Abstract
© 2017 by Guang Yang, Beihang University, Beijing, China. Shock wave boundary layer interaction is an ubiquitous and important phenomenon in supersonic and hypersonic flow scheme. In this paper, a Mach 2.5 supersonic boundary layer impinged by an oblique shock wave and its control using Micro Vortex Generator (MVG) is studied by large-Eddy Simulation (LES). A high order cut-cell immersed boundary method combined with Cartesian grid are used to deal with the geometrical complexity of MVG. The method uses a non-uniform-grid finite difference scheme for grid points near the MVG solid boundary. This approach can implement boundary condition at irregular surface without decreasing numerical accuracy, which is important for high Reynolds number boundary layer flow. Results shows that flow structures after the MVG are well captured and shock induced flow separation is successfully reduced with control.
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