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提出了一种求解带副翼偏转三维机翼绕流的 Ｅｕｌｅｒ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 Ｖａｎ Ｌｅｅｒ 分裂格式离散无粘通量项，并构造了一种 Ｌｉｍ ｉｔｅｒ函数以保证 Ｔ Ｖ Ｄ 性质。数值算例表明本方法是求解带操纵面偏转的机翼绕流的有效方法。
A new Euler equation method for solving 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 discretized non-cohesive flux term is chosen and a Limiter function is constructed to guarantee the T V D property. Numerical examples show that this method is an effective method to find the flow around the wing with the control surface deflection.