Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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methods are investigated for modeling the SGS standard deviation: Smagorinsky, gradient and scale-similarity. When properly calibrated, the gradient and scale-similarity methods give results in excellent agreement with the DNS. Author Models; Scale (Ratio); Computational Grids; Direct Numerical Simulation; Evaporation; Interpolation; Lagrangian Function; Mixing Layers (Fluids) 20000062308 NASA Glenn Research Center, Cleveland, OH USA Numerical Simulation of Non-Rotating and Rotating Coolant Channel Flow Fields, Part 1 Rigby, David L., NASA Glenn Research Center, USA; [2000]; 26p; In English; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche Future generations of ultra high bypass-ratio jet engines will require far higher pressure ratios and operating temperatures than those of current engines. For the foreseeable future, engine materials will not be able to withstand the high temperatures without some form of cooling. In particular the turbine blades, which are under high thermal as well as mechanical loads, must be cooled. Cooling of turbine blades is achieved by bleeding air from the compressor stage of the engine through complicated internal passages in the turbine blades (internal cooling, including jet-impingement cooling) and by bleeding small amounts of air into the boundary layer of the external flow through small discrete holes on the surface of the blade (film cooling and transpiration cooling). The cooling must be done using a minimum amount of air or any increases in efficiency gained through higher operating temperature will be lost due to added load on the compressor stage. Turbine cooling schemes have traditionally been based on extensive empirical data bases, quasi-one-dimensional computational fluid dynamics (CFD) analysis, and trial and error. With improved capabilities of CFD, these traditional methods can be augmented by full three-dimensional simulations of the coolant flow to predict in detail the heat transfer and metal temperatures. Several aspects of turbine coolant flows make such application of CFD difficult, thus a highly effective CFD methodology must be used. First, high resolution of the flow field is required to attain the needed accuracy for heat transfer predictions, making highly efficient flow solvers essential for such computations. Second, the geometries of the flow passages are complicated but must be modeled accurately in order to capture all important details of the flow. This makes grid generation and grid quality important issues. Finally, since coolant flows are turbulent and separated the effects of turbulence must be modeled with a low Reynolds number turbulence model to accurately predict details of heat transfer. Derived from text Flow Distribution; Rotation; Coolants; Cooling; Jet Engines; Three Dimensional Models 20000062852 Technische Univ., Faculty of Mathematical Sciences, Twente, Netherlands Accurate Boundary-Element Method for Stokes Flow in Partially Covered Cavities Driesen, C. H.; Kuerten, J. G. M.; May 1998; 44p; In English Report No.(s): PB2000-104912; MEMO-1442; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche The two-dimensional flow of a viscous fluid over an etched hole is computed with a boundary-element method. The etch-hole geometry contains sharp corners at which the solution of the traction boundary-integral equation is singular. Therefore, only the regular part of the solution is computed with the boundary-element method, using a singularity-subtraction method, and the singular part of the solution is added. However, there are regions in which these regular and singular parts are of almost equal magnitude, but different in sign. to avoid the subtraction and addition of large quantities where quantities of smaller order are computed a domain-decomposition technique is introduced. The authors show that the accuracy indeed increases by the described techniques. After extrapolation the results for a rectangular geometry agree very well with results obtained earlier with a semi-analytical method. NTIS Boundary Element Method; Boundary Integral Method; Two Dimensional Flow; Steady Flow; Stokes Flow; Viscous Fluids 20000062853 NASA Glenn Research Center, Cleveland, OH USA A Compact Dual-Crystal Modulated Birefringence-Measurement System for Microgravity Applications Mackey, Jeffrey R., NASA Glenn Research Center, USA; Das, Kamal K., NASA Glenn Research Center, USA; Anna, Shelley L., Massachusetts Inst. of Tech., USA; McKinley, Gareth H., Massachusetts Inst. of Tech., USA; Measurement Science and Technology; 1999; ISSN 0957-0233; Volume 10, pp. 946-955; In English; Sponsored in part by Fannie and John Hertz Foundation Contract(s)/Grant(s): NCC3-610; RTOP 101-33-00; Copyright; Avail: Issuing Activity A compact modulated birefringence-measurement system has been developed for use in microgravity fluid physics applications with non-Newtonian fluids such as polymer solutions. This instrument uses a dual-crystal transverse electro-optical modulator capable of modulation frequencies in excess of 100 MHz. The two crystals are modulated 180 deg. out of phase from each 78
other, The theoretical framework governing the development of this instrument using the Mueller-Stokes polarization matrices is discussed. Several ground-based experiments are performed to compare this system with the theoretical results. Results from this transverse electro-optical modulator-based birefringence-measurement system agree well with the theory. The instrument is also very stable and robust, making it suitable for the extreme acceleration environment to be encountered in a NASA Black Brandt sounding rocket. Author Birefringence; Microgravity Applications; Modulators; Measure and Integration 20000063505 Hampton Univ., School of Engineering and Technology, VA USA Advanced Methods for Acoustic and Thrust Benefits for Aircraft Engine Nozzles Final Report, 1 Jun. 1996 - 31 Dec. 1999 Morgan, Morris H., III, Hampton Univ., USA; Gilinsky, Mikhail M., Hampton Univ., USA; March 2000; 19p; In English; Original contains color illustrations Contract(s)/Grant(s): NAG1-1835; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche The Fluid Mechanics and Acoustics Laboratory (FM&AL) was established At Hampton University in June of 1996. In addition, the FM&AL jointly conducted research with the Central AeroHydrodynamics Institute (TsAGI, Moscow) in Russia under a 2.5 year Civilian Research and Development Foundation (CRDF). The goals of the FM&AL programs are two fold: 1) to improve the working efficiency of the FM&AL team in generating new innovative ideas and in conducting research in the field of fluid dynamics and acoustics, basically for improvement of supersonic and subsonic aircraft engines, and 2) to attract promising minority students to this research and training and, in cooperation with other HU departments, to teach them basic knowledge in Aerodynamics, Gas Dynamics, and Theoretical and Experimental Methods in Aeroacoustics and Computational Fluid Dynamics (CFD). The research at the FM&AL supports reduction schemes associated with the emission of engine pollutants for commercial aircraft and concepts for reduction of observables for military aircraft. These research endeavors relate to the goals of the NASA Strategic Enterprise in Aeronautics concerning the development of environmentally acceptable aircraft. It is in this precise area, where the US aircraft industry, academia, and Government are in great need of trained professionals and which is a high priority goal of the Minority University Research and Education (MUREP) Program, that the HU FM&AL can make its most important contribution. This project already benefits NASA and HU because: First, the innovation, testing, and further development of new techniques for advanced propulsion systems are necessary for the successful attainment of the NASA Long Term Goals in Aeronautics and Space Transportation Technology (ASTT) including Global Civil Aviation, Revolutionary Technology Leaps, Access to Space, R&D Services, and the economic competitiveness of the US Aircraft Industry in the 2 1 st century. Secondly, the joint theoretical and experimental research and training by the GRC-HU Teams aids: using advanced methods and experience in Aerospace Engineering for domestic industries and training of HU students for interesting innovative work in the numerical simulation field as well as engineering and experimental research. HU students use and modify existing numerical codes for the solution of actual applied problems of the NASA Langley Research Center (LaRC) Derived from text Nozzle Efficiency; Engine Design; Aircraft Engines; Aeroacoustics; Gas Dynamics; Hydrodynamics; Thrust 20000064066 Instituto Nacional de Tecnica Aeroespacial, Torrejon de Ardoz, Spain Results of Measurements from Convective Heat Transfer Tests in a Plane Circular Cylinder Resultados de las Medidas en Ensayos de Transferencia de Calor Convectivo en un Cilindro Circular Liso Otero, M. Urdiales, Instituto Nacional de Tecnica Aeroespacial, Spain; October 1999; 28p; In Spanish Report No.(s): INTA-AT/TNO/4410/023/INTA/00; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche In this document is included the set of temperature measurements get during different wind tunnel tests, in order to achieve the heat transference coefficient. The test were made in a circular cylinder with a plane exterior surface Author Temperature Measurement; Convective Heat Transfer 20000064114 NASA Glenn Research Center, Cleveland, OH USA Investigation of Density Fluctuations in Supersonic Free Jets and Correlation with Generated Noise Panda, J., Modern Technologies Corp., USA; Seasholtz, R. G., NASA Glenn Research Center, USA; [2000]; 26p; In English; 6th; Aeroacoustics, 12-14 Jun. 2000, Lahaina, HI, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA Report No.(s): AIAA Paper 2000-2099; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche The air density fluctuations in the plumes of fully-expanded, unheated free jets were investigated experimentally using a Rayleigh scattering based technique. The point measuring technique used a continuous wave laser, fiber-optic transmission and photon counting electronics. The radial and centerline profiles of time-averaged density and root-mean-square density fluctuation pro- 79
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Scientific and Technical Aerospace
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Introduction Scientific and Technic
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Subject Divisions Table of Contents
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ground equipment and systems. For a
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Subject Categories of the Division
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48 Oceanography 139 Includes the ph
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72 Atomic and Molecular Physics 191
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Document Availability Information T
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Avail: NASA Public Document Rooms.
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NASA CASI Price Tables — Effectiv
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ALABAMA AUBURN UNIV. AT MONTGOMERY
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��
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20000061433 Pisa Univ., Dipartiment
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English; 34th; 34th Thermophysics C
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ciency of the generated derivative
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20000063509 NASA Glenn Research Cen
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05 AIRCRAFT DESIGN, TESTING AND PER
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A long tradition of aerodynamic des
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sonic and transonic cases will be p
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20000061449 British Aerospace Publi
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20000064593 NASA Langley Research C
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performance required for a proposed
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ment cost and create better product
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tion (NPSS), is focused on the inte
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Page 55 and 56: primary issues for it’s adaptatio
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Page 61 and 62: necessary for ignition modeling, or
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Page 133 and 134: in Yellowstone National Park. We ar
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distributions with engine test resu
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7.6, while the 1926 events appear t
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We investigate the compositional di
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Flight Center, USA; Moore, T. E., N
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This report presents the Applied Me
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in Goa, India, by 3 - 4 days. Wind
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51 LIFE SCIENCES (GENERAL) Includes
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20000062717 Joint Inst. for Nuclear
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20000064015 Institute for Human Fac
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during 50% (SD 4%) of the breathing
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20000064711 Massachusetts Inst. of
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The analysis of this smaller data s
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vided a functional helmet mount. Th
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61 COMPUTER PROGRAMMING AND SOFTWAR
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The goal of multi-image classificat
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20000063526 Defence Science and Tec
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85 dB amplifier design evolved by o
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20000064594 New Mexico Univ., Elect
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20000064615 NASA Ames Research Cent
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declarations with a pattern recogni
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containing point where interpolatio
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has his own responsibility, while t
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the people, documents and projects
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and experimental technology, many o
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tems. In particular this applicatio
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Over the past decade, high performa
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expensive than a single analysis. I
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20000064726 Carnegie-Mellon Univ.,
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20000064099 Teledyne Brown Engineer
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20000066597 Geophysical Observatory
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20000065633 Institute TNO of Applie
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important conclusion is that for su
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est frame of the string. The modifi
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isotopes. The method and program we
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A detailed study is undertaken, usi
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20000063497 Kaiser Electro-Optics,
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delivers 60% of the x-ray flux from
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76 SOLID-STATE PHYSICS ��
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20000064660 Abdus Salam Internation
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20000067648 NASA Marshall Space Fli
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20000064703 Institute of Atomic Ene
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The BRST approach is applied to the
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20000067671 Hampton Univ., VA USA A
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82 DOCUMENTATION AND INFORMATION SC
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ecoming almost too cumbersome to be
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physical world. These are the two p
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with WFPC2 data. Tests of HSTphot
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A brief description is given of the
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gas, show variations that have rema
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egy, called Power In that would all
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20000065631 NASA Kennedy Space Cent
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20000064089 Smithsonian Astrophysic
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A ABERRATION, 143, 198 ABRASION, 22
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COMPRESSIBLE FLOW, 83 COMPRESSION L
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FATIGUE (MATERIALS), 50, 93, 96 FAT
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LASING, 90 LATE STARS, 224 LATITUDE
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PATCH ANTENNAS, 74 PATHOLOGY, 98 PA
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SPACE PLATFORMS, 38 SPACE PROBES, 2
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WIND PROFILES, 137 WIND TUNNEL TEST
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Brown, Andy, 38 Brown, April S., 20
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Grosvenor, C. A., 70 Grosvenor, J.
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Lu, Gui-Ying, 50 Lugg, Desmond J.,
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Robertson, Tony, 39 Robinson, Jeffr
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Warner, J. D., 63 Warren, James, 16
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Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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