SWEEPBACK THEORY FOR SHOCK WAVES AT HYPERSONIC SPEEDS,
RAND CORP SANTA MONICA CALIF
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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.