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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2003年第2期141-143,共3页
Journal of Propulsion Technology
