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' 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)
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),
(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),
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),
(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),
# 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' Prop.PowerUnit = W Prop.PowerUnitName = 'watt' Prop.MaxTipSpeed = None # # These are corrected for standard day # #Standard correction
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) # # 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),
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 # # These are corrected for standard day # #Standard correction
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 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 = 'Graupner 13.5x6' #This is a Santiago especial
Prop.D = 13.5 * IN
Prop.Thickness = 5 / 8 * IN
Prop.Pitch = 6 * IN
Prop.dAlpha = 3.7 * ARCDEG
Prop.Solidity = 0.0135
Prop.AlphaStall = 15 * ARCDEG
Prop.AlphaZeroCL = 0 * ARCDEG
Prop.CLSlope = 0.08 / ARCDEG
Prop.CDCurve = 2.3
Prop.CDp = 0.01
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 = [
(4560 * RPM, (2 * LBF + 13 * OZF) * STD),
#(13500 *RPM, (9 *LBF + 3*OZF)*STD),
(5760 * RPM, (3 * LBF + 7 * OZF) * STD),
