1. Wing Rock Motion of an Aircraft Model at Fixed Angle of Attack.
- Author
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Wang, Y.K., Li, Q., Shi, W., and Sun, G.L.
- Subjects
FUSELAGE (Airplanes) ,REYNOLDS number ,PERTURBATION theory ,PHYSICS experiments ,AIRPLANE tails - Abstract
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. [ABSTRACT FROM AUTHOR]
- Published
- 2013
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