Propulsion.nV = 30 if __name__ == '__main__': import pylab as pyl V = npy.linspace(0, Vmax, 30) * FT / SEC Vprop = npy.linspace(0, Vmax, 6) * FT / SEC N = Motor.NRange() Propulsion.PlotMatched(V, N, Vprop, fig=2, ylimits=[None, None, None, None]) #Propulsion.PlotTPvsN(N, Vprop, fig=3) Propulsion.PlotTestData(fig=3) #Propulsion.Draw(fig=4) Nm = Propulsion.RPMMatch(V) Ib = Motor.Ib(Nm) / A #rho = KG/M**3 #print AsUnit( 0.11 * rho * (6723*RPM/(2*math.pi))**3 * (9*IN)**4*(6*IN), 'W' ) #print AsUnit( Prop.P(N=Nm[0], V=0*FT/SEC, h=0*FT), 'W' ) print "Static Thrust : ", AsUnit(Propulsion.T(0 * FT / SEC), "ozf") print "Max efficiency current : ", AsUnit(Motor.I_Effmax(), 'A') print "Max efficiency RPM : ", AsUnit(Motor.N_Effmax(), 'rpm') print "Weight : ", AsUnit(Propulsion.Weight, 'lbf')
# Set Propulsion properties PropulsionOS = ACPropulsion(Prop, OS) PropulsionOS.Alt = 0 * FT PropulsionOS.Vmax = 100 * FT / SEC PropulsionOS.nV = 20 PropulsionMAG = ACPropulsion(Prop, Magnum) PropulsionMAG.Alt = 0 * FT PropulsionMAG.Vmax = 100 * FT / SEC PropulsionMAG.nV = 20 if __name__ == '__main__': import pylab as pyl print "Static Thrust :", AsUnit(PropulsionOS.T(0 * FT / SEC), "lbf") print "Static Thrust :", AsUnit(PropulsionMAG.T(0 * FT / SEC), "lbf") Vmax = 100 V = npy.linspace(0, Vmax, 30) * FT / SEC Vprop = npy.linspace(0, Vmax, 5) * FT / SEC N = npy.linspace(1000, 20000, 30) * RPM PropulsionOS.PlotMatched(V, N, Vprop, fig=2) PropulsionMAG.PlotMatched(V, N, Vprop, fig=2) #Propulsion.PlotTPvsN(N, Vprop, fig=3) PropulsionMAG.PlotTestData(fig=3) PropulsionOS.PlotTestData(fig=4) #Propulsion.Draw(fig=4) pyl.show()