Flap Effect on Trailing Edge of an Airfoil Simulation, ANSYS Fluent Training

In this project, steady airflow over a flapped airfoil with an attack angle equal to 12 degrees is investigated by ANSYS Fluent software. Air velocity magnitude is equal to 45 m, s. The lift coefficient of an airfoil with and without the flap is equal to 1. 2182 and 1. 0530, which shows the effectiveness of flap in aerodynamic lift force generation. Moreover, the drag coefficient of the airfoil in the presence of flap is equal to which is less than airfoil without flap where the drag coefficient is equal to which proves that flap presence is effective in drag force reduction that is favorable in aerodynamics applications.