| 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 |
| DOI： |
| 分类号:TJ760 |
| 基金项目: |
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| Numerical simulation on the plume flow structures for a missile |
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XU Chun-guang, LIU Jun
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Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China
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| 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 |
