Numerical Study of a NACA0012 Profile with Coanda Flap for a Small UAV

This study presents a numerical investigation using Computational Fluid Dynamics (CFD) on a NACA0012 airfoil equipped with an active flow-control flap based on the Coanda effect. The objective is to enhance the aerodynamic efficiency of a small Unmanned Aerial Vehicle (UAV) during various phases of flight. By combining different angles of attack, flap deflections, and jet powers that generate the Coanda effect above the flap, the study explores 75 flight conditions to find the optimal configurations for the profile and flap to improve lift and reduce drag. Aerodynamic forces are extracted for each condition and non-dimensional velocity contours show the aerodynamic effect on the flow when introducing active flow control. In comparison with the airfoil with no active flow control applied, the addition of blowing significantly increases lift values (between 10% and up to 91%), especially under low angles of attack and flap deflections. Results aim to support the development of advanced small-UAV designs with higher efficiency and maneuverability through active flow control.