from Aerothon.ACPropeller import ACPropeller from Aerothon.ACEngine import ACEngine from Aerothon.ACPropulsion import ACPropulsion import numpy as npy from scalar.units import IN, LBF, PSFC, SEC, ARCDEG, FT, OZF, RPM, HP # Set Propeller properties Prop = ACPropeller() Prop.D = 14.5 * IN Prop.Thickness = 0.25 * IN Prop.PitchAngle = 12 * ARCDEG Prop.dAlpha = 0 * ARCDEG Prop.Solidity = 0.0136 Prop.RD = 3 / 8 Prop.AlphaStall = 14 * ARCDEG Prop.Weight = 0.3 * LBF # Set Engine properties Engine = ACEngine() Engine.Rbs = 1.1 Engine.Rla = 3.5 Engine.NumCyl = 1 Engine.NumRev = 1 Engine.CompRatio = 9 Engine.Vd = 0.607 * IN**3 Engine.PistonSpeedR = 38.27 * FT / SEC Engine.MEPtlmt = 10.1526 * LBF / IN**2 Engine.SFCmt = 1 * PSFC Engine.A_F = 16 Engine.PS = 1 Engine.LWH = [6 * IN, 1.69 * IN, 2 * IN]
Prop = ACPropeller()
Prop.name = 'APC 18x8E'
Prop.D = 18 * IN
Prop.Thickness = 0.48 * IN
Prop.Pitch = 8 * IN
Prop.dAlpha = 3.6 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .0770 / ARCDEG #- 2D airfoil lift slope
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)]
###################################################
Prop = ACPropeller() Prop.name = 'XOAR 22x6' Prop.D = 22 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 6 * IN Prop.dAlpha = 5.75 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .075 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 111 * GRAM * gacc 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(29.83 * inHg, (16 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(5142 * RPM, 211 * OZF * STD),
Prop = ACPropeller() Prop.name = 'APC 18.5x10E' Prop.D = 18.5 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 10 * IN Prop.dAlpha = 3.8 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .075 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 99 * GRAM * gacc 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 = [
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'Prop 13.5x6'
Prop.D = 13.5 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 5. * IN
Prop.dAlpha = 4. * ARCDEG
Prop.Solidity = 0.014
Prop.RD = 3 / 8
Prop.AlphaStall = 14 * ARCDEG
Prop.CLSlope = 0.07 / ARCDEG
Prop.Weight = 1.25 * OZF
#
# 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),
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'APC 13x4'
Prop.D = 13 * IN
Prop.Thickness = 5 / 8 * IN
Prop.Pitch = 3.5 * IN
Prop.dAlpha = 4.9 * ARCDEG
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(30.16 * 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
Prop = ACPropeller()
Prop.name = 'APC 20x8E'
Prop.D = 20 * IN
Prop.Thickness = 0.5 * IN
Prop.Pitch = 8 * IN
Prop.dAlpha = 3.3 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .078 / ARCDEG #- 2D airfoil lift slope
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
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.
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, Pa, degR, inHg
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'Prop 14x12'
Prop.D = 14 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 6 * 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)]
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, hPa, K, W, inHg
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'APC 11x3'
Prop.D = 11 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 3 * IN
Prop.dAlpha = 3.4 * ARCDEG
Prop.Solidity = 0.0135
Prop.AlphaStall = 14 * ARCDEG
Prop.CLSlope = 0.072 / ARCDEG
Prop.Weight = .70 * 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 = [(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),
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'APC 14x5'
Prop.D = 14 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 5 * IN
Prop.dAlpha = 3.7 * ARCDEG
Prop.Solidity = 0.012
Prop.RD = 3 / 8
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(30.03 * 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),
Prop = ACPropeller()
Prop.name = 'XOAR 18x8'
Prop.D = 18 * IN
Prop.Thickness = 0.48 * IN
Prop.Pitch = 8 * IN
Prop.dAlpha = 3.6 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .077 / ARCDEG #- 2D airfoil lift slope
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02 #- Parasitic drag
Prop.Weight = 45 * 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, 78 * OZF * STD), (5430 * RPM, 124 * OZF * STD)]
#Standard correction - torque taken on different time of day
Prop = ACPropeller() Prop.name = 'APC 17x7E' Prop.D = 17 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 7 * IN Prop.dAlpha = 3.95 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .077 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 67 * GRAM * gacc 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),
Prop = ACPropeller() Prop.name = 'APC 20x8E' Prop.D = 20 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 8 * IN Prop.dAlpha = 3.3 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .078 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 115 * 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(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 = [
Prop = ACPropeller() Prop.name = 'APC 18x10E_mod' Prop.D = 18 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 10 * IN Prop.dAlpha = 5.0 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .0725 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 87 * GRAM * gacc 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),
Prop = ACPropeller()
Prop.name = 'APC 22x12E'
Prop.D = 22 * IN
Prop.Thickness = 0.5 * IN
Prop.Pitch = 12 * IN
Prop.dAlpha = 11 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .065 / ARCDEG #- 2D airfoil lift slope
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .04 #- Parasitic drag
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)
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, hPa, K, W, inHg
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'Xoar 12x4'
Prop.D = 12 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 4 * IN
Prop.dAlpha = 3.4 * ARCDEG
Prop.Solidity = 0.0135
Prop.AlphaStall = 14 * ARCDEG
Prop.CLSlope = 0.072 / ARCDEG
Prop.Weight = .88 * 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 = [(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),
Prop = ACPropeller()
Prop.name = 'APC 22x10E'
Prop.D = 22 * IN
Prop.Thickness = 0.5 * IN
Prop.Pitch = 10 * IN
Prop.dAlpha = 11 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .22 / ARCDEG #- 2D airfoil lift slope
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02 #- Parasitic drag
Prop.Weight = 163 * 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)
Prop.ThrustData = [
(2414 * RPM, 193 * OZF * STD), (2205 * RPM, 161 * OZF * STD),
Prop = ACPropeller()
Prop.name = 'APC 22x8'
Prop.D = 22*IN
Prop.Thickness = 0.5*IN
Prop.Pitch = 8*IN
Prop.dAlpha = 11*ARCDEG #### 3.3
Prop.Solidity = 0.0126
Prop.AlphaStall = 20*ARCDEG
Prop.AlphaZeroCL = 0*ARCDEG
Prop.CLSlope = .22/ARCDEG #- 2D airfoil lift slope .76
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02 #- Parasitic drag
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),
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'Graupner 14.2x4'
Prop.D = 14.2*IN
Prop.Thickness = 5/8*IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 4*IN
Prop.dAlpha = 0*ARCDEG
Prop.Solidity = 0.013
Prop.RD = 3/8
Prop.AlphaStall = 15*ARCDEG
Prop.AlphaZeroCL = 0*ARCDEG
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),
import pylab as pyl
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'Prop 13.5x4'
Prop.D = 13.5*IN
Prop.Thickness = 5/8*IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 4*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 = 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__':
Prop = ACPropeller() Prop.name = 'APC 17x10E' Prop.D = 17*IN Prop.Thickness = 0.5*IN Prop.Pitch = 10*IN Prop.dAlpha = 3.65*ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20*ARCDEG Prop.AlphaZeroCL = 0*ARCDEG Prop.CLSlope = .0765/ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 50*GRAM*gacc 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),
Prop = ACPropeller()
Prop.name = 'APC 22x10E'
Prop.D = 22 * IN
Prop.Thickness = 0.5 * IN
Prop.Pitch = 10 * IN
Prop.dAlpha = 11 * ARCDEG
Prop.Solidity = 0.0126
Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .22 / ARCDEG #- 2D airfoil lift slope
Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02 #- Parasitic drag
Prop.Weight = 240.9 * 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)
Prop.ThrustData = [
(2414 * RPM, 193 * OZF * STD), (2205 * RPM, 161 * OZF * STD),
(2003 * RPM, 131 * OZF * STD), (1848 * RPM, 108 * OZF * STD),
Prop = ACPropeller() Prop.name = 'APC 16x8E' Prop.D = 16 * IN Prop.Thickness = 5 / 8 * IN Prop.Pitch = 8 * IN Prop.dAlpha = 2.95 * ARCDEG Prop.Solidity = 0.0126 Prop.AlphaStall = 20 * ARCDEG Prop.AlphaZeroCL = 0 * ARCDEG Prop.CLSlope = .0625 / ARCDEG #- 2D airfoil lift slope Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket Prop.CDp = .02 #- Parasitic drag Prop.Weight = 56 * GRAM * gacc 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(29.74 * inHg, (16.1 + 273.15) * K) # RPM, Thrust Prop.ThrustData = [(2605 * RPM, 9 * OZF * STD), (3071 * RPM, 14 * OZF * STD),