CFD Analysis of NACA 2415 and 23012 Airfoil

Two dimensional models for the airfoils were created, drawn and meshed in ANSYS Mechanical using geometry data gathered by the National Advisory Committee for Aeronautics. ANSYS FLUENT is used for computing flow over the two dimensional NACA 2415 and 23012 airfoil at an angle of attack of 4°. The computations are carried out at high Reynolds number at standard roughness conditions. One of the popular meshes for simulating an airfoil in a stream is a C-Mesh, and that is what we will be using. At the inlet of the system, we will define the velocity as entering at a 4° angle of attack, and at a total magnitude of 1. We will also define the gauge pressure at the inlet to be 0. As for the outlet, the only thing we can assume is that the gauge pressure is 0. As for the airfoil itself, we will treat it like a wall. From the analysis, CP (Coefficient of Pressure) distribution, CL (Coefficient of Lift) and CD (Coefficient of Drag) is estimated and compared with the experimental results.