Aeronautical NASA SP-7037 (115) Engineering November 1979 A Continuing NASA Bibliography with Indexes
i CP coP1 C'Ma bid= National Aeronautics and Space AdministrationCASE FILr c 0 P -Y, Aeronautical Engineering Mu ring Aeronautical Engineerin Kjineering Aeronautical Engin al Engineering Aeronautical I ilautical Engineering Aeronau i&eronautical Engineering Aer bring Aen-NAN-Vautidal Engineerin ineering Aeronautical Engirm al Engineering Aeronautical E 0 eubCal Engineering e%rr"%n%&a%tA e Engineering Aei% ring Aeronautical Engineering NASA SP-1031(115)
AERONAUTICAL ENGINEERING
A Continuing Bibliography
Supplement 115
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 October 1979 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA).
Scientific and Technical Information Branch 1979 NfGA National Aeronautics and Space Administration Washington, DC 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 Engineeriiig -- A Continuing Bibliograph y ( NASA SP-7037) lists 273 reports, journal articles, and other documents originally announced in October 1979 in Scientific and Technical Aerospace Reports (STAR) or in International A erospace A bstracts (IA 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, IAA 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 (A79-10000 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 $6.00 per document up to a maximum of 20 pages. The charge for each additional page is $0.25. Microfiche of documents announced in FAA are available at the rate of $2.50 per microfiche on demand, and at the rate of $1.10 per microfiche for standing orders for all /AA microfiche. The price for the FAA microfiche by category is available at the rate of $1.25 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 $1.35 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 (N79-10000 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 (#) 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 US-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 $3.00 price, for those documents identified by a 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).
iv 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.
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Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (NC) 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.
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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.
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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.
v GENERAL AVAILABILITY
All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and FAA 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 $45.00 domestic; $75.00 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 Pendragon House, Inc.. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 555 West 57th Street, 12th Floor New York, New York 10019 Superintendent of Documents British Library Lending Division, U.S. Government Printing Office Boston Spa, Wetherby, Yorkshire, Washington, D.C. 20402 England
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vii NTIS PRICE SCHEDULES
Schedule A STANDARD PAPER COPY PRICE SCHEDULE
(Effective October 1. 1977)
Price P.g. R . North Anicflc.n Foreign Code Pñc. Pc. *01 Microfiche $ 3.00 $ 4.50 *02 001-025 4.00 8.00 *03 026-050 4.50 9.00 *04 051-075 5.25 10.50 *05 076-100 6.00 1200 *06 101-125 6.50 13.00
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*17 376-400 13.00 26.00 *18 401-425 13.25 26.50 *19 426-450 14.00 2800 *20 451-475 14.50 29.00 *21 476-500 1500 30.00
*22 501-525 15.25 30.50 *23 526-550 15.50 31.00 *24 551-575 16.25 32.50 A25 576-600 16.50 33.00 A99 601-op -- 1/ -- 2/
1/ Add $2.50 for each additional 100 page increment from 601 pages op.
2/ Add $5.00 for each additional 100 page increment from 601 page. op.
Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche
Price North American Foreign Cod. Price Price 801 S 3.25 $ 6.50 E02 4.75 9.50 E03 6.25 12.50 E04 750 15.00 E05 9.00 18.00
806 10.50 21.00 E07 12.50 25.00 E08 1500 30.00 809 17.50 35.00 ElO 20.00 40.00
Eli 22.50 45.00 E12 25.00 50.00 E13 2800 56.00 E14 31.00 62.00 E15 3400 68.00
E16 37.00 74.00 El? 40.00 80.00 E18 45.00 90.00 E19 50.00 10000 E20 6000 120.00
899 - Write for quote NOt 28.00 40.00
VII)
TABLE OF CONTENTS
IAAEntries ...... 561 STAREntries ...... 579
Subject Index ...... A-i Personal Author Index ...... B-i Contract Number Index ...... C-i
TYPICAL CITATION AND ABSTRACT FROM STAR
NASA SPONSORED DOCUMENT AVAILABLE ON ff MICROFICHE NASA ACCESSIONf N79-10024# Northrop Corp.. Hawthorne. Calif. Aircraft NUMBER Group .- STUDY OF AERODYNAMIC TECHNOLOGY FOR VSTOL CORPORATE FIGHTER/ATTACK AIRCRAFT: HORIZONTAL ATTITUDE SOURCE CONCEPT Final Report TITLE S. H. Brown May 1978 242 p refs Sponsored in part by I __Jthe David Taylor Naval Ship Research and Development Center, I______Bethesda. Md. PUBLICATION .-(Contract NAS2-9771) DATE AUTHOR (NASA-CR-152130; N0R78-54) Avail: NTIS - HC Al 1/MF AOl CSCL 01A A horizontal attitude VSTOL (HAVSTOL) supersonic fighter LABILITY CONTRACT attack aircraft powered by RALS turbofan propulsion system is SOURCE OR GRANT analyzed. Reaction control for subaerodynamic flight is obtained in pitch and yaw from the RALS and roll from wingtip jets powered by bleed air from the RALS duct. Emphasis is placed REPORT on the development of aerodynamic characteristics and the COSATI NUMBERS ' identification of aerodynamic uncertainties. A wind tunnel program CODE is shown to resolve some of the uncertainties. Aerodynamic data developed are static characteristics about all axes. control effectiveness, drag, propulsion induced effects and reaction control characteristics. G.Y.
TYPICAL CITATION AND ABSTRACT FROM IAA
NASA SPONSORED AVAILABLE ON $f MICROFICHE AIAA ACCESSION A79. 10266 # An experimental study of three-dimensional NUMBER turbulent boundary layer and turbulence characteristics inside a trboflcleryror passage. A. K. Anand and B. Lakshminarayana AUTHORS (Pennsylvania State University, University Park, Pa.) (A merican TITLE Society of Mechanical Engineers, Gas Turbine Con usd1. Products Show, London, England, Apr. 9-13. .7978, Paper -_ AUTHOR'S TITLE OF 78-GT-1 14.) ASME, Transaction Journal of Engineering for Power. AFFILIATION PERIODICAL vol. 100,Oct. 1978, p. 676-687; Discussion, p. 688-690. 19 refs. Grant No. NGLI9-009-007. I PUBLICATION Three-dimensional boundary layer and turbulence measurements DATE of flow inside a rotating helical channel of a turbomachinery rotor are described. The rotor is a four-bladed axial flow inducer operated at large axial pressure gradient. The mean velocity profiles, turbu- lence intensities and shear stresses, and limiting stream-line angles are measured at various radial and chordwise locations, using rotating triaxial hot-wire and conventional probes. The radial flows in the rotor channel are found to be higher compared to those at zero or small axial pressure gradient. The radial component of turbulence intensity is found to be higher than the streamwise component due to the effect of rotation. Flow near the annulus wall is found to be highly complex due to the interaction of the blade boundary layers and the annulus wall resulting in an appreciable radial inward flow, and a large defect in the mainstream velocity. Increased level of turbulence intensity and shear stresses near the midpassage are also observed near this radial location. (Author)
ix AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 115)
NOVEMBER 1979
A physical model of a single-rotor helicopter with a sling load is developed, and the equations of the hovering helicopter are derived. A stability analysis of the system in banking and in horizontal flight IAA ENTRIES is carried out by the method of small perturbations of the equilibrium State. The modes of helicopter motion are identified, along with the influence of the magnitude of the load, the length of the sling, and the location of its point of attachement on the stability A79-43946 # Parameter and state estimation applicable to of the system. V.P. aircraft identification problem. K. Kanal (National Defense Aca- demy, Yokosuka, Kanagowa, Japan), P. N. Nikiforuk, and M. M. Gupta (Saskatchewan, University, Saskatoon, Canada). Japan Society A79-44451 Service fatigue loads monitoring, simulation, for Aeronautical and Space Sciences, Transactions, vol. 22, May and analysis; Proceedings of the Symposium, Atlanta, Ga., November 1979, p. 1-15.6 refs. 14-15, 1977. Symposium sponsored by the American Society for The problem considered in this paper is the estimation of the Testing and Materials. Edited by P. R. Abelkis (Douglas Aircraft Co., states and parameters of an nth-order linear system where only the Long Beach, Calif.) and J. M. Potter (USAF, Flight Dynamics input and output can be observed. A new canonical form suitable for Laboratory, Wright-Patterson AFB, Ohio). Philadelphia, Pa., Ameri- simple adaptive observer synthesis is defined. The computational can Society for Testing and Materials (ASTM Special Technical algorithm which represents the convergence of the identification Publication, No. 671), 1979. 289 P. $29.50. scheme is derived. Proof of convergence is provided without using such techniques as the Liapunov function. Computational results for The symposium focuses on fatigue and fracture control and a VTOL aircraft estimation problem show that the implementation is emphasizes the need for more precise analytical definition and very simple and she convergence is quite rapid. S. D. testing simulation of the fatigue cyclic loading environment for higher reliability in structural design. Papers cover aircraft, bridge, ship, crane, and ground transportation fields. Specifically, papers on A79-43993 # Modern concepts for design of delta wings for random load analysis as a link between Stress measurement and supersonic aircraft of second generation. A. Nastase (Aachen, fatigue life, aircraft load monitoring, assessing service load experi- Rheinisch.Westfälische Technische Hochschule, Aachen, West Ger- ence, a crack-growth gage for monitoring fatigue cracks, flight many). (Gesellschaft für angewandte Mathematik und Mechanik, spectra development for fighter aircraft, gust spectra prediction of Wissenschaft/iche Jahrestagung, Brussels, Belgium, Mar. 28-31, fatigue damage, simulation of loads in crane beams, and test 1978.) Zeitschrift für angewandte Mathematik und Mechanik, vol. simulation of fighter aircraft maneuver load spectra are presented. 59, May 1979, p. T 246-T 248.8 refs. A.T. A fully optimal delta wing (called Model-Adela l-Aachen) has been realized for second generation supersonic aircraft. This wing A79-44453 State of the art in aircraft loads monitoring. L. model is convex in the neighborhood of its apex and assumes a wavy E. Clay, A. P. Berens, and R. J. Dominic (Dayton, University, shape in the neighborhood of the trailing edge. The wing is angular Dayton, Ohio). In: Service fatigue loads monitoring, simulation, and along the leading edges and sharp along the trailing edges. Theory analysis; Proceedings of the Symposium, Atlanta, Ga., November
predicts that this fully optimized wing has half the frictionless drag 14-15, 1977. Philadelphia, Pa., American Society of an equivalent planar delta wing flying at the same cruising speed. for Testing and Materials, 1979, p. 21-35. 6 refs. B.J. The paper summarizes current state-of-the-art equipment and techniques for the monitoring of loads during military aircraft A79-44083 Effect of inertia of blower on stability of operation. Monitoring systems are discussed which record strain, air-cushion vehicle. L. A. Maslov and Ia. G. Panovko. (Akademiia center-of-gravity motions, and control deflections, or the occurrence Nauk SSSR, lzvestiia, Mekhanika Tverdogo Tela, Sept.-Oct. 1978, p. of selected load conditions. The raw data are reduced to sequences of 51-54.) Mechanics of Solids, vol. 13, no. 5, 1978, p. 44.48. stress peaks and troughs or to tabulations of peaks and coincident Translation. values of the recorded parameters. Finally, monitoring system cost A theoretical analysis is used to investigate small vertical estimates are provided for typical applications to individual aircraft translational oscillations of an air cushion vehicle. Particular consid- tracking and loads and environmental spectra survey problems. eration is given to the role of inertia of the blower system. B.J. (Author)
A79-44094 # Longitudinal dynamic stability of a hovering A79-44454 Determination of sample size in flight loads helicopter with a sling load (Podluzna statecznosc dynamiczna programs. A. P. Berens (Dayton, University, Dayton, Ohio). In: smiglowca z podwieszonym ladunkiem w zawisie). W. Lucjanek and Service fatigue loads monitoring, simulation, and analysis; Proceed- K. Sibilski (Warszawa, Polit&chnika, Warsaw, Poland). Mechanika ings of the Symposium, Atlanta, Ga., November 14-15, 1977. Teoretyczna i Stosowana, vol. 17, no. 2, 1979, p. 263. 276. 11 refs. Philadelphia, Pa., American Society for Testing In Polish. and Materials, 1979, p. 36-47. USAF-supported research.
561 A79-44455
This paper describes the application of a statistical model of a airframe. A life history recording program monitors the actual cumulative damage index to the problem of determining the number operational environment and response by onboard recorders which of flights to be monitored in aircraft operational usage programs read aircraft speed, normal load factor, altitude, and strain level. In based on samples of flights. The method can be used to calculate the summary, the C-141A service life monitoring program is a continual optimum number of flights to achieve given precision and confidence effort to translate significant operational factors into cost-effective under stratified sampling. It also provides a method for determining force management decisions pertaining to maintenance-inspection precision at any level of confidence given a sample size. Examples of timely replacement, and operational readiness. A.T. the use of the techniques are provided using data from the operational usage programs of three aircraft types. (Author) A79-44458 Evaluation of a crack-growth gage for moni- toring possible structural fatigue-crack growth. N. E. Ashbaugh (Systems Research Laboratories, Inc., Dayton, Ohio) and A. F. A79.44455 Use of AIDS recorded data for assessing service load experience. J. B. de Jonge and D. J. Spiekhout (National Grandt, Jr. (USAF, Materials Laboratory, Wright-Patterson AFB, Lucht- en Ruimtevaartlaboratorium, Amsterdam, Netherlands). In: Ohio). In: Service fatigue loads monitoring, simulation, and analysis; Service fatigue loads monitoring, simulation, and analysis; Proceed- Proceedings of the Symposium, Atlanta, Ga., November 14-15, 1977. ings of the Symposium, Atlanta, Ga., November 14 . 15, 1977. Philadelphia, Pa., American Society for Testing Philadelphia, Pa., American Society for Testing and Materials, 1979, p. 94-117. 18 refs. The use of a precracked coupon for monitoring the effect of and Materials, 1979, p. 48-66. Results of the aircraft integrated data system (AIDS) recorded structural loads upon fatigue crack growth is presented. The coupon aircraft mission profile data and information on loading environment or 'gage' provides a convenient means for determining crack growth are presented. All primary aircraft structures must be regularly since crack extension in we ydge is a result of loads on the structure inspected for fatigue cracking. The inspection periods and safe which cause the damage. Experimental results are reported for gages service lives of transport aircraft are based on an assumed average made from two aluminum alloys with two types of crack geometries, design load, corresponding to average usage under average environ- a center crack and a crack at the edge of a hole. The effect of load mental conditions. However, the actual load experience may deviate amplitude upon crack growth in the gage as a function of the crack appreciably from these assumptions, and therefore AIDS system was growth in the structure was investigated using constant amplitude developed to extract on a routine basis fatigue load related data for cyclic load. A theoretical model was developed to predict the the 747 aircraft. AIDS criteria including time interval, flight mode, correlation between the growth of cracks in the gage and the and limit exceedance, acquisition of fatigue-relevant load data, load structure, and the load transfer from the structure through the ends data extraction, data quality assurance, data storage, and analysis of of the gage and the crack-propagation law for the crack growth in the fatigue load data are discussed. Finally, data analysis results and gage and the structure were important factors in the analysis. A.T. examples of aircraft usage are tabulated. A.T.
A79.44459 Flight spectra development for fighter aircraft, A79-44456 Overview of the C.5A Service Loads Recording N. H. Sandlin, R. R. Lauridia, and D. J. White )Vought Corp.; Dallas, Program. W. J. Stone, A. M. Stanley, M. J. Tyson, and W. H. Tex.). In: Service fatigue loads monitoring, simulation, and analysis; Kimberly (Lockheed-Georgia Co., Marietta, Ga.). In: Service fatigue Proceedings of the Symposium, Atlanta, Ga., November 14-15, 1977. loads monitoring, simulation, and analysis; Proceedings of the Philadelphia, Pa., American Society for Testing Symposium, Atlanta, Ga., November 14-15, 1977. and Materials, 1979, p. 144-157. 6 refs. Philadelphia, Pa., American Society for Testing and A method is presented for deriving realistic flight-by-flight stress Materials. 1979, p. 67.83. 8 refs. spectra which are valid for any point in the structure of fighter or The United States Air Force (USAF) C-5A Service Loads attack type aircraft. This method uses regression equations to define Recording Program (SLRP) was initiated in the early 1970s to the relationships among stresses and flight parameters. The statistical acquire in-service data in sufficient quantity to define the operational distributions of aircraft motion parameters are derived and defined in environment of an 'average' C-5A and to develop repeated loads, multi-parameter response tables. These tables are combined with (Stress) spectra for applications in loads and fatigue analyses. assigned mission profile data to establish all of the required flight Instrumentation was installed on 26 airplanes to record up to 53 parameters which are used in the regression equations to develop different data parameters on magnetic tare by means of the C-5A stress spectra. These spectra then are sequenced into a flight-by-flight MADARS recorder. Over 9000 h of usable operational data were order which can be used as input to a damage determination model acquired in the course of the program. Using these measured data or as a load program for laboratory testing. (Author) along with current analytical data for wing stresses, airplane vertical acceleration, and other responses, analyses were conducted for 13 A79.44460 Flight-by-flight spectrum development. A. G. different load sources. The results were new criteria and modified Denyer (Rockwell International Corp., El Segundo, Calif.). In: analytical wing loads which were used in the design phase of the Service fatigue loads monitoring, simulation, and analysis; Proceed- C-5A Wing Modification Program and in the updating of service life ings of the Symposium, Atlanta, Ga., November 14-15, 1977. predictions made by the C-5A Individual Aircraft Service Life Philadelphia, Pa., American Society for Testing Monitoring Program. (Author) and Materials, 1979, p. 158-175. 5 refs. A method of developing the design flight-by-flight sequenced stress spectrum at any location within the primary airframe structure A79.44457 Highlights of the C-141 service life monitoring is presented. The procedure commences with the applicable procure- program. D. S. Morcock (Lockheed-Georgia Co., Marietta, Ga.). In: ment specifications for the aircraft and concludes with the detail's Service fatigue loads monitoring, simulation, and analysis; Proceed- local stress spectrum suitable for fatigue and fracture mechanics ings of the Symposium, Atlanta, Ga., November 14-15, 1977. analyses or testing. The stress spectrum is created within a computer Philadelphia, Pa., American Society for Testing program that utilizes input data comprising mission profiles, struc- and Materials, 1979, p. 84-93. tural location data, libraries of load factor exceedance data, balanced The paper presents the C-141A aircraft structural integrity external load conditions, and corresponding internal loads solutions. program, with emphasis on the service life monitoring and life The output consists of the spectrum in tabular form and the time history recording program activities. The structural integrity program trace graphs of the stress amplitude. Included is a typical spectrum requirements including static strength and fatigue analyses are developed for a variable geometry bomber with terrain-following described. The service life monitoring includes service life analyses capability, and discussion as to load sequence effects and the utilizing velocity-acceleration-altitude and ground load data, and structural internal loads solutions necessary to describe the stress fatigue endurance life for fatigue-susceptible locations on the trace on a mission-by-mission basis. Finally, the system-generated
562 A79-44878
spectrum is discussed in terms of its effect on fatigue and fracture A79-44794 Computer aided design of mixed flow turbines mechanics analysis. (Author) for turbochargers. N. C. Baines, F. J. Wallace, and A. Whitfield (Bath, University, Bath, England). (American Society of Mechanical En- A79.44461 Methods of gust spectra prediction for fatigue gineers, Gas Turbine Conference, London, England, Apr. 9-13, 1978, damage. W. W. Wilson and J. E. Garrett (Lockheed-Georgia Co., Paper 78-GT- 191.) ASME, Transactions, Journal of Engineering for Marietta, Ga.). In: Service fatigue loads monitoring, simulation, and Power, vol. 101, July 1979, p. 440-448; Discussion, p. 448, 449; analysis; Proceedings of 'the Symposium, Atlanta, Ga., November Authors' Closure, 16 refs. Research supported by the Science 15, 1977. Philadelphia, Pa., American Society p.449. 14. Research Council and Holset Engineering Co. 176-192. 7 refs. Contract No. for Testing and Materials, 1979, p. The paper describes a comprehensive computer aided design F33657-76.D.0873. procedure and its use to investigate mixed flow turbines for The prediction of aircraft responses to atmospheric turbulence automotive turbocharger applications. The outside dimensions of using a general exponential gust exceedance equation is bated on the rotor and casing as well as blade angles are determined from assumption that altitude dependent spectra curve fit parameters one-dimensional design and off design calculations, the detailed blade contained in the exceedance equation are representative of the shape from quasi-three-dimensional analysis and mechanical stressing atmosphere and thus equally applicable to accelerations, loads, and vibration programs, and geometric data are presented as outside stresses, etc. Using vertical acceleration gust data recorded during views and sections of the rotor by a graphics subroutine. The .5A transport aircraft, altitude fleet operations of the USAF C procedure consists of a series of separate programs rather than a dependent curve fit parameters were developed; these parameters single program, so that the designer's intervention at each stage of were then shown to accurately predict the recorded wing stress gust the process can be applied. Two mixed flow rotors were designed,
experience at three wing locations, thus supporting the assumption manufactured and tested in a specially designed high speed of their uniformity between response parameters. This gust analysis dynamometer. The first was intended to achieve a substantial then was substantiated with a second, independent analysis in which increase in mass flow over the reference radial rotor without loss of the recorded vertical acceleration gust data were converted directly efficiency, while the latter was intended as a direct replacement of to stress spectra by means of analytical stress to acceleration ratios. the reference radial rotor, but should give more favorable pulse (Author) performance when operating in conjunction with an engine due to changes in the operating map viz: a) lower tip speeds for best A79.44462 Derivation of flight-by-flight spectra for fighter aircraft. M. P. Kaplan, J. A. Reiman, and M. A. Landy efficiency, and b) flatter mass flow characteristics. Both effects were (Author) (USAF, Structures Div., Wright-Patterson AFB, Ohio). In: Service predicted by analysis and confirmed by tests. fatigue loads monitoring, simulation, and analysis; Proceedings of the 15, 1977. Symposium, Atlanta, Ga, November 14. A79-44800 # Propulsion system and airframe integration Philadelphia, Pa., American Society for Testing and consideration for advanced air-to-surface aircraft. R. J. May )USAF, Materials, 1979, p. 193.207. Aero Propulsion Laboratory, Wright-Patterson, AFB, Ohio) and G. Methods of obtaining the usage data and developing a flight- K. Richey (USAF, Flight Dynamics Laboratory, Wright-Patterson, by-flight spectrum for a ground attack fighter in the design phase and AFB, Ohio). AIAA, SAE, and ASME, Joint Propulsion Conference, for an existing aircraft that has undergone a change in usage are 15th, Las Vegas, Nev., June 18-20, 1979, A IAA Paper 79-1120. 13 p. presented. The importance of predicting the durability and damage Important propulsion system and airframe integration considera- tolerance capability of aircraft structures emphasized the need for a tions for cost-effective advanced air-to-surface aircraft, resulting from realistic flight-by-flight stress spectrum. This stress spectrum is an analytical program employing data from six airframe and three generated from an analysis of the projected mission profiles, engine manufacturers, are discussed. The analysis indicates that combined with load factor exceedance curves obtained from military engine costs will account for nearly 30% of the system development specifications or recorded data. Using either exceedance curve cost, 23% of production cost, and 37% of the operation and support approach, these data are combined with the mission profile data to cost for the system. An advanced technology engine will be required develop a stress-exceedance curve for each mission. The mission to meet mission requirements and minimize system life cycle costs profiles contain information on mission length, number of times for an advanced strike fighter. A simple, single spool, fixed geometry flown per lifetime, fuel load, and weapons configuration. The final turbine turbojet engine is an attractive candidate. Reduced radar result is a random flight-by-flight stress spectra suitable for per- cross section, low inlet weight and reduced subsonic and supersonic A. T. forming damage tolerance and durability analyses and tests. drag are factors which must be considered in an air to surface design. The use of 2-0 nozzles for TCS/l R control, maneuverability A79.44463 Test simulation of fighter aircraft maneuver load spectra. L. L. Jeans and W. L. Tribble (Northrop Corp., enhancement and STOL flexibility will be primary considerations in C.K.D. Hawthorne, Calif.). In: Service fatigue loads monitoring, simulation, air-to-surface vehicle applications. and analysis; Proceedings of the Symposium. Atlanta, Ga., November 14. 15, 1977. Philadelphia, Pa., American Society A79-44874 The influence of turbulence on drag. W. H. for Testing and Materials, 1979, p. 240-254. 5 refs. Contract No. Bell (Institute of Ocean Sciences, Patricia Bay, British Columbia, F33615-75-C-5236. Canada). Ocean Engineering, vol. 6, no. 3, 1979, p. 329-340. 19 refs. The use of power spectral density (PSD) and related laboratory The use of the Reynolds number as the only correlating factor random data analysis techniques to characterize low frequency for drag force measurements may be inadequate in circumstances loading spectra output response, measured from a specimen, for involving highly turbulent flows. The results of previous investiga- comparing test machine responses is studied. A digital technique tions relating to the effects of turbulence scale and intensity are simulating aircraft maneuver spectrum loading in the time domain is examined. Of special interest is the possibility of a drag minimum, used to generate the input load spectrum signal to an electro- even at low Reynolds number, for a free-stream turbulence intensity hydraulic closed-loop test machine for fatigue testing of graphite- of about 5%. This appears to be the result of interaction between the epoxy to titanium joints at various frequencies and PSD shapes. The free stream and the boundary layer. As intensity increases beyond output signal measured from the specimen was processed to 5%, the minimum may be succeeded by an increase in drag to values determine the PSD response and root mean square history, and these exceeding the laminar flow values. Further elucidation of the subject data were compared with the recorded strain amplitude history and is required, particularly because of its importance in various the input load amplitude, frequency, and PSD information. A problems related to geophysical flows. (Author) qualitative correlation was found between specimen fatigue life, output signal waveform and amplitude, and variations in PSD, and it was concluded that the way a fatigue test machine processes an input Extremal radio-navigation )Ekstremal'naia load and frequency signal can affect the measured fatigue life of A79-44878 , # radio navigatsi ia). V. I. Alekseev, A. M. Korikov, R. I. Polonnikov, certain materials. A. T.
563 A79-44884
and V. P. Tarasenko. Moscow, lzdatel'stvo Nauka, 1978. 280 P. 149 tions, climatic effects on radio equipment, organization of radio refs, In Russian. equipment repairs, safety measures during radio operation, measure- The book presents design approaches and a basic theory of merit devices and methods related to radio systems, noise protection, automatic navigation systems based on the use of extremal control electromagnetic compatibility, and a summary of all the tactical principles and statistically optimal radio-navigation signal processing parameters of onboard radio equipment. P.T.H. procedures. Adaptive models, optimization algorithms, first-order difference-measuring systems, and second-order angle- and difference-measuring systems are considered together with the A79-44953 # The temperature at which thermal dissociation principles of partial synthesis of long-range radio-navigation systems, is initiated in jet fuels under static conditions (Temperatura nachala optimization model adaptation, accuracy and noise immunity opti- termicheskogo razlozheniia reaktivnyklu topliv v staticheskikh mizations, and coordinate determination. Attention is given to usloviiakh), A. K. Bukharkin and G. I. Kovalev, Khimiia I Tekh. models of radio channels, instabilities of on-board master oscillators, no/ogiia Topliv i Masel, no. 7, 1979, p. 16. 18. In Russian. signal sources, and navigation spaces. Possibilities of applying the - The temperature at which thermal dissociation is initiated in jet extremal principles of radio-navigation to satellite signal processing fuels was investigated by means of an instrumented autoclave are evaluated. V.T. installation. Fuels were heated to temperatures ranging from 300 to 425 C for a period of 240 mm. Little gas evolution was observed from the fuels studied over the interval 300-380 C. However, the A79-44884 # Aircraft instrument components /3rd revised amount of gas evolved sharply increased at temperatures above 400 and enlarged edition/ (Detali aviatsionnykh priborov /3rd revised and C, accompanied by changes in iodine value. The rate of cracking was enlarged edition/). B. A. Ass, E. F. Ansipov, and N. M. Zhukova. found to decrease with time. The observed temperatures at which Moscow, lzdatel'stvo Mashinottroenie, 1979. 232 p. 68 refs. In dissociation was initiated were in good agreement with results Russian. predicted by kinetic theory. Theoretical, operational, design and calculational aspects of C.K.D. typical aircraft instrument components are presented. Components considered include cylindrical, spherical, prismatic, elastic, air and A79-45067 Application of hot isostatic pressing to aircraft ball bearings, and transmission mechanisms including gears, levers, gas turbines. D. J. Evans (United Technologies Corp., Pratt and stopping mechanisms and clutches. Elastic and inertial sensors, Whitney Aircraft Group, East Hartford, Conn.). In: High-pressure including springs, membranes and Sylphon bellows, parametric science and technology; Proceedings of the Sixth International transducers, including potentiometers, strain resistors, thermoresis- Conference, Boulder, Cob., July 25-29, 1977. Volume 2. tort, capacitance and inductance sensors and photosensitive New York, Plenum Press, 1979, p. 656-663. 8 refs. elements, generating sensors, including thermoelectric, induction, Background, equipment, and applications of hot isostatic peizoelectric and barrier-layer cell devices, and magnetoelectric, pressing (HIP) of gas turbine components are reviewed. HIP electromagnetic and electrodynamic sensors are discussed. Attention equipment using pressures up to 30,000 psi and various heating is also given to gyromotors, dampers, shock absorbers, electrical methods is described. HIP powder consolidation was used to make contacts, indicators and housings. A.L.W. nickel-base superalloy turbine disks and titanium alloy compressor disks, achieving material and cost savings and improved mechanical properties. Densification of structural and rotor castings to minimize A79-44892 # Aircraft antenna systems (Samoletnye anten- porosity and segregation and improve mechanical properties was nye sistemy). lu. G. Shatrakov, M. I. Rivkin, and B. G. Tsybaev. accomplished with HIP. This process is also used to improve the Moscow, lzdatel'stvo Mash inostroenie, 1979. 184 p. 67 refs. In quality of turbine airfoil and hot-section case castings. Future uses of Russian. HIP in processing superalloy powders will include the fabrication of Factors affecting the design of aerial feeders are discussed. The hybrid structures-components requiring two different levels of characteristics and principles of operation of different types of aerial mechanical properties. A.T. antenna-feeder systems are reviewed, and the interaction of the elements of these systems with aircraft components is examined. A79-45249 Disaggregate mode-share models for air freight Theoretical methods used in design development to assess the policy analysis. L. B. Wilson (Atchison Topeka and Santa Fe Railway performance of systems and system components are considered. Co., Chicago, III.) and N. K. Taneja (MIT, Cambridge, Mass.). Systems using dipole antennas, slot antennas, driven antennas, hybrid Transportation Research, vol. 13A, Apr. 1979, p. 115-123. 22 refs. antennas, and leaky antennas are described, and test methods are This paper describes the modification and extension of a new presented. C.K.D. disaggregate simulation freight demand model, developed at MIT center for Transportation Studies, for analysis of air cargo. This model system, utilizing existing published data, develops estimates of A79-44893 # Assembly and testing of flight-vehicle hy- modal shares for individual commodity groups in any specified U.S. draulic and pneumatic systems /2nd enlarged and revised edition/ domestic city pair market. Firms are assumed to minimize 'total (Montazh i ispytanie gidravlicheskikh i pnevmaticheskikh sistem logistics Cost' in making modal choice decisions. Individual results are letatel'nykh apparatov /2nd enlarged and revised edition/). V. M. accumulated and modal share estimates developed which can then be Sapozhnikov. Moscow, lzdatel'stvo Mashinostroenie, 1979. 256 p. 37 used in preparing aggregate forecasts of modal flows. The study refs. In Russian. clearly demonstrates the feasibility of extending this demand model Theoretical and experimental results on the design and opera- to include analysis of air cargo. The model system is applied to the tional testing of aircraft hydraulic, pneumatic and fuel systems are Houston-Chicago and Los Angeles-Boston market pairs, with encour- discussed. Consideration is given to Ill determination of stress-strain aging empirical results: the model share estimates are quite plausible states during assembly, (2) techniques for cleaning such systems, (3) when compared with existing flow information. (Author) quality control techniques, (4) ways to assure hermetic conditions, and (5) performance testing techniques. B.J. A79-45250 Review of aircraft bearing rejection criteria and causes. J. S. Cunningham, Jr. and M. A. Morgan (U.S. Navy, A79'44894 # Handbook of flight communication and radio Naval Air Rework Facility, Cherry Point, NC.). Lubrication Engi- equipment (Spravochnuk p0 sviazi i radiotekhnicheskomu obespeche- 'leering, vol. 35, Aug. 1979, p. 435-441. niiu poletov). lii. I. Dukhon, N. N. ll'inskii, and G. I. Laushev. This paper presents the results of an aircraft ball and roller Moscow, Voenizdat, 1979, 287 p. 19 refs. In Russian. bearing rejection analysis undertaken at the Naval Air Rework The book supplies reference data on the choice, design, and Facility, Cherry Point, North Carolina. Data utilized in this analysis installation of aircraft communication and radio systems. Sections was derived from three 80-day engineering samples taken during are devoted to the effect of the atmosphere on flight communica- 1969, 1971 and 1977. Actual numerical and statistical failure data
564 A79-45303 pertaining to corrosion, pitting, wear, fatigue, etc. are discused and (NASA, Ames Research Center, Computational Fluid Dynamics overall conclusions are drawn concerning earth rejection category. Branch, Moffett Field, Calif.),. and D. Anderson (Iowa State The results of this analysis should provide a base for studies of the University of Science and Technology, Ames, Iowa). In: Computa- economics of bearing reprocessing and aid in identifying those areas tional Fluid Dynamics Conference, Williamsburg, Va., July 23-25, where developmental work can provide the most significant increases 1979, Collection of Technical Papers. New York, in bearing life and dependability. (Author) American Institute of Aeronautics and Astronautics, Inc., 1979, p. 204-217. 39 refs. Research supported by Iowa State University of A79.45258 • # Numerical solution for the flow field of a Science and Technology and NASA. )AIAA 79-1465) body with jet. N.-S. Liu (Joint Institute for Advancement of Flight A new technique is described for solving supersonic fluid Sciences, Hampton, Va.). In: Computational Fluid Dynamics Con- dynamic problems containing multiple regions of continuous flow, ference, Williamsburg, Va., July 23-25, 1979, Collection of Technical each bounded by a permeable or impermeable surface. Region Papers. New York, American Institute of Aero- boundaries are, in general, arbitrarily shaped and time dependent. Discretizasion of such a region for solution by conventional finite nautics and Astronautics, Inc., 1979, p. 66-73. 16 refs. Grant No. NGR-09-010.085. (AIAA 79-1452) difference procedures is accomplished using an elliptic solver which This paper presents a method of computing the laminar flow alleviates the dependence on a particular base coordinate system. field of a body with stern-mounted jet. Problems involved are the Multiple regions are coupled together through the boundary condi- numerical solutions of boundary layer and Wavier-Stokes equations tions. The technique has been applied to a variety of problems as well as the viscous-iriviscid interaction. The adequacy of a simple including the shock diffraction and pointed wedge with detached viscous-inviscid interaction approach is investigated and a technique bow shock. )Author) for connecting hybrid mesh systems without overlapping of meshes is A79-45273 • # Vector processor algorithms for transonic flow presented. The numerical results indicate that while the external calculations. J. C. South, Jr., J. D. Keller (NASA, Langley Research wake flow affects the development of the jet flow, the presence of a Center, Hampton, Va.), and M. M. Hafez (Flow Research Co., Kent, jet also influences the flow in the stern region of the body. (Author) Wash.). In: Computational Fluid Dynamics Conference, Williams- A79-45261 * II A fast, conservative algorithm for solving the burg, Va., July 23-25, 1979, Collection of Technical Papers. transonic full-potential equation. T. L. Hoist (NASA, Ames Research New York, American Institute of Aeronautics Center, Applied Computational Aerodynamics Branch, Moffett and Astronautics, Inc., 1979, p. 247-255. 13 refs. (AIAA 79-1457) Field, Calif.). In: Computational Fluid Dynamics Conference, This paper discusses a number of algorithms for solving - the .25, 1979, Collection of Technical Papers. transonic full-potential equation in conservative form on a vector Williamsburg, Va., July 23 computer, such as the CDC STAR-100 or the CRAY-1. Recent New York, American Institute of Aeronautics research with the 'artificial density' method for transonics has led to and Astronautics, Inc., 1979, p. 109-121. 23 refs. (AIAA 79-1456) development of some new iteration schemes which take advantage of A fast, fully implicit approximate factorization (AF) algorithm vector-computer architecture without suffering significant loss of designed to solve the conservative transonic full-potential equation in convergence rate. Several of these more promising schemes are either two or three dimensions is described. The algorithm uses an described and 2-13 and 3-D results are shown comparing the upwind bias of the density coefficient for stability in supersonic computational rates on the STAR and CRAY vector computers, and regions. This provides an effective upwind difference of the the CYBER-175 serial computer. Schemes included are: (1) Checker- streamwise terms for any orientation of the velocity vector (i.e., board SOR, (2) Checkerboard Leapfrog, (3) odd-even vertical line 'rotated differencing'), and thereby greatly enhances the reliability of SOR, and (4) odd-even horizontal line SOR. (Author) the present algorithm. A numerical transformation is used to establish an arbitrary body-fitted finite-difference mesh. Computed A79-45302 Atmospheric Flight Mechanics Conference for results for both airfoils and simplified wings demonstrate substantial Future Space Systems, Boulder, Cob., August 6-8, 1979, Collection improvement in convergence speed for the new algorithm relative to (Author) of Technical Papers. Conference sponsored by the American Institute standard successive-line overrelaxation algorithms. of Aeronautics and Astronautics. New York, American Institute of A79-45265 # Three-dimensional coordinates about wings. P. Aeronautics and Astronautics, Inc., 1979. 489 p. $35. R. Eiseman. In: Computational Fluid Dynamics Conference, Williamsburg, Va., July 23-25, 1979, Collection of Technical Papers. A group of papers discussing various aspects of flight mechanics New York, American Institute of Aeronautics applicable to future space systems is presented. Theoretical models and Astronautics, Inc., 1979, p. 166.174. 6 refs. (AIAA 79-1461) and experimental techniques for predicting and testing the aerody- The three-dimensional problem of mesh generation about namic performance of air- and spacecraft are considered, together airplane wings is studied with the development of a coordinate with control system hardware and software. General topics include transformation. Salient features of the coordinates are that arbitrari- aerodynamics, aircraft handling and flight qualities, flight mechanics, ly shaped wings can be specified, that coordinate distributions along parameter estimation, unsteady aerodynamics, and computer the wing surface can be specified, that coordinate angles leaving the systems. C.K.D. wing surface can be specified, that the distribution of coordinate surfaces surrounding the wing can be specified, and that the coordinates can be smoothly joined with a surrounding spherical coordinate syst'sm for a far field analysis. When a far field spherical A79-45303 # Singular perturbation techniques for on-line coordinate system is desired, there is, however, a Constraint on the optimal flight path control. A. J. Calise (Drexel University, Philadel- mesh topology which would otherwise be absent. From the phia, Pa.). In: Atmospheric Flight Mechanics Conference for Future viewpoint of computational economy, she coordinates can be Space Systems, Boulder, Cob., August 6-8, 1979, Collection of generated quickly and with little storage since the basic constructive Technical Papers. New York, American Institute process consists of a short sequence of two-dimensional construc- of Aeronautics and Astronautics, Inc.. 1979, p. 1-8. 9 refs. Grant No. tions. Moreover, when the spherical mesh topology is desired, the NsG-1496, (AIAA 79-1620) coordinates can be given in an analytically defined form so that any This paper presents a partial evaluation on the use of singular mesh point may be obtained directly and with a negligible amount of perturbation methods for developing computer algorithms for on-line storage. (Author) optimal control of aircraft. The evaluation is based on a study of the minimum time intercept problem using F-4 aerodynamic and A79-45269 • # A two-dimensional unsteady Euler-equation propulsion data as a base line. The extensions over previous work on solver for flow regions with arbitrary boundaries. R. G. Hindman this subject are that aircraft turning dynamics (in addition to (NASA, Ames Research Center, Moffett Field, Calif.; Iowa State position and energy dynamics) are included in the analysis, the University of Science and Technology, Ames, Iowa), P. Kutler algorithm is developed for a moving end point and is adaptive to
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A79-45304
unpredictable target maneuvers, and short range maneuvers that do demonstrate that the method provides an efficient nd reliable not have a cruise leg are included. Particular attention is given to procedure for solving a wide variety of trajectory optimization identifying those quantities that can be precomputed and stored (as a problems. (Author) function of aircraft total energy), thus greatly reducing the onboard computational load. Numerical results are given that illustrate the A79-45307 • # Application of the equilibrium spin technique nature of the optimal intercept flight paths, and an estimate is given to a typical low-wing general aviation design. M. B. Tischler and J. B. for the execution time and storage requirements of the control Barlow (Maryland, University, College Park, Md.). In: Atmospheric algorithm. (Author) Flight Mechanics Conference for Future Space Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. A79-45304 // The extremal trajectory map . A new represen- New York, American Institute of Aeronautics and tation of combat capability. N. Rajan (Indian Space Research Astronautics, Inc., 1979, p. 32-42. 19 refs. Research supported by Organization, Satellite Centre, Bangalore, India) and U. R. Prasad. the Minta Martin Fund for Aeronautical Research; Grant No. In: Atmospheric Flight Mechanics Conference for Future Space NsG-1570. (AIAA 79-1625) Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical A graphical implementation of the equilibrium technique for Papers. New York, American Institute of Aero- obtaining spin modes from rotary balance data is presented. Using nautics and Astronautics, Inc., 1979, p. 9-12. 13 refs, (AIAA this technique, spin modes were computed for the NASA Low-Wing 79-1622) General Aviation Aircraft. The computed angles of attack are within Aircraft pursuit-evasion in three dimensions is formulated as a 10 degrees of the NASA spin tunnel results. The method also differential game with five state variables. The aircraft are modeled in provides information on the dynamic nature of spin modes. This energy. A suitable choice of real space coordinates confers open-loop technique offers the capability of providing a great deal of optimality on the game. Its parties can be pieced together using the information on spin modes and recovery, using data from a single individual aircraft's energy extremal maps (EEM). An EEM consists experimental installation. Such a technique could be utilized in the of a stack of constant altitude extremal trajectory maps; it is preliminary design phase in order to provide basic information on essentially a family of single aircraft minimum time maneuvers. It aircraft spin and recovery characteristics. Results, advantages and represents the pursuit-evasion capability of the aircraft independent limitations of the application of this technique are discussed. of adversary, role and capture radius and is hence an effective tool (Author) for design. (Author) A79-45312 # Unsteady wing boundary layer energization. A79-45305 # Approximate trajectory solutions for fighter H. Viets, M. Ball (Wright State University, Dayton, Ohio), and M. aircraft. L. E. Miller (USAF, Flight Dynamics Laboratory, Wright- Piatt, In: Atmospheric Flight Mechanics Conference for Future Patterson AFB, Ohio). In: Atmospheric Flight Mechanics Conference Space Systems, Boulder, Cob.,' August 6-8, 1979, Collection of for Future Space Systems, Boulder, Cob., August 6-8, 1979, Technical Papers, New York, American Institute Collection of Technical Papers. New York, of Aeronautics and Astronautics, Inc., 1979, p. 79-83. 15 refs. Grant American Institute of Aeronautics and Astronautics, Inc., 1979, p. No, AF-AFOSR-78-3525. (AIAA 79-1631) 13-20. (AIAA 79-1623) A rotor mounted in the surface of a symmetrical airfoil section Approximate solutions to the segments of typical fighter is employed to generate vortices in conjunction with the flow over trajectory profiles are obtained. The specific problems addressed are the airfoil. The vortices are swept over she upper surface of the subsonic cruise, supersonic cruise, initial climb, and supersonic airfoil. For separated flow over the airfoil at high angles of attack, acceleration and climb. Closed form solutions for the initial climb the rotor is shown to reduce the size of the separated region and in problem are in good agreement with the results obtained from the addition reduce the pressure on the upper airfoil surface. The integration of the differential equations of state. The agreement is vortices produced by the rotor appear to energize the boundary layer not as good for the supersonic acceleration and climb. Theoretical by bringing higher energy flow from the main stream to the wall subsonic cruise range factor performance results agree quite well with region. the actual optimum results. For the supersonic cruise problem, it is (Author) demonstrated that universal distributions between fuel flow and thrust could be developed that are independent of altitude. Thus A79-45313 # Transonic flutter analysis of a rectangular wing minimum fuel flow or maximum range factor can be easily with conventional airfoil sections. F. E. Eastep and J. J. Olsen determined. The utility of the solutions is that relationships between (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio). performance and system characteristics are developed. The solutions In: Atmospheric Flight Mechanics Conference for Future Space do not depend upon the details of the variation in the parameters Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical along the path but only on the conditions at the ends of the path or Papers. New York, American Institute of Aero- average values. (Author) nautics and Astronautics, Inc., 1979, p. 84-92. 14 refs. (AIAA 79-1632) A79-45306 # Numerical computation of optimal evasive Flutter analysts have encountered considerable analytical diffi- maneuvers for a realistically modeled airplane pursued by a missile culties in the prediction of the flutter stability of aircraft operating with proportional guidance. C. Hargraves, F. Johnson, S. Paris, and I. in the transonic Mach number regime. Because of the shocks and Rettie (Boeing Aerospace Co., Seattle, Wash.). In: Atmospheric nonlinearities of transonic flow the aerodynamic unsteady forces Flight Mechanics Conference for Future Space Systems, Boulder, have been difficult to determine and have prohibited accurate Cob., August 6-8, 1979, Collection of Technical Papers. determination of the flutter speed. The finite-difference relaxation New York, American Institute of Aeronautics and method is used to determine the oscillatory transonic aerodynamic Astronautics. Inc., 1979, p. 21-31. 12 refs. (AIAA 79-1624) forces on a uniformly stiff cantilever rectangular wing in a flow field A second order, direct trajectory optimization method in which with mixed subtonic and supersonic regions together with shock the state time history is described by Chebyshev polynomials and the waves. The flutter speed is determined at two transonic Mach dynamical equations are satisfied by penalty functions is described. numbers and is compared to the flutter speed obtained using a linear The convergence and fidelity of the method are demonstrated with aerodynamic theory. (Author) solutions to the following problems: brachistochrone, Goddard rocket problem with a singular arc, supersonic interceptor minimum A79-45314 # Application of two synthesis methods for time climb, subsonic transport minimum time climb, supersonic active flutter suppression on an aeroelastic wind tunnel model. I. glider maximum range, subsonic transport minimum fuel for a fixed Abel, J. R. Newsom, and H. J. Dunn (NASA, Langley Research range mission including climb, cruise and descent. The method is Center, Hampton, Va.). In: Atmospheric Flight Mechanics Confer- then applied to the computation of optimal evasive maneuvers for an ence for Future Space Systems, Boulder, Cob., August 6-8, 1979, airplane pursued by a missile with proportional guidance. The results Collection of Technical Papers. New York,
566 A79-45326
American Institute of Aeronautics and Astronautics, Inc., 1979. p. University, Dayton, Ohio) and D. A. Keskar (SDC Integrated 93-103. 14 refs. (AIAA 79-1633) Services, Inc., Hampton, Va.). In: Atmospheric Flight Mechanics Two flutter suppression control laws have been synthesized, Conference for Future S pace Systems, Boulder, Cob., August 6-8, implemented, and demonstrated on an aeroelastic wind-tunnel model 1979, Collection of Technical Papers. New York, of a transport-type wing. One control law was synthesized using an American Institute of Aeronautics and Astronautics, Inc., 1979, p. aerodynamic energy method and the other from using results of 135-142,9 refs. Grant No. NsG-1417. (AIAA 79-1639) optimal control theory. At M = 0.95, the model was tested to a This paper investigates the relative importance of including dynamic pressure 44 percent above the system-off flutter dynamic unsteady effects in the lift and downwash in the longitudinal pressure. Both synthesis methods yielded control laws effective in dynamics and parameter extraction algorithm. A simple vortex suppressing flutter. The experimental results also indicate that system has been used to model unsteady aerodynamic effects into wind-tunnel turbulence is an important factor in the experimental the longitudinal equations of motion of an aircraft. Computer- demonstration of system performance. (Author) generated data and flight data were used to demonstrate that inclusion of unsteady aerodynamics in the parameter-extraction A79-45316 # Parallel procedures for aircraft parameter algorithm produced aerodynamic parameters that were different identification and state estimation. R. Travassos and H. Kaufman from those extracted when unsteady aerodynamics were left out of (Rensselaer Polytechnic Institute, Tray, N.Y.). In: Atmospheric the algorithm. The differences between derivatives associated with Flight Mechanics Conference for Future Space Systems, Boulder, the two extraction algorithms (with and without unsteady aerody- Cola., August 6-8, 1979, Collection of Technical Papers. namics) were related to acceleration derivatives which usually cannot New York, American Institute of Aeronautics and be extracted individually. (Author) Astronautics, Inc., 1979, p. 111-119. 14 refs. Grant No. AF- AFOSR-77-3418. (AIAA 79-1636) A79-45320 # Impact of digital computer technology on Parallel algorithms for simultaneously estimating the state and flight systems. T. B. Smith (Charles Stark Draper Laboratory, Inc., identifying the parameters of a noisy nonlinear dynamic system Cambridge, Mass.). In: Atmospheric Flight Mechanics Conference for without using linearization are presented. The state and parameters (SAP) estimating procedures, including parallel shooting, which are Future Space Systems, Boulder, Cob., August 6-8, 1979, Collection applicable to a wide class of nonlinear estimation problems are of Technical Papers. New York, American discussed. Parallel methods for minimization and a parallel method Institute of Aeronautics and Astronautics, Inc., 1979, p. 143-146. 6 for integrating ordinary differential equations are presented, along refs. (AIAA 79-1641) with a parallel algorithm execution time estimation. The perfor- The impact of new applications of digital computer technology, mance of these methods is demonstrated by simultaneously estimat- particularly microcomputer technology, on flight systems are dis- ing the state and identifying the aerodynamic parameters which cussed. While reducing size and cost and increasing accuracy and define the equations of motion for a T-33 aircraft. Results indicate reliability, this new technology will require matching technology that convergence to the true values of the state and parameters can advances in structure, aerodynamics, and control. The changes in the occur even if poor estimates of these values are made initially. V. T. design of future aircraft will be more evolutionary than revolution- ary. Different advantages of digital computer technology, such as quieter and more fuel efficient engines, reduction of the risk of pilot A79-45317 # Aerodynamic data development for the turbo- error in unusual contingency situations, and reduction of the wiring prop T-44A Operational Flight Trainer. R. A. Curnutt (Beech weight and complexity in an aircraft are presented. V.T. Aircraft Cor p., Wichita, Kan.). In: Atmospheric Flight Mechanics Conference for Future S pace Systems, Boulder, Cob., August 6-8, A79-45325 II Water tunnel visualization of the vortex flows 1979, Collection of Technical Papers. New York, of the F-15, D. J. Lorincz (Northrop Corp., Hawthorne, Calif.) and American Institute of Aeronautics and Astronautics, Inc., 1979, p. E. L. Friend (NASA, Flight Research Center, Stability and Control 120-128.6 refs. (AIAA 79-1637) Branch, Edwards, Calif.). In: Atmospheric Flight Mechanics Confer- A comprehensive program has been conducted to develop ence for Future Space Systems, Boulder, Cob., August 6-8, 1979, aerodynamic data for the Navy/Beech T-44A Operational Flight Collection of Technical Papers. New York, Trainer (OFT) - a full-mission flight training simulator. This program, American Institute of Aeronautics and Astronautics, Inc., 1979, p. which considerably expanded the aerodynamic data base in order to 194-208. 14 refs. Contract No. NAS4-2526. (AIAA 79-1649) satisfy OFT full-flight-envelope fidelity requirements, included Flow visualization studies were conducted in a diagnostic water special flight and ground tests, inertia measurements, wind tunnel tunnel to provide details of the wing, glove, and forebody vortex tests, a parameter identification program and an extensive data- flow fields of the F-15 aircraft over a range of angles of attack and matching effort. The paper describes the various facets of the sideslip. Both the formation and breakdown of the vortex flow as a program, discusses the sequence followed in data matching, and function of angle of attack and sideslip are detailed for the basic offers some comparisons between estimated, wind tunnel, parameter aircraft configuration. Additional tests showed that the wing upper identification and 'final' data used in the OFT. (Author) surface vortex flows were Sensitive to variations in an inlet mass flow ratio and an inlet cowl deflection angle. Two lengthened forebodies, A79.45318 • # A model for unsteady effects in lateral dy- one with a modified cross-sectional shape, were tested in addition to namics for use in parameter estimation. W. R. Wells (Wright State the basic forebody. Asymmetric forebody vortices were observed at University, Dayton, Ohio), S. S. Banda, and D. L. Quarn (Dayton, zero sideslip and high angles of attack on each forebody. A large nose University, Dayton, Ohio). In: Atmospheric Flight Mechanics Con- boom was added to each of the three forebodies, and it was observed ference for Future Space Systems, Boulder, Cob., August 6-8, 1979, that the turbulent wake shed from the boom disrupted the forebody Collection of Technical Papers. New York, vortices. V.T. American Institute of Aeronautics and Astronautics, Inc., 1979, p. 129-134. 10 refs. Grant No. NsG-1417. (AIAA 79-1638) A79-45326 # Goniometric aerodynamics: A different per- A mathematical model for the unsteady aerodynamic effects for spective: Description - Applications. R. Lecat and J. Rietschbin use in lateral aircraft dynamics has been developed. The approach is (Grumman Aerospace Corp., Bethpage, N.Y.). In: Atmospheric to derive approximations to the force and moment coefficients based Flight Mechanics Conference for Future S pace Systems, Boulder, on Weissinger's arrangement for the trailing vortex pattern for a Cob., August 6-8, 1979, Collection of Technical Papers. sideslipped wing. The main thrust of the modeling is for application New York, American Institute of Aeronautics and to estimation of the lateral stability and control derivatives. (Author) Astronautics, Inc., 1979, p. 209-223. 6 refs. (AIAA 79-1650) Good correlations have been obtained on A/C and missile A79-45319 • # The relationship of unsteadiness in downwash configurations and their components with Pobhamus potential lift to the quality of parameter estimates. W. R. Wells (Wright State constant and vortex lift constant formulations and approximations
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for Suction orientation, edge bluntness, etc. All geometries are A79-45333 * # Computation of subsonic and transonic flow reduced to two angles: semispan diagonal sweep angle and the about lifting rotor blades. R. Arieli and M. E. Tauber (NASA, Ames orientation of the total suction. A modification of the Polhamus Research Center, Moffett Field, Calif.). In: Atmospheric Flight potential lift constant formula gives good correlations across the Mechanics Conference for Future Space Systems, Boulder, Cob., Mach number range, using aspect ratio transformations. When M is August 6-8, 1979, Collection of Technical Papers. greater than 1, the apparent aspect ratio increases as the Mach cone New York, American Institute of Aeronautics and cuts the corners of the rectangular reference area, until it becomes a Astronautics, Inc., 1979, p.314-323.9 refs. (AIAA 79-1667) triangle when 1/M equals the cosine of the semispan diagonal sweep An inviscid, nonconservative, three-dimensional potential flow angle. B.J. code has been developed for computing the quasi-steady flow about an isolated lifting rotor blade. Calculations from the code were compared with chordwise pressure measurements obtained in a wind A79-45327 # Aerodynamic development of a small horizon- tunnel on a nonlifting rotor at transonic tip speeds at advance ratios tal tail for an active control relaxed stability transport application. D. from 0.40 to 0.55. The overall agreement between theoretical M. Urie and J. S. Reaser (Lock heed-Ca lifornia Co., Burbank, Calif.). calculations and experiment was good. To illustrate the early In: Atmospheric Flight Mechanics Conference for Future Space Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical capability of the program, the flow about a hypothetical lifting rotor Papers. New York, American Institute of Aero- blade having twist, airfoil thickness taper, and a 20 deg sweptback tip was analyzed at azimuthal positions of 60, 90, and 120 deg for an nautics and Astronautics, Inc., 1979, p. 224.231. 6 refs. (AIAA 79-1653) advance ratio of 0.342. Atypical run on a CDC 7600 computer Released static stability (RSS) with active control stability required about 5 min for one rotor position at transonic tip speeds. augmentation contributes to aircraft efficiency by permitting more (Author) aft center of gravity with reduced trim drag and/or by allowing a smaller horizontal tail with less parasite drag and weight. A small tail A79-45339 • # Gust alleviation using direct turbulence mea- has been designed for derivative versions of the Lockheed L .101 1 surements. E. G. Rynaski, D. Andrisani, II, and B. J. Eulrich (Calspan using state-of-the-art lifting surface definition methods. Low-speed Advanced Technology Center, Buffalo, N.Y.). In: Atmospheric and transonic wind tunnel data verifying theoretical predictions have Flight Mechanics Conference for Future Space Systems, Boulder, been obtained. A minimum size tail for this application was obtained Cob., August 6-8, 1979, Collection of Technical Papers. and design details required for maximum performance were identi- New York, American Institute of Aeronautics and fied. A configuration suitable for production has been defined and Astronautics, Inc., 1979, p. 379-386. 6 refs. NASA-supported will be developed through prototype flight testing on an L-1 011. research; Contract No. F33615-73-C-3051. (AIAA 79-1674) (Author) The research reported upon in this paper describes an effective method of gust alleviation using direct measurements of atmospheric turbulence to drive the aircraft control surfaces in a way that A79-45328 # An analysis of operational procedures and attempts to directly counter or cancel those forces and moments design modifications for aircraft fuel conservation. R. Aggarwal, A. produced on the aircraft by gusts. The method yields a feedforward Dushman (Dynamics Research Corp., Wilmington, Mass.), and A. J. or open loop control law, simple to mechanize and relatively Cause (Drexel University, Philadelphia, Pa.), In: Atmospheric Flight insensitive to changes in flight condition. When applied directly, the Mechanics Conference for Future Space Systems, Boulder, Cob., resulting control law effectively gust-alleviates in the low frequency August 6-8, 1979, Collection of Technical Papers. phugoid and short period range but has a tendency to amplify New York, American Institute of Aeronautics and structural mode vehicle motions due to the phase lag of the Astronautics, Inc., 1979, p. 232-242. 11 refs. (AIAA 79-1656) actuators. A method of design based upon the use of a diagonal or This paper is taken from a two year study conducted to Jordan form of the equations of motion enables the designer to avoid determine the effectiveness of fuel conservation measures as applied this problem of structural mode excitation. (Author) to Air Force bomber/transport type aircraft. The impact of various potential design and operational procedure improvements are quanti- A79-45340 • # Gust alleviation - Criteria and control laws. E. fied. A major contribution of this study is the approach taken to G. Rynaski (Calspan Advanced Technology Center, Buffalo, N.Y.). generate the effect of design changes on fuel consumption and direct In: Atmospheric Flight Mechanics Conference for Future Space operating Cost (DOC). Sensitivity plots of fuel and DOC savings as a Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical function of the design parameters are generated for each aircraft Papers. New York, American Institute of Aero- type. These plots are based on actual mission trajectory data as nautics and Astronautics, Inc., 1979, p. 387-392. 6 refs. NASA- opposed to 'typical' mission trajectory profiles. (Author) supported research; Contract No. F33615-73-C-3051. (AIAA 79-1676) The relationships between criteria specified for aircraft gust A79-45330 • # Effects of spanwise blowing on two fighter alleviation and the form of the control laws that result from the airplane configurations. E. L. Anglin and D. Satran (NASA, Langley criteria are considered. Open-loop gust alleviation based on the Research Center, Hampton, Va.). In: Atmospheric Flight Mechanics linearized, small perturbation equations of aircraft motion is dis- Conference for Future Space Systems, Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. New York, cussed, and an approximate solution of the open-loop control law is American Institute of Aeronautics and Astronautics, Inc., 1979, p. presented for the case in which the number of degrees of freedom of 286-294. 9 refs. (AIAA 79-1663) the aircraft exceeds the rank of the control effectiveness matrix. Excessive actuator lag is compensated for by taking into account The NASA Langley Research Center has recently conducted an actuator dynamics in the equations of motion, resulting in the investigation to determine the effects of spanwise blowing on two specification of a general load network. Criteria for gust alleviation configurations representative of current fighter airplanes. This when output motions are gust alleviated and the closed-loop control research examined not only the longitudinal, or performance, effects law derived from them are examined and linear optimal control law but was especially oriented toward determining the lateral-directional is derived. Comparisons of the control laws reveal that the effects, particularly in the stall/departure angle of attack range. The effectiveness of an open-loop control law is greatest at low aircraft wind tunnel tests included measurement of static and forced- frequencies but deteriorates as the natural frequency of the actuators oscillation aerodynamic data, visualization of the airflow changes is approached, while closed-loop methods are found to be more over the wing created by the spanwise blowing and free flight model effective at higher frequencies. tests. Effects of blowing rate, chordwise location of the blowing A.L.W. ports, asymmetric blowing, and the effects of blowing on the A79-45341 # Decoupled longitudinal controls for shear effectiveness of conventional aerodynamic controls were investi- penetration in the terminal area environment. G. K. Miller, Jr. gated. (Author) (NASA, Langley Research Center, Hampton, Va.). In: Atmospheric
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Flight Mechanics Conference for Future Space Systems, Boulder, A79-45345 • # A review of helicopter control-display require- - Cob., August 6-8, 1979. Collection of Technical Papers. ments for decelarating instrument approach. J. V. Lebacqz (NASA, New York, American Institute of Aeronautics and Ames Research Center, Moffett Field, Calif.). In: Atmospheric Flight Astronautics. Inc., 1979, p. 393-400. 8refs. (Al AA 79-1678) Mechanics Conference for Future Space Systems, Boulder, Cob., The use of decoupled longitudinal controls is simulated for the August 6-8, 1979, Collection of Technical Papers. approach and landing of a twin engine jet transport in the presence New York, American Institute of Aeronautics and of wind shear. Decoupled or independent control of pitch angle, Astronautics, Inc., 1979, p.426.439. 57 refs. )AIAA 79-1683) flight-path angle and forward velocity using constant prefilter and This paper reviews research and operational test programs that feedback gains was compared to conventional control of a B-737 have dealt with control and display requirements for helicopters aircraft simulator. It is found that the mean flight-path angle, the performing decelerating approaches in the terminal area under mean glideslope error and the mean deviation in indicated airspeed instrument flight conditions. A survey of literature concentrating on generally improved when decoupled controls were used in the flight programs resulted in approximately 50 applicable references approach. An improvement in touchdown parameters was also which were summarized and classified according to the type of observed, especially in strong shear, when 44% of conventionally- stability/control augmentation that was emphasized. On this basis, controlled flights impacted short of the runway. Simulator pilots display information requirements for each control system type were reported improved approach performance and a reduced workload hypothesized consistent with documented results of these programs. when decoupled controls were used. A.L.W. Nine control-display combinations that appear to warrant further ground simulation and flight testing are defined and discussed. (Author) A79-45342 # A simulator investigation of roll response requirements for aircraft with rate-command/attitude-hold flight A79-45346 # Aerodynamic coefficient estimation by means control systems in the landing approach and touchdown. M. F. C. of an extended Kalman filter. J. R. Kelsey (Sandia Laboratories, van Goo] and H. A. Mooij )Nationaal Lucht- en Ruimvewaartlabora- Albuquerque, N. Mex.) and D. P. Petersen (New Mexico, University, torium, Amsterdam, Netherlands). In: Atmospheric Flight Mechanics Albuquerque, N. Mex.). In: Atmospheric Flight Mechanics Confer- Conference for Future Space Systems, Boulder, Cob., August 6.8, ence for Future Space Systems, Boulder, Cob., August 6-8, 1979, 1979, Collection of Technical Papers. New York, Collection of Technical Papers. New York, American Institute of Aeronautics and Astronautics, Inc., 1979, p. American Institute of Aeronautics and Astronautics, Inc., 1979, p. 401-410. 17 refs. Research supported by the Rijksluchtvaartdienst. 440-444. Research supported by the U.S. Department of Energy. )AIAA 79-1679) (AIAA 79-1686) An investigation concerning roll response requirements for An extended, augmented Kalman filter is used to study several aircraft fitted with high-authority augmented flight control systems dynamic models of vehicle motion aimed as estimating the aero- has been carried out on a moving base flight simulator. Roll response dynamic moment coefficients. These models consider various state characteristics have been varied in an experiment in which pilots had representations as well as various measurement sets. Linear and cubic to carry out instrument approaches in a moderate windshear, symmetric moments are considered as well as linear asymmetric followed by a visual segment in which a lateral offset occurred, moments. Computer generated data representative of a reentry terminating in a landing with up to 15 knots crosswind. Analyses of vehicle flight are used as the simulated measurement information. pilot commentary and performance measures indicate that the pilot Coefficient estimates and error estimates are given for each of the assessment of the flying qualities of the evaluated configurations models studied. The computer time required for estimate conver- correlates well with roll response criteria mentioned in the literature gence is also shown, indicating that near-real-time estimation is for unaugmented aircraft in less demanding tasks. (Author) possible. (Author) A79-45343 # Effect of reduced visibility on VIOL handling quality and display requirements. R. H. Hoh and I. L. Ashkenas A79-45355 # A multi microprocessor flight control system (System Technology, Inc., Hawthorne, Calif.). In: Atmospheric design principles. R. E. Pope, J. A. White (Honeywell Systems and Flight Mechanics Conference for Future Space Systems, Boulder, ResearchCenter, Minneapolis, Minn.), I. J. Molnar, J. E. May, and S. Cob., August 6-8, 1979, Collection of Technical Papers. L. Maher (USAF, Flight Dynamics Laboratory, Wright-Patterson New York, American Institute of Aeronautics and AFB, Ohio). In: Guidance and Control Conference, Boulder, Cob., Astronautics, Inc., 1979, p. 411-418. 13 refs. (AIAA 79-1680) August 6-8, 1979, Collection of Technical Papers. Available data have been used to quantify the intuitive idea that New York, American Institute of Aeronautics and the minimum acceptable handling qualities for low speed and hover Astronautics, Inc., 1979, p.34-39. (AIAA 79-1700) are dependent on outside visibility level, augmentation, and cockpit A multi-microprocessor flight control system (M2FCS) system displays. A tentative handling quality criteria format is developed in based on tailoring the architecture to the flight control system terms of a visibility scale which quantifies the environmental application and exploiting the trend toward cheap microelectronic conditions for the intended mission in a more fine-grained manner hardware is examined. Flight control system design is comprised of than simply specifying IMC or VMC. (Author) two tasks: the first task is the design of the control laws which must satisfy requirements of stability/control augmentation, direct force control, and automatic modes. The second design task is to transform these control laws into an operational system consisting of A79-45344 # Folded shear plane control apparatus for flight control sensors, computers, and actuators. The M2FCS system aircraft steering and stabilization. A. Jones, Jr. In: Atmospheric design concentrates on the computer part of this design factors of Flight Mechanics Conference for Future Space Systems, Boulder, performance, reliability, maintainability, testability, extensibility, Cob., August 6-8, 1979, Collection of Technical Papers. and adaptability, and the design constraints of cost, character of New York, American Institute of Aeronautics and computation, operational environment, power, and packaging. A.T. Astronautics, Inc., 1979, p.419-425. )AIAA 79-1682) Banking Rudders use folded shear planes as control surfaces to A79-45356 B Dual digital flight control redundancy manage- replace the conventional airplane empennage. This new thematic ment system development program. J. D. Blair and R. D. McCorkle concept does not employ a rudder post or hinged surface, but rather (Boeing Aerospace Co., Seattle, Wash.). In: Guidance and Control a second order surface deflection generated by the movement of a Conference, Boulder, Cob., August 6-8, 1979, Collection of Tech- surface mounted bearing. As more testing is expected to show, the nical Papers. New York, American Institute of Banking Rudder has potential for the following benefits: (1) reduced Aeronautics and Astronautics, Inc., 1979, p. 40-46. (AIAA 79.1701) parasitic drag, (2) low drag configuration, (3) control force increase, A dual digital flight control system incorporating interunit (4) weight reduction, and (5) damage tolerance. (Author) selection and redundancy management of device pairs was developed
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for laboratory demonstration. Four minicomputers connected via A79.45360 # Azimuth observability enhancement during dual MIL-STD-1553A data buses perform flight control and input/ INS in-flight alignment. B. Porat and I. Y. Bar-Itzhack (Technion - output functions. The system was interfaced with a piloted flight Israel Institute of Technology, Haifa, Israel). In: Guidance and simulator to provide closed-loop operation. Software was developed Control Conference, Boulder, Cob., August 6-8, 1979, Collection of for redundancy management of system components and for flight Technical Papers. New York, American Institute control modes typical of modern transport aircraft. The system was of Aeronautics and Astronautics, Inc., 1979, p. 80-89. 11 refs. demonstrated by flying simulated mission sequences during which (AIAA 79-1706) multiple faults were inserted, showing the capability to maintain The paper investigates whether an axial acceleration maneuver is system integrity in the presence of multiple failures. (Author) superior to a lateral one during the in-flight alignment of an inertial navigation system and whether there exists a simple test or A79.45357 • # Flight test experience with an adaptive control expression which clearly indicates this fact of superiority. It was system using a maximum likelihood parameter estimation technique. found that, in general, an axial maneuver is not superior to a lateral G. Hartmann, G. Stein (Honeywell, Inc., Minneapolis, Minn.), and B. one. There are, however, three classes of alignment problems in Powers (NASA, Flight Research Center, Edwards AFB, Calif.). In: which axial maneuver is superior. These cases can be modeled by Guidance and Control Conference, Boulder, Cob., August 6-8, 1979, simple models which yield analytic expressions clearly indicating the Collection of Technical Papers. New York, superiority of the axial maneuver during the in-flight alignment of an American Institute of Aeronautics and Astronautics, Inc., 1979, p. INS. 47.53 5 refs. (AIAA 79-1702) B.J. The flight test performance of an adaptive control system for the F.8 DFBW aircraft is summarized. The adaptive system is based A79-45361 # Filtering and threat logic design and evaluation on explicit identification of surface effectiveness parameters which for the beacon collision avoidance system. J. A. Sorensen and B. are used for gain scheduling in a command augmentation system. Hulland. In: Guidance and Control Conference, Boulder, Cob., Performance of this control law under various design parameter August 6-8, 1979, Collection of Technical Papers. variations is presented. These include variations in test signal level, New York, American Institute of Aeronautics sample rate, and identification channel structure. Flight performance and Astronautics, Inc., 1979, p.90-100. 9 refs. U.S. Department of closely matches analysis and simulation predictions from previous Transportation Contract No. FAA77NA-4037. (AIAA 79-1707) references. (Author) The beacon collision avoidance system (BCAS) has been developed as an independent airborne system which provides position measurements of surrounding air traffic. The processed A79-45358 # Flight test of a VTOL digital autoland system measurements can be used by the pilot for conflict alert and along complex trajectories. D. R. Downing, W. H. Bryant, and A. J. avoidance and for general aiding of the air traffic control process. Ostroff (NASA, Langley Research Center, Flight Electronics Div., This paper describes: (1) square-root Kalman filtering developed to Hampton, Va.). In: Guidance and Control Conference, Boulder, process the BCAS measurements, (2) unique airborne threat logic Cob., August 6-8, 1979, Collection of Technical Papers. devised to evaluate whether another aircraft poses a threat and how New York, American Institute of Aeronautics and the protected aircraft should maneuver, and (3) the evaluation Astronautics, Inc., 1979, p. 54-63. 8 refs. (AIAA 79-1703) procedure for assessing BCAS performance by statistical analysis of The objective of this research is the development and flight test simulation results. (Author) of a digital multi-rate VTOL autoland system. This autoland system provided the NASA/Army Fly-by-Wire CH-47 helicopter with an A79-45362 • # Evaluation of the navigation performance of automatic 4-D trajectory following and landing capability. Flight shipboard-VTOL-landing guidance systems. L. A. McGee, C. H. tests were conducted along complex trajectories with descending, Paulk, Jr., S. A. Steck (NASA, Ames Research Center, Moffett Field, turning, and decelerating segments. The flight software consists of a Calif.), S. F. Schmidt, and A. W. Merz (Analytical Mechanics trajectory generator and guidance algorithm operating at two Associates, Inc., Mountain View, Calif.). In: Guidance and Control iterations per second and a set of sensor filters and an advanced Conference, Boulder, Cob., August 6-8, 1979, Collection of Tech- controller operating at 10 iterations per second. This low iteration nical Papers. New York, American Institute of rate digital controller has a proportional-integral structure that Aeronautics and Astronautics, Inc., 1979, p. 101-113. (AIAA provides an autotrim function. The control gains, scheduled as a 79-1708) function of flight condition, are updated every two seconds. All The objective of this study was to explore the performance of a flight software, except input/output routines, are coded in FOR- VTOL aircraft landing approach navigation system that receives data TRAN using floating point arithmetic and are exercised in a ROLM (1) from either a microwave scanning beam (MSB) or a radar- 1664 flight computer. The flight software, the ground and flight transponder (R.T) landing guidance system, and (2) information hardware, the autoland system's position tracking performance, and data-linked from an aviation facility ship. State-of-the-art low-cost- the controller's velocity and heading tracking performance are aided inertial techniques and variable gain filters were used in the presented. (Author) assumed navigation system. Compensation for ship motion was accomplished by a landing pad deviation vector concept that is a measure of the landing pad's deviation from its calm sea location. A79.45359 # The DC-9-80 digital flight guidance system's The results show that the landing guidance concepts were successful monitoring techniques. S. Osder (Sperry Flight Systems, Phoenix, in meeting all of the current Navy navigation error specifications, Ant.). In: Guidance and Control Conference, Boulder, Cob., August provided that vector magnitude of the allowable error, rather than 6-8, 1979, Collection of Technical Papers. New the error in each axis, is a permissible interpretation of acceptable York, American Institute of Aeronautics and Astronautics, Inc., performance. The success of these concepts, however, is strongly 1979, p.64-79.7 refs. (AIAA 79-1704) dependent on the distance measuring equipment bias. In addition, The DC-9.80 aircraft is equipped with an integrated digital flight the 'best possible' closed-loop tracking performance achievable with guidance system that provides autopilot, flight director, thrust the assumed point-mass VTOL aircraft guidance concept is demon- management, speed control, autothrottle, and stability augmentation strated. (Author) within a single computer complex. The present paper describes how the multiplicity of DC-9-80 software and hardware monitors are A79-45363 # Fuel-conservative guidance system for implemented and how their effectiveness can be analyzed and powered-lift aircraft. H. Erzberger and J. D. McLean (NASA, Ames verified. The system monitors are designed in such a way that fault Research Center, Moffett Field, Calif.). In: Guidance and Control detection and appropriate shutdown of the failed elements can meet Conference, Boulder, Cob., August 6-8, 1979, Collection of Tech- the 10 to the -9th hazard criterion used to certify prior autoland nical Papers. New York, American Institute of systems. B.J. Aeronautics and Astronautics, Inc., 1979, p. 114-128. 9 refs.
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A concept for automatic terminal-area guidance, comprising two cal Papers. New York, American Institute of modes of operation, has been developed and evaluated in flight tests. Aeronautics and Astronautics, Inc., 1979, p. 306 .313. 13 refs. In the first or predictive mode, fuel-efficient approach trajectories (AIAA 79-1736) are synthesized in fast time. In the second or tracking mode, the Air-to-air missile guidance laws were derived using optimal synthesized trajectories are reconstructed and tracked automatically. control and differential game theory with final miss distance as the An energy rate performance model derived from the lift, drag, and optimization criterion. Two simulation scenarios were used to propulsion-system characteristics of the aircraft is used in the evaluate the guidance laws: one with missile launch near the inner synthesis algorithm. The method optimizes the trajectory for the launch boundary and the other near the outer launch boundary. The initial aircraft position and wind and temperature profiles encoun- differential game guidance laws are less sensitive to errors in tered during each landing approach. The paper describes the design estimates of Current target acceleration than the optimal control theory and discusses the results of simulations and flight tests using laws. The laws based on a perfect missile response performed better the Augmentor Wing Jet STOL Research Aircraft. (Author) for the outer launch boundary scenario, whereas for the inner launch boundary scenario the laws based on a first order missile response A79-45373 An introduction to co-kill probability estima- achieved smaller miss distances. B.J. tion in the M on N encounter. D. S. Hague (Aerophysics Research Corp., Bellevue, Wash.). In: Guidance and Control Conference, A79-45386 # Direct force mode flight control for a vectored Boulder, Colo., August 6-8, 1979, Collection of Technical Papers. lift fighter. A. R. Mitchell (McDonnell Aircraft Co., St. Louis, Mo.). New York, American Institute of Aeronautics In: Guidance and Control Conference, Boulder, Cob., August 6-8, and Astronautics, Inc., 1979, p. 243. 249. 9 refs. (AIAA 79-1729) 1979, Collection of Technical Papers. New York, The results obtained from either flight tests or simulated M on N American Institute of Aeronautics and Astronautics, Inc., 1979, p. (2 on 2, 2 on 4 through 4 on 4) aerial combat encounters are 366-378. (AIAA 79-1744) discussed. The significance of numerical superiority is illustrated The lateral-directional flight control system synthesis for the along with the necessity to consider kill mechanisms in the purely aerodynamic direct force modes and its potential flying formulation of M on N tactics. Two models are evaluated. In the first qualities with the vectored lift fighter (VLF) are presented. The model very large forces encounter and exchange fire. Results are obtained by the application of stochastic methods alone. In the addition of direct force modes can give air superiority in close-in second model a smaller number of vehicles are engaged. Results are combat through improved maneuverability and integrated fire-flight obtained by integrating aircraft trajectories forward in time along control capability over a conventional fighter. These important force with a set of co-kill probability equations which estimate the modes on the VLF can be designed and mechanized using angle of probability of each aircraft surviving the encounter and the resulting attack and sideslip feedback in an easily applied system synthesis method. The general methodology used to synthesize flight control force survival p robabilities. V.T. of six degrees of freedom is illustrated, and it is shown that good A79-45376 # Guidance law design for tactical weapons with flying qualities are achievable with direct force modes over a wide strapdown seekers. T. R. Callen (USAF, Armament Laboratory, range of flight conditions. Potential flying qualities with the VLF are Eglin AFB, Fla.). In: Guidance and Control Conference, Boulder, exemplified using results from nonlinear six degree of freedom digital A.T. Cob., August 6-8, 1979, Collection of Technical Papers. simulations. New York, American Institute of Aeronautics and Astronautics, Inc., 1979, p. 281 . 293. )AIAA 79-1732) A79-45387 # Minimum expected cost control of linear A direct measurement of inertial line of sight is not possible .systems with uncertain parameters . Application to remotely piloted with a strapdown seeker, so alternate guidance and filtering vehicle flight control systems. A. Vinkler (California Institute of techniques must be developed. The objective of the present study is Technology, Pasadena, Calif.), U.-L. Ly (Boeing Co., Seattle, Wash.), to determine the best combination of guidance law structure, signal R. H. Cannon, Jr. (Stanford University, Stanford, Calif.), and L. J. processing technology, and achievable seeker and sensor accuracy Wood. In: Guidance and Control Conference, Boulder, Cob., August requirements for the effective use of strapdown seekers with 6-8, 1979, Collection of Technical Papers. New air-to-surface tactical guided weapons. Various filtering techniques York, American Institute of Aeronautics and Astronautics, Inc., and guidance law designs are discussed including direct PH, pursuit 1979, p. 379. 387. 22 refs. Research supported by Teledyne Ryan guidance, dynamic lead guidance, a combination of PN and pursuit, Aeronautical. (AIAA 79-1745) and a new technique, adaptive PH. This new scheme uses a dither An efficient technique for designing constant gain feedback signal to measure and correct for seeker gain errors and overcomes controllers for linear systems having uncertain or variable parameters stability problems associated with most of the other approaches. B.J. is presented and demonstrated for a realistic RPV design. This controller design technique - named Minimum Expected Cost A79-45377 # Optimal missile guidance for low miss and Control - produces closed-loop system behavior which is acceptable perpendicular impact. D. V. Stallard (Raytheon Co., Missile Systems for all values of the parameters within specified limits and is Div., Bedford, Mass.). In: Guidance and Control Conference, optimum in some overall sense. The technique is used to design a Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. constant gain lateral auto-pilot for an RPV that will fly at a wide New York, American Institute of Aeronautics range of altitudes and airspeeds. Both full and partial state feedback and Astronautics, Inc., 1979, p.294-305.6 refs. )AIAA 79-1734) situations are considered. Extension of the method to the design of A practical terminal guidance law was developed to give low dynamic feedback compensators is shown to be straightforward. miss distance and perpendicular impact, using optimal control theory (Author) with ancillary simple algorithms to find time-to-go, etc. The acceleration commands depend on the projected, zero-control, terminal heading-angle error, and miss distance. When these errors are A79-45393 # Deformable mirror surface control- Hardware, low, as in the latter part of the intercept, the linearizing assumptions algorithms. D. J. Chiarappa and C. R. Claysmith (General Dynamics necessary for the closed-form solution hold and the missile trajectory Corp., Convair Div., San Diego, Calif.). In: Guidance and Control is optimal. All 18 simulation cases had performance well within the Conference, Boulder, Cob., August 6-8, 1979, Collection of Techni- requirements and the computational load of the guidance law was cal Papers. New York, American Institute of relatively low. B.J. Aeronautics and Astronautics, Inc., 1979, p. 435-441. 5 refs. (AIAA 79-1757) A79-45378 // A comparison of air-to-air missile guidance A corrector mirror assembly within an optical train provides laws based on optimal control and differential game theory. G. M. corrections to maintain focus on a distant target despite defocus Anderson (Orincon Corp., La Jolla, Calif.). In: Guidance and Control perturbations due to air medium turbulence. Focus correction is by Conference, Boulder, Cob., August 6-8, 1979, Collection of Techni- mirror deformation provided by piezoelectric actuators and a
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companion unique solid-state drive amplifier. Actuation bandpass A79-45403 • # Preliminary study of pilot lateral control of requirements are 1 kHz. The paper describes the overall actuation two light airplanes near the stall. M. T. Moul and L. W. Brown control with emphasis on the actuator and drive amplifier design. (NASA. Langley Research Center, Hampton, Va.). In: Guidance and Hardware examples are shown and discussed. (Author) Control Conference, Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. New York, American Institute of Aeronautics and Astronautics, Inc., 1979, p. 509-521. 11 refs. A79-45400 # F.16 flight control system redundancy con- (AIAA 79-1775) cepts. E. E. Ammons (General Dynamics Corp., Fort Worth, Tex.). For two representative light, single-engine airplanes the single- In: Guidance and Control Conference, Boulder, Cob., August 6-8, axis piloting task of controlling bank angle with combined aileron 1979, Collection of Technical Papers. New York, and rudder, and a two-axis task of controlling bank angle with American Institute of Aeronautics and Astronautics, Inc., 1979. p. aileron and sideslip with rudder have been studied. For these tasks 484-490. (AIAA 79-1771) existing divergence criteria have been applied to determine condi- The analog fly-by-wire flight control system (FCS) of the F-i 6 is tions for closed-loop stability for selected flight conditions near the discussed. In order to provide undergraded performance following stall; in addition closed-loop stability characteristics and airplane any two like-failures in the stability augmentation electronics, response to bank angle command were calculated. Results obtained quad-redundant implementation of the pitch stability augmentation from applying the divergence criterion and from calculations of was selected, i.e., four branches that are physically and electrically isolated. The branches provide the system back up necessary for safe airplane responses to bank angle command indicate that aileron-alone operation by rejecting the output from a branch that disagrees with bank angle control is marginally acceptable at high angle of attack. two others, and then selecting the middle value of the remaining Of the two rudder control techniques considered, rudder used with three. A flight path control, the FCS redundancy implementation, the aileron in controlling bank angle increased stability and produced redundancy management, and the FCS gain scheduling are outlined satisfactory responses; the combined bank angle and sideslip control with consideration given to the active selector and hydraulic actuator task does not warrant further consideration because nf the task difficulty and the small improvement indicated in airplane closed- redundancy. V.T. loop response with this technique. (Author)
A79-45404 # 4-D helical approach of a transport aircraft in A79. 45401 # Development of the Navy H-Dot Automatic an ATC environment. P. 0. Grepper and F. E. Huguenin (Zurich, Carrier Landing System designed to give improved approach control Eidgenossische Technische Hochschule, Zurich, Switzerland). In: in air turbulence. J. M. Urnes, R. K. Hess, R. F. Moomaw Guidance and Control Conference, Boulder, Cob., August 6-8, 1979, (McDonnell Aircraft Co., St. Louis, Mo.), and R. W. Huff (U.S. Navy, Collection of Technical Papers. New York, Naval Air Test Center, Patuxent River, Md.). In: Guidance and American Institute of Aeronautics and Astronautics, Inc., 1979, p. Control Conference, Boulder, Cob., August 6-8, 1979, Collection of 522-528. (AIAA 79-1776) Technical Papers. New York, American Institute The results of a Simulation study are presented in which a of Aeronautics and Astronautics, Inc., 1979, p. 491-501. (AIAA minicomputer was used to compute 4-dimensional (4-d) flight 79-1772) trajectories in an air-traffic control (ATC) environment. The general The Navy Automatic Carrier Landing System (ACLS) provides concepts and the philosophy used in developing the computer fully automatic approach and landing capability for high perfor- controlled system for generating 4-D flight profiles are considered mance carrier-based fighter aircraft. Approach path air turbulence together with application of these concepts for holding, approach, produces significant touchdown error. Using Power Spectral Density landing, take-off, and go-around problems. The realization of a lift definitions of turbulence, a method to determine flight path force and lift coefficient on a minicomputer is given as well as the deviation due to turbulence and effects of changing system control block diagram and the hardware configuration of a lift computer. A laws to reduce dispersions and improve ACLS performance is test c'ce for a helical appr'-'w'.h with a DC-10 is also presented. It is presented. This technique, as applied to an F-4J ACLS fleet noted that a future study is plannea to implement the system on a configuration, results in significant improvement using a vertical rate flight simulator. V.T. (H-Dot) reference in the autopilot control law. The F-4J H-Dot avionics mechanization was implemented and flight test results are discussed. (Author) A79-45409 # Design Criteria for optimal flight control sys tems, K. S. Govindaraj and E. G. Rynaski (Calspan Advanced Technology Center, Buffalo, N.Y.). In: Guidance and Control A79-45402 # An improved lateral stability augmentation Conference, Boulder, Cob., August 6-8, 1979, Collection of Techni- system for air-to-air tracking. R. R. Huber and R. D. Hoidridge cal Papers. New York, American Institute of (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio). Aeronautics and Astronautics, Inc., 1979, p. 558-566. 5 refs. In: Guidance and Control Conference, Boulder, Cob., August 6-8, Contract No. N00014-78-G .0155. (AIAA 79-1782) 1979, Collection of Technical Papers. New York, Results of the application of linear optimal control to the design American Institute of Aeronautics and Astronautics, Inc., 1979, p. of multicontroller feedback system to satisfy aircraft flying qualities 502-508. (AIAA 79-1773) are presented. Two sequential design procedures, one computing the The design of a stability augmentation system for the F-106 Riccati solution from a set of linear equations and the other aircraft is discussed along with piloted and nonpiloted simulations computing the closed-loop eigenvectors, are presented that deter- and flight tests. The system emphasizes improvement in lateral mine, at each step, the pole-zero movements of the closed-loop handling qualities for air-to-air (ATA) tracking. Factors effecting transfer functions as the weighting matrix on the states is varied for a ATA tracking are evaluated and the system design and configuration given control weighting matrix. The weighting matrix constructed at selection is outlined. An estimated Side-slip angle rate feedback is each step is added to get a final weighting matrix to move the poles used to achieve an improved stability and turn coordination and an and zeros to more desirable locations. A control system design increased bandwidth. The design also includes a direct electric signal example, with the X-22A V/STOL aircraft as the model, is presented. from a pilot to a control system to allow for a direct command of (Author) the Side-slip rate. The system eliminates large unintentional side-slip perturbations caused by the pilot's attempts to place a gunsight A79-45410 # Initial results of an inflight simulation of pipper on a target aircraft. These conclusions are based on pilot augmented dynamics in fighter approach and landing, J. Hodgkinson comments, gun camera films, and a strip chart data of aircraft and K. A. Johnston (McDonnell Aircraft Co., St. Louis, Mo.). In: parameters. V.T. Guidance and Control Conference, Boulder, Cob., August 6-8, 1979,
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Collection of Technical Papers. New York, coordination of pilot and automatic control are described. Both American Institute of Aeronautics and Astronautics, Inc., 1979, p. simulator and flight test pilot evaluation results are presented. 567. 572. 10 refs. (AIAA 79.1783) (Author) The USAF/CALSPAN variable stability NT-33 aircraft was used to explore longitudinal and lateral dynamics during landing. The A79-45418 # Digital flight control reliability - Effects of flying qualities of several high order systems and their analytically redundancy level, architecture and redundancy management tech- derived low order equivalents were compared. Pilot ratings were used nique. J. W. Rice and R. D. McCorkle (Boeing Aerospace Co.. to determine how closely the low order equivalent system must Seattle, Wash.). In: Guidance and Control Conference, Boulder, approximate the high order system to be a valid flying qualities Cob., August 6-8, 1979, Collection of Technical Papers. prediction tool. Transport lags in the aircraft response to the pilot's New York, American Institute of Aeronautics and controller were also investigated. (Author) Astronautics, Inc., 1979, p.645-657. (AIAA 79-1893) The reliabilities of several digital flight control systems (DFCSs) A79-45412 # Alleviation of stability and control difficulties are compared, considering effects of redundancy level, control of a V/STOL Type B aircraft. P. W. Berry and J. R. Broussard system architecture, redundancy management philosophy and, where (Analytic Sciences Corp., Reading, Mass.). In: Guidance and Control applicable, fault detection and isolation coverage. Realistic reliability Conference, Boulder, Cob., August 6-8, 1979, Collection of Tech- data are used for the system components. Each system is described nical Papers. New York, American Institute of and its success criteria established. It is shown that for longer Aeronautics and Astronautics, Inc., 1979, p. 584. 593. 23 refs. missions, systems employing interunit selection at the LRU level can Contract No. N00014-77-C-0775. (AIAA 79-1785) be more reliable than systems employing one higher level of High-speed V/STOL aircraft using jet thrust support for VTOL redundancy and using midvalue signal voting as the only means of capability can have significant stability and control difficulties in fault detection. (Author) low-speed and hovering flight. In this paper, multivariable time- A79.45421 # Earth-Referenced Maneuvering Flight Path domain analysis tools are applied to a mathematical model of the Display, J. R. Watler, Jr. and W. B. Logan (Northrop Corp., Aircraft AV-8A aircraft to quantify the stability and control variations. The Group, Hawthorne, Calif.). In: Guidance and Control Conference, effects of velocity and angle-of-attack, as well as acceleration along Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. and normal to the flight path, are examined. A second section of this New York, American Institute of Aeronautics paper describes the construction of digital ly-implementable com- and Astronautics, Inc., 1979, p.682-69l. (AIAA 79-1894) mand and stability augmentation algorithms for the low-speed and The investigation of the Maneuvering Flight Path Display hover regimes. Velocity-, position-, and attitude-command systems (MFPD) field-of-view requirements, the determination of speed index for a V/STOL Type B aircraft are illustrated. (Author) and flight path display formats, and the mechanization of an earth-referenced transition path (for use when the MFPD moves A79-45413 * # A piloted simulator investigation of helicopter outside the display field-of-view) are presented. The basic Earth- precision decelerating approaches to hover to determine single-pilot Referenced MFPD computer program was modified to incorporate IFR /SPIFR/ requirements. A. V. Phatak (Analytical Mechanics the extended functional capability resulting from this work, a Associates, Inc., Mountain View, Calif.), L. L. Peach, Jr., R. A. Hess, modified computer program was validated by 'flying' it in real time V. L. Ross, G. W. Hall, and R. M. Gerdes (NASA, Ames Research from a cockpit simulator, and an improved version of the ER/MFPD Center, Moffett Field, Calif.). In: Guidance and Control Conference, was obtained from the study. It is noted that air-to-air engagements, Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. air-to-surface moving target strikes, and carrier approaches and New York, American Institute of Aeronautics landings require a moving reference version of the flight path. V.T. and Astronautics, Inc., 1979, p. 594-608. 10 refs. (AIAA 79-1886) The results of single-pilot instrument flight rules (SPIFR) experiments conducted on the NASA-Ames V/STOLAND simulator A79-45600 Liquid hydrogen fueled commercial aircraft. are presented. Several factors having a significant impact on G. D. Brewer (Lockheed-California Co., Burbank, Calif.). In: requirements for helicopter SPIFA decelerating, steep approaches to Hydrogen for energy distribution; Proceedings of the Symposium, Chicago, III., July 24-28, 1978. Chicago, Insti- landing are considered: (1) approach weather, conditions, (2) flight path geometry, (3) deceleration guidance law, (4) level of stability tute of Gas Technology, 1979, p. 541-550. and command augmentation, (5) cockpit display sophistication, (6) This statement reviews the probable future fuel problem facing accuracy of navigation aids, and (7) helipad lighting and visual aids. the commercial air transport industry and suggests an innovative Particular emphasis is placed on the relative effects of deceleration course of action. The plan involves creation of an experimental profile, control augmentation, and flight director parameters on pilot airline equipped with four liquid hydrogen-fueled, wide-body aircraft performance, workload, and opinion rating. Problems associated with flying commercial cargo on a regularly scheduled basis between the the development of a pilot acceptance analytical methodology are United States, Western Europe, and the Middle East. Development of outlined. V.T. facilities incorporating advanced technologies for production and liquefaction of hydrogen at each of four major air terminals is an integral part of she plan. (Author( A79-45414 # Development of a control wheel steering mode and suitable displays that reduce pilot workload and improve A79-46055 Enthalpies of combustion of ramjet fuels. N. efficiency and safety of operation in the terminal area and in K. Smith and W. D. Good (U.S. Department of Energy, Bartlesville windshear. A. A. Lambregts and D. G. Cannon (Boeing Commercial Energy Technology Center, Bartlesville, Okla.). AIAA Journal, vol. Airplane Co., Seattle, Wash.). In: Guidance and Control Conference, 17, Aug. 1979, p. 905-907. 16 refs. Grant No. AF-AFOSR-ISSA-78- Boulder, Cob., August 6-8, 1979, Collection of Technical Papers. 0009. New York, American Institute of Aeronautics The paper gives details of experimental measurements of the and Astronautics, Inc., 1979, p. 609-620. 19 refs. (AIAA 79.1887) enthalpies of combustion of four hydrocarbon liquids being eval- A flight path angle and ground track Control Wheel Steering uated as ramjet fuels: exo-THDC, RJ-4, RJ-4-1, and JP-9. The four System development including suitable displays, to reduce pilot liquids have high enthalpies of combustion per unit volume. workload and improve safety during manual aircraft maneuvering, is Attention is given to calibration, calorimetric results, and derived discussed. System requirements and design options are reviewed. The results. B.J. rate-command/hold system, using display of both the control A79-46060 # Axisymmetric calculations of transonic wind variables and their reference commands, is shown to meet informa- tunnel interference in slotted test sections. K. R. Karisson and Y. tion and control handling qualities requirements. The design details C.-J. Sedin (Saab-Scania AB, Aerospace Div., Linkoping, Sweden). to achieve satisfactory control sensitivity, response damping and AIAA Journal, vol. 17, Aug. 1979, p.917.919.
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A study has been performed to investigate Berndt's inviscid A79-46241 Reflection elimination in secondary surveil- theory (1977) of wall interference in slotted test sections. Only lance radar. B. A. Wyndham (Royal Signals and Radar Establishment, axisymmetric flows have been calculated, though there is no limit to Great Malvern, Worcs., England). Radio and Electronic Engineer, vol. the theory. The wall interference on the model has been defined 49, June 1979, p. 311-322. 7 refs. through a single number, called the figure of tunnel interference Two major approaches for reducing reflections in secondary (FTI). The FTI is based on an average value of the difference in surveillance radars (SSR) are presented. Both uplink interrogation model surface pressure between the tunnel case and the simulated and downlink reply methods can be employed for reducing the cross freestream case. Two different tunnel blocking ratios are demon- section of the reflector, improving antennas, and siting. In addition, strated for a parabolic arc body mounted on a sting at two different the uplink methods can be used for modifying interrogation signal Mach numbers, the higher of which gives a fully choked test section. formats and transponder circuits, while the downlink methods are B. J. useful for recognizing particular characteristics of reflected signals. It is noted that apart from sensible site evaluation and appropriate A79-46225 Monitoring stratospheric winds with antenna design, only two effectual ways are found for existing sites: Concorde-generated infrasound. W. L. Donn and D. Rind (Lamont- using either hardware or software reflection detectors, or both, in the Doherty Geological Observatory, Palisades, N.Y.). Journal of Applied downlink receiver system. V. T. Meteorology, vol. 18, July 1979, p. 945-952. 6 refs. FAA-NSF- Army-supported research. A79-46466 The global positioning system /NAVSTAR/, B. The relatively low frequency of the sonic boom generated by W. Parkinson (Colorado State University, Fort Collins, Cob.). the Concorde SST permits propagation in the form of infrasound to Bulletin Géodesique, vol. 53, no. 2, 1979, p. 89-108. long range with small attenuation. Signal characteristics at long range The NAVSTAR navigational satellite system concept is de- are a function of atmospheric propagation parameters. When the scribed. Three major segments are covered: )1) the space segment, relationship of propagation to signal is understood, the propagation consisting of 24 satellites, 8 each in three approximately circular conditions can be determined by inversion with good accuracy. It is orbits at 10,900 nautical miles, with orbital periods of 12 hours, (2) shown how signal recorded at Palisades, New York, from the the control segment which monitors the functions of the satellite and Dulles-bound SST reveals direction and speed of stratospheric wind precisely calibrates their future locations, and (3) the users which variations diurnally and seasonally and also gives details of at least include land, sea, air and space navigation users. Attention is given to local circulation change as times of stratospheric warmings. )Author) the basic system technique, expected system accuracy, applications, and test results to date. M.E.P. A7946238 # Demonstration of aircraft wing/store flutter suppression systems. C. Hwang, B. A. Winther, G. R. Mills (Northrop A79-46686 # Numerical investigation of the perpendicular Corp., Hawthorne, Calif.), T. E. Noll (USAF, Flight Dynamics injector flow field in a hydrogen fueled scramjet. J. P. Drummond Laboratory, Wright- Patterson AFB, Ohio), and M. G. Farmer )NASA, (NASA, Langley Research Center, High-Speed Aerodynamics Div., Langley Research Center, Hampton, Va.). Journal of Aircraft, vol. Hampton, Va.(. American Institute of Aeronautics and Astronautics, 16, Aug. 1979, p. 557-563. 13 refs. Contract No. F33615-76-C-3039. Fluid and Plasma Dynamics Conference, 12th, Williamsburg, Va., A wind tunnel test program was conducted to demonstrate the July 23-25, 1979, Paper 79-1482. 13 p. 17 refs. active wing/store flutter suppression systems on a lightweight fighter A computer program has been developed which numerically aircraft. The program, completed in mid-1978, included the design, solves the full (elliptic( two-dimensional Navier-Stokes and specie analysis, fabrication, and testing of a scale model. The tests were equations near a slotted perpendicular hydrogen fuel injector in a conducted at the NASA Langley 16-ft Transonic Dynamics Tunnel. scramjet engine. The program currently predicts the turbulent mixing Three store configurations were selected for testing. Two of these of injected hydrogen fuel and air without reaction, and allows the configurations were deliberately designed to exhibit low flutter study of separated regions of flow immediately preceding and speeds with rapid reductions in damping at the incipient flutter following the injector as well as the complex shock-expansion condition. After initial tunnel entries, which showed the need for structure produced by the injector in this region of the engine. certain improvements in the model and the control system design, Results are presented that describe the size of the separated regions substantial increases in the flutter speeds were achieved using both near the injector as well as locations where ignition is likely to occur. leading- and trailing-edge control surfaces, separately. For the most (Author( critical configuration, a demonstrated improvement of 18% and a projected improvement of 29% in the dynamic pressure were A79'46691 # Application of stability theory to laminar flow achieved. (Author) control. J. N. Hefner and D. M. Bushnell (NASA, Langley Research Center, High-Speed Aerodynamics Div., Hampton, Va.). American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynam- ics Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper A79-46240 Aerial isolation ' a study of the interaction 79-1493. 20 p. 104 refs. between co-sited aerials. D. A. Bull and B. W. Smithers (Electrical The paper summarizes the state-of-the-art for application of Research Association, Ltd., Leatherhead, Surrey, England). Radio stability theory to laminar flow control using suction, wall tempera- and Electronic Engineer, vol. 49, June 1979, p. 289-296. 8 refs. ture and/or favorable pressure gradient ('natural laminar flow'). Research supported by the Ministry of Defence (Procurement Discussions include current LFC problem areas requiring stability Executive). analyses, methods of relating stability theory to transition with The increased complexity of modern aircraft has resulted in a results from data and theory comparisons available thus far, and a proliferation of antennas sited in close proximity to one another, a summary of low disturbance data available for theory calibration on trend more marked in military types, which makes it even more swept wings. Critical Issues highlighted are problems peculiar to necessary to ensure compatibility of working in a crowded RF suction LFC on high performance transonic wings and application of spectrum. The paper presents the investigations that have been made the e-to-the-n-power method to both low and high speed flight data. to determine the degree of isolation between transmitting and (Author) receiving antennas in aircraft within the frequency range 30 to 1250 MHz. From measurements using cylinders, ground planes, helicopters A79-46692 # The stability of the boundary layer on a swept and fixed-wing aircraft, empirical formulas for the calculation of wing with wall cooling. S. G. Lekoudis. American Institute of antenna-to-antenna isolation have been derived. Investigations have Aeronautics and Astronautics, Fluid and Plasma Dynamics Confer- also been carried Out to determine the amplitude of the harmonics ence, 12th, Williamsburg, Va., July 23-25 1979, Paper 79-1495. 11 generated by airborne transmitters. The results obtained from both P. 26 refs. Research supported by the Lockheed-Georgia Indepen- these aspects of the work are discussed. (Author) dent Research and Development Program.
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Linear stability theory is used to examine the propagation of (NASA, Ames Research Center, Moffett Field, Calif.). American laminar instabilities in the leading edge region of a transonic swept Institute of Aeronautics and Astronautics, Fluid and Plasma Dynam- wing with wall cooling. Before this could be done, the effects of ics Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper computing real group velocity ratios for monochromatic waves 79-1503. 17 p. 22 refs. needed investigation. When crossflow disturbances were computed An Investigation of trailing-edge flows as high Reynolds number using spatial theory and for a limited range of angles of wavegrowth and subsonic Mach numbers is presented. Symmetric and asymmetric direction, the growth rate in the direction formed by the real ratio of trailing-edge flows are studied, each flow having pressure gradient the group velocities and the direction itself were insensitive to the regions upstream of the ti-ailing edge similar to an airfoil. Measure- orientation of the wave growth. When temporal theory was used, this ments include model surface pressures, mean velocity, turbulent condition resulted in a single wave of maximum amplification. It is shear stress, and turbulent kinetic energy profiles in the trailing-edge found that wall cooling has a stabilizing effect on crossflow and near-wake regions. Comparisons of the symmetric data with disturbances, but the stabilization is mild compared to the stabilizing numerical solutions of boundary layer as well as Navier-Stokes effect that wall cooling has on Tollmien .Schlichting waves. (Author) equations employing two different turbulence models show increas- ing effects on viscous interactions as the Mach number increases. A79.46693 # Investigation of three-dimensional shock/ Both turbulence models yielded solutions of the mean flow of boundary layer interactions at swept compression corners. G. S. comparable quality. The experimental results of the asymmetric case Settles and J. J. Perkins (Princeton University, Princeton, N.J.). are discussed. (Author) American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference, 12th, Williamsburg, Va., July 23-25, A79-46701 # A careful numerical Study of flowfields about 1979, Paper 79-1498. 14 p. 18 refs. Contract No. external conical corners, I - Symmetric configurations. M. D. Salas F44620-75-C-0080. (NASA, Langley Research Center, High-Speed Aerodynamics Div., The paper discusses the first phase of an experimental investiga- Hampton, Va.). American Institute of Aeronautics and Astronautics, tion of a three-dimensional shock wave/turbulent boundary layer Fluid and Plasma Dynamics Conference, 12th, Williamsburg, Va., interaction. Compression corners of 16-deg and 24-deg angles which July 23-25, 1979, Paper 79-1511. 10 p. 15 refs. cause near-incipient and well-separated two-dimensional flows at A numerical study of the flowfield about symmetrical external Mach 3 are systematically swept through angles up to 50 deg, while axial corners formed by the juncture of swept compressive wedges is maintaining a constant streamwise corner angle. The resulting presented. The geometrical configuration under investigation allows a three-dimensional flows are studied by means of detailed surface unified treatment of external corners typical of delta wings and of measurements and a few exploratory flowfield surveys. Tests at four rectangular inlets. Comparisons are made with other numerical Re numbers reveal that a Re-number influence on the interaction results. For the delta wing configuration, the occurrence of an length remains in effect across the available range of sweep. B.J. anomalous shock behavior predicted by Gonor is discussed. A parametric study shows the singular behavior of the pressure at the corner as a function of the external corner angle, and a second A79-46694 # Transonic flow past a symmetrical airfoil at parametric study shows the effect of finite corner radius on the high angle of attack. D. A. Johnson, F. K. Owen (NASA, Ames Research Center, Moffett Field, Calif.), and W. D. Bachalo (NASA, location of the crossflow stagnation point. Previous theoretical Ames Research Center, Moffett Field; Spectron Development predictions of certain flow features typical of corner flows agree well with present numerical results. Laboratories, Inc., Costa Mesa, Calif.). American Institute of (Author) Aeronautics and Astronautics, Fluid and Plasma Dynamics Confer- A79-46702 # Recent progress in finite-volume calculations ence, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1500. 15 for wing-fuselage combinations. D. A. Caughey (Cornell University, p. 21 refs. Ithaca, NY.) and A. Jameson (New York University, New York, The results of an experimental investigation of shock-induced N.Y.) - American Institute of Aeronautics and Astronautics, Fluid stall and leading-edge stall on a 64A010 airfoil section are presented. and Plasma Dynamics Conference, 12th, Williamsburg, Va., July Advanced nonintrusive techniques - laser velocimetry, holographic 23-25, 1979, Paper 79-1513, interferometry, and buried-wire anemometry - were used in charac- 13 p. 12 refs, Contracts No, N00014-78-C-0079; No. NAS-9913, terizing the inviscid and viscous flow regions. The measurements Progress in the application of finite-volume methods to the include Mach contours of the inviscid flow regions, and mean calculation of transonic potential flows past general wing-body velocity, flow direction and Reynolds shear stress profiles in the combinations is reviewed. Two different methods of generating separated regions. The experimental observations of this study are relevant to efforts to improve surface pressure prediction methods boundary-conforming grids are investigated, and the results com- pared to provide an estimate of solution sensitivity to grid geometry. for airfoils at or near stall. (Author) Both conservative and quasi-conservative difference schemes are used A79-46695 # Supercritical airfoil boundary-layer measure- in one of the coordinate systems. Results show that the error ments. F. W. Spaid (McDonnell Douglas Research Laboratories, St. introduced by the quasi-conservative formulation seems to be small, Louis, Mo.) and L. S. Stivers, Jr. American Institute of Aeronautics although a one-dimensional analysis suggests that schemes of this and Astronautics, Fluid and Plasma Dynamics Conference, 12th, type do not necessarily produce mass-conserving shocks. Comparison Williamsburg, Va., July 23-25, 1979, Paper 79-1501. 14 p.23 refs. of calculated results with experimental data for realistic fuselage A series of experiments was conducted on flowfields about two geometries clearly shows the importance of modelling the effect of models which had sections that were slight modifications of the fuselage geometry upon the wing pressure distribution. (Author) original Whitcomb supercritical airfoil section. Boundary-layer pro- A79-46703 fi The effect of blade-to-blade flow variations on files were obtained on both upper and lower surfaces for combina- the mean flow-field of a transonic compressor. A. K. Sehra (General tions of lift coefficient and freestream Mach number including both Electric Co., Lynn, Mass.) and J. L. Kerrebrock (MIT, Cambridge, subcritical cases and flows with upper-surface shocks. The data are Mass,). American Institute of Aeronautics and Astronautics, Fluid intended to provide test cases for comparison with predictions of and Plasma Dynamics Conference, 12th, Williamsburg, Va., July numerical computations, and to contribute to a more detailed 23-25, 1979, Paper 79-1515. 12 p. 16 refs. Contract No. understanding of the mechanisms associated with transonic drag rise. F-33615-76-C-2118. Comparisons are made between measured boundary-layer properties The axisymmetric mean flow field of a highly loaded transonic and results from boundary-layer computations which employed compressor rotor can be accurately predicted by a theory which measured static-pressure distributions. (Author) includes the effects of blade-to-blade flows on the axisymmetric mean by peripheral averaging. In highly loaded rotors the most A79-46697 # Trailing-edge flows at high Reynolds number, important effects of the blade-to-blade flow on the axisymmetric P. R. Visseanath, j. W. Cleary, H. L. Seegmiller, and C. C. Horstman mean arise from radial flows due to boundary layers and wakes. Of
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the three effects modeled, namely apparent stresses, mean rothalpy cal, and experimental results have all been used to demonstrate this variation, and apparent entropy variation along streamsurfaces, the conclusion. Improvements in both zero lift drag and drag due to lift last two dominate the departure of the real flow from the have been identified. The results show that the exploitation of these conventionally treated axisymmetric flow. B.J. non-linear aerodynamic effects may be a key ingredient of future supersonic aircraft. (Author) A79-46704 # Subsonic flow past an oscillating cascade with finite mean flow deflection. J. M. Verdon and J. R. Caspar (United A79.46711 # Technique for developing design tools from Technologies Research Center, East Hartford, Conn.). American the analysis methods of computational aerodynamics. W. H. Davis, Institute of Aeronautics and Astronautics, Fluid and Plasma Jr. (Grumman Aerospace Corp., Aerodynamics Section, Bethpage, Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, N.Y.) - American Institute of Aeronautics and Astronautics, Fluid Paper 79-1516. 12 p. 21 refs. Research sponsored by the United and Plasma Dynamics Conference, 12th, Williamsburg, Va., July Technologies Corp. 23-25; 1979, Paper 79-1529. 10 p. 17 refs. Research supported by A theoretical model for predicting the aerodynamic response the Grumman Aerospace Corp. due to a finite-deflection cascade oscillating in a subsonic stream is An initial attempt at a technique to generate, simply and described. Based on the assumption of small amplitude harmonic rapidly, mixed direct-inverse codes from their direct counterparts is blade motions, the unsteady flow is treated as a small fluctuation presented. A surface alteration procedure, keyed to flow type for the about the non-uniform mean flow. The mean or steady flow is mixed case, is 'wrapped around' an existing direct code. The determined as a solution of the full potential equation while the difference between calculated and target pressures determines surface unsteady flow is governed by a linear equation with variable modifications. The direct code is used as a 'black box', The coefficients which depend on the steady flow field. Numerical technique features retention of the strength of the direct analysis and solutions based on this genei a! aerodynamic model have been easy interchangeability of the analysis code. The technique is obtained for simple cascade configurations. Selected results for demonstrated in two cases, a nonlinear supersonic wing code and a sharp-edge blade profiles are described. Those for flat plate cascades transonic airfoil code. (Author) are shown to be in good agreement with previous analytical predictions for both subresonant and superresonans blade motions. A79.46712 5 Water tunnel flow visualization - Insight into Predictions for double circular arc and thin circular arc profiles complex three-dimensional flow fields. G. E. Erickson )Northrop reveals that blade thickness has a significant effect on she unsteady Corp., Hawthorne, Calif.). American Institute of Aeronautics and response while the effect of flow turning due to blade camber is only Astronautics, Fluid and Plasma Dynamics Conference, 12th, minimal. (Author) Williamsburg, Va., July 23-25 1979, Paper 79-1530. 17 p. 18 refs. Water tunnel facilities and flow visualization techniques have A79-46706 # An iterative lifting surface method for thick been developed as Northrop to provide high-quality visualization of bladed hovering helicopter rotors. K. R. Shenoy and R. B. Gray vortex interactions at high angles of attack. Results have provided (Georgia Institute of Technology, Atlanta, Ga.). American Institute considerable insight into highly-complex three-dimensional flow of Aeronautics and Astronautics, Fluid and Plasma Dynamics fields generated by contemporary fighter aircraft. Studies have been Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper made of the leading-edge vortex systems generated by wing leading- 79-1517.8 p. 17 refs. edge extensions (LEX) typical of current subsonic-transonic fighter A prescribed-wake, inviscid, lifting-surface method using surface aircraft, high angle-of-attack aerodynamic asymmetries associated vorticity distributions is developed to predict the pressure distri- with the vortex system developed on long slender forebodies, and bution on thick-bladed helicopter rotors in hover. Starting with an forebody and wing/LEX vortex interactions characteristic of highly. approximate surface vortex sheet strength distribution, the final maneuverable aircraft with hybrid wing planforms and slender strength distribution is computed iteratively by applying the Biot- forebodies. Qualitative results are in excellent agreement with Savart law. The convergence rate is rapid, and reasonably good existing subsonic wind tunnel data. The water-to-air analogy has been results can be obtained within three iterations. The results show good verified, that is, aircraft forebody and wing/LEX vortex systems, agreement with the experimental results except for very near the tip vortex system interactions, and the downstream influence on flow of the blade. At spanwise stations inboard of the maximum blade characteristics exhibited in air at high Reynolds numbers can be bound circulation, the results indicate adequacy of the lifting-line simulated at low Reynolds numbers in the water tunnel. (Author) representation for the blade. (Author) A79-46713 Steady and unsteady vortex-induced asym- A79-46709 # Peak Strouhal frequency of subsonic jet noise 5 metric loads - Review and further analysis. L. E. Ericsson (Lockheed as a function of Reynolds number. K. Yamamoto (New York, State Missiles and Space Co., Inc., Sunnyvale, Calif.). University, Buffalo, N.Y.) and R. E. A. Arndt (Minnesota, Univer- American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Confer- sity, Minneapolis, Minn.). American Institute of Aeronautics and ence, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1531. Astronautics, Fluid and Plasma Dynamics Conference, 12th, Wil - 22 p. 82 refs. Contract No. N60921-77-C-0234. liamsburg, Va., July 23-25, 1979, Paper 79-1525. 6 p. 12 refs. The unsteady aerodynamic characteristics of a cylinder normal USAF-supported research; Grant No. NG R-39-009-270. to she flow have been studied in order to obtain a better An experimental study of the narrowband spectra of radiated understanding of the steady and unsteady vortex-induced asym- sound from subsonic jets is discussed. It is found that the acoustic metric loads on slender axi-symmetric bodies at high angles of attack. field is Reynolds-number-dependent below a Reynolds number of It is found that the coupling between flow separation and body about 200,000. This has important implications for the study of surface motion, which is significant even for purely laminar or coherent structures as radiators of sound. B. J. turbulent flow, becomes very much stronger when boundary layer A79-46710 # Opportunities for supersonic performance transition occurs near the flow separation. Thus, at transcritical gains through non-linear aerodynamics. W. H. Mason and G. DaForno Reynolds numbers the asymmetric loads become almost one order of (Grumman Aerospace Corp., Aerodynamics Section, Bethpage, magnitude larger and additionally are reversed in sign relative to the N.Y.). American Institute of Aeronautics and Astronautics, Fluid loads at subcritical and supercritical flow conditions. It is shown how these effects can be explained using a moving wall/wall jet analogy. and Plasma Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1527. 21 p. 33 refs. Research sponsored by )Author) the Grumman Advanced Development Program; Contract No. NAS1-15351. A79-46114 • 5 Evaluation of flow quality in two NASA This paper contains a number of examples wherein basic transonic wind tunnels. F. K. Owen, P. C. Stainback, and W. D. aerodynamic shapes are shown to achieve improved performance Harvey )NASA, Langley Research Center, Hampton, Va.). American when non-linear effects are taken into account. Analytical, numeri- Institute of Aeronautics and Astronautics, Fluid and Plasma
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Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, of applicability of LTRAN2 in terms of reduced frequency, typically Paper 79-1532. 11 p. 16 refs. Contracts No. NAS1-14833; No. from 0.15 to 0.4. The specific transonic character of the unsteady NAS1-15223. airloads on the NACA 64 A006 airfoil is shown to be very strong at Tests have been conducted in the Langley Research Center low values of k. With increasing k the effect of the transonic flow on 8-foot Transonic Pressure Tunnel and the Ames Research Center the unsteady airloads diminishes rapidly, so that for k greater than 12-foot pressure wind tunnel in order to measure characteristic 0.4 lifting surface theory becomes an increasingly useful alternative. disturbance levels and energy spectra in their respective settling (Author) chambers, test sections, and diffusers and to determine the sources of these disturbances. Results are presented and discussed along with A79.46730 # Adverse pressure gradients effects on super- some specific recommendations. B.J. sonic boundary layer turbulence. A. J. Laderman (Ford Aerospace and Communications Corp., Newport Beach, Calif.). American Institute of Aeronautics and Astronautics, Fluid and Plasma A79-46715 # Effect of viscosity on wind-tunnel wall inter- Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, ference for airfoils at high lift. L. E. Olson (NASA, Ames Research Paper 79-1563. 12 p.23 refs. Contract No. F33615-77-c-3016. Center, Moffett Field, Calif.) and S. Stridsberg (Flygtekniska ivdsurenients were made or mean flow profiles at several Forsoksanstalten, Bromma, Sweden). American Institute of Aero- ttreamwise locations in a supersonic turbulent boundary layer nautics and Astronautics, Fluid and Plasma Dynamics Conference, growing under a continuous adverse pressure gradient, tests were 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1534. 7 p. 21 performed at Mach 3 using two curved ramps designed to produce refs. constant pressure gradient flows. Analysis of the profile data The effect of the walls of a wind tunnel on the subsonic, indicates that with an appropriate compressibility transformation, two-dimensional flow past airfoils at high angles of attack is studied the data correlates with the well-defined Coles 'wall-wake' incom- theoretically and experimentally. The computerized analysis, which pressible velocity profile. In addition, correlation of the wake is based on iteratively coupled potential-flow, boundary-layer, and parameter and the Clauser shape factor with the local pressure separated-flow analyses, includes determining the effect of viscosity gradient is in agreement with the low speed data. B.J. and flow separation on the airfoil/wall interaction. Predictions of the effects of wind-tunnel wall on the lift of airfoils are compared with wall corrections based on inviscid image analyses, and with experi- mental data. These comparisons are made for airfoils thaz are large relative to the size of the test section of the wind tunnel. It is shown that she inviscid image modeling of the wind-tunnel interaction becomes inaccurate at lift coefficients near maximum lift or when the airfoil/wall interaction is particularly strong. It is also shown that the present method of analysis (which includes boundary-layer and flow-separation effects) will provide accurate wind-tunnel wall corrections for lift coefficients up to maximum lift. (Author)
A79-46719 • # The prediction of the turbulent flow field about an isolated airfoil. S. J. Shamrosh and H. J. Gibeling (Scientific Research Associates, Inc., Glastonbury, Conn.). American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1543. 15 p. 55 refs. Contract No. NAS1-15214. A compressible time-dependent solution of the Navier-Stokes equations including a transition-turbulence model is obtained for the isolated airfoil flow field problem. The equations are solved by a consistently split linearized block implicit scheme due to Briley and McDonald. A nonorthogonal body fitted coordinate system is used which has maximum resolution near the airfoil surface and in the region of the airfoil leading edge. The transition-turbulence model is based upon the turbulence kinetic energy equation and predicts regions of laminar, transitional and turbulent flow. Mean flow field and turbulence field results are presented for an NACA 0012 airfoil at zero and nonzero incidence angles at Reynolds number up to one million and low subsonic Mach numbers. (Author)
A79-46726 Al Results of an improved version of LTRAN2 for computing unsteady airloads on airfoils oscillating in transonic flow. A. Houwink and J. van der Vooren (Nationaal Lucht- en Ruimtevaartlaboratorium, Amsterdam, Netherlands). American Insti- tute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference, 12th, Williamsburg, Va., July 23-25, 1979, Paper 79-1553. 8 p. 9 refs. Research supported by the Netherlands Agency for Aerospace Programs. Using an inpoved version of the NASA Ames code LTRAN2, unsteady airloads were computed for a flat plate and a lifting transonic NACA 64 A006 airfoil, for harmonic pitch and control surface motions at reduced frequencies based on semi-chord 0 not greater than k not greater than 0.8. The main improvement of the code was obtained by adding appropriate unsteady terms to the boundary conditions as well as to the expression for the pressure coefficient. The results demonstrate the considerably extended range
577 N79-28129
conditions necessary for wind tunnel simulation of transonic flight are examined. A.R.H.
N79-28123# Lockheed-Georgia Co., Marietta. C . 5A Aerodynam- STAR ENTRIES ics Dept. SCALING EFFECTS ON DRAG PREDICTION J. H. Paterson In Von Karman Inst. for FLuid Dyn. High Reynolds Number Subsonic Aerodyn. Apr. 1969 36 p
Avail: NTIS HC A25/MF AOl N79-281 19# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- The intended purpose of wind tunnel tests and the component Genese (Belgium). drags which compose the total cruise drag are examined in this HIGH REYNOLDS NUMBER SUBSONIC AERODYNAMICS discussion of the effects of Reynolds number on drag. The Apr. 1969 584 p refs Lecture held at Rhode-Saint-Genese. prediction of full scale drag requires highly refined accurate wind Belgium, 21-25 Apr. 1969 tunnel procedures to insure that the transition from laminar to (VKI- Lecture- Series- 16) Avail: NTIS HC A25/MF AOl turbulent flow is identified or controlled. Experience with fixing Problems associated with the design of large subsonic aircraft the transition on C-5A models shows that some increment in are addressed with emphasis on scale effect, aerodynamic loads. drag-rise Mach number will be obtained full scale. The transition and the reduction of drag, noise, and vibration. The use of strip was located at 7% chord aft of the leading edge of the interactive systems and computer graphics in aircraft design is wing root, increasing to 19% at the tip. Calculations show that also examined. the nondimensional boundary layer thickness at 50% chord on the model is about 50% greater than predicted full scale values at 20% semispan and 32% at 95% semispan. A.R.H. N79-28120# Lockheed-Georgia Co.. Marietta. ADVANTAGES AND PROBLEMS OF LARGE SUBSONIC AIRCRAFT N79-28124# Southampton Univ. (England). B. H. Little, Jr. In Von Karman Inst. of Fluid Dyn. High Reynolds NOISE AND VIBRATION PROBLEMS: OUTLINE NOTES Number Subsonic Aerodyn. Apr. 1969 30 p refs P. E. Doak In Von Karman Inst. for Fluid Dyn. High Reynolds Avail: NTIS HC A25/MF AOl Number Subsonic Aerodyn. Apr. 1969 9 p The current and projected demand for large subsonic aircraft. both commercial and military, is discussed with emphasis on Avail: NTIS HC A25/MF AOl the advantages provided by these aircraft in economy, drag The fundamental concepts and techniques of aerodynamic reduction, passenger comfort, and lessened air traffic congestion. noise and vibration are outlined. R.E.S. Aerodynamically, the most important problems to be solved concern: wing design for high subsonic speeds; wing design for N79-28125# Lockheed- Georgia Co., Marietta. good low speed performance; stability and aeroelastic effects: WING DESIGN, BODY DESIGN, HIGH LIFT SYSTEMS AND total configuration design and optimization: propulsion system FLYING QUALITIES WITH INTRODUCTION integration requirements: and fluid flow scaling effects due to D. Ryle In Von Karman Inst. for Fluid Dyn. High Reynolds large vehicle size. The need for better mathematical tools to Number Subsonic Aerodyn. Apr. 1969 286 p provide theoretical solutions to high speed wind design to supercritical flow problems is discussed. A.R.H. Avail: NTIS HC A25/MF AOl Aerodynamic design process techniques are discussed from N79-28121# Lockheed-Georgia Co.. Marietta. an aircraft company's point of view. The following areas of design AEROMECHANICS are described; (1) parametric design techniques; (2)wing design; B. H. Little, Jr. In Von Karman Inst. for Fluid Dyn. High (3) body design; (4) high lift systems; and (5) flying qualities. Reynolds Number Subsonic Aerodyn. Apr. 1969 80 p refs R.E.S. Avail: NTIS HC A25/MF AOl Relatively speaking, low-frequency interactions between an N79-28126# Lockheed-Georgia Co.. Marietta. aircraft and its flight environment are examined. The fundamental ADVANCED COMPUTER TECHNOLOGY IN AERODYNAM- concepts of unsteady aerodynamics and the present status of ICS. LECTURE 1: COMPUTER-AIDED AIRCRAFT unsteady aerodynamic theory are discussed Significant problems DESIGN B. H. Little, Jr. In Von Karman Inst. for Fluid Dyn. High related to large subsonic aircraft explored concern self-induced Reynolds Number Subsonic Aerodyn. Apr. 1969 37 refs buffet, whirl flutter, wing flutter, transonic buffet, buzz phenomena, p and aeroelastic optimization. A.R.H. Avail: NTIS HC A25/MF AOl Computer graphic applications to aerodynamics are presented. N79-28122// Lockheed-Georgia Co.. Marietta. Computer programs on aircraft design, pressure reduction, SCALING EFFECTS ON SHOCK-INDUCED SEPARATION numerical control, and structural analysis are described. R.E.S.
B. H. Little, Jr. In Von Karman Inst. for Fluid Dyn. High N79 . 28129# Information Spectrum, Inc.. Warminster, Pa. Reynolds Number Subsonic Aerodyn. Apr. 1969 33 p refs MAINTENANCE IMPROVEMENT: AN ANALYSIS AP- PROACH INCLUDING INFERENTIAL TECHNIQUES. Avail: NTIS HC A25/MF AOl VOLUME 1: OVERVIEW Final Report, 27 Dec. 1977 - Data from wind tunnel tests and subsequent flight tests of 15 Mar. 1979 the C. 141 aircraft indicate strong possibility that scaling effects Milton Clyman and Philip S. Grenetz 15 Mar. 1979 42 p are associated with separation of the boundary layer at and refs 3 Vol. downstream of the shock waves. Features of the general flow (Contract MDA903-78-C-0176) model used to establish scaling criteria are discussed. Experiments )AD-A068380; ISI-W-7958-02A-Vol- 1) Avail: NTIS reported include investigations of shock-induced separation on I-IC A03/MF AOl CSCL 01/3 circular arc airfoils in a small transonic nozzle; a study of the This final report, contained in four volumes, presents the initial boundary layer effects on transonic shock-induced separation results of research into assessing the economic (Cost and in an axisymmetric nozzle; tests of a simulated C-141 in the down-time) impact of Potentially Avoidable Maintenance actions 4' x 6' nozzle, and tests of a swept wing pane) model in the for- selected Naval aircraft subsystems. Maintenance actions NASA-Ames 11 It transonic tunnel. The sensitivty of flows with requiring no repair and those resulting in induced defects and separation or incipient separation at the trailing edge and the failure-to-correct were identified. Specific high-driver two-digit
579 N79-28130
Work Unit Codes were analyzed for the F-14A Fire Control, N79-28138t# National Aeronautics and Space Administration. S-3A Bombing Navigation, S-3A Landing Gear, and A-7E Bombing Langley Research Center. Hampton. Va. Navigation. GRA THE EFFECT OF CANARD RELATIVE SIZE AND VERTICAL LOCATION ON THE SUBSONIC LONGITUDINAL AND N79-28130# Information Spectrum, Inc.. Warminster, Pa. LATERAL-DIRECTIONAL STATIC AERODYNAMIC CHAR- MAINTENANCE IMPROVEMENT: AN ANALYSIS AP- ACTERISTICS FOR A MODEL WITH A SWEPT FORWARD PROACH INCLUDING INFERENTIAL TECHNIQUES. WING VOLUME 2: TECHNICAL REPORT Final Report, 27 Dec. Jarrett K. Huffman and Charles H. Fox, Jr. Jul. 1979 106 p 1977 - 15 Mar. 1979 refs Milton Clyman, Philip S. Grenetz, and Richard S. Schultz 15 Mar. (NASA-TM-78739) Avail: NTIS HC A06/MF AOl CSCL 1979 190 p refs 3 Vol. O1A (Contract MDA903-78-C-0176) A general research fighter model was tested in the Langley (AD8 1; ISl-W-7958-02B-Vol.2) Avail: NTIS 7- by 10-foot high speed tunnel at a Mach number of 0.3. The HC A09/MF AOl CSCL 01/3 model was tested with a 32 deg swept forward wing mounted Research methodology, results, and recommendations are in mid-, low-, and high-wing positions. For the mid-wing presented. The interim feasibility report is appended. A.R.H. configuration, the model was tested with a 51.7 deg swept back canard mounted in mid-, low-, and high-canard positions. N79-28131# Information Spectrum, Inc., Warminster, Pa. For the mid-wing mid-canard and the mid-wing high-canard MAINTENANCE IMPROVEMENT. AN ANALYSIS AP- configurations, canards of similar planform having two different PROACH INCLUDING INFERENTIAL TECHNIQUES. areas were tested. The angle-of-attack range was from ap- VOLUME 4: SOFTWARE MANUAL Final Report. 27 Dec. proximately -4 deg to 48 deg at sideslip angles of 0 deg, -5 deg, 1977 - 15 Mar. 1979 and 5 deg. Author Milton Clyman. Vito A. Gentile, and Philip S. Grenetz 15 Mar. 1979 164 p 3 Vol. N79-28142*# Rockwell International Corp., Columbus, Ohio. (Contract MDA903-78-C-01 76) LOW SPEED WIND TUNNEL TEST OF GROUND PROXIMITY (AD-A068383; lSl-W-7958-02D-Vol.4( Avail: NTIS AND DECK EDGE EFFECTS ON A LIFT CRUISE FAN V/STOL HC A08/MF AOl CSCL 01/3 CONFIGURATION, VOLUME 2 Contractor Report, Mar. Volume IV includes the logic used to develop software for 1978 - Feb. 1979 generating the tables in Volume Ill, user instructions, and a V. R. Stewart May 1979 484 p complete listing of programs that were executed to arrive at (Contract NAS2-9$82( the tables. GRA (NASA-CR-i 52248: NR79H- 1 2-Vol-2) Avail; NTIS I-IC A21/MF AOl CSCL 01A N7928134*# Kentron International, Inc., Hampton, Va, The following test results are appended: (1) wind tunnel Technical Center. data, (2) static thrust stand data, and (3) fan calibration data. SENSITIVITY STUDY FOR A REMOTELY PILOTED MICRO- R.E.S. WAVE-POWERED SAILPLANE USED AS A HIGH-ALTITUDE OBSERVATION N7928143*# General Dynamics Corp. Fort Worth, Tex. A. Victor Turrizianj Jun. 1979 15 p refs AERODYNAMIC CHARACTERISTICS OF FOREBODY AND (Contract NAS1-13500) NOSE STRAKES BASED ON F-16 WIND TUNNEL TEST (NASA-CR-159089( Avail: NTIS HC A02/MF AOl CSCL EXPERIENCE. VOLUME 1: SUMMARY AND ANALYSIS OIA Final Report, 1 Sep. 1977 - 30 Sep. 1978 The sensitivity of several performance characteristics of a C. W. Smith, J. N. Ralston, and H. W. Mann Jul. 1979 145 p proposed design for a microwave-powered, remotely piloted, refs high-altitude sailplane to changes in independently varied design (Contract NAS 1-15006) parameters was investigated. Results were expressed as (NASA-CR-3053( Avail: NTIS I-IC A07/MF AOl CSCL CiA variations from baseline values of range, final climb altitude and The YF-16 and F-16 developmental wind tunnel test program onboard storage of radiated energy. Calculated range decreased was reviewed. Geometrical descriptions, general comments, with increases in either gross weight or parasite drag coefficient: representative data, and the initial efforts toward the development it also decreased with decreases in lift coefficient, propeller of design guides for the application of strakes to future aircraft efficiency, or microwave beam density. The sensitivity trends for are presented. R.E.S. range and final climb altitude were very similar. The sensitivity trends for stored energy were reversed from those for range, N79-28144# Aeronautical Research Labs., Melbourne (Australia). except for decreasing microwave beam density. Some study results LONGITUDINAL AERODYNAMICS EXTRACTED FROM for single parameter variations were combined to estimate the FLIGHT TESTS USING A PARAMETER ESTIMATION effect of the simultaneous variation of several parameters: for METHOD two parameters, this appeared to give reasonably accurate R. A. Feik Oct. 1978 33 p refs results. A.R.H. (ARL/Aero-Note-379; AR-001-308) Avail. NTIS HC A03/MF AOl Flight data from a 60 deg delta wing fighter aircraft were analyzed using a modified Newton-Raphson parameter estimation N79-28136# New York Univ., N. Y. Courant Mathematics procedure. The model equations .jsed for the analysis were and Computing Lab. extended to account for incidence vane errors and non-linearities AN ARTIFICIAL VISCOSITY METHOD FOR-THE DESIGN in the pitching moment curves. Longitudinal derivatives extracted OF SUPERCRITICAL AIRFOILS from the data have been compared with wind tunnel measure- Geoffrey B. McFadden Jul. 1979 168 p refs ments and some theoretical estimates and areas of agreement (Grants NGR-33-016-201; NsG-1579; Contract and disagreement identified. The results demonstrate the EY-76-C-02-3077( usefulness of the parameter identification method, not only for (NASA-CR- 158840; COO-3077-158) Avail: NTIS the validation of aircraft mathematical models and for checking HC A08/MF AOl CSCL 01A flight results against wind tunnel data, but also for obtaining A numerical technique is presented for the design of aerodynamic data not easily available through other means. two-dimensional supercritical wing sections with low wave drag. A.R.H. The method is a design mode of the analysis code H which gives excellent agreement with experimental results and is widely N79-28145# Indian Inst. of Tech.. Bombay. Dept. of used in the aircraft industry. Topics covered include the partial Aeronautical Engineering. differential equations of transonic flow, the computational APPLICATION OF VORTEX LATTICE METHOD FOR THE procedure and results; the design procedure; a convergence EVALUATION OF THE AERODYNAMIC CHARACTERISTICS theorem; and description of the code. A.R.H. OF WINGS WITH AND WITHOUT STRAKES M.S. Thesis
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sponding to attached and detached shocks at.the leading edges Jatinder Singh 1979 114 p refs Avail: NTIS HC A06/MF AOl of a reentrant pyramidal waverider geometry. The MacCormack Wings characterized by small aspect ratio and large leading- shock capturing version of the Lax-Wendroff finite difference edge sweep exhibit separation along leading-edge and side-edge. technique is used with grids chosen to align with surface, symmetry Well defined vortex over leading-edge and side-edge gives rise and approximate shock traces in the transverse plane. Separate to incremental vortex lift. The aerodynamic characteristics of more natural grid systems are defined for the compression and expansion generalized planforms incorporating incremental vortex lift are regions, and an alternating region algorithm is used in combination determined by using vortex lattice method to calculate the with a sequential transfer of the edge region boundary conditions. aerodynamic characteristics for potential flows. The effects of The latter are derived from overlapping portions of the computa- the leading edge vortex, tip vortices, and the detached leading tional grids as integration proceeds axially to an asymptotic conical edge and side edge vortices over the lifting surface are considered. field. Equivalent attached shock cases result from either of two A flow chart and input parameters for wings with and without approaches: the alternating region algorithm, or a consideration strakes are given for a program calculating the aerodynamic of solely the compression region with uniform unknown conditions characteristics of a planar wing in symmetric flight in an assumed near the edges. For detached shock cases overall lift incompressible flow. Predicted values are compared with and drag coefficients exhibit smooth variations between the experimental results. A.R.H. attached edge and detached apex limits. GRA
N79-281 46*// National Aeronautics and Space Administration. N79-28157# California Inst. of Tech., Pasadena. Div. of Lewis Research Center, Cleveland, Ohio. Engineering and Applied Science. WING AERODYNAMIC LOADING CAUSED BY JET- UNSTEADY SMALL-GAP GROUND EFFECTS INDUCED LIFT ASSOCIATED WITH STOL-OTW CONFIGU- E. 0. Tuck Mar. 1979 47 p RATIONS )Contract N00014-76-C-0157; NA Proj. 062-230) U. vonGlahn and D. Groesbeck 1979 40 p refs Presented )AD-A068400: E-978-54) Avail: NTIS HC A03/MF AOl CSCL at Atmospheric Flight Mech. Conf., Boulder, Cob., 6-8 Aug. 1979: 20/4 sponsored by AIAA Fluid-dynamic problems involving bodies moving close to )NASA-TM-79218: E-1 10) Avail: NTIS HC A03/MF AOl CSCL walls are of interest in many different contexts, and there is a O1A considerable literature dealing with such problems. The present Surface pressure distributions were obtained with model-scale paper concerns itself with phenomena which can be treated on STOL-OTW configurations using various nozzles designed to an inviscid-fluid basis, and hence has little connection with the promote flow attachment to the wing/flap surface. The nozzle important branch of that literature dealing with low-Reynolds- configurations included Slot-types and both circular and slot nozzles number wall effects. The small-gap regime is defined, formally, with external flow deflectors. The wing aerodynamic loading as that in which the clearance is small compared to the horizontal caused by the jet-induced lift is presented in conventional terms length scale. Flow induced by a body moving near a plane wall of delta p/q as a function of chordwise surface distance in the is analysed on the assumption that the normal distance from nozzle centerline plane as well as outboard of the nozzle centerline. the wall of every point of the body is small compared to the Nozzle roof/deflector angle, chordwise location of the nozzle, body length. The flow is irrotational except for the vortex sheet wing size, and flap deflection angle are included in the geometric representing the wake. The gap-flow problem in the case of variables affecting the wing loading. A.R.H. unsteady motion is reduced to a nonlinear first-order ordinary differential equation in the time variable. Problems solved include N79-28149# Auburn Univ., Ala. Dept. of Aerospace airfoil starting flows and their transient wakes, and flat plates Engineering. falling toward the ground. GRA AN AERODYNAMIC ANALYSIS OF DEFORMED WINGS IN SUBSONIC AND SUPERSONIC FLOW Interim Report. N7928158*// National Aeronautics and Space Administration. Jan. - Dec. 1978 Langley Research Center. Hampton, Va. John E. Burkhalter. Milton E. Vaughn, Jr.. and John M. Abernathy POTENTIAL APPLICATIONS OF ADVANCED AIRCRAFT IN Mar. 1978 54 p refs DEVELOPING COUNTRIES )Grant DAAG29-78-G-0036) Dal V. Maddabon Jul. 1979 43 refs )AD-A067586) Avail: NTIS HC A04/MF AOl CSCL 20/4 p )NASA-TM-80133) Avail; NTIS HC A03/MF AOl CSCL The aerodynamic loading for deformed wings in both subsonic O1C and supersonic flow has been under study for the past year. Air transportation concepts for movement of cargo in The basic solution technique falls into the potential flow category developing countries are reviewed using aicraft which may appear with appropriate restrictions. A lifting surface kernel function in the future. For certain industrial applications, including mining formulation is used for both subsonic and supersonic flow and and forestry. the relative costs of doing the job using different results are obtained which agree very well with experimental types of aircraft are compared with surface transportation data Subsonic solutions for deformed wings with deflected elevons systems. Two developing countries, Brazil and Indonesia, were are obtained in a semi-closed form summation manner. Cases taken as examples to determine what impact they might have under study which include gaps between the elevon wings are on the aircraft markets of the future. Economic and demographic as yet incomplete but are presently being pursued. For supersonic data on developing countries in general. and Brazil and Indonesia flow, a modified Evvard solution forms the basis for the planar in particular, are reviewed. The concept of an industrial city in a wing cases and vorticty paneling is added to account for local remote area developed around an airport is discussed. It is noted deformations in the wing mean camber surface. Results are that developing areas generally lack extensive surface transporta- obtained which agree very well with experimental data. The gapped tion systems and that an air transportation system can be elevon cases for supersonic flow is also analyzed and preliminary implemented in a relatively short time. A developing nation results have identified thickness effect, as being very important, interested in rapid expansion may thus find the role of air cargo Author )GRA) at least for small elevon deflections, far more important than has been true in developed nations. Technological developments which may dramatically increase the N79-28156// Massachusetts Inst. of Tech,, Cambridge. Fluid performance of agricultural aircraft are also reviewed. Author Dynamics Research Lab. AN OFF DESIGN SHOCK CAPTURING FINITE DIFFERENCE APPROACH FOR CARET WAVERIDER CONFIGURATIONS N79-28160# Civil Aeromedical Inst., Oklahoma City, Okla. Final Report, 1 Apr. 1977 - 31 Dec. 1978 INJURIES IN AIR TRANSPORT EMERGENCY EVACUA- Judson R. Baron and I. Efrat Feb. 1979 96 p refs TIONS )Contract F49620-77-C-0090: AF Proj. 2307) DoneII W. Pollard Feb. 1979 32 p refs )AD-A068819: AFOSR-79-0517TR) Avail: NTIS )AD-A069372: FAA-AM-79-6) Avail; NTIS HC A03/MF AOl HC A05/MF AOl CSCL 20/4 CSCL 01/2 The three dimensional off design flow fields are calculated Twelve air transport evacuations are reviewed. Injuries are for Stream Mach numbers in the range 1.3 to 4.0 and corre- discussed with emphasis on configurational and procedural
581 N79-28161 contributing factors. Recommendations and information about STARAN array processor. Six figures detailing the analytic and possible methods of reducing injuries are provided. Author data storage concepts discussed are given. An example illustrating the improved penetration possible from these methods is N79-28161# University of Northern Illinois. De Kalb. Dept. presented. of Biological Sciences. GRA DEVELOPMENT OF COMPUTER-GENERATED PHENO- GRAMS TO FORECAST REGIONAL CONDITIONS HAZARD- N7928168*# McDonnell-Douglas Corp., St. Louis, Mo. OUS TO LOW-FLYING AIRCRAFT Interim Report, 30 Sep. HYPERSONIC AIRFRAME STRUCTURES: TECHNOLOGY 1977 - 30 Sep. 1978 NEEDS AND FLIGHT TEST REQUIREMENTS Final Report William E. Southern 15 Nov. 1978 219 p refs J. E. Stone and L. C. Koch Jul. 1979 134 p refs (Grant AF-AFOSR-3431-77: AF PrOj. 2312) (Contract NAS1 '149241 (AD-A068812; AFOSR-79-061 1TR) Avail: NTIS (NASA-CR-3 130; MDC-A4839) Avail: NTIS HC A10/MF AOl CSCL 01/2 NC A07/MF AOl CSCL 01 The seasonal distribution of all North American gull species Hypersonic vehicles, that may be produced by the year 2000, as derived from banding data and Christmas Bird Count reports were identified. Candidate thermal/structural concepts that merit is presented. The proportion of each months gull population is consideration for these vehicles were described. The current status shown for 6 square Zones designated by latitude and longitude. of analytical methods, materials, manufacturing techniques, and The number of birds present per Zone is plotted therein according conceptual developments pertaining to these concepts were to Quadrants (= 1/4 Zone). USAF bird strikes occurring during reviewed. Guidelines establishing meaningful technology goals 1974-1977 also are mapped for comparison. This preliminary were defined and twenty-eight specific technology needs were summary of gull distribution and strike data can be used to identified. The extent to which these technology needs can be identify when and where gulls may be presenting a significant satisfied, using existing capabilities and facilities without the hazard to low-flying aircraft. Application of the information during benefit of a hypersonic research aircraft, was assessed. The role flight planning could reduce the number of strikes caused by that a research aircraft can fill in advancing this technology was gulls. Continuing studies will attempt to refine the application discussed and a flight test program was outlined. Research aircraft of such bird data to predict hazard levels to aircraft. GRA thermal/structural design philosophy was also discussed. Programs, integrating technology advancements with the projected vehicle needs, were presented. Program options were provided N79-28162 Ohio State Univ.. Columbus. to reflect various scheduling and cost possibilities. R.E.S. A STUDY OF ALTIMETER-CONTROLLED TERRAIN- FOLLOWING SYSTEMS Ph.D. Thesis Donald Morris Sovine 1979 210 p N79-28169# Bell-Northern Research Ltd., Ottawa (Ontario). Avail: Univ. Microfilms Order No. 7916028 ELECTROMAGNETIC COMPATIBILITY (EMC) INVESTIGA- TION ON CH147 CHINOOK HELICOPTER The probability of crashing (or clobbering), of P sub c was R. R. estimated. The techniques for the estimation of P sub c are Goulette and K. E. Felske Jan. 1979 54 p accurate when applied to a linear vehicle with synthetically (Contract DNF-2pb77-001 86; AETE Proj. 77/16-4) (Rept-5J30-4479 .02 DSS-3P8 .2 127662) Avail: NTIS generated terrain as an input. When both real and simulated NC A04/MF AOl terrain is the input to a nonlinear vehicle model, the results are similar; however, occasionally large errors occur that are not The findings of the electromagnetic compatibility investiga- predicted by the theory. Similar errors are also apparent when tion performed on the CH147 Chinook helicopter, fitted with a real terrain is the input to the linear vehicle model, an indication high intensity anticollision strobe light, a crash position indicator, that anomalous terrain behavior as well as Certain characteristics and an Omega navigation system are presented. R.E.S of the limiters may be pronounced contributors to P sub c. It is concluded that the theory is an excellent tool for system design N79-28170# United Technologies Corp., Stratford. Conn but that an alternate technique is desirable for accurate selection Sikorsky Aircraft Div. of the required clearance altitudes for an actual flight vehicle. ESTABLISHMENT OF MANUFACTURING METHOD AND Dissert. Abstr. TECHNOLOGY FOR THE FABRICATION OF HELICOPTER MAIN ROTOR BLADE SPARS BY CONTINUOUS SEAM DIFFUSION BONDING TITANIUM SHEET MATERIAL Final N79-28165# Naval Air Rework Facility, Norfolk, Va. Report, 1 Oct. 1975 - 30 Sep. 1978 PACIFIC AREA EVALUATION OF A COMMERCIAL OMEGA Maron J. Bonassar and John L. Lucas Nov. 1978 169 p NAVIGATION SYSTEM INSTALLED IN A VC-118 AIRCRAFT, refs SUPPLEMENT 1 (Contract DAAG46-76-C-0016) Clifton G. Wrestler, Jr. 10 Apr. 1979 9 p )AD-A067590; SER-510010; AVRADCOM-TR-79-5 )AD-A068106; NARF-C-1 18-WSM-1-78-Suppl-1) Avail: NTIS AMMRC-TR-78-50( Avail: NTIS HC A08/MF AOl CSCL HC A02/MF AOl CSCL 17/7 13/8 A supplemental evaluation was deemed necessary for the This report summarizes a series of U.S. Army sponsored Pacific Area due to variations in the geographic locations and Manufacturing Methods and Technology, MM and T programs power output of the ground based transmitters. GRA which were ultimately aimed at evaluating and implementing into production the use of the Continuous Seam Diffusion Bonding. N79-28166# Army Engineer Topographic Labs.. Fort Belvoir, CSDB. process to fabricate reliable, tower cost titanium alloy Va. 6A1-4V helicopter main rotor blade spars. The current production ANALYSIS, STORAGE, AND RETRIEVAL OF ELEVATION process for manufacturing the UH-60A Army Black Hawk DATA WITH APPLICATIONS TO IMPROVE PENETRATION helicopter main rotor blade spars uses a plasma arc weld to Research Note loin a cold brake formed cylindrical shape titanium sheet pre-form. Allen Klinger Mar. 1979 21 p refs The titanium pre-form is subsequently creep formed to the required (AD-AO68747; ETL-0179( Avail: NTIS HC A02/MF AOl CSCL final contour. The subject program has investigated and fabricated 17/7 various shape spar pre-forms and manufacturing operations that A method to use terrain elevation data for guidance is could be easily cold brake formed from flat titanium sheet material presented. Tree Structure representation of contour trend data into a configuration that is capable of being Continuous seam over regions is the basis of the method. Regions of different diffusion bonded and subsequently cnep formed to the final sizes obtained by quartering given elevation matrices are used; contour. Tooling which is capable of clamping and satisfactorily region size corresponds to tree position. Two computer functions bonding the selected configuration pre-form shape has been are discussed: analysis methods to use tree-structured contour- designed and constructed. Process parameters relating to bonding trend information, suitable for onboard inflight computations; and variables and material condition have been evaluated. The storage reduction methods to present elevation data as a new subject program has successfully diffusion bonded three, ten foot digital mapping product (tree-structured contour-trend data), length BLACK HAWK spar tubes, and non-destructively inspected. computable off-line on the USAETL Computer Sciences Laboratory NDI, ten bonded spar tubes for any abnormalities. GRA
582 N79-28179
N79-28171fl Army Test and Evaluation Command. Aberdeen with valves operative kept the inlet started 4 to 28 times longer Proving Ground, Md. than with the valves inoperative. Hence, the stability system INTERNAL/EXTERNAL LIGHTING (AVIATION MATERIEL) provides additional time for the inlet control system to react Final Report and prevent unstart. This was observed for initial Mach Oct. 1978 33 p refs Supersedes MTP-7-3-527 numbers of 2.55 and 2.68. For slow increase in angle of attack (AD-A06895 1; TOP-7-3-527; MTP-7-3-527) Avail: NTIS at Mach 2.47 and 2.76. the system kept the inlet started beyond HC A03/MF AOl CSCL 01/3 the steady-state unstart angle. However, the maximum transient This TOP establishes the procedure to conduct a developmen- angles of attack without unstart could not be determined tal test of an internal and/or external lighting system as well as because wind-tunnel mechanical-stop limits for angle of attack illumination test of a single or multiple instruments set or any were reached. A.R.H. other special purpose light or lights associated with the aircraft operational capability or crew performance, including troop and N7928177*# National Aeronautics and Space Administration. cargo compartment lighting. The aircraft light or lighting system Lewis Research Center, Cleveland, Ohio. will be operated during all applicable aircraft operational phases EFFECT OF ROTOR MERIDIONAL VELOCITY RATIO ON and assessed under all applicable atmospheric and climatic RESPONSE TO INLET RADIAL AND CIRCUMFERENTIAL conditions representative of the operational environment the DISTORTION aircraft is expected to see within its operational theater. The Nelson L. Sanger Jul. 1979 73 p refs primary objectives of this TOP are: (1) to determine if the )NASA-TP-1278; E-8987) Avail: NTIS HC A04/MF AOl CSCL designated light or lighting system performs its intended function 21E in accordance with the requirements presented in the applicable Three single transonic fan stages, each having a different approved documents; Letter of Requirement (LR). Letter of meridional velocity ratio across its rotor, were tested with two Agreement (LOA), Required Operational Characteristics (ROd, magnitudes of tip radial distortion and with a 90 deg circumferen- etc., as reflected through the detailed Test Design Plan (TDP); tial distortion imposed on the inlet flow. The rotor with the (2) to establish any detrimental or compromising side effects; lowest meridional velocity ratio (less than 0.9 at the tip) (3) to insure human factors criteria have been met; and (4) to demonstrated the least degradation of performance due to these determine if the designated light or lighting system conforms to distortions. Loss and deviation angle data (as needed for the applicable military specifications and/or standards as well performance prediction with radial distortion) calculated along as system specifications. GRA actual streamlines for radially distorted flow and correlated against diffusion factor, showed consistent agreement with data calculated along design streamlines for undistorted flow. Author N79-28175# Calspan Corp.. Buffalo, N. Y. AN EXPERIMENTAL INVESTIGATION OF CONTROL- DISPLAY REQUIREMENTS FOR A JET-LIFT VIOL AIR- N79-28178# Monsanto Researcn Corp., Dayton, Ohio. CRAFT IN THE TERMINAL AREA Final Report, Jun. JET ENGINE EXHAUST ANALYSIS BY SUBTRACTIVE 1976 - Jul. 1978 CHROMATOGRAPHY Final Report, 1 Mar, 1977 - 24 Jul. 1978 J. V. Lebacqz, A. C. Radford, and J. L. Beilman Jul. 1978 Joseph J. Brooks, Diana S. West, John E. Strobel, and Leonard 399 p refs Stamper Dec. 1978 77 refs (Contract N62269-76-C-0370) p (Contract F33615-77-C-0616) )AD-A068818; CALSPAN-AK-5985-F-1( Avail: NTIS HC A05/ (AD-A067898; MRC-DA-839; SAM-TR-78-37 ) Avail: NTIS MFA01 CSCL 01/3 HC A05/MF AOl CSCL 21/2 The fourth flight research program using the variable stability, This report describes the further refinement of a method for variable display X-22A VTOL research aircraft was undertaken the sampling and analysis of organics in jet engine exhaust by with the objective of expanding the operational capability of chemical classes. Details for the selection, Construction, and VTOL aircraft under adverse weather conditions. The experiment evaluation of the combination sorbent (Tenax-GC/Ambersorb investigated a matrix of control, display and task variables for XE-340( sampling system are given along with the rationale the landing approach task in a ground simulation phase followed and operational parameters for the subtractive chromatography by an in-flight simulation phase. Aerodynamic characteristics of the McDonnell-Douglas AV-8B Advanced Harrier were simulated system mat produces the organic class analysis. The significant for a prescribed decelerating approach profile using the X-22A's improvements incorporated into both the sampling and analytical variable stability system; around this simulation, an analog of systems compared with previous systems used in a jet engine the AV-88 control system was implemented to investigate a exhaust study of March 1975 are discussed. The capabilities of range of realizable control system designs. Combinations of these the system are illustrated by the analysis of actual jet engine control concepts and a variety of head-up display formats and exhaust samples from a J85-5 engine using JP-4 and an alternate information levels were evaluated in fight for simulated instrument fuel blend that simulates the higher aromatic content expected approaches. GRA from shale and coal-derived fuels. Author (GRA)
N7928176*// Natioral Aeronautics and Space Administration. N79-28179# Air Force Aero Propulsion Lab., Wright-Patterson Lewis Research Center, Cleveland, Ohio. AFB, Ohio. A THROAT-BYPASS STABILITY-BLEED SYSTEM USING BUILD 1 OF AN ACCELERATED MISSION TEST OF A TF41 RELIEF VALVES TO INCREASE THE TRANSIENT STABILITY WITH BLOCK 76 HARDWARE Final Report. 18 Oct. OF A MIXED-COMPRESSION INLET 1977 - 13 Jan. 1978 George H. Neiner. Miles 0. Dustin. and Gary L. Cole Jul. 1979 Robert J. May, Jr.. Donald P. Mcerlean. and Doretta Holland 47 p refs Mar. 1979 191 p refs (NASA-TP-1083; E-8950( Avail: NTIS HC A03/MF AOl CSCL (AD-A068595; AFAPL-TR-79-2020( Avail: NTIS 21E HC A09/MF AOl CSCL 21/5 A stability-bleed system was installed in a YF-12 flight inlet An accelerated mission test (AMT) of a TF41 (S/N 142163) that was subjected to internal and external airflow disturbances was conducted in the Air Force Aero Propulsion Laboratory's in the NASA Lewis 10 by 10 foot supersonic wind tunnel. The D bay sea level engine test facility between 18 Oct 77 and purpose of the system is to allow higher inlet performance while 13 Jan 78. The primary objective of the test was to evaluate maintaining a substantial tolerance (without unstart) to internal the structural reliability of a series of parts changes known as and external disturbances. At Mach numbers of 2.47 and 2.76, Block 76 hardware under realistic usage conditions. A two the inlet tolerance to decreases in diffuser-exit corrected airflow hundred sixty three hour test program was initially planned but was increased by approximately 10 percent of the operating-point only one hundred and six hours were actually completed due to airflow. The stability-bleed system complemented the terminal- the failure of a second stage high pressure turbine blade. The shock-control system of the inlet and did not show interaction second stage turbine had been reworked and the verification of problems. For disturbances which caused a combined decrease this rework scheme was a secondary objective of this test. The in Mach number and increase in angle of attack, the system failure occurred at a reworked location but the actual cause of
583 N79-28181 failure could not be determined. The post-test teardown inspection N79-28187# Army Engineer Waterways Experiment Station. showed all of the Block 76 hardware to be in good condition. Vicksburg. Miss, Geotechnical Lab. G RA DEVELOPMENT OF A STRUCTURAL DESIGN PROCEDURE FOR RIGID AIRPORT PAVEMENTS Final Report. 1975 - N79-28181# Advisory Group for Aerospace Research and 1978 Development. Neuiily-Sur-Seine (France). Frazier Parker, Jr.. Walter R. Barker, Robert C. Gunkel, and Eugene TECHNICAL EVALUATION REPORT ON THE 52ND C. Odom Apr. 1979 299 p refs SYMPOSIUM OF THE PROPULSION AND ENERGETICS ON (Contract DOT-FA73WAI-377; DA Proj. 4A1-61 102-B-52E) STRESSES, VIBRATIONS, STRUCTURAL INTEGRATION )AD-A069548; WES-TR-G L-79-4; FAA-RD-77-81) Avail: NTIS AND ENGINE INTEGRITY (INCLUDING AEROELASTICIIY HC A13/MF AOl CSCL 01/5 AND FLUTTER) The development and formulation of a design procedure for L. Beitch (Gen. Elec. Co.. Evandale, Ohio) Mar. 1979 12 p rigid airport pavements are presented. The design criteria used refs Symp. held in Cleveland. Ohio. 23-27 Oct. 1978 in the procedure are based on the tensile stress in the portland (AGARD-AR- 133; ISBN-92-835-1314-2) Avail: NTIS cement concrete (PCC) slab as computed by layered elastic theory HC A02/MF AOl and the strength of the PCC slab as measured in the flexural A wide spectrum of topics associated with engine develop- beam test. The criteria were developed by the analysis of some ment, engine-aircraft integration, and engine operation were 60 test sections. Procedures are given for the characterization of the pavement materials both by laboratory testing and by addressed. M.M.M. typical values and/or correlation studies. The thickness require- ments as determined by the new Criteria are compared with the thickness as determined by present Corps of Engineers-Federal N79-28182 California Univ., Los Angeles. Aviation Administration design procedures. IDENTIFICATION OF AIRCRAFT PARAMETERS IN TUR- Author BULENCE WITH NON-RATIONAL SPECTRAL DENSITY Ph.D. Thesis N79-28188// Federal Aviation Administration, Washington, D. C Frank Chu-Chun Tung 1979 171 p Office of Management Systems. Avail: Univ. Microfilms Order No. 7915685 FAA AIR TRAFFIC ACTIVITY, FISCAL YEAR 1978 Aircraft turbulence was modeled with the von Karman Patricia Wilson 30 Sep. 1978 238 p spectrum in an attempt to improve the aircraft parameter (AD-A067910) Avail: NTIS MF AOl: HC SOD $4.50 CSCL estimation method. A new identification technique was introduced 01/2 to handle linear systems with non-rational transfer functions. This report furnishes terminal and enroute air traffic activity and the associated numerical methods were also developed. This information of the National Airspace System. The data have new technique was then applied to both simulated and actual been reported by the FAA-operated Airport Traffic Control Towers flight test data. Dissent. Abstr. (ATCTs). Air Route Traffic Control Centers (ARTCCs), Flight Service Stations (FSSs), Combined Station Towers (CS/Ts), N79-28183 Illinois Univ. at Urbana-Champaign. International Flight Service Stations (IFSSs(, and Approach Control EFFECT OF ATMOSPHERIC TURBULENCE ON THE Facilities. Author (GRA) STABILITY OF A LIFTING ROTOR BLADE Ph.D. Thesis Yoshinori Fujimori 1978 200 p N79-28189# Air Force Engineering and Services Center, Tyndall Avail: Univ. Microfilms Order No. 7913462 AFB, Fla. Engineering and Services Lab. Motion stability of a lifting rotor blade operating in a turbulent INTERIM FIELD PROCEDURE FOR BOMB DAMAGE flow is investigated. A new procedure is developed in which REPAIR USING CRUSHED LIMESTONE FOR CRATER use is made of the Markov process theory and numerical solution REPAIRS AND SILIKAL TRADE NAME FOR SPALL REPAIRS of the Floquet transition matrix and its eigenvalues. The basic Interim Report, Jun. 1978 - Mar. 1979 differential equations governing the flap, flap-torsion and Michael T. McNerney Apr. 1979 52 p refs flap-leadlag motions are first linearized and then converted into (AF Proj. 2104) corresponding stochastic differential equations in the sense of (AD-A068617; AFESC/ESL-TR-79-01) Avail: NTIS Ito. For simplicity, all parametric excitations are assumed to be HC A04/MF AOl CSCL 19/4 of the white noise type with constant spectral densities. The This report describes a recommended procedure for performing equations for the first and second moments are derived from repairs of large and small bomb craters using crushed stone as the Ito equations. Since both the first and second moment the repair material. The report also describes a rapid spall repair equations are differential equations with periodic coefficients, the technique using a proprietary polymer concrete product, The stability boundary in each case is found by a numerical search repair techniques are described to determine the equipment, involving the determination of the Floquet transition matrix and manpower, and time required to affect repairs. The report gives its eigenvalues. Numerical examples are given to illustrate the a brief description of the results of field tests using the crushed application of the theory. Dissert. Abstr. stone and polymer concrete techniques. GRA
N79-28190// General Accounting Office Washington, D. C. N79-28185 Ohio State Univ., Columbus. Community and Economic Development Div. THEORY, DESIGN AND EXPERIMENTAL STUDY OF AN DEVELOPING A NATIONAL AIRPORT SYSTEM: ADDITION- EDDY-CURRENT/HYDROMECHANICAL STABILITY AUG- AL CONGRESSIONAL GUIDANCE NEEDED Report to the MENTOR FOR AIRCRAFT Ph.D. Thesis Congress Gavin Dale Jenney 1979 248 p 17 Apr. 1979 75 p refs Avail: Univ. Microfilms Order No, 7915991 (PB-294082/3; CED-79-17) Avail: NTIS HC A04/MF AOl The hyd ro mechanical eddy-current coupler mechanization CSCL DIE described consists of an inertial reference, an eddy-current coupler. In the next decade, over $10 billion will be needed to and a hydraulic actuator controlled by a flapper-nozzle hydraulic develop a national airport system. Of this, about $3 billion is control stage. The inertial reference incorporates permanent needed to develop some 2,600 general aviation airports to serve magnets mounted on a support disc which is pivoted with business and pleasure flying. Additional congressional guidance instrument bearings at its geometric center. The magnets are is needed to help identify general aviation airports essential to the principal mass of the inertial reference. The calculations and a national airport system. State and local airport planning financed experimental test results used for the design of the experimental with Federal grants was to support development of the national unit are presented. The unit was tested at 80 F and -40 F fluid airport system; this has not occurred. Federal legislation should temperatures and met the objectives of providing the desired be enacted to require State and local airport plans as a prerequisite performance with less hydraulic flow. The total actuator weight for Federal airport development grants. Sufficient grant funds and size are equivalent to or less than prior mechanizations. have not been available to finance airport improvements. The Dissert. Abstr, existing method for funding such improvements has not been
584 N79-28373 effective in implementing a national airport system. The Congress N79-28329// Dow Corning Corp.. Midland, Mich. should establish priorities for distributing Federal airport develop- FASIL INTEGRAL FUEL TANK SEALANTS, PART 1 Final ment grants. GRA Report. Sep. 1977 - Sep. 1978 0. R. Pierce, K. M. Lee, K. Rossknecht. and A. H. McHaIe Jan. 1979 40 p refs N79-28232 Boeing Commercial Airplane Co.. Seattle, Wash. (Contract F33615-77-C-5139) ENVIRONMENTAL EXPOSURE EFFECTS ON COMPOSITE (AD-A067889; AFM L-TR-79-4009-Pt- 1) Avail: NTIS MATERIALS FOR COMMERCIAL AIRCRAFT HC A03/MF AOl CSCL 11/9 Daniel J. Hoffman Aug. 1978 49 p refs The Objective of this three year program is the synthesis, (Contract NAS1.15148) formulation, and evaluation of fasil (fluoroalkylarylene-siloxanylene) (NASA. CR- 158838: D6-44815-3; QPR-3) Avail: NTIS copolymers as curing and non-curing seals for fuel containment HC A03 CSCL 11 in high performance aircraft. This portion of the program was Activities reported include completion of the program design concerned primarily with the synthesis of monomers but a brief tasks, resolution of a high fiber volume problem and resumption examination of selected polymerization systems was also of specimen fabrication, fixture fabrication, and progress on the conducted. Polymers containing the silphenylene structure have analysis methodology and definition of the typical aircraft attracted the attention of a number of workers over the past environment. Program design activities including test specimens, twenty years because their thermooxidative stability is superior specimen holding fixtures, flap-track fairing tailcones, and ground to that of (Me2SiO)x. Copolymers of silphenylenes and dim- exposure racks were completed. The problem experienced in ethylpolysiloxanes were envisioned as materials possibly possess- obtaining acceptable fiber volume fraction results on two of the ing the desirable properties of both parent systems and this selected graphite epoxy material systems was resolved with an was realized to a certain extent. Thus incorporating silphenylene alteration to the bagging procedure called out in BAC 5562. units into polydimethylsiloxane decreases the tendency to split The revised bagging procedure, involving lower numbers of bleeder out cyclic oligomers in a hot environment but raises the Tg plies, produces acceptable results. All required laminates for the because silphenylene tends to be crystalline. GRA contract have now been laid up and cured. Progress in the area of analysis methodology has been centered about definition of the environment that a commercial transport aircraft undergoes. N79-28367 Technical Univ. of Denmark. Lyngby. Dept. of The selected methodology is analagous to fatigue life assess- Machine Elements. ment. A.R.H. EVALUATION OF STIFFNESS AND DAMPING COEF- FICIENTS FOR FLUID-FILM BEARINGS J. W. Lund In Shock and Vibration Inform. Center Shock and N7928235*# Rensselaer Polytechnic Inst., Troy, N. Y. Vibration Dig., Vol. 11, No. 1 Jan. 1979 p 5-10 refs COMPOSITE STRUCTURAL MATERIALS Semiannual Progress Report, Oct. 1978 - Apr. 1979 Avail: SVIC, Code 8404, Naval Research Laboratory, Washington, George S. Ansell, Robert G. Loewy. and Stephen E. Wiberly D. C. 20375; $15.00/set Jul. 1979 130 p Sponsored jointly by NASA and AFOSR Methods for calculating fluid film bearing stiffness and (Grant NGL-33-018-003( damping coefficients are briefly described. Restrictions imposed (NASA-CR-158851; SAPR-361I Avail: NTIS HC A07/MF AOl by such assumptions as linearity are evaulated. Experimental CSCL 11 methods used to obtain data necessary to determine the Technology utilization of fiber reinforced composite materials coefficients are presented. Author is discussed in the areas of physical properties, and life prediction. Programs related to the Composite Aircraft Program are described in detail. R.E.S. N79-28372# Textron Bell Aerospace Co.. New Orleans, La. AALC FAN MODEL TEST PROGRAM Final Report, 15 May 1978 - 8 May 1979 N79-28238# McDonnell Aircraft Co.. St. Louis, Mo. J. L. Allison 8 May 1979 212 p refs BOLTED FIELD REPAIR OF COMPOSITE STRUCTURES (Contract N00014-78-C-0493( Final Report, 27 Sep. 1977 - 30 Sop. 1978 (AD-A069058; Rept-7575-92703 1) Avail: NTIS James B. Watson. D. A. Glaeser, F. L. Harvey, W. T. Fukimoto. HC A10/MF AOl CSCL 13/9 and V. E. Padilla 1 Mar. 1979 212 p refs A 12-inch-diameter centrifugal fan impeller, which was a (Contract N62269-77-C-0366) model of an existing full-scale air cushion vehicle (ACV) fan (A D-A067923; MDC-A55J; NADC-77 1 09-30( Avail: NTIS impeller, was tested in five different volute configurations including HC A10/MF AOl CSCL 11/2 one which modeled another existing full-scale ACV installation. Mechanically fastened, field repairs for graphite/epoxy It was shown that the suitably scaled impeller could serve as a laminates 3/16 and 1/2 inch thick with through-the-thickness replacement for the other full-scale craft fans. Numerous velocity hole damage have been successfully demonstrated. These repairs and pressure surveys were performed. and their results are (titanium alloy patches and backing plates( were developed for discussed. GRA applcation on fuel cell composite wing surfaces and can be installed by maintenance personnel in the field using available equipment, materials, and methods. A total of 28 specimens N79-28373// Textron Bell Aerospace Co.. New Orleans, La. were fabricated and tested statically to evaluate effectiveness of A STUDY OF REQUIREMENTS, MODEL CONFIGURATIONS, selected repair designs. GRA AND TEST PLANS FOR AIR CUSHION SYSTEM COMPAR- ISON TESTS Final Report, 15 Aug. 1978 - 14 May 1979 J. Ryken 14 May 1979 40 p refs N79-28245// Naval Air Development Center, Warminster, Pa. (Contract N00014-78-C-0588) Aircraft and Crew Systems Technology Directorate. (AD-A069006; Rept-7575-953032( Avail: NTIS INFLUENCE OF JET FUEL ON PERMEATION AND FLAM- HC A03/MF AOl CSCL 13/10 MABILITY CHARACTERISTICS OF GRAPHITE EPDXY The Navy plans to test several models of air cushion vehicles COMPOSITES with different cushion systems. A set of model design requirements Lourdes C. Fuller, David A. Lutz. and Edward R. Wright 21 Feb. suitable for all the models was developed by the Navy with the 1979 26 p assistance of Bell Aerospace Textron and other contractors. The (WF41 400000( proposed DTNSRDC Model Test Program was reviewed. Minor (AD-A068586; NADC-79022-60) Avail: NTIS changes and additions were suggested. A preliminary model HC A03/MF AOl CSCL 11/4 configuration using Bell cushion philosophy was proposed. Ranges Graphite epoxy composites were subjected to controlled of bag and cushion pressures and airflows were established for studies of fuel permeation, fuel immersion and flammability in the model. Two existing model fans from an existing model of an effort to judge their safety and effectiveness as a material the AALC JEFF(B) could provide the required nominal flow and for use in jet fuel tanks. GRA pressure. Bell recommends installing four of these existing fans
585 N79-28374 to permit testing over a wide range of flows. Cost and schedule (Contract NAS3-21267: DA Proj. 11-1-62209-AH-76) estimates for the model detail design and construction were (NASA-CR- 159623: DDA-RN-79-4) Avail: NTIS prepared. The schedule is shown in this report: cost estimates HC A03/MF AOl CSCL 20D. were provided under separate cover. GRA An experimental study of the flow downstream of a T63-C20 gas turbine engine combustor was performed. Laser anemometer measurements of the mean and fluctuating velocities were made N79-28374# Aerojet Liquid Rocket Co.. Sacramento, Calif. in a combustion rig across an annulus simulating the inlet to ACV CUSHION COMPARISON TESTS: PRELIMINARY turbine. A window design suitable for similar measurements in REVIEW AND DEFINITION OF MODEL AND TESTS Final a gas turbine engine was made based on the results of this Report experiment. Insufficient numbers of naturally-occurring scattering Apr. 1979 30 p particles were present in the flow. Hollow phenolic particles (Contract N00014-78.C-0739) added to the flow provided adequate signal strength for (AD-A068888: ALRC-LCAC-2299-002) Avail: NTIS measurement. For each of the simulated engine operating HC A03/MF AOl CSCL 13/10 conditions of flight idle. 30% power and 90% power, both with The prime objective of this cushion comparison program is and without the addition of fuel, the mean velocities and turbulent to be able to obtain data on the various existing cushion systems, intensities were uniform across the annulus. The turbulent intensity that can be compared directly in the context of the amphibious was substantially unaffected by the addition of fuel but was assault mission. The use of a series of scale models, built and apparently only dependent on the inlet flow condition at a given tested to a common standard, will provide a means of obtain- power point. Little or no swirl was present in the flow at the ing basic performance data that can be compared directly. The annulus. Author model is to be a dynamically similar representation of an air cushion vehicle (ACV) designed to the requirements of the Navy's amphibious assault mission. The purpose of the model is to N79-28474# Ruhr Univ.. Bochum (West Germany). Inst. fuer provide data for the comparison of cushion systems. A linear Konstruktiven lngenieurbau. scale factor of 1/12 full scale for the model was selected. The FINITE ELEMENT METHODS FOR INVISCID AND VISCOUS features considered most important are flexible skirt that contains FLOW PROBLEMS the cushion, the lift fan system and the lift air distribution system Guenter Schmid In Von Karman Inst. for Fluid Dyn. Computational together with the general hull form. The amphibious assault lift Fluid Dyn., Vol. 1 1978 41 p refs ships, that are to carry the ACV's, impose strict limits on the major dimensions of the craft. These are to be reflected in the Avail: NTIS HC A18/MF AOl model. GRA A survey of the basic features of the finite element method is made: their applications to fluid dynamics are discussed. Compressible flow is discussed for subsonic velocities only. N79-28393# Ohio State Univ., Columbus. Electroscience Possible finite element procedures are considered for in- Lab. compressible viscous flow. In the special case of creeping flow, INFORMATION PROCESSING FOR TARGET DETECTION alternative extremum principles are available, as in the case of AND IDENTIFICATION Final Report potential flow, and simplify the derivation of finite elements. A. A. Ksienski Apr. 1979 15 p refs The various methods are listed together with their essential (Grant AF-AFOSR-261 1-74: AF Proj. 2304) boundary conditions and their natural (weak) boundary conditions. )AD-A068907: ESL-783815-8; AFOSR-79-0596TR) Avail: Graphical examples are shown. Author )ESA) NTIS HC A02/MF AOl CSCL 17/9 This report summarizes the accomplishments attained under N79-28475# British Aerospace Dynamics Group, Bristol the grant. The goal was the development of automatic target (England). Military Aircraft Div. classification techniques utilizing low frequency radar returns. THE PANEL METHOD FOR SUBSONIC AERODYNAMIC Reliable classification techniques were developed and shown to be effective for a large variety of target shapes. In particular, a FLOW: A SURVEY OF MATHEMATICAL FORMULATIONS reliable performance has been shown for aircraft identification, AND NUMERICAL MODELS WITH AN OUTLINE OF THE where eight classes of combat planes, both American and foreign NEW BRITISH AEROSPACE SCHEME made, were tested. The problem of classifying an object as B. Hunt In Von Karman Inst. for Fluid Dyn. Computational belonging or not belonging to a specified catalogue of classes Fluid Dyn., Vol. 1 1978 70 p refs was successfully solved and a simple and reliable implementation was devised. GRA Avail: NTIS HC A18/MF AOl A comprehensive description of the mathematical foundation of panel methods is given. An explanation, of the basic errors N79-28419# ORI, Inc., Silver Spring, Md. inherent in most schemes, but manifested most dramatically for ADVANCED RISK ASSESSMENT OF THE EFFECTS OF first order schemes employing an internal vortex lattice, is offered. GRAPHITE FIBERS ON ELECTRONIC AND ELECTRIC The observation of Certain guidelines makes it possible for first EQUIPMENT, PHASE 1 Final Report order schemes to compare with the accuracy of higher order Leon S. Pocinki, Lawrence D. Kaplan, Merrill E. Cornell, and schemes, Present Capabilities and current developments are Reynold Greenstone May 1979 217 p refs discussed. Least squares minimisation of source/vortex pseudo (Contract NAS1-1 5379) error on wing-type components is presented as an appendix. (NASA-CR-159027) Avail: NTIS HC A1O/MF AOl CSCL Author (ESA) 09C A model was developed to generate quantitative estimates N79-28477# Institut de Recherche d'lnformatique et d'Automat- of the risk associated with the release of graphite fibers during isme, Roquencourt (France). fires involving commercial aircraft constructed with graphite fiber APPLICATION OF A FINITE ELEMENT METHOD TO composite materials. The model was used to estimate the risk TRANSONIC FLOW PROBLEMS USING AN OPTIMAL associated with accidents at several U.S. airports. These results CONTROL APPROACH were then combined to provide an estimate of the total risk to M. 0. Bristeau In Von Karman Inst. for Fluid Dyn. Computational the nation. A.R.H. Fluid Dyn., Vol. 1 1978 50 p refs Sponsored by Direction des Rech. et Etudes Tech. N7928456*# Detroit Diesel Allison, Indianapolis, Ind. Avail: NTIS HC A18/MF AOl LASER ANEMOMETER MEASUREMENTS AT THE EXIT OF The least squares method is introduced as a general technique A T63-C20 COMBUSTOR Final Report, Sep. 1978 - Apr. for solving nonlinear equations. The complexity of the geometries 1979 appearing in realistic applications of transonic equations entails D. B. Zimmerman Apr. 1979 44 p refs Sponsored in part the use of the finite element method as it is well suited to the by Army Research and Develop. Command. Cleveland discretization of these problems. The results obtained for nonlifting
586 N79-28565 and lifting bodies show the validity of the method. Improvements the velocity field, that is boundary surface, viscosity, and are needed to reduce the computing time and some suggestions compressibility of the fluid. Graphic examples of applications to this end are made. Author (ESA) are given. ESA N79-28560# Office National d'Etudes et de Recherches N79-28482# British Aerospace Dynamics Group. Bristol Aerospatiales. Paris (France). (England). UNSTABLE FLOW REGIMES, INCLUDING ROTATING THE COMPUTATION OF VORTEX FLOWS BY PANEL STALL SURGE, DISTORTIONS, ETC. METHODS J. Fabri In Von Karman Inst. for Fluid Dyn. Off-Design In Von Karman Inst. for Fluid Dyn. Computational S. A. Jepps Performance of Gas Turbines. Vol. 1 1978 22 p refs Fluid Dyn., Vol. 2 1978 39 p refs Sponsored in part by Mm. of Defence Avail: NTIS I-IC A15/MF AOl Avail: NTIS HC A14/MF AOl A time dependent model of the response of the total flow Use of panel methods to calculate flows in which vorticity to the aerodynamic solicitations at conditions favorable for the exists in the body of the fluid is discussed. Calculation of the onset of stall was analyzed. Simplified special cases are discussed. vortex wake behind a lifting wing is described. The more difficult Theory and experiment compare accurately in some limited cases. problem of computing free vortices which interact strongly with The main difficulties appear when the perturbations are not of a nearly solid surfaces is then considered. A hybrid technique limited amplitude, when the hub-to-tip ratio of the compressor combining a three-dimensional attached flow method with a becomes small, and when compressibility effects have to be slender body separated flow method is discussed using a delta taken into account. Author (ESA) wing as an example. Author (ESA) N79-28561# Rolls-Royce Ltd., Bristol (England). N79-28555# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- AXIAL TURBINE PERFORMANCE PREDICTION Genese (Belgium). R. J. Latimer In Von Karman Inst. for Fluid Dyn. Off-Design OFF-DESIGN PERFORMANCE OF GAS TURBINES, Performance of Gas Turbines, Vol. 1 1978 119 p VOLUME 1 1978 349 p refs Lectures held at Rhode-Saint-Genese. Belgium. Avail: NTIS HC A15/MF AOl 30 Jan. - 3 Feb. 1978 2 Vol. Turbine off-design behavior and performance predictions are )VKI-Lec-Ser- 1978-2-Vol-i) Avail: NTIS HC Al 5/MF AOl reviewed. Actual turbine behavior is covered showing test results The off-design performance of gas turbines is discussed in from which a generalized pattern results. Difficulties predicting a series of lectures. Reviews of numerical analysis methods, the off-design behavior are shown by the multiplicity of methods computerized methods, stalling performance prediction, influence that have been published. Design point prediction methods of particular variables, etc., are included. including possible developments are discussed in detail. The effect of design point and off-design prediction methods on design criteria is commented on. A further problem, that it will probably N79-28556# Societe Nationals d'Etude at de Construction de be necessary to consider the precise blade shape and not just Moteurs d'Aviation, Villaroche (France). its overall parameters, is also mentioned. A method of performance THE IMPORTANCE OF OFF-DESIGN OPERATION estimation for axial flow turbines is presented as an appendix. Roger P. Bouillet In Von Karman Inst. for Fluid Dyn. Off-Design Author (ESA) Performance of Gas Turbines, Vol. 1 1978 39 p Avail: NTIS HC A15/MF AOl N79-28563# Brown, Boveri and Co., Ltd., Baden (Switzerland). Contributing factors, component performance prediction A GAS TURBINE OFF-DESIGN COMPUTING SYSTEM methods, and overall performance prediction methods are Utz Klingenboeck and Axel vonRappard In Von Karman Inst. reviewed. It is concluded that prediction of off-design performance for Fluid Dyn. Off-Design Performance of Gas Turbines, Vol. 2 is essential and that it must cover both steady and transient 1978 94 p refs running performance. Author (ESA) Avail: NTIS NC A10/MF AOl A program for the design of gas turbine plants is described. The program was written for an IBM 370/618 computer using N79-28557# Von Karman Inst. for Fluid Dynamics, Rhode-Saint- FORTRAN 4 language. 450 KB program length, punched cards Genese (Belgium). input, and print-out output. Program requirements and basic THE PREDICTION OF COMPRESSOR BLADE ROW concepts are explained. The calculation method is discussed In PERFORMANCE: NUMERICAL METHODS AND THEORETI- detail. Input and output specifications are considered. Aerodynamic CAL APPROACHES characteristics taken into consideration by the computer procedure R. vandenBraembussche In its Off-Design Performance of Gas are discussed. An.example is presented. Author (ESA) Turbines, Vol. 1 1978 93 p refs N79-28564# Gutehoffnungshuette Sterkrade A .G. (West Avail: NTIS NC A15/MF AOl Germany). The present status of prediction methods for fluid mechanics CONTRIBUTION TO THE CALCULATION OF THE DYNAMIC in turbomachines is reviewed. The substitution of analytical BEHAVIOR OF INDUSTRIAL TURBOCOMPRESSOR methods by numerical methods applicable to more complex CIRCUITS geometries is discussed. Author )ESA) Heinrich Voss In Von Karman Inst. for Fluid Dyn. Off-Design Performance of Gas Turbines, Vol. 2 1978 34 p refs N79-28558# Brown, Boveri and Co., Ltd., Baden (Switzerland). A THREE DIMENSIONAL FLOW COMPUTING SYSTEM Avail: NTIS HC A10/M AOl APPLICABLE TO AXIAL AND RADIAL FLOW TUR- Acalculation method was developed which can predict the BOMACHINES required turbocompressor Circuits performance from data on the M. Ribaut In Von Karman Inst. for Fluid Dyn. Off-Design various individual components. The method is based on a Performance of Gas Turbines, Vol. 1 1978 44 p refs components indexing system which, after numeric editing of the plant to be investigated, forms a circuit matrix. The program Avail: NTIS NC A15/MF AOl Contains a . set of indexed components which are treated by a The justification for and application to examples of a processing computer using digital programming techniques. Initial potential method are presented. Current interest in the method Comparison of precalculations and measurements indicate due to its simplicity and accuracy is noted. Calculations are agreement. Two examples are presented. Author )ESA) described including the calculation of the velocity field on a surface of revolution, the calculation of an axisymmetric solution, N79-28565# Ateliers de Constructions Electriques de Charleroi and the description of the effects of the three variables describing (Belgium).
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PROBLEMS INVOLVED IN STARTING AND SHUTDOWN the synthesis of an active flutter-suppression control law for an OF GAS TURBINES: THERMODYNAMIC AND MECHANI- aeroelastic wind-tunnel model. It is shown that the resulting CAL ASPECTS control law suppresses flutter over a wide range of subsonic J.-L. Guiette and Albert VanGucht In Von Karman Inst. for Mach numbers. This is a promising method for synthesizing Fluid Dyn. Off-Design Performance of Gas Turbines, Vol. 2 practical control laws using the results of optimal control 1978 95 p refs theory. A.R.H. Avail: NTIS NC A10/MF AOl A calculation method for the transient performances of the N79-28620# Lockheed-Georgia Co.. Marietta. turbine and compressor is given and the assumptions are pointed INVESTIGATION OF STRESS-STRAIN HISTORY MODELING out. Although simplifications are introduced, the work involved AT STRESS RISERS, PHASE 2 Final Report, 15 Feb. in determining start up and shutdown characteristics is consider- 1977 - 30 Sep. 1978 able. Differences occur between measured and calculated data. James R. Carroll, R. L. Brugh. and W. Wilkinson Dec. 1978 but they can be explained by the simplifications made. The 261 p refs accuracy of the calculation method is considered satisfactory. (Contract F33615-75-C-3078) Author (ESA) (AO-A069162; LG78ER240; AFFOL-TR-78-167( Avail: NTIS NC Al2/MF AOl CSCLO1/3 N79-28567# National Engineering Lab., East Kilbride (Scotland). An analytical and experimental study of the stress and strain Fluid Mechanics Div. history at stress risers was conducted to evaluate the effects of PUMP DESIGN time- and cycle-dependent changes on the fatigue life of I. S. Pearsall In Von Karman Inst. for Fluid Dyn. Off-Design aluminum alloy structures. This report covers Phase II of a Performance of Pumps. Vol. 1 1978 14 p two-phase program. Both creep and stress relaxation were modeled and measured. An elastic-plastic finite element code Avail: NTIS HC A22/MF AOl simulation was utilized to model the nonlinear stress-strain field The isolated airfoil method with corrections for blade around the stress riser and to model creep sustained load hold periods. A four-part experimental program was conducted to interference, the cascade method, and the actuator disks method are reviewed. Formulas are developed and limitations and generate constitutive data necessary for the formulation of a hysteresis analysis model. The experimental program included restrictions are explained. Author (ESA) simple coupon specimens, a unique simplified stress concentration specimen, center circularly notched super-scale specimens, and N79-28568# National Engineering Lab., East Kilbride (Scotland). notched fatigue specimens. Significant creep and stress relaxation A COMPUTER-AIDED DESIGN METHOD FOR AXIAL FLOW was measured during the experimental program. These data were PUMPS AND FANS used in the development of a creep/stress relaxation module J. E. Hesselgreaves and 0. McEwan In Von Karman Inst. for for the hysteresis analysis. The automated hysteresis analysis Fluid Dyn. Off-Design Performance of Pumps. Vol. 1 1978 developed during this program includes a material hardening/ 40 p refs softening module, a creep/stress relaxation module, locus and Avail: NTIS HC A22/MF AOl branch curve definition for the stable material response, and a Programs for the design of axial flow pumps and fans with damage accumulation module. Correlation studies have been or without stator rows are described. Controlled variation of conducted using this analysis as well as a linear damage spanwise loading is incorporated into the method which is valuable analysis method to compare predicted versus actual specimen where special design requirements are to be met. The methods life. GRA of analysis are described together with the organization of the programs. Some numerical results are given together with supporting experimental evidence. Author IESAI N7928796* # National Aeronautics and Space Administration. Langley Research Center, Hampton, Va EFFECTS OF ROAD TRAFFIC BACIGROUND NOISE ON N79-28574# Worthington Pump International, Inc.. Desio (Italy). JUDGMENTS OF INDIVIDUAL AIRPLANE NOISES PREROTATION IN CENTRIFUGAl. PUMPS: DESIGN Ph.D. Thesis CRITERIA Clemans A. Powell Jul. 1979 44 p refs A. Janigro and B. Schiavello In Von Karmen Inst. for Fluid (NASA-TP-1433; L-12651) Avail: NTIS HC A03/MF AOl Dyn. Off-Design Performance of Pumps. Vol. 1. 1978 100 p CSCL 138 refs Two laboratory experiments were conducted to investigate Avail: NTIS HC A22/MF AOl the effects of road-traffic background noise on judgments of After a survey of the literature complemented by flow individual airplane flyover noises. In the first experiment, visualization and flow measurement tests, a qualitative scheme 27 subjects judged a set of 16 airplane flyover noises in the was conceived for the Interpretation of the main phenomena presence of traffic-noise sessions of 30-min duration consisting related to separation, backflow. and prerotation in centrifugal of the combinations of 3 traffic-noise types and 3 noise levels. pumps. An identical sequence, separation-backflow-rotation, In the second experiment. 24 subjects judged the same airplane develops at part capacities in centrifugal, mixed, and axial rotors. flyover noises in the presence of traffic-noise sessions of 10-mm Onset of these phenomena is discussed and related to pump duration consisting of the combinations of 2 traffic-noise types design as well as operation characteristics. Author (ESA) and 4 noise levels. In both experiments the airplane noises were judged less annoying in the presence of high traffic-noise levels than in the presence of low traffic-noise levels. Author N79'28614t # National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. A METHOD FOR OBTAINING PRACTICAL FLUTTER- N79-28848# National Aviation Facilities Experimental Center, SUPPRESSION CONTROL LAWS USING RESULTS OF Atlantic City, N. J. OPTIMAL CONTROL THEORY THE ANALYSIS OF NATIONAL TRANSPORTATION SAFETY Jerry R. Newson Aug. 1979 34 p refs BOARD SMALL SINGLE-ENGINE FIXED-WING AIRCRAFT (NASA-TP-1471; L-12728l Avail: NTIS HC A03/MF AOl ACCIDENT/INCIDENT REPORTS FOR THE POTENTIAL CSCL 20K PRESENCE OF LOW-LEVEL WIND SHEAR Final Report The results of optimal control theory are used to synthesize Jack J. Shrager May 1979 78 p refs a feedback filter. The feedback filter is used to force the Output (AD-A069438; FAA-RD-79-3: FAA-NA-78-39) Avail: NTIS of the filtered frequency response to match that of a desired NC A05/MF AOl CSCL 04/2 optimal frequency response over a finite frequency range. This The National Transportation Safety Board aircraft accident/ matching is accomplished by employing a nonlinear programing incident data base covering the years 1964 through 1975 was algorithm to search for the coefficients of the feedback filter screened to select those accidents involving single-engine aircraft that minimize the error between the optimal frequency response of less than 12.500 pounds gross weight in which the potential and the filtered frequency response. The method is applied to of low-level wind shear as a factor could not be discounted.
588 N79-29141
The software filtering resulted in identifying 2.469 small Washington GPO 1979 427 p refs Hearing on H.R. 1786 single-engine aircraft accident briefs which met the criteria for before the Comm. on Sci. and Technol.. 96th Congr., 1st Sess.. the possible presence of wind shear. A review of these briefs 6 Feb. 1979 for the years 1964 through 1973 (excluding 1970. 1971. 1974. (GPO-46-134) Avail: Comm. on Sci. and Technol. and 1975) further reduced this number to 304. which comprised The President's budget for NASA is reviewed in the light of the final data base used in this analysis. The presence of a his civilian space policy and its impact on NASA programs. low-level wind shear was a distinct possibility in 71 of these Major activities of FY 1980 highlighted include the space takeoff, approach. or landing accidents. Of this number. 48 involved transportation system, space sciences, space and terrestrial mechanically (orographic or topographic) induced shears. In 23 applications, aeronautics and space technology, space tracking of the cases, thunderstorms were reported or observed close to and data systems. Construction of facilities, research and program the aircraft flightpath. Author management, and international programs. The budget request is considered to comprise a sound, balanced aeronautics and space National Aeronautics and Space Administration. program, given the constraints of the national anti-inflational N7928982*# effort. It supports the continued development of the space Langley Research Center, Hampton, Va. transportation system, meets commitments made in the past. JET NOISE AND PERFORMANCE COMPARISON STUDY maintains progress in ongoing programs. and provides for flexibility OF A MACH 2.55 SUPERSONIC CRUISE AIRCRAFT A.R.H. V. R. Mascitti and D. J. Maglieri Jun. 1979 24 p refs in future programs. (NASA-TM-80094) Avail: NTIS HC A02/MF AOl CSCL National Aeronautics and Space Administration, 20A N79-291 0811 Data provided by the manufacturer relating to noise and Washington, D. C. performance of a Mach 2.55 supersonic cruise concept employing SPINOFF 1979 Annual Report a post 1985 technology level, variable cycle engine was used James J. Haggerty Feb. 1979 118 p Original contains color to identify diferences in noise levels and performance between illustrations the manfacturer and NASA associated with methodology and )NASA-TM-80481) Avail: NTIS MF AOl; SOD HC $4.25 CSCL groundrules. In addition, economic and noise information is 05A provided consistent with a previous study based on an advanced NASA's current mainline programs which are producing public technology Mach 2.7 configuration. The results indicate that the benefit through direct application of technology and, at the same difference between the NASA's and manfacturer's performance time, are generating new technology which may find secondary methodology is small. Resizing the aircraft to NASA groundrules application in the future are summarized. A representative sampling also results in small changes in flyover, sideline and approach of spinoff products and processes derived from NASA technology noise levels. For the power setting chosen, engine oversizing and employed in various avenues of everyday life is included. resulted in no reduction in traded noise. In terms of summated The mechanisms of the technology transfer process, including noise level, a 10 EPNdB reduction is realized for an 8 percent the means by which NASA seeks to stimulate technology increase in total operating costs. This corresponds to an average utilization are described as well as NASA's activities in assist- noise reduction of 3.3 EPNdB at the three observer positions. ing agencies interested in exploiting the benefit potential of satellite A.R.H. remote sensing technology. A. R. H. N79-29138# Dayton Univ. Research Inst., Ohio. N79.28984*# Massachusetts Inst. of Tech.. Cambridge. Fluid PREDICTED CRACK REPAIR COSTS FOR AIRCRAFT Dynamics Research Lab. STRUCTURES Final Technical Report, Jun. 1977 - Sep. EXPERIMENTAL AND THEORETICAL STUDIES ON MODEL 1978 HELICOPTER ROTOR NOISE Interim Report, Mar. 1978 - Alan P. Berens Nov. 1978 83 p refs Dec. 1977 (Contract F33615-77-C-0800) Krishnaswamy S. Aravamudan and Wesley L. Harris Jan. 1978 )AD-A068699; ASD-TR-78-39) Avail: NTIS 158 p refs Submitted for publication HC A05/MF AOl CSCL 01/3 (Grant NsG-2095; Contract DAAG29-76-C-0027) This report presents the results of a study designed to (NASA-CR- 158844: AD-A068180; ARO- 12931 .2-EX; (1) prepare a computer program for use in predicting expected Rept-83852-1; Rept-78-1) Avail: NTIS HC A08/MF AOl CSCL repair costs of the cracks which develop during the operational 20/1 usage of a structure; (2) to provide a document which describes A simplified Mach number scaling law is obtained for rotational the use of the computer program and guides a potential user in and broadband noise components of a model helicopter rotor. the specification of the required input: and (3) to use data which The broadband noise sources are further classified into low is reasonably representative of Air Force experience as input for frequency and high frequency components. The scaling laws are use in determining the sensitivity of expected maintenance costs based on the geometric and performance parameters of the rotor to variations in input. Results are provided which compare and characteristics of the flow field. The existing theory of Lowson expected costs for changes in inspection intervals, quality of and 011erhead is used deriving the conventional sixth power law inspection, quality of repair, operational usage, and equivalent for the rotational noise of geometrically similar blades operating initial flaw size distributions. . GRA in similar flow environments. The knowledge of unsteady aerodynamics was exploited to yield analytical formulation for N7929141*# National Aeronautics and Space Administration. the low frequency broadband radiation. The ambiguous state of Langley Research Center, Hampton, Va. the art regarding the origin and nature of high frequency broadband A COMPUTER PROGRAM FOR DETAILED ANALYSIS OF noise does not permit such a straightforward scaling law for THE TAKEOFF AND APPROACH PERFORMANCE CAPA- this frequency regime. Vortices are assumed to be shed at unknown BILITIES OF TRANSPORT CATEGORY AIRCRAFT Strouhal frequency and the scaling law is derived by simply Willard E. Foss, Jr. Jun. 1979 38 p refs integrating the blade sectional velocity over the span. The MIT )NASA-TM-80120( Avail: NTIS HC A03/MF AOl CSCL 5 x 7-1/2 foot anechoic wind tunnel was used to perform O1A experiments at controlled flow environ. Turbulence was generated The takeoff and approarch performance of an aircraft is at the inlet of the tunnel and simultaneous measurements of calculated in accordance with the airworthiness standards of the acoustic and turbulence signals were made. The experimentally Federal Aviation Regulations. The aircraft and flight constraints obtained results are compared with the computed intensities are represented in sufficient detail to permit realistic sensitivity and spectra of rotational noise, low frequency broadband noise studies in terms of either configuration modifications or changes and high frequency broadband noise from model rotors. GRA in operational procedures. The program may be used to investigate advanced operational procedures for noise alleviation such as programmed throttle and flap controls. Extensive profile time N79-29105# Committee on Science and Technology (U. S. history data is generated and is placed on an interface file which House). can be input directly to the NASA aircraft noise prediction program NASA AUTHORIZATION, 1980, VOLUME 1, PART 2 (ANOPP). A.R.H.
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N7929143*// National Aeronautics and Space Administration. N79-29149fl ARO, Inc.. Arnold Air Force Station, Tenn. Lewis Research Center, Cleveland, Ohio. WING/STORE FLOW-FIELD MEASUREMENTS AT TRAN- RECENT APPLICATIONS OF THEORETICAL ANALYSIS TO SONIC SPEEDS USING A LASER VELOCIMETER Final V/STOL INLET DESIGN - Report, 18 Apr. 1977 - 30 Sep. 1978 Norbert 0. Stockman 1979 18 p refs Presented at Workshop F. L. Heltsley and V. A. Cline AEDC Apr. 1979 62 p refs on V/STOL Aerodyn.. Monterey, Calif. 16-18 May 1979; (AD-A068328; AEDC-TR-79-5) Avail: NTIS Sponsored by Naval Air Develop. Center HC A04/MF AOl CSCL 01/3 (NASA-TM-7921 1; E-096) Avail: NTIS HC A02/MF AOl CSCL A test was conducted in the AEDC Aerodynamic Wind Tunnel O1A OT) of the Propulsion Wind Tunnel Facility (PWT) to measure The theoretical analysis methods, potential flow, and boundary the flow fields about 5-percent models of several wing/store layer, used at Lewis are described. Recent application to Navy configurations. Test models included a wall-mounted swept wing V/STOL aircraft, both fixed and tilt nacelle configurations, are and MK-83 and M1 17 stores. Flow-field velocity measurements, presented. A three dimensional inlet analysis computer program made using a 2-component laser velocimeter, are presented is described and preliminary results presented. An approach to together with model surface pressures and shadowgraphs. GRA Optimum design of inlets for high angle of attack operations is dicussed. M.M.M. N79-29150# Goodyear Aerospace Corp.. Akron, Ohio. GOODYEAR AEROSPACE CONCEPTUAL DESIGN MARI- N79,29144*# National Aeronautics and Space Administration. TIME PATROL AIRSHIP ZP3G Final Report Ames Research Center, Moffett Field. Calif. N. D. Brown 1 Apr, 1979 65 p refs AERODYNAMIC CHARACTERISTICS OF A LARGE-SCALE (Contract N62269-78-M-4580( SEMISPAN MODEL WITH A SWEPT WING AND AN (AD-A068449; GER- 16607; NADC-780-75 . 60) Avail: NTIS AUGMENTED JET FLAP WITH HYPERMIXING NOZZLES HC A04/MF AOl CSCL 01/3 Thomas N. Aiken, Michael D. Falarski, and David G. Koenin A conceptual design of a modern technology airship with Jul. 1979 87 p refs precision hover capability for use in maritime patrol is described. (NASA-TM-73236: A-7013) Avail: NTIS HC A05/MF AOl The size and major characteristics are established by a series of CSCL O1A United States Coast Guard missions set forth by the contracting The aerodynamic characteristics of the augmentor wing agency. GRA concept with hypermising primary nozzles were investigated. A N79-29152# Sandia Labs., Albuquerque, N. Max. large-scale semispan model in the Ames 40- by 80-Foot Wind REAL-TIME ESTIMATION OF AERODYNAMIC COEF- Tunnel and Static Test Facility was used. The trailing edge, FICIENTS BY MEANS OF AN EXTENDED KALMAN augmentor flap system occupied 65% of the span and consisted FILTER of two fixed pivot flaps. The nozzle system consisted of J. R. Kelsey Feb. 1979 156 refs hypermixing. lobe primary nozzles, and BLC slot nozzles at the p (Contract EY-76-C-04-0789( forward inlet, both sides and ends of the throat, and at the aft (SAND-78-2032) Avail: NTIS HC A08/MF AOl flap The entire wing leading edge was fitted with a 10% chord A technique for estimation of the aerodynamic parameters slat and a blowing slot. Outboard of the flap was a blown of a flight vehicle from onboard measurements is presented. An aileron. The model was tested statically and at forward speed. extended Kalman filter is used to extract the parameters in the Primary parameters and their ranges included angle of attack presence of measurement noise and initial uncertainty of the from -12 to 32 degrees, flap angles of 20, 30, 45, 60 and parameter values. Computer generated data were used for the 70 degrees, and deflection and diffuser area ratios from 1.16 measurement information in lieu of actual flight data. Several to 2.22. Thrust coefficients ranged from 0 to 2.73, while nozzle state models of varying complexity were studied in an attempt pressure ratios varied from 1.0 to 2.34. Reynolds number per to find a model which yields adequate estimates while mini- foot varied from 0 to 1.4 million. Analysis of the data indicated mizing the required computation time. a maximum static, gross augmentation of 1.53 at a flap angle DOE of 45 degrees. Analysis also indicated that the configuration N79-29154# Royal Aircraft Establishment. Farnborough was an efficient powered lift device and that the net thrust was (England). Aerodynamics Dept. comparable with augmentor wings of similar static performance. AN EXTENSION TO THE METHOD OF GARABEDIAN AND Performance at forward speed was best at a diffuser area ratio KORN FOR THE CALCULATION OF TRANSONIC FLOW of 1.37. K.L. PAST AN AEROFOIL TO INCLUDE THE EFFECTS OF A BOUNDARY LAYER AND WAKE M. R. Collyer Jul. 1978 93 p .refs Previously announced as RAE-TR-77104; ARC-37680 N79,29146*# National Aeronautics and Space Administration. )ARC-R/M-3828; BR66513( Avail: NTIS HC A05/MF AOl; Langley Research Center, Hampton, Va. HMSO £8 AN EXPERIMENTAL AND THEORETICAL INVESTIGATION A numerical method was developed for calculating com- OF THE EFFECT OF NONMETRIC OVER-THE-WING pressible lincluding transonic) 110w past a single airfoil witfl an NACELLES ON WING-BODY AERODYNAMICS allowance for viscous effects, providing that the boundary layer David E. Reubush Aug. 1979 79 p refs is fully attached over the airfoil surface. This method was developed (NASA-TP . 1503; L-13010( Avail: NTIS HC A05/MF AOl by combining an iterative scheme for the inviscid flow, originally CSCL O1A established by Garabedian and Korn, with an integral method Draa reduction benefits due to blowing the jet exhausts (the lag entrainment method of Green et all for the calculation over the wing for a transport-type wing-body configuration were of compressible turbulent boundary layers. The inviscid scheme investigated in the Langley 16-foot transonic tunnel. A combination was modified to incorporate a boundary condition on the airfoil of a wing-body model and a powered-nacelle test rig was tested surface, which is imposed on the velocity normal to the surface, at Mach numbers of 0.50 and 0.80 at angles of attack from with a corresponding boundary condition for the wake. Wake -2 degrees to 4 degrees and jet total-pressure ratios from jet curvature effects are also included. An iterative procedure is off to 3 or 4 (depending on Mach number) for a variety of established, which iterates between successive calculations of nacelle locations relative to the wing. The experimental results the pressure distribution and of the displacement thickness of were compared with the predictions obtained from several the boundary layer and wake. Results are presented from a theoretical techniques. It was concluded that positioning of the computer program (VG K) and comparisons are made with nacelles (nonmetric) can have large effects on the wing-body experimental measurements and other theoretical results. drag. Some positions yielded higher drag than the baseline Author (ESA) position, whereas others yielded lower drag than the baseline position. The theoretical method which utilized a quasi-vortex- N79. 29155# Cambridge Univ. (England). Dept. of Engineer- lattice for the wing and wing-jet interaction in combination with ing. a let entrainment model gave generally reasonable predictions THE AERODYNAMIC NOISE OF A SLOT IN AN AERO- of the drag increments. M.M.M. FOIL
590 N79-29161
M. S. Howe Aug. 1977 45 p refs Previously announced as aircraft's full aerodynamic capability was used, collision with RAE-TR-77 129; ARC-37794 obstacles probably could have been avoided. S.E.S. (ARC-R/M-3830; BR66512) Avail: NTIS HC A03/MF AOl A theoretical investigation of the noise generated when N79-29159# National Transportation Safety Board, Washington, turbulence interacts with a slot between a wing and a flap is D. C. described. The slot is modeled by the region between two AIRCRAFT ACCIDENT REPORT: UNITED AIRLINES, INC.. overlapping, semi-infinite rigid planes representing the wing and DOUGLAS DC-8-54, N8047U NEAR KAYSVILLE, UTAH, flap. Sound is produced when turbulence convects above, below 18 DECEMBER 1977 or through the slot. The analysis determines the dependances 27 Jul. 1978 48 p of the radiated sound on the characteristics turbulence velocity. (NTSB-AAR-78-8) Avail: NTIS HC A03/MF AOl the effect of forward flight on the field shape, and properties of About 0138 mat, on December 18. 1977. a United Airlines, the field radiated to the side of the aircraft flight path. Results Inc.. DC-8F-54 cargo aircraft, operating as Flight 2860. crashed indicate that above-the-wing-turbulence generates a monopole into a mountain in the Wasatch Range near Kaysville. Utah. field in the flyover plane which is amplified in forward flight. The three flightcrew members, the only persons aboard the aircraft, For acoustic frequencies less than half that of the lowest resonant were killed. and the aircraft was destroyed. Flight 2860 frequency of the slot the radiation is that of a monopole source encountered electrical system problems during its descent and whose intensity varies. Sideline noise exhibits dipole characteristics approach to the Salt Lake City Airport. The flight requested a except at frequencies less than half the lowest resonance frequency holding clearance which was given by the approach controller of the slot, or at high sideline angles. Author (ESA) and accepted by the flightcrew. The flight then requested and received clearance to leave the approach control frequency for N79-29156# Aerospace Engineering Test Establishment. Cold a little minute to communicate with company maintenance. Lake (Alberta). Flight 2860 was absent from the approach control frequency CH-113 CRASH POSITION INDICATOR FLIGHT TRIALS for about 7 1/2 minutes. During that time, the flight entered K. D. Nelson 5 Mar. 1979 35 p • refs Original contains color an area near hazardous terrain. The approach controller recognized illustrations Flight 2860's predicament but was unable to contact the flight. )AETE-78/39) Avail: NTIS HC A03/MF AOl When Flight 2860 returned to approach control frequency, the Tests were performed on the crash position indicator (CPI) controller told the flight that it was too close to terrain on its installed on a CF CH-113 Labrador aircraft to determine the right and to make a left turn. After the controller repeated the safe deployment envelope and the effect of CPI fitment on the instructions, the flight began a left turn and about 15 seconds flying qualities of the CH- 113. The tuft predictions of CPI airfoil later the controller told the flight to climb immediately to separation and trajectory were validated. Author 8.000 feet. Eleven seconds later, the flight reported that it was climbing from 6.000 feet to 8,000 feet. The flight crashed into N79-29157# National Transportation Safety Board, Washington, a 7.665-foot mountain near the 7.200-foot level. The National D. C. Transportation Safety Board determines that the probable cause AIRCRAFT ACCIDENT REPORT: ROCKY MOUNTAIN of this accident was the approach controller's issuance and the AIRWAYS, INC., DEHAVILLAND DHC-6-300, N24RM, flightcrew's acceptance of an incomplete and ambiguous CHEYENNE, WYOMING, 27 FEBRUARY 1979 holding clearance in combination with the flightcrew's failure to 19 Jul. 1979 30 p adhere to prescribed impairment-of-communications procedures (NTSB . AAR-79-10) Avail: NTIS HC A03/MF AOl and prescribed holding procedures. The controller's and flightcrew's About 0807 mountain standard time. Rocky Mountain actions are attributed to probable habits of imprecise communica- Airways, Inc., Flight 801, crashed into rolling terrain shortly after tion and of imprecise adherence to precedures developed through takeoff in visual flight conditions from runway 34 at Cheyenne years of exposure to operations in a radar environment. Municipal Airport, Wyoming. The aircraft came to rest about Contributing to the accident was the failure of the aircraft's No. 1.3 nmi east of the departure end of the runway. There were 1 electrical system for unknown reasons. Author 14 passengers and a crew of 2 aboard: 2 passengers were injured slightly. The aircraft was damaged substantially. The N79-29160# National Transportation Safety Board. Washington, D. C. National Transportation Safety Board determined that the probable cause of the accident was the flightcrew's erroneous determination AIRCRAFT ACCIDENT REPORT: ALASKA AERONAUTICAL that the aircraft was not capable of single-engine flight and INDUSTRIES, INC.. DEHAVILLAND DHC-6-200, N563MA, their actions which precluded obtaining maximum available NEAR ILIAMNA, ALASKA, 6 SEPTEMBER 1977 4 May 1978 31 p performance from the aircraft. The cause of the engine failure (NTSB-78-5) Avail: NTIS HC A03/MF AOl was an erroneous assessment by company maintenance personnel of damage sustained by the right engine during an overtemperature On September 6. 1977, Alaska Aeronautical Industries, Inc. condition and their poor judgment in deciding to repair and Flight 302 crashed into a glacier on the southwest side of Mt. release the engine for flight without replacing the engine's power Iliamna, Alaska, about 7,000 feet above mean sea level. The aircraft crashed in level flight in instrument meteorological turbine section. Author conditions while en rouge from Iliamna. Alaska, to Anchorage. Alaska. There were two crewmenbers and eleven passengers N79-29158fl National Transportation Safety Board, Washington, aboard the aircraft; there were no survivors. The aircraft was D. C. destroyed. Because of the rapidly changing environmental AIRCRAFT ACCIDENT REPORT: CONTINENTAL AIRLINES, conditions on the glacier face, recovery of bodies or wreckage INC.. BOEING 727-224, N32725, TUCSON, ARIZONA, was not possible. The National Transportation Safety Board has 3 JUNE 1977 determined that the probable cause of the accident was the 1 Aug. 1978 43 p refs failure of the flightcrew to use proper navigational procedures )NTSB-AAR-78 . 9) Avail: NTIS HC A03/MF AOl for the route to be flown, especially their failure to use the The aircraft was damaged substantially after striking the available backup means of navigation to verify the position and powerlines and utility poles, which were located about 130 feet the progress of the flight. Author to the left of the runway centerline and about 710 feet from the departure end of the runway. The aircraft was landed safely N79-29161// National Transportation Safety Board, Washington, at the Tucson Airport; there were no injuries, The National D. C. Transportation Safety Board determines that the probable cause AIRCRAFT ACCIDENT REPORT: NATIONAL JET SERVICES, of the accident was the captain's decision to take off under INC.. DOUGLAS DC-3, N51071. EVANSVILLE DRESS evident hazardous wind conditions which resulted in an encounter REGIONAL AIRPORT, INDIANA, 13 DECEMBER 1977 with severe wind shear and subsequent collision with obstacles 17 Aug. 1978 52 p refs in the takeoff path. The rate of climb of the aircraft in these )NTSB-AAR-78-10) Avail: NTIS HC A04/MF AOl conditions 'when flown according to prescribed operating Results of an aircraft accident investigation of a Douglas procedures was not sufficient to clear the obstacles. If the DC-3, operated as a passenger charter flight to transport the
591 N79-29162
University of Evansville basketball team and associated personnel with a high intensity anti-collision strobe light, a crash position from Evansville, Indiana. to Nashville. Tennessee are reported. indicator, and Omega Navigation system in order to (1) identify The probable cause of the accident was an attempted takeoff the cause of EMI problems detected during category 1 tests; with the rudder and right aileron control locks installed, in (2) determine the EMC of the three newly installed avionics combination with a rearward center of gravity, which resulted in systems: and (3) develop and evaluate possible corrective action the aircraft's rotating to a nose-high attitude immediately after for eliminating or reducing EMI/C problems. The methods used takeoff and entering the region of reversed command from and results obtained are described. A.R.H. which the pilot was unable to recover. Contributing to the accident was the failure of the flight crew to insure that the passenger N79-291 71 National Aeronautics and Space Administration, baggage was loaded in accordance with the configuration Langley Research Center. Hampton. Va. contained on the load manifest. Their failure resulted in a rearward FRICTION AND WEAR CHARACTERISTICS OF WIRE. center of gravity that was aft of the optimum range, but forward BRUSH SKIDS A.W.H. of the rearmost limit. Robert C. Dreher Aug. 1979 30 p refs (NASA-TP-1495; L-13095) Avail: NTIS HC A03/MF AOl N79-29162# Committee on Commerce. Science, and Transporta- CSCL O1C tion (U. S. Senate). The testing technique consisted of towing the skids with a AVIATION SAFETY ground test vehicle over asphalt and concrete surfaces at ground Washington GPO 1978 163 p refs Joint hearing before speeds up to 80 km/hr (50 mph) and bearing pressures up to the Comm. on Commerce. Sci.. and Transportation and the Comm. 689 kPa (100 psi) over sliding distances up to 1585 m (5200 ft). on Public Works and Transportation. 95th Congr.. 2d Sess., Results indicate that the friction coefficient developed by wire 27 Oct. 1978 brush skids is essentially independent of ground speed, is slightly (GPO-37-810) Avail: Comm. on Commerce, Sci. and increased with increasing bearing pressure, is noticeably af- Transportation fected by surface texture, and is not degraded by surface wetness. Midair collisions and the systems improvements which will Skid wear is shown to increase with increasing bearing pressure reduce the potential of these accidents are examined. Changes and with increasing ground speed and is dependent on the nature in procedures and standards that can help prevent a potential of the surface. Runway surface damage caused by the skids accident are emphasiied. Specifically, the topics addressed are: was in the form of an abrasive scrubbing action rather than (1) the air traffic control procedures after a conflict alert; (2) physical damage. S.E.S. the requirement for positive control at more major air carrier airports: (3) the development and installation of both ground-based and airborne collision avoidance systems and what can be done N79-29173# Rockwell International Corp.. El Segundo, Calif. to accelerate the introduction of that safety hardware; and (4) AIRCRAFT TRANSPARENCY FAILURE AND LOGISTICAL the issue of accelerating the implementation of reliever airports COST ANALYSIS. VOLUME 2; DESIGN DATA AND to provide incentives for reducing the mix of general aviation MAINTENANCE PROCEDURES Final Report, Jun. 1977 - and air carriers at major airports. J.M.S. Sep. 1978 S. S. Brown Dec. 1978 151 p refs (Contract F33615-77-C-3060: AF proj. 2402) N79-29163# Payne, Inc.. Annapolis, Md. (AD-A068720; NA-78-604-Vol-2; AFFDL-TR-78-153-Vol-2) WIND TUNNEL TEST OF ACES 2 EJECTION SEAT WITH Avail: NTIS HC A08/MF AOl CSCL 01/3 ANTHROPOMETRIC DUMMY IN ASYMMETRIC CONFIG- The aircraft transparency and logistical cost analysis program URATIONS Final Report, 15 Sep. 1976 - 30 Sep. 1978 is aimed at reducing the logistical costs associated with Fred W. Hawker and Peter R. Payne Wright-Patterson AFB, transparency systems for 20 of the current Air Force inventory Ohio AMRL Jan. 1979 53 p refs aircraft. The approach for achieving this goal was to collect all (Contract F33615-76-C-0530; AF Proj. 7231) information relating to the physical and performance characteris- (AD-A068614; Working-Paper-2 10-2; AMRL-TR-78- 108) Avail: tics, and maintenance historical data of the selected study aircraft. NTIS HC A04/MF AOl CSCL 01/2 These data provide the means of initiating search for design Previous investigations have determined the aerodynamic improvement and cost reduction studies. In order to assess the forces and moments acting upon an open ejection seat and its maintenance and logistical support activity as currently being nc'upaot ..hen the seat occupant was sitting symmetrically with practical at the Air Logistics Centers and Air Force Operational respect to the seat axes, with his limbs in the correct 'stowed' Bases, both maintenance and installation procedures, as well as positions. The present investigation was undertaken to deter- qualification and testing procedures, for transparency components mine the changes in the aerodynamic forces due to deviations and support systems were collected. These data were assembled from this ideal position: principally off-center asymmetry and to determine the support structure level of effort and costs to changes to limb movement. GRA identify those procedures and practices where cost reduction N79-29164// Stanford Telecommunications, Inc., McLean, Va. may be achieved. These data plus the failure analysis conducted INVESTIGATION OF A PRELIMINARY GIPS RECEIVER in the transparency analysis phases provided the basis for DESIGN FOR GENERAL AVIATION Final Report implementing the design improvement and cost reduction studies B. D. Elrod and F. D. Natali Los Angeles AFS SAMSO 14 Jul. shown in volume 3. GRA 1978 132 p refs (Contracts F04701-75-C-0239; DOT-FA77WAI-37) N79-29174jl Rockwell International Corp.. El Segundo, Calif. (AD-A069059; STI/E-TR-8022; SAM 5O-TR-79-34( Avail: AIRCRAFT TRANSPARENCY FAILURE AND LOGISTICAL NTIS HC A07/MF AOl CSCL 17/7 COST ANALYSIS. VOLUME 3; TRANSPARENCY ANALYSIS The preliminary design and analysis of a potentially low cost Final Report, Jun. 1977 - Sep. 1978 G PS receiver for general aviation navigation applications is S. S. Brown Dec. 1978 215 p refs presented. The results indicate that the receiver could meet or (Contract F33615-77-C-3060; AF Proj. 2402) exceed 20 area navigation (RNAV( requirements without (AD-A068721; NA-78-604-VoI-3; AFFD L-TR-78- 1 53-Vol-3) dependence on external altitude data. GRA Avail: NTIS HC A1O/MF AOl CSCL 01/3 The Rockwell Maintenance Analysis Model (MAM( program was used to extract cost data from the K051 LSC system, and N79-29170# Aerospace Engineering Test Establishment, Cold maintenance failure modes troni the AFM 66-1 maintenance Lake (Alberta). data collection system in order to conduct a detailed logistical CH-147 EMC EVALUATION OF SELECTED SUBSYSTEMS, cost and failure analysis. The cost and maintenance frequencies EMC TEST REPORT were utilized to pinpoint the most productive areas for life Cycle R. A. Lagrange 17 May 1979 16 p refs cost reduction. A number of potential improvement studies were (AETE-77/16-4) Avail: NTIS HC A02/MF AOl identified in the initial phase of this program. However, the effort An electromagnetic interference/compatibility investigation required to research, analyze, and assemble these data, limited was performed on the CH 147005 Chinook helicopter fitted the development to five design improvement studies. These factors,
592 N79-29182 coupled with the relative importance of the aircraft in the Air ineffective lateral trim; and 1101 the excessive force required to Force inventory, initiated the search for concepts that would operate the radio/intercom switch. Within the scope of this test, cure or substantially reduce the failures identified in the above the flying qualities of the RU-2H (GA VI aircraft are acceptable. noted MAMs process. The verification of the feasibility of the G RA proposed changes was accomplished by trading the projected 10-year life cycle cost of the existing concept to the costs of the development, refurbishing, and the reduced maintenance for N79-29179# Air Force Inst. of Tech.. Wright-Patterson AFB, the revised concept. The five design improvement trade studies Ohio. School of Engineering. resulted in significantly reduced logistical support costs. GRA A SIMULATION MODEL OF ATTACK HELICOPTER VULNERABILITY TO HOSTILE ARTILLERY FIRE M.S. Thesis N79-29176fl Naval Postgraduate School, Monterey. Calif. Emil H. Koenig, Ill Mar. 1979 82 p refs AN ANALYSIS OF BOLTER-HOLE SPACING IN AIRCRAFT (AD-A069753; AFIT/GST/SM/79M-4) Avail: NTIS CARRIER LANDINGS HC A05/MF AOl CSCL 01/3 Kneale T. Marshall May 1978 54 p ref This thesis presents a methodology which simulates the (A0-A068585: NPS55-78-013) Avail: NTIS activity, near the FEBA, of the Army's attack helicopter and the HC A04/MF AOl CSCL 01/2 activity of hostile artillery in two formats: uniformly distributed This paper presents an analysis of aircraft landing strategies area fire and precision fire against a point target as directed by on aircraft carriers. Optimal bolter-hole spacings are determined a forward observer. A stochastic computer simulation was for various measures of effectiveness, and a short discussion is developed that varies the modeled activities from one replication included on the use of automatic landing systems. GRA to another. Current concepts of attack helicopter employment in the anti-armor role are used. Concepts of intervisibility, detectabil. N79-29177# Air Force Flight Dynamics Lab., Wright-Patterson ity. target location error. C-cubed time delay, and artillery AFB, Ohio. round-to-round dispersion are also incorporated in the model. THE EFFECT OF WINGLETS ON THE KC-135A AIRCRAFT The model was experimented upon, using a hypothetical artillery Final Report, Jun. 1975 - Oct. 1977 weapon system, and the vulnerability predictions of the model George W. Loptien Nov. 1978 118 p refs are displayed and analyzed. GRA (AF Proj. 2404) )AD-A068324; AFFDL-TR-78- 124) Avail: NTIS HC A06/MF AOl CSCL 01/3 N79-29180# Aeronautical Research Labs.. Melbourne (Australia). To investigate the effects of winglets on the aerodynamic AN EXPERIMENTAL COMPARISON OF THE READABILITY characteristics of the KC-135 aircraft. semispan and full-span OF TWO DIGITAL ALTIMETERS wind tunnel models with winglets have been investigated in the G. A. White Dec. 1979 25 p refs NASA/LRC 8-Foot Transonic Pressure Tunnel. At cruise )ARL/SYS-Note-60; AR-001-325) Avail: NTIS conditions, the full-span tests indicated a total drag reduction of HC A02/MF AOl 5.3 percent for the model with the Boeing and NASA upper Twelve male volunteer subjects with flying experience were plus lower winglet configurations and 6.5 percent for the model required to read one of two digital altimeters while performing with the NASA upper winglet configuration. A wing-tip-extension a two dimensional tracking task. It was found that the Smiths configuration tested on the semispan model had a drag reduction Type 3B servo altimeter was read in a significantly shorter time of about 3 percent compared to about 5 to 7 percent for the than was the Aero Mechanism Type 8047/20A capsule altimeter. winglet configurations, however, the tip extension was not The subjects evaluated indicate that the probability of misreading optimized for drag reduction. At cruise conditions, the wing tip this altimeter is high. S,E.S. extension produced the greatest increase in wing root bending moment and the upper winglets the least. The increase in wing N79-29181# TRW Defense and Space Systems Group, Redondo root bending moment at cruise conditions varied from about Beach, Calif. 2.5 percent with the Boeing winglets, to about 3.5 percent with DIGITAL AVIONICS INFORMATION SYSTEM (DAIS): the tip extension. At cruise flight conditions, winglets on the DEVELOPMENT AND DEMONSTRATION Final Report, KC-135A aircraft were estimated to reduce the drag about 28 Apr. 1975 - 30 Sep. 1978 8.2 percent and increase the maximum lift-drag ratio about A. C. Mason, T. R. Price, B. A. Rich, R. J. Slightam, J. A. 9.5 percent. GRA Stautberg, W. P. Whalen. and C. E. Wilent Wright-Patterson AFB, Ohio AFAL Mar. 1979 169 p refs (Contract F33615-75-C-1 178; AF.Proj. 2052) N79-29178# Army Aviation Engineering Flight Activity, Edwards )AD-A068438; AFAL-TR-79- 1027) Avail: NTIS AFB. Calif. HC A08/MF AOl CSCL 09/3 PRELIMINARY AIRWORTHINESS EVALUATION RU-21 H The Digital Avionics Information System (DAIS) has been GUARDRAIL V AIRCRAFT Final Report characterized as a system architecture which can be applied John R. Niemann, Raymond B. Smith, William A. Norton, and and configured for a broad class of avionic applications and Frederick S. Doten Mar. 1978 52 p refs missions. The DAIS concept, therefore, proposed that the (AD-A068347; USAAEFA-77-1 1; USAA EFA-77- 19) Avail: processing, information transfer, and the control and display NTIS HC A04/MF AOl CSCL 01/3 functions or core elements be common and service the avionic The RU-21H (GA VI exhibited 1 deficiency and 10 shortcom- application functional areas on an integrated basis. These ings which will degrade its overall capability. The single-engine fundamental system characteristics, along with the DAIS system minimum-control airspeeds )V sub MC) were 5 to 10 knots attributes, such as modifiability and modularity, are presented in greater than the data provided in the operator's manual. The this report. The specific system features which provide these incorrect V sub MC data presented in the operators manual are characteristics and attributes are described. GRA a deficiency which warrants further testing and, as an interim measure, requires that a WARNING be incorporated in the N79.29182# Dynamics Research Corp.. Wilmington, Mass. operator's manual. Ten shortcomings listed in order of importance. DIGITAL AVIONICS INFORMATION SYSTEM (DAIS): are: (1) The dissimilar sense of operation of the attitude indicators; RELIABILITY AND MAINTAINABILITY MODEL USERS (2) the excessive glare in the cockpit caused by the navigation GUIDE, VOLUME 2 Final Report, May 1975 - Jul. 1977 lights mounted on the upper surfaces of the external wing-tip Andrew J. Czuchry. Robert H. Kistler, John M. Glasier, and Marjorie pods: (3) the inaudibility of the stall warning horn when A. Bristol Apr. 1979 139 p wearing helmet and oxygen mask; 141 the low intensity of the (Contract F33615-75-C-5218; AF Proj. 2051) MASTER CAUTION and MASTER WARNING lights; 151 the (AD-A068826; AFHRL-TR-78-2(2(( Avail: NTIS inefficient arrangement of navigation and communications radios: HC A07/MF AOl CSCL 14/4 161 the premature activation of the artificial stall warning device; The digital avionics information system (DAIS) life cycle cost (7) the inability to shut down the engine by use of the condition )LCC( study provides the Air Force with an enhanced inhouse lever; 181 the lightly damped, easily excited phugoid; (9) the capability to incorporate LCC considerations during all stages of
593 N79-29185 the system acquisition process. This report documents a reliability which runs on Control Data Corporation (CDC) 6600/CYBEA 74 and maintainability (R & M) model developed in the study and computer systems was modified and then used to evaluate the also serves as a users manual. The R & M model, a training accuracy of a flight navigation routine coded in FORTRAN. The model, and a cost model comprise the DAIS LCC impact model routines were executed without the simulator to obtain results (LCCIM) designed for use in LCC analysis of avionics systems. used for benchmarking. The n-bit simulator was employed to In this Context, its primary function is to manipulate input data simulate the numerical characteristics of the AN/AYK-1 5A digital banks to produce intermediate products, figures of merit, and processor. Error plots were constructed which show the maximum outputs required by the training and cost models. When used in errors occurring within small plotting intervals plotted against a stand-alone mode, the A & M model provides a means for each individual input value. These plots were used to aid visually analyzing the R M impact of changes in system design and in analyzing the error characteristics of the avionics routine as maintenance concepts on system support requirements. GRA it would be implemented on the AN/AYK-15A. A critical analysis of the error plots obtained showed that routines which are coded using single-precision floating-point arithmetic are prone to errors N79-29185// Air Force Avionics Lab., Wright-Patterson AFB, which exceed the error bounds specified for the routines. This Ohio. occurs even though range reductions in the trigonometric function DISPLAY MEASUREMENTS. MEASUREMENTS OF approximations are accomplished using extended precision. GRA REFLECTANCE-TYPE DISPLAYS Final Technical Report, 1 Jan. 1917 - 30 Sep. 1978 Richard A. Spearnock Feb. 1979 29 p refs N7929188* Vought Corp., Dallas, Tex. (AD-A068602; AFAL-TR-79- 1029) Avail: NTIS RAMJET COST ESTIMATING HANDBOOK Technical Report, HC A03/MF AOl CSCL 05/8 Apr. 1976 - Jun. 1977 This report applies the Equation of Spencer and Gray to H. T. Emmons, D. L. Norwood, J. E. Rasmusen, and H. E. Reynolds specify the reflectance of reflective-type displays. This reflectance Laurel, Md. Chem. Propulsion Inform. Agency May 1978 specification uses both a diffuse component function and a 306 p specular component function to completely describe any reflecting (Contract F33615-76-C-2O43 AF Proj. 3012) surface. The particular display chosen to illustrate the use of (AD-A056991: AFAPL-TR-77-50-Vol-2(' HC Al 4/M F AOl this method of specifying reflectance was the Hughes Liquid CSCL 21/5 Crystal Matrix Display. This display is a matrix display and produces Research conducted under Air Force Contract F33615-76-C- an image by electrically controlling the reflectance of each 2043 to generate cost data and to establish a cost methodology individual cell. In the appendix. a simplified example using this that accurately predicts the production costs of ramjet engines method of reflectance specification to evaluate a liquid crystal is presented. The cost handbook contains a description of over display optical system is given. GRA one hundred and twenty-five different components which are defined as baseline components. The cost estimator selects from N79-29186# Air Force Inst. of Tech.. Wright-Patterson AFB, the handbook the appropriate components to fit his ramjet Ohio. School of Engineering. assembly, computes the cost from cost computation data sheets A METHOD FOR EVALUATING KC-135 AVIONICS CONFIG- in the handbook, and totals all of the appropriate cost elements URATIONS M.S. Thesis to arrive at the total engine cost. The methodology described in Joel A. Jerabek Mar. 1979 84 p refs the cost handbook addresses many different ramjet types from (AD-A069446; AFIT/GST/ MA/79M-5) Avail: NTIS simple podded arrangements of the liquid fuel ramjet to the NC A05/MF AOl CSCL 01/3 more complex integral rocket/ramjet configurations including solid The KC/C. 135 Avionics Modernization Program is currently fuel ramjets and solid ducted rockets. It is applicable to a range tasked with determining the feasibility of replacing the KC/C-135 of sizes from 6 in diameter to 18 in diameter and to production navigator with cost effective avionics systems. The Avionics quantities up to 5000 engines. M.M.M. Evaluation Program (AEP) is a computer model that has been built to evaluate the mission impact caused by alternate avionics N7929189 * # Teledyne CAE, Toledo, Ohio. hardware configurations. Although the AEP was designed to ADVANCED GENERAL AVIATION TURBINE ENGINE model tactical aircraft missions, this thesis examines whether it (GATE) STUDY Final Repor. could be applied to the strategic mission of the KC-135. Aircraft R. Smith and E. H. Benstein Jun. 1979 150 p refs performance data, hardware reliability data, and abort logic criteria (Contract NAS3-20757( were input into the model. A baseline simulation was conduct- (NASA-CR- 159624; Teledyne-CAE- 1600) Avail: NTIS ed using the current KC-135 configuration. Two additional HC A07/MF AOl CSCL 21E configurations, single inertial navigation systems (INS) with a The small engine technology requirements suitable for general navigator and dual INS without a navigator, were selected and aviation service in the 1987 to 1988 time frame were defined. simulations conducted. These simulations were conducted with The market analysis showed potential United States engines sales both peacetime and wartime mission scenarios. An analysis of of 31.500 per year providing that the turbine engine sales price the AEP output data revealed that the addition of a single INS approaches current reciprocating engine prices. An optimum produced a significant improvement in Navigational Accuracy and engine design was prepared for four categories of fixed wing that by replacing the navigator with a second INS, navigational aircraft and for rotary wing applications. A common core approach accuracy could be maintained without a change in the mission was derived from the Optimum engines that maximizes engine success rate. GRA commonality over the power spectrum with a projected price competitive with reciprocating piston engines. The advanced N79-29187# Air Force Inst. of Tech.. Wright-Patterson AFB, technology features reduced engine cost, approximately 50 percent Ohio. School of Engineering. compared with current technology. J.M.S. IMPLEMENTATION AND TESTING OF NUMERICAL ANALYSIS TECHNIQUES IN AVIONICS APPLICATIONS N7929190*# Notre Dame Univ., Ind. Dept. of Electrical M.S. Thesis Engineering. Richard Arthur Adams Mar. 1979 155 p refs ALTERNATIVES FOR JET ENGINE CONTROL Annual Report, (AD-AO69299; AFIT/GCS/EE/79. 1) Avail: NTIS 1 Mar. 1978 - 28 Feb. 1979 HC A08/MF AOl CSCL 09/2 Michael K. Sam 28 Feb. 1979 212 p refs Errors due to finite wordlength are unavoidable when aircraft (Grant NsG-3048( signal processing operations such as flight control, navigation, (NASA-CR-158390( Avail: NTIS HC A10/MF AOl CSCL and fire control are implemented on a digital computer. To reduce 21E these errors to tolerable levels, longer word-lengths can sometimes The research is classified in two categories: (1) the use of be employed. The effects of some of the errors, such as those modern multivariable frequency domain methods for control of due to arithmetic series truncation, machine roundoff, and engine models in the neighborhood of a set-point, and (2) the quantization of system coefficients, can be lessened somewhat use of nonlinear modelling and optimization techniques for control by appropriate numerical analysis techniques. An n-bit simulator of engine models over a more extensive part of the flight envelope.
594 N79-29199
Progress in the first category included the extension of CARDIAD (Contract NAS2-7350) (Complex Acceptability Region for Diagonal Dominance) methods (NASA-CR-152307; MAE-1422) Avail: NTIS developed with the help of the grant to the case of engine HC A03/MF AOl CSCL 01C models with four inputs and four outputs. A suitable bounding A six-degree-of-freedom variable-response research aircraft procedure for the dominance function was determined. Progress was used to determine the minimum lateral-directional control in the second category had its principal focus on automatic power required for desirable and acceptable levels of handling nonlinear model generation. Simulations of models produced qualities for the STOL landing approach task in a variety of satisfactory results where compared with the NASA DYNGEN simulated atmospheric disturbance conditions for a range of digital engine deck. R.E.S. lateral-directional response characteristics. Topics covered include the in-flight simulator, crosswind simulation, turbulence simulation, N7929191*# General Electric Co.. Evendale. Ohio. Aircraft test configrations. and evaluation procedures. Conclusions based Engine Group. on a limited sampling of simulated STOL transport configurations NASA CF6 JET ENGINE DIAGNOSTICS PROGRAM: flown to touchdown Out of 6 deg. 75 kt MLS approaches. usually LONG-TERM CF6-6D LOW-PRESSURE TURBINE DETE- with a sidestep maneuver are discussed. A.R.H. RIORATION Jeffrey J. Smith Aug. 1979 116 p refs N79-29197// Science Applications, Inc.. La Jolla. Calif. (Contract NAS3-20631) DEVELOPMENT OF CRITERIA FOR MONITORING OF (NASA-CR- 159618; R79AEG356) Avail: NTIS AIRPORT GROUND POLLUTION. VOLUME 1: STUDY Final HC A06/MF AOl CSCL 21E Report, Sep. 1975 - Jul. 1977 Back-to-back performance tests were run on seven airline Claus B. Ludwig and J. Richard Yoder Nov. 1978 439 p low pressure turbine (LPT) modules and four new CF6-6D modules. refs 2 Vol. Back-to-back test cell runs, in which an airline LPT module was (Contract DOT-FA76WA-3725) directly compared to a new production module, were included. (AD-A067242; SAI-77-910-U-Vol-1; FAA-RD-77-1 78-1-Vol-1) The resulting change, measured in fuel burn, equaled the level Avail: NTIS HC A19/MF AOl CSCL 01/5 of LPT module deterioration. Three of the LPTmodules were Criteria are developed by which the validity of pollution analytically inspected followed by a back-to-back test cell run predictions and measurements in the airport environs can be to evaluate current refurbishment techniques. Author judged. The criteria are applied to three technologies: ( 1 ) predictive mathematical models; (2) measurements by point samplers; and (3) measurements by remote monitors. For mathematical N79-29193# Naval Air Test Center, Patuxent River, Md. models, the criterion is the agreement between predicted and AIRCRAFT ENGINE DRIVEN ACCESSORY SHAFT COU- measured pollution levels. Various mathematical models are PLING IMPROVEMENTS USING HIGH-STRENGTH NONME- described, analyzed and ranked by weighted attributes as screening TALLIC ADAPTER/ BUSHINGS Progress Report models and as validation models. For point samplers, the criteria Aleck Loker 20 Apr. 1979 47 p refs have been developed based on EPA-approved measurement (AD-A068637; NATC-TM-79-1-SY; PR-2) Avail. NTIS principles and procedures for testing performance characteristics HC A03/MF AOl CSCL 21/5 and for determining a consistent relationship to reference methods. Engine driven accessories, such as generators, starters, and Remote monitors belong to an evolving technology that has not pumps, are commonly connected to their respective power takeoff yet been approved as to measurement principles. Thus, criteria shafts by splined couplings. These shaft couplings, which allow are developed to select certain remote sensing systems as potential rapid installation and removal of the accessory, are capable of candidates for air enforcement monitors. Data validation high torque transmission and are considered to be self-centering. procedures are developed for the selected remote monitors. However. because of their rapid wear and failure rate. NAVAIR- Author TESTCEN has engaged in a continuing spline coupling improve- ment program over the past 11 years. An outgrowth of this N79-29198# Science Applications, Inc.. La Jolla, Calif. program has been the development of the new high-strength DEVELOPMENT OF CRITERIA FOR MONITORING OF nonmetallic spline coupling adapter/bushing technology. Pre- AIRPORT GROUND POLLUTION. VOLUME 2: DATA vious Technical Memoranda, TM 76-1 SY and TM 78-1 SY, VALIDATION PROCEDURES Final Report. Sep. 1975 . Jul. condensed the results of these coupling improvement efforts into 1977 a description of two basic spline coupling designs (crowned circular Claus B. Ludwig and J. Richard Yoder Nov. 1978 435 p toothed and flat toothed splines), explained their apparent success, refs 2 Vol. and presented limited application and manufacturing information. (Contract DOT-FA76WA-3725( This report presents a summary of the new coupling designs (AD-A067243; SAI-77-910-U; FAA-RD-77-178-2) Avail: which have been evaluated or are planned for future tests. NTIS HC A19/MF AOl CSCLO1/5 Previously unpublished test data and the latest applicable Military Criteria are presented which will allow the FAA to methodically Standard Drawings are also contained therein. GRA interrogate remotely monitored data taken for R&D and future air enforcement purposes. While interrogation in the case of air N79.291 95*# National Aeronautics and Space Administration. enforcement appears more straightforward than for R&D, it is Langley Research Center, Hampton, Va. more demanding because of the requirement for demonstrating DESCRIPTION OF THE VIOL APPROACH AND LANDING equivalency. Appendixes include: (1) National Primary and TECHNOLOGY (VALT) CH-47 RESEARCH SYSTEM Secondary Ambient Air Quality Standards (40 CFR 50); James R. Kelly, Frank P. Nieasen, John F. Garren, Jr.. and Terence (2) Ambient Air Monitoring Reference and Equivalent Methods S. Abbott Aug. 1979 57 p refs (40 CFR 53); (3) guidelines for public reporting of daily air (NASA-TP-1436; L-12781( Avail: NTIS HC A04/MF AOl quality; (4) control of air pollution from aircraft and aircraft noise; CSCL 01 (5) review of calibration span gases; (6) list of commercially The Langley Research Center modified a CH-47B helicopter available point source samplers; (7) derivation of signal-to-noise to provide a general-purpose variable-stability capability for the ratio equations and error analysis; (8) meteorological instru- VTOL approach and landing technology (VALT( program. The ments for use in the calibration test range; and (9) electromagnetic functional aspects and capabilities of the overall system are interference characteristics requirements for equipment. A.R.H. described. Automatic decelerating approach data are presented to illustrate the performance of the overall system. A.R.H. N79-29199# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va. N7929196*# Princeton Univ.. N. J. Flight Research Lab. A UNIQUE FACILITY FOR V/STOL AIRCRAFT HOVER AN IN-FLIGHT SIMULATOR INVESTIGATION OF ROLL AND TESTING YAW CONTROL POWER REQUIREMENTS FOR STOL Richard G. Culpepper, Ronald D. Murphy (Naval Air Systems APPROACH AND LANDING: DEVELOPMENT OF CAP- Command, Washington, D. C.), Edward A. Gillespie (Rockwell ABILITY AND PRELIMINARY RESULTS Intern. Corp.. Columbus, Ohio). and Archie G. Lane Aug. 1979 D. R. Ellis and S. C. Raiainghani Apr. 1979 44 p refs 56 p ref
595 N79-29200
(NASA-TP-1473; L-12914) Avail: NTIS HC A04/MF AOl this program and data in the literature are interpreted in terms CSCL 148 of a detailed ionic mechanism for soot formation in which The Langley Impact Dynamics Research Facility (IDRF) was chemi-ions grow by adding acetylene, polyacetylenes. and C2H. modified to obtain static force and moment data and to allow G RA assessment of aircraft handling qualities during dynamic tethered hover flight. Test probe procedures were also established. Static N7929292*# National Aeronautics and Space Administration. lift and control measurements obtained are presented along with Lewis Research Center, Cleveland, Ohio. results of limited dynamic tethered hover flight. J.M.S. AN EXPERIMENTAL LOW-COST, SILICON SLURRY! ALUMINIDE HIGH-TEMPERATURE COATING FOR SUPER- N79-29200// Harco Corp.. Medina. Ohio. ALLOYS TECHNIQUES FOR CATHODIC PROTECTION TESTING Stanley G. Young and Daniel L. Deadmore Jul. 1979 24 p OVER AIRFIELD PAVEMENTS Final Report, Aug. 1977 - refs Jul. 1978 (NASA-TM-79178: E-0451 Avail; NTIS HC A02/MF AOl CSCL Bernard Husock Tyndall AFB. Fla. Civil and Environ. Eng. Develop. hF Office Apr. 1979 71 p refs A duplex silicon-slurry/aluminide coating has been developed (Contract F08635-77-C-0248; AF Proj. 2104). and cyclically tested in Mach 1 combustion gases for oxidation (AD-A069045: CEEDO-TR-78-31) Avail: NTIS and thermal fatigue resistance at 1093 C and in Mach 0.3 HC A04/MF AOl CSCL 13/11 gases for hot-corrosion resistance at 900 C. The base-metal This report summarizes the techniques developed for cathodic superalloys were VIA and 8-1900. The coated 8-1900 specimens protection testing over airfield pavements. Test results conclusively performed much better in oxidation than similar specimens coated proved that the accuracy of all pipe-to-surface potential with aluminides and almost as well as the more-expensive Pt-Al measurements taken over pavement surfaces are questionable. and MCrAIY (where M is Ni and/or Co) coatings deposited by On concrete pavement it was found that potential readings differed the physical vapor deposition process. The coating also provided from readings on adjacent soil by more than 100 millivolts. good hot-corrosion protection. Metallographic. X-ray. and electron Potential readings over well sealed asphalt surfaces were not microprobe studies were made to characterize the coating, possible even when using high input impedance, electronic determine failure mechanisms, and study some of the changes voltmeters. Potential readings over deteriorated asphalt were due to exposure. Author possible but the accuracy was poor. Accurate potential measure- ments over pavement surfaces can be made Only if the reference electrode contacts the surface beneath the pavement. This report N79-29295# Air Force Materials Lab., Wright-Patterson AFB. recommends a procedure for easily penetrating the pavement Ohio. surface and installing a pavement insert through which a modified AN ANALYSIS OF THE LOW CYCLE FATIGUE BEHAVIOR reference electrode may be inserted. GRA OF THE SUPERALLOY RENE 95 BY STRAINRANGE PARTITIONING Technical Report, Jan. 1977 - Jan. 1978 J. M. Hyzak and Henry L. Bernstein Nov. 1978 60 p refs N79-29248# Research Inst. of National Defence. Stockholm (Contract F33615-76-C-5191) (Sweden). )AD-A068252; AFM L-TR-78 . 174) Avail; NTIS CONSTRUCTION USING CARBON FIBER COMPOSITE HC A04/MF AOl CSCL 11/6 MATERIALS AND ALUMINUM: A COST COMPARISON This report describes the results of a research program to Final Report [KONSTRUKTION I KOLFIBERKOMPOSIT OCH examine the applicability of the Strainrange Partitioning (SRP) ALUMINIUM: EN KOSTNADSJAEM FOE RELSE] method for predicting high temperature low cycle fatigue )LCF) Bo Holmberg and Boerje Oestman Dec. 1978 13 p refs In crack initiation. Strain controlled LCF tests were performed at SWAHILI 922K (1200 F) on Rene 95, a high strength nickel-base superalloy. (FOA-C-20280-F9) Avail; NTIS HC A02/MF AOl and SRP was used to correlate the data, as well as, to predict A comparison of production costs for various aircraft parts the number of LCF cycles to failure for a series of validation using either carbon fiber composite materials or aluminum was tests. The data indicate that for Rene 95 compressive dwell made. The costs involved in the use of different construction cycles are more damaging than tensile dwell cycles, and the techniques, the cost of materials, and the labor costs are discussed. LCF behavior depends largely on the time in tension per cycle Previous studies on wing panels and fuel tanks as well as several and on the value of the maximum tensile stress. SAP was unable types of composite materials were considered. Results show that to satisfactorily predict the cyclic life for several types of LCF certain construction techniques make carbon fiber composites tests because the model is not capable of accounting for particular highly competitive as compared to aluminum. Author )ESA) aspects of the alloys cyclic behavior, particularly the development of mean stresses. GRA N79-29270# AeroChem Research Labs., Inc., Princeton, N. J. N79-29300N Pratt and Whitney Aircraft Group. West Palm IONIC MECHANISMS OF CARBON FORMATION IN Beach, Fla. Government Products Div. FLAMES Annual Report, 1 Jan. - 31 Dec. 1978 HOT SALT STRESS CORROSION STUDIES Final Report, H. F. Calcote, W. J. Miller. and D. B. Olson Apr. 1979 20 p 1 Apr. 1976 - 1 Jun. 1978 refs R. L. Fowler Jun. 1978 58 p refs (Contract F49620-77-C-0029; AF Proj. 2308) (Contract F33615-76-C-5155 AF Proj. 7353) )AD-AO68872; AeroChem-TP-382: AFOSR-79-052 1 TR; AR-2) (AD-A068402; PWA-FR-10247; AFML-TR-78-121) Avail; Avail; NTIS HC A02/MF AOl CSCL 21/2 NTIS HC A04/MF AOl CSCL 11/6 An experimental program is underway to determine the Effects of various flight-cycle simulations, maximum tempera- mechanism of soot formation in flames, with particular emphasis ture. and microstructure were investigated using a concept on ionic mechanisms. Mass spectroscopic measurements of analogous to a low-cycle fatigue ILCFI study. Isothermal stress positive ion profiles through sooting and non-sooting, flat premised cycling increased HSSC threshold stress over static loading. flames show a large increase in the variety of ions produced Simultaneous stress/temperature cycling increased threshold when sooting occurs, with dramatic increases in the concentration stress land cyclic life) over isothermal Stress cycling. A simple of heavier ions as the combustion mixture is made fuel rich. In takeoff/shutdown dwell simulation produced the highest test sooting flames, masses above 165 amu display two maxima in results of the thermal-mechanical cycles investigated, with no ion profiles through the flame. This has been confirmed by significant effect from the addition of idle and cruise components. electrostatic probe measurements. The effect of changing the HSSC susceptibility increased with increasing maximum cyclic initial, and thus adiabatic flame temperature, on the critical temperature. Alpha-beta processed material showed better equivalence ratio for soot formation was determined for acetylene resistance to HSSC than did beta material. GRA and benzene. For acetylene the tendency to soot decreases with increasing adiabatic flame temperature; for benzene the tendency 09-29328# Royal Aircraft Establishment. Farnborough to soot first increases and then decreases. The data obtained in (England).
596 N79-29397
ENVIRONMENTAL EFFECTS ON THE ELASTIC-PLASTIC and D-2 fuels derived from selected paraffinic and naphthenic PROPERTIES OF ADHESIVES IN BOND METAL JOINTS crudes. A pour point depressant was tested. M.M.M. Walter Althof, Gerhard Klinger, Gerhard Neumann. and Johanna Schlothauer Jan. 1979 97 refs Transl. into ENGLISH p N79-29359// Klimaeinfluss auf die Kennwerte des Elasto-Plastischen Verhal- Exxon Research and Engineering Co., Linden, N. J. Government Research Lab. tens von Kiebstoffen in Metallklebungen" Report DLR-FB-77-63 DFVLR. Brunswick. 1977 CONTINUATION STUDY OF ALTERNATE FUELS NITROGEN (RAE-Lib-Trans-1999; B867977( Avail: NTIS CHEMISTRY Final Technical Report, 1 Feb. 1978 - 31 Jan. 1979 HC A05/MF AOl The shear modulus, the stress at 1% shear strain, the shear John W. Frankenfeld and William F. Taylor Feb. 1979 58 p refs strength, the strain at fracture and the appertaining shear (Contract N00019-78-C-0177( stress-strain diagrams are analyzed for ten aircraft structural adhesives. These values are calculated from the measured (AD-A06901 1: EXXON/GRU.2KWC.79) Avail:. NTIS load-deflection behavior of the adhesives in the bond line of lap HC A04/MF AOl CSCL 21/4 joints with a thick adherend and a small overlap length, as well An investigation of the effects of nitrogen compounds on as from the torsion pendulum testing of cast adhesives. The sediment formation during fuel storage was carried out using measurements are made before and after a long exposure to model fuel systems. Various weak to non-basic nitrogen warmth, cold, moisture, warmth combined with moisture, and compounds, especially alkyl pyrroles and indoles were found to changes between cold and combined warmth and moisture. The promote sediment fcrmation: basic nitrogen compounds such as environmental effects on the adhesion between adherend and most amines did not. The sediment formation was strongly adhesives as observed in the tests are described. Author catalyzed by light and carboxylic acids. Phenols and aromatic thiols retard sedimentation. Sulfides and aliphatic thiols had little effect. Moisture and and traces of mineral acid also had little or N79-29344I Foxboro Co.. Burlington, Mass. Analytical Div. no influence on sediment formation. The structure of the sediment WEAR PARTICLE ANALYSIS OF GREASE SAMPLES was investigated using infrared and mass spectroscopy. GRA E. Roderic Bowen and John P. Bowen 18 Apr. 1979 86 p refs (Contract N68335-76-C-2291) N79-29364# Monsanto Research Corp.. Dayton, Ohio. (AD-A069114; NAEC-92-129( Avail: NTIS HC A05/MF AOl ANALYSIS OF THE EMISSIONS FROM STORAGE TANKS CSCL 11/8 DURING JP-4 FUEL TRANSFER OPERATIONS. PHASE 1: An investigation was conducted to analyze a number of WARM WEATHER CONDITIONS Final Report widely used types of grease samples by Ferrography. Solvent W. R. Feairheller 1 May 1979 66 refs systems were successfully formulated to dissolve these greases p (Contract F41608-78-C-1240( for analytical purposes. A number of grease samples from (AD-A069339( Avail: NTIS HC A04/MF AOl CSCL 21/4 aircraft components were subjected to Ferrographic analysis and This report summarizes the warm weather phase of a program results reported. GRA to measure the concentration of JP-4 vapor that is emitted to the atmosphere during filling of underground storage tanks. Tests N7929354*# California Univ., Los Angeles. School of were conducted with and without pressure - vacuum breather Engineering and Applied Science. valves. Samples were analyzed by a portable total hydrocarbon FORECAST OF FUTURE AVIATION FUELS. PART 1: analyzer containing a flame ionization detector. Data was recorded SCENARIOS Progress Report, 1 Aug. 1976 - 20 Sep. 1977 at one minute intervals during the fuel transfer operations. All J. M. English, C. Y. Liu, J. L. Smith, A. K. K. Yin, G. A. Pan, M. data was collected during August and September 1978 from B. Ayati, M. Gyamfi, and M. R. Arabzadah 17 Mar. 1978 50,000 gallon underground JP-4 fuel storage tanks at Wright- Patterson AFB. OH. Author (GRA( 140 p refs Revised (Grant NsG-3116( (NASA-CR-158871: UCLA-ENG-77-78-Pt-1( Avail: NTIS N79-29397# Sperry Research Center, Sudbury, Mass. HC A07/MF AOl CSCL 21D LOW EM SIGNATURE RESPONSE TECHNIQUES Final A preliminary set of scenarios is described for depicting the Technical Report, Sep. 1977 - Oct. 1978 air transport industry as it grows and changes, up to the year C. L. Bennett, H. Mieras, S. L. Teeter, and J. P. Tommey RADC 2025. This provides the background for predicting the needs for Griffis AFB, N. V. Mar. 1979 117 p refs future aviation fuels to meet the requirements of the industry (Contract F30602-77-C-0166: AF Proj. 2314( as new basic sources, such as oil shale and coal, which are (AD-A068211; SCRC-CR-78-61: RADC-TR-78-287( Avail: utilized to supplement petroleum. Five scenarios are written to NTIS HC A06/MF AOl CSCL 17/9 encompass a range of futures from a serious resource-constrained This study extends the technique for computing the smoothed economy to a continuous and optimistic economic growth. A impulse response to the case of scattering from triangular plates, unique feature is the choice of one immediate range scenario quadrilateral plates. and more refined aircraft models that consist which is based on a serious interruption of economic growth of a cylindrical fuselage with triangular or quadrilateral plates occasioned by an energy shortfall. This is presumed to occur for the wings, stabilizers, and rudder. To the knowledge of Sperry, due to lags in starting a synfuels program. Author this is the first time that a successful solution of these problems has been obtained. The numerical techniques developed consisted N7929355*# Lockheed-California Co., Burbank. of the simultaneous solution of two vector space-time integral EXPERIMENTAL STUDY OF LOW TEMPERATURE BEHAV- equations. A major effort was required in order to handle IOR OF AVIATION TURBINE FUELS IN A WING TANK non-rectangular plate geometries. The resulting numerical MODEL Final Report procedure consisted of a set of local coordinate transformations Francis J. Stockemer 1979 112 p refs in the plate edge regions in order to be able to properly satisfy (Contract NAS3-20814) the boundary conditions on the surface currents. Results were (NASA-CR-159615( Avail: NTIS HC A06/MF AOl CSCL computed for several triangular plates, finned cylinders, and a 21D MIG-21 aircraft model. These results were found to be in good An experimental investigation was performed to study aircraft agreement with measurements taken on the Sperry time domain fuels at low temperatures near the freezing point. The objective scattering range. In addition, measured results were obtained was an improved understanding of the flowability and pumpability for the response of scattering centers when coated with RAM of the fuels under conditions encoutered during cold weather (Radar Abosrbing Materials(. These results show that RAM can flight of a long range commercial aircraft. The test tank simulated lower the scattered response but that the amount of reduction a section of an outer wing tank and was chilled on the upper is dependent upon the spectrum of the illumination and the and lower surfaces. Fuels included commercial Jet A and Diesel aspect angle. Moreover, there were several frequencies where D-2: JP-5 from oil shale: and Jet A. intermediate freeze point. the RCS experienced nulls of an additional 8-10 db. GRA
597 N79-29519
N79-29519 Virginia Univ., Charlottesville. (Contracts F41 6O8-76-D-AOO5; F41 608-77-D-AO2 1) STABILITY AND NONLINEAR RESPONSE OF ROTOR- (AD-A068223; LG78ER0261; SA-ALC/MME-76-6-38-2) Avail: BEARING SYSTEMS WITH SQUEEZE FILM BEARINGS NTIS HC A14/MF AOl CSCL 01/3 Ph.D. Thesis The NDI Reliability Workshop was held in Houston. Texas. Lloyd Edward Barrett 1978 331 p on August 2-4. 1978, to present the results of the Air Force Avail: Univ. Microfilms Order No. 7916233 Logistics Command program. 'Determination of NDI Reliability, A method of analyzing the first mode stability and unbalance and to provide a forum for evaluating the results and discussing response of multimass flexible rotors is presented whereby the approaches for NDI Reliability improvement. Attendance at the multimass system is modeled as an equivalent single mass modal Workshop was limited to government and industry personnel model including effects of rotor flexibility, general linearized whose primary interest was in nondestructive inspection, fracture hydrodynamic journal bearings, squeeze film bearing supports mechanics, NDE equipment and quality assurance. The workshop and rotor aerodynamic cross coupling. Expressions for optimum consisted of formal presentations, working task groups involving bearing and support damping are presented for both stability all attendees, and a general discussion forum. These workshop and unbalance response. The method is intended to be used as proceedings Contain a transcript of the general discussion forum a preliminary design tool to quickly ascertain the effects of bearing which presented the task group Conclusions and recommendations and support changes on rotor-bearing system performance. for nondestructive inspection improvement. Methods of calculating the nonlinear squeeze film bearing forces GRA for finite length bearings are developed which are computationally faster than finite difference and finite element methods generally N79-29532# Vought Corp. Advanced Technology Center, Inc.. Dallas, Tex. used. Dissert. Abstr. N-RAY INSPECTION OF AIRCRAFT STRUCTURES USING MOBILE SOURCES: A COMPENDUM OF RADIOGRAPHIC N79-29520# Boeing Commercial Airplane Co.. Seattle, Wash. RESULTS Final Report, 18 May 1977 - 22 Dec. 1978 NEW CONCEPTS IN AIRCRAFT JOURNAL BEARINGS Final W. D. Dance 16 Apr. 1979 61 p refs Report, May 1976 - Aug. 1978 (Contract N68335-77-C-0555; WF41461406( W. F. Lynn Aug. 1978 96 p refs (AD-A068316; ATC-8-92200/8CR-137; NAEC-92-1 16) Avail: (Contract F33615-76 . C-3098; AF Proj. 2402) NTIS HC A04/MF AOl CSCL 01/3 (AD-A068619; AFFDL-TR-78-97) Avail: NTIS This report presents a compendium of typical results of neutron HC A05/MF AOl CSCL 13/9 radiographic inspections performed on aircraft structures and An exploratory development and test program was conducted laboratory structural specimens. The radiographs are representative to establish Optimum materials and designs for composite material of the Capability of isotope or small accelerator (nonreactor) journal bearings in aircraft joints between structural components neutron sources for imaging defects in aircraft and missile of both advanced composite and conventional metallic materials. structures. The results show that: (1) the resolution and sensitivity An initial study and design phase evaluated the characteristics of transportable sources are adequate for effective inspection of of candidate composite materials as they apply to highly loaded structures for many Commonly occurring defects (the validity of bearings in adverse environments. A second phase involved the technique is established), and (2) the systems utilized to fabrication and testing of journal bearing configurations. In the obtain these results prove the feasibility of making N-Ray systems study and design phase, composites of epoxy resin reinforced sufficiently portable for field inspection of aircraft. Recommenda- with fibers of graphite, glass. TFE. and Kevlar were evaluated in tions are made for implementing the transition from exploratory corrosion. Strength, and wear/life tests. Cost, relative weight, work to a routine field inspection capability. GRA and suitability for commercial manufacture were considered. Also, suitability for direct substitution of composite journal bearings for currently used metallic journal bearings was a major program N79.29543# Technische Hogeschool, Delft (Netherlands). Dept. goal. Early testing indicated that graphite filament-reinforced of Aerospace Engineering. composites lacked suitable friction and wear characteristics and FATIGUE PROPERTIES OF ADHESIVE-BONDED LAMI- were subject to edge breakdown due to pin bending and accepted NATED SHEET MATERIAL OF ALUMINUM ALLOYS degrees of joint misalignment. The best combination of characteris- J. Schijve, H. T. M. vanLipzig. G. F. J. A. vanGestel. and A. H. tics was obtained in filament wound glass or Kevlar fibers W. Hoeymakers Dec. 1978 41 p refs impregnated with epoxy resins. Suitable wear/life and friction (LR-276; ICAF-1086) Avail: NTIS HC A03/MF AOl characteristics were obtained by incorporating TFE fabric or Comparative fatigue tests were carried Out on centrally Cracked sprayed TFE-enriched resin liners in the composite journal specimens and lug type specimens, both made from solid sheet bearings. GRA and laminated sheet, consisting of five 1 mm sheets of 2024-T3 AlcIad material bonded by FM 123/5. Most tests were carried Out under constant amplitude loading but growth delays due to N79-29522# Detroit Diesel Allison. Indianapolis, Ind. peak loads were studied also. Observations are made for through GAS TURBINE ENGINES AND TRANSMISSIONS FOR BUS cracks and part through cracks. The significance of the results DEMONSTRATION PROGRAMS Technical Status Report, for application in aircraft structures is analyzed. 28 Aug. - 30 Oct. 1978 Author G. J. Gomolak Oct. 1978 7 p (Contract EM-78-C-02-4867) N79-29544# National Aerospace Lab.. Emmeloord (Netherlands). )COO-4867 . 1( Avail: NTIS HC A02/MF AOl THE EFFECTS OF GUST ALLEVIATION ON FATIGUE IN Progress in the procurement of gas turbine engines and 2024-T3 ALCLAD automatic transmissions and the required associated Software J. B. deJonge. A. Nederveen. and P. J. Tromp 13 Jun. 1978 47 refs for the bus demonstration programs is reported. All hardware p (NRL-TR . 78064-lJ; items were defined and were released for procurement. Engine ICAF- 1059) Avail: NTIS HC A03/MF' AOl and transmission hardware is being received, and is approximately 25 percent completed at this time. The September 1978 Cost Fatigue tests under flight simulation loading were done on Report and engine and transmission installation drawings were simple notched 2024-T3 Alclad sheet specimens. Reduction of delivered to the DOE on schedule. The program is progressing the gust load amplitudes resulted in an increase of crack initiation as planned and all items are on schedule for delivering the first life but hardly influenced crack propagation. Reduction of the overall stress level increased both initiation and crack propagation engine/transmission at the end of April 1979. DOE life. The observed variations could be analytically predicted with varying success. N79-29531 Lockheed-Georgia Co., Marietta. Author PROCEEDINGS FROM THE GOVERNMENT/INDUSTRY N79-29550# Air Force Materials Lab., Wright-Patterson AFB, WORKSHOP ON THE RELIABILITY OF NONDESTRUCTIVE Ohio. INSPECTIONS RESIDUAL SURFACE STRAIN DISTRIBUTIONS NEAR W. H. Lewis, W. H. Sproat. and W. M. Pless Dec. 1978 HOLES WHICH ARE COLDWORKED TO VARIOUS DE- 302 Workshop held at Houston. Tex., 2-4 Aug. 1978 p GREES Final Report, Oct. 1975 - Sep. 1976
598 N79-29958
Gary Cloud Nov. 1978 231 p refs as compared to that obtained on a large computer. The (AF Proj. 2307) determination of the optimum sampling rates which would give (AD-A068396; AFML-TR-78-153) Avail: NTIS the best simulation accuracy on the multi-microprocessor system HC A11/MF AOl CSCL2O/11 which has a relatively short word length was studied. They are Residual surface strain distributions were measured in the determined as functions of the characteristic frequencies of the vicinity of holes in 1/4 in. aluminum alloy plate which had system simulated, the word size of the digital machine, and the been coldworked to various degrees of by a commercial process. discretization method used for the simulation. It is concluded Seven levels of coldworking between 3.8 mils and 7.8 mils that the multi microprocessor system can be used as a fast. radial interference were studied. Attention focused mainly on accurate and yet low cost computing resource for certain real radial strains, but hoop strains were measured for two coldwork time aircraft simulation problems if a judicious design approach levels. A sophisticated moire technique was developed for this is taken. Dissert. Abstr. investigation, and refined computer routines were utilized for reduction of data and plotting of results. The moire method National Aeronautics and Space Administration. involved high-resolution photography of a specimen grating before N79-29938# Lewis Research Center, Cleveland, Ohio. and after coldworking and subsequent generation of fringe patterns in a coherent optical processor. This report contain3 considerable COMPUTERIZED SYSTEMS ANALYSIS AND OPTIMIZA- tutorial detail about these techniques. The results are quite TION OF AIRCRAFT ENGINE PERFORMANCE, WEIGHT, straightforward, and they are shown to agree reasonably well AND LIFE CYCLE COSTS Laurence H. Fishbach 1979 22 refs Presented at Flight with the limited available data. The plastic deformation process p Mech. Panel. Symp. on the Use of Computers as a Design Tool, appears to be quite complex, and minor changes of cold-working Munich, 3-6 Sep. 1979; sponsored by AGARD parameters can cause large changes in the strain--a factor which (NASA-TM-79221: E-1 12) Avail: NTIS HC A02/MF AOl CSCL must be considered by designer and manufacturer. GRA 12B The computational techniques utilized to determine the N79-29662fl Royal Aircraft Establishment. Farnborough optimum propulsion systems for future aircraft applications and (England). to identify system tradeoffs and technology requirements are AN ANALYSIS OF A PROGRAMMED LOAD FATIGUE described. The characteristics and use of the following computer FAILURE codes are discussed: (1) NNEP - a very general cycle analysis C. J. Peel 14 Jul. 1978 29 p refs code that can assemble an arbitrary matrix fans, turbines, ducts, (RAE-TR-78078; BR65871) Avail: NTIS HC A03/MF AOl shafts, etc., into a complete gas turbine engine and compute Premature failure of an undercarriage fitting occurred during on- and off-design thermodynamic performance; (2) WATE - a a fatigue test, in which the cylindrical barrel of the undercarriage preliminary design procedure for calculating engine weight using was internally pressurized in a programmed sequence of the component characteristics determined by NNEP; (3) POD pressures representing landing and taxying loads. Failure occurred DRG - a table look-up program to calculate wave and friction by the initiation of fatigue cracks at defects in the undercarraige drag of nacelles; (4) LIFCYC - a computer code developed to forging and by their growth to a critical depth. An effective calculate life cycle costs of engines based on the output from pressure range was calculated by comparison of the fatigue WATE; and (5) INSTAL - a computer code developed to striation spacings with laboratory crack growth data. It was calculate installation effects, inlet performance and inlet weight. assumed that one cycle of the effective pressure range would Examples are given to illustrate how these computer techniques proceed at the same rate of crack growth as an entire sequence can be applied to analyze and optimize propulsion system fuel of pressurizations. The effective pressure range was used to predict consumption, weight, and cost for representative types of aircraft the fatigue life of a defect free undercarriage by reference to and missions. J.M.S. the pressure-fatigue life data in the literature. It was found, by this means, that the metallurgical defects had reduced the life of the cylinder by a factor of at least 6 and that they had an N7929951* # Southwest Research Inst., San Antonio, Tex. effective stress concentration factor in fatigue of approximately ENGINE-INDUCED STRUCTURAL-BORNE NOISE IN A 2. The predicted crack growth rate underestimated that observed GENERAL AVIATION AIRCRAFT by a factor of between 2 and 3, but this analysis revealed the James F. Unruh, Dennis C. Scheidt. and Daniel J. Pomerening damaging nature of small fluctuations, in pressure, about a high Aug. 1979 123 p refs mean value. Author (ESA) (Contract NAS1-14861; SwRl Proj. 02-4860) (NASA-CR-159099) Avail: NTIS HC A06/MF AOl CSCL 20A N79-29772# National Technical Information Service. Springfield, Structural borne interior noise in a single engine general Va. aviation aircraft was studied to determine the importance of WIND SHEAR, VOLUME 1. CITATIONS FROM THE NTIS engine induced structural borne noise and to determine the DATA BASE Progress Report, 1964-1975 necessary modeling requirements for the prediction of structural Guy E. Habercom, Jr. Dec. 1978 208 p borne interior noise. Engine attached/detached ground test data (NTIS/PS-78/1314/0) Avail: NTIS HC $28.00/MF $28.00 show that engine induced structural borne noise is a primary CSCL 04B interior noise source for the single engine test aircraft, cabin The phenomena of wind shear effects in various environments noise is highly influenced by responses at the propeller tone, are investigated in these Government-sponsored research reports. and cabin acoustic resonances can influence overall noise levels. Aircraft, spacecraft launchings, atmospheric turbulence, and Results from structural and acoustic finite element coupled models air/water interactions are among the areas reviewed. This updated of the test aircraft show that wall flexibility has a strong influence bibliography contains 203 abstracts, none of which are new on fundamental cabin acoustic resonances, the lightweight entries to the previous edition. GRA fuselage structure has a high modal density, and finite element analysis procedures are appropriate for the prediction of structural borne noise. A.W.H. N79-29800 Virginia Univ., Charlottesville. DESIGN OF A MILTI-MICROPROCESSOR SYSTEM FOR REAL-TIME AIRCRAFT SIMULATION Ph.D. Thesis Young Chang Lee 1978 208 p N79-29958# Kansas Univ. Center for Research. Inc.. Lawrence. Avail: Univ. Microfilms Order No. 7916283 - THE EFFECT OF OBLIQUE ANGLE OF SOUND INCIDENCE, With the use of low cost LSI microprocessors operating in REALISTIC EDGE CONDITIONS, CURVATURE AND parallel, a fast and yet inexpensive modularly constructed aircraft IN-PLANE PANEL STRESSES ON THE NOISE REDUCTION simulator is envisioned. A system architecture that yields effective CHARACTERISTICS OF GENERAL AVIATION TYPE PANELS parallel processing for the special purpose digital computel system Progress Report is presented. Special concern is given to comparisons of the Ferd Grosveld, Jaap Lameris. and David Dunn Jul. 1979 simulation accuracy obtaiable on the multimicroprocessor system 134 p refs
599 N79-29962
(Grant NsG-1301) at a distance of 76 meters (250 feet) are also provided as a (NASA-CR-157452; KU-FRL-41 7-10) Avail: NTIS function of angle around the aircraft during stationary hover HC A07/MF AOl CSCL 20A conditions. GRA Experiments and a theoretical analysis were conducted to predict the noise reduction of inclined and curved panels. These predictions are compared to the experimental results with N79-30134# Air Force Academy, Cob. reasonable agreement between theory and experiment for panels AIR FORCE ACADEMY AERONAUTICS DIGEST, FALL 1978 under an oblique angle of sound incidence. Theoretical as well Final Report as experimental results indicate a big increase in noise reduction E. J. Jumper, M. M. Tower, and John P. Eaton Feb. 1979 when a flat test panel is curved. Further curving the panel slightly 157 p refs decreases the noise reduction. Riveted flat panels are shown to (AD-A069044: USAFA-TR-79- 1) Avail: NTIS give a higher noise reduction in the stiffness-controlled frequency HC A08/MF AOl CSCL 20/4 region, while bonded panels are superior in this region when This digest covers unclassified research in aeronautics the test panel is curved. Experimentally measured noise reduction performed at the United States Air Force Academy during the characteristics _of flat aluminum panels with uniaxial in-plane six months ending 1 January 1979. This report includes individual stresses are presented and discussed. These test results indicate technical papers in the specific areas of aerodynamics, fluid an important improvement in the noise reduction of these panels mechanics, experimental instrumentation, engineering education in the frequency range below the fundamental panel/cavity and thermodynamics and heat transfer. GRA frequency. A.W.H.
N79-29962# Massachusetts Inst. of Tech.. Cambridge. Fluid Dynamics Research Lab. PARAMETRIC STUDIES OF MODEL HELICOPTER BLADE SLAP AND ROTATIONAL NOISE Final Technical Report James E. Hubbard, Jr.. N. G. Humbad, Paul Bauer, and Wesley L. Harris Feb. 1979 93 p refs (Contract DAAG29-76-C-0027l (AD-A068181; ARO-12931.1-EX: Rept-79-1( Avail: NTIS HC A05/MF AOl CSCL 20/1 A parametric study of model helicopter rotor blade slap due to blade/vortex interaction was studied in an anechoic wind tunnel. The parameters studied were blade number, advance ratio, pitch, and shaft angle. The separate effect of each parameter was studied with other parameters held fixed. The intensity of blade slap was found to decrease with an increase in the number of blades, as the advance ratio was increased to a maximum and then decreased with higher advance ratios indicating a blade slap envelope. The intensity of blade slap was observed to be directly proportional to pitch. The intensity increased with increasing pitch until unsteady lift was encountered, at which time the intensity rapidly diminished. As the rotor shaft angle was increased, the intensity of blade slap was found to decrease to a condition of no blade slap. Directivity measurements were made of blade slap due to blade/vortex interaction in the plane normal to the tunnel wrid axis. No blade slap was encountered at the intersection of the rotor disc plane and the plane normal to the tunnel wind axis. The first indication of blade slap occurred at 30 deg below the rotor disc plane and increased in intensity, reaching a maximum intensity at 90 deg below the rotor. In all studies the presence of blade slap was determined subjectively by observing and listening to the transient acoustic signature. G RA
N79-29964# Bolt, Beranek, and Newman, Inc.. Canoga Park, Calif. HELICOPTER NOISE LEVEL FUNCTIONS FOR USE IN COMMUNITY NOISE ANALYSES Final Report William J. Galloway AMRL Wright-Patterson AFB, Ohio Jan. 1979 49 p refs (Contract F33615-76-C-0528l (AD-A068455: BBN-3713: AMR L-TR-78-87( Avail: NTIS HC A03/MF AOl CSCL 01/3 Acoustical data obtained from helicopters in level flight and during 6 degree approaches are used to obtain the variation of A-weighted sound exposure level and effective perceived noise level with distance. These functions are normalized to a reference airspeed which differs for individual helicopter types. Sound level functions at airspeeds different from the reference airspeed, either higher or lower, are obtained by adding a decibel increment to the reference functions. This increment is obtained by multiplying a constant, different for each helicopter, times the square of the difference between the airspeed of interest and the reference airspeed. These data are provided for the following aircraft: CH-3C, CH-47C, CH-54B, HH-53B/C. OH-6A, TH-55A, UH-1N, UH-13. Maximum A-weighted sound levels and perceived noise levels
600 SUBJECT INDEX
AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl. 115) NOVEMBER 1979 Typical Subject Index Listing SUBJECT EXTENSIONTITLE AERODYNAMIC LOADS____["' Aerodynamic data development for the turboprop rSupersOnicunsta].led flutter --- aerodynamic T-44A Operational Flight Trainer I loading of thin airfoils induced by cascade notion [AIAA 79-1637] 579-145317 I [NASA-TM-79001] 1479-11000 A model for unsteady effects in lateral dynamics for use in parameter estimation --- aircraft stability REPORT [AIAA 79-16381 579-145318 NUMBER ACCESSION II The relationship of unsteadiness in downwash to TITLE U ENR the quality of parameter estimates [AlAS 79-1639] A79-145319 Impact of digital computer technology on flight systems The title is used to provide a description of the subject matter. When the title is (AlAS 79-16411 579-45320 insufficiently descriptive of the document content, a title extension is added. Goniometric aerodynamics: A different perspective: separated from the title by three hyphens. The NASA or AIAA accession number Description - Applications --- missile is included in each entry to assist the user in locating the abstract in the abstract configurations section of this supplement. If applicable, a report number is also included as an [AlAS 79-1650] 579-45326 Effects of spanwise blowing on two fighter aid in identifying the document. airplane configurations (5155 79-16631 579-45330 Aerodynamic coefficient estimation by means of an extendedKalman filter [AlAS 79-1686] 579-45346 Subsonic flow past an oscillating cascade with ACCELERATED LIFE TESTS finite mean flow deflection Build 1 of an accelerated mission test of a TF41 [AlAS PAPER 79-15161 A79-46704 with block 76 hardware Opportunities for supersonic performance gains rAD-A0685951 879-28179 through non-linear aerodynamics ACCELERATION (PHYSICS) [AlAS PAPER 79-15273 A79-46710 Azimuth observability enhancement during INS Steady and Unsteady vortex-induced asymmetric in-flight alignment loads - Review and further analysis --- on rAIAS 79-17061 579-145360 slender axisymmetric bodies ACOUSTIC MEASUREMENTS [AIAA PAPER 79-1531] 579-146713 Helicopter noise level functions for use in High Reynolds Number Subsonic Aerodynamics community noise analyses [VKI-LECTURE-SERIES-16) 879-28119 r 50-60681455] 1479-299611 Advantages and problems of large subsonic aircraft ACOUSTIC PROPERTIES N79-28120 The effect of oblique angle of sound incidence, Scaling effects on drag prediction --- wind tunnel realistic edge conditions, curvature and tests in-plane panel stresses on the noise reduction N79-28123 characteristics of general aviation t y pe panels Noise and vibration problems: Outline notes INASA-CF-1574521 1479-29958 U79-28124 ACTUATORS Aerodynamic characteristics of forebody and nose Deformable mirror surface control - Hardware, strakes based on F-16 wind tunnel test algorithms experience. Volume 1: Summary and analysis rATSA 79-17571 579-45393 [NASA-CR-3053] 1479-281113 Theory, design and experimental study of an Longitudinal aerodynamics extracted from flight eddy-current/hydromechanical stability augmentor tests using a parameter estimation method for aircraft I ARL/ABRO-NOTE-379] N79-28144 1479-28 185 Application of vortex lattice method for the ADAPTIVE CONTROL evaluation of the aerodynamic characteristics of Flight test experience with an adaptive control wings with and without strakes system using a maximum likelihood parameter 1479-281145 estimation technique Aerodynamic characteristics of a large-scale 'AlAS 79-17021 579-45357 semispan model with a swept wing and an ADHESIVE BONDING augmented jet flap with hypermixing nozzles Fatigue properties of adhesive-bonded laminated Ames 40- by 80-Foot Wind Tunnel and Static Test sheet material of aluminum alloys Facility [18-276] 1179-295143 [NASA-TM-73236] 1479-291144 ADHESIVES The effect of winglets on the KC-135A aircraft .nvironmental effects on the elastic-plastic tests in the Langley 8 ft transonic pressure properties of adhesives in bond metal joints tunnel RAE-LIB-TRANS-1999] R79-29328 I AD-A068324] N79-29177 AERIAL RUDDERS AERODYIA!IC COEFFICIENTS Folded shear plane control apparatus for aircraft Computation of subsonic and transonic flow about steering and stabilization lifting rotor blades [AlAS 79-16821 579-4531411 [AIAA 79-16671 A79-45333 AERODYNAMIC CHARACTERISTICS Aerodynamic coefficient estimation by means of an Singular perturbation techniques for on-line extended Kalman filter optimal flight path control (AlAS 79-16861 579-45346 15155 79-16201 679-45303 Real-time estimation of aerodynamic coefficients Parallel procedures for aircraft parameter by means of an extended Kalman filter identification and state estimation (SAND-78-2032) 1479-29152 [A1AS 79-1636] 579-45316
A-i
AERODYNAMIC CONFIGURATIONS SUBJECT INDEX
AERODYNAMIC CONFIGURATIONS vechnical evaluation report on the 52nd Symposium Wing design, body design, high lift systems and of the Propulsion and Energetics on Stresses, flying qualities with introduction vibrations, Structural Integration and Engine N79-28125 Integrity (Including Aeroelasticity and Flutter) An aerodynamic analysis of deformed wings in [AGARD-AR-133] 879-28181 subsonic and supersonic flow A method for obtaining practical IAD-A0675861 879-28149 flutter-suppression control laws using results An off design shock capturing finite difference of optimal control theory approach for caret waverider configurations [19ASA-TP-1471] 879-28610 (AD-A068819] 879-28156 AERONAUTICAL ENGINEERING An experimental and theoretical investigation of Composite structural materials the effect of nonmetric over-the-wing nacelles [NASA-CR-158851] 879-28235 on wing-body aerodynamics Spinoff 1979 INASA-FP-15031 879-29146 NASA-TN-80481] 879-29108 AERODYNAMIC DRAG AEROSPACE SYSTEMS M odern concepts for design of delta wings for Atmospheric Flight Mechanics Conference for Future supersonic aircraft of second generation --- for Space Systems, Boulder, Cob., August 6-8, 1979, drag reduction Collection of Technical Papers A79-43993 A79-45302 AERODYNAMIC LOADS AEROSPACE TECHNOLOGY TRANSFER State of the art in aircraft loads monitoring Spinoff 1979 A79-44453 RASA-TN-80481] N79-29108 Determination of sample size in flight loads AIR CARGO programs --- for aircraft structures Disaggregate mode-share models for air freight A79-44454 policy analysis Use of AIDS recorded data for assessing service A79-45249 load experience --- Aircraft Integrated Data Potential applications of advanced aircraft in System developing countries --- Brazil and Indonesia A79-44455 [NASA-TN-80133] 879-28158 Overview of the C-SA Service Loads Recording Program AIR CUSHION LANDING SYSTEMS A79-44456 AALC fan model test program Steady and unsteady vortex-induced asymmetric [ AD-A069058] N79-28372 loads - Review and further analysis --- on AIR INTAKES slender axisymmetric bodies A throat-bypass stability-bleed system using AIAA PAPER 79-1531] A79-46713 relief valves to increase the transient An aerodynamic analysis of deformed wings in stability of a mixed-compression inlet --- YF-12 subsonic and supersonic flow aircraft inlet tests in the Lewis 10 by 10 ft [AD-A067586] 879-28149 supersonic wind tunnel AERODYNAMIC NOISE [NASA-TP-1 083] 879-28176 Noise and vibration problems: Outline notes AIR NAVIGATION 879-28124 Handbook of flight communication and radio equipment y xperimental and theoretical studies on model Russian book helicopter rotor noise A79-44894 tNASA-CR-158844] 879-28984 AIR QUALITY The aerodynamic noise of a slot in an aerofoil Development of criteria for monitoring of airport APC-R/M-38301 N79-29155 ground pollution. Volume 1: Study Parametric studies of model helicopter blade slap (AD-A067242) 879-29197 and rotational noise Development of criteria for monitoring of airport [AD-A0681811 879-29962 ground pollution. Volume 2: Data validation AERODYNAMIC STABILITY procedures Theory, design and experimental study of an (AD-A067243] 879-29198 eddy-cnrrent/hydromechanical stability augmentor AIR TO AIR MISSILES for aircraft A comparison of air-to-air missile guidance laws N79-28185 based on optimal control and differential game AERODYNAMIC STALLING theory Unstable flow regimes, including rotating stall, tAIAA 79-17361 A79-45378 surge, distortions, etc. An improved lateral stability augmentation system N79-28560 for air-to-air tracking AERODYNAMICS [AIAA 79-1773] A79-45402 Atmospheric Flight Nechanics Conference for 5utnre AIR TO SURFACE MISSILES Space Systems, Boulder, Cob., August 6-8, 1979, Guidance law design for tactical weapons with Collection of Technical Papers strapdown seekers A79-45302 [AIAA 79-1732] A79-45376 Investigation of three-dimensional shock/boundary AIR TRAFFIC CONTROL layer interactions at swept compression corners Filtering and threat logic design and evaluation rAIAA PAPER 79-14981 A79-46693 for the beacon collision avoidance system r railing-edge flows at high Reynolds number [AIAA 79-17071 A79-45361 rAIAA PAPER 79-1503] A79-46697 Fuel-conservative guidance system for powered-lift Technique for developing design tools from the aircraft analysis methods of computational aerodynamics [AIAA 79-17091 A79-45363 rAIAA PAPER 79-1529] A79-46711 4-U helical approach of a transport aircraft in an Aeromechanics --- unsteady flow, aeroelasticity, ATC environment flutter, and servocontrol [AIAA 79-1776] A79-45400 N79-28121 Reflection elimination in secondary surveillance Air Force Academy aeronautics digest, fall 1978 radar --- for air traffic control IAD-A069041*1 879-30134 A79-46241 AEROELASTICITY FAA air traffic activity, fiscal year 1978 Application of two synthesis methods for active [AD-A067910] N79-28188 flutter suppression on an aeroelastic wind Aircraft accident report: United Airlines, Inc., tunnel mo1el Douglas DC-8-54, 880470 near Kaysville, Utah, 18 rAIAA 79-1633] A79-45314 December 1977 High Reynolds Number Subsonic Aerodynamics [NTSB-AAR-78-8] 879-29159 VKI-LECTURE-SERIES-161 N79-28119 AIR TRANSPORTATION Aeromechanics --- unsteady flow, aeroelasticity, Potential applications of advanced aircraft in flutter, and servocontrol developing countries --- Brazil and Indonesia N79-28121 tRASA-TM-801331 N79-28158 Injuries in air transport emergency evacuations [AD-A069372] 979-28160
A-2
SUBJECT INDEX AIRCRAFT ENGINES
AIRBORWE,ISPACEBORME COMPUTERS Effects of spanwise blowing on two fighter Dual digital flight control redundancy management airplane configurations system development program (AIAA 79-16631 119-45330 tAIAA 79-1701] A79-45356 Identification of aircraft parameters in The DC-9-80 digital flight guidance system's turbulence with non-rational spectral density monitoring techniques N79-28182 [AIAA 79-17091 A79-45359 AIRCRAFT CONSTRUCTION MATERIALS nescription of the VTOL Approach and Landing Environmental exposure effects on composite Technology (VALT) CH-47 research system materials for commercial aircraft rNAsA-T p-14361 979-29195 [NASA-CR-158838) 919-28232 AIRCRAFT AIRCRAFT CONTROL Construction using carbon fiber composite Gust alleviation using direct turbulence materials and aluminum: A cost comparison measurements F0A-C-20280-F9] 979-29248 [AIAA 79-16741 A19-95339 AIRCRAFT ACCIDENT INVESTIGATION Gust alleviation - Criteria and control laws Injuries in air transport emergency evacuations [AIAA 79-1676] A79-45340 IAD-A0693721 979-28160 Effect of reduced visibility on VIOL handling Aircraft accident report: Rocky Mountain Airways, quality and display requirements Inc., DeHavilland 0HC-6-300, N24BN, Cheyenne, (AIRA 79-1680) 179-45343 Wyoming, 27 February 1979 Folded shear plane control apparatus for aircraft rwrSB-AAR-79-101 979-29157 steering and stabilization Aircraft accident report: Continental Air Lines, [AIAA 79-1682] A79-45349 Inc., Boeing 727-224, 932725, Tucson Arizona, 3 Direct force mode flight control for a vectored June 1977 lift fighter [NTSB-AAR-78-9] 979-29158 [ATAA 79-1744] A79-45386 Aircraft accident report: United Airlines, Inc., Alleviation of stability and control difficulties Douglas DC-8-54, N8047U near Kaysville, Utah, 18 of a V/STOL Type B aircraft December 1977 tAIAA 79-17851 A79-45912 [NTSB-AAR-78-R] 979-29159 Theory, design and experimental study of an Aircraft accident report: Alaska Aeronautical eddy-current/hydromechanical stability augmentor Industries, Inc., DeHavilland DHC-6-200, 956391, for aircraft near Iliamna, Alaska, 6 September 1977 979-28185 [NTSB-78-5] 979-29160 An in-flight simulator investigation of roll and Aircraft accident report: Rational Jet Services, yaw control power requirements for STOL approach Inc., Douglas Dc-3, 951071, Evansville Dress and landing: Development of capability and Regional Airport, Indiana, 13 December 1977 preliminary results NTSB-AAR-78-101 979-29161 [NASA-CR-152307) 879-29196 AIRCRAFT ACCIDENTS AIRCRAFT DESIGN Advanced risk assessment of the effects of Parameter and state estimation applicable to graphite fibers on electronic and electric aircraft identification problem equipment, phase 1 --- simulating vulnerability A19-43946 to airports and communities from fibers released Modern concepts for design of delta wings for during aircraft fires supersonic aircraft of second generation --- for [NASA-CR-159027] 979-28419 drag reduction The analysis of National Transportation Safety A79-43993 Board small single-engine fixed-wing aircraft Atmospheric Flight Mechanics Conference for Future accident/incident reports for the potential Space Systems, Boulder, Cob., August 6-8, 1979, presence of low-level wind shear Collection of Technical Papers AD-A0699381 979-28848 A79-45302 Aircraft accident report: Alaska Aeronautical Application of the equilibrium spin technique to a Industries, Inc., Dellavilland DHC-6-200, N5638A, typical low-wing general aviation design near Iliamna, Alaska, 6 September 1977 tAIAA 79-16251 A79-45301 rNTSB-78-51 979-29160 Parallel procedures for aircraft parameter Aircraft accident report: National Jet Services, identification and state estimation Inc., Douglas DC-3, 951071, Evansville Dress (AIAA 79-1636) A79-45316 Regional Airport, Indiana, 13 December 1977 Impact of digital computer technology on flight 975 B-AAR-78-101 N79-29161 systems AIRCRAFT ANTENNAS [AIAA 79-16411 A19-45320 Aircraft antenna systems --- Russian book An analysis of operational procedures and design A79-44892 modifications for aircraft fuel conservation Aerial isolation - a study of the interaction [AIAA 79-16561 A79-45328 between co-sited aerials --- transmitting and Opportunities for supersonic performance gains receiving aircraft antennas through non-linear aerodynamics A79-46240 (AIAA PAPER 79-1527) A19-46710 AIRCRAFT APPROACH SPACING Technique for developing design tools from the A simulator investigation of roll response analysis methods of computational aerodynamics requirements for aircraft with (AIAA PAPER 79-15291 A79-46711 rate-command/attitude-hold flight control High Reynolds Number Subsonic Aerodynamics systems in the landing approach and touchdown [VET-LECTURE-SERIES- 16) 979-28119 IAIAA 79-16791 A79-45342 Advantages and problems of large subsonic aircraft An analysis of bolter-hole spacing in aircraft N79-28120 carrier landings Wing design, body design, high lift systems and [AD-A068585) 979-29176 flying qualities with introduction AIRCRAFT CARRIERS W79-28125 Development of the Navy H-Dot Automatic Carrier Advanced computer technology in aerodynamics. Landing System designed to give improved Lecture 1: Computer-aided aircraft design approach control in air turbulence W79-28126 IAIAA 79-17721 A79-45401 AIRCRAFT ENGINES An analysis of bolter-hole spacing in aircraft Application of hot isostatic pressing to aircraft carrier landings gas turbines r AD-A068585] N79-29176 A79-45067 AIRCRAFT COMMUNICATION Technical evaluation report on the 52nd Symposium Handbook of flight communication and radio equipment of the Propulsion and Energetics on Stresses, Russian book Vibrations, Structural Integration and Engine A79-44894 Integrity (Including Aeroelasticity and Flutter) AIRCRAFT CONFIGURATIONS (AGARD-AR-133] N79-28181 Propulsion system and airframe integration Advanced General Aviation Turbine Engine (GATE) consideration for advanced air-to-surface aircraft study rAIAA PAPER 79-1120] A79-44800 [NASA-CR-159624) N79-2N185
A-3
AIRCRAFT FURL SYSTEMS SUBJECT INDEX
Aircraft engine driven accessory shaft coupling Maintenance improvement: An analysis approach improvements using high-strength nonmetallic including inferential techniques. Volume 2: adapter/bushings Technical report IAU-A0686371 879-29193 [AD-A068381] 879-28130 Computerized systems analysis and optimization of Maintenance improvement. An analysis approach aircraft engine performance, weight, and life including inferential techniques. Volume 4: cycle costs Software manual rnFSA-TN-79221) 879-29938 (AD-A068383) 879-28131 AIRCRAFT FUEL SYSTEMS Bolted field repair of composite structures Assembly and testing of flight-vehicle hydraulic repairing fuel cell composite wing surfaces and pneumatic systems /2nd enlarged and revised (AD-A067923) 879-28238 edition! --- Russian book AIRCRAFT MANEUVERS A79-44893 The extremal trajectory map - A new representation AIRCRAFT FUELS of combat capability An analysis of operational procedures and design [AIAA 79-1622) A79-45304 modifications for aircraft fuel conservation Numerical computation of optimal evasive maneuvers (AIAA 79-16561 A79-45328 for a realistically modeled airplane pursued by Liquid hydrogen fueled commercial aircraft a missile with proportional guidance A79-45600 (AIAA 79-16241 A79-115306 Ionic mechanisms of carbon formation in flames Azimuth observability enhancement during INS aircraft fuel combustion in-flight alignment r AD-A068872] 879-29270 rAIAA 79-1706] A79-115360 Forecast of future aviation fuels. Part 1: An introduction to co-kill probability estimation Scenarios in the N on N encounter --- during combat INASA-CR-1588711 879-29354 aircraft maneuvers Experimental study of low temperature behavior of (AIAA 79-17291 A79-45373 aviation turbine fuels in a wing tank model Earth-Referenced Maneuvering Flight Path Display (NASA-CS-159615) 879-29355 (ATAR 79-18941 A79-45421 AIRCRAFT GUIDANCE AIRCRAFT MODELS The DC-9-80 digital flight guidance system's Low EM signature response techniques monitoring techniques [AD-A068211] 879-29397 (AIAA 79-17041 A79-115359 AIRCRAFT NOISE Evaluation of the navigation performance of Effects of road traffic background noise on shipboard-VIOL-landing guidance systems judgments of individual airplane noises (AIAA 79-17081 A79-45362 [NASA-TP-1433) 879-28796 Fuel-conservative guidance system for powered-lift Engine-induced structural-borne noise in a general aircraft aviation aircraft rAIRA 79-1709] A79-45363 [NASA-CR-159099] 879-29957 Guidance law design for tactical weapons with The effect of oblique angle of sound incidence, strapdown seekers realistic edge conditions, curvature and (AIAA 79-17321 A79-45376 in-plane panel stresses on the noise reduction Aircraft accident report: United Airlines, Inc., characteristics of general aviation type panels Douglas DC-8-54, N8047U near Eaysville, Utah, 18 rNASA-CR-157452) 879-29958 December 1977 Parametric studies of model helicopter blade slap NTSB-AAR-78-81 N79-29159 and rotational noise AIRCRAFT HYDRAULIC SYSTEMS [AD-A068181) 879-29962 Assembly and testing of flight-vehicle hydraulic Helicopter noise level functions for use in and pneumatic systems /2nd enlarged and revised community noise analyses edition! --- Russian book t AD-A068455] 879-299611 A79-44893 AIRCRAFT PARTS Theory, design and experimental study of an Review of aircraft bearing rejection criteria and eddy-current/hydromechanical stability augmentor causes for aircraft A79-45250 N79-28185 AIRCRAFT PERFORMANCE AIRCRAFT INSTRUMENTS Opportunities for supersonic performance gains Aircraft instrument components /3rd revised and through non-linear aerodynamics enlarged edition! --- Russian book [AIAA PAPER 79-1527] A79-46710 A79-44884 Jet noise and performance comparison study of a Handbook of flight communication and radio equipment Mach 2.55 supersonic cruise aircraft Russian book [NASA-TN-80094] 879-28982 A79-44894 A computer program for detailed analysis of the CR-illl EMC evaluation of selected subsystems, EMC takeoff and approach performance capabilities of test report transport category aircraft AETE-77/16-41 N79-29170 [NASA-TN-80120) 879-29141 AIRCRAFT LANDING Aircraft accident report: Rocky Mountain Airways, Decoupled longitudinal controls for shear Inc., Deflavilland DHC-6-300, N24RM, Cheyenne, penetration in the terminal area environment Wyoming, 27 February 1979 during approach and landing engine jet transport [NTSB-AAR-79-10] 879-29157 rATAR 79-16781 A79-45341 AIRCRAFT PILOTS Development of the Navy H-Dot Automatic Carrier Gust alleviation - Criteria and control laws Landing System designed to give improved (AIRA 79-1676] A79-45340 approach control in air turbulence Preliminary study of pilot lateral control of two tAIRA 79-17721 A79-45401 light airplanes near the stall Initial results of an inflight simulation of [ATAR 79-1775] A79-45403 augmented dynamics in fighter approach and landing AIRCRAFT RELIABILITY tAtAA 7.9-17831 A79-451410 Preliminary airworthiness evaluation 110-21 H An in-flight simulator investigation of roll and guardrail V aircraft yaw control power requirements for STOL approach (AD-A068347) 879-29178 and landing: Development of capability and AIRCRAFT SAFETY preliminary results Use of AIDS recorded data for assessing service SAA-CP-1523071 879-29196 load experience --- Aircraft Integrated Data AIRCRAFT LIGHTS System Internal/external lighting (aviation materiel) A79-44455 1An-80689511 879-28171 Development of computer-generated phenograms to AIRCRAFT MAINTENANCE forecast regional conditions hazardous to ainrnance improvement: An analysis approach low-flying aircraft including inferential techniques. Volume 1: [AD-A068812) 879-28161 vu r view FAA air traffic activity, fiscal year 1978 AD-60681801 879-28129 AD-A0679101 879-28188
A-4
SUBJECT INDEX ALUMINUM ALLOTS
Aviation safety An artificial viscosity method for the design of (GPO-37-810] 879-29162 supercritical airfoils AIRCRAFT STABILITY (NASA-CR-158840] 879-28136 A model for unsteady effects in lateral dynamics An extension to the method of Garabedian and form for use in parameter estimation --- aircraft for the calculation of transonic flow past an stability aerofoil to include the effects of a boundary [AIAA 79-16381 A79-45318 layer and wake The relationship of unsteadiness in downwash to (ARC-R/N-3828] r79-29154 the quality of parameter estimates AIRFOILS IATAA 79-16391 A79-45319 Effect of viscosity on wind-tunnel wall Aerodynamic development of a small horizontal tail interference for airfoils at high lift for an active control relaxed stability [AIAA PAPER 79-1534] 879-46715 transport application The prediction of the turbulent flow field about IAIAA 79-1653) A79-45327 an isolated airfoil Folded shear plane control apparatus for aircraft (AIAA PAPER 79-1543] A79-46719 steering and stabilization Results of an improved version of LTRAN2 for AIAA 79-1682] A79-45344 computing unsteady airloads on airfoils A review of helicopter control-display oscillating in transonic flow requirements for decelarating instrument approach (AIAA PAPER 79-1553] A79-46726 (AIAA 79-16831 679-45345 Unsteady small-gap ground effects Alleviation of stability and control difficulties AD-A0684001 879-28157 of a V/STOL Type B aircraft The aerodynamic noise of a slot in an aerofoil rAIAA 79-17851 A79-45412 [ARC-R/N-3830] W79-29155 AIRCRAFT STRUCTURES AIRFRANES Service fatigue loads monitoring, simulation, and Propulsion system and airframe integration analysis; Proceedings of the Symposium, Atlanta, consideration for advanced air-to-surface aircraft Ga., November 14-15, 1977 (AIAA PAPER 79-11201 879-44800 A79-44451 Investigation of stress-strain history modeling at State of the art in aircraft loads monitoring stress risers, phase 2 A79-44453 (AD'-A069162] 879-28620 Determination of sample size in flight loads Predicted crack repair costs for aircraft structures programs --- for aircraft structures [AD-A068699] 879-29138 A79-44454 Hot salt stress corrosion studies Evaluation of a crack-growth gage for monitoring [AD-A068402] 879-29300 possible structural fatigue-crack growth AIRLINE OPERATIONS A79-44458 Liquid hydrogen fueled commercial aircraft Flight-by-flight spectrum development --- sequence 879-45600 stress analysis for aircraft structures AIRPORT PLANNING A79-44460 Developing a national airport system: Additional Methods of gust spectra prediction for fatigue congressional guidance needed damage (PB-294082/3] 879-28190 A79-44461 AIRPORT TOWERS Application of two synthesis methods for active FAA air traffic activity, fiscal year 1978 flutter suppression on an aeroelastic wind [AD-A067910] 879-28188 tunnel model AIRPORTS (AIAA 79-1633] 879-45314 Development of a structural design procedure for Aerodynamic coefficient estimation by means of an rigid airport pavements extended Kalman filter (AD-A069548] 879-28187 tAIAA 79-16861 A79-45346 Development of criteria for monitoring of airport Hypersonic airframe structures: Technology needs ground pollution. Volume 1: Study and flight test requirements [AD-A067242] 879-29197 [NASA-CN-3130] 879-28168 Development of criteria for monitoring of airport Predicted crack repair costs for aircraft structures ground pollution. Volume 2: Data validation [AD-A068699] 879-29138 procedures Aircraft transparency failure and logistical cost tAD-A0672431 879-29198 analysis. Volume 2: Design data and AIRSHIPS maintenance procedures Goodyear aerospace conceptual design maritime IAD-A0687201 879-29173 patrol airship ZP3G Aircraft transparency failure and logistical cost (AD-A068449] 879-29150 analysis. Volume 3: Transparency analysis ALGORITHMS rAD-A0687211 879-29174 A fast, conservative algorithm for solving the Fnvironmental effects on the elastic-plastic transonic full-potential equation properties of adhesives in bond metal joints (AIAA 79-14561 679-45261 (RAE-LIB-TRANS-1999] 879-29328 Vector processor algorithms for transonic flow New concepts in aircraft journal bearings calculations (80-8068619] 879-29520 [AIAA 79-14571 A79-45273 Proceedings from the Government/Industry Workshop Flight test of a VTOL digital autoland system on the Reliability of Nondestructive Inspections along complex trajectories (AD-A068223] 879-29531 [AIAA 79-1703] 879-45358 N-ray inspection of aircraft structures using Deforinable mirror surface control - Hardware, mobile sources: A compendum of radiographic algorithms results (AIAA 79-17571 A79-45393 (AD-A068316) 879-29532 ALIGNMENT AIRFOIL PROFILES Azimuth observability enhancement during INS T!nsteady wing boundary layer energization in-flight alignment rAIAA 79-16311 A79-45312 [AIAA 79-1706] A79-45360 Transonic flutter analysis of a rectangular wing ALTIMETERS with conventional airfoil sections A study of altimeter-controlled terrain-following tAIAA 79-16321 A79-45313 systems Transonic flow past a symmetrical airfoil at high N79-28162 angle of attack An experimental comparison of the readability of rATAA PAPER 79-15001 A79-46694 two digital altimeters Supercritical airfoil boundary-layer measurements (ARL/SYS-NOTE-60] 879-29180 rAIAA PAPER 79-15011 879-46695 ALUMINUM ALLOTS Opportunities for supersonic performance gains Investigation of stress-strain history modeling at through non-linear aerodynamics stress risers, phase 2 FAIAA PAPER 79-1527] A79-46710 (AD-A069162] 879-28620
A-S
ALUMINUM COATINGS SUBJECT INDEX
Patigue properties of adhesive-bonded laminated ARCHITECTURE (COMPUTERS) sheet material of aluminum alloys Digital flight control reliability - Effects of ILR-2761 N79-29543 redundancy level, architecture and redundancy The effects of gust alleviation on fatigue in management technique 2024-T3 Alciad [AIAP. 79-18931 P.79-45418 r NRL-TR-78064-T1] N79-29544 ARTILLERY FIRE ALUMINUM COATINGS A simulation model of attack helicopter An experimental, low-cost, silicon vulnerability to hostile artillery fire slurry/aluminide high-temperature coatina for [AD-A069753] R79-29179 superalloys ASSEMBLING rNRSA_T8_79178] N79-29292 Assembly and testing of flight-vehicle hydraulic AMPHIBIOUS VEHICLES and pneumatic systems /2nd enlarged and revised ACV cushion comparison tests: Preliminary review edition/ --- Russian book and definition of model and tests A79-44893 [AD-A0688881 N79-28374 ATMOSPHERIC TURBULENCE AMPLIFIERS Gust alleviation using direct turbulence Deformable mirror surface control - Hardware, measurements algorithms [AIP.A 79-1674] P.79-45339 rAIAA 79-17571 P.79-45393 Gust alleviation - Criteria and control laws ANALYTICAL CHEMISTRY [AIAA 79-1676] A79-45340 wear particle analysis of grease samples Development of the Navy H-Dot Automatic Carrier rAD-A0691141 879-29344 Landing System designed to give improved ANGLE OF ATTACK approach control in air turbulence Transonic flow past a symmetrical airfoil at high [AIAA 79-1772] A79-45401 angle of attack Effect of atmospheric turbulence on the stability IAIRA PAPER 79-15001 A79-46694 of a lifting rotor blade ANGLES (GEOMETRY) B79-28183 Goniometric aerodynamics: A different perspective: ATTACK AIRCRAFT Description - Applications --- missile Derivation of flight-by-flight spectra for fighter configurations aircraft --- stress analysis for ground attack IAIRA 79-16501 A79-45326 A79-44462 ANTENNA DESIGN A simulation model of attack helicopter Aircraft antenna systems --- Russian book vulnerability to hostile artillery fire A79-44892 [AD-A069753] N79-29179 Aerial isolation - a study of the interaction ATTITUDE CONTROL between co-sited aerials --- transmitting and An in-flight simulator investigation of roll and receiving aircraft antennas yaw control power requirements for STOL approach P.79-46240 and landing: Development of capability and AN TH HO P0 METR Y preliminary results Wind tunnel test of ACES 2 ejection seat with [NASA-CR-152307] N79-29196 anthropometric dummy in asymmetric configurations AUTOMATIC FLIGHT CONTROL rAD-A0686141 N79-29163 The DC-9-80 digital flight guidance system's APPLICATIONS PROGRAMS (COMPUTERS) monitoring techniques Implementation and testing of numerical analysis [AIAA 79-17041 P.79-45359 techniques in avionics applications Development of a control wheel steering mode and fAD-A0692991 N79-29187 suitable displays that reduce pilot workload and APPROACH improve efficiency and safety of operation in A computer program for detailed analysis of the the terminal area and in windshear takeoff and approach performance capabilities of [P.IP.A 79-1887] P.79-45414 transport category aircraft Digital flight control reliability - Effects of rNASA-TM-801201 N79-29141 redundancy level, architecture and redundancy APPROACH CONTROL management technique Decoupled longitudinal controls for shear [AIAA 79-18931 P.79-45418 penetration in the terminal area environment AUTOMATIC LARDING CONTROL during approach and landing engine jet transport Flight test of a VTOL digital autoland system tAIAA 79-16781 A79-45341 along complex trajectories A simulator investigation of roll response [AIAA 79-17031 P.79-45358 requirements for aircraft with Development of the Navy H-Dot Automatic Carrier rate-command/attitude-hold flight control Landing System designed to give improved systems in the landing approach and touchdown approach control in air turbulence r. AIAA 79-16791 P.79-45342 (AIRA 79-17721 A79-45401 A review of helicopter control-display AUTOMATIC PILOTS requirements for decelarating instrument approach Minimum expected cost control of linear systems TAIAA 79-16831 P.79-45345 with uncertain parameters - Application to Development of the Navy H-Dot Automatic Carrier remotely piloted vehicle flight control systems Landing System designed to give improved [AIAA 79-1745] A79-45387 approach control in air turbulence AUXILIARY POWER SOURCES AJAR 79-17721 P.79-45401 Sensitivity study for a remotely piloted 4-0 helical approach of a transport aircraft in an microwave-powered sailplane used as a LTC environment high-altitude observation rATAP. 79-17761 P.79-45404 [NASA-CR-159089] N79-28134 An in-flight simulator investigation of roll and AVIONICS yaw control power requirements for STOL approach Digital Avionics Information System (DAIS) and landing: Development of capability and Development and demonstration preliminary results [P.D-A068438] N79-29181 rNP.SA-CR-152307] N79-29196 Digital Avionics Information System (DAIS) APPROACH INDICATORS Reliability and maintainability model users Development of a control wheel steering mode and guide, volume 2 --- life cycle costs suitable displays that reduce pilot workload and AD-A068826] 879-29182 improve efficiency and safety of operation in A method for evaluating KC-135 avionics the terminal area and in windshear configurations [AIAA 79-18871 P.79-45414 I AD-A069446] 879-29186 APPROPRIATIONS Implementation and testing of numerical analysis NASA authorization, 1980, volume 1, part 2 techniques in avionics applications [GP0-46-134] N79-29105 (AD-A069299] N79-29187 AXIAL FLOW PUMPS Pump design N79-28567
A-6 P1
SUBJECT INDEX CH-47 HELICOPTER
A computer-aided design method for axial flow BOUNDARY LAYER TRANSITION pumps and fans Application of stability theory to laminar flow W79-28568 control AXIAL FLOW TURBINES [AIAA PAPER 79-1493] A79-46691 Axial turbine performance prediction BRAZIL 879-28561 Potential applications of advanced aircraft in AZISYNNETRIC FLOW developing countries --- Brazil and Indonesia Axisymmetric calculations of transonic wind tunnel [NASA-TM-80133] N19-28158 interference in slotted test sections BYPASSES A79-46060 A throat-bypass stability-bleed system using The effect of blade-to-blade flow variations on relief valves to increase the transient the mean flow-field of a transonic compressor stability of a mixed-compression inlet --- YP-12 rAIBA PAPER 79-15153 A79-46703 aircraft inlet tests in the Lewis 10 by 10 ft Steady and unsteady vortex-induced asymmetric supersonic wind tunnel loads - Review and further analysis --- on [NASA-TP-10833 879-28176 slender axisymmetric bodies IAIAA PAPER 79-15313 A79-46713 C C-S AIRCRAFT B Overview of the C-5A Service Loads Recording Program BACKGROUND NOISE A79-44456 Effects of road traffic background noise on C-118 AIRCRAFT judgments of individual airplane noises Pacific area evaluation of a commercial Omega tHASA-TP-19331 879-28796 navigation system installed in a VC-118 BACKSCATTBRING aircraft, supplement 1 Low EN signature response techniques [AD-A068106] N79-28165 [AD-A068211] 879-29397 C-135 AIRCRAFT BALL BEARINGS The effect of winglets on the KC-135A aircraft Review of aircraft bearing rejection criteria and tests in the Langley 8 ft transonic pressure causes tunnel A79-45250 (AD-A068324] 819-29177 BEACON COLLISION AVOIDANCE SISTER A method for evaluating KC-135 avionics Filtering and threat logic design and evaluation configurations for the beacon collision avoidance system (AD-A069 1146] 879-29186 !ATAA 79-1707) A79-45361 C-141 AIRCRAFT BEARINGS Highlights of the C-191 service life monitoring Stability and nonlinear response of rotor-bearing program systems with squeeze film bearings A79-44457 N79-29519 CANARD CONFIGURATIONS BIBLIOGRAPHIES The effect of canard relative size and vertical Wind shear, volume 1. Citations from the NTIS location on the subsonic longitudinal and data base - lateral-directional static aerodynamic CNTIS/PS-78/1314/01 879-29772 characteristics for a model with a swept forward BIRD-AIRCRAFT COLLISIONS wing --- in the Langley 7i10 ft high speed tunnel Development of computer-generated phenograms to [NASA-TM-78739] N79-28138 forecast regional conditions hazardous to CARBON low-flying aircraft Tonic mechanisms of carbon formation in flames rAD-A0688121 879-28161 aircraft fuel combustion BLOWERS (AD-A068872] 879-29270 Effect of inertia of blower on stability of CARBON FIBERS air-cushion vehicle Advanced risk assessment of the effects of A79-44083 graphite fibers on electronic and electric BODY-WING CONFIGURATIONS equipment, phase 1 --- simulating vulnerability Recent progress in finite-volume calculations for to airports and communities from fibers released wing-fuselage combinations --- transonic during aircraft fires potential flow [NASA-CR-159027] 879-28419 rAIRA PAPER 79-15131 A79-46702 Construction using carbon fiber composite BOLTS materials and aluminum: A cost comparison Bolted field repair of composite structures (FOA-C-20280-F9 3 879-29248 repairing fuel cell composite wing surfaces CARET WINGS rAD-A0679231 879-28238 An off design shock capturing finite difference BONBS (ORDNANCE) approach for caret waverider configurations Interim field procedure for bomb damage repair (AD-A068819] R79-28156 using crushed limestone for crater repairs and CARGO AIRCRAFT silikal trade name for spall repairs Advantages and problems of large subsonic aircraft tAD-A068617 879-28189 N79-28120 BOUNDARY LAYER CONTROL CASCADE FLOW Application of stability theory to laminar flow The effect of blade-to-blade flow variations on control the mean flow-field of a transonic compressor [AIAA PAPER 79-1993] A79-46691 [AIAA PAPER 79-15151 A79-46703 BOUNDARY LAYER EQUATIONS Subsonic flow past an oscillating cascade with Scaling effects on shock-induced separation finite mean flow deflection W79-28122 [AIAA PAPER 79-15161 A79-46704 BOUNDARY LAYER FLOW CENTER OF GRAVITY Numerical solution for the flow field of a body Aircraft accident report: National Jet Services, with jet Inc., Douglas DC-3, 851071, Evansville Dress [ATAA 79-14521 A79-45258 Regional Airport, Indiana, 13 December 1977 Supercritical airfoil boundary-layer measurements (NTSB-AAR-78-10] 979-29161 [ATAA PAPER 79-15011 A79-96695 CENTRIFUGAL PUNPS An extension to the method of Garabedian and Korn Prerotation in centrifugal pumps: Design criteria for the calculation of transonic flow past an N79-28574 aerofoil to include the effects of a boundary CH-46 HELICOPTER layer and wake CH-113 crash position indicator flight trials [ARC-R/N-3828] 879-29154 (AETE-78/39) N79-29156 BOUNDARY LAYER STABILITY CH-47 HELICOPTER The stability of the boundary layer on a swept CH-147 EMC evaluation of selected subsystems, EMC wing with wall cooling test report IAIAA PAPER 79-14951 A79-96692 [AETE-77/16-4] N79-29170
A-i
CHORDS (GEOMETRY) SUBJECT INDEX
Description of the VTOL Approach and Landing COMPUTATIONAL FLUID DYNAMICS Technology (VALT) CH-47 research system A two-dimensional unsteady Euler-equation solver (NASA-TP-1436] 079-29195 for flow regions with arbitrary boundaries CHORDS (GEOMETRY) (AIAA 79-14651 A79-45269 Application of vortex lattice method for the Vector processor algorithms for transonic flow evaluation of the aerodynamic characteristics of calculations wings with and without strakes (AIAA 79-1457] A79-45273 079-28145 Numerical investigation of the perpendicular CHROMATOGRAPHY injector flow field in a hydrogen fueled scramjet Jet engine exhaust analysis by subtractive [AIAA PAPER 79-14821 A79-46686 chromatography An artificial viscosity method for the design of [AD-A067898] 079-28178 supercritical airfoils CIRCULAR CYLINDERS [NASA-CR-1588 110] 079-28136 The influence of turbulence on drag COMPUTER GRAPHICS A79-44874 Advanced computer technology in aerodynamics. Steady and unsteady vortex-induced asymmetric Lecture 1: Computer-aided aircraft design loads - Review and further analysis --- on N79-28126 slender axisymmetric bodies COMPUTER PROGRAMMING IAIAA PAPER 79-1531] A79-46713 Contribution to the calculation of the dynamic CIVIL AVIATION behavior of industrial turbocompressor circuits Aviation safety 079-28564 rGPo-37-8101 079-29162 COMPUTER PROGRAMS CLIMBING FLIGHT Digital flight control reliability - Effects of Approximate trajectory solutions for fighter redundancy level, architecture and redundancy aircraft management technique AIAA 79-16231 A79-45305 (AIAA 79-18931 A79-45418 COLD WORKING Maintenance improvement: An analysis approach Residual surface strain distributions near holes including inferential techniques. Volume 1: which are coidworked to various degrees Overview [AD-A068396] 079-29550 [AD-A068380] 079-28129 COLLISION AVOIDANCE Maintenance improvement: An analysis approach Aviation safety including inferential techniques. Volume 2: rGPO-37-810] 079-29162 Technical report COMBUSTIBLE FLOW [AD-A068381] N79-28130 Numerical investigation of the perpendicular Maintenance improvement. An analysis approach injector flow field in a hydrogen fueled scramjet including inferential techniques. Volume 4: [AIAA PAPER 79-14821 A79-46686 Software manual COMBUSTION (AD-A068383] 079-28131 Laser anemometer measurements at the exit of a Application of vortex lattice method for the T63-C20 combustor evaluation of the aerodynamic characteristics of NASA-CR-159623] 079-28456 wings with and without strakes COMBUSTION CHAMBERS W79-28145 Laser anemometer measurements at the exit of a Advanced risk assessment of the effects of T63-C20 combustor graphite fibers on electronic and electric r NASA-CR-159623] N79-28456 equipment, phase 1 --- simulating vulnerability COMBUSTION PRODUCTS to airports and communities from fibers released Ionic mechanisms of carbon formation in flames during aircraft fires aircraft fuel combustion [NASA-CR-159027] 079-28419 AD-A068872] 079-29270 A gas turbine off-design computing system COMMAND AND CONTROL N79-28563 Development of a control wheel steering mode and Predicted crack repair costs for aircraft structures suitable displays that reduce pilot workload and (AD-A068699] N79-29138 improve efficiency and safety of operation in A computer program for detailed analysis of the the terminal area and in vindshear takeoff and approach performance capabilities of [AIRA 79-18871 A79-45414 transport category aircraft COMMERCIAL AIRCRAFT (NASA-T0-80120] 079-29141 Liquid hydrogen fueled commercial aircraft COMPUTER TECHNIQUES A79-45600 Computerized systems analysis and optimization of Environmental exposure effects on composite aircraft engine performance, weight, and life materials for commercial aircraft cycle costs I NASA-CR-158830] 079-28232 [NASA-TM-79221] 079-29938 COMPONENTS COMPUTERIZED DESIGN Aircraft instrument components /3rd revised and Computer aided design of mixed flow turbines for enlarged edition! --- Russian book turbochargers A79-44884 (ASME PAPER 78-GT-191] A79-44794 COMPOSITE MATERIALS Impact of digital computer technology on flight Environmental exposure effects on composite systems materials for commercial aircraft tAIAR 79-16411 A79-45320 NASA-CP-1588381 079-28232 Technique for developing design tools from the Construction using carbon fiber composite analysis methods of computational aerodynamics materials and aluminum: A cost comparison (AIAA PAPER 79-15291 A79-46711 IFDA-C-20280-F9] 079-29248 Advanced computer technology in aerodynamics. New concepts in aircraft journal bearings Lecture 1: Computer-aided aircraft design I AD-A068619] 079-29520 N79-28126 COMPOSITE STRUCTURES An artificial viscosity method for the design of Bolted field repair of composite structures supercritical airfoils repairing fuel cell composite wing surfaces (NASA-CR-158840] 079-28136 AD-A0679231 079-28238 A gas turbine off-design computing system COMPRESSOR BLADES 079-28563 The effect of blade-to-blade flow variations on Contribution to the calculation of the dynamic the mean flow-field of a transonic compressor behavior of industrial turbocompressor circuits IAIAA PAPER 79-15151 A79-46703 B79-28564 COMPRESSOR ROTORS A computer-aided design method for axial flow Effect of rotor meridional velocity ratio on pumps and fans response to inlet radial and circumferential N79-28568 listortion COMPUTERIZED SIMULATION INA7A-'D-12781 079-28177 Disaggregate mode-share models for air freight policy analysis A79-45249
A-8
SUBJECT INDEX CURVED PANELS
Vector processor algorithms for transonic flow COPOLYMERS calculations Fasil integral fuel tank sealants, part 1 [AIAA 79-1457] A79-45273 (AD-A067889) 879-28329 Experimental and theoretical studies on model CORNER FLOW helicopter rotor noise Investigation of three-dimensional shock/boundary NASA-CR- i5884l) 879-28984 layer interactions at swept compression corners Design of a milti-microprocessor system for [AIAA PAPER 79-141981 A79-46693 real-time aircraft simulation A careful numerical study of tlowfields about N79-29800 external conical corners. I - Symmetric CONCORDE AIRCRAFT configurations Monitoring stratospheric winds with [AIAA PAPER 79-15111 A79-46701 Concorde-generated infrasound CORROSION PREVENTION A79-46225 Techniques for cathodic protection testing over CONCRETES airfield pavements Development of a structural design procedure for [AD-A069045] N79-29200 rigid airport pavements COST ANALYSIS rAD-A0695481 879-28187 Aircraft transparency failure and logistical cost CONFERENCES analysis. Volume 2: Design data and Service fatigue loads monitoring, simulation, and maintenance procedures analysis; Proceedings of the Symposium, Atlanta, [AD-A068720) 879-29173 Ga., November 14-15, 1977 Aircraft transparency failure and logistical cost A79-44451 analysis. Volume 3: Transparency analysis Atmospheric Flight Mechanics Conference for Future [AO-A068721) 879-291744 Space Systems, Boulder, Cob., August 6-8, 1979, Ramjet cost estimating handbook Collection of Technical Papers [AD-A056991) N79-29188 A79-45302 Construction using carbon fiber composite Technical evaluation report on the 52nd Symposium materials and aluminum: A cost comparison of the Propulsion and Energetics on Stresses, [FOA-C-20280-F9] 879-292148 Vibrations, Structural Integration and Engine COST EFFECTIVENESS Integrity (Including Aeroelasticity and Flutter) Propulsion system and airframe integration fAGARD-AR-1331 879-28181 consideration for advanced air-to-surface aircraft Off-design performance of gas turbines, volume 1 [AIAA PAPER 79-11201 A79-44800 conferences, Belgium, Jan.-Feb. 1978 COST ESTIMATES [VKJ-LEC-SER-1978-2-VOL-i] 4479-28555 Minimum expected cost control of linear systems CONGRESSIONAL REPORTS with uncertain parameters - Application to NASA authorization, 1980, volume 1, part 2 remotely piloted vehicle flight control systems tGPO-46-134] 879-29105 [AIAA 79-1745] A79-45387 Aviation safety COUPLINGS fGPO-37-810] 879-29162 Aircraft engine driven accessory shaft coupling CONICAL FLOW improvements using high-strength nonmetallic A careful numerical study of flowfields about adapter/bushings external conical corners. I - Symmetric [AD-A068637] R79-29193 configurations CRACK INITIATION rAr7lA PAPER 79-13111 7.79-146701 Residual surface strain distributions near holes CONTROL CONFIGURED VEHICLES which are coldworked to various degrees Parameter and state estimation applicable to tAD-A0683961 879-29550 aircraft identification problem CRACK PROPAGATION 7.79-43946 Evaluation of a crack-growth gage for monitoring Parallel procedures for aircraft parameter possible structural fatigue-crack growth identification and state estimation A79-44458 (ATAP. 7Q-16361 7.79-45316 CRACKING (FRACTURING) Direct force mode flight control for a vectored Predicted crack repair Costs for aircraft structures lift fighter [AD-A068699] 879-29138 AIAA 79-174141 7.79-145386 CRASH LANDING CONTROL STABILITY Aircraft accident report: Rocky Mountain Airways, Aerodynamic development of a small horizontal tail Inc., DeHavilland DHC-6-300, N24R8, Cheyenne, for an active control relaxed stability Wyoming, 27 February 1979 transport application [NTSB-AAR-79-10) N79-29157 IAIAA 79-16531 A79-45327 CRASHES Direct force node flight control for a vectored CH-113 crash position indicator flight trials lift fighter [AETE-78/39] N79-29156 IAIAA 79-17441 7.79-45386 Aircraft accident report: Rational Jet Services, Initial results of an inflight simulation of Inc., Douglas DC-3, 851071, Evansville Dress augmented dynamics in fighter approach and landing Regional Airport, Indiana, 13 December 1977 [AIAR 79-1783] A79-45410 [NTSB-RAR-78-10] 879-29161 A piloted simulator investigation of helicopter CROSS FLOW precision decelerating approaches to hover to The stability of the boundary layer on a swept determine single-pilot IFR /SPIFR/ requirements wing with wall cooling !AIAA 79-18861 7.79-45413 [AIAA PAPER 79-1 4195] A79-46692 CONTROL SURFACES CRUISE MISSILES Direct force mode flight control for a vectored Analysis, storage, and retrieval of elevation data lift fighter with applications to improve penetration [AIAA 79-174111 7.79-45386 (AD-A068747] 879-28166 CONTROL THEORY CRUISING FLIGHT A method for obtaining practical Approximate trajectory solutions for fighter flutter-suppression control laws using results aircraft of optimal control theory (AIAA 79-16231 A79-115305 INASA-TP-1 1471] 879-286114 CUMULATIVE DAMAGE CONTROLLABILITY Determination of sample size in flight loads An in-flight simulator investigation of roll and programs --- for aircraft structures yaw control power requirements for STOL approach A79-44454 and landing: Development of capability and CURVED PANELS preliminary results The effect of oblique angle of sound incidence, fNASA-CR-1523071 879-29196 realistic edge conditions, curvature and COORDINATE TRANSFORMATIONS in-plane panel stresses on the noise reduction Three-dimensional coordinates about wings characteristics of general aviation type panels rAIAA 79-14611 A79-45265 (NASA-CR-157452) N79-29958
A-9
DATA ACQUISITION SUBJECT INDEX
DIFFUSION WELDING Establishment of manufacturing method and D technology for the fabrication of helicopter DATA ACQUISITION main rotor blade spars by continuous seam Helicopter noise level functions for use in diffusion bonding titanium sheet material community noise analyses (AD-A067590) 879-28170 r AD-A068455] 879-29964 DIGITAL COMPUTERS DATA BASES Impact of digital computer technology on flight Analysis, storage, and retrieval of elevation data systems with applications to improve penetration [AIAA 79-1641] 879-45320 [AD-A068747] 879-28166 DIGITAL NAVIGATION DATA PROCESSING Extremal radio-navigation --- Russian book Information processing for target detection and A79-44878 identification The DC-9-80 digital flight guidance systems [80-8068907 ] 879-28393 monitoring techniques The analysis of National Transportation Safety [8188 79-1704] 879-45359 Hoard small single-engine fixed-wing aircraft DIGITAL SIMULATION accident/incident reports for the potential Alternatives for jet engine control presence of low-level wind shear [NASA-CR-1583901 879-29190 F AD-A069438] 879-28848 DIGITAL SYSTEMS DATA RECORDERS Dual digital flight control redundancy management Use of AIDS recorded data for assessing service system development program load experience --- Aircraft Integrated Data [8188 79-17011 A79-45356 System Flight test of a VTOL digital autoland system 879-44455 along complex trajectories Overview of the C-SA Service Loads Recording Program [8188 79-1703] A79-45358 879-44456 Digital flight control reliability - Effects of DATA REDUCTION redundancy level, architecture and redundancy Review of aircraft hearing rejection criteria and management technique causes [AIAA 79-1893] 879-45418 879-45250 An experimental comparison of the readability of DATA 580018180 two digital altimeters Low EM signature response techniques [APL/S!S-NOTE-60] 879-29180 r AD-A068211] 879-29397 Digital Avionics Information System (DAIS) DC 3 AIRCRAFT Development and demonstration Aircraft accident report: National Jet Services, [80-8068438) 879-29181 Inc., Douglas DC-3, 851071, Evansville Dress DISPLAY DEVICES Regional Airport, Indiana, 13 December 1977 Effect of reduced visibility on VTOL handling [NTSB-AAR-78-10] 879-29161 quality and display requirements DC 8 AIRCRAFT [AIAA 79-1680] 879-45343 Aircraft accident report: United Airlines, Inc., A review of helicopter control-display Douglas DC-8-54, 880470 near Kavsville, Utah, 18 requirements for decelarating instrument approach December 1977 [8188 79-16831 879-45345 INTSB-AkR-78-8] 879-29159 Development of a control wheel steering mode and DR HAVILLAND AIRCRAFT suitable displays that reduce pilot workload and Aircraft accident report: Rocky Mountain Airways, improve efficiency and safety of operation in Inc., DeHavilland DHC-6-300, 82488, Cheyenne, the terminal area and in windshear Wyoming, 27 February 1979 [AIAA 79-1887] A79-45414 FNTSB-AAR-79-101 879-29157 Earth-Referenced Maneuvering Flight Path Display Aircraft accident report: Alaska Aeronautical [AIAA 79-1894] A79-45421 Industries, Inc., DeHavilland DHC-6-200, 8563N8, Display measurements. Measurements of near Iliamna, Alaska, 6 September 1977 reflectance-type displays rNTSB-78-51 879-29160 [AD-A068602] N79-29185 DECELERATION DOWNTIIE A piloted simulator investigation of helicopter Maintenance improvement: An analysis approach precision decelerating approaches to hover to including inferential techniques. Volume 1: determine single-pilot lYR /SPIFR/ requirements Overview IAIAA 79-1886 A79-45413 [AD-A068380] 879-28129 DELTA WINGS Maintenance improvement: An analysis approach Modern concepts for design of delta wings for including inferential techniques. Volume 2: supersonic aircraft of second generation --- for Technical report drag reduction [AD-8068381] 879-28130 A79-43993 Maintenance improvement. An analysis approach A careful numerical study of flowfields about including inferential techniques. Volume 4: external conical corners. I - Symmetric Software manual configurations [AD-A068383) 879-28131 [8188 PAPER 79-1511] 879-46701 DO WI N A SR DESIGN ANALYSIS The relationship of unsteadiness in downwash to Gust alleviation using direct turbulence the quality of parameter estimates measurements [AIAA 79-1639] A79-45319 rAIAA 79-16741 879-45339 DRAG off-design performance of gas turbines, volume 1 An experimental and theoretical investigation of conferences, Belgium, Jan.-Feb. 1978 the effect of nonmetric over-the-wing nacelles [VKI-LEC-SER-1978-2-VOL-1) H79-28555 on wing-body aerodynamics Tho importance of off-design operation [NASA-TP-1503] 879-29146 N79-28556 DRAG REDUCTION Axial turbine performance prediction The influence of turbulence on drag N79-28561 A79-44874 Pump design DYNAMIC CHARACTERISTICS N79-28567 Aeromechanics --- unsteady flow, aeroelasticity, A computer-aided design method for axial flow flutter, and servocontrol pumps and fans N79-28121 N79-28568 Contribution to the calculation of the dynamic Prerotation in centrifugal pumps: Design criteria behavior of industrial turbocompressor circuits N79-28574 N79-28564 DEVELOPING NATIONS Potential applications of advanced aircraft in developing countries --- Brazil and Indonesia [NASA-TN-80133) 879-28158
8-10
SUBJECT INDEX ERROR ANALYSIS
DYNAMIC LOADS ENCOUNTERS Results of an improved version of LTRAN2 for An introduction to co-kill probability estimation computing unsteady airloads on airfoils in the M on N encounter --- during combat oscillating in transonic flow aircraft maneuvers [AIAA PAPER 79-15531 A79-46726 tAIAA 79-17291 A79-45373 DYNAMIC MODELS ENERGY CONSERVATION The relationship of unsteadiness in dovnwash to An analysis of operational procedures and design the quality of parameter estimates modifications for aircraft fuel conservation rAIAA 79-16391 A79-45319 [AIAA 79-16561 A79-45328 Aerodynamic coefficient estimation by means of an ENERGY REQUIREMENTS extended Kalman filter Forecast of future aviation fuels. Part 1: (AIAA 79-16861 A79-45346 Scenarios DYNAMIC RESPONSE (RASA-CR-158871] N79-29354 Longitudinal aerodynamics extracted from flight ENERGY SPECTRA tests using a parameter estimation method Evaluation of flow quality in two NASA transonic [ARL/AENO-ROTE-379] N79-28144 wind tunnels Stability and nonlinear response of rotor-bearing [AIAA PAPER 79-1532] P39-46714 systems with squeeze film bearings ENGINE CONTROL 879-29519 Alternatives for jet engine control DYNAMIC STABILITY [NASA-CN-158390] 879-29190 Longitudinal dynamic stability of a hovering ENGINE DESIGN helicopter with a sling load Computer aided design of mixed flow turbines for A79-44094 turbochargers [ASME PAPER 78-GT-191] A79-44794 Off-design performance of gas turbines, volume 1 E conferences, Belgium, Jan.-Feb. 1978 EARTH RESOURCES [VKI-LEC-SE8-1978-2-VOL-1] 879-28555 Forecast of future aviation fuels. Part 1: The importance of off-design operation Scenarios N79-28556 r NASA-CN-158871 ) 879-29354 The prediction of compressor blade row ECHO SUPPRESSORS performance: Numerical methods and theoretical Reflection elimination in secondary surveillance approaches radar --- for air traffic control N79-28557 A79-46241 three dimensional flow computing system ECONOMIC ANALYSIS applicable to axial and radial flow turbomachines Maintenance improvement: An analysis approach N79-28558 including inferential techniques. Volume 1: Axial turbine performance prediction Overview w79-28561 tAD-A0683801 879-28129 A gas turbine off-design computing system Maintenance improvement: An analysis approach N79-28563 including inferential techniques. Volume 2: Advanced General Aviation Turbine Engine (GATE) Technical report study AD-A0683811 879-28130 [NASA-CE-1596241 N79-29189 Maintenance improvement. An analysis approach ENGINE INLETS including inferential techniques. Volume 4: AALC fan model test program Software manual [AD-A069058) 879-28372 rAo-A068383] 879-28131 Recent applications of theoretical analysis to ECONOMIC DEVELOPMENT V/STOL inlet design Forecast of future aviation fuels. Part 1: (NASA-TN-79211) 879-29143 Scenarios ENGINE NOISE [NASA-cP,-158871 ] 879-293514 Engine-induced structural-borne noise in a general EDDY CURRENTS aviation aircraft Theory, design and experimental study of an (NASA-CR-159099) 879-29957 eddy-current/hydromechanical stability augmentor ENGINE PARTS for aircraft Application of hot isostatic pressing to aircraft N79-28185 gas turbines EJECTION SEATS A79-45067 Wind tunnel test of ACES 2 ejection seat with Build 1 of an accelerated mission test of a TF41 anthropometric dummy in as ymmetric configurations with block 76 hardware rAD-A0686141 879-29163 (AD-A068595) 879-28179 ELECTRIC EQUIPMENT ENGINE TESTING LABORATORIES Advanced risk assessment of the effects of NASA Cr6 jet engine diagnostics program: graphite fibers on electronic and electric Long-term CF6-60 low-pressure turbine equipment, phase 1 --- simulating vulnerability deterioration to airports and communities from fibers released [NASA-CR-159618) 879-29191 during aircraft fires ENGINE TESTS INAsA-CR-159027) 879-28419 NASA Cr6 jet engine diagnostics program: ELECTROMAGNETIC COMPATIBILITY Long-term CF6-60 low-pressure turbine Electromagnetic compatibility (EMC) investigation deterioration on CR147 Chinook helicopter (NASA-CB-159618] 879-29191 IREPT-5330-4479-02) 879-28169 ENTHALPY CH-147 EMC evaluation of selected subsystems, EMC Enthalpies of combustion of ramjet fuels test report A79-46055 AETE-77/16-141 879-29170 ENVIRONMENT EFFECTS ELECTRONIC EQUIPMENT Environmental effects on the elastic-plastic Aircraft accident report: united Airlines, Inc., properties of adhesives in bond metal joints Douglas DC-8-54, R8047U near Eaysville, Utah, 18 [RAE-LIB-TRANS-1999] 879-29328 December 1977 ENVIRONMENTAL TESTS rwTsB-AAR-78-81 879-29159 Experimental study of low temperature behavior of ELEVATION aviation turbine fuels in a wing tank model Analysis, storage, and retrieval of elevation data [NASA-CR-159615] N79-29355 with applications to improve penetration EQUILIBRIUM METHODS rAD-A0687147] 879-28166 Application of the equilibrium spin technique to a ELI VO MS typical low-wing general aviation design An aerodynamic analysis of deformed wings in [AIAA 79-1625] A79-45307 subsonic and supersonic flow ERROR ANALYSIS AD-A0675861 W79-28149 A study of altimeter-controlled terrain-following systems 819-28162
A-i 1
ESTIMATING SUBJECT INDEX
Implementation and testing of numerical analysis An analysis of the low cycle fatigue behavior of techniques in avionics applications the superalloy Rene 95 by strainrange partitioning (AD-A069299] 879-29187 [AD-A068252] N79-29295 ESTIMATING Hot salt stress corrosion Studies A model for unsteady effects in lateral dynamics [AD-A068402] 879-29300 for use in parameter estimation --- aircraft FATIGUE TESTS stability Service fatigue loads monitoring, Simulation, and [AIAA 79-16381 A79-45318 analysis; Proceedings of the Symposium, Atlanta, The relationship of unsteadiness in downwash to Ga., November 14-15, 1977 the quality of parameter estimates A79-44451 IA T AA 79-16391 A79-115319 State of the art in aircraft loads monitoring An introduction to co-kill probability estimation A79-44453 in the N on N encounter --- during combat Determination of sample size in flight loads aircraft maneuvers programs --- for aircraft structures [ATAA 79-17291 A79-45373 A79-44454 EVACUATING (TRANSPORTATION) Overview of the C-5A Service Loads Recording Program Injuries in air transport emergency evacuations A79-144456 [AD-A069372] 879-28160 Highlights of the C-141 service life monitoring EVASIVE ACTIONS program W umerical computation of optimal evasive maneuvers A79-44457 for a realistically modeled airplane pursued by Evaluation of a crack-growth gage for monitoring a missile with proportional guidance possible structural fatigue-crack growth [AIAA 79-16241 A79-45306 A79-44458 EXHAUST GASES Plight spectra development for fighter aircraft Jet engine exhaust analysis by subtractive A79-44459 chromatography Plight-by-flight spectrum development --- sequence [AD-A067898] 879-28178 stress analysis for aircraft structures EXPOSURE A79-44460 Environmental exposure effects on composite Methods of gust spectra prediction for fatigue materials for commercial aircraft damage rNASA-CR-1588381 879-28232 A79-44461 EXTERNAL STORES Derivation of flight-by-flight spectra for fighter Demonstration of aircraft wing/store flutter aircraft --- stress analysis for ground attack suppression systems A79-44462 A79-46238 Test simulation of fighter aircraft maneuver load Wing/store flow-field measurements at transonic spectra speeds using a laser velocimeter A79-44463 [AD-A068328] 879-291149 Fatigue properties of adhesive-bonded laminated sheet material of aluminum alloys [LR-276] 879-29543 F The effects of gust alleviation on fatigue in F-H AIRCRAFT 20214-T3 Alciad Plight test experience with an adaptive control [NRL-TR-78064-D] N79-29544 system using a maximum likelihood parameter An analysis of a programmed load fatigue failure estimation technique [RAE-TN-78078] N79-29562 rAIAA 79-17021 A79-45357 FEDERAL BUDGETS F-iS AIRCRAFT NASA authorization, 1980, volume 1, part 2 Water tunnel visualization of the vortex flows of (GPO-46-134] 879-29105 the P-iS FEEDBACK CONTROL IAIAA 79-16491 A79-45325 Gust alleviation - Criteria and control laws F-16 AIRCRAFT [P.IAA 79-1676] A79-45340 F-16 flight control system redundancy concepts Minimum expected cost control of linear systems (AIAA 79-1771) A79-45400 with uncertain parameters - Application to Aerodynamic characteristics of forebody and nose remotely piloted vehicle flight control systems strakes based on P-16 wind tunnel test [AlAP. 79-1745] P.79-45387 experience. Volume 1: Summary and analysis Design criteria for optimal flight control systems (NASA-C14-30531 879-281113 (P.IAA 79-17821 P.79-45409 F-106 AIRCRAFT FIBER COMPOSITES An improved lateral stability augmentation system Composite structural materials for air-to-air tracking [NASA-CR-158851] 879-28235 FAIAA 79-17731 A79-45402 New concepts in aircraft journal bearings FAILURE ANALYSIS [AD-A068619] 879-29520 Review of aircraft bearing rejection criteria and FIGHTER AIRCRAFT causes Flight spectra development for fighter aircraft A79-45250 P.79-4(4459 Aircraft transparency failure and logistical cost Derivation of flight-by-flight spectra for fighter analysis. Volume 2: Design data and aircraft --- stress analysis for ground attack maintenance procedures A79-44462 AD-A068720] H79-29173 Test simulation of fighter aircraft maneuver load Aircraft transparency failure and logistical cost spectra analysis. Volume 3: Transparency analysis A79-44463 [AD-A068721] 879-291711 The extremal trajectory map - A new representation An analysis of a programmed load fatigue failure of combat capability rRAETp_78078] 879-29562 [P.IAA 79-1622] A79-45304 FATIGUE (MATERIALS) Approximate trajectory solutions for fighter Determination of sample size in flight loads aircraft programs' --- for aircraft structures [AIAA 79-1623] P.79-45305 A79-44454 An analysis of operational procedures and design Fvatuation of a crack-growth gage for monitoring modifications for aircraft fuel conservation possible structural fatigue-crack growth [AIAA 79-16561 P.79-45328 A79-44458 Effects of spanwise blowing on two fighter Flight-by-flight spectrum development --- sequence airplane configurations stress analysis for aircraft structures [AIAA 79-1663] A79-45330 A79-44460 An introduction to co-kill probability estimation Uethods of gust spectra prediction for fatigue in the N on N encounter --- during combat damage aircraft maneuvers A79-4l$461 [AIAA 79-1729] P.79-45373
A-12
SUBJECT INDEX FLIGHT TESTS
Direct force mode flight control for a vectored Direct force mode flight control for a vectored lift fighter lift fighter rAIAA 79-174111 A79-45386 (AlAN 79-171141 - A79-45386 Development of the Navy H-Dot Automatic Carrier Minimum expected cost control of linear systems Landing System designed to give improved with uncertain parameters - Application to approach control in air turbulence remotely piloted vehicle flight control systems rAIAA 79-1772] A79-45401 (AIAA 79-17451 839-45387 Initial results of an inflight simulation of Design criteria for optimal flight control systems augmented dynamics in fighter approach and landing (AIAA 79-17821 A79-45409 rAIAA 79-1783] A79-45410 An experimental investigation of control-display Demonstration of aircraft wing/store flutter requirements for a let-lift VTOL aircraft in the suppression systems terminal area A79-46238 [AD-A068818] 819-28175 water tunnel flow visualization - Insight into Description of the VTOL Approach and Landing complex three-dimensional flow fields --- around Technology (VALT) CH-47 research system fighter aircraft [NASA-TP-1 1136] 879-29195 IATAA PAPER 79-1530] 839-46712 FLIGHT HAZARDS FINANCIAL MANAGEMENT Development of computer-generated phemograms to Developing a national airport system: Additional forecast regional conditions hazardous to congressional guidance needed low-flying aircraft rPB-294082/31 N79-28190 CAD-A0688121 819-28161 FINITE DIFFERENCE THEORY FLIGHT INSTRUMENTS Recent progress in finite-volume calculations for Earth-Referenced Maneuvering Flight Path Display wing-fuselage combinations --- transonic (AIAA 79-18941 A19-45421 potential flow FLIGHT MECHANICS rAIAA PAPER 79-1513] 839-46702 Atmospheric Flight Mechanics Conference for Future An off design shock capturing finite difference Space Systems, Boulder, Cob., August 6-8, 1979, approach for caret waverider configurations Collection of Technical Papers rAD-A068819) 879-28156 A79-45302 FINITE ELEMENT METHOD FLIGHT OPTIMIZATION Finite element methods for inviscid and viscous Approximate trajectory solutions for fighter flow problems aircraft 879-281174 [AlAN 79-16231 A79-45305 Application of a finite element method to FLIGHT PATHS transonic flow problems using an optimal control Singular perturbation techniques for on-line approach optimal flight path control 879-281177 (AlAN 79-1620] A19-45303 Investigation of stress-strain history modeling at arth-Referenced Maneuvering Flight Path Display stress risers, phase 2 [AlAN 79-18981 A79-451321 rAD-A0691621 879-28620 FLIGHT SAFETY FLAME SPECTROSCOPY Aviation safety Ionic mechanisms of carbon formation in flames (GPO-37-810) 879-29162 aircraft fuel combustion FLIGHT SIMULATION CAD-A0688721 W79-29270 The extremal trajectory map - A new representation FLAMMABILITY of combat capability Influence of let fuel on permeation and [AIAA 79-1622] A79-45304 flammability characteristics of graphite epoxy Decoupled longitudinal controls for shear composites penetration in the terminal area environment [AD-A068586] R79-28245 during approach and landing engine jet transport FLIGHT CHARACTERISTICS [AIAA 79-1678] A79-45341 Flight spectra development for fighter aircraft An improved lateral stability augmentation system A79-44459 for air-to-air tracking Design criteria for optimal flight control systems [AIAA 79-17731 A79-45402 (AIAA 79-17821 A79-451109 4-0 helical approach of a transport aircraft in an Preliminary airworthiness evaluation RU-21 H ATC environment guardrail V aircraft [AlAN 79-17761 A19-45404 IAD-A0683117) 879-29178 Initial results of an inflight simulation of FLIGHT CONDITIONS augmented dynamics in tighter approach and landing Effect of reduced visibility on VTOL handling [AIAA 79-17831 A79-45410 quality and display requirements A piloted simulator investigation of helicopter fAIRA 79-16801 A79-45343 precision decelerating approaches to hover to A review of helicopter control-display determine single-pilot IFR /SPIFR/ requirements requirements for decelarating instrument approach [AlAN 79-18861 A79-45413 {AIAA 79-16831 A79-45345 An in-flight simulator investigation of roll and Preliminary study of pilot lateral control of two yaw control power requirements for STOL approach light airplanes near the stall and landing: Development of capability and fAIAA 79-17751 A79-45403 preliminary results FLIGHT CONTROL [NASA-CN-152307] 879-29196 Singular perturbation techniques for on-line FLIGHT SIMULATORS optimal flight path control A simulator investigation of roll response [AIAA 79-16201 A79-45303 requirements for aircraft with Gust alleviation using direct turbulence rate-command/attitude-hold flight control measurements systems in the landing approach and touchdown TTAIAA 79-1674] A79-45339 [AIAA 79-1679] A79-45382 A simulator investigation of roll response FLIGHT TESTS requirements for aircraft with Effects of spanvise blowing on two fighter rate-command/attitude-hold flight control airplane configurations systems in the landing approach and touchdown (AlAN 79-16631 A79-45330 IAIAA 79-16791 A79-45342 Plight test experience with an adaptive control Folded shear plane control apparatus for aircraft system using a maximum likelihood parameter steering and stabilization estimation technique tATAA 79-16821 A79-45344 [AlAN 79-17021 A79-45357 A multi microprocessor flight control system Plight test of a VTOL digital autoland system design principles along complex trajectories [AIAA 79-1700] A79-45355 (AlAN 79-17031 A79-45358 Dual digital flight control redundancy management Azimuth observability enhancement during INS system development program in-flight alignment rAIRA 79-17011 A79-45356 (AlAN 79-17061 A19-45360
A-i 3
FLIGHT TRAINING SUBJECT INDEX
An improved lateral stability augmentation system Evaluation of flow quality in two NASA transonic for air-to-air tracking wind tunnels [AIAA 79-17731 679-45402 [AIAA PAPER 79-1532] #79-46714 Initial results of an inflight simulation of FLOW STABILITY augmented d y namics in fighter approach and landing Application of stability theory to laminar flow IAIAA 79-17831 679-451410 control Longitudinal aerodynamics extracted from flight (AIAA PAPER 79-1493] 679-46691 tests using a parameter estimation method A throat-bypass stability-bleed system using [ARL/AERO-NOTE-379] N79-28144 relief valves to increase the transient CH-113 crash position indicator flight trials stability of a mixed-compression inlet --- YF-12 r AETE-78/39] 879-29156 aircraft inlet tests in the Lewis 10 by 10 ft An experimental comparison of the readability of supersonic wind tunnel two digital altimeters [NASA-TP-1083] N79-28176 [ARL/SYS-NOTE-60] N79-29180 Unstable flow regimes, including rotating stall, unique facility for V/STOL aircraft hover testing surge, distortions, etc. Langley Impact Dynamics Research Facility W79-28560 IRASA-TP-14731 879-29199 PLOW VISUALIZATION FLIGHT TRAINING Unsteady wing boundary layer energization Aerodynamic data development for the turboprop [AIAA 79-16311 A79-45312 I-VIA Operational Flight Trainer Water tunnel visualization of the vortex flows of [A1AA 79-16371 A79-45317 the F-iS FLOW DISTORTION rAIAA 79-1649] A79-45325 'ffect of rotor meridional velocity ratio on Water tunnel flow visualization - Insight into response to inlet radial and circumferential complex three-dimensional flow fields --- around distortion fighter aircraft IWASA-TP-12781 879-28177 [AIAA PAPER 79-1530] #79-46712 PLOW DISTRIBUTION FLUID MECHANICS Numerical solution for the flow field of a body Air Force Academy aeronautics digest, fall 1978 with let [AD-A069044) N79-30134 AIAA 79-14521 679-45258 FLUTTER A fast, conservative algorithm for solving the Aeromechanics --- unsteady flow, aeroelasticity, transonic full-potential equation flutter, and servocontrol fAIAA 79-14561 #79-45261 N79-2812i Three-dimensional coordinates about wings A method for obtaining practical [#166 79-14611 679-45265 flutter-suppression control laws using results Water tunnel visualization of the vortex flows of of optimal control theory the F-is [NASA-TP-1471] N79-28614 (AIAA 79-16491 679-45325 FLUTTER ANALYSIS Numerical investigation of the perpendicular Transonic flutter analysis of a rectangular wing injector flow field in a hydrogen fueled scramjet with conventional airfoil sections [#166 PAPER 79-14821 679-46686 [AIAA 79-1632] #79-45313 Transonic flow past a symmetrical airfoil at high Application of two synthesis methods for active angle of attack flutter suppression on an aeroelastic wind [AIAA PAPER 79-1500] 679-46694 tunnel model Supercritical airfoil boundary-layer measurements [AIAA 79-16331 679-45314 [6166 PAPER 79-15011 #79-116695 Demonstration of aircraft wing/store flutter A careful numerical study of flowfields about suppression systems external conical corners. I - Symmetric A79-46238 configurations Technical evaluation report on the 52nd Symposium [#166 PAPER 79-15111 A79-46701 of the Propulsion and Energetics on Stresses, Recent progress in finite-volume calculations for Vibrations, Structural Integration and Engine wing-fuselage combinations --- transonic Integrity (Including Aeroelasticity and Flutter) potential flow [AGARD-AR-133] 879-28181 [AIAA PAPER 79-15131 679-46702 PLY BY WIRE CONTROL The effect of blade-to-blade flow variations on Flight test experience with an adaptive control the mean flow-field of a transonic compressor system using a maximum likelihood parameter [#166 PAPER 79-1515] #79-46703 estimation technique Subsonic flow past an oscillating cascade with (AIAA 79-1702] A79-45357 finite mean flow deflection F-16 flight control system redundancy concepts [ATAA PAPER 79-15161 679-46704 [ATAA 79-1771] #79-45400 Water tunnel flow visualization - Insight into FRACTURE MECHANICS complex three-dimensional flow fields --- around Highlights of the C-ill service life monitoring fighter aircraft program rAIAA PAPER 79-15301 679-46712 A79-44457 Evaluation of flow quality in two NASA transonic Proceedings from the Government/Industry Workshop wind tunnels on the Reliability of Nondestructive Inspections [AIAA PAPER 79-15321 679-46714 (A0-A068223] N79-29531 The prediction of the turbulent flow field about FREE FLOW an isolated airfoil The influence of turbulence on drag IAIAA PAPER 79-15431 679-46719 A79-44874 Scaling effects on shock-induced separation FREQUENCY MEASUREMENT N79-28122 Peak Stronhal frequency of subsonic let noise as a Prerotation in centrifugal pumps: Design criteria function of Reynolds number N79-28574 (AIAA PAPER 79-15251 A79-46709 Wing/store flow-field measurements at transonic FRICTION speeds using a laser velocimeter Friction and wear characteristics of wire-brush [AD-A068328] 879-29149 skids FLOW EQUATIONS tRASA-TP-14951 879-29171 A two-dimensional unsteady Euler-equation solver FUEL COMBUSTION for flow regions with arbitrary boundaries Enthalpies of combustion of ramjet fuels [AIAA 79-14651 679-115269 #79-46055 FLOW GEOMETRY Ionic mechanisms of carbon formation in flames Unsteady wing boundary layer energization aircraft fuel combustion rAIAA 79-1631] A79-45312 [AD-A068872] N79-29270 PLOW MEASUREMENT FUEL CONSUMPTION Supercritical airfoil boundary-layer measurements An analysis of operational procedures and design [AIAA PAPER 79-15011 #79-46695 modifications for aircraft fuel conservation [AIAA 79-1656] A79115328
A-ill
SUBJECT INDEX BEAT TRANSFER
Fuel-conservative guidance system for powered-lift GLASS FIBERS aircraft New concepts in aircraft journal bearings [AIAA 79-1709] A79-45363 (AD-A068619] 879-29520 FUEL FLOW GLIDERS Numerical investigation of the perpendicular Sensitivity study for a remotely piloted injector flow field in a hydrogen fueled scranjet microwave-powered sailplane used as a rAIAR PAPER 79-1482) A79-46686 high-altitude observation FUEL INJECTION [NASA-CR-159089] 879-28134 Numerical investigation of the perpendicular GLOBAL POSITIONING SYSTEM injector flow field in a hydrogen fueled scramjet The global positioning system /RAVSTAR/ tAIAA PAPER 79-14821 A79-46686 A79-46466 FUEL TANKS Investigation of a preliminary GPS receiver design Fasil integral fuel tank sealants, part 1 for general aviation AD-A0678891 879-28329 (AD-A069059) 879-29164 FUEL TESTS GONIORETERS The temperature at which thermal dissociation is Goniometric aerodynamics: A different perspective: initiated in jet fuels under static conditions Description - Applications --- missile A79-44953 configurations FULL SCALE TESTS [AIAA 79-1650] A79-45326 Application of the equilibrium spin technique to a GOVERNMENT PROCUREMENT typical low-wing general aviation design Developing a national airport system: Additional ATAA 79-1625] A79-45307 congressional guidance needed [PB-294082/31 879-28190 GRAPHITE-EPDXY COMPOSITE MATERIALS G Bolted field repair of composite structures GAME THEORY repairing fuel cell composite wing surfaces The extremal trajectory map - A new representation (AD-A0679231 879-28238 of combat capability Influence of jet fuel on permeation and tAIAA 79-16221 P.79-45304 flammability characteristics of graphite epoxy A comparison of air-to-air missile guidance laws composites based on optimal control and differential game [AD-A068586] N79-28245 theory Advanced risk assessment of the effects of IAIAA 79-17361 A79-45378 graphite fibers on electronic and electric GAS BEARINGS equipment, phase 1 --- simulating vulnerability Evaluation of stiffness and damping coefficients to airports and communities from fibers released for fluid-film bearings during aircraft fires N79-28367 [NASA-CR-159027) 879-28419 GAS TURBINE ENGINES GREASES Application of hot isostatic pressing to aircraft Near particle analysis of grease samples gas turbines (AD-A0691141 879-29344 A79-45067 GROUND EFFECT Laser anemometer measurements at the exit of a Unsteady small-gap ground effects T63-C20 combustor AD-A068400] 879-28157 rNASA-C8-159623] 879-28456 GROUND EFFECT (AERODYNAMICS) Advanced General Aviation Turbine Engine (GATE) Low speed wind tunnel test of ground proximity and study deck edge effects on a lift cruise fan V/STOL INASA-CR-159624] 879-29189 configuration, volume 2 An experimental, low-cost, silicon (NASA-CR-1522 118) 879-28142 slurry/aluminide high-temperature coating for GROUND EFFECT MACHINES sup era lloys Effect of inertia of blower on stability of fNASA-TN-791781 879-29292 air-cushion vehicle Gas turbine engines and transmissions for bus P.79-44083 demonstration programs A study of requirements, model configurations, and [COO-4867-1) 879-29522 test plans for air cushion system comparison tests GAS TURBINES [AD-A0690061 N79-28373 Off-design performance of gas turbines, volume 1 ACV cushion comparison tests: Preliminary review conferences, Belgium, Jan.-Feb. 1978 and definition of model and tests r VKI-LEC-SER-1978-2-VOL-1] N79-28555 (AD-A068880) R79-28374 The importance of off-design operation GUST ALLEVIATORS 879-28556 Gust alleviation using direct turbulence The prediction of compressor blade row measurements performance: Numerical methods and theoretical [AIRA 79-1674] A79-45339 approaches Gust alleviation - Criteria and control laws N79-28557 [AIAA 79-16761 A79-45340 P gas turbine off-design computing system GUST LOADS N79-28563 Methods of gust spectra prediction for fatigue Problems involved in starting and shutdown of gas damage turbines: Thermodynamic and mechanical aspects A79-44461 N79-28565 GAS-GAS INTERACTIONS Numerical solution for the flow field of a body with jet HARRIER AIRCRAFT rAIAA 79-14521 P.79-45258 Alleviation of stability and control difficulties GENERAL AVIATION AIRCRAFT of a V/STOL Type 8 aircraft Application of the equilibrium spin technique to a [AIAP. 79-1785] A79-45412 typical low-wing general aviation design HEAT RESISTANT ALLOYS rAIAA 79-16251 A79-45307 An experimental, low-cost, silicon Investigation of a preliminary uPS receiver design slurry/aluminide high-temperature coating for for general aviation superalloys rkD-A0690591 N79-29164 [NASA-TN-79178] 879-29292 Advanced General Aviation Turbine Engine (GATE) An analysis of the low cycle fatigue behavior of study the superalloy Rene 95 by strainrange partitioning rNP.sA-CR-159624] 879-29189 (AD-A068252] N79-29295 The effect of oblique angle of sound incidence, HEAT TRANSFER realistic edge conditions, curvature and Air Force Academy aeronautics digest, fall 1978 in-plane panel stresses on the noise reduction AD-A0690441 879-30134 characteristics of general aviation type panels IN&SA-CR-1574521 879-29958
A-iS
HEAVY LIFT HELICOPTERS SUBJECT INDEX
HEAVY LIFT HELICOPTERS HYPERSONIC VEHICLES Longitudinal dynamic stability of a hovering Hypersonic airframe structures: Technology needs helicopter with a sling load and flight test requirements P.79-44094 (NASA-CR-3130] 879-28168 HELICOPTER CONTROL A piloted simulator investigation of helicopter precision decelerating approaches to hover to determine single-pilot IFR /SPIFR/ requirements IDENTIFYING rAmP. 79-18861 A79-45413 Parameter and state estimation applicable to HELICOPTER PERFORMANCE aircraft identification problem longitudinal dynamic stability of a hovering A79-43946 helicopter with a sling load IMPACT DAMAGE P.79-44094 Interim field procedure for bomb damage repair P. review of helicopter control-display using crushed limestone for crater repairs and requirements for decelarating instrument approach silikal trade name for spall repairs rAlAP. 79-1683] A79-45345 [AD-A068617) 1179-28189 HELICOPTER WAKES IMPACT PREDICTION An iterative lifting surface method for thick Optimal missile guidance for low miss and bladed hovering helicopter rotors perpendicular impact I ATAP. PAPER 79-15171 P.79-46705 [P.IP.A 79-1734] P.79-45377 HELICOPTERS IN-FLIGHT MONITORING Experimental and theoretical studies on model State of the art in aircraft loads monitoring helicopter rotor noise A79-44453 [NASA-CR-1588441 879-28984 INCOMPRESSIBLE FLUIDS P. simulation model of attack helicopter The panel method for subsonic aerodynamic flow: A vulnerability to hostile artillery fire survey of mathematical formulations and rAD-A0697531 879-29179 numerical models with an outline of the new Helicopter noise level functions for use in British aerospace scheme community noise analyses N79-28475 I P.D-A0684551 879-29961 INDONESIA HIGH ALTITUDE Potential applications of advanced aircraft in Sensitivity study for a remotely piloted developing countries --- Brazil and Indonesia microwave-powered sailplane used as a (NASA-TM-80133] 879-28158 high-altitude observation INERTIAL GUIDANCE [NP.SA-CR-1590891 879-28134 Evaluation of the navigation performance of HOLE DISTRIBUTION (MECHANICS) shipboard-VTOL-landing guidance systems Bolted field repair of composite structures (AIlA 79-17081 179-45362 repairing fuel cell composite wing surfaces INERTIAL NAVIGATION P.D-A067923] 879-28238 Azimuth observability enhancement during INS HORIZONTAL TAIL SURFACES in-flight alignment Aerodynamic development of a small horizontal tail tAIP.A 79-17061 P.79-45360 for an active control relaxed stability A method for evaluating KC-135 avionics transport application configurations lATAP. 79-16531 179-45327 AD-A069446) 879-29186 HOT PRESSING INFORMATION SYSTEMS Application of hot isostatic pressing to aircraft Digital Avionics Information System (DAIS) gas turbines Development and demonstration A79-45067 [AD-P.068438] N79-29181 HOVERING Digital Avionics Information System (DAIS) P. unique facility for V/STOL aircraft hover testing Reliability and maintainability model users Langley Impact Dynamics Research Facility guide, volume 2 --- life cycle costs rNP.sP.-To-14731 879-29199 P.0-10688261 879-29182 HOVERING STABILITY INFRASONIC FREQUENCIES 'ffect of inertia of blower on stability of monitoring stratospheric winds with air-cushion vehicle Concorde-generated infrasound A79-44083 Longitudinal dynamic stability of a hovering INLET FLOW helicopter with a sling load Effect of rotor meridional velocity ratio on A79-44094 response to inlet radial and circumferential Alleviation of stability and control difficulties distortion of a V/STOL Type B aircraft (NASA-TP-1 278] 879-28177 thIP.P. 79-17851 P.79-45412 Recent applications of theoretical analysis to A piloted simulator investigation of helicopter V/STOL inlet design precision decelerating approaches to hover to (NASA-TM-79211] 879-29143 determine single-pilot IFR /SPIFP/ requirements INSPECTION r ATAP. 79-18861 679-45413 8-ray inspection of aircraft structures using HYDRAULIC TEST TUNNELS mobile sources: A compendum of radiographic Water tunnel visualization of the vortex flows of results the F-is [AD-A068316] 879-29532 P.P. 79-16491 P.79-45325 INSTRUMENT APPROACH Water tunnel flow visualization - Insight into A review of helicopter control-display complex three-dimensional flow fields --- around requirements for decelarating instrument approach fiq hter aircraft (AIAA 79-1683] P.79-45345 IAIP.A PAPER 79-15301 179-46712 INSTRUMENT FLIGHT RULES HYDROCARBON FUELS A piloted simulator investigation of helicopter The temperature at which thermal dissociation is precision decelerating approaches to hover to initiated in jet fuels under static conditions determine single-pilot IFR /SPI?R/ requirements A79-44953 (AlAP. 79-18861 A79-45413 Enthalpies of combustion of ramjet fuels INTERFERENCE LIFT A79-46055 Effect of viscosity on wind-tunnel wall HYDROGEN FUELS interference for airfoils at high lift Liquid hydrogen fueled commercial aircraft (P.IAA PAPER 79-15341 P.79-46715 A79-45600 INVISCID FLOW Numerical investigation of the perpendicular Finite element methods for inviscid and viscous injector flow field in a hydrogen fueled scramjet flow problems IATP.A PP.°BP 79-14821 P.79-46686 N79-28474
A-16
SUBJECT INDEX LIFE CYCLE COSTS
The panel method for subsonic aerodynamic flow: A survey of mathematical formulations and numerical models with an outline of the new L British aerospace scheme LAMINAR BOUNDARY LATER H79-28475 Application of stability theory to laminar flow ISOLATION control Aerial isolation - a study of the interaction (AIAA PAPER 79-1493] A19-86691 between co-sited aerials --- transmitting and The stability of the boundary layer on a swept receiving aircraft antennas wing with wall cooling A70- 46240 (AIAA PAPER 79-14951 A79-46692 ISOSTATIC PRESSURE LAMINAR PLOW Application of hot isostatic pressing to aircraft Numerical solution for the flow field of a body gas turbines with jet A79-45067 [AIAA 79-14521 A79-45258 The prediction of the turbulent flow field about an isolated airfoil J [AIAA PAPER 79-1543] P.79-46719 JET AIRCRAFT NOISE LAMINAR FLOW AIRFOILS Peak Strouhal frequency of subsonic jet noise as a Application of stability theory to laminar flow function of Reynolds number control rAIAA PAPER 79-1525] A79-46709 (AIAA PAPER 79-1493] A79-46691 Jet noise and performance comparison study of a LAMINATES Mach 2.55 supersonic cruise aircraft Fatigue properties of adhesive-bonded laminated NASA-TN-800941 879-28982 sheet material of aluminum alloys JET ENGINE FUELS (LE-276) 879-29543 The temperature at which thermal dissociation is LASER DOPPLER V!LOCINETERS initiated in jet fuels under static conditions Laser anemometer measurements at the exit of a A79-44953 T63-C20 combustor Enthalpies of combustion of ramjet fuels [NASA-CR-159623] 879-28456 A79-46055 Wing/store flow-field measurements at transonic Influence of jet fuel on permeation and speeds using a laser velocimeter flammability characteristics of graphite epoxy [AD-A068328] 879-29149 composites LATERAL CONTROL rAn-A0685861 879-28245 A simulator investigation of roll response Continuation study of alternate fuels nitrogen requirements for aircraft with chemistry rate-command/attitude-hold flight control (AD-A0690111 879-29359 systems in the landing approach and touchdown Analysis of the emissions from storage tanks [AIAA 79-1679] A79-145342 during JP-4 fuel transfer operations. Phase 1: Preliminary study of pilot lateral control of two Warm weather conditions light airplanes near the stall [AD-A069339) 879-29364 tAIAA 79-17751 A79-45403 JET ENGINES LATERAL STABILITY Jet engine exhaust analysis by subtractive A model for unsteady effects in lateral dynamics chromatography for use in parameter estimation --- aircraft fAD-A0678981 879-28178 stability Alternatives for jet engine control (AIAA 79-16381 A79-45318 NASA-CR-1583901 879-29190 An improved lateral stability augmentation system JET FLAPS for air-to-air tracking Aerodynamic characteristics of a large-scale [AIAA 79-1773] A79-145402 semispan model with a swept wing and an Preliminary study of pilot lateral control of two augmented jet flap with hypermixing nozzles light airplanes near the stall Ames 40- by 80-Foot Wind Tunnel and Static Test [AIAA 79-1775] A79-115403 Facility LEADING EDGE SWEEP TNASA-TN-73236] N79-29144 Water tunnel flow visualization - Insight into JET FLOW complex three-dimensional flow fields --- around Numerical solution for the flow field of a body fighter aircraft with jet [AIBA PAPR 79-1530] A79-46712 rAIAP. 79-14521 P.79-45258 Application of vortex lattice method for the JET LIFT evaluation of the aerodynamic characteristics of Wing aerodynamic loading caused by jet-induced wings with and without strakes lift associated with STOL-OTW configurations N79-28145 (NASA-TM-792181 879-28146 LEADING EDGES JOURNAL BEARINGS Transonic flow past a symmetrical airfoil at high New concepts in aircraft journal bearings angle of attack AD-A068619] 879-29520 [ATAA PAPER 79-1500] A79-116694 LEAST SQUARES METHOD Application of a finite element method to transonic flow problems using an optimal control KALE AN FILTERS approach Aerodynamic coefficient estimation by means of an N79-28477 extended Kalman filter LIFE (DURABILITY) [ATAA 79-16861 A79-45346 Derivation of flight-by-flight spectra for fighter Filtering and threat logic design and evaluation aircraft --- stress analysis for ground attack for the beacon collision avoidance system A79-44462 rATAA 79-17071 A79-45361 LIFE CYCLE COSTS Real-time estimation of aerodynamic coefficients Aircraft transparency failure and logistical Cost by means of an extended Kalman filter analysis. Volume 2: Design data and fSAND-78-20321 879-29152 maintenance procedures KARMAN VORTEX STREET AD-A068720] 1179-29173 Steady and unsteady vortex-induced asymmetric Aircraft transparency failure and logistical cost loads - Review and further analysis --- on analysis. Volume 3: Transparency analysis slender axisymmetric bodies (AD-A068721] 879-29174 fAIAA PAPER 79-15311 A79-46713 Digital Avionics Information System (DAIS) Reliability and maintainability model users guide, volume 2 --- life cycle costs (AD-A068826] 1179-29182 Ramjet cost estimating handbook [AD-A056991] N79-29188
A-17
LIFT DEVICES SUBJECT INDEX
Computerized systems analysis and optimization of LOGISTICS aircraft engine performance, weight, and life Aircraft transparency failure and logistical cost cycle costs analysis. Volume 2: Design data and NASA-T11-79221 J 1179-29938 maintenance procedures LIFT DEVICES [AD-A068720] 1179-29173 Unsteady small-gap ground effects Aircraft transparency failure and logistical cost [AD-A06814001 1179-28157 analysis. Volume 3: Transparency analysis LIFT DRAG RATIO [AD-A068721] 1179-29174 Scaling effects on drag prediction --- wind tunnel LONGITUDINAL CONTROL tests Decoupled longitudinal controls for shear 1179-28123 penetration in the terminal area environment LIFT PANS during approach and landing engine jet transport Low speed wind tunnel test of ground proximity and [AIRA 79-1678] A79-45341 deck edge effects on a lift cruise fan V/STOL LONGITUDINAL STABILITY configuration, volume 2 Longitudinal dynamic stability of a hovering [NASA-CR-152248] 1179-281142 helicopter with a sling load LIFTING BODIES A79-44094 An iterative lifting surface method for thick The relationship of unsteadiness in downwash to bladed hovering helicopter rotors the quality of parameter estimates (ATAti PAPER 79-15171 A79-46705 (AIAA 79-16391 A79-45319 LIFTING ROTORS LOW PRESSURE Computation of subsonic and transonic flow about NASA Cr6 jet engine diagnostics program: lifting rotor blades Long-term CF6-6D low-pressure turbine fAIAA 79-16671 A79-45333 deterioration Effect of atmospheric turbulence on the stability [NASA-C4l-159618] 1179-29191 of a lifting rotor blade LOW TEMPERATURE N79-28183 Experimental study of low temperature behavior of LIGHT AIRCRAFT aviation turbine fuels in a wing tank model Preliminary study of pilot lateral control of two [NASA-CR-1 59615] 1179-29355 light airplanes near the stall LOW WING AIRCRAFT rAIRA 79-17751 A79-45403 Application of the equilibrium spin technique to a LIGHTING EQUIPMENT typical low-wing general aviation design Internal/external lighting (aviation materiel) [AIAA 79-1625] A79-145301 tAD-A068951" 1179-28171 LUBRICANTS LINEAR SYSTEMS Wear particle analysis of grease samples Parameter and state estimation applicable to AD-A069114] 1179-29344 aircraft identification problem A79-43946 LIQUID BEARINGS M Evaluation of stiffness and damping coefficients EACH REFLECTION for fluid-film bearings A two-dimensional unsteady Euler-equation solver W79-28367 for flow regions with arbitrary boundaries LIQUID COOLING (AIAA 79-14651 A79-452149 The stability of the boundary layer on a swept MAINTAINABILITY wing with wall cooling A multi microprocessor flight control system [AIAA PAPER 79-1495] A79-46692 design principles LIQUID CRYSTALS (AIAA 79-17001 A79-45355 Display measurements. Measurements of Digital Avionics Information System (DAIS) reflectance-type displays Reliability and maintainability model users [AD-A068602) 1179-29185 guide, volume 2 --- life cycle costs LIQUID HYDROGEN (AD-A068826] 1179-29182 Liquid hydrogen fueled commercial aircraft MAINTENANCE A79-45600 Predicted crack repair costs for aircraft structures The stability of the boundary layer on a swept [AD-A0686991 1179-29138 wing with wall cooling MAN MACHINE SYSTEMS AIAA PAPER 79-14951 A79-46692 Development of a control wheel steering mode and LOAD TESTS suitable displays that reduce pilot workload and The effects of gust alleviation on fatigue in improve efficiency and safety of operation in 2024-T3 Alclad the terminal area and in windshear I NRL-TP-78064-U] W79-29544 (AIAA 79-1887] A79-45414 An analysis of a programmed load fatigue failure MANAGEMENT METHODS FAE-TR-780781 W79-29562 Maintenance improvement: An analysis approach LOADS (FORCES) including inferential techniques. Volume 1: Service fatigue loads monitoring, simulation, and Overview analysis; Proceedings of the Symposium, Atlanta, (AD-A068380) 1179-28129 Ga., November 14-15, 1977 Maintenance improvement: An analysis approach A79-44451 including inferential techniques. Volume 2: Use of AIDS recorded data for assessing service Technical report load experience --- Aircraft Integrated Data [AD-A068381] N79-28130 System Maintenance improvement. An analysis approach A79-44455 including inferential techniques. Volume 4: Evaluation of a crack-growth gage for monitoring Software manual possible structural fatigue-crack growth (AD-A068383] 1179-28131 A79-44458 MANAGEMENT PLANNING Flight spectra development for fighter aircraft Forecast of future aviation fuels. Part 1: A79-44459 Scenarios Flight-by-flight spectrum development --- sequence tNASA-CR-158871) 1179-29354 stress analysis for aircraft structures MANUAL CONTROL A79-44460 Development of a control wheel steering mode and Derivation of flight-by-flight spectra for fighter suitable displays that reduce pilot workload and aircraft --- stress analysis for ground attack improve efficiency and safety of operation in A79-44462 the terminal area and in windshear Test simulation of fighter aircraft maneuver load [AIAA 79-18871 A79-45414 spectra MAPPING A79-44463 Analysis, storage, and retrieval of elevation data LOGIC DESIGN with applications to improve penetration Filtering and threat logic design and evaluation (AD-A068747) H79-28166 for the beacon collision avoidance system (AIAA 79-17071 A79-45361
A-i 8
SUBJECT INDEX MOUNTAINS
MARINE RUDDERS MIDAIR COLLISIONS Folded shear plane control apparatus for aircraft Aviation safety steering and stabilization (GPO-37-810] 879-29162 (8188 79-16821 #79-45344 MILITARY AIRCRAFT MARITIME SATELLITES State of the art in aircraft loads monitoring Good year aerospace conceptual design maritime A79-44453 patrol airship ZP3G Propulsion system and airframe integration [AD-A068449] 879-29150 consideration for advanced air-to-surface aircraft MATERIALS HANDLING (8188 PAPER 79-1120) 879-44800 Analysis of the emissions from storage tanks MILITARY HELICOPTERS during JP-4 fuel transfer operations. phase 1: Electromagnetic compatibility (EMC) investigation Warm weather conditions on CR147 Chinook helicopter [AD-A069339] 879-29364 [REPT-5330-4479-02] 079-28169 MATHEMATICAL MODELS MINICOMPUTERS A model for unsteady effects in lateral dynamics Dual digital flight control redundancy management for use in parameter estimation --- aircraft system development program stability IAIAA 79-1701] 879-45356 [A'AA 79-16381 879-45318 MIRRORS The prediction of the turbulent flow field about Deformable mirror surface control - Hardware, an isolated airfoil algorithms rP.IAA PAPER 79-15431 879-46719 (8188 79-17571 #79-45393 Longitudinal aerodynamics extracted from flight MISS DISTANCE tests using a parameter estimation method Optimal missile guidance for low miss and ARL/AERO-NOTE-3791 879-28144 perpendicular impact A study of altimeter-controlled terrain-following [AIAA 79-17341 819-45377 systems A comparison of air-to-air missile guidance laws R79-28162 based on optimal control and differential game The panel method for subsonic aerodynamic flow: A theory survey of mathematical formulations and [AIAA 79-1736] #79-45378 numerical models with an outline of the new MISSILE CONFIGURATIONS British aerospace scheme Goniometric aerodynamics: A different perspective: N79-28475 Description - Applications --- missile Development of criteria for monitoring of airport configurations ground pollution. Volume 1: Study [AIAA 79-16501 879-45326 tAD-A0672421 879-29197 MISSILE CONTROL Development of criteria for monitoring of airport Numerical computation of optimal evasive maneuvers ground pollution. Volume 2: Data validation for a realistically modeled airplane pursued by procedures a missile with proportional guidance AD-A0672431 879-29198 (AIAA 19-16241 #79-45306 MAXIMUM LIKELIHOOD ESTIMATES Optimal missile guidance for low miss and Parallel procedures for aircraft parameter perpendicular impact identification and state estimation (AIAA 79-1734] #79-45377 rAIAA 79-16361 879-45316 A comparison of air-to-air missile guidance laws Flight test experience with an adaptive control based on optimal control and differential game system using a maximum likelihood parameter theory estimation technique (AIAA 79-1736] 879-45378 [AIAA 79-17021 #79-45357 MISSILE DESIGN MEASURING INSTRUMENTS Atmospheric Flight Mechanics Conference for Future Evaluation of a crack-growth gage for monitoring Space Systems, Boulder, Cob., August 6-8, 1979, possible structural fatigue-crack growth Collection of Technical Papers A79-44458 A79-45302 MECHANICAL DEVICES MISSILE LAUNCHERS Aircraft instrument components /3rd revised and A comparison of air-to-air missile guidance laws enlarged edition! --- Russian book based on optimal control and differential game A79-44884 theory MECHANICAL PROPERTIES (AIAA 79-1736] #79-45378 Environmental exposure effects on composite MISSILE TRACKING materials for commercial aircraft An improved lateral stability augmentation system NASA-CR-1588381 N79-28232 for air-to-air tracking MERIDIONAL FLOW (AIAA 79-17731 A79-45402 Effect of rotor meridional velocity ratio on MISSILE TRAJECTORIES response to inlet radial and circumferential Analysis, storage, and retrieval of elevation data distortion with applications to improve penetration rNASA-T p-12781 079-28177 [AD-A068747] 879-28166 METAL BONDING MODELS Environmental effects on the elastic-plastic A study of requirements, model configurations, and properties of adhesives in bond metal joints test plans for air cushion system comparison tests BAE-LIB-TRANS-19991 879-29328 (AD-A069006] 079-28373 MICROPROCESSORS MODULUS OF ELASTICITY A multi microprocessor flight control system Development of a structural design procedure for design principles rigid airport pavements [#188 79-17001 #79-45355 (AD-A069548] R79-28187 Design of a nilti-microprocessor system for MONITORS real-time aircraft simulation The DC-9-80 digital flight guidance system's 879-29 800 monitoring techniques MICROWAVE ANTENNAS (#188 79-17041 #79-45359 Aerial isolation - a study of the interaction NOTION STABILITY between co-sited aerials --- transmitting and Effect of atmospheric turbulence on the stability receiving aircraft antennas of a lifting rotor blade A79-46240 N79-28183 MICROWAVE SCANNING BEAM LANDING SYSTEM MOTOR VEHICLES Evaluation of the navigation performance of Gas turbine engines and transmissions for bus shipboard-VTOL-landing guidance systems demonstration programs #188 79-17081 879-45362 (COO-4867-1] 019-29522 MICROWAVES MOUNTAINS Sensitivity study for a remotely piloted Aircraft accident report: United Airlines, Inc.. microwave-powered sailplane used as a Douglas DC-8-54, 880470 near Kaysville, Utah, 18 high-altitude observation December 1977 rNASA-CR-1590891 879-28134 [NTSB-AAR-18-8] 879-29159
1-19
MULTIPROCESSING (COMPUTERS) SUBJECT INDEX
MULTIPROCESSING (COMPUTERS) N-ray inspection of aircraft structures using A multi microprocessor flight control system mobile sources: A compendum of radiographic design principles results (AIAA 79-17001 A79-45355 AD-A0683161 879-29532 Design of a milti-microprocessor system for NONLINEAR SYSTEMS real-time aircraft simulation Opportunities for supersonic performance gains W79-29800 through non-linear aerodynamics -(AIAA PAPER 79-1521) A19-46710 NONUNIFORM FLOW Unsteady small-gap ground effects NACELLES [AD-A068400] 819-28151 Recent applications of theoretical analysis to NOSE FINS V/STOL inlet design Aerodynamic characteristics of forebody and nose (NASA-TM-79211] 879-29183 strakes based on F-16 wind tunnel test NASA PROGRAMS experience. Volume 1: Summary and analysis NASA authorization, 1980, volume 1, part 2 fNP.SA-CB-30531 819-28143 rGPo-46-1341 879-29105 NOSES (FOREBODIES) Spinoff 1979 Rater tunnel visualization of the vortex flows of NASA-TM-80481 1 879-29108 the F-iS NAVIGATION AIDS (AIAA 79-16491 P.19-45325 FTandbook of flight communication and radio equipment NOTCH TESTS Russian book The effects of gust alleviation on fatigue in A79-44894 2024-13 Alclad Electromagnetic compatibility (EMC) investigation [NRL-TR-78064-U) 879-29588 on CR187 Chinook helicopter NOZZLES [REPT-5J30-4879-02] 879-28169 Aerodynamic characteristics of a large-scale NAVIGATION INSTRUMENTS semispan model with a swept wing and an Extremal radio-navigation --- Russian book augmented jet flap with hypermixing nozzles A79-44878 Ames 40- by 80-Foot Wind Tunnel and Static Test NAVIGATION SATELLITES Facility Extremal radio-navigation --- Russian book [NASA-TN-73236) 819-29144 A79-44878 NUMERICAL ANALYSIS NAVIGATION TECHNOLOGY SATELLITES A careful numerical study of flovfields about The global positioning system /NAVSTAR/ external conical corners. I - Symmetric A79-46466 configurations NAVSTAR SATELLITES (AIRA PAPER 79-1511] P.79-46701 The global positioning system /NAVSTAR/ Finite element methods for inviscid and viscous A79-46466 flow problems Investigation of a preliminary GPS receiver design W79-28474 for general aviation The panel method for subsonic aerodynamic flow: A AD-A0690591 N79-29164 survey of mathematical formulations and NETWORK SYNTHESIS numerical models with an outline of the new Design criteria for optimal flight control systems British aerospace scheme [AIAA 79-17821 A79-45409 N19-28475 NEUTRON SOURCES The computation of vortex flows by panel methods N-ray inspection of aircraft structures using N79-28482 mobile sources: A compendum of radiographic The prediction of compressor blade row results performance: Numerical methods and theoretical IAD-A0683161 879-29532 approaches NITROGEN COMPOUNDS N79-28557 Continuation study of alternate fuels nitrogen Implementation and testing of numerical analysis chemistry techniques in avionics applications r. A0-A069011] 879-29359 I AD- P.069299) N79-29187 NOISE INTENSITY NUMERICAL CONTROL Engine-induced structural-borne noise in a general Flight test of a VTOL digital autoland system aviation aircraft along complex trajectories [NASA-CR-159 099] 879-29957 [AIAP. 79-1703] P.79-45358 NOISE MEASUREMENT NUMERICAL FLOW VISUALIZATION Effects of road traffic background noise on P. two-dimensional unsteady Euler-equation solver judgments of individual airplane noises for flow regions with arbitrary boundaries rBASA-TP-14331 N79-28796 (AIAA 79-1465] A79-45269 Engine-induced structural-borne noise in a general Vector processor algorithms for transonic flow aviation aircraft calculations rNAsA-CR-1590991 879-29957 (AIP.A 79-14571 P.79-45273 NOISE REDUCTION Jet noise and performance comparison study of a ach 2.55 supersonic cruise aircraft 0 NASA-TN-800981 879-28982 OMEGA NAVIGATION SYSTEM P. computer program for detailed analysis of the Pacific area evaluation of a commercial Omega takeoff and approach performance capabilities of navigation system installed in a VC-118 transport category aircraft aircraft, supplement 1 rNP.SA-TM-801201 879-29181 [AD-A068106] N79-28165 Enqine-induced structural-borne noise in a general ON-LINE PROGRAMMING aviation aircraft Singular perturbation techniques for on-line I NASA-CR-159099] 879-29957 optimal flight path control The effect of oblique angle of sound incidence, (AIAA 79-16201 P.19-45303 realistic edge conditions, curvature and ONBOARD EQUIPMENT in-plane panel stresses on the noise reduction Aircraft antenna systems --- Russian book characteristics of general aviation type panels A79-44892 I NASA-CP-157452J 879-29958 CH-147 EPIC evaluation of selected subsystems, EMC NOISE SPECTRA test report Peak Strouhal frequency of subsonic jet noise as a [AETE-77/16-4] 879-29170 function of Peynolds number OPTICAL TRACKING r AIAA PAPER 79-15251 A79-46709 Deformable mirror surface control - Hardware, NONDESTRUCTIVE TESTS algorithms Procoerlings from the Government/Industry Workshop (AIAA 79-1757] P.79-45393 on the Peliability of Nondestructive Inspections OPTIMAL CONTROL I AD-AO4223) 879-29531 Extremal radio-navigation --- Russian book A79-44878
A-20
SUBJECT INDEX POTENTIAL FLOW
Singular perturbation techniques for on-line Axial turbine performance prediction optimal flight path control 879-28561 CAIAA 79-16201 A79-45303 Problems involved in starting and shutdown of gas Numerical computation of optimal evasive maneuvers turbines: Thermodynamic and mechanical aspects for a realistically modeled airplane pursued by 879-28565 a missile with proportional guidance Prerotation in centrifugal pumps: Design criteria (AIAA 79-16241 A79-45306 879-28574 Application of two synthesis methods for active PERFORMANCE TESTS flutter suppression on an aeroelastic wind Assembly and testing of flight-vehicle hydraulic tunnel model and pneumatic systems /2nd enlarged and revised rAIAA 79-16331 A79-45314 edition! --- Russian book Gust alleviation - Criteria and control laws A79-4t1893 rATAA 79-16761 A79-45340 Internal/external lighting (aviation materiel) Optimal missile guidance for low miss and [AD-A068951] 879-28171 perpendicular impact AALC fan model test program [AIAA 79-1734] A79-95377 (AD-A069058] 879-28372 A comparison of air-to-air missile guidance laws NASA CF6 jet engine diagnostics program: based on optimal control and differential game Long-term C1'6-6D low-pressure turbine theory deterioration AIAA 79-17361 A79-45378 [NASA-CR-159618] 879-29191 Design criteria for optimal flight control systems PERMEABILITY AIAA 79-17821 A79-45409 Influence of jet fuel on permeation and Application of a finite element method to flammability characteristics of graphite epoxy transonic flow problems using an optimal control composites approach (AD-A068586) 879-28245 879-28477 PIEZOELECTRIC GAGES A method for obtaining practical Oeformable mirror surface control - Hardware, flutter-suppression control laws using results algorithms of optimal control theory (AIAA 79-17571 679-45393 tNASA-TP-1471] 879-28614 PILOT PERFORMANCE OPTIMIZATION Effect of reduced visibility on VTOL handling Pump design quality and display requirements 879-28567 [AIAR 79-1680) A79-45343 OSCILLATING PLOW Initial results of an inflight simulation of Subsonic flow past an oscillating cascade with augmented dynamics in fighter approach and landing finite mean flow deflection [AIAA 79-17831 679-45410 [AINA PAPER 79-1516] A79-46704 PILOT TRAINING Aerodynamic data development for the turboprop T-446 Operational Flight Trainer P IAIAA 79-16371 A79-45317 PARALLEL COMPUTERS PIPELINES Parallel procedures for aircraft parameter Techniques for cathodic protection testing over identification and state estimation airfield pavements [AIAA 79-1636] 679-45316 AD-A069045] 879-29200 PARAMETERIZATION PITCH (INCLINATION) Longitudinal aerodynamics extracted from flight Longitudinal aerodynamics extracted from flight tests using a parameter estimation method tests using a parameter estimation method ARL/AERO-NOTE-3791 N79-28144 [ARL/AERO-NOTE-379] 879-28144 Parametric studies of model helicopter blade slap Parametric studies of model helicopter blade slap and rotational noise and rotational noise tAD-A0681811 879-29962 AD-A0681811 879-29962 PARTICLE SIZE DISTRIBUTION PLATES (STRUCTURAL MEMBERS) Wear particle analysis of grease samples Low EM signature response techniques (AD-A0691141 879-29344 [AD-A068211] 879-29397 PASSENGER AIRCRAFT Residual surface strain distributions near holes Advantages and problems of large subsonic aircraft which are coidworked to various degrees N79-28120 [AO-A068396] 879-29550 PATROLS PNEUMATIC EQUIPMENT Goodyear aerospace conceptual design maritime Assembly and testing of flight-vehicle hydraulic patrol airship ZP3G and pneumatic systems /2nd enlarged and revised AD-A0684491 879-29150 edition/ --- Russian book PAVEMENTS A79-4L4893 Development of a structural design procedure for POLICIES rigid airport pavements Disaggregate mode-share models for air freight UAD-60695481 879-28187 policy analysis Interim field procedure for bomb damage repair A79-45249 using crushed limestone for crater repairs and POLLUTION MONITORING silikal trade name for spall repairs Development of criteria for monitoring of airport 160-6068617] 879-28189 ground pollution. Volume 1: Study Techniques for cathodic protection testing over [AD-A067242] 879-29197 airfield pavements Development of criteria for monitoring of airport AD-A069045] 879-29200 ground pollution. Volume 2: Data validation PENETRATION procedures Analysis, storage, and retrieval of elevation data tAD-A0672431 879-29198 with applications to improve penetration PORTABLE EQUIPMENT 1AD-A0687471 879-28166 H-ray inspection of aircraft structures using PERFORMANCE PREDICTION - mobile sources: A compendum of radiographic Off-design performance of gas turbines, volume 1 results conferences, Belgium, Jan.-Feb. 1978 [AD-A068316) 879-29532 VI-LNC-SER-1978-2-VOL-11 879-28555 POSITION INDICATORS The importance of off-design operation Earth-Referenced Maneuvering Flight Path Display R79-28556 [AIAA 79-1894] A79-45421 The prediction of compressor blade row CH-113 crash position indicator flight trials performance: Numerical methods and theoretical [AET!-78/39] N79-29156 approaches POTENTIAL FLOW W79-28557 Recent progress in finite-volume calculations for Unstable flow regimes, including rotating stall, wing-fuselage combinations --- transonic surge, distortions, etc. potential flow N79-28560 [AIAA PAPER 79-1513) A79-46702
6-21
POTENTIAL THEORY SUBJECT INDEX
POTENTIAL THEORY Low EM signature response techniques A three dimensional flow computing system AD-A0682111 879-29397 applicable to axial and radial flow turbomachines RADAR TARGETS N79-28558 Low EM signature response techniques POWER SPECTRA [60-6068211) 879-29397 Peak Strouhal frequency of subsonic jet noise as a RADIO COMMUNICATION function of Reynolds number Handbook of flight communication and radio equipment AIAA PAPER 79-15251 A79-46709 Russian book POWERED LIFT AIRCRAFT A79-4489q Fuel-conservative guidance system for powered-lift RADIO NAVIGATION aircraft Extremal radio-navigation --- Russian book AIAA 79-17091 A79-45363 A79-44878 PREDICTION ANALYSIS TECHNIQUES Pacific area evaluation of a commercial Omega Scaling effects on drag prediction --- wind tunnel navigation system installed in a VC-118 tests aircraft, supplement 1 879-28123 [AD-A068106] N79-28165 PRESSURE DISTRIBUTION RADIO RECEIVERS An iterative lifting surface method for thick Investigation of a preliminary GPS receiver design bladed hovering helicopter rotors for general aviation rATRA PAPER 79-1517] 679-46705 [AD-A069059) N79-29164 PRESSURE DRAG RADIOGRAPHY Scaling effects on drag prediction --- wind tunnel N-ray inspection of aircraft structures using tests mobile sources: A compendum of radiographic 879-28123 results PRESSURE GRADIENTS rAD-60683161 N19-29532 Adverse pressure gradients effects on supersonic RA!JET ENGINES boundary layer turbulence Enthalpies of combustion of ramjet fuels (6166 PAPER 79-15631 679-46730 A79-46055 PROBABILITY THEORY Ramjet cost estimating handbook An introduction to co-kill probability estimation (60-6056991] 879-29188 in the N on N encounter --- during combat REAL TIME OPERATION aircraft maneuvers Real-time estimation of aerodynamic coefficients tAIAA 79-17291 679-45373 by means of an extended Kalman filter PRODUCTION ENGINEERING [SAND-78-2032] 879-29152 Ramjet cost estimating handbook Design of a milti-microprocessor system for AD-A056991 ] N79-29188 real-time aircraft simulation PROPELLER FANS N79-29800 AALC fan model test program RECTANGULAR WINGS [AD-A0690581 N79-28372 Transonic flutter analysis of a rectangular wing PROPULSION SYSTEM PERFORMANCE with conventional airfoil sections Propulsion system and airframe integration (6166 79-1632] A79-45313 consideration for advanced air-to-surface aircraft REDUNDANCY r AIAA PAPER 79-11201 679-44800 Dual digital flight control redundancy management Computerized systems analysis and optimization of system development program aircraft engine performance, weight, and life (AIAA 19-17011 679-45356 cycle costs F-16 flight control system redundancy concepts [NASA-TM-79221' 879-29938 (AIAA 79-1771] 679-45400 PROTECTIVE COATINGS Digital flight control reliability - Effects of An experimental, low-cost, silicon redundancy level, architecture and redundancy slurry/aluminide high-temperature coating for management technique superalloys [AIAA 79-1893] A79-45418 rNASA-TN-791781 879-29292 REFLECTANCE PSYCROACOUSTICS Display measurements. Measurements of Effects of road traffic background noise on reflectance-type displays judgments of individual airplane noises [AD-A068602] 879-29185 [NASA-TP-14331 879-28796 RELIABILITY Digital Avionics Information System (DAIS) Reliability and maintainability model users 0 guide, volume 2 --- life cycle costs QUALITY CONTROL (AD-60688261 N79-29182 Review of aircraft bearing rejection criteria and RELIABILITY ANALYSIS causes Digital flight control reliability - Effects of A79-45250 redundancy level, architecture and redundancy Proceedings from the Government/Industry Workshop management technique on the Reliability of Nondestructive Inspections [AIAA 79-18931 A79-45418 t AD-6068223] N79-29531 RELIABILITY ENGINEERING QUEUEING THEORY A multi microprocessor flight control system An analysis of bolter-bole spacing in aircraft design principles carrier landings [AIAA 79-1100] 679-45355 AD-A068585] 879-29176 REMOTE REGIONS Potential applications of advanced aircraft in developing countries --- Brazil and Indonesia R [NASA-TM-80133] N19-28158 RADAR ANTENNAS REMOTELY PILOTED VEHICLES Reflection elimination in secondary surveillance Minimum expected cost control of linear systems radar --- for air traffic control with uncertain parameters - Application to 679-46241 remotely piloted vehicle flight control systems RADAR ECHOES (AIAA 79-1745) A79-45387 Reflection elimination in secondary surveillance Sensitivity study for a remotely piloted radar --- for air traffic control microwave-powered sailplane used as a A79-46241 high-altitude observation RADAR NAVIGATION [NASA-CR-159089] N79-28134 Evaluation of the navigation performance of RENE 95 shipboard-VTOL-landing guidance systems An analysis of the low cycle fatigue behavior of rAIAA 79-1708] A79-45362 the superalloy Rene 95 by strainrange partitioning RADAR SIGNATURES (60-6068252] N79-29295 Information processing for target detection and RESEARCH AND DEVELOPMENT identification NASA authorization, 1980, volume 1, part 2 AD-A0689071 N79-28393 [GPO-46-134] N79-29105
A-22 SUBJECT INDEX SHOCK WAVES
RESEARCH FACILITIES Interim field procedure for bomb damage repair A unique facility for V/STOL aircraft hover testing using crushed limestone for crater repairs and Langley Impact Dynamics Research Facility silikal trade name for spall repairs (RASA-TP-1473] P79-29199 [AD-A068617] P79-28189 RESIDUAL STRESS Residual surface strain distributions near holes which are coidworked to various degrees rAD-A0683961 R79-29550 SAFETY FACTORS REYNOLDS NUMBER Injuries in air transport emergency evacuations Trailing-edge flows at high Reynolds number (AD-A069372] H79-28160 IAIAA PAPER 79-15031 A79-46697 SATELLITE NAVIGATION SYSTEMS Peak Strouhal frequency of subsonic jet noise as a The global positioning system /RAVSTAR/ function of Reynolds number A79-46466 rAIAA PAPER 79-15251 A79-46709 SCALE EFFECT High Reynolds Number Subsonic Aerodynamics Scaling effects on shock-induced separation VKI-LECTURE-SERTES-161 P79-28119 N79-28122 RISK Scaling effects on drag prediction --- wind tunnel Advanced risk assessment of the effects of tests graphite fibers on electronic and electric W79-28123 equipment, phase 1 --- simulating vulnerability SCALE MODELS to airports and communities from fibers released ACV cushion comparison tests: Preliminary review during aircraft fires and definition of model and tests rPASA-CR-159027] P79-28919 (AD-A068888] P79-28374 ROLLER BEARINGS SCHEDULING Review of aircraft bearing rejection criteria and An analysis of bolter-hole spacing in aircraft causes carrier landings A79-45250 AD-A0685851 P79-29176 ROTARY VIRUS SEALERS Computation of subsonic and transonic flow about Fasil integral fuel tank sealants, part 1 lifting rotor blades [AD-A067889] 979-28329 rATAR 79-16671 P39-45333 SECONDARY RADAR An iterative lifting surface method for thick Reflection elimination in secondary surveillance bladed hovering helicopter rotors radar --- for air traffic control [AIAA PAPER 79-15171 A79-46705 A79-46241 Establishment of manufacturing method and SEDIMENTS technology for the fabrication of helicopter Continuation study of alternate fuels nitrogen main rotor blade spars by continuous seam chemistry diffusion bonding titanium sheet material [AD-A069011] P79-29359 (AD-A067590] P79-28170 SEMISPAR MODELS Experimental and theoretical studies on model Aerodynamic characteristics of a large-scale helicopter rotor noise semispan model with a swept wing and an [NASA-CR-158844) N79-28984 augmented jet flap with hypermixing nozzles Parametric studies of model helicopter blade slap Ames 40- by 80-Foot Wind Tunnel and Static Test and rotational noise Facility [AD-A0681811 P79-29962 [NASA-TN-73236) ROTOR AERODYNAMICS SENSITIVITY Computation of subsonic and transonic flow about Sensitivity study for a remotely piloted lifting rotor blades microwave-powered sailplane used as a rAIAA 79-1667] A79-45333 high-altitude observation Effect of rotor meridional velocity ratio on [RASA-CR-159089) P79-28134 response to inlet radial and circumferential SEPARATED FLOW distortion Transonic flow past a symmetrical airfoil at high (NASA-IP-1278] P79-28177 angle of attack Evaluation of stiffness and damping coefficients [AIAA PAPER 79-15001 979-96694 for fluid-film bearings Scaling effects on shock-induced separation N79-28367 W79-28122 Experimental and theoretical studies on model SERVICE LIFE helicopter rotor noise Service fatigue loads monitoring, simulation, and r NASA-CR-15884 141 P79-28984 analysis; Proceedings of the Symposium, Atlanta, Parametric studies of model helicopter blade slap Ga., November 19-15, 1977 and rotational noise A79-44451 (AD-A068181) 979-29962 Overview of the C-SA Service Loads Recording Program ROTOR BLADES 979-44456 An iterative lifting surface method for thick Highlights of the C-141 service life monitoring bladed hovering helicopter rotors program [ATAA PAPER 79-1517] P39-46705 A79-44457 ROTOR BLADES (TURBOMACRIWERY) S ER V OCON T ROL Subsonic flow past an oscillating cascade with Aeromechanics --- unsteady flow, aeroelasticity, finite mean flow deflection flutter, and servocontrol AIAA PAPER 79-15161 A79-46704 N79-28121 Establishment of manufacturing method and SHAFTS (MACHINE ELEMENTS) technology for the fabrication of helicopter Aircraft engine driven accessory shaft coupling main rotor blade spars by continuous seam improvements using high-strength nonmetallic diffusion bonding titanium sheet material adapter/bushings [AD-A067590] P79-28170 [AD-A068637] P79-29193 ROTOR SPEED SHIPS Unsteady wing boundary layer energization A study of requirements, model configurations, and tAIAA 79-16311 739-45312 test plans for air cushion system comparison tests ROTORS [AD-A0690061 N79-28373 Stability and nonlinear response of rotor-bearing SHOCK WAVE INTERACTION systems with squeeze film bearings Investigation of three-dimensional shock/boundary P79-29519 layer interactions at swept compression corners RUNWAYS (AIAA PAPER 79-1498) A79-46693 Development of a structural design procedure for SHOCK WAVES rigid airport pavements Scaling effects on shock-induced separation 1 P.D-A069548] P79-28187 P79-28122 An off design shock capturing finite difference approach for caret waverider configurations (AD-9068819] P79-28156
A-23
SHORT TAKEOFF AIRCRAFT SUBJECT INDEX
SHORT TAKEOFF AIRCRAFT STARTING Wing aerodynamic loading caused by jet-induced Problems involved in starting and shutdown of gas lift associated with STOL-OTW configurations turbines: Thermodynamic and mechanical aspects fNASA-TR-792181 N79-28146 P79-28565 An in-flight simulator investigation of roll and STATE VECTORS yaw control power requirements for STOL approach Parameter and state estimation applicable to and landing: Development of capability and aircraft identification problem preliminary results A79-43946 rNASA-cR-1523071 N79-29196 STATIC AERODYIARIC CHARACTERISTICS SHUTDOWNS The effect of canard relative size and vertical Problems involved in starting and shutdown of gas location on the subsonic longitudinal and turbines: Thermodynamic and mechanical aspects lateral-directional static aerodynamic N79-28565 characteristics for a model with a swept forward SIGNAL PROCESSING wing --- in the Langley 7x10 ft high speed tunnel Extremal radio-navigation --- Russian book (NASA-TM-78739] 979-28138 A79-44878 STATIC STABILITY Guidance law design for tactical weapons with Aerodynamic development of a small horizontal tail strapdown seekers for an active control relaxed stability tAIAA 79-17321 A79-45376 transport application Information processing for target detection and [AIAA 79-1653] A79-45327 identification F-16 flight control system redundancy concepts r AD-A068907] N79-28393 (AIAA 79-17711 A79-45400 SILICONISING STATIC TESTS An experimental, low-cost, silicon Aerodynamic characteristics of a large-scale slurry/ainminide high-temperature coating for semispan model with a swept wing and an unperalloys augmented jet flap with hypermixing nozzles rNASA-TM-791781 879-29292 Ames 40- by 80-Foot Wind Tunnel and Static Test SINGULARITY (RATHEHATICS) Facility Singular perturbation techniques for on-line (NASA-TM-73236] R79-29144 optimal flight path control STATISTICAL ANALYSIS AIAA 79-16201 A79-45303 Determination of sample size in flight loads SKIDDING programs --- for aircraft structures Friction and wear characteristics of wire-brush A79-44454 skids Test simulation of fighter aircraft maneuver load [NASA-TP-1495) N79-29171 spectra SKIRTS A79-44463 A study of requirements, model configurations, and STEADY FLOW test plans for air cushion system comparison tests A fast, conservative algorithm for solving the AD-A0690061 N79-28373 transonic full-potential equation SLENDER BODIES [AIAA 79-14561 A79-45261 Steady and unsteady vortex-induced asymmetric STIFFNESS loads - Review and further analysis --- on Evaluation of stiffness and damping coefficients slender axisymnetric bodies for fluid-film bearings tAIAA PAPER 79-15311 A79-46713 SLOTTED WIND TUNNELS STORAGE STABILITY Axisyinmetric calculations of transonic wind tunnel Continuation study of alternate fuels nitrogen interference in slotted test sections chemistry A79-46060 [AD-A069011] N79-29359 SONIC BOOMS STORAGE TANKS Monitoring stratospheric winds with Analysis of the emissions from storage tanks Concorde-generated infrasound during JP-4 fuel transfer operations. Phase 1: A79-'46225 Warm weather conditions SOOT (A0-A069339) N79-29364 Ionic mechanisms of carbon formation in flames STRAPOOWN INERTIAL GUIDANCE aircraft fuel combustion Guidance law design for tactical weapons with AD-A06 8872] P79-29270 strapdown seekers SPACE NAVIGATION [AIAA 79-1732] A79-45376 The global positioning system /NAVSTAR/ STRATOSPHERE A79-46466 Monitoring stratospheric winds with SPACECRAFT DESIGN Concorde-generated infrasound Atmospheric Flight Mechanics Conference for Future A79-46225 Space Systems, Boulder, Cob., August 6-8, 1979, STRESS ANALYSIS Collection of Technical Papers Service fatigue loads monitoring, simulation, and A79-45302 analysis; Proceedings of the Symposium, Atlanta, SPACECRAFT TRAJECTORIES Ga., November 14-15, 1977 4-0 helical approach of a transport aircraft in an A79-44451 ATC environment Flight spectra development for fighter aircraft IAIAA 79-17761 A79-45404 A79-44459 SPAIWISE BLOWING Flight-by-flight spectrum development --- sequence P ffects of spanwise blowing on two fighter stress analysis for aircraft structures airplane configurations A79-44460 [AlAn 79-16631 A79-45330 Methods of gust spectra prediction for fatigue SPIN REDUCTION damage Application of the equilibrium spin technique to a A79-44461 typical low-wing general aviation design Derivation of flight-by-flight spectra for fighter [AlAn 79-1625 A79-45307 aircraft --- stress analysis for ground attack STABILITY DERIVATIVES A79-44462 A model for unsteady effects in lateral dynamics Test simulation of fighter aircraft maneuver load for use in parameter estimation --- aircraft spectra stability A79-44463 [AlAn 79-16381 A79-45318 Technical evaluation report on the 52nd Symposium STANDARDS of the Propulsion and Energetics on Stresses, Development of criteria foi monitoring of airport Vibrations, Structural Integration and Engine ground pollution. Volume 1: Study Integrity (Including Aeroelasticity and Flutter) I AD-AO6'2'l21 N79-29197 (AGARD-AR-133] N79-28181 Development of criteria for monitoring of airport Investigation of stress-strain history modeling at qround pollution. volume 2: Data validation stress risers, phase 2 procedures [AD-A069162] N79-28620 P79-29198
A-24
SUBJECT INDRI SWEPT WINGS
The effects of gust alleviation on fatigue in SUPERCHARGERS 2024-T3 lilclad Computer aided design of mixed flow turbines for (NRL-TR-78064-U) N79-29544 turbochargers STRESS CONCENTRATION (ASME PAPER 78-GT-1911 A79-44794 Residual surface strain distributions near holes SUPERCRITICAL WINGS which are coidworked to various degrees Supercritical airfoil boundary-layer measurements [AD-A068396] W79-29550 (ArAA PAPER 79-15011 A79-116695 STRESS CORROSION An artificial viscosity method for the design of Rot salt stress corrosion studies supercritical airfoils IAD-A068402] N79-29300 (NASA-CR-158840] N79-28136 STRESS MEASUREMENT SUPERSONIC AIRCRAFT Residual surface strain distributions near holes Opportunities for supersonic performance gains which are coidworked to various degrees through non-linear aerodynamics r AD-A068396) N79-29550 (AIAA PAPER 79-15271 A19-46710 STRESS-STRAIN RELATIONSHIPS Technique for developing design tools from the Investigation of stress-strain history modeling at analysis methods of computational aerodynamics stress risers, phase 2 (AlAP. PAPER 79-1529) A79-46711 [AD-A0691621 N79-28620 SUPERSONIC AIRFOILS STRESSES An off design shock capturing finite difference The effect of oblique angle o f sound incidence, approach for caret waverider configurations realistic edge conditions, curvature and (AD-A068819) N79-28156 in-plane panel stresses on the noise reduction SUPERSONIC BOUNDARY LAYERS characteristics of general aviation type panels Adverse pressure gradients effects on supersonic (NASA-CR-157452) 879-29958 boundary layer turbulence STRUCTURAL ANALYSIS (AIRA PAPER 79-15631 A79-46730 Service fatigue loads monitoring, simulation, and SUPERSONIC COMBUSTION RAMJET ENGINES analysis; Proceedings of the Symposium, Atlanta, Numerical investigation of the perpendicular Ga., November 14-15, 1977 injector flow field in a hydrogen fueled scranjet A79-44451 [AIAA PAPER 79-14821 A79-46686 STRUCTURAL DESIGN SUPERSONIC CRUISE AIRCRAFT RESEARCH State of the art in aircraft loads monitoring Jet noise and performance comparison study of a A79-44453 Mach 2.55 supersonic cruise aircraft Highlights of the C-141 service life monitoring (NASA-TM-800911) N79-28982 program A computer program for detailed analysis of the A79-44457 takeoff and approach performance capabilities of Wing design, body design, high lift systems and transport category aircraft flying qualities with introduction [NASA-TM-80120] 879-29141 N79-28125 SUPERSONIC FLOW STRUCTURAL DESIGN CRITERIA A two-dimensional unsteady Ruler-equation solver Development of a structural design procedure for for flow regions with arbitrary boundaries rigid airport pavements (AIAA 79-14651 P.79-45269 rAD-A0695481 879-28187 An aerodynamic analysis of deformed wings in STRUCTURAL RELIABILITY subsonic and supersonic flow Derivation of flight-by-flight spectra for fighter [AD-A067586) N79-28149 aircraft --- stress analysis for ground attack SUPERSONIC INLETS A79-44462 A throat-bypass stability-bleed system using Build 1 of an accelerated mission test of a TF41 relief valves to increase the transient with block 76 hardware stability of a mixed-compression inlet --- YF-12 (AD-A0685951 N79-28179 aircraft inlet tests in the Lewis 10 by 10 ft STRUCTURAL VIBRATION supersonic wind tunnel Noise and vibration problems: Outline notes [NASA-TP-1083) N79-28176 N79-28124 SUPERSONIC TRANSPORTS STRUCTURAL WEIGHT Modern concepts for design of delta wings for Computerized systems analysis and optimization of supersonic aircraft of second generation --- for aircraft engine performance, weight, and life drag reduction cycle costs P.79-43993 rNASA-Tn-79221] N79-29938 SUPERSONIC WAKES SUBSONIC AIRCRAFT An extension to the method of Garabedian and Korn High Reynolds Number Subsonic Aerodynamics for the calculation of transonic flow past an r VKI-LECTURE-SERIES-16] N79-28119 aerofoil to include the effects of a boundary Advantages and problems of large subsonic aircraft layer and wake P179-28120 [ARC-R/N-3828] H79-29154 SUBSONIC FLOW SURVEILLANCE RADAR Computation of subsonic and transonic flow about Reflection elimination in secondary surveillance lifting rotor blades radar --- for air traffic control rAIAP. 79-16671 A79-45333 A79-L16241 Trailing-edge flows at high Reynolds number SWEEP ANGLE [P.IAA PAPER 79-1503] P.79-46697 Investigation of three-dimensional shock/boundary Subsonic flow past an oscillating cascade with layer interactions at swept compression corners finite mean flow deflection (AIAA PAPER 79-14981 A79-46693 [AlAP. PAPER 79-1516) P.79-46704 SWEPT FORWARD WINGS Peak Strouhal frequency of subsonic jet noise as a The effect of canard relative size and vertical function of Reynolds number location on the subsonic longitudinal and rAIAP. PAPER 79-15251 A79-46709 lateral-directional static aerodynamic Effect of viscosity on wind-tunnel wall characteristics for a model with a swept forward interference for airfoils at high lift wing --- in the Langley 7i10 ft high speed tunnel IATAA PAPER 79-15341 A79-46715 (NASA-TM-18739) 879-28138 An aerodynamic analysis of deformed wings in SWEPT WINGS subsonic and supersonic flow The stability of the boundary layer on a swept [AD-A067586] N79-28149 wing with wall cooling The computation of vortex flows by panel methods (AIAA PAPER 79-1495] A79-46692 N79-28482 Aerodynamic characteristics of a large-scale SUBSONIC SPEED semispan model with a swept wing and an The effect of canard relative size and vertical augmented jet flap with hypermixing nozzles location on the subsonic longitudinal and Ames 140- by 80-Foot Wind Tunnel and Static Test lateral-directional static aerodynamic Facility characteristics for a model with a swept forward (NASA-TN-73236) P179-29144 wing --- in the Langley 7x10 ft high speed tunnel [NASA-TM-78739) 879-28138
A-25
SYSTEM EFFECTIVENESS SUBJECT INDEX
Wing/store flow-field measurements at transonic TERMINAL GUIDANCE speeds using a laser velocimeter Fuel-conservative guidance system for powered-lift [60-60683281 879-29149 aircraft SYSTEM EFFECTIVENESS [6166 79-17091 679-45363 Flight test experience with an adaptive control Optimal missile guidance for low miss and system using a maximum likelihood parameter perpendicular impact estimation technique [AIAA 79-17341 679-45377 6166 79-17021 679-45357 TERRAIN FOLLOWING AIRCRAFT Filtering and threat logic design and evaluation A study of altimeter-controlled terrain-following for the beacon collision avoidance system systems tAIRA 79-17071 A79-45361 R79-28162 SYSTEM FAILURES TEST CHAMBERS The DC-9-80 digital flight guidance system's NASA Cr6 jet engine diagnostics program: monitoring techniques Long-term CF6-6D low-pressure turbine [6166 79-17091 679-45359 deterioration SYSTEMS ANALYSIS [NASA-CB-159618] 879-29191 Disaggregate mode-share models for air freight TETHERING policy analysis A unique facility for V,'STOL aircraft hover testing A79-45249 Langley Impact Dynamics Research Facility Maintenance improvement: An analysis approach (RASA-TP-1 I$73] N79-29199 including inferential techniques. Volume 1: THERMAL DECOMPOSITION Dverview The temperature at which thermal dissociation is [AD-A068380] 979-28129 initiated in jet fuels under static conditions Maintenance improvement: An analysis approach A79-44953 including inferential techniques. Volume 2: THERMODYNAMICS Technical report Air Force Academy aeronautics digest, fall 1978 rAD-A0683811 979-28130 [AD-A069044] 879-30134 A gas turbine off-design computing system THREE DIMENSIONAL FLOW 979-28563 A fast, conservative algorithm for solving the SYSTEMS ENGINEERING transonic full-potential equation Description of the VTOL. Approach and Landing [AjAR 79-1456] A79-45261 Technology (VALT) CH-47 research system Three-dimensional coordinates about wings rNA5A-TD-14361 979-29195 [AIAA 79-1461] 679-45265 SYSTEMS MANAGEMENT Investigation of three-dimensional shock/boundary Dual digital flight control redundancy management layer interactions at swept compression corners system development program [AIAA PAPER 79-1498] 679-46693 [AIAA 79-17011 679-45356 Water tunnel flow visualization - Insight into SYSTEMS STABILITY complex three-dimensional flow fields --- around Stability and nonlinear response of rotor-bearing fighter aircraft systems with squeeze film bearings [RIAA PAPER 79-1530] A79-46712 N79-29519 The computation of vortex flows by panel methods N79-28482 A three dimensional flow computing system II applicable to axial and radial flow turbomachines TAKEOFF N79-28558 A computer program for detailed analysis of the TITANIUM ALLOYS takeoff and approach performance capabilities of Not salt stress corrosion studies transport category aircraft [AD-6068402] 979-29300 rNAsA-TN-801201 979-29141 TRAILING EDGES Aircraft accident report: Continental Air Lines, Trailing-edge flows at high Reynolds number Inc., Boeing 727-224, 832725, Tucson Arizona, 3 [AIAA PAPER 79-1503] 679-96697 June 1977 TRAINING AIRCRAFT IWTSB-AAR-78-91 979-29158 Aerodynamic data development for the turboprop Aircraft accident report: National Jet Services, T-44A Operational Flight Trainer Inc., Douglas DC-3, 951071, Evansville Dress [AIAA 79-1637] 679-45317 Regional Airport, Indiana, 13 December 1977 TRAJECTORY OPTIMIZATION NTSB-AAR-78-101 879-29161 The extremal trajectory map - A new representation TANKER AIRCRAFT of combat capability The effect of winglets on the KC-135A aircraft [AIAA 79-16221 A79-45304 tests in the Langley 8 ft transonic pressure Approximate trajectory solutions for fighter tunnel aircraft rAD-60683241 979-29177 [AIAA 79-16231 679-45305 TARGET RECOGNITION Numerical computation of optimal evasive maneuvers Information processing for target detection and for a realistically modeled airplane pursued by identification a missile with proportional guidance AD-A06890 7 1 W79-28393 [AIAA 79-1624] A79-45306 TECHNOLOGICAL FORECASTING Fuel-conservative guidance system for powered-lift Hypersonic airframe structures: Technology needs aircraft and flight test requirements [AIAA 79-1709] 679-45363 [NASA-CR-3130] 879-28168 Optimal missile guidance for low miss and TECHNOLOGY UTILIZATION perpendicular impact Composite structural materials [6166 79-1734] 679-45377 rNASA-CR-158851] 879-28235 TRANSIENT RESPONSE Spinoff 1979 Problems involved in starting and shutdown of gas [NASA-TN-804811 979-29108 turbines: Thermodynamic and mechanical aspects TEMPERATURE EFFECTS N79-28565 The temperature at which thermal dissociation is TRANSLATIONAL MOTION initiated in let fuels under static conditions Effect of inertia of blower on stability of 679-94953 air-cushion vehicle Experimental study of low temperature behavior of A79-44083 aviation turbine fuels in a wing tank model TRANSMISSIONS (MACHINE ELEMENTS) [NASA-CR-159615) 979-29355 Gas turbine engines and transmissions for bus TERCOM demonstration programs Analysis, storage, and retrieval of elevation data [COO-4867-1) N79-29522 with applications to improve penetration TRANSONIC COMPRESSORS (AD-A0687471 H79-28166 The effect of blade-to-blade flow variations on the mean flow-field of a transonic compressor [6166 PAPER 79-1515] A79-46703
6-26
SUBJECT INDEX USER MANUALS (CONPUTEB PROGRAMS)
TRANSONIC PLOW Contribution to the calculation of the dynamic A fast, conservative algorithm for solving the behavior of industrial turbocompressor circuits transonic full-potential equation W79-28564 [AIAA 79-1456] 679-45261 TURBOFAN ENGINES Vector processor algorithms for transonic flow Build 1 of an accelerated mission test of a FF41 calculations with block 76 hardware #166 79-1457] #79-45273 (AD-A068595] N79-28179 Computation of subsonic and transonic flow about NASA CF6 jet engine diagnostics program: lifting rotor blades Long-term CF6-6D low-pressure turbine [AIAA 79-16671 679-45333 deterioration Transonic flow past a symmetrical airfoil at high [NASA-CR-159618] - 819-29191 angle of attack TURBOF AN S r#i#A PAPER 79-15001 679-46694 Pump design Recent progress in finite-volume calculations for N79-28567 wing-fuselage combinations --- transonic A computer-aided design method for axial flow potential flow pumps and fans r#i#A PAPER 79-15131 #79-46702 N79-28568 Results of an improved version of LTRAN2 for TURBONACHIIERY computing unsteady airloads on airfoils A three dimensional flow computing system oscillating in transonic flow applicable to axial and radial flow turbomachines rAIAA PAPER 79-15531 #79-46726 879-28558 Application of a finite element method to Unstable flow regimes, including rotating stall, transonic flow problems using an optimal control surge, distortions, etc. approach B79-28560 879-28477 TURBOPROP AIRCRAFT An extension to the method of Garabedian and Korn Aerodynamic data development for the turboprop for the calculation of transonic flow past an T-44A Operational Flight Trainer aerofoil to include the effects of a boundary (AIAA 79-16371 A79-45317 layer and wake TURBULENCE IARC-R/M-3828] 879-29154 Identification of aircraft parameters in TRANSONIC FLUTTER turbulence with non-rational spectral density Transonic flutter analysis of a rectangular wing N79-28182 with conventional airfoil Sections TURBULENCE EFFECTS IAIAA 79-16321 #79-45313 The influence of turbulence on drag TRANSONIC SPEED A79-44874 Wing/store flow-field measurements at transonic Effect of atmospheric turbulence on the stability speeds using a laser velocirneter of a lifting rotor blade [#0-60683281 879-29149 879-28183 TRANSONIC WIND TUNNELS TURBULENT BOUNDARY LAYER T%xisymmetric calculations of transonic wind tunnel The influence of turbulence on drag interference in slotted test sections A79-44874 A79-46060 Investigation of three-dimensional shock/boundary Evaluation of flow quality in two NASA transonic layer interactions at swept compression corners wind tunnels [AIAA PAPER 79-1498] 679-46693 (AIAA PAPER 79-15321 #79-46714 Adverse pressure gradients effects on supersonic TRANSPORT AIRCRAFT boundary layer turbulence Use of AIDS recorded data for assessing service [AIAA PAPER 79-1563] A79-46730 load experience --- Aircraft Integrated Data TURBULENT FLOW S vs tern The prediction of the turbulent flow field about #79-441455 an isolated airfoil Aerodynamic development of a small horizontal tail [AIAA PAPER 79-15431 #79-46719 for an active control relaxed stability Laser anemometer measurements at the exit of a transport application T63-C20 combustor [AIAA 79-16531 679-45327 fRASA-CR-1596231 879-28456 Decoupled longitudinal controls for shear TURNING FLIGHT penetration in the terminal area environment Folded shear plane control apparatus for aircraft during approach and landing engine jet transport steering and stabilization ATAA 79-16781 #79-45341 [AIAA 79-16821 A79-45344 4-0 helical approach of a transport aircraft in an TWO DIMENSIONAL FLOW ATC environment A fast, conservative algorithm for solving the rAIAA 79-17761 #79-45404 transonic full-potential equation Pacific area evaluation of a commercial Omega (AIAA 79-1456) 679-45261 navigation system installed in a VC-118 A two-dimensional unsteady Euler-equation solver aircraft, supplement 1 for flow regions with arbitrary boundaries [AD-6068106) N79-28165 [AIAA 79-14651 A79-45269 A computer program for detailed analysis of the Trailing-edge flows at high Reynolds number takeoff and approach performance capabilities of [#166 PAPER 79-1503] A19-46697 transport category aircraft Effect of viscosity on wind-tunnel wall rRASA-TM-801201 879-29141 interference for airfoils at high lift An experimental and theoretical investigation of [AIAA PAPER 79-1534] A79-46715 the effect of nonmetric over-the-wing nacelles on wing-body aerodynamics rRASA-TP-1503) 879-29146 U TURBINE BLADES UNSTEADY FLOW Unstable flow regimes, including rotating stall, Unsteady wing boundary layer energization surge, distortions, etc. [AIAA 79-1631] 679-45312 N79-28560 Aeromechanics --- unsteady flow, aeroelasticity, TURBINE ENGINES flutter, and servocontrol Computer aided design of mixed flow turbines for 879-28121 turbochargers USER MANUALS (COMPUTER PROGRAMS) [ASNE PAPER 78-Gr-1911 A79-44794 Maintenance improvement. An analysis approach Experimental study of low temperature behavior of including inferential techniques. Volume 4: aviation turbine fuels in a wing tank model Software manual tNASA-CR-1596151 879-29355 [#0-6068383] 819-28131 TURB OCO! PR ES SONS Digital Avionics Information System (DAIS) Computer aided design of mixed flow turbines for Reliability and maintainability model users turbochargers guide, volume 2 --- life cycle costs rASM? PAPER 78-GT-1911 A79-44794 [AD-A068826) 879-29182
6-27
UTILITY AIRCRAFT SUBJECT INDEX
UTILITY AIRCRAFT VIBRATION DAMPING Preliminary airworthiness evaluation RU-21 B Demonstration of aircraft wing/store flutter guardrail V aircraft suppression systems (AD-A068347] N79-29178 A79-46238 Evaluation of stiffness and damping coefficients for fluid-film bearings V 879-28367 V/SlOT. AIRCRAFT A method for obtaining practical Plight test of a VIOL digital autoland system flutter-suppression control laws using results along complex trajectories of optimal control theory [AIAA 79-1703] A79-45358 (NASA-TP-1471) 879-28614 Fuel-conservative guidance system for powered-lift VISCOSITY aircraft Effect of viscosity on wind-tunnel wall {AIAA 79-17091 A79-45363 interference for airfoils at high lift Design criteria for optimal flight control systems [8188 PAPER 79-1534] A79-46715 rATAA 79-1782] A79-45409 An artificial viscosity method for the design of Alleviation of stability and control difficulties supercritical airfoils of a V/STOL Type B aircraft [NASA-cR-158840) B79-28136 rAIAA 79-17851 879-45412 VISCOUS FLOW Low speed wind tunnel test of ground proximity and Finite element methods for inviscid and viscous deck edge effects on a lift cruise fan V/STOL flow problems configuration, volume 2 W79-28474 (NASA-CR-152248] 879-28142 VISUAL FLIGHT Recent applications of theoretical analysis to Effect of reduced visibility on VIOL handling V,'STOL inlet design quality and display requirements (NASA-TM-792111 879-29143 (8188 79-16801 879-45343 A unique facility for V/STOL aircraft hover testing VON KARMAN EQUATION Langle y Impact Dynamics Research Facility Identification of aircraft parameters in CNASA-T P-14731 N79-29199 turbulence with non-rational spectral density VALIDITY 979-28182 Development of criteria for monitoring of airport VORTEX SHEETS ground pollution. Volume 1: Study An iterative lifting surface method for thick AD-A0672421 879-29157 bladed hovering helicopter rotors Development of criteria for monitoring of airport [8188 PAPER 79-15171 879-46705 ground pollution. Volume 2: Data validation Water tunnel flow visualization - Insight into procedures complex three-dimensional flow fields --- around [AD-80672431 879-29198 fighter aircraft VAPORS [AIAA PAPER 79-15301 879-46712 Analysis of the emissions from storage tanks Application of vortex lattice method for the during JP-4 fuel transfer operations, p hase 1: evaluation of the aerodynamic characteristics of Warm weather conditions wings with and without strakes rAD-A0693391 879-29364 VECTOR ANALYSIS VORTICES Vector processor algorithms for transonic flow Water tunnel visualization of the vortex flows of calculations the F-15 [AIAA 79-14571 879-45273 [AIAA 79-16491 879-45325 VELOCITY DISTRIBUTION The computation of vortex flows by panel methods Effect of rotor meridional velocity ratio on W79-28482 response to inlet radial and circumferential VULNERABILITY distortion Advanced risk assessment of the effects of [NASA-TP-12781 879-28177 graphite fibers on electronic and electric VERTICAL LANDING equipment, phase 1 --- simulating vulnerability Flight test of a VTOL digital autoland system to airports and communities from fibers released along complex trajectories during aircraft fires TAIAA 79-1703] A79-45358 [NASA-CR-159027] 879-28419 Evaluation of the navigation performance of A simulation model of attack helicopter shipboard-VTOL-landing guidance systems vulnerability to hostile artillery fire [8188 79-17081 879-45362 [AD-A069753] 879-29179 An experimental investigation of control-display requirements for a jet-lift VIOL aircraft in the terminal area LTITA [AD-A068818] 879-28175 WALL TEMPERATURE Description of the VIOL Approach and Landing The stability of the boundary layer on a swept Technology (VALT) CH-47 research system wing with wall cooling IWASA-TO-14361 879-29195 [8188 PAPER 79-14951 A79-46692 VERTICAL TAKEOFF WEAPON SYSTEMS Description of the VTOL Approach and Landing Guidance law design for tactical weapons with Technology (VALT) CH-47 research system strapdowo seekers tNASA-TP-14361 879-29195 [AIAA 79-17321 A79-45376 VERTICAL TAKEOFF AIRCRAFT WEAR Parameter and state estimation applicable to Friction and wear characteristics of wire-brush aircraft identification problem skids A79-439'46 [NASA-IP-1495] 879-29171 Effect of reduced visibility on VTOL handling Wear particle analysis of grease samples quality and display requirements [AD-A069114) 879-29344 [8188 79-16801 A79-45343 WEATHERING Evaluation of the navigation performance of Environmental exposure effects on composite shipboard-VTOL-landing guidance systems materials for commercial aircraft rArAA 79-17081 879-45362 [NASA-CR-158838) 879-28232 An experimental investigation of control-display WIND (METEOROLOGY) requirements for a jet-Lift VIOL aircraft in the Wind shear, volume 1. Citations from the NTIS terminal area data base 185-8064618) 879-28175 [NTIS/PS-78/1314/0] 879-29772 VIBRATION WIND DIRECTION Technical evaluation report on the 52nd Symposium Monitoring stratospheric winds with of tho Propulsion and Snergetics on Stresses, Concorde-generated infrasound 'ibrations, Structural Integration and Fngine 879-46225 1ntrqrity (Tncluding Aeroelasticity and Flutter) I #cAPD-AR-1331 879-28181
8-28
SUBJECT INDEX TF-12 AIRCRAFT
WIND SHEAR WING NACELLE CONFIGURATIONS Decoupled longitudinal controls for shear Wing aerodynamic loading caused by jet-induced penetration in the terminal area environment lift associated with S yOL-OTW configurations during approach and landing engine jet transport (NASA-TN-79218) 879-28146 (AIAA 79-16781 A79-45341 An experimental and theoretical investigation of The analysis of National Transportation Safety the effect of nonmetric over-the-wing nacelles Board snail single-engine fixed-wing aircraft on wing-body aerodynamics accident/incident reports for the potential [NASA-TP-1 503] 879-29146 presence of low-level wind shear WING OSCILLATIONS t AD-A069438) 879-28848 Results of an improved version of LTR&N2 for Aircraft accident report: Continental Air tines, computing unsteady airloads on airfoils Inc., Boeing 727-224, 832725, Tucson Arizona, 3 oscillating in transonic flow June 1977 (AIAA PAPER 79-1553) A79-46726 [NTSB-AAR-78-9] 879-29158 WING PLANPORMS Wind shear, volume 1. Citations from the NTIS Application of vortex lattice method for the data base evaluation of the aerodynamic characteristics of NTTSfPS-78/1314/0) 879-29772 wings with and without strakes WIND TUNNEL MODELS 879-28145 Application of two synthesis methods for active WING PROFILES flutter suppression on an aeroelastic wind Three-dimensional coordinates about wings tunnel model (AIAA 79-14611 A79-45265 fAIAA 79-16331 A79-45314 Application of two synthesis methods for active Demonstration of aircraft wing/store flutter flutter suppression on an aeroelastic wind suppression systems tunnel model A79-46238 (AIAA 79-16331 A79-45314 The effect of canard relative size and vertical Recent progress in finite-volume calculations for location on the subsonic longitudinal and wing-fuselage combinations --- transonic lateral-directional static aerodynamic potential flow characteristics for a model with a swept forward [AIAA PAPER 79-1513] A79-46702 wing --- in the Langley 7x10 ft high speed tunnel Technique for developing design tools from the (NASA-TN-78739] 879-28138 analysis methods of computational aerodynamics WIND TUNNEL TESTS (AIAA PAPER 79-1529) A79-46711 Axisymmetric calculations of transonic wind tunnel WING SLOTS interference in slotted test sections The aerodynamic noise of a slot in an aerofoil R79-46060 (ARC-R/M-3830) N79-29155 Demonstration of aircraft wing/store flutter WINGLETS suppression systems The effect of winglets on theKC-135A aircraft A79-46238 tests in the Langley 8 ft transonic pressure Evaluation of flow quality in two NASA transonic tunnel wind tunnels [AD-A068324] 879-29177 [AIRA PAPER 79-15321 A79-46714 WINGS Scaling effects on shock-induced separation An aerodynamic analysis of deformed wings in N79-28122 subsonic and supersonic flow Scaling effects on drag prediction --- wind tunnel [AD-A067586] N79-28149 tests WORKLOADS (PSYCHOPHYSIOLOGY) N79-28123 Development of a control wheel steering mode and Aerodynamic characteristics of forebody and nose suitable displays that reduce pilot workload and strakes based on V-16 wind tunnel test improve efficiency and safety of operation in experience. Volume 1: Summary and analysis the terminal area and in vindshear [NASA-CR-3053] 879-28143 [AIAA 79-1887] A19-145414 A throat-bypass stability-bleed system using WYOMING relief valves to increase the transient Aircraft accident report: Rocky Mountain Airways, stability of a mixed-compression inlet --- YF-12 Inc., Deflavilland DHC-6-300, N24RN, Cheyenne, aircraft inlet tests in the Lewis 10 by 10 ft Wyoming, 27 February. 1979 supersonic wind tunnel [NTSB-AAR-79-10) 879-29157 (NASA-TP-10831 879-28176 Aerodynamic characteristics of a large-scale semispan model with a swept wing and an Y augmented jet flap with hypermixing nozzles YF-12 AIRCRAFT Ames 40- by 80-Foot Wind Tunnel and Static Test A throat-bypass stability-bleed system using Facility relief valves to increase the transient rNASA-TM-732361 879-29144 stability of a mixed-compression inlet --- !F-12 An experimental and theoretical investigation of aircraft inlet tests in the Lewis 10 by 10 ft the effect of nonmetric over-the-wing nacelles supersonic wind tunnel on wing-body aerodynamics [NASA-TP-1083) 879-28176 (NASA-TP-1503) 879-29146 Wind tunnel test of ACES 2 ejection seat with ant hropometric dummy in asymmetric configurations (AD-A068614) 879-29163 The effect of winglets on the IC-135A aircraft tests in the Langley 8 ft transonic pressure tunnel (AD-A0683241 879-29177 WIND TUNNEL WALLS Effect of viscosity on wind-tunnel wall interference for airfoils at high lift [AIAA PAPER 79-1534] A79-46715 WING FLAPS Unsteady wing boundary layer energization [AIRA 79-16311 A79-45312 WING LOADING Results of an improved version of LTRAN2 for computing unsteady airloads on airfoils oscillating in transonic flow [AIAA PAPER 79-1553] A79-46726 Wing aerodynamic loading caused by jet-induced lift associated with STOL-OTW configurations (RASA-T#-79218) 879-28146
A-29 PERSONAL AUTHOR INDEX
AERONAUTICAL ENGINEERING/A Continuing Bibliography (Suppl. 115) NOVEMBER 1979
Typical Personal Author Index Listing
1PERSONALAUTH ACKEB, L. V. ,,_ ANDERSON, 0. N. Aerodynamic and acoustic effects of eliminating A comparison of air-to-air missile guidance laws r core swirl from a full scale 1.6 stage pressure based on optimal control and differential game ratio fan (OF-5A) theory [AIAA 79-1736] A79-45378 I (NASA-TN-78991) 579-11001 ANDRISANI, D., II Gust alleviation using direct turbulence measurements tAIAA 79-16741 EPORI NASA A79-45339 NUMBER I ACCESSION ANGLIE, B.L. Li NUMBER Effects of spanwise blowing on two fighter airplane configurations [AIAA 79-1663] A79-45330 ANSELL, G. S. Listings in this index are arranged alphabetically by personal author. The title Composite structural materials of the document provides the user with a brief description of the subject matter. (NASA-CR-158851] 579-28235 The report number helps to indicate the type of document cited (e.g.. NASA ANTIPOY, B. F. report, translation. NASA contractor report). The accession number is located Aircraft instrument components /3rd revised and beneath and to-the right of the title. e.g. N79-11 001. Under any one author's enlarged edition/ name the accession numbers are arranged in sequence with the /AA accession ARABZADAH, N. B. numbers appearing first. Forecast of future aviation fuels. Part 1: Scenarios A [NASA-cR-158871] 579-293511 ABBOTT, T. S. ARAVAMODA!, K. S. Description of the VIOL Approach and Landing Experimental and theoretical studies on model Technology (VALT) CH-47 research system helicopter rotor noise (NASA-T p-1436) 579-29195 (NASA-CR-158844] 579-28984 ABEL, I. ARIELI, B. Application of two synthesis methods for active Computation of subsonic and transonic flow about flutter suppression on an aeroelastic winil lifting rotor blades tunnel model :AIAA 79-16671 579-45333 CAIAA 79-1633] 579-115314 ARWDT, A. B. A. ABELKIS, P. R. Peak Strouhal frequency of subsonic jet noise as a Service fatigue loads monitoring, simulation, and function of Reynolds number anal ysis; Proceedings of the Symposium, Atlanta, (AIAA PAPER 79-15251 A79-46709 Ga. , November 14-15, 1977 ASHBAUGB, I. B. 579-44451 Evaluation of a crack-growth gage for monitoring ABERWATHY, J. W. possible structural fatigue-crack growth An aerodynamic analysis of deformed wings in A79-44458 subsonic and supersonic flow ASBKBIAS, I. L. I 50-5067586] R79-28149 Effect of reduced visibility on VIOL handling ADARS, N. A. quality and display requirements Implementation and testing of numerical analysis [ATAA 79-1680] 579-1153113 techniques in avionics applications ASS, B. A. [50-5069299] N79-29187 Aircraft instrument components /3rd revised and AGGARWAL, P. enlarged edition/ An analysis of operational procedures and design A79-44884 modifications for aircraft fuel conservation AYATI, N. B. CAIAS 79-16561 579-45318 Forecast of future aviation fuels. Part 1: AIKEW, T. N. Scenarios Aerodynamic characteristics of a large-scale [NASA-CR-158871] 579-29354 setnispan model with a swept wing and an augmented jet flap with hypertuixing nozzles [NASA-FM-73236] N79-29144 B ALEKSEEV, V. I. BACHALO, W. D. Extremal radio-navigation Transonic flow past a symmetrical airfoil at high angle of attack ALLISON, J. L. [AlAS PAPER 79-1500] 579-466911 AALC fan model test program BAINES, I. C. [50-50690581 579-28372 Computer aided design of mixed flow turbines for ALTHO?, W. turbochargers Environmental effects on the elastic-plastic [ASNE PAPER 78-GT-191] A79-41I794 properties of adhesives in bond metal joints BALL, N. [RAS-LIB-Tt1ANS-1999] 579-29328 rinsteady wing boundary layer energization ANNOYS, B. B. [AIAA 79-16311 A79-45312 F-16 flight control system redundancy concepts BANDA, S. S. AIAA 79-17711 579-115400 A model for unsteady effects in lateral dynamics ANDERSON, 0. for use in parameter estimation A two-dimensional unsteady Puler-equation solver [AIAA 79-16381 A79-45318 for flow regions with arbitrary boundaries BAR-ITZHACK, I. V. [AlAS 79-1465] 579-45269 Azimuth observability enhancement during INS in-flight alignment [AIAA 79-1706] A79-45360
B-i
BARKER, V. P. PERSONAL AUTHOR INDEX
BARKER, V. B. BROOKS, J. J. Development of a structural design procedure for Jet engine exhaust analysis by subtractive rigid airport pavements chromatography (AD-A0695481 879-28187 [80-8067898) 879-28178 BARLOW, J. B. BROUSSARD, J. R. Application of the equilibrium spin technique to a Alleviation of stability and control difficulties typical low-wing general aviation design of a V/STOL Type B aircraft (AIAA 79-16251 A79-45307 (AIAA 79-1785] 879-45412 BARON, J. B. BROWN, L. N. An off design shock capturing finite difference Preliminary study of pilot lateral control of two approach for caret waverider configurations light airplanes near the stall rAD-60688191 879-28156 rATA?. 79-17751 879-45403 BARRETT, L. B. BROWN, N. D. Stability and nonlinear response of rotor-bearing Goodyear aerospace conceptual design maritime systems with squeeze film bearings patrol airship ZP3G 879-29519 [AD-A068449] 879-29150 BArTER, P. BROWN, S. S. Parametric studies of model helicopter blade slap Aircraft transparency failure and logistical cost and rotational noise analysis. Volume 2: Design data and (AD-A068181] 879-29962 maintenance procedures BEILIAN, J. L. [AD-A068720] 879-29173 An experimental investigation of control-display Aircraft transparency failure and logistical cost requirements for a let-lift VIOL aircraft in the analysis. Volume 3: Transparency analysis terminal area [AD-A068721] N79-29174 (AD-8068818] 879-28175 BRUGH, P. L. BEITCH, I. Investigation of stress-strain history modeling at Technical evaluation report on the 52nd Symposium stress risers, phase 2 of the Propulsion and Energetics on Stresses, [AD-A069162] 879-28620 Vibrations, Structural Integration and mngine BRYANt, V. H. Integrity (Including Aeroelasticity and Flutter) Flight test of a VIOL digital autoland system [AGARD-AR-1333 879-28181 along complex trajectories BELL, W. H. [ATAA 79-17033 P.79-45358 The influence of turbulence on drag BTJKHARKIW, A. K. A79-44874 The temperature at which thermal dissociation is BENNETT, C. I. initiated in jet fuels under static conditions Low E1 signature response techniques A79-44953 I AD-A06821 11 N79-29397 BULL, D. A. BENSTEIN, B. H. Aerial isolation - a study of the interaction Advanced General Aviation Turbine Engine (GATE) between co-sited aerials study A79-46240 [NASA-CR-1596214] 879-29189 BURKHALTER, J. B. BERENS, A. P. An aerodynamic analysis of deformed wings in State of the art in aircraft loads monitoring subsonic and supersonic flow A79-44453 AD-A0675863 N79-28149 Determination of sample size in flight loads BUSHNELL, D. H. programs Application of stability theory to laminar flow P.79-44454 control Predicted crack repair costs for aircraft structures [AIAA PAPER 79-1493] 879-46691 IAD-A0686991 879-29138 BERNSTEIN, B. L. An analysis of the low cycle fatigue behavior of C the superalloy Rene 95 by strainrange partitioning CALCOTE, H. F. rAo-A0682521 879-29295 Ionic mechanisms of carbon formation in flames BERRY, P. V. 80-80688721 879-29270 Alleviation of stability and control difficulties CALISE, A. J. of a 475101 Type B aircraft Singular perturbation techniques for on-line [AIAA 79-1785] P.79-45412 optimal flight path control BLAIR, J. D. [AIAA 79-1620] 819-45303 Dual digital flight control redundancy management An analysis of operational procedures and design system development program modifications for aircraft fuel conservation [AlA?. 79-17011 P.79-45356 [AlP.?. 79-16561 A19-45328 RONASSAR, H. J. CALLER, T. B. Establishment of manufacturing method and Guidance law design for tactical weapons with technology for the fabrication of helicopter strapdown seekers main rotor blade spars by continuous seam [AIAA 79-1732] 879-45376 diffusion bonding titanium sheet material CANNON, D. G. 180-80675901 879-28170 Development of a control wheel steering mode and BOUILLET, B. P. suitable displays that reduce pilot workload and he importance of off-design operation improve efficiency and safety of operation in N79-28556 the terminal area and in windshear BOWER, E. R. (8188 79-18871 A79-45414 Wear particle analysis of grease samples CANNON, P. H., JR. AD-A0691141 879-29344 N j njffinm expected cost control of linear systems BOWER, J. P. with uncertain parameters - Application to Sear particle analysis of grease samples remotely piloted vehicle flight control systems P.0-80691141 879-29344 (AlP.?. 79-17451 A79-45387 BREWER, G. D. CARROLL, J. R. Liquid hydrogen fueled commercial aircraft Investigation of stress-strain history modeling at A79-45600 stress risers, phase 2 BRISTEAD, M. 0. (AD-8069162] 819-28620 Application of a finite element method to CASPAR, J. R. transonic flow problems using an optimal control Subsonic flow past an oscillating cascade with approach finite mean flow deflection N79-28477 [AIAA PAPER 79-1516] A79-46704 BRISTOL, H. A. CAUGHET, D. A. Piqital Avionics Information System (DAIS) Recent progress in finite-volume calculations for - p liability and maintainability model users wing-fuselage combinations guide, volume 2 (AIAA PAPER 79-15131 A79-46702 1AD-04882] 879-29182
8-2 PERSONAL AUTHOR INDEX ELROD, B. D.
C8IARAPPA D. J. DEADMORE, D. L. Deformable mirror surface control - Hardware, An experimental, low-cost, silicon algorithms slurry/aluminide high-temperature coating for (P.11k 79-17571 P.79-45393 superalloys CLAY, L. E [NASA-TN-79178] 4479-29292 State of the art in aircraft loads monitoring DEJORGE, J. B. A79-44453 The effects of gust alleviation on fatigue in CLAYSNITH, C. B. 2024-T3 Aiclad Deformable mirror surface control - Hardware, (14RL-TR-78064-O) N79-29544 algorithms DEWIER, A. C. rAlAP. 79-17571 P.79-145393 Plight-by-flight spectrum development CLEARY, J. V. P.79-441460 Trailing-edge flows at high Reynolds number DOAK, P. E. P.IAA PAPER 79-15031 P.79-46697 Noise and vibration problems: Outline notes CLINE, V. A. 4479-281214 wing/store flow-field measurements at transonic DONIWIC, B. J. speeds using a laser velocimeter State of the art in aircraft loads monitoring rAD-A0683281 879-29149 A79-44453 CLOUD, C. DOWN, W. L. Residual surface strain distributions near holes Monitoring stratospheric winds with which are coldworked to various degrees Concorde-generated infrasound r AD-A068396] N79-29550 P.19-46225 CLYWAW, M. DOTER, F. S. Naintenance improvement: An analysis approach Preliminary airworthiness evaluation RU-21 H including inferential techniques. Volume 1: guardrail V aircraft Overview [AD-A0683147] 879-29178 (P.D-A0683801 4479-28129 DOWNING, D. B. Maintenance improvement: An analysis approach Flight test of a VTOL digital autoland system including inferential techniques. Volume 2: along complex trajectories Technical report (AIP.A 79-1703) P.19-45358 I AD-A068381] 4479-28130 DEER ER, B. C. Maintenance improvement. An analysis approach Friction and wear characteristics of wire-brush including inferential techniques. Volume 4: skids Software manual (NASA-TP-1495) - 4479-29171 [AD-A068383] R79-28131 DRONNOND, J. P. COLE, C. L. Numerical investigation of the perpendicular A throat-bypass stability-bleed system using injector flow field in a hydrogen fueled scramjet relief valves to increase the transient (AIAA PAPER 79-114821 P.19-46686 stability of a mixed-compression inlet DUKHOJ, ID. I. rNASA-TP-1083] 4479-28176 Handbook of flight communication and radio equipment COLLIER, N. R. A79-44894 An extension to the method of Garabedian and Korn DUNN, D. for the calculation of transonic flow past an The effect of oblique angle of sound incidence, aerofoil to include the effects of a boundary realistic edge conditions, curvature and layer and wake in-plane panel stresses on the noise reduction [ARC-R/N-3828] 879-29154 characteristics of general aviation type panels CORNELL, N. B. (NASA-CR-1 571452) 879-29958 Advanced risk assessment of the effects of DUNN, H. J. graphite fibers on electronic and electric Application of two synthesis methods for active equipment, phase 1 flutter suppression on an aeroelastic wind INASA-CR-159027] 4479-281419 tunnel model CULPEPPER, B. C. (AIAA 79-16331 P.19-1453114 P. unique facility for V,'STOL aircraft hover testing DUSHNAN, A. rNP.sA-T p-14731 879-29199 An analysis of operational procedures and design CUNNINGHAM, J. 5., JR. modifications for aircraft fuel conservation Review of aircraft bearing rejection criteria and (AIAA 79-1656) - P.79-45328 causes DUSTIN, I. 0. A79-45250 A throat-bypass stability-bleed system using CDRIUTT, B. A. relief valves to increase the transient Aerodynamic data development for the turboprop stability of a mixed-compression inlet T-44A Operational Plight Trainer [NASA-TP-1083] 879-28176 IIIAP. 79-16371 A79-145317 CZDCHRY, A. J. Digital Avionics Information System (DAIS): E Reliability and maintainabilit y model users EASTEP, F. N. guide, volume 2 Transonic flutter analysis of a rectangular wing [AD-A068826) 879-29182 with conventional airfoil sections (P.IAA 79-1632) A79-145313 EATON,-J. P. D Air Force Academy aeronautics digest, fall 1978 DP.PORNO, C. [AD-A06901414] 879-301314 Opportunities for supersonic performance gains EFRAT, I. through non-linear aerodynamics An off design shock capturing finite difference rAlAP. PAPER 79-1527] P.79-46710 approach for caret waverider configurations DANCE, V. D. [AD-A068819] 879-28156 44-ray inspection of aircraft structures using EISE!AN, P. B. mobile sources: A compendum of radiographic Three-dimensional coordinates about wings results (AIAA 79-11461) P.79-45265 rAD-A0683161 4479-29532 ELLIS, D. B. DAVIS, V. H., JR. An in-flight simulator investigation of roll and Technique for developing design tools from the yaw control power requirements for STOL approach analysis methods of computational aerodynamics and landing: Development of capability and [AIP.A PAPER 79-15291 P.79-46711 preliminary results DE JORGE, J. B. (NASA-CH-152307] 4479-29196 Use of AIDS recorded data for assessing service ELROD, B. D. load experience Investigation of a preliminary GPS receiver design A79-44455 for general aviation [AD-A069059] 879-291614
B-3
ERRORS, H. T. PERSONAL AUTHOR INDEX
ERRORS, B. T. FOKINOW, N. T. Ramjet cost estimating handbook Bolted field repair of composite structures (AD-A056991] 879-29188 [AD-A067923] 879-28238 ENGLISH, J. 8. FULLER, L. C. Forecast of future aviation fuels, part 1: Influence of jet fuel on permeation and cenanios flammability characteristics of graphite epoxy rRASA-CR-158871] 879-29354 composites ERICNSOW, G. E. [P.D-A068586] 879-28245 eater tunnel flow visualization - Insight into complex three-dimensional flow fields IAIAA PAPER 79-1530] A79-46712 G ERICSSON, L. E. GALLOWAY, N. J. Steady and unsteady vortex-induced asymmetric Helicopter noise level functions for use in loads - Review and further analysis community noise analyses IAIAA PAPER 79-15311 A79-46713 (AD-A068455] 879-29964 ERZBEBGER, B. GABBER, J. F., JR. Fuel-conservative guidance system for powered-lift Description of the VTOL Approach and Landing aircraft Technology (VALT) CH-47 research system rAIAA 79-17091 A79-45363 (NASA-TP-1436) 879-29195 EOLBICH, B. J. GARRETT, J. E. Gust alleviation using direct turbulence Methods of gust spectra prediction for fatigue measurements damage [AIAA 79-16741 P.79-45339 17 9-44461 EVANS, D. J. GENTILE, V. A. Application of hot isostatic pressing to aircraft Maintenance improvement. An analysis approach gas turbines including inferential techniques. Volume 4: A79-45067 Software manual (AD-A068383] 879-28131 GERDES, R. M. F A piloted simulator investigation of helicopter FABRI, J. precision decelerating approaches to hover to Instable flow regimes, including rotating stall, determine single-pilot IYR /SPIFR/ requirements surge, distortions, etc. [P.IAA 79-1886] A79-45413 879-28560 GIBELING, H. J. FAL&RSI, B. D. The prediction of the turbulent flow field about Aerodynamic characteristics of a large-scale an isolated airfoil semispan model with a swept wing and an tAIAA PAPER 79-15431 P.19-46719 augmented jet flap with hypermixing nozzles GILLESPIE, E. A. (NASA-TN-73236] 879-29144 A unique facility for V/STOL aircraft hover testing FARMER, B. G. [NASA-TP-1473] 879-29199 Demonstration of aircraft wing/store flutter GLABSER, D. A. suppression systems Bolted field repair of composite structures A79-46238 [AD-A067923] 879-28238 PHAIRHELLER, W. R. GLASIER, J. B. Analysis of the emissions from storage tanks Digital Avionics Information System (DAIS) during JP-4 fuel transfer operations. Phase 1: Reliability and maintainability model users Warm weather conditions guide, volume 2 r AD-A0693391 879-29364 AD-A0688261 879-29182 FEIK, H. A. GONOLAK, G. J. Longitudinal aerodynamics extracted from flight Gas turbine engines and transmissions for bus tests using a parameter estimation method demonstration programs ARL/AEifO-NOTF-3791 879-28144 (CO0-4867-1] N79-29522 FELSKE, K. E. GOOD, V. D. Electromagnetic compatibility (NBC) investigation Enthalpies of combustion of ramjet fuels on CR147 Chinook helicopter A79-46055 REPT-5J30-4479-021 H79-28169 GOULETTE, H. B. FISHBACH, L. H. Electromagnetic compatibility (EMC) investigation Computerized systems analysis and optimization of on CH147 Chinook helicopter aircraft engine performance, weight, and life (REPT-5J30-4479-02] N79-28169 cycle costs GOVINDARAJ, K. S. rNAsP.-TM-792211 879-29938 Design criteria for optimal flight control systems FOSS, W. B., JR. (AIAA 79-1782) P.19-45409 A computer program for detailed analysis of the GRP.NDT, A. F., JR. takeoff and approach performance capabilities of Evaluation of a crack-growth gage for monitoring transport category aircraft possible structural fatigue-crack growth NASA-TB-80120] 879-29141 A79-44458 FOWLER, R. L. GRAY, H. B. Hot salt stress corrosion studies An iterative lifting surface method for thick [AD-A0684021 879-29300 bladed hovering helicopter rotors FOX, C. H., JR. (AIAA PAPER 79-15171 A19-46705 The effect of canard relative size and vertical GREENSTONE, R. location on the subsonic longitudinal and Advanced risk assessment of the effects of lateral-directional static aerodynamic graphite fibers on electronic and electric characteristics for a model with a swept forward equipment, phase 1 wing [NASA-CR-159027] 879-28419 [NASA-TN-787391 879-28138 GRENETZ, P. S. FRARKEIFELD, J. V. Maintenance improvement: An analysis approach Continuation study of alternate fuels nitrogen including inferential techniques. Volume 1: chemistry Overview IAD-A0690111 879-29359 (AD-A068380] 879-28129 FRIEND, E. L. Maintenance improvement: An analysis approach Water tunnel visualization of the vortex flows of including inferential techniques. Volume 2: the F-iS Technical report rATAP. 79-16491 P.79-45325 (AD-A068381] 879-28130 FUJIBOHI, Y. Maintenance improvement. An analysis approach Effect of atmospheric turbulence on the stability including inferential techniques. Volume 4: of a lifting rotor blade Software manual N79-28183 [AD-A068383] H79-28131
B-4
PERSONAL AUTHOR INDEX HOLLAND, B.
GREPPER, P. o. HESS, H. A. 4-D helical approach of a transport aircraft in an A piloted simulator investigation of helicopter ATC environment precision decelerating approaches to hover to [AIAA 79-1776] A79-65409 determine single-pilot IFR /SPIFR/ requirements GROESBECK, D_ (AIAA 79-1886] 939-45413 wing aerodynamic loading caused by jet-induced NESS, B. K. lift associated with STOL-09'W configurations Development of the Navy H-Dot Automatic Carrier rNASA-TN-792181 N79-28146 Landing System designed to give improved GROSVELD, F. approach control in air turbulence The effect of oblique angle of sound incidence, (ATIA 79-1772) A79-95401 realistic edge conditions, curvature and HESSELUREAVES, J. H. in-plane panel stresses on the noise redaction A computer-aided design method for axial flow characteristics of general aviation type panels pumps and fans INASA-CR-1579521 N79-29958 W79-28568 COlETTE, J. L. HIWD!AI, H. C. Problems involved in starting and shutdown of gas A two-dimensional unsteady Euler-equation solver turbines: Thermodynamic and mechanical aspects for flow regions with arbitrary boundaries N79-28565 (AIAA 79-1965) A79-45269 GuIKEL, H. C. HODGKINSOI, J. Development of a structural design procedure for Initial results of an inflight simulation of rigid airport pavements augmented dynamics in fighter approach and landing rAD-A0695481 N79-28187 [AIAA 79-1783] A79-45910 GUPTA, N. N. HOEYMAKBRS, A. H. H. Parameter and state estimation applicable to Fatigue properties of adhesive-bonded laminated aircraft identification problem sheet material of aluminum alloys A79-43946 [LR-276] N79-29543 UTAH?!, N. HOFFNAN, D. J. Forecast of future aviation fuels, p art 1: Environmental exposure effects on composite Scenarios materials for commercial aircraft r NASA-CR-158871] R79-29354 [NASA-CR-158838] N79-28232 BOB, B. H. Effect of reduced visibility on VTOL handling H quality and display requirements HABERCO!, C. B., JR. (AIAA 79-1680) A79-45343 Wind shear, volume 1. Citations from the HITS HOLDEIDGE, H. D. data base An improved lateral stability augmentation system I NTIS/PS-78113114/O] N79-29772 for air-to-air tracking HAFEZ, N. N. (AIAA 79-1773] 939-45402 Vector processor algorithms for transonic flow HOLLAND, D. calculations Build 1 of an accelerated mission test of a TF41 [AIAA 79-19571 A79-145273 with block 76 hardware HAGGERTY, J. J. [AD-A068595] N79-28179 Spinoff 1979 HOL!BERG, B. rNASA-TN-804811 N79-29108 Construction using carbon fiber composite HAGUE, D. S. materials and aluminum: A cost comparison An introduction to co-kill probability estimation [FOA-C-20280-F9] N79-29248 in the N on N encounter HOIST, T. L. rAIAA 79-1729] A79-95373 A fast, conservative algorithm for solving the HALL, U. H. transonic full-potential equation A piloted simulator investigation of helicopter (AIAA 79-1456] A79-45261 precision decelerating approaches to hover to HORSTEAP, C. C. determine single-pilot IFR /SPIFR/ requirements Trailing-edge flows at high Reynolds number IAIAA 79-18861 A79-45413 [AIAA PAPER 79-1503] P.79-46697 H&RGRAVES, C. HOUWINK, H. Numerical computation of optimal evasive maneuvers Results of an improved version of LTRAW2 for for a realistically modeled airplane pursued by computing unsteady airloads on airfoils a missile with proportional guidance oscillating in transonic flow (AIAA 79-16241 A79-45306 [AIAA PAPER 79-15531 A79-46726 HARRIS, H. L. HOVE, B. S. Experimental and theoretical studies on model The aerodynamic noise of a slot in an aerofoil helicopter rotor noise [ARC-R/M-3830] N79-29155 [NASA-CR- 158849] N79-28984 HUBBARD, J. B., JR. Parametric studies of model helicopter blade slap Parametric studies of model helicopter blade slap and rotational noise and rotational noise [AD-A068181] N79-29962 [AD-A068181] N79-29962 HARTNANN, U. HUBER, H. R. Flight test experience with an adaptive control An improved lateral stability augmentation system system using a maximum likelihood parameter for air-to-air tracking estimation technique [AIAA 79-1773] A79-45402 rAIAA 79-1702] A79-45357 HUFF, B. V. HARVEY, F. L. Development of the Navy H-Dot Automatic Carrier Bolted field repair of composite structures Landing System designed to give improved IAD-A0679231 N79-28238 approach control in air turbulence HARVEY, H. D. [AIAA 79-1772) P.79-45401 Evaluation of flow quality in two NASA transonic HUFFNAN, J. K. wind tunnels The effect of canard relative size and vertical rAIAA PAPER 79-15321 A79-46714 location on the subsonic longitudinal and HAWKER, F. V. lateral-directional static aerodynamic Wind tunnel test of ACES 2 ejection seat with characteristics for a model with a swept forward anthropometric dummy in asymmetric configurations wing tAD-A0686191 N79-29163 [NASA-TM-78739] H79-28138 HEFEER, J. N. HUGUERIW, F. E. Application of stability theory to laminar flow 4-D helical approach of a transport aircraft in an control ATC environment rAIAA PAPER 79-1493] A79-46691 (AIAA 79-17761 P.79-45404 HELTSLEY, F. L. HULLAND, B. Wing/store flow-field measurements at transonic Filtering and threat logic design and evaluation speeds using a laser velocimeter for the beacon collision avoidance system [AD-A0683281 N79-29149 (AIAP. 79-1707] P.79-95361
B-S
BORBAD, N. C. PERSONAL AUTHOR INDEX
RURBAD, N. C. KAPLAN, 8. P. Parametric studies of model helicopter blade slap Derivation of flight-by-flight spectra for fighter and rotational noise aircraft [AD-A068181] 979-29962 A79-44462 HURT, B. KARLSSOW, K. B.. The panel method for subsonic aerodynamic flow: A Axisymmetric calculations of transonic wind tunnel survey of mathematical formulations and interference in slotted test sections numerical models with an outline of the new A79-46060 British aerospace scheme KAUPHAB, H. 979-28475 Parallel procedures for aircraft parameter HUSOCK, B. identification and state estimation Techniques for cathodic protection testing over [AIAA 79-1636] 879-45316 airfield pavements KELLER, J. D. [AD-A069045] 979-29200 Vector processor algorithms for transonic flow HWANG, C. calculations Demonstration of aircraft wing/store flutter [AIAA 79-14571 A79-45273 suppression systems KELLY, J. K. A79-46238 Description of the VTOL Approach and Landing HYZAK, J. 8. Technology (VALT) CH-47 research system An analysis of the low cycle fatigue behavior of (NASA-TP-1436] 979-29195 the superalloy Rena 95 by strainrange partitioning KELSEY, J. B. AD-8068252] N79-29295 Aerodynamic coefficient estimation by means of an extended Kalman filter [AIAA 79-1686] 879-45346 Real-time estimation of aerodynamic coefficients ILIESKII, N. N. by means of an extended Kalman filter Handbook of flight communication and radio equipment [SAND-78-2032] 979-29152 A79-44894 KERREBROCK, J. L. The effect of blade-to-blade flow variations on the mean flow-field of a transonic compressor J (AIAA PAPER 79-1515] 879-46103 JARESON, A. KESKAR, D. A. Recent progress in finite-volume calculations for The relationship of unsteadiness in downwash to wing-fuselage combinations the quality of parameter estimates (AIAA PAPER 79-15131 A79-46702 [AIAA 79-16391 879-45319 JARIGBO, A. KIMBERLY, B. H. Prerotation in centrifugal pumps: Design criteria Overview of the C-5A Service Loads Recording Program N79-28574 A79-44456 JEANS, I. L. KISTLER, B. H. Test simulation of fighter aircraft maneuver load Digital Avionics Information System (DAIS) spectra Reliability and maintainability model users A79-44463 guide, volume 2 JERNEY, G. D. [AD-A068826] 979-29182 Theory, design and experimental study of an KLINGENBOECK, U. eddy-current/hydromechanical stability augmentor A gas turbine off-design computing system for aircraft N79-28563 N79-28185 KLINGER, A. JEPPS, S. A. Analysis, storage, and retrieval of elevation data The computation of vortex flows by panel methods with applications to improve penetration 979-28482 [80-8068747] 979-28166 JERABEK, J. B. KLINGER, C. A method for evaluating KC-135 avionics Environmental effects on the elastic-plastic configurations properties of adhesives in bond metal joints [80-8069446] 979-29186 [RAE-LIB-TRANS-1999] 979-29328 JOHNSON, D. A. KOCH, L. C. Transonic flow past a symmetrical airfoil at high Hypersonic airframe structures: Technology needs angle of attack and flight test requirements rAIAA PAPER 79-15001 879-46694 [NASA-CR-3130] 979-28168 JOHNSON, P. KOENIG, B. H., III Numerical computation of optimal evasive maneuvers A simulation model of attack helicopter for a realistically modeled airplane pursued by vulnerability to hostile artillery fire a missile with proportional guidance [AD-A069753] 979-29179 [8188 7 9-1624] 879-45306 KOENIN, D. G. JOHNSTON, K. A. Aerodynamic characteristics of a large-scale Initial results of an inflight simulation of semispan model with a swept wing and an augmented dynamics in fighter approach and landing augmented jet flap with hypermixing nozzles rAIRA 79-17831 879-45410 [NASA-TM-73236] 979-29144 JONES, A., JR. KORIKOV, A. N. Folded shear plane control apparatus for aircraft Extremal radio-navigation steering and stabilization A79-44878 [AIAA 79-1682] A79-45344 KOVALEV, G. I. JUMPER, H. J. The temperature at which thermal dissociation is Air Force Academy aeronautics digest, fall 1978 initiated in jet fuels under static conditions rAu-A0690441 979-30134 879-44953 KSIENSKI, A. A. Information processing for target detection and K identification KANAL, K. [A0-A068907] 919-28393 Parameter and state estimation applicable to ROTtER, P aircraft identification problem A two-dimensional unsteady Euler-equation solver A79-43946 for flow regions with arbitrary boundaries KAPLAN, L. D. [AIAA 79-1465] 879-45269 Advanced risk assessment of the effects of graphite fibers on electronic and electric equipment, phase 1 L r NAgACR159021] 979-28419 LADEBNAN, A. J. Adverse pressure gradients effects on supersonic boundary layer turbulence (AIAA PAPER 79-1563] 879-46730
B-6
PERSONAL AUTHOR INDEX MAT, J. E.
LAGRANGE, H. A. LOPTIEN, C. V. cH-147 ENC evaluation of selected subsystems, EMC The effect of winglets on the KC-135A aircraft test report [#0-6068328] 979-29177 [AETE-77/16] 979-29170 LORINZ D. .3. LAMBREGTS, A. A. Water tunnel visualization of the vortex flows of Development of a concrol wheel steering mode and the F-15 suitable displays that reduce pilot workload and (6166 79-1649] 679-45325 improve efficiency and safety of operation in LUCAS, J. L. the terminal area and in windshear Establishment of manufacturing method and (AIAA 79-18871 679-954114 technology for the fabrication of helicopter LAMERIS, J. main rotor blade spars by continuous seam The effect of oblique angle of sound incidence, diffusion bonding titanium sheet material realistic edge conditions, curvature and (AD-A067590] 879-28170 in-plane panel stresses on the noise reduction LUCJAN, V. characteristics of general aviation type panels Longitudinal dynamic stability of a hovering rNASA-CR-1579521 979-29958 helicopter with a sling load LARD!, H. A. A79-44094 Derivation of flight-by-flight spectra for fighter LUDWIG, C. B. aircraft Development of criteria for monitoring of airport A79-44462 ground pollution. Volume 1: Study LANE, A. U. [60-6067242] 979-29197 A unique facility for V/STOL aircraft hover testing Development of criteria for monitoring of airport IRASA-TP-14731 979-29199 ground pollution. Volume 2: Data validation LATIMER, H. J. procedures Axial turbine performance prediction (60-6067243] 979-29198 979-28561 LUND, J. V. LAURIDIA, H. H. Evaluation of stiffness and damping coefficients Flight spectra development for fighter aircraft for fluid-film bearings A79-44459 979-28367 LAUSHEY, C. I. LUTZ, D. A. Handbook of flight communication and radio equipment Influence of jet fuel on permeation and A79-44894 flammability characteristics of graphite epoxy LEBACQZ, J. V. composites A review of helicopter control-display [AD-A068586] 979-28245 requirements for decelarating instrument approach LY, U.-L. rAIAA 79-1683] #79-45345 Minimum expected cost control of linear systems An experimental investigation of control-display with uncertain parameters - Application to requirements for a :jet-lift VTOL aircraft in the remotely piloted vehicle flight control systems terminal area IAIAA 79-17451 #79-45387 [#0-6068818] 979-28175 LYNN, W. F. LECAT, H. New concepts in aircraft journal bearings Goniometric aerodynamics: A different perspective: [60-6068619] 979-29520 Description - Applications 16166 79-16501 679-45326 LEE, K. H. M Fasil integral fuel tank sealants, part 1 NADDALON, D. V. [60-6067889] 979-28329 Potential applications of advanced aircraft in LEE, I. C. developing countries Design of a milti-microprocessor system for [NASA-TN-80133] 919-28158 real-time aircraft simulation MAGLIERI, D. J. N79-29800 Jet noise and performance comparison study of a LEKOUDIS, S. C. Mach 2.55 supersonic cruise aircraft The stability of the boundary layer on a swept (NASA-TH-80094) 979-28982 wing with wall cooling MAHER, S. L. 16166 PAPER 79-14951 679-46692 A multi microprocessor flight control system LEWIS, V. H. design principles Proceedings from the Government/Industry Workshop (6166 79-17001 A79-45355 on the Reliability of Nondestructive Inspections MANN, H. V. [AD-#068223] N79-29531 Aerodynamic characteristics of forebody and nose LITTLE, B. H., JR. strakes based on F-16 wind tunnel test Advantages and problems of large subsonic aircraft experience. Volume 1: Summary and analysis H79-28120 (NASA-CR-3 053] B79-28143 Aeromechanics MARSHALL, K. T. N79-28121 An analysis of bolter-hole spacing in aircraft Scaling effects on shock-induced separation carrier landings N79-28122 (60-6068585) 979-29176 Advanced computer technology in aerodynamics. HASCITTI, V. H. Lecture 1: Computer-aided aircraft design Jet noise and performance comparison study of a 979-28126 Mach 2.55 supersonic cruise aircraft LID, C. I. (NASA-TN-80098) 879-28982 Forecast of future aviation fuels. Part 1: MASLOY, L. A. Scenarios Effect of inertia of blower on stability of [NASA-CR-158871] 979-29354 air-cushion vehicle LID, 9.-S. A79-44083 Numerical solution for the flow field of a body MASON, H. C. with jet Digital Avionics Information System (DAIS) 16166 79-14521 #79-45258 Development and demonstration LORRY, H. C. [60-6068438] 919-29181 Composite structural materials MASON, W. H. NASA-CR-1588511 979-28235 Opportunities for supersonic performance gains LOGAN, N. B. through non-linear aerodynamics Earth-Referenced Maneuvering Flight Path Display (#166 PAPER 79-1527] 679-46710 16166 79-1894] 679-45421 MAT, J. B. LOKER, A. A multi microprocessor flight control system Aircraft engine driven accessory shaft coupling design principles improvements using high-strength nonmetallic [6166 79-17001 #79-45355 adapter/bushings rAD-A0686371 979-29193
8-7 MAY, B. J. PERSONAL AUTHOR INDEX
MAY, B. J. BORG?.!, B. A. Propulsion system and airframe integration Review of aircraft bearing rejection criteria and consideration for advanced air-to-surface aircraft causes AIAA PAPER 79-1120] A79-144800 A79-45250 MAY, R. 1., JR. NOUL, B. T. Build 1 of an accelerated mission test of a TFII1 Preliminary study of pilot lateral control of two with block 76 hardware light airplanes near the stall r An-A068595) 879-28179 (AlA?. 79-1775] A79-45403 MCCORKLE, R. D. MURPHY, B. D. 'lual digital flight control redundancy management P. unique facility for V/STOL aircraft hover testing system development program (NASA-TP-1473] H79-29199 lArk?. 79-1701) P.79-45356 Digital flight control reliability - Effects of redundancy level, architecture and redundancy management technique NASTASE, A. lArk?. 79-18931 P.79-45418 Modern concepts for design of delta wings for MCEBLEAR, D. P. supersonic aircraft of second generation Build 1 of an accelerated mission test of a TF41 A79-43993 with block 76 hardware NATALI, P. D. IAD-A0685951 879-28179 Investigation of a preliminary GPS receiver design MCEWAN, 0. for general aviation A computer-aided design method for axial flow [AD-A069059] W79-29164 pumps and fans SEDERVEEI, A. N79-2B568 The effects of gust alleviation on fatigue in MCFADDEN, G. B. 2024-T3 Alclad An artificial viscosity method for the design of NRL-TR-78064-U] 819-29544 supercritical airfoils SEXIER, C. H. rNAsA-cR-1588401 879-28136 A throat-bypass stability-bleed system using MCGEE, L. A. relief valves to increase the transient Evaluation of the navigation performance of stability of a mixed-compression inlet shipboard-VIOL-landing guidance systems (NASA-TP-1093] 879-28176 lArk?. 79-17081 P.79-45362 NELSON, K. D. MCHALE, A. U. CH-113 crash position indicator flight trials Fasil integral fuel tank sealants, part 1 [P.ETE-78/39] N79-29156 AD-A0678891 879-28329 SEUNASI, C. MCLEAS, J. D. Environmental effects on the elastic-plastic Fuel-conservative guidance system for powered-lift properties of adhesives in bond metal joints aircraft RAE-LIB-TBP.NS-19991 879-29328 (P.1k?. 79-17091 A79-45363 SEWSOM, J. R. MCNERI4EY, N. T. Application of two synthesis methods for active Interim field procedure for bomb damage repair flutter suppression on an aeroelastic wind using crushed limestone for crater repairs and tunnel model silikal trade name for spall repairs (AIAA 79-1633) A79-45314 AD-A0686171 H79-28189 SENSOR, J. B. MERE, A. V. A method for obtaining practical Evaluation of the navigation performance of flutter-Suppression control laws using results shipboard-VIOL-landing guidance systems of optimal control theory [AIAA 79-1708] A79-45362 (NASA-TP-1471) 879-286114 MIEBAS, B. StEM?.!!, J. B. Low EN signature response techniques Preliminary airworthiness evaluation RU-21 H [AD-A068211] 879-29397 guardrail V aircraft MILLER, G. K., JR. AD-A068347] 879-29178 Decoupled longitudinal controls for shear NIESSEN,F. B. penetration in the terminal area environment Description of the VIOL Approach and Landing [AlA?. 79-16781 P.79-45341 Technology (VALT) CH-47 research system MILLER, L. E. (19ASA-TP-1436) 879-29195 Approximate trajectory solutions for fighter WIKIFORUK, P. W. aircraft Parameter and state estimation applicable to IAIAA 79-1623] A79-45305 aircraft identification problem MILLER, W. J. P.79-443946 Ionic mechanisms of carbon formation in flames ROLL, I. E. (AD-A068872] 879-29270 Demonstration of aircraft wing/store flutter MILLS, C. B. suppression systems Demonstration of aircraft wing/store flutter P.79-46238 suppression systems NORTON, V. A. A79-46238 Preliminary airworthiness evaluation 80-21 II MITCHELL, A. R. guardrail V aircraft Direct force mode flight control for a vectored AD-A068347] N79-29178 lift fighter SORW000, D. L. (AIAA 79-174441 A79-45386 Ramjet cost estimating handbook MOLIAB, I. J. AD-A056991] 879-29188 A multi microprocessor flight control system design principles (AIAA 79-17001 P.79-45355 0 MOOIJ, H. A. 000ff, E. C. A simulator investigation of roll response Development of a structural design procedure for requirements for aircraft with rigid airport pavements rate-command/attitude-hold flight control [AD-A069548) N19-28187 systems in the landing approach and touchdown OEST!A!, B. (AlA?. 79-16791 A79-453142 Construction using carbon fiber composite !OOMAV, B. V. materials and aluminum: A cost comparison Development of the Navy H-Dot Automatic Carrier (FOA-C-20280-F9] 879-29248 Landing System designed to give improved OLSE!, J. J. approach control in air turbulence Transonic flutter analysis of a rectangular wing (AlA?. 79-1772] A79-45401 with conventional airfoil sections !ORCOCK, D. S. (AlA?. 79-1632) A19-45313 Highlights of the C-141 service life monitoring OLSOS, D. B. program Ionic mechanisms of carbon formation in flames A79-44457 (?.D-A068872) 879-29270
8-8
PERSONAL AUTHOR INDEX REASER, J. S.
OLSON, L. E. PLESS, V. N. Effect of viscosity on wind-tunnel wall Proceedings from the Government/Industry Workshop interference for airfoils at high lift on the Reliability of Nondestructive Inspections (AIAA PAPER 79-15341 879-46715 (AD-A068223] N79-29531 OSDEB, S. POCINKI, L. S. The Dc-9-90 digital flight guidance system's Advanced risk assessment of the effects of monitoring techniques graphite fibers on electronic and electric r#IAA 79-17041 879-45359 equipment, phase 1 OSTROFF, A. J. (NASA-CR-159027) 979-28419 Flight test of a VTOL digital autoland system POLLARD, D. V. along complex trajectories Injuries in air transport emergency evacuations [AIAA 79-1703] A79-45358 (80-8069372) W79-28160 OVEN, F. K. POLONNIKOV, R. I. Transonic flow past a symmetrical airfoil at high Extremal radio-navigation angle of attack A79-44878 IP.IAA PAPER 79-15001 A79-46694 POMEREJIEC, D. J. Evaluation of flow quality in two NASA transonic Engine-induced structural-borne noise in a general wind tunnels aviation aircraft [AIAA PAPER 79-1532] A79-46718 (NASA-CR-159099) N79-29951 POPE, H. H. A multi microprocessor flight control system P design principles PADILLA, V. E. [AIAA 79-1700] 879-45355 Bolted field repair of composite structures PORAT, B. rAD-A0679231 N79-28238 Azimuth observability enhancement during INS PAR, 0. A. in-flight alignment Forecast of future aviation fuels, part 1: [AIAA 79-1706] 819-45360 Scenarios POTTER, J. N. (NASA-CR-158871) N79-29354 Service fatigue loads monitoring, simulation, and PANOVKO, IA. C. analysis; Proceedings of the Symposium, Atlanta, Effect of inertia of blower on stability of Ga., November 14-15, 1977 air-cushion vehicle A79-44451 A79-44083 POWELL, C. A. PARIS, S. Effects of road traffic background noise on Numerical computation of optimal evasive maneuvers judgments of individual airplane noises for a realistically modeled airplane pursued by (NASA-Tp-1433) N79-28796 a missile with proportional guidance POWERS, B. [AIAA 79-16241 879-45306 Flight test experience with an adaptive control PARKER, F., JR. system using a maximum likelihood parameter Development of a structural design procedure for estimation technique rigid airport pavements IAIAA 79-1702] 879-45357 (AD-A0695481 N79-28187 PHASAD, U. R. PARKINSON, B. V. The extremal trajectory map - A new representation The global positioning system /NAVSTAR/ of combat capability A79-46466 (AIAA 79-16221 819-45304 PATERSON, J. H. PRICE, T. H. Scaling effects on drag prediction Digital Avionics Information System (DAIS) N79-28123 Development and demonstration PAULK, C. H., JR. (AD-A068438] N19-29181 Evaluation of the navigation performance of shipboard-VTOL-landing guidance systems FAIAA 79-1708] A79-45362 0 PAYNE, P. R. QUAN, D. L. Wind tunnel test of ACES 2 ejection seat with A model for unsteady effects in lateral dynamics anthropometric dummy in asymmetric configurations for use in parameter estimation [AD-A068614) N79-29163 (8188 79-16381 A79-45318 PEACH, L. L., JR. A piloted simulator investigation of helicopter precision decelerating approaches to hover to R determine single-pilot IFR /SPIFR/ requirements RADFORD, R. C. (8188 79-18861 A79-45413 An experimental investigation of control-display PEARSALL, I. S. requirements for a jet-lift VIOL aircraft in the Pump design terminal area 879-28567 [AD-8068818] N79-28175 PEEL, C. J. RAISINCHARI, S. C. An analysis of a programmed load fatigue failure An in-flight simulator investigation of roll and rRAE-TR-780781 N79-29562 yaw control power requirements for STOL approach PERKINS, J. J. and landing: Development of capability and Investigation of three-dimensional shock/boundary preliminary results layer interactions at swept compression corners [19ASA-CR-152307] N79-29196 [AIAA PAPER 79-1498] 879-46693 RAJAB, I. PETERSEN, D. P. The extremal trajectory map - A new representation Aerodynamic coefficient estimation by means of an of combat capability extended Kalman filter (8188 79-1622) A79-45304 (AIAA 79-16861 879-45346 RALSTON, J. N. PHATAK, A. V. Aerodynamic characteristics of forebody and nose A piloted simulator investigation of helicopter strakes based on ?-16 wind tunnel test precision decelerating approaches to hover to experience. Volume 1: Summary and analysis determine single-pilot lEN /SPIFR/ requirements (NASA-CR-3053) N79-28143 [AIAA 79-18861 A79-45413 RASNUSER, J. E. PIATT, N. Ramjet cost estimating handbook Unsteady wing boundary layer energization (AD-8056991) N79-29188 [AIAA 79-16311 A79-45312 REASER, J. S. PIERCE, 0. B. Aerodynamic development of a small horizontal tail Fasil integral fuel tank sealants, part 1 for an active control relaxed stability AD-A0678891 N79-28329 transport application [AIAA 79-1653) 879-45327
B-9 REINAW, J. A. PERSONAL AUTHOR INDEX
REINAW, J. A. SAPOZHNIKOV, V. N. Derivation of flight-by-flight spectra for fighter Assembly and testing of flight-vehicle hydraulic aircraft and pneumatic systems /2nd enlarged and revised A79-44462 edition/ RETTIE, I. A79-44893 Numerical computation of optimal evasive maneuvers SATRAN, D. for a realistically modeled airplane pursued by Effects of spanwise blowing on two fighter a missile with proportional guidance airplane configurations [AIAA 79-162 (4] A79-45306 [AIAA 79-1663] A79-45330 REUBUSH, D. N. SCHEIDT, D. C. An experimental and theoretical investigation of Engine-induced structural-borne noise in a general the effect of nonmetric over-the-wing nacelles aviation aircraft on wing-body aerodynamics (NASA-CR-159099] 879-29957 rRASA-TP-15031 '179-29146 SCHIAVELLO, B. REYNOLDS, H. N. Prerotation in centrifugal pumps: Design criteria Ramjet cost estimating handbook rAD-A0569911 879-29188 SCHIJVE, J. RIBAUT, N. Fatigue properties of adhesive-bonded laminated A three dimensional flow computing system sheet material of aluminum alloys applicable to axial and radial flow turbomachines (LR-276] 879-29543 879-28558 SCHLOTB&UER, J. RICE, J. 8. Environmental effects on the elastic-plastic Digital flight control reliability - Effects of properties of adhesives in bond metal joints redundancy level, architecture and redundancy (RAE-LIB-TRANS-1999] 879-29328 management technique SCHNID, G. tAIAA 79-18931 A79-45418 Finite element methods for inviscid and viscous RICH, B. A. flow problems Digital Avionics Information System (DAIS) 879-28(474 Development and demonstration SCH!IDT, S. F. [AD-A068438] 879-29181 Evaluation of the navigation performance of RICHEY, G. K. shipboard-VTOL-landing guidance systems Propulsion system and airframe integration fAIAA 79-1708] A79-45362 consideration for advanced air-to-surface aircraft SCHULTZ, B. S. rAIAA PAPER 79-11201 A79-44800 Maintenance improvement: An analysis approach RIETSCHLIN, J. including inferential techniques. Volume 2: Goniometric aerodynamics: A different perspective: Technical report Description - Applications CAD-A0683811 879-28130 [AIAA 79-16501 A79-45326 SEDIN, Y. C.-J. RIND, D. Axisymmetric calculations of transonic wind tunnel Monitoring stratospheric winds with interference in slotted test sections Concorde-generated infrasound A79-46225 SEEGNILLER, H. L. RIVKII, N. I. Trailing-edge flows at high Reynolds number Aircraft antenna systems tAIAA PAPER 79-15031 A79-46697 A79-44892 SEHRA, A. K. ROSS, V. L. The effect of blade-to-blade flow variations on A piloted simulator investigation of helicopter the mean flow-field of a transonic compressor precision decelerating approaches to hover to (AIAA PAPER 79-15151 A79-46703 determine single-pilot 188 /SPIFR/ requirements SETTLES, G. S. [AIAA 79-18861 A79-45413 Investigation of three-dimensional shock/boundary ROSSKNECHT, K. layer interactions at swept compression corners Fasil integral fuel tank sealants, part 1 [AIRA PAPER 79-14981 A79-46693 At)-A0678891 879-28329 SHANROTR, S. J. RYKEN, J. The prediction of the turbulent flow field about A study of requirements, model configurations, and an isolated airfoil test plans for air cushion system comparison tests (AIAA PAPER 79-15(43] A79-146719 rAD-A0690061 879-28373 SHATRAKOV, ID. C. RYLE, D. Aircraft antenna systems Wing design, body design, high lift systems and flying qualities with introduction SHENOY, K. B. N79-28125 An iterative lifting surface method for thick RYNASKI, E. G. bladed hovering helicopter rotors Gust alleviation using direct turbulence [AIAA PAPER 79-1517] A79-46705 measurements SHRAGER, J. J. rAIRA 79-167 (4] A79-45339 The analysis of Rational Transportation Safety Gust alleviation - Criteria and control laws Board small single-engine fixed-wing aircraft IAIAA 79-1676] A19-45340 accident/incident reports for the potential Design criteria for optimal flight control systems presence of low-level wind shear AIAA 79-1782] A79-145409 (AD-A069438] 879-28848 SIBILSKI, K. Longitudinal dynamic stability of a hovering S helicopter with a sling load SAIN, N. K. A79-44094 Alternatives for jet engine control SINGS, J. [NASA-CR-158390] 879-29190 Application of vortex lattice method for the SALAS, N. D. evaluation of the aerodynamic characteristics of A careful numerical study of flowfields about wings with and without strakes external conical corners. I - Symmetric B79-28145 configurations SLIGHTA!, N. J. r ATAA PAPER 79-1911] A79-46701 Digital Avionics Information System (DAIS) SARDLIN, N. H. Development and demonstration Flight spectra development for fighter aircraft [AD-A068438] 879-29181 A79-44459 SMITH, C. N. SANGER, N. L. Aerodynamic characteristics of forebody and nose Fffect of rotor meridional velocity ratio on strakes based on 8-16 wind tunnel test response to inlet radial and circumferential experience. Volume 1: Summary and analysis istortion [RASA-CR-3053] 879-28143 ASA-9'P-12781 879-28177
8-10 PERSONAL AUTHOR INDEX TURRIZIANI, H. V.
SIXTH, J. J. STEWART, V. N. NASA cY6 let engine diagnostics program: Low speed wind tunnel test of ground proximity and Long-term CF6-6D low-pressure turbine deck edge effects on a lift cruise fan V/STOL deterioration configuration, volume 2 [NASA-CR-159618] 179-29191 [NASA-CR-152248) N79-28142 SIXTH, J. L. STIVERS, L. S., JR. Forecast of future aviation fuels. Part 1: Supercritical airfoil boundary-layer measurements Scenarios [AIAA PAPER 79-15011 *79-46695 (NASA-CR-158871) 179-29354 STOCKENER, F. J. SMITH, N. K. Experimental study of low temperature behavior of Enthalpies of combustion of ramjet fuels aviation turbine fuels in a wing tank model A79-46055 [NASA-CR-159615] 1379-29355 SMITH, H. STOCKMAN, N. 0. Advanced General Aviation Turbine Engine (GATE) Recent applications of theoretical analysis to study V/STOL inlet design [NASA-CR-15962 11] N79-29189 [NASA-Tfl-79211) 1379-29143 511TH, H. B. STONE, J. E. Preliminary airworthiness evaluation RU-21 H Hypersonic airframe structures: Technology needs guardrail V aircraft and flight test requirements [*0-1.068347) N79-29178 [NASA-CR-3130] 1379-28168 511TH, T. B. STONE, V. J. Impact of digital computer technology on flight Overview of the C-SA Service Loads Recording Program systems A79-44456 [AIAA 79-16411 *79-45320 STRIDSBERG, S. SlITHERS, B. N. Effect of viscosity on wind-tunnel wall Aerial isolation - a study of the interaction interference for airfoils at high lift between co-sited aerials [AIAA PAPER 79-15341 A79-46715 A79-46240 STROBEL, J. N. SORENSEN, J. A. Jet engine exhaust analysis by subtractive Filtering and threat logic design and evaluation chromatography for the beacon collision avoidance system [AD-A067898] 1379-28178 1*1*1. 79-1707] *79-45361 SOUTH, J. C., JR. Vector processor algorithms for transonic flow T calculations TANEJA, N. K. [A1AA 79-14571 *79-45273 Disaggregate mode-share models for air freight SOUTHERN, V. B. policy analysis Development of computer-generated phenograms to A79-45249 forecast regional conditions hazardous to TARASENKO, V. P. low-flying aircraft Extremal radio-navigation rAD-A0688121 N79-28161 A79-44878 SOVIJE, D. I. TAUBER, N. E. A study of altimeter-controlled terrain-following Computation of subsonic and transonic flow about systems lifting rotor blades N79-28162 (AIAA 79-1667) *79-45333 SPAID, F. V. TAYLOR, V. F. Supercritical airfoil boundary-layer measurements Continuation study of alternate fuels nitrogen fAIAA PAPER 79-15011 A79-46695 chemistry SPEARNOCK, R. A. [*0-1.069011] 1379-29359 Display measurements. Measurements of TEETER, S. L. reflectance-type displays Low EN signature response techniques [AD-A068602) 979-29185 [AD-A068211) 179-29397 SPIEKHOUT, D. J. TISCHLER, N. B. Use of AIDS recorded data for assessing service Application of the equilibrium spin technique to a load experience typical low-wing general aviation design A79-44455 [AIAA 79-16251 A79-45307 SPROAT, B. H. TOIlET, J P. Proceedings from the Government/Industry Workshop Low EN signature response techniques on the Reliability of Nondestructive Inspections [AD-A068211) 1379-29397 [AD-A068223] 1379-29531 TOWER, N. N. STAINBACK, P. C. Air Force Academy aeronautics digest, fall 1978 Evaluation of flow quality in two NASA transonic [*0-1.0690413] 179-30134 wind tunnels TRAVASSOS, N. [AI*A PAPER 79-15321 *79-46714 Parallel procedures for aircraft parameter STALLARD, D. V. identification and state estimation Optimal missile guidance for low miss and [AIAA 79-16361 *79-45316 perpendicular impact TRIBBLE, B. L. AIAA 79-17341 A79-5377 Test simulation of fighter aircraft maneuver load STAIPER, L. spectra Jet engine exhaust analysis by subtractive A79-44463 chromatography TRONP, P. J. [AD-A067898) 1379-28178 The effects of gust alleviation on fatigue in STANLEY, A. N. 2024-T3 Aiclad Overview of the C-SA Service Loads Recording Program [NRL-TR-78061$-U] N79-2954$ A79-44456 TSYBAEV, B. G. STAUTBERG, J. A. Aircraft antenna systems Digital Avionics Information System (DAIS) A79-44892 Development and demonstration TUCK, E. 0. IAD-A0684381 1379-29181 Unsteady small-gap ground effects STECK, S. A. [*11-1.068400] 1379-28157 Evaluation of the navigation performance of TONG, F. C. C. shipboard-VIOL-landing guidance systems Identification of aircraft parameters in [*1*1. 79-17081 *79-45362 turbulence with non-rational spectral density STEIN, G. N79-28182 Flight test experience with an adaptive control TURRIZIANI, B. V. system using a maximum likelihood parameter Sensitivity study for a remotely piloted estimation technique microwave-powered sailplane used as a (*1*1. 79-17021 *79-45357 high-altitude observation [NASA-CR-159089) 179-28134
B-Il
TYSON, N. J. PERSONAL AUTHOR INDEX
TYSON, !. J. WATLER, J. H., JR. Overview of the C-SR Service Loads Recording Program Earth-Referenced Maneuvering Flight Path Display A79-44456 [AIAR 79-1894] A79-45421 WATSON, J. B. Bolted field repair of composite structures U AD-A067923] 879-28238 U!RUH, J. P. WELLS, W. H. Engine-induced structural-borne noise in a general A model for unsteady effects in lateral dynamics aviation aircraft for use in parameter estimation r NAsA_cR_159099] 879-29957 fRIAR 79-1638] A79-45318 ITRIE, D. N. The relationship of unsteadiness in downwash to Aerodynamic development of a small horizontal tail the quality of parameter estimates for an active control relaxed stability (AIAA 79-1639] A79-45319 transport application WEST, D. S. [AIAA 79-16331 A79-45327 Jet engine exhaust analysis by subtractive ORNES, J. N. chromatography Development of the Navy H-Dot Automatic Carrier [AD-A061898] N79-28178 Landing System designed to give improved WHALER, H. P. approach control in air turbulence Digital Avionics Information System (DAIS) [AIAA 79-17721 A79-45401 Development and demonstration [AD-A068438] 979-29181 WHITE, D. J. V Flight spectra development for fighter aircraft VAN DER VOOREN, J. A79-44459 Results of an improved version of LTRAN2 for WHITE, C. H. computing unsteady airloads on airfoils An experimental comparison of the readability of oscillating in transonic flow two digital altimeters IAIAA PAPER 79-1553] A79-46726 (ARL/SYS-NOTE-60] 879-29180 VAN GOOL, N. F. C. WHITE, J. A. A simulator investigation of roll response A multi microprocessor flight control system requirements for aircraft with design principles rate-command/attitude-hold flight control [RIAR 79-1700] A79-45355 systems in the landing approach and touchdown WHITFIRID, A. [AIAA 79-16791 A79-45342 Computer aided design of mixed flow turbines for VANDEIHRAENBUSSCHE, H. turbochargers The prediction of compressor blade row [ASNE PAPER 78-GT-191] A79-44794 performance: Numerical methods and theoretical WIBERLY, S. E. approaches Composite structural materials N79-28557 (NASA-CR-158851] 879-28235 VARGESTEL, U. P. J. A. WILENT, C. E. Fatigue properties of adhesive-bonded laminated Digital Avionics Information System (DAIS) sheet material of aluminum alloys Development and demonstration [LR-276] 879-29543 EAD-A0684381 H79-29181 VANGUCHT, A. WILKINSON, W. Problems involved in starting and shutdown of gas Investigation of stress-strain history modeling at turbines: Thermodynamic and mechanical aspects stress risers, phase 2 N79-28565 AD-A069162] 879-28620 VANIIPZIG, H. T. N. WILSON, L. B. Fatigue properties of adhesive-bonded laminated Disaggregate mode-share models for air freight sheet material of aluminum alloys policy analysis [LP-2761 879-29543 A79-45249 VAUGHN, N. B., JR. WILSON, P. An aerodynamic analysis of deformed wings in FAA air traffic activity, fiscal year 1978 subsonic and supersonic flow [AD-A067910] 879-28188 (AD-A067586) N79-28149 WILSON, W. W. VENDOR, J. N. Methods of gust spectra prediction for fatigue Subsonic flow past an oscillating cascade with damage finite mean flow deflection A79-44461 rATAR PAPER 79-1516] A79-46704 VINTNER, B. A. VIETS, H. Demonstration of aircraft wing/store flutter Unsteady wing boundary layer energization suppression systems rAIAA 79-16311 A79-45312 A79-46238 VIRELER, A. WOOD, L. J. Minimum expected cost control of linear systems Minimum expected cost control of linear systems with uncertain parameters - Application to with uncertain parameters - Application to remotely piloted vehicle flight control systems remotely piloted vehicle flight control systems fRIAR 79-17451 A79-45387 [AIRA 79-17451 A79-45387 VISWANATH, P. R. WRESTLER, C. C., JR. Trailing-edge flows at high Reynolds number Pacific area evaluation of a commercial Omega rAIAA PAPER 79-15031 A79-46697 navigation system installed in a VC-118 VONGLAHN, U. aircraft, supplement 1 Wing aerodynamic loading caused by jet-induced AD-A0681061 N79-28165 lift associated with STOL-OTW configurations WRIGHT, B. N. rNASA-TM-79218] N79-28146 Influence of jet fuel on permeation and VONRAPPARD, A. flammability characteristics of graphite epoxy A gas turbine off-design computing system composites N79-28563 [AD-A068586] 879-28245 TOSS, H. WYNDHAE, B. A. Contribution to the calculation of the dynamic Reflection elimination in secondary surveillance behavior of industrial turbocompressor circuits radar N79-28564 A79-46241
WALLACE, P. J. YAMAHOTO, K. Computer aided design of mixed flow turbines for Peak Strouhal frequency of subsonic jet noise as a turbochargers function of Reynolds number ANNE PAPER 78-Gt-1911 A79-44794 [RIAR PAPER 79-1525] A79-46709
B-12 PERSONAL AUTHOR INDEX ZINWERWAB, D. B.
TIN, A. K. K. Forecast of future aviation fuels, part 1: Scenarios (NASA-CR- 158871] 879-29358 YDDER, J. B. Development of criteria for monitoring of airport ground pollution. Volume 1: Study rAD-A067242] 879-29197 Development of criteria for monitoring of airport ground pollution. Volume 2: Data validation procedures AO-A0672431 R79-29198 YOUNG, S. U. An experimental, low-cost, silicon slurry/aluminide high-temperature coating for superalloys INASA-TM-79178) 879-29292
z ERUKOVA, N. N. Aircraft instrument components /3rd revised and enlarged edition/ A79-44884 ZIN!R!AW, D. B. Laser anemometer measurements at the exit of a 763-C20 combustor NASA-CR- 159623] 879-28456
B-13
CONTRACT NUMBER INDEX
AERONAUTICAL ENGI NEE RING / A Continuing Bibliography (Suppl. 115) NOVEMBER 1979
HAS-9913 #79-46702 Typical Contract Number Index Listing NAS1-13500 879-28134 RAS1-14833 #79-46714 RAS1-14861 879-29957 NAS1-14924 879-28168 NAS2-9460 879-10038 TIAS1-15005 979-28143 - I N#Si-15148 879-28232 CONTRACT NASA ACCESSION 1(451-15214 #79-46719 NUMBER NUMBER ?fAS1-15223 479-46714 8(151-15351 479-46710 NAS1-15379 879-28419 84S2-7350 879-29196 Listings in this index are arranged alphanumerically by contract number. NAS2-9882 879-28142 Under each contract number, the accession numbers denoting documents 8453-20631 879-29191 that have been produced as a result of research done under that contract NAS3-20757 879-29189 are arranged in ascending order with the /AA accession numbers appearing 314S3-20814 979-29355 RAS3-21267 979-28456 first. The accession number denotes the number by which the citation is 9454-2526 #79-45325 identified in either the /AA or STARsectiorr, NGL-33-018-003 !IRTS PROJ. 77/16-4 1y-76-C-02-3077 N79-28235 179-29169 879-28136 RGR-09-010-085 IF PROJ. 2051 EY-76-C-04-0789 A79-45258 1179-29182 879-29152 908-33-016-201 AV P p OJ. 2052 F-33615-76-C-2118 879-28136 5179...7918 479-46703 NGR-3 9-009-270 SF PROJ. 2104 F04701-75-C-0739 A79-46709 879-28189 879-29164 88 PROJ. 062-230 879-29200 P08635-77-C-0248 N79-28157 SF PROJ. 2304 879-29200 NSG-1301 879-29958 1179-28393 P30 602-77-C-0166 NSG-1417 #79-45318 A? PROJ. 2307 N79-29397 479-45319 N79-28156 F33615-73-C-3051 9511-1496 #79-45303 979-791150 579-45339 NSG-1570 #79-45307 SF PROJ. 2308 479-45340 NSG-1579 879-28136 879-29270 F33615-75-c-1178 NSG-2095 879-28984 411 PROJ. 2312 N79-29181 NSG-30 118 879-29190 879-28161 P33615-75-0-3078 NSG-3116 979-29354 A? PROJ. 2314 379-28620 N00014-76-C-0157 1179-29397 F33615-75-C-5218 N79-28157 SF PROJ. 2402 879-29182 N00014-77-C-0775 R79- 29173 F33615-75-c-5 236 #79-45412 979-291-74 A79-44463 N00014-78-C-0079 879-29520 P33615-76-C-0528 A79-46702 SF PROJ. 2404 R79-29964 N00014-78-C-0493 1179-29177 F33615-76-C-0930 N79-28372 SF PROJ. 3012 1179-29163 N00014-78-C-0588 1179-29188 F33615-76-C-2043 879-28373 4? PROJ. 7231 W79-29188 N00014-78-C-0739 P79-29163 F33615-76-C-3039 N79-28374 SF PROJ. 735' #79-46238 N00014-78-G-0155 979-29300 ?33615-76-C-3098 A79-45409 AF- AFOsR-ISPA-78-0009 N79-29520 N00019-78-C-0177 479-46055 F33615-76-C-5155 N79-29359 AF- AFOSP-77-3418 R79-29300 F60921-77-C-0234 179-45316 P33615-76-C-5191 479-46713 IF-S p0511-78-3575 N79-29295 N62269-76-C-0370 #79-45312 F33615-77-C-0616 979-28175 AF-#FOSR-2611-74 979-28178 N62269-77-C-0366 F79-28393 F33615-77-C-0800 N79-28238 AP-AFOSR-3431-77 879-29138 862269-78-8-4580 879-28161 P33615-77-0-3016 979-29150 04 PROJ. 1T,1-62209-kfl-76 A79-46730 P68335-76-C-2281 879-28456 F33615-77-C-3060 N79-29344 DR PRO-3. 4(11-61102-8-525 N79-29173 N68335-77-C-0555 R79-28187 879-29174 H79-29532 D44G29-76-C-0027 F33615-77-C-5139 SWRI PROJ. 02-4860 N79-2898h N79-28329 R79-29957 879-29962 P33657-76-0-0873 RP41400000 879-28245 D##G29-78-G-0036 A79-44461 WP41461406 879-29532 1179-28149 P41608-76-0-4005 505-02-33-05 879-28614 04 #G46-76-C-0016 W79-29531 505-04 879-28117 1179-28170 P41608-77-0-4021 505-04-22 879-28456 111fF- 2°B77-001136 H79-29531 505-06-53-01 879-28138 R79-28169 ?41608-78-C-1240 505-08-33-11 879-29171 DT-PAA77NA-4037 879-29364 505-09-13-11 879-28796 479-45361 F44620-75-C-0080 505-10-31 879-29144 DOT-FA73EI-377 A79-46693 505-11-13-04 979-29146 879-28187 P49620-77-C-0029 505-11-43-07 879-29199 DOT- 11 #76 1' (1-3 725 979-29270 513-54-13-02 879-29195 879-29197 F49620-77-C-0090 517-53-43-01 879-28982 R.79-?9199 N79-28156 879-291(11 DOT-FA77UST-37 804903-78-C- 0176 743-03 979-28176 879-29 164 N79-28129 791-40-13-01 879-28158 F -7ff-C-02-4867 879-28130 1179-29522 U79-29131 c-i 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No.
NASA SP-7037 (115) ______4. Title and Subtitle 5. Report Date AERONAUTICAL ENGINEERING November 1979 A Continuing Bibliography (Supplement 115) 6. Performing Organization Code
7. Author(s) 8. Performing Organization Report No.
10. Work Unit No. 9. Performing Organization Name and Address
11. Contract or Grant No. National Aeronautics and Space Administration Washington, D. C. 205146 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address
14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
This bibliography lists 273 reports, articles, and other documents introduced into the NASA scientific and technical information system in October 1979.
17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies
19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price E02 Unclassified Unclassified 98 $14.75 HC
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