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文摘
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在钝体高焓流动中,热化学非平衡效应使膨胀区壁面压力显著低于冻结流动,相关研究表明,再压缩效应可以消除上述差异.为详细分析此问题,数值求解了Euler方程,化学反应源项采用有限速率模型并考虑了5个组分,17个基元反应.结果表明,随着再压缩角的增大,热化学非平衡效应引起锥面压力先降后增非单调变化,这是由于再压缩流场中放热复合反应与吸热分解反应的强度变化决定的,其宏观表现为比热比的空间不均衡分布. |
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其他语种文摘
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Thermo-chemical non-equilibrium effects may cause decrease in the surface pressure within the expansion region of a high-enthalpy blunt body flow as compared with a frozen flow. Research indicates that a recompression structure appended to the blunt body can eliminate the aforementioned difference. In the present study, a multi-component reactive Euler solver was applied to simulate the hypervelocity flow over a sphere-cone model. The numerical results show that thermo-chemical non-equilibrium induces a nonmonotonic variation to the conic surface pressure, i.e., it decreases first then increases as the recompression angle increases. The underlying mechanism for such a phenomenon is found to be the competing exothermal and endothermal reactions, which is macroscopically reflected by the inhomogeneity of the specific heat ratio in the recompression flowfield. |
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来源
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力学学报
,2015,47(2):346-350 【核心库】
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DOI
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10.6052/0459-1879-14-220
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关键词
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高焓流动
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热化学非平衡
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再压缩效应
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气动力规律
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不均衡分布
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地址
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中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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0459-1879 |
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学科
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航天(宇宙航行) |
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基金
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中国科学院知识创新工程重要方向项目
;
国家自然科学基金
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文献收藏号
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CSCD:5375702
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1.
姜宗林. 长试验时间爆轰驱动激波风洞技术研究.
力学学报,2012,44(5):824-831
|
CSCD被引
35
次
|
|
|
|
|
2.
Brauckmann G J. Experimental and computational analysis of the Space Shuttle Orbiter hypersonic pitch-up anomaly.
Journal of Spacecraft and Rockets,1995,32(5):758-764
|
CSCD被引
7
次
|
|
|
|
|
3.
李康. 高超声速流动上仰异常现象关键因素数值研究.
中国科学:物理学.力学.天文学,2014
|
CSCD被引
1
次
|
|
|
|
|
4.
Hirschel E H.
Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles,2009
|
CSCD被引
12
次
|
|
|
|
|
5.
Kodera M.
Comparison of re-entry flow computations with high enthalpy shock tunnel experiments. AIAA 2009-7305, 2009
|
CSCD被引
1
次
|
|
|
|
|
6.
Kliche D. The hypersonic Mach number independence principle in the case of viscous flow.
Shock Waves,2011,21(4):307-314
|
CSCD被引
3
次
|
|
|
|
|
7.
Miller J H.
Computational aerothermodynamic datasets for hypersonic heat transfer on reentry vehicles. AIAA 2005-5911,2005
|
CSCD被引
1
次
|
|
|
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