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 Calculate Longitudinal Static Stability of Airplane

 Method to Calculate the Longitudinal Static Stability of Airplane

 

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Longitudinal Static Stability of Airplane

In order to Calculate the Longitudinal Static Stability of Airplane Model 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 we can find out whether the Airplane is Static Stable or Statically Unstable.

 

Furthermore, we can also find out whether the Airplane is Longitudinally balanced or not.

 

And value of dCm,cg/dalpha and Cm,0 are calculated.

 

Download Free Program to Calculate the Longitudinal Static Stability of an Airplane