Wing Rock Induced by Forebody Asymmetric Vortex in Coning Motion and its Control Method

An experimental investigation of wing rock induced by forebody vortex in coning motion over wing/body model with sweep angle of 30° and its control method has been conducted in wind tunnel at angle of attack of 50° and Reynolds number of 1.56×105 based on the diameter of the cylinder body with free-to-roll equipment. Firstly, wing rock pattern is determined by nose tip perturbation in coning motion, which is same as the static case. Secondly, coning rate has no effect on the frequency and amplitude of wing rock. Finally, wing rock can be suppressed by control technique of rotating nose perturbation also.