The large-scale unsteadiness that occurs in shock-wave/boundary layer interactions imposes severe aero-thermo-acoustic loads on high-speed aircraft. Much progress has been made on this problem in the last two decades: these interactions can now be tackled with large eddy simulation, at least for relatively low Reynolds numbers. Further, a large body of evidence now suggests that the physical mechanism for the unsteadiness lies in the selective amplification, within the separated flow, of large-scale disturbances originating in the incoming turbulent flow. The present paper examines the kinematics of these incoming structures in a turbulent boundary layer, and the scaling of the corresponding response of a reattaching shear layer flow. In particular, it presents an overview of the influence on recent research of experimental work carried out by Smits’ group at Princeton University in the 1990s.
Experiments in Fluids – Springer Journals
Published: Nov 3, 2015
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