北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (6): 631-635.

• 论文 •    下一篇

操纵面加装Gurney襟翼对无人机纵向气动特性的影响

 王晋军, 张子军, 冯立好   

  1. (北京航空航天大学 流体力学教育部重点实验室, 北京 100191)
  • 收稿日期:2010-01-23 出版日期:2010-06-30 发布日期:2010-07-02
  • 作者简介:王晋军(1963-),男,山西寿阳人,教授,jjwang@buaa.edu.cn.
  • 基金资助:

    国家部委基金资助项目

Influence of Gurney flap on longitudinal aerodynamic characteristics of  multiple-control-surface UAV

 WANG  Jin-Jun, ZHANG  Zi-Jun, FENG  Li-Hao   

  • Received:2010-01-23 Online:2010-06-30 Published:2010-07-02

摘要: 通过风洞测力实验研究了矩形Gurney襟翼对多操纵面飞翼布局无人机纵向气动特性的影响.升降副翼和襟副翼加装Gurney襟翼都会增加全机升力系数以及低头力矩系数.通过比较发现,升降副翼加装Gurney襟翼的增升效果好于襟副翼,外侧操纵面控制效果好于内侧.升降副翼和襟副翼分别组合加装Gurney襟翼会进一步提高增升效果,并且升力系数随着Gurney襟翼高度的增加而增加.鸭翼上加装Gurney襟翼可以减小全机低头力矩系数,因此鸭翼和升降副翼、襟副翼组合加装Gurney襟翼在线性段提高全机升力系数的同时,可以保持低头力矩系数增量基本为0,该特性对改善飞行器性能尤为有利.

Abstract: An experiment had been conducted to investigation the effect of different control surfaces with Gurney flaps on the aerodynamic characteristic of a multiple-control-surface tailless aircraft model. It is found that either the individual elevons and flaperons, or their combinations with Gurney flaps can increase the lift coefficient, while the drag and nose-down pitching moment coefficients are also enhanced inevitably. In contrast, when the canard wing is equipped with Gurney flaps, the lift and drag coefficients have nearly no change at the linear stage, while the nose-down pitching moment coefficients decrease significantly during the angles of attack tested. Therefore, the combinations of the canard wing and either the elevons or flaperons with Gurney flaps were further tested. The results show that such combinations can increase the lift coefficient while keep the pitching moment coefficient almost unchanged, which is benefit to improve the aerodynamic performance of aircraft.

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发