Simulation of Various Angles of Attack of NACA 23012 Airfoil Using CFD

This study focuses on the numerical investigation of the NACA 23012 aerofoil to improve its aerodynamic efficiency across different angles of attack. The primary goal is to enhance the lifting characteristics of the wing, which plays a crucial role during take-off and landing phases of flight. By implementing 20% split flaps, the aerofoil can generate higher lift without increasing the overall wing size, thereby effectively reducing drag and maintaining fuel efficiency. The aerofoil geometry and flap configuration were modelled using CATIA V5, and a Computational Fluid Dynamics (CFD) approach was employed for the analysis using ANSYS Fluent. Aerodynamic parameters, including lift coefficient, drag coefficient, and pressure distribution, were evaluated at various angles of attack to assess the performance improvements. The results of this study provide insights into the design optimization of aerofoils for high-lift applications in aircraft wings.