| 旁侧四超声速进气道弹体内外流一体化数值研究 |
| |
| 引用本文： | 孟宇鹏,闫晓娜,朱守梅.旁侧四超声速进气道弹体内外流一体化数值研究[J].战术导弹技术,2008(5). |
| |
| 作者姓名： | 孟宇鹏 闫晓娜 朱守梅 |
| |
| 作者单位： | 中国航天科工集团第三研究院31所; |
| |
| 摘 要： | 以数值模拟为主要手段,通过求解雷诺时均方程,分别对弹体外流场的流动特性以及四个二元旁侧超声速进气道与弹体、燃烧室一体化内外流动特性进行了计算研究.通过对典型飞行状态的计算,获得了进气道的总压恢复系数、流量系数随马赫数的变化关系以及随攻角的变化关系.对计算结果和部分试验结果进行了比较,获得的进气道总压恢复系数和试验值较为接近,计算流量系数稍高于试验值.进气道速度特性、攻角特性与试验变化基本一致,规律性明显.
|
| 关 键 词： | 飞航导弹 冲压发动机 超声速进气道 计算流体动力学 |
Numerical Investigation into Integrated External Flow around Missile Body and Internal Flow for Four Supersonic Inlets |
| |
| Meng Yupeng,Yan Xiaona,Zhu Shoumei.Numerical Investigation into Integrated External Flow around Missile Body and Internal Flow for Four Supersonic Inlets[J].Tactical Missile Technology,2008(5). |
| |
| Authors: | Meng Yupeng Yan Xiaona Zhu Shoumei |
| |
| Affiliation: | Meng Yupeng,Yan Xiaona,Zhu Shoumei(The 31 Research Academy,CASIC,Beijing 100074,China) |
| |
| Abstract: | A simulation has been conducted to study the body external flow field and internal flow field in ramjet combustor and 4 supersonic rectangle inlet which locates on missile-body.Numerical simulations have been performed with a Reynolds-averaged Navier-Stokes.The results reveal the relationship between the inlet performance,flight velocity and pitch angle,such as total pressure recovery coefficient and flow coefficient which changed with the change of Mach number.Lastly,the results comparison between CFD and ... |
| |
| Keywords: | aerodynamic missile ramjet supersonic inlet computing fluid dynamics |
| 本文献已被 CNKI 等数据库收录！ |
|
