HYPERSONIC CROSSING SHOCK-WAVE TURBULENT-BOUNDARY-LAYER INTERACTIONS

Experimental data for two three-dimensional intersecting shock-wave/tu rbulent-boundary-layer interaction flows at Mach 8.3 are presented. Th e test bodies, composed of two sharp fins fastened to a flat plate tes t bed, were designed to generate flows with varying degrees of pressur e gradient, boundary-layer separation, and turning angle. The data inc lude 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 flowfi eld 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 h ypersonic flows.