摘要
旋翼翼型的动态失速现象限制了直升机的最大飞行速度和机动性,并且其产生机理复杂、抑制困难,是直升机空气动力学领域持续关注的重点与难点问题。本文首先介绍了试验、半经验模型和计算流体力学(CFD)等旋翼翼型动态失速研究方法的发展,分析了不同方法的优缺点和适用范围。其次,梳理了旋翼翼型动态失速机理及气动外形、迎角及来流等参数影响机制的研究进展。综合对比发现,变来流-变迎角耦合状态的动态失速更符合旋翼桨叶剖面的流动特征,是未来旋翼翼型动态失速研究的重要方向之一。然后,阐述了旋翼翼型设计方法和设计理念的发展历程,分析了主流翼型定常设计与少数非定常设计理念的优缺点。分析结果表明,非定常设计可以获得既能缓解动态失速又能显著提高静态气动特性的翼型,综合考虑旋翼桨叶剖面运动与来流特征的非定常设计是当前旋翼翼型设计的一个新方向。最后,对旋翼翼型设计的未来发展方向进行了讨论,提出了旋翼翼型设计与旋翼桨叶一体化设计的多层级、多阶段发展设想。
The dynamic stall of rotors limits the flight speed and maneuverability of helicopters.It has a complex mechanism and it is therefore difficult to get suppressed.Consequently,the dynamic stall is a major and persistent concern in the field of helicopter aerodynamics.This paper firstly introduces the development of experimental methods,semi-empirical models,and computational fluid dynamics(CFD)methods for the study of dynamic stall,and analyzes the advantages,disadvantages,and application scope of different methods.Secondly,research progresses on the dynamic stall mechanism of rotor airfoils and the influence mechanism of parameters such as aerodynamic shape of airfoil,angle of attack,and freestream conditions are sorted out.It is found that the dynamic stall under coupled freestream and pitch oscillations is more consistent with the flow characteristics of the rotor blade profile,and is one of the important directions for future research.Then,the development of design methods and concepts of rotor airfoils are described,and the advantages and disadvantages of the mainstream steady design and several unsteady design concepts are analyzed.Results show that the unsteady design can obtain an airfoil that can not only alleviate the dynamic stall but also improve the steady aerodynamic characteristics significantly.The unsteady design that comprehensively considers the motion and inflow of blade profile is a new direction for the current rotor airfoil design.Finally,the future development direction of rotor airfoil design is discussed,and a multi-level and multi-stage development concept of rotor airfoil design and blade design is proposed.
作者
招启军
井思梦
赵国庆
王清
ZHAO Qijun;JING Simeng;ZHAO Guoqing;WANG Qing(National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Energy and Power Engineering,Lanzhou University of Technology,Lanzhou 730050,China)
出处
《空气动力学学报》
CSCD
北大核心
2021年第6期70-84,I0001,共16页
Acta Aerodynamica Sinica
基金
国家自然科学基金(12072156,12032012)
国家重点实验室基金(61422010401)
江苏高校优势学科建设工程资助项目。
关键词
旋翼翼型
动态失速
失速机理
非定常设计
未来发展
rotor airfoil
dynamic stall
stall mechanism
unsteady design
future development
