AN ESTIMATE OF COMPRESSIBLE BOUNDARY LAYER DEVELOPMENT AROUND A CONVEX CORNER IN SUPERSONIC FLOW.
Rept. no. 6,
BROWN UNIV PROVIDENCE R I
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An analysis of the effect of a sharp convex corner on the momentum thickness of a compressible, supersonic boundary layer flow is presented. The problem is attacked by a momentum integral technique in which an approximate pressure field is used. The shape factor is approximated by a simple expression which is also of general application. The main result of the analysis is an analytic expression for the ratio of the momentum thicknesses downstream and upstream of the corner. The results are also presented graphically over appropriate ranges of the major flow parameters. Author