Abstract
The solution of the windward conical-subsonic region over cones at angle of attack in steady, supersonic, inviscid flow is obtained by coordinate expansions about the plane of symmetry of the flow field, using the method of series truncation. Cases of a circular cone at large angles of attack are calculated, and good agreement with experimental results is obtained.
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More From: Zeitschrift für angewandte Mathematik und Physik ZAMP
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