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Supersonic wind tunnel experiments have been conducted with a Mach 4 laminar boundary layer. Various angles of ramps have been investigated to assess shock boundary layer interactions at different Reynolds numbers and with different strengths. Mid-interaction transition was observed in strong high-Reynolds number configurations and analyzed further with high-speed schlieren. Density disturbances identified in the separated flow were shown to directly influence the unsteady separation shock motion, with negligible influence from upstream.
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This page is a summary of: Transitional Shock Boundary Layer Interactions on a Compression Ramp at Mach 4, AIAA Journal, December 2021, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.j059981.
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