权益分类	功能权益	普通用户	{{item.name}}会员
{{category.name}}	{{benefitItem.name}}

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.

在层流边界层从翼型表面分离后，流动可以作为湍流剪切层重新附着到翼型表面。在层流分离和再附着之间的这个区域称为层流分离泡。当翼型失速时，层流分离气泡破裂。翼型的失速特性强烈依赖于层流分离泡。本文研究的目的是研究层流分离气泡的破裂，并建立一种抑制翼型失速的方法。为此，本文进行了以下几个方面的研究：一是扩展了对层流分离气泡非定常流动特性的认识；二是验证了爆破抑制装置对翼型的影响；三是利用智能结构装置控制翼型失速，从而控制翼型周围的流动。1)揭示了层流分离泡在失速附近的非定常特性。2)在翼型上成功应用爆燃抑制控制板控制翼型失速。3)采用智能结构装置进行失速抑制。使用这种装置取得了一些效果。4)研究了与普通翼型不同截面的弧形板翼上形成的层流分离气泡的行为。