多段翼型的一种增升控制方法

A Lift-enhancing Mothed on Multielement Airfoil

如何在提高增升装置性能的同时降低机构的重量和复杂程度有着重要的意义。采用CFD手段对一种在多段翼型主翼后缘凹陷处加薄片(cover tab)的主动控制方法进行了数值研究。以Gaw—1两段翼型为基准翼型,对不同参数组合的tab构型进行了计算。最佳构型是在主翼后缘凹陷处距离后缘1%主翼弦长处增加高度为0.5%主翼弦长的tab,增加最大升力系数4.88%。结合计算结果对这种主动控制技术方法的参数对流动的影响以及改善流动的机理等做了探讨。计算结果表明,该方法可以改善后缘襟翼上翼面的流动,推迟流动的分离,从而增加多段翼型的最大升力系数。

The method of computational fluid dynamics(CFD) was used to calculate a lift-enhancing mothed on multielement airfoil,which contain a tab placed in the main-element trailing edge cover.A series of models with different parameters were calculated.The best configuration calculated,a 0.5%-chord tab placed 1% chord of the main-element trailing edge cover,increased the maximum lift coefficient of the airfoil by 4.88%.The mechanism of tab and the effect of the tab parameters were disscussed.The results show that this method can not only delay flow separation,but also increase the maximum lift coefficient.