from __future__ import division # let 5/2 = 2.5 rather than 2 #from os import environ as _environ; _environ["scalar_off"] = "off" from Aircraft_Models.Adv2014Aircraft_AeroCats.MonoWing.Aircraft import Aircraft import pylab as pyl Aircraft.PlotTailLoad(fig=2) Aircraft.Draw() pyl.show()
#from Aircraft_158 import Aircraft #from Aircraft_160 import Aircraft #from Aircraft_Models.Reg2013Aircraft_AeroCats.MonoWing.AircraftGE import Aircraft #from Aircraft_144GE import Aircraft #from Aircraft_148GE import Aircraft #from Aircraft_150GE import Aircraft #from Aircraft_152GE import Aircraft #from Aircraft_154GE import Aircraft #from Aircraft_155GE import Aircraft #from Aircraft_156GE import Aircraft #from Aircraft_158GE import Aircraft #from Aircraft_Models.Reg2013Aircraft_AeroCats.TradeStudies.LowMoment.Aircraft import Aircraft Aircraft.Draw(fig=2) pyl.figure(1) # # Get the design point # dsgnGR = Aircraft.Groundroll() / (FT) dsgnCR = Aircraft.Rate_of_Climb() / (FT / MIN) pyl.plot([dsgnCR], [dsgnGR], 'ro', markersize=8) # # Set up ranges # S = npy.linspace(1800, 3200, 4) * IN**2 TotalWeight = npy.linspace(27, 30, 5) * LBF