| Citation: | LI Junhong, MIAO Wenbo, SHEN Junmou, et al. Ground test and numerical simulation on high temperature non-equilibrium flow[J]. Journal of Aerospace Power, 2023, 38（11）：2574-2582 doi: 10.13224/j.cnki.jasp.20220243
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Because of the insufficiency of numerical simulation and test verification of high temperature non-equilibrium flow status, the high temperature flow field ground test simulation technology and display technology in high enthalpy shock wave wind tunnel were developed respectively. The ground tests of high temperature non-equilibrium flows were carried out in FD-21 high enthalpy shock wave wind tunnel and FD-20 normal shock wave wind tunnel, then the spatial flow field structure and the aerodynamic heating results of the test hemisphere were obtained. Meanwhile, the numerical simulation technology of high altitude and hypersonic thermochemical non-equilibrium flow was established for the supersonic flight environment, and the reliability of the calculation method was verified by the ground test. The test models were of a hemisphere structure with radius of 20 mm and 60 mm. The calculation results showed that: (1) The inlet flow parameters in the wind tunnel were verified by numerical simulation and the pressure and species can be taken as input parameters for the below numerical simulation. (2) Numerical simulations were carried out on the above typical hemispheres, and the test and calculation results of the hemisphere heat flux were compared and analyzed. The results showed that the two-temperature model (thermal chemical non-equilibrium model-2T) was in good agreement with the test. Under the condition of non-catalytic wall, the relative error between the calculated heat flux result of 2T model and the test result was 11.6% when the total temperature was 2700 K. The relative error was 17.5% when the total temperature was 4050 K. (3) The test schlieren (hemisphere shock wave off distance) obtained from the calculated results was in good agreement with each other. Under the condition of non-catalytic wall, the relative error between the shock wave off distance and schlieren of 2T model was −1.9%−0.86%.
| [1] |
欧阳水吾, 谢中强. 高温非平衡空气绕流[M]. 北京: 国防工业出版社, 2001.
|
| [2] |
柳军,刘伟,曾明,等. 高超声速三维热化学非平衡流场的数值模拟[J]. 力学学报,2003,35(6): 730-734. doi: 10.3321/j.issn:0459-1879.2003.06.011
LIU Jun,LIU Wei,ZENG Ming,et al. Numerical simulation of 3D hypersonic thermochemical nonequilibrium flow[J]. Acta Mechanica Sinica,2003,35(6): 730-734. (in Chinese) doi: 10.3321/j.issn:0459-1879.2003.06.011
|
| [3] |
OLYNICK D, CHEN Y K, TAUBER M, et al. Wake flow calculations with ablation for the Stardust Sample Return Capsule[R]. AIAA1997-2477, 1997.
|
| [4] |
MCNEIL C F, PETER A. User’s manual for the langley aerothermodynamic upwind relaxation algorithm (LAURA) [R]. NASA-TM-4674, 1996
|
| [5] |
SRINIVASAN S, BITTNER R, BOBSKILL G J. Summary of the GASP code application and evaluation effort for scramjet combustor flowfields[R]. AIAA-93-1973, 1993
|
| [6] |
欧阳水吾,谢中强. 非平衡化学反应流场NS方程计算研究[J]. 计算物理,1997,14(1): 6-12. doi: 10.19596/j.cnki.1001-246x.1997.01.002
OUYANG Shuiwu,XIE Zhongqiang. Navier stokes computation of nonequilibrium chemically reacting flowfields[J]. Chinese Journal of Computation Physics,1997,14(1): 6-12. (in Chinese) doi: 10.19596/j.cnki.1001-246x.1997.01.002
|
| [7] |
黄华,瞿章华. 11组元轴对称热化学非平衡流场的数值研究[J]. 空气动力学学报,1999,17(4): 462-465. doi: 10.3969/j.issn.0258-1825.1999.04.015
HUANG Hua,QU Zhanghua. Numerical study for symmetric thermochemical nonequilibriumflowfield with eleven species air model[J]. Acta Aerodynamica Sinica,1999,17(4): 462-465. (in Chinese) doi: 10.3969/j.issn.0258-1825.1999.04.015
|
| [8] |
董维中,高铁锁,丁明松. 高超声速非平衡流场多个振动温度模型的数值研究[J]. 空气动力学学报,2007,25(1): 1-6. doi: 10.3969/j.issn.0258-1825.2007.01.001
DONG Weizhong,GAO Tiesuo,DING Mingsong. Numerical studies of the multiple vibrational temperature model in hypersonic non-equilibrium flows[J]. Acta Aerodynamica Sinica,2007,25(1): 1-6. (in Chinese) doi: 10.3969/j.issn.0258-1825.2007.01.001
|
| [9] |
GRANTHAM W. Flight results of a 25 000-foot-per-second reentry experiment using microwave reflectometers to measure plasma electron density and standoff distance[R]. NASA TND-6062, 1970
|
| [10] |
周禹. 高超声速热化学非平衡流场数值模拟研究[D]. 北京: 北京航空航天大学, 2009.
ZHOU Yu. Numerical simulation of hypersonic thermal and chemical non-equilibrium flowfields[D]. Beijing: Beihang University, 2009. (in Chinese)
|
| [11] |
GNOFFO P, GUPTA R, SHINN J. Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium[R]. NASA TP-2867, 1989
|
| [12] |
周靖云. 高超声速热化学非平衡等离子体流场数值模拟[D]. 北京: 中国航天空气动力技术研究院, 2020.
ZHOU Jingyun. Numerical simulation of thermochemical non-equilibrium hypersonic plasma flow[D]. Beijing: China Academy of Aerospace Aerodynamics, 2020. (in Chinese)
|
| [13] |
FURUMOTO G H,ZHONG Xiaolin,SKIBA J C. Numerical studies of real-gas effects on two-dimensional hypersonic shock-wave/boundary-layer interaction[J]. Physics of Fluids,1997,9(1): 191-210. doi: 10.1063/1.869162
|
| [14] |
董维中. 热化学非平衡效应对高超声速流动影响的数值计算与分析[D]. 北京: 北京航空航天大学, 1996.
DONG Weizhong. Numerical calculation and analysis of the influence of thermochemical non-equilibrium effect on hypersonic flow[D]. Beijing: Beihang University, 1996. (in Chinese)
|
| [15] |
GUPTA R, YOS J, THOMPSON R A. A review of reaction rates and thermodynamic and transport properties for the 11-species air model for chemical and thermal nonequilibrium calculations to 30 000 K[R]. NASA-TM-101528, 1989
|
| [16] |
汪球,赵伟,滕宏辉,等. 高焓激波风洞喷管流场非平衡特性研究[J]. 空气动力学学报,2015,33(1): 66-71.
WANG Qiu,ZHAO Wei,TENG Honghui,et al. Numerical simulation of non-equilibrium characteristics of high enthalpy shock tunnel nozzle flow[J]. Acta Aerodynamica Sinica,2015,33(1): 66-71. (in Chinese)
|
| [17] |
PARK C. Assessment of two-temperature kinetic model for ionizing air[R]. AIAA 1987-1574, 1987.
|
| [18] |
苗文博,罗晓光,程晓丽,等. 壁面催化对高超声速飞行器气动特性影响[J]. 空气动力学学报,2014,32(2): 235-239. doi: 10.7638/kqdlxxb-2012.0096
MIAO Wenbo,LUO Xiaoguang,CHENG Xiaoli,et al. Surface recombination effects on aerodynamic loads of hypersonic vehicles[J]. Acta Aerodynamica Sinica,2014,32(2): 235-239. (in Chinese) doi: 10.7638/kqdlxxb-2012.0096
|
| [19] |
LIOU M S. A further development of the AUSM+ scheme towards robust and accurate solutions for all speeds[R]. AIAA 2003-4116, 2003.
|
| [20] |
SAPPEY A, SUTHERLAND L, OWENBY D, et al. Flight-ready TDLAS combustion sensor for the HIFiRE 2 hypersonic research program[R]. Arnold Engineering Development Center AEDC-TR-10-T-6, 2009
|
| [21] |
王保国,李翔. 多工况下高超声速飞行器再入时流场的计算[J]. 西安交通大学学报,2010,44(1): 71-76.
WANG Baoguo,LI Xiang. Prediction of hypersonic vehicle reentry flowfields in multiple cases[J]. Journal of Xi’an Jiaotong University,2010,44(1): 71-76. (in Chinese)
|
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