Aerodynamic Load Analysis on Flapping Wings Using Unsteady Vortex-Lattice Method

Aeroelastic studies of flapping wings on Micro Aerial Vehicle (MAV) that adopts bird or insect wing motion are very important because of their excellent maneuverability. Analysis in this simulation study with Unsteady Vortex-Lattice Methods (UVLM). The simulation results can be noted that in the downstroke motion, high vortex strength values produce significant lift force and vice versa in the upstroke. The greater flow deflection at high angles of attack and airfoil curvature that depends on the camber value produce pressure differences at the bottom and top of the wing. The lift force value affects the pitching moment value and induced drag value.