Flight Stability And Automatic Control Nelson Solutions Now

Cm = ∂m / ∂α

Design an autopilot system to control an aircraft's altitude.

where n is the yawing moment.

The lateral stability derivative (Clβ) is given by:

Therefore, the aircraft is longitudinally stable. Flight Stability And Automatic Control Nelson Solutions

The directional stability derivative (Cnβ) is given by:

-0.1 < 0

where xcg is the center of gravity, xnp is the neutral point, and c is the chord length.