Abstract
Experimental data for two three-dimensional intersecting shock-wave/turbulent-boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flowfield surveys both in the undisturbed and interaction regimes. The persistence of an extensive low-pressure region throughout the flowfield demonstrates that a sidewall compression inlet is not an efficient pressure increasing device. The data have been obtained in sufficient detail to validate existing or future computational models of these hypersonic flows.
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