ON THE STRUCTURE OF SUBSONIC FLOW BETWEEN AN ASYMMETRIC BODY AND A DETACHED SHOCK-WAVE

Subsonic vortex flow behind a detached shock wave (SW) that arises dur ing supersonic plane flow around an asymmetric body of finite is consi dered. For bodies with convex leading edges it is shown that the subso nic section of the SW is convex, and that there are no interal branch points in the region between the body, the SW and the isobars emerging from the sonic points of the SW. It is shown that this region is cove red by the family of isoclines emerging from the stagnation point. Thi s convexity of the subsonic section of the SW is also possible for a n on-convex body provided the values of the angles of inclination of the walls at the leading edge of the body lie outside the range of shock polar angles.