翼型几何参数对涵道共轴双旋翼气动特性影响研究  

Research on influence of geometric parameters of airfoil on aerodynamic characteristics of ducted coaxial double rotors

作　　者：杨永刚[1] 郑炜 YANG Yonggang;ZHENG Wei(College of Transportation Science and Engineering,CAUC,Tianjin 300300,China;College of Aeronautical Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学交通科学与工程学院,天津300300 [2]中国民航大学航空工程学院,天津300300

出　　处：《中国民航大学学报》2025年第1期41-46,共6页Journal of Civil Aviation University of China

基　　金：中国民航大学实验技术创新基金项目(2021CXJJ73)。

摘　　要：翼型几何参数对旋翼的气动特性影响较大。本文针对涵道共轴双旋翼模型进行数值模拟计算,研究不同几何参数对旋翼气动特性的影响规律,以提高涵道共轴双旋翼的气动效率。结果表明,翼型弯度和桨根安装角的增加均可以显著提高涵道共轴双旋翼的总拉力。当拉力系数小于0.04时,小弯度翼型的气动性能参数高于大弯度翼型;随着拉力系数继续增大,在涵道唇口绕流与上旋翼翼尖涡之间以及双旋翼尾迹之间出现气动干扰和涡流轨迹紊乱;涵道出口内壁面发生局部流动分离成为小弯度翼型气动性能参数迅速下降的主要原因。大弯度翼型的气动性能参数变化平稳,拉力系数较大时的气动效率优于小弯度翼型,NACA6412的桨根安装角在20°~40°之间进行旋翼设计是更好的选择。The geometric parameters of the airfoil have a great influence on the aerodynamic characteristics of the rotor.This article focuses on numerical simulation calculations of the ducted coaxial double rotors model,studying the influ-ence of dfferent geometric parameters on the aerodynamic characteristics of the rotor,in order to improve the aero-dynamic efficiency of the ducted coaxial double rotors.The results indicate that increasing the airfoil camber and the installation angle of the blade root can significantly improve the total thrust of the ducted coaxial double rotors.When the thrust coefficient is less than 0.04,the aerodynamic performance parameters of the small camber airfoil were higher than those of the large camber airfoil.As the thrust coefficient continues to increase,aerodynamic in-terference and vortex trajectory disorder occurred between the lip airflow of the duct and the tip vortex of the upper rotor,as well as between the wakes of the double rotors.Local flow separation occurred on the inner wall surface of the duct outlet.These are the main reasons for the rapid decline of aerodynamic performance parameters of small camber airfoil.The aerodynamic performance parameters of the large camber airfoil change smoothly,and the aero-dynamic efficiency is better than that of the small camber airfoil when the thrust coefficient is large.It is a better choice to design the rotor with a blade root installation angle for NACA6412 between 20°to 40°.

关 键 词：旋翼几何参数 涵道共轴双旋翼 数值模拟 气动特性 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]