TestData = [(7000 * RPM, 107.35 * IN * OZF, 0.75 * HP),
(8500 * RPM, 104.24 * IN * OZF, 0.88 * HP),
(9500 * RPM, 101.13 * IN * OZF, 0.95 * HP),
(9700 * RPM, 98.02 * IN * OZF, 0.94 * HP),
(10600 * RPM, 102.69 * IN * OZF, 1.08 * HP),
(10800 * RPM, 98.02 * IN * OZF, 1.05 * HP),
(11000 * RPM, 101.13 * IN * OZF, 1.1 * HP),
(11200 * RPM, 99.57 * IN * OZF, 1.11 * HP),
(11600 * RPM, 98.02 * IN * OZF, 1.13 * HP),
(12900 * RPM, 93.35 * IN * OZF, 1.19 * HP),
(13300 * RPM, 91.79 * IN * OZF, 1.21 * HP),
(13600 * RPM, 91.79 * IN * OZF, 1.24 * HP),
(14600 * RPM, 88.68 * IN * OZF, 1.28 * HP),
(15600 * RPM, 79.35 * IN * OZF, 1.23 * HP),
(16300 * RPM, 77.76 * IN * OZF, 1.26 * HP)]
Engine.TestData = TestData
Engine.PlotTestData()
print "Static Thrust :", AsUnit(Propulsion.T(0 * FT / SEC), 'lbf')
V = npy.linspace(0, 100, 30) * FT / SEC
N = npy.linspace(1000, 20000, 30) * RPM
#Propulsion.PlotMatched(V, fig = 2)
V2 = npy.linspace(0, 100, 5) * FT / SEC
Propulsion.PlotTPvsN(N, V2, fig=3)
Propulsion.Draw(fig=4)
pyl.show()
BoxWing.UpperWing.WingWeight.MainSpar.SparMat = CarbonBar.copy()
BoxWing.UpperWing.WingWeight.SkinMat = Monokote.copy()
BoxWing.UpperWing.WingWeight.WingMat = PinkFoam.copy()
BoxWing.UpperWing.WingWeight.WingMat.ForceDensity *= 0.5
BoxWing.EndPlate.SetWeightCalc(ACSolidWing)
BoxWing.EndPlate.WingWeight.AddSpar("MainSpar", 0.25 * IN, 0.125 * IN)
BoxWing.EndPlate.WingWeight.MainSpar.SparMat = CarbonBar.copy()
BoxWing.EndPlate.WingWeight.SkinMat = Monokote.copy()
BoxWing.EndPlate.WingWeight.WingMat = PinkFoam.copy()
BoxWing.EndPlate.WingWeight.WingMat.ForceDensity *= 0.4
if __name__ == '__main__':
import pylab as pyl
print "V lift of : ", AsUnit(BoxWing.GetV_LO(), 'ft/s')
print "V stall : ", AsUnit(BoxWing.V_Stall, 'ft/s')
print "Wing Area : ", AsUnit(BoxWing.S, 'in**2')
print "Wing Span : ", AsUnit(BoxWing.b, 'ft')
print "Wing AR : ", BoxWing.AR
print "Wing MAC : ", AsUnit(BoxWing.MAC(), 'in')
print "Wing Xac : ", BoxWing.Xac()
print "Wing dCM_da : ", BoxWing.dCM_da()
print "Wing dCL_da : ", BoxWing.dCL_da()
print "Lift of Load: ", AsUnit(BoxWing.Lift_LO, 'lbf')
print "Wing BWFC : ", BoxWing.BWCF()
print
print "Wing Thickness: ", BoxWing.LowerWing.Thickness(0 * FT)
print "Wing Chord : ", BoxWing.LowerWing.Chord(0 * FT)
print "LowerWing Area: ", BoxWing.LowerWing.S
print "UpperWing Area: ", BoxWing.UpperWing.S
MainGear.Wheel.Weight = 0.1 * LBF
NoseGear = Aircraft.NoseGear
NoseGear.StrutW = 0.1 * IN
NoseGear.StrutH = 0.1 * IN
NoseGear.WheelDiam = 2.5 * IN
NoseGear.Strut.Weight = 0.1 * LBF
NoseGear.Wheel.Weight = 0.1 * LBF
if __name__ == '__main__':
#TCG = Aircraft.CG()
ACG = Aircraft.Fuselage.AircraftCG()
#dCG = TCG - ACG
print 'Aircraft Xnp :', AsUnit(Aircraft.Xnp(), 'in')
print 'Aircraft Xcg :', AsUnit(Aircraft.Xcg(), 'in')
print 'Aircraft CM :', Aircraft.CM(15 * ARCDEG, del_e=10 * ARCDEG)
print 'Aircraft dCM_da:', AsUnit(Aircraft.dCM_da(), '1/rad')
print
print 'Wing Area :', AsUnit(Aircraft.Wing.S, 'in**2')
print 'Wing MAC :', AsUnit(Aircraft.Wing.MAC(), 'in')
print 'Wing dCl_da :', AsUnit(Aircraft.Wing.dCL_da(), '1/rad')
print 'Wing Xac :', AsUnit(Aircraft.Wing.Xac(), 'in')
print
print 'Horiz Area :', AsUnit(Aircraft.HTail.S, 'in**2')
print 'Horiz Length :', AsUnit(Aircraft.HTail.L, 'in')
print 'Horiz iht :', AsUnit(Aircraft.HTail.i, 'deg')
print 'Horiz dCl_da :', AsUnit(Aircraft.HTail.dCL_da(), '1/rad')
print 'Horiz Design CL:', Aircraft.GetHT_Design_CL()
print
(5000 *RPM, (8.2*Arm*OZF)),
(4560 *RPM, (6.5*Arm*OZF)),
(4000 *RPM, (4.7*Arm*OZF)),
(3525 *RPM, (3.4*Arm*OZF)),
# begin 2nd taking of torque data in closet
(5690 *RPM, (9.5*Arm2*OZF)),
(5018 *RPM, (7.1*Arm2*OZF)),
(4525 *RPM, (5.7*Arm2*OZF)),
(4118 *RPM, (4.8*Arm2*OZF))]
#==============================================================================#
# VISUALIZATION & RESULTS
#==============================================================================#
if __name__ == '__main__':
print " D : ", AsUnit( Prop.D, 'in')
print " Pitch : ", AsUnit( Prop.Pitch, 'in')
Vmax = 50
h=0*FT
N=npy.linspace(1000, 6800, 5)*RPM
Alpha = npy.linspace(-25,25,41)*ARCDEG
V = npy.linspace(0,Vmax,30)*FT/SEC
Prop.CoefPlot(Alpha,fig = 1)
Prop.PTPlot(N,V,h,'V', fig = 2)
# N = npy.linspace(0, 13000,31)*RPM
# V = npy.linspace(0,Vmax,5)*FT/SEC
Motor.SpeedController.WeightGroup = 'Electronics'
Motor.WeightGroup = 'Propulsion'
#
# This data has been corrected for standard day
STD = STDCorrection(30.2 * inHg, (16.1 + 273.15) * K)
Arm = 19.5 * IN
# RPM, Torque Current Voltage
TestData = [(6030 * RPM, (7.3 * Arm * OZF) * STD, 32.0 * A, 22.8 * V),
(5670 * RPM, (8.3 * Arm * OZF) * STD, 36.0 * A, 22.2 * V),
(5430 * RPM, (9.3 * Arm * OZF) * STD, 39.5 * A, 21.5 * V),
(5340 * RPM, (9.0 * Arm * OZF) * STD, 38.7 * A, 21.1 * V),
(5370 * RPM, (8.3 * Arm * OZF) * STD, 35.3 * A, 20.9 * V)
] #this is actual test data from a test stand
Motor.TestData = TestData
if __name__ == '__main__':
import pylab as pyl
print "V to Motor : ", AsUnit(Motor.Vmotor(Ib=3.75 * A), 'V')
print "Efficiency : ", Motor.Efficiency(Ib=3.75 * A)
print "Max efficiency : ", Motor.Effmax()
print "Max efficiency current : ", AsUnit(Motor.I_Effmax(), 'A')
print "Max efficiency RPM : ", AsUnit(Motor.N_Effmax(), 'rpm')
Motor.PlotTestData()
pyl.show()
Motor.xRm = 100000
Motor.Pz = 0.0
# This data has been corrected for standard day #SPH: confirm the methodology behind these calculations 151113
STD = STDCorrection(29.9 * inHg, (23.9 + 273.15) * K)
Arm = 19.5 * IN
# Test data from the test stand
# RPM, Torque Current Voltage
TestData = [(6200 * RPM, (7.5 * Arm * OZF) * STD, 34.8 * A, 23.0 * V),
(5900 * RPM, (8.7 * Arm * OZF) * STD, 39.0 * A, 21.9 * V),
(5600 * RPM, (9.9 * Arm * OZF) * STD, 44.2 * A, 21.5 * V),
(6000 * RPM, (8.9 * Arm * OZF) * STD, 35.8 * A, 22.06 * V),
(5800 * RPM, (11.1 * Arm * OZF) * STD, 45.2 * A, 21.9 * V)]
Motor.TestData = TestData
#==============================================================================#
# VISUALIZATION & RESULTS
#==============================================================================#
if __name__ == '__main__':
print 'V to Motor : ', AsUnit(Motor.Vmotor(Ib=45 * A), 'V')
print 'Efficiency : ', Motor.Efficiency(Ib=45 * A)
print 'Max efficiency : ', Motor.Effmax()
print 'Max eff. current : ', AsUnit(Motor.I_Effmax(), 'A')
print 'Max eff. RPM : ', AsUnit(Motor.N_Effmax(), 'rpm')
Motor.PlotTestData()
pyl.show()