摘要
通过进行微型扑翼飞行器低速风洞试验,研究了带弯度机翼下翼面翼刀对扑翼飞行器升阻特性的影响。文中进行了带翼刀机翼和不带翼刀机翼在不同迎角下的风洞吹风试验。试验结果表明,带翼刀机翼升力系数大于不带翼刀机翼升力系数,从而证明了翼刀可以阻止机翼下表面气流展向流动,起到增加机翼升力的作用。当扑翼在小迎角飞行时,带翼刀机翼可以有效地提高扑翼的气动效率,改善扑翼的飞行性能。研究结果可为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
In order to investigate the effect of camber wing with wing-blade located beneath the wing surface on the aerodynamic characteristics of flapping-wing micro air vehicle,wind tunnel test of flapping-wing MAV（Micro Air Vehicle） was performed in a special micro air vehicle wind tunnel of NPU（Northwestern Polytechnical University）.Wing with wing-blade and wing without wing-blade were employed for wind tunnel tests at different attack angle.Experimental results indicate that the lift coefficient of wing with wing-blade is larger than that of wing without wing-blade.So it is proved that wing-blade can prevent spanwise airflow beneath wing surface and increase wing lift.At small attack angles,wing with wing-blade can increase effectively aerodynamic efficiency of flapping-wing air vehicle and improve flight performance.Results of wind tunnel test provide technology support for application of wing with wing-blade in flapping-wing micro air vehicle.
出处
《实验力学》
CSCD
北大核心
2011年第2期146-150,共5页
Journal of Experimental Mechanics
基金
博士后基金(2010048136420100481369)
关键词
微型扑翼飞行器
升阻特性
翼刀
风洞试验
micro flapping-wing air vehicle
lift-drag characteristics
wing-blade
wind tunnel test
