An experimental study of a three-dimensional shock wave/turbulent boundary-layer interaction at a hypersonic Mach numberExperimental data for a series of three-dimensional shock-wave/turbulent-boundary-layer interaction flows at Mach 8.2 are presented. The test bodies, composed of sharp fins fastened to a flat-plate test surface, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface-pressure, heat-transfer, and skin-friction distributions, as well as limited mean flowfield surveys both in the undisturbed and interaction regimes. The data were obtained for the purpose of validating computational models of these hypersonic interactions.
Document ID
19910057956
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kussoy, M. I. (Eloret Corp. Palo Alto, CA, United States)
Horstman, K. C. (Eloret Institute Palo Alto, CA, United States)
Kim, K.-S. (NASA Ames Research Center Moffett Field, CA, United States)