Comparison of a 3-D CFD-DSMC Solution Methodology With a Wind Tunnel Experiment

Details Comparison of a 3-D CFD-DSMC Solution Methodology With a Wind Tunnel Experiment Comparison of a 3-D CFD-DSMC Solution Methodology With a Wind Tunnel Experiment

May 2003

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003aipc..663..441g&link_type=abstract

RAREFIED GAS DYNAMICS: 23rd International Symposium. AIP Conference Proceedings, Volume 663, pp. 441-448 (2003).

Statistics

Computation

Supersonic And Hypersonic Flows, Aerodynamics

Scientific paper

A solution method for problems that contain both continuum and rarefied flow regions is presented. The methodology is applied to flow about the Mars Sample Return Orbiter (MSRO), a 3-D blunt body, which contains a region of highly compressed forebody flow, a shear layer where the flow separates from a forebody lip (i.e., where the base plane intersects the forebody), and a low density wake region about the afterbody. Because the blunt body flow contains such disparate regions, employing a single numerical technique to solve the entire flow field for a 3-D configuration is often impractical, or the technique does not apply. Direct simulation Monte Carlo (DSMC) could be employed to solve the entire flow field; however, the technique would require inordinate computational resources for continuum to near continuum regions, since, it is best suited for the rarefied wake region. Computational fluid dynamics (CFD) is appropriate for the high-density region on the forebody, but in the rarefied wake region, continuum assumptions do not apply. This problem poses a situation where the CFD-DSMC approach presented herein may be a suitable way to obtain a higher fidelity solution.

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