Control of Vortex Breakdown-Fin Interaction on a Delta Wing

三角翼上涡流击穿与翅片相互作用的控制

• 批准号: 12650896
• 负责人: OKAMOTO Satoru
• 金额: $ 1.02万
• 依托单位: Shimane University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2000
• 资助国家: 日本
• 起止时间: 2000 至 2002
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-12650896/
• 关键词: Unsteady Flows; Flow-Induced Vibration; Vortex Breakdown; Delta Wing; Fin Interaction; PIV; Visualization

Modern high performance aircraft exploit vortex flows for enhanced maneuverability and control. Streamwise vortices, which are generated at various locations on the aircraft, can interact with fins and tails, and result in flow-induced vibration. In recent years, there have been a number of studies of vortex impingement upon various appendages of models of the aircraft as well as simple delta wing representations of aircraft. The interaction of broken-down vortices with downstream appendages is expected to exhibit certain generic features irrespective of the geometrical details of the aircraft.The objective of this study is to relate the ensemble-averaged and instantaneous structure of vortex breakdown incident upon a fin to spectra of surface pressure along the fin. High-image-density particle image velocimetry (PIV) is used to determine the velocity fields and vorticity distributions, which, in turn, lead to a physical interpretation of the pressure spectra. Various combinations of i … More nstantaneous and averaged velocity fields, in conjunction with root-mean-square representations of vorticity fluctuations, provide a rational basis for the corresponding pressure spectra, which are measured at crucial locations on the surface of the fin.The delta wing-fin system was mounted in an inverted position in the water channel, such that the wing was at a negative angle of attack, in order to facilitate laser diagnostics. Instantaneous velocity fields and surface pressure measurements were obtained at two different distances from the trailing-edge of the delta wing to the leading-edge of the fin. This inverted position of the wing allowed acquisition of instantaneous images of the velocity over the fields of view.Impingement of a broken-down vortex on a fin having a swept leading-edge generates a complex flow structure associated with a large-scale separation zone extending over the surface of the fin. This paper is focused on establishing a relationship between the instantaneous velocity and vorticity fields of a broken-down vortex incident upon a fin and the surface pressure fluctuations induced along the leading-edge region of a fin. The principal features of this flow and the associated pressure fluctuations are as follows: Less

现代高性能飞机利用涡流来增强机动性和控制力。飞机上不同位置产生的流向涡流可以与尾翼和尾翼相互作用，并导致流引起的振动。近年来，人们对飞机模型的各种附件以及简单的三角翼飞机模型的涡流冲击进行了许多研究。无论飞机的几何细节如何，破裂涡流与下游附件的相互作用预计都会表现出某些通用特征。本研究的目的是将入射在翅片上的涡流破裂的整体平均和瞬时结构与沿翅片的表面压力谱联系起来。高图像密度粒子图像测速 (PIV) 用于确定速度场和涡度分布，进而对压力谱进行物理解释。瞬时和平均速度场的各种组合，结合涡度涨落的均方根表示，为相应的压力谱提供了合理的基础，压力谱是在翅片表面的关键位置测量的。三角翼翅片系统安装在水道中的倒置位置，使翼片处于负迎角，以便于 激光诊断。在从三角翼后缘到翅片前缘的两个不同距离处获得瞬时速度场和表面压力测量值。机翼的这种倒置位置允许采集视场上速度的瞬时图像。破碎涡流对具有后掠前缘的翅片的冲击产生与在翅片表面上延伸的大规模分离区相关的复杂流动结构。本文的重点是建立入射到翅片上的破碎涡流的瞬时速度和涡度场与沿翅片前缘区域引起的表面压力脉动之间的关系。该流动的主要特征和相关的压力波动如下： 少

项目成果

S.Okamoto: "Visualization of Impingement of Broken-Down Vortex on Tail"Proceeding of the Fifth Asia-Pacific Conference on Wind Engineering, APCWE V, Kyoto, Japan, October 21-24, 2001. 137-140 (2001)

S.Okamoto：“尾部破碎涡流冲击的可视化”第五届亚太风工程会议记录，APCWE V，日本京都，2001 年 10 月 21-24 日。137-140 (2001)

S.Okamoto: "Visualization Study of Vortex Breakdown-Fin Interaction Using PIV and Pressure Measurement"Proceedings of 23rd International Symposium on Space Technology and Science, 23rd ISTS, Matsue. Paper No.2002-e-17. 365-370 (2002)

S.Okamoto：“利用 PIV 和压力测量对涡流击穿-翅片相互作用的可视化研究”第 23 届国际空间技术与科学研讨会论文集，第 23 届 ISTS，松江。

板野青畝: "OpenGLによる数値シミュレーション情報の可視化"第9回計測自動制御学会中国支部学術講演会論文集. 266-267 (2000)

Aoune Itano：《利用OpenGL实现数值模拟信息的可视化》中国仪器仪表学会分会第九届学术会议论文集266-267（2000）。

Satoru Okamoto: "Visualization of Impingement of Broken-Down Vortex on Tail"Proceedings of The Fifth Asia-Pacific Conference on Wind Engineering. (2001)

Satoru Okamoto：“尾部破碎涡冲击的可视化”第五届亚太风工程会议论文集。

S,Okamoto.: "Flow Visualization and Pressure Distribution over a Fin Undergoing Vortex-Breakdown Interaction, CD-ROM Proceedings of 10^<th> International Symposium on Flow Visualization"ISFV10, Kyoto, Japan, Paper. No.F0010. August 26-29 (2002)

S，Okamoto.：“翅片经历涡流击穿相互作用的流动可视化和压力分布，第 10 届国际流动可视化研讨会 CD-ROM 会议记录”ISFV10，日本京都，论文。