在现有的尖头旋成弹体气动力计算中，通常都忽略了顶点附近弹体表面曲率的影响，而将子午线处理成直线段进行分析。本文考虑了这种曲率的存在，得到了顶点处的弹体表面压力梯度和激波曲率，在此基础上，给出了顶点附近超音速流场的一种近似计算方法。与现有理论进行比较，它们有较好的一致性。

In present theory concerning the aerodynamical calculation of the sharp nose body of the revolution, the effect of the surface curvature nearby the nose is usually neglected. Here, a meridian is treated as a straight line. In this paper, the effect of the curvature on the aerodynamic behaviour of the projectile is taken into consideration and both pressure gradient and shock wave curvature are obtained. On this basis, an approximate method for calculating supersonic flow field nearby the nose is presented. The results are compared with the present theory and good agreement has been found.