Gary Elfstrom
Abstract
A hypersonic gun tunnel has been used to investigate turbulent shock-boundary-layer interaction at a wedge-compression corner. The results extent the Mach number range of existing data, in particular of incipient separation.
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A hypersonic gun tunnel has been used to investigate turbulent shock-boundary-layer interaction at a wedge-compression corner. The results extent the Mach number range of existing data, in particular of incipient separation.
Key concepts: Hypersonic speed, Wedge (geometry), Boundary layer, Mach number, Mechanics, Expansion tunnel, Turbulence, Flow separation