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()