微型扑翼飞行器风洞试验初步研究

Experimental Investigation of Flapping-wing MAV in Wind Tunnel

为了对微型扑翼飞行器空气动力学基本特性进行定量研究,利用西北工业大学微型飞行器专用风洞对微型扑翼飞行器机翼进行初步风洞吹风试验。试验中进行了扑动频率、风速、迎角、机翼平面形状、翼型弯度对机翼气动特性影响的研究。通过试验得出了微型扑翼飞行器升力、推力产生的基本规律,为微型扑翼飞行器总体设计和气动设计提供了参考。

In order to quantificationally investigate the aerodynamics of flapping-wing MAV（Micro Air Vehicle）, the wind tunnel test of flapping-wing MAV is performed in special micro air vehicle wind tunnel of NPU （Northwestern Polytechnical University）. The effects of flapping frequency, wind velocity, Jangle of attack, plane shape of wing and cambered aerofoil are investigated. In this experiment the producing rules of lift and thrust are found. The result of experiment can guide the conceptual design and aerodynamic design of the flap ping-wing MAV.