# from os import environ as _environ; _environ["scalar_off"] = "off" import numpy as npy import pylab as pyl from scalar.units import FT, SEC, LBF, MIN, IN from Aircraft_Models.Adv2014Aircraft_AeroCats.MonoWing.Aircraft import Aircraft pyl.figure(1) # # Get the design point # dsgnGR = Aircraft.Groundroll() / (FT) dsgnCR = Aircraft.Rate_of_Climb(1.07*Aircraft.GetV_LO()) / (FT/MIN) pyl.plot([dsgnCR],[dsgnGR],'ro', markersize = 8) # # Set up ranges # Vstl = npy.linspace(31,35,5)*FT/SEC WT = npy.linspace(30,34,5)*LBF Vplt = Vstl / (FT/SEC) lgnd = ['Design'] arealist = [] # Initialize data arrays grndroll = npy.zeros((len(WT),len(Vstl))) clmbrate = npy.zeros((len(WT),len(Vstl)))
#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 lgnd = ['Design W = %2.2f (lbf)' % (Aircraft.TotalWeight / LBF)] arealist = [] # Initialize data arrays grndroll = npy.zeros((len(TotalWeight), len(S))) clmbrate = npy.zeros((len(TotalWeight), len(S)))