风力机叶片吸力面波浪翼型气动性能数值研究

Numerical Study on Aerodynamic Performance of Wavy Airfoil on Suction Surface of Wind Turbine Blade

为提高风力机翼型气动性能,提出一种新的被动流动控制方法:在翼型吸力面设计波浪形片段。选取S809为基础翼型,以T-SST模型为计算模型,研究波浪形片段结构参数(相对深(高)度、位置和波浪长度)对翼型气动性能的影响。结果表明:凹陷深度和放置位置以及波浪长度存在最佳设计尺寸,并非与气动性能呈现简单的线性关系;在失速攻角之前波浪翼型和原始翼型气动性能相差不大,在大攻角(16°~22°)下升力系数增幅较小,凹腔内伴有涡团产生,压力重新分配压差阻力减小,且流体浮在涡团上运动形成涡垫效应使得摩擦阻力减小;16°~20°攻角时相比于原始翼型升阻比提升15%~36%。

In order to improve the aerodynamic performance of the wind turbine airfoil,a new passive flow control method was proposed:Design a wavy segment on the airfoil suction surface.S809 airfoil was selected as the basic airfoil,and the T-SST model was used as the calculation model to study the structural parameters of the wavy segment(influence of relative depth,height,position and length of wavy segment)on the aerodynamic performance of airfoil.The results showed that there was an optimal design scale for the depth and placement of the depression,and the length of the wave.Before the stall angle of attack,the aerodynamic performance of the wavy airfoil and the original airfoil were not much different.The lift coefficient increased at a large angle of attack(16°~22°),and a vortex blob was generated in the cavity,leading to pressure redistribution and reduced pressure resistance.The fluid afloat on the vortex blob forms a vortex effect,resulting in reduced frictional resistance.The lift-to-drag ratio of the wavy airfoil was increased by 15%~36%compared to that of the original airfoil at 16°~20°angle of attack.