Shock wave/turbulent boundary-layer interactions with and without surface cooling

An experimental investigation was conducted to delineate the structure of the flowfield and temperature distributions in a shock wave/turbulent boundary-layer interaction with and without surface cooling. The Mach number upstream was about 3.5, and the wave angle was 23°. The wall to stagnation temperature ratio was 0.44 with cooling and 1.1 with heating. A detailed map of the interaction flowfields deduced from numerous boundary-layer traversing stations revealed the influence of wall cooling on the flowfield, wave structure, and size of the flow separation region. With surface cooling, the size of the separation region was much smaller, and the separation and reflected shock waves merged together near the edge of the velocity boundary layer, extending into the freestream as one wave. The measured rise in pressure P2/P j across the interactions of 3.1-3.2 could be estimated using oblique shock relations in conjunction with the observation that the mass flux p Kocl/r in the expanding flow between the incident and separation shock waves in the diffuser. The increase in the measured heat-transfer coefficient h2/h1 = 2.3 and wall shear stress T2/Ti = 1-6-1.7 across the interactions were estimated reasonably well by using semiempirical relations.

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