Ballistic range measurement and numerical calculation of shock standoff distances in CO2
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摘要: 在中国空气动力研究与发展中心超高速所超高速弹道靶进行了CO2条件下圆球和火星着陆巡视器模型的激波脱体距离测量实验，为数值模拟提供验证依据。实验模型为φ10mm圆球和头部半径12.5mm的着陆巡视器模型。圆球模型的飞行速度为2.122~4.220km/s，靶室压力为2.42~12.30kPa；着陆巡视器模型的飞行速度为2.802km/s，对应靶室压力为1.836kPa。实验数据与采用双温度非平衡模型计算的结果进行了对比。得到以下结论：采用双温度非平衡模型能够较准确地再现模型头部激波脱体距离；根据计算结果推测绕模型流动主要为非平衡流动；需补充更高模型飞行速度（>5km/s）的实验数据，验证CO2中更高流速状态下双温度非平衡模型的适用性与准确性，并进一步研究多温度模型和不同化学反应动力模型对CO2下非平衡流数值计算准确性的影响。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.
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Key words:
- nonequilibrium /
- shock standoff distance /
- ballistic range experiment /
- two-temperature model /
- CO2
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图 5 圆球激波脱体距离测量方法示例
Figure 5. Schematic of the measurement method of the shock standoff distance
图 7 实验C10-1阴影图像(D=10mm，V=2.122km/s，p=12.300kPa，ρR=1.1×10-3kg/m2)
Figure 7. Shadowgraph of the test C10-1
图 9 计算密度云图与实验阴影图像对比
Figure 9. Comparison between the shadowgraph and the calculated density contour
图 10 模型头部激波脱体距离实验数据与计算结果的对比
Figure 10. Comparison between the tested and the calculated shock standoff distances at the models' nose
图 11 实验C10-1脱体激波形状和对应的计算结果对比
Figure 11. Comparison between the tested and the corresponding calculated shock shape of the test C10-1
图 12 C10-1状态下模型驻点线上平动、振动温度分布计算结果
Figure 12. Calculated translational and vibrational temperature distributions along the stagnation line of the model under the condition of C10-1
表 1 模型头部激波脱体距离测量数据和对应实验状态
Table 1. Shock standoff distances at the spheres' nose under various test conditions
编号 模型直径
D/mm飞行速度
V/(km·s-1)靶室压力
p/kPa靶室温度
T/K马赫数
Ma雷诺数
Re*双尺度参数
ρR/(kg·m-2)无量纲激波脱体距离
δ/R测量误差
E/RC10-1 10 2.122 12.300 292.1 7.6 3.2×105 1.1×10-3 0.0795 ±3.89% C10-2 10 2.845 7.425 293.2 10.2 2.6×105 6.7×10-4 0.0705 ±4.37% C10-3 10 4.220 2.420 293.7 15.1 1.2×105 2.2×10-4 0.0618 ±4.88% *雷诺数以直径10mm计。 
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表 2 着陆巡视器头部激波脱体距离测量数据和对应实验状态
Table 2. Shock standoff distances at the entry vehicle models' nose under various test conditions
编号 头部半径
Rn/mm飞行速度
V/(km·s-1)靶室压力
p/kPa靶室温度
T/K马赫数
Ma雷诺数
Re*双尺度参数
ρRn/(kg·m-2)无量纲激波脱体距离
δ/Rn测量误差
E/RnC10-4 12.5 2.802 1.836 294.7 10.0 1.6×105 4.1×10-4 0.0623 ±8.34% *雷诺数以大底直径25mm计。
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表 3 模型头部激波脱体距离实验数据与计算结果对比
Table 3. Comparison between tested and the calculated shock standoff distances at the models' nose
编号 激波脱体距离实验值δ/R(δ/Rn) 测量误差E/R 激波脱体距离计算值δ/R(δ/Rn) 计算结果相对实验数据偏差 C10-1 0.0795 ±3.89% 0.0783 -1.51% C10-2 0.0705 ±4.37% 0.0676 -4.11% C10-3 0.0618 ±4.88% 0.0596 -3.56% C10-4 0.0623 ±8.34% 0.0607 -2.57%
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[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/htqgc200803001Han 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.shtmlLiao 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.1672-9897.2002.01.011Liu 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=QK199700941240Shi 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.1672-9897.2013.06.005Liu 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.1674-5825.2011.06.004Liu 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.0258-1825.2001.02.010Dong 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 -
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