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 Method to Calculate the Moment Coefficient about the Center of Gravity Cm,cg of Airplane Model





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Moment Coefficient Cm,cg of Airplane

In order to Calculate the Moment Coefficient about the Center of Gravity, Cm,cg of Airplane Model (wing body arrangement) being testing in a sub-sonic wind tunnel.



We must first have the value at which the Lift is found to zero at geometric angle of attack, alpha


We must also have the Angle of Attack, AOA alpha value and the corresponding Lift Coefficient Cl at this AOA.


Furthermore, we must also have two additional alpha values and the corresponding Moment Coefficients about the center of gravity.


The center of gravity in terms of Mean aerodynamic chord c is then entered.


Now, the Aircraft design parameters are entered,

  • Area of the Wing in meters^2 (m^2)

  • Chord of the Wing (c)

  • Tail Moment Arm - Distance from Airplane's Center of Gravity to Tail's Aerodynamic Center

  • Tail Area

  • Tail Setting Angle

  • Tail Lift Slope

  • Epsilon and depsilon/dalpha values.

Performing the calculation, the following parameters are computed,

  • Value of a

  • h-hac (wb)

  • Vh = ltSt/Sc

  • Value of at

  • Valule of it

  • Cm,cg value

Download Free Program to Calculate the Cmcg, Moment about Center of gravity of an Airplane