Compressible turbulence measurements in a supersonic boundary layer with impinging shock wave interaction
1997, American Institute of Aeronautics and Astronautics, Inc. The turbulence intensities and Reynolds shear stresses in a Mach 2.9 turbulent flat plate with an impinging shock wave were measured using laser Doppler velocimetry techniques. The shock strength was varied by using three wedge shock generators having turning angles of 5, 7, and 10, respectively. Each flow field was studied at streamwise locations both upstream and downstream of the interaction. To facilitate examination of the streamwise development of the boundary layer downstream of the interaction, additional measurements were obtained along a line several centimeters long and running parallel to the wall. Increases in the velocity fluctuations, Reynolds shear stresses and Turbulent Kinetic Energy (TKE) aft of the interaction were noted for all cases and were observed to increase with increasing shock strength. Flow visualization via shadowgraph and Schlieren imagery provided evidence of a separation bubble for the largest wedge angle. Correspondingly, the turbulent properties aft of the separated region were noticeably different than that seen for the unseparated cases. Wall shear stress aft of the interaction was highly elevated for each shock angle.