| 弹体尾部轴对称干扰流场数值模拟 |
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| 引用本文： | 周伟江,马汉东.弹体尾部轴对称干扰流场数值模拟[J].计算物理,1993,10(4):422-428. |
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| 作者姓名： | 周伟江 马汉东 |
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| 作者单位： | 北京空气动力研究所, 北京 100074 |
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| 摘 要： | 绕弹体的超声速气流与发动机喷流相互作用,在尾部形成复杂的干扰流场。本文用有限差分法求解全N-S方程,对这一复杂流场进行了数值模拟,得到了实验观察到的各种流场结构及其随喷口压力比的变化规律。外流M∞=1.94,Re∞=2.2×105,喷流Mj=3.0,喷口压力比pj/p∞分别为1.03,0.527,0.15三种。差分算法为一种改进的Beam-Warming格式。计算底部压力和激波在喷流中心的反射位置与实验数据进行了比较,吻合较好。
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| 关 键 词： | 喷流 尾迹流动 数值模拟 |
| 收稿时间： | 1992-04-14 |
| 修稿时间： | 1992-12-21 |
NUMERICAL STUDY OF THE AXISYMMETRIC FLOW OVER A MISSILE AFTERBODY |
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| Zhou Weijiang,Ma Handong.NUMERICAL STUDY OF THE AXISYMMETRIC FLOW OVER A MISSILE AFTERBODY[J].Chinese Journal of Computational Physics,1993,10(4):422-428. |
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| Authors: | Zhou Weijiang Ma Handong |
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| Institution: | Beijing Institute of Aerodynamics, Beijing 100074 |
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| Abstract: | The interaction between supersonic external flow and an exhaust jet forms a complex flowfield region near the missile afterbody. In this paper, the research about this interaction flows was completed with finite-difference method to solve N-S equations. The flowfield structures observed in experiment and it's relation with jet pressure ratio pj/p∞ were obtained. For freestream, M∞=1.94, Re∞=2.2×105, for jet flow, Mj=3.0, three pj/p∞(1.03, 0.527 and 0.15) were selected. The numerical algorithm used is a modified Beam-Warming scheme. The nozzle base pressure coeficient and shock reflection length were compared with experimental data, good agreements were reached. |
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| Keywords: | jet flow wake flow numerical simulation |
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