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 cfx by normalized roll rate

Change of cfx by normalized pitch rate

Change of cfx by normalized yaw rate

Change of cfy by normalized roll rate

Change of cfy by normalized pitch rate

Change of cfy by normalized yaw rate

Change of cfz by normalized roll rate

Change of cfz by normalized pitch rate

Change of cfz by normalized yaw rate

Change of cmx by normalized roll rate

Change of cmx by normalized pitch rate

Change of cmx by normalized yaw rate

Change of cmy by normalized roll rate

Change of cmy by normalized pitch rate

Change of cmy by normalized yaw rate

Change of cmz by normalized roll rate

Change of cmz by normalized pitch rate

Change of cmz by normalized yaw rate