Numerical Simulation of Supersonic and Hypersonic Turbulent Compression Corner Flows

A relaxation turbulence eddy viscosity model is incorporated to solve the complete Navier-Stokes equations for supersonic and hypersonic flows over a two-dimensiona l compression corner. The system of equations is solved by a time-split, second-order accurate numerical scheme. Details of the relaxation process are studied. In general, using the relaxation model, the eddy viscosity value in the outer layer of the separation region is reduced substantially, and good improvement in the prediction of upstream pressure propagation is obtained for a Mach number of 2.96 and Reynolds number of 10 7, with wedge angle of 25°. However, the application of the relaxation model to hypersonic flow at Mach number 8.66 and Reynolds number of 22 x 106, with highly cooled wall, shows unfavorable effects on heat transfer and skin friction in the reattachment and recompression regions.

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