Three-dimensional swept shock/turbulent boundary-layer separations with control by air injection

Experimentally determined wall pressure distributions, local surface shear stresses and their directions, and detailed turbulent boundary layer traverses in near zero heat transfer conditions, are presented through skewed shock/boundary layer interaction regions generated by a wedge standing normal to a test wall. The mainstream Mach numbers were 2 and 4, while the Reynolds number based on the undisturbed test boundary layer thickness of 0.2-in., growing along the nozzle sidewall of the NAE 5 x 5-in. blowdown wind tunnel, was approximately 200,000. Tangential air injection at a jet exit Mach number of 3 was then introduced into the 3D shock separated Mach 2 boundary layer, to control the separation. The optimum direction of blowing was found to be along a line somewhere between the deflected surface of the wedge and the line of the oblique shock wave.