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作用在超声速飞行器底部的压强对飞行器设计具有十分重要的意义，因为它可能提供飞行器总阻力的一半以上。目前，底压数据的来源主要还是依靠实验。而风洞实验时支杆的存在又增加了底阻估算的困难。本文用隐式有限体积法求解轴对称ＮＳ方程，在ＰＶＭ平台下数值模拟超声速底部流场，根据底压分布计算出了底压系数。分析了网格密度，支杆直径对底压系数的影响，网格足够密时，计算结果与实验吻合较好。
The pressure acting on the bottom of the supersonic aircraft is of great importance to aircraft design as it may provide more than half the total drag of the aircraft. At present, the source of the bottom pressure data mainly depends on the experiment. However, the existence of the struts in the wind tunnel experiment also increases the difficulty of the bottom resistance estimation. In this paper, the implicit finite volume method is used to solve the axisymmetric NS equations, and the supersonic flow field at the PVM platform is numerically simulated. The bottom pressure coefficient is calculated according to the bottom pressure distribution. The influence of grid density and strut diameter on pressure coefficient was analyzed. When the grid was dense enough, the calculated result was in good agreement with the experiment.