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DSMC Grid Methodologies for Computing Low-Density, Hypersonic Flows About Reusable Launch VehiclesTwo different grid methodologies are studied for application to DSMC simulations about reusable launch vehicles. One method uses an unstructured, tetrahedral grid while the other uses a structured, variable-resolution Cartesian grid. The relative merits of each method are discussed in terms of accuracy, computational efficiency, and overall ease of use. Both methods are applied to the computation of a low-density, hypersonic flow about a winged single-stage-to-orbit reusable launch vehicle concept at conditions corresponding to an altitude of 120 km. Both methods are shown to give comparable results for both surface and flowfield quantities as well as for the overall aerodynamic behavior. For the conditions simulated, the flowfield about the vehicle is very rarefied but the DSMC simulations show significant departure from free-molecular predictions for the surface friction and heat transfer as well as certain aerodynamic quantities.
Document ID
20040110893
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Wilmoth, Richard G. (NASA Langley Research Center Hampton, VA, United States)
LeBeau, Gerald J. (NASA Johnson Space Center Houston, TX, United States)
Carlson, Ann B. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1996
Subject Category
Launch Vehicles And Launch Operations
Distribution Limits
Public
Copyright
Public Use Permitted.

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