翼缝宽度对翼型水动特性的影响

Influence of the Flap Slot Width on the Hydrodynamic Characteristics of an Airfoil

针对翼型失速问题,采用CFD(流体动力计算软件)数值模拟方法,以NACA0018为基准翼型,分析了不同翼缝宽度对翼型压力云图及流场等值线分布的影响。计算结果表明:当翼型处于小攻角时,翼缝宽度对翼型吸力面影响较小,对压力面高压区范围影响较大;当翼型处于大攻角时,翼缝的存在改变了翼型流场结构,减少了翼型尾缘处发展涡的数量,且缩小了涡的范围;在大攻角下,翼缝对翼型压力面高压区和吸力面低压区范围影响较大;对比三种不同翼缝宽度对翼型压力云图及流线等值线图可知,翼缝宽度w=0.1%c时,翼型水动性能最佳。

In the light of the problem of the stall of an airfoil,the CFD numerical simulation method was employed. With the airfoil NACA0018 serving as the reference airfoil,the influence of the flap slot width on the distribution of the pressure and flow field contours was analyzed. The calculation results show that when the airfoil has a small attack angle,the flap slot width exerts a relatively small influence on the suction side of the airfoil while exercise a relatively big influence on the high pressure zone in the pressure side of the airfoil. When airfoil has a big attack angle,the presence of the flap slot will change the configuration of the flow field formed by the airfoil,thus reducing the number of vortexes evolved in the wake and narrowing the range of the vortexes. At a large attack angle,the flap slot will exert a relatively big influence on the range of the high pressure zone on the pressure surface and the low pressure zone on the suction surface. It has been known by comparing the influence of the three kinds of flap slot width on the pressure and streamline contours of the airfoil that when the flap slot width w = 0. 1% c,the hydrodynamic performance of the airfoil will be optimal.