Computational analysis of NACA 0010 at moderate to high Reynolds number using 2D panel method

Abstract

Wing structures as found in aircrafts and wind turbine blades are built from airfoils. Computational methods are often used to predict the aerodynamic characteristics of airfoils, typically the force and pressure coefficients along its chord length. In the present work, pressure coefficient distribution of NACA 0010 is evaluated using the 2D panel method for incompressible lifting flows at moderate to high Reynolds number, Re-3 x10 5 , 5 x10 5 , 1x10 6. The analysis was conducted for various AOA (angle of attack), between-40 to 200 for the airfoil. The non-dimensional pressure is illustrated for upper and lower surfaces of airfoil between 00 to 200 angle of attack at specific chord locations of airfoil. The present results from the 2D panel method are validated using the results from Hess & Smith method and inverse airfoil design method implemented for conformal mapped symmetric Jukouwski airfoil of 10% thickness at 40 angle of attack.