Large-eddy simulation of MVG controlled oblique Shockwave/Boundary layer interaction

Yang, Guang; Fang, Jian; Liu, Chaoqun; Yao, Yufeng; Lu, Lipeng

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.

• Presentation Conference Type: Conference Paper (published)
• Conference Name: AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
• Start Date: Jan 8, 2017
• End Date: Jan 13, 2017
• Acceptance Date: Aug 31, 2016
• Publication Date: Jan 1, 2017
• Deposit Date: Oct 21, 2016
• Publicly Available Date: May 4, 2017
• Peer Reviewed: Peer Reviewed
• DOI: https://doi.org/10.2514/6.2017-0945
• Public URL: https://uwe-repository.worktribe.com/output/900165
• Publisher URL: https://arc.aiaa.org/doi/pdf/10.2514/6.2017-0945
• Additional Information: Additional Information : This is the accepted version of the paper available from: https://arc.aiaa.org/doi/pdf/10.2514/6.2017-0945; Title of Conference or Conference Proceedings : 55th AIAA Aerospace Sciences Meeting, AIAA Science and Technology Forum and Exposition 2017
• Contract Date: May 4, 2017