Accession Number : AD0606864
Title : SWEEPBACK THEORY FOR SHOCK WAVES AT HYPERSONIC SPEEDS,
Corporate Author : RAND CORP SANTA MONICA CALIF
Personal Author(s) : Cole,J. D.
Report Date : 04 APR 1958
Pagination or Media Count : 8
Abstract : The report presents the results of hypersonic smalldeflection theory for the pressure coefficient, density, and other characteristics behind the shock wave on a sweptback wedge. The results have application to computation of the pressure on sweptback wings of wedge cross-section outside the region of influence of the tips. They can also be used to estimate the lift of a flat delta wing flying at very high speeds. In addition, the behavior of the shock waves deduced here is the first step in computing non-uniform flow fields behind the shock wave.
Descriptors : (*SHOCK WAVES, AERODYNAMIC CHARACTERISTICS), (*SWEPTBACK WINGS, GAS FLOW), HYPERSONIC FLOW, WEDGES, LIFT, DELTA WINGS, DEFLECTION, PRESSURE, DENSITY
Distribution Statement : APPROVED FOR PUBLIC RELEASE