NASA Technical Memorandum 81175 February 1980
i1@1t81 Ames Research Center Publications: A Continuing Bibliography
l/) luation of the Tilt Rotor Concept: The XV-1S's Role. Future Requirements and Roles of Computers in Aerodynami IX) 'luting Viscous Flows. A Simple Method for Estimating Minimum Autorotative Descent Rate of Single Rotor Helie .g; '!nd Dynamic Stability Analysis of the Space Shuttle Vehicle-Orbiter. Comparison of Measured and Calculated Heli 'lPulsive Noise. Effect of High Lift Flap Systems on the Conceptual Design of a 1985 Short-Haul CommlOrcial ST "n Multicyclic Control by Swashplate Oscillation. Low-Speed Aerodynamic Characteristics 0 '~odel at High Angles of Attack and Sideslip. Generalization Of Huffman Coding to Minimiz. w. Optimum Horizontal Guidance Techniques for Aircraft. Quasi-Optimal Control of a Mavin! ~e and Control for Investigating Aircraft Noise-Impact Reduction. Trajectory Module of the A.,craft Synthesis Program ACSYNT. A Flight Investigation of the Stability, Control, and Hanc N
1978 Ames Research Center Publications: A Continuing Bibliography
NASA National Aeronautics and Space Administration Ames Research Center Moffett Field, California 94035 FOREWORD
This sixth annual edition of Ames Research Center Publications: A Continuing Bibliography lists Ames-sponsored literature indexed during 1978 in Scientific and Technical Aerospace Reports (STAR), Limited Scientific and Technical Aerospace Reports (LSTAR) and International Aerospace Abstracts (IAA).
The Bibliography is divided into two sections: Section I contains citations and abstracts of published works listed by directorate, type of publication (NASA formal report, NASA contractor report, journal article, meeting paper, book or chapter of a book, and patents); Section II iscom prised of subject, author, contract number and report number indexes.
Information for ordering publications cited may be obtained by referring to, NASA's STAR, LSTAR, and IAA. The NASA unlimited reports are available in either hard copy or microfiche through the National Technical Information Service (NTIS), Springfield, VA 22151, or through the Government Printing Office (GPO), Washington, D.C. 20402. Items identified with an X accession number are often limited or classified and available only to certain individuals or organizations. These documents must be ordered from the NASA center or from the institution which produced. them. Patents are available through the Commissioner of Patents, U.S. Patent Office, Washington, D.C. 20231.
The Library Branch Staff is available to advise Ames requestors which form, ARC 80 "Library Resource Request" or ARC 81 "Published Material Request," should be used to order copies of published works from either the Ames Technical Library, 202-3, extension 5157, or the Life Sciences Library, 239-13, extension 5387.
Because this edition of Ames Research Center Publications: A Continuing Bibliography isthe first to be based upon the indexing services of STAR, LSTAR, and IAA, some published work may . not he included. 'If this is the case, send two copies of the published work to Betty Sherwood, 202-3, and the citation will appear in the next annual bibliography.
Betty Sherwood, Compiler
iii TABLE OF CONTENTS
Page
SECTION I -PUBLICATIONS
ORGANIZATION
Office of the Director (D) ...... 1
Adm inistration (A) ...... 3
Aeronautics and Flight Systems (F) ...... 4
Astronautics (S) ...... 22
Life Sciences (L) ...... 51
Research Support (R) ...... 59
Federal Aviation Administration ...... 61,
U.S. Army Research and Technology Laboratories and Aeromechanics Laboratory (X, Y) ...... 62
SECTION 11 - INDEXES
INDEXES
Subject Index ...... 65
Personal Author Index ...... 125
Corporate Source Index ...... 147
Contract Number Index ...... 154
Report/Accession Number Index ...... 156
v SECTION I
PUBLICATIONS OFFICE OF THE DIRECTOR
FORMAL REPORTS
N78-26152*# National Aeronautics and Space Administration N78-23993*# Operations Research. Inc. Silver Spring. Md_ Ames Research Center. Moffett Field. Calif PHASE 1: DEFINITION OF INTERCITY TRANSPORTATION PLANNING FOR AIRPORT ACCESS: AN-ANALYSIS OF COMPARISON FRAMEWORK. VOLUME 1: SUMMARY THE SAN FRANCISCO BAY AREA Final Report Jarir S Dajani. ed (Stanford Univ.. Calif). James V Jucker, ad 19 Jul 1978 42 p refs (Stanford Univ. Calif). and J Loyd Jones May 1978 300 p (Contract NAS2-9815) refs Stanford-NASA-ASEE Summer Faculty Fellowship Program (NASA-CR-152152-VoI-1. ORI-TR-1298-Vol-2) Avail NTIS on Engineering System Design held at Moffett Field, Calif. HC A03/MF AOl CSCL 13F 1977 A unified framework for comparing intercity passenger and (NASA-CP-2044. A-7347) Avail NTIS HCA13/MFAOI CSCL freight transportation systems is presented Composite measures 09E for cost, service/demand, energy, and environmental unpact were A multidisciplinary systems analysis of airport access to the determined. A set of 14 basic measures were articulated to major airports of the San Francisco Bay Area was made Basically, form the foundation for computing the composite measures A it was found that there is no major airport access problem The parameter dependency diagram, constructed to explicitly interre- D argument of the report is that commonly perceived airport access late the composite and basic measures is discussed Ground problems are either minor inconvenience magnified out of rules and methodology for developing the values of the basic proportion by a corn bination of the traveler's unreasonable measures are provided and the use of the framework with existing expectations, anxiety over flight departure and lack of information, cost and service data is illustrated for various freight systems. or not subject to solutions which do not consider the entire A R.H. urban transit system Nine specific conclusions ard recommenda tions for improvement are oresented and discussed A.,P,nr N78.29996'f Econergy Inc. Los Angeles, Caif A STUDY OF CHARACTERISTICS OF INTERCITY TRANS. PORTATION SYSTEMS. PHASE 1. DEFINITION OF TRANSPORTATION COMPARISON METHODOLOGY NASA CONTRACTOR REPORTS Executive Summary J. Morley English. Jeffrey L Smith. and Melvin W Ufson Aug 1978 42 p Sponsored in pan by DOT N78-10946" Pepperdine Univ. Los Angeles. Calif School (Contract NAS2-9814) of Business and Management iNASA-CR-152153-2) Avail NTIS HC A03/MF AOl CSCL WHO SHOULD CONDUCT AERONAUTICAL R AND D FOR 13F THE FEDERAL GOVERNMENT? The objectives of this study are (1) to determine a unified H Harvey Album Aug 1977 219 p refs '-ethodological framework for the comparison of intercity (Grant NsG-2159) iassenger and freight transportation systems. (2) to review the (NASA-CR-152021) Avail NTIS HC AIO/MF AOl CSCL ittributes of existing and future transportation systems for the OSA purpose of establishing measures of comparison. These objectives It was found that Government laboratories, and especially were made more specific to include (1) development of a NASA laboratories should be the prime national producers of methodology for comparing long term transportation trends arising applied research in aeronautics American aeronautic needs the l-om implementation of various R&D programs. (2) definition of new stimulus of markedly increased outputs of broad-based value functions and attribute weightings needed for further innovative research from NASA laboratories more than it needs transportation goals G Y most of the technology advancement and development-oriented programs currently underway in these laboratories. The Govern ment should use manufacturing companies for the vast bulk of development and most technology advancement However, the Government will have to implement programs to encourage the transfer of full information on technology and research advance- JOURNAL ARTICLES, BOOKS AND ments. from the companies that do this work for the Government. CHAPTERS OF BOOKS to competing companies Universities should be the primary sources of basic research Service R&D companies and non-profit R&D institutions provide valuable, specialized, supplementary A78-36722 Space industrialization - Education. K. M. technical capabilities and other unique attributes, which together Joels (NASA, Ames Research Center, Moffett Field. Calif.) In: The span the entire spectrum ofaeronautcal R&D Author industrialization of space, Proceedings of the Twenty-third Annual Meeting, San Francisco, Calif., October 18-20, 1977. Part 1 (A78-3 6701 15-12) San Diego, Calif , American Astronautical 4 9 1 4 9 9 Society, Univelt, Inc, 1978, p. - . 18 refs (AAS 77-258) The components of an educational system based on, and perhaps enhanced by, space industrialization communications tech nology are considered Satellite technology has introduced a synoptic distribution system for various transmittable educational media. The cost of communications satellite distribution for educational pro: -gramming-hai'bTriiii. It lis therefore, been proposed to utilize Space Shuttle related technology and Large Space Structures (LSS) to construct a system with a quantum advancement in communica tion capability and a quantum reduction in user cost. LSS for communications purposes have three basic advantages for both developed and emerging nations, including the ability to distribute signals over wide geographic areas, the reduced cost of satellite communications systems versus installation of land based systems, and the ability of a communication satellite system to create instant educational networks. G R.
D
2 ADMINISTRATION
FORMAL REPORTS
N78-27042*# National Aeronautics and Space Administration Ames Research Center, Moffett Field. Calif AMES RESEARCH CENTER PUBLICATIONS-1976 Betty Sherwood May 1978 168 p refs (NASA-TM-78493; A-7346)[ Avail. NTIS HC A08/MF A01 CSCL O5B Bibliography of the publications of Ames Research Center authors and contractors, which appeared in formal NASA publications, journal articles, books. chapters of books, patents. and contractor reports Covers 1976 Author-
A AERONAUTICS AND FLIGHT SYSTEMS
FORMAL REPORTS
N78-10019d# National Aeronautics and Space Administration flight vehicles are discussed as well as the general character of Ames Research Center Moffett Field. Calif the three dimensional attached boundary layer. the concept of LOW SPEED AERODYNAMIC CHARACTERISTICS OF AN limiting streamlines, and the present understanding of the physics 0 075-SCALE F-15 AIRPLANE MODEL AT HIGH ANGLES of three dimensional separation and reattachment The advantages OF ATTACK AND SIDESLIP of swept, sharp edges that generate controlled (or fixed) three Daniel N Petroff. Stanley H Scher. and Lee E Cohen (ARO. dimensional flow separations on a vehicle because of the Inc. Moffett Field Calif) Jul 1974 118 p refs qualitatively unchanging flow field developed throughout the range (NASA-TM-X-62360) Avail: NTIS HC AOS/MF AOl CSCL of flight conditions are promoted in preference to allowing for CIA uncontrolled (or unfixed) separations Author An 0076 scale model representative of the F-1 airplane was tested in the Ames 12 foot pressure wind tunnel at a Mach number of 0 16 to determine static longitudinal and lateral directional characteristics at spin attitudes for Reynolds numbers N78-18882S# National Aeronautics and Space Adm:mistraticon from 148 to 164 million per meter (045 to 50 million per Ames Research Center Moffett Field, Calif foot) Angles of attack ranged from 0 to -90 deg and from EXCHANGE AND RELAXATION EFFECTS IN LOW-ENERGY -40 deg to -80 deg while angles of sideslip were varied from RADIATIONLESS TRANSITIONS -20 deg to +30 deg Data were obtained for nacelle inlet ramp Mau Hsiung Chen (Oregon Umv. Eugene), Bernd Crasemann angles of 0 to 11 deg with the left and right stabilators deflected (Oregon Umv. Eugene), Michio Aoyagi. and Hans Mark (Depart 0. -25 deg, and differentially 5 deg and -5 deg The normal ment of the Air Force, Washington. D C) [1978] 28 p refs pointed nose and two alternate nose shapes were also tested (Grants NGR-38-003-036. DAAG29-78-G-0010) along with several configurations of external stores Analysis of (NASA-TM-79383) Avail: NTIS HC AO3/MF ACT CSCL 20H the results indicate that at higher Reynolds numbers there is a The effect on low-energy atomic inner-shell Coster-Kronig F slightly greater tendency to spin inverted than at lower Reynolds and super Coster-Kronig transitions that is produced by relaxation numbers. Use of a hemispherical nose in place of the normal and by exchange between the continuum electron and bound pointed nose provided an over correction in simulating yawing electrons was examined and illustrated by specific calculations moment effects at high Reynolds numbers' Author for transitions that deexcite the [3p] vacancy state of Zn Taking exchange and relaxation into account is found to reduce, but not to eliminate the discrepancies between theoretical rates and measurements Author N78-17999'# Nation 1 ieronautics and Space Administration Ames Research Center. Moffett Field, Calif TWO-DIMENSIONAL TRANSONIC TESTING WITH SPLIT- TER PLATES N78-19142*# National Aeronautics and Space Administration Sanford Davis and Bodapati Satyanarayana Feb 1978 24 p Ames Research Center, Moffett Field, Calif refs EVALUATION OF THE TILT ROTOR CONCEPT: THE XV-15'S INASA-TP-1153 A-7221) Avail NTIS HCAO2/MFAO1 CSCL ROLE 01A James H Brown, Jr, H. Kipling Edenborough (Textron Bell The use of splitter plates for tv o dimensional transonic testing Helicopter. Fort Worth. Tex). and Kenneth G Wernicke In AGARD in wind tunnels was investigated on a 12% biconvex airfoil section Rotorcraft Design Jan 1978 9 p Prepared in cooperation over the Mach number range 06 to 1.0 Measured pressure with Army Air Mobility Res and Develop. Lab, Moffett Field. distributions were compared to transonic theory and to other Calif (For availability see N78-19126 10-05) experiments, including an investigation in the same facilitv without Avail NTIS HCA15/MFAO1 CSCL01C splitter plates The results of the experiment show the best agreement with theory ower the entire transonic Mach number The need for an aircraft combining the efficient vertical takeoff range Author and landing capability of a helicopter with the efficient high speed characteristics of a fixed wing turboprop is examined The ability of the tilt rotor concept to fill this requirement and examples as to its potential usefulness in both military and civil missions are discussed Author N78-18380*S National Aeronautics and Space Administration Ames Research Center, Moffett Field. Calif PHENOMENOLOGICAL ASPECTS OF QUASI-STATIONARY CONTROLLED AND UNCONTROLLED THREE- DIMENSIONAL FLOW SEPARATIONS - N78-19786* National Aeronautics and Space Administration- David J. Peake In AGARD Three Dimensional and Unsteady Ames Research Center. Moffett Field. Calif Separation at High Reynolds Numbers Feb 1978 52 p refs FUTURE REQUIREMENTS AND ROLES OF COMPUTERS (For availability see N78-18375 09-34) IN AERODYNAMICS c6O Avail. NTIS HC Al1/MF A01 CSCL 20D Thomas J Gregory In Its Future Computer Requirements for Interest in three dimensional flow separation is linked closely Computational Aerodynamics Feb 1978 p 102-107 (For - with wings of high leading edge sweep and bodies of fineness availability see N78-19778 10-59) ratio operating at large angles of incidence or yaw, that are Avail NTIS HC A22/MF A01 CSCL 098 typical of many high-speed aircraft and missile layouts The While faster computers will be needed to make solution of quasi-steady three dimepsional separated flows about practical the Navier-Stokes equations practical and useful, most all of
4 the other aerodynamic solution techniques can benefit fr6m faster model is treated in the static stability analysis for the flight computers There is a wide variety of computational and conditions of Mach number 09 for rectilinear flight (1 g) and measurement techniques, the prospect of more powerful for a pull-up maneuver (25 g) at an altitude of 1524 km. computers permits extension and an enhancement across all Static stability parameters and structural deformations of the aerodynamic methods, including wind-tunnel measurement. It is Orbiter am calculated at trim conditions for the dynamic stability expected that, as in the past, a blend of methods will be usdd analysis, and the characteristics of damping in pitch are to predict aircraft aerodynamics in the future. These will include investigated for aMach number range of 03 to 1 2. The calculated methods based on solution of the Navier-Stokes equations and results for both the static and dynamic stabilities are compared the potential flow equations as well as those based on empincal with the-available experimental data Author and measured results. The primary flows of interest in aircraft aerodynamics are identified, the predictive methods currently in -use and/or under development are reviewed and two of these methods are analyzed in terms of the computational resources needed to improve their usefulness and practicality. Author 1l78-20917-# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif. COMPARISON OF MEASURED AND CALCULATED HEUCOPTER ROTOR IMPULSIVE NOISE N78-19794# National Aeronautics and Space Administration. Wayne Johnson and Albert Lee (Beam Eng. Inc) Mar 1978 Ames Research Center. Moffett Field. Calif. 29 p refs VISCOUS FLOWS (Contract NAS2-9399) COMPUTING A01 J. D. Murphy In its Future Computer Requirements for (NASA-TM-78473; A-7355) Avail NTIS HC A03/MF Computational Aerodynamics Feb. 1978 p 209-220 refs (For CSCL 20A availability see N78-19778 10-59) The thickness noise theory is discussed Two tull-scale rotors NTIS HC A22/MF A01 CSCL 20D were tested in a wind tunnel with several tips involving changes Av'ail in chord, thickness, and sweep Impulsive noise data reduction Although the goals and techniques of computational aerody- procedures used are descnbed The calculated and measured namics and computational fluid dynamics differ, advancement in impulsive noise peak pressures as a function of advancing tip Ite physical and mathematical aspects of the latter are required Mach number are compared, showing good correlation for all for progress in aerodynamic computation. The most attractive rotors considered Author approach is the use of hybrid methods where both the equations treated and the solution algonthms reflect the local character of the flow. A working general turbulence model that is only peripherally related to the availability of large fast computers would provide a significant breakthrough in computational N78-21094# National Aeronautics and Space Administration aerodynamics. There is no unanimity of opinion as to what may Ames Research Center, Moffett Field, Calif be the optimum algorithm or family of algorithms in the next EFFECT OF HIGH LIFT FLAP SYSTEMS ON THE CONCEP- decade. While it is premature to develop an optimum processor, TUAL DESIGN OF A 1986 SHORT-HAUL COMMERCIAL such a machine dedicated to study the structure of solutions to STOL TILT ROTOR TRANSPORT the three-dimensional time-dependent Navier-Stokes equations Michael D Shovlin and Bruno J Gambucci Apr. 1978 29 p and to the computability of turbulence would be very valuable refs A.R H. (NASA-TM-78474; A-7364) Avail: NTIS HC AO3/MF A01 CSCL 01C The performances of a derivative concept of a 1985 STOL tilt rotor transport, and of a second concept having a complex mechanical flap system similar to a short field 8737 aircraft N78-20113*4 National Aeronautics and Space Administration were compared for a 370 kilometer (200 nautical mile) shoit Ames Research Center. Moffetn Field, Calif haul mission The flap system of the latter allowed lift to be A SIMPLE METHOD FOR ESTIMATING MINIMUM AUTO- shifted from the rotor system to the wing, permitting a 26 percent ROTATIVE DESCENT RATE OF SINGLE ROTOR HEUCOP- reduction in dynamic component weight, while also permitting -TENS the use of a smaller wing The wing and disc loading of this Peter D. Talbot and Laurel G Schroers (Army R & T Labs, concept were 5746 (120 psi) and 1915 (40 psf) newtons per Moffett Field. Calif.) Mar. 1978 17 p refs square meter. respectively, while the wing and disc loading of (NASA-TM-78452. A-7134) Avail NTIS HC A02/MF A01 the derivative concept were 4788 (100 psf) and 1197 (25 CSCL 01C psf) newtons per square meter. respectively The high-lift wing Flight test results of minimum autorotative descent rate are tilt rotor showed slightly improved fuel usage over its entire compared with calculations based on the minimum power required operating range and about 6 to 8 percent improvement in direct for steady level flight. Empirical correction factors are derived openinng costs, resulting from its improved cruise efficiency and that account for differences in energy dissipation between these redu-ed weight. Other advantages include improved reliability two flight conditions. A method is also presented for estimating with c,%entially reduced maintenarnce and bette' riding quality the minimum power coefficient for level flight for any helicopter Altho, for use in the empincal estimation procedure of autorotative descent rate Author
N78-21159-# National Aeronautics and Space Administration Ames Research Center, Moffett Field. Calif SAHiT N78-20176# National Aeronautics and Space Administration A N e C CONTROL BY Ames Research Center. Moffett Field, Calif STATIC AND DYNAMIC STABIUTY ANALYSIS OF THE OSCILLATION SPACE SHUTTLE VEHICLE-ORBITER James C Biggers and John L McCloud. III Apr 1978 11 p Wei J. Chyu. Ralph K. Cavin (Texas A and M Univ. College refs ADl Station), and Larry L Erickson Mar 1978 62 p refs (NASA-TM-78475: A-7367) Avail NTIS HC A02/MF (NASA-TP-1179; A-7217) Avail NTIS HCAO4/MF A0l CSCL CSCL 0IC 228 It was shown that for two, three, or four bladed rotors, The longitudinal static and dynamic stability of a Space Shuttle simple oscillation of the nonrotating swashplate controls can Vehicle-Orbier (SSV Orbiter) model is analyzed using the produce prescribed blade pitch schedules of the sort which were Nonlinear effects are accoud suggested for vibration alleviation. Equations were given which ForbyFLEXSTAB applicatiooft computer aporrectiontehniqueprogram. inethae a unted relate the swashplate for by application of a correction technique in the FLEXSTAB schedules motions to the resulting blade Authorpitch system: the technique incorporates experimental force and pressure data into the linear aerodynamic theory, A flexible Orbiter
5 N78-22025*# National Aeronautics and Space Administration ' N78-23100"# National Aeronautics and Space Administration Ames Research Center, Moffett Field, Calif Ames Research Center, Moffett Field Calif LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A OPTIMALGUIDANCE AND CONTROL FOR INVESTIGATING 0.00-SCALE YF-17 AIRPLANE MODEL AT HIGH ANGLES AIRCRAFT NOISE-IMPACT REDUCTION OF ATTACK AND SIDESLIP Elwood C Stewart and Thomas M_ Carson May 1978 58 p Daniel N Petroff. Stanley H Scher. and Carl E Sutton (ARO. refs Inc. Moffett Field. Calif) Apr 1978 118 p refs (NASA-TP-1237. A-7121) Avail NTIS HCA04/MF A01 CSCL (NASA-TM-78438. A-7214) Avail NTIS HC A06/MF A01 01C CSCL 01A A methodology for investigating-the-reduction-of-community Data were obtained-with and without the nose boom and noise impact is reported This report is concerned with the with several strake configurations: also. data were obtained for development of two models to provide data a guidance generator various control surface deflections Analysts of the results revealed and an aircraft control generator suitable for various current and that selected strake configurations adequately provided low advanced types of aircraft The guidance generator produces the Reynolds number simulation of the high Reynolds number commanded path information from inputs chosen by an opera characteristics The addition of the boom in general tended to tor from a graphic scope display of a land-use map of the reduce the Reynolds number effects Author terminal area The guidance generator also produces smoothing at the junctions of straight-line paths The aircraft control generator determines the optimal set of the available controls such that the aircraft will follow the commanded path The solutions for the control functions are given and shown to be dependent on N78-22754# Massachusetts Inst of Tech . Cambridge Elec- the class of aircraft to be considered, that is. whether the thrust tronic Systems Lab vector is rotatable and whether the thrust vector affects the GENERAUZATION OF HUFFMAN CODING TO MINIMIZE aerodynamic forces For the class of aircraft possessing a rotatable THE PROBABILITY OF BUFFER OVERFLOW thrust vector, the solution is redundant, this redundancy is removed Pierre A Humblet Feb 1978 12 p refs Presented at the by the additional condition that the noise inpact be minimized 1977 Intern. Symp. on Inform. Theory, Ithaca, N. Y Information from both thd guidance generator and the aircraft (Contract N00014-75-C-1183) control generator is used by the footprint program to construct (AD-A050974, ESL-P-800) Avail. NTIS HC A02/MF AOl the noise footprint Author CSCL 09/2 An algorithm is given to find a prefix condition code that minimizes the value of the moment generating function of its codeword length distribution for a given positive argument This N78-26133*# National Aeronautics and SpaLe Administration algorithm is used inan iterative way to yield a code that maximizes Ames Research Center. Moffett Field. Calif- the rate of decay of the probability of buffer length increases TRAJECTORY MODULE OF THE NASA AMES RESEARCH Author (GRAI CENTER AIRCRAFT SYNTHESIS PROGRAM ACSYNT Michael E_Tauber and John A Paterson Jul 1978 73 p refs N78-23016*# National Aeronautics and Space Administration (NASA-TM-78497. A-7480) Avad- NTIS HC A04/MF A01 Ames Research Center, Moffett Field. Calif CSCL 01C OPTIMUM HORIZONTAL GUIDANCE TECHNIQUES FOR A program was developed to calculate trajectories for both AIRCRAFT military and commercial aircraft for use in the aircraft synthesis Heinz Erzberger and Homer 0. Lee In NASA. Washington Fourth program. ACSYNT The function of the trajectory module was Inter-Center Control Systems Conf Jan 1978 p 175-184 to calculate the changes in the vehicle's flight conditions and refs (For availability see N78-23010 13-99) weight, as fuel is consumed, during the flying of one or more Avail NTIS HC A22/MF A01 CSCL 17G missions- The trajectory calculations started with a takeoff. Some problems of automatic guidance of an aircraft in the followed by up to 12 phases chosen from among the following horizontal plane are described The horizontal guidance tasks, climb, cruise, acceleration, combat, loiter, descent, and paths In which such a flight control system should be capable of performing addition, a balanced field length was computed The emphasis were identified as being of three types guiding the aircraft from was on relatively simple formulations and analytic expressions any initial location and initial heading to (1) any final location suitable for rapid computation since a prescnbed trajectory had and heading. (2) intercept and fly along a line of specified direction, to be calculated many times in the process of converging an and (3) a final location with arbitrary final heading Guidance aircraft design, or finding an optimum configuration The trajectory problems such as capturing an ILS beam at a specified point module consists of about 2500 cards and operational on a on the beam, intercepting a VOR radial, and point-to-point- CDC 7600 computer G G_ navigation can be formulated in terms of these problems The guidance laws minimize the arc distance to fly between initial and final conditions subject to constraints on the minimum turning radius Author N78-26151*# National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif A FLIGHT INVESTIGATION OF THE STABILITY, CONTROL AND HANDLING QUALITIES OF AN AUGMENTED JET N78-23021'# National Aeronautics and Space Administration FLAP STOL AIRPLANE Ames Research Center. Moffett Field Calif. Richard F. Vomaske. Robert C. Innis, Brian E Swan (Canadian QUASI-OPTIMAL CONTROL OF A MOVING-BASE SIMULA- Armed Forces, Ottawa). and Seth W Grossmith (Canadian Dept TOR cO9 of Transport. Ottawa) Jun 1978 147 p refs Elwood C Stewart In NASA. Washington Fourth Inter-Center (NASA-TP-1254, A-7246) Avail NTIS HCA07/MFA01 CSCL Control Systems Conf Jan 1978 p 253-259 refs (For availability 01C see N78-23010 13-99) The stability, control. and handling qualities of an augmented Aval NTIS HC A22/MF A01 CSCL 14B jet flap STOL airplane are presented. The airplane is an extensively The optimal control of a degree-of-freedom moving-base modified de Havilland Buffalo military transport The modified simulator is considered The quasi-optimal control method due airplane has two fan-jet engines which provide vectorable thrust to Friedland was utilized The problem, in broad terms, was to and compressed air for the augmentor jet flap and Boundary- determine a control law for moving the simulator cab so that Layer Control (BLC). The augmentor and BLC air is cross ducted its motion would- (1) best approximate the desired aircraft to minimize asymmetric moments produced when one engine is response, and (2) not exceed the limited translational capability inoperative The modifications incorporated in the airplane include of the simulator A variety of optimal responses were obtained a Stability Augmentation System (SAS). a powered elevator, and by the method which emphasized different features of the response a powered lateral control system. The test gross weight of the which were thought to be important in motion perception airplane was between 165,000 and 209.000 N (37.000 and Examples of such results are given, and the considerations 47.000 lb) Stability. contro, and handling qualities are presented important in initial subjective evaluations by experienced flight for the airspeed range of 40 to 180 knots The lateral-dirbctional personnel are discussed Author handling qualities are conside~ed satisfactory for the normal
6 operating range of 65" to 160 knots airspeed when the SAS is shocked flows observed experimentally were reproduced compu functioning With the SAS inoperative. poor turn coordination tationally The ability to identify the effects of design modifications and spiral instability are primary deficiencies contributing to was demonstrated both in terms of pressure distributions and marginal handling qualities in the landing approach The powered shock drag characteristics G G. elevator control system enhanced the controllability in pitch. particularly in the landing flare and stall recovery Author
N78-28278# Army Natick Research and Development Command Mass N78-26741* National Aeronautics and Space Administration ACCORDION SHELTER HARDWARE ANALYSIS Ames Research Center. Moffett Field. Calif Final Report, Feb. 1976 - Aug. 1977 G-SEAT SYSTEM STEP INPUT AND SINUSOIDAL RE- Predrag Shopalovich and Franklin Barca Feb 1978 37 p refs SPONSE CHARACTERISTICS IDA Prol 1L7-62723-A-42701) Thomas W Showalter and Robert J. Miller Jun 1978 11 p AD-AO53592. NATICK/TR-78/01 1) Avail NTIS (NASA-TM-78478: A-7393) Avail NTIS HC A02/MF AO1 H / CSCL 13/13 CSCL 05H This report presents the results of an investigation into some The step input and smusoidal response characteristics of a of the hardware difficulties experienced with the accordion shelter Pneumatcally driven computer controllod G set are examined in during field tests The accordion shelter is a prototype rigid this study The response data show that this system c wall. general purpose, expandable military shelter In the closed, thisled afistudyTheressea swthat t syteme can be transportation configuration the shelter serves as its own shipping modeled as a 0 53 .see timea first constant order system with an 0.08 sec time lagAuthor andcotiean container and conformscnfrsoth to the dimensionaldmninlaidtegh and strength requirements of the International Organization for Standardization Type IC freight container In the habitation mode the container expands from both sides to form an enclosed, environmentally N78-27043*# National Aeronautics and Space Administration controlled, lighted shelter approximately 24 metres high by Ames Research Cenier, Moffett Field Calf. 24 matres wide by 15 2 metres long The main problem areas APPLICATION OF A COST/PERFORMANCE MEASURE- are identified as container jacks, floor lacks, leveling system MENT SYSTEM ON A RESEARCH AIRCRAFT PROJECT and expansion system The specific causes of the problems are James J Diehl Jun. 1978 24 p refs identified and solutions to the problems are proposed (NASA-TM-78498. A-7488) Avail NTIS HC A02/IF A01 Author (GRA) CSCL OBA The fundamentals of the cost/performance management system used in the procurement of two tilt rotor aircraft for a joint NASA/Army research project are discussed The contractor's N78-28402"# National Aeronautics and Space Administration reporting system and the GPO's analyses are examined The Ames Research Center Moffett Fled. Calif use of this type of reporting system is assessed Recommendation- PHENOMENOLOGICAL ASPECTS OF QUASI-STATIONARY concerning the use of like systems on future projects are CONTROLLED AND UNCONTROLLED THREE- included AR H DIMENSIONAL FLOW SEPARATIONS David J Peake In AGARD Three Dimensional and Unsteady Separation at High Reynolds No. Feb 1978 52 p refs (For F document see N7S-28397 19-34) N7e27113 # National Aeronautics and Space Administration Availpnmary NTIS HC Al1/MF A01 CSCL 20D Ames Research Center. Moffett Field. CalIf Quasi-steady three dimensional separated flows about bodies APPLICATION OF SPECIAL-PURPOSE DIGITAL COMPUT of large fineness ratio operating at large angles of incidence or ERS TO ROTORCRAFT REAL-TIME SIMULATION yaw are discussed The general character of the three dimensional o rain Mackie and Seth tMichelson (Computer Se Corp attached boundary layer, the concept of limiting streamlines, and, Mountain View, Cahif) Jul 1978 37 p refs the physics of three dimensional separation and reattachment (NASA-TP-1267. A-7343) Avail NTIS HC AOS/MF A0l CSC are among the factors considered Specific examples are given 010 •The advantages of swept, sharp edges that generate controlled The use of an array processor as a computational eleme (or fixed) three dimensional flow separations on a vehicle, due in rotorcraft real-time simulation is studied A multilooping schen.e to the qualitatively unchanging flow field developed throughout was considered in which the rotor would loop over its calculatioi. the range of flight conditions, are emphasized J i S a number of time while the remainder of the model cycled once on a host computer To prove that such a method would realistically simulate rotorcraft. a FORTRAN program was constructed 1o emulate a typical host-array processor computing configuration The multilooping of an expanded rotor model. which N78-2906D# National Aeronautics and Space Administration. included appropriate kinematic equations, resulted in an accurate Ames Research Center. Moffett Field, Calif and stable simulation GG A METHOD FOR THE ANALYSIS OF THE BENEFITS AND COSTS FOR AERONAUTICAL RESEARCH AND TECHNOL- OGY c85 - Louis J Williams Herbert H Hoy, and Joseph L Anderson In NASA Langley Res Center CTOL Transport Technol. 1978 N78-28053*# National Aeronautics and Space Admintstratior 1978 p 871-894 refs (For primati document see N78-29046 Ames Research Center. Moffett Field. Calif 20-01) WING ANALYSIS USING A TRANSONIC POTENTIAL FLOW Avail NTIS HC A18/MF A01 CSCL OSA COMPUTATIONAL METHOD A relatively simple. consistent, and reasonable methodology P A Henne (McDonnell Douglas Corp, Long Beach. Calif) and for performing cost-benefit analyses which can be used to guide R M Hicks Jui 1978 60 p refs justify and explain investments in aeronautical research and (NASA-TM-78464" A-7308) Avail NTIS HC A04/MF A01 technology is presented The elements of this methodology (labeled CSCL 0A ABC-ART for the Analysis of the Benefits and Costs of Aeronautical The ability of the method to compute wing transonic Research and Technology) include estimation of aircraft mar performance was determined by comparing computed results with kets. manufacturer costs and return on investment versus aircraft both experimental data and results computed by other theoretical price, airline costs and return on investment versus aircraft price procedures. Both pressure distributions and aerodynamic forces and passenger yield, and potential system benefits--fuel savings. were evaluated Comparisons indicated that the method is a cost savings, and noise reduction The application of this significant improvement in transonic wing analysis capability. In methodology is explained using the introduction of an advanced particular, the computational method generally calculated the turboprop powered transport aircraft in the medium range market correct development of three-dimensional pressure distributions in 1978 as an example J M S from subcritical to transonic conditions Complicated, multiple
7 N7-29061f# National Aeronautics and Space Administration obtained These resultsdemonstratethepowerofthecomputation- Ames Research Center Moffett Field. Calif. al method to predict optimum inlet location, orientation, and SHORT-HAUL CTOL AIRCRAFT RESEARCH c05 centerbody control schedule for design and off design performance. Louis J Williams In NASA Langley Res. Center CTOL Transport The effects of inlet location and a forward canard on the Technol. 1978 1978 p 891-908 refs (For primary document angle of-attaer nerformance of a normal shock inlet at transonic see N78-29046 20-01) speeds were studied. The data show that proper integration of Avail NTIS HC-A18/MF AOl CSCL 0IC inlet location and a forward canard can enhance ,the angle-of- The results of the reduced energy for commercial air attack performance of a normal shock inlet. Two lower lip transportation studies on air transportation energy, efficiency treatments- for *mproving the angle-of-attack performance of improverht alternatives are reviewed along with subsequent rectangular inlets at transonic speedsare discussed Author design studies of advanced turboprop powered transport aircraft The application of this research to short-haul transportation is discussed The results of several recent turboprop aircraft design are included The potential fuel savings and cost saVings for N7B-32045*# National Aeronautics and Space Administration advanced turboprop aircraft appear substantial, particularly at Ames Research Center. Moffett Field Calif.' shorter ranges J M S SYMMETRICAL AND ASYMMETRICAL SEPARATIONS ABOUT A YAWED CONE David J. Peake. F Kevin Owen (Owen Intern . Inc. Palo Alto, N7S-29068*# National Aeroitautics and Space Adnimstration 3oCalf). p refsand SponsoredHiroshi Higuchi in part(Dyn by AFAL-Technol, IncI Sep 1978 Ames Research Center. Moffett Field. Calif 30ontrefs S 2-9 i a3) CLOSED-FORM EQUATIONSCLOSD-FOM EUATINSFOROR THETE LIFT,LIT, DRAG.RAGAND(NASA-TM-78532.AND (Contract NAS2-9663)A-7639) Avail. NTIS HC A03//MF A01 PITCHING-MOMENT COEFFICIENTS OF AIRFOIL SEC- CSCL 0A TIONS IN SUBSONIC FLOW Three dimensional flow separations about a circular cone Roger L Smith Aug 1978 58 p rots Prepared in cooperation were investigated in the Mach number range 06 - 1 8. The with the US Army Aviation Research and Development Command, cone was tested in the Ames 1 8 by 1 8 m wind tunnel at St Louis. Mo Reynolds numbers based on the cone length from 4.500.000 to (NASA-TM-78492. AVRADCOM-TR-78-l5(AM) A-7464) Avail: 13.500.000 under nominally zero heat transfer conditions Results NTIS HC A04/MF A01 CSCL 01A indicate that (1) the lee-side separated flow develops from initially Closed-form equations for the lift. drag. and pitching moment symmetrically disposed and near-conical separation lines at angle coefficients of two dimensional airfoil sections in steady subsonic of incidence/cone semiangle equal to approximately 1. with the flow were obtained from published theoretical and experimental free shear layers eventually rolling up into tightly coiled vortices results A turbulent boundary layer was assumed to exist on at all Mach numbers. (2) the onset of asymmetry of the lee-side the airfoil surfaces The effects of section angle of attack. Mach separated flow about the mean pitch plane is sensitive to Mach number. Reynolds number, and the specific airfoil type were number. Reynolds number, and the nose bluntness: and (3) as considered The equations were applicable through an angle of the Mach number is increased beyond 1 8. the critical angle of attack range of -180 deg to I 180 deg. however, above about incidence for the onset of asymmetry increases until at abdut L or - 20 deg, the section characteristics were assumed to be M = 2 75 there is no longer any significant side force develop functions only of angle of attack A computel program is presented ment JMS which evaluates the equations for a range of Mach numbers F and angles of attack Calculated results for the NACA 23012 airfoil section were compared with experimental data JAM N78-32835"# National Aeronautics and Space Administration Ames Research Center, Moffett Field Calif A STUDY OF THE NOISE RADIATION FROM FOUR ROTOR BLADES N78-31739*# National Aeronautics and Space Administration HEUCOPTER Ames Research Center. Moffett Field. Calif Albert Lee (Beam Eng. Inc) and Marianne Mosher In NASA 3 8 A PILOT EVALUATION OF TWO G-SEAT CUEING Langley Res Center Helicopter Acoustics Aug 1978 p 7 - 4 0 2 SCHEMES refs (For primary document see N78-32816 23-71) Thomas W Showalter Aug 1978 34 p refs Avail NTIS HC A17/MF A01 CSCL 20A (NASA-TP-1255. A-7390) Avail NTIS HC A03/MF A0l CSCL Acoustic measurements were taken of a modern helicopter 05H rotor with four blade tip shapes in the NASA Ames 40-by-SO-Foot A comparison was made of two contrasting G-seat cueing Wind Tunnel The four tip shapes are rectangular, swept. schemes The G-seat, an aircraft simulation subsystem, creates trapezoidal, and swept tapered in platform. Acoustic effects due aircraft acceleration cues via seat contour changes Of the two to tip shape changes were studied based on the dSA level. cueing schemes tested. one was designed to create skin pressure peak noise pressure and subjective rating The swept tapered cues and the other was designed to create body position cues. blade was found to be the quietest' above an advancing tip Each cueing scheme was tested and evaluated subjectively by Mach number of about 09. and the swept blade was the quietest five pilots regarding its ability to cue the appropriate accelerations at low speed The measured high speed impulsive noise was in each of four simple maneuvers: a pullout, a pushover, an compared with theoretical predictions based on thickness effects S-turn maneuver, and a thrusting maneuver. A divergence of good agreement was found J M S pilot opinion occurred, revealing that the perception and acceptance of G-seat stimuli is a highly individualistic phenomena The creation of one acceptable G-seat cueing scheme was, t therefore, deemed to be quite difficult L S N/e-33043 # National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif LASER-VELOCIMETER SURVEYS OF MERGING VORTICES IN A WIND TUNNEL: COMPLETE DATA AND ANALYSIS N78-32044g National Aeronautics and Space Administration Victor R Corsigha. James 0. Iversen (Iowa State Univ. Ames), Ames Research Center. Moffett Field, Calif. and Kenneth L Orloff Oct 1978 48 p refs ,HIGH ANGLE OF INCIDENCE IMPLICATIONS UPON AIR (NASA-TM-78449; A-7262) Avail: NTIS HC A03/MF A01 INTAKE DESIGN AND LOCATION FOR SUPERSONIC CSCL 01A CRUISE AIRCRAFT AND HIGHLY MANEUVERABLE The merger of two corotating vortices was studied with a TRANSONIC AIRCRAFT laser velocrmeter designed to measure the two cross-stream Leroy S Presley Sep 1978 13 p refs components of velocity Measurements were made at several (NASA-TM-78530, A-7634) Avail- NTIS HC A02/MF A01 downstream distances in the vortex wake shed by two semispan CSCL OlA wings mounted on the wind-tunnel walls The velocity data provided wall-defined contours of crossflow velocity, stream Computational results which show the effects of angle of function, and vorticity for a variety of test conditions Downstream attack on supersonic mixed compression inlet performance at of the merger point, the vorticity was found to be independent four different locations about a hypothetical forebody were of the downstream distance for radii smaller than r/b = 005
8 For larger radii, the vorticity depended on the distance from the N7S-17062*# Boeing Co. Seattle. Wash wing Upstream of the merger, a multicell vorticity pattern was LOW SPEED TEST OF A HIGH-BYPASS-RATIO PROPUL found. Author SION SYSTEM WITH AN ASYMMETRIC INLET DESIGNED FOR A TILT-NACELLE V/STOL AIRPLANE J Syberg Jan. 1978 115 p refs (Contract NAS2-9640) (NASA-CR- 152072, D-180-22888-1) Avail NTIS NASA CONTRACTOR REPORTS HC AO6/MF A01 CSCL 21E A large scale model of a lift/cruise fan inlet designed for a tilt nacelle V/STOL airplane was tested with a high bypass ratio turbofan Testing was conducted at low freestream velocities N78-137658# Stanford Univ.. Calif Joint Inst for Aeronautics with inlet angles of attack ranging from 0 deg to 120 deg, The and Acoustics operating limits for the nacelle were found to be related to inlet MULTI-CALCULATION RATE SIMULATIONS Final Report boundary layer separation Small separations originating in the J David Powell and Mahboob Akhter Nov. 1977 59 p refs inlet diffuser cause little or no performance degradation However, (Grant NsG-2250) at sufficiently severe freestream conditions the separation changes (NASA-CR-155335) Avail NTIS HC A04/MF A01 CSCL abruptly to a lip separation This change is associated with a 098 significant reduction in nacelle net thrust as well as a sharp It is common in real time simulations of large aerospace increase in fan blade vibratory stresses Consequently. the onset systems to separate the high and low frequency subsystems of lip separation is regarded as the nacelle operating limit The within the simulation and perform the integrations of the test verified that the asymmetric inlet design will provide high subsystems at different calculation rates This is done to strike performance and stable operation at the design forward speed a balance between accuracy of calculation and capacity of the and angle of attack conditions At some of these, however. digital computer Questions arising as to the accuracy of this operation near the lower end of the design inlet airflow range structure compared to single calculation rates were studied using is not feasible due to the occurrence of lip separation Author a linear aircraft model. Also investigated were interactions arising to cause errors worse than those expected Problems are specifically identified and guidelines are given for selection of sample rates for multiple rate simulations. Author N78-19094 q McD6nnell-Douglas Corp. St Louis. Mo. CONCEPTUAL DESIGN STUDY-OF A HARRIER V/STOL RESEARCH AIRCRAFT Waldemar E Bode, Roger L Berger. Glen A Elmore. and Thomas N78-14016"# Stanford Univ. Calif. Dept of Civil Engineer- R Lacey Feb. 1978 293 p ing. (Contract NAS2-9748) ASSESSING THE FUTURE OF AIR FREIGHT Final Technical (NASA-CR-152086) Avail: NTIS HC A13/MF A01 CSCL Report, Feb. - Oct. 1977 01C Janr S. Dajam Nov 1977 34 p refs MCAIR recently completed a conceptual design study to (Grant NsG-2203) define modification approaches to. and derive planning prices (NASA-CR-155356) Avail NTIS HC A03/MF A01 CSCL for the conversion of a two place Hprner to a VJSTOL control. 01C displa9 and guidance research aircraft Control concepts such as The role of air cargo in the current transportation system in* rate damping, attitude stabilization, velocity command, and cockpit the United States is explored Methods for assessing the future controllers are to be demonstrated. Display formats will also be role of this mode of transportatibn include the use of continuous- investigated, and landing, navigation and guidance systems flight time recursive systems modeling for the simulation of different tested The rear cockpit is modified such that it can be quickly components of the air freight system, as well as for the adapted to faithfully simulate the controls, displays and handling development of alternative future scenarios which may result qualities of a Type A or Type B V/STOL The safety pilot zlwa's from different policy actions A basic conceptual framework for has take command capability The modifications studied, tall into conducting such a dynamic simulation is presented within the two categories basic modifications and optional modifications context of the air freight industry Some research needs are. Technical descriptions of the basic modifications and of the identified and recommended for further research. The benefits, optional modifications are presented The modification plan and limitations, pitfalls, and problems usually associated with large schedule as well as the test plan and schedule are presented scale systems models are examined Author I The failure mode and effects analysis, aircraft performance, aircraft weight, and aircraft support are discussed Author
N78-17061*# Raman Aeronautics Research and Engineering, Inc. Palo Alto. Calif AN ANALYSIS OF THE ROTOR BLADE STRESSES OF THE N78-19481-# Mathematical Sciences Northwest Inc., Bellevue. THREE STAGE COMPRESSOR OF THE AMES RESEARCH Wash. CENTER 11- BY 11-FOOTTRANSONIC WIND TUNNEL Final STUDY, OPTIMIZATION, AND DESIGN OF A LASER HEAT Report ENGINE Final Report Jules B. Dods. Jr. Nov. 1977 147 p refs 12 Jan. 1978 160 p refs (Contract NAS2-9112) (Contact'NA92-9668) (NASA-CR-152083) Avail. NTS HC A07/MF A01 CSCL (NASA-CR-152104. MSNW-78-1082-1) Avail: NTIS 2NAE HC A08/MF AOl CSCL 20E The static and dynamic rotor blade stresses of the three Laser heat engine concepts, proposed for satellite applications. stage compressor were measured Data are presented in terms were analyzed to determine which engine concepts best meet of total blade stress for the complete operational range of the requirements of high efficiency (50 percent or better) compressor speeds and tunnel total pressures Modal frequen- continuous operation in space. The best laser heat engine for a cies and variations with tunnel conditions were measured Phase near-term experimental demonstration, selected on the basis of angles and coherences between various gage combinations are -high overall operating efficiency, high power-to-weightcharacters also presented Recommendations for improvements are given tics, and availability of the required technology, is an Otto/Diesel for future rotor blade experimental investigations. Author cycle piston engine using a diamond window to admit C02 laser radiation. The technology with the greatest promise of scaling to megawatt power levels in the long term is the energy exchanger/gas turbine combination Author
9 N7-198 8 *# Douglas Aircraft Co. Inc. Santa Monica. Calif. a sawtooth shape at high advancing tip Mach numbers Based A SOLUTION TO THE SURFACE INTERSECTION PROBLEM on the amplitude of the impulsive noise, it appears the swept Final Report tapered tip is the quietest, tapered tip the second, swept tip H G. Timer 29 Nov. 1977 50 p third and square tip the most noisy The data presented in this (Contract NAS2-9590) report should be useful as data bases for modeling and evaluating (NASA-CR-152116: MDC-J7789) Avail- NTIS haticoptse impulsive noise Author HC A03/MF A01 CSCL 12A An application-independent geometric model within a data base framework should support the-use of- Boolean operators N78:21092-# Northwestern Univ. Evanston.ill Transportation which allow the user to construct acomplex model by appropriately Center combining a series of simple models The use of these operators FACTORS AFFECTING THE RETIREMENT OF COM- leads to the concept of implicitly and explicitly defined surfaces MERCIAL TRANSPORT JET AIRCRAFT Progress Report With an explicitly defined model, the surface area may be Frank A Spencer and Joseph A Swanson 15 Feb 1978 computed by simply summing the surface areas of the bounding 209 p refs surfaces For an implicitly defined model, the surface area (Grant NsG-2149) computation must deal with active and inactive regions Because (NASA-CR-152115. P19-2) Avail: NTIS HC A1O/MF A01 CSCL the surface intersection problem involves four unknowns and its 01C solution is a space curve, the parametric coordinates of each A brief historical background of the technology and economics surface must be determined as a function of the arc length of aircraft replacement and retirement in the prejet era is presented Various subproblems involved in the general intersection problem 'to see whether useful insights can be obtained applicable to are discussed, and the mathematical basis for their solution is the jet era Significant differences between the two periods presented along with a program written in FORTRAN IV for were demonstated Current technological and operational implementation on the IBM 370 TSO system Author economic perspectives were investigated in detail Some conclusions are drawn to aircraft retirement policies Author
N78-20136"# Lockheed-California Co. Burbank ROTORCRAFT LINEAR SIMULATION MODEL VOLUME 1: N78-21095"# Lockheed-California Co, Burbank Commercial ENGINEERING DOCUMENTATION Final Report, Nov. Advanced Design Div. 1976- Jan. 1978 FUEL CONSERVATION MERITS OF ADVANCED TUR- J S. Reaser Jan 1978 185 p ref 3 Vol- BOPROP TRANSPORT AIRCRAFT Final Report, Jan. - Aug. ,(Contract NAS2-9374) 1977 (NASA-CR-152079-VoI-1: LR-28200-VoI-1) Avail NTIS J D Revell and R H Tullis Aug 1977 154 p refs HC A09/MF A01 CSCL 01C (Contract NAS2-8612) A rotorcraft small perturbation linear model is, described (NASA-CR-152096, LR-28283) Avail NTIS Rotor flap, inplane and feathering degrees of freedom, as well HC AO8/MF A01 CSCL 01C as control and augmentation systems are defined in addition to The advantages of a propfan powered aircraft for the the classical vehicle six degrees of freedom. The primary commercial air transportation system were assessed by the application was intended to be an analytic too] to assess the , comparison with an equivalent turbofan transport Comparisons F handling qualities of a dynamically combined main rotor and were accomplished on the basis of fuel utilization and operating body The modeling method retained the higher frequency response costs, as well as aircraft weight and size Advantages of the properties which aided in evaluating control and stability propfan aircraft, concerning fuel utilization and operating costs, adgmentatron systems Author were accomplished by considering (1) incorporation of propfan performance and acoustic data. (2) revised mission profiles (longer design range and reduction in: and cruise speed), and (3)utilization N78-20137*# Lockheed-California Co. Burbank of alternate and advanced technology engines Author ROTORCRAFT UNEAR SIMULATION MODEL VOLUME 2: COMPUTER IMPLEMENTATION Final Report, Nov. 1976 - Jan. 1978 N78-21115# Rao and Associates Inc. Palo Alto. Calif J S Reaser and D H Saiki Jan 1978 77 p ref 3 Vol USE OF LEANING VANES IN A TWO STAGE FAN (Contract NAS2-9374) G.V R Rao and R V Digumarthi Nov 1975 53 p refs (NASA-CR-152079Vol-2. LR-28200-Yol-2) Avail: NTIS (Contract NAS2-8680) HC AO5/MF A01 CSCL 01C (NASA-CA-152134) Avail NTIS HC A04/MF A01 CSCL A computer program used to process the equations is presented. 21E and a full description of equation implementation is given The The use of leaning vanes for tone noise reduction was model was implemented in the IBM 360 and CDC series computer examined in terms of their application in a typical two-stage systems M V. high pressure ratio fan. In particular for stages designed with outlet guide vanes and zero swirl between stages, leaning the vanes of the first stage stator was studied, since increasing the number of vanes and the gap between stages do not provide N78-20918'# Beam Engineering, Inc. Sunnyvaie. Calif the desired advantage It was shown that noise reduction at ACOUSTICAL EFFECTS OF BLADE TIP SHAPE CHANGES higher harmonics of blade passing frequency can be obtained ON A FULL SCALE HELICOPTER ROTOR IN A WIND by leaning the vanes Autho TUNNEL Albert Lee Apr 1978 59 p refs (Contract NAS2-9399) (NASA-CR-1520B2) Avail NTIS HC A04/MF AOl CSCL N78-21161V# Princeton Univ. N J Instrumentation and 20A Control Lab Four tip shapes were tested They were rectangular, swept. OPTIMAL CONTROL THEORY (OWEM) APPLIED TO A tapered, and swept-tapered The measured data covered a wide HELICOPTER IN THE HOVER AND APPROACH PHASE range of operating conditions The range of advancing tip Mach Gerard J Born and Tadao Kai Jan 1975 289 p refs 'numbers were between 072 to 096, and the advance ratios (Contract NAS2-7187) were from 02 to 0.375 At low and moderate advancing tip (NASA-CR-152135; Rept-1205) Avail NTIS Mach number, the data in the dbA scale appear to indicate the HC A13/MF A01 CSCL 01C swept tip is the quietest, swept tapered the second, tapered A major difficulty in the practical application of linear third and rectangular the most noisy Above an advancing tip quadratic regulator theory is how to choose the weighting matrices Mach number of about 0 89. a distinct acoustical pulse can be in quadratic cost functions The control system design with optimal Observed. which dominates the acoustical waveform The pulse weighting matrices was applied to a helicopter in the hover and shape is symmetric at moderate tip Mach number, changing to approach phase The weighting matrices were calculated to
10 extremize the closed loop total system damping subject to airplane is structures Also, preliminary investigation of advanced constraints on the determinants The extremization is really a aerodynamics flight controls, ride control and gust load allevia minimization of the effects of disturbances, and interpreted as a tion systems, aircraft systems and turbo-prop propulsion systems compromise between the generalized system accuracy and the was performed. The most beneficial advanced technology generalized system response speed The trade-off between the examined was bonded aluminum primary structure The use of accuracy and the response speed is adjusted by a single parameter, this structure in large wing panels and body sections resulted in the ratio of determinants By this approach an objective measure a greatly reduced number of parts and fasteners and therefore, can be obtained for the design of a control system The measure labor hours The resultant cost of assembled airplane structure is to be determined by the system requirements Author was reduced by 40% and the total airplane manufacturing cost by 16% - a major cost reduction With further development, test verification and optimization appreciable weight saving is also achievable Other advanced technology items which showed N78-2144*# Harvey Mudd Colt. Claremont, Calif Engineering significant gains are as follows. (1) advanced turboprop-reduced Clinic block fuel by 1530% depending on range, (2) configuration GENERATION OF A MONODISPERSED AEROSOL revisions (vee-tail)-empennage cost reduction of 25%: Final Report (3) leading-edge flap addition-weight reduction of Helma Schenck Miles Mikasa, and Ralph DeVicars Jun 1974 2500 pounds Author 61 p refs (Contract NAS2-8143) (NASA-CR-152133) Avail NTIS HC A04/MF AOl CSCL 20E N79-22100# Rockwell International Corp. Columbus, Ohio The identity and laboratory test methods for the generatior Aircraft Div. of a monodispersed aerosol are reported on. and are subjected STATIC TESTS OF A LARGE SCALE SWIVEL NOZZLE to the following constraints and parameters. (1) size distribution, THRUST DEFLECTOR (2) specific gravity; (3) scattering properties. (4) costs, John F Federspiel Feb 1978 44 p refs (5) production The procedure called for the collection of (Contract NAS2-9176) information from the literature, commercial available products. (NASA-CR-152091, NR78H-10) Avail NTIS and experts working in the field The following topics were HC A03/MF AOl CSCL 21E investigated (1) aerosols, (2) air pollution -- analysis. Tests were conducted on a swivel nozzle thrust deflector (3) atomizers.'(4) dispersion. (5) particles -- optics, size analysis. installed on a 91 centimeter (36 inch) low pressure ratio tip (6) smoke -- generators, density measurements: (7) sprays, turbine fan Fan power was supplied by a J-85 hot gas generator (8) wind tunnels -- visualization Author The configuration was typical of a vertical/short takeoff and landing (V/STOL) aircraft propulsion system employing lift cruise fans The performance was compared to results obtained on an 0.15 scale cold flow model Data were obtained at-an pressure N78-22071* Systems Technology. Inc.. Hawthorne. Calif ratios from I I to 1 2 and at nozzle deflections from cruise DEVELOPMENT OF AUTOMATIC AND MANUAL FLIGHT (0 deg) to VTOL (90 deg) The nozzle thrust performance was DIRECTOR LANDING SYSTEMS FOR THE XV-15 TILT in good agreement with small scale VTOL thrust coefficients. ROTOR AIRCRAFT IN HEUCOPTER MODE Configurations with increased nozzle area showed lower perform L G. Hofmann. Roger Hoh. H. Wayne F.Jewell, Gary L Taper. ance Fan operation was routine and nozzle rotation caused no and Pradip D Patel Jan 1978 254 p refs circumferential distortions of the fan exit flow. Nozzle flow F (Contract NAS2-9392) characteristics did not repeat small scale model results Measured (NASA-CR-152040. TR-1092-1) Avail: NTIS flow coefficients were smaller on the large scale test It was HC A12/MF AOl CSCL OlE concluded that lack of simulation of pressure and temperature The objective of this effort is to determine IFR approach profiles of the tip driven fan was the most probable cause of path and touchdown dispersions for manual and automatic XV- 15 the discrepancy Author tilt rotor landings, and to develop missed approach criteria Only helicopter mode XV-15 operation is considered The analysis and design sections develop the automatic and flight director guidance equations for decelerating curved and straight-in. N78-25057ff Nielsen Engineering and Research, Inc, Mountain approaches into a typical VTOL landing site equipped with an View, Calif MLS navigation aid These system designs satisfy all known HIGH ANGLE CANARD MISSILE TEST IN THE AMES pilot-centered, guidance and control requirements for this flying 11-FOOT TRANSONIC WIND TUNNEL task Performance data. obtained from nonstationary covariance Richard G Schwind Jun 1978 81 p refs propagation dispersion analysis for the system. are used to develop (Contract NAS2-921 1) the approach monitoring criteria The autoland and flight director (NASA-CR-2993. NEAR-TR-134) Avail NTIS guidance equations are programmed for the VSTOLAND 1819B HC A05/MF AO1 CSCL 01A digital computer The system design dispersion data developed Four blunted ogive-cylinder missile models with a length-to through analysis and the 1819B digital computer program are diameter ratio of 10 4 were tested at transonic speeds and large verified and refined using the fixed-base, man-in-the-loop XV-15 angles of attack The configurations are body, body with tail VSTOLAND simulation Author panels. body with canards. and body with canards and tails Forces and moments from the entire model and each of the eight fins were measured over the pitch range of 20 deg to 50 deg and 0 deg to 45 deg roll Canard deflection angles N78-22074=# Boeing Commercial Airplane Co. Seattle. Wash between 0 deg and 15 deg were tested Exploratory vapor screen Preliminary Design Dept. flow visualization testing was also performed Sample force and APPLICATION OF ADVANCED TECHNOLOGIES TO SMALL moment data are reported along with observations from the SHORT-HAUL AIRCRAFT Final Report vapor screen tests Author D G Andrews. P W. Brubaker. S L Bryant. C W. Clay. B. Girdharadas. M_ Hamamoto. T J Kelly. D K Proctor. C F Myron. and R L Sullivan 1 Mar 1978 332 p refs (Contract NAS2-9506) N78-25078"# Kansas Uni Center for Research Inc, Lawrence (NASA-CR-152089. D6-46320) Avail. NTIS A STUDY OF COMMUTER AIRPLANE DESIGN OPTIMIZA- HC A15/MF A01 CSCL 01C TION Status Report The results of a preliminary design study which investigates Bob Van Keppel. Han Eysink. Jim Hammer. Kevin Hawley. Paul the use of selected advanced technologies to achieve low cost Meredith and J. Roskaam 12 May 1978 457 p refs design for small (5i0-pas~enger). short haul (50 to 1000 mile) (Grant NsG-2145) transports are reported The largest single item in the cost of (NASA-CR-157210. KU-FRL-313-5: SR-4) Avail. NTIS manufacturing an airplane of this type is labor. A careful HC A20/MF AOl CSCL 01C examination of advanced technology to airframe structure was The usability of the general aviation synthesis program (GASP) performed since one of the most labor-intensive pans of the was enhanced by the development of separate computer
11 subroutines which can be added as a package to this assembly N7-26153# Iowa State Univ of Science and Technolog/. of computerized design methods or used as a separate subrou- Ames Dept of Mechanical Engineering tine program to compute the dynamic longitudinal, lateral- A STUDY OF TEST SECTION CONFIGURATION FOR SHOCK directional stability characteristics for a given airplane Currently TUBE TESTING OF TRANSONIC AIRFOILS Final Report available analysis methods were evaluated to ascertain those William J Cook Jun 1978 70 p refs most appropriate for the design functions which the GASP ,-,rant NsG-2152: ISU Proj 1233) computerized design program perfornis Methods for providing .iASA-CR-157237. ISU-ERI-Ames-78336) Avail: NTIS proper constraint and/or analysis functions for GASP were HC A04/MF A01 CSCL 148 developed as well as the appropriatp subroutines A-R-H. Two methods are investigated for alleviating wall interfor etce effects in a shock tube test section intended for testinp two-dimensional transonic airfoils The first method involves N78-25359*# Aeronautical Research Associates of Princeton, contouring the test section walls to match approximate streamlines Inc. N J in the flow. Contours are matched to each airfoil tested to produce APPlICATION OF SECOND-ORDER TURBULENT MODEL- esults close to those obtained in a conventional wind tunnel. ING TO THE PREDICTION OF RADIATED AERODYNAMIC Data from a previous study and the present study for two different SOUND airfoils demonstrate that useful results are obtained in a shock Alan J Bilanin and Joel E. Hirsh Jun 1978 76 p refs tube using a test section with contoured walls The second method (Contract NAS2-8832) involves use of a fixed-geometry slotted-wall test section to provide (NASA-CR-2994) Avail NTIS HC A05/MF AO CSCL 20D automatic flow compensation for various airfoils. The slotted-wall The Ribner formulation of the generation of aerodynamic rest section developed exhibited the desired performance sound is coupled with predictions of second-order velocity characteristics in the approximate Mach number range 082 to correlations and integral scale to estimate the sound radiated 0 89. as evidenced by good agreement obtained between shock from several complicated let flows In particular, it is shown tube and wind tunnel results for several airfoil flows G G that the sound radiated from a cold swirling jet is greater than from its nonswirling equal thrust counterpart. The noise radiated from the flow field of a multatube suppressor was estimated N78-27087*# Boeing Commercial Airplane Co. Seattle. Wash and compared with an equal thrust diameter Gaussian jet It is A MACH LINE PANEL METHOD FOR COMPUTING THE shown that the multitube concept is indeed quieter. Author LINEARIZED SUPERSONIC FLOW OVER PLANAR WINGS F. E Ehlers and Paul E Rubber May 1978 91 p (Contract NAS2-7729) (NASA-CR-152126. D6-46373) Avail NTIS N78-26824s# Stanford Univ Calif Dept of Civil Engineer- HC A05/MF AOl CSCL 01A ing A method is described for solving the linearized supersonic INFRASTRUCTURE DYNAMICS: A SELECTED BIBLIOGRA- flow over planar wings using panels bounded by two families of PHY Mach lines Polynomial distributions of source and doublet strength Jarir S Dajani and Arturo J Bencosme Jan 1978 25 p refs lead to simple, closed form solutions forthe aerodynamic influence (Grant NsG-2203) coefficients, and a nearly triangular matrix yields rapid solutions F (NASA-CR-152162. SU-IPM-5) Avail NTIS for the singularity parameters The source method was found ir HC AO2/MF A01 CSCL 12B be agcurate and stable both for analysis and design boundary The term infrastructure is used to denote the set of life conditions Similar results were obtained with the duiblel nil.h.id support and public service systems which is necessary for the [or analysis boundary conditions on the portion of the wing development of growth of human settlements Included are some downstream of the supersonic leading edge. but instabilities in basic references in the field of dynamic simulation, as well as a the solution occurred for the region containing a portion of the number of relevant applications in the area of infrastructure subsonic leading edge Research on the method was discontinued planning The intent is to enable the student or researcher to before this difficulty was resolved Author quickly identify such applications to the extent necessary for initiating further work in the field Author
N78-27094*# California Univ. Berkeley Institute of Transporta tion Studies N78-25832'# Massachusetts Inst of Tech. Cambridge Fluid AN INVESTIGATION OF SHORT HAUL AIR TRANSPORTA- Dynamics Research Lab TION IN THE SOUTHEASTERN UNITED STATES THE EFFECT OF TIP VORTEX STRUCTURE ON HELICOPTER Abib Kanafanim and Huey-Shn Yuan Jul 1977 202 p ref NOISE DUE TO BLADE/VORTEX INTERACTION (Grant NsG-2127) Thomas L Wolf and Sheila E Widnall Mar 1978 94 p refs (NASA-CR-152166. UCB-ITS-RR-77-6) Avail NTIS (Grant NsG-2142) HC A1O/MF AO CSCL 05C - '(NASA-CR-152150. MIT-78-2) Avail NTIS HC A05/MF A01 The specific objectives of this stage of the study are CSCL 20A numerous First. an attempt is made to characterize the travel A potential cause of helicopter impulsive noise, commonly patterns in the study region, both in terms of origin destination called blade slap, is the unsteady lift fluctuation on a rotor blade patterns, and connecting and through trip patterns Second. the due to interaction with the vortex trailed from another blade, structure of the air service in the region is characterized in an The relationship between vortex structure and the intensity of attempt to develop an understanding of the evolution of the the acoustic signal is investigated The analysis is based on a short haul air transportation network Finally. a look is taken at theoretical model for blade/vortex interaction. Unsteady lift on the socioeconomic environment of Atlanta and the region in the blades due to blade/vortex interaction is calculated using order to seek an explanation for the historic evolution of short linear unsteady aerodynamic theory, and expressions are derived for the directivity. frequency spectrum, and transient signal of 'the radiated noise An inviscid rollup model is used to calculate the velocity profile in the trailing vortex from the spanwise distribution of-blade tip loading A few cases of tip loading are N78-271056# Analytical Mechanics Associates. InL. Mountain investigated, and numerical results are presented for the unsteady View. Calif lift and acoustic signal due to blade/vortex interaction The DEVELOPMENTAND FLIGHTTESTS OF A KALMAN FILTER intensity of the acoustic signal is shown to be quite sensitive to FOR NAVIGATION DURING TERMINAL AREA AND changes in tip vortex structure. Author LANDING OPERATIONS Stanley F. Schmidt, Paul F. Flanagan, and John A Sorenson Jul 1978 136 p refs (Contract NAS2-8862) (NASA-CR-3015) Avail NTIS HC AO7/MF AOl CSCL 17G A Kalman filter for aircraft terminal area and landing navigation was implemented and flight tested in the NASA Ames STOLAND avionics computer onboard a Twin Otter aircraft This
12 system combines navaid measurements from TACAN. MODILS. N78-28989fl Washington Univ. Seattle Dept of Civil 3ir data. radar altimeter sensors along with measurements from Engineering .trap-down accelerometer and attitude angle sensors The flight A TECHNOLOGY ASSESSMENT OF TRANSPORTATION test results demonstrate that the Kalman filter provides improved SYSTEM INVESTMENTS estimates of the aircraft position and velocity as compared with Lonnie E Haefner 31 Mar 1978 206 p refs estimates from the more standard complementary filter The (Grant NsG-2170) onboard computer implementation requirements to achieve this (NASA-CR-152154-2) Avail NTIS HC A1O/MF A01 CSCL iiipoved prformance ore discussed Authol 05C An abstract technology assessment format, capable of generic evaluation over a heirarchy of city sizes, shapes and modal transportation technology characteristics, using unit cost and N78-27128*# Hamilton Standard. Windsor Locks. Conn impact data is presented The formal analytic model used is PROP-FAN DATA SUPPORT STUDY Final Report Markovian decision theory. The analyst is not required to know J A Baum P J Dumais. M. G Mayo. F. B. Metzger. A M or explore the historical data characteristics of the region in Shenkman. and G G Walker 28 Feb 1978 11I p depth and can, therefore, rapidly examine sensitivities and (Contract NAS2.9750) boundaries of rational or optimal transportation investments This (NASA-CR-152141) Avail NTIS HC AO6/MF AOl CSCL examination may occur ever a group of similar or different regions, 01 C and may draw significant conclusions about the mix of transporta Updated parametric prop-fan data packages are presented tion technology investments most likely needed and capable of and the rationale used in developing the new prop-fan data is compatible operation AR H detailed These data represent Hamilton Standard's projections of prop-fan characteristics for aircraft that are expected to be in-service in the 1985 to 1990 time frame. The basic prop-fan N78-30070# Aeronautical Research Foundation. Cambridge. configuration was designed for efficient cruise operation at Mass. 08 Mach number and 10.668M altitude The design blade tip REQUIREMENTS FOR REGIONAL SHORT-HAUL AIR speed is 244 trps and the design power loading is 301 KW/M SERVICE AND THE DEFINITION OF A FLIGHT PROGRAM squared GG TO DETERMINE NEIGHBORHOOD REACTIONS TO SMALL TRANSPORT AIRCRAFT Kornel Feher. Lynn Bollinger. Jeffrey V Bowles. and Mark H Waters Aug 1978 153 p refs Prepared in cooperation with N78-28083*# Gorham Associates. Thousand Oaks, Calif NASA AMES Res Center. Moffett Field. Calif STUDY TO DETERMINE OPERATIONAL AND PERFORM- (Contract NAS2-9050) ANCECRITERIAFORSTOLAIRCRAFTOPERATINGINLOW (NASA-CR*152151) Avail NTIS HC A08/MF A01 CSCL VISIBILITY CONDITIONS 05C John A Gorham May 1978 63 p refs An evaluation of the current status and future-requirements (Contract NAS2-8790) of an intraregional short haul air service is-given A brief definition (NASA-CR-152164) Avail NTIS HC A04/MF A01 CSCL of the different types of short haul air service is given This is 0iC followed by a historical review of previous attempts to develop The operational and performance criteria for civil CTOL short haul air service in high density urban areas and an passenger-carrying airplanes landing in low visibilities depend assessment of the current status The requirements for intrare- F upon the characteristics of the airplane, the nature and use of gional air service. the need for economic and environmental the ground and airborne guidance and control systems, and the viability and the need for a flight research program are defined geometry and lighting of the landing field Based upon these A detailed outline of a research program that would determine criteria. FAA advisory circulars. airplane and equipment design urban community reaction to frequent operations of small transport characteristics, and airline operational and maintenance procedures aircraft is also given Both the operation of such an experiment were formulated The documents are selected, described and in a specific region (San Francisco Bay area) and the necessary discussed in relationship to the potential low weather minima design modifications of an existing fixed wing aircraft which operation of STOL aircraft An attempt is made to identify could be used in the experiment are established An estimate is fundamental differences between CTOL and STOL aircraft nade of overall program costs GY. characteristics which could impact upon existing CTOL documenta tion Further study and/or flight experiments are recommended GY N78-33113"# General Dynamics/Fort Worth, Tex AN INVESTIGATION OF WING BUFFETING RESPONSE AT N78-28988-# Washington Univ. Seattle Dept. of Civil SUBSONIC AND TRANSONIC SPEEDS: PHASE 1: F-111A Engineering FUGHT DATA ANALYSIS. VOLUME 1: SUMMARY OF EXECUTIVE SUMMARY: BENEFIT-COST EVALUATION OF TECHNICAL APPROACH. RESULTS AND CONCLUSIONS AN INTRA-REGIONAL AIR SERVICE IN THE BAY AREA David B Benepe. Atlee M. Cunningham. Jr. and W David AND A TECHNOLOGY ASSESSMENT OF TRANSPORTA- Dunmyer 1978 188 p refs TION SYSTEM INVESTMENTS Technical Report, 1 Jan. (Contract NAS2-7091) 1977 - 31 Mar. 1978 (NASA-CR-152109) Avail NTIS HC A09/MF AOl CSCL Lonnie E Haefner 31 Mar 1978 37 p ref 0lC (Grant NsG,2170) The structural response to aerodynamic buffet during moderate (NASA-CR-152154-1) Avail- NTIS HC AO3/MF AOl CSCL to high-g maneuvers at subsonic and transonic speeds was 0C investigated The investigation is reported in three volumes This The benefits and costs that would result from an intra-regional volume presents a summary of the investigation with a complete air service operation in the San Francisco Bay area were description of the technical approach, description of the aircraft. determined by utilizing an iterative statistical decision model to its instrumentation, the data reduction procedures, results and evaluate combinations of commuter airport sites and surface conclusion GY transportation facilities in conjunction with service by a given commuter aircraft type in light of area regional growth alternatives and peak and off-peak regional travel patterns The model evaluates such transportation option with respect to criteria of N78-33117*# General Dynamics/Fort Worth. Tex airline profitability, public acceptance, and public and private AN INVESTIGATION OF WiNG BUFFETING RESPONSE AT non-user costs In so doing, it incorporates information on modal SUBSONIC AND TRANSONIC SPEEDS. PHASE 2: F-111A split, peak and off:peak use of the air commuter fleet, terminal FUGHT DATA ANALYSIS. VOLUME 2: PLOTTED POWER and airport costs, development costs and uses of land in proximity SPECTRA to the airport sites, regional population shifts, and induced zonal David B Benepe. Atlee M Cunningham. Jr. Sam Traylor, Jr. shifts in travel demand The model is multimodal in its analytic and W. David Dunmyer 1978 724 p refs capability, and performs exhaustive sensitivity analysis A R.H (Contract NAS2-7091)
13 (NASA-CR-152113) Avail NTIS HC A99/MF A01 CSCL A78-12243" I Advanced Digital Avionics System for general 10A aviation. R K. Smyth (Milco International, Inc, Huntington Beach, Plotted power spectra for all of the flight points examined Calif.), R. H. Hoh, and G L Teper (Systems Technology, Inc, during the Phase 2 flight data analysis are presented Detailed Hawthorne, Calif.). In' Digital Avionics Systems Conference, 2nd, descriptions of the aircraft, the flight instrumentation and the Los Angeles, Calif., November 2-4, 1977, Collection of Technical analysis techniques are given Measured 'and calculated vibra- Papers. (A78-12226 02-04) New York, American Institute of Aero tion mode frequencies are also presented to assist in further nautics and Astronautics, Inc., 1977, p. 96-102 Contract No. interpretation of the PSD data GY. NAS2-9311. (AIA_77-1494) Objectives and functions of the Advanced Digital Avionics System (ADAS) for general aviation are outlined with particular reference to navigation, flight control, engine management, ATC N7BE33118"AGeneral Dynamics/Fort Worth, Ex surveillance, flight management, communications, and the pilot SUBSONIC AND TRANSONIC SPEEDS PHASE 2: F-111A controls and displays The resulting ADAS design comprises the
FUGHT DATA ANALYSIS. VOLUME 3: TABULATED selection of off-the-shelf avionics to be integrated with ADAS-unique POWER SPECTRA elements including new pilot displays and controls along with a David B Benepe. Atlee M Cunningham. Jr. Sam Traylor. Jr., microcomputer control complex (MCC). Reasons for which the and W David Dunmyer 1978 286 p refs ADAS achieves increased avionics capability are mentioned, includ (Contract NAS2-7091) ing overall system integration through the MCC and pilot orientation (NASA-CR-152114) AvaL NTIS HC A13/MF A01 CSCL from navigation map display. SD. 01C Power spectral density (PSD) data for all of the flight points examined during the Phase 2 flight data analysis are presented in tabular form Detailed descriptions of the aircraft, the flight A78-14063 * Peripheral processors for high-speed simula instrumentation and the analysis techniques are given Measured "tion. W. J Karplus (California, University, Los Angeles, Calif ) and calculated vibration mode frequencies are also presented to Simulation, vol. 29, Nov. 1977, p 143-153. 7 refs. NSF Grant No. assist in further interpretation of the PSD data. G.Y. ENG-76-0781 1, Contract No. NAS2-7806. This paper describes some of the results of astudy directed to the specification and procurement of a new cockpit simulator for an N78-33876-# Nielsen Engineering and Research. Inc. Mountain advanced class of helicopters A pad of the study was the definition View, Calif of a challenging benchmark problem, and detailed analyses of it were PROPAGATION OF SOUND THROUGH A SHEARED FLOW made to assess the suitability of a variety of simulation techniques Final Report, 30 Aug. 1976 - 1 Jul. 1977 The analyses showed that a particularly cost-effective approach to James P.Woolley. Charles A Smith.and Knshnamurty Karamchet the attainment of adequate speed for this extremely demanding Aug 1978 83 p refs application is to employ a large minicomputer acting as host and (Contract NAS2-9357) controller for a special-purpose digital peripheral processor Various (NASA-CR-152196, NEAR-TR-171) Avail NTIS realizations of such peripheral processors, all employing state-of HC A05/MF AOl CSCL 20A the-art electronic circuitry and a high degree of parallelism and Sound generated in a moving fluid must propagate through pipelining, are available or under development The types of a shear layer in order to be measured by a fixed instrument peripheral processors - array processors, simulation-oriented pro These propagation effects were evaluated for noise sources typically associated with single and co-flowing subsonic jets and cessors, and arrays of processing elements are analyzed and for subcritical flow over airfoils in such lets The techniques for compared. They are particularly promising approaches which should describing acoustic propagation fall into two categories, geometric be suitable for high-speed simulations of all kinds, the cockpit acoustics and wave acoustics. Geometric acoustics is most simulator being acase in point (Author) convenient and accurate for high frequency sound In the frequency range of interest to the present-study (greater than 150 Hz), the geometric acoustics approach was determined to be most useful and practical. G G A78-17395 * A fifty channel electrically scanned pressure module. J. R. Mallon (Kuite Semiconductor Products, Inc, Ridge field, N J ). In International Instrumentation Symposium, 23rd, Las Vegas, Nev, May 1-5, 1977, Proceedings (A78-17351 05-35) Pitts burgh, Pa, Instrument Society of America, 1977, p 443-450. 8 refs Contract No. NAS2-8931 JOURNAL ARTICLES, BOOKS AND A unique miniature pressure sensor system consisting of an array CHAPTERS OF BOOKS of fifty integrated sensor pressure transducers with integral electronic logic and switching is described. Solid state processing of the piezoresistive array is combined with hybrid microelectronics to displacement), high reliability A78-10455 * # Coplanar tail-chase aerial combat as a differ- produce a very small, dense (80 cc D. S. Hague (Aerophysics Research pressure measuring system. Application to high speed data acquisi Corp.,ential game.Mountain A. View,W. Merz Calif.) and AAA Journal, vol. 15, Oct 1977, p tion, energy conservation in wind tunnels and flight test isdiscussed. 1419-1423. 5 refs Contract No NAA2-8844 Test data are presented typifying system performance. (Author)
A reduced-order version of the one-on-one aerial combat problem is studied as a pursuit-vasion differential game. The coplanar motion takes place at given speeds and given maximum A78-1805g * Robustness in linear quadratic feedback design available turn rates, and is described by three state equations which with application to an aircraft control problem R V. Patel, B are equivalent to the range, bearing, and heading of one aircraft Sridhar, and M Toda (NASA, Ames Research Center, Moffett Field, relative to the other. The purpose of the study isto determine those Calif ). In: Annual Asilomar Conference on Circuits, Systems, and relative geometries from which either aircraft can be guaranteed a Computers, 10th, Pacific Grove, Calif, November 22-24, 1976, win, regardless of the maneuver strategies of the other. Termination Conference Record (A78-18051 05-59) North Hollywood, Calif, is specified by the tail-chase geometry, at which time the roles of Western Periodicals Co., 1977, p 293-300.9 refs pursuer and evader are known The roles are found in general, Some new results concerning robustness and asymptotic proper together with the associated optimal turn maneuvers, by solution of ties of error bounds of alinear quadratic feedback design are applied the differential game of kind, For the numerical parameters chosen, to an aircraft control problem An autopilot for the flare control of neither aircraft can win from the majority of possible initial the Augmentor Wing Jet STOL Research Aircraft (AWJSRA) is conditions if the other turns optimally in certain critical geometries. 'designed based on Linear Quadratic (LQ) theory and the results (Author) developed in this paper The variation of the error bounds to changes
14 in the weighting matrices in the LQ design is studied by computer A78-22555 * 4 Wake vortex measurements of bodies at high simulations, and appropriate weighting matrices are chosen to obtain angle of attack. F K Owen (Owen International Inc, Palo Alto. a reasonable error bound for variations in the system matrix and at Calif.) and D A Johnson (NASA, Ames Research Center, Moffett the same time meet the practical constraints for the flare maneuver Field, Calif) American Institute of Aeronautics and Astronautics, of the AWJSRA Results from the computer simulation of a Aerospace Sciences Meeting, 16th, Huntsville, Ala ,Jan. 16-18, 1978, satisfactory antopilet design for the flare control of the AWJSRA are Paper 78-23 10 p- 7 refs USAF-ssipported research. Contract No presented (Author) NAS2-9168 Three-dimensional laser velocimeter measurements have been made of the wake vortices of aslender tangent ogive body which had A78-20686 Transonic wing analysis using advanced co- nose and body fineness ratios of 3 5 and 12. respectively Data were AT- aa obtained for an angle of attack to seminose angle ratio of 23 at a putational methods P A Henne (Douglas Aircraft Co, Long Beach, free stream Mach number of 0 6 and unit Reynolds number of 2 CalifFielCalif ) and I AR ricknnstitNAS M Hicks (NASA, AmesfAesrearich Research CntrofCenter, Moffett million/ft Details of the mean flow field aie presented and features Field, Calif ) Amencan Institute of Aeronautcs and Astronautics, of the turbulent and unsteady nature of the vortex flow field are Aerospace Sciences Meeting, 16th, Huntsville, Ala Jan. 16-18, 1978, discussed Problems associated with obtaining meaningful vortex Paper 78-105 10 p 9 refs measurements in high-speed flows are addressed (Author) This paper discusses the application of three-dimensional com putational transonic flow methods to several different types of transport wing designs The purpose of these applications is to evaluate the basic accuracy and limitations associated with such A78-22578 * # Measured wake-vortex characteristics of air numerical methods. The use of such computational methods for craft in ground effect. D. L. Ciffone (NASA. Ames Research Center, practical engineering problems can only be justified after favorable Moffett Field, Calif I and B Pedley. American Institute of Aero evaluations are completed The paper summarizes astudy of both the 1 nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts small-disturbance and the full potential technique for computing vlle, AlaJan 16-18, 1978, Paper 78-109. 10p. 13 refs three-dimensional transonic flows Computed three-dimensional re- In support of the NASA wake vortex alleviation program, suits ae compared to both experimental measurements and theoret- measurements were made of the influences of a ground plane on cal results Comparisons are made not only of pressure distributions vortex trajectories and velocity profiles within lift-generated wakes but also of lift and drag forces Transonic drag rise characteristics are The wakes were generated by towing 0 61-m (2-ft) span models of compared Three-dimensional pressure distributions and aerodynamic two jumbo jets under water in a ship model basin. The models were forces, computed from the full potential solution, compare reason- configured with landing flaps and flight spoilers to investigate the ably well with experimental results for a wide range of configurations wake characteristics of these aircraft in ground effect at simulated and flow conditions (Author) full-scale distances of 19 m (62 ft) to 116 m (380 ft) above the ground The ground plane caused modifications in the vortex trajectories but did not alter vortex interactions and merging patterns in these multiple vortex wakes Some distortions in vortex vertical A78-20087 - Laser-velocimeter surveys of merging vortices (tangential) velocity profiles were recorded as a result of vortex in a wind tunnel V R Corsiglia, K L Orloff (NASA, Ames lateral motions and vortex interactions with the viscous boundary Research Center, Moffett Field, Calif ). and J D Iversen (NASA, layer on the ground plane, however, maximum tangential velocities F Ames Research Center, Moffett Field, Calif , Iowa State University remained unchanged (Author) of Science and Technology, Ames, Iowa) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan. 16-18, 1978, Paper 78-107 10 p. 28 refs radiation The merger of two vortices was studied with a laser velocimeter A78-22594 * J Analysis of flight effects on noise designed to measure the two cross-stream components of velocity from let flow using aconvecting quadrupole model R Dash (NASA, Measurements were made at several downstream distances in the Ames Research Center. Moffett Field, Calif ). American Institute of vortex wake shed by two semispan wings mounted on the wino Aeronautics and Astronautcs, Aerospace Sciences Meeting, 16th, tunnel walls The velocity data provided well difined contours of Huntsville, Ala., Jan. 76-18, 1978, Paper 78-192 14 p 29 refs- cross-flow velocity, stream function and vorticity. Downstream of The effects of flight on noise radiation from convecting the merger point the vorticity was shown to be independent of the quadrupoles in a let flow are examined. The analysis shows that as downstream distance for small radii, and at larger radii was flight velocity increases there is asteadily increasing amplification of dependent on the distance from the wing rather than from the the sound that is radiated into the forward arc and a large reduction merger point Upstream of the merger point a multicell vorticity of the sound that is radiated into the rearward arc The analysis also pattern was shown (Author, shows the same trend when there is a reduction in the exhaust velocity with, however, afurther rise in amplification in the forward quadrant and a drop in attenuation in the aft quadrant Finally, it is concluded that there is a transmission effect tending to enhance the A78-22554 - I Measurements of unsteady vortex flow fields sound radiation by a density ratio pf/pj which increases with F K Owen (Owen International, Inc , Palo Alto, Calif.) and D A increasing let temperature. (Authnri Johnson (NASA. Ames Research Center, Moffett Field. Calif American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16.18, 1978, Paper 78-18. 10 p USAF-supported research; Contract No. NAS2-9168 A78-23883 * New frequency domain methods for system A combined surface hot film and laser velocimeter measurement identification. N K Gupta (Systems Control, Inc, Palo Alto, Calif.). technique, used to obtain new information on the mean, constant In Joint Automatic Control Conference. San Francisco, Calif., June phase-averaged and turbulent structure of time-dependent flow 22-24. 1977, Proceedings Volume 2. (A78-23861 08-63) New York. fields, is described Data obtained in a cylinder wake are presented, Institute of Electrical and Electronics Engineers, Inc., 1977, p. and its structure in both the Eulerian and Lagrangian frames is 804 808. 10 refs. Contracts No. N00014-76-C-0420; No. NAS2 discussed Turbulence data obtained by conventional and conditional 8799 averaging of the velocity fluctuations are also presented These data I This paper presents two new techniques for frequency domain provide details of the small- and large-scale contributions to the total identification of linear system parameters The first technique uses turbulent field (Author) the instrumental variables approach, The frequency domain formula ton is shown to give a considerable insight into the selection of efficient and convergent instrumental variables The new maximum likelihood formulation affords simplier numerical solution and provides a way to select parameter starting values in the gradient based optimization method (Author)
15 A78-23917' Robustness of linear quadratic state feedback A78-26599 * A uniqueness proof for a transonic flow designs in the presence of system uncertainty. R. V. Patel, M. Toda, problem. L. P. Cook (California, University, Los Angeles, Calif.). and B Srcdhar (NASA, Ames Research Center, Moffett Field, Calif ) Indiana University Mathematics Journal, vol. 27, Jan.-Feb. 1978, p In. Joint Automatic Control Conference, San Francisco, Calif, June 51-71.11 refs. Grant No. NsG-2171 22-24, 1977, Proceedings Volume 2. (A78-23851 08-63) New York, The uniqueness of the first-order lifting-line correction to the Institute of Electrical and Electronics Engineers, Inc., 1977, p two-dimensional transonic small disturbance potential for the flow 1668-1673 15 refs. past a lifting, three-dimensional, large-aspect-ratio wing is proved. The paper deals with the problem of expressing the robustness The correction is the solution of a linear equation of mixed type in ,(stability)- property of a linear quadratic state feedback (LQSF) the plane slit along the positive x-axis. The boundary data consist of design quantitatively in terms of bounds on the perturbations Neumann data, continuity restrictions, the Kutta condition, and the (modeling errors or parameter variations) in the system matrices so form of the asymptotic behavior at infinity. The zeroth-order flow is that the closed-loop system remains stable. Nonlinear time-varying assumed to be shock-free, and hence the correction isshock-free and linear time-invariant perturbations are considered The only P.T.H. computation required in obtaining ameasure of the robustness of an LQSF design is to determine the eigenvalues of two symmetric matrices determined when solving the algebraic Riccati equation A78-29295 * # Flight simulation - A vital and expanding corresponding to the LQSF design problem Results are applied to a technology in aircraft development. P.A. Reynolds (Calspan Corp, complex dynamic system consisting of the flare control of a STOL Buffalo, N.Y.) and G. W Hall (NASA, Ames Research Center, aircraft. The design of the flare control is formulated as an LQSF Moffett Field, Calif.). American Institute of Aeronautics and tracking problem. S D Astronautics, Annual Meeting and Technical Display, 14th, Wash ington, D.C., Feb. 7-9, 1978, Paper 78-337 11 p 28 refs Flight simulation, both ground and in-flight, is experiencing major technological improvement and growth. The increased capa A78-24367 * # Comments on 'Feasibility study of a hybrid bilities are providing new opportunities for support of the aircraft airship operating in ground effect' M. D Ardema (NASA, Ames development process The development of faster digital computers, Research Center, Moffett Field, Calif ). Journal of Aircraft, vol. 15, improved visual displays, better motion systems and increased Feb. 1978, p. 126, 127, Author's Reply, p. 127, 128 9 refs interest in simulation fidelity has improved the ground simulator to the point where it accomplishes a major portion of the aircraft development before work on the flight article begins. The efficiency of the ground simulator as a forecaster for the flight testing phase is A78-26274 * # Three-dimensional canard-wing shape optimi- becomrig well established. In-flit simulation is properly being used zation in aircraft cruise and maneuver environments. B M. E.da to bridge the gap between the ground simulator and the flight test Silva and R. L Carmichael (NASA, Ames Research Center, Moffett article. Simulation provides the vital link between analysis, aero Field, Calif.). American Institute of Aeronautics and Astronautics, dynamic tests, and subsystem tests and the flight test article. This Annual Meeting and Technical Display, 14th, Washington, D.C., Feb. paper describes the latest advances in flight simulation and its 7-9, 1978, Paper 78-99.8 p.39 refs increasing role in the aircraft development process (Author) This paper demonstrates a numerical technique for canard-wing shape optimization at two operating conditions. For purposes of F simplicity, a mean surface wing paneling code is employed for the aerodynamic calculations. The optimization procedures are based on A78-29804 * # Visualization of quasi-periodic unsteady flows. the method of feasible directions. The shape functions for describing R. A. Kadlec (Colorado, University, Boulder, Colo.) and S. S. Davis the thickness, camber, and twist are based on polynomial representa- (NASA, Ames Research Center, Moffett Field, Calif.) In Structures, tions. The primary design requirements imposed restrictions on the Structural Dynamics and Materials Conference, 19th, Bethesda, Md., canard and wing volumes and on the lift coefficients at the operating April 3-5, 1978, Technical Papers (A78-29776 11-39) New York, conditions. Results indicate that significant improvements in American Institute of Aeronautics and Astronautics, Inc., 1978, p. minimum drag and lift-to-drag ratio are possible with reasonable 275-281. 10 refs. (AIAA78-502) aircraft geometries Calculations were done for supersonic speeds A self-synchronizing schlieren flow visualization technique has with Mach numbers ranging from 1 tb 6. Planforms were mainly of a been developed to study unsteady periodic flows which may result delta shape with aspect ratio of 1. (Author) from aeroelastic effects The technique allows the experimentalist to stroboscopically 'freeze' the streak line pattern at any phase in one period of the motion by driving the schheren light source with an electronically processed synchronizing signal that is derived by A78-26495 * Use of coherence and phase data between two measuring a periodic flow variable with a convenient sensor. Results receivers in evaluation of noise environments. A. G. Piersol (Bolt for the visualization of the near-wake behind an oscillating airfoil at Beranek and Newman, Inc, Canoga Park, Calif.), Journal of Sound low speeds which show an ordered series of discrete vortices and a and Vibration, vol 56, Jan 22, 1978, p. 215-228 11 refs. Contract curious short-wave-length wake disturbance are examined Results No. NAS2-8382. are also presented for edge tone sound generation. (Author) For certain types of noise control problems, where transducers cannot be mounted on suspected sources, valuable information can often be obtained by comparing the coherence and phase data A78-31300 Multichannel electrochemical microbial detec measured between two closely spaced microphones with analytical tion unit. J. R. Wilkins (NASA, Langley Research Center, Hampton, models deduced from the physics of the problem. However, the Va.), R. N. Young (NASA, Ames Research Center, Moffett Field, application of such analysis techniques must be pursued with care, Calif.; Northrop Services, Inc, Hampton, Va ), and E H. Boykin particularly when the measurements are made ina reverberant area. (Northrop Services, Inc., Hampton, Va.).AppliedandEnvironmental A simple illustration is presented where the acoustic field in the test Microbiology, vol. 35, Jan. 1978, p. 214, 215. section of a wind tunnel is evaluated by modelling the field asa The paper describes the design and capabilities of a compact combination of diffuse noise due to the boundary layer turbulence in multichannel electrochemical unit devised to detect and automati the test section and propagating noise generated by the tunnel fan cally, indicate detection time length of bacteria By connecting this and possible flow disturbances outside the test section. The unit to a strip-chart recorder, a permanent record is obtained of the coherence and phase between two closely spaced microphones in the end points and growth curves for each of eight channels. The tunnel test section are predicted for various ratios of diffuse to experimental setup utilizing the multichannel unit consists of a test propagating noise contributions and compared to actual measure- tube (25 by 150 mm) containing acombination redox electrode plus ments under several different tunnel operating conditions (Author) 18 ml of lauryl tryptose broth and positioned in a 35-C water bath.
16 Leads from the electrodes are connected to the multichannel unit, April 19-21, 1978, Technical Papers. (A78-32326 12-09) New York, which inturn isconnected to a strip-chart recorder. After addition of American Institute of Aeronautics and Astronautics, Inc., 1978, p. 2 0 ml of moculum to the test tubes, depression of the push-button 330-335. 5 refs. Contracts No. NAS2-6690; No NAS2-8745; No starter activates the electronics, timer, and indicatorlight for each NAS2-9155 (AIAA78-814) channel. The multichannel unit is employed to test tenfold dilutions Belt-type moving ground equipment, used for ground-effect of various members of the Enterobacteriaceae group, and a typical simulation in STOL and VTOL tests, can be inconvenient and costly, dose-response curve is presented. S.D. especially in larger tunnels, In most cases such difficulties may be avoided by employing tangential blowing at the ground surface, from a single slot. The paper reviews several powered model tests using both moving ground and tangential blowing and describes the slot A78-31306 Fuel swing potential of Mach 0.8 win engine configuration, and the test techniques which were developed. prop-fan transports F. J. Davenport (Boeing Commercial Airplane Ground skin friction is monitored to set blowing levels and no Co., Seattle, Wash ). In. Canadian Symposium on Energy Conserving model-dependent calculations are needed It is also shown that Transport Aircraft, Ottawa, Canada, October 3, 4, 1977, Proceed- application to center-tunnel testing can delay tunnel flow breakdown ings (A78-31301 12-05) Ottawa, Canadian Aeronautics and Space very considerably. (Author) Institute, 1978, p. 5-1 to 5-19 Contract No. NAS2-9104. The fuel saving and economic potentials of the prop-fan high-speed propeller concept have been evaluated for twin-engine commercial transport airplanes designed for 3333 6 km range, 180 A78-32386 * # New rotation-balance apparatus for measuring passengers, and Mach 0.8 cruise. A fuel saving of 9.7% at the design airplane spin aerodynamics in the wind tunnel. G. N Malcolm range was estimated for a prop-fan aircraft having wing-mounted (NASA, Ames Research Center, Moffett Field, Calif.). In Aero engines, while a 5.8% saving was estimated for a design having the dynamic Testing Conference, 10th, San Diego, Calif., April 19-21, Technical Papers. fA78-32326 12-09) New York, American engines mounted on the aft body. The fuel savings and cost were 1978, 495 6 02 found to be sensitive to the propeller noise level and to aerodynamic Institute of Aeronautics and Astronautics, Inc., 1978, p. . 7 drag effects due to wing-slipstream interaction. Uncertainties in these refs (AIAA 78-835) effects could change the fuel savings as much as plus or minus 50% An advanced rotation-balance apparatus has been developed for A modest improvement in direct operating cost was estimated for the the Ames 12-ft pressure tunnel to study the effects of spin rate, wing-mounted prop-fan at current fuel prices. (Author) angles of attack and sideslip, and, particularly, Reynolds number on the aerodynamics of fighter and general aviation aircraft in asteady spin. Angles of attack to 100 deg and angles of sideslip to 30 deg are possible with spin rates to 42 rad/sec (400 rpm) and Reynolds with wing spans that are A78-32330 * # The shock tube as a device for testing tran- numbers to 30 million/m on fighter models sonic airfoils at high Reynolds numbers. W. J. Cook (Iowa State typically 0.7 m A complete description of the new rotation balance University of Science and Technology, Ames, Iowa), L L. Presley, apparatus, the sting/balance/model assembly, and the operational and G. T. Chapman (NASA, Ames Research Center, Aerodynamics capabilities isgiven. (Author) Research Branch, Moffett Field, Calif-) In: Aerodynamic Testing Conference, 10th, San Diego, Calif., April 19-21, 1978, Technical Papers (A78-32326 12-09) New York, American Institute of Aero- A78-35371 * A simplified Mach number scaling law for F nautics and Astronautics, Inc., 1978, p. 30-39. 16 refs Grant No. helicopter rotor noise K S. Aravamudan, A Lee, and W L Harris NsG-2152. (AIAA 78-769) (MIT, Cambridge, Mass.) Journal of Sound and Vibratton, vol. 57, A performance analysis of gas-driven shock tubes shows that Apr 22, 1978, p 555-570 17 refs Grants No DAAG29-C-027, No. transonic airfoil flows with chord Reynolds numbers in the range of NsG-2095 100 million can be generated behind the primary shock in a large Mach number scaling laws are derived for the rotational and the shock tube. A study of flowover simple airfoils has been carried out high-frequency broadband noise from helicopter rotors. The at low and intermediate Reynolds numbers to assess the testing rotational scaling law isobtained directly from the theory of Lowson technique. Results obtained from schheren photos and airfoil and Ollerhead (1969) by exploiting the properties of the dominant pressure measurements show that steady transonic flows similar to terms in the expression for the complex Fourier coefficients of those observed for the airfoils in wind tunnels can be generated sound radiation from a point source The scaling law for the within the available testing time in a shock tube with either high-frequency broadband noise is obtained by assuming that the properly-contoured test section walls or a properly-designed slotted- noise sources are acoustically compact and computing the wall test section. The study indicates that the shock tube is a useful instantaneous pressure due to an clement on an airfoil where vortices facility for studying two-dimensional high Reynolds number tran- are shed. Experimental results on the correlation lengths for sonic airfoil flows (Author) stationary airfoils are extended to rotating airfoils. On the assumption that the correlation length varies as the boundary layer displacement thickness, it is found that the Mach number scaling law contains a factor of Mach number raised to the exponent 5 8. Both A78-32353 * Buried wire gage for wall shear stress measurc- scaling laws were verified by model tests P.T.H ments V S Murthy and W C Rose (NASA, Ames Research Center, Moffett Field, Calif ) In' Aerodynamic Testing Conference, 10th. San Diego, Calif., April 19-21, 1978, Technical Papers (A78 32326 12-09) New, York, American Institute of Aeronautics and A78-37742 * II Transonic lifting line theory - Numerical pro Astronautics, Inc, 1978, p 203-212 IS refs. (AIAA 78-798) cedure for shock-free flows. R D. Small AIAA Journal, vol 16, A buried wire gage for measuring wall shear stress in fluid flow June 1978, p 632-634. 12 refs Grant No NSG-2171. was studied and further developed Several methods of making this An algorithm for computing transonic lifting line theory relatively new type of gage were examined to arrive at a successful without shocks is presented, the numerical procedure relies on technique that is well-suited for wind-tunnel testing A series of two-dimensional analyses developed to solveanviscad flow equations measurements was made to demonstrate the adequacy of atwo-point for slender airfoils From a series of solutions to two dimensional calibration procedure for these gages The buried wire gage is also problems in which span effects appear parametrically, the three demonstrated to he ideally suited for quantitative measurement of dimensional potential field characterization is obtained Numerical wall shear stress in wind-tunnel testing (Author) results are given for a lifting wing with an elliptic (spanwrise) distribution of chord and a NACA-0012 cros section (a freestream Mach number of 0 63 andI an angle of attack of 2(leg are assumed). A78-32368 * # Moving ground simulation by tangential blow ing J E. Hackett and R. A. Boles (Lockheed-Georgia Co, Marietta, Ga.). In Aerodynamic Testing Conference, 10th, San Diego, Calif,
17 A78-38789 * Simulation replay - Implementation and flight the Iowa State University of Science and Technology and NASA simulation applications. D. F. Crane (NASA, Ames Research Center, Single and multiple trailing vortices shed from semi-span wings Moffett Field, Calif.) In: Summer Computer Simulation Conference, and a transport model in a wind tunnel were studied by means of a Chicago, Ill, July 18-20, 1977, Proceedings. (A78-38776 16-59) laser-velocimeter, hot-wire anemometer, and a trailing model incor Montvale, N.J , AFIPS Press, 1977, p 731-734. porating a 6-component force balance Velocity profile and turbu Throughout the aircraft development process flight simulators lence data from the laser-velocimeter and hot-wire anemometer are are used to evaluate design concepts, 'handling' qualities, and presented and shown to compare well with the Betz inviscid operational procedures. A modem flight research simulator corn- circulation model Lift and rolling moment measurements on the prises a cockpit equipped with flight instruments and controls, following model are compared with those predicted from the flow subsystems to provide visual, motion, and other flight cues, and a field measurements. (Author) digital computer. REPLAY is a computer program which enables a user to reproduce the multidimensional flight cues for an entire simulation 'run'. Attention is given to simulation fidelity improve- A78-41886 * IF The spanwise lift distribution on a wing from ment, simulation data recovery, simulation quality assurance, and flow-field velocity surveys K. L Orloff (NASA, Ames Research aircraft systems research. It is pointed out that each of the Center, Moffett Field, Calif ) American Institute of Aeronautics and applications discussed supports aircraft systems research by improv- Astronautics, Fluid and Plasma Dynamics Conference, 11th, Seattle, ing the realism, efficiency, or reliability of thesimulation facility. Wash., July 10-12, 1978, Paper 78-1195.12 p 8 refs. G R. The application of the incompressible three-dimensional mo mentum integral equation to a finite wing isreviewed. The objective is to interpret the resulting equations in a way that suggests an
A78-39184 * # Dual-loop model of the human controller R alternate experimental method for determining the span-wise distri A Hess (NASA, Ames Research Center, Moffett Field, Calif.). bution of lift Consideration is given to constraints that must be Journal of Guidance and Control, vol. 1,July-Aug. 1978, p. 254-260. placed on the character of the vortex wake of the wing to provide 12 refs the familiar relationship between lift and bound vorticity. A novel A dual-loop model of the human controller in single-axis technique is then presented for obtaining, from behind the wing, the compensatory tracking tasks is introduced This model possesses an spanwise lift distribution from velocity surveys that are made over inner-loop closure that involves feeding back that portion of only a short distance above and below the wing trailing edge. The controlled element output rate that is due to control activity. A necessary formalism is developed to use these measured values to novel feature of the model is the explicit appearance of the human's obtain the actual span loading by using an equivalent single internal representation of the manipulator-controlled element horseshoe vortex model to account for the unmeasured portion of dynamics in the inner loop. The sensor inputs to the human the downward (or upward) momentum The results of a numerical controller are assumed to be system error and control force The simulation are presented for a typical loading distribution The former can be sensed via visual, aural, or tactile displays, whereas the technique is then verified experimentally using laser velocimeter data latter is assumed to be sensed in kinesthetic fashion. A set of general for the flow field around a model iving (Author) adaptive characteristics for the model is hypothesized, including a method for selecting simplified internal models of the manipulator controlled element dynamics It is demonstrated that the model can A78-41887 * # Flying-hot-wire study of two-dimensional F produce controller describing functions that closely approximate mean flow past an NACA 4412 airfoil at maximum lift. D. Coles and those measured in four laboratory tracking tasks in which the A. J Wadcock (California Institute of Technology, Pasadena, Calif.) controlled element dynamics vary considerably in terms of ease of American Institute of Aeronautics and Astronautics, Fluid and control An empirically derived expression for the normalized Plasma Dynamics Conference, 11th, Seattle, Wash, July 10-12, injected error remnant spectrum isintroduced (Author) 1978, Paper 78-1196 12 p 10 refs. Grants No. NGL-05002-229, No NsG-2319 Hot-wire measurements have been made in the boundary layer, flow past an NACA 4412 A78-40949 * Numerical solution of a class of integral the separated region, and the near wake for equations arising in two-dimensional aerodynamics J Fromme and airfoil at maximum lift The Reynolds number based on chord was M. A. Golberg (Nevada. University, Las Vegas, Nev.)_ Journal of about 1,500,000 The main instrumentation was a hot-wire probe mounted on the end of a rotating arm. A digital computer was used 169-206 20 refs Grant No Nsa2140 to control synchronized sampling of hot-wire data at closely spaced
We consider the numerical solution of a class of integral points along the probe arc. Ensembles of data were obtained at equations arising in the determination of the compressible flow several thousandtwo locationscomponents in ofthe mean flow velocity,field. The and datatwelve include mean about a thin airfoil in a ventilated wind tunnel The integral itermittency, equations are of the first kind with kernels having a Cauchy values for double, triple, and quadruple products of two velocity singularity Using appropriately chosen Hilbert spaces, it is shown fluctuations The data are available on punched cards in raw form that the kernel gives rise to a mapping which isthe sum of aunitary and also after use of smoothing and interpolation routines to obtain operator and a compact operator This allows the problem to be values on a fine rectangular grid aligned with the airfoil chord The studied in terms of an equivalent integral equation of the second data are displayed in the paper as contour plots (Author) kind A convergent numerical algorithm for its solution isderived by using Galerkin's method It isshown that this algorithm isnumerical ly equivalent to Bland's collocation method, which is then used as A78-43521 * ii Effects of inlet airframe integration on the the method of computation Extensive numerical calculations are inlet of an upper surface blowing four-engine STOL aircraft. M. D presented establishing the validity of the theory. (Author) Shovlin (NASA, Ames Research Center, Moffett Field, Calif ) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Joint Propulsion Conference, 14th, Las Vegas, Nevt,July 25-27, 1978, AIAA Paper 78-959 9 p 7.refs. A78-41885 * If Hot-wire, laser anemometer and force balance Inlet and nacelle static pressures were measured on a0 5-scale measurements of cross-sectional planes of single and interacting mt,el of the Quiet Short-Hdul Research Airplane (OSRA) in the trailing vortices. J. D. Iversen, S. Park, D_ R Backhus, R A Ames Research Center's 40- by 80 Foot Wind Tunnel This model is Brickman (Iowa State University of Science and Technology, Ames, powered by four JT-15D engines located above the wing with closely Iowa), and V R Corsigha (NASA, Ames Research Center, Moffett spaced adjacent inlets A fifth JT-15D engine in the fuselage provides Field, Calif.) American Institute of Aeronautics and Astronautics, boundarylayer control air Each inlet was instrumented with four to Fluid and Plasma Dynamics Conference, 11th, Seattle, Wash., July eight rows of axial pressure taps located between X/R approximately 10-12, 1978, Paper 78-1194. 14 p 19 refs. Research supported by plus or minus 1. The tests simulated a broad range of aircraft
18 operating conditions, including engine-out, with lift coefficients from A78-46011 * Meteorological control of lower stratospheric U8 to 10.0. Results indicate that the inlets perform well under most minor species variations - An observational example. F.N. Alyea and operating conditions with little interaction between inlets when the D. M. Cunnold (MIT, Cambridge, Mass.).Atmosphenc Environment, aircraft is moving. Potential problem areas identified are high sideslip vol. 2, no, 5. 1978, p. 1075-1080 8 refs Research supported bythe angle during approach and an interaction effect between adjacent Manufacturing Chemists Association; Grants No. INsG-2010, No inlets with high mass flows in staticconditions (Author) NsG-2196. Lower stratospheric air trajectories entering the region over Alaska at the approximately 125 mb level during late May, 1975 A78-43525 * N Estimating maximum instantaneous distortion indicate a substantial shift in the geographical source regions forthe from inlet total pressure rms measurements. H. C. Melick, Jr., A H. air masses present during that time. This shift coincides with an Ybarra (Vought Corp, Dallas, Tex ),and D P. Bencze (NASA, Ames approximately 25% decrease in the observed halocarbon mixing Research Center, Mcffett Field, Calif ) American Institute of ratios at the 125 mb level as determined from adaily sequence of Aeronautics and Astronautics and Society ofAutomotive Engineers, halocarbon profiles Since the halocarbon species measured are Joint Propulsion Conference, 14th, Las Vegas, Nov., July 25-27, essentially chemically inactive at this level, the observed variation is 1978, AIAA Paper 78-970. 15 p. 12 refs. Contracts No. NAS2-6901, linked to the changing meteorological pattern. (Author) No NAS2-8878. In the present paper, a new mathematical model of inlet turbulence is developed by application of basic fluid dynamics and 'A78-46514 * # A historical overview of stall/spin characteris statistical concepts. The model provides an understanding of the tics of general aviation aircraft. S B. Anderson (NASA, Ames turbulent inlet flow as well as a means of describing the flow in Research Center, Moffett Field, Calif ) American Institute of quantitative terms. Specifically, the maximum instantaneous distor- Aeronautics and Astronautics, Conference on Air Transportation: tion produced by inlet unsteady flow can be estimated by the simple Technical Perspectives and Forecasts, Los Angeles, Calif., Aug measurement of rms data. Practical application of these techniques 21-24, 1978, Paper78-1551 10 p. 19 refs leads to a data/acquisition/reduction system that is at least one, and Even today, stall/spin accidents involving general aviation maybe two, orders of magnitude less expensive than conventional aircraft account for more fatal and serious injuries than any other methods. Each data point can be reduced in terms of the mean kind of accident. The classic stall/spin accident is one in which the strength of the turbulent vortices. By storing these two parameters pilot stalls the aircraft at too low an altitude to affect recovery The (that are representative of the unsteady flow with the steady state primary attention in the investigation is given to aerodynamic information), the maximal instantaneous distortion can be recon- considerations, although it isrecognized that human factors and pilot structed for other distortion factors at any time subsequent to the training are also very important aspects of the total problem. A test V.P. review of some 70 years of flight indicates that incorporation of the proper combination of aerodynamic parameters to provide good stall/spin avoidance has persistently remained an elusive goal for ,A78-45148 * # Theoretical and experimental study of the designers of general aviation aircraft. GR. drag of multielement airfoils L E. Olson (NASA, Ames Research Center; US Army, Aeromechanics Laboratory, Moffett Field, Calif.), W. D. James (Iowa State University of Science and A78-46545" # High performance dash-on-warning air mobile F Technology, Ames, Iowa), and P. R. McGowan (Computer Sciences missile system. D. S. Hague (Astrophysics Research Corp., Bellevue, Corp., Mountain View, Calif.). American Institute of Aeronautics Wash ) and A D. Levin (NASA, Ames Research Center, Moffett and Astronautics, Fluid and Plasma Dynamics Conference, 71th, Field, Calif.). In: Atmospheric Flight Mechanics Conference. Palo Seattle, Wash,July 1012, 1978, Paper 78-1223.12 p. 17 refs Alto, Calif., August 7-9, 1978, Technical Papers (A78-46526 20-08) The viscous/potential flow past single-element and multielement New York, American Institute of Aeronautics and Astronautics, Inc., airfoils is studied theoretically and experimentally. A computerized 1978, p 166-172. 10 refs (AIAA 78-1353) analysis, based on iteratively coupled potential-flow and boundary- Because fixed missile bases have become increasingly vulnerable layer analysis, is used to predict the flow field of the airfoil. The to strategic nuclear attack, an air-mobile missile system isproposed, method yields detailed characteristics of conventional laminar and whereby ICBMs can be launched frem the hold of large subsonic turbulent boundary layers, turbulent wakes, and confluent boundary aircraft following a missile-assisted supersonic dash of the aircraft to layers. The viscous flows are analyzed with a method that uses a sfe distance from their base (about 50 n mi) Three major finite-difference solutions of the boundary-layer equations. Reynolds categories of vehicle design are presented: staged, which employs stress in the boundary layers and wakes is simulated with eddy- vertical take-off and a single solid rocket booster similar to that used viscosity models for the various flow zones The viscous calculations on the Space Shuttle, unstaged, which employs vertical take-off and are carried into the wake of the airfoil where the drag is found from four internally-carried reusable liquid rocket engines, and alternative the defect inthe wake momentum. (Author) concepts, some using horizontal take-off with duct-burning after burners Attention is given to the economics of maintaining 200 - ICBMs airborne during an alert (about $600 million for each fleet A78-45535 Numerical experiments on the stability of alert, exclusive of acquisition costs). The chief advantages of the disklike galaxies. R. H. Miller (NASA, Ames Research Center, system lie in its reduced vulnerability to suprise attack, because it Moffett Field, Calif ) AstrophysicalJournal, Part 1, vol 223, Aug 1, can be launched on warning, and in the possibility for recall of the 78 19 ,p 811-823 16 refs aircraft if the warning proves to be afalse alarm. D M.W. It is noted that the stability properties of available galactic models are not consistent with presumptions based on observation and that'axisymmetric disk systems with velocity dispersions like A78-46560 * # Flight tests of a simple airborne device for those of the Galaxy display major changes in form on a dynamical predicting clear air turbulence encounters. R. L. Kurkowski, C. E time scale A report is given on a series of numerical experiments Duller, III (NASA, Ames Research Center, Moffett Field, Calif.), and carried out as part of a systematic search for purely self-consistent P M. Kuhn (NOAA, Environmental Research Laboratories, Boulder, disk galaxy models that might undergo little change over the time of Colo I. In: Atmospheric Flight Mechanics Conference, Palo Alto, several galactic rotations The stability problem is reviewed, the Calif., August 7-9, 1978, Technical Papers. (A78-46526 20-08) New method and calculations used are described, and initial conditions are York, American Institute of Aeronautics and Astronautics, Inc, outlined. The problem of estimating growth rates is discussed, and 1978, p 320-324.6 refs (AIAA 78-1375) growth rates are evaluated for various disturbances Experimental An airborne clear-air turbulence detector is being flight-tested results are presented concerning growths of axisymmetric distur- on board NASA's C-141 and Learjet aircraft. The device is an bances in 'cold' systems as well as disturbanceswith m = 1, 2, and 3. infrared (IR) sensor in the water vapor band and isdesigned to detect It is found that m = 2 disturbances are the most virulent and should changes in vapor concentrations associated with turbulence in shear dominate when all m values are allowed, but that the most rapidly conditions Warnings of about 5 min have been demonstrated at growing disturbancesare inhibited when several m valuesare allowed flight altitudes from 9.1 to 13.7 km (30,000 to 45,000 ft). F.G M. Encounter predictions were obtained 80% of the time, and false
19 alarms were given about 6%of the time. Several simple algorithms Astronautics, Aircraft Systems and Technology Conference, Los were studied for use as signal output analyzers and for alert Angeles, Calif., Aug. 21-23, 1978, Paper 78-1482. 13 p. 18 refs. triggering (Author) The program described was initiated in 1975 to provide the critical information for the design of an advanced avionics system suitable for general aviation. Emphasis is on the use of data busing, A78-47354 * On the stability of disklgke galaxies in massive distributed microsensors, shared electronic displays and pilot entry halos. R. H. Miller (NASA, Ames Research Center, Moffett Field, devices, innovative low-cost sensors, and improved functional char Calif.). Astrophysical Journal, Part 1, vol. 224, Aug. 15, 19 78.-p. acteristics. -Design considerations include cost, reliability, maintain 32-38. 15"refs. ability, and modularity. V.P. Results are reported for a series of disk-galaxy simulations carried out as part of a systematic search for disk-galaxy models that show little change over the time of several galactic rotations. Systems A78-47946 * # Studies of aerodynamic technology for in agiven fixed external field, such as might be provided by amassive VSTOL fighter/attack aircraft. W. P. Nelms (NASA, Ames Research halo, are considered. The analysis is performed in terms of two Center, Moffett Field, Calif.). American Institute ofAeronautics and parameters the fraction of the total mass that resides in the active Astronautics, Aircraft Systems and Technology Conference, Los disk and the velocity dispersion in the active disk. The amount of Angeles, Cahf., Aug. 21-23, 1978, Paper 78-1611.32 p. 17 refs. halo mass required to stabilize a disk with agiven velocity dispersion The paper summarizes several studies to develop aerodynamic is investigated along with the question of whether any amount of technology for high performance VSTOL aircraft anticipated after halo mass can stabilize a completely 'cold' disk galaxy. The 1990. A contracted study jointly sponsored by NASA-Ames and experimental results are quoted as growth rates estimated from plots David Taylor Naval Ship Research and Development Center is of the amplitudes of Fourier analyses of the density in each of aset emphasized. Four contractors analyzed two vertical-attitude and of narrow annuli, and systematic trends in the dependence of growth three horizontal-attitude takeoff and landing concepts with gross rates on the adjustable parameters are examined. It is shown that a weights ranging from about 10433 kg (23,000 Ib) to 17236 kg massive inert halo contributes to the stability of disk-galaxy models, (38,000 Ib). The aircraft have supersonic capability, high maneuver but some velocity dispersion isrequired. F.G.M. performance (sustained load factor 6 2 at Mach 0.6, 3048 mn(10,000 ft)) and a 4536 kg (10,000-1b) STO overload capability. The contractors have estimated the aerodynamics and identified aero A78-47907 * # Some observations on the mechanism of air- dynamic uncertainties associated with their concept. Example craft wing rock. C Hwang and W. S. Pi (Northrop Corp., Aircraft uncertainties relate to propulsion-induced flows, canard-wing interac Div, Hawthorne, Calif). American Institute of Aeronautics and tions, and top inlets Wind-tunnel research programs were proposed Astronautics, Aircraft Systems and Technology Conference, Los to investigate these uncertainties. (Author) Angeles, Calif., Aug. 21-23, 1978, Paper 78-1456. 11 p. 6 refs Contract No. NAS2-8734. A pressure scale model of Northrop F-6A was tested in NASA A78-48991 * Lifting line theory for transonic flow. L P. Ames Research Center Eleven-Foot Transonic Tunnel to simulate the Cook and J. D. Cole (California, University, Los Angeles, Calif.). wing rock oscillations in a transonic maneuver For this purpose, a SIAM Journal on Applied Mathematics, vol. 35, Sept. 1978, p flexible model support device was designed and fabricated which 209-228 7 refs. Grant No. NsG-2171. F allowed the model to oscillate in roll at the scaled wing rock Lifting line theory is applied to describe the flow about a lifting frequency. Two tunnel entries were performed to acquire the wing at transonic speeds. The method extends that of Van Dyke pressure (steady state and fluctuating) and response data when the (1975), in which lifting line theory is viewed as a singular model was held fixed and when it was excited by flowto oscillate in perturbation problem, to transonic flows. Inner and outer expansions roll. Based on these data, a,limit cycle mechanism was identified as the aspect ratio approaches infinity of the transonic small which supplied energy to the aircraft model and caused the Dutch disturbance equations are found. It is shown that the solutions match roll type oscillations, commonly called wing rock. The major origin asymptotically. A boundary value problem is formulated which of the fluctuating pressures which contributed to the limit cycle was describes the first aspect ratio correction to the two dimensional traced to the wing surface leading edge stall and the subsequent lift cross sectional transonic flow. The theory is especially applicable to recovery. For typical wing rock oscillations, the energy balance wings of similar cross-sections (Author) between the pressure work input and the energy consumed by the model aerodynamic and mechanical damping was formulated and numerical data presented. (Author) A78-49255* A preference-ordered discrete-gaming ap proach to air-combat analysis. H.J. Kelley and L. Lefton (Analytical A78-47916 * # Quiet, Short-Haul Research Aircraft - Current Mechanics Associates, Inc., Jericho, N.Y.). (Institute of Electrical status and future plans. J. A Cochrane and A. G. Boissevain (NASA and Electronics Engineers, Conference on Decision and Control, New Ames Research Center, Moffett Field, Calif.). American Institute of Orleans, La., Dec. 1977.) IEEE Transactions on Automatic Control, Aeronautics and Astronautics, Aircraft Systems and Technology vol. AC-23, Aug. 1978, p. 642-645. 6 refs. Contracts No. NAS2 Conference, Los Angeles, Calif., Aug. 21-23, 1978, Paper 78-1468. 8738, No. F33615-77-C-3144. 11 p. An approach to one-on-one air-combat analysis is described The Quiet Short-Haul Research Aircraft (QSRA) is a new which employs discrete gaming of a parameterized model featuring research aircraft which NASA will use as a flight-test facility for choice between several closed-loop control policies. A preference advanced flight experiments in terminal area operations. The data ordering formulation due to Falco is applied to rational choice resulting from the OSRA flight research program will be used by the between outcomes: win, loss, mutual capture, purposeful disen U.S. aircraft industry to establish design criteria and by regulatory gagement, draw. Approximate optimization is provided by an agencies to establish certification criteria for advanced STOL aircraft, active-cell scheme similar to Falco's obtained by a 'backing up' The total funding for the QSRA was established at $29 million in process similar to that of Kopp. The approach is designed primarily January 1974. Attention is given to an aircraft description, wind- for short-duration duels between craft with large-envelope weaponry. tunnel results, simulation, predicted aircraft performance, initial Some illustrative computations are presented for an example airworthiness flight tests, design configuration studies, and training modeled using constant-speed vehicles and very rough estimation of studies. G.R. energy shifts. (Author)
A78-47927 * # Integrated avionics for future general aviation A78-49787 * # A method for localizing wing flow separation aircraft. 0. G. Denery, C. T. Jackson, Jr, G P. Callas, B. K. at stall to alleviate spin entry tendencies. T. W. Feistel, S. B. Berkstresser, and G. H. Hardy (NASA, Ames Research Center, Anderson (NASA, Ames Research Center, Moffett Field, Calif.), and Moffett Field, Calif.). American Institute of Aeronautics and R. A. Kroeger (Michigan, University, Ann Arbor, Mich.). American
20 Institute of Aeronautics and! Astronautics, Aircraft Systems and A78-52628 * I An improved higher order panel method for Technology Conference, Los Angeles, Calif., Aug 21-23, 1978, Paper linearized supersonic flow. F. E Ehlers, M A Epton, F_T. Johnson, 78-1476. 8 p. A E Magnus, and P E. Rubbert (Boeing Commercial Airplane Co, A wing leading-edge modification has been developed, applicable Seattle, Wash ) American Institute of Aeronautics and Astronautics, at present to single-engine.light aircraft, which produces stabilizing Aerospace Sciences Meeting, 16th, Huntsville, Aia, Jan. 1- 18, 1978, vortices at stall and beyond. These vortices have the effect of fixing Paper 78-15 7 p 8 refs Contract No NAS2-7729. the stall pattern of the wing such that the various portions of the An improved higher order panel method for linearized super wing upper surface stall nearly symmetrically. The lift coefficient sonc flow is described Each panel, defined by four points on the produced is essentially constant to very high angles of attack above surface, is divided into eight subpanels in such a way that all the stall angle of the unmodified wing. It is hypothesized that these subpanel and panel edges are contiguous By prescribing aouadratic characteristics will help prevent inadvertent spin entry after astall. distribution of the doublet on each subpanel, the doublet strength is Results are presented from recent larascale vind-tunnel tests of a made strictly continuous on the paneled surface. A linea source complete light aircraft, bot with and without the rodification. distribution is also used Numerical results are smoother and i- better (Author) agreement with experiment than the previous method with re, trict continuity. A brief discussion of superincined panels used to A78-497B9 0 f V/STOL aircraft simulation - Requirements eliminate interior interference in nacelles is included (Author) and capabilities at Ames Research Center. D E. Wilcox and H C Quigley (NASA, Ames Research Center, Moffett Field, Calif.). American Institute of Aeronautics and Astronautics, Aircraft Sys- A78-52630 * Advanced panel-type influence coefficient tens and Technology Conference, Los Angeles, Calif, Aug 21-23, methods applied to unsteady three dimensional potential flows. A. 1978, Paper 78-1616. 12 p R Dusto, M A Epton, and F T Johnson (Boeing Co, Seattle, Ground-based flight simulation contributes greatly to the Wash.) American Institute of Aeronautics and Astronautics, Aero. development of new aircraft and flight management systems and will space Sciences Meeting. 16th. Huntsville, Ala-, Jan 16-18. 1978. be especially important in improving the performance, safety, and Paper 78-229 9 p. 7 refs Contract No NAS2-7729. environmental characteristics of future civil and military VISTOL A panel method for solving unsteady, subsonic wind-body-tail aircraft. This paper describes existing simulation facilities at Ames flow problems is formulated and partially verified The method is Research Center and discusses their capabilities and limitations for applicable to general aircraft configurations consisting of arbitrary V/STOL aircraft investigations. Simulation requirements for NASA arrangements of wings, bodies, tails, and nacelles The wake may be research and support of DOD programs are also discussed, including located arbitrarily and the unsteady, transverse component of technology development for advanced rotorcraft and civil and vorticity in the wake may be assigned any covection velocity The military V/STOL aircraft Current efforts and future plans are wake in the unsteady flow problem, therefore, can be given the described for the upgrading of Ames simulation facilities to meet location and convection velocity of the wake produced by a steady those requirements Recent advances in equipment technology and flow which is the mean flow of the unsteady flow problem. The operational methodology are shown to provide significantly im- panel method has been used as a basis for expanding the unsteady proved simulation fidelity through better motion and visual cues and kernel function in a power series to obtain panel influence faster system response to pilot inputs (Author) coefficients which can be integrated in closed form G R. F A78-49804"# C02 laser-driven Stirling engine. G. Lee (NASA, Ames Research Center, Moffett Field, Calif.), R. L Perry (NASA, Ames Research Center, Moffett Field; University of the Pacific, Stockton, Calif.), and B. Carney. Journal of Energy, vol 2, July-Aug. 1978, p. 203-209 10 refs. A 100-W Beale free-piston Stirling engine was powered remotely by a C02 laser for long periods of time. The engine ran on both continuous-wave and pulse laser input. The working fluid was helium doped with small quantities of sulfur hexafluoride, SF6 The C02 radiation was absorbed by the vibrational modes of the sulfur hexafluoride, which in turn transferred the energy to the helium to drive the engine. Electrical energy was obtained from a linear alternator attached to the piston of the engine Engine pressures, volumes, and temperatures were measured to determine engine performance. It was found that the pulse radiation mode was more efficient than the continuous-wave mode. An analysis of the engine heat consumption indicated that heat losses around the cylinder and the window used to transmit the beam into the engine accounted for nearly half the energy input. The overall efficiency, that is,electrical output to laser input, was approximately 0.75% However, this experiment was not designed for high efficiency but only to demonstrate the concept of a laser-driven engine. Based on this experiment, the engine could be modified to achieve efficiencies of perhaps 25-30% (Author)
A78-51860 * Applications of algebraic geometry to systems theory - The McMillan degree and Kronecker indices of transfer functions as topological and holomorphic system invariants. C Martin (NASA, Ames Research Center, Moffett Field, Calif ) and A. Hermann (Harvard University, Cambridge, Mass ). SIAM Journal on Control and Optimization, vol 16, Sept. 1978, p 743-755. 16 refs Contract No A-35046-B.
21 ASTRONAUTICS
FORMAL REPORTS
N78-10148*# Hughes Aircraft Co. El Segundo. Calif Space N78-18274# Army Electronics Command Fort Monmouth. N J. and Communications Group Communications/ADP Lab PIONEER VENUS SPACECRAFT CHARGING MODEL c15 LOW PROFILE ANTENNA PERFORMANCE STUDY. P A Robinson. Jr and A B Holman In NASA Lewis Res PART 2" BROADBAND ANTENNA TECHNIQUES SURVEY Center Proc of the Spacecraft Charging Technol. Conf 24 Feb Final Report, Sep. 1975 - Mar. 1977 1977 p 297-308 refs (For availability see N78-10129 01-12) C M. DeSantis Oct 1977 43 p refs (Contract NAS2-8300) DA Proj 1T1-61101-A-91A) Avail NTIS HC A99/MF A01 CSCL 22B (AD:A047992. ECOM-4542-Pt-2) - Avail NTIS Five environmental models were constructed to represent HC A03/MF A01 CSCL 09/5 the solar wind and the upper middle, and lower ionosphere of This report is Part It of a three part series of reports Vends The spacecraft structure was modeled with over 140 investidating small antennas, their bandwidth and efficiency passive electrical elements representing structural elements of capabilities Reviews and brief outlines of techniques published the spacecraft Electron. ion, secondary electron, and photocurrents in the literature over the past 10-20 years. for broadbanding to the spacecraft from the plasma were calculated. ignoring sheath antennas are provided in this report Experimental results from effects In all but one case. potentials of interest were less than measurements of the Goubau antenna, a low-profile antenna 1 volt Potential differences between widely separated points on (=O 05 lambda at the lowest operating frequency) are presented the equipment shelf were less than I mV. The one area of to show that this antenna possesses an octave bandwidth. concern is the solar panel potential when the orbiter is passing regarding both impedance and radiation characteristics Numerical through the bowshock region Author results for some top-loaded structures are presented and matching network element variations are determined in order to estimate the bandwidth It is shown that approximately 2 1 and ap proximately 4 1 increases in bandwidth are achieved when N78-13492?# National AeronutiL, a I -pace oi, pr t.aton. top-loading is applied to the stub and the loop antenna. Ames Research Center Moffett Field. Calif respectively, and an L-network is used for tuning and matching It is concluded that there may be several small but broadband S ABSTRACTS FOR THE PLANETARY GEOLOGY FIELD antenna configurations possible from a clever (but as yet unknown) CONFERENCE ON AEOUAN PROCESSES combination of the ideas and techniques presented in this Ronald Greeley. ed (Arizona State Univ) and David Black. ed report Author (GRA) Jan 1978 63 p refs (NASA-TM-78455: A-7279) Avail NTIS HC A04/MF A01 CSCL 08G The Planetary Geology Field Conference on Aeolian Processes was organized at the request of the Planetary Geology Program N78-18366# Naval Civil Engineering Lab, Port Hueneme. Calif office of the National Aeronautics and Space Administration to CABLE STRUMMING SUPPRESSION Technical Note, bring together geologists working on aeolian problems on earth Apr. - Jun. 1976 and planetologists concerned with similar problems on the planets B E Hafe, and D J Meggist Sep 1977 107 p refs Abstracts of papers presented at the conference are arranged (AD-A047996; CEL-TN-1499) Avail NTIS HC AO/MF A0l herein by alphabetical order of the senior author. Papers fall into three broad categories (1) Viking Orbiter and Viking Lander CSCL 13/9 results on aeolian processes and/or landforms on Mars. (2) This report presents a consolidation of existing data on various laboratory results on studies of aeolian processes, and (3) devices used to suppress vortex-induced motions of cables and photogeology and field studies of aeolian processes on Earth circular cylinders in the ocean The types of devices discussed Author herein include 'fringe,' hair. and ribbon flexible fairings and helical ridges In general, the available data show that all of these methods do. in fact, suppress vortex-induced vibrations to N78-16326*# National Aeronautics and Space Administration a greater or lesser degree However. because of the diverse Ames Research Center. Moffett Field. Calif ways in which suppression effectiveness has been measured. EFFECTS OF MASS ADDITION ON BLUNT-BODY BOUN- comparisons among different types of devices are difficult to DARY-LAYER TRANSITION AND HEAT TRANSFER make Criteria for such comparisons are suggested Relatively George E KetRAn Jan 1978 67 p refs few measurements of the effects of strumming suppression devices (NASA-TP-1 139. A-7169) Avail NTIS HC A04/MF AOl CSCL on the drag of a cable or cylinder have been reported The 20D available data indicate that a large drag penalty may be incurred The model bodies tested at Mach number 732 were by use of such devices, depending on the configuration hemispheres, blunt cones, and spherical segments The mass employed Author (GRA) additoi onsisted of air elected through porous forward surfaces of',the.-models. The experimental data consisted of heat transfer measurements from which boundary layer transitions were deducel 'The data verified various applicable boundary layer codes N78-18388*# National Aeronautics and Space Administration in the laminar and transitional flow regimes Empirical heating Ames Research Center. Moffett Field. Calif rate data correlations were developed for the laminar and turbulent STATUS AND FUTURE PROSPECTS OF USING NUMERI. flow regimes Author CAL METHODS TO STUDY COMPLEX FLOWS AT HIGH REYNOLDS NUMBERS Robert W McCormack In AGARD Three Dimensional and Unsteady Separation at High Reynolds Numbers Feb 1978 14 p refs (For availability see N78-18375 09-34) Avail NTIS HC All1/MF AOl CSCL 20D The Navier-Stokes equations adequately describe aerodynamic .flows at standard atmospheric temperatures and pressures If these equations could be efficiently solved, there would be no need for experimental tests to design flight vehicles or other
22 aerodynamic devices Alth6ugh much progress has been made N78-19779*# National Aeronautics and Space Administration toward the solution, including complex unsteady two- Ames Research Center Moffett Field. Calif dimensional and steady three-dimensional separated flows and COMPUTATIONAL AERODYNAMICS AND THE NUMERI- have recently made some dramatic improvements in developing CAL AERODYNAMIC SIMULATION FACIUTY cO2 numerical methods, the calculation of flow frelds past complete Victor L Peterson In ,ts Future Computer Requirements for aircraft configurations at flight Reynolds numbers are far beyond Computational Aerodynamics Feb 1978 p 5-30 (For availability our reach, perhaps as long as a decade away They await see N78-19778 10-59) substantial progress in devising accurate and efficient numerical Avail. NTIS HC A22/MF AOl CSCL 09B methods. inunderstanding and modeling the physics of turbulence. Technical and economic reasons for accelerating the matura and in developing reliable and powerful computer hardware tion of the discipline of computational aerodynamics include the Author cost of conducting the experiments required to provide the empirical data base for new aeronautical vehicles and the N78-190295*, Hughes Aircraft CO Culver Ca9 Cdkf limitations in test facilities (Reynolds number, wall and support MAGNETOtAETER DEPLOYMENT MCCHANISM FGR interferences, aeroelastic distortions. real-gas effects, etc) for PIONLER VENUS 19 simulating the full-scale vehicle environment General purpose William L Town,end In NASA Goddard R.s Center i-e computers do not have the necessary capability for the next 11RI Aerospace Much Symp Apr !977 p 23-33 iFor avaiab, :y stage of development Solution of the three dimensional Reynolds see N78S Ib026 00-99) averaged Naiver-Stokes equations in a short time to be practical (Contract NAS2.8300) for design purposed will require 40 times the power of current Avail NTIS hC At 1/MF AOl CSCL 14B supercomputers. However, it is feasible to construct a special A three segment. 15-foot boom mechanism was devclo,,,j purpose processor that will -meet these requirements to enhance to deploy magnetometers rom teo Pioneer Venus orbiter spinnrg the nation's aerodynamic design capability in the 1980"s Author shelf The stowage mechanism is designed to contain he magnetcmet s djning :aunch and to depioy those ,irrurE.:t by cntrifuqal force upon pyrotechnic r t cobe Unqu2 grap,, epoxy Woom .cqmrnts asi uCeO totor ii..0tw Ciiga N78-19781* National Aeronautics and Space Administration sufficieni strnngth to witthstand a 7 5 g orbit irser.on.z .. Ames Research Center. Moffett Field. Calif. while extended The octaled cesiqn is dLscr,bec alorg wrih 1: THREE-DIMENSIONAL COMPUTATIONAL AERODYNAM- test methods develoeu for Quahfication in a one g fie:d MA_,r ICS IN THE 190"S Ce1 Harvard Lomax In its Future Computer Requirements for N78-190S6# National Aeronautics and Space Administration. Computational Aerodynamics Feb 1978 p 33-38 (For availability Ames Research Center. Moffett Field. Calif. see N78-19778 10-59) THE ROLE OF TIME-HISTORY EFFECTS IN THE FORMULA- Avail NTIS HC A22/MF AOl CSCL 098 TION OF THE AERODYNAMICS OF AIRCRAFT DYNAM- The future requirements fcr constructing codes that can be ICS used to compute three-dimensional flows about aerodynamic Murray Tobak and Lewis B Schiff Mar 1978 12 p refs shapes should be assessed in light of the constraints imposed Proposed for Presentation at the AGARD Symp. on Dyn Athens, by future computer architectures and the reality of usable Greece. 22-24 May 1978 algorithms that can provide practical three-dimensional simula (NASA-TM-78471" A-7328) Avail: NTIS HC A02/MF AOl tions. On the hardware side. vector processing is inevitable in CSCL OA order to meet the CPU speeds required To cope with three The scope of any aerodynamic formulation proposing to dimensional geometries, massive data bases with fetch/store embrace a range of possible maneuvers is shown to be determined conflicts and transposition problems are inevitable On the software principally by the extent to which the aerodynamic indicial side, codes must be prepared that (1) can be adapted to complex response is allowed to depend on the past motion Starting geometries. (2) can (at the very least) predict the location of from the linearized formulation, in which the indicial response is laminar and turbulent boundary layer separation, and (3) will independent of the past motion, two successively more compre- converge rapidly to sufficiently accurate solutions Author hensive statements about the dependence on the past motion are assigned to the indlicial response {t) dependence only on the recent past and (2) dependence additionally on acharacteristic feature of the distant past The first enables the rational N78-19782*# Burroughs Corp. Paoli. Pa introduction of nonlinear effects and accommodates a description NUMERICAL AERODYNAMICS SIMULATION FACIUITY of the rate dependent aerodynamic phenomena characteristic of PREUMINARY STUDY, EXECUTIVE SUMMARY airfoils in low speed dynamic stall; the second permits adescription Final Rai Cal of the double valued aerodynamic behaviorcharacteristic ofcertain In NASA Ames Res Center Future Computer Requirements kinds of aircraft stall An aerodynamic formulation based on the for Computational Aerodynamics Feb. 1978 p 41-62 (For second statement, automatically embracing the first. may be availability see N78-19778 10-59) sufficiently comprehensive to include a large part of the aircraft's (Contract NAS2-9456) possible maneuvers The results suggest a favorable conclusion Avail NTIS HC A22/MF AOl CSCL 09B regarding the role of dynamic stability experiments in flight The Burroughs Corporation solution to the problem of numeric dynamics studies Author aerodynamic simulation consists of a computing system designed to meet an effective throughput of one billion floating point operations per second for three-dimensional Navier-Stokes codes In order to fully appreciate the design, its features, and subtleties. N78-19778# National Aeronautics and Space Administration the methodology of the study which evolved this solution and Ames Research Center. Moffett Field. Calif the impact on the processor architecture evolution are de FUTURE COMPUTER REQUIREMENTS FOR COMPUTA- scribed as well as details of the baseline design Author TIONAL AERODYNAMICS Feb 1978 515 p refs Proceedings held at Moffett Field. N78-19783*# Control Data Corp. Minneapolis. Minn Calif. 4-6 Oct 1977 PREUMINARY STUDY FOR A NUMERICALAERODYNAMIC (NASA-CP-2032. A-7291) Avail NTIS HC A22/MF AO1 CSCL SIMULATION FACIUITY Summary Report c61 09B N. R Lincoln In NASA Ames Res Center Future Computer Recent advances incomputational aerodynamics are discussed Requirements for Computational Aerodynamics Feb 1978 as well as motivations for and potential benefits of a National p 63-79 (For availability see N78-19778 10-59) Aerodynamic Simulation Facility having the capability to solve (Contract NAS2-9457) fluid dynamic equations at speeds two to three orders of magnitude Avail NTIS HC A22/MF AOl CSCL 098 faster than presently possible with general computers Two The state of the art of relevant technologies, of systems contracted efforts to define processor architectures for such a and processor architectures, and the measurable computational facility are summarized For individual titles, see N78-19779 requirements of the two existing-Navier-Stokes solution programs through N78-19819. were assessed by Control Data Corporation to determine the
23 best approach for designing a system for aerodynamic simulation N78-21214# National Aeronautics and Space Administration Standard parts and components were used to identify the support Ames Research Center. Moffett Field. Calif Drocessing system, which is composed of commercially avail- FIRE RESISTIVITY AND TOXICITY STUDIES OF CANDI- able equipment and software Technological achievements in large DATE AIRCRAFT PASSENGER SEAT MATERIALS scale integration technology and system organization of subcompo- L L Fewell. Ed Trabold (McDonnell Douglas Corp. Long Beach. nents borrowed from the STAR-100C project were used in the Calif.). and H Spieth (McDonnell Douglas Corp. Long Beach. design of the Navier-Stokes solver AR H Calif) Mar 1978 44 p refs (NASA-TM-78468; A-7334) Avail NTIS HC A03/MF A01 -CSCL 218 Fire resistivity studies were conducted on a wide range of N78-19797e# National Aeronautics and Space Administration candidate nonmetallic maierials being considered for the Ames Research Center. Moffett Field. Calf. construction of improved fire resistant aircraft passenger seats MODEUNG OF THE REYNOLDS STRESSES cO2 These materials were evaluated on the basis of FAA airworthiness Morris W. Rubesin In its Future Computer Requirements for burn and smoke generation tests, colorfastness, limiting oxygen Computational Aerodynamics Feb 1978 p 239-247 (For index, and animal toxicitytests Physical, mechanical, and aesthetic availability see N78-19778 10-59) properties were also assessed Candidate seat materials that have Avail NTIS HC A22/MF A01 CSCL 01A significantly improved thermal response to various thermal loads In their most general form. the Reynolds averaged conserve- corresponding to reasonable fire threats as they relate to tion equations result from ensemble or time averages of the in-flight fire situations, are identified Author instantaneous Navier-Stokes equations or their compressible counterparts For these averaging processes to be consistent, N78-21215"# National Aeronautics and Space Adminstration the averaging time period must exceed the periods identified Ames nt eronaticd ac m r with the largest time scales of the turbulence, and yet be shorter Ames Research Cnter. Moffett Field. Calif than the characteristic times of the flow field With thesw equations +A0CYILDSEDIR+T02CBETWN 220 AND 1000 CEO long period variations in the flow fields are deterministic, provided c aYIELDS ClJ 02 BETWEEN 220 AND 1000 DE K initial conditions are known The average dependent variables RichatAon are sufficiently smooth to be resolvable by finite difference (NASA-TM-78483. A-6613) Avail NTIS HC A4/MF A01 techniques consistent with the size and speed of modern CSCL 07D computers Author Classical trajectory calculations are presented for the reaction CIO + 0 yields Cl+ 02. a reaction which is an important N78-20186 Martin Marietta Aerospace. Denver. Colo step in the chlorine-catalyzed destruction of ozone which is thought FLUID INTERACTION WITH SPINNING TOROIDAL to occur in the 220 and 1000 K The calculated rate constant TANKS is 4.36 x 10 to the minus 11th power exp (-191/T)cu cm D A Fester and J E. Anderson In ESA Attitude Control of molecule (-1)s(-1) and its value at 300 K is 23 plus or minus SpaceVehicles Technol and Dyn Probl Assoc.with the Presence 10 to the 11th power cu cm molecule I-1)s(-1) about a factor of Liquids Det 1977 p 77-86 refs (For availability see of 2 lower than recent experimental data The empirical potential N78-20178 11-18) energy surface used in the calculations was constructed to fit (Contract NAS2-7489) experimental data for CIO. 02 and CIOO molecules Other Avail. NTIS HC A1O/MF AOl CSCL 228 important features of this potential surface, such as the barrier An experimental study was conducted to evaluate pro- to reaction, were varied systematically and calculations were pellant behavior in spinning torroidal tanks that could be used performed for a range of conditions to determine the best in a retropropulsion system of an advanced outer-planet Pioneer theoretical rate constants Results demonstrate the utility of orbiter Information on propellant slosh and settling and on ullage classical trajettory methods for determining activation energies orientation and stability was obtained. The effects of axial and other kinetic data for important atmospheric reactions acceleration, spin rate. spin-rate change. and spacecraft wobble. Author both singly and in combination.- were evaluated using a one eighth scale transparent tank in one-g and low-g environments. Liquid loadings ranged from 5% to 96% full The impact of a N78-21407-# National Aeronautcs and Space Admmnstraton surface tension acquisition device was assessed by comparison Nmes nt eronuticd ac m r ,with bare-tank results The testing simulated the behavior of Ames Research Center. Moffett Field. CaTif the fluorne/hydrazine and nitrogen textroxide/ ONTHE PERIOD OF THE COHERENT STRUCTURE IN monomethyhydrazine propellants Results are presented that BOUNDARY LAYERS AT LARGE REYNOLDS NUMBERS indicate that no major fluid behavior problems would be M. A Badr Narayanan and Joseph 6 Maivin Apr 1978 23 p encountered with any of the four propellants in the toroidal refs tanks of a spin-stabilzed orbiter spacecraft Author (ESA) (NASA-TM-78477. A-7380) Avail NTIS HC A02/MF AO1 CSCL 20D The period of the large coherent structure in a subsonic. N78-21193*# National Aeronautics and Space Administration compressible, turbulent boundary layer was determined using the Ames Research Center Moffett Field, Calif autocorrelation of the velocity and pressure fluctuations for THEORETICAL CONTAMINATION OF CRYOGENIC SATEL- Reynolds numbers between 5.000 and 35.000. In low Reynolds LITE TELESCOPES number flows the overall correlation period scaled with the outer variables - namely, the free stream velocity and the boundary M Murakam (Tokyo Univ. Japan) Apr 1978 49 p refs layer thickness Author (NASA-TP-1177. A-7024) Avail NTIS HCAO3/MF AO1 CSCL 22A The stateof contaminant molecules, the deposition rate on key surfaces, and-the heat transfer rate were estimated by the N78-21490"# National Aeronautics and Space Administration use of a zeroth-order approximation. Optical surfaces of infrared -Ames Research Center. Moffett Field, Calif. telescopes cooled to about 20 K should be considered to be SIMPLE TORSION TEST FOR SHEAR MODULI DETERMINA- covered with at leastmolcues cotainaioseveralitoutan deposition cotrls layers heeffctvensslONof condensible OF ORTHOTROPIC COMPOSITES molecules w mthoutany contamination controls The effectveness H Theodore Sumsion and Yapa D S Rajapakse Apr, 1978 of the purge gas method of contamination controls was discussed 15 p refs Presented at 2d Intern Conf on Composite Mater. This method attempts to drive condensible molecules from the Toronto, 16-20 Apr 1978 telescope tube by impacts with a purge gas in the telescope (NASA-TM-78485; A-7418) Avail- NTIS HC A02/MF A01 tube For this technique to be sufficiently effective, the pressure CSCL 20K of the purge gas must be more than 2 x 000001 tort The By means of torsion tests performed on test specimens of influence caused by interactions of the purged gas with the the same material having a minimum of two different cross particulate contaminants was found to slightly increase the resident sections (flat sheet of different widths), the effective in-plane times of the particulate contaminants within the telescope field (G13) and out-of-plane (G23) shear moduli were determined for of view Author
24 two composite materials of uniaxial and angleply fiber orientations so that the boundary treatment is accurate and relatively simple Test specimens were 16 plies (nominal 2 mm) thick. 100 mm Shock waves and other flow discontinuities are captured in length, and in widths of 6.3 9 5. 12 5. and 15 8 mm Torsion monotonically without any type of fitting procedures The tests were run under controlled deflection (constant angle of Lagrangian method is employed so that the problem of mesh twist) using an electrohydraulic servocontrolled test system, generation is completely avoided The method is applicable to In-plane and out-of-plane shear moduli were calculated from an all Mach numbers except the low subsonic range where equation derived in the theory of elasticity which relates applied compressibility effects are small The method is applied to a torque, the torsional angle of twist, tile specimen width/thickness one-dimensional Riemann problem (shock tube) and to a ratio, and the ratio of the two shear moduli G13/G23 Results two-dimensional supersonic channel flow with reflecting shock demonstrate that torsional shear moduli, G23 as well as G13. waves Author can be determined by simple torsion tests of flat specimens of rectangular cross section. Neither the uniaxial nor angleply composite material were transversely isotropic Author N78-25017*# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif ENGINEERING TESTS OF THE C-141 TELESCOPE N78-220695# National Aeronautics and Space Administration Edwin F Erickson and Donald W Strecker May 1978 9 p Ames Research Center. Moffett Field. Calif (NASA-TM-78467. A-7323) Avail NTIS HC A02/MF A01 DYNAMIC STALL OF AN OSCILLATING AIRFOIL CSCL 20F Unmeal B Mehte (Stanford Univ. Calif) In AGARD Unsteady Data on image quality, chopper performance, and the Aerodyn Feb 1978 32 p refs Sponsored in part by ARMDL closed-loop operation of the 91 cm telescope of the Kuiper (For availability see N78-22033 13-02) Airborne Observatory which were obtained in September 1977 (Contract NCA2-or745-602: Grant NSG-2253) are presented Author Avail NTIS HC A99/MF A01 CSCL OlA Unsteady separated boundary layers and wakes were studied by investigating flow past an oscillating airfoil which in part models the retreating blade stall on the helicopters The N78-26101*# 'National Aeronautics and Space Administration Navier-Stokes equations in terms of the vortiCtly and stream Ames Research Center. Moffett Field. Calif function for laminar flow were solved to determine the flow CALCULATION OF SUPERSONIC VISCOUS FLOW OVER field around a modified NACA 0012 airfoil After a fully developed DELTA WINGS WITH SHARP SUBSONIC LEADING flow was determined at zero incidence, the airfoil was oscillated EDGES in pitch through an angle of attack range from 0 deg to Yvon C Vigneron (Iowa State Univ.. Ames). John V. Rakich. 20 deg. The computed streamlines during this pitch-up motion and John C Tannehill (Iowa State Univ, Ames) Jun 1978 are in qualitative agreement with the trajectories of air bubbles 81 p refs Presented at the AIAA 11th Fluid and Plasma observed in water tunnel experiments conducted with a Dynamics Conf. Seattle. 10-12 Jul 1978 NACA 0012 airfoil under the same conditions During the (NASA-TM-78500) Avail: NTIS HC A05/MF AOl CSCL OIA pitch-down motion of the airfoil, the computed flow patterns Two complementary procedures were developed to calculate cannot be compared with the experiments because the trajectories the viscous supersonic flow over conical shapes at large angles of air bubbles intersect Author of attack, with application to cones and delta wings In the first approach the flow is assumed to be conical and the governing equations are solved at a given Reynolds number with a time-marching explicit finite-difference algorithm In the second N78-24000*# National Aeronautics and Space Administration method the parabolized Navier-Stokes equations are-solved with Ames Research Center. Moffett Field Calif a space-marching implicit noiterative finite-difference algorithm A REVIEW OF NASA-SPONSORED TECHNOLOGY ASSESS- This latter approach is not restricted to conical shapes and provides MENT PROJECTS a large improvement in computational efficiency over published Alfred C Mascy. Arthur D. Alexander. III. and Richard D_Wood methods Results from the two procedures agree very well with May 1978 59 p refs each other and with available experimental data Author (NASA-TM-78472 A-7410) Avail NTIS HC A04/MF AOt CSCL 05B N78-26106*g National Aeronautics and Space Adr,,is-aoun Recent technology assessment studies sponsored by NASA Ames Research Center. Moffett Field Calif are reviewed and a summary of the technical results as well as COMPUTATIONAL WING OPTIMIZATION AND COMPAR- acritique of the methodologies are presented The revievs include ISONS WITH EXPERIMENT FOR A SEMI-SPAN WING Assessment of Lighter-Than-Air Technology Technology Assess- MODEL ment of Portable Energy RDT&P. Technology Assessment of Future E G. Waggoner (Vought Corp . Dallas Tex ). H P. Haney (Vought Intercity Pas-enger Transportation Systems. and Technology Corp, Dallas, Tex). and W F Ballhaus Jun 1978 90 p refs Assessment of Space Disposal of Radioactive Nuclear Waste (NASA-TM-78480. A-7395. AVRADCOM-TR-78-33(AM)) Avail The use of workshops has been introduced as a unique element NTIS HC AOS/MF A01 CSCL 01A of some of these assessments Also included in this report is a A computational wing optimization procedure was developed brief synopsis of a method of quantifying opinions obtained through and verified iu an experimental investigation of a seml-span such group interactions Representative of the current technol- variable camber wing model in the NASA Ames Research Center ogy assessments these studies cover a broad range of socio- 14 foot transonic wind tunnel The Baley-BaRhaus transonic political factors and issues in greater depth than previously pn fow anais nd Woodelrd-Carmichael lineartheory considered in NASA sponsored studies In addition to the lessons potential flow analysis and Woodward-Carmichael linear theory cds codes were linked to Vanderplaats constrained minimization learned through the conduct of these studies, a few suggestions routine to optimize model configurations at several subsonic and for improving the effectiveness of future technology assessments transonic design points The 35 deg swept wing is characterized are provided Author by multi-segmented leadingand trailing edge flaps whose hinge lines are swept relative to the leading and trailing edges of the wing By varying deflection angles of the flap segments, camber N7-24860r# National Aeronautics and Space Administration and twist distribution can be optimized for different design Ames Research Center. Moffett Field. Calif conditions. Results indicate that numerical optimization can be LAGRANGIAN COMPUTATION OF INVISCID COM- both an effective and efficient design too The optimized PRESSIBLE FLOWS configurations had as good or better lift to drag ratios at the G H. Klopfer May 1978 60 p refs design points as the best designs previously tested during an INASA-TM-78456. A-7288) Avail NTIS HC A04/MF AOt extensive parametric study J M S CSCL 12A A Lagrangian method is developed to solve the Euler equations of gas dynamics The solution of the equations is obtained by a numerical computation with the well-known Flux-Corrected- Transport (FCT) numerical method This procedure is modified
25 N78-26391'# National Aeronautics and Space Administration N78-28173"# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif. Ames Research Center. Moffett Field. Calif. SOLUTION OF TRANSONIC FLOWS BY AN INTEGRO- STABILITY OF CHROMIUM (1il) SULFATE IN AT- DIFFERENTIAL EQUATION METHOD MOSPHERES CONTAINING OXYGEN AND SULFUR Wandera Ogana (Nairobi Univ Kenya) Jun 1978 30 p refs K TJacob (Lawrence Berkeley Lab Berkeley. Calif.). Bhogeswara (NASA-TM-78490. A-7434) Avail NTIS HC A03/MF AOl D_Rao and Howard G Nelson Jul 1978 21 p refs CSCL 20D {NASA-TM-78504. A-7508) Avail NTIS HC A02/MF A01 Solutions of steady transonic flow past a two-dimensional CSCL 07D airfoil are obtained from- a singular integro-differential -equation TheT stability of chromium sulfate in the temperature range which involves a tangential derivative of the perturbation velocity from 880 K to 1040 K was determined by employing a dynamic potential Subcritical flows are solved by taking central differences gas-solid equilibration technique The solid chromium sulfate was everywhere For supercritical flows with shocks, central differences equilibrated in a gas stream of controlled S03 potential- are taken in subsonic flow regions and backward differences in Thermogravimetric and differential thermal analyses were used supersonic flow regions The method is applied to a nonifting to follow the decomposition of chromium sulfate X-ray diffraction parabolic-arc airfoil and to a lifting NACA 0012 airfoil Results analysis indicated that the decomposition product was crystalline compare favorably with those of finite-difference schemes Cr203 and that the mutual solubility between Cr2(SO4)3 and Author Cr203 was negligible Over the temperature range-investigated. the decomposition pressure were significantly high so that chromium sulfate is not expected to form on commercial alloys containing chromium when exposed to gaseous environments N78-26795# National Aeronautics and Space Administration containing oxygen and sulfur (such as those encountered in Ames Research Center. Moffett Field, Calif coalgasification) inq ON IMPROVING THE ITERATIVE CONVERGENCE PROPER- TIES OF AN IMPLICIT APPROXIMATE-FACTORIZATION FINITE DIFFERENCE ALGORITHM Jean-Antoine Desiden (Iowa State Univ. Ames). J L Steger, N78.28410*# National Aeronautics and Space Administration and J C Tannehill (Iowa State Univ- Ames) Jun 1978 121 p Ames Research Center. Moffett Field. Calif refs STATUS AND FUTJRE PROSPECTS OF USING NUMERI- (NCA2-OR340-706) CAL METHODS TO STUDY COMPLEX FLOWS AT HIGH (NASA-TM-78495. A-7474) Avail NTIS HC AO6/MF A01 REYNOLDS NUMBERS CSCL 12A Robert W. MacCormack In AGARD Three Dimensional and The iterative convergence properties of an approximate- Unsteady Separation at High Reynolds No Feb 1978 2 p factorization implicit finite-difference algorithm are analyzed both For primary document see N78-28397 19-34) theoretically and numerically Modifications to the base algorithm Avail NTIS HC Al 1/MF A01 CSCL 20D were made to remove the inconsistency in the original implementa- Th- calculation of flow fields past aircraft configuration at tion of artificial dissipation In this way, the steady-state solution light . iy (,lds numbers is considered Progress in devising became independent of the time-step, and much larger time-steps accurate and efficient numerical methods, in understanding and can be used stably To accelerate the iterative convergence, large modeling the physics of turbulence, and in developing reliable time-steps and a cyclic sequence of time-steps were used. For and powerful computer hardware is discussed Emphasis is placed a model transomc flow problem governed by the Euler equa- on efficient solutions to the Navier-Stokes equations J M S tions. convergence was achieved wilh 10 times fewer time-steps using the modified differencing scheme. A particular form of S instability due to variable coefficients is also analyzed Author NJ78-29067"l National Aeronautics and Space Administration Ames Research Center Moffett Field Calif WIND TUNNEL INVESTIGATION OF COMPUTATIONALLY N78-26796*# National Aeronautics and Space Adm ion OPTIMIZED VARIABLE CAMBER WING CONFIGURA- Ames Research Center. Moffett Field. Calif TIONS TECHNIQUES FOR CORRECTING APPROXIMATE FINITE E G Waggoner (Vought -Corp Dallas). H P Haney (Vought DIFFERENCE SOLUTIONS Corp, Dallas). and W. F Hallhaus Jun 1978 140 p refs David Nixon Jun 1978 19 p refs Prepared in part by AVRADCOM (NASA-TM-78499. A-7491) Avail- NTIS TC A02/MF AO1 (NASA-TM-78479. AVRADCOM-TR-78-32AM) A-7394) Avail CSCL 12A NTIS HC A07/MF ACT CSCL OJA A method of correcting finite-difference solutions for the An experimental investigation was performed in the NASA effect of truncation error or the use of an approximate basic Ames Research Center 14 foot transonic wind tunnel to determine equation is presented Applications to transonic flow problems aerodynamic characteristics for several optimized configurations are described and examples are given Author of a variable camber wing model Camber and twist distributions which were computationally defined using both subsonic and transonic potential flow analysis codes linked to an optimization N78-27364*# National Aeronautics and Space Administration technique were verified The 35 deg swept wing was characterized Ames Research Center. Moffett Field. Calif by multisegmented leading and trailing edge flaps whose hinge AN EXPERiMENTAL DOCUMENTATION OF PRESSURE lines are swept relative to the leading and trailing edges of the GRADIENT AND REYNOLDS NUMBER EFFECTS ON wing The deflection angles of the flap segments could be varied COMPRESSIBLE TURBULENT BOUNDARY LAYERS therefore affording the possibility of optimizing the camber and M ._-Kussoy, C C Horstman, and M Acharya Jun 1978 twist distribution for a given design condition The test configura 11'4"p refs tions were designed using potential flow analysis codes linked (NASA-TM-78488. A-7426) Avail NTIS HC A06/MF AOl to a constrained minimization technique Camber and twist CSCL 20D distributions were optimized at lift coefficients of 0 2. 04. and Attached supersonic turbulent boundary layers with a wide 0 6 for Mach numbers of 0 6 and 0 9 8 B range of adverse pressure gradient strengths, are investigated for Reynolds numbers from 11 7 x 1 million to 314 x 1 million Surface pressure and surface shear measurements were obtained for six flow fields over the entire Reynolds number range In N78-29149*# National Aeronautics and Space Administration addition two flow fields - one with a moderate pressure gradient Ames Research Center Moffett Field. Calif and the other with a severe pressure gradient - are thoroughly ON THE POSSIBILITY OF NEGATIVE ACTIVATION documented at a single Reynolds number This experimental ENERGIES IN BIMOLECULAR REACTIONS documentation includes both mean and fluctuating profiles Richard L Jaffe Aug 1978 26 p refs throughout the flow field. and issuffictent to define the complete (NASA-TM-78509; A-7537) Avail NTIS HC A03/MF A01 flow field. including the upstream undisturbed flow region G.G CSCL 06C The temperature dependence of the rate constants for model
26 reacting systems was studied to understand some recent of an advanced supersonic transport operations is presented experimental measurements which imply the existence of negative This assessment, which was undertaken because of NASA's desire activation energies A collision theory model and classical trajectory for an up-to-date evaluation to guide programs for the development calculations are used to demonstrate that the reaction probabil- of supersonic technology and improved aircraft engine designs, ity can vary inversely with collision energy for bimolecular uses the most recent chemical reaction rate data From the reactions occurring on attractive potential energy surfaces results of the present assessment it would appear that realistic However. this is not a sufficient condition to ensure that the fleet sizes should not cause concern with regarc to the depletion rate constant has a negative temperature dependence On the of the total ozone overburden. For example the NOx emission basis of these calculations, it seems unlikely that a true bimolecular of one type designed to cruise at 20 km altitude will cause the reaction between neutral molecules will have a negative activation ozone overburden to increase by 003% to 0 12%, depending energy AR H upon which vertical transport is used These ozone changes can be compared with the predictions of a 1 74% ozone decrease (for 100 Large SSTs flying at 20 kn) made in 1974 by the - N7B-29436"# National Aeronautics and Space Administration FAA's Climatic Impact Assessment Proaram Author Ames Research Center. Moffett Field, Calif SYSTEM OPTIMIZATION OF GASDYNAMIC LASERS, COMPUTER PROGRAM USER'S MANUAL N78-31030# National Aeronautics and Space Adiilistralrori L J Otten Ill R C Saunders, Ill, and S J Morris (Langley Ames Research Center Moffett Field Calif Research Center, Hampton. Va) Apr 1978 49 p refs PIONEER 10 OBSERVATION OF THE SOLAR WIND (NASA-TM-73193. A-6865) Avail NTIS HC A03/MF AOl PROTON TEMPERATURE HELIOCENTRIC GRADIENT CSCL 20E J D Mihalov and J H Wolfe Aug 1978 15 p refs The users manual for a computer program that performs (NASA-TM-78515 A-75791 Avail NTIS HC A02/MF A01 system optimization of gasdynamic lasers is provided. Detailed CSCL 03B input/output formats are CDC 7600/6600 computers using a Solar wind isotropic proton temperature's as measured out dialect of FORTRAN Sample input/output data are provided to to 12 2 AU heliocentric distance by the Ames plasma analyzer verify correct program operation along with a program listing aboard Pioneer 10 are presented as consecutive averages over " Y three Carrington solar rotations and discussed The weighted least-squares fit of average temperature 0 hliphocentic radial distance. R. yields the power law R sup 12 Hiese average N78-29451T# National Aeronautics and Space Administration - proton temperatures are not correlated at well with Pioneer Ames Research Center. Moffett Field Calif 10s heliocentric radial distance . 86) as are the corresponding TORQUING PRELOAD IN A LUBRICATED BOLT average Zurich sunspot numbers R sub z 1 95). Consequently, H Lee Seegmiller Aug 1978 14 p refs it is difficult to isolate the spatial gradient in the Pioneer 10 (NASA-TM-78501. A-7503) Avail NTIS HC A02/MF AOl solar wind proton temperatures using that data alone Author CSCL 131 The tension preload obtained by torquing a 7/8 in diam UNC high strength bolt was determined for lubricated and dry N78-31608 # National Aeronautics and Space Administration. conditions Consistent preload with a variation of + or - 3% Ames Research Center, Moffett Field. Calif was obtained when the bolt head area was lubricated prior to HIGH ALTITUDE PERSPECTIVE each torque application Preload tensions nearly 70% greater 1978 33 p Original contains color illustrations than the value predicted with thecommonly used formula occurred (NASA-SP-427) Avail- NTIS MF A01: SOD HC $1.6.0 CSCL with the lubricated bolt A reduction to 39% of the initial preload 14E was observed during 50 torque applications without relubrica- The capabilities of the NASA Ames Center U-2 aircraft for tion Little evidence of wear was noted after 203 cycles of research or experimental programs are described for such areas tightening Author as Earth resources inventories, remote sensing data interpretation electronic sensor research and development, satellite investigative support, stratospheric gas studies, and astronomy and astrophys ics The availability of this aircraft on a cost-reimbursable basis N78-301498 National Aeronautics and Space Administration for use in high-altitude investigations that cannot be performed Ames Research Center. Moffett Field. Calif by the private sector is discussed A R H NASA/ESA CV-990 SPACELAB SIMULATION (ASSESS 2) Jul 1977 47 p Prepared in cooperation with ESA Paris N78-32029* National Aeronautics and Space Administration (NASA-TM-7S748) Avail NTIS HC AO3/MF AOl CSCL 22A Ames Research Center, Moffett Field. Calif Cost effective techniques for addressing management and CRUSTAL EVOLUTION INFERRED FROM APOLLO MAG- operational activities on Spacelab were identified and analyzed NETIC MEASUREMENTS during a ten day NASA-ESA cooperative mission with payload Palmer Dyal. William D Daily (Eyring Res Inst ) and Leonid L and flight responsibilities handled by the organization assigned Vanyan (Acad of Sci Moscow) Sep 1978 31 p refs for early Spacelabs Topics discussed include (1) management (Grant NsG-2082) concepts and interface relationships. (2) experiment selection. (NASA-TM-78524. A-7608) Avail NTIS HC A03/MF AOl (3) hardware development. (4) payload integration and checkout CSCL 03B (5) selection and training of mission specialists and payload Magnetic field and solar wind plasma density measurements specialists. (6) mission control center/payload operations were analyzed to determine the scale size characteristics of control center interactions with ground and flight problems. remanent fields at the Apollo 12. 15. and 16 landing sites (7) real time interaction during flight between principal investiga- retical mdel al the fieldplaainte tors and the mission specialist/payload specialist flight crew, involvimg-odlffusion of the remanent field into the solar plasma, and 18) retrieval of scientific data and its analysis A R H were compared to the data The information provided by all these experiments shows that remanent fields over most of the N78-3O774*# National Aeronautics and Space Administration lunar surface are characterized by spatial variations as small as N7A-30e74"s a naleroffettFisld. ace Aa few kilometers Large regions (50 to 100 kin) of the lunar Ame RSSESMEarCne MoHEt EFECali OFSUPERcrust were probably uniformly magnetized during early crustal AN ASSESSMENT OF THE EFFECT OF SUPERSONIC evolution Bombardment and subsequent gardening of the upper OZONE CONTENT layers of these magnetized regions left randomly oriented. smaller OZONE CONTENTRscale (5 to 10 kin) magnetic sources close to the surface. The I n Poppff R C Whlitten.R P Turco ( and D Associates, larger scale size fields of magnitude approximately 0.1 gammas Maina Aug Ray. Cali. ad Lf Aare measured by the orbiting subsatellite experiments and the Cahif) Aug 1978 60 p refs small scale sized remanent fields of magnitude approximately (NASA-RP-1026. A-7399) Avail NTIS HC A04/MF A01 CSCL 100 gammas are measured by the surface experiments Author 138 An assessment of the potential effect on stratospheric ozone
27 N78-328566# National Aeronautics and Space Administration temperature, volatile-rich matrix- The obvious candidates for parent Ames Research Center. Moffett Field. Calif meteoroids of this type of silicate sphere is a carbonaceous PEAKER: AN AUTOMATIC BORESIGHT PEAKING chondrite ARH ROUTINE FOR THE C-141 TELESCOPE Edwin F. Erickson. Kevin Krisciunas (Informatics. Inc. Palo Alto. NASA CONTRACTOR REPORTS Calif ). and Thomas Mathieson (Informatics. Inc. Palo Alto. Calif) Sep 1978 8 p (NASA-TM-78516. A-7584) Avail NTIS HC A02/MF A01 CSCL 20F .N78-10411"i- Sigma Research. Inc. Richland. Wash The operation of an automated procedure is detailed which STUDY OF A HIGH PERFORMANCE EVAPORATIVE HEAT maximizes the signal from a detector by pointing the telescope TRANSFER SURFACE Final Report at an astronomical source .G G Elric W Saaski and R H Hamasak 27 May 1977 82 p refs (Contract NAS2-9120) N78-32947*# National Aeronautics and Space Administration (NASA-CR-152008) Avail NTIS HC A05/MF AO1 CSCL Ames Research Center. Moffett Field. Calif 20D OPTIMIZING INDIUM ANTIMONIDE (InS) DETECTORS An evaporative surface is described for heat pipes and other FOR LOW BACKGROUND OPERATION two-phase heat transfer applications that consists of a hybrid Richard R Treffers Sep 1978 18, p refs composition of'V-grooves and capillary wicking Characteristics (NCA2-OR050-606) of the surface include Both a high heat transfer coefficient and ZNASA.TM-73273 A-7149) Avail NTIS HC A02/MF A01 high heat flux capability relative to conventional open-faced screw CSCL 03A thread surfaces With agroove density of 12 6 cm/ I and ammonia The anous noise sources that affect InSb detectors (and working fluid, heat transfer coefficients in the range of I to similar voltaic devices) are discussed and calculated Methods 2 W/sq cm have been measured along with maximum heat are given for measuring detector resistance photon loading flux densities in excess of 20 W/sq cm- A peak heat transfer detector and amplifiei capacitance amplifier frequency response, coefficient in excess of 2 3 W/sq cm was measured with a amplifier noise, and quantum efficiency A photovoltaic InSL 378 cm/i hybrid surface Author detector with increased sensitivity in the I to 56 mu region is dicussed ARH N78-19050*# Burroughs Corp. Paoli. Pa N78-4014*j National Aeronautics and Space Adni.rstration NUMERfCAL AERODYNAMIC SIMULATION FACILITY Ames Research Center. Moffett Field. Calif PRELIMINARY STUDY EXTENSION EXECUTIVE SUM- ARE THE STRATOSPHERIC DUST PARTICLES METEOR MARY Final Report ABLATION DEBRIS OR INTERPLANETARY DUST? Feb 1978 11 p Maxwell B Blanchard and Frank T Kyte (San Jose State Univ.. (Contract NAS2-9456) Calif) Aug 1978 50 p refs (NASA-CR-152106) Avail NTIS HC A02/MF AOl CSCL (NASA-TM-78507. A-7524) Avail NTIS HC AOJ/MF AOI 01A S CSCL 038 An optimized functional design of key elements of the Natural and laboratory created fusion crusts and debri- from Numerical Aerodynamic Simulation Facility was investigated The artificial meteor samples were used to develop criteria for following tasks were performed and are discussed (1) develop. recognizing meteor ablation debris in a collectioni of 5 to optimize, and describe the functional description of the custom 50 micron particles from the stratosphere These laboratory hardware. (2) delineate trade-off areas between performance. studies indicate that meteor ablation debris hon nickel-iron reliability, availability, serviceability, and programmability. meteoroids produce spherules containing taenite. wuestite (3) develop metrics and models for validation of the candidate magnetite. and hematite These same studies also indicate that system's performance. (4) conduct a functional simulation of ablation debris from chondintic meteoroids produce spheres and the system design. (5) perform a reliability analysis of the fragmentiry debris The spheres may be either silicate rich. system design, and (6) develop the software specifications to containing zoned olivine. magnetite. and glass, or sulfide rich. include a user level high level programming language, 4 containing iron oxides (e g . magnetite, wuestite) and iron correspondence between the programming language and sulfides (e g. pyrrhotite pentlandite). The fragmentar- debris may instruction set, and outline the operating system requirements be either fine-grained aggregates of olivine. magnetite. pyroxeie. Author and occasionally pyrrhotite (derived from the meteo'ite matrix) N78-19051-# Burroughs Corp Paoli. Pa or individual olivine and pyroxene grains (deivrd front meteorite NUMERICAL AERODYNAMIC SIMULATION FACILITY. mclusions). A RH PRELIMINARY STUDY EXTENSION Final Report Feb 1978 273 p N78-340214R National Aeronautics and Space Administration, (Contract NAS2-9456) Ames Research Center. Moffett Field, Calif (NASA-CR-152107) Avail NTIS HC A12/MF A01 CSCL METEOR ABLATION SPHERES FROM DEEP-SEA SEDI- CIA MENTS The production of an optimized design of key elements of M. B Blanchard D E Brownlee (California Inst of Technology. the candidate facility was the primary objective of this report Pasadena). T. E. Bunch. P. W. Hodge (Washington Univ. Seattle). This was accomplished by effort in the following tasks, (1) to and F T Kyte (San Jose State Univ. Caf) Sep 1978 45 p further develop optimize and describe the function description refs of the custom hardware: (2) to delineate trade off areas between (NASA-TM-78510. A-7549) Avail NTIS HC A03/MF AOl performance, reliability, availability, serviceability, and program CSCL 03B mability. (3) to develop metrics and models for validation of the Spheres from mid-Pacific abyssal clays (0 to 500.000 yrs candidate systems performance (4) to conduct a functional old). formed from particles that completely melted and subse- simulation of the system design. (5) to perform a reliability analysis quently recrystallized as they separated from their meteoroid of the system design, and (6) to develop the software specifications bodies, or containing relict grains of parent meteoroids that did to include a user level high level programming language a not experience any melting were analyzed The spheres were corresoondence between the programming language and readily divided into three groups using their dominant mineralogy instruction set and outline the operation system requirements The Fe-rich spheres were pioduced during ablation of Fe and Author metal-rich silicate meteoroids, The glassy spheres are considerably more Fe-rich than the silicate spheres. They consist of magnetite N78-19062 Control Data Corp. St Paul. Minn Research and an Fe glass which is relatively low in Si Bulk compositions and Advanced Design Lab and relict grains are useful for determining the parent meteor oid types for the silicate spheres Bulk analyses-of recrystallized PRELIMINARY STUDY FOR A NUMERICAL AERODYNAMIC spheres show that nonvolatile elemental abundances are similar SIMULATION FACILTY. PHASE 1: EXTENSION to chondrite abundances Analysis of relict grains identified high N R Lincoln Feb. 1978 434 p refs temperature minerals associated with a fine-grained. low (Contract NAS2-9457) (NASA-CR-152108) Avail: NTIS HC A19/MF A01 CSCL 01A
28 Functional requirements and preliminary design data wore systems were reviewed Specific comparison variables, applicable identified for use in the design of all system components and in to all modes were defined, and the functional relationships by the construction of a facility to perform aerodynamic simulation which these variables are interdependent were explored A for airframe design A skeleton structure of specifications for framework by which the set of variables may be employed for the flow model processor and monitor, the operating system. comparison of data from the individual systems was construc and the language and its compiler is presented A R H ted A R.H.
N78-29146"# Martin Mlarietta Aerospace Denver Colt.. N78-21223*# Douglas Aircraft Co Inc Long Beach Calif EXPERIMENTAL INVESTIGATION OF CONTAMINATION PREVENTION TECHNIQUES TO CRYOGENIC SURFACES AIRCRAFT CARGO COMPARTMENT FIRE TEST SIMULA- ON BOARD ORBITING SPACECRAFT TION PROGRAM Final Report, Oct. 1974 - Jan. 1977 M A Hetrick R 0 Ranianen. E B Res. and J. F Froechtenigt R E Blumkte Jan 1977 84 p refs Aug 1978 96 p refs (Contract NAS2-8699) (Contract NAS2-9816) (NASA-CR-l5l9: MDC-J747 t) Avail: INTIS (NASA-CR-152171, MCR-78-578) Avail NTIS HC A05/MF AO1 CSCL 11D HC AOS/MF A01 CSCL 22B The objective of the test was to assess fire containment and fire extinguishment in the cargo by reducing the ventilation Within the simulation limitations of on-orbit conditions ii through the cargo compartment Parameters which were measured wasdemonstrated that a helium purge system could be an effective included ignition time. burnthrough time. and physical damage method foi reducing the incoming flux of contaminant species to the cargo liner. composition of selected combustible gases. Although a generalized purge system was employed in conjunction temperature-time histories, heat flux, and detector response The with basic telescope components the simulation provided data ignitor load was made of a typical cargo consisting of filled that could be used for further modeling and design of a specific cardboard canons occupying 50% of the compartment volume helium iniection system Experirierial ielescope pressures Author required for 90% attenuation appeared to be slightly higher (factor of 2 to 51. Cooling the helium purge gas and telescope components from 300 to 140 K had no measurable effect on stopping efficiency of a given mass flow of hshun, from the diffuse iniector J A M N78-22000#D Santa Barbara Research Center- Goleta Calif CONTINUED DEVELOPMENT OF DOPED-GERMANIUM N78-32991" National Aeronautics and Space Administration. PHOTOCONDUCTORS FOR ASTRONOMICAL OBSERVA. Ames Research Center, Moffett Field Calif TIONS AT WAVELENGTHS FROM 30 TO 120 MICROME ACCELERATION AND HEAriNG OF THE SOLAR WIND TERS Final Technical Report Aaron Sarnes In JPL A Cose-up of the Sun 1 Sep 1978 P R Bratd N N Lewis and L E Long 24 Apr 1978 61 p p 334-344 refs (For pnmary document see N78-32964 23-921 refs Avail NTIS HC A25/MF A01 CSCL 03B (Contract NAS2-9599) Some of the competing theories of solar wind acceleration (NASA-CR-152125) Avail NTIS HC A04/MF A01 CSCL and heating are reviewed, and the observations that are required S 03A to distinguish among them are discussed In most cases what The development of doped-germanium detectors which ha e is required is measurement of plasma velocity and temperature' optimized performance in the 30- to 120-mu m wavelength and magnetic field, as near the sun as possible- and certainly range and are capable of achieving the objectives of the infrared inside 20 solar radii. another critical aspect of this question is astronomical satellite (IRAS) space mission is discussed. Topics determining whether a turbulent envelope exists in this inner covered include the growth and evaluation of Ge Ga and Ge Be region, and if so. defining its properties Plasma and magnetic crystals, procedures for the fabrication and testing of detectors observations from the proposed Solar Probe mission would thus irradiance calculations detector responsivity, and resistance yield a quantum jump in our understanding of the dynamics of measurements through MOSFET. Tes: data are presented in graphs the solar wind Author and charts. Author
N78-23117*.# Maivex Corp. Saratoga. Calif NASA/ESA CV-990 SPACELAB SIMULATION (ASSESS 2) Final Report o R Muihollid t, M Mndio., aind J F Heners Jan 1978 N78-33127"# McDonnell-Douglas Astronautics Co. St Louis. 198 p refs Mo (Contract NAS2-9514) PIONEER JUPITER ORBITER PROBE MISSION 1980. (NASA-CR-152122) Avail NTIS HC A09/MF AOl CSCL PROBE DESCRIPTION 22A R E DeFrees 8 Nov 1974 51 p t To test the validity of the ARC approach to Spacelab several (Contract NAS2-8377) missions simulating aspects of Spacelab operations have been (NASA-CR-137591) Avail. NTIS HC A04/MF AOl CSCL conducted as part of the ASSESS Program Each mission was 22A designed to evaluate potential Shuttle/Spacelab concepts in The adaptation of the Saturn-Uranus Atmospheric Entry Probe increasing detail For this mission, emphasis was placed on (SUAEP) to a Jupiter entry probe is summarized This report is development and exercise of management techniques planned extracted from a comprehensive study of Jovian missions. for Spacelab using management participants ron NASA and atmospheric model definitions and probe subsystem alternatives ISA who have responsihilities for Spacvlab I which will be G G launched u. 9q8, Aitnor
N78-28994S# Operations Research. Inc- Silver Spring, Md N78-333798# TRW Defense and Space Systems Group Rednndo PHASE 1. DEFINITION OF INTERCITY TRANSPORTATION Beach. Calif COMPARISON FRAMEWORK VOLUME 2: METHODOL- EXTENDED DEVELOPMENT OF VARIABLE CONDUCTANCE OGY Final Report HEAT PIPES Final Raport ,9 Jul 19'!S 251 p refs D Antoniuk. D K Edwards and E E. Luedke Sep 1978 Contract NAS2-9815) 56 p NASA-CR-152152-VoI-2. ORI-TR-129B-Vol-2) Avail. NTIS -IC A12/MF A01 CSCL 1SF Categories of cost and service measures that will appropriately define the characteristics of all intercity transportation systems were established Previous methods of comparing transportation
29 (Contract NAS2-9834) (NASA-CR-152183 TRW-31183-6001 RU-0O) Avail NTIS HC A04/MF AOl CSCL 20D A high-capacity vapor-modulated heat pipe was designed and tested In 1977, a program was undertaken to use the aforementioned heat pipe to study protection from freezing-point failure increase control sensitivity, and transient behavior under a wide range of operating conditions in order to determine the full performance--potential of the heat pipe A new concept. based on the vapor-induced-dry-out principle, was developed for passive feedback temperature control as a heat pipe diode This report documents this work and describes (1) the experimental and theoretical investigation of the performance of the vapor modulated heat pipe. and (2) the design, fabrication and test of the heat pipe diode GY
N78-33384*# Rockwell International Corp. Downey, Calif Satellite Systems Div DEVELOPMENT OF A CRYOGENIC ROTATING HEAT PIPE JOINT Fini Report. Nov. 1977 - Sep 1978 Sep 1978 72 p refs (Contract NAB2-9726) (NASA-CR-152188. SD-78-AP,0124) Avail NTIS HC A04/MF A01 CSCL 20D The performance of two critical technology components required for a continuously rotatable heat pipe (1) a low-leakage rotatable coupling for the heat pipe pressure vessel, and (2) a rotatable internal wick, is reported Performance and leakage requirements were established based on 12 months operation of a cryogenic rotatable heat pipe on a satellite in earth orbit GY
JOURNAL ARTICLES, BOOKS AND CHAPTERS OF BOOKS S
surface, the mean temperature is about 145 K, and the profiles A78-10405 * Simultaneous determination of rotational and exhibit wavelike structures with a peak-to-peak amplitude of 35 K translational temperatures of OH/2 Pi/int a agas discharge.tthe C, C.Wang and aatmosphere vertical scale at of4500 about A 20and km. 7500 The ratioA is ofconsistent the refractivity with the of (Ford Motor Co, Dearborn, Mich ) and fK. Killinger (Michigan, atmospheric composition measured by Viking I From the 'central University, Ann Arbor, Mich.) Physical Review Letters, vol 39, Oct. flash' - a bright feature in the light curve midway between immersion 10, 1977, p 929-932 15 refs NSF-supported research, Contract No. and emersion - an optical depth at 4500 A of 3.3 + or - 1.7 per km NAS2-8797 atm (about 0 23 per equivalent Martian air mass) is found for the A simultaneous determination of the rotational and translational atmosphere about 25 km above the mean surface near the south temperatures of OH(2 Pi) in a water-vapor discharge is reported. polar region This large value and its weak wavelength dependence These temperatures were determined by measuring the strength and rule out Rayleigh scattering as the principal cause of the observed line shape of the absorption lines in the 2 Pi (v = 0) - 2 Sigma(+) (v = extinction (Author) 0) transitions of OH using a CW tunable laser it was found that the rotational distribution was thermalized, but the corresponding rotational temperature was much lower than the translational temperature Possible implications of these results are discussed (Author) A78-1 1403 * Some Martian volcanic features as viewed from the Viking orbiters. M. H Carr (US. Geological Survey, Branch of Astrogeology, Menlo Park, Calif.), R Greeley (NASA, Ames Re search Center, Moffett Field, Calif.), K R Blasius (Planetary Science A78-1097 Occultation of Epsilon Geminorurm by Mars 1 Institute, Pasadena, Calif.), J. E Guest, and J B. Murray (London,
- The structure and extinction of the Martian upper atmosphere. J. L. University, Observatory, Mill Hill, , England) Journal of Elliot, R G. French,EllotRE Dunham,Gunhm,Frnch P .JJ Gierasch,iersch .2.J.Vevrka Veverka. CCGeophysical refs Research, vol 82, Sept 30, 1977, p 3985-4015. 32 Church, and C Sagan (Cornell University, Ithaca, N Y I Astro- r A summary is presented of the results of some new observations physical Journal, Part 7,vol 217, Oct 15. 1977, p 661-679 32 refs on Martian volcanic features made from the Viking orbiters. Most of NSF Grant No. MPS-75-06670, Grants No. NsG-7243, No. these observations are concerned with the Tharsis and Alba regions. NGR-33-010-082, No. NGR-33-010-186, No NsG-2174, No The youth, size, and style of the volcanic features in these areas NsG-7126 render them particularly susceptible to analysis. Excellent coverage The occultation of Epsilon Geminorum by Mars on April 8. was also acquired of Apollnaris Patera It has many features of the 1976. was observed at three wavelengths and 4-ms time resolution Tharsis shields, with a cliff around its circumference and a large with the 91-cm telescope aboard NASA's G. P. Kuiper Airborne central caldera. Olympus Mons and its vicinity are examined, taking Observatory Temperature, pressure, and number-density profiles of into account the shield of Olympus-Mons, mass movement features the Martian atmosphere were obtained for both the immersion and along the basal scarp, the basal plains, the relative ages of Olympus emersion events Within the altitude range 50-80 km above the mean Mons and the basal plains, and grooved terrain. G.R.
30 A78-13752 - On the relative locations of the bow shocks of The collisionless dissociation of SF6 has been studied using the terrestrial planets. C T Russell (California, University, Los simultaneous irradiation by two frequencies from a C02 laser which Angeles, Calif ) Geophysical Research Letten, vol 4, Oct 1977, p. are both nearly resonant with the SF6nu3 absorption band. It was 387-390. 21 refs. Contract No NAS2.8808; Grant No found that the dissociation was enhanced, and occurred over awider MGR-O5-067-004. frequency range, than for single frequency dissociation No threshold The observed bow shock encounters at Mercury, Venus and effect was observed for a weak resonant and a much higher energy Mars are least square fit using the same technique so that their sizes field pumping slightly off-resonance. For such two frequency and shapes can be intercompared The shock front of Mercury most irradiation, the peak in the dissociation curve was found to be shifted resembles the terrestrial shock in shape, and the shock stand off to lower frequencies with respect to that for single frequency distance is consistent with the observed moment. The shapes of the dissociation. (Author) Venus and Mars shock fronts more resemble each other than the earth's and the stand off distances are consistent with direct interaction of the solar wind with the ionosphere on the dayside The A78-15204 * Food and oxygen requirements for growing Venus shock is closer to the planet than the Mars shock suggesting mice and turtles after hypergravitational development. C C Wunder, more absorption of the solar wind at Venus. (Author) W. J. Moressi (Iowa. University, Iowa City. Iowa), C H Dodge (Library of Congress, Washington, D C), and K. M Cook (Coe College, Cedar Rapids, Iowa). In Life sciences and space research A78-13845 * Demand-type gas supply system for rocket XV, Proceedings of the Open Meeting of the Working Group on borne thin-window proportional counters. L W Acton, R Caraval- Space Biology. Philadelphia, Pa, June 8-19, 1076 [A78 ho, R. C. Catura. and E G Jokli (Lockheed Research Laboratories, 15177 04-51) Oxford and New York. Pergamon Press, 1977, p. Palo Alto, Calif ). Review of Scientific Instruments, vol. 48, Nov. 245-249 24 refs Grants No NIH.GM-10093; No. NGR-16-001-031, 1977. p 1604-1506 Research supported by the Lockheed Indepen- Contract No NAS2.6064 dent Research Program, Contracts No. NAS2-6723, No. NASw-2660. A simple closed loop control system has been developed to A78-15267 * Survey of adaptive image coding techniques. maintain the gas pressure in thin-window proportional counters during rocket flights This system permits convenient external A labibi (TRW Defenso and Spae SystemsGroup, Redondo each, control of detector pressure and system flushing rate The control Caif) IEEE Transactions on Conm catons, vol. COM-25, Nov assystem the existingis activated system at launch pressure. with Inflight the sealing control of toa reference plus or minusvolume 2 1977,The p. 1275-1284general problem 46 refs. of Contract image dataNo NAS2-8394compression is discussedu torr at a working pressure of 760 torr has been achieved on s2 briefly with attention given to the use of Karhunen-Loeve trans rocket flights (Author) forms, suboptimal systems, and block quantization A survey isthen conducted encompassing the four categories of adaptive systems (1) adaptive transform coding (adaptive sampling, adaptive quantization, etc ), (2) adaptive predictive coding (adaptive delta modulation, A78-14622 * t The instability of the thin vortex ring of adaptive DPCM encoding. etc ), [3) adaptive cluster coding (blob constant vorticity S E. Widnall (MIT. Cambridge, Mass) and C .Y algorithms and the multispectral cluster coding technique), and (4) Tsai (NASA, Ames Research Center, Moffett Field, Calif, MIT, adaptive entropy coding BJ_ Cambridge, Mass-). Royal Society (London), Philosophical Transac tions, Series A, vol. 287, no 1344, Oct- 13, 1977, p 273 305 22 refs NSF Grant No ENG-7414978 A78-16180 *f Effect of a nonconstant efm-alpha/ on the A theoretical study indicating that vortex rings at moderate stability of rolling aircraft. B. Davari (NASA, Ames Research Center, Reynolds numbers are unstable to azimuthal bending waves s Moffett Field, California, University, Berkeley, Calif) and E V presented Only the case of athin vortex ring with acore of constant Laitone (California, University, Berkeley, Calif-) JournalofAircraft. vorticity in an inviscid flow is examined. The disturbance flow and vol 14, Dec 1977, p 1169-1174. 15 refs Grant No the mean flow of the vortex ring are derived asasymptotic solutions NGR.05-003-451. near the core, the stability analysis is developed completely for a An analytical study is carried out of the behavior of modern certain class of bending waves that are unstable on aline filament in high-speed aircraft of nertially slender configurations in maneuvers the presence of strain The vortex ring is found to be always unstable involving large rates of roll. Inertia cross-coupling, as well as alinear for at least two wavenumbers for which waves on a line filament of variation of longitudinal static stability (Clm-alpha/) with angle of the same vorticity distribution would not rotate. Published experi- attack, are considered. The steady-state solutions of the nonlinear mental results are cited to support these conclusions J.M8 equations of motion, based on principal inertia axes, are studied to obtain useful information on the response behavior of the state variables during roll maneuvers. It is shown that, in addition to the A78-14651 * Diagrammatic evaluation of the density opera- critical values of aileron deflection that have been previously found tor for nonlinear optical calculations S Y Yee. T K Gustafson to limit a steady-state roll with constant longitudinal static stability, (California, University. Berkeley, Calif ). S A. J. Druet, and J.-P E. there can be two new critical values introduced by a linear decrease Taran (ONERA, Chtttillon-sous-Bagneux, Hauts de-Serne. France). of the absolute value of longitudinal static stability with angle of Optics Communications, vol 23. Oct 1977, p 1.7 11 refs NSF attack. For aileron deflections near these critical values, the response Grant No ENG-72-03860-AO1, Grants No DAHC94-75-C-0095, No of the aircraft exhibits violent oscillations and dangerous peak loads, NsiG.2151 due to the cross-coupled motion accompanying a roll maneuver Time ordered diagrammatic representations are shown to pre. These critical values define a new range of aileron deflections in cisely define and to simplify calculations of radiative perturbations which no steady-state roll ispossible. (Author) to the density matrix Nonlinear optical susceptibilities, here exemplified by that of CARS, can be obtained by simple propagator rules An interpretation of transient Raman scattering in terms of A78-16454 Quantum mechanical theory of a structured time ordered contributions is also discussed (Author) atom diatom collision system - A + BC1-Sigma/. P L DeVnes (Rochester, University, Rochester, N Y.) and T F. George Journal A78-14655 * Collisionless dissociation of SF6 using two of Chemical Physics, vol. 67, Aug. 15, 1977, p. 1293.1301 23 refs resonant frequency C02 laser fields I. C. Gower and T. K NSF Grant No. CHE-75-06775-AOI, Contract No. Gustafso (California, University, Berkeley, Calif.). Optics Com F44620-74-C-0073, Grant No NsG-2198 2 munications, voi 23, Oct. 1977, p 69-72. 22 refs Grants No The problem of a -p state atom colliding with a singlet sigma NsG-2151; No NCA2.OY-050-701 state diatom, which involves multiple potential surfaces, isinvestigat ed Within a diabatic representation for the electronic degrees of
31 freedom (plus spin-orbit interaction), coupled scattering equations imaging data show complex detail within the Red Spot is well as are derived in both space-fixed and body-fixed coordinate systems indications of flow around it' Bright spots with trailing plumes are Coefficients, analogous-to Percival-Seaton coefficients, are obtained seen in the Equatorial Zone The North Polar Region is devoid of Approximations to the exact equations, including angular momenta belt structure, but numerous irregular cells are seen in red light. The decouplhng approximations, are discussed for both the space-fixed Galilean satellites were imaged with a resolution of several hundred and body-fixed formalisms. (Author) kilometers (Author)
A78:17612* # Displacement thickness distributions in tran- 0,78-18274 * # Unsteady transonic flow computations -A R. sonic flows about 3-D wings. W. Kordulla (NASA, Ames Research Scebass. N. J. Yu, and K -Y. Fung (Arizona, University, Tucson, Center, Moffett Field, Calif) In Conference on Numerical Methods Oriz.). NATO, AGARD, Symposium on Unsteady Aerodynamics, in Fluid Mechanics, 2nd, Cologne, West Germany, October 11-13, 2ttawa, Canada, Sept 26-28, 1977, Paper 18 p 31 refs Grants No 1977, Proceedings (A78-17601 05-34) Cologne, Deutsche For- 4LF-AFOSR-76-2954B; No NsG-2112; Contract No. schungs- und Versuchsanstalt fur Luft- und Raumfahrt, 1977, p. N0014-76-C-0182 81-88 13 refs The numerical procedures previously developed for computing The transonic 3-D inviscid small-perturbation solution of Bailey nonlinear and time-linearized small-perturbation unsteady transonic and Ballhaus is combined with a finite-difference solution for flows are briefly reviewed, and the effects of unsteady modes of Prandtlrs boundary-layer equations in order to include viscous motion on two-dimensional transonic flows are evaluated The effects. The inviscid-viscous interaction is modeled by means of the numerical procedure used comprises an alternating-direction implicit displacement surface, which can be thought of as the effective body scheme and treats shock waves as discontinuities in the flow. surface seen by the inviscid flow. Displacement thickness, lift, and Comparison of the time-linearized results with fully nonlinear pressure distributions resulting from the combined solution are calculations delineates their range of applicability The unsteady presented for transonic flows about the RAE 101 A wing and a behavior due to harmonic pitching and flap oscillations of an NACA Lockheed transport wing, both at small angles of attack The airfoil is also examined. S D influence of changing arbitrarily the start of transition on the displacement surface and lift is discussed for the RAE wing flow. (Author) A78-18732 * On determining magnetospheric diffusion co efficients from the observed effects of Jupiter's satellite lo. M F A78-17837 f Absorption measurements of OH using a CW Thomsen, C. K. Goertz, and J. A. Van Allen (Iowa, University, Iowa tunable laser. D K Killinger and C C_ Wang (Ford Motor Co., City, Iowa) Journal of Geophysical Research, vol 82, Dec 1. 1977, Dearborn, Mich ). Chemical Physics Letters, vol. 52, Dec. 1, 1977, p. p 5541-5550 41 refs NSF Grant No. ATM-72-01282; Contract No. 374-376 7 refs. NSF-supported research; Contract No. NAS2-8797 NAS2-6553 Absorption of OH was measured using a CW tunable laser A method is derived for determining the radial diffusion Results indicate that this technique, when combined with frequency coefficient from observed satellite effects of the inner Jovian modulation, promises a sensitivity of 100,000 molecules/cu cm for satellites on the energetic particle fluxes The method is based on OH monitoring in the atmosphere (Author) data from L values which are significantly removed from the actual S sweeping region With regard to the large losses to the protons at to's L shell, it is suggested that in addition to satellite sweepup, the losses A78-17881 Toroidal tank evaluation D. A Fester and j. may be associated with an enhanced precipitation due to resonant E Anderson (Martin Marietta Aerospace, Denver, Colo.) Society of interaction with ton cyclotron waves near Io's orbit It is noted that Allied Weight Engineers, Annual Conference. 36th. San Diego. Calif. such additional loss mechanisms may also apply to electrons, and May 9.12, 1977, Paper 9 refs Contract No NAS2-7489 that such losses may significantly affect the estimated diffusion The reported study had been conducted to determine the coefficient S C.S feasibility of developing toroidal tanks for an auxiliary propulsion system that could be integrated into a Pioneer spin-stabilized spacecraft The system evaluated consisted of two toroidal tanks A78-18874 The composition of Phobos - Evidence for equipped with surface tension devices One tank is intended for carbonaceous chondrite surface from spectral analysis. K. D. Pang nitrogen tetroxide, the other for monomethylhydrazirie The study (Planetary Science Institute, Pasadena. Calif ), J. B Pollack (NASA, included the definition of a propellant acquisition system concept Ames Research Center, Moffett Field, Calif ). J Veverka (Cornell that could satisfy the requirements of a spinning tank. It was found University, Ithaca. N.Y ). A. L. Lane. and J. M Ajello (California that an oxidizer tank spin rate of 76 rpm and a fuel tank spin rate of Institute of Technology, Jet Propulsion Laboratory, Pasadena, 110 rpm would be required to produce liquid loss from the Calif.) Science, vol 199, Jan 6, 1978, p 64-66 35 refs NASA acquisition system during spacecraft operation. An investigation supported research showed that toroidal tanks can be fabricated with present technology In connection with a need for more definitive information using either titanium or aluminum alloys The preferred material concerning the composition of Phobos in a study of its origin, an would be titanium because of its significantly higher strength G.R ultraviolet-visible-ifrared reflectance spectrum of the Martian satel lite was compiled from the Mariner 9 ultraviolet spectrometer, Viking lander imaging, and ground-based photometric data The by comparing A78-18173 The Pioneer 11 imaging experiment of Jupiter probable surface composition of Phobos was deduced of known W Swindell and J. Fountain (Arizona, University, Tucson, Ariz ) In. the obtained spectrum with the spectra of asteroids Space research XVII; Proceedings of the Open Meetings of Working composition The considered data show that the reflectivity of Groups on Physical Sciences, June 8-19, 1976 and Symposium 6n Phobos is flat from 1100 to 400 nm but decreases sharply in the spectrum is Minor Constituents and Excited Species, Philadelphia, Pa , June 9, ultraviolet to about 1 percent at 212 nm The reflectance 10, 1976 A78-18101 05-42) Oxford and New York, Pergamon similar to the spectra of asteroids Ceres and Pallas which weredound 68 7 7 0 1 8 Press, 1977, p. - . refs. Contract No. NAS2-6265 to have surface compositions similar to that of carbonaceous Phobos is Pioneer 11 flew by Jupiter in December 1974 and obtained chondrites It is concluded that the surface composition of The results of the several hundred images of the planet It is presently targeted for also similar to that of carbonaceous chondrites for Mars and Phobos. encounter with Saturn in 1979. The imaging photopolarimeter investigation point to different modes of origin recorded spin-scan images with high photometric accuracy It also G R recorded polarimetric and zodiacal-light data Careful design of the instrument resulted in excellent performance in the Jovian radiation A78-18875 * Multicolor observations of Phobos with the environment Imaging, data were displayed to maintain the proper Viking lander cameras - Evidence for a carbonaceous chondrtic shape of the planet. Color images were made by synthesizing green - composition J B. Pollack, D Colburn (NASA, A- Research data from red and blue data Pictures created from Pioneer 11 Center, Theoretical and Planetary Studies Branch, M,,ett Field,
32 Calif ). J Veverka (Cornell Unmversty. Ithaca, N Y), K. Pang tion technique is employed so that the small grid sizes required for (Planetary Science Institute, Pasadena, Calif ), A L Lane, and J M- spatial accuracy and viscous resolution do not impose stringent Aiello (California Institute of Technology, Jet Propulsion Labora- stability limitations. Results obtained from the program include tory. Pasadena. Calf ) Science. vol 199, Jan 6, 1978, p 66 69 16 transonic invScid and laminar-turbulent solutions about simple body refs configurations Comparisons with existing theories and experiments The reflectivity of Phobos has been determined in the spectral are made Numerical accuracy and the effect of three dimensional region from 0.4 to 1 I micrometers from images taken with a Viking coordinate singularities are also discussed (Author) lander camera. The reflectivity curve is flat in this spectral interval and the geometric albedo equals 0 05 + or - 0 01 These results, together with Phobos's reflectivity spectrum in the ultraviolet, are A78-20632 * 'S Calculation of unsteady transonic flows using compared with laboratory spectra of carbonaceous chondrites and the integral equation method 0 Nixon (NASA, Ames Research basalts The spectra of carbonaceous chondrites are consistent with Center, Moffett Field, Calif ) American InstituteofAeronauticsand the observations, whereas the basalt spectra are not. These findings Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, raise the possibility that Phobos may he a captured object rather Jan. 16-18, 1978, Paper 78.13 12 p. 13 refs than anatural satellite of Mars (Author) The basic integral equations for aharmonically oscillating airfoil in a transonic flow with shock waves are derived, the reduced frequency is assumed so be small The problems associated with A78-19768 - Radiation pressure and Poynting-Robertscn shock wave motion are treated using astrained coordinate system drag for small spherical particles S Soter (Cornell University, Ithaca. The integral equation is linear and consists of both line integrals and N Y), J A Burns (NASA, Ames Research Center. Moffett Field. surface integrals over the flow field which are evaluated by Calif ) and P L Lamy (CNRS, Laboratoire d'Astronomie Spatiale, quadrature This leads to a set of linear algebraic equations that can Marseille. France) In: Comets, asteroids, meteorites. Interrelations, be solved directly. The shock motion is obtained explicitly by evolution and origins, Proceedings of the Thirty-ninth International enforcing the condition that the flow is continuous except at a shock Colloquium, Lyons. France, August 17-20, 1976 (A78-19751 06 88) wave Results obtained for both lifting and nonlifting oscillatory Toledo, Ohio, University of Toledo, 1977, p 121-125 5 refs. flows agree satisfactorily with other accurate results (Author) Robertson's expression for the velocity-dependent effect of solar radiation on the motion of small particles is difficult because of its dependence on relativistic considerations, and it is also deficient A78-20730 * ' Aerothermodynamic environment for Jovian in that it assumes perfectly absorbing particles The present paper entry with silica heat shield. M. J Green (NASA, Ames Research gives a heuristic derivation of the Poynting-Robertson effect. Center. Moffett Field, Calif.) and W. E_ Niclet (Acurex Corp, Robertson's expression for perfectly absorbing particles isobtained Mountain View, Calif.) American Institute of Aeronautics and but on a much simpler physical basis, and an expression is also Astronautics, Aerospace Sciences Meeting, 16th, Huntville, Ala, obtained for aparticle that in general scatters, transmits, and absorbs -Jan. 16-18, 1978, Paper 78-186 16 p. 15 refs light Some numerical results on the solar radiation forces felt by Solutions are presented for the stagnation-region shock-layer small particles of cosmochemrically important compositions are given equations, including radiative transfer with spectral lines and silica PTH_ ablation during Jovian entry Results for variations of entry angle, sphere-cone configuration, and atmospheric model are given The effect of silica ablation on the radiative and convective surface A78-19895 The prediction of toxic atmospheres from heating is correlated with the ratio of the wall to free-stream mass decomposing polymers. A Buchler and C J. Hilado (San Francisco, flux. Correlations are also given for spectral distributions- The effect University, San Francisco, Calif ). Journal of Fire and Flammability, of newly obtained SiO radiation properties on the surface heating is vol 8, Oct 1977, p 478493 5 refs Grants No NsG-2039; No examined (Author) NsG-2164 The generation of carbon monoxide from polymehyl meth. acrylate and polyethylene, and of hydrogen chloride from polyvinyl A78-20741 * 5 Reynolds number and pressure gradient effects chloride, was calculated Calculations were made for various amounts on compressible turbulent boundary layers. M Acharya, M. I of polymer evolving gaseous products into a 60 cu ft compartment Kussoy, and C.C Horstman (NASA, Ames Research Center, Moffett (Author) Field, Calif.). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville. Ala ,Jan 16-18, 1978, A78-20223 Signal-to-noise ratios for stellar occultations Paper 78-199. 17 p 29 refs. by the rings of Uranus, 1977-1980. J L Elliot (Cornell University, A detailed investigation of attached supersonic turbulent bound Ithaca, N Y.). Astronomical Journal, vol 82. Dec 1977, p ary layers over an extensive range of Reynolds numbers (12 x 10 to 1036-1038 13 refs Grants No NsG-2174, No NsG-7126. the 6th to 314 x 10 to the 6th) is presented Experimental Approximate signal-to-noise ratios are calculated for 12 stellar measurements were obtained for adverse pressure gradients ranging in occultations by the rings of Uranus during 1977-1980. Four of the magnitude from those of previous investigations to those approach stars are apparently bright enough to permit observation of the ing separation The measurements include mean values of surface epsilon-ring occultations with a large telescope For the best of these pressure and skin-friction, mean-flow profiles, and profiles of the events, occultations by rings alpha through delta should also be three turbulent velocity fluctuation components and turbulent shear observable with a large telescope, and epsilon ring occultationsa stress Numerical solutions, employing three turbulence models of sgnal-to-noseshould be detectable ratios are with given smallerto ad potentialtelescopes observers Formula$ inevaluating for the ofvarious the measureddegrees of flow complexity fields Generally, have been it comparedwas found with that the the details more ths qualty o the results they an expect to obtain with their own sophisticated turbulence models are superior to a mixing length pothetlit expect to(wheir) model for predicting the Reynolds number and pressure gradient effects However, some details of the turbulent fluctuations as well as the exact Reynolds number trends indicated by the data were not A78-20630 * On implicit finite-difference simulations of accurately predicted with any of the turbulence models considered three dimensional flow. T. H. Pulliam and J L Stager (NASA, Ames (Author) Research Center, Moffett Field, Calif ) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, A78-20776 Thin-layer approximation and algebraic model Huntsville, Ala, Jan 16-18, 1978, Paper 78.10 12 p 31 refs for separated turbulent flows B Baldwin and H. Lornax (NASA. An implicit finite difference procedure for unsteady three- Ames Research Center. Moffett Field. Calif ) American Institute of dimensional flow capable of handling arbitrary geometry through the Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, use of general coordinate transformations is described Viscous Huntsville, Ala,Jan 16.18. 1978, Paper 78-267.9 p 13 refs effects are optionally incorporated with a 'thin layer' approximation An algebraic turbulence model for two- and three dimensional of the Naver-Stokes equations An implicit approximate factorize- separated flows is specified that avoids the necessity for finding the
33 flow over an airfoil. Separation and reattachment points from A rapid numerical scheme is used to solve the complete numerical Navier-Stokes solutions agree with experiment within one mass-averaged Naver-Stokes equations for supersonic turbulent flow boundary-layer thickness Use of law-of-the-wall boundary condi- over athree-dimensional compression corner. A simple eddy viscosity tions does not alter the predictions significantly. Applications of the model is developed, and the interaction of aswept shock wave and a model to other cases are contained in companion papers (Author) three-dimensional turbulent-boundary layer is studied. Good agree ment is obtained between the present results and experimental measurements for the case of a wedge-withan.angle of-6.deg on-a A78-21624 * Thermodynamic processes-induced-by coher- flat-plate sidewall. For the case of a 12-deg wedge angle, the ent radiation M Garbuny (Westinghouse Research and Development computed results do not show the existence of apeak pressure found Center, Pittsburgh, Pa ) Journal of Chemical Physics, vol. 67, Dec experimentally. However, the range of interaction, the plateau 15,1977, p. 5676-5687. 29 refs. Contract No. NAS2-9185 pressure, and the peak heat transfer are closely predicted for all It is shown by quantum statistics that under certain stated cases The high heat transfer near the axial corner is due to the conditions the entropy of coherent radiation is zero and it is still thinning of the boundary layer and inflow of fresh high-momentum negligible for multimode laser operation. This makes possible gas fluid. The heat transfer is relieved through pressure reduction and kinetic processes which, to a small extent, have already been boundary-layer thickening. (Author) observed or even utilized, but which can be greatly enhanced by an optimized choice of molecular structures and radiation conditions. Radiative cooling of gases is discussed in detail The conditions for A78-22595 * ; Behavior of a turbulent boundary layer sub maximum heat withdrawal are derived, and it is proposed that the jected to sudden transverse strain. H. Higuch (Dynamics Tech processes of cooling and relaxation heating can be sufficiently nology, Inc, Torrance, Calif and M. W Rubesin (NASA, Ames separated in time to achieve certain effects and thermodynamic Research Center, Moffett Field. Calif.) American Institute of cycles One of these is the complete conversion, possible inprinciple, Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, of coherent radiation into work This concept is based on a heat Huntsville, Aia,Jan 16-18, 7978, Paper 78-201 20 p 12 refs pump process followed by heat-to-work conversion, the heat rejected Data from two experiments on the development of the being just equal to that withdrawn by radiation. The conditions for components of the Reynolds stress tensor after a sudden application complete conversion turn out to be the same as for maximum heat of transverse strain are compared Computations were based on four withdrawal. The feasibility of these processes depends on the degree different turbulence models: a first-order mixing length model, a to which practical conditions can be met, and on the validity of second-order two-equation eddy viscosity model, and two second certain assumptions which have to await experimental verification, order Reynolds stress models The second-order models do not (Author) produce dramatic improvements over the simple mixing length model The Reynolds stress models still need development to A78-22575 * I Computational wing optimization and wind represent the physics of shear-strained-turbulence well. Finally. it is tunnel test of semi-span model H P Haney, E. G. Waggoner demonstrated that the assumption of a scalar eddy viscosity, often (Vought Corp, Dallas, Tex.), and W F. Ballhaus (NASA, Ames used engineering calculations Of three-dimensional boundary Research Center, Computational Fluid Dynamics Branch, U S Army, ayers is quite reasonable (Author) Air Mobility Research and Development Laboratory, Moffett Field, Calif I. American Institute.of Aeronautics and Astronautics, Acro space Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, -A78-22602 * # Shock-tube studies of atomic silicon emission Paper 78-102. 7 p. 13 refs. in the spectral range 180 to 300 nm. S G. Prakash (Stanford A computational transonic wing design procedure has beer University, Stanford, Calif.) and C Park (NASA, Ames Research developed and verified by a wind tunnel test of a variable cambei Center, Entry Technology Branch, Moffett Field, Calif.) American semi span wing model. The Bailey Ballhaus transonic potential floe Institute of Aeronautics and Astronautics, Aerospace Sciences analysis code linked to Vanderplaat's constrained minimizatior Meeting, 16th, Huntsville, Ala, Jan. 16-18, 1978, Paper 78-234. 10 routine was used to optimize test configurations at 0 9 Macl- p. 17 refs Grant No. NsG-208S number Based on wind tunnel test results, computationally opti Emission spectroscopy of shock-heated atomic silicon was mized designs were as efficient as the best configurations determinec performed in the spectral range 180 to 300 rm, in an environment by previous parametric testing and performed better at off-desigr simulating the ablation layer expected around a Jovian entry probe points. Wind tunnel wing pressures agreed well with predictions fror with asilica heat shield. From the spectra obtained at temperatures the improved Bailey-Ballhaus code at moderate CL's. Computational from 6000 to 10,000 K and electron number densities from 1 optimization was shown to be an effective transonic wing design quadrillion to 100 quadrillion per cu cm, the Lorentzian line-widths tool. (Author) were determined The results showed that silicon lines are broadened significantly by both electrons (Stark broadening) and hydrogen atoms (Van der Waals broadening), and the combined line-widths are much larger than previously assumed. From the data, the Stark and A78-22583 * ,y The response of heat shield materials to in the Van der Waals Ine-widths were determined for 34 silicon lines. tense laser radiation. J. H Lundell and R R Dickey (NASA. Ames Radiative transport through a typical shock layer was computed Research Center, Entry Technology Branch. Moffett Field, Calif I using the new line-width data The computations showed that silicon American Institute of Aeronautics and Astronautics, Aerospace emission in the hot region is large, but it is mostly absorbed in.the Sciences Meeting, 16th, Huntsvlle, Ala, Jan 16-18, 1978, Paper colderregion adjacentto the wall (Author) 78-138.9 p. 13 refs Experimental results for the response of ATJ graphite, Carbitex A78-22606 * # Airborne infrared interferometric observations 100, and carbon phenolic to intense continuous-wave laser achation and analysis of stratospheric trace constituents. L. L Smith and T.' are presented Roth Tpenetratrnn and mass los test techniques are Hdgeman (Grumman Aerospace Corp., Bethpage, N Y.). American used and compared The results are also compared with a simple Institute of Aeronautics and Astronautics, Aerospace Sciences ablation theory applicable to laser irradiation Reasons for the Meeting, 16th, Huntsville, Ala ,Jan 16-78, 1978, Paper 78-252.3 p. disparity between experiment and theory, anti applicability of the Contract No. NAS2-8664 results to other heating situations, such as planetary entry, are Infrared interferometric observations of key trace constituents discussed (Author) of the stratosphere have been obtained. The NASA Lear Airborne Observatory with the Grumman airborne interferometer system was flown in the lower stratosphere at an altitude of 13 7 km to obtain A78-22591 * i Numerical solution of a three-dimensional transmission spectra in the 2800-6000 per cm region at aresolution shock wave and turbulent boundary-layer interaction. C.M. Hung of 2.5 per cm using the moon as a source An atmospheric modeling and R W MacCormack (NASA, Ames Research Center, Moffett program and the AFGL line parameter atlas are used to identify Field, Calif.) American Institute of Aeronautics and Astronautics, H20, CH4, 03 and other trace constituents and to derive strato Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, sphericcolumndensities (molecules/sqcm) (Author) Paper 78-161 1Op. 21 refs
34 A78-22608 * # Navier-Stokes calculations for laminar and .1,78-23450 - Effects of potassium titanate fiber on the wear turbulent hypersonic flow over indented nosetips J. V. Rakich of automotive brake linings M. L Halberstadt, J. A. Mansfield, and (NASA, Ames Research Center, Moffett Field, Calif.), Y C S K Rhee (Bendix Corp , Southfield, Mich ) In: Wear of materials Vigneron, and J. C Tannehill (Iowa State University of Science and 1977; Proceedings of the International Conference, St Louis. Mo, Technology, Ames, Iowa) American Institute of Aeronautics and April 25-28, 1977. (A78-23426 08-37) New York, American Society Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala., of Mechanical Engineers, 1977, p 560-568. 7 refs Contract No. Jan 16-18. 1978. Paper 78-260. 11 p- 11 refs NA92-7759 A time-accurate finite-difference Navier-Stokes code has been Asbestos reinforcing fiber in an automotive friction material was used to calculate the viscous flow over a severely indented blunt replaced by an experimental ingredient having better thermal body in a supersonic stream. An algebraic turbulence model isused stability, and the effects on wear and friction were studied. A and the results are compared with experimental data -from wind- friction materials test machine (SAE J661a) was used to determine tunnel tests. Qualitative agreement is obtained for the surface friction and wear, under constant energy output conditions, as a pressure distribution and flow-field structure, including the separated function of temperature between 121 and 343 C (250 and 650 F) bubble in the indented region However, uncertainties still exist in When potassium titanate fiber replaced one half of the asbestos in a the heating calculations, which are attributed to the turbulence standard commercial lining, with a40 percent upward adjustment of model For both laminar and turbulent calculations, the flow phenolic resin content, wear above 204 C (400 F) was improved by exhibits a fundamental unsteady character at a frequency of about 40% and friction by 30%. Tests on a full-scale inertial dynamometer 50 kHz. (Author) supported the findings of the sample dynamometer tests It was demonstrated that the potassium titanate fiber contributes directly to the improvement in wear and friction (Author)
A78-23083 * Generation of a parallel X-ray beam and its use for testing collimators. J H Underwood (Aerospace Corp , Los Angeles, Calif ). Space Science Instrumentation, voL 3, Nov. 1977, p A78-23543 * Thermal structure of the primitive ionosphere 259-270. 15 refs Contracts No. NAS2-8684, No F04701-75-C 0076 0 Ashihara (Tokyo, University. Tokyo, Japan), M. Shimizu (NASA, A technique is described, by which a glass strip may he bent to Ames Research Center, Moffett Field, Calif.; Tokyo, University, match any curve of large radius of curvature, to a high degree of Tokyo, Japan), and T. Shimazaki (NASA, Ames Research Center, accuracy, so that it may be used as a glancing incidence X-ray or Moffett Field, Calif.) Journal of Geophysical Research, vol. 83, Jan extreme ultraviolet optical element The desired match is obtained 1, 1978, p. 191-194. 16 refs by applying the optimum combination of end couples and by varying Exospheric neutral and electron temperatures have been atl the cross-sectional moment of inertia along the length of the strip A mated for the primitive upper atmosphere and ionosphere with particular case, that of a parabola for use as a laboratory X-ray various oxygen content in the scheme of our previous model collimator, is considered in detail. The analysis predicts that a (Shimizu and Shimazaki, 1976) The exospheric neutral temperature colmatilon of one or two arc seconds should be obtainable in has been shown to be rather insensitive to the change of oxygen practice, with simple and inexpensive appaiatus A prototype content, justifying our previous assumption for the temperature collimator to be used for the testing of space payloads using variation, while the exospheric electron temperature has been found geometric (McGrath) collimators is described and laboratory results to be quite sensitive to the compositional change, mainly owing to presented (Author) the strong dependence of electron density on the oxygen concentra- S tion (Author)
A78-23124 Measuring the velocity of individual atoms in real time- C Y. She (Colorado State University, Fort Collins, Colo ), A78-23576 * Quantum mechanical theory of collisional K W Biliman (NASA, Ames Research Center, Moffett Field, Calif ), ionization in the presence of intense laser radiation. J. C Bellum and W M Fairbank, Jr. Optics Letters, vol 2, Feb. 1978, p.30-32 9 (Rochester, University, Rochester, N.Y ) and T F. George. Journal refs of Chemical Physics, vol 68, Jan 1. 1978, p 134-144. 64 refs NSF It is proposed that the thermal velocity of a single atom could Grant No. CHE-75-06775-AO1; Contracts No. F44620-74-C-0073, be measured in eal time using a laser time-of-light velocineter No F49620-78-C 0005, Grant No. NsG-2198 (LTV) operating on the principle of laser resonance fluorescence- The paper presents aquantum mechanical formalism for treating Theoretical data are presented for several atomic species that have ionizing collisions occurring in the presence of an intense laser field resonances within the range of available dye laser systems. It is Both the intense laser radiation and the internal electronic con shown that measurements in the subsonic region are certainly tinuum states associated with the emitted electrons are rigorously feasible The atoms could be either in vacuum or in a buffer gas, e g , taken into account by combining discretization techniques with at atmospheric pressure Measurements in the transonic and super- expansions in terms of electronic-field representations for the some region also appear possible One potential application is the quasi-molecule-plus-photon system. The procedure leads to a measuiement of flow speeds in wind tunnels, perhaps as high as Mach coupled-channel description of the heavy-particle dynamics which 45. (Author) involves effective electronic-field potential surfaces and continua. It is suggested that laser-influenced ionizing collisions can be studied to verify the effects of intense laser radiation on inelastic collisional of stellar occultation data - Effects of processes Calculation procedures for electronic transition dipole A78-23164 Analysis omatrix elements between discrete and continuum electronic states photon noise and initial conditions. R.G French, J L Elliot, and P. are outlined M.L J Gierasch (Cornell University, Ithaca, N Y.). Icarus, vol 33, Jan. 1978, p 186-202. 16 refs Grants No. NGL-33-010-086, No NsG-7128; No. NsG-2174. An occultation light curve can be analyzed to provide informa- A78-23610 * Lower stratosphere measurements of variation tion about a planetary atmosphere Temperature, pressure, and with latitude of CF2CI2, CFCI3, CCI4, and N20 profiles in the number density profiles for the atmosphere of Mars are derived from northern hemisphere J. F Vedder, B J. Tyson, R B Brewer, E C a series of boundary layer equations, which invert equal increments Y Inn (NASA, Ames Research Center, Moffett Field, Calif ), and C. of altitude (as opposed to time) in order to predict the noise quality A Boitnott Geophysical Research Letters, vol 5, Jan 1978, p of the occultation Numerical results are given for anoisy isothermal 33-36 15 refs Iigt curve, with special attention to error analysis 0.M.W. Measurements were made from a U-2 aircraft of profiles of CF2CI2, CFCI3, CC14 and N20 in the lower stratosphere in a meridional survey at a longitude of 159 deg W during the period October I to November 14, 1976. The latitude distributions obtained show a marked decrease in mixing ratio with increasing
35 latitude from about 7 deg N in the Intertropical Convergence Zone observations of the absolute value, wavelength dependence, and to about 79 deg N. The results suggest the importance of meridional degree of depolarization of the rings' radar cross section (reflectiv transport and mixing in the stratosphere in accounting, at least in ity). The doubling method is used to calculate reflectivties for part, for the observed profile variation with latitude The contami- systems that are many particles thick using optical depths derived nants C2F4Cl2, C2F3CI3, CHCCI3 and SF6 were also detected but from observations at visible wavelengths If the rings are many their mixing ratios were small and no accurate standards were particles thick, irregular centimeter- to metersized particles com prepared for them BJ. posed primarily of water ice attain sufficiently high albedos and scattering efficiencies to.explain-the-radar observations. In that case, the wavelength independence of radar reflectivity implies the existence of a broad particle size distribution: a narrower size A78-23646 The rings of Saturn J. B. Pollack (NASA, distribution is also a possibility Particles of primarily silicate Ames Research Center, Moffett Field, Calif ) American Scientist, composition are ruled out by the radar observations. Purely metallic vol 66, Jan.-Feb. 1978, p 30-37. 29 refs. particles may not be ruled out on the basis of existing radar Consideration is given to the development of theories con- observations A monolayer of very large ice 'particles' that exhibit corning the rings of Saturn. Particular attention is given to ring multiple internal scattering may not yet be ruled out. (Author) structure, noting its thinness, the separations between rings, and observed variations in brightness Data gathered via infrared, radio and radar techniques are described in terms of ring particle A78-26079 Dynamic MHD modeling of the solar wind composition and size Hypotheses about ring origin and evolution are di8-rb07e durien the sogar with outlined, including the tidal disruption model, calculations of disturbances during the August 1972 events. M Dryer,C. K.Smith Saturn's gravitational contraction history, grazing, and meteoroid (NOAA, Space Environment Laboratorysviller,Bl Col) , R. S bombardment. Prospects for future observations of Saturn's rings are Stenolfson (Alabama, University, Huntsvlle, Ala ), E. J. Smith reviewed, such as the variation in their radar reflectivity as afunction (California Institute of Technology, Jet Propulsion Laboratory, of the tilt of the ring plane S.C S. Pasadena, Calif.), J. H. Wolfe, J. D. Mihalov (NASA, Ames Research Center, Moffett Field, Calif ), P. Rosenau (New York University, New York, N.Y), and C. Candelaria Journal of Geophysical Research, vol. 83, Feb 1, 1978, p. 532-540 26 refs. Grant No. A78-25264 * Microparticle accelerator of unique design J AF-AFOSR-76-2881 F. Vedder (NASA, Ames Research Center, Moffett Field, Calif.) A time-dependent one-dimensional MHD theoretical model is Review of Scientific Instruments, vol. 49, Jan. 1978, p. 1-7 23 refs tested by using plasma and magnetic field observations of Pioneer 9 A microparticle accelerator has been devised for micrometeoroid and Pioneer 10 during the August 1972 events on the sun and in the impact and cratering simulation; the device produces high-velocity interplanetary medium These spacecraft were nearly aligned along a (0 5.15 km/see), micrometer-sized projectiles of any cohesive ma- common heliocentric radius during these events, considered now to teral. In the source, an electrodynamic levitator, single particles are be the most spectacular and best-documented events during solar charged by ion bombardment in high vacuum. The vertical accelera- cycle 20 The observations of Pioneer 9 at 0 78 AU were used as tor has four drift tubes, each initially at ahigh negative voltage After input for the theoretical model. The plasma and magnetic field injection of the projectile, each tube is grounded in turn at a time forcing functions were superimposed upon a preexisting ambient determined by the voltage and charge/mass ratio to give four solar wind at this inner boundary, and the response was simulated as acceleration stages with a total voltage equivalent to about 17 MV. far as 8 AU. The simulated output at 2.2 AU is compared directly BJ. with the Pioneer 10 observations at 2.2 AU Qualitative comparison is good, although several limitations of the one-dimensional theory are noted, (Author) A78-25295 * Airborne photometric observations between 1.25 and 3 25 microns of late-type stars. H. L. Nordh, S. G.Olofsson (Stockholms Observatorium, Saltslobaden, Sweden), and G. C. Augason (NASA, Ames Research Center, Astrophysics Branch, A78-26080 * The interplanetary modulation and transport Moffett Field, Calif ). Astronomical Journal, vol. 83, Feb 1978, p. of Jovian electrons T F Conlon (Chicago, University, Chicago, Ill.). 188-193. 30 refs. Swedish Board for Space Activities Grant No. Journal of Geophysical Research, vol 83, Feb. 1, 197 8 , p 541-552. DR-1148. 29 refs Contract No NAS2-6551, Grant No. NGL-14-001-006. The stars Alpha Aur (GS III + GO Ill). Alpha Boo (K2 IIlp), Based on simultaneous measurements by Pioneer 11 of the 3-6 Alpha On (M1-M2 la-lb), Alpha Sco (M1.6 lab), Mu Gem (M3 Ill), MeV Jovian electron flux, interplanetary magnetic field magnitude, and Alpha Her (M5 lb-Il) have been observed using interference and solar wind speed, the interplanetary transport of energetic filters in five photometric bands between 1.25 and 3 25 microns particles is studied. It is found that corotating interaction regions during seven flights with NASA's Lear Jet Infrared Observatory. The (CIR's) greatly inhibit electron transport across the average field filters were designed to measure molecular features, primarily from direction. Cross-field transport is also influenced by the degree of CN and CO, and continuum fluxes. By calibrating the photometer in compression of the solar wind since ClR's are areas of compressed the laboratory against a stabilized blackbody source, relative flux solar wind plasma. The propagation of Jovian electrons isstudied by curves have been derived. The energy distributions and the strength a model that includes the effects of CIR's The model tests whether of molecular features are discussed The most interesting result or not the three-dimensional convection-diffusion theory adequately obtained is that the fluxes from Mu Gem and Alpha Her in the filter describes the cross-field transport of electrons. The model is also centered at 3.25 microns seem to be depressed by at least some valid for Jovian electron observations from earth-orbitng satellites. tenths of.a magnitude. Tentatively this depression is proposed to be The model may be further applied to 1 AU from the sun where it is due to the, wings of the two vibration-rotation bands (about 2 7 found that the cross-field diffusion of electrons explains why Jovian microns) of hot water vapor. Since water vapor is an important electrons are detected at the earth even during periods when the opacity source and its abundance is a sensitive C/O indicator, the interplanetary magnetic field does not connect the earth directly to proposed interpretation makes renewed efforts to detect water bands Jupiter. S.C.S in early M stars highly desirable. (Author)
A78-26081 Energetic protons associated with inter A78-25676 * Saturn's rings Particle composition and size planetary active regions 1-5 AU from the sun. M. E. Posses, J. A Van distribution as constrained by microwave observations. I - Radar Allen, and C K. Goertz (Iowa, University, Iowa City, Iowa).Journal observations. J. N. Cuzzi and J. B. Pollack (NASA, Ames Research of Geophysical Research, vol. 83, Feb. 1, 1978, p.553-562 . 36 refs. Center, Space Sciences Div, Moffett Field, Calif). Icarus, vol. 33, Contract No. NAS2-6553. Feb. 1978, p 233-262 84 refs Pioneer 11 has yielded data on approximately 100 energetic The radar backscattering characteristics of compositional and proton events at heliocentric distances between 1 and 2 AU. structural models of Saturn's rings are calculated and compared with Measurements of absolute intensities, anisotropees, and crude energy
36 spectra are studied in connection with interplanetary active regions A78-29472 * On the apparent source depth of planetary lIAR's). It is found that in close vicinity to IAR's, the number of magnetic fields. R. C. Elphic and C. T. Russell (California, events observed per unit time interval is 10 times greater than in University. Los Angeles, Calif ). Geophysical Research Letters, vol 5, other areas of interplanetary space, and that the frequency of events 'Mar 1978, p. 211-214 14 refs Contract No. NAS2-8808; Grant No. has a maximum at plus or minus 5 hours of the time IAR edges are NGR-05-007-004. crossed. It is also noted that events in IAR vicinity have greater Two simple assumptions regarding the ratios of the strengths of particle densities, softer energy spectra, and smaller time widths than the field contributions of the multipole moments of the terrestrial other events. For many events associated with IAR's, particle magnetic field at its effective source depth are used to examine the anisotropies correspond to the net flow of particles along the consistency between the apparent source depths for the magnetic interplanetary magnetic field toward the sun This suggests that a fields of Mercury and Jupiter and the present understanding of their mechanism in MHD shocks is responsible for local acceleration in the interior structure. Both fields are consistent with the present interplanetary medium. SCS understanding However, the comparison would be facilitated by further measurements of the magnetic fields at both planets, especially at Mercury. (Author) A78-26350 * An integral solution to a nonlinear diffusion problem M. Y. Hussami (NASA, Ames Research Center, Moffett Field, Calif.) and K. J Devasia (NASA, Ames Research Center, A78-29489 * The co-adsorption of copper and oxygen on a Moffett Field, Calif.; Indian Space Research Organization, Ahmed- tungsten 100 plane-type surface. E. Bauer (Clausthal, Technische abad, India) Computer Methods in Applied Mechanics and Engineer- Universitat, Clausthal.Zellerfeld, West Germany), H. Poppa (NASA, ing, vol. 13, Jan. 1978, p. 119-123. Ames Research Center, Moffett Field, Calif.), P. R Davis (NASA, The generalized Galerkin method (or the method of integral Ames Research Center, Moffett Field;Stanford University, Stanford, relations) is applied to the type of problem described by quasilinear Calif), and Y'. Viswanath (NASA, Ames Research Center, Moffett parabolic equations As an example the problem of nonlinear Field, Calif.; Amoco Research Center, Naperville, III I. Surface transient slab diffusion with a general reservoir boundary condition is Science, vol. 71, no 3, Feb 1978, p. 503-518 5 refs Grants'No. worked out. The integral relations are given for an arbitrary number NsG-2071; No NCA2-OR450-602. NASA Order R-05-030-001. of strips, and solutions using up to seven strips have been obtained in The coadsorption of Cu on 02 and a W 100 plane-type surface is order to investigate the convergence of the method (Author) studied by Auger electron spectroscopy, thermal desorption, low energy electron diffraction and by work function change measure ments. It is shown that the presence of Cu on the surface initially A78-27743 * A new concept in laser-assisted chemistry decreases the sticking coefficient of 02 For longer oxygen exposures The electronic-field representation. T F. George, I H Zimmerman, and for higher adsorption temperatures, the coverage of preadsorbed L-M Yuan, J R. Laing, and P. L. DeVries (Rochester, University. oxygen reaches values larger than those on the clean surface for the Rochester, N.YJ). Accounts of Chemical Research, vol 10, 1977, p same 02 exposure Except at the highest valuesand temperatures of 449-455 22 refs. NSF Grant No CHE-75-06776-A01; Grant No the coverage of preadsorbed oxygen, the sticking coefficient for NsG-2198; Contract No. F44620-74-C-0073. copper is unity and is independent of the oxygen coverage in the Electronic-field representation is proposed as a technique for range studied. Coadsorpton at room temperatures does not produce laser-assisted chemistry. Specifically, it is shown that several field- any long range order while coadsorption at elevated temperature S assisted chemical processes can be described in terms of mixed leads to ordered structures. The saturation coverage of the two matter-field quantum states and their associated energies. The dimensional coadsorbate at 800 K is given by a relation. The work technique may be used to analyze the effects exerted by an intense function is a complicated function of the coverage of preadsorbed laser on both bound and unbound molecular systems, and to oxygen and the coverage of preadsorbed Cu and is determined investigate other field-induced effects including multiphoton pro- predominantly by the temperature at which oxygen is adsorbed. At cesses, emission, and photodissociation. S.C S high temperatures the sequence of adsorption has no influence, in contrast to the room temperature behavior. (Author)
A78-27744 Semiclassical approach to coilision-induced emission in the presence of intense laser radiation - An aspect in the A78-29532 * An analytic study of impact ejecta trajectories study of cooperative chemical and optical pumping K.-S Lam, I H. in the atmospheres of Venus, Mars, and earth M E. Tauber, D. B. Zimmerman, J-M. Yuan, J R Laing (Rochester, University, Kirk, and D E. Gault (NASA, Ames Research Center, Moffett Field, Rochester, N Y.), and T F. George Chemical Physics, vol. 26. Dec Calif I Icarus,vol 33, Mar 1978, p 529-536. 10 refs 15, 1977, p. 455-486 54 refs. NSF Grant No CHE-75 06775.AOl, Calculations have been made to determine the effects of GrantNo. NsG-2198, Contract No F44620-74-C 0073 atmospheric drag and gravity on impact ejecta trajectories on Venus, Mars, and earth The equations of motion were numerically integrated for a broad range of body sizes, initial velocities, and A78-28926 * Characteristics of integrated MOM junctions at initial elevation angles. A dimensionless parameter was found from dc and at optical frequencies. M Heiblum, S Wang, J R. Whinnery, approximate analytic solutions which correlated the ejecta range, and T. K. Gustafson (California, University, Berkeley, Calif.). IEEE final impact angle, and final impact velocity for all three planets Journal of Quantum Electronics, vol QE-14, Mar 1978, p. 159-169 (Author) 3B refs NSF Grant No ENG-72-03960-AO1, Contract No F44620-76.C-0100, Grant No. NsG-2151 A78-29684 Acceleration of nucleons in the interplanetary A new metal-oxide-metal device (Ni-NiO-Ni. Edge MOM) which space and the modulation of Jupiter electrons in the interval from 1 is stable, reproducibly fabricated, and with a 10 to the -10th sq cm to 10 A.U. by corotating regions of solar origin. C W Barnes, D. L. tunneling area is presented. Performing detection experiment% the Chenette, T. F. Conlon, K R. Pyle, and J. A. Simpson (Chicago, device's nonlinear I-V characteristic is shown to be invariant at audio University, Chicago, IlI ) (Akademita Nauk SESR, Izvestda, Serna frequencies, 106, 339, and 0.6328 microns. Similar devices with 10 Fizicheskaia, vol 41, Feb 1977, p. 303 -32 1 )AcademyofSciences, to the -8th sq cm tunneling areas perform aswell as the Edge MOM's USSR, Bulletin, Physical Seres, vol 41, no 2, 1977, p 58-71 46 in the visible and the near-infrared range, but deteriorate in refs Contract No. NAS2-6551; Grant No NGL-14-001-006. performance at the 10-micron range A dominant competing effect is (For abstract see issue 14, p 2453, Accession no. A77-32859) a thermal-induced signal, which increases with frequency and temperature. Coupling mechanisms at the various regimes are investigated. The device can serve- as a broad-band detector and mixer, and might in the future be a basic element of broad-band amplifiers and oscillators (Author)
37 00 7 A78-3 1 * A comprehensive model of the Venus lono- (California, University, Berkeley, Calif ), and J. A Tyson Review of sphere. R. H Chen and A. F Nagy (NOAA, Space Physics Research Scientific Instuments, vol 49, Apr. 1978, p- 440-44 8. 15 refs Grant Laboratory, Ann Arbor, Mich ). Journal of Geophysical Research, No. NsG-2125, Contract No. W-7405-eng-48. vol 83. Mar. 1, 1978, p. 1133-1140 53 refs NSF Grant No. A 33-GHz airborne radiometer system has been developed to ATM-75-21049; Grant No. NGR-23-005-015; Contract No. NAS2- map large angular scale variations in the temperature of the 3 K 9130 cosmic background radiation A ferrite circulator switches a room Coupled time-dependent continuity-momentum and energy temperature mixer between two antennas pointing 60 deg apart in balance equations for the Venus ionosphere were simultaneously the sky. In 40 mm of observing, the.radiometer can-measure the solved for C02(+), 02(+), O(+), He(+), and- H(+) densities and anisotropy of the microwave background with an accuracy of plus or electron and ion temperatures for an altitude range of 120-500 kin. minus 1 mK rms, or about 1 part in 3000 of 3 K. The apparatus is Values of the solar zenith angle varied from 0 deg (subsolar point) to flown in a U-2 jet to 20 km altitude where 33-GHz thermal 90 deg (terminator). The calculations include the horizontal bulk microwave emission from the atmosphere is at alow level. A second transport of ions by neutral winds but not the horizontal diffusion, radiometer, tuned to 54 GHz near oxygen emission lines, monitors The two-stream photoelectron transport method was used to find the spurious signals from residual atmospheric radiation The antennas, heating rates for the ambient electrons. Different boundary con- which have an extremely low side-lobe response of less than -65 dB ditions were considered, and a nightside ionosphere was calculated, past 60 deg, reject anisotropc radiation from, the earth's surface The results of these model calculations are in good agreement with Periodic interchange of the antenna positions and reversal of the measurements in the region of maximum electron density. Charac- aircraft's flight direction cancel equipment-based imbalances The teristics of topside and nightside densities and temperatures are system has been operated successfully in U-2 aircraft flown from discussed. M.L NASA-Ames at Moffett Field, Calif (Author)
A78-30078 * On the observation of a flare-generated shock A78-30893 * Coefficient matrices for implicit finite dif wave at 9.7 AU by Pioneer 10. M. Dryer (NOAA, Space Environment ference solution of the inviscid fluid conservation law equations. J. Laboratory, Boulder, ColD), M. A Shea, D F. Smart (USAF, L Steger (NASA, Ames Research Center, Moffett Field, Calif). Geophysics Laboratory, Bedford, Mass.), H R. Collard, J D. Computer Methods in Applied Mechanics and Engineering, vol 13, Mihalov, J H Wolfe (NASA, Ames Research Center, Moffett Field, Feb. 1978, p 175-188 22 refs. Calif.), and J W. Warwick (Colorado, University, Boulder, Colo.) Although the Navier-Stokes equations describe most flows of Journal of Geophysical Research, vol. 83, Mar. 1, 1978, p. interest in aerodynamics, the inviscid conservation law equations 1165-1168 23refs may be used for small regions with viscous forces. Thus, Euler An apparent solar-flare-generated shock wave detected by equations and several time-accurate finite difference procedures, Pioneer-10 at 9 7 AU on April 9, 1976 is discussed The shock wave explicit and implicit, are discussed Although implicit techniques may be correlated with a radio emission burst from Jupiter not require more computational work, they permit larger time steps to associated with lo (March 30). The fact that solar flares observed on be taken without instability. It is noted that the Jacobian matrices March 20 were at the central meridian with respect to Jupiter and for Euler equations in conservation-aw form have certain eigenvalue Pioneer-10 and the fact that solar activity was very low before March elgenvector properties which may be used to construct conservative 20 contribute to the argument that a shock wave had propagated to form coefficient matrices This reduces the computation time of the region of the spacecraft J.M.B. several implicit and semimplicit schemes Extensions of the basic approach to other areas are suggested S.C.S
A78-30647 * Stimulated emission of surface plasmons by electron tunneling in metal-barrier-metal structures. D. P Siu and T. . A7831108 * The quiet coronal X-ray spectrum of highly K Gustafson (California, University, Berkeley, Calif ) Applied ionized oxygen and nitrogen. D L. McKenzie, H R Rugge, J. H. Physics Letters, vol. 32, Apr. 15, 1978, p. 500-502. 14 refs. NSF Underwood, and R M Young (Aerospace Corp, Space Sciences Grant No ENG-76-84532, Grant No NsG-2151. Laboratory, Los Angeles, Calif.) Astrophysical Journal, Part 1, vol It is shown that correlation currents arising from the super- 221, Apr 1, 1978, p 342-349. 27 refs Research supported by the position of pairs of states on distinct sides of a potential barrier in Aerospace Corp, Contract No NAS2-8684 metal-barrier-metal structures can result in inelastic tunneling through the emission of surface plasmons Net gain of an externally excited plasmon field is possible (Author) A78-31921 * # Earth reencounter probabilities for aborted space disposal of hazardous nuclear waste. A L Friedlander and H Femgold (Science Applications, Inc. Schaumburg, I11.).American A78-30690 * Influence of spin rate on side force of an Astronautical Society and American Institute of Aeronautics and axisymmetric body R. L Kruse (NASA, Ames Research Canter, Astronautics, Astrodynamics Specialist Conference, Jackson Hole, Moffett Field, Calif ) AIAA Journal, vol 16, Apr 1978, p 415, Wyo, Sept. 7-9, 1977, Paper. 51 p 14 refs Contract No. 416. NAS2-9272. Results are presented for an experimental study in which a A quantitative assessment is made of the long-term risk of earth 10-deg half-angle pointed cone model 57.9 cm long and made of reencounter and reentry associated with aborted disposal of haz. magnesium (for liqhtness and minimization of inertial effects) is spun ardous material in the space environment. Numerical results are at several rates about its axis of symmetry The model is spun in both presented for 10 candidate disposal options covering a broad directions, but most of the data presented are for the counter- spectrum of disposal destinations and deployment propulsion sys clockwise rotation The resulting side force is recorded on an tems Based on representative models of system failure, the prob oscillograph. It is shown that the side force observed occurs under ability that asingle payload will return and collide with earth within conditions of spin about the longitudinal axis, and that the general a period of 250,000 years is found to lie in the range 0002- 006. shape of the side-force curve with roll position does not depend Proportionately smaller risk attaches to shorter time intervals strongly on spin rate However, the peak-to-peak value of side force Risk-critical factors related to trajectory geometry and system decreases substantially with spin rate, suggesting that the vortices reliability are identified as possible mechanisms of hazard reduction. producing the side force require a significant amount of time to (Author) change position and/or strength SD. A78-32467 * Bar-driven spiral waves in disk galaxies J M. Huntley (NASA, Ames Research Center, Moffett Field, Calif A78-30691 Radiometer system to map the cosmic back. Virginia, University, Charlottesville, Va.), R H Sanders (Pittsburgh, ground radiation M V. Gorenstein, A. A Muller, G F Smoot University, Pittsburgh, Pa.), and W. W. Roberts, Jr. (Virginia,
38 University, Charlottesville, Va.). Astrophysical Journal, Part 1, vo University, San Jose, Calif.). Journal of Geophysical Research, vol 221, Apr. 15, 1978, p. 521-525, 527, 529 (7 ff,). NSF Grant No. 83, Apr. 10, 1978, p 1793-1808.24 refs Contracts No. NAS2-6005; AST-72-05124A04. No. NCAR-675414. The response of rotating disks of gas to barlike perturbations in Iron and nickelron samples subjected to treatment by an galactic gravitational fields is investigated. In particular, two- arc-leated plasma of ionized air were used to model meteor ablation dimensional time-dependent numerical hydrodynamical calculations The artificial ablation debris and fusion crusts were cormpared to the have been performed in order to determine the steady-state response fusion crusts of three natural iron meteorites and to magnetic of disks of gas to rotating barlike perturbations. Two types of barlike spherules from deep-sea manganese nodules An outer discontinuous perturbations are considered oval distortiens in the axisymmetric crust of magnetite and wJstite, followed by an unoxidized metallic gravitational field of the disk, and heterogeneous prolate spheroids. zone, was observed in the artificially produced samples. Fractiona The calculations reveal that in the absence of gaseous self-gravity, a tion of lessvolatile elements was al, noted. J M B. viscous differentially rotating disk of gas responds to a rotating barlike perturbation by forming a central gas bar with two trailing spiral waves. The local phase of the gas response is primarily a function of the number and spacing of the principal resonances in A78-34567 * Quiet time interplanetary cosmic ray anisot -the disk. This result may be understood in terms of particle orbit ropies observed from Pioneer 10 and 11. W.-H. Ip, W. Fillius, A. theory. The gas response to barlike perturbations also depends on the Mogro-Campero (California, University, La Jolla, Calif.), L J. relative strength and the effective axial ratio of the bar. In these Gleason (Monash University, Clayton, Victeria, Australia), andW. I. calculations strong narrow bars produce offset shocks in the central Axford (Max-Planck-lnstitut fur Aeronome, Katlenburg, West Ger D;i eo;inoltsg.s (,is well as for 'taod-l-ght' cosmioloics) ,], -many). Journal of Geophysical Research, vol 83, Apr. 1, 1978, p. ,'noimots The Planckian (or ne~r-Planckian) spectral form . 1633-1640. 21 refs. Contract No. NAS2-6552, Grant No. ncroave r dliaton proviocs a crucial tst, failed by such cos- NGR-O-009-081 molog.s. (Authoi Cerenkov counters on the Pioneer 10 and 11 spacecraft, capable of detecting alpha particles and protons with energies up to 480 MeV, and nucleons and electrons with energies up to 6 MeV, have yielded data on cosmic ray anisotropes during periods of low solar A78-34137 * Low energy ionizing collisions between N2 activity. Observations from Pioneer 11 place east-west anisotropy at and CO beam molecules and CO, N2, NO, CH4, and C02 target 0.41 plus or minus 011%, and the north-south anisotropy at near molecules N G. Utterback (TRW, Inc., Redondo Beach, Calif.)-and zero; Pioneer 10 results show east-west anisotropy to be ap B. VanZyl (Denver, University, Denver, Colo.).Journalof Chemical proximately 0.59 plus or minus 0.18%, and the north-south Physics, vol. 08, Mar. 15, 1978, p 2742-2752. 18 refs Contracts No. component at 0.25 plus or minus 0 08%. It isnoted that the Pioneer NAS2-4924; No. DA-01-021-AMC-1 13592. 10 observations were obtained at the 6 AU range, while those from Absolute total negative charge production cross sections for fN2 Pioneer 11 originated closer to the sun (1.1 to 2.7 AU). Attention is + CO, CO + N2, CO + CO, N2 + NO, N2 + CR4, and N2 + C02 given to the ratio of the perpendicular to parallel components of the collisions are reported, and asimple model of collisions isdiscussed, diffusion coefficient, and to the large north-south anisotropy The cross sections were measured to within about I eV of their reported by Pioneer 10, an effect due possibly to gradient drift, and thresholds. Specific reaction channels were investigated by referring to an additional streaming independent of the magnetic field to mass spectrometric identification of the product ions scattered in polarity. D.M.W. the forward direction, and these product on identifications were S used to explain characteristic structures in the total charge produ-, tion cross sections in the near-threshold regions The extent of the importance of dissbciative ionization and 'simple' ionization in the A78-34682 Semiclassical theory of unimolecular dissocia studied collisions at low energy is considered, and charge transfer tion induced by a laser field. J.-M Yuan (Rochester, University, cross sections for (CO)+ + CO, CO(+) + CH4, and N2(+) + CR4 are Rochester, N.Y.) and T F. George. Journal of Chemical Physics, vol. presented. M.L, 68, Apr. 1, 1978, p 3040-3052. 72 refs. NSF Grant No ClE-l 06775-A l; Contracts No. F44620-74-C-0073; No. F49620-78-C-0005, Grant No. NsG-2198. A semiclassical ronperturbtve theory of direct photodissocia A78-34352 * A note on the diurnal averaging of aero- tion in a laser field is developed in which photon absorption and noinical models. R. P. Turco (R & 0 Associates, Marina del Rey, dissociation are treated in a unified fashion. This is achieved by Calif.) and R. C. Whitten (NASA, Ames Research Center, Moffett visualizing nuclear dynamics as a representative particle moving on Field. Calif.), Journal of Atmosphericand Terrestrial Physics, vol. clectronic-field surfaces. Methods are described for calculating 40, Jan. 1978, p. 13-20.5 refs. dissociation rates and probabilities by Monte Carlo selection of initial An approximate technique for diurnally time-averaging atma- conditions and integration of classical tralectories on these surfaces. spheric photochemical-dynamical models which eliminates the need This unified theory reduces to the golden rule expression in the for a detailed numerical resolution of sunrise and sunset transitions is weak-field and short-tme limits, and predicts nonlinear behavior, ie.. developed. The schemels equivalent to scaling certain chemical rate breakdown of the golden rule expression in intense fields. Field constants and photodissociation coefficients by appropriate aero- strengths above which lowest-order perturbation theory fails to work nomical factors. To calculate the scaling factors, diurnal variations have been estimated for some systems Useful physical insights are parameterized with a step-function behavior, assuming that each provided by the electronic-field representation have been illustrated. species has a constant day-time and night-time concentration whose Intense field effects are discussed which are amenable to experi ratio can be determined by analyzing the chemical interactions mental observation. The semiclassical methods used here are also occurring after sunset. The solution accounts for the effects of applicable to multiple-surface dynamics in fieldfree urnolecular and night-time reactions on the 24 h average values of species bimolecular reactions (Auther) abundances, and on the average daily rates of the catalytic processes consuming ozone in the stratosphere. The accuracy of the technique is demonstrated by comparing its predictions to those of a full A78-35403 * Geographical variations of NO and 03 in the diurnal simulation; typically, the precision is better than 10% By lower stratosphere. M. Loewenstein, W. J Borucki, H. F. Savage, J. contrast, it is shown that the use of soma other well-known G. Borucki, and R. C. Whitten (NASA, Ames Research Center, computational schemes can result in significantly larger predictive Moffett Field, Calif ),Journal of Geophysical Research, vol. 83, Apr errors. (Author) 20, 1978, p. 1875-1882. 14 refs. Nitric oxide and ozone concentrations in the loweestratosphere have been measured from a high-altitude research aircraft using in A78-34508 * Analysis of ablation debris from natural and situ measuring techniques Results of several geographical surveys are artificial iron meteorites. M. 8. Blanchard (NASA, Ames Research presented along with predictions of two two-dimensional strato Center, Moffett Field, Calif.) and A. S. Davis (San Jose State spheric models. Meridional and zonal data were obtained in June
39 1974 and in June, July, and August 1975. At longitudes 122-158 deg A78-35997 * 1 A method for determining structural proper W the meridional data taken between 5 and 80 deg N latitude show ties of RCC thermal protection material. R M Wakefield and K. R an increasing NO concentration with latitude, by a factor of 4 dt Fowler (NASA, Ames Research Center, Moffett Field, Calif) 21-km altitude and a less marked increase at 18 km. The minimum American Institute of Aeronautics and Astronautics and.American NO concentration at 21 km is observed at 5 deg N latitude and is Society of Mechanical Engineer, Thermophysics and Neat Transfer about 6 x 10 to the 8th power/cu cm. Zonal data at latitudes 22-38 Conference, 2nd, Palo Alto, Calf., May 24-26, 1978, AIAA Paper' deg N taken from 55 to 176 deg N longitude show little variation of 78-869 12 p the NO and 03 concentrations with longitude. (Author) A method was developed for evaluation and prediction of effects of oxidation of the graphjitic substrate on structural proper. ties of Reinforced Carbon-Carbon (RCC) thermal protection ma A78-35601 * Investigation of a cryogenic thermal diode. R. terial. Test specimens of RCC material were exposed to successive J. Williams (NASA, Ames Research Center, Moffett Field, Calif ). In periods of convective heating in a plasma-let facility to simulate the International Heat Pipe Conference, 3rd, Palo Alto, Calif., May chemical reactions of Shuttle atmospheric entry After each period 22-24, 1978, Technical Papers (A78-35576 14-34) New York, of testing, the test specimen mass loss and performance in a American Institute of Aeronautics and Astronautics, Inc, 1978, p: nondestructive flexure test were determined. A computational model 177-183.7 refs (AIAA 78-417) of the RCC specimen was developed for the NASA Structural This paper describes a series of parametric investigations to Analysis (NASTRAN) program and validated by comparison of determine the effect of various fluid charges on the performance of a calculated and experimental results of flexure tests. The elastic 0.635-cm-diameter spiral-artery, liquid-trap diode in both the moduli and ultimate loads in tension and compression were then ,forward and reverse modes. Specific parameters such as forward- and computed for various levels of substrate oxidation. (Author) reverse-mode conductances, shutdown times and energies, and recovery to forward-mode operation, are evaluated for ethane as a working fluid in the temperature range 170 K to 220 K. Results A78-36040 * Chemisorption of CO on Pd particles sup indicate that the heat pipe will not reliably start up in the forward ported on mica M Thomas, H Poppa (NASA, Ames Research mode. However, startup can be initiated when preceded by a diode Center, Moffett Field, Calif), J T. Dickinson (NASA, Ames reversal. Also concluded are data which show the susceptibility of Research Center, Moffett Field, Calif ; Washington State University, the diode to fluid charge and tilt. The optimum fluid charge was Pullman, Wash.), and G. M Pound (NASA, Ames Research Center, found to be 2.67 g, and transport capability at this charge was in Moffett Field; Stanford University, Stanford, Calif.). (American excess of 1200 W-cm at 200 K. The diode in the reverse mode Vacuum Society, National Symposium, 24th, and Conference on exhibited a rapid shutdown (within 9 min) with a shutdown energy Microbalance Techniques, 15th, Boston, Mass, Nov. 8-11, 1977.) of 115J (0.32Wh) (Author) Journal of Vacuum Science and Technology, vol 15, Mar.-Apr. 1978, p. 568-571. 8 refs. Contracts No. NCS2-OR840-701; No. NCA2-OR745-711. A78-35603 * # A re-entrant groove hydrogen heat pipe. J. A UHV technique is presented for evaluating the adsorption Alario, R. Kosson (Grurmman Aerospace Corp., Bethpage, N Y.), and desorption properties of UHV' vapor-deposited metal particles C McCreight (NASA, Ames Research Center, Moffett Field, Calif.). supported on insulating substrates. Desorption studies of CO from In. International Heat Pip; Conference, 3rd, Palo Alto, Calif., May particulate and continuous Pd films supported on mica were S 22-24, 1978, Technical Papers. (A78-35576 14-34) New York, performed. The desorption results indicate that: the CO desorption American Institute of Aeronautics and Astronautics, Inc, 1978, p energies from the deposited metals are much lower than those from 194-202.7 refs. (AIAA 78-420) bulk single crystals, two desorption states exist for the This paper extends the development of reentrant groove vapor-deposited films; and the lower energy desorption peak of the technology to hydrogen heat pipes. Parametric analyses are presented vapor-deposited films is coverage dependent. Possible reasons for the which optimize the theoretical design while considering the limita- difference between previously reported CO desorption studies on tions of state-of-the-art extrusion technology. Acceptable bulk substrates and the present results are discussed. (Author) production-type runs of extruded lengths (over 300 m) could only be achieved at the expense of a wider nominal groove opening than specified (0.33 mm vs. 0.20 mm). However, dimensional variations of other critical dimensions were within 0.05 mm, which exceeded A78-36596 * ALC/50/ values for some polymeric materials. expectations. The 6063-T6 aluminum extrusion is 14.6 mm OD with C J Hilado, H J Cumming, J. E. Schneider (San Francisco, J. A. Parker surrounda wall thickness of 1.66 mm and contains 20 axial grooves whch University, San Francisco, Calif.), 0. A. Kourtides, and a central 9.3-mm-diam vapor core Each axial groove is (NASA, Ames Research Center, Moffett Field, Calif). Journal of 5 refs. Grant No. 0.776-mm-diam with a 0 33 mm opening An excess vapor reservoir Combustion Toxicology, vol 5, Feb. 1978, p.5-10 is provided at the evaporator to minimize the pressure containment NsC-2039. hazard during ambient storage Details of the instrumentation and Apparent lethal concentrations for 50 per cent of the test helium-cooled test installation are also presented. (Authorl, animals within a 30-mn exposure period (ALC/50/) were determined for seventeen samples of polymeric materials, using the screening test method. The materials evaluated included resin-glass composites, film values, based on A78-35622 * I Jet pump assisted arterial heat pipe. W. B. composites, and miscellaneous resins. ALC(SO) Bienert, A S Ducao, and D S Trimmer (Dynatherm Corp , weight of original sample charged, ranged from 24 to 110 mg/l. Cockeysville, Md ) In International Heat Pipe Conference, 3rd, Palo Modified phenolic resins seemed to exhibit less toxicity than the Alto, Calif, May 22-24, 1978, Technical Papers. (A78-35576 14-34) baseline epoxy resins Among the film composites evaluated, only New York, American Institute of Aeronautics and Astronautics, Inc, flame modified polyvinyl fluoride appeared to exhibit less toxicity 1978, p.335-345, 12 refs- Contract No. NAS2-9233. (A[AA 78-443) than the baseline polyvinyl fluoride film. (Author) This paper discusses the concept of an arterial heat pipe with a capillary driven jet pump. The jet pump generates a suction which pumps vapor and noncondensible gas from the artery. The suction A78-36717 Satellite mirror systems for providing terres also forces liquid into the artery and maintains it in a primed trial power - System concept K. W Billman, W. P Gilbreath (NASA, condition. A theoretical model was developed which predicts the Ames Research Center, Moffett Field, Calif-), and S W. Bowen. In: existence of two stable ranges Up to a certain tilt the artery will The industrialization of space; Proceedings of the Twenty-third prime by itself once aheat load isapplied to the heat pipe At higher Annual Meeting, San Francisco, Calif., October 18-20, 1977. Part 1 tilts, the jet pump can maintain the artery in a primed condition but (A78-36701 15-12) San Diego, Calif, American Astronautical self-priming is not possible. A prototype heat pipe was tested which Society, Univelt, Inc-, 1978, p.391-414. 11 refs. (AAS77-240) self-primed up to a tilt of 1.9 cm, with a heat load of 500 watts The A system of orbiting reflectors, SOLARES, has been studied as a heat pipe continued to prime reliably when operated as aVCHP, i e., possible means of providing terrestrial power with a space system of after a large amount of noncondensible gas was introduced (Author) minimum mass-and complexity The key impact that such asystem,
40 providing continuous and slightly concentrated insolation, makes on A78-37275 * # Thermal design and development of a plane the economic viability of solar farming is demonstrated New tary probe - Pioneer Venus large probe. L A Hennis and M. N developments in solar sailing are incorporated to reduce mirror mass Varon (Hughes Aircraft Co, El Segundo, Calif ). American Institute and transportation cost The system is compatible with incremental of Aeronautics and Astronautics and American Society of Mechani implementation and continual expansion to produce the world's cal Engineers, Thermophysics and Heat Transfer Conference, 2nd, power needs Key technology, environmental, and economic issues Palo Alto, Calif., May 24-26, 1978, AIAA Paper 78-916. 10 p. and payoffs are identified SOLARES appears to be economically Contract No. NAS2-8300. superior to other advanced, and even conventional, energy systems The thermal control system developed for the Large Atmo and could be scaled to completely abate our fossil fuel usage for spheric Probe of the Pioneer Venus Multiprobe Mission isdescribed power generation. (Author) The scope of the thermal control task requires maintaining the probe internal equipment shelf temperatures within a nonoperating range of -40 to 122 F and an operating range of -4to 122 F during three A78-36776 * A theoretical study of the electronic transition different mission phases (1) preseparation, the transit phase of the moment for the C2 Swan band system. J. 0. Arnold and S. R. mission when the probe is attached to the Multiprobe Spacecraft Langhoff (NASA, Ames Research Center, Computational Chemistry Bus, (2) postseparation, the free-flight cruise-phase of the mission Group, Moffett Field, Calif.). Journal of Quantitative Spectroscopy following release from the Bus, and (3) descent, the phase of the and Radiative Transfer,vol 19, May 1978, p. 461-466 26 refs mission from preentry equipment turn-on to impact on the Venus Large-scale self-consistent-field plus configuration-interaction surface Thermal control for these phases is achieved by a combina calculations have been performed for the a3Pi u and d 3Pi gstates of tion of passive thermal finishes on the probe exterior surfaces and C2 The theoretical potential curves are in good agreement with heaters mounted on the equipment shelves. Verification of the those found by a Klein-Dunham analysis of measured molecular adequacy of the total thermal design to meet all mission require constants in terms of shape and excitation energy. The sum of the ments has been completed. B.J. squares of the theoretical transition moments between the states at 2 44 bohr is 4.12 a.u which agrees with the results of shock tube measurements The variation in the sum of the squares of the A78-37354 * Rigidity-independent coronal propagation and theoretical moments with internuclear separation agrees with the escape of solar protons and alpha particles. C. Perron, V. Domingo, values of Danylewych and Nicholls (1974). Based on the data for C2 R. Reinhard, and K -P. Wenzel (ESA, Space Science Dept, Noord and mother molecules, it is suggested that Cl calculations using near wijk, Netherlands) Journal of Geophysical Research, vol 83, May 1, 20 17 2029 42 Hartree-Fock quality Slater basis sets produce highly reliable 1978, p. - . refs. Contract No. NAS2-6551. transition moments. - SCS. In a study of rigidity-independent coronal propagation pro cesses, data on the azimuthal variation of the solar proton/alpha particle ratio were obtained. Sources for the data included a statistical analysis of events observed by Heos-2, a comparative study A78-36809 Synthesis of N-substituted bisitaconimide of events recorded by both Heos-2 and Pioneer-10 and -11, and a monomers for use asthermosetting polyinide resins. S.L. Hartford, multiday survey of individual events observed by Heos-2 and S Subramanian, and J A Parker (NASA, Ames Research Center, Pioneer-10. The statistical investigation of Heos-2 events reveals an Moffett Field, Calif.) Journal of Polymer Science, Pan A - Polymer increase of the lower value of the proton/alpha-particle ratio away Chemistry, vol 16,19 7 8, p 137-153 19refs from thewell-connected region- Thedata from one or two spacecraft connected at different heliolongitudes indicates no azimuthal depen dence of the proton/alpha-particle ratio. All the data appear to A78-37270 * # Jupiter probe heatshield configuration opti- suggest rigidity-independent propagation or escape processes. J.M.B mization R. B. Dirling, Jr and J D Binder (Science Applications, Inc , Santa Ana, Calif ) American Institute of Aeronautics and Astronautics and American Society of Mechanical Engineers, Ther. A78-37649 * Nova-driven winds in globular clusters. E. H mophysics and Heat Transfer Conference, 2nd, Palo Alto, Calif., May Scott (NASA. Ames Research Center. Theoretical and Planetary 24-26, 1978, AIAA Paper 78-843 10 p. 18 refs Contract No. Studies Branch, Moffett Field, Calif ) and R. H Duriskn (NASA, NAS2-9363 Ames Research Center, Theoretical and Planetary Studies Branch, The effect of initial probe heatshield shape on the total probe Moffett Field, Calif.; Indiana, University, Bloomington, Ind.).Astro. mass loss during Jovian entry is considered. Modification of the physical Journal, Part 1, vol 222, June 1, 1978, p. 612-620. 53 refs. aerothermal environment and probe entry trajectory due to changing Recent sensitive searches for H-alpha emission from ionized probe heatshield shape is included in a computerized technique intracluster gas in globular clusters have set upper limits that conflict designed for rapid assessment of the effect of probe initial shape on with theoretical predictions. It issuggested that nova outbursts heat heatshield ma loss Results obtained indicate te importance of the gas, producing windsthat resolve this discrepancy. The incidence trajectory and lheating distribution coupling with probe shape and of novae in globular clusters, the conversion of kinetic energy of the mass change. (Author) nova shell to thermal energy of the intracluster gas, and the characteristics of the resultant winds are discussed Calculated emission from the novadriven models does not conflict with any A78-373 Carbonaceous moextr observations to date. Some suggestions are made concerning the most A78-37273 maters subjected to reme promising approaches for future detection of intracluster gas on the heating - A comparison of numerical simulation and experiments. W. basis of these models. The possible relationship of nova-driven winds C. Davy, G. P. Menees, J H Lundell, and R R. Dickey (NASA, b lar te Xresoueposlsoeconsiered . Ames Research Center, Moffett Field, Calif ). American Institute of to globular cluster X-ray sources isalso considered. iA,,th',. Aeronautics and Astronautics and American Society of Mechanical Engineers, Therneophysics and Heat Transfer Conference, 2nd, Palo A78-37732 Notes on the transonc mdiial method. D Alto, Calif., May 24-26, 1978, AIAA Paper 78-866 9 p. 22 refs. Nixon (NASA, Ames Research Center, Moffnt Field, Calmf) AAA The ablation of carbonaceous materials in a hydrogen-helium Journal,voL 16, June 1978, p 613-616 stream has been simulated using a charring materials abltor Junavo16Jne97p61-6The indicial method for calculating flutter derivatives for computer code These results are compared with the first ablation twodimensional airfoils at transonic speeds is discussed, with datadaciita to bbeest eobtained a ined fromgfrosthes the amnAmes-NASA A GiantctGiant PlanetPne PparticularPilot attention given to the effect of amoving shock on the flow Facility Test stream diagnostics and ablation effects on convective variables in the indicial method An expression for the pressure and radiative heat transfer are discussed since these parameters coefficient is developed on the basis of an explicit treatment of the constitute important input data to the numerical simulation sokmtotepesr itiuinmyte ecluae o GaphehGraphite ableatnablation was predictedpredicted t.Ato within 10 to 20%, and carbon-bon- general oscillations through use of the indicial method Explicit phenolic somewhat less accurately. (Author) inclusion cf the shock motion is not necessary if only the lift and pitching moment coefficients are desired. J M.B.
41 8228 and 0l6gation Gdndrale 4 Ia Recherche A78-3 * Zodiacal light as an indicator of interplanetary Recherche Scientifilue, Grant No. ATM-72-01282, Contracts dust. J L Weinberg (New York, State University, Albany, N.YJ and Scientifique etTechnique; NSF J G Sparrow (Weapons Research Establishment, Aeronautical No NAS25603; No. NAS2-6553. analysts of the current circuit between to and the Research Laboratories, Melbourne, Australia). In Cosmic dust A steady-state 2 is performed, assuming that the current iscarried (A78-382 6 16-90) Chichester, Sussex, England and New York, Jovian ionosphere accelerated through potential double layers in the to Wley-lnterscince, 1978, p. 75-122 191 refs. Grants No NsG-7093; by electrons The circuit analysis indicates that electrons may be No. NsG.8040. Contract No NASI-7963. flux tube. of several hundred keV. Several problems striking feature of the night sky in the tropics isthe accelerated up to energies The most of double layers are also discussed. lightwhich appears as acone in-the west-after sunset'andi associated with the formation zodiacal potential drops decouple the flux tube from the the east before sunrise. It iscaused by sunlight scattered or absorbed The parallel motion. (Author) by particles in the interplanetary medium. The zodiacal light is the satellite'sorbital only source of information about the integrated properties of the whole ensemble of interplanetary dust. The brightness and polariza tion in different directions and at different colors can provide A78-41123 * Stratospheric NO and HNO3 observations in information on the optical properties and spatial distribution of the the Northern Hemisphere for three seasons. M. Loewenstein, W. L scattering particles. The zodiacal light arises from two independent Starr (NASA, Ames Research Center, Moffett Field, Calif ), and D. physical processes related to the scattering of solar continuum G. Murcray (Denver, University, Denver, Colo-). Geophysical Re radiation by interplanetary dust and to thermal emission which arises search Letters, vol 5, June 1978, p.531-534. 12 refs by interplanetary dust and N a from solar radiation reemttethatnfraed is absorbedmanlyataveenghs ttenionis ive toNO. HNOS, and 03 levels and air temperature were measured as reertted mainly at infrared wavelengths Attention is given to a function of latitude in the 18 to 21 km region of the stratosphere, observational parameters of zodiacal lght, the methods of observa- and the sum of odd nitrogen, equal to NO + N02 + HNO3, was tion, errors and absolute calibration, and the observed characteristics calculated and compared with model predictions (N02 values were of zodiacal light G.N. inferred from photochemical equilibrium characteristics ) The data show that NO measurements generally exhibit good agreement with model predictions for low and midlatitudes but poor agreement at A78-38569 ISAs and the dwarf content of the inner high latitudes. The experimental sum of odd nitrogen mixing ratios nuclear regions of M31. 8 J.Taylor (NASA, Ames Research Center, and model predictions agree within a factor of 2-1/2 or better at Moffett Field, Calif ) and S. A Kellman. Astrophysical Journal both 20 and 40 deg N, and show excellent agreement for latitudinal SuppementSeris, vol 37, May 1978, p 101-115 90 refs dependence. M.L
A78-39448 C3 and infrared spectropiotoetry, of Y A78-41124 Interhemispheric gradients of CF2CI2, CFC13, Canum Venaticorum. J. H Goebel, J. D. Bregman, D. W.Strecker, F CCI4, and N20. B J Tyson, J. C Arvesen, and D O'Hara (NASA, C Witteborn, and E F Erickson (NASA, Ames Research Center, Ames Research Center, Moffett Field, Calif) Geophysical Research Space Sciences Div, Moffett Field, Calif.). Astrophysical Journal, Letters, vol 5, June 1978, p 535 538 13 refs Part 2 - Letters to the Editor, vol 222, June 15, 1978, p. Direct real-time gas chromatographic measurements of CF2CI2, S L129-L132 30 refs CFCI3, CCI4, and N20 were made at latitudes from 74 deg N to 62 The 1 2- to 5.6-micron spectrum of the carbon star Y CVn is deg S aboard a NASA Convair 990 as part of the 1976 NASA presented and discussed The observations were made from the CV-990 Latitude Survey Mission between Alaska and New Zealand Kuiper Airborne Observatory at an altitude of 12.5 kin, thereby A difference was found in the average mixing ratios of CF2CI2 and avoiding most of the absorption due to terrestrial water vapor. CFC13 between the Northern and Southern Hemispheres, but no Comparison of Y CVn near 5 microns with laboratory spectra differences were noted for CCI4 and N20 Tte results support some provides possible evidence for the presence of the linear natomic of the previous studies of interhemispheric tropospheric gradients molecule C3 For the first time in a carbon star the clearly formed and suggest the lack of any siqmificant tropospheric sinks (Author) band heads of the CN red system between 1.2 and 2.3 microns are observed Corroborative evidence for the presence of the molecules HCN and C2H2 is presented, and the relative contributions of C3, HCN, and C2H2 to the 3 1-micron absorltion band are discussed A78-41213 * Relative toxicity of the pyrolysis products Spectra of two other carbon stars, TX Psc and S Cep, are presented from some thermoplastic and thermoset polymers. D, A Kourtides, for comparison (Author) W J. Gilwee, Jr. (NASA, Ames Research Center, Moffett Field, Calif.), and C J. 'Hilado (San Francisco, University, San Francisco, Calif) Polymer Engineering and Science, vol. 18, June 1978, p. into a nonequilibrium, 674-676. A78-40838 * Carbon vaporization Ames Research Relative toxicity data on the pyrolysis products of a variety of stagnation-point boundary layer. T. Suzuki (NASA, The data are Center, Moffett Field, Caf ). AIAA Journal, Sl16, July 1978, p thermoplastic and thermoset polymers are presented vith a presented in terms of time to incapacitation and time to death 754-756 8 refs fixed sample weight of 1 0 g, and in terms of the apparent lethal The heat transfer to the stagnation point of an ablating concentration required to produce 50 percent mortality within a carbonaceous heat shield, where both the gas-phase boundary layer exposure period of 30 mi. (Author) and the heterogeneous surface reactions are not in chemical fixed equilibrium, is examined. Specifically, the nonequildbrium changes in the mass fraction profiles of carbon species calculated for frozen lunar craters. P_ flow are studied A set of equations describing the steady-state, A78-41753 * Interpreting statistics of small Tex.), hbnequilibrium laminar boundary layer in the axisymmetric stagna- H. Schultz, D. Gault (Lunar and Planetary Institute, Houston, In: tion region, over an ablating graphite surface, is solved, with and R. Greeley (Santa Clara, Uiversity, Moffett Field, Calif.), 14-18, 1977, allowance for the effects of finite rate of carbon vaporization P.T H. Lunar Science Conference, 8th, Houston, Tex , March Proceedings. Volume 3. (A78-41551 18-91) New York, Pergamon Press, Inc., 1977, p 3539 3564 22 refs Contract No. NSR-09-051-O01. On the modulation of the Jovian decametric Some of the wide variations in the crater-size distributions in A78-41074 as radiation by to. I - Acceleration of charged particles R A. Smith lunar photography and in the resulting statistics were interpreted (Paris, Observatorre, Meudon, Hauts-de-Seme, France) and C. K different degradation rates on different surfaces, different scaling Goertz (Iowa, University, Iowa City, Iowa). Journalof Geophysical laws in different targets, and a possible population of endogenic Research, vol. 83, June 1, 1978, p 2617-2627 26 refs Research cratois These possibilities are reexamined for statistics of 26 diameters supported by the National Research Council, Centre National de Ia different regions. In contrast to most other studies, crater
42 as small as 5 irnwere measured from enlaiged Lunar Orbiter State University of Science and Technology; Grant No. framelets According to the results of the reported analysis, the NGR-16-002-038 different crater dlist bution types appear to be most consistent with Two complementary procedures have been developed to calcu. the hypotheses of differential degradation and a superposed crater late the viscous supersonic flow over conical shapes at large angles of population Differential degradation caln account for the low level of attack, with application to cones and delta wings. In the first equilibrium in incompetent materials suchb as olecta deposits, mantle approach the flow is assumed to be conical and the governing deposits, and deep regoliths where scaling law changes and cata- equations are solved at a given Reynolds number with a time strophic processes introduce contradictions w;tl othe observations, marching explicit finite-difference algorithm In the second method G R the parabolized Navier-Stokes equations ate solved with a space marching implicit noniterative finite-difference algorithm. This latter approach is not restricted to conical shapes and provides a large A78-41796 * Influence of temperature and the role of improvement in computational efficiency over published methods chromium on the kinetics of sulfidation of 310 stainless steel D. 8 Results from the two procedures agree very well with each other and Rao (NASA, Ames Research Center, Materials and Physical Sciences with available experimental data (Author) Research Branch, Moffett Field, California, University, Lawrence Radiation Laboratory, Berkeley, Calif I and H G Nelson (NASA, Ames Research Center, Materials and Physical Sciences Research A78-41859 - An evaluation of several compressible turbu Branch, Moffett Field, Calif ). Oxidation of Metals, vol 12, Apr lent boundary-layer models - Effects of pressure gradient and 1978, p. 111-138 14 refs ERDA.NASA-sponsored research Reynolds number C C Horstman. M I Kussoy, and M J. Lanfranco (NASA, Ames Research Center, Moffett Field, Calif . American Institute of Aeronautics and Astronautics, Fluid and Seattle, Wash, July 10-12, A78-41826 - A78182 AntmpcitalgritmAn* implicit algorithm forfr thete consercnsevative Plasma1978, Paper Dynamics 78-1160. Conference, 11 p- 12 refs 11th, transonic full potential equation using an arbitrary mesh T L Hoist 17 par711. li- 12 refs (NASA, Ames Research Center, Moffett Field. Calif I American paedw tasies och supersn turbulent odary-laye turbulent boundary-layer lnstitute of Aeronauticsand Astronautics.FluidandPlasma Dyn- pared with a series of attached supersonic ics Conference. 71ti,I Seattle, Wash., July 10 12, 1978, Paper experiments over an extensive range of Reynolds numbers (11.7 x 10 78.1113 13p l9refs to the 6th to 314 x 10 to the 6th). These experiments included adverse A new, implicit approximate factorization (AF) algorithm measurements of surface pressure and skin friction for in magnitude from those of previous transonicdesigned to solve the conservative full-potential equation for the pressure gradients ranging flow past arbitrary airfois has been developed The new investigations to an order of magnitude greater. The turbulence models evaluated include algebraic and two-equation eddy-viscosity algorithm uses an upwind bias of the density coefficient to provide modelsand two full Reynoldsstress models In general all the models stability in supersonic regions This allows the simple two- and three-banded matrix form of the AF scheme to be retained over the performed e ndne of the magn it the could predict the entire flow field, even in regions of supersonic flow A numerical pressure gradient or Reynolds number and with sufficient accuracy for is used to establish an arbitrary body-fitted finite- measured skin friction for most cases transformation (Author) difference mesh Airfoil pressure distributions have been computed engineering purposes. and are in good agreement with independent results. (Author)
A78-41863 * ,, Comparison of multiequation turbulence mod' boundary-layer interaction flows. J R A78-41839 Computation of the viscous supersonic flow els for several shock-separated (NASA, Ames Research Center, Moffett over symmetrical and-asym metrical external axial corners P. Kutler Viegas and C C Horstman and Astronautics, Research Center, Computational Fluid ynamis Field, Calif ) American Institute of Aeronautics (NASA,BNch. Amesmffet Feldr Clif), TCH.mputia a d c igneros Fluid and Plasma Dynamics Conference, 71th, Seattle, Branch, Moffett Field, Calif ), T H. Pulam, and Y. C. Vigneron 1o-12, 1978, Paper78-1165 21 p 27 refs Wash., July (NASA, Ames Research Center, Moffest Field, Calfi, Iowa State 1-2 98 ae 81152 7rf Several multiequation eddy viscosity models of turbulence are University of Science and Technology, Ames, Iowa) American used with the Navier-Stokes equations to compute three classes of Institute ofAeronautics and Astronautics, Fluidand Plasma Dynam- experimentally documented sh'ock-separated turbulent boundary ics Conference, 11th, Seattle, Wash, July 10-12, 1978, Paper layer flows The types of flow studied are (1) a normal shock at 78.1135 10 p. 10 refs Research supported by the Iowa State transonic speeds in both a circular duct and a two-dimensional University of Science and Technology and NASA. channel; (2) an incident oblique shock at supersonic speeds on a flat The primary ob]ective of the reported investigation is the surface, and (3) a two-dimensional compression corner at supersonic computational verification of the experimental results obtained by speeds. Established zero-equation (algebraic), one-equation (kinetic Salas and Daywitt (1978). Two existing computer codes were used to energy), and two equation (kinetic energy plus length scale) turbu compute the supersonic flow field surrounding the external axial lence models are each utilized to describe the Reynolds shear stress corner. For the inviscid and turbulent flow results, the unsteady, for the three classes of flows These models are assessed by three-dimensional implicit code of Pulliam and Steger (1978) was comparing the calculated values of skin friction, wall pressure used. For the lamnar flow results, the unsteady two dimensional distribution, velocity, Mach number, and turbulent kinetic energy explicit procedure of Vigneron t al. (1977) was employed Inviscid profiles with experimental measurements Cf the models tested the solutions for a symmetric configuration with a rounded corner two-equation model results gave the best overall agreement with the resulted in either single or triple surface crossflow stagnation point data (Author) flows, depending on the corner radius Numerical results obtained for the same symmetric configuration tested experimentally show the crossflow in the vicinity of the corner to be away from the corner and separated and thus in agreement with the experimental oil flow results G R A78-41865 * A detailed study of attached compression corner flowfields in high Reynolds number supersonic flew G S. Settles, T J. Fitzpatrick, and S M. Bogdonoff (Princeton University, Princeton, N.J.). American Institute of Aeronautics and A78-41841 * Calculation of supersonic viscous flow over Astronautics, Fluid and Plasma Dynamics Conference, 11th, Seattle, delta wings with sharp subsonic leading edges Y C Vigneron, J. C Wash, July 1012, 1978, Paper 78-1167 10 p. 21 refs. Contract No. Tannehill (NASA, Ames Research Center, MoffettField, Calif., Iowa F44620-75-C-0080, Grant No NSG-2114. State University of Science and Technology, Ames, Iowa), and J V. An experimental study has been carried out to detail the Rakich (NASA, Ames Research Center, Moffett Field, Calif.) interaction of a compressible turbulent boundary layer with shock American Institute of Aeronautics and Astronautics, Fluid and waves of varying strengths. The interaction was produced by Plasma Dynamics Conference, 11th, Seattle, Wash., July 10-12, two-dimensional compression corners of 8, 16, 20, and 24,deg angles 1978, Paper 78-1137 20 p 32 refs Research supported by the Iowa The incoming boundary layer had an edge Mach number of 2.85 and
43 a Reynolds number of 1.7 million based on overall thickness, brief period of time (10-100 million years), liquid alkanes would not Detailed mean-flow and surface measurements are presented for the be the major factor in the formation of the channels, although their four corner angles. The 8 deg corner flow was found to be fully derivatives could contribute to the greenhouse effect or depress the attached, while the 16 deg case was near incipient separation Both freezing point of water M.L. the 20 deg and 24 deg corners produced significant flow separation regions. In the discussion of these results, emphasis is placed on the development of flowfield properties from attached to separated A78-42818 Computational study of a molecular colision conditions. Comparisons made with a computational solution of the Navier-Stokes-equations-show good-agreement-when-the corner flow process- in the -presence of an, intense radiation field - Enhanced isnot separated (Author) quenching of F by Xe in the 248-nm light of the KrF laser P L. DeVries, M S Mahlab, and T F. George (Rochester, University, Rochester, N YI Physical Review A - General Physics, 3rd Series, vol. 17, Feb 1978, p. 646 650. 36 refs NSF Grant No CHE-76 A78-41866 * Injection slot location for boundary-layer con- 06775-AO1. Grant No NsG-2198; Contracts No. F44620-74-C-0073; trol in shock-induced separation. P' R. Viswanath (NASA, Ames No F49620-78-C-0005. Research Center, Moffett Field, Calif), L. Sankaran (Hindustan Aeronautics, Ltd., Bangalore, India), P. M. Sagdeo, R_ Narasimha, and A Prabhu (Indian Institute of Science, Bangalore, India) American Institute of Aeronautics and Astronautics, Fluid and A78-43384 * Controlled vapor growth of small particles of Plasma Dynamics Conference, 11th, Seattle, Wash., July 10-12, Pd and Fe on thin A1203 substrates. H Poppa, E. H. Lee, and R D. 1978, Paper 78-1168. 10 p 15 refs. Moorhead (NASA, Ames Research Center. Institute for Surface and An experimental investigation of the effect of tangential air Microstructural Research, Moffett Field, Calif.). (American Vacuum injection, when the injection slot is located inside of what would Society and Institute of Electrical and Electronics Engineers, otherwise have been the dead air zone in a separated flow, in Symposium on Electron, Ion, and Photon Beam Technology, 14th, controlling shock-induced turbulent boundary layer separation is Palo Alto, Calif., May 26-27, 1977.) Journal of Vacuum Science and presented. The experiments were carried out at a free-stream Mach Technology, vol. 15, May-June 1978, p. 1100-1104. 10 refs. number of 26 in the separated flow induced by a compression An exploratory study, dealing with the preparation of well' corner with a 20 deg angle. The observations made were wall static defined particulate metal deposits that can be used in model studies pressures, pitot profiles, and schlieren visualizations of the flow. The of catalytic reactions, was performed. Small metal particles of Fe and results show that the present-location for injection is more effective Pd were grown in situ in an electron microscope by vapor deposition in suppressing boundary-layer separation than the more conventional onto different phase of electron transparent alumina substrates The one, where the slot is located upstream of where separation would results show that characteristic properties of the deposits, such as occur inthe absence of injection (Author) particle density, size distribution, habit, and orientation, are strongly dependent on the cleanliness, phase, and crystallographic orientation of the alumina substrate; also, the deposition conditions can be chosen in such a way as to reproducibly manipulate the overall A78-41875 * // Computation of transonic flow past projectiles deposit structure. (Author) S at angle of attack. R P. Reklis, W B. Sturek (US Army, Ballistics Research Laboratory, Aberdeen Proving Ground, Md ), and F R Bailey (NASA, Ames Research Center, Moffett Field, Calif ). American Institute of Aeronautics and Astronautics, Fluid and A78-44033 * Application of high explosion cratering data to Plasma Dynamics Conference, 11th, Seattle, Wash, July 10-12, planetary problems. V. R. Oberbeck (NASA, Ames Research Center, 1978, Paper 78-1 182. 9 p 11 refs. Moffett Field, Calif ) In Impact and explosion cratering Planetary Aerodynamic properties of artillery shell such as normal force and terrestrial implications; Proceedings of the Symposium on and pitching moment reach peak values in a narrow transonic Mach Planetary Cratering Mechanics, Flagstaff, Ariz , September 13-17, number range In order to compute these quantities, numerical 1976. (A78-44030 19-91) New York, Pergamon Press, Inc., 1977, p techniques have been developed to obtain solutions to the three. 46-65.33 refs dimensional transonic small disturbance equation about slender The present paper deals with the conditions of explosion or bodies at angle of attack. The computation is based on a plane nuclear cratering required to simulate impact crater formation Some relaxation technique involving Fourier transforms to partially de- planetary problems associated with three different aspects of crater couple the three-dimensional difference equations. Particular care is formation are discussed, and solutions based on high-explosion data taken to assure accurate solutions near corners found in shell designs, are proposed. Structures of impact craters and some selected Computed surface pressures are compared to experimental measure- explosion craters formed in layered media are examined and are ments for circular arc and cone cylinder bodies which have been related to the structure of lunar basins. The mode of ejection of selected as test cases. Computed pitching moments are compared to material from impact craters is identified using explosion analogs range measurements for atypical projectile shape (Author) The ejection mode isshown to have important implications for the origin of material in crater and basin deposits Equally important are the populations of secondary craters on lunar and planetary surfaces VP. A78-42460 * Primitive atmosphere and implications for the formation of channels on Mars. Y. L. Yung (California Institute of Technology, Pasadena, Calif) and J P Pinto (NASA, Goddard A78-44108 * Hydrogen attack - Influence of hydrogen Institute for Space Studies, New York, N.Y.) Nature, vol. 273, June sulfide. D. Eliezer and H.G. Nelson (NASA Ames Research Center, 29, 1978, p 730-732. 23 refs. Grants No. NsG-2283; No. NsG-6163 Moffett Field, Calif.). National Association of Corrosion Engineers, It is suggested that, if primitive Mars had a reducing atmosphere internationalCorrosion Forum Devoted Exclusively to the Protec of methane, this atmosphere could be polymerized tion and Performance of Materials, Houston, Tex., Mar. 6-10, 1978, composed mainly 9 by solar ultraviolet radiation to produce higher hydrocarbons These Paper. 9 p. refs. study is conducted on 12.5-mm-thick SAE compounds4 which would be low-viscosity liquids at present tempera. An experimental tures on Mars, could have contributed to the formation of channels. 1020 steel (plain carbon steel) plate to assess hydrogen attack at The Martian atmosphere model used in the analysis is similar to room temperature after specimen exposure at 525 Cto hydrogen and Sagan's (1977), except that ammonia is omitted. Major reactions in a blend of hydrogen sulfide and hydrogen at a pressure of 3.5 MN/sq this early Martian atmosphere are examined, and the number m for exposure times up to 240 hr. The results are discussed in terms densities of the lighter alkanes in the lower atmosphere of Mars are of tensile properties, fissure formation, and surface scales. It isshown determined. Since the photochemical mechanism investigated here that hydrogen attack from a high-purity hydrogen environment is would provide only a modest amount of fluid for a comparatively severe, with the formation of numerous methane fissures and bubbles along with a significant reduction in the room-temperature tensile
44 yield and ultimate strengths. However, no hydrogen attack is Aeronautics and Astronautics, Fluid and Plasma Dynamics Confer observed in the hydrogen/hydrogen sulfide blend environment, i.e. ence, I1th, Seattle, Wash., July 1012, 1978, Paper 78.1114 35 p. no fissure or bubble formation occurred and the room-temperature 21 refs. Grants No. AF-AFOSR-76-2954E, No NsG-2112, Contract tensile properties remained unchanged. It is suggested that the No N00014-76-C-0182. observed porous discontinuous scale of FeS acts as a barrier to A new method for the design of shock-free supercritical airfoils, hydrogen entry, thus reducing its effective equilibrium solubility in wings, and three-dimensional configurations is described. Results the iron lattice. Therefore, hydrogen attack should not occur in illustrating this procedure in two 'and three dimensions are given. pressure-vessel steels used in manycoal gasification processes. S.D. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock-free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications A78-44773 * The ionosphere and airglow of Venus - Pros- required on part of the upper surface of aswept wing with an NACA pets for Pioneer Venus. T E Cravens, A F Nagy (Michigan, 64A410 root section to achieve shock-free flow. Whilethe results are University, Ann Arbor, Mich ), R. H Chen, and A. I. Stewart given for invid flow, the same procedures can be employed (Colorado, University, Boulder, Colo.) Geophysical Research Let- iteratively with a boundary layer calculation in order to achieve ters, vol. 5, July 1978, p. 613616 34 refs Grant No. shock-free viscous designs. With a shock-free pressure field the NGR-23-005 015; Contracts No. NAS2-9130; No. NAS2-9477 boundary layer calculation will be reliable and not complicated by The paper presents model calculations for the Cytherean the difficulties of shock-wave boundary-layer interaction. (Author) nighttime and daytime ionosphere. It is shown how some of the proposed mechanisms can be tested with the aid of the Pioneer Venus observations scheduled for December 1978. Theoretical A78-45139 * i Computation of supersonic laminar viscous calculations of the energetics of the Cytherean ionosphere are flow past a pointed cone at angle of attack in spinning and coning performed, and it is concluded that the Project Venus measurements motion. R Agarwal and J V Rakich (NASA, Ames Research Center, will find elevated ion and electron temperatures, resulting primarily Moffett Field, Calif ). American Institute of Aeronautics and from energy fluxes associated in some manner with the solar wind. Astronautics, Fluid and Plasma Dynamics Conference, 11th, Seattle, According to this model, the energy flux will act directly on the ion Wash, ,July 10. 12, 1978, Pape, 78-1211 12 p. 8 refs. gas Ultraviolet dayglow intensities were calculated, and it IS Computational results obtained with a parabolic Naver-Stokes anticipated that hundreds of kR's of C02-related emission features marching code are presented for supersonic viscous flow past a such as the CO Cameron bands will be observed Nightside pointed core at angle of attack undergoing a combined spinning and ionosphere calculations were made assuming the precipitation of coning motion. The code takes into account the asymmetries in the energetic electrons as an ionization source, and the intensities of flow field resulting from the motion and computes the asymmetric some of the resulting emission features are calculated. M L shock shape, crossflow and streamw'se shear, heat transfer, crossflow separation and vortex structure. The side force and moment are also computed Reasonably good agreement is obtained with the side A78-44775 Correction to 'Recrculathon of energetic parti. force measurements of Schiff and Tobak Comparison is also made cles in Jupiter's magnetosphere'. D D Sentman, J A Van Allen, and with the only available numerical inviscid analysis It is found that C_ K. Goertz (Iowa, University, Iowa City, Iowa) Geophysical the asymmetric pressure loads due to coning motion are much larger Research Letters, vol 5, July 1978, p 621, 622. 6 refs Navy- than all other viscous forces due to spin and coning, making viscous supported research, Contract No. NAS2-6553 forces negligible in the combined motion (Author) An error in Pioneer 11 data reduction software has, when present, caused a phase shift of 180 deg in the assignment of spacecraft roll angles. The corrected analysis of the pitch angle distributions of energetic particles in Jupiter's magnetosphere reveals A78-45144 - # Numerical solution of two-dimensional turbu significant proton anisotropies directed toward the planet in the lent blunt body flows with an impinging shock. J. C Tannehill, Y C. southern hemisphere, contrary to the authors' (1975) original report- Vigneron (iowaState University of Science and Technology, Ames, In the northern hemisphere, both proton and electron anisotropies Iowa), and J. V. Rakich (NASA, Ames Research Center, Moffett are directed away from the planet, as reported previously The Field, Calif.). American Institute of Aeronautics and Astronautics, revised data show that the claim of direct evidence for the hypothesis Fluid and Plasma Dynamics Conference, lth, Seattle, Wash., July of recirculation of energetic particles in the Jovian magnetosphere is I10-2, 1978, Paper 78-1209 16 p 20 refs Grant No. invalid. It is suggested that indirect evidence still supports the NGR-16-002-038. hypothesis, although the recirculation process must be weaker than An implicit finite-difference method has been developed to originally envisioned and obscured by other processes M.L. compute two-dimensional, turbulent, blunt body flows with an impinging shock wave. The full time-averaged Navier-Stokes equa tions are solved with algebraic eddy viscosity and turbulent Prandtl - number models employed for shear stress and heat flux. The A78-45126 * ;, A view toward future flird dynamicscomput- irregular-shaped bow shock is treated as a discontinuity across which ang. F R Bailey (NASA, Ames Research Center, Moffett Field, are applied. A Type III turbulent Calif ) American Institute of Aeronautics and Astronautics, Fluid the Ranke-Hugondot equations and the numerical and Plasma Dynamics Conference, 11th, Seattle, Wash., July 10-12, shock interference flow field has been computed In 1978,Paper781112 11 p 10 refs results compare favorably with existing experimental data. implicit code Advances in computational fluid dynamics are paced by addition, comparisons are made between the present simulation methodology and computer resources Examples of and a previous explicit code (Author) three-dimensional fluid dynamic simulations are presented to illus trate recent developments in equation modeling and numerical inner mag methods and to point out the need for increased computer power A78-45188 Whistler mode noise in Jupiter's Electronic technology dictates that to fill this need, computers will netosphere. D D Sentman and C. K. Goertz (Iowa, University, Iowa be based on parallel processing principles. The identification of City, Iowa). Journal of Geophysical Research, vol 83, July 1, 1978, 3 1 5 1 3 1 6 5 No. parallelism in three dimensions is illustrated by examining an p. - 50 refs NSF Grant No ATM-76-82739; Contract implicit, approximate-factorization approach to the Navier-Stokes NAS2-6553 equations. Finally, two computer concepts aimed at satisfying the A study is made of the amplitude and spectral extent of whistler demands of the three dimensional Reynolds averaged Navier-Stokes mode noise in the inner magnotosphere of Jupiter. It is found that simulations are discused. (Author) the 'hat-shaped' pitch angle distributions of energetic electrons (21 and 31 MeV at L=3) are consistent with those predicted in the presence of a band-hmited spectrum of whistler mode noise The A78-45127 * 9 A new method for designing shock-free tran- equatorial maximum linear growth rate of parallel propagating sonic configurations. H. Sobieczky, N J Yu, K.-Y. Fung, and A R. whistlers are consistent with those necessary to limit the energetic Seebass (Arizona, University, Tucson, Ariz ) American Institute of electron intensities by the whistler mode instability. It is noted that
45 the wave phase speeds before wave reflection can occur at high The 45-degree half-cone forebody common to both the small and latitudes and that wave growth is limited to a disk-like region large probe configurations provides a design which meets all stability centered around the magnetic equator. The frequency extent of the and attitude requirements. The uncertainty in the dynamic stability whistler mode noise spectrum may be estimated by the range of parameter coupled with the possible variability of roll rate due to frequencies maximally unstable to equatorial linear growth A value ablation induced roll torques could, however, result in slight angle of is found for the spectral density of the broadband whistler mode attack divergence in the transonic flight regime. Minimum roll rate noise necessary to balance radial diffusion of energetic electrons requirements on the small probe are passively achieved by a vane above the critical range, and an expression is-derivedfor the energetic mounted- on the pressure-temperature sensing arm The vane was electron systemi response to fluctuations about the limiting flux sizedto provide minimum dynamic disturbance (Author) value SCS
A78-45475 * The relative fire resstance of select thermo- A78-47273 * A short history of Pulkovo Observatory. K. pasicmaterias Te rtive fir retaceres Krisciunas (NASA, Ames Research Center, Moffett Field, Calif). plastic materials D. A Kourtidles and J. A Parker (NASA, Ame Vistas in Astronomy, vol. 22. pt 1, 1978, p 27-37 9 refs. Research Center, Moffett Field, Calif ). Plastic Design and Processing, Apr 1978 11 p 11 refs The relative thermal stability, flammability, and related thermo chemical properties of some thermoplastic materials currently used A78481 12 * The radii of Uranian rings alpha, beta, gamma, in aircraft interiors as well as of some candidate thermoplastics were delta, epsilon, eta, 4, 5, and 6 from their occultations of SAO investigated Currently used materials that were evaluated include 158687. J. L. Elliot, E. Dunham (Cornell University, Ithaca, N Y), acrylonitrile butadiene styrene, bisphenol A polycarbonate, poly- L H Wasserman, R. L. Millis (Lowell Observatory, Flagstaff, Ariz) phenylene oxide, and polyvinyl fluoride Candidate thermoplastic and J. Churms (South African Astronomical Observatory, Observa materials evaluated include: 9.9-bis(4-hydroxypbenyl)fluorene tory, Republic of South Africa).Astronomical Journal, vol 83, Aug polycarbonate-poly(dimethylsiloxane) block polymer, chlorinated 1978, p. 980-992. 30 refs. NSF Grant No. AST-76-14832, Grants polyvmylchloride homopolymer, phenolphthalein polycarbonate, No. NsG.2174, No NGR-03-003-001 polyethersulfone, polyphenylene sulfide, polyarylsulfone, and poly. All available timing data for the occultations of SAO 158687 on vinylidene fluoride M.L March 10, 1977, by the cited rings of Uranus are analyzed Least-squares fits to the data are performed using a model which postulates that rings alpha, beta, gamma, and delta are circular and A78-45963 * Semirigorous bounds for the dipole moments coplanar A solution obtained under the assumption that the ring and transition moments of the LiH molecule S R. Langhoff and D plane coincides with the plane of the satellite orbits is adopted which P Chong (NASA, Ames Research Center, Moffett Field, Calif.). yields radii of 44,844 km for ring alpha, 45,799 km for ring beta, Journal of Chemical Physics, vol 69, July 1, 1978, p. 194-199 42 47,746 km for ring gamma, and 48,423 km for ring delta. The refs uncertainties in these values are discussed along with the apparent Semirigorous error limits for the dipole moments and transition shapes and inclinations of these main rings The mean radii estimated moments of LiH at R = 3.015 bohr are reported. Weinhold's formula for the other rings are 47,323 km for ring eta, 42,663 km for ring 4, for the upper and lower bounds to transition moments isextended to 42,360 km for ring 5, and 41,980 km for ring 6 F.G M_ include transitions between states of the same symmetry, and S Chong's (1976) semirigorous expression for the lower bound to the overlap between the approximate and the true wavefunctions is A78-48281 * The spiral field inhibition of thermal conduc applied to the calculation. The semirigorous theory of Chong was tion in two-fluid solar wind models. S. Nerney and A Barnes (NASA, also generalized in the sense that the zeroth-order wavefunction was Ames Research Center, Space Sciences Div , Moffett Field, Calif allowed to contain many configuration state functions instead of just Journal of Geophysical Research, vol. 83, Aug 1, 1978, p. the Hartree-Fock or first natural configuration state function M L. 3729-3739 28 refs The paper reports on two-field models which include the inhibition of thermal conduction by the spiraling interplanetary field A78-46360 The numerical solution of viscous flows at to determine whether any of the major conclusions obtained by high Reynolds number. R W MacCormack (NASA, Ames Research Nerney and Barnes (1977) needs to be modified. Comparisons with Center, Computational Fluid Dynamics Branch, Moffett Field, straight field line models reveal that for most base conditions, the Calif ) In Heat Transfer and Fluid Mechanics Institute, Meeting. primary effect of the inhibition of thermal conduction is the 26th, Pullman, Wash., June 26-28, 1978, Proceedings (A78- bottling-up of heat in the electrons as well as the quite different 46351 20-34) Stanford, Calif., Stanford University Press, 1978, p temperature profiles at a large heliocentric radius The spiral field 218-221.16 refs. solutions show that coronal hole boundary conditions do not A review is presented of implicit and hybrid methods applicable correspond to states of high-speed streams as observed at 1 AU. The to solving viscous flows at high Reynolds numbers Flows within two-fluid models suggest that the spiral field inhibition of thermal conduction in the equatorial plane will generate higher gas pressures axisymmetric channels containing stationary shock' waves, past in comparison with fows along the solar rotation axis (between 1 blunt-nosed lifting airfoils, past sharp-nosed symmetric airfoils with and 10 AU) in particular, massive outflows of stellar winds, such as buffet, past three-dimensional compression ramps with side walls, outflow from T Tauri stars, cannot be driven by thermal conduction and past ogive- and hemisphere-cylinders at angle of attack have been The conclusions of Nerney and Barnes remain essentially unchanged examined Reynolds numbers as high as 10 to the 9th power have S D been used. SCS
A78-48425 * Intensities, self-broadening, and broadening by Ar and N2 for the 301/111/- 000 band of C02 measured at different A78-46557 * I Entry dynamics performance predictions for temperatures. C B Suarez and F P. J Valero (NASA, Ames Pioneer Venus probes. R D McCloy (General Electric Co , Re-Entry Research Center, Moffett Field, Calif ) Journal of Molecular and Environmental Systems Div, Philadelphia, Pa.) In Atmospheric Spectroscopy, vol 71, June 15, 1978, p. 46 63. 32 refs- Flight Mechanics Conference. Palo Alto, Calif., August 7-9, 1978, Technical Papers (A78-46526 20 03) New York, American Institute of Aeronautics and Astronautics, Inc, 1978. p. 285-293. 8 refs A78-48835 Experimental temperature distribution and Contract No. NAS2-8300 (AIAA 78-1370) heat load characteristics of rotating heat pipes. T. C Daniels The scientific experiments planned for the Pioneer Venus entry (Swansea, University College, Swansea, Wales) and R J Williams probes require that the probes provide a stable platform at a (NASA, Ames Research Center, Moffett Field, Calif.). International controlled roll rate throughout-the atmospheric phase of the mission Journal of Heat and Mass Transfer, vol 21, Feb- 1978, p 193-201 8 refs.
46 Experimental results show conclusively that the presence of a A78-49693 * Assessment of relative flammability and small quantity of a noncondensable gas (NCG) mixed with the thermochemical properties of some thermoplastic materials. D. A working fluid has aconsiderable effect on the condensation process Kourtides and J. A. Parker (NASA, Ames Research Center, Moffett in a rotating heat pipe. The temperature distribution in the Field, Calif.). Polymer Engineering and Science, vol 18, Aug 1978, condenser shows the blanketing effect of the NCG and the ratio of p. 855-860. 10 refs the molecular weight of the working fluid to that of the NCG has a The thermochernical and flammability characteristics of some very definite effect on the shape of this distribution Some of the typical thermoplastic materials currently in use and others being effects are quite similar to the well-established data on stationary considered for use in aircraft interiors are described. The properties heat pipes (Author) studied included (1) thermal mechanical properties such as glass transition and melt temperature, (2) changes in polymer enthalpy by differential scanning calorimetry, (3) thermogravimetric analysis in (4) oxygen index, (5) A78-49231 * Comparison between infrared Martian disk an anaerobic and oxidative environment, spectra and optical properties of terrestrial analogs. W. G. Egan, T. smoke evolution, (6) relative toxicity of the volatile products of Hilgeman. and L L Smith (Grumman Aerospace Corp.. Bethpage, pyrolysis, and (7) selected physical properties The generic polymers N.Y.). Icarus, vol. 35, Aug 1978, p 209-226. 44 refs Contract No. which were evaluated included acrylonitrile-butadiene-styrene, NAS2-8664. bisphenol A polycarbonate, bisphenol fluorenone carbonate Medium spectral resolution (20 kaysers) infrared measurements dimethylsiloxane block polymer, phenolphthalein-bisphenol A poly of the Martian disk made between 2900 and 5600 kaysers from the carbonate, phenolphthalem polycarbonate, polyether sulfone, poly NASA Lear Airborne Observatory have been successfully compared phenylene oxide, polyphenylene sulfide, polyaryl sulfone, chlori with predictions derived from a model of the Martian soil and nated polyvinyl chloride homopolymer, polyvinyl fluoride, and atmosphere. Modeling of the Martian atmosphere permitted the polyvinylidene fluoride. Processing parameters including molding extraction of Martian soil reflectance in the C02 bands centered at characteristics of some of the advanced polymers are described Test 3657 kaysers. Three Martian soil analogs previously considered results and relative rankings of some of the flammability, smoke and acceptable - limonite, montmorillonte, and basalt - were analyzed to toxicity properties are presented (Author) determine the optical complex indices of refraction in the same range as the airborne observations, for mathematical modeling A charac teristic surface particle size approximately 1to 3 microns diameter is A78-50240 * # Post-Viking models for the structure of the indicated. It is concluded that the Martian soil surface near-infrared summer atmosphere of Mars A: Seiff (NASA, Ames Research optical properties are consistent with a soil composition similar to Center, Moffett Field, Calif.) In. The Mars reference atmosphere, montmorillonite or Jinonite, mixed with abasalt. (Author) Proceedings of the Twenty-first Plenary Meeting, Innsbruck, Austria, May 29-June 10, 1978 (A78-50239 23-91) Pasadena, Calif., Cali fornia Institute of Technology, Jet Propulsion Laboratory, 1978, p. A78-49471 * Evolution of rotating interstellar clouds. 1-20 11refs. III hA reference model is proposed for the structure of the Mars AmesOn the Researchformation Cnter,of multiple Space star Science systems Div., P BodenheimnerMoffett Field; (NASA.,topeeu Likatmosphere up too10k 100-kin altitude.liue Basedae onnVkn Viking data,aa theh modeloe AmesReserarch entr, Space sienhsic Jorft t l; Lick incorporates the mean temperature structure, mean surface pressure, Observatory, Santa Cruz, Calif.) Astrophysical Journal, Part 1, vol ma oeua egtadgscntnadpesr 224, Sept 1, 1978, p 488496. 60 refs. NSF Grant No. AST-76- mean molecular weight s V nant, and pressure andn densityest 17590, Grant No. NCA2-OR660-703. profiles Model profiles with Viking and Mars 6 data are compared, The evolution of a rotating massive cloud, starting at interstellar and attention is given to warm and cool models The thermal densities, continuing through a series of intermediate fragmentation boundary layer isconsidered along with the role of thermal tides 8 J. stages, and ending with stellar multiple systems with components near the main sequence, is outlined The scenario is based on results of two- and three-dimensional numerical hydrodynamical calcula tions of collapsing clouds. Transfer of spin angular momentum A78-50488 Absolute intensity measurements at different primarily into orbital motion is assumed to occur at each fragmenta- temperatures of the C-12/O-16/2 bands 30 0 1 I--00 0 0 and 30 0 1 tion stage Expected initial conditions in the cloud lead to final IV--00 0 0 C B. SuArez and F P.J Valero lNASA, Ames Research fragments which have in many cases the masses and angular momenta Center, Moffett Field, Calif.) Journal of Quantitative Spectroscopy appropriate to observed main-sequence systems. Other points of and Radiative Transfer, vol. 19, June 1978, p.569-578 13 rats. comparison with observations are briefly noted. (Author)
A78-50489 Measurement at different temperatures of A78-49475 Infrared excesses in early-type stars - Gamma absolute intensities, line half-widtls, and broadening by Ar and N2 Cassiopeiae. J. D. Scargle, E. F. Erickson, F. C.Witteborn, and D. W. for the 30 0 1 I1--0 0 0band of C02 F.P J Valero (NASA, Ames Strecker (NASA, Ames Research Center, Space Sciences Div, Research Center, Moffett Field, Calif ) and C. B Sutrez. Journal of Moffett Field, Calif.). Astrophysical Journal, Part 1,vol 224, Sept. Ouantitative Spectroscopy and Radiative Transfer, vol 19, June 1, 1978, p.527-534 39 refs. 1978, p-579-590.30 refs. Spectrophotometry of the classical Be star Gamma Cas (1-4 Vibration-rotation line intensities, self-broadening coefficients, microns, with about 2% spectral resolution) is presented. These data, and foreign-gas-broadening (Ar and N2) coefficients were measured together with existing broad-band observations, are accurately at 197, 233, and 294 K for the 30 0 1 HI-00 0 0 band of C02 at described by simple isothermal LTE models for the IR excess which 6348/cm. Values for the total band intensity, purely vibrational differ from most previously published work in three ways (1) transition moment, and vibration-rotation interaction factor were hydrogenic bound-free emission is included, (2) the attenuation of deduced from the measurements PT.H the star by the shell is included, and (3) no assumption is made that the shell contribution is negligible in some bandpass It is demon' strated that the bulk of the IR excess consists of ,hydrogenic A78-50909 * The general solution to the classical problem bound-free and free-free emission from a shell of hot ionized of the finite Euler-Bernoulli beam. M. Y Hussaini (NASA, Ames hydrogen gas, although a small thermal component cannot be ruled Research Center, Moffet Field, Calif ) and C. L Amba-Rao (NASA, out. The bound-free emission is strong, and the Balmer, Paschen, and Ames Research Center, Moffett Field, Calif., Indian Space Research Bracken discontiniities are correctly represented by the shell model Organization, Vikram Sarabhai Space Centre, Trivandrum, India). with physical parameters as follows ashell temperature of approx- Zeitschrft fur angewandte Mathematrk und Physik, vol 29, July 25, imately 18,000 K, an optical depth (at 1 micron) of about 0 5, an 1978, p. 70 4- 710 8 refs electron density of approximately 1 trillion per cu cm, and asize of An analytical solution is obtained for the problem of free and about 2 trillion cm Phantom shells (i.e., ones which do not alter the forced vibrations of a finite Euler-Bernoulli beam with arbitrary observed spectrum of the underlying star) are discussed. (Author) (partially fixed) boundary conditions. The effects of linear viscous
47 damping, Winkler foundation, constant axial tension, aconcentrated 1,4-hexadiene) (CHD) and 1,2-po[y(trans-1.4-hexadiene) (THD). It is mass, and an arbitrary forcing function are included in the analysis shown that both CHO and THD have a predominatly 1,8 diene No restriction isplaced on the values of the parameters involved, and structure and seem to cyclize mainly by the (2 + 2) thermal the solution presented here contains all cited previous solutions as cycloaddition of double bonds, and to a small extent also by special cases. (Author) sigmatropic rearrangement with hydrogen shift. V.P.
A78-51067-* A cesium-plasma TEEEC device for conversion A78-52137 * I Transport of contaminants in the planetary of laser radiation to electric power. E. J. Britt, N. S Rasor (Rasor boundary layer. I Y Lee and P. R. Swan (NASA, Ames Research Associates, Inc., Sunnyvale, Calif.), G. Lee, and K. W. Billman Center, Theoretical and Planetary Studies Branch, Moffett Field, (NASA, Ames Research Center, Moffett Field, Calif.) Applied Calif.) In Joint Conference on Applications of Air Pollution Physics Letters, vol. 33, Sept. 1, 1978, p. 384-386 11 refs. Contract Meteorology, Salt Lake City, Utah, November 29-December 2, 1977, No. NAS2-9109. Preprints. (A78-52079 24-45) Boston, Mass, American MeteorologL Tests of the thermoelectronic laser energy converter (TELEC) cal Society, 1978, p. 392-399. 10 refs concept are reported. This device has been devised as a means to A planetary boundary layer model is described and used to convert high-average-power laser radiation into electrical energy, a simulate PBL phenomena including cloud formation and pollution crucial element in any space laser power transmission scheme using transport in the San Francisco Bay Area. The effect of events in the the available high-power/efficiency infrared lasers Theoretical cal- PBL on air pollution is considered, and governing equations for the culations, based upon inverse bremsstrahlung absorption in acesium average momentum, potential temperature, water vapor mixing ratio, plasma, indicate internal conversion efficiency up to 50% with an andair contaminants are presented These equations are derived by overall system efficiency of 42%. The experiments reported were integrating the basic equations vertically through the mixed layer made with a test cell designed to confirm the theoretical model Characteristics of the day selected for simulation are reported, and rather than demonstrate efficiency; 10.6-micron laser-beam absorp- the results suggest that the diurnally cyclic features of the mesoscale tion was limited to about 0.001 of the incident beam by the short motion, including clouds and air pollution, can be simulated in a absorption region Nevertheless, confirmatory results were obtained, readily interpretable way with the model M L and the conversion of absorbed radiation to electric power is estimated to be near 10%. (Author)
A78-52388 * Comments on the note by Ara et al. on the transition moment of the C02 band near 7740 kaysers. F P. J A78-51811 Nitric oxide production by Tunguska meteor. Valero and R. W. Boese (NASA, Ames Research Center, Moffett C Park (NASA, Ames Research Center, Moffett Field, Calif.) Acta Field, Calif). Journal of Quantitatve Spectroscopy and Radiative Astronautica, vol. 5, July-Aug. 1978, p. 523-542. 40 refs Transfer, vol 20, Oct 1978, p 427. The nonequilibrium chemical processes of nitric oxide forma tion are computed for the wake of the Tunguska meteor of 1908 The wake characteristics are derived by carrying out an optically- A78-52482 * Europa - Ultraviolet emissions and the possibil- S thick radiation field analysis for ablation of the meteoroid The wake ity of atomic oxygen and hydrogen clouds. F -M Wu, D. L Judge, flow field is approximated by a one-dimensional, well-stirred reactor and R. W. Carlson (Southern California, University, Los Angeles, model. Known characteristics of the Tunguska event are imposed as Calif.). Astrophysical Journal, Part 1, vol 225, Oct 1, 1978, p constraints, and three controlling parameters -chemical composition, 325-334.39 refs Contract No NAS2-6558 density, and velocity - are varied over a range around the values Emission signals from Europa with wavelength below 800 A derived by Korobeinikov et al. (1976) and Petrov and Stulov (1975). were detected by the Pioneer 10 ultraviolet photometer. In the The calculation shows that at least 19 million tons of nitric oxide is present paper, improved procedures for data reduction are used to produced between the altitudes of 10 and 50 km. The anomalous determine the spatial region as well as the intensity of the suggested atmospheric phenomena following the event are attributed to the emission sources. The observations indicate a cloud with a radius of reactions involving nitric oxide thus produced and atmospheric about 1.5 Jupiter radii and an apparent brightness of approximately ozone. It is speculated that the nitric oxide produced by the event 10 rayleighs for a wavelength of 500 A. It is argued that neutral fertilized the area near the fall, causing the observed rapid plant oxygen atoms, along with neutral hydrogen, are produced through growth. (Author) dissociation of water ice on the surface of Europa by particle impact. Electron impact ionization excitation of oxygen atoms in the resulting cloud then gives rise to the observed emission The present are used to estimate an A78-51838 * Fire resistivity and toxicity studies of candi- source brightness and cloud radius results date aircraft passenger seat materils. L L. FeweLl (NASA. Ames oxygen column density of the order of 10 trillion per sq cm, while Research Center Moffett Field, CaLf.), F L. Trabod and, H H. the density of atomic hydrogen is at most 100 billion per sq cm and Spieth (Douglas Aircraft Co., Long Beach. Calif.). Journal of Fire 1 trillon per sq cm for molecular hydrogen. (Author) and Flammability, vol. 9, July 1978, p 377-402 8 refs- This paper describes fire resistivity studies of a wide range of candidate nonmetallic materials for the construction of improved fire A78-52504 * # The radial dependences of the interplanetary resistant aircraft passenger seats These materials were evaluated on magnetic field between 1 and 5 AU - Pioneer 10. R. L Rosenberg, M the basis of FAA airworthiness burn and smoke generation tests, G. Kivelson, P.J. Coleman, Jr. (California, University, Los Angeles, colorfastness, and animal toxicity tests. Physical, mechanical, and Calif ), and E J Smith (California Institute of Technology, Jet aesthetic properties were also included in the evaluations. Candidate Propulsion Laboratory, Pasadena, Calif ) Journal of Geophysical seat materials that have significantly improved thermal response to Research, vol 83, Sept 1, 1978, p 4165-4176 46 refs. Contract No. various thermal loads corresponding to reasonable fire threats, as NAS2-7251; Grants No NsG-7276; No. NsG-7295. they relate to in-fight fire situations, are identified (Author) Pioneer 10 vector helium magnetometer data acquired in 1972-1973 during Bartels solar rotations 1896-1918 are used to investigate the radial dependences of the distant interplanetary magnetic field (IMF) between 1 and 5 AU. Least-square fits were A78-51870 * Thermal rearrangements in 1,2-poly/1,4- determined for the radial dependences of the averages of the hexadiene/s. M A Golub (NASA, Ames Research Center, Moffett magnitudes of IMF components and total field and plane projections, Field, Calif.). Journal of Polymer Science, Part B - Polymer Letters, and radial fits were prepared for the standard deviations of these vol 16, 1978, p. 253 -260 . 6 refs. variables over the solar rotation, one day, and three-hour intervals. The work described was carried out to study the thermal The variation of the weighted averages of the radial component of rearrangements of two unsaturated diene polymers - 1,2-poly(cs- the field with respect to the heliocentric distance, the variation of
48 the tangential component of the field, and the characteristics of a, -New 1,1.1-taiayl Z,2,2-trifluoro ethanes in which the aryl subset corresponding to a relatively low average solar wind velocity radicals carry one or more substituents, were prepared by are reported. M.L. condensing trifluoro acetophanones with substituted aromatic compounds in the presence of catalytic quantities of tnfluoro methyl sulfonilc acid The reaction can be earned out under reflux in toluene or. for strikingly better results in certain cases, reactants -A78-52522 Dynamic MHD modeling of solar wind corm- are simply stirred at room temperature for about 24 to 48 tating stream interaction regions observed by Pioneer 10 and 11. M. hours. NASA Dryer, Z. K. Smith (NOAA, Space Environment Laboratory, Boulder, Colo.), E. J. Smith (California Institute of Technology, Jet Propulsion Laboratory, Pasadena, Calif.), J 0. Mihalov, J. H. Wolfe (NAS, Aes eserchCenerMofettFied, ali.),R SN78-22185"# National Aeronautics and Space Administration (NASA, Ames Research Center, Moffett Field, Calif.), R.S. Ames Research Center, Moffett Field. Calif. Stemolfson, and S. T. Wo (Alabama, University, Huntsville, Ala.). SYNTHESIS OF MULTIFUNCTION TRIARYLTRIFLUORO- Journal of Geophysical Research, vol. 83, Sept. 1, 1978, p. ETHANES POtent Applicalion 4347-4352.23 refs. Contract No. NAS7-100. William P Kray (Talladega Coll.. Ala) and Robert W. Rosser. The use of the Pioneer 10 and 11 projects to test an MHD inventors (to NASA) (Talladega Coll. Ala) Filed 30 Mar. 1978 one-dimensional time-dependent model of corotating solar wind 10 p Sponsored by NASA streams during the period from Sept. 30 to Nov. 25, 1973 is (NASA-Case-ARC-11097-2; US-Patent-AppI-SN-891875) Avail: 'described. During this period, five or six corotating interaction NTIS HC AO2/MF A01 CSCL 07C regions streamed past the two spacecraft, and, as a result of The 1.1.1-triaryl 2.2,2-trifluoro ethanes, in which the awl multiple-spacecraft radial alignment and temporally varying condi- radicals have nitrogen containing substtuents such as the amino, tions at the solar wind source, the pattern predicted by the nitrle, and acetamido groups, were prepared by the acid catalyzed. Steinolfson et al. (1975) model could be compared with observe- condensation of trifluoro acetophenones with aromatic substrates tions. The results, in general, support the validity of the model, containing aminogroups.The aminogroups maythen be converted although the neglect of thermal energy exchange leads to incorrect to nitriles, acetamides, and other derivatives by standard dlscussed.values for the proton temperature. A detailed analysis of a stream is procedures The products obtained may be used as monomers M.L. or as crosslinking agents in polymer formation. NASA
7 Arrheus' Idan N78-221566# National Aeronautics and Space Administration A78-g2,47 r law in turbulent media and Ames Research Center, Moffett Field, Calif equivalent tunnel effect. S. Tsuge (NASA, Ames Research Center, CATALYSTS FOR IMIDE FORMATION FROM AROMATIC Moffett Field, Nielsen Engineering and Research, Inc., Mountain ISOCYANATES AND AROMATIC DIANHYDRIDES Patmnt View, Calif.) and K. Sagara (Tokyo, University, Tokyo, Japan) Applcato Combustion Science and Technology, vol. 18, no. 5-6, 1978, p. Salvatore Riceitiello, Paul M. Sawko. and Carlos A Estrella. 179-189.21 refs Contract No. NAS2-9535 inventors (to NASA) Filed 24 Feb. 1978 16 p The indeterminacy inherent to the formal extension of (NASA-Case-ARC-1 1107-1; US-Patent-AppI-SN-883961) Avail: Arrhemus' law to reactions in turbulent flows is shown to be NTIS HC A02/MF A01 CSCL 07C surmountable in the case of a binary exchange reaction with a This invention relacos to the use of metal salts of caprylic; S sufficiently high activation energy. A preliminary calculation predicts (octic) acid for catalyzing the formation of imide linkages by that the turbulent reaction rate is invariant in the Arrhenius form the reaction of aromatic tetracarboxylic acid dianhydrides with aromatic polyisocyanates The preferred catalysts are stannous, except for a equivalently lowered activation energy. This is a ferric and aluminum octoates The reaction can be carried out reflection of turbulence-augmented molecular vigor, and causes an in one operation, i.e. by placing all the ingredients in a mold appreciable increase in the reaction rate. A similariw to the tunnel and heating at asuitable temperature to obtain afoamed product. effect in quantum mechanics is indicated. The anomaly associated Alternatively and preferably, a prepolymer is allowed to form with the mild ignition of oxy-hydrogen mixtures is discussed in this between the reactants, with loss of carbon monoxide equal to light. (Author) about half the theoretical quantity that can be liberated by complete reaction of the ingredients. This prepolymer is then placed in a mold and heated to form the final polyimide foam 6 Fproduct The product has outstanding thermal and fire perform A78-53674" Fire detector response in aircraft applicatons. ance, as shown by burn-through time and flame spread S J Wiersma and R G. McKee (SRI International, Menlo Park, characteristics. NASA Calif.) Aviation Engineering and Maintenance, vol. 2, Aug-Sept. 1978. p 12, 13. 18 Contract No. NAS2-8583. Photoelectric, ionization, and gas sensors were used to detect N78-27180' National'Aeronautuis and Space Administration the signatures from the radiant heat or flame of various aircraft Ames Research Center, Moffett Field. Calif materials. It was found that both ionization and photoelectric INTUMESCENT-ASLATOR COATINGS USING ENDOTHER detectors are about equally capable of detecting products of MIC FILLERS Patent pyrolysis and combustion of synthetic polymers, especially those Paul M Sawko and Salvatore R Riccitello. inventors (to NASA) containing fire-retardant additives Ionization detectors alone ap- Issued 9 May 1978 11 p Filed 23 Dec 1976 Supersedes peared to be sensitive to combustion products of simple cellulosic N77-14372 (15 - 05. n 0609) materials A gas sensor detector appeared to be insensitive to (NASA-Case-ARC-1 1043-1: US-Patent-4,088.806: pyrolysis or combustion products of many of the materials. PT.H US-Patent-Appl-SN-753964. US-Patent-Class-428-332, U S-Patent-Class-260-33.6EP. US-Patent-Class-260-33 6PQ. US-Patent-Class-260-338EP. US-Patent-Class-260-33.8UA; US-Patent-Class-260-37EP; US-Patent-Class-260-42 43, PATENTS US- Patent- Class-260-45.7 R; US-Patent-Class-260-45 75W, US-Patent-Class-260-45.85N: US-Patent-Class-260-45 9R; US-Patent-Class-427-386; US-Patent-Class-427-388A. N78.22154*# National teronautics and Space Administration. US-Patent-Class-428-313; US-Patent-Class-428-921) Avail US Ames Research Center. Moffett Field, Calif. Patent Office CSCL 110 SYNTHESIS OF MULTIFUNCTION TRIARYLTRIFLUORO- An intumescent-ablator coating composition which contains ETHANES Patent Applickion the ammonium salt of 1.4-nitroanilne-2-sulfonmc acid or 4,4 William P. Kray (Talladega Coll, Ala.) and Robert,,W Rosser. dinicrosul fanilide, a polymeric binder system and about 5 to inventors (to NASA) (Talladega. Col, Ala.) Filed 30,Mar. 1978 30% weight of an endothermic filler is reported. The filler has a 17 p Sponsored by NASA decomposition temperature about or within the exothermic region (NASA-Case-ARC-11097-1; US-Patent-Appl-SN-891872) Avail of the intumescent agent NTIS HC A02/MF A01 CSCL 07C Official Gazetteof the U S Patent Office
49 N78-27184*# National Aeronautics and Space Administration Daniel B Leiser (Stanford Univ). Howard E Gotdstein. and Marnell Ames Research Center. Moffett Field. Calif. Smith. inventors (to NASA) Filed 8 Sep. 1978 17 p LOW DENSITY BISMALEIMIDE-CARBON MICROBALLOON (NASA.Case-ARC-11169-1; US-Patent-Appl-SN-9406B8) Avail COMPOSITES Patent Application NTIS HC A02/MF Aol CSCL IID Demetrius A. Kourtides and John A Parker. inventors (to NASA) A high temperature insulating material suitable for reusable Filed 30 Jun 1978 25 p reentry heat shielding was prepared from silica fibers and (NASA-Case-ARC-11040-2; US-Patent-Appi-SN-920878) Avail: aluminostlicate fibers in a weight ratio ranging from 1"19 to NTIS HC A02/MF A01 CSCL 11D 19:1. and about 05% to 30% boron oxide, based on the total A process is described, for -constructing for -a composite fiber-weight. -Aluminoborosilicate ibersh and additibnal-free boron laminate structure which exhibits a high resistance to heat and_ oxide, up to the 30% limit. may be substituted for the aluminosili flame provides safer imntenor structures for aircraft and submarine cate fibers and boron oxide requirements Small quantities of compartments Composite laminate structures are prepared by refractory opacifiers. such as silicon carbide. may be added The the bismaleimide resin preimpregnation of a fiberglass cloth to composites are charactered by the absence of nonfibrous form a face sheet which is bonded with a bismaleimide hot matrix NASA melt adhesive to a porous core structure selected from the group consisting of polyamide paper and bismaleimide-glass fabric which is filled with carbon microballoons The carbon microballoons N78-32260 National Aeronautics and Space Administration are prepared by pyrolyzing phenolic micro-balloons in the presence Ames a naenteroatieldCas of nitrogen A slurry of the carbon microballoons is prepared to Ames Research Center. Moffett Field. Calif fill the porous core structure The porous core structure and REACTION CURED GLASS AND GLASS COATINGS r face sheet are bonded to provide panel structures exhibiting PoatE.t increased mechanicaland capacitiesmok desityvales and lower oxygen limit values'ASA Univ.).Howard and 2. GoldsteinVictor W. (Stanford Katvala. Unive.inventorsDaniel(to 8 NASA)Leiser (Stanford and smoke density values NASA Umv) Issued 8 Jun 1978 8 p Filed 29 Oct 1976 Supersedes
N77-10201 (15 - 01. p 0031) Sponsored by NASA N78-2817r*# National Aeronautics and Space Administration (NASA-Case-ARC-11051-1; US-Patent-4.093.771: Ames Research Center. Moffett Field. Calif. US-Patent-Appl-SN736910. US-Patent-Class428-312. STRUCTURAL WOOD PANELS WITH IMPROVED FIRE US-Patent-Class-65-30R. US-Patent-Class-65-60D. RESISTANCE Patent Application US-Patent-Class-106-48. US-Patent-Class106-54. Paul M Sawko. inventor (to NASA) Filed 28 Jul 1978 13 p US-Patent-Class-427-3768; US-Patent-Class-427379. (NASA-Case-ARC-i 1174-1; US-Patent-AppI-SN-929086) AvaI US-Patent-Class-427-38 US-Patent-Class-42-35; NTIS HC A02/MF AO CSCL 11D US-Patent-Class-427-380. US-Patent-Class-428-325; Wood paneling or other molded wood compositions are US-Patent-Class-428-331. US-Patent-Class-428-341; prepared from lignocellulosic particles such as finely divided wood US-Patent-Ctass-428-446: US-Patent-Class-428-920; chips, flour. or strands, by bonding such particles with 10 to US-Patent-Ctass-428-406) Aval aten Ofie SC A 33% by weight of a modified novolac resin The resin prepolymer 1R and a hardening agent such as hexamethylene tetramne are 1oa sprayed onto the particles and the mix is hot pressed to form The invention elates to reaction cured glass and glass coatings the panel or other article and.cure the prepolymer to form the prepared by reacting a compound selected from the group resin The prepolymer is formed from an alkaryl ether or halide, consisting of silicon tetrabonde. silicon hexaboride. other boron SfaSiliCides.eg. 1.4-dimethoxy-methylbenzene. and a phenol. By using the of a porousboron high and silica mixtures borosilicate with a glassreactive and glass boron frit oxidecomposed The modified resins, panels are formed that have a burn-through time of about 450 seconds as opposed to about 280 seconds, glassy composites of the present invention are useful as coatings ends. on low density fibrous porous silica insulations used as heat when tested under the same condition. The incorporation of shields and for articles such as reaction vessels that are subjected certain inorganic fillers into the prepolymer will decrease the to high temperatures with rapid heating and cooling and that flame spread index of panels in which this is done, from less ru r antemperaturet ad eated toermanshat than 200 to 60 or 70. The preferred fillers are ammonium require resistance to temperature and repeated thermal shock at phosphate or a mixture of that with ammonium oxalate Such temperatures up about 1482C (2700PF)of panels, meet Class 2 standards of the Unified Building Code- NASA
N78-31232* National Aeronautics and Space Administration N78-32434* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif Ames Research Center. Moffett Field. Calif POLYMERIC FOAMS FROM CROSS-LINKABLE POLY-N- SPRAY COATING APPARATUS HAVING A ROTATABLE ARYLENEBENZIMIDAZOLES Patent WORKPIECE HOLDER Patent Application Edward S. Harrison (Whittaker Corp. San Diego). Chadwick B Marnell 'Smith. Victor W Katvala. and Ernest E. Porter, inventors Delano (Whittaker Corp. San Diego). and Salvatore R. Riccitello. (to NASA) Filed 22 Sep 1978 12 p inventors (to NASA) (WhittakerCorp. San Diego) Issued 30 May (NASA-Case-ARC-11110-1;US-Patent-Appi-SN-945040) Avail. 1978 10 p Filed 26 Jul 1976 Supersedes N76-28421 (14 NTIS HC A02/MF AOl CSCL 13H 19 p 2447) Sponsored by NASA A spray coating apparatus is described for rotating a (NASA-Case-ARC-11008-1. US-Patent-4,092.274: workpiece relative to a spray station to obtain a uniform bwating US-Patent-Appl-SN-708951, US-Patent-Class-260-2 5N, of the workpiece. The apparatus for rotating the workpiece includes US-Patent-Class-260-47CP. US-Patent-Class-260-63N; a base support with a rotatable stage for rotation in the horizontal US-Patent-Class-260-78 41) Avail- US Patent Office CSCL plane and a rotatable stage for rotation in a second plane inclined 07D at an angle to the horizontal plane. The workpiece is rotatable Foamed cross-linked poly-N-arylenebinzimidazoles are pre- in both of two planes of rotation The workpiece support is pared by mixing an organic tetraamme and an ontho substituted detachable from the first rotatable stage and the workpiece is aromatic dicarboxylic acid anhydride in the presence of a blowing readily detachable from the worlpiece support to facilitate off agent, and then heating the prepolymer to a temperature sufficient loading of the spray coated workpiece. The workpiece holder to complete polymerization and foaming of the reactants In includes a spray guard extending around the periphery of the another embodiment of the process, the reactants are heated to workpiece to shield that surface of the workpiece where no form a prepolymer The prepolymer is then cured at higher coating is desired The two degrees of freedom provided ii the temperatures to complete foaming and polymerization rotation of the workpiece relative to the spray station permits Official Gazette of the U.S Patent Office the various f.cets nf . zaianc ti . b, sequentially ouated into an orthogonal "relationship to the sprby stationi unioronn coAfting NASA tJ78-3218s-" National Aeronautics and Space Administration Ames Research Center, Moffett Field, Calif FIBROUS REFRACTORY COMPOSITE INSULATION Patent Application
50 LIFE SCIENCES
FORMAL REPORTS
N78-19S4"4 National Aeronautics and Space Administration N78-26740* National Aeronautics and Space Administration Ames Research Center, Moffett Field. Calif Ames Research Center. Moffett Field. Calif. A COMPUTER PROGRAM FOR CALCULATING LAMINAR SPACE ECOSYNTHESIS: AN APPROACH TO THE DESIGN AND TURBULENT BOUNDARY LAYERS FOR TWO- OF CLOSED ECOSYSTEMS FOR USE IN SPACE DIMENSIONAL TIME-DEPENDENT FLOWS R D MacEiroy and M M. Averner (California Univ. at Berkeley) Tuncer Cobeci (Calif State Univ. Long Beach) and Lawrence Jun 1978 41 p refs W Carr Mar 1978 62 p refs (NASA-TM-78491) Avail NTIS HC A03/MF AOl CSCL 06K (NASA-TM-78470. A-7340) Avail NTIS HC AO4/MF A01 The use of closed ecological systems for the regeneration CSCL 20D of wastes, air and water is discussed It is concluded that such A computer program is described which provides solutions systems, if they are to be used for the support of humans in of two dimensional equations appropriate to laminar and turbulent space, will require extensive mechanical and physico-chemical boundary layers for boundary conditions with an external flow support The reason for this is that the buffering capacity which fluctuates in magnitude The program is based on the available in small systems is inadequate, and that natural biological numerical solution of the governing boundary layer equations by and physical regulatory mechanisms rapidly become inoperative an efficient two point finite difference method An eddy viscosity It is proposed that mathematical models of the dynamics of a formulation was used to model the Reynolds shear stress term closed ecological system may provide the best means of studying The main features of the method are briefly described and the initial problems of ecosystem closure A conceptual and instructions for the computer program with a listing are provided mathematical model of a closed ecosystem is described which Sample calculations to demonstrate its usage and capabilities treats the biological components as a farm. calculates the rates for lammarandturbulent unsteady boundary layerswith an external of flow of elements through the system by mass-balance flow which fluctuated in magnitude are presented Author techniques and control theory postulates, and can evaluate the requirements for mechanical buffering activities It is suggested that study of the closure of ecosystems can significantly aid in the establishment of general principles of ecological systems N78-21019#i National Aeronautics and Space Administration Author Ames Research Center. Moffett Field. Calif L A BIBLIOGRAPHY ON THE SEARCH FOR EXTRATER- N78-26973"l National Aeronautics and Space Administration RESTRIAL INTELLIGENCE Ames Research Center, Moffett Field. Calif Eugene F Mallove (Analytic Sci Corp. Reading. Mass ). Mary CRITICAL REVIEW OF AMES LIFE SCIENCE PARTICIPA- M Connors. Robert L Forward (Hughes Res Labs. Malibu. Calif). TION IN SPACELAB MISSION DEVELOPMENTTEST 3: THE and Zbligniew Paprotny (Orzeszkowej. Poland) Mar. 1978 SMD 3 MANAGEMENT STUDY 135 p refs Robert Helmreich (Texas Unv.. Austin). John Wilhelm (Texas (NASA-RP-1021) Avail NTIS HC A07/MF AOl CSCL 05B Univ., Austin) Trieve A Tanner. Joan E. Sieber (Calif. State This report presents a uniform compilation of works dealing Unv. Hayward). and Susan Burgenbauch Jun 1978 84 p with the search for extraterrestrial intelligence Entries are by refs first author with cross-reference by topic index and by periodical (NASA-TM-78494. A-7471) Avail. NTIS HC A05/MF AOl index This bibliography updates earlier bibliographies on this CSCL 05A general topic while concentrating on research related to listening A management study was conducted to specify activities for signals from extraterrestrial intelligence. Author and problems encountered during the development of procedures for documentation and crew training on experiments, as well as during the design, integration and delivery of a life sciences N78-25071*# National Aeronautics and Space Administration experiment payload to Johnson Space Center for a 7 day Ames Research Center Moffett Field, Calif simulation of a Spacelab mission Conclusions and recommenda NASA AVIATION SAFETY REPORTING SYSTEM Quarterly tions to project management for current and future Ames' life Report. 1 Apr. - 30 Jun. 1977 sciences projects are included Broader issues relevant to the Apr 1978 62 p Prepared in cooperation with Battelle Columbus conduct of future scientific missions under the constraints imposed Labs Mountain View Calif by the environment of space are also addressed A R H
tNASA-'TM.78476 A-7373 OR-5) Avail NTIS HC A04/MF AO CSCL 02A N78-27736*# National Aeronautics and Space Administration Reports describing various types of communication problems Ames Research Center, Moffett Field Calif are presented along with summaries dealing with judgment and CV 990 INTERFACE TEST AND PROCEDURE ANALYSIS decision making Concerns relating to the ground proximity OF THE MONKEY RESTRAINT, SUPPORT EQUIPMENT, warning system are summarized and several examples of true AND TELEMETRY ELECTRONICS PROPOSED FOR terrain proximity warnings are provided An analytic study of SPACELAB reports relating to profile descents was performed Problems were Bernard D Newsom Jun 1978 85 p refs found to be associated with charting and graphic presentation (NASA-TM-78484. A-7417) Avail NTIS HC A05/MF A01 of the descents with lack of uniformity of the descent procedures CSCL 06C among facilities using them and with the flight crew workload A biological system proposed to restrain a monkey in the engendered by profile descents, particularly when additional Spacelab was tested under operational conditions using typical requirements are interposed by air traffic control during the metabolic and telemetered cardiovascular instrumentation execution of the profiles A selection of alert bulletins and Instrumentation. interfaced with other electronics, and data responses to them were reviewed Author gathering during a very active operational mission were analyzed for adequacy of procedure and success of data handling by the onboard computer G
51 N78-28979f# National Aeronautics and Space Administration N78-16620# SRI International Corp. Menlo Park Calif Ames Research Center. Moffett Field. Calif STUDY TO DESIGN AND DEVELOP REMOTE MANIPULA- PROJECT PLAN FOR JOINT FAA/NASA HEAD-UP DISPLAY TOR SYSTEMS Annual Report. 1 Aug 1976 - 30 Nov. CONCEPT EVALUATION 1977 R F Haines Aug 1978 16 p Sponsored in part by DOT J W Hill and J K Salisbury. Jr Nov 1977 121 p refs (NASA-TM-78512; 'HUD-I: A-7562) Avail NTIS (Contract NAS2-8652; SRI Proi 4055) HC A02/MF AO CSCL 05A (NASA-CR-152092. AR-2) Avail NTIS HCA06/MFAOl CSCL Head-Up Display (HUD) concept for large commercial 05H turbojet transport aircraft is considered for the its contribution A description is given of part of a continuing etiort both to to aviation safety in the form of improved performance during develop models for and to augment the performance of humans the approach and landing phase flight- The basic reearch areas controlling remote manpulators The project plan cells for the represent fundamental questions that are still unresolved and performance of several standard tasks with a number of different which were considered important to the effective use of the manipulators controls, and viewing conditions using an auto HUD by pilots Project documentation and management mated performance measuring system. in addition, the project responsibilities are outlined GG plan calls for the development of a force-reflecting joystick and supervisory display system Author
N78-320764# National Aeronautics and Space Administration N78-21235# Life Systems. Inc Cleveland. Ohio Ames Research Center. Moffett Field. Calif ADVANCED SOLID ELECTROLYTE CELL FOR C02 AND NASA AVIATION SAFETY REPORTING SYSTEM Otaitrly H20 ELECTROLYSIS Final Report Report. 1 Jul. - 30 Sep. 1977 J W Shumar and T A Berger Mar 1978 52 p refs Jul 1978 62 p refs Prepared in cooperation with Battelle (Contract NAS2-7862) Columbus Labs. Mountain View. Calif (NASA-CR-152093. ER-190-25) Avail NTIS (NASA-TM-78511. A-7559. OR-6) Avail NTIS HC A04/MF A01 CSCL 07D HC A04/MF A01 CSCL 01C A solid electrolyte cell with improved sealing characteristics was examined A tube cell was designed, developed fabricated. Art analytical study of reports relating to cockpit altitude and tested Design concepts incorporated in the tube cell to alert systems was performed A recent change in the Federal improve its sealing capability included minimizing the number of Air Regulation permits the system to be modified so that the seals per cell and moving seats to lower temperature regions alerting signal approaching altitude has only a visual component. The advanced tube cell design consists of one high temperature the auditory signal would continue to be heard if a deviation ceramic cement seal. one high temperature gasket seal. and from ar assigned altitude occurred Failure to observe altitude three low temperature silicone elastomer seals The two high alert signals and failure to reset the system were the commonest temperature seals in the tube cell design represent a significant cause of altitude deviations related to this system Cockpit crew improvement over the ten high temperature precious metal seals distraction was the most frequent reason for these failures. It required by the electrolyzer drum design For the tube cell was noted by numerous reporters that the presence of altitude design the solid electrolyte was 8 mole percent yttria stabilized alert system made them less aware of altitude- this lack of zirconium oxide slip cast into the shape of a tube with electrodes altitude awareness is discussed Failures of crew coordination applied on the inside and outside surfaces Author L were also noted It is suggested that although modification of the altitude alert system may be highly desirable in short-haul aircraft. it may not be desirable for long-haul aircraft in which cockpit workloads are much lower for long periods of time In N78-22723*# Life Systems Inc. Cleveland. Ohio these cockpits, the aural alert approaching attitudes is perceived TECHNOLOGY ADVANCEMENT OF THE ELECTROCHEMP. as useful and helpful If the systems are to be modified, it CAL C02 CONCENTRATING PROCESS Annual Report appears that additional emphasis on altitude awareness during F H Schubert R R Woods. T M Hallick. and D B Heppner recurrent training will be necessary. it is also possible that flight Mar 1978 75 p refs crew operating procedures during climb and descent may need (Contract NAS2-8666) exanmination with respect to monitoring responsibilities. A selection (NASA-CR-152098. LSI-ER-258-11) Avail NTIS of alert bulletins and responses to them is presented B.B HC AO4/MF A01 CSCL 06K The overall objectives of the present program are to (1) improve the performance of the electrochemical C02 removal NASA CONTRACTOR REPORTS technique by increasing C02 removal efficiencies at pCO2 levels below 400 Pa. increasing cell power output and broadening the tolerance of electrochemical cells for operation over wide ranges of cabin relative humidity. (2) design, fabricate, and assemble N78-10684*# Pittsburgh Univ. Pa Vestibular Function development hardware to continue the evolution of the electro Research Lab chemical concentrating technique from the existing level to an FURTHER INVESTIGATION OF THE SPONTANEOUS AND advanced level able to efficiently meet the C02 removal needs EVOKED ACTIVITY OF THE PRIMARY NEURONS OF of a spacecraft air revitalization system ARS). (3) develop and STATORECEPTORS (AND OTHER RECEPTORS) OF THE incorporate into the EDC the components and concepts that LABYRINTH OF THE BULLFROG BEFORE, DURING AND allow for the efficient integration of the electrochemical technique AFTER AN EXTENDED PERIOD OF WEIGHTLESSNESS, with other subsystems to form a spacecraft ARS. (4) combine INCLUDING ALTERNATIVE INTERVALS OF ARTIFICIAL ARS functions to enable the elimination of subsystem components GRAVITY Final Report. 15 Dec 1976 - 15 Oct. 1977 and interfaces, and (5) demonstrate the integration concepts 15 Oct 1977 24 p ref through actual operation of a functionally integrated ARS (Grant NsG-2197) Author (NASA-CR-154507) Avail NTIS HC A02/MF AOl CSCL 05C N78-23748-# Life Systems, Inc. Cleveland. Ohio Vestibular neuron activity was examined by studying nerve EVALUATION OF A SPACECRAFT NITROGEN GENERATOR stimulation and evoked response A cooling element, applied to Final Report the nerve consisted of a silver hook through which a coolant R D Marshall. M K Lee. and F H Schubert Apr. 1978 fluid flowed Temperature changes were recorded via microtermis- 51 p refs tors on an eight channel brush recorder, together with response (Contract NAS2-8732) Diffusion of the cooling effect was measured, recovery time (NASA-CR-152097. ER-251-6) Avail NTIS HC A04/MF A01 was assessed, and the nerve was then studied hystologically CSCL 06K and ultrastructurally. Problems in frog preparation were discussed A research and development program was successfully along with problems in maintaining healthy specimens and bacteria completed towards the development of a method of generating controlled aquaria Author nitrogen for cabin leakage makeup aboard space vehicles. The
52 nitrogen generation concept used liquid hydrazine as the stored N78-30808*il Florida Agricultural and Mechanical Uiv. form of nitrogen. This reduced tankage and expendables weight Tallahassee School of Pharmacy associated with high p'essure gaseous and cryogenic liquid REGULATION OF THE ADRENAL CORTEX FUNCTION nitrogen storage The hydrazine was catalytically dissociated to DURING STRESS Annual Report yield a mixture of nitrogen and hydrogen. The latter was separated Karam F A Soliman 1 Sep 19_78 53 p refs to provide the makeup nitrogen The hydrogen will be used in (Grant NsG-2183) the reduction of metaboic caron dioxide Author (NASA-CR-157397) Avail NTIS HC A04/MF A01 CSCL 06S A proposal to study the function of the adrenal gland in the rat during stress is presented In the proposed project, three N78-25767*# Lockheed Missiles and Space Co. Sunnyvale, different phases of experimentation will be undertaken The first Calif phase includes establishment of the circadian rhythm of both AN INVESTIGATION OF THE REDUCTION OF CARBON brain amines and glucocoticoids. under normal conditions and DIOXIDE IN A SILENT ELECTRIC DISCHARGE Final under chromc and acute stressful conditions The second phase Report includes the study of the pharmacokinetics of glucocorticod Robert S Luce and Barbara Greenough. ed Jun 1978 63 p binding under normal and stress conditions The third phase refs includes brain uptake and binding under different experimental (Contract NAS2-9551)' conditions In the outlined experiments brain biogenic amines (NASA-CR-152146. LMSC-D626407) Aval NTIS will be evaluated, adrenal functions will be measured and stress HC A04/MF A01 CSCL 06K effect on those parameters will be studied It is hoped that this The reduction of C02 to 02 and CO in a silent electric investigation can explain some of the complex relationships discharge was studied It was found that current alone (in the between the brain neurotransmitter and adrenal function Author ionized plasma induced by the silent electric discharge) was reponsible for the C02 reduction process Voltage and frequency - were important only in so far as they induced current in the plasma Pressure and temperature were of minimum influence N78-32106# Systems Technology. Inc. Mountain View. Calif in the process The large power consumption in the process COMPUTED RESPONSES OF SEVERAL AIRCRAFT TO was recognized as resulting from the low power factor of the ATMOSPHERIC TURBULENCE AND DISCRETE WIND reactor vessel which electrically behaved like a capacitor The SHEARS Final Report power factor was subsequently improved-by adding an inductive Wayne F. Jewell. Robert L Stapleford. and Robert K Heffley element to make the reactor vessel capacitance part of a resonant Feb 1977 79 p refs circuit It was found that the C02 reduction process was most (Contract NAS2-8889) efficient in terms of power vs reduction rate when a voltage (NASA-CR-152185, STI-TR-1063-2) Avail NTIS was employed that was only slightly higher than that needed to HC A05/MF AOl CSCL 01C induce the plasma Author The computed RMS and peak responses due to atmospheric turbulence and discrete wind shears, respectively, are presented for several aircraft in different flight conditions The responses are presented with and without the effects of a typical second N7B-28807'# Life Systems. Inc. Cleveland. Ohio order washout filter. A complete set of dimensional stability ADVANCED INSTRUMENTATION CONCEPTS FOR ENVI- derivatives for each aircraft/flight condition combination evalu RONMENTAL CONTROL SUBSYSTEMS Final Report, Jul. ated is also presented Author L 1976 -Jun 1978 P Y Yang F H Schubert. J R Gyorki. and R A Wynveen Jun 1978 59 p refs (Contrac) NAS2-9251) JOURNAL ARTICLES,-BOOKS AND (NASA-CR-152100. ER-309-6) Avail: NTIS NC A04/MF A01 CSCL 05H CHAPTERS OF BOOKS Design, evaluation and demonstration of advanced instrumen tation concepts for improving performance of manned spacecraft environmental control and life support systems were successfully completed Concepts to aid maintenance following fault detection A78-25560 Chemical interpretation of Viking Lander 1 and isolation were defined A computer-guided fault correction life detection experiment G. V. Balgou, P C. Wood (San Jose State instruction program was developed and demonstrated in a University, San Jose, CalifI, T Wydeven, M E Lehwalt, and R E packaged unit which also contains the operator/system inter- Mack (NASA, Ames Research Center. Moffett Field, Calif ). Nature, face G.G vol271. Feb 16.1978, p 644, 645.9 refs An earth based evaluation of the Viking Lande 1 life detection experiments was conducted using a radiofrequency glow discharge in a simulated Martian atmosphere. The Gas Exchange Experiment N78-29699*# Systems Technology, Inc Mountain View. Calif conducted in the humid mode released substantial amounts of C02, SIMULATION AND ANALYSIS OF WIND SHEAR HAZARD 02, N2, At, and CO into the atmosphere, indicating that these Final Report, Jun. 1976 : Oct 1977 the Martian soil An adsorption John M Lehman. Robert K Heffley. and Warren F Clement substances were adsorbed onto time (d) For Dec 1977 156 p refs potential plot is given, giaphing quantity of gas against (Contract NAS2-8889) a model surfacearea of 17 sqtiares meters per gram of measured (NASA-CR 157470. AD.A052435, STI-TR-1063-3. substance, oxygen adsorption was found to be relatively high, a FAA-RD-78-7) Avail NTIS HC AOB/MF A01 CSCL 018 result which tends to confirm the hypothesis that Maitian oxygen The results of an unmanned simulation and an analysis of exists largely in chemisorbed states or in active oxygen compounds, wind shear hazard are presented The study involved the e g. peroxide. superoxide, hydroperoxide D M W. application of mathematical models of four diverse passenger aircraft types ranging from a small STOL commuter aircraft to a jumbo jet and of pilot models appropriate to eah flight situation A78-27124 * Effects of exercise and excitement on mesen The hazard to each aircraft was evaluated for both approach teric and renal dynamics in conscious, unrestrained baboons. S F. and takeoff in three severe wind shear profiles The effects of Vatner (Harvard University, Peter Bent Brigham Hospital;Children's vaiying operational techniques and propulsion system features Hospal Medical Center, Boston, New Englmd Regional Primate were investigated and explained with the aid of a simplified Hospal e Center . Bo ston.Ne in Ronal Pra linear analysis No direct correspondence was found between Posearch Center, Southboro, Mass). American Journal of Physl wind shear hazard and aircraft size or type per se Instead. the ogy, vol 234, Feb 1978, p H210-H214.24 refs..Research supported main factors affecting sensitivity to wind shear were shown to by the American Heart Association, Grants No PHS-HL.15416; No. be airspeed, flight path regulation, and airspeed regulation. Also. NsG-2136 the shear dependency as modeled in the simulation was found Raehotelemetry was used to measure arterial pressure and to be important Author mesenieric anti renal blood flows from nine unrestrained, conscious
53 baboons during periods of rest moderate exercise, and extreme A78-34503 * Light element geochemistry of the Apollo 12 excitement. A description of the experiments hardware ispresented, site. J F Kerridge, I. R. Kaplan, C C. Kung, D. A. Winter, D. L including artificial depressants phenylcyclidine hydrochloride, Friedman (California, University, Los Angeles, Calif.), and D. J. 05-1.0 mg/kg, and pentobarbital sodium, 15 mg/kg, and an DesMarais (NASA, Ames Research Center, Extraterrestrial Biology ultrasonic telemetry flow meter. Results showed rising heart rate and Div., Moffett Field, Calif.). Geochimica et Cosmochimica Acta, vol arterial pressure coupled with a reduction of mesenteric and renal 42, Apr. 1978, p.391-402.59 refs. Grant No. NGR-05-007-289. flows as the level of exercise was increased. These findings are Analytical techniques of improved sensitivity have revealed compared with mesenteric-and-renal flows.somewhat-above control details of the concentratibhs and isotopic compositions of light level, but relatively stable heart rate and arterial pressure, post. elements for a comprehensive suite of samples from the Apollo 12 prandially. Attention is given to a quantitative analysis of the regolith. These samples show a wide spread in maturity, although experimental results D M.W maximum contents observed for solar wind elements are less than observed at other sites, possibly reflecting relative recency of craters at the Apollo 12 site. Isotopic composition of nitrogen isconsistent with the idea that N-15/N-14 in the solar wind has increased with A78zon562 of Responsesa rticuarsandnepiphyteant cartil2-G time, at least a major part of this increase having occurred in the past zones of developing avian radii to estrone treatment and a 2t 3.1 Gyr. Sulfur isotope systematics support a model in which sulfur environment. J. A Negulesco and T. Kossler (Ohio State University. is both added to the regolith, by meteoritic influx, and lost, by an Columbus, Ohio). Aviation, Space, and EnvironmentalMedicine, vol isotopically selective process Most sols from this site are heavily 49, Mar. 1978, p 489-494. 42 refs. Research supported by the Ohio contammiated with terrestrial carbon. (Author) State University, Contract No. NAS2-6634, Grant No. NIH-5409. Histological measurements of radii from chickens exposed to estrone and hypergravity are reported Female chicks at two weeks post-hatch were maintained for two weeks at earth gravity or 2 G A7B-36602 * Fluid-electrolyte shifts and maximal oxygen with daily injections of 0.2 or 0.4 mg estrone Animals were uptake in man at simulated altitude /2,287 m/. J E. Greenleaf, E. M sacrificed after the last Injection, and the radii were processed by Bernauer, W. C. Adams, and L Juhos (NASA, Ames Research described histological techniques The results suggest that proximal Center, Laboratory of Human Environmental Physiology, Moffett and distal epiphysesof developing radii show different morphological Field; California, University, Davis, Calif). Journal of Applied responses to estrone and hypergravity. M L. Physiology: Respiratory, Environmental and Exercise PIysiology, vol 44, May 1978, p 652-658.33 refs. Experiments were conducted on six trained distance runners Hm(21-23 yr) subjected to an eight-day dietary control at sea level. A78-32673 Human problem solving performance in a fault followed by an eight-day stay in an altitude chamber (2287-m diagnosis task W B Rouse (Illinois, University, Urbana, Ill I IEEE altitude) and a four-day recovery at sea level. Fluid and electrolyte Transactions on Systems, Man, and Cybernetics, vol SMC-8, Apr shifts during exercise at altitude were evaluated to gain insight into 1978, p 258-271 52 refs Grant No NsG-21 19 the mechanism of reduction in working capacity. The results are It is proposed that humans in automated systems will be asked discussed in terms of resting fluid volumes and blood constituents, to assume the role of troubleshooter or problem solver and that the maximal exercise variables, and maximal exercise fuid-electrolyte L problems which they wil be asked to solve in such systems wil not shifts. Since there are no significant changes in fluid balance or be amenable to rote solution The design of visual displays for resting plasma volume (PV) at altitude, it is concluded that neither problem solving in such situations is considered, and the results of these nor the excessive PV shifts with exercise contribute to the two experimental investigations of human problem solving per- reduction in maximal oxygen uptake at altitude. During altitude formance in the diagnosis of faults in graphically displayed network exposure the percent loss in PV is found to follow the percent problems are discussed The effects of problem size, forced-pacing, reduction in maximal oxygen uptake, however, on the first day of computer aiding, and training are considered. Results indicate that recovery the percent change in PV remains depressed while maximal human peiformance deviates from-optimality as problem size oxygen uptake returns to control levels S D. increases. Forced-pacing appears to cause the human to adopt fairly brute force strategies, as compared to those adopted in self-paced situations Computer aiding substantially lessens the number of mistaken diagnoses by performing the bookkeeping portions of the A78-37055 * Stratospheric measurements of CF2CI2 and task (Author) N20. B. J. Tyson, J. F. Vedder, J. C Arvesen (NASA, Ames Research Center, Moffett Field, Calif), and R. B. Brewer Geo physical Research Letters, vol 5, May 1978, p. 369-372 21 refs Concentrated samples of stratospheric air were obtained at A78-33522 Extent of utilization of the Frank-Starling pressure altitudes of 18 3 km and 21 3 km aboard U-2 aircraft, and mechanism in conscious dogs D H Boettcher (Harvard University, at 28 3 km and 35.9 km aboard a balloon platform. The mixing Harvard Medical School, Boston, Mass ), S F. Vatner (Peter Bent ratios of CF2CI2 and N20 are reported for locations in California, Brigham Hospital, Boston, Mass.), G R. Heyndrickx (Children's Oregon, Texas, and Quebec, Canada. The observed mixing ratios - -Hospital Medical Center, Boston, Mass), and E. Braunwald (New compare within a factor of 2 to those reported by other investigators England Regional Primate Research Center, Southborough, Mass ) and show a more rapid decrease with altitude than predicted by a 1 9 7 8 American Journal ofPhysiology, vol 234, Apr. , p. H338-H345 two-dimensional model. (Author) 36 refs Research supported by the American Heart Association, Grants No. PHS-HL-15416,No PHS.HL-17459;No PHS-HL-17665, No NsG-2136 A78-37130 * A model of human decisionmaking in a fault The left ventricular end-diastolic pressure-dimension relation- diagnosis task W B. Rouse (Illinois, University, Urbana, 111.).IEEE ships in conscious dogs were studied, the ventricle was stressed to its Transactions on Systems, Man, and Cybernetics, vol. SMC-8, May limit in terms of myocardial preload in order to assess the extent of 1978, p. 357-362. Grant No. NsG-2119. use of the Frank.Starling mechanism under these conditions The Utilizing elementary concepts from the theory of fuzzy sets as preload was increased through volume loading with saline infusions, well as several nonfuzzy heuristics, a model is presented of human the provocation of global myocardial ischemia by constriction of the decisionmaking in the task of troubleshooting graphically displayed left main coronary artery, and infusion of methoxamine While left networks. The performance of the model is compared to the results ventricular end-diastolic pressure increased substantially in the of two previously reported experimental studies The ability of the reclining conscious animals, the left ventricular end-diastolic diame- model to represent human decisionmaking as a function of network ter did not increase, suggesting a minimum role for the Frank- size, forced-pacing, and computer aiding is considered. (Author) Starling mechanism in this case. J M B
54 A78-39746 * The Viking biological experiments on Mars H A McGee, and C H. Paulk (NASA, Ames Research Center, Flight P Klein (NASA, Ames Research Center, Moffett Field, Calif.) Systems Research Div. Moffelt Field, Calif) IEEE Transactions o' Icans, vol. 34, June 1978, p 666674.24 refs Systems, Mai,. and Cybernetcs, vol. SMC-8, July 1978, p 563 571 5 'The three biological expeiiments on board the Viking Mars rels Landers are discussed The gas exchange expeiiment provided A simulator study was undertaken to compare aid evaluate the periodic measurements of the composition and quantity of gases design features of the electronic displays for possible use in V/STOL from Martian surface material, either in a humid or a wet nutrient aircraft, a combined transitiOn display (Display A), a perspective sampling mode The labeled release expeiient demonstrated that display (Display B). and a hover display (Display C). Display B adding an aqueous solution of dilute radioactive compounds to presents height information via integrated elements. Displays A and Martian material caused a rapid release of labeled gas Tile results of C present information similarly except that Display C presents the pyrolytic release experiment remain difficult to interpret Data vertical and lateral guidance via conventional cross pointers. High from the first two experiments suggest that oxidants (including pilot work load was attained by evaluating the displays only as H202 and Iron oxide) rathe than biota may account for all the situational guidance displays in a simulated vehicle without stability observed reactions- J.M B. augmentation. Glide slopes of 6 and 15 deg were used, and steady-state and no-wind conditions were randomly presented Six pilots participated, and fifty-five objective performance measures A78-41162 Hormonal indices of tolerance to +Gz accelera. wale taken along with pilot opinons PTH tion in female subjects J Vernikos-Danells, M F Dallman, P Forsham, A L Goodwin, and C S Leach (NASA, Ames Research Center. Biomedical Research Div., Moffett Field, California, Univer. A78-48574 Calcium transport in Halobacterium halobium sity, San Francisco, Calif ; NASA, Johnson Space Center, Biomedical envelope vesicles. J W Belliveau and J. K Lanyl (NASA. Ames Research Div., Houston, Tex.). Aviation, Space, and Environmental Reseaich Center, Extraterrestrial Biology Div, Moffett Field, Calif.). Medic,e. vol 49, July 1978, p.886 889 17 refs Archives of Biochemistry and Biophysics, vol 186, Feb 1978, p. As a possible predictive test for screening Space Shuttle 98-105.42 rats. passengers, the secretions of the pituitary adienal system and the adrenal medulla have beeilstudsed in conjunction with exposure to gravitational acceleration three times the normal level. The 12 female subjects in the test were divided into ambulatory and bedrest groups A78-48577 * Synthesis of porous polyaromatic column Before bedrest, a high tolerance to centrifugation appeared to be packings for GC analysis of extraterrestrial atmospheres. F H linked to increases in plasma ACTH and cortisol This relationship Woeller and G. E Pollock (NASA, Ames Research Center, Moffett did not hold after bedrest Tile correlation between tolerance to Field. Califh Journal of Chromatographic Science, vol. 16, Apr. centrifugation and 24-hour urinary epinephne-to-norepinephrine 1978, p 137-140. 8refs ratios was not significant. d M B- The preparation of a polymer for the Pioneer-Venus Large Probe Gas Chromatograph and another polymer for gas-chromatographic analysis of the Jovian atmosphere is described. Technical-grade A7841164 Space colonization - Some physiological per- divinylbenzene is used as a reliable and economical source of p7ectivas L SpaWinke(NASAAmesoResearch- ee rso lpe monomer for the preparation of polymer beads. The discussion L Fie Cali AvtionSaf aEnvirme n e icne, Metiercovers monomeric preparation, polymerization apparatus, first-stage July 1978, p 98-901. 5 refs polymer beads, second-stage polymer beads, amino-polymer, col Physologial crteria dtermants g the design of the habitat f umns and gas-chromatographic testing instrumentation used The oora polymer for the Pioneer-Venus gas chromatograph is also suitable for space colony with 10,000 people are discussed Centrifugally ammonia but not for amine-analysis. However, the polymer for the generated earth-normal gravity, maximum ionizing radiation dose analysis of the Jovian atmosphere is a chemically derivatized standards less than or equal to 0 5 rem/year (obtained with passive aromatic polymer that issuitable for amine analysis. The two-stage pressures wereshielding), and an atmosphere with reduced nitrogen partial established as design requirements for the habitat However, polymerization produces a highly efficient polymer packing clearly further research is needed to determine whether humans experience superior to others prepared by adjusted dilution of the aqueous complete adaptation to weightlessness and whether there are organic suspension system. SD9 long-term effects of breathing various atmospheric mixtures and pressures JM B A78-48578 Illumination-dependent changes in the in trinsic fluorescence of bacteriorhodopsin R A Bogomolni, L Stubbs, and J K Lanyi (NASA, Ames Research Center, Extra A78-42817 Physilogic regulation of body energy storage terrestrial Biology Div , Moffett Field, California, University, San G C Pits (Virginia, University. Charlottesville, Va ) Metabolism, Francisco, Calif ) Biochemistry, vol. 17, no 6, 1978, p 1037-1041 vol. 27. Apr 1978. p 469-478 57 refs Grants No 27 refs Grants No. NIH-1-ROJ-GM-23651-01, No NSG-7151 K NGR-47-005-213, No NsG-2225 The-paper describes the intrinsic UV fluorescence of bacteria Both new and published data (rats, mice, and human beings) on rhodopsin i some detai and determines the changes during the rapid three parameters - fat mass, fat-free body mass (PFBM), and total cyclic reaction following light flashes The-results suggest that several body mass in some cases - are evaluated. Steady state values of the tryptophan residues are affected in the protein, among them one or parameters are analyzed for changes in response to specific perturb- more exposed to aqueous medium. The kinetics of the fluorescence ing agents and for their frequency distributions Temporal sequences changes coincide closely with events involving the retinal residue of values on individuals are examined for evidence of regulatory during the deprotonation and reprotonation of the Schiff base group responses The results lead to the hypothesis that the FFBM is SD regulated, but probably not as a unit, and that mass of fat is regulated with a high priority near the range extremes but with a much lower priority in the mid-range Properties and advantages of A78-48579 Methionine transport in Halobacteriurn halo. such a mechanism are discussed. (Author) bium vesicles - Noncompetitive, asymmetric inhibition by L-Cyste me. S L Helgerson (California, University, San Francisco, Calif ) and J. K. Ltnyi (NASA, Ames Research Center, Extraterrestrial Biology A78-44131 * Simulator evaluation of three situation and Div , Meffit Field, Calif) Biochemistry, vol 17, no. 6, 1978, p guidance displays for V/STOL aircraft zero-zero landing approaches. 1042-1046 24 refs M. R. Murphy, E A. Palmer, T E.Wempe (NASA, Ames Research Center, Man-Vehicle Systems Research Div , Moffett Field, Calif.), L
55 A78-48581 - Spectrophotofluorometric and electron micro- 49776 22-12) Los Angeles, American Institute of Aeronautics and scopic study of Lipofuscin accumulation in the testis of aging mice. Astronautics, Inc, 1978, p. 76-84.8 refs. J. Miquel, P_ R Lundgren (NASA, Ames Research Center, Bio- Differences between space industrialization and space coloniza medical Research Div, Moffett Field, Calif I, and J. E. Johnson, Jr tion are outlined along with the physiological, psychological, and (National Institults of Health, National Institute on Aging, Bdlti- esthetic needs of the inhabitants of a space habitat The detrimental more, Md ).Journalof Gerontology. vol 33, no 1, 1978, p. 5-19 55 effects of zero gravity on human physiology are reviewed, and the rels necessity of providing artificial gravity, an acceptable atmosphere, -and-comfortable relative humidity and temperature'm a space habitat is discussed. Consideration is also given to social organization and .A78-48671 I Gravity as a biochemical determinant. S. M. governance, supply of food and water, and design criteria for space Bi Siegel (Hawaii, University, Honolulu, Hawaii) COSPAR, Plenary colonies. Meeting, 21st, Innsbruck, Austria, May.29June 10, 1978, Paper. 20 p. 67 refs Grant No NGR-12-001-053; Contracts No NAS2-6624 No NAS2-8687. A7&-51225 Inhibition of bone formation during space Hypogravity effects on the biochemistry of living organisms are flight E. R Morey (NASA, Ames Research Center, Biomedical surveyed, and the differences found under orbital, clinostat, and Research Div , Moffett Field, Calif.) and D J Baylnk (U.S Veterans flotation conditions are examined Changes can be transient - such as Administration Hospital, Tacoma, Washington, University, Seattle, altered serum hormone and electrolyte levels in man - and disappear Wash I Science, vol 201, Sept. 22, 1978, p. 11381141. 20 refs. shortly after return to earth, or changes can be more persistent or Grant No NIH-DE-02600 NASA Order RA-18698-B permanent, as seems to be the case for changes in the skeletal system Parameters of bone formation and resorption were measured in mineral and protein constituents for humans who have been in space, rats orbited for 19.5 days aboard the Soviet Cosmos 782 biological While plant ethylene and peroxidase both increase under orbital, satellite. The most striking effects were on bone formation During clnostat, or flotation conditions, 3-PGA-dehydrogenase increases flight, rats formed significantly less periosteal bone than did control under orbital but not clinostat conditions and cytochrome C rats on the ground An arrest line at both the periosteum and the reductase and malic dehydrogenase are affected by clinostat but not endosteum of flight animals suggests that a complete cecessation of actual free fall conditions Reasons for these discrepancies are bone growth occurred During a 26-day postflight period, the defect considered. M.L. in bone formation was corrected No significant changes in bone resorption were observed. (Author)
A78-48717 * Carbon suboxide polymer, an explanation for the wave of darkening on Mars. V. I Oyama, B. J Berdahl, and F. A78-51346 * Digital filter structures having low errors and Woeller (NASA, Ames Research Center, Moffett Field, Calif.). simple hardware implementation A I.Abu.E]-Haila (IBM Thomas J COSPAR, Plenary Meeting, 21st, Innsbruck, Austria, May 29-June Watson Research Center, Yorktown Heights, N Y.), K. Shenoi 10, 1978, Paper. 14 p. 30 refs (Telecommunications Center, Stamford, Conn I, and A M Peterson The carbon suboxide thermal polymer or its irradiated product (Stanford University, Stanford, Calif ) IEEE Transactions on is affected by water vapor. The polymerized carbon suboxide Circuits and Systems, vol. CAS-25, Aug 1978, p. 593-599 20 refs simulates the Martian wave of darkening on the inner wall of a glass Grants No. NGL-05-020 014, No NsG-2121, No NCA2.OR745-614, tube when humidified by passage of water vapor through the tube. Contract No N00014-75-C-0601 The polymer was visibly darkened by the advancing vapor front. Sensitivity and roundoff errors can seriously limit the With increasing polymer thickness and/or water vapor concentration application of recursive digital filters in practice, particularly when the wave of darkening similarly intensifies simulating the dark fringe the filters have poles near z = + 1 A filter structure, based on digital in the Martian circumpolar areas Surfaces are lightened constantly incremental computers is proposed, which has low sensitivity, good being renewed by particulate material settling from the atmosphere, error characteristics, and simple hardware implementation for pole It is hypothesized that light and dark areas have polymer coatings, locations close to z = + 1. Expressions for the roundoff errors are but light areas have small particles which scatter white light more derived and compared to those for conventional structures. A design effectively and appear brighter on the surface of Mars (Author) procedure is suggested to implement the new filter structure given the transfer function Simulation results are presented (Author)
A78-48719 // Continuous metabolic and cardiovascular rtea surements on a monkey subject during a simulated 6-day Spacelab A78-51886 * Square Ising ferromagnetic and mission. N Pace, D F Rah]mann, R C Mains. A M Kodama antiferromagnetic lattices in a magnetic field - A new perturbation (California, University, Berkeley, Calif), and E. P. McCutcheon approach. S Aronowitz (NASA, Ames Research Center, Chemical (NASA, Ames Research Center, Biomedical Research Div, Moffett Evolution Branch, Moffett Field, Calif). Physical Review B -Solid Field, Calif.). COSPAR, Plenary Meeting, 21st, Innsbruck, Austria, State, 3rd Series, vol 17, Mar 1, 1978, p 2305-2315 15 refs May 29-June 10, 1978, Paper. 5 p 6 refs Grant No NsG.7262 Contract No A-3994-B. An adult male pig-tailed monkey (Macaca nemestrina) with -surgically implanted biotelemetry unit was inserted into a fiberglass .pod system which was installed in a Spacelab mock-up to simulate a A78-53400 * Computer display and manipulation of biolog 6-day mission during which extensive physiological measurements cal molecules. Y Coeckelenbergh, R D. MacElroy (NASA, Ames were obtained. The purpose of the pod was to make possible the Research Center, Extraterrestrial Biology Div, Moffett Field. Calif ), study of respiratory gas exchange. Body temperature and selected Har (NASA, Ames Research Center, Computation Div , Moffett cardiovascular parameters were recorded continuously for 2.6 days Field, Calif I, and R.Ben (Roswell Park Memorial Institute, Buffalo, prior to 'launch', 6.3 days during 'flight', and 1 8 days after 'landing' N Y . Computers and Graphics, vol 3,1978, p 9-16.20 refs The results are surveyed, and it is concluded that it is feasible to This Paper describes a computer model that was designed to perform sound physiological experiments on nonhuman primates in investigate the conformation of molecules, macromolecules and subsequent complexes. Utilizing an advanced 3-D dynamic computer display system, the model is sufficiently versatile to accommodate a large variety of molecular input and to generate data for multiple A78-49780 * #t Space habitats. R. D. Johnson (NASA, Ames purposes such as visual representation of conformational changes, Research Center, Moffett Field, Calif.). In: Our extraterrestrial and calculation of conformation and interaction energy. Molecules heritage: From UFO's to space colonies, Proceedings of the Joint can be built on the basis of several levels of information. These Symposium, Los Angeles, Calif., January 28, 1978. (A78- include the specification of atomic coordinates and connectivities
56 and the grouping of building blocks and duplicated substructures disposed between two circular bellows. Cables are secured to using symmetry rules found in crystals and polymers such asproteins the rings, shell, and bellows. The cables limit the motion.of the and nucleic acids. Called AIMS (Ames Interactive Molecular model- bellows when the suit is pressurized NASA ing System), the model is now being used to study pre-biotic molecular evolution toward life (Author) N78-22720# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif A78-53874 * Degradation of biochemical activity in so,. SWEAT COLLECTION CAPSULE Patent Application sterilized by dry heat and gamma radiation. K L. Shih and K A. John'E. Greenleaf and Robert W Delaplame. inventors (to NASA) Souza (NASA, Ames Research Center, Extraterrestrial Biology Div, Filed 19 Apr. 1978 10 p Moffett Field, Calif.). Originsof Life, vol. 9, Sept. 1978 p 51-63 16 (NASA-Case-ARC-11031-1, US-Patent-AppI-SN-897828) Avail refs NTIS HC A02/MF A01 CSCL 06B The 'effect of soil sterilization by dry heat (0.08% relative A sweat collection capsule permitting quantitative collection humidity),gamma radiation, or both on soil phosphatase, urease, and of sweat is described The capsule was comprised of a frame decarboxyase activity was studied. Son sterilzed by a long exposure held immobile on the skin, a closure secured to the frame and toderboxyeas areltivy w tdie.rSoiastelize atong ex 5 e absorbent material located next to the skin in a cavity formed to dry heat at relatiely low temperatures (eight weeks at 100.5 C) by the frame and the closure. The absorbent materials was retained higher activities than did soil exposed to a higher, tempera. removed from the device by removing the closure from the frame ture (two weeks at 124.5 C), while all activity was destroyed by four while the frame was held immobile on the skin. NASA days at 148 5 C Sterilization with 7 5 Mrads destroyed less activity than did heat sterilization. The effect of several individually nonsterizing doses of heat radiation isdescribed M.L. N78-272756# National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif -CHELATE-MODIFIED POLYMERS FOR ATMOSPHERIC GAS A78-53875 Chemical evolution and the origin of life - CHROMATOGRAPHY Patent Application Bibliography supplement 1976. M. W. West, R. A. Koch (San Jose Warren W Christensen. Ludwig A Mayer (San Jose State Univ, State University, San Jose, Calif.), and S. Chang (NASA, Ames Calif). and Fritz H. Woeller, inventors (to NASA) (San Jose State Research Center, Moffett Field, Calif.). Origins of Life, vol. 9, Sept. Univ. Calif) Filed 30 Jun 1978 20 p Sponsored by NASA . 1978, p.67-74. 125 refs. Grant No. NCA2-0A675-707 (NASA-Case-ARC-11154-1; US-Patent-Appi-SN-921626) Avail. NTIS HC AO2/MF AO1 CSCL 07D New polymeric materials were developed to serve as the stationary phase in chromatographic columns These materials consist of a crosslinked polymer matrix, e g , a divinylbenzene PATENTS polymer, into which was embedded an inorganic complexed ion or chelate, eg. Co(acacen), which is NN*-ethylene-bis (acetylacetoniminato)cobalt (2) Organic nitrogenous bases, such N78-14104" National Aeronautics and Space Administration as pyridine. may be incorporated into the chelate-polymer Ames Research Center. Moffett Field. Calif. complexes to increase their chromatographic utiity- Critical factors L AUTOMATIC MULTIPLE-SAMPLE APPLICATOR AND in obtaining satisfactory chromatographic performance from the ELECTROPHORESIS APPARATUS Patent polymer-chelate complexes are identified as (1) the nature and Benjamin W Grunbaum inventor (to NASA) (Calif Univ, Berkeley) concentration of the nonpolar diluent, n-heptane and ethylbenzene Issued 6 Dec 1977 7 p Fied 24 Nov 1976 Supersedes being preferred. (2) completeness of crosslinking of the matrix, N77-12157 (15 - 03. p 0305) Sponsored by NASA (3) the chelate content of the complex, and (4) the nature and (NASA-Case-ARC-10991-1. US-Patent-4.061.561: concentration of the coordinating organic base employed. NASA US-Patent-Appl-SN-744574. US-Patent-Class-204-299R. US-Patent-Class-204-18OG) Avail US Patent Office CSCL 07D N78-27733- National Aeronautics and Space Administration An apparatus for performing electrophoress and a multiple- Ames Research Center. Moffett Field. Calif sample applicator is described Electrophoresis is a physical TREAD DRUM FOR ANIMALS Patent process in which electrically charged molecules and colloidal Wayne H Howard. inventor (to NASA) Issued 9 May 1978, particles, upon the application of a do current, migrate along a 7 p Filed 31 Mar 1976 Supersedes N76-20485 (14 - 11, gel or a membrane that is wetted with an electrolyte. A p 1394) multiple-sample applicator is provided-which coacts with a novel (NASA-Case-ARC-10917-1: US-Patent-4.088.094. tank cover to permit an operator either to depress a single US-Patent-Appl-SN-672223: US-Patent-Class-119-29) Avail button, thus causing multiple samples to be deposited on the US Patent Office CSCL 06B gel or on the membrane simultaneously, or to depress one or A device for exercising animals such as primates is described, more sample applicators separately by means of a separate button for each applicator. Official Gazette of the U S Patent Office which includes a cylindrical housing mounted for rotation about a horizontal axis of revolution and has a cylindrical treadway portion on which the animal treads while the drum is rotated by means of a motorized drive The treadway portion of the N78-18763*# National Aeronautics and Space Administration drum includes an electrode structure-with sectors being indepen Ames Research Center. Moffett Field. Calif dently energizable by means of a commutator and source of SPACESUIT MOBILITY JOINTS Patent Application potential so that an electrical shock station is created behind a Hubert C Vykukal. inventor (to NASA) Filed 3 Mar. 1978 running-m-place station on the moving tre&dway. In this manner 45 p if the animal should fall behind its running-m-place station, it (NASA-Case-ARC-11058-2: US-Patent-AppI-SN-883094) Avail may be shocked by treading on the energzed electrode structure NTIS HC AO3/MF A01 CSCL 05H One end of the tread drum comprises a transparent wall for Aspacesuit is presented having a waist joint, shoulder joints, unobstructed viewing of the animal being exercised elbow joints, hip joints, and ankle joints Each of the jointsincludes Official _Gazette of the U S Patent Office at least one pair of annuli supported for pivotal displacement about paralleling axes and a flexible, substantially impermeable diaphragm of a tubular configuration spanning the distance N78i31233 National Aeronautics, and Space Administration. between the annuli and connected thereto in a hermetically sealed Ames Research Center. Moffett Field, Calif. relationship The diaphragm includes at least one rolling convolu- BORON TRIFLUORIDE COATINGS FOR THERMOPLASTIC lion having a crown disposed in a fixed relation with an axis MATERIALS AND METHOD OF APPLYING SAME IN GLOW about which one of the annuli pivots The knee joint is constructed DISCHARGE Patent slightly different from the other joints. A curved tubular shell is Ronald Michael Kubacki. inventor (to NASA) (Bell and Howell,
57 Chicago) Issued 23 May 1978 4 p Filed 17 Jun 1977 Alow temperature plasma polymerization process is described Supersedes N77-26308 (15 - 17, p 2243) Sponsored by for applying an optical plastic substrate, such as a polymethyl NASA methacrylate lens, with a single layer abrasive resistant coating (NASA-Case-ARC-11057-1; US-Patent-4.091.166. to improve the durability of the plastic US-Patent-AppI-SN-807762. US-Patent-Ciass-428-41 1. Official Gazette of the U.S. Patent Office US-Patent-Class-350-165; US-Patent-Class-350-175NG. US-Patent-Class-427-40. US-Patent-Class-427-41, US-Patent-Class-427-164: US-Patent-Class-428-412. US-Patent-Class-428-422, US-Patent-Class-428-447. US:Patent-Clhsso428-51 5. US-Patent-Class-428-5 2 3 US-Patent-Class-428-538) Avail US Patent Office CSCL 07D Plastic surfaces can be improved physically and optically by treating them with a plasma of boron trifluonde The trifluoride can be the sole reactant or be part of a mixture also containing an organic monomeric substance such as perfluorobutene-2 or an organosdane. The boron trifluoride-containing coating can also serve as an intermediate-coating between the plastic surface and a plasma deposited organic polymer. Official Gazette of the U S Patent Office
N78-317359 National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif SPACESUIT MOBILITY JOINTS Patent Hubert C Vykukal. inventor (to NASA) Issued 30 May 1978 22 p Filed 23 Dec 1976 Supersedes N77-15641 (15 - 06 p 0789) (NASA-Case-ARC-11058-1. US-Patent-4.091.464. US-Patent-Appl-SN-753965: US-Patent-Class-2-2 1A. US-Patent-Class-285-235) Avail- US Patent Office CSCL OSH Joints for use in interconnecting adjacent segments of an hermetically sealed spacesut which have low torques, low leakage and a high degree of reliability are described Each of the joints is a special purpose joint characterized by substantially constant volume and low torque characteristics Linkages which restrain the joint from longitudinal distension and a flexible, substantially impermeable diaphragm- of tubular configuration spanning the distance. between pivotally supported annuli are featured The diaphragms of selected joints include rolling convolutions for balancing the joints while various joints include wedge-shaped sections which enhance the range of motion for the joints Official Gazette of the U.S Patent Office
N78-31736- National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif. SPACESUIT TORSO CLOSURE Patent Bruce W Webbon and Hubert C Vykukal, inventors (to NASA) Issued 30 May 1978 8 p Filed 23 Mar 1977 Supersedes N77-25784 (15 - 16, p 2170) (NASA-Case ARC-11100 1; US-Patent 4.091.465. US:Patent-Appl-SN-780569; US-Patent-Class-2-2 1A) Avail US Patent Office CSCL 05H A simple, economical and reliable entry cloure is described for joining opposite halves of a torso section for a pressure suit in a manner which simplifies self-donning A single coupling ,joins coaxially aligned, axially separable. tubular segments of a .hard spacesuit along an angulated zone of separation, adapted to bd mated in an hermetrically sealing relation A releasable C section clamp secures the members in their mated relation ;hip Official Gazette of the U S Patent Office
N78-32854' National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif PROCESS FOR PRODUCING A WELL-ADHERED DURABLE OPTICAL COATING ON AN OPTICAL PLASTIC SUBSTRATE Patent Ronald M Kubacki. inventor (to NASA) (Bell and Howell Chicago) Issued 20 Jun 1978 7 p Filed 15 Dec 1976 Sponsored by NASA (NASA-CArs.ARr.1 1039.1 US.Palont-4 096 115 US-Patent-Appl-SN-750655: US-Patent-Class-428-412: US-Patent-Class-35 1-166. US-Patent-Class-427-38: US-Patent-Class-427-41: US-Patent-Class-427-44. US-Patent-Class-427-164, US-Patent-Class-427-302. US-Patent-Class 427-322, US-Patent-Class-427-387. US-Patent-Class-428-447) Avail US Patent Office CSCL 2OF
58 RESEARCH SUPPORT
FORMAL REPORTS
N78-19801# National Aeronautics and Space Adrinnistration and Bill A- Williams (San Jose State Univ. Calif) May 1978 Ames Research Center Moffett Field. Calif. 43 p refs A SINGLE USER EFFICIENCY MEASURE FOR EVALUATION (Grait NsG-2293) OF PARALLEL OR PIPEUNE COMPUTER ARCHITEC- (NASA-TM 78486. A-7423) Avail NTIS HC A03/MF A01 TURES coo CSCL 06B W P Jones In its Future Computer Requirements for Compute- An implant telemetry system for the simultaneous monitoring tional Aerodynamics Feb 1978 p 363-371 (For availability of temperature activity, and EKG from small animals, such as see N78-19778 10-9) rats. was designed with the feature that instead of a battery Avail NTIS HC A22/MFA01 CSCL098 the system is energized by an inductive field A 250 kHz resonant A precise statement of the relationship between sequential coil surrounds the cage (30 x 30 x 20 cm) and provides the computation at one rate, parallel or pipeline computation at a approximately 100 microns of power required to operate the much higher rate. the data movement rate between levels of implant transmitter while allowing the animal unrestrained memory, the fraction of inherently sequential operations or data movement in the cage The implant can also be battery operated that must be processed sequentially the fraction of data to be - if desired RF transmission is in the 8-10 MHz band which moved that cannot be overlapped with computation, and the allows the use of a simple, essentially single IC chip, receiver relative computational complexity of the algorithms for the two Author processes, scalar and vector, was developed The relationship should be applied to the multirate processes that obtain in the employment of various new or proposed computer architectures N78.24364# California Uni Berkeley Dept of Chemical for computational aerodynamics The relationship, an efficiency Engineering measure that the single user of the computer system perceives. STRESS-STRAIN BEHAVIOR OF SOME ACRYLIC GRADI argues strongly in favor of separating scalar and vector proces- ENT POLYMERS ses. sometimes referred to as loosely coupled processes. to achieve C F Jasso. S D Hong. and M. Shen 10 Feb 1978 17 p optimum use of hardware. Author refs (Contract N00014-75-C-0955) (AD-A052617. TR-17) Avail NTIS HC A02/MF AOl CSCL R 11/9 N7S-19911# California Univ. Los Angeles Dept of Physics Multcomponent polymers whose structure or composition NON-UNEAR PARAMETRIC GENERATION OF SOUND BY varies as a function of position in the sample are called gradient RESONANT MODE CONVERSION Intrim Report polymers One way to prepare gradient polymers is-to permit a Steven Lurie Garrett Dec 1977 201 p refs guest monomer to diffuse into a host polymer network The (Contract N00014-75-C-0246) resulting profile of the diffusion gradient is fixed by polymerizing (AD-A049157. TR-39) Avail NTIS HC A1O/MF AO CSCL the monomer in situ In this work we used 2-chloroethyl acrylate 20/1 as the monomer and poly(methyl methacrylate) as the polymer When non-linear terms are included in the two fluid matrix Both gradient polymers and interpenetrating networks hydrodynamic description of superfluid helium-4. first sound and were prepared It was found that the stress-strain behavior of second sound are coupled The interaction of two second sound gradient polymers is quite different from that of the interpenetra of comparable composition The former shows a wavesoccur atto aproduce speciic a propagating first sound wave is shown to ting networks angle which makes the pont of intersection yield point, and considerably enhanced fracture strain. The latter of the second sound waves travel at the speed of first sound is essentially rubber in character Possible mechanisms for the An experiment to observe this mode conversion process in a unique properties of gradient polymers are discussed waveguide of rectangular cross-section is described Measure- Author (GRA) ments show that the resonant conversion occurs at the theoretically predicted frequency The amp;,tude of the mode N78-30862*# National Aeronautics and Space Administration converted first sound is found to exhibit a quadratic dependence Ames Research Center,.Moffett Field, Calif. on the amplitude of the primary wave which is characteristic of A -DECODING PROCEDURE FOR THE -REEb-SOLOMON a second order effect. A new application of the reciprocity CODES calibration technique allowed an absolute calibration of the Raymond S rim Aug 1978 25 p refs pressure microphones in situ Absolute measurements of the (NASA-TP-1286: A-7372) Avail NTIS HCA02/MF AOl CSCL coupling of first sound to second sound agree with theory. This 09B agreement is a direct confirmation of the importance of the A decoding procedure is described for the (n.k) t-error additional, intrinsically non-linear, Galilean invariant variable, in correcting Reed-Solomon (RS) code, and an implementation of the thermohydrodynamics of superfluid helium. The theoretical the (31.15) RS code for the 14-TENEX central system. This code formalism is applied to the parametric amplification of second can be used for error correction in large archival memory systems sound by high intensity first sound and the results are in The principal features of the decoder are a Galois field arithmetic disagreement with a previous calculation by Khokhlov and unit implemented by microprogramming a microprocessor, and Pushkina Author ifRAl syndrome calculation by using the g(x) encoding shift register Complete decoding of the (31.15) code is expected to take less than 500 microsecs The syndrome calculation is performed by hardware using the encoding shift register and a modified Chien N78-23706r# National Aeronautics and Space Administration. search The error location polynomial is computed by using Lin's Ames Research Center. Moffett Field Calif table, which is an interpretation of Berlekamp's iterative algorithm AN INDUCTIVELY POWERED TELEMETRY SYSTEM FOR The error location numbers are calculated by using the Chien TEMPERATURE, EKG, AND ACTIVITY MONITORING search Finally. the error values are computed by using Forney's Tnomas B Fryer Gordon F Lund (San Jose State Univ Calif), method LS
59 N78-33784"# Informatics-PMI. Inc. Palo Alto, Calif. N78-3239S National Aeronautics and Space Administration X10: A FORTRAN DIRECT ACCESS DATA MANAGEMENT Ames Research Center. Moffett Field. Calif SYSTEM ANGLE DETECTOR Ptint David P. Roland In NASA Langley Res. Canter Eng and Sci. Gilbert T Parra, inventor (to NASA) Issued 13 Jun. 1978 8 p Data Management 1978 p 155-182 (For primary document Filed 10 Nov 1976 Supersedes N77-11364 (15 - 02. p see N78-33776 24-61) 0194) (Contract NAS2-6914) (NASA-Case-ARC-11036-1. US-Patent-4.094.073. Avail NTIS HC A12/MF AOl CSCL 09B US-Patent-AppI-SN-740457: US-Patent-Class-33-366) Avail The XIO system isaset ofsubroutmesthat provide generalized US-Patent-Office CSCL 14B data management capability for FORTRAN programs using a An angle detector for determining a transducer's angular direct access file. Arrays of integer, real, double precision, and disposition to a capacitive pickup element is described The character data may be stored, each logical group of data transducer comprises a pendulum mounted inductive element identified by a unique matrix number. A matrix may be organized moving past the capacitive pickup element. The capacitive pickup and stored as batches to reduce core requirements Batches element divides the inductive element into two parts L sub 1 may be accessed randomly or sequentially. The file may be and L sub 2 which form the arms of one side of an a-c bridge checkpointed and retained, allowing for restarts with stored values Two networks R sub 1 and R sub 2 having a plurality of binary The XIO subroutines operate on either IBM 360-370/OS/VS or weighted resistors and an equal number of digitally controlled DEC PDP-11/RSX computing systems. G.G. switches for removing resistors from the networks form the arms of the other side of the a-c bridge. A binary counter, controlled by aphase detector, balances the bridge by adjusting the resistance of R sub 1 and R sub 2 The binary output of the counter is representative of the angle- NASA CONTRACTOR REPORTS Official Gazette of the U S Patent Office
N78-32731*# Technology Development Corp, Sunnyvale, Calif N78-33717"# National Aeronautics and Space Administration. THE ILMAC IV MEMORY SYSTEM: CURRENT STATUS Ames Research Center. Moffett Field. Calif. AND FUTURE POSSIBILITIES MCR-FLUID CAN E FOeINGA. David Stevenson 8 May 1978 142 p Prepared in cooperation MICRO-FLUID EXCHANGE COUPUNG APPARATUS Ptnt with Lear Siegler. Inc.. Santa Monica. Calif and Computer Sci. Application Corp, Los Angeles John E Johnson (San Francisco Univ. Calif) and Paul F Swartz. (Contracts NAS2-8870; NAS2-8728: NAS2-9359) inventor (to NASA) Filed 16 Oct. 1978 13 p (NASA-CR-152177) Avail NTIS HC A07/M 1 CSCL (NASA-Case-ARC-11114-1. US-Patent-Appl-SN-951422) Avail: 09 e NTIS HC A02/MF AO CSCL 06B The future needs of researchers who will use the Iliac were In a microfluid exchange apparatus for exchanging fluid with examined and the requirements they will place on the memory an organ, such as the trachea or a blood vessel of a small system were evaluated Various alternatives to replacing critical animal, a syringe needle is provided for penetrating the fluid memory components were considered with regard to cost, risk, conduit of the animal. The syringe needle is coupled to a plenum system impact, software requirements, and implementation chamber having an inlet and outlet port The plenum chamber schedules The current system, its performance and status, and is coupled to the syringe needle via the intermediary of a standard the limitations it places on possible enhancements are discussed quick disconnect coupling fitting. The plenum chamber is R as well as the planned enhancements to the Iliac processor, carried at the end of adrive rod which is coupled to a micrometer After a brief technology survey, different implementations are drive head. The micrometer drive head is slidably and pivotably presented for each system memory component Three different coupled to a pedestal for adjusting the height and angle of memory systems are proposed to meet the identified needs of inclination of the needle relative to a reference base support the Iliac user community. These three alternatives differ The needle is positioned adjacent to the incised trachea or a considerably with respect to storage capacity and accessing blood vessel of a small animal and the micrometer drive head capabilities, but they all offer significant improvements over the is operated for penetrating the fluid conduit of the animal. current system. The proposed systems and their relative merits NASA are analyzed A R.H
PATENTS
N78-27425- National Aeronautics and Space Administration- Ames Research Canter, Moffett Field, Calif ROTARY LEVEUNG BASE PLATFORM Patent Robert W Delaplame and Daniel L Mossolani. inventors (to NASA) Issued 9 May 1978 5 p Filed 2 Nov. 1976 Supersedes N77-10498 (15 - 01. p 0069) (NASA-Case-ARC-10981-1: US-Patent-4.088.291; US-Patent-Appi-SN-738218. US-Patent-Class-248-186. US-Patent-Class-248-178) Avail: US Patent Office CSCL 131 A leveling apparatus for the precise adjustment of a 'scientific instrument is reported A base member is provided having a hollow cylindrical shape. A table for supporting the instrument rests on the base and has a shaft portion extending below the table The upper portion of the shaft fits tightly into the hollow portion of the base member whereas the lower portion of the shaft is machined to fit loosely The lower portion of the shaft is provided with a groove Adjusting screws are threaded through the hollow cylindrical portion and are adapted to enter the groove By adjusting the screws, the lower portion of the shaft is moved in a vertical plane since the shaft isloosely fitted into the cylinder The upper portion of the shaft which is tightly fitted into the upper end of the cylinder causes the cylinder to deform slightly providing a fulcrum point which allows the table to be leveled in response to the adjustment of the adjusting screws- Official Gazette of the U S Patent Office
60 FEDERAL AVIATION ADMINISTRATION
FORMAL REPORTS
N78-14033# Federal Aviation Administration. Moffett Field. Calif Flight Simulation Branch CERTIFICATION STUDY OF A DERIVATIVE MODEL OF A SMALL JET TRANSPORT AIRPLANE USING A PILOTED RESEARCH SIMULATOR Final Report Raymond D Forrest Jun 1977 86 p refs (AD-A046442. FAA-RD-77-105). Avail NTIS HC A05/MF A01 CSCL 01/3 The flight simulator for advanced aircraft at Ames Research Center was used to evaluate the flying qualities of a srmall let transport and those of a derivative model of that airplane Technical criteria that piloted simulations must meet to enable their increased use for demonstrating compliance with transport category aircraft airworthiness requirements -were defined Flying-qualities data were obtained for numerous test configurations and conditions using conventional certification flight test procedures These data correlated well with the basic airplane data from the manufactur er's certification test report Analysis of the simulator data show valid results in critical test cases, such as the demonstration of static longitudinal stability and minimum control speed, with confidence that all influencing and limiting factors were identified An important aspect was the accurate simulation of the control force-feel qualities of the reversible flight control system The simulator was judged to have duplicated actual flight results with a high degree of confidence Author T
61 U.S. ARMY RESEARCH AND TECHNOLOGY LABORATORIES AND AEROMECHANICS LABORATORY
FORMAL REPORTS
N78-17000*# National Aeronautics and Space Administration. unsteadiness. In some 'cases, the fluctuations will be almost Ames Research Center. Moffett Field. Calif complete stochastic: in others it will be highly organized; and DYNAMIC STALL EXPERIMENTS ON THE NACA 0012 :m still others, it will be a combination of random and periodic AIRFOIL :componehts Some peculiar unsteady phenomena are reviewed Kenneth W. McAlister, Lawrence W. Carr. and William J and several classes of flow problems are discussed Flow McCroskey Jan. 1978 166 p refs visualization and pressure measurements are used to explore (NASA-TP-1100, A-7096) Avail NTIS HCAOB/MF A01 CSCL externaLflows past fluff bodies, unsteady separation on slender 0.1A bodies, and internal flows A R H The flow over a NACA 0012 airfoil undergoing large oscillations in pitch was experimentally studied at a Reynolds number of 2.5 million and over a range of frequencies and ampli- tudes Hot-wire probes and surface-pressure transducers were N78-18383# National Aeronautics and Space Administration. used to clarify the role of the laminar separation bubble, to delne- Ames Research Center. Moffett Field. Calif ate the growth and shedding of the stall'vortex, and to quantify the SOME UNSTEADY SEPARATION PROBLEMS FOR SLI- resultant aerodynamic loads. In addition to the pressure DER BODIES distributions and normal force and pitching moment data that W J McCroskey In AGARD Three Dimensional and Unsteady have often been obtained in previous investigations, estimates Separation at High Reynolds Numbers Feb. 1978 11 p refs of the unsteady drag force during dynamic stall have been derived (For availability see N78-18375 09-34) from the surface pressure measurements Special characteristics Avail NTIS HC Al1/MF A01 CSCL 20D of the pressure response, which aresymptomaticoftheoccurrence The development of reliable prediction techniques for and relative severity of moment stall, have also been examined, engineering purposes requires a fundamental and detailed Author understanding of the unsteady flow fields on wings and rotating blades. Some of the peculiar features of unsteady separated flows that are not simple analogs or extensions of quasi-steady flows are discussed. These include the unsteady Kutta- S N78-18043" Natinal Aeronautics and Space Administraion. Joukowski condition, dynamic stall on oscillating airfoils (with shock STABIUITY OF HELICOPTERS WITH applications to helicopter rotor blades) and unsteady AEROMECHANICAL layer interaction A BEARINGLESS MAIN ROTOR. PART 1: EQUATIONS wave-boundary OF MOTION Dewey H Hodges Feb. 1978 102 p refs Prepared in cooperation with Army Aviation Res and Develop Command. Moffett Field. N78-18387*# National Aeronautics and Space Administration. Calif Ames Research Center, Moffett Field. Calif. (NASA-TM-78459; A-7301-Pt-1) Avail NTIS PREDICTION OF UNSTEADY SEPARATED FLOWS ON HC A06/MF A01 CSCL 01C OSCILLATING AIRFOILS Equations of motion for a coupled rotor-body system were W. J. McCroskey In AGARD Three Dimensional and Unsteady derived for the purpose of studying air and ground resonance Separation at High Reynolds Numbers Feb. 1978 8 p refs characteristics of helicopters that have bearingless main rotors (For availability see N78-18375 09-34) For the fuselage, only four rigid body degrees of freedom are Avail- NTIS HC A1/MF A01 CSCL 20D considered longitudinal and lateral translations, pitch, and, roll Calculating the flow around an airfoil undergoing dynamic The rotor is assumed to consist of three or more rigid blades stall is a task which has not yet been accomplished at high Each blade is joined to the hub by means of a flexible beam Reynolds numbers, although several approximate analytical segment Jflexbeam or strap). Pitch change is accomplished by methods have been proposed, The most promising of those •twisting the flexbeam with the pitch-control system, the methods seemstobeerthera combination of the discrete potential characteristics of which are variable Thus, the analysis is capable vortex and thin boundary layer approaches, or a significantly of implicitly treating aeroelastic couplings generated by the improved version of the strong viscous-inviscid interaction flexbeam elastic deflections, the pitch-control system, and the approach The former may prove to be superior for low speed. angular offsets of the blade and flexbeam. The linearized high amplitude flows, but the latter seems likely to be more equations are written in the nonrotating system retaining only suitable for airfoils that operate under supercritical transonic flow the cyclic rotor modes: thus. they comprise a system of conditions and for cases that do not penetrate deeply into stall. homogeneous ordinary differential equations with constant At the present time, the engineer who is faced with the need coefficients All contnbutions to the linearized perturbation to predict the aerodynamic forces and moments on oscillating equations from inertia, gravity, quasi-steady aerodynamics, and airfoils would be better advised to turn to one of the empirical the flexbeam equilibrium deflections are retained exactly. Author correlation techniques. or perhaps to utilize more than one method and average the results In any event, these methods permit the essential features of dynamic stall to be described, even though further improvements are highly desirable Future efforts N78-18381"# National Aeronautics and Space Administration will probably see more use made of the two-dimensional Ames Research Center. Moffett Field. Calif theoretical analyses, while experiments can be expected to play INTRODUCTION TO UNSTEADY ASPECTS OF SEPARA- the majorrole in assessing the importance of the three-dimensional TION IN SUBSONIC AND TRANSONIC FLOW effects that are likely to be encountered in practice. Author W. J. McCroskey In AGARD Three Dimensional and Unsteady Separation at High Reynolds Numbers Feb. 1978 8 p refs (For availability see N78-18375 09-34) Avail. NTIS HC Al1/MF A01 CSCL 20D N78-19065# National Aeronautics and Space Administration. Almost any flow that separates will have some degree of Ames Research Center. Moffett Field, Calif.
62 WATER-TUNNEL EXPERIMENTS ON AN OSCILLATING N78-29044# National Aeronautics and Space Administration AIRFOIL AT RE EQUALS 21,000 Ames Research Center. Moffett Field. Calif Kenneth W. McAlister and Lawrence W_ Carr Mar 1978 84 p AN EXPERIMENTAL INVESTIGATION OF HINGELESS refs HELICOPTER ROTOR-BODY STABILITY IN HOVER (NASA-TM-78446. A-7232) Avail. NTIS HC A05/MF AOl William G Rousman Jun 1978 49 p refs Prepared in CSCL O1A cooperation with US Army Aviation Research and Development Flow visualization experiments were performed in a water Command. St Louis, Mo. tunnel on a modified NACA 0012 airfoil undergoing large (NASA-TM-78489 AVRADCOM-TR-78-17(AM). A-7430) Avail amplitude harmonic oscillations in pitch Hydrogen bubbles were NTIS HC A03/MF AO CSCL 02A used to (1) create a conveniently striated and well preserved Model tests of a 1 62 m diameter rotor were performed to set of inviscid flow markers, and (2) to expose the succession investigate the aeromechanical stability of coupled rotor-body of events occurring within the viscous domain during the onset systems in hover Experimental measurements were made of of dynamic stall. Unsteady effects were shown to have an modal frequencies and damping over a wide range of rotor speeds important influence on the progression of flow reversal along Good data were obtained for the frequencies of the rotor lead-lag the airfoil surface prior to stall. A region of reversed flow underlying regressing mode The quality of the damping measurements of a free shear layer was found to momentarily exist over the the body modes was poor due to nonlinear damping in the entire upper surface without any appreciable disturbance of the gimbal ball bearings Simulated vacuum testing was performed viscous-inviscid boundary. A flow protuberance was observed to using substitute blades of tantalum that reduced the effective develop near the leading edge. while minor vortices evolve from lock number to 0 2% of the model scale value while keeping an expanding instability of the free shear layer over the rear the blade inertia constant The experimental data were compared portion of the airfoil The complete breakdown of this shear with theoretical predictions and the correlation was in general layer culminates in the successive formation of two dominant very good Author vortices Author
N78-32831"# National Aeronautics and Space Administration fJ78-28403*# National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif Ames Research Center, Moffett Field. Calif HOVERING IMPULSIVE NOISE: SOME MEASURED AND INTRODUCTION TO UNSTEADY ASPECTS OF SEPARA- CALCULATED RESULTS- TION IN SUBSONIC AND TRANSONIC FLOW D A Boxwell (AVRADCOM Res and Techro Labs). Y H. Yu W. J McCroskey In AGARD Three Dimensional and Unsteady (AVRADCOM Res and Technol Labs). and F H Schmitz Sepaiation at High Reynolds No Feb 1978 8 p refs (For (AVRADCOM Res and Techno Labs) In NASA Langley Res primary document see N78-28397 19-34) Center Helicopter Acoustics Aug 1978 p 309-322 refs (For Avail NTIS HC A11/MF A0l CSCL 20D primary document see N78-32816 23-71) Unsteady flow phenomena are reviewed with emphasis on Avail NTIS HC A17/MF A0I CSCL 20A separated flow in the subsonic and transonic regimes Specific In-plane impulsive noise radiating from a hovering model topics discussed include external flows past bluff bodies. unsteadj rotor was measured in an anechoic environment The hover separation on slender bodies, and internal flows J MS acoustic signature was compared with existing theoretical prediction models with previous forward flight experiments using the same model rotor These hover tests showed good experimen tal consistency with forward flight measurements, both in X y pressure level, and waveform character, over the range of Mach -- Y N7s-2840E# National Aeronautics and Space Administration numbers tested (0 8 to 1.0) Generally poor correlation, however, Ames Research Center. Moffett FIld. CahLf was confirmed with current linear theory prediction efforts Failure SOME UNSTEADY SEPARATION PROBLEMS FOR SLEN- to predict' both the peak pressure levels and the shape was DER BODIESreotdesealywt resntpMahnmr JMS W J McCroskey In AGARD Three Dimensional and Unsteady reported, especially with increasing tip Mach number JMS Separation at High Reynolds No Feb-1978 11 p refs (For primary document see N78-28397 19-34) Avail NTIS HC Al1/MF A01 CSCL20D N78-33209*# National Aeronautics and pace Admiistration The unsteady Kutta-Joukowski condition, dynamic stall on N7es3eseach1Cnt eronaticd ac m r oscillating airfoils, and unsteady shock wave-boundary layer AN APPROXIMATE SOLUTION FORTHE FREEVIBRATIONS interaction are discussed Emphasis is placed on developing reliable OF ROTATING UNIFORM CANTILEVER BEAMS orediction techniques and suppression of unsteady separation David A Peters Sep 1973 43 p refs Revised on oscillating control surfaces, wings, and rotating blades to Aters Sep 17 43 p rf Revised improve aerodynamic stability J M S CSCL(NASA-TM-X-62299: 20K A-5137) Avail NTIS HC AO3/MF AO Approximate solutions are obtained for the uncoupled frequencies and modes of rotating uniform cantilever beams N78-28409*# National Aeronautics and Space Administration The frequency approximations for flab bending, lead-lag bending. Ames Research Center. Moffett Field Calif and torsion are simple expressions having errors of less than a PREDICTION OF UNSTEADY SEPARATED FLOWS ON few percent over the entire frequency range These-expressions OSCILLATING AIRFOILS provide a simple way of determining the relations between mass W J McCroskey In AGARD Three Dimensional and Unsteady and stiffness parameters and the resultant frequencies and mode Separation at High Reynolds No. Feb 1978 8 p refs (For shapes of rotating unform beams Author primary document see N78-28397 19-34) Avail NTIS HC A11/MF AOl CSCL 20D Techniques for calculating high Reynolds number flow around an airfoil undergoing dynamic stall are reviewed - Emphasis is NASA CONTRACTOR REPORTS placed on predicting the values of lift, drag and pitching moments Methods discussed include the discrete potential vortex method; thin boundary layer method, strong interaction between inviscid N78-10117'# Systems Technology. Inc Mountain View. Calif. and viscous flows, and solutions to the Navier-Stokes equations THE DETERMINATION OF SOME REQUIREMENTS FOR A Empirical methods for estimating unsteady airloads on oscillating HELICOPTER FLIGHT RESEARCH SIMULATION FACILITY airfoils are also described These methods correlate force and J B Sinacori Sep 1977 59 p refs moment data from wind tunnel tests to indicate the effects of (Contract NAS2-9421) various parameters, such as airfoil shape. Mach number, amplitude (NASA-CR-152066: TR-1097-1) Avail NTIS and frequency of sinosoldal oscillations, mean angle, and type HC A04/MF AOl CSCL 14B of motion j M S Important requirements were defined for a flight simulation facility to support Army helicopter development In particular requirements associated with the visual and motion subsystems
63 of the planned simulator were studied The method used in the With an overall goal of defining the needs and requirements for motion requirements study is presented together with the short-haul transport aircraft research and development, the objective underlying assumptions and a description of the supporting data of this paper is to determine the performance and noise impact of Results are given in a form suitable for use in a preliminary short-haul transport aircraft designed with an advanced turboprop design- Visual requirements associated with a television camera/ propulsion system. This propulsion system features high-speed model concept are related The important parameters are described propellers that have more blades and reduced diameters Aircraft are together wth substantiating data and assumptions Research designed for short and medium field lengths; mission block fuel and recommendations are given Author direct-operating.costs-(DOC)-are used-as-performance measures. The propeller diameter was optimized to minimize DOC Two methods are employed to estimate the weight of the acoustic treatment N78-19155*g Cincinnati Univ. Ohio Dept. of Aerospace needed to reduce interior noise to an acceptable level. Results show Engineering and Applied Mechanics decreasing gross weight, block fuel, DOC, engine size, and optimum THEORETICAL AND EXPERIMENTAL STUDY OF AERODY- propfan diameter with increasing field length The choice of acoustic NAMICS, HEAT TRANSFER AND PERFORMANCE OF A treatment method has asignificant effect on the aircraft design. RADIAL TURBINE Final Report. 1 Oct. 1973 - 30 Oc (Author) 1977 W. Tabakoff Sep 1975 56 p refs Sponsored in part by Army Air Mobility Res and Develop Lab (Contract NAS2-7850) (NASA-CR-152105) Avail NfIS HC A04/MF AOl CSCL 21E A two-dimensional finite difference numerical technique is presented to determine the temperature distribution in a solid blade of a radial turbine guide vane. A computer program is written in FORTRAN 4 for the IBM 370/165 computer. The computer results obtained from these programs have a similar behavior and trend as those obtained by experimental results Author
N78-33065*# Kaman.Aerospace Corp. Bloomfield, Conn THEORETICAL STUDY OF MULTICYCUC CONTROL OF A CONTROLLABLE TWIST ROTOR A Z Lemnios and Frank K Dunn Apr 1976 68 p refs (Contract NAS2-7738) (NASA-CR-151959; R-1393) Avail NTIS HC A04/MF A01 CSCL 010 Analytical studies were performed to ascertain the feasibility of reducing helicopter rotor induced 4/rev vibratory forces by mdans of multicychc flap control input on a dual control, four bladed rotor system The dual control consisted of a primary )(5y inboard pitch horn blade control and a secondary outboard flap control Flap control was put in at frequencies greater than the rotor rotational speed Author
JOURNAL ARTICLES, BOOKS AND CHAPTERS OF BOOKS
A78-22570 * 4' Stress analysis study in cooled radial inflow turbine. A Hamed, Y Sheorin, and W Tabakoff (Cincinnati, University, Cincinnati, Ohio). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala., Jan. 16-18, 1978, Paper 78-94. 10 p. 9 refs Contract No. NAS2-7850. With increased turbine inlet temperatures, numerical methods of thermal and stress analysis are becoming more valuable in the design of air-cooled turbines This paper presents a study of the stresses associated with different cooling patterns in a radial inflow turbine rotor. The finite element method is used in the stress calculations taking into consideration centrifugal, thermal and aerodynamic loading. The effects of temperature distribution and the presence of internal cooling passages are discussed (Author)
A78-47930 * # Application of advanced high speed turboprop technology to future civil short-haul transport aircraft design. J. A Conlon (U.S. Army, Research and Technology Laboratories, Moffett Field, Calif.) and J. V. Bowles (NASA, Ames Research Center, Moffett Field, Calif.). American Institute of Aeronautics and / Astronautics, Aircraft Systems and Technology Conference, Los Angeles, Calif., Aug. 21-23, 1978, Paper 78-1487 13 p 8 refs.
64 SECTION II
INDEXES SUBJECT INDEX
Typical Subject Index Listing rt ILEIO
AERIAL PHOTOGRAPHY Gco ib j ACCELERATION (PHYSICS) High altitude perspective --- cost-reiAburSa NT RIGH GRAVITY ENVIONMENTS services using NASA U-2 aircraft NT PARTICLE ACCELERATION [NASA-SP-41273 p0027 N78-3150P, Acceleration and heating of the solar wind 2 ACCELERATION TOLERANCEpO NI-91 NASA Hormonal indices of tolerance to *Gz acceleration TITLEEPORT aGCACESO in female subjects -- personnelslcini 5 p005 A78-41162 ACCIDENT PREVENTION Tle title isused to provide a description of the subject matter When the title is Fire detector response in aircraft applications 4 insufficiently desctiptive of the document content a tile extension is added sep- p00 9 A78-53674 ratediomtrhe tile by three hyphens The SfAR or /AA accession number isin- ACCUMULATORS eluded in each entry to assist the user in Iocaing the abstract in the abstract sec- NT SOLAR REFLECTORS Iron If applicable a report number is also included as an aid in identifying the ACIDS document Tihe page and accession numbers are located beneath and to the right NT CYSTEINE of the title Under any one subject heading the accession numbers are arranged NT KETIONINE in sequence with the lAA accession numbers appearing fist NT NITRIC ACID ACOUSTIC GENERATORS U SOUND GENERATORS ACOUSTIC MEASUREMENTS NT NOISE MEASUREMENT A Use of coherence and phase data between two ABIOGENESIS receivers in evaluation of noise environments chemical evolution and the origin of life - pOO16 A78-26495 Bibliography supplement 1976 ACOUSTICS p0057 A78-53875 NT AEROACOUSTICS ABLATION Non-linear parametric generation of sound by vhe response of heat-shield materials to intense resonant mode conversion 9 laser radiation fAD-AO49157] pG05 N78-19901 [AIAA PAPER 78-138] p0034 A78-22583 ACRYLIC RESINS Analysis of ablation debris from natural and Stress-strain behavior of some acrylic gradient artificial iron meteorites polymers p0039 A78-34506 [AD-AO52617] pOO59 N78-24364 Carbon vaporization into a nonequilibrium, ACTINOMETERS stagnation-point boundary layer NT INFRARED DETECTORS p004 2 &78-40838 NT RADIOMETERS Meteor ablation spheres from deep-sea sediments NT SPECTEOHELIOGRAPHS [NASA-TK-78510] p0028 U78-34021 ACTIVATION ENERGY ABLATIVE MATERIALS Arrhenius' law in turbulent media and an Carbonaceous materials subjected to extreme eguivalent tunnel effect --- in binary exchange heating - A comparison of numerical simulation chemical reactions 0 0 4 9 and experiments --- Jovian entry conditions p A78-52547 FAIAA PAPER 78-866] - p0041 A78-37273 On the possibility of negative activation energies Intumescent-ablator coatings using endotheraic in bimolecular reactions 26 fillers . [NASA-TM-78509] p00 N78-29149 FNASA-CASE-ARC-11O43-1] pOG49 $78-27180 ACTIVITY (BIOLOGY) ABLATIVE NOSE CONES Degradation Of biochemical activity in sol1 Jupiter probe heatshield configuration optimization sterilized by dry heat and gamma radiation 7 [AIAA PAPER 78-843] pOOl A78-37270 pOO5 A78-53874 ABORTED MISSIONS An inductively powered telemetry system for Earth reencounter probabilities for aborted space temperature, EKG, and activity monitoring disposal of hazardous nuclear waste [NASA-TM-78486] pOO59 H78-23706 p0038 A78-31921 ADAPTIVE CONTROL ABRASION RESISTANCE Survey of adaptive image coding techniques process for producing a well-adhered durable p003 1 A78-15267 optical coating on an optical plastic substrate ADAPTIVE CONTROL SYSTEMS --- abrasion resistant pclymethyl metbacrylate U ADAPTIVE CONTROL lenses ADDITION RESINS FIASA-CASE-ARC-11039-1] p0058 N78-3285Q NT ACRYLIC RESINS ABSORBENTS ADDITIVES Sweat collection capsule Continued development of doped-germanium (NASA-CASE-ARC-11031-1] p0057 N78-22720 photoconductors for astronomical observations at ABSORPTION BANDS wavelengths from 30 to 120 micrometers 29 U ABSORPTION SPECTRA [NAS-CR-152125] pOO N78-22000 ABSORPTION SPECTRA ADRENAL GLAND Simultaneous determination of rotational and Regulation of the adrenal cortex function during translational temperatures of OH/2 Pi/ in a gas stress discharge [NASA-CR-157397J pOO53 N78-30808 p00O A78-10405 ADRENAL METABOLISM ABSTRACTS Regulation of the adrenal cortex function during Abstracts for the Planetary Geology Field stress Conference on Aeolian Processes [NASA-CR-157397] pOO53 R7e-30808 [HASA-TN-78455] p0022 N78-13492
65 ADSORPTION SUBJECT INDEX
ADSORPTION Closed-form equations for the lift, drag, and NT CHEMISORPTION pitching-moment coefficients of airfoil sections The co-adsorption of copper and oxygen on a in subsonic flow tungsten 100 plane-type surface [NASA-TM-78492] pO0O8 N78-29068 37 p00 A78-29489 AERODYNAMIC FORCES AEOLOTROPISM NT AERODYNAMIC DRAG Abstracts for the Planetary Geology Field NT AERODYNAMIC LOADS Conference on Aeolian Processes NT -LIFT- r-INASA-TH-78459]- p0022 N78-13492 NT SUPERSONIC DRAG AERIAL IMAGERY NT WING LOADING U AERIAL PHOTOGRAPHY Influence of spin rate on side force of an AERIAL PHOTOGRAPHY axisymmetric body 0 0 3 8 High altitude perspective --- cost-reimbursable p A78-30690 services using NASA U-2 aircraft AERODYNAMIC LIFT (NASA-SP-4271] p0O27 N78-31508 U LIFT AEROACOUSTICS AERODYEAMIC LOADS Use of coherence and phase data between two Dynamic stall experiments on the NACA 0012 airfoil receivers in evaluation of noise environments [NASA-TP-1100] pOO6 2 N78-17000 pOO16 A78-26495 Status and future prospects of using numerical AERODYNAMIC AXIS methods to study complex flows at Nigh Reynolds U AERODYNAMIC BALANCE numbers AERODYNAMIC BALANCE pO26 N78-28410 New rotation-balance apparatus for measuring An investigation of wing buffeting response at airplane spin aerodynamics in the wind tunnel subsonic and transonic speeds: Phase 1: F-111A [AIAA 78-835] p0017 A78-32386 flight data analysis. Volume 1: Summary of Hot-wire, laser anemometer'and force balance technical approach, results and conclusions measurements of cross-sectional planes of single [fASA-CR-152109] pOO13 N78-33113 and interacting trailing vortices AERODYNAMIC NOISE EAIAA PAPER 78-1194] pOOl8 A78-41885 Analysis of flight effects on noise radiation from AERODYNAMIC BRAKES jet flow using a convecting quadrupole model NT WING FLAPS [AIAA PAPER 78-192] pOOl5 A78-22594 AERODYNAMIC CENTER Application of second-order turbulent modeling to U AERODYNAMIC BALANCE the prediction of radiated aerodynamic sound AERODYNAMIC CHARACTERISTICS [NASA-CR-2994) p0012 178-25359 NT AERODYNAMIC BALANCE The effect of tip vortex structure on helicopter HT AERODYNAMIC DRAG noise due to blade/vortex interaction N' AERODYNAMIC STABILITY (NASA-CR-152150] pOO1 2 178-25832 NT LINT AERODYNAMIC STABILITY NT SUPFRSONIC DRAG Aeromechanical stability of helicopters with a Transonic wing analysis using advanced bearingless main rotor. Part 1: Eouations of computational methods motion rAIAA PAPER 78-105] pOOl5 A78-20686 [NASA-TM-78459] p0 0 6 2 N78-18043 A historical overview of stall/spin AERODYNAMIC STALLING characteristics of general aviation aircraft A historical overview of stall/spin [AIAA PAPER 78-1551] pOO19 A78-46514 characteristics of general aviation aircraft Quiet, Short-Haul Research Aircraft - Current [AIAA PAPER 78-1551] p0019 A78-46514 status and future plans A method for localizing wing flow separation at [AIAA PAPER 78-1468] p0020 A78-47916 stall to alleviate spin entry tendencies Low speed aerodynamic characteristics of an [AIAA PAPER 78-1476] p0020 A78-49787 ,O.075-scale F-15 airplane model at high angles Dynamic stall experiments on the NACA 0012 airfoil of attack and sideslip [NASA-TP-1100] pOD6 2 N78-17000 rNASA-TM-X-62360] pOR0 N78-10019 Dynamic stall of an oscillating airfoil Numerical aerodynamic simulation facility. pOO 2 5 N78-22055 Preliminary study extension. Executive summary Prediction of unsteady separated flows on [NASA-CR-152106] p0028 1178-19050 oscillating airfoils The role of time-history effects in the pO0 6 3 178-28409 formulation of the aerodynamics of aircraft AERODYNAMICS dynamics- 0 0 2 3 NT AEROTHBRMODYNAMICS rNASA-TM-78471] p N78-19056 NT ROTOR AERODYNAMICS Effect of high lift flap systems on the conceptual A uniqueness proof for a transonic flow problem design of a 1985 short-haul commercial STOL tilt pOOl6 A78-26599 rotor transport Numerical solution of a class of integral rNASA-TM-78474] pOODS N78-21094 equations arising in two-dimensional aerodynamics Low-speed aerodynamic characteristics of a pOOl8 A78-40949 0.08-scale YF-17 airplane model at high angles An evaluation of several compressible turbulent of attack and sideslip boundary-layer models Effects of pressure (NASA-TM-7843R] pOOR6 N78-22025 gradient and Reynolds number Prop-fan data support study [AIAA PAPER 78-1160] p0 0 4 3 A78-41859 [NASA-CR-1521411 pOO13 N78-27128 Numerical aerodynamic simulation facility. Wing analysis using a transonic potential flow Preliminary study extension 0 0 2 8 computational method 7 (NASA-CR-152107] p N78-19051 rHASA-TM-78464] pOOO N78-28053 Preliminary study for a numerical aerodynamic mind tunnel investigation of computationally simulation facility. Phase 1: Extension optimized variable camber wing configurations [NASA-CR-152108 pO 2 8 N78-19052 rNASA-TM-78479] pOO26 N78-29067 Future Computer Requirements for Computational AERODYNAMIC CHORDS Aerodynamics q AIRFOIL PROFILES (NASA-CP-2032] pOD2 3 178-19778 AERODYNAMIC CONFIGURATIONS Computational aerodynamics and the numerical A new method for designing shock-free transonic aerodynamic simulation facility configurations p00 2 3 N78-19779 0 0 4 5 (AIAA PAPER 78-1114] p A7R-45127 Three-dimensional computational aerodynamics in Studies of aerodynamic technology for VSTOL the 1980's fighter/attack aircraft p09 2 3 178-19781 FAIAA PAPER 78-1511] pOO20 A78-47946 Numerical Aerodynamics Simulation Facility AERODYNAMIC DRAG preliminary study, executive summary --- three NT SUPERSONIC DRAG dimensional flow Theoretical and experimental study of the drag of pOO 2 3 N78-19782 multielement airfoils Preliminary study for a Numerical Aerodynamic FATAA PAPER 78-1223) pOO19 A78-45148 Simulation Facility --- three dimensional flow
66 SUBJECT INDEX AIRCRAFT CONTROL
2 p00 3 U78-19783 AIR POLLUTION Future requirements and roles of computers in Stratospheric measurements of CF2Cl2 and N20 aerodynamlac pOO5 4 A78-37055 p000Q F78-19786 Interhemispheric gradients of CF2C12, CFCl3, CCl4, A Mach line panel method for computing the and 120 linearized supersonic flow over planar wings p0042 A78-41124 [NASA-CR-152126] p0012 E78-27087 Transport of contaminants in the planetary AEROMASTICITI boundary layer Aeromechanical stability of helicopters with a pO008 A78-52137 bearingless main rotor. Part 1: Equations of Generation of a monodisperued aerosol motion [NASA-CR-152133] p0011 H78-21445 [rNASA-TM-784591 p0062 F78-18043 AIR TRAFFIC CONTROL AEEoMAGNETISH Integrated avionics for future general aviation U GEOMAGNETISM aircraft AERONAUTICAL ENGINEERING [AIAA PAPER 78-1482] p0020 A78-47927 Rotorcraft linear simulation model. Volume 1: NASA aviation safety reporting system Engineering documentation [NASA-TN-784761 p051 78-25071 rNASA-CR-152079-VOL-1] pO010 V78-20136 AIR TRANSPORTATION A method for the analysis of the benefits and An investigation of short haul air transportation costs for aeronautical research and technology in the southeastern United States p0007 P78-29060 [NASA-CR-152166] pOD12 78-27094 AERONOMY Executive summary: Benefit-cost evaluation of an A tote on the diurnal averaging of aeronomical intra-regional air service in the may Area and a models technology assessment of transportation system p0039 A78-34352 investments --- regional planning for the San AEROPHYSICS Francisco Bay area of California U ATMOSPHERIC PHYSICS [NASA-CR-15215-1] pOOl3 N78-28988 AEROSOLS AIRBORNE EQUIPMENT Generation of a monodispersed aerosol HT AIRBORNE/SPACEBORNE COMPUTERS rIASA-CR-152133] pO011 N78-21445 Airborne infrared interferometr.c observations and AEROSPACE ENGINEERING analysis of stratospheric trace constituents NT AEROAUTICAL ENGINEERING [AIAA PAPER 78-252] p0034 A78-22606 AEROSPACE ENVIRONMENTS Airborne photometric observations between 1.25 and NT INTERPLANETARY SPACE 3.25 microns of late-type stars Gravity as a biochemical determinant p0036 A78-25295 po056 A78-48671 AIRBORNE/SPACEBORNE COMPUTERS Inhibition of bone formation during space flight Development and flight tests of a Kalman filter p0056 A78-51225 for navigation during terminal area and landing Space ecosynthesis: An approach to the design of operations closed ecosystems for use in space [NASA-CR-3015] pOO12 V78-27105 [NASA-T-78491] p0051 $78-26740 AIRCRAFT BRAKES AEROSPACE MEDICINE NT WING FLAPS Continuous metabolic and cardiovascular AIRCRAFT CABINS measurements on a monkey subject during a U AIRCRAFT COMPARTMENTS simulated 6-day Spacelab mission AIRCRAFT COMMUNICATION p0056 A78-48719 NASA aviation safety reporting system AEROSPACE TECROLOGY TRANSFER [NASI-TM-78476] pOOg E178-25071 Who should conduct aeronautical R and D for the AIRCRAFT COMPARTMENTS Federal Government? Aircraft cargo compartment fire test simulation UNASA-CR-152021] pOOOI 78-10946 program AEROSTATS (NXSA-CR-151951] p0 029 178-21223 U AIRSHIPS Low density bismaleimide-carbon microballoon AEROTHERMODYNAMICS composites --- aircraft and submarine Aerothermodynamic environment for Jovian entry compartment safety with silica heat shield [NASA-CASE-ARC-11040-2] p0050 N78-27184 [AIAA PAPER 78-186] p0033 A78-20730 AIRCRAFT CONFIGURATIONS AGING (BIOLOGY) An improved higher order panel method for Spectrophotofluorometric and electron microscopic linearized supersonic flow study of tipofuscin accumulation in the testis [AIAA PAPER 18-15] p0021 A78-52628 of aging mice Status and future prospects of using numerical p0056 A78-48581 methods to study complex flows at High Reynoldo AILERONS numbers Effect of a nonconstant C/a-alpha/ on the p0026 H78-28410 stability of rolling aircraft AIRCRAFT CONSTRUCTION MATERIALS p0031 m78-16180 ALC/5O/ values for some polymeric materials --- AIR CARGO Apparent Lethal Concentration fire toxicity Assessing the future of air freight p004 0 A78-36596 [NASA-CR-152161] p0O09 F78-14016 The relative fire resistance of select AIR COOLING thermoplastic materials --- for aircraft interiors Stress analysis study in cooled radial inflow p0046 A78-45475 turbine Assessment of relative flammability and fAIAA PAPER 78-94] p0064 A78-22570 thermochemical properties of some thermoplastic AIR FlOW materials Visualization of quasi-periodic unsteady flows 6 p0047 A78-49693 fAIAA 78-502] - pOOl A78-29804 AIRCRAFT CONTROL AIR FREIGHT Robustness in linear quadratic feedback design U AIR CARGO with application to an aircraft control problem AIR INTAKES p0014 A78-18059 NT ENGINE INlETS Robustness of linear quadratic state feedback AIR LAUNCHIVG designs in the presence of system nncertninty High performance dash-on-warning air mobile --- application to Augmentor Wing Jet STOL missile system --- first strike avoidance for Research Aircraft flare control autopilot design retaliatory aircraft-borne counterattack ICBM 9 p0016 A78-23917 rAIAA 78-1353] pOOl A78-46545 New rotation-balance apparatus for measuring AIR HTIGATION airplane spin aerodynamics in the wind tunnel Development and flight tests of a Kalman filter fAIAl 78-8353 p0017 A78-32386 for navigation during terminal area and landing Optimum horizontal guidance techniques for aircraft operations p0006 W78-23016 2 [NASA-CR-3015] pOO1 78-27105
67 AIRCRAFT DESIGN SUBJECT INDE
A flight investigation of the stability, control, Flight tests of a simple airborne device for flap predicting clear air turbulence encounters and handling qualities of an augmented jet 9 STOL airplane [AIAA 78-1375] pOO1 A78-46560 rNASA-TP-1254] p006 N78-26151 AIRCRAFT LANDING AIRCRAFT DESIGN Measured wake-vortex characteristics of aircraft NT HELICOPTER DESIGN in ground effect Trans.onic wing analysis using advanced (AIAA PAPER 78-109] pOO15 178-22578 computational methods Simulator -evaluation of three-situation and F-ATAl PAPER 78-105] p0015 A78-20686 guidance displays for V/STOL aircraft zero-zero Fuel saving potential of Mach 0.8 twin engine landing approaches prop-fan transports pOO55 A78-44131 p0017 A78-31306 Development of automatic and manual flight Effects of inlet airframe integration on the inlet director landing systems for the XY-15 tilt of an upper surface blowing four-engine STOL rotor aircraft in helicopter mode aircraft [NASA-C-152140] pOO11 H78-22071 [AIAA PAPER 78-959] pOO18 A78-43521 Simulation and analysis of wind shear hazard -- study of the drag of for aircraft landing and takeoff Theoretical and experimental 0 0 5 3 multielement airfoils (NASA-CR-157470] p 1178-29699 [1AA PAPER 78-1223] pOO19 A78-451468 AIRCRAFT MANEUVERS High performance dash-on-warning air mobile A preference-ordered discrete-gaming approach to missile system --- first strike avoidance for air-combat analysis 0 0 20 retaliatory aircraft-borne ICBM counterattack p A78-49255 [AIAA 78-1353] pOO19 A78-46545 AIRCRAFT MODELS Quiet, Short-Haul Research Aircraft - Current Low speed aerodynamic characteristics of an status and future plans 0.075-scale F-15 airplane model at high angles 0 0 20 [IAA PAPER 78-1468] p A78-47916 of attack and sideslip Application of advanced high speed turboprop [NASA-TM-I-62360] p0004 N78-10019 technology to future civil short-haul transport Certification study of a derivative model of a aircraft design small jet transport airplane using a piloted 4 [AIAA PAPER 78-1487] pOO0 A78-47930 research simulator Studies of aerodynamic technology for VSTOL [AD-A046442] pOO61 78-14033 fighter/attack aircraft Rotorcraft linear simulation model. Volume 1: [AIAA PAPER 78-1511) p0020 A78-47946 Engineering documentation A method for localizing wing flow separation at (NASA-CR-152079-VOL-1] p0OlO N78-20136 stall to alleviate spin entry tendencies Rotorcraft linear simulation model. Volume 2: rAIAA PAPER 78-1476] p0020 A78-49787 Computer implementation 0 An improved higher order panel method for [NASA-CR-152079-VOL-2] pOOl F78-20137 linearized supersonic flow AIRCRAFT NOISE rAIAA PAPER 78-15] pOO21 A78-52628 NT JET AIRCRAFT NOISE Application of advanced technologies to small, A simplified Mach number scaling law for short-haul aircraft helicopter rotor noise 7 rNASA-CR-152089] p0011 178-22074 pOO1 178-35371 A study of commuter airplane design optimization Comparison of measured and calculated helicopter [NASA-CR-157210] p011 N78-25078 rotor impulsive noise --- wind tunnel test data Computational wing optimization and comparisons and prediction analysis technigues 0 0 5 with experiment for a semi-span wing model [VASA-TH-78473] pO B78-20917 (NASA-TM-78480) p0025 N78-26106 optimal guidance and control for investigating performance aircraft noise-impact reduction Study to determine operational and 0 6 criteria for STOL aircraft operating in low [NASA-TP-1237] pO0 178-23100 visibility conditions Hovering impulsive noise: Some measured and 3 (NASA-CR-152164] pOO1 1178-28083 calculated results 0 0 6 3 Phenomenological aspects of quasi-stationary p 178-32831 controlled and uncontrolled three-dimensional A study of the noise radiation from four flow separations --- in relation to aircraft helicopter rotor blades --- tests in Ames 40 by design considerations and swept wings 20 foot wind tunnel pOO07 N78-28402 pOODS N78-32835 Some unsteady separation problems for slender bodies AIRCRAFT PERFORMANCE p0 0 6 3 N78-28405 NT HELICOPTER PERFORMANCE An assessment of the effect of supersonic aircraft Simulation replay - Implementation and flight operations on the stratospheric ozone content simulation applications 0 0 2 7 [NASA-RP-1026] p N78-30774 pOO18 178-38789 AIRCRAFT ERGINES The role of time-history effects in the Effects of inlet airframe integration on the inlet formulation of the aerodynamics of aircraft of an upper surface blowing four-engine STOL dynamics 0 0 2 3 aircraft [NASA-T-78471] p 178-19056 [AIAA PAPER 78-959] pO018 A78-43521 Application of a cost/performance measurement Estimating maximum instantaneous distortion from system on a research aircraft project 0 0 0 7 inlet total pressure rms measurements [ASA-TH-78498] p 178-27043 rAIAA PAPER 78-970] pOO19 A78-43525 AIRCRAFT PILOTS Fuel conservation merits of advanced turboprop NT TEST PILOTS transport aircraft AIRCRAFT POWER SOURCES rNASA-CR-152096) pOO10 N78-21095 U AIRCRAFT ENGINES AIRCRAFT EQUIPMENT AIRCRAFT RELIABILITY Study to determine operational and performance Integrated avionics for future general aviation criteria for STOL aircraft operating in low aircraft 0 2 0 visibility conditions (AIAA PAPER 78-1482] p0 A78-47927 [NASA-CR-1521641 pO013 N78-28083 Certification study of a derivative model of a 'AIRCRAFT FUELS small jet transport airplane using a piloted Fuel conservation merits of advanced turboprop research simulator 0 0 6 1 transport aircraft (1D-A046442] p 178-14033 rNASA-CR-152096] pOO10 N78-21095 AIRCRAFT SAFETY AIRCRAFT HAZARDS Fire resistivity and toxicity studies of candidate Fire resistivity and toxicity studies of candidate aircraft passenger seat materials aircraft passenger seat materials pO048 A78-51838 2 4 (NASA-Tf-78468] p00 N78-21214 Fire detector response in aircraft applications 4 AIRCRAFT INSTRUMENTS p00 9 A78-53674 NT AUTOMATIC PILOTS NASA aviation safety reporting system 2 NT HOT-WIRE ANEMOMETERS (NASA-TM-78511] pOO5 178-32075
68 SUBJECT INDEX ANALYSIS (MATHEMATICS)
AIRCRAFT STABILITY system on a research aircraft project NT HOVERING STABILITY [NASA-TM-78498] pOO07 178-27043 Effect of a nonconstant C/m-alpha/ on the AIRPORT PLANNING stability of rolling aircraft Planning for airport access: An analysis of the 0 0 3 1 p A78-16180 San Francisco Bay area A historical overview of stall/spin [NASA-CP-2044] pOO1 N78-26152 characteristics of general aviation aircraft AIRSHIPS rAIAA PAPER 78-1551) p0019 A78-46514 Comments on 'Feasibility study of a hybrid airship A flight investigation of the stability, control, operating in ground effect' and handling gualities of an augmented jet flap pOO16 A7-24367 STOL airplane AIRWORTHINESS 6 rNASA-TP-12541 pOO0 R78-26151 U AIRCRAFT RELIABILITY AIRCRAFT STRUCTURES AIRWORTHINESS REQUIREMENTS NT AIRFRAMES U AIRCRAFT RELIABILITY AIRCRAFT WAKES ALARMS Measured wake-vortex characteristics of aircraft U WARRING SYSTEMS in ground effect ALBEDO (AIAA PAPER 78-1093 pOO15 A78-22578 Multicolor observations of Phobos with the Viking AIRFOIL CHARACTERISTICS lander cameras - Evidence for a carbonaceous U AIRFOILS chondritic compositiow AIRFOIL PROFILES p0032 A78-18875 NT WING SPAN Carbon suboxide polymer, an explanation for the A new method for designing shock-free transonic wave of darkening on Mars configurations p00 5 6 A78-48717 rAIAA PAPER 78-1114] p0045 A78-45127 ALGEBRA Theoretical and experimental study of the drag of NT LINEAR TRANSFORMATIONS multielement airfoils NT MATRICES (MATHEMATICS) [ATAA PAPER 78-1223] p0019 A78-45148 NT NONLINEAR EQUATIONS The numerical solution of viscous flows at high NT VORTICITY Reynolds number ALGORITHMS p0846 A78-46360 An implicit algorithm for the conservative AIRFOIL SECTIONS transonic full potential equation using an U AIRFOIL PROFILES arbitrary mesh AIRFOIL THICKNESS (AIAA PAPER 78-1113] p0043 A78-41826 U AIRFOIL PROFILES ALIPHATIC COMPOUNDS AIRFOILS NT CYCLIC HYDROCARBONS NT AILERONS NT CYSTEINE NT CAMBERED WINGS NT ETHANE NT DELTA WINGS NT HEXADIENE NT RIGID ROTORS NT HEXAMETHYLENETRAMIRE NT ROTARY WINGS ALKANES NT SLENDER WINGS NT ETHANE NT SUPERCRITICAL WINGS ALLOYS NT SWEPT WINGS NT RUSTENITIC STAINLESS STEELS NT THIN WINGS NT CARBON STEELS NT TILTING ROTORS ALPHA PARTICLES NT UNSWEPT WINGS Rigidity-independent coronal propagation and NT WING FLAPS escape of solar protons and alpha particles NT WINGS pOO4 1 A78-37354 Calculation of unsteady transonic flows using the ALPHA-RADIATION integral equation method U ALPHA PARTICLES 3 3 (AIAA PAPER 78-13] pO A78-20632 ALTERATION The shock tube as a device'for testing transonic U REVISIONS airfoils at high Reynolds numbers ALTITUDE 7 (AIAA 78-769] pOO1 A78-32330 NT HIGH ALTITUDE Notes on the transonic indicial method --- for two ALTITUDE CONTROL dimensional airfoil flutter derivative calculation NASA aviation safety reporting system p0041 A78-37732 (NASA-TM-785111 pOOS 2 N78-32075 Flying-hot-wire study of two-dimensional mean flow ALTITUDE SIMULATION past an NACA 4412 airfoil at maximum lift Fluid-electrolyte shifts and maximal oxygen uptake [AIAA PAPER 78-11961 pOO18 A78-41887 in man at simulated altitude /2,287 m/ Dynamic stall experiments on the NACA 0012 airfoil pOOS 4 A78-36602 [NASA-TP-1100] p0062 V78-17000 ALUMINA Water-tunnel experiments on an oscillating airfoil U ALUMINUM OXIDES at RE equals 21,000 ALUMINUM COMPOUNDS tNASA-TM-7846] p0062 P78-19058 NT ALUMINUM OXIDES Dynamic stall of an oscillating airfoil ALUMINUM OXIDES p0025 N78-22055 Controlled vapor growth of small particles of Pd A study of test section configuration for shock and Fe on thin A1203 substrates tube testing of transonic airfoils 2 pOO44 A78-43384 (NASA-CR-157237] pOO1 N78-26153 AMBIT Prediction of unsteady separated flows on U FIELD THEORY (PHYSICS) oscillating airfoils AM1NES p0063 N78-28409 NT HEXAMETHYLENETETRAMINE Closed-form equations for the lifc, drag, and AMINO ACIDS pitching-moment coefficients of airfoil sections NT CYSTEINE in subsonic flow 'ITMETHIONINE rNASA-TM-78492] pOO08 N78-29068 ANALYSIS (MATHEMATICS) AIRFRAMES , NT DIFFERENTIAL EQUATIONS Effects of inlet airframe integration on the inlet NT FINITE DIFFERENCE THEORY of an upper surface blowing four-engine STOL NT INTEGRAL EQUATIONS aircraft NT NONLINEAR EQUATIONS [AIAA PAPER 78-959] pOO18 A78-43521 NT NUMERICAL ANALYSIS AIEGLOW NT NUMERICAL INTEGRATION The ionosphere and airglow of Venus - Prospects NT PARABOLIC DIFFERENTIAL EQUATIONS for Pioneer Venus NT PERIODIC PUNCTIONS p0045 A78-44773 NT VORTICITY AIRPLANE PRODUCTION COSTS PT WEIGHTING FUNCTIONS Application of a cost/performance measurement
69 ANATOMY SUBJECT INDEX
ANATOMY guidance displays for V/STOL aircraft zero-zero NT ADRENAL GLAND landing approaches HT CARDIAC VENTRICLES p055 A78-44131 NT CARDIOVASCULAR SYSTEM Optimal control theory (OWEM) applied to a NT CARTILAGE helicopter in the hover and approach phase NT HUMAN BODY (NASA-CR-152135) pOOlO N78-21161 NT JOINTS (ANATOMY) Project plan for joint FAA/NASA head-np display NT LABYRINTH concept evaluation NY YOCARDIM (NASA-TM-78512] pOO52 N78-28979 NT TESTES APPROXIMATIOR NT TORSO NT FINITE DIFFERENCE THEORY XT TRACHEA ARCHITECTURE (COMPUTERS) ANDROMEDA GALAXIES A view, toward future fluid dynamics computing ISAs and the dwarf content of the inner nuclear [AIAA PAPER 78-1112] pO045 A78-45126 regions of M31 --- Intrinsic Strength Anomalies2 Preliminary study for a numerical aerodynamic p004 A78-38569 simulation facility. Phase i Extension ANEMOMETERS [NASA-CR-1521081 p0028 78-19052 NT HOT-WIRE ANEMOMETERS A single user efficiency measure for evaluation of ANEMOMETEY parallel or pipeline computer architectures 0 U 'VELOCITY MEASUREMENT p 059 NB78-19808 ANGLE OF ATTACK ARIP (IMPACT PREDICTION) wake vortex measurements of bodies at high angle U COMPUTERIZED SIMULATION of attack AROMATIC COMPOUNDS rAIAA PAPER 78-23] pOO15 A78-22555 Synthesis of multifunction triaryltrifluoroethanes Computation of transonic flow past projectiles at tNASA-CASE-ARC-11097-11 p0049 H78-22154 angle of attack Synthesis of multifunction triaryltrifluoroethanes rAIAA PAPER 78-1182] p0044 A78-41875 [NASA-CASE-ARC-11097-2) p0049 W78-22155 Computation of supersonic laminar viscous flow Polymeric foams from cross-linkable past a pointed cone at angle of attack in poly-n-arylenebenzimidazoles spinning and coning motion (NASA-CASE-ARC-11008-1) p0050 N78-31232 4 rAIAA PAPER 78-1211] pOO 5 A78-45139 ARTIFICIAL SATELLITES Low speed aerodynamic characteristics of an HT COMMUNICATION SATELLITES 0.075-scale F-15 airplane model at high angles ARYL COMPOUNDS of attack and sideslip U AROMATIC COMPOUNDS 4 [NASA-TM-X-62360] pOO0 N78-10019 ASSESS PROGRAM Low-speed aerodynamic characteristics of a NASA/ESA CV-990 Spacelab simulation (ASSESS 2) O.8-scale YF-17 airplane model at high angles [NRASA-CR-152122] p0029 H78-23117 of attack and sideslip NASA/ESA CV-990 spacelab simulation (ASSESS 2) [NASA-TM-78438] p0O06 N78-22025 [NASA-TM-79748] p0O27 N78-30149 High angle canard missile test in the Ames 11-foot ASSESSMERTS transonic wind tunnel NT TECHNOLOGY ASSESSMENT (NASA-CR-29q3] pO11 H78-25057 ASTROBIOLOGY High angle of incidence implications upon air U EXOBIOLOGY intake design and location for supersonic cruise ASTROSETRY aircraft and highly maneuverable transonic The radii of Uranian rings alpha, beta, gamma, aircraft delta, epsilon, eta, 4, 5, and 6 from their [NASA-TM-78530] pOOD8 N78-32044 occultations of SAO 158687 Angle detector p0046 A78-48112 rNASA-CASE-ARC-11036-1] pOO60 N78-32395 ASTRONAUT LOCOMOTION ANGLES (GEOMETRY) Spacesuit mobility knee joints NT ANGLE OF ATTACK [NASA-CASE-ARC-11058-2] pO07 N78-18763 ANIMALS ASTRONAUT PERFORMANCE NT ICE Spacesuit mobility joints VT RATS [NASA-CASE-AC-11058-1] pOO58 N78-31735 Tread drum for animals --- having an electrical ASTRONOMICAL MODELS shock station NT DENSITY WAVE MODEL 5 7 rNASA-CASE-ARC-10917-1] pO 178-27733 Saturn's rings: Particle composition and size CV 990 interface test and procedure analysis of distribution as constrained by microwave the monkey restraint, support equipment, and observations. I - Radar observations telemetry electronics proposed for Spacelab pOO36 A78-25676 rNASA-TM-78484] p0051 N78-27736 Ear-driven spiral waves in disk galaxies RRNUAL VARIATIONS pOO38 A78-32467 Stratospheric NO and HN03 observations in the Numerical experiments on the stability of disklike Northern Hemisphere for three seasons galaxies p0042 A78-41123 pOOl9 78-45535 ANTENNAS On the stability of disklike galaxies in massive Low profile antenna performance study. Part 2: halos Broadband antenna techniques survey pO02O A78-47354 rAD-A0479921 p0022 W78-18274 ASTRONOMICAL OBSERVATORIES AWTIFERROMAGNETISM A short history of Pulkovo Observatory Square Ising ferromagnetic and antiferromagnetic pOO4 6 A78-47273 lattices in a magnetic field - A new ASTRONOMICAL PHOTOGRAPHY perturbation approach The Pioneer 11 imaging experiment of Jupiter p0056 A78-51886 p0032 A78-18173 ANTIMONIDES ASTRONOMICAL PHOTOMETRY NT INDIUM ANTIMONIDES NT STELLAR SPECTROPHOTOMETRY ANTIMONY COMPOUNDS Occultation of Epsilon Geminorum by Mars. II - The NT INDIUM ANTIMONIDES structure and extinction of the Martian upper APOLLO FLIGHTS atmosphere NT APOLLO 12 FLIGHT pO030 A78-10587 APOLLO SPACECRAFT The Pioneer 11 imaging experiment of Jupiter Crustal evolution inferred from Apollo magnetic pO32 A78-18173 measurements Analysis of stellar occultation data - Effects of r NASA-l'-78524 1 p0027 W78-32029 photon noise and initial conditions -- APOLLO 12 FLIGHT planetary atmosphere temperature, pressure and Light element geochemistry of the Apollo'125 4 site density profiles from occultation light curve p00 A78-34503 pOO35 A78-23164 APPROACH CONTROL Zodiacal light as an indicator of interplanetary Simulator evaluation of three situation and dust
70 SUBJECT INDEX AIISYNRETRIC BODIES
p0042 (78-38228 ATOMIC BEAKS ISAs and the dwarf content of the inner nuclear Measuring the velocity of individual atoms in real regions of M31 --- Intrinsic Strength Anomalies time 4 2 pOO A78-38569 pOO35 A78-23124 ASTRONOMICAL TELESCOPES ATOMIC COLLISIONS Peaker: An automatic boresight peaking routine Quantum mechanical theory of a structured for the C-141 telescope atom-diatom collision system - A - HC/1-Sigma/ [NASA-TM-78516] p0028 478-32856 [AD-A051266) p0031 A78-16454 ASTRONOMY Quantum mechanical theory of collisional NT INFRARED ASTRONOMY ionization in the presence of intense laser NT RADAR ASTRONOMY radiation NT ULTRAVIOLET ASTRONOMY [AD-A052981) p0035 A78-23576 NT X RAY ASTRONOMY ATOMS ATMOSPHERIC BOUNDARY LAYER NT OXYGEN ATOMS Transport of contaminants in the planetary ATTACK AIRCRAFT boundary layer NT F-5 AIRCRAFT pO048 A78-52137 NT F-15 AIRCRAFT ATMOSPHERIC CHEMISTRY NT F-111 AIRCRAFT A comprehensive model of the Venus ionosphere NT FIGHTER AIRCRAFT 0 0 3 8 p A78-30071 Low-speed aerodynamic characteristics of a Stability of chromium (III) sulfate In atmospheres 0o08-scale YF-17 airplane model at high angles containing oxygen and sulfur of attack and sideslip 2 6 rNASA-TM-785041 p00 78-28173 [NASA-TH-78438] p0006 N78-22025 ATHOSPHERIC CIRCULATION ATTITUDE (INCLINATION) Meteorological control of lower stratospheric NT PITCH (INCLINATIO) minor species variations - An observational NT BOLL example ATTITUDE CONTROL pOO1S X78-46011 NT THRUST VECTOR CONTROL ATMOSPHERIC COMPOSITION AUSTEITIC STAINLESS STEELS NT IONOSPHERIC COMPOSITION Influence of temperature and the role of chromium Lover stratosphere measurements of variation with on the kinetics of sulfidation of 310 stainless latitude of CF2C12, CFCI3, CClI, and N20 steel profiles in the northern hemisphere p043 A78-41796 0 0 3 5 p A78-23610 AUTOCOLLIMATORS Stratospheric measurements of CF2C12 and N20 U COLLIMATORS 4 pOO A78-37055 AUTOMATIC CONTROL Stratospheric NO and HN03 observations in the NT ADAPTIVE CONTROL Northern Hemisphere for three seasons NT CASCADE CONTROL 2 pOO4 A78-41123 NT FEEDBACK CONTROL Primitive atmosphere and implications for the NT NUMERICAL CONTROL formation of channels on Mars NT OPTIMAL CONTROL - p0044 A78-42460 Development of automatic and manual flight Meteorological control of lower stratospheric director landing systems for the XV-15 tilt minor species variations - An observational rotor aircraft in helicopter mode example ENASA-CR-152140] p0011 N78-22071 p0019 A78-46011 Peaker: An automatic boresight peaking routine Are the stratospheric dust particles meteor for the C-141 telescope ablation debris or interplanetary dust? [NASA-TM-785161 p0O28 N78-32856 [NASA-TM-78507] pOO28 H78-34014 AUTOMATIC DATA PROCESSING ATMOSPHERIC EMISSION U DATA PROCESSING U AIRGLOW AUTOMATIC PILOTS ATMOSPHERIC ENTRY Robustness in linear quadratic feedback design NT HYPERSONIC REENTRY with application to an aircraft control problem NT SPACECRAFT REENTRY p0014 A78-18059 Aerothermodynamic environment-for Jovian entry Robustness of linear quadratic state feedback with silica heat shield designs in the presence of system uncertainty rAIAA PAPER 78-186] p0033 A78-20730 --- application to Augmentor Wing Jet STOL 'Jupiter probe heatsbield configuration optimization Research Aircraft flare control autopilot design 4 [AIAA PAPER 78-8431 pOO 1 A78-37270 pOO16 A78-23917 Entry dynamics performance predictions for Pioneer AUTOMATIC ROCKET IMPACT PREDICTORS Venus probes U COMPUTERIZED SINULATION LAIAA 78-1370] p04 6 A78-46557 AUTOMATION ATMOSPHERIC IMPURITIES Spray coating apparatus having a rotatable U AIR POLLUTION workpiece holder ATMOSPHERIC MODELS [NASA-CASE-ARC-11110-1] pOO50 N78-32434 NT DYNAMIC MODELS AUTOMOBILES HT REFERENCE ATMOSPHERES Effects of potassium titanate fiber on the wear of A comprehensive model of the Venus ionosphere automotive brake linings 0 0 3 8 p A78-30071 p0035 A78-23450 A note on the diurnal averaging of aeronomical AUTOPILOTS models U AUTOMATIC PILOTS pOO39 A78-34352 AUTOROTATION ATMOSPHERIC PHYSICS A simple method for estimating minimum The ionosphere and airglow of Venus - Prospects autorotative descent rate of single rotor for Pioneer Venus helicopters p0045 A78-4773 [NASA-TH-78452] pOO05 N78-20113 ATMOSPHERIC RADIATION AV-81 AIRCRAFT NT AIRGLOW U HARRIER AIRCRAFT NT WISTLENS AVIONICS ATMOSPHERIC TEMPERATURE Advanced Digital Avionics System for general NT IONOSPHERIC TEMPERATURE aviation ATMOSPHERIC TURBULENCE [AIA& 77-1494] p0Ol' A78-12243 NT CLEAR AIR TURBULENCE Integrated avionics for future general aviation Computed responses of several aircraft to aircraft atmospheric turbulence and discrete wind shears [AIAA PAPER 78-1482] p0020 A78-47927 [ENSA-CR-152185) p053 N78-32106 AXISYNETRIC BODIES ATMOSPHERICS Influence of spin rate on side force of an NT WHISTLERS axisymmetric body p0038 A78-30690
71 AXISYMMETRIC FLOW SUBJECT INDEX
AXISYMMETRIC fLOW NT BIOTELEMETRY The numerical solution of viscous flown at b1gh NT ELECTROCARDIOGRAPHY Reynolds number 0 0 4 6 BIOIXSTRUMENTATION p A78-46360 T BIOTELEMETRY NT IMPLANTED ELECTRODES (BIOLOGY) B Multichannelunit electrochemical microbial detection 6 B STARS poo1 178-31300 Infrared excesses in early-type stars - Gamma BIOLOGICAL- ACTIVITY Cassiopeiae U ACTIVITY (BIOLOGY) pOO47 A78-49475- BIOLOGICAL ANALYSIS BACKGROUND NOISE U BIOASSAY Optimizing indium antimonide (InSb) detectors for BIOLOGICAL EFFECTS low background operation --- infrared astronomy Gravity as a biochemical determinant [NAA-T-73273J p0028 V78-32947 I p0056 A78-48671 BACKGROUND RADIATION Inhibition of bone formation during space flight Radiometer system to map the cosmic background pOO56 R78-51225 radiation BIOLOGICAL EVOLUTION pOO38 A78-30691 WT ABIOGERESIS BACTERIA BIOMETRICS Multichannel electrochemical microbial detection NT ELECTROCARDIOGRAPHY CV 990 interface test and procedure analysis of unit 6 pOOl A78-31300 the monkey restraint, support equipment, and Calcium transport in Halobacterium halobium telemetry electronics proposed for Spacelab envelope vesicles [NASA-TH-78484] pOO51 N78-27736 p0U55 A78-48574 BIOREGENERATIVE LIFE SUPPORT SYSTEMS Illumination-dependent changes in the intrinsic U CLOSED ECOLOGICAL SYSTEMS fluorescence of bacteriorhodopsin BIOSENSODS 0055 A78-48578 U BIOINSTEUMENTATION BALLISTIC MISSILES BIOTELEMETRY NT INTERCONTINENTAL BALLISTIC MISSILES An inductively powered telemetry system for BANDWIDTH temperature EKG, and activity monitoring r 9 1T BROADBAND [NASA-TM-78486] p005 N78-23706 NT SPECTRAL LINE WIDTH BIPROPELLAVTS BARDEEN APPROXIMATION U LIQUID ROCKET PROPELLANTS U SURFACE PROPERTIES BLACKOUT (PROPAGATION) BATTER SEPARATORS NT ELECTROMAGNETIC NOISE U SEPARATORS NT WHISTLERS BAYS (TOPOGRAPHIC FEATURES) BLADE TIPS NT SAN FRANCISCO BAY (CA) Acoustical effects of blade tip shape changes on a BEAMS (RADIATION) full scale helicopter rotor in a wind tunnel 0 NT ATOMIC BEAMS [NASA-CR-152082] pOOl 178-20918 NT MOLECULAR BEAMS The effect of tip vortex structure on helicopter Generation of a parallel X-ray beam and its use noise due to blade/vortex interaction for testing collimators [HASA-CE-152150] pOO12 B78-25832 0 0 3 5 p A78-23083 BLOOD FLOW BEAMS (SUPPORTS) Effects of exercise and excitement on mesenteric NT CANTILEVER BEAMS and renal dynamics in conscious, Unrestrained The general solution to the classical problem of baboons the finite Euler-Bernoulli beam pOO53 A78-27124 0 0 4 7 p A78-50909 BLOOD PRESSURE BELL. AIRCRAFT Effects of exercise and excitement on mesenteric NT XV-15 AIRCRAFT and renal dynamics in conscious, unrestrained BENCHES baboons U SEATS p0053 478-27124 BERNOULLI EQUATION BLOOD VOLUME I BERNOULLI THEOREM Fluid-electrolyte shifts and maximal oxygen uptake BERNOULLI THEOREM in man at simulated altitude /2,287 m/ The general solution to the classical problem of p0054 A78-36602 the finite Euler-Bernoulli beam BLOWING 4 p00 7 A78-50909 Moving ground simulation by tangential blowing BIBLIOGRAPHIES [AIAA 78-814] p0017 A78-32368 Chemical evolution and the origin of life - BLUNT BODIES Bibliography supplement 1976 Havier-Stokes calculations for laminar and p0057 A78-53875 turbulent hypersonic flow over indented nosetips A bibliography on the search for extraterrestrial [1IAA PAPER 78-260] pOO35 178-22608 intelligence Numerical solution of two-dimensional turbulent [NASA-Ro-1021] pOO51 N78-21019 blunt body flows with an impinging shock Infrastructure dynamics: A selected bibliography rAIAA PAPER 78-1209] p0 0 4 5 A78-45144 [5ASA-CR-152162] p012 N78-2582 Effects of mass addition on blunt-body Ames Research Center Publications-1976 boundary-layer transition and heat transfer 0 0 2 2 FNASA-TH-78493] pOOH3 N78-27042 (NASA-TP-1139] p 78-16326 BINARY SYSTEMS (DIGITAL) BMC U DIGITAL SYSTEMS U BORE MINERAL CONTENT BIOASSAY BODIES OF REVOLUTION Gravity as a biochemical determinant NT CONICAL BODIES p00 5 6 A78-48671 NT ROTATING CYLINDERS BIOCHEMISTRY Influence of spin rate on side force of an Gravity as a biochemical determinant axisymmetric body p00 5 6 A78-48671 p0038 A78-30690 Computer display and manipulation of biological BODY FLUIDS molecules 5 6 NT SWEAT pOO A78-53400 Fluid-electrolyte shifts and maximal oxygen uptake Degradation of biochemical activity in soil in man at simulated altitude /2,287 m/ 0 0 54 sterilized by dry heat and gamma radiation p 178-36602 pOO57 A78-53874 BODY WEIGHT BIOENGINEERING Physiologic regulation of body energy storage NT BIOINSTRUMERTATION p0D55 178-42817 NT BIOMETRICS
72 SUBJECT INDEX CAPTIVE TESTS
BOEING MILITARY AIRCRAFT U SHOCK WAVES U MILITARY AIRCRAFT BOW WAVES BOLTS On the relative locations of the how shocks of the Torquing preload in a lubricated bolt terrestrial planets rNASA-TM-78501] n0027 N78-29451 p0031 A78-13752 BOMBS (PRESSURE GAGES) BRAKES (FOR ARRESTING NOTION) 9 PRESSURE GAGES NT WING FLAPS BORE MINERAL CONTENT Effects of potassium titanate fiber on the wear of Inhibition of bone formation during space flight automotive brake linings pO056 A78-51225 p0 0 3 5 A78-23450 BONES BREAKAWAY NT CARTILAGE U BOUNDARY LAYER SEPARATION BOOLEAN ALGEBRA BRIGHTNESS TEMPERATURE NT BOOLEAN FUNCTIONS Radiometer system to map the cosmic background BOOLEAN FUNCTIONS radiation A solution to the surface intersection problem --- pO038 A78-30691 Boolean functions in geometric modeling BROADBAND FNASA-CR-152116] pOO10 N78-19869 Low profile antenna performance study. Part 2: BOOMS (EQUIPMENT) Broadband antenna techniques survey 2 2 Magnetometer deployment mechanism for Pioneer Venus (AD-A047992] pOO N78-18274 pog23 N78-19029 BRONCHIAL TUBE BOOST NT TRACHEA U ACCELERATION (PHYSICS) BUFFER STORAGE BORON COMPOUNDS Generalization of Huffman coding to minimize the NT BORON FLUORIDES probability of buffer overflow BORON FLUORIDES (AD-AO50974] pOO06 N78-22754 Boron trifluoride coatings for thermoplastic BUFFETING materials and method of applying same in glow An investigation of wing buffeting response at discharge subsonic and transonic speeds: Phase 1: F-111A rNASA-CASE-ARC-11057-1] p0057 N78-31233 flight data analysis. Volume 1: Summary of BORON TRITLUORIDE technical approach, results and conclusions U BORON FLUORIDES [NASA-CH-152109] pOOl3 B78-33113 BOSONS An investigation of wing buffeting response at NT ALPHA PARTICLES subsonic and-transonic speeds. Phase 2: F-111A BOUNDARY LAYER CONTROL flight data analysis. Volume 2: Plotted power Injection slot location for boundary-layer control spectra in shock-induced separation [NASA-CR-152113] p0013 F78-33117 [AIAA PAPER 78-1168] p0044 A78-41866 An investigation of wing buffeting response at BOUNDARY LAYER EQUATIONS subsonic and transonic speeds. Phase 2: F-i11A Displacement thickness distributions in transonic flight data analysis. Vdlume 3: Tabulated flows about 3-D wings power spectra pOO32 A78-17612 [NASA-CR-152114] pOO14 N78-33118 An evaluation of several compressible turbulent boundary-layer models Effects of pressure C gradient and Reynolds number (ATAA PAPER 78-1160] poo43 A78-41859 CABIN ATMOSPHERES Comparison of multiequation turbulence models for NT SPACECRAFT CABIN ATMOSPHERES several shock-separated boundary-layer CABLES (ROPES) interaction flows Cable strumming suppression [AIAA PAPER 78-1165] p0043 A78-41863 [AD-A047996] pOg22 N78-18366 BOUNDARY LAYER FLOW CALCIUM NT BOUNDARY LAYER,SEPARATION Calcium transport in Ealobacterium halobium NT SEPARATED FLOW envelope vesicles Thin-layer approximation and algebraic model for pOO 5 5 A78-48574 separated turbulent flows CALCULATION [AIAA PAPER 78-257] p0033 A78-20776 U COMPUTATION BOUNDARY LAYER NOISE CALCULUS U AERODYNAMIC NOISE NT VORTICIT7 U BOUNDARY LAYERS CALIFORNIA BOUNDARY LAYER SEPARATION Executive summary: Benefit-cost evaluation of an Comparison of multiequation turbulence models for intra-regional air service in the Bay Area and a several shock-separated boundary-layer technology assessment of transportation system interaction flows investments --- regional planning for the San (AIAA PAPER 78-1165) p0043 A78-41863 Francisco Bay area of California Injection slot location for boundary-layer control [NASA-CH-152154-l] pOO13 178-28988 in shock-induced separation CAMBER rAIAA PAPER 78-1168] p0044 A78-41866 ST WING CAMBER Dynamic stall of an oscillating airfoil CAMBERED WINGS p0025 N78-22055 Wind tunnel investigation of computationally BOUNDARY LAYER TRANSITION optimized variable camber wing configurations Effects of mass addition on blunt-body [NASA-TM-78479] pOO2 6 N78-29067 boundary-layer transition and heat transfer CANARD CONFIGURATIONS [fASA-TP-1139) p0022 N78-16326 Three-dimensional canard-wing shape optimization BOUNDARY LAYERS in aircraft cruise and maneuver environments BT ATMOSPHERIC BOUNDARY LAYEB (AIAA PAPER 78-99] pOOl6 A78-26274 NT COMPRESSIBLE BOUNDARY LAYER High.angle canard missile test in the Ames 11-foot NT LAMINAR BOUNDARY LAYER transonic wind tunnel UT SUPERSONIC BOUNDARY LAYERS [NASA-CR-2993] pOOl1 H78-25057 ST TURBULENT BOUNDARY LAYER CANTILEVER BEAMS NT TWO DIMENSIONAL BOUNDARY LAYER An approximate solution for the free vibrations of On the period of the coherent structure in rotating uniform cantilever beams boundary layers at large Reynolds numbers [NASA-TM-X-62299] pOO6 3 N78-33289 [NASA-TH-784771 p0024 N78-21407 CANTILEVER MEMBERS BOUNDARY VALUE PROBLEMS NT CANTILEVER BEAMS Numerical solution of a class of integral CANTILEVER WINGS equations arising in two-dimensional aerodynamics U WINGS pOOl8 A78-40949 CAPTIVE TESTS BOW SHOCK WAVES NT STATIC TESTS U BOW WAVES
73 CANDOR SUBJECT INDEX
CARBON Multicolor observations of Phobos with the Viking Carbon vaporization into a nonequilibrium, lander cameras - Evidence for a carbonaceous stagnation-point boundary layer 4 chondritic composition 0 0 2 pOO P A78-40838 p 3 A78-18875 Low density bismaleimide-carbon microballoon CARDIAC'VENTRICLES composites --- aircraft and submarine Extent of utilization of the Frank-Starling compartment safety mechanism in conscious dogs --- preload effects rNASA-CASE-ARC-11040-2) pOO5O N78-27184 on myocardial regulation CARBON COMPOUNDS pOO54 A78-33522 NT CHLOROCARBONS CARDIOGRAPHY HT HALOCARBONS NT ELECTROCARDIOGRAPHY A theoretical study of the electronic transition CARDIOVASCULAR SYSTEM moment for the C2 Swan band system NT CARDIAC VENTRICLES p0041 A78-36776 NT MYOCARDIUM CARBON DIOXIDE Continuous metabolic and cardiovascular Intensities, self-broadening, and broadening by Ar measurements on a monkey subject during a and N2 for the 301/111/ - 000 band of C02 simulated 6-day Spacelab mission measured at different temperatures pOO56 A78-48719 pOO4 S 178-48425 CARGO Absolute intensity measurements at different NT AIR CARGO temperatures of the C-12/0-16/2 bands 30 0 1 A study of characteristics of intercity 1--00 0 0 and 30 0 1 IV--0 0 0 4 7 transportation systems. Phase 1: Definition of p00 A78-50488 transportation comparison methodology Measurement at different temperatures of absolute [NASA-CR-152153-2] pOODI N78-29996 intensities, line half-widths, and broadening by CARGO AIRCRAFT Ar and 42 for the 30 0 1 11--OO 0 0 band of C02 Aircraft cargo compartment fire test simulation 7 pOO A78-50489 program Comments on the note by Arie et al. on the (NASA-CR-151951] p0029 N78-21223 transition moment of the C02 band near 7740 CARTILAGE kaysers Responses of articular and epiphyseal cartilage pOo8 A78-52388 zones of developing avian radii to estrone Advanced solid electrolyte cell for C02 and H20 treatment and a 2-G environment electrolysis --- for extended duration manned pOO54 A78-29562 spaceflights CASCADE CONTROL rNASA-CR-152093] pOO52 S78-21235 Application of special-purpose digital computers An investigation of the reduction of carbon to rotorcraft real-time simulation dioxide in a silent electric discharge [NASA-TP-1267] p807 N78-27113 rNASA-CR-152146] pOO53 N78-25767 CASCADES (FLUID DYNAMICS) CARBON DIOXIDE CONCENTRATION U FLUID DYNAMICS Technology advancement of the electrochemical C02 CATALYSTS concentrating process Catalysts for imide formation from aromatic 2 rNASA-CR-1520981 pOO5 N78-22723 isocyanates and aromatic dianhydrides CARBON DIOXIDE LASERS [NASA-CASE-ARC-11107-1] pOO4 9 N78-22156 Collisionless dissociation of SF6 using two CELESTIAL BODIES resonant frequency C02 laser fields NT ANDROMEDA GALAXIES pOO3 1A78-14655 NT B STARS C02 laser-driven Stirling engine --- space power NT CARBON STARS applications NT CARBONACEOUS CHONDRITES p0021 A78-49804 NT DWARF STARS CARBON FIBER REINFORCED PLASTICS NT EARLY STARS The response of heat-shield materials to intense NT EARTH (PLANET) laser radiation NT EUROPA 4 [AIAA PAPER 78-138] pOO3 A78-22583 NT GLOBULAR.CLUSTERS CARBON MONOXIDE NT 10 Low energy ionizing collisions between N2 and CO NT IRON METEORITES beam molecules and CO, N2, NO, CR4, and C02 NT JUPITER (PLANET) target molecules NT LATE STARS 3 9 pOO A78-34137 NT MARS (PLANET) Chemisorption of CO on Pd particles supported on NT MERCURY (PLANET) mica 4 NT METEORITES pOO O A78-36040 NT MICROMETEOROIDS CARBON STARS NT NOVAE C3 and infrared spectrophotometry of Y Canum NT PROBOS Venaticorum NT SATURN RINGS p0042 A78-39448 NT SOLAR SYSTEM CARBON STEELS NT TERRESTRIAL PLANETS Hydrogen attack - Influence of hydrogen sulfide NT TUNGUSK METEORITE --- on carbon steel NT URANUS (PLANET) p0044 A78-44108 CELLS (BIOLOGY) CARBON SUBOXIDES NT NEURONS Carbon suboxide polymer, an explanation for the CERAMAL PROTECTIVE COATINGS wave of darkening on Mars U PROTECTIVE COATINGS p0056 A78-48717 CERAMIC COATINGS CARBON-CARBON COMPOSITES Spray coating apparatus having a rotatable The response of heat-shield materials to intense workpiece holder laser radiation [RASA-CASE-ARC-11110-1) pOO5O N78-32434 0 0 34 rAIAA PAPER 78-138] p A78-22583 CERTIFICATION A method for determining structural properties of Certification study of a derivative model of a CC thermal protection material --- Reinforced small jet transport airplane using a piloted Carbon-Carbon research simulator [AIAA PAPER 78-8691 p0040 A78-35997 [AD-A0464421 pOO61 N78-14033 Jupiter probe heatshield configuration optimization CESIUM PLASMA rAIAA PAPER 78-8433 p0041 A78-37270 A cesium plasma TELEC device for conversion of CARBONACEOUS CHONDRITES laser radiation to electric power The composition of Phobos - Evidence for p 0 0 4 8 A78-51067 carbonaceous chondrite surface from spectral CESSNA MILITARY AIRCRAFT -analysis U MILITARY AIRCRAFT pOO32 A78-18874 CFRP U CARBON FIBER REINFORCED PLASTICS
74 SUBJECT INDEX CLOSURES
CHAIRS NT PHOTOCHEMICAL REACTIONS U SEATS NT PYROLYSIS CHALCOGENIDES NT REDUCTION (CHEMISTRY) NT ALUMINUM OXIDES A new concept in laser-assisted chemistry - The NT CARBON DIOXIDE electronic-field representation IT CARBON MONOXIDE p0037 A78-27743 IT CARBON SUBOXIDES Synthesis of N-substituted bisitaconimide monomers NT CHLORINE OXIDES for use as thermosetting polyimide resins NT HYDROGEN SULFIDE pO0g A78-36809 NT METAL OXIDES Calculated rate constants for the reaction CIO + 0 NT NITRIC OXIDE yields CA * 02 between 220 and 1000 deg E --- NT NITROUS OXIDES molecular trajectories and stratospheric ozone NT DIOXIDE SILICON [NASA-TM-78483 ] p0024 N78-21215 NT SULFIDES CHEMICAL RELAXATION CHANCE-VOUGHT MILITARY AIRCRAFT U MOICULAR RELAXATION I MILITARY AIRCRAFT CHEMICAL TESTS CHARNEL FLOW NT OZONOMETRY The numerical solution of viscous flows at high CHEMBISORPTION Reynolds number 6 Chemisorption of CO on Pd particles supported on p004 A78-46360 mica CHARELS (DATA TRANSMISSIOR) pOO40 A78-36040 A fifty channel electrically scanned pressure module CHLORINE COMPOUNDS pOO14 A78-17395 NT CHLORINE OXIDES Multichannel electrochemical microbial detection NT CHLOROCAPBONS unit CHLORINE OXIDES pOO16 A78-31300 Calculated rate constants for the reaction C10 + 0 CHARGE EXCHANGE yields Cl * 02 between 220 and 1000 deg K --- Exchange and relaxation effects in low-energy molecular trajectories and stratospheric ozone radiationless transitions [NASA-TM-78483] p0024 N78-21215 rNASh-TM-79383] - pO04 N78-18882 CHLORUCARBONS On the possibility of negative activation energies Lover stratosphere measurements of variation with in bimolecular reactions latitude of CF2Cl2, CFCl3, CClG, and R20 [NAS-TE-785091 p0026 N78-29149 profile.s in the northern hemisphere CHARGED PARTICLES p0035 A7S-23610 NT ALPHA PARTICLES Stratospheric measurements of CP2CI2 and N20 NT CESIUM PLASMA p0054 A78-37055 NT ENERGETIC PARTICLES Interhemispheric gradients of CP2CI2, CC13, CCI4, NT SOLAR PROTONS and N20 NT SOLAR WIND pOO'2 A78-41124 IT STELLAR WINES CHONDRITES CHARGING NT-CARBONACROUS CHONDRITES Pioneer Venus spacecraft charging model CMROMATOGRAPEY 2 2 p00 N78-10148 NT GAS CHROMATOGRAPHY CIELATE COMPOUNDS CHROME U CHELATES U CHROMIUM CNELATES CHROMIUM Chelate-modified polymers for atmospheric gas Influence of temperature and the role of chromium chromatography on the kinetics 5 7 of sulfidation of 310 stainless [NASA-CASE-ARC-11154-1] p00 N78-27275 steel CHEMICAL ANALYSIS pO043 A78-41796 NT OZONOMETRY CHROMIUM COMEPOUNDS CHEMICAL COMPOSITION Stability of chromium (II) sulfate in atmospheres NT CARBON DIOXIDE CONCENTRATION containing oxygen and sulfur CHEMICAL ELEMENTS [NASA-TM-78504] p0026 N78-28173 NT CALCIUM CIRCUITS NT CARBON NT INTEGRATED CIRCUITS NT CHROMIUM CIRCULAR CONES NT COPPER Synmetrical and asymmetrical separations about a IT HYDROGEN yawed cone --- tests in the Ames 1.8 x 1.8 wind N IRON tunnel NT LIGHT ELEMENTS [NASA-T-78532] pOO08 N78-32045 NT NITROGEN CIRCULATION NT NITROGEN IONS NT ATMOSPHERIC CIRCULATION NT OXYGEN CITIES NT OXYGEN ATOMS Phase 1: Definition of intercity transportation NT OXYGEN IONS comparison framework. Volume 1: Summary --- NT PALLADIUM operations research of passenger and freight NT SILICON transporatation systems IT SULFUR ENASA-CR-152152-VOL-1] p0001 N78-28992 NT TRACE ELEMENTS Phase 1: Definition of intercity transportation NT TUNGSTEN comparison framework. volume 2: Methodology CHEMICAL EVOLUTION --- operations research of passenger and freight Chemical evolution nd the origin of life - transportation systems Bibliography supplement 1976 [NASA-CR-152152-VOL-2] pOO 2 N78-2899 7 p005 478-53875 CLARK Y AIRFOIL CHEMICAL FU4LS U AIRFOIL PROFILES NT AIRCRAFT FUELS CLEAR AIR TURBULENCE CHEMICAL KINETICS Flight tests of a simple airborne device for U REACTION KINETICS predicting clear air turbulence encounters CHEMICAL LASERS [AIRA 78-1375] p0019 A78-4656( Semiclassical approach to collision-induced CLOSED ECOLOGICAL SYSTEMS emission in the presence of intense laser Space ecosynthesis: An approach to the design of radiation - An aspect in the study of closed ecosystems for use in space 1 cooperative chemical and optical pumping [NASA-TM-78 911 pOOSI1N78-2674( 7 p003 A78-27744 CLOSED LOOP SYSTEMS CHEMICAL PROPERTIES U FEEDBACK CONTROL NT THERMOCHEMICAL PROPERTIES CLOSURES CHEMICAL REACTIONS Spacesuit torso closure NT OXIDATION fNASA-CASE-ARC-11100-1) p0058 N78-3173(
75 CLOTHING SUBJECT INDEX
CLOTHING [NASA-TM-78497) POOO6 N78-26133 NT GARMENTS COMMERCIAL AVIATION NT SPACE SUITS U COMMERCIAL AIRCRAFT CLOUDS COMMUNICATING VT HYDROGEN CLOUDS NT AIRCRAFT COMMUNICATION CH EMISSION COMMUNICATION SATELLITES Airborne photometric observations between 1.25 and Space industrialization - Education --- via 3.25 microns of late-type stars communication satellites. 'p0036 A78-25295 [AAS 77-2583 pOOO1 A78-36722 COATING COMPARISON Boron trifluoride coatings for thermoplastic Phase 1: Definition of intercity transportation materials and method of applying same in glow comparison framework. Volume 1: Summary -- discharge operations research of passenger and freight rNASA-CASE-ARC-11057-1] p0057 N78-31233 transporatation systems 'rocess for producing a well-adhered durable (NASA-CR-152152-VOL-1] pOO1 N78-28993 optical coating on an optical plastic substrate Phase 1: Definition of intercity transportation --- abrasion resistant polymethyl methacrylate comparison framework. Volume 2: Methodology lenses --- operations research of passenger and freight rNASA-CASE-ARC-11039-13 pOO58 U78-32854 transportation systems COATINGS [NASA-CR-152152-VOL-2] POO29 N78-28994 NT CERAMIC COATINGS COMPARTMENTS NT INORGANIC COATINGS NT AIRCRAFT COMPARTMENTS NT PROTECTIVE COATINGS NT PRESSURIZED CABINS NT SPPAYED COATINGS COMPLEXITY NT THERMAL CONTROL COATINGS NT TASK COMPLEXITY COCKPIT SIMULATORS COMPOSITE MATERIALS Peripheral processors for high-speed simulation NT CARBON FIBER REINFORCED PLASTICS --- helicopter cockpit simulator NT CARBON-CARBON COMPOSITES .0014 A78-14063 NT FIBER COMPOSITES CODING NT GRAPHITE-EPOXY COMPOSITE MATERIALS NT DECODING NT LAMINATES NT SIGNAL ENCODING NT POLYMER MATRIX COMPOSITE MATERIALS COEFFICIENTS COMPOSITE STRUCTURES NT DIFFUSION COEFFICIENT NT LAMINATES NT INFLUENCE COEFFICIENT Low density bismaleimide-carbon microballoon NT NOTZLE THRUST COEFFICIENTS composites --- aircraft and submarine COHERENT RADIATION compartment safety Thermodynamic processes induced by coherent (NASA-CASE-ARC-I1040-2) pOO5O N78-27184 radiation COMPOSITION (PROPERTY) pOO4 A78-21624 NT ATMOSPHERIC COMPOSITION COHERENT SCATTERING NT CARBON DIOXIDE CONCENTRATION Diagrammatic evaluation of the density operator NT IONOSPHERIC COMPOSITION for nonlinear optical calculations NT METEORITIC COMPOSITION ONERA, TP NO. 1977-166] pOO31 A78-14651 COMPRESSIBLE BOUNDARY LAYER COHERENT SOURCES Reynolds number and pressure gradient effects on q COHERENT RADIATION compressible turbulent boundary layers COHERENT TRANSMISSION [AIAA PAPER 78-199] p0 0 3 3 A78-20741 U COHERENT RADIATION An evaluation of several compressible turbulent COIN AIRCRAFT boundary-layer models Effects of pressure NT F-5 AIRCRAFT gradient and Reynolds number COLLIMATORS [AIAA PAPER 78-1160] p00 4 3 A78-41859 Generation of a parallel I-ray-beam and its use COMPRESSIBLE FLOW for testing collimators NT TRANSONIC FLOW p0035 A78-23083 COMPRESSORS COLLISION WARNING DEVICES - An analysis of the rotor blade stresses of the U WARNING SYSTEMS three stage compressor of the Ames Research COLLISIONS Center 11- by 11-foot transonic wind tunnel NT ATOMIC COLLISIONS [NASA-CR-152083] p0009 N78-17061 NT METEORITE COLLISIONS COMPUTATION NT MOLECULAR COLLISIONS A computer program for calculating laminar and COLLOIDS turbulent boundary layers for two-dimensional NT AEROSOLS time-dependent flows COLUMNS (PROCESS ENGINEERING) [NASA-TM-78470] pOO51 N78-19444 Synthesis of porous polyaromatic column packings Computational aerodynamics and the numerical for GC analysis of extraterrestrial atmospheres aerodynamic simulation facility pOO55 A78-48577 p 0 0 2 3 N78-19779 COMBAT Computing viscous flows Coplanar tail-chase aerial combat as a pOOO5 N78-19794 differential game COMPUTER COMPONENTS pOOlQ A78-10455 The ILLIAC IV memory system: Current status and, A preference-ordered discrete-gaming approach to future possibilities air-combat analysis [NASA-CR-1521771 pOO60 N78-32731 pOO 2 O A78-49255 COMPUTER GRAPHICS COMBUSTIBILITY Computer display and manipulation of biological U FLAMMABILITY molecules COMBUSTION PRODUCTS pOO5 6 A78-53400 The prediction of toxic atmospheres from COMPUTER METHODS decomposing polymers U COMPUTER PROGRAMS p0033 A78-19895 COMPUTER PROGRAMMING Fire resistivity and toxicity studies of candidate Three-dimensional computational aerodynamics in aircraft passenger seat materials the 198-Os pO 4 8 A78-51838 p0023 N78-19781 COMMERCIAL AIRCRAFT COMPUTER PROGRAMS NT CV-99O AIRCRAFT NT OPERATING SYSTEMS (COMPUTERS) Fuel saving potential of Mach 0.8 twin engine NT SUBROUTINES prop-fan transports Computation of the viscous supersonic flow over pOO17 A78-31306 symmetrical and asymmetrical external axial Trajectory module of the NASA Ames Research Center corners aircraft synthesis program ACSYRT [AIAA PAPER 78-1135) pOO 4 3 A78-41839
76 SUBJECT INDEX CONSUMPTION
Theoretical and experimental study of the drag of V/STOL aircraft simulation - Requirements and multielement airfoils capabilities at Ames Research Center rAIAA PAPER 78-12231 pOO19 A78-45148 CAIAA PAPER 78-1515] p0021 A78-49790 A computer program for calculating laminar and Numerical aerodynamic simulation facility. turbulent boundary layers for two-dimensional Preliminary study extension. Executive summary time-dependent flows [fASA-CR-152106] p0O28 H78-19050 rNASA-TM-78470] p051 N78-19444 Preliminary study for a numerical aerodynamic Rotorcraft linear simulation model. Volume 2: simulation facility. Phase 1: Extension computer implementation [NASA-CR-152108] p0 0 2 8 H78-19052 [NASA-CR-152079-VOL-2] pOO10'N78-20137 Computational aerodynamics and the numerical Trajectory module of the NASA Ames Research Center aerodynamic simulation facility aircraft synthesis program ACSYNT pOO 2 3 N78-19779 [NASA-IM-78497] pOO06 U78-26133 Computing viscous flows System optimization of gasdynamic lasers, computer I pOOO5 N78-19794 program user's manual Infrastructure dynamics: A selected bibliography (NASA-TM-73193] p0027 N78-29436 [NASA-CR-152162] pO12 N78-25824 COMPUTER SIMULATION . Application of special-purpose digital computers U COMPUTERIZED SIMULATION to rotorcraft real-time simulation 7 COMPUTER STORiGE DEVICES (NASA-TP-1267] pOOO V78-27113 NT BUFFER STORAGE COMPUTERS The ILLIAC IV memory system: Current status and NT AIRBORNE/SPACEBORNE COMPUTERS future possibilities NT DIGITAL COMPUTERS rWASA-CR-152177] p0060 H78-32731 NT ILLIAC COMPUTERS COMPUTER SYSTEMS DESIGN CONCENTRATION (COMPOSITION) Peripheral processors for high-speed simulation NT CARBON DIOXIDE CONCENTRATION --- helicopter cockpit simulator CONDENSING pOO14 A78-14063 Experimental temperature distribution and heat Preliminary study for a numerical aerodynamic load characteristics of rotating heat pipes simulation facility. Phase 1: Extension p0046 A78-48835 [NASA-CR-152108] pO028 N78-19052 CONDITIONS Future Computer Requirements for Computational NT FLIGHT CONDITIONS Aerodynamics CONDUCTANCE r.NASA-CP-2032] p0023 N78-19778 U RESISTANCE Computational aerodynamics and the numerical CONDUCTIVE HEAT TRANSFER aerodynamic simulation facility The spiral field inhibition of thermal conduction p0023 N78-19779 in two-fluid solar wind models Numerical Aerodynamics Simulation Facility pO8m6 A78-48281 preliminary study, executive summary --- three CONDUCTORS dimensional flow NT PROTOCONDUCTORS pOO23 N78-19782 CORES Preliminary study for a Numerical Aerodynamic NT ABLATIVE ROSE CONES Simulation Facility --- three dimensional flow NT CIRCULAR CONES pO0 2 3 N78-19783 NT CONICAL BODIES future requirements and roles of computers in NT NOSE CONES aerodynamics Computation of supersonic laminar viscous flow pOO0 578-19786 past a pointed cone at angle of attack in A single user efficiency measure for evaluation of spinning and coning motion parallel or pipeline computer architectures [AIAA PAPER 78-1211] pOO45 A78-45139 pO059 N78-19808 CONFERENCES The ILLIAC IV memory system: 'Current status and Abstracts for the Planetary Geology Field future possibilities Conference on Aeolian Processes 2 rNASA-CR-152177) p0060 78-32731 [NASA-TH-78455] pOO 2 N78-13492 COMPUTER SYSTEMS PROGRAMS Future Computer Requirements for Computational NT OPERATING SYSTEMS (COMPUTERS) Aerodynamics COMPUTER TECHNIQUES [NASA-CP-2032] p0023 N78-19778 A view toward future fluid dynamics computing CONICAL BODIES [AAA PAPER 78-1112] pOOl5 A78-45126 Calculation of supersonic viscous flow over delta Project plan for joint FAA/NASA head-up display wings with sharp subsonic leading edges concept evaluation [NASA-T-78500] pO025 N78-26101 2 [NASA-TM-78512] pOO5 578-28979 CONICAL FLARE Peaker: An automatic boresight peaking routine U CONES for the C-ill telescope CONICAL FLOW [NASA-TM-78516] 1 0028 N78-32856 Calculation of supersonic viscous flow over delta COMPUTERIZED CONTROL wings with sharp subsonic leading edges U NUMERICAL CONTROL [AIAA PAPER 78-1137] pOO43 A78-41841 COMPUTERIZED DESIGN CONNECTIONS Robustness in linear quadratic feedback design U JOINTS (JUNCTIONS) with application to an aircraft control problem CONNECTIVE TISSUE pOOl' A78-18059 NT CARTILAGE Computational wing optimization and wind tunnel / CONOIDS test of semi-span model U CONICAL BODIES AIAR PAPER 38-102] p0034 A78-22575 CONSERVATION A study of commuter airplane design optimization NT ENERGY CONSERVATION (NASA-CR-157210] pOOl1 N78-25078 CONSERVATION EQUATIONS COMPUTERIZED SIMULATION Coefficient matrices for implicit finite NT DIGITAL SIMULATION difference solution of the inviscid fluid Behavior of a turbulent boundary layer subjected conservation law equations to sudden transverse strain p0 0 38 A78-30893 [AIAA PAPER 78-201] pOO34 A78-22595 CONSTANTS Carbonaceous materials subjected to extreme Calculated rate constants for the reaction CIO + 0 heating - A comparison of numerical simulation yields Cl + 02 between 220 and 1000 deg K -- and experiments -- Jovian entry conditions molecular trajectories and stratospheric ozone [AIAA PAPER 78-8661 pO41 A78-37273 [NASA-TM-78483] pOO2 N78-21215 Simulation replay - Implementation and flight CONSTRAINTS simulation applications NT METEOROLOGICAL PARAMETERS pOOl8 A78-38789 CONSTRUCTION MATERIALS A view toward future fluid dynamics computing NT AIRCRAFT CONSTRUCTION MATERIALS tAIAA PAPER 78-1112] pOO5 A78-45126 CONSUMPTION NT FUEL CONSUMPTION
77 CONTAMINANTS SUBJECT INDEX
FT OXYGEN CONSUMPTION CORONAS CONTAMINANTS NT SOLAR CCRONA Transport of contaminants in the planetary CORPUSCULAR RADIATION boundary layer NT ENERGETIC PARTICLES p0048 A78-52137 NT SOLAR PROTONS CONTAMINATION CORROSION NT SPACECRAFT CONTAMINATION NT SCALE (CORROSION) Experimental investigation of contamination CORUNDU_ -prevention-technigues-to cryogenit surfaces on U ALUMINUM OXIDES board orbiting spacecraft COSMIC DUST fNASA-C-152171] p0029 N78-29146 NT INTERPLANETARY DUST CONTENT Evolution of rotating interstellar clouds. III - NT BONE MINERAL CONTENT On the formation of multiple star systems CONTINUOUS RADIATION pOO7 A78-49471 NT MODULATED CONTINUOUS RADIATION COSMIC GASES CONTINUOUS WAVE LASERS NT INTERSTELLAR GAS Absorption measurements of OH using a CW tunable COSMIC RADIATION laser U COSMIC RAYS p0032 A78-17837 COSMIC RAYS CONTOURS Radiometer system to map the cosmic background A study of test section configuration for shock radiation tube testing of transonic airfoils p0038 A78-30691 rNASA-CR-157237] p0012 N78-26153 Quiet time interplanetary cosmic ray anisotropies CONTROL observed from Pioneer 10 and 11 Conceptual design study of a Harrier V/STOL p0039 A78-34567 research aircraft COST ANALYSIS rNASA-CH-152086] pO09 N78-19094 Phase 1: Definition of intercity transportation CONTROL SIMULATION comparison framework. Volume 1: Summary -- Dual-loop model of the human controller operations research of passenger and freight pOO18 A78-39184 transporatation systems Hotorcraft linear simulation model. Volume 1: [NASA-CR-152152-VOL--1] p0001 N78-28993 Xngineering documentation Phase 1: Definition of intercity transportation rNASA-CR-152079-VOL-1I pOO10 N78-20136 comparison framework. Volume 2: Methodology Rotorcraft linear simulation model. Volume 2: --- operations research of passenger and freight Computer implementation transportation systems rNASA-CR-152079-VOL-2) pOO10 N78-20137 [NASA-CR-152152-VOL-2J p0029 N78-28994 CONTROL STABILITY COST EFFECTIVENESS Theoretical study of multicyclic control of a Executive summary: Benefit-cost evaluation of an controllable twist rotor intra-regional air service in the Nay Area and a (NASA-CN-151q59] p0064 N78-33085 technology assessment of transportation system CONTROL SURFACES investments --- regional planning for the San NT AILERONS Francisco Ray area of California NT GUIDE VANES [NASA-CR-152154-13 p0O13 N78-28988 NT WING FLAPS A method for the analysis of the benefits and CONTROL SYSTEMS costs for aeronautical research and technology U CONTrOL pOO07 N78-29060 CONTROL THEORY COSTS Applications of algebraic geometry to systems NT AIRPLANE PRODUCTION COSTS theory - The McMillan degree and Kronecker NT FREIGHT COSTS indices of transfer functions as topological and Application of a cost/performance measurement holomorphic system invariants system on a research aircraft project p00 2 1 A78-51860 [NASA-TM-78498] pOO07 N78-27043 Optimal control theory (OWEN) applied to a COUNTERS helicopter in the hover and approach phase NT PROPORTIONAL COUNTERS [EASA-CR-152135] p0010 N78-21161 COWELL METHOD CONTROLLED ATMOSPHERES U NUMERICAL INTEGRATION NT SPACECRAFT CABIN ATMOSPHERES CRACKING (CHEMICAL ENGINEERING) CONTROLLED STABILITY NT PYROLYSIS U CONTROL CRATERING CONVAIR MILITARY AIRCRAFT NT PROJECTILE CRATERING U MILITARY AIRCRAFT An analytic study of impact ejecta trajectories in CONVAIR 990 AIRCRAFT the atmospheres of Venus, Mars. and earth U CV-990 AIRCRAFT p0037 A78-29532 CONVECTIVE HEAT TRANSFER Application of high explosion cratering data to Study of a high performance evaporative beat planetary problems transfer surface 2 p0044 A78-q4O33 (NASA-C-152008] pOO 8 N78-10411 CRATERS CONVERTAPLANES NT LUNAR CRATERS U V/STOL AIRCRAFT NT METEORITE CRATERS COOLING CRITICAL REYNOLDS NUMBER NT AIR COOLING U REYNOLDS NUMBER NT EVAPORATIVE COOLING CROSS FLOW NT RADIANT COOLING Laser-velocimeter surveys of merging vortices in a COPPER wind tunnel The co-adsorption of copper and oxygen on a [AIAA PAPER 78-107) pO15 A78-20687 tungsten 100 plane-type surface CHOSSLINKING pO037 A78-29489 Polymeric foams from cross-linkable CORNER FLOW poly-n-arylenebenzimidazoles Numerical solution of a three-dimensional shock rNASA-CASE-ARC-11008-11 p0050 N78-31232 wave and turbulent boundary-layer interaction CRUSTS FAIAA PAPER 78-161] p0034 A78-22591 NT LUNAR CRUST Computation of the viscous supersonic flow over CRYOGENIC EQUIPMENT symmetrical and asymmetrical external axial Investigation of a cryogenic thermal diode corners [AIAA 78-417] p0040 A78-35601 EAIAA PAPER 78-1135] p0043 A78-41839 Theoretical contamination of cryogenic satellite A detailed study of attached and separated telescopes 2 4 compression corner flowfields in high Reynolds [NASA-TP-1177] pOO N78-21193 number supersonic flow. CRYOGENICS fAIAA PAPER 78-1167] pO043 A78-41865 Experimental investigation of contamination
78 SUBJECT INDEX DIFFERENTIAL ALGEBRA
prevention techniques to cryogenic surfaces on DECAMETRIC WAVES board orbiting spacecraft on the modulation of the Jovian decametric [NASA-CR-152171] p0029 N78-29146 radiation by to. I - Acceleration of charged CRYSTAL LATTICES particles Square Ising ferromagnetic and antiferromagnetic pOOU2 A78-41074 lattices in a magnetic field - A new DECAY perturbation approach NT FLUORESCENCE pO5 6 A78-51886 NT HYDROXYL EMISSION CURING NT SPONTANEOUS EMISSION Reaction cured glass and glass coatings N NT STIMULATED EMISSION FNASA-CASE-AEC-11051-1] pOO50 N78-32260 DECELERATORS CURL (VECTORS) U BRAKES (FOR ARRESTING MOTION) NT VORTICITY DECISION MAKING CURTISS-WRIGHT MILITARY AIRCRAFT A model of human decisionmaking in a fault 0 MILITARY AIRCRAFT diagnosis task 5 4 CURVED SURFACES pOO A78-37130 V CONTOURS DECISION THEORY CY-990 AIRCRAFT A technology assessment of transportation system NASA/ESA CV-990 Spacelab simulation (ASSESS 2) investments --- Markovian decision theory [NASA-CR-152122] p0029 N78-23117 [NASA-C-152154-2] pOOl3 N78-28989 NASA/ESA cV-990 spacelab simulation (ASSESS 2) DECODING [NASA-TH-79748] pOO27 N78-30149 A decoding procedure for the Reed-Solomon codes CYARATES fNASA-TP-1286] pOO5 N78-30862 Catalysts for imide formation from aromatic DECOMPOSITION isocyanates and aromatic dianhydrides NT PHOTODISSOCIATION [NASA-CASE-ARC-11107-1] pOO49 N78-22156 DEEP SPACE CYANIDE EMISSION NT INTERPLANETARY SPACE U CN EMISSION DREFLECTORS CYCLES Static tests of a large scale swivel nozzle thrust NT STIRLING CYCLE deflector CYCLIC COMPOUNDS (NASA-CR-152091) pOO11N78-22100 NT CYCLIC HYDROCARBONS DELTA WINGS CYCLIC HYDROCARBONS calculation of supersonic viscous flow over delta Thermal rearrangements in 1,2-poly/1,4-hexadiene/s wings with sharp leading edges subsonic 4 p0048 A78-51870 [AIAA PAPER 78-1137] pO0 3 A78-41841 CYLINDRICAL BODIES Calculation of supersonic viscous flow over delta NT ROTATING CYLINDERS wings with sharp subsonic leading edges CYSTEINE [NASA-TM-78500] pOO 2 5 N78-26101 Methionine transport in Halobacterium halobium DENSITY (NUMBER/VOLUME) vesicles - Noncompetitive, asymmetric inhibition NT IONOSPHERIC ELECTRON DENSITY by 1-Cysteine DENSITY (RATE/AREA) pOO55 A78-48579 U FLUX DENSITY DENSITY WAVE MODEL D Bar-driven spiral waves in disk galaxies p0 0 3 8 A78-32467 DAEMO (DATA ANALYSIS) DEPOSITION U DATA PROCESSING NT VACUUM DEPOSITION DAMAGE NT VAPOR DEPOSITION NT IMPACT DAMAGE DESCENT TRAJECTORIES DAMPING IN PITCH A simple method for estimating minimum U PITCH (INCLINATION) autorotative descent rate of single rotor DAMPING IN ROLL helicopters U ROLL [NASA-T-78452] pOOO5 N78-20113 DATA ADAPTIVE EVALUATOR/MONITOR DESCRIPTIVE GEOMETRY U DATA PROCESSING A solution to the surface intersection problem --- DATA ANALYSIS Boolean functions in geometric modeling U DATA PROCESSING [NASA-CR-152116] pOOlO N78-19869 DATA EASES DESIGN ANALYSIS Generalization of Huffman coding to minimize the A re-entrant groove hydrogen heat pipe 0 0 4 0 probability of buffer overflow (AIAA 78-420] p A78-35603 rAD-AO50974] pOO06 N78-22754 Study to design and develop remote manipulator DATA BUSSES systems 2 U CHANNELS (DATA TRANSMISSION) [NASA-CR-152092] pOO5 N78-16620 DATA COMPACTION Conceptual design study of a Harrier V/STOL U DATA COMPRESSION research aircraft DATA COMPRESSION [NASA-CR-152086] pOO9 N78-1994 Survey of adaptive image coding techniques Study, optimization, and design of a laser heat 0 0 3 1 p A78-15267 engine DATA CONVERSION ROUTINES [NASA-CR-152104] pOOO9 N78-19481 NT SUBROUTINES Wing analysis using a transonic potential flow DATA MANAGEMENT computational method X10: A FORTRAN direct access data management system [NASA-TM-78464] pOOO7 N7S-28053 pOO6O N78-33784 DETONABLE GAS MIXTURES DATA PROCESSING Arrhenius' law in turbulent media and an NT PARALLEL PROCESSING (COMPUTERS) equivalent tunnel effect --- in binary exchange NT SIGNAL PROCESSING chemical reactions Generalization of Huffman coding to minimize the p0049 A78-52547 probability of buffer overflow DEWAR SYSTEMS [AD-A050974] pOO0 6 U78-22754 U CRYOGENIC EQUIPMENT DATA PROCESSING EQUIPMENT DIAMOND WINGS NT AIRBORNE/SPACEBORRE COMPUTERS U SWEPT WINGS NT DIGITAL COMPUTERS DIATONIC MOLECULES NT ILLIAC COMPUTERS Quantum mechanical theory of a structured DATA READOUT SYSTEMS atom-diatom collision system - A * BC/1-Sigma/ U DISPLAY DEVICES [AD-AO51266] pOO31 A78-164s DEBRIS DIENES Are the stratospheric dust particles meteor NT SEXADIENE ablation debris or interplanetary dust? DIFFERENTIAL ALGEBRA rNASA-TM-78507] p0028 N78-34014 U MATRICES (MATHEMATICS)
79 DIFFERENTIAL EQUATIONS SUBJECT INDEX
DIFFERENTIAL EQUATIONS p0056 A78-53400 NT PARABOLIC DIFFERENTIAL EQUATIONS DISPLAY SYSTEMS Solution of transonic flows by an U DISPLAY DEVICES integro-differential equation method DISPOSAL 2 6 rNASA-TM-78490] p00 N78-26391 NT WASTE DISPOSAL DIFFERENTIAL GEOMETRY DISSOCIATION Coplanar tail-chase aerial combat as a NT GAS DISSOCIATION differential game NT PHOTODISSOCIATION pOOlU A78-10455 DISTORTION DIFFERENTIAL OPERATORS UT FLOW DISTORTION U DIFFERENTIAL EQUATIONS DISTRIBUTION (PEOPERTY) DIFFUSION NT FLOW DISTRIBUTION NT PARTICLE DIFFUSION NT FORCE DISTRIBUTION DIFFUSION COEFFICIENT NT RADIAL DISTRIBUTION On determining magnetospheric diffusion NT RADIATION DISTRIBUTION coefficients from the observed effects of NT SPATIAL DISTRIBUTION Jupiter's satellite Io NT STAR DISTRIBUTION p0032 A78-18732 RT STRESS CONCENTRATION DIFFUSION THEORY NT TEMPERATURE DISTRIBUTION An integral solution to a nonlinear diffusion NT VELOCITY DISTRIBUTION problem 7 DISTURBANCE THEORY pOO3 A78-26350 U PERTURBATION THEORY DIGITAL COMPUTERS DIURNAL VARIATIONS NT ILLIAC COMPUTERS A note on the diurnal averaging of aeronomical Future requirements and roles of computers in models aerodynamics p0039 A78-34352 pOOO4 N78-19786 DOCUMENTS DIGITAL FILTERS HT ABSTRACTS Digital filter structures having low errors and NT BIBLIOGRAPHIES simple hardware implementation NT USER MANUALS (COMPUTER PROGRAMS) pOO56 A78-51346 DOPING (ADDITIVES) DIGITAL SIMULATION U ADDITIVES Peripheral processors for high-speed simulation DOUGLAS MILITARY AIRCRAFT --- helicopter cockpit simulator U MILITARY AIRCRAFT pOO1 4 A78-14063 DRAG Simulator evaluation of three situation and NT AERODYNAMIC DRAG guidance displays for V/STOL aircraft zero-zero NT SUPERSONIC DRAG landing approaches Radiation pressure and Poynting-Robertson drag for p0055 A78-44131 small spherical particles --- in interplanetary Multi-calculation rate simulations space 9 rNASA-CR-155335] pOO0 N78-13765 p0033 A78-19768 Numerical aerodynamic simulation facility. DRAG BALANCE Preliminary study extension U AERODYNAMIC BALANCE CLASA-CP-152107) p0028 N78-19051 U LIFT DRAG RATIO DIGITAL SYSTEMS DRAG COEFFICIENT Advanced Digital Avionics System for general U AERODYNAMIC DRAG aviation DRAG DEVICES 14 fAIAA 77-14941 pOl A78-12243 NT WING FLAPS DIGITAL TRANSDUCERS DRAG EFFECT Anqle detector U DRAG 6 [NASA-CASE-ARC-11036-1] pOO 0 578-32395 DRAG MEASUREMENT DIMENSIONLESS NUMBERS Theoretical and experimental study of the drag of NT REYNOLDS NUMBER multielement airfoils DIMENSIONS [AIAA PAPER 78-1223) pO019 A78-45148 NT RADII DRAG REDUCTION DIODES Three-dimensional canard-wing shape optimization NT JUNCTION DIODES in aircraft cruise and maneuver environments Extended development of variable conductance heat [AIlA PAPER 78-99] pOOl 6 A78-26274 pipes 2 9 DRAGULATORS [NASA-CR-152183] p00 N78-33379 U BRAKES (FOR ARRESTING NOTION) DIOXIDES DRONE RELICOPTERS NT CARBON DIOXIDE U HELICOPTERS NT SILICON DIOXIDE DRUGS DIPOLE MOMENTS NT CYSTEINE Semirigorous bounds for the dipole moments and DRY HEAT transition moments of the LiH molecule Degradation of biochemical activity in soil p0046 A78-45963 sterilized by dry heat and gamma radiation DIRECTIONAL CONTROL pOO5 7 A78-53874 NT THRUST VECTOR CONTROL f DUIGETS WIND SHEAR MECHANISM DIRIGIBLES U WIND SHEAR 9 AIRSHIPS DUST DISCONTINUITY NT COSMIC DUST NT SHOCK DISCONTINUITY NT INTERPLANETARY DUST DISKS (SHAPES) DWARF STARS NT ROTATING DISKS ISAS and the dwarf content of the inner nuclear DISPERSIONS regions of M31 --- Intrinsic Strength Anomalies NT AEROSOLS p0042 A78-38569 NT SMOKE DYE LASERS Generation of a monodispersed aerosol Absorption measurements of OR using a CW tunable (NASA-CR-152133] pOO11 N78-21445 laser DISPLAY DEVICES p 0 0 3 2 A78-17837 NT READ-UP DISPLAYS DYNAMIC CHARACTERISTICS NT ROT-WIRE ANEMOMETERS NT AERODYNAMIC DRAG Simulator evaluation of three situation and NT AERODYNAMIC STABILITY guidance displays for V/STOL aircraft zero-zero NT AIRCRAFT STABILITY landing approaches NT CONTROL STABILITY p0055 A78-44131 NT DRAG Computer display and manipulation of biological NT DYNAMIC STABILITY molecules NT FLOW DISTRIBUTION
80 SUBJECT INDEX ELECTROMAGNRETIC FIELDS
NT FLOW STABILITY EDDY VISCOSITY NT HOVERING STABILITY Comparison of multieguation turbulence models for NT LIFT several shock-separated boundary-layer NT MOTION STABILITY interaction flows NT ROTARY STABILITY [AIAA PAPER 78-1165] p00 4 3 A78-41863 NT SUPERSONIC DRAG EDGES The role of time-history effects in the NT LEADING EDGES formulation of the aerodynamics of aircraft NT SHARP LEADING EDGES dynamics EDUCATION rNASA-PM-78471] p0023 N78-19056 Space industrialization - Education --- via DYNAMIC LOADS communication satellites NT AERODYNAMIC LOADS [AAS 77-258] pODO1 A78-36722 NT WING LOADING EFFECTIVENESS DYNAMIC MODELS NT COST EFFECTIVENESS Dynamic HqD modeling of the solar wind NT SYSTEM EFFECTIVENESS disturbances during the August 1972 events EFFICIENCY p0036 A78-26079 A single user efficiency measure for evaluation of Dual-loop model of the human controller parallel or pipeline computer architectures p0018 A78-39184 pO059 E78-19808 Numerical experiments on the stability of disklike EMAB LAYER galaxies U BOUNDARY LAYER TRANSITION 9 pOO1 A78-45535 ELASTIC PROPERTIES Dynamic MHD modeling of solar wind corotating NT AEROELASTICITY stream interaction regions observed by Pioneer ELASTIC WAVES 10 and 11 NT AERODYNAMIC NOISE p0049 A78-52522 NT AIRCRAFT NOISE On the period of the coherent structure in NT ENGINE NOISE boundary layers at large Reynolds numbers NT JET AIRCRAFT NOISE [NASA-TR-78477] p0024 N78-21407 NT SHOCK WAVES Infrastructure dynamics: A selected bibliography ELECTRIC CURRENT [NASA-CR-152162] p0012 N78-25824 NT ELECTRIC DISCHARGES DYNAMIC PROGRAMMING NT GAS DISCHARGES Assessing the future of air freight NT GLOW DISCHARGES [NASA-CR-152161] pOO09 N78-14016 NT RADIO FREQUENCY DISCHARGE DYNAMIC PROPERTIES ELECTRIC DISCHARGES U DYNAMIC CHARACTERISTICS NT GAS DISCHARGES DYNAMIC RESPONSE NT GLOW DISCHARGES Dynamic stall experiments on the NACA 0012 airfoil NT RADIO FREQUENCY DISCHARGE [NASA-TP-1100] pO062 N78-17000 An investigation of the reduction of carbon STABILITY dioxide in a silent electric discharge DYNAMIC 3 4NT AERODYNAMIC STABILITY [NASA-CR-152146] pOO5 N78-25767 NT AIRCRAFT STABILITY ELECTRIC FILTERS NTCONTROL STABILTTY NT DIGITAL FILTERS NT FLOW STABILITY ELECTRIC POWER SUPPLIES NT HOVERING STABILITY NT SPACECRAFT POWER SUPPLIES NT MOTION STABILITY ELECTRIC STIMULI NT ROTARY STABILITY Tread drum for animals --- having an electrical Influence of spin rate on side force of an shock station axisymmetric body [NASA-CASE-ARC-10917-1] pOD57 N78-27733 pO038 A78-30690 ELECTRICAL PROPERTIES On the stability of disklike galaxies in massive NT INDUCTANCE halos ELECTROCARDIOGRAMS pOO2D A78-47354 9 ELECTROCARDIOGRAPHY Static and dynamic stability analysis of the space ELECTROCARDIOGRAPHY shuttle vehicle-orbiter An inductively powered telemetry system for [NASA-TP-1179] pODS N78-20176 temperature, EKG. and activity monitoring DYNAMIC STRUCTURAL ANALYSIS [VASA-TM-78486] p 0 0 5 9 178-23706 The general solution to the classical problem of ELECTROCHEMISTRY the finite Euler-Bernoulli beam NT ELECTROLYSIS pO04 7 A78-50909 Multichannel electrochemical microbial detection unit E p0016 A78-31300 Technology advancement of the electrochemical C02 EAR concentrating process NT LABYRINTH [NASA-CR-152098] pOO52 N78-22723' EARLY STARS ELECTRODES Infrared excesses in early-type stars - Gamma NT IMPLANTED ELECTRODES (BIOLOGY) Cassiopeiae ELECTROLYSIS p0047 A78-49475 Advanced solid electrolyte cell for C02 and H20 EART (PLANET) electrolysis --- for extended duration manned Abstracts for the Planetary Geology Field spaceflights Conference on Aeolian Processes (NASA-CR-152093] p0052 N78-21235 [NASA-TM-78455] p0022 N78-13492 ELECTROLYTE METABOLISM EARTE ATMOSPHERE Fluid-electrolyte shifts and maximal oxygen uptake NT EXOSPHERE in man at simulated altitude /2,287 m/ NT MAGNETOSPHERE pO054 A78-36602 NT TROPOSPHERE ELECTROLYTIC CELLS NT UPPER ATMOSPHERE Advanced solid electrolyte cell for C02 and 820 An analytic study of impact ejecta trajectories in electrolysis --- for extended duration manned the atmospheres of Venus, Mars, and earth spaceflights p0837 A78-29532 fNASA-CR-152093] p0052 N78-21235 EARTH SATELLITES ELECTROMAGNETIC ABSORPTION NT COMMUNICATION SATELLITES NT, PHOTOABSORPTION ECONOMIC ANALYSIS NT ULTRAVIOLET ABSORPTION Comments on 'Feasibility study of a hybrid airship ELECTROMAGNETIC FIELDS operating in ground effect' Semiclassical theory of unimolecular dissociation pOO16 A78-24367 induced by a laser field EDDIES (AD-A056671] pOO39 A78-34682 U VORTICES
81 ELECTROMAGNETIC INTERFERENCE SUBJECT INDEX
ELECTROMAGNETIC INTERFERENCE ELECTROPHORESIS NT ELECTROMAGNETIC NOISE Automatic multiple-sample applicator and NT WHISTLERS electrophoresis apparatus ELECTROMAGNETIC NOISE [NASA-CASE-ARC-10991-1] p0057 N78-14104 NT WHISTLERS ELEMENTARY EXCITATIONS Signal-to-noise ratios for stellar occultations by NT PLASNONS the rings of Uranus, 1977-1980 ELEBENTARY PARTICLES p0033 A78-20223 NT -ALPHA PARTICLES -ELECTROMAGNETIC PROPERTIES NT NUCLEONS NT INDUCTANCE NT SOLAR PROTONS NT OPTICAL 'ROPERTIES EMISSION NT OPTICAL REFLECTION NT FLUORESCENCE ELECTROMAGNETIC RADIATION NT HYDROXYL EMISSION NT AINGLOW NT SPONTANEOUS EMISSION NT DECAMETRIC WAVES NT STIMULATED EMISSION NT GAMMA RAYS EMISSION SPECTRA NT HYDROXYL EMISSION Shock-tube studies of atomic silicon emission in NT MODULATED CONTINUOUS RADIATION the spectral range 180 to 300 nm --- environment NT PLANETARY RADIATION simulation for Jupiter probes 3 NT SOLAR X-RAYS (AIAA PAPER 78-234] pOO I A78-22602 NT ZODIACAL LIGHT Europa - Ultraviolet emissions and the possibility ELECTROMAGNETIC SCATTERING of atomic oxygen and hydrogen clouds NT HALOS pO848 A78-52482 NT LIGHT SCATTERING ENDOCRINE GLANDS NT RAMAN SPECmRA NT ADRENAL GLAND ELECTROMAGNETIC SPECTRA ENDOCRINE SECRETIONS NT INFRARED SPECTRA NT ESTROGENS NT RAMAN SPECTRA NT HORMONES NT VIBRATIONAL SPECTRA ENERGETIC PARTICLES NT X RAY SPECTRA Whistler mode noise in Jupiter's inner magnetosphere ELECTROMAGNETIC WAVE FILTERS p0045 A78-45188 NT DIGITAL FILTERS ENERGY ABSORPTION ELECTROMAGNETIC WAVE TRANSNISSION NT PHOTOABSORPTION NT HALOS NT ULTRAVIOLET ABSORPTION NT LIGHT SCATTERING ENERGY CONSERVATION NT LIGHT TRANSMISSION Fuel saving potential of Mach 0.8 twin engine ELECTRON DENSITY (CONCENTRATION) prop-fan transports NT IONOSPHERIC ELECTRON DENSITY p017 A78-31306 ELECTRON ENERGY Short-haul CTOL aircraft research --- on reduced NT ELECTRON STATES energy for commercial air transportation Thermal structure of the primitive ionosphere pOOD8 N78-29061 p035 A78-23543 ENERGY CONVERSION ELECTRON FLUX DENSITY NT SATELLITE SOLAR ENERGY CONVERSION The interplanetary modulation and transport of A cesium plasma TELEC device for conversion of Jovian electrons 3 laser radiation to electric power pOO 6 A78-26080 pOO48 A78-51067 ELECTRON INTENSITY ENERGY DENSITY U ELECTRON FLUX DENSITY U FLUX DENSITY ELECTRON IONIZATION ENERGY LEVELS U IONIZATION NT ELECTRON STATES ELECTRON MICROSCOPY NT MOLECULAR ENERGY LEVELS Spectrophotofluorometric and electron microscopic ENERGY REQUIREMENTS study of Lipofuscin accumulation in the testis Satellite mirror systems for providing terrestrial of aging mice power - System concept p0056 A78-48581 [AAS 77-240] p0040 A78-36717 ELECTRON STATES ENERGY SPECTRA A new concept in laser-assisted chemistry - The Energetic protons associated with interplanetary electronic-field representation active regions 1-5 AU from the sun pOO37 A78-27743 pO03 6 A78-26081 ELECTRON TEMPERATURE ENERGY STORAGE " ELECTRON ENERGY Physiologic regulation of body energy storage ELECTRON TRANSITIONS p0055 A78-42817 A theoretical study of the electronic transition ENERGY STORAGE DEVICES moment for the C2 Swan band system U ENERGY STORAGE 4 pOO l A78-36776 ENGINE INLETS Semirigorous bounds for the dipole moments and Effects of inlet airframe integration on the inlet transition moments of the LiE molecule of an upper surface blowing four-engine STOL pO046 A78-45963 aircraft Absolute intensity measurements at different (AIAA PAPER 78-959] pGO1 8 A78-43521 temperatures of the C-12/0-16/2 bands 30 0 1 Estimating maximum instantaneous distortion from I--0 0 0 and 30 0 1 IV--0 0 0 inlet total pressure rms measurements 4 pOO 7 A78-50488 [AIAA PAPER 78-9701 pOO1S A78-43525 Exchange and relaxation effects in low-energy ENGINE NOISE radiationless transitions Analysis of flight effects on noise radiation from ENASA-TM-79383] pOOO4 N78-18882 jet flow using a convecting quadrupole model ELECTRON TUNNELING [AIAA PAPER 78-192] pOO15 A78-22594 Characteristics of integrated MOM junctions at dc ENGINE TESTS and at optical frequencies Low speed test of a high-bypass-ratio propulsion rAD-A056165] p0037 A78-28926 system with an asymmetric inlet designed for a Stimulated emission of surface plasmons by tilt-nacelle V/STOL airplane electron tunneling in metal-barrier-metal [NASA-CR-152072] pOO0g P78-17062 structures ENGINES pOO38 A78-30647 NT TURBINE ENGINES ELECTRONIC EQUIPMENT ENVIRONMENT EFFECTS NT DIODES An assessment of the effect of supersonic aircraft NT JUNCTION DIODES operations on the stratospheric ozone content ELECTRONIC LEVELS [NASA-EP-1026] pO0 2 7 N78-30774 U ELECTRONWENERGY ENVIRONMENT POLLUTION NT AIR POLLUTION
82 SUBJECT INDEX F-111 AIRCRAFT
ENVIRONMENT SIMULATION pOO1 A78-10455 NT ALTITUDE SIMULATION A preference-ordered discrete-gaming approach to NT SPICE ENVIRONMENT SIMULATION air-combat analysis NT THERMAL SIMULATION pOO20 A78-49255 ENVIRONMENT SIMULATORS EVOKED RESPONSE (PSYCHOPHYSIOLOGY) NT SPACE SIMULATORS Further investigation of the spontaneous and ENVIRONMENTAL CONTROL evoked activity of the primary neurons of Advanced instrumentation concepts for statoreceptors (and other receptors) of the environmental control subsystems labyrinth of the bullfrog before, diring and [PASA-CR--152100] " pDO53 N78-28807 after an extended period of weightlessness , ENVIRONMENTS including alternative intervals of artificial NT AEROSPACE ENVIRONMENTS gravity NT HIGH GRAVITY ENVIRONMENTS [NASA-CR-154507] p0052 N78-10684 NT INTERPLANETARY SPACE EVOLUTION (DEVELOPMENT) NT JUPITER ATMOSPERER NT ABIOGENESIS NT MAGNETOSPHERE NT CHEMICAL EVOLUTION NT MARS ATMOSPHERE NT PLANETARY EVOLUTION NT PLANETARY ATMOSPHERES NT STELLAR EVOLUTION NT PLANETARY ENVIRONMENTS EVOLUTION (LIBERATION) UT VENUS ATMOSPHERE NT GAS EVOLUTION ENZTME ACTIVITY EXCHANGING Methionine transport in Halobacterium halobium NT CHARGE EXCHANGE vesicles - Noncompetitive, asymmetric inhibition NT GAS EXCHANGE by L-Cysteine EXCITATION pOO55 A78-48579 Effects of exercise and excitement on mesenteric EQUATIONS OF NOTION and renal dynamics in conscious, unrestrained NT RULER EQUATIONS OF MOTION baboons NT NAVIER-STOKES EQUATION p0053 A78-27124 Aeromechanical stability of helicopters with a EXCITED STATES bearingless main rotor. Part 1: Equations of U EXCITATION motion EXECUTIVE AIRCRAFT 2 [NASA-TM-78459] p006 N78-18043 U GENERAL AVIATION AIRCRAFT Rotorcraft linear simulation model. Volume 1: U PASSENGER AIRCRAFT Engineering documentation EXERCISE (PHYSIOLOGY) rXASA-CR-152079-VOL-1] pOO10 N78-20136 U PHYSICAL EXERCISE EQUATIONS OF STATE EXHAUST FLOW SIMULATION Applications of algebraic geometry to systems NT FLIGHT SIMULATION theory - The McMillan degree and Kronecker EXOBIOLOGY indices of transfer functions as topological and The Viking biological experiments on Mars holomorphic systemwinvariants pOOS5 A78-39746 p0021 A78-51860 EXOSPHERE EQUIPMENT Thermal structure of the primitive ionosphere NT PERIPHERAL EQUIPMENT (COMPUTERS) p0035 A78-23543 ERGONOMICS EXPLOSIONS U HUMAN FACTORS ENGINEERING Application of high explosion cratering data to ERROR CORRECTING CODES planetary problems A decoding procedure for the Reed-Solomon codes p0044 A78-44033 [rASA-TP-12861 pO59 N78-30862 EXTRATERRESTRIAL ENVIR0NMENTS ERRORS NT INTERPLANETARY SPACE NT TRUNCATION ERRORS NT JUPITER ATMOSPHERE ESA NT MARS ATMOSPHERE U EUROPEAN SPACE AGENCY NT PLANETARY ATMOSPHERES ESRD NT PLANETARY ENVIRONMENTS U EUROPEAN SPACE AGENCY NT VENUS ATMOSPHERE ESTROGENS EXTRATERRESTRIAL LIFE Responses of articular and epiphyseal cartilage A bibliography on the search for extraterrestrial zones of developing avian radii to estrone intelligence treatment and a 2-G environment [NASA-RP-1021] pOD51 N78-21019 pOO5 A78-29562 EXTRATERRESTRIAL MATTER ETHANE NT INTERSTELLAR GAS Synthesis of multifunction triaryltrifluoroethanes EXTRATERRESTRIAL RADIATION rNASA-CASE-APC-I1O97-1] pOOL9 N78-22154 NT GALACTIC RADIATION Synthesis of mUltifunction triaryltritluoroethanes NT PLANETARY RADIATION [NASA-CAS-AC-11097-2] pOO;9 N78-22155 NT SOLAR PROTONS EUCLIDEAN GEOMETRY NT SOLAR RADIATION NT ANGLE OF ATTACK NT SOLAR WIND NT DESCRIPTIVE GEOMETRY NT SOLAR X-RAYS RT RADII HT STELLAR WINDS RULER EQUATIONS OF MOTION NT ZODIACAL LIGHT Coefficient matrices for implicit finite EXTRAVEHICULAR MOBILITY UNITS difference solution of the inviscid fluid NT ASTRONAUT LOCOMOTION conservation law equations EUROPA p003R A78-30893 F Europa - Ultraviolet emissions and the possibility F-5 AIRCRAFT of atdmic oxygen and hydrogen clouds Some observations on the mechanism of aircraft 8 p004 A78-52482 wing rock EUROPEAN SPACE AGENCY [AIAA PAPER 78-1456) p0020 A78-47907 NASA/ESA CV-990 spacelab simulation (ASSESS2 7 2) F-i5 AIRCRAFT (NASA-TM-797483 p00 N78-30149 Low speed aerodynamic characteristics of an EUROPEAN SPACE RESEARCH ORGANIZATION 0.075-scale P-15 airplane Rodel at high angles U EUROPEAN SPACE AGENCY of attack and sideslip EVAPORATIVE COOLING (NASA-TM-X-62360] pOOOI N78-10019 Study of a high performance evaporative beat F-11 AIRCRAFT transfer surface An investigation of wing buffeting response at rNASA-CR-152008] pOO28 N78-10411 subsonic and transonic speeds: Phase I. F-li A EVASIVE ACTIONS flight data analysis. Volume I: Summary of Coplanar tail-chase aerial combat as a technical approach, results and conclusions differential game [NASA-CR-152109] pOOIJ N78-33113
83 FAB (PROGRAMMING LANGUAGE) SUBJECT INDEX
An investigation of wing buffeting response at pOO60 878-33784 subsonic and transonic speeds. Phase 2: F-1liA FILLERS flight data analysis. Volume 2: Plotted power Intumescent-ablator coatings using endothermic spectra fillers rNASA-CR-152113] pOOl3 N78-33117 [NASA-CASE-ARC-11043-1] p0049 H78-27180 An investigation of wing buffeting response at FINITE DIFFERENCE THEORY subsonic and transonic speeds. Phase 2: F-1I1A On implicit finite-difference simulations -of flight data analysis. Volume 3: Tabulated three-dimensional flow power spectra (AIAA PAPER 78-10] p0033 A78-20630 (NASA-CR-152114] pOO1 4 H78-33118 Coefficient matrices for implicit finite FAB (PROGRAMMING LANGUAGE) difference solution of the inviscid fluid U FORTRAN conservation law equations FABRICATION p 0 0 3 8 A78-30893 Continued development of doped-germanium An implicit algorithm for the conservative photoconductors for astronomical observations at transonic full potential equation using an wavelengths from 30 to 120 micrometers arbitrary mesh FNASA-CR-152125] p0029 H78-22000 [AIAA PAPER 78-1113] pO43 A78-41826 FAILURE ANALYSIS Calculation of supersonic viscous flow over delta Human problem solving performance in a fault wings with sharp subsonic leading edges diagnosis task (AIAA PAPER 78-1137] p0043 A78-41841 pOO54 A78-32673 Numerical solution of two-dimensional turbulent A model of human decisionmaking in a fault blunt body flows with an impinging shock diagnosis task (AIAA PAPER 78-1209] p0045 A78-45144 p0054 A78-37130 Theoretical and experimental study of FAILURE MODES aerodynamics, heat transfer and performance of a Earth reencounter probabilities for aborted space radial turbine disposal of hazardous nuclear waste fNASA-CR-1521051 p0064 N78-19155 p0038 A78-31921 On improving the iterative convergence properties FAIRCHILD MILITARY AIRCRAFT of an implicit approximate-factorization finite U MILITARY AIRCRAFT difference algorithm --- considering transonic FASTENERS flow NT BOLTS [NASA-TM-78495] p0 0 2 6 378-26795 FEASIBILITY ANALYSIS Techniques for correcting approximate finite Toroidal tank evaluation --- propellant tanks for difference solutions --- considering transonic spin-stabilized Pioneer spacecraft flow p0032 A78-17881 [NASA-TM-78499] p00 2 6 N78-26796 Comments on 'Feasibility study of a hybrid airship FIRE POINT operating in ground effect' ALC/50/ values for some polymeric materials --- p0016 A78-24367 Apparent Lethal Concentration fire toxicity FEEDBACK CONTROL pOO4 O A78-36596 NT CASCADE CONTROL FIRE PREVENTION Demand-type gas supply system for rocket borne Fire detector response in aircraft applications thin-window proportional counters p0049 A78-53674 p0031 A78-13845 FIREPROOFING Pobustness in linear quadratic feedback design The relative fire resistance of select with application to an aircraft control problem thermoplastic materials --- for aircraft interiors 4 pOO1 A78-18059 pO0 6 A78-45475 Robustness of linear quadratic state feedback FIXED-WING AIRCRAFT designs in the presence of system uncertainty U AIRCRAFT CONFIGURATIONS --- application to Augmentor Wing Jet STOL FIXTURES Research Aircraft flare control autopilot6 design Development of a cryogenic rotating heat pipe joint - pOO1 A78-23917 [NASA-CR-152188] p0030 N78-33384 A preference-ordered discrete-gaming approach to FLAmE INTERACTION air-combat analysis U CHEMICAL REACTIONS p0O 2 0 A78-49255 FLAIE RETARDANTS FERMIOMS Fire resistivity and toxicity studies of candidate NT SOLAR PROTONS aircraft passenger seat materials FERROMAGNETISH pOO 4 8 A78-51838 Square Ising ferromagnetic and antiferromagnetic Fire resistivity and toxicity studies of candidate lattices in a.magnetic field - A new aircraft passenger seat materials perturbation approach [NASA-TM-78468] p0 0 2 4 178-21214 pOO56 A78-51886 Structural wood panels with improved fire resistance FIBER COMPOSITES --- using prepolymers and hexamethylenetetramine NT CARBON FIBER REINFORCED PLASTICS fNASA-CASE-ARC-11174-1] p0 0 5 0 178-28178 Fibrous refractory composite insulation --- FLIAMMABILITY shielding reusable spacecraft The relative fire resistance of select rNASA-CASE-ARC-11169-1] p0050 U78-32189 thermoplastic materials --- for aircraft interiors 0 0 4 6 FIBERS p A78-45475 NT REINFORCING-FIBERS Assessment of relative flammability and FIELD THEORY (PHYSICS) thermochemical properties of some thermoplastic A new concept in laser-assisted chemistry - The materials . 4 7 electronic-field representation 1 pOO A78-49693 p00 3 7 A78-27743 Fire resistivity and toxicity studies of candidate Semiclassical theory of unimolecular dissociation aircraft passenger seat materials induced by a laser field (NASA-TK-78468] p 0 0 24 N78-21214 (AD-A056671) p00 3 9 A78-34682 Aircraft cargo compartment fire test simulation FIGHTER AIRCRAFT program NT F-5 AIRCRAFT [NASA-CR-151951] p00 2 9 N78-21223 NT F-15 AIRCRAFT FLAP CONTROL NT F-111 AIRCRAFT U AIRCRAFT CONTROL NT HARRIER AIRCRAFT FLAPS (CONTROL SURFACES) Coplanar tail-chase aerial combat as a NT WING FLAPS differential game FLAT PLATES p0014 A78-10455 To-dimensional transonic testing with splitter Studies of aerodynamic technology for VSTOL plates - fighter/attack aircraft [NASA-TP-1153] p0004 B78-17999 [AIAA PAPER 78-1511] p0020 A78-47946 FLIGHT COMPUTERS FILE MAINTENANCE (COMPUTERS) U AIRBORNE/SPACEBORNE COMPUTERS 710: A FORTRAN direct access data management system
84 SUBJECT INDEX FLUID FLOW
FLIGHT CONDITIONS FLOW DISTORTION Computed responses of several aircraft to Estimating maximum instantaneous distortion from atmospheric turbulence and discrete wind shears inlet total pressure rms measurements INASA-CF-152185] p0053 V78-32106 [AIAA PAPER 78-970] pOOl9 178-43525 FLIGHT CONTROL FLOW DISTRIBUTION IT POINTING CONTROL SYSTEMS Measurements of unsteady vortex flow fields HT THRUST VECTOR CONTROL [AIAA PAPER 78-18) pOO15 A78-22554 V/STOL aircraft simulation - Requirements and Wake vortex measurements of bodies at high angle capabilities at Ames Research Center of attack (ATAA PAPER 78-1515] p0021 A78-49790 [AIAA PAPER 78-23) pOOl5 A78-22555 Optimum horizontal guidance techniques for aircraft An implicit algorithm for the conservative pOO06 N78-23016 transonic full potential equation using an FLIGHT HAZARDS arbitrary mesh 0 0 4 3 Simulation and analysis of wind shear hazard --- [hIAA PAPER 78-1113) p A78-41826 for aircraft landing and takeoff Calculation of supersonic viscous flow over delta rNASA-CR-157470] p0053 N78-29699 wings with sharp subsonic leading edges FLIGHT IXSTEUMENTS [XIAA PAPER 78-1137] pO43 A78-41841 NT AUTOMATIC PILOTS Computation of transonic flow past projectiles at FLIGHT MECHANICS angle of attack Entry dynamics performance predictions for Pioneer [AIAA PAPER 78-1182] pOO 4 k78-41875 Venus probes The spanwise lift distribution on a wing from 4 [LAIAA 78-1370] p00 6 A78-46557 flow-field velocity surveys FLIGHT ROLES [AIAR PAPER 78-1195] pOO18 &78-41886 NASA aviation safety reporting system Computation of supersonic laminar viscous flow [NASA-TN-78476] p0051 N78-25071 past a pointed cone at angle of attack in FLIGHT SAFETY spinning and coning motion NASA aviation safety reporting system (AIAA PAPER 78-1211] pOO5 A78-45139 [NASA-TM-78476] p0051 N78-25071 Status and future prospects of using numerical FLIGHT SIMULATION methods to study complex flows at High Reynolds Flight simulation - A vital and expanding numbers technology in aircraft development pOO26 H78-28410 [AIAA PAPER 7P-337] pOO16 A78-29295 FLOW FIELDS Moving ground simulation by tangential blowing U FLOW DISTRIBUTION 7 rAIAA 78-8141 pOO1 A73-32368 FLOW GEOMETRY Simulation replay - Implementation and flight Propagation of sound through a sheared flow simulation applications [NASA-CR-152196] pOOl4 178-33876 p0O18 A78-38789 FLOW HBASUREMENT Simulator evaluation of three situation and Measurements of unsteady vortex flow fields guidance displays for V/STOL aircraft-zero-zero [AIAA PAPER 78-18] pOOl5 178-22554 landing approaches Wake vortex measurements of bodies at high angle p0O55 A78-44131 of attack V/STOL aircraft simulatioa - Reguirements and EkIAA PAPER 78-23] poo1 5 A78-22555 capabilities at Ames Research Center FLOW PATTERNS rAIAA PAPER 78-1515] p0021 A78-49790 U FLOW DISTRIBUTION The determination of some requirements for a FLOW RESISTANCE helicopter flight research simulation facility NT AERODYNAMIC 0 0 6 3 DRAG (NASI-CR-152066) p N78-10117 NT SUPERSONIC DRAG ulti-calculation rate simulations FLOW SEPARATION [NASA-CH-155335] p0O09 N78-13765 U BOUNDARY LAYER SEPARATION A pilot evaluation of two G-seat cueing schemes U SEPARATED FLOW [NASA-TP-1255] p0008 N78-31739 FLOW STABILITY FLIGHT SIMULATORS The instability of the thin vortex ring of IT COCKPIT SIMULATORS constant vorticity 3 V/STOL aircraft simulation - Reguirements and pOO 1A78-14622 capabilities at Ames Research Center 0 02 FLOW THEORY rATAA PAPER 78-1515] p 1 A78-49790 lifting line theory for transonic flow Certification study of a derivative model of a p0020 A78-48991 small jet transport airplane using a piloted FLOW VELOCITY research simulator NT SOLAR WIND VELOCITY [AD-AO4HSB2] pOO61 878-14033 FLOW VISUALTZATION FLIGHT TESTS NT NUMERICAL FLOW VISUALIZATION Flight tests of a simple airborne device for Visualization of quasi-periodic unsteady flows predicting clear air turbulence encounters [AIAA 78-5021 pOO16 A78-29804 (AIAL 78-13751 pOO19 A78-46560 PLORMETEDS Engineering tests of the c-141 telescope NT HOT-WIRE PLOWMETERS [NASA-TN-78467] pO025 U78-25017 FLUID DYNAMICS Development and flight tests of a Kalman filter NT AERODYNAMICS for navigation during terminal area and landing NT ARROTHERMODYNAMICS operations NT GAS DYNAMICS 2 (NASA-CD-30151 pOO1 N78-27105 NT HYDRODYNAMICS An investigation of wing buffeting response at NT MAGNETOHYDRODYNAMICS subsonic and transonic speeds: Phase 1: P-1liA NT ROTOR AERODYNAMICS flight data analysis. Volume 1: Summary of A view toward future fluid dynamics computing technical approach, results and conclusions [A1AA PAPER 78-1112] pOO5 A78-45126 [NASA-Clt-152109] pOO13 H78-33113 FLUID FLOW An investigation of wing buffeting response at NT AIR FLOW subsonic and transonic speeds. Phase 2: F-11A NT AXISYMZETRIC FLW flight data analysis. volume 2: Plotted power NT BLOOD FLOW spectra NT BOUNDARY LAYER FLOW (NASa-CR--152113] p0013 178-33117 NT BOUNDARY LAYER SEPARATION An investigation of wing buffeting response at NT CHANNEL FLOW subsonic and transonic speeds. Phase 2: F-111A NT CONICAL FLOW flight data analysis. Volume 3: Tabulated IT CORNER FLOW power spectra NT CROSS FLOW [NISA-CR-152114] pOO14 N78-33118 NT INLET FLOW FLOW CHARACTERISTICS NT INVISCID PLOW IT FLOW DISTRIBUTION NT JET FLOW IT FLOW STABIXITY NT LAMINAR FLOW NT MAGNETOHYDRODYNAMIC FLOW
85 FLUID INJECTION SUBJECT INDEX
NT OSCILLATING FLOW FLYING PERSONNEL NT POTENTIAL FLOW NT TEST PILOTS NY RADIAL FLOW PLYING PLATFORM STABILITY NT SEPARATED FLOW U AERODYNAMIC STABILITY NT SHEAR FLOW FOAMS NT SMALL PERTURBATION FLOW Polymeric foams from cross-linkable NT SUBSONIC FLOo poly-n-arylenebenzimidazoles NT SUPFPSONIC FLOW (NASA-CASE-ARC-1IOO8-1]- pO5ON78-31232 NT THREE DIMENSIONAL FLOW- FOOD INTAKE WT TRANSONIC FLOW Food and oxygen requirements for growing mice and RT TURBULENT FLOW turtles after hypergravitational development NT TWO DIMENSIONAL FLOW pO31 A78-15204 NT UNSTEADY FLOW FORCE DISTRIBUTION NT VISCOUS FLOW Influence of spin rate on side force of an NT WALL FLOW axisymmetric body FLUID INJECTION p0038 A78-30690 Injection slot location for boundary-layer control The spanwise lift distribution on a wing from in shock-induced separation 4 4 flow-field velocity surveys rAIA PAPER 78-1168] p0O A78-41866 [AIAA PAPER 78-1195] pOOl8 178-41886 FLUID MECHANICS FORCE FIELDS NT AERODYNAMICS U FIELD THEORY (PHYSICS) NT AEROTHERMODYNAMICS FOREBODIES NT FLUID DYNAMICS HT ABLATIVE NOSE CONES NT GkS DYNAMICS NT NOSE CONES NT HYDRODYNAMICS FORECASTING RT MAGNRTOHYDRODYNAMICS NT PERFORMANCE PREDICTION NT ROTOR AERODYNAMICS NT PREDICTION ANALYSIS TECHNIQUES An experimental documentation of pressure gradient NT TECHNOLOGICAL FORECASTING and Reynolds number effects on compressible FORTRAN turbulent boundary layers Application of special-purpose digital computers fNASA-TM-78488] p0026 N78-27364 to rotorcraft real-time simulation FLUORESCENCE [NASA-TP-1267] pOO 0 7 178-27113 Illumination-dependent changes in the intrinsic X10: A FORTRAN direct access data management system fluorescence of bacteriorhodopsin p0060 U78-33784 p0055 A78-48578 FOSSIL METEORITE CRATERS Spectrophotofluorometric and electron microscopic U METEORITE CRATERS study of Lipofuscin accumulation in the testis FRAMES of aging mice NT AIEFRAMES pOg56 A78-48581 FREE OSCILLATIONS FLUORESCENT EMISSION U FREE VIBRATION U FLUORESCENCE FREE RADICALS FLUORIDES NT HYDROXYL RADICALS NT BORON FLUORIDES FREE VIBRATION NT SULFUR FLUORIDES An approximate solution for the free vibrations of FLUORINE COMPOUNDS rotating uniform cantilever beams NT BORON FLUORIDES [NASA-TM-X-62299] p0063 V78-33289 NT FLUORO COMPOUNDS FREEDOM FIGHTER AIRCRAFT NT FLUOROCARBONS U F-5 AIRCRAFT NT SULFUR FLUORIDES FREIGHT FLUORINE ORGANIC COMPOUNDS U CARGO NT FLUOROCARBONS FREIGHT COSTS FLUORO COMPOUNDS Phase 1: Definition of intercity transportation NT FLUOROCARBONS comparison framework. Volume 1: Summary -- Synthesis of multifunction triaryltrifluoroethanes operations research of passenger and freight rNASA-CASE-ARC-11097-1] p0049 N78-22154 transporatation systems Synthesis of multifunction triaryltrifluoroetbanes [NASA-CR-152152-VOL-1] pOO1 N78-28993 [NASA-CASE-AVC-11097-2] p00G9 N78-22155 Phase 1: Definition of intercity transportation FLUOROCARBONS comparison framework. Volume 2: Methodology Lower stratosphere measurements of variation with --- operations research of passenger and freight latitude of CF2Cl2, CFCI3, CCI4, and N20 transportation systems profiles in the northern hemisphere [RNASA-CR-152152-VOL-2] p0029 E78-28994 n0035 A78-23610 FREIGHTERS Stratospheric measurements of CF2CI2 and 120 Accordion shelter hardware analysis p0054 A78-37055 [AD-A0535923 pO007 N78-28278 Interhemispheric gradients of CF2Cl2t CFCI3, CCI, FREQUENCIES and N20 NT BROADBAND pOO'2 A78-41124 NT RESONANT FREQUENCIES FLUOROMICA FREQUENCY RESPONSE U MICA New frequency domain methods for system FLUTTER identification NT TRANSONIC FLUTTER pOOl5 A78-23883, FLUTTER ANALYSIS G-seat system step input and sinusoidal response Notes on the transonic indicial method --- for two characteristics dimensional airfoil flutter derivative calculation [NASA-TM-78'78] pOO07 78-26741 pOol A78-37732 FRICTION FLUX (RATE PER UNIT AREA) NT AERODYNAMIC DRAG U FLUX DENSITY NT SUPERSONIC DRAG FLUX DENSITY FRICTION DRAG NT ELECTRON FLUX DENSITY NT AERODYNAMIC DRAG NT RADIANT FLUX DENSITY NT SUPERSONIC DRAG An investigation of wing buffeting response at FUEL CONSUMPTION subsonic and transonic speeds. Phase 2: F-111A Fuel saving potential of Mach 0.8 twin engine flight data analysis. Volume 2: Plotted power prop-fan transports spectra pOO1 7 A78-31306 [NASX-CR-152113] p0013 N78-33117 Fuel conservation merits of advanced turboprop FLUX MAPPING transport aircraft U FLUX DENSITY [NASA-CR-152096] pO0O W78-21095 FLUXMETERS FUELS U MAGNETIC MEASUREMENT ST AIRCRAFT FUELS
86 SUBJECT INDEX GASES
NT LIQUID ROCKET PROPELLANTS translational temperatures of O/2 Pi/ in a gas FUNCTIONAL ANALYSIS discharge NT INTEGRAL EQUATIONS pOO30 A78-10405 FUNCTIONS (MATREMATICS) GAS DISSOCIATION NT BOOLEAN FUNCTIONS Collisionless dissociation of SF6 using two NT LINEAR TRANSFORMATIONS resonant frequency C02 laser fields NT PERIODIC FUNCTIONS pOf31 A78-14655 NT RECURSIVE FUNCTIONS GAS DYNAMICS NT TRANSFER FUNCTIONS NT AERODYNAMICS UT WEIGHTING FUNCTIONS NT AEROTNERMODYNAMICS FUSIFORM SHAPES NT ROTOR AERODYNAMICS U CONES Thermodynamic processes induced by coherent radiation pOOR34 A78-21624 G Lagrangian computation of inviscid compressible G FORCE flows 5 U ACCELERATION (PHYSICS) [NASA-TM-78456] p002 N78-24860 GALACTIC NUCLEI GAS EVOLUTION ISAs and the dwarf content of the inner nuclear Nitric oxide production by Tunguska meteor regions of M31 --- Intrinsic Strength Anomalies 0 0 pOOQ8 A78-51811 p 42 A78-38569 GAS EXCHANGE GALACTIC RADIATION The Viking biological experiments on Mars Quiet time interplanetary cosmic ray anisotropies pOD5 5 A78-39746 observed from Pioneer 10 and 11 GAS PLOW p0039 A78-34567 NT AIR FLOW GALACTIC ROTATION GAS GIANT PLANETS Evolution of rotating interstellar clouds. III - NT JUPITER (PLANET) On the formation of multiple star systems NT URANUS (PLANET) 7 pOO4 A78-49471 GAS HEATING GALACTIC STRUCTURE Nova-driven winds in globular clusters Bar-driven spiral wves in disk galaxies p004l A78-37649 pO038 A78-32467 GAS IONIZATION Numerical experiments on the stability of disklike Low energy ionizing collisions between N2 and CO galaxies beam molecules and CO, N2, NO, CHU, and C02 pOO19 A78-45535 target molecules On the stability of disklike galaxies in massive p0039 A78-34137 halos LASERS 2 GAS pO0 O A78-47354 NT CARBON DIOXIDE LASERS GALAXIES Computational study of a molecular collision NT ANDROMEDA GALAXIES process in the presence of an intense radiation GALERKIN METHOD field - Enhanced quenching of F by Xe in the An integral solution to a nonlinear diffusion 248-nm light of the KrF laser problem (AD-AO54078) p0044 7 A78-42818 p003 A78-26350 -System optimization of gasdynamic lasers, computer Numerical solution of a class of integral program user's manual equations arising in two-dimensional aerodynamics (NASA-TM-73193] p0027 N78-29436 pOOlS A78-40949 GAS LIQUEFACTION GALILEAN SATELLITES U CONDENSING NT EUROPA GAS MIXTURES NT 10 NT DETONABLE GAS MIXTURES GALVANIC CELLS GAS PRESSURE U ELECTROLYTIC CELIS Demand-type gas supply system for rocket borne GAME THEORY thin-window proportional counters Coplanar tail-cLase aerial combat as a p0031 A78-13845 diffetential game GAS TURBINES pOo1 A78-10455 Theoretical and experimental study of A preference-ordered discrete-gaming approach to aerodynamics, heat transfer and performance of a air-combat analysis radial turbine p0020 A78-49255 [NASA-CR-152105] p0064 N78-19155 GAMMA RADIATION GAS-GAS INTERACTIONS U GAMMA RAYS Low energy ionizing collisions between N2 and CO GAMMA RAYS beam molecules and CO. N2, NO, CR4, and C02 Degradation of biochemical activity in soil target molecules sterilized by dry heat and gamma radiation p039 A78-34137 p0057 A78-53874 GAS-METALJINTERACTIONS GANGLIA The co-adsorption of copper and oxygen on a NT NEURONS tungsten 100 plane-type surface GARMENTS p0037 A78-29489 Spacesuit torso closure Hydrogen attack - Influence of hydrogen sulfide [rASA-CASE-ARC-11100-1] pON58 N78-31736 --- on carbon steel GAS ANALYSIS p0044 A78-44108 NT OZONOMETRY GAS-SOLID INTERACTIONS GAS CHROMATOGRAPHY NT GAS-METAL INTERACTIONS Interhemispheric gradients of CF2C12, CFCA3. CC14, GASES and N20 NT CARBON DIOXIDE pOO2 A78-41124 NT CARBON MONOXIDE Synthesis of porous polyaromatic column packings NT CARBON SUBOXIDES for GC analysis of extraterrestrial atmospheres 3T DETONABLE GAS MIXTURES p0055 A78-48577 NT HYDROGEN Chelate-modified polymers for atmospheric gas NT INTERSTELLAR GAS chromatography NT MOLECULAR GASES rHNASA-CASE-ARC-11154-1] p0057 N78-27275 HT NITROGEN GAS COMPOSITION NT NITROGEN IONS NT CARBON DIOXIDE CONCENTRATION NT NONCONDENSABLE GASES GAS DETECTORS NT OXYGEN Fire detector response in aircraft applications NT OXYGEN ATOMS pO049 A78-53674 NT OXYGEN IONS GAS DISCHARGES NT OZONE simultaneous determination of rotational and
87 GENERAL AVIATION AIRCRAFT SUBJECT INDEX
GENERAL AVIATION AIRCRAFT turtles after hypergravitational development Advanced Digital Avionics System for general p0031 A78-15204 aviation 1 4 Gravity as a biochemical determinant [AIAA 77-1494] p0O A78-12243 pOO56 178-48671 A historical overview of stall/spin G-seat system step input and sinusoidal response characteristics of general aviation aircraft characteristics [lIAA PAPER 78-1551] pOOI9 A78-46514 [WASA-Th-78478] pOO07 W78-26741 Integrated avionics for future general aviation GROOVES aircraft A re-entrant groove hydrogen heat pipe 2 [AlAA PAPER 78-1482) pO0 O A78-47927 [AIAA 78-420] p0040 A78-35603 Certification study of a derivative model of a GROUND BASED CONTROL small jet transport airplane using a piloted NT AIR TRAFFIC CONTROL research simulator GROUND EFFECT (AERODYNAHICS) [AD-A046442] p0061 M78-14033 Measured wake-vortex characteristics of aircraft A study of commuter airplane design optimization in ground effect rNASA-CR-157210] pO011 N78-25078 [AA PAPER 78-109] pOOl5 A78-22578 GENERAL DYNAMICS AIRCRAFT Comments on 'Feasibility study of a hybrid airship NT CV-990 AIRCRAFT operating in ground effect' HT F-111 AIRCRAFT pOOl6 178-24367 GENERAL DYNAMICS MILITARY AIRCRAFT Moving ground simulation by tangential blowing U MILITARY AIRCRAFT [AIAA 78-814] pOOl7 A78-32368 GENITOURINARY SYSTEM GROUP BEHAVIOR NT TESTES U GROUP DYNAMICS GEOCREMISTRY GROUP DYNAMICS Light element geochemistry of the Apollo 12 site Critical review of Ames Life Science participation pOO054 A78-34503, in Spacelab Mission Development Test 3: The SMD GEOLOGY 3 management study NT VOLCANOLOGY (NASA-TM-78494] P0051 N78-26973 Abstracts for the Planetary Geology Field GROWTH Conference on Aeolian Processes Food and oxygen requirements for growing mice and 2 r.NASA-TN-784551 p002 N78-13492 turtles after hypergravitational development GEOMAGNETIC EFFECTS p0031 A78-15204 U MAGNETIC EFFECTS Responses of articular and epiphyseal cartilage GEOMAGNETIC FIELD zones of developing avian radii to estrone 0 GEOMAGETISM treatment and a 2-G environment GEOMAGNETISK pOO54 A78-29562 On the apparent source depth of planetary magnetic GRUMMAN AIRCRAFT fields NT F-111 AIRCRAFT p0037 A78-29472 GUIDANCE (NOTION) GEOMETRICAL HYDROAGNETICS Optimum horizontal guidance techniques for aircraft U MAGNETOHYDRODYNAMICS pOO06 N78-23016 GEOMETRY GUIDE VANES NT ANGLE OF ATTACK Use of leaning vanes in a two stage fan NT DESCRIPTIVE GEOMETRY [NASA-CR-152134] p010 N78-21115 UT DIFFERENTIAL GEOMETRY GYMNASTICS NT FLOP GEOMETRY U PHYSICAL EXERCISE NT RADII GYRATION NT TANK GEOMETRY NT AUTOROTATION NT VORTICITY NT MOLECULAR ROTATION GEON (TRADEMARK) NT SATELLITE ROTATION U POLYVINYL CHLORIDE NT SOLAR ROTATION GERMANIUM COMPOUNDS GYROPLANES Continued development of doped-germanium U HELICOPTERS photoconductors for astronomical observations at wavelengths from 30 to 120 micrometers H rNASA-CR-152125] p0029 N78-22000 GIANT STARS HABITATS NT CARBON STARS Space habitats --- prognosis for space colonization GLANDS (ANATOMY) pO56 A78-49780 NT ADRENAL GLAND HALIDES NT TESTES NT BORON FLUORIDES GLASS NT SULFUR FLUORIDES Peaction cured glass and glass coatings HALOCARBONS fNASA-CASE-ARC-11051-1] p0O50 78-32260 NT CHLOROCARBONS GLAUERT COEFFICIENT NT FLUOROCARBONS U AERODYNAMIC FORCES Meteorological control of lower stratospheric GLOBULAR CLUSTERS minor species variations - An observational Nova-driven winds in globular clusters example pO001 A78-37649 pOO19 A78-46011 GLOW DISCHARGES HALOGEN COMPOUNDS Boron trifluoride coatings for thermoplastic NT BORON FLUORIDES materials and method of applying same in glow NT CHLORINE OXIDES discharge NT FLUORO COMPOUNDS rNASA-CASE-ARC-11057-1] pOO57 N78-31233 NT FLUOROCARBONS GOVERNMENT/INDUSTRY RELATIONS NT HALOCARRONS Who should conduct aeronautical R and D for the NT SULFUR FLUORIDES Federal Government? HALOPHILES 0 1 rNASA-CR-152021] pOO 78-10946 Calcium transport in Halobacterium halobium GRADIENTS envelope vesicles NT PRESSURE GRADIENTS p0055 A78-48574 NT TEMPERATURE GRADIENTS HALOS GRAPHITE On the stability of disklike galaxies in massive NT PYROLYTIC GRAPHITE halos 2 GRAPHITE-EPOXY COMPOSITE MATERIALS p0O O A78-47354 Simple torsion test for shear moduli determination HANDBOOKS of orthotropic composites NT USER MANUALS (COMPUTER PROGRAMS) [NASA-TM-78485] p0024 N78-21490 HARMONIC OSCILLATION GRAVITATIONAL EFFECTS Calculation of unsteady transonic flows using the Food and oxygen requirements for growing mice and integral eguation method
88 SUBJECT INDEX HIGH GRAVITY (ACCELERATION)
[FAIAA PAPER 78-13] p0033 A78-20632 radial turbine A note on multicyclic control by swashplate [NASA-CR-152105] pO064 U78-19155 oscillation HEAT TRAINSMISSION [FIASA-TM-78475] pOOOS5 N78-21159 NT CONDUCTIVE HEAT TRANSFER HARMONICS NT CONVECTIVE HEAT TRANSFER NT HARMONIC OSCILLATION NT HEAT TRANSFER HARNESSES NT LAMINAE BEAT TRANSFER CV 990 interface test and procedure analysis of NT RADIATIVE HEAT TRANSFER the monkey restraint, support equipment, and BEATING telemetry electronics proposed for Spacelab NT GAS HEATING [NASA-TM-78484 p0051 U78-27736 NT PLASMA HEATING HARRIER AIRCRAFT Extended development of variable conductance heat Conceptual design study of a Harrier V/STOL pipes research aircraft [NASA-CE-1521833 pOO29 N78-33379 (NASA-CR-152086] pOOS9 N78-19094 HELICOPTER ATTITUDE INDICATORS HAWKER SIDDELEY AIRCRAFT U HELICOPTERS NT HARRIER AIRCRAFT HELICOPTER DESIGN HAZARDS Theoretical study of multicyclic control of a NT AIRCRAFT HAZARDS controllable twist rotor NT. FLIGHT HA7ARDS [NASA-CE-151959] p0064 NIB-3385 NT RADIATION HAZARDS HELICOPTER PERFORMANCE NT TOXIC HAZARDS Aeromechanical stability of helicopters with a HEAD-UP DISPLAYS bearingless main rotor. Part 1: Equations of Project plan for joint FAA/NASA head-up display motion 2 concept evaluation [NASA-T-78459] pOO6 N78-18043 rNASA-T-78512] p0052 N78-28979 A simple method for estimating minimum HEART autorotative descent rate of single rotor NT CARDIAC VENTRICLES helicopters NT MYOCARDIUM [NASA-T-784523 pOO05 N78-20113 HEART RITE An experimental investigation of hingeless rotor-body stability in hover Extent of utilization of the Frank-Starling helicopter 3 mechanism in conscious dogs --- preload effects [NASA-T-78489] pO06 N78-29044 on myocardial regulation HELICOPTER ROTORS p0054 A78-33522 U ROTARY RINGS HEAT HELICOPTERS NT DRY HEAT NT MILITARY HELICOPTERS HEAT CONDUCTION A simplified Mach number scaling law for U CONDUCTIVE BEAT TRANSFER helicopter rotor noise HEAT EFFECTS pOO17 A78-35371 U TEnPERATURE EFFECTS The determination of some requirements for a research simulation facility HEAT EQUATIONS helicopter flight 3 U THERMODYNAMICS (NASA-CR-152066J pOO6 N78-10117 HEAT GAIN Optimal control theory (OWEM) applied to a U HEATIG helicopter in the hover and approach phase' HEAT PIPES [NASA-CR-152135] pOOlO N78-21161 Investigation of a cryogenic thermal diode The effect of tip vortex structure on helicopter rAIAA 78-417] p0040 A78-35601 noise due to blade/vortex interaction 2 A re-entrant groove hydrogen heat pipe (NASA-CR-152150] pOO1 N78-25832 [ATAA 78-420] p0040 A78-35603 Hovering impulsive noise: Some measured and Jet pump assisted arterial heat pipe calculated results 3 [AIAA 78-443] pOOO A78-35622 pOO6 978-32831 Experimental temperature distribution and heat A study of the noise radiation from four load characteristics of rotating heat pipes helicopter rotor blades --- tests in Ames 10 by p0046 A78-48835 20 foot wind tunnel HEAT EGULATION pOS8 N78-32835 U TEMPERATURE CONTROL RELIOGRAPHS HEAT RESISTANCE U SPECTROHELIOGRAPHS U THERMAL RESISTANCE HELIOGRAPHY HEAT SHIELDING U SPECTROHELIOGRAPHS NT REENTRY SHIELDING HELIOMAGNETISM Aerothermodynamic environment for Jovian entry U SOLAR MAGNETIC FIELD with silica heat shield HELIUM HYDROGEN ATMOSPHERES [AIAA PAPER 78-186] p0033 A78-20730 Carbonaceous materials subjected to extreme The response of heat-shield materials to intense heating - A comparison of numerical simulation laser radiation and experiments --- Jovian entry conditions rAIAA PAPER 78-138] p0034 A78-22583 [AIAA PAPER 78-866] p0041 A78-37273 Shock-tube studies of atomic silicon emission in HEMODYNAMIC RESPONSES the spectral range 180 to 300 em --- environment Effects of exercise and excitement on mesenteric simulation for Jupiter probes and renal dynamics in conscious, unrestrained [AIAA PAPER 78-234] p0034 A78-22602 baboons p053 A78-27124 Jupiter probe heatshield configuration 0 0optimization 4 1 FAIAA PAPER 78-843] p A78-37270 HEXADIENE Carbonaceous materials subjected to extreme Thermal rearrangements in 1,2-poly/1,4-hexadiene/s heating - A comparison of numerical simulation pOO48 A78-51870 and experiments --- Jovian entry conditions HEXAMETHYLENETETRAMINE [AIAA PAPER 78-866] pO041 A78-37273 Structural wood panels with improved fire resistance Carbon vaporization into a nonegQilibrium, --- using prepolymers and hexamethylenetetramine stagnation-point boundary layer [NASA-CSE-ARC-1117'-1 pOSO 78-28178 p0042 A78-40838 HIGH ALTITUDE HEAT TRANSFER High altitude perspective --- cost-reimbursable NT CONDUCTIVE HEAT TRANSFER services using NASA U-2 aircraft NT CONVECTIVE HEAT TRANSFER [NASA-SP-427] p0027 N78-31508 NT LAMINAR HEAT TRANSFER HIGH ALTITUDE FLIGHT NT RADIATIVE HEAT TRANSFER U HIGH ALTITUDE Experimental temperature distribution and heat HIGH ASPECT RATIO WINGS load characteristics of rotating beat pipes U SLENDER WINGS pOO46 A78-48835 HIGH GRAVITY (ACCELERATION) Theoretical and experimental study of U HIGH GRAVITY ENVIRONMENTS aerodynamics, heat transfer and performance of a
89 HIGH GRAVITY ENVIRONMENTS SUBJECT INDEX
HIGH GRAVITY ENVIRONMENTS and the definition of a flight program to Food and oxygen requirements for growing mice and determine neighborhood reactions to small turtles after hypergravitational development transport aircraft p0031 A78-15204 [rASA-CR-1521511 pOO13 N78-30070 Responses of articular and epiphyseal cartilage HUMAN TOLERANCES zones of developing avian radii to estrone Hormonal indices of tolerance to +Gz acceleration treatment and a 2-G environment in female subjects --- personnel selection in pOOS4 A78-29562 Shuttle program HIGH BELTING COMPOUNDS p0055 A78-41162 ' REFRACTORY MATERIALS HUMAN WASTES HIGH PRESSURE NT SWEAT use of leaning vanes in a two stage fan HYDRAULIC TEST TUNNELS [RASA-CR-152134) pOO10 N78-21115 Water-tunnel experiments on an oscillating airfoil HIGH TEMPERATURE MATERIALS at RE equals 21,000 U REFRACTORY MATERIALS (NASA-TM-784'46 pOO62 H78-19058 HILLER MILITARY AIRCRAFT HYDRIDES U MILITARY AIRCRAFT NT LITHIUM HYDRIDES HINGE MOMENTS HYDROAEROMECHANICS U TORQUE U AERODYNAMICS RNGED ROTOR RLADES HYDROCARBONS U ROTARY RINGS UT CYCLIC HYDROCARBONS HIRGELESS ROTORS NT ETHANE U RIGID ROTORS HT HEXADIENE HISTOLOGY HYDRODYNAMIC STABILITY Responses of articular and epiphyseal cartilage U FLOW STABILITY zones of developing avian radii to estrone HYDRODYNAMICS treatment and a 2-G environment NT MAGNETOHYDRODYNAMICS pO054 A78-29562 Bar-driven spiral waves in disk galaxies HOMEOSTASIS p0038 A78-32467 Inhibition of bone formation during space flight HYDROGEN p0056 A78-51225 A re-entrant groove hydrogen heat pipe HORMONES (AIAA 78-4201 pOO4o A78-35603 NT ESTROGENS HYDROGEN CLOUDS Hormonal indices of tolerance to +Gz acceleration Europa - Ultraviolet emissions and the possibility in female subjects --- personnel selection in of atomic oxygen and hydrogen clouds shuttle proqram p0048 A78-52482 p0055 A78-41162 HYDROGEN COMPOUNDS HOT JETS NT HYDROGEN SULFIDE U JET FLOW NT LITHIUM HYDRIDES HOT STARS HYDROGEN EMBRITTLEMEET NT B STARS Hydrogen attack - Influence of hydrogen sulfide HOT-WIRE ANEMOMETERS --- on carbon steel Hot-wire, laser anemometer and force balance p0044 A78-44108 measurements of cross-sectional planes of single HYDROGEN SULFIDE and interacting trailing vortices Hydrogen attack - Influence of hydrogen sulfide rAIAA PAPER 78-1194] pOOl8 A78-41885 --- on carbon steel HOTWIRE FLOWMETERS pOO04 A78-44108 Buried wire gage for wall shear stress measurements HYDROEAGETIC FLOW [AIAA 78-798] p0017 A78-32353 U MAGNETOHYDRODYNAMIC FLOW HBOT-WIRE TURBULENCE METERS HYDROEAGETICS U HOT-WIRE FLOWMETERS U MAGNETOHYDRODYAMICS HOVERING HYDROMAGNETISH Hovering impulsive noise: Some measured and U MAGNETOHYDRODTEAMICS calculated results HRDROMECHAWICS p0063 N78-32831 NT HYDRODYNAMICS HOVERING STABILITY NT MAGETOHYDRODYNAMICS Optimal control theory (OWEM) applied to a HYDROXYL EMISSION helicopter in the hover and approach phase Simultaneous determination of rotational and [NASA-CR-152135] pOOl0 N78-21161 translational temperatures of OH/2 Pi/ in a gas An experimental investigation of hingeless discharge helicopter rotor-body stability in hover pOO3O A78-10405 [NASA-TM-784891 p0O63 N78-29044 HYDROXYL RADICALS HUGHES MILITARY AIRCRAFT Absorption measurements of OR using a CW tunable U MILITARY AIRCRAFT laser HUMAN BODY p0032 A78-17837 Sweat collection capsule HYPERSONIC REENTRY (NASA-CASE-ARC-11031-1] p057 N78-22720 Navier-Stokes calculations for laminar and HUMAN ENGINEERING turbulent hypersonic flow over indented nosetips U HUMAN FACTORS ENGINEERING (AIAA PAPER 78-260] p0035 A78-22608 HUMAN FACTORS ENGINEERING HYPERTORIA Infrastructure dynamics: A selected bibliography U OSMOSIS [HASA-CF-152162 I p0012 R78-25824 HYPERTROPHY Spacesuit mobility joints -U GROWTH fNASA-CASE-ARC-11058-1] pOO58 N78-31735 HYPERVELOCITY CRATERING Spacesuit torso closure U PROJECTILE CRATERING FNASA-CASE-ARC-11100-1 p0058 N78-31736 HYPOTHESES NASA aviation safety reporting system NT LAGRANGE SIMILARITY HYPOTHESIS rHASA-TM-78511] p0052 N78-32075 HUMAN PERFORMANCE I NT ASTRONAUT PERFORMARCE NT OPERATOR PERFORMANCE ICBM (MISSILES) Human problem solving performance in a fault U INTERCONTINENTAL BALLISTIC MISSILES diagnosis task ILLIAC COMPUTERS p0054 A78-32673 The ILLIAC IV memory system: Current status and A model of human decisionmaking in a fault future possibilities diagnosis task [RASA-CR-152177] p0060 978-32731 t p0OS A78-37130 ILLUMINATION HUMAN REACTIONS Illumination-dependent changes in the intrinsic Requirements for regional short-haul air service fluorescence of bacteriorhodopsin
90 SUBJECT INDEX IRTERPLAYETARY DUST
pOO55 A78-48578 INPRARED RADIOMETERS IMAGE PROCESSIEG Flight tests of a simple airborne device for Survey of adaptive image coding techniques predicting clear air turbulence encounters pOO31 A78-15267 [AIAA 78-1375] pOO1S A78-46560 IMAGERY INFRARED SPECTRA NT AERIAL PHOTOGRAPHY Comments on the note by Arie et al. on the NT ASTRONOMICAL PHOTOGRAPHY transition moment of the C02 band near 7740 NT INFRARED IMAGERY kaysers NT LUNAR PHOTOGRAPHY pOO48 A78-52388 NT SCHLIEREN PHOTOGRAPHY INFRARED SPECTROSCOPY NT SPACEBORNE PHOTOGRAPHY Comparison between infrared Martian disk spectra MT SPECTEOHELIOGRAPHS and optical properties of terrestrial analogs IMAGING TECHNIQUES pOO47 A78-49231 The Pioneer 11 imaging experiment of Jupiter2 INITIAL VALUE PROBLEMS pOD3 X78-18173 U BOUNDARY VALUE PROBLEMS IMIDES INJECTION Catalysts for imide formation from aromatic NT FLUID IFJECTION isocyanates and aromatic dianhydrides INLET FLOW rNASA-CASE-ARC-11107-1] p0049 N78-22156 Stress analysis study in cooled radial inflow IMPACT DAbAGE turbine Application of high explosion cratering data to [AIAA PAPER 78-943 pOO64 A78-22570 planetary problems Estimating maximum instantaneous distortion from p0044 A78-44033 inlet total pressure rms measurements IMPELLER BLADES (AIlA PAPER 78-970] pO019 A78-43525 U ROTOR BLADES (TURBOMACHINERY) ISLET PRESSURE IMPLANTED ELECTRODES (BIOLOGY) Estimating maximum instantaneous distortion from CV 990 interface test and procedure analysis of inlet total pressure rns measurements the monkey restraint, support equipment, and (AIAA PAPER 78-970] pOOlS A78-43525 telemetry electronics proposed for Spacelab INLETS (DEVICES) [NASA-TN-78484] pO051 R78-27736 U INTAKE SYSTEMS TMPULSE GENERATORS IFORGANIC COATINGS Comparison of measured and calculated helicopter NT CERAMIC COATINGS rotor impulsive noise --- wind tunnel test data Boron trifluoride coatings for thermoplastic and prediction analysis techniques materials and method of applying same in glow [NASA-TM-78473J pOOO5 N78-20917 discharge INDICATING INSTRUMENTS [NASA-CASE-ARC-11057-1] pO857 E78-31233 NT HOT-WIRE ANEBOMETERS INORGANIC SULPIDES INDIUM ANTIMONIDES -ET HYDROGEN SULFIDE Optimizing indium antimonide (InSb) detectors for INSTRUCTIONS low background operation --- infrared0 0astronomy 2 8 U EDUCATION (NASA-T-732731 p N78-32947 INSTRUMENTAL ANALYSIS INDIUM COMPOUNDS U AUTOMATION NT INDIUM ANTIMONIDES INSTRUMEETATION INDUCTANCE U INSTRUMENTS An inductively powered telemetry system for INSTRUMENTS temperature, EKG, and activity monitoring Rotary leveling base platform (NASA-TM-78486] pOO59 N78-23706 [NASA-CASE-AUC-10981-1] pO60 N78-27425 INDUCTION SYSTEMS Advanced instrumentation concepts for U INTAUE SYSTEMS environmental control subsystems INELASTIC BODIES [NASA-CR-152100] pOO53 B78-28807 U RIGID STRUCTURES INSULATIOS INERTIA 9OrENTS NT THERMAL INSULATION U MOMENTS OF INERTIA INTAKE SYSTEMS INFLUENCE COEFPICIENT NT ENGINE INLETS Advanced panel-type influence coefficient methods High angle of incidence implications upon air applied to unsteady three dimensional potential intake design and location for supersonic cruise flows aircraft 2 and highly maneuverable transonic rAIAA PAPER 78-229) p08 1 A78-52630 aircraft INFRARED ASTRONOMY [VASA-TM-78530] pOOD8 078-32044 Airborne photometric observations between 1.25 and INTEGRAL EQUATIONS 3.25 microns of late-type stars Calculation of unsteady transonic flows using the p0036 A78-25295 integral equation method C3 and infrared spectrophotometry of Y Canum (AIA PAPER 78-13] pOO33 A78-20632 Venaticorum Numerical solution of a class of integral 2 p04 178-39448 equations arising in two-dimensional aerodynamics Infrared excesses in early-type stars - Gamma pOOlS A78-40949 Cassiopeiae Solution of transonic flows by an 4 7 p00 A78-49475 integro-differential equation method Continued development of doped-germanium [NASA-TM-78490] pO026 N78-26391 photoconductors for astronomical observations at INTEGRATED CIRCUITS wavelengths from 30 to 120 micrometers Characteristics of integrated MOMjunctions at do [NASA-CR-152125] p0029 N78-22000 and at optical frequencies Optimizing indium antimonide (InSb) detectors for [AD-A056165] p0037 A78-28926 low background operation --- infrared astronomy INTEGEODIFFXRENTIAL EQUATIONS (NASA-TM-3273] p0028 N78-32947 U DIFFERENTIAL EQUATIONS INFRARED DETECTORS U INTEGRAL EQUATIONS Optimizing indium antimonide (InSb) detectors for INTERACTIVE GRAPHICS low background operation --- infrared astronomy U COMPUTER GRAPHICS 00 2 8 rHASA-T-73273) p N78-32947 INTERCEPTOR AIRCRAFT INFRARED IMAGERY U FIGHTER AIRCEAFT Engineering tests of the C-141 telescope INTERCONTINENTAL BALLISTIC MISSILES ENASA-T-78467] pOCUS N78-25017 High performance dash-on-warning air mobile INFRARED INSTRUMENTS missile system --- first strike avoidance for NT INFRARED DETECTORS retaliatory aircraft-borne ICBM counterattack NT INFRARED INTERTEROMETERS [(AIA 78-1353] pOOlS A78-46545 INFRARED INTERFEROMETERS INTERFEROMETERS Airborne infrared interferometric observations and NT INFRARED INTERFEROlETERS analysis of stratospheric trace constituents INTERPLAUETAR! DUST [kIAA PAPER 78-252] pG034 A78-22606 Radiation pressure and Poynting-Hobertson drag for
91 INTERPLANETARY MAGNETIC FIELDS SUBJECT INDEI
small spherical particles --- in interplanetary IONIZING RADIATION space NT ALPHA PARTICLES p0033 A78-19768 NT COSMIC RAYS Zodiacal light as an indicator of interplanetary NT GAMMA RAYS dust NT SOLAR X-RAYS p0O 4 2 A78-38228 IONOSPHERIC COMPOSITION Are the stratospheric dust particles meteor A comprehensive model of the Venus ionosphere ablation debris or interplanetary dust? p 0 0 38 A78-30071 [NASA-TH-78507] p0028 178-34014 The ionosphere and airglow of Venus - Prospects Meteor ablation spheres from deep-sea sediments for Pioneer Venus 0 0 [NASA-TM-78510] pO020 N78-34021 p 45 A78-4773 INTERPLANETARY MAGNETIC FIELDS IONOSPHERIC ELECTRON DENSITY .The interplanetary modulation and transport of Thermal structure of the primitive ionosphere Jovian electrons pOO35 A78-23543 p0036 A78-26080 IONOSPHERIC NOISE The spiral field inhibition of thermal conduction NT WHISTLERS in two-fluid solar wind models IONOSPHEBIC TEMPERATURE p0046 A78-48281 Thermal structure of the primitive ionosphere The radial dependences of the interplanetary p0 0 3 5 A78-23543 magnetic field between I and 5 AU Pioneer 10 IONS p0048 A78-52504 NT NITROGEN IONS INTERPLANETARY MEDIUM NT OXYGEN IONS NT INTERPLANETARY DUST NT SOLAR PROTONS Energetic protons associated with interplanetary IP (IMPACT PREDICTION) active regions 1-5 AU from the sun U COMPUTERIZED SIMUIATION pOO36 178-26031 IRON INTERPLANETARY SPACE Controlled vapor growth of small particles of Pd Acceleration of nucleons in the interplanetary and Fe on thin A1203 substrates space and the modulation of Jupiter electrons in p0044 A78-43384 the interval from 1 to 10 A.U. by corotating IRON AllOyS regions of solar origin NT AUSTEITIC STAINLESS STEELS pO037 A78-29684 NT CARBON STEELS Quiet time interplanetary cosmic ray anisotropies IRON METEORITES observed from Pioneer 10 and 11 Analysis of ablation debris from natural and p0039 A78-34567 artificial iron meteorites INTERPLANETARY SPACECRAFT pO039 A78-34506 NT JUPITER PROBES IRRITATION NT PIONEER SPACE PROBES NT TOXICITY AND SAFETY HAZARD NT PIONEER VENUS SPACECRAFT IRROTATIONAl FLOW NT PIONEER 10 SPACE PROBE U POTENTIAL FLOW NT VENUS PROBES SING RoDEL NT VIKING LANDER SPACECRAFT U FERROMAGNETISM NT VIKING LANDER 1 U MATHEMATICAL MODELS NT VIKING ORBITER SPACECRAFT ITERATION INTERSTELLAR GAS NT ITERATIVE SOLUTION Nova-driven winds in globular clusters ITERATIVE SOLUTION pO041 A78-37649 On improving the iterative convergence properties INTEBSTELLAR MATTER of an implicit approximate-fectorization finite Evolution of rotating interstellar clouds. III - difference algorithm --- considering transonic On the formation of multiple star systems flow 0 2 6 pOOl7 A78-49471 [NASA-TM-78495] p0 N78-26795 INVESTMENTS A technology assessment of transportation system J investments --- Markovian decision theory [NASA-CR-152154-2] pO013 N78-28989 JEEPS INVISCID FLOW U AUTOMOBILES Lagrangian computation. of inviscid compressible JET AIRCRAFT flows NT CV-990 AIRCRAFT rNASA-TM-78456] p0025 N78-24860 NT F-5 AIRCRAFT TO NT F-15 AIRCRAFT On determining magnetospheric diffusion NT F-111 AIRCRAFT coefficients from the observed effects of NT TURBOPROP AIRCRAFT Jupiter's satellite Io NT U-2 AIRCRAFT pO032 A78-18732 Certification study of a derivative model of a On the modulation of the Jovian decametric small jet transport airplane using a piloted radiation by 10. I - Acceleration of charged research simulator particles [AD-A046442] p00 61 N78-14033 p0042 A78-41074 Factors affecting the retirement of commercial IONIZATION transport jet aircraft NT GAS IONIZATION [NASA-CR-152115] pO10O N78-21092 Quantum mechanical theory of collisional CT 990 interface test and procedure analysis of ionization in the presence of intense laser the monkey restraint, support equipment, and radiation telemetry electronics proposed for Spacelab rAD-A052981] pO035 A78-23576 [NASA-T-78484] p00 5 1 N78-27736 IONIZATION CHAMBERS Project plaf for joint FAA/NASA head-up display NT PROPORTIONAL COUNTERS concept evaluation IONIZATION CROSS SECTIONS [NASA-TM-78512] p0052 N78-28979 Low energy ionizing collisions between N2 and CO JET AIRCRAFT NOISE beam molecules and CO, N2, NO, CHR, and C02 Analysis of flight effects on noise radiation from target molecules jet flow using a convecting quadrupole model pOO39 A78-34137 [AIAA PAPER 78-192] pOO15 A78-22594 IONIZATION POTENTIALS Propagation of sound through a sheared flow An investigation of the reduction of carbon [NASA-CR-152196] pOO1 N78-33876 -dioxide in a silent electric discharge JET LUGMENTED WING FLAPS [NASA-CR-152146] pO053 N78-25767 U WING FLAPS IONIZED GASES JET FLAMES NT CESIUM PLASMA U JET FLOW NT SOLAR WIND JET FLIGHT NT STELLAR WINDS U JET AIRCRAFT
92 SUBJECT INDEX LASER DOPPLER VELOCIMETERS
JET FLOW Analysis of flight effects on noise radiation from jet flow usinq a convecting quadrupole model L [AIAA PAPER 78-192] p0015 A78-22594 LABORATORY EQUIPMENT JET NOISE Automatic multiple-sample applicator and U JFT AIRCRAFT NOISE electrophoresis apparatus JET PUMPS [NASA-CSE-AC-10991-11 p0057 N78-14104 Jet pump assisted arterial heat pipe LABYRINTH [AIMA 78-443] p0040 A78-35622 Further investigation of the spontaneous and JETAVATORS evoked activity of the primary neurons of U GUIDE VANES statortcoptors (and other receptors) of the JITTER labyrinth of the bullfrog before, during and U VIBRATION after an extended period of weightlessness, JOINTS (ANATOMY) including alternative intervals of artificial Spacesuit mobility knee joints gravity 5 t[ASA-CASE-ARC-11058-2) p0057 B78-18763 (NASA-CR-154507] p0O 2 N78-10684 JOINTS (JUNCTIONS) LAGRANGE SIMILARITY HYPOTHESIS Spacesuit mobility joints Lagrangian computation of inviscid compressible pOO58 H78-31735 flows FNAA-CAs-ARC-11058-1] 0 0 2 5 JUNCTION DIODES [NASA-TM-78456] p N78-24860 Characteristics of integrated MOMjunctions at dc LAMINAR BOUNDARY LATER and at optical frequencies Carbon vaporization into a nonequilibrium, (AD-A0561651 p003 7 A78-28926 stagnation-point boundary layer 2 JUPITER (PLANET) pOOQ A78-40838 The Pioneer 11 imaging experiment of Jupiter A computer program for calculating laminar and p0032 A78-18173 turbulent boundary layers for two-dimensional The interplanetary modulation and transport of time-dependent flows Jovian electrons [NASA-TM-78470] pOOS1N78-19444 pOO36 A78-26080 LAMINAE BOUNDARY LAYER SEPARATION On the apparent source depth of planetary magnetic U LAMINAR BOUNDARY LAYER fields LAMINAR FLAMES p0037 A78-29472 U LAMINAR FLOW Acceleration of nocleons in the interplanetary LAMINAR PLOW space and the modulation of Jupiter electrons in Navier-stlkes calculations for laminar and the interval from 1 to 10 A.U. by corotating turbulent hypersonic flow over indented nosetips regions of solar origin [AIMA PAPER 78-260] pOO35 A78-226O8 p0037 A78-29684 Computation of the viscous supersonic flow over JUPITER ATMOSPHERE symmetrical and asymmetrical external axial On determining magnetospheric diffusion corners coefficients from the observed effects of [AIAA PAPER 78-1135] p0043 A78-41839 Jupiter's satellite Yo Computation of supersonic laminar viscous flow p0032 A78-18732 past a pointed cone at angle of attack in Aerothermodynamic environment for Jovian entry spinning and coning motion with silica heat shield [AIAA PAPEB 78-1211] pO'Q5 A78-45139 EAIAA PAPER 78-186] p0033 A78-20710 LAMINAR FLOW CONTROL on the modulation of the Jovian decametric U BOUNDARY LAYER CONTROL radiation by Io. I - Acceleration of charged U LAMINAR BOUNDARY LAYER particles IAMINAR HEAT TRANSFER p0042 A78-41074 Effects of mass addition on blunt-body Correction to 'Recircnlation of energetic boundary-layer transition and heat transfer particles in Jupiters magnetospherel [NASA-TP-1139] p0022 H78-16326 pO0 4 5 A78-44775 LAMINAR JETS Whistler mode noise in Jupiter's inner magnetosphere U JET FLOW 4 pOO 5 A78-45188 U LAMINAR FLOW Pioneer Jupiter orbiter probe mission 1980, probe LAMINATED MATERIALS description U LAMINATES FNASA-CR-137591) p0 0 2 9 N78-33127 LAMINATES JUPITER PROBES Simple torsion test for shear moduli determination Shock-tube studies of atomic silicon emission in of orthotropic composites the spectral range 180 to 300 no --- environment [NASA-TM-78485] p0024 N78-21490 simulation for Jupiter probes LAMINATIONS [AIAA PAPER 78-2341 p0034 A78-22602 U LAMINATES Jupiter probe heatstield configuration optimization IARDIDG [AIAA PAPER 78-843] p0041 A78-37270 NT AIRCRAFT LANDING Pioneer Jupiter orbiter probe mission 1980, probe LANGUAGES description NT FORTRAN [NASA-CR-137591] p0029 N78-33127 LASER APPLICATIONS A new concept in laser-assisted chemistry - The K electronic-field representation pOO3 7 A78-27743 KALMAN FILTERS C02 laser-driven Stirling engine --- space power Development and flight tests of a Kalman filter applications 2 for navigation during terminal area and landing pOO 1A78-49804 operations Study, optimization, and design of a laser heat 2 [NASA-CR-3015] pOO1 N78-27105 engine KINETIC THEORY [NASA-CR-1521O4] p0OO 9 N78-19481 Thermodynamic processes induced by coherent LASER DOPPLER VELOCIMETERS radiation Laser-velocimeter surveys of merging vortices in a pOO3 A78-21624 wind tunnel Arrhenius' law in turbulent media and an [AIAA PAPER 78-107] pOO15 A78-20687 equivalent tunnel effect --- in binary exchange Measuring the velocity of individual atoms in real chemical reactions tine p0O 4 A78-52547 p0035 A78-23124 KINETICS Hot-wire, laser anemometer and force balance HT REACTION KINETICS measurements of cross-sectional planes of single KIRCHHOFF-HOYGENS PRICIPLE and interacting trailing vortices 8 U WAVE PROPAGATION (AIAM PAPER 78-1194] pOO1 A78-41885 laser-velcoimeter surveys of merging vortices in a wind tunnel: Complete data and analysis
G3 LASER OUTPUTS SUBJECT INDEX
(NASA-Tf-78449] pOOO8 N78-33043 procedure for shock-free flows LASER OUTPUTS pOO17 A78-37742 Thermodynamic processes induced by coherent The spanwise lift distribution on a wing from radiation flow-field velocity surveys p0034 A78-21624 [AIAA PAPER 78-1195] pO018 A78-41886 The response of heat-shield materials to intense Flying-hot-wire study of two-dimensional mean flow laser radiation past an NACA 4412 airfoil at maximum lift rAIAA PAPER 78-138] pD034 A78-22583 [AIAA PAPER 78-1196-- pODA8 A78-41887 QAuantum mechanical- theory of collisionar Closed-form equations for the lift, drag, and ionization in the presence of intense laser pitching-moment coefficients of airfoil sections radiation in subsonic flow fAD-A052981] pOUS5 A78-23576 (HASA-TN-784921 pOOD8 l78-29068 Semiclassical theory of unimolecular dissociation LIFT COEFFICIENTS induced by a laser field U LIFT [AD-AO56671] p003 9 A78-34682 LIFT DEVICES A cesium plasma TELEC device for conversion of Effect of high lift flap systems on the conceptual laser radiation to electric power design of a 1985 short-haul commercial STOL tilt p004 8 A78-51067 rotor transport LASERS (NASA-TM-78474] pOO5 N78-21094 NT CARBON DIOXIDE LASERS LIFT DISTRIBUTION NT CHEMICAL LASERS U FORCE DISTRIBUTION NT CONTINUOUS WAVE LASERS U LIFT NT DYE LASERS LIFT DRAG RATIO NT GAS LASERS Three-dimensional canard-wing shape optimization NT TWO-WAVELENGTH LASERS in aircraft cruise and maneuver environments LAST [AIAA PAPER 78-99] pOOl6 A78-26274 U F-111 AIRCRAFT LIFT FORCES LATE STARS U LIFT Airborne photometric observations between 1.25 and LIFTING BODIES 3.25 microns of late-type stars Lifting line theory for transonic flow pd036 A78-25295 p0020 A78-48991 LATTICES (MATHEMATICS) LIFTING SURFACES NT BOOLEAN FUNCTIONS U LIFT DEVICES LAU1CHING U LIFTING BODIES NT AIR LAUNCHING LIGHT (VISIBLE RADIATION) LAWS NT AIHGLOW NT SCALING LAWS NT ZODIACAL LIGHT LEADING EDGES LIGHT AIRCRAFT NT SHAPP LEADING EDGES A method for localizing wing flow separation at A method for localizing wing flow separation at stall to alleviate spin entry tendencies stall to alleviate spin entry tendencies [AIAA PAPER 78-1476] p0020 A78-49787 FAIAA PAPER 78-1476] p0020 A78-49787 LIGHT CURVE LEGEEDRE CODE Occultation of Epsilon Geminorum by Mars. XI - The U COMPUTER PROGVAMMING structure and extinction of the Martien upper LENSES atmosphere Process for producing a well-adhered durable p0O30 A78-10587 optical coating on an optical plastic substrate Analysis of stellar occultation data - Effects of --- abrasion resistant polymethyl methacrylate photon noise and initial conditions -- lenses planetary atmosphere temperature, pressure and rEASA-CASE-ARC-11O39-l] p0058 N78-32854 density profiles from occultation light curve LETHAIITY pOO35 A78-23164 AIC/50/ values for some polymeric materials --- LIGHT ELEMENTS Apparent Lethal Concentration fire toxicity light element geochemistry of the Apollo 12 site p004O A78-36596 p0054 A78-34503 LEVEL (HORIZONTAL) LIGHT EMISSION Rotary leveling base platform NT FLUORESCENCE FNASA-CASE-ARC-10981-l] p0O60 N78-27425 LIGHT SCATTERING LEVEL (QUANTITY) NT HALOS NT ELECTRON STATES Diagrammatic evaluation of the density operator NT MOLECULAR ENERGY LEVELS for nonlinear optical calculations LIFE (BIOLOGY) [ONERA, TP NO. 1977-166] p0031 A78-14651 U LIFE SCIENCES LIGHT TRANSHISSION LIFE DETECTORS NT HALOS chemical interpretation of Viking Lander I life NT LIGHT SCATTERING detection experiment Characteristics of integrated MOM junctions at dc pOe53 A78-25560 and at optical freguencies Multichannel electrochemical microbial detection [AD-A056165] pO03 7 A78-28926 unit LINEAR FILTERS pOO16 A78-31300 HT KALMAN FILTERS The Viking biological experiments on Mars LINEAR SYSTEMS pOO55 A78-39746 New frequency domain methods for system LIFE SCIENCES identification NT EXTRATERRESTRIAL LIFE F0015 A78-23883 Critical review of Ames Life Science participation Robustness of linear quadratic state feedback in Spacelab Mission Development Test 3: The SKD designs in the presence of system uncertainty 3 management study --- application to Augmentor Wing Jet STOL [NASA-TM-7849;3 pOO51 F78-26973 Research Aircraft flare control autopilot design LIFE SUPPORT SYSTEMS pOO16 A78-23917 NT CLOSED ECOLOGICAL SYSTEMS Applications of algebraic geometry to systems Technology advancement of the electrochemical C02 theory - The Mcfillan degree and Kronecker concentrating process indices of transfer functions as topological and 2 ENASA-CR-152098] pOO5 N78-22723 holomorphic system invariants Evaluation of a spacecraft nitrogen generator pOO 2 1 A78-51860 5 2 rNASA-CP-52097] pOC N78-23748 LINEAR TRANSFORMATIONS Advanced instrumentation concepts for Applications of algebraic geometry to systems environmental control subsystems theory - The McIillan degree and Kronecker TNASA-CR-1521001 pOO53 N78-28807 indices of transfer functions as topological and LIFT holomorphic system invariants Transonic lifting line theory - Numerical pOO 2 1 A78-51860
94 SUBJECT INDEX MANAGEMENT METHODS
LIPIDS MAGNETIC FIELD CONFIGURATIONS NT LIPOPROTEINS on the apparent source depth of planetary magnetic Physiologic regulation of body energy storage fields p0055 A78-42817 p 0 0 37 A78-29472 LIPOPEOTEIRS The spiral field inhibition of thermal conduction Spectrophotoflnorometric and electron microscopic in two-fluid solar wind models study of Lipofuscin accumulation in the testis p0 4 6 A78-48281 of aging mice MAGNETIC FIELDS p0056 A78-48581 NT GEOMAGNETISM LIQUID ROCKET PROPELLANTS NT INTERPLANETARY MAGNETIC FIELDS Fluid interaction with spinning toroidal tanks NT PLANETARY MAGNETIC FIELDS pOOP4 178-20186 NT SOLAR MAGNETIC FIELD LIQUID-GAS MIXTURES MAGNETIC MEASUREMENT NT AEROSOLS Crustal evolution inferred from Apollo magnetic LIQUIDS measurements NT LIQUID ROCKET PROPELLANTS [NASA-TM-78524] p0027 N78-32029 LITHIUM COMPOUNDS MAGNETIC MEMORIES NT LITHIUM HYDRIDES U MAGNETIC STORAGE LITHIUM HYDRIDES MAGNETIC PROPERTIES Semirigorous bounds for the dipole moments and NT ANTIFERROMAGNETISM transition moments of the EiR molecule NT FERROMAGNETISM pO046 A78-45963 NT GEOMAGNETISE LOADS (FORCES) NT MAGNETIC EFFECTS NT AERODYNAMIC LOADS NT SPIR-LATTICE RELAXATION NT WING LOADING MAGNETIC RELAXATION LOCKHEED AIRCRAFT NT SPIN-LATTICE RELAXATION NT U-2 AIRCRAFT MAGNETIC STORAGE LOCKHEED U-2 AIRCRAFT A decoding procedure for the Reed-Solomon codes U U-2 AIRCRAFT [NASA-TP-1286] p0059 H78-30862 LOCOMOTION MAGNTOGASDYNAMICS NT ASTRONAUT LOCOMOTION V MAGNETOHYDRODYNAIICS LOGISTICS MAGNETORYDRODYIRMIC FLOW NT SPACE LOGISTICS Acceleration of nucleons in the interplanetary LOW ASPECT RATIO WINGS space and the modulation of Jupiter electrons in NT DELTA WINGS the interval from 1 to 10 A.U. by corotating LOW DENSITY MATERIALS regions of solar origin Low density biamaleimide-carbon microballoon p0037 A78-29684 composites --- aircraft and submarine Dynamic MHD modeling of solar wind corotating compartment safety stream interaction regions observed by Pioneer [NASA-CASE-ARC-110O4-2] pO050 H78-27184 10 and 11 LOW SPEED p0049 A78-52522 Low speed aerodynamic characteristics of an MAGNETOHYDRODYNAMICS 0.075-scale P-15 airplane model at high angles Dynamic MHD modeling of the solar wind of attack and sideslip disturbances during the August 1972 events rFASA-TM--62360] p00 N78-10019 p0 0 3 6 A78-26079 Low-speed aerodynamic characteristics of a MAGRETOMETRY 0.08-scale YP-17 airplane model at high angles U MAGNETIC MEASUREMENT of attack and sideslip MAGNETOPLASMADYNAMICS r[ASA-TM-78438] pO006 E78-22025 U MAGNETOHYDRODYNAMICS LOW SPEED WIND TUNNELS MAGNETOSPHERE Low speed test of a high-bypass-ratio propulsion On the relative locations of the boy shocks of the system with an asymmetric inlet designed for a terrestrial planets tilt-nacelle V/STOL airplane p0031 A78-13752 fNASA-CR-152072] pOO09 N78-17062 On determining magnetospheric diffusion LOW VELOCITY coefficients from the observed effects of U LOW SPEED Jupiter's satellite to LOWER ATMOSPHERE p0 0 3 2 A78-18732 NT TROPOSPHERE Whistler mode noise in Jupiter's inner magnetosphere LUCITE (TRADEMARK) p0045 A78-45188 U POLYMETHYL METRACRYLATE NGNETOSPHERIC INSTABILITY LUMINESCENCE Correction to 'Recirculation of energetic FT FLUORESCENCE particles in Jupiter's magnetosphere LUNAR CINEHATOGRAPEY pOO45 A78-44775 U LUNAR PHOTOGRAPHY MAINTEMANCE LgRAR CRATERS NT FILE MAINTENANCE (COMPUTERS) Interpreting statistics of small lunar craters MAMMALS pOO2 A78-41753 NT MICE LUNAR CRUST NT RATS Crustal evolution inferred from Apollo magnetic MAN MACHINE SYSTEMS measurements Flight simulation - A vital and expanding (NASA-T-78524] p0027 N78-3202g technology in aircraft development LUNAR PHOTOGRAPHY [AIAA PAPER 78-337] pOO1 A78-29295 Interpreting statistics of small lunar craters Human problem solving performance in a fault p0042 h78-41753 diagnosis task LUNAR SOIL p0054 A78-32673 Light element geochemistry of the Apollo 12 site A model of human decisionmaking in a fault p0054 178-34503 diagnosis task LOAR SPACECRAFT pO054 A78-37130 NT APOLLO SPACECRAFT Dual-loop model of the human controller pOO18 A78-39184 MANAGEMENT M NT DATA MANAGEMENT MACHINE STORAGE NT PROCUREMENT MANAGEMENT U COMPUTER STORAGE DEVICES NT PROJECT MANAGEMENT MAGNETIC EFFECTS NT RESEARCH MANAGEMENT Square Tsing ferromagnetic and antiferromagnetic MANAGEMENT METHODS lattices in a magnetic field - A new Critical review of Ames Life Science participation perturbation approach in spacelab Mission Development Test 3: The SMD p0056 A78-51886 3 management study
95 MANAGEMENT PLANNING SUBJECT INDEX
(NASA-TN-78494] p0051 N78-26973 Assessing the future of air freight MANAGEMENT PLANNING [NASA-CR-152161] pO009 S78-Iq016 NASA/ESA CV-990 Spacelab simulation (ASSESS 2) NATHEMATICAL LOGIC [HASA-CR-152122] p0029 N78-23117 NT ALGORITHMS MANEUVERABLE SPACECRAFT NT BOOLEAN FUCTIONS NT APOLLO SPACECRAFT MATHEMATICAL MODELS MANEUVERS MT DIGITAL SIMULATION NT AIRCRAFT MANEUVERS Computational study- of a-molecular -collisihn VT EVASIVE ACTIONS process in the presence of an intense radiation NT SIDESLIP field - Enhanced quenching of F by Xe in the MANIPULATION 248-no light of the Kr laser U MANIPULATORS [AD-AO54078) pOO44 A78-42818 NANIPULATORS Modeling of the Reynolds stresses Study to design and develop remote manipulator p0024 N78-19797 systems Application of second-order turbulent modeling to [NASA-CR-152092] p0052 078-16620 the prediction of radiated aerodynamic sound MANNED SPACE FLIGHT [NASA-CR-2994] p0012 H78-25359 NT APOLLO 12 LIGHT MATHEMATICAL PROGRANMING MANNED SPACECRAFT NT DYNAMIC PROGRAMMING NT APOLLO SPACECRAFT MATRICES (MATHEMATICS) NT SPACE SHUTTLES A solution to the surface intersection problem --- Advanced instrumentation concepts for Boolean functions in geometric modeling environmental control subsystems [NASA-CR-152116] pOOl0 M78-19869 fNASA-CR-152100] pOO53 N78-28807 MATRIX ANALYSIS MANUAL CONTROL U MATRICES (MATHEMATICS) Development of automatic and manual flight MATURING director landing systems for the XV-15 tilt U GROWTH , rotor aircraft in helicopter mode MAXIMUM LIKELIHOOD ESTIMATES rNlSA-CR-152140] p0011 N78-22071 New frequency domain methods for system MANUALS identification RT USER MANUALS (COMPUTER PRUGRAMS) pOOl5 A78-23883 MAPPING MEASURE AID INTEGRATION NT PLANETARY MAPPING NT NUMERICAL INTEGRATION MARKOW PROCESSES NT WEIGHTING FUNCTIONS A technology assessment of transportation system MEASURING INSTRUMENTS investments --- Markovian decision theory NT HOT-WIRE ANEMOMETERS rNASA-CR-152154-2] p0013 N78-28989 NT HOT-WIRE FLOWMETERS MARS (PLANET) NT INFRARED DETECTORS Abstracts for the Planetary Geology Field NT INFRARED INTERFEROMETERS Conference on Aeolian Processes NT INFRARED RADIOMETERS rNASA-TM-784551 p0022 N78-13492 NT LASER DOPPLER VELOCIMETERS SANS ATMOSPHERE NT PRESSURE GAGES Occultation of Epsilon Geminorum by Mars. I - The NT PROPORTIONAL COUNTERS structure and extinction of the Martian upper NT RADIOMETERS atmosphere NT SPECTRONELIOGRAPHS p0030 A78-10587 MECHANICAL DEVICES chemical interpretation of Viking Lander I life Magnetometer deployment mechanism for Pioneer Venus detection experiment 3 p0023 N78-19029 pOD5 A78-25560 MECHAXICAL MEASUREMENT An analytic study of impact ejecta trajectories in NT DRAG MEASUREMENT the atmospheres of Venus, Mars, and earth NT FLOW MEASUREMENT 3 7 pOD A78-29532 NT PRESSURE MEASUREMENTS Primitive atmosphere and implications for the NT STRESS MEASUREMENT formation of channels on Mars NT VELOCITY MEASUREMENT pO044 A78-42460 MECHANICAL PROPERTIES Post-viking models for the structure of the summer NT ABRASION RESISTANCE atmosphere of Mars NT AEROELASTICITY p0047 A78-50240 HT SHEAR PROPERTIES MARS ENVIRONMENT NT TENSILE STRENGTH .AT MARS ATMOSPHERE NT THERMAL RESISTANCE MARS PROBES NT THERMOPLASTICITY NT VIKING LANDER SPACECRAFT A method for determining structural properties of NT VIKING LANDER 1 RCC thermal protection material --- Reinforced in VIKING ORBITER SPACECPAFT Carbon-Carbon MARS SURFACE [AIAA PAPER 78-8691 p0040 A78-35997 Some Martian volcanic features as vieea from the MEDIA Viking orbiters HT INTERPLANETARY DUST p0030 A78-11403 NT INTERPLANETARY MEDIUM Primitive atmosphere and implications for the MEDICAL EQUIPMENT formation of channels on Mars NT RESPIRATORS p004 A78-42460 MEDICAL SCIENCE Carbon suboxide polymer, an explanation for the NT HISTOLOGY wave of darkening on Mars MEETINGS p0056 A78-48717 U CONFERENCES Comparison between infrared Martian disk spectra MEMBRANE ANALOGY and optical properties of terrestrial analogs 7 U STRUCTURAL ANALYSIS p004 A78-49231 MEMBRANE THEORY MARS SURFACE SAMPLES U STRUCTURAL ANALYSIS The Viking biological experiments on Mars MEMBRANES p0055 178-39746 Calcium transport in Halobacterium halobium MASS TRANSFER envelope vesicles Effects of mass addition on blunt-body pO055 A78-48574 boundary-layer transition and heat transfer Methionine transport in Halobacterum halobium 2 2 (NASA-TP-1139] pO0 N78-16326 vesicles - noncompetitive, asymmetric inhibition .MATERIAL BALANCE by L-Cysteine NT WATER BALANCE pOO55 A78-48579 MATERIALS HANDLING MERCURY (PLANET) NT REMOTE HANDLING On the apparent source depth of planetary magnetic fields
95 SUBJECT INDEX MODELS
p0037 A78-29472 by L-Cysteine EESOMETEOPOLOGY p 0 0 5 5 A78-48579 Transport of contaminants in the planetary METROPOLITAN AREAS boundary layer U CITIES pOO 8 A78-52137 MICA METABOLISM Chemisorption of CO on Pd particles supported on NT ADRENAL METABOLISM mica NT ELECTROLYTE METABOLISM pOO4 O A78-36040 NT ENZYME ACTIVITY MICE Continuous metabolic and cardiovascular Micro-fluid exchange coupling apparatus --- a seasurements on a monkey subject during a microrespirator to allow surgery on rats or mice simulated 6-day Spacelab mission (NASA-CASE-ARC-11114-1] p0060 N78-33717 pOO56 A78-48719 MICROBIOLOGY METAL HYDRIDES Multichannel electrochemical microbial detection NT LITHIUM HYDRIDES unit METAL OXIDES pOO16 A78-31300 NT ALUMINUM-OXIDES MICROMETEOROIDS Characteristics of integrated MOM junctions at dc icroparticle accelerator of unique design --- for and at optical frequencies micrometeoroid impact and cratering simulation CAD-A0561651 p0037 A78-28926 p0036 A78-25264 METAL'PARTICLES Are the stratospheric dust particles meteor Chemisorption of CO on Pd particles supported on ablation debris or interplanetary dust? mica [NASA-TM-78507] p00 2 8 N78-34014 0 p004 A78-36040 MICROMETEORS Controlled vapor growth of small particles of Pd U MICROMETEOROIDS and Fe on thin A1203 substrates MICROORGANISMS pN044 A78-43384 NT BACTERIA METAL SURFACES EICROPARTICLES Stimulated emission of surface plasmons by Microparticle accelerator of unique design --- for electron tunneling in metal-barrier-metal micrometeoroid impact and cratering simulation structures p0036 A78-25264 p0038 A78-30647 Are the stratospheric dust particles meteor METALLIC PLASMAS ablation debris or interplanetary dust? NT CESIUM PLASMA [NASA-TM-78507] p0028 N78-34014 METALLOIDS MICROSCOPY NT SILICON NT ELECTRON MICROSCOPY METALS ICROSTRUCTURE NT CALCIUM NT METEORITIC MICROSTRUCTURES NT CHROMIUM MILITARY AIRCRAFT NT IRON Trajectory module of the NASA Ames Research Center NT PALLADIUM aircraft synthesis program ACSYNT NT TUNGSTEN [NASA-TM-78497] pOOO6 N78-26133 META2OA MILITARY HELICOPTERS t ANIMALS Evaluation of the tilt rotor concept: The XV-iS's METEORITE COLLISIONS role Microparticle accelerator of unique design --- for pOOON N78-19142 micrometeoroid impact and cratering simulation < MILITARY OPERATIONS p0036 A78-25264 NT COMBAT METEORITE COMPRESSION TESTS MILITARY TECHNOLOGY U MECHANICAL PROPERTIES Accordion shelter hardware analysis U METEORITES [AD-AD53592] poo07 N78-28278 METEORITE CRATERS MINERALS An analytic study of impact ejecta trajectories in NT MICA the atmospheres of Venus, Mars, and earth MINIMIZATION p0037 A78-29532 U OPTIMIZATION METEORITES MISSILE BODIES HT CARBONACEOUS CEONDRITES High angle canard missile test in the Ames 11-foot HT IRON METEORITES transonic wind tunnel NT TUNGUSK METEORITE [NASA-CE-2993] pOO11 N78-25057 Meteor ablation spheres from deep-sea sediments MISSILE CASES [NASA-TH-785101 p0028 N78-34021 U MISSILE BODIES METEORITIC COMPOSITION MISSILE COMPONENTS Analysis of ablation debris from natural and NT MISSILE BODIES artificial iron meteorites MISSILES p0039 A78-34506 NT INTERCONTINENTAL BALLISTIC MISSILES Nitric oxide production by Tunguska meteor MISSION PLANNING p0 0 4 8 A78-51811 Critical review of Ames Life Science participation METEORITIC DUST in Spacelab Mission Development Test 3: The SaD U MICROMETEOROIDS 3 management study METEORITIC MICROSTRUCTURES [NASA-TM-78494] p0051 N78-26973 Analysis of ablation debris from natural and NASA/ESA CV-990 spacelab simulation (ASSESS 2) artificial iron meteorites (NASA-TM-7978] pO027 N78-30149 p0039 A78-34506 Pioneer Jupiter orbiter probe mission 1980, probe METEOROID CRATERS description U METEORITE CRATERS (NASA-CR-137591] p0029 N78-33127 METEOROIDS MIXTURES NT MICMOMETEOROIDS NT AEROSOLS METEOROLOGICAL PARAMETERS NT DETONABLE GAS MIXTURES Meteorological control of lower stratospheric NT DISPERSIONS minor species variations - An observational NT SMOKE example MODELS 9 pOO1 A78-46011 NT AIRCRAFT MODELS METEOROLOGY NT ASTRONOMICAL MODELS NT MESOMETEOROLOGY NT ATMOSPHERIC MODELS METEACRYLATE RESINS NT DIGITAL SIMULATION U ACRYLIC RESINS NT DYNAMIC MODELS MET1IONINE NT MATHEMATICAL MODELS Mithionine transport in Halobacterium halobium NT REFERENCE ATMOSPHERES vesicles - Noncompetitive, asymmetric inhibition NT SCALE MODELS
97 MODES SUBJECT INDEX
NT SEMISPAN MODELS Absolute intensity measurements at different NT MIND TUNNEL MODELS temperatures of the C-12/0-16/2 bands 30 0 1 MODES I--00 0 0 and 30 0 1 IV-- 0 0 NT FAILURE MODES p0047 A78-50488 MODIFICATION Measurenent at different temperatures of absolute U REVISIONS intensities, line half-widths, and broadening by MODULATED CONTINUOUS RADIATION Ar and H2 for the 30 0 1 I--00 0 0 band of C02 On themodulation of the Jovian decametric p0047 78-50489 radiation by Io. I - AcceleratiOn of charged MOLECULAR STRUCTURE particles Thermal rearrangements in 1,2-poly/1,4-hexadiene/s 2 pO04 , A78-41074 p0048 A78-51870 MOLECULAR BEAKS Computer display and manipulation of biological low energy ionizing collisions between N2 and CO molecules beam molecules and CO. F2. NO, CR1, and C02 p0056 A78-53400 target molecules Stress-strain behavior of some acrylic gradient p0039 A78-34137 polymers MOLECULAR COLLISIONS [AD-4052617] p0059 N78-24364 Quantum mechanical theory of collisional MOLECULAR TRAJECTORIES ionization in the presence of intense laser Calculated rate constants for the reaction CIO + 0 radiation yields Cl * 02 between 220 and 1000 dog K -- [A-A052981] p0035 A78-23576 molecular trajectories and stratospheric ozone semiclassical approach to collision-induced [NASA-TM-78483] p0024 N78-21215 emission in the presence of intense laser MOLECULES radiation - An aspect in the study of NT DIATOMIC MOLECULES cooperative chemical and optical pumping OLIERE FORMULA p0037 A78-27744 U SPATIAL DISTRIBUTION Low energy ionizing collisions between N2 and CO MOMENTS bean molecules and CO, U2, NO, CH4. and C02 NT DIPOLE MOMENTS target molecules NT MOMENTS OF INERTIA p0039 A78-34137 NT TORQUE computational study of a molecular collision MOMENTS OF INERTIA process in the presence of an intense radiation Effect of a nonconstant C/m-alpha/ on the field - Enhanced quenching of F by Xe in the stability of rolling aircraft 218-nm light of the KrF laser p0031 A78-16180 rAD-A054078] p0044 A78-42818 MONITORS on the possibility of negative activation energies NT INFRARED RADIOMETERS in bimolecular reactions MONOLITHIC CIRCUITS rNASA-TF -785091 p0026 N78-29149 U INTEGRATED CIRCUITS MOLECULAR ENERGY LEVELS MONOMERS A theoretical study of the electronic transition Synthesis of N-substituted bisitacoimide monomers moment for the C2 Swan band system for use as thermosetting polyimide resins p004I A78-36776 pO04 1 A78-36809 On the possibility of negative activation energies MONOPLAIES in bimolecular reactions NT CV-990 AIRCRAFT fNASA-TM-78509] p0026 78-29149 NT F-5 AIRCRAFT MOLECULAR GASES NT U-2 AIRCRAFT Low energy ionizing collisions between N2 and CO NOTION EQUATIONS beam molecules and CO, N2, NO, CR1, and C02 U EQUATIONS OF NOTION target molecules MOTION SIMULATORS pOO39 A78-34137 Quasi-optimal control of a moving-base simulator MOLECULAR INTERACTIONS p0006 B78-23021 NT MOLECULAR COLLISIONS G-seat system step input and sinusoidal response Diagrammatic evaluation of the density operator characteristics for nonlinear optical calculations (NASA-TM-78478] p007 N78-26741 rONERA, TP NO. 1977-166] p0031 A78-14651 MOTION STABILITY Measurement at different temperatures of absolute NT AERODYNAMIC STABILITY intensities, line half-widths, and broadening by NT AIRCRAFT STABILITY Rr and N2 for the 30 0 1 II--00 0 0 band of C02 NT FLOW STABILITY pOO7 A78-50489 NT HOVERING STABILITY MOLECULAR PHYSICS NT ROTARY STABILITY Semirigorous bounds for the dipole moments and Numerical experiments on the stability of disklike transition moments of the Li molecule galaxies p0046 A78-45963 pOUl9 A78-45535 MOLECULAR RELAXATION MOTOR VEHICLES Exchange and relaxation effects in low-energy NT AUTOMOBILES radiationless transitions MULTILAYED STRUCTURES (NASA-TM-793831 p0004 N78-18882 U LAMINATES MOLECULAR ROTATION MUITILOOP SYSTEMS Simultaneous determination of rotational and U CASCADE CONTROL t'anslational temperatures of OH/2 Pi/ in a gas MUSCLES discharge NT IYOCARDIUM p0030 A78-10105 HUSCULOSKELETAL SYSTEM Comments on the note by Arie et al. on the NT CARTILAGE transition moment of the C02 band near 7710 NT JOINTS (ANATOMY) aysers MYOCARDIUM p0048 A78-52388 Extent of utilization of the Frank-Starling MOLECULAR SIEVES mechanism in conscious dogs --- preload effects U ABSORBENTS on myocardial regulation MOLECULAR SPECTRA p0 0 5 q A78-33522 NT RAMAN SPECTRA NT VIBRATIONAL SPECTRA N C3 and infrared spectrophotometry of Y Canum Venaticorum 1-156 AIRCRAFT 0 pO 2 A78-39448 U F-5 AIRCRAFT Intensities, self-broadening, and broadening by Ar NASA PROGRAMS and 112for the 301/111/ - 000 band of C02 NT ASSESS PROGRAM measured at different temperatures NT SUPERSONIC CRUISE-AIRCRAFT RESEARCH 4 6 p00 A78-48425 NT TILT ROTOR RESEARCH AIRCRAFT PROGRAM
98 SUBJECT INDEX NOSE CORES
Ames Research Center Publications-1976 NITROGEN OXIDES (NASA-TM-784931 pOO03 N78-27042 NT NITRIC OXIDE NASA/ESA CV-990 spacelab simulation (ASSESS 2) NITROUS 2 NT OXIDES [NASA-TM-79748J pOO 7 N78-30149 NITROUS OXIDES High altitude perspective --- cost-reimbursable Lower stratosphere measurements of variation with services using NASA U-2 aircraft latitude of CF2CI2, CFCL3, CCI4, and B20 [NASA-SP-427] pOO27 N78-31508 profiles in the northern hemisphere NASA aviation safety reporting system p003 5 A78-23610 [NASA-T-78511] pOO52 U78-32075 Stratospheric measurements of CF2CI2 and B20 NATIONAL AVIATION SYSTEM pOO54 A78-37055 NASA aviation safety reporting system Interhemispheric gradients of CF2C12, CFC13, CCIq, (NASA-TM-784761 pOO51 N78-25071 and 120 NATURAL FREQUENCIES p04 2 A78-41124 U RESONANT FREQDENCIES NOISE (SOUND) NATURAL SATELLITES NT AERODYNAMIC NOISE NT EUROPA NT AIRCRAFT NOISE NT 10 NT ENGINE NOISE NT PHOBOS NT JET AIRCRAFT NOISE RAVIER-STOKES EQUATION NOISE ATTENUATION Thin-layer approximation and algebraic model for U NOISE REDUCTION separated turbulent flows NOISE ELIMINATION rAIAA PAPER 78-2571 pOO33 A78-20776 U NOISE REDUCTION Numerical solution of a three-dimensional shock NOISE MEASUREMENT wave and turbulent boundary-layer interaction Comparison of measured and calculated helicopter [AIAA PAPER 78-161] pOO34 A78-22591 rotor impulsive noise --- wind tunnel test data Navier-Stokes calculations for laminar and and prediction analysis techniques turbulent hypersonic flow over indented nosetips rNASA-TM-78473] p 0 0 0 5 N78-20917 0 0 3 5 [AIAA PAPER 78-2601 p A78-22608 The effect of tip vortex structure on helicopter Calculation of supersonic viscous flow over delta noise due to blade/vortex interaction wings with sharp subsonic leading edges (NASA-CR-152150] pOOl 2 N78-25832 rAIA PAPER 78-1137] pOO43 A78-4181 NOISE PROPAGATION Comparison of multieguation turbulence models for Analysis of flight effects on noise radiation from several shock-separated boundary-layer jet flow using a convecting quadrupole model interaction flows [AIAA PAPER 78-192] pOBlS A78-22594 rAIA PAPER 78-1165] p0043 A78-41863 A study of the noise radiation from four NAVIGATION helicopter rotor blades --- tests in Ames 40 by NT AIR NAVIGATION 20 foot wind tunnel NEAR GAMES pOOD 8 U78-32835 Flying-hot-wire study of two-dimensional mean flow NOISE REDUCTION past an NACA 4412 airfoil at maximum lift use of coherence and phase data between two [AIAA PAPER 78-1196] pOOl8 A78-41887 receivers in evaluation of noise environments NERVOUS SYSTEM pOO1 6 A78-26495 NT NEURONS Use of leaning vanes in a two stage fan NETWORK SYNTHESIS (NASA-CR-152134] pOO10 N78-21115 Digital filter structures having low errors and Optimal guidance and control for investigating simple hardware implementation aircraft noise-impact reduction pOO56 A78-51346 [NASA-TP-1237] pOO06 N78-23100 NEURONS Optimizing indium antimonide (InSb) detectors for Further investigation of the spontaneous and low background operation --- infrared astronomy evoked activity of the primary neurons of (NASA-TM-73273) p0028 N78-32947 statoreceptors (and other-receptors) of the NOISE SPECTRA labyrinth of the bullfrog before, during and Whistler mode noise in Jupiter's inner magnetosphere after an extended period of weightlessness, pOO5 A78-45188 including alternative intervals of artificial NOISE SUPPRESSORS gravity U NOISE REDUCTION fNASA-CR-154507] p0052 N78-10684 NONADIABATIC PROCESSES NEUTRAL BEAMS U HEAT TRANSFER NT MOLECULAR BEAMS NONCONDENSABLE GASES NITRIC ACID Experimental temperature distribution and heat Stratospheric NO and HN03 observations in the load characteristics of rotating heat pipes 6 Northern Hemisphere for three seasons pOO4 &78-4883 pOO2 A78-41123 NONEUCLIDIAN GEOMETRY NITRIC OXIDE U DIFFERENTIAL GEOMETRY Geographical variations of NO and 03 in the lower NONLINEAR EQUATIONS stratosphere An integral solution to a nonlinear diffusion pOO39 A78-35403 problem Stratospheric NO and 1103 observations in the p0837 A78-26350 Northern Hemisphere for three seasons NONLINEAR OPTICS pOO42 A78-41123 Diagrammatic evaluation of the density operator Nitric oxide pr6duction by Tunguska meteor for nonlinear optical calculations 4 pOO 8 A78-51811 [ONERA, TP NO. 1977-166] p0 0 3 1 A78-14651 NITROGEN NONVISCOUS FLOW NT NITROGEN IONS U TURBULENT FLOW Low energy ionizing collisions between W2 and CO NORMAL FORCE DISTRIBUTION beam molecules and Co. N2. NO, CH4, and C02 U FORCE DISTRIBUTION target- molecules 'NORTHERN HEMISPHERE pOO39 A78-34137 Stratospheric NO and 1N03 observations in the Evaluation of a spacecraft nitrogen generator Northern Hemisphere for three seasons ENASA-CH-152097) pOS52 N78-23748 p0042 A78-g1123 NITROGEN COMPOUNDS NORTHROP AIRCRAFT NT IMtDIS NT F-5 AIRCRAFT NT NITRIC ACID NOSE CAPS NT NITRIC OXIDE U NOSE CONES NT NITROUS OXIDES NOSE CONES NITROGEN IONS NT ABLATIVE NOSE CONES The quiet coronal X-ray spectrum of highly ionized Navier-Stokes calculations for laminar and oxygen and nitrogen turbulent hypersonic flow over indented nosetips pOO38 A78-31108 [AIAA PAPER 78-260] p0035 A78-22608
99 NOSES (FOREBODIES) SUBJECT INDEX
DOSES (FOREBODIES) pOO04 78-19786 NT ABLATIVE HOSE COVES -Computing viscous flows NT NOSE CONES pO005 78-19794 NOVAE NUMERICAL INTEGRATION Nova-driven inds in globular clusters An integral solution to a nonlinear diffusion 4 pOO l A78-37649 problem NOXIOUS MATERIALS p0037 A78-26350 U CONTAMINANTS Numerical solution -of -a class.of- integral NOZZLE-THRUST,-COEFFICIENTS equations arising in two-dimensional aerodynamics Static tests of a large scale swivel nozzle thrust pOOl8 A78-40949 deflector Solution of transonic flows by an rNASA-CR-152091] pOO11 N78-22100 integro-differential equation method NUCLEAR INTERACTIONS [NASA-TM-78490] p0026 N78-26391 NT SPIN-ORBIT INTERACTIONS NUTRITIONAL REQUIREMENTS NUCLEAR PARTICLES Food and oxygen requirements for growing mice and NT ALPHA PARTICLES turtles after hypergravitational development NT NUCLEONS pO31 A78-15204 NUCLEAR RADIATION -NT GAMna RAYS NUCLEAR REACTIONS NT SPIN-ORBIT INTERACTIONS OBSERVATION AIRCRAFT NUCLEI (NUCLEAR PHYSICS) NT F-5 AIRCRAFT NT ALPHA PARTICLES NT U-2 AIRCRAFT NUCLEONS OBSERVATORIES Acceleration of nucleons in the interplanetary NT ASTRONOMICAL OBSERVATORIES space and the modulation of Jupiter electrons in OCCULTATION the interval from I to 10 A.U. by corotating NT STELLAR OCCULTATION regions of solar origin OCEAN BOTTOM 3 7 p0O A78-29684 Meteor ablation spheres from deep-sea sediments NUMERICAL ANALYSIS [NASA-TM-78510] pRO2 8 R78-34021 NT FINITE DIFFERENCE THEORY ONBOARD COSPUTERS NT ITERATIVE SOLUTON U AIRBORNE/SPACEBORNE COMPUTERS NT NUMERICAL INTEGRATION OEBOARD EQUIPMENT NT TRUNCATION ERRORS NT AIRBORNE EQUIPMENT Unsteady transonic flow computations NT AIRBORNE/SPACEBORNE COMPUTERS p0032 A78-18274 NT AIRCRAFT EQUIPMERT Transonic lifting line theory - Numerical OPERATING SYSTEMS (COMPUTERS) procedure for shock-free flows Preliminary study for a numerical aerodynamic po017 A78-37742 simulation facility. Phase 1: Extension Preliminary study for a numerical aerodynamic fNASA-CR-152108] pO0 2 8 N78-19052 simulation facility. Phase I: Extension 2 OPERATIONS RESEARCH (NASA-CP-152108] p0O 8 N78-19052 Phase 1: Definition of intercity transportation Future Computer Requirements for Computational comparison framework. Volume 1: Summary -- Aerodynamics operations research of passenger and freight [NASA-CP-2032] p0023 N78-19778 transporatation systems Computational aerodynamics,and the numerical [NASA-CR-152152-VOL-1] pODOl 178-28993 aerodynamic simulation facility Phase 1: Definition of intercity transportation p0023 N78-19779 comparison framework. Volume 2: Methodology Three-dimensional computational aerodynamics in --- operations research of passenger and freight the 1980's transportation systems p0023 H78-19781 (NASA-CR-152152-VOL-2] pOO 2 9 F78-28994 Numerical Aerodynamics Simulation Facility OPERATOR PERFORMANCE preliminary study, executive summary --- three Dual-loop model of the human controller dimensional flow pOO18 A78-39184 pO023 N78-19782 OPERATORS (PERSONNEL) Preliminary study for a Numerical Aerodynamic NT TEST PILOTS Simulation 'acility --- three dimensional flow OPTICAL ABSORPTION 2 3 pO0 N78-19783 U LIGHT TRANSMISSION computing viscous flows OPTICAL EMISSION SPECTROSCOPY pOO05 R78-19794 Absolute intensity measurements at different NUMERICAL CONTROL temperatures of the C-12/0-16/2 bands 30 0 1 Numerical aerodynamic simulation facility. I--0O 0 0 and 30 0 1 IV--0O 0 0 Preliminary study extension. Executive summary pO047 A78-50488 fNASA-CR-152106] p0028 N78-19050 OPTICAL EQUIPMENT NUMERICAL FLOW VISUALIZATION NT ASTRONOMICAL TELESCOPES On implicit finite-difference simulations of NT COLLIMATORS three-dimensional flow NT LASER DOPPLER VELOCIMETERS ATIAA PAPER 78-10] pRO33 A78-20630 NT SPECTROHELIOGRAPHS Numerical solution of two-dimensional turbulent Process for producing a well-adhered durable blunt body flows with an impinging shock optical coating on an optical plastic substrate FAIAA PAPER 78-1209] p0045 A78-45144 --- abrasion resistant polymethyl methacrylate Future Computer Requirements for Computational lenses Aerodynamics [BASA-CASE-ARC-11039-1) pOOSS 78-32854 !rNASA-CP-2032] p0023 H78-19778 OPTICAL MEASUREMENT Computational aerodynamics and the numerical NT ASTRONOMICAL PHOTOMETRY aerodynamic simulation facility NT STELLAR SPECTROPHOTOMETRY p0023 N78-19779 OPTICAL POLARIZATION Three-dimensional computational aerodynamics in Diagrammatic evaluation of the density operator the 1980's for nonlinear optical calculations p0023 N78-19781 fONERA, TP NO. 1977-166] p0031 A78-14651 Numerical Aerodynamics Simulation Facility OPTICAL PROPERTIES preliminary study, executive summary --- three NT OPTICAL REFLECTION dimensional flow NT SPECTRAL REFLECTANCE p0023 N78-19782 Comparison between infrared Martian disk spectra Preliminary study for a Numerical Aerodynamic and optical properties of terrestrial analogs Simulation Facility --- three dimensional flow p0047 A78-49231 2 3 pO N78-19783 OPTICAL PUMPING Future requirements and roles of computers in Semiclassical approach to collision-induced aerodynamics emission in the presence of intense laser
100 SUBJECT INDEX PARTICLE ACCELERATION
radiation - An aspect in the study of VT CHLORINE OXIDES cooperative chemical and optical pumping NT METAL OXIDES p0037 &78-27744 FT NITRIC OXIDE OPTICAL REFLECTION NT NITEOUS OXIDES Generation of a parallel X-ray beam and its use NT SILICON DIOXIDE for testing collimators OXYGEN p0035 A78-23083 NT OXYGEN ATOMS OPTICAL TRACKING NT OXYGEN 1OS Peaker: An automatic boresight peaking routine NT OZONE for the C-141 telescope The co-adsorption of copper and oxygen on a rNASA-TM-785161 p0O08 N78-32856 tungsten 100 plane-type surface OPTIMAL CONTROL pO037 A78-29489 New frequency domain methods for system Stability of chromium (I) sulfate in atmospheres identification containing oxygen and sulfur pO15 A78-23883 [NASA-TM-785041 p0026 N78-28173 Quasi-optimal control of a moving-base simulator OXYGEN ATOMS pOO06 P78-23021 Europa - Ultraviolet emissions and the possibility OPTIMIZATION of atomic oxygen and hydrogen clouds NT OPTIMAL CONTROL p004 8 A78-52482 NT TRAJECTORY OPTIMIZATION OXYGEN CONSUMPTION Computational wing optimization and wind tumnel Food and oxygen reguirements for growing mice and test of semi-span model turtles after hypergravitational development 3 [ATAA PAPER 78-102] p00 4 A78-22575 p00 3 1 A78-15204 Study, optimization, and design of a laser heat Fluid-electrolyte shifts and maximal oxygen uptake engine in man at simulated altitude /2.287 a/ (NASA-CE-152104] p0009 N78-19t81 pOOS4 A78-36602 A study of commuter airplane design optimization OXYGEN IONS" [NASA-CR-1572101 p0011 N7S-2S078 The quiet coronal X-ray spectrum of highly ionized Computational wing optimization and comparisons oxygen and nitrogen with experiment for a semi-span wing model p0038 A78-31108 (NASA-TM-78480] p0025 178-26106 OZONE Optimizing indium antimonide (luSb) detectors for Stratospheric measurements of CF2Cl2 and V20 low background operation --- infrared astronomy p0054 A78-37055 ENASA-TM-73273] p0028 V78-32947 Stratospheric NO and RE03 observations in the OPTIMUM CONTROL Northern Hemisphere for three seasons U OPTIMAL CONTROL p0042 A78-41123 ORBITAL SIMULATORS Calculated rate constants for the reaction CIO + 0 U SPACE SIMULATORS yields Cl + 02 between 220 and 1000 deg K -- ORGARIC COMPOUNDS molecular trajectories and stratospheric ozone NT CYSTEINE ENASA-TM-78483] p0024 N78-21215 NT FLUOROCARBONS An assessment of the effect of supersonic aircraft NT METHIONINE operations on the stratospheric ozone content ORGANIC LASERS (NASA-RP-1026) p00 27 N78-30774 NT DYE LASERS OZOROMETRT ORGAIZATIONS Geographical variations of NO and 03 in the lower NT EUROPEAN SPACE AGENCY stratosphere ORGANS pOO 3 9 A78-35403 NT TESTES ORNITHOPTER AIRCRAFT U RESEARCH AIRCRAFT p ORRERIES P-T-N DIODES U ASTRONOMICAL MODELS U DIODES ORTHOTROPIS PALLADIUM simple torsion test for shear moduli determination Chemisorption of CO on Pd particles supported on of ortbotropic composites mica fNASA-TM-78485) p0024 V78-21490 pO04O A78-36040 OSCILLATING FLOW Controlled vapor growth of small particles of Pd Visualization of quasi-periodic unsteady flows and Fe on thin A1203 substrates [AIAA 78-502] pOO16 A78-29804 po044 k78-43384 OSCILLATIONS PANELS NT HARMONIC OSCILLATION NT WING PANELS NT WING OSCILLATIONS An improved higher order panel method for Water-tunnel experiments on an oscillating airfoil linearized supersonic flow at RE equals 21,000 [AIAA PAPER 78-15] pOOl A78-52628 [NASA-TM-78446] p0062 N78-19058 Structural wood panels with improved fire resistance Dynamic stall of an oscillating airfoil --- using prepolymers and hexamethylentetranine p0025 R78-22055 [NASA-CASE-AC-11174-1] pOOSO N78-28178 OSMOSIS PARABOLIC DITF1ERETIAL EQUATIONS Calcium transport in Halobacterium halobium An integral solution to a nonlinear diffusion envelope vesicles problem p0055 A78-4857 pOO 3 7 A78-26350 OSMOTIC PRESSURE PARALLEL FLOW U OStOSIS NT THREE DIMENSIONAL FLOW OUTPUT PARALLEL PROCESSING (COMPUTERS) NT LYSB OUTPUTS A single user efficiency measure for evaluation of OXIDATION parallel or pipeline computer architectures A method for determining structural properties of pOOS9 R78-19808 FCC thermal protection material --- Reinforced PARTIAL DIFFERENTIAL EQUATIONS Carbon-Carbon NT PARABOLIC DIFFERENTIAL EQUATIONS [AIAA PAPER 78-869] p0040 A78-35997 PARTICLE ACCELERATION OXIDE FILMS Acceleration of nucleons in the interplanetary Controlled vapor growth of small particles of Pd space and the modulation of Jupiter electrons in and Fe on thin A1203 substrates the interval from 1 to 10 A.U. by corotating 4 XIDEhn 2 ss e pOO' A78-43384 regions of solar origin OXIDES p0037 A78-29684 NT AlUMINUE OXIDES On the modulation of the Jovian decametric NT CARBON DIOXIDE radiation by lo. I - Acceleration of charged NT CARBON MONOXIDE particles NT CARBON SBOXIDES pOO42 A78-41074
10t PARTICLE ACCELERATORS SUBJECT INDEX
PARTICLE ACCELERATORS PERIODIC VARIATIONS Microparticle accelerator of unique design --- for FT ANNUAL VARIATIONS nicrometeoroid impact and cratering simulation FT DIURNAL VARIATIONS p0036 A78-25264 PERIPHERAL EQUIPMENT (COMPUTERS) PARTICLE BEANS NT COMPUTER STORAGE DEVICES NT ATOMIC BEAMS Peripheral processors for high-speed simulation WT MOLECULAR BEANS --- helicopter cockpit simulator PARTICLE DENSITY (CONCENTRATION) .pOO14- A78-14063- NTIONOSPHERIC ELECTRON tE'41TY PERSONNEL PARTICLE DIFFUSION NT TEST PILOTS on determining manetospheric diffusion PERTURBATION THEORY coefficients from the observed effects of Diagrammatic evaluation of the density Operator for nonlinear optical calculations Jupiter's satellite Io 3 p0032 A78-18732 (ONERA, TP NO. 1917-166] p00 1 A78-14651 for transonic flow PARTICLE ENERGY Lifting line theory 0 2 NT ELECTRON ENERGY p O 0 A78-48991 NT ELECTRON STATES Square Ising ferromagnetic and antiferromagnetic NT PROTON ENERGY lattices in a magnetic field - A new perturbation approach PARTICLE FLUX DENSITY 5 6 NT ELECTRON FLUX DENSITY pRO A78-51886 PARTICLE INTERACTIONS Techniques for correcting approximate finite NT MOLECULAR COLLISIONS difference solutions --- considering transonic NT MOLECaLAR INTERACTIONS flow NT SPIN-ORBIT INTERACTIONS [NASA-TM-78499] p0026 N78-26796 PARTICLE MOTION PHARMACOLOGY leasuring the velocity of individual atoms in real Extent of utilization of the Frank-Starling time mechanism in conscious dogs --- preload effects O0035 A78-23124 on myocardial regulation Rigidity-independent coronal propagation and pO054 A78-33522 escape of solar protons and alpha particles PHASE COHERENCE pOO1 A78-37354 Use of coherence and phase data between two Correction to 'Recirculation of energetic receivers in evaluation of noise environments particles in Jupiter's magnetosphere pOOl6 A78-26495 p0O5 A78-44,775 PHOBOS PARTICLE SIZE DISTRIBUTION The composition of Phobos - Evidence for Saturn's rings: Particle composition and size carbonaceous chondrite surface from spectral distribution as constrained by microwave analysis 2 observations. I - Radar observations pOR3 A78-18871 pO036 A78-25676 Multicolor observations of Phobos with the Viking PARTICLES lander cameras - Evidence for a carbonaceous NT AEROSOLS chondritic composition ' 3 FT ALPHA PARTICLES p0O 2 A7R-18875 NT CESIUM PLASMA PHOTOABSORETIOX NT ENERGETIC PARTICLES Computational study of a molecular collision NT METAL PARTICLES process in the presence of an intense radiation NT MICHOPARTICLES field - Enhanced quenching of F by Xe in the 248-nm light of the KrF laser NT NfrCLEONS 4 NT SOLAR PPOTONS [AD-A054078] pOOq A78-42818 NT SOLAR WIND PHOTOCHEMICAL REACTIONS NT STELLAR WINDS A note on the diurnal averaging of aeronbmical PASSENGER AIRCRAFT models NT CV-990 AIRCRAFT pOO39 A78-34352 Fire resistivity and toxicity studies of candidate Primitive atmosphere and implications for the aircraft passenger seat materials formation of channels on Mars pOOQ8 A78-51838 p0O44 A78-42460 Fire resistivity and toxicity studies of candidate Illumination-dependent changes in the intrinsic aircraft passenger seat materials fluorescence of bacteriorhodopsin [NASA-TM-78468] p0024 N78-21214 pO55 A78-48578 A study of commuter airplane design optimization PHOTOCHEMISTRY rNASA-CR-157210] pO011 H78-25078 U PHOTOCHEMICAL REACTIONS PASSENGERS PHOTOCONDUCTORS Phase 1: Definition of intercity transportation Continued development of doped-germanium comparison framework. Volume 2: Methodology photoconductors for astronomical observations at --- operations research of passenger and freight wavelengths from 30 to 120 micrometers transportation systems (NASA-CR-152125] p0029 H78-22000 rNASA-CR-152152-VOL-2] p0029 N78-28994 PHOTODISSOCIATION A study of characteristics of intercity Semiclassical theory of unimolecular dissociation transportation systems. Phase 1- Definition of induced by a laser field transportation comparison methodology [AD-AO566713 pORS9 A78-34682 FNASA-C-152153-2] p0OO01 N78-29996 PHOTOGRAPH INTERPRETATION PERFORMANCE PREDICTION U PROTOINTERPRETATION NTPREDICTION ANALYSIS TECHNIQUES PHOTOGRAPHY Entry dynamics performance predictions for Pioneer NT AERIAL PHOTOGRAPHY Venus probes WT ASTRONOMICAL PHOTOGRAPHY (AIAA 78-1370] pOO06 A78-46557 NT INFRARED IMAGERY PERFORMANCE TESTS NT LUNAR PHOTOGRAPHY Investigation of a cryogenic thermal diode NT SCHLIEREN PHOTOGRAPHY (ATAA 78-417] pO0O A78-35601 NT SPACEHORNE PHOTOGRAPHY Low profile antenna performance study. Part 2: PHOTOINTERPEETATION Broadband antenna techniques survey Interpreting statistics of small lunar craters 1 2 [AD-A0479921 poo22 N78-18274 p00 A78-41753 A pilot evaluation of two G-seat cueing schemes PHOTOMETRY UNASA-"P-1255] pOO08 N78-31739 HT ASTRONOMICAL PHOTOMETRY PERIOD EQUATIONS NT STELLAR SPECTROPHOTOMETRY U PERIODIC FUNCTIONS PHOTON-ELECTRON INTERACTION PERIODIC FUNCTIONS A new concept in laser-assisted chemistry - The On the period of the coherent structure in electronic-field representation boundary layers at large Reynolds numbers pG037 A78-27743 rNASA-TM-78477] p002 4 N78-21407
102 SUBJECT INDEX PLANETARY SURFACES
PIOTOEDUCTION Pioneer 10 observation of the solar wind proton U PHOTOCHEMICAL REACTIONS temperature heliocentric gradient PUOTORESISTORS [NAS-TM-785151 p0 0 2 7 NT7-31030 B PHOTOCONDUCTORS PIONEER 11 SPACE PROBE PHOTOTHEROTROPISM The Pioneer 11 imaging experiment of Jupiter U TEMPENATURE EFFECTS p0032 A78-18173 PHUGOID OSCILLATIONS Quiet time interplanetary cosmic ray anisotropies U OSCILLATIONS observed from Pioneer 10 and 11 " PITCH (INCLINATIQN) p0039 A78-34567 PHYSICAL EXERCISE Dynamic MED modeling of Solar wind corotating Effects of exercise and excitement on mesenteric stream interaction regions observed by Pioneer and renal dynamics in conscious, unrestrained 10 and 11 baboons p0O4S A78-52522 pOO53 A78-27124 PTPES (TUBES) PHYSIOLOGICAL EFFECTS Study of a high performance evaporative heat NT HEMODYNAMIC RESPONSES transfer surface NT PHYSIOLOGICAL RESPONSES [tASA-CR-152008] pO02B R78-10411 PHYSIOLOGICAL RESPONSES Extended development of variable conductance heat UT HEHOPYNANIC RESPONSES pipes Space colonization - Some physiological perspectives (NASA-CR-152183] pUO29 N78-33379 p0055 A78-41164 Development Of a cryogenic rotating heat pipe joint Physiologic regulation of body energy storage tNASA-CR-152188] pOCDO 78-33384 pU055 A78-42817 PITCH (INCLINATION) Gravity as a biochemical determinant Closed-form equations for the lift, drag, and p0056 A78-48671 pitching-moment coefficients of airfoil sections PHYSIOLOGICAL TELEMETRY in subsonic flow U BIOTELEnETRY (NASA-TM-78492] pOCOB H78-29068 PHYSIOLOGICAL TESTS PITCH ANGLES Extent of utilization of the Frank-Starling U PITCH (INCLINATION) mechanism in conscious dogs --- preload effects PLANAR STRUCTURES on myocardial regulation A Mach line panel method for computing the pOO54 A78-33522 linearized supersonic flow over planar wings CV 990 interface test and procedure analysis of [NASA-CR-152126] pOOl2 078-27D87 the monkey restraint, support equipment, and PLANET ORIGINS telemetry electronics proposed for Spanelab U PLANETARY EVOLUTION NBASA-Tn-78484 pOOSi N78-27736 PLANETARY ATMOSPHERES PIEZORESISTIVE TEARSfUCERS NT HELIUM HYDROGEN ATMOSPHERES A fifty channel electrically scanned pressure module UT JUPITER ATMOSPHERE pOO14 A78-17395 NT MARS ATMOSPHERE PIGMENTS NT VENUS ATMOSPHERE NT VISUAL PIGMENTS Analysis of stellar occultation data - Effects of Spectrophotofluorometric and electron microscopic photon noise and initial conditions -- study of Lipofuscin accumulation in the testis planetary atmosphere temperature, pressure and of aging nice density profiles from occultation light curve pOOS6 A78-48581 pO03S A78 2 3 164 PILOTS (PERSONNEL) Synthesis of porous polyaromatic column packings NT TEST PILOTS for GC analysis of extraterrestrial atmospheres PIONEER F SPACE PROBE P0055 A78-48577 " PIONEER 10 SPACE PROBE PLANETARY ENTRY PIONEER G SPACE PROBE U ATMOSPHERIC ENTRY U PIONEER 11 SPACE PROBE PLANETARY ENVIRONMENTS PIONEER SPACE PROBES NT JUPITER ATMOSPHERE NT PIONEER 10 SPACE PROBE NT MARS ATMOSPHERE NT PIONEER 11 SPACE PROBE NT PLANETARY ATMOSPHERES Toroidal tank evaluation --- propellant tanks for NT VENUS ATMOSPHERE spin--tabilized Pioneer spacecraft, Abstracts for the Planetary Geology Field p0032 A78-17881 Conference on Aeolian Processes The ionosphere and airglow of Venus - Prospects [NASA-TM-78455] p0022 N78-13492 for Pioneer Venus PLANETARY EVOLUTION p0045 A78-44773 The rings of Saturn Pioneer Jupiter orbiter probe mission 1980, probe p0036 A78-23646 description PLANETARY MAGNETIC FIELDS (NASA-CR-137591] pOO29 N78-33127 On the apparent source depth of planetary magnetic PIONEER VENUS SPACECRAFT fields Thermal design and development of a planetary p0037 A78-29472 probe - Pioneer Venus large probe PLANETARY MAPPING [AIRA PAPER 78-9163 pOOm1 A78-37275 Some Martian volcanic features as viewed from the Entry dynamics performance predictions for Pioneer Viking orbiters Venus probes p0O3O A78-11403 [ IAA 78-1370) pOW 4 6 A78-46557 PLANETARY RADIATION Pioneer Venus spacecraft charging model Acceleration of nucleons in the interplanetary p0022 N78-10148 space and the modulation of Jupiter electrons in Magnetometer deployment mechanism for Pioneer Venus the interval from 1 to 10 R.I. by cor.otating p0023 NI8-19029 regions of solar origin PIONEER 10 SPACE PROBE p0037 A78-29684 On the observation of a flare-generated shock wave On the modulation of the Jovian decametric at 9V7 AU by Pioneer 10 radiation by Io. I - Acceleration of charged 0 0 3 8 [D-A053721] p A78-30078 particles Quiet time interplanetary cosmic ray anisotropies p0042 A78-41074 observed from Pioneer 10 and 11 PLANETARY STRUCTURE p0039 A78-34S567 On the apparent source depth of planetary magnetic The radial dependences of the interplanetary fields magnetic field between I and 5 AU Pioneer 10 p0037 A78-29472 p0048 A78-52504 PLANETARY SURFACES Dynamic MHD modeling of solar wind corotating NT MARS SURFACE stream interaction regions observed by Pioneer Application of high explosion cratering data to 10 and 11 planetary problems p0049 A78-52522 p0044 A78-44033
103 PLANETOLOGY SUBJECT INDEX
PLANETOLOGY Relative toxicity of the pyrolysis products from The rings of Saturn some thermoplastic and thermoset polymers p0036 A78-23646 p0042 A78-41213 PLANETS Synthesis of porous polyaromatic column packings NT EARTH (PLANET) for CC analysis of extraterrestrial atmospheres NT JUPITER (PLANET) p0055 A78-48577 NT MARS (PLANET) Carbon suboxide polymer, an explanation for the NT MERCURY (PLANET) wave of darkening on Mars NT TERRESTRIAL PLANETS p0056 A78-48717 NT URANUS (PLANET). Thermal rearrangements in 1,2-poly/1,4-hexadiene/S PLARNFOEMS p0048 A78-51870 NT DELTA WINGS Catalysts for imide formation from aromatic NT WING PLANFORIS isocyanates and aromatic dianhydrLdes PLANNING [NASA-CASE-ARC-11107-1] p0049 N78-22156 NT AIRPORT PLANNING POLYMER MATRIX COMPOSITE MATERIALS NT MANAGEMENT PLANNING Intumescent-ablator coatings using eadothermic NT MISSION PLANNING fillers NT REGIONAL PLANNING [NASA-CASE-ARC-11O13-1] p0049 N78-27180 PLASMA FLOW POLYMERIZATION U MAGNETOHYDRODYNAMIC FLOW Synthesis of porous polyaromatic column packings PLASMA HEATING for GC analysis of extraterrestrial atmospheres Acceleration and heating of the solar wind p0055 A78-48577 p0029 N78-32991 Polymeric foams from cross-linkable PLASMAS (PHYSICS) poly-n-arylenebenzimidazoles NT CESIUM PLASMA [NASA-CASE-ARC-11008-1] p0050 H78-31232 NT SOLAR WIND POLYNMERS NT STELLAR WINDS Chelate-modified polymers for atmospheric gas PLASMOPS chromatography Stimulated emission of surface plasmons by [NASA-CASE-ARC-11154-1] p0057 N78-27275 electron tunneling in netal-barrier-metal POLYMETHYL METHACRYLATE structures The prediction of toxic atmospheres from pOOR A78-30647 decomposing polymers PLASTIC MATERIALS p 0033 A78-19895 U PLASTICS Process for producing a well-adhered durable PLASTIC PROPERTIES optical coating on an optical plastic substrate NT THERMOPLASTICITY --- abrasion resistant polymethyl methacrylate PLASTICS lenses NT ACRYLIC RESINS (NASA-CASE-ARC-11039-1] p0058 N78-32854 NT CARBON FIBER REINFORCED PLASTICS POLYVINYL CHLORIDE NT POLYETHYLENES The prediction of toxic atmospheres from NT POLYMETRYL METHACRYLATE decomposing polymers NT POLYVINYL CHLORIDE pOO33 A78-19895 NT THERMOPLASTIC RESINS POSITIONING DEVICES (MACHINERY) 'T THERMOSETTING RESINS NT BOOMS (EQUIPMENT) ALC/50/ values for some polymeric materials --- POSTFLIGHT ANALYSIS Apparent Lethal Concentration fire toxicity Inhibition of bone formation during space flight p0040 A78-36596 pOO56 A78-51225 PLASTISOLS POTASSIUM COMPOUNDS NT SMOKE Effects of potassium titanate fiber on the wear of PLEXIGLASS (TRADEMARK) automotive brake linings 3 U POLYMETHYL METHACRYLATE pOO 5 A78-23450 POINT HATCHING METHOD (MATHEMATICS) POTENTIAL ENERGY 0 BOUNDARY VALUE PROBEIS NY IONIZATION POTENTIALS POINTING CONTROL SYSTEMS On the possibility of negative activation energies Peaker: An automatic boresight peaking routine in bimolecular reactions for the C-141 telescope [NASA-TM-78509) p0026 N78-29149 rNASA-TM-785163 p0 0 2 8 V78-32856 POTENTIAL FLOW POISBUILLE FLOW A uniqueness proof for a transonic flow problem U LAMINAR FLOW pOOl6 A78-26599 POLLUTANTS An implicit algorithm for the conservative U CONTAMINANTS transonic full potential equation using an POLLUTION arbitrary mesh NT AIR POLLUTION [(IAA PAPER 78-1113) p0O43 ATl-41826 POLYACRYLATES Advanced panel-type influence coefficient methods U ACRYLIC RESINS applied to unsteady three dimensional potential POLYATOMIC MOLECULES flows NT DIATOMIC MOLECULES [AIAA PAPER 78-229] p0021 A78-52630 POLTEENZIMIDAZOLE POTENTIOMETERS Polymeric foams from cross-linkable Angle detector poly-n-arylenebenzimidazoles [NASA-CASE-ARC-11036-l) p0O 6O N78-32395 NASA-CASE-ARC-11008-1) p0050 N78-31232 POWER DENSITY (ELECTROMAGNETIC) POLYETHER RESINS 11RADIANT FLUX DENSITY NT POLYMETHYL METHACRYLATE POWER SPECTRA POLYETHYLENES Energetic protons associated with interplanetary The prediction of toxic atmospheres from active regions 1-5 AU from the sun decomposing polymers p0036 A78-26081 p0033 A78-19895 POYNTING-ROBERTSON EFFECT POLYIMIDE RESINS Radiation pressure and Poynting-Robertson drag for Synthesis of N-substituted bisitaconimi3e monomers small spherical particles --- in interplanetary for use as thermosetting polyimide resins space pO0i A78-36809 pOO33 A78-19766 Low density bismaleimide-carbon microballoon PRECAUTIONS composites --- aircraft and submarine U ACCIDENT PREVENTION compartment safety PREDICTION ANALYSIS TECHNIQUES [NASA-CASE-ARC-11040-2] p0050 N78-27184 Comparison of measured and calculated helicopter POLYMER CHEEISTEI rotor impulsive noise --- wind tunnel test data The prediction of toxic atmospheres from and prediction analysis techniques decomposing polymers [NASA-T-78473] pOO5 N78-20917 pOD33 A78-19895
104 SUBJECT INDEX PROTONS
Prediction of unsteady separated flows on A solution to the surface intersection problem -- oscillating airfoils Boolean functions in geometric modeling p0063 N78-28409 (NASA-CR-152116J pOO 0 B78-19869 Status and future prospects of using numerical Solution of transonic flows by an methods to study complex flows at Nigh Ppynolds integro-differential equation method numbers [NASA-TM-78490] N78-26391 6 p0026 pO02 N78-28410 PROCUREMENT MANAGEMENT PREDICTIONS Application-of a cost/performance measurement NT PERFORMANCE PREDICTION system on a research aircraft project PREHEATING [NASA-TH-78498] pOO07 E78-27043 U HEATING PROGRAM MANAGEMENT PRELOADING U PROJECT MANAGEMENT U PRESTRESSING PROGRAMMING LANGUAGES PREPARATION NT FORTRAN NT PRESTRESSING PROGRAMS PREPOLYMERS NT ASSESS PROGRAM Structural wood panels with improved fire resistance VT NASA PROGRAMS --- using prepolyners and hexamethylenetetramine NT PROJECT SETI [NASA-CASE-ARC-11174-1] pOO50 N78-28178 NT SUPERSONIC CRUISE AIRCRAFT RESEARCH PRESSURE NT TILT ROTOR RESEARCH AIRCRAFT PROGRAM NT BLOOD PRESSURE PROJECT MANAGEMENT NT GAS PRESSURE Critical review of Ames Life Science participation NT HIGH PRESSURE in Spacelab Mission Development Test 3: The SMD NT INLET PRESSURE 3 management study NT RADIATION PRESSURE [NASA-TM-78494-J p0 0 5 1 N78-26973 NT STATIC PRESSURE Application of a cost/performance measurement PRESSURE CABINS system on a research aircraft project U PRESSURIZED CABINS (NASA-TM-78498] pOO0 7 N78-27043 PRESSURE DRAG PROJECT SETI NT SUPERSONIC DRAG A bibliography on the search for extraterrestrial PRESSURE EFFECTS intelligence Reynolds number and pressure gradient effects on [NASA-RP-1021] - pOO51 V78-21019 compressible turbulent boundary layers PROJECTILE CRATERING rAIAA PAPER 78-199] p0033 A78-20741 Microparticle accelerator of unique design --- for PRESSURE GAGES micrometeoroid impact and cratering simulation Buried wire gage for wall shear stress measurements p0036 A78-25264 7 rAIAA 78-798] pOO1 A78-32353 PROJECTILES PRESSURE GRADIENTS Computation of transonic flow past projectiles at Reynolds number and pressure gradient effects on angle of attack compressible turbulent boundary layers [AIAA PAPER 78-1182] pOOC8 A78-41875 (AIAA PAPER 78-199] p0033 A78-20741 PROJECTS An evaluation of several compressible turbulent NT PROJECT SETI boundary-layer models Fffects of pressure PROPELLANT TINKS gradient and Reynolds number Toroidal tank evaluation --- propellant tanks for [AIAA PAPER 78-1160] pUOQ3 A78-41859 spin-stabilized Pioneer spacecraft PRESSURE MEASUREMENTS p0032 A78-17881 Estimating maximum instantaneous distortion from PROPELLANTS inlet total pressure rms measurements NT LIQUID ROCKET PROPELLANTS rAIAA PAPER 78-970] pOO19 A78-43525 PROPELLER FANS PRESSURE PROBES Fuel saving potential of Mach 0.8 twin engine U PRESSURE SENSORS prop-fan transports PRESSURE SENSORS pOO17 A78-31306 A fifty channel electrically scanned pressure module Prop-fan data support study pOO14 A78-17395 (NASA-CR-152141] pOO13 578-27128 PRESSURE SUITS PROPELLERS NT S'ACE SUITS NT PROPELLER FANS PRESSURE TRANSDUCERS PROPORTIONAL COUNTERS U PRESSURE SENSORS Demand-type gas supply system for rocket borne PRESSURE VESSELS thin-wiraow proportional counters Development of a cryogenic rotating heat pipe joint p 0 0 3 1 A78-13845 rNASA-CR-192188] pOO30 N78-33384 PROPULSION PRESSURIZED CABINS NT SPACECRAFT PROPULSION Evaluation of a spacecraft nitrogen generator PROPULSION SYSTEM CONFIGURATIONS [RNASA-CR-152097] po52 N78-23748 Low speed test of a high-bypass-ratio propulsion PRESTRAINING system with an asymnetric inlet designed for a U PRESTRESSING tilt-nacelle V/STOL airplane PRESTRESSING (HASA-CR-152072] pOOS9 N78-17062 Torquing preload in a lubricated bolt Static tests of a large scale swivel nozzle thrust (NASA-TM-78501] p0027 N78-29451 deflector PRETREATMENT [NASA-CE-152091] pOOlh N78-22100 NT PRESTRESSING PROTECTION PRETWISTING NT THERMAL PROTECTION U PRESTRESSING PROTECTIVE CLOTHING PREVENTION NT SPACE SUITS NT ACCIDENT PREVENTION PROTECTIVE COATINGS NT FIRE PREVENTION NT CERAMIC COATINGS PRIVATE AIRCRAFT Reaction cured glass and glass coatings U GENERAL AVIATION AIECRAFT [NASA-CASE-ARC-11051-1] pOO5O N78-32260 PROBABILITY Spray coating apparatus having a rotatable U PROBABILITY THEORY workpiece holder PROBARILITY THEORY [NASA-CZSE-ARC-11110-1) pOO50 578-32434 Earth reencounter probabilities for aborted space PROTEINS disposal of hazardous nuclear waste I NT LIPOPROTEINS 3 8 pOO A78-31921 PROTON ENERGY PROBLEm SOLVING Energetic protons associated with interplanetary NT ITERATIVE SOLUTION active regions 1-5 AU from the sun 3 - Human problem solving performance in a fault pOO 6 A78-26081 diagnosis task PROTONS pOOSU A7-32673 NT SOLAR PROTONS
105 PUBLIC RELATIONS SUBJECT INDEX
PUBLIC RELATIONS RADIATION DISTRIBUTION Requirements for regional short-haul air service Quiet time interplanetary cosmic ray anisotropies and the definition of a flight program to observed from Pioneer 10 and 11 determine neighborhood reactions to small pOO39 A78-34567 transport aircraft RADIATION FIELDS (NASA-CR-152151J pOO13 N78-30070 U RADIATION DISTRIBUTION PULSATING FLOW RADIATION HAZARDS, U UNSTEADY FLOW Earth reencounter probabilities for -aborted' space PUMPS disposal of hazardous nuclear waste iT JET PUMPS p0038 A78-31921 PURSUIT TRACKING RADIATION INTENSITY Coplanar tail-chase aerial combat as a U RADIANT FLUX DENSITY differential game RADIATION MEASURING INSTRUMENTS pOOlI A78-10455 UT INFRARED DETECTORS A preference-ordered discrete-gaming approach to NT INFRARED RADIOMETERS air-combat analysis NT PROPORTIONAL COUNTERS 2 pDO O A78-49255 NT RADIOMETERS PYROGRAPHALLOY NT SPECTROELIOGRAPHS U PYROLYTIC GRAPHITE RADIATION NOISE U REFRACTORY MATERIALS U ELECTROMAGNETIC NOISE PYROLYSIS RADIATION PRESSURE- The Viking biological experiments on Mars Radiation pressure and Poynting-Robertson drag for pg055 A78-39746 small spherical particles --- in interplanetary relative toxicity of the pyrolysis products from space some thermoplastic and thermoset -polymers pOO33 A78-19768 p0042 A78-41213 RADIATION SPECTRA PYROLYTIC GRAPHITE NT ABSORPTION SPECTRA The response of heat-shield materials to intense NT EMISSION SPECTRA laser radiation NT INFRARED SPECTRA rAAA PAPER 78-1381 pO034 A78-22583 NT RAMAN SPECTRA Carbonaceous materials subjected to extreme NT VIBRATIONAL SPECTRA heating - A comparison of numerical simulation NT I RAY SPECTRA and experiments --- Jovian entry conditions RADIATIVE HEAT TRANSPER rAIAA PAPER 78-866] p0041 A78-37273 Nova-driven winds in globular clusters 4 PYROLYTIC MATERIALS pOO 1 A78-37649 NT PYROLYTIC GRAPHITE RADIATIVE TRANSFER QRADICALS HT RADIATIVE HEAT TRANSFER NT HYDROXYL RADICALS QUADRUPOLES RADII Analysis of flight effects on noise radiation from The radii of Uranian rings alpha, beta, gamma, jet flow using a convecting quadrupole model delta, epsilon, eta, 4, 5, and 6 from their rAIAA PAPER 78-192] pOOl5 A78-22594 occultations of 530 158687 QUANTUM MECHANICS p0046 A78-48112 Quantum mechanical theory of a structured RADIO EMISSION atom-diatom collision system - A * BC/1-Sigma/ NT CN EMISSION 0 0 3 1 [AD-A0512661 p A78-16454 NT HYDROXYL EMISSION Quantum mechanical theory of collisional RADIO FREQUENCY DISCEARGE ionization in the presence of intense laser Chemical interpretation of Viking Lander 1 life radiation detection experiment 3 [AD-AO5?9811 p0035 A78-23576 pOO5 A78-25560 RADIO FREQUENCY INTERFERENCE NT ELECTROMAGNETIC NOISE R NT WHISTLERS RADAR ASTRONOMY RADIO FREQUENCY NOISE Saturngs rings: Particle composition and size U ELECTROMAGNETIC NOISE distribution as constrained by microwave RADIO WAVES observations. I - Radar observations NT DECAMETRIC WAVES pOOR6 A78-25676 NT HYDROXYL EMISSION RADIAL DISTRIBUTION NT WHISTLERS The radial dependences of the interplanetary RADIOACTIVE WASTES magnetic field between 1 and 5 AU Pioneer 10 Earth reencounter probabilities for aborted space p0048 A78-52504 disposal of hazardous nuclear waste RADIAL FLOW ' p0038 A78-31921 Stress analysis study in cooled radial inflow RADIOMETERS turbine NT INFRARED DETECTORS [AIAA PAPER 78-94] p0064 A78-22570 NT INFRARED RADIOMETERS RADIANT COOLING Radiometer system to map the cosmic background Thermodynamic processes induced by coherent radiation radiation pO38 A78-30691 p0034 A78-21624 RADIUS RADIANT FLUX DENSITY U RADII NT ELECTRON FLUX DENSITY RAMAN EFFECT Intensities. self-broadening, and broadening by Ar U RAMAN SPECTRA and N2Erfor the 301/II/ - 000 band of C02 RAMAN SCATTERING measured at different temperatures U RAMAN SPECTRA p0046 A78-48425 RAMAN SPECTRA RADIANT INTENSITY Diagrammatic evaluation of the density operator U6,RADIANT FLUX DENSIvY for nonlinear optical calculations RADIATION ADSORPTION (ONERA. TP NO. 1977-166] pOO31 A78-14651 NT PHOTOABSORPTION RANDOM DISTRIBUTIONS NT ULTRAVIOLET ABSORPTION U STATISTICAL DISTRIBUTIONS RADIATION CREMISTRY RARE GAS COMPOUNDS NT PHOTODISSOCIATION Computational study of a molecular collision A new concept in laser-assisted chemistry - The process in the presence of an intense radiation electronic-field representation field - Enhanced quenching of F by Xe in the p0037 A78-27743 248-nm light of the KrF laser RADIATION COUNTERS [AD-A054078) pOO 4 4 A78-42818 NT PROPORTIONAL COUNTERS
106 SUBJECT INDEX RESEARCH MANAGEMENT
RAREFIED GASES REFRACTORY MATERIALS NT INTERSTELLAR GAS BT CHROMIUM RATES (PER TIRE) NT TUNGSTEN NT ACCELERATION (PHYSICS) Fibrous refractory composite insulation -- NT ELECTRON FLUX DENSITY shielding reusable spacecraft HT FLUX DENSITY [NASA-CASE-ARC-11169-1J p0050 N78-32189 NT HEART RATE REFRACTORY METALS NT HIGH GRAVITY ENVIRONMENTS NT CHROMIUM NT LOW SPEED NT TUNGSTEN NT PARTICLE ACCELERATION REFRASIL (TRADEMARK) NT RADIANT FLUX DENSITY U SILICON DIOXIDE NT SOLAR WIND VELOCITY REGIONAL PLANNING NT SUBSONIC SPEED Execative sunmary: Benefit-cost evaluation of an NT SUPERSONIC SPEEDS intra-regional air service in the Bay Area and a NT TRANSONIC SPEED technology assessment of transportation system RATIOS investments --- regional planning for the San NT LIFT DRAG RATIO Francisco Bay area of California NT REYNOLDS NUMBER [NASA-CR-152154-1] pOO13 N78-28988 NT SIGNAL TO NOISE RATIOS A technology assessment of transportation system RATS investments --- Markovian decision theory micro-fluid exchange coupling apparatus --- a (NASA-CR-152154-2) pOO13 N78-28989 microrespirator to allow surgery on rats or mice REGIONS [NASA-CASE-ARC-11114-1] p0060 N78-33717 NT HABITATS REACTION JETS REGULATION U JET FLOW U CONTROL REACTION KINETICS REHEATING Influence of temperature and the role of chromium U HEATING on the kinetics of sulfidation of 310 stainless REINFORCING FIBERS steel Effects of potassium titanate fiber on the wear of 4 3 p00 A78-41796 automotive brake linings Nitric oxide production by Tunguska meteor p0035 A78-23450 p0048 A78-51811 RELATIONSHIPS Arrhenius- law in turbulent media and an NT STRESS-STRAIN RELATIONSHIPS equivalent tunnel effect --- in binary exchange RELAXATION (MECHANICS) chemical reactions NT SPIN-LATTICE RELAXATION p0049 A78-52547 RELIABILITY On the possibility of negative activation energies NT AIRCRAFT RELIABILITY in bimolecular reactions RELIABILITY CONTROL FNASA-TH-78509] p0026 N78-29149 U RELIABILITY ENGINEERING REAL TIME OPERATION RELIABILITY ENGINEERING Measuring the velocity of individual atoms in real Robustness in linear quadratic feedback design time with application to an aircraft control problem pOO35 A78-23124 pO01fi A78-18059 HANDLING qulti-calculation rate simulations REMOTE [NASA-CR-155335] p0009 N78-13765 Study to design and develop remote manipulator REAL VARIABLES systems HT DIFFERENTIAL EQUATIONS [NASA-CR-152092] pO052 N78-16620 NT NONLINEAR EQUATIONS REMOTE SENSORS NT NUMERICAL INTEGRATION The composition of Phobos - Evidence for NT PARABOLIC DIFFERENTIAL EQUATIONS carbonaceous chondrite surface from spectral NT PERIODIC FUNCTIONS .nalysis NT VORTICITY p0032 A78-18874 NT WEIGHTING FUNCTIONS High altitude perspective --- cost-reimbursable RECONNAISSANCE AIRCRAFT services using NASA U-2 aircraft NT F-5 AIRCRAFT [NASA-SP-q273 p0027 N78-31508 NT U-2 AIRCRAFT REPRODUCTIVE SYSTEMS RECOVERABLE SPACECRAFT NT TESTES NT APOLLO SPACECRAFT REPUDLIC MILITARY AIRCRAFT NT SPACE SHUTTLES U MILITARY AIRCRAFT RECURSION FORMULAS RESEARCH U RECURSIVE FUNCTIONS NT DYNAMIC PROGRAMMING RECURSIVE FUNCTIONS NT GAME THEORY Digital filter structures having low errors and NT OPERATIONS RESEARCH simple hardware implementation RESEARCH AIRCRAFT 0 5 6 p0 A78-51346 NT 0-2 AIRCRAFT REDUCTION (CHEMISTRY) Quiet, Short-Haul Research Aircraft - Current An investigation of the reduction of carbon status and future plans dioxide in a silent electric discharge [AIAA PAPER 78-1468 p00 2 0 A78-47916 rNASA-CR-152146] p0053 N78-25767 Conceptual design study of a Harrier V/STOL REENTRY research aircraft NT HYPERSONIC REENTRY [NASA-CR-152086] p0009 N78-19094 NT SPACECRAFT REENTRY Application of a cost/performance, measurement REENTRY SHIELDING system on a research aircraft project Fibrous refractory composite insulation --- [NASA-TM-78498] p00 N78-27043 shielding reusable spacecraft RESEARCH AND DEVELOPMENT rNASA-CASE-ARC-11169-1) p0050 N78-32189 Flight simulation - A vital and expanding REENTRY VEHICLES technology in aircraft development NT APOLLO SPACECRAFT [AIAA PAPER 78-337] p0016 A78-29295 REFERENCE ATMOSPHERES . A method for the analysis of the benefits and Post-Vikinq models for the structure of the summer costs for aeronautical research and technology atmosphere of Kars 0 0 4 7 p0007 N78-29060 p A78-50240 RESEARCH FACILITIES REFLECTANCE Who should conduct aeronautical R and D for the NT SPECTRAL REFLECTANCE Federal Government? REFLECTION [NASA-C--152021] pOOOl N78-10946 NT OPTICAL REFLECTION RESEARCH MANAGEMENT REFLECTORS Who should conduct aeronautical R and D for the NT SOLAR REFLECTORS Federal Government? [NASA-CR-1520211 p0001 H78-10946
107 RESEARCH PROJECTS SUBJECT INDEX
RESEARCH PROJECTS p0033 A78-20223 Ames Research Center Publications-1976 ROCKET PROPELLANT TANKS [NASA-TM-78493] pOOO3 E78-27042 U PROPELLANT TANKS RESINS ROCKET PROPELLANTS NT ACRYLIC RESINS VT LIQUID ROCKET PROPELLANTS NT POLYIMIDE RESINS ROCKET-BODNE INSTRUMENTS NT POLYMETHYL METRACRYLATE Demand-type gas supply system for rocket borne NT THERMOPLASTIC RESINS thin-window-.proportional-counters NT THERMOSETTING-RESINS pOO31 178-138q5 AIC/SO/ values for some polymeric materials --- RODENTS Apparent Lethal Concentration fire toxicity NT MICE p8840 A78-36596 NT RATS RESISTANCE ROLL Extended development of variable conductance heat Effect of a nonconstant C/m-alpha/ on the pipes stability of rolling 2 9 aircraft FNASA-CR-152183] pRO R78-33379 p0031 A78-16180 RESISTANCE COEFFICIENTS ROTARY STABILITY U PESISTANCE New rotation-balance apparatus for measuring RESONANT FREQUENCIES airplane spin aerodynamics in the wind tunnel Collisionless dissociation of SF6 using two (AIAA 78-835] pOO1 7 A78-32386 resonant frequency C02 laser fields 3 An experimental investigation of hingeless pRO 1 A78-14655 helicopter rotor-body stability in hover RESPIRATORS fNASA-TN-78489) p00 6 3 N78-29044 Micro-fluid exchange coupling apparatus --- a ROTARY WING AIRCRAFT microrespirator to allow surgery on rats or mice NT HELICOPTERS (NASA-CASE-ARC-11114-1] pRO60 H78-33717 NT MILITARY HELICOPTERS RESPIRATORY SYSTEM NT XV-15 AIRCRAFT NT TRACHEA Rotorcraft linear simulation model. Volume 1: RESPONSES Engineering documentation FT DYNAMIC RESPONSE fNASA-CR-152079-VOL-1) pOOlO 178-20136 NT HEHODYNAMIC RESPONSES Rotorcraft linear simulation model. Volume 2: NT PHYSIOLOGICAL RESPONSES Computer implementation RETARDANTS [NASA-CR-152079-VOL-2] pOOl0 178-20137 NT FLAME RETARDANTS ROTARY WINGS RETINA NT RIGID ROTORS NT VISUAL PIGMENTS NT TILTING ROTORS RETIREMENT A simplified Mach number scaling law for Factors affecting the retirement of commercial helicopter rotor noise transport jet aircraft pOOl 7 A78-35371 rNASA-CF-152115) pO010 N78-21092 Aeromechanical stability of helicopters with a REUSABLE SPACECRAFT bearingless main rotor. Part 1: Equations of NT SPACE SHUTTLES motion REVISIONS fNASA-T-784591 pOO62 N78-18043 Conceptual design study of a Harrier V/STOL A simple method for estimating minimum research aircraft autorotative descent rate of single rotor 9 [NASA-CR-152086] pOOO H78-19094 helicopters REYNOLDS NUMBER [NASA-TM-78452] pOOS5 B78-20113 Reynolds number and pressure gradient effects on Comparison of measured and calculated helicopter compressible turbulent boundary layers 0 0 3 3 rotor impulsive noise --- wind tunnel test data rAIAA PAPER 78-199] p A78-20741 and prediction analysis techniques The shock tube as a device for testing transonic [NASA-T-78473) pOO0 5 N78-20917 airfoils at high Reynolds numbers- Acoustical effects of blade tip shape changes on a EAIAA 78-769) p0017 A78-32330 full scale helicopter rotor in a wind tunnel An evaluation of several compressible turbulent (NASA-CR-152082] pOOlO N78-20918 boundary-layer models Effects of pressure The effect of tip vortex structure on helicopter gradient and Reynolds number noise due to blade/vortex interaction rAIAA PAPER 78-1160] p0043 A78-41859 [WASA-CR-152150] pOO12 N78-25832 The numerical solution of viscous flows at high An experimental investigation of hingeless Reynolds number helicopter rotor-body stability in hover 6 pOO' A78-46360 [NASA-TM-78489] pOO63 H78-29044 Status and future prospects of using numerical Hovering impulsive noise: Some measured and methods to study complex flows at High Reynolds calculated results numbers p0 0 6 3 N78-32831 pOO26 N78-28410 A study of the noise radiation from four REYNOLDS STRESS helicopter rotor blades --- tests in Ames 40 by Behavior of a turbulent boundary layer subjected 20 foot wind tunnel to sudden transverse strain pOO8 N78-32835 [AInA PAPER 78-201) p0034 A78-22595 Theoretical study of multicyclic control of a Modeling of the Reynolds stresses controllable twist rotor pOO2 H78-19797 [NASA-CR-151959] pOO64 078-33085 RICHARDSON-DUSHMAN EQUATION ROTATING BODIES U TE'PERATURE EFFECTS NT RIGID ROTORS RIGID BODIES NT ROTARY WINGS U RIGID STRUCTURES NT ROTATING CYLINDERS RIGID ROTORS NT ROTATING DISKS Aeromechanical stability of helicopters with a NT TILTING ROTORS bearingless main rotor. Part 1: Equations of An approximate solution for the free vibrations of motion rotating uniform cantilever beams (NASA-TM-78459] p0062 N78-18043 [NASA-T-X-62299] p0063 178-33289 An experimental investigation of hingeless ROTATING CYLINDERS helicopter rotor-body stability in hover Experimental temperature distribution and heat rHASA-T-78489] p0063 H78-29044 load characteristics of rotating heat pipes RIGID STRUCTURES pOOU6 A78-48835 NT RIGID ROTORS Tread drum for animals --- having an electrical Accordion shelter hardware analysis shock station [AD-A053592] pO07 78-28278 [NASA-CASE-ARC-10917-1] pO 5 7 W78-27733 RING STRUCTURES ROTATING DISKS Signal-to-noise ratios for stellar occultations by Bar-driven spiral waves in disk galaxies 3 the rings of Uranus, 1977-1980 pOO 8 A78-32467
108 SUBJECT INDEX SEPARATED FLOW
ROTATING SHAFTS steel Rotary leveling base platform pO043 A8-41796 [NASA-CASE-ARC-10981-1] p0060 N78-27425 SCALE MODELS Development of a cryogenic rotating heat pipe joint Some observations on the mechanism of aircraft rNASA-CR-152188] pOO3O N78-33384 wing rock ROTATING VEHICLES [AIAA PAPER 78-14563 p0020 A78-47907 U ROTATING BODIES SCALING LAWS ROTATION A simplified Mach number scaling law for NT AUTOROTA'ION helicopter rotor noise NT MOLECULAR ROTATION p0017 A78-35371 NT SATELLITE ROTATTON SCANNERS NT SOLAR POTATION A fifty channel electrically scanned pressure module ROTATIONAL FLOW pOO14 A78-17395 U VORTICES SCANNING DEVICES ROTOR AERODYNAMICS U SCANNERS Rotorcraft linear simulation model. Volume 1: SCAR PROGRAM Engineering documentation U SUPERSONIC CRUISE AIRCRAFT RESEARCH rNASA-CR-152079-VOL-l1 pO010 N78-20136 SCATTERING potorcraft linear simulation model. Volume 2:, NT COHERENT SCATTERING Computer implementation NT HALOS rNASA-CR-152079-VOL-2] pOO0 N78-20137 NT LIGHT SCATTERING ROTOR BLADES (TURBOMACHINERY) NT RAMAN SPECTRA An analysis of the rotor blade stresses of the SCF three stage compressor of the Ames Research U SELF CONSISTENT FIELDS Center 11- by 11-foot transonic wind tunnel SCHEDULING rNASA-CR-152083] pOO09 N78-17061 NT PREDICTION ANALYSIS TECHNIQUES A note on multicyclic control by swashplate SCHLIEREM PHOTOGRAPHY oscillation Visualization of quasi-periodic unsteady flows rN&SA-TM-78475I p8085 N78-21159 [LIAA 78-502] pOO16 A78-29804 ROTORCRAFT SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE U ROTARY WING AIRCRAFT U PROJECT SETI ROTONCRAFT AIRCRAFT SEASONAL VARIATIONS Application of special-purpose digital computers U ANNUAL VARIATIONS to rotorcraft real-time simulation SEASONS 7 (NASA-TP-1267] pOOO N78-27113 NT SUMMER ROTORS SEATS NT RIGID ROTORS Fire resistivity and toxicity studies of candidate NT ROTARY WINGS aircraft passenger seat materials NT TILTING ROTORS pOO48 A78-51838 RULES Fire resistivity and toxicity studies of candidate NT FLIGHT RULES aircraft passenger seat materials (NASA-TM-78468] p0024 N78-21214 G-seat system step input and sinusoidal response S characteristics SAFETY [NASA-TM-78478] pDO07 N78-267 1 NT AIRCRAFT SAFETY SECRETIONS NT FLIGHT SAFETY NT ESTROGENS SAFETY DEVICES NT HORMONES NT SPACE SUITS NT SWEAT SAMPLES SEDIMENTS NT MARS SORFACE SAMPLES Meteor ablation spheres from deep-sea sediments SAN FRANCISCO BAY (CA) [NASA-TH-78510] p0028 N78-34021 Planning for airport access: An analysis of the SELF CONSISTENT FIRLDS San Francisco Bay area A theoretical study of the electronic transition rNASA-CP-2044] pOO01 N78-26152 moment for the C2 Swan band system Executive summary: Benefit-cost evaluation of an pOO4l A78-36776 intra-regional air service in the Bay Area and a SELF INDUCED VIBRATION technology assessment of transportation system NT TRANSONIC FLUTTFm investments --- regional planning for the San SELF REGULATING Francisco Bay area of California U AUTOMATIC CONTROL rNASA-CR-152154-1] p00 13 N78-28988 SEMICONDUCTOR DEVICES SATELLITE POWER TRANSMISSION (TO EARTH) NT JUNCTION DIODES Satellite mirror systems for providing terrestrial SEMICONDUCTOR DIODES power - System concept NT JUNCTION DIODES [AAS 77-2401 p0040 A78-36717 SEMICONDUCTORS (MATERIALS) SATELLITE ROTATI6N NT.PEOTOCODUCTORS Fluid interaction with spinning toroidal tanks SEMISPAN MODELS p0024 N78-20186 Computational wing optimization and wied tunnel SATELLITE SOLAR ENERGY CONVERSION test of semi-span model Satellite mirror systems for providing terrestrial [AIAA PAPER 78-102] pDO34 A78-22575 power - System concept SENSE ORGANS [AAS 77-240] p0040 A78-36717 NT LABYRINTH SATELLITE TRANSMISSION SEPARATED FLOW Space industrialization - Education --- via NT BOUNDARY LA!ER SEPARATION communication satellites Thin-layer approximation and algebraic model for rAAS 77-258] pOOOl A78-36722 separated turbulent flows SATELLITES (AIAA PAPER 78-257] p0O33 A78-20776 NT COMMUNICATION SATELLITES Injection slot location for boundary-layer control NT PHOROS in shock-induced separation SATURN RINGS [AIAA PAPER 78-1168] pOoq4 A78-41866 The rings of Saturn A method for localizing wing flow separation at p0036 A78-23646 stall to alleviate spin entry tendencies Saturn's rings: Particle composition and size [AIAA PAPER 78-1476] pDO20 A78-49787 distribution as constrained by microwave Phenomenological aspects of quasi-stationary observations. I - Radar observations controlled and uncontrolled three-dimensional p0036 A78-25676 flow separations --- in relation to aircraft SCALE (CORROSION) design considerations and swept wings Influence of temperature and the role of chromium pOO07 N78-28402 on the kinetics of sulfidation of 310 stainless
109 SEPARATORS SUBJECT INDEX
Introduction to unsteady aspects of separation in SHOCK RAVE PROFILES subsonic and transonic flow 6 The shock tube as a device for testing transonic pOO 3 S78-28403 airfoils at high Reynolds numbers Some unsteady separation problems for slender bodies [AIAA 78-769] pOOl 7 A78-32330 pOO6 3 P78-28405 SHOCK RAVE PROPAGATION Prediction of unsteady separated flows on Calculation of unsteady transonic flows using the oscillating airfoils integral equation method p0063 N78-28409 [AIAA -APER. 78-13] pOO33 A78.2O632 -. 'ymmetrical and asymmetrical separations about a Notes on the transonic indicial method --- for two yawed cone --- tests in the Ames 1.8 x 1.8 wind dimensional airfoil flutter derivative calculation tunnel 8 p0041 A78-37732 (NASA-TM-78532] pOOO N78-32045 SHOCK WAVES SEPARATORS On the relative locations of the bow shocks of the Automatic multiple-sample applicator and terrestrial planets electrophoresis apparatus pO031 A78-13752 rNASA-CASE-ARC-10991-11 pOO57 N78-14104 Numerical solution of a three-dimensional shock SeTI wave and turbulent boundary-layer interaction ' PROJECT SETI [AIAA PAPER 78-161] p034 A78-22591 SEX FACTOR On the observation of a flare-generated shock wave Hormonal indices of tolerance to +Gz acceleration at 9.7 AU by Pioneer 10 in female subjects --- personnel selection in [AD-A053721] p0038 A78-30078 Shuttle program A new method for designing shock-free transonic pOO55 A78-41162 configurations SEX GLANDS [AIAA PAPER 78-1114] pOQ5 A78-45127 nT TESTES Numerical solution of two-dimensional turbulent SHADOWGRAPH PHOTOGRAPHY blunt body flows with an impinging shock 0 0 4 5 NT SCHLIEREN PHOTOGRAPHY [AIAA PAPER 78-1209] p A78-45144 SHARKS SHORT HAUL AIRCRAFT U JOYNTS .(JUNCTIONS) Quiet, Short-Haul Research Aircraft - Current SHARP LEADING EDGES status and future plans Calculation of supersonic viscous flow over delta [AIAA PAPER 78-1468] p0 0 2 0 A78-47916 wings with sharp subsonic leading edges Application of advanced high speed turboprop [NASA-TH-78500] p0025 N78-26101 technology to future civil short-haul transport SHEAR FATIGUE aircraft design 0 0 64 U SHEAR STRESS [AIAA PAPER 78-1487] p A78-47930 SHEAR FLOW Effect of high lift flap systems on the conceptual Propagation of sound through a sheared flow design of a 1985 short-haul commercial STOL tilt 4 f1ASA-CR-152196] pOO1 N78-33876 rotor transport SHEAR PROPERTIES [NASA-TM-78474] pOOD5 N78-21094 Simple torsion test for shear moduli determination Application of advanced technologies to small, of orthotropic composites short-haul aircraft [NASA-TM-78485] p0024 78-21490 [NASA-CR-152089] p0011 $78-22074 SHEAR STRESS A study of commuter airplane design optimization NT TORSIONAL STRESS [tASA-CR-1572101 pOO11 78-25078 Buried wire gage for wall shear stress measurements Short-haul CTOL aircraft research --- on reduced rAIAA 78-798] pOO17 A78-32353 energy-for commercial air transportation SHEARING STRESS pOOOS N78-29061 U SHEAR STRESS Requirements for regional short-haul air service SHELTERS and the definition of a flight program to Accordiop shelter hardware analysis determine neighborhood reactions to small EAD-AO535921 pOO07 N78-28278 transport aircraft SHIELDING [NASA-CR-152151] pOO1 3 H78-30070 IT HEAT SHIELDING SHORT TAKEOFF AIRCRAFT NT REENTRY SHIELDING Robustness in linear quadratic feedback design NT SPACECRAFT SHIELDING with application to an aircraft control problem SHIPS pOO14 A78-18059 NT SUBMARINES Robustness of linear quadratic state feedback SHOCK DISCONTINUITY designs in the presence of system uncertainty Unsteady transonic flow computations --- application to Augmentor Wing Jet STOL pOO32 A78-18274 Research Aircraft flare control autopilot design SHOCK TUBES pOO16 A78-23917 Shock-tube studies of atomic silicon emission in Effects of inlet airframe integration on the inlet the spectral range 180 to 300 nm --- environment of an upper surface blowing four-engine STOL simulation for Jupiter probes aircraft rAIAA PAPER 78-234] pOO34 A78-22602 [ATAA PAPER 78-959] pOO18 A78-43521 The shock tube as a device for testing transonic Effect of high lift flap systems on the conceptual airfoils at high Reynolds numbers design of a 1985 short-haul commercial STOL tilt FAIAA 78-769] pOO17 A78-32330 rotor transport A study of test section configuration for shock [NASA-TM-78474] p0O05 N78-21094 tube testing of transonic airfoils A flight investigation of the stability, control, 2 [NASA-CR-157237] pOO1 578-26153 and handling qualities of an augmented jet flap SHOCK WAVE CONTROL STOL airplane Transonic lifting line theory - Numerical [NASA-TP-1254] pOO06 N78-26151 procedure for shock-free flows Study to determine operational and performance p017 A78-37742 criteria for STOL aircraft operating in low SHOCK WAVE GENERATORS visibility conditions NT SHOCK TUBES [NASA-CR-152164] pOO13 F78-28083 SHOCK WAVE INTERACTION SHUTTLE ORBITERS Thin-layer approximation and algebraic model for U SPACE SHUTTLE ORBITERS separated turbulent flows SIDERITE METEORITES 0 0 3 3 [AIAA PAPER 78-257] p A78-20776 U IRON METEORITES Comparison of multieguation turbulence models for SIDESLIP several shock-separated boundary-layer Low speed aerodynamic characteristics of an interaction flows 0.075-scale F-15 airplane 0 0 4 3 model at high angles rAIAA PAPER 78-1165) p A78-41863 of attack and sideslip A detailed study of attached and separated [NASA-TMX-62360) pOOO4 N78-lOU compression corner flowfields in high Reynolds Low-speed aerodynamic characteristics of a number supersonic flow 0.08-scale YF-17 airplane model at high angles 4 3 rAIAA PAPER 78-1167] pOO A78-41865 of attack and sideslip
• 110 SUBJECT INDEX SOLAR SYSTEM
CIASA-TM-78438] p006 N78-22025 projects SIGNAL ENCODING [NASA-TS-78472] p0025 N78-24000 Survey of adaptive image coding techniques SOCIOLOGY pOO31 A78-15267 NT SOCIAL FACTORS SIGNAL PROCESSING SOFT LANDING SPACECRAFT Digital filter structures having low errors and NTAPOLLO SPACECRAFT simple hardware implesentation SOFTWARE (COMPUTERS) POOSS A7-51346 U COMPUTER PROGRAMS SIGNAL TO POISE RATIOS SOILS Signal-to-noise ratios for stellar occultations by HT LUNAR SOIL the rings of Uranus, 1977-1980 Comparison between infrared Martian disk spectra p0033 A78-2D223 and optical properties of terrestrial analogs SIGNAL TRANSMISSION pO047 A78-49231 NT BIOTELEMETRY Degradation of biochemical activity in soil NT SATELLITE TRANSMISSION sterilized by dry heat and gamma radiation SILICA pOO57 A78-53874 U SILICON DIOXIDE SOLAR ACTIVITY ,SILICON NT SOLAR FLARES Shock-tube studies of atomic silicon emission in SOLAR ACTIVITY EFFECTS the spectral range 180 to 300 no --- environment Dynamic MUD modeling of the solar wind simulation for Jupiter probes disturbances during the Angust 1972. events !AIAA PAPER 78-234] pOO3 A78-22602 p0036 A78-26079 SILICON COMPOUNDS SOLAR COLLECTORS NT SILICON DIOXIDE VT SOLAR REFLECTORS SILICON DIOXIDE SOLAR CORONA Aerothermodynamic environment for Jovian entry The quiet coronal X-ray spectrum of highly ionized with silica heat shield oxygen and nitrogen 3 (AIAA PAPER 78-186] p00 3 A78-20730 p0038 A78-311D08 Fibrous refractory composite insulation --- Rigidity-independent coronal propagation and shielding reusable spacecraft escape of solar protons and alpha particles 0 4 ([ASA-CASE-ARC-11169-1] pO050 N78-32189 p0 1 A78-37354 SILICON OXIDES SOLAR CORPUSCULAR RADIATION NT SILICON DIOXIDE HT SOLAR PROTONS STITS SOLAR FLARES U SEDIMENTS Dynamic MUD modeling of the solar wind SIMILARITY THEOREM disturbances during the August 1972 events NT LAGRANGE SIMILARITY HYPOTHESIS p0036 A78-26079 SIMULATED ALTITUDE on the observation of a flare-generated shock wave U ALTITUDE SIMULATION at 9.7 AU by Pioneer 10 SIMULATION [AD-A053721] pO038 A78-30078 NT ALTITUDE SIMULATION Rigidity-independent coronal propagation and NT COMPUTERIZED SIMULATION escape of solar protons and alpha particles NT CONTROL SIMULATION pO004 A78-37354 NT DIGITAL SIMULATION SOLAR INSTRUMENTS NT PLIGHT SIMULATION NT SPECTROHELIOGRAPHS NT SPACE ENVIRONMENT SIMULATION SOLAR MAGNETIC FIELD NT THERMAL SIMULATION Dynamic MHD modeling of the solar wind Aircraft cargo compartment fire test simulation disturbances during the August 1972 events program pOC3 6 A78-26079 CNASA-CR-151951] p0029 N78-21223 SOLAR NEBULA SIMULATORS U SOLAR CORONA NT COCKPIT SIMULATORS SOLAR PLASMA (RADIATION) NT CONTROL SIMULATION U SOLAR WIND NT FLIGHT SIMULATORS SOLAR PROBES NT MOTION SIMULATORS Pioneer 10 observation of the solar wind proton NT SPACE SIMULATORS temperature heliocentric gradient SKIN FRICTION [NASA-TM-78515] p0027 N78-31030 NT AERODYNAMIC DRAG SOLAR PROTONS NT SUPERSONIC DRAG Energetic protons associated with interplanetary SKY RADIATION active regions 1-5 AU from the sun NT AIRGLOW p0036 A78-26081 SKY WAVES Rigidity-independent coronal propagation and NT WHISTLERS escape of solar protons and alpha particles SLENDER BODIES p 00 4 1 A78-37354 Wake vortex measurements of bodies at high angle Pioneer 10 observation of the solar wind proton of attack temperature heliocentric-gradient [AIAA PAPER 78-23] p0015 A78-22555 [NASA-TM-78515] p0027 N78-31030 Computation of transonic flow past projectiles at SOLAR RADIATION angle of attack NT SOLAR PROTONS 4 [ATAA PAPER 78-1182] p0O 4 A78-41875 NT SOLAR WIND Some unsteady separation problems for slender bodies NT SOLAR I-RAYS pOO63 N78-28405 Radiation pressure and Poynting-Robertsen drag for SLENDER WINGS small spherical particles --- in interplanetary Transonic lifting line theory - Numerical space procedure for shock-free flows p0033 A78-19768 pOOl7 A78-37742 SOLAR REFLECTORS SMALL PERTURBATION FLOW Satellite mirror systems for providing terrestrial Displacement thickness distributions in transonic power - System concept flows about 3-D wings 3 [AAS 77-240] pOOCO A78-36717 p00 2 A78-17612 SOLAR ROTATION A uniqueness proof for a transonic flow problem Dynamic MUD modeling of solar wind corotating 0 1 p 0 6 A78-26599 stream interaction regions observed by Pioneer Lifting line theory for transonic flow 10 and 11 pOO2O A78-48991 pOO49 A78-52522 SMOKE SOLAR SYSTEM Fire detector response in aircraft applications 4 Radiometer system to map the. cosmic background p0O 9 A78-53674 radiation SOCIAL FACTORS p0038 A78-30691 A review of NAS-sponsored technology assessment SOLAR WIND SUBJECT INDEX
SOLAR WIND SPACE PLIGHT on the relative locations of the bow shocks of the HT APOLLO 12 FLIGHT terrestrial planets NT HYPERSONIC REENTRY p001 A78-13752 NT SPACECRAFT REENTRY Dynamic MHD modeling of the solar wind SPACE INDUSTRIALIZATION disturbances during the August 1972 events Space industrialization - Education --- via pOO36 A78-26079 communication satellites Acceleration of nucleons in the interplanetary (-AAS 77-258] pOO01 A78-36722 -space and the "modulation of Jupiter electrons in SPACE LOGISTICS the interval from 1 to 10 A.U. by corotating Space habitats --- prognosis for space colonization regions of solar origin pOO56 A78-49780 pU037 A78-29684 SPACE MISSIONS The spiral field inhibition of thermal conduction Earth reencounter probabilities for aborted space in two-fluid solar wind models 0 disposal of hazardous nuclear waste p 046 A78-48281 p0038 A78-31921 Dynamic MHD modeling of solar wind corotating SPACE PHOTOGRAPHY stream interaction regions observed by Pioneer U SPACEBORNE PHOTOGRAPHY 10 and'll SPICE PROBES p0049 A78-52522 NT JUPITER PROBES Pioneer 10 observation of the solar wind proton NT PIONEER SPACE PROBES temperature heliocentric gradient NT PIONEER 10 SPACE PROBE [NASA-TM-78515] p0027 N78-31030 RT PIONEER 11 SPACE PROBE Acceleration and heating of the solar wind SOLAR PROBES 2 9 NT p00 P78-329911 N VENUS PROBES SOLAR WIND VELOCITY SPACE SHUTTLE ORBITERS The interplanetary modulation and transport of Static and dynamic stability analysis of the space Jovian electrons shuttle vehicle-orbiter pO036 A78-26080 [NISA-TP-1179] p0005 H78-20176 SOLAR X-RAYS SPACE SIUTTLE PAYLOADS The quiet coronal X-ray spectrum of highly ionized NT SPACELAB oxygen and nitrogen SPACE SHUTTLES p0038 A78-31108 Hormonal indices of tolerance to +Gz acceleration SOLID ROTATION in female subjects --- personnel selection in U ROTATING BODIES Shuttle program SOLID STATE DEVICES p0055 A78-41162 NT JUNCTION DIODES SPACE SIMULATORS SOLID SURFACES Continuous metabolic and cardiovascular Study of a high performance evaporative heat measurements on a monkey subject during a transfer surface simulated 6-day Spacelab mission 2 8 rNASA-CR-152008] pO0 B78-10411 p0 0 5 6 A78-48719 SOLUTIONS SPACE SUITS NT DETONABLE GAS MIXTURES Spacesuit mobility knee joints SONIC FLOW [NASA-CASE-ARC-i1058-2) p0057 N78-18763 U TRANSONIC FLOW Spacesuit mobility joints SORBENTS [NASA-CASE-ARC-11058-1] p0058 H78-31735 NT ABSORBENTS Spacesuit torso closure SORPTION [NASA-CASE-ARC-11100-1) pOO58 N78-31736 NT ADSORPTION SPACE TRANSPORTATION SYSTEM NT CHEMISORPTION NT SPACE SHUTTLE ORBITERS SORTIE CAN NT SPACE SHUTTLES U SPACELAD SPACE VEHICLES SORTIE LAB U SPACECRAFT U SPACELAB SPACEBOBNE PHOTOGEAPEY SOUND Some Martian volcanic features as viewed from the U ACOUSTICS Viking orbiters SOUND GENERATORS p0030 A78-11403 Non-linear parametric generation of sound by SPACECRAFT resonant mode conversion Experimental investigation of contamination (AD-A0491571 pOO59 P78-19901 prevention techniques to cryogenic surfaces on SOUND MEASUREMENT board orbiting spacecraft U ACOUSTIC MEASUREMENTS [NASA-CH-152171] pOO29 N78-29146 SOUND PBOPAGATION SPACECRAFT CABIN ATMOSPHERES Acoustical effects of blade tip shape changes on a Evaluation of a spacecraft nitrogen generator full scale helicopter rotor in a wind tunnel [NASA-CR-152097] p0052 N78-23748 rNASA-CR-152082] pOO10 N78-20918 SPACECRAFT CONTAMINATION Propagation of sound through a sheared flow Theoretical contamination of cryogenic 4 satellite CNASA-CR-152196] pOO1 H78-33876 telescopes SOUND WAVES [NASA-TP-1177] p0024 N78-21193 NT AERODYNAMIC NOISE SPACECRAFT DESIGN NT AIRCRAFT NOISE Toroidal tank evaluation --- propellant tanks for NT ENGINE NOISE spin-stabilized Pioneer spacecraft NT JET AIRCRAFT NOISE p0032 A78-17881 SPACE BASES Thermal design and development of a planetary NT SPACE COLONIES probe - Pionee Venus large probe SPACE BIOLOGY [AIRA PAPER 78-916] p0041A78-37275 U EXOBIOLOGY Entry dynamics performance predictions for Pioneer SPACE COLONIES Venus probes Space colonization - Some physiological perspectives [AIAA 78-1370] p0046 A78-46557 p0055 A78-41164 SPACECRAFT INSTRUMENTS Space habitats --- prognosis for space colonization Synthesis of porous polyaromatic column packings pOO56 A78-49780 for GC anlalysis of extraterrestrial atmospheres SPACE ENVIRONMENT p0055 A78-48577 U AEROSPACE ENVIRONMENTS SPACECRAFT POWER SUPPLIES SPACE ENVIRONMENT SIMULATION C02 laser-driven Stirling engine --- space power Shock-tube studies of atomic silicon emission in applications the spectral range 180 to 300 am --- environment p0021 A78-49804 simulation for Jupiter probes 4 SPACECRAFT PROPULSION [AIAA PAPER 78-234) p003 A78-22602 Study, optimization, and design of a laser heat engine
112 SUBJECT INDEX STAGNATION REGION
FNASA-CR-152104] p000q N78-19481 SPECTROMETERS SPACECRAPT REENTRY NT SPECTRONELIOGRAPHS Earth reencounte probabilities for aborted space SPECTEOPHOTOMETRY disposal of hazardous nuclear waste NT STELLAR SPECTROPHOTOMETRY p0038 A78-31921 SPECTROSCOPY A method for determining structural properties of NT INFRARED SPECTROSCOPY PCC thermal protection material --- Reinforced NT OPTICAL EMISSION SPECTROSCOPY Carbon-Carbon NT STELLAR SPECTROPHOTOMETRY 0 0 4 0 rAIAA PAPER 78-869] p A78-35997 SPEED INDICATORS SPACECRAFT SENSORS NT HOT-WIRE ANEMOMETERS N SPACECRAFT INSTRUMENTS SPHERULES SPACECRAFT SEIELDIEG Meteor ablation spheres from deep-sea sediments Aerothermodynamic environment for Jovian entry [NASA-TM-78510] p028 N78-34021 with silica heat shield SPIN rAIAA PAPER 78-186] p0033 A78-20730 NT SPIN-ORBIT INTERACTIONS Jupiter probe heatsbield configuration optimization SPIN DYNAMICS rArAA PAPER 78-843] p0041 A78-37270 Influence Of spin rate on side force of an axisymmetric body Carbon vaporization into a noneguilibrium, 3 stagnation-point boundary layer pOO 8 A78-30690 p0 0 4 2 A78-40838 New rotation-balance apparatus for measuring SPACECRAFT STRUCTURES airplane spin aerodynamics in the wind 7tunnel Magnetometer deployment mechanism for Pioneer Venus [ATAA 78-8353 pOO1 A78-32386 p0023 N78-19029 SPIN STABILIZATION SPACELAB Toroidal tank evaluation --- propellant tanks for spin-stabilized Pioneer spacecraft Continuous metabolic and cardiovascular 3 2 measurements on a monkey subject during a pRO A78-17881 simulated 6-day Spacelab mission A historical overview of stall/spin p056 A78-48719 characteristics of general aviation aircraft NASA/ERA CV-990 spacelab simulation (ASSESS 2) [ARIAA PAPER 78-1551] pOOlS A78-46514 3 0 2 7 [ASA-TM-7978] p H78-30149 SPIN-LATTICE RELAXATION SPACELAB PAYLOADS Square Ising ferromagnetic and antiferromagnetic NT POINTING CONTROL SYSTEMS lattices in a magnetic field - A new Critical review of Ames Life Science participation perturbation approach in Spacelab Mission Development Test 3: The SME p0056 A78-51886 3 management study SPIN-ORBIT INTERACTIONS (NASA-Tn-78494] pO051 N78-26973 Quantum mechanical theory of a structured system - A + BC/1-Sigma/ SPACELAB SIMULATION PLIGHTS atom-diatom collision 0 0 3 1 U ASSESS PROGRAM [AD-A051266] p A78-16454 SPARWISE BLOWING SPLASHING NT BLOWING A note on multicyclic control by swashplate SPATIAL DISTRIBUTION oscillation NT STAR DISTRIBUTION (NASA-TM-'8475] pOO05 P78-21159 Geographical variations of NO and 03 in the lower SPONTANEOUS EMISSION stratosphere Semiclassical approach to collision-induced p0039 A78-35403 emission in the presence of intense laser SPATIAL ISOTROPY radiation - An aspect in the study of U SPATIAL DISTRIBUTION cooperative chemical and optical pumping SPECTRA pO037 A78-27744 NT ABSORPTION SPECTRA SPRAYED COATINGS NT EMISSION SPECTRA Spray coating apparatus having a rotatable NT ENERGY SPECTRA workpiece holder NT INFRARED SPECTRA [NASA-CASE-ARC-1111O-1] pooo N78-32434 NT MOLECULAR SPECTRA SPRAYED PROTECTIVE COATINGS NT NOISE SPECTRA U PROTECTIVE COATINGS NT POWER SPECTRA U SPRAYED COATINGS NT RAMAN SPECTRA SPRAYERS NT SWAN BANDS Spray coating apparatus having a rotatable NT VIBRATIONAL SPECTRA workpiece holder NT X RAY SPECTRA [NASA-CASE-ARC-11110-1] p0O5O N78-32434 SPECTRAL ABSORPTION SPRAYING APPARATUS U ABSORPTION SPECTRA U SPRAYERS SPECTRAL BANDS SPRAYS NT ABSORPTION SPECTRA U SPRAYERS NT SWAN BANDS STABILITY SPECTRAL ,INE WIDTH NT AERODYNAMIC STABILITY Intensities, sel.-brncdening. and broadening by Ar NT AIRCRAFT STABILITY and N2 for the 301/111/ - 000 band of C02 NT CONTROL STABILITY measured at different temperatures 0 0 4 6 NT DYNAMIC STABILITY p A78-48425 NT FLOW STABILITY Measurement at different temperatures of absolute NT HOVERING STABILITY intensities, line half-widths, and broadening by NT MAGNETOSPHERIC INSTABILITY Ar and V2 for the 30 0 1 II--00 0 0 band of C02 NT MOTION STABILITY p0047 A78-50489 NT ROTARY STABILITY SPECTRAL REFLECTAECE . NT STATIC STABILITY The composition of Phobos - Evidence for STABILITY TESTS carbonaceous chondrite surface from spectral An experimental investigation of hingeless in hover analysis helicopter rotor-body stability 00 63 p003 2 A78-18874 [NASA-TM-78489] p N78-29044 Multicolor observations of Phobos with the Viking STABILIZATION lander cameras - Evidence for a carbonaceous NT SPIN STABILIZATION chondritic composition STABILIZED PLATFORMS p0032 A78-18875 Rotary leveling base platform SPECTROHELIOGRAPHS [NASA-CASE-ARC-10981-1) p0060 N78-27425 The quiet coronal X-ray spectram of highly ionized STAGNATION POINT oxygen and nitrogen Carbon vaporization into a nonequilibrium p0038 A78-31108 stagnation-point boundary layer 0 0 4 2 SPECTSOHELIOSCOPES p 178-40838 U SPECTROHELIOGRAPBS STAGNATION REGION U STAGNATION POINT
113 STAINLESS STEELS SUBJECT INDEX
STAINLESS STEELS C3 and infrared spectrophotometry of Y Canum NT AUSTENITIC STAINLESS STEELS Venaticorum 2 STANDARD ATMOSPHERES p004 178-39448 s REFERENCE ATMOSPHERES Infrared excesses in early-type stars - Gamma STANDARDS Cassiopeiae NT REFERENCE ATMOSPHERES p0047 A78-49475 STAR DISTRIUTION STELLAR WINDS ISAs and the dwarf content of the inner nuclear Nova-driven winds-in globular clusters 1 -regions of N31 --- Intrinsic Strengfh Anomalies pO4 A78-37649 p0042 A78-38569 STERILIZATION STAR FIELDS Degradation of biochemical activity in soil U STAR DISTRIBUTION sterilized by dry heat and gamma radiation 7 STARS p005 A78-53874 NT B STARS STIFF STRUCTURES NT CARBON STARS U FIGID STRUCTURES NT DWARF STARS STIMULATED EMISSION NT EARLY STARS Semiclassical approach to collision-induced NT LATE STARS emission in the presence of intense Inner NT NOVAE radiation - An aspect in the study of and optical pumping STATE EQUATIONS cooperative chemical 0 0 3 7 O EQUATIONS OF STATE p A78-27744 STATIC PRESSURE Stimulated emission of surface plasmons by Two-dimensional transonic testing with splitter electron tunneling in metal-barrier-metal plates structures rMASA-TP-1153] pOO04 N78-17999 p0038 A78-3O647 STATIC STABILITY Computational study of a molecular collision Static and dynamic stability analysis of the space process in the presence of an intense radiation shuttle vehicle-orbiter field - Enhanced quenching of F by Xe in the [NASA-TP 1179] pOOO5 N78-20176 248-nm light of the Kr? laser STATIC TESTS rAD-A0540781 pO044 A78-42818 Static tests of a large scale swivel nozzle thrust STIMULATED EMISSION DEVICES deflector NT CARBON DIOXIDE LASERS [NASA-CP-152091] pOO11 N78-22100 NT CHNNICAL LASERS STATISTICAL DISTRIBUTIONS NT CONTINUOUS WAVE LASERS Interpreting statistics of small lunar craters NT DYE LASERS pO04 2 A78-41753 NT GAS LASERS STATISTICAL PROBABILITY NT TWO-WAVELENGTH LASERS U PROBABILITY THEORY STIRLING CYCLE STATOR BLADES C02 laser-driven Stirling engine --- space power Use of leaning vanes in a two stage fan applications (IASA-CP-15213$ pOO10 N78-21115 p0021 A78-49804 STEELS STOCHASTIC PROCESSES NT AUSTENITIC STAINLESS STEELS NT MARKOV PROCESSES NT CARBON STEELS STOL AIRCRAFT STEEP GRADIENT AIRCRAFT U SHORT TAKEOFF AIRCRAFT U V/STOL AIRCRAFT STONY METEORITES STELLAR CORONAS NT TUNGUSK METEORITE NT SOLAR CORONA STORABLE PROPELLANTS STELLAR EVOLUTION NT AIRCRAFT FUELS Evolution of rotating interstellar clouds. III STRAIN DISTRIBUTION on the formation of multiple star systems U STRESS CONCENTRATION - p0047 A78-49471 STRATA STELLAR FIELDS NT SUBSTRATES U STAR DISTRIBUTION STRATOSPHERE STELLAR MAGNETIC FIELDS Airborne infrared interferometric observations and NT SOLAR MAGNETIC FIELD analysis of stratospheric trace constituents STELLAR MOTIONS EAIAAPAPEr 78-252] pOO03 A78-22606 Numerical experiments on the stability of disklike Lower stratosphere measurements of variation with galaxies latitude of CF2Cl2, CFCl3, CC14, and N20 pOOs A78-45535 profiles in the northern hemisphere On the stability of disklike galaxies in massive p0035 A78-23610 Geographical variations of NO and 03 in the lower halos 2 pOO 0 A78-47354 stratosphere 0 3 9 STELLAR OCCULTATION p 0 A78-35403 Occultation of Epsilon Geminorum by Mars. II - The Stratospheric measurements of CP2C12 and N20 structure and extinction of the Martian upper p0054 A7-37055 atmosphere Stratospheric NO and HN03 observations in the p003O A78-10587 Northern Hemisphere for three seasons 2 Signal-to-noise ratios for stellar occultations by p0O4 A78-41123 ,the rings of Uranus, 1977-1980 Meteorological control of lower stratospheric p0033 A78-20223 minor species variations - An observational Analysis of stellar occultation data - Effects of example .photon noise and initial conditions --- pOO19 A78-46011 planetary atmosphere temperature, pressure and Calculated rate constants for the reaction C1o * 0 density profiles from occultation light curve yields Cl + 02 between 220 and 1000 deg E-- stratospheric ozone p0035 A78-23164 molecular trajectories and 4 The radii of Uranian rings alpha, beta, gamma, rNASA-TM-7 #3] p002 N78-21215 delta, epsilon, eta, 4, 5, and 6 from their An assessment of the effect of supersonic aircraft operations on the stratospheric ozone content occultations of SAO 158687 0 p004 6 A78-48112 fNASA-RP-1026] p0 27 N78-30774 STELLAR RADIATION Are the stratospheric dust particles meteor NT STELLAR WINDS ablation debris or interplanetary dust? 2 8 STELLAR ROTATION (NASA-TM-78507] p00 N78-34014 NT SOLAR ROTATION STREAMLINE FLOW STELLAR SPECTROPHOTOMETRY U LAMINAR FLOW Airborne photometric observations between 1.25 and STRENGTH OF MATERIALS 3.25 microns of late-type stars U MECHANICAL PROPERTIES pOO36 A78-25295 STRESS (PHYSIOLOGY) Regulation of the adrenal cortex function during
114 SUBJECT INDEX SUPERSONIC FLOW
stress flight data analysis. Volume 2: Plotted power [NASA-CR-157397] pOO53 E78-30808 spectra STRESS ANALYSIS (NASA-C-152113] p0 013 B78-33117 Stress analysis study in cooled radial inflow An investigation of wing buffeting response at turbine 0 64 subsonic and transonic speeds. Phase 2: F-111A (AIAA PAPER 78-94] pO A78-22570 flight data analysis. Volume 3: Tabulated An analysis of the rotor blade stresses of the power spectra three stage compressor of the Ames Research (RSA-CR-152114] pO014 H7-33118 Center 11- by 11-foot transonic wind tunnel SUBSTRATES fNASA-CR-152083] p0009 V78-17061 Process for producing a vell-adhered durable STRESS CALCULATIONS optical coating on an optical plastic substrate U STRESS ANALYSIS --- abrasion resistant polymethyl methacrylate STRESS CONCENTRATION lenses Behavior of a turbulent boundary layer subjected [NASA-CASE-AC-11039-1] pOO58 N78-32854 to sudden transverse strain 4 SUITS rAIAA PAPER 78-201] p003 A78-22595 NT SPACE SUITS STRESS DISTRIBUTION SULFATES U STRESS CONCENTRATION Stability of chromium (II1) sulfate in atmospheres STRESS MEASUREMENT containing oxygen and sulfur Buried wire gage for wall shear stress measurements [ENASA-TM-785C41 p0026 P78-28173 [AIAA 78-798] pOOl7 A78-32353 SULFIDES STRESS-STRAIN DISTRIBUTION NT HYDROGEN SULFIDE U STRESS CONCENTRATION Influence of temperature and the role of chromium STRESS-STRAIR RELATIONSHIPS on the kinetics of sulfidation of 310 stainless Stress-strain behavior of some acrylic gradient steel polymers pO043 A78-41796 [AD-A052617] pOO59 V78-24364 SULFUR STRESSES Stability of chromium (III) sulfate in atmospheres NT REYNOLDS STRESS containing oxygen and sulfur NT SHEAR STRESS [WASA-TM-78504] p0026 H78-28173 HT THER HAL STRESSES SULFUR COMPOUNDS NT TORSIONAL STRESS VT CYSTREIE STRUCTURAL ANALYSIS NT HYDROGEN SULFIDE NT DYNAMIC STRUCTURAL ANALYSIS NT SULFATES NT FLUTTER ANALYSIS NT SULFIDES A method for determining structural properties of NT SULFUR FLUORIDES RCC thermal protection material --- Reinforced SULFUR PLUORIDRS Carbon-Carbon Collisionless dissociation of SF6 using two [AIAA PAPER 78-869] p0040 A78-35997 resonant frequency C02 laser fields STRUCTURAL BEAMS p0031 A78-14655 q BEAMS (SUPPORTS) SUMMARIES STRUCTURAL DYNAMICS NT ABSTRACTS ITDYNAMIC STRUCTURAL ANALYSIS SUMMER STRUCTURAL ERMBERS Post-Viking models for the structure of the summer HT BEAMS (SUPPORTS) atmosphere of Mars NT CANTILEVER BEAMS p 0 04 7 A78-50240 HT FLAT PLATES SUPERCEITICAL WINGS NT WING PANELS A new method for designing shock-free transonic STRUCTURAL VIBRATION configurations NT TRANSONIC FLUTTER [AIAA PAPER 78-1114] pO045 A78-45127 The general solution to the classical problem of SUPERSONIC AIRCRAFT the finite Euler-Bernoullibeam NT F-5 AIRCRAFT 0 0 4 7 p 178-50909 NT F-15 AIRCRAFT Theoretical study of multicyclic control of a HT F-111 AIRCRAFT controllable twist rotor HT SUPERSONIC TRANSPORTS fNASA-CR-151959] pOO64 H78-33085 High performance dash-on-warning air mobile SUBLAYERS missile system --- first strike avoidance for U SUBSTRATES retaliatory aircraft-borne ICBM counterattack SUBMARINES (AIAA 78-1353) p0019 A78-46545 Low density bismaleimide-carbon microballoon High angle of incidence implications upon air composites -- aircraft and submarine intake design and location for supersonic cruise compartment safety aircraft and highly maneuverable transonic .[NASA-CASE-ARC-11040-2] pOO50 178-27184 aircraft SUBROUTINES [RASA-TE-78530] pg08 N78-32044 10: A FORTRAN direct access data management system SUPERSONIC BOUNDARY LAYERS pO060 P70-33784 Reynolds number and pressure gradient effects on SUBSONIC FLOW compressible turbulent boundary layers Advanced panel-type influence coefficient methods [IAA PAPER 78-199] p0033 A78-20741 applied to unsteady three dimensional potential An evaluation of several compressible turbulent flows 1 boundary-layer models Effects of pressure [AIAA PAPER 78-2291 p002 A78-52630 gradient ad Reynolds number A Mach line panel method for computing the (AIAA PAPER 78-11603 p0043 A78-41859 An experimental documentation linearized supersonic flow over planar 2wings of pressure gradient rNASA-CR-152126] p001 N78-27087 and Reynolds number effects on compressible Introduction to unsteady aspects of separation in turbulent boundary layers subsonic and transonic flow 0 6 3 [NASA-TH-78488] p0026 N78-27364 p0 978-28403 SUPERSONIC CRUISE AIRCRAFT RESEARCH Closed-form equations for the lift, drag, and High angle of incidence implications upon air pitching-moment coefficients of airfoil sections intake design and location for supersonic cruise in subsonic flow aircraft and highly maneuverable transonic TNASA-TK-78492] po 0 8 178-29068 aircraft SUBSONIC SPEED [(ASA-TM-78530J p0008 N78-32044 An investigation of wing buffeting response at SUPERSONIC DRAG subsonic and transonic speeds: Phase 1: F-llA Three-dimensional canard-wing shape optimization flight data analysis. Volume 1: summary of in aircraft crise and maneuver environments technical approach, results and conclusions [AIAA PAPER 78-99] 3 pO016 A78-26274 (NASA-CR-1521093 pOO1 N78-33113 SUPERSONIC FLOW An investigation of wing buffeting response at Numerical solution of a three-dimensional shock subsonic and transonic speeds. Phase 2: F-111A wave and turbulent boundary-layer interaction
115 SUPERSONIC SPEEDS SUBJECT INDEX
[AIAA PAPER 78-1611 pO034 A78-22591 SYNTHETIC RESINS Computation of the viscous supersonic flow over NT ACRYLIC RESINS symmetrical and asymmetrical external axial NT POLYMETHYL METHACRILATE corners NT THERMOPLASTIC RESINS 3 [AIAA PAPER 78-1135] p084 A76-41839 VT THERMOSETTING RESINS Calculation of supersonic viscous flow over delta SYSTEM EFFECTIVEBESS wings with sharp subsonic leading edges Human problem solving performance in a fault 0 0 [AIAA PAPER 78-1137] p 43 A78-4184_1 diagnosis task A detailed study of--attached'and separated pOO5 178-32673 compression corner flowfields in high Reynolds SYSTEMS ANALYSIS number supersonic flow Study to design and develop remote manipulator [AIRA PAPER 78-1167] pOO43 A78-41865 systems Computation of supersonic laminar viscous flow [NASA-CR-152092] p0052 N78-16620 past a pointed cone at angle of attack in An investigation of short haul air transportation spinning and coning motion in the southeastern United States fATAA PAPER 78-1211] p0045 A78-45139 (NASA-CR-152166] pOO12 N78-27094 An improved higher order panel method for SYSTEMS DESIGN linearized supersonic flow U SYSTEMS ENGINEERING rAIAA PAPER 78-15] pOO2 1A78-52628 SYSTEMS ENGINEERING Calculation of supersonic viscous flow over delta NT COMPUTER SYSTEMS DESIGN wings with sharp subsonic leading edges Advanced Digital Avionics System for general [ENASA-TM-785003 p0025 H78-26101 aviation SUPERSONIC SPEEDS [AIAA 77-1494] pOOl1 A78-12243 An investigation of wing buffeting response at Robustness of linear guadratic state feedback subsonic and transonic speeds. Phase 2: F-1lIA designs in the presence of system uncertainty flight data analysis. Volume 2: Plotted power --- application to Augmentor Wing Jet STOL spectra 3 Research Aircraft flare control autopilot design [NASA-CR-152113] pOO1 N78-33117 pOO16 A78-23917 - An investigation of wing buffeting response at Integrated avionics for future general aviation subsonic and transonic speeds. Phase 2: F-111A aircraft flight data analysis. Volume 3: Tabulated [AlIA PAPER 78-1482] p020 178-47927 power spectra The determination of some requirements for a [MASA-R-1521141 pOO14 N78-33118 helicopter flight research simulation facility SUPERSONIC TRANSPORTS [NASA-CR-152066] pOO63 N78-10117 An assessment of the effect of supersonic aircraft Evaluation of a spacecraft nitrogen generator operations on the stratospheric ozone content (sASA-CR-152097) p805 2 2 7 N78-23748 rNASA-RP-1026] p0O E78-30774 Space ecosynthesis: An approach to the design of SUPPORT SYSTEMS closed ecosystems for use in space NT CLOSED ECOLOGICAL SYSTEMS [NASA-TH-78491] pOD51S78-26740 NT LIFE SUPPOPT SYSTEMS SUPPRESSORS T Cable strumming suppression 2 2 (AD-A047996) pOO N78-18366 TABLES (DATA) Application of second-order turbulent modeling to Prop-fan data support study the prediction of radiated aerodynamic sound [NASA-CR-152141] p0813 N78-27128 (NASA-CR-2991] pO12 N78-25359 TAKEOIF SURFACE PROPERTIES Simulation and analysis of wind shear hazard -- NT SPECTRAL REFLECTANCE for aircraft landing and takeoff Stimulated'emission of surface plasmons by [NASA-CR-157470] p 0 5 3 H78-29699 electron tunneling in metal-barrier-metal TANK GEOMETRY structures Toroidal tank evaluation --- propellant tanks for - p0038 A78-30647 spin-stabilized Pioneer spacecraft SURFACE TO SURFACE MISSILES pD032 A78-17881 NT INTERCONTINENTAL BALLISTIC MISSILES TANKS (CONTAINERS) SURFACE VEHICLES NT PROPELLANT TANKS NT AUTOMOBILES Fluid interaction with spinning toroidal tanks SWAN BANDS pOO24 178-20186 A theoretical study of the electronic transition TAPERED WINGS moment for the C2 Swan band system U SWEPT WINGS 0 0 1 p A78-36776 TASK COMPLEXITY SPASH A model of human decisionmaking in a fault U SPLASHING diagnosis task SWEAT pOO5 A78-37130 Sweat collection capsule TEACHING 00 5 7 [NASA-CASE-ARC-11031-11 p N78-22720 U EDUCATION SWEPT WINGS TECHNOLOGICAL FORECASTING NT DELTA WINGS Space habitats --- prognosis for space colonization Computational wing optimization and comparisons p8O56 A78-49780 with experiment for a semi-span wing model 0 0 2 5 Assessing the future of air freight (NASA-TH-784801 p N78-26106 [NASA-C-152161] pOOO9 N78-14016 Phenomenological aspects of quasi-stationary Future Computer Requirements for Computational controlled and uncontrolled three-dimensional Aerodynamics 0 0 2 3 flow separations --- in relation to aircraft (NASA-CP-2032) p N78-19778 design considerations and swept wings Three-dimensional 0 7 computational aerodynamics in pOO N78-28402 the 1980's SWEPTBACK WINGS pOO 2 3 N78-19781 NT DELTA WINGS TECHNOLOGIES SWIRLING WAKES NT MILITARY TECHNOLOGY U TRBULRENT WAKES TECHNOLOGY ASSESSMENT SYMMETRICAL BODIES Flight simulation - A vital and expanding NT AXISYMETRIC BODIES technology in aircraft development NT BODIES OF REVOLUTION [AIA PAPER 78-337) pOO16 A78-29295 NT CONICAL BODIES Quiet, Short-Haul Research Aircraft - Current NT ROTATING CYLINDERS status and future plans SYNTHESIS [AIAA PAPER 78-1468) pOD 2 0 A78-47916 Synthesis of multifunction triaryltrifluoroethanes Application of advanced technologies to small, rHASA-CASE-ARC-11097-1] p0049 N78-22154 short-haul aircraft synthesis of multifunction triaryltrifluoroethanes [NASA-CR-152089] pOOl1 R78-22074 rNASA-CASE-ARC-i1097-2] p0049 178-22155
116 SUBJECT INDEX THERMOCHEMl2AL PROPERTIES
A review of NASA-sponsored technology assessment pOO 3 5 A78-23543 projects TENSILE STRENGTH [NASA-TM-78i721 pO025 W78-24000 Hydrogen attack - Influence of hydrogen sulfide An investigation of short haul air transportation --- on carbon steel in the southeastern united States pOO44 A78-4i108 rNASA-CR-152166] pO012 N18-27094 TERNARY SYSTEMS (DIGITAL) Precutive summary: Benefit-cost evaluation of an I DIGITAL SYSTEMS intra-regional air service in the Bay Area and a TERRESTRIAL MAGNETISM technology assessment of transportation system 0 GEOMAGNETISM investments --- regional planning for the San TERRESTRIAL PLANETS Francisco Bay area of California NT EARTH (PLANET) [NAqA-CR-152154-1] pOOl3 M78-28988 NT MASS (PLANET) A technology assessment of transportation system IT MERCURY (PLANET) investments --- markovian decision theory On the relative locations of the bow shocks of the [NASA-CR-152154-2) pOO13 N78-28989 terrestrial planets Requirements for regional short-haul air service pO031 A78-13752 and the definition of a flight program to TEST FACILITIES determine neighborhood reactions to small NT HYDRAULIC TEST TUNNELS transport aircraft NT LON SPEED WIND TUNNELS [NASRA-CR-1521511 pOO13 H78-30070 NT TRANSONIC WIND TUNNELS The ILLIAC IV memory system: current status and The determination of some requirements for a ruture possibilities helicopter flight research simulation facility 0 0 (NASA-CR-152177] p 60 178-32731 [NASA-CR-152066) pOO63 178-10117 TECHNOLOGY TRANSFER Numerical aerodynamic simulation facility. NT AEROSPACE TECHNOLOGY TRANSFER Preliminary study extension. Executive summary TECHNOLOGY UTILIZITION fNASA-CR-152106) pOOE8 N7e-19050 Space industrialization - Education --- via Numerical aerodynamic simulation facility. communication satellites Preliminary study extension [AAS 77-258] pO01 k78-36722 [NASA-CR-152107] pOO28 V78-19051 High altitude perspective --- cost-reimbursable TEST PILOTS services using NASA U-2 aircraft A pilot evaluation of two G-seat cueing schemes 7 [UASA-SP-427] pOO2 N78-31508 (NASA-TP-1255) pOO08 N78-31739 TELRCHIDICS TESTES U REMOTE HANDLING Spectrophotofluorometric and electron microscopic TELECOMMUNICATION study of Lipofuscin accumulation in the testis NT AIRCRAFT COMNURICATIOR of aging mice NT BTDTELEMETRY pOOS6 A78-48581 NT VIDEO COMMICATION TX AIRCRAFT TELEMETRY U B-111 AIRCRAFT NT BIOTELEMETRY THEOREMS TELESCOPES NT BERNOULLI THEOREM NT ASTRONOMICAL TELESCOPES NT LAGRANGE SIMILARITY HYPOTHESIS Theoretical contamination of cryogenic satellite IT UNIQUENESS THEOREM telescopes THERMAL CONDUCTIVITY 0 ENASA-TP-1177] p0 24 N78-21193 The spiral field inhibition of thermal conduction Engineering tests of the C-141 telescope in two-fluid solar wind models rNASA-TM-78467] p0O25 N78-25017 p0046 A78-48281 TELLEGEN THEORT THERMAL CONTROL COATINGS U NETWORK SYNTHESIS Intumescent-ablatOr coatings using endothermic TEMPERATURE fillers NT BRIGHTNESS TEMPERATURE [ASA-CASE-AGC-11043-1] pO049 N78-27180 NT IONOSPHERIC TEMPERATURE THERMAL DECOMPOSITION TEMPERATURE CORTEOL NT PYROLYSIS Thermal design and development of a planetary THERMAL EFFECTS probe - Pioneer venus large probe U TEMPERATURE EFFECTS EAIAA PAPER 78-916] pOQ4i A78-37275 THERMAL INSULATION TEMPERATURE DIPEHENCES A method for determining structural properties of U TEMPERATURE GRADIENTS RCC thermal protection material --- Reinforced TEMPERATURE DISTHIBUTIO Carbon-Carbon Theoretical ana experimental study of (AIAA PAPER 78-869] p 0 0 4 0 A78-35997 aerodynamics, heat transfer and performance of a Fibrous refractory composite insulation - radial turbine shielding retsable spacecraft (NASA-CR-152105] pOO6 N78-19155 [nASA-CaSR-APC-11169-13 pOOSO 178-32189 TEMPERATURE EFFECTS THERMAL PROTECTION The co-adsorption of copper and oxygen on a Reaction cured glass and glass coatings tungsten 100 plane-type serface (NXSA-CISE-ABC-11051-1] 7 pOO0O M79-32260 pO03 A78-29489 THERMAL RESISTANCE Influence of temperature and the role of chromium Fire resistivity and toxicity studies of candidate on the kinetics of sulfidation of 310 stainless aircraft passenger seat materials steel [NASA-T8-78468] p02 4 178-21214 p0043 A78-41796 THERMAL SHIELDING Absolute intensity measurements at different U HEAT SHIELDING temperatures of the C-12/0-16/2 hands 30 0 1 THERMAL SIMULATION I--00 0 0 and 30 0 1 IV--GO 0 0 Carbonaceous materials subjected to extreme pOO47 A78-50488 heating - A comparison of numerical simulation Measurement at different temperatures of absolute and experiments --- Jovian entry conditions 00 4 1 intensities, line half-widths, and broadening by [AIAA PAPER 78-8663 p A78-37273 Ar and N2 for the 30 0 1 Il--0O 0 0 band of C02 THERMAL STRESSES p0047 A78-50489 Stress analysis study in cooled radial inflow Thermal rearrangements in 1,2-poly/1,-hexadiene/s turbine 0 pOO48 A78-51870 [thAA PAPER 78-94] p 064 A78-22570 TEMPERATURE FIELDS THERMOCHEMICAL PROPERTIES U TEMPERATURE DISTRIBUTION The response of heat-shield materials to intense TEMPERATURE GRADIENTS laser radiation Pioneer 10 observation of the solar wind proton [AIAA PAPER 78-138] p0034 A78-22583 temperature heliocentric gradient Assessment of relative flammability and (NASA-T-78515] pO027 178-31030. thermochemical properties of some thermoplastic TEIPERATURE PROFILES materials Thermal structure of the primitive ionosphere pOO 4 7 A78-49693
117 THEREODYNAMIC CYCLES SUBJECT INDEX
TRERMCDYNAMIC CYCLES THREE DIMENSIONAL NOTION NT STIRLING CYCLE NT THREE DIMENSIONAL FLOP THERMODYNAMIC PROPERTIES THRUST CONTROL NT THERMAL CONDUCTIVITY NT THRUST VECTOR CONTROL PT THERMOCHEMICAL PROPERTIES THRUST VECTOR CONTROL THERMODYNAMICS Optimal guidance and control for investigating NT AEROTHERNODYNAMICS aircraft noise-impact reduction Thermodynamic processes induced by coherent [NASA-TP-123:1] p0006-N78-23100 radiation TILT ROTOR AIRCRAFT p0034 A78-21624 NT XV-15 AIRCRAFT THERMOELECTRIC CONVERSION SYSTEMS TILT ROTOR RESEARCH AIRCRAFT PROGRAM U THERMOELECTRIC POWER GENERATION Development of automatic and manual flight THERMOELECTRIC POWER GENERATION director landing systems for the XV-15 tilt A cesium plasma TELEC device for conversion of rotor aircraft in helicopter mode laser radiation to electric power [NASA-CR-152140] p0011 H78-22071 p0048 A78-51067 Application of a cost/performance measurement TEERECMECHANICS system on a research aircraft project U THERMODYNAMICS ENASA-TM-78498] p0007 N78-27043 THERMOPHYSICAL PROPERTIES TILTING ROTORS NT THERMAL CONDUCTIVITY Evaluation of the tilt rotor concept: The XV-15's THERMOPHTSICS role U THERMODYNAMICS pO004 N78-19142 THERMOPLASTIC RESINS Effect of high lift flap systems on the conceptual The relative fire resistance of select design of a 1985 short-haul commercial STOL tilt thermoplastic materials --- for aircraft interiors rotor transport p0046 A78-45475 [NASA-T-78474] pO005 N78-21094 Assessment of relative flammability and TIPS thermochemical properties of some thermoplastic PT BLADE TIPS materials TITANATES p0047 A78-49693 Effects of potassium titanate fiber on the wear of Boron trifluoride coatings for thermoplastic automotive brake linings materials and method of applying sane in glow p035 A78-23450 discharge TITANIUM COMPOUNDS FNASA-CASE-ARC-11057-1] po57 N78-31233 NT TITANATES THERMOPLASTICITY TOLERANCES (PEYSIOLOGY) Pelative toxicity of the pyrolysis products from NT ACCELERATION TOLERANCE some thermoplastic and thermoset polymers NT HUMAN TOLERANCES p0042 A78-41213 TOROMETRY THERMOSETTING RESINS U PRESSURE MEASUREMENTS Synthesis of N-substituted bisitaconimide monomers TOROIDS for use as thermosetting polyimide resins Fluid interaction with spinning toroidal tanks 0 0 24 0041 A78-36809 P R78-20186 Relative toxicity of the pyrolysis products from TORQUE some thermoplastic and themoset polymers Torguing preload in a lubricated bolt p0042 A78-41213 (NASA-T-78501] p0027 N78-29451 THERMOTROPISM TORSIONAL STRESS U TEMPERATURE EFFECTS Simple torsion test for shear moduli determination THIN AIRFOILS of orthotropic composites 2 4 NT THIN WINGS (NASA-TM-78485] pOO N78-21490 THIN FILMS TORSO Controlled vapor growth of small particles of Pd Spacesuit torso closure and Fe on thin A1203 substrates [NASA-CASE-ARC-11100-1] pOOSS N78-31736 p0044 A78-43384 TOWNSEND DISCHARGE THIN WINGS NT GAS DISCHARGES A uniqueness proof for a transonic flow problem TOXIC HAZARDS pOOl6 A78-26599 ALC/5O/ values for some polymeric materials --- THIOLS Apparent Lethal Concentration fire toxicity 4 NT CYSTEINE pOO O A78-36596 THREE DIMENSIONAL FLOW The relative fire resistance of select Displacement thickness distributions in transonic thermoplastic materials --- for aircraft interiors flows about 3-D wings p0046 A78-45475 p0O3 2 A78-17612 TOXICITY On implicit finite-difference simulations of The prediction of toxic atmospheres from three-dimensional flow decomposing polymers rAIAA PAPER 78-10] p0033 A78-20630 pOO3 3 A78-19895 Numerical solution of a three-dimensional shock Relative toxicity of the pyrolysis products from wave and turbulent boundary-layer interaction some thermoplastic and thermoset polymers [AIAA PAPER 78-161] p0O34 A78-22591 p0042 A78-41213 A ,view toward future fluid dynamics computing TOXICITY AID SAFETY HAZARD (.ATAA PAPER 78-1112] p0O45 A78-45126 Fire resistivity and toxicity studies of candidate ,dvanced panel-type influence coefficient methods aircraft passenger seat materials applied to unsteady three dimensional potential p80 4 8 A78-51838 flows TRACE ELEMENTS rAIAA PAPER 78-229] p0021 A78-52630 Airborne infrared interferometric observations and Three-dimensional computational aerodynamics in analysis of stratospheric trace constituents 0 0 34 the 1880s [ATA PAPER 78-252] p A78-22606 pO023 N78-19781 TRACREA Numerical Aerodynamics Simulation Facility Micro-fluid exchange coupling apparatus -- a preliminary study, executive summary --- three microrespirator to allow surgery on rats or mice dimensional flow [NASA-CASE-ARC-111l-1 ] pOO60 R78-33717 p0023 R78-19782 TRACKING (POSITION) Preliminary study for a Numerical Aerodynamic NT OPTICAL TRACKING simulation Facility --- three dimensional flow NT PURSUIT TRACKING p0023 N78-19783 Dual-loop model of the human controller Phenomenological aspects of quasi-stationary pOO18 A78-39184 controlled and uncontrolled three-dimensional TRACKING STUDIES flow separations --- in relation to aircraft U TRACKING (POSITION) design considerations and swept wings TRAFFIC pDO07 N78-28402 Planning for airport access: An analysis of the
118 SUBJECT INDEX TRANSPORT AIRCRAFT
San Francisco Bay area A uniqueness proof for a transonic flow problem 0 0 1 [NASA-CP-2044] p 078-26152 pOO16 A78-26599 TRAFFIC CONTROL The shock tube as a device for testing transonic NT AIR TRAFFIC CONTROL airfoils at high Reynolds numbers TRAINING [ATAA 78-769) p0017 A78-32330 U EDUCATION Notes on the transonic indicial method --- for two TRAINING SIMULATORS dimensional airfoil flutter derivative calculation NT COCKPIT SIMULATORS p0041 A78-37732 NT FLIGHT STMULATORS Transonic lifting line theory - Numerical TRAJECTORIES procedure for shock-free flows NT DESCENT TRAJECTORIES p0017 A78-37742 NT MOLECULAR TRAJECTOPIES An implicit algorithm for the conservative TRAJECTORY ANALYSIS transonic full potential equation using an An analytic study of impact ejecta trajectories in arbitrary mesh the atmospheres of Venus, Mars, and earth (AIAA PAPER 78-1113] pOO 3 A78-41826 p0037 A78-29532 Computation of transonic flow past projectiles at - Trajectory module of the NASA Ames Research Center angle of attack aircraft synthesis program ACSYT [AIAA PAPER 78-1182] p0O44 A78-41875 FHASA-TN-78497] pOO06 H78-26133 A new method for designing shock-free transonic TRAJECTORY CONTROL configurations MT TRAJECTORY OPTIMIZATION (AIAA PAPER 78-1114] p0045 A78-45127 TRAJECTORY OPTIMIZATION Lifting line theory for transonic flow High performance dash-on-warning air mobile p0020 A78-48991 missile system --- first strike avoidance for Two-dimensional transonic testing with splitter retaliatory aircraft-borne ICBM counterattack plates [AIAA 78-1353] pO19 A78-46545 (NASA-TP-1153] p0004 N78-17999 TRANSCENDENTAL PUNCTIONS A study of test section configuration for shoct IT PERIODIC FUNCTIONS tube testing of transonic airfoils TRANSDUCERS [NASA-CR-157237] pOO12 N78-26153 NT DIGITAL TRANSDUCERS Solution of transonic flows by an NT PIEZORESISTIVE TRANSDUCERS integro-differeatial equation method NT PRESSURE SENSORS [NASA-TM-78490] p0026 B78-26391 TRANSFER FUNCTIONS On improving the iterative convergence properties Applications of algebraic geometry to systems of an implicit approximate-factorization finite theory - The McMillan degree and Kronecker difference algorithm --- considering transonic indices of transfer functions as topological and flow holomorphic system invariants [NASA-TM-78495] p0026 H78-26795 p0021 A78-51860 Techniques for correcting approximate finite TRANSITION METAlS difference solutions --- considering transonic NT CHROMIUM flow NT IRON [NASA-TM-78499] p0 0 2 6 N78-26796 NT PALLADIUM Wing analysis using a transonic potential flow NT TUNGSTEN computational method TRANSITION PROBABILITIES [NASA-TM-78464] p000 7 N78-28053 Exchange and relaxation effects in low-energy Introduction to unsteady aspects of separation in radiationless transitions subsonic and transonic flow rNASA-TM-79383] pOO00 N78-18882 pO06 3 W78-28403 TRANSLATIONAL MOTION TRANSONIC PLOTTER NT THREE DIMENSIONAL FLOW Notes on the transonic indicial method --- for two Simultaneous determination of rotational and dimensional airfoil flutter derivative calculation translational temperatures of OH/2 Pi/ in a gas p004 1 A78-37732 discharge TRANSONIC SPEED 3 p00 0 &78-10405 An investigation of wing buffeting response at TRANSLRNAR SPACE subsonic and transonic speeds: Phase 1: F-111A U INTERPLANETARY SPACE flight data analysis. Volume 1: Summary of TRANSMISSION technical approach, results and conclusions 3 NT CONDUCTIVE HEAT TRANSFER [NASA-CR-152109) pOO1 R78-33113 NT CONVECTIVE HEAT TRANSFER TRANSONIC WIND TUNNELS NT HALOS Some observations on the mechanism of aircraft NT HEAT TRANSFER wing rock NT LAMINAR HEAT TRANSFER [AIAA PAPER 78-1456] p0020 A78-47907 HT LIGHT SCATTERING An analysis of the rotor blade stresses of the NT LIGHT TRANSMISSION three stage compressor of the Ames Research NT RADIATIVE HEAT TRANSFER Center 11- by 11-foot transonic wind tunnel NT SATELLITE TRANSMISSION [NASA-CR-152083] pOO09 N78-17061 RT SHOCK WAVE PROPAGATION Two-dimensional transonic testing with splitter NT WAVE PROPAGATION plates TRANSONIC AIRCRAFT [NASA-TP-1153] pOO00 H78-17999 U SUPERSONIC AIRCRAFT wim tunnel investigation of computationally TRNSONIC FLIGHT optimized variable camber wing configurations Transonic wing analysis using advanced fNASA-TM-78479] pO026 N7-29067 computational methods TRARSONICS [AIAA PAPER 78-1051 pUBlS A78-20686 U TRANSONIC FLOW TRANSONIC FLOW TRANSPORT AIRCRAFT Displacement thickness distributions in transonic NT CARGO AIRCRAFT flows about 3-D wings NT SHORT HAUL AIRCRAFT 2 pOO3 A78-17612 Fuel saving potential of Mach 0.8 twin engine Unsteady transonic flow computations prop-fan transports p0032 A78-18274 pO017 A78-31306 Calculation of unsteady transonic flows using the Application of advanced high speed turboprop integral equation method technology to future 0 0 3 civil short-haul transport rATAA PAPER 78-13] p 3 A78-20632 aircraft design Thin-layer approximation and algebraic model for [AIAA PAPER 78-1487] pO064 A78-47930 separated turbulent flows Factors affecting the retirement of commercial rAIAA PAPER 78-257] pOO33 A78-20776 transport jet aircraft Computational wing optimization and wind tunnel [NASA-CR-152115] pOO1 0 78-21092 test of semi-span model Effect of high lift flap systems on the conceptual fAIAA PAPER 78-102] p0O34 A78-22575 design of a 1985 short-haul commercial STOL tilt rotor transport
119 TRANSPORT COEFFICIENTS SUBJECT INDEX
rNASA-T1-78474 p00 5 TN78-21094 TUNNEL RESISTORS Fuel conservation merits of advanced turboprop U ELECTRON TUNNELING transport aircraft TURBINE ENGINES [NASA-CR-152096] p0M H78-21095 Stress analysis study in cooled radial inflow Short-haul CTOL aircraft research --- on reduced turbine energy for commercial air transportation (AIAA PAPER 78-9q] p0064 A78-22570 p0OO8 N78-29061 TURBINES equirements for regional short-haul air service HT GAS TURBINES and the definition of a flight program to TURBOFAN AIRCRAFT determine neighborhood -reactions to small NT CV-990 AIRCRAFT transport aircraft ET F-111 AIRCRAFT CNASA-CR-152151] p0013 H78-30070 TURBOJET AIRCRAFT TRANSPORT COEFFICIENTS U JET AIRCRAFT U.TRANSPORT PROPERTIES TURBOAACHINE BLADES TRANSPORT PROPERTIES NT ROTOR BLADES (TURBONACHINERY) NT DIFFUSION COEFFICIENT NT STATOR BLADES PT EDDY VISCOSITY Theoretical and experimental study of FT THRFMAL CONDUCTIVITY aerodynamics, heat transfer and performance of a Calcium transport in Ralobacterium halobium radial turbine envelope vesicles (NASA-CR-152105] p0064 978-19155 p055 A78-48574 TURBONACRIXERT Methionine transport in falobacterium halobium ST GAS TURBINES vesicles - Noncompetitive, asymmetric inhibition TURBOPROP AIRCRAFT by L-Cysteine Application of advanced high speed turboprop p0055 A78-48579 technology to future civil short-haul transport Transport of contaminants in the planetary aircraft design boundary layer [AIAA PAPER 78-1487] p0064 A78-47930 p0048 A78-52137 TURBULENCE TRANSPORTATION ST ATMOSPHERIC TURBULENCE NT AIR TRANSPORTATION NT CLEAR AIR TURBULENCE NT URBAN TRANSPORTATION TUBULMNT BOUNDARY LAYER A review of NASA-sponsored technology assessment Reynolds number and pressure gradient effects on projects compressible turbulent boundary layers [NASA-TE-78472] p0025 S78-24000 [AIAA PAPER 78-199] p0033 A78-20741 A technology assessment of transportation system Numerical solution of a three-dimensional shock investments --- narkovian decision theory wave and turbulent boundary-layer interaction EnASA-CR-152154-2] pOO13 W78-28989 [AIAA PAPER 78-161] p0034 A78-22591 Phase 1: Definition of intercity transportation Behavior of a turbulent boundary layer subjected comparison framework, volume 1: Summary --- 3 to sudden transverse strain 0 3 operations research of passenger an freight (ArIA PAPER 78-201] pD 4 A78-22595 transporatation systems An evaluation of several compressible turbulent rNASA-CF-152152-VOL-1] p0001 N78-28993 boundary-layer models Effects of pressure Phase 1: Definition of intercity transportation gradient and Reynolds number comparison framework. Volume 2: Methodology [AIAA PAPER 78-1160] pOMS A78-41859 --- operations research of passenger and freight Comparison of Multieguation turbulence models for transportation systems several shock-separated boundary-layer rNASA-CR-152152-VOL-2] p0029 N78-28994 interaction flows ' A study of characteristics of intercity [AIAA PAPER 78-1165] p 0 0 4 3 A78-41863 transportation systems. Phase 1: Definition of A detailed study of attached and separated transportation comparison methodology compression corner flowfields in high Reynolds (NASA-CR-152153-2] p000I N78-29996 number supersonic flow TEADSMILLS [a3A1 PAPER 78-1167J p0043 A78-41865 Tread drum for animals --- having an electrical Injection slot location for boundary-layer control shock station in shook-induced separation 0 0 4 FNASA-CASE-RC-10917-1) p0057 N78-27733 [AIAA PAPER 78-1168] p 4 A78-41866 TRIANGELAR WINGS A computer program for calculating laminar and U DELTA WINGS turbulent boundary layers for two-dimensional TRIM (BALANCE) time-dependent flows U AERODYNAMIC BALANCE [NASA-TM-78470) p0051 N78-19444 TRIPFOPELLANTS An experimental documentation of pressure gradient U LIQUID ROCKET PROPELLANTS and Reynolds number effects on compressible TROPISM turbulent boundary layers NT AEOLOTROPISM (NASA-TM-78488] p0026 N78-27364 TROPOSPHERE TURBULENT FLOW Interhemispheric gradients of CF2Cl2, CFCl3, CC14r Thin-layer approximation and algebraic model for and 120 separated turbulent flows p 0 04 2 A78-41124 [AIAA PAPER 78-257) p0 0 3 3 A78-20776 TRUNCATION ERRORS Measurements of unsteady vortex flow fields Digital filter structures having low errors and (AIAA PAPER 78-18] pOO15 378-22554 simple hardware implementation Navier-Stokes calculations for laminar and p0056 A78-51346 turbulent hypersonic flow over indented nosetips Techniques for correcting approximate finite rAIAA PAPER 78-260] 1 p 0 0 3 5 378-22608 difference solutions --- considering transonic Computation of the viscous supersonic flow over flow symmetrical and asymmetrical external axial rNASA-TH-78499] p 0 0 2 6 178-26796 corners TUBES [AIAA PAPER 78-1135] pOOM3 A78-41839 Advanced solid electrolyte cell for C02 and H20 Estimating maximum instantaneous distortion from electrolysis --- for extended duration manned inlet total pressure rms measurements spaceflights [AIAA PAPER 78-970] pOO19 A78-43525 rNASA-C-152093] pOOS2 N78-21235 Numerical solution of two-dimensional turbulent TUBING blunt body flows with an impinging shock U PIPES (TUBES) rAIAA PAPES 78-1209] pOO4S A78-45144 TUNGSTEN Arrhenius' law in turbulent media and an The co-adsorption of copper and oxygen on a equivalent tunnel effect --- in binary exchange tungsten 100 plane-type surface chemical reactions 3 p00 7 A78-29489 po09 A78-52547 TURUSK METEORITE Application of second-order turbulent modeling to Nitric oxide production by Tunguska meteor the prediction of radiated aerodynamic sound p0048 A78-51811 [NASA-C-2994] pO02 N78-25359
120 SUBJECT INDEX VAPOR DEPOSITION
TURBULENT WAKES Introduction to unsteady aspects of separation in Wake vortex measurements of bodies at high angle subsonic and transonic flow of attack pO63 N78-28403 (AIAA PAPER 78-23] pOO15 A78-22555 Some unsteady separation problems for slender bodies Measured wake-vortex characteristics of aircraft pOO63 N78-28405 in ground effect UNSWEPT RINGS rAIAA PAPER 78-109] pOO1S A78-22578 Transonic lifting line theory - Numerical
TVC (CONTROL) procedure for shock-free flows 7 U THRUST VECTOR CONTROL pOO1 A78-37742 TWO DIMENSIONAL BODIES UPPER AIR Not.s on the transoic indicial method --- for two U UPPER ATMOSPHERE dimensional airfoil flutter derivative calculation UPPER ATMOSPHERE pOO41 A78-37732 NT EXOSPHERE TWO DIMENSIONAL BOUNDARY LAYER NT MAGNETOSPHERE Behavior of a turbulent boundary layer subjected Occultation of Epsilon Geminorum by Mars. II - The to sudden transverse strain , structure and extinction of the Martian upper CAIAA PAPER 78-2013 pO034 A78-22595 atmosphere Flying-hot-wire study of two-dimensional mean flow pOO30 A78-10587 past an NACA 4412 airfoil at maximum lift BRANDS (PLANET) rAIAA PAPER 78-1196] pOO18 A78-41887 NT URANUS RINGS TWO DIMENSIONAL FLOW Signal-to-noise ratios for stellar occultations by nsteady transonic flow compntations the rings of Uranus. 1977-1980 3 3 p00 3 2 A78-18274 p0 A78-20223 Numerical solution of a class of integral URANUS RINGS equations arising in two-dimensional aerodynamics The radii of Uranian rings alpha, beta, gamma, pOOl8 A78-40949 delta, epsilon, eta, 4, 5, and 6 from their Numerical solution of two-dimensional turbulent occultations of SAO 158687 blunt body flows with an impinging shock pO046 A78-48112 [AIAA PAPER 78-1209] p 0 04 5 A78-45144 URBAN AREAS A computer program for calculating laminar and U CITIES turbulent boundary layers for two-dimensional URBAN TRANSPORTATION time-dependent flows Planning for airport access: An analysis of the [NASA-TM-784701 pOO1 N78-19444 San Francisco Bay area TWO FLUID MODELS [NASA-CP-2044] pOOOl N78-26152 The spiral field inhibition of thermal conduction A study of characteristics of intercity in two-fluid solar wind models transportation systems. Phase 1: Definition of p0046 A78-48281 transportation comparison methodology TWO-WAVELENGTH LASERS [NASA-R-152153-2] pOO01 N78-29996 Collisionless dissociation of SF6 using two USER MANUALS (COMPUTER PROGRAMS) resonant frequency C02 laser fields System optimization of gasdynamic lasers, computer p0031 A78-14655 program user's manual 2 [NASA-TH-731931 p00 7 N78-29436 U USER REQUIREMENTS Uuter. quire.ments and roles of computers in U-2 AIRCRAFT aerodynamics High altitude perspective --- cost-reimbursable pOO04 H78-19786 services using NASA U-2 aircraft UTILITY AIRCRAFT rNASA-SP-427] p0027 N78-31508 NT U-2 AIRCRAFT ULTRAVIOLET ABSORPTION UTILIZATION Absorption measurements of OH using a CR tunable NT LASER APPLICATIONS laser 2 pOO3 A78-17837 V ULTRAVIOLET ASTRONOMY Europa - Ultraviolet emissions and the possibility V/STOL AIRCRAFT of atomic oxygen and hydrogen clouds NT HRLICOPTERS p0048 A78-52482 NT MILITARY HELICOPTERS UNDERWATER VEHICLES NT ROTARY WING AIRCRAFT NT SUBMARINES NT SHORT TAKEOFF AIRCRAFT UNIQUENESS THEOREM NT VERTICAL TAKEOFF AIRCRAFT A uniqueness proof for a transonic flow problem NT XV-15 AIRCRAFT pO016 A78-26599 Simulator evaluation of three situation and UNITED STATES OF AMERICA guidance displays for V/STOL aircraft zero-zero NT CALIFORNIA landing approaches UNMARRED SPACECRAFT pOO55 A78-44131 NT JUPITER PROBES Studies of aerodynamic technology for VSTOL NT PTIONEER SPACE PROBES fighter/attack aircraft NT PIONEER VENUS SPACECRAFT [AIAA PAPER 78-15111 p0020 A78-47946 NT PIONEER 10 SPACE PROBE V/STOL aircraft simulation - Requirements and NT PIONEER 11 SPACE PROBE capabilities at Ames Research Center IT SOLAR PROBES [AIAA PAPER 78-1515] pO021 A78-49790 NT VENUS PROBES Low speed test of a high-bypass-ratio propulsion ,UNSTEADY FLOW system With an asymmetric inlet designed for a NT OSCILLATING FLOW tilt-nacelle V/STOL airplane Unsteady transonic flow computations [NASA-CR-152072] pOOOS N78-17062 p0032 A78-18274 Conceptual design study of a arrier V/STOL On implicit finite-difference simulations of research aircraft three-dimensional flow (NASA-CR-152086] pOO09 N78-19094 [AIAA PAPER 78-10] p0033 A78-20630 Static tests of a large scale swivel nozzle thtust Calculation of unsteady transonic flows using the deflector integral equation method [NASA-C-152091] pOO11 U78-22100 [AIAA PAPER 78-13] p00 3 3 A78-20632 VACUUM DEPOSITION Measurements of unsteady vortex flow fields Controlled vapor growth of small particles of Pd [AIAA PAPER 78-18] pOOlS A78-22554 and Fe on thin A1203 substrates Advanced panel-type influence coefficient methods poo44 A78-43384 applied to unsteady three dimensional potential VANES flows NT GUIDE VANES [AIAA PAPER 78-229] p021 A78-52630 VAPOR DEPOSITION Dynamic stall of an oscillating airfoil NT VACUUM DEPOSITION pOO25 H78-22055
121 VARIABLE LIFT SUBJECT INDEX
Chemisorption of CO on Pd particles supported on The Viking biological experiments on Mars mica pOO55 A78-39746 p0040 A78-36040 Post-Viking models for the structure of the summer VARIABLE LIFT atmosphere of Mars U IIFT pOO47 A78-50240 VARIABLE STARS VIKING LANDER I NT NOVAE Chemical interpretation of Viking Lander I life VARIATIONS detection experiment NT ANNUAL VARIATIONS p0 0 53 A78-25560 NT DIURNAL VARIATIONS VIKING ORBITER SPACECRAFT VECTOR ANALYSIS Some Martian volcanic features as viewed from the NT VORTICITY Viking orbiters VECTOR SPACES p0030 A78-11403 NT MATRICES (MATHEMATICS) VIKING SPACECRAFT NT VORTICITY NT VIKING LANDER SPACECRAFT VECTORS (MATHEMATICS) NT VIKING ORBITER SPACECRAFT NT VORTICITY VIKING 1 SPACECRAFT VELOCITY NT VIKING LANDER SPACECRAFT NT LOW SPEED NT VIKING LANDER 1 NT SOLAR WIND VELOCITY NT VIKIKG ORBITER SPACECRAFT NT SUBSONIC SPEED VIKING 2 SPACECRAFT NT SUPERSONIC SPEEDS NT VIKING LANDER SPACECRAFT NT TRANSONIC SPEED NT VIKING ORBITER SPACECRAFT VELOCITY DISTRIBUTION VISCERA The spanwise lift distribution on a wing from NT ADRENAL GLAND flow-field velocity surveys NT TESTES [AIA PAPER 78-1195] pOO18 A78-41886 VISCOSITY VELOCITY FIELDS NT EDDY VISCOSITY U VELOCITY DISTRIBUTION VISCOUS FLOW VELOCITY MEASUREMENT NT BOUNDARY LAYER FLOW Measuring the velocity of individual atoms in real NT BOUNDARY LAYER SEPARATION time NT SEPARATED FLOW p0035 A78-23124 Computation of the viscous supersonic flow over VELOCITY PROFILES symmetrical and asymmetrical external axial U VELOCITY DISTRIBUTION corners VENUS ATMOSPHERE [AIAA PAPER 78-1135] pO0 4 3 A78-41839 An analytic study of impact ejecta trajectories in Calculation of supersonic viscous flow over delta the atmospheres of Venus, Mars, and earth wings with sharp subsonic leading edges PO37 A78-29532 [AIAA PAPER 78-1137] pOOW3 A78-41841 A comprehensive model of the Venus ionosphere The numerical solution of viscous flows at high p0038 A78-30071 Reynolds number Thermal design and development of a planetary p0 0 4 6 A78-46360 probe - Pioneer Venus large probe Computing viscous flows rAIAA PAPER 78-916] pOOh 1 A78-37275 pOODS N78-19794 The ionosphere and airglow of Venus - Prospects VISUAL DISPLAYS for Pioneer Venus U DISPLAY DEVICES pOO5 A78-44773 VISUAL PIGMENTS VENUS PROBES Illumination-dependent changes in the intrinsic Thermal design and development of a planetary fluorescence of bacteriorhodopsin probe - Pioneer Venus large probe pO55 A78-48578 rATAA PAPER 78-916] pOO1 A78-37275 VISUAL TRACKING VERTEBRATES U OPTICAL TRACKING NT MICE VISUALIZATION OF FLOW NT RATS U FLOW VISUALIZATION VERTICAL DISTRIBUTION VOLCANICS NT STAR DISTRIBUTION U VOLCANOLOGY VERTICAL TAKEOFF AIRCRAFT VOLCANOLOGY Evaluation of the tilt rotor concept- The XV-15ts Some Martian volcanic features as viewed from the role Viking orbiters pOO04 H78-19142 pOO 3 O A78-11403 VIBRATION VOLT-AMPERE CHARACTERISTICS NT FREE VIBRATION Characteristics of integrated MOM junctions at dc NT STRUCTURAL VIBRATION and at optical frequencies NT TRANSONIC FLUTTER (AD-AO56165] p0 0 3 7 A78-28926 Cable strumming suppression VORTEX COLUMNS CAD-A047996] pO0 2 2 f78-18366 U VORTICES VIBRATIONAL FREQUENCIES VORTEX DISTURBANCES U VIBRATIONAL SPECTRA U VORTICES VIBRATIONAL RELAXATION VORTEX FLOW UJIOLECULAR RELAXATION U VORTICES VIBRATIONAL SPECTRA VORTEX RINGS Absolute intensity measurements at different The instability of the thin vortex ring of temperatures of the C-12/0-16/2 bands 30 0 1 constant vorticity I--o0 00 and 30 0 1 Iv--OO 0 0 p8031 A78-14622 p0047 A78-50488 VORTEX SHEETS Measurement at different temperatures of absolute Measured wake-vortex characteristics of aircraft intensities, line half-widths, and broadening by in ground effect Ar and N2 for the 30 0 1II--O0 0 0 band of C02 [AIAA PAPER 78-109] pOO15 A78-22578 7 pOf4 A78-50489 VORTEX TUBES Comments on the note by Arie et al. on the U VORTICES transition moment of the C02 band near 7740 VORTICES kaysers Laser-velocimeter surveys of merging vortices in a 4 pOO 8 A78-52388 wind tunnel VIDEO COMMUNICATION [AAA PAPER 78-107] pOO15 A78-20687 Survey of adaptive image coding techniques Measurements of unsteady vortex flow fields 0 0 3 1 p A78-15267 [AIAA PAPER 78-18] pOO15 A78-22554 VIKING LARDER SPACECRAFT Wake vortex measurements of bodies at high angle NT VIKING LANDER 1 of attack [AIAA PAPER 78-233 pOO15 A78-22555
122 SUBJECT INDEX WIND TUNNEL TESTS
not-wire, laser anemometer and force balance WEIR TESTS measurements of cross-sectional planes of single Effects of potassium titaate fiber on the wear of and interacting trailing vortices automotive brake linings [AIAA PAPER 78-11943 pOO18 A78-41885 pOO35 A78-23450 On the period of the coherent structure in WEBS (MENBRANES) boundary layers at large Reynolds numbers U MEMBRANES 2 (NASA-TM-78477] pOO 4 N78-21407 WEIGET (MASS) The effect of tip vortex structure on helicopter NT BODY WEIGHT noise due to blade/vortex interaction WEIGHTING FUNCTIONS rNkSA-CR-152150] pOO12 N78-25832 A study of characteristics of intercity Laser-velocimeter surveys of merging vortices in a transportation systems. Phase 1: Definition of wind tunnel: Complete data and analysis transportation comparison methodology (NASA-TM-78449] pOO08 N78-33043 [(ASA-CD-152153-2) pOO01 N78-29996 VORTICITY WEIGHTLESSNESS The instability of the thin vortex ring of Space colonization - Some physiological perspectives constant vorticity p0 0 5 5 A78-41164 p0031 A78-14622 Further investigation of the spontaneous and VTOL AIRCRAFT evoked activity of the primary neurons of U VERTICAL TAKEOFF AIRCRAFT statoreceptors (and other receptors) of the labyrinth of the bullfrog before, during and W after an extended period of weightlessness, including alternative intervals of artificial WAKES gravity NT AIRCRAFT WAKES (NASA-CR-154507] pOO52 M78-10684 NT NEAR WAKES WHIRL INSTABILITY NT TURBULENT WAKES U ROTARY STABILITY WALL FLOW WHISTLERS Buried wire gage for wall shear stress measurements histler mode noise in Jupiter's inner magnetosphere fAIAA 78-798] p0017 A78-32353 p0045 78-45188 1study of test section configuration for shock WIDERAND tube testing of transonic airfoils U BROADBAND rNASA-CR-157237] pOO12 N78-26153 WIGHTBAN THEORY WARFARE U FIELD THEORY (PHYSICS) NT COMBAT WIND CIRCULATION WARMING U ATMOSPHERIC CIRCULATION U HEATING WIND SHEAR WARNING DEVICES Simulation and analysis of wind shear hazard -- 9 WARNING SYSTEMS for aircraft landing and takeoff WARNING SIGNALS rNASA-CR-157470) pOO53 N78-29699 U WARNING SYSTEMS Computed responses of several aircraft to WARNING SYSTEMS atmospheric turbulence and discrete wind shears Flight tests of a simple airborne device for [NASA-CR-152185) pODS3 N78-32106 predicting clear air turbulence encounters WIND TUNNEL APPARATUS 9 rAIAA 78-1375] pOO1 A78-46560 Laser-velocimeter surveys of merging vortices in a NASA aviation safety reporting system wind tunnel (NASA-TM-78511) pOO52 N78-32075 [AIAA PAPER 78-1073 pOO15 A78-20687 WASTE DISPOSAL Use of coherence and phase data between two Earth reencounter probabilities for aborted space receivers in evaluation of noise environments disposal of hazardous nuclear waste pOO16 A78-26495 3 pOO 8 A78-31921 New rotation-balance apparatus for measuring Space ecosynthesis: An approach to the design of airplane spin aerodynamics in the wind tunnel closed ecosystems for use in space [AIAA 78-835 p0017 A78-32386 UNASA-TM-784911 pO051 H78-26740 WIND TUNNEL BALANCES WASTES U WIND TUNNEL APPARATUS NT RADIOACTIVE WASTES WIND TUNNEL MODELS WATER Computational wing optimization and comparisons Advanced solid electrolyte cell for CO2 and H20 with experiment for a semi-span wing model electrolysis --- for extended duration manned [NASA-TM-78180] p0025 N78-26106 spaceflights WIND TUNNEL TESTS fNASA-CR-1520932 p0052 N78-21235 Laser-velocimeter surveys of merging vortices in a WATER BALANCE wind tunnel Fluid-electrolyte shifts and maximal oxygen uptake [AIAA PAPER 78-107) p0015 A78-20687 in man at simulated altitude /2,237 m/ Computational wing optimization and wind tunnel pOO5 A78-36602 test of semi-span model 0 0 WATER TUNNELS [AIAA PAPER 78-102] p 3 4 A78-22575 U HYDRAULIC TEST TUNNELS Buried wire gage for wall shear stress measurements WATER VEHICLES EAIAA 78-798) pOO17 A78-32353 NT SUBMARINES Moving ground simulation by tangential blowing WAVE INTERACTION [AIAA 78-814) pOO17 k78-32368 NT SHOCK WAVT INTERACTION Hot-wire, laser anemometer and force balance The instability of the thin vortex ring of measurements of cross-sectional planes of single constant vorticity and interacting trailing vortices pO031 A78-14622 (AIAA PAPER 78-1194] pOO16 h78-41885 WAVE PROPAGATION Effects of inlet airframe integration on the inlet NT HALOS of an upper surface blowing four-engine STOL NT LIGHT SCATTERING aircraft NT SHOCK WAVE PROPAGATION - [AIAA PAPER 78-959] pOO18 178-43521 On the observation of a flare-generated shock wave Some observations on the mechanism of aircraft at 9.7 AD by Pioneer 10 wing rock 8 [AD-R053721] p003 A78-30078 [AIAA PAPER 78-1456] pO020 A78-47907 WAVE SCATTERING Two-dimensional transonic testing with splitter NT HALOS plates NT LIGHT SCATTERING [NASA-TP-1153] p0004 N78-17999 NT RAMAN SPECTRA Comparison of measured and calculated helicopter WAVELENGTHS rotor impulsive noise --- wind tunnel test data Continued development of doped-germanium and prediction analysis techniques photoconductors for astronomical observations at [NASA-TM-78473) pOOOS 378-20917 wavelengths from 30 to 120 micrometers Acoustical effects of blade tip shape changes on a [NASA-CR-152125) pOU29 N78-22000 full scale helicopter rotor in a wind tunnel
123 WIND TUNNELS SUBJECT INDEX
[NASA-CR-152082] pOO10 U78-20918 An investigation of wing buffeting response at High angle canard missile test in the Ames 1-foot subsonic and transonic speeds: Phase 1: Y-111A transonic wind tunnel flight data analysis. Volume 1: Summary of rNASA-CE-2993] p0011 N78-25057 technical approach, results and conclusions wind tunnel investigation of computationally [NASA-CR-152109] p0013 N18-33113 optimized variable camber wing configurations WOODEN STRUCTURES [NASA-T-78479] p0026 N78-29067 Structural wood panels with improved fire resistance Symmetrical and asymmetrical separations about a ---- using- prepolymers and,heiamethylenetetramine Yawed cone ---- tests- in'the -Ames' 1.8-i 1 8 wind [NASA-CASE-ARC-11174-1) p0050 N78-28178 tunnel WORLD r[ASA-TM-785321 pOO08 178-32045 U EARTH (PLANET) A study of the noise radiation from four WU-2 AIRCRAFT helicopter rotor blades --- tests in Ames 40 by U U-2 AIRCRAFT 20 foot wind tunnel pOO08 178-32835 X Laser-velocimeter surveys of merging vortices in a wind tunnel: Complete data and analysis I RAY ASTRONOMY rNASA-TM-784491 pOO08 178-33043 Generation of a parallel X-ray beam and its use WIND TUNNELS for testing collimators NT LOW SPEED WIND TUNNELS p0035 A78-23083 NT TRANSONIC WIND TUNNELS X RAY SPECTRA WIND VELOCITY The quiet coronal X-ray spectrum of highly ionized NT SOLAR WIND VELOCITY oxygen and nitrogen WINDBILLING pOO38 A78-31108 U AUTOROTATION X RATS WING CAMBER NT SOLAR X-RAYS Computational wing optimization and wind tunnel XV-15 AIRCRAFT test ofsemi-span model Evaluation of the tilt rotor concept: The XV-15's [AIAA PAPER 78-1021 pOO34 A78-22575 role Three-dimensional canard-wing shape optimization pOOOU N78-19142 in aircraft cruise and maneuver environments Development of automatic and manual flight [AIAA PAPER 78-99] pOO16 A78-26274 director landing systems for the XV-15 tilt Computational wing optimization and comparisons rotor aircraft in helicopter mode with experiment for a semi-span wing model [NASA-CE-152140] pO011 N78-22071 rNASA-TM-78480] p 0 0 2 5 N78-26106 WING FLAPS Z Effect of high lift flap systems on the conceptual design of a 1985 short-haul commercial STOL tilt ZERO-GRAVITY rotor transport U WEIGHTLESSNESS [NASA-mM-78474] pOOO5 V78-21094 ZODIACAL LIGET WING FLOW METHOD TESTS Zodiacal light as an indicator of interplanetary Displacement thickness distributions in transonic dust flows about 3-D wings pOO42 A78-38228 p0032 A78-17612 A method for localizing wing flow separation at stall to alleviate spin entry tendencies [AIAA PAPER 78-1476] p0020 A78-49787 WING LOADING The spanvise lift distribution on a wing from flow-field velocity surveys rAIAA PAPER 78-11951 __ pOO18 A78-41886 WINGOSCILLATIONS Some observations on the mechanism of aircraft wing rock [AIAA PAPER 78-1456] p0020 A78-47907 WING PANELS Advanced panel-type influence coefficient methods applied to unsteady three dimensional potential flows 'AIAA PAPER 78-229] p0021 A78-52630 WING PLANFORMS RT DELTA WINGS Three-dimensional canard-wing shape optimization in aircraft cruise and maneuver environments [AIAA PAPER 78-99] p0016 A78-26274 WING PROFILES NT WING SPAN WING SPAN The spanwise lift distribution on a wing from flow-field velocity surveys rAIAA PAPER 78-1195] pOOl A78-41886 WINGS NT CAMBEPED WINGS NT DELTA WINGS NT RIGID ROTORS NT ROTAPY WINGS NT SLENDER WINGS NT SUPERCRITICAL WINGS NT SWEPT WINGS NT THIN WINGS HT TILTING ROTORS NT UNSWEPT WINGS Transonic wing analysis using advanced computational methods rAIAA PAPER 78-105] pOO15 A78-20686 Wing analysis using a transonic potential flow computational method [NASA-TM-78464 pOO07 N78-28053
124 PERSONAL AUTHOR INDEX
Typical Personal Author Index Listing
PERSONALAUTOR CARR, L. W. Water-tunnel experiments on an oscillating airfoil at RE equals 21,000 fNA5A-TM-784q6] p0062 178-19058 AEBA-EAO, C. I. The general solution to the classical problem of the finite Euler-Bernoulli beam p04A7599 ARDEESOl. a. B. TITLE 5c.EON ACCESS.o Toroidal tank evaluationp03A7181 Fluid interaction with spinning toroidal tanks p0 2 4 N78-20186 Listings in this index are arranged alphabeically by personal author The title ANDERSON, J. L. of the document provides the user with a brief descriptimon of the subject matter A method for the analysis of the benefits an The report number helps to indicate the type of document listed le g NASA p07 N78-29060 report translation NASA contractor report) The page and2 arrnn nm bers ADERSON, S. B. are located beneath and to the right of the title e q OO6 N78-19058 Under A h r o. any one authors name the accession numbers are arranged in sequence with A historical the AA ccesionnume'sapperinfist.characteristics overviewof generalof stall/spin aviation aircraft the A accession numbersappearingfirst. [IA PAPER 78-1551) pOO19 A78-46514 A method for localizing wing flow separation at stall to alleviate spin entry tendencies 0 2 0 [AIAA PAPER 78-1476] pO A78-49787 ADUEL-HAIJA, A. I. ANDREWS, D. 0. Digital filter structures having low errors and Application of advanced technologies to small, simple hardware implementation short-haul aircraft p0056 A78-51346 [NASA-CR-1520893 p0Ol 1178-22074 ACHARYA, 1. ANDROES, G. M. Reynolds number and pressure gradient effects on NASA/ESA CV-990 Spacelab simulation (ASSESS 2) compressible turbulebt boundary layers [NASA-CR-152122] p@029 B78-23117 [ATAA PAPER 78-1991 p0D33 A.78-20741 ANTOwIfK, D. An experimental documentation of pressure gradient Extended development of variable conductance heat and Reynolds number effects on compressible pipes turbulent boundary layers 0 0 2 9 6 [NASA-CR-152183] p N78-33379 [ASA-TH-7888] p002 N78-27364 AOYA I, M. ACTOR, L. W. Exchange and relaxation effects in low-energy Demand-type gas supply system for rocket borne radiationless transitions thin-vindow proportional counters [ASA-TM-79383) 000 N78-18882 1 p 4 p003 A78-13845 ARXAYMUDAR, K. S. ADAMS, W. C. A simplified Mach number scaling law for Fluid-electrolyte shifts and maximal oxygen uptake helicopter rotor noise in man at simulated altitude /2,287 in/ p0017 A78-35371 4 pO5 A78-36602 ARDENA, M. D. AGARVAL, B. Comments on 'Feasibility study of a hybrid airship Computation of supersonic laminar viscous flow operating in ground effect' past a pointed cone at angle of attack in pO016 A78-21367 spinning and coning motion ARhOID. a. 0. [AIAA PAPER 78-1211] pO4Q5 A78-45139 A theoretical study of the electronic transition AJBLLO, J. K. moment for the C2 Swan band system The composition Of Phobos - Evidence for p0041 A78-36776 carbonaceous chondrite surface from spectral AROBOWITZ, S. analysis Square Ising ferromagnetic and antiferromagnetic 1. p0032 A78-18874 lattices in a magnetic field - A new multicolor observations of Phobos with the Viking perturbation approach lander cameras - Evidence for a carbonaceous p0056 A8-51886 chondritic composition 2 ARVESER, a. C. p003 A71-1887S Stratospheric measurements of CF2CI2 and 120 AKHTER. A. p 0 0 54 A78-37055 Multi-calculation rate simulations Interhemispheric gradients of CF2C12, CFC13, CCi4, [HAS5A-CR-1553353 pOO09 N78-13765 and N20 AIARIO, a. p0 O4 2 A78-41124 A re-entrant groove hydrogen heat pipe ASHIHARA, a. 4 [AIA 78-420] p0D 0 A78-35603 Thermal structure of the primitive ionosphere ALBUR, H. H. p0O 3 5 A78-23543 Who should conduct aeronautical R and D for the AUGASON, G. C. Federal Government? Airborne photometric observations between 1.25 and 0 1 [NASA-CR-152021] pOO 178-10946 3.25 microns of late-type stars ARMAWDER, A. D. ITT p0036 A78-25295 A review of NASA-sponsored technology assessment AVEREE, B. 3. projects- Space ecosyrthesis: An approach to the design of (NASA-TM-78472] p0025 B78-24000 closed ecosystems for use in space ALYEA, F. N. [ItASA-TM-78491] pO051 N78-26740 eteorological control of lower stratospheric AXFOED, W. I. minor species variations - An observational Quiet time interplanetary cosmic ray anisotropies example observed fromPioneer 10 and 11 pools1978-6011 p0039 A78-4567
125 DACKBUS' D. R. PERSONAL AUTHOR INDEX
BEXDAL,. B. J. Carbon suboxide polymer, an explanation for the wave of darkening on Mars BACKUS, D. R. p0056 A78-48717 Hot-wire, laser anemometer and force balance BERGER, B_ I. measurements of cross-sectional planes of single Conceptual design study of a Harrier V/STO and interacting trailing vortices research aircraft [AIAA PAPER 78-1194] pOO18 A78-41885 [NASA-CR-152086]_ p0009-1178-19094 BAILEY, F- E. BERGER, T. A. Computation of transonic flow past projectiles at Advanced solid electrolyte cell for C02 and H20 angle of attack electrolysis (AIAA PAPER 78-1182] p0044 A78-41875 [VASA-CR-152093] p0052 378-21235 A view toward future fluid dynamics computing BEBKSTBESSE, B. K. [AIAA PAPER 78-1112] pOD45 A78-45126 Integrated avionics for future general aviation BALDWIN, B. aircraft Thin-layer approximation and algebraic model for [AIAA PAPER 78-1482] p0 0 2 0 A78-47927 separated turbulent flows BEREAUEP, B. H. [AIlA PAPER 78-257) p0033 A78-20776 Fluid-electrolyte shifts and maximal oxygen uptake BALLEAUS, W. P. in man at simulated altitude /2,287 a/ Computational wing optimization and wind tunnel p0054 A78-36602 test of semi-span model HIXHEET, V. B. [AIAA PAPER 78-102] pO034 A78-22575 Jet pump assisted arterial heat pipe Computational wing optimization and comparisons [AIAA 78-443] p0040 A78-35622 with experiment for a semi-span wing model BIGGERS, J. C. [NASA-TM-78480] p0025 N78-26106 A note on multicyclic control by swashplate Wind tunnel investigation of computationally oscillation optimized variable camber wing configurations [NASA-TM-78475] pOO05 H78-21159 [NASA-TK-78479] p0026 N78-29067 BILAMI, A. J_ BALLOU, E. V. Application of second-order turbulent modeling to Chemical interpretation of Viking Lander 1 life the prediction of radiated aerodynamic sound detection experiment [NASA-CR-2994] pOO12 V78-25359 pOO53 A78-25560 BILLHA, A. W. BARCA, y. Measuring the velocity of individual atoms in real Accordion shelter hardware analysis 0 0 7 time [AD-A053592] pO 378-28278 p0 0 3 5 A78-23124 BARNES, A. Satellite mirror systems for providing terrestrial The spiral field inhibition of thermal conduction power - System concept in two-fluid solar wind models 4 0 0 4 6 (AAS 77-240] pO O A78-36717 p A78-48281 A cesium plasma TELEC device for conversion of Acceleration and heating of the solar wind laser radiation to electric power 0 0 29 p N78-32991 p 0 04 8 A78-51067 BARNES, C. W BINDER, J_ D. Acceleration of nucleons in the interplanetary Jupiter probe heatshield configuration optimization space and the modulation of Jupiter electrons in - CAIAA PAPER 78-843] p0 0 4 1 A78-37270 the interval from 1 to 10 A.U- by corotating BLACK, D. regions of solar origin 7 Abstracts for the Planetary Geology Field pOO3 A78-29684 Conference on Aeolian Processes BAUER, Z. [NASA-TM-78455] p0 0 2 2 N78-13492 The co-adsorption of copper and oxygen on a BLANCHARD, M_ B. tungsten 100 plane-type surface Analysis of ablation debris from natural and 0 03 7 p A78-29489 artificial iron meteorites BAUM, J. A. pOO39 A78-34506 Prop-fan data support study Are the stratospheric dust particles meteor [NASA-CR-152141] pOOl3 N78-27128 ablation debris or interplanetary dust? BAYLINK, D. J. (ASA-TH-78507] p0 0 2 8 378-34014 Inhibition of bone formation during space flight Meteor ablation spheres from deep-sea sediments pOO56 A78-51225 [NASA-TM-78510] p0 0 2 8 N78-34021 BBLLIVEAU, J. W. BLASIUS, K. R. Calcium transport in Halobacterium halobium Some Martian volcanic features as viewed from the envelope vesicles Viking orbiters pOO55 h78-48574 p0030 A78-11403 BELLUM, J. C. BLDHKE, I. E. Quantum mechanical theory of collisional Aircraft cargo compartment fire test simulation ionization in the presence of intense laser program radiation [NASA-CR-1519513 0 0 3 5 p0029 N78-21223 (AD-A052981] p A78-23576 BODE, V. E. BENCOSME, A. J. Conceptual design study of a Harrier V/STOL Infrastructure dynamics: A selected bibliography research 2 aircraft (NASA-CR-152162] pOO1 N78-25824 [EASA-CR-152086] pOO09 N78-19094 BENCZE, D_ P. BODE3BHRER, P. Estimating maximum instantaneous distortion from Evolution of rotating interstellar clouds. III - inlet total pressure rms measurements On the formation of multiple star systems (AhAA PAPER 78-970] pOO19 A78-43525 p0047 A78-49471 BEBEPE, D. B. BOESE, R. W_ An investigation of wing buffeting response at Comments on the note by Arie et al. on the subsonic and transonic speeds: Phase 1: F-11lA transition moment of the C02 band near 7740 flight data analysis. Volume 1: Summary of kaysers technical approach, results and conclusions pOO 4 8 A78-52388 3 [(ASA-C-152109] pOO1 878-33113 BOETTCHER, D. H. An investigation of wing buffeting response at Extent of utilization of the Frank-Starling subsonic and transonic speeds. Phase 2: F-i11A mechanism in conscious dogs flight data analysis. Volume 2: Plotted power pOO5 A78-33522 spectra BOGDOOFF, S. 1. [NASA-CR-152113] pOO13 378-33117 A detailed study of attached and separated An investigation of wing buffeting response at compression corner flowfields in high Reynolds subsonic and transonic speeds. Phase 2: F-111A number supersonic flow flight data analysis. Volume 3: Tabulated [AIAA PAPER 78-1167] p0043 A78-41865 power spectra BOGOMOLVI, R. A. [NASA-CR-1521141 pOO14 N78-33118 Illumination-dependent changes in the intrinsic
126 PERSONAL AUTHOR INDEX CEBECI, T.
fluorescence of bacteriorhodopsin role 4 p0055 178-48578 pOO0 178-19142 BOISSEVAIX. A. G. BREiLERB, D. E. Quiet, Short-Haul Research Aircraft - Current Meteor ablation spheres from deep-sea sediments 0 0 status and future plans [NASA-TM-78510] p 2 8 U78-34021 (AIAA PAPER 78-1468] p0020 A78-47916 BRUBAKER, P. V. BOITBOT?, C. . Application of advanced technologies to small, Lover stratosphere measurements of variation with short-haul aircraft latitude of CF2C12, CFC3, CC14, and N20 [NASA-CR-152089] p0011 H78-22074 profiles in the northern hemisphere BRTAT, S. 1. p0035 A78-23610 Application of advanced technologies to smll, BOLES, R. A. short-haul aircraft Moving ground simulation by tangential blowing [NASA-C-152089] pOO11 178-22074 EAIAA 78-814] pO017 178-32368 BUCHIER, A. BOLLINGER, L. The prediction of toxic atmospheres from Requirements for regional short-haul air service decomposing polymers and the definition of a flight program to p0033 A78-19895 determine neighborhood reactions to small BUNCH, T. B. transport aircraft Meteor ablation spheres from deep-sea sediments [RASA-CR-152151] p0013 N78-30070 [tASA-TH-78510] p0 0 2 8 N78-34021 BORN, G. J. BURGENBAUCH, S. optimal control theory (OwBn) applied to a Critical review of Ames Life Science participation helicopter in the hover and approach phase in Spacelab Mission Development Test 3: The SMD (lASA-CR-152135] p0010 178-21161 3 management study BORUCKI, a. G. [NAS&-TM-78494] pOO51 178-26973 Geographical variations of' NO and 03 in the lower BURRS, J. A. stratosphere Radiation pressure and Poynting-obertson drag for p0039 A78-35403 small spherical particles DeDUcKE, V. J. pOO3S 178-19768 Geographical variations of No and 03 in the lower stratosphere C p0039 178-35403 BOUSBiA, W- G. CALLAS, 0. P. An experimental investigation of hingeless Integrated avionics for future general aviation helicopter rotor-body stability in hover aircraft [NASA-TH-78489] po63 N78-29044 [AIAA PAPER 78-1482] p 0 0 2 0 A78-47927 BRER, S. W. CANDFIARIA, C. Satellite mirror systems for providing terrestrial Dynamic MHD modeling of the solar wind power - System concept disturbances during the August 1972 events [AAS 77-240] p0040 178-36717 p0036 178-26079 BOWLES, J. V. CAPONE, t. A- Application of advanced high speed turboprop An assessment of the effect of supersonic aircraft technology to future civil short-haul transport operations on the stratospheric ozone content aircraft design [ISAI-RP-1026] p0 0 2 7 178-30774 [AIAA PAPER 78-1487] p0064 A78-47930 CARAVALnO, R. Requirements for regional short-haul air service Demand-type gas supply system for rocket borne and the definition of a flight program to thin-window proportional counters determine neighborhood reactions to small p0031 178-13845 transport aircraft CARLSON, R. W. [ASA-CE-152151] p0013 N78-30070 Europa - Ultraviolet emissions and the possibility BOXWLL, D. A. of atomic oxygen and hydrogen clouds Hovering impulsive noise: Some measured and p0048 178-52482 calculated results CARMICHAEL, B. L. p0063 N78-32831 Three-dimensional canard-wing shape optimization BOYKIR, . - in aircraft cruise and mancuver environments Multichannel electrochemical microbial detection (111 PIPER 78-99] pOO1 6 178-26274 unit CARNEY, B. p0016 178-31300 C02 laser-driven Stirling engine 2 BU TT. P. R. pO0 1 178-49804 Continued development of doped-germanium CARE, I. V. photoconductors for astronomical observations at Dynamic stall experiments on the NACA 0012 airfoil wavelengths from 30 to 120 micrometers fNASA-TP-11001 p006 2 178-17000 [ASA-CR-152125] p0029 N78-22000 Water-tunnel experiments on an oscillating airfoil BRANWALD, B. at RE equals 21,000 Extent of utilization of the Frank-Starling [NASA-TH-78446] p00 6 2 178-19058 mechanism in conscious dogs A computer program for calculating laminar and p0054 A78-33522 turbulent boundary layers for two-dimensional BERGMAN, J_ D. time-dependent flows C3 and infrared spectrophotometry of Y Canum [NASA-TM-78470] pOO51 178-19444 Venaticorum dRID, M. H. p0042 A78-39448 Some Martian volcanic features as viewed from the BREWED, R. B. Viking orbiters Lower stratosphere measurements of variation with p0030 178-11403 latitude of CF2C12, C1C13, CC14, and N20 CARSOR, T. M. profiles in the northern hemisphere Optimal guidance and control for investigating p0035 A78-23610 aircraft noise-impact reduction Stratospheric measurements of CF2CI2 and 120 [ASA-TP-1237] p0006 V78-23100 p0054 A78-37055 CATURA, I. C. BRICKMAR, R_ A. Demand-type gas supply system for rocket borne Hot-wire, laser anemometer and force balance thin-window proportional counters measurements of cross-sectional planes of single p0031 A78-13845 and interacting trailing vortices CIVIl, R. K. [AIA PAPER 78-1194] p0018 A78-41885 Static and dynamic stability analysis of the space BRITT, B. _ shuttle vehicle-orbiter A cesium plasma TELEC device for conversion of [NISA-TP-11791 p0 0 0 5 B78-20176 laser radiation to electric power CEBECI, T. pO048 A78-51067 A computer program for calculating laminar and BROWN, J. B.- JR. turbulent boundary layers for two-dimensional Evaluation of the tilt rotor concept: The XV-15's time-dependent flows
127 CRANG S. PERSONAL AUTHOR INDEX
at 9.7 AU by Pioneer 10 NASA-TM-78470] pOO51 N78-19444 0 CHANG, S. [AD-AO53721] p 038 A78-30078 Chemical evolution and the origin of life - CONLON, J. A. Bibliography supplement 1976 Application of advanced high speed turboprop pOO57 A78-53875 technology to future civil short-haul transport CHAPMAN, G. T. aircraft design The shock tube as a device for testing transonic f[ATIAPAPER 78-1487] p0064 178-47930 airfoils at high Reynolds numbers CONLON, T. F.- 7 [-AIAA 7.8s769.] pOO1 &78-32330 The interplanetary modulation and transport of CHER, a. H. Jovian electrons Exchange and relaxation effects in low-energy p0036 A78-26080 radiationless transitions Acceleration of nucleons in the interplanetary 4 [NASA-TM-79383J pOOO N78-18882 space and the modulation of Jupiter electrons in CHEN, R. H. the interval from I to 10 A.U. by corotating A comprehensive model of the Venus ionosphere regions of solar origin pOO38 A78-30071 p0037 A78-29684 The ionosphere and airglow of Venus - Prospects CONNORS, M. a. for Pioneer Venus A bibliography on the search for extraterrestrial p0845 k78-44773 intelligence CUENETTE, D. I. [NASA-RP-1021] pOO1 B78-21019 Acceleration of nucleons in the interplanetary COOK, K. N. space and the modulation of Jupiter electrons in Food and oxygen requirements fof growing mice and the interval from 1 to 10 A.1. by corotating turtles after hypergravitational development 0 0 3 1 regions of solar origin 7 p A78-15204 p003 178-29684 cOOK, I. P. CHOeG, D. P. A unigueness proof for a transonic flow problem semirigorous bounds for the dipole moments and pO016 A78-26599 transition moments of the LiH molecule Lifting line theory for transonic flow 0 4 6 pO A78-45963 pOO20 A78-48991 CHRISTENSEN, W. N. COOK, W. a. Chelate-modified polymers for atmospheric gas The shock tube as a device for testing transonic chromatography airfoils at high Reynolds numbers [NASA-CASE-AR-11154-1] pOO57 H78-27275 [hAl 78-769] pOO17 A78-32330 CHURCH, C. A study of test section configuration for shock Occultation of Epsilon Geminorum by Mars. II - The tube testing of transonic airfoils structure and extinction of the Martian upper [NASA-CR-157237] p0012 N78-26153 atmosphere CORSIGLIA, V. E_ p0030 A78-10587 Laser-velocimeter surveys of merging vortices in a CHURNS, J. wind tunnel The radii of Uranian rings alpha, beta, gamma, [AIAA PAPER 78-107] pools 178-20687 delta, epsilon, eta, 4, 5, and 6 from their Hot-wire, laser anemometer and force balance occultations of SA0 158687 measurements of cross-sectional planes of single pO46 A78-48112 and-interacting trailing vortices CUYU, W. J [IAA PAPER 78-1194] pOOlS A70-41885 Static and dynanic stability analysis of the space Laser-velocimeter surveys of merging vortices in a shuttle vehicle-orbiter wind tunnel: Complete data and analysis 0 0 0 5 [NAS-TP-1179] p V78-20176 [NASA-TH-78449] pOOOS 78-33043 CIFFOXE, D. L. CRANE, D. F_ Measured wake-vortex characteristics of aircraft Simulation replay - Implementation and flight in ground effect simulation applications [aIAl PAPER 78-109] pOOls X78-22578 p0018 A78-38789 CLAY, C. W. CRASEANN, B. Application of advanced technologies to small, Exchange and relaxation effects in low-energy short-haul aircraft radiationless transitions [NASA-CR-152089] pOO11 178-22074 [NASA-TH-79383] p0004 178-18882 CLEBENT, W. F. CRAVEES, T. 3. Simulation and analysis of wind shear hazard The ionosphere and airglow of Venus - Prospects [NASA-CR-157470] p0053 H78-29699 for Pioneer Venus COCHERAE, J. A. pOO45 A78-44773 Quiet, Short-Haul Research Aircraft - Current CUMMING, H. 3. status and future plans ALC/50/ values for some polymeric materials 0 [A(AA PAPER 78-1468] p0020 178-47916 pO04 A78-36596 COECKEUENBEEGH, Y. CUNNINGEM, A. M., JR. Computer display and manipulation of biological An investigation of wing buffeting response at molecules subsonic and transonic speeds: Phase 1: F-111A 0 0 5 6 p &78-53400 flight data analysis. Volume 1: Summary of COHEN, L. E_ technical approach, results and conclusions Low speed aerodynamic characteristics of an [NASA-CR-152109] pOO13 N78-33113 0.075-scale F-15 airplane model at high angles An investigation of wing buffeting response at of attack and sideslip subsonic and transonic speeds. Phase 2: F-111A 4 - [NASA-TN-X-62360] pOO0 H78-10019 flight data analysis. Volume 2: Plotted power COLBURN, D. spectra Multicolor observations of Phobos with the Viking (NASA-CR-152113] p0013 N78-33117 lander cameras - Evidence for a carbonaceons An investigation of wing buffeting response at chondritic composition subsonic and transonic speeds. Phase 2: F-111A p0032 A78-18875 flight data analysis. Volume 3: Tabulated COLE, J. D. power spectra Lifting line theory for transonic flow [NASA-CR-152114] pOO14 N78-33118 p0020 178-48991 CURNOLD, D. M. COLEMAN, P. a. JR. Meteorological control of lower stratospheric The radial dependences of the interplanetary minor specaes variations - An observational magnetic field between 1 and 5 AD Pioneer 10 example 8 pOO4 178-52504 p0019 A78-46011 COTES, D. CUSRI, 2. 5. Flying-hot-wire study of two-dimensional mean flow Saturn's rings: Particle composition and size past an BACA 4412 airfoil at maximum lift distribution as constrained by microwave [ATAl PAPER 78-1196] p0018 A78-41887 observations. I - Radar observations COLLARD, f. R. p0036 178-25676 On the observation7 of a flare-generated shock wave
128 PERSONAL AUTHOR INDEX DUNHAM, E.
DEVASIA, K. J. D An integral solution to a nonlinear diffusion problem DAILY, W. D p0037 A78-26350 Crustal evolution inferred from Apollo magnetic DEVICARIIS. R_ measurements Generation of a monodispersed aerosol [rASA-TM-78524] p0027 W78-32029 fNASA-CR-152133] pOOl1 H78-21445 DAJARI, J. S. DEVRIES, P. L. Assessing the future of air freight Quantum mechanical theory of a structured [N&SA-CR-152161] pOO09 W78-14016 atom-diatom collision system - A + BC/1-Sigma/ Infrastructure dynamics: A selected bibliography [AD-AO51266] 2 p0031 A78-16454 fNASA-CR-152162] pOO1 N78-25824 A new concept in laser-assisted chemistry - The Planning for airport access: An analysis of the electronic-field representation San Francisco Bay area p0037 A78-27743 (NASA-CP-2044] pOO01 N78-26152 Computational study of a molecular collision DALLEAN, t. F_ process in the presence of an intense radiation Hormonal indices of tolerance to *Gz acceleration field - Enhanced quenching of F by Xe in the in female subjects 248-nm light of the KrF laser pOO55 A78-41162 [AD-AO54078] p0044 A78-42818 DANIELS, T. C_ DICKEY, R. I. Experimental temperature distribution and heat The response of heat-shield materials to intense load characteristics of rotating heat pipes laser radiation 0 04 6 p A78-48835 EAIAA PAPER 78-138] p0034 A78-22583 DASH, R. Carbonaceous materials subjected to extreme Analysis of flight effects on noise radiation from heating - A comparison of numerical simulation jet flow using a convecting quadrupole model and experiments [AIAA PAPER 78-192] pOO15 A78-22594 [AIAA PAPER 78-866] p0041 A78-37273 DAVflI, B. DICKINSON, J. T. Effect of a nonconstant C/m-alpha/ on the Chemisorption of CO on Pd particles supported on stability of rolling aircraft mica p0831 A78-16180 p0040 A78-36040 DAVENPORT, F. J. DIEHL, J. J. Pel saving potential of Mach 0-8 twin engine application of a cost/performance measurement prop-fan transports 7 system on a research aircraft project . pOO1 A78-31306 NAS-T8-78498] p0007 H78-27043 DAVIS, A. S. DIGONARTHI, R. V. Analysis of ablation debris from natural and Use of leaning vanes in a two stage fan artificial iron meteorites [NASA-CR-152134] p0O10 N78-21115 p0039 A78-34506 DIRLIRG, R. B., JR. DAVIS. P. R. Jupiter probe heatshield configuration optimization The co-adsorption of copper and oxygen on a [AIAA PAPER 78-843] p0041 A78-37270 tungsten 100 plane-type surface DODGE, C. H. p0037 A78-29489 Food and oxygen requirements for growing mice and DAVIS, S_ turtles after hypergravitational development Two-dimensional transonic testing with splitter p0031 k78-15204 plates 4 DODS, J. H., JR. (NASA-TP-1153] pOOD H78-17999 An analysis of the rotor blade stresses of the DAVIS, S. S. three stage compressor of the Ames Research Visualization of quasi-periodic unsteady flows Center 11- by 11-foot transonic wind tunnel [AIAA 78-502] p0016 &78-29804 [NASA-CR-152083] p0O09 N78-17061 DAVY, 9- C_ DOMINGO, V. Carbonaceous materials subjected to extreme Rigidity-independent coronal propagation and heating - A comparison of numerical simulation escape of solar protons and alpha particles and experiments 1 p0041 A78-37354 [ATAA PAPER 78-866] pOO4 A78-37273 DRUET, S. A. J. D SILVA, B. M. R. Diagrammatic evaluation of the density operator Three-dimensional canard-wing shape optimization for nonlinear optical calculations in aircraft cruise and maneuver environments [ONERA, TP NO. 1977-166] p0031 A78-14651 ,[AIA PAPER 78-99] pOO16 A78-26274 DRYER, N. DEEREES, RE. Dynamic NED modeling of the solar wind Pioneer Jupiter orbiter probe mission 1980, probe disturbances during the August 1972 events -description 0 0 29 p0036 A78-26079 [ASA-CR-137591] p H78-33127 On the observation of a flare-generated shock wave DELAEO, C. B. at 9.7 AU by Pioneer 10 Polymeric foams from cross-linkable [AD-A053721] p0038 178-30078 pnly-n-arylnebenrimidazoles Dynamic MHD modeling of solar wind corotating 0 0 50 [NASA-CASE-ARC-11008-1] p N78-31232 stream interaction regions observed by Pioneer DELAPLAINE, R. W, 10 and 11 Sweat collection capsule p0049 A78-52522 [NASA-CASE-hRC-11031-1] p805 7 N78-22720 DUCAO, A. S. Rotary leveling base platform Jet pump assisted arterial heat pipe [NASA-CASE-ARC-10981-1] p0060 V78-27425 [AIAA 78-443] p0040 A78-35622 DENERY, D. G. DULLER, C. E., III Integrated avionics for future general aviation Flight tests of a simple airborne device for aircraft predicting clear air turbulence encounters 2 [AIAA PAPER 78-14823 pOO 0 A78-47927 [ATIA 78-1375) pOO19 A78-46560 DESANTIS, C_ M. DUMAS, P. a. Low profile antenna performance study. Part 2: Prop-fan data support study Broadband antenna techniques survey [RASA-CR-152141] pOO13 N78-27128 0 0 2 2 (AD-A047992] p N78-18274 DURHAE, E. DESIDERI, J. A. Occultation of Epsilon Geminorum by Mars. I1 - The On improving the iterative convergence properties structure and extinction of the Martian upper of an implicit approximate-factorization finite atmosphere difference algorithm 1 p0030 A78-10587 0 0 2 6 [NASA-TM-78495] p H78-26795 The radii of Uranian rings alpha, beta, gamma, DESMARAIS, D_ J. delta, epsilon, eta, 4, 5, and 6 from their Light element geochemistry of the Apollo 12 site occultations of SAO 158687 4 pOO A78-34503 p0046 A78-48112
129 DUNMEER, W. D. PERSONAL AUTHOR INDEX
DUNMTER, R. D. Advanced panel-type influence coefficient methods An investigation of wing buffeting response at applied to unsteady three dimensional potential flows subsonic and transonic speeds: Phase 1: F-111A 00 2 1 flight data analysis. Volume 1: Summary of [AIAA PAPER 78-2291 p A78-52630 technical approach, results and conclusions ERICKSON, E. F (NASA-CE-152109] pOO13 N78-33113 C3 and infrared spectrophotometry of Y Canum An investigation of wing buffeting'response at Venaticorum 0 0 4 2 subsonic and transonic speeds. Phase 2: F-1liA -p A78-39448 flight data-analysis. -volume-2: Plotted'power Infrared excesses in early-type stars - Gamma spectra Cassiopeiae [NASA-CR-152113] pOO13 N78-33117 p0047 A78-49475 Engineering tests of the C-i4 telescope An investigation of wing buffeting response at 2 subsonic and transonic speeds. Phase 2: p-llA [ASA-TM-78467) p0O 5 V78-25017 flight data analysis, volume 3: Tabulated Peaker: An automatic boresight peaking routine power spectra for the C-141 telescope [(D&SA-CR-152114] pOOl 4 N78-33118 [VASA-TM-78516] pO028 N78-32856 DUNKN, F. K_ ERICKSON, L_ L- Theoretical study of multicyclic control of a Static and dynamic stability analysis of the space controllable twist rotor shuttle vehicle-orbiter 0 0 6 4 [NASA-CR-151959] p N78-33085 [NASA-TP-1179] pOO05 N78-20176 DURISEN, R H. ERZBEDGER, S. Nova-driven winds in globular clusters 0 4 1 Optimum horizontal guidance techniques for aircraft p0 A78-37649 p0 0 0 6 N78-23016 DUSTO, A. R. ESTRELLA, C. A- Advanced panel-type influence coefficient methods Catalysts for imide formation from aromatic applied to unsteady three dimensional potential isocyanates and aromatic dianhydrides flows [ASA-CASE-AfC-11107-1) p0049 V78-22156 [AAA PAPER 78-229] p0021 A78-52630 EYSIiK, H. DYAL, P. A study of commuter airplane design optimization Crustal evolution inferred from Apollo magnetic [HASA-CR-157210] pOO1178-25078 measurements [NASA-TM-78524] p0027 978-32029 F YAIRBARK, . M., JR. E Measuring the velocity of individual atoms in real EDENHOROUGH, H. K_ time Evaluation of the tilt rotor concept: The XV-15's pOO 3 5 A78-23124 role FEDERSPIEL, Jo P. pOO04 N78-19142 Static tests of a large scale swivel nozzle thrust EDWARDS, D. K. deflector Extended development of variable conductance beat (NASA-CR-152091) pOO11 N78-22100 pipes FREER, K. [NASA-CR-152183) p0029 N78-33379 Requirements for regional short-haul air service EGAN, W. G and the definition of a flight program to Comparison between infrared Martian disk spectra determine neighborhood reactions to small and optical properties of terrestrial analogs transport aircraft p0047 A78-49231 [EASA-CE-152151] p0013 N78-30070 EHLERS, F. E. FEINGOLD, H. An improved higher order panel method for Earth reencounter probabilities for aborted space linearized supersonic flow disposal of hazardous nuclear waste [AIAA PAPER 78-15] p0 0 2 1 A78-52628 pOO38 A77-31921 A Mach line panel method for computing the FEISTEL, T_ M_ linearized supersonic flow over planar wings A method for localizing wing flow separation at 2 [NASA-CR-152126] pOO1 H78-27087 stall to alleviate spin entry tendencies 2 ELIEZER, D_ [AIAA PAPER 78-1476] pGO O A78-49787 Hydrogen attack - Influence of hydrogen sulfide FESTER, D_ A- 4 4 p00 A78-44108 Toroidal tank evaluation ELLIOT, J. L. p0 0 3 2 A78-17881 Occultation of Epsilon Geminorum by Mars. II - The Fluid interaction with spinning toroidal tanks structure and extinction of the Martian upper p00 2 4 178-20186 atmosphere FEWELI, L. I. p0030 A78-10587 Fire resistivity and toxicity studies of candidate Signal-to-noise ratios for stellar occultations by aircraft passenger seat materials the rings of Uranus, 1977-1980 p0048 A78-51838 p0033 A78-20223 Fire resistivity and toxicity studies of candidate Analysis of stellar occultation data - Effects of aircraft passenger seat materials 24 photon noise and initial conditions [ASA-TM-78468] p00 178-21214 pOO35 A78-23164 FILLIUS, 1- The radii of Uranian rings alpha, beta, gamma, Quiet time interplanetary cosmic ray anisotropies delta, epsilon, eta, 4, 5, and 6 from their observed from Pioneer 10 and 11 0 0 3 9 occultations of SAO 158687 p A78-34567 p0046 A78-48112 FITZPATRICK, T. J. - ELMORE, G. A. A detailed study of attached and separated Conceptual design study of a Harrier V/STOL compression corner flowfields in high Reynolds research aircraft number supersonic flow 9 [NASA-CR-152086] pOOO V78-19094 [AIAA PAPER 78-1167] p00 4 3 A78-41865 EIPHIC, R. C. FLANAGAN, P. F. On the apparent source depth of planetary magnetic Development and flight tests of a Kalman filter fields for navigation during terminal area and landing pOO37 A78-29472 operations ENGLISH, J. R. [NASA-CR-3015] pOO1 2 N78-27105 A study of characteristics of intercity FORREST, R. D. transportation systems. Phase 1: Definition of Certification study of a derivative model of a transportation comparison methodology small jet transport airplane using a piloted [NASA-CN-152153-2] pOO01 178-29996 research simulator EPTO, 5. . [AD-A0464421 pOO 6 178-14033 An improved higher order panel method for FORSHAM, P. linearized supersonic flow Hormonal indices of tolerance to *Gz acceleration 0 0 2 1 rAIAA PAPER 78-15] p A78-52628 in female subjects
130 PERSONAL AUTEOR INDEX GREELEY, I.
pO055 A78-41162 Computational study of a molecular collision FORWARD, R. I- process in the presence of an intense radiation A bibliography on the search for extraterrestrial field - Enhanced quenching of F by Xe in the intelligence 248-m light of the KrF laser fNASA-RP-1021] p0051 N78-21019 [AD-AO54078 p0 0 4 4 A78-42818 FOUNTAIN, J. GXERASCH, P. J. The Pioneer 11 imaging experiment of Jupiter occultation of Epsilon Geminorum by Mars- I - The p0032 A78-18173 structure and extinction of the Martian upper FOWLER, K. R. atmosphere A method for determining structural properties of pOO 3O A78-10587 RCC thermal protection material Analysis of stellar occultation data - Effects of [AIA PAPER 78-869] p0040 A78-35997 photon noise and initial conditions FRENCH, R. G. p0035 A78-23164 Occultation of Epsilon Geminorum by Mars. II - The GILBREATH, W. P. structure and extinction of the Martian upper satellite mirror systems for providing terrestrial atmosphere power - System concept pO030 A78-10587 ([AS77-240] p0040 A78-36717 Analysis of stellar occultation data - Effects of GILWER, W. J., JR. photon noise and initial conditions Relative toxicity of the pyrolysis products from p0035 A78-23164 some thermoplastic and thermoset polymers FRIEDLANDER, A. L. pOO 4 2 A78-41213 Earth reencounter probabilities for aborted space GIRIDHARADAS, B. disposal of hazardous nuclear waste Application of advanced technologies to small, p0038 A78-31921 short-haul aircraft FRIEOAH, D. L. [8ASA-CR-152089] pOO11 78-22074 Light element geochemistry of the Apollo 12 site GIEESOY, L. ._ pO54 A78-34503 Quiet time interplanetary cosmic ray anisotropies FEOECHTEIGT, J. P. observed from Pioneer 10 and 11 Experimental investigation of contamination pO0 3 9 A78-34567 prevention techniques to cryogenic surfaces on GOEBEL, J. B. board orbiting spacecraft C3 and infrared spectrophotometry of Y Canum ([ASA-CR-152171] p0029 U78-29146 Venaticorum PROMME, 0. p0 0 4 2 178-39448 Numerical solution of a class of integral GOESTZ, C. K. equations arising in two-dimensional aerodynamics On determining magnetospheric diffusion pOOl8 A78-40949 coefficients from the observed effects of FRYER, T. B_ Jupiter's satellite 10 An inductively powered telemetry system for p0O 3 2 A78-18732 temperature, EKG, and activity monitoring Energetic protons associated with interplanetary (NASA-TM-78486] pOO5S N78-23706 active regions 1-5 AU from the sun FURG, .-Y. p0 0 3 6 A78-26081 Unsteady transonic flow computations On the modulation of the Jovian decametric p0032 A78-18274 radiation by lo. I - Acceleration -of charged A new method for designing shock-free transonic narticles configurations p00 4 2 A78-41074 [AIAA PAPER 78-1114] pOO45 A78-45127 Correction to 'Recirculation of energetic particles in Jnpiter's magnetosphere' 4 pOO 5 A78-44775 G Whistler mode noise in Jupiter's inner magnetosphere GAMBUCCI, B. J. pOO5 A78-45188 Effect of high lift flap systems on the conceptual GOLBERG, M. A. design of a 1985 short-hlal-comaexcial STOL tilt Rumerical solution of a class of integral rotor transport equations arising in two-dimensional aerodynamics [8ASA-TH-78474] po05 U78-21094 pOOl8 178-40949 GARBUNY, N° GOLDSTEIN, B. E. Thermodynamic processes induced by coherent Fibrous refractory composite insulation radiation [ASA-CASE-ARC-11169-1I p005 0 x78-32189 p0034 A78-21624 Reaction cured glass and glass coatings GARRETT, S_ 1. [VASA-CASE-AEC-11051-11 p0050 U78-32260 Non-linear parametric generation of sound by GOLUB, B. A. resonant mode conversion Thermal rearrangements in 1,2-poly/1,4-hexadiene/s (AD-A0491573 p0059 H78-19901 pOO48 A78-51870 GAULT, D. GOODWIN, A. L. Interpreting statistics of small lunar craters Hormonal indices of tolerance to *Gz acceleration p0042 A78-41753 in female Subjects GAULT, D. E. pO55 A78-41162 An analytic study of impact ejecta trajectories in GORESSTEIR, S. V. the atmospheres of Venus, Mars, and earth Radiometer system to map the cosmic background p0037 A78-29532 radiation GEORGE, T. F. pOO3 8 A78-30691 Quantum mechanical theory of a structured GOREHAM, . A atom-diatom collision system - A . BC/1-Sigma/ Study to determine operational and performance [AD-1051266] pOOf31A78-16454 criteria for STOL aircraft operating in low Quantum mechanical theory of collisional visibility conditions ionization in the presence of intense laser [ASA-CR-152164] pOO1 3 W78-28083 radiation GOVER, M. C. [A0-AO52981] pOO35 A78-23576 Collisionless dissociation of SF6 using two A new concept in laser-assisted chemistry - The resonant frequency C02 laser fields electronic-field representation 0 0 3 7 p0031 178-14655 p A78-27743 GREELEY, R_ Semiclassical approach to collision-induced Some Martian volcanic features as viewed from the enission in the presence of Intense laser Viking orbiters radiation - An aspect in the study of p0030 A78-11403 cooperative chemical and optical pumping7 Interpreting statistics of small lunar craters p003 A78-27744 pOO4 2 178-41753 Semiclassical theory of unimolecular dissociation Abstracts for the Planetary Geology Field induced by a laser field Conference on Aeolian Processes 0 039 CAD-A056671] p A78-34682 ([ASA-TM-78455) p0022 78-13492
131 GREEN, f. J. PERSONAL AUTHOR INDEX
GREEN, M. J. HALL, G. W. Aerothermodynamic environment for Jovian entry Flight simulation - A vital and expanding with silica heat shield technology in aircraft development (A1IA PAPER 78-186] pO033 A78-20730 [AIAA PAPER 78-337] pOO16 A78-29295 GREENLEAF, J. H. SA1LICK, T. N. Fluid-electrolyte shifts and maximal oxygen uptake Technology advancement of the electrochemical C02 in man at simulated altitude /2,287 m/ concentrating process pOO5 A78-36602 [.NASA-CR-152098]- p0052 178-22723 Sweat collection capsule 7 HARANOTO, f. [NASA-CASE-ARC-11031-1] p005 N78-22720 Application of advanced technologies to small, GREENOUGH. B. short-haul aircraft An investigation of the reduction of carbon [NASA-C-152089] pOO11N78-22074 dioxide in a silent electric discharge HAASAKI, R. H. [NASA-CR-152146) p8o53 978-25767 Study of a high performance evaporative heat GREGORY, T- J. transfer surface 2 Future requirements and roles of computers in fNASA-CR-152008] pOO 8 N -78-10411 aerodynamics NAMED, A. p0004 P78-19786 Stress analysis study in cooled radial inflow GROSSITH, S. W. turbine A flight investigation of the stability, control, [AIAA PAPER 78-94] p0064 A78-22570 and handling qualities of an augmented jet flap BAMNER, J_ STOL airplane A study of commuter airplane design optimization [NASA-TP-1254] pO006 N78-26151 [NASA-CE-157210] pOO11 N78-25078 GRUNBADUE, B. W_ HANEY, H. P. Automatic multiple-sample applicator and Computational wing optimization and wind tunnel electrophoresis apparatus test of semi-span model 0 [NASA-CASE-ARC-10991-1] p 057 R78-14104 [lIAA PAPER 78-102] p0034 A78-22575 GUEST, .. - Computational wing optimization and comparisons Some Martian volcanic features as viewed from the with experiment for a semi-span wing model Viking orbiters [NASA-TH-78480] p0 0 2 5 178-26106 p0030 A78-11403 Wind tunnel investigation of computationally GUPTA, N. K. optimized variable camber wing configurations New frequency domain methods for system [NASA-TM-78479] p0026 N78-29067 identification HARDY, G. H. pOOl5 A78-23883 Integrated avionics for future general aviation GUSTAFSON, T. K. aircraft Diagrammatic evaluation of the density operator [AIA PIPED 78-1482] p0020 A78-47927 for nonlinear optical calculations HARRIS, W. L. 3 1 [ONERA, TP NO. 1977-1663 pOD A78-14651 A simplified Macb number scaling law for collisionless dissociation of SF6 using two helicopter rotor noise resonant frequency C02 laser fields pO17 A78-35371 3 1 pOD A78-14655 HARRISON, E. S_ Characteristics of integrated MOM junctions at dc Polymeric foams from cross-linkable and at optical frequencies poly-n-arylenebenzimidazoles [AD-A056165] p 0 037 A78-28926 [NASA-CASE-ARC-11008-1] pODSO N78-31232 Stimulated emission of surface plasmons by HART, J. electron tunneling in metal-barrier-metal Computer display and manipulation of biological structures molecules p0038 A78-30647 p0056 A78-53400 GTORIa, J. R_ HARTFORD, S. L. Advanced instrumentation concepts for Synthesis of N-substituted bisitaconimide monomers environmental control subsystems for use as thermosetting polyimide resins [NASA-CR-152100) p0053 N78-28807 p0041 A78-36809 HAWLEY, K. H A study of commuter airplane design optimization [NASA-CR-157210] p0011 N78-25078 HABIBI, A. HEFLEY, P. K. Survey of adaptive image coding techniques and analysis of wind shear hazard Simulation 3 p0031 A78-15267 [NASA-CR-157470] p005 178-29699 HACKETT, J. E. Computed responses of several aircraft to Moving ground simulation by tangential blowing atmospheric turbulence and discrete wind shears [AIAA 78-814] pOO17 A78-32368 [NASA-CR-152185] pOO53 178-32106 RAEPNER, L. R. HEIBLU, N. Executive summary: Benefit-cost evaluation'of an Characteristics of integrated Mom junctions at dc intra-regional air service in the Bay Area and a and at optical frequencies technology assessment of transportation system [AD-A056165] p0 0 3 7 A78-28926 investments HELGERSO. S. L. [NASA-CR-152154-1) p0013 H78-28988 Methionine transport in alobacterium halobium A technology assessment of transportation system vesicles - Noncompetitive, asymmetric inhibition investments by L-Cysteine [NAS5-CR-152154-2] p0013 N78-28989 p0055 A78-48579 HRAED, B- B. HENBREICR H. Cable strumming suppression Critical review of Ames Life Science participation [AD-A047996] p0022 N78-18366 in Spacelab Mission Development Test 3: The SMD HAGUE, D. S. 3 management study Coplanar tail-chase aerial combat as a [NASA-TH-78494] pOO51 N78-26973 differential game HEEE, P. A. pOO14 178-10455 Transonic wing analysis using advanced High performance dash-on-warning air mobile computational methods missile system [EA11 PAPER 78-105] pOO15 A78-20686 fAIAl 78-1353) pOOls A78-46545 wing analysis using a transonic potential flow BAINES, R. P. computational method Project plan for joint FAA/NASA head-up display [VASA-TM-78464] p0O07 R78-28053 concept evaluation BENNIS, L. A- [NASA-TH-785121 p0052 178-28979 Thermal design and development of a planetary EALBERSTADT, N. I. probe - Pioneer Venus large probe Effects of potassium titanate fiber on the wear of [AIAA PAPER 78-916] pOO4 l A78-37275 automotive brake linings HEPPIEB, H. H. 0 0 3 5 p A78-23450 Technology advancement of the electrochemical C02
132 PERSONAL AUTHOR INDEX JAPEE, R. L.
concentrating process polymers [NASA-CR-152098] pOO52 N78-22723 [AD-A0526171 p0059 M78-24364 HERMANN, R. HORSTMAN, C. C. Applications of algebraic geometry to systems Reynolds number and pressure gradient effects on theory - The McMillan degree and Kronecker compressible turbulent boundary layers indices of transfer functions as topological and [AIAA PAPER 78-199] p0033 A78-20741 holomorphic system invarints An evaluation of several compressible turbulent pOO21 A78-51860 boundary-layer models Effects of pressure HESSr R. A. gradient and Reynolds number Dual-loop model of the human controller (AIAA PAPER 78-1160] pd43.k78-41859 p0018 A7B-39184 Comparison of multiequation turbulence models for HETRICK, M. A. several shock-separated boundary-layer Experimental investigation of contamination interaction flows prevention techniques to cryogenic surfaces on fAIAA PAPER 78-1165] pOO3 k78-41863 board orbiting spacecraft An experimental documentation of pressure gradient [NASA-CR-152171] p0029 N78-29146 and Reynolds number effects on compressible HEflDRICKX, G. R. turbulent boundary layers Extent of utilization of the Frank-Starling [NASA-TM-78488] pO026 H78-27364 mechanism in conscious dogs HOWARD, W. H. pO05 A78-33522 Tread drum for animals HICKS, R. M_ fNASA-CASE-RC-10917-1] po0 5 7 M78-27733 Transonic wing analysis using advanced HOY, H. H. computational methods A method for the analysis of the benefits and [AIAA PAPER 78-105] pOOl5 A78-20686 costs for aeronautical research and technology Wing analysis using a transonic potential flow pO0 7 H78-29060 computational method HUMBLET, P. A. 7 [NASA-T-78464] pOO0 578-28053 Generalization of Huffman coding to minimize the HIGUCHI, H. probability of buffer overflow Behavior of a turbulent boundary layer subjected [AD-AO50974] pOOO6,78-22754 to sudden transverse strain HUNG, C. N. [AIAA PAPER 78-201] p0034 A79-22595 Numerical solution of a three-dimensional shock Symmetrical and asymmetrical separations about a wave and turbulent boundary-layer interaction yawed cone [AIAA PAPER 78-161] pO03 4 78-22591 [NASA-TM-78532] pO0OR N7-32045 HIITLEY, J. M. HILADO, C. J. Bar-driven spiral waves in disk galaxies 0 3 8 The prediction of toxic atmospheres from pO A70-32467 decomposing polymers HUSSAINI. M. Y. pOO33 A78-19895 An integral solution to a nonlinear diffusion AIC/50/ values for some polymeric materials problem pOOO, A78-36596 pOO3 7 A78-26350 Relative toxicity of the pyrolysis products from The general solution to the classical problem of some thermoplastic and themoset polymers the finite Euler-Bernoulli beam 4 2 pOO A78-41213 p0 4 7 A78-50909 BILGENAU, T. HWANG, C. Airborne infrared interferometric observations and Some observations on the mechanism of aircraft analysis of stratospheric trace constituents wing rock 0 034 (AIAA PAPER 78-252] p A78-22606 (AIAA PAPER 78-1456] p0 0 2 0 A78-47907 Comparison between infrared Martian disk spectra and optical properties of terrestrial analogs 7 pOO4 A78-49231 HILL, J. ° IN, B. C. I. Study to design and develop remote manipulator Lower stratosphere measurements of variation with systems 2 latitude of CF2C12, CFC13, CC', and 520 [NASA-CB-152092] pOOS H78-16620 profiles in the northern hemisphere HIRSH, a. E po035 A78-23610 Application of second-order turbulent modeling to fINNS, B. C. the prediction of radiated aerodynamic sound A flight 2 investigation of the stability, control, [NASA-CR-2994] pOOl N78-25359 and handling qualities of an augmented jet flap HODGE, P_ V- STOL airplane Meteor ablation spheres from deep-sea sediments [NASA-TP-1254] p0006 H78-26151 0 2 [NASA-TH-78510] pO 8 N78-34021 IP, W-H HODGES, D H. Quiet time interplanetary cosmic ray anisotropies Aeromechanical stability of helicopters with a observed from Pioneer 10 and 11 bearingless main rotor. Part 1: Equations of p0 0 3 9 A78-34567 motion IVERSEN, J. D. (NASA-TM-78459) p0062 N78-18043 Laser-velocimeter surveys of merging vortices in a HOFMANN, I. G. wind tunnel Development of automatic and manual flight (AIAA PAPER 78-107] pOO15 178-20687 director landing systems for the XV-15 tilt Hot-wire, laser anemometer and force balance rotor aircraft in helicopter mode measurements of cross-sectional planes of single CRASA-CR-152140] pOO 11 78-22071 and interacting trailing vortices NOB, H. H. (AIAA PAPER 78-1194] pOOl8 A78-41885 Advanced Digital Avionics System for general laser-velocimeter surveys of merging vortices in a aviation wind tunnel: Complete data and analysis (AlAA 77-14941 pOO14 A78-12243 [NASA-TM-18#49] pOU 8 H78-33043 Development of automatic and manual flight director landing systems for the XV-15 tilt rotor aircraft in helicopter mode [NASA-CR-152140] pOO11 N78222071 JACKSON, C. T-, JI. HOLMAN, A. B_ - Integrated avionics for future general aviation Pioneer Venus spacecraft charging model aircraft pO022 578-10148 [AlAA PAPER 78-1482] p0020 A78-47927 HOIST, T. I. JACOB, X. T. An implicit algorithm for the conservative Stability of chromium (111) sulfate in atmospheres transonic full potential equation using an containing oxygen and sulfur arbitrary mesh [NASA-TM-78504] 0 0 4 3 p026 578-28173 (AIA PAPER 78-1113] p A78-41826 JAFFE, R. A. HONG, 5- D on the possibility of negative activation energies Stress-strain behavior of some acrylic gradient in bimolecular reactions
133 JAFPEE, R. L. PERSONAL AUTHOR INDEX
0 0 2 6 [NASA-TM-78509] p 878-29149 helicopter in the hover and approach phase JAFFEr, R. L. [NASA-Cn-152135] pOO10 N78-21161 Calculated rate constants for the reaction CIO + 0 KANAFAI, A. yields C1 + 02 between 220 and 1000 deg K An investigation of short haul air transportation [NSA-TM-78483] p0024 U78-21215 in the southeastern United States JAMES, W.D. ENASA-CR-152166] pOO1 2 N78-27094 Theoretical and experimental study of the drag of KAPLAN, I. R. multielement airfoils Light element geochemistry of the Apollo 12 site [AT-AA PAPER 78=-1223] pOO19 A78-45148 p0054 A78-34503 JASSO, C. KARAECHETI, K. stress-strain behavior of some acrylic gradient Propagation of sound through a sheared flow polymers [NASA-CR-152196] p8014 N78-33876 [AD-AO526171 p0059 N78-24364 KARPLUS, W. J. JEWELL, W. . Peripheral processors for high-speed simulation Development of automatic and manual flight pOO14 A78-14063 director landing systems for the XV-15 tilt KATVAA, V. 9. rotor aircraft in helicopter mode Reaction cured glass and glass coatings [NASA-CR-152140] pOO11 N78-22071 (NASA-CASE-ARC-11051-1] pOO50 N78-32260 Computed responses of several aircraft to Spray coating apparatus having a rotatable atmospheric turbulence and discrete wind shears workpiece holder (NASA-CR-152185] p0053 H78-32106 (NASA-CASE-ARC-1h110-1] pOO50 N78-32434 JOELS, K. H. KELLEY, H_ J. Space industrialization Education A preference-ordered discrete-gaming approach to [AAS 77-258] p0 O 0 1 A78-36722 air-combat analysis JOHNSON, D_ A. p0O 2 0 A78-49255 Measurements of unsteady vortex flow fields KELINAB, S. A. (AIAA PAPER 78-18] pOO15 A78-22554 ISAs and the dwarf content of the inner nuclear Wake vortex measurements of bodies at high angle regions of M31 of attack pO0q2 A78-38569 [AIAA PAPER 78-23] pOO15 A78-22555 KELLY, T. J. JOHNSON, F. T. Application of advanced technologies to small, An improved higher order panel method for short-haul aircraft linearized supersonic flow [NASA-Cl-152089] 0 0 2 1 pOO11 N78-22074 [AIAA PAPER 78-15] p A78-52628 KEPPEL, B_ Vo Advanced panel-type influence coefficient methods A study of commuter airplane design optimization applied to unsteady three dimensional potential (NASA-CR-157210] pOO11 N78-25078 flows KERRIDGE, . F. [AIAA PAPER 78-229] p00 2 1 A78-52630 Light element geochemistry of the Apollo5 412 site JOHNSON, a. B. pOO A78-34503. Micro-fluid exchange coupling apparatus KILLIGEE, D. K. (NASA-CASE-ARC-11114-1) p0060 H78-33717 Simultaneous determination of rotational and JOHNSON, J. E., JR. translational temperatures of OH/2 Pi/ in a gas Spectrophotofluorometric and electron microscopic discharge study of lipofuscin accumulation in the testis p0030 A78-10405 of aging mice Absorption measurements of OH using a CW tunable 6 pOO5 A78-48581 laser JOHHSON, R. D. p0032 A78-17837
Space habitats 0 0 5 6 KIRK, D_B. p A78-49780 An analytic study of impact ejecta trajectories in JOHNSON, W. the atmospheres of Venus, Mars, and earth Comparison of measured and calculated helicopter p0037 A78-29532 rotor impulsive noise KIVELSON, f. G. ([ASA-TM-78473] pOO05 N78-20917 The radial dependences of the interplanetary JOKI, E. G. magnetic field between 1 and 5 AU Pioneer 10 4 Demand-type gas supply system for rocket borne pOO 8 A78-52504 thin-window proportional counters KLEIX, H. P. p0031 A78-13845 The Viking biological experiments on Mars JONES, J. 1. p0855 A78-39746 Planning for airport access: An analysis of the KLOPFED, G. H. San Francisco Bay area Lagrangian computation of inviscid compressible [NASA-CP-2044] p0001 N78-26152 flows JONES, W. P. [NASA-T-78456] p0025 N78-24060 A single user efficiency measure for evaluation of KOCH, R. A. parallel or pipeline computer architectures 9 Chemical evolution and the origin of life - pO05 H78-19808 Bibliography supplement 1976 J cKER. a.V. p0057 178-53875 Planning for airport access: An analysis of the KODAHA, A. x_ San Francisco Bay area Continuous metabolic and cardiovascular fNASA-CP-2044] p0O01 N78-26152 measurements on a monkey subject during a JUDGE, D. 1. simulated 6-day Spacelab mission Europa - Ultraviolet emissions and the possibility p 0 0 5 6 A78-48719 - of atomic oxygen and hydrogen clouds KORDULLA, W. p0048 A78-52482 Displacement thickness distributions in transonic JUROS, L_ flows about 3-D wings Fluid-electrolyte shifts and maximal oxygen uptake pOO32 A78-17612 in man at sinulated altitude /2,287 m/ KOSSLER, T. p0054 A78-36602 Responses of articular and epiphyseal cartilage Zones of developing avian radii to estrone K treatment and a 2-G environment p0054 A78-29562 KATTARI, ofx. KOSSON, B. Effects of mass addition on blunt-body A re-entrant groove hydrogen heat pipe boundary-layer transition and heat transfer [AIAA 78-420] p004O A78-35603 [NASA-TP-1139] p0022 H78-16326 KOURTIDES, D_ A. KADLEC, R_ A. ALC/50/ values for some polymeric materials Visualization of quasi-periodic unsteady flows p0 0 4 0 A78-36596 [AIAA 78-502] pO016 A78-29804 Relative toxicity of the pyrolysis products from KAI, T_ some thermoplastic and thermoset polymers Optimal control theory (OWEM) applied to a pOO42 A78-41213
134 PEBSODAL AUTHOR IFDEX LEHMAN, J. .
The relative fire resistance of select stability of rolling aircraft thermoplastic materials 0 0 4 p0031 A78-16180 p 6 A78-45475 LAW, K.-8. Assessment of relative flammability and Semiclassical approach to collision-induced thermoctemical properties of some thermoplastic emission in the presence of intense laser materials radiation - An aspect in the study of 7 pO04 A78-49693 cooperative chemical and optical pumping Low density hismaleimide-carbon microballoon p0037 A78-27744 composites lAEY, P. I- [NASA-CISE-ARC-11040-2] p005O 878-27184 Radiation pressure and Poynting-Eobettson drag for KERA, W. P. small spherical particles Synthesis of multifunction triaryltrifluoroethanes p0 0 3 3 A78-19768 [ASA-CASE-ARC-11097-1) p0049 878-22154 LAE, A. . Synthesis of multifunction triaryltrifluoroethanes The composition of Phobos - Evidence for [HASA-CSE-ARC-11097-2] pO049 H78-22155 carbonaceous chondrite surface from spectral KRISCIUNAS, K. analysis A short history of Pulkovo Observatory 4 p0032 A78-18874 p00 6 &78-47273 Multicolor observations of Phobos with the Viking Peaker: An automatic boresigbt peaking routine lander cameras - Evidence for a carbonaceous for the C-11 telescope chondritic composition 2 [ASA-TM-78516] pO0 8 878-32856 p003 2 378-18875 KHOEGE, H. A. LAWPRANCO, M. J. A method for localizing wing flow separation at An evaluation of several compressible turbulent stall to alleviate spin entry tendencies boundary-layer models Effects of pressure [AIAA PAPER 78-1476] pO020 K78-49787 gradient and Reynolds number MUSE, R. L. [&IA PAPER 78-1160] p0043 A78-41859 Influence of spin rate on side force of an LANGHOFF, S. R. arisymetric body A theoretical study of the electronic transition p0038 A78-30690 KUDACKI. II. N. moment for the C2 Swan band system pOO0l1 78-36776 Boron trifluoride coatings for thermoplastic Semirigorous bounds for the dipole moments and materials and Method of applying same in glow transition moments of the Li8 molecule discharge p00 4 6 178-45963 7 [NASA-ASE-ARC-11057-1) pOOS S70-31233 LANYI, J. K. Process for producing a well-adhered durable Calcium transport in Halobacterium halobium optical coating on an optical plastic substrate envelope vesicles [NASA-CASE-ARC-11039-1) p0058 H78-32854 p0055 A78-48574 KUH, P_ fN- Illumination-dependent changes in the intrinsic Plight tests of a simple airborne device for fluorescence of bacteriorhodopsin predicting clear air turbulence encounters p8855 A78-48578 [AIAA 78-1375] pOO19 A78-46560 Methionine transport in Ralobacterium halobium KUnG, C. C. vesicles - Noncompetitive, asymmetric inhibition Light element geochemistry of the Apollo 5 12 site by L-Cysteine 0 5 p00 4 1.78-34503 p0 5 178-48579 EACH, C. S. KURKOxSKI, R. L. Plight tests of a simple airborne device for Hormonal indices of tolerance to *cz acceleration predicting clear air turbulence encounters in female subjects [IRA 78-13753 pOO9 A78-46560 p0055 178-41162 KUSSOY, N. LEE,8. A. Reynolds number and pressure gradient effects on A simplified Mach number scaling law for compressible turbulent boundary layers helicopter rotor noise (AIA PAPER 78-199] p0033 A78-20741 pOO17 A78-35371 An evaluation of several compressible turbulent Comparison of measured and calculated helicopter boundary-layer models Effects of pressure rotor impulsive noise gradient and Reynolds number [HASA-TI-78473] 0 5 0 0 4 3 pO B78-20917 [AIAA PAPER 78-1160] p A78-41859 Acoustical effects of blade tip shape changes on a An experimental documentation of pressure gradient full scale helicopter rotor in a wind tunnel and Reynolds number effects on compressible [RASA-CR-152082] p0010 E78-20918 turbulent boundary layers A study of the noise radiation from four 0 2 6 rotor blades [NASA-TM-78488] p N78-27364 helicopter KUTLER, P. pOOO8 N78-32835 Computation of the viscous supersonic flow over LEE, E. H. symmetrical and asymmetrical external axial Controlled vapor growth of small particles of Pd corners and Fe on thin A1203 substrates [AIAA PIPER 78-1135] pOO43 A78-41839 p0044 A78-43384 KITE,I. T.T LEE, G. Are the stratospheric dust particles meteor C02 laser-driven Stirling engine ablation debris or interplanetary dust? p021 A78-49804 [NASA-TM-78507] p028 N78-34014 A cesium plasma TELEC device for conversion of Meteor ablation spheres from deep-sea sediments2 laser radiation to electric power [(ASA-T-78510) pOO 8 478-34021 p0 04 8 178-51067 LEE, H. Q. L Optimum horizontal guidance techniques for aircraft 0 0 0 6 p N. 178-23016 LEE, I. LACEY, T. . Conceptutl design study of a Harrier V/STOL Transport of contaminants in the planetary research aircraft boundary layer [tlAS-CR-152086J p0009 N78-19094 p00 8 A78-52137 tA~ING, 3. It. LEE, M. K. A new concept in laser-assisted chemistry - The Evaluation of a spacecraft nitrogen generator electronic-field representation [ASA-CR-152097] pOD5 2 178-23748 pOO37 A78-27743 LEFTON, 1. Semiclasicsl approach to collision-induced A preference-ordered discrete-gaming approach to emission in the presence of intense laser air-combat analysis radiation - An aspect in the study of p0020 178-49255 cooperative chemical and optical pumping LEHMAN, J. 9. pOO37 A78-2774 Simulation and analysis of wind shear hazard LAITOE, E. V. [NASA-CR-157470] pOO53 U78-29699 Effect of a nonconstant C/m-alpha/ on the
135 LEEWALT. A. B. PERSONAL AUTHOR INDEI
fl-...RHWA.T, The numerical solution of viscous flows at high Chemical interpretation of Viking Lander life Reynolds number 1 0 0 4 6 detection experiment p A78-46360 3 pOO5 A78-25560 Status and future prospects of using numerical LEISER, D. B. methods to study complex flows at High Reynolds Fibrous refractory composite insulation numbers 0 0 5 0 ENAS-CAS-ARC-11169-1] p N78-32189 p0026 E78-28410 Reaction cured glass and glass coatings MACELROT, . P. [NASA-CASE-ARC-11051-1] pOO5O.N78-32260 Computer display and manipulation of biological LENIOS, A- 2 molecules Theoretical study of multicyclic control of a p0056 A78-53400 controllable twist rotor Space ecosynthesis: An approach to the design of [NASA-CR-151959] p 0 0 6 4 878-33085 closed ecosystems for use in space LEVIN, A. D. NASA-TB-78491] pOOS1 878-26740 High performance dash-on-warning air mobile BACK, R. E. missile system Chemical interpretation of Viking Lander 1 life [AlA 78-1353] pOO19 A78-46545 detection experiment LEWIS, 1. . p0053 A78-25560 Continued development of doped-germanium HACKIE, D. B. photoconductors for astronomical observations at Application of special-purpose digital computers wavelengths from 30 to 120 micrometers to rotorcraft real-time simulation [NASA-CR-152125] p 0 O29 N78-22000 tNASA-TP-1267] pOO07 N78-27113 LIFSON, B. W. MAGNUS, A. B. A study of characteristics of intercity An improved higher order panel method for transportation systems. Phase 1: Definition of linearized supersonic flow transportation comparison methodology PAPER 7-151 p0021A78-52628 0 1 [lIAA [NAS-CR-152153-2] pOO 78-29996 HAHLAB. S. S. LIB, R. S. Computational study of a molecular collision A decoding procedure for the Reed-Solomon codes process in the presence of an intense radiation [NASA-TP-1286] poo59 N78-30862 field - Enhanced quenching of F by Am in the INCOLN, F. R. 248-nm light of the Kr? laser Preliminary study for a numerical aerodynamic [AD-A054078] pOO44 A78-42818 simulation facility. Phase 1: Extension RAINS, R. C. [NASA-CR-152108] p00 2 8 78-19052 Continuous metabolic and cardiovascular Preliminary study for a Numerical Aerodynamic measurements on a monkey subject during a Simulation Facility simulated 6-day Spacelab mission p0 0 2 3 N78-19783 pOO5 6 A78-48719 LOEWENSTEIN. 9. MALCOLM, G. N. Geographical variations of NO and 03 in the lower New rotation-balance apparatus for measuring stratosphere airplane spin aerodynamics in the wind tunnel 3 7 pOO 9 A78-35403 [AAA 78-835] pOO1 A78-32386 Stratospheric NO and H103 observations in the 0ALLON,J. R. Northern Hemisphere for three seasons A fifty channel electrically scanned pressure module pOO* 2 A78-41123 pOOl# A78-17395 LOMAX. H_ BALLOVE, E. 1. Thin-layer approximation and algebraic model for A bibliography on the search for extraterrestrial separated turbulent flows intelligence [AIAA PAPER 78-257) pOO33 A78-20776 [NASA-RP-1021] pO0 5 1 78-21019 Three-dimensional computational aerodynamics in MANSPIELD, J. A- the 1980's Effects of potassium titanate fiber on the wear of p0023 N78-19781 automotive brake linings LONG, 1. F p0035 A78-23450 Continued development of doped-germanium HARK, H. photoconductors for astronomical observations at Exchange and relaxation effects in low-energy wavelengths from 30 to 120 micrometers radiationless transitions (NASA-OR-152125] p 0 0 2 9 N78-22000 [NASA-TM-79383] pOOO# N78-18882 LUCE, R. . MARSHALL, R. D. An investigation of the reduction of carbon Evaluation of a spacecraft nitrogen generator dioxide in a silent electric discharge [NASA-CH-152097] pOO 5 2 178-23748 [NASA-CR-152146] p00 53 N78-25767 MARTIR, C. LUDAE, B. E. Applications of algebraic geometry to systems Extended development of variable conductance heat theory - The Mc~illan degree and Kronecker pipes indices of transfer functions as topological and 2 [NASA-CR-152183] p00 9 N78-33379 holomorphic system invariants LUND, G. F pOO 2 1 A78-51860 An inductively powered telemetry system for MARVIN, . G_ temperature, EKG, and activity monitoring On the period of the coherent structure in [NASA-TM-78486] pOd59 N78-23706 boundary layers at large Reynolds numbers 0 0 24 LUEIL, J H. [1NASA-TN--784771 p N78-21407 The response of heat-shield materials to intense NASCY, A. C. - laser radiation A review of NASA-sponsored technology assessment (AIAA PAPER 78-138] 0 3 4 A78-22583 projects p 0 2 Carbonaceous materials subjected to extreme [NASA-TH-78472] pOD 5 178-24000 heating - A comparison of numerical simulation BATHIESON, T. and erperiments Peaker: An automatic boresight peaking routine 0 0 4 1 [AIA PAPER 78-866] p A78-37273 for the C-14l telescope LUNDGREN, P. R_ [NASA-TE-78516] p0028 N78-32856 Spectrophotofluorometric and electron microscopic SAYER, I. A. study of Lipofuscin accumulation in the testis Chelate-modified polymers for atmospheric gas of aging mice chromatography p00 5 6 A78-48581 [RASA-CASE-ARC-11154-1] p0 0 5 7 378-27275 MAYO, M. C. Prop-fan data support study M [NASA-CR-152141] pOO13 N78-27128 NACCOBBACK, B. W. CALISTER . W. Numerical solution of a three-dimensional shock Dynamic stall experiments on the BACA 0012 airfoil wave and turbulent boundary-layer interaction [NASA-TP-1100] pO0 6 2 N78-17000 [AIAA PAPER 78-161J p0O34 A78-22591 Water-tunnel experiments on an oscillating airfoil at RE equals 21,000
136 PERSONAL AUTHOR INDEX MAGI, A. F.
(NASA-TM-78446] p0062 878-19058 [UASA-CR-1521331 pOO11 N78-21445 MCCLOUD, 3 L._ III MILLER, R. H. A note on multicyclic control by'swashplate Numerical experiments on the stability of disklike oscillation galaxies [NASA-TM-78475] p0005 N78-21159 pOO19 A78-45535 MCCLOY, R. D. On the stability of disklike galaxies in massive Entry dynamics performance predictions for Pioneer halos Venus probes p0020 A78-47354 [AIAt 78-1370] p0046 A78-46557 MILLER, R- J. MCCREIGHT, C. G-seat system step input and sinusoidal response A re-entrant groove hydrogen heat pipe characteristics 7 [AIAA 78-420] p0040 A78-35603 tNASA-TM-784781 pOO0 878-26741 BCCROSKEY, W. J. MILLIS, R. . Dynamic stall experiments on the HACk 0012 airfoil The radii of Uranian rings-alpha, beta, gamma, (NASA-TP-1100] p0062 H78-17000 delta, epsilon, eta, 4, 5, and 6 from their Introduction to unsteady aspects of separation in occultations of SAO 158687 subsonic and transonic flow p0046 A78-48112 p0 0 6 3 878-28403 SIQUEL, J. Some unsteady separation problems for slender bodies Spectrophotofluorometric and electron microscopic pOO63 878-28405 study of Lipofuscin accumulation in the testis Prediction of unsteady separated flows on of aging mice oscillating airfoils p0056 A78-U8581 p0063 878-28409 HOGRO-CAPERO, A. MCCUTCHEO8, E. P. Quiet time interplanetary cosmic ray anisotropies Continuous metabolic and cardiovascular observed from Pioneer 10 and 11 measurements on a monkey subject during a p0 0 39 178-34567 simulated 6-day Spacelab mission MOORBEAD, R. D. p0056 A78-48719 Controlled vapor growth of small particles of Pd MCGEE, L. A. and Fe on thin-A1203 substrates Simulator evaluation of three situation and pOO4 4 A78-43384 guidance displays for V/STOL aircraft zero-zero MORESSI, W. . landing approaches Food and oxygen reguirements for growing mice and pOO55 A78-44131 turtles after hypergravitational development MCGOWAH, P. B. p0 0 31 A78-15204 Theoretical and experimental study of the drag of MOBEY, B. R. multielement airfoils Inhibition of bone formation during space flight (AIAA PAPER 78-1223] pOO19 A78-45148 p0856 A78-51225 MCKEE, R. G. MORRIS, S. .. Fire detector response in aircraft applications System optimization of gasdynamic lasers, computer p0049 A78-53674 program userts manual MCKENZIE, D. I. [NASA-TM-73193] pOO27 N78-29436 The quiet coronal X-ray spectrum of highly ionized MOSHER, A. oxygen and nitrogen A study of the noise radiation from four pOOS8 A78-31108 helicopter rotor blades MEGGITT, D. J. pOOOS 878-32835 Cable strumming suppression MOSSOLARI, D. L. [AD-A047996] p0022 878-18366 Notary leveling base platform KENT&, V. B. [NASA-CASE-ARC-10981-1] pOO6O N78-27425 Dynamic stall of an oscillating airfoil 0 0 2 5 MULHOLLAED, D. R. p N78-22055 NASA/ESA cv-990 Spacelab simulation (ASSESS 2) HELICK, B. C., aM. [NASA-C-152122] p029 878-23117 Estimating maximum instantaneous distortion from MULLER, R. 1. inlet total pressure rms measurements Radiometer system to map the cosmic background
[AIAA PAPER 78-970] pOO19 A78-43525 radiation 0 0 3 BRiEMS, C. P. p 8 A78-30691 Carbonaceous materials subjected to extreme MURAKABI, M. heating - A comparison of numerical simulation Theoretical contamination of cryogenic satellite and experiments telescopes 0 0 4 1 0 0 2 (A1A1 PAPER 78-866] p A78-37273 (NASA-TP-1177] p 4 N78-21193 MEREDITH, P. EURCRA!, D. C. A study of commuter airplane design optimization Stratospheric NO and HN03 observations in the [NAS-CR-157210] pOO11 N78-25078 Northern Hemisphere for three seasons 4 2 HERZ, A. W. pOO A78-41123 Coplanar tail-chase aerial combat as a MURPHY, J. D. differential game computing viscous flows pOOQ A78-10455 pOO0 N78-19794 METZGER, F. B. MURPHY, M. B. Prop-fan data support study Simulator evaluation of three situation and [NASA-CR-152141] pOOl3 178-27128 guidance displays for V/STOL aircraft zero-zero EICHELSON, S. landing approaches Application of special-purpose digital computers pOO55 A78-44131 to rotorcraft real-time simulation MURRAY, J. B. [NASA-TP-1267] pO00 7 N78-27113 Some artian volcanic features as viewed from the IBA1OV, J._D. Viking orbiters Dynamic MHD modeling of the solar wind pOO30 A78-11403 disturbances during the August 1972 events MUTH, V. S. pO36 A78-26079 Buried vire gage for wall shear stress measurements On the observation of a flare-generated shock wave [IAA 78-798] pOO1 7 A78-32353 at 9.7 AU by Pioneer 10 MYRON, C. R. [AD-A053721] p0038 A78-30078 Application of advanced technologies to small, Dynamic BHD modeling of solar wind corotating short-haul aircraft stream interaction regions observed by Pioneer [(ASA-C-152089] p0011 M78-22074 10 and 11 pi14v A78-52522 N Pioneer 10 observation of the solar wind proton temperature heliocentric gradient 0 0 2 7 NAGY, A. F. [ASA-T-78515] p E78-31030 A comprehensive model of the venus ionosphere MIKSA, a. pO038 A78-30071 Generation of a monodispersed aerosol
137 NARASIRHA, R. PEESONAL AUTHOR INDEX
The ionosphere and airglow of Venus - Prospects OTTEN, I. J., III for Pioneer Venus System optimization of gasdynamic lasers, computer poO45 178-44773 program uservs manual 0 0 2 7 WARASIHHA. R. [NASA-TM-73193] p N78-29436 'njection slot location for boundary-layer control OVER, F. K. in shock-induced separation Measurements of unsteady vortex flow fields [AIRA PAPER 78-1168] p0 0 44 A78-41866 [AIA PAPER 78-18] pOOi5. 178-22554 NARAYARA, M. A. L Wake vortex-measufements of bodies at high angle On the period of the cohereht structure in of attack boundary layers at large Reynolds numbers [AIAA PAPER 78-23] pOO15 A78-22555 [NASA-TM-78477] p0024 N78-21407 Symmetrical and asymmetrical separations about a BEGOLESCO, J_ A- yawed cone Responses of articular and epiphyseal cartilage [NAS-TM-78532] p0O08 N73-32045 zones of developing avian radii to estrone OAKA, V. I. treatment and a 2-G environment Carbon suboxide polymer, an explanation for the 5 4 p00 A78-29562 wave of darkening on Mars 0 0 5 6 NELMS, W. p. p A78-48717 Studies of aerodynamic technology for VSTOL fighter/attack aircraft [AIAA PAPER 78-1511] p0020 A78-47946 SNESON, H. G. PACE, B. Influence of temperature and the role of chromium Continuous metabolic and cardiovascular on the kinetics of sulfidation of 310 stainless measurements on a monkey subject during a steel simulated 6-day Spacelab mission p0 0 4 3 A78-41796 p0056 178-48719 Hydrogen attack - Influence of hydrogen sulfide 0 4 PALMER, E. A. p 0 4 A78-44108 Simulator evaluation of three situation and Stability of chromium (III) sulfate in atmospheres guidance displays for V/STOI aircraft zero-zero containing oxygen and sulfur landing approaches fNASA-TM-78504] p0826 H78-28173 p0055 A78-44131 REREYE, 5. PANG, X. The spiral field inhibition of thermal conduction Multicolor observations of Phobos with the Viking in two-fluid solar wind models lander cameras - Evidence for a carbonaceous 4 6 pOO A78-48281 chondritic composition EEWSOK. E. D. p08 3 2 A78-18875 cV 990 interface test and procedure analysis of PASG, K_ D. the monkey restraint, support equipment, and The composition of Phobos - Evidence for telemetry electronics proposed for Spacelab carbonaceous chondrite surface from spectral [NASA-T-78484] p0051 U78-27736 analysis WICOLET, W. E. p0 0 3 2 A78-18874 Aerothermodynamic environment for Jovian entry PAPROTEYT Z. with silica heat shield A bibliography on the search for extraterrestrial [AIAA PAPER 78-186) p0033 A78-20730 intelligence NIXON, D. [ASA-RP-1021] p0 0 5 1 N78-21019 Calculation of unsteady transonic flows using the PARK, C_ integral eguation method Shock-tube studies of atomic silicon emission in [AIAA PAPER 78-13] p0033 A78-20632 the spectral range 180 to 300 nm Notes on the transonic indicial method [AIAA PAPER 78-234] p 0 0 34 A78-22602 p0041 A78-37732 Nitric oxide production by Tunguska meteor 8 Techniques for correcting approximate finite p00 A78-51811 difference solutions PARK, S. fRASA-TM-78499] p0 0 2 6 H78-26796 Hot-wire, laser anemometer and force balance HOERR, H. L. measurements of cross-sectional planes of single Airborne photometric observations between 1.25 and and interacting trailing vortices 3.25 microns of late-type stars [AIA PAPER 78-1194] pOOl 8 A78-41885 p0 0 3 6 A78-25295 PARKER, J. A ALC/5O/ values for some polymeric materials pOO4O A78-36596 0 Synthesis of N-substituted bisitaconimide monomers OBERDECK, V. R. for use as thermosetting polyimide resins Application of high explosion cratering data to pOO4l A78-36809 planetary problems The relative fire resistance of select pO044 A78-44033 thermoplastic materials OGSA, W. pOO46 A78-45475 Solution of transonic flows by an Assessment of relative flammability and integro-differential equation method thermochemical properties of some thermoplastic [NASA-TM-78490] p0026 N78-26391 materials OHARA, D. pOO47 A78-49693 Interhemispheric gradients of CF2C12, CFCI3, CClg, Low density bismaleimide-carbon microballoon and N20 composites pOO42 A78-41124 (NASA-CASE-ARC-11040-2] pOO5g N78-27184 OLOPSSON, S. C. PARRA, G_ T Airborne photometric observations between 1.25 and Angle detector 3.25 microns of late-type stars [NASA-CASX-ARC-11036-1] p0060 N78-32395 p0036 A78-25295 PATEL, P. D. OLS0O, I. E. Development of automatic and manual flight Theoretical and experimental study of the drag of director landing systems for the XV-15 tilt multielement airfoils rotor aircraft in helicopter mode [AAA PAPER 78-1223] pOO19 A78-45148 [NASA-CR-152140] pOOh1 878-22071 ORLOP, A. 1. PATEL, R. V_ laser-velocimeter surveys of merging vortices in a Robustness in linear quadratic feedback design wind tunnel with application to an aircraft control problem [AIAA PAPER 78-107] p0015 A78-20687 pOOl! A78-18059 The spanwise lift distribution on a wing from Robustness of linear quadratic state feedback flow-field velocity surveys designs in the presence of system uncertainty [AAAt PAPER 78-11951 p0018 A78-41886 4 pOOl6 A78-23917 Laser-velocimeter surveys of merging vortices in a PATERSON. J. A. wind tunnel: Complete data and analysis Trajectory module of the NASA Ames Research Center [NASA-TM-78449] pOOd8 E78-33043 aircraft synthesis program ACSYNT
138 PERSONAL AUTHOR IRDEX RAKICH, a. V.
[HISA-TI-78497] p0006 N78-26133 Chemisorption of CO on Pd particles supported on PAULK, C. U. mica Simulator evaluation of three situation and pOWO A78-36040 guidance displays for V/STOL aircraft zero-zero Controlled vapor growth of small particles of Pd landing approaches and Fe on thin A1203 substrates 0 0 4 4 pOOSS A78-44131 p A78-43384 PEASE, P.J3. POPPOFF, I. 5. Phenomenological aspects of quasi-stationary An assessment of the effect of supersonic aircraft controlled and uncontrolled three-dimensional operations on the stratospheric ozone content 00 flow separations [NASA-RP-1026] p 27 V78-30774 0 0 0 7 p N78-28402 PORTER, E. E. Symmetrical and asymmetrical separations about a Spray coating apparatus having a rotatable yawed cone workpiece holder [NtS1-TM-78532] pOO08 H78-32045 [NASA-CASE-ARC-11110-1] pOOSO N78-32434 PEPLeY, B. POUDh, G. M. Measured wake-vortex characteristics of aircraft Chemisorption of CO on Pd particles supported on in ground effect mica [AIAA PAPER 78-109] pOO15 A78-22578 p0040 A78-36040 PERON, C_ POWR11 J. D. Rigidity-independent coronal propagation and 8lti-calculation rate simulations escape of solar protons and alpha particles [NASA-CR-1553351 pOOC9 B78-13765 p0041 A78-37354 PRABEU, A. PERRY, R. L. Injection slot location for boundary-layer control CO2 laser-driven Stirling engine in shock-induced separation 0 0 2 1 p A78-49804 [AIAA PAPER 78-11683 p0O44 A78-41866 PESSES, M. E. PRARISH, S. g. Energetic protons associated with interplanetary Shock-tube studies of atomic silicon emission in active regions 1-5 AU from the sun the spectral range 180 to 300 nm 0 0 3 6 p A78-26081 [AIAA PAPER 78-234] p0034 A78-22602 PETERS, D. A. PRESLEY, L. L. An approximate solution for the free vibrations of The shock tube as a device for testing transonic rotating uniform cantilever beams airfoils at high Reynolds numbers 0 0 6 3 (NASA-TM-X-62299] p B78-33289 [AIAA 78-769] pOO17 A78-32330 PETERSON, A. . PRESlRY, I. S. Digital filter structures having low errors and High angle of incidence implications upon air simple hardware implementation intake design and location for supersonic cruise pOO56 A78-51346 aircraft and highly maneuverable transonic PETERSON, VL. aircraft Computational aerodynamics and the numerical [NASA-TS-78530] p0OO8 N78-32044 aerodynamic simulation facility PROCTOR, D. K. 0 0 2 3 p N78-19779 Application of advanced technologies to small, PETROFF, D. H. short-haul aircraft Low speed aerodynamic characteristics of an [NASA-CR-152089] p011 B78-22074 0.075-scale F-15 airplane model at high angles PULLIAM, T. 3, of attack and sideslip On implicit finite-difference simulations of [NASA-TM-X-62360] pOOO' N78-10019 three-dimensional flow Low-speed aerodynamic characteristics of a [fIAA PAPER 78-10] p0033 A78-20630 0.08-scale YF-17 airplane model at high angles Computation of the viscous supersonic flow over of attack and sideslip symmetrical and asymmetrical external axial 6 [NISA-TM-78438] pOOO H78-22025 corners PI, W. - [AIAA PAPER 78-1135] p0O43 A78-41839 Some observations on the mechanism of aircraft PYLE, K. R. wing rock Acceleration of nucleons in the interplanetary 0 0 2 0 [AI1 PAPER 78-1456] p A78-47907 space and the modulation of Jupiter electrons in PIERSOL, A. G. the interval from 1 to 10 A.U. by corotating Use of coherence and phase data between two regions of solar origin receivers in evaluation of noise environments p0037 178-29684 6 pOO1 A78-26495 PINTO, J. PQ Primitive atmosphere and implications for the Q formation of channels on Mars QUIGLEY, H. C. 4 p004 A78-42460 V/STOL aircraft simulation - Requirements and PITTS. G. C. capabilities at Ames Research Center Physiologic regulation of body energy storage [IA PAPER 78-15151 p0021 178-49790 pOO55 A78-42817 POLLACK, J. B. The composition of Phobos - Evidence for carbonaceous chon.dite surface from spectral RALEAXN, D. F. analysis Continuous metabolic and cardiovascular p0032 A78-18874 measurements on a monkey subject during a Multicolor observations of Phobos with the Viking simulated 6-day Spacelab mission lander cameras - Evidence for a carbonaceous pOO56 A78-L8719 chondritic composition RAJAPAKSE, Y. D. S. 2 p003 A78-18875 Simple torsion test for shear moduli determination The rings of Saturn of orthotropic composites 0 0 3 6 p A78-23646 [AShS-TM-78485] p0024 U78-21490 Saturn's rings: Particle composition and size RAKICH, a. V. distribution as constrained by microwave Navier-Stokes calculations for laminar and observations. I - Radar observations turbulent hypersonic flow over indented nosetips 3 6 p88 A78-25676 [AIAR PAPER 78-260] p0O35 A78-22608 POLLOCK, .G - calculation of supersonic viscous flow over delta Synthesis of porous polyaromatic column packings wings with sharp subsonic leading edges for GC analysis of extraterrestrial atmospheres [AIAA PAPER 78-1137] p0043 A78-41841 p0855 A78-48577 Computation of supersonic laminar viscous flow POPPA, E_ past a pointed cone at angle of attack in The co-adsorption of copper and oxygen on a spinning and coning motion tungsten 100 plane-type surface 7 [AIh PAPER 78-1211] p0045 A78-45139 p003 A78-29489 Numerical solution of two-dimensional turbulent blunt body flows with an impinging shock
139 RANTANEN, R. 0. PERSORAL AUTHOR INDEX
[AIAA PAPER 78-12091 p0045 A78-45144 disturbances during the August 1972 events Calculation of supersonic viscous flow over delta p0036 A78-26079 wings with sharp subsonic leading edges ROSENBERG, B. L. [NASA-T-785001 p0025 N78-26101 The radial dependences of the interplanetary RANTAIEN, R. 0- magnetic field between 1 and 5 AU Pioneer 10 0 0 4 Experimental investigation of contamination p 8 A78-52504 prevention techniques to cryogenic surfaces on ROSKAN, 3. board orbiting spacecraft A study of commuter airplane design optimization [fASA-CR-152171]. pO029-N78-29146 ROSSE-C8-157210] p0011 78-25078 RAO, B.. D. BOSSED, B. I Stability of chromium (i1) sulfate in atmospheres Synthesis of multifunction triaryltrifluoroethanes containing oxygen and sulfur [NASA-CASE-ARC-11097-1] p0049 N78-22154 [8ASA-TM-78504] p0026 N78-28173 Synthesis of multifunction triaryltrifluoroethanes RAO, DB. NASA-CASE-ARC-11097-2] p0049 N78-22155 Influence of temperature and the role of chromium ROUSE, W. B. on the kinetics of sulfidation of 310 stainless Human problem solving performance in a fault steel diagnosis task p0043 178-41796 p054 A78-32673 RAO, G. V- . A model of human decisionmaking in a fault Use of leaning vanes in a two stage fan diagnosis task [NASA-CR-152134] pOO10 N78-21115 p0054 A78-37130 BAS, H. S. RUBBERT, P. E. A cesium plasma TELEC device for conversion of An improved higher order panel method for laser radiation to electric power linearized supersonic flow p0 0 4 8 A78-51067 [AIAA PAPER 78-15] p0021 A78-52628 REASER, J. S A Mach line panel method for computing the Rotorcraft linear simulation model. Volume 1: linearized supersonic flow over planar wings Engineering documentation [HSA-CR-15 2 1 2 6 ] pOO12 N78-27087 [NASA-CR-152079-VOL-1] pOO10 H78-20136 BUBESIN, M. W Rotorcraft linear simulation model. Volume 2: Behavior of a turbulent boundary layer subjected Computer implementation to sudden transverse strain [NASA-CR-152079-VOL-2] pOO10 N78-20137 [AIAA PAPER 78-201] p0034 A78-22595 REEVES, J. P. Modeling of the Reynolds stresses NASA/ESA CV-990 Spacelab simulation (ASSESS 2) p0024 78-19797 [NASA-CR-152122] p0029 N78-23117 RUGGE. H. R. REIN, a. The quiet coronal X-ray spectrum of highly ionized Computer display and manipulation of biological oxygen and nitrogen molecules A78-31108 p0056 178-53400 RUSSELL, t. T. pOO38 REINHARD, R_ On the relative locations of the bow shocks of the Rigidity-independent coronal propagation and terrestrial planets escape of solar protons and alpha particles p0031 A78-13752 p0 0 4 1 A78-37354 On the apparent source depth of planetary magnetic EKLIS, B. P. fields computation of transonic flow past projectiles at p0037 A78-29472 angle of attack 0 4 4 [ATAA PAPER 78-1182] pO A78-41875 S BESS, E. B. Experimental investigation of contamination SIASKI. E. V. prevention techniques to cryogenic surfaces on Study of a high performance evaporative heat board orbiting spacecraft transfer surface 0 0 2 8 (NSA-CR-152171] p0029 N78-29146 [NASA-CR-152008] p N78-10411 REVELL, 3. D. SAGAN, C. Fuel conservation merits of advanced turboprop occultation of Epsilon Geminorum by Mars. I1 - The transport aircraft structure and extinction of the Martian Upper [NASA-CR-152096] pOO10 78-21095 atmosphere REYNOLDS, P. A. - p0030 A78-10587 Flight simulation - A vital and expanding SAGABA, K. technology in aircraft development Arrhenius' law in turbulent media and an [AIAA PAPER 78-337] pOOl6 A78-29295 equivalent tunnel effect 4 RHEE, S. K. p00 9 A78-52547 Effects of potassium titanate fiber on the wear of SAGDEO, P. M. automotive brake linings Injection slot location for boundary-layer control p0035 A78-23450 in shock-induced separation HICCITELLO, S. B. [IAA PAPER 78-1168] pO044 A78-41866 Polymeric foams from cross-linkable SAIKI, D. H. poly-n-arylenebenzimidazoles Rotorcraft linear simulation model. Volume 2: [NASA-CASE-ARC-11008-1J p0O50 N78-31232 Computer implementation RICCITIELLO, S. R. [ASA-CR-152079-VOL-2] p0010 B78-20137 catalysts for imide formation from aromatic SALISBURY, J3 K- D. isocyanates and aromatic dianhydrides Study to design and develop remote manipulator [fASA-CASE-ARC-11107-1] p0 0 4 9 N78-22156 systems Intumescent-ablator coatings using endothermic [NASA-CE-152092) p0052 178-16620 fillers SANDERS, .. H. [NASA-CASE-ARC-11043-1] pO049 878-27180 Bar-driven spiral waves in disk galaxies 0 0 3 8 ROBERTS, . W., JR. p A78-32467 Bar-driven spiral waves in disk galaxies SANKARn, I. p0 0 3 8 A78-32467 Injection slot location for boundary-layer control ROBINSON, P. A-. JR. in shock-induced separation Pioneer Venus spacecraft charging model [AIAA PAPER 78-1168] p0044 A78-41866 p00 2 2 N78-10148 SATTAARAYAA, B ROLAND, B. P. Two-dimensional transonic testing with splitter XlO: A FORTRAN direct access data management system plates pOO60 78-33784 [ASA-TP-1153] pOO04 78-17999 ROSE, W. C. SAUNDERS, R. C., III Buried wire gage for wail shear stress measurements System optimization of gasdynamic lasers, computer [AIAA 78-798] pOO17 A78-32353 program user's manual ROSENAU, P. fNASA-TB-73193] p0027 178-29436 Dynamic MHD modeling of the solar wind
140 PERSONAL AUTHOR IDBI SMALL, R. D.
SAVAGE, H. F. SETTLES, G. S. Geographical variations of NO and 03 in the lower A detailed study of attached and separated stratosphere compression corner flowfields in high Reynolds pOO39 A78-35403 number supersonic flow 3 SARKO, P. M. (AIAA PAPER 78-11671 pO4 A78-41865 Catalysts for imide formation from aromatic SHE, C. T. isocyanates and aromatic dianhydrides easuring the velocity of individual atoms in real [NASA-CASE-ARC-11107-1] pCO'9 N78-22156 time tntumescent-ablator coatings using endothetmic pOO35 A78-23124 fillers SHEA, M_ A. (NASA-CASE-ARC-11043-1] p0049 N78-27180 On the observation of a flare-generated shock wave Structural wood panels with improved fire resistance at 9.7 AU by Pioneer 10 fNASA-CASE-ARC-11174-1) p0O0 N78-28178 [AD-A053721] pOO 3 8 A78-30078 SCARGLE, J. D. SHEN, M. Infrared excesses in early-type stars - Gamma Stress-strain behavior of some acrylic gradient Cassiopeiae polymers p0047 A78-49475 (AD-A052617] p0059 E78-24364 SCHENCK, H. SHEIKA1. A. S. Generation of a monodispersed aerosol Prop-fan data support study (RASA-CR-152133] pOO11 78-21445 [NASA-CR-152141] pOO13 878-27128 SCHER,. S E- SSEOI. K Low speed aerodynamic characteristics of an Digital filter structures having low errors and 0.075-scale V-15 airplane model at high angles simple hardware implementation of attack and sideslip 0 5 6 04 p 0 6 A78-51346 ([ASA-T-X-62360) p0 E78-10019 SHEORAN, 7. Low-speed aerodynamic characteristics of a Stress analysis study in cooled radial inflow 0.08-scale YF-17 airplane model at high angles turbine of attack and sideslip [AIAA PAPER 78-943 p0 064 A78-22570 ([ASA-TM-78438] pOOO 6 N78-22025 SHERWOOD, B. SCHP, L. B_ Ames Research Center Publications-1976 The role of time-history effects in the (NASA-TH-78493) pO003 N78-27042 formulation of the aerodynamics of aircraft SHIP, K. 1. dynamics Degradation of biochemical activity in soil [WASA-Tt-78471] p0023 N78-19056 sterilized by dry heat and gamma radiation SCHMIDT, S._P. pOO57 A78-53874 Development and flight tests of a Kalman filter SHIHAZAKI, T. for navigation during terminal area and landing Thermal structure of the primitive ionosphere operations p0035 A78-23543 [RASA-CR-3015] pOO12 N78-27105 SHIMIZU, M. SCHNITZ, F. H. Thermal structure of the primitive ionosphere Hovering impulsive noise: some measured and p 0 035 A78-23543 calculated results SHOPnOVCH P- pO0 6 3 N78-32831 Accordion shelter hardware analysis 7 SCHNEIDER, a. B_ [AD-A053592) pOO0 B78-28278 AnC/50/ values for some polymeric materials SHOILIN, R. D. pOO4I A78-36596 Effects of inlet airframe integration on the inlet SCHROERS, L. G. of an upper surface blowing four-engine STOL A simple method for estimating minimum aircraft autorotative descent rate of single rotor [AIAA PAPER 78-959] pOO18 A78-43521 helicopters Effect of high lift flap systems on the conceptual 00 5 fNASA-TM-78452] pg 878-20113 design of a 1985 short-haul commercial STOL tilt SCHUBERT, F. H. rotor transport Technology advancement of the electrochemical C02 [NASA-TM-78474] pOOO5-N78-21094 concentrating process 5 SHOWALTER, T. W [NASA-CR-152098] p00 2 878-22723 G-seat system step input and sinusoidal response Evaluation of a spacecraft nitrogen generator characteristics 5 2 7 [(ASA-CR-1520973 pOO N78-23748 [lASA-TH-78781 pOOO E78-26741 Advanced instrumentation concepts for A pilot evaluation of two G-seat cueing schemes environmental control subsystems [NASA-TP-1255] N78-31739 0 0 5 3 pOO8 [NASA-CR-152100 p 878-28807 SHUBAR, J. V. SCHULTZ. p. H Advanced solid electrolyte cell for C02 and H20 Interpreting statistics of small lunar craters electrolysis p0042 A78-41753 [VASA-CR-152093] pO52 178-21235 SCEWIRD. R. G. SIEBER, J. B. High angle canard missile test in the Ames 11-foot Critical review of Ames Life Science participation transonic wind tunnel in Spacelab Mission Development'Test 3: The SMD [NASA-CE-2993] pOO11 H78-25057 3 management study SCOTT, B. H. [fASA-TM-78494] p0 0 5 1 N78-26973 nova-driven winds in globular clusters SIEGEL, S. 0 0 4 1 I B- p A78-37649 Gravity as a biochemical determinant SEEBASS, A. R. p0056 A78-48671 Unsteady transonic flow computations SIMPSON, J. A. pOO32 A78-18274 Acceleration of nucleons in the interplanetary A new method for designing shock-free transonic space and the modulation of Jupiter electrons in configurations the interval from I to 10 A.U. by corotating 0 0 4 5 (AIAA PAPER 78-1114] p A78-45127 regions of solar origin SEEGEILIEH, H. 1. p037 A78-29684 Torguing preload in a lubricated bolt SIhACORI, J. B. [VASA-TM-78501] p0027 N78-29451 The determination of some requirements for a SEIFF, A. helicopter flight research simulation facility Post-Viking models for the structure of the summer [NASA-CR-152066] p0063 B78-10117 atmosphere of Mars SIB, D. P. p001 A78-50240 Stimulated emission of surface plasnoan by SENTMAR. 1). D electron tunneling in metal-barrier-metal Correction to -Recirculation of energetic structures particles in Jupiter's magnetosphere p0038 A78-30647 p0045 A78-44775 SNAIL, R. D_ Whistler mode noise in dupiterts inner magnetosphere Transonic lifting line theory - Numerical pOOL5 A78-45188 procedure for shock-free flows
141 SMIRT. D. F. PERSONAL AUTHOR INDEX
7 pOO1 178-37742 SPENCER, P. A- SMART, D. F. Factors affecting the retirement of commercial on the observation of a flare-generated shock wave transport jet aircraft at 9.7 AU by Pioneer 10 [NASA-CE-152115] p0010 878-21092 rAD-A053721] p0036 178-30078 SPIETH, 0. SMITH, C. A- Fire resistivity and toxicity studies of candidate propagation of sound through a sheared flow aircraft passenger seat materials 4 0 ENASA-CR-152196] pOOl B78-33876 [NASA-TH-78468] pO 24. 878-21214 SMITH, E. J. SPIETHi H. H Dynamic MED- modeling of the solar wind Fire resistivity and toxicity studies of candidate disturbances during the August 1972 events 6 aircraft passenger seat materials pO03 178-26079 p004 8 A78-51838 The radial dependences of the interplanetary SEIDHAR, B. magnetic field between 1 and 5 AU Pioneer8 10 Robustness in linear quadratic feedback design p004 A78-52504 with application to an aircraft control problem Dynamic HD modeling of solar wind corotating pOO14 A78-18059 stream interaction regions observed by Pioneer Robustness of linear quadratic state feedback 10 and 11 designs in the presence of system uncertainty p0049 A78-52522 p0016 A78-23917 SMITH. J. 1. STAPLEPORD, R. 1. A study of characteristics of intercity Computed responses of several aircraft to transportation systems, phase 1: Definition of atmospheric turbulence and discrete wind shears transportation comparison methodology [ASA-CR-152185] pO53 N78-32106 [NASA-CR-152153-2] p0001 N78-29996 STARR, W. L. SMITH, 1. 1. Stratospheric NO and HN03 observations in the Airborne infrared interferometric observations and Northern Hemisphere for three seasons analysis of stratospheric trace constituents p0042 A78-41123 [AIAA PAPER 78-252] pO034 A78-22606 STEGER, .. 1. Comparison between infrared Martian disk spectra On implicit finite-difference simulations of and optical properties of terrestrial analogs three-dimensional flow pOW7 A78-49231 [1IAA PAPER 78-103 p0033 178-20630 SMITH, M. Coefficient matrices for implicit finite Fibrous refractory composite insulation difference solution of the inviscid fluid [NASA-CASE-ARC-11169-I] pOOSO B78-32189 conservation law equations Spray coating apparatus having a rotatable p0038 A78-30893 workpiece holder On improving the iterative convergence properties (NASA-CASE-ARC-11110-1] pOO0O R78-32434 of an implicit approximate-factorization finite SMITH, R. A. difference algorithm On the modulation of the Jovian decametric [NASA-TM-78495] p00 2 6 N78-26795 radiation by Io. I - Acceleration of charged STEIROLFSON, R. S. particles Dynamic MHD modeling of the solar wind pO042 A78-41074 disturbances during the August 1972 events SMITH, R. . pOO36 178-26079 Closed-form equations for the lift, drag, and Dynamic MHD modeling of solar wind corotating pitching-moment coefficients of airfoil sections stream interaction regions observed by Pioneer in subsonic flow 10 and 11 (HASA-TM-784923 pOO08 H78-29068 p0049 A78-52522 SMITE, Z. K. STEVENSON, D. K. Dynamic MHD modeling of the solar wind The ILLIAC IV memory system: Current status and disturbances during the August 1972 events future possibilities p0036 A78-26079 [NASA-CR-152177] pOO 6 O R78-32731 Dynamic ERB modeling of solarvwind corotating STEWART, A. I. stream interaction regions observed by Pioneer The ionosphere and airglow of Venus - Prospects 10 and 11 for Pioneer Venus p0049 A78-52522 p 0 0 4 5 A78-q773 SOOT, . F. STEWART, 2. C. Radiometer system to map the cosmic background Quasi-optimal control of a moving-base simulator radiation p0006 B78-23021 p0038 178-30691 Optimal guidance and control for investigating SMYTH, R. K. aircraft noise-impact reduction Advanced Digital Avionics System for general [NASA-TP-1237] pOD 0 6 N78-23100 aviation STRECKER, D. V. [AIAA 77-1494] pOOl 4 A78-12243 C3 and infrared spectrophotometry of Y Canum .SOBIECZKY, H. Venaticorum 0 0 4 2 A new method for designing shock-free transonic p A78-39448 configurations Infrared excesses in early-type stars - Gamma [AIA PAPER 78-1114] pOO 4 5 178-45127 Cassiopeiae SO1IMR, K. F. A. p0047 A78-49475 Regulation of the adrenal cortex function during Engineering tests of the C-141 telescope stress [NASA-TM-78467] p0025 N78-25017 (NASA-CR-157397] p0053 178-30808 STUBBS, 1. SORESON, aA... Illumination-dependent changes in the intrinsic Development and flight tests of a Kalman filter fluorescence of hacteriorhodopsin for navigation during terminal area and landing p0055 A78-48578 operations STURE!, W. B. [NAS-CR-3015] p0012 H78-27105 Computation of transonic flow past projectiles at SOTER, S. angle of attack Radiation pressure and Poynting-lobertson drag for [AIAA PAPER 7)-1182] p0044 A78-41875 small spherical particles SUAREZ, C. B. p0033 178-19768 Intensities, self-broadening, and broadening by Ar SOuza, K. a. and H2 for the 301/111/ - 000 band of C02 Degradation of biochemical activity in soil measured at different temperatures sterilized by dry heat and gamma radiation p004 6 A78-48425 p0057 A78-53874 Absolute intensity measurements at different SPARROW, J.. G temperatures of the C-12/0-16/2 bands 30 0 1 Zodiacal light as an indicator of interplanetary 1--O0 0 0 and 30 0 1 IV--0 0 0 0 0 7 dust p 4 A78-50488 p0042 A78-38228 Measurement at different temperatures of absolute intensities, line half-widths, and broadening by
142 PERSONAL AUTHOR INDEX TURCO, R. P.
Ar and H2 for the 30 0 1 11--0g 0 0 band of C02 TAUBER, M. E. pD047 A78-50489 An analytic study of impact ejecta trajectories in SOBRMARIAN, S. the atmospheres of Venus, Mars, and earth Synthesis of N-substiteted bisitaconimide monomers p0 0 37 A78-29532 for use as thermosetting polyimide resins Trajectory module of the NASA Ames Research Center 1 pOD4 A78-36809 aircraft synthesis program ACSYNT SULLIVAN,. R.1. [NASA-TM-784973 pOOQ6 U78-26133 Application of advanced technologies to small, TAYLOR, B. J. short-haul aircraft ISAs and the dwarf content of the inner nuclear [tASA-CR-152089] pOO11 N78-22074 regions of B31 SUSIOR, H. T. p0042 A78-38569 simple torsion test for shear moduli determination TEPER, G. L. of orthotropic composites Advanced Digital Avionics System 0 2 4 for general [NASA-TM-784853 pD N78-21490 aviation SUTTON, C. E. [AIAA 77-1494] p0014 A78-12243 Low-speed aerodynamic characteristics of a Development of automatic and manual flight 00-scale YP-17 airplano model at high angles director landing systems for the XV-IS tilt of attack and sideslip rotor aircraft in helicopter mode [NASA-TM-78438] pOO06 N78-22025 (NASA-C-152140] pOOl1 178-22071 SUZUKI, T. THOMAS, M. Carbon vaporization into a nonequilibrium, Chemisotption of CO on Pd particles supported on stagnation-point boundary layer mica 2 pO04 A78-40838 p000 A78-36040 SWAN. B. F. THOSE, M. F. A flight investigation of the stability, control, On determining magnetospheric diffusion and handling qualities of an augmented jet flap coefficients from the observed effects of STOL airplane 6 Jupiter's satellite lo [NASA-TP-1254] pOOO N78-26151 p0032 A78-18732 SWAB, P. R. TIMER. H. 6. Transport of contaminants in the planetary A solution to the surface intersection problem boundary layer [NASA-CR-152116] pOO10 N78-19869 0 4 8 pD A78-52137 TOBAK, M. SWANSON, J. A. The role of time-history effects in the Factors affecting the retirement of commercial formulation of the aerodynamics of aircraft transport jet aircraft dynamics [NASA-CR-152115] pOOlO N78-21092 [(ASA-TM-78471] p0023 N78-19056 SWARTS, . pF. TODA, M. Micro-fluid exchange coupling apparatus Robustness in linear quadratic feedback 0 0 6 0 design [XASA-CASE-AEC-11114-1] p N78-33717 with application to an aircraft control problem SWINDELL. _. pOO 1 4 A78-18059 The Pioneer 11 imaging experiment of Jupiter Robustness of linear quadratic state feedback 0 0 3 2 p A78-18173 designs in the presence of system uncertainty SYBERG, J. p0016 A78-23917 Low speed test of a high-bypass-ratio propulsion TOINSEID. V. L. system with an asymmetric inlet designed fot a Magnetometer deployment mechanism for Pioneer Venus -. tilt-nacelle V/STOL airplane pO023 H78-19029 9 [UASA-CR-152072] pOO0 N78-17062 TRABOLD, B. 1. Fire resistivity and toxicity studies of candidate T aircraft passenger seat materials p0 048 A78'51838 TABkKOPF, V. Fire resistivity and toxicity studies of candidate Stress analysis study ib cooled radial inflow aircraft passenger seat materials turbine [NASA-TM-784683 p0024 N78-21214 3 0 64 [AIAA PAPER 78-94] p A78-22570 TRAYLOR, S., 3R. Theoretical and experimental study of, An investigation of wing buffeting response at aerodynamics, heat transfer and performance of a subsonic and transonic speeds. Phase 2: F-111A radial turbine flight data analysis. Volume 2: Plotted power 0 4 [NASA-CR-152105] p O6 B78-19155 spectra TALBOT, P..D_ NASA-CR-1521133 pOO1 3 E78-33117 A simple method for estimating minimum An investigation of wing buffeting response at autorotative descent rate of single rotor subsonic and transonic speeds. Phase 2: F-111A helicopters flight data analysis. Volume 3: Tabulated (RASA-TH-18452] pOO05 E78-20113 power spoctra TANNEHILL, J. C. [NASA-CR-152114] pOOI4 N78-33118 Navier-Stokes calculations for laminar and TREPPERS, R. R. turbulent hypersonic flow over indented nosetips Optimizing indium antimonide (InSb) detectors for [AIAA PAPER 18-260] p0035 A78-22608 low background operation Calculation of supersonic viscous flow over delta [ASA-T-73273] pO028 118-32947 wings with sharp subsonic leading edges TRIMMER, D. S. [AIAh PAPER 78-1137] p0043 A78-4181 Jet pump assisted arterial heat pipe Numerical solution of two-dimensional turbulent [AIAA 78-443] p004O A78-35622 blunt body flows with an impinging shock TSAI, C.-T. tAIAA PAPER 78-1209) p0045 A78-45144 The instability of the thin vortex ring of Calculation of supersonic viscous flow over delta constant vorticity wings with sharp subsonic leading edges p0031 A78-14622 2 tNASA-TM-78500] pGO 5 U78-26101 TSUOE, S. On improving the iterative contergence properties ArrheniusO law in turbulent media and an of an implicit approximate-factorization finite equivalent tunnel effect difference algorithm 0 0 0 2 6 p 049 A78-52547 CSASA-TH-78495] p N78-26795 TULLIS, R. H. TARMER T. A. Fuel conservation merits of advanced turboprop Critical review of Ames Life Science participation transport aircraft in Spacelab Mission Development Test 3: The SMD [NASA-CD-152096] p0O10 178-21095 3 management study TURCO, R. P. [NASA-TM-78494) pOO51 N78-26973 A note on the diurnal averaging of aeronomical TAIRA, J.-P. E. models Diagrammatic evaluation qf the density operator p 0 039 A78-34352 for nonlinear optical calculations An assessment of the effect of supersonic aircraft [ONERA, TP NO. 1977-166] p0031 A78-14651 operations on the stratospheric ozone content
143 TYSON, B- J. PERSONAL AUTHOR INDEX
2 7 [NASA-RP-10263 p00 N78-30774 Stratospheric measurements of CF2CI2 and N20 TYSON, B. J. p054 A78-37055 Lower stratosphere measurements of variation with VERNIKOS-DARELLIS, Jo latitude of CP2Cl2, CFCl3, CCl4, and N20 Hormonal indices of tolerance to *Gz acceleration profiles in the northern hemisphere in female subjects p0035 A78-23610 p0055 A78-41162 Stratospheric measurements of CF2C12 and N20 0 5 VEVERKA, 3. p0 4 A78-37055 Occultation ,of-Epsilon Geminorum by Mars. IT - The InterhemisRheric gradients of Cp2C12, Cfcl3, CC14, structure and extinction of the Martian upper and 920 atmosphere 0 0 4 2 3 p A78-41124 pOO 0 178-10587 TYSON, J. A. The composition of Phobos - Evidence for Radiometer system to map the cosnic background carbonaceous chondrite surface from spectral radiation analysis 0 3 8 p0 A78-30691 p0 0 3 2 178-18874 Multicolor observations of Phobos with the Viking lander cameras - Evidence for a carbonaceous chondritic composition UNDERWOOD, J. B. p0032 A78-18875 Generation of a parallel X-ray beam and its use VIEGAS, J. R, for testing collimators Comparison of multiequation turbulence models for pO035 A78-23083 several shock-separated boundary-layer The quiet coronal x-ray spectrum of highly ionized interaction flows oxygen and nitrogen [AlAA PAPER 78-1165] p0043 A78-41863 pOO38 A78-31108 VIGNHEON, Y. C. UTTEDBACK, N. G. Navier-Stokes calculations for laminar and Low energy ionizing collisions between 92 and CO turbulent hypersonic flow over indented nosetips beam molecules and CO. N2, NO, CH4, and C02 [AIAA PAPER 78-260] p 0 0 3 5 178-22608 target molecules Computation of the viscous supersonic flow 9 over pOO3 178-34137 symmetrical and asymmetrical external axial corners fATAA PAPER 78-1135] p0043 A78-41839 V Calculation of supersonic viscous flow over delta VA.EEO, F_ P. J. wings with sharp subsonic leading edges Intensities, self-broadening, and broadening by Ar [AIAA PAPER 78-1137) pOO43 A78-41841 and R2 for the 301/III/ - 000 band of C02 Numerical solution of two-dimensional turbulent measured at different temperatures blunt body flows with an impinging shock pOO46 A78-48425 [AIAA PAPER 78-1209] pO0 4 5 A78-45144 Absolute intensity measurements at different calculation of supersonic viscous flow over delta temperatures of the C-12/0-16/2 bands 30 0 1 wings with sharp subsonic leading edges 1--0O 0 0 and 30 0 1 xV--00 0 0 7 [(NSA-TM-78500] p0025 N78-26101 pO04 A78-50488 VISWANATH, P. R. Measurement at different temperatures of absolute Injection slot location for boundary-layer control intensities, line half-widths, and broadening by in shock-induced separation Ar and N2 for the 30 0 1 11--0O 0 0 band of C02 [ATAA PAPER 78-1168] pOO 4 4AA78-41866 4 7 - pOD A78-50489 VISVANATH, I° Comments on the note by Aria et al. on the The co-adsorption of copper and oxygen on a transition moment of the C02 band near 7740 tungsten 100 plane-type surface kays.rs p0037 A78-29489 8 pO04 A78-52388 VOMASKE, N. P. VAN ALLEN, J. A. A flight investigation of the stability, control, On determining magnetospheric diffusion and handling qualities of an augmented jet flap coefficients from the observed effects of STOL airplane 2 54 Jupiter's satellite xo [NASA-TP-1 ] pOOO6 H78-26151 pO03 2 A78-18732 VYKUKAL, H. C. Energetic protons associated with interplanetary Spacesuit mobility knee joints active regions 1-5 AU from the sun [NASA-CASE-ARC-11058-2] pO057 178-18763 pOD36 178-26081 Spacesuit mobility joints correction to fRecirculation of energetic (NASA-CASE-ARC-11058-1] p0050 B78-31735 particles in Jupiter's magnetospherel Spacesuit torso closure pO0U5 A78-44775 [NASA-CASE-ARC-11100-1] p0O58 878-31736 VAN ZYL. B. Low energy ionizing collisions between 12 and CO W beam molecules and Co, N2, NO, C4, and C02 target molecules 9 1ADCCCK, A. Jo p003 A78-34137 Flying-hot-wire study of two-dimensional mean flow YARYAN. L. I. past an NACA 4412 airfoil at maximum lift Crustal evolution inferred from Apollo magnetic [AIAA PAPED 78-1196] pOO18 A78-41887 measnrements WAGGONER, 7- G. 0 0 2 7 [NASA-TN-78524] p 178-32029 Computational wing optimization and wind tunnel VAEON, M. N. test of semi-span model Thermal design and development of a planetary [AIAA PAPER 78-102] pO034 A78-22575 probe - Pioneer Venus large probe Computational wing optimization and comparisons [AIAA PAPER 78-916] pO041 178-37275 with experiment for a semi-span wing model VATNEfR S. P. [NASA-TM-78480] pOO25 N78-26106 Effects of exercise and excitement on mesenteric Wind tunnel investigation of computationally and renal dynamics in conscious, unrestrained optimized variable camber wing configurations baboons [NASA-TH-78479] pOO 2 6 18-29067 3 pOO5 A78-27124 WAKEFIELD, R_ M. Extent of utilization of the Frank-Starling A method for determining structural properties of mechanism in conscious dogs RCC thermal protection material pOO5Q A78-33522 (AIlA PAPER 78-869] pOO4 0 A78-35997 VEDDEE, . P. WALKER, G. G. Lower stratosphere measurements of variation with Prop-fan data support study latitude of CF2Cl2, CFC13, CCI4, and 820 [NASA-C-1521413 pOO1 3 N78-27128 profiles in the northern hemisphere WANs, C. C. p0035 A78-23610 Simultaneous determination of rotational and Microparticle accelerator-of unique design translational temperatures of OH/2 Pi/ in a gas p0036 A78-25264 discharge
144 PERSONAL AUTHOR INDEX WYNVEEN. R. A.
p0030 A78-10405 . WILLIAMS, 1. 3. Absorption measurements of OH using a c tunable A method for the analysis of the benefits and costs for aeronautical research and technology laser 0 0 0 7 p0 0 3 2 A78-17837 p 378-29060 ARG, S. Short-haul CTOL aircraft research Characteristics of integrated KOM junctions at dc pOOOB 178-29061 and at optical frequencies WILLIAMS, R. J. [AD-AO56165] p0037 A78-28926 Investigation of a cryogenic thermal diode 4 0 WARWICK, .. W. [AIAA 78-q171 pOO A78-35601 On the observation of a flare-generated shock wave Experimental temperature distribution and heat at 9.7 AU by Pioneer 10 load characteristics of rotating heat pipes 0 0 3 8 0 0 4 6 [AD-AO53721) p A78-30078 p A78-48835 WASSER AN, I- H. RIEFLER, L. H. The radii of Uranian rings alpha, beta, gamma, Space colonization - Some physiological perspectives 0 0 5 5 delta, epsilon, eta, 4, 5, and 6 from their p A78-41164 occultations of SAO 158687 WINTER, D. A. Light element geochemistry of the Apollo 12 site p0046 A78-48112 0 54 WATERS, M. H. p A78-34503 Requirements for regional short-haul air service WITTEBORN, F. C_ and the definition of a flight program to C3 and infrared spectrophotometry of Y Canum determine neighborhood reactions to small Venaticorum transport aircraft p0042 A78-39448 [NSA-CR-152151] pOO13 N78-30070 Infrared excesses in early-type stars - Gamma WEBOnR. B W. Cassiopeiae p0047 A78-49475 Spacesuit torso closure 8 [NASA-CASE-ARC-11100-1] . p005 N78-31736 VOEILER, Y. WEINBERG, J. 1. Carbon suboxide polymer, an explanation for the Zodiacal light as an indicator of interplanetary wave of darkening on Mars dust pO056 A78-48717 p 0 0 4 2 A78-38228 WOELLER, F. H_ WEMPE, T_ B Synthesis of porous polyaromatic column packings Simulator evaluation of three situation and for GC analysis of extraterrestrial atmospheres guidance displays for V/STOL aircraft zero-zero pOO55 A78-48577 landing approaches Chelate-modified polymers for atmospheric gas pOO55 A78-44131 chromatography 5 7 WENZEL, K.-P. [N3A3-CASE-AC-11154-1) p00 U78-27275 igidity-independent coronal propagation and WOLF. T. I. escape of solar protons and alpha particles The effect of tip vortex structure on helicopter due to blade/vortex interaction p0041 A78-37354 noise 2 WERNICKE, K. G. [NASA-CR-152150] pOO1 378-25832 Evaluation of the tilt rotor concept: The XV-15ts VOLPE, J. H. role Dynamic HD modeling of the solar wind pOO04 78-19142 disturbances during the August 1972 events VEST, M. W. p0036 A78-26079 Chemical evolution and the origin of life - On the observation of a flare-generated shock wave Bibliography supplement 1976 at 9.7 AU by Pioneer 10 0 0 3 8 pOO 5 7 A78-53875 [AD-A053721] p A78-30078 WIEERY, J. R. Dynamic ERB modeling of solar wind corotating Characteristics of integrated MOM junctions at dc stream interaction regions observed by Pioneer and at optical freguencies 10 and 11 0 0 3 7 0 0 4 9 [AD-A056165] p A78-28926 p A78-52522 WHITTEN, R. C. Pioneer 10 observation of the solar wind proton A note on the diurnal averaging of aeronomical temperature heliocentric gradient 2 7 models [NASA-T-78515] pOO 878-31030 p0 0 3 9 A78-34352 WOOD, P. C. Geographical variations of NO and 03 in the lower Chemical interpretation of Viking Lander 1 life stratosphere 0 0 3 9 detection experiment 3 p 378-35403 pOD5 A78-25560 An assessment of the effect of supersonic aircraft WOOD, R. D. on the stratospheric ozone content review of VASA-sponsored technology assessment operations 0 0 27 A [NASA-RP-1026] p N78-30774 projects WIDNALL. S .F [NASA-TM-78472] p0025 378-24000 The instability of the thin vortex ring of WOODS, . R. constant vorticity Technology advancement of the electrochemical C02 p0031 A78-14622 concentrating process 0 0 5 2 The effect of tip vortex structure on helicopter [DASA-CR-152098] p N78-22723 noise due to blade/vortex interaction WOOLLEY, J. P. [NASA-CR-152150] p0012 N78-25832 Propagation of sound through a sheared flow VIXRSMA, S. J. [NASA-CR-152196] pOO1 978-33876 Fire detector response in aircraft applications WO, F.-11. p 0 0 4 9 A78-53674 Europa - Ultraviolet emissions and the possibility WILCOX, D. of atomic oxygen and hydrogen clouds V/STOL aircraft simulation - Requirements and pOO48 A78-52482 capabilities at Ames Research Center WU, S. T. [AIAA PAPER 78-15151 p0021 A78-49790 Dynamic MHD modeling of solar wind corotating WILHELE, J. stream interaction regions observed by Pioneer Critical review of Ames Life Science participation 10 and 11 4 9 in Spacelab Mission Development Test 3: The SMD pO0 A78-52522 3 management study WUNDER, C. C. (NASA-TH-78494] pO51 378-26973 -Food and oxygen requirements for growing mice and development WILKINS, J. . turtles after hypergravitational 1 Multichannel electrochemical microbial detection p003 A78-15204 unit WYDEVEX, ?. - pOO16 A78-31300 Chemical interpretation of Viking Lander 1 life WILLIAMS, B. A. detection experiment An inductively powered telemetry system for p053 A78-25560 temperature, EKE, and activity ronitoring RYhVEEN, R. A. 0 0 5 9 [NSA-TM-78486] p 378-23706 Advanced instrumentation concepts for environmental control subsystems
145 TANG, P. Y. PERSORAL AUTHOR INDEX
[NASA-CR-152100] pOO 53 n78-28807 Y !AXG, P. 7. Advanced instrumentation concepts for environmental control subsystems [ERSA-CR-152100] pOO53 N78-28807 IBARRA, A--H. Estimating maximum instantaneous distortion from inlet total pressure rms measurements [AIAA PAPER 78-970] p0019 A78-43525 YEE, S. Y. Diagrammatic evaluation of the density operator for nonlinear optical calculations [ONERA, TP NO. 1977-166] pOO31 A78-14651 YOUNG. R- M The quiet coronal X-ray spectrum of highly ionized oxygen and nitrogen p0038 A78-31108 YOUNG, R. W Multichannel electrochemical microbial detection unit p0016 A78-31300 YU, N. J. Unsteady transonic flow computations p0032 A78-18274 A new method for designing shock-free transonic configurations fAIAA PAPER 78-1114] pOO4 5 A78-45127 YU, Y. I.T Hovering impulsive noise: Some measured and calculated results p0 0 63 178-32831 YUAN, 1. S_ An investigation of short haul air transportation in the southeastern United States [NHASA-CB-152166] p0012 878-27094 YUAN, J.-M.. A new concept in laser-assisted chemistry - The electronic-field representation p00 3 7 A78-27743 Semiclassical approach to collision-induced emission in the presence of intense laser radiation - An aspect in the study of cooperative chemical and optical pumping p00 37 A78-27744 Semiclassical theory of unimolecular dissociation induced by a laser field EAD-A056671 p0 0 39 A78-34682 YUNG, Y. L. Primitive atmosphere and implications for the formation of channels on Mars 4 z pOO4 A78-42460 ZIMMERMAN, I. H. A new concept in laser-assisted chemistry - The electronic-field representation p00 3 7 A78-27743 Semiclassical approach to collision-induced emissibn in the presence of intense laser radiation - An aspect in the study of cooperative chemical and optical pumping p0037 A78-27744
146 CORPORATE SOURCE INDEX
Typical Corporate Source Index Listing
SCORPORATE SOURCE
ANALYTICAL MECHANICS ASSOCIATES, INC., MOUNTAIN VIEW, CALIF. BEAM ENGINEERING, INC., SUNNYVALE, CALIF. Development and flight tests of a Kalman filter Acoustical effects of blade tip shape changes on for navigation during terminal area and a full scale helicopter rotor in a wind tunnel landing operations 0 [(ASA-CR-152082] pOO1 N78-20918 ENASA-CR-30151 p00 12 P78-27105 ARIZONA UIV.i TUCSON. The Pioneer 11 imaging experiment of Jupiter p0 0 32 A78-18173 TITLRT PAUnsteady transonic f1ow computations UNUMBER p0 0 32 A78-18271. A new method for designing shock-free transonic configurations [1111 PAPER 78-1114] pOih5 A78-45127 The title of the document is used to provide a brief description of the subject ARMY AIR MOBILITY RESEARCH AND DEVELOPMENT LAB., iteEe', The page u.ber aid NASA or AIAA accession number are included BOFFETT FIELD, CALIF. in each entry to assist the user in locating the abstract in the abstract section Computational wing optimization and wind tunnel If applicable a report number is also included as an aid in identifying thedocu- test of semi-span model ment [AIAA PAPER 78-102) p 0 034 A78-22575 Evaluation of the tilt rotor concept: The XV-15s role pOC00 N78-19142 A ARMY AVIATION RESEARCH AND DEVELOPHENT COMMAND, MOFFETT FIELD, CALIF. ACUREX CORP., MOUNTAIN VIER, CALIF. Theoretical and experimental study of the drag Aerothermodynamic environment for Jovian entry of multielement airfoils with silica heat shield [AIAA PAPER 78-1223] pOO19 A78-45148 3 [AIlA PAPER 78-186 pOO3 A78-20730 Aeromechunical stability of helicopters with a AERONAUTICAL RESEARCS ASSOCIATES OF PRINCETON, bearingless main rotor. Part 1: Equations of INC., N. J. motion Application of second-order turbulent modeling [NASA-TI-78459] p0062 N78-18043 t0 the prediction of radiated aerodynamic sound Wind tunnel investigation of computationally 2 [NASA-CB-2994] pOO1 V78-25359 optimized variable camber wing configurations AERONAUTICAL RESEARCH FOUNDATION, CAMBRIDGE, BASS. (TASA-TH-78479] p0026 H78-29067 Requirements for regional short-haul air service ARMY AVIATION RESEARCH AND DEVELOPMENT CONAIND, ST. and the definition of a flight program to LOUIS, O. determine neighborhood reactions to small An experimental investigation of hingeless transport aircraft helicopter rotor-body 3 stability in hover [NASA-CR-152151] pOO1 N78-30070 [NASA-TM-78489] p0063 N78-29044 AERONAUTICAL RESEARCH LABS., MELBOURNE (AUSTRALIA). Closed-form equations for the lift, drag, and Zodiacal light as an indicator of interplanetary pitching-moment coefficients of airfoil dust 2 sections in subsonic flow p00 78-38228 [ASA-T-78492] pOGOS N78-29068 AEROPHYSICS RESEARCH COR. MOUNTAIN VIEW. CAIP. ARMY ELECTRONICS COMMAND, PORT MONMOUTH. N. J. Coplanar tail-chase aerial combat as a Low profile antenna performance study. Part 2: differential game Broadband 1 antenna techniques survey pOOl A78-10455 [AD-A047992] p0022 U78-18274 AEROSPACE CORP., LOS ANGELES, CALIF. ARMY MATERIEL SYSTEMS ARLYSIS ACTIVITY, ABERDEEN Generation of a parallel X-ray beam and its use PROVING GROUND, MD. for testing collimators Computation of transonic flow past projectiles p0035 A78-23083 at angle of attack The quiet coronal X-ray spectrum of highly [AIAA PAPER 78-1182] p0044 A78-41875 ionized oxygen and nitrogen ARMY NATICK RESEARCH AND DEVELOPMENT CDOMAND, 3 MASS. p00 8 &78-31108 Accordion shelter hardware analysis AIR FORCE GEOPHYSICS LAB., HRANSCOM APB, MASS. [AD-A053592] pOO07 R78-28278 On the observation of a flare-generated shock ARMY RESEARCH AND TECHNOLOGY LABS., MOFFETT FIELD, wave at 9.7 AU by Pioneer 10 CALIF. [AD-A053721] p0038 A78-30078 Application of advanced high speed turboprop ALABAMA UNIV.. HUNTSVILLE. technology to future civil short-haul Dynamic liD modeling of the solar wind transport aircraft design disturbances during the August 1972 events [AIAA PAPER 78-1487] p0064 A78-47930 p0036 A78-26079 ASTRONOMICAL OBSERVATORY, CAPE TOWN (SOUTH AFRICA) Dynamic MHD modeling of solar wind corotating The radii of Uranian rings alpha, beta, gamma, stream interaction regions observed by Pioneer delta, epsilon, eta, a, 5& and 6 from their 10 and 11 occultations of SAO 150687 p0049 178-52522 p04 6 A78-48112 AMOCO OIL CO., NAPERVILLE, ILL. ASTROPHYSICS RESEARCH CORP., BELLEVUE, WASH. The co-adsorption of copper and oxygen on a High performance dash-on-warning air mobile tungsten 100 plane-type surface missile system p0037 A78-29489 [AIAA 78-1353] p0019 A78-46545 ANALYTICAL MECHANICS ASSOCIATES, INC., JERICHO, N.Y. A preference-ordered discrete-gaming approach to air-combat analysis p0020 A78-49255 BATTELLE COLUMBUS LABS., MOUNTAIN VIEW, CALIF. NASA aviation safety reporting system
147 BEAR ENGINEERING, INC., SUNNYVALE, CALIF. CORPORATE SOURCE INDEX
(ASA-TH-78476] p8051 N78-25071 Automatic multiple-sample applicator and NASA aviation safety reporting system electrophoresis apparatus (NASA-TM-78511] p0052 B78-32075 [EASA-CASE-ARC-1O991-11 pOO5 7 N78-14104 BEAM ENGINEERING, INC., SUNNYVALE, CALIF. Stress-strain behavior of some acrylic gradient Acoustical effects of blade tip shape changes on polymers a full scale helicopter rotor in a wind tunnel [AD-A0526171 pgO59 378-24364 (NASA-CE-152082] pO010 H78-20918 An investigation of short haul air BELL AND HOWELL CO., CHICAGO, ILL. transportation in the .southeastern United Stated oron trifluoride coatings for -thermoplastic rNASA-CR-152166] pOOl 2 B78-27094 materials and method of applying same in glow CALIFORNIA UNIT., BERKELEY. LAWRENCE RADIATION LAB. discharge Influence of temperature and the role of (IASA-CASE-ARC-11057-1] p057 V78-31233 chromium on the kinetics of sulfidation of 310 process for producing a well-adhered durable stainless steel optical coating on an optical plastic substrate pOO43 A78-41796 [NASA-CASE-ARC-11039-1] p0058 N78-32854 CALIFORNIA UNIY., DAVIS. BENDIX CORP., SOUTHFIELD, BICE. Fluid-electrolyte shifts and maximal oxygen Effects of potassium titanate fiber on the wear uptake in man at simulated altitude /2,287 a/ of automotive brake linings pO054 AI8-36602 pO035 A78-23450 CALIFORNIA UNIV., LA JOLLA. BOEING CO., SEATTLE. WASH. Quiet time interplanetary cosmic ray Advanced panel-type influence coefficient anisotropies observed from Pioneer 10 and 11 methods applied to unsteady three dimensional p0O 3 9 A78-34567 potential flows CALIFORNIA UNIV., LOS ANGELES. [AIAA PAPER 78-229] p0021 A78-52630 On the relative locations of the bow shocks of Low speed test of a high-bypass-ratio, propulsion the terrestrial planets System with an asymmetric inlet designed for a p031 A78-13752 tilt-nacelle V/STOL airplane Peripheral processors for high-speed simulation (NhASA-CR-152072] pOO09 W78-17062 pOO14 A78-14063 BOEING COMMERCIAL AIRPLANE CO., SEATTLE, WASH. A uniqueness proof for a transonic flow problem Fuel saving potential of Mach 0.8 twin engine pO016 A78-26599 prop-fan transports On the apparent source depth of planetary pOol? A78-31306 magnetic fields An improved higher order panel method for p0037 A78-29472 linearized supersonic flow Light element geochemistry of the Apollo 12 site 0 0 2 1 4 (AIlA PAPER 78-151 p A18-52628 pOO5 A78-34503 Application of advanced technologies to small, Lifting line theory for transonic flow short-haul aircraft pOO20 A78-48991 [NASA-CR-152089] pO011 N78-22074 The radial dependences of the interplanetary A Mach line panel method for computing the magnetic field between I and 5 AU Pioneer 10 linearized supersonic flow over planar wings p0 0 4 8 A78-52504 [NASA-CR-152126] p0012 u78-27087 Ron-linear parametric generation of sound by BOLT, BERANEK, AND NEWMAN, INC., CANOGA EARK, CALIF. resonant mode conversion Use of coherence and phase data between two fAD-A049157] p0059 N78-19901 receivers in evaluation of noise environments CALIFORNIA UNIV., SAN FRANCISCO. pOO16 A78-26495 Hormonal indices of tolerance to +Gz BURROUGHS CORP., PAOLI, PA- acceleration in female subjects Numerical aerodynamic simulation facility. p0055 A78-41162 Preliminary study extension. Executive summary Illumination-dependent changes in the intrinsic [NASA-CR-152106] p0028 N78-19050 fluorescence of bacteriorhodopsin Numerical aerodynamic simulation facility. p055 A78-48578 Preliminary study extension Methionine transport in Halobacterium halobium [NASACR152107) p0028 E78-19051 vesicle.s - V.oncompetitive., symmetric Numerical Aerodynamics SimulationFacility inhibition by L-Cysteine preliminary study, executive summary pOO55 A78-48579 p0023 N78-19782 CALSPAR CORP., BUFFALO, N. Y. Flight simulation - A vital and expanding technology in aircraft development [AIAA PAPER 78-337] pOOl6 A78-29295 CALIFORNIA INST. OF TECH., PASADENA. CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, Flying-hot-wire study of two-dimensional mean MARSEILLES (FRANCE). flow past an MACA 4412 airfoil at maximum lift Radiation pressure and Poynting-Robertson drag [AIAA PAPER 78-1196] pOO18 A78-41887 for small spherical particles Primitive atmosphere and implications for the p0033 A78-19768 formation of channels on Mars CHICAGO UNIV., ILL. 0 0 4 4 p A78-42460 The interplanetary modulation and transport of CALTFORNIA UIV.# BERKELEY. Jovian electrons Diagrammatic evaluation of the density operator p0036 A78-26080 for nonlinear optical calculations Acceleration of nucleons in the interplanetary ONERA, TP NO. 1977-1661 p0031 A78-14651 space and the modulation of Jupiter electrons Collisionless dissociation of SF6 using two in the interval from I to 10 1.U. by resonant frequency C02 laser fields corotating regions of solar origin pOO31 A78-14655 p0037 A78-29684 Effect of a nonconstant C/m-alpha/ on the CHILDRENS HOSPITAL MEDICAL CENTER, BOSTON, MASS. stability of rolling aircraft Effects of exercise and excitement on mesenteric pOO31 A78-16180 and renal dynamics in conscious, unrestrained Characteristics of integrated MOM junctions at baboons dc and at optical frequencies p005 3 A78-27124 [AD-A056165] p0037 A78-28926 Extent of utilization of the Frank-Starling stimulated emission of surface plasmons by mechanism in conscious dogs electron tunneling in metal-barrier-metal pO054 A78-33522 structures CINCINNATI UNIV., OHIO. p0038 A78-30647 stress analysis study in cooled radial inflow Radiometer system to map the cosmic background turbine radiation [AIAA PAPER 78-94] p 00 64 A78-22570 p0038 A78-30691 Theoretical and experimental study of continuous metabolic and cardiovascular aerodynamics, heat transfer and performance of measurements on a monkey subject during a a radial turbine simulated 6-day Spacelab mission (lAS-CR-152105] p0064 N78-19155 pOO56 A78-48719
148 CORPORATE SOURCB INDEX HARVARD MEDICAL SCHOOL, BOSTON, MASS.
COLORADO STATE UVIV., 7ORT COLLINS. Measuring the velocity of individual atoms in E real time p0035 A78-23124 ECONERGY IBC-, LOS ANGELES, CALIF. COLORADO UNIV., BOULDER- A study of characteristics of intercity Visualization of quasi-pariodic unsteady flows transportation systems. Phase 1: Definition EAIAA 78-5021 pO016 A78-29804 of transportation comparison methodology On the observation of a flare-generated shock [NASA-CR-152153-2] pOO0 1 78-29996 wave at 9.7 AU by Pioneer 10 EUROPEAN SPACE AGENCY, NOORDWIJ (IETHEREAUDS). [AD-AO53721] p0038 A78-30078 Rigidity-inaependent coronal propagation and The ionosphere and airglow of Venus - Prospects escape of solar protons and alpha particles 4 for Pioneer Venus 4 pOO 1 A78-37354 pOO 5 A78-44773 EUROPEAN SPACE AGENCY, PARIS (FRANCE). COMPUTER SCIENCES CORP., LOS ANGELES, CALIF. NASA/ESA CV-990 spacelab simulation (ASSESS 2) The ILLIAC IV memory system: Current status and [NASA-TM-79748] p0 0 2 7 N78-30149 future possibilities [N&SA-CR-152177] p0860 178-32731 F COMPUTER SCIENCES CORP., MOUNTAIN VIEW, CALIF. Theoretical and experimental study of the drag FEDERAL AVIATION ADMINISTRATION, MOFFETT FIELD, of multielement airfoils CALIF. [AA PAPER 78-1223] pOO19 A78-45148 Certification study of a derivative model of a CONTROL DATA CORP., MINHEAPOLIS, HIRN. small jet transport airplane using a piloted Preliminary study for a Numerical Aerodynamic research simulator Simulation Facility [hD-A46442) pOO61 N78-14033 p0023 N78-19783 FLORIDA AGRICULTURAL AND MECHANICAL UNIV., CONTROL DATA CORP., ST. PAUL, MINN. TALLAHASSEE. Preliminary study for a nuerical aerodynamic Regulation of the adrenal cortex function during simulation facility. Phase 1: Extension stress [NkSA-CR-152108] p0028 178-19052 [NASA-CR--157397] p0 0 5 3 N78-30808 CORNELL UNIV., ITHACA, M. Y. FORD MOTOR CO., DEARBORN, MICH. Occultation of Epsilon Geminorum by Mars. 11 - Simultaneous determination of rotational and The structure and extinction of the Martian translational temperatures of O/2 Pi/ in a upper atmosphere gas discharge 3 pO0 O A78-10587 pO30 A78-10405 The composition of Phobou - Evidence for Absorption measurements of OH using a CW tunable carbonaceous chondrite surface from spectral laser analysis p 0 0 3 2 A78-17837 pO0 3 2 A78-18874 Multicolor observations of Phobos with the Viking lander cameras - Evidence for a carbonaceous chondritic composition GENERAL DYNAMICS/FORT WORTH, TEX. p0032 378-18875 An investigation of wing buffeting response at Radiation pressure and Poynting-Dobertson drag subsonic and transonic speeds: Phase 1: for small spherical particles F-111A flight data analysis. Volume 1: p0033 A78-19768 Summary of technical approach, results and Signal-to-noise ratios for stellar occultations conclusions by the rings of Uranus, 1977-1980 [NASA-CR-152109] nO13 F78-33113 3 p003 A78-20223 An investigation of wing buffeting response at Analysis of stellar occultation data - Effects subsonic and transonic speeds. Phase 2: of photon noise and initial conditions F-1lIA flight data analysis. Volume 2: p0035 A78-23164 Plotted power spectra The radii of Uranian rings alpha, beta, gamma, fNASA-CR-152113] pOO13 N78-33117 delta, epsilon, eta, 4, 5, and 6 from their An investigation of wing buffeting response at occultations of SAO 158687 subsonic and transonic speeds. Phase 2: 4 6 pO0 A78-48112 F-111A flight data analysis. Volume 3: Tabulated power spectra D [NASA-CR-152114] pOO1 4 N78-33118 GENERAL ELECTRIC CO., PHILADELPHIA, PA. DENVER UNIV.,. COLD. Entry dynamics performance predictions for Low energy ionizing collisions between N2 and Co Pioneer Venus probes beam molecules and CO, N2, NO, CH4, and C02 [AIAA 78-1370] pO46 A78-46557 target molecules GEOLOGICAL SURVEY, MENLO PARK, CALIF. 9 pO03 A78-34137 Some Martial volcanic features as viewed from Stratospheric 10 and BE03 observations in the the Viking orbiters 3 Northern Hemisphere for three seasons pOO O A78-11403 p042 A78-41123 GORHAM ASSOCIATES, THOUSAND OAKS, CALIF. DOUGLAS AIRCRAFT CO., INC., LONG BEACH, CALIF. Study to determine operational and performance Transonic wing analysis using advanced criteria for STOL aircraft operating in low computational methods visibility conditions [AAA PAPER 78-1053 pO15 A78-20686 [(ASA-CR-152164] pOO13 N78-28083 Fire resistivity and toxicity studies of GRUMMAN AEROSPACE CORP., BETHPAGE, N.Y. candidate aircraft passenger seat materials Airborne infrared interferometric observations pO48 A78-51838 and analysis of stratospheric trace constituents Aircraft cargo compartment fire test-simulation [AIAA PAPER 78-252) p0 0 3 4 A78-22606 program A re-entrant groove hydrogen heat 2 pipe 0 [NASA-CR-151951] pOO 9 H78-21223 [ATAA 78-420] pOO4 A78-35603 DOUGLAS AIRCRAFT CO., INC., SANTA MONICA, CALIF. Comparison between infrared Martian disk spectra A solution to the surface intersection problem and optical properties of terrestrial analogs [NASA-CE-152116] p001O N78-19869 pOO47 A78-49231 DYNAMICS TECRNOLOGY, INC., TORRANCE, CALIF. Behavior of a turbulent boundary layer subjected strain to sudden transverse 4 (AIAA PAPER 78-201] p003 A78-22595 HAMILTON STANDARD, WINDSOR LOCKS, COHN. DYNATSEE CORP., COCKEYSVILLE, MD. Prop-fan data support study , Jet pump assisted arterial heat pipe [NASA-CR-152141] pOO1 3 H78-27128 [ATAA 78-443] p0040 A78-35622 HARVARD MEDICAL SCHOOL, BOSTON, MASS. Extent of utilization of the Frank-Starling mechanism in conscious dogs p054 A78-33522
149 HARVARD UNIV., CORPORATE SOURCE INDEX
HARVARD UNIV., BOSTON, MASS. Theoretical and experimental study of the drag Effects of exercise and excitement on ieenteric of multielement airfoils 9 and renal dynamics in conscious, unrestrained [AIA PAPER 78-1223] pOO1 A78-4514B8 baboons A study of test section configuration for shock pRO53 A78-27124 tube testing of transonic airfoils 2 HARVARD URIV., CAMBRIDGE, MASS. [NASA-CH-157237] pOO1 E78-26153 Applications of algebraic geometry to systems IOWA UNIV., IOWA CITY. theory - The McMillan degree and Krorecker Food and oxygen regurements,for growing,mice indices of transfer functions as -opological au-d turiles after hypergravitational development and holoorphic system invariants p0031 A78-15204 p0021 A78-51860 On determining magnetospheric diffusion HARVEY MUDD COLL.. CLAREMONT, CALIF. coefficients from the observed effects of Generation of a monodispersed aerosol Jupiter's satellite Io 2 rNASA-CR-152133] pOO11 N78-21445 p0O3 A78-18732 HAWAII UNIV., HONOLULU. Energetic protons associated with interplanetary Gravity as a biochemical determinant active regions 1-5 AU from the sun 6 pOO5 A78-48671 p0036 A78-26081 HINDUSTAN AERONAUTICS LTD., BANGALORE (INDIA). On the modulation of the Jovian decametric Injection slot location for boundary-layer radiation by Io. I - Acceleration of charged control in shock-induced separation particles [1IAA PAPER 78-11681 pOO 4 4 A78-41866 pO042 A78-41074 HUGHES AIRCRAFT CO., CULVER CITY, CALIF. Correction to 'Recirculation of energetic magnetometer deployment mechanism for Pioneer particles in Jupitets magnetosphere' Venus pO04 5 A78-44775 p0023 N78-19029 Whistler mode noise in Jupiter's inner HUGHESAIRCRAFT CO., EL SEGUNDO, CALIF. magnetosphere Thermal design and development of a planetary p004 5 A78-45188 probe - Pioneer Venus large probe [AIAA PAPER 78-916] p0041 A78-37275 J Pioneer Venus spacecraft charging model p0022 N78-10148 JET PROPULSION LAB., CALIF. INST. OF TECH., PASADENA. _ The composition of Phobos - Evidence for carbonaceous chondrite surface from spectral analysis 2 IBM WATSON RESEARCH CENTER, YORKTOWN HEIGHTS, B.1. pO3 A78-18874 Digital filter structures baying low errors and Multicolor observations of Phobos with the simple hardware implementation Viking lander cameras - Evidence for a p0056 A78-51346 carbonaceous chondritic composition ILLINOIS UNIV., URBANA. pO032 A78-18875- Human problem solving performance in a fault Dynamic MRD modeling of the solar wind diagnosis task disturbances during the August 1972 events pOO5 A78-32673 p0036 A78-26079 A model of human decisionnaking in a fault The radial dependences of the interplanetary diagnosis task magnetic field between 1 and 5 AU Pioneer 10 0 8 p0054 A78-37130 p 04 A78-52504 INDIAN IEST. OF SCIENCE, BARNGALORE. Dynamic MMD modeling of solar wind corotating Injection slot location for boundary-layer stream interaction regions observed by Pioneer control in shock-induced separation 10 and 0 0 4 4 ii [(IAl PAPER 78-1168] p A78-41866 p0049 A78-52522 INDIAN SPACE RESEARCH ORGAIZATIOX, AHMEDABAD. An integral solution to a nonlinear diffusion problem p037 A78-26350 KAMAN AEROSPACE CORP., BLOOMFIELD, CONN. INDIAN SPACE RESEARCH ORGANIZATION, TRIVANDRUB. Theoretical study of multicyclic control of a The general solution to the classical problem of controllable twist rotor the finite Euler-Bernoulli beam [NASA-CR-151959] N78-33085 4 p0064 pOO 7 A78-50909 KANSAS URIV. CETER FOR RESEARCH, INC., LAWRENCE. INDIANA UNIV., BLOOMINGTON- A study of commuter airplane design optimization Nova-driven winds in globular clusters [NASA-CR-157210] pOOh1 N78-25078 pOMl A78-37649 KOLITE SEMI-CONDUCTOR PRODUCTS, INC., RIDGEFIELD, INFORMATICS-PHI, INC., PALO ALTO, CALIF. N... 110: A FORTRAN direct access data management A fifty channel electrically scanned pressure system module p0060 H78-33784 pOO14 A78-17395 IOWA STATE UNIV. OF SCIENCE AND TECHNOLOGY, AMES. Laser-velocimeter surveys of merging vortices in L a wind tunnel [IAA PAPER 78-107] pOO15 A78-20687 LEAR SIEGLER, INC., SANTA MODICA, CALIF. Navier-Stokes calculations for laminar and The ILLIAC IV memory system: Current status and turbulent hypersonic flow over indented nosetips future possibilities [AIAA PAPER 78-260] p0035 A78-22608 [NASA-CR-152177] pO06O 78-32731 The shock tube as a device for testing transonic LIRARY OF CONGRESS, WASHINGTON, D. C. airfoils at high Reynolds numbers Food and oxygen requirements for growing mice [AIAA 78-769] pOO17 A78-32330 and turtles after hypergrvitationul development Computation of the viscous supersonic flow over . p0031 A78-15204 symmetrical and asymmetrical external axial LICK OBSERVATOBY, SARTA CRUZE, CALIF. corners Evolution of rotating interstellar clouds. III [AIAA PAPER 78-1135] p0043 A78-41839 On the formation of multiple star systems Calculation of supersonic viscous flow over p0047 A78-49471 delta wings with sharp subsonic leading edges LIFE SYSTEMS, INC., CLEVELAND, OHIO. [lIAA PAPER 78-1137] pO003 A78-41841 Advanced solid electrolyte cell for C02 and R20 Hot-wire, laser anemometer and force balance electrolysis measurements of cross-sectional planes of [NAS-CR-152093] pOO52 N78-21235 single and interacting trailing vortices Technology advancement of the electrochemical [AIAA PAPER 78-11943 pO018 A78-41885 C02 concentrating process Numerical solution of two-dimensional turbulent [NASA-CR-152098] p0052 N78-22723 blunt body flows with an impinging shock Evaluation of a spacecraft nitrogen generator 0 0 5 2 [AIA PAPER 78-1209] p0045 A78-45144 - (NASA-CR-152097] p N78-23748
150 CORPORATE SOURCE INDEX NIELSEN ENGINEERING AND RESEARCH, INC.,
Advanced instrumentation concepts for gas discharge environmental control subsystems pOO30 A78-10405 [NASA-CE-152100] p0053 N78-28807 The ionosphere and airglow of Venus - Prospects LOCKHEED-CALIFORNIA CO., BURBANK. for Pioneer Venus Hotorcraft linear simulation model. Volume 1: pO045 A78-44773 Engineering documentation A method for localizing wing flow separation at [NASA-CR-152079-VOL-13 p0010 M78-20136 stall to alleviate spin entry tendencies Rotorcraft linear simulation model. Volume 2: [AIAA PAPER 78-1476] pOO 2 0 A78-49787 Computer implementation MILCO INTERNATIONAL, INC., HUNTINGTON BEACH, CALIF. [NASA-CE-152079-VOL-2] pOOlO N78-20137 Advanced Digital Avionics System for general Fuel conservation merits of advanced turboprop aviation transport aircraft [AIAA 77-1494] pOOlU A78-12243 [NAS-CR-1520961 pOOlO 178-21095 EONASH UNIV., CLAYTON (AUSTRALIA). LOCKHEED-GEORGIA CO.. MARIETTA. Quiet time interplanetary cosmic ray Moving ground simulation by tangential blowing anisotropies observed fro% Pioneer 10 and 11 7 [AIAA 78-814] pOOl A78-32368 pOO 3 9 A78-34567 LOCKHEED MISSILES AND SPACE CO., PALO ALTO, CALIF. Demand-type gas supply system for rocket borne thin-window proportional counters 3 pOO 1 A78-13845N LOCKHEED MISSILES AND SPACE CO., SUNNYVALE, CALIF. An investigation of the reduction of carbon NATIONAL AERONAUTICS AND SPACE ADMINISTRATION. dioxide in a silent electric discharge GODDARD INST. FOR SPACE STUDIES, NEW YORK. [NASA-CR-152146] pOO53 N78-25767 Primitive atmosphere and implications for the LONDON UNIV. OBSERVATORY (ENGLAND)- formation of channels on Xars Some Martian volcanic features as viewed from p0 0 4 4 A78-42460 the Viking orbiters NATIONAL AERONAUTICS AND SPACE ADMINISTEATION. 3 pOO O &78-11403 LYNDON B. JOHNSON SPACE CENTER, HOUSTON, TEX. LOWELL OBSERVATORY, FLAGSTAFF, AIZ. HormoAl indices of tolerance to -Gz The radii of Uranian rings alpha, beta, gamma, acceleration in female subjects delta, epsilon, eta, 4, 5, and 6 from their pOO55 A78-41162 occultations of SO 158687 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION. p0046 A78-48112 LANGLEY RESEARCH CENTER, HAMPTON, VA. LUNAR MID PLANETARY INST., HOUSTON, TEX. Multichannel electrochemical microbial detection Interpreting statistics of small lunar 4 craters unit p00 2 A78-41753 pOOl6 A78-31300 NATIONAL INST. ON AGING, BALTIMORE, MD. Spectrophotofluorometric and electron microscopic study of lipofuscin accumulation MARTIN MARIETTA AEROSPACE, DENVER, COLO. in the testis of aging mice Toroidal tank evaluation pO056 A78-48581 p0032 A78-17881 NATIONAL OCEANIC AND ATMOSPHERIC ADMINISTRATION, Fluid interaction with spinning toroidal tanks ANN ARBOR, MICH. p024 N78-20186 A comprehensive model of the Venus ionosphere Experimental investigation of contamination pOO38 A78-30071 prevention techniques to cryogenic surfaces on NATIONAL OCEANIC AND ATMOSPHERIC ADMINISTRATION, board orbiting spacecraft 2 BOULDER, COLO. [NASA-CR-1521713 pOO 9 H78-29146 Dynamic MHD modeling of the solar wind HARVEY CORP., SARATOGA, CALIF. disturbances during the August 1972 events NASA/ESA CV-990 Spacelab simulation (ASSESS 2) pOO36 A78-26079 [ENASA-CR-152122J p0029 N78-23117 On the observation of a flare-generated shock MASSACHUSETTS INST. OF TECH., CAMBRIDGE. wave at 9.7 AU by Pioneer 10 The instability of the thin vortex ring of rAD-A0537211 p00 3 8 A78-30078 constant vorticity Flight tests of a simple airborne device fot pOOD 1A78-14622 Dredicting clear air turbulence encounters A simplified Mach number scaling law for [AIAA 78-1375] pOO19 A78-46560 helicopter rotor noise Dynanic NED modeling of solar wind corotating pOOl7 A78-35371 stream interaction regions observed by Pioneer Meteorological control of lower stratospheric 10 and 11 0 0 4 9 minor species variations - An observational p A78-52522 example NAVAL CIVIL ENGINEERING LAB., SORT HUENEME, CALIF. pOO19 A78-46011 Cable strumming suppression Generalization of Huffman coding to minimize the [1A-A047996] p0022 P78-18366 probability of buffer overflow NEVADA UNIV., LAS VEGAS. [AD-A50974] pOo06 N78-22754 Numerical solution of a class of integral The effect of tip vortex structure on helicopter equations arising in two-dimensional noise due to blade/vortex interaction aerodynamics (NASA-CR-152150) pOO12 N78-25832 pOO18 A78-40949 MATHEMATICAL SCIENCES NORTHWEST, INC., BELLEVUE, NEW ENGLAND REGIONAL PRIMATE RESEARCH CENTER, WASH. SOUTHBOROUGHr MASS. Study, optimization, and design of a laser heat Fffects of exercise and excitement on mesenteric engine and renal dynamics in conscious, unrestrained [NASA-CR-1521O] pOOO9 178-19481 baboons MAX-PLANCK-INSTITUT PUER AIRONOMIE, p 0 5 3 A78-27124 KATLERUBURG-T.IWHAU (VEST GERMANY). Extent of utilization of the Frank-Starling Quiet time interplanetary cosmic ray mechanism in conscious dogs 5 anisotfopies observed from Pioneer 10 aid 11 D00 4 A78-33522 pOO39 A78-34567 NEW YORK UNIV., N. Y. KCDONEL-DOUGLAS ASTRONA TICS CO., ST. LOUIS, MO. Dynamic MED modeling of the solar wind Pioneer Jupiter orbiter probe mission 1980, disturbances during the August 1972 events probe description p0036 A78-26079 [NASA-C-137591] pO29 N78-33127 NIELSEN ENGINEERING AND RESEARCH, INC., MOUNTAIN MCDONNELL-DOUGLAS CORP., ST. LOUIS, NO. VIEW, CALIF. Conceptual design study of a Harrier V/STOL ArrheDius' law in turbulent media and an research aircraft equivalent tunnel effect 0 0 4 9 [NASA-CR-152086] pOOO9 H78-19094 p A78-52547 MICHIGAN UNIV., ANN ARBOR. High angle canard missile test in the Ames Simultaneous determination of rotational and 11-foot transonic wind tunnel translational temperatures of OH/2 Pi/ in a rIASA-CR-29931 p011 P78-25057
151 NORTHROP CORP. HAWTHORNR, CXATF. CORPORATE SOURCE INDEX
Propagation of sound through a sheared 4flow R rN&SA-CR-152196) pOOl N78-33876 NORTHROP CORP., HAWTHORNE, CALIF. R AND D ASSOCIATES, MARINA DEL REY, CAlIF. Some observations on the mechanism of aircraft A note on the diurnal averaging of aeronomical wing rock models rAIAA PAPER 78-1456] p00 2 0 A78-47907 p0O39 h78-34352 NORTHROP SERVICES, INC., HAMPTON, VA. RMRAN AERONAUTICS RESEARCH AND ENGINREEIG, IFC., ultichannel electrochemical microbial detection -PALO- ALTO, CALIF. -unit An analysis of the rotor blade stresses of the p1O16 178-31300 three stage compressor of the Ames Research NORTHWESTERN UNIV., EVANSTON, ILL. Center 11- by 11-foot transonic wind tunnel 9 Factors affecting the retirement of commercial [RASA-CR-152083] pOO0 N78-17061 transport jet aircraft RAO AND ASSOCIATES. INC.. PALO ALTO, CAMI. rIIASA-CP-1521151 pOO0 R78-21092 Use of leaning vanes in a two stage fan [NASA-CE-152134] pOOl 0 N78-21115 RASOR ASSOCIATES, INC., SUNNYVALE, CALIF. A cesium plasma TELEC device for conversion of laser radiation to electric power p0 0 4 8 A78-51067 ROCHESTER URIV., H. Y_ 0 Quantum mechanical theory of a structured OBSERVATOIRE DR PARIS-EUPON (FRANCE). atom-diatom collision system - A . C/1-Sigaa/ On the modulation of the Jovian decametric [AD-A051266] p0031 A78-16454 radiation by To. I - Acceleration of charged Quantum mechanical theory of collisional particles ionization in the presence of intense laser pO1 2 A78-41074 radiation OFFICE NATIONAL D'ETUDES ET DE RECHERCHES [AD-A052981] p0 0 3 5 A78-23576 AEBROSPATIALES, PARIS (FRANCE). A new concept in laser-assisted chemistry - The Diagrammatic evaluation of the density operator electronic-field representation for nonlinear optical calculations p0 O 3 7 A78-27743 [OVERA, TP NO. 1977-166] p0031 A78-14651 Semiclassical approach to collision-induced OHIO STATE UNIV., COLUMBUS. emission in the presence of intense laser Responses of articular and epiphyseal cartilage radiation - An aspect in the study of zones of developing avian radii to estrone cooperative chemical and optical pumping treatment and a 2-G environment p0037 A78-27744 pOO5 A78-29562 Semiclassical theory of unimolecular OPERATIONS RESEARCH, INC., SILVER SPRING, MD. dissociation induced by a laser field Phase 1: Definition of intercity transportation (AD-A056671] p0039 A78-34682 comparison fre.work. Volume 1; Summary Computational study of a molecular collision [NASA-CR-152152-VOL-1] pODOl R78-28993 process in the presence of an intense Phase I: Definition of intercity transportation radiation field - Enhanced quenching of F by comparison framework. Volume 2: Methodology Xe in the 248-nm light of the RIF laser 04 4 [NASA-CR-152152-VOL-2J p0O29 78-28994 [AD-A054078] p0 A78-42818 OWEN (F. K.), PALO ALTO, CALIF. ROCKWELL INTEREATIOXAL CORP., CCLUMBUS, OHIO. Measurements of unsteady vortex flow fields Static tests of a large scale swivel nozzle {AIAA PAPER 78-18) pOO15 A78-22554 thrust deflector Wake vortex measurements of bodies at high angle [HASA-C-152091] pOOl1 N78-22100 of attack ROCKWELL INTERNATIONAL CORP., DOWNEY, CALIF. [AIA PAPER 78-23] pOO15 A78-22555 Development of a cryogenic rotating heat pipe joint p (NASA-C8-152188] pOO3O H78-33384 ROSWELL PAEK MEMORIAL INST., BUFFALO, N. Y. PEPPERDINE UNIV., LOS ANGELES, CALIF. Computer display and manipulation of biological Who should codduct aeronautical R and D for the molecules 5 6 Federal Government? p00 A78-53400 [fAS-CR-1520211 pOO01 U78-10946 PETER BENT BRIGHAM HOSPITAL, EOSTON, MASS. Effects of exercise and excitement on mesenteric and renal dynamics in conscious, unrestrained SAN FRANCISCO UNIV., CALIF. baboons The prediction of toxic atmospheres from pOO53 A78-27124 decomposing polymers Extent of utilization of the Frank-Starling p0 0 3 3 A76-19895 mechanism in conscious dogs ALC/50/ values for some polymeric materials pOO54 A78-33522 p0 0 4 0 A78-36596 PITTSBUHGH URIV., PA. Relative toxicity of the pyrolysis products from Bar-driven spiral waves in disk galaxies some thermoplastic and thermoset polymers p0038 A78-32467 p0O 4 2 A78-41213 Further investigation of the spontaneous and Micro-fluid exchange coupling apparatus evoked activity of the primary neurons of [NASA-CASE-ARC-11114-1] pOO60 H78-33717 statoreceptors (and other receptors) of the SAN JOSE STATE UNIV., CALIF. labyrinth of the bullfrog before, during and Chemical interpretation of Viking Lander 1 life after an extended period of weightlessness, detection experiment including alternative intervals of artificial p0O0 3 A78-25560 gravity Analysis of ablation debris from natural and rNASA-CE-1545071 pOO52 N78-10684 artificial iron meteorites PLANETARY SCIENCE INST., PASADENA, CALIF. p0039 A78-34506 Some Martian volcanic features as viewed from Chemical evolution and the origin of life - the Viking orbiters Bibliography supplement 1976 p0030 A78-11403 p 0 5 7 A78-53875 PRICETON UNIV., N. J. chelate-modifie polymers for atmospheric gas A detailed study of attached and separated chromatography compression corner flowfields in high Reynolds [NASA-CASE-ARC-11154-1] p0057 N78-27275 number supersonic flow SANTA BARBARA RESEARCH CENTER, GOLETA, CALIF. [AA PAPER 78-1167) p0043 A78-41865 Continued development of doped-germanium Optimal control theory (OWEN) applied to a photoconductors for astronomical observations helicopter in the hover and approach phase at wavelengths from 30 to 120 micrometers [NASA-C8-152135] pOOIO N78-21161 [NASA-CR-152125] p 0 029 B78-22000
152 CORPORATE SOURCE INDEX WHITTAKER CORP., SAN DIEGO, CALIF.
SANTA CLARA UIV., CALIF. TECHNOLOGY DEVELOPMENT COHP., SUNNYVALE, CALIp. Interpreting statistics of small lunar craters The ILLIAC IV memory system: Current status and pOO42 A78-41753 future possibilities SCIENCE APPLICATIONS, INC., SANTA ANA, CALIF. [NASA-CR-1521773 pO060 N78-32731 Jupiter probe heatshield configuration TELECOMMUNICATIONS CENTER, STANFORD, CONN. optimization Digital filter structures having low errors and [AIAA PAPER 78-843] pOOg4 A78-37270 simple hardware implementation SCIENCE APPLICATIONS, INC., SCUAUMBURG, ILL. p0056 A78-51346 Earth reencounter probabilities for aborted TEYO UNIV. (JAPAN). space disposal of hazardous nuclear waste Thermal structure of the primitive ionosphere 3 p0035 A78-23543 pOO 8 A78-31921 t SIGMA RESEARCH, INC., RICHLAND, WASH. Arrhenius law in turbulent media and an Study of a high performance evaporative heat equivalent tunnel'effect transfer surface pO049 A78-52547 rNASA-CR-152008] p0028 R78-10411 TRW DEFENSE AND SPACE SYSTEMS GROUP, REDONDO BEACH, CALIF. SRI INTERNATIONAL CORP., MENLO PARK, CALIF. Survey of adaptive image coding techniques Fire detector response in aircraft applications p0031 A78-15267 9 pOOf A78-53674 Extended development of variable conductance Study to design and develop remote manipulator heat pipes systems [NASA-CR-152183) pOO 2 9 N78-33379 0 5 2 [NASA-CR-152092] p0 B78-16620 TRW, INC., ERDOWDO BEACH, CALIF. Low energy ionizing collisions between H2 and CO STANFORD UNIV., CALIF. beam molecules and CO, U2, NO, CH4, and C02 Shock-tube studies of atomic silicon emission in target molecules the spectral range 180 to 300 nm pOO 3 9 A78-34137 [AIAA PAPER 78-234] p0034 A78-22602 The co-adsorption of copper and oxygen on a tungsten 100 plane-typ surface pOO 3 7 A78-29489 Chemisorption Pa mica of CO on particles supported on U p0040 A78-36040 Digital filter structures having low errors and UNIVERSITY COLL. OF SWAVSEA (WALES). simple hardware implementation 6 Experimental temperature distribution and heat - pOO5 A78-51346 load characteristics of rotating heat pipes Multi-calculation rate simulations pO0 4 6 A78-48835 [NASA-CR-155335) pO009 N78-13765 UNIVERSITY OF SOUTHERN CALIFORNIA, LOS ANGELES. Assessing the future of air freight Europa - Ultraviolet emissions and the (NASA-CR-152161] pOO0S N78-14016 possibility of atomic oxygen and hydrogen clouds Infrastructure dynamics: A selected bibliography 2 p0048 A78-52482 [NASA-CR-152162] pOO1 N78-25824 UNIVERSITY OF THE PACIFIC, STOCKTON, CALIF. Reaction cured glass and glass coatings 0 0 5 0 C02 laser-driven Stirling engine [NASA-CASE-ARC-11051-1] p N78-32260 p021A78-49804 Fibrous refractory composite insulation (NASA-CASE-ARC-11169-1] pOO50 179-24062 STATE UNIV. OF NEW YORK, ALBANY. Zodiacal light as an indicator of interplanetary VETERANS ADMINISTRATION HOSPITAL, TACOMA, WASH. dust 1 Inhibition of bone formation during space flight ,pOO I2 178-38228 pODS6 A78-51225 STOCKHOLM OBSERVATORY (SWEDEN). VIRGINIA UNIV., CHARLOTTESVILLE. Airborne photometric observations between 1.25 Bar-driven spiral waves in disk galaxies and 3.25 microns of late-type stars pO0 3 8 A78-32467 p0036 A78-25295 Physiologic regulation of body energy storage SYSTEMS CONTROL, INC., PALO ALTO, CALIF. pOO55 A78-42817 New frequency domain methods for system VOUGHT CORP., DALLAS, TE. identification Computational wing optimization and wind tunnel pOBIS A78-23883 test of semi-span model 3 SYSTEMS TECHNOLOGY, INC-, HAWTHORNE, CALIF. (AIA PAPER 78-102] pOO A78-22575 Advanced Digital Avionics System for general Estimating maximum instantaneous distortion from aviation inlet total pressure rms measurements [AIAA 77-1494] pOOl A78-12243 [AIAA PAPER 78-970] pOO19 A78-43525 Development of automatic and manual flight director landing systems for the XV-15 tilt rotor aircraft in helicopter-mode [NASA-CR-152140] - pOO11 N78-22071 WASHINGTON STATE UNIV., PULLMAN. SYSTEMS TECHNOLOGY, INC., MOUNTAIN VIEW, CAlIF. Chemisorption of CO on Pd particles supported on The determination of some requirements for a mica helicopter flight research simulation facility pO4O A78-36040 [NASA-CR-152066] p0063 178-10117 WASHINGTON UNIV., SEATTLE. Simulation and analysis of wind shear hazard Inhibition of, bone formation during space flight [NASA-CR-157470) p0053 M78-29699 p0056 A78-51225 Computed responses of several aircraft to Executive summaryr Benefit-cost evaluation of atmospheric turbulence and discrete wind shears an intra-regional air service in the Bay Area (NASA-CR-152185] pOO53 U78-32106 and a technology assessment of transportation system investments [NASA-CH-152154-1] p0013 178-28988 TAtechnology assessment of transportation system TALLADEGA CO L-_ ALA. investments Synthesis of multifunction triaryltrifluoroethanes [NASA-CR-152154-2] pOO13 N78-28989 [NASA-CASE-ARC-11097-1] pOO49 178-22154 WESTINGHOUSE ELECTRIC CORP., PITTSBURGH, PA. Synthesis of multifunction triaryltrifluoroethanes 4 9 Thermodynamic processes induced by coherent [NASA-CASE-ARC-11097-2] pOO M78-22155 radiation TECHRISCHE UNIVIRSTTAET. CLAUSTRAE-ELLERFELD p0034 A78-21624 (WEST GERMARNY). WHITTAKER CORP., SAN DIEGO, CALIF. The co-adsorption of copper and oxygen on a Polymeric foams from cross-linkable tungsten 100 plane-type surface poly-n-arylenebenzimidazoles 0 0 3 7 p A78-29489 [NASA-CASE-ARC-11008-1] pO05O 178-31232
153 CONTRACT NUMBER INDEX
Typical Contract Number Index Listing WAs2-8652 VAS2-9359 p0052 N78-16620 p0060 N78-32731 1AS2-8664 HAS2-9363 4 NAS2-6553 p003 A78-22606 p0041 A78-37270 pOO32 A78-18732 p0047 A78-49231 VAS2-9374 NAS2-8666 p0010 P78-20136 2 p005 N78-22723 p0010 N78-20137 NAS2-8680 N1S2-9392 CON11CTPAE ~ cS~ONp0010 N7-21115 pOOh11 78-22071 NUMOEN NUMOER NUMBER 1N$2-8684 NAS2-93990 0 0 5 p0035 A78-23083 p N78-20917 0 03 8 p A78-31108 pOO10 N78-20918 Listings in this index are arranged alphanumerically by contract number Under NAS2-8687 1AS2-9421 6 each contract number the accession numbers denoting documents that have p0056 A78-48671 p00 3 N78-10117 been produced as a result of research done under that contract are arranged in NAS2-8699 NAs2-9456 ascending order with the 1AA accession numbers appearing first Preceding the 2 2 7 p002 9 N78-21223 p0028 178-19050 accession number is the page number in the abstract section in which the cita. UAS -8 8 p0028 F78-19051 tion may be found pO060 N78-32731 p0023 V78-19782 N112-8732 NAS2-9457 00 2 8 AF-AOS-76-2881 HAS2-6553 p0052 178-23748 p H78-19052 p0036 A78-26079 p0032 A78-18732 NAS2-8734 p0 02 3 N78-19783 AF-AFOSR-76-2954B p0036 A78-26081 p0020 A78-47907 N1S2-9a77 p0032 A78-18274 pOO2 A78-41074 1AS2-8738 p0045 A78-44773 AF-AFOSR-76-2954E p0045 A78-44775 p0020 A78-49255 NAS2-9506 p0045 A78-45127 p005 A78-45188 NAS2-8745 pOO11 78-22074 DA PROJ- 117-62723-A-42701 0 0 0 7 AS32-6558 p0017 A78-32368 AS2-9514 p N78-28278 p0048 A78-52482 NAS2-8790 p0 02 9 178-23117 DA PROJ. 1T1-61101-A-91A NAS2-6624 3 0 0 2 2 pOO1 N78-28083 1AS2-9535 p N78-18274 p0056 A78-48671 NAS2-8797 0 0 p0049 A78-52547 DA-01-021-ANC-113592 8AS2-6634 p 3 0 A78-10405 N1$2-9551 0 0 3 9 0 0 54 0 0 3 2 0 5 3 p A78-34137 p A78-29562 p A78-17837 p O N78-25767 DAAG29-C-027 AS2-6690 1AS2-8799 NAS2-9590 p0017 A78-35371 p0017 A78-32368 pOO15 A78-23883 p0010 N78-19869 DAAG29-78-G-O010 1AS2-6723 WA$2-8808 NAS2-9599 p0004 N78-18882 .p0031A78-13845 p0031 A78-13752 p0029 N78-22000 DAHC04-75-C-0095 NAS2-6901 p0037 A78-29472 WAS2-9640 p0031 A78-14651 pOO19 A78-43525 1AS2-8832 pOO09 178-17062 F04701-75-C-0076 NAS2-6914 0 0 60 p0012 N78-25359 N1S2-9663 p0035 A78-23083 p N78-33784 1AS2-8844 pO0O8 N78-32045 F33615-77-C-3144 NAS2-7091 pOO14 A78-10455 N$2-9668 p0020 A78-49255 p0013 N78-33113 N1$2-8862 p0 0 0 9 178-19481 F44620-74-C-0073 pOO13 178-33117 pOOl 2 N78-27105 FA$2-9726 p0031 A78-16454 p0014,N78-33118 N1$2-8870 p 0 0 3 0 N78-33384 p0035 A78-23576 1AS2-7187 p0060 N78-32731 1AS2-9748 p0037 A78-27743 p0010 N78-21161 1AS2-8878 0 03 7 p0009 178-19094 p A78-27744 NAS2-7251 9 0 03 9 8 pO0 A78-43525 N1$2-9750 p 178-34682 p00 A78-52504 1AS2-8889 pOO13 178-27128 0 05 3 p0044 A78-42818 1AS2-7489 p N78-29699 VAS2-9814 F4620-75-C-0080 0 03 2 0 0 4 3 p A78-17881 p0053 N78-32106 p0001 N78-29996 p A78-41865 p0024 178-20186 N1$2-8931 1AS2-9815 F44620-76-C-01000 0 3 7 AS2-7729 pOO14 A78-17395 p0001 N78-28993 p A78-28926 p0021 A78-52628 1AS2-9050 p00 2 9 878-28994 F9620-78-C-0005 p0021 A78-52630 pOOl3 178-30070 NAS2-9816 p00350 0 3 9 A78-23576 p0012 N78-27087 NAS2-9104 p0029 U78-29146 p 178-34682 1A2-7738 pOO17 A78-31306 HA$2-9834 4 4 0 06 4 p00 A78-42818 p 178-33085 11$2-9109 p00 2 9 178-33379 ISO PROJ. 1233 N1$2-7758 p0048 A78-51067 1AS7-100 p0012 N78-26153 p0035 A78-23450 1AS2-9112 pOOLS A78-52522 NAS ORDER A-3994-B 1AS2-7806 0 0 09 0 0 5 6 p N78-17061 NCAR-675-414 p A78-51886 pOO14 A78-14063 NA$2-9120 p 0 0 3 9 A78-34506 2 8 NASA ORDER A-35046-B 1AS2-7850 p00 178-1041 NCA2-OR-340-706 p0021 A78-51860 0 064 0 0 2 6 p 0 0 64 A78-22570 1AS2-9130 p 178-26795 NASA ORDER R-05-030-001 p 178-19155 p0038 A78-30071 NCA2-OR-745-602 0 0 4 5 p0037 A78-29489 NAS2-7862 p A78-44773 p 0 0 2 5 178-22055 NSA ORDER RA-18698-B p0052 N78-21235 NAS2-9155 NCA2-OR450-602 0 0 5 6 p A78-51225 1AS2-7963 pOO17 A78-32368 p 0 0 3 7 A78-29489 NAS-2660 p0042 A78-38228 NA$2-9168 NCA2-OR745-614 p0031 A78-13845 NAS2-8143 pOO15 A78-22554 p0 05 6 A78-51346 AS2-4924 pOO11w78-21445 pOO15 A78-22555 NCA2-O745-711 p0039 378-34137 11$2-8300 0 0 4 0 0 0 4 1 1AS2-9176 p A78-36040 NAS2-5603 p A78-37275 pOO11N78-22100 NC2-OY050-701 0 04 6 p0042 A78-41074 p A78-46557 NAS2-9185 p0 0 3 1 A78-14655 00 3 NAS2-6006 p0022 N78-10148 p 4 A78-21624 NCA2-0A675-707 3 9 p00 A78-34506 p0023 178-19029 NAS2-9211 p 0 0 5 7 A78-53875 NA$2-6064 NAS2-8377 pOO11V78-25057 1C2-OROSO-606 p0031 A78-15204 p0029 178-33127 N1$2-9233 p0028 N78-32947 0 0 4 0 AS2-6265 1AS2-8382 p A78-35622 RC2-0R660-703 0 0 4 7 p0032 A78-18173 p0016 A78-26495 NAS2-9251 p A78-49471 AS2-6551 NAS2-8394 p0053 N78-28807 NCS2-OR840-701 00 4 0 p00360 0 37 178-26080 p0031 A78-15267 1AS2-9272 p A78-36040 p A78-29684 N$2-8583 p0038 A78-31921 1GL-05-002-229 00 4 1 0 04 9 p A78-37354 p A78-53674 N$2-9311 A78-41887 4 pOOlS NA12-6552 11$2-8612 pOO1 A78-12243 NGL-05-020-014 p0039 A78-34567 p0010 N78-21095 NAS2-9357 p0056 A78-51346 pOOll N78-33876
154 CONTRACT NUMBER INDEX
RCL-14-001-006 p0045 A78-45127 NSr-7295 505-09-42-02 p0036 378-26080 NSG-2114 p0048 178-52504 pC052 N78-28979 SG-8040 - 505-10-11 p0037 A78-29684 p0043 A78-41865 2 C NGL-33-010-086 15G-2119 p004 A78-38228 p 006 N78-26133 p0035 A78-23164 p0054 A78-32673 HS-09-051-001 505-10-21 p0 0 05 178-20917 NGR-03-003-001 pOO!SL378-37130 p0042 A78-41753 0 0 E0014-76-C-0182 p0 5 178-21159 p0046 178-48112 NSG-2121 3 2 0 0 6 4 NGE-05-003-451 p0056 A78-51346 pO A78-18274 p U78-33085 1 N00014-75-C-0246 505-10-23 p003 A78-16180 1SG-2125 9 p0038 h78-30691 p005 N78-19901 p0005 N78-20113 HGR-05-007-0043 p00 1 A72-13752 N5G-2127 H00014-75-C-0601 505-10-31 0 0 5 6 poO1 0 178-21115 p0037 A78-29472 pOO12 178-27094 p A78-51346 0 0 0 8 NGR-05-007-289 NSG-2136 000014-75-C-0955 p 178-32044 505-15-31 pOO54 A78-34503 p0053 A78-27124 p0059 N78-24364 0 0 2 6 WG0-05-009-081 pOO5 A78-33522 100014-75-C-1183 p B78-26795 0 0 0 6 506-15-21 p0039 A78-34567 NSG-2140 p 178-22754 0 6 8 U00014-76-C-0182 p 02 H78-29149 NGE-05-020-409 pOO1 A78-40949 0 0 45 p0001 N78-26152 1SG-2142 p A78-45127 506-16-11 HG60-12-001-053 p0012 178-25832 100014-76-C-0420 pO024 N78-21215 p0056 A78-48671 N50-2145 pOO15 A78-23883 506-16-31 NGR-16-001-031 p0011 N78-25078 PHS-BL-15416 p0030 N78-33384 p 0 0 5 3 A78-27124 506-16-41-02 p0031 A78-15204 S5G-2149 0 5 4 0 0 2 7 NGR-16-002-038 pOO0O N78-21092 pO 178-33522 p N78-29436 506-25-21-02-00 p0043 A78-41841 1SG-2151 Pns-1L-17459 00 2 4 p0045 A78-45144 p0031 378-14651 p0054 A78-33522 p N78-21193 p0031 A78-14655 PHS-BL-17665 506-26-01-00-21 NGR-23-005-015 0 0 3 7 2 p0038 378-30071 p 378-28926 pOO54 378-33522 p002 N78-16326 0 0 4 5 506-26-08-00-21 p A78-44773 p0038 A78-30647 SBSA-DE-1148 0 0 2 5 NGR-33-010-082 NSG-2152 p0036 A78-25295 p 178-26101 0 0 3 0 SRI PROJ. 4055 506-26-11 p 378-10587 p0017 A78-32330 0 0 5 2 00 26 NOR-33-010-186 pOO12 N78-26153 p N78-16620 p 178-27364 510-56-01 p0030 A78-10587 N5G-2159 W-7405-ENG-48 0 0 2 9 N0-38-003-036 pOO01 N78-10946 p0038 A78-30691 p N78-21223 N5G-2164 YF52556091 513-53-06 pO04 N78-18882 3 3 0 0 2 2 0 0 0 6 NGR-47-005-213 p00 A78-19895 p 178-18366 p N78-23100 192-55-69 515-51-11-01 p0055 A78-42817 5SG-2170 0 0 5 1 0 0 5 1 H1-DE-02600 pOO13 178-28988 p 178-26740 p 178-25071 0 0 56 195-21-04 p0052 N78-32075 p A78-51225 p0013 N78-28989 0 0 2 8 NIH-GH-10093 FSG-2171 p 178-34014 515-52-10 pO0 0 8 178-33043 p0031 178-15204 pOO16 A78-26599 195-21-04-022 pOO17 A78-37742 pOO R 178-34021 744-01-01 NIH-1-R01-GM-23651-01 0 0 2 0 0 0 0 7 p0055 A78-48578 p A78-48991 198-30-02 p N78-27043 10H-5409 15-2174 p0027 N78-30774 760-17-01 0 03 0 p 00 0 4 N78-10019 pO054 A78-29562 p A78-10587 199-01-02 0 0 0 6 NSF AST-72-05124-004 p0033 A78-20223 p0051 178-27736 p 178-22025 8 p0035 A78-23164 199-17-02 761-72-02 p003 A78-32467 0 04 6 0 0 5 1 0 0 06 NSF AST-76-14832 p A78-48112 p 178-26973 p 178-26151 199-21-02-07-00 778-11-02 p0046 A78-48112 NSG-2183 0 05 9 0 02 6 1SF AST--6-17590 p0053 178-30808 p N78-23706 p 178-28173 0 0 4 7 p A78-49471 1SG-2196 352-02-03-02 790-40-06-01 1SF AT-72-01282 p0019 A78-46011 p0025 N78-25017 pD051 178-21019 0 03 2 352-03-01-02 791-40-11 p A78-18732 NS-2197 2 8 p00 2 A78-41074 p0052 N78-10684 pOD 178-32947 p0005 N78-21094 NSF ATM-75-21049 NSG-2198 352-03-03 791-40-41 0 03 8 0 0 3 1 pOO1 0 N78-21092 p 378-30071 p A78-16454 p0028 178-32856 0 0 2 5 0 0 35 366-18-50-00-00 p 178-24000 1SF AT5-76-82739 p k78-23576 0 0 5 9 p0037 A78-27743 p H78-30862 992-21-01 p0O5 A78-45188 0 0 3 7 0 0 6 0 1SF CE-75-06775-101 p A78-27744 p 178-32731 pOO01 178-26152 0 3 1 383-21-03-02 p0063 178-29044 pO A78-16454 p0039 178-34682 2 7 p0035 A78-23576 p0044 A78-42818 p00 N78-32029 992-21-01-90-010 0 6 2 p0037 178-27743 US-2203 384-50-60-01 p 178-18043 0 0 3 7 0 0 9 2 992-22-08 p 378-27744 pO 178-14016 p002 U78-13492 0 0 8 p 0 03 9 A78-34682 pOO12 N78-25824 385-36-01 pO N78-29068 p002 7 178-31030 992-23-10-90-01 p004 A78-42818 1SG-2225 0 0 3 505-01-11 pO N78-27042 NSF ENG-72-03860-A01 p0055 A78-42817 0 0 2 3 p0031 178-14651 NSG-2250 p N78-19778 178-13765 505-01-21 NSF E0-72-03960-301 pO009 0 0 24 p0037 A78-28926 NSG-2253 p 178-21490 1SF ENG-76-07811 p0025 178-22055 505-02-21-08-000 0 05 p0014 A78-14063 NSG-2283 p N78-20176 1SF NG-76-84532 pOOS A78-42460 505-06-11 p0025 178-26106 p0038 A78-30647 NSG-2293 0 0 26 pOO5 9 178-23706 p 178-26391 NSF E1-7414978 0 0 2 6 p0031 178-14622 NSG-2319 p 178-29067 pOO18 A78-41887 505-06-11-05 NSF EPS-75-06670 2 6 p 0 0 3 0 178-10587 N5G-5163 p00 N78-26796 p0044 A78-42460 505-06-11-05-00 N5-2010 0 0 2 5 N5-7093 p N78-24860 pO01 A78-46011 2 NS-2039 p004 A78-38228 505-06-11-06-00-21 pG03 3 A78-19895 FSG-7126 p0027 N78-29451 0 0 4 0 A78-36596 pOO30 A78-10587 505-06-21 p 0 03 3 0 0 8 NSG-2071 p A78-20223 pO 178-32045 p0 0 3 5 A78-23164 505-06-51-03-00 p0037 378-29489 7 1SG-2082 NSG-7151 pOO0 178-28053 2 7 pOO 178-32029 pOO55 A78-48578 505-08-210 0 2 4 NSG-2085 NSG-7243 p 178-21214 0 03 0 505-09-41 p0034 A78-22602 p 178-10587 0 0 0 7 N5-2095 ESG-7262 p N78-26741 0 0 5 6 505-09-42 p0017 178-35371 p A78-48719 0 0 0 1SG-7276 p 7 178-27113 1S5-2112 0 0 4 8 0 0 0 8 p0032 A78-10274 p 378-52504 p 178-31739
155 REPORT/ACCESSION NUMBER INDEX
Typical Report/Accession Number Index Listing
DOCUMENT MICOFICI8 ...... p00 78 SYMBOL SYMBOL -5------00617213* Fb I A-7524- .te------*...... PO02 N78 41 T-7537------p0026 178-29149*# e-7549------p0020 0 5 2 N78-34021*1 A-7597- .------p N78-32075*4
NSA--78452------p0005 V78-20113* A-7562- ...... p00520 0 2 7 H78-28979*# A-7579------p H78-31030*1 A-7584-- -...... p0028 U78-32856*# A-7608------.-...... pO0027 78-32029*# 1-7634------POODS H78-32044*1 REPRTPAG NSACCESINA-7639------P0008 U78-32045*1
-AS 77-240---...... p0040 A78-36717* -.7 77-258 ...... pOO1 A78-36722*
Listings in is index are arranged alphanumerically by report number The page AD-A046442 ...... pOO31 E78-14033 # number indicates the Page in the abstract section in which the citation is located AD-A057 ...... --...... p0022 N78-18274 The accessio number denotes the number by which the citation is identified An AD-A047996------p0022 N78-19366 1 asterisk 1 indicates that the item is a NASA report A pound sign (#) indicates AD-A049157------p0059 N178-19901 f that the ...... alable on microfiche. hD-A050974---....------...... p00060 0 3 1 78-22754 t AD-A05126------...... p A78-16454* 0 0 53 A-A-52435p ...... p 78-29699*1 D-A526177-...... pOO59 N78-24364 A-5137 ...... pOO63 B78-33289* AD-A052981-8.6 ...... p0035 A78-23576* A-6613 ...... p0024 N78-21215* AD-A053592 --...... - p0007 178-28278 # 7 A78-30078* A-6865 ...... p002 178-29436*1 AD-A053721------p00384 0 02 4 1078 ...... p00 4 178-42818 A-7024 ...... p 2 78-21193* AD- pOO 78-17000* A7-.56165.------p0037 A78-28926* A-7096 ------0 0 0 6 A-7121 ...... p N78-23100* AD-A56671------p0039 A78-34682 B78-20113* A-7134 ...... p00050 0 2 8 A-7149-.- - -...... p 78-32947*4 AIGL-TR-78-0097------pO038 78-30078* A-7169 ...... *...... p0022 B78-16326*# 0 00 6 A78-16454*4 A-7214 ...... p 78-22025*# AFOSR-78-0294T9 ...... p0010 0 4 4 A-7217 ...... pOO0O 178-20176*1 APOSR-78-0806TR ...... p A78-42818* 00 3 7 A-7221 ...... p 24 P78-17999*# IFOSR-78-0896TR- ...... pO A78-28926* A-7232 ...... p0062 178-19058* AFSER-78-1042TR- ...... p0039 A78-34682* 00 6 A-7246 ...... pO N78-26151*1 0 0 0 8 A-7262 ------p 78-33043*1 lIAA PAPER 78-10- ...... pO033 78-20630*# A-7279 ...... p0 02 2 178-13492*# AIAA PAPER 78-13- ...... pOO33 A78-20632*1 AIA PAPER 78-15 ...... p0021 A78-52628* A-7288 ...... p00250 02 3 178-2860*4 A-7291 ...... p 78-19778*# AIAA PAPER 78-18- ...... pO15 A78-22554*# p0062 178-18043*9 11A PIPER 78-23- ...... p015 A78-22555*1# A-7301-T-1...... 0 00 7 A-7308 ...... p H78-28053* # AiA PAPER 78-94 ...... p0064 A78-22570*1 A-7323 ...... p0025 178-25017*4 1IAA PAPER 78-99 ...... pOO1 A78-2627i 2 A-7328 ...... pOO 3 V78-19056*# AIAA PAPER 78-102 ...... p0034 A78-22575*1 A-7334 ...... - p0024 178-21214*4 AIA1 PAPER 78-105 ...... p0015 A78-20686*1 A-7340 ...... p0051 178-19444*1 RIAA PAPER 78-107 ...... pOOl A78-20687* A-7343 ...... p0007 N78-27113*# AIA PAPER 78-109 ...... pOO5 178-22578*4 3 A-7346 ...... pOO0 N78-27012*# 1AA PAPER 78-138 ...... p0034 178-22583*# 0 0 0 1 A-7347 ...... p N78-26152*# A1AA PAPER 78-161 ...... p0034 A78-22591*4 A-7355 ...... p0 0 0 5 178-20917*1 AI1 PAPER 78-186 ...... POOR A78-20730*# 0 00 5 A-7364 ...... p N78-21094*# A1AA PAPER 78-192 ...... pOOO 178-22591t*1 78-21159*t AI1 PAPER 78-199 ...... pO033 A78-20741.9 A-7367------pO005 0 0 3 4 ...... p 78-22595*1 A-7372 ...... p0059 178-30862*1 111A PIPED 78-201 0 0 2 1 A-7373 ------P0 0 5 1 178-25071*1 lIAA PAPER 78-229 ...... p A78-52630*# 3 4 A-7380 ...... p0024 B78-21407*# I1 PAPER 78-234 ...... pO0 A78-22602*1 A-7390 ...... p 0 0 0 8 N78-31739*# AIA PAPER 78-252- ...... p0034 78-22606*# 00 7 3 A-7393 ...... pO 78-26741* AIAA PAPER 78-257 ...... p00 A78-20776*# 0 0 2 6 0 3 A-7394 ...... p N78-29067*# 1IA PAPER 78-260- ...... p0 5 A78-22608*1 1-7395 ------P 0 0 2 5 H78-26106*4 AAA PAPER 78-337 ...... pOOl6 0 0 2 7 178-29295*# A-7399 ...... o...... p 178-30774*1 AIA PAPER 78-843- ...... p041 A78-37270*# 1-7410------...... p0025 1178-211000*4 1111 PIPED 78-866------pOO41 A78-37273*# 0 0 5 1 A-7417------p U78-27736*4 AIAA PAPER 78-869------p0040 178-35997*1 A1AA PAPER 78-916- ...... p0041 78-37275*1 A-7418 ...... -...... p00240 N78-21490*1 A-7423------P 059 1118-22706*4 lIAA PIPED 78-959------pO. E0 l 1 78-43521*1 2 A-7426------pOO 6 178-27364*4 A111 PIPED 78-970------pOOlS A78-43525*1 A-7430------p0063 N78-29044*4 1111 PAPER 78-1112------p0045 178-45126*4 2 A-7434------pOO 6 N78-26391*l 1111 PIPED 78-1113------p0O43 178-41826*1 1-7464------P0OO8 N78-29068*4 A111 PAPER 78-1114------p0045 178-45127*1 A-7471------p0051 178-26973*4 A3:AA PIPED 78-1135------p0043 A78-41839*4 0 0 4 3 A-74741------p0O26 178-26795*4 AIAA PAPER 78-1137------p A78-41841*4 0 0 4 3 A-7480------p0006 N78-26133*t 1111 PAPER 78-1160------p A78-41859** 4 A-7488------p0007 N78-27043*4 AI11 PIPED 78-1165------pOO 3 I78-41863** A-7491 ...... p 0 0 2 6 178-26796*4 AIlA PAPER 78-1167 ...... p0 0 4 3 A78-41865*4 1-7503 ...... p0027 N78-29451*l AIAA PAPER 78-1168 ...... p0 0 4 4 A78-41866*#
156 REPORT/ACCESSION NUMBER IBDRI
AIAA PAPER 78-1182 ...... p0O 4 4 A78-41875*1 NASA-CASE-ARC-11097-1 ...... P0049 878-221541* AIAA PAPER 78-1194 Pl...... p0018 A78-41885*I ASA-CASE-ADC-11097-2 ...... p0049 N78-22155*1 AIAA PAPER 78-1195 ...... p0018 A78-41886-1 NASA-CASE-ARC-11100-1 ...... p0058 N78-31736* AIAA PAPER 78-1196 ...... p0018 A78-41887** VASA-CASE-ARC-11107-1 ...... p0049 V78-22156*1 0 AIAK PAPER 78-1209- ...... -...... p 00 4 5 A78-45144*t NASA-CASE-ARC-11110-1 ...... p005 178-32434*1 AIRA PAPER 78-1211 ...... p 0 04 5 A78-45139*# NASA-CASE-ARC-11114-1 ...... p0060 U78-337171* AIAA PAPER 78-1223 ...... p0019 A78-C5148*4 NASA-CASE-ARC-11154-1 ...... -- p0057 N78-27275*1 AIMA PAPER 78-1456 ...... p0020 A78-47907*l. NASA-CASE-ARC-11169-1 ...... p0050 N78-32189* AIA PAPER78-1468 ...... p0020 A78-47916*I 1ASA-CSE-ARC-11174-1 ...... p0050 H78-28178*4 AIAA PAPER 78-1476------P0020 A78-419787*4 AIAA PAPER 78-1482 ...... p 0 0 20 A78-47927*# NASA-CP-2032 ...... p0023 178-197780* AIAA PAPER 78-1487 ...... -...... p0064 A78-47930*0 NASA-CP-2044 ...... p0001 N78-261521# 2 AIAA PAPER 78-1511 ...... p0O O A78-47946*t AIAA PAPER 78-1515 ...... p0021 A78-09790*# NASA-CR-2993 ...... p0011 878-250571* AIAA PAPER 78-1551 ...... p0019 A78-46514*# NASA-CR-2994 ...... p0012 N78-25359*4 AIAA 77-1494 ...... pO014 A78-12243*1 NASA-CR-3015 ...... p0012 H78-27105*# AIAA 78-417 ...... p 00 4 0 A78-35601*l BASA-CR-137591 ...... p0029 U78-33127*# 0 4 0 AIM 78-420- ...... p O A78-35603*l NASA-CR-151951 ...... p0029 178-212231* AYhA 78-443- ...... p0040 A78-35622*4 1ASA-CR-151959 ...... p0064 178-330851* 6 AIAA 78-502 ...... pOO1 A78-29804*1 NASA-CR-152008 ...... p0028 178-10411*4 AIAA 78-769 ...... P0017 A78-32330*# 1ASA-CR-152021 ...... p0001 V78-109465* 7 78-798 ...... pOO1 A78-32353*0 NASA-CR-152066 ...... pOO63 178-10117*1 AIAA 7 AIAA 78-814 ...... pOO1 A78-32368*0 1ASA-CR-152072 ...... p0009 178-17062*1 AIAA 78-835 ...... P0017 A78-32386*# 1ASA-CR-152079-VO-1 ...... p001O 178-20136*1 AIAA 78-1353 ...... POO19 NASA-CR-152079-VOL-2 ...... p010 N78-20137*# 0 0 4 6 A78-46545*4 AIA 78-1370- ...... p A78-46557*# HASA-CR-152082 ...... p0010 V70-20918*# 9 AIAA 78-1375- ...... pOOl A78-46560*1 NASA-CR-152083 ...... p0009 N78-17061*# NASA-CR-152086 ...... p0 0 0 9 878-19094*1 Av-2 ...... p0052 N78-16620*1 NASA-CR-152089 ...... pool1 878-22074*1 NASA-CR-152091 ...... p0011 E78-22100*# AYRADCOM-TR-78-1S(AM)------p0OO8 78-29068*1 1ASA-CR-152092 ------0052 N78-16620*# AVRADCOM-TR-78-17(AN) ...... p 00 63 178-29044*4 NASA-CR-152093 ...... p0052 178-21235*1 2 AVRADCOM-T-78-32(AM) ...... p08 6 178-29067*9 1ASA-CR-152096 ...... p0010 878-21095*4 AVRADCOM-TR-78-33 (AM) ...... p 0 02 5 178-26106*1 ASA-CR-15209- ...... -p052 178-237481# EASA-CR-152098-- ...... 0052 878-2272311 CEL-TW-1499 ...... p00 2 2 N78-18366 4 1ASA-CR-152100 ...... p0053 N78-28807*t 1ASA-CR-15210- ...... 8p09 178-19481*4 00 09 D-180-22888-1 ...... P V78-17062*# NASA-CR-152105 ...... p0054 178-19155*1 NASA-CR-152106 ...... P0 0 2 8 178-19050*1 D6-46320 ...... pO011 N78-22074*# NASA-CR-152107 ...... p0028 U78-19051*1 D6-46373 ...... p0012 178-27087*4 NASA-CR-15210- ...... p0028 N78-1905211 VASA-CR-1S2109 ...... p0013 178-33113*1 ECON-4542-PT-2 ...... p0022 178-18274 NASA-CR-152113 ...... 0013 178-33117*# 1ASA-CR-152114 ...... p0014 178-331181* E78-21092*# ER-190-25 ...... p00520 0 5 2 878-21235*1 1ASA-CR-152115 ...... pO10 E8-251-6 ...... p 178-2374811 NASA-CR-152116 ...... p0010 N78-19869*1 ER-309-6 ...... p0053 V78-20807*# NASA-CR-152122 ...... - p0029 U78-23117*1 1AS-CR-152125 ...... p0029 878-22000*1 ESL-P-800 ...... pOO06 178-22754 # UASA-CR-152126 ...... P0012 178-27087*4 NASA-CR-152133 ...... pOO 178-21445*4 0 06 1 PAA-RD-77-105 ...... p 3 H78-14033 4 NASA-CR-152134 ...... p0010 178-21115*4 FAA-RD-78-7------p00 178-29699*1 NSA-CR-152135 ------0010 178-21161*1 NASA-CR-152140 ...... p0011 178-22071*1 88-D- ...... p 0 0 5 2 N78-28979*# NASA-CR-152141 ...... P0013 878-27128*# NASA-CR-152146 ...... p0053 178-25767*# 2 ISU-ERI-AMES-78336 ...... p0012 78-26153*# 8ASA-CR-152150 ...... p001 178-25832*4 HASA-CR-152151 ...... 0013 178-30070*# rU-FRL-313-5 ...... P0011 78-25078*1 1ASA-CR-152152-VOI-1 ...... P0001 178-289931# 1ASA-CR-152152-VOI-2 ...... p0029 M78-28994*# 0 0 0 1 LMSC--D626407 ...... -..... p0053 178-25767*1 1ASA-C-152153-2 ...... P V78-29996*# NASA-CR-152154-1 ...... p0013 878-28988*1 IR-28200-VOL-1 ...... P001 878-20136*1 NASA-CR-18215q-2 ...... p0013 R78-28989*t LR-28200-VOL-2 ...... pOOl0 B78-20137-# NASA-CE-152161 ...... -p009 V78-14016*; 0 L8-28283 ...... POO1 178-21095*4 NASA-CR-152162 ...... p0012 N78-25824*# 1ASA-CR-152164 ...... p0013 178-28083*0 0 0 5 2 2 tSI-ER-258-11 ...... p 178-22723*4 NASA-CR-152166 ...... pOO1 178-27094*# NASA-CR-152171 ...... p0029 H78-291461* 0 0 6 0 CR-78-578 ...... p0 02 9 178-29146*1 BASA-CR-152177 ...... P V78-32731*# NASA-C-152183 ...... p0029 B78-33379*0 MDC-J7471 ...... p0029 378-21223*t NASA-CR-152185 ...... p0053 N78-32106*# 0 0 3 0 DC-37789 ...... pOO1 178-19869*# NASA-C-152188 ...... p 978-33384*# 4 NASA-CR-152196 ...... pOO1 878-33876*1 MTT-78-2 ...... p0012 178-25832*1 HASA-CR-154507 ...... p0052 H78-10684*t NASA-CR-155335 ...... pOO09 178-13765*1 0 0 0 9 N51NW-78-1082-1 ...... p 178-19481*# 8ASA-CR-157210 ...... P0011 878-25078*1 NASA-CR-157237 ...... pOO12 178-26153*1 NAS-CASE-ARC-10917-1 ...... p 0 05 7 178-27733* NASA-CR-157397 ...... p0053 N78-30808*1 0 0 5 3 NAS-CASE-ARC-10981-1 ...... p0060 N78-27425* 1ASA-CR-157470 ...... p E78-29699*# NASA-CASE-ARC-10991-1 ...... 0 0 5 7 V78-14104* p 0 5 1 NASA-CASE-ARC-11008-1 ...... pOOSO H78-31232* HASA-RP-1021 ...... pO 178-21019*1 NASA-CASE-ARC-11031-1 ...... p0057 178-22720*4 NASA-RP-1026 ...... pOO27 N78-30774*# NASA-CASE-ARC-11036-1 ...... p0060 878-32395* 0 0 2 7 NAS-CSE-ARC-11039-1 ...... 1 0 05 8 H78-32854* NASA-SP-427 ...... P 178-31508*# IIASA-CASE-ARC-11040-2 ...... 878-27184*# p0050 6 3 NASA-CASE-ARC-11043-1 ...... p0049 978-27180* BASA-TM--62299------p00 N78-33289*# NASA-CASE-ARC-11051-1 ...... p0050 178-32260* NSA-TM-X-62360 ...... p0004 178-10019*1 NASA-CASE-ARC-11057-1 ...... p057 U78-31233* NASA-CASE-ARC-11058-1 ...... p0 0 5 8 H78-31735* 1ASA-TH-73193 ...... p0027 B78-29436*t 1ASA-CESE-ARC-11058-2 ...... p00 57 N78-18763* NASA-T-73273 ...... p0028 178-32947*1
167 EPORT/ACCESSIO NUBBER INDEX
8 4 3 - 6 NASA-Tf7 8 ...... p000 N78-22025*4 STI-TR-1063-3 ...... p0053 N78-29699*1 NASA-TM-7 8 4 4 6 ...... p00 6 2 E78-19058*; 4 4 0 0 0 8 2 NASA -Tr78 9 ...... p N78-33043*4 SU-Ipm-5 ...... pO1 N78-25824*# NASA-Tf- 7 8 4 5 2 ...... F78-20113*4 8 pOO05 NASA--Tm-7 455 ...... p0022 F78-13492* TR-17 ...... p0059 N78-24364 # 5 0 059 NASA-TM- 7 8 456 ...... p 0 0 2 178-24860*1 TR-39 ...... p N78-19901 I NASA-TM-78459 ...... p0 0 6 2 F78-18043*4 TR-1092-1 ...... p0011N78-22071*# 4 6 NASA-TN-78 - ...... p0007 N78-28053*4 TR-1097-1 ...... --...... p0063 N78L -f *# 4 6 7 5 1 0 1 7 NASA--IT78 ...... p002 178250174* 2 NASA-T- 7 8 4 6 8 ...... p00 2 4 B78-21214*# TRW-31183-6001-RU-00 ...... p00 9 M78-33379*# 0 0 5 1 1ASA-TM-78470 ...... p N78-19444*4 NASA-T-78 4 71 ...... p0 0 2 3 N78-19056*# UCB-ITS-RR-77--6 ...... p0012 N78-27094*1 0 0 2 5 NSA-TI-78472 ...... p U78-24000*; 3 5 N78-27733* NASA-Tm-7847 ...... p000 N78-20917*# US-PATBNT-APPL-SN-672223 ...... p005700 5 0 NASA-TH-78474 ...... p0 0 0 5 F78-21094*# US-PATENT-APPL-SN-708951 ...... p B78-31232* N1SA-Tf-784 7 5 ...... pOO05 F78-21159*# US-PATBNT-APPL-SN-736910 ...... p0050 H78-32260* 0 0 6 0 VASA-T-78476 ...... p0051 E78-25071*# US-PATENT- PP-SN-738218 ...... p U78-27425* 4 0 06 1ASA-T2-78477 ...... p002 178-21407*1 US-PAT3NT-APPL-S1-740457 ...... p 0 N78-32395* 7 5 NASA-TM-78478 ...... pOO0 N78-26741*4 US-PATET-APPL-SH-744574 ...... p00 7 N78-14104* NASA-TH-78479 ------p0026 178-29067*9 US-PATBN-APPr-SN-750655------p058 1178-32854* 0 0 2 5 NASA-TI-78480 ...... ------p N78-26106*# US-PATENT-APPL-SH-753964 ...... p0049 B78-27180* WASA-Tm-78483 ...... --p00 24 N78-21215*# US-PATEVT-APPL-SN-753965 ...... p058 N78-31735* 00 57 NASA-Tm-78484 ...... p0051 N78-27736*4 US-PATENT-APL-SN-753965 ...... p N78-18763* NASA-TH-78485 ...... p0024 V78-21490*4 US-PATENT-APPI-SW-780569 ...... p058 N78-31736* NASA-T-78486 ...... p0059 N78-23706*4 US-PATBNTAPL-SN-807762 ...... p0057 H78-31233* 00 57 NASA-TH-78488 ...... p0026 B78-27364*# US-PATENT-APPL-SN-883094 ...... p M78-18763* 00 4 9 NASAT-78489 ...... p0063 V78-29044*# US-PATBNT-APPL-SN-883961 ...... p W78-221564# ...... p0026 178-26391*4 US-PATE2T-APPI-SN-891872 ...... 78-22154*# NSA-Tm-78490 p00490 04 9 NASA-TN-78491 ...... p0 0 5 1 N78-26740*# US-PA 2T-AEPL-SN-891875 ...... p 178-22155*1 0 0 0 8 0 0 5 7 NSA-Tm-78492...... p N78-29068*4 uS-PAT1T-APPL-S1-897828 ...... p 1178-22720*# 4 NASA-TH-78 93 ...... p0003 N78-27042*# uS-PATT-APL-SN-920878 ...... - p0050 N78-27184*# NASA-TH-78494 ...... p0 0 5 1 N78-26973** US-PATENT-APPL-SH-921626 ...... p0057 178-27275*# NASA-T-78495 ...... p 0 0 2 6 N78-26795*# JS-PATENT-APPL-SN-929086 ...... pOC50 178-28178*4 0 0 0 6 p0050 N78-32189* NASA-Tm-78497 ...... p 178-26133*4 US-PATENT-APPL-S1-940688 ...... 0 0 5 0 NASA-Tm-78498 ...... p 0 0 0 7 N78-27043*# US-PATENT-APPL-SN-945040 ...... p N78-32434*1 0 06 0 WASA-TM-78499 ...... p0 0 2 6 N78-26796*# US-PATENT-APL-S1-951422 ...... p E78-33717*4 NASA-TM-78500 ...... p0025 178-26101*4 00 5 8 NASA-Tf-78501 ...... p0 0 2 7 N78-29451** US-PATflNT-CASS-2-2.1A ...... p B78-31735* NASA-TH-78504 ...... p0026 N78-28173*# - US-PATENT-CASS-2-2.A ...... p0058 N78-31736* NASA-TM-78507 ...... p0028 N78-34014*4 US-PATENT-CASS-2-2.A- ...... p0057 N78-18763* NASA-Tm-78509 ...... p0026 R78-29149*1 US-PATENT-CASS-33-366 ...... p0060 N78-32395* NASA-Tm-78510 ...... p0028 178-34021*4 US-PATENT-CLASS-65-30R ...... p0050 178-32260* NASA-Tm-78511 ...... p0052 N78-32075*1 US-PATENT-CIASS-65-60D ...... p0050 178-32260* 0 05 0 NASA-TM-78512 ...... p0052 178-28979*4 US-PATgNT-CASS-106-48 ...... p N78-32260* NASA-TN-78515 ...... p 0 0 2 7 U78-31030*# US-PATE1TCIASS-106-54 ...... p0050 178-32260* WASA--T-78516 ...... p 0 0 2 8 H78-32856*# US-PATBENCIASS-119-29 ...... p0057 178-27733* NASA-TM-78524 ...... p0027 H78-32029*4 US-PZTETCIASS-204-180G ...... p0057 N78-14104* NASA-Tm-78530 ...... p0008 N78-32044*# US-PATN1T-CLASS-204-299R ...... p0057 N78-14104* NASA-T-78532 ...... p0008 H78-32045*# US-PATENT-CIASS-248-178 ...... p0060 178-27425* WASA-TM-79383 ...... P000 178-18882*4 US-PATENT-CLASS-248-186 ...... p0060 H78-27425* 2 NASA-Tm-79748 ...... p00 7 H78-30149*4 US-PATENT-CASS-260-2.5 ...... p0050 U78-31232* 4 US-PATNU-CLASS-260-33.6EP ...... pOO0 0 4 9 N78-27180* NASA-TP-1100 ...... p0062 N78-17000*4 US-PATENTCLASS-260-33.6PQ ...... p 178-27180* 0 0 2 2 HASA-TP-1139 ...... p H78-16326*# US-PATENTCIASS-260-33.SEP ...... p0049 R78-27180* NASA-TP-1153 ...... - .p0004 N78-17999*# US-PATERT-CASS-260-33.8UA ...... p00494 178-27180* NASA-TP-1177 ...... p 0 0 24 H78-21193*4 US-PATE1T-CLASS-260-37EP ...... p00 9 178-27180* WASA-TP-1179 ...... p0005 E78-20176*# ...... N78-27180* 0 0 0 6 0S-PATE1T-CISS-260-42.43 p0049 NASA-TP-1237 ...... p 178-23100*4 US-PATENT-CASS-260-45.71t ...... p0049 N78-27180* 4 NASA-TP-1254 ...... p0006 N78-26151*4 US-PATNT-CLASS-260-45.9R ...... p00 9 978-27180* 0 0 0 8 NASA-TP-1255 ...... p H78-31739*# US-PATENT-CASS-260-4575- ...... p00490 0 4 9 N78-27180* WASA-TP-1267 ...... p0007 178-27113*4 US-PATENT-CLASS-260-45.85N ;...... p H78-27180* 1286 ...... p0059 N78-30862*# US-PATENT-CIASS-260-47CP ...... p0OS0 N78-31232* NASA-TP- 0 0 5 0 US-PATEUT-CISS-260-63N ...... p 178-31232* 0 0 0 7 NATICK/TR-78/011 ...... p 178-28278 4 US-PATEBT-CASS-260-78.41 ...... p0050 178-31232* US-PATEBT-CASS-285-235 ...... p0058 N78-31735* NEAR-TR-134- ...... p0011 N78-25057*4 tS-PATENT-CLASS-285-235 ...... p0057 N78-18763* NEAR-TR-171 ...... P0014 N78-33876*4 US-PATENT-CLASS-350-165 ...... p0057 N78-31233* US-PATENT-CLASS-350-175G ...... p0057 N78-31233* 0 0 5 8 1R78H-10 ...... 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159 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TM-81175 4. Title and, Subtitle 5. Report Date AMES RESEARCH CENTER PUBLICATIONS: A CONTINUING BIBLIOGRAPHY 6.Performing Organization Code
7. Author(s) -8. -Perfbming Organization Report No. A-8079 10 Work Unit No. 9. Performing Organization Name and Address 992-23-10-90-03 Ames Research Center, NASA 11. Contract or Grant No. Moffett Field, Calif. 94035 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Memorandum
National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D.C. 20546 15. Supplementary Notes
16 Abstract
This bibliography lists formal NASA publications, journal articles, books, Chapters of books, patents and contractor reports issued by Ames Research Center which were indexed by Scientific and Technical Aerospace Abstracts, Limited Scientific and Technical Aerospace Abstracts, and International Aerospace Abstracts in 1978. Citations are arranged by direc torate, type of publication and NASA accession numbers. Subject, Personal Author, Corporate Source, Contract Number, and Report/Accession Number Indexes are provided.
17. Key Words (Suggested by Author(s)) 18 Distribution Statement Bibliographies, NASA programs, Unlimited Research projects, Aeronautics, Astronautics, Fluid dynamics, Human factors engineering, Life Sciences STAR Category -' 99
19 Security Classif. (of this report) 20 Security Classif. (of this page) 21. No.'of Pages 22. Price' Unclassified Unclassified 165 $8.00
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