Open zonexo opened 4 years ago
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.
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)
@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
Hi,
I got the naca0012 example working. Is there an example how to get it working with non NACA airfoil? Thanks!