# 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) Prop.ThrustData = [
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),
(6510 * RPM, (3 * LBF + 2 * OZF) * STD),
(5610 * RPM, (1 * LBF + 12 * OZF) * STD)]
# 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 STD = STDCorrection(29.79 * inHg, (29.79 + 273.15) * K)
# 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), # (10650 *RPM, (8 *LBF + 6 *OZF)*STD), # (10500 *RPM, (6 *LBF + 12*OZF)*STD),
# 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 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