Flight Stability And Automatic Control Nelson Solutions

An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability.

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

Substituting the given values, we get:

Substituting the given values, we get:

Therefore, the aircraft is directionally unstable. An aircraft has a static margin of 0

where m is the pitching moment and α is the angle of attack. we get: Substituting the given values