...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of the American Helicopter Society >Spanwise Differences in Static and Dynamic Stall on a Pitching Rotor Blade Tip Model
【24h】

Spanwise Differences in Static and Dynamic Stall on a Pitching Rotor Blade Tip Model

机译：变桨转子叶尖模型中静态和动态失速的跨度差异

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

An experimental investigation of static and dynamic stall on a rotor blade tip model with an aspect ratio of 6.2 at a chord Reynolds number of 900,000 and a Mach number of 0.16 is presented. The spatiotemporal behavior of the flow separation was analyzed using unsteady surface pressure measurements and high-speed particle image velocimetry. The maximum effective angle of attack prior to stall is shifted to approximately two-thirds of the span outboard because of an increasing geometric angle of attack of the model toward the tip. Different stages of flow separation for static angles of attack were identified, including the occurrence of two stall cells. During dynamic stall, the leading edge vortex formation starts near the spanwise position of the static stall onset. The subsequent spanwise evolution of the vortex formation results in two Omega vortices for deep stall conditions, covering the same spanwise areas as the two static stall cells.
机译：提出了在动叶片雷诺模型上进行静态和动态失速的实验研究，该模型的弦比为900,000，马赫数为0.16，长宽比为6.2。使用非稳态表面压力测量和高速粒子图像测速仪分析了流动分离的时空行为。由于模型朝向尖​​端的几何攻角增加，因此失速之前的最大有效攻角被移至跨度外侧的大约三分之二。确定了静态迎角流动分离的不同阶段，包括两个失速室的发生。在动态失速期间，前沿涡流的形成在静态失速开始的翼展方向位置附近开始。涡旋形成的随后沿展向方向演变导致在深度失速条件下产生两个欧米茄涡流，覆盖了与两个静态失速单元相同的跨展区域。

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