Numerical Investigation on Wing Performance using Singularity Method

The numerical method is represented to predict wing performance at low speed. In this paper, the wing is simulated with airfoil NACA 0012, which is divided to a large number of panels, each panel approximated with linear strength vortex to model the flow pattern around an airfoil. The pressure coefficient distribution around the airfoil is numerically obtained for the same speed and different angles of attack which results to calculate the lift and drag coefficients. This paper is focused on the verification of lift and drag coefficients, where very good agreements have been obtained with several wellknown classical methods.