Abstract: A detailed numerical investigation of a kind of missile’ s plume fields was simulated using an existing three dimensional TLA N-S computational technique based on ENO difference scheme for Mach number Ma = 0.8 - 1.6, altitude H = 2km -15km, combustor total pressure pc = 20MPa and 40 MPa. The result shows altitude and combustor total pressure markedly influence plume fields width. A formula was obtained by analyzing flows structures and measurement. The result can be used as the foundation to evaluate the edge of plume flows.

Key words: Air to air missile;Wake;Numerical simulation;Navier-Stokes equation

摘要： 从三维薄层近似N-S方程出发,采用ENO差分格式,对某型导弹尾流场进行了数值模拟。计算模拟了飞行马赫数Ma=0.8～1.6,海拔高度H=2km～15km,燃烧室总压为20MPa和40MPa条件下导弹的尾流场。计算结果表明与飞行速度相比,海拔高度和燃烧室总压对尾流宽度有显著影响。通过对流场结构的分析与测量,建立了尾流宽度与上述参数的拟合公式,为工程估算这一类型导弹尾流影响边界提供参考。

关键词: 空空导弹;尾流;数值仿真;纳维尔-斯托克斯方程