NASA SP-7037 (89) AERONAUTICAL ENGINEERING A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 89 NOVEMBER 1977 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION https://ntrs.nasa.gov/search.jsp?R=19780008043 2020-03-22T05:30:01+00:00Z ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges: STAR(N-10000 Series) N77-28060 N77-30064 IAA (A-10000 Series) A77-40471 A77-44313 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 (89) AERONAUTICAL ENGINEERING A Special Bibliography Supplement 89 A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in October 1977 in • Scientific and Technical Aerospace Reports (STAR) • Internationa/ Aerospace Abstracts f/AA) Scientific and Technical Information Office NOVEMBhR 1977 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Wafhington, D C. 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 tha t t i m e , m o n t h l y supplements have been issued This supplement to Aeronautical Engineering -- A Special Bibliography (NASA SP-7037) lists 538 reports, journal articles, and other documents originally announced in October 1977 in Scienlijic and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (I A A) The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems It also incjudes 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 (A77-10000 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 are available at $5 00 per document up to a maximum of 20 pages The charge for each additional page is 25 cents Microfiche are available at the rate of $1 50 per microfiche for documents identified by the § symbol following the accession number A number of publications, because of their special characteristics, are available only for reference in the AIAA Technical Information Service Library Minimum airmail postage to foreign countries is $1 00 Please refer to the accession number, eg. (A77-10026). when requesting publications STAR ENTRIES (N77-10000 Series) One or more sources from which a document announced m 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 vn of the current issue of STAR Microfiche'" is available regardless of age for those accessions followed by a § 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 1 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 U S-Patent-Appl-SN number Non-NASA publications (no asterisk) should be ordered by the AD, PB, or other report number shown on the last line of the citation not by the N accession number It is also advisable to cite the title and other bibliographic identification Avail SOD (or GPO) Sold by the Superintendent of Documents, U S Government Printing Office, in hard copy The current price and order number are given following the availability line (NTIS will fill microfiche requests, at the standard $3 00 price for those documents identified by a § symbol) Avail NASA Public Document Rooms Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration. 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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. Ann 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 0 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 NASA Scientific and Technical Information Facility PO Box 8757 B W I Airport. 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Colorado 80225 Zentralstelle fur Luftfahrtdoku- mentation und -Information 8 Munchen 86 Postfach 880 Federal Republic of Germany TABLE OF CONTENTS IAA Entries 441 STAR Entries 471 Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT NASA ACCESSION NUMBER i TITLE. t*N77-10048*# Lockheed Missiles and Space Co Sunnyvale Calif Research and Development Div CIVIL USES OF REMOTELY PILOTED AIRCRAFT Summary Report Jon R Aderhold G Gordon and George W Scon Jul 1976 •«- 28 p ref AUTHORS. CONTRACT OR GRANT. REPORT NUMBERS. F Avail NTIS-*- P». (Contract NAS2-8935) ^(NASA-CR-137895 LMSC-D057322) H C A03/MF A 0 1 CSCL Q I C < — . The economic, technical and environmental implications of remotely piloted vehicles (RVP) are examined The time frame is 1980-85 Representative uses are selected, detailed functional and performance requirements are derived for RPV systems and conceptual system designs are devised Total system cost comparisons are made with non-RPV alternatives The potential market demand for RPV systems is estimated Environmental and safety requirements are examined and Jegal and regulatory concerns are identified A potential demand for 2.000-11.000 RVP systems is estimated Typical cost savings of 25 to 35% compared to non-RPV alternatives are determined There appear to be no environmental problems, and the safety issue appears manageable Author .AVAILABLE ON MICROFICHE -CORPORATE SOURCE .PUBLICATION DATE .AVAILABILITY SOURCE . COSATI CODE TYPICAL CITATION AND ABSTRACT FROM IAA NASA SPONSORED. AIAA ACCESSION NUMBER J TITLE. PUBLICATION DATE_ H A77-10214 * # Resizing procedure for structures under com- ,-»• bined mechanical and thermal loading H M AdelmarT^NASA, Langley Research Center, Hampton, Va ) and R Narayanaswami (Old Dominion University, Norfglk, Va ) AIAA Journal, vol 14, r»0ct 1976, p 1484 1486 6 refs L The fully-stressed design (FSD) appears to be the most widely used approach for sizing of flight structures under strength and minimum-gage constraints Almost all of the experience with FSD has been with structures primarily under mechanical loading as opposed to thermal loading In this method the structural sizes are iterated with the step size, depending on the ratio of the total stress to the allowable stress In this paper, the thermal fully stressed design (TFSD) procedure developed for problems involving substantial thermal stress is extended to biaxial stress members using a Von Mises failure criterion The TFSD resizing procedure for umaxial stress is restated and the new procedure for biaxial stress members is developed Results are presented for an application of the two procedures to size a simplified wing structure S D • AVAILABLE ON MICROFICHE -AUTHORS AUTHOR'S AFFILIATION VIII AERONAUTICAL ENGINEERING A Special Bibliography (Suppl. 89) NOVEMBER 1977 tube display and a primary recorder using an electron beam to record on 5-inch film J M B IAA ENTRIES A77-40638 Monitoring Concorde emissions. H Segal (FAA, Office of Environmental Quality, Washington, D C ) (Air Pollution Control Association, Annual Meeting, 70th, Toronto, Canada, June 20-24, 1977, Paper 77-413) Air Pollution Control Association, Journal, vol 27, July 1977, p 623-630 10refs The low-altitude emission plume of Concorde was investigated to determine any adverse effects on air qual'ty at Dulles Airport and in the nearby Sterling Park Community resulting from its operation The change in pollutant concentrations from a single aircraft as it started, taxied, and took off was measured by six mobile air quality control stations and two vertical towers using continuously recording instruments coupled with high-speed chart recorders Preliminary results show that the average CO concentration of Concorde emissions is 1 7 times greater than that of any other aircraft monitored However, CO emissions from Concorde are undetectable at 2000 ft from the taxiing aircraft The single event emissions of Concorde contribute less than 0 1 ppm of CO to ambient air concentrations at locations as close as 200 ft from a taxiing aircraft Tower measurements show that the hot emission plume tends to lie close to the ground C K D A77-40643 Transmissometer measurement of particulate emissions from a jet engine test facility D P Y Chang (California, University, Davis, Calif, USAF, Regional Environmental Health Laboratory, McClellan AFB, Calif) and B C Grems (USAF, Civil Engineering Center, Tyndall AFB, Fla) Air Pollution Control Association, Journal, vol 27, July 1977, p 673-675 An optical transmissometer was assessed as a possible means of monitoring potential mass emissions in turbojet test facilities Simultaneous cascade impactor samples and opacity measurements were used to determine the relationship between mass concentration and plume opacity A correlation coefficient of 0 87 was found in a least squares regression analysis of total mass concentration on optical density A better correlation coefficient was obtained when particles with diameters greater than 3 microns were excluded However, a successful correlation of total mass emissions rate with opacity is believed to be unlikely, even for smaller engines C K 0 A77-40665 Real time aerial reconnaissance using the return-beam vidicon M J Cantella and R J Gildea RCA Engineer, vol 22, Apr -May 1977, p 30-35 7 refs USAF-supported research Testing has established the return beam vidicon (RBV) as a feasible real-time reconnaissance sensor under a variety of flight profiles and visibility conditions, and especially in low-contrast conditions Advantages of the RBV include one foot resolution at 10,000 feet, 'snapshot' operation, in which exposure, readout, and erasure time intervals are segregated, slow-scan readout, electronic zoom, and automatic black level correction, allowing the camera to function in poor visibility The reconnaissance system consists of an airborne pod, mounted on an RF-4C aircraft, and a ground station to monitor and record data The ground station includes a cathode ray A77-40700 * ;/ Computation of viscous transonic flow about a lifting airfoil L Walitt (Numerical Continuum Mechanics, Inc, Woodland Hills, Calif), L S King (NASA, Ames Research Center, Moffett Field, Calif), and C Y Liu (California, University, Los Angeles, Calif) American Institute of Aeronautics and Astronautics, Fluid and Plasmadynamics Conference, 10th, Albuquerque, N Mex , June 27-29, 1977, Paper 77-679 11 p 33 refs The Reynolds averaged Navier-Stokes equations are solved numerically for the viscous transonic flow about a stationary NACA 64A010 airfoil in free air This paper presents descriptions of the numerical method, turbulence models employed, and boundary conditions appropriate to simulation of free-air flight Computed results are presented for the airfoil at a free-stream Mach number of 0 8, angles of attack of 0 and 2 deg, and a Reynolds number based on a chord of 4 x 10 to the 6th For the lifting case, unsteady periodic motion was calculated along the aft portion of the airfoil and in its wake Recent experimental results obtained by Johnson indicate periodicity aft of the shock closely approximates the computed frequency, but the amplitude of the disturbances was significantly less than the calculated amplitude (Author) A77-40703 I; Acoustic properties of pneumatic vortex sprayers (Akusticheskie svoistva vikhrevykh pnevmaticheskikh for- sunok) A N Belousov, lu A Knysh, and S V Lukachev Aviatsionnaia Tekhnika, vol 20, no 1, 1977, p 17-22 7 refs In Russian Experiments have shown that pneumatic vortex sprayers can be used to generate intense oscillations of velocity and pressure in the acoustic frequency range The frequency and amplitude of oscilla- tions can be selected by varying the geometrical dimensions of the sprayers and their mode of operation It is shown that the level of sound pressure produced is sufficient to intensify mixing and combustion processes in the combustion chambers of gas turbine engines BJ A77-40708 ~ Certain problems associated with the applica- tion of the transpiration cooling of gas turbine engine blades (Nekotorye problemy primeneniia ponstogo okhlazhdenna lopatok GTD) V M Epifanov Aviatsionnaia Tekhnika, vol 20, no 1,1977, p 4247 12 refs In Russian Attention is given to problems associated with the implementa- tion of the transpiration cooling of turbine blades for cases of high temperatures of working fluid before the turbine Emphasis is on the augmentation of energy loss due to coolant injection, contamination of the pores by foreign particles carried in by the coolant and the working fluid, and the oxidation of the porous material and its mechanical properties B J A77-40711 # The effect of the structural features of a combustion chamber on the emission of toxic compounds (Vluanie konstruktivnykh osobennostei kamery sgoranna na vykhod toksi- cheskikh soedmenu) A V Ivliev, lu A Knysh, and V P Lukachev Aviatsionnaia Tekhnika, vol 20, no 1, 1977, p 60-65 5 refs In Russian Experiments were conducted investigating the influence of modifications in combustion chambers of gas turbine engines on completeness of combustion and the emission of toxic gases The 441 A77-40712 characteristics of the toxic exhaust gases of the NK-12CT gas turbine engine with two types of fuel sprayers were determined for the case of methane combustion It is shown that by replacing fluidic-gas sprayers with centrifugal sprayers, it is possible to reduce the emission of nitrogen oxides by 40-50% B J A77-40712 ii Analytical construction of the throttle charac- teristic of a gas turbine engine (K analiticheskomu postroennu drossel'noi kharaktenstiki GTD) lu V Kozhevnikov Aviatsionnaia Tekhnika, vol 20, no 1,1977, p 66-71 In Russian The problem of an analytical representation of the throttle characteristic of a gas turbine engine is examined with consideration of statistical data on engine parameters An optimal solution is obtained to the problem in the context of linear estimation theory The optimization criterion is a minimum estimate-error dispersion in an arbitrary regime with respect to the totality of engines of a given series B J A77-40715 " Statistical modeling of the optimal adjustment of the parameters of a gas turbine engine (Statisticheskoe modeliro- vanie optimal'noi otladki parametrov GTD) lu V Meluzov Avia- tsionnaia Tekhnika, vol 20, no 1, 1977, p 83 88 5 refs In Russian This paper examines digital statistical simulation of gas turbine engine tests in an investigation of the efficiency of adaptive algorithms of optimal estimation and correction Particular attention is paid to the identification of the dependence of engine character- istics on regulating elements and to the determination of the number of requited corrections of engine characteristics as a function of the amount of a priori information on the distribution of engine parameters B J A77-40721 # Structural-logic diagram for ensuring high-rate products (Strukturno-logicheskaia skhema obespechemia pokazatelei kachestva izdelu) A S Shevelev Aviatsionnaia Tekhnika, vol 20, no 1,1977,p 117-124 In Russian The paper deals with the application of automation and computers to the development of technological processes in the aircraft industry Specifically, a structural-logic diagram, using which a functional connection can be established between design pa rameters and technological factors, is proposed as a means of obtaining reliable initial information for use in the development of automated and computer aided technological processes V P • A77-40725 # Study of the inflow process to an air scoop with a screen, using an EGDA integrator (Issledovanie protsessa vtekanna vozdushnogo potoka v vozdukhozabormk s ekranom metodom EGDA) I A Gnshin, V F Ivannikov, and E 0 Nesterov Aviatsionnaia Tekhnika, vol 20, no 1, 1977, p 134137 In Russian Using the EGDA 9/60 integrator, patterns of flows to a plane air scoop were obtained on electrically conducting paper at various distances between the scoop's axis and a screen The patterns are represented in the form of a grid composed of lines of flow and equipotentials The velocities at the grid nodes are determined by a method proposed by Fil'chakov and Panchishm (1961) The effect of injection of foreign matter is studied by analyzing the flow field in front of the scoop Means of reducing this effect are examined V P A77-40726 ff Selection of an atomizer and its modes of operation for the removal of ice deposits, frost and frozen snow from aircraft surfaces (Vybor raspylitelia i rezhimov ego raboty dha udalenna ledianykh otlozhenn, meia i primerzshego snega s poverkh- nostei samoleta) M la Moroshkin, V N Smolin, lu A Skobel'tsyn, and A F Komlev Aviatsionnaia Tekhnika, vol 20, no 1, 1977, p 137-140 In Russian A77-40830 * i Unsteady linearized transonic flow analysis for slender bodies D D Liu (Northrop Corp , Hawthorne, Calif), M F Platzer (U S Naval Postgraduate School, Monterey, Calif), and S Y Ruo (Lockheed-Georgia Co, Marietta, Ga ) AIAA Journal, vol 15, July 1977, p 966-973 29 refs Research supported by the Lockheed-Georgia Independent Research Program and Northrop Independent Research Program, Contract No NAS8-20082 An unsteady linearized formulation based on Oswatitsch- Keune's parabolic method is developed to analyze transonic flow past oscillating slender bodies In contrast to the widely used integral transform method, it is shown that all solutions can be derived by a simpler method directly in the physical plane By various expansion procedures, low-frequency solutions then are derived according to two clearly defined frequency ranges Adams-Sears' iteration is employed to account for the second-order effects Stability deriva- tives are compared with available theories and data It is found that the derivatives depend more sensitively on thickness than on the reduced frequency Finally, a critical assessment of the present method is given (Author) A77-40834 * tt Expansion tunnel performance with and with- out an electromagnetically opened tertiary diaphragm C G Miller (NASA, Langley Research Center, Entry Gas Dynamics Group, Hampton, Va) AIAA Journal, vol 15, July 1977, p 1045-1047 A study was conducted to examine the effect of synchroniza tion of an electromagnetically opened tertiary diaphragm with flow arrival at the diaphragm on the pilot pressure measured at the test section of an expansion tunnel The effect of tertiary diaphragm pressure ratio (ratio of initial nozzle pressure to quiescent accelera- tion section piessure) on the pilot pressure time history is also determined The inadequacy of a pressure transducer protection arrangement used in previous expansion tube and expansion tunnel tests was revealed B J A77-40901 # Hot gas dynalpy test bench for model testing of jet or turbofan outlet systems J Coste and P Broussaud (ONERA, Chatillon-sous Bagneux, Hauls de-Seine, France) (Super- sonic Tunnel Association, Semiannual Meeting, 46th, Columbus, Ohio, Sept 30-Oct 1, 1976) ONERA, TP no 1977-7E, 1977 9 p The hot gas dynalpy test bench which is described enables simulating directly the performance of jet engine exhaust nozzles and afterbodies with real gas duplicating real engine outflow conditions in dynalpy, composition, and temperature The compressed air supply, kerosene burner, the ducts for the primary (hot) and secondary (cold) air flows, and the pressure and temperature measurement arrangements are described Some models used in calibration tests are shown, and some tests results showing the thrust measurement repeatability on a given model are presented P T H A77 40924 Criteria for large scale fire testing of aircraft interiors R B Williamson and H Hasegawa (California, University, Berkeley, Calif ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 32 p Key considerations in designing aircraft fire safety include controlling the risk of fire outbreak, containing fire within interior spaces, maintaining structural integrity and air-worthiness during fires, and reducing the toxic threat of combustion products A test is developed for the containment of fire in interior spaces, similar to the standard fire containment test for building materials The test allows comparative data to be obtained on the fire resistance of newly-developed aircraft interior panels Toxic gas analyses and bioresponse data are also given, and calculations are made to determine the amount of time needed to burn through the test specimen, to reach excessive temperature levels on the back face of panels, and to reach untenable smoke conditions J M B A77-40925 The airport and fire from the airport fire chief's view S U van der Meulen (Luchthaven Schiphol, Amster- dam, Netherlands) National Fire Protection Association, Interna- tiona/ Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 9p A 77-40926 Lessons from individual aircraft fire accidents TWA L1011 aircraft fire - Logan International Airport, Boston, 442 A77-40934 Massachusetts, U S A , 20 April 1974 G H Tryon (National Fire Protection Association, Boston, Mass) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 7 p A77-40927 An evaluation of worldwide transport aircraft fire experiences A F Taylor (Cranfield Institute of Technology, Cranfield, Beds, England) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976. Paper 35 p 6 refs This further study of turbine engmed transport aircraft acci- dents has concentrated on 269 survivable accidents where there was either a post impact fire, major fuel spillage or an inflight fire involving the fuel An evaluation has been made of the effects on the final fatality rate of such parameters as fuel type, aircraft type and size, load factor, initial impact severity, phase of flight and type of flight The advantage of kerosine over wide cut gasoline is again confirmed and it is shown that the majority of people who die by the effects of fire do so in approach accidents but nevertheless in those involving comparatively few or no deaths directly due to the actual impact Turboprops and jets exhibit a different pattern of cause of death and although a higher proportion of turboprop accidents occur during the approach this does not account for the difference When considering fire alone the effects of aircraft age and type are small compared to the effects of fuel volatility (Author) A77-40928 Crash management at airports J C Self (Aerospace Management Services International, Los Angeles, Calif ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 11 p Meshing of community supported rescue agencies (mutual aid or civil defense organizations) and airport based crash rescue teams is discussed Generally an airport should concentrate on providing immediately needed services, such as prompt firefighting In accidents involving serious fire, for example, only sixty to ninety seconds may be available for evacuating the cabin Evacuation teams should arrive with the second wave of firefighting equipment and should be equipped to gain access to the cabin in the presence of fire damage and in any crash configuration, be able to work in a toxic atmosphere, and be trained in using backboard and other victim handling techniques Back up manpower should be capable of controlling crowds, manning first aid stations, and coordinating airport and community rescue services Creating a victim profile and a spectrum of hypothetical accidents is discussed, and a typical response system for an airport with two ambulances, a paramedic team, and one doctor is outlined The time periods needed to evacuate, triage, transport, and begin treatment of victims are also defined J M B A77-40929 US air carrier accidents involving fire /1965 through 1974/ R L Schleede (National Transportation Safety Board, Bureau of Aviation Safety, Washington, D C ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 24 P A previous 10 year study (1955-1964) published by CAB is updated for the 1965 1974 period and although the number of people involved in certified air carrier aircraft accidents is found to have increased over the previous decade, the numbei killed in those accidents and the number of deaths due to fire have decreased Accident data is divided into categories according to the survivability of the accident (ranging from those incidents in which all occupants were killed, to those in which all iniunes were minor), and the origin of the fire (m-fhght, as a result of impact, or on-ground) Comparison between accident rates of U S air carriers in all operations and U S air carriers in passenger service is also made, with non passenger operations found to involve a greater incidence of fire accidents Pievious suggestions for improving survival rates are recapitulated, including increasing strength of environmental structures and occupant restraints, developing of fuel merting and fire suppression systems, reducing toxic fumes from burning cabin materials, improv- ing evacuation procedures, and improving effectiveness of airport firefighting and rescue facilities Statistics are presented showing good improvement in some of the areas mentioned above J M B A77-40930 Overseas National Airways DC-10-30 CF fire- November 12, 1975, JFK International Airport, New York, New York J W Hannan and A M Sloane (Port Authority of New York and New Jersey, New York, N Y) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 11 p A77-40931 The airport and fire from the air carrier's view P R Powers (American Airlines, Inc . Flushing, N Y ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 9 P The ability of airport firefighting crews to provide adequate protection and assistance to air carriers in the case of accidents involving fires or entailing risk of fire is assessed The performance of firefighting crews in four recent jet aircraft accidents is evaluated Problems arising from failure to designate authority and responsibil- ity in firefighting efforts and difficulties in coordinating firefighting and rescue operations are discussed The need for strict standards regarding the training of firefighting and rescue personnel and equipment is stressed, together with the importance of developing plans for integrating available personnel and equipment in individual airports * C K D A77-40932 Vehicles and extmguishants (Les vehicules et les extmcteurs) R Pizel (Aeroportde Paris, Service Etudes Secunte, Orly Airport, France) National Fire Protection Association, Inter- national Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 9p In French Three fire-extinguishing foams used to combat aircraft fires are compared with respect to the quantities of precursor water and powder required for different categories of airports The three foams are a protein foam, an aqueous film-forming foam, and a fluoropro- tem foam (FP 70) The properties of the fluoroprotem powder are examined Characteristics of the fire-fighting vehicles which transport the foam precursors are discussed, and powder and water delivery rates are examined Other topics, such as fire-fighting in a fog and the development of foam-delivering boats for use at airports adjacent to a body of water, are considered M L A77 40933 Combined agent techniques and new agent developments W Mutzelburg (Flughafen Berlin Tegel, Berlin, West Germany) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13 17, 1976, Paper 28 p In German The use of suitable materials for the production of foam in aircraft fire-fighting applications is discussed, taking into account the definitions of terms employed in the description of the character- istics and the effectiveness of the extinguishing agent Details concerning the application of the various available agents are discussed and the effects produced by the different agents are compared A description is also presented of a new extinguishing agent which utilizes the heat of the fire for the foam generating process The agent consists essentially of a AFFF-Halon emulsion G R A77-40934 The aircraft and fire from the fire protection engineer's view W H McClarran (Society of Fire Protection Engineers, Boston, Mass ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976. Paper 10 p Fire hazards associated with aircraft are described It is urged that materials used for interior finishing be tested in the actual environment and configuration in which they would occur in an aircraft Problems associated with jet fuels and the flammable oil used in hydraulic systems are examined, and the fire hazards caused 443 A77-40935 by combustibles in the form of maintenance materials, supplies, and passenger carry on luggage are discussed Design modifications that would reduce these hazards are considered M L A77-40935 Extmguishants for aircraft fire fighting - Auxil- iary fire suppressants S B Martin and R S Alger (Stanford Research Institute, Menlo Park, Cal i f) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 25 p 6 refs Effective as it is against the class B fires that commonly result from aircraft mishaps, foam is not the whole answer Some kinematic situations often require the application of auxiliary agents This paper reviews recent test and evaluation work pertaining to the selection and effective use of auxiliary agents, including research with halocarbon and dry-chemical agents This review deals with three aspects of the fire suppression system (1) agents, (2) application equipment, and (3) operation techniques Specific emphasis is given to techno economic criteria for selecting agents to fit particular situations and to test methods for evaluating equipment and application techniques The significance of test results from kinematic fuel fires is discussed with respect to firemen training (Author) A77-40936 Safety on board/evacuation procedures and training of cabin crew L Kozlowski (Swissair AG, Zurich, Switzer- land) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 10 p Survival in the case of aircraft accidents occurring at or near the airfield depends on seriousness of the emergency landing (fire, structural damage, gear collapse), the number of exits not blocked by fire, the adequacy of evacuation equipment and procedures, and efficiency of the ground rescue personnel and their fire fighting equipment Suggestions for improving evacuation procedures include use of slides that are functional under a variety of aircraft attitudes on crash, increased passenger briefing, and availability of ground equipment for speedy removal of passengers from aircraft with exits 'five meters above ground Furthermore, the number of cabin 'attendants should in general equal the number of exits, with an additional attendant provided to secure overwmg life rafts Types of ' 'unprepared emergencies' (i e , those for which there is no time to secure cabin and passengers) and 'prepared emergencies' are listed, procedures to cope with these contingencies should be frequently rehearsed by cabin attendants J M B A77-40S37 * A composite system approach to aircraft cabin fire safety D A Kourtides, J A Parker, W J Gilwee, Jr, N R Lerner (NASA, Ames Research Center, Moffett Field, Cal i f) , C J Hilado, L A LaBossiere (San Francisco, University, San Francisco, Calif), and M -T Hsu (San Jose State University, San Jose, Calif I National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 49 p 20 refs The thermochemical and flammabihty characteristics of two polymeric composites currently in use and seven others being considered for use as aircraft interior panels are described The properties studied included (1) limiting oxygen index of the composite constituents, (2) fire containment capability of the composite, (3) smoke evolution from the composite, (4) thermo- gravimetric analysis, (5) composition of the volatile products of thermal degradation, and (6) relative toxicity of the volatile products of pyrolysis The performance of high-temperature laminating resins such as bismaleimides is compared with the performance of phenolics and epoxies The relationship of increased fire safety with the use of polymers with high anaerobic char yield is shown Processing parameters of one of the bismaleimide composites is detailed (Author) A77-40938 Aircraft fire fighting tactics - Handling of equipment A J Koppert (Mmistene van Verkeer en Waterstaat, Rijksluchtvaartdienst, The Hague, Netherlands) National Fire Pro- tection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 6p Rescue equipment and techniques in use at Dutch airports are discussed An inexpensive firefighting unit designed for single-man operation at the smallest airports is described, as well as a larger version of the same vehicle, employing a combination of premix and dry chemical extinguishing agents A medium-sized airport requires one of the larger vehicles and two foam tenders, while a large airport (such as the Schiphol Airfield) requires at least two sets of this equipment, operating from separate stations Use of monitors and hoselmes in combatting open fuel fires is assessed, together with the special problems of engine and wheel fires Techniques for forcing entry into disabled craft and evacuating victims are considered, and a portable breathing apparatus permitting nine minutes of rescue work time inside a smoke-filled craft is described J M B A77-40939 Lessons from individual aircraft fire accidents - Accident of the Boeing 707-PP-VJZ at Saulx-les-Chartreux, July 11, 1973 B V Hewes (National Fire Protection Association, College Park, Ga) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 7p A77-40940 The aircraft and fire from the pilot's new B V Hewes (International Federation of Air Line Pilots Association, London, England, Air Line Pilots Association, International, Wash mgton, D C ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13 17, 1976, Paper 6 p An airline pilot is concerned with fire both in the air and on the ground Fortunately, in flight engine fires are very rare and it is hoped that with suitable improvements of cabin interiors the in flight fire hazard will soon be eliminated However, the situation regarding the crash fire is entirely different Experimentation with modified fuels has only had limited success The approaches which remain to reduce significantly the crash fire hazard involve crashworthy, fuel systems and improved fuel containment Such systems are now being retrofitted to helicopters and race cars with considerable success Airline pilots have requested that a similar system be designed for commercial aircraft G R A77 40941 Handling aircraft accident/incident survivors and victims - Accountability techniques and body management G J Haas (Lee County, Div of Protective Services, Fla ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13 17, 1976, Paper 13 P The large number of victims involved m many aircraft accidents necessitates waiver of junsdictional boundaries among rescue teams, more widespread use of trauma kits and multi casualty kits, and training of aircraft crash specialist teams in problems of extrication and handling of victims Training should emphasize the need to stabilize victims rather than treat them, tagging and classification of casualties to prevent duplication of victim evaluation, and the use of a 'triage' system, i e , separation of victims into three categories, from assumed fatalities to those requiring speedy treatment, to those not needing immediate attention The distinction between initial, intermediate, and advanced treatment is made, and co ordmating the removal of casualties by ambulance and the distribu tion of victims to hospitals is also discussed Procedures in body removal and identification are described, with attention given to the role of autopsies in the eventual determination of the causes of a crash J M B A77 40943 Methods to measure aircraft fire fighting equipment capabilities G B Geyer (FAA, National Aviation Facilities Experimental Center, Atlantic City, N J ) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13 17, 1976, Paper 44 P 444 A77-41379 Foam dispensing systems employed in airport firefighting are analyzed The influence of nozzle shape and rate of discharge on the shape and depth of foam deposits is compared for protein foam and aqueous-film-forming foam (AFFF) Full-scale fire modeling experi- ments involving both types of foam are performed to determine the fire control time under various conditions, including foam applica- tion with an operator positioned on the monitor platform and using a hand-operated override system, application with a fireman posi- tioned at the nozzle console to change foam pattern at the discretion of the nozzle operator, and application with an operator on the monitor platform using an electro-pneumatic monitor control Among the recommendations for improving performance are devel- opment of a foam range finder based on nozzle elevation and azimuth position, and use of devices to increase solution discharge rate Problems of visibility from the cab of the firefightmg vehicle and the relative efficacy of protein foam and AFFF are also discussed J M B A77-40944 The airport fire defense - The basic mission and needs R J Ferguson (British Airports Authority, London, England) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 10 p The basic mission of airport fire defense involves the ability to respond to a fire within three minutes and preferably in less than two minutes, the mamtanance of survivable conditions within the aircraft until fire control has been achieved, the creation of safe conditions for evacuation or rescue, and the effective transportation of casualties To fulfill this mission specialized equipment and training are needed Aspects of the basic mission and needs are discussed, and traits of airport accidents are considered M L A77-40946 Extinguishants for aircraft fire fighting foam- ing agents - Protein, fluoroprotem and AFFF L R DiMaio (National Foam System, Inc , Lionville, Pa ) National Fire Protection Associa- tion, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 12 p 8 refs The three foams which are used as primary agents include a regular type involving protein, an aqueous film-forming foam, and a fluoroprotem type The regular protein-type mechanical foams, based on hydrolyzed protein, are and have been in use for over 30 years The AFFF or aqueous film forming foam makes use of fluormated surfactants The fluoroprotem type is a protein based liquid which is modified by the addition of a selected fluormated surfactant which bonds itself loosely to the pro'em to give the foam oleophobicity G R A77-40947 Improving fire prevention measures on board commercial transport aircraft (Comment s'ameliore la secunte contre I'mcendie a bord des avions de transport public) A Blavy (Societe Nationale Industnelle Aerospatiale, Suresnes, Hauts-de-Seme, France) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976, Paper 8 p In French Several aspects of fire control for commercial transport aircraft are considered with attention to measures that would reduce the likelihood of a fire starting, or would protect crew and passengers if a fire does start, or would facilitate fighting the fire The economics of fire control systems in general as well as space and weight constraints are considered The causes of onboard aircraft fires are discussed M L A77-40948 The aircraft and fire from the operator's view J J Brenneman (United Airlines, Inc, San Francisco, Calif) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13 17, 1976, Paper 10 p A77-40950 Balancing the costs of rescue services and fire fighting among different categories of airports (Equihbre des couts des services de sauvetage et de lutte contre I'mcendie entre les differentes categories d'aeroportsl F Ansart (Direction Generale de ('Aviation Civile, Service Technique de la Navigation Aenenne, Paris, France) National Fire Protection Association, International Seminar on Aircraft Rescue and Fire Fighting, Geneva, Switzerland, Sept 13-17, 1976. Paper 16 p In French The difficulties that minor airports face in financing rescue services and fire fighting procedures suitable for the largest airplanes are examined, and the costs are analyzed with respect to traffic A method of balancing costs is proposed which is based on the total traffic of the airport as the total traffic is a determinant of its actual resources Cost efficiency optimization is considered ML A77-41125 TSDMA - A novel secondary radar (TSDMA - Em neuartiges Sekundarradar) UFA Fusban Nachrichten Elektromk,vo\ 31, June 1977, p 171,172 In German The Time Space Division Multiple-Access System (TSDMA) considered is a secondary radar system which is particularly suited for object identification in the case of an unexpected attack of low-flying aircraft The principles of operation of conventional secondary radar systems and the implementation of these principles are examined It is pointed out that the mam problem concerning an employment of these systems is related to the danger of over- interrogation In the proposed system, discrete time-slots are assigned to the interrogators This approach is to prevent overmterrogation m crisis situations The described system can be termed four dimensional because it makes use of the time dimension, as the fourth dimension, m addition to the three spatial dimensions G R A77-41268 ff Steady linearized aerodynamics II Super- sonic (Aerodynamique stationnaire lineansee II - Supersonique) D Homentcovschi (Bucuresti, Institutul Polytehmc, Bucharest, Rumania) Archiwum Mechaniki Stosowane], vol 29.no 1,1977, p 41-51 7 refs In French Fluid-mechanics equations, written m distribution form, are used in studying the steady supersonic flow of a compressible fluid past a slender body The obtained integral equation allows the direct calculation of lift Attention is given to wings with and without subsonic trailing edges and to the case when the supersonic leading edge is reduced to a point In considering the case of a conical body, it is shown that if the supersonic leading edge cannot be reduced to a point, then the solution of the problem is obtained m an explicit form B J A77 41270 ,7 Wave structure and density distribution in a nonstationary gas jet I M Naboko, V V Golub, A V Eremm, V A Kochnev, and A A Kulikovskn (Akademua Nauk SSSR, Nauchno Issledovatel'skn Institut Vysokikh Temperatur, Moscow, USSR) Archiwum Mechaniki Stosonanej, vol 29, no 1, 1977, p 69-80 7 refs The paper deals with the unsteady jet flow when the ratio of the nozzle exit stagnation pressure to the ambient pressure vares in a wide range A specific wave pattern during the initial stages of the supersonic outflow has been observed The observed wave pattern is found to depend on the physical properties of the particular gas Consideration is also given to time dependence of the flow structure and the density distribution in the unsteady jet The generalized data for the gas front along the flow are found to be in fair agreement with calculation by a spherical source model The time taken for the steady jet to be estabhshed.as observed in the experiment is found to be an order of magnitude longer than that obtained by calculations (Author) A77-41379 Cost-benefit analysis for airport development A H Stratford (Alan Stratford and Associates, Ltd, England) Airport Forum, vol 7, June 1977, p 59, 60, 62, 63 In English and German Prime initial requirements for cost-benefit studies include a measurement of all the factors which are relevant to costs and revenue that are likely to arise from a project and its development It is generally necessary to estimate the costs and benefits under a series of alternative conditions Attention is given to the secondary effects from airport development, the setting up of the study program. 445 A77-41388 questions of cost estimation, the types of revenues, and the final analysis of cost-benefit relations „„ GR A77-41388 ff Programmable data logger for automatic test equipment (Programova menci ustredna AKZI J Stepanovsky Zpravodaj VZLU, no 1,1977, p 7-16 In Czech ' The paper describes a programmable data logger designed for use with test equipment for aircraft control systems A block diagram of the whole system is shown, and the individual parts of the system are described, which include a control block, address system, measuring block, auxiliary signal source, digital-analog converters, power supply, and control block Tables showing the accuracy charac- teristics of the system operating under different temperature conditions are given P T H A77-41389 ff Software for automatic test equipment (Pro- gramove vybaveni AKZ) J Stepanovsky Zpravodaj VZLU, no 1, 1977, p 17-21 In Czech' The programming characteristics of automatic test equipment for testing the individual systems of an aircraft are described Different types of programs are characterized, and the self- programming capability of the system is described The structure of the programming language is described, and some instruction formats and programming examples are illustrated P T H A77-41390 # Testing gyroscopic systems with automatic test equipment (Kontrola gyroskopickych pristroju pomoci automa- tickeho kontrolniho zarizem) K Horak Zpravodai VZLU, no 1, 1977, p 23-30 In Czech The article describes the procedures for carrying out tests of aircraft gyroscopic systems and their main components including the gyromagnetic compass, artificial horizon, and the compensation switch A block diagram of some of the test equipment is described, and some programming characteristics are discussed P T H A77-41391 ff Measuring the motion of an aircraft with direct lift control during flight along the approach path (Mereni letounu s pnmym rizenim vztlaku pn letu po pnblizovacim paprsku) V Pokorny Zpravodai VZLU.no 2, 1977, p 51-58 In Czech The paper describes flight simulator measurements of an aircraft's motion during landing approach for an aircraft that has direct lift control realized by a simple coupling of spoiler and elevator deflections Measurements showed that this simple coupling results in an improvement in the accuracy of flight control on the approach path, especially under turbulent conditions Important factors on performance were differences in ijneasurements on individual pilots, training, fatigue, and alcohol P T H A77-41392 ft Analysis of identification errors in flight dy- namics (Rozbor chyb identifikace v dynamice letu) V Kocka Zpravodaj VZLU, no 2, 1977, p 59-64 9 refs In Czech Three stages in identification and their variants used in flight dynamics as a method of identification of mathematical models of aircraft motions are characterized Random and systematic errors in two of these variants are analyzed In order to verify the insignifi- cance of the values of the systematic errors in the output quantities, a means of selecting a control parameter is outlined A global statistical test for closeness of fit is proposed for verifying the identity of the values of the output quantities measured on the system and obtained on the model Specific properties of ide.ntifica- tion in flight dynamics are discussed P T H A77-41394 •/ Aircraft simulation on computer (Simulace letounu na cishcovem pocitaci) J Homola Zpravodaj VZLU, no 2, 1977, p 73-79 11 refs In Czech Some numerical methods used in digital flight simulation are described Simplified equations of aircraft longitudinal motion are given Examples of simulation of short-period oscillations of a small passenger aircraft and of a hypothetical supersonic aircraft are discussed The influence of the numerical method used and of the integration step on the accuracy of the solution is illustrated An organization'scheme for a simulation program for real time solution of digital flight simulation problems is proposed P T H A77-41450 Some research problems on the fatigue of aircraft structures W T Kirkby (Royal Aircraft Establishment, Farnborough, Hants, England) Society of Environmental Engineers, Journal, vol 16-2, June 1977, p 7-15,24 15 refs The principal aircraft design philosophies ('safe-life', 'fail-safe', and 'damage-tolerant design') have promoted various emphases on three areas of research into the fatigue of structures loading actions, cumulative fatigue damage, and monitoring and managing of fatigue life consumption Two investigations into loading actions are discussed, one studying atmospheric turbulence during low-level flights over land and sea, the other measuring severity of load experienced during different sorties Examples of research into cumulative fatigue damage behavior include tests of stress applied to aluminum alloy plates, the effect of surface cladding on nearly pure aluminum, prediction of crack growth under variable amplitude loading and under combined mechanical and thermal stress cycling Research in monitoring and managing of fatigue life consumption is illustrated by a study of structural loads incurred in landing large jet aircraft in relation to piloting technique, and development of means to indicate to the pilot, while airborne, the rate at which fatigue life is being consumed J M B A77-41462 Services and installations for aviation at air- ports and airfields of regional importance (Oienste und Anlagen fur die Luftfahrt auf Flughafen und Landeplatzen von regionaler Bedeutung) Dusseldorf, Deutsche Gesellschaft fur Ortung und Navigation, 1977 83 p In German The reported investigation is to provide an evaluation criterion concerning the future characteristics of the services and installations for the considered airports in the Federal Republic of Germany An evaluation scheme for the determination of the requirement thresh- old for services and installations for aviation is discussed, taking into account flight-operational aspects, the air traffic control service, the flight information service, the communications service, the naviga- tion service, the weather service, aspects of air space supervision, and details regarding the evaluation scheme Attention is given to lighting systems, visual aids, instrument landing system installations, and VOR installations G R A77-41473 An LED numeric display for the aircraft cockpit R N Tyte, J H Wharf, B Ellis (Royal Aircraft Establish- ment, Farnborough, Hants, England), T F Knibb, R G O'Rourke, and R M Gibb (Plessey Co, Ltd, Allen Clark Research Centre, Towcester, Northants, England) IEEE Transactions on Electron Devices, vol ED-24, July 1977, p 982-986 Research supported by the Ministry of Defence This paper describes the construction and performance of an LED numeric display designed specifically for aircraft cockpit applications The display, using yellow or green LED chips, is a 4-character 7-bar numeric with 4-mm character height mounted in a hermetically sealed package to meet full military device specifica- tions Legibility\tudies are reported for this display in ambient illuminations up \> 100 000 lux, using different, comercially available contrast-enhancement filters The results show that the display is completely legible in the highest illumination for a relatively modest power consumption (Author) A77-41547 tr Optimization of an oleo-pneumatic shock absorber of an aircraft during landing C Venkatesan Journal of Aircraft, vol 14, Aug 1977, p 822,823 5 refs The paper describes the results of the application of an optimum design procedure for landing gears of the oleo-pneumatic type for an aircraft of the 5000-lb class Peak ground load is the performance index, the constraint is on the stroke of the shock absorber, the variable is the diameter of the orifice in the shock absorber For a given landing mode, it is observed from the transient of the ground load that there are two peaks in the response, the relative magnitudes 446 A77-41753 of which depend on the damping constant of the shock absorber In the optimum case, the magnitudes of the peaks are almost the same P T H A77-41548 * ft Evaluation of flight spoilers for vortex allevia- tion D R Groom (NASA, Langley Research Center, Hampton, Va ) Journal of Aircraft, vol 14, Aug 1977, p 823-825 The paper describes the facilities and test procedures used in a series of wind-tunnel and full scale flight investigations of the effectiveness of flight spoilers currently existing on wide-bodied transport jet aircraft when used as trailing vortex hazard alleviation devices Examples of the results of such studies include the variation of trailing wing rolling moment coefficient with downstream distance behind a B-747 airplane model with various segments of its flight spoilers deflected 45 deg, and comparisons with models without spoilers deflected It is concluded that the existing flight spoilers on the B-747 are effective as trailing vortex attenuators PTH A77-41549 it Consideration of clogging in boundary-layer control system design P Crimi Journal of Aircraft, vol 14, Aug 1977,p 825-827 8 refs A model is proposed for the clogging mechanism of boundary layer control systems that employ suction through perforated surfaces The primary parameters are perforation size, particle size, boundary layer thickness and velocity profile, external flow static and dynamic pressures, and suction pressure An equation describes the limiting condition for no clogging of an individual particle, which is satisfied when the moment on a particle due to drag about the furthest downstream contact point is sufficient to overcome the moment due to the suction on the portion of the particle in the whole Curves for maximum suction for no clogging vs hole size were obtained from this condition for both laminar and turbulent boundary layers These results are applied to some specific systems, and it was found that clogging need not be a problem for boundary layer control used to prevent leading edge stall PTH A77-41575 H Aircraft aeromechanics (Aeromekhanika samo- leta) V V Andreevskn, V M Belokonov, A F Bochkarev, V I Khmov, L A Matveeva, V M Turapin, and M S Tuger Moscow, Izdatel'stvo Mashmostroeme, 1977 416 p 37 refs In Russian Methods for calculating the trajectories of aircraft motion in flight, flight stability, and maneuverability (handling) are expounded First the aircraft is treated as a point of mass equal to the aircraft mass in free flight with forces applied (gravitational, aerodynamic, and propulsive thrust) Then motion of the center of mass is investigated in the ideal case Finally the aircraft is studied as a three-dimensional mass with disturbances in flight and control inputs taken into account Fuel consumption, take-off and landing charac- teristics, moments and their derivatives, longitudinal and lateral trim, stability and controllability with automatic controls functioning, spin, autorotation of the wing, aileron reversal, and airframe elasticity are among the topics treated R D V A77-41636 YC-15 in the air H Field Flight Interna- tional, vol 112, July 23, 1977, p 269-272 The McDonnell Douglas YC-15, developed for the US Air Force's Tactical Air Command, delivers payloads twice those handled by the C-130 transport and has a range of 2,300 nautical miles Principal features of the YC-15 include need for a field length equal to half the C-130's, flight system controls located on the glareshield, leaving center panels free for engine instruments and pressunzation controls, and Visual Approach Monitors (VAM), displays which monitor the conduct of STOL approach and landing The craft is adapted to both low-altitude low cruise velocities and a high-altitude cruise at Mach 0 68 Similar to VTOL craft, the YC-15's airspeed is primarily controlled by attitude, while altitude in the approach mode is governed by thrust Slope of descent is normally 6 degrees, but a slope of up to 9 degrees is attainable J M B A77-41648 ff Operational reliability of aircraft powerplants (Ekspluatatstonnaia nadezhnost' aviatsionnykh silovykh ustanovok) K P Alekseev Moscow, Izdatel'stvo Transport, i9"6 160p 27 refs In Russian The book analyzes the fuel and lubn:<>tion systems of modern transport aircraft from the viewpoint of their operational reliability and safety, and also examines some general factors influencing the stability of powerplant operation The causes of engine fires are investigated and suitable preventative measures are discussed Methods for evaluating the safety margins of powerplants are described Special attention is given to the problem of bird collisions and means of alleviating their effects The reliability of an engine is estimated by means of partial relative indices, and the effect of engine reliability on safety and economy of flight is analyzed A general method for estimating the technical economic indices of an engine taking into account its reliability is set forth PTH A77-41751 Lighter Than Air Systems Technology Confer- ence, Melbourne, Fla, August 11, 12, 1977, Technical Papers Conference sponsored by the American Institute of Aeronautics and Astronautics New York, American Institute of Aeronautics and Astronautics, Inc. 1977 138 p Members, $12 , nonmembers, $17 Numerous trends in research and development work on lighter- than air (LTA) craft and systems are surveyed, an updated LTA bibliography is included Semibuoyant LTA vehicles, hot air bal- loons, tethered aerostats, cargo airships, Naval support LTA craft, heavy lift airships, and metal-clad airship hulls are discussed The present and potential roles of universities in LTA research are dealt with Hypothetical concepts and theoretical investigation predomi- nate in the contributions R D V A77-41752* # Theoretical study of hull-rotor aerodynamic interference on semibuoyant vehicles S B Spangler, C A Smith, and M R Mendenhall (Nielsen Engineering and Research, Inc. Mountain View, Calif) In Lighter Than Air Systems Technology Conference, Melbourne, Fla , August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc. 1977, p 1-7 8 refs Contract No NAS2- 9512 (AIAA 77-1172) Theoretical methods are being developed to predict the .mutual interference between rotor wakes and the hull for semibuoyant vehicles The objective of the investigation is to predict the pressure distribution and overall loads on the hull in the presence of rotors whose locations, tilt angles, and disk loading are arbitrarily specified The methods involve development of potential flow models for the hull alone in a nonumform onset flow, a rotor wake which has the proper features to predict induced flow outside the wake, and a wake centerlme specification technique which accounts for the reactions of the wake to a nonumform crossflow The flow models are used in sequence to solve for the mutual influence of the hull and rotor(s) on each other and the resulting loads A flow separation model is included to estimate the influence of separation on hull loads at high sideslip angles Only limited results have been obtained to date These were obtained on a configuration which was tested in the Ames Research Center 7- by 10- Foot Low Speed Tunnel under Goodyear Aircraft Corporation sponsorship and indicate the nature of the interference pressure distribution on a configuration in hover (Author) A77-41753 # The inverse problem for axisymmetnc aero- dynamic shapes M F Zedan and C Dalton (Houston, University, Houston, Tex ) In Lighter Than Air Systems Technology Confer- ence. Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics. Inc . 1977, p 8-14 18 refs (AIAA 77-1175) The flow of an incompressible fluid past an axisymmetnc shape is considered in the form of the 'inverse problem' in hydrodynamics For a given pressure or velocity distribution, the appropriate body shape is determined iteratively The method of line sources and sinks is used to represent the body shape The procedure is simple and accurate and convergence is more rapid than that obtained by other investigators using surface-source distributions Examples chosen to 447 A77-41754 represent the method include spheres, Rankine bodies, a constant velocity body and an airfoil-shape axisymmetnc body Results compare very well with exact solutions and with calculated results of others when comparison is possible (Author) A77-41754 # A lighter-than-air bibliography D E Wood- ward and G E Wright, Jr (Association of Balloon and Airship Constructors, Rosemead, Calif) In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 15-40 816 refs Research supported by the Association of Balloon and Airship Constructors (AIAA 77-1177) This bibliography consists primarily of 'unpublished' material, including (1) proposals and contract reports, (2) technical investiga- tions by or for manufacturers and users of LTA vehicles, (3) user organization training materials, specifications, and technical regula- tions, and (4) reports of inspections, acceptance tests, surveys, and accident investigations Wherever possible, availability of the items in the bibliography has been noted (Author) A77-41755 ff A comparison of different forms of dirigible equations of motion J R Pretty and R 0 Hookway (Martin Marietta Aerospace, Denver, Colo ) In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11. 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 41-47 8 refs (AIAA 77-1179) Several formulations of airship equations of motion are current- ly in use in the LTA industry The most significant differences in the equations are due to (1) treating the apparent masses and apparent inertias as added masses or added inertias, or (2) treating them as aerodynamic acceleration reaction forces and moments Although there has been little opportunity to correlate the predicted LTA response with actual flight test data, the equations can be verified by examining the correlation between test data and predicted responses for submarines From this data it is concluded that approach (2) is correct Predicted responses of a dirigible represented by both sets of the equations are shown Better stability margins are predicted with approach (2) (Author) A77-41757 *' Tethered aerostats - Technology improve- ments H E Reed (Pan American World Airways, Patrick AFB, Fla ) and J A Sechnst (RCA, Patrick AFB, Fla ) In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 53-57 (AIAA 77-1184) The tethered aerostat system, known as Family II, developed by government and industry at the Range Measurements Laboratory, Patrick AFB, Florida has proven to be a major milestone in balloon technology The concepts and approaches that produced this system have led to the acceptability of the tethered aerostat as a meaningful and cost-effective tool by government and to its exploitation on a commercial basis This paper presents a summary of technology improvements aimed at reducing the airborne weight of the Family II system in order to increase its payload capability Principally covered is the design and development of a mooring system that eliminates the need for a metal mooring structure to be carried on-board the aerostat A comprehensive program to test and evaluate Kevlar, a high strength-to-weight fiber, as a tether material and to certify its operational use wil be discussed (Author) A77-41758 # The university's role in the new era of LTA technology and applications E F Strother (Florida Institute of Technology, Melbourne, Fla ) In Lighter Than Air Systems Tech- nology Conference, Melbourne, Fla , August 11, 12, 1977. Technical Papers New York, American Institute of Aero- nautics and Astronautics, Inc, 1977, p 58-62 11 refs (AIAA 77-1187) Universities often seem unsure of their proper role in the current LTA revival Uncertainty still exists in the nontechnical areas concerning economics, vested interests, and socio-political accep- tance If developed in the private sector, LTA design will be rigidly constrained by economic boundary conditions, while military devel- opment would emphasize uniqueness of mission Universities offer both civil and military LTA developers a wide range of research and interdisciplinary benefits which are described in this paper Through a systems approach the objectivity of university research will provide valuable direction to the development and public acceptance of LTA concepts (Author) A77-41759 tt Structural response of the Heavy Lift Airship /HLA/ to dynamic application of collective pitch W N Brewer (Goodyear Aerospace Corp, Akron, Ohio) In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 63-69 (AIAA 77-1188) This paper presents results of a preliminary analysis of the dynamic response of the Heavy Lift Airship (HLA) to rapid application of collective pitch and to wheel loads induced in a symmetrical four-point landing condition Masses, springs and forcing functions are defined Natural frequencies and mode shapes are determined The response of the system to the forcing functions is determined first by analytical techniques (partially) and then by numerical integration of the equations of motion on a digital computer It is shown that no cables will go slack in the specified conditions but structurally significant excursions in the suspension system do occur (Author) A77-41760 ff MATASS - Moored Airship Towed Array Sonar System F D Buckley In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics. Inc, 1977, p 70 80 (AIAA 77-1190) MATASS is an independently produced concept formulation which assumes an ASW mission which an airship could perform, using a towed array sonar While monitoring the array, the airship remains moored to the array cable This permits a protracted Time On Station with minimal energy expenditure The minimal airship volume required to perform the mission is determined The effect of different propulsion engine installations on mission radius is deter- mined For airships of larger than minimal volume, Loiter Time, free of the array, is determined for different loiter engine installations Conclusions and recommendations are presented for further investi- gation (Author) A77-41763 # Semi-buoyant lifting body hybrid characteris- tics for advanced Naval missions J W Lancaster (Goodyear Aerospace Corp, Akron, Ohio) In Lighter Than Air Systems Technology Conference, Melbourne, Fla, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc , 1977, p 99-110 Contract No N62269-76-C-0466 (AIAA 77-1194) A summary of the results of the parametric Analysis and Conceptual design study of a Semi Air Buoyant (SAB) Lifting Body Vehicle for Advanced Naval Operations is presented The SAB is a VTOL vehicle which has full hover capability, 150 knot cruise speed, and can provide from 12 hours to 7 days endurance depending on speed, mission profiles and payload The ferry range is about 8000 nautical miles at the optimum range speed profile An IOC of 1990 appears achievable with low technical risk Operationally, the SAB would operate primarily in conjunction with surface assets (shipping convoys and task forces) to provide ASW and AEW screening protection The SAB is not deck-space constrained and has a special purpose support module for at sea replenishment Independent, shore based operations are also possible Time on station perfor- mance of one to three days can be achieved depending on range to station and speed profile on station (Author) 448 A77-41930 A77-41764 ff Metalclad airship hulls V H Pavlecka (Turbo- machines, Inc, Irvine, Calif) In Lighter Than Air Systems Technology Conference. Melbourne, Ra, August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 111-121. 6 refs Navy-supported research (AIAA 77 1196) A range of five large Metalclad airship hulls was explored analytically for the determination of their structural weights as purely lifting hulls, at several altitudes and at maximum speed of 100 knots under the most severe gust moment exposure Exploration involved the determination of suitable Metalclad structures, hull pressures, metal skin thicknesses and their distribution, elastic interaction between skin and structure, internal gas containment means and study of methods of construction It was determined that Metalclad hulls can be designed and constructed economically, using simple cellular structures and can be expected to have extraordinarily low (weight)/(gross lift) ratios in all sizes of hulls (Author) A77-41765 § ZPG-X design and performance characteristics for advanced Naval operations J W Lancaster (Goodyear Aerospace Corp, Akron, Ohio) In Lighter Than Air Systems Technology Conference, Melbourne, Fla , August 11, 12, 1977, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1977, p 122-133 6 refs Contract No N62269-76-M-4325 (AIAA 77-1197) A summary of the results of a point design study of the ZPG-X (90 knot top speed, 5000 ft normal cruise altitude, and a 4000 n mi ferry range) Significant improvements in low speed and hover control result from the three propeller vectored thrust propulsion system The stern propulser includes a defected slip-stream control surface which provides control capability in hover, low speed - no wind conditions, and in statically heavy or light conditions Operationally, the ZPG-X could be employed in ship supported operations to provide ASW and AEW screening for shipping convoys and non-carrier task forces The low speed control capability allows towed array sensors to be used for passive ASW screening operations On-station times of one to two days can be achieved (Author) A77-41774 Use of changeover designs in subjective experi- ments J A John (Southampton, University, Southampton, England) Journal of Sound and Vibration, vol 53, July 8, 1977, p 117-126 5 refs In constructing a Latin square design, it is sought that the design should be balanced in the sense that, over the entire design, the stimuli are presented to subjects such that each stimulus is preceded by every other stimulus the same number of times Such a design is called a balanced changeover design This paper considers the concepts of balance and orthogonality associated with such design, and applies it to a subjective noise experiment, namely the comparison of the noise levels from a Boeing 707, a Concorde landing, a Concorde takeoff, and a DCS B J A77-41850 ff Market development problems for local service air carriers J W Crichton (Bradley Air Services, Ltd , Carp, Ontario, Canada) (Canadian Aeronautics and Space Institute, Annual General Meeting, Toronto, Canada, May 10-12, 1976) Canadian Aeronautics and Space Journal, vol 23, July Aug 1977, p 212-216 The paper discusses some of the fundamental problems facing local service air carriers in Canada trying to establish a viable operation Some of these are the following (1) lack of clear definition, and hence government policy protection, (2) relatively unattractive markets, and (3) modern equipment capable of meeting service dependability requirements is expensive However, it is argued that in many situations a short haul service would provide benefits to the public, outweighing the disadvantages of possible increased block flying time and marginal inflight inconveniences Such benefits include larger and more convenient choice of flying times, non-rising air fares, and fuel savings Remedies suggested are (1) clarification of government policy with regard to local service operations, (2) cooperation among local service and regional and mainline carriers, and (3) development of the proper aircraft for short haul transport P T H A77-41857 * ft Upper surface blowing aerodynamic and acoustic characteristics 0 M Ryle, Jr, J A Braden, and J S Gibson (Lockheed Georgia Co , Marietta, Ga ) American Institute of Aeronautics and Astronautics and NASA Ames Research Center, V/STOL Conference, Palo A/to. Calif, June 6-8, 1977, AIAA Paper 77-608 15 p 13 refs Contracts No NAS1 13870, No NAS1 13871 Aerodynamic performance at cruise, and noise effects due to variations m nacelle and wing geometry and mode of operation are studied using small aircraft models that simulate upper surface blowing (USB) At cruise speeds ranging from Mach 50 to Mach 82, the key determinants of drag/thrust penalties are found to be nozzle aspect ratio, boattailing angle, and chordwise position, number of nacelles, and streamlined versus symmetric configuration Recom- mendations are made for obtaining favorable cruise configurations The acoustic studies, which concentrate on the noise created by the let exhaust flow and its interaction with wing and flap surfaces, isolate several important sources of USB noise, including nozzle shape, exit velocity, and impingement angle, flow pathlength, and flap angle and radius of curvature Suggestions for lessening noise due to trailing edge flow velocity, flow pathlength, and flow spreading are given, though compromises between some design options may be necessary J M B A77-41863 * /? Quantitative density visualization in a tran- sonic compressor rotor A H Epstein (MIT, Cambridge, Mass) ASME, Transactions, Series A - Journal of Engineering for Power, vol 99, July 1977, p 460-475 15 refs Grant No NGL 22-009-383 The flow in a 59-cm-diameter high work transonic compressor rotor has been visualized using a fluorescent gas, 2,3, butanedione, as a tracer The technique allows the three-dimensional flow to be imaged as a set of distinct planes Quantitative static density maps were obtained by correcting the images for distortion and non- linearities introduced by the illumination and imaging systems These images and maps were used to analyze the three dimensional nature of the blade's boundary layer and shock system (Author) A77-41929 ," The future of rotorcraft m aviation J P Jones (Westland Helicopters, Ltd, Yeovil, Somerset, England) In The place of aviation in society. Proceedings of the Fifteenth Anglo American Aeronautical Conference, London, England, May 31-June 2, 1977 London, Royal Aeronautical Society, 1977 15p The evaluation concerning the future of rotorcraft takes into account the conventional helicopter, the supersonic rotor helicopter, the tilt (wing) rotor, and remotely piloted helicopters With respect to the conventional helicopter, it is expected that new developments will more than double its cost effectiveness The aerodynamic problems of the helicopter disappear if rotation at supersonic tip speeds is employed There are, however, problems of increased noise and power consumption for the supersonic rotor helicopter, which will probably limit its use to military applications Convertible rotorcraft have possibly the best technical chance of finding a civil market, but the investment requirements are high Remotely piloted- helicopters require a long period of engineering development work, which will probably only be performed in connection with extended military service G R A77-41930 ft Civil aviation activities in global perspective J Lukasiewicz (Carleton University, Ottawa, Canada) and K W Studnicki-Gizbert (Canadian Transport Commission, Ottawa, Canada) In The place of aviation in society. Proceedings of the Fifteenth Anglo-American Aeronautical Conference, London. England, May 31 June 2, 1977 London, Royal Aeronautical Society, 1977 17 p 29 refs A brief review is conducted of the major causes of the spectacular growth of aviation since 1945 The share of passenger and freight traffic that belongs to the air mode is examined, taking into account also a continental comparison which reveals the 449 A77-41936 predominance iof North America in air travel The U S domination of the air transport is reflected even more strongly in the industrial sphere Attention is given to economic dimensions, the international aspects of air transportation and the aircraft production industry, questions of research and development, and general aviation and special civil applications of aircraft in agriculture It is pointed out that commercial air transportation appears currently to have entered a period of transition from fast growth to maturity The causes responsible for this change are analyzed G R A77-41936 H Canadian Forces Search and Rescue M L King In The place of aviation in society, Proceedings of the Fifteenth Anglo American Aeronautical Conference, London, England, May 31 June 2, 1977 London, Royal Aeronautical Society, 1977 8p The Canadian Search and Rescue (SAR) organization is an outgrowth of the military air/sea rescue service which operated on an ad hoc basis in the coastal areas of Canada during World War II The SAR organization as authorized by Cabinet came into being in late 1947 The Canadian Forces is reponsible for coordinating and participating in SAR operations involving aircraft and vessels in distress within the Canadian areas of responsibility The Canadian Coast Guard, SAR provides the marine element for the national air sea rescue organization Attention is also given to problems of distress signal communication, legislative and juridical issues, the employment of electronic locator transmitters, a Search and Rescue Satellite System, computer assisted search planning, the major air disaster plan, and SAR statistics G R A77-41938 # Basic safety concepts W Tye (Civil Aviation Authority, Airworthiness Requirements Board, London, England) In The place of aviation in society, Proceedings of the Fifteenth Anglo-American Aeronautical Conference, London, England, May 31-June 2, 1977 London, Royal Aeronautical Society, 1977 13 p The safety of air transport is compared with that of other modes of travel, taking into account accident risks in general, the present safety level of air transport, the fatalities per billion passenger-miles, railway versus air transport, road versus genera! aviation, total fatalities, and injuries It is found that on a passenger-miles basis the number of fatalities in the U K is about twice the corresponding number for rail General aviation is clearly less safe than driving The practicality of improving air transport safety is investigated Atten tion is given to the economics of air safety, factors concerning risk taking, the effect of the press and of political pressures, the view of the public, and problems of private flying G R A77-41946 # The changing horizons for technical progress L E Fnsbee and R H Hopps (Lockheed-California Co, Burbank, Calif) In The place of aviation in society, Proceedings of the Fifteenth Anglo American Aeronautical Conference, London, England, May 31 June 2, 1977 London, Royal Aeronautical Society, 1977 23 p Some of the most promising potential technological develop ments in the air transportation field are discussed, including improvements in airframe design, aircraft engines, and active controls hardware Major obstacles to these relatively short term develop ments are considered Special attention is given to the problem of fuel economy Technologies requiring a longer time-scale for research and development, including advanced turboprop engines, all wing concepts, and laminar flow control, are outlined The potential impact of hydrogen based power plants on the development of super- and hypersonic transports is examined C K D A77-41960 # The next SST - What will it be L T Goodmanson and A Sigalla (Boeing Commercial Airplane Co, Seattle, Wash ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla. July 11-13, 1977, AIAA Paper 77-797 21 p 28 refs Progress in technology is reviewed in order to make a prediction of the shape, features, operations, economics, and noise character istics of the next generation of SST's Advances in aerodynamics, structures, propulsion, and jet noise control are examined, and examples of how they can integrate to form a complete airplane configuration meeting economic and noise requirements are shown P T H A77-41961 ff Airframe/engine integration with variable cycle engines J R Wilson and B R Wright (Lockheed California Co, Burbank, Calif I American Institute of Aeronautics and Astronautics and Society of Automot Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-798 8p 5 refs The paper studies the feasibility of using variable cycle engines, which have the ability to operate like turbofans during subsonic cruise and like turbojets at supersonic cruise, to regulate airflow and better match the engine with the inlet and reduce off-design penalties for second generation SST designs employing the over/under concept of engine installation A study of engine performance penalties related to inlet matching was performed on a advanced SST baseline aircraft with under/over nacelles containing VCE's with two different mixed compression inlet designs a translating centerbody axisym- metric inlet, and a two dimensional, articulated centerbody, vertical wedge Mission analyses show that the variable geometry features of VCE's allow engine airflow to be scheduled to match either type of inlet for minimum installations costs PTH A77-41963 # Propulsion designed for V/STOL E G Smith (General Electric Co , Aircraft Engine Group, Cincinnati, Ohio) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-804 9 p Major design criteria for propulsion systems used in V/STOL aircraft are identified Among the topics discussed are take-off versus cruise thrust matching, take off/engine out landing thrust matching, control requirements for vertical take-off and for short take-off/ vertical landing flight profiles, and engine-out safety Duty cycles for V/STOL propulsion systems are examined, together with the problems of inlet remgestion and pressure distortion C K D A77-41968 # The application of new technology for per- formance improvement and noise reduction of supersonic transport aircraft P H Calder and P C Gupta (Rolls Royce /1971/, Ltd, Aero Div , Filton, England) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-830 14 p 8 refs Performance improvements and environmental considerations associated with intercontinental supersonic transport aircraft are discussed, with emphasis given to noise reduction features Present capacities of variable cycle engines, which can be throttled to achieve acceptable takeoff and flyover noise levels, are described, and further innovations to reduce noise are suggested These include increasing engine mass flow to decrease jet velocity at a given thrust level, development of silencing devices (eg an ejector to mix extra mass flow into exhaust before it leaves the engine, thus reducing its velocity and noise), and improvements in takeoff aerodynamics Cost, thrust, drag, and weight penalties are taken into account in considering airframe modifications, choice of inlet configurations and Mach cruise number, the merits of high bypass ratios, use of acoustic linings in turbojet exhaust, use of a dual exhaust stream with a nonconventional velocity profile, methods of increasing mass flow, turbine cooling, duct burning, and suppressor exhaust systems J M B A77-41969 // Advanced supersonic transport propulsion re- quirements R W Mines (United Technologies Corp, Pratt and Whitney Aircraft Group, East Hartford, Conn ) American Institute of Aeronautics and Astronautics and Society of Automotive Engi- neers, Propulsion Conference, 13th, Orlando, Fla, July 11 13, 1977, AIAA Paper 77-831 7 p 8 refs One of the most promising propulsion systems (The Variable Stream Control Engine) for supersonic commercial transport applica- tion is reviewed The benefits of advanced propulsion technology, as 450 A77-41980 applied to the Variable Stream Control Engine, are presented on an overall systems basis showing the full impact on a supersonic transport airplane from an environmental, performance, and eco nomic viewpoint The advanced propulsion program, required for the United States to maintain a competitive position in the future commercial airplane market, is also presented (Author) A77-41970 # Supeisonic propulsion - 1970 to 1977 J N Krebs (General Electric Co , Aircraft Engine Group, Lynn, Mass I and R D Allan (General Electric Co, Aircraft Engine Group, Evendale, Ohio) American Institute of Aeronautics and Astronautics and Society of Automotive engineers. Propulsion Conference, 13th, Orlando, Fla, July 11-13. 1977, AIAA Paper 77-832 7 p In 1972 NASA initiated study programs to identify the required propulsion system and airplane technology necessary for an environ mentally acceptable supersonic cruise vehicle The Advanced Super- sonic Propulsion System Technology Studies at General Electric screened conventional turbojets, mixed flow and duct burning turbofans and variable cycle engines This resulted in the selection of a Variable Cycle Engine (VCE) concept that provides high airflow for low takeoff noise levels, using a co annular acoustic exhaust nozzle, and a cruise airflow matched to the airplane inlet flow schedule This VCE has been refined, and its mechanical design simplified to improve reliability and maintainability The propulsion system technology has improved to the point that definition of a second generation supersonic cruise aircraft propulsion system much improved from the 1971 GE4 turbojet is now possible (Author) A77-41971 # Technology status of let noise suppression concepts for advanced supersonic transports W T Rowe, E S Johnson, and R A McKmnon (Douglas Aircraft Co , Long Beach, Calrf) American Institute of Aeronautics and Astronautics and ^ Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13. 1977, AIAA Paper 77-833 9 p This paper presents one aircraft manufacturer's views on the technology status of three of the most promising exhaust nozzle designs meeting the noise constraints the coannular, the coannular with plug, and the retractable mechanical suppressor Each type is defined along with predicted operational characteristics Theoretical and test performance, for both thrust loss and noise suppression, are summarized Each of these three nozzles is combined with an appropriate engine, and is sized and integrated into a baseline Mach 2 2 supersonic transport to evaluate range performance The sensitivi- ty of aircraft performance to changes in noise requirements is presented Also, the impact on performance for improved noise test results is summarized (Author) A77-41972 # Full authority digital electronic control /FADEC/ preliminary design overview for a variable cycle engine B A Barclay (U S Naval Air Propulsion Test Center, Trenton, N J ) and J C Richards (General Electric Co , Aircraft Engine Group, Cincinnati, Ohio) American Institute of Aeronautics and Astro- nautics and Society of Automotive Engineers, Propulsion Con- ference, 13th, Orlando, Fla , July 11-13, 1977, AIAA Paper 77-837 10 p Contract No N00019-76 C-0423 A requirements analysis and a preliminary design of the control system for an advanced variable cycle engine has been conducted Through application of latest state-of-the-art electronics and complex control laws, the Full Authority Digital Electronic Control (FADEC) is shown to provide the capability necessary with significant advantage in life cycle cost, weight and reliability New techniques such as fault detection and compensation and hybrid electronic construction as well as advanced sensor, actuator and fuel system designs are employed to enhance the performance and reliability of the control system operating in the harsh engine environment (Author) A77-41973 * ff Two-dimensional nozzle/airframe integration technology - An overview G K Richey (USAF, Flight Dynamics Laboratory, Wright Patterson AFB, Ohio), B L Berrier (NASA, Langley Research Center, High Speed Aerodynamics Div , Hampton, Va ), and J L Palcza (U S Naval Air Propulsion Test Center, Trenton, N J ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla , July 11-13, 1977, AIAA Paper 77-839 11 p 23 refs The paper reviews the objectives and some of the accomplish- ments of a number of programs to develop nonaxisymmetric nozzle technology for future tactical aircraft applications Specific existing fighter aircraft model tests and preliminary studies are discussed which are designed to generate installed nozzle data, including the effects of thrust vectoring and reversal P T H A77-41974 * # Static performance of vectoring/reversing non- axisymmetric nozzles C M Willard (McDonnell Aircraft Co, St Louis, Mo), F J Capone (NASA, Langley Research Center, Hampton, Va ), M Konarski (General Electric Co , Cincinnati, Ohio), and H L Stevens (United Technologies Corp , Pratt and Whitney Aircraft Group, West Palm Beach, Fla ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference. 13th, Orlando, Fla . July 11-13, 1977, AIAA Paper 77-840 13 p 8 refs An experimental program sponsored by the Air Force Flight Dynamics Laboratory is currently in progress to determine the internal and installed performance characteristics of five different thrust vectoring/reversing non-axisymmetric nozzle concepts for tactical fighter aircraft applications Internal performance character- istics for the five non-axisymmetric nozzles and an advanced technology axisymmetric baseline nozzle were determined in static tests conducted in January 1977 at the NASA-Langley Research Center The non-ax isymmetric nozzle models were tested at thrust deflection angles of up to 30 degrees from horizontal at throat areas associated with both dry and afterburning power In addition, dry power reverse thrust geometries were tested for three of the concepts The best designs demonstrated internal performance levels essentially equivalent to the baseline axisymmetric nozzle at unvec- tored conditions The best designs also gave minimum performance losses due to vectoring, and reverse thrust levels up to 50% of maximum dry power forward thrust The installed performance characteristics will be established based on wind tunnel testing to be conducted at Arnold Engineering Development Center in the fall of 1977 (Author) A77-41975 ff Non-axisymmetric nozzle concepts for an F-111 test bed D Bergman (General Dynamics Corp, Fort Worth, Tex ), J L Mace (USAF, Flight Dynamics Laboratory, Wright Patterson AFB, Ohio), and E B Thayer (United Technologies Corp , Pratt and Whitney Aircraft Group, West Palm Beach, Fla ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-841 11 p 6 refs The paper describes the objectives, plans, and accomplishments to date of a study to determine the capability of the F-111 to demonstrate two dimensional (nonaxisymmetric) nozzle technology, with emphasis on propulsion system design and modification Various types of two dimensional nozzles employing internal gas expansion and mixed gas expansion are being evaluated with regard: to their effects on aircraft performance, i e , range, acceleration, and deceleration P T H ' A77-41980 * # Use of experimental separation limits in the theoretical design of V/STOL inlets M A Boles (Indiana Institute of Technology, Fort Wayne, Ind ) and N O Stockman (NASA, Lewis Research Center, Wind Tunnel and Flight Div , Cleveland, Ohio) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13. 1977. AIAA Paper 77-878 24 p 9 refs Experimental data from several model inlets have been used to generate two parameters which are related to the limit of operation for inlet flow separation One parameter, called the diffusion ratio, is the ratio of the peak velocity on the inlet surface to the velocity at the diffuser exit and is related to the boundary-layer separation at low throat Mach numbers The other parameter, the peak Mach 451 A77-41981 number on the inlet surface, is related to the separation at high throat Mach nbmbers These parameters are easily calculated from potential flow/ solutions and thus can be used as a design tool in screening proposed inlet geometries Any of the geometric design variables can be analyzed by this technique, but, this paper is restricted to the consideration of the internal lip contraction ratio An illustrative example of an application to an inlet design study for a tilt nacelle VTOL airplane is presented The study will show what value of contraction ratio is required to meet the operating requirements yet allow the inlet to remain free of separation as indicated by the two separation parameters (Author) A77-41981 # An engineering approach to estimating propul- sion contributions to system life cycle costs F F Tolle (Boeing Co , Seattle, Wash ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, F/a, July 11 13, 1977, AIAA Paper 77-879 8 p 7 refs Propulsion systems contribute directly to fuel cost, and to engine acquisition and maintenance cost, their performance in- fluences airframe weight and cost, and their reliability affects the numbers of systems needed to satisfy operational requirement These costs and their interactions are discussed Techniques relying primarily on engineering analysis are proposed to estimate the principle cost categories Acquisition cost estimates derive from an engine performance and weight estimating code, while maintenance costs are based on physics of failure, reliability theory and a maintenance simulation Applications to management of engine costs are outlined (Author) A77-41983 * Testing of propulsion system diagnostic equip- ment' T C Belrose (U S Army, Systems Concepts and Technology Div, St Louis, Mo ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, F/a, July 11-13, 1977, AIAA Paper 77-895 8 p 9 refs Judicious prior selection of diagnostic testing philosophy is juxtaposed to cut-and-try approaches, and preference is established for the former Several testing arrangements (in-flight engine condi- tion monitoring system, automatic inspection diagnostic and prog- nostic system, flight data recording system, advanced diagnostic engine monitoring system, aircraft integrated data systems) adopted in the U S , UK, and West Germany are compared as to applicability, cost, and accuracy The amount of testing or proof needed prior to a decision of diagnostics, consistency of results from laboratory models to test cell work and actual aircraft tests, and cost control are viewed as important Field testing of a diagnostic testing approach as early as possible is recommended, with further logic refinements and final touches to be added in service , R D V A77-41984 # New technology ATE in support of the YAH- 64 advanced attack helicopter D R Bartlett (RCA, Automated Systems Div, Burlington, Mass) and V F Cremonese (Hughes Helicopters, Culver City, Calif) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-896 12 p The U S Army advanced attack helicopter, YAH 64 is under development by Hughes Helicopters Avionic, air vehicle and mission subsystems of the YAH-64 present a broad spectrum of test requirements and will be supported at intermediate and depot levels using the Army's AIM/USM410 automated support system The AN/USM-410 is a new technology, general purpose ATE which uses its host computer to synthesize stimulus waveforms and analyze digital outputs from its sampled data measurement system Termed 'third-generation' ATE, the AIM/USM-410 will be van-mounted for deployment at aviation intermediate level (Author) A77-41985 # Simulation of turbine engine operational loads G M Mulenburg and J G Mitchell (ARO, Inc, Arnold Engineering Development Center, Arnold Air Force Station, Tenn ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando. Fla , July 11-13, 1977, AIAA Paper 77912 10 p 8 refs The Arnold Engineering Development Center (AEDC) has been working for four years on the definition and optimization of a new and unique test facility concept which will simulate flight maneuver loads on aircraft propulsion systems Contributions to the definition of test requirements have come from both the military and civil segments of the propulsion community This paper is intended as a progress report to interested parties and summarizes the planning and rationale which have led to the proposed facility performance and facility conceptual design The results of several Air Force and contractor studies are noted and the Turbine Engine Loads Simulator (TELS) is described (Author) A77-41986 ff Engine design decisions impact aircraft life cycle costs W Q Wagner (Teledyne CAE, Toledo, Ohio) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977, AIAA Paper 77-916 9 p 11 refs Contract No F33657-75-C-0606 This paper discusses the concept of design to life cycle cost (DTLC) as applied to propulsion subsystems of military aircraft It describes the resources necessary for DTLC effort during various engine life cycles, emphasizing the need for engine oriented LCC models Two examples of DTLC applications are cited, a deployed engine component study and a concept phase selection task These results highlight the need for both early attention and 'front end loading' to reduce propulsion - subsystem-affected elements of aircraft life cycle cost (LCC) (Author) A77-41989 # Advanced design procedure for aircraft engine selection J Eschweiler, F C Glaser, and R E Martens (McDonnell Aircraft Co, St Louis, Mo I American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11 13, 1977, AIAA Paper 77-953 10 p 7 refs A systematic and economical program for engine and airframe selection for advanced fighter aircraft is discussed, with attention given to the interactions between performance requirements, life cycle cost, and effectiveness During initial concept formulation, performance and cost are used as criteria in design development, and a computer based technique is employed to select engine variables (airflow schedule parameters, overall pressure ratio, and turbine inlet temperature) which meet performance and cost specifications while also minimizing gross takeoff weight Life cycle cost, including development, investment and maintenance costs, is also analyzed, and a second computer program is used to determine the most cost effective design The available techniques for assessing engine production cost yield sufficiently accurate estimates, however, long range cost variations encountered in modifying turbine inlet temperature need to be lessened Finally, to determine effectiveness of the selected design, the engine duty cycle, simulations for usage definition, and the impact of mission and environmental changes on the life of components are studied J M B A77-41990 # Life considerations in the engine design pro- cess R R Sellers and W F Zavatkay (United Technologies Corp , Pratt and Whitney Aircraft Group, East Hartford, Conn ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11 13, 1977, AIAA Paper 77954 4 p Life criteria m the engine design process is composed of anticipated steady endurance and cyclic life requirements Actual usage often differs from the anticipated due to the changing mission priorities, tactics, and even system application The sensitivity of turbine airfoil life to changing utilization is illustrated Potential approaches to reduce engine sensitivity to more stringent usage than that anticipated during the design process are suggested (Author) A77-41991 $ Simplified multi-mission exhaust nozzle sys- tem D J Dusa and A McCardle (General Electric Co , Cincinnati, 452 A77-42052 Ohio) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13. 1977, AIAA Paper 77-960 6 p For multi-mission aircraft applications, the exhaust nozzle operating conditions vary significantly during the mission In order to maintain high performance over the entire operating range of the aircraft the exhaust nozzle configuration becomes complex This complexity has a direct impact on weight, cost, and reliability Most current multi mission applications employ variable area convergent- divergent (C-D) nozzles to meet system requirements In the past, weight and performance have had the greatest influence on setting the exhaust nozzle design requirements However, cost has become a dominant factor in the procurement of weapon systems, therefore, a more balanced trade between life cycle cost, maintenance features, weight and performance is necessary in the selection process of exhaust systems A simplified variable area C-D exhaust nozzle system has been identified which addresses these factors This paper describes the design features of this simplified exhaust system and compares it with an existing exhaust system and other candidate simplified nozzles (Author) A77-42000 # The airjet distortion generator system - A new tool for aircraft turbine engine testing B W Overall and R E Harper (ARO, Inc , Arnold Engineering Development Center, Arnold Air Force Station, Tenn ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 13th, Orlando, Fla, July 11-13, 1977. AIAA Paper 77-993 9 p 6 refs An airjet distortion generator system has been developed to produce steady-state total pressure distortion at the inlet of turbine engines The system employs a method of injecting controlled amounts of high-velocity secondary air counter to the primary airstream to effect a local total pressure decay Digital computer control provides an on-demand distortion pattern capability The AJDG system is described, and the pattern-generating logic is presented Operational characteristics, turbulence, cycle times, and distortion pattern fidelity are discussed An engine stability assess- ment with comparison of stability response to screens and airjet- produced inlet distortion is included (Author) A77-42038 The impact of the energy crisis on the demand for fuel efficiency - The case of general aviation R B Archibald and W S Reece (US Department of Labor, Bureau of Labor Statistics, Washington, D C ) Transportation Research, vol 11, June 1977, p 161 165 17 refs One of the most important questions accompanying the debate over energy policy is whether or not consumers will react to increased fuel prices by choosing more fuel efficient transportation modes This paper addresses this question by developing a theoretical rationale for the hypothesis that the energy crisis has induced an increase in the demand for fuel efficiency as a characteristic of aircraft and empirically tests this hypothesis with data from the U S general aviation market (Author) A77-42039 Doppler m i s - The landing guidance system for the future J G Flounders (Plessey Co , Ltd , Weybridge, Surrey, England) Electronics and Power, vol 23, July 1977, p 556-558 The Doppler microwave landing system (D m I s) submitted by Great Britain to the International Civil Aviation Organization in response to their requirement for a new, nonvisual landing-guidance system is discussed Following a brief outline of the principle of operation of the D m I s, its advantages are examined The equip- ment is compact, can be quickly installed, and does not adversely affect the performance of existing instrument landing systems Its commutation is derived from the same crystal that controls the transmitter offset frequency, so that constancy of velocity is assured without necessitating critical adjustments in the field Since the D m I s technique uses sequential radiation of a uniform phase and amplitude along the elements of a linear array, there is great flexibility in the manner m which signals are processed The system can be adapted to handle a 360 deg azimuth signal with relative ease C KD A77-42044 The Analytical Maintenance ,Program - No more 'maintenance as usual' C T Faulders, Jr (U S Navy, Naval Air Systems Command, Washington, D C ) Defense Management Journal, vol 13, July 1977, p 1521 The Analytical Maintenance Program adopted by the U S Naval Air Systems Command is described Included in the program are provisions for establishment of maintenance requirements and schedules for each type of aircraft, assignment of maintenance tasks to various levels of operation, and a monitor and correction capability to insure effectiveness A detailed division of maintenance responsibilities is given, and decreases in the frequency of depot maintenance and the number of depot maintenance tasks, as well as in the frequency and number of organizational maintenance interven- tions, are reported Suggestions for implementing analytical main- tenance programs, including training of working engineers, coping with the shift from new to in-service aircraft maintenance, making the system cost effective, and emphasizing accountability of the various task forces, are also considered J M B A77-42049 Airport planning and economics - Some chang- ing perspectives J R Goodwin (FAA, Washington, D C ) Society of Automotive Engineers, Air Transportation Meeting, Washington, D C, May 10-12, 1977, Paper 770581 6 p Airport planners need to consider the effects of economic fluctuations on the accuracy of long-range projections of air traffic, and should plan adequate lead times for improving capacity in handling aircraft, passengers, baggage, and surface transport The FAA's Upgraded Third Generation Air Traffic Control System is discussed, and increased capacities attainable through its wake-vortex avoidance system, metering and spacing capability, and discrete address beacon system are mentioned Other problems confronting airport planners are considered, including the integration of public transport into airport transport systems, effects of environmental accountability legislation on airport development, and methods for choosing or arranging compromises between central, linear, or transporter design of airports J M B A77-42050 Wake turbulence detection and economic impact of proposed improvements W D Wood and I G McWilhams (U S Department of Transportation, Transportation Systems Center, Cambridge, Mass ) Society of Automotive Engineers, Air Transporta- tion Meeting, Washington D C, May 10-12, 1977, Paper 770583 8 p 5 refs Increased separations of aircraft following heavy jets, which have been mandated because of the threat posed by aircraft trailing wake vortices, have aggravated the problem of air traffic delays at some of the busier airports An extensive vortex measurement program at three major airports has provided the data base for the design of a Vortex Advisory System which will permit reduction of the vortex imposed separations under certain measurable wind conditions This system which promises to effect an appreciable reduction m traffic delay is currently undergoing testing at Chicago's O'Hare International Airport (Author) A77-42052 , Some aspects of mechanical instability prob- lems for a fully articulated rotor helicopter P Bellavita, C Giorgi, and M Galeazzi (Costruziont Aeronauttche Giovann Agusta Sp A, Cascma Costa, Italy) Deutsche Gesellschaft fur Luft und Raum- fahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20 22, 1976, Paper 40 p 6 refs Helicopter instability, particularly ground resonance, is studied using a combination of the method of Floquet and a direct integration method, which involves variable coefficients representing mechanical components and permits simulation of the landing dynamics The comb'ned method is applied to a model hydraulic damper, the model's behavior is investigated by systematic variation of individual components, such as geometry, valve flow, support stiffness, and spring hysteresis A flow chart for a computer program which approximates an equilibrium of flows and loads for the system is given Properties of elastomeric materials suitable for damper applications, including shear stress and hysteresis phenomena, are also evaluated These analysis of the damping system lead to a design proposal which involves a hydraulic piston damper lacking calibrated valves but having an open orifice coupled to the structure via elastomeric material J M B A77-43356 ,4' Ship landing trials with the BO 105 D Bender (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 16 p Helicopter testing and pilot training for landing helicopters on shipboard platforms at various ship speeds and in a variety of weather conditions (sea state, wind direction, wind force) are described An on land rolling platform employed for tests and training under controlled conditions is described and illustrated Experience with 90 landings on board vessels at sea is described and summarized Alternating mam rotor shaft bending moment, bending moment on rear port undercarriage cross tube, tailboom vertical bending moment, and vertical acceleration under pilot's seat are plotted vs angle of roll during touchdown R D V A77-43357 g Dynamic problems of unmanned tethered rotor platform Sea-Kiebitz with special regard to the landing W Benner (Dormer GmbH, Fnednchshafen, West Germany) Deutsche Gesellschaft fur Luft und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20 22, 1976, Paper 8 p The dynamics of an unmanned rotor observation platform tethered from a surface vessel, the pronounced influence of the tethering cable on the system dynamics, and advantages of a tethered rotor-hft/hover platform are discussed This 'Sea Kiebitz' system greatly increases the radar horizon and surface surveillance capability of the tethering vessel, while eliminating interference from masts and masthead antennas, mission height is 300 m, radar horizon about 60 km Automatic cable tension control, system dynamics in takeoff and ascent/loitering and surveillance/hauldown and landing, and system performance at high winds and high seas are dealt with R D V 464 A77-43365 A77-43358 fj HIFLAS - Helicopter infrared flight command and landing system W Dieter and U Rathmann (Elektronik System GmbH, Munich, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20 22, 1976, Paper 14 p The HIFLAS avionics package for all weather military helicopter operation with enroute navigation and no assistance from ground is described The package includes a BNS self contained navigation system, FLIR equipment for low altitude and napof-earth flying with forewarning of obstacles (including wires) and landing aids, and integrated display of all data including FLIR video Package structure, imaging sensor requirements, low-light optics (including imaging charge-coupled devices), symbol layout and information display spectrum, flight command modes (vertical and horizontal display modes), and detection range of representative ground obstacles are dealt with Possible future additions to the open-ended HIFLAS concept are indicated R D V A77-43359 # An experimental study on a combined outside world/instrument display for helicopter operation at night and in bad weather R Beyer (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Flugfuhrung, Braunschweig, West Germany) Deutsche Gesellschaft fur Luft und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 2022, 1976, Paper 18 p Helicopter test flights were performed by pilots using either conventional guidance instruments and visual assessment of meteo- rological conditions or a combined outside world and instrument display Features of the combined outside world instrument display system are described Factors taken into account in the 48 experimental flights run included roughness of the terrain and the pilot's knowledge of the course In addition, velocity, altitude, roll and pitch angles, and roll, pitch, and yaw rates were monitored Results indicate that with adequate training pilots were able to operate the helicopters equally well whether using visual assessment of meteorological conditions and conventional instruments or the combined display system alone Thus, the combined outside world instrument display may be a feasible guidance system for use during bad weather or night flights J M B A77-43360 # Ballistic and impact resistance of composite rotorblades K Brunsch and P M Wackerle (Messerschmitt-Bolkow- Blohm GmbH, Munich, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20 22, 1976, Paper 30 p 6 refs It has been found that the majority of rotor blade failures is related to an unforeseen occurrence of damage or to unexpected defects Such damage can be produced in connection with impacts involving moving or stationary barriers, birds, bullets, hail, and small particles A comparison of the properties of the materials employed for rotor blades shows the superiority of fiber reinforced plastics over metals with respect to dynamic resistance Attention is given to aspects of design and production technology, the influence of stress concentration on rotor blade fatigue life, the propagation of cracks caused by an impact on rotor blades, a fatigue test conducted with a tail rotor blade which had been damaged by a bullet, and an impact test involving tail rotor blades in contact with wooden rods G R A77-43361 ,?' Environmental reliability testing of helicopter systems B M M Faulkner (Westland Helicopters, Ltd, Yeovil, Somerset, England) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22. 1976. Paper 22 p A description is presented of the environmental reliability tests conducted with the Westland WG 13, Lynx helicopter The objec tives of reliability testing are examined, taking into account questions regarding the choice of a test rig framework, the selection of environmental conditions, and the choice of systems under test Previous reliability tests discussed are related to autopilot/ autostabihzer systems, a section of aircraft fuselage including all pilots controls, and a joint Anglo-French reliability trial Lynx reliability tests were carried out during the development phase from 1972 to 1974 and in connection with the production phase which began in 1976 G R A77-43362 * h Recent developments in rotary-wing aero- elasticity P Friedmann (California, University, Los Angeles, Calif ) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 35 p 65 refs Army-supported research, Grant No NCR 05-007-414 The purpose of this review is to present the research done in rotary wing aeroelasticity during the past eight years in a unified manner The following topics are reviewed with considerable detail (1) recent development in the aeroelastic modeling of the coupled flap-lag-torsional problem in hover (2) effect of unsteady aero- dynamics on the coupled flap lag-torsional aeroelastic problem in hover (3) the coupled flap-lag and the coupled flap-lag-torsional problem in forward flight (4) complete rotor and coupled rotor fuselage aeroelastic problems including both hmgeless and teetering rotors (Author) A77-43363 // A model for wind-tunnel rotorcraft research - Model design and test objectives B Gmelin (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Braunschweig, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 17 p 9 refs Factors underlying the design of components for a rotorcraft wind-tunnel test stand are discussed Transferability of the data to full-scale helicopters, using model scaling laws, is investigated The rotor drive system, geometrical scaling, handling of dimensionless ratios (Reynolds and Froude numbers, density and elasticity ratios), wind-tunnel interference effects, hover testing, and details of the wind-tunnel test program are covered An outline of future DFVLR rotorcraft wind-tunnel test programs is presented R D V A77-43364 •/ Recent experience in the testing of a gener- alized rotor aeroelastic model at Langley Research Center C E Hammond and W H Wel le r (US Army, Air Mobility Research and Development Laboratory, Hampton, Va ) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 20 p 8 refs The use of aeroelastically scaled helicopter rotor wind-tunnel models in establishing or verifying the dynamic characteristics of new or existing rotor designs is discussed A model, termed the generalized rotor aeroelastic model (GRAM), which has been developed for testing aeroelastically scaled rotor models is described, and the utility of the model in being able to test a variety of rotor systems to meet a broad range of test objectives is demonstrated through presentation of data from recent tests Data are presented from tests of an AH-1G Cobra model to determine whether or not the two-blade teetering rotor can experience stall flutter, tests of two wide chord teetering rotors to evaluate the effect of the wide chord on blade loads and rotor performance, and tests of a new four-blade flex hinge rotor configuration to provide information for the designer relative to its dynamic characteristics Recent tests of a variable geometry rotor are also described although final data are currently unavailable Since the GRAM was developed for testing in a wind tunnel which has the capability of using Freon-12 as a test medium, some of the advantages of Freon 12 for testing of aeroelastically scaled models are also discussed (Author) A77-43365 ff Studies on rotor and flight dynamics of a horizontally stoppable hmgeless rotor aircraft H Huber and H Krafka (Messerschmitt Bolkow Blohm GmbH, Munich. West Ger- many) Deutsche Gesellschaft fur Luft- und Raumfahrt. European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 21 p 465 A77-43366 The concept of a V/STOL aircraft with two horizontally stoppable rotors in a side-by-side arrangement is described, and some initial investigations on the control and stability of the aircraft during transition and conversion phases are reported These studies included isolated rotor tests to determine the influence of rotor thrust, flight speed, and rotor speed, and tests on the whole aircraft to study the trim characteristics in the level flight speed range from hover to 250 km/h and the full rotor speed range Theoretical results on the aircraft lift slope, pitch rate damping, static longitudinal stability, and speed stability are given Results of dynamic simula- tions of transition and conversion are presented P T H A77-43366 ff Aircraft of wide speed and manoeuvering range G Kannamuller and E Oberdorffer (Dormer GmbH, Fried richshafen. West Germany) Deutsche Gesellschaft fur Luft und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd. Buckeburg, West Germany, Sept 20 22, 1976, Paper 15 p 8 refs The technical concept of an aircraft of wide speed and maneuvering range is described The three main features are (1) shrouded, single stage fan with horizontal rigid intake, (2) thrust vectoring by an efficient deflector system, and (3) optimal Integra tion of thrust deflector and wing Four different thrust deflector systems under consideration and six possible configurations for the propulsion system are briefly described Brief comments on various aspects of operational capabilities of the aircraft are made P T H A77-43367 # The shrouded tail rotor 'Fenestron' M Lafargue (Societe Nationale Industnelle Aerospatiale, Division Heli- copteres, Paris, France) Deutsche Gesellschaft fur Luft- und Raum- fahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 18 p Advantages of a shrouded rotor integrated into the tail fin ('Fenestron' configuration) are reviewed, and a description is given of two Aerospatiale rotorcraft incorporating that feature All-weather flight safety, vulnerability to small arms fire and encounters with trees, noise abatement and comfort enhancement, protection of the tail rotor against foliage, stones, curious or incautious bystanders at landings, maneuverability and flying/handling qualities, weight and cost, hover performance, and design simplifications in the shrouded tail rotor vehicles are described Advantages of an antitank rotorcraft loitering under foliage cover with tail rotor so protected are pointed out R D V A77-43368 # Helicopter icing - A problem to be defined H B Lake (RAF, London, England) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 8 P The status of research on helicopter icing and de icing is surveyed, and found to lack credible supporting theory or acceptable data base More progress has been made on combatting windshield icing, some progress on dealing with engine icing and ice mgestion, but the problem is 'not defined' in the case of rotor icing Meteorological understanding of low-altitude ice and snow is inadequate, the amount of icing that a rotor can tolerate is still obscure, and empirical data on 100%/mm increases in the torque on unprotected rotors during icing are unsettling Radar and atmo spheric sampling probes of ice clouds do not yield reliable data Problems in all-weather certification of rotois and helicopters are discussed, with particular emphasis on pressures exerted on certifica- tion engineers by project managers R D V A77-43369 !/ A model for windtunnel rotorcraft research - Ground resonance investigations H -J Langer, R Schroder (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Flugmechamk, Braunschweig, West Germany), and F Kiesslmg (Deutsche Forschungs- und Versuchsanstalt fur Luft und Raumfahrt, Institut fur Aeroelastik, Gottmgen, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 12 p To describe mathematically the ground resonance of a simulated rotorcraft, a system having equivalent vibration characteristics is defined and analyzed Natural frequencies, eigenforms, generalized mass, and damping values are determined experimentally for the rotor support stand For the rotor itself, a transfer matrix is used to calculate the natural lagging frequency of the blade, the state variables for the equation of motion are determined using an equivalent rotor system for simplicity An equation of motion for the ground resonance which takes into account both rotor and support-stand vibrations is then obtained The combination of experimental and analytical evaluation is found to yield good predictions of the simulated rotorcraft's stability J M B A77-43370 # The relative importance of acoustic sources generated by helicopter rotors in high speed flight S E Wright Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 2022, 1976, Paper 16 p 8 refs A simple easy to use linear source theory is described This theory represents most of the essential radiation properties of sources in arbitrary motion, including circular and helical motion appropriate to hover and forward flight Possible sources of helicopter noise in high speed flight are then assessed, with particular reference to blade displacement, steady blade forces, unsteady blade forces and fluid stresses It appears that unsteady blade forces are the most likely source of rotor noise, at least for present day forward flight speeds (Author) A77-43371 » Main and tail rotor interaction noise during hover and low-speed conditions E Laudien (Messer schmidt Bolkow Blohm GmbH, Munich, West Germany) Deutsche Gesellschaft fur Luft und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 2nd, Buckeburg, West Germany, Sept 20-22, 1976, Paper 16 p 12 refs A measured spectrum of a BO 105 rotorcraft in partial power descent is illustrated and analyzed Flight conditions and recording of impulsive noise signals, and effect of light wind and partial power descent on hover flight, are discussed Interaction noise resulting from intersection of the tip vortex from a preceding blade by the mam rotor blade in hover flight under light wind was investigated Analysis of recorded noise signals revealed up to 20 tail rotor harmonics for tail rotor interaction noise, and over 50 harmonics for mam rotor impulsive noise R D V A77-43393 XF-19 EW suite R Hartman Military Elec- tronics/Countermeasures, vol 3, July 1977, p 13, 18, 69, (3 f f ) Electronic warfare (EW) hardware organization in the projected XF-19 U S STOL fighter-bomber is described and characterized The XF-19 is designed for forward area tactical interception of hostile aircraft and missies, or for tactical close air support, with capability of operating from unimproved/mimmal/damaged runways, or small ships The phased array IR warning system, rack-mounted placement of EW modules, responses to hostile treats, detect/preamp/presort equipment, jamming and smart chaff dispensing, and anti-track laser systems are outlined Limitations imposed by aircraft blind spots, volume and weight penalties, and exorbitant sensitivity (with indiscriminate acquisition of threats and swamping of the system) are considered, in addition to difficulties in transferring signal mforma tion and commands to the jammer R D V A77-43399 National Airlines Fuel Management and Allocation Model D W Darnell (National Airlines, Inc. Miami, Fla ) and C Lofhn Interfaces vol 7, Feb 1977, p 1 16 Tne Fuel Management ard Allocation Model determines the optimal strategy for fueling aircraft and can be used to support both short and long-term planning It has been used operationally by the Fuels Management and Flight Control Departments of National Airlines for over two years, resulting in multi million dollar savings 466 A77 43619 The model specifies the best fueling station and vendor for each flight, based on prices, availability, fuel burn, flight data, and cost of tankerage The model also uses extensive sensitivity analysis tech- niques to alert management as to when a new policy may be required (Author) A77-43468 ff Determination of the components of the specific force of a gravimeter for the general case of a moving base (Opredeleme sostavliaiushchikh udel'noi sily gravimetra v obshchem sluchae podvizhnogo osnovaniia) E N Bezvesil'naia and S L Riabykin (Kievskn Pohtekhmcheskn Institut, Kiev, Ukrainian SSR) Vychislitel'naia i Pnkladnaia Matematika, no 30, 1976, p 147-153 In Russian Equations are presented for the components of the specific force of a gravimeter which are pertinent to an aviational gravimetric system which can be used in the determination of gravitational anomalies The functional subsystems of the gravimetric system consist of the gravimeter, stabilization system, navigation system, altimeter, and computer M L A77-43576 The electromagnetic autonavigation system /the EMAN system/ (Das Elektromagnetische Autonavigationssystem /EMAN-System/) A Seeger Ortung und Navigation, no 2, 1977, p 1 10 In German An apparatus used for electromagnetic direction and velocity determination is described The principle of its operation involves the Hall effect and induction The device is intended for use in flights that would require readjustment of the magnetic compass gyro scopic compass system, or in situations when that system is not convenient M L A77 43577 Automatic correction of position error by means of a digital correlation of surface structures (Automatische Korrektur von Positionsfehlern durch digitale Korrelation von Oberflachenstrukturen) Mr Hessel and Mr Eckl (Messerschmitt Bolkow-Blohm GmbH, Munich, West Germany) Ortung und Naviga tion.no 2, 1977, p 63-89 17refs In German A navigation system is considered which involves the com parison of actual images of the earth's surface features with reference images Location would be determined by the correlation maximum A simulation procedure is described which would determine the characteristics of such a system, choose a suitable correlation algorithm, and estimate the necessary computational and storage capacity The results of this simulation procedure are presented M L A77-43578 The vehicle mapping device FKG-1, a device for indicating the location of land vehicles and helicopters on the map (Das Fahrzeugkartengerat FKG-1, em Gerat zur Anzeige des Standortes von Landfahrzeugen und Hubschraubern in der Karte) K Ramsayer (Stuttgart, Universitat, Stuttgart, West Germany) Ortung und Navigation, no 2, 1977, p 91 95 In German A77-43598 f. Reduction of exhaust smoke from gas-turbine engines by using fuel emulsions II C A Moses (Southwest Research Institute, San Antonio, Tex ) Comoustion Institute, Fall Meeting, La Mia, Calif. Oct 18-20, 1976, Paper 76-34 27 p 27 refs Contracts No N00150-74-C-1717, No N68335-76-C-1136 A stabilized low-internal-phase-ratio emulsion of water in oil is used to promote abatement of exhaust smoke from on-ground gas turbine test engines The emulsifying mechanism, which involves selective vaporization of the internal phase during the period of droplet heating, followed by a sudden lowering of pressure, is described, a variety of water/fuel ratios are studied, with the aim of providing the maximum smoke reduction while retaining high combustor efficiency Emulsions composed of 15% and 30% water/ fuel ratios are tested throughout the engine power range, and smoke reductions are observed at all power points The greatest reductions are noted at the highest power points where the smoke problem is greatest Combustion efficiency is calculated, and found to be minimal at full power, but significant at lower power levels Data on gaseous exhaust emissions are also given J M B A77-43604 /.' Theory of automatic aircraft power plant control Air-breathing engines (Teorna avtomaticheskogo upravlenna silovymi ustanovkami letatel'nykh apparatov Upravleme VRD) lu S Belkm. L N Getsov, lu V Kovachich, lu A Litvmov, T S Mart'ianova. S A Sirotm, G P Stepanov, A V Forafontov, and A A Sheviakov Moscow, Izdatel'stvo Mashmostroeme, 1976 344 p 134 refs In Russian Theoretical methods used to study the dynamics of aircraft power plants and to analyze possible automatic control systems for aircraft engines are presented Mathematical models of power plants with gas turbine engines of different types are outlined The methods used to investigate control systems for power plants with iet engines in single-shaft, double-shaft or by pass configurations are given, and results are reported Characteristics of hydraulic, electronic, com- bined control systems and of on-board computer systems are reviewed, and approaches used in assessing the reliability of these systems are discussed C K D A77-43610 // Unsteady processes in aircraft piston com- pressors (Nestatsionarnye protsessy v porshnevykh kompressorakh letatel'nykh apparatov) B M Ryzhov Moscow, Izdatel'stvo Mashi- nostroeme, 1976 180 p 18 refs In Russian Unsteady thermodynamic processes taking place in aircraft piston compressors are discussed The energy parameters, operation and vacuum regime of piston compressors and the kinematics and construction of the crankshaft-swashplate mechanism are examined A method for analyzing the energy parameters of a pneumatic piston compressor is presented C K D A77-43612 ;7 Low-temperature heat pipes for aircraft (Nizkotemperaturnye teplovye truby dlia letatel'nykh apparatov) V G Voronin, A V Reviakin, V la Sasm, and V S Tarasov Moscow, Izdatel'stvo Mashmostroeme, 1976 200 p 31 refs In Russian The theoretical basis of heat and mass transfer processes in low-temperature heat pipes operating at temperatures from minus 200 to plus 300 C is presented Methods used to predict the parameters of heat pipes with different configurations and different conditions of operation are outlined The construction and control of heat pipes are discussed, and present and possible future applications of heat pipes in aircraft and spacecraft in heat regulation air conditioning, and life support systems are considered C K D A77-43617 H Chemical power sources in aviation (Khimi- cheskie istochn.ki toka v aviatsn) V A Prituhuk Moscow, Voemz- dat, 1976 88 p 9 refs In Russian The principles of operation and construction of different types of primary and secondary cells used in ground support activities in aviation are reviewed These include manganese-zinc, silver-zinc, acid, and alkali nickel-cadmium cells The performance characteristics of each type of cell are presented, and the advantages and applications of each cell are discussed Undesirable properties are described, and means of eliminating or mitigating them are considered CKD A77-43619 # Equivalent testing of gas turbine engines (Ekvi- valentnye ispytanna gazoturbmnykh dvigatelei) N D Kuznetsov and V I Tseitlin Moscow, Izdatel'stvo Mashmostroeme, 1976 216p 73 refs In Russian Tne problem of estimating and increasing the service life of gas turbine engines is the subject of this book The relevant thermo- mechamcal properties of engine materials are studied, and methods of measuring, predicting, and increasing the service life of individual engine components are examined These investigations serve as a basis for planning programs of equivalent accelerated tests of gas turbine engines for service life P T H 467 A77-43657 A77-43657 Aviation system planning D L Rubin (COMSIS Corp , Wheaton, Md ) Transportation Engineering, vol 47, June 1977. p 1618 8 refs Research supported by the US Department of Transportation and Federal Highway Administration The approach which has been used by the State of Maryland in planning for future airport needs is described Airports are con- sidered as competitive attractions, and aircraft and air passenger forecasts are generated on the basis of the socioeconomic charac tenstics of small geographic units Aircraft and air passengers are assigned to airports by computer modeling techniques C K D A77-43726 * # Minimum required capture radius in a coplanar model of the aerial combat problem J V Breakwell (Stanford University, Stanford, Calif ) and A W Merz (Aerophysics Research Corp , Mountain View, Calif ) AIAA Journal, vol 15, Aug 1977, p 10891094 5 refs Contract No NAS2 9223 Coplanar aerial combat is modeled with constant speeds and specified turn rates The minimum capture radius which will always permit capture, regardless of the initial conditions, is calculated Th.s 'critical' capture radius is also the maximum range which the evader can guarantee indefinitely if the initial range, for example, is large A composite barrier is constructed which gives the boundary, at any heading, of relative positions for which the capture radius is less than critical (Author) A77-43727 * # Optimization of flexible wing structures sub- ject to strength and induced drag constraints R T Haftka (Illinois Institute of Technology, Chicago, III I AIAA Journal, vol 15, Aug 1977, p 1101-1106 13 refs Grant No NsG 1266 An optimization procedure for designing wing structures subject to stress, strain, and drag constraints is presented The optimization method utilizes an extended penalty function formulation for converting the constrained problem into a series of unconstrained ones Newton's method is used to solve the unconstrained problems An iterative analysis procedure is used to obtain the displacements of the wing structure including the effects of load redistribution due to the flexibility of the structure The induced drag is calculated from the lift distribution Approximate expressions for the constraints used during major portions of the optimization process enhance the efficiency of the procedure A typical fighter wing is used to demonstrate the procedure Aluminum and composite material designs are obtained The tradeoff between weight savings and drag reduction is investigated (Author) A77-43735 * # A computationally fast one-dimensional diffusion-photochemistry model of SST wakes G L Mat! off and M I Hoffert (New York University, New York, N Y ) AIAA Journal, vol 15, Aug 1977, p 1205-1207 14 refs Grant No NsG 1298 A computational technique applicable to analysis of supersonic transport (SST) wake photochemistry and diffusion is presented Sensitivity studies of SST effluent effects upon ozone depletion are facilitated by the computational rapidity of the method The article compares results from other studies and predictions of some variables related to global NOx input Results indicate that the NO/NO2 ratio in an SST wake at photochemical equilibrium is a sensitive function of photolysis rates R D V A77-43737 * jj Low Reynolds number flow past a blunt axisymmetric body at angle of attack A Kumar (NASA, Langley Research Center, Hampton, Va , National Research Council, Wash- ington, DC) AIAA Journal, vol 15, Aug 1977, p 1212-1214 8 refs Low Reynolds number flow of an ideal gas over a blunt axisymmetric body of large half-angle at small angles of attack is investigated, for the case of laminar hypersonic flow Time varying viscous shock layer equations describing the flowfield are obtained from the full Navier-Stokes system by keeping terms to second order in the inverse square root of Re in both viscous and inviscid regions, the equations are valid for moderate to high Re Drag, skin friction, and heating rates were obtained at small (or zero) angles of attack Conditions experienced by planetary entry probes during the high-altitude (early) legs of an atmospheric entry trajectory are pertinent to the problem RDV A77-43771 * Linear regulator design for stochastic systems by a multiple time-scales method D Teneketzis and N R Sandell, Jr (MIT, Cambridge, Mass) IEEE Transactions on Automatic Control, vol AC 22 Aug 1977, p 615621 32 refs Grant No NGL 22-009-124, Contract No E(49 18) 2087 This short paper develops a hierarchically structured, suboptimal controller for a linear stochastic system composed of fast and slow subsystems It is proved that the controller is optimal in the limit as the separation of time scales of the subsystems becomes infinite The methodology is illustrated by design of a controller to suppress the phugoid and short period modes of the longitudinal dynamics of the F-8 aircraft (Author) A77-43832 ff Blast from aircraft guns at subsonic and supersonic speeds D G Mabey and D S Capps (Royal Aircraft Establishment, Bedford, England) In International Symposium on Ballistics, 3rd, Karlsruhe, West Germany, March 2325, 1977, Proceedings Pfinztal, West Germany, Institut fur Chemie der Trieb- und Explosivstoffe, 1977, p 86 1 to B6-14 11 refs There is currently considerable interest in the influence of gun blast on military aircraft but few reliable measurements are available to the aircraft designer A theory to estimate the approximate level and duration of these blast loads for both static and moving aircraft was outlined by Smith at a previous conference (1974) This paper presents a brief outline of the theory and summary of wind tunnel measurements made to verify it In the experiment, a 7 62 mm caliber rifle was fired in the RAE 3 ft x 3 ft wind tunnel over the speed range from M = 0 to 18, and over a wide range of static pressures (representing altitude variations) The blast wave arrival times and the local static pressure ratios were measured by transducers mounted on an adjacent plate, offset at spacings of 10, 20, and 30 calibers These measurements were generally well correlated by Smith's theory, both with respect to the variation of speed and pressure However, downstream of the muzzle discrepan- cies between the measurements and the theory increased with speed, particularly when the plate was closest to the gun (Author) A77-43923 // Convective heat and mass transfer in a hyper- sonic near wake (Konvektivnyi teplomassoobmen v gtperzvukovom btizhnem slede) L I Skurin and A V (urkov (Lemngradskti Gosudarstvennyi Universitet, Leningrad, USSR) In Heat and mass transfer - V, All-Union Conference on Heat and Mass Transfer, 5th, Minsk, Belorussian SSR, May 17 20, 1976, Proceedings Volume 1, Part 2 Minsk, AN BSSR Institut Teplo i Massoobmena, 1976, p 140147 In Russian Some aspects of calculating the viscous near wake behind a hypersonic blunted body are examined, treating the disturbed area as a gas mixture formed by physicochemical transformations The near wake is a relatively narrow region characterized by pronounced changes in the direction of the lines of flow in the presence of strong viscosity effects It is proposed to simplify the calculations by assuming that dynamic and thermal effects, rather than the effects of chemical reactions, influence the pressure distribution, the mean mass velocity, and enthalpy, and to calculate these characteristics without allowance for physicochemical transformations, substituting a certain effective flow of a perfect gas for the ac'ual source V P A77-43928 „ Study of a nomsothermal axisymmetric near wake (Issledovame neizoternncheskogo osesimmetrichnogo blizhnego sleda) V E Aerov B A Kolovandin, G G Starobmets, N N Luchko, and lu M Dmitrenko (Akademna Nauk Belorusskoi SSR, Institut Teplo i massoobmena Minsk, Belorussian SSR) In Heat and mass transfer V, All Union Conference on Heat and Mass Transfer, 5th, Minsk, Belorussian SSR, May 1720, 1976, Proceed ings Volume 1, Part 2 Minsk AN BSSR Institut Teplo-i Massoobmena 1976, p 192196 In Russian 468 A77-44094 A mathematical model and numerical solution method for a nomsothermal turbulent jet flow with zero excess momentum are presented The motor is located on the axis of symmetry of the resistance source consisting of a body of revolution To determine initial conditions and to verify the solution, an experimental study of the near region of an axisymmetric nomsothermal turbulent wake with zero excess momentum was carried out P T H A77-43993 # Calculation of radiant cooling of air behind intense shock waves using mean optical characteristics (Raschet radiatsionnogo okhlazhdenna vozdukha za sil'nymi udarnymi volnami s ispol'zovaniem srednikh opticheskikh kharaktenstik) V P Zamuraev, I I Maslennikova, and R I Soloukhin (Akademna Nauk SSSR, Institut Teoretitheskoi i Prikladnoi Mekhaniki, Novosibirsk, USSR) In Heat and mass transfer - V, All-Union Conference on Heat and Mass Transfer, 5th, Minsk Belorussian SSR May 17-20, 1976, Proceedings Volume 8 Minsk, AN BSSR Institut Teplo- i Massoobmena, 1976, p 196-205 8 refs In Russian The mean absorption coefficients of air are calculated for the temperature range 10,000 20,000 K and at pressures of 0 1-100 atm These mean coefficients are used to calculate the radiant cooling of air behind shock waves at velocities of 12 and 18 km/s and static pressures of 10 to the -3rd to 10 to the -5th atm B J A77-44078 Monolithic wing design. M A Bogomol'nyi (Aviatsionnaia Tekhnika, vol 19, no 4 1976, p 1 7 2 2 ) Soviet Aeronautics, vol 19, no 4. 1976, p_ 11-15 8 refs Translation A swept monolithic wing with longitudinal spar webs, subiected to a constant distributed force is examined A steepest descent algorithm is proposed for determining the number of webs and the web and skin thicknesses (variable over the wing span) for which the weight, deflection, the induced stresses in the skin, and the shear stresses in the webs satisfy the design constraints (derived in the form of inequalities) The results of a numerical solution to the problem of analytical wing design are examined, along with means of reducing computer time V P A77-44079 Analytic design of flight vehicle alighting gear with random scatter of initial conditions and structural parameters A I Bogomolov, lu P Gorshenin, A V Svilm, and T K Sirazetdmov (Aviatsionnaia Tekhnika, vol 19, no 4, 1S76, p 2 3 2 6 ) Sower Aeronautics, vol 19, no 4, 1976, p 1619 Translation A77-44083 Determining gas turbine engine tolerance monitoring parameters lu V Kozhevmkov and M Kh Bikchantaev (Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 5359) Soviet Aeronautics, vol 19, no 4, 1976, p 42-47 Translation In the present paper, the tolerances of gas turbine engine parameters are determined from the condition of least total losses Formulas for calculating the probability of erroneous and correct acceptance-inspection solutions are proposed, along with formulas for the normal error distribution The special case of determining parameter tolerances from the condition of least measurement error probability is discussed V P A77-44085 The aircraft cabin as a temperature-controlled plant V I Krutov and A V Shcherbakov (Aviatsionnaia Tekhnika, vol 19, no 4, 1976. p 63-67 I Sower Aeronautics, vol 19, no 4, 1976, p 51-53 Translation A system of differential equations describing the thermal processes occurring in the passenger compartment is derived The number of equations in this system depends on the number of wall and equipment elements with identical heat accumulating and insulating properties, that must be taken into consideration in each case An operator relation, written in dimensionless form, which describes the dependence of the compartment temperature on perturbing factors is obtained The relation yields the general and particular (with specific assumptions) transfer functions of the mathematical model of the compartment The use of the transfer functions is demonstrated The results are useful in designing aircraft temperature regulating systems V P A77-44086 Influence of flight vehicle mission on optimal GTE powerplant parameters V G Maslov, S K Bochkarev, and V S Kuz'michev /Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 68-74 ) Sower Aeronautics, vol 19, no 4, 1976, p 54 59 6 refs Translation The dependence of accepted criteria for evaluating the engine/ aircraft system on the gas-turbine engine parameters is examined Equations relating the weight, cost-effectiveness, and air technical criteria to the specific weight and specific fuel consumption of gas-turbine engines are derived, along with equations interrelating the optimal engine parameters for various evaluation criteria and various flight ranges V P A77-44087 Empennage snapthrough stability and vibra- tions in supersonic flow V A Pavlov (Aviatsionnaia Tekhnika, vol "19, no 4, 1976, p 75 78 ) Sower Aeronautics, vol 19, no 4, 1976, p 60-62 5 refs Translation 'Snapping vibrations' are understood to mean a type of natural vibrations associated with the transition from subcntical to super- critical stable equilibrium and vice versa The vibrations are as- sociated with forces acting at the middle surface of the tail unit that arise in the presence of simultaneous deformations of the vertical fin and (deviated) rudder The analysis of the stability of tail surfaces and their snapping vibrations, carried out in the present paper, leads to differential equations, with nonlinear potential and kinetic energy terms, which are solved by the Bubnov-Galerkm method The ' solutions of the vibration and stability equations are used to determine the critical flow rate at which snapping vibrations may set in VP A77-44088 On invanance of the disturbed longitudinal motion of VTOL airplane with vectored control system V I Pentiukhov (Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 79-81 ) Soviet Aeronautics, vol 19, no 4, 1976, p 6365 Translation The thrust-vector control system discussed was developed, on the basis of a combinational principle proposed by Petrov (1967), for controlling the longitudinal motion of VTOL aircraft The transfer coefficients of the system are determined which ensure invanance of normal acceleration and angle of pitch and also the simultaneous invanance of the angle of pitch and normal acceleration with respect to vertical gusts The obtained value of the transfer coefficients are shown to be functions of the aerodynamic characteristics of the VTOL aircraft, of the time constant of the lift engines, and the flight altitude and velocity V P A77-44091 Construction of stable programmed flight vehi- cle motion V A Sgilevsku (Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 9297 ) Soviet Aeronautics, vol 19, no 4, 1976, p 74 78 Translation The equations of flight-vehicle motion programmed with allow- ance for deviations are derived The conditions for programmed flight stability are analyzed on the basis of a Liapunov function The equations derived are written in generalized parameters characteristic of a large family of flight vehicles and engines V P A77-44094 Analysis of slightly-conical small-aspect-ratio wings beyond the proportional limit V G Shataev and A S Kretov (Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 106-111 ) Sower Aeronautics, vol 19, no 4, 1976. p 86-90 7 refs Translation A vanational technique is proposed for nonumformly heated thin-walled stub wings allowance for the nonlmearity of the stress-strain diagrams of the load-carrying members The method is based on the assumption that the cross-section contour is non- deformable and that the skin and spar webs operate in shear and the longitudinal ribs in tension Numerical example computations show that the approximation accuracy improves with increasing plastic deformation V P 469 A77-44097 A77-44097 Influence of middle-surface curvature on stress state of low-aspect-ratio wing V L Glezer, A I Danilm.andV A Komarov (Aviatstonnata Tekhnika, vol 19, no 4, 1976, p 123125) Soviet Aeronautics, vol 19, no 4, 1976, p 100-102 7 refs Translation The influence of a curved middle surface is evaluated by applying the finite element method to a set of programs for simulating the wing geometry It is shown that this curvature leads to appreciable symmetry breakdown in the stress distribution between the upper and lower panels of the wing Possible reasons for this phenomenon are examined It is shown that calculations with allowance for middle-surface curvature lead to improved agreement with the experiment V P A77-44100 Analytic construction of 'aerodynamic profile' curves E M Shanin and V A Osipov (Aviatsionnaia Tekhnika, vol 19, no 4, 1976, p 132135) Soviet Aeronautics, vol 19, no 4, 1976, p 110-113 Translation Analytical methods of designing plane contours from the prescribed geometrical characteristics, on the basis of a family of strophoidal curves are discussed A simple method of controlling the shape of curves is proposed, and a technique for shaping airfoil surfaces by deforming the cross sections is demonstrated V P A77-44291 # Simulation and data analysis of a scanning laser Doppler velocimeter system for sensing aircraft wake vortices J A L Thomson and J C S Meng (Physical Dynamics, Inc , Berkeley, Calif ) In Minnesota Symposium on Laser Anemometry, Bloomington, Minn, October 22-24, 1975, Proceedings (A77 44283 20-35) Minneapolis, University of Minnesota, 1976, p 231-276 5 refs The paper discusses the spectral signal characteristics of coaxial scanning laser Doppler velocimeter systems which are relevant to the modeling of the response of such systems to simulated and actual aircraft vortex wakes transported through the atmosphere Some examples of the analyse of the measurements on real and simulated wakes are presented P T H A77-44294 * ft Wind tunnel flow seeding for laser velocimetry applications M K Mazumder, C W Blevins, and K J Kirsch (Arkansas, University, Little Rock, Ark ) In Minnesota Symposium on Laser Anemometry, Bloomington, Minn, October 22-24, 1975, Proceedings Minneapolis, University of Minnesota, 1976, p 327341 12 refs Grant No NGL-04-001-007 Flow-seeding requirements for wind tunnel studies of subsonic and transonic flow fields are discussed with reference to laser velocimeter applications Design of an aerosol generator with an output flow rate of 60 scfm is presented The generated aerosol is fairly monodisperse, tracer partic'e diameter can be varied from 0 2 to 0 5 micron, and seeding density can be varied from 100 to 10,000 particles/cu sec Experimental data on the use of this aerosol generator with various aerosol injection mechanisms indicate that the method is suitable for wind tunnel flow seeding (Author) A77-44295 * ff' Development of a controllable particle genera- tor for LV seeding in hypersonic wind tunnels W V Feller (NASA, Langley Research Center, High Speed Aerodynamics Div , Hampton, Va ) and J F Meyers (NASA, Langley Research Center, Instrument Research Div , Hampton, Va ) In Minnesota Symposium on Laser Anemometry, Bloomington, Minn, October 22-24 1975, Proceed- ings Minneapolis, University of Minnesota, 1976 p 343-357 7 refs The paper describes the considerations that went into the development of a controllable particle generator tor laser velocimeter seeding'in a hypeisomc wind tunnel operating at 345 million N/sq m, 533 K, and stieam speed of about 1000 m/sec Operating conditions determined the choice of a silicone oil as the material, and the requirement that the particle follow the flow within a certain accuracy range put constraints on the allowable particle size range The principle of the particle generating device chosen was that of the LaMer generator, in which a liquid is f irst vaporized mixed with the carrier gas, and then condensed under carefully controlled con- ditions Prehmmaiy results of studies on the effect of various apparatus parameters on the particle median diameter are given P TH A77-44301 * ft Modular high accuracy tracker for dual chan- nel laser Doppler velocimeter J D Fridman R M Young, R E 'Seavey (Raytheon Equipment Development Laboratories. Sudbury, Mass ), and K L Orloff (NASA, Ames Research Center. Moffett Field, Calif ) In Minnesota Symposium on Laser Anemometry, Bloomington, Minn , October 22-24, 1975, Proceedings Minneapolis, University of Minnesota, 1976, p 485503 5 refs In the study described, a scanning dual channel cross beam laser Doppler velocimeter (developed for measuring simultaneously the two orthogonal components of flow velocity and turbulence intensity) was used to measure the instantaneous velocity charac- teristics of a model helicopter rotor and in a vortex wake survey experiment on a Boeing 747 aircraft model Particular attention is given to a special purpose dual loop frequency tracker developed to track and demodulate 10 microsecond wide pulse burst Doppler signals with a study cycle of 25% (or narrower signals at a higher duty cycle) generated by the laser Doppler velocimeter V P A77 44304 * £' Laser velocimeter turbulence spectra measure- ments J C F Wang (General Electric Co Schenectady N Y ) In Minnesota Symposium on Laser Anemometry, Bloomington Minn , October 2224, 1975, Proceedings Minneapolis, University of Minnesota, 1976 p 538-567 5 refs Contract No NAS1-12895 A unique laser velocimeter system employing a digital frequency-counter has been developed by the General Electnc Company's Corporate Research and Development undei sponsorship of NASA/Langley This system has been successfully developed for measurements of turbulence spectra in jet exhaust flows This paper describes the LV spectra data acquisition system and discussions on the important parameters in the spectra analysis procedure Results from computer simulation and actual jet flow tests are reported Reasonable agreement was obtained between the experimental measurements and the predictions from error analysis of the LV processor (Author) 470 IM77-28069 STAR ENTRIES N77-28061*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va COMPARISON OF VGH DATA FROM WIDE-BODY AND NARROW-BODY LONG-HAUL TURBINE-POWERED TRANSPORTS John A Zalovcik Joseph W Jewel Jr and Garland J Morris Washington Jul 1977 41 p refs ' " (NASA-TN-D-8481 1-11381) Avail NTIS HC A03/MF A01 CSCL 02A Data are presented on incremental normal accelerations due to gusts operational maneuvers and check flight maneuvers derived gust velocities and the airspeed and altitude operating practices of one type of wide body long haul transport airplane flown by five airlines on international routes These data are compared with VGH data obtained from long haul narrow body transport airplanes also flown over international routes Author N77-28063*# Rail Co Baltimore. Md MAINTENANCE COST STUDY OF ROTARY WING AIRCRAFT Jun 1977 159 p (Contract NAS2-9143) (NASA-CR-152003) Avail NTIS HC A08/MF A01 CSCL 05C The feasibility was studied of predicting rotary wing operation maintenance costs by using several aircraft design factors for the aircraft dynamic systems The dynamic systems considered were engines drives and transmissions rotors and flight controls Multiple regression analysis was used to correlate aircraft design and operational factors with manhours per flight hour and equations for each dynamic system were developed Results of labor predictions using the equations compare favorably with actual values F 0 S N77-28064# Naval Aviation Integrated Logistic Support Center. Paluxent River Md PROCEDURE FOR THE DEVELOPMENT OF NAVAL AVIATION MAINTENANCE OBJECTIVES William F Lavallee Philip Seidenberg Walter J Light Brian P Sneade and James E Ervm 18 Feb 1977 34 p refs (AD-A038201, NAILC-03-47X) Avail NTIS HC A03/MF A01 CSCL 15/5 This document describes a methodology for developing Naval Aviation Maintenance Objectives These objectives when accomplished are intended to provide for an effective aviation maintenance establishment in support of naval aviation'and the Chief of Naval Operations objective of fleet readiness through the 1977-1985 time frame GRA N77-2806S California Inst of Tech Pasadena EXPERIMENTAL INVESTIGATION ON AXISYMMETRIC TURBULENT WAKES WITH ZERO MOMENTUM DEFECT Ph D Thesis Hiroshi Higuchi 1977 225 p Avail Univ Microfilms Order No 77-3131 An experimental investigation of a turbulent axisymmetnc wake with zero momentum defect was carried out The experiment was conducted in a low speed wind tunnel with a circular tube mounted parallel to the stream A controlled amount of air was injected into the stream at the end of the model to cancel the drag produced by the turbulent boundary layer on the model The measurements on the mean flow and the fluctuation quantities were carried up to 90 diameters downstream By adjusting the strength of the injection, the behavior of the pure wake the coflowing jet and the matched injection were examined and the selfsimilar properties both m the mean velocity and the turbulent intensity were found to exist in these cases Rapid decays of the centerlme velocity and the maximum turbulent intensity were observed in the matched injection case The effect of the initial condition was studied by artificially thickening the boundary layer on the model and it was observed that the wake relaxes into the final decay law sooner Dissert Abstr N77-28066 Tennessee Univ , Knoxville A NEW METHOD TO CALCULATE THE VORTEX STRENGTH AND LOCATION OF SLENDER WINGS WITH FLOW SEPARATION PhD Thesis Dieter Kurt Nowak 1976 207 p Avail Univ Microfilms Order No 77-3671 Vortex shedding from side and leading edges of slender wings at angles of attack is examined A flow model was developed that allows the calculation of the strength and location of the edge vortices from parameters obtained by linear potential flow theory The Polhamus leading edge suction analogy and the Betz vortex laws were used The model was applied to the case of a slender delta wing Special emphasis was placed upon experimental information concerning the vortex shedding The evaluation included water tunnel experiments The flow model is based on an analogy between the sharp edge in potential flow without separation and the edge vortex in a flow with edge separation and subsequent reattachment Dissert Abstr N77-28067*# Scientific Translation Service Santa Barbara Calif LIFT CALCULATION AND FLOW MECHANISMS WHEN THE MAXIMUM LIFT IS EXCEEDED Peter Jordan Washington NASA Jun 1977 52 p refs Transl into ENGLISH from Luftfahrt-Forsch (Munich) v 16. no 4 p 184-193 (Contract NASw-2791) (NASA-TT-F-17429) Avail NTIS HC A04/MF A01 CSCL 01A Flow observations and recordings of unsteady flow processes over straight and twisted wings were performed for one profile and a Reynolds number of 200 000 The foundations are laid for calculating the lift distributions which must be supplemented with systematic measurements Author N77-28068*# Illinois Univ Urbana Dept of Aeronautical and Astronautical Engineering PROGRAM MANUAL FOR THE EPPLER AIRFOIL INVER- SION PROGRAM William G Thomson May 1975 54 p (Grant NGR-14-005-144) (NASA-CR-153928 UILU-ENG-75-0504, AAE-75-4) Avail NTIS HC A04/MF A01 CSCL 01A A computer program is described for calculating the profile of an airfoil as well as the boundary layer momentum thickness and energy form parameter The theory underlying the airfoil inversion technique developed by Eppler is discussed A R H N77-28069*# Illinois Univ Urbana-Champaign Aeronautical and Astronautical Engineering Dept LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A 13 1-PERCENT-THICK, HIGH-LIFT AIRFOIL Kenneth R Sivier Allen I Ormsbee, and Randal W Awker Apr 1974 38 p refs Presented at Business Aircraft Meeting Wichita Kans 2-5 Apr 1974. sponsored by Soc Automotive Eng (Grant NGR-14-005-144) INASA-CR-153937, SAE-740366) Avail NTIS HC A03/MF A01 CSCL 01A Low speed sectional characteristics of a high lift airfoil are studied and a comparison is made of those charactenstics with the predictions of the theoretical methods used in the airfoil's design The 13 1 percent-thick UI-1720 airfoil was found to achieve the predicted maximum lift coefficient of nearly 2 0 No 471 N77-28070 upper-surface flow separation was found below the stall angle of attack of 16 degrees it appeared that stall was due to an abrupt leading edge flow separation Author N77-28070*# Mississippi State Univ Mississippi State Dept of Aerophysics and Aerospace Engineering A HIGH REYNOLDS NUMBER NUMERICAL SOLUTION OF THE NAVIER-STOKES EQUATIONS IN STREAM FUNCTION VORTICITY FORM M S Thesis John H Bearden Aug 1977 50 p refs (Grant NGR-25-001-055) (NASA-CR-153933) Avail NTIS HC A03/MF A01 CSCL 01A Problems encoutered in investigations of high Reynolds number, incompressible flow are reviewed A numerical solution computer program was modified to solve the stream function- vorticity form of the Navier-Stokes equations Using a body fitted coordinate system with a U-shaped outer boundary a simulation of incompressible flow at a Reynolds number of one million and a body angle of attack of zero was achieved Author N77-28073*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif REYNOLDS NUMBER EFFECTS ON THE AERODYNAMIC CHARACTERISTICS OF IRREGULAR PLANFORM WINGS AT MACH NUMBER 03 Robert L Kruse George H Lovette and Bernard Spencer Jr (NASA Langley Res Center) Jul 1977 422 p refs (NASA-TM-X-73132 A-6599) Avail NTIS HC A18/MF A01 CSCL 01A The subsonic aerodynamic characteristics of a series of irregular planform wings were studied in wind tunnel tests conducted at M = 03 over a range of Reynolds numbers from 1 6 million to 26 million/m The five basic wing planforms varied from a trapezoidal to a delta shape Leading edge extensions added to the basic shape varied in approximately 5 deg increments from the wing leading edge sweep-back angle to a maximum 80 deg Most of the tests were conducted using an NACA 0008 airfoil section with grit boundary layer trips Tests were also conducted using an NACA 0012 airfoil section and an 8% thick wedge In addition the effect of free transition (no grit) was investigated A body was used on all models Author N77-28075# Aeronautical Research Council London (England) THE CHARACTERISTICS OF A FAMILY OF ROOFTOP AEROFOILS DESIGNED AT THEIR DRAG-RISE CONDITION IN VISCOUS. COMPRESSIBLE FLOW PART 2 OFF DESIGN CONDITIONS B G J Thompson and S W Cosby (Short Brothers and Harland Ltd Belfast) 1975 29 p refs Supersedes RAE-TR-72142 and ARC-34467 (ARC-CP-1321 RAE-TR-72142 ARC-34467 ISBN-011-470931-9) Avail NTIS HC A03/MF A01 HMSO £ 1 50 PHI The problems of computing and of presenting off-design variations of profile drag for the new family of rooftop aerofoils described are examined by considering as a typical example a 50% rooftop section designed at a Mach number of 0 7 and having a thickness-chord ratio of 0 1 Profile drag results are presented as a set of polar curves of c sub d vs c sub I for a range of Mach numbers and as contours of c sub d in the c sub I -m plane Boundaries for rear separation drag rise, and peak local Mach number equal to 1 2 are shown For sections of given thickness-chord ratio and Mach number the present results indicate that the minimum drag anywhere along the flight locus m squared c sub I = constant is obtained by choosing the particular section which has its design point on this locus Author N77-28076# Aeronautical Research Council London (England) DEVELOPMENTS IN THE LIFTING SURFACE THEORY TREATMENT OF SYMMETRIC PLANFORMS WITH A LEADING EDGE CRANK IN SUBSONIC FLOW B L Hewitt and W Kellaway 7975 51 p refs Supersedes ARC-33412 (ARC-CP-1323 ARC-33412 ISBN-0-1 1-4709335) Avail NTIS HC A04/MF A01. HMSO £200 PHI An attempt was made to develop a subsonic lifting surface theory method capable of calculating convergent loading solutions for symmetric planforms with a leading edge crank A trace was made of the time history of thought and method development at B A C which connects the successful treatments of regular and cropped delta type planforms Finally some mention is made of possible future generalisations of the basic cranked planform method Author N77-28077# Aeronautical Research Council London (England) LOW-SPEED WIND-TUNNEL TEST OF A TWO- DIMENSIONAL WING FITTED WITH TWO PLAIN DIFFER- ENTIALLY-DEFLECTED TRAILING EDGE FLAPS John Mckie (RAE Farnborough Engl) 1975 39 p refs Supersedes RAE-TR-74174 and ARC-35971 (ARC-CP-1326 RAE-TR-94174 ARC-35971 ISBN-01 1-470936-X) Avail NTIS HC A03/MF A01 HMSO £1 80 PHI Chordwise pressure distributions were measured at several spanwise stations on a two dimensional model wing fitted with a plain hinged, trailing edge flap at a Reynolds number of 1 9 million based on chord The flap was divided into two parts and was deflected to a maximum of 5 deg When the flaps were deflected differentially the transition from a pressure distribu- tion characteristic of the flaps deflected configuration to one characteristic of te flaps up situation took place within a spanwise distance of about 10% of the chord The length was independent of the angle of incidence Integrations for sectional normal force indicated however that modifications to the local circulation caused by a discontinuity in angle of flap deflection were apparent more than one chord distance away from the flap junction Author N77-28078# Aeronautical Research Council London (England) MEASUREMENTS OF PRESSURE DISTRIBUTION ON A HALF-MODEL WING-BODY COMBINATION OF 55 DEG SWEEP OVER A WIDE RANGE OF REYNOLDS NUMBER K G Winter (RAE Bedford Engl) and J B Moss (RAE Bedford Engl) 1975 157 p refs Supersedes RAE-TR-74149 and ARC-35978 (ARC-CP-1328, RAE-TR-74149 ARC-35978 ISBN-011-470938-6) Avail NTIS HC A08/MF A01 HMSO £490 PHI The tests were made in a 8ft x 8ft wind tunnel mainly at a Mach number of 0 55 where a range of Reynolds number based on wing chord of 2 to 27 million was obtained for the pressure plotting station situated at about two thirds span Limited tests were also made at a Mach number of 0 8 and at supersonic speeds For angles of incidence for which the upper surface pressure distribution is of the design type changes in Reynolds number do not produce changes in character of the flow The lift developed depends upon the trailing edge boundary layer thickness and can be increased considerably by the action of vortex generators At higher angles of incidence the pressure recovery at the trailing edge is strongly influenced by the boundary layer condition The results at supersonic speeds illustrate some features of shock wave boundary layer interaction Author N77-28079// Aeronautical Research Council London (England) INTERFERENCE PROBLEMS ON WING-FUSELAGE COMBI- NATIONS PART 1 LIFTING UNSWEPT WING ATTACHED TO A CYLINDRICAL FUSELAGE AT ZERO INCIDENCE IN MIDWING POSITION J Weber(RAE Farnborough Engl) 1975 45 p refs Supersedes RAE-TR-69130 and ARC-31532 (ARC-CP-1331 RAE-TR-69130 ARC-31532 ISBN-011-470941-6) Avail NTIS HC A03/MF A01 HMSO £ 1 60 PHI The incompressible flow field past a single straight vortex line which crosses a cylindrical circular fuselage at right angles was studied In particular the downwash induced in the plane through the vortex and the axis of the fuselage was determined numerically The results are used to solve the design problem for an unswept wing of infinite aspect ratio for which the chordwise load distribution is given and the spanwise distribution in the presence of the fuselage is required to be constant It is shown 472 N77-28087 how the interference effect varies with the ratio R/c between the body radius and the wing chord and with the spanwise distance from the junction A modification of existing methods for calculating the spanwise load distribution of wing-fuselage combinations is suggested to take account of the body interference with the chordwise load distribution Author N77-28080# Aeronautical Research Council. London (England) INTERFERENCE PROBLEMS ON WING-FUSELAGE COMBI- NATIONS PART 2 SYMMETRICAL UNSWEPT WING AT ZERO INCIDENCE ATTACHED TO A CYLINDRICAL FUSELAGE AT ZERO INCIDENCE IN MIDWING POSI- TION J Weber (RAE Farnborough Engl) and M G Joyce (RAE Farnborough Engl) 1975 71 p cefs Supersedes RAE-TR-71179 and ARC-33437 (ARC-CP-1332, RAE-TR-71179 ARC-33437 ISBN-01 1-470942-4) Avail NTIS HC A04/MF A01. HMSO £230 PHI The incompressible flow field past a single straight infinitely long source line which crosses a circular cylindrical fuselage at right angles was studied In particular the streamwise velocity component induced in the plane through the source line and the axis of the fuselage and the streamwise and circumferential velocity components induced on the surface of the fuselage were determined numerically The results are used to determine the interference effect on the displacement flow past an unswept wing of infinite aspect ratio attached to a cylindrical fuselage It is shown how the interference effect varies with the ratio R/c between the body vadms and the wing chord Author N77-28081# Aeronautical Research Council. London (England) INTERFERENCE PROBLEMS ON WING-FUSELAGE COMBI- NATIONS PART 3 SYMMETRICAL SWEPT WING AT ZERO INCIDENCE ATTACHED TO A CYLINDRICAL FUSELAGE J Weber (RAE Farnborough Engl) and M Gaynor Joyce (RAE Farnborough. Engl) 1975 83 p refs Supersedes RAE-TR-73189 and ARC-35413 (ARC-CP-1333 RAE-TR-73189 ARC-35413 ISBN-01 1-470943-2) Avail NTIS HC A05/MF A01 HMSO £260 PHI The interference effect on the incompressible displacement flow past a swept wing attached to a cylindrical fuselage in midwmg position is studied It is shown how this vanes with the angle of sweep with the section shape and with the ratio R/c between the body radius and the wing chord To reduce the amount of computation only wings of constant chord and constant section shape are considered For these wings the results can easily be derived from the velocity field past a single kinked swept source line in the presence of a fuselage The streamwise velocity component induced in the plane through the source line and the axis of the fuselage and the streamwise and circumferential velocity components induced on the surface of the fuselage were determined numerically, and the values are tabulated It is shown by comparison with results from other methods that, by means of these tables, good estimates of the interference velocity can be derived also for tapered wings Author N77-28082# Aeronautical Research Council London (England) INTERFERENCE PROBLEMS ON WING-FUSELAGE COMBI- NATIONS PART 4 THE DESIGN PROBLEM FOR A LIFTING SWEPT WING ATTACHED TO A CYLINDRICAL FUSELAGE J Weber (RAE Farnborough. Engl) and M Gaynor Joyce (RAE Farnborough Engl) 1975 59 p refs Supersedes RAE-TR-73190 and ARC-35294 (ARC-CP-1334 RAE-TR-73190 ARC-35294 ISBN-011-470944-0) Avail NTIS HC A04/MF A01 HMSO £220 PHI The incompressible flow field past a circular cylindrical fuselage and a kinked infinite swept vortex which lies in a plane through the axis of the fuselage was studied Values for the downwash in the plan and on the surface of the fuselage were determined numerically The values are tabulated for four angles of sweep 0 30 45. and 60 degrees The results are used to design wings of constant chord and infinite aspect ratio, attached to a cylindrical fuselage in midwmg position for which the chordwise load distribution is given and the spanwise distribution in the presence of the fuselage is required to be constant It is shown how the interference effect varies with the angle of sweep with the ratio R/c between the body radius and the wing chord with the spanwise distance from the wing body junction and with the thickness of the wing Author N77-28083jjl Weapons Research Establishment Salisbury (Australia) CALCULATION OF PRESSURE DISTRIBUTIONS ON TWO AXISYMMETRIC BOATTAILED CONFIGURATIONS M K Haselgrove Feb 1977 19 p refs (WRE-TR-1779IW) AR-000-518) Avail NTIS HC A02/MF A01 Computer programs are used to calculate the pressure distributions on two axisymmetnc boattailed configurations in inviscid incompressible flow Realistic results are obtained in the base region by extending the body surface to simulate the surface streamline separating from the base The results show that a favorable pressure gradient is created by replacing the rear portion of a boattail by a cylindrical section, and conversely an adverse gradient on a boattail is strengthened by the presence of a large sting on wind tunnel models Author N77-28086*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif A COMPARISON OF THE EXPERIMENTAL AERODYNAMIC CHARACTERISTICS OF AN OBLIQUE WING WITH THOSE OF A SWEPT WING Edward J Hopkins and Sam C Yee (ARO Inc Moffett Field. Calif) Jun 1977 483 p refs (NASA-TM-X-3547 A-6894) Avail NTIS HC A21/MF A01 CSCL 01A Force and moment characteristics were measured for two trapezoidal oblique wings and a conventional swept wing mounted on a body of revolution at Mach numbers from 0 25 to 2 0 Both oblique wings had the same planform. but differed in profile and flexibility One of the oblique wings was made of solid steel and had a maximum thickness-to-chord ratio of 4 percent The other wing was built up by taking an aluminum wing and adding epoxy material to the upper surface to increase the maximum thickness-to-chord ratio to 8 2 percent The aspect ratio for both oblique wings when swept 45 deg and for the swept wing with 45 deg of sweep, was 4 1 Data were obtained at unit Reynolds numbers ranging from 33 to 82 million per meter and were compared with previously obtained data on the aluminum wing before it was built up witFTepoxy Wing flexibility designed into the aluminum and built-up aluminum oblique wings increased the range of lift coefficients from 0 30 to 0 70 over which the pitchmg-moment curves were linear However, flexibility did not improve the linearity of the rolling-moment curves and produced sizable side forces At a Mach number of 095. the trapezoidal oblique wing had little or no improvement in the lift/drag ratios over those for a conventional swept wing of the same aspect ratio sweep, and profile Author N77-28087*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio COMPARISON OF JET MACH NUMBER DECAY DATA WITH A CORRELATION AND JET SPREADING CONTOURS FOR A LARGE VARIETY OF NOZZLES Donald E Groesbeck. Ronald G Huff, and Uwe H VonGlahn Washington Jun 1977 300 p refs (NASA-TN-D-8423 E-8561) Avail NTIS HC A13/MF A01 CSCL 01A Small-scale circular noncircular single- and multi-element nozzles with flow areas as large as 122 sq cm were tested with cold airflow at exit Mach numbers from 0 28 to 1 15 The effects of multi-element nozzle shape and element spacing on let Mach number decay were studied in an effort to reduce the noise caused by iet impingement on externally blown flap (EBF) 473 N77-28088 STOL aircraft The jet Mach number decay data are well represented by empirical relations Jet spreading and Macri number decay contours are presented-for all configurations tested Author N77-28088*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio AERODYNAMIC PERFORMANCE OF 0 4066 SCALE MODEL OF JT8D REFAN STAGE WITH S-DUCT INLET Royce D Moore George Kovich and George W Lewis Jr Washington May 1977 296 p refs (NASA-TN-D-8458 E-8268) Avail NTIS HC A13/MF A01 CSCL 01A A scale model of the JT8D refan stage was tested with a scale model of the S-duct inlet design for the refanned Boeing 727 center engine Detailed survey data of pressures tempera- tures and flow angles were obtained over a range of flows at speeds from 70 to 97 percent of design speed Two S-duct configurations were tested one with a bellmouth inlet and the other with a flight lip inlet The results indicated that the overall performance was essentially unaffected by the distortion generated by the S-duct inlet The stall weight flow increased by less than 0 5 kg/sec (approximately 1 5% of design flow) with the S-duct inlet compared with that obtained with uniform flow The detailed measurements indicated that the inlet guide vane (IGV) signif- icantly reduced circumferential variations For example the flow angles ahead of the IGV were positive in the right half of the inlet and negative in the left half Behind the IGV the flow angles tended to be more uniform circumferentially Author N77-28090*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC CHARACTERISTICS OF A 1/6 SCALE POWERED MODEL OF THE ROTOR SYSTEMS RESEARCH AIRCRAFT Raymond E Mmeck and Carl E Freeman Washington Jun 1977 240 p refs Prepared in cooperation with Army Air Mobility Res and Develop Lab Moffett Field Calif (DA Pro) 1F1-61101-AH-45) (NASA-TM-X-3489. L-11287) Avail NTIS HCA11/MFA01 CSCL 01A A wind-tunnel investigation was conducted to determine the effects of the main-rotor wake on the aerodynamic characteristics of the rotor systems research aircraft (RSRA) For the investigation a 1/6-scale model with a four-blade articulated main rotor was used Tests were conducted with and without the main rotor Both the helicopter and the compound helicopter were tested The latter configuration included the auxiliary thrust engines and the variable-incidence wing Data were obtained over ranges of angle of attack angle of sideslip and main-rotor collective pitch angle at several main-rotor advance ratios Results are presented for the total loads on the airframe as well as the loads on the rotor, the wing and the tail The results indicated that without the effect of the rotor wake, the RSRA had static longitudinal and directional stability and positive effective dihedral With the effect of the mam rotor and its wake, the RSRA exhibited longitudinal instability but retained static directional stability and positive effective dihedral Author N77-28091*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va WIND-TUNNEL INVESTIGATION OF A VARIABLE CAMBER AND TWIST WING James C Ferris Washington Aug 1977 81 p refs (NASA-TN-D-8475. L-11357) Avail NTIS HC A05/MF A01 CSCL 01A The longitudinal aerodynamic characteristics of a 35 deg swept variable camber and twist semispan wing in the presence of a body were studied The variable camber and twist were incorporated to allow a near optimum lift distribution over the wing for both the cruise condition and the high lift conditions for maneuverability The wing incorporated movable leading- edge segments whose swept hinge lines provided maximum camber variations at the outboard leading edge and movable trailmg-edge segments whose swept hinge lines provided maximum camber variations near the inboard trailing edge The model was investigated at Mach numbers of 0 60 0 80. and 090 through an angle-of-attack range from 0 deg to 10 deg or buffet onset 1 , , . Author N77-28092*# National Aeronautics and Space Administration Langley Research Center Langley Station Va FREE-FLIGHT WIND-TUNNEL INVESTIGATION OF A FOUR-ENGINE SWEPTWING UPPER-SURFACE BLOWN TRANSPORT CONFIGURATION Lysle P Parlett Washington Aug 1977 35 p refs (NASA-TN-D-8479 L-11332) Avail NTIS HC A03/MF A01 CSCL 01A The dynamic stability and control characteristics of a four-engine turbofan transport model having an upper-surface blown jet flap were investigated by means of the free-flight technique in the Langley full-scale tunnel The flight characteristics of the model were investigated through a range of lift coef- ficients from 3 to 8 with all four engines operating and with one outboard engine not operating Static characteristics were investigated by conventional power-on force tests over the flight-test angle-of-attack range and through the stall Author N77-28093*# National Aeronautics and Space Administration Langley Research Center Langley Station Va INVESTIGATION OF EFFECT OF PROPULSION SYSTEM INSTALLATION AND OPERATION ON AERODYNAMICS OF AN AIRBREATHING HYPERSONIC AIRPLANE AT MACH 0 3 TO 1 2 James M Cubbage and Charles E Mercer Washington Jul 1977 94 p refs (NASA-TN-D-8503) Avail NTIS HC A05/MF A01 CSCL 01A Results from an investigation of the effects of the operation of a combined turboiet/scramjet propulsion system on the longitudinal aerodynamic characteristics of a 1/60-scale hyper- sonic airbreathmg launch vehicle configuration are presented Decomposition products of hydrogen peroxide were used for simulation of the propulsion system exhaust Author N77-28094*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC CHARACTERISTICS OF WING-BODY CONFIGURATION WITH TWO ADVANCED GENERAL AVIATION AIRFOIL SECTIONS AND SIMPLE FLAP SYSTEMS Harry L Morgan Jr and John W Paulson Jr Washington Aug 1977 71 p refs (NASA-TN-D-8524 L-11305) Avail NTIS HC A05/MF A01 CSCL 01A Aerodynamic characteristics of a general aviation wing equipped with NACA 65 sub 2-415 NASA GA(W)-1 and NASA GA(PC)-1 airfoil sections were examined The NASA GA(W)-1 wing was equipped with plain split and slotted partial- and full-span flaps and ailerons The NASA GA(PC)-1 wing was equipped with plain partial- and full-span flaps Experimental chordwise static-pressure distribution and wake drag measure- ments were obtained for the NASA GAIPQ-1 wing at the 22 5-percent spanwise station Comparisons were made between the three wing configurations to evaluate the wing performance stall and maximum lift capabilities The results of this investigation indicated that the NASA GA(W|-1 wing had a higher maximum lift capability and almost equivalent drag values compared with both the NACA 65 sub 2-415 and NASA GAIPC1-1 wings The NASA GA(W)-1 had a maximum lift coefficient of 1 32 with 0 deg flap deflection and 1 78 with 41 6 deg deflection of the partial-span slotted flap The effectiveness of the NASA GA(W)-1 plain and slotted ailerons with differential deflections were equivalent The NASA GAIPO-1 wing with full-span flaps deflected 0 deg for the design climb configuration showed improved lift and drag performance over the cruise flap setting of -10 deg Author 474 N77-28109 N77-28097# Naval Ship Research and Development Center. Bethesda Md Aviation and Surface Effects Dept EXPERIMENTAL OBSERVATIONS OF THE TWO- DIMENSIONAL POWER AUGMENTED RAM WING OPER- ATED STATICALLY OVER WATER Final Report. Jun - Feb. 1977 B H Carson Mat 1977 33 p refs (AD-A038163. DTNSRDC/ASED-372) Avail NTIS HC A03/MF A01 CSCL 20/4 Experiments were performed in a rectangular tank partially filled with water and spanned by a flat-bottomed airfoil section derived from an NACA 0015 thickness distribution Upstream of the airfoil was placed a two-dimensional air jet also spanning the tank One side of the tank was transparent to permit flow visualization Two-dimensional turbulent jet theory was used to establish the relationship between the jet exit dynamic pressure and the pressure recovery under the wing which was supported by experimental evidence It was found that the recovery of pressure was not highly sensitive to jet geometry however the formation of spray was For minimum spray formation a jet impingement angle of about 25 deg was established Several interesting wind-wave flow instabilities were observed A thrust-reversal phenomenon, predicted by inviscid theory could not be duplicated in the present experiment Author (GRA) N77-28100*# Little (Arthur D) Inc Cambridge Mass THE MARKET FOR AIRLINE AIRCRAFT A STUDY OF PROCESS AND PERFORMANCE Nov 1976 204 p refs Prepared in cooperation with Simat. Helliesen and Eichner Inc Tarrytown. N J (Contract NASw-2971) (NASA-CR-154617) Avail NTIS HC A10/MF A01 CSCL 01C The key variables accounting for the nature timing and magnitude of the equipment and re-equipment cycle are identified and discussed Forecasts of aircraft purchases by U S trunk airlines over the next 10 years are included to examine the anatomy of equipment forecasts in a way that serves to illustrate how certain of these variables or determinants of aircraft demand can be considered in specific terms Author N77-28102# Naval Weapons Center. China Lake. Calif AIRCRAFT FIRE SIMULATOR TESTING OF CANDIDATE FIRE BARRIER SYSTEMS Test and Evaluation Report. Feb - Sep 1976 Herman H Hoffman and John S Fontenot Nov 1976 43 p (AD-A038601 NWC-TP-5915) Avail NTIS HC A03/MF A01 CSCL 01/2 The results of a study to evaluate candidate aircraft fire barrier materials to m-flight fires are presented Four organic materials two inorganic materials, and three metallics combined with insulators were tested in an in-flight fire simulator Eight mtumescent coatings were evaluated to determine their ability to close barrier gaps in the event of a fire Author (GRA) N77-28103 Purdue Umv Lafayette Ind MANUAL CONTROL DISPLAYS FOR A FOUR DIMEN- SIONAL LANDING APPROACH Ph D Thesis James Taylor Silverthorn 1976 136 p Avail Umv Microfilms Order No 77-1776 Six instrument rated pilots flew a STOL fixed base simulator to study the effectiveness of three displays for a four-dimensional approach The three examined displays weie a digital readout of forward position error a digital speed command and an analog display showing forward position error and error prediction A flight director was used in all conditions All test runs were for a typical four-dimensional approach in moderate turbulence that included a change in commanded ground speed a change in flight path angle and two standard late sixty degree turns Use of the digital forward position error display resulted in large overshoot in the forward position error The best overall performance was obtained using the speed command display It was demonstrated that curved approaches can be flown with relative ease Dissert Abstr N77-28104# Aeronautical Research Council London (England) DESIGN AND THEORETICAL ASSESSMENT OF EXPERI- MENTAL GLIDE PATH AND FLARE SYSTEMS FOR A BAG 1-11 AIRCRAFT (INCLUDING DIRECT LIFT CONTROL) F R Gill (RAE Farnborough Engl) and M J Cor bin (RAE Farnborough Engl) 1975 66 p refs Supersedes RAE-TR-74013 and ARC-35979 (ARC-CP-1337 RAE-TR-74013 ARC-35979 ISBN-01 1-470947-5) Avail NTIS HC A04/MF A01 HMSO £260 PHI Two experimental glide path and flare systems are described one using spoilers installed in the aircraft to provide direct lift control The various longitudinal control modes altitude hold glide path and flare have similar feedback control gains whose values were determined by parameter optimisation An assessment of the performance of these two systems is described Using elevator and throttle control only there was little improvement over current flare systems but use of high gain direct lift control gives significant improvement Author N77-28106# Facility Checking Squadron (1868th) (AFCS) APO New York 09332 TRACALS EVALUATION REPORT NAVAIDS STATION EVALUATION REPORT. AVIANO AB. ITALY (16-23 AUGUST 1976) Final Report Robert L Jones 25 Feb 1977 65 p IAD-A038062 Rept-76/68-T-18) Avail NTIS HC A04/MF A01 CSCL 17/7 This Traffic Control and Landing Systems (TRACALS) station evaluation report presents data collected to define the capabilities and limitations of the Tactical Air Navigation (TACAN) System AN/GRN-19A with an AN/GRA-120 antenna system and associated power equipment at Aviano Air Base Italy Included in the report are coverage diagrams and analysis of airborne and ground performance data Data analysis indicates the configuration to be capable of satisfying the required mission The data presented in this report can be used as a valid guide to this facility s anticipated performance until there is a configura- tion change which alters the capabilities of the equipment or until a change occurs in the horizontal profile Author (GRA) N77-28108*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif FLUT - A PROGRAM FOR AEROELASTIC STABILITY ANALYSIS Erwm H Johnson Jun 1977 57 p refs (NASA-TM-73217 A-6955) Avail NTIS HC A04/MF A01 CSCL 01 C A computer program (FLUT) that can be used to evaluate the aeroelastic stability of aircraft structures in subsonic flow is described The algorithm synthesizes data from a structural vibration analysis with an unsteady aerodynamics analysis and then performs a complex eigenvalue analysis to assess the system stability The theoretical basis of the program is discussed with special emphasis placed on some innovative techniques which improve the efficiency of the analysis User information needed to efficiently and successfully utilize the program is provided In addition to identifying the required input the flow of the program execution and some possible sources of difficulty are included The use of the program is demonstrated with a listing of the input and output for a simple example Author N77-281O9*# National Aeronautics and Space Administration Langley Research Center Langley Station Va LOW-SPEED WIND-TUNNEL INVESTIGATION OF A LARGE-SCALE ADVANCED ARROW WING SUPERSONIC TRANSPORT CONFIGURATION WITH ENGINES MOUNTED ABOVE THE WING FOR UPPER-SURFACE BLOWING James P Shivers H Clyde McLemore and Paul L Coe Jr 2 Aug 1977 67 p refs (NASA-TM-X-72761) Avail NTIS HC A04/MF A01 CSCL OIC The Langley full scale tunnel was used to investigate the low speed stability and control of an advanced arrow wing supersonic transport with engines mounted above the wing for upper-surface blowing Tests were made over an angle of attack 475 N77-28110 range of -10 to 32 deg slideshp angles of + or -5 deg and a Reynolds number ranging from 353 million to 7u33 million(referenced to mean aerodynamic chord of the wing) Configuration variables included trailmg-edge flap deflection, engine jet nozzle angle engine thrust coefficient engine out operation, and asymmetrical trailing-edge BLC for providing roll trim Downwash measurements at the tail were obtained for different thrust coefficients tail heights and at two fuselage stations Author N77-28110# Aeronautical Research Council. London (England) AN ASSESSMENT OF THE ACCURACY OF SUBSONIC LINEARIZED THEORY FOR THE DESIGN OF WARPED SLENDER WINGS Patricia J Davies (RAE Farnborough Engl) 1975 40 p refs Supersedes RAE-TR-73159 and ARC-35314 (ARC-CP-1324 Rae-TR-73159 ARC-35314 ISBN-011-470934-3) Avail NTIS HC A03/MF A01 HMSO £l 80, PHI A series of warped slender wings were designed using the linearized theory of subsonic flow as a basis for a systematic experimental investigation of the drag reduction obtainable by warp at low speeds The force measurements on these wings are supplemented by measurements of the pressure distribution over one of them and the pressure distribution on it was calculated for inviscid incompressible flow by a surface singularity method The distribution of pressure used in the design is compared with those measured and calculated for the design incidence at which the flow was attached and assesses the validity of the linear theory The chief weaknesses are found to be on the thicker cross sections near the apex, and towards the trailing edge where boundary layer effects become significant Author N77-28111*jj( National Aeronautics and Space Administration Ames Research Center Moffett Field Calif CONSTANT LIFT ROTOR FOR A HEAVIER THAN AIR CRAFT Patent Application < , Robert H Stroub inventor (to NASA) Filed 25 Jul 1977 17 p (NASA-Case-ARC-11045-1 US-Patent-Appl-SN-818916) Avail NTIS HC A02/MF A01 CSCL01C A constant lift rotor is described It consists of a rotor blade radially from a hub with an elongated spar and several axially aligned shells pivotally mounted on the spar each having an aerodynamic center located in trailing relation with the spar and supported for simultaneous axial and angular displacement as centrifugal forces are applied The pitch is contiolled by limiting arms transverse to the spar each characterized by a cam surface along one edge supporting a cam follower of a truck pivotally connected to a shell and supported for pivotal motion about an axis coincident with a radius of the spar A push-pull link interconnects the arms for imparting pivotal motion whereby the angular relationship of the arms to the spar is varied for changing the motion of the trucks along the arms for limiting the pitch of the segments about the spar NASA N77-28112*# National Aeronautics and Space Administration Langley Research Center Langley Station Va LOAD AND STABILITY MEASUREMENTS ON A SOFT INPLANE ROTOR SYSTEM INCORPORATING ELASTO- MERIC LEAD-LAG DAMPERS William H Weller Washington Jul 1977 70 p refs Prepared in cooperation with the US Army Air Mobility R and D Lab Hampton Va (DA Proj 1L2-62209-AH-76) (NASA-TN-D-8437 L-11315) Avail NTIS HC A04/MF A01 CSCL 01 C An experimental investigation was conducted of the dynamic response and inplane stability associated with a new soft-mplane helicopter rotor The unique feature of this rotor was the use of an internal elastomeric damper to restrain the blade inplane motion about the lead-lag hinge The properties of the elastomer were selected to provide both a nominal first inplane frequency ratio of 0 65 and sufficient damping to eliminate the need for additional external damping sources to prevent ground resonance on a typical fuselage structure For this investigation a 1/5-scale aeroelastic model was used to represent the rotor The four-blade model had a diameter of 3 05 m (10 ft) and a solidity of 0 103 The first out-of-plane frequency ratio was 1 06 The model was tested in hover and in forward flight up to an advance ratio of 0 45 At each forward speed the rotor lift was varied up to simulated maneuver conditions The measured rotor loads and response were within acceptable limits and no adverse re sponse qualities were observed Moderate out-of-plane hub moments were measured even for zero lift to indicate the beneficial control power available for this design Blade inplane stability testing indicated that the rotor system damping remained at moderate levels throughout the operating envelope Author N77-28113*# Computer Sciences Corp Mountain View Calif COMPUTERS FOR REAL TIME FLIGHT SIMULATION A MARKET SURVEY George A Bekey and Walter J Karplus Washington NASA Jul 1977 84 D (Contract NAS2-7806) (NASA-CR-2885) Avail NTIS HC A05/MF A01 CSCL01C An extensive computer market survey was made to determine those available systems suitable for current and future flight simulation studies at Ames Research Center The primary requirement is for the computation of relatively high frequency content (5 Hz) math models representing powered lift flight vehicles The Rotor Systems Research Aircraft (RSRA) was used as a benchmark vehicle for computation comparison studies The general nature of helicopter simulations and a description of the benchmark model are presented and some of the sources of simulation difficulties are examined A description of various applicable computer architectures is presented along with detailed discussions of leading candidate systems and comparisons between them Author N77-28114# Army Materials and Mechanics Research Center Watertown Mass SECONDARY DAMAGE TO AIRCRAFT BY RICOCHETED SMALL ARMS PROJECTILES AND FRAGMENTS Final Report Stuart V Arnold and Russel G Hardy Nov 1976 26 p (AD-A038755 AMMRC-TR-76-35) Avail NTIS HC A03/MF A01 CSCL 19/1 Under certain conditions of oblique impact against aircraft structures small arms projectiles (or fragments thereof) ricochet thereby causing damage to adjoining structures components or personnel This report describes terminal ballistics of caliber 30 AP M2 and 7 62-mm ball M59 projectiles striking 0 375-mch-thick 2024-T351 aluminum and 0 25-mch-thick Ti-6AI-4V alloy plates over ranges of obliquity and velocity Effects of these factors upon potential for secondary damage are assessed Principles for design of aircraft structures to reduce vulnerability to ricochet damage are proposed Author (GRA) N77-28115# Air Force Flight Test Center Edwards AFB Calif C-141A PITOT STATIC SYSTEM CALIBRATION TESTS Ronald K Pomeroy Herbert Klein Joseph A Guthne Jr and Thomas P Stafford Dec 1976 25 p refs (AD-A036241) Avail NTIS HC A02/MF A01 CSCL 14/2 The flight test program consisted of six C 141A/T-38A pacer flights On flight 2 a series of tower fly-by points were also accomplished Prior to each flight a ground calibration of the aircraft s pilot-static systems was performed (Appendix B) Each of the six pacer flights consisted of 30 000 and 20 000 feet (MSL) cruise configuration and 10000 feet (MSL) takeoff and landing configuration points On flight 5 adverse weather conditions prohibited flight operations at 10000 feet The T 38A pacer position and alignment detailed in figure A1 enabled the pacer pilot to perceive small airspeed and altitude changes while maintaining a position outside the C-141A pressure wave GRA N77-28116# Naval Postgraduate School Monterey Calif A PERSONALIZED SYSTEM OF INSTRUCTION TOR AIRCRAFT PERFORMANCE MS Thesis Donald Leslie Finch Mar 1977 412 p refs (AD-A039654) Avail NTIS HC A18/MF A01 CSCL 05/9 476 N77-28126 A personalized system of instruction utilizing self-contained text material and combining the principle of autotutonal instruction with modified self-pacing was developed for a course in aircraft performance The course material was applied to the aircraft performance portion (six weeks) of a 12 week course in aircraft performance control and stability taught to 11 students The course results tended to confirm the advantages and substantial value of this instructional method GRA N77-28118* National Aeronautics and Space Administration Langley Research Center Langley Station Va DUAL CYCLE AIRCRAFT TURBINE ENGINE Patent Mark R Nichols inventor (to NASA) Issued 5 Jul 1977 8 p Filed 6 Sep 1973 Supersedes N73-31699 ( 1 1 - 2 2 p 2710) (NASA-Case-LAR-11310-1 US-Patent-4 033.119 US-Patent-Appl-SN-394898 US-Patent-Class-60-226R US-Patent-Class-60-263 US-Patent-Class-415-145) Avail US Patent Office CSCL 21E A method and apparatus are presented for improving operating efficiency over broad ranges of flight conditions and for reducing jet engine noise output in takeoff and landing by controlling the airflow entering and exiting the engines A turbojet engine apparatus is described which operates efficiently at both subsonic and supersonic speeds and a method is described which enables a turbofan with an associated satellite turbojet or turbofan to operate more efficiently at both subsonic and supersonic speeds In both cases takeoff and landing noise is reduced substantially The apparatus consists essentially of arranging for two separate portions of an engine to act upon one airstream or alternately to operate on independent airstreams Official Gazette of the U S Patent Office N77-28119*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio AERO-ACOUSTIC PERFORMANCE COMPARISON OF CORE ENGINE NOISE SUPPRESSORS ON NASA QUIET ENGINE C Harvey E Bloomer and John W Schaefer Jul 1977 20 p refs Presented at the 13th Propulsion Conf Orlando Fla 11-13 Jul 1977 Cosponsored by the Am Inst of Aeron and the Soc of Automotive Engr (NASA-TM-X-73662 E-9182) Avail NTIS HC A02/MF A01 CSCL 21H The relative aero-acoustic effectiveness of two core engine suppressors a contractor-designed suppressor delivered with the Quiet Engine, and a NASA-designed suppressor was evaluated The NASA suppressor was tested with and without a splitter making a total of three configurations being reported in addition to the baseline hardwall case The aerodynamic results are presented in terms of tailpipe pressure loss corrected net thrust and corrected specific fuel consumption as functions of engine power setting The acoustic results are divided into duct and far-field acoustic data The NASA-designed core suppressor did the better |ob of suppressing aft end noise, but the splitter associated with it caused a significant engine performance penality The NASA core suppressor without the spltter suppressed most of the core noise without any engine performance penalty Author N77-28121$ Aeronautical Research Council London (England) THE EFFECT OF TEMPERATURE ON SUBSONIC JET NOISE B J Cocking (Natl Gas Turbine Estab Farnborough Engl) 1975 41 p refs Supersedes NGTER-331 and ARC 35575 (ARC-R/M-3771 NGTER-331 ARC-35575 ISBN-0-1 1-4709165) Avail NTIS HC A03/MF A01 HMSO £350. PHI The noise levels produced by hot and cold subsonic jets were measured using a convergent circular nozzle in an anechoic chamber The effects of jet temperature on the sound power the overall sound pressure levels, and the spectra of the jet noise are presented Results show an unexpected increase in noise with increasing jet temperature at low jet velocities The possibility of observation arising from sources upstream of the nozzle exit is considered and discounted It is concluded that both the spectral shapes and the overall sound p.eSMjre level of a hot |et are significantly affected by refrac'ion of the sound jet The overall sound pressure levels were correlated to form the basis of a method for the prediction of the noise from static jets Author N77-28122*# General Electric Co Evendale Ohio Aircraft Engine Group ATTENUATION OF UPSTREAM-GENERATED LOW FREQUENCY NOISE BY GAS TURBINES Final Report V L Doyle and R K Malta Aug 1977 232 p refs (Contract NAS3-19435) (NASA-CR-135219 R77AEG482) Avail NTlS HC A11/MF A01 CSCL 20A The acoustic transfer functions of low frequency (below 3500 Hz) noise through aircraft turbines were investigated Model test results were compared with theoretical predictions in order to assess the validity of the theory Component tests were conducted on both high pressure and low pressure model turbines The influence of inlet temperature and turbine speed attenuation was evaluated, while the effects of turbine pressure ratio blade-row choking and additional downstream stages were determined Preliminary identification of pertinent aeroacoustic correlating parameters was made Author N77-28123*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio FULL-SCALE ALTITUDE ENGINE TEST OF A TURBOFAN EXHAUST-GAS-FORCED MIXER TO REDUCE THRUST SPECIFIC FUEL CONSUMPTION Richard R Cullom and Roy L Johnson Jul 1977 31 p rets (NASA-TM-X-3568 E-9111) Avail NTIS HC A03/MF A01 CSCL 21 E The specific fuel consumption of a low-bypass-ratio confluent- flow turbofan engine was measured with and without a mixer installed Tests were conducted for flight Mach numbers from 0 3 to 14 and altitudes from 10,670 to 14 630 meters (35 000 to 48 000 ft) for core-stream-to-fan-stream temperature ratios of 2 0 and 2 5 and mixmg-length-to-diameter ratios of 0 95 and 1 74 For these test conditions, the reduction in specific fuel consumption varied from 25 percent to 4 0 percent Pressure loss measurements as well as temperature and pressure surveys at the mixer inlet the mixer exit and the nozzle inlet were made Author N77-28126# General Electric Co Cincinnati, Ohio SUPERSONIC JET EXHAUST NOISE INVESTIGATION VOLUME 2 TECHNICAL REPORT Paul R Knott, R Mam C L Merkle, H S Ribner and P Scott Jul 1976 393 p refs (Contract F33615-73-C-2031) (AD-A038613 R74AEG452-Vol-2 AFAPL-TR-76-68-Vol-2) Avail NTIS HCA17/MFA01 CSCL 20/1 This report discusses detailed accounts of major theoretical and experimental investigations directed toward obtaining better understanding and mathematical specification of supersonic turbulent jets Complete theoretical discussions are given describing the influence of a jet s mean flow shrouding on acoustic radiation of heated and unheated jets approximate closed form acoustic expressions for turbulent mixing noise characterized by self-noise and shear-noise are given and theoretical aero- acoustic formulations for the orderly structure of supersonic jets are reviewed Extensive theory/data comparisons of developed acoustic models are given Experimental investigations aimed at studying high velocity jet refraction and the influence of jet swirl and upstream combustion roughness on jet noise is presented Additionally an extensive series of laser velocimeter measurements for high velocity and high temperature simple circular jets is discussed Results include hot-film/laser velocimeter comparisons for ambient jets mean velocity and turbulent velocity plume surveys of heated supersonic shock-free and shocked flow nozzles and a demonstration experiment illustrating the capability of performing in-jet turbulence to far-field acoustic cross-correlation Author (GRA) 477 N77-28127 N77-28127# Go.neral Electric Co. Cincinnati. Ohio SUPERSONIC JET EXHAUST NOISE INVESTIGATION VOLUME 3 COMPUTER USERS MANUAL FOR AERO- ACOUSTIC PREDICTIONS Final Technical Report, 1 Dec 1972 - 23 Sep 197S David R Ferguson Michael A Smith, and Paul R Knott Jul 1976 701 p refs (Contract F33615-73-C-2031) (AD-A038614 R74AEG452-Vol-3. AFAPL-TR-76-68-Vol-3) Avail NTIS HC A99/MF A01 CSCL 20/1 This report gives a detailed description of aerodynamic (Shock-free/Shocked flow) and acoustic turbulent mixing computer prediction programs developed by the General Electric Company for subsonic and supersonic simple exhaust jets In addition to giving detailed descriptions of the aeroacoustic formulations and discussions of computer manual instructions for operating the program extensive theory/data comparisons are given as well as computer program listings and sample test cases Author (GRA) N77-28129# General Motors Corp , Indianapolis Ind Detroit Diesel Allison Div LOW-EMISSIONS COMBUSTOR DEMONSTRATION Final Report, 1 Mar 1974 - 31 Dec 197S 0 L Troth Mar 1977 405 o refs (Contract DAAJ02-74-C-0025) (AD-A038550 DDA-EDR-8723 USAAMROL-TR-76-29] Avail NTIS HCA18/MFA01 CSCL 21/5 The objectives of this eighteen-month program were to further develop two low-emission combustors-the prechamber combustor and the modified conventional combustor to install them in a Detroit Diesel Allison Model 250-C20B engine and to evaluate their performance in an engine environment The combustors were to retain the 50% overall reduction in gas turbine mass emissions with no increase in any individual pollutant when tested over a typical Army light observation helicopter (LOH) duty cycle GRA N77-28130# Air Force Inst of Tech Wright-Patterson AFB Ohio School of Engineering THE ELECTROSTATIC SENSING OF SIMULATED MA-1A GAS PATH DISTRESSES M S Thesis Robert Wesley Dunn Dec 1976 77 p refs (AD-A038527 AFIT/GNE/PH/76-2) Avail NTIS HC A05/MF A01 CSCL 14/2 Jet engine distresses were simulated using a MA-1A start cart Three primary methods were used to distress the gas turbine engine Material was ingested through the compressor intake the compressor section was rubbed with an aluminum rod and foreign material was burned in the combustor can The current wave forms created by these distresses were observed with four separate detectors Since the MA-1A was on rubber tires the current between the chassis and ground could be measured This chassis current was equal to the rate at which charge was expelled in the exhaust A Gaussian ring around the exhaust port provided a second way of detecting charges leaving the start cart The third and fourth devices were an ion probe and a screen that were placed in the exhaust GRA N77-28131# Massachusetts Inst of Tech Cambridge Gas Turbine Lab STUDIES ON TRANSONIC TURBINES WITH FILM-COOLED BLADES Annual Technical Report. 1 Jul 1975 - 30 Jun 1976 H 0 Demuren N Adams F Hajjar 0 M Amana and Jean F Louis Jun 1976 110 p refs (Contract N00014-67-A-0204-0079) (AD-A036402 TR-76-1 ATR-3) Avail NTIS HC A06/MF A01 CSCL 21/5 In the third year of the contract further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled highly-loaded transonic turbine bladmg The MIT cascade blowdown facility now fully operational was used in evaluating the heat transfer performance of the four blade profiles designed in the first year of the program The results show that the level of turbulence is an important parameter in determining heat transfer in transonic cascades )t also shows that the heat transfer to the trailing edge of the blades is very high being about 75% of the heat transfer to the leading edge A comparison of the Nusselt number calculated from heat transfer measurements with the Nusselt number obtained by a prediction method using the pressure distribution shows good correspondence The variation of average Stanton number over a range of Mach numbers shows that the reference blade has the most superior heat transfer performance Pre- liminary data has been obtained on the off-design performance of the blades and full scale tests are underway Comparative studies show that about 21% less heat needs to be taken out by internal cooling if one stage of a transonic turbine is used to replace two moderately loaded subsonic stages which produce the same outpu* have the same inlet stagnation conditions have the same mass flow and the same tip speed This demonstrates one of the potential advantages of transonic turbines GRA N77-28132# Detroit Diesel Allison Indianapolis Ind COMPRESSOR STATOR TIME-VARIANT AERODYNAMIC RESPONSE TO UPSTREAM ROTOR WAKES Interim Report Sanford Fleeter Robert L Jay and William A Bennett Nov 1976 121 p refs (Contract F44620-74-C-0065 AF Proj 9781) (AD-A036343 DDA-EDR-9005 AFOSR-77-0066TR) Avail NTIS HC A02/MF A01 CSCL 21/5 An experimental investigation was conducted to determine the fluctuating pressure distribution on a stationary vane row with the primary source of excitation being the wakes from the upstream rotor blades This was accomplished in a large scale low speed single stage research compressor The forcing function the velocity defect created by the rotor wakes was measured with a crossed hot-wire probe The aerodynamic response on the vanes was measured by means of flush mounted high response dynamic pressure transducers The dynamic data were analyzed to determine the chordwise distribution of the dynamic pressure coefficient and aerodynamic phase lag as referenced to a transverse gust at the vane leading edge Vane suction and pressure surface data as well as the pressure difference across the vane were obtained for reduced frequency values ranging from 3 65 to 16 80 and for incidence angles from -4 5 to -31 0 deg The pressure difference data were correlated with a state-of-the-art aerodynamic cascade transverse gust analysis Author (GRA) N77-28133# California Inst of Tech Pasadena Guggenheim Jet Propulsion Center ANALYTICAL STUDIES OF SOME ACOUSTIC PROBLEMS OF JET ENGINES Ph D Thesis Interim Report Sebastien M Candel Washington DOT May 1976 240 p refs (Contract DOT-OST-20197) (PB-264918/4 DOT-TST-76-104) Avail NTIS HC A11/MF A01 CSCL 21E The propagation and generation of acoustic waves in a choked nozzle is considered where pressure and entropy fluctuations caused by gas stream non-uniformities like hot spots are incident on the nozzle entrance A noise-generation mechanism is found which produces acoustic waves of strength proportional to the entrance entropy fluctuation and local gradient of the mean flow velocity A transformation is introduced which relates the solutions of problems involving the propagation of acoustic waves in a moving medium to the solutions of associated problems in a stationary medium GRA 478 N77-28140 N77-28134 Aeronautical Research Labs. Melbourne (Australia) THE EFFECT OF SPANWISE GUST VARIATIONS ON THE TRANSFER FUNCTION OF AN AIRCRAFT MODEL WITH ONE DEGREE OF FREEDOM Douglas John Sherman Aug 1976 31 p refs (ARL-Struc-Note-431 AR-228) Copyright Avail Issuing Activity Charts are derived for the determination of the power spectrum parameters (a standard deviation of vertical acceleration at aircraft center of gravity/standard deviation of vertical gust velocity and N sub 0 rate of level crossings of mean value), due to atmospheric turbulence The method takes account of spanwise variations in gust loading and so overcomes the paradox of an infinite N sub 0 which is found with a one-dimensional gust model Author N77-28135*# Kansas Univ Center for Research Inc Lawrence FLIGHT EVALUATION OF A SPOILER ROLL CONTROL SVSTEM ON A LIGHT TWIN-ENGINE AIRPLANE David L Kohlman Dec 1976 50 p refs (Grant NsG-1227) (NASA-CR-154121 KU-FRL-203) Avail NTIS HC A03/MF A01 CSCL01C Slot lip spoilers were designed installed and flight tested on a modified Piper PA34-200 aircraft Data obtained during in-flight monitoring are presented and discussed Topics include configuration description instrumentation, spoiler roll characteris- tics, and wheel deflections and forces A R H N77-28136*| Old Dominion Univ Research Foundation Norfolk. Va EXPERIMENTAL AND ANALYTICAL INVESTIGATIONS TO IMPROVE LOW-SPEED PERFORMANCE AND STABILITY AND CONTROL CHARACTERISTICS OF SUPERSONIC CRUISE FIGHTER VEHICLES Final Report A B Graham Jun 1977 5 p (Grant NsG-1309) (NASA-CR-154122) Avail NTIS HC A02/MF A01 CSCL 01C Small- and large-scale models of supersonic cruise fighter vehicles were used to determine the effectiveness of airframe/ propulsion integration concepts for improved low-speed perform- ance and stability and control characteristics Computer programs were used for engme/airframe sizing studies to yield optimum vehicle performance Author N77-28137*# National Aeronautics and Space Administration Langley Research Center Langley Station Va FLIGHT INVESTIGATION OF A VERTICAL-VELOCITY COMMAND SYSTEM FOR VTOL AIRCRAFT James R Kelly Frank R Niessen Kenneth R Yenni and Lee H Person Jr Washington Jul 1977 26 p refs (NASA-TN-D-8480 L-11454) Avail NTIS HC A03/MF A01 CSCL 01C A flight investigation was undertaken to assess the potential benefits afforded by a vertical-velocity command system (WCS) for VTOL (vertical take-off and landing) aircraft This augmentation system was conceived primarily as a means of lowering pilot workload during decelerating approaches to a hover and/or landing under category Ml instrument meteorological conditions The scope of (he investigation included a determination of acceptable system parameters a visual flight evaluation and an instrument flight evaluation which employed a 10 deg decelerating simulated instrument approach task The results indicated that the WCS which decouples the pitch and vertical degrees of freedom provides more accurate glide-path tracking and a lower pilot workload than does the unaugmented system Author N77-28138*# National Aeronautics and Space Administration Langley Research Center Langley Station Va A THEORETICAL ANALYSIS OF AIRPLANE LONGITUDINAL STABILITY AND CONTROL AS AFFECTED BY WIND SHEAR Windsor L Sherman Washington Jul 1977 53 p refs (NASA-TN-D-8496 L-11392) Avail NTIS HC A04/MF A01 CSCL QIC The longitudinal equations of motion with wind shear terms were used, to analyze the stability and motions of a |et transport A positive wind shear gives a decreasing head wind or changes a head wind into a tail wind A negative wind shear gives a decreasing tail wind or changes a tail wind into a head wind It was found that wind shear had very little effect on the short period mode and that negative wind shear although it affected the phugoid did not cause stability problems On the other hand, it was found that positive wind shear can cause the phugoid to become aperiodic and unstable In this case a stability boundary for the phugoid was found that is valid for most aircraft at all flight speeds Calculations of aircraft motions confirmed the results of the stability analysis It was found that a flight path control automatic pilot and an airspeed control system provide good control in all types of wind shear Appendixes give equations of motion that include the effects of downdrafts and updrafts and extend the longitudinal equations of motion for shear to six degrees of freedom Author N77-28139*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va AN INVESTIGATION OF A CLOSE-COUPLED CANARD AS A DIRECT SIDE-FORCE GENERATOR ON A FIGHTER MODEL AT MACH NUMBERS FROM 0 4O TO 0 90 Richard J Re and Francis J Capone Washington Jul 1977 37 p refs (NASA-TN-D-8510 L-11613) Avail1 NTIS HC A03/MF A01 CSCL 01C ' The canard panels had 5 deg of dihedral and were deflected differentially or individually over an incidence range from 10 deg to -10 deg and a model angle-of-attack range from -4 deg to 15 deg Significant side forces were generated in a transonic tunnel by differential and single canard-panel deflections over the Mach number and angle-of-attack ranges The yawing moment resulting from the forward location of the generated side force would necessitate a vertical tail/ rudder trim force which would augment the forebody side force and be of comparable magnitude Incremental side forces yawing moments, lift and pitching moments due to single canard-panel deflections were additive that is. their sums were essentially the same as the forces and moments produced by differential canard-panel deflections of the same magnitude Differential and single canard-panel deflections produced negligible rolling moments over the Mach number and angle-of-attack ranges Author N77-2814O# Boe.ng Vertol Co . Philadelphia Pa THE CH-47C VULNERABILITY REDUCTION MODIFICATION PROGRAM FLY-BY-WIRE BACKUP DEMONSTRATION Final Report. Jul 1975 - Mar 1976 Bruce McManus and Joseph Gonsalves Aug 1976 157 p refs (Contract DAAJ02-75-C-0052. DA Pro) 1F2-62209-AH-76) (AD-A030682, D210-11046-1 USAAMRDL-TR-76-22) Avail NTIS HC A08/MF A01 CSCL 01/3 The purpose of the work performed was to accomplish a laboratory demonstration of a fly-by-wire (FBW) backup flight control system for application to the CH-47C helicopter Tests, evaluations, and an analysis were conducted to determine the feasibility of using an electrical linkage as a backup to the existing mechanical flight control system Of primary concern was the interfacing technique between the two systems, which was to result in no degradation of control system performance during normal operation and which would permit safe operation of the aircraft in the event of a failure in either the mechanical or the FBW backup system The program was performed in four tasks Task I involved the definition of a FBW backup system based on use of HLH ATC components suitable to demonstrate concept feasibility on the Boeing Iron Bird flight control test rig Task II involved the modification and installation of the system on the test rig with the actual testing and performance evaluation being conducted during Task III Task IV effort involved the reassessment of effects analysis conducted under Contract DAAJ02-74-C-0052 Author (GRA) 479 N77-38141 N77-28141# Human Engineering Labs Aberdeen Proving Ground Md HELICOPTER INTEGRATED CONTROL (GAT-2H) Final Report John D Waugh and John A Stephens Dec 1976 33 p refs (AD-A036204 HEL-TM-39-76) Avail NTIS HC A03/MF AOJ CSCL 01/3 Two experimental three-axis helicopter controls combining collective and cyclic functions into an optional one-handed controller were simulator flight tested and their performance measured in energy-expended terms was compared to conven- tional helicopter controls The nature of the results indicates that further development through flight testing should be undertaken Author (GRA) N77-28143*# National Bureau of Standards, Boulder Colo Cryogenics Div CRYOGENIC DESIGN AND SAFETY REVIEW NASA- LANGLEY RESEARCH CENTER 03 METER TRANSONIC CRYOGENIC TUNNEL R O Voth and T R Strabridge Apr 1977 28 p refs Sponsored by NASA (NASA-TM-74767. NBSIR-77-857) Avail NTIS HC A03/MF A01 CSCL 14B A cryogenic design and safety review of a 0 3 m transonic cryogenic tunnel is presented The tunnel working fluid and coolant is nitrogen The nitrogen, supplied as liquid is exhausted as a low temperature gas The tunnel and ancilliary systems are generally well designed but several recommendations to improve the cryogenic systems are made The cost of recovering the cold vent gas is compared to the cost of producing the required liquid nitrogen using a captive air separation plant Although the economic analysis is preliminary it shows that because of the periodic operation of the tunnel a captive air separation plant has a lower annual operating cost than the vent gas recovery systems considered Author N77-28144jjl Aeronautical Research Council, London (England) UREA FORMADEHYDE FOAMED PLASTIC EMERGENCY ARRESTERS FOR CIVIL AIRCRAFT G M Gwynne (RAE Bedford England) 1975 62 p refs Supersedes RAE-TR-74002 and ARC-35771 (ARC-CP-1329. RAE-TR-74002. ARC-35771 ISBN-011-470939-4) Avail NTIS HC A04/MF A01 HMSO £220.PHI Arresting trials with a Comet 3B aircraft at its maximum landing mass of 54.400 kg at speeds up to 56 kn in test beds of urea formaldehyde foam of varying depth length and density are described The mam conclusions from the trials are that retardation of the aircraft in the arrester is independent of entry speed and significant drag is contributed by both the leading and trailing wheels of a bogie arrangement and the drag is predictable The performance of the arrester is unaffected by the application of antiskid controlled wheel brakes The foam causes no significant damage to turbine engines or aircraft structure, and the addition of a foam lead in gradient to the full depth foam bed reduces the ratio of peak to mean retardation A number of minor conclusions are also presented Design examples for foarn arresters demonstrating that it should be possible to devise configurations suitable for airfields where overrun hazards exist for arresting aircraft safety without Overstressing undercarriage units due to the foam drag loads are also included Author N77-28145*# National Aeronautics and Space Administration Langley Research Center Langley Station Va FORCE TESTING MANUAL FOR THE LANGLEY 20-INCH MACH 6 TUNNEL J Wayne Keyes Jul 1977 100 p (NASA-TM-74026) Avail NTIS HC A05/MF A01 CSCL 14B Data reduction and procedures for conducting force tests in a 20 inch Mach 6 tunnel are described A discussion of pretest and testing phases are included Items that are to be checked during model design and construction are outlined as well as safety requirements, starting loads tests instructions for data acquisition and model installation Measurement of balance and model misalignment and instructions for calibrating the angle of attack screen are covered Procedures for making reference pressure attitude tare and data runs are included The 20 inch tunnel force program is examined and a description of data recording system input and load contrast sheets is given An appendix presents a description operating characteristics and Mach number calibration of the tunnel as well as tunnel characteristics Author N77-28146# Illinois Univ Urbana-Champaign Savoy Aviation Research Lab SIMULATORS FOR TRAINING AND PROFIT Charles 0 Hopkins Jul 1976 10 p refs (Contract F44620-76-C-0009) (AD-A038190. ARL-76-10/AFOSR-76-5 AFOSR-77-0373TR) Avail NTIS HC A02/MF A01 CSCL 05/9 The use of simulators for training and profit is discussed in terms of the concept of cost effectiveness Increased degree and fidelity of simulation requre greater equipment complexity and cost Data are presented that show a high negative correlation between cost and field reliability of avionics equipment There is a paucity of research data on the relationships between simulator fidelity and transfer effectiveness The results of the first and only recently completed experiment to investigate transfer of initial flight training as a function of simulator cockpit motion are summarized A rational basis for simulator selection and use developed by Jacobs and Roscoe is presented The need for research to establish relationships between transfer of training and physical characteristics such as degree and fidelity of simulation is seen as critical to the widespread future use of simulators for training and profit Author (GRA) N77-28147# Illinois Univ Urbana-Champaign Savoy Aviation Research Lab SIMULATOR COCKPIT MOTION AND THE TRANSFER OF INITIAL FLIGHT TRAINING Robert S Jacobs Jun 1976 90 p refs (Contract F44620-76-C-0009) (AO-A038194 ARL-76-8/AFOSR-76-4 AFOSR-77-0380TR) Avail NTIS HC A05/MF A01 CSCL 05/9 Transfer of flight training from a Singer-Link GAT-2 training simulator modified to approximate a counterpart Piper Cherokee Arrow airplane was measured for independent groups of nine flight-naive subjects each trained m one of three simulator cockpit motion conditions normal washout motion in bank with sustained pitch angles washout banking motion in which the drection of motion relative to that of the simulated airplane was randomly reversed 50% of the time as the cab passed through a wings-level attitude and a fixed-base condition Subjects received predeter- mined fixed amounts of practice in the simulator on each of 11 flight maneuvers drawn from the Private Pilot flight curriculum Transfer performance measures including flight time and trials to FAA performance criteria and total errors made in the process showed reliable transfer for all groups with differential transfer effects and cost effectiveness implications depending upon the type of simulator motion An aptitude estimator measure and the analysis of covanance technique provided increased discrimina- tion among groups in the presence of considerable individual variation in performance within treatment conditions Author (GRA) N77-28149# Naval Civil Engineering Lab Port Hueneme Calif EXPEDIENT STRUCTURAL SANDWICH SOIL SURFACING OF FIBERGLASS REINFORCED POLYESTER AND POLY URETHANE FOAM Technical Note, Jun 1973 - Jun 1976 M C Hironaka R B Brownie and S Tuccillo Feb 1977 66 p refs (AD-A038417 CEL-TN-1472) Avail NTIS HC A04/MF A01 CSCL 13/13 A structural soil surfacing (FOMAT) consisting of a rigid polyurethane foam core sandwiched between two fiberglass reinforced plastic (FRP) layers is being developed to fulfill a need for a designable heavy-duty expedient surfacing for Marine 480 N77-28316 Corps amphibious landing applications In analytical and laboratory investigations FOMAT showed very good potential for meeting expedient surfacing requirements The FOMAT constructed of 15- and 20-pcf-density foams will adequately carry F4 aircraft wheel loadings as determined from finite element computer analyses and plate loading tests in a mechanical simulated subgrade Tests performed on FOMAT with 20-pcf foam core showed that it meets or exceeds F4 aircraft arresting gear hook/impact and jet engine heat/blast performance specifications for a heavy-duty matting Construction of FOMAT under field conditions indicated a problem with bonding of the polyurethane foam core and the bottom FRP layer causing premature termination of simulated F4 aircraft wheel traffic tests on eight FOMAT panels located on heavy clay lean clay, and sand soils FOMAT panels consisting of 15- and 20-pcf density and 1- and 2-mch-thick foam cores were subjected to the traffic loadings At a maximum of 40 passes on two panels ot 2-mch-thick 15-pcf and 2-mch-thick 20-pcf foam core a wheel deflection of 1 inch on the FOMAT surface was experienced Development of field construction techniques to insure a positive bond between the foam core and bottom FRP layer is recommended Author (GRA) N77-2815O# Air Force Inst of Tech Wright-Patterson AFB. Ohio School of Engineering TECHNIQUES FOR THE INITIAL EVALUATION OF FLIGHT SIMULATOR EFFECTIVENESS M S Thesis Ralph L Miller Dec 1976 105 p refs (AD-A036460 GSM/SM/76D-34) Avail NTIS HC A06/MF A01 CSCL 14/2 This report presents an analysis of the development and initial evaluation of Air Force flight simulators The objectives of the study were to determine the criterion variables most applicable to an initial flight simulator evaluation and to develop a general technique for the evaluation of these criterion variables The research began with a review of current Navy Army and Air Force flight simulator development and evaluation techniques This review combined with information gathered from related sources provided the basis for examination and selection of criterion variables The variables examined by this effort were aircraft flight time saved, training efficiency transfer of training fidelity of psychological simulation fidelity of engineering simulation and simulator effectiveness The examination of these variables concentrated on their measurabihty during an initial flight simulator evaluation and their ability to predict how well a flight simulator would perform its intended mission Following the examination of criterion variables the research concentrated on the development of a technique for the evaluation of applicable criterion variables The resulting technique is a combination of the traditional quantitative techniques plus some subjective techniques The purpose of the subjective techniques is to identify simulator characteristics that are perceived to be different from the real work aircraft characteristics and to assess the impact that these differences will have on the operational use of the flight simulator Author (GRA) N77-28225* National Aeronautics and Space Administration Lyndon B Johnson Space Center Houston Tex SURFACE FINISHING Patent Jack A Kinzler James T Hefferman Leroy G Fehrenkamp and William S Lee inventors (to NASA) Issued 28 Jun 1977 8 p Filed 16 Apr 13/5 Supersedes N75-23476 (13 - 15. p 1752) (NASA-Case-MSC-12631-1 US-Patent-4 032 089 US-Patent-Appl-SN-568541 US-Patent-Class-244-123 US-Patent-Class-428-141. US-Patent-Class-428-161 US-Patent-Class-428-425 US-Patent-Class-428-457 US-Patent-Class-428-458. US-Patent-Class-156-229) Avail US Patent Office CSCL 11D A surface of an article adapted for relative motion with a fluid environment is finished by coating the surface with a fluid adhesive The adhesive is covered with a sheet of flexible film material under tension and the adhesive is set while maintain- ing tension on the film material Official Gazette of the U S Patent Office N77-28232# Hercules Inc Magna Utah Bacchus Works GRAPHITE COMPOSITE AIRCRAFT LANDING GEAR WHEEL Final Report. 18 Mar 1974 - 30 Oct 1975 May 1976 91 p (Contract F33615-74-C-3040) (AD-A036207 AFFDL-TR-76-38) Avail NTIS HC A05/MF A01 CSCL 01/3 The effort during Phase I of the contract included detailed design of a composite wheel assembly to function structurally and mechanically in a manner identical to the existing metal braked mam landing gear wheel for the T-39 aircraft The design and analysis of the graphite composite landing gear wheel was based on demonstrated material properties A thermal analysis of the composite structure showed the maximum wheel temperature to be 406 F adjacent to the steel brake keys (inner wheel half) and 223 F on the outer wheel half Hercules 4397/AS resin system was selected for the inner wheel half and 3501/AS for the outer half During Phase II one inner and two outpr wheel halves were fabricated Author (GRA) N77-28267 Aeronautical Research Labs Melbourne (Australia) THE DISTRIBUTION OF FRACTURE TOUGHNESS DATA FOR D6ac STEEL Jacqueline Coyle J M Grandage and D G Ford Aug 1976 13 p refs (ARL/Struc Note-429) Copyright Avail Issuing Activity Data on the fracture toughness of D6ac steel is analyzed for conformity with three probability distributions The three parameter extreme value distribution is selected and parameters are estimated for specified conditions Author N77 28282# Wright State Umv Dayton, Ohio Dept of Engineering LIFE PREDICTION TECHNIQUES FOR ANALYZING CREEP- FATIGUE INTERACTION IN ADVANCED NICKEL-BASE ALLOYS Final Technical Report. 8 Jul 1976 - 7 Jul 1976 M N Menon Wright-Patterson AFB. Ohio AFML Nov 1976 65 p refs (Contract F33615-76-C-5030 AF Proj 2279) (AD-A038069 AFML-TR-76-172) Avail NTIS HC A04/MF A01 CSCL 11/6 On the basis of the limited data that are presented in this study it may be concluded that the effect of creep damage on the low cycle fatigue behavior of Rene 95 at 1200 F is not very severe This is probably because of the good stress rupture properties of the material at this temperature Strain Range Partitioning approach does not seem to hold much promise for analyzing, and therefore, for predicting strain controlled low cycle fatigue behavior of Rene 95 under creep-fatigue conditions at 1200 F When compared to the SRP approach the Frequency Modified approach appears less cumbersome and, hence, more advantageous The present study indicates however that the FM approach using the frequencies calculated on the basis of the actual cycles holds only a slight edge over that involving unmodified inelastic strain range versus cyclic life representation At present, the damage approach proposed by Ostergren seems to offer more potential as it takes into account the aspect of loop shift that accompanies fatigue cycling of Rene 95 GRA N77 28316# Drexel Umv Philadelphia Pa Dept of Mechanical Engineering and Mechanics IMPACT BEHAVIOR OF POLYMERIC MATRIX COMPOSITE MATERIALS Final Technical Report. Mar 1975 - Jiri 1976 Pei Chi Chou and Richard W Mortimer Wright-Patterson AFB Ohio AFML Dec 1976 93 p refs (Contract F33615-73-C-5102) (AD-A038188. AFML-TR-76-242) Avail NTIS HC A05/MF A01 CSCL 21/5 The problem of foreign-object impacts of jet-engine fan-blades is studied by two approaches First the overall response of a blade-like structure is predicted by a one-degree-of-freedom impact model in which the blade is treated as a cantilever beam or plate Design curves are presented for finding the peak stress levels in many impact situations including both hard and soft 481 N77-28322 (fluid) impactors Second, the local response to an edge impact is studied using a finite-difference method based on amsotropic constitutive relations In addition experiments have been conducted to compare with each method Author (GRA) N77-28322*# National Aeronautics and Space Administration Langley Research Center Langley Station Va ALTERNATE AIRCRAFT FUELS PROSPECTS AND OPERATIONAL IMPLICATIONS Robert D Witcofski May 1977 44 p refs (NASA-TM-X-74030) Avail NTIS HC A03/MF A01 CSCL 21D The potential use of coal-derived aviation fuels was assessed The studies addressed the prices and thermal efficiencies associated with the production of coal-derived aviation kerosene liquid methane and liquid hydrogen and the air terminal requirements and subsonic transport performance when utilizing liquid hydrogen The fuel production studies indicated that liquid methane can be produced at a lower price and with a higher thermal efficiency than aviation kerosene or liquid hydrogen Ground facilities of liquefaction storage, distribution and refueling of liquid hydrogen fueled aircraft at airports appear technically feasibile The aircraft studies indicate modest onboard energy savings for hydrogen compared to conventional fuels Liquid hydrogen was found to be superior to both aviation kerosene and liquid methane from the standpoint of aircraft engine emissions Author N77-28325# Exxon Research and Engineering Co Linden, NJ Government Research Lab EVALUATION OF METHODS TO PRODUCE AVIATION TURBINE FUELS FROM SYNTHETIC CRUDE OILS. PHASE 2. VOLUME 2 Final Report. 24 Jan 1976 - 24 Apr 1976 Charles D Kalfadelis Wright-Patterson AFB Ohio AFAPL May 1976 365 p * (Contract F33615-74-C-2036) (AD-A03619CHEXXON/GRU2PEA76-Vol-2 AFAPL-TR-75-tO-Vol-2) Avail NTIS HC A16/MF A01 CSCL 07/1 An experimental pilot-plant program is described which has demonstrated that specification JP-4 wide-cut type and Jet A narrow-cut type aviation turbine fuels may be produced from domestic shale oils Three shale oils and two coal-derived liquids were evaluated in the program which is the second phase in a three phase overall program The original whole crude samples were assayed and fractionated to yield kerosene-boilmg-range feedstocks for catalytic hydrotreatment experiments Three levels of hydrotreatment severity were investigated using nickel- molybdenum and cobalt-molybdenum catalysts Hydrotreated products were fractionated and reblended to yield finished fuels The experimentally obtained process and analytical information will be used in the third phase of the program to provide a basis for an engineering and and economic evaluation of the effect of the use of synthetic crude oil in a refinery processing both petroleum and synthetic crude Author (GRA) N77-28440# Cambridge Univ (England) Dept of Engineer- ing A NOTE ON COMPRESSOR EXIT STATIC PRESSURE MALDISTRIBUTIONS IN ASYMMETRIC FLOW E M Greitzer 1976 18 p refs (CUED/A-Turbo/TR-79) Avail NTIS HC A02/MF A01 Conditions were examined in which a static pressure maldistribution existed at the exit of an axial flow compressor It was shown that contrary to what was often assumed the exit static pressure could be substantially nonuniform whenever there was a velocity maldistribution which was unsteady relative to the last blade row of the compressor This occurred for example in the case of a rotor moving through a steady circumferential maldistribution A physical explanation is given for the existence of this nonuniformity in static pressure as well as the phase relationship between velocity and pressure maldistributions Author N77-28485# Royal Aircraft Establishment Farnborough (England) FATIGUE STRENGTH OF JOINTS WITH SPECIAL FASTEN- ING SYSTEMS D Schuetz and J J Gerharz 1977 17 p refs Transl into ENGLISH of Schwmgfestigkeit von Fuegungen mit Sonderbefest- igungselementen Rept TM-69/73 Laboratonum fuer Betnebsfestigkeit Darmstadt 1973 (RAE-Ub-Trans-1914 BR58073 TM-69-73) Copyright Avail PHI 0 The performance of various special liutigue resistant) fasteners has been evaluated by testing under variable amplitude loading to an LBF standard spectrum for a transport aircraft wing The fasteners were tested in three types of joints which had varying degrees of load transfer and additional bending The report presents the results of the first phase of the test programme Author N77-28518# Lmkoepmg Univ (Sweden) Dept of Mechanical Engineering COMPUTER SIMULATION OF FATIGUE CRACK PROPAGA- TION IN AIRCRAFT COMPONENTS Jan Baecklund Soeren Sjoestroem and Hans Wennerstroem Feb 1977 49 p refs Sponsored by SAAB-SCANIA AB (ISBN-91-7372-147-6 ICAF-Doc-9 J4) Avail NTIS HC A03/MF A01 Cracks emanating from fastener holes propagated faster than expected in a part of the wing beam close to the fuselage Laboratory tests were performed on specimens with simplified geometry designed so as to imitate the conditions in the critical part of the wing beam Attempts to simulate the fatigue crack propagation in these specimens in a computer are presented Author N77-28525*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif AEROELASTIC ANALYSIS FOR ROTORCRAFT IN FLIGHT OR IN A WIND TUNNEL Wayne Johnson Washington Jul 1977 253 p refs Prepared in cooperation with Army Air Mobility Res and Develop Lab Moffett Field Calif (NASA-TN-D-8515 A-6740) Avail NTIS HC A12/MF A01 CSCL 01 C An analytical model is developed for the aeroelastic behavior of a rotorcraft in flight or in a wind tunnel A unified development is presented for a wide class of rotors helicopters and operating conditions The equations of motion for the rotor are derived using an integral Newtonian method which gives considerable physical insight into the blade inertia! and aerodynamic forces The rotor model includes coupled flap-lag bending and blade torsion degrees of freedom and is applicable to articulated hmgeless gimballed and teetering rotors with an arbitrary number of blades The aerodynamic model is valid for both high and low inflow and for axial and nonaxial flight The rotor rotational speed dynamics including engine inertia and damping and the perturbation inflow dynamics are included For a rotor on a wind-tunnel support a normal mode representation of the test module strut and balance system is used The aeroelastic analysis for the rotorcraft in flight is applicable to a general two-rotor aircraft including single mam-rotor and tandem helicopter configurations and side-by-side or tilting proprotor aircraft configurations Author N77-28630# Air Force Civil Engineering Center Tyndall AFB Fla THE EFFECT OF NAVY AND AIR FORCE AIRCRAFT ENGINE TEST FACILITIES ON AMBIENT AIR QUALITY Final Report, 1 Jun 1975 - 31 Jul 1976 Bradford C Grems III and Dennis F Naugle 8 Oct 1976 26 p Supersedes AFCEC-TM-76-7 (AD-A036393 AFCEC-TR-76-36 AFCEC-TM-76-7) Avail NTIS HC A03/MF A01 CSCL 21/5 An investigation of the air quality impact of DoD turbine engine test facilities was performed Emissions and pollutant dispersion from test cells and aircraft at six DoO installations were predicted using a sophisticated computer model Predicted 482 N77-29062 pollutant concentrations are compared to ambient air quality standards and measured ambient values for hydrocarbons oxides of nitrogen, and participates Jet engine test cells have no significant impact on air quality for any pollutant at any location studied Test cell pollutant concentrations are considerable less than the levels generated by aircraft operations and well below measured ambient air quality levels in the areas studied Ambient carbon monoxide and sulfur dioxide levels resulting from test cell emissions are insignificant Control of any pollutants generated by test cells would not measurably improve ambient air quality Author (GRA) N77-28911*# National Aeronautics and Space Administration Langley Research Center Langley Station Va INTERIOR NOISE REDUCTION IN A LARGE CIVIL HELICOP- TER James T Hewlett Sherman A Clevenson John A Rypf (Joint Inst for Advan of Flight Sci Hampton Va) and William J Snyder Jul 1977 43 p refs (NASA-TN-D-8477 L-11349) Avail NTIS HC A03/MF A01 CSCL 20A The results of an evaluation of the effectiveness of current noise reduction technology in attaining acceptable levels of interior noise in a large (about 20 000 kg) passenger-carrying helicopter are presented The helicopter studied is a modified CH-53A with a specially designed acoustically treated passenger cabin The acoustic treatment reduced the average A-weighted interior noise levels from 115 db to 87 db The study suggests selected improvements in the acoustic treatment which could result in additional reduction in cabin noise levels The resulting levels would be only slightly greater than the interior noise levels of current narrow-body jet transports Author N77-28914# California Inst of Tech Pasadena Guggenheim Jet Propulsion Center EXPERIMENTAL STUDIES OF THE NOISE PRODUCED IN A SUPERSONIC NOZZLE BY UPSTREAM ACOUSTIC AND THERMAL DISTURBANCES Final Report Jerome M Auerbach Washington DOT Jun 1976 259 p refs (Contract DOT-OST-20197) (PB-264933/3 DOT-TST-76-105) Avail NTIS HC A12/MF A01 CSCL 21E A steady accelerating flow was produced in a rectangular supersonic nozzle with an entrance Mach number of 0 2 - and an exit Mach number of 1 38 A rotary valve bleed flow system and an electrical wire resistance heater upstream of the nozzle introduced mass flow and temperature fluctuations into the nozzle flow at frequencies up to 500 Hz Sound measurements were made at six positions along the nozzle and outside the nozzle assembly, which was enclosed in an anechoic chamber All data acquisition and processing was done with a computer- controlled data acquisition system By synchronization of the bleed flow and heater a pure temperature disturbance without an associated pressure disturbance caused by heating was produced GRA are made to the single event noise levels to account for frequency of operations and the adjusted levels are added logarithmically to represent all of the classes of aircraft using the airport GRA N77-28980# Defense Systems Management School Fort Belvoir Va RETURNING ROT AND E ASSETS (AIRCRAFT) TO OPERATIONAL USAGE Student Project Report David M Sjuggerud Nov 1976 36 p refs (AD-A036484) Avail NTIS HC A03/MF A01 CSCL 05/1 The purpose of this study report is to review past aircraft programs to gain insight as to what aircraft utilization and program management techniques can be considered in the recovery and continued service utilization of RDT and E aircraft after reconfigura- tion GRA N77-29059*jjl National Aeronautics and Space Administration Langley Research Center Langley Station, Va COLLECTED WORKS OF CHARLES J DONLAN [1976] 772 p refs (NASA-TM-74826) Avail NTIS HC A99/MF A01 CSCL 02A Spin tests and wind tunnel tests for various types of experimental aircraft are discussed The fighter aircraft and monoplanes of the World War II era are emphasized N77-29060*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AN APPROXIMATE SPIN DESIGN CRITERION FOR MONOPLANES. 1 MAY 1939 Oscar Seidman and Charles J Donlan In its Collected Works of Charles J Donlan [1976] 11 p refs (NACA-TN-711) Avail NTIS HC A99/MF A01 CSCL QIC An approximate empirical criterion based on the projected side area and the mass distribution of the airplane was formulated The British results were analyzed and applied to American designs A simpler design criterion based solely on the type and the dimensions of the tail was developed, it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning Author N77-29061*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SPIN TESTS OF A 1/20 SCALE MODEL OF THE XP 39 AIRPLANE. 15 MARCH 1939 Charles J Donlan In iti Collected Works of Charles J Donlan [1976] 23 p refs Sponsored in part by Army Avail NTIS HC A99/MF A01 CSCL 01C The tests were performed to determine the spinning characteristics of a 1/20-scale model of the Bell XP-39 airplane Effects of loading changes and of various control dispositions were studied Subsequent tests were performed to determine the effect of a change in wing dihedral Author N77-28918# Bolt Beranek and Newman. Inc Canoga Park, Calif CALCULATION OF DAY-NIGHT LEVELS (LDN) RESULTING FROM CIVIL AIRCRAFT OPERATIONS Final Report D E Bishop A P Hays N H Reddmgius and H Seidman Mar 1976 374 p refs (Contract EPA-68-01-3218) (PB-266165/0 BBN-3157 EPA-550/9-77-450) Avail NTIS HCA16/MFA01 CSCL 20A A method is described for calculating the day/night noise level at a point due to aircraft operations from an airport Factors considered include type of takeoff and landing procedure range and non-standard glide slopes The procedure used is to locate the position of the point in question relative to the runway and aircraft flight track A series of charts give Ldn values for different types of aircraft in terms of the distance parameters Adjustments N77-29062*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SPIN TESTS OF A 1/2O-SCALE MODEL OF THE XF4U-1 AIRPLANE. 12 JULY 1939 Charles J Donlan In its Collected Works of Charles J Donlan [1976] 47 p refs Sponsored in part by Navy Avail NTIS HC A99/MF A01 CSCL01C These tests were performed to determine the spinning characteristics of the 1/20-scale model of the XF4U-1 airplane Effects of loading changes and vanous control dispositions using both the original and modified vertical taH surfaces were studied Subsequent tests were made to determine the effects of additional tail modifications Author 483 N77-29063 N77-29063*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SPIN TESTS OF 1/16 SCALE MODELS OF THE N3N-3 LANDPLANE AND SEAPLANE. 12 JANUARY 194O Charles J Donlan In its Collected Works of Charles J Oonlan [1976] 37 p refs Sponsored in part by Navy Avail NTIS HC A99/MF A01 CSCL01C The test program included the study of both the seaplane and landplane types On both versions of the model the effects of loading changes and control dispositions were examined and on the seaplane the effect of the cowled and uncowled engine was investigated Author N77-29064*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SPIN TESTS OF A LOW-WING MONOPLANE TO INVESTI- GATE SCALE EFFECT IN THE MODEL TEST RANGE. MAY 1941 Charles J Donlan In its Collected Works of Charles J Donlan [1976] 23 p refs (NACA-TN-807) Avail NTIS HC A99/MF A01 CSCL01C Concurrent tests were performed on a 1/16 and a 1/20 scale model (wing spans of 2 64 and 2 11 ft respectively) of a modern low wing monoplane in the NACA 15 foot free-spinning wind tunnel Results are presented in the form of charts that afford a direct comparison between the spins of the two models for a number of different conditions Qualitatively the same characteristic effects of control disposition mass distribution and dimensional modifications were indicated by both models Quantitatively the number of turns for recover and the steady spin parameters with the exception of the inclination of the wing to the horizontal, were usually in good agreement Author N77-29065*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va METHODS OF ANALYZING WIND-TUNNEL DATA FOR DYNAMIC FLIGHT CONDITIONS Charles J Donlan and I G Recant In its Collected Works of Charles J Donlan [1976] 43 p refs (NACA-TN-828) Avail NTIS HC A99/MF A01 CSCL 01A The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind tunnel tests alone Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power The response of an airplane to a rolling and a yawing disturbance is dis- cussed particularly in regard to changes in wing dihedral and fin area Solutions of the lateral equations of motion are given in a form suitable for direct computations An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections Author N77-29066*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THE EFFECT OF COWLING SHAPE ON THE STABILITY CHARACTERISTICS OF AN AIRPLANE. SEPTEMBER 1942 Charles J Donlan and W Letko In its Collected Works of Charles J Donlan [1976] 21 p refs (L-343) Avail NTIS HC A99/MF A01 CSCL01C Three widely different nose shapes were tested on a fuselage alone and on a complete model in the NACA stability tunnel to investigate the effect of cowling shape on stability characteristics The results are presented in the form of charts which show the variation in the aerodynamic characteristics with the three nose shapes for the propeller-removed condition over a wide range of angles of attack and yaw The results indicated that large changes in the cowling shape produced relatively small changes in the aerodynamic characteristics The effects may be appreciable however m the case of an airplane that has marginal stability Author N77-29067*# National Aeronautics and Space Administration Langley Research Center Langley Station Va SOME THEORETICAL CONSIDERATIONS OF LONGITUDI- NAL STABILITY IN POWER-ON FLIGHT WITH SPECIAL REFERENCE TO WIND-TUNNEL TESTING. NOVEMBER 1942 Charles J Donlan In its Collected Works of Charles J Donlan [1976] 25 p refs (L-309) Avail NTIS HC A99/MF A01 CSCL01C Some problems relating to longitudinal stability in power-on flight are considered A derivation is included which shows that under certain conditions the rate of change of the pitching moment coefficient with lift coefficient as obtained in wind tunnel tests simulating constant power operation is directly proportional to one of the indices of stability commonly associated with flight analysis (the slope of the curve relating the elevator angle for trim and lift coefficient) The necessity of analyzing power-on wind tunnel data for trim conditions is emphasized and a method is provided for converting data obtained from constant thrust tests to simulated constant throttle flight conditions Author N77-29068*# National Aeronautics and Space Administration Langley Research Center Langley Station Va LATERAL STABILITY AND CONTROL TESTS OF THE XP-77 AIRPLANE IN THE NACA FULL-SCALE TUNNEL. 16 JUNE 1944 K R Czarnecki and Charles J Donlan In its Collected Works of Charles J Donlan [1976] 84 p refs Sponsored in part by Army Avail NTIS HC A99/MF A01 CSCL01C Tests were made in the NACA full-scale tunnel to determine the lateral stability and control characteristics of the XP-77 airplane Measurements were made of the forces and moments on the airplane at various angles of attack and angles of yaw The measurements were made with the propeller removed and with the propeller installed and operating at various thrust coefficients and with the landing flaps retracted and deflected The effects of aileron elevator and rudder deflection on control surface effectiveness and hinge moments were determined The tests were planned to obtain the data required to evaluate as completely as possible the Army Air Force requirements on lateral stability and control for pursuit-type airplanes Author N77-29069*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THE LATERAL FLYING QUALITIES OF THE BELL XP-77 AIRPLANE AS ESTIMATED FROM FULL-SCALE TUNNEL TESTS. 16 JUNE 1944 Charles J Donlan and K R Czarnecki In its Collected Works of Charles J Donlan [1976] 23 p refs Sponsored in part by Army Avail NTIS HC A99/MF A01 CSCL 01A Results are presented for tests made of the full scale model of the airplane in the NACA full scale tunnel These tests were planned so as to cover as completely as possible the lateral flying quality requirements for pursuit-type airplanes contracted for by the United States Army Air Forces Author N77-29070*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THE STABILITY AND CONTROL OF TAILLESS AIRPLANES. 19 AUGUST 1944 Interim Report Charles J Donlan comp In its Collected Works of Charles J Donlan (1976) 16 p refs (Rept-796) Avail NTIS HC A99/MF A01 CSCL 01C In the present state of the design of tailless airplanes it appears that (1) Sweepback affords a method of supplying tail length for directional and longitudinal stability and control and allows the utilization of a high lift flap but introduces undersirable 484 N77-29077 tip stalling tendencies that must be overcome before the advantages of sweepback can be realized (2) The damping in pitching appears to have little effect on the longitudinal behavior of the airplane provided the static margin is never permitted to become negative (3) The directional stability must be as great as for conventional airplanes if the same requirements regarding satisfactory stability and control characteristics are to be adhered to (4) The influence of the lateral resistance and the damping in yawing on the flying qualities is somewhat obscure Author N77-29071*# National Aeronautics and Space Administration Langley Research Center. Langley Station. Va WIND-TUNNEL TESTS OF A 1/4 SCALE MODEL OF THE BELL XS-1 TRANSONIC AIRPLANE 1 LONGITUDINAL STABILITY AND CONTROL CHARACTERISTICS Charles J Donlan W B Kemp and E C Polhamus In its Collected Works of Charles J Donlan [1976] 78 p refs (DA Pro) 653) (L6D12) Avail NTIS HC A99/MF A01 CSCL01A A 1/4 scale model of the Bell XS-1 transonic aircraft was tested in the Langley 300 mile-per-hour 7 by 10 foot tunnel to determine its low speed longitudinal stability and control characteristics Pertinent longitudinal flying qualities expected of the XS-1 research airplane were estimated from the results of these tests including the effects of compressibility likely to be encountered at speeds below the force break It appears that the static longitudinal stability and elevator control power will be adequate, but that the elevator control force gradient in steady flight will be undesirably low for all configurations It is suggested that a centering spring be incorporated in the elevator control system of the airplane in order to increase the control force gradient in steady flight and in maneuvers Author N77-29072*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va CURRENT STATUS OF LONGITUDINAL STABILITY. 24 MAY 1948 Charles J Donlan In its Collected Works of Charles J Donlan [1976] 17 p refs (L8A28) Avail NTIS HC A99/MF A01 CSCL01C The problems of static and dynamic longitudinal stability both at high speeds and at low speeds are discussed and data are presented which indicate progress made in the solution of these problems It is shown that the incorporation of large amounts of sweepback on both the wing and the horizontal tail can significantly increase the Mach number at which critical trim changes and stability changes occur and can greatly reduce the trim changes and stability changes encountered at supercritical speeds Data are also presented which demonstrate the possibility of obtaining satisfactory longitudinal stability in the landing configuration for wings with sweepback of the order of 45 deg utilizing various stall control devices Optimum arrange- ments for such devices however should be determined experimentally Author N77-29073*# National Aeronautics and Space Administration Langley Research Center Langley Station Va FACTORS AFFECTING STATIC LONGITUDINAL STABILITY AND CONTROL Charles J Donlan In its Collected Works of Charles J Donlan [1976] 16 p refs Avail NTIS HCA99/MFA01 CSCL01C The various factors that constitute static longitudinal stability and control are reviewed and the influence on these factors of power effects and Mach number effects are indicated Author N77-29074*jjl National Aeronautics and Space Administration Langley Research Center Langley Station Va LOW-SPEED WIND-TUNNEL INVESTIGATION OF THE LONGITUDINAL STABILITY CHARACTERISTICS OF A MODEL EQUIPPED WITH A VARIABLE-SPEED WING. 23 MAY 1949 Charles J Donlan and William C Sleeman Jr In its Collected Works of Charles J Donlan [1976] 43 p refs (L9B18) Avail NTIS HC A99/MF A01 CSCL 01A The longitudinal stability characteristics of a complete model equipped with a variable sweep wings at angles of sweepback of 45 deg 30 deg 15 deg and 0 deg investigated Various wing modifications and an extern 1 flap arrangement designed to minimize the shift in neutral point accompanying the change in sweep angle were studied The results indicate that stability at the stall was obtained at a sweep angle of 15 deg without recourse to stall control devices The basic neutral point movement accompanying the change in sweep angle from 45 deg to 15 deg amounted to 56 percent of the mean aerodynamic chord (at zero sweep angle) and the most effective modification investigated only reduced this change to 47 percent of the chord It appears, therefore that for designs in which the fuselage is the major load carrying element some relative movement between the wing and center of gravity will be required to assure satisfactory stability at all sweep angles Author N77-29075*# National Aeronautics and Space Administration Langley Research Center Langley Station Va ESTIMATED TRANSONIC FLYING QUALITIES OF A TAILLESS AIRPLANE BASED ON A MODEL INVESTIGA- TION. 8 JUNE 1949 Charles J Donlan and Richard E Kuhn In its Collected Works of Charles J Donlan [1976] 62 p refs (L9D08) Avail NTIS HC A99/MF A01 CSCL 01A Flying qualities of a tailless airplane with the wing quarter chord line swept back 35 deg were analyzed in the Mach number range from 040 to 091 based on tests of a model of this airplane in the Langley high speed 7 by 10 foot tunnel The results indicate that longitudinal control position instability exists at transonic speeds but the accompanying trim changes are not large Control position maneuvering stability however, is present for all speeds Longitudinal and lateral control appear adequate, but the damping of the short period longitudinal and lateral oscillations at high altitudes is poor and would probably require artificial damping Author N77-29076*# National Aeronautics and Space Administration Langley Research Center. Langley Station, Va SOME EFFECTS OF SWEEPBACK AND AIRFOIL THICK- NESS ON LONGITUDINAL STABILITY AND CONTROL CHARACTERISTICS AT TRANSONIC SPEEDS Charles J Donlan and An/a A Luoma In its Collected Works of Charles J Donlan [1976] 12 p refs Avail NTIS HCA99/MFA01 CSCL 01C Information on the longitudinal stability and control character- istics of complete transonic airplane configurations is compiled in a form that might indicate whether or not a consistent pattern of behavior exists in regard to the effects of airfoil thickness and sweepback on overall stability and control characteristics at transonic speeds Author N77-29077*# National Aeronautics and Space Administration Langley Research Center Langley Station Va A COMPARISON OF THE AERODYNAMIC CHARACTERIS- TICS AT TRANSONIC SPEEDS OF FOUR WING-FUSELAGE CONFIGURATIONS AS DETERMINED FROM DIFFERENT TEST TECHNIQUES. 4 OCTOBER 1960 Charles J Donlan Boyd C Myers II and Axel T Mattson In its Collected Works, of Charles J Donlan [1976] 65 p refs (L50H02) Avail NTIS HC A99/MF A01 CSCL 01A ' The high speed aerodynamic characteristics of a family of four wing-fuselage configurations of 0 35 45 and 60 deg sweepback were determined from transonic bump model tests that were conducted in the Langley high speed 7 by 10 foot tunnel sting supported model tests were conducted in the Langley 8 foot high speed tunnel and in the Langley high speed 7 by 10 foot tunnel and rocket model tests were conducted by the Langley Pi'otless Aircraft Research Division A complementary 485 N77-29078 study of the effect of Mach number gradients and streamline curvature on bump resul's is also included The qualitative data obtained from the various test facilities for the wing-fuselage configurations were in essential agreement as regards the relative effects of sweepback and Mach number except for drag at zero lift Quantitatively important differences were present Author N77-29078*# National Aeronautics and Space Administration Langley Research Center Langley Station Va CHARACTERISTICS OF SWEPT WINGS AT HIGH SPEEDS. 30 JANUARY 1952 Charles J Donlan and Joseph Weil In its Collected Works of Charles J Donlan [1976] 20 p refs (L52A15) Avail NTIS HC A99/MF A01 CSCL01C Some results of recent swept wing investigations are presented that were undertaken to determine the effects of thickness and thickness distribution camber and twist nose-flap deflection and devices or fixes for improving the wing pitching moment characteristics at high lift coefficients Author N77-29079*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AN ASSESSMENT OF THE AIRPLANE DRAG PROBLEM AT TRANSONIC AND SUPERSONIC SPEEDS, 15 JULY 1974 Charles J Donlan In its Collected Works of Charles J Donlan [1976] 16 p refs Presented at Meeting of NACA Comm on Aerodyn Langley Station Va 28 Apr 1954 (L54F16) Avail NTIS HC A99/MF A01 CSCL 01A The factors influencing the drag of bodies of revolution are reviewed and the effectiveness in reducing wave drag of various methods of improving the cross sectional area distribution of aircraft configurations is illustrated It is demonstrated that irrespective of the method adopted for improving area distribution a high effective fineness ratio and smooth area progressions along the equivalent body are essential to the achievement of low drag Author N77-29082*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va PROPORTIONING THE AIRPLANE FOR LATERAL STABIL- ITY Charles J Donlan In its Collected Works of Charles J Donlan [1976] 6 p refs Avail NTIS HC A99/MF A01 CSCL QIC Proportioning for lateral aircraft control included (1) directional stability (slope of curve of yawing moment coefficient against sideslip) and (2) effective dihedral factor (slope of curve of rolling moment coefficient against sideslip) Basic forces influencing the directional stability of aircraft are indicated Propeller side force, basic fuselage yaw and vertical tail side force contributed to yaw moment about center of gravity JAM N77-29085*# Aerophysics Research Corp Bellevue. Wash NSEG. A SEGMENTED MISSION ANALYSIS PROGRAM FOR LOW AND HIGH SPEED AIRCRAFT VOLUME 1 THEORETICAL DEVELOPMENT Final Report D S Hague and H L Rozendaal Washington NASA Aug 1977 82 p refs 3 Vol (Contract NAS1-13599) (NASA-CR-2807) Avail NTIS HC A05/MF A01 CSCL 02A A rapid mission analysis code based on the use of approximate flight path equations of motion is presented Equation form varies with the segment type for example accelerations climbs cruises descents and decelerations Realistic and detailed characteristics were specified in tabular form The code also contains extensive flight envelope performance mapping capabilities Approximate take off and landing analyses were performed At high speeds centrifugal lift effects were accounted for Extensive turbojet and ramjet engine scaling procedures were incorporated in the code Author N77-29086 California Umv Los Angeles A STUDY OF THE EFFECT OF UNSTEADY AERODYNAMICS ON THE AEROELASTIC STABILITY OF ROTOR BLADES IN HOVER Ph D Thesis Cheng-Hsien Yuan 1976 166 p Avail Umv Microfilms Order No 77-8539 Various existing unsteady aerodynamic strip theories which have been developed in the past for both fixed and rotary wing aerodynamic analyses are modified so as to make them applicable to the coupled flap-lag-torsional aeroelastic problem of a rotor blade in hover The modified strip theories are incorporated in a coupled flap-lag-torsional aeroelastic analysis The results indicate that the various unsteady aerodynamic strip theories available must be modified and reinterpreted when applying them to the coupled flap-lag-torsional aeroelastic problem of a rotor blade in hover These modifications are primarily due to constant angle of attack constant inflow and variable free stream velocity due to lead-lag motion Dissert Abstr N77-29087 Minnesota Umv Minneapolis DYNAMICS AND STABILITY OF LIFTING PARACHUTES Ph D Thesis David Paul Saan 1976 209 p Avail Umv Microfilms Order No 77-6999 ' ' A dynamic model is formulated which is capable of describing the three-dimensional motion of a general parachute-load system with general initial conditions and a method is presented for determining five components of aerodynamic force and moment as functions of general angles of attack in three-dimensional motion Wind tunnel measurements of the aerodynamic coef- ficients for a lifting parachute made at a Reynolds number of 5 500 00 is presented Dissert Abstr N77-29089 California Umv Los Angeles THE COUPLED FLAP-LAG-TORSIONAL AEROELASTIC STABILITY OF HELICOPTER ROTOR BLADES IN FORWARD FLIGHT Ph D Thesis Manuel Reyna-Allende 1976 295 p Avail Umv Microfilms Order No 77 8530 A set of coupled flap lag torsional equations of motion capable of simulating general hingeless rotor blade configurations are derived for the case of a rotor blade having moderate deflections The final equations of motion are represented by a system of coupled nonlinear partial differential equations The equations are capable of simulating rotor blades having (1) precone (2) droop (3) built in twist (4) distributed torsion (5) root torsion (or pitch link flexibility) (6) blade root offsets (7) and offsets between the elastic axis aerodynamic center and the blade cross sectional center of mass Quasisteady aerodynamic loads are used and the effects of stall and compressibility are neglected Reversed flow is included in the representation of the airloads Dissert Abstr N77-29090 Georgia Inst of Tech Atlanta A METHOD OF COMPUTING THE POTENTIAL FLOW ON THICK WING TIPS Ph D Thesis Pradeep Rao 1976 174 p Avail Umv Microfilms Order No 77-7352 An iterative procedure to compute detailed velocity and pressure distributions on the surface of thick wing tips is developed using potential flow theory The method uses a two dimensional surface vorticity distribution as an initial approximation Therefore the two dimensional problem ii> first formulated in the form of an integral equation using vorticity as the surface singularity which is solved by the elementary vortex distribution technique A comparison of the flow computed on a circular cylinder with the exact analytical results provides a measure of accuracy The two dimensional noncirculatory and circulatory flow is computed for NACA basic thickness form airfoils Dissert Abslr N77-29091 Cornell Umv Ithaca N Y TWO PROBLEMS THAT ARISE IN THE GENERATION AND PROPAGATION OF SONIC BOOMS 1 FLOW FIELD IN 486 N77-29102 THE PLANE OF SYMMETRY BELOW A DELTA WING 2 FOCUSING OF AN ACOUSTIC PULSE AT AN ARETE Ph D Thesis Mark Stephen Cramer 1976 42 p Avail Univ Microfilms Order No 77-8353 The flow field in the plane of symmetry of a thin lifting delta wing with supersonic leading edges is examined A simplified treatment of the interaction between the plane expansion wave enamatmg from the trailing edge and the three-dimensional bow shock is presented In the region unaffected by the wing tips the shock decays inversely with distance from the wing The focusing of a nearly straight acoustic wavefront is examined The equation that describes this focusing is derived and the resulting similitude discussed The initial conditions come from a formal matching of this nonlinear description with the linear solution The maximum value of the pressure coefficient is shown to be proportional to the two thirds power of both the initial strength of the wavefront and a small parameter characterizing its straightness Dissert Abstr N77-29095*# Rockwell International Corp Los Angeles Calif Aircraft Div LOW SPEED AERODYNAMIC CHARACTERISTICS OF A VECTORED THRUST V/STOL TRANSPORT WITH TWO LIFT/CRUISE FANS Dirk J Renselaer Jul 1977 201 p refs (Contract NAS2-9003) (NASA-CR-152029) Avail NTIS HC A10/MF A01 CSCL 01A A wind tunnel test was conducted to obtain power on low speed characteristics of a twin fan vectored thrust V/STOL transport aircraft Longitudinal as well as some lateral directional data were analyzed Hover STOL and conventional flight modes were investigated Determination of STOL characteristics hover characteristics roll control effectiveness and aircraft attitude were evaluated The study also included various means to improve the lifting capability of the aircraft such as by application of fuselage strakes exhaust vanes capable of shifting the thrust vector aft and external flap blowing for STOL performance Author N77-29096*# National Aeronautics and Space Administration Langley Research Center Langley Station Va LOW-SPEED WIND TUNNEL INVESTIGATION OF AN ADVANCED SUPERSONIC CRUISE ARROW-WING CONFIGURATION Paul L Coe Jr Paul M Smith (Vought Corp Hampton Va) and Lysle P Parlett Jul 1977 85 p refs (NASA-TM-74043) Avail NTIS HC A05/VF A01 CSCL 01A A preliminary assessment of possible means for improving the low speed aerodynamic characteristics of advanced supersonic cruise arrow wing configurations and to extend the existing data base of such configurations has been made Principle configuration variables included wing-leading and trailmg-edge flap deflection fuselage nose strakes and engine exhaust nozzle deflection Results showed that deflecting the wing leading edge apex flaps downward provided improved longitudinal stability but resulted in reduced directional stability The model exhibited relatively low values of directional stability over the operational angle of attack range and experienced large asymmetric yawing mo- ments at high angles of attack The use of nose strakes was found to be effective in increasing the irectional stability and eliminating the asymmetric yawing moment Author N77-29O97*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va LOAD DISTRIBUTION ON A CLOSED-COUPLED WING CANARD AT TRANSONIC SPEEDS Blair B Gloss and Karen E Washburn Aug 1977 11 p refs (NASA-TM-74053) Avail NTIS HC A02/MF A01 CSCL 01A A wind tunnel test where load distributions were obtained at transonic speeds on both the canard and wing surfaces of a closely coupled wing canard configuration is reported Detailed component and configuration arrangement studies to provide insight into the various aerodynamic interference effects for the leading edge vortex flow conditions encountered are included Data indicate that increasing the Mach number from 0 70 to 095 caused the wing leading edge vortex to burst over the wing when the wing was in the presence of the high canard Author N77-29O98'# National Aeronautics and Space Administration Hugh L Dryden Flight Research Center Edwards Calif F-8 SUPERCRITICAL WING FLIGHT PRESSURE, BOUNDARY LAYER. AND WAKE MEASUREMENTS AND COMPARISONS WITH WIND TUNNEL DATA Lawrence C Montoya and Richard D Banner Washington Jun 1977 194 p refs (NASA-TM-X-3544. H-850) Avail NTIS HC A09/MF A01 CSCL01A Data for speeds from Mach 0 50 to Mach 0 99 are presented for configurations with and without fuselage area-rule additions with and without leading-edge vortex generators and with and without boundary-layer trips on the wing The wing pressure coefficients are tabulated Comparisons between the airplane and model data show that higher second velocity peaks occurred on the airplane wing than on the model wing The differences were attributed to wind tunnel wall interference effects that caused too much rear camber to be designed into the wing Optimum flow conditions on the outboard wing section occurred at Mach 0 98 at an angle of attack near 4 deg The measured differences in section drag with and without boundary-layer trips on the wing suggested that a region of laminar flow existed on the outboard wing without trips Author N77-29100*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif MEASUREMENTS OF SURFACE-PRESSURE AND WAKE- FLOW FLUCTUATIONS IN THE FLOW FIELD OF A WHIT- COMB SUPERCRITICAL AIRFOIL ' Frederick W Roos (McDonnell Douglas Corp St Louis Mo) and Dennis W Riddle Washington Aug 1977 %3 p refs (NASA-TN-D-8443 A-6877) Avail NTIS HC^A04/MF A01 CSCL 01A Measurements of surface pressure and wake flow fluctuations were made as part of a transonic wind tunnel investigation into the nature of a supercritical airfoil flow field Emphasis was on a range of high subsonic Mach numbers and moderate lift coefficients corresponding to the development of drag diver- gence and buffeting Fluctuation data were analyzed statistically for intensity frequency content and spatial coherence Variations in these parameters were correlated with changes in the mean airfoil flow field Author N77-29101*# National Aeronautics and Space Administration Langley Research Center Langley Station. Va EFFECT OF WINGLETS ON A FIRST-GENERATION JET TRANSPORTWING 2 PRESSURE AND SPANWISE LOAD DISTRIBUTIONS FOR A SEMI SPAN MODEL AT HIGH SUBSONIC SPEEDS Lawrence C Montoya (NASA Dryden Flight Research Center) Stuart G Flechner and Peter F Jacobs Washington Jul 1977 211 p refs (NASA-TN-D-8474 L-1 1026) Avail NTIS HC A10/MF A01 CSCL 01A Pressure and spanwise load distribution on a first generation jet transport semispan model at high subsonic speeds are presented The data were given for the basic wing and for configurations with an upper wmglet only upper and lower winglets. and a simple wing tip extension Selected data were discussed to show the general trends and effects of the various configurations Author N77-29102*# National Aeronautics and Space Administration Langley Research Center Langley Station. Va SUBSONIC AND SUPERSONIC AERODYNAMIC CHARAC- TERISTICS OF A SUPERSONIC CRUISE FIGHTER MODEL WITH A TWISTED AND CAMBERED WING WITH 74 DEG SWEEP 487 N77-29105 Odell A Morns Washington Aug 1977 63 p refs (NASA-TM-X-3530 L-11457) Avail NTIS HC A04/MF A01 CSCL 01A A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic characteristics of a model of a supersonic cruise fighter configuration with a design Mach number of 2 60 The configuration is characterized by a highly swept arrow wing twisted and cambered to minimize supersonic drag due to lift twin wing mounted vertical tails, and an aft mounted integral underslung duel-engine pod The investigation also included tests of the configuration with larger outboard vertical tails and with small nose strakes Author N77-29105# National Aerospace Lab Amsterdam (Netherlands) Fluid Dynamics Div PREDICTION OF AERODYNAMIC INTERFERENCE EFFECTS ON A FIGHTER TYPE WING-TIP TANK CONFIGURATION WITH AND WITHOUT PYLON AND STORE H A Sytsma 5 Mar 1975 36 p refs (Contract RNLAF-RB-KL-1975/S3) (NLR-TR-75070-U) Avail NTIS HC A03/MF A01 Using the NLR panel method pressure distribution was calculated for a fighter type wing-tiptank configuration with and without pylon and store to establish the applicability of this panel mwthod to the aerodynamic interference problems associated with this type of configurations Calculated pressure distributions on wing and store are compared with experimental results Agreement between theoretical and experimental results is satisfactory Author (ESA) N77-29108# European Space Agency Pans (France) BEHAVIOR OF A SUBSONIC FLOW PAST A THIN WING IN THE VICINITY OF THE LEADING EDGE Jean-Sylvestre Darrozes Jul 1977 48 p refs Transl into ENGLISH of 'Comportement d'un Ecoulement Subsonique au Voismage du Bord dAttaque dune Aile Mince ONERA Pans Report ONERA-NT-1976-16 Feb 1977 Original report in FRENCH previously announced as N77-25107 (ESA-TT-401 ONERA-NT-1976-16) Avail NTIS HC A03/MF A01 The technique of matched asymptotic expansions leads to a uniformly valid description of a subsonic flow past a thin wing with round edges The outer solution is the classical one given by the linearized theory The inner problem requires a local formulation which corresponds to a local subsonic flow past a parabola in a plane normal to the leading edge The inner solution is given explicitly in the case of weakly subsonic flows Author (ESA) N77-29111*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif REAL-TIME MANNED SIMULATION OF ADVANCED TERMINAL AREA GUIDANCE CONCEPTS FOR SHORT- HAUL OPERATIONS Leonard Tobias and Paul J OBrien Washington Aug 1977 33 p refs Prepared in cooperation with the Natl Aviation Facilities Exptl Center, Atlantic City N J (NASA-TN-D-8499 A-6841) Avail NTIS HC A03/MF A01 CSCL 17G A real-time simulation was conducted of three-dimensional area navigation and four-dimensional area navigation equipped (STOL) aircraft operating in a high-density terminal area traffic environment The objectives were to examine the effects of 3D RNAV and 40 RNAV equipped aircraft on the terminal area traffic efficiency, and to examine the performance of an air traffic control system concept and associated controller display proposed for use with advanced RNAV systems Three types of STOL aircraft were simulated each with different performance capabilities System performance was measured in both the 4D mode and in a 3D mode, the 3D mode used as a baseline was simply the 4D mode less any time specification The results show that communications workload in the 4D mode was reduced by about 35 percent compared to the 3D while 35 percent more traffic was handled with the 4D Aircraft holding time in the 4D mode was only 30 percent of that required in the 3D mode In addition the orderliness of traff ic was improved significantly in the 4D mode Author N77-29112# Civil Aeromedical Inst Oklahoma City Okla AN EPIDEMIOLOGIC INVESTIGATION OF OCCUPATION. AGE AND EXPOSURE IN GENERAL AVIATION AC- CIDENTS Charles F Booze Apr 1977 22 p refs (AD-A040978 FAA-AM-77-10) Avail NTIS HC A02/MF A01 CSCL 01/2 A census of general aviation accident-involved airmen records was studied Population comparison data for occupation age exposure and other epidemiologic profile information were obtained from a sample of currently certified airmen medical records Author N77-29113# National Aviation Facilities Experimental Center Atlantic City N J ANALYSIS OF SELECTED GENERAL AVIATION STALL/SPIN ACCIDENTS Final Report. Feb - Jun 1975 Jack Shrager Apr 1977 90 p refs (FAA Pro) 184-520-100) (AD-A040824 FAA-NA-77-2 FAA-RD-77-411 Avail NTIS HC A05/MF A01 CSCL 01/2 An automated data search of existing general avia'ion data bases was employed in an effort to relate aircraft stall/spin accident history to general design characteristics The technique utilized a chi square analysis to evaluate a stall/spin history of selected aircraft The statistical analysis indicated that accident rates are influenced by aircraft usage and by pilot experience Low horsepower low stallspeed aircraft have a higher propensity to stall/spin accidents the highest incidence being in the takeoff phase of flight Author N77-29114*# Summerfield Associates Santa Monica Calif A STUDY OF COMMUTER AIRLINE ECONOMICS Final Report John R Summerfield Dec 1976 24 p refs (NASA Order A-29917-B) (NASA-CR-152035) Avail NTIS HC A02/MF A01 CSCL 05C Variables are defined and cost relationships developed that describe the direct and indirect operating costs of commuter airlines The study focused on costs for new aircraft and new aircraft technology when applied to the commuter airline industry With proper judgement and selection of input variables the operating costs model was shown to be capable of providing economic insight into other commuter airline system evalua- tions J H N77-29115# Naval Air Development Center Warmmster Pa Crew Systems Dept DEVELOPMENT OF AN INFLATABLE HEAD/NECK RE- STRAINT SYSTEM FOR EJECTION SEATS Interim Report Thomas J Zenobi 28 Feb 1977 32 p (AD-A038762 NADC-76357-40) Avail NTIS HC A03/MF A01 CSCL 06/7 A ring-shaped inflatable head/neck restraint system for ejection seats is being developed at the Crew Systems Department NADC The purpose of this system is to reduce neck injuries due to violent forward head rotation at the time of ejection thrust and parachute opening shock Inflation of the neck ring will be conducted by a solid propellant gas generator Design considerations include form-and-fit cost effectiveness packaging and integration into life support equipment Author (GRA) N77-29117# National Aviation Facilities Experimental Center Atlantic City N J LONGITUDIAL SEPARATION ANALYSIS OF THE CENTRAL EAST PACIFIC TRACK SYSTEM Final Report, Dec 1973 - Jun 1974 488 N77-29128 Wayne E Smoot Jun 1977 109 p refs (AD-A040759 FAA-NA-76-39 FAA-EM-77-3) Avail NTIS HC A06/MF A01 CSCL 01/2 An evaluation of aircraft Mach number spacing and tnertial navigation systems is represented as regards their impact on longitudinal separation and collision risk in the Central East Pacific A nomograph was produced for predicting maximum expected changes in longitudinal separation of aircraft flying on long distance transoceanic flights Results indicate that a statistically significant difference in maintaining longitudinal separation exists between those aircraft employing Mach number spacing techniques and those not using the techniques and likewise between aircraft with more sophisticated air data systems than those without Collision risk from loss of longitudinal separation was found to be at an acceotable level Author N77-29119# Systems Control Inc Palo Alto Calif AREA NAVIGATION ROUTE WIDTH REQUIREMENTS Final Report A R Stephenson and W H Clark Dec 1976 119 p refs (Contract DOT-FA72WA-3098) (AD-A04Q153 FAA-RD-77-21) Avail NTIS HC A06/MF A01 CSCL 01/2 Route width requirements for both high altitude enroute and terminal areas are quantified based on the impact of route width on route efficiency airspace capacity and route length Results of this study which based on analysis of specific high traffic demand geographical areas indicate that there is a requirement to eliminate the current splayed route widths and provide constant width routes but that there is no requirement for reduction of route widths below a constant + or - 4 nm in the high altitude enroute structure or below the t- or - 2 nm or + or - 4 nm in the high altitude enroute structure, or below the + or - 2 nm or -f- or - 4 nm, dependent upon distance from the VORTAC. which are currently required in the terminal area Author N77-29120# Stanford Research Inst Menlo Park, Calif ADVANCED PRODUCTIVITY ANALYSIS METHODS FOR AIR TRAFFIC CONTROL OPERATIONS Final Report. Jan 1974 - Dec 1976 Paul L Tuan H Steven Procter and George J Couluris Dec 1976 199 p refs (Contract DOT-TSC-1128) (AD-A035095 OOT-TSC-FAA-76-27 FAA-RD-76-164) Avail NTIS HC A09/MF A01 CSCL 17/7 A description of the air traffic control productivity analysis methods is reported The relative capacity estimating process models the traffic handling capabilities of individual sectors in terms of routine surveillance, and conflict processing workloads The air traffic flow model simulates a multisector network by tracing aircraft flows from sector to sector and measuring traffic loadings workload requirements and delays under given sets of traffic input parameters and congestion relief strategy Author N77-29123/C West Virginia Univ Morgantown Dept of Electrical Engineering AIRCRAFT ANTENNA ANALYSIS AND MICROWAVE LANDING SYSTEM (MLS) APPLICATIONS Final Summary Report. 1 Jan 1974 - 31 Dec 1975 Constantme A Balanis and Yuk-Bbn Cheng 31 Jan 1976 223 p refs (Contract DOT-OS-40013) (AD-A041484 FAA-RD-76-37) Avail NTIS HC A10/MF A01 CSCL 01/2 Analytical methods for predicting the radiation characteristics of antennas on aircraft were developed Diffraction techniques in conjunction with other classical electromagnetic methods were used to take into account contributions from various structural features of an airframe Computed values were compared with measured data of antennas on scaled model aircraft A very good agreement between theory and experiment was indicated Computations were made for antennas on full scale aircraft with the frequency of operation remaining within the proposed band for the MLS A circumferential aperture mounted below the nose or above the cockpit of a Boeing 747 provides the most attractive coverage for MLS application Author N77-29124* Federal Aviation Administration Washington DC BOSTON AIR ROUTE TRAFFIC CONTROL CENTER (ARTCC) LIGHTING STUDY Final Report. Apr - Nov 1976 Alan J Kopala Charles M Hall (Raytheon Co Sudbury. Mass) and Richard M Carr (Raytheon Co Sudbury Mass) May 1977 163 p refs (Contract DOT-FA76WA-3738) (AD-A041324 FAA-RD-76-203) Avail NTIS HC A08/MF A01 CSCL 17/7 Work at an air route traffic control center was accomplished in reducing reflections on the faceplates of the plan view displays while increasing the level of ambient lighting This was intended to improve the observation of flight data by air traffic controllers and to facilitate reading and walking in the immediate aisle area Lighting experts identified glare and reflection sources and lighting deficiencies measured their various intensities with photometric test equipment and provided practical suggestions to rectify the lighting problems The results of this project were the significant reduction of reflections and glare and an increase in the ambient illumination Author N77-29125# Transportation Systems Center Cambridge Mass ILS GLIDE SLOPE PERFORMANCE PREDICTION MULTI- PATH SCATTERING Final Report. Jul 1975 • Mar 1976 S Morm D Newsom and M Scotto Dec 1976 81 p ref (AD-A035298. DOT-TSC-FAA-76-16 FAA-RD-76-216) Avail NTIS HC A05/MF A01 CSCL 07/7 A mathematical model has been developed which predicts the performance of instrument landing glide slope systems sub/ect to multipath scattering and the effects of irregular terrain contours The model is discussed in detail and then applied to a test case for purposes of illustration A complete listing of all computer programs has been appended to the report Author N77-29126# National Aviation Facilities Experimental Center, Atlantic City N J EVALUATION OF RADIO REMOTE CONTROL SYSTEM FOR AIRPORT VISUAL AIDS Final Report, Nov 1975 - Aug 1976 Bret B Castle Jun 1977 18 p (AD-A041603 FAA-NA-76-51 FAA-RD-77-67) Avail NTIS HC A02/MF A01 CSCL 17/7 An evaluation was made to determine if a particular radio remote control system could provide reliable control of distant airport visual aids in place of laying lengthy control cables to the system s power regulators Simple operation and flexibility of usage were required of the system as well as continual monitoring of the status of the remote stations emergency operation during electrical power failures and reliability of operation approaching hard-wire systems Results show that during the 5 000 hours of testing the system worked well, except for high and low operating temperature problems caused by the use of unreliable commercial components in the transceiver It was recommended that following transceiver improvements, operational evaluation in-service type tests be performed on the system in an operating airport environment Author N77-29127# Lincoln Lab Mass Inst of Tech , Lexington DEVELOPMENT OF A DISCRETE ADDRESS BEACON SYSTEM Quarterly Technical Summary, 1 Jan - 31 Mar 1977 1 Apr 1977 30 p (Contracts DOT-FA72WAI-261 FAA Proj 034-241-012) (AD-A041089 FAA-RD-77-64) Avail NTIS HC A03/MF A01 CSCL 17/7 Results to date of analytical studies, laboratory and flight experiments and software developments supporting the concept feasibility and performance definition phase of the discrete address beacon system are presented Author N77-29128# Transportation Systems Center Cambridge Mass USER'S MANUAL FOR GENERALIZED ILSGLD ILS GLIDE SLOPE PERFORMANCE PREDICTION MULTIPATH SCATTERING Final Report. Jul 1975 - Mar 1976 489 N77-29129 S Monn D Newsom. and M Scotto Nov 1976 81 p refs (AD-A034492 DOT-TSC-FAA-76-19 FAA-RD-76-186) Avail NTIS HC A05/MF A01 CSCL 17/7 The computer program package for the generalized ILSGLD scattering model is presented The text includes a complete description of the program as well as a brief outline of the instrument landing system and antenna patterns The program listings are included as appendixes and contain both input generation programs and output plotting programs Author N77-29129# Ohio Univ Athens Dept of Electrical Engineer- ing THE PERFORMANCE OF THE NULL-REFERENCE GLIDE- SLOPE SYSTEM IN THE PRESENCE OF DEEP SNOW. 1975 - 1976 Final Report. Dec 1975 - May 1976 Lawrence H Mitchell and Richard H McFarland Jan 1977 50 p / (Contract DOT-FA76WA-3764) (AD-A041139 FA'A-RD-77-24 EER29-1) Avail NTIS HC A03/MF A01 CSCL 17/7 An experimental glide slope established at 3308 MHz on a runway at the airport in Houghton County Michigan was used for measuring response to ground plane snow cover up to 34 inches Results indicate that the path angle increases ap- proximately 0 10 degree for each foot of snow cover and no significant deterioration occurs in path width or clearance Special far-field monitoring using a two-frequency capture type monitor was only marginally successful Author N77-29130# Transportation Systems Center Cambridge Mass USER'S MANUAL FOR ILSS (REVISED ILSLOC) SIMULA- TION FOR DEROGATION EFFECTS ON THE INSTRUMENT LANDING SYSTEM Final Report. Aug 1973 - Mar 1976 0 Chin L Jordan D Kahn S Monn. D Newsom and M Scotto Dec 1976 121 p ref (AD-A035690 DOT-TSC-FAA-76-7 FAA-RD-76-217) Avail NTIS HC A06/MF A01 CSCL 17/7 The complete ILSS computer program package is presented A thorough description of the program and a listing with comments are included as well as a brief description of the instrument landing system and antenna patterns A test case has been created and the figures of the case are incorporated in the report Author N77-29133# Champlam Technology Inc West Palm Beach Fla AN OPERATIONAL FLIGHT TEST EVALUATION OF A LORAN-C NAVIGATOR Final Report M Hughes and R J Adams Mar 1977 127 p refs (Contract DOT-CG-63154-A) (AD-A039498. USCG-D-9-77) Avail NTIS HC A07/MF A01 CSCL 17/7 This report presents the results of an operational test and evaluation of a Loran-C navigation system The tests were performed in a Coast Guard HH-52A helicopter from 21 September to 19 October 1976 The flight test profiles, procedures and test objectives were developed to determine the applicability of5the prototype Loran-C navigator to Coast Guard operations as well as to assess the functional and accuracy performance^ the Loran-C navigator operating as an area navigation system in the National Airspace System The operational testing reported in this document includes search and rescue missions as well as surveillance and enforcement missions The former consisted of evaluating the Loran-C navigator during creeping line sector and expanding square search patterns The latter involved performing low altitude hovers over fixed and movable objects and documenting Loran-C accuracy and repeatability This latter data is also directly applicable to the operations of the off-shore oil industry GRA N77-29134# Federal Aviation Administration Washington D C Office of Management Systems FAA AIR TRAFFIC ACTIVITY. CALENDAR. YEAR 1976 Semiannual Report Patricia Wilson 31 Dec 1976 236 p (AD-A040474) Avail NTIS HCA11 /MFA01 CSCL 01/2 This report furnishes terminal and enroute air traffic activity information of the National Airspace System The data have been reported by the FAA-operated Airport Traffic Control Towers (ATCTs) Air Route Traffic Control Centers (ARTCCs) Flight Service Stations (FSSs) Combined Station Towers (CS/Ts) International Flight Service Stations (IFFSSs) and Approach Control Facili- ties Author IGRA) N77-29139*# Operations Research Inc Silver Spring Md AVIATION AND PROGRAMMATIC ANALYSES. VOLUME 1. TASK 1 AVIATION DATA BASE DEVELOPMENT AND APPLICATION 28 Mar 1977 114 p refs 3 Vol (Contract NAS5-23477) (NASA-CR-152581) Avail NTIS HC A06/MF AOI CSCL 01C A method was developed for using the NASA aviation data base and computer programs m conjunction with the GE management analysis and projection service to perform simple and complex economic analysis for planning forecasting and evaluating OAST programs Capabilities of the system are discussed along with procedures for making basic data tabulations updates and entries The system is applied in an agricultural aviation study m order to assess it> value for actual utility in the OAST working environment A R H N77-2914O*# Operations Research Inc Silve' Spring Md AVIATION AND PROGRAMMATIC ANALYSES VOLUME 2. TASK 2 IDENTIFICATION OF PLANNING FACTORS AND ACTIVITIES Final Report 28 Mar 1977 250 p refs 3 Vol (Contract NAS5-23477) (NASA-CR-152582) Avail NTIS HC A11/MF AOI CSCL 01C For abstract see N77-29139 N77-29141*# Operations Research Inc Silver Spring Md AVIATION AND PROGRAMMATIC ANALYSES VOLUME 3. TASK 3 DEVELOPMENT OF SPECIAL ISSUE PAPERS Final Report 28 Mar 1977 204 p refs 3 Vol (Contract NAS5-23477) (NASA-CR-152583) Avail NTIS HC A10/MF AOI CSCL 01C For abstract see N77-29139 N77-29142*# Kansas Univ Center for Research Inc Lawrence A STUDY OF COMMUTER AIRPLANE DESIGN OPTIMIZA- TION J Roskam R David Wyatt Douglas A Griswold and James L Hammer 31 Aug 1977 276 p refs (Grant NsG-2145) (NASA-CR-154270 K U - F R L - 3 1 3 - 4 S R - 3 ) Avail NTIS HC A13/MF A01 CSCL01C Problems of commuter airplane configuration design were studied to affect a minimization of direct operating costs Factors considered were the minimization of fuselage drag methods of wing design and the estimated drag of an airplane submerged in a propeller slipstream all design criteria were studied under a set of fixed performance mission and stability constraints Configuration design data were assembled for application by a computerized design methodology program similar to the NASA-Ames General Aviation Synthesis Program J H N77-29143*# National Aeronautics and Space Administration Langley Research Center Langley Station Va COMPATIBILITY CHECK OF MEASURED AIRCRAFT RESPONSES USING KINEMATIC EQUATIONS AND EXTENDED KALMAN FILTER Vladislav Klein (George Washington Un:v Washington D C I and James R Schiess Washington Aug 1977 49 n refs (NASA-TN-D-8514 L-11420) Avail NTIS HC A03/MF AOI CSCL 01C An extended K aim an filter smoother and a fixed point smoother were used for estimation of the state variables in the 490 N77-29154 six degree of freedom kinematic equations relating measured aircraft responses and for estimation of unknown constant bias and scale factor errors in measured data The computing algorithm includes an analysis of residuals which can improve the filter performance and provide estimates of measurement noise characteristics for some aircraft outout variables The technique developed was demonstrated using simulated and real flight test data Improved accuracy of measured data was obtained when the data were corrected for estimated bias errors Author N77-29144# National Aerospace Lab Amsterdam (Netherlands) Structures and Materials Div COMPARISON BETWEEN THE STATISTICAL DISCRETE GUST METHOD AND THE POWER-SPECTRAL DENSITY METHOD R Noback 25 Nov 1975 77 p refs Sponsored by Dept of Civil Aviation (NLR-TR-75158-U) Avail NTIS HC A05/MF A01 These two= methods of ca'culatmg aircraft design loads due to atmospheric turbulence were compared qualitatively and quantitatively on the basis of the load exceedance curves for certain aircraft models It is shown that for the first and second order models without unsteady aerodynamic forces and within certain ranges of model-parameters the two methods give the same results for the design loads when the desiyn criteria are also based on these types of models It is shown that the iiethods are related to each other giving the same results foi simple first and second order airplane models It is concluded that the statistical discrete gust method has no advantages and a number of disadvantages compared to the power spectral density method and is not suitable as an airworthiness requirement for the calculation of design loads Author (ESA) N77-29145# National Aerospace Lab Amsterdam (Netherlands) Structures and Materials Div EQUATIONS FOR THE RESPONSE OF AN AIRPLANE TO NON-STATIONARY ATMOSPHERIC TURBULENCE PATCHES R Noback 8 Mar 1976 62 p refs (Contract NIVR-1775) (NLR-TR-76056-U) Avail NTIS HC A04/MF A01 A method to calculate the load exceedance curve for a linear system having a finite modulated Gaussian process as input is described The derivation is based on the use of ensemble averages defined as the expected values at a certain point of time The equations can be used for any airplane-transfer function to which the power spectral density method is applicable Author (ESA) N77-29146# Army Materials and Mechanics Research Center Watertown Mass EVALUATION OF SCRATCH-AND SPALL-RESISTANT WINDSHIELDS Final Report John R Plumef and Wilson C McDonald Dec 1976 30 p (AD-A038849 AMMRC-TR-76-39 AVSCOM-76 22) Avail NTIS HC A03/MF A01 CSCL 06/17 A program was conducted to develop and assess materials configurations offering a potential improvement to the scratching and spalling problems present in existing Army helicopter windshields Two prototype designs were fabricated for the UH-1 helicopter flight tested at Ft Rucker Alabama and subjected to ballistic and bird impact tests while under flight simulated conditions The designs tested included an acrylic windshield (used as the standard) a monolithic polycarbonate windshield with an abrasion-resistant coating on both surfaces and a glass-plastic composite using Chemcor and polycarbonate materials GRA N77-29148 Georgia Inst of Tech Atlanta A VORTEX WAKE ANALYSIS OF OPTIMUM HIGH BY-PASS RATIO DUCTED FANS Ph D Thesis Damaraju Subtamanya Janakiram 1976 177 p Avail Umv Microfilms Order No 77-7622 -=- A consistent mathematical potential wake model is presented for the fan wake and the boundary sheets and the compatibility relationships to be satisfied by each of the cylindrical boundary vortex sheets are obtained It is shown that for the wake model to be consistent, the jet wake needs to satisfy certain conditions as far as the induced velocities in it are concerned The compressibility and viscous effects are neglected in the analysis of the wake Using the Biot-Savart law the vortex strength distribution of the ultimate wake is found numerically and then is related to the blade bound vortex strength distribution The expressions for the thrust induced power and induced efficiency are developed using integral theorems and evaluated numerically The ultimate wake vortex model for a ducted fan with infinite number of blades is also developed Dissert Abstr N77-29149 Engineering Sciences Data Unit London (England) EFFECT OF INTAKE TOTAL PRESSURE LOSS ON NET THRUST AT TAKE-OFF TURBOJET AND TURBO-FAN ENGINES Mar 1977 6 p (ESDU-77001 ISBN-0-85678-172-5) For information on availability of series sub-series and other individual data items write NTIS attn ESDU Springfield Va 22161 H C$98 50 A method is given for estimating the effect of intake total pressure loss on the net thrust of turbojet and turbofan engines at takeoff conditions The total pressure loss characteristics of typical intakes are included along with data for use in estimating the consequent reduction in net thrust ESDU N77 29151# Lockheed-California Co Burbank EXPERIMENTAL INVESTIGATIONS OF AERODYNAMIC NOISE DURING FISCAL YEARS 1974. 1975 AND 1976 J D Revell and G J Healy 15 Aug 1977 134 p refs (LR-27438) Avail NTIS HC A07/MF A01 CSCL 20A Arguments exist for expecting an airframe noise contribution related to the induced drag associated with dissipation of trailing vortices Turbulence in the swirling shear layers surrounding the trailing vortices causes extra pressure fluctuations to be generated at the wing trailing edge these fluctuations are described The experimental effort on aerodynamic noise was devoted to free jet anechoic wind tunnel tests with airfoils and sting mounted models The noise levels measured for scale model were higher than the theory at Mach numbers between 0 2 and 0 4 by a maximum of 5 db gradually decreasing with Mach number The increase in noise at low Mach numbers above the theory was associated with low Reynolds number laminar instability tones Author N77-29152# IIT Research Inst Chicago. Ill TURBINE ENGINE PARTICULATE EMISSION CHARACTER- IZATION Final Report Donald L Fenton Sep 1976 140 p refs (Contract DOT-FA75WA-3722) (AD-A041499. C-6352-10 FAA-RD-76-141) Avail NTIS HC A07/MF A01 CSCL 21/5 A paniculate material sampler was designed to be used in conjunction with commercial aircraft turbine engines The engines of interest include a low bypass ratio turbofan a mixed flow turbofan and a high bypass ratio turbofan The samples and information provided by the sampler included particle size distribution particle size/shape characteristics and particulate mass concentration The influence of engine operating variables such as power setting and compressor inlet conditions on particle characteristics can be determined Author N77-29184)jl Dormer-System G m b H Friednchshafen (West Germany) DETERMINATION OF COMPRESSIBLE UNSTEADY AER- ODYNAMIC FORCES ON A FINITE NUMBER OF WEAKLY CURVED CASCADE OF ARBITRARY DEPTH IN PLANE FLOW [BESTIMMUNG KOMPRESSIBLER. INSTATION- AERER LUFTKRAEFTE AN EINER ENDLICHEN ZAHL SCHWACH GEKRUEMMTER KASKADENSCHAUFELN BELIEBIGER TIEFE IN EBENER STROEMUNG] W Schuler Bonn DOKZENTBw 1976 45 p refs In GERMAN ENGLISH summary Sponsored by Bundesmm der Verteidig- ung 491 N77-29155 (BMVg-FBWT-76-24) Avail NTIS HC A03/MF A01 DOKZENTBw Bonn DM 30 The method described is based on the panel-technique which allows the calculation of approximate unsteady aerodynamic forces on a finite harmonically vibrating cascade consisting of slightly curved lifting surfaces (vanes) and boundary surfaces in a two-dimensional, compressible subsonic airstream Some results obtained from applying the method to a special cascade are presented, and comparison is made with a proven method for the case of a single vane Author (ESA) N77-29155# Pohtecnico di Torino (Italy) 1st di Macchme e Moton per Aeromobili ANALYSIS OF UNSTEADY FLOW IN TURBOJET ENGINE AFTERBURNERS [ANALISI DELMOTONON STAZIONARIO IN POSTBRUCIATORI DI TURBOREATTORI] Matteo Andriano and Luca Zannetti Oct 1976 19 p refs In ITALIAN ENGLISH summary (Publ-185) Avail NTIS HC A02/MF A01 Transients due to the fuel throttling and a variable geometry exhaust nozzle in turbojet engine afterburners were numerically investigated using a one-dimensional theory An unsteady combustion model is proposed Hyperbolic partial differential equations representative of unsteady flow and combustion are integrated by means of a finite difference method Computa- tional examples are described Author (ESA) N77-29156# Loughborough Umv of Technology (England) Dept of Transport Technology NOISE LEVELS OF JET TRANSPORT AIRCRAFT^ DURING INITIAL CLIMB M Lanzer D Brown and J B Ollerhead Mar 1977 39 p refs (Contract SN/1170/012) (TT-7702) Avail NTIS HC A03/MF A01 Noise peak level data measured for 271 jet transport departure flights at minimum slant range distances of between 1000 ft (305 m) and 6000 ft (1830m) are given The nose data in D-weighted sound levels dB(D) were obtained by analyses of noise history tape recordings each of which was accompanied by a photographic record of the flight track Propagation laws relating peak sound level and minimum slant range are derived for ten different aircraft types and for two categorized groupings (2- and 4-engmed turbofan aircraft) These empirical laws show that for the maximum power climb condition of flight the radiated peak" levels diminish at a rate of about 10 to 12 dB(0) per distance doubling Directivity properties of the D-weighted sound level of selected aircraft are also derived from the sound history and photographic records These are shown to be reasonably approximated by a spherically uniform radiation model Author (ESA) N77-29159# McDonnell Aircraft Co St Louis Mo AIRCRAFT HYDRAULIC SYSTEM DYNAMIC ANALYSIS VOLUME 3 FREQUENCY RESPONSE (HSFR) COMPUTER PROGRAM USER MANUAL Interim Technical Report Gerry Amies and Bob Greene Wright-Patterson AFB Ohio AFAPL Feb 1977 77

)77-28138 ADTOBATIC LABDIBG COSTBOL Information processing reguirements for on-board nonitorinq of autcnatic landing fAIAA 77-1093] A77-I42798 Dynamic problems of unmanned tethered rotor platform Sea-Kiebitz with special regard to the landing A77-U3357 ADTOHATIC PILOTS Spacecraft flight control with the new phase space control law and optimal linear jet select [AIAA 77-1071] A77-H2781 Automatic rollout control of the 7U7 airplane [AIAA 77-1101] A77-U2806 AUTOMATIC TEST EQOIPBEHT Programmable data logger for automatic test equipment for aircraft control systems A77-U1388 Software for automatic test equipment for aircraft systems A77-U1389 Testing gyroscopic systeos with automatic test equipment A77-U1390 Testing of propulsion system diagnostic equipment aircraft engine nonitonng and inspection systems f A I A A PAPEB 77-895] A77-11983 lew technology ATE in support of the TAH-61 advanced attack helicopter Automatic Test Eguipment f A I A A PAPEB 77-896] A77-14198<4 AVIOJICS A fliqht control system using the DAIS architecture Digital Avionics Information System [ A I A A 77-11001 A77-1280<4 Application of microelectronic technology to general aviation fliqht control f A I A A 77-11021 A77-142805 An experimental study on a combined outside world/instrument display for helicopter operation at night and in bad weather A77-U3359 A X I A L FLO? & note on compressor exit static pressure maldistributions in asymmetric f low rcOED/A-TOBBO/TE-79] N77-281110 AXIAL FL08 TDBBIBES Investigations on axial flow fan impellers with forward swept blades T A S H E PAPEB 77-FE-i] A77-12052 AXISIBIETBIC BODIES The inverse problem for axisynmetric aerodynamic sh? pes f A I A A 77-1175] A77-41753 Low Reynolds number flow past a blunt axisymnetric body at angle of attack A77-«3737 AIISTHBETBIC FLOi Study of a nonisothermal axisymmetric near wake A77-I13928 B B-1 AIBCBAFT Fracture Mechanics Evaluation of B-1 Materials. Volume 1: Text f iP-A0398831 N77-29287 Fracture Mechanics Evaluation of B-1 Materials. Volume 2: Fatigue crack growth data [AD-A0397851 ' B77-29288 BAC 111 JIBCEAFI Design and theoretical assessment of experimental glide path and flare systems for a BAC 1-11 aircraft (including direct lift control) [ARC-CP-1337] N77-2810I4 BALLOOHS Lighter Than Air Systems Technology Conference, Melbourne, Fla., August 11, 12, 1977, Technical Papers A77-U1751 A lighter-than-air bibliography [ A I A A 77-1177] A77-1175U Tethered aerostats - Technology improvements [AIAA 77-1 18U] A77-1I1757 BABBIEBS Aircraft fire simulator testing of candidate fire barrier systems [AD-A038601] N77-28102 BEBDIBG BOHEHTS Ship landing trials with the BO 105 A77-H3356 BIBLIOGBAPBIBS SUBJECT INDEI BIBLIOGBAPBIES A iiqhter-than-air bibliography [AIAA 77-11771 A77-41754 BIODTSAHICS Measurement and prediction of structural and biodynanic crash-impact response; Proceedings of the Ninter Annual Meeting, New York, N.Y., December 5-10, 1976 A77-42564 BIBD-AIBCBAFT C01LISIOIS Impact behavior of polymeric matrix composite materials [AD-A0381881 177-28316 BLADE TIPS The flow ever a helicopter blade tip in the transonic regime fOHZBA, IP NO. 1976-115] A77-43351 BLAST LOADS Blast from aircraft guns at subsonic and supersonic speeds A77-43832 BLOBIBG Upper surface blovinq aerodynamic and acoustic characteristics fAIAA PAPEB 77-6081 A77-41857 BLOHT BODIES Lou Reynolds number flow past a blunt azisymmetnc body at angle of attack A77-43737 Convective heat and nass transfer in a hypersonic near Hake A77-43923 BO-105 BELICOPTEB Dynamics of a small helicopter with a high capacity rescue hoist A77-43336 Botor isolation of the hinqeless rotor BO-105 and YDH-61A helicopters A77-43350 Development, fabrication and testing of a hybrid composite tailbocra for BO 105 A77-43354 Ship landing trials with the BO 105 A77-43356 Ham and tail rotor interaction noise during hover and low-speed conditions A77-U3371 BOATTAILS Calculation of pressure distributions on two axisymmetric boattailed configurations [HBE-TB-1779 (H) ] N77-28083 BODY-ilHG AID,TAIL COIFIGOBATIOHS Hi-fidelity airplane simulation model [ A I A A 77-1166] A77-43191 BODY-KING CONFIGURATIONS Two-dimensional nozzle/airframe integration technology - An overview [ A I A A P A P E B 77-8391 A77-41973 Measurements of pressure distribution on a half-BOdel winq-body combination of 55 deg. sweep over a wide range of reynolds number [ARC-CP-13281 N77-28078 Interference problems on winq-fuselaqe combinations. Part 1: Lifting unswept winq attached to a cylindrical fuselage at zero incidence in midwing position [ARC-CP-1331] N77-28079 Interference problems on wing-fuselaqe combinations. Part 2: Symmetrical unswept winq at zero incidence attached to a cylindrical fuselage at zero incidence in midwing position fABC-CP-1332] N77-28080 Interference problems on winq-fuselage combinations. Part 3: Symmetrical swept wing at zero incidence attached to a cylindrical fuselage IABC-CP-13331 H77-28081 Aerodynamic characteristics of winq-body configuration with two advanced general aviation airfoil sections and simple f lap systems [HASA-TS-D-8524] N77-28094 Prediction of aerodynamic interference effects on a fighter type wing-tip tank configuration with and without pylon and store [HLB-TB-75070-01 N77-29105 BOEING 747 AIBCBAFT Automatic rcllcut control of the 747 airplane [ A I A A 77-11041 A77-42806 BOBBIHG EQUIPBEHT D a v e bombing simulation results using direct side force control modes [ A I A A 77-11181 A77-43152 BOOHDABI LAYEB EQUATIONS Program manual for the Eppler airfoil inversion program [NASA-CB-1539281 N77-28068 B R A K E S (FOB ARRESTING MOTION) Urea formadehyde foamed plastic emergency arresters for civil aircraft [AHC-CP-1329] N77-28144 BBEAKIBG Tire runway interface friction prediction subsystem [AD-A0399681 N77-29532 BOBBLES Profile flows taking cavitation bubble dynamics into account rBB7G-PBWT-76-22] N77-29329 BUCKLING A muJtilevel' approach in opt imum design of structures including buckling constraints N77-29552 BOOIANCY Theoretical study of hull-rotor aerodynamic interference on seaibuoyant vehicles [ A I A A 77-11721 A77-41752 Semi-buoyant lifting body hybrid characteristics for advanced Naval missions [ A I A A 77-11941 A77-41763 C-15 AIBCBAFT YC-15 in the air A"'7-41636 C-141 AIBCBAFT C-141A pitot-static system calibration tests [AD-A0362411 N77-28115 CABLES (BOPES) Dynamics of a small helicopter with a high capacity rescue hoist A77-43336 Dynamic problems of u n m a n n e d tethered rotor platform Sea-Kiebitz with special regard to the landing A77-43357 CAHBEB Flight evaluation of a highly cambered tail rotor A77-if33il1 CAHBERED BISGS Wind-tunnel investigation of a variable camber ai.d twist wing in the Langley 8-ft transonic wind tunnel [NASA-TN-D-84751 B77-28091 Subsonic and supersonic aerodynamic characteristics of a supersonic cruise fighter model with a twisted and cambered wing with 74 deq sweep [NASA-TH-X-3530] N77-29102 CAHABD COHFIGURATIONS Load distribution on a close-coupled winq canard at transonic speeds [AIAA PAPEH 77-1132] A77-43198 An investigation of a close-coupled canard as a direct side-force generator on a fighter model at Mach numbers from 0.40 to 0.90 [NiSA-TH-D-8510] H77-28139 Load distribution on an closed-coupled wing canard at transonic speeds [HASA-T1-740531 N77-29097 CAPACITY Advanced productivity analysis methods for air traffic control operations [AD-A035095] N77-29120 Beport on airport capacity: Large hub airports in the United States [AD-A0414351 N77-29176 CAPTOBE EFFECT Minimum reguncd capture radius in a coplanar model of the aerial combat problem A77-43726 CABGO AIBCBAFT Civil aviation activities in global perspective A77-41930 A-10 SUBJECT IBDEX CORPDTEB TECHHIQOES CASCADE FLOi Determination of compressible unsteady aerodynamic forces on a finite number of weakly curved cascade of arbitrary depth in plane flow rBMVG-FEHT-76-24 1 S77-29154 CAVITATIOB FLOW Profile flows taking cavitation bubble dynamics into account fBHVG-FEl.T-76-221 877-29329 CH-H7 BELICOPIEB The CH-47C vulnerability reduction modification program: Fly-by-vire backup demonstration rAD-A03C6B2] 177-28140 CBEBICAL AOXILIABT POSEB OBITS Cflpmical pcwer sources in aviation Russian book A77-13617 CIVI1 AVIATIOH O.S. air carrier accidents involving fire /1965 through 1971/ A77-40929 The airport and fire from the air carrier's view A77-10931 The airport fire defense - The basic mission and needs A77-40944 Cost-benefit analysis for airport development A77-41379 Market development problems for local service air carriers A77-41850 Civil aviation activities in global perspective A77-41930 The changing horizons for technical progress in air transportation A77-41946 Airport planning and economics - Some changing perspectives fSAE PAPFR 7705811 A77-42049 Runway length as a basic criterion in analyzing the development of classification of Polish technical civil airfields A77-43330 Aviation system planning airport planning in Maryland A77-43657 Calculation of day-night levels (Ldn) resulting from civil aircraft operations FPB-266165/01 1177-28918 CLIBBIHG FLIGHT Noise levels of ]et transport aircraft during initial climb fTT-77021 N77-29156 COAL LIQDEFJCTIOS Alternate aircraft fuels: Prospects and operational implications r i lASJ>-TM-X-740301 N77-28322 COCKPITS An LED numeric display for the aircraft cockpit A77-41473 Simulator cockpit motion and the transfer of initial flight training rAD-A03819in 1177-28147 COHBAT ninimam reguired capture radius in a coplanar model of the aerial combat problem A77-43726 COSBOSTIOH CHABBEES The effect of the structural features of a combustion chamber on the emission of toxic compounds A77-110711 Low-emissions comtustor demonstration fAD-A038550] N77-28129 COHBOSTIOI BFFICIEBCY Acoustic properties of pneumatic vortex sprayers A77-40703 The effect of the structural features of a combustion chamber on the emission of toxic compounds A77-40711 COIBABD ABD COBTBOL Command augmentation control laws for maneuvering aircraft fAIAA 77-101411 A77-II2759 COBHEBCIAL AIECBAFT Improving fire prevention measures on board commercial transport aircraft A77-40947 Our next commercial ttansport - Colli inns of interest A77-<42562 Brea formadehyde foamed plastic ea%.rgency arresters for civil aircraft [ARC-CP-1329] H77-23144 A study of commuter airline economics fHASA-CB-152035] N77-29114 COHPARISOB A comparison of the experimental aerodynamic characteristics of an obligue wing with those of a swept wing in the Ames 6 by 6 foot wind tunnel rHASi-TM-X-35471 H77-28086 COBPLEX SISTERS Linear regulator design for stochastic systems by a multiple time-scales method hierarchically structured suboptimal controller A77-43771 COMPOSITE BATEBIALS A composite system approach to aircraft cabin fire safety A77-40937 Graphite composite aircraft landing gear wheel f A D - A 0 3 6 2 0 7 ] N77-28232 Impact behavior of polymeric matrix coaposite materials TAD-AOJ81881 N77-28316 COSPBESSIBLE FLOI Steady lineariz&a aerodynamics II - Supersonic A77-11268 The characteristics of a family of rooftop aerofoils designed at their drag-rise condition in viscous, compressible f low. Part 2* Off design conditions , TARC-CP-1321] 1177-28075 COBPBESSOB BLADES Compressor stator time-variant aerodynamic • response to upstream rotor wakes , TAD-A03631131 N77-28132 COMPRESSOR ROTORS Quantitative density visualization in a transonic compressor rotor A77-1I1863 COBPEESSORS Unsteady processes in aircraft piston compressors Russian book A77-13610 A note on compressor exit static pressure maldistributions in asymmetric flow rCDED/A-TBBBO/TR-79] 877-28410 COSPOTATIOX Calculation of day-night levels (Ldn) resulting from civil aircraft operations [PB-266165/0] N77-28918 COBPOTEE GBAPHICS , • Analytic construction of 'aerodynamic profile' curves A77-41100 COSPOTEfi PROGEAHS neasurement and'ptediction of structural and biodynamic crash-impact response; Proceedings of the Winter Annual Beeting, New York, N.Y., December 5-10, 1976 A77-42561 A method of analysis for general aviation airplane structural crashworthiness A77-12566 Program manual for the Eppler airfoil inversion program fNASA-CH-1539281 N77-28068 PLOT - A program for aeroelastic stability analysis of aircraft structures in subsonic flow fNASA-TS-732171 N77-28108 Aviation and programmatic analyses; Volume 1, Task 1: Aviation data base development and application for N A S A OAST programs FNASA-CR-152581 1 H77-29139 Aircraft hydraulic system dynamic analysis. Volume 3: Freguency response ( H S F B ) . Computer program user manual CAD-A038691 ] IH7-29159 Aircraft hydraulic system dynamic analysis. Volume 6: Steady state Flow Analysis ( S S F A N ) . Computer program technical description [AD-A0386921 1177-29162 COHPOTEB TECHNIQUES - Canadian Forces Search and Rescue A77-41936 A-11 COUPOTEBIZBD DESIGN SUBJECT IHDEI Is the pilot necessary in a liqht observation helicopter • A77-43340 CDHPOTEBIZED DESIGN Application of a computer program system to the analysis and desiqn of supersonic aircraft [AIAA 77-1131] A77-113163 Hanoiithic wirq desiqn with spanwise web-spars A77-44078 A study of commuter airplane desiqn optimization [NASA-CB-154270] N77-29142 COBPOTEBIZED SIHDIATION Effects of the airfoil choice on rotor aerodynamic behaviour in forward fliqht A77-43338 Simulation and data analysis of a scanninq laser Doppler velocime'te'r system for sensing aircraft wa> e vortices A77-44291 Laser velocimeter turbulence spectra measurements A77-44304 Computer simulation of fatique crack propaqation in aircraft components [ISBN-91-7372-147-6 1 "J77-28518 Simulation of a synergistic six-post motion system on the fliqht simulator for advanced aircraft at NASA-Ames [HASA-CB-1520101 S77-29173 COBEUTEBS Computers for real time fliqht simulation: A market survey [NASA-CB-2885] K77-28113 COHCOBDE ilBCBAJT Monitoring Ccncorde emissions [APCA EAPEB 77-141] A77-40633 COHFEBENCES Liqhter Than Air Systems Technoloqy Conference, Melbourne, Fla., Auqust 11, 12, 1977, Technical Papers A77-41751 CONFIGOBATIOS H4HACEHEHT Seturninq BDT and E assets (aircraft) to operational usage [AD-A03648M1 N77-28980 CONGRESSIONAL BBFOBTS FAA procedures in makinq no hazard determinations with respect to structures near airports [GPO-79-322] N77-29171 CONICAL BODIES Analysis of slightly-conical small-aspect-ratio winqs beyond the proportional limit A77-144091 CONSTBAINTS Development of an inflatable head/neck restraint system for ejection seats [AD-A038762] N77-29115 CONTBOL BOABIS i Boston Air Boute Traff ic Control Center (ABTCC) lighting study [AD-A0413241 N77-29124 CONTBOL CONFIGURED VEHICLES Synthesis of active controls for flutter suppression on a f l iqht research winq f A I A A 77-10621 A''7-l|2773 Equivalent sys tem approaches to handling qualities analysis and desaqn problems of auqmented aircraft [ A I A A 77-1122] A77-43155 Prediction of elastic-airplane lateral dynamics from rigid-body aerodynamics [ A I A A 77-11251 A77-43158 Direct-force flight-path control - The new way to fly [ A I A A P A P E E 77-1119] A77-43197 Calculation of the dynamic response of CCV-type aircraft flexible T tail aircraft lateral motion [DLB-FB-76-781 877-29168 COHIBOL EQOTFBEST Design and flight test of a decoupled velocity control system for VTOL landing approach f A I A A P A P E B 77-11431 A77-43199 COBTBOL SIBDLATION Aircraft simulation on computer A77-41394 Flight contrcl system of an advanced air superiority fighter [ A I A A 77-10791 A77-42785 CONTBOL STABILITY Command augmentation control lawi for maneuvering aircraft [ A I A A 77-10441 A77-42759 heetinq the maneuverability requirements of military helicopters A77-433K9 Desiqn and theoretical assessment of experimental glide path and flare systems for a BAG 1-11 aircraft (including direct lift control) [ABC-CP-1337] N77-28104 CONTBOL STICKS Flight test of stick force stability in attitude-stabilized aircraft [AIAA 77-11211 A/7-43154 COHTBOL THEOBT. A two-level adaptive controller for application to fliqht control systems [AIAA 77-1092] A77-42797 Some analytical control laws for the design of desirable lateral handlinq qualities using the model matching method for aircraft [AIAA 77-10451 A77-42812 Theory of automatic aircraft power plant control: Bussian book A77-43604 CONTBOLLABILIII Some analytical control laws for the desiqn of desirable lateral handling qualities using the model matching method for aircraft [ A I A A 77-10451 A77-42812 Eguivalent system approaches to handling qualities analysis and design problems of augmented aircraft f A I A A 77-11221 A77-43155 CONVECTIVE HEAT TBANSFEB Convective heat and mass transfer in a hypersonic near wake A77-43923 COHTEBGENT NOZZLES The effect of temperature on subsonic net noise [ABC-K/M-37711 N77-28121 CONVEBGENT-DI7EBGENT NOZZLES Simplified multi-mission exhaust nozzle system [ A I A A PAPEB 77-960] A77-41991 COST ANALYSIS Balancing the costs of rescue services and fire fighting among different categories of airports A77-40950 Cost-benefit analysis for airport development A77-41379 An engineering approach to estimating propulsion contributions to system life cycle costs [ A I A A PAPER 77-879] A77-41981 Maintenance cost study of rotary wing aircraft [NASA-CE-152003 ] N77-28063 COST EFFECTIVENESS The fu ture of rotorcraft in aviation A77-41929 Simplified multi-mission exhaust nozzle system [ A I A A PAPER 77-960] A77-41991 Cost effective design of an air transport flight control maintenance system [ A I A A 77-1103] A77-42816 Tilt rotor V/STOL aircraft technology A77-4133? Simulators for training and profit cost effectiveness [AD-A0381901 N77-28146 A s tudy of commuter airplane design optimization [S1SA-CB-15ll2701 N77-291U? COST ESTIHATES \ study of commuter airline economics [NASA-CE-1520351 N77-29114 COST SEDUCTION The aircraft energy efficiency active controls technology program [ A I A A 77-1076 ] A77-42784 CO H. INGS The effect of cowling shape on the stability characteristics of i77-2917i| PBBFORBAHCE PBEDICTIOB Laser velocimeter turbulence spectra measurements A77-i(i(304 Supersonic net exhaust noise investigation. Volume 3: Computer users manual for aero-acoustic predictions fAD-A03861i(l N77-28127 Estimation of enqine removal times and prediction of replacement requirements fAD-A0380761 S77-29165 PEBFOBBAHCE TESTS Criteria for larqe scale fire testinq of aircraft interiors A77-40924 Static performance of vectorinq/reversinq non-axisymmetnc nozzles [A1AA EiPEH 77-8401 A77-II1974 An operational fliqht test evaluation of a Loran-c navigator f AD-A039l(98} N77-29133 PHOTOCHEMICAL BBACTIOBS A computationally fast one-dimensioiial diffusion-photochemistry model of SST wakes A77-43735 PBOTCB4PPIBG The vehicle mapping device FKG-1, a device for indicatinq the location of land vehicles and helicopters on the map A77-U3578 PILOT PEBFOBHJHCE Techniques for the initial evaluation of fliqht sinulatcr effectiveness [ AD-A03611601 N77-28150 PILOT PLAITS Evaluation of methods to produce aviation Turbine fuels from synthetic crude oils, phase 2, volume 2 TAD-A0361901 N77-23325 PILOT TBAIBIHG Ship landinq trials with the BO 105 A77-«3356 PIPES (TUBES) Plastic pipe in airport drainaqe system, phase 2 fAD-AOU12001 N77-29175 PISTOH EHGISES Unsteady processes in aircraft piston compressors Russian took A77-U3610 PITOT TUBES C-141A pitot-static system calibration tests FAD-A03621M 1 -J77-28115 PLASTICS Plastic pipe in airport drainaqe system, phase 2 fAD-AOU12001 H77-29175 PLDG IOZZLBS Non-axisymmetric nozzle concepts for an F-111 test ted fAIAA PAPEB 77-8411 A77-41975 PLDGGISG Consideration of clogging in boundary-layer control system design A77-141519 PHEOBATIC COBTBOL Development of a controllable particle generator for LV seedinq in hypersonic wind tunnels A77-Ui(295 PBEOBATIC BQOIPBENT Acoustic properties of pneumatic vorter sprayers A77-«0703 Optimization of an oleo-pneumatic shock absorber of an aircraft during landinq 177-1(15117 POLICIES Aviation common qround support equipment replacement policy investigation fAD-A0391603 577-29180 POLLOTIOB COSTEOL The effect of the structural features of a coobusticn chamber on the emission of toxic compounds A77-M0711 POLLUTION BOHITOHING Monitoring Concorde emissions T A P C A PAPEB 77-1111 A77-K0638 POLTBEBS Impact behavior of polymeric matrix composite materials fAD-A038138] N77-28316 POLTDBBTHAIB FOAH Expedient structural sandwich soil surfacing of fiberglass reinforced polyester and polyurethane foam UD-A0381M7] N77-28U9 POBODS BOOHDABI LATEB COHTROL Consideration of cloqqinq in boundary-layer control system design A77-U.151I9 POBODS BATEBIALS Certain problems associated with the application of the transpiration cooling of gas turbine enqine blades 177-M0708 POSITIOH EBBOBS Automatic correction of position error by means of a digital correlation of surface structures for air naviqation A77-U3577 POSITIOH HDICATOBS The vehicle mapping device PKG-1, a device for indicating the location of land ve'aicles and helicopters on the map A77-43578 POTEBTI6L FLOB A method of computing the potential flow on thick wing tips S77-29090 POSDEB (PARTICLES) Combined agent techniques and new agent developments in aircraft fire fighting A77-D0933 POREB SPECTBA Comparison between the statistical discrete gust method and the power-spectral density method [NLH-TB-7515S-U1 N 7 7 - 2 9 1 U U Equations for the response of an airplane to non-stationary atmospheric turbulence patches f NI.B-TB-76056-U1 S77-291U5 POBEBED LIFT AIBCBAFT Investiqation of the vulnerability of powered-lif t STOL's to wind shear f A I A H 77-11201 A77-K3153 PBEDICTIOH ANALYSIS TECHHIQOES Simplified unsteady aerodynamic concepts, with application to parameter estimation f A I A A 77-11211 A77-K3157 Prediction of elastic-airplane lateral dynamics f rom riqid-body aerodynamics f A I A A 77-11251 A77-U3158 Prediction of l u m p pnenomena in rotationally-coupled maneuvers of aircraft, including nonlinear aerodynamic effects T A I A A 77-11261 ' *77-U3159 Rotor response prediction with non-linear aerodynamic loads on the retreating blade r O N E B A , TP NO. 1976-1161 A77-IH1S7 A model to predict mutual interference effects on an airframe [AD-A03')22l(/1 1 177-2931(7 PBESSOBE DISTRIBUTION Expansion tunnel performance wi th and without an electromaqnetically opened tertiary diaphragm A77-«083H Measurements of pressure distribution on a half-model wing-body combination of 55 deq. sweep over a wide range of reynolds number fARC-CP-1328] N77-28078 Calculation of pressure distributions on two axisymmetric boattailed configurations r»3E-TB-1779m 1 N77-28083 Compressor stator time-variant aerodynamic response to upstream rotor wakes TAD-A0363i(3 1 N77-28132 A method of coaputinq the potential rlow on thick wing tips N77-29090 Measurements of surface-pressure and wake-flow fluctaations in the flow field of a whitcomb supercritical airfoil * f HASA-TH-D-8l(!(31 N77-29100 A-28 SUBJECT IHDEI BEGIOBAI. PLAHBIBG Effect of winqlets on a first-generation let transport wing. 2: Pressure and spanwise load distributions for a semi span model at high subsonic speeds fHASA-TN-D-ei711 H77-29101 EBESSOBE GBJD1EBTS Effect of intake total pressure loss on net thrust at take-cff: Turbo-jet and turbo-fan engines fESDO-770011 H77-29119 PBBSSDBE SEJSOBS Coapressor stator tine-variant aerodynamic response to upstream rotor wakes fAD-A0363131 H77-28132 PBODDCTJOH EBGIHEEBI1G Structural-logic diagran for ensuring high-rate products in aircraft industry quality control A77-10721 PBOGBSHflED IHSTBOCTIOB Programmable data logger for automatic test eqnipnent for aircraft control systems 477-1(1388 Construction of stable programmed flight vehicle notion A77-11091 A personalized system of instruction for aircraft performance fAD-A0396511 177-23116 PBOGBABBIBG LABGDAGBS Software for automatic test equipment for aircraft systems A77-11389 PBOJECT HAHAGEHBHT A nation and progranmatic analyses. Volume 3, Task 3: Development of special issue papers for NASA OAST programs fllASA-CB-1525831 N77-29111 PBOJECT PLABBING Procedure for the development of naval aviation maintenance objectives fAD-A038201l N77-28061 PBOJBCTILES Secondary damage to aircraft by ricocheted small arms projectiles and fragments rAD-40367551 N77-28111 PBOPOBTIOBAL LIBIT Analysis of slightly-conical small-aspect-ratio Kings beyond the proportional limit A77-11091 PBOPOISI08 SISTEB COBFIGOBATIOBS Advanced supersonic transport propulsion reguirements fAIAA PAPEB 77-831] A77-11969 Supersonic propulsion - 1970 to 1977 fAIAA PAEEE 77-8321 A77-11970 Two-dimensional nozzle/airframe integration technoloqy - An overview UIAA PAEEF 77-8391 A77-iti973 Non-axisymmetnc nozzle concepts for an P-111 test ted fAiAA PAPER 77-3111 ] 477-11975 Aircraft of wide speed and manoeuverinq ranqe vertical or short takeoff fiqhter aircraft 477-13366 PBOPD1SIOB SYSTEB PEBPOBBABCB An engineering approach to estimating propulsion contributions to system life cycle costs fAIAA PAEEB 77-8791 A77-11981 Testing of propulsion system diagnostic equipnent aircraft engine monitoring and inspection systems f A I A A E 4 E E B 77-8951 477-11983 Influence of f l ight vehicle mission on optimal GTE powerplant parameters A7 7-11086 PBOTECTIVE COATIHGS Evaluation of scratch-and spall-resistant windshields fAD-40388191 N77-29116 QUALITY COBTBOI Structural-logic diagram for ensuring high-rate products in aircraft industry quality control A77-10721 Determining qas turbine enqine tolerance ttonitorinq parameters A77-11083 QOIZT EBGIHE PBOGBAB Aero-acoustic performance comparison of core enqine noise suppressors on NASA quiet engine C [HASA-TB-X-73662] H77-28119 BADAB APPBOACB COHTBOL TBACALS evaluation report. I^VAIDS station evaluation report, Aviano AB, Italy {16-23 August 197b) [AD-A0380621 H77-28106 BADAB SCATTBBIHG IIS glide slope performance prediction nultipath scattering fAD-A035298] H77-29125 User's manual for generalized ILSGLD-ILS glide slope performance prediction: Hultipath scattering FAD-A031192} H77-29128 Bser's manual for ILSS (revised ILSLOC)J simulation for derogation effects on the instrument landing system 3 [AD-40356901 H77-29130 B4DAB TBACKIBG TSDH4 - A novel secondary radar Time Space Division Multiple Access A77-11125 BADAB TBAHSBISSIOS Antenna tilting experiments over radar microwave links TAD-A0367271 N77-29316 BADIAST C001IHS Calculation of radiant cooling of air behind intense shock waves using mean optical characteristics A77-13993 BADIO BEACOHS Development of a discrete address beacun system rAD-A0110891 1177-29127 BADIO COBBOBICATIOS Evaluation of radio remote control system for airport visual aids rAD-4011603] N77-29126 BADIO FBEQOEBCY IHTEBFEBEHCE The reduction of interference from large reflecting surtaces instrument landing system interference reduction at airports for aircraft communication A77-U2511 BADIO HATIGATIOH Tracer decoder - A receiver for radio navigation relay systems 477-12211 BADIO BECEIVEBS Tracer decoder - A receiver for radio navigation relay systems A77-12211 BADIO BELAY SISTERS Tracer decoder - A receiver for radio navigation relay systems1 A77-12211 B&HDOH PBOCESSES Analytic design of flight vehicle alighting gear with random scatter of initial conditions and structural parameters A77-14079 BEAL TIHE OFEBATIOB Seal-time aerial reconnaissance using the return-beam vidicon A77-10665 Computers for real time flight simulation: A market survey CHASA-CB-28851 N77-28113 BEDBBDABT COBPOBEHfS Redundant integrated flight control/navigation ineitial sensor complex CAIAA 77-1109 ] A77-12808 BEPLBCTABCE Boston Air Route Traffic control Center (4BTCC) lighting study fAD-A011321] H77-29121 BEGIOSAL PLABBIHG Aviation systea planning airport planning xn Maryland 477-13657 A-29 BEGOIATOBS SUBJECT INDEX BEGOLATOBS Linear regulator design for stochastic systems by a multiple time-scales method hierarchically structured suboptimal controller A77-13771 BBHUOBCBHBHt (SIEDCTOBBS) £vdluation of scratch-and spall-resistant windshields UD-A03881I91 H77-29116 BELIfiBILITY ANALYSIS Operational reliability of aircraft poiierplants Russian took A77-11618 Environmental reliability testinq of helicopter systems A77-13361 The distribution of fracture toughness data for D6ac steel fARL/STBUC-NOTE-129 ] N77-28267 BELIABILITI ESGIBEERIHG Life considerations in the engine design process fAIAA PAPEB 77-9511 A77-11990 Simplified multi-mission exhaust nozzle system fAIAA PAPEE 77-960] 177-11991 Redundant integrated flight control/navigation inertial sensor complex IAIAA 77-1109] A77-12808 BEHOTE COHTEOL Evaluation of radio remote control system for airport visual aids rAD-A011603l N77-29126 REHOTE SEHSOBS Beal-tiue aerial reconnaissance using the return-team vidicon A77-10665 Simulation and data analysis of a scanning laser Doppler velocimeter system for sensing aircraft wake vortices A77-11291 BEHOTELY PILOTED VEHICLES The future of rotorcraft in aviation A77-11929 BEFLACING Aviation ccmmon ground support eguipment replacement policy investigation TAD-A0391601 N77-29180 BESCOE OPEBATIOHS The airport and fire from the airport fire chief's view A77-10925 Lessons from individual aircraft fire accidents: THA L1011 aircraft fire - Logan International Airport, Boston, Massachusetts, O.S.A., 20 April 197'l A77-40926 Crash management at airports A77-10928 The airport fire defense - The basic mission and needs A77-10911 Balancing the costs of rescue services and fire fighting among different categories of airports A77-10950 Canadian forces Search and Rescue A77-41936 Dynamics of a small helicopter vith a high capacity rescue hoist A77-13336 BESEABCH AIBCBAFT Studies on rotor and flight dynamics of a horizontally stoppable hingeless rotor aircraft A77-U3365 Aerodynamic characteristics of a 1/6-scale powered model of the rotor systems research aircraft f IJASA-TH-X-34891 N77-28090 Betnrning BDT and E assets (aircraft) to operational usage fAD-A0361811 N77-28930 BESEABCB ADD DEVELOPHEHT The university's role in the new era of LTA technology and applications fAlAA 77-1187] 477-11758 Becent developnents in rotary-wing aeroelasticity A77-13362 BESIIOAL STBESS Bate effects on residual strength of flawed structures and materials fNLB-TB-76001-U] N77-29565 Residual strength data of riveted panels with different stiffener configurations fSLR-TB-76033-a ] N77-29569 BESOHAHT PBEQOEHCIES A model for uindtunnel rotorcraft research - Ground resonance investigations A'7-13369 BESOOBCE ALLOCATION National Airlines FUP! Management and Allocation Model A77-13399 BETOBH BEAM VIDICONS Beal-time aerial reconnaissance using the return-beam vidicon A77-10665 BEIHOLDS DUMBER Low Reynolds number flow past a blunt aitisymmetric body at angle of attack A77-13737 A high Reynolds number numerical solution of the Navier-Stokes eguations in stream function-vorticity form CNASA-CB-153933] N77-23070 Reynolds number effects on the aerodynamic characteristics of irregular planform wings at Hach number 0.3 in the Ames 12 ft pressure wind tunnel r N A S A - T M - X - 7 3 1 3 2 ] N77-28073 Measurements of pressure distribution on a half-model wing-body combination of 55 deg. sweep over a wide rapge of reynold^ number fAEC-CP-1328] N77-28078 BIGID BOTOBS Wind tunnel testing of model rotors at RAE Farnborougii A 77-13318 Rotor isolation of the hingeless rotor 80-105 and YOH-61A helicopters A77-13350 Studies on rotor and flight dynamics o£ a horizontally stoppable hingeless rotor aircraft A77-13365 BIGID STRUCTURES Prediction of elastic-airplane lateral dynamics from rigid-body aerodynamics f A I A A 77-1125] A77-13158 SOCKET EBGINE HOISE Supersonic jet exhaust noise investigation. Volume 2: Technical report T A D - A 0 3 8 6 1 3 ] N77-28126 Supersonic let exhaust noise investigation. Volume 3: Computer useis manual for aero-acoustic predictions r AD-A03861"4] N77-28127 ROCKET EXHAUST Supersonic jet exhaust noise investigation. Volume 3: Computer users manual for aero-acoustic predictions rA l ) -A03861 l4 ] N77-28127 BOLL Prediction of j u m p phenomena in rotationally-coupled maneuvers of aircraft, including nonlinear aerodynamic effects T A I A A 77-1126] A77-U3159 BOTABT ilHG AIBCBAFT A model for wind-tunnel rotorcraft research - Model design and test obiectives A77-13363 BOTABT RINGS New aircraft airfoils. I for transonic aircraft, light aviation and for helicopter rotor blades A77-Q3329 Rotor ice protection systems A77-U3331 Bign-speed helicopter impulsive noise A77-13335 Trailing vortex wake structure A77-13337 Effects of the airfoil choice on rotor aerodvnamic behaviour in forward flight A77-13338 Design philosophy for helicopter rotor heads A77-13315 A revaluation of helicopter main rotor noise A77-1331fi Hind tunnel testing of model rotors at EfE Farnborough A77-13318 A-30 SUBJECT IHDEI SERVICE LIFE fiotor isolation of the hinqeless cotor BO-105 and TOH-61A helicopters A77-13350 Tte flow over a helicopter blade tip in the transonic regime fOHEBA, TP BO. 1976-1151 A77-U3351 Botor response prediction with non-linear aerodynaiic loads on the retreating blade fOHERA, TP BO. 1976-116] A77-U3352 Ballistic and impact resistance of composite rotorblades A77-13360 Becent developnents in rotary-wing aeroelasticity A77-03362 Becent experience in the testing of a generalized rotor aeroelastic nodel at Langley Besearch Center A77-U336U A model for windtunnel rotorcraft research - Ground resonance investigations A77-U3369 The relative importance of acoustic sources generated by helicopter rotors in high speed flight A77-13370 Ham and tail rotor interaction noise during hover and low-speed conditions A77-U3371 Maintenance cost study of rotary winq aircraft fBAI.A-CB-1520031 H77-28063 BOTOB AEBODYHASICS Theoretical study of hull-rotor aerodynamic interference on semibuoyant vehicles TAIAA 77-11721 A77-41752 Quantitative density visualization in a transonic compressor rotor A77-U1863 Effects of the airfoil choice on rotor aerodynamic behaviour in forward flight A77-H3338 Test of a convertible aircraft rotor in the modane larqe wind tunnel A77-&3317 The flow over a helicopter blade tip in the rONKBA, TP NO. 1976-1151 A77-I43351 Compressor stator time-variant aerodynamic response to upstream rotor wakes fAD-A0363131 N77-28132 A study of the effect of unsteady aerodynamics on the aeroelastic stability of rotor blades in hover H77-29086 BOTOB BLADES The investigation of some unusnal handling characteristics of a light autogyro A77-U3339 A study of the effect of unsteady aerodynamics on the aeroelastic stability of rotor blades in hover H77-29086 The coupled flap-lag-torsional aeroelastic stability of helicopter rotor blades in forward flight N77-29089 BOTOB LIFT Dynamic problems of unmanned tethered rotor platform Sea-Kiebitz with special regard to the landing A77-43357 Constant lift rotor for a heavier than air craft fHASA-CASE-ABC-11015-1 1 N77-28111 BOTOBCBAFT AIBCBAFT The future of rotorcraft in aviation A77-11929 Aeroelastic analysis for rotorcraft in flight or in a wind tunnel fNASA-TB-D-8515] N77-28525 BOTOBS Aerodynamic characteristics of a 1/6-scale powered model of the rotor systems research aircraft fNASA-TM-X-3189] N77-28090 Load and stability measureaents on a soft-inplane rotor system incorporating elastomeric lead-lag dampers fNASA-TN-D-814371 N77-28112 BDHIAYS Runway lenqth as a basic criterion in analyzing the development of classification of polish technical civil airfields A77-I13330 Tire runway interface friction prediction subsystem CAD-A039968] H77-29532 S&FETY PACTOBS Infcreation processing requirements for on-board monitoring of automatic landing C A I A A 77-10931 A77-12798 Cryogenic design and safety review HASA-Langley Besearch Center 0.3 meter transonic cryogenic tunnel fHASA-TS-76 Experimental and analytical investigations to improve low-speed performance and stability and control characteristics of supersonic cruise fighter vehicles fNASA-CB-1541221 B77-28136 Kind-tunnel tests of a 1/4 scale model of the Bell XS-1 transonic airplane. 1: Lonqitudinal stability and control characteristics CL6D121 ,, N77-29071 Seme effects of sueepback and airfoil thickness on longitudinal stability and control characteristics at transonic speeds B77-29076 lew-speed wind tunnel investiqation of an advanced supersonic cruise arrow-wing configuration fNASA-TM-740431 N77-29096 Subsonic and supersonic aerodynamic characteristics of a supersonic cruise tighter oodel with a twisted and cambered winq with 74 deg sweep r N A S A - T d - X - 3 5 3 0 1 N77-29102 Development of hiqh stability fuel, phase 3 [AD-A0389771 H77-29322 SOPEBSOHIC CCBBOSTIOH BSBJET EHGIHBS Investigation of e f fec t of propulsion system installation and operation on aerodynamics of an airbreatbinq hypersonic airplane at Bach 0.3 to 1.2 fNASA-TN-D-85031 N77-28093 SDPEBSONIC CBDISE AIBCBAF1 BBSBiBCH Recent ground-based and in-fliqht simulator studies of low-speed handlinq characteristics of supersonic cruise transport aircraft f A I A A 77-1111(1 A77-43174 SOPEBSOBIC PlOB Steady linearized aerodynamics. II - Supersonic A77-41268 Two problems that arise in the generation and propagation of sonic booms. 1: Flow field in the plane of symmetry below a delta wing. 2; Focusing of an acoustic pulse at an arete 1177-29091 SOPEBSOHIC FLOTTEB Empennage snapthrough stability and vibrations in supersonic f low A77-44087 SDPEBSONIC NOZZLES Experimental studies of the noise produced in a sjpersonic nozzle by upstream acoustic and thernal disturbances FPB-264S33/31 1177-28914 SOPEBSOBIC SPEEDS An assessment of the airplane drag problem at transonic and supersonic speeds, 15 Ju ly 1974 CL5l(F16l N77-29079 SDPEBSOHIC TBAHSPOBTS The next SST - Hhat will it ba ( A I A A PAPEB 77-7971 A77-41960 The application of new technology for performance improvement and noise reduction of supersonic transport aircraft f A I A A PAPEB 77-8301 A77-41968 Advanced supersonic transport propulsion regnirements f A I A A PAPEB 77-8311 A77-41969 Technology status of }et noise suppression concepts for advanced supersonic transports f A I A A PAPER 77-8331 A77-41971 Recent ground-based and in-fliqht simulator studies of low-speed handlinq characteristics of supersonic cruise transport aircraft f A I A A 77-1,1441 . , A77-43174 A computationally fast one-dimensional diffusion-photochemistry model of SST wakes A77-43735 Low-speed wind-tunnel investigation of a large-scale advanced arrow wing supersonic transport configuration with engines mounted above the wing for upper-surface blowing rHASA-TM-X-727611 1177-28109 SOPBBSOBIC BIHD TOHSELS Methods and problems in practical aerodynamics /4th revised and enlarged edition/ Russian book A77-42219 SOPPBESSOBS Aero-acoustic performance comparison of core engine noise suppressors on N A S A quiet engine c f N A S A - T M - X - 7 3 6 6 2 1 1177-28119 SDBFACB FIBISUIHG Structural-logic diagram for ensuring high-rate products in aircraft industry quality control A77-40721 Surface finishing for aircraft wings fNASA-CASE-HSC-12631-1 ] N77-28225 SURFACE LATEBS Expedient structural sandwich soil surfacing of fiberglass reinforced polyester and polyurethana foam [AD-A0384171 B77-28149 SOBFACE VEHICLES The vehicle mapping device FKG-1, a device for indicating the location of land vehicles and helicopters on the map A77-43578 SOBVEILLAHCE Is the pilot necessary in a light observation helicopter A77-43340 SOBTITAL EQUIPHEHT Aircraft fire fighting tactics - Handling of equipment A77-40938 SHEiT COOLIHG Certain problems associated with the application of the transpiration cooling of gas turbine engine blades A77-40708 SIEPT flIHGS Monolithic wing desiqn with spanwise web-spars A77-44078 Interference problems on wing-fuselaqe combinations. Part 3: Symmetrical swept wing at zero incidence attached to a cylindrical fuselage fARC-LP-13331 1177-28081 Interference problems on wing-fuselage combinations. Part 4: The design problem for a lifting swept wing attached to a cylindrical fuselage rAHC-CP-1334] N77-28082 A comparison of the experimental aerodynamic characteristics of an oblique winq with those of a swept winq in the Ames 6 by 6 foot wind tunnel rHASA-TM-X-35471 B77-28086 Characteristics of swept wings at hiqh speeds, 30 January 1952 C L 5 2 A 1 5 1 N77-29078 A-34 SUBJECT IBDEX THEBHAL IBSOLATIOB SiEPTBACK BUGS Sone effects of sweeptack and airfoil thickness on longitudinal stability and control characteristics at transonic speeds R77-29076 SIHCBBOHISH Expansion tunnel performance with and without an eloctronaqnetically opened tertiary diapbraqn 477-008311 SYBTBBTIC POE1S Alternate aircraft fuels: Prospects and operatiooal implications rHASA-Tfl-I-71|0301 H77-28322 Evaluation of methods to produce aviation Turbine fuels troi synthetic crude oils, phase 2, volume 2 flD-A03619-m N77-291I45 TBAJSBISSIOH EFFICIEMCI Tracer decoder - A receiver for radio navigation relay systems S77-1422H TBABSfllSSION LIHES A-7 airborne Light Optical Fiber Technology (ALOFT) demonstration project rAD-A0384551 N77-29952 TBAHSIIISSOBETBBS Transmissometer measurement of particulate emissions from a net engine test facility A77-14.06143 TBASSONIC COHPBESSOBS Quantitative density visualization in a transonic compressor rotor A77-I11,863 TRANSONIC FLIGHT Estimated transonic f lying guallties of a tailless airplane based on a model investigation, 8 June 19<49 C L 9 D 0 8 1 N77-29075 Some effects of sweepback and airfoil thickness on longitudinal stability and control characteristics at transonic speeds N77-29076 A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined f rom di f ferent test techniques, 14 October 1960 C L 5 0 B 0 2 1 N77-29077 TBAHSONIC FLOH Computation of viscous transonic f low about a lifting airfoil F A I A A PAPEB 77-6791 A77-140700 Unsteady linearized transonic flow analysis for slender bodies A77-«0830 Load distribution on a close-coupled wing canard at transonic speeds f A I A A PAPEB 77-11321 A77-1I3198 The f low over a helicopter blade tip in the transonic regime f O N E R A , TP NO. 1976-115] A77-143351 Studies on transonic turbines wi th film-coole'd blades f A D - A 0 3 6 l 4 0 2 1 H77-28131 TB&HSOIIC SPEED An assessment of the airplane drag problem at transonic and supersonic speeds, 15 Ju ly 19714 C L b Q F 1 6 l N77-29079 Load distribution on an closed-coupled winq canard at transonic speeds r H A S f - T M - 7 a 0 5 3 1 N77-29097 TBASSONIC BUD TOHHELS Hind-tunnel investigation of a variable camber and twist wing in the Langley 8-ft transonic .find tunnel f NASA-TD-D-8'4751 N77-28091 A-36 SOBJBCT IHDEX OBSTEADY FLOB Cryoqeoic desiqn and safety review BASA-Langley Besearcb Center 0.3 meter transonic cryoqenic tunnel rH4S4-TH-747671 H77-2BU3 TBAHSPOBT AIBCBAFT An evaluation of worldwide transport aircraft fire experiences 477-110927 I orroving fire prevention measures on board commercial transport aircraft A77-409Q7 Evaluation of fliqbt spoilers for vortex alleviation on wide-bodied jets 477-1)1518 Operational reliability of aircraft powerplants Bu£>sian took 477-416118 Our next conmercial transport - Collisions of interest 477-142562 Cost effective desiqn of an air transport fliqht control naintenance system f4144 77-11031 477-02816 Ccoparison of VGU data from vide-body and narrow-body lonq-haul turbine-powered transports fNASA-TB-D-8481] H77-28061 The aarket for airline aircraft: 4 study of process and performance fNASA-CR-1511617] B77-28100 An assessaent of the accuracy of subsonic linearized theory for the desiqn of warped slender winqs r4RC-CP-132 A77-43318 COILE, J. The distribution of fracture toughness data for b6ac steel fABL/STROC-qOTB-1291 N77-28267 CBABEB, B. S. Two problems that arise in the generation and propagation of sonic booms. 1: Flow field in the plane of symmetry below a delta wing. 2: Focusing of an acoustic pulse at an arete H77-29091 CREBOHESE, V. F. New technology ATE in support of the Y A H - 6 4 advanced attack helicopter T A I A A PAPEB 77-896] A77-H984 CBICHTOB, J. B. Narket development problems for local service air carriers 477-41850 CEIHI, P. Consideration of clogging in boundary-layer control system design A77-11549 CBOOB, D. B. Evaluation of flight spoilers for vortex alleviation A77-41548 CBOOPBICK, S. B. Spacecraft flight control with the new phase space control law and optimal linear net select 77-1071 ] A77-42781 B-3 COBBAGB. J. B. PEBSOHiL ADTHOB INDEX CUBBA6E, J. H. Investigation of effect of propulsion system installation and operation on aerodynamics of an airbreathinq hypersonic airplane at Hach 0.3 to 1.2 fNASA-TN-D-85031 N77-28093 COLLCH, B. B. Full-scale altitude engine test of a turbofan exhaust-gas-forced mixer to reduce thrust specific fuel consumption rNASA-TH-X-3568] N77-28123 CZABHECKI. K. B. Lateral stability and control tests of the XP-77 airplane in the NACA full-scale tunnel, 16 June 19<41 N77-29068 The lateral flying gualities of the Bell XP-77 airplane as estimated from full-scale tunnel tests, 16 June 1944 N77-29069 DALTOH, C. The inverse problem for axisymmetnc aerodynamic shapes fAIAA 77-11751 A77-41753 DAHILIR, A. I. Influence of middle-surface curvature on stress state of low-aspect-ratio wing A77-11097 DAEHELL, D. 8. National Airlines Fuel Management and Allocation Sodel A77-43399 DABBOZES, J. S. Behavior of a subsonic flow past a thin wing in the vicinity of the leading edge fESA-TT-401 ] N77-29108 DAVIES, F. J. An assessment of the accuracy of subsonic linearized theory for the design of warped slender wings fABC-CP-13241 N77-28110 DEBEA, D. B. The effects of relative instrument orientation upon gravity qradiometer system performance fAIAA 77-10701 A77-U2780 Application of microelectronic technology to general aviation flight control CAIAA 77-11021 A77-12805 DEBOEES, B. 0. Studies on transonic turbines with film-cooled blades fAD-A036U021 N77-28131 DESJABDIHS, B. A. Botor isolation of the hingeless rotor BO-105 and YOH-61A helicopters A77-43350 DETHOHAS. A. F. A flight control system using the DAIS architecture fAIAA 77-11001 H77-12804 DETOBE, J. Tilt rotor 7/STOL aircraft technology A77-43332 DIETEE, 8. HIFLAS - Helicopter infrared flight command and landing system A77-43358 DIBAIO, L. B. Extinguishants for aircraft fire fighting foaming agents - Protein, fluoroprotein and AFFF A77-40946 DRITBEHKO, 10. B. Study of a nonisothermal axisymmetnc near wake A77-13928 DOB1AH, C. J. Ar approximate spin design criterion for monoplanes, 1 Hay 1939 rNACA-TN-7111 N77-29060 Spin tests of a 1/20-scale model of the XP-39 airplane, 15 Harch 1939 N77-29061 Spin tests of a 1/20-scale model of the XF40-1 airplane, 12 July 1939 N77-29062 Stin tests of 1/16-scale models of the S3N-3 landplane and seaplane, 12 January 1940 N77-29063 Spin tests of a low-wing monoplane to investigate scale effect in the model test range, nay 1911 [NACA-TH-807] 177-29061 Methods of analyzing wind-tunnel data for dynamic flight conditions r»ACA-m-828] N77-29065 The effect of cowling shape on the stability characteristics of an airplane, September 1912 CL-3431 H77-29066 Some theoretical considerations of longitudinal stability in power-on flight with special reference to wind-tunnel testing, November 1912 CL-3091 N77-29067 Lateral stability and control tests of the XP-77 airplane in the NACA full-scale tunnel, 16 June 1914 N77-29068 The lateral flying qualities of the Bell XP-77 airplane as estimated from full-scale tunnel tests, 16 June 1914 , N77-29069 The stability and control of tailless airplanes, 19 August 1914 rBEPT-7961 N77-29070 Wind-tunnel tests of a 1/4 scale model of the Bell XS-1 transonic airplane. 1: Longitudinal stability and control characteristics C L 6 D 1 2 ] N77-29071 Current status of longitudinal stability, 24 May 1948 CL8A281 N77-29072 Factors affect ing static longitudinal stability and control N77-29073 Low-speed wind-tunnel investigation of the longitudinal stability characteristics of a model eguipped with a variable-speed wing, 23 May 1949 f L 9 B 1 8 l N77-29074 Estimated transonic flying qualities of a tailless airplane based on a model investigation, 8 June 1949 CL9D081 N77-29075 Some effects of sweepback and airfoil thickness on longitudinal stability and control characteristics at transonic speeds H77-29076 A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques, 4 October 1960 CL50H021 N77-29077 Characteristics of swept wings at high speeds, 30 January 1952 CL52A151 N77-29078 An assessment of the airplane drag problem at transonic and supersonic speeds, 15 July 1974 CL54F161 N77-29079 Proportioning the airplane for lateral stability N77-29082 DOYLE, V. L. Attenuation of upstream-generated low freguency noise by gas turbines fNASA-CR-1352191 N77-28122 DONN, B. 8. The electrostatic sensing of simulated I1A-1A gas path distresses fAD-A0385271 N77-28130 DDSA, D. J. Simplified multi-mission exhaust nozzle system fAIAA PAPEE 77-960] A77-41991 DWTEB, F. A. A model to predict mutual interference effects on an airframe fAD-A039224 /11 N77-29347 EBBESON, G. B. The reduction of interference from large reflecting surfaces A77-42544 EBHEB, B. E. Redundant integrated flight control/navigation inertial sensor complex TAIAA 77-11091 A77-42808 PBBSOBAL AOTBOB IHDBX GEBSTE8, A. BCKl. HE. Automatic correction of positioa error by means of a digital correlation of surface structures A77-U3577 EDBABDS, J. B. Active flutter control using generalized unsteady aerodynamic theory A77-H2772 ELLIS. B. in IED numeric display for the aircraft cockpit A77-U1U73 BPIFABOV, V. B. Certain problems associated mth the application of the transpiration cooling of qas turbine engine tlades A77-U0708 EPSTEIH, ». B. Quantitative density visualization in a transonic compressor rotor A77-U1863 BBEBIB. ». V. Save structure and density distribution in a nonstationary qas jet A77-41270 EBVIB, J. B. Procedure for the development of naval aviation naintenance objectives rAD-A0382011 B77-280614 ESCBiEILEB, 3. Advanced design procedure for aircraft engine selection [AIAA PAPEB 77-953] A77-U1989 FABBBB. H. G. A wind tunnel technique for determining stability derivatives from cable mounted aeroelastic models TAIAA 77-11281 A77-U3161 FAOLDBBS. C. T.. JB. The Analytical naintenance Program - No more 'maintenance as usual1 A77-U20UU FAOIKSBB. B. B. B. Environmental reliability testing of helicopter systems A77-43361 FEBBEHKABP, L. G. Surface finishing CNASA-CASE-BSC-12631-11 N77-28225 FBLLEH, I. V. Development of a controllable particle generator for LV seeding m hypersonic vind tunnels A77-44295 FEBTOB, 0. L. Turbine engine particulate emission characterization rAD-AOi|1i|991 N77-29152 FEBGOSOB. D. B. Supersonic -)et exhaust noise investigation. Volume 3: Computer users manual for aero-acoustic predictions rAD-A03861<4] N77-28127 FEBGOSOB, B. Fracture Mechanics Evaluation of B-1 Materials. Volume 1: Text fAD-A0398831 1177-29287 Fracture Mechanics Evaluation of B-1 Materials. Volume 2: Fatigue crack growth data fAD-A0397851 H77-29288 FEBGOSOH. B. J. The airport fire defense - The basic mission and needs i77-U094)ASA-CB-154270] H77-29142 GBOBSBECK, 0. E. Comparison of jet Mach number decay data with a correlation and ]et spreading contours for a large variety of nozzles fNASA-TH-D-8423] B77-28087 GOPTA, D. B. A two-level adaptive controller for application to flight control systems f A I A A 77-1092] A77-42797 Some analytical control laws for the design of desirable lateral handlinq qualities using the model matching method f A I A A 77-1045] A77-42812 GOPTA, P. C. The application of new technology for performance improvement and noise reduction of supersonic transport aircraft T A I A A PAPEB 77-830] A77-41968 GUTHBIE, J. A., JE. C-1U1A pitot-static system calibration tests f A D - A 0 3 6 2 4 1 ] H77-28115 GilSHE, G. B. Urea formadehyde foamed plastic emergency arresters for civil aircraft fABC-CP-1329] N77-28144 H HAAS, G. J. Handling aircraft accident/incident survivors and victims - Accountability techniques and body management A77-40941 BAFTKA, B. T. Optimization of flexible wing structures subject to strength and induced drag constraints A77-U3727 BAGDE, D. S. tlSEG, a seqmented mission analysis program for low and high speed aircraft. Volume 1: Theoretical development fHASA-CB-2807] N77-29085 HAJJAB, F, Studies on transonic turbines with film-cooled blades fAD-A036402] N77-28131 BALL, C. 8. Boston Air Boute Traffic Control Center (ABTCC) lighting study rAD-A041324] N77-29124 HALL, I. E., JB. A wind tunnel technigue for determining stability derivatives from cable mounted aeroelastic models fAIAA 77-1128] A77-43161 B-6 PBBSOBAL 40TBOB IHDBI BSD, H.-T. Identification of stability derivatives fron wind tunnel tests of cable-mounted aeroelastic aodels fNASA-CB-1 TAD-A0356901 S77-29130 JOBDAB, P. Lift calculation and flow mechanisms when the maximum lift is exceeded rNASA-TT-F-171291 H77-28067 JOYCE, B. 6. Interference problems on wing-fuselage combinations. Part 2: Symmetrical unswept wing at zero incidence attached to a cylindrical fuselage at zero incidence in midwing position fABC-CP-13321 N77-28080 Interference problems on wing-fuselage combinations. Part 3: Symmetrical swept wing at zero incidence attached to a cylindrical fuselage fABC-CP-13331 N77-28081 Interference problems on wing-fuselage combinations. Part 4: The design problem for a lifting swept wing attached to a cylindrical fuselage FAHC-CP-133U] , H77-28082 JOLL. B. V. The reduction of interference from large reflecting surfaces - S77-U25t|U KAHH, 0. User's manual for ILSS (revised ILSLOC): simulation for derogation effects on the instrument landing system rAD-A0356901 H77-29130 KALFADELIS. C. D. Evaluation of methods to produce aviation Turbine fuels from synthetic crude oils, phase 2, volume 2 [AD-A0361901 N77-28325 KABBABOELLSB, G. Aircraft of wide speed and manoenvering range ,A77-U3366 KAEBAEKAB, J. S. Information processing'requirements for on-board monitoring of automatic landing f A I A A 77-10931 A77-*2798 KABPLOS. B. J. Computers for real time flight simulation: A market survey rHASA-CH-28851 H77-28113 KEATES, F. B. A comparison of fatigue crack propagation rates in CN002 (unclad BBSS) aluminium alloy immersed in jet fuel and a fuel simulant ' fABC-CP-13651 N77-29230 KELLAIAT, B. Developments in the lifting surface theory treatment of symmetric planforms with a leading edge crank in subsonic flow [ABC-CP-1323] H77-28076 KELLY, J. B. Flight investigation of a vertical-velocity command system for VTOL aircraft rSASA-TH-D-SUSOl S77-28137 KEBP, B. B. Kind-tunnel tests of a 1/1 scale model of the Bell X3-1 transonic airplane. 1: Longitudinal stability and control characteristics TL6D121 N77-29071 B-8 PEBSOHAL AOTBOB IBDBX KOBZISEB. B. I. KBSKAB, D. A. Load factor response of digitally controlled aircraft fAIAA 77-10801 A77-42786 KBYES, J. i. Force testing manual for the Langley 20-inch Hach 6 tunnel [NASA-Ttl-714026] N77-28115 KIESSLIBG, F. A model for vindtunnel rotorcraft research - Ground resonance investigations A77-13369 KIHBBIBL, H. A. Our next commercial transport - Collisions of interest A77-42562 KIHS, B. L. Canadian Forces Search and Bescue A77-11936 KIHG, L. S. Computation of viscous transonic flow about a lifting airfcil TAIAA PAPER 77-6791 A77-40700 KINGSIOB, 1. Tilt rotor V/STOL aircraft technology I A77-13332 KIHZIEB. J. A. Surface finishing rNASA-CASE-MSC-12631-11 H77-28225 KIBKBY. I. I. Some research problems on the fatigue of aircraft • - structures A77-II1U50 KIBSCB, K. .J. Wind tunnel flow seeding for laser velocimetry applications A77-1K129U KLEIS, B. C-141A pitot-static system calibration tests r AD-A0362I411 N77-28115 KLEIB. V. Determination of longitudinal aerodynamic derivatives from steady-state measurement of an aircraft FAIAA 77-11231 A77-43156 i Compatibility check of measured aircraft responses using kinematic equations and extended Kalman filter rNASA-TH-D-8514] H77-29113 KLIBOV. V. I. Aircraft aeromechanics A77-U157S KHIBB, T. F. An LED nuneric display for the aircraft cockpit A77-41U73 KBOTT, P. B. Supersonic net exhaust noise investigation. Volume 2: Technical report CAD-A038613] , N77-28126 Supersonic net exhaust noise investigation. Volume 3: Computer users manual for aero-acoustic predictions » fAD-A03861«l H77-28127 KHYSB, ID. A. Acoustic properties of pneumatic vortex sprayers A77-140703 The effect of the structural features of a combustion chamber on the emission of toxic 1 compounds A77-10711 KOCHBEV, V. A. wave structure and density distribution in a nonstationary gas ^t A77-U1270 KOCKA, V. Analysis of identification errors in flight dynamics A77-Q1392 KOBLRAH. D. L. Flight evaluation of a spoiler roll control system on a light twin-engine airplane [NASA-CR-15K121 1 N77-28135 KOLOVSNDIS, B. A. Study of a nonisothermal axisymmetric near wake A77-U3928 KOBABOV, V. A. Influence of middle-surface curvature on stress state of low-aspect-ratio wing 177-UD097 KOHECHAK, G. J. Development of an integrated fire/flight control system for a high-perforoance fighter aircraft fAIAA PAPEB 77-10781 A77-U3201 KOBLEV. A. F. Selection of an atomizer and its modes of operation for the removal of ice deposits, frost and frozen snow from aircraft surfaces A77-40726 KOSABSKI, B. Static performance of vectoring/reversing non-axisymnetnc nozzles TAIAA PAPEB 77-8101 A77-11971) KOPALA, 1. J. Boston Air Boute Traffic Control Center (ABTCC) lighting study fAD-A01(132 A77-13335 8-17 VEHKSTBSAH, C. PEBSOBAL iOTHOE IHDBX VEHKATBSiH, C. Optimization of an oleo-pneumatic shock absorber of an aircraft during landing A77-415U7 VLIBGIB, B. Besidual strength data of riveted panels with different stiffener configurations rHLB-TB-76033-0] N77-29569 VOBGIAHB, 0. B. Comparison of net Mach number decay data with a correlation and jet spreading contours for a larqe variety of nozzles rHASA-TN-D-8423] N77-28087 VOBOHIN, V. G. Low-temperature heat pipes for aircraft 477-43612 TOSS, B. Profile flows taking cavitation bubble dynamics into account rBHVG-FE»T-76-22] H77-29329 TOTB. B. O. Cryogenic design and safety review NASA-Langley Besearch Center 0.3 meter transonic cryogenic tunnel rNASA-TH-74767] N77-28143 w 1ACKEBLE, P. H, Ballistic and impact resistance of composite rotorblades A77-43360 BAGHEB, H. Q. Engine design decisions impact aircraft life cycle costs fAIAA PAPEB 77-916] A77-41986 •ABI, B. Tire runway interface friction prediction subsystem rAD-A0399681 B77-29532 iALITI. I. Computation of viscous transonic flow about a lifting airfoil FAIAA PAPEB 77-679] A77-40700 BAHG. J. C. F. Laser velocimeter turbulence spectra measurements A77-44304 BAIBILL, B. J. B. Ambient temperature crack growth in titanium alloys and its significance for aircraft structures rHLB-BP-76008-U] N77-29278 WASBBOBH, K. E. Load distribution on a close-coupled wing canard at transonic speeds TAIAA PAPEB 77-1132] A77-43198 Load distribution on an closed-coupled wing canard at transcnic speeds rNASA-TH-74053] 877-29097 BATSOH. J. B. Direct-force flight-path control - The new way to fly fAIAA P8PEB 77-1119] A77-43197 Development of an integrated fire/flight control system for a high-performance fighter aircraft TAIAA PAPEB 77-1078] A77-I1J201 BAOGB, J. D. Helicopter integrated control (GAT-2H) FAD-A036204] N77-28141 BBBBB, J. Interference problems on wing-fuselage combinations. Part 1: Lifting unswept wing attached to a cylindrical fuselage at zero incidence in mdwing position fABC-CP-1331 ] H77-28079 Interference problems on wing-fuselage combinations. Part 2: Symmetrical unswept wing at zero incidence attached to a cylindrical fuselage at zero incidence in Didwing position fABC-CP-1332] N77-28080 Interference problems on wing-fuselage combinations. Part 3: Symmetrical swept wing at zero incidence attached to a cylindrical fuselage fABC-CP-1333] S77-28081 Interference problems on wing-fuselage combinations. Part 4: The design problem for a lifting swept wing attached to a cylindrical fuselage TABC-CP-1334] N77-28082 BEEKS, T. H. Application of a computer program system to the analysis and design of supersonic aircraft f A I A A 77-1131] A77-43163 BBIL. J. Characteristics of swept wings at high speeds, 30 January 1952 C L 5 2 A 1 5 ] H77-29078 BEISS, B. Dynamics of a small helicopter with a high capacity rescue hoist A77-43336 BELLES, B. H. Becent experience in the testing of a generalized rotor aeroelastic model at Langley Besearch Center A77-43361 Load and stability measurements on a soft-inplane rotor system incorporating elastomeric lead-lag dampers [NASA-TN-Dr8437] H77-28112 BELLS, B. B. Simplified unsteady aerodynamic concepts, with application to parameter estimation f A I A A 77-1124] A77-43157 BEHHEBSTBOEH, B. Computer simulation of fatigue crack propagation in aircraft components riSBN-91-7372-147-6] ' N77-28518 BHABF, J. B. , . An LED numeric display for the aircraft cockpit A77-41473 BBITESIDE, Q. A. Aircraft simulator data requirements study. Volume 1: Executive summary [AD-A040955 ] .N77-29181 Aircraf t simulator data reguirements s tudy, volume 3 C A D - A 0 4 0 9 2 8 1 N77-29182 BILLABD, C. H. Static performance of vectoring/reversing non-axisymmetric nozzles [ A I A A PAPEB 77-840] • ' A77-41974 KILLIABSOB, B. B. Criteria for large scale fire testing of aircraft interiors A77-40924 BILSOH, J. B. Airframe/engine integration with variable cycle engines f A I A A PAPEB 77-798] A77-41961 BILSOH, F. FAA air traffic activity, calendar, year 1976 T A D - A 0 4 0 4 7 4 1 N77-29134 BIHTEB, K. G. Measurements of pressure distribution on a half-model wing-body combination of 55 deg. sweep over a wide range of reynolds number fABC-CP-1328] N77-28078 BITCOPSKI, B. D. Alternate aircraft fuels. Prospects and operational implications r H A S A - T N - X - 7 4 0 3 0 ] N77-28322 BITTLIB, G. A method of analysis for general aviation airplane structural crashworthiness A77-42566 BOOD, B. D. Hake turbulence detection and economic impact of proposed improvements f S A E PAPEB 770583] A77-42050 BOODBABD, D. E. A liqhter-than-air bibliography f A I A A 77-1177] A77-U1754 BOODBABD, R. A. A revaluation of helicopter main rotor noise A77-43346 BOBK, C. C. Spacecraft flight control with the new phase space control law and optimal linear -jet select f A I A A 77-1071] A77-42781 BBIGBT. B. B. Airframe/engine integration wi th variable cycle engines f A I A A PAPEB 77-798] A77-41961 BBIGBT. G. E., JB. A liqhter-than-air bibliography f A I A A 77-1177] A77-41754 B-18 PEBSOHAL iOTBOB ISDEX ZEIOBI, T. J. RBI6BT, S. B. The relative importance of acoustic sources generated by helicopter rotors ID high speed fliqht 477-13370 iliTI, B. D. A study of coBauter airplane desiqn optioization ,fHASA-CH-151270) H77-291«2 Y TAZAB4, B. Identification of aircraft stability and control derivatives in the presence of turbulence [4IAA 77-11311 A77-13165 YBB, S. C. A comparison of the experimental aerodynamic characteristics of an oblique winq with those of a swept winq rHASA-TB-X-35«71 177-28086 TBHHI. K. B. Fliqht investigation of a vertical-velocity command system for VTOL aircraft fHASA-TN-D-8180) N77-2B137 II. C. J. Fliqht contrcl system of an advanced air superiority fiqhter ftl&l 77-1C791 H77-H2785 YOSBIBO, B. Hi-fidelity airplane simulation model [AIAA 77-1166] A77-13191 loose. B. Aircraft hydraulic system dynamic analysis. Volume 6: Steady State Plow Analysis (SSFAN). Computer proqraa technical description UD-A038692) 177-29162 IODNG. J. 1. Prediction of lump phenomena in rotationally-coupled maneuvers of aircraft, locludinq nonlinear aerodynamic effects fAIAA 77-1126) A77-l»3159 IODHG. B. a. nodular hiqh accatacy tracker for dual channel laser Doppler velocimeter A77-1U301 T.OAH, C. B. A study of the effect of unsteady aerodynamics on the aercelastic stability of rotor blades in hover H77-29086 I ZALOVC1K. J. A. Comparison of VGH data from wide-body and narrow-body lonq-haul turbine-powered transports rSASA-TB-D-SISli H77-28061 ZAHOBASV, T. P. Calculation of radiant cooling of air behind intense shock waves using mean optical characteristics A77-43993 ZAHBETTI, L. Analysis of unsteady flow in tucbojet enqine afterburners fPOBl-1851 N77-29155 ZAVATKAI, B. F. Lif£ considerations in the enqi&e desiqn process — f»IAA PAPEB 77-9511 A77-41990 _ ___ ZEDAB. 8. F. — - - The inverse problem for azisymmetric aerodynamic shapes fAIAA 77-1175) A77-11753 ZEBOBI. 1. 3. Development of an inflatable head/neck restraint system for election seats fAD-A038762) N77-29115 B-19 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING IA Special Bibliography (Suppl 89) NOVEMBER 1977 Typical Contract Number Index Listing BAS2-9177 . 877-11064 Listings m this index ate arranged alphanumencally by contract number Undei each contract numbei 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 lAAot SMffsection AF PBOJ. 2279 N77-28282 AF PBOJ. 3115 N77-29159 N77-29162 AF PEOJ. 7071 H77-29165 AF PBOJ. 9781 N77-28132 DA PBOJ. 1F1-61101-AH-15 N77-28090 DA PBOJ. 1F2-62209-AH-76 N77-28110 DA PBOJ. 1L2-62209-AH-76 N77-28112 DA PBOJ. 653 H77-29071 DAAJ02-71-C-0025 N77-28129 DAAJ02-75-C-OOS2 H77-28140 DOT-CG-63151-A 877-29133 DOT-FS70BAI-175 N77-29317 DOT-JA72HA-3098 N77-29119 DOT-FA72HAI-261 1177-29127 DOT-FA7lmAI-qi9 N77-293U6 DOT-FA75HA-3707 A77-12566 DOT-FA75HA-3722 H77-29152 DOT-FA75HAI-526 N77-2917« DOT-FA75HAI-536 H77-29175 DOT-FA76WA-3738 N77-29121 DOT-FA76HA-3761 H77-29129 DOT-OS-10013 H77-29123 DOT-OST-20197 " 177-28133 N77-28911 DOT-TSC-1128 N77-29120 E(t)9-18) -2087 A77-U3771 EPA-68-01-3218 N77-28918 FAA PBOJ. 031-2141-012 N77-29127 FAA PBOJ. 181-520-100 N77-29113 F19628-76-C-0002 N77-29318 F33615-73-C-2031 S77-28126 X77-28127 F33615-73-C-5102 H77-28316 F33615-71-C-2016 M77-29159 N 7 7 - 2 9 I 6 2 F33615-71-C-2036 N77-28325 F33615-71-C-3010 H77-28232 F33615-71-C-3069 N77-29577 F33615-75-C-3070 A77-U3152 F33615-76-C-0106 N77-29181 U77-29182 F33615-76-C-3012 N77-29165 F33615-76-C-5030 N77-28282 F33657-70-C-0800 N77-29287 N77-29288 F33657-71-C-0129 N77-29532 F33657-75-C-0606 A77-11986 F11620-71-C-0065 1177-28132 F11620-76-C-0009 S77-28116 N77-28117 LI/LB/1969 N77-29565 N A S A OEDEB A-29917-B N77-29111 NASH-2791 N77-28067 NASM-2971 H77-28100 NAS1-12895 A77-11304 NAS1-13190 A77-12798 NAS1-13511 A77-12773 NAS1-13599 S77-29085 NAS1-13817 A77-H2808 NAS1-13870 A77-11857 NAS1-13871 A77-11857 NAS1-13938 1177-29166 NAS1-11163 H77-29918 NAS2-7806 N77-28113 H77-29173 NAS2-7926 A77-13175 BAS2-9003 N77-29095 NAS2-9083 A77-12805 NAS2-9113 1177-28063 SAS2-9223 A77-13726 NAS2-9382 A77-12805 NAS2-9512 A77-11752 NAS3-19135 N77-28122 HAS5-23177 S77-29139 S77-29110 1177-29111 HAS8-20082 A77-10830 1IAS9-13809 A77-12781 NCA2-OR785-601 B77-29921 NGL-0«-001-007 A77-11291 HGL-22-009-121 H77-13771 1IGL-22-009-383 A77-H1863 NGR-05-007-111 A77-13362 NGB-11-005-111 B77-28068 877-28069 1GB-25-001-055 • ' 877-28070 BGB-36-001-061 477-13157 BIVH-1705 877-29569 BI»B-1775 877-29115 HBC A-1080 477-12797 477-12812 NBC A-5625 477-12797 8SG-1161 477-13156 NSG-1227 N77-28135 NSG-1266 477-13727 NSG-1298 477-13735 NSG-1309 H77-28136 NSG-2115 D77-29112 NSG-11003 477-13158 N0011-75-C-0132 477-12759 N0019-73-C-0501 477-13199 NOOO11-67-4-0201-0079 877-28131 N00019-76-C-0123 477-11972 B00110-71-C-0618 N77-29322 800150-71-C-1717 477-13598 B62269-76-C-0166' 477-11763 H62269-76-S-1325 477-11765 B68335-76-C-1136 477-13598 RHLAP-8B-KL-197S/S3 B77-29105 SH/1170/012 H77-29156 50107056 B77-29331 505-02-21 K77-29100 505-03 877-28087 505-01 H77-28088 505-01-11-01 877-28139 505-05 N77-28123 505-06-93-01 877-29113 505-08-25-01 877-28061 505-08-26-02 B77-28138 505-10-11-10 877-28091 505-10-21-05 877-28090 505-10-22 877-28525 505-10-26-01 877-28112 505-10-26-01 B77-28911 505r11-12 N77-28086 505-11-16-08 877-28091 H77-29101 505-11-16-11 877-2B092 505-11-21-02 N77-29097 505-11-21-03 N77-29102 505-11-31-02 'B77-28093 506-26-31 877-28073 513-53-06 877-29111 513-51-02-01 877-28137 517-51-01 ' 877-29098 713-01-12-02 877-28109 877-29096 C-1 1. Report No. NASA SP-7037(89) 2. Government Accession No 3 Recipient's Catalog No 4 Title and Subtitle AERONAUTICAL ENGINEERING A Special Bibliography (Supplement 89) S Report Date November, 1977 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. 20546 11 Contract or Grant No 13 Type of Report and Period Covered 12. Sponsoring Agency Name and Address 14 Sponsoring Agency Code IS Supplementary Notes 16. Abstract This bibliography lists 538 reports, articles, and other documents introduced into the NASA scientific and technical information system in October 1977. 17. Key Words (Suggested by Author(s)) Aerodynamic s Aeronautical Engineering Aeronautics Bibliographies 18. Distribution Statement Unclassified - Unlimited 19. Security dassif. (of this report) Unclassified 20 Security Classif. (of this page) Unclassified 21 No of Pages 130 22 Price' $4.75 HC For sale by tt* National Technical Information Service, Springfield. Virginia 22161 •U.S. GOVERNUEMT PRINTING OFFICE! 1977- 735-078/69 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to eleven special libraries located in the organizations listed below Each library is prepared to furnish the public such services as reference assistance mterlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention 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. 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Seattle following the accession number) are also received by 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 TENNESSEE Memphis Public Library TEXAS Dallas Public Library Fort Worth Public Library WASHINGTON Seattle Public Library WISCONSIN Milwaukee Public Library An extensive collection of NASA an6 NASA-sponsored documents and aerospace publications available to the public for reference purposes is maintained by the American Institute of Aeronautics and Astronautics. Technical Information Service. 75O Third Avenue. New York. Nevv York 10017 EUROPEAN An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa, Wettierby. Yorksftire. 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Europe&n' Space Agency. -8-1C rue Mano-Nikis. 75738 Pans CEDEX 15, France NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC 2OS46 POSTAGE AND FEES PAID NATIONAL AERONAUTICS AND OFFICIAL BUSINESS AUTY FOR PR.VATE USE ,3OO SPECIAL FOURTH CUSS MAIL NASA-451 Book If I lndolivpr. iblP (Section 158 POSTMASTER pn^t.il M.it I) DM Not Roturn NASA CONTINUING BIBLIOGRAPHY SERIES NUMBER TITLE FREQUENCY NASA SP--7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP-7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP -7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY ° Quarterly Energy sources, solar energy, energy conversion, transport, and storage NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques Details on the availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL 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 special bibliography with indexes, supplement 89, November 1977

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