共轴旋翼悬停测力实验与数值模拟  

Force Measurement and CFD Validation of Coaxial Rotor in Hover

作　　者：闫修 赵旭[1] 郭汉青[1] 李晓东[1] 王年华[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2015年第2期65-67,71,共4页Aeronautical Computing Technique

基　　金：航空科学基金项目资助(20145753030);国家大学生创新训练计划项目资助(201210699018)

摘　　要：为改善单旋翼的拉力不足的问题,对具有前后对称翼型的共轴旋转机翼,进行悬停测力实验,探索了单、双旋翼的最佳安装角。通过三维非定常旋翼绕流的CFD数值模拟,分析了上下旋翼之间的相互干扰影响。研究发现,受上旋翼下洗流影响,下旋翼的最佳安装角远大于单旋翼最佳安装角;共轴旋翼间的气动干扰使下旋翼拉力减小比上旋翼拉力减小程度大。实验表明,同转速双旋翼最大拉力超过单旋翼最大拉力的两倍,表明在特定情况下,双旋翼能改善单旋翼的拉力不足的缺点。This paper presents thrust measurement and CFD validation of a coaxial rotating wing composed of the fore- and- after symmetrical airfoil in hovering. The optimal installation angles of the single and coaxial wings are investigated. Interference factors between coaxial wings are analyzed via 3D unsteady flow simulation. The optimal installation angle of downstream wing is much larger than that of upstream wing.Aerodynamic interference between the coaxial wings leads to a significant thrust decrease of downstream wing than that of the upstream wing. It is found that the thrust of coaxial wing under optimal installation angle is twice more than that of the single wing,which demonstrates that coaxial wing has the potential of enhance thrust in some condition.

关 键 词：共轴旋转机翼 悬停实验 CFD 非定常流动 拉力 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]