低雷诺数下层流分离的等离子体控制

doi:10.7527/S1000-6893.2015.0244

Abstract

Abstract:

In order to control the laminar separation effectively and eliminate or decrease the nonlinearities of the lift curve, the mechanism is detected using pressure measurements and surface oil visualization measurements on the tripped airfoil. An experimental study of an elliptic airfoil with 16% thickness is performed in wind tunnel. Based on the baseline airfoil aerodynamics, an alternating current single dielectric barrier discharge plasma actuator set at 10% chord is designed, combined with surface pressure distribution measurements. The results show that the plasma actuator would re-energize the boundary layer, thereby delay the trailing-edge laminar boundary layer separation and result in the enhancement of the lift like a trip strip. When the laminar separation bubble occurs at trailing or leading edge region of the airfoil, the plasma actuation can eliminate or decrease the bubble, thus leading to a reduction in the airfoil lift. The linear proportional control is achieved with the enhancement and reduction lift changes by duty-cycled plasma actuation.

Key words: low Reynolds number, laminar separation bubble, plasma, flow control, lift nonlinearity

CLC Number:

V211.7

MENG Xuanshi, YANG Zeren, CHEN Qi, BAI Peng, HU Haiyang. Laminar separation control at low Reynolds numbers using plasma actuation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(7): 2112-2122.

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Laminar separation control at low Reynolds numbers using plasma actuation

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