Abstract
Numerical solutions of hypersonic flows over different compression ramps are obtained. Reynolds averaged, thin layer, compressible Navier Stokes equations are solved. Finite differencing approach and LU- ADI splitting technique are used. Results are presented as surface pressure and heat transfer distributions. Streamlines are plotted along the corner to observe the separated flow zones. Present predictions are compared with the available experimental data and other computational results. For a compression corner flow, laminar solutions predicted earlier and larger separated zones than the experiment. Turbulent predictions obtained using Baldwin-Lomax turbulence model were in better agreement with the experiment.
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