Abstract: 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.