高超声速流场等离子体逆向喷流减阻特性

doi:10.7527/S1000-6893.2022.27727

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高超声速流场等离子体逆向喷流减阻特性

张旭东¹^,², 李铮³, 董昊¹^,²(), 高思源¹^,², 纪祖赑³, 黎凯昕¹^,², 白光辉³

^1.南京航空航天大学航空学院，南京 210016
^2.南京航空航天大学非定常空气动力学与流动控制工业和信息化部重点实验室，南京 210016
^3.中国运载火箭技术研究院空间物理重点实验室，北京 100076

收稿日期:2022-06-30 修回日期:2022-07-29 接受日期:2022-08-25 出版日期:2022-12-25 发布日期:2022-08-31
通讯作者: 董昊 E-mail:donghao@nuaa.edu.cn
基金资助:
国家数值风洞工程(0747-2266SCCMY003);国家自然科学基金(11872208)

Drag reduction characteristics of opposing plasma synthetic jet in hypersonic flow

Xudong ZHANG¹^,², Zheng LI³, Hao DONG¹^,²(), Siyuan GAO¹^,², Zubi JI³, Kaixin LI¹^,², Guanghui BAI³

^1.College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
^2.Key Laboratory of Unsteady Aerodynamics and Flow Control，Ministry of Industry and Information Technology，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
^3.Science and Technology on Space Physics Laboratory，China Academy of Launch Vehicle Technology，Beijing 100076，China

Received:2022-06-30 Revised:2022-07-29 Accepted:2022-08-25 Online:2022-12-25 Published:2022-08-31
Contact: Hao DONG E-mail:donghao@nuaa.edu.cn
Supported by:
National Numerical Windtunnel Project(0747-2266SCCMY003);National Natural Science Foundation of China(11872208)

摘要/Abstract

摘要：

等离子体合成射流（PSJ）是指半封闭腔体内通过电弧放电产生的高温高速零质量射流，具有射流速度高、穿透能力强、响应速度快等优势，在高超声速飞行器流动控制方面具有极大的应用潜力。为研究等离子体合成射流对高超声速飞行器的流动控制和减阻效果，对马赫数6流场中的球头模型进行了数值模拟，研究表明：等离子体合成射流能显著改变脱体激波距离以及球头阻力特性，在放电后一个周期内，平均阻力下降可达37.67%，最大减阻效果可达76.03%，验证了等离子体合成射流对激波控制和流动减阻的效果，并分析了流场长短穿透模态的转换机制。

关键词: 高超声速, 等离子体合成射流（PSJ）, 逆向喷流, 流动控制, 减阻, 模态

Abstract:

Plasma Synthetic Jet （PSJ） is a high-temperature， high-speed and zero-net mass flux jet generated by arc discharge in a semi-closed cavity， with the advantages of high jet velocity， strong penetration ability and fast response， thus having significant application potential in the flow control of hypersonic vehicles. To study the flow control and drag reduction effect of the PSJ on hypersonic vehicles， we numerically simulate the bluff body model in the Mach 6 flow field. The results show that the PSJ can significantly change the shock wave distance and drag characteristics. Within a cycle after discharge， the average drag can be reduced by 37.67%， the maximum drag reduction effect can reach 76.03%， the effect of shock wave control and flow drag reduction by the PSJ is verified， and the conversion mechanism of the short penetration mode and long penetration mode of the flow field is analyzed.

Key words: hypersonic, Plasma Synthetic Jet (PSJ), opposing jet, flow control, drag reduction, mode

中图分类号:

V211

张旭东, 李铮, 董昊, 高思源, 纪祖赑, 黎凯昕, 白光辉. 高超声速流场等离子体逆向喷流减阻特性[J]. 航空学报, 2022, 43(S2): 115-123.

Xudong ZHANG, Zheng LI, Hao DONG, Siyuan GAO, Zubi JI, Kaixin LI, Guanghui BAI. Drag reduction characteristics of opposing plasma synthetic jet in hypersonic flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 115-123.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

半径/mm	最大减阻效果/%	平均减阻效果/%	控制时长/μs
1	28.75	10.80	736.6
2	62.81	16.26	474.6
3	73.92	37.58	294.5
4	76.03	37.67	253

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高超声速流场等离子体逆向喷流减阻特性

Drag reduction characteristics of opposing plasma synthetic jet in hypersonic flow

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