采用 Hermite 插值函数生成代数网格，分别计算了翼型在雷诺数为5 ×10⁴ 、1 ×10⁵ 、2 ×10⁵ 和 5 ×10⁵ 时的流动情况，对翼型在不同雷诺数下的尾涡脱落机制进行了分析。结果表明: 翼型出现周期性流动后，流体黏性效应的降低导致相同攻角下的斯特劳哈尔数随雷诺数的增大而增大; 不同雷诺数下翼型升力系数的变化规律与翼型尾涡的脱落规律保持一致; 翼型升力系数峰值出现在尾缘逆时针涡刚脱落完毕时，谷值出现在尾缘逆时针涡发展至最大时; 翼型进入周期性流动后，尾涡脱落将随着攻角的增大呈现2S (Single) 模态—2P (Pair) 模态—混沌状态—准周期性流动的发展规律。文中对不同雷诺数和攻角下翼型气动特性和尾涡脱落机制的分析，为流动控制方法的设计提供了依据。

The wake vortex shedding flow mechanism of airfoils at different Reynolds numbers (Re =5 ×10⁴ ，1 ×
10⁵ ，2 ×10⁵ ，5 ×10⁵ ，respectively) was analyzed in this paper，by generating algebraic meshes with Hermite in-
terpolation function． The results show that，when periodic flow occurs，Strouhal number increases with the increase
of Re at the same angle of attack as the fluid viscosity decreases; and that，the variation of lift coefficient of airfoil
is consistent with that of wake vortex shedding． The peak lift coefficient appears just after the tail edge counter-
clockwise vortex sheds，while the valley lift coefficient appears when the tail edge counterclockwise vortex reaches
the maximum size． When the airfoil enters the periodic flow state，the development law of wake vortex shedding is
2S (Single) mode first，then 2P (Pair) mode，chaotic state，and finally quasi-periodic flow state，as the angle of
attack increases． The investigation into the aerodynamic characteristics and wake vortex shedding mechanism pro-
vides a basis for the design of flow control methods．