本文对三维隅角机翼声速喷流与超声速主流的干扰流场进行了数值模拟。三维欧拉方程的求解采用非结构网格有限体积伽辽金法 (Finite Volume Galerkin Method)。引入了总体结点积分域的概念 ,简化了从单元矩阵到总体矩阵的汇总过程。通量的分裂采用 Osher格式 ,通过外差使其由一阶精度上升为二阶精度。发展了一种基于线化流量的逆风非结构网格隐式有限元格式以提高求解精度及效率。最后给出了三维隅角机翼喷流场的算例。 In this paper, the three-dimensional corner wing velocity jet and supersonic mainstream flow field were numerically simulated. The Eulerian equation is solved using the Finite Volume Galerkin Method. The concept of total knot integral field is introduced, which simplifies the process of aggregation from unit matrix to total matrix. The fission of flux is in the form of Osher, which is increased from first-order to second-order accuracy by heterodyning. An implicit finite element scheme of upwind unstructured grid based on linearized flow was developed to improve the accuracy and efficiency of the solution. Finally, an example of wing jet flow field in three-dimensional corner is given.