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 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
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
NACA1408 = ACAirfoil('NACA1408', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA1408.PlotPolar()
NACA1408.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA4406 = ACAirfoil('NACA4406', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
NACA4406.PlotPolar()
NACA4406.PlotAirfoil(fig=2)
pyl.show()
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 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
Michael2 = ACAirfoil('Michael2', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
Michael2.PlotPolar()
Michael2.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
LNV109A_9_TV = ACAirfoil('LNV109A_9_TV', fext = '.txt', nalpha = 20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
LNV109A_9_TV.PlotPolar()
LNV109A_9_TV.Plot2DPolar(fig=2)
LNV109A_9_TV.PlotAirfoil(fig=3)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA2612 = ACAirfoil('NACA2612', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
#NACA2612.Inverted = True
NACA2612.PlotPolar()
NACA2612.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
NACA2808 = ACAirfoil('NACA2808', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
#NACA2808.Inverted = True
NACA2808.PlotPolar()
NACA2808.PlotAirfoil(fig=2)
pyl.show()
from Aerothon.ACAirfoil import ACAirfoil
import os
NACA0008 = ACAirfoil('NACA0008', fext='.txt', nalpha=20)
if __name__ == '__main__':
import pylab as pyl
#
# Plot the polars and the airfoil
#
#NACA0008.Inverted = True
NACA0008.PlotPolar()
NACA0008.Plot2DPolar(fig=2)
NACA0008.PlotAirfoil(fig=3)
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 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
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()
