print 'Ground Roll : ', AsUnit(Aircraft.Groundroll(), 'ft')
print 'Total Weight : ', AsUnit(Aircraft.TotalWeight, 'lbf')
#print 'Payload Weight : ', AsUnit( Aircraft.PayloadWeight(), 'lbf')
print 'Wing Height : ', AsUnit(Aircraft.Wing.Upper(0 * IN), 'in')
print 'Vertical Tail H: ', AsUnit(Aircraft.VTail.Tip()[2], 'in')
print 'HTail Incidence: ', AsUnit(Aircraft.HTail.i, 'deg')
print "Lift of AoA : ", AsUnit(Aircraft.GetAlphaFus_LO(), 'deg')
print "Zero CM AoA : ", AsUnit(Aircraft.Alpha_Zero_CM, 'deg')
print 'HTail VC : ', AsUnit(Aircraft.HTail.VC)
print 'VTail VC : ', AsUnit(Aircraft.VTail.VC)
print 'VTail Area : ', AsUnit(Aircraft.VTail.S, 'in**2')
print 'HTail Area : ', AsUnit(Aircraft.HTail.S, 'in**2')
print 'HTail Length : ', AsUnit(Aircraft.HTail.L, 'in')
#print 'Empty Weight : ', AsUnit( Aircraft.EmptyWeight, 'lbs')
Aircraft.Draw()
Aircraft.WriteAVLAircraft('AVLAircraft.avl')
Wing.WingWeight.DrawDetail = True
# VTail.WingWeight.DrawRibs = False
# VTail.WingWeight.DrawDetail = False
# VTail.WingWeight.Draw(fig = 2)
# VTail.Draw(fig = 2)
#
# HTail.WingWeight.DrawRibs = False
# HTail.WingWeight.DrawDetail = False
# HTail.WingWeight.Draw(fig = 3)
# HTail.Draw(fig = 3)
# Aircraft.PlotPolarsSlopes(fig=3)
print " 2nd Spar Wt : ", AsUnit(Wing.WingWeight.SecondSpar.Weight,
'ozf')
print " L.E. Weight : ", AsUnit(Wing.WingWeight.LeadingEdge.Weight+\
Wing.WingWeight.LeadingEdgeBent1.Weight+\
Wing.WingWeight.LeadingEdgeBent2.Weight,'ozf')
print " T.E. Weight : ", AsUnit(Wing.WingWeight.TrailingEdge1.Weight+\
Wing.WingWeight.TrailingEdge2.Weight,'ozf')
print " Rib Weight : ", AsUnit(Wing.WingWeight.RibWeight(), 'ozf')
print " Skin Weight : ", AsUnit(Wing.WingWeight.SkinWeight(), 'ozf')
# print " Servos Weight: ", AsUnit(2*Wing.Aileron.Servo.Weight,'ozf')
print
##
######### SPH: ADD THESE OUTPUTS ##########
#Cn beta, Cm alpha, Cl beta
Aircraft.Draw(fig=1)
## Wing.WingWeight.MainSpar.Draw(fig = 1)
## Wing.WingWeight.SecondSpar.Draw(fig = 1)
Aircraft.WriteAVLAircraft('AVLAircraft.avl')
Aircraft.PlotPolarsSlopes(fig=2)
## Aircraft.PlotCMPolars(3, (-10*ARCDEG, -5*ARCDEG, 0*ARCDEG, +5*ARCDEG, +10 * ARCDEG), XcgOffsets=(+0.05, -0.05))
# CG LIMITS: AFT = +12%, FWD = -22%
## HTail.Draw2DAirfoilPolars(fig=4)
## Aircraft.PlotCLCMComponents(fig = 5, del_es = (-10*ARCDEG, -5*ARCDEG, 0*ARCDEG, +5*ARCDEG, +10 * ARCDEG))
## Aircraft.PlotPropulsionPerformance(fig=6)
VTail.WingWeight.DrawRibs = True
VTail.WingWeight.DrawDetail = True
## VTail.WingWeight.Draw(fig = 7)
## VTail.Draw(fig = 8)