Volume 39, Number 3, June 2021
|Page(s)||668 - 674|
|Published online||09 August 2021|
Research on the forward flight performance of rotor based on variable-droop leading edge
Aiming at the dynamic stall phenomenon of the retreating side of the rotor in forward flight, the existing flow control method of dynamic leading edge droop was applied to the flow control of forward-flying rotor at three-dimensional scale. A numerical simulation method based on variable droop leading edge is established in this paper. The seesaw rotor is taken as the research object, the moving overset mesh method and RBF grid deformation technology are used, the integral form of Reynolds average N-S equation is the main control equation. The influence of the dynamic leading edge at r/R=0.75~1 on the aerodynamic characteristics of the rotor when the forward ratio is 0.3 is investigated. It is found that variable droop leading edge on the retreating side can effectively inhibit the generation and development of separation vortices near the trailing edge, and has a significant effect on lifting lift coefficient and section normal force coefficient, reducing torque coefficient, and thus improving the equivalent lift-drag ratio of the rotor. In a certain range, the control effect is better with the increase of the droop amplitude under the leading edge.
Key words: rotor / variable droop leading edge(VDLE) / forward flight performance / motion overset mesh / helicopter
关键字 : 旋翼 / 动态前缘下垂 / 前飞性能 / 运动嵌套网格 / 直升机
© 2021 Journal of Northwestern Polytechnical University. All rights reserved.
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