This type contains aerodynamic performance maps with the damping derivatives. The derivatives are calculated using rotational rates [rad/s], normalized by: Rate*ReferenceLength/flow speed. The rotations are performed around the global axis directions with the aircraft model's global reference point as origin. The damping derivative performance maps are arrays consisting of semicolon separated values, simular to the baseline aerodynamic performance maps.

Change of cd by normalized roll rate

Change of cd by normalized pitch rate

Change of cd by normalized yaw rate

Change of cs by normalized roll rate

Change of cs by normalized pitch rate

Change of cs by normalized yaw rate

Change of cl by normalized roll rate

Change of cl by normalized pitch rate

Change of cl by normalized yaw rate

Change of cmd by normalized roll rate

Change of cmd by normalized pitch rate

Change of cmd by normalized yaw rate

Change of cms by normalized roll rate

Change of cms by normalized pitch rate

Change of cms by normalized yaw rate

Change of cml by normalized roll rate

Change of cml by normalized pitch rate

Change of cml by normalized yaw rate