CFD SIMULATIONS FOR FLOW BEHAVIOR AROUND NACA 0012 AIRFOIL

This research examines the aerodynamic behavior of a NACA 0012 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. Lift coefficient 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. We used the finite volume method to solve our problem. All tasks of simulations are accomplished using ANSYS Workbench 16.2.