Abstract
Based on Large Eddy Simulation (LES), combined with high-order WENO scheme, Ghost Fluid Method (GFM) and Adaptive Mesh Refinement (AMR) technique, the supersonic flow separation controlled by a wall-mounted micro-ramp has been simulated. The flow structure past micro-ramp was presented and discussed. Afterwards, the micro-ramp was used to control the shock/ boundary layer separation. The numerical results showed that wake structures behind the micro-ramp consist of stream wise vortex tubes and vortex rings. During the separation control, the incident shock compresses the wake of micro-ramp, enhances the strength of stream wise vortex. The up wash and downwash motion of gases make the energy change between the boundary layer and out flow and suppress the flow separation.
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