Effects of camber angle on aerodynamic performance of flapping-wing micro air vehicle |
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| Institution: | 1. Faculty of Aerospace Engineering, Delft University of Technology, Kluyverweg 1, 2629 HS Delft, The Netherlands;2. Temasek Laboratories, National University of Singapore, 5A Engineering Drive 1, 117411, Republic of Singapore;1. School of Mechanical Engineering and Automation, Harbin Institute of Technology, Shenzhen, China;2. School of Aeronautics, Northwestern Polytechnical University, Xi''an, China;1. Artificial Muscle Research Center, Konkuk University, Seoul 143-701, South Korea;2. National Research Laboratory for Biomimetics and Intelligent Microsystems, Konkuk University, Seoul 143-701, South Korea;3. Department of Advanced Technology Fusion, Konkuk University, Seoul, 143-701, South Korea;4. Laboratory of Applied Mechanics, Faculty of Applied Science, Ho Chi Minh City University of Technology, Ho Chi Minh, 740-128, Vietnam;1. National Key Laboratory of Science and Technology on Micro/Nano Fabrication, Key Laboratory for Thin Film and Microfabrication of the Ministry of Education, Department of Micro-Nano Electronics, School of Electronic Information and Electrical Engineering, Shanghai Jiao tong University, 200240, Shanghai, People''s Republic of China;2. Zhiyuan College, Shanghai Jiao tong University, 200240, Shanghai, People''s Republic of China |
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| Abstract: | This study investigates the unsteady aerodynamic characteristics of the cambered wings of a flapping-wing micro air vehicle (FW-MAV) in hover. A three-dimensional fluid–structure interaction solver is developed for a realistic modeling of large-deforming wing structure and geometry. Cross-validation is conducted against the experimental results obtained also in the present study to establish more accurate analyses of cambered wings. An investigation is carried out on the unsteady vortex structures around the wings caused by the passive twisting motion. A parametric study is then conducted to evaluate the aerodynamic performance with respect to the camber angle at three different flapping frequencies including normal operating conditions. The camber angles producing the largest thrust and highest propulsive efficiency are estimated at each flapping frequency, and their effects on aerodynamic performance are analyzed in terms of the stroke phase. The timing and magnitude of the passive twisting motion, which are dependent on the camber angle at the operating frequency, greatly affects the unsteady vortex structure. Consequently, the camber angle designed at the operating frequency plays a key role in enhancing the aerodynamic performance of FW-MAVs. |
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| Keywords: | Flapping-wing micro air vehicles (FW-MAV) Fluid–structure interaction (FSI) Cambered wing Passive twist Insect-like |
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