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')
pyl.figure(1)
pyl.subplot(221)
pyl.title(Propulsion.Engine.name + ', ' + Propulsion.Prop.name)
pyl.plot(V / (FT / SEC), Ib)
pyl.grid()
pyl.xlabel('Aircraft Velocity (ft/s)')
pyl.ylabel('Current (A)')
pyl.subplot(222)
pyl.plot(V / (FT / SEC), Motor.Duration(N=Nm) / MIN)
pyl.grid()
# 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()
