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.
SM = (xcg - xnp) / c
The pitching moment coefficient (Cm) is given by: Flight Stability And Automatic Control Nelson Solutions
Altitude Sensor → Controller → Actuator → Aircraft → Altitude Sensor
Clβ = ∂l / ∂β
For lateral stability, the following condition must be satisfied:
Cnβ = ∂n / ∂β
∂m / ∂α < 0