Abstract
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.
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