A comparison of upwind schemes for computation of three-dimensional hypersonic real-gas flowsThe method of Suresh and Liou (1992) is extended, and the resulting explicit noniterative upwind finite-volume algorithm is applied to the integration of 3D parabolized Navier-Stokes equations to model 3D hypersonic real-gas flowfields. The solver is second-order accurate in the marching direction and employs flux-limiters to make the algorithm second-order accurate, with total variation diminishing in the cross-flow direction. The algorithm is used to compute hypersonic flow over a yawed cone and over the Ames All-Body Hypersonic Vehicle. The solutions obtained agree well with other computational results and with experimental data.
Document ID
19930029309
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gerbsch, R. A. (NASA Ames Research Center Moffett Field, CA, United States)
Agarwal, R. K. (McDonnell Douglas Research Labs. Saint Louis, MO, United States)