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The advent of vehicles, moving many times the velocity of sound makes it necessary to understand clearly the various phenomena occuring near the sharp leading edge of a flat plate. A few theoretical attempts to tackle this problem are made and several experiments are performed at various places. Unfortunately wide areas of disagree ment exist between the various theoretical investigations and experimental results. It is the purpose of the note to try to gather some useful information from the available literature on this subject and present some suggestions which might be useful or worth consideration in any future attempt of solving this problem. (Author).
The flow near the tip of pointed nosed bodies in hypersonic flight is considered. In particular, the region where continuum concepts are applicable, but where boundary layer theory is no longer valid, is studied using the model proposed by Oguchi for the flat plate problem. Both two-dimensional and axiallysymmetric bodies are considered. Solutions are obtained in the form of expansions valid near the nose tip. The surface pressure is found to approach a finite value as the tip is approached; numerical results for this limit value are obtained for various wall to total temperature ratios and tip semi-vertex angles. (Author).