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

Abstract

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

CLC Number:

V211

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

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