鸭翼后掠角对鸭翼展向吹气增升效果的实验研究  

Effect of canard sweeps on lift increment with canard-spanwise blowing

作　　者：温瑞英[1] 刘沛清[1] 徐南波[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《实验流体力学》2008年第1期40-45,共6页Journal of Experiments in Fluid Mechanics

基　　金：航空基金(项目编号:2006ZD51051)

摘　　要：利用低速风洞测力、测压以及水洞流动显示实验,对一组由机翼前缘后掠角为50°与不同鸭翼后掠角的三角翼构成的近耦合简化鸭式布局模型,系统研究了鸭翼后掠角在有无鸭翼展向吹气情况下该布局的增升效果及规律性。实验结果表明:在机翼前加装一鸭翼,增大了布局的升力系数和失速迎角,增升量值决定于鸭翼涡和机翼涡在机翼翼面上的干扰情况,说明鸭翼可以作为一种涡控部件。在对鸭翼进行展向吹气时,随着鸭翼后掠角的增大,布局开始出现增升的迎角和升力增量开始减小的迎角均增大,但最大增升百分比在减小。这表明,要在大迎角阶段充分发挥鸭式布局的优势,应选用中等后掠角组合的布局。On the basis of wind-tunnel force-measurement, pressure-measurement and water-tunnel flow visualization, the effect and law of canard sweeps on lift increment were studied for the canard configurations with a 50° swept delta-wing and different delta-canards on the condition of without canard-spanwise blowing and with canard-spanwise blowing. The results show that the lift coefficient and angles of stall are increased when add a canard in front of the wing, so the canard can be used as an element for vortex control. The magnitude of increased lift-coefficient has a relationship with the interference of wing＇s and canard＇s vortexes. When canard-spanwise blowing, the bigger is canard sweep, the larger is the angle beginning to appear lift increment and the angle decreasing the lift increment, but the smaller is the percentage of maximum flirt increament. So in order to take full advantage of canard configuration at high angle of attack, the middle sweep is worthy of taking into account.

关 键 词：鸭式布局 展向吹气 后掠角 涡控制 三角翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]