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Limiting value of Reynolds Averaged Simulation in numerical prediction of flow over NACA4415 airfoil

机译：雷诺平均模拟在NACA4415翼型流动数值预测中的极限值

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Reynolds Averaged Simulation (RAS) and Large Eddy Simulation (LES) are two widely used turbulence modeling approaches in Computational Fluid Dynamics (CFD). RAS simulations require less computing times than used by LES. When large eddies of flow become dominant, RAS simulations cannot predict accurate results. Hybrid RAS-LES approach is effective solution to reduce computational cost and time. In this approach, only parts of flow where larger eddies become dominant are solved using LES, and other areas are resolved using RAS. In order to apply RAS-LES hybrid models, regions of flow where RAS simulation cannot be applied need to be identified. The present work finds the limiting value of angle of attack for a NACA4415 airfoil where RAS simulation can be applied. Simulations were performed using two widely used RAS turbulence models for angles of attacks ranging from -6 to 16.3 degrees. Then results are compared against experimental data. It is found that for NACA4415 airfoil at a Reynolds number of 1.5 million, RAS simulation can be used to successfully predict flow behavior up to an angle of attack of 4.1 degrees. Based on this limiting angle of attack, an approach is suggested for hybrid RAS-LES simulation for a wind turbine.
机译：雷诺平均模拟（RAS）和大涡模拟（LES）是计算流体力学（CFD）中两种广泛使用的湍流建模方法。 RAS仿真所需的计算时间少于LES使用的时间。当大的涡流占主导地位时，RAS模拟无法预测准确的结果。混合RAS-LES方法是减少计算成本和时间的有效解决方案。在这种方法中，仅使用LES解决了较大涡流占优势的部分流量，而使用RAS解决了其他区域。为了应用RAS-LES混合模型，需要确定无法应用RAS模拟的流动区域。本工作找到了可以应用RAS模拟的NACA4415机翼的迎角极限值。使用两个广泛使用的RAS湍流模型进行了仿真，其攻角范围为-6至16.3度。然后将结果与实验数据进行比较。发现对于雷诺数为150万的NACA4415机翼，可以使用RAS模拟成功地预测高达4.1度迎角的流动行为。基于该限制的迎角，提出了一种用于风力涡轮机的混合RAS-LES仿真的方法。

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