Ejemplo n.º 1
0
if __name__ == '__main__':
    import pylab as pyl

    print "V lift of   : ", 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: ", Wing.Thickness(0 * FT)
    print "Wing Chord    : ", Wing.Chord(0 * FT)
    print "Wing Area     : ", Wing.S
    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=5)
    #    Wing.Draw2DAirfoilPolars(fig=4)
    #
    #    Wing.Draw3DWingPolars(fig=3)
    #    Wing.Draw2DAirfoilPolars(fig=2)

    Wing.Draw(fig=1)
Ejemplo n.º 2
0
#==============================================================================#
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.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')
Ejemplo n.º 3
0
#==============================================================================#
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 "Root Chord   : ", AsUnit(Wing.Chord(0 * FT), 'in')
    print "Tip Chord    : ", AsUnit(Wing.Chord(0 * FT) * endChord, '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')