# RPM, Thrust
#Prop.ThrustData = [(8100 *RPM, 4 *LBF + 8*OZF),
# (9200 *RPM, 5 *LBF + 13*OZF),
# (11200 *RPM, 9 *LBF + 3*OZF)]
#
# RPM, Torque
#Prop.TorqueData = [(11000 *RPM, 114.768*IN*OZF)]
################################################################################
if __name__ == '__main__':
print "Max " + AsUnit(Prop.MaxRPM(), 'rpm', '%3.0f') + " at " + AsUnit(Prop.MaxTipSpeed, 'ft/s') + " tip speed ",
Vmax = 100
h=0*FT
N=npy.linspace(1000, 13000,4)*RPM
Alpha = npy.linspace(-25,25,31)*ARCDEG
V = npy.linspace(0,Vmax,11)*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)
pyl.show()
(9210 * RPM, (3.40 * Arm * OZF) * STD),
(10050 * RPM, (4.20 * Arm * OZF) * STD),
(10410 * RPM, (4.55 * Arm * OZF) * STD)]
################################################################################
if __name__ == '__main__':
Vmax = 100
h = 0 * FT
N = npy.linspace(1000, 10500, 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 = 10500 * RPM
print "Max " + AsUnit(Prop.MaxRPM(), 'rpm', '%3.0f') + " at " + AsUnit(
Prop.MaxTipSpeed, 'ft/s') + " tip speed "
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
