摘要
对悬停和前飞状态下共轴双旋翼的气动特性开展数值仿真研究。首先,分别对悬停状态的旋翼标模和前飞状态的试验模型计算旋翼拉力系数,数值仿真结果与试验结果符合良好。然后,基于多重参考系法建立共轴双旋翼CFD数值模型,分析共轴双旋翼上、下旋翼气动特性变化规律。结果表明,悬停状态下,共轴双旋翼每个旋翼的拉力系数均低于单旋翼拉力系数,本文算例中,双旋翼/单旋翼拉力比可达1.844,且随转速增加而降低。前飞状态下,从避免风车效应的角度考虑,共轴双旋翼优于单旋翼,旋翼间距近的共轴双旋翼优于旋翼间距远的共轴双旋翼。
The aerodynamic performance of coaxial twin-rotors in either hover or level flight is simulated.The numerical method using multiple reference frame method is firstly applied in a benchmark rotor and wind tunnel model in hover and level flight,respectively.The simulated thrust coefficients agree with the results from experiment.Then the CFD(computational fluid dynamics)model is established for coaxial twin-rotors,and the aerodynamic performance of upper and lower rotors are analyzed.Numerical results show that the single rotor generates higher thrust coefficient than either the upper or the lower rotor of the coaxial twin-rotor in hover.The thrust ratio between the coaxial twin-rotor and the single rotor reaches 1.844 in present simulation.The thrust ratio decreases with the increase of the rotating speed.In level flight,to avoid the windmill effect,the coaxial twin-rotor is better than the single rotor,and a small space between upper and lower rotors is preferred.
作者
杨海涛
夏巍
刘悦
胡淑玲
Yang Haitao;Xia Wei;Liu Yue;Hu Shuling(State Key Laboratory for Strength and Vibration of Mechanical Structures,Xi'an Jiaotong University,Xi'an 710049,China;AVIC Chengdu Aircraft Industrial(Group)Co.,Ltd.,Chengdu 610091,China)
出处
《机械科学与技术》
CSCD
北大核心
2020年第2期303-308,共6页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(11632014)
高等学校学科创新引智计划项目[111计划](B18040)
中央高校基本科研业务费专项资金项目(XJJ2018028)资助.
关键词
共轴双旋翼
气动特性
数值仿真
多重参考系法
coaxial twin-rotors
aerodynamics
computational fluid dynamics
multiple reference frame method
thrust coefficient
simulation
models
作者简介
杨海涛(1994-),硕士研究生,研究方向为倾转旋翼气动分析,yanghaitao@stu.xjtu.edu.cn;通信作者:夏巍,副教授,博士,xwei@mail.xjtu.edu.cn
