论文部分内容阅读
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。
The micro-flapping wing low-speed wind tunnel test was carried out to study the influence of flank wing blades with camber wing on lift-drag characteristics of flapping-wing aircraft. In this paper, the wind tunnel blowing experiment with wings with wings and wings without wings at different angles of attack is carried out. The experimental results show that the lift coefficient of wing with wings is larger than that of wings without wings, which proves that wing blades can prevent the air under the wings from spreading to the air and increase the wing lift. When the flapping wing is flying at a small angle of attack, the wing with a blade can effectively improve the aerodynamic efficiency of the flapping wing and improve the flight performance of the flapping wing. The results of the research can provide technical support for the application of wing-equipped airfoils in flapping-wing aircraft.