Computation of Viscous Shock/Shock Hypersonic Interactions with an Implicit Flux Split Scheme
Final rept. Sep 1989-Sep 1990,
UNIVERSAL ENERGY SYSTEMS INC DAYTON OH
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The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic Mach 8, perfect gas flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leers flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leers splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.
- Fluid Mechanics