the duct is proposed as the aircraft safety, radio meteorology, circuit protection, electro- primary mechanism producing the attenuation and dispersion of magnetic pulses, and electromagnetic radiation are included. combustion noise propagating in an operating liquid fuel Articles concerning atmospheric electricity and thunderstorms are combustion system. First, a complex mathematical model for stressed. This updated bibliography contains 304 citations, 95 calculating attenuation and dispersion taking into account mass of which are new additions to be previous edition. GRA transfer, heat transfer, and viscosity effects due to the presence of liquid fuel droplets or solid soot particles is discussed. Next, a simpler single parameter model for calculating pressure N81-15649*# New Mexico Univ., Albuquerque. Technology auto-spectra and cross-spectra which takes into account Application Center. dispersion and attenuation due to heat transfer between solid CLEAN AIR TURBULENCE. CITATIONS FROM THE soot particles and air is developed. Then, auto-spectra and INTERNATIONAL AEROSPACE ABSTRACTS DATA BASE cross-spectra obtained from internal pressure measurements in Progress Report. 1974 - Jul. 1980 a combustion system consisting of a J-47 combustor can, a Samuel C. Mauk Sep. 1980 61 p Supersedes NTIS/PS-79/ spool piece, and a long duct are presented. Last, analytical results 0858/5 Sponsored by NASA and NTIS obtained with the single parameter model are compared with 146 N81 15819 the experimental measurements. The single parameter model results are shown to be in excellent agreement with the measurements. J.M.S. N81-15769*# Pratt and Whitney Aircraft Group. East Hartford. Conn. Commercial Products Div. IMPROVED METHODS FOR FAN SOUND FIELD DETER- MINATION D. E. Cicon. T. G. Sofrin. and D. C. Mathews Jan. 1981 180 p refs (Contract NAS3-21391) (NASA-CR-165188: PWA-5635-43) Avail: NTIS HC A09/MF A01 CSCL 20A Several methods for determining acoustic mode structure in aircraft turbofan engines using wall microphone data were studied. A method for reducing data was devised and implemented which makes the definition of discrete coherent sound fields measured in the presence of engine speed fluctuation more accurate. For the analytical methods, algorithms were developed to define the dominant circumferential modes from full and partial circumferen- tial arrays of microphones. Axial arrays were explored to define mode structure as a function of cutoff ratio, and the use of data taken at several constant speeds was also evaluated in an attempt to reduce instrumentation requirements. Sensitivities of the various methods to microphone density, array size and measurement error were evaluated and results of these studies showed these new methods to be impractical. The data reduction method used to reduce the effects of engine speed variation consisted of an electronic circuit which windowed the data so that signal enhancement could occur only when the speed was within a narrow range. T.M. N81-16819*# Institut Franco-Allemand de Recherches. St Louis (France). APPLICATION OF OPTICAL METHODS TO THE STUDY OF JET NOISE AND TURBULENCE [APPLICATION DES METHODES OPTIQUES, EN PARTICULAR A L'ETUDE DE LA TURBULENCE ET DU BRUIT DES JETS] P. G. Sava and J. Haertig 1 Aug. 1980 16 p refs In FRENCH Presented at Journees sur les Methodes Optiques a la Mecanique des Fluides, Orsay, France. 26-27 Nov. 1979 (ISL-CO-201/80) Avail: NTIS HC A02/MF A01 Optical methods are generally applied in fluid mechaics for either visualization or measurement. The use of a laser anemometer to study flow velocity in a jet and its relaton to the sound • radiated is described. The same acoustic emission phenomenon is also measued by combining the signals from four Schlieren systems with that from an interferometer. The use of an optical Fourier transformation approach with real time analysis to determine the spatio-temporal structure of a field of mass volume such as a waveguide or free jet is also examined. Transl. by A.R.H. 147 SUBJECT INDEX AERONAUTICAL ENGINEERING/M Continuing Bibliography (Suppl. 134) APRIL 1981 Typical Subject Index Listing IIUUHS ACOUSTICS rDe*elopient of advanced interceptor sabstractaral The Dalembertometer •aterial —- graphite epoxy missile stroctnres- [ISL-CO-220/79] H81-14292 [AD-A090127] 181-11116 ADAPTIVE COHTHOl Further investigations of adaptive-wall wind tunnels [AD-A091774] H81-13977 ADHESIVE BOHDIHG REPORT Automatization of the adhesion process for TITU NUMBER supporting airframe parts in light contour systems A81-19297 Surface finishing [HASA-CASE-SSC-12631-3] H81-14077 The title is used to provide a description of the subject matter. When the title is AEEIAL PHOTOGRAPH! insufficiently descriptive of the document content, a title extension is added, Aerial surveying of small areas from a small remotely controlled drone separated from the title by three hyphens. The NASA or AIAA accession number A81-17525 is included in each entry to assist the user in locating the abstract in the abstract Autonomous navigation using passively sensed section of this supplement. If applicable, a report number is also included as an terrain images aid in identifying the document. A81-17977 ABROACOOSIICS Hoise and noise abatement in fans and blowers: A review [DFVLR-FB-80-16] H81-14796 Analysis of pressure spectra measurements in a A-6 AIRCRAFT ducted combustion system Circulation Control iing /CCB/ flight tests [HASA-Tn-81583] H81-15768 181-19469 AEBODIHAHIC CHARACTERISTICS 1-300 AIRCRAFT Concorde aerodynamics and associated systems Stress measurements on landing gear for the Airbus development Book A-300 B2 A81-16718 A81-19299 The method of superelenents in the dynamics of ABLATIVE HATBRIALS complex structures Captive carry and free flight rain erosion A81-16969 considerations for reinforced ablative Optimum selection of main parameters for the flnorocarbon radome materials reverse design of a supersonic military aircraft A81-17U53 A81-17047 iCCIDBlT PBEVEITIOI Aerodynamic design of a ducted propeller - Helicopter alarms - The use of ALAT incident and Optimization of efficiency accident record cards A81-17146 A81-16689 Variational principles and generalized variational ACOUSTIC ATTBBOATIOH principles for the hybrid aerodynamic problem of Analysis of pressure spectra measurements in a airfoil cascades on an arbitrary stream sheet of ducted combustion systen revolution [NASA-TH-81583] H81-15768 A81-17741 ACOUSTIC DDCTS Aerodynamic calculations and design of snbcritical Sound radiation from a finite length unflanged aerofoils circular duct vith uniform axial flow. I - A81-17804 Theoretical analysis. II - Computed radiation An aerodynamic design method for transonic axial characteristics flow compressor stage A81-16712 A81-17805 &CODSTIC BHISSIOH Characteristics of the velocity field near a Application of optical methods to the study of jet wing-body combination located at an angle of noise and turbulence attack to an oncoming supersonic flow [ISL-CO-201/80] H81-15819 A81-19337 ACOUSTIC HEASOBEHEITS Drag redaction through formation flight Improved methods for fan sound field determination [DGLB PAPEB 80-106] A81-19393 [HASA-CR-165188] 1181-15769 Experimental investigation of a right angle wing ACODSTIC PROPAGATION with partially separated flow with and without Propagation of three-dimensional acoustic ground effects perturbations in channels of variable [DGLB PAPEB 80-111] A81-19397 cross-sectional area at frequencies close to Conditions of generation and methods of damping cutoff frequency the inlet vortex of a turbojet engine A81-19338 A81-19442 The sonic boom from an aircraft flying along an Nonlinear aerodynamic characteristics of a thin arbitrary path in a stratified atmosphere in the airfoil of arbitrary plane configuration presence of a three-component vind 481-19629 A81-19636 Rotary balance data for a single-engine ACOUSTIC PEOPEBTIES agricultural airplane configuration for an Sound radiation fron a finite length unflanged angle-of-attack range of 8 deg to 90 deg circular duct vith uniform axial flow. I - [HASA-CE-3311] H81-13923 Theoretical analysis. II - Computed radiation Effects of nonlinearities on wing store flutter characteristics [HBB-FE-17/S/POB/27] H81-13974 A81-16712 A-1 AEEODIHAHIC COEFFICIEBTS SUBJECT IID8I Experimental aerodynaaic characteristics of two AERODIBASIC BOISE 7/STOL fighter/attack aircraft configurations at Exhaust noise in flight: The role of acoustic Bach numbers from 0.1 to 1.4 installation effects [BASA-TH-81234] H81-14981 [PBH-90029] B81-14793 Curved centerline air intake for a gas turbine Static source locations for four nozzles aoanted engine on a J-85 engine [BASA-CASE-LEB-13201-1] B81-14999 [HASi-CB-152401] B81-14998 ABBODIBAHIC COEFPICIEITS Carved centerline air intake for a gas turbine Mind-tunnel test of an articulated helicopter engine rotor model vith several tip shapes [BASA-CASE-LEi-13201-1 ] B81-14999 [BASA-TB-80080] H81-13918 ABRODIBAHIC STIBILIIt AEBODTSAHIC COBFIGOBAIIORS The effect of aerodynamic coupling on the dynamics Some aspects of optimizing the aerodynanics of of aircraft in fast rolling motion turbine stages A81-17471 A81-19325 Practical aerodynaaics of the helicopter S1-6A Fighters for the 1990s Russian book A81-19497 481-18600 A system for aerodynamic design and analysis of A contribution to stabilization of flight vehicle supersonic aircraft. Part 2: User's manual parachute systems [HASA-CR-3352] B81-13920 [ DFVLH-BITT-80-05] B81-13926 Computational aerodynaaic design tools and Active flutter suppression on an P-4P aircraft techniques used at fighter developnent with external stores using already existing [HBB-FE-122/S/POB/13] B81-13950 control surfaces Laminar-airfoils for transport aircraft [BBB-FE-17/S/POB/24] B81-13972 [DFVLR-liITT-80-07] B81-13952 Aerodynamic stability analysis of BASA Lou-speed wind-tunnel tests of two weathercocking J85-13/planar pressure pulse generator sensors installation [HSBL-0171-TB] B81-14575 [HASA-CB-165141] B81-15004 An investigation into grid patching techniques TF34 engine compression system computer study B81-14708 simulation of flow stability Grid generation for general three-dimensional [HASA-CB-159889] B81-15005 configurations ABRODIBABIC ST1LUHG B81-14714 A status report on BASA general aviation A system for aerodynamic design and analysis of stall/spin flight testing supersonic aircraft. Fart 1: General A81-19471 description and theoretical development Bodel vibrations beyond low-speed stall [SASA-CR-3351 ] B81-14970 A81-19552 A system for aerodynamic design and analysis of Aerodynamic side-force alleviator means supersonic* aircraft. Fart 3: Computer program [BASA-CASE-LAH-12326-1] H81-14968 description Supersonic stall flutter of high speed fans in [BASA-CB-3353] B81-14971 tnrbofan engines Leading-edge deflection optimization for a highly •HASA-TH-81613] B81-14978 swept arrow wing configuration AEBODIIABICS [8ASA-1P-1777] N81-14974 Steady flow past a rectangular wing with An investigation of support-interference effects circulation that is variable along the span [BAL-TB-622] S81-14984 A81-16551 Development of finite-volume methods for Review of theoretical and experimental results on three-dimensional transonic flows three dimensional turbulent wakes and boundary [AD-A090829] B81-14986 layers AEBODTBABIC DRAG [OHERA-ST-1980-4] B81-13930 Calculation of the lift dependent drag polar of Development of high-rtemperatnre turbine subsystem cambered fighter plane configurations with technology to a technology readiness status, deflected maneuver flaps in the subsonic region phase 2 by Beans of a modified procedure according to [PE-1806-72] B81-14332 Lamar Bird flight and airplane flight instruments to [DGLB PAPEB 80-109] A81-19395 measure air currents and flight characteristics Drag estimations for stream-line and cylindrical CBASA-TB-75777] B81-14962 contour distortions on aircraft fuselages and Bibliography of Supersonic Cruise Research (SCB) train cars program from 1977 to mid-1980 [DGLB PAPEB 80-116] A81-19399 [BASA-BP-1063] B81-14973 The determination of the induced drag on slim Experimental determination of unsteady blade wings with high lift systems in the transonic element aerodynamics in cascades. Volume 2: region Translation mode cascade [BBB-FE122] A81-19400 [HASA-CB-165166] B81-14976 Thin minimum-drag airfoils AEBOELiSTICIII 481-19630 Passive control of wing/store flutter AERODIBAHIC FORCES [HASA-TB-81865] B81-13922 Clear air turbulence: Historical comments The effects of warhead-induced damage on the B81-14562 aeroelastic characteristics of lifting surfaces. A system for aerodynamic design and analysis of Volume 1: Aeroelastic effects supersonic aircraft. Part 1: General [AD-A091674] H81-13955 description and theoretical development AEBOBAOTICAi EBGIBEEBH6 [HASA-CB-3351] H81-14970 A summary of proposals for airflight research by ABBODTBAHIC IBIEBFBBEBCB the BBPT A wall interference analysis in wind tunnels A81-19298 A81-17472 A system for aerodynamic design and analysis of ABBODISAHIC LOADS supersonic aircraft. Part 2: User's manual Survey of lorkshops on Heteorological and [BASA-CB-3352] H81-13920 Environmental Inputs to Aviation Systems Computational aerodynamic design tools and H81-14556 techniques used at fighter development Transonic wind tunnel tests on an oscillating wing [HBB-FE-122/S/PUB/13] B81-139SO with external store. Part 4: The wing with Fundamentals of conceptual design optimization of nnderwing: Store subsonic transport aircraft [AD-A077370] B81-14969 [VTH-LB-292] B81-13951 The velocity induced by the wake of a wind turbine ABBOHAOIICiL SATELLITES in a shear layer, including ground effect Aeronantical-Baritime Engineering satellite /ABES/ [FFA-TB-HO-2189-PT-3] B81-14985 program of Japan [IAF PAPEB 80-D-171] A81-18318 A-2 SUBJECT IHDBX AIBCBAPI CiBBIEBS ABBOSPACB SISTEBS Bidair and near midair collisions on two- and Avionics and displays in a future airspace system three-dimensional curvilinear flight paths A81-18070 [DFVLB-FB-80-13] H81-13944 AFTERBODIES Hind shear systems integration plan, VICOB (visual An evaluation of wind tunnel test techniques foe confirmation) reliability analysis aircraft nozzle afterbody testing at transonic [PB80-218233] N81-13919 Bach numbers Proceedings: Fourth Annual Workshop on [AD-A091775] H81-13931 Heteorological and Environmental Inputs to Evaluation of wind tunnel nozzle afterbody test Aviation systems techniques utilizing a modern twin engine ( MASA-CP-2139] H81-14555 fighter geonetry at Hach numbers from 0.6 to 1.2 Applicated techniques for the control of approach IF-17 aircraft traffic [AD-A091545] H81-13932 [DFVLB-BITT-79-20] H81-14992 AB-64 HELICOPTER Advanced flight deck/crew station simulator Advanced Attack Helicopter /TAH-64/ - Status report functional requireaents A81-16580 [HASA-CB-159331] H81-14994 AIB BBEATHIH6 EiSISES AIB TBASSPOBTATIOB A study of air breathing rockets - Subsonic mode Fuel conservation in the air transportation combustion industry - General and operational aspects [IAF PAPEB 80-F-270] A81-18371 A81-17143 AIB COBBEBTS International Air Transportation Conference, Bew Bird flight and airplane flight instruments to Orleans, La., April 30-Bay 3, 1979, Proceedings. measure air currents and flight characteristics Volumes 1 5 2 [HASA-IB-75777] H81-14962 A81-18051 AIB IHTAKBS Hew major U.S. airports - Capacity considerations Curved centerline air intake for a gas turbine 481-18060 engine Aviation assumptions in the eighties [HASA-CASE-LE»-13201-1] H81-14999 A81-18068 AIB JETS A new perspective in aviation systems planning Experimental investigations on shock-associated A81-18069 noise Southern California aviation system study A81-17735 [PB80-215544] H81-13916 The Dalembertometer AIBBOBHE EQUIPSBBT [ISL-CO-220/79] B81-14292 Principle for the design of hybrid control systems AIB HAVI6ATIOH for passenger transport systems Autonomous navigation using passively sensed A81-17577 terrain images Observing lightning from ground-based and airborne A81-17977 stations BNAV benefits today - Today and future requirements H81-14566 A81-18056 AIBBOBIE/SPACEBOBIB COSPUTEBS Omega - An economic Loran A replacement An overview - 1980 generation avionic developments A81-18077 A81-18061 Cruise-missile-carrier navigation requirements L-1011 Flight aanagement System design A81-18576 considerations Badio navigation for aircraft: Handbook A81-18074 Bussian book Computer generated displays and pilot effectiveness A81-18599 A81-18082 Hap-type displays for air navigation System considerations in the implementation of A81-19443 digital control AIB 10 AIB BBFOELIHG [AAS 80-032] A81-19375 An investigation of safety hazards and reliability AIECHAFT ACCIDEBT IBVESTIGATIOI problems in aerial refueling stores Testimony of Elwood T. Driver, Vice Chairman, [AD-A091788] 1181-13938 national Transportation Safety Board, AIB TRAFFIC accompanied by Serrit J. Ralhont, Chief, Human Traffic forecasting for the HBIA Hew Biyadh Factors Division, and Matthew B. BcCormick, International Airport Senior Air Safety Investigator, Human Factors A81-18090 Division AIB TBAFFIC COITBOL H81-13934 The future ATC system as influenced by advanced AIBCBAFT ACCIDEHTS avionics Helicopter alarms - The use of ALAT incident and A81-16586 accident record cards Airspace analysis in airport system planning A81-16689 A81-18052 A survey of propulsion systems' Canada's national aviation forecasting models malfunctions/failures resulting in helicopter A81-18072 mishaps Increasing capacity with computer-assisted A81-17513 decision making airport planning Turbulence: From a pilot's viewpoint A81-18080 H81-14561 Airport visual approach, guidance and landing The microburst: Common factor in recent aircraft systems - Airline pilots viewpoint accidents A81-18083 B81-14571 Bodeling of the terminal area Air Traffic Briefs of accidents involving commuter air Management and Control carriers and on-demand air taxi operations, D.S. A81-1808S General Aviation 1978 Airspace simulation in airport system planning [PB81-101701] H81-14987 A81-18086 AIHCBAFT AHTEHIAS The role of aircraft separation assurance in the Volumetric pattern prediction of antennas on cockpit aircraft using the geometrical theory of A81-18092 diffraction Aeronautical-Baritime Engineering Satellite /ABES/ [DFVIB-FB-80-01] B81-14195 program of Japan AIBCBAFT BBAKBS [IAF PAPEB 80-D-171] A81-18318 Today and the future in aircraft wheel and brake Performance evaluation of an interrogation-reply development scheduling technique for a discrete address A81-17046 beacon system of radar surveillance and AIBCBAFT CABBIEBS aircraft communication in ATC Planning for and evaluating the potential of a A81-19417 land based aircraft for carrier operations Southern California aviation system study A81-19470 [PB80-215544] H81-13916 A-3 AIBCBAFT COBBOHICATIOH SUBJECT IIDBZ AIBCBAFT COBBUIICATIOH Theoretical investigation of the influence of Automating airborne company communications spoiler dynamics on the handling qualities of an A81-18064 aircraft with direct lift control Performance evaloation of an interrogation-reply [DFVLB-FB-80-07] H81-13975 scheduling technique for a discrete address AIBCBAFT DESIGg beacon systea of radar surveillance and 757/767 design considerations for improved aircraft communication in ATC productivity A81-19417 A81-16584 AIBCBAPT COHPABTHEHTS Development and certification of the Gulfstream III Aviation safety: Interior compartment materials A81-16587 [GPO-50-388] H81-13933 A case study in aircraft design: The de Havilland AIBCBAFT COIFIGDBAtlOlS family of STOL commuter aircraft Book Finite difference computation of the steady A81-16717 transonic potential flov around airplanes Concorde aerodynamics and associated systems A81-17802 development Book Calculation of the lift dependent drag polar of A81-16718 cambered fighter plane configurations with The Grnaman Aerospace and Gnlfstream American deflected maneuver flaps in the subsonic region Gulfstream III case study in aircraft design by means of a modified procedure according to Book Lamar A81-16720 [DG1B PAPEB 80-109] A81-19395 The Gossamer Condor and Albatross: A case study in Drag estimations for stream-line and cylindrical aircraft design Book contour distortions on aircraft fuselages and [AV-B-80/540] A81-16721 train cars Optimum selection of main parameters for the [DGLB PAPEB 80-116] A81-19399 reverse design of a supersonic military aircraft Component-adaptive grid embedding A81-17047 H81-14697 Transonic axisymmetric bodies with minimal nave drag Experimental aerodynamic characteristics of tvo A81-17048 V/STOL fighter/attack aircraft configurations at Application of fracture mechanics in designing Bach numbers from 0.4 to 1.4 lover wing skin of transport aircraft [HASA-TB-81234] H81-14981 A81-17049 Computational Fluid Dynamics, volume 2 Becent selected papers of Northwestern [VKI-LS-1980-5-VOL-2] 1181-15310 Polytechnical University. Parts 162 Book An economic and versatile panel method for A81-17801 aircraft and aircraft/store configurations. An Second order approximation theory of an arbitrary outline of the principal features of the aerofoil in incompressible potential flov mathematical modeling and numerical A81-17803 implementation of the British Aerospace (Harton) ' Aerodynamic calculations and design of subcritical Bk II Panel Method aerofoils H81-15311 A81-17804 AI EC BAFT COISTBOCTIOI UIBKULS Structural analysis .of fuselages with cutouts by Prediction methods for fatigue crack growth in finite element method aircraft material A81-17816 A81-18777 The matrix analysis of vings Testimony of James J. Kramer, Associate A81-17818 Administrator for Aeronautics and Space Sukhoi's pivotal interdictor Technology, National Aeronautics and Space A81-17832 Administration, accompanied by John H. Enders, Avionics and displays in a future airspace system Project Hanager, Aviation Safety Technology A81-18070 Office, John A. Parker, Chemical Research A summary of proposals for airflight research by Projects Office, NASA-Ames Sesearch Center, and the BBFT Demitrius A. Kourtides, Chemical Besearch A81-19298 Projects Office, NASA-SUES Besearch Center Stress measurements on landing gear for the Airbus H81-13935 A-300 B2 Testimony of Bichard W. Taylor, Vice President and AB1-19299 Special Assistant to the President, and Eugene Design to cost and new technologies A. Bara, Chief Engineer, Payloads Systems, A81-19347 Boeing Commercial Airplane Company Procedures for optimal drag design of camber and H81-13936 flap deflection in supersonic regions with Testimony of a panel consisting of: Lloyd E. consideration to geometric limits Frisbee, Vice President, Engineering and [DGLB PAPEB 80-110] A81-19396 Operations, Lockheed California Company; Lyle A. Circulation Control iing /CCS/ flight tests Iright, Director, Powerplant Engineering, 481-19469 Douglas Aircraft Company, accompanied by Doctor Industry proposes supersonic V/STOL H. C. Schjeldernp, chief Technology Engineer, A81-19490 Baterials and Process Engineering, and F. E. Fighters for the 1990s Duskin, Senior Design Engineer, Interiors A81-19497 Engineering, Douglas Aircraft Company A system for aerodynamic design and analysis of H81-13937 supersonic aircraft. Part 2: User's manual AIBCBAFT COITBOL [NASA-CB-3352] B81-13920 Inverse problems of controlled flight dynamics - Computational aerodynamic design tools and Longitudinal motion techniques used at fighter development A81-16968 CBBB-FE-122/S/POB/13] H81-13950 Principle for the design of hybrid control systems Fundamentals of conceptual design optimization of for passenger transport systems subsonic transport aircraft A81-17577 [VTB-LB-292] H81-13951 Modeling of the terminal area Air Traffic Laninar-airfoils for transport aircraft Management and Control [DFVLB-BITT-80-07] H81-13952 A81-18085 Technological forecasting—aircraft design. Bodel-following system with assignable error Citations from the International Aerospace data dynamics and its application to aircraft base A81-18577 tHASA-CB-163833] N81-13957 System considerations in the implementation of Economic evaluation of flying-qualities design digital control criteria for a transport configured with relaxed [AAS 80-032] A81-19375 static stability Landing flying qualities evaluation criteria for [HASA-TP-1760] H81-13968 augmented aircraft Bird flight and airplane flight instruments to [HASA-CB-163097] H81-13969 measure air currents and flight characteristics [HASA-TB-75777] H81-14962 1-4 SUBJECT IIDBI AIRCRAFT HOI SB A systen for aerodynamic design and analysis of Aeronautical concerns and Rational Aeronautics and supersonic aircraft. Part 1: General Space Administration atmospheric electricity description and theoretical development projects CNASA-CB-3351] H81-14970 N81-14567 A system for aerodynamic design and analysis of The microburst: Common factor in recent aircraft supersonic aircraft. Part 3: COBputer program accidents description N81-14571 [HASA-CB-3353] N81-14971 Doctor Fujita's microbarst analysis at Chicago Remotely piloted vehicles. Citations from the N81-14572 International Aerospace abstracts data base Lightning. Citations from the International [H4S1-CB-163864] B81-14996 Aerospace abstracts data base &IECBAFT BNGIIES [NASA-CR-163857] N81-15614 8 Productivity - The challenge of aircraft and Clean air turbulence. Citations from the engine maintenance International Aerospace Abstracts data base 481-17045 [NASA-CB-163863] N81-15649 Bolls-Boyce engines status report AIBCBAFI BIDBADLIC SISTERS A81-17166 Elimination of vibrations in aircraft piping systems Coatings in the aero gas turbine Bussian book A81-17167 A81-18497 Turbopropeller engine PZL-10S AIRCRAFT IBDOSTBI A81-17324 Aviation assumptions in the eighties Composition of sludge formed in B-3V oil A81-18068 A81-17373 An assessment of General Aviation utilization of Joint-laboratory qualification testing of oils for advanced avionics technology gas turbine engines [NASA-CB-159328] 881-13941 A81-17375 Current aircraft survey (approach speeds, gross The digital control system as part of an weights, and Dimensions) integrated accessory fit for fntuce engines [PB80-225691] H81-13956 A81-17505 AIBCBAFI IISIBDBEITS Turbine blade technology - Present and future A new system for the study of visual information IISVS PAPEB 80-C2/ABBO-10] A81-18639 presentation in aeronautics - GIBI Calculated and experimental data for a 118-nm bore A81-16688 roller bearing to 3 million DH Radio navigation for aircraft: Handbook [ASME PAPEB 80-C2/LUB-14] A81-18668 Russian book Aircraft engine programs employing cost objectives A81-18599 A81-19346 Simulator study of conventional general aviation Calculation of propeller efficiency for an ideal instrument displays in path-following tasks with propeller emphasis on pilot-induced oscillations A81-19444 [HASA-TP-1776] N81-14997 An evaluation of wind tunnel test techniques for AIBCBAFI LANDING aircraft nozzle afterbody testing at transonic Micro-wave landing system - An operational point Bach numbers of view [AD-A091775] H81-13931 A81-18055 Advanced Technology Spark-Ignition Aircraft Piston Flight instrumentation requirements for Engine Design Study all-weather approach and landing [NASA-CB-165162] N81-13963 A81-18059 Prevention of spline wear by soft metallic coatings Experimental investigation of orographic waves and aircraft engines vertical motions in the Krasnovodsk airport area [AD-A091861] N81-14064 A81-19441 Compressor configuration and design optimization Flight evaluation of the terminal guidance system for the high reliability gas turbine tHASA-CB-163859] N81-14991 [DOE/ET-15425/T1] H81-14327 AIBCBAFI MAIITBSAMCB The measurement of aero gas turbine noise Productivity - The challenge of aircraft and [PNB-90032] H81-14795 engine maintenance Analysis of pressure spectra measurements in a A81-17045 ducted combustion system Issues regarding Army tnrboshaft engines CNASA-TH-81583] H81-15768 diagnostics and condition monitoring AIBCBAFI EQOIPHEIT A81-17514 A fault tolerant multiprocessor system with Aircraft maintenance, citations from the reconfiguration suitable for mnltiazial flight International Aerospace Abstracts data base stabilization and trimming CNASA-CB-163837] N81-13917 481-19296 AIBCBAFI MAMBUTBBS Solid-state power systen use expands The effect of aerodynamic coupling on the dynamics A81-19491 of aircraft in fast rolling motion Evaluation of a computer-generated perspective A81-17471 tunnel display for flight path following Drag reduction through formation flight [HASA-TP-1736] N81-13958 [DGLR PAPEB 80-106] A81-19393 Flight evaluation of the terminal guidance system Planning for and evaluating the potential of a [HASA-CH-163859] H81-14991 land based aircraft for carrier operations AIBCBAFT FDELS A81-19470 Formation of solid phase during the heating of jet Maneuvering aircraft: Noise pollution and fuels control. Citations from the HTIS data base A81-17372 [PB80-815566] H81-14525 Testimony of Elwood I. Driver, Vice Chairman, AIRCRAFT MODELS national Transportation Safety Board, Testing model rotorcraft for overwater operations accompanied by Gerrit J. Halhout, Chief, Human A81-18058 Factors Division, and Hatthew H. HcCoriuick, AIBCBAFI BOISE Senior Air Safety Investigator, Human Factors The federal role in airport noise control planning Division A81-18073 881-13934 The sonic boom from an aircraft flying along an AIBCBAFI GUIDANCE arbitrary path in a stratified atmosphere in the Airport visual approach, guidance and landing presence of a three-component wind systems - Airline pilots viewpoint A81-19636 A81-18083 Maneuvering aircraft: Noise pollution and AIBCBAFI HAZARDS control. Citations from the NTIS data base An investigation of safety hazards and reliability [PB80-815566] N81-14525 problems in aerial refueling stores Assessment of ground effects on the propagation of [AD-A091788] H81-13938 aircraft noise: The T-38A flight experiment [NASA-IP-1747] N81-14788 A-5 AIRCRAFT P1HIS SUBJECT IIDBI The rating of helicopter noise: Development of a Testimony of a panel consisting of: Lloyd E. proposed impulse correction Frisbee, Vice President, Engineering and [NPL-AC-93] H81-11792 Operations, Lockheed California company; Lyle A. The annoyance caused by noise around airports (right. Director, Powerplant Engineering, [HASA-TH-75784] H81-15579 Douglas Aircraft Company, accompanied by Doctor Aircraft annoyance evaluations asing field and B. c. Schjelderup, Chief Technology Engineer, laboratory simulation techniques Materials and Process Engineering, and F. E. [DTIAS-248] H81-15580 Dnskin, senior Design Engineer, Interiors AIRCBAFT PARIS Engineering, Douglas Aircraft Company Renewal function for any arbitrary period - A H81-13937 Bayesian nay Proceedings: Fourth Annual Workshop on A81-16939 Meteorological and Environmental Inputs to The rigidity and performance of a siaple spiral Aviation systems bevel helicopter gearbox [NASA-CP-2139] H81-14555 [ASHE PAPER 80-C2/DET-103] A81-18654 Aviation meteorology research and development: A Performance of computer-optimized tapered-roller status report bearings to 2.4 million DN H81-14557 [ASHE PAPER 80-C2/LUB-18] A81-18672 measuring weather for aviation safety in the 1980's The vear of PTFE-containing dry bearing liners N81-14568 contaminated by fluids Commuter airline safety [ASLE PBEPHIHT 80-LC-6B-3] A81-18758 [PB81-1 04267] B81-14988 URCBAFT PERFORHARCE AIRCBAFT SPECIFICATIONS F/A-18 full scale development test Current aircraft survey (approach speeds, gross A81-16579 weights, and Dimensions) The Grumman Aerospace and Gulfstrean American [PB80-225691] H81-13956 Gulfstream III case study in aircraft design AIRCBAFT STRUCTURES Book The automatic matrix force method and techniques A81-16720 for handling more complex computations with The Gossamer Condor and Albatross: A case study in given computer capacity aircraft design Book A81-17815 [AV-B-80/540] A81-16721 Elimination of vibrations in aircraft piping systems History of flight testing the L-1011 Tristar jet Russian book transport. I - The L-1011-1 A81-18497 A81-17976 Automatization of the adhesion process for AIECBAFT PILOTS supporting airframe parts in light contour systems Primary training of military pilots - Changing A81-19297 theories and new trainers The effects of warhead-induced damage on the A81-19498 aeroelastic characteristics of lifting surfaces. Turbulence: From a pilot's viewpoint Volume 1: Aeroelastic effects N81-14561 [AD-A091674] N81-13955 AIRCRAFT PEODOCTIOS Controls of aeronautical structures under fatigue The Grumman Aerospace and Gnlfstream American testing by holographic pulsed lasers Gnlfstream III case study in aircraft design interferometry Book [ISL-CO-218/79] H81-14300 A81-16720 AIRCRAFT SORVIVABILITI Automatization of the adhesion process for Helicopter survivability in overwater situations supporting airframe parts in light contour systems A81-18081 A81-19297 Aviation safety: Interior compartment materials AIRCBAFT PRODOCTIOI COSTS [GPO-50-388] N81-13933 The design-to-cost of aircraft AIRCRAFT TIRES A81-19344 Today and the future in aircraft wheel and brake Design to cost and new technologies development A81-19347 A81-17046 »IECBAFT BELIABILITI AIRFIELD SURFACE BOVEBBITS A case study on the F-16 fly-by-wire flight Non-destructive pavement evaluation control system Book A81-18062 A81-16719 AIRFOIL PROFILES The problems of helicopter ditching Variational principles and generalized variational A81-18071 principles for the hybrid aerodynamic problem of AIRCBAFT SAFETY airfoil cascades on an arbitrary stream sheet of Sarsat - A rescue system for ships and aircraft revolution A81-16684 A81-17741 Safety considerations for helicopter drive systems Second order approximation theory of an arbitrary of the 1980s aerofoil in incompressible potential flow A81-17510 A81-17803 Helicopter survivability in overwater situations Aerodynamic calculations and design of snbcritical A81-18081 aerofoils Pyrotechnics serving safety in aircraft air A81-17804 and ground escape systems Reduction of profile drag by blowing out through A81-19348 peg holes in areas of streamline separation Aviation safety: Interior compartment materials bubbles [GPO-50-388] H81-13933 [DGLB PAPER 80-103] A81-19392 Testimony of James J. Kramer, Associate Experimental investigation of a right angle wing Administrator for Aeronautics and Space with partially separated flow with and without Technology, National Aeronautics and Space ground effects Administration, accompanied by John H. Enders, [DGLR PAPER 80-111] A81-19397 Project Nanager, Aviation safety Technology Wind-tunnel test of an articulated helicopter Office, John A. Parker, Chemical Besearcb rotor model with several tip shapes Projects Office, HASA-Ames Research Center, and [NASA-TB-80080] H81-13918 Deoitrios A. Konrtides, Chemical Research AIRFOILS Projects Office, NASA-ABES Research Center A computer program for the design and analysis of H81-13935 low-speed airfoils, supplement Testimony of Richard B. Taylor, Vice President and [HASA-TH-81862] 1181-13921 Special Assistant to the President, and Eugene Surface finishing A. Bara, Chief Engineer, Payloads Systems, [BASA-CASE-HSC-12631-3] H81-14077 Boeing Commercial Airplane Company Experimental determination of unsteady blade N81-13936 element aerodynamics in cascades. Volume 2: Translation mode cascade [SASA-CB-165166] N81-14976 A-6 SUBJECT ISDBI APPBOACH COIIB01 A nethod for obtaining shockless transonic flows 4IBPOBTS past airfoils, partially modified from a given International Air Transportation Conference, Hew arbitrary airfoil Orleans, La., April 30-Hay 3, 1979, Proceedings. [NAL-TB-602T] N81-14983 Volumes 162 AIBPBA8ES 481-18051 fieview of engine/airframe/drive train dynamic Non-destructive pavement evaluation interface development problems 481-18062 481-17516 Prestressed concrete airfield pavements Engine-airframe transient compatibility - Analysis 481-18063 and test Bnnway rehabilitation, Washington National Airport 481-17517 4B1-18066 Automatization of the adhesion process for OK pavement design and evaluation - 4 new approach supporting airfrane parts in light contour systems 481-18076 481-19297 Experimental investigation of orographic waves and AIBLINE OPEBATIOiS vertical motions in the Krasnovodsk airport area The future 4TC system as influenced by advanced 481-191111 avionics Statistical relationship between median visibility 481-16586 and conditions of vorstcase manmade impact on Airline flight departure procedures - Choosing visibility between noise abatement, minimum fuel [L4-OE-80-2185] H81-14550 consumption and mininum cost Applicated technigues for the control of approach 481-17011 traffic Productivity - The challenge of aircraft and [DFVLB-MITT-79-20] N81-11992 engine maintenance The annoyance caused by noise around airports 481-17015 [NASA-TM-75781] N81-15579 An overview - 1980 generation avionic developments Aircraft annoyance evaluations using field and 481-18061 laboratory simulation techniques Aircraft maintenance. Citations from the [UTI4S-248] N81-15580 International Aerospace Abstracts data base 4IBSP4CB (SASA-CB-163837J H81-13917 airspace analysis in airport system planning Commuter airline safety 481-18052 [PB81-104267] H81-11988 4LL-iB4TBBH 41B HATIGATIOB AIBPOBT LIGHTS Problems of flight mechanics involved in Airport visual approach, guidance and landing all-weather helicopter operation systems - Airline pilots viewpoint 481-17167 181-18083 Sukhoi's pivotal interdictor AIBPOBT PLAN BUG 481-17832 Airspace analysis in airport system planning Helicopters - Help for the all weather terminal A81-18052 481-18065 Introduction to a rigid pavement design procedure ALL-iBATBEB LASDIHG SISTERS A81-18051 Flight instrumentation reguirements for Micro-wave landing system - An operational point all-weather approach and landing of view 481-18059 A81-18055 ALPHA JET 4IBCB4FT The introduction of STOL and BNAV to large Planning for and evaluating the potential of a commercial operations land based aircraft for carrier operations A81-18057 481-19470 New major O.S. airports - Capacity considerations ALOMIHOH ALLOTS A81-18060 Prediction methods for fatigue crack growth in Community participation in airport planning aircraft material A81-18067 481-18777 4 new perspective in aviation systems planning AMPHIBIOUS fEHICLES 481-18069 Heave instabilities of amphibious air cushion Canada's national aviation forecasting models suspension systems 481-18072 [OTIAS-216] N81-15156 The federal role in airport noise control planning ANGLE OF ATTACK 481-18073 Laminar boundary layer on swept-back wings of Fully bonded concrete overlay for an airport runway infinite span at an angle of attack 481-18075 A81-17656 Investment decision-making in international airports Characteristics of the velocity field near a 481-18079 wing-body combination located at an angle of Increasing capacity with computer-assisted attack to an oncoming supersonic flow decision making airport planning A81-19337 481-18080 Hypersonic gas flow over a delta wing Design of the new Tehran International Airport A81-19632 481-18081 Aerodynamic side-force alleviator Deans Modeling of the terminal area 4ir Traffic [NASA-CASE-LAB-12326-1] N81-11968 Management and Control Effects of angle of attack and ventral fin on 481-18085 transonic flutter characteristics of an Airspace simulation in airport system planning arrow-wing configuration 481-18086 [HASA-TM-81911] N81-15397 The importance of 'Interim Standard Microwave AIGOLAB ACCELBBATIOI Landing System' for small community airports Calculated and experiiental.data for a 118-mm bore 481-18087 roller bearing to 3 million DN 4irport/environs plan making - Managing the [ASHE PAPER 80-C2AOB-14] A81-18668 planning process Performance of computer-optimized tapered-roller 481-18088 bearings to 2.4 million DN Bnnway Configuration Management System concepts [ASME PAPEB 80-C2/LOB-18] A81-18672 481-18089 AiTIOIIDAITS Traffic forecasting for the BBIA Sen Biyadh Composition of sludge formed in B-3f oil International Airport A81-17373 481-18090 APPBOACH COHTBOL Environmental aspects of airport planning Flight instrumentation regnirements for 481-18091 all-weather approach and landing Saudi Arabia's new Gateway Airports A81-18059 A81-18093 Airport visual approach, guidance and landing Southern California aviation system study systems - Airline pilots viewpoint [PB80-2 155111 ] H81-13916 A81-18083 1-7 APPBOIIBATIOI SOBJECT IIDBI The importance of 'Interim Standard Bicrowave A?IOHICS Landing System' for small comnnnity airports Air traffic management enhancement through new A81-18087 avionics /4-D/ Flight evaluation of the terminal guidance system A81-16583 [BASA-CB-163859] B81-14991 A cockpit view of advanced airline avionics Applicated techniques for the control of approach A81-16585 traffic The future ATC system as influenced by advanced [DPVLB-BITT-79-20] H81-14992 avionics APPBOIIBATIOI A81-16586 Second order approximation theory of an arbitrary An overview - 1980 generation avionic developments aerofoil in incoopressible potential flow A81-18061 A81-17803 Avionics and displays in a future airspace system Daal nethods and approxiaation concepts in A81-18070 structural synthesis Cruise-aissile-carrier navigation requirements [HASA-CB-3226] B81-14347 AS 1-18576 ABE1 IAVIG&TIOB System considerations in the implementation of BSAV benefits today - Today and future requirements digital control A81-18056 [AAS 80-032] A81-19375 ABB01 BIHGS Solid-state power system use expands Leading-edge deflection optimization for a highly A81-19491 swept arrow wing configuration Fighters for the 1990s [BASA-TP-1777] B81-14974 A81-19497 Effects of angle of attack and ventral fin on An assessment of General Aviation utilization of transonic flutter characteristics of an advanced avionics technology arrov-wing configuration [HASA-CB-159328] B81-13941 [BASA-TH-81914J N81-15397 DC-to-DC power supply for light aircraft flight ASTHPTOTIC HETHODS testing Benewal function for any arbitrary period - A [BASA-CB-163850] H81-14989 Bayesian way A survey of new technology for cockpit application A81-16939 to 1990's transport aircraft simulators ATLABTIC OCEAH [HASA-CB-159330] H81-14993 Catalog of sea state and wind speed in the South Validation Bethods Besearch for Fault-Tolerant Atlantic Bight Avionics and Control Systems Sub-Borking Group [NASA-CB-156872] 881-14601 Heeting. CASE 3 peer review AIHOSPBEBIC BLBCTHICITI [BASA-CP-2167] H81-15702 Observing lightning from ground-based and airborne AXIAL FL01 stations Sound radiation from a finite length unflanged B81-14566 circular duct with uniform axial flow. I - Aeronaatical concerns and Bational Aeronautics and Theoretical analysis. II - Computed radiation Space Administration atmospheric electricity characteristics projects A81-16712 B81-14567 AXIAL FLO! TDBBIBES Lightning. Citations from the International The velocity induced by the wake of a wind turbine Aerospace abstracts data base in a shear layer, including ground effect [HASA-CB-163857] B81-15648 [FFA-TH-HO-2189-PT-3] H81-14985 ATBOSPHEBIC STBATIFICATIOH AXISIBHBTBIC FLO! The sonic boom from an aircraft flying along an Effects of axisymmetric sonic nozzle geometry on arbitrary path in a stratified ataosphere in the Hach disk characteristics presence of a three-component wind A81-18022 A81-19636 AIHOSPBEBIC TEHPERATOBE Aircraft icing instrumentation: Unfilled needs B rotary wing aircraft BAFFLES N81-14560 Low-speed wind-tunnel tests of two weathercocking ATHOSPHEEIC TDBBDLESCE sensors Survey of Workshops on Heteorological and [ISBL-0171-TB] H81-14575 Environmental Inputs to Aviation Systems BASE PHBSSOBB H81-14556 An investigation of support-interference effects Turbulence: From a pilot's viewpoint [HAL-TB-622] H81-14984 N81-14561 BAI8S THBOBEB ATTACK AIBCBAFT Benewal function for any arbitrary period - A Sukhoi's pivotal interdictor Bayesian way A81-17832 A81-16939 Experimental aerodynamic characteristics of two BEABIBG ALLOTS V/STOL fighter/attack aircraft configurations at Surface analysis of bearing steels after solvent Bach numbers from 0.4 to 1.4 treatments. II - Lubricant-coated bearing surfaces [NASA-TB-81234] H81-14981 [ASLE PBEPBIBT 80-LC-8A-6] A81-18748 ADTOBATIC COBT1OL BEABIBGS Principle for the design of hybrid control systems Experience with advanced high performance gear steel for passenger transport systems for CH-47 A81-17577 [ASHE PAPEB 80-C2/DET-77] A81-18648 Gas turbine engines and transmissions for bus The wear of PTPE-containing dry bearing liners demonstration programs contaminated by fluids [COO-4867-07] N81-14329 CASLE PBEPBIBT 80-LC-6B-3] A81-18758 AUTOMATIC PLIGHT COHTBOL Service life determination for the OH-60-A (OTTAS) Inverse problems of controlled flight dynamics - helicopter elastomeric bearings Longitudinal motion [AD-A091756] B81-14324 A81-16968 Improved capabilities to detect incipient bearing Beaotely piloted vehicles, citations from the failures International Aerospace abstracts data base CAD-A091687] H81-14325 [HASA-CB-163864] B81-14996 BIBLIOSBAPHIES AUTOMATIC PILOTS Aircraft maintenance. Citations from the Aatononons navigation using passively sensed International Aerospace Abstracts data base terrain images [SASA-CB-163837] B81-13917 A81-17977 Microwave landing systems. Citations from the AOTOBATIOI Engineering Index data base Automating airborne company communications [PB80-814643] B81-13947 A81-18064 A -8 SUBJECT IHDEX CEHAHICS Bicrovave landing systems. Citations from the BOONDABI LAIEB TBABSITIOB BUS data base Thren-dimensional boundary layer transition via [PB80-814635] H81-13948 the mechanisms of 'attachment line Technological forecasting—aircraft design. contamination1 and 'cross flow instability1 Citations from the International Aerospace data A81-18122 base Ball cooling and the laminar-turbulent boundary [HASA-CB-163833] B81-13957 layer transition at supersonic flow velocities Maneuvering aircraft: Noise pollution and A81-19644 control. Citations from the BUS data base BOOIDABT TILDE PBOBLEHS [PB80-815566] B81-14525 Component-adaptive grid embedding Bibliography of Supersonic Cruise Besearch (SCB) B81-11697 prograa from 1977 to mid-1980 An analytic model of subsonic flow around an [H4SA-HP-1063] B81-14973 airflow with a spoiler Bemotely piloted vehicles. Citations from the B81-14966 International Aerospace abstracts data base A method for obtaining shockless transonic flows [BASA-CB-163864] H81-14996 past airfoils, partially modified from a given Lightning, citations froa the International arbitrary airfoil Aerospace abstracts data base [BAL-TR-602T] B81-14983 [HASA-CB-163857] H81-15648 BBOADCASTHG Clean air turbulence. Citations from the Canada's national aviation forecasting models International Aerospace Abstracts data base A81-18072 [HASA-CB-163863] B81-15649 BIBD-AIiCBAFT COLLISIOIS Collisions between aircraft and birds A81-19445 CALIFORNIA BIHOS Southern California aviation system study Bird flight and airplane flight instruments to CPB80-215544] N81-13916 measure air currents and flight characteristics CABABD CONFIGOBATIONS [HASA-TH-75777] 1181-14962 Computational aerodynaaic design tools and BLADE TIPS techniques used at fighter development Rind-tunnel test of an articulated helicopter [UBB-FE-122/S/POB/13] N81-13950 rotor model with several tip shapes CANOPIES [HASA-TH-80080] H81-13918 A contribution to stabilization of flight vehicle BLOiBBS parachute systems Noise and noise abatement in fans and blowers: A [DFVLB-HITT-80-05] N81-13926 review CABBON FIBEB BEIBFOBCBD PLASTICS [DFVLB-FB-80-16] B81-14796 Constant-amplitude and flight-by-flight tests on BLOIIB6 CEBP specimens Reduction of profile drag by blowing out through [HBB-FE-2/S/POB-26] B81-14006 peg holes in areas of streamline separation CABBON FIBBBS bubbles A resin injection technique for the fabrication of [DGLB PAPEB 80-103] A81-19392 aero engine composite components BODI-BTBG CONFIGOBATIONS [PBB-9002U] H81-14004 Characteristics of the velocity field near a CABTESIAN COOBDIBATES wing-body combination located at an angle of Component-adaptive grid embedding attack to an oncoming supersonic flow B81-14697 A81-19337 CASCADE FLOW Development of finite-volume methods for Variational principles and generalized variational three-dimensional transonic flows principles for the hybrid aerodynamic problem of [AD-A090829] B81-14986 airfoil cascades on an arbitrary stream sheet of BOBIie AIBCBAFT revolution Testimony of Bichard I. Taylor, Vice President and A81-17741 Special Assistant to the President, and Eugene An aerodynamic design method for transonic axial A. Bara, chief Engineer, Payloads Systems, flow compressor stage Boeing Commercial Airplane Company A81-17805 B81-13936 Experimental determination of unsteady blade BOEING 757 AIBCBAFT element aerodynamics in cascades. Volume 2: 757/767 design considerations for improved Translation mode cascade productivity [NASA-CB-165166] B81-14976 A81-16584 Supersonic stall flutter of high speed fans in Computer generated displays and pilot effectiveness turbofan engines A81-18082 [HASA-TH-81613] N81-14978 BOEIHG 767 AIBCBAFT Solution of plane cascade flow using improved 757/767 design considerations for improved surface singularity methods application of productivity panel method to internal aerodynamics A81-16584 [HASA-Tn-81589] H81-14979 Computer generated displays and pilot effectiveness Full potential solution of transonic quasi-3-D A81-18082 flow through a cascade using artificial BOOSTEBS compressability The T700 booster engine [NASA-TB-81637] B81-14980 A81-17506 CASE HISTOBIBS BOOBDABI LAIKB COBTBOL A case study on the F-16 fly-by-wire flight A computer program for the design and analysis of control system Book low-speed airfoils, supplement A81-16719 [NASA-Tn-81862] B81-13921 CATESOBIBS Active flutter suppression on an F-4F aircraft Current aircraft survey (approach speeds, gross with external stores using already existing weights, and Dimensions) control surfaces [PB80-225691] B81-13956 [HBB-FE-17/S/POB/24] 881^13972 CA7ITATIOH FLOB Aerodynamic side-force alleviator means Beduction of profile drag by blowing out through [ BASA-CASE-LAB-12326-1 ] H81-14968 peg holes in areas of streamline separation BODHDABI LAIEB FLO! bubbles Hind-tunnel measurements and comparison with [DGLB PAPEB 80-103] A81-19392 flight of the boundary layer and heat transfer CEBABIC HOSEICOHBS on a hollow cylinder at Bach 3 Improved ceramic heat exchanger materials [NASA-TP-1789] B81-14975 [BASA-CB-159678] B81-14082 CEBAHICS Improved ceramic heat exchanger materials [NASA-CB-159678] N81-14082 A-9 CBBTIFICATIOB SUBJECT ISDEI CBBTIFICATI01 The role of aircraft separation assurance in the History of flight testing the 1-1011 Tristar jet cockpit transport. I - The L-1011-1 A81-18092 A81-17976 COHBBBBT ACOOSTIC BADIATIOB CH-47 HBLICOPTBB Improved methods for fan sound field determination Experience with advanced high performance gear steel [BASA-CB-165188] B81-15769 for CH-47 COLLISION AVOIDABCB [ASSE PAPEB 80-C2/DET-77] A81-18648 The role of aircraft separation assurance in the CBAHBE1 FLOi cockpit Propagation of three-dimensional acoastic 181-18092 perturbations in channels of variable Satellites to aid flight safety cross-sectional area at frequencies close to [IAF PAPEB 80-IAA-17] A81-18410 cutoff frequency Collisions between aircraft and birds A81-19338 A81-19445 CHABBBLS (DATA TRABSBISSIOB) Midair and near midair collisions on two- and A survey of new technology for cockpit application three-dimensional curvilinear flight paths to 1990*s transport aircraft simulators [DFVLB-FB-80-13] B81-13944 [BASA-CB-159330] B81-14993 COBBOSTIOB CHAHBEBS CHEBICAL COBPOSITIOi A simple combnstor system for a small gas turbine Composition of sludge formed in B-3V oil engine A81-17373 A81-17503 CBBOBIOB STEELS A vaporizing combustor with double combustion spaces The effect of cyclic loading on the apparent A81-17827 cleavage fracture toughness of 1Cr-Ho-V rotor An experimental study on kerosene-hydrogen hybrid steel combustion in a gas turbine combustor A81-17488 A81-17841 CIBCDIT PHOTECTIOI Vector and scalar characteristics of opposing jets A case study on the F-16 fly-by-wire flight discharging normally into a cross-stream control system Book A81-17997 A81-16719 Analysis of pressure spectra measurements in a Lightning. Citations from the International ducted combustion system Aerospace abstracts data base [BASA-TB-81583] B81-15768 [HASA-CB-163857] H81-15648 COBBOSTIOI EFFICIEBCI CIRCULATION COHTBOL AIBFOILS A simple combustor system for a small gas turbine Circulation Control Bing /CCw/ flight tests engine A81-19469 A81-17503 CIVIL AVIATIOS COBSABD ABD COBTBOL A cockpit view of advanced airline avionics The collision course: Conditions, guidance laws A81-16585 and properties The future ATC system as influenced by advanced [DFVLB-FB-80-06J B81-13942 avionics COBBEBCIAL AIBCBAFT A81-16586 Today and the future in aircraft wheel and brake Design of the new Tehran International Airport development A81-18084 A81-17046 Saudi Arabia's new Gateway Airports The introduction of STOL and BHAV to large A81-18093 commercial operations Pyrotechnics serving safety in aircraft air A81-18057 and ground escape systems SNIAS helicopters A81-19348 A81-19342 Aircraft maintenance. Citations from the Briefs of accidents involving commuter air International Aerospace Abstracts data base carriers and on-demand air taxi operations, D.s. [NASA-CB-163837] M81-13917 General Aviation 1978 An assessment of General Aviation utilization of [PB81-101701] N81-14987 advanced avionics technology Conmuter airline safety [BASA-CB-159328] B81-13941 [PB81-104267] B81-14988 The future of civil turbo-fan engines COBBDBICATIOI BQUIPSEIT [PBB-90034] 1181-13964 Automating airborne company communications Briefs of accidents involving commuter air A81-18064 carriers and on-demand air taxi operations, O.S. COBHOIICATIOB SATELLITES General Aviation 1978 Aeronautical-Maritime Engineering Satellite /ABES/ [PB81-101701] H81-14987 program of Japan Commuter airline safety [IAF PAPEB 80-D-171] A81-18318 [PB81-104267] H81-14988 Satellites to aid flight safety CLBABIHG [IAF PiPEB 80-IAA-17] A81-18410 Surface analysis of bearing steels after solvent COBPLEI SISTEHS treatments. II - Lubricant-coated bearing surfaces The method of saperelements in the dynamics of [ASLE PBEPBIHT 80-LC-8A-6] A81-18748 complex structures CLKAB AIB TOBBOLEICE A81-16969 Clear air turbulence: Historical comments COHPOSITB BATEBIALS B81-14562 A resin injection technique for the fabrication of Clean air turbulence. Citations froa the aero engine composite components International Aerospace Abstracts data base [PBB-90024] B81-14004 [BASA-CB-163863] H81-15649 Constant-amplitude and flight-by-flight tests on CLEAVAGE CEBP specimens The effect of cyclic loading on the apparent [BBB-FE-2/S/POB-26] H81-14006 cleavage fracture toughness of 1Cr-Ho-V rotor Cost/benefit analysis of advanced materials steel technologies for future aircraft turbine engines A81-17488 [BASA-CB-165225] B81-15006 COCKPIT SIHOLATOBS COBPOSITE STBOCTDBES A survey of new technology for cockpit application Hingeless tailrotor in fiber composite to 1990's transport aircraft simulators construction and vibration-isolation systems [BASA-CB-159330] B81-14993 /ABIS, ASIS/ for helicopters COCEPITS [HBB-0D-311-80-0] A81-19300 757/767 design considerations for improved COBPBESSIBILITI productivity Solution of plane cascade flow using improved A81-16584 surface singularity methods application of A cockpit view of advanced airline avionics panel method to internal aerodynamics A81-16585 [BASA-TB-81589] B81-14979 A-10 SUBJECT IBDEI COHGBBSSIOHAl BEPOHIS COHPBBSSIBLB BOONDABY LAYBB Aerodynamic calculations and design of subcritical Laminae boundary layer on svept-back wings of aerofoils infinite span at an angle of attack A81-17804 A81-17656 An aerodynamic design method for transonic axial COHPBBSSIBLB FLOR flow compressor stage Inlet flow distortion in tnrbouachinery A81-17805 [ASHE P4PEB 80-GT-20J A81-17952 An optimum design procedure of total-temperature Influence of free-streaa turbalence intensity on thermocouple probes heat transfer in the two-dimensional turbulent A81-17807 boundary layer of an accelerated compressible flow The automatic matrix force nethod and techniques A81-17994 for handling aore complex computations with COHPBBSSOB BLADBS given computer capacity Becent selected papers of Northwestern A81-17815 Polytechnical Dniversity. Parts 162 Book Structural analysis of fuselages with cutouts by A81-17801 finite element method An aerodynamic design method for transonic axial A81-17816 flow compressor stage The measurement and analysis of station parameters A81-17805 of a turbojet engine Structure and decay characteristics of turbulence A81-17825 in the near- and far-wake of a moderately loaded Increasing capacity with computer-assisted compressor rotor-blade decision making airport planning [ASHE PAPEB 80-GT-95] A81-17951I A81-18080 COHPBBSSOB EFFICIENCY Airspace simulation in airport system planning The T700 booster engine AS 1-18086 A81-17506 Frequency-shaped cost functionals - Extension of COHPBBSSOB BOIOBS linear-quadratic-Gaussian design methods Comparison of experimental and computational shock A81-18578 structure in a transonic compressor rotor Performance of computer-optimized tapered-roller [ASHE PAPEB 80-GT-81] A81-17953 bearings to 2.4 million DN COHPBBSSOBS [ASHE PAPEB 80-C2/LDB-18] A81-18672 Effects of downstream distance on turbulence decay Application of the HHA design method to a for the compressor research facility low nonlinear turbofan engine multivariable conditioning system Nyquist array method [AD-A091543] N81-14276 [ NASA-CB-163855] H81-15001 Compressor configuration and design optimization COHPOTBBIZBD SIHOLATIOI for the high reliability gas turbine Airspace simulation in airport system planning [DOE/ET-15425/T1] N81-14327 A81-18086 COBPOTATIOSiL FLUID DIBASICS The rigidity and performance of a simple spiral The method of superelements in the dynamics of bevel helicopter gearbox complex structures [ASHE PAPEB 80-C2/DET-103] A81-18654 A81-16969 An analytic model of subsonic flow around an Computational Fluid Dynamics, volume 2 airflow with a spoiler [VKI-LS-1980-5-VOL-2] N81-15310 N81-14966 An economic and versatile panel method for Advanced flight deck/crew station simulator aircraft and aircraft/store configurations. An functional requirements outline of the principal features of the [NASA-CB-159331] N81-14994 mathematical modeling and numerical Aerodynamic stability analysis of NASA implementation of the British Aerospace (Rarton) J85-13/planar pressure pulse generator Hk II Panel Hethod installation H81-15311 [NASA-CB-165141] N81-15004 Vortex methods for two- and three-dimensional flov Computer Generated Imagery (CGI) current simulations technology and cost geasures feasibility study H81-15313 [AD-A091636] N81-15729 COHPOTEB PB06BAHS COICOBDE AIBCBAFT The matrix analysis of wings Concorde aerodynamics and associated systems A81-17818 development Book A computer program for the design and analysis of A81-16718 low-speed airfoils, supplement CONCBEIES [NASA-TH-81862] H81-13921 Fully bonded concrete overlay for an airport runway Development of a computer program data base of a A81-18075 navigation aid environment for siaulated IFB Sealing joints and cracks, thin resurfacing, and flight and landing studies locating voids under concrete slabs (NASA-TH-80064] S81-13959 [PB80-215635] N81-14182 Prediction of sound radiated from different COIFEBEICBS practical jet engine inlets Specialists' Heeting on Belicopter Propulsion [NASA-CB-163824] H81-14789 Systems, Rilliamsbnrg, Va., November 6-8, 1979, A system for aerodynamic design and analysis of Technical Papers supersonic aircraft. Part 3: Computer program A81-17501 description International Air Transportation Conference, New [NASA-CB-3353] H81-14971 Orleans, La., April 30-Hay 3, 1979, Proceedings. COHPOtBB SISTERS DESIGI Volumes 162 L-1011 Flight Management System design A81-18051 considerations Aviation safety:' Interior compartment materials A81-18074 [GPO-50-388] N81-13933 COHPOIEB TECHNIQUES Proceedings: Fourth Annual Workshop on A computer-based laser Doppler velocimeter Heteorological and Environmental Inputs to [DFVLB-HITT-79-14] H81-14289 Aviation systems COBPOIBBIZED DESI61 [NASA-CP-2139] N81-14555 Aerodynamic design of a ducted propeller - Computational Fluid Dynamics, volume 2 Optimization of efficiency [VKI-LS-1980-5-VOL-2] N81-15310 A81-17146 CONFIGOBATIOH HAHAGBHEiT Becent selected papers of Northwestern Bunway Configuration Hanagement system concepts Polytechnical Dniversity. Parts 162 Book A81-18089 A81-17801 COI6BESSIOSAL HEPOBTS Finite difference computation of the steady Aviation safety: Interior compartment materials transonic potential flow around airplanes [GPO-50-388] N81-13933 A81-17802 A-11 COHICAL NOZZLES SDBJECI IIDBI TestiBony of Elwood I. Driver, Vice Chairnan, COBfBBGBHT-DIVBRGEHT HOZZLES Hational Transportation Safety Board, Investigation of convergent-divergent nozzles accompanied by Gerrit J. Halhout, Chief, Human applicable to reduced-power supersonic cruise Factors Division, and Matthew H. McCormick, aircraft Senior Air Safety Investigator, Hasan Factors [HASA-TP-1766] H81-1I1972 Division CONVEYORS N81-13931 System for refurbishing and processing parachutes Testiiaony of James J. Kramer, Associate [ NASA-CASE-KSC-11012-1] B81-14967 Administrator for Aeronautics and Space COOLIBG SYSTEMS Technology, Hational Aeronautics and Space Turbine blade technology - Present and future Administration, accompanied by John H. Enders, [ ASME PAPER 80-C2/AERO-10] A81-18639 Project Manager, Aviation Safety Technology COOEDI BATES Office, John A. Parker, Chemical Research Grid generation for general three-dimensional Projects Office, NASA-Ames Research Center, and configurations Demitrius A. Konrtides, Chemical Research B81-11711 Projects Office, NASA-ARES Research Center CORHOSIOH PREVENTION N81-13935 The resistance of tank protective measures to Testimony of Richard B. Taylor, vice President and microorganisms Special Assistant to the President, and Eugene [SHIAS-801-551-107] H81-15072 A. Bara, Chief Engineer, Payloads Systems, CORROSION BBSISTAMCB Boeing commercial Airplane Company Development of high-temperature turbine subsystem N81-13936 technology to a technology readiness status, Testimony of a panel consisting of: Lloyd E. phase 2 Frisbee, Vice President, Engineering and [FE-1806-72] N81-14332 Operations, Lockheed California Company; Lyle A. COST AHALYSIS Hright, Director, Powerplant Engineering, The design-to-cost of aircraft Douglas Aircraft Company, accompanied by Doctor A81-19314 H. c. Schjelderup, Chief Technology Engineer, Aircraft engine programs employing cost objectives Materials and Process Engineering, and P. E. A81-193U6 Duskin, senior Design Engineer, Interiors Design to cost and new technologies Engineering, Douglas Aircraft Company A81-193U7 N81-13937 Microwave landing systems. Citations from the COHICAL HOZSLES Engineering Index data base . Static source locations for four nozzles mounted [PB80-8116113] H81-13917 on a J-85 engine Microwave landing systems. Citations from the [HASA-CR-152101] N81-11998 BTIS data base COHSTBAINTS [PB80-811635] N81-13918 Fundamentals of conceptual design optimization of Technological forecasting—aircraft design. subsonic transport aircraft Citations from the International Aerospace data [VTH-Lfi-292] , H81-13951 base Economic evaluation of flying-gualities design [NASA-CB-163833] S81-13957 criteria for a transport configured with relaxed Cost/benefit analysis of advanced materials static stability technologies for future aircraft turbine engines [NASA-TP-1760] H81-13968 [NASA-CB-165225] B81-15006 CO8STBOCTIOS Computer Generated Imagery (CGI) current Prestressed concrete airfield pavements technology and cost measures feasibility study A81-18063 [AD-A091636J N81-15729 COHSTBUCTIOH HATEBIALS COST EFFECTIVENESS Introduction to a rigid pavement design procedure Aviation assumptions in the eighties A81-1805U A81-18068 COHTAHIHAITS Onega - An economic Loran A replacement The wear of PTFE-containing dry bearing liners A81-18077 contaminated by fluids COST BEDDCTIOI [ASLE PREPBIHT 80-LC-6B-3] A81-18758 Productivity - The challenge of aircraft and COHTBOL BOAKDS engine maintenance A survey of new technology for cockpit application A81-17015 to 1990"s transport aircraft simulators .A-jcraft engine programs employing cost objectives [NASA-CB-159330] H81-11993 A81-19346 COHTBOL SIMULATION Design to cost and new technologies Modeling of the terminal area Air Traffic A81-19317 Management and Control COUPLED BODES A81-18085 The effect of aerodynamic coupling on the dynamics Airspace simulation in airport system planning of aircraft in fast rolling motion A81-18086 A81-17II71 COHTBOL STABILITY CRACK PROPAGATION Model-following system with assignable error The effect of cyclic loading on the apparent dynamics and its application to aircraft cleavage fracture toughness of ICc-Mo-V rotor A81-18577 steel COHTBOL SURFACES A81-17488 Analysis of unsteady pressure measurements on an Prediction methods for fatigue crack growth in aerofoil section with an harmonically aircraft material oscillating, slotted flap A81-18777 [DFVLB-FB-80-22] N81-13929 CRACKS System identification of the longitudinal motion Sealing joints and cracks, thin resurfacing, and of the DFVLB HFB 320 research aircraft with locating voids under concrete slabs particular consideration of control surface [PB80-215635] N81-1U182 effectiveness CREEP PROPERTIES [DFVLH-MITT-79-16] N81-13971 Mechanisms of damage accumulation in Active flutter suppression on an F-1F aircraft time-dependent cyclic deformation with external stores using already existing [DOE/EB-10570/1] N81-11363 control surfaces CRITERIA [MBB-FE-17/S/POB/2II] H81-13972 Landing flying qualities evaluation criteria for Aerodynamic side-force alleviator means augmented aircraft [NASA-CASE-LAR-12326-1 ] H81-1U968 [NASA-CR-163097] B81-13969 COH7ECTIOH COBREHTS CROSS FLO! Bird flight and airplane flight instruments to Vector and scalar characteristics of opposing jets measure air currents and flight characteristics discharging normally into a cross-stream [HASA-TM-75777] N81-14962 A81-17997 A-12 SDBJBCT IHDBI DISPLAY DETICBS Three-dimensional boundary layer transition via DEFLECTIOB the nechanisas of 'attachment line Leading-edge deflection optimization for a highly contamination' and 'cross floe instability* swept arrow wing configuration 181-18122 [BASA-TP-1777] B81-14974 Time dependent Havier-Stokes solution of a DELTA III6S turbulent gas jet ejected fcoa a rectangular Procedures for optimal drag design of camber and orifice into a high-subsonic crossflow flap deflection in supersonic regions with 881-14964 consideration to geometric limits Aerodynamic side-force alleviator means [DGLB PAPEB 80-110] A81-19396 [HASA-CASB-LAB-12326-1 ] H81-14968 The coordinate-deformation method in the problem CBOTSB HISSILES of a supersonic gas flow over an airfoil Cruise-missile-carrier navigation requirements delta Kings 481-18576 A81-19631 CBISTAL DISLOCATIONS Bypersonic gas flow over a delta wing Mechanisms of damage accumulation in A81-19632 time-dependent cyclic deformation Experimental study of supersonic viscous leeside [DOB/EB-10570/1] H81-14363 flow over a slender delta ving CYCLIC LOADS [HASA-TH-81248J H81-14265 The effect of cyclic loading on the apparent DBSCEBT TBAJECTOBIBS cleavage fracture toughness of ICr-Ho-V rotor Air traffic management enhancement through new steel avionics /4-D/ A81-17488 A81-16583 The stress behavior of three advanced nickel base DESIGI AIALISIS snperalloys daring high temperature low cycle Optimum selection of main parameters for the fatigue reverse design of a supersonic military aircraft [AD-A091694] H81-14061 A81-17047 Mechanisms of damage accuDulation in OK pavement design and evaluation - A new approach time-dependent cyclic deformation A81-18076 [DOE/EB-10570/1] B81-14363 Fundamentals of conceptual design optimization of Rotor model for verification of coaputation methods subsonic transport aircraft [ISD-262] H81-15467 [VTH-LB-292] . B81-13951 CILIHDBICAL BODIES Economic evaluation of flying-qualities design Aerodynamic side-force alleviator means criteria for a transport configured with relaxed [NASA-CASE-LAB-12326-1] N81-14968 static stability CILIIDBICAL SHELLS [BASA-TP-1760] N81-13968 Rind-tunnel measurements and comparison with Full potential solution of transonic guasi-3-D flight of the boundary layer and heat transfer flow through a cascade using artificial on a hollo" cylinder at Bach 3 compressability [HASA-TP-1789] B81-14975 [NASA-TH-81637] R81-14980 The resonance frequencies of ventilated wind tunnels [ABC-B/B-3841] H81-15009 DETBCTIOI DAHA6B Observing lightning from ground-based and airborne Mechanisms of danage accumulation in stations time-dependent cyclic deformation B81-14566 [DOE/EB-10570/1] H81-14363 DIFFBACTIOI PATTBBIS DABPIIG TESTS Volumetric pattern prediction of antennas on Nondestructive dynamic testing aircraft using the geoaetrical theory of A81-19657 diffraction DATA ACQDISITIOB [DFVLB-FB-80-01] B81-14195 Botor model for verification of computation methods DIFFDSBBS [ISD-262] H81-15467 Compressor configuration and design optimization DATA PBOCBSSIHG for the high reliability gas turbine Detection of moving objects Eussian book [DOE/ET-15425/T1] H81-14327 A81-18773 DIGITAL SISTEHS Statistical relationship between median visibility A new system for the study of visual information and conditions of vorstcase manmade impact on presentation in aeronautics - GIBI visibility A81-16688 [LA-BB-80-2485] H81-14550 The digital control system as part of an DATA BECOBDIIG integrated accessory fit for future engines Equipment for testing and measuring a "helmet A81-17505 mounted sight and display" system with a coupled System considerations in the implementation of movable television camera in the digital control flight-simulator for research of the DFVLB [AAS 80-032] A81-19375 [DFVLB-HITT-80-04] B81-13960 DIBEC1 LIFT COHTBOLS DATA BEDOCTIOI Theoretical investigation of the influence of A computer-based laser Doppler velocimeter spoiler dynamics on the handling qualities of an [DFVLB-HITT-79-14] H81-14289 aircraft with direct lift control DATA TBABSHISSIOB [DFVLB-FB-80-07] H81-13975 A survey of new technology for cockpit application DIBECTIOHAL COMTBOL to 1990 *s transport aircraft simulators The collision course: conditions, guidance laws [HASA-CB-159330] H81-14993 and properties DC 3 AIBCBAFT [DFVLB-FB-80-06] H81-13942 DC-to-DC power supply for light aircraft flight DISCBBIE ADDBBSS BBACOI SISCEH testing Performance evaluation of an interrogation-reply [HASA-CB-163850] H81-14989 scheduling technique for a discrete address DB 8ATCLLAID AIBCB&FT beacon system of radar surveillance and A case study in aircraft design: The de Bavilland aircraft communication in ATC family of STOL commuter aircraft Book A81-19417 A81-16717 DISPLAI DEVICES DBCISIOB BAKIHG 4 new system for the study of visual information Investment decision-making in international airports presentation in aeronautics - GIBI A81-18079 481-16688 Increasing capacity with computer-assisted An overview - 1980 generation avionic developments decision making airport planning A81-18061 481-18080 Automating airborne company communications Airport/environs plan making - Hanaging the A81-18064 planning process Avionics and displays in a future airspace system 481-18088 A81-18070 A-13 DITCHISG (LABDIBG) SDBJECT IIDEI Computer generated displays and pilot effectiveness DIIABIC BBSPOHSB A81-18082 Periodically stiffened fluid-loaded plates. I - The role of aircraft separation assurance in the Besponse to convectei harmonic pressure and free cockpit wave propagation. II - Besponse to line and A81-18092 point forces Bap-type displays for air navigation A81-17067 A81-191M3 The effects of warhead-induced damage on the The flying hologram - Latest in head-op display aeroelastic characteristics of lifting surfaces. systems Volume 1: Aeroelastic effects A81-19500 [AD-A09167U] B81-13955 Evaluation of a computer-generated perspective Experimental analysis and methods to determine the tunnel display for flight path following dynamic behavior of propulsion shafting systems [HiSA-TP-1736] , H81-13958 B81-15401 A survey of new technology for cockpit application Botor model for verification of computation methods to 1990's transport aircraft simulators [ISD-262] H81-15167 [NASA-CB-159330] B81-1Q993 DIBASIC STABILITY. DITCBIRG (IAIDI1G) Beview of engine/airframe/drive train dynamic Testing model rotorcraft for overwater operations interface development problems A81-18058 A81-17516 The problems of helicopter ditching Engine-airframe transient compatibility - Analysis A81-18071 and test Helicopter survivability in overwater situations A81-17517 A81-18081 Heave instabilities of amphibious air cushion DOBHBASH suspension systems Dowuuash calculation at close range behind a [OTIAS-2U6] B81-15156 trapezoidal wing in supersonic flow DI1AHIC.STBDCIOBAL ABALISIS [PFA-TN-AO-1661] 1181-13925 Periodically stiffened fluid-loaded plates. I - DBAS CHOTES Besponse to convected harmonic pressure and free A contribution to stabilization of flight vehicle wave propagation. II - Besponse to line and parachute systens point forces [DFVLB-HITT-80-05] H81-13926 A81-17067 DBAG BKASOBEBEBT On the steady state and dynamic performance Drag estimations for stream-line and cylindrical characteristics of floating ring bearings contour distortions on aircraft fuselages and [ASBE PAPEB 80-C2/LUB-17] A81-18671 train cars DIIABIC TESTS [DGLB PAPEB 80-116] A81- 19399 Nondestructive dynamic testing Rind-tunnel measurements and comparison with A81-19657 flight of the boundary layer and heat transfer on a hollow cylinder at Bach 3 [8ASA-TP-1789] H81-11975 DBAG BBDOCTIOI ECOSOBIC ABALISIS Transonic axisymmetric bodies with minimal wave drag Traffic forecasting for the HBIA New Biyadh A81-17018 International Airport Reduction of profile drag by blowing out through 481-18090 peg holes in areas of streamline separation Economic evaluation of flying-gnalities design bubbles criteria for a transport configured with relaxed [DGLB PAPEB 80-103] A81-19392 static stability Drag reduction through formation flight [NASA-TP-1760] N81-13968 [DGLB PAPEB 80-106] A81-19393 ECOSOBIC IBPACT Procedures for optimal drag design of canber and Aviation assumptions in the eighties flap deflection in supersonic regions.with A81-18068 consideration to geometric limits EFFECTITE PBBCBIVED BOISE LEVELS [DGLB PAPEB 80-110] A81-19396 The rating of helicopter noise: Development of a Laminar-airfoils for transport aircraft proposed impulse correction [DFVLB-BITT-80-07] N81-13952 [BPL-AC-93] H81-1U792 DBOHE &IBCBAFT EJECTIOB SEATS Aerial surveying of small areas from a small Advanced ejection seat for high dynamic pressure remotely controlled drone escape. Bind tunnel test A81-17525 [AD-A091810] 881-13940 DBOPS (LIQUIDS) ELASTOBIDBODIBABICS Fuel injector characterization studies Lubrication of rolling element bearings [8ASA-CB-165200] S81-15003 A81-18738 DOCIED FLOI ELASIOSETEBS Analysis of pressure spectra measurements in a Service life determination for the OH-60-A (DTTAS) ducted combustion system helicopter elastomeric bearings [SASA-TB-81583] N81-15768 [AD-A091756] B81-1«324 DIBASIC CHABACTBSISTICS ELECTBIC POTBBTIAL Dynamic characteristics of a high-speed rotor with DC-to-DC power supply for light aircraft flight radial and axial foil-bearing supports testing [ASBE PAPEB 80-C2/LOB-35] A81-18683 [BASA-CB-163850] B81-14989 Detection of moving objects Bussian book ELECTBIC POBEB SOPPLIES A81-18773 Solid-state power system use expands A contribution to stabilization of flight vehicle A81-19191 parachute systems ELECTBO-OPTICS [DFVLB-BITT-80-05] B81-13926 Application of optical methods to the study of jet DIH1BIC SODELS noise and turbulence Inverse problems of controlled flight dynamics - [ISL-CO-201/80] B81-15819 Longitudinal motion ELECTBOHECHABICAL DEVICES A81-16968 A case study on the F-16 fly-by-wire flight Model-following system with assignable error control system Book dynamics and its application to aircraft A81-16719 AB1-18577 BLECTBOBIC PACKAGIBG DIH1BTC PBESSUBE DC-to-DC power supply for light aircraft flight Advanced ejection seat for high dynamic pressure testing escape. Bind tunnel test [BASA-CB-163850] B81-14989 [AD-A091810] M81-13940 ELECIBOPLATIBG Prevention of spline wear by soft metallic coatings aircraft engines [AD-A091861] H81-1U06U A-11 SUBJECT IBDBI BXH10ST G1SBS EHBB6T COISBBVATIOB Improved methods for fan sound field determination Airline flight departure procedures - Choosing CHASA-CB-165188] H81-15769 between noise abatement, minimum fuel BH6ISB PABIS consumption and minimum cost Is the engine helicopter-worthy A81-17044 481-17518 Fuel conservation in the air transportation Turbine blade technology - Present and future industry - General and operational aspects [ASHE PAPEB 80-C2/AEHO-10] A81-18639 481-17143 A resin injection technique for the fabrication of EH6IBE COHTBOL aero engine composite components Digital control for helicopter powerplants [PHB-90024] H81-14004 181-17504 Cost/benefit analysis of advanced materials The digital control system as part of an technologies for future aircraft turbine engines integrated accessory fit for future engines [HASA-CB-165225] H81-15006 A81-17505 EISIBB TESTS Failure Indication and Corrective Action for Advanced transmission component development and turboshaft engines test program for helicopters A81-17515 A81-17507 Power control for hot gas engines Safety considerations for helicopter drive systems [NASA-CASE-HPO-14220-1] N81-14318 of the 1980s EH6IHB DESIGM A81-17510 Bolls-Eoyce engines status report - Development and operational flight test of the A81-17166 model 250-C28B gas turbine engine Turbopropeller engine PZL-10S &81-17512 A81-17324 Issues regarding Army turboshaft engines Specialists' Heeting on Helicopter Propulsion diagnostics and condition nonitoring Systems, Hilliamsburg, Va., November 6-8, 1979, A81-17514 Technical Papers Advanced technology turboshaft IB suppression A81-17501 A81-17519 The impact of contingency ratings on advanced A preliminary experimental investigation of the turboshaft engine design response of a turbojet engine to inlet pressure A81-17502 distortion The T700 booster engine A81-17824 A81-17506 The measurement and analysis of station parameters Drive system development for the 1980's of a turbojet engine helicopter transmissions A81-17825 A81-17508 EI?IBOB8BBT HAIASBBEIT Development of helicopter transmission components Environmental aspects of airport planning for the 1980s A81-18091 A81-17509 BBVIBOIBESt PEOTBCTIOI Helicopter propulsion system development and Airport/environs plan making - Managing the qualification planning process A81-17511 A81-18088 Is the engine helicopter-worthy EPOXI BBSIBS A81-17518 A resin injection technique for the fabrication of The measurement and analysis of station parameters aero engine composite components of a turbojet engine [PHB-90024] H81-14004 A81-17825 EBBOB AHALISIS Calculation of propeller efficiency for an ideal An optimum design procedure of total-temperature propeller thermocouple probes A81-19444 A81-17807 Advanced Technology Spark-Ignition Aircraft Piston Geometric dilution of precision in Global Engine Design Study positioning System navigation [HASA'CB-165162] N81-13963 A81-18100 Application of the HBA design method to a EBBOB COBBECTIIS DEVICES nonlinear tnrbofan engine multivariable The practical application of the Rake Blocking Nyguist array method Corrections according to Raskell for large [HASA-CB-163855] H81-15001 wind tunnel models El SI HE PAIJ.OBE [DS1B PAPEE 80-112] A81-19398 A survey of propulsion systems' EBBOB SI6BALS malfunctions/failures resulting in helicopter Hodel-following system with assignable error mishaps dynamics and its application to aircraft A81-17513 A81-18577 Failure Indication and Corrective Action for ESCAPE SISTBHS tnrboshaft engines Pyrotechnics serving safety in aircraft air A81-17515 and ground escape systems EIGIBB IILBTS A81-19348 Exhaust gas reingestion measurements in ETAIOATIOB helicopters Evaluation of a computer-generated perspective A81-17521 tunnel display for flight path following A preliminary experimental investigation of the [HASA-TP-1736] S81-13958 response of a turbojet engine to inlet pressure Landing flying qualities evaluation criteria for distortion augmented aircraft A81-17824 [BASA-CB-163097] B81-13969 Prediction of sound radiated from different BIHAOST S1SBS practical jet engine inlets Advanced technology turboshaft IB suppression [BASA-CB-163824] H81-14789 A81-17519 EHSISB BOIITOBIIS IISTBOHBBIS Exhaust gas reingestion measurements in Failure Indication and Corrective Action for helicopters turboshaft engines A81-17521 A81-17515 Organic compounds in the exhaust of a J85-5 BBSIHE IOISE turbine engine Propagation of three-dimensional acoustic [AD-A091712] S81-13966 perturbations in channels of variable Exhaust noise in flight: The role of acoustic cross'Sectional area at frequencies close to installation effects cutoff frequency [PBH-90029] N81-14793 A81-19338 Analysis of pressure spectra measurements in a ducted combustion system [HASA-TH-81583] S81-15768 A-15 EXHAUST HOSZLBS SUBJECT IIDEI EIUOST I02ZLBS Constant-amplitude and flight-by-flight tests on An evaluation of wind tunnel test techniques for CEBP specimens aircraft nozzle afterbody testing at transonic [HBB-FE-2/S/POB-26] H81-14006 Bach numbers The stress behavior of three advanced nickel base [AD-4091775] H81-13931 superalloys during high temperature lov cycle Evaluation of vind tunnel nozzle afterbody test fatigue techniques utilizing a modern twin engine [AD-A091694] B81-14061 fighter geometry at Bach numbers from 0.6 to 1.2 FAULT TOLBBABCE IF-17 aircraft A fault tolerant multiprocessor system vith [AD-A0915U5] N81-13932 reconfiguration suitable for multiaxial flight BIPLOSIVBS stabilization and trimming Tool force evaluation of lathe machined high A81-19296 explosives Validation Nethods Besearch for Fault-Tolerant [HHSHP-80-20] H81-151U8 Avionics and Control Systems Snb-Korking Group EXTEBHAL STOBES neeting. CABE 3 peer reviev Active flutter suppression on an F-4F aircraft [HASA-CP-2167] H81-15702 with external stores using already existing FEASIBILITY AHALISIS control surfaces Hicrovave landing systems, citations from the [HBB-FE-17/S/PDB/20] H81-13972 Engineering Index data base Effects of nonlinearities on ving store flutter [PB80-814643] H81-13947 [HBB-FE-17/S/P OB/27] H81-13974 Hicrovave landing systems, citations from the Transonic wind tunnel tests on an oscillating ving BUS data base with external store. Part 4: The wing vith [PB80-814635] H81-13948 underwing: store laser-Baman/Bayleigh flov diagnostic techniques [AD-A077370] H81-14969 applied to subsonic flov An economic and versatile panel nethod for (AD-A091695] B81-14275 aircraft and aircraft/store configurations. An FEEDBACK COHTBOL outline of the principal features of the Hodel-folloving system vith assignable error mathematical modeling and numerical dynamics and its application to aircraft implementation of the British Aerospace (Barton) A81-18577 Hk II Panel nethod Frequency-shaped cost functionals - Extension of H81-15311 linear-quadratic-Gaussian design methods A81-18578 System considerations in the implementation of digital control F-« AIRCRAFT [AAS 80-032] A81-19375 Application of vector performance optimization to Active flutter suppression on an F-I»F aircraft a robust control loop design for a fighter with external stores using already existing aircraft control surfaces [DFVLB-FB-80-14] H81-13970 [HBB-FE-17/S/PUB/24] H81-13972 Active flutter suppression on an F-4F aircraft FIBEB COMPOSITES with external stores using already existing Hingeless tailrotor in fiber composite control surfaces construction and vibration-isolation systems CHBB-FE-17/S/POB/24] H81-13972 /ABIS, ISIS/ for helicopters F-15 AIBCBAFI [HBB-UD-311-80-0] A81-19300 Flight evaluation of a simplified gross thrust FI6BTBB AIBCBAFT calculation technique using an FIDO turbofan Calculation of the lift dependent drag polar of engine in an F-15 airplane cambered fighter plane configurations vith [HASA-TP-1782] H81-15000 deflected maneuver flaps in the subsonic region F-16 AIRCRAFT by means of a modified procedure according to A case study on the F-16 fly-by-vire flight Lamar control system Book £DGLB PAPEB 80-109] A81-19395 A81-16719 Procedures for optimal drag design of camber and F-17 AIRCRAFT flap deflection in supersonic regions vith Evaluation of vind tunnel nozzle afterbody test consideration to geonetric limits techniques utilizing a modern tvin engine [DGLB PAPEB 80-110] A81-19396 fighter geometry at Mach numbers from 0.6 to 1.2 Industry proposes supersonic ?/STOL IF-17 aircraft A81-19490 [AD-A091545] N81-13932 Fighters for the 1990s Active control of an explosive ving-store flutter A81-19497 case Computational aerodynamic design tools and [HBB-FE-17/S/POB/25] N81-13973 techniques used at fighter development F-18 AIRCRAFT [HBB-FE-122/S/POB/13] N81-13950 F/A-18 full scale development test Constant-amplitude and flight-by-flight tests on A81-16579 CEBP specimens FAIL-SAFE SISTBHS [HBB-FE-2/S/PDB-26] H81-14006 Failure Indication and Corrective Action for FIIITB DIFFERENCE TBBOBI tnrboshaft engines Finite difference computation of the steady A81-17515 transonic potential flov around airplanes FAILURE BODES A81-17802 Lubrication of rolling element bearings FIHTE ELEHEBT BBTHOD A81-18738 The method of snperelements in the dynamics of FAB FIELDS complex structures Prediction of sound radiated from different A81-16969 practical jet engine inlets Variational principles and generalized variational [HASA-CB-163824] N81-14789 principles for the hybrid aerodynamic problem of FATIGUE (HATEEIALS) airfoil cascades on an arbitrary stream sheet of Constant-amplitude and flight-by-flight tests on revolution CEBP specimens A81-17741 [SBB-FE-2/S/POB-26] H81-1 A-16 SUBJECT ZBDBZ PLIGHT TESTS Testimony of Elwood T. Driver, Vice Chairman, FLIGHT OPTIMISATION National Transportation Safety Board, L-1011 Flight Management System design accompanied by Gerrit J. lalhoat. Chief, Hanan considerations Factors Division, and Hatthev B. BcCormick, A81-18074 Senior Air Safety Investigator, Hunan Factors Drag reduction through formation flight Division [DGLB PAPER 80-106] A81-19393 N81-13934 FLIGHT PATHS Testimony of a panel consisting of: Lloyd E. Midair and near midair collisions on two- and Frisbee, Vice President, Engineering and three-dimensional curvilinear flight paths Operations, Lockheed California Company; Lyle A. [DFVLB-FB-80-13] N81-13944 Wright, Director, Foverplant Engineering, Flight evaluation of the terminal guidance system Douglas Aircraft Company, acconpanied by Doctor [HASA-CB-163859] H81-14991 H. C. Schjelderup, Chief Technology Engineer, FLIGHT SAFETI Materials and process Engineering, and F. E. Micro-wave landing system - An operational point Duskin, Senior Design Engineer, Interiors of view Engineering, Douglas Aircraft Company A81-18055 N81r13937 RNAV benefits today - Today and future reguirements FLIGHT CHARACTERISTICS A81-180-56 Shipboard trials of the Quiet Short-Haul Research Satellites to aid flight safety Aircraft /QSHA/ [IAF PAPEB 80-IAA-17] A81-18410 A81-16581 Pyrotechnics serving safety in aircraft air History of flight testing the L-1011 Tristar jet and ground escape systems transport. I - The L-1011-1 A81-19348 A81-17976 Midair and near midair collisions on two- and Practical aerodynamics of the helicopter Hi-6A three-dimensional curvilinear flight paths Russian book CDFVLB-FB-80-13] N81-13944 181-18600 Measuring weather for aviation safety in the 1980's The collision course: Conditions, guidance lavs 081-111568 and properties Commuter airline safety [DFVLH-FB-80-06] N81-13942 [PB81-104267] K81-14988 FLIGHT COIDITIOIS Lightning. Citations from the International The microburst: Common factor in recent aircraft Aerospace abstracts data base accidents [NASA-CB-163857] N81-15648 N81-14571 FLIGHT SIMULATION Doctor Fujita's microburst analysis at Chicago Prediction methods for fatigue crack growth in N81-14572 aircraft material FLIGHT CONTROL A81-18777 The implications of current flight control Evaluation of wind tunnel nozzle afterbody test research and development techniques utilizing a modern twin engine A81-16578 fighter geometry at Mach numbers from 0.6 to 1.2 A fault tolerant multiprocessor system with YF-17 aircraft reconfiguration suitable for mnltiaxial flight [AD-A091545] N81-13932 stabilization and trimming Development of a computer program data base of a A81-19296 navigation aid environment for simulated IFB System considerations in the implementation of flight and landing studies digital control [HASA-TM-80064] N81-13959 [AAS 80-032] A81-19375 Simulator study of conventional general aviation Evaluation of a computer-generated perspective instrument displays in path-following tasks with tunnel display for flight path following emphasis on pilot-induced oscillations [NASA-TP-1736] 1181-13958 [8ASA-TP-1776] N81-14997 Landing flying qualities evaluation criteria for Computer Generated Imagery (CGI) current augmented aircraft technology and cost measures feasibility study [HASA-CH-163097] N81-13969 [AD-A091636] N81-15729 Validation Methods Besearch for Fault-Tolerant FLIGHT SIMULATORS Avionics and control Systems Sub-lorking Group Visual systems at Lufthansa's simulator centre Meeting. CARE 3 peer reviev A81-19499 [NASA-CP-2167] H81-15702 Equipment for testing and measuring a "helmet FLIGHT HAZARDS mounted sight and display" system with a coupled Collisions between aircraft and birds movable television camera in the A81-19445 flight-simulator for research of the DFVLR Aeronautical concerns and National Aeronautics and [DFVLB-HITT-80-04] N81-13960 Space Administration atmospheric electricity FLIGHT TESTS projects F/A-18 full scale development test N81-14567 A81-16579 FLIGHT IHSTBOHEBTS Head-Op-Display flight tests Flight instrumentation reguirements for A81-16582 all-weather approach and landing The PZL-Sokol - New Polish helicopter A81-18059 A81-17325 Advanced flight deck/crew station simulator Development and operational flight test of the functional requirements model 250-C28B gas turbine engine [NASA-CB-1593313 N81-14994 A81-17512 FLIGHT MECHASICS Engine-airframe transient compatibility - Analysis Inverse problems of controlled flight dynamics - and test Longitudinal motion A81-17517 A81-16968 Exhaust gas reingestion measurements in PLIGHT OPERATIOIS helicopters Problems of fligbt mechanics involved in A81-17521 all-weather helicopter operation History of flight testing the L-1011 Tristar jet A81-17467 transport. I - The L-1011-1 Micro-wave landing system - An operational point A81-17976 of view Testing model rotorcraft for overwater operations A81-18055 A81-18058 BNAV benefits today - Today and future reguirements Circulation Control ling /CCW/ flight tests A81-18056 A81-19469 The introduction of S10L and BNAV to large A status report on NASA general aviation commercial operations stall/spin flight testing A81-18057 A81-19471 The problems of helicopter ditching A81-18071 A-17 FLOfATIOI SUBJECT IIDEI Flight test investigation of IOBAH-C for en route FLOB VBLOCITT navigation in the Gulf of Bexico Vector and scalar characteristics of opposing jets [AD-A091637] 881-13945 discharging normally into a cross-stream Active flutter suppression on an F-4F aircraft A81-17997 vith external stores using already existing Analysis of unsteady pressure measurements on an control surfaces aerofoil section with an harmonically [HBB-FE-17/S/POB/24] H81-13972 oscillating, slotted flap Constant-amplitude and flight-by-flight tests on [DFTLB-FB-80-22] 881-13929 CEBP specimens FLOI TISOALIZATIOB [HBB-FE-2/S/PUB-26] U81-14006 Application of optical methods to the study of jet Assessment of ground effects on the propagation of noise and turbulence aircraft noise: The T-38A flight ezperiaent [ISL-CO-201/80] H81-15819 [NASA-TP-1747] 881-14788 FLUID FILBS DC-to-DC power supply for light aircraft flight On the steady state and dynamic performance testing characteristics of floating ring bearings [NASA-CB-163850] H81-14989 [ASHE PAPEB 80-C2/L0B-17] A81-18671 FLOTATION Surface analysis of bearing steels after solvent Testing model rotorcraft for overvater operations treatments. II - Lubricant-coated bearing surfaces A81-18058 [ASLE PHEPBIHT 80-LC-8A-6] A81-18748 The problems of helicopter ditching FLUID FLOI A81-18071 Vortex methods for two- and three-dimensional flow FLOS CHABACfEBISTICS simulations Time dependent Navier-stokes solution of a B81-15313 turbulent gas jet ejected from a rectangular FLDID PBESSOBE orifice into a high-subsonic crossflov Periodically stiffened fluid-loaded plates. I - H81-14964 Besponse to convected harmonic pressure and free FLOB DISTOBTIOS wave propagation. II - Besponse to line and Steady flow past a rectangular wing irith point forces circulation that is variable along the span A81-17067 A81-16551 FLOOBOCABBOHS A preliminary experimental investigation of the Captive carry and free flight rain erosion response of a turbojet engine to inlet pressure considerations for reinforced ablative distortion flnorocarbon radome materials A81-17824 A81-17453 Inlet flow distortion in tnrbomachinery FLOTTEB [ASflE PAPEB 80-GT-20] A81-17952 passive control of wing/store flutter Characteristics of the velocity field near a [NASA-TB-81865] H81-13922 ving-body combination located at an angle of Active flutter suppression on an F-4F aircraft attack to an oncoming supersonic flow with ezternal stores using already ezisting A81-19337 control surfaces The practical application of the Hake Blocking [BBB-FE-17/S/POB/24] H81-13972 Corrections according to Baskell for large Active control of an ezplosive wing-store flutter wind tunnel models case [DGLB PAPEB 80-112] A81-19398 [MBB-FE-17/S/POB/25] S81-13973 FLOS DISTBIBDTIOH FLDTTBB AHALISIS The supercritical profile of the supercritical wing Effects of nonlinearities on wing store flutter A81-17522 [BBB-FE-17/S/POB/27] H81-13974 The measurement and analysis of station parameters FLT BI ilBE COHTBOL of a turbojet engine A case study on the F-16 fly-by-wire flight A81-17825 control system Book The coordinate-deformation method in the problem A81-16719 of a supersonic gas flow over an airfoil FOBCB DISTBIBDTIOI delta wings The velocity induced by the wake of a wind turbine A81-19631 in a shear layer, including ground effect An investigation into grid patching technigues [FFA-TH-HO-2189-PT-3] H81-14985 881-14708 Tool force evaluation of lathe machined high FLO! BQOATIO8S explosives An investigation into grid patching techniques [BHSBP-80-20] 881-15148 881-14708 FOBBBODIBS FLOI GEOHETBI Aerodynamic side-force alleviator means Development of finite-volume methods for [NASA -CASE-LAB- 12326-1] 881-14968 three-dimensional transonic flows FOBECASTIBG [AD-A090829J 881-11986 Canada's national aviation forecasting Bodels FlOB BEASOBEBEIT A81-18072 vector and scalar characteristics of opposing jets Traffic forecasting for the HBIA Bew Biyadh discharging normally into a cross-stream International Airport 181-17997 A81-18090 FLOW STABILITY FODIDATIOBS One-dimensional considerations concerning the Probabilistic analysis of foundation forces for a stability behavior of inlet diffasers for class of unbalanced rotating machines supersonic aircraft German thesis 881-15362 A81-17548 FOOBIBB SEBIES Dialogue on bridging some gaps in stability and A pure direct force/moment control for coaxial transition research in external, internal counterrotating rotors and free-shear layer through-flow systems 881-15007 A81-18105 FBACT08E BECHA8ICS The influence of flow disturbances on the Application of fracture mechanics in designing laminar-turbulent transition in a supersonic lower wing skin of transport aircraft boundary layer A81-17049 A81-19643 FBACIDBE STRBB6TB iall cooling and the laminar-turbulent boundary The effect of cyclic loading on the apparent layer transition at supersonic flow velocities cleavage fracture toughness of ICr-Bo-V rotor A81-196UI) steel Static source locations for four nozzles aounted A81-17488 on a J-85 engine FBBB FLIGHT [HASA-CB-152401] 881-14998 Captive carry and free flight rain erosion TF34 engine compression system coiputer study considerations for reinforced ablative simulation of flow stability fluorocarbon radome materials [SASA-CB-1598893 H81-15005 A81-17453 A-18 SUBJECT ISDBX GBABS FBBE JETS Propagation of three-dimensional acoustic Effects of axisymmetric sonic nozzle geometry OD perturbations in channels of variable Hach disk characteristics cross-sectional area at frequencies close to A81-18022 cutoff frequency FBEQOEHCI BESPOISE A81-19338 Frequency-shaped cost functionals - Extension of Plane vortex gas flows emphasizing supersonic linear-quadratic-Gaussian design methods case 181-18578 181-19631 FBICTIOS GAS JETS Effects of nonlinearities on ving store flutter Time dependent Havier-Stokes solution of a [HBB-FE-17/S/POB/27] H81-1397U turbulent gas jet ejected from a rectangular FDEL COHSDBPTIOI orifice into a high-subsonic crossflow Airline flight departure procedures - Choosing H81-14964 between noise abatement, minimum fuel GAS STBEAHS consumption and minimum cost 1 vaporizing combustor with double combustion spaces A81-17044 181-17827 Fuel conservation in the air transportation GAS TOBBIHE BIGIHES industry - General and operational aspects Coatings in the aero gas turbine 181-17113 181-17167 Bolls-Boyce engines status report Joint-laboratory qualification testing of oils for 181-17166 gas turbine engines L-1011 Flight Kanagemeut System design 181-17375 considerations A simple combustor system for a small gas turbine 181-18074 engine Technological forecasting—aircraft design. A81-17503 Citations from the International Aerospace data The digital control systei as part of an base integrated accessory fit for future engines [SASl-CB-163833] K81-13957 A81-17505 The future of civil turbo-fan engines Development and operational flight test of the [PNB-90031] H81-13964 model 250-C28B gas turbine engine FUEL COHTAHIHATIOI 181-17512 The resistance of tank protective measures to Failure Indication and Corrective Iction for microorganisms turboshaft engines [SBIAS-801-551-107] H81-15072 181-17515 FUEL CORBOSIOS Advanced technology turboshaft IK suppression Formation of solid phase during the heating of jet 181-17519 fuels An experimental study on kerosene-hydrogen hybrid 181-17372 combustion in a gas turbine combustor FDEL IHJECTIOH A81-17841 A simple conbustor system for a small gas turbine Turbine blade technology - Present and future engine [ASBE PAPEB 80-C2/1EBO-10] 181-18639 181-17503 Calculated and experimental data for a 118-mm bore 1 vaporizing combustor vith doable combustion spaces roller bearing to 3 million DH 181-17827 [1SHE PAPEB 80-C2/LDB-14] A81-18668 Fttel injector characterization studies Power control for hot gas engines [H1S1-CB-165200] 1181-15003 [H1S1-CASE-HPO-14220-1] H81-14318 FUEL TASKS Improved capabilities to detect incipient bearing The resistance of tank protective measures to failures microorganisms [1D-1091687] H81-14325 [SHIAS-801-551-107] H81-1S072 Compressor configuration and design optimization FUEL TESTS for the high reliability gas turbine Comparative evaluation of the quality of jet fuels [DOE/ET-15425/T1] N81-11327 A81-17371 Gas turbine engines and transmissions for bus FOEL-AIB BATIO demonstration programs Fuel injector characterization studies CCOO-4867-07] N81-14329 [H1S1-CB-165200] N81-15003 The measurement of aero gas turbine noise POLL SCALE TESTS [PHB-90032] N81-14795 F/A-18 fall scale development test Curved centerline air intake for a gas turbine 181-16579 engine FUHCTIOiAL ABALTSIS [H1SA-CASE-LEB-13201-1] N81-14999 Frequency-shaped cost fnnctionals - Extension of Cost/benefit analysis of advanced materials linear-guadratic-Gaussian design methods technologies for future aircraft turbine engines A81-18578 [HASA-CB-165225] H81-15006 FOICIIOIS (BATBEBATICS) Compressor configuration and design optimization Dual methods and approximation concepts in for the high reliability gas turbine structural synthesis [DOE/ET-15332/T1] N81-15414 [HASl-CB-3226] H81-14347 GAS TOBBISES FUSELAGES Vector and scalar characteristics of opposing jets Structural analysis of fuselages Kith cutouts by discharging normally into a cross-stream finite element method A81-17997 181-17816 Effects of downstream distance on turbulence decay Beduction of profile drag by blowing out through for the compressor research facility low peg holes in areas of streamline separation conditioning system bubbles [1D-1091543] H81-14276 [DGLB PAPEB 80-103] 181-19392 Development of high-temperature turbine subsystem Drag estimations for stream-line and cylindrical technology to a technology readiness status, contour distortions on aircraft fuselages and phase 2 train cars [FE-1806-72] N81-14332 [DGLB PAPEB 80-116] 181-19399 GAS-SOLID IHTEBFACES Stationary displacement of a body by a shock wave A81-17622 GASEOUS ROCKET PBOPELLAITS SAS CBHOHITOGBIPHY A study of air breathing rockets - Subsonic mode Organic compounds in the exhaust of a J85-5 combustion turbine engine [IAF PAPEB 80-F-270] 181-18371 [AD-A091712] N81-13966 GEABS GAS FLO! Water content of helicopter gear oils Stationary displacement of a body by a shock wave [1SME PAPEB 80-C2/DET-12] A81-18640 A81-17622 A-19 SBNBBAL 4VIATIOH AIBCBAFT SOBJECT IHDEI A low height 2300 ki helicopter transmission with GBOOHD-AIB-GBOOHD COBBDIICATIOIS an enclosed planetary gear Automating airborne company communications [&SHE PAPEB 80-C2/DET-17] A81-186U2 A81-18064 Approximation of gear transmission error by GBUHHAH AIBCBAFT standard gear errors Development and certification of the Gulfstream III [ASHE PAPEB 80-C2/DET-71] A81-18646 A81-16587 Experience with advanced high performance gear steel The Grumman Aerospace and Gulfstrean American for CH-47 Galfstream III case study in aircraft design [ASHE PAPEB 80-C2/DET-77] A81-18648 Book The rigidity and performance of a simple spiral A81-16720 bevel helicopter gearbox GOIDAICE SEISOBS £ASBE PAPEB 80-C2/DET-103] A81-18654 Low-speed wind-tunnel tests of two weathercocking Ferrography as a health monitor and a design aid sensors for the development of helicopter gearboxes [DSBL-0171-TB] H81-14575 A81-18759 GUST LOADS Pover control for hot gas engines Aviation meteorology research and development: A . [NASA-CASE-HPO-14220-1] H81-14318 status report GEHBBAL AVIATIOI AIBCBAFT H81-14557 Development and certification of the Gnlfstreau III easts A81-16587 Clear air turbulence: Historical comnents The Grumman Aerospace and Galfstream American B81-14562 Gnlfstream III case stndy in aircraft design Book A81-16720 H A status report on NASA general aviation HABBOHIC AHALISIS stall/spin flight testing A pure direct force/moment control for coaxial A81-19471 counterrotating rotors GLASS FIBEES H81-15007 Vanadium trineodecanoate promoter for HABBOHIC EICITATIOS fiberglass-polyester soil surfacings Periodically stiffened fluid-loaded plates. I - [AD-A091785] N81-14084 Besponse to convected harmonic pressure and free SLIDERS wave propagation. II - Besponse to line and Bird flight and airplane flight instruments to point forces measure air currents and flight characteristics A81-17067 [HASA-TB-75777] N81-14962 BABHOHIC OSCILLATIOH GLOBAL POSITI01IBG SISTEH • Experimental determination of unsteady blade Seometric dilution of precision in Global element aerodynamics in cascades. Volume 2: Positioning System navigation Translation mode cascade A81-18100 [NASA-CB-165166] H81-14976 Characteristics of NATSTAB user stations HiBBIEB AIBCBAFT A81-19425 Industry proposes supersonic V/STOL GOVEBHHEHT/IHDOSTBT BELATIOSS A81-19490 The federal role in airport noise control planning BEAD-OP DISPLAYS A81-18073 Head-Op-Display flight tests An assessment of General Aviation utilization of A81-16582 advanced avionics technology The flying hologram - Latest in head-up display [HASA-CB-159328] N81-13941 systems GBAPHS (CHABTS) A81-19500 Experimental aerodynamic characteristics of two BEAT EXCHAHGEBS V/STOL fighter/attack aircraft configurations at Improved ceramic heat exchanger materials Bach numbers from 0.4 to 1.4 fHASA-CB-159678] H81-14082 [NASA-TB-81234] H81-14981 BEAT BESISTAHT ALLOTS SBKEH FOBCTIOH Becent selected papers of Northwestern A wall interference analysis in wind tunnels Polytechnical University. Parts 162 Book A81-17472 A81-17801 GEIDS The stress behavior of three advanced nickel base An investigation into grid patching techniques snperalloys during high temperature low cycle K81-14708 fatigue SBOOBD BASED COHTBOL [AD-A091694] N81-14061 The role of aircraft separation assurance in the BEAT TBABSFBB cockpit Hind-tunnel measurements and comparison with A81-18092 flight of the boundary layer and heat transfer GBOOHD EFFECT on a hollow cylinder at Bach 3 Assessment of ground effects on the propagation of [HASA-TP-1789] N81-14975 aircraft noise: The T-38A flight experiment BEAVIBG [HASA-TP-1747] M81-14788 Heave instabilities of amphibious air cushion The velocity induced by the wake of a wind turbine suspension systems in a shear layer, including ground effect [OTIAS-246] N81-15156 [FFA-TN-HO-2189-PT-3] H81-14985 BKLICAL FLOB SEODSD EFFECT (AEBODTIABICS) Botary balance data for a single-engine Determination of the effect of transverse cutouts agricultural airplane configuration for an on the hydrodynamic characteristics of a angle-of-attack range of 8 deg to 90 deg finite-span wing in the case of steady and [NASA-CB-3311] N81-13923 unsteady motion near a wall BELICOPTEB COHTBOL A81-19335 The problems of helicopter ditching Experimental investigation of a right angle wing A81-18071 with partially separated flow with and without A pure direct force/moment control for coaxial ground effects counterrotating rotors [DGLB PAPEB 80-111] A81-19397 H81-15007 GBOOHD EFFECT H&CHIHES BELICOPTEB DBS1GH Heava instabilities of amphibious air cushion Advanced Attack Helicopter /TAH-6U/ - status report suspension systems A81-16580 [OTIAS-246] N81-15156 The PZL-Sokol - Hew Polish helicopter GBOOHD SOPPOBT EQOTPHER A81-17325 Characteristics of NAVSTAB user stations SNIAS helicopters A81-19425 A81-19342 Observing lightning from ground-based and airborne stations H81-14566 A-20 SUBJECT IHDEI HOgAI fOLBBASCBS BBLICOPIBB BHGIIES Performance of computer-optimized tapered-roller Specialists' Meeting on Helicopter Propulsion bearings to 2.1 million DB Systems, Billiamsbarg, Va., Hovenber 6-8, 1979, [4SHE P4PEB 80-C2/LDB-18] 481-18672 Technical Papers HBLICOPTEB TAIL BOTOBS 481-17501 Hingeless tailrotor in fiber composite The impact of contingency ratings on advanced construction and vibration-isolation systems tnrboshaft engine design /4BIS, 4SIS/ for helicopters A81-17502 CBBB-OD-311-80-0] 481-19300 A simple conbustor system foe a small gas turbine HELICOPTEBS engine Helicopter alarms - The use of AtAT incident and 481-17503 accident record cards Digital control for helicopter poverplants 481-16689 481-17501 Exhaust gas reingestion measurements in The T700 booster engine helicopters 481-17506 481-17521 Advanced transmission conponent development and Helicopters - Help for the all weather terminal test program for helicopters 481-18065 481-17507 The rating of helicopter noise: Development of a Development of helicopter transmission components proposed impulse correction for the 1980s [HPL-AC-93] H81-11792 481-17509 HELIDH-HBOH LASBBS Helicopter propulsion system development and The Dalembertometer qualification [ISL-CO-220/79] N81-11292 481-17511 HELflET BOOSTED DISPL4IS Development and operational flight test of the Equipment for testing and measuring a "helmet model 250-C28B gas turbine engine mounted sight and display" system with a coupled 481-17512 movable television camera in the 4 survey of propulsion systems' flight-simulator for research of the DFVLB malfunctions/failures resulting in helicopter [DFVLB-HITT-80-01] H81-13960 mishaps HFB-320 AIBCB4FT 481-17513 System identification of the longitudinal motion Failure Indication and Corrective Action for of the DFVLB HFB 320 research aircraft with turboshaft engines particular consideration of control surface 481-17515 effectiveness Review of engine/airframe/drive train dynamic [DFVLB-HITT-79-16] N81-13971 interface development problems HIGH STBBHGTH STEELS 481-17516 Becent selected papers of Northwestern Engine-airframe transient compatibility - 4nalysis Polytechnical University. Parts 162 Book and test A81-17801 481-17517 HIGB TEBPBBATOBE GASES Is the engine helicopter-worthy A vaporizing combustor with double combustion spaces 481-17518 A81-17827 HELICOPTBB PEBFOBHABCE Development of high-temperature turbine subsystem The XV-15 tilt rotor research aircraft technology to a technology readiness status, 481-16588 phase 2 The PZL-Sokol - New Polish helicopter [FE-1806-72] H81-11332 481-17325 HIGH TEHPBBATOBB IBSIS Problems of flight mechanics involved in The stress behavior of three advanced nickel base all-weather helicopter operation superalloys during high temperature low cycle 48 1-17 167 fatigue General Electric infrared suppressors for the [AD-A091691] H81-11061 Black Hawk helicopter HISTOGBlflS 481-17520 Catalog of sea state and wind speed in the South Testing model rotorcraft for overwater operations Atlantic Bight 481-18058 [N4S4-CB-156872] H81-11601 Helicopter survivability in overwater situations HOLOGB4PHIC IBTEBFEBOBETBT 481-18081 Controls of aeronautical structures under fatigue Practical aerodynamics of the helicopter Hi-64 testing by holographic pulsed lasers Russian book interferometry 481-18600 [ISL-CO-218/79] N81-14300 The rigidity and performance of a simple spiral HOLOGB4PHI bevel helicopter'gearbox The flying hologram - Latest in head-up display [ASME P4PEE 80-C2/DET-103] 481-18654 systems Petrography as a health monitor and a design aid 481-19500 for the development of helicop'ter gearboxes HOBIIG 481-18759 The collision course: Conditions, guidance laws SNI4S helicopters and properties 481-193*2 [DFVLB-FB-80-06] H81-13912 HBLICOPTBB PBOPELLBB DRIVE HOBIXOHTAL OBIBHTATIOI Drive system development for the 1980's The velocity induced by the wake of a wind turbine helicopter transmissions in a shear layer, including ground effect 481-17508 [FFA-TH-HU-2189-PT-3] H81-14985 Development of helicopter transmission components HOVEBIIG for the 1980s Heave instabilities of amphibious air cushion 481-17509 suspension systems Safety considerations for helicopter drive systems [UTIAS-216] 881-15156 of the 1980s HOVEBIBG STABILITY 481-17510 4 pure direct force/moment control for coaxial Beview of engine/airframe/drive train dynamic counterrotating rotors interface development problems H81-15007 481-17516 HOHAI F4CTOBS EiGIHEEBIUG Rater content of helicopter gear oils 757/767 design considerations for improved [4SHE P4PEB 80-C2/DET-12] 481-18610 productivity 4 low height 2300 kw helicopter transmission with A81-16581 an enclosed planetary gear HOHAH TOLEBAHCES [4SHE P4PEB 80-C2/DET-17] 481-18612 Aircraft annoyance evaluations using field and Experience with advanced high performance gear steel laboratory simulation techniques for CH-47 [UTIAS-218] H81-15580 [4SHE P4PEB 80-C2/DET-77] 481-18618 A-21 BIBBID BAVIG4TIOB SISTEHS SUBJECT ISDBI fllBBID BAVIGATIOB StSTEHS IBGEStTOi (BH6IBBS) Principle for the design of hybrid control systems Exhaust gas reingestion measurements in for passenger transport systems helicopters A81-17577 A81-17521 BIDBAOLIC EQOIPHEST IBJDBIES Elimination of vibrations in aircraft piping systems Briefs of accidents involving commuter air Russian book carriers and on-demand air taxi operations, Q.S. 481-18497 General Aviation 1978 BYDSODYBAHIC COEFFICIEBT5 [PB81-101701] 881-11987 Determination of the effect of transverse cutouts HLBT FLOI on the hydrodynamic characteristics of a One-dimensional considerations concerning the finite-span ving in the case of steady and stability behavior of inlet diffusers for unsteady motion near a wall supersonic aircraft German thesis A81-19335 A81-17548 BIDBOSES EHSISES Inlet flov distortion in tnrbonachinery In experimental study on kerosene-hydrogen hybrid [ASHB PAPEB 80-GT-20J A81-17952 combustion in a gas turbine combustor Conditions of generation and methods of damping 481-178U1 the inlet vortex of a turbojet engine BIPEBSOHIC BODHDABI LilEB A81-19112 hypersonic gas flov over a delta ving IILET PBESS088 481-19632 4 preliminary experimental investigation of the BIPEBSOBIC FLOW response of a turbojet engine to inlet pressure in investigation of support-interference effects distortion [NAL-TB-622] B81-14984 481-17824 IBSPBCIIOB System for refurbishing and processing parachutes fSASA-CASE-KSC-11012-1 ] S81- 11967 ICE FOBHATIOB IBSTBOBBBT BBBOBS Aircraft icing instrumentation: Unfilled needs An optimum design procedure of total-temperature rotary wing aircraft thermocouple probes N81-14560 A81-17807 IHABB EBBABCBHEHT Approximation of gear transmission error by F-111 vindscreen machining standard gear errors [Y-2232} N81-1U995 " [ASBE PAPEB 80-C2/DBT-71J A81-18646 IHASE PBOCESSIB6 IBSTBBBEBT FLIGHT BOLES Autonomous navigation using passively sensed Development of a computer program data base of a terrain images navigation aid environment for simulated IFB 481-17977 flight and landing studies IMAGE TOBES [NASA-TH-80064] N81-13959 A new system for the study of visual information IBTAES SYSTEMS presentation in aeronautics - GIBI Effects of downstream distance on turbulence decay A81-16688 for the compressor research facility lov IHAGBBT conditioning system Computer Generated Imagery (CGI) current [AD-A091543] B81-14276 technology and cost measures feasibility study IBTEGBATED CIBCOITS [AD-A091636] B81-15729 DC-to-DC pover supply for light aircraft flight IHAGIHG TECHHIQDES testing Application of optical methods to the study of jet [NASA-CB-163850] N81-14989 noise and turbulence ISTEKBOGATIOM [ISL-CO-201/80] 881-15819 Performance evaluation of an interrogation-reply IHPACT DAHAGE scheduling technique for a discrete address The effects of varhead-induced damage on the beacon system of radar surveillance and aeroelastic characteristics of lifting surfaces. aircraft communication in ATC Volume 1: Aeroelastic effects 481-19117 [AD-A091674] N81-13955 IBVEHTOBT CO8TBOLS IB-FLIGST HOBITOBIiG Beneval function for any arbitrary period - A Flight evaluation of a simplified gross thrust Bayesian vay calculation technique nsing an F100 turbofan A81-16939 engine in an F-15 airplane IBTESTBBH1S [8AS4-rP-1782] B81-15000 Investment decision-makinq in international airports IBCOHPHESSIBLE FLOS A81-18079 Second order approximation theory of an arbitrary IBTISCID FLOI aerofoil in incompressible potential flov Nonlinear aerodynamic characteristics of a thin A81-17803 airfoil of arbitrary plane configuration Nonlinear aerodynamic characteristics of a thin A81-19629 airfoil of arbitrary plane configuration An investigation into grid patching techniques 481-19629 N81-11708 IBEBTIAL NAVIGATION Finite element analysis of inviscid subsonic Cruise-missile-carriec navigation requirements boattail flov 481-18576 [BASA-TH-81650] N81-11977 Flight test investigation of LOBAB-C for en route IBAS navigation in the Golf of Hexico Design of the new Tehran International Airport [AD-A091637] B81-13945 A81-18081 IBFIBITB SPAH HUGS Laminar boundary layer on svept-back vings of infinite span at an angle of attack 481-17656 J-85 EBGIBE 1SFBASBD IfliGBBY Organic compounds in the exhaust of a J85-5 The flying hologram - Latest in head-up display turbine engine systems [AD-A091712] B81-13966 A81-19500 Static source locations for four nozzles mounted IBFBABBD BADIATIOS on a J-85 engine Advanced technology turboshaft IB suppression [NASA-CB-152101] 881-14998 A81-17519 lerodynanic stability analysis of NASA IHFB4BED IBACKIBG J85-13/planar pressure pulse generator General Electric infrared suppressors for the installation Black Havk helicopter [BAS4-CB-165111] N81-15004 A81-17520 4-22 SUBJECT IHDBI LIGHT ilBCHAFT JET AIBCBAFT LAST BAB BOUBDABT LATEB Development and certification of the Gulfstream III Laminar boundary layer on svept-back wings of A81-16587 infinite span at an angle of attack The Grumman Aerospace and Gulfstream American A81-17656 Gulfstream III case stndy in aircraft design The influence of flow disturbances on the Book laminar-turbulent transition in a supersonic A81-16720 boundary layer JET AIHCBAPT BOISE A81-19643 Sound radiation from a finite length unflanged LAHIHAB FLOi circular duct with uniform axial flow. I - Dialogue on bridging some gaps in stability and Theoretical analysis. II - Computed radiation transition research in external, internal characteristics and free-shear layer through-flow systems A81-16712 A81-18105 Experimental investigations on shock-associated Laminar-airfoils for transport aircraft noise [ DFVLB-MITT-80-07] H81-13952 A81-17735 LAHINATES A study of multiple jets The matrix analysis of wings A81-18024 A81-17818 Propagation of three-dimensional acoustic LAHD DSE perturbations in channels of variable Investment decision-making in international airports cross-sectional area at frequencies close to A81-18079 cutoff frequency LAIDING AIDS A81-19338 Airport visual approach, guidance and landing Exhaust noise in flight: The role of acoustic systems - Airline pilots viewpoint installation effects A81-18083 [PHB-90029] N81-14793 LAHDIHG GBAB The measurement of aero gas turbine noise Today and the fatare in aircraft wheel and brake [PHB-90032] N81-14795 development JET BH6IHE FUELS A81-170U6 Comparative evaluation of the quality of jet fuels Stress measurements on landing gear for the Airbus A81-17371 A-300 B2 Formation of solid phase during the heating of jet A81-19299 fuels LASEB DOPPLEB VELOCIHETEBS A81-17372 A computer-based laser Doppler velocimeter JET BNGISES [DFVLB-HITT-79-14] 1181-14289 An evaluation of wind tunnel test techniques for LASEB IHTBHFEHOHETBI aircraft nozzle afterbody testing at transonic Controls of aeronautical structures under fatigue Hach numbers testing by holographic pulsed lasers [AD-A091775] H81-13931 interferometry Prediction of sound radiated from different [ISL-CO-218/79] H81-14300 practical jet engine inlets LATEBAl COHTBOL [HASA-CR-163824] N81-14789 Simulator study of conventional general aviation JET BIBAOST instrument displays in path-following tasks with Vector and scalar characteristics of opposing jets emphasis on pilot-induced oscillations discharging normally into a cross-stream [HASA-TP-1776] B81-14997 A81-17997 LATEBAL STABILITY Organic compounds in the exhaust of a J85-5 Leading-edge deflection optimization for a highly turbine engine swept arrow wing configuration [AD-A091712] N81-13966 [HASA-TP-1777] H81-14974 JET FLO» LATHES Static source locations for four nozzles mounted Tool force evaluation of lathe machined high on a J-85 engine explosives [NASA-CH-152M01 ] HB1-14998 [HHSMP-80-20] N81-15148 JET TBBOST LEADIHG EDGES Flight evaluation of a simplified gross thrust Experimental study of supersonic viscous leeside calculation technique using an F100 turbofan flow over a slender delta wing engine in an F-15 airplane [8ASA-TM-81248] N81-14265 [NASA-TP-1782] H81-15000 Leading-edge deflection optimization for a highly JOINTS (JOHCTIOIS) swept arrow wing configuration Sealing joints and cracks, thin resurfacing, and [HASA-TP-1777] 881-14974 locating voids under concrete slabs LIFT AOGHEBTATIOB [PB80-21563S] B81-14182 Circulation control Wing /CCW/ flight tests JOOBBAL BEABIiGS A81-19469 On the steady state and dynamic performance Downwash calculation at close range behind a characteristics of floating ring bearings trapezoidal wing in supersonic flow [ASME PAPEB 80-C2/LUB-17] A81-18671 [FFA-TH-AD-1661] 881-13925 Dynamic characteristics of a high-speed rotor with LIFT DBAS BATIO radial and axial foil-bearing supports Calculation of the lift dependent drag polar of [ASME PAPEB 80-C2/1UB-35] A81-18683 cambered fighter plane configurations with deflected maneuver flaps in the subsonic region by means of a modified procedure according to K Lamar KEBOSEHE [ DGLB PAPEB 80-109] A81-19395 An experimental study on kerosene-hydrogen hybrid LIFTING BODIES combustion in a gas turbine combustor The effects of warhead-induced damage on the A81-17841 aeroelastic characteristics of lifting surfaces. Volume 1: Aeroelastic effects [AD-A091674] N81-13955 LIFTING BOTOBS L-1011 AIBCBAFT Rind-tunnel test of an articulated helicopter Air traffic management enhancement through new rotor model with several tip shapes avionics /4-D/ [NASA-TH-80080] B81-13918 A81-16583 LIGHT AIBCBAFT History of flight testing the L-1011 Tristar jet A status report on NASA general aviation transport. I - The L-1011-1 stall/spin flight testing A81-17976 A81-19471 L-1011 Flight Management System design considerations A81-18074 A-23 LIGBTHIH6 SUBJECT IBDBX LISHTSIS6 HAIHTEHASCE Observing lightning from ground-based and airborne System for refurbishing and processing parachutes stations [BASA-CASE-KSC-11012-1] B81-14967 H81-11566 HAS MACHISE STSTEMS Aeronautical concerns and National Aeronautics and A cockpit view of advanced airline avionics Space Administration atmospheric electricity A81-16585 projects A new system for the study of visual information H81-14567 presentation in aeronautics - GIBI Lightning, citations from the International A81-16688 Aerospace abstracts data base Coupater generated displays and pilot effectiveness [NiSA-CB-163857] N81-15648 A81-18082 LIGHTSIIG SOPPBBSSIOI HAB46BBBHT PLASBIBG A case study on the P-16 fly-by-wire flight Microwave landing systems. Citations from the control system Book Engineering Index data base 481-16719 [PB80-814643] N81-13947 LIBIHGS Hicrowave landing systems. Citations froa the The near of PTPE-containing dry bearing liners NTIS data base contaminated by fluids CPB80-81463S] K81-13948 [ASLE PBEPBINT 80-LC-6B-3] A81-18758 HAIAGEBBHT SYSTEMS LOAD TESTS L-1011 Flight Management System design Performance of computer-optimized tapered-roller considerations bearings to 2.4 million ON A81-18074 [ASHE PAPEB 80-C2/LUB-18] A81-18672 Bodeling of the terminal area Air Traffic LOADS (FOBCES) Management and Control Probabilistic analysis of foundation forces for a A81-18085 class of unbalanced rotating machines Bunway Configuration Management System concepts N81-15362 A81-18089 LOHGITUDIBiL COBTBOL HABKOVBBABILITI Landing flying gualities evaluation criteria for The collision course: Conditions, guidance laws augmented aircraft and properties [NASA-CB-163097] N81-13969 [DFVLB-FB-80-06] N81-13942 Application of vector performance optimization to Theoretical investigation of the influence of a robust control loop desiga for a fighter spoiler dynamics on the handling qualities of an aircraft aircraft with direct lift control [DFVLB-FB-80-14] N81-13970 [DFVLB-FB-80-07] H81-13975 System identification of the longitudinal motion A pure direct force/moment control for coaxial of the DFVL8 HFB 320 research aircraft with counterrotating rotors particular consideration of control surface N81-15007 effectiveness HAPPING [DFVLB-MITT-79-16] N81-13971 Sap-type displays for air navigation LOHAB A81-19««3 Omega - An economic Loran A replacement BABITIBE SATELLITES A81-18077 Aeronautical-Maritime Engineering satellite /AMES/ LOBAB C program of Japan Flight test investigation of LOBAS-C for en route [IAF PAPEB 80-D-171] A81-18318 navigation in the Gulf of Mexico BASS SPECTBOSCOPT [AD-A091637] N81-13945 Organic compounds in the exhaust of a J8S-S DC-to-DC power supply for light aircraft flight turbine engine testing [AD-A091712] N81-13966 [NASA-CB-163850] N81-14989 HATBBIALS TESTS LOB SPEED Nondestructive dynamic testing A computer program for the design and analysis of A81-19657 low-speed airfoils, supplement MATHEMATICAL MODELS [NASA-TH-81862 ] N81-13921 i contribution to stabilization of flight vehicle LUBRICANT TESTS parachute systems Joint-laboratory gualification testing of oils for [DF7LB-HITT-80-05] N81-13926 gas turbine engines Service life determination for the DH-60-A (OTTAS) A81-17375 helicopter elastomeric bearings Lubrication of rolling element bearings [AD-A0917S6] N81-11321 A81-18738 An analytic model of subsonic flow around an LUBRICATING OILS airflow with a spoiler Composition of sludge formed in B-3V oil B81-14966 A81-17373 HATBICES (MATHEMATICS) Joint-laboratory qualification testing of oils for Grid generation for general three-diaensional gas turbine engines configurations A81-17375 N81-14714 Hater content of helicopter gear oils HACBIX METHODS [ASHE PAPEB 80-C2/DET-12] A81-18640 The automatic matrix force method and techniques Surface analysis of bearing steels after solvent for handling more complex computations with treatments. II - Lubricant-coated bearing surfaces given computer capacity [ASLE PB2PBINT 80-LC-8A-6] A81-18748 A81-17815 LUBRICATION Structural analysis of fuselages with cutouts by Lubrication of rolling element bearings finite element method A81-18738 A81-17816 The matrix analysis of wings A81-17818 M HAI1BOH LIKELIHOOD ESTIMATES HACB CO1ES System identification of the longitudinal notion Hypersonic gas flow over a delta wing of the DFTLB HFB 320 research aircraft with A81-19632 particular consideration of control surface HACH-ZEBNDEB IBTERFEBOHBTEBS effectiveness The Dalembertometer [DFVLB-MITT-79-16] S81-13971 [ISL-CO-220/79] N81-14292 METAL COATINGS HACBISIHG Coatings in the aero gas turbine F-111 windscreen machining A81-17167 [Y-2232] N81-14995 Prevention of spline waar by soft metallic coatings Tool force evaluation of lathe aachined high aircraft engines explosives [AD-A091861] N81-14064 [MHSMP-80-20] N81-15148 A-2» SUBJECT IBDBI NAVIGATIOI AIDS HBT1L F1TISOE Solid-state power system use expands The effect of cyclic loading on the apparent A81-19491 cleavage fracture toughness of 1Cr-Ho-v rotor Primary training of military pilots - Changing steel theories and new trainers 181-17*88 A81-19498 Prediction methods for fatigue crack growth in MILITABI A7IATIOB aircraft material Pyrotechnics serving safety in aircraft air A81-18777 and ground escape systems HBTAL SOBFACES A81-19348 Surface analysis of bearing steels after solvent Aircraft maintenance. Citations from the treatments. II - lubricant-coated bearing surfaces International Aerospace Abstracts data base [ASLE PBEPBINT 80-LC-8A-6] A81-18748 [NASA-CB-163837] N81-13917 Surface finishing HIIITABI BE1ICOETEBS [HASA-CASB-MSC-12631-3] N81-14077 Helicopter propulsion system development and BBTALLOGBAPBY gualification Ferrography as a health nonitor and a design aid A81-17511 for the development of helicopter gearboxes Issues regarding Army turboshaft engines A81-18759 diagnostics and condition monitoring HETBOBOLOGICAL JiSTBUHBNTS A81-17514 Survey of Hotkshops on Meteorological and MILITABI OPEBATIOHS Environmental Inputs to Aviation Systems Planning for and evaluating the potential of a N81-14556 land based aircraft for carrier operations Hinds and wind shear in-situ sensors A81-19470 N81-14563 MIIITABI TBCBHOLOGT Bird flight and airplane flight instruments to Advanced Attack Belicopter /IAH-64/ - status report measure air currents and flight characteristics A81-16580 [NASA-TM-75777] N81-14962 Head-Op-Display flight tests BETEOEOL06ICAL PABABETBBS A81-16582 Proceedings: Fourth Annual Horkshop on BISS DISTAHCE Heteorological and Environmental Inputs to The collision coarse: Conditions, guidance laws Aviation systems and properties [UASA-CP-2139] N81-14555 [ DFVLB-FB-80-06] S81-13942 Survey of Bookshops on Meteorological and MISSILE COBTBOL Environmental Inputs to Aviation Systems The collision course: Conditions, guidance laws N81-14556 and properties Aviation meteorology research and development: A [DFV1B-FB-80-06] N81-13942 status report •ISSUE DEFENSE H81-14557 General Electric infrared suppressors for the Federal Aviation Administration and National Black Hawk helicopter Heather Service Aviation Research and Development A81-17520 N81-14558 HISSILE LADBCHEBS Aircraft icing instrumentation: Unfilled needs Cruise-aissile-carrier navigation reguirements rotary wing aircraft A81-18576 H81-14560 BODAL BESPOISE BETBOBO1OGICAL SEHVICES Improved methods for fan sound field determination An assessment of General Aviation utilization of [NASA-CB-165188] S81-15769 advanced avionics technology BOISTOBE CONTBNT [NASA-CR-159328] N81-13941 Hater content of helicopter gear oils Measuring weather for aviation safety in the 1980's [ASME PAPER 80-C2/DET-12] A81-18640 1181-14568 MOTIBG IAEGET IBDICATOBS BICBOOBGAHSBS Detection of moving objects Bnssian book The resistance of tank protective measures to A81-18773 microorganisms HOLTIPBOCESSING (COHPOTEBS) [SNIAS-801-551-107] H81-15072 A fault tolerant multiprocessor system with BICBOWAVE LABDIK6 SYSTEMS reconfiguration suitable for multiaxial flight International Air Transportation Conference, New stabilization and trimming Orleans, la., April 30-Hay 3, 1979, Proceedings. A81-19296 Volumes 1 & 2 481-18051 Micro-wave landing system - An operational point N of view BASA PBOGRAHS A81-18055 Shipboard trials of -the Quiet Short-Haul Besearch The importance of 'Interim Standard Microwave Aircraft /QSBA/ Landing System1 for small community airports A81-16581 A81-18087 A status report on NASA general aviation Microwave landing systems. Citations from the stall/spin flight testing Engineering Index data base A81-19471 [PB80-814643] B81-13947 •ATIOBAL AVIATION STSTEB Microwave landing systems. Citations from the Canada's national aviation forecasting models NTIS data base A81-18072 [PB 80-8 14635] H81-13948 IAVIEB-STOKES EQUATION HIOAIB COLLISIONS Time dependent Bavier-Stokes solution of a Midair and near midair collisions on two- and turbulent gas jet ejected from a rectangular three-dimensional curvilinear flight paths orifice into a high-subsonic crossflow [DFV1B-FB-80-13J B81-13944 N81-14964 MILITABI AIB FACILITIES IAVIGATION AIDS Southern California aviation system study International Air Transportation Conference, New [PB 80-2 15544] N81-13916 Orleans, la., April 30-Hay 3, 1979, Proceedings. MILITARY AIBCBAFT Volumes 162 The implications of current flight control A81-18051 research and development Omega - An economic loran A replacement A81-16578 A81-18077 Optimum selection of main parameters for the Hap-type displays for air navigation reverse design of a supersonic military aircraft A81-19443 A81-17047 Development of a computer program data base of a Cruise-missile-carrier navigation reguirements navigation aid environment for simulated IFB A81-18576 flight and landing studies Design to cost and new technologies [NASA-TM-80064] N81-13959 A81-19347 A-25 BAVI6ATIOH IISTBOHEBTS SOBJECT IIDEI HAVIGATIOH INSTBOMEITS Controls of aeronautical structures under fatigue Badio navigation for aircraft: Handbook testing by holographic pulsed lasers Bussian book interferometry A81-18599 [ISL-CO-218/79] N81-14300 NAVIGATION SATELLITES IOIFLAHSABLB MATERIALS Satellites to aid flight safety Aviation safety: Interior compartment materials [ IAF PAPEB 80-IAA-17J A81-18410 [GPO-50-388] N81-13933 NAVSTAB SATELLITES Testimony of James J. Kramer, Associate Geometric dilation of precision in Global Administrator for Aeronautics and Space Positioning System navigation Technology, National Aeronautics and Space A81-18100 Administration, accompanied by John H. Enders, Characteristics of BAVSTAB user stations Project Manager, Aviation Safety Technology A81-19425 Office, John A. Parker, Chemical Besearch NICKEL ALLOTS Projects Office, NASA-Ames Besearch Center, and The stress behavior of three advanced nickel base Oemitrins A. Kourtides, Chemical Besearch superalloys daring high temperature low cycle Projects Office, NASA-AMES Besearch Center fatigae H81-13935 [AD-A091694] N81-14061 Testimony of Bichard R. Taylor, Vice President and SIGHT FLIGHTS (AIBCBAFT) Special Assistant to the President, and Eugene The flying hologram - Latest in head-up display A. Bara, Chief Engineer, Payloads Systems, systems Boeing Commercial Airplane Company A81-19500 N81-13936 BOISE (SOtJND) Testimony of a panel consisting of: Lloyd E. The Dalembertometer Frisbee, Vice President, Engineering and [ISL-CO-220/79] N81-14292 Operations, Lockheed California Company; Lyle A. NOISE HEASOBEHEHT (right. Director, Powerplant Engineering, Experimental investigations on shock-associated Douglas Aircraft Company, accompanied by Doctor noise H. C. Schjelderup, Chief Technology Engineer, A81-17735 Materials and Process Engineering, and F. E. The me&sarement of aero gas tarbine noise Duskin, Senior Design Engineer, Interiors [PBB-90032] N81-14795 Engineering, Douglas Aircraft company BOISE POLLOTIOI B81-13937 Maneuvering aircraft: Boise pollution and BOBLINB1B STSTEHS control. Citations froa the HTIS data base Application of the MNA design method to a IPB80-815566] N81-14525 nonlinear turbofan engine multivariable HOISE PBEDICTIOH (AIBCBAFT) Hyquist array method Prediction of sound radiated from different [NASA-CB-163855] N81-15001 practical jet engine inlets NOSLIBEABITI [NASA-CB-163824] N81-14789 Effects of nonlinearities on wing store flutter BOISE PBOPAGATIOI [MBB-FE-17/S/PUB/27] N81-13974 Assessment of ground effects on the propagation of IOZZLE DESIGN aircraft noise: The T-38A flight experiment One-dimensional considerations concerning the [NASA-TP-1747] H81-14788 stability behavior of inlet diffusers for Noise and noise abatement in fans and blovers: A supersonic aircraft German thesis review A81-17548 [DFVlK-FB-80-16] H81-14796 Investigation of convergent-divergent nozzles Static source locations for four nozzles mounted applicable to reduced-power supersonic cruise on a j-85 engine aircraft [BASA-CB-152401] N81-14998 [NASA-TP-1766] B81-14972 NOISE SEDUCTION NOZZLE FLO! Airline flight departure procedures - Choosing Effects of azisymmetric sonic nozzle geometry on between noise abatement, minimam fuel aach disk characteristics consumption and minimum cost A81-18022 A81-17044 A study of multiple jets A study of multiple jets A81-18024 A81-18024 NOZZLE 6EOMETBI The federal role in airport noise control planning Effects of axisymmetric sonic nozzle geometry on A81-18073 Mach disk characteristics Technological forecasting—aircraft design. A81-18022 Citations fron the International Aerospace data Static source locations for four nozzles mounted base on a J-85 engine [NASA-CB-163833] N81-13957 [SASA-CB-152401] B81-14998 Noise and noise abatement in fans and blowers: A NOHBBICAL ANALYSIS review The automatic matrix force method and techniques [DFVlB-PB-80-16] N81-14796 for handling more complex computations with Carved centerline air intake for a gas turbine given computer capacity engine A81-17815 [BASA-CASE-LEU-13201-1] N81-14999 Dual methods and approximation concepts in HOISE SPECTBA structural synthesis Experitoental investigations on shock-associated [BASA-CB-3226] B81-14347 noise HDIBBICAL CONTBOL A81-17735 Digital control for helicopter powerplants A study of multiple jets A81-17504 A81-18024 •OHEBICAL FLO! VISUALIZATION Analysis of pressure spectra measurements in a An analytic model of subsonic flow around an ducted combustion systea airflow with a spoiler [BASA-TH-81583] N81-15768 N81-14966 NOISE TOLEBABCE BIQOIST DIAGBAH The annoyance caused by noise around airports Application of the HNA design method to a [NAS4-TM-75784] N81-15579 nonlinear turbofan engine multivariable BOHDESTBOCTIVE TEStS Byguist array method Bon-destructive pavement evaluation [NASA-CB-163855] B81-15001 A81-18062 Becent developments in NDT techniques for airport pavement testing A81-18078 OIL ADDITIVES Nondestructive dynamic testing Composition of sludge formed in B-3V oil A81-19657 A81-17373 A-26 SUBJECT IHDBZ PILOT PEHFOBHABCE OMEGA BAVIGATI08 SYSTEH PABAHETEBIZATIOH Omega - An economic Loraa A replacement Economic evaluation of flying-qualities design A81-18077 criteria for a transport configured with relaxed OiBOABD EQOIPHEBT static stability Survey of Workshops on Heteorological and [HASA-TP-1760] N81-13968 Environmental Inputs to Aviation Systems PASSBSGEB ilBCBiPf N81-14556 A case study in aircraft design: The de Havilland Kinds and Hind shear in-situ sensors family of Slot commuter aircraft Book H81-11I563 A81-16717 OPEBATIOHil PBOBLEHS Principle for the design of hybrid control systems Problems of flight mechanics involved in for passenger transport systems all-weather helicopter operation A81-17577 A81-17467 The introduction of STOL and BHAV to large OPTICAL HEASOBIHS IHSTBOHEHtS commercial operations Application of optical methods to the study of jet A81-18057 noise and turbulence Canada's national aviation forecasting models [ISL-CO-201/80] H81-15819 481-18072 OPTIOAL COITBOL The role of aircraft separation assurance in the Hodel-folloving system with assignable error cockpit dynamics and its application to aircraft A81-18092 iBI-18577 PATHOLOGY Frequency-shaped cost functionals - Extension of The annoyance caused by noise around airports linear-quadratic-Gaussian design methods [HASA-TH-75784] N81-15579 A81-18578 PAVBHEHTS OPTIHIZATIOI Introduction to a rigid pavement design procedure Some aspects of optimizing the aerodynamics of A31-18054 turbine stages Non-destructive pavement evaluation A81-19325 481-18062 Computational aerodynamic design tools and Prestressed concrete airfield pavements techniques used at fighter development A81-18063 [MBB-FE-122/S/POB/13] N81-13950 Runway rehabilitation, Washington National Airport fundamentals of conceptual design optimization of 481-18066 subsonic transport aircraft Fully bonded concrete overlay for an airport runway • [VTH-LB-292] H81-13951 A81-18075 Economic evaluation of flying-qualities design OK pavement design and evaluation - A new approach criteria for a transport configured with relaxed A81-18076 static stability Recent developments in HOT techniques for [HASA-TP-1760] N81-13968 airport pavement testing Application of vector performance optimization to A81-18078 a robust control loop design for a fighter Sealing joints and cracks, thin resurfacing, and aircraft locating voids under concrete slabs [DFVLB-FB-80-14] N81-13970 [PB80-215635] N81-14182 Dual methods and approximation concepts in PEBFOBBAICE PBBDICTIO1 structural synthesis A case study in aircraft design: The de Havilland [NASA-CB-3226] N81-14347 family of STOL commuter aircraft Book OBSAHIC COHPOOMDS A81-16717 Organic compounds in the exhaust of a J85-5 Non-destructive pavement evaluation turbine engine A81-18062 [AD-A091712] N81-13966 The rigidity and performance of a simple spiral OBOGBAPHI " bevel helicopter gearbox Experimental investigation of orographic naves and [ASHE PAPEB 80-C2/DET-103] 481-18654 vertical motions in the Krasnovodsk airport area Prediction methods for fatigue crack growth in 481-19441 aircraft material OSCILLATIOSS 481-18777 Simulator study of conventional general aviation PBBFOBHANCE TBSIS instrument displays in path-following tasks with Statistical relationship between median visibility emphasis on pilot-induced oscillations and conditions of worstcase nanmade impact on [NAS4-TP-1776] S81-14997 visibility OXIDATION [L4-DB-80-2485] N81-14550 Formation of solid phase during the heating of jet Investigation of convergent-divergent nozzles fuels applicable to reduced-power supersonic cruise A81-17372 aircraft OIIDATIOB BESISTAICE [NASA-IP-1766] N81-14972 Joint-laboratory qualification testing of oils for PEBIPBEBAL JET FLOB gas turbine engines Downwash calculation at close range behind a 481-17375 trapezoidal wing in supersonic flow [PFA-TN-AO-1661] N81-13925 PEBTUBBATION THEOBI Second order approximation theory of an arbitrary PANEL BBTBOD (FLUID DIHAHICS) aerofoil in incompressible potential flow Solution of plane cascade flov using improved A81-17803 surface singularity methods application of PHOTOGBAPHIC BQDIPBBBT panel method to internal aerodynamics Bird flight and airplane flight instruments to [NASA-TH-81589] 881-14979 measure air currents and flight characteristics PARACHUTE FABRICS [NASA-TH-75777] N81-14962 System for refurbishing and processing parachutes PHYSIOLOGICAL EFFECTS [NASA-CASE-KSC-11042-1] N81-14967 The annoyance caused by noise around airports PABACBOTBS [NASA-TB-75784] N81-15579 System for refurbishing and processing parachutes PILOT PEBFOBHAHCB [NASA-CASE-KSC-11042-1] B81-14967 Avionics and displays in a future airspace system PABABETBB IDENTIFICATION 481-18070 Theoretical investigation of the influence of Computer generated displays and pilot effectiveness spoiler dynamics on the handling qualities of an 481-18082 aircraft with direct lift control Airport visual approach, guidance and landing [DFVLB-FB-80-07] N81-13975 systems - Airline pilots viewpoint 481-18083 Evaluation of a computer-generated perspective tunnel display for flight path following [N4SA-TP-1736] N81-13958 A-27 PILOT TBAIHIIG SOBJECT IBDEI Simulator study of conventional general aviation PBEESDBB OSCILLATIOBS instrument displays in path-following tasks with Analysis of unsteady pressure measurements on an emphasis on pilot-induced oscillations aerofoil section with an harmonically [8ASA-TP-1776] B81-14997 oscillating, slotted flap PILOT TBAIBIB6 [DF7LB-FB-80-22] B81-13929 Primary training of military pilots - Changing PBESTBESSISS theories and nev trainers Prestressed concrete airfield pavements 181-19498 A81-18063 Visual systems at Lufthansa's simulator centre PBODDCT DEVBLOPBBBT 481-19*99 The Grumman Aerospace and Gulfstream American PIPES (TUBES) Gulfstream III case study in aircraft design Elimination of vibrations in aircraft piping systems Book Russian book 481-16720 481-18497 The design-to-cost of aircraft PISIOH EB6IHES 481-19344 Advanced Technology Spark-Ignition Aircraft Piston Development of high-temperature turbine subsystem Engine Design Study technology to a technology readiness status, [B4S4-CB-165162] H81-13963 phase 2 PISTOIS [FE-1806-72] B81-14332 Power control for hot gas engines PBODDCTIOfl COSTS [BASA-CASB-BPO-14220-1] N81-14318 Aircraft engine programs employing cost objectives PITCH (IHCLIBATIOI) 481-19316 Landing flying' qualities evaluation criteria for PBODUCTIOB ESGIBEBBIBS augmented aircraft Design to cost and new technologies [BASA-CB-163097] H81-13969 A81-19347 PITC8IHG BOBEHTS PEOPELLAHT COHBOSTIOS Probabilistic analysis of foundation forces for a A study of air breathing rockets - Subsonic mode class of unbalanced rotating machines combustion B81-15 362 [IAF PAPEB 80-F-270] A81-18371 PLENOfl CB1BBEBS PBOPELLABT EIPLOSIOBS The resonance frequencies of ventilated wind tunnels Testimony of Elwood T. Driver, Vice Chairman, [ABC-B/li-3841] B81-15009 Bational Transportation Safety Board, POLLUTIOB COBTBOL accompanied by Gerrit J. Valhout, Chief, Human The federal role in airport noise control planning Factors Division, and Batthew B. BcCormick, A81-18073 Senior Air Safety Investigator, Human Factors Maneuvering aircraft: Boise pollution and Division control. Citations from the HTIS data base B81-1393U [PB80-815566] H81-14525 PBOPBLLEB EFFICIEHCI POLTHBB BATBIX COHPOSITE HATEBIALS Aerodynamic design of a ducted propeller - Captive carry and free flight rain erosion Optimization of efficiency considerations for reinforced ablative 481-17146 fluorocarfaon radome materials Calculation of propeller efficiency for an ideal 481-17153 propeller POLIHEBIC FILBS A81-19444 Surface finishing PBOPOLSIOB [N4S4-C4SE-HSC-12631-3] B81-11077 Bibliography of Supersonic Cruise Besearch (SCB) POLITETB4FLDOBOETHTLEBE program from 1977 to mid-1980 The wear of PTFE-containing dry bearing liners [BASA-BP-1063] B81-14973 contaminated by fluids PBOPOLSIOB SISTEB COBFI60BATIOHS [ASLE PBEPHIBT 80-LC-6B-3] A81-18758 Advanced Technology Spark-Ignition Aircraft Piston POTEBTIAL FLO! Engine Design Study Becent selected papers of Borthwestern [B4S4-CB-165162] B81-13963 Polytechnical Oniversity. Parts 162 Book Experimental analysis and methods to determine the A81-17801 dynamic behavior of propulsion shafting systems Finite difference computation of the steady B81-15401 transonic potential flow around airplanes PBOPOLSIOB SISTEB PEBFOBMABCE A81-17802 Specialists' Beeting on Helicopter Propulsion Second order approximation theory of an arbitrary Systems, Hilliamsbnrg, Va., Bovember 6-8, 1979, aerofoil in incompressible potential flow Technical Papers A81-17803 A81-17501 Aerodynamic calculations and design of subcritical Helicopter propulsion system development and aerofoils qualification A81-17801 481-17511 POBEB EFFICIEHCI A survey of propulsion systems' Some aspects of optimizing the aerodynamics of malfunctions/failures resulting in helicopter turbine stages mishaps A81-19325 A81-17513 PBECIPIIATIOB (CHEHISTBT) PBOPOLSIVE EFFICIBBCT Composition of slndge formed in B-3V oil The impact of contingency ratings on advanced 481-17373 turboshaft engine design PBEDICTIOB ABALISIS TECBHIQOES A81-17502 Service life determination for the DH-60-A (UTTAS) PBOTECTIVE COATIB6S helicopter elastomeric bearings Coatings in the aero gas turbine C4D-4091756] B81-11324 A81-17167 PEESSOBB DISTBIBOTIOB The resistance of tank protective measures to Some characteristics of subsonic flow over the microorganisms root area of a sweptback wing [SBIAS-801-551-107] B81-15072 481-19633 PBOTOBBB4BCES Analysis of unsteady pressure measurements on an An investigation of support-interference effects aerofoil section with an harmonically [B4L-TB-622] B81-14984 oscillating, slotted flap PULSED L4SEBS [DFVLB-FB-80-22] B81-13929 Controls of aeronautical structures under fatigue Transonic wind tunnel tests on an oscillating wing testing by holographic pulsed lasers with external store. Part 1: The wing with interferometry underwing: Store [ISL-CO-218/79] H81-14300 [4D-4077370] B81-14969 PTBOTECHBICS An investigation of support-interference effects Pyrotechnics serving safety in aircraft air [ BAL-TB-622 ] B81-11981 and ground escape systems 481-19348 4-28 SUBJECT IIDBI BIB6 STBOCIOBBS BEGIOHAL PLABIIiG Environmental aspects of airport planning A81-18091 Q01LITI COBTBOL BBIBFOBCED PLASTICS Coaparative evaluation of the quality of jet fuels Vanadium trineodecanoate promoter for 481-17371 fiberglass-polyester soil snrfacings Automatization of the adhesion process for [AD-A091785] H81-14084 supporting airframe parts in light contour systems BBIBFOBCBD PLATES A81-19297 Periodically stiffened fluid-loaded plates. I - Response to convected harmonic pressure and free wave propagation. II - Besponse to line and point forces RADAB B A TIG AII01 A81-17067 Hidair and near midair collisions on tvo- and RELIABILITY ABALISIS three-dimensional curvilinear flight paths iind shear systems integration plan, TICOB (visual [DFVLH-FB-80-13] H81-13944 confirmation) reliability analysis BADIATIOB SHIELDING [PB80-218233] B81-13949 General Electric infrared suppressors for the Validation Methods Research for Fault-Tolerant Black Hawk helicopter Avionics and Control Systens Sub-Working Group A81-17520 Heeting. CASE 3 peer review BADIO COHHUBICATIOB [BASA-CP-2167] B81-15702 Aeronautical-Haritime Engineering Satellite /AHES/ BELIABILITI EB6IIBEBHG program of Japan Stress measurements on landing gear for the Airbus [IAF PAPER 80-D-171] A81-18318 A-300 B2 BAPIO COITBOL A81-19299 Aerial surveying of small areas from a small An investigation of safety hazards and reliability remotely controlled drone problems in aerial refueling stores A81-17525 [AD-A091788] B81-13938 BADIO BATIGATIOB Compressor configuration and design optimization Omega - An economic Loran A replacement for the high reliability gas turbine A81-18077 [DOE/ET-15332/T1] B81-15414 Radio navigation for aircraft: Handbook BESOTS SEBSORS Eussiao book Hinds and wind shear in-situ sensors A81-18599 B81-14563 BADOBB BATEBIALS REHOtELI PILOTED VEHICLES Captive carry and free flight rain erosion Aerial surveying of small areas from a small considerations for reinforced ablative remotely controlled drone fluorocarbon radoae materials A81-17525 A81-17453 Remotely piloted vehicles. Citations from the RAIL TBABSPORTATIOI International Aerospace abstracts data base Drag estimations for stream-line and cylindrical [SASA-CB-163864] B81-14996 contour distortions on aircraft fuselages and BESCDE OPEBATIOBS train cars Sarsat - A rescue system for ships and aircraft [DGLB PAPER 80-116] A81-19399 A81-16684 BAIH BBOSIOI RESEARCH AIRCRAFT Captive carry and free flight rain erosion Shipboard trials of the Quiet Short-Haul Besearch considerations for reinforced ablative Aircraft /QSBA/ fluorocarbon radome materials A81-16581 A81-17453 RBSEABCB ABO DBVELOPBEIT BAIIAB SPECTBA The implications of current flight control Laser-Baman/Rayleigh flow diagnostic techniques research and developnent applied to subsonic flow A81-16578 [AD-A091695] H81-14275 RBSEABCH FACILITIES BASDOH PBOCESSBS Effects of downstream distance on turbulence decay Detection of moving objects Russian book for the compressor research facility low A81-18773 conditioning system RAT TRACIHG [AD-A091543] B81-14276 Volumetric pattern prediction of antennas on Advanced flight deck/crew station simulator aircraft using the geometrical theory of functional requirements diffraction [BASA-CR-159331] N81-14994 [DFVLR-FB-80-01 ] H81-1M95 BBSEABCB PROJECTS B4ILEI6H SCATTEBIBG A summary of proposals for airflight research by Laser-Baxan/Bayleigh flow diagnostic techniques the BBFT applied to subsonic flow A81-19298 CAD-A091695] B81-11I275 RESOIAHT FREQUEHCIBS BECTABGDLAB HUGS The resonance frequencies of ventilated wind tunnels Steady flow past a rectangular ling with [ABC-B/a-3841] B81-15009 circulation that is variable along the span BEHOLDS BOHBBB A81-16551 Hind-tnnnel measurements and comparison with Determination of the effect of transverse cutouts flight of the boundary layer and heat transfer on the hydrodynamic characteristics of a on a hollow cylinder at Bach 3 finite-span wing in the case of steady and [BASA-TP-1789] B81-14975 unsteady motion near a wall RIGID ROTOR HELICOPTERS A81-19335 Engine-airfraae transient compatibility - Analysis Experimental investigation of a right angle wing and test with partially separated flow with and without A81-17517 ground effects RIGID BOTORS CDGLR PAPER 80-111] A81-19397 Ringeless tailrotor in fiber composite BBDOBDABT COHPOBEBTS construction and vibration-isolation systems The automatic matrix force method and technigues /ABIS, ASIS/ for helicopters for handling more complex computations with [SBB-DD-311-80-0] A81-19300 given computer capacity RIGID STBOCTOBES A81-17815 Introduction to a rigid pavement design procedure BEFLECIBD BAVBS A81-18054 Exhaust noise in flight: The role of acoustic BUS STRUCTURES installation effects On the steady state and dynamic performance [PHR-90029] H81-14793 characteristics of floating ring bearings [ASME PAPER 80-C2AOB-17] A81-18671 A-29 BOBDSTBBSS (BATBEflATICS) SOBJECT IIOEX EOBOSTHBSS (HATHBHATICS) Fully bonded concrete overlay for an airport runway Application of vector performance optimization to A81-18075 a robust control loop design for a fighter BOHiATS aircraft Frestressed concrete airfield pavements [DFVLB-FB-80-1U] B81-13970 A81-18063 SOCKET EB6IIES OK pavement design and evaluation - A new approach A study of air breathing rockets - Subsonic oode A81-18076 combustion Bunvay Configuration Hanagement System concepts [IAF PAPEB 80-F-270] A81-18371 481-18089 BOLL The effect of aerodynamic coupling on the dynamics of aircraft in fast rolling motion A8 1-17 471 SAFETY DEVICES BOLLEH BEABUGS Pyrotechnics serving safety in aircraft air Calculated and experimental data for a 118-mm bore and ground escape systems roller bearing to 3 million DH A81-19348 [ASHE PAPBB 80-C2/IOB-11] A81-18668 SAFETY FACTOKS Performance of computer-optimized tapered-roller Safety considerations for helicopter drive systems bearings to 2.4 million DN of the 1980s [ASHE PAPER 80-C2/LUB-18] 481-18672 A81-17510 Lubrication of rolling element bearings SAFETY HABAGEHEBT A81-18738 An investigation of safety hazards and reliability BOIABT STABILITY problems in aerial refueling stores An experimental investigation of the rotating [AD-A091788] H81-13938 stall/ surge, and wake behind the rotor for a Commuter airline safety single stage axial compressor [PB81-104267] H81-14988 481-17826 SA8SAT Dynamic characteristics of a high-speed rotor with Sarsat - A rescue system for ships and aircraft radial and axial foil-bearing supports A81-16684 [ASHE PAPER 80-C2/LOB-35] A81-18683 SATELLITE BA7IGATIOB SYSTBHS BOIABT ilHS AIECBAFT Characteristics of NAVSTAB user stations Aircraft icing instrumentation: Unfilled needs A81-19425 rotary wing aircraft SATELLITE OBSEBVATIOB H81-14S60 Catalog of sea state and wind speed in the South BOTABI 0IHGS Atlantic Bight Practical aerodynamics of the helicopter Hi-6A [SASA-CB-156872] M81-14601 Russian book SADDI ABABIA A81-18600 Saudi Arabia's new Gateway Airports A loir height 2300 kf helicopter transmission with A81-18093 an enclosed planetary gear SCALE HODELS [ASHE PAPEB 80-C2/DET-17] A81-18642 Rotary balance data for a single-engine Service life determination for the OH-60-A (UTTAS) agricultural airplane configuration for an helicopter elastomeric bearings angle-of-attack range of 8 deg to 90 deg [AD-A091756] H81-14324 [BASA-CB-3311] H81-13923 A pure direct force/moment control for coaxial Active control of an explosive wing-store flutter counterrotating rotors case »81-15007 [HBB-FE-17/S/POB/25] H81-13973 BOTATING STALLS Effects of angle of attack and ventral fin on An experimental investigation of the rotating transonic flutter characteristics of an stall/ surge, and wake behind the rotor for a arrow-wing configuration single stage axial compressor [BASA-TM-81914] N81-15397 A81-17826 SCHEDOLIBG BOTOB ABBODIBAHICS Performance evaluation of an interrogation-reply An experimental investigation of the rotating scheduling technique for a discrete address stall, surge, and wake behind the rotor for a beacon system of radar surveillance and single stage axial compressor aircraft communication in ATC A81-17826 A81-19417 Practical aerodynamics of the helicopter Hi-6A SEA STATES Russian book Catalog of sea state and wind speed in the South A81-18600 Atlantic Bight Botor model for verification of computation methods [BASA-CB-156872] B81-14601 [ISD-262] H81-15167 SEALIBG BOTOB BLADES (TOBBOHACHIiEBY) Sealing joints and cracks, thin resurfacing, and Structure and decay characteristics of turbulence locating voids under concrete slabs in the near- and far-vake of a moderately loaded [PB80-215635] H81-14182 compressor rotor-blade SEPARATED FLO! [ASHE PAPEB 80-GT-95] 481-17954 Experiaental investigation of a right angle wing Botor model for verification of computation methods with partially separated flow with and without [ISD-262] H81-15467 ground effects BOTORCRAFT AIRCRAFT [DGLH PAPEB 80-111] A81-19397 Testing model rotorcraft for overvater operations Experimental study of supersonic viscous leeside A81-18058 flow over a slender delta wing BOTOBS [BASA-TH-81248] B81-14265 The effect of cyclic loading on the apparent An analytic model of subsonic flow around an cleavage fracture toughness of 1Cr-Ho-v rotor airflow with a spoiler steel M81-14966 A81-17488 in investigation of support-interference effects Dynamic characteristics of a high-speed rotor with [BAL-TB-622] N81-14984 radial and axial foil-bearing supports SERVICE LIFE [ASBE PAPER 80-C2/UJB-35] A81-18683 Service life determination for the DH-60-A (UTTAS) Mechanisms of damage accumulation in helicopter elastomeric bearings time-dependent cyclic deformation [AD-A0917S6] B81-14324 [ DOE/EH-10570/1] H81-14363 SHAFTS {HACHUB ELEHBBTSI Probabilistic analysis of foundation forces for a Improved capabilities to detect incipient bearing class of unbalanced rotating machines failures H81-15362 [AD-A091687] B81-14325 BUBSAT COBDITIOBS Runvay rehabilitation, Washington National Airport A81-18066 A-30 SOBJECT IHDBI STE1DT FLO! SBEAB LAYERS SOIIC BOOBS Dialogue on bridging sone gaps in stability and The sonic boon from an aircraft flying along an transition research in external, internal arbitrary path in a stratified atmosphere in the and free-shear layer through-flow systems presence of a three-component wind A81-18105 A81-19636 The velocity induced by the vake of a wind turbine SOBIC HOZZLES in a shear layer, including ground effect Effects of axisymmetric sonic nozzle geometry on [FFA-TN-HO-2189-PT-3] B81-14985 Hach disk characteristics SBEAE STBESS A81-18022 Beviev of theoretical and experimental results on SOOBD FIELDS three dimensional turbulent wakes and boundary Experimental investigations on shock-associated layers noise [OBEBA-BT-1980-4] 881-13930 A81-17735 SHIPS SOOBD PBESSDBE Sarsat - A rescue system for ships and aircraft Analysis of pressure spectra neasurements in a A81-16684 ducted combustion system SHOCK TESTS [ KASA-TM-81583] B81-15768 Development of high-temperature turbine subsystem SODBD iAVES technology to a technology readiness status, Sound radiation from a finite length unflanged phase 2 circular duct with uniform axial flow. I - [FE-1806-72] B81-14332 Theoretical analysis. II - Computed radiation SHOCK IAVE PBOPAGATIOB characteristics Stationary displacement of a body by a shock wave &81-16712 A81-17622 Periodically stiffened fluid-loaded plates. I - Experimental investigations on shock-associated Besponse to convected harmonic pressure and free noise wave propagation. II - Besponse to line and A81-17735 point forces Comparison of experimental and computational shock A81-17067 structure in a transonic compressor rotor Propagation of three-dimensional acoustic [ASBE PAPEB 80-GT-81] A81-17953 perturbations in channels of variable The sonic boom fron an aircraft flying along an cross-sectional area at freguencies close to arbitrary path in a stratified atmosphere in the cutoff freguency presence of a three-component wind A81-19338 A81-19636 Prediction of sound radiated from different SBOET HAUL lIBCBAPT practical jet engine inlets Shipboard trials of the Quiet Short-Haul Besearch [NASA-CB-163824] H81-14789 Aircraft /QSBA/ Improved methods for fan sound field determination A81-16581 [NASA-CB-165188] B81-15769 SHOBT TAKEOFF AIBCB&FT SPACECBAFT COBHDBICATIOH Shipboard trials of the Quiet Short-Haul Besearch Satellites to aid flight safety Aircraft /QSBA/ [IAF PAPEB 80-IAA-17] A81-18410 A81-16581 SPACBCBAFT PBOPDLSIOB A case study in aircraft design: The de Havilland A study of air breathing rockets - Subsonic mode family of STOL commuter aircraft Book combustion A81-16717 [IAF PAPEB 80-F-270] A81-18371 Turbopropeller engine PZL-10S SPABK IGHITIOB A81-1732U Advanced Technology Spark-Ignition Aircraft Piston The introduction of STOL and BBAV to large Engine Design study commercial operations [BASA-CB-165162] H81-13963 A81-18057 SPIB TESTS SBBODDED PBOPELLEBS A status report on BASA general aviation Aerodynamic design of a ducted propeller - stall/spin flight testing Optimization of efficiency A81-19471 A81-171U6 SPLIBES SIGHAL ABALYSIS Prevention of spline wear by soft metallic coatings Detection of moving objects Bnssian book aircraft engines A81-18773 [AD-A091861] N81-14064 SKII (STBDClOBAL HEBBEB) SPOILEBS Application of fracture mechanics in designing Theoretical investigation of the influence of lower wing skin of transport aircraft spoiler dynamics on the handling qualities of an A81-17049 aircraft with direct lift control SKIS FRICTIOB [DFVLB-FB-80-07] B81-13975 Hind-tunnel measurements and comparison with An analytic model of subsonic flow around an flight of the boundary layer and heat transfer airflow with a spoiler on a hollow cylinder at Bach 3 B81-14966 [BASA-TP-1789] H81-1U975 SPBAIBD COATIBGS SLEIDEB BIBGS Coatings in the aero gas turbine The determination of the induced drag on slim A81-17167 wings with high lift systems in the transonic STABILITY AUGHEUTATIOH region Economic evaluation of flying-qualities design [HBB-FE122] A81-19400 criteria for a transport configured with relaxed Nonlinear aerodynamic characteristics of a thin static stability airfoil of arbitrary plane configuration [BASA-TP-1760] B81-13968 A81-19629 STATISTICAL ANALYSIS Thin minimum-drag airfoils Statistical relationship between median visibility A81-19630 and conditions of worstcase lanmade impact on SLOTTED WIBD TOHBELS visibility The resonance freguencies of ventilated wind tunnels [LA-OB-80-2485] N81-14550 [ABC-B/S-3841] B81-15009 The annoyance caused by noise around airports SOLID PHASES [BASA-Ta-75784] B81-15579 Formation of solid phase during the heating of jet STATISTICAL DBCISIOB TBEOBT fuels Renewal function for any arbitrary period - A A81-17372 Bayesian way SOLID STATE DEVICES A81-16939 Solid-state power system use expands STEADI FLOI A81-19491 Steady flow past a rectangular wing with circulation that is variable along the span A81-16551 A-31 STIFFBESS SDBJECT IHDBX Finite difference computation of the steady Laser-Baman/Bayleigh flow diagnostic techniques transonic potential flow around airplanes applied to subsonic flow A81-17802 [AD-A091695] S81-11275 STIFFHBSS An analytic model of subsonic flow around an The rigidity and performance of a simple spiral airflow with a spoiler bevel helicopter gearbox H81-14966 [ASHE PAPEB 80-C2/DET-103] A81-18654 Finite element analysis of inviscid subsonic STIFFHBSS HATBII boattail flow The matrix analysis of wings [HASA-TH-81650] H81-14977 A81-17818 SOBSOHIC SPEED STIBLIHG CICLE Calculation of the lift dependent drag polar of Power control for hot gas engines cambered fighter plane configurations with [HASA-CASE-HPO-14220-1] N81-14318 deflected maneuver flaps in the subsonic region STOCHASTIC PROCESSES by means of a modified procedure according to Frequency-shaped cost functionals - Extension of Lanar linear-quadratic-Gaassian design methods [OGLE PAPEB 80-109] A81-19395 A81-18578 SUCTION STBESS ABALYSIS Thin minimum-drag airfoils Structural analysis of fuselages with cutouts by A81-19630 finite element method SUPERCRITICAL HIHGS 481-17816 The supercritical profile of the supercritical wing The stress behavior of three advanced nickel base A81-17522 superalloys during high temperature low cycle SDPEBSOIIC AIBCBAFT fatigue Optimum selection of main parameters for the [AD-A091694] H81-14061 reverse design of a supersonic military aircraft STUESS-STBAIH-TIHE RELATIO8S A81-17047 Bechanisms of damage accumulation in Transonic axisymmetric bodies with minimal wave drag time-dependent cyclic deformation A81-170U8 [DOE/EB-10570/1] H81-14363 One-dimensional considerations concerning the STBUCTOBAL ANALYSIS stability behavior of inlet diffusers for Experimental analysis and methods to determine the supersonic aircraft German thesis dynamic behavior of propulsion shafting systems A81-17548 H81-15401 Sukhoi's pivotal interdictor STBOCTDBAL DESIGH A81-17832 Introduction to a rigid pavement design procedure Industry proposes supersonic V/STOL A81-18054 A81-19490 SNIAS helicopters A system for aerodynamic design and analysis of A81-19342 supersonic aircraft. Part 1: General A computer program for the design and analysis of description and theoretical development low-speed airfoils, supplement [HASA-CB-3351] N81-14970 [NASA-TM-81862] N81-13921 A system for aerodynamic design and analysis of Dual methods and approximation concepts in supersonic aircraft. Part 3: Computer program structural synthesis description [NASA-CR-3226] H81-143U7 [HASA-CB-3353] N81-14971 STBOCTDBAL DESIGH CBITEBIA SDPEBSOHIC BOUBDABI LAIEBS Advanced transmission component development and The coordinate-deformation method in the problem test program for helicopters of a supersonic gas flow over an airfoil A81-17507 delta wings Safety considerations for helicopter drive systems A81-19631 of the 1980s The influence of flow disturbances on the A81-17510 laminar-turbulent transition in a supersonic Clear air turbulence: Historical comments boundary layer N81-14562 A81-19643 STRUCTURAL RELIABILITY Hind-tunnel measurements and comparison with Fully bonded concrete overlay for an airport runway flight of the boundary layer and heat transfer A81-18075 on a hollow cylinder at Bach 3 Becent developments in HDT techniques for [BASA-TP-1789] N81-14975 airport pavement testing SOPEBSOHIC CBOISE AIBCBAFT BESEABCB A81-18078 Bibliography of Supersonic Cruise Besearch (SCB) STBOCTOBAL STABILITY program from 1977 to mid-1980 On the steady state and dynamic performance [NASA-BP-1063] H81-10973 characteristics of floating ring bearings SDPEBSOHIC DIFFDSEHS [ASHE PAPEB 80-C2/LOB-17] A81-18671 One-dimensional considerations concerning the STBOCTOBAL VIBBATIOH stability behavior of inlet diffusers for Periodically stiffened fluid-loaded plates. I - supersonic aircraft German thesis Besponse to convected harmonic pressure and free A81-17548 wave propagation. II - Besponse to line and SOPKBSOHIC DBAG point forces Procedures for optimal drag design of camber and A81-17067 flap deflection in supersonic regions with On the steady state and dynamic performance consideration to geometric limits characteristics of floating ring bearings [DGLB PAPEB 80-110] A81-19396 [ASHE PAPEB 80-C2/10B-17] A81-18671 SDPEBSOSIC FLIGHT Hodel vibrations beyond low-speed stall Computational aerodynamic design tools and A81-19552 techniques used at fighter development SOBCBITICAL FLOS [HBB-FE-122/S/PUB/13J K81-13950 Aerodynamic calculations and design of subcritical SOPERSOHIC FLO! aerofoils Characteristics of the velocity field near a A81-17801 wing-body combination located at an angle of SOBSOSIC FLOB attack to an oncoming supersonic flow A study of air breathing rockets - Subsonic mode A81-19337 combustion Plane vortex gas flows emphasizing supersonic [IAF PAPEB 80-F-270] A81-18371 case Some characteristics of subsonic flow over the A81-19634 root area of a sweptback wing Downwash calculation at close range behind a A81-19633 trapezoidal wing in supersonic flow Plane vortex gas flows emphasizing supersonic [FFA-TH-AU-1661] H81-13925 case A81-19631 A-32 SUBJECT IHDJSI TBHPBB1TOBE COHTBOL SOPEBSOHIC FLDTTBB SISTBHS ESGIBEBEIH6 Experimental determination of ansteady blade The future ATC system as influenced by advanced element aerodynamics in cascades. Volume 2: avionics Translation mode cascade A81-16586 [NAS1-CH-165166 ] H81-1II976 Bicrowave landing systems. Citations from the SOPEBSOHIC IHLETS Engineering Index data base Supersonic stall flatter of high speed fans in [PB80-814643] H81-13947 turbofan engines Bicrowave landing systems. Citations from the [SASA-TB-81613] B81-14978 Nils data base SDPBBSOIIC 1IHD IOH8LS [PB80-814635] B81-139U8 Tbe influence of flow disturbances on the SISTEBS IBTBGBATIOH laminar-turbulent transition in a supersonic An overview - 1980 generation avionic developments boundary layer A81-18061 A81-19613 SISTEHS HAHAGEBBHT Rail cooling and the laminar-turbulent boundary Airport/environs plan making - Banaging the layer transition at supersonic flow velocities planning process A81-19644 A81-18088 SUPPOBT IHTBBFBREHCE STSIEBS SIHOLATIOS An investigation of support-interference effects Increasing capacity with computer-assisted [NAL-TB-622] S81-14981 decision making airport planning SOPPBESSOBS A81-18080 Advanced technology turboshaft IB suppression Bodeling of the terminal area Air Traffic A81-17519 Banagement and Control General Electric infrared suppressors for the A81-18085 Black Hawk helicopter Airspace simulation in airport system planning A81-17520 A81-18086 SORFACE COOLIHG Hall cooling and the laminar-turbulent boundary layer transition at supersonic flow velocities A81-19614 TABLES (DATA) SOBFACB DEFECTS Experimental aerodynamic characteristics of two Bunway rehabilitation. Washington National Airport V/STOL fighter/attack aircraft configurations at A81-18066 Bach numbers from 0.1 to 1.4 SDBFACE FIBISHIHG [HASA-TB-81234] H81-14981 Surface analysis of bearing steels after solvent TAKEOFF treatments. II - Lubricant-coated bearing surfaces Hind shear systems integration plan, 7ICOH (visual [ASLE PBEPBINT 80-LC-8A-6] A81-18748 confirmation) reliability analysis Surface finishing [PB80-218233] N81-13949 [HASA-CASE-BSC-12631-3] 118 1-11077 TAKEOFF BOBS SDBFACB BOOGHIESS Airline flight departure procedures - Choosing A computer program for the design and analysis of between noise abatement, minimum fuel low-speed airfoils, supplement consumption and minimum cost [8ASA-TB-81862] H81-13921 A81-17011 SDBSBS TBCBIOLOGICAL FOBECASTIIG An experimental investigation of the rotating An overview - 1980 generation avionic developments stall, surge, and wake behind the rotor for a A81-18061 single stage axial compressor Aviation assumptions in the eighties A81-17826 A81-18068 SOBVBILLAHCB BADAB Avionics and displays in a future airspace system Performance evaluation of an interrogation-reply A81-18070 scheduling technique for a discrete address Turbine blade technology - Present and future beacon system of radar surveillance and [ASHE PAPEB 80-C2/AEBO-10] A81-18639 aircraft communication in ATC Fighters for the 1990s A81-19417 A81-19497 SOSPBMSIOB STSTBHS (VEHICLES) TECHIOLOGI ASSESSBEBT Heave instabilities of amphibious air cushion The implications of current flight control suspension systems research and development [OTIAS-246] H81-15156 A81-16578 SIEPI BIHSS Head-Op-Display flight tests Laminar boundary layer on swept-back wings of A81-16582 infinite span at an angle of attack A cockpit view of advanced airline avionics 481-17656 A81-16585 Three-dimensional boundary layer transition via Today and the future in aircraft wheel and brake the mechanisms of 'attachment line development contamination1 and 'cross flow instability* A81-17016 A81-18122 fiolls-Boyce engines status report Some characteristics of subsonic flow over the A81-17166 root area of a sweptback wing TBCHBOLOSr TBABSFBB A81-19633 An assessment of General Aviation utilization of The effects of warhead-induced damage on the advanced avionics technology aeroelastic characteristics of lifting surfaces. [HASA-CB-159328] N81-13911 Volume 1: Aeroelastic effects TECHIOLOGI OTILIZATIOB [AD-A091671] 1181-13955 The future of civil turbo-fan engines Development of finite-volume methods for CPNB-90031] N81-13964 three-dimensional transonic flows TBLEVISIOS CABBBAS [AD-A090829] H81-14986 Autonomous navigation using passively sensed STBCBBOBOOS SATELLITES terrain images Aeronautical-Maritime Engineering Satellite /AHES/ A81-17977 program of Japan Eguipment for testing and measuring a "helmet [IAF PAPEB 80-D-171] A81-18318 mounted sight and display" system with a coupled S1STEH EFFECTIVENESS movable television camera in the Productivity - The challenge of aircraft and flight-simulator for research of the DFVLH engine maintenance [DFVLB-BITT-80-04] B81-13960 A81-17015 TESPEBiTOEE COITBOL Hind shear systems integration plan, VICOS (visual Advanced technology tarboshaft IB suppression confirmation) reliability analysis A81-17519 [PB80-218233] H81-13949 A-33 TBHPERATORB EFFECTS SOBJECX IIDEI TEBPBBATOBE EFFECTS THBEB DIHEHSIOBAL FLOI Formation of solid phase during the heating of jet The coordinate-deformation aethod in the problem fuels of a supersonic gas flow over an airfoil A81-17372 delta wings TEBPEBITOBE SE1SOBS A81-19631 An optimum design procedure of total-temperature Pull potential solution of transonic guasi-3-D thermocouple probes flow through a cascade using artificial &81-17807 compressability TBRHINAL BALLISTICS [HASA-TB-81637] H81-14980 The effects of warhead-induced damage on the Development of finite-volume methods for aeroelastic characteristics of lifting surfaces. three-dimensional transonic flows Volume 1: Aeroelastic effects [AD-A090829] N81-14986 [AD-A091674] N81-13955 Vortex methods for two- and three-dimensional flow TBRHIHAL FACILITIES simulations Airspace analysis in airport system planning H81-15313 A81-18052 TBBDST BEARIBSS Helicopters - Help for the all Heather terminal Dynamic characteristics of a high-speed rotor with A81-18065 radial and axial foil-bearing supports Investment decision-making in international airports [ASBE PAPEB 80-C2/LDB-35] A81-18683 A81-18079 TBDBDBBSTOBBS Design of the new Tehran International Airport The microbnrst: Common factor in recent aircraft A81-18084 accidents The importance of 'Interim Standard Hicrowave H81-14571 Landing System1 for small community airports Doctor Fujita's microburst analysis at Chicago A81-18087 N81-14572 Saudi Arabia's new Gateway Airports Lightning. Citations from the International A81-18093 Aerospace abstracts data base TERSIHAL GUIDANCE [NASA-CB-163857] N81-15648 Flight evaluation of the terminal guidance system TILT BOTOB RESEARCH AIBCB1FT PBOGRAH [NASA-CR-163859] H81-1M991 The XV-15 tilt rotor research aircraft Applicated techniques for the control of approach A81-16588 traffic TIBS DEPEHDEBCE [DFVLB-BITT-79-20] H81-11992 Time dependent Havier-stokes solution of a TEBRAIN ABALISIS turbulent gas jet ejected from a rectangular Autonomous navigation using passively sensed orifice into a high-subsonic crossflow terrain images N81-14964 A81-17977 TOPOLOGI TBBBAIR FOLLOWING AIRCRAFT Component-adaptive grid embedding Sukhoi's pivotal interdictor N81-14697 A81-17832 TOBQDE TEST EQOIPBBIT Hind-tunnel test of an articulated helicopter Equipment for testing and measuring a "helmet rotor model with several tip shapes mounted sight and display11 system with a coupled CHASA-TH-80080] H81-13918 movable television camera in the TBACKIHG (POSITIOH) flight-simulator for research of the DFVLR Simulator study of conventional general aviation [DFVLR-BITT-80-04] N81-13960 instrument displays in path-following tasks with IF-31 ESCIHE emphasis on pilot-induced oscillations TF34 engine compression system computer study [NASA-IP-1776] ' N81-14997 simulation of flow stability TRAILING EDGES [HASA-CB-159889] H81-15005 Structure and decay characteristics of turbulence TBEBBAL COHTBOL COATIBGS in the near- and far-wake of a moderately loaded Cost/benefit analysis of advanced materials compressor rotor-blade technologies for future aircraft turbine engines [ASHE PAPEB 80-GT-95] A81-17954 [NASA-CR-165225] N81-15006 Downwash calculation at close range behind a TBERHAL STABILITY trapezoidal wing in supersonic flow Joint-laboratory qualification testing of oils for [ FFA-TH-AU-1661] H81-13925 gas turbine engines TRAILIHG-EDGB FLAPS A81-17375 The determination of the induced drag on slim TSEBBOCOOPLES wings with high lift systems in the transonic An optimum design procedure of total-temperature region thermocouple probes [MBB-FE122] A81-19400 481-17807 THAIHIH6 AIRCRAFT TBEBHODTBAHIC PBOPEBTIES Primary training of military pilots - Changing Time dependent Navier-Stokes solution of a theories and new trainers turbulent gas jet ejected from a rectangular A81-19498 orifice into a high-subsonic crossflow TBAIBIBG DEVICES H81-14964 Visual systems at Lufthansa's simulator centre • TBERHOPLASTIC BESIHS A81-19499 A resin injection technique for the fabrication of TRAJECTORI OPTIHIZATIOU aero engine composite components Evaluation of a computer-generated perspective [PHR-90024] N81-14004 tunnel display for flight path following IBIS nses [BASA-TP-1736] N81-13958 Determination of the effect of transverse cutouts TBABSITIOI FLOi on the hydrodynamic characteristics of a Dialogue on bridging some gaps in stability and finite-span wing in the case of steady and transition research in external, internal unsteady motion near a wall and free-shear layer through-flow systems A81-19335 A81-18105 TBBEE DIHEHSIOSAL BODIDABI LAIEB TRABSLATIOHAL BOTIOH Three-dimensional boundary layer transition via Experimental determination of unsteady blade the mechanisms of 'attachment line element aerodynamics in cascades. Volume 2: contamination* and 'cross flow instability1 Translation mode cascade A81-18122 [BASA-CB-165166] N81-14976 Review of theoretical and experimental results on Probabilistic analysis of foundation forces for a three dimensional turbulent wakes and boundary class of unbalanced rotating machines layers H81-15362 [ONEBA-HT-1980-4] N81-13930 TBAISBISSIOBS (BACBIHE ELEBEBTS) Advanced transmission component development and test program for helicopters A81-17507 A-3« SUBJECT IHDEI TOBBOF1B EHGIIBS Drive system development for the 1980's A survey of nev technology for cockpit application helicopter transmissions to 1990's transport aircraft simulators A81-17508 [HASA-CB-159330] B81-14993 Development of helicopter transmission components Advanced flight deck/crew station simulator for the 1980s functional requirements A81-17509 [NASA-CB-159331J B81-14994 Hater content of helicopter gear oils TBAHSPOBTATIOB BBTBOBKS [ASHE PAPER 80-C2/DET-12] A81-18610 A new perspective in aviation systems planning A low height 2300 kf helicopter transmission vith &81-18069 an enclosed planetary gear TRAPEZOIDAL BIB6S [&SHE PAPER 80-C2/DET-17] A81-186IJ2 Dovnvash calculation at close range behind a Approximation of gear transmission error by trapezoidal wing in supersonic flow standard gear errors [FFA-TS-AU-1661] N81-13925 [ASHE PAPER 80-C2/DET-71] A81-186U6 TOBBISE BLADES Experience vith advanced high performance gear steel Tariational principles and generalized variational for CH-47 principles for the hybrid aerodynamic problem of [ASHE PAPEB 80-C2/DET-77] A81-18618 airfoil cascades on an arbitrary stream sheet of Gas turbine engines and transmissions for bus revolution demonstration programs A81-17741 [COO-<4867-07] H81-1U329 Turbine blade technology - Present and future TBABSOfXC COHPBESSOBS [ASBE PAPEB 80-C2/AERO-10] A81-18639 Comparison of experimental and computational shock TDBBIME ESGIBBS structure in a transonic compressor rotor Helicopter propulsion system development and [ASHE PAPEB 80-GT-81] A81-17953 qualification TBABSOHIC FLIGHT A81-17511 Transonic axisymmetric bodies Kith minimal wave drag TBBBISE iHEELS A81-17048 Comparison of experimental and computational shock The determination of the induced drag on slim structure in a transonic compressor rotor wings vith high lift systems in the transonic [ASBE PAPEB 80-GT-81] A81-17953 region TOBBIHES [H8B-FE122] A81-19400 Some aspects of optimizing the aerodynamics of An evaluation of vind tunnel test techniques for turbine stages aircraft nozzle afterbody testing at transonic A81-19325 Haeh numbers TDBBOCOHPBESSOBS [AD-A091775] N81-13931 An aerodynamic design method for transonic axial TBABSOHIC FLOB flow compressor stage The supercritical profile of the supercritical wing A81-17805 A81-17522 A preliminary experimental investigation of the Finite difference computation of the steady response of a turbojet engine to inlet pressure transonic potential flow around airplanes distortion A81-17802 A81-17824 An aerodynamic design method for transonic axial An experimental investigation of the rotating flow compressor stage stall, surge, and vake behind the rotor for a A81-17805 single stage axial compressor Component-adaptive grid embedding A81-17826 H81-14697 Inlet flow distortion in turbomachinery An investigation into grid patching techniques [ASBE PAPEB 80-GT-20] A81-17952 B81-14708 Comparison of experimental and computational shock Transonic vind tunnel tests on an oscillating wing structure in a transonic compressor rotor vith external store. Part 4: The ving with [ASHE PAPER 80-GT-81] A81-17953 underving: Store Structure and decay characteristics of turbulence [AD-A077370] H81-1<1969 in the near- and far-wake of a moderately loaded Full potential solution of transonic quasi-3-D compressor rotor-blade flow through a cascade using artificial [ASBE PAPER 80-GT-95] A81-17954 compressability Supersonic stall flutter of high speed fans in [NASA-TB-81637] B81-14980 turbofan engines A method for obtaining shockless transonic flows [BASA-TB-81613] 881-14978 past airfoils, partially modified from a given Aerodynamic stability analysis of NASA arbitrary airfoil J85-13/planar pressure pulse generator [B&L-TB-602T] B81-14983 installation Development of finite-volume methods for [BASA-CR-1651U1] N81-15004 three-dimensional transonic flows TF34 engine compression system computer study [AD-A090829] B81-14986 simulation of flow stability TBAHSOHIC FLUTTER [BASA-CB-159889] B81-15005 Effects of angle of attack and ventral fin on Compressor configuration and design optimization transonic flutter characteristics of an for the high reliability gas turbine arrow-wing configuration [DOE/ET-15332/T1] B81-15414 [HASA-TB-81914] H81-15397 TDBBOFA8 AIBCBAFT TBABSOBIC BIBD TOiiELS Sukhoi's pivotal interdictor Further investigations of adaptive-wall wind tunnels A81-17832 [AP-A09177U] N81-13977 TOBBOFAH EHGIHES TBABSPOBT AIRCRAFT Bolls-Royce engines status report Principle for the design of hybrid control systems A81-17166 for passenger transport systems The future of civil turbo-fan engines A81-17577 [PSfl-9003!»] N81-13961 Fundamentals of conceptual design optimization of Supersonic stall flutter of high speed fans in subsonic transport aircraft turbofan engines [VTH-LB-292] N81-13951 [BASA-TB-81613] H81-1U978 Laminar-airfoils for transport aircraft Flight evaluation of a simplified gross thrust [DFVLB-HITT-80-07] H81-13952 calculation technique using an F100 turbofan Economic evaluation of flying-qualities design engine in an F-15 airplane criteria for a transport configured vith relaxed [BASA-TP-1782] H81-15000 static stability Application of the BBA design method to a [HASA-TP-1760] B81-13968 nonlinear tnrbofan engine multivariable Theoretical investigation of the influence of Byquist array method spoiler dynamics on the handling qualities of an [BASA-CB-163855] H81-15001 aircraft vith direct lift control Improved methods for fan sound field determination [DFVLH-FB-80-07] B81-13975 [HASA-CB-165188] N81-15769 A-35 IORBOFAHS SUBJECT IHDSI TUBBOFANS TOBBOLEHT JETS TF34 engine compression system computer study Application of optical methods to the study of jet simulation of flow stability noise and turbulence [NASA-CB-159889] N81-15005 [ISL-CO-201/80] B81-15819 TOBBOJBT EH6IHB COBTBOL TOBBOLB8T RAKES Application of the UNA design method to a An experimental investigation of the rotating nonlinear turbofan engine multivariable stall, surge, and wake behind the rotor for a Hyguist array method single stage axial compressor [HASA-CB-163855] B81-15001 A81-17826 TDEBOJBT EBGIBBS Structure and decay characteristics of turbulence Bolls-Boyce engines status report in the near- and far-wake of a moderately loaded 181-17166 compressor rotor-blade A preliminary experimental investigation of the [ASHE PAPEB 80-GT-95] A81-17954 response of a turbojet engine to inlet pressure Beview of theoretical and experimental results on distortion three dimensional turbulent wakes and boundary A81-17824 layers The measurement and analysis of station parameters [OHEBA-NT-1980-4] H81-13930 of a turbojet engine The velocity induced by the wake of a wind turbine 481-17825 in a shear layer, including ground effect Conditions of generation and methods of damping [FFA-TH-HD-2189-PT-3] B81-14985 the inlet vortex of a turbojet engine TIO DIMENSIONAL BODBDABY LATEB 481-19442 Influence of free-stream turbulence intensity on TDBBOHACBIHB BLADES heat transfer in the two-dimensional turbulent Supersonic stall flutter of high speed fans in boundary layer of an accelerated compressible flow turbofan engines A81-17994 [NASA-TM-81613] H81-14978 TIO DIHEISIONAL FLOB Solution of plane cascade flow using improved Plane vortex gas flows emphasizing supersonic surface singularity methods application of case panel method to internal aerodynamics A81-19634 [NASA-TH-81589] N81-14979 An analytic model of subsonic flow around an Full potential solution of transonic guasi-3-D airflow with a spoiler flow through a cascade using artificial B81-14966 compressability [NASA-TH-81637] N81-14980 Aerodynamic stability analysis of NASA u j85-13/planar pressure pulse generator OB-601 HBLICOPTBfi installation General Electric infrared suppressors for the [NASA-CB-165111] N81-15004 Black Hawk helicopter TOBBOPBOP BBGIBES A81-17520 Turbopropeller engine PZL-10S DBIFOBB PLOB A81-17324 Sound radiation from a finite length unflanged lOBBOSBAFTS circular duct with uniform axial flow. I - The impact of contingency ratings on advanced Theoretical analysis. II - Computed radiation turboshaft engine design characteristics A81-17502 A81-16712 Issues regarding Army tnrboshaft engines UBBAH PLABBIBG diagnostics and condition monitoring Community participation in airport planning AS 1-17 514 A81-18067 TURBULENCE DBBAB TBABSPOBTATIOS Time dependent Navier-Stokes solution of a A new perspective in aviation systems planning turbulent gas jet ejected from a rectangular A81-18069 orifice into a high-subsonic crossflow Gas turbine engines and transmissions for bus N81-1496M demonstration programs TOEBOLEST BOOHDABY LATEB [COO-4867-07] N81-14329 Influence of free-stream turbulence intensity on OSEB SANDALS (COHPUTEB PBOGBiHS) heat transfer in the two-dimensional turbulent A system for aerodynamic design and analysis of boundary layer of an accelerated compressible flow supersonic aircraft. Part 2: User's manual A81-17994 [NASA-CB-3352] N81-13920 The influence of flow disturbances on the DSEB BEQOIBBBEHTS laminar-turbulent transition in a supersonic BNAV benefits today - Today and future requirements boundary layer A81-18056 A81-19643 Beview of theoretical and experimental results on three dimensional turbulent wakes and boundary layers V/STOL AIBCBAFT [ONEBA-NT-1980-4] N81-13930 Industry proposes supersonic V/STOL TUEBULEHT PLOW A81-19490 Dialogue on bridging some gaps in stability and Experimental aerodynamic characteristics of two transition research in external, internal V/STOL fighter/attack aircraft configurations at and free-shear layer through-flow systems Hach numbers from 0.4 to 1.4 A81-18105 [NASA-TB-81234] N81-14981 Plane vortex gas flows emphasizing supersonic VALUE EHGIBEEBIN6 case Aircraft engine programs employing cost objectives A81-19634 A81-19346 Effects of downstream distance on turbulence decay VABADIDH COHPOOBDS for the compressor research facility low Vanadium trineodecanoate promoter for conditioning system fiberglass-polyester soil snrfacings [AD-A091543] N81-14276 [AD-A091785] H81-14084 Time dependent Navier-Stokes solution of a VAPOUZIBG turbulent gas jet ejected from a rectangular A vaporizing combustor with double combustion spaces orifice into a high-subsonic crossflow A81-17827 N81-14964 VARIABLE SHEEP BIBGS TUBBULEHT BEAT TBANSPEB Sukhoi's pivotal interdictor Influence of free-stream turbulence intensity on A81-17832 heat transfer in the two-dimensional turbulent boundary layer of an accelerated compressible flow A81-17994 4-36 SUBJECT ISDBI •HO (HBTBOBOLOGI) TABIATIORAL PBINCIPLES Experimental study of supersonic viscous leeside Variational principles and generalized variational flow over a slender delta wing principles foe the hybrid aerodynamic problem of [SASA-TH-81248] N81-14265 airfoil cascades on an arbitrary strean sheet of Vortex methods for two- and three-dimensional flow revolution simulations A81-17741 B81-15313 VECTOR ANALYSIS Application of vector performance optimization to a robust control loop design for a fighter w aircraft •AKES [DFVLB-FB-80-14] H81-13970 The practical application of the Rake Blocking VELOCITY DISTBIBOTIOS Corrections according to Baskell for large Characteristics of the velocity field near a wind tunnel models King-body combination located at an angle of [DGLB PAPEB 80-112] A81-19398 attack to an oncoming supersonic flow BALL FLOI A81- 19337 A wall interference analysis in wind tunnels VENTILATION PASS A81-17472 Boise and noise abatement in fans and blowers: A The practical application of the Bake Blocking review Corrections according to Haskell for large [DFVLB-FB-80-16] N81-14796 wind tunnel models VBBTICAL AIB CUBBBITS [DGLB PAPEB 80-112] A81-19398 Experimental investigation of orographic waves and 1ABIISG SISTEHS vertical motions in the Krasnovodsk airport area Helicopter alarms - The use of ALAT incident and A81-19441 accident record cards VIBBATION DAHPING A81-16689 Elimination of vibrations in aircraft piping systems •1BPA6B Russian boo* P-111 windscreen machining A81-18497 [1-2232] 881-14995 Passive control of wing/store flutter WATBB LAHDISG [HASA-TH-81865] N81-13922 Helicopter survivability in overwater situations TIBBATI01 EFFECfS A81-18081 Beview of engine/airframe/drive train dynamic IATBB IAVES interface development problems Catalog of sea state and vind speed in the South A81-17516 Atlantic Bight Engine-airframe transient compatibility - Analysis [NASA-CB-156872] N81-14601 and test WAVE DIFPHACTIOS A81-17517 Exhaust noise in flight: The role of acoustic VIBBATION ISOLATOBS installation effects Hingeless tailrotor in fiber composite [PNB-90029] N81-14793 construction and vibration-isolation systems •ATE DBAG /ABIS, ASIS/ for helicopters Transonic axisymmetric bodies with minimal wave drag [MBB-OD-311-80-0] A81-19300 A81-17048 VIBBATI01 TESTS •ATE PBOPAGATION Becent developments in HOT techniques for Becent developments in HOT techniques for airport pavement testing airport pavement testing A81-18078 A81-18078 Nondestructive dynamic testing 8BAPON SISTEBS A81-19657 Advanced Attack Helicopter /YAH-64/ - status report VISCOSITY A81-16580 Time dependent Navier-Stokes solution of a •BAB turbulent gas jet ejected from a rectangular Improved capabilities to detect incipient bearing orifice into a high-subsonic crossflow failures N81-14964 [AD-A091687] N81-14325 VISIBILITY •BAB INHIBITORS Statistical relationship between median visibility Prevention of spline wear by soft metallic coatings and conditions of worstcase maamade impact on aircraft engines visibility [AD-A091861] N81-14064 [LA-OB-80-2485] N81-14550 •BAB TESTS VISUAL AIDS The wear of PTFE-containinq dry bearing liners Visual systems at Lufthansa's simulator centre contaminated by fluids A81-19U99 [ASLE PBEPBINT 80-LC-6B-3] A81-18758 VISDAl FLIGHT Ferrography as a health monitor and a design aid Airport visual approach, guidance and landing for the development of helicopter gearboxes systems - Airline pilots viewpoint A81-18759 A81-18083 Prevention of spline wear by soft metallic coatings Nidair and near midair collisions on two- and aircraft engines three-dimensional curvilinear flight paths [AD-A091861] 1181-14064 [DFVLB-FB-80-13] N81-13944 REATBEB VISUAL PBBCBPTIOB Heasuring weather for aviation safety in the 1980's A new system for the study of visual information N81-14568 presentation in aeronautics - GIBI IBATBBB FORECASTING A81-16688 Federal Aviation Administration and National VOLTAGE COBVEBTEBS (DC TO DC) leather Service Aviation Besearch and Development DC-to-DC power supply for light aircraft flight N81-14558 testing •BATHBB STATIOBS [BASA-CB-163850] N81-14989 Federal Aviation Administration and National VOBTBI 4VOIDASCE Heather Service Aviation Besearch and Development Conditions of generation and methods of damping N81-14558 the inlet vorter of a turbojet engine WEIGHT (BASS) A81-19442 Current aircraft survey (approach speeds, gross VOHTEI SHEETS weights, and Dimensions) Nonlinear aerodynamic characteristics of a thin [PB80-225691] N81-13956 airfoil of arbitrary plane configuration HID (HBTEOBOLOSI) A81-19629 Experimental investigation of orographic waves and VOBTICK5 vertical motions in the Krasnovodsk airport area Plane vortex gas flows emphasizing supersonic A81-19441 case iinds and wind shear in-situ sensors A81-19634 N81-14563 A-37 BIHD DIBECTIOH SUBJECT IIDEI BIHD DIEECTIOB The practical application of the Bake Blocking Lou-speed Hind-tunnel tests of two weathercocking Corrections according to Haskell for large sensors wind tunnel models [WSBL-0171-TSJ H81-1457S CDGLE PAPEH 80-112] A81-19398 •IHD EFFECTS Further investigations of adaptive-wall wind tunnels The sonic boom from an aircraft flying along an [AD-A091774] H81-13977 arbitrary path in a stratified atmosphere in the The resonance frequencies of ventilated wind tunnels presence of a three-cooponent wind [ARC-B/S-3841] H81-15009 A81-19636 BIRD IOHHELS BUD SHEAR A computer-based laser Doppler velocimeter Hinds and wind shear in-situ sensors [DFVLB-HITT-79-14] H81-14289 H81-14563 II ID TELOCIir The oicroburst: Common factor in recent aircraft Catalog of sea state and wind speed in the South accidents Atlantic Bight H81-14571 [HASA-CH-156872] H81-14601 Doctor Fujita's microborst analysis at Chicago BIHDHILLS (BIHDPOBKBED BACHIIES) H81-14572 Botor model for verification of computation methods Clean air turbulence. Citations from the [ISD-262] H81-15467 International Aerospace Abstracts data base BIIDPOBBB OTILIZATIOH [HASA-CB-163863] H81-15649 Botor model for verification of computation methods BIHD TDDBEL APPARATUS [ISD-262] H81-15467 A vaporizing coobustor with double combustion spaces IIIDSHIELDS A81-17827 P-111 windscreen machining BIHD TDHHEL HODELS [T-2232] H81-14995 The practical application of the Hake Blocking HUG LOADIHG Corrections according to naskell for large Circulation Control ding /CCW/ flight tests wind tunnel models A81-19469 [DGLR PAPER 80-112] A81-19398 Effects of nonlinearities on wing store flutter Hodel vibrations beyond low-speed stall [HBB-FE-17/S/POB/27] H81-13974 A81-19552 Transonic wind tunnel tests on an oscillating wing BIHD TDHHEL STABILITY TESTS with external store. Part 4: The wing with Low-speed wind-tunnel tests of two weathercocking underwing: Store sensors [AD-A077370] H81-14969 [BSRL-0171-TM] N81-14575 BUG OSCILLATIOHS BIHD TOHHEL TESTS The method of superelements in the dynamics of Hodel vibrations beyond low-speed stall complex structures A81-19552 A81-16969 Some characteristics of subsonic flow over the BUS PLAHFOBHS root area of a sweptback wing Honlinear aerodynamic characteristics of a thin A81-19633 airfoil of arbitrary plane configuration Hind-tunnel test of an articulated helicopter A81-19629 rotor model with several tip shapes Thin minimum-drag airfoils [HASA-TM-80080] H81-13918 A81-19630 Passive control of wing/store flutter Laminar-airfoils for transport aircraft [HASA-TM-81865] N81-13922 [DFVLE-BITT-80-07] H81-13952 Botary balance data for a single-engine BUG PROFILES agricultural airplane configuration for an The supercritical profile of the supercritical wing angle-of-attack range of 8 deg to 90 deg A81-17522 [NASA-CB-3311] H81-13923 Stationary displacement of a body by a shock wave An evaluation of wind tunnel test technigues for A81-17622 aircraft nozzle afterbody testing at transonic The matrix analysis of wings flach numbers A81-17818 [AD-A091775] H81-13931 Some characteristics of subsonic flow over the Evaluation of wind tunnel nozzle afterbody test root area of a sweptback wing techniques utilizing a modern twin engine A81-19633 fighter geometry at Hach numbers from 0.6 to 1.2 Development of finite-volume methods for IF-17 aircraft three-dimensional transonic flows [AD-A091545] N81-13932 [AD-A090829] H81-14986 Advanced ejection seat for high dynamic pressure BIBS BOOTS escape. Rind tunnel test Some characteristics of subsonic flow over the [AD-A091810] H81-13940 root area of a sweptback wing Active control of an explosive wing-store flutter A81-19633 case BUG SLOTS [HBB-FE-17/S/POB/25] H81-13973 Determination of the effect of transverse cutouts Laser-Raman/Bayleigh flow diagnostic techniques on the hydrodynamic characteristics of a applied to subsonic flow finite-span wing in the case of steady and [AD-A091695] H81-14275 unsteady motion near a wall Transonic wind tunnel tests on an oscillating wing A81-19335 with external store. Part 4: The wing with BIHG SPAH underwing: store Steady flow past a rectangular wing with [AD-A077370] H81-14969 circulation that is variable along the span Hind-tunnel measurements and comparison with A81-16551 flight of the boundary layer and heat transfer HIHGS on a hollow cylinder at Hach 3 Application of fracture mechanics in designing [HASA-TP-1789] H81-14975 lower wing skin of transport aircraft Experimental aerodynamic characteristics of two A81-170H9 V/STOL fighter/attack aircraft configurations at BOBKLOADS (PSICHOPBISIOLOGT) Bach numbers from 0.4 to 1.4 BHAY benefits today - Today and future requirements [HASA-TS-81234] H81-14981 A81-18056 An investigation of support-interference effects [HAL-TB-622] H81-14984 Development of finite-volume methods for three-dimensional transonic flows IV-15 AIBCBAFT [AD-A090829] U81-14986 The XV-15 tilt rotor research aircraft BIHD TOHHEL BALLS A81-16588 A wall interference analysis in wind tunnels A81-17472 A-38 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 134) APRIL 1981 Typical Personal Author Index Listing PERSONAL AUTHOR COIE. 6. 1. I I Simulating stud; of the interaction between the A8TIS. G. I. propulsion and flight control systems of a Airspace analysis in airport system planning subsonic lift fan VIOL A81-18052 [HASA-Ig-81239] H81-110*3 ABAI, B. An experimental study on kerosene-hydrogen hybrid combustion in a gas turbine combustor 1 A81-17841 NASA TITLE REPORT ABBHDTS, F. J. NUMBER ACCESSION Constant-amplitude and flight-by-flight tests on NUMBER CEBP specimens (SBB-FE-2/S/POB-26] N81-14006 ABGIBT.S, J. B. Listings in this index are arranged a'lphabetically by personal author. The title Rotor model for verification of computation methods of the document provides the user with a brief description of the subject matter. [ISD-262] 881-15467 The report number helps to indicate the type of document cited (e.g.. NASA ABBAOD, J. L. Controls of aeronautical structures under fatigue report, translation. NASA contractor report}. The accession number is located testing by holographic pulsed lasers beneath and to the right of the title, e.g. N81-11043. Under any one author's interferometry name the accession numbers are arranged in sequence with the IAA accession [ISL-CO-218/79] N81-14300 numbers appearing first. ABTABOHOV, L. I. Practical aerodynamics of the helicopter Bi-6A A81-18600 ASTAFBV, 7. A. Formation of solid phase during the heating of jet ADABCZTK, J. fuels Full potential solution of transonic quasi-3-D A81-17372 flow through a cascade using artificial ATTA, E. B. compressability Component-adaptive grid embedding [UASA-TH-81637] N81-14980 H81-14697 ADABCZIK, J. J. ATTEID6E. A. G. Inlet flow distortion in turbomachinery Is the engine helicopter-worthy [ASBE PAPER 80-GT-20] A81-17952 A81-17518 Supersonic stall flutter of high speed fans AOPOII, B. [HASA-TB-81613] 1181-14978 Review of theoretical and experimental results on ADA8S, J. J. three dimensional turbulent wakes and boundary Simulator study of conventional general aviation layers instrument displays in path-following tasks with [ONERA-NT-1980-4] N81-13930 emphasis on pilot-induced oscillations [HASA-TP-1776] H81-14997 ADDI, A. L. B Effects of axisymmetric sonic nozzle geometry on BACHALO, i. D. Bach disk characteristics Fuel injector characterization studies A81-18022 [HASA-CH-165200] 881-15003 ADICOFF, A. BAILEI, B. Vanadium trineodecanoate promoter for Landing flying qualities evaluation criteria for fiberglass-polyester soil surfacings augmented aircraft [AD-A091785] H81-14084 [HASA-CB-163097] N81-13969 AICBEB, I. BAIBO, G. 1. Rotor model for verification of computation methods Recent developments in NOT techniques [ISD-262] N81-15467 A81-18078 4LBK, F. BAKDT, P. A. Controls of aeronautical structures under fatigue Detection of moving objects testing by holographic pulsed lasers A81-18773 interferometry BABCHE. J. [ISL-CO-218/79] N81-14300 A wall interference analysis ALCOBTA, J. A. A81-17472 Improved capabilities to detect incipient bearing BARESBBBG, B. J. failures Fully bonded concrete overlay for an airport runway [AD-A091687] N81-14325 A81-18075 ALEKSEEV, H. A. BABKEB, B. B. Hall cooling and the laminar-turbulent boundary Introduction to a rigid pavement design procedure layer transition at supersonic flow velocities A81-18054 A81-19644 BAB1ETT, B. E. ALLEi, B. E. Surface analysis of bearing steels after solvent Turbine blade technology - Present and future treatments. II - Lubricant-coated bearing surfaces [ASBE PAPER 80-C2/AEBO-10] A81-18639 [ASLE PREPRINT 80-LC-8A-6] A81-18748 ALRAHG. J. B. BAROi. A. Engine-airframe transient compatibility - Analysis Aerodynamic design of a ducted propeller - and test Optimization of efficiency A81-17517 A81-17146 AHDEBSOI, I. J. BATTLES. B. A. Dynamic characteristics of a high-speed rotor vith Development of helicopter transmission components radial and azial foil-bearing supports for the 1980s [ASBE PAPER 80-C2/LOB-35] A81-18683 A81-17509 B-1 BiOEB, K. PBBSOIAL AOIHOB ISDEI BAUBB. S. BBAHHAH. B. B. InflaeDce of free-stream turbulence intensity on The wear of PTFE-containing dry bearing liners heat transfer in the two-dimensional turbulent contaminated by fluids boundary layer of an accelerated compressible flow CASLE PBEPBIHT 80-LC-6B-3] A81-18758 A81-1799U BBISKS. I. B. BBiTII, A. J. F/A-18 full scale development test Micro-wave landing system - An operational point A81-16579 of view BBITTLE, C. A81-18055 Airspace analysis in airport system planning BBISHAKBB, P. B. A81-18052 Investment decision-Baking in international airports BBOOKS, 1. A81-18079 The impact of contingency ratings on advanced BBLOTSEBKOVSKII. S. B. turboshaft engine design Nonlinear aerodynamic characteristics of a thin A81-17502 airfoil of arbitrary plane configuration The T700 booster engine A81-19629 A81-17506 BBHBAB. P. E. BBOIB. D. P. Productivity - The challenge of aircraft and Low-speed wind-tunnel tests of two weathercocking engine maintenance sensors A81-17045 [BSBL-0171-TS] H81-11575 BEHTLBI. L. B. BBOIB, B. J. The measurement of aero gas turbine noise F-111 windscreen machining [PSB-90032] N81-14795 [1-2232] N81-10995 BBB6BBOH, B. P. BBOBBB, 6. Development of a computer program data base of a SNIAS helicopters navigation aid environment for simulated IFB A81-19312 flight and landing studies BBIKIHA, I. G. [UASA-TH-8006II ] H81-13959 Laminar boundary layer on swept-back wings of BEBHSTBIH. B. L. infinite span at an angle of attack The stress behavior of three advanced nickel base A81-17656 superalloys during high temperature low cycle BOCCI, B. fatigue Performance evaluation of an interrogation-reply [AD-A091694] N81-11061 scheduling technique for a discrete address BEBBIEB, B. L. beacon system Investigation of convergent-divergent nozzles A81-19<417 applicable to reduced-power supersonic cruise BODD, L. D. aircraft An investigation of safety hazards and reliability [HASA-TP-1766] H81-14972 problems in aerial refueling stores BEBBI. B. F. [AD-A091788] N81-13938 The rating of helicopter noise: Development of a BOLL, J. 0. proposed impulse correction Advanced ejection seat for high dynamic pressure [NPL-AC-93] S81-1U792 escape. Bind tunnel test BEBBI, J. 0. [AD-A091810] H81-13910 Hind-tunnel test of an articulated helicopter BOBCBAB, F. B.. JB. rotor model with several tip shapes Flight evaluation of a simplified gross thrust [NASA-TH-80080] H81-13918 calculation technique using an F100 turbofan BEBDBE, B. A. engine in an F-15 airplane BNAV benefits today - Today and future reguirements [HASA-TP-1782] H81-15000 A81-18056 BOBEE?A, B. B. BHAITACBABIA, D. 0. Joint-laboratory qualification testing of oils for Beneval function for any arbitrary period - A gas turbine engines Bayesian vay A81-17375 A81-16939 BOBKE, J. D. 'BIEBTDEHPEL. E. The Gossamer Condor and Albatross: A case study in Equipment for testing and measurin1 g a "helmet aircraft design mounted sight and display' system vith a coupled [AV-B-80/5<10] A81-16721 movable television camera in the BOBBOBS, L. T. flight-simulator for research of the DFVLB A survey of propulsion systems' tDFVLB-HITT-80-04] H81-13960 malfunctions/failures resulting in helicopter BIHDEB. S. mishaps Experience vith advanced high performance gear steel A81-17513 [ASHE PAPEB 80-C2/DET-77] A81-18648 BOIBAOB, 0. BIPPES. B. Stress measurements on landing gear for the Airbus Experimental investigation of a right angle wing A-300 B2 with partially separated flow with and without A81-19299 ground effects [DELS PAPEB 80-111] A81-19397 BLAIDOB, C. J. The introduction of STOL and BHAV to large CAI, I. commercial operations The matrix analysis of wings • A81-18057 A81-17818 BOCK, S.-B. CAIHE, 0. A. Drag reduction through formation flight Digital control for helicopter powerplants [DGLB PAPEB 80-106] A81-19393 A81-17504 BOEHIG, F. B. CABP, D. B. Compressor configuration and design optimization Proceedings: Fourth Annual workshop on for the high reliability gas turbine aeteorological and Environmental Inputs to [DOE/ET-15*25/11 ] H81-11327 Aviation systems BOIKO, L. V. [HASA-CP-2139] H81-1U555 Composition of sludge formed in B-3T oil Survey of Borkshops on aeteorological and A81-17373 Environmental Inputs to Aviation Systems BOICB, L. H81-1«556 Probabilistic analysis of fonndation forces for a CAHPBELL, B. class of unbalanced rotating machines Saudi Arabia's new Gateway Airports B81-15362 A81-18093 BOILS, D. CABACEBA, F. The flying hologram - Latest in head-up display The microbnrst: Common factor in recent aircraft systems accidents A81-19500 H81-11571 B-2 PEBSOJA1 ADTBOB IHDBZ DIIII, C. S. CAB8, B. P. COPLIH. J. F. An investigation into grid patching techniques The future of civil turbo-fan engines H81-14708 [PBH-90034] 881-13961 CAUGHBY, 0. A. COPPI, CB. Development of finite-volume methods for The Grumman Aerospace and Gnlfstream American three-dimensional transonic flows Gulfstream III case study in aircraft design [SD-A090829] N81-14986 A81-16720 CASIBB. F. »., JB. CORBIB, 3. C., JR. Passive control of wing/store flatter * Observing lightning from ground-based and airborne [HASA-TH-81865] H81-13922 stations CHAI, I. I. N81-14566 Transonic axisymmetric bodies with minimal Have drag COBDIB, F. A81-170118 Design to cost and new technologies CBAI6. J. 8. A81-19347 The effects of warhead-induced damage on the COOHTSEI, S. J. aeroelastic characteristics of lifting surfaces. .Ferrography as a health monitor and a design aid Volume 1: Aeroelastic effects for the development of helicopter gearboxes [AD-A091674] N81-13955 A81-18759 CBBH. F. COOSIBIX, J. A preliminary experimental investigation of the Review of theoretical and experimental results on response of a turbojet engine to inlet pressure three dimensional turbulent wakes and boundary distortion layers A81-17824 COHERA-NT-1980-4] B81-13930 CHESTi, L. CBAGO. I. A. Effects of nonlinearities on wing store flutter Testing model rotorcraft for overwater operations [HBB-FE-17/S/POB/27] N81-13974 A81-18058 CBIHA, B. T. CBORBLL, B. T. Finite element analysis of inviscid subsonic System for refurbishing and processing parachutes boattail flow [NASA-CASE-KSC-11012-1] N81-14967 [HASA-TH-81650] N81-14977 CaiBZEI. H. A study of air breathing rockets - Subsonic mode combustion DAI, G. [IAF PAPER 80-F-270] A81-18371 Experimental investigations on shock-associated ceo, j. noise Botary balance data for a single-engine A81-17735 agricultural airplane configuration for an DALE, J. H. angle-of-attack range of 8 deg to 90 deg Advanced technology turboshaft IB suppression [HASA-CR-3311] N81-13923 A81-17519 CBDHG, K. DALLESAGHB, 6. Aerodynamic stability analysis of NASA The resistance of tank protective measures to J85-13/planar pressure pulse generator microorganisms installation [SNIAS-801-551-107] N81-1S072 [HASA-CB-165111] N81-15004 DALI, K. C. CBBALCSIK, I. System considerations in the implementation of The PZL-Sokol - Hew Polish helicopter digital control A81-17325 [AAS 80-032] A81-19375 CICOB, D. B. DA06BTBRT, D. C. Improved methods for fan sound field determination Further investigations of adaptive-wall wind tunnels [N4SA-CR-165188] N81-15769 [AD-A091774] N81-13977 CLABI. J. B. DAVID, G. Validation Methods Research for Fault-Tolerant Characteristics of NAVSTAB user stations Avionics and Control Systems Sub-iorking Group A81-19425 fleeting. CARE 3 peer review DAI, D. L. [BASA-CP-2167] N81-15702 Compressor configuration and design optimization COB, B. B. for the high reliability gas turbine Calculated and experimental data for a 118-mm bore [ DOE/ET-15425/T1] N81-14327 roller bearing to 3 million DB DE POIfB, S. [ASHE PAPER 80-C2/LOB-14] A81-18668 Aerodynamic design of a ducted propeller - COB, f. I., JB. Optimization of efficiency Leading-edge deflection optimization for a highly A81-17146 swept arrow wing configuration DBAB, B. G. [8ASA-TP-1777] N81-14974 Increasing capacity with computer-assisted COLEHAS. R. 6. decision making A system for aerodynamic design and analysis of A81-18080 supersonic aircraft. Part 2: User's manual DECELLES. J. L. [HASA-CR-3352] N81-13920 Flight instrumentation requirements for A system for aerodynamic design and analysis of all-weather approach and landing supersonic aircraft. Part 3: Computer program A81-18059 description DBFBBBARI, G. [HASA-CR-3353] B81-14971 Effects of nonlinearities on wing store flutter COHG, 8. [SBB-FE-17/S/PUB/27] B81-13974 The measurement and analysis of station parameters DEBAITIO, J. B. of a turbojet engine Hind shear systems integration plan, VICOH (visual A81-17825 confirmation) reliability analysis COHKLB, J. P. [PB80-218233] N81-13949 Organic compounds in the exhaust of a J8S-5 DIEBKB. B. turbine engine Equipment for testing and measuring a "helmet [AD-A091712] H81-13966 mounted sight and display" system with a coupled COHBOLLI, 3. «. movable television camera in the Federal Aviation Administration and National flight-simulator for research of the DFVLR Heather Service Aviation Research and Development [DFVIB-HITT-80-04] N81-13960 N81-14558 DIXIT, C. S. COOK, J. P. Optimum selection of main parameters for the Sealing joints and cracks, thin resurfacing, and reverse design of a supersonic military aircraft locating voids under concrete slabs A81-17047 [PB80-215635] N81-14182 B-3 DOGGBTT, B. V. PEBSOIAL AUTHOR IIDKI DOGGETT, B. V. ETTIiGBB, B. C. Effects of angle of attack aod ventral fin on The implications of current flight control transonic flutter characteristics of an research and development arrow-wing configuration 481-16578 [NASA-TK-81914] H81-15397 BTTLBS, C. a. B. DOHG. Q. The rigidity and performance of a simple spiral The measurement and analysis of station parameters bevel helicopter gearbox of a turbojet engine [AS8E PAPER 80-C2/DET-103] 481-18654 481-17825 BVASS, B. J. DOBOFF, S. B. Helicopter sarvivability in overvater situations Dynamic characteristics of a high-speed rotor with 481-18081 radial and axial foil-bearing supports [ASHE P&PEB 80-C2/10B-35] A81-18683 DOTLB, B. B. Airport/environs plan making - nanaging the FADDEH, D. B. planning process Computer generated displays and pilot effectiveness A81-18088 481-18082 DRAAH. A. H. FAGOT, B. Transonic wind tunnel tests on an oscillating wing Controls of aeronautical structures under fatigue vith external store. Part 4: The ving with testing by holographic pulsed lasers underving: store interferometry [AD-A077370] H81-14969 [ISL-CO-218/79] N81-14300 DBAGO, 7. J. FAIi, B. L. Hen major O.s. airports - Capacity considerations Bunvay Configuration Management System concepts 481-18060 A81-18089 DROSTE, C. S. FAIBCBH.D, J. E. 4 case study on the F-16 fly-by-wire flight 4 pure direct force/moment control for coaxial control system counterrotating rotors A81-16719 H81-15007 DO. Q. FAB, F. A vaporizing coibustor vith doable combustion spaces An aerodynamic design method for transonic axial A81-17827 flov compressor stage DDGAH, D. C. A81-17805 The JtY-15 tilt rotor research aircraft FAB, B. A81-16588 Airspace analysis in airport system planning DOULAT. H. J., JB. 481-18052 Airspace analysis in airport system planning FAHG, B. T. 481-18052 Geometric dilution of precision in Global DOBSTOH, O. A. Positioning System navigation Experimental aerodynamic characteristics of tvo 481-18100 V/STOL fighter/attack aircraft configurations at PABBELL, C. Bach numbers from 0.4 to 1.1 Full potential solution of transonic quasi-3-0 [SASA-TB-81234] N81-1U981 flov through a cascade using artificial compressability [HASA-TM-81637] N81-14980 FBBBBBKABP, L. G. EAVES, A. 7. Surface finishing Coatings in the aero gas turbine [HASA-CASE-BSC-12631-3] N81-14077 A81-17167 FEIBBBT, J. I. BD1ABDS, B. G. Leading-edge deflection optimization for a highly An investigation into grid patching technigues svept arrov ving configuration N81-14708 [NASA-TP-1777] N81-14974 BD8ABDS, V. B. FEBBIS, B. Helicopter propulsion system development and Safety considerations for helicopter drive systems qualification of the 1980s 481-17511 A81-17510 EHBBHBEEGEB. L. J. FIRE, D. A. Clear air turbulence: Historical comments Vanadium trineodecanoate promoter for H81-11562 fiberglass-polyester soil surfacings BBLBBS, B. [AD-4091785] N81-14084 Eguipment for testing and measuring a "helmet FIBSCHEIH. O. . mounted sight and display" system vith a coupled Sutonoaous navigation using passively sensed movable television camera in the terrain images flight-simulator for research of the DFVLR 481-17977 [DFVLB-HITT-80-04] H81-13960 FITZGEBALD, P. C. EILISOH, I. A. Advanced transmission component development and An overviev - 1980 generation avionic developments test program 481-18061 481-17507 BHDBBS, J. FLEDBT, C. Aviation meteorology research and development: 4 Dual methods and approximation concepts in status report structural synthesis H81-14557 [8ASA-CB-3226] H81-14347 EPPLBB, B. FLOIBBS, G. L. 4 computer program for the design and analysis of Tool force evaluation of lathe machined high lov-speed airfoils, supplement explosives [HASA-TB-81862J H81-13921 [ HHSHP-80-20] H81-15148 BBDSAHH, F. FOBBBB, I. Eguipment for testing and measuring a "helmet The effect of aerodynamic coupling on the dynamics mounted sight and display" system vith a coupled of aircraft in fast rolling motion movable television camera in the A81-17471 flight-simulator for research of the DPVLB FORBES, B. C. [DFVLR-BITT-80-04] H81-13960 4 simple combustor system for a small gas turbine BBBABT. B. G. engine The XV-15 tilt rotor research aircraft 481-17503 481-16588 FOBGAS, J. A. EBICKSOH, J. C., JB. Airport visual approach, guidance and landing Further investigations of adaptive-vall wind tunnels systems - Airline pilots viewpoint [4D-4091774] N81-13977 A81-18083 B-1 PESS014L ADTHOH IHDEI BITFIELD, J. J. FOBSBT, C. R. GOLBIfZ, I. C. An investigation into grid patching techniques Time dependent Navier-Stokes solution of a 881-11708 turbulent gas jet ejected from a rectangular FODGBiEB. J. I., JR. orifice into a high-subsonic crossflow Passive control of wing/store flutter N81-14964 [HASA-TH-81865] H81-13922 COLDBin, L. B. FOOBB, C. Southern California aviation system study Aircraft engine programs employing cost objectives [PB80-215544] N81-13916 A81-19346 GOLOBISSKII. A. I. FBOST, B. Hypersonic gas flow over a delta wing Proceedings: Fourth Annual Rorkshop on A81-19632 Meteorological and Environmental Inputs to GOREIKOV. A. F. Aviation systems Comparative evaluation of the quality of jet fuels [HASA-CP-2139] N81-14555 A81-17371 Survey of Workshops on Meteorological and GBAHGIBB. H. Environmental Inputs to Aviation Systems Primary training of military pilots - changing N81-14556 theories and new trainers FOLLBH, H. C. A81-19498 The rating of helicopter noise: Development of a GBIGOLL, D. proposed impulse correction Influence of free-stream turbulence intensity on [NPL-AC-93] 1181-14792 heat transfer in the two-dimensional turbulent boundary layer of an accelerated compressible flow A81-17994 GROdLI, J. I. GAJERSSI, T. Advanced Attack Helicopter /YAB-64/ - Status report Conditions of generation and methods of damping A81-16580 the inlet vortex of a turbojet engine GROHRALD, A. J. A81-19442 Evaluation of a computer-generated perspective GALLAGHER, M. K. tunnel display for flight path following Technological forecasting—aircraft design. CHASA-TP-1736] H81-13958 Citations from the International Aerospace data GOLDBB, t. base Sealing joints and cracks, thin resurfacing, and [NASA-CB-163833] N81-13957 locating voids under concrete slabs GAIGLOFF, B. [PB80-215635] N81-14182 Helicopter alarms - The use of ALAT incident and GDPIA, H. K. accident record cards Frequency-shaped cost functionals - Extension of A81-16689 linear-quadratic-Gaussian design methods SABDBEB, G. F. A81-18578 Advanced transmission component development and test program A81-17507 H SATIBEAO. R. J. BAASZ. A. A. History of flight testing the L-1011 Tristar jet Aircraft annoyance evaluations using field and transport. I - The L-1011-1 laboratory simulation techniques A81-17976 [UTIAS-248] H81-15580 GAODETTE. B. P. HABEBCOB, G. E., JR. Service life determination for the OH-60-A (DTTAS) Maneuvering aircraft: Noise pollution and helicopter elastomeric bearings control. Citations from the NTIS data base [AD-A0917S6] N81-14324 [PB80-815566] H81-14525 GE. S. BAERTIG, J. Structural analysis of fuselages with cutouts by Application of optical methods to the study of jet finite element method noise and turbulence A81-17816 [ ISL-CO-201/80] H81-15819 GBGEBLE, J. HABBI. C. I. Visual systems at Lufthansa's simulator centre Bind shear systems integration plan, VICOH (visual A81-19199 confirmation) reliability analysis GEBHABT. P. H. [PB80-218233] N81-13949 Finite element analysis of inviscid subsonic BABBL, P. boattail flow Problems of flight mechanics involved in [NASA-TH-81650] N81-14977 all-weather helicopter operation GERSBBEIH. B. A. 481-17467 Laminar boundary layer on swept-back wings of HABiA, R. F. infinite span at an angle of attack A cockpit view of advanced airline avionics A81-17656 A81-16585 GBRIB. B. L. BAISAH. M. J. F-111 windscreen machining Autonomous navigation using passively sensed [Y-2232] H81-14995 terrain images SILLFILLAB, I. E. A81-17977 Southern California aviation system study BABE, B. E. [PB80-215544] H81-13916 Non-destructive pavement evaluation SIRS, J. 0. A81-18062 Statistical relationship between median visibility HABBOLD, H. C. and conditions of worstcase manmade impact on General Electric infrared suppressors for the visibility Black Hawk helicopter [LA-OB-80-2485] N81-14550 481-17520 GHELIH, B. BASBIHOTO, H. Problems of flight mechanics involved in An investigation of support-interference effects all-weather helicopter operation [NAL-TB-622] H81-14984 A81-17467 BASSELBOT, A. 60BDEL, B. Downwash calculation at close range behind a Active control of an explosive wing-store flutter trapezoidal winq in supersonic flow case [FFA-TH-AD-1661] N81-13925 [MBB-FE-17/S/POB/25] H81-13973 HATFIELD, J. J. GOFF. R. C. Evaluation of a computer-generated perspective Hinds and wind shear in-situ sensors tunnel display for flight path following H81-14563 [SASA-TP-1736] N81-13958 B-5 BAIBAHB-BABBB, 6. PEESOHAL AOTBOB IBDEI HAIBABH-BABEB, G. HOOSBB, H. 3. Comparison of experimental and computational shock Fuel injector characterization studies structure in a transonic compressor rotor [HASA-CH-165200] B81-15003 [ASHE PAPEB 80-GT-81] A81-17953 BOIT, J. HAYBIB, A. T. Saudi Arabia's new Gateway Airports Development of a computer program data base of a A81-18093 navigation aid environment for simulated IFE BOZOHI, K. flight and landing studies An investigation of support-interference effects [NASA-TB-80064] 1181-13959 [NAL-TB-622] N81-14984 BEFPEBHAH, J. T. BSIB, C.-C. Surface finishing Hodeling of the terminal area Air Traffic [NiSA-CASE-SSC-12631-3] H81-11077 Banagement and Control HEIBEB, B. A81-18085 Prestressed concrete airfield pavements HD, Z. A81-18063 A preliminary experimental investigation of the BEBBI, B. A. response of a turbojet engine to inlet pressure Vanadium trineodecanoate pronoter for distortion fiberglass-polyester soil snrfacings A81-17824 [AD-A091785] 881-14081 The measurement and analysis of station parameters BBBBBBT. I. of a turbojet engine Dialogue on bridging some gaps in stability and A81-17825 transition research BOABG, B. A81-18105 Grid generation for general three-dimensional BEBTHICB. B. configurations A summary of proposals for airflight research by N81-14714 the BHFT BDFFSAB, J. K. A81-19298 Leading-edge deflection optimization for a highly HISCBBT. a. J. swept arrow wing configuration Heave instabilities of amphibious air cushion [NASA-TP-1777] N81-14974 suspension systems HDLIH, P. B. [UTIAS-246] H81-15156 Computer Generated Imagery (CGI) current BIBOTASO. B. technology and cost measures feasibility study An experimental study on kerosene-hydrogen hybrid [AD-A091636] H81-15729 combustion in a gas turbine combustor BOHBEL, D. A81-17841 Drag reduction through formation flight BISCOCKS, B. D. [DGLB PAPEB 80-106] A81-19393 i case study in aircraft design: The de Havilland SUBLET. J. F. family of STOL commuter aircraft Advanced technology turboshaft IB suppression A81-16717 A81-17519 BODGE, B. J. BUSTED, F. Design of the new Tehran International Airport Advanced technology tnrboshaft IB suppression A81-18084 A81-17519 BOBHLIB6EB. H. BDTSOI, B. B. Active flutter suppression on an F-4F aircraft UK pavement design and evaluation - A new approach uith external stores using already existing A81-18076 control surfaces [HBB-FE-17/S/POB/24] H81-13972 Active control of an explosive wing-store flutter case ISBII, S. [BBB-FE-17/S/PUB/25] N81-13973 A study of air breathing rockets - subsonic mode BOFFBAB, S. combustion Bibliography of Supersonic Cruise Research (SCB) [IAF PAPEB 80-F-270] A81-18371 program from 1977 to mid-1980 ITABCBOK. S. A. [BASA-BP-1063] H81-14973 Detection of moving objects BOFHAHB, I. A81-18773 The collision course: Conditions, guidance laws and properties [DFVLB-FB-80-06] H81-13942 HOGG. G. B. JACOB, K. Issues regarding Army turboshaft engines Experimental investigation of a right angle wing diagnostics and condition monitoring vith partially separated flow with and without A81-17514 ground effects BOGLUBD. L. E. CDGLB PAPER 80-111] A81-19397 Static source locations for four nozzles mounted JiBES, L. L. on a J-85 engine Omega - An economic Loran A replacement [HASA-CB-152401 ] 881-14998 A81-18077 BOLT, A. P., JB. JABESOB, A. A survey of new technology for cockpit application Development of finite-volume methods for to 1990's transport aircraft simulators three-dimensional transonic flows [NASA-CB-1S9330] H81-11993 [AD-A090829] H81-14986 BOBBEB, B. 8. JiSIK, S. Development of high-temperature turbine subsystem Digital control for helicopter powerplants technology to a technology readiness status, A81-17S04 phase 2 JAIK, T. [FE-1806-72] M81-11332 Volumetric pattern prediction of antennas on BOBSTBAHB, K. B. aircraft using the geometrical theory of Reduction of profile drag by bloving out through diffraction peg holes in areas of streamline separation [ DFVLB-FB-80-01] H81-14195 bubbles JIABG, 3. [DGLB PAPEB 80-103] A81-19392 The matrix analysis of wings BOSBT, H. B. A81-17818 Aerodynamic stability analysis of SASA JOBABSSOB, B. C. A. J85-13/planar pressure pulse generator The velocity induced by the wake of a wind turbine installation in a shear layer, including ground effect [NASA-CB-165141] H81-15004 [FFA-TH-HD-2189-PT-3] B81-14985 TF34 engine compression system computer study JOBS, A. J. [NASA-CB-159889] N81-15005 The rating of helicopter noise: Development of a proposed impulse correction [BPL-AC-93] B81-14792 B-6 PBBSOBAl AOIHOB IHDEI LALETIB, K. H. JOHHSOH. J. B. KIBZLBB, J. A. A resin injection technique foe the fabrication of Surface finishing aero engine conposite components [BASA-CASE-BSC-12631-3] H81-11077 [PSB-90024] 881-11004 EITCBBBS, P. t. JOHBSOS, B. E. Aircraft icing instrumentation: Dnfilled needs Automating airborne company communications B81-11560 A81-18061 ELASS, P. 3. JOBBSXOB. G- i. Solid-state power system use expands Sound radiation from a finite length unflanged AS 1-19191 circular duct with anifors axial flow. I - EOBDSIBSEI, V. Theoretical analysis. II - Computed radiation Turbopropeller engine PZL-10S characteristics A81-17321 A81-16712 KOYASA, I. Aircraft annoyance evaluations using field and An investigation of support-interference effects laboratory simulation techniques [SAL-TB-622J 881-11981 [OTIAS-218] H81-15580 KBAOS, I. JOLZBB. B. S. Computational aerodynamic design tools and Airspace simulation in airport system planning techniques used at fighter development 481-18086 [HBB-PE-122/S/POB/13] B81-13950 JOHBS, D. J. KBEIB, S. B. Transonic azisyametric bodies with minimal wave drag Joint-laboratory qualification testing of oils for A81-17018 gas turbine engines JOBBS, E. B. A81-17375 Airline flight departure procedures - Choosing EBEISSBLHBIBB, G. between noise abatement, minimum fuel Application of vector performance optimization to consumption and minioun cost a robust control loop design for a fighter A81-17011 aircraft JOHBS. R. B. [DPVLB-FB-80-11] B81-13970 A resin injection technigne for the fabrication of KRUTKO, P. D. aero engine composite components Inverse problems of controlled flight dynamics - [PHB-90021] B81-11001 Longitudinal motion JOSSS A81-16968 The annoyance caused by noise around airports KDBHB, B. [BASA-TM-75781] H81-15579 Active control of an explosive wing-store flutter JOD, 8. H. case Development of finite-volume methods for [HBB-FE-17/S/POB/25] B81-13973 three-dimensional transonic flows KOBHBBBLB, I. [AD-A090829] H81-11986 Botor model for verification of computation methods JOTBAS. B. [ISD-262] B81-15167 Supersonic stall flutter of high speed fans KOBIBA. B. A. tHASA-TB-81613] B81-11978 Composition of sludge formed in B-3T oil AS 1-17373 KOBZ, B. K Computational aerodynamic design tools and KADOTA. I. technigues used at fighter development An experimental study on kerosene-hydrogen hybrid [MBB-FE-122/S/POB/13] H81-13950 combustion in a gas turbine combustor KOBTBBBACB, F. J. A81-17811 Plight evaluation of a simplified gross thrust KABBBB, B. calculation technique using an F100 turbofan The practical application of the lake Blocking engine in an F-15 airplane Corrections according to Haskell [BASA-TP-1782] B81-15000 [DS1B PAPEB 80-112] A81-19398 KOSAKIi, S. I. EABL, F. Characteristics of the velocity field near a Botor model for verification of computation methods wing-body combination located at an angle of [ISD-262] N81-15467 attack to an oncoming supersonic flow KAiAEATA. H. A81-19337 Hodel-following system with assignable error The coordinate-deformation method in the problem dynamics and its application to aircraft of a supersonic gas flow over an airfoil A81-18577 A81-19631 KBBBBDI. T. I. KBZHIiSKII, V. A. An evaluation of wind tunnel test technigues for Hall cooling and the laminar-turbulent boundary aircraft nozzle afterbody testing at transonic layer transition at supersonic flow velocities Bach numbers A81-19611 [AD-A091775J B81-13931 KOZHBISOT. T. G. KETTLES. J. C. Composition of sludge formed in B-37 oil Helicopters - Help for the all weather terminal A81-17373 A81-18065 KHAIH07ICH, I. A. Badio navigation for aircraft: Handbook A81-18599 LACEBI, I. B. EBAB. I. A. Organic compounds in the exhaust of a J85-5 Vector and scalar characteristics of opposing jets turbine engine discharging normally into a cross-stream [AD-A091712] B81-13966 A81-17997 LAIBD, C. KBABITOBOV, A. 8. Hechanisms of damage accumulation in The influence of flow disturbances on the time-dependent cyclic deformation laminar-turbulent transition in a supersonic [DOE/EB-10570/1] H81-11363 boundary layer LAKSHHIHABAIABA, B. A81-19613 Structure and decay characteristics of turbulence KIBBAPPBL. f. in the near- and far-wake of a moderately loaded Analysis of unsteady pressure measurements on an compressor rotor-blade aerofoil section with an harmonically [ASSE PAPER 80-GT-95] A81-17951 oscillating, slotted flap LALETIB. E. B. [DFVLR'FB-80-22] B81-13929 Practical aerodynamics of the helicopter Hi-6A KIBG, B. B. A81-18600 The wear of PTPE-containing dry bearing liners contaminated by fluids [ASLE ?BEPBIHT 80-LC-6B-3] A81-18758 B-7 LABB, g. PEBSOBAL ADTBOH IIDBI LABB, B. A preliminary experimental investigation of the Mind-tunnel measurements and comparison vith response of a turbojet engine to inlet pressure flight of the boundary layer and heat transfer distortion on a hollow cylinder at Hach 3 A81-1782U [HASA-TP-1789] B81-14975 The measurement and analysis of station parameters LAHBBai. B. of a turbojet engine Fighters for the 1990s &81-17825 A81-19497 LID, S. LAHCASTEB, J. K. An experimental investigation of the rotating The wear of PTFE-containing dry bearing liners stall, surge, and wake behind the rotor for a contaminated by fluids single stage axial compressor [ASLE PBEPBIBT 80-LC-6B-3] A81-18758 A81-17826 LEE, K. D. i LOEHB, B. Grid generation for general three-dimensional Equipment for testing and measuring a "helmet configurations mounted sight and display" system with a coupled H81-1117114 movable television camera in the LEE, ¥. S. flight-simulator for research of the DFYLB Surface finishing C DFVLB-BITT-80-04 ] H81-13960 [HASA-CASE-HSC- 12631-3} US 1-11*077 LOTZE, A. LBIIIBGBB, e. Effects of nonlinearities on wing store flutter Application of the HHA design method to a [HBB-FE-17/S/POB/27] N81-13974 nonlinear turbofan engine LDCAS, E. J. [HASA-CB-163855] H81-15001 Evaluation of wind tunnel nozzle afterbody test LBHSKI, J. I., JB. techniques utilizing a modern twin engine Drive system development for the 1980's fighter geometry at Hach numbers from 0.6 to 1.2 A81-17508 [AD-A091545] H81-13932 LBOHABD, A. LOBHOS, J. B. Vottex methods for two- and three-dimensional flow Experimental aerodynamic characteristics of two simulations V/STOL fighter/attack aircraft configurations at H81-15313 Hach numbers from 0.4 to 1.4 LEIdAH, C. S. [HASA-TB-81234] H81-14981 Concorde aerodynamics and associated systems LOIOBI, J. L. development A system for aerodynamic design and analysis of A81-16718 supersonic aircraft. Part 2: User's manual LI, C.-H. [HASA-CB-3352] H81-13920 On the steady state and dynamic performance A'system for aerodynamic design and analysis of characteristics of floating ring bearings supersonic aircraft. Part 1: General [ASHB PAPEH 80-C2/LOB-17] A81-18671 description and theoretical development LI, P, [HASA-CB-3351] H81-14970 Experimental investigations on shock-associated A system for aerodynamic design and analysis of noise supersonic aircraft. Part 3: Computer program A81-17735 description LI, », [HASA-CB-3353] H81-14971 A preliminary experimental investigation of the LOO, S. response of a turbojet engine to inlet pressure Finite difference computation of the steady distortion transonic potential flow around airplanes A81-17824 A81-17802 LIAPISA. O. A. Experimental investigation of orographic waves and vertical motions in the Krasnovodsk airport area M A81-19441 BA, 0. LIGHT, L. Experimental investigations on shock-associated Dynamic characteristics of a high-speed rotor with noise radial and axial foil-bearing supports A81-17735 [ASME PAPEB 80-C2/LOB-35] A81-18683 BABBI. D. 6. LIB. C. The resonance frequencies of ventilated wind tunnels Second order approximation theory of an arbitrary [ABC-H/H-3841] S81-15009 aerofoil in incompressible potential flow BACE, B. B. A81-17803 Periodically stiffened fluid-loaded plates. I - Aerodynamic calculations and design of subcritical Besponse to convected harmonic pressure and free aerofoils wave propagation. II - Besponse to line and A81-17804 point forces LIB, Q. A81-17067 A preliminary experimental investigation of the HACGLASBAH, I. F. response of a turbojet engine to inlet pressure Power control for hot gas engines distortion [HASA-CASE-BPO-14220-1] H81-14318 A81-17821 HACK, J. C. The measurement and analysis of station parameters Drive system development for the 1980's of a turbojet engine A81-17508 A81-17825 Experience with advanced high performance gear steel LID. C. [ASHE PAPEB 80-C2/DET-77] A81-186B8 An optimum design procedure of total-temperature BACLBOD, B. I. thermocouple probes Low-speed wind-tnnnel tests of two weathercocking A81-17807 sensors LID, G. [SSBL-0171-TH] B81-14575 Variational principles and generalized variational HACPHEBSOB,. P. B. principles for the hybrid aerodynamic problem of Water content of helicopter gear oils airfoil cascades on an arbitrary stream sheet of [ASBE PAPEB 80-C2/DET-12] A81-18640 revolution The rigidity and performance of a simple spiral A81-17741 bevel helicopter gearbox LID, a. [ASBE PAPEB 80-C2/DET-103] A81-18654 An experimental investigation of the rotating BIGBAB, A. stall, surge, and wake behind the rotor for a Bird flight and airplane flight single stage axial compressor [BASA-TH-75777] H81-14962 A81-17826 BAIO, 0. LID, S. Performance evaluation of an interrogation-reply An aerodynamic design method for transonic axial scheduling technigne for a discrete address flow compressor stage beacon system A81-17805 A81-19U17 B-8 PERSOMAL 10THOB ISDEI 8YBBS, B. D. DaLISHBV, V. T. BIKHALBV, I. A. Formation of solid phase daring the heating of jet Principle for the design of hybrid control systems fuels for passenger transport systems A81-17372 A81-17577 BARKOB. B. J. BILES. J. H. Bunny rehabilitation, lashington National Airport Analysis of pressure spectra measurements in a A81-18066 ducted combustion system BABTIH, C. L. [NASA-TB-81583] H81-15768 Organic compounds in the exhaust of a J85-S BIBBCK, B. S. turbine engine Hind-tunnel test of an articulated helicopter [AD-A091712] H81-13966 rotor model with several tip shapes BABTIB, J. I. [8ASA-TS-80080] N81-13918 Shipboard trials of the Quiet Short-Haul Research BISKABAB, I. Aircraft /QSRA/ Sealing joints and cracks, thin resurfacing, and A81-16581 locating voids under concrete slabs BASOIA, e. CPB80-215635] 1181-14182 A study of air breathing rockets - subsonic mode BIOBA. S. combustion Aeronautical-Saritime Engineering Satellite /ABES/ [IAF PAPEE 80-P-270] A81-18371 program of Japan BATHB1S, D. C. [IAF PAPEB 80-D-171] A81-18318 Improved methods for fan sound field determination BOAVBBZADEH. F. [NASA-CR-165188] N81-15769 Runway rehabilitation, Washington National Airport BATSOZAKI. T. A81-18066 An investigation of support-interference effects BOH», J. B. [NAL-TR-622] N81-14984 Improved capabilities to detect incipient bearing BATIBI. a. D. failures Inlet flow distortion in turbomachinery [AD-A091687] N81-14325 [ASBE PAPER 80-GT-20] A81-17952 BOLL, T. B. BIOK, S. C. Active flutter suppression on an F-4F aircraft Remotely piloted vehicles. Citations from the with external stores using already existing International Aerospace abstracts data base control surfaces [NASA-CR-163864] N81-14996 [MBB-FE-17/S/PDB/24] N81-13972 Lightning. Citations from the International BOIAGAB, S. J. Aerospace abstracts data base Head-tJp-Display flight tests [NASA-CR-163857] N81-15648 A81-16582 Clean air turbulence. Citations from the BOOB, 0. A. International Aerospace Abstracts data base Air traffic management enhancement through new [NASA-CR-163863] N81-15649 avionics /4-D/ flCCABB. L. B. A81-16583 The importance of 'Interim Standard Bicrowave BORIKAiA, H. Landing System1 for small community airports Aeronautical-Baritime Engineering Satellite /AMES/ A81-18087 program of Japan aCCARTBT. J. [IAF PAPER 80-D-171] A81-18318 Doctor Pujita's aicroburst analysis at Chicago BORIBOTO, S. H81-14572 Aeronautical-Baritiue Engineering satellite /ABES/ BCDBDE, J. B. program of Japan Development of a computer program data base of a [IAF PAPEB 80-D-171] A81-18318 navigation aid environment for simulated IFR BORKO7IH, B. T. flight and landing studies Dialogue on bridging some gaps in stability and [NASA-TB-80064] H81-13959 transition research HCFARLABD, B. B. A81-18105 Solution of plane cascade flow using in proved BOHLAH, S. surface singularity methods Pyrotechnics serving safety [NASA-TB-81589] N81-14979 A81-19348 HCBILLAH. J. D. BOBTOH. T. 6. Catalog of sea state and wind speed in the South The digital control system as part of an Atlantic Bight integrated accessory fit for future engines [HASA-CR-156872] H81-11601 A81-17505 BEAD. U H. BOSS, a. j. The Grumman Aerospace and Gulfstream American Advanced flight deck/crew station simulator Gulfstream III case study in aircraft design functional reguirements A81-16720 [NASA-CR-159331] N81-14994 BBHU. J. P. BROTEK, Z. A new system for the study of visual information Map-type displays presentation in aeronautics - GIBI A81-19443 A81-16688 BDELLEB, B. BEBCBB, J. B. Rotor model for verification of computation methods Development of finite-volume methods for [ISD-262] N81-15467 three-dimensional transonic flows HOEBSCHER, D. [AD-A090829] H81-14986 A contribution to stabilization of flight vehicle BERIIH, J. T. parachute systems Southern California aviation system study [DFVLR-MITT-80-05] N81-13926 [PB80-215544] H81-13916 BOLCAI, I. BBIEB. B. I. Rotary balance data for a single-engine Prediction of sound radiated from different agricultural airplane configuration for an practical jet engine inlets angle-of-attack range of 8 deg to 90 deg [BASA-CR-163824] N81-14789 [NASA-CB-3311] N81-13923 BIDDLETOH, i. D. BOBDIE, D. L. A system for aerodynamic design and analysis of Transonic axisymmetric bodies with minimal wave drag supersonic aircraft. Part 2: User's manual A81-17048 [HASA-CB-3352] H81-13920 BDRPBI, L. D. A system for aerodynamic design and analysis of Southern California aviation system study supersonic aircraft. Part 1: General [PB80-215544] H81-13916 description and theoretical development BIBBS, B. D. [SASA-CB-3351] S81-14970 Community participation in airport planning A system for aerodynamic design and analysis of A81-18067 supersonic aircraft. Part 3: Computer program description [NASA-CB-3353] N81-14971 B-9 BAKASUBA, H. PBBSOHAL iDTBOB IgDEI OKOBB07, B. 8. Principle for the design of hybrid control systems N for passenger transport systems HAKABOBA, H. A81-17577 & method foe obtaining shockless transonic flows OLIVES. B. J. past airfoils, partially modified fcon a given L-1011 Flight Hanageaent system design arbitrary airfoil considerations [HAL-TB-602T] N81-14983 A81-18074 HAHDOBI, V. G. OIO, K. Application of fracture mechanics in designing The effect of cyclic loading on the apparent lover wing skin of transport aircraft cleavage fracture toughness of 1cr-Bo-V rotor 481-170119 steel BAOCK, J. A81-17488 Sarsat - A rescue system for ships and aircraft OPDIKE, G., JB. A81-16684 A siiple combnstor system for a small gas turbine HBISB. 8. engine Noise and noise abatement in fans and blowers: A A81-17503 review OSIPOI, A. A. [DFVLH-FB-80-16 ] H81-14796 Propagation of three-dimensional acoustic NEKBASOTA. H. B. perturbations in channels of variable Some characteristics of snbsonic flow over the cross-sectional area at frequencies close to root area of a sveptback wing cutoff frequency A81-19633 A81-19338 HELBS, B. P. Experinental aerodynamic characteristics of tvo V/STOL fighter/attack aircraft configurations at Mach numbers from 0.4 to 1.4 PACKBB, L. L. [SASA-TB-81234] H81-14981 Improved capabilities to detect incipient bearing BBPPEBT, B. failures Drag estimations for stream-line and cylindrical [AD-A091687J N81-14325 contour distortions on aircraft fuselages and PAILHAS. G. train cars Beview of theoretical and experimental results on [DGLB PAPEB 80-116] A81-19399 three dimensional turbulent wakes and boundary HE1IOB, A. G. layers The future of civil tarbo-fan engines [OHEBA-NT-1980-4] H81-13930 [PNB-90034] N81-13964 PAPIB, J. P. HIELSEH, J. P. Helicopter alarms - The use of ALAT incident and Becent developments in NOT techniques accident record cards A81-18078 A81-16689 HIGBO, 0. B. PAHKBB. B. J. Gas turbine engines and transmissions for bus Performance of computer-optimized tapered-roller demonstration programs bearings to 2.4 million DN [COO-4867-07] H81-14329 [ASBB PAPEH 80-C2/LOB-18] A81-18672 BIKOLSKII. A. A. Lubrication of rolling element bearings Plane vortex gas flows A81-18738 A81-19634 PABE, P. BISHT, B. I. Current aircraft survey (approach speeds, gross Nonlinear aerodynamic characteristics of a thin weights, and Dimensions) airfoil of arbitrary plane configuration [PB80-225691] N81-13956 A81-19629 PATEL, T. S. NIXOB, 0. Optimum selection of main parameters for the Development of finite-volume methods for reverse design of a supersonic military aircraft three-dimensional transonic flows A81-17047 [AD-A090829] N81-14986 PATTOS. J. H.. JB. BOCBOBSOB. D. A status report on NASA general aviation Statistical relationship between median visibility stall/spin flight testing and conditions of worstcase manmade impact on A81-19471 visibility PEISIS, S. T. [LA-DB-80-2485] N81-14550 Laminar boundary layer on swept-back wings of MOHBAKEB. D. O. infinite span at an angle of attack A survey of new technology for cockpit application A81-17656 to 1990's transport aircraft simulators PBBKS, B. P. [NASA-CB-159330] N81-14993 The digital control system as part of an HOBTOH. P. S. integrated accessory fit for future engines Planning for and evaluating the potential of a A81-17505 land based aircraft for carrier operations PEBSOOB, A. J. A81-19470 Transonic wind tunnel tests on an oscillating wing NOfOSABTOV, G. T. with external store. Part 4: The wing with Composition of sludge formed in B-3V oil underwing: Store A81-17373 [AD-A077370] 881-14969 Joint-laboratory gualification testing of oils for PETEBSEH, J. C. gas turbine engines A computer-based laser Doppler velocimeter A81-17375 [DF7LB-HTTT-79-14] B81-14289 PETBOT, B. B. Inverse problems of controlled flight dynamics - Longitudinal motion OBBAZTSOV, I. F. A81-16968 The method of superelements in the dynamics of PFEIFFEB, H. J. complex structures An analytic aodel of subsonic flow around an A81-16969 airflow with a spoiler OSIHOTO. K. N81-14966 Sound radiation from a finite length nnflanged PIIEL. S. I. circular duct with uniform axial flow. I - Performance of computer-optimized tapered-roller Theoretical analysis. II - Computed radiation bearings to 2.4 million DH characteristics [ASBE PAPEB 80-C2/LOB-18] A81-18672 A81-16712 PISABO, A. 0. Failure Indication and Corrective Action for turboshaft engines A81-17515 B-10 PEBSOBAL AOTHOB ISDBI BOOS, B. PLATSBK. B. B. BADCB, B. B. Airport/environs plan making - Hanaging the Improved ceramic heat exchanger materials planning process [HASA-CB-159678] M81-14082 481-18088 BAVIIDBABATfl, A. POCOCK, C. L. Structure and decay characteristics of turbulence Turbulence: From a pilot's viewpoint in the near- and far-wake of a moderately loaded H81-14561 compressor rotor-blade POCOCE, e. [ASBE PAPER 80-GT-95] A81-17954 Ferrography as a health monitor and a design aid BAT, 6. K. foe the developnent of helicopter gearboxes Sealing joints and cracks, thin resurfacing, and 181-18759 locating voids under concrete slabs P08STEOKE, B. [PB80-215635] H81-14182 Transonic wind tunnel tests on an oscillating ving BE, B. J. Kith external store. Part 4: The wing with Investigation of convergent-divergent nozzles onderwing: Store applicable to reduced-power supersonic cruise [AD-A077370] H81-14969 aircraft POLIAKBOV, I. B. [NASA-TP-1766] 881-14972 Stead; flow past a rectangular wing with BECB, J. circulation that is variable along the span Concorde aerodynamics and associated systems A81-16551 development POLL, 0. I. A. A81-16718 Three-dimensional boundary layer transition via SEED, B. E. the mechanisms of 'attachment line Microwave landing systems. Citations from the contamination' and 'cross flow instability' Engineering Index data base A81-18122 [PB80-814643] N81-13947 PBICB, I. L. Microwave landing systems. Citations from the Laser-Baman/Bayleigh flow diagnostic techniques NTIS data base applied to subsonic flow [PB80-814635] N81-13948 [AD-A091695] H81-14275 BEEO, 8. B., Ill PBIIOLO. B. F. Passive control of wing/store flutter The coordinate-deformation method in the problem [HASA-TS-81865] N81-13922 of a supersonic gas flow over an airfoil BEICBEB1, G. A81-19631 Hingeless tailrotor in fiber composite PDBSBL, B. construction and vibration-isolation systems Flight test investigation of LOBAS-C for en route /ARIS, ASIS/ for helicopters navigation in the Gulf of Mexico [HBB-OD-311-80-0] A81-19300 [AO-A091637] H81-13945 BEID, I. H. POZTBEVSU, B. A study of eultiple jets Some aspects of optimizing the aerodynamics of A81-18024 turbine stages BICBABDSOH, A.. Ill A81-19325 Organic compounds in the exhaust of a J85-5 turbine engine [AD-A091712] N81-13966 Q BICKETTS, B. A. QIAB, B. Effects of angle of attack and ventral fin on Finite difference computation of the steady transonic flutter characteristics of an transonic potential flow around airplanes arrow-wing configuration A81-17802 [NASA-TH-81914] H81-15397 QUASI, A. BIECKBOF, B.-J. Reduction of profile drag by blowing out through Automatization of the adhesion process for peg holes in areas of streamline separation supporting airframe parts in light contour systems bubbles A81-19297 [DGLH PAPER 80-103] A81-19392 BIFPEL, B. E. Laminar-airfoils for transport aircraft Experimental determination of unsteady blade [DFVLB-BITT-80-07] H81-13952 element aerodynamics in cascades. Volume 2: QOIRBI. 6. t. Translation mode cascade An assessment of General Aviation utilization of [NASA-CB-165166] N81-14976 advanced avionics technology BIX, 0. CNASA-CB-159328] H81-13941 System identification of the longitudinal motion of the DFVLR HFB 320 research aircraft with particular consideration of control surface effectiveness BABE, D, C. [DFYLH-HITT-79-16] H81-13971 Effects of downstream distance on turbulence decay BOBEBTSOH. J. B. for the compressor research facility low Evaluation of a computer-generated perspective conditioning system tunnel display for flight path following [AD-A091543] H81-14276 [NASA-TP-1736] N81-13958 HADFOBD. B. C. BOBIHSOH, C. A., JR. Landing flying qualities evaluation criteria for Industry proposes supersonic V/STOL augmented aircraft A81-19490 [NASA-CE-163097] N81-13969 BOBIHSOH, 0. I. BA6BOHATHAB, S. The rating of helicopter noise: Development of a A study of multiple jets proposed impulse correction A81-18024 [HPL-AC-93] H81-14792 BAGOLIB, B. t. BOBOB, S. B. Rail cooling and the laminar-turbulent boundary On the steady state and dynamic performance layer transition at supersonic flow velocities characteristics of floating ring bearings A81-19644 [ASME PAPER 80-C2/LOB-17] A81-18671 BAO. D. H. ROHAH, I. Aerodynamic side-force alleviator means The effect of cyclic loading on the apparent [HASA-CASE-LAB-12326-1] H81-14968 cleavage fracture toughness of 1Cr-Ho-V rotor BAPBAEL. D. E. steel Aviation assumptions in the eighties A81-17488 A81-18068 BOOS, B. BATTEBBBB, B. L. Transonic wind tunnel tests on an oscillating wing Fully bonded concrete overlay for an airport runway with external store. Part 4: The wing with A81-18075 underwing: Store [AD-A077370] H81-1U969 B-11 BOSEITI. C. PEBSOBAl AOTBOB IIDBI BOSBTTI, C. SCBBIDT, D. Satellites to aid flight safety A fault tolerant nnltiprocessor system with [IAF PAPEB 80-IAA-17] A81-18410 reconfiguration suitable for multiaxial flight BOTHBOCK, B. 0. stabilization and trimming Experimental determination of unsteady blade A81-19296 element aerodynamics in cascades. Volume 2: SCBHIDT, G. 1. Translation mode cascade Crnise-missile-carrier navigation requirements [NASA-CB-165166] 1181-14976 A81-18576 BOTBSCHILD. S. I. SCHBIT, L. A., JB. The future ATC system as influenced by advanced Dual methods and approximation concepts in avionics structural synthesis A81-16586 [HASA-CB-3226] B81-14347 BOOBD. D. P. SCBHItf, C. F.. JB. Analysis of unsteady pressure measurements on an Captive carry and free flight rain erosion aerofoil section with an harmonically considerations for reinforced ablative oscillating, slotted flap fluorocarbon badome materials [DFVLB-FB-80-22] H81-13929 A81-17453 EOZBDESTVESSKII. K. T. SCBIIPPEBS, P. Determination of the effect of transverse cutouts Transonic wind tunnel tests on an oscillating wing on the hydrodynamic characteristics of a with external store. Part 4: The wing with finite-span wing in the case of steady and underwing: Store unsteady motion near a vail [AD-A077370] H81-14969 A81-19335 SCHBOEBS, L. G. BOBBEBT, P. E. The XV-15 tilt rotor research aircraft Grid generation for general three-dimensional A81-16588 configurations SCHOBEBT, H. S81-1U714 Applicated techniques for the control of approach BOEBB, I. C. traffic Curved centerline air intake for a gas turbine [DFVLB-HITT-79-20] N81-14992 engine SCBDLLEB, F. T. [BASA-CASE-LEH-13201-1] N81-14999 Calculated and experimental data for a 118-am bore BOPPE, J. P. roller bearing to 3 million DH Today and the future in aircraft wheel and brake [ASHE PAPER 80-C2/LOB-14] A81-18668 development SCBIEIBOLD. F. J. A81-17046 Development and operational flight test of the arm, H. j., JB. model 250-C28B gas turbine engine A new perspective in aviation systems planning A81-17512 &81-18069 SBIDBL. B. S. Inlet flow distortion in tnrbouachinery [ASBE PAPEB 80-GT-20] A81-17952 SEHPLE, ». G. SACBEH, P. An economic and versatile panel method for Computational aerodynamic design tools and aircraft and aircraft/store configurations. An techniques used at fighter development outline of the principal features of the [HBB-FE-122/S/POB/13] H81-13950 mathematical modeling and numerical SACHS, G. implementation of the British Aerospace (Barton) The effect of aerodynamic coupling on the dynamics Sk II Panel Method of aircraft in fast rolling motion N81-15311 A81-17471 SEiSBOBG, O. SAKA, H. Active flutter suppression on an F-4F aircraft Prevention of spline vear by soft metallic coatings with external stores using already existing [AD-A091861] H81-14064 control surfaces SALIABIS, C. [HBB-FE-17/S/PUB/24] B81-13972 A contribution to stabilization of flight vehicle Active control of an explosive wing-store flutter parachute systems case [DFVLB-HITT-80-05] S81-13926 [HBB-FE-17/S/PDB/25] H81-13973 SALHIBS, S. Effects of nonlinearities on wing store flutter Avionics and displays in a future airspace system [HBB-FE-17/S/PDB/27] H81-13974 A81-18070 SBTTEBLOBD. B. B. SABDLIB, O. B. Cruise-missile-carrier navigation reguirements Flight evaluation of the terminal guidance system A81-18576 [HASA-CB-163859] N81-11991 SEIELL, C. SAHTOCCI, 6. F. Circulation Control ling /CC»/ flight tests A nev system for the study of visual information A81-19469 presentation in aeronautics - GIBI SEIPBIED, A. A81-16688 Applicated techniques for the control of approach SAVA, P. e. traffic The Dalembertometer [DFVLB-BITT-79-20] B81-14992 [ISL-CO-220/79] N81-14292 SBCHEDBIH, A. I. Application of optical methods to the study of jet Hypersonic gas flow over a delta wing noise and turbulence 481-19632 [ISL-CO-201/80] H81-15819 SHESTEBHISA, t. H. SCABLOI. J. Steady flow past a rectangular wing with The problems of helicopter ditching circulation that is variable along the span A81-18071 A81-16551 SCBAFBABEK. D. SBOBIH, T. P. Theoretical investigation of the influence of Elimination of vibrations in aircraft piping systems spoiler dynamics on the handling qualities of an A81-18497 aircraft with direct lift control SBVALEV, 10. G. [DFVLB-FB-80-07] H81-13975 Rail cooling and the laminar-turbulent boundary SCBIATO. A. layer transition at supersonic flow velocities Fuel conservation in the air transportation A81-19644 industry - General and operational aspects SIDEHSTICK, J. E. A81-17143 Turbine blade technology - Present and future SCBIJVB. J. [ASHE PAPEB 80-C2/AEBO-10] A81-18639 Prediction methods for fatigue crack growth in aircraft material A81-18777 B-12 PEBSOBAt AOTHOB IHDEI TATB, J. L. SIEBEBT, C. H. STEE8KE8, H. S. Transonic wind tunnel tests on an oscillating ving Aerodynamic stability analysis of BASA vith external store. Part 4: The wing with j85-13/planar pressure pulse generator underving: Store installation [AD-A077370] 881-11(969 [BASA-CH-165141] B81-15004 SIGBBfl. B. B. TF34 engine compression system computer study Performance of computer-optimized tapered-roller [BASA-CB-159889] 881-15005 bearings to 2.1 million DM STBIBBAOSEB, B. [ASSE PAPEB 80-C2ADB-18] A81-18672 Application of vector performance optimization to SIB, 8. C. a robust control loop design for a fighter Prevention of spline vear by soft metallic coatings aircraft [AD-A091B61] 881-14064 [DFVLB-FB-80-14] 881-13970 SIHCtAIB. 0. I. STEPBBBS. 6. E. Laser-Baman/Rayleigh flov diagnostic technigues Cost/benefit analysis of advanced materials applied to subsonic flov technologies for future aircraft turbine engines [AD-A091695] 881-14275 [SASA-CB-165225] B81-15006 SIBBi. A. B. STEVBBS, B. Bunvay Configuration Management System concepts Supersonic stall flutter of high speed fans A81-18089 [BASA-TK-81613] 881-14978 SIPPEL. K. 0. STIHPFLIBG, A. Constant-amplitude and flight-by-flight tests on Controls of aeronautical structures under fatigue CEBP specimens testing by holographic pulsed lasers [HBB-FE-2/S/POB-26] 881-14006 interferometry SLIIi, S. H. [ISL-CO-218/79] 881-14300 Economic evaluation of flying-qualities design STBAKOSCB. J. criteria for a transport configured vith relaxed The Grumman Aerospace and Gulfstream American static stability Gulfstream III case study in aircraft design [NASA-TP-1760] B81-13968 A81-16720 SalGIKLSKI, P. STBAOB, J. The Dalembertooeter Influence of free-stream turbulence intensity on [ISL-CO-220/79] 881-14292 heat transfer in the tvo-dimensional turbulent Controls of aeronautical structures under fatigue boundary layer of an accelerated compressible flov testing by holographic pulsed lasers A81-17994 interferometry STHICKLABD, P. B. [ISL-CO-218/79] N81-11300 Shipboard trials of the Quiet short-Haul Research SS1TB. E. B. Aircraft /QSHA/ Carved centerline air intake for a gas turbine A81-16581 engine SIBOBG, B. E. [BASA-CASE-LEH-13201-1] 881-14999 Compressor configuration and design optimization SNUB. B. for the high reliability gas turbine Landing flying qualities evaluation criteria for [DOE/ET-15332/11] B81-15414 augmented aircraft STOCKAS, K. J. [HASA-CB-163097] H81-13969 Advanced Technology Spark-Ignition Aircraft Piston SUITS, B. E. Engine Design study Bead-Dp-Display flight tests [BASA-CB-165162] B81-13963 A81-16582 SOB, I. P. SHITB, B. K. Prevention of spline vaar by soft metallic coatings Development and certification of the Gulfstream III [AD-A091861] 881-14064 A81-16587 SOLTiS, S. H. SOFIBV, E. I. Traffic forecasting for the BfilA Experimental investigation of orographic vaves and A81-18090 vertical motions in the Krasnovodsk airport area SOHIBSKI, L. I.. JB. A81-19441 Computer Generated Imagery (CGI) current SOFBIB, I. 6. technology and cost measures feasibility study Improved methods for fan sound field determination [AD-A091636] B81-15729 [8ASA-CB-165188] 881-15769 SDH, C. SOBERS. D. H. Structural analysis of fuselages vith cutouts by A computer program foe the design and analysis of finite element method lov-speed airfoils, supplement A81-17816 [NASA-TB-81862] 881-13921 SZODBOCB, J. SOBBLEIIIBB, I. Experimental study of supersonic viscous leeside The determination of the induced drag on slim flov over a slender delta wing Kings vith high lift systems in the transonic [SASA-TH-81248] B81-14265 region [HBB-FE122] A81-19400 SOSBOYSKU, A. A. Badio navigation for aircraft: Handbook TABA, H. B. A. A81-18599 The rigidity and performance of a simple spiral SOOTHBBH. I. S. bevel helicopter gearbox Exhaust noise in flight: The role of acoustic [ASHE PAPER 80-C2/DET-103 ] A81-18654 installation effects TABS, 0. [PBB-90029] B81-14793 A preliminary experimental investigation of the SPIKES, H. A. response of a turbojet engine to inlet pressure Rater content of helicopter gear oils distortion [ASHE PAPEB 80-C2/DET-12] A81-186UO A81-17824 STALLIHGS, B. L., JB., TABS, B. Sind-tunnel measurements and comparison vith A vaporizing combustor vith double combustion spaces flight of the boundary layer and heat transfer A81-17827 on a hollow cylinder at Bach 3 TABS, X. [SASA-TP-1789] 881-14975 Structural analysis of fuselages vith cutouts by STEABBAB, B, O. finite element method The effects of warhead-induced damage on the A81-17816 aeroelastic characteristics of lifting surfaces. TASSIBABI, H. Volume 1: Aeroelastic effects The design-to-cost of aircraft [AD-A091674] B81-13955 A81-19344 TAIB, J. L. Advanced flight deck/crev station simulator functional requirements [HASA-CB-159331] 881-14994 B-13 TBBBOiB. G. PBBSOBAL AOTHOH IIDEI TBBHUBB, G. Flight instramentation reqnireients for all-weather approach and landing A81-18059 VALOT, C. L. TEBSEIKB, T. S. A new system for the study of visual information The method of superelements in the dynamics of presentation in aeronautics - GIBI complex structures A81-16688 A81-16969 VAI UFFBLBB, J. P. IEIBLHAH. A. S. Characteristics of HAVSTAB user stations The effect of cyclic loading on the apparent A81-19125 cleavage fracture toughness of 1Cr-Mo-V rotor Hill, A. S. steel Aerial surveying of small areas froi a small A81-17488 remotely controlled drone TBBB, D. I. A81-17525 Advanced ejection seat for high dynamic pressure YAIIDIBB, J. I. G. escape. Hind tunnel test Transonic wind tunnel tests on an oscillating wing [AD-A091810] H81-139UO with external store. Part 4: The wing with THOHBT. a. A. nnderwing: Store Traffic forecasting for the HBIA [AD-A077370] N81-14969 A81-18090 7AOCBEBET, X. IHOBPKIIS. B. T.. JB. Model vibrations beyond low-speed stall Comparison of experimental and computational shock A81-19552 structure in a transonic coapressor rotor VAOSHA8. t. W. [ASBE PAPER 80-GT-81] A81-17953 Aeronautical concerns and National Aeronautics and TBOBBTOH, J. B. Space Administration atmospheric electricity Sealing joints and cracks, thin resurfacing, and projects locating voids under concrete slabs H81-11567 [PB80-215635] N81-14182 VOELCKEBS, 0. TIJDEHAH. H. Applicated techniques for the control of approach Transonic wind tunnel tests on an oscillating wing traffic with external store. Part 4: The King with [DFVLB-BITT-79-20] H81-14992 underwing: store VOLHIB, A. S. £»D-A077370] H81-11969 The method of superelements in the dynamics of TODA, 4. complex structures Approximation of gear transmission error by A81-16969 standard gear errors [&SBE PAPEB 80-C2/DET-71] A81-18646 TOBDIOB. G. T. w Approximation of gear transmission error by IADIA, A. B. standard gear errors A pure direct force/moment control for coaxial [&SSE PAPEB 80-C2/DET-71] A81-18646 counterrotating rotors TOBEHBEEK, B. H81-15007 Fundamentals of conceptual design optimization of 1AGBEB, O. subsonic transport aircraft The supercritical profile of the supercritical wing [VTH-LB-292] H81-13951 A81-17522 TBIJ08IS. J. BALKEB, J. E. Statistical relationship between median .visibility A case study on the F-16 fly-by-wire flight and conditions of vorstcase manmade impact on control system visibility A81-16719 [LA-UH-80-2485] . N81-11550 IALI, B. L. IBITEDI. K. S. Advanced flight deck/crew station simulator Validation Methods Besearch for Fault-Tolerant functional requirements Avionics and Control Systems Sub-Dorking Group [HASA-CB-159331] N81-11991 Beeting. CABE 3 peer review IALLBB, B. A. [NASA-CP-2167] N81-15702 Environmental aspects of airport planning TDCKBB, B. T. A81-18091 Canada's national aviation forecasting models IALIBOOB. L. A81-18072 A•survey of new technology for cockpit application TDJAKA, S. to 1990's transport aircraft simulators Collisions between aircraft and birds [HASA-CE-159330] N81-14993 A81-19445 IAB6, D. TOBCZEBIBK, B. Finite difference computation of the steady Exhaust gas reingestion ueasurements transonic potential flow around airplanes A81-17521 A81-17802 TDBE. B. IABG. B. Experimental investigation of a right angle wing Experimental investigations on shock-associated with partially separated flow with and without noise ground effects A81-17735 [DGLB PAPEB 80-111] A81-19397 iAIG, z. liJGGS, I. E. A preliminary experimental investigation of the 757/767 design considerations for improved response of a turbojet engine to inlet pressure productivity distortion A81-1658I1 A81-17824 TiOBBI. B. J. The measurement and analysis of station parameters Beview of engine/airframe/drive train dynamic of a turbojet engine interface development problems A81-17825 A81-17516 iATAHABE, T. Aeronautical-Baritiae Engineering satellite /AaES/ program of Japan u [IAF PAPEB 80-D-171] A81-18318 UIGDB. E. B. BBBBB, O. Nondestructive dynamic testing flidair and near midair collisions on two- and A81-19657 three-dimensional curvilinear flight paths [DFV1B-FB-80-13] H81-13944 BEOAB, B. I. Beasuring weather for aviation safety in the 1980's H81-11568 B-11 PBBSOIU. 40IHOB IIDBI ZHOU, I. IEDBKZB0. 6. IB. T. Calculation of the lift dependent drag polar of Structural analysis of fuselages vith cutouts by cambered fighter plane configurations with finite element method deflected maneuver flaps in the subsonic region A81-17816 by Beans of a nodified procedure according to TOSBIZABA. A. Lanar An investigation of support-interference effects [DGLB PAPEB 80-109] 481-19395 [BAL-TH-622] 581-1198" Procedures for optimal drag design of camber and IOSO, J. flap deflection in supersonic regions vith An experimental study on kerosene-hydrogen hybrid consideration to geometric limits combustion in a gas turbine combnstor [DGLB PAPEB 80-110] A81-19396 481-17841 1ED6B. B. B. lOSt, S. B. Coatings in the aero gas turbine DC-to-DC pover supply for light aircraft flight A81-17167 testing BBBBBB, B. P. [S4SA-CB-163850] H81-14989 Computer generated displays and pilot effectiveness 100. S. A81-18082 The measurement and analysis of station parameters HBIHBBJCB, B.-l. of a turbojet engine One-dimensional considerations concerning the A81-17825 stability behavior of inlet diffnsers for TODS6BAHS. J. L. supersonic aircraft Curved centerline air intake for a gas turbine A81-17548 engine RBISGBBBBB, D. [NAS4-CASE-LEB-13201-1] N81-14999 Constant-amplitude and flight-by-flight tests on TO. J. CEBP specimens 4 preliminary experimental investigation of the [8BB-FE-2/S/POB-26] H81-14006 response of a turbojet engine to inlet pressure •BSLBB, J. B. distortion The federal role in airport noise control planning 481-17824 A81-18073 TO, I. J. iEVBBS, L. J. Gcid generation for general three-dimensional Experimental analysis and methods to determine the configurations dynamic behavior of propulsion shafting systems N81-14714 H81-15401 IOBCZIK. B. F. IBITB. P. C. Advanced ejection seat for high dynamic pressure The role of aircraft separation assurance in the escape. Hind tunnel test cockpit [AD-A091810] M81-13940 481-18092 •BITE, 6. 4 low height 2300 kW helicopter transmission Kith an enclosed planetary gear ZABABAKBIH, B. I. [ASHE PAPER 80-C2/DET-17] A81-18642 Stationary displacement of a body by a shock vave BHITBLAB, J. B. 481-17622 Vector and scalar characteristics of opposing jets ZABABAKBIH, H. B. discharging normally into a cross-stream Stationary displacement of a body by a shock vave 481-17997 A81-17622 ilUIAHS. D. t. ZBABG, C. Testing model rotorcraft for overvater operations An experimental investigation of the rotating 481-18058 stall, surge, and vake behind the rotor for a 8ILLI4MS. i. D. single stage axial compressor Laser-Baman/Rayleigh flow diagnostic techniques A81-17826 applied to subsonic flov ZHASS, B. [AD-A091695] S81-14275 An experimental investigation of the rotating ilLLSHlBE, I. L.. JB. stall, surge, and vake behind the rotor for a Assessment of ground effects on the propagation of single stage axial compressor aircraft noise: The 1-384 flight experiment 481-17826 [HASA-TP-1747] H81-14788 ZBAO. 3. BinLIFF, C. B. An optimum design procedure of total-temperature Further investigations of adaptive-vall wind tunnels thermocouple probes [AD-A091774] H81-13977 A81-17807 BOODBAS, A. L. 4 preliminary experimental investigation of the Vanadium trineodecanoate promoter for response of a turbojet engine to inlet pressure fiberglass-polyester soil snrfacings distortion [AD-A091785] H81-14084 481-17824 •BICBT, F. F. The measurement and analysis of station parameters L-1011 Flight Management System design of a turbojet engine considerations A81-17825 A81-18074 ZflBH, I. BO. I. Finite difference computation of the steady A preliminary experimental investigation of the transonic potential flov around airplanes response of a turbojet engine to inlet pressure A81-17802 distortion ZBBBG, L. A81-17824 The measurement and analysis of station parameters The measurement and analysis of station parameters of a turbojet engine of a turbojet engine 481-17825 A81-17825 ZBIGDLBV, T. H. Thin minimum-drag airfoils 481-19630 ZHI1IH, ID. L. ID. I. The sonic boom from an aircraft flying along an The matrix analysis of wings arbitrary path in a stratified atmosphere in the A81-17818 presence of a three-component vind 481-19636 ZBOO, I. An aerodynamic design method for transonic axial IAH6. Q. flov compressor stage The automatic matrix force method and technigues 481-17805 for handling more complex computations vith given computer capacity A81-17815 B-15 ZBD, t. PBBSOIAL ADTBOB IIDEX SHO. f. An aerodynamic design method for transonic axial flow compressor stage A81-17805 SHO, a. A vaporising combastor Kith doable combustion spaces A81-17827 KBD, 8. The matrix analysis of wings A81-17818 ZBDLISA. 10. v. Detection of moving objects A81-18773 ZIHH, B. T. Prediction of sound radiated from different practical jet engine inlets [NASA-CR-16382«] H81-1«789 ZOLLA8S, G. F. Aircraft maintenance. Citations from the International Aerospace Abstracts data base [NASA-CB-163837] 881-13917 Technological forecasting—aircraft design. Citations from the International Aerospace data base [NASA-CB-163833] B81-13957 B-16 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 134) APRIL 1981 Typical Contract Number Index Listing HASl-16000 H81-11013 CONTRACT NASA ACCESSION NUMBER NUMBER Listings in this index are arranged alphanumerically by contract number. Under each contract number, the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first. The accession number denotes the number by which the citation is identified in either the fAAor STAR section. 4F PBOJ. 2301 NASU-3198 N81-15579 N81-13955 NASB-3199 N81-1U962 &F PBOJ. 2U02 NAS1-1U849 N81-13923 N81-13940 HAS1-1553U N81-13920 AF PBOJ. 3018 H81-14970 N81-14325 N81-14971 AP PBOJ. 3066 HAS1-15546 H81-la993 N81-14276 H81-14994 4F PBOJ. 7351 NAS2-9399 N81-14998 N81-1U061 SAS3-19698 N81-14082 AF PROJ. 7930 SAS3-20055 H81-14976 H81-13966 SAS3-20072 H81-15006 AF-AFOSB-3233-77 NAS3-20599 881-15005 N81-14969 SAS3-21259 H81-15004 AF-AFOSB-3569-78 NAS3-21272 N81-13963 N81-13955 HAS3-21288 N81-15003 BHFT-ET-4086-A NAS3-21391 N81-15769 N81-15467 KAS4-2534 H81-13969 DAAG46-78-C-0030 SAS5-24300 A81-18100 N81-14324 HAS6-2639 N81-14601 DAAJ02-77-C-0037 BAS8-32692 M81-1t555 A81-17516 NE-5061-013 N81-14985 DE-AC02-78CS-54867 NGL-22-009-383 N81-14329 A81-17953 DE-AC02-80EB-10570 SGB-39-009-017 N81-14363 N81-14989 DE-AC03-79ET-15332 NSEBC-A-7945 A81-16712 N81-15414 HSG-1490 H81-14347 DE-AC03-79ET-15425 NSG-3012 A81-17954 H81-14327 NSG-3171 N81-15001 DE-AC04-76DP-00487 NSG-3189 A81-17952 H81-15148 NSG-4022 N81-14991 DE-AI01-77CS-510I10 H00014-76-C-0068 N81-14082 H81-14064 DOT-FA79HA-4184 H00014-77-C-0247 A81-18089 A81-18578 DOT-FA79WA-4279 S00014-78-C-0079 N81-13949 N81-14986 EC-77-A-31-1011 S61339-79-D-0008 H81-14082 N81-15729 EJ-76-C-01-1806 PBOJ. AFS-560-79-17 N81-14332 N81-13956 FAA PBOJ. 015-390-130 B-7U05-EHG-26 N81-13915 N81-14995 FSV-F-K-80123-78-017-21-001 U-7405-ENG-36 K81-13925 N81-14550 F33615-76-C-5191 501-31-33-05 N81-13921 N81-14061 505-04-82 H81-14977 F33615-78-C-1563 505-06-64 H81-13969 A81-18576 505-10-13-16 N81-13923 F33615-78-C-2008 505-32 N81-14980 N81-14325 505-32-03-01 N81-14788 F33615-79-C-3106 505-32-13-01 N81-14972 N81-139I10 505-33-53-01 N81-13922 F33657-78-C-0473 505-33-63-02 N81-14347 A81-18576 505-34-23-01 H81-13958 F10600-78-C-0003 505-34-33-05 N81-13968 N81-13977 505-34-43-05 H81-15702 F19620-77-C-013 505-41-73-01 H81-13959 A81-18105 H81-14997 F49620-77-C-0066 505-42-71 H81-14981 N81-1II789 505-43-23-02 H81-14975 SAG1-70 H81-15702 505-51-11 H81-14265 HAG3-67 N81-1I1789 506-51-34 S81-15000 HASA OEDEB L-11593 533-01-13-07 N81-15397 N81-13941 533-01-43-01 H81-14973 533-01-43-02 N81-14974 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-703703^) 4. Title and Subtitle 5. Report Date April 1981 AERONAUTICAL ENGINEERING 6. Performing Organijation Code A Continuing Bibliography (Supplement 7. Author(s) 8. Performing Organization Report No. 10. Work Unit No. 9. Performing Organization Name and Address National Aeronautics and Space Administration 11. Contract or Grant No. Washington, O.C. 20546 13. Type of Report and Period Covered 12. Sponsoring Agency Name and. Address 14. Sponsoring Agency Code 15. Supplementary Notes 10. Abstract This bibliography lists 387 reports, articles, and other documents introduced into the NASA scientific and technical information system in March 1981. 17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronaut ics Bi bliograph ies 19. Security Classif. (of this report) 20. Security Classif. (of tr.:; page) 21. No. of Pages 22. Price* Unclass i fied Unclassi fied 117 $5.00 HC For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Lanpley, 1981 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA ents and bibliographic tools to eleven specia ganizations listed below. Each library is prepared to furnish the public such services as terlibrary loans, photocopy service, and assistance in obtaining copies of NASA 'ents for retention CALIFORNIA MASSACHUSETTS University of C Massachi itute of Technology, Cambridge COLORADO MISSOURI University of Colorado, Boulder Linda Hall Library. Kansas City DISTRICT OF COLUMBIA NEW YORK Library of Com Columbia v. New > GEORGIA OKLAHOMA Georgia Institute of Technology University of Oklahoma, Bizzell Library ILLINOIS PENNSYLVANIA The John Crerar Library. Chi Carnegie Library of Pittsburgh WASHINGTON University of Washington, Seattle NASA publications (those H >y an 'd by the following public and free libraries: CALIFORNIA NEW YORK Los Angeles Public Library Brooklyn Public Library San Diego Public Library Buffalo and Erie County Public Library COLORADO Rochester Public Library Denver Public Library New York Public Library CONNECTICUT OHIO Hartford Public Library Akron Public Library MARYLAND Cincinnati Public Library Enoch Pratt Free Library, Baltimore Cleveland Public Library MASSACHUSETTS Dayton Public Library Boston Public Library Toledo Public Library MICHIGAN TENNESSEE Detroit Public Library Memphis Public Library MINNESOTA TEXAS Minneapolis Public Library Dallas Public Library MISSOURI Fort Worth Public Library Kansas City Public Library WASHINGTON St. Louis Public Library Seattle Public Library NEW JERSEY WISCONSIN Trenton Public Library Milwaukee Public Library An extensive collection of NASA and NASA-sponsored documents and aerospace publications available to the public for reference purposes is maintained by the American Institute of Aeronautics and Astronautics, Technical Information Service. 555 West 57th Street, 12th Floor. New York. New York 10019 EUROPEAN An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. By virtue of arrangements other than with NASA, the British Library Lending Division also has available many of the non-NASA publications cited in STAR. European requesters may purchase facsimile copy of microfiche of NASA and NASA-sponsored documents, those identified by both the symbols "#" and "*", from: ESA - Information Retrieval Service, European Space Agency, 8-10 rue Mario-Nikis. 75738 Paris CEDEX 15, France. National Aeronautics and THIRD-CLASS BULK RATE Postage and Fees Paid National Aeronautics and Space Administration Space Administration NASA-451 Washington, D.C. 20546 Official B 5 1 SP-7037, 05J881 S90569AU 850609 Penalty f< NASA SJiEN 6 TECH INiO FACILITY ATTN: ACCESSIONING DEPT P 0 30X 8757 BW1 AfiPfiT BALTIMOBE MD 21240 POSTMASTER: If Undeliverable (Section 158 IWNSA Postal Manual) Do Not Return NASA CONTINUING BIBLIOGRAPHY SERIES NUMBER TITLE FREQUENCY AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation n , and spai AERONAUTICAL ENGINEERING Monthly Engineerin >nd operati' aircraft an imponents NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA p.'. • :or patent NASA SI' EARTH RESOUR' Quarterly , by aircraft and spacecraft RGY Quarterly Annually Details on the'availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. 20546