Year-end Sale % OFF 
Abstract
This study aims to develop an unsteady aerodynamic model and blade element momentum theory to analyze the aeroelasticity of a rotating airfoil with trailing edge flap of a wind turbine blade. The Hamiltonian principle serves to define the equations of motion. Theodorsen and Loewy aerodynamic models alone and together with blade element momentum (BEM) theory are applied to form aeroelastic equation of motion. Theodorsen or Loewy aerodynamics together with BEM theory present a new flexible unsteady blade element momentum aerodynamic model. Verification of developed aeroelastic equation motion is conducted on a fixed and a rotating airfoil successfully. Flutter boundary results imply the superiority of proposed aerodynamic model. Besides, we investigated theoretical effects of pitch and flap stiffness changes on flutter. The derived results demonstrate that pitch stiffness is the dominant mode on flutter boundary of the rotating blade section with a control surface.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: Journal of the Brazilian Society of Mechanical Sciences and Engineering
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
