纳秒脉冲等离子体激励控制小后掠三角翼低速绕流试验

doi:10.7527/S1000-6893.2014.0341

Abstract

Abstract:

In order to explore the flow control effect and mechanism of nanosecond dielectric barrier discharge (NS DBD) on the low swept delta wing with sharp leading edge, force measurements and flow visualization experiments are conducted on a 30° swept delta wing. When the flow speed is 30 m/s and 45 m/s, it is found that leading-edge plasma actuation can significantly improve the aerodynamics of delta wing at a high angle of attack, with the maximum lift coefficient increased by about 18.3%. The influence law of the actuation frequency on the control effect is investigated, that is the optimum reduced frequency of F⁺≈1 to 2. When the flow speed is 20 m/s, particle image velocimetry (PIV) measurement is conducted to investigate the formation of leading edge vortices affected by the pulsed NS DBD at different angles of attack. The flow pattern obtained from the PIV measurement shows that flow reattachment is promoted by excitation, and an intensified vortex flow pattern develops. Based on the experimental results, it is supposed that the reforming of leading-edge vortex, resulting from periodic emanation of small-scale vortices moving along the shear layer due to the pulsed actuation, may be the mechanism.

Key words: flow control, dielectric barrier discharge, plasma, nanosecond pulse, delta wing

CLC Number:

V211.7

ZHAO Guangyin, LIANG Hua, LI Yinghong, HAN Menghu, HUA Weizhuo. Experiment of flow control on a low swept delta wing using pulsed nanosecond plasma actuation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(7): 2125-2132.

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Experiment of flow control on a low swept delta wing using pulsed nanosecond plasma actuation

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