Turbulence modeling of deep dynamic stall at relatively low Reynolds number
Turbulence modeling of deep dynamic stall at relatively low Reynolds number
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DOI：
10.1016/j.jfluidstructs.2012.04.011
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发表时间：
2012-08-01
影响因子：
3.6
通讯作者：
Tao, Zhi
中科院分区：
文献类型：
--
作者：
Wang, Shengyi;Ingham, Derek B.;Tao, Zhi
本文数值研究了绕正弦振荡翼型俯仰运动引起深度动态失速的非定常分离湍流流动。基于翼型的弦长，流动处于10（5）量级的相对低雷诺数的状态。URANS和更先进的DES方法都被采用。URANS与两个先进的湍流模式耦合，即RNG k-R模式和过渡SST模式（γ-Re-0模式），DES与SST k-omega模式耦合。与实验数据的比较表明，基于SST k-ω的DES方法比URANS方法优越上级，并且与实验数据基本一致，尽管对实验观察到的峰值失速迎角的预测可能没有保证。详细讨论了动态失速和边界层转捩的复杂流动发展过程。(C)2012爱思唯尔有限公司保留所有权利。
This paper investigates numerically the unsteady separated turbulent flows around an oscillating airfoil pitching in a sinusoidal pattern that induces deep dynamic stalls. The flow is in the regime of relatively low Reynolds number of the order of 10(5) based on the chord length of the airfoil. Both the URANS and the more advanced DES approaches are employed. The URANS is coupled with two advanced turbulence models, namely the RNG k-epsilon model and the Transition SST model (gamma-Re-0 model) and the DES is coupled with the SST k-omega model. A comparison with experimental data shows that the SST k-omega based DES approach is superior to the URANS approach and presents generally good agreement with the experimental data, although the prediction of experimentally observed peek stall angle of attack may not be warranted. The details of the complex flow development of the dynamic stall and the boundary layer transition have been discussed. (C) 2012 Elsevier Ltd. All rights reserved.