Direct numerical simulation of supersonic turbulent flow in an expansion-compression corner at mach=2.9

Fang, Jian; Yao, Yufeng; Lu, Lipeng; Zheltovodov, A. A.

Abstract

Shock-wave/turbulent boundary layer interactions (SWTBLI) are prevalent phenomena in high-speed flights, which could cause large flow separation and high wall heat flux and strong pressure fluctuation, therefore, affect significantly the aero-thermodynamic loads of the vehicles and the performance of propulsion systems. Among all kinds of SWTBLI, the supersonic expansion–compression corner is an important flow configuration consisting in the forebody, intake, combustion chamber and nozzle of high-speed flying vehicle1. In an expansion–compression corner, the supersonic flow is accelerated and turned through an expansion fan formed at the expansion corner (EC), then compressed by a shock-wave formed around the compression corner (CC)1. The boundary layer in the compression corner region can be either attached or separated, depending on the strength of the shock-wave. This kind of flows is complicated and essentially non-equilibrium due to the strong interaction among the turbulence, expansion-wave, and shock-wave.

Citation

Fang, J., Yao, Y., Lu, L., & Zheltovodov, A. A. (2014, June). Direct numerical simulation of supersonic turbulent flow in an expansion-compression corner at mach=2.9. Paper presented at ICMAR 2014

• Presentation Conference Type: Conference Paper (unpublished)
• Conference Name: ICMAR 2014
• Start Date: Jun 30, 2014
• End Date: Jul 6, 2014
• Publication Date: Jul 1, 2014
• Peer Reviewed: Peer Reviewed
• Keywords: numerical simulation, supersonic, turbulent flow, expansion-compression
• Publisher URL: http://conf.nsc.ru/icmar2014/en/
• Related Public URLs: http://conf.nsc.ru/files/conferences/icmar2014/239877/%D0%9F%D1%80%D0%BE%D0%B3%D1%80_ICMAR2014%20_%20finalen.pdf
• Additional Information: Title of Conference or Conference Proceedings : ICMAR 2014