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    Supersonic turbulent flow past a swept compression corner at Mach 3. II (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The three-dimensional Mach 3.0 shock wave-turbulent boundary layer interaction generated by a swept compression corner whose geometry is characterized by the angle of streamwise compression angle alpha and the angle of sweep lambda is presently treated by the Baldwin-Lomax (1978) algebraic turbulent eddy viscosity model. The results obtained, and those previously derived by means of Cebeci and Smith (1974) and Jones and Launder (1972) models, are compared with experimental measurements. The rate of change of the mean kinetic energy along a streamline is investigated, and evidence is obtained that the flowfield structure is rotational and inviscid.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0310
    Format: text
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