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应用Harten-ThD格式和时间推进方法求解Euler方程，对高超声速钝头飞行器绕流流场进行了计算．物面压力系数与实验数据进行比较，结果表明本文所提出的求解方法是可行的．本文的计算方法可应用到再入弹体绕流流场和再入气动特性的研究．
The Euler equation was solved using the Harten-ThD scheme and time-propulsion method, and the flow around the flow field was calculated. The comparison between the surface pressure coefficient and the experimental data shows that the solution proposed in this paper is feasible. The calculation method of this paper can be applied to the study of the flow field around the reentry missile and the reentry aerodynamic characteristics.