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.