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18 April 2008 An aeroelastic analysis of a flexible flapping wing using modified strip theory
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Abstract
The present study proposed a coupling method for the fluid-structural interaction analysis of a flexible flapping wing. An efficient numerical aerodynamic model was suggested, which was based on the modified strip theory and further improved to take into account a high relative angle of attack and dynamic stall effects induced by pitching and plunging motions. The aerodynamic model was verified with experimental data of rigid wings. A reduced structural model of a rectangular flapping wing was also established by using flexible multibody dynamics and a modal approach technique, so as to consider large flapping motions and local elastic deformations. Then, the aeroelastic analysis method was developed by coupling these aerodynamic and structural modules. To measure the aerodynamic forces of the rectangular flapping wing, static and dynamic tests were performed in a low speed wind-tunnel for various flapping pitch angles, flapping frequencies and the airspeeds. Finally, the aerodynamic forces predicted by the aeroelastic analysis method showed good agreement with the experimental data of the rectangular flapping wing.
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Dae-Kwan Kim, Jun-Seong Lee, Jin-Young Lee, and Jae-Hung Han "An aeroelastic analysis of a flexible flapping wing using modified strip theory", Proc. SPIE 6928, Active and Passive Smart Structures and Integrated Systems 2008, 69281O (18 April 2008); https://doi.org/10.1117/12.776137
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