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.

层流边界层与翼型表面分离后，流动可以作为湍流剪切层重新附着到表面。层流分离和重新附着之间的这个区域称为层流分离泡。当机翼失速时，发生层流分离气泡破裂。翼型的失速特性很大程度上取决于层流分离气泡。还已知在失速附近的层流分离气泡内部观察到低频振荡。本研究的目的是研究层流分离气泡的破裂并构建抑制翼型失速的方法。为此，进行了以下研究项目：首先扩展对层流分离气泡非定常流动行为的认识，其次确认爆裂抑制装置对翼型的影响，最后通过以下方法控制翼型周围的流动：利用智能结构装置控制翼型失速本研究的结论如下：1）揭示了失速附近层流分离气泡的非定常性质。2）爆破抑制控制板成功应用于翼型失速控制中。 3)采用智能结构装置进行失速抑制。使用该装置观察到了一些好处。4) 还研究了在具有与普通翼型不同的横截面的弧形板翼上形成的层流分离气泡的行为。