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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。
How to reduce the weight and complexity of the mechanism while improving the performance of the lifting device is of great significance. A CFD method is used to study the active control method of a cover tab in the trailing edge recess of a multi-stage airfoil. Based on the Gaw-1 two-stage airfoil, the tab configurations of different parameters were calculated. The best configuration is to increase the height of the main chord 0.5% of the main tab at the recess of the trailing edge of the main wing by 1% of the main chord, and increase the maximum lift coefficient by 4.88%. Combining with the calculation results, the influence of the parameter of the active control technique on the flow and the mechanism of improving the flow were discussed. The calculation results show that this method can improve the flow on the airfoil on the trailing edge flap and delay the separation of the flow so as to increase the maximum lift coefficient of the multi-section airfoil.