The Study of Streamlines and Pressure Distribution around a NACA 0015 Airfoil

In this paper the incompressible subsonic flow distribution and aerodynamic characteristics of NACA 0015 airfoil in Reynolds number 2e6 is verified. Contours of pressure distribution, velocity and streamlines are shown around the airfoil. Pressure coefficients, lift coefficients and lift to drag coefficient are obtained at different angles of attack. Th e simulation is done by Abaqus finite element software and XFLR5. Th e domain of analysis includes 24620 elements and 27775 nodes. Th e results were repeated as the number of elements increased. It means Increasing the number of elements does not affect the accuracy of the results and only increases the analysis time. However, In order to increase the accuracy and more detailed study of the boundary layer, meshing is done more carefully near the surface. Th e results show that by increasing the angle of attack, pressure coefficient increases. Th e stall angle is 18.3 degrees in Reynolds number 2e6.