超临界机翼介质阻挡放电等离子体流动控制

doi:10.7527/S1000-6893.2016.0015

流动控制

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超临界机翼介质阻挡放电等离子体流动控制

张鑫¹, 黄勇², 王勋年², 王万波², 唐坤², 李华星¹

1. 西北工业大学航空学院, 西安 710072;
2. 中国空气动力研究与发展中心, 绵阳 621000

收稿日期:2015-10-22 修回日期:2016-01-10 出版日期:2016-06-15 发布日期:2016-01-12
通讯作者: 张鑫男,博士研究生,助理研究员。主要研究方向:等离子体流动控制技术。Tel:0816-2461286 E-mail:lookzx@mail.ustc.edu.cn E-mail:lookzx@mail.ustc.edu.cn
基金资助:
武器探索研究重大项目(7130711)

Flow control on a supercritical wing using dielectric barrier discharge plasma actuator

ZHANG Xin¹, HUANG Yong², WANG Xunnian², WANG Wanbo², TANG Kun², LI Huaxing¹

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2015-10-22 Revised:2016-01-10 Online:2016-06-15 Published:2016-01-12
Supported by:
Exploration Foundation of Weapon System of China (7130711)

摘要/Abstract

摘要：

为了进一步提高等离子体激励器可控雷诺数,采用测力以及粒子图像测速(PIV)等研究方法,从二维机翼到三维半模,从低雷诺数到高雷诺数,开展了对称布局式介质阻挡放电(DBD)等离子体激励器控制超临界机翼气动特性的试验研究,分析了控制机理,实现了等离子体"虚拟舵面"的功能。结果表明:在雷诺数为2×10⁶的情况下,对称布局式等离子体气动激励能较好地抑制超临界机翼绕流流场分离,使失速迎角推迟2°,最大升力系数提高8.98%。

关键词: 超临界机翼, 流动控制, 等离子体, 介质阻挡放电, 风洞试验

Abstract:

In order to improve the plasma actuator authority at higher Reynolds number, a test investigation is conducted to evaluate the effect of symmetrical dielectric barrier discharge (DBD) plasma actuators on a two-dimensional supercritical wing and three-dimensional half model using force measurement and particle image velocimetry (PIV) at different Reynolds number. The controlling mechanism is analyzed and the function of "Virtual Section Shape" by plasma actuator is achieved. The results show that the flow separation around wing can be obviously suppressed by the symmetrical plasma actuator at Reynolds number 2×10⁶. It turned out that the stall angle of attack is delayed by approximately 2° and the maximum lift coefficient is increased by approximately 8.98%.

Key words: supercritical wing, flow control, plasma, dielectric barrier discharge, wind tunnel test

中图分类号:

V211

张鑫, 黄勇, 王勋年, 王万波, 唐坤, 李华星. 超临界机翼介质阻挡放电等离子体流动控制[J]. 航空学报, 2016, 37(6): 1733-1742.

ZHANG Xin, HUANG Yong, WANG Xunnian, WANG Wanbo, TANG Kun, LI Huaxing. Flow control on a supercritical wing using dielectric barrier discharge plasma actuator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1733-1742.

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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

超临界机翼介质阻挡放电等离子体流动控制

Flow control on a supercritical wing using dielectric barrier discharge plasma actuator

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