| 喷管尺寸对电弧风洞流场和热环境的影响分析 |
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| 引用本文： | 罗万清,梁剑寒,杨远剑,赵金山,孙海浩.喷管尺寸对电弧风洞流场和热环境的影响分析[J].宇航学报,2021,42(2):159-166. |
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| 作者姓名： | 罗万清 梁剑寒 杨远剑 赵金山 孙海浩 |
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| 作者单位： | 1. 国防科技大学高超声速冲压发动机技术重点实验室，长沙 410073；2. 中国空气动力研究与发展中心超高速空气动力研究所，绵阳 621000；3. 哈尔滨工业大学航天学院，哈尔滨 150080 |
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| 基金项目： | 国家自然科学基金（91641201） |
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| 摘 要： | 为获得电弧风洞喷管尺寸对试验流场以及模型表面热流的影响规律，针对某特定模拟参数试验状态，采用高焓流动数值模拟方法对不同尺寸锥形喷管下的球柱校核模型试验流场进行了模拟和比较分析。研究发现，在模拟气流焓值和模型驻点热流的条件下，采用出口尺寸小的喷管所需电弧加热功率更低，同时单位流向截面上气流能量转化为模型驻点气动热的比例更低。不同喷管出口尺寸下，试验流场喷管出口区域热力学非平衡程度、波后氧原子质量分数、模型驻点区域压力以及表面传导热流和扩散热流占比都比较接近，但相较飞行状态存在明显差异；不同喷管出口尺寸下来流速度、激波脱体距离以及驻点线上平动温度之间的差异明显，喷管出口尺寸越大，其与飞行状态越接近。
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| 关 键 词： | 喷管尺寸 电弧风洞 高焓流场 数值模拟 |
| 收稿时间： | 2020-05-28 |
Influence Analysis of Nozzle Size on Flowfield and
ThermalEnvironment in Archeated Wind Tunnel |
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| LUO Wan qing,LIANG Jian han,YANG Yuan jian,ZHAO Jin shan,SUN Hai hao.Influence Analysis of Nozzle Size on Flowfield and
ThermalEnvironment in Archeated Wind Tunnel[J].Journal of Astronautics,2021,42(2):159-166. |
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| Authors: | LUO Wan qing LIANG Jian han YANG Yuan jian ZHAO Jin shan SUN Hai hao |
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| Affiliation: | 1. Science and Technology on Scramjet Laboratory,
National University of Defense Technology, Changsha 410073, China;2.
Hypervelocity Aerodynamics Institute, China Aerodynamics Research and
Development Center, Mianyang 621000, China;3. School
of Astronautics, Harbin Institute of Technology, Harbin 150080, China |
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| Abstract: | In order to obtain the influence of nozzle size on the
test flowfield and the heat flux on the model surface in an arc heated
wind tunnel, the numerical simulation method is used to simulate and analyze
the high enthalpy flowfield of the spherical cylinder calibration model with
different sizes of conical nozzles for specific test parameters. The comparison
of the flowfield characteristics and the heat flux on the model surface reveals
that, under the condition of simulating enthalpy and stagnation point heat
flux, the nozzle with small exit size requires lower arc heating power, and the
ratio of airflow energy transferred to aerodynamic heat per unit section is
lower. At different nozzle exit sizes, the thermodynamic nonequilibrium degree
in the exit region, the mass fraction of oxygen atom after shock wave, the
pressure in the region near the stagnation point, and the proportion of
conduction heat flux and diffusion heat flux are all approximate, while with
any sizes of nozzles their differences between the ground experiment and the
flight are obvious. The difference between the inflow velocity, the stand off distance of shock wave and the translational temperature on the
stagnation line are obvious. The larger the nozzle exit size is, the more
similar they are to the flight condition. |
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