采用有限体积法高效求解Ｅｕｌｅｒ方程，成功地计算了全机亚跨超音速迎角可达６０°的绕流流场及空气动力。还就应用求解Ｅｕｌｅｒ方程模拟大迎角分离流动的能力进行了探讨。计算表明，应用本方法能自动捕获大后抓角机翼前缘分离涡，机身分离涡及其相互干扰。计算结果与实验的压力分布及气动力吻合良好。 The finite volume method is used to solve the Euler equation efficiently and the flow fields and aerodynamics of the whole aircraft with sub-supersonic anomaly angles up to 60 ° are successfully calculated. The application of the Euler equation to simulate the separation flow at high angle of attack is also discussed. The calculation shows that the proposed method can automatically capture the separation vortex at the front and the separation vortex and the mutual interference between the two wings. The calculated results are in good agreement with the experimental pressure distribution and aerodynamic forces.