import pylab as pyl from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K, degR, inHg, MM from scalar.units import AsUnit # Set Propeller properties 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'
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller import numpy as npy 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)]
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, Pa, degR, W, inHg, K
from scalar.units import AsUnit
# 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),
# link path to Aerothon sys.path.append(trunkDir) from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K, degR, inHg, MM from scalar.units import AsUnit # Set Propeller properties 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'
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, Pa, degR, W, inHg, K
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),
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl 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 12.25x3.75 ADV' Prop.D = 12.25 * IN Prop.Thickness = 5 / 8 * IN Prop.Pitch = 3.75 * IN Prop.dAlpha = 6.25 * ARCDEG # for correlating Prop.Solidity = 0.013 # for correlating Prop.AlphaStall = 18 * ARCDEG # for correlating Prop.AlphaZeroCL = 0 * ARCDEG #- 2D curvature of the airfoil drag bucket Prop.CLSlope = 0.095 / ARCDEG #- 2D airfoil lift slope (default 0.068/deg) Prop.CDCurve = 2.5 #- 2D curvature of the airfoil drag bucket Prop.CDp = 0.01 #- 2D parasite drag 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(30.16*inHg, (1.6667 + 273.15)*K)
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
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),
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K, degR, inHg, MM from scalar.units import AsUnit # Set Propeller properties Prop = ACPropeller() Prop.name = 'APC 24x12E' Prop.D = 24 * IN Prop.Thickness = 0.5 * IN Prop.Pitch = 12 * 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 = 150 * GRAM * gacc Prop.ThrustUnit = LBF Prop.ThrustUnitName = 'lbf' Prop.PowerUnit = W Prop.PowerUnitName = 'watt' Prop.MaxTipSpeed = None
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, Pa, degR, W, inHg, K
from scalar.units import AsUnit
# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'APC 13x6_5'
Prop.D = 13 * IN
Prop.Thickness = 5 / 8 * IN
Prop.Pitch = 6.5 * 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(30.03 * inHg, (19 + 273.15) * K)
# RPM, Thrust
Prop.ThrustData = [(5000 * RPM, (1 * LBF + 5 * OZF) * STD),
(6000 * RPM, (2 * LBF + 3 * OZF) * STD),
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
import numpy as npy
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 14.2x4'
Prop.D = 14.5 * 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)]
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl 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 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
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
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),
from __future__ import division # let 5/2 = 2.5 rather than 2
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection
import numpy as npy
import pylab as pyl
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 12.2x4.5'
Prop.D = 12.2 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch = 4.5 * IN
Prop.dAlpha = 3.4 * ARCDEG
Prop.Solidity = 0.0135
Prop.AlphaStall = 14 * ARCDEG
Prop.CLSlope = 0.072 / ARCDEG
Prop.Weight = 1.80 * 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),
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller from Aerothon.AeroUtil import STDCorrection import numpy as npy import pylab as pyl from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K, degR, inHg, MM from scalar.units import AsUnit # Set Propeller properties 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
