某型导弹尾喷流形状的数值模拟  

Numerical simulation on the plume flow structures for a missile

作　　者：徐春光[1] 刘君[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第2期141-143,共3页Journal of Propulsion Technology

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。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=2 km-15 km, combustor total pressure pc=20 MPa 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.

关 键 词：空空导弹 层流 数值仿真 纳维尔-斯托克斯方程 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]