# 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
