Validation of shock-wave/turbulent boundary-layer interaction flows by high-fidelity numerical simulations

Zheltovodov, A A; Fang, J; Yao, Yu

Abstract

Shock-wave/turbulent-boundary-layer interactions (SWTBLI) are prevalent phenomena around high-speed vehicles. The resultant strong adverse pressure gradient will induce large flow separation, high wall heat flux, and strong pressure fluctuation, along with other complex physical phenomena. The research on SWTBLI has been conducted persistently for more than 70 years, although some fundamental flow mechanisms are still not completely understood and the prediction of its aerodynamic performance is still unsatisfactory [1]. Four key configurations involving a high-speed vehicle are studied using DNS and LES, which are respectively the oblique shock-wave/flat plate boundary layer interaction (OSWFPBLI) flow, the compression-expansion corner (ComExpCor) flow, the expansion-compression corner (ExpComCor) flow and the flow past a single fin (SFIN). The sketch of these configurations are presented in Fig. 1.
The in-house code ASTR was adopted to solve the compressible Navier – Stokes (NS) equations. The 7th-order MP-LD scheme [2] is used to solve the convection terms, and the diffusion terms are solved with the 6th-order compact central scheme. The 3rd-order Runge – Kutta method isused to advance the solution in time

• Presentation Conference Type: Conference Paper (unpublished)
• Conference Name: The 21st International Conference on the Methods of Aerophysical Research (ICMAR 2022)
• Start Date: Aug 8, 2022
• End Date: Aug 14, 2022
• Deposit Date: Aug 17, 2022
• Publicly Available Date: Aug 17, 2022
• DOI: https://doi.org/10.53954/9785604788967_220
• Keywords: Shock-waves; turbulent boundary-layer interaction flows; numerical simulations
• Public URL: https://uwe-repository.worktribe.com/output/9776718
• Publisher URL: https://www.elibrary.ru/item.asp?id=49163751
• Related Public URLs: http://conf.nsc.ru/icmar2022