Abstract
Abstract: This research paper gives insight to the analysis of NACA 1412 airfoil. The airfoil is the two-dimensional cross section of the aircraft’s wing. The aircraft flies due to generation of the lift, this lift is caused by the pressure difference on the upper and lower surface of the airfoil. The pressure on the lower surface is greater than the pressure on upper surface which provides a lift to the airfoil. We are going to see the airfoil’s behaviour in incompressible flow at different angles of attack with constant velocity. In this research, we are going to use the Ansys software to do the analysis. This research is based on the computational fluid dynamics concepts. At the end, we will see how the lift and drag changes at different angles of attack and some graphical results from the research.
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