基于自由尾迹方法的自转旋翼气动特性研究

doi:10.7527/S1000-6893.2015.0076

流体力学与飞行力学

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基于自由尾迹方法的自转旋翼气动特性研究

王俊超¹, 谭剑锋², 李建波¹, 徐明¹

1. 南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016;
2. 南京工业大学机械与动力工程学院, 南京 211816

收稿日期:2014-12-10 修回日期:2015-03-13 出版日期:2015-11-15 发布日期:2015-03-20
通讯作者: 李建波,Tel.:025-84895188,E-mail:ljb101@nuaa.edu.cn E-mail:ljb101@nuaa.edu.cn
作者简介:王俊超,男,博士研究生。主要研究方向:直升机总体设计、直升机空气动力学、直升机飞行力学。E-mail:wjc@nuaa.edu.cn;谭剑锋,男,博士,讲师。主要研究方向:旋翼空气动力学与结构动力学,风机空气动力学。E-mail:windtam2003@gmail.com;李建波,男,博士,研究员,博士生导师。主要研究方向:旋翼类飞行器总体设计研究、直升机气动及飞行动力学研究、旋翼结构及动力学设计。Tel:025-84895188,E-mail:ljb101@nuaa.edu.cn;徐明,男,博士研究生。主要研究方向:直升机总体设计、旋翼空气动力学、直升机飞行力学。E-mail:xuming18237@nuaa.edu.cn
基金资助:
国家自然科学基金(11202097);航空科学基金(2013ZA52014);江苏高校优势学科建设工程资助项目

Investigation of autorotating rotor aerodynamic characteristics based on free wake method

WANG Junchao¹, TAN Jianfeng², LI Jianbo¹, XU Ming¹

1. Science and Technology on Rotorcraft Aeromechanics Laboratory, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. School of Mechanical and Power Engineering, Nanjing University of Technology, Nanjing 211816, China

Received:2014-12-10 Revised:2015-03-13 Online:2015-11-15 Published:2015-03-20
Supported by:
National Natural Science Foundation of China(11202097);Aeronautical Science Foundation of China(2013ZA52014);A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

为研究自转旋翼的气动特性,建立了自转旋翼的自由尾迹方法计算模型,并耦合桨叶挥舞运动模型和自转旋翼配平模型,建立了一种分析自转旋翼气动特性的方法。以某试验自转旋翼为算例对该方法进行了验证并运用该方法研究了自转旋翼的尾迹几何形状和桨盘诱导入流分布特性。研究结果表明:建立的自由尾迹方法计算模型可以满足自转旋翼气动特性分析的需求,相比传统的近似入流模型,该自由尾迹方法模型精度更高;前飞时自转旋翼尾迹随时间推移自桨盘处向桨盘后上方运动,水平面内自转旋翼尾迹畸变略小于驱转旋翼;自转旋翼桨盘诱导入流呈非均匀分布,从桨盘前缘到后缘,下洗入流大致呈不断增加趋势,在相同拉力水平下,自转旋翼90°方位角附近及桨盘后缘的诱导入流小于驱转旋翼。

关键词: 旋翼, 尾迹, 桨叶, 挥舞, 配平, 气动特性, 直升机

Abstract:

To investigate autorotating rotor aerodynamic characteristics, a free wake method calculation model which couples blade flapping motion model and trim model of autorotating rotor is established in this paper, and an analysis method for autorotating rotor aerodynamic characteristics is established. Then, this method is verified by a test example of an autorotating rotor based on the method. Lastly, wake geometry and rotor disk induced inflow distribution characteristics of autorotating rotor are investigated by the method. The results indicate that the free wake method calculation model established in this paper can meet the requirement of autorotating rotor aerodynamic characteristics analysis and the model accuracy is higher compared with the traditional approximate inflow model. Autorotating rotor wake moves upward and backward from the rotor disk as time goes on in the forward flight. The distortion of autorotating rotor wake is slightly smaller than powered rotor in the horizontal plane. The distribution of autorotating rotor disk induced inflow is nonuniform. Downwash inflow generally increases gradually from the leading edge to the trailing edge of the rotor disk. Autorotating rotor induced inflow is less than powered rotor near 90° azimuth and at the trailing edge of the rotor disk at the same thrust.

Key words: rotor, wake, blade, flap, trim, aerodynamic characteristics, helicopter

中图分类号:

V211.52

王俊超, 谭剑锋, 李建波, 徐明. 基于自由尾迹方法的自转旋翼气动特性研究[J]. 航空学报, 2015, 36(11): 3540-3548.

WANG Junchao, TAN Jianfeng, LI Jianbo, XU Ming. Investigation of autorotating rotor aerodynamic characteristics based on free wake method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(11): 3540-3548.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于自由尾迹方法的自转旋翼气动特性研究

Investigation of autorotating rotor aerodynamic characteristics based on free wake method

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