小型旋翼气动特性研究  

Study on Aerodynamic Characteristics of Small Rotor

作　　者：雷瑶[1] 纪玉霞[1] 汪长炜 LEI Yao;JI Yuxia;WANG Changwei(School of Mechanical Engineering and Automation,Fuzhou University,Fuzhou Fujian 350116,China)

机构地区：[1]福州大学机械工程及自动化学院,福建福州350116

出　　处：《机床与液压》2018年第17期61-65,共5页Machine Tool & Hydraulics

基　　金：国家自然科学基金资助项目(51505087);福建省教育厅资助项目(JA15054)

摘　　要：为研究小型旋翼的气动特性,运用CFD方法对旋翼的流场进行数值模拟,通过旋翼表面压力分布、速度矢量、流场流线以及升阻比来详细分析旋翼的流场分布特点和气动特性。设计试验系统并搭建气动测试实验平台,实际测量旋翼的拉力和功耗并验证数值模拟结果的可行性。研究结果表明,旋翼桨尖处压力最大且存在负压区域,桨尖压力梯度最大的地方逸出了桨尖涡。在雷诺数范围0.8×10~5~1.16×10~5内,旋翼翼型在雷诺数约为90 000时的升阻比达到最大。低转速下旋翼的功率载荷较大,在转速约为1 700 r/min时,旋翼的拉力较大同时功耗较小。In order to study the aerodynamic characteristics of small rotor,pressure distribution,velocity vector,streamline of flow field and lift-to-drag ratio are obtained with the numerical simulation by Computational Fluid Dynamics(CFD)method,which are used to analyze the distribution features and aerodynamic characteristics of flow field in detail.Test system was designed to set up the pneumatic experiment platform for the measurement of thrust and power consumption in practice,and the results of numerical simula-tion were verified by the experiments.The study results show that the pressure of blade tip is the highest and there is also negative pres-sure existing in the blade tip,and come out tip eddy at the maximum pressure gradient.When the Reynolds number is ranged from 0.8×105to 1.16×105,the maximum lift-drag ratio is achieved with 90 000.Power loading of the rotor at lower speed is larger,while the rotor has higher thrust and smaller power consumption at about 1 700 r/min.

关 键 词：小型旋翼 数值模拟 升阻比 流场特性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]