This project aimed to develop a vortex panel method for 2D airfoils to visualize stream lines around an airfoil as well as estimate the airfoils lift, pitching moment around the leading edge, pitching moment around the quarter cord, and pressure around the airfoil. The code is also capable of doing automated angle of attack sweeps. 

Airfoil user-defined options:

• NACA 4-digit airfoils.

• Uniform Load airfoils.

• Arbitrary airfoils provided an input text file.

• Open or closed trailing edge options.

• User-defined angle of attack and freestream velocity. 

This code is available for download on my git hub page, listed below.