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用三步显式格式时间推进求解物理空间曲线网格上有限体积离散的Ｅｕｌｅｒ方程，数值模拟一种战斗机外形的涡流场．计算的机翼表面压力分布与实验符合较好，用Ｅｕｌｅｒ方程捕获到机翼前缘分离涡（主涡）及翼面上的二次分离涡．Ｅｕｌｅｒ方程解中出现的二次涡可能是逆压梯度、尖锐边缘和人工粘性共同作用的结果，它的流谱与实验定性符合．
A three - step explicit format time - driven solution to a finite volume discrete Euler equation on a curved grid of a physical space is used to numerically simulate a vortex field of a fighter shape. The calculated pressure distribution on the wing surface is in good agreement with the experiment. The Euler equation is used to capture the separation vortex (main vortex) at the leading edge of the wing and the secondary separation vortex at the airfoil. The secondary vortex that appears in the Euler equation solution may be the result of the interaction of the reverse pressure gradient, the sharp edge and the artificial viscosity, and the fluid flow spectrum is consistent with the experiment qualitatively.