对风力机专用的S809翼型尾缘上表面不同位置添加小圆柱的方法对后缘气流的流动状态进行控制,通过N-S方程数值模拟0°~20°攻角下翼型的气动性能变化.结果表明,在大攻角时小圆柱扰流能够推迟翼型上表面的流动分离点,改善后缘上表面的涡流结构,使得上表面气流的绕流效应减弱,增大上表面流速,减小翼型上表面压力,从而提高翼型升力、降低翼型阻力.同时,小圆柱存在最优尺寸使得对尾部涡流的控制效果最佳,气动性能达到最好.

 The flow state of the tail edge airflow is controlled by adding a small cylinder at different positions above the tail edge of the S809 airfoil, and the aerodynamic performance of the airfoil under the 0-20 degree angle of attack is simulated by the N-S equation. The results show that the cylindrical spoiler can postpone the flow separation point of the airfoil and improve the vortex structure on the upper surface of the tail edge, which makes the flow around the upper surface weaken, thus increasing the velocity of the upper surface, reducing the surface pressure of the airfoil, and improving the lift of the airfoil and reducing the drag of the airfoil. At the same time, the optimal size of the small cylinder has the best control effect on the tail vortex, and the aerodynamic performance is the best.