计算超声速战术导弹大攻角气动力的数值方法

A Numerical Method for Calculating the Aerodynamic Characteristics of Tactical Missile to High Angles of Attack at Supersonic Speeds

本文给出了超声速大攻角情况下战术导弹气动力特性及压力分布的计算方法。该方法以Woodward,F.A.等人的有限基本解方法为基础。考虑了弹身头部涡、翼面前缘涡、翼面侧缘涡、后缘涡及诸运动涡系的影响,使其应用范围超出了小攻角的限制。 本方法适用于有、滚转有任意舵面偏转情况下正常式或前控导弹外形的气动力特性及压力分布计算。攻角范围直到25°。

In this paper a Computational method for aerodynamic characteristics and pressure distribution of tactical missile at supersonic high angles of attack is given. The theoretical approach described in this article is based on the finite elementary numerical solution method of Woodward, F.A..The method is to be extended to include the effects of body nose vortex, fin trailing vorticity, leading and side-edge vortex and moving vortex systems.Calculating exemples show that the method is capable of calculating detailed aerodynamic loadings and pressure distributions acting on the normal and the forward control missile configurations with rolling and arbitrary deflected angles. The applicable range for angles of attack is up to 25°.