# 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