A 3-D coupled CFD-DSMC solution method with application to the Mars Sample Return Orbiter

Details A 3-D coupled CFD-DSMC solution method with application to the Mars Sample Return Orbiter A 3-D coupled CFD-DSMC solution method with application to the Mars Sample Return Orbiter

Aug 2001

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001aipc..585..723g&link_type=abstract

RAREFIED GAS DYNAMICS: 22nd International Symposium. AIP Conference Proceedings, Volume 585, pp. 723-729 (2001).

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Aerodynamics, Applications Of Monte Carlo Methods, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

A method to obtain coupled CFD-DSMC, 3-D flow field solutions for highly blunt bodies at low incidence is presented and applied to one concept of the Mars Sample Return Orbiter vehicle as a demonstration of the technique. CFD is used to solve the high-density blunt forebody flow defining an inflow boundary condition for a DSMC solution of the afterbody wake flow. By combining the two techniques in flow regions where most applicable, the entire mixed flow field is modeled in an appropriate manner. .

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