Python ACPropeller.name示例

示例#1

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 12x5'
Prop.D          = 12.5*IN
Prop.Thickness  = 5/8*IN
#Prop.PitchAngle = 12*ARCDEG
Prop.Pitch      = 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),

示例#2

# (USER) set-up directories
trunkDir = r'C:\eclipse\workspace\AircraftDesign\trunk'
atlasDir = os.path.join(trunkDir,r'Aircraft_Models\Reg2017Aircraft_BearcatAirlines\BAP')

# 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

示例#3

文件： APC_13x4.py 项目： Aerothon-2020/Adv2019Aircraft

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),

示例#4

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)

示例#5

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 = '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),

示例#6

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 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

示例#7

文件： APC_13X6_5.py 项目： Aerothon-2020/Adv2019Aircraft

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),

示例#8

文件： APC_18x10E.py 项目： Aerothon-2020/Adv2019Aircraft

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 18x10E'
Prop.D          = 18*IN
Prop.Thickness  = 0.5*IN

Prop.Pitch      = 10*IN
Prop.dAlpha     = 2.8*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     = 87*GRAM*gacc

Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W 
Prop.PowerUnitName = 'watt' 
Prop.MaxTipSpeed = None

示例#9

文件： APC_14X4.py 项目： Aerothon-2020/Adv2019Aircraft

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 14x4'
Prop.D = 14 * IN
Prop.Thickness = 5 / 8 * IN
#Prop.PitchAngle  = 12*ARCDEG
Prop.Pitch = 4 * IN

Prop.dAlpha = 3.7 * ARCDEG
Prop.Solidity = 0.014
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

示例#10

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 = '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

示例#11

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),

示例#12

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),

示例#13

文件： Xoar_11x4.py 项目： Aerothon-2020/Adv2019Aircraft

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 = 'Xoar 11x4'
Prop.D = 11 * 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 = .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),

示例#14

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 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 = 100 * 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 = [(3750 * RPM, (0 * LBF + 14 * OZF) * STD),
                   (6210 * RPM, (2 * LBF + 4 * OZF) * STD),
                   (7830 * RPM, (1 * LBF + 15 * OZF) * STD),

示例#15

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

示例#16

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

示例#17

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 18.25x10E'
Prop.D          = 18.25*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    = .077/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

示例#18

文件： APC_20x8E.py 项目： Aerothon-2020/Reg2019Aircraft

# link path to Aerothon
sys.path.append(trunkDir)

# import Aerothon modules
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K,\
     degR, inHg, MM
from scalar.units import AsUnit
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection

#==============================================================================#
# PROPELLER MODEL
#==============================================================================#
# Set Propeller properties
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

示例#19

文件： APC_18_5x10E.py 项目： Aerothon-2020/Adv2020Aircraft

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 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

示例#20

文件： APC_22x12W.py 项目： Aerothon-2020/Adv2019Aircraft

import os
import sys
import numpy as npy
import cmath as math
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 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

示例#21

文件： APC_18x8E.py 项目： Aerothon-2020/Adv2020Aircraft

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 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

示例#22

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        = '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

示例#23

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
######################################################################
# THIS PROPELLER WAS AN APC 19X10E THAT WAS CUT TO 18 INCH DIAMETER
######################################################################
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'

示例#24

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)]

示例#25

文件： APC_14x12.py 项目： Aerothon-2020/Adv2019Aircraft

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),

示例#26

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 19x10E'
Prop.D = 19 * IN
Prop.Thickness = 0.5 * IN

Prop.Pitch = 10 * IN
Prop.dAlpha = 2.9 * ARCDEG
Prop.Solidity = 0.0126

Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .085 / ARCDEG  #- 2D airfoil lift slope (started at 0.08/ARCDEG)
Prop.CDCurve = 2.2  #- 2D curvature of the airfoil drag bucket (started at 2.2)
Prop.CDp = 0.02  #- Parasitic drag (started at 0.02)

Prop.Weight = 99 * GRAM * gacc

Prop.ThrustUnit = LBF
Prop.ThrustUnitName = 'lbf'
Prop.PowerUnit = W
Prop.PowerUnitName = 'watt'
Prop.MaxTipSpeed = None

示例#27

文件： Prop_13_5x4.py 项目： Aerothon-2020/Adv2019Aircraft

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)]

示例#28

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 19x10E_base'
Prop.D = 19 * IN
Prop.Thickness = 0.5 * IN

Prop.Pitch = 10 * IN
Prop.dAlpha = 2.9 * ARCDEG
Prop.Solidity = 0.0126

Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .08 / 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

示例#29

文件： APC_22x10E.py 项目： Aerothon-2020/Adv2019Aircraft

import os
import sys
import numpy as npy
import cmath as math
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

示例#30

文件： APC_19x8E.py 项目： Aerothon-2020/Reg2019Aircraft

sys.path.append(trunkDir)

# import Aerothon modules
from scalar.units import IN, LBF, SEC, ARCDEG, FT, RPM, OZF, GRAM, gacc, W, K,\
     degR, inHg, MM
from scalar.units import AsUnit
from Aerothon.ACPropeller import ACPropeller
from Aerothon.AeroUtil import STDCorrection

#==============================================================================#
# PROPELLER MODEL
#==============================================================================#

# Set Propeller properties
Prop = ACPropeller()
Prop.name = 'APC 19x8E'
Prop.D = 19 * IN
Prop.Thickness = .5 * IN

Prop.Pitch = 8 * IN
Prop.dAlpha = 5.6 * ARCDEG
Prop.Solidity = 0.0126

Prop.AlphaStall = 20 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = .14 / ARCDEG  #- 2D airfoil lift slope
Prop.CDCurve = 2.0  #- 2D curvature of the airfoil drag bucket
Prop.CDp = .02  #- Parasitic drag

Prop.Weight = 99 * GRAM * gacc