from Aerothon.ACAirfoil import ACAirfoil
import os
Tiger = ACAirfoil('Tiger', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Tiger.PlotPolar()
Tiger.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA4408 = ACAirfoil('NACA4408', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA4408.PlotPolar()
NACA4408.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
E169_101 = ACAirfoil('E169_101', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
#E169_101.PlotPolar(fig=1)
E169_101.Plot2DPolar(fig=2)
#E169_101.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
E169 = ACAirfoil('E169', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
E169.PlotPolar(fig=1)
E169.Plot2DPolar(fig=2)
E169.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
S1223THKTE = ACAirfoil('S1223THKTE', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
S1223THKTE.PlotPolar()
S1223THKTE.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
LNV109A_9 = ACAirfoil('LNV109A_9', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
LNV109A_9.PlotPolar()
LNV109A_9.Plot2DPolar(fig=2)
LNV109A_9.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
S1223 = ACAirfoil('S1223', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
S1223.PlotPolar()
S1223.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
S1223RTL = ACAirfoil('S1223RTL', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
S1223RTL.PlotPolar()
S1223RTL.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
DFS03 = ACAirfoil('DFS03', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
DFS03.PlotPolar()
DFS03.Plot2DPolar(fig=2)
DFS03.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import pylab as pyl
from scalar.units import ARCDEG
af1 = ACAirfoil('e423')
af2 = ACAirfoil('S1223')
af3 = ACAirfoil('ch10sm')
af4 = ACAirfoil('fx74modsm')
#af1.PlotAirfoil(fig = 1, Alpha2d = 0*ARCDEG, subfig = 221)
#af2.PlotAirfoil(fig = 1, Alpha2d = 0*ARCDEG, subfig = 222)
#af3.PlotAirfoil(fig = 1, Alpha2d = 0*ARCDEG, subfig = 223)
#af4.PlotAirfoil(fig = 1, Alpha2d = 0*ARCDEG, subfig = 224)
af1.PlotAirfoil(fig=1, Alpha2d=0 * ARCDEG, subfig=None, yo=0.375, clr='g')
af2.PlotAirfoil(fig=1, Alpha2d=0 * ARCDEG, subfig=None, yo=0.125, clr='b')
af3.PlotAirfoil(fig=1, Alpha2d=0 * ARCDEG, subfig=None, yo=-0.125, clr='m')
af4.PlotAirfoil(fig=1, Alpha2d=0 * ARCDEG, subfig=None, yo=-0.375, clr='r')
#pyl.figure(1)
#pyl.subplot(221)
#pyl.title('Eppler 423 Airfoil')
#pyl.grid()
#
#pyl.subplot(222)
#pyl.title('Selig 1223 Airfoil')
#pyl.grid()
#
#pyl.subplot(223)
#pyl.title('Hollinger 10 smoothed Airfoil')
#pyl.grid()
from Aerothon.ACAirfoil import ACAirfoil
import os
Whale_14C = ACAirfoil('Whale_14C', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Whale_14C.PlotPolar()
Whale_14C.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
Michael1E423_D = ACAirfoil('Michael1E423_D', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Michael1E423_D.PlotPolar(fig=1)
Michael1E423_D.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA1410 = ACAirfoil('NACA1410', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA1410.PlotPolar()
NACA1410.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA4412 = ACAirfoil('NACA4412', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA4412.PlotPolar()
NACA4412.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import pylab as pyl
Airfoils = ["E423","E423_B","S1223"]#Main wing
#Airfoils = ["NACA2408","E169"]#Horz tail
#Airfoils = ["NACA0010","NACA0012","NACA0015"]#vert tail
for AirfoilName in Airfoils:
Airfoil = ACAirfoil(AirfoilName)
Airfoil.PlotReportPolars(fig=1, Re=413946)#main wing
#Airfoil.PlotReportPolars(fig=1, Re=174000)#tail horz and vert
pyl.subplot(311)
pyl.legend(Airfoils, loc = "best")
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
S1223Mod = ACAirfoil('S1223Mod', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
S1223Mod.PlotPolar()
S1223Mod.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
S1223_Awesome = ACAirfoil('S1223_A', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
S1223_Awesome.PlotPolar()
S1223_Awesome.Plot2DPolar()
S1223_Awesome.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA2812 = ACAirfoil('NACA2812', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA2812.Inverted = True
NACA2812.PlotPolar()
NACA2812.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
CLi4005b = ACAirfoil('CLi4005b', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
CLi4005b.PlotPolar()
CLi4005b.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import pylab as pyl
Airfoils = ["S1223", "S1223_TC", "E423"] #Main wing
# Airfoils = ["NACA6413","E169", "NACA0015"]
#Airfoils = ["E220", "E221", "E222"]#Horz tail
#Airfoils = ["NACA0010","NACA0012","NACA0015"]#vert tail
#
for AirfoilName in Airfoils:
Airfoil = ACAirfoil(AirfoilName)
Airfoil.PlotReportPolars(fig=1, Re=500000) #main wing
# Airfoil.PlotReportPolars(fig=1, Re=200000)#tail horz and vert
pyl.subplot(311)
pyl.legend(Airfoils, loc="best")
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
CLi4000 = ACAirfoil('CLi4000', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
CLi4000.PlotPolar()
CLi4000.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA0012 = ACAirfoil('NACA0012', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA0012.PlotPolar()
NACA0012.Plot2DPolar(fig=2)
NACA0012.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
Baby10_S1223A_LNV109A = ACAirfoil('Baby10_S1223A_LNV109A',
fext='.txt',
nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Baby10_S1223A_LNV109A.PlotPolar()
Baby10_S1223A_LNV109A.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
Michael1 = ACAirfoil('Michael1', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Michael1.PlotPolar()
Michael1.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
E423 = ACAirfoil('E423', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
E423.PlotPolar()
E423.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import pylab as pyl
afv = ACAirfoil('/NACA0012/NACA0012.dat','NACA0012')
afh = ACAirfoil('clarky/clarky.dat','clarky')
afh.Inverted = True
afv.PlotAirfoil(1)
afh.PlotAirfoil(2)
pyl.figure(1)
pyl.title('Vertical Tail Airfoil')
pyl.grid()
pyl.figure(2)
pyl.title('Horizontal Tail Airfoil')
pyl.grid()
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
SG6043 = ACAirfoil('SG6043', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
SG6043.PlotPolar()
SG6043.PlotAirfoil(fig=2)
pyl.show()
