VTail2.WingWeight.TrailingEdge1.WeightGroup = "VTail2"
VTail2.WingWeight.AddSpar("TrailingEdge2", 1 / 16 * IN, 13 / 8 * IN,
(0.25, 1), 1.0, False)
VTail2.WingWeight.TrailingEdge2.SparMat = Balsa.copy(
) #.LinearForceDensity = .008*LBF/(1*IN)
VTail2.WingWeight.TrailingEdge2.Position = (0.915, -0.2)
VTail2.WingWeight.TrailingEdge2.ScaleToWing = [False, False]
VTail2.WingWeight.TrailingEdge2.WeightGroup = "VTail2"
###############################################################################
#
# Landing Gear
#
###############################################################################
Aluminum = Aluminum.copy()
Steel = Steel.copy()
MainGear = Aircraft.MainGear
MainGear.Theta = 89.9 * ARCDEG
#MainGear.GearHeight = 3 * IN
MainGear.StrutL = 4 * IN
MainGear.StrutW = 0.2 * IN
MainGear.StrutH = 0.1 * IN
MainGear.WheelDiam = 4 * IN
MainGear.X[1] = 2.0 * IN
MainGear.Strut.Weight = 0.1 * LBF #math.pi*(0.125/2*IN)**2*12*IN*Aluminum.ForceDensity #1/8 inch diameter steel, l=12in
MainGear.Strut.WeightGroup = "LandingGear"
MainGear.Wheel.Weight = 0.1 * LBF
MainGear.Wheel.WeightGroup = "LandingGear"
NoseGear = Aircraft.NoseGear
# Main Spar Material 1/8th in steel web
# Spar material (basswood, 1/4in width at max airfoil thickness + d-spar skin, balsa 1/16in)
#
SparW = 1*IN
SparH = 2*IN
CapH = 1/8*IN
WebW = 1/8*IN
CapArea = SparW*CapH*2
WebArea = WebW*SparH*2
SparLinearDensity = WebArea*Balsa.ForceDensity + CapArea*Balsa.ForceDensity
Wing.SetWeightCalc(ACRibWing)
Wing.WingWeight.AddSpar("MainSpar", SparH, SparW, (0.25,0), 1.0, False)
Wing.WingWeight.MainSpar.SparMat = Aluminum.copy()
Wing.WingWeight.MainSpar.SparMat.LinearForceDensity = SparLinearDensity
Wing.WingWeight.MainSpar.ScaleToWing = [False, False]
Wing.WingWeight.MainSpar.WeightGroup = "MainWing"
Wing.WingWeight.SkinMat = Ultracote.copy()
Wing.WingWeight.AddSpar("SecondSpar", 1/2*IN, 1/2*IN, (0.75,-0.01),1.0, False)
Wing.WingWeight.SecondSpar.SparMat = Balsa.copy()
Wing.WingWeight.SecondSpar.ScaleToWing = [False, False]
Wing.WingWeight.SecondSpar.WeightGroup = "MainWing"
Wing.WingWeight.AddSpar("ThirdSpar", 1/2*IN, 1/2*IN, (0.5,-0.01),1.0, False)
Wing.WingWeight.ThirdSpar.SparMat = Balsa.copy()
Wing.WingWeight.ThirdSpar.ScaleToWing = [False, False]
Wing.WingWeight.ThirdSpar.WeightGroup = "MainWing"