Study of NACA 0012 Behavior at Different Angle of Attack

In this work computational fluid dynamics (CFD) flow simulation is performed on a 2D NACA 0012 airfoil. The simulations predict the fluid flow characteristics such as pressure and velocity around the airfoil by solving the steady state governing equations of continuity and momentum conservation. The lift (CL) and drag (CD) coefficients computed are compared with the available experimental data. The variation in different flow parameters are observed at various angles of attack. The computation is performed on various turbulence models that have been extensively implied i.e. Realizable
$k-\varepsilon$
and
$k-\omega$
shear stress transport (SST). The surface pressure distribution is also depicted and analyzed with respect to the angle of attack.