Create a mesh of a airfoil
Run the file mainSU2 in python 3
Input data:
N = 101 # Airfoil number of points
M = 50 # 20
c = 1. # Chord [m]
m = 2. # Is the maximum camber (100 m is the first of the four digits),
p = 5. # Is the location of maximum camber (10 p is the second digit in the NACA xxxx description).
t = 12. # Is the maximum thickness as a fraction of the chord # (so t gives the last two digits in the NACA 4-digit denomination divided by 100)