def test_Power(self):
"""
Tests that the engine class is working properly
"""
# Create the propeller defined in the mathcad pdf documents
Prop = ACPropeller()
Prop.D = 14.2*IN
Prop.PitchAngle = 12*ARCDEG
# Prop.Pitch = 7.1117*IN
Prop.dAlpha = 0*ARCDEG
Prop.Solidity = 0.0136
Prop.RD = 3/8
Prop.AlphaStall = 14*ARCDEG
N = 11400 * RPM
self.assertAlmostEqual(Prop.P(N, 0*FT/SEC, 0*FT) / HP, 1.2950, 4)
print " D : ", AsUnit(Prop.D, 'in')
print " Pitch : ", AsUnit(Prop.Pitch, 'in')
Vmax = 50
h = 0 * FT
N = npy.linspace(1000, 6800, 6) * RPM
Alpha = npy.linspace(-25, 25, 41) * ARCDEG
V = npy.linspace(0, Vmax, 30) * FT / SEC
Prop.CoefPlot(Alpha, fig=1)
Prop.PTPlot(N, V, h, 'V', fig=2)
#
# N = npy.linspace(0, 13000,31)*RPM
# V = npy.linspace(0,Vmax,5)*FT/SEC
#
# Prop.PTPlot(N,V,h,'N', fig = 3)
Prop.PlotTestData(fig=4)
N = 2414 * RPM
print
print "Static Thrust : ", AsUnit(Prop.T(N, 0 * FT / SEC, h), 'lbf')
print "Measured Thrust : ", AsUnit(max(npy.array(Prop.ThrustData)[:, 1]),
'lbf')
print
print "Static Torque : ", AsUnit(
Prop.P(N, 0 * FT / SEC, h) / N, 'in*ozf')
# print "Measured Torque : ", AsUnit( max(npy.array(Prop.TorqueData)[:,1]), 'in*ozf' )
pyl.show()
print " D : ", AsUnit( Prop.D, 'in')
print " Pitch : ", AsUnit( Prop.Pitch, 'in')
Vmax = 50
h=0*FT
N=npy.linspace(1000, 6800, 5)*RPM
Alpha = npy.linspace(-25,25,41)*ARCDEG
V = npy.linspace(0,Vmax,30)*FT/SEC
Prop.CoefPlot(Alpha,fig = 1)
Prop.PTPlot(N,V,h,'V', fig = 2)
#
# N = npy.linspace(0, 13000,31)*RPM
# V = npy.linspace(0,Vmax,5)*FT/SEC
#
# Prop.PTPlot(N,V,h,'N', fig = 3)
Prop.PlotTestData(fig=4)
N = 6024*RPM
print
print "Static Thrust : ", AsUnit( Prop.T(N, 0*FT/SEC, h), 'lbf' )
print "Measured Thrust : ", AsUnit( max(npy.array(Prop.ThrustData)[:,1]), 'lbf' )
N = 6410*RPM
print
print "Static Torque : ", AsUnit( Prop.P(N, 0*FT/SEC, h)/N, 'in*ozf' )
print "Measured Torque : ", AsUnit( max(npy.array(Prop.TorqueData)[:,1]), 'in*ozf' )
pyl.show()
