Hypersonic Flow around Blunt Body at Angles of Attack

概要

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An analytical method for solving the hypersonic flow around a blunt body (two-dimensional flat-faced body) at angles of attack is presented. The origin of the coordinate system is placed at the stagnation point and the position of the shoulder is determined as the point where the flow variables change abruptly. By doing so, the position of the stagnation point relative to that of the shoulders can be determined. The solution in the stagnation region is obtained first by solving the Navier-Stokes equations under the constant density assumption. The appropriate forms of the velocity components are used in the stagnation region. The flow field from the stagnation region to the shoulder is solved using the solution obtained in the stagnation region as the initial condition under the constant density assumption. The results are shown for the shape of the shock wave, the position of the stagnation point relative to that of the shoulders and the deviation of the maximum-entropy-stream-line from the zero- or stagnation-stream-line, for several values of the angle of attack and the Reynolds number. And the validity of the procedure used is examined by comparing the results obtained for the inviscid symmetrical problem with the already obtained ones. Finally, the procedures for extending the present method to the analysis of the flow field around the curved blunt body with shoulders at angles of attack are described.
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