AERODYNAMIC CHARACTERISTICS OF TWO DIFFERENT AIRFOILS USING PANEL METHOD

In this paper, a numerical investigation to analysis the potential flow over 2D airfoil, is carried out. The governing equation for potential flow is Laplace's equation, a widely studied linear partial differential equation. One of Green's theorem can be used to write a solution to Laplace's equation in a two-dimensional domain subjected to the Neumann boundary condition using Panel method. A computer program is developed by implementing a specific model using doublet panels of constant strength to compute the flow over a member of two different airfoil shapes (NACA0020 & NACA4412). The results are presented in terms of streamlines to show the behavior of the fluid flow for several values of angle of attack ( ). Also, pressure distribution, lift coefficient, pitching moment, and drag coefficient are calculated for the airfoils. The results show that the pressure distribution, lift coefficient, pitching moment, and drag coefficient are a strong function of the airfoil's geometry and the angle of attack. Also the peak value of the lift coefficient for NACA4412 is observed to occur at angle of attack of (10o) and its value is equal to (1.82), while its value is equal to (0.9) for NACA0020 at the same value of angle of attack. The numerical results of lift coefficient have been confirmed by comparing it with experimental and other numerical results. Good agreement was obtained.