Abstract
The interaction of a weak normal shock wave with a turbulent boundary layer developing along the wall surface of a supersonic diffuser was investigated experimentally, where the flow Mach number was 1.14∼1.53 and the Reynolds number based upon boundary layer thickness was 1.35∼2×104. Detailed streamwise surface pressures were measured, and a number of data sets obtained by wall pressure transducers were statistically analyzed. The power spectral density function, the intermittency and the higher-order moments of the surface pressure fluctuations were taken. The objective of the present experiment was to investigate the behaviors of the oscillations caused by the normal shock wave/turbulent boundary layer interaction (STBI). The results show that the intermittent feature of the unsteady shock motion is similar to those in external flows and that the maximum standard deviations correspond to points where the intermittency factor approaches 0.5 and are significantly influenced by flow separation. Also the present study indicates that far downstream from the STBI region the amplitude of pressure fluctuations is nearly independent of the flow Mach number.
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