This project aimed to modify the vortex panel code developed previously to accept multiple airfoils and plot the streamlines around the airfoil system. The code also estimates each airfoil's lift coefficient and the whole system's total lift coefficient. The code was written in Python and uses an input JSON file to control the user-defined inputs. The code also implements an RK45 numerical integration method to calculate the streamline locations. 

User-defined Inputs:

• Number of Airfoils

• NACA 4-digit series for each airfoil with a closed trailing edge

• Chord lengths for each airfoil

• Mounting angle for each airfoil

• Location of the leading edge for each airfoil

• Number of nodes for each airfoil

• Free stream velocity

• The angle of attack relative to the aircraft centerline

• Number of streamlines 

• Y spacing of the streamlines