Computational fluid dynamics-based aerodynamic performance evaluation of naca 64A206 airfoil using ansys fluent

Aerodynamic performance evaluation of aircraft wings is a critical stage in aircraft design due to its direct influence on lift generation, flight stability, and overall efficiency. Computational Fluid Dynamics (CFD) methods provide an effective approach for predicting flow characteristics around airfoil geometries before experimental testing. Therefore, the objective of this study was to numerically investigate the aerodynamic behavior of the NACA 64A206 airfoil using ANSYS Fluent by evaluating velocity distribution, pressure variation, and lift coefficient characteristics.