Details of a Shock-Separated Turbulent Boundary Layer at a Compression Corner

An experimental study is described in which detailed mean-flow measurements are made in a shock waveboundary-layer interaction. The interaction is produced by a 24° compression corner mounted on the wall of the Princeton University high Reynolds number wind tunnel. The experiments are performed at Mach 2. 85 and Redo = 1. 33 million. A detailed mapping of the flowfield is presented, including separated region shape and location and velocity profiles. Results indicate a relatively straight zero-velocity line, a persistent downstream normal pressure gradient, and reverse velocities up to 16% of u^.