DESIGN OPTIMISATION AND PERFORMANCE ANALYSIS OF NACA 5 SERIES

This paper discusses about the Computational Analysis of NACA23012 and different parameters like Pressure contour, Velocity profile, Turbulence viscosity along with Streamline flow over NACA23012 2D Airfoil without any external surface like flaps slats and slots. NACA 23012 is a 5-digit NACA series having coefficient of lift 0.3. This Airfoil is analyzed by using Computational method with FLUENT in ANSYS software for Different Angle of attacks like -50, 00, 50, 70, 100,120, 16o. Analysis is carried out at a free stream velocity of 40m/s. The graphs between the performance parameters such as lift coefficient (cl) versus Alpha, lift coefficient Versus Drag Coefficient, Moment coefficient Versus Angle of attack and ci/cd versus Alpha which is the angle between chord line and free stream velocity vector has done using MATLAB and XFOIL software