In one of my YouTube videos, I show how to run XFoil from a MATLAB script. For those of you that don’t have MATLAB or prefer Python, here is the same script, but now in Python. The functionality should be the exact same. I have uploaded a .txt file with the Python code because I am not able to upload Python files to my website at the moment. Just save it as a .py file when you download it (it will open in a new window).
Python_XFoil.py
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The code can also be seen below.
import os
import numpy as np
import matplotlib.pyplot as plt
# %% CREATE LOADING FILE
# Knowns
NACA = '0012'
AoA = '0'
numNodes = '170'
saveFlnmAF = 'Save_Airfoil.txt'
saveFlnmCp = 'Save_Cp.txt'
xfoilFlnm = 'xfoil_input.txt'
# Delete files if they exist
if os.path.exists(saveFlnmAF):
os.remove(saveFlnmAF)
if os.path.exists(saveFlnmCp):
os.remove(saveFlnmCp)
# Create the airfoil
fid = open(xfoilFlnm,"w")
fid.write("NACA " + NACA + "\n")
fid.write("PPAR\n")
fid.write("N " + numNodes + "\n")
fid.write("\n\n")
fid.write("PSAV " + saveFlnmAF + "\n")
fid.write("OPER\n")
fid.write("ALFA " + AoA + "\n")
fid.write("CPWR " + saveFlnmCp + "\n")
fid.close()
# Run the XFoil calling command
os.system("xfoil.exe < xfoil_input.txt")
# Delete file after running
if os.path.exists(xfoilFlnm):
os.remove(xfoilFlnm)
# %% READ DATA FILE: AIRFOIL
flpth = "C:/Users/Josh/Documents/Python/Panel_Methods/"
flnm = flpth + saveFlnmAF
# Load the data from the text file
dataBuffer = np.loadtxt(flnm, skiprows=0)
# Extract data from the loaded dataBuffer array
XB = dataBuffer[:,0]
YB = dataBuffer[:,1]
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if os.path.exists(saveFlnmAF):
os.remove(saveFlnmAF)
# %% READ DATA FILE: PRESSURE COEFFICIENT
# Load the data from the text file
dataBuffer = np.loadtxt(saveFlnmCp, skiprows=3)
# Extract data from the loaded dataBuffer array
X_0 = dataBuffer[:,0]
Y_0 = dataBuffer[:,1]
Cp_0 = dataBuffer[:,2]
# Delete file after loading
if os.path.exists(saveFlnmCp):
os.remove(saveFlnmCp)
# %% EXTRACT UPPER AND LOWER AIRFOIL DATA
# Split airfoil into (U)pper and (L)ower
XB_U = XB[YB >= 0]
XB_L = XB[YB < 0]
YB_U = YB[YB >= 0]
YB_L = YB[YB < 0]
# Split XFoil results into (U)pper and (L)ower
Cp_U = Cp_0[YB >= 0]
Cp_L = Cp_0[YB < 0]
X_U = X_0[YB >= 0]
X_L = X_0[YB < 0]
# %% PLOT DATA
# Plot airfoil
fig = plt.figure(1)
plt.cla()
plt.plot(XB_U,YB_U,'b.-',label='Upper')
plt.plot(XB_L,YB_L,'r.-',label='Lower')
plt.xlabel('X-Coordinate')
plt.ylabel('Y-Coordinate')
plt.title('Airfoil')
plt.axis('equal')
plt.legend()
plt.show()
# Plot pressure coefficient
fig = plt.figure(2)
plt.cla()
plt.plot(X_U,Cp_U,'b.-',label='Upper')
plt.plot(X_L,Cp_L,'r.-',label='Lower')
plt.xlim(0,1)
plt.xlabel('X-Axis')
plt.ylabel('Y-Axis')
plt.title('Pressure Coefficient')
plt.show()
plt.legend()
plt.gca().invert_yaxis()