The 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.
A comparison of upwind schemes for computation of three-dimensional hypersonic real-gas flows
AIAA, Atmospheric Flight Mechanics Conference ; 1992 ; Hilton Head Island, SC, United States
1992-08-01
Conference paper
No indication
English
On the Performance of Upwind Schemes and Turbulence Models in Hypersonic Flows
British Library Conference Proceedings | 2001
|FLUID DYNAMICS - Performance of Upwind Schemes and Turbulence Models in Hypersonic Flows
Online Contents | 2004
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