Numerical study of unsteady effects in the interaction of an incident shock with the transitional boundary layer on a flat plate

摘要

The numerical simulation of the unsteady effects in the interaction of an incident shock wave with the transitional flat-plate supersonic boundary layer has been performed. The Mach 2 supersonic boundary layer excited by unstable disturbances in the form of linear stability waves undergoes laminar-turbulent transition. An incident oblique shock wave impinges on the transitional boundary layer thus causing boundary layer separation. Large-scale turbulence structures evolving in the transitional boundary layer cause significant flow oscillations in the shock wave/boundary layer interaction region which manifests in fluctuations of the position and shape of the separation and reattachment lines, and also in staggering of the reflected shock wave.