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| 不同热化学非平衡模型对高超声速喷管流场影响的数值分析 | |
| 引用本文： | 曾明,杭建,林贞彬,瞿章华.不同热化学非平衡模型对高超声速喷管流场影响的数值分析[J].空气动力学学报,2006,24(3):346-349. |
| 作者姓名： | 曾明 杭建 林贞彬 瞿章华 |
| 作者单位： | 1. 中国科学院力学研究所,高温气体动力学重点实验室,北京,100080;国防科学技术大学,航天与材料工程学院,湖南,长沙,410073 2. 中国科学院力学研究所,高温气体动力学重点实验室,北京,100080 3. 国防科学技术大学,航天与材料工程学院,湖南,长沙,410073 |
| 摘 要： | 采用轴对称NS方程,数值研究不同热化学非平衡模型对高超声速喷管流场的影响,包括:(1)不同组元数的高温空气模型(5组元、7组元1、1组元)的比较;(2)热力非平衡(双温度)的化学动力过程与热力平衡(单温度)的化学动力过程的比较。计算结果表明,高焓风洞实验条件下喷管流场处于热力和化学都是非平衡的状态。在计算条件下,数值模拟以采用7组元或11组元的热化学非平衡模型为宜。 |
| 关 键 词： | 高超声速 热化学模型 非平衡流 喷管流 |
| 文章编号： | 0258-1825（2006）03-0346-04 |
| 收稿时间： | 2005-08-21 |
| 修稿时间： | 2005-08-212005-11-05 |
Numerical analysis of the effects of different thermo-chemical nonequilibrium models on hypersonic nozzle flow |
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| ZENG Ming,HANG Jian,LIN Zhen-bin,QU Zhang-hua.Numerical analysis of the effects of different thermo-chemical nonequilibrium models on hypersonic nozzle flow[J].Acta Aerodynamica Sinica,2006,24(3):346-349. | |
| Authors: | ZENG Ming HANG Jian LIN Zhen-bin QU Zhang-hua |
| Institution: | 1. Key Laboratory of High Temperature Dynamics, Inst. of Mechanlcs, Chinese Academy of Sciences, Beijing 100080, China 2. College of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China |
| Abstract: | Using axisymmetric full Navier-Stokes equations,the effects of different thermo-chemical nonequilibrium air models on the hypersonic nozzle flow are analyzed numerically.They include(1) the comparision of different high temperature air models(5 species,7 species and 11 species);(2) the comparision of chemical nonequilibrium flow with thermo-nonequilibrium(two temperature model) and thermo-equilibrium(one temperature model).The results show that the flow tends to be in thermo and chemical frozen not far from throat.7 species or 11 species thermochemical nonequilibrium model should be taken for such situation. |
| Keywords: | hypersonic thermo-chemical model nonequilibrium flow nozzle flow |
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