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提出了一种求解带副翼偏转的翼身组合体绕流的Euler方程计算方法 .将对接分区网格与分区求解算法相结合 ,有效地求解了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 ,并构造了一种限制器 (Limiter)函数以保证TVD性质 .数值算例表明本文方法是求解带操纵面偏转的翼身组合体绕流的有效方法 .
An Euler equation method for solving the flow around a wing body assembly with aileron deflection is proposed. Combining the docking grid with the partitioning algorithm, the complex flow around this contour is effectively solved. Flux boundary condition.The VanLeer splitting scheme was used in the numerical method to discretize the non-adifable flux term and a Limiter function was constructed to ensure the TVD properties.The numerical examples show that the proposed method solves the problem with the control surface An efficient method of deflecting the wing body assembly around the flow.