Got the NACA5 example working

example_naca5_drag.py

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+"""
+An example to show how to combine NACA5 airfoil_generator and XFOIL
+"""
+
+from airfoil_generators.naca5series import NACA5
+from xfoil.xfoil import oper_visc_cl
+import os
+
+import matplotlib.pyplot as plt 
+import numpy as np 
+
+Re = 1000000
+Cl = 0.2
+
+drags = np.zeros((5,3))
+
+for i in range(1,6):
+	if i==1:
+		mld = 210
+	elif i==2:
+		mld = 220
+	elif i==3:
+		mld = 230
+	elif i==4:
+		mld = 240 
+	else: 
+		mld = 250
+
+	if mld == 210:
+		m = .0580
+		k1 = 361.40
+		p = 0.05
+	elif mld ==220:
+		m = .1260
+		k1 = 51.640
+		p = 0.10
+	elif mld == 230:
+		m = .2025
+		k1 = 15.957
+		p = .15
+	elif mld == 240:
+		m = .2900
+		k1 = 6.643
+		p = 0.20
+	elif mld == 250:
+		m = .3910
+		k1 = 3.23
+		p = .25
+	for t in range(13,16):
+		airfoil = NACA5(mld,t)
+
+		temp_af_filename = "temp_airfoil_{}{}.dat".format(mld,t)
+
+		with open(temp_af_filename,'w') as af:
+			af.write(airfoil.get_coords_plain())
+
+		polar = oper_visc_cl(temp_af_filename, Cl, Re, iterlim=1000)
+
+		try:
+			drags[i-1][t-13] = polar[0][0][2]
+		except IndexError:
+			raise Warning("Shit! XFOIL didn't converge on NACA{}{} at Cl={}.".format(mld,t,Cl))
+
+		xl, yl, xu, yu, xc, yc = airfoil.get_coords()
+		def translated_plt(x, y, *args):
+			plt.plot(x*0.8 + (t-12.9), y*0.8 + (i-0.5) , *args)
+		translated_plt(xl, yl, 'w')
+		translated_plt(xu, yu, 'w')
+		translated_plt(xc, yc, 'w--')
+
+		os.remove(temp_af_filename)
+
+print drags
+plt.pcolor(drags, cmap=plt.cm.RdBu)
+
+plt.xlabel("Location of max. camber $p$")
+plt.ylabel("Max. camber $m$")
+
+cbar = plt.colorbar()
+cbar.ax.set_ylabel("Drag coefficient $C_d$")
+
+plt.tight_layout()
+plt.yticks( (.5,1.5,2.5,3.5,4.5), ("210t", "220t", "230t", "240t", "250t") )
+plt.xticks( (.5,1.5,2.5), ("mld13", "mld14", "mld15") )
+plt.show()

xfoil/__init__.py

@@ -0,0 +1 @@
+# This file lets Python see this directory as module.

xfoil/temp.dat

@@ -0,0 +1,161 @@
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