INVESTIGATING THE LIFT AND DRAG COEFFICIENTS OF NACA 4412 AIRFOIL USING CFD SIMULATIONS

This research examines the aerodynamic behavior of a NACA 4412 airfoil under subsonic flow conditions. The behavior is examined in terms of the lift which is produced as a result of air attacking the airfoil. The paper systematically including pressure and velocity distribution as well as the variations in the lift , drag coefficient and lift to drag ratio is calculated against angle of attack for different inlet velocity conditions using a C-type geometry. The mathematical model comprises the Nervier-Stokes equations along with the Standard k-ϵ turbulence model to capture the turbulence. The mathematical model is a set of nonlinear partial differential equations to be solved simultaneously. Employing the fluid simulation software Ansys Fluent, which is based on finite volume method for numerical analysis to solve our problem. The results indicate that at the peak value of the lift to drag ratio of NACA 4412airfoil is attained under the various inlet velocity (2,4,6,8 )m/s 4 0 angle of attack. All tasks of simulations are accomplished using ANSYS Workbench 16.2.