Beispiel #1
0
    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)
Beispiel #2
0
    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)