Ballistic range measurement and numerical calculation of shock standoff distances in CO<sub>2</sub>

Liao Dongjun; Liu Sen; Huang Jie; Jian Hexiang; Xie Aimin; Wang Zonghao

doi:10.11729/syltlx20170157

Volume 32 Issue 3

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2018 > 32(3): 69-74, 93

Liao Dongjun, Liu Sen, Huang Jie, et al. Ballistic range measurement and numerical calculation of shock standoff distances in CO2[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 69-74, 93. doi: 10.11729/syltlx20170157

Citation:

Liao Dongjun, Liu Sen, Huang Jie, et al. Ballistic range measurement and numerical calculation of shock standoff distances in CO₂[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 69-74, 93. doi: 10.11729/syltlx20170157

Citation:

PDF( 6045 KB)

Ballistic range measurement and numerical calculation of shock standoff distances in CO₂

doi: 10.11729/syltlx20170157

China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2017-12-07
Rev Recd Date: 2018-04-26
Publish Date: 2018-06-25

Abstract

Abstract

Measurement of shock standoff distances over spheres and the Mars entry vehicle model in CO₂ has been conducted in the hypervelocity ballistic range of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center. Test models were spheres with the diameter of 10mm and entry vehicle models with the nose radius of 12.5mm. For spheres, the flight velocities were between 2.122 and 4.220km/s with ambient pressures between 2.42 and 12.3kPa. For the entry vehicle model, the flight velocity was 2.802km/s with the ambient pressure of 1.836kPa. Comparison was made between the test data and calculated results using the two-temperature nonequilibrium model. Under present test conditions, the two-temperature nonequilibrium model can basically reproduce the shock standoff distances over the test models. The flow over the test models is speculated to be mainly nonequilibrium. More test data with higher flight velocities (>5km/s) are needed for the validation of the two-temperature nonequilibrium model in CO₂ with higher freestream velocity. The influence of multi-temperature models and different chemical reaction models on the accuracy of the numerical simulation for the nonequlilbirum flow in CO₂ can be further studied.
- nonequilibrium,
- shock standoff distance,
- ballistic range experiment,
- two-temperature model,
- CO₂

FullText(HTML)

References(19)

References

[1]	韩鸿硕, 陈杰. 21世纪国外深空探测发展计划及进展[J].航天器工程, 2008, 17(3):1-22. http://d.old.wanfangdata.com.cn/Periodical/htqgc200803001 Han H S, Chen J. 21st century foreign deep space exploration development plans and their progresses[J]. Spacecraft Engineering, 2008, 17(3):1-22. http://d.old.wanfangdata.com.cn/Periodical/htqgc200803001
[2]	廖东骏, 柳森, 简和祥, 等.高超声速球头激波脱体距离研究综述[J].实验流体力学, 2015, 29(6):1-7. http://www.syltlx.com/CN/abstract/abstract10882.shtml Liao D J, Liu S, Jian H X, et al. A review of hypersonic sphere shock standoff distance research[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(6):1-7. http://www.syltlx.com/CN/abstract/abstract10882.shtml
[3]	Park C. The limits of two-temperature model[R]. AIAA-2010-911, 2010.
[4]	Nonaka S, Mizuno H, Takayama K, et al. Measurement of shock standoff distance for sphere in ballistic range[J]. Journal of Thermophysics and Heat Transfer, 2000, 14(2):225-229. doi: 10.2514/2.6512
[5]	柳军, 乐嘉陵, 杨辉.高超声速圆球模型飞行流场的数值模拟和实验验证[J].流体力学实验与测量, 2002, 16(1):67-73. doi: 10.3969/j.issn.1672-9897.2002.01.011 Liu J, Le J L, Yang H. Numerical simulation of hypersonic flowfield around sphere model and experimental verification[J]. Experiments and Measurements in Fluid Mechanic, 2002, 16(1):67-79. doi: 10.3969/j.issn.1672-9897.2002.01.011
[6]	Zander F, Gollan R J, Jacobs P A, et al. Hypervelocity shock standoff on spheres in air[J]. Shock Wave, 2014, 14:171-178. doi: 10.1007/s00193-013-0488-x
[7]	史建魁, 张仲谋, 刘振兴, 等.火星环境探测结果分析[J].地球物理学进展, 1997, 12(4):98-108. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK199700941240 Shi J K, Zhang Z M, Liu Z X, et al. An analysis of results of the Martian environment exploration[J]. Progress in Geophysics, 1997, 12(4):98-108. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK199700941240
[8]	MacClean M, Holden M. Catalytic effects on heat transfer measurements for aerothermal studies with CO₂[R]. AIAA-2006-0182, 2006. http://www.researchgate.net/publication/268564464_catalytic_effects_on_heat_transfer_measurements_for_aerothermal_studies_with_co2
[9]	Doraiswamy S, Kelley D, Candler V G. Vibrational modeling of CO₂ in high-enthalpy nozzle Flow[J]. Journal of thermophysics and heat transfer, 2010, 24(1):9-17. doi: 10.2514/1.43280
[10]	MacLean M, Dufrene A, Holden M. Spherical capsule heating in high enthalpy carbon dioxide in LENS-XX expansion tunnel[R]. AIAA-2013-0906, 2013. http://www.researchgate.net/publication/268468442_Spherical_Capsule_Heating_in_High_Enthalpy_Carbon_Dioxide_in_LENS-XX_Expansion_Tunnel
[11]	Sharma S P, Park C. Survey of simulation and diagnostic techniques for hypersonic nonequilibrium flows[J]. Journal of Thermophysics and Heat Transfer, 1990, 4(2):129-142. doi: 10.2514/3.155
[12]	柳森, 王宗浩, 谢爱民, 等.高超声速锥柱裙模型边界层转捩的弹道靶实验[J].实验流体力学, 2013, 27(6):26-31. doi: 10.3969/j.issn.1672-9897.2013.06.005 Liu S, Wang Z H, Xie A M, et al. Ballistic range experiments of hypersonic boundary layer transition on a cone-cylinder-flare configuration[J]. Journal of Experiments in Fluid Dynamics, 2013, 27(6):26-31. doi: 10.3969/j.issn.1672-9897.2013.06.005
[13]	Park C. Assessment of two-temperature kinetic model for dissociating and weakly-ionizing nitrogen[J]. Journal of Thermophysics and Heat Transfer, 1988, 2(1):8-16. doi: 10.2514/3.55
[14]	Kay R D, Netterfield M P. Thermochemical non-equilibrium computations for a Mars entry vehicle[R]. AIAA-93-2841, 1993. doi: 10.2514/6.1993-2841
[15]	Suzuki K, Abe T. Thermochemical nonequilibrium viscous shock-layer analysis for a Mars aerocapture vehicle[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(4):773-780. doi: 10.2514/3.611
[16]	Furudate M, Suzuki T, Takayanagi H, et al. Three-dimensional aerodynamics study for Mars aeroshellin nonequilibrium flow[R]. AIAA-2010-4647, 2010. doi: 10.2514/6.2010-4647
[17]	柳森, 黄洁, 李毅, 等.中国空气动力研究与发展中心的空间碎片超高速撞击试验研究进展[J].载人航天, 2011, 17(6):17-23. doi: 10.3969/j.issn.1674-5825.2011.06.004 Liu S, Huang J, Li Y, et al. Recent advancement of hypervelocity impact tests at HAI[J]. Journal of Manned Spacecraft, 2011, 17(6):17-23. doi: 10.3969/j.issn.1674-5825.2011.06.004
[18]	Park C, Howe J, Jaffe R, et al. Review of chemical-kinetic problems of future NASA missions, Ⅱ:Mars entries[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(1):9-23. doi: 10.2514/3.496
[19]	董维中.气体模型对高超声速再入钝体气动参数计算影响的研究[J].空气动力学学报, 2001, 19(2):197-202. doi: 10.3969/j.issn.0258-1825.2001.02.010 Dong W Z. Thermal and chemical model effect on the calculation of aerodynamic parameter for hypersonic reentry blunt body[J]. Acta Aerodynamica Sinica, 2001, 19(2): 197-202. doi: 10.3969/j.issn.0258-1825.2001.02.010