Force and moment characterization of flapping wings for micro air vehicle application

摘要: This paper presents a method for investigating the unsteady aerodynamics of flapping wings micro air vehicle application. For this purpose, robotic flapper was designed and fabricated which can flap dynamically scaled in desired kinematic pattern. An aerodynamic model wing testing methodology developed based on mechanisms. additionally accounts twisting. The experimental results show good agreement with published data compares well results. focus present work is hovering flight, however, general be extended to forward flight future.