:给出了带襟翼偏转的三维机翼绕流的一种求解NS方程的计算方法。采用区域求解算法和对接分区网格技术相结合的方法,有效地求解了绕此外形的复杂流动。区域求解算法中提出了一种满足通量守恒的内边界耦合条件。流场求解时采用中心差分的有限体积方法对空间通量项进行离散,采用显式推进方法进行时间方向的积分。数值算例表明本方法是求解带襟翼偏转的机翼绕流的有效方法。 : A method of calculating the Navier-Stokes equations for a three-dimensional wing with flap deflection is given. By using the method of regional solution and docking partitioned grid technique, the complex flow around this shape is effectively solved. In the region solving algorithm, a condition of inner boundary coupling satisfying the flux conservation is proposed. When solving the flow field, the finite volume method of central difference is used to discretize the space flux term, and the explicit propulsion method is used to integrate the time direction. The numerical example shows that this method is an effective method to solve the flap-deflected wing flow.