The flow structure in the hypersonic inlet and flow path of the scramjet models was investigated both experimentally and numerically. The detailed description of the shock wave facility is presented. Cold air flows with Mach number of 7 and 4.5 were captured on the high-speed video camera for both sharp and blunt wedge inlet models. The numerical simulation of the flow in the inlet models was performed using unstructured Navier-Stocks solver. The comparison the experimental data with the computed results shows that the numerical simulation allows obtaining the flow structure well. Both experimental and numerical results confirm that flows over sharp-nosed and blunt-nosed bodies may differ significantly.
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