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- W2898858908 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." @default.
- W2898858908 created "2018-11-09" @default.
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- W2898858908 date "2018-01-01" @default.
- W2898858908 modified "2023-09-23" @default.
- W2898858908 title "Numerical study of unsteady effects in the interaction of an incident shock with the transitional boundary layer on a flat plate" @default.
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- W2898858908 doi "https://doi.org/10.1063/1.5065357" @default.
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