print "Wing Thk : ", AsUnit(Wing.Thickness(0 * FT), 'in')
print "Wing Chord : ", AsUnit(Wing.Chord(0 * FT), 'in')
print "Wing Lift : ", AsUnit(Wing.Lift_LO, 'lbf')
print "Wing MOI : ", AsUnit(Wing.MOI(), 'slug*ft**2')
print
print "WEIGHT CALCULATIONS"
print "Main Spar Wt : ", AsUnit(Wing.WingWeight.MainSpar.Weight, 'ozf')
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 "WING WEIGHT : ", AsUnit(Wing.Weight, 'ozf')
print
Wing.WriteAVLWing('ATLASWing.avl')
Wing.Draw(fig=1)
Wing.Draw3DWingPolars(fig=2)
Wing.Draw2DAirfoilPolars(fig=3)
Wing.WingWeight.DrawRibs = True
Wing.WingWeight.DrawDetail = True
Wing.WingWeight.Draw(fig=4)
pyl.show()
print "V stall : ", AsUnit(Wing.V_Stall, 'ft/s')
print "Wing Area : ", AsUnit(Wing.S, 'in**2')
print "Wing Span : ", AsUnit(Wing.b, 'ft')
print "Wing AR : ", Wing.AR
print "Wing MAC : ", AsUnit(Wing.MAC(), 'in')
print "Wing Xac : ", Wing.Xac()
print "Wing dCM_da : ", Wing.dCM_da()
print "Wing dCL_da : ", Wing.dCL_da()
print "Lift of Load: ", AsUnit(Wing.Lift_LO, 'lbf')
print "Wing Thickness: ", AsUnit(Wing.Thickness(0 * FT), 'in')
print "Wing Chord : ", AsUnit(Wing.Chord(0 * FT), 'in')
print "Wing Area : ", AsUnit(Wing.S, 'in**2')
print "Wing Lift : ", Wing.Lift_LO
print
print "Wing Weight : ", AsUnit(Wing.Weight, 'lbf')
print "Wing MOI : ", AsUnit(Wing.MOI(), 'slug*ft**2')
#Wing.WriteAVLWing('MonoWing.avl')
Wing.Draw3DWingPolars(fig=3)
Wing.Draw2DAirfoilPolars(fig=2)
Wing.WingWeight.DrawRibs = False
Wing.WingWeight.DrawDetail = True
Wing.WingWeight.Draw(fig=1)
Wing.Draw3DWingPolars(fig=4)
Wing.Draw2DAirfoilPolars(fig=5)
Wing.Draw(fig=1)
pyl.show()