Blade-twist aerodynamic characteristics of coaxial rotors in hover

SHAO Wei-ping; HE Min-tao; HAO Yong-ping

doi:10.13224/j.cnki.jasp.2014.11.010

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Blade-twist aerodynamic characteristics of coaxial rotors in hover

更新时间：2026-07-07

- Blade-twist aerodynamic characteristics of coaxial rotors in hover
- Vol. 29, Issue 11, Pages: 2606-2612(2014)
- 作者机构：
  
  沈阳理工大学机械工程学院辽宁省先进制造与装备重点实验室,沈阳,110159
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.11.010
  CLC：
- Published：2014
- 稿件说明：
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邵伟平, 何敏桃, 郝永平. 悬停状态共轴双旋翼桨叶扭转气动特性[J]. 航空动力学报, 2014, 29(11): 2606-2612.

doi: 10.13224/j.cnki.jasp.2014.11.010
邵伟平, 何敏桃, 郝永平. 悬停状态共轴双旋翼桨叶扭转气动特性[J]. 航空动力学报, 2014, 29(11): 2606-2612. DOI： 10.13224/j.cnki.jasp.2014.11.010.

doi: 10.13224/j.cnki.jasp.2014.11.010 DOI：

摘要

针对桨叶气动性能的提高

建立了一套基于悬停状态的共轴双旋翼桨叶扭转设计方法.在该方法中

设定单旋翼桨叶扭转几何安装角

通过仿真验证

合理的桨叶扭转

可提高旋翼性能7.0%;根据桨尖涡对桨叶的影响

以及共轴双旋翼气动特性

分别对桨尖几何安装角及上下旋翼几何安装角进行修正

实现悬停状态共轴双旋翼桨叶扭转设计.最后

对所设计的共轴双旋翼进行模拟仿真

结果表明该扭转翼较未经扭转的矩形翼升力提高了10.3%.

Abstract

To meet the improvement of blade aerodynamic performance

blade-twist of coaxial rotors in hover design method was proposed.In this method

geometric installation angle was set for single rotor blade-twist

and the simulation results show reasonable blade-twist design can improve the rotor performance by 7.0%.In order to achieve hover coaxial rotor blade-twist design

the installation angle of upper and lower blade tips and rotors must be corrected

according to the blade tip vortex's impact

as well as coaxial rotor aerodynamic characteristics. Finally

the simulation results of coaxial rotors method show wing-twist lift is increased by 10.3% than that without twist of rectangular wing.

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