The results obtained by xfoi-python are different from those obtained by xfoil #27
Description
I'm trying to calculate the drag coefficient, but the same parameters give different results in xfoil and xfoil-python.
airfoil-2.0_0.7.txt
Re = 400000, alfa = 0.0.
The cd obtained from xfoil is 0.00519, while the cd obtained from xfoil-python is 0.0033630472607910633.