Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
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(30.00 * inHg, (22 + 273.15) * K)
STD2 = STDCorrection(29.63 * inHg, (21.1 + 273.15) * K)
STD3 = STDCorrection(30.10 * inHg, (12.7 + 273.15) * K)
Prop.ThrustData = [
(5520 * RPM, 176 * OZF * STD), (5040 * RPM, 139 * OZF * STD),
(4590 * RPM, 116 * OZF * STD), (4110 * RPM, 91 * OZF * STD),
(3540 * RPM, 66 * OZF * STD), (5862 * RPM, 187 * OZF * STD2)
] # this point taken after initial points on Hacker A50. Used to verify good data.
Arm = 19.5 * IN * STD
Arm3 = 19.5 * IN * STD3 # Took torque data in closet with known prop to observe difference between temp
Prop.TorqueData = [
(5490 * RPM, (8.3 * Arm * OZF)),
(5000 * RPM, (6.8 * Arm * OZF)),
(4560 * RPM, (5.5 * Arm * OZF)),
(4000 * RPM, (4.3 * Arm * OZF)),
(3525 * RPM, (3.4 * Arm * OZF)),
# begin 2nd taking of torque data in closet
(5690 * RPM, (9.5 * Arm3 * OZF)),
(5018 * RPM, (7.1 * Arm3 * OZF)),
(4525 * RPM, (5.7 * Arm3 * OZF)),
Prop.Weight = 240*GRAM*gacc
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
### These are corrected for a standard day
STD = STDCorrection(29.4*inHg, 293.7*K)
Prop.ThrustData = [(2427 *RPM, 202*OZF*STD),
(2322 *RPM, 182*OZF*STD),
(2102 *RPM, 146*OZF*STD),
(1678 *RPM, 93*OZF*STD),
(1387 *RPM, 63*OZF*STD),
(98 *RPM, 29*OZF*STD)]
################################################################################
if __name__ == '__main__':
print " D : ", AsUnit( Prop.D, 'in')
print " Pitch : ", AsUnit( Prop.Pitch, 'in')
Vmax = 50
Prop.Weight = 1.80 * OZF
STD = STDCorrection(30.16 * inHg, (1.667 + 273.15) * K)
# RPM, Thrust
ThrustData1 = [(12080 * RPM, (10 * LBF + 4 * OZF) * STD),
(11650 * RPM, (9 * LBF + 6 * OZF) * STD),
(10980 * RPM, (8 * LBF + 13 * OZF) * STD),
(10280 * RPM, (8 * LBF + 0 * OZF) * STD),
(9630 * RPM, (6 * LBF + 12 * OZF) * STD),
(8400 * RPM, (5 * LBF + 3 * OZF) * STD),
(7215 * RPM, (3 * LBF + 14 * OZF) * STD),
(6900 * RPM, (3 * LBF + 9 * OZF) * STD),
(6510 * RPM, (3 * LBF + 2 * OZF) * STD),
(5610 * RPM, (1 * LBF + 12 * OZF) * STD)]
Prop.ThrustData = ThrustData1
STD = STDCorrection(30.34 * inHg, (15.55 + 273.15) * K)
#
ThrustData2 = [(5000 * RPM, (1 * LBF + 5 * OZF) * STD),
(6000 * RPM, (1 * LBF + 8 * OZF) * STD),
(7000 * RPM, (2 * LBF + 9 * OZF) * STD),
(8000 * RPM, (3 * LBF + 1 * OZF) * STD),
(9000 * RPM, (3 * LBF + 10 * OZF) * STD),
(10000 * RPM, (5 * LBF + 5 * OZF) * STD),
(11000 * RPM, (6 * LBF + 13 * OZF) * STD),
(11800 * RPM, (8 * LBF + 6 * OZF) * STD)]
Prop.ThrustData = ThrustData1 + ThrustData2
# (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)]
################################################################################
# Marietta GA
STD = STDCorrection(30.3 * inHg, (21.1 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [
(13440 * RPM, (10 * LBF + 8 * OZF) * STD),
(12340 * RPM, (10 * LBF + 5 * OZF) * STD),
(11750 * RPM, (9 * LBF + 0 * OZF) * STD),
(10650 * RPM, (8 * LBF + 6 * OZF) * STD),
(10500 * RPM, (6 * LBF + 12 * OZF) * STD),
(10180 * RPM, (6 * LBF + 0 * OZF) * STD),
(9630 * RPM, (5 * LBF + 6 * OZF) * STD),
(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),
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
#
# RPM, Thrust
Prop.ThrustData = [(3750 * RPM, (0 * LBF + 14 * OZF) * STD),
(6210 * RPM, (2 * LBF + 4 * OZF) * STD),
(7830 * RPM, (1 * LBF + 15 * OZF) * STD),
(8160 * RPM, (4 * LBF + 4 * OZF) * STD),
(9090 * RPM, (4 * LBF + 14 * OZF) * STD),
(10110 * RPM, (4 * LBF + 10 * OZF) * STD),
(11190 * RPM, (6 * LBF + 4 * OZF) * STD),
(11670 * RPM, (7 * LBF + 4 * OZF) * STD),
(12060 * RPM, (7 * LBF + 8 * OZF) * STD),
(12270 * RPM, (8 * LBF + 7 * OZF) * STD),
(12570 * RPM, (8 * LBF + 13 * OZF) * STD),
(13110 * RPM, (9 * LBF + 1 * OZF) * STD),
(2880 * RPM, (0 * LBF + 8 * OZF) * STD),
(5250 * RPM, (1 * LBF + 13 * OZF) * STD),
(6120 * RPM, (2 * LBF + 3 * OZF) * STD),
(6840 * RPM, (1 * LBF + 14 * OZF) * STD),
(7680 * RPM, (2 * LBF + 12 * OZF) * STD),
(8520 * RPM, (4 * LBF + 10 * OZF) * STD),
(9090 * RPM, (4 * LBF + 5 * OZF) * STD),
(9870 * RPM, (4 * LBF + 8 * OZF) * STD),
(10410 * RPM, (4 * LBF + 9 * OZF) * STD),
(11370 * RPM, (6 * LBF + 9 * OZF) * STD),
(12120 * RPM, (7 * LBF + 3 * OZF) * STD),
(12360 * RPM, (7 * LBF + 11 * OZF) * STD)]
#Prop.ThrustData += ThrustData
STD = STDCorrection(30.34 * inHg, (15.55 + 273.15) * K)
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
#
#Standard correction
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__':
Prop.Solidity = 0.015
Prop.AlphaStall = 15 * ARCDEG
Prop.CLSlope = 0.065 / ARCDEG
Prop.CDCurve = 2.2
Prop.CDp = 0.01
Prop.Weight = 1.80 * OZF
#
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(5000 * RPM, (1 * LBF + 5 * OZF) * STD),
(6000 * RPM, (2 * LBF + 3 * OZF) * STD),
(7000 * RPM, (2 * LBF + 8 * OZF) * STD),
(8000 * RPM, (3 * LBF + 5 * OZF) * STD),
(8700 * RPM, (4 * LBF + 13 * OZF) * STD)]
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),
#
# These are corrected for standard day
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
#
# RPM, Thrust
Prop.ThrustData = [(3330 * RPM, (1 * LBF + 4 * OZF) * STD),
(5460 * RPM, (2 * LBF + 9 * OZF) * STD),
(7890 * RPM, (3 * LBF + 12 * OZF) * STD),
(9330 * RPM, (5 * LBF + 8 * OZF) * STD),
(10380 * RPM, (7 * LBF + 8 * OZF) * STD),
(10950 * RPM, (8 * LBF + 15 * OZF) * STD),
(10950 * RPM, (9 * LBF + 1 * OZF) * STD),
(4890 * RPM, (2 * LBF + 3 * OZF) * STD),
(6060 * RPM, (2 * LBF + 10 * OZF) * STD),
(7590 * RPM, (5 * LBF + 2 * OZF) * STD),
(8070 * RPM, (5 * LBF + 10 * OZF) * STD),
(8340 * RPM, (6 * LBF + 1 * OZF) * STD),
(9720 * RPM, (6 * LBF + 4 * OZF) * STD),
(10170 * RPM, (6 * LBF + 8 * OZF) * STD),
(10530 * RPM, (7 * LBF + 7 * OZF) * 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),
Prop.CDp = .02 #- Parasitic drag
Prop.Weight = 4.05 * OZF
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
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(30.48 * 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))
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
#
#Standard correction
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__':
Prop.AlphaStall = 15 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = 0.0725 / ARCDEG #- 2D airfoil lift slope (default 0.068/deg)
Prop.CDp = 0.01
Prop.Weight = 1.8 * OZF
#
# These are corrected for standard day
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.34 * inHg, (15.55 + 273.15) * K)
#
# RPM, Thrust
Prop.ThrustData = [(5000 * RPM, (1 * LBF + 4 * OZF) * STD),
(6000 * RPM, (2 * LBF + 9 * OZF) * STD),
(7000 * RPM, (3 * LBF + 12 * OZF) * STD),
(8000 * RPM, (5 * LBF + 8 * OZF) * STD),
(9120 * 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),
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
#
#Standard correction
STD = STDCorrection(29.93 * inHg, (25 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(5580 * RPM, 170 * OZF * STD),
(4920 * RPM, 132 * OZF * STD),
(4410 * RPM, 109 * OZF * STD), (3960 * RPM, 85 * OZF * STD),
(3480 * RPM, 64 * OZF * STD), (3090 * RPM, 48 * OZF * STD)]
STD2 = STDCorrection(29.92 * inHg, (24 + 273.15) * K)
Arm = 19.5 * IN * STD2
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')
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# 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')
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
#
#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__':
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 6 * IN
Prop.dAlpha = 0.8 * ARCDEG
Prop.Solidity = 0.013 #0.0125 seems to match the old data better...
Prop.RD = 3 / 8
Prop.AlphaStall = 16 * ARCDEG
Prop.Weight = 3 / 32 * LBF
#
# These are corrected for standard day
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(1726 * RPM, (1 * LBF + 10 * OZF) * STD),
(3560 * RPM, (4 * LBF + 12 * OZF) * STD),
(4600 * RPM, (6 * LBF + 5 * OZF) * STD),
(4850 * RPM, (6 * LBF + 11 * OZF) * STD)]
#Standard correction for 2:00 pm for the test day
#STD = STDCorrection(3003*3385*Pa, (19 + 273.15*9/5)*degR)
# 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
Prop.Weight = 159.89 * GRAM * gacc
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
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(28.14*inHg, (294.16)*K)
Arm = 19.5
Prop.ThrustData = [
(4250 * RPM, 209 * OZF * Arm), (4250 * RPM, 195.2 * OZF * Arm)
] # this point taken after initial points on Hacker A50. Used to verify good data.
################################################################################
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.Weight = 1.80 * OZF
Prop.WeightGroup = 'Propulsion'
#
# These are corrected for standard day
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
#
# RPM, Thrust
Prop.ThrustData = [(4110 * RPM, (1 * LBF + 0 * OZF) * STD),
(7770 * RPM, (2 * LBF + 8 * OZF) * STD),
(8850 * RPM, (3 * LBF + 10 * OZF) * STD),
(9750 * RPM, (4 * LBF + 8 * OZF) * STD),
(9960 * RPM, (4 * LBF + 9 * OZF) * STD),
(10950 * RPM, (5 * LBF + 12 * OZF) * STD),
(11610 * RPM, (6 * LBF + 9 * OZF) * STD),
(11910 * RPM, (7 * LBF + 13 * OZF) * STD),
(12330 * RPM, (8 * LBF + 8 * OZF) * STD),
(12780 * RPM, (9 * LBF + 7 * OZF) * STD),
(12870 * RPM, (9 * LBF + 13 * OZF) * STD),
(12900 * RPM, (9 * LBF + 15 * OZF) * STD)]
STD = STDCorrection(30.3 * inHg, (19 + 273.15) * K)
ThrustData = [(3510 * RPM, (0 * LBF + 12 * OZF) * STD),
(5010 * RPM, (1 * LBF + 7 * OZF) * STD),
(6660 * RPM, (2 * LBF + 9 * OZF) * STD),
(6810 * RPM, (2 * LBF + 12 * OZF) * STD),
(7830 * RPM, (3 * LBF + 5 * OZF) * STD),
(9360 * RPM, (4 * LBF + 2 * OZF) * STD),
(10410 * RPM, (5 * LBF + 3 * OZF) * STD),
Prop.CLSlope = 0.07/ARCDEG #- 2D airfoil lift slope (default 0.068/deg)
Prop.CDp = 0.01
Prop.Weight = 1.95*OZF
#
# These are corrected for standard day
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03*inHg, (19 + 273.15)*K)
#
# RPM, Thrust
Prop.ThrustData = [(4020 *RPM, (0 *LBF + 8*OZF)*STD),
(5640 *RPM, (0 *LBF + 10*OZF)*STD),
(7860 *RPM, (2 *LBF + 1*OZF)*STD),
(9150 *RPM, (6 *LBF + 7*OZF)*STD),
(9900 *RPM, (7 *LBF + 9*OZF)*STD),
(10890 *RPM, (9 *LBF + 2*OZF)*STD),
(11130 *RPM, (9 *LBF + 11*OZF)*STD),
(10320 *RPM, (8 *LBF + 1*OZF)*STD),
(9870 *RPM, (7 *LBF + 0*OZF)*STD),
(9030 *RPM, (5 *LBF + 3*OZF)*STD)]
#(3150 *RPM, (1 *LBF + 7*OZF)*STD)
STD = STDCorrection(30.3*inHg, (19 + 273.15)*K)
ThrustData = [(3270 *RPM, (0 *LBF + 10*OZF)*STD),
(6030 *RPM, (2 *LBF + 12*OZF)*STD),
(7140 *RPM, (4 *LBF + 3*OZF)*STD),
(8340 *RPM, (5 *LBF + 14*OZF)*STD),
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# 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')
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 4. * IN
Prop.dAlpha = 3.1 * ARCDEG #0.8*ARCDEG
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
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02 #- Parasitic drag
Prop.Weight = 86 * GRAM * gacc
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
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, 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))]
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
#
#Standard correction
STD = STDCorrection(29.79 * inHg, (29.79 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(5460 * RPM, (154 + 18) * OZF * STD),
(4500 * RPM, (99 + 18) * OZF * STD),
(3990 * RPM, (74 + 18) * OZF * STD),
(3540 * RPM, (51 + 18) * OZF * STD),
(2970 * RPM, (34 + 18) * OZF * STD),
(2520 * RPM, (15 + 18) * OZF * STD)]
STD2 = STDCorrection(29.92 * inHg, (24 + 273.15) * K)
Arm = 19.5 * IN * STD2
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__':
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# 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')
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# These are corrected for standard day
###############
# 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')
Prop.dAlpha = 0.8 * ARCDEG
Prop.Solidity = 0.021 #0.0125 seems to match the old data better...
Prop.RD = 3 / 8
Prop.AlphaStall = 16 * ARCDEG
Prop.Weight = 100 * LBF
#Standard correction for 2:00 pm for the test day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
#
# These are corrected for standard day
#
# RPM, Thrust
Prop.ThrustData = [(2370 * RPM, (0 * LBF + 10 * OZF) * STD),
(4140 * RPM, (3 * LBF + 2 * OZF) * STD),
(5160 * RPM, (4 * LBF + 14 * OZF) * STD),
(5880 * RPM, (6 * LBF + 0 * OZF) * STD),
(5970 * RPM, (5 * LBF + 10 * OZF) * STD)]
# 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
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
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(30.00 * 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')
#
# These are corrected for standard day
STD = STDCorrection(30.03 * inHg, (19 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(3200 * RPM, (1 * LBF + 6 * OZF) * STD),
(5610 * RPM, (3 * LBF + 2 * OZF) * STD),
(7380 * RPM, (3 * LBF + 13 * OZF) * STD),
(8640 * RPM, (5 * LBF + 7 * OZF) * STD),
(9250 * RPM, (6 * LBF + 11 * OZF) * STD),
(10320 * RPM, (7 * LBF + 3 * OZF) * STD),
(10410 * RPM, (7 * LBF + 2 * OZF) * STD),
(3600 * RPM, (1 * LBF + 2 * OZF) * STD),
(4470 * RPM, (1 * LBF + 14 * OZF) * STD),
(5580 * RPM, (2 * LBF + 10 * OZF) * STD),
(6510 * RPM, (3 * LBF + 8 * OZF) * STD),
(7470 * RPM, (4 * LBF + 5 * OZF) * STD),
(8280 * RPM, (5 * LBF + 5 * OZF) * STD),
(8640 * RPM, (5 * LBF + 14 * OZF) * STD),
(9300 * RPM, (6 * LBF + 13 * OZF) * STD),
(9690 * RPM, (7 * LBF + 0 * OZF) * STD),
(9840 * RPM, (6 * LBF + 14 * OZF) * STD),
(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
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None
#
# 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
Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
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(28.14 * inHg, (294.16) * K)
Prop.ThrustData = [
(2414 * RPM, 193 * OZF * STD), (2205 * RPM, 161 * OZF * STD),
(2003 * RPM, 131 * OZF * STD), (1848 * RPM, 108 * OZF * STD),
(1622 * RPM, 82 * OZF * STD), (1283 * RPM, 50 * OZF * STD),
(2386 * RPM, 203 * OZF * STD), (2233 * RPM, 177 * OZF * STD),
(2006 * RPM, 145 * OZF * STD), (1991 * RPM, 141 * OZF * STD),
(1632 * RPM, 94 * OZF * STD), (1363 * RPM, 68 * OZF * STD)
] # this point taken after initial points on Hacker A50. Used to verify good data.
################################################################################
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, 6) * RPM
Alpha = npy.linspace(-25, 25, 41) * ARCDEG
Prop.ThrustUnitName = 'lbf'
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(30.00 * inHg, (22 + 273.15) * K)
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__':