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Transport Phenomena in Thermal Engineering. Volume 2

ISBN:
1-56700-015-0 (Print)

UNSTEADINESS OF NORMAL SHOCK WAVE/BOUNDARY LAYER INTERACTION IN A SUPERSONIC DIFFUSER

Kazuyasu Matsuo
Graduate School of Engineering Sciences, Kyushu University, Kasuga, Fukuoka 816, JAPAN

Heuy-Dong Kim
Graduate School of Engineering Sciences, Kyushu University, Kasuga, Fukuoka 816, JAPAN

Jong-Woo Hong
Graduate School of Engineering Sciences, Kyushu University, Kasuga, Fukuoka 816, JAPAN

Shigetoshi Kawagoe
Kurume College of Technology, Komorino, Kurume 830, JAPAN

Abstract

In order to characterize the unsteadiness of normal shock wave/turbulent boundary layer interaction, the detailed experimental explorations were carried out in the supersonic diffusers with the half angle of divergence of 5 to 9 deg. Measurements included the time-mean and fluctuating wall pressures, the shock displacements, the surface oil-tracers, and the pitot pressures in the boundary layer. The optical observation of the interacting flow fields was made by using a spark schlieren method. The Mach number immediately up-stream of the interacting shock wave was in a range of 1.10 to 1.50. The results obtained show that the instantaneous displacements of the shock wave are consisted of large-amplitude, low-frequency and well correlated with the fluctuating wall pressures in the intermittent region of shock wave/boundary layer inter-action.