-0.2 > 0 (not satisfied)
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.
-0.1 < 0
Cnβ = ∂n / ∂β
Substituting the given values, we get:
Therefore, the aircraft is longitudinally stable.
∂n / ∂β > 0