超临界机翼介质阻挡放电等离子体流动控制
收稿日期: 2015-10-22
修回日期: 2016-01-10
网络出版日期: 2016-01-12
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
Received date: 2015-10-22
Revised date: 2016-01-10
Online published: 2016-01-12
Supported by
Exploration Foundation of Weapon System of China (7130711)
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 . DOI: 10.7527/S1000-6893.2016.0015
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%.
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