What is it about?
Experimental turbulent shock-wave/boundary-layer interactions are studied on a conical compression corner configuration at Mach 6.25. Oscillatory behavior along the shock and propagation of boundary-layer structures are investigated using edge-detection and image correlation techniques.
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Why is it important?
This work offers a new take at studying unsteady SWBLI behavior. These experiments were completed in a recently characterized facility which allows for high Reynold's numbers over relatively long (~100 ms) steady test times.
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This page is a summary of: Shock Perturbations in Attached Turbulent Shock-Wave/Boundary-Layer Interactions at Mach 6, January 2025, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2025-1341.
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