低雷诺数旋翼翼型设计及气动仿真

高庆嘉; 白越; 孙强; 赵柱; 赵常均; 宫勋

doi:10.3788/OPE.20152302.0511

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低雷诺数旋翼翼型设计及气动仿真

微纳技术与精密机械 | 更新时间：2020-08-13

- 低雷诺数旋翼翼型设计及气动仿真
- Design and aerodynamic simulation of low Reynolds number rotor airfoil
- 光学精密工程 2015年23卷第2期页码：511-519
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院大学北京,中国,100049
  3. 大陆汽车电子(连云港)有限公司长春分公司,吉林长春,130000
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目(No.11372309,No.61304017)()
- DOI：10.3788/OPE.20152302.0511
  中图分类号： TP391.1;V211.52
- 收稿日期：2013-11-12，
  
  修回日期：2014-01-10，
  
  纸质出版日期：2015-02-25
- 稿件说明：
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高庆嘉, 白越, 孙强等. 低雷诺数旋翼翼型设计及气动仿真[J]. 光学精密工程, 2015,23(2): 511-519

GAO Qing-jia, BAI Yue, SUN Qiang etc. Design and aerodynamic simulation of low Reynolds number rotor airfoil[J]. Editorial Office of Optics and Precision Engineering, 2015,23(2): 511-519
高庆嘉, 白越, 孙强等. 低雷诺数旋翼翼型设计及气动仿真[J]. 光学精密工程, 2015,23(2): 511-519 DOI： 10.3788/OPE.20152302.0511.

GAO Qing-jia, BAI Yue, SUN Qiang etc. Design and aerodynamic simulation of low Reynolds number rotor airfoil[J]. Editorial Office of Optics and Precision Engineering, 2015,23(2): 511-519 DOI： 10.3788/OPE.20152302.0511.

摘要

研究了低雷诺数下薄圆弧旋翼的翼型

考虑其对高气动性能、高结构强度和便于制造和轻量化的要求

提出一种具有上凸结构的薄圆弧翼型。通过在翼型上表面增加凸起结构

增加部分弦长的翼型厚度并安装加强筋来提高翼型延展向的结构强度;设计出了最大厚度为4.3%、圆弧均匀厚度为2.5%、最大弯度为5.5%和均匀弯度为4.5%的薄圆弧翼型。采用基于二维定常、不可压缩Navier-Stoke方程的数值仿真方法计算了该翼型在雷诺数为40

000~100

000

迎角为-4°~12°下的气动性能

并获得了该翼型上下表面的压力系数分布线和速度矢量图。采用该翼型制作了直径为40 cm

质量为15 g

桨距为15.7 cm的碳纤维旋翼;在悬停状态下完成了它的升力和结构强度试验。实验结果显示其性能满足使用要求。目前

研制的旋翼已成功地应用于某型多旋翼飞行器。

Abstract

This research focuses on the thin circular arc rotor airfoils at a low Reynolds number. A novel thin circular arc airfoil with a convex structure was designed in consideration of its demand for high aerodynamic performance

high structural strength

lightweighting and easy manufacture. A convex curve on the upper surface of the airfoil was adopted to increase the thickness of airfoil at the partial chord and a stiffener in the airfoil was installed to improve the structural strength of blade span wise. The designed thin circular arc airfoil has the maximum thickness of 4.3%

a circular average thickness of 2.5%

the maximum camber of 5.5% and an average camber of 4.5%. Numerical simulations for computing the aerodynamic performance of the airfoil were performed at the representative Reynolds number between 40

000 and 100

000

and the angle of attack (AOA) from -4°to 12° by using the two dimensional steady and incompressible Navier-Stoke equations. The pressure coefficient distribution line of airfoil surfaces and the velocity vector were acquired. A carbon fiber rotor with a diameter of 40 cm

a mass of 15 g and rotor pitch of 15.7 cm was manufactured with the present airfoil

and the experiments on the lift force and the structural strength in a hover state were performed and the results show the performance of the airfoil meets the use requirments. At present

the developed rotor airfoil has been successfully used in a rotor aircraft.

关键词

Keywords

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