回流襟翼控制S809翼型动态失速的数值模拟研究

Numerical Investigation of a Back-Flow Flap Control for S809 Airfoil Dynamic Stall

选取风力机常用S809翼型为研究对象,采用雷诺平均(RANS)方法对其动态绕流流场进行二维非定常模拟。为了控制翼型动态失速,考虑了一种在翼型吸力面放置回流襟翼的控制方法,对翼型动态失速时襟翼的控制效果进行了研究,并通过气动力系数迟滞环的分析和流场的显示,探讨了襟翼对翼型动态失速流场控制的内在机理。数值模拟结果表明:襟翼的位置对翼型动态失速流场的控制效果有明显的影响,在翼型吸力面60%弦长位置施加襟翼控制后,平均升力提高了7%,俯仰力矩峰值降低了20%。

In this study,the S809 airfoil commonly used in wind turbines was selected as the research object.A two-dimensional unsteady simulation of its dynamic flow field was performed using the RANS method.In order to control the dynamic stall of the airfoil,a control method of placing the back-flow flap on the airfoil suction surface is considered,and the control effect of the flap during the dynamic stall of the airfoil is studied.Through the analysis of the aerodynamic coefficient hysteresis loop and the display of the flow field,the inherent mechanism of the flaps controlling the airfoil dynamic stall flow field was discussed.Numerical simulation results show that the position of the flaps has a significant effect on controlling the airfoil dynamic stall flow field.With the flap control applied at the airfoil 60%chord position,the average lift is increased by 7%,pitching moment is reduced by 20%.