Abstract
Computational Fluid Dynamics (CFD) techniques are widely used in product development processes due to efficient algorithms to solve Navier Stokes equations. In this study, the coordinates of the NACA 1412 and NACA 2415 sections selected from the standard wing sections of the National Aviation Advisory Committee (NACA) have been implemented with specific procedures to create new geometries and a new wing profile design using the coordinate method. The wing profile geometry is created from the coordinates available in the literature. Fixed two-dimensional viscous flows around the generated wing profiles are simulated using commercially available ANSYS-Fluent software. The mesh structure used was created using the C type and rectangular structure. CFD and wind tunnel analysis of attack angles ranging from certain degrees. The aerodynamic coefficients of the related statuses, i.e. the lift and drag coefficients obtained from the analysis, have been compared with the wind tunnel test results. Aerodynamic research in recent years focuses on active flow control concepts, laminar flow control, fuel economy and higher transport/drag force ratio. This is designed to understand and analyze flow behavior around airfoils using the CFD method.
Sign-in/Register to access full text options 
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 callDisclaimer: 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.
