航空学报 > 2016, Vol. 37 Issue (2): 437-450   doi: 10.7527/S1000-6893.2015.0185

GAW-1翼型前后缘变弯度气动性能研究

陆维爽1, 田云1, 刘沛清2, 王涛1, 张良富1   

  1. 1. 北京航空航天大学大型飞机高等人才培训班, 北京 100083;
    2. 北京航空航天大学航空科学与工程学院, 北京 100083
  • 收稿日期:2015-03-17 修回日期:2015-06-16 出版日期:2016-02-15 发布日期:2015-06-29
  • 通讯作者: 刘沛清,男,博士,教授,博士生导师。主要研究方向:实验空气动力学、机翼及增升装置设计。Tel:010-82318967,E-mail:lpq@buaa.edu.cn E-mail:lpq@buaa.edu.cn
  • 作者简介:陆维爽,女,硕士研究生。主要研究方向:计算流体力学。Tel:010-62314528,E-mail:lujiaww@163.com;田云,男,博士,讲师。主要研究方向:计算流体力学、翼型及机翼设计。Tel:010-82316670,E-mail:aircraft@buaa.edu.cn;王涛,男,硕士研究生。主要研究方向:计算流体力学。E-mail:273872093@qq.com;张良富,男,硕士研究生。主要研究方向:计算流体力学。E-mail:1053165986@qq.com

Aerodynamic performance of GAW-1 airfoil leading-edge and trailing-edge variable camber

LU Weishuang1, TIAN Yun1, LIU Peiqing2, WANG Tao1, ZHANG Liangfu1   

  1. 1. Large Aircraft Advanced Training Center, Beihang University, Beijing 100083, China;
    2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2015-03-17 Revised:2015-06-16 Online:2016-02-15 Published:2015-06-29

摘要:

传统增升装置主要用于提高飞机起降气动性能。利用计算流体力学(CFD)的方法,引入了通用飞机翼型的前后缘变弯装置的概念,数值模拟了GAW-1翼型在爬升状态时,前缘变弯装置、后缘襟翼/副翼偏转以及前后缘装置综合偏转对翼型气动特性的影响。研究表明,前缘变弯装置可以有效地改善翼型的失速特性,失速迎角提高了3°左右,最大升力系数提高了4.56%;同时提高升阻比50%~120%;但在设计升力系数下,升力系数和阻力系数都略微减小。另一方面,后缘变弯装置可以改变最大升阻比所对应的迎角,以及在小迎角时,提高升力系数6%左右。翼型综合偏转可以在小迎角时增加升力系数,在大迎角时增加升阻比。

关键词: 通用飞机, 前缘下垂, 后缘襟翼, 副翼, 变弯度, 气动性能

Abstract:

The traditional high-lift device is used to improve the taking-off and landing aerodynamic performance of aircraft. By using the method of computational fluid dynamics(CFD), an idea of leading-edge and trailing-edge variable camber devices based on general aviation airfoil is introduced. The influences of leading-edge variable camber device, trailing-edge flap/aileron, and both leading-edge and trailing-edge variable camber devices of GAW-1 airfoil in the climbing state on airfoil aerodynamic performances are studied respectively. Learning from the results, leading-edge variable camber device can effectively improve the airfoil stall characteristics, increasing the angle of stall by about 3°, and the maximum lift coefficient has been increased by 4.56%. At the same time, the lift-to-drag ratio has been increased by 50% to 120%. But with the design lift coefficient, both lift coefficient and drag coefficient have been decreased. On the other hand, the function of trailing-edge variable camber device is to reposition the maximum of lift-to-drag ratio and to increase the lift coefficient by about 6% at a small angle of attack. Composite deflection of airfoil can increase lift coefficient at small angle of attack and increase lift-to-drag ratio at large angle of attack.

Key words: general aircraft, leading-edge droop nose, trailing-edge flap, ailerons, variable camber, aerodynamic performance

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