Vol. 11, No. 4 (November 1998) 197-206   

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A. Pishevar
Department of Mechanical Engineering
Isfehan University of Technology
Isfehan, Iran

Abstract    Numerical results are presented for the shock-boundary layer interactions in a hypersonic flow over a sharp leading edge compression corner. In this study, a second- order Godunov type scheme based on solving a Generalized Riemann Problem (GRP) at each cell interface is used to solve thin shear layer approximation of laminar Navier-Stokes (N-S) equations. The calculated flow-field shows general agreement with the experimental data. The heat transfer coefficient and the extent of the separation are predicted with an adequate accuracy. Furthermore, the effects of the employed slope-limiter on the present computations are addressed.


Keywords    TVD Scheme, Slope-Limiter, Generalised Riemann Problem, Compression Corner Flow



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