等离子体合成射流对钝头激波的控制与减阻

doi:10.7527/S1000-6893.2020.24773

流体力学与飞行力学

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等离子体合成射流对钝头激波的控制与减阻

陈加政¹, 胡国暾², 樊国超¹, 陈伟芳¹

1. 浙江大学航空航天学院, 杭州 310027;
2. 中国运载火箭技术研究院研究发展中心, 北京 100076

收稿日期:2020-09-21 修回日期:2020-09-30 发布日期:2020-11-27
通讯作者: 陈伟芳 E-mail:chenwfnudt@163.com
基金资助:
国家自然科学基金（6162790014）

Bow shock wave control and drag reduction by plasma synthetic jet

CHEN Jiazheng¹, HU Guotun², FAN Guochao¹, CHEN Weifang¹

1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;
2. Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2020-09-21 Revised:2020-09-30 Published:2020-11-27
Supported by:
National Natural Science Foundation of China (6162790014)

摘要/Abstract

摘要： 为了验证等离子体合成射流对超声速流动的流动控制和减阻效果，在考虑热完全气体效应的情况下，工程拟合等离子体热力学属性和输运系数，利用能量源项模型对超声速平板和球头等典型流场结构进行了数值模拟，并取得了与实验较为一致的结果。研究结果表明：对于马赫数为2的超声速平板流动，等离子体合成射流能有效干扰边界层的发展，并诱导产生一系列大尺度结构；对于马赫数为3的球头流场，等离子体合成射流能显著改变激波脱体距离与球头的阻力特性；在放电后第1个周期内，合成射流能使球头平均阻力降低6.3%，而在射流峰值情况下使阻力降低32.0%，激波脱体距离增加2倍，实现了激波控制和流动减阻的预期效果。

关键词: 等离子体合成射流, 能量源项模型, 超声速流, 流动控制, 减阻

Abstract: To verify the flow control and drag reduction effects of plasma synthetic jets on supersonic flows, we fit the plasma thermodynamic properties and transport coefficients in the case of considering the thermally perfect gas effect, and use the energy source term model to simulate the typical flow field structures such as the supersonic flat plate and sphere, yielding consistent results with those of the experiment. The results show that the plasma synthetic jet can effectively disturb the development of the boundary layer and induce a series of large-scale structures for a supersonic flow of Mach number 2 over a plate; for a supersonic flow of Mach number 3 over a sphere, the plasma synthetic jet can significantly change the shock separation distance and the drag of the sphere. In the first cycle after discharge, the average drag of the sphere can be reduced by 6.3%, while the drag is reduced by 32.0% when the jet reaches a peak value, and the shock separation distance is increased by two times, realizing the expected effect of shock control and drag reduction.

Key words: plasma synthetic jet, energy source term model, supersonic flow, flow control, drag reduction

中图分类号:

V211.3

陈加政, 胡国暾, 樊国超, 陈伟芳. 等离子体合成射流对钝头激波的控制与减阻[J]. 航空学报, 2021, 42(7): 124773-124773.

CHEN Jiazheng, HU Guotun, FAN Guochao, CHEN Weifang. Bow shock wave control and drag reduction by plasma synthetic jet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124773-124773.

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E-mail：hkxb@buaa.edu.cn

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等离子体合成射流对钝头激波的控制与减阻

Bow shock wave control and drag reduction by plasma synthetic jet

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