微型扑翼飞行器气动机理风洞试验研究

Experimental Investigation of Aerodynamic Characteristics of Flapping-wing MAV in Wind Tunnel

为了对微型扑翼飞行器的气动机理进行研究,利用西北工业大学微型飞行器专用风洞进行了一系列吹风试验。试验中研究了迎角、扑动频率、风速对微型扑翼飞行器气动特性的影响。通过试验得到了关于微型扑翼飞行器气动特性的基本规律,为进一步研究微型扑翼飞行器的气动机理打下了基础,同时也可以为微型扑翼飞行器总体设计提供参考。

In order to investigate the aerodynamic characteristics of FMAV （flapping-wing Micro Air Vehicle）, a series of wind tunnel tests were performed in the Purpose-designed micro air vehicle wind tunnel of NPU （Northwestern Polytechnical University, PRC）. the wind tunnel and the test model are shown. The influence of angle of attach, flapping frequency and freestream velocity was investigated. Severe conclusions were gained ： （ 1 ） lift, drag and longitudinal moment vary periodically with the flapping of the wing; （2） the angle of attach and the freestream velocities are the primary aspects which influence the lift. The lift coefficient don＇ t increase when the flapping frequency increases; （3） drag is primary influenced by the flapping frequency, which will make the drag coefficient decreases remarkably when it increases; （4）the longitudinal moment is mainly influence by the angle of attack. The results of the tests will be beneficial to the further research of aerodynamic characteristics of FMAV and can give advice to the design of it.