An experimental study of a three-dimensional shock wave/turbulent boundary-layer interaction at a hypersonic Mach number

摘要: Experimental data for a series of three-dimensional shock-wave/turbulent-boundary-layer interaction flows at Mach 8.2 are presented. The test bodies, composed sharp fins fastened to flat-plate surface, were designed generate with varying degrees pressure gradient, boundary-layer separation, and turning angle. include surface-pressure, heat-transfer, skin-friction distributions, as well limited mean flowfield surveys both in the undisturbed regimes. obtained purpose validating computational models these hypersonic interactions.