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)