NASA Aeronautical NASA SP-7037 (100)Engineering Septem ber 1978I \MM %J 1J % A Continuing -^ • ^** Wt^m m Bibliography with Indexes National Aeronautics and Space Administra >>Aeronautical Engineering Aen sring Aeronautical Engineering gineering Aeronautical Engine ^al Engineering Aeronautical E lautical Engineering Aeronaut Aeronautical Engineering Aerc ring Aeronautical Engineeringjineer jng Aeronautical Engine al Engineering Aeronautical Ei autical Engineering Aeronaut! leronautical Engineering Aero ing Aeronautical Engineering https://ntrs.nasa.gov/search.jsp?R=19780025092 2020-03-22T02:05:47+00:00Z ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges: STAR(N-10000 Series) N78-24042—N78-26046 IAA (A-10000 Series) A78-36170—A78-39782 This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information Systems Company. NASA SP-7037(100) AERONAUTICAL ENGINEERING A Continuing Bibliography Supplement 100 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 August 1978 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA) Scientific and Technical Information Branch 1978 National Aeronautics and Space Administration Washington, DC This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, at the price code E02 ($475 domestic, $9 50 foreign) INTRODUCTION Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971 Since that t ime, monthly supplements have been issued. Tins supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 295 reports, journal articles, and other documents originally announced in August 1978 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (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 (A78-10000 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 IAA are available at the rate of $250 per microfiche on demand, and at the rate of $1 10 per microfiche for standing orders for all IAA microfiche The price for the IAA 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 (N78-10000 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 Price codes are given in the tables on page VH of the current issue of STAR Microfiche is available regardless of age for those accessions followed by a ft symbol 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 Unit 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. 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Science Information Available from the Energy Research and Development Administration (TID-4550). which may be obtained without charge from the ERDA Technical Information Center Avail Univ Microfilms Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm All requests should cite the author and the Order Number as they appear in the citation Avail USGS Originals of many reports from the U S Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction Avail HMSO Publications of Her Majesty's Stationery Office are sold in the U S by Pendragon House. 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U S Patent Office, at the standard price of 50 cents each, postage free Other availabilities If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line GENERAL AVAILABILITY All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA A listing of public collections of NASA documents is included on the inside back cover SUBSCRIPTION AVAILABILITY This publication is available on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements is $45 00 domestic. $75 00 foreign All questions relating to the subscriptions should be referred to NTIS. Attn Subscrip- tions, 5285 Port Royal Road. Springfield Virginia 22161 VI ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics and Astronautics Technical Information Service 750 Third Ave New York. NY 10017 British Library Lending Division. Boston Spa. Wetherby. Yorkshire. England Commissioner of Patents U S Patent Office Washington. D C 20231 Pendragon House. Inc 899 Broadway Avenue Redwood City. California 94063 Superintendent of Documents U S Government Printing Office Washington, D C 20402 University Microfilms A Xerox Company 300 North Zeeb Road Ann Arbor. Michigan 48106 Energy Research and Development Administration Technical Information Center P O Box 62 Oak Ridge. Tennessee 37830 ESA-Space Documentation Service ESRIN ' Via Galileo Galilei 00044 Frascati (Rome) Italy Her Majesty's Stationery Office P O Box 569. S E 1 London. England University Microfilms. Ltd Tylers Green London, England U S Geological Survey 1033 General Services Administration Building Washington. D C 20242 U S Geological Survey 601 E Cedar Avenue Flagstaff. Arizona 86002 NASA Scientific and Technical Information Facility PO Box 8757 B W I Airport. Maryland 21240 National Aeronautics and Space Administration Scientific and Technical Information Branch (NST-41) Washington. D C 20546 National Technical Information Service 5285 Port Royal Road Springfield. Virginia 22161 U S Geological Survey 345 Middlefield Road Menlo Park. California 94025 U S Geological Survey Bldg 25. Denver Federal Center Denver, Colorado 80225 Zentralstelle fur Luftfahrtdoku- mentation und -Information 8 Munchen 86 Postfach 880 Federal Republic of Germany vn TABLE OF CONTENTS IAA Entries 369 STAR Entries 389 Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT If NASA ACCESSION NUMBER TITLE AUTHORS. CONTRACT OR GRANT. REPORT NUMBERS. »-N78-10020*/jf Boeing Vertol Co Philadelphia Pa •« •-WIND TUNNEL INVESTIGATION OF ROTOR LIFT AND PROPULSIVE FORCE AT HIGH SPEED DATA ANALYSIS —»-Frank McHugh Ross Clark and Mary Soloman Oct 1977 211 p 3 Vol ^.(Contract NAS1-14317) pMNASA-CR-145217-App-l 0210 -11135 -1 ) Avail NTIS- HC A10/MF A01 CSCL01A-* The basic test data obtained during the lift-propulsive force limit wind tunnel test conducted on a scale model CH-47b rotor are analyzed Included are the rotor control positions blade loads and six components of rotor force and moment corrected for hub tares Performance and blade loads are presented as the rotor lift limit is approached at fixed levels of rotor propulsive force coefficients and rotor tip speeds Performance and blade load trends are documented for fixed levels of rotor lift coefficient as propulsive force is increased to the maximum obtainable by the model rotor Test data is also included that defines the effect of stall proximity on rotor control power The basic test data plots are presented in volumes 2 and 3 Author -AVAILABLE ON MICROFICHE — CORPORATE SOURCE -PUBLICATION DATE -AVAILABILITY SOURCE - COSATI CODE TYPICAL CITATION AND ABSTRACT FROM IAA NASA SPONSORED. AIAA ACCESSION NUMBER TITLE . TITLE OF PERIODICAL- H ,-* A78-13071 • ft J I anrTsf _^. Toward a new V/STOL generation L Roberts-*- B Anderson (NASA, Ames Research Center, Moffett Field, •*- Astronautics and Aeronautics, volCalif^Astrona ti 15, Nov 1977;T> 22-27 While many V/STOL problems are now better understood and technology has progressed to the point where higher thrust/weight ratios and greater stability augmentation are achievable, a number of still existing insufficiencies provide a sobering reminder that learning in ground testing and simulation, and careful methodical planning, are a prerequisite for any research and development program The present paper is centered on the major technical problems for the Navy Type multimission V/STOL aircraft The aircraft's configura- tions with and without forward lift fan are discussed, along with the propulsion systems, testing techniques, controls, displays, flight dynamics, and ground/flow field interactions V P AVAILABLE ON MICROFICHE -AUTHORS AUTHOR'S AFFILIATION .PUBLICATION DATE VIII AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 100) SEPTEMBER 1978 IAA ENTRIES A78-36203 H Characteristics of flow past fuselages and wing-fuselage systems of gliders (Zjawiska oplywu kadlubow szybowcow i ukladow skrzydlo-kadlub) J Ostrowski, M Litwm- czyk, and L Turkowski Archiwum Budowy Maszyn, vol 25, no 1, 1978, p 91-104 In Polish Flow visualization tests were conducted on gliders, and the velocity fields in the diffusor regions with positive pressure gradient on the fuselage and wing-fuselage transition were measured Secon- dary flow effects, influencing the rate of separation, were shown The influence of geometry of the wing-fuselage system on flow separation was studied Different types of separation on the wing near the fuselage are shown in photographs Principles for proper design of fuselage and wing-fuselage transition zone ensuring minimal effect of secondary flows on separation are announced P T H A78-36204 fl Discussion of results of studies on the design of laminar airfoils for stunt gliders (Omowieme wynikow badan zwiazanych z konstruowaniem profilow lammarnych dla szybowcow wvczynowych) J Ostrowski, S Skrzynski, and M Litwmczyk Archiwum Budowy Maszyn, vol 25.no 1,1978, p 105-120 5 rets In Polish The mam results of several studies dealing with phenomena influencing the properties of laminar airfoils are examined Deflec- tion of the flow in the boundary layer and local separations of the laminar layer (laminar bubbles) were investigated on several airfoils These phenomena are classified and their influence on the airfoil characteristics is evaluated The choice of pressure distribution leading to best lift-to-drag ratio is studied P T H A78-36205 f/ Hot-wire velocity measurements in thin boun- dary layers (Pomiary termoanemometryczne w cienkich warstwach przysciennych) S Skrzynski and M Litwmczyk Archiwum Budowy Maszyn, vol 25, no 1,1978, p 137-145 5 refs In Polish Hot wire techniques for measurements in the thin boundary layer on a laminar airfoil are studied Errors in analog measurement of the velocity profile in the boundary layer due to linearization, the rectifying effect of the hot wire anemometer, the effect of the wall on the hot wire probe, and the change in the heat transfer law in the presence of a velocity gradient are analyzed A special copper plating process for the probes is described P T H A78-36210 ft Calculation of airfoil drag (Obliczema oporu prof Now lotniczych) Z Nowak Archiwum Budowy Maszyn, vol 25, no 1,1978, p 213-222 10 refs In Polish A numerical method based on classical boundary layer theory is proposed for calculating the drag coefficient of airfoils at small angle of attack, Reynolds number of several million, and low subsonic speeds The polar function of the airfoil, that is, the drag coefficient as a function of lift coefficient and Reynolds number, is calculated A point on the polar function curve is determined in two steps (1) for a given value of the lift coefficient, the pressure distribution along the airfoil contour in the flow of an ideal fluid without separation is determined, and (2) for a given Reynolds number, the preceding results are used to calculate momentum losses in the boundary layer P T H A78-36216 ff Remarks on design of supersonic wind tunnels (Uwagi o projektowamu naddzwiekowych tuneli aerodynami- cznych) 2. Dzygadlo, J Kaczmarczyk, and A Tarnogrodzki Archiwum Budowy Maszyn, vol 25, no 1, 1978, p 285-294 9 refs In Polish A brief survey of various design solutions for supersonic wind tunnels is presented A method of determining the mam aerodynamic parameters of a high-pressure continuously acting tunnel is given Remarks on the design of individual parts and auxiliary installations are made P T H A78-36279 Aircraft propulsion from the back room /Sixty-sixth Wilbur and Orville Wright Memorial Lecture/ W Hawthorne (Cambridge University, Cambridge, England) Aero- naut/catJournal, vol 82, Mar 1978, p 93-108 25 refs A brief review is presented of the early history of jet engines and gas turbines along with a historical review of work done at the RAE Turbine Division Particular attention is given to gas dynamics, axial compressor research and fuel economy B J A78-36280 The certification of tight aircraft D Stinton (Civil Aviation Authority, Airworthiness Div, Redhill, Surrey, England) Aeronautical Journal, vol 82, Mar 1978, p 109-116 Consideration is given to various aspects of the airworthiness certification of light aircraft according to British Civil Airworthiness Requirements Airworthiness design is discussed along with the tasks of flight testing It is maintained that adequate test flying should be the standard by which to judge the reliability of light aircraft B J A78-36323 # Study on problems of terminal site location Y Nagao and I Wakai (Kyoto University, Kyoto, Japan) Kyoto University, Faculty of Engineering, Memoirs, vol 39. Oct 1977, p 548-565 16 refs The location of a large terminal facility, e g , an airport, harbor, or truck depot, is considered with reference to the environmental factors which affect it, and its effect, in turn, upon the environment Two cases of land use are presented, single purpose use, and mixed use Linear programming is applied to the problems associated with mixed use, while 0-1 mixed integer programming is applied to single purpose use Also considered is the role of the government, both in establishing environmental standards, and in the regulation of commerce Attention is given to airport planning, which is discussed in terms of the Japanese Act for Prevention of Negative Effects upon Areas Surrounding Airports, passed in 1967 • D M W 369 A78-36366 A78-36366 ff Application of the integral-transformation method to three-dimensional unsteady problems of the theory of cascades (Primeneme metoda mtegral'nykh preobrazovann k tre- khmernym nestatsionarnym zadacham teorn reshetok) G S Lipovoi (Akademna Nauk Ukramskoi SSR, Institut Matematiki, Kiev, Ukrai- nian SSR) In Analytical, numerical and analog methods in problems of heat conductivity Kiev, Izdatel'stvo Naukova Dumka, 1977, p 173-183 7 refs In Russian The Fourier transformation and the factorization method are used to solve the problem of determining pressure differences on elements of a three-dimensional cascade oscillating harmonically in a subsonic gas flow The problem is posed for rectangular plates and for plates whose edges are directed to the flow at angles not equal to 90 deg The method can be extended easily to the case of an immobile multirow cascade with equal spacing, oscillating with equal phase shift and with phase shift in every row B J A78-36380 Experimental evaluation of an array technique for zenith to horizon coverage W G Mavroides and FL J Mailloux (USAF, Bedford, Mass) IEEE Transactions on Antennas and Propagation, vol AP 26, May 1978, p 403-406 11 refs An experimental study of a new array concept with application to providing low cost efficient antennas with hemispherical coverage for aircraft to satellite communication links is described The combined array-surface wave antenna consists of 64 waveguide elements scanned conventionally except at endfire At endfire the array is shorted to become a corrugated surface-wave antenna and excited by an eight-element feed to provide a directional beam near the horizon The array is rotated to give hemispherical coverage iAuthor) A78-36431 Integrally stiffened laminate construction E E House (Lockheed-Georgia Co , Marietta, Ga ) (Society for the Advancement of Material and Process Engineering, National Tech- nical Conference, 9th, Atlanta, Ga , Oct 4-6, 1977) SAMPE Journal, vol 14, May-June 1978, p 1720 Integral stiffening is defined as the occurring of conventional stiffener shapes, e g , Js, Zs, hats, channels, etc , with the facing plies Attention is given to graphite-epoxy and fiberglass stiffening as it pertains to wing-to-fuselage C-5A fairings Comparisons are made between composite material and honeycomb stiffening It is found that the former saves weight without jeopardizing safety or perfor- mance It is noted that composite material stiffening was able to reduce life cycle costs by requiring fewer and less costly repairs than honeycombs, requiring only visual inspection (as opposed to X-ray and ultrasonic), and simply by lasting longer Tooling and manufac- turing procedures are also reviewed D M W A jointly financed German-Dutch wind tunnel is under develop- ment to provide aeronautical testing facilities in the speed range 62-145 m/sec The flow characteristics of the 6- to 9 5-m cross section wind tunnel include relative deviation of stationary and dynamic pressure across the tunnel section of + or - 0 3%, a local deviation of flow direction of + or -0 1 deg, turbulence of 0 1-0 2%, and local temperature fluctuations of + or - 1C Among the applications of the facility are studies to improve low-speed characteristics of aircraft, and investigations of engme/airframe interference, aircraft noise, helicopter rotor dynamics, flutter charac- teristics and the performance of full-scale aircraft components J M __B A78-36453 System requirements for transition from en- route to approach guidance D H Meyer (Rockwell International Corp, Cedar Rapids, Iowa) Navigation, vol 24, Winter 1977-1978, p 312-328 12 refs The airborne system operational/functional requirements (from navigation using enroute aids to navigation using approach guidance) are examined for the transitional phase of an aircraft flight In this paper the automated navigation system (based nominally on enroute aids) and the ILS/MLS system capabilities are described, and the complementary nature of each is treated To achieve the full potential benefits of proposed landing system operations, it is suggested that on-board enroute navigation systems will be an important aid to exploit fully the resulting operational capabilities Proposed microwave landing system capabilities suggest new opera- tional procedures for predefined maneuvers in the terminal area such as close-in captures and complex approach paths These operational procedures, although only partially available at this time, can be expanded upon based on the operational advantages of the system Equipment configurations are presented to demonstrate the system requirements (Author) A78-36454 Jeppesen charting for area navigation J E Terpstra (Jeppesen-Sanderson, Denver, Colo ) (Institute of Naviga- tion, National Aerospace Meeting, Denver, Colo , Apr 14, 1977) Navigation, vol 24, Winter 1977-1978, p 338344 Area navigation (RNAV) provides freedom for establishing courses This type of system allows the airplane to proceed via navigational guidance to almost any geographical position without having to overfly a radio navaid This capability requires ingenuity for charting since many routes flown by RIMAV-equipped aircraft do not fly on published courses, but prefer to go present position direct to their destination (Author) A78-36446 The design of future cockpits for high perfor- mance fighter aircraft G Roe (British Aerospace, Future Projects Dept, Kmgston-upon-Thames, Surrey. England) Aeronautical Jour- nal,vo\ 82, Apr 1978, p 159-166 8 refs Means of increasing a pilot's g-tolerance through increasing the recline angle of the seat are discussed, and the corresponding modifications required in cockpit displays and ejector design are considered In particular, an articulated seat providing the additional recline angle to give a tolerance increase of about 2-g magnitude over present levels is proposed Optimum locations for flight, sensor and systems data displays are determined on the basis of information requirements for the pilot during takeoff, climb, cruise and other maneuvers A head-up display for flight information and a head-level display for sensor data are suggested J M B A78-36455 Concerning the logical comparison of ATC separation standard assessment models A L Names (Mitre Corp , Metrek Div , McLean, Va ) Navigation, vol 24, Winter 1977-1978, p 345-351 6 refs There exist many models for the determination or assessment of safe separation standards between aircraft flying under an air traffic control (ATC) system Most models fall within the general categories of collision risk or collision avoidance This paper presents a framework for the qualitative comparison of the logical structure of these several models Thus the merits and appropriateness of the several models may be more critically evaluated, and better defini- tion of model applicability made (Author) A78-36447 The German-Dutch low speed wind tunnel DNW M Seidel and F Jaarsma (Stichtmg Duits-Nederlandse Windtunnel, Noordoostpolder, Netherlands) Aeronautical Journal, vol 82, Apr 1978, p 167-173^ A78-36483 ff Preliminary experience with the use of the Yak-40 aircraft in studies of cloud physics and artificial modifica- tions (Predvantel'nyi opyt ispol'zovanna samoleta lak-40 v issledova- nnakh po fizike oblakov i aktivnym vozdeistvnam) F la Voit, E E Kormenko, L A Mirmovich, and A I Furman In Artificial modification of clouds and fogs Moscow, Gidrometeoizdat, 1977, p 96-101 In Russian 370 A78-36941 A78-36494 # Reliability of aviation techniques and flight safety (Bezotkaznost' aviatsionnoi tekhniki i bezopasnosf poletov) P A Solomonov Moscow, Izdatel'stvo Transport, 1977 272 p 114 refs In Russian Basic quantitative flight safety indicators and their determina- tion are discussed Methods of evaluating the effects of failure involving components of the crew-aircraft-groundbase-flight condi- tions are analyzed, and on-board and ground-based technical safety procedures are considered with attention directed to the use of objective monitoring procedures Methods of investigating aviation accidents and component failures are described M L A78-36498 Design for flying D B Thurston New York, McGraw-Hill Book Co , 1978 284 p 56 refs $14 95 Design criteria for civil aviation aircraft are reviewed, with emphasis on FAA handling requirements for flight profiles from takeoff to landing Practical information on changing the speed or climb range of a propeller, equipping an aircraft for IFR flight, and installing position avionics antennas is also presented Among the topics included in the manual are crosswind handling, the advantages of tricycle gear design, the angle-of-attack indicator for approach maneuvers, center-of-gravity determinations, performance com- parisons for advanced aircraft designs, powerplant noise reduction, seaplane design, protective coatings for aluminum and steel structural components, and steps required to obtain FAA certification for an aircraft design J M B A78-36596 * ALC/507 values for some polymeric materials C J Hilado, H J Cummmg, J E Schneider (San Francisco, University, San Francisco, Calif), D A Kourtides, and J A Parker (NASA, Ames Research Center, Moffett Field, Calif) Journal of Combustion Toxicology, vol 5, Feb 1978, p 5-10 5 refs Grant No NsG-2039 Apparent lethal cpncentrations for 50 per cent of the test animals within a 30-min exposure period (ALC/50/) were determined for seventeen samples of polymeric materials, using the screening test method The materials evaluated included resin-glass composites, film composites, and miscellaneous resins ALC(SO) values, based on weight of original sample charged, ranged from 24 to 110 mg/l Modified phenolic resins seemed to exhibit less toxicity than the baseline epoxy resins Among the film composites evaluated, only flame modified polyvinyl fluoride appeared to exhibit less toxicity than the baseline polyvinyl fluoride film (Author) A78-36621 # Ergonomics in commercial aircraft landing (Ergonomik der Landung ernes Verkehrsflugzeugs) R Hemig (Gesell- schaft fur Internationalen Flugverkehr mbH, Berlin, East Germany) Technische-okonomische Information der zivilen Luftfahrt, vol 13, no 5, 1977, p 264-278 In German Various aircraft currently in Interflug service (IL-14, -18, 62, An-24, and Tu-134) are evaluated in terms of overall performance during the landing phase, with attention to the demands different system components place on the pilot and flight personnel The man-machine interface is examined on the basis of navigational and mechanical parameters Approach speed and angles are considered with regard to minimizing pilot strain, and maximizing both pilot and aircraft reaction time DMW A78-36622 ft The technical concepts behind the IL-62M/8/ landing gear (Die techmsche Konzeption der IL-62M /8/ - Fahrwerk) G Dolgushev, N Som, and V Volobuev (Opytno-Konstruktorskoe Biuro, Moscow, USSR) (Grazhdanskaia AviaKna, no 12, 1976 ) Technisch-okonomische Information der zivilen Luftfahrt, vol 13, no 5, 1977, p 292-296 In German (Translation) The landing gear of the IL-62M is identical to that of the IL-62 In both aircraft there is a two-wheel nose gear together with a double tandem mam gear Attention is given to the positioning of the center of gravity, noting that it falls behind the main gear in both empty and loaded configurations The wheels of the nose gear are steerable. and all wheels of the main gear are equipped with hydraulic disk brakes. The shock absorber systems of the main gear and the rear gear are considered especially well engineered The lowering and retraction, respectively, of the rear landing gear is signaled to the pilot by a bright yellow light and a buzzer D M.W A78-36706 * Structural and assembly concepts for large erectable space systems E Katz (Rockwell International Corp, Space Div , Downey, Calif ), E T Kruszewski, and E C Naumann (NASA, Langley Research Center, Structures and Dynamics Div., Hampton, Va ) In The industrialization of space, Proceedings of the Twenty-third Annual Meeting, San Francisco, Calif, October 18-20, 1977 Part 1 San Diego, Calif, American Astronautical Society, Umvelt, Inc , 1978, p 101-113 (AAS 77-205) This paper presents a summary of studies performed by the Space Division of Rockwell un3er contract to the Langley Research Center of the NASA The studies specifically addressed requirements and concepts for erectable structures ranging in size from 100 to 300 .meters - using the Shuttle Orbiter as the operation/assembly base This paper discusses various types of structural configurations and building block elements and the cntena which influence their designs. A brief review is given concerning the subject of flight control An assembly concept is presented - showing how the Orbiter may be equipped and operated to build large area structures .Estimates are also given for cargo bay stowage and mission timelines (Author) A78-36721 Maritime satellite communications - Where we are and where we're going D W Lipke (COMSAT General Corp , Washington, D C ) In The industrialization of space. Proceedings of the Twenty-third Annual Meeting, San Francisco, Calif, October 18-20,1977 Parti San Diego, Calif, American Astronautical Society, Umvelt, Inc , 1978, p 485-490 (AAS 77-257) The need for high quality, reliable, real-time maritime communi- cations has been recognized for some time Satellites now offer the opportunity to overcome the long delays and unpredictable quality commonly experienced with HF and MF transmissions The use of satellites for commercial maritime communications had its origin m 1973 when it was determined that both Navy and commercial maritime requirements could be met with a single satellite system The ensuing program, known as Marisat, now fulfills both require- ments The status of the Marisat program and the European maritime satellite program (Marots) is reviewed, together with the status of international efforts in the development of a maritime satellite communications system (Author) A78-36941 Case of damage involving aircraft and heli- copter components of light metal (Schadensfalle an Flugzeug- und Hubschrauberteilen aus Leichtmetall) G Lange Metall, vol 32, May 1978, p 435-439. In German In most investigations regarding the cause of damage in the case of aircraft it has to be determined whether a certain component has failed because of fatigue or as a consequence of a forced rupture The two types of fracture can be distinguished on the basis of macroscopic and microscopic criteria Macro and microfractography techniques are currently considered as equivalent complementary methods. It appears advisable that a macroscopic fracture analysis precedes an investigation with the scanning microscope The macro- scopic criteria are in many cases sufficient to determine unambigu- ously the type of fracture An investigation with the scanning microscope becomes vital if for some reason macroscopic fracture characteristics are not available or are not sufficient for an adequate fracture analysis In many cases the scanning microscope can also provide information in addition to that required for a determination of the type of fracture It can give indications regarding the origin of cracks or the existence of structural defects. The application of the available investigative techniques is illustrated with the aid of a number of specific cases involving various aircraft and helicopter components. G R 371 A78-36947 A78-36947 Compressible flow about helicopter rotors B C A Johansson (Forsvarsdepartementet Flygtekniska Forsoks- anstalten, Bromma, Sweden) Vertica, vol 2, no 1, 1978, p 1-9 5 refs A lifting-line theory for a helicopter rotor in vertical climb, hover or slow descent, and a disk approximation for the induced velocity field of a helicopter rotor in forward flight are presented The method of matched asymptotic expansions serves to treat the problem of the vertically moving rotor, series solutions are developed in terms of the ratio of a typical blade chord to the rotor diameter and the ratio of the climb velocity to the tip velocity of the rotor A disk of continuous thrust and in-plane force distributions provide the rotor approximations for the case of forward flight Both methods assume a compressible fluid J M B A78-36980 Color displays for airborne weather radar R H Aires and G A Lucchi (RCA, Avionics Systems Div , Van Nuys, Calif) RCA Engineer, vol 23, Feb-Mar 1978, p 5460 The basic characteristics of the PnMUS-400 ColoRadar weather radar system are described Rainfall rates in four different ranges are indicated by four different colors on the display A block diagram of the complete system, including antenna, receiver transmitter, and digital indicator, is provided The transmitter has a variable pulse width and the receiver has a very good noise figure Three comparators determine the four levels corresponding to rainfall of four intensity ranges Range and azimuth are collected in polar coordinate format, but displayed in Cartesian format The resolution of the display is four times better than previously available digital storage type indicators P T H A78-36948 A theoretical study of the effect of blade ice accretion on the power-off landing capability of a Wessex helicopter C Young (Royal Aircraft Establishment, Farnborough, Hants, England) (European Rotorcraft and Powered Lift Aircraft Forum, 3rd, Aix-en-Provence, France, Sept 7-9, 1977) Vertica, vol 2, no 1, 1978, p 11-25 The effect of rotor blade icing on helicopter performance is investigated, calculations are presented to indicate the maximum torque rise which can be tolerated in forward flight before the helicopter autorotational performance is seriously degraded Various decreases in the lift curve slope, together with increases in the drag of the blade section, are employed to simulate the effects of blade ice The excess torque at engine failure provides a measure of the ability of the helicopter to make a successful power-off landing with iced blades J M B A78-37108 A computer-based system for processing dynamic data R E Harper and F M Reichenbach (United Technologies Corp, Pratt and Whitney Aircraft Group, East Hartford, Conn ) ISA Transactions, vol 17, no 1, 1978, p 57-64 Large numbers of dynamic strain measurements are necessary during aircraft gas turbine development to insure product durability A new computer based system for the digital processing of dynamic strain data has just entered service at Pratt & Whitney Aircraft This system features automated handling of calibration and labeling information, and interactive operator communications Special purpose digital devices are used to increase the throughput rate, to perform FFTs and to provide a high quality hard copy readout Expansion to handle other dynamic data, including vibration and pressure, is planned (Author) A78-36949 Flight experiments on aerodynamic features affecting helicopter blade design P Brotherhood and M J Riley (Royal Aircraft Establishment, Farnborough, Hants, England) (European Rotorcraft and Powered Lift Aircraft Forum, 3rd, Aix-en-Provence, France, Sept 7-9, 1977) Vertica, vol 2, no 1, 1978, p 27-42 5 refs From a continuing program of flight research, several features of blade aerodynamics which are associated with rotor performance limits are discussed By systematically roughening sections of the leading edge, those parts of the blade which are most sensitive to a reduction in the local value of maximum life coefficient have been identified The results have been used to examine the feasibility of using reflex cambered sections with nose-up pitching moments but attendant reduced value of maximum lift coefficient, in the inboard regions of the blade In this way, the nose-down moments of highly cambered sections used to advantage nearer the tip may be balanced and control loads reduced From detailed surface pressure measure- ments near the blade tip, the features of the chordwise pressure distribution attributable to unsteady aerodynamics are studied during retreating blade stall, and three dimensional effects assessed The spanwise and chordwise progression of the 'dynamic stall front' is discussed Finally, recent tests to examine the detailed distribution of local incidence and stall are described (Author) A78-36950 IDS - An advanced hingeless rotor system W Jonda and H Frommlet (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany) (European Rotorcraft and Powered Lift Aircraft Forum, 3rd, Aix-en-Provence, France, Sept 7-9, 1977) Vertica, vol 2, no 1, 1978, p 61-72 Research supported by the Bundesmmistenum der Verteidigung The integrated dynamic system (IDS), a hingeless helicopter rotor design, consists of flexible fiberglass blades^ with a single bearing for blade pitching motion, the bearing is supported on the stiff titanium rotor hub The IDS construction permits high control and trimming moments, together with a considerable reduction in moving parts At present, an economical production scheme for the IDS is under development Modular integration of subsystems, high degrees of maintainability and reliability, and lower weight and life cycle costs are being sought J M B A78-37114 Aero engines climb towards better fuel effi- ciency M Hewish New Scientist, vol 78, May 11, 1978, p 380, 381 The low-by-pass-ratio turbofans of the early 1960s had specific fuel consumptions about 15 percent lower than the previous straight turbojets The introduction of high-bypass turbofans in the early 1970s led to a further 20 percent reduction Studies financed by NASA have the objective to reduce fuel consumption by another 12 percent Gams to be made are related to improved components performance, revised maintenance procedures to reduce deterioration in use, reduced sensitivity to factors which cause performance to fall while the engine is in service, and a modified operating cycle, mainly involving changes in bypass ratio, overall pressure ratio, and turbine inlet temperatures The integrated fan duct, which provides struc- tural strength and damps out fan noise, contributes to performance gains by more efficient mixing of the fan flow and hot gas stream from the engine core G R A78-37124 A three-dimensional finite-difference solution of the external response of an aircraft to a complex transient EM environment I - The method and its implementation II - Compari- son of predictions and measurements K S Kunz and K -M Lee (Mission Research Corp , Albuquerque, N Mex ) IEEE Transactions on Electromagnetic Compatibility, vol EMC-20, May 1978, p 328-341 14 refs Contract No F29601 76 C-0064 Experimental charge and current measurements have been performed on an aircraft exposed to the transient electromagnetic field of an electromagnetic pulse simulator These data allow a test of the predictive capabilities of the three-dimensional finite difference method for realistic aircraft simulator test problems The workings of the method and its required inputs and sensitivity to variations in the A78-37154 # SST flight planning and navigation - The first year's experience T C R Guest (British Airways, London, England) Journal of Navigation, vol 31, May 1978, p 250-255, Discussion, p 255-258 372 A78-37409 The triple mertial navigation system (INS) on board the Concorde has proved a valuable aid in insuring accurate and reliable track-keeping on the complex routes operated by the aircraft The Concorde INS includes a Distance Measuring Equipment (DME) update and a card-reader facility for the insertion of waypomt and DME information Problems in the London-Bahrain route, as well as the London-Washington route, are discussed The use of the false waypomt technique to move the aircraft track and provide better sonic boom protection for a given area is considered The approach to Heathrow Airport with the INS also receives attention J M B A78-37155 ff Fully-automated, pilot-monitored air traffic control R L Ford (Royal Signals and Radar Establishment, Malvern, Worcs , England) Journal of Navigation, vol 31, May 1978, p 259267 An analysis of trends in Air Traffic Management indicates that fully automated pilot-monitored ATC may be the system which will prevail in the future The advent of airborne collision-avoidance systems and the economic difficulties in maintaining ever larger contingents of air traffic controllers to meet increases in traffic are among the factors which suggest the likelihood of a transfer of strategic and tactical control of air traffic to the flight deck The fully automated pilot-monitored ATC system would involve develop- ment of on-board electron traffic situation displays and a radical redesigning of flight-deck instrumentation to integrate the ATC, naviaation and aircraft management systems J M B A78-37183 Computer-aided holographic vibration analysis for vectonal displacements of bladed disks K A Stetson and I R Harrison (United Technologies Instrumentation Laboratory, East Hartford, Conn) Applied Optics, vol 17, June 1, 1978, p 1733-1738 Photographs of hologram reconstructions which display vibra- tion modes of bladed disks are digitized and numerically processed to determine translations and rotations of blade segments at radial locations Because the blades are assumed not to move in the radial direction, only two holograms, each with a different sensitivity vector, are required of each vibration mode In addition, a photograph of fringes projected onto the bladed disk is used to determine blade surface contours and compensate for their effect on the holographic fringes (Author) A78-37246 New model VOR/DME E Chaki, M Yamagishi, and T Dejima (Tokyo Shibaura Electric Co, Ltd, Toyo, Japan) Toshiba Review, Mar-Apr 1978, p 10-12 A completely solid-state VOR/DME unit has been developed for R-NAV operation Attention is given to the design characteristics of both the VOR unit and the DME unit Major performance data are presented for the two units B J A78-37297 Analysis of spray combustion in a research gas turbine com bust or P B Patil, M Sichel, and J A Nicholls (Michigan, University, Ann Arbor, Mich ) Combustion Science and Technology, vol 18, no 1-2, 1978, p 21-31 9 refs US Environmental Protection Agency Grant No R-802925-02-2 This paper deals with the analysis of liquid fuel spray combus- tion in an idealized gas turbine combustor The flow, which is assumed to be one dimensional, is divided into two regions (1) the heat up region and (2) the combustion region Appropriate non- dimensional equations have been solved for each region and the solutions matched at the common boundary Analytical expressions have been developed for the burning velocity eigenvalue as well as for the solution in the combustion region The effects of the properties of the fuel and the air as well as effects of the conditions prevalent within the combustor on the solution are discussed Typical results for JP-4 fuel are presented The research gas turbine combustor designed and built at The University of Michigan comes very close to satisfying the assumptions made in this analysis (Author) A78-37341 Modern RF system design for aircraft R A Stampfl (US Naval Material Command, Naval Air Development Center, Warmmster, Pa ) Archiv fur Elektronik und Ubertragungs- techmk, vol 32, May-June 1978, p 247-250 A description is presented of a new system approach, called Tactical Information Exchange System (TIES), which is currently being developed to satisfy RF system design requirements for aircraft Basic developments which make TIES possible are related to the advent of inexpensive surface acoustic wave filters of superior properties, the availability of microprocessors of small size, and the low cost and the great variety of high speed LSI logic The complexity of the avionics design problem for military aircraft is illustrated with the aid of a table which provides a summary of the kind of function which must be performed The advantages of TIES are shown by comparing it with the conventional avionics design approach The state of development of the new system approach is discussed Currently, a demonstration system with all the required modules is being built G R A78-37406 ff Cross-flow characteristics on a cylindrical body at incidence in subsonic flow M L Robinson (Weapons Research Establishment, Adelaide, Australia) Institution of Engi- neers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 4 p 5 refs The flow over a cylindrical body at incidence is examined with special reference to the behavior and role of the attachment line boundary layer Results of previous work on the flow on the leading edges of swept wings are used to establish conditions governing cross-flow behavior on an inclined cylinder Flow observations and measurements of forces and moments on a cylindrical body have confirmed the theoretical prediction that, over a range of Reynolds number encountered in wind tunnel testing, an initially turbulent cross-flow reverts to a predominantly laminar flow at a critical incidence angle Both Reynolds number and conditions on the nose such as roughness greatly influence the critical incidence angle (Author) A78-37408 ff The computation of the unsteady aero- dynamics of bodies near a ground surface G H S Pike (Sydney, University, Sydney, Australia) Institution of engineers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Austra- lia, Dec 5-9, 1977, Paper 4 p As a design aid for ground-effect wing aircraft, a technique for computing the steady or unsteady aerodynamic properties of bodies moving above a ground surface has been developed The computa- tional technique, based on nonlinear aerodynamics rather than the 'small perturbation' method of standard aerodynamic stability theory, is compared to lifting surface theory and experimental data For steady calculations, the nonlinear aerodynamics approach proves superior to lifting surface theory, though for the unsteady case lifting surface theory appears more accurate J M B A78-37409 // The next approximation after boundary layer theory A R Oliver (Tasmania, University, Hobart, Australia) Institution of Engineers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 4 p 10 refs Research supported by the Australian Research Grants Commit tee A rapid stable solution method for the Navier-Stokes equations in terms of vorticrty is developed as a design aid for dealing with unsteady flow effects associated with machine blades The solution technique is intended to provide an intermediate approximation between thin boundary layer theory and the full Navier-Stokes equations, if used close to the trailing edge of the blade, the solution method may reduce the length over which the full equations need to be applied The case of laminar flow with zero pressure gradient in two dimensions is treated J M B 373 A78-37411 A78-37411 ft Boundary layer blowing tests on a radial d iff user in low and subsonic Mach range J S de Krasmski (Calgary, University, Calgary, Alberta, Canada) and M Mehra Institution of Engineers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 5 p 9 refs Research supported by the National Research Council of Canada Radial diffusers in incompressible flow are shown to exhibit acceptable maximum efficiencies if blowing of the boundary layer at the origin of the entry bells is instituted Increasing the ratio of the jet velocity at the slot to the entry velocity results in higher stability for the diffusers, the overall efficiency of the diffusers may approach 70% for specified slot area and entry area geometries Cones of varying angles may be adopted to reduce the initial Mach number to unity at the throat, and thus make the radial diffuser design suited to supersonic diffusion The quiet operation of the radial diffusers is also noted J M B A78-37413 « The turbulent flow through a sudden enlarge- ment at subsonic speeds S Kangovi (National Aeronautical Laboratory, Bangalore, India) and R H Page (Rutgers University, New Brunswick, N J ) Institution of Engineers, Australian Hydrau- lics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 4 p 10 ref s The flow through a sudden enlargement was experimentally investigated in the Mach number range of 01 to 095 Results include variation of base pressure and recovery pressure with reference Mach number The upstream influence distance and the locations of reattachment and secondary separation points are also reported (Author) A78-37417 # The mean velocity field of unsteady subsonic air jets W H Harch and K Bremhorst (Queensland, University, St Lucia, Australia) Institution of Engineers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 4p 17 refs Mean streamwise velocity data and calculated entramment rates are presented for a fully pulsed subsonic jet and for a steady subsonic jet with a fully pulsed subsonic coaxial core, both the jets exhaust into stationary air The same functional relationships used to characterize the mean velocity fields of steady jets are found to apply to the case of the systematically perturbed jets The perturbed jets appear to establish developed flow regimes more rapidly than steady jets Thus the perturbed jets exhibit faster growth of the jet half width and a slower decay of the jet centerlme velocity, resulting in increased entramment of the surrounding air J M B A78-37423 f/ Minimisation of relaxation drag E Becker (Darmstadt, Techmsche Hochschule, Darmstadt, West Germany) and W Ellermeier Institution of Engineers, Australian Hydraulics and Fluid Mechanics Conference, 6th, Adelaide, Australia, Dec 5-9, 1977, Paper 5 p 6 refs An analytical expression is derived in order to minimize relaxation drag It is noted that thermodynamic relaxation processes caused by a body moving through a fluid induce the production of entropy and the subsequent drag force on the body The correlation between entropy production and drag is derived for a slender two-dimensional profile moving with a constant velocity The drag force is represented by a functional of the velocity potential for cases of near-equilibrium and near-frozen flow The result for the nonequilihrium flow may be used to determine a profile which has the minimum relaxation drag for a given area and lift coefficient S C S A78-37477 Evaluation of airborne radar Doppler pro- cessors G A Andrews (U S Navy, Naval Research Laboratory, Washington, DC) In EASCON-77, Electronics and Aerospace Systems Convention, Arlington, Va, September 26-28, 1977, Record New York, Institute of Electrical and Electronics Engineers, Inc , 1977, p 4-5Ato 4-5H. 10 refs Detection of moving targets from moving platforms is investi gated in terms of the effects of platform motion and antenna pattern Using motion-compensation techniques, the performance of an MTI canceler is evaluated in terms of cascaded combinations of this canceler with additional Doppler processing The cascaded processors investigated are fast Fourier transform (FFT) filters and optimized Doppler filters Comparisons are made to determine the best configurations for particular conditions (Author) A78-37485 The effect of correlated missed detections, correlated false alarms and interclutter visibility on the performance of an automated radar tracking system R. M O'Donnell (MIT, Lexington, Mass) In EASCON-77, Electronics and Aerospace Systems Convention, Arlington, Va, September 26-28, 1977, Record New York, Institute of Electrical and Electronics Engineers, Inc, 1977, p 10-2A to 10-21 6 refs USAF-sponsored research In the specification of radar detection and false alarm perfor- mance required to permit good automatic tracker performance, little regard has been given in the past to the need for radar signal processing and thresholding which will ensure that both the false alarms and missed detections fed to the tracker are uncorrelated The physical phenomena and radar design features which can cause either correlated false alarms or missed detections are rain and ground clutter, angel clutter, blind speeds, missed detections, blind phase problems and poor low velocity Doppler filter response The effect of interclutter visibility has been found to be significant in enhancing the detection of aircraft flying tangentially through ground clutter Extensive experimental results are presented illustrating these phe- nomena and their effects on tracking performance (Author) A78-37486 Dealing with false targets in the Air Traffic Control Radar Beacon System J E Freedman (ARINC Research Corp , Annapolis, Md ) In EASCON-77, Electronics and Aerospace Systems Convention, Arlington, Va, September 26-28, 1977, Record New York, Institute of Electrical and Electronics Engineers, Inc , 1977, p 10-3Ato10-3J 15 refs The generation of false beacon targets in the Air Traffic Control Radar Beacon System (ATCRBS) has long been a problem and a limiting factor to its performance This paper begins by examining the origins and characteristics of false targets and surveys present preventive and elimmative remedies in terms of their principles of operation and their practical limitations It is shown that, while improvements have been made and more can be expected, no one remedy will solve all false target problems The discussion then turns to consideration of software filters as a potentially valuable new tool for eliminating whatever false targets still remain due to the technical, economic, and political limitations of the preventive remedies The paper describes as an example one candidate filter - a simple algorithm based on detection of duplicate code reports - and examines its potential effectiveness Conclusions are then drawn regarding the potential role for software filters and their relation to the other false target remedies (Author) A78-37490 CRT update. J E Wurtz (Litton Industries, Electron Tube Div , San Carlos, Calif ) In EASCON-77, Electronics and Aerospace Systems Convention, Arlington, Va, September 26-28, 1977, Record New York, Institute of Electrical and Electronics Engineers, Inc , 1977, p 12-2A to 12-2F 16 refs 374 A78-37538 Innovation in phosphor mixes and advanced tube design have contributed to the continuing wide application of CRTs for TV monitors, oscilloscopes, air traffic control and cockpit displays, as well as for nondirect projection and scanning The advanced gun design adopted for the stringent shock and vibration conditions of airborne displays is discussed, and advanced green-line emitters for CRT airborne displays are mentioned Use of CRTs to record the output of radars, infrared scanners, scanning electron microscopes and medical scanners is also considered, filter optic coupling makes the CRT especially suitable for film recording A CRT-based device for superimposing information onto the scene perceived by aircraft pilots from the cockpit is described J M B A78-37501 Modern millimeter wave instrumentation radar development and research methodology. J A Scheer, J L Eaves, and N C Currie (Georgia Institute of Technology, Atlanta, Ga ) In EASCON 77, Electronics and Aerospace Systems Convention, Arling- ton, Va , September 26-28, 1977, Record New York, Institute of Electrical and Electronics Engineers, Inc , 1977, p 16-6Ato 16-6H 11 refs A millimeter-wave radar is described, and its various modes of operation are related to the research associated with signal processing techniques The new system is based on a K-sub-a band radar characterized as state-of-the-art, solid-state, self-contained, portable, coherent, frequency-agile, dual-polarized, and polarization-agile Pre- liminary hard target and clutter data and analyses are presented and related to the determination of appropriate processing algorithms for target discrimination ML A78-37525 Results of the NASA/MARAD L-band satellite navigation experiment B P Gibbs (EG&G/Washmgton Analytical Services Center, Inc, Riverdale.'Md ) In EASCON 77, Electronics and Aerospace Systems Convention, Arlington, Va , September 26-28, 1977, Supplement New York, Institute of Electrical and Electronics Engineers, Inc, 1977, p 25-30 9 refs During the period from October 1974 to May 1975, the National Aeronautics and Space Administration (NASA) and the Maritime Administration (MARAD) conducted two, independent mobile-vehicle position experiments using the Application Tech- nology Satellites (ATS) 5 and 6 NASA used an FAA aircraft as the mobile platform while MARAD used two commercial ships This paper summarizes the results of these experiments The data was analyzed to determine the operational accuracy, the dominant error sources and the potential accuracy of the system Overall, both experiments demonstrated accuracies of 2 to 30 nautical miles using the 'real time' data The dominant error source was found to be satellite ephemens error Using refined ephemendes (either from trilateration or a two-week prediction from normal ATS-6 tracking), both systems demonstrated accuracies of 2 to 4 nautical miles Random measurement errors generally resulted in less than one nautical mile position error (Author) A78-37530 fj Prediction of the ground effect - Side-line noise from aircraft J E Piercy, T F W Embleton, and R J. Donato (National Research Council, Ottawa, Canada) Acoustical Society of America, Meeting, 93rd, State College. Pa, June 6-10, 1977, Paper 8 p 5 refs Distance and angle functions are used to calculate the attenua tion due to grass alongside airport runways for JT8-D powered aircraft Attention is given to the aircraft's angle of elevation It is noted that a large (5-20 dB) attenuation is reported for very small angles (less than 3 deg), due to Lloyd's mirror cancellation, while much smaller (less than 3 dB) attenuation is observed for larger angles, due to ground absorption The attenuation in the latter case depends much more on distance than on angle Measurements of the SAE are contrasted with those of the CSIR (Committee of Scientific and Industrial Research) of the Republic of South Africa D M W A78-37532 ff Azimuthal decomposition of the power spec- tral density of |et noise K Yamamoto and R E A Arndt (Pennsylvania State University, University Park, Pa ) Acoustical Society of America, Meeting, 93rd, State College, Pa, June 6-10, 1977, Paper. 20 p The reported results have been obtained in a research program which was conducted to increase the fundamental understanding of the jet noise generation mechanism which is essential to the development of further advanced techniques of noise reduction The experiments included measurements of the coherence function of the circumferentially cross correlated signals of |et noise The coherence functions plotted versus frequency for various azimuthal separation angles are shown in a graph With an increase of the azimuthal separation angle, the coherency decreases In the high frequency range the coherency falls off drastically There is a strong azimuthal coherency over a rather broad range of frequency The coherence data were sampled at 13 arbitrarily selected frequencies and expanded in terms of a Fourier-series with respect to the azimuthal angle The results of the Fourier decomposition for two different jets are presented Michalke's spectral theory was used for the prediction of the single-azimuthal-frequency component of jet noise G R A78-37536 H An economic and technical perspective of the turboprop engine in Ag-aviation D C Emmerson (Pratt and Whitney Aircraft of Canada, Ltd , Longueuil, Quebec, Canada) (Canadian Aeronautics and Space Institute, Annual General Meeting, Quebec, Canada, May 18, 1977) Canadian Aeronautics and Space Journal, vol 24, Mar-Apr 1978, p 73-82 The development of turboprop technology for agricultural aircraft is reviewed Some of the more important technical considera- tions, cost factors, and productivity questions involved in applying turbines to agricultural aviation are examined Experience with current turboprop aircraft for agriculture with regard to reliability, time between overhauls, disk life, noise, purchase price, fuel costs, maintenance costs, insurance, payload capacity, and flight perfor- mance is discussed P T H A78-37537 ft Wind tunnel tests of a slotted flapped wing section D J Marsden (Alberta, University, Edmonton, Canada) (Canadian Symposium on Recreational and New Generation Light Aircraft, 2nd, Toronto, Canada, Sept 1976) Canadian Aeronautics and Space Journal, vol 24, Mar-Apr 1978, p 83-91 8 refs Research supported by the National Research Council of Canada and University of Alberta The slotted flapped wing section that was the subject of wind tunnel tests allows a high wing loading to be used for fast cruising flight and yet retains good climb performance with the flap extended for circling flight Flow visualization revealed clearly the transition from laminar to turbulent flow Laminar separation followed by reattachment to form a laminar separation bubble was a common mechanism for transition The position of transition for angle of attack from -4 to 14 deg was plotted for retracted and extended flap, and a sharp stall point was determined. Lift and drag characteristics were obtained, and the effect of leading edge roughness, such as may result from collecting insects on the leading edge, was determined The extension of the flight regime due to the flap is revealed The useable lift coefficient range of the section is nearly doubled by the slotted flap P T H A78-37538 # Rolls-Royce RB401 turbofan - A new business jet engine for the 1980's P E Peck (Rolls Royce, Ltd , Aero Div , Bristol, England) Canadian Aeronautics and Space Journal, vol 24, Mar-Apr 1978, p 92-97 375 A78-37539 The new RB401 engine delivers 5400 Ib of thrust and is aimed at business jet aircraft for the 1980s It has a bypass ratio of 4 2 1, and in retrofit applications it will increase aircraft range up to 50% with accompanying improvements in climb and cruise performance It employs conventional straight flow with axial compressors and turbines at an overall pressure ratio of 164 1 The selected design point provides an optimum solution in the tradeoff between fuel consumption and powerplant installed thrust and weight The thermodynamic cycle permits the design of a two-stage low-pressure turbine with the same constant mean radius as the high-pressure turbine and with direct drive to the fan The fan is a low-hub-tip ratio design giving a mean pressure ratio of 1 72 at cruise conditions and passing 182 Ib/sec at takeoff The high-pressure compressor incorporates a constant-diameter casing and blading produced in groups The gas generator features a supersonic nozzle and a single-stage turbine, resulting in 100 C reduction in gas temperature on the rotor blades PTH A78-37683 * # On the use of relative velocity exponents for jet engine exhaust noise J R Stone (NASA, Lewis Research Center, Cleveland, Ohio) Acoustical Society of America, Meeting, 95th, Providence, R I, May 16-19, 1978, Paper 16 p 14 refs The effect of flight on jet engine exhaust noise has often been presented in terms of a relative velocity exponent, n, as a function of radiation angle The value of n is given by the OASPL reduction due to relative velocity divided by 10 times the logarithm of the ratio of relative jet velocity to absolute jet velocity It is shown in this paper that the exponent n is positive for pure subsonic jet mixing noise and vanes, in a systematic manner, as a function of flight conditions and jet velocity On the basis of calculations from simple empirical models for jet mixing noise, shock noise and internally-generated noise, it is shown that when other soi'rces are present, the resulting lufii),. of n is increased over the range for jet mixing noise, and in some cases negative values of n are obtained (Author) A78-37539 # Expansion potential for the local service air carrier I Macleod (North Canada Air, Ltd, Prince Albert, Saskatchewan, Canada) (Canadian Aeronautics and Space Institute, Annual General Meeting, Toronto, Canada, May 1976) Canadian Aeronautics and Space Journal, vol 24, Mar-Apr 1978, p 98-104 The paper discusses the possibilities for the expansion of local air service in Northern and Western Canada The prospects for increased mining and tourism m Northern Saskatchewan may call for extension of the local air carrier service To keep up with competition from surfaces modes of transportation, existing local air services carriers on established routes will have to concentrate on frequency and scheduling of service, fast and reliable baggage handling, and scheduling interfacing In the process of route development, the local carrier should be allowed greater scope with limited competition on regional and mainline routes Route transfers should be encouraged Cooperation between local, regional and mainline earners will be needed A limited and conditional subsidy policy is suggested PTH A78-37712 The role of meteorology in helicopter icing problems P Ryder (Meteorological Office, Bracknell, Berks, England) Meteorological Magazine, vol 107, May 1978, p 140-147 9 refs An analysis of helicopter icing is presented The role of the meteorologist in preventing accidents resulting from icing is exam- ined with reference to policy decisions on the need for widescale use of helicopters It is concluded that the discipline of meteorology is more suited for planning and performing basic research concerning icing rather than in devising some simple means of predicting icing hazards The responsibility of a meteorologist as an adjunct to a policy decision is considered M L A78-37603 # Electronic aircraft collision avoidance system (Radiotekhmcheskie sistemy preduprezhdenna stolknovemi samoletov) S I Bychkov, G A Pakholkov, and V N lakovlev Moscow, Izdatel'stvo Sovetskoe Radio, 1977 272 p 60 refs In Russian The principles of operation and design of airborne electronic collision avoidance systems for aircraft are set forth The physical basis for the problem of avoiding collisions in midair is studied, and methods of designing and using components and systems for determining the mutual position of two objects and the parameters of their motion are studied Special attention is given to interacting systems based on interrogation and response, synchronous systems, and systems using the signal format and equipment of secondary air traffic control radar PTH A78-37732 * * Notes on the transonic indicial method D Nixon (NASA, Ames Research Center, Moffett Field, Calif ) AIAA Journal, vol 16, June 1978, p 613-616 The indicial method for calculating flutter derivatives for two-dimensional airfoils at transonic speeds is discussed, with particular attention given to the effect of a moving shock on the flow variables in the indicial method An expression for the pressure coefficient is developed on the basis of an explicit treatment of the shock motion, the pressure distribution may then be calculated foi general oscillations through use of the indicial method Explicit inclusion cf the shock motion is not necessary if only the lift and pitching moment coefficients are desired J M B A78-37613 ft Uniqueness 'in the large' of the solution to the direct problem of the Laval nozzle (O edmstvennosti 'v tselom' reshemia pnamoi zadachi sopla Lavalia) E G Shifrm Zhurnal Vychislite/'noi Matematiki i Matematicheskoi Fiziki, vol 18, Mar Apr 1978, p 509-512 5 refs In Russian Uniqueness 'in the large' is established for two classes of solutions to the direct problem of the Laval nozzle in the transonic approximation of the equations of motion on the assumption that no shocks are present First it is proved that for a nozzle of infinite length, if the flow acceleration is nonnegative the solution, if any, is unique Then it is proved that there do not exist two different solutions that are elliptic on the same domain and degenerating on a rectilinear segment of the boundary PTH A78-37733 # Nonlinear formulation for low-frequency transonic flow W C Chin (Boeing Commercial Airplane Co , Seattle Wash) AIAA Journal, vol 16, June 1978, p 616-618 Two-dimensional unsteady transonic flow past a thin airfoil performing small-amplitude harmonic oscillations is studied in an analysis which takes into account the 'back-interaction' arising from the nonlinear harmonic interplay The back-interaction phenomenon may have important effects on mean shock jumps and location in low-frequency problems, though the effect is probably less signifi- cant for the high-frequency case The nonlinear analysis demon- 376 A78-37885 A78-37743 * It Pressure pulsations on a flat plate normal to an underexpanded supersonic jet L H Back and V Sarohia (California Institute of Technology, Jet Propulsion Laboratory, Pasadena, Calif) AIAA Journal, vol 16, June 1978, p 634-636 Contract No NAS7-100 An experiment was devised to study the interaction between an underexpanded supersonic gas jet and a flat plate, with the plate located in a region in which the interaction produces shock wave and flow fluctuations Nitrogen gas at ambient stagnation temperature flowed through a convergent nozzle with exit diameter of 2 03 cm and impinged on a square metal plate normal to the |et Results revealed local peak pressure fluctuations on the plate at nozzle pressure ratios of about 2 and 4 5, with the latter case producing fluctuations of the same order as the mean pressure on the plate, the frequency of the oscillations was as large as 20 kHz For choked jet flow at ambient pressure higher than atmospheric, the pressure fluctuations would increase accordingly, and adjacent solid structures would therefore be subjected to proportionately higher normal stresses B J A78-37744 * H Round jet in a cross flow - Influence of injection angle on vortex properties D Krausche, R L Fearn (Florida, University, Gainesville, Fla ), and R P Weston (NASA, Langley Research Center, Low Speed Aerodynamics Branch, Hamp- ton, Va ) AIAA Journal, vol 16. June 1978, p 636,637 Grant No NGL-10-005-127 A model is developed to infer the properties of a pair of diffuse contrarotatmg vortices for perpendicular jet injection into the cross flow Attention is given to pressure distribution on the surface where the jet exhausts, especially in terms of V/STOL applications A V/STOL wind tunnel experiment is described, whereby a round jet of air (10 16 cm dia) was discharged through a horizontal flat plate into the cross flow of the wind tunnel test section at angles of 45, 60, 75, and 90 deg Results indicate that the effective vortex strength for both velocity ratios is highest near the jet orifice, and decreases as the vortices are swept downstream, at which point the effective vortex spacing increases In addition, the core radius of the vortex exhibits properties similar to those of the effective vortex spacing DM W A78-37772 Review of flashback reported in prevaponzing/ premixing combustors S L Plee and A M Mellor (Purdue University, West Lafayette, Ind ) Combustion and Flame, vol 32, June 1978, p 193203 42 refs Grant No AF-AFOSR-76 2936 Upstream flame propagation into the fuel preparation tanks of prevaporizmg/premixing combustors is discussed, this type of com- bustor is under consideration for aircraft, ramjet and automotive propulsion systems Classical flashback, autoigmtion, flame propaga- tion through reversed flow fields, and preigmtion of the fuel/air mixture in separated flow regions of the mixing tube are the phenomena examined A literature review suggests that the latter three mechanisms, rather than classical flashback, are present in noncatalytic combustion systems burning liquid jet fuels and propane This finding is important for development of engine burners capable of simultaneously reducing both oxides of nitrogen and carbon monoxide J M B A78-37775 tt Flow past nonconical wings with separation S V Ramakrishnan and N R Subramaman (National Aeronautical Laboratory, Bangalore, India) Journal of Aircraft, vol 15, June 1978, p 383, 384 5 refs The Brown and Michael (1954) method is extended to evaluate the effect of flow separation on wings of nonconical planform It is assumed that the spiral vortex sheets that separate from the leading edges can be replaced by two isolated vortices at the cores of the vortex sheets. The boundary conditions on the wing are such that (1) the normal velocity is zero, (2) the velocity is finite at the leading edge, and (3) the conditions in the field are that the disturbances vanish at infinity and the fluid pressure is continuous The vortex strength increases in the downstream direction, and the increase in vorticity is achieved in this model by a feeding sheet of vorticity in order to satisfy Kelvin's theorem Although this approximation method yields higher values for the lift coefficient than those obtained from experiments on delta wings, it gives a first approxima- tion for evaluating the vortex lift SD A78-37860 Investigating the efficiency of gas turbines in off-design operation G G Ol'khovskii and N I Ol'khovskaia (Vsesoiuznyi Nauchno-lssledovatel'skn Teplotekhmcheskn Institut, Moscow, USSR) (Teploenergetika, vol 24, no 9, 1977, p. 25-29.) Thermal Engineering, vol 24, no 9, 1978, p 16-19 8 refs Translation. Parameters useful in characterizing the efficiency of gas turbines have been studied on the basis of information accumulated while refining the starting and operating performance of multistage gas turbines Among the parameters discussed are the expansion ratio, the characteristic ratio (on which individual turbine-stage efficiency is strongly dependent), available heat drop, and internal efficiency In addition, the internal capacity of the turbines is obtained from the capacity balance (allowance being made for the capacity of the starting motor) A number of the parameters are monitored for multistage gas turbines from cold start to operational gas tempera- ture J M B A78-37873 # Aircraft radar systems (Radiolokatsionnye sis- temy letatel'nykh apparatov) P S Davydov, V P Zhavoronkov, G V Kashcheev, V V Krimtsyn, V S Uvarov, and I N--Khresm (Moskovskn Institut Inzhenerov Grazhdanskoi Aviatsn, Moscow, USSR) Moscow, Izdatel'stvo Transport, 1977 352 p 96 refs In Russian The book deals with various aspects of designing onboard radar systems, calculating and selecting the principal system parameters on the basis of statistical approaches, and assessing system performance The major topics covered include radar transmitters and antennas, onboard receiver systems, radar displays, automatic radar data processing, Doppler velocity and sideslip meters, radar altimeters, radar adjustment and checking techniques, and the automatic monitoring and documentation of radar parameters V P A78-37885 H Aircraft auxiliary power units (Vspomogatel'- nye silovye ustanovki samoletov) N I Pavlovskn Moscow, Izdatel'- stvo Transport, 1977 240 p In Russian The design, operation, and maintenance features of the TA-6A and TA-8 auxiliary power units, which serve to start up the turbojet engines of the 1162, Tu-134A and Tu-154 aircraft, are described Descriptions are provided of all the main subsystems of these engines, such as the fuel system, lubrication system, air supply, ignition system, generator, and measuring systems Attention is given to procedures for preparing the engines for operation, starting the engines, regulating the servicing done on the engines, engine installation and removal, and parts replacement P T H 377 A78-37887 A78-37887 ff Factorization methods in hydroaeromechamcs (Metod faktorizatsu v zadachakh gidroaeromekhaniki) G S Lipovoi Kiev, Izdatel'stvo Naukova Dumka, 1977 120p 78 refs In Russian The theory of complex variables is applied in a discussion of factorization methods used in the investigation of nonsteady-state problems in hydromechanics and aeromechanics Topics include the periodic movement of an infinite or finite wing span along a solid surface, the aperiodic movement of a profile along a solid surface, the aperiodic movement of finite wing spans along a screen, the periodic fluctuations of thin spatial cascades or of multisenes cascades in subsonic gas flows, and the movement of a thin finite wing span under the free surface of a liquid of infinite or finite depth M L A78-37979 Laser velocimeter for wind tunnel measure- ments A Boutier, G Fertm, and J Lefevre (ONERA, Chatillon- sous-Bagneux, Hauts-de-Seme, France) IEEE Transactions on Aero- space and Electronic Systems, vol AES-14, May 1978, p 441-455 32 refs (ONERA, TP No 1977-63) Laser velocimetry principles are briefly recalled, the optical and mechanical elements making up a velocimeter are described Their purpose is to create two laser beams of equal intensity which are focused and crossed in a probe volume where a fringe pattern is formed, the light scattered by submicron particles passing through the volume is collected by an optics rigidly connected to the emitting optics and focused on a photomultipher Among the various signal processing techniques, counters are now widely used, in connection with minicomputers The different means used to determine the velocity sign and to measure simultaneously two components of the velocity are described, the simultaneous measurement of the three velocity components is more a matter of technology and cost than a theoretical problem The modular operational velocimeter developed at ONERA is described, as examples of application, some typical results obtained in different aerodynamic flows are reported (Author) A78-38083 Halogenated solvent-induced corrosion in hydraulic systems L C Lipp (Hughes Aircraft Co , Culver City, Calif) American Society of Lubrication Engineers, Annual Meeting, 33rd, Dearborn, Mich, Apr 17-20, 1978, Preprint 78-AM-4A-2 8 p 10 refs Halogenated solvents and water contaminants in MIL-H-5606 hydraulic fluid were found to induce corrosion in systems used to drive radar antennas in the F-14 airplane. The predominant corrosion product found was identified as beta-iron oxide hydroxide The formation of this unusual iron oxide requires the presence of chlorine or fluorine, water and sufficiently high temperature to provide energy of activation Analyses of F-14 radar hydraulic systems revealed excessive amounts of tnchlorotrifluoroethane, 1,1,1 tnchloroethane and water Investigation of component manufactur- ing, assembly and cleaning procedures identified the sources of these contaminants Hot spots in the operating system provided reaction temperature Process controls limiting halogenated solvents in operat- ing systems and procedures to remove excessive solvent and water contaminants were successfully incorporated to control corrosion (Author) A78-38095 Circumferential seals for use as oil seals P C Stem (Stem Seal Co , Philadelphia, Pa) American Society of Lubrication Engineers, Annual Meeting, 33rd, Dearborn, Mich , Apr 17-20, 1978, Preprint 78-AM-3D-2 7 p Segmented circumferential rubbing seals have been widely used, especially as mam shaft seals for aircraft turbine engines, for well over two decades They have operated satisfactorily at high perfor- mance levels when sealing air and products of combustion In the presence of substantial amounts of oil, however, particularly with low pressure differentials, they are subject to high oil leakage, due primarily to 'surf-boarding' effects Incorporation of 'negative-lift' pockets in the bore of the segments effectively prevents the surf-boarding and makes the segmented ring into a convenient and efficient seal for many applications involving both oil rich gaseous environments and those involving solid oil The paper outlines theoretical considerations, shows their application to a number of seal structures and presents results of laboratory testing under a variety of conditions to define regions of applicability (Author) A78-37987 Evaluation of geometric performance of global positioning system C T Leo rides and K Yonezawa (California, University, Los Angeles, Calif ) IEEE Transactions on Aerospace and Electronic Systems, vol AES-14, May 1978, p 533-539 7 refs The global positioning system (GPS) is a satellite-based radio navigation system to provide extremely accurate three-dimensional position fixes and system time to users anywhere on the earth at any time regardless of weather conditions The most significant perfor- mance parameter of the GPS is the degree of navigation accuracy which is strongly coupled to the choice of orbit configuration The 3 x 8 orbit configuration has been considered as an operational GPS which consists of 24 satellites deployed in circular 63 deg inclined, subsynchronous 12-h orbits In this paper, the geometric perfor- mance of several orbit configurations, including a 3 x 8 orbit configuration, is analyzed numerically by altering orbit period and elevation mask, respectively It is shown that (1) there are a few orbit configurations which are comparable to or better than the baseline 3 x 8 orbit configuration, and (2) for higher elevation mask, the geometric performance can be improved effectively by increasing orbit period to some extent (Author) A78-38122 Stress intensity factors, for collmear cracks in a stiffened sheet D P Rooke (Royal Aircraft Establishment, Farnborough, Hants, England) and D J Cartwnght (Southampton, University, Southampton, England) International Journal of Frac- ture, vol 14, Apr 1978, p R61-R64 Research supported by the Ministry of Defence (Procurement Executive) An analytical technique is described for determining the stress intensity factors of large airframe structural elements with stiffeners riveted to them In such configurations, cracks are initiated at the rivets and grow at right angles to the main stress direction which is parallel to the stiffeners This results in an array of collmear cracks S C S A78-38246 ff Titanium and titanium alloys in aircraft main- tenance and repair I (Titan und Titanlegierungen bei der Instand- haltung und Instandsetzung von Flugzeugen I) L Ahnert (VEB Kombmat Spezialtechnik, Dresden, East Germany) Technisch- okonomische Information der zivilen Luftfahrt, vol 14, no 1, 1978, p 41-49 8 refs In German 378 A78-38641 Increasing aircraft speeds and engine efficiency (usually in- volving higher engine temperatures) has led to the widespread use of titanium in aircraft structures Titanium is noted to combine structural stability with lightweight (specific gravity = 45 g/cu cm) and temperature resistance to over 500 C It is noted that the Tu-144 aircraft incorporates approximately 2500 elements of titanium or its alloys Tables are presented listing various physical properties for Ti-alloys containing Al, Mn, Mo, V, Zr, Cr, and Sn, with attention to thermal stability and creep resistance D M W A78-38247 ff On the compensation of radio direction find- ers (Zur Kompensation von Funkkompassen) P Korrell (Gesell- schaft fur internationalen Flugverkehr mbH, Berlin, East Germany) Technisch-okonomische Information der z/vi/en Luftfahrt, vol 14, no 1, 1978, p 50-59 In German The relationship between local ground conditions and field disturbances in the radio spectrum near the ground is considered with reference to improving the direction finding ability of the standard radio navigation antenna of the ICAO Design and operating characteristics of the antenna are reviewed, and equations are given for the optimum positioning of the antenna coils Emphasis is placed on antenna wave propagation in various airport environments, eg, tower, runway, taxiway, highway access, etc Finally, a comparison between the modeling of positioning errors and their measurement is presented D M W A78-38248 Calculation of transonic flow through a tur- bine cascade by the time-step method (Berechnung der trans- sonischen Stromung durch ebene Turbmengitter nach dem Zeit- Schntt-Verfahren) F Lehthaus VDI-forschungsheft, no 586, 1978, p 5-24 33 refs In German Research supported by the Bundes- ministenum fur Wirtschaft On the basis of conservation laws in integral form for mass, momentum and energy, a procedure for calculating the steady mviscid two-dimensional transonic flow in a turbine cascade by the time-dependent finite element method is developed Results of computer calculations of pressure distributions on the profile contour and of the cascade characteristics are given for two cascades of strongly different geometry Calculations are compared with extensive experimental results obtained from using both a planar array and a rotating array Good agreement is achieved between theory and experiment wherever the assumption of attached flow is reproduced in the experiments The agreement between calculated and experimental homogeneous Mach number and homogeneous outflow angle was good, while the agreement in the total pressure losses was qualitatively close P T H A78-38475 H Aerodynamics of the annular wing (Aero- dmamika prstenastog krila) S Pivko Srpska Akademi/a Nauka i Umetnosti, Posebna Izdanja, no 499, Odel/enje Tekhnichkikh Nauka, no 12,1977 103 p 20 refs In Serbian The aerodynamic properties of three types of annular airfoils are studied theoretically (1) cylindrical annular airfoil with symmetrical sections at zero incidence, (2) annular airfoil with thin cambered sections at zero incidence, and (3) thin cylindrical ring with axis at angle of attack The cylindrical annular airfoil with symmetric sections is replaced according to the method of singularities by a system of source and sink rings over the mean surface, and the annular foil with thin cambered sections is replaced by a distribution of bound vortex rings on a cylinder The thin cylindrical wing is replaced by a bound vortex ring of variable strength and by a system of trailing vortices escaping from the trailing edge of the ring sections Results of graphical integration are compared with some wind tunnel data P T H A78-38521 * # High-flying Mini-Snifter RPV-Mars bound R D Reed (NASA, Flight Research Center, Edwards, Calif ) Astro- nautics and Aeronautics, vol 16, June 1978, p 26-39 The Mini Sniffer is a small unmanned survey aircraft developed by NASA to conduct turbulence and atmospheric pollution measure- ments from ground level to an altitude of 90,000 ft Carrying a 25-lb air sampling apparatus, the Mini-Sniffer typically cruises for one hour at 70,000 ft before being remotely piloted back to earth A hydrazme monopropellant engine powers the craft, while a PCM telemetering system and a radar transponder provide control func tions Development of a high-performance low-Reynolds-number airfoil could make the research craft suitable for a low-altitude terrain-following mission on Mars J M B A78-38522 # Grumman's radio-controlled experimental air force B Frisch Astronautics and Aeronautics, vol 16, June 1978, p 40,41 Construction of V/STOLand forward-swept-wing experimental aircraft" models is discussed The models may provide a good indication of the static stability and control characteristics of aircraft, though they are not generally useful in studying the stall regime and the V/STOL hovering case Spin testing through use of the foam/balsa/epoxy models is also possible J M B A78-38524 # A rising sun in aircraft A E Fuhs (U S Naval Postgraduate School, Monterey, Calif ) Astronautics and Aero- nautics, vol 16, June 1978, p 52-59 5 refs A survey of the Japanese aircraft industry indicates that in the short term the Japanese will probably sign license agreements to build the F-15 and P-3C, in the longer term (1990-2000), joint commercial aircraft development programs with other nations may place Japan in the fifth rank among world aerospace producers The YS-11, a 64-passenger aircraft first marketed by the Japanese in 1965, resulted in a loss of $100 million for the manufacturer, despite sales in 13 nations Limited domestic demand for small commercial transports and general aviation aircraft has also contributed to a low level of confidence in the national aerospace industry A quiet STOL craft and a fanjet for short-range domestic flights are principal current development projects of the Japanese national aerospace program J M B A78-38575 Subisokmetic sampling errors for aircraft tur- bine engine smoke probes J A Martone (USAF, Armament Development and Test Center, Tyndall AFB, Fla ) Air Pollution Control Association, Journal, vol 28, June 1978, p 607-609 11 refs Estimates are made of subisokmetic sampling errors for aircraft turbine engine smoke probes The aerosol sampling data reported by Martone et al (1977) are discussed The study co'lected samples of submicrometer particles suspended in unheated near-sonic and supersonic free jets Subisokmetic sampling errors were found for free jet velocities of Mach 0 6, 0 8, 1 26, and 1 27 An expression was derived for the ratio of the sampled aerosol concentration to true freestream aerosol concentration These data are used to assess the validity of applying Zenker's (1975) results to the prediction of subisokmetic sampling errors in compressible flows When applied to turbine engine exhausts, it is found that a smoke probe may produce a 15-30% subisokmetic sampling error at a take off engine power setting S C S A78-38641 Experimental investigation of gasdynamic pro- cesses at sudden start-up of a supersonic nozzle L G Gvozdeva and lu V Zhilin (PMTF - Zhurnal Pnkladnoi Mekhaniki i Tekhnicheskoi Fiziki, July-Aug 1977, p 66-74) Journal of Applied Mechanics and Technical Physics, vol 18, no 4, Jan 20, 1978, p 484-491 15 refs Translation 379 A78-38696 A78-38696 // Remarks on the noise emitted by the jet ot a gas turbine engine (Remarques sur le bruit emis par le jet d'un turboreacteur) R Legendre La Recherche Aerospatiale, Mar -Apr 1978, p 53-58 7 refs In French Without regard for entropy noise, three distinct noise sources are analyzed turbulence, nonhomogeneity of temperature or entropy, and combustion An equation is obtained in which the state variables are eliminated as far as possible The form of the equation satisfied by the acoustic agitation potential is obtained so that the three sources mentioned above can be identified P T H A78-38698 Study of magnetic noise in the Ka-26 heli- copter (Izucheme magnitnykh pomekh vertoleta Ka-26) A E Vatsuro and V S Tsirel' Geofizicheskaia Apparatura, no 62,1977, p 68-78 5 refs In Russian A method of measuring the magnetic noise produced by the Ka-26 helicopter is described, and some measurement results are given and discussed On the basis of ground and m-fhght studies, the optimal location for attaching the sensitive element of the proton aeromagnetometer was selected, and the magnitude and stability of the magnetic noise were determined Significant decrease in the course deviation was obtained through use of a rigid component compensator P T H 385 A78-39189 A78-39189 ff Prospects for using new flight vehicles in aerophysical studies (Perspektivy ispol'zovanna novykh letatel'nykh apparatov na aerogeofizicheskikh rabotakh) G D Knvolapov and V la Fridland Geofizicheskaia Apparatura, no 62, 1977, p 78-83 In Russian The flight characteristics and technical specifications of poten- tial aircraft for use in aerophysical studies are examined and compared with those of the currently used An-2 airplane and Mi-4 helicopter Two airplanes considered are the An-28, a two-turboprop aircraft with convertible undercarriage (floats or skis), and the L-410, also powered by two turboprop engines, and designed for servicing local airlines These planes are discussed in terms of length of flight with payload of 1000 kg, range of photographing velocities and altitudes, static ceiling, and climb rate The An 28 is already available m a version for geological photographic surveying Two helicopters briefly examined are the Ka-25 with gas turbine engines, especially suited for research over water, and the Mi-2 and Mi-8 helicopters P T H A78-39393 # British Airways Tn-Star - Present and future T Ford Aircraft Engineering, vol 50, May 1978, p 23, 24, 26, 27 Both TnStar 1 and the longer range TnStar-500 aircraft are considered together in terms of check-out, maintenance, and overhaul requirements Attention is given to a breakdown of the aircraft into area zones for periodic evaluation It is noted that since the TriStars in service with British Airways are often maintained at airfields outside Britain, eg , Paris, Bahrein, integration and unifor- mity of maintenance procedures are essential Finally, the TnStar RB 211 engine is examined in terms of life cycle, down time, and reliability, i e , number of in-flight shut downs and unscheduled engine removals D M W A78-39395 # Lighter-than-air concepts and recent develop- ments E F Strother (Florida Institute of Technology, Melbourne, Fla ) AIAA Student Journal, vol 16, Summer 1978, p 10-16 Lighter than air (LTA) vehicles are considered in terms of two broad categories fully buoyant and partially buoyant Included in the first category are rigid, pressure nonngid, and pressure rigid hulls Among partially buoyant LTAs are hybrid vehicles, eg, Aerocrane and Helistat, which use rotors as well as gas for lift, and lifting body hull designs Attention is given both to the historical development of the airship, beginning with Graf Zeppelin, and to the energy and ecological advantages of LTAs m current applications A two phase NASA design program leading to the production of an 100 ton payload LTA is outlined, stressing flight stability, safety, maneuver- ability, and reliability as a means of passenger and freight transport in otherwise inaccessible regions, especially in the third world D M W A78-39396 # Airships - The next generation and beyond F Morse (Boston University, Boston, Mass ) AIAA Student Journal, vol 16, Summer 1978, p 20-25 Developments currently in the design stage for LTA (lighter than air) vehicles are reviewed with reference to a 12 million cu ft rigid airship The ship would be inflated with helium, have a skin of alumimzed Kevlar fabric, a gross lift of 800,000 Ibs (equal to that of a Boeing 747), and be used for both short and long range passenger and freight applications A set of 18 Tedlar lined helium cells would be equipped with automatic pressure valves for lift control and maneuvering Propellers would be located m the slipstream for optimized L/D ratio Attention is given to LH2 and nuclear fuel as propulsion material Also discussed are the possibilities of substi- tuting Be for Al in the rigid structure, thus greatly increasing payload, and of an ion drive using the boundary layer surrounding the hull inflight DMW A78-39540 # Deformation curve of rotary airfoil blades M Nenadovich Academie Serbe des Sciences et des Arts, Bulletin, Classe des Sciences Techniques, vol 58, no 12, 1977, p 57-61 An integral differential equation is presented tur the deflection curve of a rotary airfoil blade for any external load The equation can be solved analytically by an operator method For conventional blade designs, the equation is readily reducible to an easily soluble simple differential equation, the bending moment produced by aerodynamical loads of the rotary airfoil blades is approximated by second-order polynomials, and the differential equation is solved by computer techniques M L A78-39579 # Prediction of the aerodynamic characteristics of an aircraft on the basis of the comparison of results for a calibration model m various large transonic wind tunnels (Prevision des caractenstiques aerodynamiques d'un avion d'apres la comparai- son des resultats sur une maquette etalon dans diverses grandes soufflenes transsoniques) P Poisson-Qumton and X Vaucheret (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) (NATO, AGARD, Reunion sur les Methodes de Prevision des Performances des Avions, Pans, France, Oct 11-13, 1977) ONERA, TP no 1978-22, 1978 18 p 19 refs In French The main transonic wind tunnels m the U S , Canada, Great Britain, the Netherlands and France were used to study the aerodynamic characteristics of a calibration model representing a transport aircraft The accuracy of the wind-tunnel measurements in predicting aerodynamic characteristics over a range of Mach and Reynolds numbers was the focus of the tests Drag level, lift/drag ratio, longitudinal stability, pitch-up onset, spanwise pressure distri- butions, shock wave locations, and boundary layer transition and separation locations were among the aerodynamic properties investi- gated A Reynolds number above about 2 million appeared to ensure accurate results for the predictions J M B A78-39580 ti Combustion in gas turbine engines - A review of ONERA recent works M Barrere (ONERA, Chatillon sous- Bagneux, Hauts-de-Seme, France) (Combustion Institute, General Conference, West Lafayette, Ind, Apr 3-5, 1978) ONERA, TP no 197825, 1978 28 p 12 refs Results obtained at ONERA in the field of combustion in turbomachmes (main combustor and reheat combustor) are sum- marized in a three part study The first part concerns the recirculation zone, with experiments without combustion in order to investigate the basic aerodynamic phenomena, and with combustion in a stirred reactor in order to acquire data on chemical kinetics Theoretical models of this zone are also mentioned The second part is devoted to the turbulent propagation of the flame, the structure of which (pressure, velocity, composition) is given for various upstream conditions of equivalence ratio and velocity The results obtained are compared to a theoretical model taking into account the chemical production in a turbulent medium The third part concerns the heat transfer at the wall in a region of active combustion The experimental results obtained are compared to a two dimensional model which accounts reasonably well for the flow field, but yields a somewhat different flux distribution at the wall (Author) A78-39582 ,*' Cobalt-base alloys produced by powder metal- lurgy for compressor and turbine disks (Alliages a base de cobalt elabores par metallurgy des poudres pour disques de compresseurs et turbines) M Marty and A Walder (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) (Symposium European de Metallurgy des Poudres, 5th, Stockholm, Sweden, June 4-8, 1978 ) ONERA, TP no 1978-7, 1978 7 p In French Cobalt-base alloys containing high concentrations of chromium carbides have been produced by powder metallurgy for application to compressor and turbine disks Micrographic structural studies of the CoCrC alloy, as well as a survey of the role of aging temperature on the hardness of the alloy, are reported Low-cycle fatigue resistance investigations of the alloy are also discussed The powder metallurgy production technique results in cobalt-base alloys with a high degree of ductility, though problems remain in obtaining optimal carbide dispersions J M B 386 A78-39772 A78-39596 Fatigue crack propagation of titanium alloys under dwell-time conditions P J Bania (Avco Corp , Avco Lycom- ing Stratford Div, Stratford, Conn ) and D Eylon (Cincinnati, University, Cincinnati, Ohio) Metallurgical Transactions A -Physical Metallurgy and Materials Science, vol 9A, June 1978, p 847-855 13 refs USAF-supported research An experimental study was carried out to assess the fatigue crack growth (FCG) behavior of titanium alloys with a variety of compositions, microstructures, textures, and interstitial contents with a view toward gaming insight into the most important parameters which may contribute to the dwell-time effect at peak load under fatigue cycling with a 5-mm dwelling time A near-alpha alloy (Ti-11) and an alpha + beta alloy (TV6AI-4V) are examined Three specimen forms of Ti-6AI-4V are considered a cross=rolled 50 mm thick plate, a highly textured 7 mm thick standard-grade plate, and a highly textured 7 mm thick low-interstitial plate No adverse effect on the FCG rate is detected for fatigue cycling with a 5-mm dwell at peak load Similar fracture surface patterns, e g , ductile vs cleavage-like features, are observed for the dwell and nondwell test specimens Reduced FCG rate in Ti-6AI-4V is attributed solely to an increase in crack-path tortuosity, probably due to a crack tip blunting mechanism operating during the dwell period of the load cycle S D wing the work performed by the pressure or the energy spent on rolling up is neglected Lift and induced drag coefficients and the maximum lift coefficient are computed for cases with and without leading edge separation P T H A78-39632 Flight-testing of a continuous laser remote sensing system (Flugerprobung eines kontmuierlichen Laser- Femmess-Systems) W Wiesemann (Battelle Institut, Frankfurt am Mam, West Germany) In Laser 77 opto electronics. Proceedings of the Conference, Munich, West Germany, June 20 24, 1977 Guildford, Surrey, England, IPC Science and Technol- ogy Press, Ltd , 1977, p 756 762 In German Flight testing of a hdar system developed for airborne remote sensing of trace gases is described The flight test involved a C02 laser, the signal-to-noise ratio of the system and the effects of various reflective surfaces (streets, forests, bodies of water) on the quality of the laser signal were assessed Quantitative measurement of the specific absorption properties of atmospheric pollutants through use of the airborne lidar is also discussed J M B A78-39674 A relative motion analysis of horizontal colli- sion avoidance J W Andrews (MIT, Lexington, Mass) SAFE Journal, vol 8, Summer 1978, p 20-23 U S Department of Transportation Contract No FA77 WAI 432, Contract No F19628-78 C-0002 In the design of automated collision avoidance systems, it is difficult to devise resolution strategies which are valiH for the wide range of aircraft speeds and collision geometries which may be encountered in normal flight This is especially true with regard to collision avoidance in the horizontal plane A technique for the analysis of horizontal relative motion between aircraft is discussed and the results are applied to the collision avoidance problem The aircraft pair are described in terms of a dynamic system for which the actual motion is decomposed into pure nonturning (rectilinear) motion and pure turning motion By expressing the projected miss distance as a fraction of range, a set of miss distance contours may be constructed which allow determination of the effect of heading changes upon the ultimate closest approach Inspection of these contours allows identification of geometries in which specific resolution strategies are appropriate The heading change required to achieve a given miss distance is readily determined (Author) A78-39772 ft On lift of delta wings with leading-edge vor- tices at low speeds M Hayashida, M Sato, and K Matsuoka (Osaka Prefecture, University, Sakai, Japan) Osaka Prefecture, University, Bulletin, Series A - Engineering and Natural Sciences, vol 26, no 2, 1977, p 37-51 19 refs A vortex model of the delta wing is considered Analysis is performed in a Trefftz plane at an infinite distance behind the wing In calculating the velocity potential due to the vortices leaving the 387 Page Intentionally Left Blank N78-24050 STAR ENTRIES N78-24O42# Defense Systems Management School Fort Belvoir Va THREE DEGREE INTERMEDIATE LEVEL MAINTENANCE OF NAVY AERONAUTICAL MATERIALS Robert Edward Bates Jr 9 Nov 1977 79 p refs (AD-A052389) Avail NTIS HC A05/MF A01 CSCL 01/5 This report discusses the development implementation and impact of the concept of three degree maintenance relative to the traditional maintenance policy of three levels of maintenance for Navy aeronautical materials An additional management tool specifically designed to supplement efforts directed towards improving the maintenance support posture of aeronautical materials at the intermediate level of maintenance results from the development of three degree maintenance concept A formal methodology is provided to supplement management capability on an individual equipment/component basis to (1) classify maintenance functions within levels and by activity (2) assign maintenance responsibility to a specific level and activity (3) assign maintenance tasks consistent with complexity, depth, scope and range of work to be performed and (4) ensure optimum use of limited resources Author (GRA) N78-24O43*# Rockwell International Corp Los Angeles Calif AERODYNAMIC PRELIMINARY ANALYSIS SYSTEM PART 2 USER'S MANUAL AND PROGRAM DESCRIP- TION P Divan. K Dunn and J Kojima Apr 1978 192 p (Contract NAS1-14686) (NASA-CR-145300) Avail NTIS HC A09/MF A01 CSCL 01A A comprehensive aerodynamic analysis program based on linearized .potential theory is described The solution treats thickness and attitude problems at subsonic and supersonic speeds Three dimensional configurations with or without jet flaps having multiple nonplanar surfaces of arbitrary planform and open or closed slender bodies or noncircular contour are analyzed Longitudinal and lateral-directional static and rotary derivative solutions are generated The analysis is implemented on a time sharing system in conjunction with an input tablet digitizer and an interactive graphics input/output display and editing terminal to maximize its responsiveness to the preliminary analysis problem Nominal case computation time of 45 CPU seconds on the CDC 175 for a 200 panel simulation indicates the program provides an efficient analysis for systematically performing various aerodynamic configuration tradeoff and evaluation studies Author N78-24O46*# National Aeronautics and Space Administration Langley Research Center Langley Station Va POWERED-UFT AERODYNAMICS AND ACOUSTICS Washington 1976 502 p refs Conf held at Hampton Va-. 24-26 May 1976 (NASA SP-4O6) Avail NTIS HC A22/MI- AOi CSCL 01A Powered lift technology is reviewed Topics covered include (1) high lift aerodynamics (2) high speed and cruise aerodynamics (3) acoustics |4) propulsion aerodynamics and acoustics (5) aerodynamic and acoustic loads and (6) full-scale anrt flight research N78-24O47*# Joint Inst for Acoustics and Flight Sciences Hampton. Va OVERVIEW OF POWERED-LIFT TECHNOLOGY John P Campbell In NASA Langley Res Center Powered-Lift Aerodyn and Acoustics 1976 p 1-27 refs Avail NTIS HC A22/MF A01 CSCL 01A The concept and application of powered lift and the effects of some fundamental design variables are discussed A brief chronology of significant developments in the field is also presented and the direction of research efforts in recent years is indicated All powered lift concepts are included but emphasis is on the two externally blown schemes which involve blowing either above or below the wing and which are utilized in the YC-14 and YC-15 aircraft Aerodynamics and vehicle design are emphasized The areas of acoustics propulsion and loads are briefly considered Author N78-24O48*# National Aeronautics and Space Administration Langley Research Center Langley Station. Va UPPER-SURFACE-BLOWING FLOW-TURNING PERFORM- ANCE William C Sleeman, Jr and Arthur E Phelps III (Army Air Mobility R and D Lab Hampton. Va I In its Powered- Lift Aerodyn and Acoustics 1976 p 29-43 refs Avail NTIS HC A22/MF A01 CSCL 01A Jet exhaust flow-turning characteristics were determined for systematic variations in upper-surface blowing exhaust nozzles and trailmg-edge flap configuration variables from experimental wind-off (static) flow studies For conditions with parallel flow exhausting from the nozzle jet height (as indicated by nozzle exit height) and flap radius were found to be the most important parameters relating to flow turning Nonparallel flow from the nozzle, as obtained from an internal roof angle and/or side spread angle had a large favorable effect on flow turning Comparisons made between static turning results and wind tunnel aerodynam- ic studies of identical configurations indicated that static flow-turning results can be indicative of wind-on powered lift performance for both good and poor nozzle-flap combinations but for marginal designs can lead to overly optimistic assessment of powered lift potential Author N78-24O49*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va RESULTS OF STATIC TESTS OF A 1/4 SCALE MODEL OF THE BOEING YC-14 POWERED-LIFT SYSTEM James L Hassell Jr In its Powered-Lift Aerodyn and Acoustics 1976 p 45-62 refs Avail NTIS HC A22/MF A01 CSCL 01A One quarter scale static ground tests of the Boeing YC-14 powered lift system were conducted for correlation with full scale test results The 1/4 scale model utilized a JT-15D turbofan engine to represent the CF6-50D engine employed on the YC-14 advanced medium STOL transport prototype aircraft The tests included evaluation of static turning performance, static surface pressure and temperature distributions, fluctuating loads and accelerations of portions of the wing flaps and fuselage Results are presented for the landing flap configuration over an appropriate range of fan pressure ratio as affected by several variables including ground height and vortex generator modifications Static turning angles of the order of 60 deg were obtained The highest surface pressures and temperatures were concentrated over the upper surface of the flaps in the region immediately aft of the upper surface blown nozzle Author N78-24O50*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SUMMARY OF LOW-SPEED AERODYNAMIC CHARACTER- ISTICS OF UPPER-SURFACE-BLOWN JET-FLAP CONFIG- URATIONS Arthur E Phelps. Ill (Army Air Mobility R and D Lab Hampton Va ) Joseph L Johnson Jr and Richard J Margason In its Powered-Lift Aerodyn and Acoustics 1976 p 63-87 refs Avail NTIS HC A22/MF A01 CSCL 01A The results of recent wind tunnel investigations to provide fundamental information on the upper surface blown (USB) jet flap concept demonstrated that the USB concept provides good high-lift performance It is shown that the low speed performance is dependent upon the jet turning angle and turning efficiency and on the use of proper leading and trailing edge treatment to prevent premature flow separation The best means of achieving good turning performance in any particular USB application must be determined from overall operational considerations in which 389 N78-24051 high speed performance structures and noise as well as low speed performance are evaluated The large diving moments generated at high lift coefficients can be trimmed satisfactorily with a large, conventional horizontal tail, a high tail position is best from longitudinal stability considerations Large rolling and yawing moments are introduced with the loss of an engine but these moments can be trimmed satisfactorily through the use of asymmetrical boundary layer control and through the use of spoiler and rudder deflection as needed Author N78-24O61*# National Aeronautics and Space Administration Langley Research Center Langley Station Va APPUCATION OF POWERED LIFT CONCEPTS FOR IMPROVED CRUISE EFFICIENCY OF LONG-RANGE AIRCRAFT Paul L Coe Jr and Paul G Fourmer In its Powered-Lift Aerodyn and Acoustics 1976 p 89-101 refs Avail NTIS HC A22/MF A01 CSCL 01A Results of studies conducted to explore the use of powered lift concepts for improved low speed performance of long range subsonic and supersonic cruise vehicles are summarized It is indicated that powered lift can provide significant improvements in low speed performance as well as substantial increases in cruise efficiency and range for both subsonic and supersonic cruise configurations Author N78-24052* § National Aeronautics and Space Administration Langley Research Center. Langley Station. Va COMPARISON OF AERODYNAMIC THEORY AND EXPERI- MENT FOR JET-FLAP WINGS Thomas G Gainer Long P Yip and Raymond P Vogler In its Powered-Lift Aerodyn and Acoustics 1976 p 103-118 refs Avail NTIS HC A22/MF A01 CSCL 01A Aerodynamic theory predictions made for a )et flapped wing were compared with experimental data obtained in a fairly extensive series of tests in the Langley V/STOL tunnel The tests were made on a straight rectangular wing and investigated two types of jet flap concepts a pure let flap with high jet deflection and a wing with blowing at the knee of a plain trailing edge flap The tests investigated full and partial span blowing for wing aspect ratios of 8 0 and 5 5 and momentum coefficients from 0 to about 4 The total lift drag and pitching moment coefficients predicted by the theory were in excellent agreement with experimental values for the pure jet flap even with the high jet deflection The pressure coefficients on the wing and hence the circulation lift coefficients were underpredicted however, because of the linearizing assumptions of the ianar theory The lift drag and pitching moment coefficients as well as pressure coefficients were underpredicted for the wing with blowing over the flap because of the failure of the theory to account for the interaction effect of the high velocity jet passing over the flap Author N78-24O53*# Army Air Mobility Research and Development Lab Hampton, Va EXTERNALLY BLOWN FLAP IMPINGEMENT PARAME- TERS Danny R Hoad In NASA Langley Res Center Powered Lift Aerod"i and Acoustics 1976 p 119-134 refs Avail NTIS HC A22/MF A01 CSCL 01A The performance of two externally blown flap (EBF) wind tunnel models was compared with an engine exhaust flap impingement correlation parameter One model was a four engine EBF triple slotted flap transport Isolated engine wake surveys were conducted to define the wake properties of five separate engine configurations for which performance data were available The other model was a two engine EBF transport for which the engine wake properties were estimated The correlation parameter was a function of engine exhaust dynamic pressure at the flap location area of engine exhaust flap impingement total exhaust area at the flap location, and engine thrust The distribution of dynamic pressure for the first model was measured however the distribution for the second model was assumed to be uniform Author N78-24054*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SOME MEASUREMENTS OF AN EBF POWERED-LIFT WAKE William G Johnson Jr In its Powered-Lift Aerodyn and Acoustics 1976 p 135-143 refs Avail NTIS HC A22/MF A01 CSCL 01A Results from a wind tunnel investigation in which velocity vector measurements were obtained in the near wake of an externally blown flap powered lift configuration were analyzed These measurements were used to develop spanwise distributions for the momentum strength and location of the engine exhaust stream tube with the results used as input parameters to one jet flap analytical method It is shown that a comparison of the momentum coefficients obtained from forward speed wake surveys with the predicted values from static force data results in a good correlation which verifies the use of the flap thrust recovery factor as a means of predicting the momentum strength at the flap trailing edge Also when wake survey distributions of momentum strength and direction are used as input parameters to one analytical jet flap method the results show reasonable agreement between the experimental data and analytical results Author N78-24O55*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC CHARACTERISTICS IN GROUND PROXIM- ITY James L Thomas James L Hassell Jr and Luat T Nguyen In its Powered- Lift Aerodyn and Acoustics 1976 p 145-158 refs Avail NTIS HC A22/MF A01 CSCL 01A Results from recent investigations in the Langley V/STOL tunnel of an externally blown flap and an upper surface blown flap configuration in ground proximity are presented Comparisons of longitudinal aerodynamic characteristics indicate that in ground proximity, drag is reduced for both configurations, but changes in lift are configuration dependent Steady state analyses of the landing approach indicate an increase in flight path angle for both configurations in ground proximity because of the drag reduction Dynamic analyses with a fixed-base simulator indicate that the resultant flight path during landing approach is dependent on the initial flight path angle and the control technique used Author N78-24O56*# National Aeronautics and Space Administration Langley Research Center Langley Station Va DISTRIBUTED UPPER-SURFACE BLOWING CONCEPT Paul G Fourmer and Paul L Coe. Jr In its Powered-Lift Aerodyn and Acoustics 1976 p 159-164 refs '/ Avail NTIS HC A22/MF A01 CSCL 01A A low speed investigation was conducted in the Langley V/STOL tunnel to determine the powered lift aerodynamic performance of a distributed upper surface blown propulsive lift transport model The model used blowing slots across the span of the wing to produce a thin jet efflux near the leading edge and at the knee of the trailing edge flap (internally blown jet flap) Results indicate that these concepts have both good propulsive related lift and low drag due to lift characteristics because of uniform spanwise propulsive thrust The leading edge blowing concept provides low speed lift characteristics which are competitive with the flap-hinge-line blowing concept and does not require additional leading edge treatment for prevention of abrupt stall Author N78-24057*# Lockheed-Georgia Co Marietta CRUISE AERODYNAMICS OF USB NACELLE/WING GEOMETRIC VARIATIONS John A Braden. John P Hancock, and Kenneth P Burdges In Nasa Langley Res Center Powered-Lift A»rodyn and Acoustics 1976 p 165-181 390 N78 24065 (Contract NAS1-13871) Avail NTIS HC A22/MF A01 CSCL 01A Experimental results are presented on aerodynamic effects of geometric variations in upper surface blown nacelle configura- tions at high speed cruise conditions Test data include both force and pressure measurements on two and three dimensional models powered by upper surface blowing nacelles of varying geometries Experimental results are provided on variations in nozzle aspect ratio nozzle boattail angle and multiple nacelle installations The nacelles are ranked according to aerodynamic drag penalties as well as overall installed drag penalties Sample effects and correlations are shown for data obtained with the pressure model Author N78-24O58*# National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio EFFECTS OF NOZZLE DESIGN AND POWER ON CRUISE DRAG FOR UPPER-SURFACE-BLOWING AIRCRAFT Edward T Meleason In NASA Langley Res Center Powered-Lift Aerodyn and Acoustics 1976 p 183-196 refs , Avail NTIS HC A22/MF A01 CSCL01A A high speed wind tunnel investigation was conducted on a series of upper surface blowing nozzles with D-shaped exits installed on a representative short haul aircraft model Both two and four engine configurations were investigated Powered engine simulators were used to properly represent nacelle flows Large differences in cruise drag penalties associated with the various nozzle designs were seen Some geometric parameters influencing nozzle cruise drag are identified Author N78-24059*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THEORETICAL PREDICTIONS OF JET INTERACTION EFFECTS FOR USB AND OWB CONFIGURATIONS C Edward Lan (Kansas Umv) and James F Campbell In its Powered-Lift Aerodyn and Acoustics 1976 p 197-211 refs (Grant NsG-1139) determine if the lower wattage lamp and fixture combination would be satisfactory for category 1 and category 2 low-visibility operations where a Federal Aviation Administration Specification type L-862 runway edge light fixture would be required Pilot opinion during flight tests indicates that an installed group A version of the experimental runway edge light unit is visually adequate for category 1 weather operations and should be adequate for category 2 operations Group A lights how- ever did not meet the Office of Airport Programs Specifications for L-862 runway edge lights An improved group B version will meet both requirements, since it satisfactorily passed the L-862 photometric specifications Author N78-24154# National Aviation Facilities Experimental Center Atlantic City N J FEASIBILITY STUDY FOR SIMULATION OF AN AIRPORT TOWER CONTROL ENVIRONMENT Final Report. May 1976 - Mar 1977 Helen W Hamilton Feb 1978 84 p refs (FAA Pro) 216-102-100) (AD-A051174 FAA-NA-77-33 FAA-RD-77-190) Avail NTIS HC A05/MF A01 CSCL 01/2 I he feasibility and desirability of developing an airport tower control simulation training facility at the FAA Academy was investigated Training program needs were assessed and the state-of-the-art in simulation technology was surveyed Several large-scale airpoit tower and ship's bridge simulators are described and evaluated from an operational and engineering viewpoint also a number of flight simulators and image generation and projection systems die considered with regard to the applicability of the concepts to the FAA training requirements Computer geneiated image systems versus other imaging technologies are discussed with reference to realism requirements capability for efficient generation of instructional materials and for objective student evaluation The large number of visual-scene simulation facilities presently m use or under contract development for a wide variety of uses indicates that a tower control application is entirely feasible Author N78-24155# Department of Transportation Washington, D C ATC Systems Div PROJECT PLAN TOWER AUTOMATED GROUND SURVEIL- LANCE SYSTEM DEVELOPMENT PROGRAM Development Plan. FY 1978 M E Pene Jan 1978 18 p refs (AD-A051621 FAA-RD-78-4) Avail NTIS HC A02/MF A01 CSCL 17/9 The tower automated ground surveillance system (TAGS) is designed to provide automation support for air traffic controllers in the tower cab and increase surface traffic handling capacity minimise delays and provide all-weather control and guidance for the airport surface traffic control (ASTC) system The TAGS system having a clear uncluttered presentation of each target and its identity will eliminate voice channel saturation and permit ground tontiol capacity in bad visibility to equal that m good visibility TAGS will also become the baseline automation system 10 increase ASIC system capacity in the future air traffic control system Author N78-24156# Institute for Defense Analyses Arlington Va Science and Technology Div COST-EFFECTIVENESS OF FLIGHT SIMULATORS FOR MILITARY TRAINING VOLUME 1 USE AND EFFECTIVE- NESS OF FLIGHT SIMULATORS Final Report. Apr 1976 - Jul 1977 Jesse Orlansky and Joseph String Aug 19/7 16/ p refs (Contract DAHC15-73-C-0200) (AD-A052801 AD-E500013 IDA/HQ-77-19470 P-1275-Vol-1) Avail NTIS HC A08/MF A01 LS<_L 01/1 Flight simulators cost less to operate than do aircraft estimates range fiom 5 to 20 percent Many studies have shown that skills learned in flight simulators can be performed successfully m aircraft i e the use of flight simulators for training purposes saves flight time The critical issue is whether the amount of flight time saved by the use of simulators is worth their cost The cost-effectiveness of flight simulators foi training has been demonstrated only in a few recent studies which it-port that the procurement cost of simulators can be amortized in a few years Current R and D about flight simulators rentpis about the need for motion and wide angle visual display systems ! hylit simulators have achieved their greatest use by the military so far in undergraduate flight training Their greatest potential for future savings lies in transition and continuation training which account for the major costs of military flying Consistent methods of data collection and cost estimating not now available are needed to evaluate the cost-effectiveness of alternative flight training programs including the use of various types of simulators part-task trainers new instructional strategic., and the like The report provides a preliminary cost model which identifies the data needed to develop cost estimates for use in cost- effectiveness analyses of flight training Author (GRA) N7824158# AiResearch Mfg Co . Phoenix Ariz ADVANCED TECHNOLOGY SERVICING EQUIPMENT FOR ARMY AIRCRAFT Final Report R R MejdnchDec 1977 192p (Contract DAAJ02-76-C-0042, DA Pro) 1F2-62209-AH-76) (AD-A052652, AiResearch-31-2491B USAAMRDL-TR-77-33) Avail NTIS HCA09/MFA01 CSCL01/5 The purpose of this effort was to define an advanced Ground Power Unit (GPU) to service AAH and UTTAS helicopters The GPU was to be lightweight air-transportable, highly mobile^ and use aircraft equipment wnerever possible The program included the following activities Aircraft requirements verification trade-off analyses to select specific components, design and component compatability verification and preparation of specification and layout drawings defining conceptual design Author (GRA) N78-24159# Civil and Environmental Engineering Development Office Tyndall AFB Fla Detachment 1 ADTC NONDESTRUCTIVE PAVEMENT EVALUATION Final Report. 1 Oct 1976 - 30 Sep 1977 B M Das Oct 1977 23 p refs (AD-A052707, CEEDO-TR-77-41) Avail NTIS HC A02/MF A01 CSCL 01/5 Research has been m progress for about 10 years to develop a compatible pavement evaluation procedure for airfields based on nondestructive tests A successful nondestructive pavement evaluation technique will reduce the time of closure of various airfield facilities needed to conduct destructive tests required for conventional pavement evaluation This study provides a comparison of the projected pavement life of several airfield features estimated by nondestructive and destructive pavement evaluation procedures For aircraft and gross loads on similar pavement sections the nondestructive evaluation procedure yields higher numbers of allowable operations as compared to that obtained by the destructive test evaluation technique at this point in the research effort Follow-on research is planned which will cause the two evaluation procedures to yield more closely compatible numbers Author (GRA) 400 N78-24380 N78-24292*# National Aeronautics and Space Administration. Washington D C CARBON FIBER STUDY (1977] 43 p (NASA TM-79449) Avail NTIS HC A03/MF A01 CSCL11D A coordinated Federal Government action plan for dealing with the potential problems arising from the increasing use of graphite fiber reinforced composite materials in both military and civilian applications is presented The required dissemination of declassified information and an outline of government actions to minimize the social and economic consequences of proliferated composite materials applications were included Author N78-24320]jf Air Force Inst of Tech Wright-Patterson AFB Ohio AN ATOMIC FLUORESCENCE SYSTEM USING A CONTIN- UUM SOURCE FOR THE RAPID DETERMINATION OF WEAR METALS IN JET ENGINE LUBRICATING OILS M S Thaws - Fla Univ Robert L Vaughn Mar 1978 65 p refs (AD-A052721 AFIT-CI-78-53) Avail NTIS HC A04/MF A01 CSCL 07/4 A brief review is presented of atomic absorption and atomic fluorescence methods of trace wear-metal analysis of jet engine lubricating oil The theory of atomic fluorescence in flames is presented for the case of a continuum excitation source A system for atomic fluorescence measurements is described that employs an electrically-heated graphite rod and a N20/C2H2 flame atomizer with a 300-W Eimac xenon arc as the continuum excitation source With this system, small samples (1 microhter) having complex matrices can be analyzed rapidly, conveniently and with no pretreatment Analytical calibration curves are given for Cr, Al and Mo and these metals are determined in synthetic and real jet engine lubricating oils The determinations of these elements are evaluated with respect to the accuracy and repeatability criteria of the Interservice Oil Analysis Program Author (GRA) N78-24344# Aluminum Co of America Alcoa Center Pa EXPLORATORY DEVELOPMENT FOR DESIGN DATA ON STRUCTURAL ALUMINUM ALLOYS IN REPRESENTATIVE AIRCRAFT ENVIRONMENTS Final Report. 1 May 1974 - 30 Apr 1977 D J Brownhill R E Davies G E Nordmark and B M Ponchel Jul 1977 197 p refs (Contract F33615-74-C-5089 AF Proj 7381) (AD-A052809. AFML-TR-77-102) Avail NTIS HC A09/MF A01 CSCL 11/6 The mechanical properties fracture toughness, fatigue, fatigue-crack growth rates in three environments and corrosion characteristics of 10 lots each of 2048-T851 7050-T7351 and 7475-T7351 plate and 2219-T852 hand forgmgs have been evaluated Data for establishing MIL-HDBK-5 values, including modulus of elasticity and stress-strain are presented GRA N78-24348# Army Materials and Mechanics Research Center Watertown Mass TRIP STEELS PROMISE HIGH RELIABILITY HARDWARE Final Report Kenneth H Abbott Feb 1978 18 p (AO-A052765 AMMRC-MS-78-2) Avail NTIS HC A02/MF A01 CSCL 11/6 Based on a review of the properties of typical TRIP steels a discussion is presented of possible Army applications for this new material Problems related to component fabrication and specification controls are presented and a brief outline of a recommended R and 0 program is included Author (GRA) N78-24369*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio IMPACT OF FUTURE FUEL PROPERTIES ON AIRCRAFT ENGINES AND FUEL SYSTEMS R A Rudey and J S Grobman 1978 33 p refs To be presented at Lecture Ser 96 Pans Munich and London 12-20 Oct 1978 sponsored by AGARD (NASA-TM-78866, E-9597) Avail NTIS HC A03/MF A01 CSCL 21D This paper describes and discusses the propulsion-system problems that will most likely be encountered if the specifications of hydrocarbon-based jet fuels must undergo significant changes in the future and correspondingly the advances in technology that will be required to minimize the adverse impact of these problems Several investigations conducted are summarized Illustrations are used to describe the relative effects of selected fuel properties on the behavior of propulsion-system components and fuel systems The selected fuel properties are those that are most likely to be relaxed in future fuel specifications Illustrations are also used to describe technological advances that may be needed in the future Finally the technological areas needing the most attention are described and programs that are under way to address these needs are briefly discussed Author N78-24370*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio CHARACTERISTICS AND COMBUSTION OF FUTURE HYDROCARBON FUELS R A Rudey and J S Grobman 1978 26 p Proposed for presentation at Lecture Series 96 Pans Munich London 12-20 Oct 1978 sponsored by AGARD (NASA-TM-78865 E-9596) Avail NTIS HC A03/MF A01 CSCL 21D As the world supply of petroleum crude oil is being depleted the supply of high-quality crude oil is also dwindling This dwindling supply is beginning to manifest itself m the form of crude oils containing higher percentages of aromatic compounds sulphur, nitrogen and trace constituents The result of this trend is described and the change in important crude oil characteristics as related to aircraft fuels, is discussed As available petroleum is further depleted the use of synthetic crude oils (those derived from coal and oil shale) may be required The principal properties of these syncrudes and the fuels that can be derived from them are described In addition to the changes in the supply of crude oil increasing competition for middle-distillate fuels may require that specifications be broadened in future fuels The impact that the resultant potential changes in fuel properties may have on combustion and thermal stability characteristics is illustrated and discussed in terms of ignition soot formation carbon deposition flame radiation, and emissions Author N78-24380*# Jet Propulsion Lab. Calif Inst of Tech , Pasadena PERFORMANCE EVALUATION OF A CATALYTIC PARTIAL OXIDATION HYDROGEN GENERATOR USING TURBINE ENGINE FUELS Final Report. 1 Oct 1976 - 30 Apr 1977 Richard M Clayton Oct 1977 43 p refs (Contract MIPR-FY14557-601611) (AO-A047355 AFAPL-TR-77-62) Avail NTIS HC A03/MF A01 CSCL 21/4 Operation of a catalytic partial oxidation reactor under simulated turbine engine idle power air state conditions, using a conventional aviation turbine fuel (JP-5) and an unconventional fuel (blend of JP-5/xylene), is shown to produce a fuel gas' stream of near theoretical equilibrium composition at very fuel-rich A/F ratios in the range of 5 0-5 6 The combustibles in the fuel gas comprise about 6% H2 and 93% CO by mass and therefore the fuel gas exhibits superior lean-burning qualities relative to the fuel gas exhibits superior lean-burning qualities 401 N78-24385 relative to the fuel feed stock The concept of using the very fuel-rich partial oxidation process as a first stage of a two-stage combustion system for onboard processing of broadened specification fuels to improve their combustion characteristics is discussed For the nonoptimal reactor design used excessive catalyst bed temperatures and a propensity for solid carbon deposition in the bed were observed These phenomena are not fully understood and need further elucidation Thermal reactor schemes (without catalysts) may be more advantageously applied to aviation turbine engines but these schemes also require additional investigation to delineate design requirements Author (GRA) N78-24385# National Bureau of Standards Washington. D C PROBLEMS IN WORLD-WIDE STANDARDIZATION OF THE UNITS OF HEIGHT MEASUREMENT Interim Report Judith F Gilsmn Feb 1978 23 p refs (Contract DOT-FA76WAI-594) (AD-A051150 NBSIR-77-1386 FAA-EM-78-2) Avail NTIS HC A02/MF A01 CSCL 17/7 The U S commitment to a voluntary conversion to metric units raises changeover problems in the fields of air traffic control and airspace management Current practice in altitude measure- ment and the rules for height maintenance now in effect worldwide are discussed Four desirable features are given for an altitude measurement system, encompassing both the units of height measurement and the designation of cruising levels Three alternative bases for the design of such a system are described and related to the desirable characteristics Problems associated with each of the approaches were examined and the many factors to be considered and the many interrelationships involved were studied Author mo, make several degrees of change in relative bearing before the change is noticeable on the PPI display Also, a small change in heading of 'own ship' is not immediately apparent on a PPI display Radar Systems Company has developed a Perspective Radar Display System which provides a perspective presentation on a cathode ray tube of the volume of space being scanned by an electromechanical scanning (nonrotattng) radar antenna This type of display has higher lateral position and lateral motion sensitivity than a PPI display It has the additional capability of varying the apparent altitude of perspective This report covers a technical and operational evaluation of the Perspective Radar Display System to determine its effectiveness as an aid to piloting for precision maneuvers in low-visibility conditions, for collision avoidance intercept solution, and shadowing, and for aiding SEAL team cast and recovery operations Author (GRA) N78-24515* National Aeronautics and Space Administration Langley Research Center Langley Station Va NON-DESTRUCTIVE METHOD FOR APPLYING AND REMOVING INSTRUMENTATION ON HELICOPTER ROTOR BLADES Patent Walt C Long and Milton L Williams inventors (to NASA) Issued 4 Apr 1978 8 p Filed 19 Apr 1977 Supersedes N77-22452 (15 - 13 p 1725) (NASA-Case-LAR-11201-1 US-Patent-4 082 001 US-Patent-Appl-SN-788705 US-Patent-Class-73-756 US-Patent-Class-73-456 US-Patent-Class-416-61 US-Patent-Class-416-144) Avail US Patent Office CSCL 14B A nondestructive method of applying and removing instrumen- tation on airfoils Official Gazette of the U S Patent Office N78-24391* National Aeronautics and Space Administration Pasadena Office Calif THIN CONFORMAL ANTENNA ARRAY FOR MICROWAVE POWER CONVERSIONS Patent Richard M Dickinson, inventor (to NASA) (JPL) Issued 14 Mar 1978 8 p Sponsored by NASA (NASA-Case-NPO-13886-1 US-Patent-4,079 268 US-Patent-Appl-SN-730045, US-Patent-Class-307-151. US-Patent-Class-361-395. US-Patent-Class-343-700MS) Avail US Patent Office CSCL 09C A structure of a circularly polarized thin conformal antenna array which may be mounted integrally with the skin of an aircraft employs rnicrostnp elliptical elements and interconnecting feed lines spaced from a circuit ground plane by a thin dielectric layer The feed lines are impedance matched to the elliptical antenna elements by selecting a proper feedpomt inside the periphery of the elliptical antenna elements Diodes connected between the feed lines and the ground plane rectify the microwave power and microstrip filters (low pass) connected in series with the feed lines provide dc current to a microstrip bus Low impedance matching strips are included between the elliptical elements and the rectifying and filtering elements Official Gazette of the U S Patent Office N78-24418# Naval Ocean Systems Center, San Diego. Calif PERSPECTIVE RADAR DISPLAY SYSTEM TV-LIKE PRESENTATION ON CRT PROVIDES HIGHER LATERAL POSITION AND LATERAL MOTION SENSITIVITY THAN A PPI Technical Report. Mar - Dec 1977 L G Hams 17 Jan 1978 21 p (AD-A052342. NOSC/TR-198) Avail NTIS HC A02/MF A01 CSCL 14/2 The data rate and display format of a conventional navigation radar/PPI display are adequate for most purposes but have limitations in certain close-range applications such as precision maneuvers in low-visibility conditions At close ranges the PPI format bunches the close targets near the center of the scope where the inherent azimuth resolution is poorest Close targets N78-24544* National Aeronautics and Space Administration Lyndon B Johnson Space Center Houston Tex STATOR ROTOR TOOLS Patent Donald D Diamond inventor (to NASA) (Serv-Air Inc Houston Tex) Issued 14 Mar 1978 6 p Filed 8 Nov 1976 Supersedes N77-13062 ( 1 5 - 0 4 p 0426) Sponsored by NASA (NASA-Case-MSC-16000-1. US-Patent-4.078,290. US-Patent-Appl-SN-739915 US-Patent-Class-29-252 US-Patent-Class-29-244. US-Patent-Class-29-23 5, US-Patent-Class-29-1568R) Avail US Patent Office CSCL 131 An apparatus and method for removing and reinserting base member segments in an arcuate slot in an engine part are described Each base member separately includes blades or stators holding the engine part in place while manipulating fingers or an arm onto an interfiling abutting relationship with most of the blades A torque force is applied to the base of the blades to move a base member relative to such an arcuate slot Official Gazette of the U S Patent Office N78-24556# Pratt and Whitney Aircraft Group, West Palm Beach Fla Government Products Div DEVELOPMENT OF MAINSHIFT HIGH SPEED CYLINDRI- CAL ROLLER BEARINGS FOR GAS TURBINE ENGINES Interim Report, 1 Oct 1975 - 1 Apr 1977 P F Brown L J Dobek F C Hsmg. and J R Miner Apr 1977 121 p refs (Contract N00140-76-C-0383) (AD-A052351 PWA-FR-8615) Avail NTIS HC A06/MF A01 CSCL 21/5 This combined analytical and experimental program is aimed at generating a manual that will permit the design of 3 0 MDN cylindrical roller bearings The roller bearing analysis will be correlated with the results from a series of bearing tests designed to determine, by statistical methods the effect of geometrical variables on bearing performance An existing quasi-static design optimization system has been upgraded and the basic analyses for use in developing a program to predict the dynamic behavior 402 N 78 24899 of roller bearing components are nearly complete A study identified a total of thirty separate bearing parameters that can influence roller skewing and skidding Two groups of 124 mm roller bearing designs were then prepared using statistical design techniques and incorporating parameters from the list of thirty Fabrication of full-scale bearing hardware was completed and testing was initiated on the first group of bearings Author (GRA) N78-24557# United Technologies Corp Stratford Conn Sikorsky Aircraft Div ADVANCED OVERRUNNING CLUTCH TECHNOLOGY Progress Report. 14 Mar - 14 Jun. 1976 Jules G Kish Dec 1977 316 p refs (Contract DAAJ02-74-C-0028. DA Proj 1F2-62209-AH-76) (AD-A052635 USAAMRDL-TR-77-16) Avail NTIS HC A14/MF A01 CSCL 01/3 This report documents a study to find overrunning clutch concepts suitable for use in helicopters Ten designs were selected for in-depth evaluation and from these three were selected for fabrication and testing the spring the sprag and the ramp-roller clutches These performed satisfactorily in the tests, and a design guide was compiled for them (USAAMRDL-TR-77-18) Author (GRA) N78-24803*# New York Univ N Y Courant Inst of Mathematical Sciences NUMERICAL CALCULATION OF TRANSONIC FLOW PAST A SWEPT WING BY A FINITE VOLUME METHOD Antony Jameson Dec 1977 25 p refs Presented at the 3d IFIPConf on Computing Methods in Appl Sci and Eng Versailles France 1973 (Grants NGR-33-016-167 NGR-33-016-201 Contracts N00014-77-C-0032 EY-76-C-02-3077) (NASA-CR-157012) Avail NTIS HC A02/MF A01 CSCL 098 The utility of numerical methods for predicting transonic flows over wings and bodies is well established The computer program FL022 based on a method presented earlier has actually been widely used to calculate the aerodynamic performance of wings of transport aircraft Provided that a correction is made for the displacement effect of the viscous boundary layer this code has been found to give predictions which are accurate enough to serve as a useful design guide The mam disadvantages of the scheme used in FL022 are the use of nonconservative difference formulas which result in a failure to satisfy conservation of mass across shock waves and the difficulty of finding suitable transformations of coordinates to permit the treatment of more complex geometric configurations The method described here is an attempt to overcome these shortcomings while retaining the successful features of the previous method The basic idea is to use a discrete approximation which directly represents a balance of the mass flow through small volume elements This leads to a relatively simple treatment of the potential flow equation in conservation form Author N78-24587# Societe Nationale Industnelle Aerospatiale Suresnes (France) Lab Central CAN FATIGUE CRACKS BE DETECTED IN AN EARLY STAGE BY ACOUSTIC EMISSION? APPLICATION TO HIGH RESISTANCE LIGHT ALLOYS USED IN AERONAUTICS C Bathias B Brintet and G Sertour Pans Assoc Aeron et Astronautique de France 1977 11 p refs In FRENCH ENGLISH summary Presented at the 8th World Conf on Nondestructive Testing Cannes France 6-11 Sep 1976 (AAAF-NT-77-35 IS8N-2-7170-0460-2) Avail NTIS HC A02/MF A01 CEDOCAR Pans FF 15 (France and EEC) FF 19 (others) A study carried out on different types of test pieces (shot blasted anodized notched) has shown that acoustic emission provides an accurate method for following fatigue damage up to crack initiation ESA N78-24755# Toronto Univ (Ontario) Inst for Aerospace Studies THE EFFECTS OF WIND SHEAR ON AIRCRAFT FLIGHT PATH AND METHODS FOR REMOTE SENSING AND REPORTING OF WIND SHEAR AT AIRPORTS Gaston Beaulieu Feb 1978 61 p refs (UTIAS-TN-216 CN-ISSN-0082-5263) Avail NTIS HC A04/MF A01 Strong wind shear can cause large flight path disturbances with modern jet transport aircraft The meteorological conditions causing wind shear and aircraft response to wind shear are described in general terms to provide a basic understanding of the wind shear phenomenon The dynamic response of an aircraft/pilot system to wind shear is explained based on one hundred approaches flown with a simple flight simulator in very strong wind shear The basic philosophy of flight control displays and integrated automatic flight control systems is discussed with regard to enhanced flight path and airspeed control under extreme wind shear conditions Wind shear remote sensors now under development are briefly described with their limitations advan- tages and disadvantages A complete description of an airborne display for wind shear information and a proposed acoustic Doppler installation in an airport environment conclude the present investigation Author N78-24897*# National Aeronautics and Space Administration Lewis Research Center Cleveland. Ohio ACOUSTIC EVALUATION OF A NOVEL SWEPT-ROTOR FAN James G Lucas Richard P Woodward and Michael J Mackmnon 1978 24 p refs Proposed for Presentation at 11th Fluid and Plasma Dyn Conf Seattle 10-12 Jul 1978 sponsored by AIAA (NASA-TM-78878 E-9612 AIAA-Paper-78-1121) Avail NTIS HC A02/MF A01 CSCL 20A Inlet noise and aerodynamic performance are presented for a high tip speed fan designed with rotor blade leading edge sweep that gives a subsonic component of inlet Mach number normal to the edge at all radii The intent of the design was to minimize the generation of rotor leading edge shock waves thereby minimizing multiple pure tone noise Sound power level and spectral comparisons are made with several high-speed fans of conventional design Results show multiple pure tone noise at levels below those of some of the other fans and this noise was initiated at a higher tip speed Aerodynamic performance of the fan did not meet design goals for this first build which applied conventional design procedures to the swept fan geometry Author N78-24899# DyTec Engineering. Inc Huntmgton Beacn Calif ATMOSPHERIC-ABSORPTION ADJUSTMENT PROCEDURE FOR AIRCRAFT FLYOVER NOISE MEASUREMENTS Final Report, May - Sap 1977 Alan H Marsh Dec 1977 89 p refs (W1-77-5660-1) (AD-A051700. DyTec-R-7705. FAA-RD-77-167) Avail NTIS HC A05/MF A01 CSCL 20A An analytical method was developed for adjusting measured aircraft noise levels for differences in atmospheric absorption between test and reference meteorological conditions a'ong the sound propagation path The method is based on the procedure in the proposed American National Standard ANS S1 26 for calculating pure-tone sound absorption as a function of the frequency of the sound and the temperature, humidity, and 403 N78-24900 pressure of the air Measured aircraft noise levels are assumed to be 1/3-octave-band sound pressure levels A computer program was written in FORTRAN IV to carry out the calculations The operation of the computer program, the required input data, and all symbols and terms used in the program are described A program listing of source statements is provided Recommenda- tions are given for applying the method to routine processing of aircraft noise measurements Author N78-24900*# Boeing Commercial Airplane Co, Seattle Wash LOW FREQUENCY CABIN NOISE REDUCTION BASED ON THE INTRINSIC STRUCTURAL TUNING CONCEPT THE THEORY AND THE EXPERIMENTAL RESULTS. PHASE 2 G SenGupta Mar 1978 104 p refs Sponsored in part by NASA (Contract F33657-72-C-0829) (NASA-CR-145262 D6-44283, 0748-10113-3) Avail NTIS HC A06/MF A01 CSCL 20A Low frequency cabin noise and somcally induced stresses in an aircraft fuselage may be reduced by intrinsic tuning of the various structural members such as the skin stringers, and frames and then applying damping treatments on these members The concept is also useful in iden'ifying the key structural resonance mechanisms controlling the fuselage response to broadband random excitation and in developing suitable damping treatments for reducing the structural response in various frequency ranges The mathematical proof of the concept and the results of some N7B-249O3*# Boeing Verto! Co . Philadelpma. Pa EVALUATION OF THE ANNOYANCE DUE TO HELICOPTER ROTOR NOISE Final Report Harry Sternfeld Jr and Linda Bukowski Doyle Washington NASA Jun 1978 74 p refs (Contract NAS1-14192) (NASA-CR-3001) Avail NTIS HC A03/MF A01 CSCL 20A A program was conducted in which 25 test subjects adjusted the levels of various helicopter rotor spectra until the combination of the harmonic noise and a broadband background noise was judged equally annoying as a higher level of the same broad- band noise spectrum The subjective measure of added harmonic noise was equated to the difference in the two levels of broadband noise The test participants also made subjective evaluations of the rotor noise signatures which they created The test stimuli consisted of three degrees of rotor impulsiveness, each presented at four blade passage rates Each of these 12 harmonic sounds was combined with three broadband spectra and was adjusted to match the annoyance of three different sound pressure levels of broadband noise Analysis of variance indicated that the important variables were level and impulsiveness Regression analyses indicated that inclusion of crest factor improved correlation between the subjective measures and various objective or physical measures Author N78-24999# Defense Systems Management School Fort Belvoir Va LIFE COST MANAGEMENT. METHODOLOGY. AND CASE STUDIES Andrew H Berard Oct 1977 64 p refs (AD-A052388) Avail NTIS HC A04/MF A01 CSCL 14/1 This study project examines the management policies that have initiated 0 and S cost control and the progress made on 0 and S costing methodology Costing guidelines prepared by LMI are summarized to provide the reader with an overview of the guidelines content and a preview of CAIG 0 and S costing methodology guidelines The RAND report on LCC analysis for aircraft turbine engines provides analysis methods that allows performance to be assessed with the present technology and determines cost and schedule risks Further commercial operational and maintenance practices are reviewed for military applicability Three case studies representative of LCC manage- ment techniques are discussed in detail showing the impact of logistics alternatives, reliability by design, and maintainability features that contribute towards reduced 0 and S costs and lower LCC The cases were selected from a LCC Seminar held on 29 Sept 1977 The Army s Black Hawk program, Navys F-18 program and the Air Forces ARC-164 program are the three case studies selected Important lessons learned on all three of the case studies should serve as models for other programs to follow that are concerned with LCC procurement The results of the case studies provide positive indications that LCC management does work and can provide affordable systems Author (GRA) N78-25048*# National Aeronautics and Space Administration Wallops Station, Wallops Island Va PRECISION POSITIONAL DATA OF GENERAL AVIATION AIR TRAFFIC IN TERMINAL AIR SPACE W E Melson Jr U C Parker A M Northam (Computer Sciences Corp Wallops Island Va ), and R P Singh (Computer Sciences Corp Wallops Island Va) May 1978 13 p (NASA-RP-1020) Avail NTIS HC A02/MF A01 CSCL 02A Three dimensional radar tracks of general aviation air traffic at three uncontrolled airports are considered Contained are data which describe the position-time histories, other derived parame- ters and reference data for the approximately 1200 tracks AM information was correlated such that the date time flight number and runway number match the pattern type aircraft type, wind visibility and cloud conditions Author N78-25050# Anne Research Corp Annapolis Md LOGISTICS AND OPERATIONAL EFFECTIVENESS OF THE P-3 AIRCRAFT Final Summary Report Mar 1978 37 p (Contract N00019-77-C-0309) (AD-A052239 Rept-1701-01-1-1728) Avail NTIS HC A03/MF A01 CSCL 01/3 This report summarizes a 12-month logistics, engineering, and program analysis effort performed by ARINC Research Corporation for the Naval Air Systems Command It describes the activities that provided the P-3 Project Manager with an independent and objective evaluation of factors affecting the P-3's operational availability and logistic support posture The effort consisted primarily of analysis tasks for the major P-3 modification programs integrated logistic support foreign military sales programs operational readiness programs and P-3 site transition programs Author (GRA) 404 N78 25059 N78-25051# Administrative Sciences Corp Alexandria Va NAVAL AIRCRAFT OPERATING AND SUPPORT COST MODEL - FISCAL YEAR 1976 REVISION Mar 1978 84 p (Contract N00014-77-C-0180) (AD-A053180 ASC-R-116) Avail NTIS HC A05/MF A01 CSCL 01/3 This report documents the revisions of a parametric model for estimating Naval aircraft operating and support costs developed by Administrative Sciences Corporation The model provides an estimate of average annual and life cycle 0 and S costs based on aircraft physical characteristics and basic program parameters using parametric cost-estimating relationships cost factors and throughputs and has been used to support numerous cost analyses prepared for CAIG review as well as other special studies such as the Naval Escort Force Mix Study and the Sea Based Air Study It is updated often in order to remain responsive to each particular analysis to reflect the changing nature of Naval aviation, and simply to remain timely This report reflects the status of the model after incorporation of all FY1976 data The bulk of the report is concerned with providing a clear concise and complete definition of each cost element and the way it is estimated by the model GRA N78-25054*# Vought Corp Hampton Va PANELING TECHNIQUES FOR USE WITH THE VORLAX COMPUTER PROGRAM Glenn L Martin Apr 1978 23 p ref (Contract NAS1-13500) (NASA-CR-145364) Avail NTIS HC A02/MF A01 CSCL 01A A method is presented for determining the geometric input data required by the VORLAX computer program in order to accurately model an aircraft configuration Techniques are described for modeling each of the major components of a configuration and for joining these individual components into a complete configuration The effects of trailing vortex filaments and methods of avoiding their intersection with downstream panels are also discussed The methods presented here are applicable to most conventional aircraft configurations Author N78-25055*# National Aeronautics and Space Administration Hugh L Dryden Flight Research Center Edwards Calif FLIGHT-MEASURED PRESSURE CHARACTERISTICS OF AFT-FACING STEPS IN HIGH REYNOLDS NUMBER FLOW AT MACH NUMBERS OF 220. 250. AND 280 AND COMPARISON WITH OTHER DATA Sheryll Goecke Powers May 1978 38 p refs (NASA-TM-72855 H-956) Avail NTIS HCA03/MFA01 CSCL 01A The YF-12 airplane was studied to deter"vne the pressure characteristics associated with an aft-facing step in high Reynolds number flow for nominal Mach numbers of 2 20, 2 50 and 2 80 Base pressure coefficients were obtained for three step heights The surface static pressures ahead of and behind the step were measured for the no-step condition and for each of the step heights A boundary layer rake was used to determine the local boundary layer conditions The Reynolds number based on the length of flow ahead of the step was approximately 10 to the 8th power and the ratios of momentum thickness to step height ranged from 0 2 to 10 Base pressure coefficients were compared with other available data at similar Mach numbers and at ratios of momentum thickness to step height near 1 0 In addition the data were compared with base pressure coefficients calculated by a semiempincal prediction method The base pressure ratios are shown to be a function of Reynolds number based on momentum thickness Profiles of the surface pressures ahead of and behind the step and the local boundary layer conditions are also presented Author N78-25056*# Polytechnic Inst of New York Aerodynamics Labs A FINITE-STEP METHOD FOR ESTIMATING THE SPAN- WISE LIFT DISTRIBUTION OF WINGS IN SYMMETRIC. YAWED. AND ROTARY FLIGHT AT LOW SPEEDS Final Report A R Krenkel Jun 1978 107 p refs (Grants NsG-1107 NsG-1300) (NASA-CR-157043 Poly-M/AE-78-17) Avail NTIS HC A06/MF A01 CSCL 01A The finite-step method was programmed for computing the span loading and stability derivatives of trapezoidal shaped wings in symmetric, yawed and rotary flight Calculations were made for a series of different wing planforms and the results compared with several available methods for estimating these derivatives in the linear angle of attack range The agreement shown was generally good except in a few cases An attempt was made to estimate the nonlinear variation of lift with angle of attack in the high alpha range by introducing the measured airfoil section data into the finite-step method The numerical procedure was found to be stable only at low angles of attack Author N78-25057*# Nielsen Engineering and Research Inc , Mountain View Calif HIGH ANGLE CANARD MISSILE TEST IN THE AMES 11-FOOT TRANSONIC WIND TUNNEL Richard G Schwmd Jun 1978 81 p refs (Contract NAS2-9211) (NASA-CR-2993 NEAR-TR-134) Avail NTIS HC A05/MF A01 CSCL 01A Four blunted ogive-cylinder missile models with a length-to- diameter ratio of 104 were tested at transonic speeds and large angles of attack The configurations are body body with tail .panels, body with canards and body with canards and tails Forces and moments from the entire model and each of the eight fins were measured over the pitch range of 20 deg to 50 deg and 0 deg to 45 deg roll Canard deflection angles between 0 deg and 15 deg were tested Exploratory vapor screen flow visualization testing was also performed Sample force and moment data are reported along with observations from the vapor screen tests Author N78-25058*# National Aeronautics and Space Administration Langley Research Center Langley Station Va A DISTRIBUTED VORTEX METHOD FOR COMPUTING THE VORTEX FIELD OF A MISSILE Raymond L Barger Jun 1978 19 p refs (NASA-TP-1183 L-11963) Avail NTIS HC A02/MF A01 CSCL 01A Vortex sheet development in the flow field of a missile was investigated by approximating the sheets in the cross-flow plane with short straight-line segments having distributed vorticity In contrast with the method that represents the sheets as lines of discrete vortices this distributed vortex method produced calculations with a high degree of computational stability Author N78-25059*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC CHARACTERISTICS AT MACH NUMBER 02 OF A WING-BODY CONCEPT FOR A HYPERSONIC RESEARCH AIRPLANE James L Dillon and Theodore R Creel Jr Jun 1978 48 p refs (NASA-TP-1189 L-12063) Avail NTIS HC A03/MF A01 CSCL 01A The static aerodynamic characteristics were studied on a model wing-body concept for a high-speed research airplane in a low-turbulence pressure tunnel The experiment consisted of configuration buildup from the basic body by adding a wing center vertical tail three-module scramjet and six-module scramjet engine The test Mach number was 0 2 at Reynolds numbers based on fuselage length ranging from 2 78 x 1 million to 23 x 2 million The test angle-of-attack range was approximately -5 to 30 deg at constant angles of sideslip of 0 deg and 4 deg The elevens were deflected from 5 deg to -15 deg Roll and yaw control were investigated Author 405 N78-25060 N78-25060*# National Aeronautics and Space Administration Langley Research Center Langley Station Va EFFECTS OF SPANWISE NOZZLE GEOMETRY AND LOCATION ON THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A VECTORED ENGINE OVER WING CONFIGURATION AT SUBSONIC SPEEDS Laurence D Leavitt and Long P Yip May 1978 78 p refs (NASA-TP-1215 L-12015) Avail NTIS HC A05/MF A01 CSCL 01A A V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aerodynamic characteristics of a model using a vectored-over-wmg powered lift concept The effects of spanwise nozzle throat area internal and external nozzle geometry and vertical and axial location were investigated These effects were studied at a Mach number of 0 186 over an angle-of-attack range from 14 deg to 40 deg A high pressure air system was used to provide jet-exhaust simulation Engine nozzle pressure ratio was varied from 1 0 (jet off) to approximately 3 75 Author N78-25067# National Technical Information Service Springfield Va PARACHUTES AND DECELERATORS. VOLUME 2 A BIBLIOGRAPHY WITH ABSTRACTS Progress Report. 1974 - Mar 1978 Guy E Habercom Jr Apr 1978 286 p Supersedes NTIS/PS-77/0317 NTIS/PS-76/0259 and NTIS/PS-75/224 (NTIS/PS-78/0320 NTIS/PS-77/0317 NTIS/PS-76/0259. NTIS/PS-75/224) Avail NTIS HC $28 00/MF $28 00 CSCL 01C Citations describe devices such as towplates ballutes servoactuators patented mechanisms semiautomatic openers and release systems This document discusses inflatable supersonic autorotor retrorocket and other structures Descent characteris- tics trajectories aerodynamic reefing shroud line and snatch forces and flare engineering are included Also presented are materials on flight testing models wind tunnel tests and computer aided design Applications are to target drone retrieval air drop and delivery coastal upwellmg sewage water tracking and mine ventilation GRA compared to a more conventional network using conventionally- designed long-haul freighters which travel between numerous major airports The analysis calculates all of the transportation costs including handling charges and pickup and delivery costs The results show that the economics of the hub/spoke system are severely compromised by the extensive use of feeder aircraft to deliver cargo into and from the large freighter terminals Not only are the higher costs for the smaller feeder airplanes disadvantageous but their use implies an additional exchange of cargo between modes compared to truck delivery The conventional system uses far fewer feeder airplanes and in many cases, none at all When feeder aircraft are eliminated from the hub/spoke system however that system is universally more economical than any conventional system employing smaller line-haul aircraft Author N78-25071*# National Aeronautics and Space Administration Ames Research Center, Moffett Field Calif NASA AVIATION SAFETY REPORTING SYSTEM Quarterly Report. 1 Apr - 30 Jun 1977 Apr 1978 62 p Prepared in cooperation with Battelle Columbus Labs Mountain View Calif (NASA-TM-78476 A-7373 QR-5) Avail NTIS HC A04/MF A01 CSCL 02A Reports describing various types of communication problems are presented along with summaries dealing with judgment and decision making Concerns relating to the ground proximity warning system are summarized and several examples of true terrain proximity warnings are provided An analytic study of reports relating to profile descents was performed Problems were found to be associated with charting and graphic presentation of the descents with lack of uniformity of the descent procedures among facilities using them and with the flight crew workload engendered by profile descents particularly when additional requirements are interposed by air traffic control during the execution of the profiles A selection of alert bulletins and responses to them were reviewed Author N78-25O68*# Virginia Univ Charlottesville Research Labs for the Engineering Sciences SURVEY OF AIR CARGO FORECASTING TECHNIQUES Final Report A R Kuhlthan and R S Vermuri May 1978 159 p refs (Contract NAS1-14908) (NASA-CR-145329 UVA/528156/CE78/1 10) Avail NTIS HC A08/MF A01 CSCL 05A Forecasting techniques currently in use in estimating or predicting the demand for air cargo in various markets are discussed with emphasis on the fundamentals of the different forecasting approaches References to specific studies are cited when appropriate The effectiveness of current methods is evaluated and several prospects for future activities or approaches are suggested Appendices contain summary type analyses of about 50 specific publications on forecasting and selected bibliographies on air cargo forecasting air passenger demand forecasting and general demand and modalsplit modeling Author N78-25069*# National Aeronautics and Space Administration Langley Research Center Langley Station Va PRELIMINARY ANALYSIS OF HUB AND SPOKE AIR FREIGHT DISTRIBUTION SYSTEM Allen H Whitehead Jr Apr 1978 36 p refs (NASA-TM-72656) Avail NTIS HC A03/MF A01 CSCL 01C A brief analysis is made of the hub and spoke air freight distribution system which would employ less than 15 hub centers world wide with very large advanced distributed-load freighters providing the line-haul delivery between hubs This system is N78-25077# Nationaal Lucht-en Ruimtevaartlaboratonum Amsterdam (Netherlands) A NON-STATIONARY MODEL FOR ATMOSPHERIC TURBULENCE PATCHES FOR THE PREDICTION OF AIRCRAFT DESIGN LOADS R Noback 19 Nov 1976 67 p refs (NLR-TR-76131-U ICAF-999) Avail NTIS HC A04/MF A01 A model for atmospheric turbulence is proposed It is assumed that atmospjienc turbulence appears in patches and that within the patches the turbulence can be described as a modulated Gaussian process Statistical properties of the model and of atmospheric turbulence are compared Using data from various sources a probability distribution function for patch lengths was derived and the relation between patch intensity and patch length was investigated Author N78-25078*# Kansas Univ Center for Research Inc Lawrence A STUDY OF COMMUTER AIRPLANE DESIGN OPTIMIZA- TION Status Report Bob Van Keppel Han Eysink Jim Hammer Kevin Hawley Paul Meredith and J Roskam 12 May 1978 457 p refs (Grant NsG-2145) (NASA-CR-157210 KU-FRL-313-5 SR-4) Avail NTIS HC A20/MF A01 CSCL 01C 406 N78-25084 The usability of the general aviation synthesis program (GASP) was enhanced by the development of separate computer subroutines which can be added as a package to this assembly of computerized design methods or used as a separate subrou- tine program to compute the dynamic longitudinal lateral- directional stability characteristics for a given airplane Currently available analysis methods were evaluated to ascertain those most appropriate for the design functions which the GASP computerized design program performs Methods for providing proper constraint and/or analysis functions for GASP were developed as well as the appropriate subroutines A R H N78-25079*# National Aeronautics and Space Administration Langley Research Center Langley Station Va PRELIMINARY STUDY OF A LARGE SPAN-DISTRIBUTED- LOAD FLYING-WING CARGO AIRPLANE CONCEPT Lloyd S Jernell May 1978 105 p refs (NASA-TP-1158 L-11943) Avail NTIS HC A06/MF A01 CSCL 01C An aircraft capable of transporting containerized cargo over intercontinental distances is analyzed The specifications for payload weight density and dimensions in essence configure the wing and establish unusually low values of wing loading and aspect ratio The structural weight comprises only about 18 percent of the design maximum gross weight Although the geometric aspect ratio is 453 the wmglet effect of the wing-tip-mounted vertical tails increase the effective aspect ratio to approximately 7 9 Sufficient control power to handle the large rolling moment of inertia dictates a relatively high minimum approach velocity of 315 km/hr (170 knots) The airplane has acceptable spiral Dutch roll and roll-damping modes A hardened stability augmentation system is required The most significant noise source is that of the airframe However for both take-off and approach the levels are below the FAR-36 limit of 108 db The design mission fuel efficiency is approximately 50 percent greater than that of the most advanced currently operational large freighter aircraft The direct operating cost is significantly lower than that of current freighters the advantage increasing as fuel price increases Author N78-25080*# Sikorsky Aircraft Stratford Conn OIL-AIR MIST LUBRICATION FOR HELICOPTER GEARING Final Report F McGrogan Dec 1976 52 p refs (Contract NAS3-18538} (NASA-CR-135081 SER-50959) Avail NTIS HC A04/MF A01 CSCL 01 C The applicability of a once-through oil mist system to the lubrication of helicopter spur gears was investigated and compared to conventional jet spray lubrication In the mist lubrication mode cooling air was supplied at 366K (200 F) to the out of mesh location of the gear sets The mist air was also supplied at 366K (200 F) to the radial position mist nozzle at a constant rate of 0 0632 mol/s (3 SCFM) per nozzle The lubricant contained in the mist air varied between 32 - 44 cc/hour In the recirculatmg jet spray mode the flow rate was varied between 1893 - 2650 cc/hour Visual inspection revealed the jet spray mode produced a superior surface finish on the gear teeth but a thermal energy survey showed a 15 - 20% increase in heat generated The gear tooth condition in the mrSt lubrication mode system could be improved if the cooling air and lubricant/air flow ratio were increased The test gearbox and the procedure used are described Author N78-25081j(l Kaman Avidyne Burlington Mass MODELING OF THE UH-1B TAIL BOOM FOR ANALYSIS BY THE NASTRAN COMPUTER PROGRAM Final Report. 19 Apr - 19 Oct 1976 Raffi P Yeghiayan Feb 1978 52 p (Contract OAAD05-76-C-0763) (AD-A052303 KA-TR-139 AR8RL-CR-OOJ58) Avail NTIS HC A04/MF A01 CSCL 01/3 A representative tail boom of the UH-1 B helicopter is modeled for dynamic structural analysis by the NASTRAN computer program The finite-element model employs beam and plate elements to construct the structural model which will subsequently be used to study the effects of simulated nuclear detonations subjecting the model to blast overpressure exposure with and without thermal effects The lower mode shapes and frequencies of the structural model are generated and presented as a validation check Author (GRA) N78-25082# Cleveland Pneumatic Tool Co Ohio GRAPHITE COMPOSITE LANDING GEAR COMPONENT UPPER DRAG BRACE HARDWARE FOR F 15 AIRCRAFT Final Report. Jul 1975 - Jan 1977 Myron J Bieber and Walter W Fricker Sep 1977 160 p (Contract F33615-75-C-3152 AF Proj 1369) (AD-A052764 ACFDL-TR-77-88) Avail NTIS HC A06/MF A01 CSCL 01/3 This report summarizes work performed to design fabricate and test a graphite epoxy composite material upper drag brace suitable for direct replacement of the current titanium upper drag brace for the F-15 aircraft landing gear assembly Design fabrication test procedures test results and failure analysis are presented in detail The composite material brace failed at less than design load The program established at the present time that drag braces and similar landing gear hardware can not be satisfactorily fabricated from graphite epoxy material for use as a direct replacement of existing metallic hardware in some applications The volume and shape of available space in these direct replacement applications does not normally allow the use of optimum graphite epoxy material design and fabrication techniques However as demonstrated by the successful development of a graphite epoxy side brace suitable for direct replacement of existing metallic hardware on the A-37B aircraft weight and cost saving applications to current aircraft are feasible Therefore each potential application must be individually evaluated Work is required to improve analytical fabrication and nondestructive inspection techniques for graphite epoxy materials It can be reasonably expected that current and future efforts by the Air Force industry and the educational community aimed at these improvements will increase the profitable application of graphite epoxy material to landing gear hardware Author (GRA) N78-25083# Air Force Inst of Tech Wright-Patterson AFB Ohio School of Engineering AN INVESTIGATION OF THE TRACKING PERFORMANCE OF THE FIRE FLY MANUAL DIRECTOR GUNSIGHT FOR AIR-TO-AIR GUNNERY MS Thesis David L Frostman Dec 1977 179 p refs (AD-A053348 AFIT/GGC/EE/77-5) Avail NTIS HC A09/MF A01 CSCL 19/5 The tracking performance of the Fire Fly manual director gunsight is evaluated during the terminal phase of air-to-air gunnery using the F-106 aircraft as the test bed A digital simulation of the closed loop tracking task is performed The multi-axis analytical pilot model is adapted for use in the F-106/Fire Fly gunsight simulation A set of nominal pilot model parameter values determined by root locus analysis is used in simulating the tracking performance of the Fire Fly gunsight against targets in constant altitude constant airspeed constant rate turns at bank angles of 30 60 and 70 degrees The tracking error responses are found to have characteristics similar to those observed in the tracking responses obtained from man-m-the-loop simulation studies The dependence of the tracking error responses on the pilot model parameter values is demonstrated by simulation runs in which several pilot model parameter values are varied GRA N78-25084# Naval Air Test Center Patuxent River Md ENVIRONMENTAL REQUIREMENTS FOR SIMULATED HELICOPTER/VTOL OPERATIONS FROM SMALL SHIPS AND CARRIERS 407 N78-25085 C W Woomer and R L Williams 12 Apr 1978 35 p refs (AD-A053078 NATC-TM-78-2-RW) Avail NTIS HC A03/MF A01 CSCL 05/9 Helicopter/VTOL operations from ships create demanding flying qualities and performance requirements The environment in which takeoff and landing evolutions must occur has a significant influence on these tasks Aircraft and simulator designers each in their own way must make appropriate provisions for environmental factors such as visual landing aids (VLA) ship motion turbulence relative wind and ground effect The paper discusses the specific requirements for the simulated environment to satisfactorily provide training for shipboard takeoff and landing Test techniques to validate trainer fidelity in flying qualities performance and environmental simulation are discussed The specific subject of calligraphic visual systems is extensively covered including a report on the current state-of-the- art as related to the at-sea environment Finally the utilization of a high-fidelity trainer is explored for research as well as for expanded fleet training GRA N78-25085# Grumman Aerospace Corp Bethpage N Y DEMONSTRATION OF ACOUSTIC EMISSION SYSTEM FOR DAMAGE MONITORING OF FULL SCALE METALLIC AIRCRAFT STRUCTURES DURING FATIGUE TESTING Final Report. Aug 1976 - Jul 1977 Alan D Mencken and Charles R Horak Sep 1977 82 p (Contract F33615-76-C-3073I (AD-A053108 AFFDL-TR-77-87) Avail NTIS HC A05/MF A01 CSCL 01/3 This report describes the acoustic emission monitoring work performed on a full scale metallic aircraft wing carry through structure of the swing wing bomber type The structure was monitored during fatigue testing with a Grumman developed system The program was designed to prove the feasibility of using a real time acoustic emission monitoring system to detect and locate crack propagation in a full scale complex airframe structure during fatigue cycling The report includes a description of the Acoustic Emission System operation and the concepts of noise discrimination used on fatigue tests The installation and monitoring techniques used on the fatigue test are described The test results the problems associated with monitoring the complex structure the conclusions and system monitoring recommendations are also discussed in this report Author (GRA) N78-25086# Army Test and Evaluation Command Aberdeen Proving Ground Md TEST OPERATIONS PROCEDURES PHYSICAL CHARAC- TERISTICS AVIATION MATERIAL Roy L Miller 29 Nov 1977 15 p Supersedes the aviation portions of TOP-1-3-5 (AD-A053196 TOP-7-3-500 TOP-1-3-51 Avail NTIS HC A02/MF A01 CSCL 15/5 This document identifies testing methods and techniques necessary to determine the degree to which Army aviation materiel s physical characteristics are determined Author (GRA) N78-25087/JI Rockwell International Corp Los Angeles Calif PRELIMINARY DESIGN OF LOW-COST TITANIUM STRUC- TURE Final Report. Apr 1976 - Sep 1977 J K Pulley Sep 1977 160 p refs (Contract F33615-76-C-3066) (AD-A053327 NA-77-389 AFFDL-TR-77-81) Avail NTIS HC A08/MF A01 CSCL 01/3 Results of a study program to evaluate the application of advanced titanium fabrication techniques to the Air Force B-1 bomber engine nacelle structure for improvements in cost and weight are presented There are five items for the study Two of them are primary structure one of which is a removable access panel The remaining three items are secondary structure Superplastic forming with concurrent diffusion bonding including expanded sandwich were investigated Weight savings range up to 49 percent Potential weight savings are 362 pounds per aircraft Cost savings range up to 69 percent resulting in a potential savings of up to $48 622 800 for 240 aircraft Author (GRA) N78-25088*/? National Aeronautics and Space Administration Hugh L Dryden Flight Research Center Edwards Calif AIR SPEED AND ATTITUDE PROBE Patent Application Merle A Economu inventor (to NASA) Filed 30 May 1978 13 p (NASA-Case-FRC-11009-1 US-Patent-Appl-SN-910708) Avail NTIS HC A02/MF A01~ CSCL 01 D A probe was designed which can be mounted on a data boom and extended in parallel with the longitudinal axis of symmetry of an aircraft to provide local air speed and aircraft attitude intelligence The probe employs both static pressure and total pressure transducers mounted in a tubular body supported for wind induced angular displacement about an axis normally related to the longitudinal axis of the aircraft NASA N78-25089* National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio GAS TURBINE ENGINE WITH RECIRCULATING BLEED Patent Arthur P Adamson inventor (to NASA) (GE Cincinnati Ohio) Issued 11 Apr 1978 5 p Filed 14 Jun 1976 Sponsored by NASA (NASA-Case-LEW-12452-1 US-Patent-4.083 181 US-Patent-Appl-SN-695513. US-Patent-Class-60-39 52 US-Patent-Class-60-226R) Avail US Patent Office CSCL 21E Carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine are reduced by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet As this hot inlet air is recycled the combustor inlet temperature rises rapidly at a constant engine thrust level In most combustors, this will reduce carbon monoxide and unburned hydrocarbon emissions significantly The preferred locations for hot air extraction are at the compressor discharge or from within the turbine whereas the preferred reentry location is at the compressor inlet Official Gazette of the U S Patent Office N78-2S090* National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio COUNTER PUMPING DEBRIS EXCLUDER AND SEPARA- TOR Patent Lawrence P Ludwig inventor (to NASA) Issued 18 Apr 1978 5 p Filed 31 Mar 1976 Supersedes N76-20487 (14 - 11 p 1394) (NASA-Case-LEW-11855-1 US-Patent-4 084 825 US-Patent-Appl-SN-672222 US-Patent-Class-277-25 US-Patent-Class-277-134) Avail US Patent Office CSCL 21E A dirt separator and excluder for removing entrained debris from gas turbine shaft seals is described A helical groove pattern is constructed on the rotating shaft with the pumping- pattern such that it tends to pump seal nressunzing gas toward the gas turbine seal A second helicaTgTbove pattern is provided on the stationary housing or counter rotating member coaxial with the shaft and this pattern is designed to provide pumping in the direction opposite from that of the groove pattern on the shaft Gas with entrained debris entering this grooved area will be subjected to high centrifugal forces due to the swirl motion induced by the groove pattern and the rotation of the shaft This debris is centrifuged outwardly into the outer groove pattern on the housing or counter rotating member Because the outer groove pattern has a pumping direction opposite from that of the seal dirt is pumped away from the seal and can be collected in a suitable debris trap remote from the seal location Official Gazette of the U S Patent Office N78-25091 Ecole Polytechmque Federate de Lausanne (Switzer- land) Inst de Thermique Appltquee DEPOSITION OF FINE PARTICLES IN THE OPENING OF FILM-COOLED GAS TURBINE BLADES Jean-Claude Mevillot Zurich Juns-Verlag 1975 197 p refs In FRENCH ENGLISH summary (EPFL-ITA-2 ISBN-3-260-04048-X) Avail Juns-Verlag Sw Fr "6 408 N78-25098 The film cooled blades of high temperature gas turbines have tiny cooling air-openings on the blade surface which could eventually get blocked by deposition of fine particles contained in the hot gas formed eg in the combustion chamber To study the risk of blockage two fundamental problems must be treated The trajectories of the particles near the blades and in the cooling-air holes for which the impinging mass-rate •$ calculated for statistical distributions of the particle size and the problem of adhesion in order to decide whether the particle adheres or is repelled after impact are both studied The governing parameters for both problems are defined together with the probable order of magnitude for application All results are presented in a dimensionless manner in order to facilitate the transposition to any practical case The theoretical results were verified on several experimental stands As a result only the cooling holes near the leading hedge of blades risk being blocked by particles If the cooling air flows correctly little is to be feared from dry solid particles (carbon) Weaker particles existing eg during the starting of the combustion can be more dangerous In any case particles less than 1 5 diameter will not reach the cooling hole walls Author (ESA) N78-25092*# Pennsylvania State Univ University Park Dept of Aerospace Engineering RESEARCH ON THE STATICALLY THRUSTING PROPELLER Final Report. Mar 1970 - Jun 1978 Joseph J Eisenhuth Jun 1978 41 p refs IGrant NGL-39-009-172) (NASA-CR-157214) Avail NTIS HC A03/MF A01 CSCL 01A Methods for calculating the induced flow at propeller blades were analyzed by treating the wake formation as an initial problem in time An unsteady vortex lattice technique was applied to the wake formation and the vortex core size was studied B B N78-25093# National Aerospace Lab Tokyo (Japan) A HIGH-PRESSURE. SECTOR-SHAPED MODEL COMBUS- TOR TEST FACILITY FOR DEVELOPMENT OF TURBOFAN ENGINES Kunio Suzuki Kenji Nishio Shoji Honuchi Mamoru Koshmurna Yujiro Kabe and Kyuzo Ishihara Nov 1977 32 p refs In JAPANESE ENGLISH summary (NAL-TR-517) Avail NTIS HC A03/MF A01 A high-pressure blow-down type turbine combustor test facility is reported that has a capacity of up to 30 atm of air from ambient temperature to 720 K The test section can supply an airflow rate of either 10 kg/s in weight or 0 6 cu m/s in volume at the maximum The combustor inlet temperature and pressure are independently regulated Test duration is limited to between 60 and 100 seconds depending on the experimental condition Control of the facility and experimental measurements are conducted by a minicomputer Author N78-25094# National Aerospace Lab Tokyo (Japan) ACOUSTICS AND PERFORMANCE OF HIGH-SPEED, UNEQUALLY SPACED FAN ROTORS Shoichi FUJII Hideo Nishiwaki and Katsumi Takeda Feb 1977 20 p refs In JAPANESE ENGLISH summary (NAL-TR-526) Avail NTIS HC A02/MF A01 The effects of uneven blade spacing on the acoustic and aerothermodynamic characteristics of high-speed high-pressure- ratio fan rotors were measured at two selected spacing configurations A test rig consisting of inlet guide vanes and transonic rotor blades was employed to explore the redistribution of harmonics sound energy into a series of multiple tones of lower sound pressure level The measured data indicated that a 10 percent modulated rotor exhibited a six to eight decibel decrease in sound pressure level as compared with the original first blade passage frequency harmonic Disadvantages in aerodynamic performance resulting from spacing modulation were not unfavorable for 10 percent modulated blades However with 5 percent modulated blades, serious deterioration in aerodynam- ic performance was observed particularly near the blade tip section which produced an unfavourable acoustic signature A calculation method assuming a pulse event for each blade sound pressure provided agreeable results with the measured data Author N78-25095jjf National Mechanical Engineering Research Inst Pretoria (South Africa) Aeronautics Research Unit PERFORMANCE TESTS AND DESIGN MODIFICATIONS OF A WANKEL TYPE ROTARY COMBUSTION AUTOMOBILE ENGINE IN ORDER TO DETERMINE ITS SUITABILITY FOR AIRCRAFT APPLICATION E R Leeman A J VanWyk and I S Myburgh Jun 1977 19 p refs (CSIR-ME-1521) Avail NTIS HC A02/MF A01 Performance tests and design modifications are reported for a standard production Mazda RX2 automobile engine of the Wankel type in order to make it suitable for aircraft applica- tions Author N78-25096# Maxwell Labs Inc Woburn Mass Utility Products Div INDUCTOR NETWORK DEVELOPMENT FOR AIRCRAFT HIGH POWER SUPPLIES Final Report. Jan 1974 - Feb 1977 J Tenko R L Bryan S Ghoshroy L M Lontai and O K Son|u Apr 1977 248 p (Contract F33615-74-C-20 AF Proj 3145) (AD-A052750 AFAPL-TR-77-15) Avail NTIS HC A11/MF A01 CSCL 10/2 This report presents the results of a study program undertaken to perform a comparative analysis of several approaches to the generation of high electrical power by storing tens to hundreds of kilo|Oules of energy in a compact superconducting inductive system with efficient extraction in short bursts at high repetition rates The critical factors for the comparison were the weight volume dissipation and reliability of the system and components for various operating regimes characterized by pulse power repetition rate and pulse shape Research and development work hitherto undertaken in the U S and abroad indicate the engineering feasibility of operating inductive storage systems storing ten to perhaps one hundred kiloioules of energy with extraction rates of tens of pulses per second at pulse durations of the order of a few hundred microseconds with state-of-the-art technology The major effort of this study was directed towards developing analytical tools to predict the performance of superconducting coils at repetition rates of 100 - 1000 pps with pulse discharge times of 20 - 40 microseconds and to evaluate the relative merits of different circuit configurations for storage and extraction of energy at high average power ( 3 - 1 0 MW) At frequencies of a few hundred pulses per second it appears that inductive storage has a distinct advantage over capacitive storage at power levels of the order 1 - 10 MW GRA N78-250970 McDonnell Aircraft Co St Louis Mo VARIABLE CYCLE ENGINE EVALUATIONS FOR SUPER- SONIC V/STOL FIGHTERS PHASE 2 AND 3 TECHNICAL REPORT Final Report. Jun 1975 - Mar 1978 J E Cupstid and D G Glennie Apr 1978 153 p refs (Contract N00140-75-C-0034} (AD-A053361) Avail NTIS HC A08/MF A01 CSCL 21/5 Variable cycle engines (VCE) have been evaluated using advanced V/STOL fighter designs The VCE payoffs were assessed in terms of total weapon system cost effectiveness and results indicate that they offer potential benefits in supersonic V/STOL fighters A systematic engine/airframe evaluation procedure was developed and used to assess interactions for advanced engine concepts in L - L/C aircraft designs The evaluation procedure provides a rapid and inexpensive technique for evaluating engine concepts considering a large matrix for engine and airframe design and sizing variables The procedure was used to establish a parametric data base using both fixed cycle turbofans and variable geometry turbine turbojets Specific engine/airframe designs were then selected for detailed comparisons Engine/airframe design evaluations were also conducted using a variable cycle turbofan engine capable of being used with both L - L/C and L/C aircraft These aircraft designs were compared to the fixed cycle turbofan and variable geometry turbine turbojet aircraft designs in terms of TOGW performance life cycle cost and operational flexibil- ity Author (GRA) N78-25098# McDonnell Aircraft Co St Louis Mo VARIABLE CYCLE ENGINE EVALUATIONS FOR SUPER 409 N78 25099 SONIC V/STOL FIGHTERS MANAGEMENT SUMMARY REPORT Final Summary Report. Jun 1975 - Mar 1978 J E Cupstid and D G Glennie Apr 1978 58 p refs (Contract N00140-75-C-0034) (AD-A053362) Avail NTIS HC A04/MF A01 CSCL 21/5 For abstract see N78-25097 N78-25099# National Technical Information Service. Springfield Va AIRCRAFT SONIC BOOM EFFECTS ON BUILDINGS A BIBLIOGRAPHY WITH ABSTRACTS Progress Report. 1964 - Feb 1978 Guy E Habercom Jr Mar 1978 77 p Supersedes NTIS/PS-77/ 0219 NTIS/PS-77/0176 2 Vol (NTIS/PS-78/0239 NTIS/PS-77/0219 NTIS/PS-76/0176) Copyright Avail NTIS HC $28 00/MF $28 00 CSCL 20A Research findings are cited on the effects of sonic booms on buildings structural components forms windows and walls Test-house investigations are included along with damage analysis and vibration response Documentation is made on residential buildings Other topics contained in the volume range from theory to failure analysis Sonic boom propagation and effects on biological forms including human responses are cited in separate bibliographies GRA N78-2510O# National Technical Information Service Springfield Va AIRCRAFT SONIC BOOM STUDIES ON A IRCRAFT FLIGHT, AIRCRAFT DESIGN. AND MEASUREMENT A BIBLIOGRAPHY WITH ABSTRACTS Progress Report. 1964 - Feb 1978 Guy E Habercom Jr Mar 1978 187 p Supersedes NTIS/PS-77/0218 NTIS/PS-76/0175 2 Vol (NTIS/PS-78/0238 NTIS/PS-77/0218 NTIS/PS-76/0175) Copyright Avail NTIS HC $28 00/MF $28 00 CSCL 20A The reports discuss aerodynamic design of aircraft and wings flight characteristics and maneuvers supersonic transport characteristics acoustic fields and noise measurement govern- ment policies and regulations meteorological parameters shock waves and supersonic and hypersonic wind tunnel tests along with other theoretical and general investigations Structural and biological effects are documented in separate published searchers GRA A number of ongoing long-term environmental effects programs for composite materials are evaluated The flight service experience was evaluated for 142 composite aircraft components after more than 5 years and 1 million successful component flight hours Ground-based outdoor exposures of composite material coupons after 3 years of exposure at 5 sites have reached equilibrium levels of moisture pickup which are predictable Solar ultraviolet-induced material loss is discussed for these same exposures No significant degradation was observed in residual strength for either stressed or unstressed specimens or for exposures to aviation fuels and fluids Author N78-25199# Nationaal Lucht-en Ruimtevaartlaboratci.jm Amsterdam (Netherlands) HEAT TREATMENT STUDIES OF ALUMINUM ALLOY TYPE 705O FORCINGS THE EFFECT OF HEAT TREATMENT ON A VARIETY OF ENGINEERING PROPERTIES Interim Report L Schra and H P vanLeeuwen 19 Jan 1976 131 p (NLR-TR-76008-U IR-2) Avail NTIS HC A07/MF A01 The effect of variety of heat treatments on various engineer- ing properties was studied with the aim to derive an optimum heat treatment The engineering properties comprised Vickers hardness short-time tensile strength fatigue crack propagation resistance fracture toughness and stress corrosion resistance The test results were compared with those obtained in earlier investigations on the older forging alloys of American and British origin 7079 and DTD 5024 and on the newly developed German forging alloy AZ7461 The performance of the alloy 7050 proved to be generally superior to that of AZ7461 and far superior to that of 7079 and DTD 5024 However it was found that quenching in boiling water leads to relatively inferior fracture toughness and stress corrosion properties while in the SCC resistant condition the alloy proved to be very susceptible to general corrosive attack if exposed to an aggressive environ- ment Author N78-25101*# National Aeronautics and Space Administration Langley Research Center Langley Station Va MODAL CONTROL THEORY AND APPLICATION TO AIRCRAFT LATERAL HANDLING QUALITIES DESIGN S Srinathkumar Jun 1978_ 63 p refs (NASA"-TP-1234 L-12177) Avail NTIS HC A04/MF A01 CSCL 01 C A multivanable synthesis procedure based on eigenvalue/ eigenvector assignment is reviewed and is employed to develop a systematic design procedure to meet the lateral handling qualities design objectives of a fighter aircraft over a wide range of flight conditions The closed loop modal characterization developed orovides significant insight into the design process and plays a pivotal role in the synthesis of robust feedback systems The simplicity of the synthesis algorithm yields an efficient computer aided interactive design tool for flight control system synthesis Author N78-25235'# Gordian Associates Inc New York COMPUTER MODEL FOR REFINERY OPERATIONS WITH EMPHASIS ON JET FUEL PRODUCTION VOLUME 3 DETAILED SYSTEMS AND PROGRAMMING DOCUMENTA- TION Final Report Daniel N Dunbar and Barry G Tunnah 27 Jun 1978 53 p (Contract NAS3-20620) (NASA-CR-135335 Rept-1099-1-Vol-3) Avail NTIS HC A04/MF A01 CSCL 21 D The FORTRAN computing program predicts flow streams and material energy and economic balances of a typical petroleum refinery, with particular emphasis on production of aviation turbine fuels of varying end point and hydrogen content specifications The program has a provision for shale oil and coal oil in addition to petroleum crudes A case study feature permits dependent cases to be run for parametric or optimization studies by input of only the variables which are changed from the base case Author N78-25135*# National Aeronautics and Space Administration Langley Research Center Langley Station Va ENVIRONMENTAL EFFECTS ON COMPOSITES FOR AIRCRAFT Richard A Pride May 1978 24 p refs Presented at CTOL Transport Technol Conf Hampton Va 28 Feb - 3 Mar 1978 Published in NASA-CP-2036 (NASA-TM-78716 L-12288) Avail NTIS HC A02/MF A01 CSCL 11D N78-25239# Exxon Research and Engineering Co Linden N J Government Research Lab EVALUATION OF METHODS TO PRODUCE AVIATION TURBINE FUELS FROM SYNTHETIC CRUDE OILS. PHASE 3, VOLUME 3 Final Report. 24 Apr 1976 - 30 Apr 1977 William F Taylor J L Kaufman E C Brown A R Cunningham and C A Smith Jun 1977 88 p refs (Contract F33615-74-C-2036 AF Pro| 3048) (AD-A053106 EXXON/GRU 3PEA 77-Vol-3 AFAPL-TR-75-10-Vol-3) Avail NTIS HC A05/MF A01 CSCL 21/4 410 N78-25466 An engineering planning study was made of the effect of processing shale oil in a refinery processing both shale oil and petroleum to a full product slate including jet fuel This study was part of an overall program whose object was to investigate the feasibility of producing aviation turbine fuels from synthetic crude oils In this Phase 3 engineering planning study the results and conclusions of the Phase 1 state-of-the-art assessment and Phase 2 pilot plant experimental study were further investigated The Exxon RESCUE Linear Program for Refinery Planning was used to provide a framework for the analysis The study which involved a number of arbitrary but well-defined assumptions was done in the context of a grass roots refinery processing shple oil and petroleum in segregated operations Shale oil processing was restricted to distillation and hydrotreating of the kerosene and gas oil fractions whereas petroleum processing involved a full spectrum of refinery processes with a relatively high level of conversion of heavier fractions to lighter fractions to meet a high motor gasoline demand GRA N78-25240# Exxon Research and Engineering Co Linden N J Government Research Lab ALTERNATE FUELS NITROGEN CHEMISTRY Final Technical Report. 19 Oct 1976 - 20 Oct 1977 John W Frankenfeld and William F Taylor Nov 1977 62 p refs (Contract N00019-76-C-0675) (AD-A053299 EXXON/GRUS 1KWC 77) Avail NTIS HC A04/MF A01 CSCL 21/4 An investigation of the effects of nitrogen compounds on sediment formation was initiated Several different nitrogen compounds were studied- including 2 5-dimethylpyrrole mdole carbazole and a number of aromatic and aliphatic amines The diluent employed was purified n-decane All of the compounds caused darkening of the fuel although appreciable amounts of sediment were formed only with the pyrrole derivatives The sediment formation was found to be strongly catalyzed by light and by organic acids Some phenols retarded the sedimentation A start was made toward characterizing the sediment obtained from 2 5-dimethylpyrrole It appeared to be a low molecular weight oligomer of partially oxidized pyrrole units Author (GRA) N78-25359*# Aeronautical Research Associates of Princeton Inc N J APPLICATION OF SECOND-ORDER TURBULENT MODEL- ING TO THE PREDICTION OF RADIATED AERODYNAMIC SOUND Alan J Bilanm and Joel E Hirsh Jun 1978 76 p refs (Contract NAS2-8832) (NASA-CR-2994) Avail NTIS HC A05/MF A01 CSCL 20D The Ribner formulation of the generation of aerodynamic sound is coupled with predictions of second-order velocity correlations and integral scale to estimate the sound radiated from several complicated jet flows In particular it is shown that the sound radiated from a cold swirling jet is greater than from its nonswirhng equal thrust counterpart The noise radiated from the flow field of a multitube suppressor was estimated and compared with an equal thrust diameter Gaussian jet It is shown that the multitube concept is indeed quieter Author N78-25453# National Aerospace Lab Tokyo (Japan) Second Airframe Div RELATIONSHIP BETWEEN SCATTER OF FATIGUE LIFE AND S-N CURVE OF 2024-T4 AIRCRAFT STRUCTURAL ALUMINUM ALLOY SPECIMENS WITH A SHARP NOTCH (Kt EQUALS 825) UNDER A CONSTANT TEMPERATURE AND HUMIDITY* CONDITION Toshiyuki Shimokawa and Yasumasa Hamaguchi Oct 1977 14 p refs Repr from J of the Japanese Soc for Strength and Fracture of Mater (Japan) v 10 no 2 1975 (NAL-TR-412T) Avail NTIS HC A02/MF A01 The accumulated effect of all factors producing fatigue life scatter which is found in a fatigue test by nominally identical specimens subjected to nominally identical repeated stresses is regarded as an error in applied stress Equivalent stress is defined as the sum of applied stress and the error in applied stress This concept is used for analyzing the results of a series of fatigue tests on aircraft structural aluminum alloy specimens with a sharp notch under a constant temperature and humidity condition The interrelationship between scatter of equivalent stress and fatigue life scatter is discussed It is shown that equivalent stresses are distributed in almost normal distribution and their standard deviation is nearly constant regardless of stress level and that fatigue life distribution has a strong correlation to the slope and shape of S-N curve Author N78-25454# Technion - Israel Inst of Tech Haifa Dept of Aeronautical Engineering THE DAMAGE SUM IN FATIGUE OF STRUCTURE COMPO- NENTS Alfred Buch 1978 15 p refs Repr from Eng Fracture Mech (England) v 10 1978 p 233-247 (ICAF-1032) Avail NTIS HC A02/MF A01 The effect of loading spectrum parameters and type of tested specimen was studied from the viewpoints of deviations from Miner s rule and of the value of the minimum cycle ratio sum at failure A minimum cycle sum may be chosen for sufficiently high values of spectrum parameters sigma max and sigma mm The increase of the cycle ratio sum with the parameters of the spectrum is connected with the effect of increased strain hardening and residual compressive stresses Some complex effects of sigma max and of the failure stress level on the damage sum were observed which cannot be explained by the residual stress concept A normal and a reversed loading sequence effect was established in two-stress level tests Author N78-25455# Israel Aircraft Industries Ltd Lod ANALYTICAL AND EXPERIMENTAL FATIGUE PROGRAM FOR THE KFIR MAIN AND NOSE LANDING GEARS B Abraham 1977 7 p refs Repr from Israel J of Tech (Israel) v 15 1977 p 70-78 Presented at the 19 ISR Ann Conf on Aviation and Astronautics Israel 1977 Avail NTIS HC A02/MF A01 The fatigue program began in the detail phase next came the development of loading spectra used for analysis and test A fatigue analysis was then performed for several suspected critical locations on both gears A fhght-by-flight test was performed on both landing gears with the aim of demonstrating four service lifetimes of operation Design modifications were introduced based on the results of these tests Rational inspection and replacement intervals were established for the mam and nose gear some of which require monitoring of aircraft Author N78-25466# Naval Postgraduate School Monterey Calif AN EXPERIMENTAL STUDY TO DETERMINE THE REDUC- TION IN ULTIMATE BENDING MOMENT OF A COMPOSITE PLATE DUE TO AN INTERNAL DELAMINATION M S Thesis Robert Gary Spngg Dec 1977 38 p refs (AD-A052662) Avail NTIS HC A03/MF A01 CSCL 20/11 The purpose of this study was to determine experimentally the effects of internal delammations in a graphite-epoxy composite plate on the plate s ultimate bending moment The experiments were conducted using 4 inch by 7 inch specimens with a balanced 0 or - 45 90, 8 ply layup The delammations were created by inserting a thin teflon disc between two lamina during layup preparation The location of the disc i e delammation was varied in each test and two disc sizes were considered The test results revealed that delammations located near an outer surface resulted in a greater reduction in the ultimate moment than those located near the center of the layup Furthermore the reduction in ultimate bending moment was found to be independent of the disc size The tendency for the internal delammations to propagate at relatively low load levels was observed and recorded Author (GRA) 411 N78-25545 N78-25545*# National Aeronautics and Space Administration Langley Research Center Langley Station Va PROGRESS ON COAL-DERIVED FUELS FOR AVIATION SYSTEMS Robert D Witcofski May 1978 27 p refs Presented at CTOL Transport Technol Conf Hampton Va 28 Feb - 3 Mar 1978 Published in NASA-CR-2036 (NASA-TM-78696 L-12275) Avail NTIS HC A03/MF A01 CSCL 21D Synthetic aviation kerosene (Syn Jet-A) liquid methane (LCH4) and liquid hydrogen (LH2) appear to be the most promising coal-derived fuels Liquid hydrogen aircraft configurations their fuel systems and their ground requirements at the airport are identified These aircraft appear viable particularly for long haul use, where aircraft fueled with coal derived LH2 would consume 9 percent less coal resources than would aircraft fueled with coal derived Syn Jet-A Distribution of hydrogen from the point of manufacture to airports may pose problems Synthetic JET-A would appear to cause fewer concerns to the air transportation industry Of the three candidate fuels LCH4 is the most energy efficient to produce, and an aircraft fueled with coal derived LCH4 may provide both the most efficient utilization of coal resources and the least expensive ticket as well Author N78-25787# National Technical Information Service Springfield Va AEROSPACE COMPUTER SYSTEMS PART 1 AVIONICS APPLICATIONS. VOLUME 2 A BIBLIOGRAPHY WITH ABSTRACTS Progress Report. 1976 - Jan 1978 William E Reed Mar 1978 208 p Supersedes NTIS/PS-77/ 0126. NTIS/PS-76/0042 (NTIS/PS-78/0289, NTIS/PS-77/0126 NTIS/PS-76/0042) Copyright Avail NTIS HC $28 00/MF $28 00 CSCL 098 This updated bibliography contains 203 abstracts of research reports on onboard data processing equipment as well as navigation and guidance computers for aircraft applications Fifty-two of the abstracts are new entries to the previous edition Author N78-25827*# Avco Lycommg Div. Stratford Conn YF 102 IN-DUCT COMBUSTOR NOISE MEASUREMENT, VOLUME 1 Final Report. 24 Jul 1976 - 31 Aug 1977 Craig A Wilson Nov 1977 72 p refs 3 Vol (Contract NAS3-20052) (NASA-CR-135404-Vol -1 LYC-77-56-Vol-1) Avail NTIS HC A04/MF A01 CSCL 20A The combustion chamber from a YF 102 gas turbine engine was instrumented with semi-infinite acoustic wave guide probes and installed in a test rig to complement the combustor noise test These combustor rig tests are described and the recorded data are listed Internal dynamic pressure level measurements were made at the same locations and at the same operating conditions of the NASA YF 102 test In addition the combustor was operated at various off-designed points where one parameter at a time was varied Background noise recordings were made to determine the magnitude of facility or test rig noise present Author N78-25831*# United Technologies Research Center East Hartford, Conn EXPERIMENTAL ASSESSMENT OF THEORY FOR REFRAC- TION OF SOUND BY A SHEAR LAYER Final Report Robert H Schlmker and Roy K Amiet Jun 1978 122 p refs (Contract NAS1-14973) (NASA-CR-145359) Avail NTIS HC A06/MF A01 CSCL 20A The refraction angle and amplitude changes associated with sound transmission through a circular open-jet shear layer were studied in a 091 m diameter open jet acoustic research tunnel Free stream Mach number was varied from 01 to 0 4 Good agreement between refraction angle correction theory and experiment was obtained over the test Mach number frequency and angle measurement range for all on-axis acoustic source locations For off-axis source positions good agreement was obtained at a source-to-shear layer separation distance greater than the jet radius Measureable differences between theory and experiment occurred at a source-to-shear layer separation distance less than one jet radius A shear layer turbulence scattering experiment was conducted at 90 deg to the open jet axis for the same free stream Mach numbers and axial source locations used in the refraction study Significant discrete tone spectrum broadening and tone amplitude changes were observed at open jet Mach numbers above 0 2 and at acoustic source frequencies greater than 5 kHz More severe turbulence scattering was observed for downstream source locations Author N78-25832*# Massachusetts Inst of Tech Cambridge Fluid Dynamics Research Lab THE EFFECT OF TIP VORTEX STRUCTURE ON HELICOPTER NOISE DUE TO BLADE/VORTEX INTERACTION Thomas L Wolf and Sheila E Widnall Mar 1978 94 p refs (Grant NsG-2142) (NASA-CR-152150 MIT-78-2) Avail NTIS HC A05/MF A01 CSCL 20A A potential cause of helicopter impulsive noise commonly called blade slap is the unsteady lift fluctuation on a rotor blade due to interaction with the vortex trailed from another blade The relationship between vortex structure and the intensity of the acoustic signal is investigated The analysis is based on a theoretical model for blade/vortex interaction Unsteady lift on the blades due to blade/vortex interaction is calculated using linear unsteady aerodynamic theory and expressions are derived for the directivity, frequency spectrum and transient signal of the radiated noise An inviscid rollup model is used to calculate the velocity profile in the trailing vortex from the spanwise distribution of blade tip loading A few cases of tip loading are investigated and numerical results are presented for the unsteady lift and acoustic signal due to blade/vortex interaction The intensity of the acoustic signal is shown to be quite sensitive to changes in tip vortex structure Author N78-2S829*# Avco Lycommg Div Stratford Conn YF 102 IN-DUCT COMBUSTOR NOISE MEASUREMENT. VOLUME 3 Final Report Craig A Wilson Nov 1977 194 p 3 Vol (Contract NAS3-20052) (NASA-CR-135404-Vol-3, LYC-77-56-Vol-3) Avail NTIS HC A09/MF A01 CSCL 20A For abstract see N78-25827 N78-25840# National Technical Information Service Springfield Va NONLINEAR ACOUSTICS A BIBLIOGRAPHY WITH ABSTRACTS Progress Report, 1966 - Feb 1978 George W Reimherr Mar 1978 141 p Supersedes NTIS/PS- 77/0203 NTIS/PS-76/0235 NTIS/PS-75/351 COM-74- 10868 (NTIS/PS-78/0240 NTIS/PS-77/0203 NTIS/PS-76/0235 NTIS/PS-75/351 COM-74-10868) Copyright Avail NTIS HC $28 00/MF $2800 CSCL 20A This updated bibliography contains 135 abstracts 18 of which are new entries to the previous edition Topics covered include nonlinear acoustic theory and applications to sound transmission in the atmosphere underwater solids liquids and gases Nonlinear relationships are presented for shock tubes, sonar equipment sonic booms acoustic defectors sound generators acoustic delay lines porous materials pipes ducts and jet engine noise GRA 412 N78 25987 N78-25966*# City Coll of the City Umv of New York AN ADAPTIVE LEARNING CONTROL SYSTEM FOR AIRCRAFT Ralph Mekel and Solomon Nachmias Apr 1978 222 p refs (Grant NsG-1169) (NASA-CR-156930) Avail NTIS HC A10/MF A01 CSCL 05A A learning control system and its utilization as a flight control system for F-8 Digital Fly-By-Wire (DFBW) research aircraft is studied The system has the ability to adjust a gam schedule to account for changing plant characteristics and to improve its performance and the plant s performance in the course of its own operation Three subsystems are detailed (1) the information acquisition subsystem which identifies the plant s parameters at a given operating condition. (2) the learning algorithm subsystem which relates the identified parameters to predetermined analytical expressions describing the behavior of the parameters over a range of operating conditions and (3) the memory and control process subsystem which consists of the collection of updated coefficients (memory) and the derived control laws Simulation experiments indicate that the learning control system is effective in compensating for parameter variations caused by changes in flight conditions Author N78-2597O# Defense Systems Management School Fort Belvoir Va DOCTRINE VERSUS CAPABILITIES A PROJECT MANAG- ER'S DILEMMA WITH THE CH-47 HELICOPTER Billy V Center Nov 1977 37 p refs (AD-A052376 PMC-77-2) Avail NTIS HC A03/MF A01 CSCL 01/3 This report examines an existing dilemma facing the CH-47 Modernization PM The dilemma is the conflict between the tactical doctrine and the CH-47 external load capabilities including the near term modernized capabilities The external load limitations are defined and future technology to improve the CH-47 capabilities is identified Two promising external load carrying concepts are highlighted The primary recommendation is for the user to question if the external load NOE all weather day-night capability is a valid requirement Author (GRA) N78-25974# Air Force Inst of Tech Wright-Patterson AFB Ohio School of Engineering A STUDY OF THE F-4 PROGRAM MANAGEMENT RESPON- SIBILITY TRANSFER (PMRT) FROM THE AIR FORCE SYSTEMS COMMAND TO THE LOGISTICS COMMAND M S Thesis Wesley K Darrell Dec 1977 155 p refs (AD-A052903 AFIT/GSM/SM/77D-19) Avail NTIS HC A08/MF A01 CSCL 01/3 The increasing costs of weapon systems have created a demand for more efficient program management The Air Force organizational structure for acquiring and supporting weapon systems results in two commands sharing this responsibility The Air Force Systems Command is responsible for research development procurement and production The Air Force Logistics Command is responsible for supply maintenance and other logistical support Program management responsibility transfers from the Systems Command to the Logistics Command at some point in the acquisition cycle This transition has in the past resulted in confusion duplication and fragmented responsibility In an effort to provide for more efficient program management during program transition the Program Management Responsibility Transfer concept was initiated in 1975 The F-4 program was the first program to transfer under this new concept The purpose of this study is to provide a critical analysis of the new transfer process through a study of the F-4 transfer GRX Jam S Dajani and Gerald W Bernstein May 1978 31 p refs (NCAZ-OR745-720) (NASA-CR-152148) Avail NTIS HC A03/MF A01 CSCL 05C A suivey is presented of some of the approaches which have been considered in freight demand estimation The few existing continuous time computer simulations of aviation systems are reviewed with a view toward the assessment of this approach as a tool for structuring air freight studies and for relating the different components of the air freight system The variety of available data types and sources without which the calibration validation and the testing of both modal split and simulation models would be impossible are also reviewed Author N78-25985*# United Technologies Research Center East Hartford Conn APPLICATIONS OF ADVANCED TRANSPORT AIRCRAFT IN DEVELOPING COUNTRIES Contractor Report. Mar 1977 - Apr 1978 F W Gobetz R J Assarabowski and A A LeShane May 1978 340 p refs (Contract NAS1-14795) (NASA-CR-145343 R78-912839-14) Avail NTIS HC A15/MF A01 CSCL 05A Four representative market scenarios were studied to evaluate the relative performance of air-and surface-based transportation systems in meeting the needs of two developing contnes Brazil and Indonesia which were selected for detailed case studies The market scenarios were remote mining low-density transport tropical forestry and large cargo aircraft serving processing centers in resource-rich remote areas The long-term potential of various aircraft types together with fleet requirements and necessary technology advances is determined for each application Author N78-25986*# Delco Electronics Santa Barbara Calif ELECTROMECHANICAL FLIGHT CONTROL ACTUATOR. VOLUME 2 Final Report Jan 1978 192 p 3 Vol (Contract NAS9-14952) (NASA-CR-151734 R78-1-Vol-2) Avail NTIS HC A09/MF A01 CSCL 13F Schematic diagrams are given for both the four-channel electromechanical actuator and the single-channel power electronics breadboard Detailed design data is also given on the gears used in the differential gearbox and a copy of the operations manual for the system is included Performance test results are given for the EMA motor and its current source indicator the drive control electronics and the overall system The power converter waveform test results are also sum- marized Author N78-25987*# Delco Electronics Santa Barbara Calif ELECTROMECHANICAL FLIGHT CONTROL ACTUATOR VOLUME 3 Final Report Jan 1978 188 p 3 Vol (Contract NAS9-14952) (NASA-CR-151735 R78-1-Vol-3) Avail NTIS HC A09/MF A01 CSCL 13F The design verification tests which were conducted on the electromechanical actuator are described A description is also given of the power components tests which were conducted to aid in selecting the power transistors for use in the single-channel power electronics breadboard and the results of tests which were conducted on the power electronics breadboard Author N78-25979*# Stanford Umv Calif Dept of Civil Engineer- ing AIR FREIGHT DEMAND MODELS AN OVERVIEW 413 SUBJECT INDEX AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl 100) Typical Subject Index Listing SEPTEMBER 1978 TAPOBIZBBS •Liquid hydrogen flash vaporizer — fuel systeis rHASA-CaSE-LAB-12159-11 TITLE REPORT NUMBER — for aircraft - H78-11260 The title is used to provide a description of the subject matter When the title is insufficiently descriptive of the document content a title extension is added separated from the title by three hyphens The NASA or AIAA accession number is included in each entry to assist the user in locating the abstract in the abstract section of this supplement If applicable a report number is also included as an aid tn identifying the document 4BSOBPTION SPECTBOSCOPY Jin atonic fluorescence system using a continuum source for the rapid determination of near metals in jet engine lubricating oils [AD-A052721] N78-21320 1BSTBJCTS Parachutes and decelerators, volume 2. A bibliography with abstracts [RTIS/PS-78/0320] N78-25067 ACODSTIC EHIS5IOH Can fatigue cracks be detected in an early stage by acoustic emission? Application to high resistance light alloys used in aeronautics A-BU61, A-026N T6 [AAAF-NT'77-35] N78-21S87 Demonstration of acoustic emission system for damage monitoring of full scale metallic aircraft structures during fatigue testing [AD-A053108] H78-25085 ACOUSTIC HBASOBEHEJTS Acoustic evaluation of a novel swept-rotor fan noise reduction ID tarbofan engines [HASA-TH-78878] 178-21897 ACOUSTIC PBOPBBTIES Powered-Lift Aerodynamics and Acoustics conferences CSASA-SP-M06] H78-210U6 ACOUSTIC SCATTBB1HG Experimental assessment of theory for refraction of sound by a shear layer [NASA-CB-145359] N78-25831 ACOUSTICS Acoustic design of the QCSEE propulsion systems N78-21067 Nonlinear acoustics. A bibliography with abstracts [NTIS/PS-78/0240] N78-25810 ACTUATOBS Electromechanical flight control actuator, volume 2 [NASA-CB-15173U] H78-25986 Electromechanical flight control actuator, volume 3 [NASA-CB-151735] R78-25987 AEBOACOUSTICS Powered-lift Aerodynanics and tcoustics conferences [NASA-SP-106] N78-21016 Acoustics and aerodynamics of over-the-wing thrust reversers N78-2a071 AEBOD1BABIC CHAB1CTEBISTICS Discussion of results of studies on the design of laminar airfoils for stunt gliders 478-36201 Bemarks on design of supersonic vind tunnels A78-36216 Flight experiments on aerodynamic features affecting helicopter blade design A78-3C919 Rind tunnel tests of a slotted flapped wing section J78-37537 Aerodynamics of the annular wing A78-38175 Local method in rarefied gas aerodynamics J78-38726 Prediction of the aerodynamic characteristics of an aircraft on the basis of the comparison of results for a calibration model in various large transonic wind tunnels [ONEBA, TP NO. 1978-22] A78-39579 Aerodynamic preliminary analysis system. Part 2: User's manual and program description [NASA-CB-115300] N78-21013 Powered-lift Aerodynamics and Acoustics conferences [NASA-SP-1106] H78-2UOU6 Summary of low-speed aerodynamic characteristics of upper-surface-blown jet-flap configurations N78-21050 Comparison of aerodynamic theory and experiment for jet-flap wings N78-21052 Aerodynamic characteristics in ground proximity N78-21055 Theoretical predictions of jet interaction effects for DSB and OWB configurations N78-21059 Hind-tunnel investigation of basic aerodynamic characteristics of a supercritical-wing research airplane configuration [NASA-TM-X-2170] N78-21078 Aerodynamic characteristics of an NAS? supercritical-wing research airplane model with and without fuselage area-rule additions at Bach 0.25 to 1.00 [NASA-TH-X-2633] N78-21080 Experimental investigation of aerodynamic characteristics of a tracked ram air cushion vehicle [PB-277671] 1178-21099 Fundamental aspects of the aerodynamics of turbojet engine combustors tNASA-TH-75287] N78-21112 Aerodynamic characteristics at Hach number 0.2 of a wing-body concept for a hypersonic research airplane [BASA-TP-1189] N78-25059 Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds CSASA-TP-1215] N78-25060 Preliminary study of a large span-distributed-load flying-wing cargo airplane concept [HASA-TP-1158] N7.8-25079 Acoustics and performance of high-speed, unequally spaced fan rotors [NAL-TB-526] N78-25091 AEBODTRAHIC COEFFICIENTS On lift of delta wings with leading-edge vortices at low speeds A7B-39772 AEBODTNAHIC CORFIGOBATIOHS Design for flying Book A78-36198 A-1 AEHODVHAHIC DBAG SUBJECT IHDEI Simplified input for certain aerodynamic nose configurations to the Grumman quick-geometry system. A KHIKNOSE user's manual [SD-A051U25] N78-2U089 Aircraft sonic boom: Studies on aircraft flight, aircraft design, and measurement. A bibliography with abstracts CHTIS/PS-78/0238] H78-25100 AEEODYHiBIC DRAG Calculation of airfoil drag A78-36210 ninimisation of relaxation drag A78-37123 Effects of nozzle design and power on cruise drag for upper-surface-blowing aircraft N78-24058 Drag reduction for gliders [NASA-TH-75293] N78-21116 AEBODYSAHIC LOADS Deformation curve of rotary airfoil blades A78-395HO Measured and calculated steady aerodynamic loads on a large-scale upper-surface blown model N78-2U072 Rind-tunnel measurements of aerodynamic load distribution on an NASA supercritical-wing research airplane configuration [NASA-TH-X-2U69] N78-2Q079 The development and application of a simple method for determining unsteady airloads in subsonic compressible flow CAD-A052H17] S78-21096 AERODYNAMIC BOISE Azimuthal decomposition of the power spectral density of jet n'oise A78-37532 Remarks on the noise emitted by the jet of a gas turbine engine A78-38696 Acoustic-loads research for powered-lift configurations N78-21073 Acoustics and performance of high-speed, unequally spaced fan rotors [NAL-TB-526] H78-25091 Application of second-order turbulent modeling to the prediction of radiated aerodynamic sound [NASA-CB-2991] N78-25359 The effect of tip vortex structure on helicopter noise due to blade/vortex interaction [NASA-CB-152150] N78-25832 AERODYHAHIC STABILITY The computation of the unsteady aerodynamics of bodies near a ground surface A78-37q08 AERODYNAMICS The turbulent flow through a sadden enlargement at subsonic speeds A78-37I413 Factorization methods in hydroaeromechanics Russian book A78-37887 laser velocimeter for wind tunnel measurements A78-37979 AEEOELASTICITY On the optimization of discrete structures with aeroelastic constraints A78-39135 Deformation curve of rotary airfoil blades A78-39540 AEROLOGY The role of meteorology in helicopter icing problems A78-37712 Prospects for using new flight vehicles in aerophysical studies A78-39189 AEROHAUTICAL BFGIHEEBIHG Application of modern methods in civil aircraft construction A78-38808 Cobalt-base alloys produced by powder metallurgy for compressor and turbine disks [ONEBA, TP HO. 1978-7] A78-39582 iEHOSPACB SYSTEBS Aerospace computer systems. Part 1: Avionics applications, volume 2. A bibliography with abstracts [NTIS/PS-78/0289] H78-25787 AEBOTHEBHODYHAMICS Unsteady heat transfer from a cylinder with radial injection A78-390U2 AGHICDLTOBE An economic and technical perspective of the turboprop engine in Ag-aviation A78-37536 AIB CARGO Survey of air cargo forecasting techniques [NASA-CH-145329] H78-25068 Preliminary analysis of hub and spoke air freight distribution system [HASA-TH-72656] K78-25069 Air freight demand models: An overview [NASA-CB-1521 US] N78-25979 AIB FLOW Oil-air mist lubrication for helicopter gearing [NASA-CB-135081] B78-25080 Gas turbine engine with recircnlating bleed [NASA-CASE-LEw-121152-1 ] N78-25089 AIB JETS The mean velocity field of unsteady subsonic air }ets A78-37Q17 AIB NAVIGATION System requirements for transition from enroute to approach guidance A78-36U53 AIB POLLUTION Flight-testing of a continuous laser remote sensing system J78-39632 AIB SAHPLING Snbisokinetic sampling errors for aircraft turbine engine smoke probes A78-38575 AIH TBiFFIC Expansion potential for the local service air carrier A78-37539 Airport activity statistics of certificated route air carriers [AD-A052728] N7B-21102 AIB TBSFFIC CONTROL Concerning the logical comparison of ATC separation standard assessment models A78-36155 Fully-automated, pilot-monitored air traffic control A78-37155 Dealing with false targets in the Air Traffic Control Radar Beacon System A78-37M86 The new system for processing and presenting radar data in the fir Traffic Control Center of Barcelona A78-38997 A relative motion analysis of horizontal collision avoidance A78-3967U Verification of DABS sensor surveillance performance (ATCEBS mode) at typical ASR sites throughout CONOS [AD-A051128] N78-21105 Use of simulation techniques in the problem of air traffic control [QOAD-CALC-ELETT-21] H78-21111 Feasibility study for simulation of an airport tower control environment [AD-A051174] B78-21151 Project Plan: Tower automated ground surveillance system development program [AD-A051621] H78-21155 Problems in world-wide standardization of the units of height measurement [AD-A051150] B78-2U385 Perspective radar display system: TV-like presentation on CBT provides higher lateral position and lateral motion sensitivity than a PPI [AD-A052342] N78-2U118 Precision positional data of general aviation air traffic in terminal air space [NASA-HP-1020] N78-250II8 NASA aviation safety reporting system [NASA-TH-78176] N78-25071 AIB TRANSPORTATION Reliability of aviation techniques and flight safety Bussian book A78-36U9I! A-2 SUBJECT IIDEI AIBCB1FT DESIGB Airport activity statistics of certificated route air carriers [AD-A052728] H78-214102 Pircraft size and air transport costs N78-21I112 Supersonic transportation faced with energy savings [AAAF-NT-77-28] H78-21131 AIBBOBHE EQOIPHEHT Color displays for airborne weather radar A^S-36980 Evaluation of airborne radar Doppler processors A78-37H77 CRT update for airborne displays A78-371I90 Hodern millimeter wave instrumentation radar development and research methodology A78-37501 Susceptibility testing of airborne equipment - The way ahead A78-39086 An approach to EBP testing of complete strike aircraft A78-39088 Aircraft measurement of radio frequency noise at 121.5 HHz, 213HHZ and 106HHZ A78-39105 Study of magnetic noise in the Ka-26 helicopter A78-39188 Flight-testing of a continuous laser remote sensing system A78-39632 AIRBOEUE/SPACEBOEBE COHPOTEBS Testing of the YC-1U flight control system software [AIAA PAPEE 77-1077] A78-39183 Aerospace computer systems. Part 1: Avionics applications, volume 2. A bibliography with abstracts [NTIS/PS-78/0289] N78-25787 AIBCB4FT Thin conformal antenna array for microwave power conversions [NASA-CASE-NPO-13886-1 ] N78-21391 AIBCBSFT ACCIDENTS Reliability of aviation techniques and flight safety Russian book A78-36U91 Optimal flare in presence of wind shears for aircraft in automatic approach A78-39186 AIBCBAFT ASTESBAS Experimental evaluation of an array technique for zenith to horizon coverage aircraft to satellite communication links A78-36380 AIBCBAFT iPPBOACB SPACIHG Concerning the logical comparison of ATC separation standard assessment models A78-36Q55 AIRCRAFT CABRIEBS Environmental requirements for simulated helicopter/VTOl operations from small ships and carriers [AD-A053078] N78-25081 AIBCBAFT COHBDHICATIOB A three-dimensional finite-difference solution of the external response of an aircraft to a complex transient EH environment. I - The method and its implementation. II - Comparison of predictions and measurements A78-37120 Modern BF system design for aircraft tactical information exchange system A78-373U1 Assessment procedure application utilizing OHF transistor BF pulse susceptibility data ?nc studies of approach radar and of aircraft DBF-receiver A78-39101 NASA aviation safety reporting system [HASA-TB-78I176] B78-25071 AIBCBAFT COHPABTHEHTS Low frequency cabin noise reduction based on the intrinsic structural tuning concept: The theory and the experimental results, phase 2 jet aircraft noise [NASA-CR-1H5262] N78-29900 AIBCBAFT COHFIGOBATIOSS Lighter-than-air concepts and recent developments A78-39395 A V - 8 B composite wing government/industry briefing N78-211113 Paneling techniques for use with the VOBLAX computer program [BASA-CB-1«536il] N78-25051 AIBCBAFT COHSTBDCTIOB BATEBIiLS Integrally stiffened laminate construction A78-36H31 ALC/50/ values for some polymeric materials Apparent Lethal Concentration fire toxicity A78-36596 Case of damage involving aircraft and helicopter components of light metal A78-369I41 Application of modern methods in civil aircraft construction A78-38808 Heavily loaded carbon-fiber-reinforced-plastic primary structure with the Tornado taileron as an example A78-38810 naterial selection for the Tornado taileron A78-38811 Influence of the type of corrosion of the aircraft skin on limiting value of the damage A78-38907 Test operations procedures physical characteristics aviation material [AD-A053196] N78-25086 Environmental effects on composites for aircraft [NASA-TB-78716] N78-25135 AIBCBAFT COHTBOL 7-5E/F spin avoidance testing A78-38717 The effects of wind shear on aircraft flight path and methods for remote sensing and reporting of wind shear at airports [UTIAS-TS-216] N78-21755 AIBCEAFT DESIGN Characteristics of flow past fuselages and wing-fuselage systems of gliders A78-36203 Discussion of results of studies on the design of laminar airfoils for stunt gliders A78-36200 Calculation of airfoil drag A78-36210 The design of future cockpits for high performance fighter aircraft A78-36116 Design for flying Book A78-36198 The computation of the unsteady aerodynamics of todies near a ground surface 178-37408 Flow past nonconical wings with separation A78-37775 Theoretical investigation on the crash behavior of cell structures aircraft structural design A78-38805 Material selection for the Tornado taileron A78-38811 Airships - The next generation and beyond A78-39396 Deformation curve of rotary airfoil blades A78-395UO Aerodynamic preliminary analysis system. Part 2: User's manual and program description [HASA-CB-115300] N78-2140U3 A non-stationary model for atmospheric turbulence patches for the prediction of aircraft design loads fHLR-TB-76131-0] H78-25077 A study of commuter airplane design optimization [NASA-CB-157210] N78-25078 Preliminary study of a large span-flistributed-load flying-wing cargo airplane concept [HASA-TP-1158] N78-25079 Aircraft sonic boom: Studies on aircraft flight, aircraft design, and measurement. A bibliography with abstracts [HTIS/PS-78/0238] H78-25100 Nodal control theory and application to aircraft lateral handling qualities design [NASA-TP-1230] H78-25101 A-3 AIRCRAFT DETECTION SUBJECT IBDEI 1IBCHAPT DETECTIOB The effect of correlated missed detections, correlated false alarms and interclutter visibility on the performance of an automated radar tracking system A78-37H85 AIBCEAFT EFGISBS Pircraft propulsion from the back room /Sixty-sixth Wilbur and Orville Bright Memorial Lecture/ A78-36279 Aero engines climb towards better fuel efficiency A78-37114 Bolls-Eoyce BB401 turbofan - ft nev business 3et engine for the 1980's A78-37538 Aircraft auxiliary power units Bussian book A78-37885 Subisokinetic sampling errors for aircraft turbine engine suoke probes A78-38575 Replacement process analysis: An interim report on replacement models [AD-A052011 1 N78-24150 An atomic fluorescence system using a continuum source for the rapid determination of wear metals in net engine lubricating oils [AD-A0527211 N78-24320 Impact of future fuel properties on aircraft engines and fuel systems [NASA-TM-78866] N78-24369 Performance tests and design modifications of a Wankel type rotary combustion automobile engine in order to determine its suitability for aircraft application [CSIB-ME-1521 ] N78-25095 Inductor network development for aircraft high power supplies [AD-A052750] N78-25096 &IBCBAFT EQOIPBENT The technical concepts behind the IL-62M /8/ landing gear A78-36622 Modern BF system design for aircraft tactical information exchange system A78-37341 Air speed and attitude probe [NASA-CASE-FEC-11009-1] N78-25088 AIBCBAFT FDE1S Characteristics and combustion of future hydrocarbon fuels aircraft fuels [NASA-Tn-78865] N78-2H370 Evaluation of methods to produce aviation turbine fuels from synthetic crude oils phase 3, volume 3 [AD-A053106] N78-25239 Progress on coal-derived fuels for aviation systems [ NASA-TM-78696] N78-255U5 ilBCEAFT BYDBADLIC STSTBBS Halogenated solvent-induced corrosion in hydraulic systems hydraulic drives for aircraft radar antennas [ASIE PBEPBINT 78-AN-UA-2] A78-38083 AIBCBAFT IBDOSTBY A rising sun in aircraft Japanese commercial aircraft development programs A78-3852U AIBCBAFT INSTBOBEBTS fircraft radar systems Eussian book A78-37873 AIBCBAFT LANDING Ergonomics in commercial aircraft landing A78-36621 i theoretical study of the effect of blade ice accretion on the power-off landing capability of a Wessex helicopter 478-36948 Soviet landing aid draws FAA scrutiny laser approach guidance A78-38773 AIBCBAFT MAINTENANCE Titanium and titanium alloys in aircraft maintenance and repair. I A78-38216 Problem-solving with selective plating for aircraft metal coating repair A78-38900 British Airways Tri-Star - Present and future A78-39393 Three degree intermediate level maintenance of Navy aeronautical materials [AD-A052389] N78-240U2 General aviation avionics equipment maintenance [NASA-CB-145312] N78-24132 Naval aircraft operating and support cost model - Fiscal Year 1976 revision [AD-A053180] N78-25051 AIBCBAFT fl&SEOVEBS F-5E/F spin avoidance testing A78-38747 AIBCBAFT BODELS Grumman's radio-controlled experimental air force A78-38522 EHP induced currents on a simplified missile theory and experiment A78-39109 AIBCBAFT BOISE Atmospheric-absorption adjustment procedure for aircraft flyover noise measurements computer program [AD-A051700] N78-24899 Aircraft sonic boon: Effects on buildings. A bibliography with abstracts [NTIS/PS-78/0239] N78-25099 Aircraft sonic boom: Studies on aircraft flight, aircraft design, and measurement. A bibliography with abstracts [NTIS/PS-78/0238] N78-25100 AIBCBAFT PASTS Case of damage involving aircraft and helicopter components of light metal A78-36941 AIBCBAFT PEBFOBBABCE The design of future cockpits for high performance fighter aircraft A78-36446 The German-Dutch low speed wind tunnel DNH A78-36447 Planning and procedures for aircraft demonstrations - v/STOL aircraft A78-38749 Simulation replay - Implementation and flight simulation applications A78-38789 AIBCBAFT PILOTS Fully-automated, pilot-monitored air traffic control A78-37155 AIBCBAFT BBLIABILITY The certification of light aircraft A78-36280 AIBCBAFT SAFETY Electronic aircraft collision avoidance system Eussian book A78-37603 The role of meteorology in helicopter icing problems A78-37712 On the compensation of radio direction finders antenna optimization in airport environments A78-38247 The impact of flight simulators on U-S. airlines A78-38798 The determination of margins of safety for critical aircraft systems electromagnetic interference effects on flight and engine controls A78-39082 Study of a safety margin system for powered-lift STOI aircraft [NASA-CE-152139] N78-21117 AIBCBAFT STABILITY F-5E/F spin avoidance testing A78-38747 AIBCBAFt SIBDCTOBES Stress intensity factors, for collinear cracks in a stiffened sheet aircraft structures A78-38122 Titanium and titanium alloys in aircraft maintenance and repair. I A78-38246 Problems of the theory of strength related to aircraft construction and civil engineering; Structural Mechanics Meeting, Ottobrunn, Best Germany, June 1, 2, 1977, Lectures and Discussion Contributions A78-38802 New technologies for aircraft structures A78-38803 A-n SUBJECT ISDEI APPBOXIBATION On the optimization of discrete structures »ith aeroelastic constraints A78-39135 Can fatigue cracks be detected ID an early stage by acoustic emission? Application to high resistance light alloys nsed in aeronautics A-0461, A-026N T6 [AAAF-NT-77-35] S78-2U587 Low fregoency cabin noise redaction based on the intrinsic structural tnning concept: The theory and the experimental results, phase 2 jet aircraft noise [NASA-CB-115262] N78-21900 The damage sum in fatigue of structure components aircraft structures [ICAF-1032] N78-25151 AIBCBAFT SAFES Some measurements of an EB? powered-lift wake N78-2405U AIBFOIl PBOFILBS Discussion of results of studies on the design of laminar airfoils for stunt gliders A78-3620M Hot-wire velocity measurements in thin boundary layers A78-36205 Calculation of airfoil drag A78-36210 Aerodynamics of the annular wing A78-38U75 Investigations of the transonic flow around oscillating airfoils Thesis A78-38978 AIBFOILS The next approximation after boundary layer theory machine blade associated unsteady flow effects A78-37409 Notes on the transonic indicial method for two dimensional airfoil flutter derivative calculation A78-37732 AV-8B composite wing government/industry briefing N78-21113 AIBFBABB HATEBIALS New technologies for aircraft structures A78-38803 Heat treatment studies of aluminum alloy type 7050 forgings. The effect of heat treatment on a variety of engineering properties [NLR-TB-76008-0] N78-25199 AIBFHiBES Exploratory development for design data on structural aluminum alloys in representative aircraft environments [AD-A052809] 578-213411 Demonstration of acoustic emission system for damage monitoring of full scale metallic aircraft structures during fatigue testing FAD-A0531081 N78-25085 SIBLIHE OPEBATIOBS Expansion potential for the local service air A78-37539 The impact of flight simulators on 0.S. airlines A78-38798 British Airways Tri-Star - Present and future A78-39393 Aircraft size and air transport costs 178-21112 An operator's viewpoint: How to reduce the fuel consumption in aeronautical maintenance [AAAF-NT-77-26] 578-21129 AIBPOBT BEACONS On the compensation of radio direction finders antenna optimization in airport environments A78-38247 AIBPOBT PLANNING Study on problems of terminal site location environmental effects on airport, harbcr or truck depot A78-36323 AIBPOBT SOBFACE DETECTION EQDIPHEIIT Project Plan: Tower automated ground surveillance system development program [AD-A051621 ] N78-21155 AIBPOBT TOIEBS Feasibility study for simulation of an airport tower control environment [AD-A051171] H78-2115I4 Project Plan: Tower automated gronnd surveillance system development program [AD-A051621] N78-2I1155 AIBPOBTS Airport activity statistics of certificated route air carriers [AD-A052728] N78-2H102 The effects of wind shear on aircraft flight path and methods for remote sensing and reporting of wind shear at airports [DTIAS-TH-216] N78-21755 Precision positional data of general aviation air traffic in terminal air space [NASA-BP-1020] N78-25018 AIBSBIPS Lighter-than-air concepts and recent developments 478-39395 Airships - The next generation and beyond A78-39396 AIBSPEED On the use of relative velocity exponents for ]et engine exhaust noise A78-37683 Air speed and attitude probe [NASA-CASE-FRC-11009-1 ] H78-25088 ALTITUDE Problems in world-wide standardization of the units of height measurement [AD-A051150] N78-2U385 ALUHIHOH ALLOTS Influence of the type of corrosion of the aircraft skin on limiting value of the damage A78-38907 Exploratory development for design data on structural aluminum alloys in representative aircraft environments [AD-A052809] 578-21311 Heat treatment studies of aluminum alloy type 7050 forgings. The effect of heat treatment on a variety of engineering properties [NLB-TB-76008-0] N78-25199 Relationship between scatter of fatigue life and S-B curve of 2021-T1 aircraft structural aluminum alloy specimens with a sharp notch (Kt equals 8.25) under a constant temperature and humidity condition [NAL-TR-112T] 578-25U53 ANGLE OF ATTACK High angle canard missile test in the Ames 11-foot transonic wind tunnel [NASA-CB-2993] K78-25057 ANNOLAB PLATES Aerodynamics of the annular wing A78-38175 ANTENNA 4BBAYS Thin conformal antenna array for microwave power conversions [SASA-CASE-NPO-13886-1] N78-24391 ANTENNA DESIGN Experimental evaluation of an array technique for zenith to horizon coverage aircraft to satellite communication links J78-36380 On the compensation of radio direction finders antenna optimization in airport environments A78-38217 A high-power switching network for a dual-mode antenna for airborne transmitter application A78-38811 ANTENNA BADIATION PATTEBNS Verification of DABS sensor surveillance performance (ATCBBS mode) at typical ASB sites throughout CONUS [AD-A051128] 578-21105 1PPBOACH COBTBOL System requirements for transition from enroute to approach guidance J78-36153 Soviet landing aid draws FA? scrutiny laser approach guidance A78-38773 APPBOXIBATION Nonlinear theory of a bearing surface of arbitrary extent [AD-A051385] 578-21090 1 distributed vortex method for computing the vortex field of a missile [NASA-TP-1183] N78-25058 A-5 ABBA NAVIGATIOH SUBJECT IHDBX ABBA NAVIGATION Jeppesen charting for area navigation A78-36i)51 Hew model VOB/DHE A78-37216 ATMOSPHERIC ATTEHOATIOH Atmospheric-absorption adjustment procedure for aircraft flyover noise measurements computer program [AD-A051700] H78-2U899 ATMOSPHEBIC CHEHISTBI Photochemistry and dynamics of the ozone layer A78-38766 ATBOSPHEBIC HODE1S Photochemistry and dynamics of the ozone layer A78-38766 iTHOSPHEBIC TOBBOLBHCE A non-stationary model for atmospheric turbulence patches for the prediction of aircraft design loads [NLR-TR-76131-D] 1178-25077 ATS 5 Results of the NASA/HABAD L-band satellite navigation experiment A78-37525 ATS 6 Results of the NASA/HABAD I-band satellite navigation experiment A78-37525 ATTACK AIRCBAFT An approach to EHP testing of complete strike aircraft A78-39088 ATTITDDE INDICATORS Air speed and attitude probe [NASA-CASE-FRC-11009-1] N78-25088 AUTOMATIC FLIGHT COHTBOl Fully-automated, pilot-monitored air traffic control A78-37155 AOTOHATION The effect of correlated missed detections, correlated false alarms and interclutter visibility on the performance of an automated radar tracking system A78-37485 AOXILIABY POREB SOOBCES Aircraft auxiliary power units Russian book A78-37885 AVIONICS Hodern BF system design for aircraft tactical information exchange system A78-37341 Electronic aircraft collision avoidance system Russian book A78-37603 The F-UE Austere HDD/Gunsight project A78-387U6 Jaguar and Tornado avionic development testing A78-387U8 The determination of margins of safety for critical aircraft systems electromagnetic interference effects on flight and engine controls A78-39082 Filtering techniques in avionic transmitters A78-3908U Diary of an international team co-ordinating system electromagnetic compatibility of an avionic sub-system A78-39085 Susceptibility testing of airborne eguipment - The way ahead A78-39086 EMC control of the tornado aircraft A78-39087 General aviation avionics equipment maintenance [NASA-CH-1t53t2] N78-21132 On setting avionic subsystem unit production cost goals contract management and procurement policy [AD-A051337] N78-21133 Aerospace computer systems. Part 1: Avionics applications, volume 2. A bibliography with abstracts fNTIS/PS-78/0289] H78-25787 AXIAL FLOS TOBBIHES Calculation of transonic flow through a turbine cascade by the time-step method A78-382118 B B-1 AIBCBAFT Preliminary design of low-cost titanium structure B-1 aircraft engine nacelles [AD-A053327] H78-25087 BASE PBESSOBB Flight-measured pressnre characteristics of aft-facing steps in high Reynolds number flow at Bach numbers of 2.20, 2.50, and 2.80 and comparison with other data [HASA-Tn-72855] S78-250S5 BEBDIHG MOMENTS An experimental study to determine the reduction in ultimate bending moment of a composite plate due to an internal delamination [AD-A052662] H78-25166 BIBLIOGRAPHIES Parachutes and decelerators, volume 2. A bibliography with abstracts [NTIS/PS-78/0320] N78-25067 Aircraft sonic boom: Effects on buildings. A bibliography with abstracts [NTIS/PS-78/0239] 578-25099 Aircraft sonic boom: Studies on aircraft flight, aircraft design, and measurement. A bibliography with abstracts [NTIS/PS-78/0238] N78-25100 Aerospace computer systems. Part 1: Avionics applications, volume 2. A bibliography with abstracts [HTIS/PS-78/0289] H78-25787 Nonlinear acoustics. A bibliography with abstracts [NTIS/PS-78/02HO] N78-258UO BLADE TIPS The effect of tip vortex structure on helicopter noise due to blade/vortex interaction [NASA-CR-152150) 1178-25832 BO-105 HELICOPTEB IDS - An advanced hingeless rotor system A78-36950 BODY-»ING COHTIGOBATIOHS Characteristics of flow past fuselages and wing-fuselage systems of gliders A78-36203 Aerodynamic characteristics at Mach number 0.2 of a wing-body concept for a hypersonic research airplane [NASA-TP-1189] N78-25059 BOOHDABY LAIBR COHTBOL Boundary layer blowing tests on a radial diffnser in low and subsonic Nach range A78-37U11 Application of laminar flow control to large subsonic military transport airplanes [AD-A052M22] N78-21098 BOONDABY LAYBB FLOW Hot-wire velocity measurements in thin boundary layers A78-36205 BOUNDARY LATEB STABILITY Calculation of airfoil drag A78-36210 BOOHDABY L&Y.2B TBAHSITIOH The next approximation after boundary layer theory machine blade associated unsteady flow effects A78-37U09 BOOHDABY LAYEBS Methods and results of boundary layer measurements on a glider [NASA-TH-7529U] H78-24085 BBAKES (FOB ABBESTIHG MOTION) Parachutes and decelerators, volume 2. A bibliography with abstracts [NTIS/PS-78/0320] B78-25067 BUILDINGS Aircraft sonic booo: Effects on buildings. A bibliography with abstracts [NTIS/PS-78/0239] N78-25099 BDBNIHG BATE Analysis of spray combustion in a research gas turbine combustor A78-37297 A-6 SUBJECT IHDEI COHBUNICATIOH EQOIPBENT C-15 AIBCBAFT Overview of powered-lift technology as used on the YC-11 aircraft and C-15 aircraft 878-21017 CALIBBATING Prediction of the aerodynamic characteristics of an aircraft on the basis of the comparison of results for a calibration nodel in various large transonic wind tunnels [OHEBA, TP NO. 1978-22] A78-39579 CAHABD COHFIGUBATIOBS High angle canard missile test in the Anes 11-foot transonic vind tnnnel [NASA-CB-2993] H78-25057 CABBOH FIBBB BEIHFOHCED FUSTICS Sailplanes of carbon-fiber construction A78-38800 Heavily leaded carbon-fiber-reinforced-plastic primary structure with the Tornado taileron as an example A78-38810 Material selection for the Tornado taileron A78-38811 CABBON FIBEBS Carbon fiber study [NASA-TM-79qU9] H78-2U292 CABGO AIBCBAPT Survey of air cargo forecasting technigues [NASA-CB-1S5329] N78-25068 Preliminary analysis of hut and spoke air freight distribution system [NASA-TB-72656] B78-25069 Preliminary study of a large span-distnbuted-load flying-wing cargo airplane concept CNASA-TP-1158] N78-25079 Doctrine versus capabilities: A project manager's dilemma with the CH-U7 helicopter [AD-A052376] H78-25970 CASCADE FLO! Application of the integral-transformation nethod to three-dimensional unsteady problems of the theory of cascades A78-36366 Calculation of transonic flow through a turbine cascade by the time-step method A78-382U8 Investigations of the influence of the profile thickness of the compressible plane flow through compressor cascades [NASA-TH-75277] H78-2U08U CATALYTIC ACTIVITY Performance evaluation of a catalytic partial oridation hydrogen generator using turbine engine fuels CAD-AOH7355] B78-24380 CATHODE BAT TUBES CBT update for airborne displays 178-371)90 Perspective radar display system: TV-like presentation on CBT provides higher lateral position and lateral motion sensitivity than a PPI [AD-A052302] H78-2H«18 CEBTIPICATIOB The certification of light aircraft A78-36280 CH-Q7 HELICOPTE8 Doctrine versus capabilities: A project manager's dilemma with the CH-17 helicopter [AD-A052376] B78-25970 CBABTS Jeppesen charting for area navigation A78-3645II CIVIL AVIATIOB Expansion potential for the local service air carrier A78-37539 Application Of modern methods in civil aircraft construction A78-38808 Precision positional data of general aviation air traffic in terminal air space [NASA-BP-1020] B78-25018 CtEABAICSS Acoustics and performance of high-speed, unequally spaced fan rotors [BAL-TB-526] H78-25090 CLIHBIB6 FLIGHT Compressible flow about helicopter rotors A78-36917 CLOUD SEEDING Preliminary experience with the use of the Yak-DO aircraft in studies of cloud physics and artificial modifications A78-36183 CLUTCHES Advanced overrunning clutch technology for use in helicopters [AD-A052635] N78-20b57 CLOTTEB The effect of correlated missed detections, correlated false alarms and interclutter visibility on the performance of an automated radar tracking system A78-37485 COAL LIQBEFACTIOS Progress on coal-derived fuels for aviation systems [NASA-TB-78696] N78-255U5 COBALT ALLOYS Cobalt-base alloys produced by powder metallurgy for compressor and turbine disks [OSBBA, TP BO. 1978-7] A78-39582 COCKPITS The design of future cockpits for high performance fighter aircraft A78-36116 COLLISIOB AVOIDANCE Concerning the logical comparison of ATC separation standard assessment models A78-36D5S Fully-automated, pilot-monitored air traffic control A78-37155 Electronic aircraft collision avoidance system Russian book A78-37603 A relative motion analysis of horizontal collision avoidance A78-3967Q COLOB PBOTOGBAPHY Color displays for airborne weather radar J78-36980 COHBUSTIOH CBAIBEBS Analysis of spray combustion in a research gas turbine combustor A78-37297 Review of flashback reported in prevaporizing/premixing combustors A78-37772 Combustion in gas turbine engines - A review of OHEBA recent works [ONEBA, TP NO. 1978-25] A78-39580 Design and preliminary results of a semitranspiration cooled (lamilloy) liner for a high-pressure high-temperature combustor [BASS-TH-7887H] N78-2U138 Fundamental aspects of the aerodynamics of turbojet engine combustors [NASA-TB-75287] 878-29142 A high-pressure, sector-shaped model combustor test facility for development of turbofan engines [NAL-TB-517] H78-25093 YF 102 in-duct combustor noise measurement, volume 1 [NASA-CB-135U04-VOL-1] B78-25827 YF 102 in-duct combustor noise measurement, volume 3 [HASA-CB-135l|Ot-VOL-3] B78-25829 COHBDSTIOH EFFICIENCY Combustion in gas turbine engines - A review of OBEBA recent works [ONEBA, TP NO. 1978-25] A78-39580 COHBUSTIOB PBODOCTS Characteristics and combustion of future hydrocarbon fuels aircraft fuels [NASA-TH-78865] N78-2H370 COSHBBCIAL AIBCBAFT Ergonomics in commercial aircraft landing A78-36621 A rising sun in aircraft Japanese commercial aircraft development programs f78-3852« Energy savings. An aircraft constructor's viewpoint [AAAF-NT-77-2U] N78-21127 COSSOBICATIOB EQ01PBBBT Test operations procedures physical characteristics aviation material [AD-A053196] N78-25086 A-7 COBBONIC1TION HBTWOBKS SUBJECT INDEX COBBONIC1TIOS NETiOBKS Maritime satellite communications - Where we are and where we're going [AAS 77-257] 478-36721 COBHUNICATION SATELLITES Maritime satellite communications - where we are and where we're going [AAS 77-257] A78-36721 COBP1ES VABIABIES Factorization methods in hydroaeronechanics Russian book A78-37887 COBPONENT BELIABILITY Case of damage involving aircraft and helicopter components of light metal A78-369«1 The damage sum in fatigue of structure components aircraft structures [ICAF-1032] N78-25i»SU COBPOSITB^BATEBIALS New technologies for aircraft structures A78-38803 Environmental effects on composites for aircraft [SASA-TH-78716] N78-25135 COBPOSITE STBOCTUBBS An experimental study to determine the reduction ill ultimate bending moment of a composite plate due to' an internal delamination [BD-A052662] N78-25166 COHPBESSIBLE PIOS Compressible flow about helicopter rotors A78-369U7 Investigations of the influence of the profile thickness of the compressible plane flow through compressor cascades [NASA-TM-75277] N78-2U08I1 The development and application of a simple method for determining unsteady airloads in subsonic compressible flow [AD-A052I)17] N78-2U096 COBPRESSOH BLADES Investigations of the influence of the profile thickness of the compressible plane flow through compressor cascades [NASA-TM-75277] N78-21081 COBPBESSOB EFFICIENCY Loss prediction in axial compressors - A bibliographic study A78-38892 COBPBESSOB BOTOBS Acoustics and performance of high-speed, unequally spaced fan rotors rSPL-TR-526] S78-2509U COHPBESSOBS Cobalt-base alloys produced by powder metallurgy for compressor and turbine disks [ONERA, IP NO. 1978-7] A78-39582 COBPDTEB PBOGBABBING Design and construction of a flight monitor and data recorder component selection and software design [AD-A052105] N78-24135 COHPDTEB PBOGBSBS Ose of structural analysis programs for calculating states of stress in helicopter rotor elements A78-38807 Simplified input for certain aerodynamic nose configurations to the G r u m m a n quick-geometry system. A KSIKNOSE user's manual [ A D - A 0 5 1 U 2 5 ] N78-2H089 nse of simulation techniques in the problem of air traffic control [QtRD-CALC-ELETT-21 ] N78-21111 Atmospheric-absorption adjustment procedure for aircraft flyover noise measurements computer program [AD-A051700] N78-2<4899 Naval aircraft operating and support cost model - Fiscal Year 1976 revision [AD-A053180] N78-25051 Paneling techniques for use with the VOBLAX computer program rNASA-CR-14536«] N78-2505I4 Computer model for refinery operations with emphasis on jet fuel production. Volume 3: Detailed systems and programming documentation fNASA-CR-135335] N78-25235 COBPDTEE SYSTEBS PROGHAHS Reduction of transient gas turbine test data using a hybrid computer A78-38782 Testing of the YC-1U flight control system software [AIAA PiPEB 77-1077] A78-39183 Aerospace computer systems. Part 1: Avionics applications, volume 2. A bibliography with abstracts [HTIS/PS-78/0289] N78-25787 COBPOTER TECHNIQUES Computer-aided holographic vibration analysis for vectorial displacements of fcladed disks A78-37183 Formulas for takeoff performance P3-A, B and C airplanes [AD-A05235U] N78-21H2M COHPOTEBIZED DESIGN Hybrid computer models as an aid in design of gas turbine control systems for helicopters A78-38783 On the optimization of discrete structures with aeroelastic constraints A78-3913S A study of commuter airplane design optimization [NASA-CR-157210] N78-25078 COHPDTERIZED SIMULATION Hybrid computer models as an aid in design of gas turbine control systems for helicopters A78-38783 Time delay measurements for flight simulators A78-38788 Simulation replay - Implementation and flight simulation applications A78-38789 Dse of simulation techniques in the problem of air traffic control [QtJlD-CALC-BLSTT-21] H78-2U111 Modeling of the OH-1B tail boom for analysis by the NASTRAN computer program [AD-A052303] N78-25081 CONCORDE AIBCBAFT SST flight planning and navigation - The first year's experience A78-37154 COHFEBEHCBS Problems of the theory of strength related to aircraft construction and civil engineering; Structural Mechanics Heeting, Ottobrunn, West Germany, June 1, 2, 1977, Lectures and Discussion Contributions A78-38802 Powered-Lift Aerodynamics and Acoustics conferences [NASA-SP-Q06] N78-2IIOI16 CONTRACT BABAGEBENT On setting avionic subsystem unit production cost goals contract management and procurement policy [AD-A051337] N78-21133 CONTROL SURFACES Nonlinear theory of a bearing surface of arbitrary extent [AD-A051385] N78-24090 Heavy lift helicopters. Advanced Technology component program: Hub and upper controls [AD-A0513 A78-38978 TOBHEBDABL, 3. B. General aviation avionics equipment maintenance [HASA-CB-1153112] N78-2Q132 TOPPIHG, B. F. Studies on transonic turbine with film-cooled blades [AD-A052»23] H78-2II149 TBOOT, 1. B. Design and preliminary results of a semitranspiration cooled (Lamilloy) liner for a high-pressure high-temperature combustor [NASA-TH-788711] H78-21138 TSIBE1, T. S. Study of magnetic noise in the Ka-26 helicopter A78-39188 TOKHAH, B. G. Computer model for refinery operations with emphasis on jet fuel production, volume 3: Detailed systems and programming documentation [BASA-CB-135335] N78-25235 TOBKOiSKI, L. Characteristics of flow past fuselages and wing-faselage systems of gliders A78-36203 u OVSEOV, V. S. Aircraft radar systems A78-37873 VACBAL, J. D. Application of laminar flow control to large subsonic military transport airplanes IAD-A052H22] N78-21098 VASLEEOBEH, B. P. Heat treatment studies of aluminum alloy type 7050 forgings. The effect of heat treatment on a variety of engineering properties [m.R-TB-76008-0] B78-25199 VAHBYK, A. J. Performance tests and design modifications of a Rankel type rotary combustion automobile engine in order to determine its suitability for aircraft application [CSIB-BE-1521] N78-25095 VATSDBO, A. E. Study of magnetic noise in the Ka-26 helicopter A78-39188 VADCBEBET, X. Prediction of the aerodynamic characteristics of an aircraft on the basis of the comparison of results for a calibration model in various large transonic wind tunnels [OHEBA, TP HO. 1978-22] A78-39579 VAOGBH, B. L. An atomic fluorescence system using a continuum source for the rapid determination of wear metals in jet engine lubricating oils [AD-A052721] N78-2H320 VEBBDBI, B. S. Survey of air cargo forecasting techniques [HASA-CB-11153293 1178-25068 VOGIEB, B. P. Comparison of aerodynamic theory and experiment for jet-flap wings N78-2U052 VOIT, F. U. Preliminary experience with the use of the Yak-10 aircraft in studies of cloud physics and artificial modifications A78-36083 B-11 VOLOBOET, 7. PERSONAL ADTBOB INDEX VOLOBOEV, V. The technical concepts behind the T1-62H /8/ landing gear A78-36622 80, J. 3. Vibrations of a helicopter rotor blade using finite element unconstrained variational formulations w W1KAI, I. Study on problems of terminal site location A78-36323 WALDEE, A. Cobalt-base alloys produced by powder metallurgy for compressor and turbine disks [ONEBA, TP NO. 1978-7] A78-39582 REAB, J. D. Design and preliminary results of a semitranspiration cooled (Lamilloy) liner for a high-pressure high-temperature combustor [NASA-TH-78874] H78-24138 WEIHEB, D. C. On setting avionic subsystem unit production cost goals [AD-A051337] N78-2U133 VEILS, W. I. Verification of DABS sensor surveillance performance (ATCEBS mode) at typical ASE sites throughout CONOS [AD-A051128] 178-24105 WESTON, B. P. Bound jet in a cross flow - Influence of injection angle on vortex properties A78-377U4 8HALBH, J. J. Assessment procedure application utilizing DBF transistor BF pulse susceptibility data A78-39101 WBITBBEAD, A. H., JB. Preliminary analysis of hub and spoke air freight distribution system [NASA-TM-72656] N78-25069 WIDN1LL, S. E, The effect of tip vortex structure on helicopter noise due to blade/vortex interaction [NASA-CB-152150] H78-25832 WIBSBHAHF, W. Flight-testing of a continuous laser remote sensing system A78-39632 BILLIABS, H. 1. Non-destructive method for applying and removing instrumentation on helicopter rotor blades [NASA-CASE-LAB-11201-1 ] 178-21(515 BILLIABS, B. t. Environmental reguirements for simulated helicoptfir/VTOL operations from small ships and carriers [AD-A053078] N78-2508U WILLIS, C. H. Acoustic-loads research for powered-lift configurations N78-2U073 WILSON, C. A. YF 102 in-duct combustor noise measurement, volume 1 [NASA-CH-135404-VOL-1] N78-25827 YF 102 in-i3uct combustor noise measurement, volume 3 tNASA-CE~13540I|-VOL-3] N78-25829 WITCOFSKI, B. D. Progress on coal-derived fuels for aviation systems [BASA-TB-78696] N78-255U5 BOEEBDLE, B. Ose of structural analysis programs for calculating states of stress in helicopter rotor elements A78-38807 WOLF, I. L. The effect of tip vortex structure on helicopter noise due to blade/vortex'interaction [NASA-CB-152150] N78-25832 WOODWABD, B. P. Acoustic evaluation of a novel swept-rotor fan [NASA-TM-78878] N78-21897 BOOBEB, C. W. Environmental reguirements for simulated helicopter/VTOL operations from small ships and carriers [AD-A053078] N78-2508t BOBTBiBN, F. X. Drag reduction for gliders [SASA-TJt-75293] H78-21116 [AD-A052670] WOBTZ, 3. E. CBT update N78-2U125 A78-371490 YABAGISHI, H. New model VOB/DBE A78-37216 YAHABOTO, K. Azimuthal decomposition of the power spectral density of net noise A78-37532 YEGHIAYAH, B. F. Modeling of the DB-1B tail boom for analysis by the NASTBAN computer program [AD-A052303] N78-25081 YIP, L. P. Comparison of aerodynamic theory and experiment for let-flap wings N78-2II052 Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds [NASA-TP-1215] N78-25060 YONEZAWA, K. Evaluation of geometric performance of global positioning system A78-37987 YOOHG, C. A theoretical study of the effect of blade ice accretion on the power-off landing capability of a Vessel helicopter A78-369U8 ZBAVOBONKOV, V. P. Aircraft radar systems A78-37873 ZHILIH, 10. V. Experimental investigation of gasdynamic processes at sudden start-up of a supersonic nozzle A78-38611 B-12 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 100) SEPTEMBER 1978 Typical Contract Number Index Listing HASB-2483 H78-11061 1 CONTRACT NASA ACCESSION NUMBER NUMBER Listings in this index are arranged alphanumerically by contract number Under each contract number the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first The accession number denotes the number by which the citation is identified in either the lAAoi STARseclion PF PBOJ. 1369 N78-25082 ;F PROJ. 1476 N78-211098 AF PEOJ. 3018 N78-25239 AF PEOJ. 3066 N78-21141 B78-21145 AF PEOJ. 3115 N78-25096 AF PEOO. 7381 N78-24344 AF-AFOSB-76-2936 A78-37772 iF-AFOSB-3501-78 H78-24150 AEO PBOJ. V33A-A8A H78-24089 DA PBOJ. 1F1-63204-DB-38 H78-24118 H78-24119 DA PROJ. 1F2-62209-AH-76 B78-24126 N78-24158 F78-245S7 DA PROJ. 1L1-61102-AH-45 N78-24125 DAAD05-76-C-0763 B78-25081 DAAG29-76-G-0241 B78-24096 DAAG29-77-G-0067 N78-24094 DAAJ01-71-C-0840 N78-2H122 DAAJ02-72-C-0082 N78-211118 N78-2U119 DAAJ02-71-C-0028 N78-2U557 DAAJ02-75-C-0053 N78-2U126 DA&J02-76-C-00«2 H78-21158 DAHCOU-7a-G-0 /18H N78-2«096 DAHC15-73-C-0200 H78-21133 B78-2I1156 DOT-FA72BAI-261 H78-21105 DOT-FA76»AI-59a 178-211385 DOT-FA77-WAI-032 A78-3967P DOT-TSC-682 F78-21099 EPA-E-802925-02-2 A78-37297 ET-76-C-02-3077 N7 8-24808 FAA PBOJ. 031-211-012 N78-2U105 FAA PBOJ. 072-121-500 S78-21153 FAA PBOJ. 216-102-100 M78-21151 F19628-78-C-0002 A78-396714 H78-21105 F29601-76-C-0064 A78-37121 F33615-71-C-20 S78-25096 F33615-71-C-2036 B78-25239 F33615-71-C-5089 N78-21311 F33615-75-C-2053 B78-21111 H78-21115 F33615-75-C-3152 H78-25082 F33615-76-C-3035 H78-21098 F33615-76-C-3066 H78-25087 F33615-76-C-3073 H78-25085 F33657-72-C-0829 N78-21900 F19620-77-C-0055 A78-39135 HIPB-FT11557-601611 B78-21380 NASH-2790 S78-21085 F78-21112 NASW-2791 S78-21081 K78-21116 NAS1-13500 H78-25051 NAS1-13870 H78-24061 K78-21062 BAS1-13871 N78-24057 NAS1-11192 N78-21903 HAS1-11686 K78-2U013 BAS1-11795 H78-25985 BAS1-1U908 178-25068 BAS1-14939 B78-21132 SAS1-11973 B78-25831 BAS2-8832 B78-25359 BAS2-9211 878-25057 BAS2-9418 B78-21117 SAS3-18538 B78-25080 BAS3-20052 N78-25827 N78-25829 SAS3-20620 B78-25235 BAS7-100 A78-37743 BAS9-11952 B78-25986 B78-25987 BCSZ-OE745-720 B78-25979 BGL-05-020-243 A78-39135 NG1-10-005-127 A78-377IHI BGL-39-009-172 B78-25092 BGB-33-016-167 B78-21808 BGB-33-016-201 B78-21808 BSG-1107 H78-25056 HSG-1139 B78-21059 BSG-1169 B78-2S966 BSG-1300 B78-25056 FSG-2010 478-38766 NSG-2039 A78-36596 BSG-2112 H78-25832 BSG-2145 B78-25078 B00014-76-C-0253 F78-24119 B00011-77-C-0032 H78-24808 B00014-77-C-0180 B78-25051 H00014-77-C-0161 B78-24121 B00019-76-C-0675 B78-25210 H00019-77-C-0309 F78-25050 B00110-75-C-0034 B78-25097 S78-25098 N00140-76-C-0383 B78-24556 B1-77-5660-1 N78-24899 505-02-13-14 B78-25135 505-03-12 B78-25827 B78-25829 505-06-34 S78-25055 505-07-33-04 B78-25101 505-09-13-11 S78-24903 505-11-13-04 B78-25060 505-11-23-03 B78-25058 505-11-33-00 B78-25059 515-51-11-01 B78-25071 516-50-23-01 B78-25054 H78-25079 B78-25545 712-73-01-14 B78-24078 B78-24079 B78-24080 767-73-01-04 B78-24077 791-40-13-01 B78-25069 f C-1 1 Report No. NASA-SP-7037 (100) 2 Government Accession No 3 Recipient's Catalog No 4 Title and Subtitle AERONAUTICAL ENGINEERING A Continuing Bibliography (Supplement 100) 5 Report Date September 1978 6. Performing Organization Code 7 Author(s) 8 Performing Organization Report No. 10 Work Unit No 9 Performing Organization Name and Address National Aeronautics and Space Administration Washington, D. C. 205^ 6 11 Contract or Grant No 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 295 reports, articles, and other documents introduced into the NASA scientific and technical information system in August 1978. 17 Key Words (Suggested by Author(s)) Aerodynamics Aeronautical Engineering Aeronautics Bibliography 18 Distribution Statement Unclass i f ied - Unlimited 19 Security Classif (of this report) Unclass if led 20 Security Classif (of this page) Unclass i f ied 21. No of Pages 100 22 Price* $^.75 HC For sale by the National Technical I nformation Service, Springfield, Virginia 22161 NASA-Langley, 1978 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organizations luted below Each library it prepared to furnish the public such sen/ices as reference assistance, interhbrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention MASSACHUSETTS Massachusetts Institute of Technology. Cambridge CALIFORNIA University of California. Berkeley COLORADO University of Colorado. Boulder DISTRICT OF COLUMBIA Library of Congress GEORGIA Georgia Institute of Technology, Atlanta ILLINOIS The John Crerar Library. Chicago MISSOURI Linda Hall Library. Kansas City NEW YORK Columbia University. New York PENNSYLVANIA Carnegie Library of Pittsburgh WASHINGTON University of Washington. Seattle NASA publications (those indicated by an "*" following the accession number) are also received by the following public and free libraries CALIFORNIA Los Angeles Public Library San Diego Public Library COLORADO Denver Public Library CONNECTICUT Hartford Public Library MARYLAND Enoch Pratt Free Library. Baltimore MASSACHUSETTS Boston Public Library MICHIGAN Detroit Public Library MINNESOTA Minneapolis Public Library MISSOURI Kansas City Public Library St Louis Public Library NEW JERSEY Trenton Public Library NEW YORK Brooklyn Public Library Buffalo and Erie County Public Library Rochester Public Library New York Public Library OHIO Akron Public Library Cincinnati Public Library Cleveland Public Library Dayton Public Library Toledo Public Library OKLAHOMA Oklahoma County Libraries. 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England By virtue of arrangements other than with NASA, the British Library Lending Division also has available many of the non-NASA publications cited in STAR European requesters may purchase facsimile copy or microfiche of NASA and NASA-sponsored documents, those identified by both the symbols #" and "*". from ESRO/ELDO Space Documentation Service, European Space Research Organization, 114, av Charles de Gaulle 92-Neuilly-sur-Seme. France National Aeronautics and Space Administration Washington, D.C. 20546 Official Business Penalty for Private Use, $300 THIRD-CLASS BULK RATE Postage and Fees Paid National Aeronautics and Space Administration NASA-451 NASA POSTMASTER: If Undehverable (Section 158Postal Manual) Do Not Return NASA CONTINUING BIBLIOGRAPHY SERIES NUMBER NASA SP-7011 NASA SP-7037 NASA SP-7039 NASA SP-7041 NASA SP-7043 NASA SP-7500 TITLE AEROSPACE MEDICINE AND BIOLOGY Aviation medicine, space medicine, and space biology AERONAUTICAL ENGINEERING Engineering, design, and operation of aircraft and aircraft components NASA PATENT ABSTRACTS BIBLIOGRAPHY NASA patents and applications for patent EARTH RESOURCES Remote sensing of earth resources by aircraft and spacecraft ENERGY Energy sources, solar energy, energy conversion, transport, and storage MANAGEMENT Program, contract, and personnel management, and management techniques FREQUENCY Monthly Monthly Semiannually Quarterly Quarterly Annually Details on the'availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N Washington, D.C. 20546

Aeronautical engineering: A continuing bibliography with indexes, supplement 100

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