Wing Rock Motion of an Aircraft Model at Fixed Angle of Attack

This paper examined the wing rock motion of an aircraft model with a configuration of slender fuselage, 81°-swept strake wing, 48°-swept wing and twin vertical tails. These experiments covered the alpha range of 0° to 70° and zero sideslip with a Reynolds number (Re) of 1.2×105.The roll motion pattern can be divided into three regions: No wing rock region (α=0-20°), micro-vibration region (α=20°-35° and α=60°-70°), wing rock region (α=35°-60°). At the wing rock region, the motion was not induced by asymmetric vortices on slender forebodythrough the analysis of response relationship between wing rock motion and location of nose perturbation.