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 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 in both the undisturbed and interaction regimes. The data were obtained for the purpose of validating computational models of these hypersonic interactions.
Three-dimensional hypersonic shock wave/turbulent boundary-layer interactions
AIAA Journal ; 31 , 1
1993-01-01
Miscellaneous
No indication
English
Three-Dimensional Hypersonic Shock Wave-Turbulent Boundary-Layer Interactions (SYN)
Online Contents | 1993
|Hypersonic crossing shock-wave/turbulent-boundary-layer interactions
Tema Archive | 1993
|Hypersonic Crossing Shock-Wave-Turbulent-Boundary-Layer Interactions
Online Contents | 1993
|