How to use with non NACA airfoil?

[zonexo]

Hi,

I got the naca0012 example working. Is there an example how to get it working with non NACA airfoil? Thanks!

[parmonom]

import numpy as np
from xfoil import XFoil
from xfoil.model import Airfoil

xf = XFoil()

#x, y coordinates of your airfoil
x = np.array([1.     , 0.98037, 0.93064, 0.8537 , 0.75616, 0.64594, 0.53099,
              0.41638, 0.30609, 0.20549, 0.11999, 0.05468, 0.01338, 0.     ,
              0.01338, 0.05468, 0.11999, 0.20549, 0.30609, 0.41638, 0.53099,
              0.64594, 0.75616, 0.8537 , 0.93064, 0.98037, 1.     ])
y = np.array([0.001341,  0.008009,  0.014067,  0.026066,  0.040484,  0.054959,
              0.06816 ,  0.078438,  0.083164,  0.080166,  0.068108,  0.047083,
              0.019785, -0.000696, -0.018018, -0.032271, -0.041626, -0.048684,
             -0.053613, -0.052991, -0.048566, -0.041285, -0.031565, -0.021308,
             -0.012699, -0.007986, -0.00155 ])

xf.airfoil = Airfoil(x, y)

This worked for me. With x, y, the coordinates of your airfoil.

[sahilbhola14]

airfoil_data.txt XFOIL works with the attached file with the following set of commands,

LOAD airfoil_data.txt airfoil_data PANE OPER Visc 6000000 PACC polar_file.txt

ITER 100 alfa 10

quit

However, it is not working with the package,
x = data_1[:, 0] y = data_1[:, 1] xf.airfoil = Airfoil(x, y) xf.Re = 6e6 xf.max_iter = 500 cl, cd, cm, cp = xf.a(10)

[sphh]

@sahilbhola14: Without seeing your error message, it is difficult to say, what is going wrong. But the ongoing development at codepage added the possibility to load the airfoil data from a file (and save it to a file). See https://codeberg.org/xfoil-python/xfoil-python/issues/12