Abstract:
Numerical investigation of supersonic flow over two-dimensional compression corner. The laminar viscous and inviscid flow equations were discretised using finite different technique and the computer program code was developed using MATLAB. The analysis was conducted for corner angles of 5 to 20° and the flow velocity was varied from 2.5 to Mach 3.5. In the current study, we found that the magnitudes of peak pressure and recirculation region on the ramp were significantly affected by the flow velocity and corner angles. Results obtained were validated by using analytical solutions as well as from previous researchers and they are found to be in good agreement.
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