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提出了一种求解带副翼偏转三维机翼绕流的Ｎ－Ｓ方程计算方法。采用对接分区网格与分区求解算法的结合，有效地求解绕此外形的复杂流动。提出了一种满足通量守恒的内边界耦合条件。数值方法中选用ｖａｎＬｅｅｒ分裂格式离散无粘通量项，并构造了一种Ｌｉｍｉｔｅｒ函数以保证ＴＶＤ性质，采用中心差分格式来离散粘性通量项。数值算例表明该方法是求解带操纵面偏转的机翼绕流的有效方法。
A new method for solving the N-S equation of a three-dimensional wing with aileron deflection is proposed. The combination of docking grid and partitioning algorithm effectively solves the complex flow around this shape. An internal boundary coupling condition that satisfies the flux conservation is proposed. In the numerical method, van Leer’s split-form discrete non-tacky flux term is chosen. A Limiter function is constructed to ensure the TVD property. The central difference scheme is used to disperse the viscous flux term. Numerical examples show that this method is an effective method to solve the wing flow around the deflection of the control surface.