An experimental program has been conducted to investigate the behavior of hypersonic shock wave/turbulent boundary layer interactions in the vicinity of an expansion corner. Tests were run in the Calspan 96" shock tunnel at nominal Mach 11.5 free-stream conditions for a unit Reynolds number of approximately 17 million per foot. Fully turbulent boundary layers were generated with a flat plate, and oblique shocks were generated with a planar shock generator canted at angles of 10, 12, and 15 deg relative to the free stream. Shock impingement points were varied to create impingement points upstream, in the vicinity, and downstream of an expansion corner with an angle that was similar in magnitude to the shock generator. Wall static pressure and heat transfer were measured in the region of the shock interaction to determine the effects of the expansion corner on the character of the shock wave/boundary layer interaction. Detailed data has been generated for comparison with computational codes and to enable a better understanding of hypersonic inlet design.
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