Naca airfoil ploting in matplotlib python

Code:

from matplotlib.pyplot import *

from numpy import *

t = .2 

c= 1.5

xc = linspace(0,1,100)

y1 = t*c/.2*(.296*sqrt(xc)-.126*xc-.3516*xc**2+.2843*xc**3-.1015*xc**4)

y2= -y1

plot(xc*c,y1,xc*c,y2)

Code explanation in video