Direct numerical simulation of flow separation around a NACA 0012 airfoil

被引：81

作者：

Shan, H ^{[1
]}

Jiang, L ^{[1
]}

Liu, CQ ^{[1
]}

机构：

[1] Univ Texas, Dept Math, Arlington, TX 76019 USA

来源：

COMPUTERS & FLUIDS | 2005年 / 34卷 / 09期

关键词：

D O I：

10.1016/j.compfluid.2004.09.003

中图分类号：

TP39 [计算机的应用];

学科分类号：

081203 ; 0835 ;

摘要：

Direct numerical simulation (DNS) for the flow separation and transition around a NACA 0012 airfoil with an attack angle of 4 degrees and Reynolds number of 105 based on free-stream velocity and chord length is presented. The details of the flow separation, detached shear layer, vortex shedding, breakdown to turbulence, and re-attachment of the boundary layer are captured in the simulation. Though no external disturbances are introduced, the self-excited vortex shedding and self-sustained turbulent flow may be related to the backward effect of the disturbed flow on the separation region. The vortex shedding from the separated free shear layer is attributed to the Kelvin-Helmholtz instability. (C) 2004 Elsevier Ltd. All rights reserved.

引用

页码：1096 / 1114

页数：19

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