Comparison of the Aerodynamic Performance characteristics of NACA 2312 and NACA 2412 aerofoils under the same flow conditions at a Reynolds number of 2.74 x 106 is presented. ANSYS is used for the creation of geometry and meshing and FLUENT is used as a solver. Coefficient of lift and coefficient of drag for both aerofoils are compared for a range of Angle of Attack while the free stream velocity of air is kept constant. This analysis can be used for the wing design and other aerodynamic modelling corresponds to these aerofoils.

Keywords : Aerofoil, Angle of Attack, Coefficient of lift, Coefficient of drag, K-omega SST, NACA2312, NACA2412.