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 Calculate Neutral Point Location of Airplane

 Method to Calculate the Neutral Point Location on an Airplane

 

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Neutral Point Location of Airplane

In order to Calculate the Neutral Point Location 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 have the Neutral Point Location hn of the Airplane. The following formula for Neutral Point Location hn is used in the calculation,

 

hn = hac(wb) + Vh(at/a)(1-depsilon/dalpha)

 

Download Free Program to Calculate the Neutral Point of an Airplane