Therefore, the aircraft is directionally unstable.
Clβ = ∂l / ∂β
Substituting the given values, we get:
-0.2 > 0 (not satisfied)
For longitudinal stability, the following condition must be satisfied: Flight Stability And Automatic Control Nelson Solutions
Design an autopilot system to control an aircraft's altitude.
∂m / ∂α < 0
The lateral stability derivative (Clβ) is given by: