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Investigation of shock-induced boundary layer separation extended to the flat plate leading-edge

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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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Authors and Affiliations

  1. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, 410073, People’s Republic of China

    Yuan Tao, Wei-Dong Liu & Xiao-Qiang Fan

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  1. Yuan Tao
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  2. Wei-Dong Liu
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  3. Xiao-Qiang Fan
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Correspondence to Wei-Dong Liu.

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Tao, Y., Liu, WD. & Fan, XQ. Investigation of shock-induced boundary layer separation extended to the flat plate leading-edge. Acta Mech 227, 1791–1797 (2016). https://doi.org/10.1007/s00707-016-1599-0

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  • DOI: https://doi.org/10.1007/s00707-016-1599-0

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