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The CG position of an aeroplane is 12.40 m aft of the datum. Determine the CG position as % MAC, given:

Leading edge of the wing root: 11.83 m aft of the datum
Leading edge of MAC: 12.12 m aft of the datum
Leading edge of the wing tip: 12.81 m aft of the datum
Length of the wing root chord: 1.55 m
Length of MAC: 1.34 m
Length of the wing tip chord: 0.61 m

  • A

    20.90% MAC

  • B

    36.77% MAC

  • C

    86.94% MAC

  • D

    90.65% MAC

MAC length = 1.34 m

Distance between LE MAC and CG = 12.40 m - 12.12 m = 0.28 m

CG is 0.28 m behind the LE, which is (0.28 / 1.34) x 100 of the MAC = 20.90% MAC

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