前缘气动滑片对翼型动态失速特性影响

Effect of Leading Edge Aerodynamic Slider on Airfoil Dynamic Stall Characteristics

为减小翼型动态俯仰过程中的失速现象,提出了采用前缘气动滑片改善动态失速特性的控制方法。基于NACA0012翼型,在翼型前缘设计气动滑片,采用非定常雷诺平均(URANS)方程对失速状态进行数值模拟,研究前缘气动滑片对翼型气动特性的影响。结果表明:随着攻角不断增大,前缘气动滑片翼型能有效抑制动态失速,延缓分离涡从翼型前缘脱落;在升力系数保持不变或增加的情况下,滑片可以显著降低阻力系数,并且使翼型在运动过程中的迟滞效应减弱;在上仰过程中,较之原始翼型,当滑片最大高度为1.5%c时,翼型升阻比可提高13.2%。

In order to reduce the stall in the airfoil dynamic pitching process,a control method was proposed by using the leading edge sliding vane to improve the dynamic stall characteristics.Aerodynamic sliding vane was designed at the leading edge of the NACA0012 airfoil,and the unsteady Reynolds average(URANS)equation was used to simulate the stall state,to study the influence of the leading edge sliding vane on the aerodynamic characteristics of the airfoil.The results show that as the angle of attack increases,the leading edge aerodynamic sliding vane can effectively suppress dynamic stall and delay the separation vortex from the leading edge of the airfoil.The sliding vane can significantly reduce the drag coefficient while the lift coefficient remains constant or increases,and the hysteresis effect of the airfoil is weakened.During its pitch up process,compared to the clean airfoil,when the maximum height of the sli der at 1.5%c,the lift-drag ratio of the airfoil can be increased by 13.2%.