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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。
Aiming at the problem of airfoil stalling, CFD (Fluid Dynamic Computation Software) numerical simulation method and NACA0018 as the reference airfoil are used to analyze the influence of different winglet width on the airfoil pressure cloud and the contour distribution of the flow field. The calculation results show that when the airfoil is at a small angle of attack, the width of the wing slot has little effect on the airfoil suction surface and greatly affects the pressure surface high pressure area. When the airfoil is at a high angle of attack, the existence of the wing seam changes The airfoil flow field structure reduces the number of development vortices at the trailing edge of the airfoil and reduces the vortex area. At large angles of attack, the airfoil greatly affects the range of the high pressure area and the low pressure area of the suction surface. Comparing the airfoil pressure and the contours of the airfoil with three different widths of wing joints, we can see that the wing hydrodynamic performance is the best when the width of wing joint is 0.1% c.