Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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nal design did not perform as well as expected in model-scale, wind-tunnel testing. The object of this project was to determine why and develop a reliable tool to be used for an improved design. Predictions were done for the inlet operating in the presence of a ground plane (runway) with a crosswind at zero forward speed, a critical design point for inlet operation. The Wind Navier- Stokes code was used with structured Chimera grids having about five million grid points and divided into 30 to 40 zones. Fine grid calculations used 30 processors. The computations were made using the NAS SGI Origin computing cluster. Analysis predictions agreed with data, predicting the onset of separation and the details of the flow field for attached and separated flows, including the effects of the ground vortex. The analysis proved capable of predicting the influence of the wind-tunnel walls on the measured flow field. Part of the effort was directed at determining grid topology and density requirements and identifying the best procedure for running the code. A process has been developed that can provide flow prediction results in several days for a new design. Predictions correspond well with experiment, but additional test cases are needed to increase confidence in the procedure. Author Computational Fluid Dynamics; Inlet Flow; Navier-Stokes Equation; Parallel Processing (Computers); Structured Grids (Mathematics); Engine Inlets 20000064614 NASA Ames Research Center, Moffett Field, CA USA Fast Particle Methods for Multiscale Phenomena Simulations Koumoutsakos, P., NASA Ames Research Center, USA; Wray, A., NASA Ames Research Center, USA; Shariff, K., NASA Ames Research Center, USA; Pohorille, Andrew, NASA Ames Research Center, USA; Welcome to the NASA High Performance Computing and Communications Computational Aerosciences (CAS) Workshop 2000; February 2000; In English; See also 20000064579; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document We are developing particle methods oriented at improving computational modeling capabilities of multiscale physical phenomena in : (i) high Reynolds number unsteady vortical flows, (ii) particle laden and interfacial flows, (iii)molecular dynamics studies of nanoscale droplets and studies of the structure, functions, and evolution of the earliest living cell. The unifying computational approach involves particle methods implemented in parallel computer architectures. The inherent adaptivity, robustness and efficiency of particle methods makes them a multidisciplinary computational tool capable of bridging the gap of micro-scale and continuum flow simulations. Using efficient tree data structures, multipole expansion algorithms, and improved particle-grid interpolation, particle methods allow for simulations using millions of computational elements, making possible the resolution of a wide range of length and time scales of these important physical phenomena.The current challenges in these simulations are in : [i] the proper formulation of particle methods in the molecular and continuous level for the discretization of the governing equations [ii] the resolution of the wide range of time and length scales governing the phenomena under investigation. [iii] the minimization of numerical artifacts that may interfere with the physics of the systems under consideration. [iv] the parallelization of processes such as tree traversal and grid-particle interpolations We are conducting simulations using vortex methods, molecular dynamics and smooth particle hydrodynamics, exploiting their unifying concepts such as : the solution of the N-body problem in parallel computers, highly accurate particle-particle and grid-particle interpolations, parallel FFT’s and the formulation of processes such as diffusion in the context of particle methods. This approach enables us to transcend among seemingly unrelated areas of research. Author Computer Techniques; Data Structures; Parallel Computers; Computerized Simulation; Particles 20000064696 Sverdrup Technology, Inc., Huntsville, AL USA Interfacing the Generalized Fluid System Simulation Program with the SINDA/G Thermal Program Schallhorn, Paul, Sverdrup Technology, Inc., USA; Palmiter, Christopher, Sverdrup Technology, Inc., USA; Farmer, Jeffery, NASA Marshall Space Flight Center, USA; Lycans, Randall, Sverdrup Technology, Inc., USA; Tiller, Bruce, NASA Marshall Space Flight Center, USA; [2000]; 13p; In English; 34th; 34th Thermophysics Conference, 19-22 Jun. 2000, Denver, CO, USA Contract(s)/Grant(s): NAS8-40386; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche A general purpose, one dimensional fluid flow code has been interfaced with the thermal analysis program SINDA/G. The flow code, GFSSP, is capable of analyzing steady state and transient flow in a complex network. The flow code is capable of modeling several physical phenomena including compressibility effects, phase changes, body forces (such as gravity and centrifugal) and mixture thermodynamics for multiple species. The addition of GFSSP to SINDA/G provides a significant improvement in convective heat transfer modeling for SINDA/G. The interface development was conducted in two phases. This paper describes the first (which allows for steady and quasi-steady - unsteady solid, steady fluid - conjugate heat transfer modeling). The second (full transient conjugate heat transfer modeling) phase of the interface development will be addressed in a later paper. Phase 1 development has been benchmarked to an analytical solution with excellent agreement. Additional test cases for each develop- 82
ment phase demonstrate desired features of the interface. The results of the benchmark case, three additional test cases and a practical application are presented herein. Author One Dimensional Flow; Computer Programs; Thermal Analysis; Computerized Simulation; Fluid Dynamics; Steady State; Unsteady State; Quasi-Steady States 20000064720 NASA Ames Research Center, Moffett Field, CA USA Compressibility Effects on the Passive Scalar Flux Within Homogeneous Turbulence Blaisdell, G. A., Purdue Univ., USA; Mansour, N. N., NASA Ames Research Center, USA; Reynolds, W. C., Stanford Univ., USA; Physics of Fluids; October 1994; ISSN 1070-6631; Volume 6, No. 10, pp. 3498-3500; In English Contract(s)/Grant(s): F49620-86-K-0022; Copyright; Avail: Issuing Activity Compressibility effects on turbulent transport of a passive scalar are studied within homogeneous turbulence using a kinematic decomposition of the velocity field into solenoidal and dilatational parts. It is found that the dilatational velocity does not produce a passive scalar flux, and that all of the passive scalar flux is due to the solenoidal velocity. Author Compressibility Effects; Compressible Flow; Homogeneous Turbulence; Isotropic Turbulence; Turbulent Flow; Shear Flow 20000067660 NASA Marshall Space Flight Center, Huntsville, AL USA Observations on Rotating Cavitation and Cavitation Surge from the Development of the Fastrac Engine Turbopump Zoladz, Thomas F., NASA Marshall Space Flight Center, USA; [2000]; 9p; In English; 36th; Joint Propulsion, 17-19 Jul. 2000, Huntsville, AL, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA Report No.(s): AIAA Paper 2000-3403; Copyright Waived; Avail: CASI; A02, Hardcopy; A01, Microfiche Observations regarding rotating cavitation and cavitation surge experienced during the development of the Fastrac engine turbopump are discussed. Detailed observations acquired from the analysis of both water flow and liquid oxygen test data are offered in this paper. Scaling and general comparison of rotating cavitation between water flow and liquid oxygen testing are discussed. Complex data features linking the localized rotating cavitation mechanism of the inducer to system surge components are described in detail. Finally a description of a lumped-parameter hydraulic system model developed to better understand observed data is given. Author Cavitation Flow; Rotation; Fabrication; Turbine Pumps 20000067663 NASA Glenn Research Center, Cleveland, OH USA Experimental Investigation of Boundary Layer Behavior in a Simulated Low Pressure Turbine Shyne, Rickey J., NASA Glenn Research Center, USA; Sohn, Ki-Hyeon, Toledo Univ., USA; DeWitt, Kenneth J., Toledo Univ., USA; [1999]; 8p; In English; No Copyright; Avail: CASI; A02, Hardcopy; A01, Microfiche A detailed investigation of the flow physics occurring on the suction side of a simulated Low Pressure Turbine (LPT) blade was performed. A contoured upper wall was designed to simulate the y pressure distribution of an actual LPT blade onto a flat plate. The experiments were carried out at Reynolds numbers of 100,000 and 250,000 with three levels of freestream turbulence. The main emphasis in this paper is placed on flow field surveys performed at a y Reynolds number of 100,000 with levels of freestream turbulence ranging from 0.8% to 3%. Smoke-wire flow visualization data was used to confirm that the boundary layer was separated and formed a bubble. The transition process over the separated flow region is observed to be similar to a laminar free shear layer flow with the formation of a large coherent eddy structure. For each condition, the locations defining the separation bubble were determined by careful examination of pressure and mean velocity profile data. Transition onset location and length determined from intermittency profiles decrease as freestream turbulence levels increase. Additionally, the length and height of the laminar separation bubbles were observed to be inversely proportional to the levels of freestream turbulence. Author Low Pressure; Turbine Blades; Computerized Simulation; Flow Distribution; Turbulent Boundary Layer 83
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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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surface measurement techniques used
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with emphasis on the search for lin
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Page 125 and 126: 20000064527 Analytical Imaging and
Page 127 and 128: 20000064533 Austin State Univ., Dep
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Page 133 and 134: in Yellowstone National Park. We ar
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Page 145 and 146: 20000064912 New Energy and Industri
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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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20000064070 NASA Ames Research Cent
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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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