Experimental and Numerical Results of a Flapping Wing Four Bar Mechanism

2017-01-13
Şenol, Münire Gülay
Arıkan, Kutlu Bilge
Kurtuluş, Dilek Funda
This paper exploresthedesign and testing ofa 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 apure flapping motion at afixed pitchangle. Force measurements are performed for hover modeby using a force transducer. In addition, 3D numericalanalyses are performed and the results are compared with the experimental measurements. Overall, CFD results showgood agreement with the experimental data.

Suggestions

Computational investigation of flow through a louvered inlet configuration
Tuncer, İsmail Hakkı (2001-01-01)
Viscous, subsonic flows through a flush louvered inlet configuration without inlet vanes are investigated using the overflow Navier-Stokes solver with overset grids. The variation of the mass flow rate through the engine intake as a function of intake pressure is assessed. The computed results show that the flow distortion and the pressure loss in the plenum chamber are significant, yet a sufficient amount of mass flow rate may be obtained at the expense of total pressure recovery.
Experimental analysis of 3-D sweeping wings
Çakır, Hasan; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2015)
The aim of this thesis is to modify the mechanism, which is capable of mimicking the insect flight and developed previously by the Aerospace Engineering Department, and to measure the forces and moments of three types of flapping wings fixed to this mechanism. The flapping wing design is a new research topic, comparably young area and can be the future for micro unmanned air vehicles. Time varying force and moment data obtained from the experiments conducted in water as part of this thesis can be used to de...
Numerical and experimantal analysis of flapping motion
Sarıgöl, Ebru; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2007)
The aerodynamics of two-dimensional and three-dimensional flapping motion in hover is analyzed in incompressible, laminar flow at low Reynolds number regime. The aim of this study is to understand the physics and the underlying mechanisms of the flapping motion using both numerical tools (Direct Numerical Simulation) and experimental tools (Particle Image Velocimetry PIV technique). Numerical analyses cover both two-dimensional and three-dimensional configurations for different parameters using two differen...
Testing of Flapping Wing Four Bar Mechanism
Şenol, Münier Gülay; Cömez, F Yudum; Kurtuluş, Dilek Funda; Arıkan, Kutluk Bilge (null; 2015-10-29)
The purpose of this paper is to do preliminary work to design and test a flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced forequation of motion of flapping wing. A validation case is selected upon the works of Konkuk University [4]. The type of mechanism is double rocker and the motion has a single-degree of freedom Four-bar mechanism is activated by a servo motor (ART-TECH AS-100) which is driven by Arduino Uno...
Experimental investigation of the effects of tip injection on the characteristics of the tip vortex on a model wind turbine
Anık, Ezgi; Uzol, Oğuz; Department of Aerospace Engineering (2015)
This study presents the results of an experimental study performed on a horizontal axis wind turbine to investigate the effects of spanwise steady tip injection on the tip flow characteristics of a model turbine. Experiments are performed in front of an open-jet wind tunnel facility on a specially designed model wind turbine that has a 3-bladed rotor with NREL S826 airfoil profile. The turbine has a specially designed injection system which consists of a pressure chamber, a hollow shaft, pressurized hub and...
Citation Formats
M. G. Şenol, K. B. Arıkan, and D. F. Kurtuluş, “Experimental and Numerical Results of a Flapping Wing Four Bar Mechanism,” 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/45979.