# Set Propulsion properties
Propulsion = ACPropulsion(Prop, Motor)
Propulsion.Alt = 0 * FT
Propulsion.Vmax = Vmax * FT / SEC
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),
##from Scorpion250KV import Motor
#==============================================================================#
# PROPULSION MODEL
#==============================================================================#
# Set Propulsion properties
Propulsion = ACPropulsion(Prop, Motor)
Propulsion.Alt = 0 * FT
Propulsion.Vmax = 60 * FT / SEC
Propulsion.nV = 20
#==============================================================================#
# VISUALIZATION & RESULTS
#==============================================================================#
if __name__ == '__main__':
import pylab as pyl
print "Static Thrust :", AsUnit(Propulsion.T(0 * FT / SEC), "lbf")
Vmax = 60
V = npy.linspace(0, Vmax, 30) * FT / SEC
Vprop = npy.linspace(0, Vmax, 5) * FT / SEC
N = npy.linspace(1000, 20000, 30) * RPM
Propulsion.PlotMatched(V, N, Vprop, fig=2)
Propulsion.PlotTPvsN(N, Vprop, fig=1)
Propulsion.PlotTestData(fig=3)
Propulsion.Draw(fig=4)
pyl.show()
#
# RPM, Torque, Power
TestData = [(7000 * RPM, 107.35 * IN * OZF, 0.75 * HP),
(8500 * RPM, 104.24 * IN * OZF, 0.88 * HP),
(9500 * RPM, 101.13 * IN * OZF, 0.95 * HP),
(9700 * RPM, 98.02 * IN * OZF, 0.94 * HP),
(10600 * RPM, 102.69 * IN * OZF, 1.08 * HP),
(10800 * RPM, 98.02 * IN * OZF, 1.05 * HP),
(11000 * RPM, 101.13 * IN * OZF, 1.1 * HP),
(11200 * RPM, 99.57 * IN * OZF, 1.11 * HP),
(11600 * RPM, 98.02 * IN * OZF, 1.13 * HP),
(12900 * RPM, 93.35 * IN * OZF, 1.19 * HP),
(13300 * RPM, 91.79 * IN * OZF, 1.21 * HP),
(13600 * RPM, 91.79 * IN * OZF, 1.24 * HP),
(14600 * RPM, 88.68 * IN * OZF, 1.28 * HP),
(15600 * RPM, 79.35 * IN * OZF, 1.23 * HP),
(16300 * RPM, 77.76 * IN * OZF, 1.26 * HP)]
Engine.TestData = TestData
Engine.PlotTestData()
V = npy.linspace(0, 100, 30) * FT / SEC
N = npy.linspace(1000, 20000, 30) * RPM
Propulsion.PlotMatched(V, fig=2)
V2 = npy.linspace(0, 100, 5) * FT / SEC
Propulsion.PlotTPvsN(N, V2, fig=3)
Propulsion.Draw(fig=4)
pyl.show()
# 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()