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共轴刚性旋翼桨毂中间轴涡流发生器设计与减阻研究
引用本文:龙海斌,吴裕平,解望.共轴刚性旋翼桨毂中间轴涡流发生器设计与减阻研究[J].南京航空航天大学学报,2019,51(2):244-250.
作者姓名:龙海斌  吴裕平  解望
作者单位:中国直升机设计研究所,景德镇,333001
摘    要:为最大程度地降低共轴刚性旋翼桨毂的气动阻力,在其减阻设计方案中间轴处加装翼型截面的涡流分割器。首先设计了不同展长、弦长、安装位置和数量的涡流发生器加装方案,之后采用求解N-S方程的方法计算和分析了加装涡流发生器之后的桨毂阻力特性、表面压力和空间流动情况等。结果表明加装涡流发生器能使桨毂减阻方案的阻力降低约5%,弦长增大、涡流发生器位置向下桨毂方向移动有利于进一步降低阻力。研究结果可为涡流发生器的应用和桨毂减阻设计提供一定的参考。

关 键 词:共轴刚性旋翼  桨毂  中间轴  涡流发生器  减阻
收稿时间:2018/11/11 0:00:00
修稿时间:2019/3/8 0:00:00

Design and Drag Reduction Research on Vortex Generator of Coaxial Rigid Rotor Hub Shaft Fairing
Institution:China Helicopter Research and Development Institute, Jingdezhen, 333001, China
Abstract:In order to minimize the aerodynamic drag of coaxial rigid rotor hub, the airfoil cross-section vortex generator installed on the shaft fairing. The vortex generator installation programs with different expansion length, chord length, installation number and locations are designed, then calculate and analysis the drag characteristics of coaxial twin hub by the method of solving N-S equation. Finally, the surface pressure and spatial flow are analyzed. The results show that vortex generator can reduce about 5% of the drag of coaxial twin hub drag reduction program. The increment of chord length and the movement of vortex generator to lower hub is conducive to further reduce the drag. The research results can provide a reference for the application of vortex generator and the drag reduction design of rotor hub.
Keywords:coaxial rigid rotor  hub  shaft  vortex generator  drag reduction
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