Numerical Investigation of Aerodynamic Characteristics of NACA 4312 Airfoil with Gurney Flap

This paper presents a two-dimensional Computational Fluid Dynamics (CFD) analysis on the effect of gurney flap NACA 4312 airfoil in subsonic flow. These numerical simulations were conducted for heights 1.5%, 1.75%, 2% and 3% chord length at fixed Reynold Number, Re (5×105) different angle attack (0o ~16o). ANSYS Fluent commercial software was used to conduct these simulations. The flow considered as incompressible K-omega Shear Stress Transport (SST) model selected. results demonstrate that lift coefficient increase up around 12o AoA (angle attack) with without flap. For every drag presented proportionate behavior height. However, co-efficient decreased after due separation. Maximum ratio found 4o 1.5%C (chord length) had shown most optimized aerodynamic performance through analysis. study concluded displayed enhanced than delay