Two-dimensional shock wave boundary layer interactions

A wind tunnel test was conducted in the Air Force Flight Dynamic Laboratory's High Temperature Facility to investigate the two-dimensional shock wave boundary layer interaction produced by a remote shock generator-receiver configuration. The program was conducted at a free stream Mach number of 10 and over a unit Reynolds number range of 150,000 to 600,000 per foot. The receiver plate pitch angle was 0 deg except for a portion of the program when the receiver plate was pitched to 6 deg compression to produce a local Mach number of 8 and a corresponding unit Reynolds number range of 500,000 to 2.2 million per foot. The generator plate deflection angle range was from 0 deg to 8 deg.