航空学报 > 2016, Vol. 37 Issue (6): 1733-1742   doi: 10.7527/S1000-6893.2016.0015

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. 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. 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:

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

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