Experimental investigation of shock wave and boundary layer interaction near convex corners in hypersonic flow

grantor: University of TorontoThe hypersonic impulse gun tunnel at the UTIAS was used to experimentally investigate the interaction between an oblique shock wave and boundary layer near convex corners in hypersonic flow. Experiments were conducted in two phases. The first phase involved tunnel test operating conditions that presumably developed turbulent boundary layer on the model surface in Mach 7.2 flow. Schlieren photographs indicated that it was not possible to conclude that the boundary layer developed was, in fact, turbulent. The second phase of the program included preliminary investigation of shock-laminar boundary layer interaction near rounded convex conners. As a first step, experiments were repeated to validate previously documented results achieved at the current facility. Surface static pressure measurements and Schlieren photographs were taken to investigate interaction near a 5 degrees convex corner. Results obtained in this phase supported the repeatable characteristics of the facility.M.A.Sc