Simulação computacional do escoamento em torno de perfis de asa aeronáutica: uma abordagem numérica utilizando gurney flap

Abstract

The tool known as Computational Fluid Dynamics (CFD) has become increasingly effective in studies involving aerodynamics of limited-span aircraft. To apply this tool in projects developed by the GRIFO AERODESIGN team, a participant in the SAE AERODESIGN competition, this work aims to develop and validate a numerical methodology for analyzing aerodynamic devices, focusing on the Gurney flap, which can be replicated for other aerodynamic studies within the project. Initially, validation and mesh independence tests were conducted. Subsequently, CFD simulations were performed on NACA 4412 and 0012 airfoils with and without the Gurney flap, using Ansys Fluent® software with structured meshes of 50,000 to 100,000 elements. Mesh independence tests confirmed variations below 0.5%. Results demonstrated that implementing a 25 mm Gurney flap on the NACA 0012 airfoil increased the lift coefficient by up to 38% at angles of attack between 0∘ and 10∘, while raising drag by 25%, reducing the maximum lift-todrag ratio by 15%. The vorticity patterns generated by the Gurney flap aligned with referenced studies. It is concluded that the developed methodology can benefit the Grifo Aerodesign project, as the comparisons revealed expected behavioral trends for the device.