def test_Power(self):
"""
Tests that the engine class is working properly
"""
# Create the propeller defined in the mathcad pdf documents
Prop = ACPropeller()
Prop.D = 14.2*IN
Prop.PitchAngle = 12*ARCDEG
# Prop.Pitch = 7.1117*IN
Prop.dAlpha = 0*ARCDEG
Prop.Solidity = 0.0136
Prop.RD = 3/8
Prop.AlphaStall = 14*ARCDEG
N = 11400 * RPM
self.assertAlmostEqual(Prop.P(N, 0*FT/SEC, 0*FT) / HP, 1.2950, 4)
from __future__ import division # let 5/2 = 2.5 rather than 2 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
from __future__ import division # let 5/2 = 2.5 rather than 2 from Aerothon.ACPropeller import ACPropeller from Aerothon.ACEngine import ACEngine from Aerothon.ACPropulsion import ACPropulsion import numpy as npy from Aerothon.scalar.units import IN, LBF, PSFC, SEC, ARCDEG, FT, OZF, RPM, HP from Aerothon.scalar.units import AsUnit # Set Propeller properties Prop = ACPropeller() Prop.D = 13.5 * IN # Diameter Prop.Thickness = .5 * IN # Thickness at the hub... just for drawing purposes Prop.PitchAngle = 14 * ARCDEG # Pitch angle.. aka \Beta Prop.dAlpha = 0 * ARCDEG # Difference between measured alpha and zero lift alpha Prop.Solidity = 0.0136 # Proportional to the blade disk area, similar to the activity factor (AreaBlades/(2*D**2)) Prop.RD = 3 / 8 # The location on the profile chord where the PitchAngle is defined (default 3/8) Von Mises 306 Prop.AlphaStall = 12 * ARCDEG # Stall angle of attack Prop.Weight = 3 / 32 * LBF # Weight # Use these parameters to match test data if need be. # Prop.CLSlope = .078/ARCDEG #- 2D airfoil lift slope # Prop.CDCurve = 2.2 #- 2D curvature of the airfoil drag bucket # Prop.CDp = .02 #- Parasitic drag # Set Engine properties - glow engine... see 2015 files for setting up electric motor Engine = ACEngine() Engine.Rbs = 1.1 Engine.Rla = 3.5 Engine.NumCyl = 1 Engine.NumRev = 1 Engine.CompRatio = 9