高超声速流动上仰异常现象关键因素数值研究
Numerical studies on the effect of the key parameter to hypersonic “pitch-up anomaly”
查看参考文献22篇
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文摘
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高温真实气体效应所引起气体比热比γ的降低被认为是导致航天飞机"上仰异常"的主要原因.为详细研究此问题,本文数值求解了Euler方程,化学反应源项采用有限速率模型,考虑了5个组分、17个基元反应.研究结果表明采用低比热比气体CF4作为实验气体会导致膨胀区的压力分布与真实气体效应的影响规律不一致,并不能反映出"上仰异常"现象的本质.在高温真实气体效应的影响下,化学反应所带来的影响大于振动激发的影响,对于y方向半模压力积分Cay来说是3.8倍,而对于半模力矩积分系数Cam来说是1.7倍.对比分析表明,热化学反应导致的比热比分布不均衡是导致"上仰异常"现象出现的根本原因. |
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其他语种文摘
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Real-gas effects, e.g., vibrational excitation, dissociation and ionization of air, are critical issues in the hypervelocity flow around a reentry vehicle. In this work, a chemical and thermal nonequilibrium Euler solver is used to evaluate the real-gas effects on the aerodynamic forces of a typical hypervelocity test model. It is found that using an inert gas model with a lower specific heat ratio to simulate the real-gas effects may cause an under prediction of the forces and the pitching moment. Comparative simulations indicate that dissociation results in much more significant difference to the aerodynamic performance than the vibrational excitation. It is also found that the streamwise inhomogeneity of chemistry in the flowfield instead of the decreased specific heat ratio is the primary reason of “Pitch-up anomaly”. |
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来源
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中国科学. 物理学
, 力学, 天文学,2015,45(3):034701-1-034701-14 【核心库】
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DOI
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10.1360/sspma2014-00137
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关键词
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高超声速流动
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上仰异常
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真实气体效应
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比热比
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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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1674-7275 |
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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
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文献收藏号
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CSCD:5374925
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参考文献 共
22
共2页
|
|
1.
Giuseppe P.
Finite Rate Chemistry Effects on the High Altitude Aerodynamic of An Apollo-Shaped Reentry Capsule,2009
|
被引
1
次
|
|
|
|
|
2.
Park C.
Validation of CFD Codes for Real-Gas Regime,1997
|
被引
1
次
|
|
|
|
|
3.
Mundt C.
Calculation of Hypersonic, Viscous, Nonequilibrium Flows Around Reentry Bodies Using A Coupled Boundary Layer/Euler Method,1992
|
被引
1
次
|
|
|
|
|
4.
Ernst H H.
Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles,2009
|
被引
2
次
|
|
|
|
|
5.
Compton H R.
Stability and control over the supersonic and hypersonic speed range. Conference Paper,1983
|
被引
1
次
|
|
|
|
|
6.
Brauckmann G J. Experimental and computational analysis of the space shuttle orbiter hypersonic pitch-up anomaly.
J Spacecr Rockets,1995,32(5):758-764
|
被引
7
次
|
|
|
|
|
7.
Muylaert J.
Extrapolation from Wind Tunnel to Flight: Shuttle Orbiter Aerodynamics. Technical Report,1998
|
被引
3
次
|
|
|
|
|
8.
Griffith B J.
Explanation of the hypersonic longitudinal stability problem lessons learned. Conference Paper,1983
|
被引
1
次
|
|
|
|
|
9.
Romere P O.
Space shuttle entry longitudinal aerodynamic comparison of flights 1-4 with preflight predictions. Conference Paper,1983
|
被引
1
次
|
|
|
|
|
10.
Galloway R L.
Real Gas Simulation for the Shuttle Orbiter and Planetary Entry Configurations Including Flight Results. Technical Report,1984
|
被引
1
次
|
|
|
|
|
11.
Gnoffo P A.
Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium. Technical Report,1989
|
被引
1
次
|
|
|
|
|
12.
Dunn M G.
Theoretical and experimental studies of reentry plasmas. Technical Report,1973
|
被引
1
次
|
|
|
|
|
13.
Chul P. Nonequilibrium hypersonic aerothermodynamics.
Phys Tod,1991,42(2):98
|
被引
1
次
|
|
|
|
|
14.
Millikan R C. Systematics of vibrational relaxation.
J Chem Phys,1963,39:3209-3213
|
被引
20
次
|
|
|
|
|
15.
White F A.
Viscous Fluid Flow,1974
|
被引
1
次
|
|
|
|
|
16.
Seokkwan Y. Lower-Upper Symmetric-Gauss-Seidel method for the Euler and Navier-Stokes equations.
AIAA J,1988,26:1025-1026
|
被引
155
次
|
|
|
|
|
17.
Kim K H. Methods for the accurate computations of hypersonic flows I.
J Comput Phys,2001,174:38-80
|
被引
76
次
|
|
|
|
|
18.
Kim K H. An improvement of AUSM schemes by introducing the pressure-based weight functions.
Comput Fluids,1998,27(3):311-346
|
被引
19
次
|
|
|
|
|
19.
Keiichi K. Evaluation of Euler flux for hypersonic heating computations.
AIAA J,2010,48(4):763-776
|
被引
2
次
|
|
|
|
|
20.
Kliche D. The hypersonic Mach number independence principle in the case of viscous flow.
Shock Waves,2011,21:307-314
|
被引
3
次
|
|
|
|
|
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