Direct numerical simulation of a hypersonic shock wave/turbulent boundary layer interaction
ORAL
Abstract
The direct numerical simulation of a hypersonic shock wave/turbulent boundary layer interaction generated by a 33-degree compression ramp is presented. The fully-turbulent inflow boundary layer is at Mach 7.2, and the Reynolds number based on momentum thickness is $Re_{\theta}=3500$. The evolution of the mean and fluctuating field through the interaction region and the properties of the low-frequency unsteadiness are investigated.
*This research is supported by AFOSR Grant Number AF 9550-09-1-0464.
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