| 某型导弹尾喷流形状的数值模拟 |
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| 引用本文： | 徐春光,刘君.某型导弹尾喷流形状的数值模拟[J].推进技术,2003,24(2):141-143. |
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| 作者姓名： | 徐春光 刘君 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 从三维薄层近似N—S方程出发，采用EN0差分格式，对某型导弹层流场进行了数值模拟。计算模拟了飞行马赫数Mα0．8—1．6，海拔高度H＝2km—15km，燃烧室总压为20MPa和40MPa条件下导弹的层流场。计算结果表明与飞行速度相比，海拔高度和燃烧室总压对层流宽度有显著影响。通过对流场结构的分析与测量，建立了层流宽度与上述参数的拟合公式，为工程估算这一类型导弹层流影响边界提供参考。
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| 关 键 词： | 空空导弹 层流 数值仿真 纳维尔－斯托克斯方程 |
| 文章编号： | 1001-4055(2003)02-0141-03 |
| 修稿时间： | 2002年5月8日 |
Numerical simulation on the plume flow structures for a missile |
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| XU Chun-guang and LIU Jun.Numerical simulation on the plume flow structures for a missile[J].Journal of Propulsion Technology,2003,24(2):141-143. |
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| Authors: | XU Chun-guang and LIU Jun |
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| Institution: | Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;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. |
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| Keywords: | Air to air missile Wake Numerical simulation Navier-Stokes equation |
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