Flight Stability And Automatic Control Nelson Solutions | No Password |
An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability.
The static margin (SM) is given by:
-0.05 < 0
∂n / ∂β > 0
Therefore, the aircraft is longitudinally stable. Flight Stability And Automatic Control Nelson Solutions
For longitudinal stability, the following condition must be satisfied: An aircraft has a static margin of 0
The pitching moment coefficient (Cm) is given by: 0 ∂n / ∂β >