不同头部形状单孔位微吹气扰动控制实验研究

孙淑园; 邓学蓥; 詹慧玲

不同头部形状单孔位微吹气扰动控制实验研究

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 国家自然科学基金资助项目(10172017);航空科学基金资助项目(02A51048);武器装备预研基金资助项目(51413020103HK0167)

详细信息

作者简介:
孙淑园(1976-),男,陕西西安人,硕士生,sysun cn@hotmail.com.

中图分类号: V 211.42
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- 文章访问数: 3026
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- 被引次数: 0
出版历程
- 收稿日期: 2004-01-12
- 网络出版日期: 2005-06-30

Study of flow control over different noses with single hole microblowing

School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 在亚临界流动范围内,对具有不同头部形状的尖拱形细长旋成体在无侧滑大迎角下进行单孔位微吹气扰动控制实验.通过对物面压力分布、截面侧向力分布和以前细长旋成体结果的对比和分析,发现单孔位微吹气扰动对于细长旋成体横侧向控制作用在于模型头部背风侧非对称二涡结构对扰动的敏感性.实验分析表明,单孔位微吹气扰动这一大迎角非对称控制手段具有较强的适应能力,其控制能力的大小则由该头部形状的初始状态决定.
- 细长体 /
- 空气动力学 /
- 非对称涡 /
- 前体涡控制
Abstract: The SHM(single hole microblowing) as a new perturbation active control technique has been applied to the slender body with different model noses at zero sideslip and high angle of attack. The analyzed and contrasted results of the distribution of the surface pressure distributions and the sectional side forces with the former results of the slender body in the same flow conditions show that the SHM’s control effect to the slender body is due to that the two asymmetric vortices over the slender body model are sensitive to the nose perturbations. The analyses indicate that the SHM’s control ability has strong adaptability to various slender body at high angles of attack, and its control ability is determined by the original state of the flowfield around the slender body.
- slender body /
- aerodynamics /
- asymmetric vortices flow /
- forebody vortex control

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参考文献(1)

[1] Allen H J, Perkins E W. Characteristics of flow over inclined bodies of revolution[J]. NACA RMA50L07, 1951 [2] Hunt B L. Asymmetric vortex forces and wakes on slender bodies [J]. AIAA Paper 82-1336, 1982 [3] Chapman G T, Keener E R. Aerodynamics of bodies of revolution at angle of attack to 90° [J]. AIAA Paper 79-0023, 1979 [4] Lamont P J, Hunt B L. Pressure and force distributions on a sharp-nosed circular cylinder at large angles of inc1ination to a uniform subsonic stream[J]. J Fluid Mech, 1976, 76 (3):519~559 [5] Deng Xueying, Wang Gang, Chen Xuerui, et al. A physical model of asymmetric vortices flow structure in regular state over slender body at high angle of attack [J]. Science in China (English Version), 2003, 46(6):561~573 [6] 邓学蓥,王刚. 细长体大迎角流动的确定性和多涡系结构的研究 . 全国第九届分离流、旋涡和流动控制会议论文集 . 北京,2002. 191~200 Deng Xueying, Wang Gang. The study of determinacy of flow and multi-vortices structure over slender body at high angle of attack . The Proceedings of 9^th National Separated Flow, Vortex and Flow Control Conference . Beijing, 2002.191~200(in Chinese) [7] Chen Xuerui, Deng Xueying, Wang Yankui, et al. Influence of nose perturbations on behaviors of asymmetric vortices over slender body . ACTA Echanica Sinica , 2002, 18(6):581~593 [8] Deng Xueying. Certainty and physical model of the flow over slender body at high angles of attack . 4^th APCATS (Invited Paper), 2002 [9] Malcolm G N. Forebody vortex control . Progress Aerospace Sci, 1991,28:171~234 [10] Malcolm G N. Forebody vortex control—a progress review . AIAA 93-3540, 1993 [11] Williams D. A review of forebody vortex control scenarios[J]. AIAA 97-1967, 1997 [12] Bernhardt J E, Williams D R. Proportional control of asymmetric forebody vortices [J]. AIAA Journal, 1998, 36 (11):2087~2093 [13] Roos F W. Microblowing:an effective, efficient method of vortex-asymmetry management [J]. AIAA 2000-4416, 2000 [14] 邓学蓥.前体非对称涡流动及其扰动主动控制 .空气动力学前沿研究论文集 . 北京:中国宇航出版社,2003. 8~17 Deng Xueying. Forebody asymmetric vortices and its active control with perturbation . Proceedings of Frontier Research on Aerodynamics .Beijing:China Astronautics Publishing House,2003.8~17(in Chinese) [15] 陈学锐. 细长体非对称涡的扰动效应及其主动控制研究 .北京:北京航空航天大学航空科学与工程学院,2003 Chen Xuerui. Perterbation effect and active control on behaviors of asymmetric vortices over slender body . Beijing:School Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, 2003(in Chinese)

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