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.