Experimental investigation of aerodynamic parameters on flapping wing

WOS: 000417994200003Increasing the application areas of unmanned aerial vehicles has increased the number of studies in this field. Micro air vehicles that are smaller models of the unmanned aerial vehicles are used in many areas of civil and military. Micro air vehicles are basically divided into three classes as fixed, rotary and flapping wings. The most important advantage of flapping wing air vehicles examined in this study, thrust force occurs as a result of flapping motion of the wings and thus an external thrust system is not required. The aim of this study, unsteady flow in flapping wings is to examine with experiments in wind tunnel. The scope of work a flapping wing mechanism was designed and the aerodynamics parameters at different wind speed, angle of attack and flapping frequencies were examined while the wings produced with different materials were flapping. According to the obtained results; while the lift force was increased at higher wind speed and angle attack, the thrust force was reduced because of friction. At high flapping frequency while the thrust force was increased, the lift force was decreased. Thrust force of airfoils made of nylon sheet and latex airfoils are better than those of wood airfoils is found