非对称布局形式的涵道尾桨气动特性  

Aerodynamic characteristics of a ducted tail rotor with asymmetric layout

作　　者：刘顺安[1] 贺兴柱 陈延礼[1] 杨璐鸿 李万林[1] 

机构地区：[1]吉林大学机械科学与工程学院,长春130022

出　　处：《吉林大学学报（工学版）》2014年第5期1353-1359,共7页Journal of Jilin University:Engineering and Technology Edition

基　　金：'863'国家高技术研究发展计划项目(SS2013AA060403)

摘　　要：针对现行涵道尾桨无法提供升力的缺点,提出一种非对称布局形式的涵道尾桨结构。通过理论分析和数值模拟的方法,对该涵道尾桨的拓扑结构进行气动性能研究,得出涵道尾桨升力、拉力和扭矩分别与飞行速度和开口角有关的结论。对称结构和非对称结构的涵道尾桨气动特性对比结果表明:该非对称布局的涵道尾桨不仅可以产生较大的轴向拉力,对飞行器姿态进行操纵,而且还产生一定的径向力,为飞行器提供额外的升力。总之,该非对称布局的涵道尾桨具有一定的可行性和应用价值。To overcome the shortcoming of the current ducted tail rotor that is unable to provide lift force, a ducted tail rotor with asymmetric layout was proposed. The aerodynamic performance of the topological structure of the ducted tail rotor was theoretically and numerically studied. The effects of the flight speed and opening angular displacement on the lift force, pull force and moment were obtained respectively. The aerodynamic characteristics of the symmetric and asymmetric ducted tail rotors were compared. It was shown that this ducted tail rotor with asymmetric layout can not only produce axial force to control aircraft attitude, but also produce radial force to provide additional lift force for the aircraft. Therefore, proposed ducted tail rotor with asymmetric layout has certain feasibility and application value.

关 键 词：计算流体动力学 涵道尾桨 非对称布局 气动特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]