Theoretical Prediction Of Pressures In Hypersonic Flow With Special Reference To Configurations Having Attached Leading Edge Shock
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Hypersonic Flow Theories for Predicting Pressures on Blunt Two-dimensional and on Conical Shapes
An investigation has been undertaken to develop theories for predicting pressures in hypersonic flows, with special reference to low-aspect ratio, delta-winged configurations. This report is the fourth of four covering our work to date. This work is concerned primarily with: (1) A relatively simple numerical procedure for determining the pressure distribution on two-dimensional wings with blunt leading edges, (2) Further development of the thin-shock layer theory for conical flows with emphasis on uniformly valid zeroth-order solutions in the vicinity of entropy layer singularities, (3) Initial theoretical results extending Dorodnitsyn's method of integral relations to conical flows, including expression of the gas dynamic equations in divergence form for a variety of coordinate systems.