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Shock Wave Boundary Layer Interaction (SWBLI) can cause extreme aerothermodynamic loads in high speed flights and neglecting its effects can be severely destructive. In this paper, hypersonic SWBLI in a blunt fin - plate configuration in a flow with freestream Mach number of 14 is numerically simulated and the results are compared with the experimental data for validation purposes.

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This page is a summary of: Simulation of Hypersonic-Shock-Wave–Laminar-Boundary-Layer Interaction over Blunt Fin, AIAA Journal, August 2019, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.j057940.
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