In order to investigate the effect of aspect ration and stiffness and camber of flapping-wing on thrust force characteristic

the wind tunnel test of Flapping-wing MAV(Micro air vehicle) was performed in special micro air vehicle wind tunnel of NPU(Northwestern Polytechnical University).The rectangular wing which has the aspect ration of 2

4.5 and 7 and cambered aerofoil and flat aerofoil were fabricated.Structure strength of three different stiffness rectangular flapping-wings was analysed.The velocity(from 4m/s to 10m/s) and flapping frequency(between4Hz to 8Hz) were applied for test.In this experiment we find it improves thrust efficiency of flapping-wing through increase aspect ration or decrease stiffness of flapping-wing.It is disadvantageous to thrust characteristic through increase camber of airfoil.