NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
NASA Scientific and Technical Aerospace Reports
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20040070802 QSS Group, Inc., Clevel<strong>and</strong>, OH, USA<br />
EUPDF-II: An Eulerian Joint Scalar Monte Carlo PDF Module : User’s Manual<br />
Raju, M. S.; Liu, Nan-Suey, <strong>Technical</strong> Monitor; April 2004; 24 pp.; In English<br />
Contract(s)/Grant(s): NAS3-00145; WBS 714-20-06<br />
Report No.(s): <strong>NASA</strong>/CR-2004-213073; E-14549; No Copyright; Avail: CASI; A03, Hardcopy<br />
EUPDF-II provides the solution for the species <strong>and</strong> temperature fields based on an evolution equation for PDF<br />
(Probability Density Function) <strong>and</strong> it is developed mainly for application with sprays, combustion, parallel computing, <strong>and</strong><br />
unstructured grids. It is designed to be massively parallel <strong>and</strong> could easily be coupled with any existing gas-phase CFD <strong>and</strong><br />
spray solvers. The solver accommodates the use of an unstructured mesh with mixed elements of either triangular,<br />
quadrilateral, <strong>and</strong>/or tetrahedral type. The manual provides the user with an underst<strong>and</strong>ing of the various models involved in<br />
the PDF formulation, its code structure <strong>and</strong> solution algorithm, <strong>and</strong> various other issues related to parallelization <strong>and</strong> its<br />
coupling with other solvers. The source code of EUPDF-II will be available with National Combustion Code (NCC) as a<br />
complete package.<br />
Author<br />
Monte Carlo Method; Probability Density Functions; Computational Fluid Dynamics; Euler Equations of Motion; Computer<br />
Programs; Modules; Sprayers; Combustion<br />
20040070834 <strong>NASA</strong> Stennis Space Center, Bay Saint Louis, MS, USA<br />
Innovative, High-Pressure, Cryogenic Control Valve: Short Face-to-Face, Reduced Cost<br />
Wilkes, Karlin; Larsen, Ed; McCourt, Jackson; [2004]; 1 pp.; In English<br />
Report No.(s): <strong>NASA</strong>/NP-2002-05-00019; SSC-00159; No Copyright; Avail: CASI; A01, Hardcopy<br />
A control valve that can throttle high pressure cryogenic fluid embodies several design features that distinguish it over<br />
conventional valves designed for similar applications. Field <strong>and</strong> design engineers worked together to create a valve that would<br />
simplify installation, trim changes, <strong>and</strong> maintenance, thus reducing overall cost. The seals <strong>and</strong> plug stem packing were<br />
designed to perform optimally in cryogenic temperature ranges. Unlike conventional high-pressure cryogenic valves, the trim<br />
size can be changed independent of the body. The design feature that provides flexibility for changing the trim is a split body.<br />
The body is divided into an upper <strong>and</strong> a lower section with the seat ring s<strong>and</strong>wiched in between. In order to maintain the plug<br />
stem packing at an acceptable sealing temperature during cryogenic service, heat-exchanging fins were added to the upper<br />
body section (see figure). The body is made of stainless steel.<br />
Derived from text<br />
Control Valves; Cost Reduction; Cryogenic Temperature; High Pressure<br />
20040071073 <strong>NASA</strong> Marshall Space Flight Center, Huntsville, AL, USA<br />
Comparison of SPHC Hydrocode Results with Penetration Equations <strong>and</strong> Results of Other Codes<br />
Evans, Steven W.; Stallworth, Roderick; Stellingwerf, Robert F.; 2004; 9 pp.; In English; 45th AIAA/ASME/ASCE/AHS<br />
Structures, Structural Dynamics, <strong>and</strong> Materials Conference, 19-24 Apr. 2004, Palm Springs, CA, USA; Copyright; Avail:<br />
CASI; A02, Hardcopy<br />
The SPHC hydrodynamic code was used to simulate impacts of spherical aluminum projectiles on a single-wall aluminum<br />
plate <strong>and</strong> on a generic Whipple shield. Simulations were carried out in two <strong>and</strong> three dimensions. Projectile speeds ranged<br />
from 2 kilometers per second to 10 kilometers per second for the single-wall runs, <strong>and</strong> from 3 kilometers per second to 40<br />
kilometers per second for the Whipple shield runs. Spallation limit results of the single-wall simulations are compared with<br />
predictions from five st<strong>and</strong>ard penetration equations, <strong>and</strong> are shown to fall comfortably within the envelope of these analytical<br />
relations. Ballistic limit results of the Whipple shield simulations are compared with results from the AUTODYN-2D <strong>and</strong><br />
PAM-SHOCK-3D codes presented in a paper at the Hypervelocity Impact Symposium 2000 <strong>and</strong> the Christiansen formulation<br />
of 2003.<br />
Author<br />
Hydrodynamics; Computerized Simulation; Mathematical Models; Penetration; Computer Programs; Hypervelocity<br />
Projectiles<br />
20040071144 Civil <strong>Aerospace</strong> Medical Inst., Oklahoma City, OK, USA<br />
CFD Validation for Contaminant Transport in Aircraft Cabin Ventilation Flow Fields<br />
Garner, Robert P.; Wong, Kwai L.; Ericson, Shawn C.; Baker, A. J.; Orzechowski, Joseph A.; April 2004; 9 pp.; In English<br />
Report No.(s): DOT/FAA/AM-04/7; No Copyright; Avail: CASI; A02, Hardcopy<br />
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