where xcg is the center of gravity, xnp is the neutral point, and c is the chord length.
where Kp, Ki, and Kd are the controller gains.
Substituting the given values, we get:
∂n / ∂β > 0
Here are some solutions to problems related to flight stability and automatic control: Flight Stability And Automatic Control Nelson Solutions
Gc(s) = Kp + Ki / s + Kd s
-0.1 < 0
where m is the pitching moment and α is the angle of attack.