Hypersonic flow around blunt body at angles of attack
Abstract
An analytical method for solving the hypersonic flow around a blunt body (twodimensional flatfaced 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 NavierStokes 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 maximumentropystreamline from the zero or stagnationstreamline, 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.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 October 1974
 Bibcode:
 1974STIN...7512246K
 Keywords:

 Angle Of Attack;
 Blunt Bodies;
 Hypersonic Flow;
 Flow Distribution;
 Shock Waves;
 Stagnation Point;
 Fluid Mechanics and Heat Transfer