ACPlyBH.Thickness = 0.125 * IN
ACPlyBH.ForceDensity = ACPly.ForceDensity * (1 - cutout)
# Section plywood (truss structure + monokote)
# 1/8 inch thick with 80% material cut out
cutout = 0.8
ACPlySkin = ACMaterial()
ACPlySkin.AreaDensity = ACPly.ForceDensity * (
1 - cutout) * 0.125 * IN / g + Monokote.AreaDensity
# Stringer material from basswood (w=0.25 in , t=0.25 in)
# NOTE: added balsa to the stringer to approximate length of the balsa truss members
w = 0.25 * IN
t = 0.25 * IN
BassStringer = ACMaterial()
BassStringer.LinearForceDensity = (Basswood.ForceDensity +
8 * Balsa.ForceDensity) * w * t
###############################################################################
# Wing Materials
###############################################################################
#
# Spar material (balsa, 1/4in width at max airfoil thickness + d-spar skin, balsa 1/16in)
#
sparw = 1 * IN
UWthick = 1.5 * IN
LWthick = 1.5 * IN
LsparFD = Balsa.ForceDensity * sparw * LWthick
UsparFD = Balsa.ForceDensity * sparw * UWthick
# Dspar density as balsa at 1/16in thick and the distance around the front of the airfoil
# approximated as 2 times the airfoil thickness at the root
ACPlyBH = ACMaterial()
ACPlyBH.Thickness = 0.125 * IN
ACPlyBH.ForceDensity = ACPly.ForceDensity * (1 - cutout)
# Section plywood (truss structure + monokote)
# 1/8 inch thick with 80% material cut out
cutout = 0.8
ACPlySkin = ACMaterial()
ACPlySkin.AreaDensity = ACPly.ForceDensity * (
1 - cutout) * 0.125 * IN / g + Monokote.AreaDensity
# Stringer material from basswood (w=0.25 in , t=0.25 in)
w = 0.25 * IN
t = 0.25 * IN
BassStringer = ACMaterial()
BassStringer.LinearForceDensity = Basswood.ForceDensity * w * t
Fuselage = ACFuselage()
#
# Create the sections of the fuselage
#
Fuselage.AddSection('Nose', 6 * IN, 1)
Fuselage.AddSection('PyldBay', 11 * IN, 1)
Fuselage.AddSection('TailTaper')
#
# Size the engine fire wall
#
Fuselage.Nose.FrontBulk.Width = 2.7 * IN
Fuselage.Nose.FrontBulk.Height = 2.7 * IN
Fuselage.Nose.FrontBulk.Material = ACPlyBH