...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Gust response of rigid and elastically mounted airfoils at a transitional Reynolds number
【24h】

Gust response of rigid and elastically mounted airfoils at a transitional Reynolds number

机译：雷诺数为过渡时刚性和弹性安装的机翼的阵风响应

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

This article explores the evolution of the unsteady flow structure for rigid and elastically mounted NACA0012 airfoils subject to a parallel vortical gust disturbance at a Reynolds number of Re = 150,000 using implicit large-eddy simulation coupled with a structural dynamics model. A Taylor vortex is supplied upstream of the airfoil and shown to be successful at eliciting laminar separation flutter in the elastically mounted system under conditions which normally require an artificial disturbance. Much of the gust-induced moment responsible for flutter excitation is supplied by a two-stage flow transition process on the undersurface of the wing after the gust passes the airfoil. The gust response triggers transition of the separated lower-surface boundary layer into spanwise coherent vortices followed by a laminar separation bubble accompanied by a secondary emergence of flow transition. These events appear to be analogous in some ways to the processes that appear during fully developed flutter but occur over a shorter timescale. Published by Elsevier Masson SAS.
机译：本文使用隐式大涡模拟和结构动力学模型，研究了雷诺数Re = 150,000时受到平行涡旋阵风干扰的刚性和弹性安装的NACA0012机翼的非定常流动结构的演变。在翼型的上游提供了泰勒涡流，泰勒涡流显示出在通常需要人为干扰的条件下成功引发弹性安装系统中的层流分离颤振的效果。阵风经过机翼后，由两级气流过渡过程提供了引起阵风激发的大部分阵风诱发力矩。阵风响应触发了分离的下表面边界层向展向相干涡旋的过渡，随后是层流分离泡，伴随着二次流的出现。这些事件在某些方面似乎类似于在完全发展的颤动期间出现的过程，但发生的时间较短。由Elsevier Masson SAS发布。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号