通过对光滑 NACA0018翼型进行数值模拟计算，所得结果与实验数据进行对比，表现出较好的一致性，证明了所用数值模拟方法的有效性。对比研究带襟翼翼型（以 NACA0018为基准翼型）和基准翼型的气动特性，得出襟翼有延迟失速的作用；对带襟翼翼型不同粗糙度进行数值模拟，分析得出粗糙度对翼型升力系数与阻力系数的不同影响；分别研究翼型主翼和襟翼相同粗糙度时翼型气动特性，表明主翼粗糙度对翼型气动特性影响较大，襟翼粗糙度对翼型气动特性影响相对较小。%Using the SST turbulence model to simulate the aerodynamic characteristics of smooth NACA0018 airfoil and compa-ring it with experimental data,the good consistency proved the validity of the numerical simulation method.Comparative study with flap airfoil (reference to NACA0018 airfoil)and baseline airfoil’s aerodynamic characteristics,the result showed that the stall angle of airfoil will be delay.Numerical simulations of different roughness of airfoil with flap indicated that different rough-ness resulted in different effects of airfoil lift coefficient and drag coefficient.The study on aerodynamic characteristics when the wing and flap had the same roughness pointed out that the effect of the main wing’s roughness on the airfoil aerodynamic charac-teristics was large while the effect of the flap’s roughness on the airfoil aerodynamic characteristics was relatively small.
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