# These are corrected for standard day # # Second set of data taken - concern about first set since taken at night STD = STDCorrection(30.00 * inHg, (22 + 273.15) * K) Prop.ThrustData = [ (2179 * RPM, 19.28 * OZF * STD), (2459 * RPM, 91 * OZF * STD), (3124 * RPM, 147 * OZF * STD), (3505 * RPM, 187 * OZF * STD), (3693 * RPM, 205 * OZF * STD), (3952 * RPM, 235 * OZF * STD) ] # this point taken after initial points on Hacker A50. Used to verify good data. # Torque is calculated from motor kv and RPM # Took torque data in closet with known prop to observe difference between temp Prop.TorqueData = [(2072 * RPM, (47 * STD * OZF * IN)), (2730 * RPM, (81 * STD * OZF * IN)), (3182 * RPM, (132 * STD * OZF * IN)), (3659 * RPM, (200 * STD * OZF * IN)), (4414 * RPM, (331 * STD * OZF * IN))], ################################################################################ if __name__ == '__main__': 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
(8670 * RPM, (8 * LBF + 3 * OZF) * STD), (9210 * RPM, (8 * LBF + 8 * OZF) * STD), (9660 * RPM, (9 * LBF + 1 * OZF) * STD), (9670 * RPM, (9 * LBF + 3 * OZF) * STD)] Prop.ThrustData += ThrustData Arm = 19.5 * IN # RPM, Torque Prop.TorqueData = [(9720 * RPM, (4.75 * Arm * OZF) * STD), (4470 * RPM, (.50 * Arm * OZF) * STD), (5610 * RPM, (1.20 * Arm * OZF) * STD), (6690 * RPM, (1.75 * Arm * OZF) * STD), (8010 * RPM, (3.0 * Arm * OZF) * STD), (8640 * RPM, (3.60 * Arm * OZF) * STD), (9330 * RPM, (4.35 * Arm * OZF) * STD), (9720 * RPM, (4.65 * Arm * OZF) * STD), (9300 * RPM, (4.40 * Arm * OZF) * STD), (8460 * RPM, (3.25 * Arm * OZF) * STD), (7230 * RPM, (2.30 * Arm * OZF) * STD), (4560 * RPM, (.75 * Arm * OZF) * STD)] ################################################################################ if __name__ == '__main__': Vmax = 100 h = 0 * FT N = npy.linspace(1000, 10000, 5) * RPM Alpha = npy.linspace(-25, 25, 41) * ARCDEG V = npy.linspace(0, Vmax, 30) * FT / SEC
# PROPELLER A ############### # Standard correction STD = STDCorrection(29.96 * inHg, (12.7 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(5550 * RPM, 177 * OZF * STD), (5020 * RPM, 142 * OZF * STD), (4540 * RPM, 116 * OZF * STD), (4030 * RPM, 88 * OZF * STD), (3530 * RPM, 72 * OZF * STD)] Arm = 19.5 * IN * STD Prop.TorqueData = [(5580 * RPM, (9.3 * Arm * OZF)), (4980 * RPM, (7.1 * Arm * OZF)), (4500 * RPM, (5.7 * Arm * OZF)), (3930 * RPM, (4.5 * Arm * OZF)), (3450 * RPM, (3.4 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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
# # These are corrected for standard day # #Standard correction STD = STDCorrection(30.32 * inHg, (5 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(5661 * RPM, 167 * OZF * STD), (5010 * RPM, 128 * OZF * STD), (4500 * RPM, 102 * OZF * STD), (4088 * RPM, 85 * OZF * STD), (3514 * RPM, 61 * OZF * STD)] Arm = 19.5 * IN * STD Prop.TorqueData = [(5802 * RPM, (11.1 * Arm * OZF)), (5050 * RPM, (8.4 * Arm * OZF)), (4580 * RPM, (6.85 * Arm * OZF)), (4024 * RPM, (5.3 * Arm * OZF)), (3557 * RPM, (4.1 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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
(10140 * RPM, (7 * LBF + 4 * OZF) * STD), (10380 * RPM, (7 * LBF + 3 * OZF) * STD), (10380 * RPM, (7 * LBF + 1 * OZF) * STD)] #Standard correction for 2:00 pm for the test day STD = STDCorrection(29.75 * inHg, (17 + 273.15) * K) Arm = 19.5 * IN # RPM, Torque Prop.TorqueData = [(10560 * RPM, (4.6 * Arm * OZF) * STD), (5670 * RPM, (.9 * Arm * OZF) * STD), (7800 * RPM, (2.35 * Arm * OZF) * STD), (9060 * RPM, (3.50 * Arm * OZF) * STD), (11130 * RPM, (4.25 * Arm * OZF) * STD), (10440 * RPM, (4.5 * Arm * OZF) * STD), (5670 * RPM, (1.35 * Arm * OZF) * STD), (7230 * RPM, (1.95 * Arm * OZF) * STD), (8250 * RPM, (2.35 * Arm * OZF) * STD), (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
STD = STDCorrection(30.05*inHg, (16 + 273.15)*K) # RPM, Thrust Prop.ThrustData = [(5910 *RPM, 138*OZF*STD), (5550 *RPM, 117*OZF*STD), (5010 *RPM, 97*OZF*STD), (4530 *RPM, 80*OZF*STD), (3960 *RPM, 60*OZF*STD), (3450 *RPM, 46*OZF*STD)] STD2 = STDCorrection(29.90*inHg, (24 + 273.15)*K) Arm = 19.5*IN*STD2 Prop.TorqueData = [(5920 *RPM, (7.7*Arm*OZF)), (5550 *RPM, (6.6*Arm*OZF)), (4980 *RPM, (5.3*Arm*OZF)), (4410 *RPM, (4.7*Arm*OZF)), (4050 *RPM, (3.6*Arm*OZF)), (3540 *RPM, (2.5*Arm*OZF))] ################################################################################ if __name__ == '__main__': 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
# RPM, Thrust Prop.ThrustData = [(2500 * RPM, 21 * OZF * STD), (3500 * RPM, 46 * OZF * STD), (4500 * RPM, 81 * OZF * STD), (5430 * RPM, 122 * OZF * STD)] ################################################### # TORQUE DATA NOT YET TAKEN - not from this prop. ################################################### STD2 = STDCorrection(29.95 * inHg, (28 + 273.15) * K) Arm = 19.5 * IN * STD2 # RPM TORQUE Prop.TorqueData = [(6250 * RPM, (7.6 * Arm * OZF)), (6000 * RPM, (7.4 * Arm * OZF)), (5520 * RPM, (6.1 * Arm * OZF)), (4980 * RPM, (4.9 * Arm * OZF)), (4050 * RPM, (3.1 * Arm * OZF)), (3000 * RPM, (1.8 * Arm * OZF)), (2010 * RPM, (0.8 * Arm * OZF))] ################################################################################ if __name__ == '__main__': # print "##################" # print " Torque and Power data is not for this propeller!!!!!" # print "##################" print " D : ", AsUnit(Prop.D, 'in') print " Pitch : ", AsUnit(Prop.Pitch, 'in') Vmax = 50
# These are corrected for standard day # #Standard correction STD = STDCorrection(30.48 * inHg, (7.22 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [ (4500 * RPM, 193 * OZF * STD), (4000 * RPM, 178 * OZF * STD), (3600 * RPM, 144 * OZF * STD), (3400 * RPM, 130 * OZF * STD) ] Arm = 19.5 * IN * STD Prop.TorqueData = [(5520 * RPM, (9.3 * Arm * OZF)), (4980 * RPM, (7.3 * Arm * OZF)), (4440 * RPM, (5.5 * Arm * OZF)), (3990 * RPM, (4.4 * Arm * OZF)), (3450 * RPM, (3.1 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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.MaxTipSpeed = None #Standard correction STD = STDCorrection(30.26 * inHg, (27.2 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(2500 * RPM, 21 * OZF * STD), (3500 * RPM, 46 * OZF * STD), (4500 * RPM, 78 * OZF * STD), (5430 * RPM, 124 * OZF * STD)] #Standard correction - torque taken on different time of day STD2 = STDCorrection(29.95 * inHg, (28 + 273.15) * K) Arm = 19.5 * IN * STD2 # RPM TORQUE Prop.TorqueData = [(6060 * RPM, (7 * Arm * OZF)), (5520 * RPM, (6 * Arm * OZF)), (5040 * RPM, (4.9 * Arm * OZF)), (4020 * RPM, (3.1 * Arm * OZF)), (3000 * RPM, (.5 * Arm * OZF)), (2100 * RPM, (.2 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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.ThrustData = [ (2489 * RPM, 143 * OZF * STD), (3754 * RPM, 3754 * OZF * STD), (4487 * RPM, 228 * OZF * STD), (4487 * RPM, 228 * OZF * STD), # (4110 * RPM, 91 * OZF * STD), #(3540 * RPM, 66 * OZF * STD), (5862 * RPM, 187 * OZF * STD) ] # this point taken after initial points on Hacker A50. Used to verify good data. Arm = 24 * IN * STD #Arm3 = 19.5 * IN * STD3 # Took torque data in closet with known prop to observe difference between temp Prop.TorqueData = [(2489 * RPM, (43 * STD * OZF * IN)), (3752 * RPM, (123 * STD * OZF * IN)), (4470 * RPM, (208 * STD * OZF * IN)), (4668 * RPM, (237 * STD * OZF * IN)), (4806 * RPM, (280 * STD * OZF * IN))], ################################################################################ if __name__ == '__main__': 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
# #Standard correction STD = STDCorrection(30.05 * inHg, (16 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(6330 * RPM, 130 * OZF * STD), (6030 * RPM, 111 * OZF * STD), (5520 * RPM, 97 * OZF * STD), (5020 * RPM, 80 * OZF * STD), (4530 * RPM, 61 * OZF * STD), (4050 * RPM, 48 * OZF * STD), (3570 * RPM, 34 * OZF * STD)] STD2 = STDCorrection(29.90 * inHg, (24 + 273.15) * K) Arm = 19.5 * IN * STD2 Prop.TorqueData = [(5910 * RPM, (4.8 * Arm * OZF)), (5520 * RPM, (4.1 * Arm * OZF)), (5040 * RPM, (3.25 * Arm * OZF)), (4470 * RPM, (2.56 * Arm * OZF)), (3960 * RPM, (1.9 * Arm * OZF)), (3480 * RPM, (1.5 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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.MaxTipSpeed = None # # These are corrected for standard day # #Standard correction STD = STDCorrection(29.83 * inHg, (16 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(5142 * RPM, 211 * OZF * STD), (4320 * RPM, 137 * OZF * STD), (3540 * RPM, 93 * OZF * STD)] Arm = 19.5 * IN * STD Prop.TorqueData = [(5010 * RPM, (10.8 * Arm * OZF)), (4350 * RPM, (7.8 * Arm * OZF)), (3930 * RPM, (6.6 * Arm * OZF)), (3450 * RPM, (5 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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.PowerUnit = W Prop.PowerUnitName = 'watt' Prop.MaxTipSpeed = None # These are corrected for standard day # (Second set of data taken - concern about first set since taken at night) STD = STDCorrection(30.13 * inHg, (-5 + 273.15) * K) STD2 = STDCorrection(30.10 * inHg, (12.7 + 273.15) * K) Prop.ThrustData = [ (4250 * RPM, 209.2 * OZF * STD), (4250 * RPM, 195.2 * OZF * STD) ] # this point taken after initial points on Hacker A50. Used to verify good data. Arm = 19.5 * IN * STD Arm2 = 19.5 * IN * STD2 # Took torque data in closet with known prop to observe difference between temp Prop.TorqueData = None #==============================================================================# # VISUALIZATION & RESULTS #==============================================================================# if __name__ == '__main__': 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
# # (4170 *RPM, 11.8*OZF*STD), # (3840 *RPM, 10.3*OZF*STD), # (3690 *RPM, 9.65*OZF*STD), # (3570 *RPM, 9.1*OZF*STD), # (3480 *RPM, 8.5*OZF*STD), # (3240 *RPM, 7.1*OZF*STD), # (2730 *RPM, 5.2*OZF*STD)] STD2 = STDCorrection(29.93 * inHg, (28.3 + 273.15) * K) Arm = 19.5 * IN * STD2 # RPM, Torque Prop.TorqueData = [ (6960 * RPM, 5.7 * OZF * Arm), (6360 * RPM, 4.9 * OZF * Arm), (6030 * RPM, 4.2 * OZF * Arm), (5490 * RPM, 3.4 * OZF * Arm), (5040 * RPM, 2.8 * OZF * Arm), (4410 * RPM, 2.1 * OZF * Arm), (3900 * RPM, 1.6 * OZF * Arm), (3480 * RPM, 1.2 * OZF * Arm) ] # (3750 *RPM, 27*GRAM*Arm), # (3600 *RPM, 24.5*GRAM*Arm), # (3510 *RPM, 23*GRAM*Arm), # (3420 *RPM, 21*GRAM*Arm), # (3210 *RPM, 19*GRAM*Arm), # (3000 *RPM, 16*GRAM*Arm), # # (4020 *RPM, 30*GRAM*Arm), # (3750 *RPM, 26*GRAM*Arm), # (3600 *RPM, 24.5*GRAM*Arm), # (3480 *RPM, 23*GRAM*Arm), # (3300 *RPM, 20*GRAM*Arm), # (3180 *RPM, 16.5*GRAM*Arm),
# # These are corrected for standard day # #Standard correction STD = STDCorrection(29.69*inHg, (12.7 + 273.15)*K) # RPM, Thrust Prop.ThrustData = [(5674 *RPM, 164*OZF*STD), (5060 *RPM, 133*OZF*STD), (4490 *RPM, 103*OZF*STD), (4020 *RPM, 80*OZF*STD)] Arm = 19.5*IN*STD Prop.TorqueData = [(5562 *RPM, (9.2*Arm*OZF)), (4485 *RPM, (6*Arm*OZF)), (4060 *RPM, (4.9*Arm*OZF)), (3497 *RPM, (3.6*Arm*OZF))] ################################################################################ if __name__ == '__main__': 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
STD = STDCorrection(30.05*inHg, (19 + 273.15)*K) # RPM, Thrust Prop.ThrustData = [(5880 *RPM, 161*OZF*STD), (5400 *RPM, 149*OZF*STD), (5010 *RPM, 116*OZF*STD), (4500 *RPM, 93*OZF*STD), (4050 *RPM, 75*OZF*STD), (3450 *RPM, 59*OZF*STD)] STD2 = STDCorrection(29.90*inHg, (24 + 273.15)*K) Arm = 19.5*IN*STD2 Prop.TorqueData = [(5490 *RPM, (7.2*Arm*OZF)), (4980 *RPM, (5.9*Arm*OZF)), (4500 *RPM, (4.65*Arm*OZF)), (3960 *RPM, (3.55*Arm*OZF)), (3480 *RPM, (3*Arm*OZF))] ################################################################################ if __name__ == '__main__': 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
(15200 * RPM, (6 * LBF + 1 * OZF) * STD, 73.33333 * FT / SEC)] Prop.DynThrustData = DynThrustData #Static torque STD = STDCorrection(29.75 * inHg, (17 + 273.15) * K) Arm = 19.5 * IN * OZF # RPM, Torque Prop.TorqueData = [(13110 * RPM, (4.50 * Arm) * STD), (6990 * RPM, (1.00 * Arm) * STD), (8520 * RPM, (2.00 * Arm) * STD), (11430 * RPM, (3.90 * Arm) * STD), (12360 * RPM, (3.95 * Arm) * STD), (12510 * RPM, (4.10 * Arm) * STD), (10950 * RPM, (2.80 * Arm) * STD), (8730 * RPM, (1.85 * Arm) * STD), (6600 * RPM, (.85 * Arm) * STD), (4740 * RPM, (.35 * Arm) * STD)] STD = STDCorrection(29.63 * inHg, (12.4 + 273.15) * K) Arm = 19.5 * IN * OZF # RPM, Torque Prop.TorqueData = [(3240 * RPM, (0.25 * Arm) * STD), (4290 * RPM, (0.55 * Arm) * STD), (5370 * RPM, (0.8 * Arm) * STD), (6270 * RPM, (1.05 * Arm) * STD), (6630 * RPM, (1.2 * Arm) * STD),
(10860 * RPM, (8 * LBF + 3 * OZF) * STD), (11160 * RPM, (8 * LBF + 11 * OZF) * STD)] STD = STDCorrection(29.75 * inHg, (17 + 273.15) * K) Arm = 19.5 * IN * OZF # RPM, Torque Prop.TorqueData = [(10950 * RPM, (4.50 * Arm) * STD), (5730 * RPM, (1.30 * Arm) * STD), (9330 * RPM, (3.25 * Arm) * STD), (10860 * RPM, (4.45 * Arm) * STD), (10950 * RPM, (4.60 * Arm) * STD), (11160 * RPM, (4.70 * Arm) * STD), (6060 * RPM, (1.05 * Arm) * STD), (7920 * RPM, (2.15 * Arm) * STD), (9150 * RPM, (3.05 * Arm) * STD), (10440 * RPM, (4.20 * Arm) * STD), (10920 * RPM, (4.65 * Arm) * STD), (10320 * RPM, (4.00 * Arm) * STD), (8880 * RPM, (2.90 * Arm) * STD), (7620 * RPM, (1.90 * Arm) * STD), (5100 * RPM, (.75 * Arm) * STD), (3210 * RPM, (.10 * Arm) * STD)] ################################################################################ if __name__ == '__main__': Vmax = 100 h = 0 * FT N = npy.linspace(1000, 12000, 5) * RPM
# # These are corrected for standard day # #Standard correction STD = STDCorrection(29.64 * inHg, (12.7 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [ (5800 * RPM, 173 * OZF * STD), (5700 * RPM, 168 * OZF * STD), (5050 * RPM, 137 * OZF * STD), (4590 * RPM, 105 * OZF * STD), (3960 * RPM, 80 * OZF * STD) ] Arm = 19.5 * IN * STD Prop.TorqueData = [(5670 * RPM, (10.1 * Arm * OZF)), (4984 * RPM, (7.7 * Arm * OZF)), (4450 * RPM, (6.1 * Arm * OZF)), (3950 * RPM, (4.8 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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
# (Second set of data taken - concern about first set since taken at night) STD = STDCorrection(30.48 * inHg, (7.22 + 273.15) * K) STD2 = STDCorrection(30.10 * inHg, (12.7 + 273.15) * K) Prop.ThrustData = [ (5700 * RPM, 204 * OZF * STD), (5400 * RPM, 175 * OZF * STD), (4800 * RPM, 131 * OZF * STD), (4000 * RPM, 98 * OZF * STD) ] # this point taken after initial points on Hacker A50. Used to verify good data. Arm = 19.5 * IN * STD Arm2 = 19.5 * IN * STD2 # Took torque data in closet with known prop to observe difference between temp Prop.TorqueData = [ (5490 * RPM, (9.8 * Arm * OZF)), (5000 * RPM, (8.2 * Arm * OZF)), (4560 * RPM, (6.5 * Arm * OZF)), (4000 * RPM, (4.7 * Arm * OZF)), (3525 * RPM, (3.4 * Arm * OZF)), # begin 2nd taking of torque data in closet (5690 * RPM, (9.5 * Arm2 * OZF)), (5018 * RPM, (7.1 * Arm2 * OZF)), (4525 * RPM, (5.7 * Arm2 * OZF)), (4118 * RPM, (4.8 * Arm2 * OZF)) ] #==============================================================================# # VISUALIZATION & RESULTS #==============================================================================# if __name__ == '__main__': print " D : ", AsUnit(Prop.D, 'in') print " Pitch : ", AsUnit(Prop.Pitch, 'in') Vmax = 50
(8025 * RPM, (4 * LBF + 3 * OZF) * STD), (7290 * RPM, (3 * LBF + 4 * OZF) * STD), (4070 * RPM, (2 * LBF + 6 * OZF) * STD), (2840 * RPM, (1 * LBF + 3 * OZF) * STD), ] STD = STDCorrection(30.3 * inHg, (21.1 + 273.15) * K) Arm = 19.5 * IN # RPM, Torque Prop.TorqueData = [(4290 * RPM, (0.03 * Arm * LBF) * STD), (5790 * RPM, (0.05 * Arm * LBF) * STD), (6330 * RPM, (0.07 * Arm * LBF) * STD), (7650 * RPM, (0.09 * Arm * LBF) * STD), (9220 * RPM, (0.13 * Arm * LBF) * STD), (11920 * RPM, (0.24 * Arm * LBF) * STD), (12750 * RPM, (0.28 * Arm * LBF) * STD), (13600 * RPM, (0.32 * Arm * LBF) * STD), (13800 * RPM, (0.34 * Arm * LBF) * STD)] ################################################################################ if __name__ == '__main__': Vmax = 100 h = 0 * FT N = npy.linspace(1000, 13000, 5) * RPM Alpha = npy.linspace(-25, 25, 41) * ARCDEG V = npy.linspace(0, Vmax, 30) * FT / SEC Prop.CoefPlot(Alpha, fig=1)
(9390 *RPM, (6 *LBF + 12*OZF)*STD), (10140 *RPM, (7 *LBF + 8*OZF)*STD), (10590 *RPM, (9 *LBF + 2*OZF)*STD), (11100 *RPM, (9 *LBF + 9*OZF)*STD)] Prop.ThrustData += ThrustData Arm = 19.5*IN*OZF # RPM, Torque Prop.TorqueData = [(11400 *RPM, (5.00*Arm)*STD), (6660 *RPM, (1.10*Arm)*STD), (7800 *RPM, (1.85*Arm)*STD), (9990 *RPM, (3.30*Arm)*STD), (10980 *RPM, (4.25*Arm)*STD), (11100 *RPM, (4.90*Arm)*STD), (10380 *RPM, (4.25*Arm)*STD), (9030 *RPM, (3.05*Arm)*STD), (8040 *RPM, (2.25*Arm)*STD), (6390 *RPM, (1.35*Arm)*STD), (3690 *RPM, (.40*Arm)*STD)] ################################################################################ if __name__ == '__main__': Vmax = 100 h=0*FT N=npy.linspace(1000, 12000, 5)*RPM Alpha = npy.linspace(-25,25,41)*ARCDEG V = npy.linspace(0,Vmax,30)*FT/SEC
(12630 * RPM, (8 * LBF + 2 * OZF) * STD)] Prop.ThrustData += ThrustData #Standard correction for 2:00 pm for the test day STD = STDCorrection(29.75 * inHg, (17 + 273.15) * K) Arm = 19.5 * IN # RPM, Torque Prop.TorqueData = [(12390 * RPM, (3.65 * Arm * OZF) * STD), (7950 * RPM, (1.40 * Arm * OZF) * STD), (9270 * RPM, (1.75 * Arm * OZF) * STD), (11280 * RPM, (3.10 * Arm * OZF) * STD), (12660 * RPM, (3.85 * Arm * OZF) * STD), (12660 * RPM, (4.25 * Arm * OZF) * STD), (5570 * RPM, (1.00 * Arm * OZF) * STD), (7920 * RPM, (1.35 * Arm * OZF) * STD), (9120 * RPM, (2.05 * Arm * OZF) * STD), (11370 * RPM, (3.20 * Arm * OZF) * STD), (12030 * RPM, (3.80 * Arm * OZF) * STD), (12360 * RPM, (4.25 * Arm * OZF) * STD)] ################################################################################ if __name__ == '__main__': Vmax = 100 h = 0 * FT N = npy.linspace(1000, 13200, 5) * RPM Alpha = npy.linspace(-25, 25, 41) * ARCDEG V = npy.linspace(0, Vmax, 30) * FT / SEC
Prop.CLSlope = .07 / ARCDEG Prop.Solidity = 0.0102 Prop.RD = 3 / 8 Prop.AlphaStall = 13 * ARCDEG #13*ARCDEG Prop.Weight = 3 / 32 * LBF # # These are corrected for standard day # # 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.ThrustData = ThrustData1 + ThrustData2 STD = STDCorrection(29.75 * inHg, (17 + 273.15) * K) Arm = 19.5 * IN # RPM, Torque Prop.TorqueData = [(12360 * RPM, (4.00 * Arm * OZF) * STD), (7050 * RPM, (1.40 * Arm * OZF) * STD), (9270 * RPM, (1.75 * Arm * OZF) * STD), (11280 * RPM, (3.10 * Arm * OZF) * STD), (12660 * RPM, (3.85 * Arm * OZF) * STD), (12540 * RPM, (4.70 * Arm * OZF) * STD), (5610 * RPM, (1.25 * Arm * OZF) * STD), (7650 * RPM, (1.60 * Arm * OZF) * STD), (8550 * RPM, (2.20 * Arm * OZF) * STD), (11730 * RPM, (4.15 * Arm * OZF) * STD), (12330 * RPM, (4.55 * Arm * OZF) * STD), (11310 * RPM, (3.90 * Arm * OZF) * STD), (9900 * RPM, (2.90 * Arm * OZF) * STD), (8430 * RPM, (2.25 * Arm * OZF) * STD), (7050 * RPM, (1.45 * Arm * OZF) * STD), (4560 * RPM, (.65 * Arm * OZF) * STD), (2700 * RPM, (.30 * Arm * OZF) * STD)] # ################################################################################ if __name__ == '__main__': Vmax = 100 h = 0 * FT N = npy.linspace(1000, 12300, 5) * RPM
Prop.MaxTipSpeed = None # # These are corrected for standard day # #Standard correction STD = STDCorrection(29.59 * inHg, (12.7 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(5684 * RPM, 172 * OZF * STD), (4980 * RPM, 131 * OZF * STD), (4555 * RPM, 108 * OZF * STD), (4080 * RPM, 85 * OZF * STD)] Arm = 19.5 * IN * STD Prop.TorqueData = [(5640 * RPM, (10.1 * Arm * OZF)), (5000 * RPM, (7.9 * Arm * OZF)), (4600 * RPM, (6.6 * Arm * OZF)), (3955 * RPM, (4.8 * Arm * OZF))] ################################################################################ if __name__ == '__main__': 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