Computational Analysis of the Effect of Change in Leading Edge Radius, Blending Distance from the leading edge and their combined effect on a standard NACA 0012 aerofoil

aerofoil is the cross-sectional shape obtained when a wing is brought in perpendicularity with a plane. The aerofoil used is the NACA 0012 symmetric aerofoil, alterations are duly made in order to analyse the flow pattern such as altering the leading-edge radius or the blending distance or both simultaneously in addition to change in angle of attack. This paper deals with the fundamental equations associated with the generation of NACA aerofoils. The aerofoil generation is done using MATLAB. Certain elementary changes are then made in the wing geometry and their respective changes are studied through their effects on the characteristic aerodynamic configuration of the aerofoil. Since the aerofoil chosen is symmetric the changes in the aerodynamic properties can be easily studied and their variation can be easily understood. These aerodynamic characteristics are studied by the non-dimensional flow parameters such as Cl, Cd and Cm