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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.


Jian Fang

Yufeng Yao
Professor in Aerospace Engineering

Lipeng Lu

A. A. Zheltovodov


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.


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Presentation Conference Type Conference Paper (unpublished)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
Related Public URLs
Additional Information Title of Conference or Conference Proceedings : ICMAR 2014


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