The following represents an aerodynamic analysis of a NACA12 airfoil using ANSYS's fluid flow module (Fluent). A pressure-based turbulence model is employed (K-Omega SST). The fluid medium is air and the airfoil itself is modeled as aluminum. From an initial and boundary conditions perspective, an input velocity is fed on one end and a pressure outlet is set on the other. The remaining edges are prescribed with a no-slip stationary wall condition.

The entire mesh and bounding region (left) and a close-up of the airfoil (right).

The results below demonstrate the basic principles of how lift is generated.