Analysis of flow over NACA Airfoil

Objective: Objective of this project is to find and compare the drag and lift forces on the airfoil for various angles of attack, say 0,2,4,6,8,10. Procedure: Firstly, I downloaded the NACA0017 airfoil data from the link provided in the challenges page. Then, I opened a new part file in SolidWorks and inserted the airfoil…