#-----------------------------------------------------------------------------#
Wing.WingWeight.WeightGroup = 'MainWing'
#==============================================================================#
# Visualization & Results
#==============================================================================#
if __name__ == '__main__':
import pylab as pyl
print "V lift off : ", AsUnit(Wing.GetV_LO(), 'ft/s')
print "V stall : ", AsUnit(Wing.V_Stall, 'ft/s')
print "Wing Area : ", AsUnit(Wing.S, 'in**2')
print "Wing Span : ", AsUnit(Wing.b, 'in')
print "Wing AR : ", Wing.AR
print "Wing MAC : ", AsUnit(Wing.MAC(), 'in')
print "Wing Xac : ", AsUnit(Wing.Xac(), 'in')
print "Wing dCM_da : ", Wing.dCM_da()
print "Wing dCL_da : ", Wing.dCL_da()
print "Lift off Load: ", AsUnit(Wing.Lift_LO, 'lbf')
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.SetWeightCalc(ACSolidWing)
#Wing.WingWeight.SparMat.LinearForceDensity = 0.0051*LBF/IN
#Wing.WingWeight.SkinMat = Monokote.copy()
#Wing.WingWeight.WingMat = PinkFoam.copy()
#Wing.WingWeight.WingMat.ForceDensity *= 0.5
if __name__ == '__main__':
import pylab as pyl
print "V lift off : ", AsUnit( Wing.GetV_LO(), 'ft/s' )
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)