This paper presented direct numerical simulations of hypersonic boundary layer transition over cones in Mach 6 flow with zero angle of attack induced by fresstream waves. A disturbance pulse model that embraces a wide range of frequencies is introduced in the freestream to capture the receptivity response at different frequencies. Approach that breaks the direct numerical simulation into three parts: meanflow computation, linear receptivity simulation and nonlinear breakdown simulation is utilized. One test case has been completed using the three-step approach. The simulation is carried up to the early stage of breakdown. The preliminary result shows strong evidence of fundamental resonance mechanism during the early stage into breakdown.
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