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Calculate Static Margin of Airplane Method to Calculate the State Margin of the Airplane 

Aerospace



Static Margin of Airplane In order to Calculate the Longitudinal Static Stability of Airplane Model (wing body configuration) being testing in a subsonic 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,
Performing the Calculation the Neutral Point Location is computed and then the Static Margin is computed.
The formula used in calculation for Static Margin is, Static Margin = hnh
Download Free Program to Calculate the Static Margin of an Airplane

