An Investigation on NACA 2312 Aerofoil With Curved And Straight Leading Edge Wing

Abstract

The Theoretical and experimental investigation to explore better aerodynamic performance by incorporating curvature at the leading edge of a wing. A model with straight leading and trailing edge i.e. rectangular planform and another model with curved leading edge and straight trailing edge are prepared with NACA 2312 airfoil in equal length (span) and surface area. Both the models are tested in a  wind tunnel at air speed of  23.71 m/s (0.07 Mach) i.e. at Reynold’s number 1.82 x 10⁵. The lift coefficient, drag coefficient and lift to drag ratio of both the models are analysed. The Theoretical investigation to explore better aerodynamic performance by incorporating the leading edge of a wing. A NACA 2312 Airfoil is designed and modelled by using SOLIDWORKS. Modelled the NACA 2312 airfoil with the straight leading edge wing and curved leading edge wing by using SOLIDWORKS and analyse the two wings by using SOLIDWORKS-Flow simulation. After analysing the results by using experimental and theoretical investigation the NACA 2312 airfoil with curved leading edge wing having higher lift to drag ratio than the NACA 2312 Airfoil with straight leading edge wing. After comparing the theoretical results and experimental results there is a 20% of deviation exists. The theoretical results are 20% better than the experimental results..