Abstract
The two dimensional unsteady structure including the interaction between a normal shock wave and turbulent boundary layer in a transonic diffuser is quantitatively and qualitatively visualized using high-speed Mach-Zehnder interferometry. Experiments have been performed at an operating pressure ratio of 1.4 where the freestream Mach number just ahead of the normal shock wave is around 1.1. The normal shock oscillatory characteristics in the diffuser are also investigated by a high-speed schlieren method. Streamwise static pressures on the diffuser side wall have been measured and the time-mean wall pressure distribution in the diffuser is compared with that from the RANS equation with the k- SST turbulent model. The dominant frequency of the normal shock oscillation obtained from the Mach-Zehnder interferometry is quantitatively identical to that from the high-speed schlieren mothod.
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