CAS-W1-450大厚度钝尾缘翼型气动性能数值模拟研究

Computational Aerodynamic Investigation of a Very Thick Wind Turbine Airfoil CAS-W1-450 With Blunt Trailing Edge

风电叶片叶根附近的翼型对发电量的贡献随着机组的大型化越来越重要,促使了大厚度翼型的发展。为了探索大厚度翼型的数值模拟方法,本文模拟了CAS-W1-450翼型在实验状态下的流动特征。结果表明:在线性段,升力系数模拟值与实验值吻合良好,失速后,三维模拟结果优于二维结果;大攻角时,翼面不同展向位置的压力分布体现了流动分离的三维性,并且,尾缘附近的脱落涡使流动呈现非定常性,随着攻角的增加,升力系数变化幅值增加,频率降低。

With the development of large-scale wind turbines,airfoils used in the inboard section of a blade play an increasingly important role in power generation,contributing to the development of thick airfoils.In order to investigate the numerical simulation method of large-thickness airfoil,this paper studies the CAS-W1-450 airfoil,and simulates the airfoil under the experimental condition.The results indicate that the calculated lift coeficients agree well with the experimental data in linear region,3 D simulation predicts better results than 2 D simulation after stall.Pressure distributions of the airfoil at different spanwise positions reflect a three-dimensional characteristic of flow separation.Furthermore,the flow exhibits unsteady characteristics at high angles of attack due to the shedding vortices in the wake.With the increase of angle of attack,the fluctuation amplitude of lift coefficient curve becomes more significant while the fluctuation frequency decreases.