Numerical Simulation of Hypersonic Air Intake Flow in Scramjet Propulsion Using a Mesh-Adaptive Approach

The intake of a supersonic combustion Ramjet (Scramjet) mostly consists of one or more external compression ramps followed by an internal part. Oblique shock waves generated by the ramps, the cowl and the side walls are performing the compression of the incoming flow. Multiple interesting and complex physical phenomena may occur, such as shock-boundary layer interaction, laminar-turbulent transition, compressible relaminarization, flow separation, etc.

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