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Effects of angle of attack on wing rock motion induced by the flows over slender body with low swept wing 被引量:1

Effects of angle of attack on wing rock motion induced by the flows over slender body with low swept wing
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摘要 The patterns of wing rock motion at 52.5° angle of attack have already been investigated in detail (Rong, 2009; Wang, 2010). These patterns are completely different from those at other angles of attack. This phenomenon indicates that angle of attack affects wing rock motion. The present study alms to examine the different patterns of wing rock motion at different angles of attack. The flow mechanisms of the motion patterns are also revealed, especially the uncommanded lateral motions, including wing rock and lateral deflection, induced by regular asymmetric separated flow from wings at low angles of attack and fore- body asymmetric vortices at angles of attack of 27.5°〈 α 〈 70°. The test conditions, including the testing Reynolds number, wind tunnel, experimental techniques, and test model, are all the same as those used in a previous study at a = 52.5°. Finally, the experimental technique of rotating nose of the model to suppress the wing rock or lateral deflection, which is induced by forebody asymmetric vortex flow, is applied. The uncommanded lateral motions are successfully suppressed by this technique. The patterns of wing rock motion at 52.5°angle of attack have already been investigated in detail(Rong,2009;Wang,2010).These patterns are completely different from those at other angles of attack.This phenomenon indicates that angle of attack affects wing rock motion.The present study aims to examine the different patterns of wing rock motion at different angles of attack.The flow mechanisms of the motion patterns are also revealed,especially the uncommanded lateral motions,including wing rock and lateral deflection,induced by regular asymmetric separated flow from wings at low angles of attack and forebody asymmetric vortices at angles of attack of 27.5°≤α≤70°.The test conditions,including the testing Reynolds number,wind tunnel,experimental techniques,and test model,are all the same as those used in a previous study at α=52.5°.Finally,the experimental technique of rotating nose of the model to suppress the wing rock or lateral deflection,which is induced by forebody asymmetric vortex flow,is applied.The uncommanded lateral motions are successfully suppressed by this technique.
出处 《Science China(Physics,Mechanics & Astronomy)》 SCIE EI CAS CSCD 2015年第4期67-74,共8页 中国科学:物理学、力学、天文学(英文版)
基金 supported by the National Natural Science Foundation of China(Grant Nos.11172030 and 11102012)
关键词 uncommanded motions forebody asymmetric vortices effect of angle of attack artificial tip perturbation flow control 机翼摇滚 运动模式 分离流动 攻角 车身 实验技术 横向运动 非对称涡
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