where m is the pitching moment and α is the angle of attack.
An aircraft has a lateral stability derivative of -0.1 and a directional stability derivative of -0.2. Determine the aircraft's lateral and directional stability.
where xcg is the center of gravity, xnp is the neutral point, and c is the chord length. Flight Stability And Automatic Control Nelson Solutions
∂m / ∂α < 0
The lateral stability derivative (Clβ) is given by: where m is the pitching moment and α is the angle of attack
where l is the rolling moment and β is the sideslip angle.
∂l / ∂β < 0
Cm = ∂m / ∂α