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Three-Dimensional Shock-Wave/Boundary-Layer Interaction in Supersonic Flow Past a Finite-Span Sharp Wedge

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Abstract

Shock-wave/boundary-layer interactions (SWBLI) are of great importance in supersonic transport vehicles. The shock-induced separation and its unsteadiness may lead to harmful influences on the aerodynamic performance and fatigue life of supersonic air-intakes, turbo-machine cascades and supersonic nozzles. We particularly focus on a three-dimensional SWBLI in supersonic flow past a finite-span sharp wedge. Implicit large-eddy simulation is performed to investigate the flow features in the three-dimensional SWBLI. Results show that a bow-type side-edge shock wave is generated from the leading edge of the finite-span sharp wedge. The shock impinges on the turbulent boundary layer and causes additional turbulence fluctuations in the spanwise direction. Three-dimensional features dominate the shock impingement and reflection. A large-scale separation bubble is induced by the bow-type side-edge shock wave. Properties of this separation bubble are examined and qualitatively compared with a two-dimensional SWBLI case.

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Acknowledgements

The authors acknowledge the support of National Natural Science Foundation of China (11202131, 11772194), and the supply of the super computer π in SJTU. Funding was provided by National Basic Research Program of China (973 program) (2014CB744804).

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  1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, 200-240, China

    Weipeng Li

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  1. Weipeng Li
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Li, W. Three-Dimensional Shock-Wave/Boundary-Layer Interaction in Supersonic Flow Past a Finite-Span Sharp Wedge. Int. J. Aeronaut. Space Sci. 21, 329–336 (2020). https://doi.org/10.1007/s42405-019-00220-2

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  • DOI: https://doi.org/10.1007/s42405-019-00220-2

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