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Wall-Modeled LES for Flows over an NACA-0012 Airfoil

机译：壁式LES，用于流经NACA-0012机翼

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Wall-modeled large-eddy simulations (WMLES) of flows through a channel and flows over an NACA-0012 airfoil at high Reynolds numbers are performed using equilibrium wall models. The LES equations are solved using higher-order compact schemes. The results are compared with existing DNS~(26) and experimental reference data sets.~(25) The mean profiles and the Reynolds shear stress obtained with the WMLES for the channel flow agree very well with the DNS results beyond the exchange location. The skin friction coefficients are predicted within 2-3% of the DNS results using the WMLES. However, the normal stresses are under predicted by the WMLES. A priori analysis performed for the flow over an NACA-0012 airfoil at a moderate Reynolds number of 1×10~6 and at a high angle of attack of 15 degrees showed that the equilibrium model predicts the skin friction within 5-15% accuracy compared to the DNS results. WMLES simulations were performed at a higher Reynolds number of 3*10~6 and at two angles of attack of 0.0 and 9.86 degrees. The pressure distributions agreed well with the experiment~(25) and the skin friction coefficient also agrees well with the DNS results of Rizzetta and Visbal.~(26) The mean Nflow profiles and the Reynolds stresses are also predicted very well by the WMLES. However, the turbulent intensity and the shear stresses are overpredicted by the WMLES compared to the DNS near the trailing edge.
机译：使用平衡壁模型对高通道流过通道并在高雷诺数下流经NACA-0012机翼的壁模型进行大涡模拟（WMLES）。 LES方程使用高阶紧致格式求解。将结果与现有的DNS〜（26）和实验参考数据集进行比较。〜（25）用WMLES获得的通道流的平均剖面和雷诺剪切应力与交换位置以外的DNS结果非常吻合。使用WMLES预测皮肤摩擦系数在DNS结果的2-3％之内。但是，WMLES预测法向应力不足。对NACA-0012翼型在1×10〜6的雷诺数和15度的高攻角下的流动进行的先验分析表明，平衡模型预测，与5-15％的精度相比，皮肤摩擦更精确DNS结果。 WMLES模拟在较高的雷诺数3 * 10〜6以及0.0和9.86度的两个攻角下进行。压力分布与实验吻合良好（25），皮肤摩擦系数也与Rizzetta和Visbal的DNS结果吻合良好。（26）WMLES也很好地预测了平均N流量剖面和雷诺应力。但是，与后缘附近的DNS相比，WMLES过度预测了湍流强度和剪切应力。

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