| CO2中激波脱体距离的弹道靶实验测量和数值计算 |
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| 引用本文： | 廖东骏,柳森,黄洁,简和祥,谢爱民,王宗浩.CO2中激波脱体距离的弹道靶实验测量和数值计算[J].实验流体力学,2018,32(3):69. |
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| 作者姓名： | 廖东骏 柳森 黄洁 简和祥 谢爱民 王宗浩 |
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| 作者单位： | 中国空气动力研究与发展中心, 四川 绵阳 621000 |
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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。
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| 关 键 词： | 非平衡 激波脱体距离 弹道靶实验 双温度模型 CO2 |
| 收稿时间： | 2017-12-07 |
Ballistic range measurement and numerical calculation of shock standoff distances in CO2 |
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| Affiliation: | China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China |
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| 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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