Effects of tip perturbation and wing locations on rolling oscillation induced by forebody vortices  

作　　者：Bing Wang Xue-Ying Deng Bao-Feng Ma Zhen Rong 

机构地区：[1]Key Laboratory of Fluid Mechanics, (Beihang University),

出　　处：《Acta Mechanica Sinica》2010年第5期787-791,共5页力学学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (10432020, 10872019 and 10702004)

摘　　要：The wing rock motion is frequently suffered by a wing-body configuration with low swept wing at high angle of attack. It is found from our experimental study that the tip perturbation and wing longitudinal locations affect significantly the wing rock motion of a wing-body. The natural tip perturbation would make the wing rock motion of a nondeterministic nature and an artificial mini-tip perturbation would make the wing rock motion deterministic. The artificial tip perturbation would, as its circumferential location is varied, generate three different types of motion patterns： （1） limit cycle oscillation, （2） irregular oscillation, （3） equilibrium state with tiny oscillation. The amplitude of rolling oscillation corresponding to the limit cycle oscillatory motion pattern is decreased with the wing location shifting downstream along the body axis.The wing rock motion is frequently suffered by a wing-body configuration with low swept wing at high angle of attack. It is found from our experimental study that the tip perturbation and wing longitudinal locations affect significantly the wing rock motion of a wing-body. The natural tip perturbation would make the wing rock motion of a nondeterministic nature and an artificial mini-tip perturbation would make the wing rock motion deterministic. The artificial tip perturbation would, as its circumferential location is varied, generate three different types of motion patterns： （1） limit cycle oscillation, （2） irregular oscillation, （3） equilibrium state with tiny oscillation. The amplitude of rolling oscillation corresponding to the limit cycle oscillatory motion pattern is decreased with the wing location shifting downstream along the body axis.

关 键 词：Wing rock motion- Asymmetric vortices flow High angle of attack aerodynamics Nose tip perturbation 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] O357.52[理学—流体力学]