Refer to figure.
DUTCH ROLL. This is an oscillation involving roll, yaw and sideslip. Because of these characteristics of the Dutch roll oscillation, lateral dynamic stability has always been more of a problem than longitudinal dynamic stability.

With a dominant lateral stability this will, when a yaw is introduced, roll the aircraft due to the lift increase on the wing into the wind. The increased induced drag on the rising wing will yaw the aircraft in the opposite direction, reversing the coupled oscillations. This is called Dutch roll. Dutch roll might occur when the lateral stability is large compared to the directional stability. Therefore, the moments involved are roll and yaw.

• With increasing altitude (decreasing density) or increasing Mach number, the possibility of a Dutch roll increases. The CG position has little influence on the lateral stability, but an aft CG will reduce the directional stability because the Moment Arm of the stabilizing moment from the fin will decrease and thus increasing the likelihood of a Dutch roll.