Arıkan, Kutluk BilgeSenol,M.G.Arikan,K.B.Kurtulus,D.F.Department of Mechatronics Engineering2024-07-052024-07-0520171978-162410447-310.2514/6.2017-04982-s2.0-85017281907https://doi.org/10.2514/6.2017-0498https://hdl.handle.net/20.500.14411/3839This paper explores the design and testing of a flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced for flapping wing motion. Four-bar mechanism is activated by a servo motor which is driven by microcontroller. The wing undergoes a pure flapping motion at a fixed pitch angle. Force measurements are performed for hover mode by using a force transducer. In addition, 3D numerical analyses are performed and the results are compared with the experimental measurements. Overall, CFD results show good agreement with the experimental data. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.eninfo:eu-repo/semantics/closedAccess[No Keyword Available]Conference Object