Study of three-dimensional flow fields generated by the interaction of a skewed shock wave with a turbulent boundary layer

A detailed experimental investigation has been carried out on the three-dimensional flow fields caused by the interaction of oblique shock waves and a turbulent boundary layer. The study was performed at a free stream Mach No. of 2.95, near adiabatic wall conditions. The interaction was studied on two models having the same geometries but with different initial boundary layer thicknesses (about 0.13 and 0.55 inches). By perturbing the geometry of the experimental arrangement, it was possible to define a test region that is free of extraneous interference effects. Surface pressure measurements and oil flow patterns were obtained for both models with shock generator angles varying from 2 up to 14 deg.