Flight Stability And Automatic Control Nelson Solutions Fix Review
An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability.
∂m / ∂α < 0
Cm = ∂m / ∂α
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