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流以增强可操作性和控制性。在飞机上的各个位置生成的流向涡流可以与鳍和尾部相互作用，并导致流动引起的振动。近年来，对飞机模型的各种附属以及飞机的简单Delta机翼表示，已经进行了许多涡流撞击的研究。破碎的涡流与下游附属物的相互作用有望接纳某些通用特征，而与飞机的几何细节无关。这项研究的目的是将一体散布的和瞬时结构联系起来，并将涡流崩溃的圆锥体发生在鳍片沿鳍上的鳍片上。高图像密度粒子图像速度法（PIV）用于确定速度场和涡度分布，从而导致压力光谱的物理解释。 i…的各种组合……更加含量和平均速度场以及涡流的涡流形式的旋转波动的结合为相应的压力谱提供了合理的基础，这些压力光谱是在FIN的至关重要位置测量的相应压力光谱。激光诊断。瞬时速度场和表面压力测量在与三角洲翼的尾随边缘到鳍的前沿的两个不同距离处获得。机翼的倒置位置允许在视野上获取速度的瞬时图像。在鳍片上破碎的涡流的模板具有扫掠的前沿产生的复杂流动结构，与大规模的分离区域相关联，延伸到鳍片的表面上。本文的重点是建立瞬时速度的瞬时速度和涡轮上涡流的涡流场之间的关系，以及沿鳍片的前沿区域引起的表面压力波动。该流量的主要特征和相关的压力波动如下：较少

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: "Impingement of Broken-Down Vortex on Tail"Proceedings of the 4th Pacific International Conference on Aerospace Science and Technology. 119-122 (2001)

S.Okamoto：“尾部破碎涡流的撞击”第四届太平洋航空​​航天科学技术国际会议论文集。