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.
Wing Rock Motion of an Aircraft Model at Fixed Angle of Attack
2013
10 Seiten, 8 Quellen
Conference paper
English
Aircraft Wing Rock in High-Angle-of-Attack Flight
AIAA | 2010
|European Patent Office | 2018
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