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

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.