Abstract
A method is presented for the optimum aeroelastic design of a flapping wing employing a lifting-surface theory as an aerodynamic tool and the complex method as the optimization algorithm. The method is applied to the optimum design of a flapping wing of a Kite Hawk (Milvus migrans) unmanned air vehicle and the optimum thickness distribution of the main spar is determined. As a result of the optimization, a high propulsive efficiency of 75% is attained considering only dihedral flapping of the main spar. By evaluating the viscous effect for this optimum design using a three-dimensional Navier-Stokes code, the effectiveness of the design is confirmed.
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