冲压发动机进气道掺混段与弹体内外流场一体化数值模拟  

The integrated computational simulation of the inner and outer flow fields above the athodyd inlet/firebox and missile body

作　　者：白鹏[1] 朱守梅[2] 孟宇鹏[2] 李稳绪[2] 马汉东[1] 周伟江[1] 

机构地区：[1]北京空气动力研究所,北京100074 [2]航天科工集团第31研究所,北京100074

出　　处：《空气动力学学报》2005年第1期5-9,共5页Acta Aerodynamica Sinica

摘　　要：采用二阶迎风隐式TVD格式分区求解可压缩N S方程 ,数值模拟了导弹、进气道和掺混段内外流一体化通气模型的复杂流场。本文给出了掺混段出口压力与来流压力比为P/P∞ =3.5 ,4 .2和 4 .9情况的数值模拟结果。并分析了流场特性及激波波系结构 ,总压恢复系数σ和流量系数 φ。同风洞试验结果进行比较 ,表明计算结果是合理的。The second order upwind implicit TVD scheme is used to solve the compressible N-S equations for integrated simulating the complex flowfields above the missile body, athodyd inlet and firebox. The computational results of the pressure ratio between firebox exit and freefield P/P_∞=3.5,4.2 and 4.9 were given in this paper. The characters of the flowfields and the structure of the shock are analyzed. The total pressure recovery coefficient σ and the flow coefficient φ were also obtained. Comparing with the results of the experiment, the conclusion is drawn that the results of the computational simulations are reasonable. The transaction of boundary condition of the multi-zone computation is described in the paper.

关 键 词：进气道 冲压发动机 总压恢复系数 N—S方程 TVD格式 弹体 复杂流场 二阶 隐式 激波 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V430