中文摘要：

很多湍流模型忽略了层流区域的存在,但实际流动在翼型某位置处开始转捩,此时模型显然偏离实质,计算结果精度较低。因此加入γ-Reθ转捩模型,将转捩动量厚度雷诺数Reθ作为经验关联函数来控制边界层内间歇因子γ的生成,再通过间歇因子来控制湍动能产生项,使湍流模型在层流区域失效。首先为了验证数值计算的准确性,采用上述方法针对风力机翼型A2121,在高雷诺数4×106下对几种典型攻角的气动性能进行计算,对比普通全湍流模型、湍流转捩模型和风洞试验的计算结果,发现湍流转捩模型结果更精确。之后在更大攻角范围-10.14°~25.09°内,采用此转捩模型数值方法进行气动仿真,发现其总体计算结果与风洞试验实验数据较吻合,验证了此数值方法的正确性和有效性。

英文摘要：

Most of the turbulence models ignored the existence of laminar flow. However, the reality is that transition process will be triggered at some point on airfoil. Therefore, full turbulence models have deviated from the real flow phenomenon, and so the precision of the results attained from these methods are comparatively low. Consequently theγ-Reθ transition model is added into full turbulence models here, where transition momentum thickness Reynolds number is treated as empirical correlation function to control the production of intermittency factor T＂ Then intermittency factor is used to control the production term of the turbulent kinetic energy, making the turbulence model unavailable in laminar flow area. Above all, in order to verify the accuracy of the numerical simulation, aforementioned methods are used to simulate the aerodynamic performance of the airfoil A2121 under some typical angles of attack, with the high Reynolds number of 4 × 10^6 . It is found that the transition model is of higher accuracy through comparing the results gained from full turbulence models, transition model and wind tunnel experiment. Afterwards, this transitional turbulence model is adopted to get the aerodynamic data within the attack angle ranges from - 10.14° to 25.09° . The experiment and computational fluid dynamics method are demonstrated and compared. The results from transitional turbulence model showed great agreement with the outcomes from wind tunnel experiment, which provide a validation of this numerical simulation method for airfoil.