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Direct numerical simulation of the Mach 6 flow approaching a 35 degree ramp. Simulation shows the laminar-to-turbulent transition of the separated boundary layer and its impingement and reflection from the ramp. Calculations performed by Mr. Fabian Dettenrieder. Corresponding experiment performed at the NASA Langley 20-inch Mach 6 tunnel by Dr. Stuart Laurence and his team at the University of Maryland.
Aeroacoustics and Flow Physics Research Group
Email: bodony@illinois.edu