Flow over a Airfoil- NACA 0012

A Flow analysis was done on NACA 0012 at the 15 Degree angle of Attack with the Turbulent flow at the velocity of 50 m/s. The Values of Aerodynamic Forces were obtained in the form of Coefficient of Lift and Drag.

Software used: STAR CCM+

Geometry and Meshing

Airfoil data was taken from Airfoil tools website. By using excel and the data was imported and geometry was made. Polygonal Meshing was done. Prism layers were added to capture better accuracy in computation near the wall. Wake refinement was done to better flow visualization at the wake region.

Boundary Conditions

A steady state simulation was done using gas with constant density as fluid. The flow type was set to be segregated Turbulent flow. K- epsilon Turbulent model was used.

Inlet Velocity was set to 50m/s

Gauge pressure was 0. (at Atmospheric pressure of 101325 kPa)