Two-dimensional supersonic flow over concave surfaces

Planar, constant curvature wedge configurations are experimentally and numerically studied in order to determine conditions relating to singly curved shock waves and the effects of varying surface curvatures on shock geometry and downstream flow. Post-shock flow compression is seen to be an important factor in determining conditions on the reflecting surface. A symmetrical configuration of constant radii, concave wedges, similar to that of an internal compression intake, was experimentally investigated. Three models were tested with surface curvature radii of 160, 120, and 80 mm, each at Mach numbers of 3.0, 3.2, and 3.4 and at two separation distances. In addition, the applicability of planar curved shock theory (CST) is briefly examined for the conditions immediately behind the shock and the following streamline geometry calculated using a Taylor series expansion. Streamline shapes, as predicted by CFD and CST, agree exactly on the downstream surface of the shock waves. Agreement deteriorates with downstream distance as well as with increasing surface curvature.