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Computational methods for hypersonic viscous flow over finite ellipsoid-cones at incidenceA numerical method, which is simpler than others currently in use, is proposed for determining the full viscous flow over a finite body in hypersonic stream at high altitude. It treats the shock layer surrounding the blunt foebody and the near wake behind the base simultaneously by formulating the Navier-Stokes equations in conformal and azimuthal-angle coordinates. The computational domain is confined to the body wall, outflow surface and the bow shock, which is adjusted along the coordinate normal to the wall in the course of iterations. Because of the optimal grid and a well developed alternating direction implicit factorization technique for the governing equations, reasonably accurate results can be obtained on a 30 by 36 by 6 grid with 400 time-marching iterations. Results for body shapes belonging to the ellipsoid-cone family are compared with the experimental data for the Apollo command module and the Viking aeroshell. Validation of the method based on self-consistency is also discussed.
Document ID
19850055443
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Li, C. P.
(NASA Johnson Space Center Aerosciences Branch, Houston, TX, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 85-0925
Accession Number
85A37594
Distribution Limits
Public
Copyright
Other

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