Research on Airfoil Stall Suppression Control by Use of a Smart-structure Device

智能结构装置机翼失速抑制控制研究

基本信息

批准号：
17360406
负责人：
RINOIE Kenichi
金额：
$ 7.62万
依托单位：
The University of Tokyo
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
2005
资助国家：
日本
起止时间：
2005 至 2007
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-17360406/
关键词：
Airfoil Stal Laminar Separation Bubble Stall Control Smart-structure Device

项目摘要

After the laminar boundary layer separates from the airfoil surface, the flow can reattach to the surface as a turbulent shear layer. This region between the laminar separation and the reattachment is called a laminar separation bubble. When the airfoil stalls, the laminar separation bubble burst occurs. The stall characteristics of the airfoil are strongly dependent upon the laminar separation bubble. It is also known that a low frequency oscillation is observed inside the laminar separation bubble near stallThe purpose of this research is to investigate the laminar separation bubble burst and to construct a method to suppress the airfoil stall. For this purpose, the following research items were investigated, firstly to extend the knowledge on an unsteady flow behavior of the laminar separation bubble, secondly to confirm the effect of burst suppression device on the airfoil, and finally to control the flow around the airfoil by use of a smart-structure device to control the airfoil stallThe conclusions of the present research are as follows.1) It was revealed the unsteady nature of the laminar separation bubble near stall.2) Burst suppression control plate was successfully applied for the airfoil to control the airfoil stall.3) Smart-structure device was also applied for the stall suppression. Some benefit was observed by use of this device.4) The behavior of the laminar separation bubble formed on a cambered plate wing, that has a different cross section compared with an ordinary airfoil, was also investigated.

层流边界层与机翼表面分离后，流动可以作为湍流剪切层重新触及表面。层间分离和重新介绍之间的该区域称为层流分离气泡。当机翼摊位时，会发生层状分离气泡爆发。机翼的失速特性在很大程度上取决于层流分离气泡。众所周知，在失速附近的层流分离气泡内观察到低频振荡，这项研究的目的是研究层流分离气泡爆发，并构建一种抑制机翼失速的方法。为此，研究了以下研究项目，首先是为了扩展层状分离气泡的不稳定流动行为的知识，其次是确认爆发抑制装置对机翼的影响，最后是通过使用智能结构设备来控制机翼周围的流动，通过使用智能构造装置来控制air的结论。 2）成功地应用了爆发抑制控制板，以控制机翼以控制机翼失速。3）智能结构设备也用于摊位抑制。通过使用该设备可以观察到一些好处。4）还研究了与普通机翼相比，在凹形板机翼上形成的层分离气泡的行为。