Mechanical Engineering, Isfahan University of Technology
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.
Pishevar, A. R. (1998). Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow. International Journal of Engineering, 11(4), 197-206.
MLA
A. R. Pishevar. "Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow". International Journal of Engineering, 11, 4, 1998, 197-206.
HARVARD
Pishevar, A. R. (1998). 'Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow', International Journal of Engineering, 11(4), pp. 197-206.
VANCOUVER
Pishevar, A. R. Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow. International Journal of Engineering, 1998; 11(4): 197-206.