Abstract
Experimental investigations and numerical simulations have been carried out to investigate the shock-induced boundary layer separation, which is extended to the flat plate leading-edge. Three typical separation structures are obtained when an incident shock interacts with an boundary layer: one contains an overall regular reflection, one contains an overall Mach reflection, and one contains a detached shock. All the three structures show comparatively stable characteristic in the experiment. Numerical results demonstrate that there possibly exist two different flow field solutions for a uniform flow condition from different initializations. It could be explained as the asymmetric shock reflection hysteresis phenomenon, analyzed from the shock polars.
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