Aerodynamic Analysis and Wind Tunnel Test for Flapping-wing Mavs
نویسندگان
چکیده
A lightweight flapping-wing micro air vehicle (MAV) was designed and built and successfully filed in the sky. The unsteady aerodynamics associated with this MAV was detailedly studied by using the method of computational fluid dynamics (CFD).The variations of different parameters of the flapping MAV, such as flapping amplitude, pitch amplitude and flapping frequency, were investigated with numerical simulation. The Fluid-Structure coupling mechanics for flexible flapping-wings were subsequently researched and discussed. According to the practically developed MAV, a 2-D model for flexible flapping-wings was established. Fluid-Solid interaction deformation and its effects on the aero dynamic performance were analyzed, which offers a theoretical basis for design of the aircraft with flexible flapping-wing. The results of numerical simulation for the rigid and flexible flapping-wings were finally verified by conduct the aerodynamic performance tests in a low turbulence and low Reynolds number wind tunnel.
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