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()