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Fang, J.; Yao, Y.; Zheltovodov, A. A.; Lu, L. (2015)
Languages: English
Types: Unknown
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arxiv: Physics::Fluid Dynamics
The three-dimension (3D) shock-wave/turbulent boundary layer interaction (SWTBLI) raised from a hypersonic flow passing a single-fin at Mach 5 is investigated i by using LES. The performed LES has demonstrated very good agreements with available experimental data in terms of the mean flowfield structure, the surface pressure and as well as the surface flow pattern. However, significant under-prediction in the surface skin-friction peak in the vicinity of the reattachment line is observed.
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    • [1] Schülein, E., “Skin-Friction and Heat Flux Measurements in Shock/Boundary-Layer Interaction Flows,” AIAA Journal, Vol. 8, No. 4, 2006, pp. 1732-1741
    • [2] Zheltovodov, A., Maksimov, A., and Schülein, E., “Development of Turbulent Separated Flows in The 1.2 1.4 1.6 1.0
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