前掠翼气动布局中鸭翼高度影响的实验  

Experimental investigation on the effects of the height of distant canard wing of a forward-swept configuration

作　　者：展京霞[1] 王晋军[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：《北京航空航天大学学报》2005年第9期994-998,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家部委基金资助项目

摘　　要：基于前掠翼-鸭式前翼布局的风洞测力实验,分析了距离主机翼较远的鸭翼相对于主机翼的高度对布局纵向气动性能的影响.基于主机翼根弦长的雷诺数约为1.44×105.实验结果表明,较大的主机翼前掠角与较低的鸭翼配合,产生的升力系数增量比较显著.低于主机翼的鸭翼将加强前掠翼布局的缓失速特性.鸭翼增大升力的同时也增大了阻力;大攻角时,鸭翼带来的阻力增量较大.高于主机翼的鸭翼对最大升阻比的改善较多,但也不宜过高.主机翼前掠角较小时,鸭翼改善和提高升阻比的效果比较明显.Force measurement in a low speed wind tunnel was conducted to investigate the effects of the height of a distant canard wing on the longitudinal aerodynamic characteristics of a forward-swept configuration. The Reynolds number is about 1.44×10^5 based on the average chord length of forward-swept main wings. The results indicate that it is more favorable for the lift characteristic to equip a lower canard wing away from a greater forward-swept main wing, and the canard wing below the main forward-swept wing also slows down the stalling of the configuration. Canard wing increases lift coefficient with the penalty of the increase of drag coefficient. The increase of drag coefficient is significant at higher angles of attack. An upper canard, which is in the vicinity height of forward-swept main wing, could improve the maximum lift-to-drag ratio. Much more increase of maximum lift-to-drag ratio can be obtained with a forward-swept main wing with a small sweepback angle leading edge.

关 键 词：前掠机翼 鸭翼 升力 阻力 升阻比 低速风洞 

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]