Pressure Distribution & Aerodynamic characteristics of NACA Airfoils using Computational Panel Method for 2D Lifting flow

Determination of pressure distribution on airfoil profiles enables to understand the dynamic flow characteristics around the surface of wings or blades. Computational methods are widely applied in the field of aerodynamics to predict the aerodynamic characteristics such as the pressure, lift and drag coefficients on an airfoil. In the present paper, the pressure distribution of NACA airfoil profiles is calculated using the numerical panel method for 2D lifting air flow conditions. The analysis of airfoil geometry subjected to various AOA (angle of attack) including the stalling angles is considered to observe the variation in pressure coefficients along the chord. The zero lift AOA for the profiles are also evaluated in order to assess influence of thickness to chord ratios on airfoil characteristics.