飞翼布局无人机微射流控制参数效能分析

doi:10.7527/S1000-6893.2014.0100

Abstract

Abstract: The control effectiveness of typical micro-jet flow control parameters on the aerodynamic performance of the flying-wing Unmanned Aerial Vehicle (UAV) was investigated by numerical simulation. Validation was conducted with TAU0015 airfoil experiment data for flow control model and numerical method. The flow control model was tested with eight array of synthetic jet actuators embedded in the leading edge and 1%c along the wing span. The change in the control effect was examined and the control efficiency of control parameters was performed. The numerical results of the UAV aerodynamic coefficients revealed lift increments over the baseline uncontrolled case as large as 25%. The actuators arranged in leading edge and inboard of UAV were found to be more effective at separation control, the larger jet momentum coefficient were more pronounced and the most effective frequency seemed to be one. Which indicate that correct control parameter is critical to the design of an efficient flow separation control scheme.

Key words: active flow control, micro-jet, flying-wing UAV, aerodynamics, flow control parameter

CLC Number:

V211

References

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The Efficiency of Micro-jet Flow Control Parameter for the Flying-wing UAV

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