A. Adeel-Ur-Rehman, J. Theron, H. Kassem, B. Stoevesandt, J. Peinke
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引用次数: 0
摘要
采用标准形式的 k - ω 剪切应力传输(SST)湍流模型、修正了 a 1 常量的 k - ω SST 湍流模型(称为 a 1 方法)、Spalart-Allmaras 湍流模型和面板方法 XFoil 对设计用于风力涡轮机转子叶片的各种机翼进行了模拟。为了评估它们的性能,将机翼升力、阻力和压力系数的结果与现有的风洞数据(如有)进行了比较。结果发现,标准 k -ω SST 湍流模型对雷诺切应力的预测过高,延迟了气流分离,对机翼吸入侧的分离气流区域的预测不足。研究的机翼厚度介于弦长的 11% 和 36% 之间。使用修改后的 a 1 常量,一些机翼在失速后攻角(AoA)范围内的升力和阻力系数预测结果最多可提高 20%。值得注意的是,a 1 方法的适用性和有效性是专门针对机翼进行测试的,其性能在很大程度上取决于机翼的几何形状。
Improved performance of k − ω SST turbulence model in predicting airfoil characteristics for a wide range of airfoil thicknesses
A variety of airfoils designed for wind turbine rotor blade applications were simulated with k − ω shear stress transport (SST) turbulence model in its standard form, the k − ω SST turbulence model with a modified a 1 constant (referred to as the a 1 method), the Spalart-Allmaras turbulence model, and the panel method XFoil. To assess their performance, the results of airfoil lift, drag, and coefficient of pressure were compared against available wind tunnel data, where available. The standard k −ω SST turbulence model is found to over-predict Reynolds shear stresses, delay the flow separation, and under-predict the separated-flow region on the airfoil’s suction side. Airfoil thicknesses between 11% and 36% of the chord length were studied. Using a modified a 1 constant, some airfoils exhibited up to a 20% improvement in the prediction of lift and drag coefficients within the post-stall range of angle of attack (AoA). It is important to note that the a 1 method’s applicability and effectiveness is specifically tested for airfoils, and its performance is highly dependent on the airfoil geometry.