等离子体气动激励改善增升装置气动性能的试验

doi:10.7527/S1000-6893.2016.0131

Abstract

Abstract:

Flow separation on high lift systems will result in the aerodynamic characteristic deterioration. Wind tunnel test of high lift system flow separation control by plasma aerodynamic actuation were conducted. The effects of actuation parameters such as pulse frequency and duty cycle and actuation position were investigated. The test results show that plasma aerodynamic actuation can suppress flow separation and improve aerodynamic characteristic for high lift system by inducing flow acceleration and enhancing energy mixing in boundary layer. When the actuation is operated on the leading edge of the main airfoil, the stall separation at high angle of attacks can be suppressed effectively. The maximal lift coefficient and the stall angle of attack are increased by 18.1% an 4° respectively. When the actuation is operated on the leading edge of the flap, the aerodynamic characteristics at small angles of attack can be improved effectively. The lift coefficient of the tested model is increased by 7.1% and the drag coefficient is reduced by 28.7% after actuation at an angle of attack of 4°. The duty cycle is important in flow control. When the duty cycle is 10%~30%, the actuation is characterized by its intense unsteady property and the flow control effects are better than that of 50%. The control effects are the worst when the duty cycle is 100%. The flow separation is hard to control at higher inflow velocities for its strong reverse pressure gradient. The investigation can lay a foundation for the application of plasma flow control technology on high life systems.

Key words: high lift system, plasma, aerodynamic actuation, flow separation, flow control

CLC Number:

V232

LIANG Hua, WU Yun, LI Jun, HAN Menghu, MA Jie. Test of high lift system flow control by plasma aerodynamic actuation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(8): 2603-2613.

References

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Test of high lift system flow control by plasma aerodynamic actuation

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