• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>The Fourth International Conference on Pumps and Fans (4th ICPF) Aug 26-29, 2002 Beijing, China >NUMERICAL ANALYSIS ON WING TIP VORTEX OF RECTANGULAR AIRFOIL AT LOW REYNOLDS NUMBER FLOWS
【24h】

NUMERICAL ANALYSIS ON WING TIP VORTEX OF RECTANGULAR AIRFOIL AT LOW REYNOLDS NUMBER FLOWS

机译：低雷诺数流下矩形翼型翼尖涡旋的数值分析

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

The near-field behaviors of a wing tip vortex flow on the rectangular airfoil have been studied numerically and experimentally. The flow characteristics at low Reynolds numbers are different from high Reynolds number flows due to laminar-separated bubbles and hysteresis loop. In this study, the computational approach using low Reynolds Navier-Stokes equation is calculated, using two different turbulence models: large eddy simulation (LES) - sub-grid scale method and k-ω equation at low Reynolds number flows, respectively. The parameters of mainstream characteristics are indicated with Reynolds number based on chord length Re_c=0.9x10~5 and Mach number M=0.03. The numerical analyses using Cartesian cut-cell method are performed with 8 degree of AOA (angle of attack) on the NACA 64108 airfoil. Comparisons are also made with experimental data, including flow structures and pressure distributions on the suction side of wing and in the near wake.
机译：数值和实验研究了翼型涡流在矩形翼型上的近场行为。由于层流分离的气泡和磁滞回线，低雷诺数下的流动特性不同于高雷诺数下的流动。在这项研究中，使用两种不同的湍流模型，分别计算了使用低雷诺兹Navier-Stokes方程的计算方法：大涡模拟（LES）-子网格比例法和低雷诺数流下的k-ω方程。主流特性的参数由基于弦长Re_c = 0.9x10〜5和马赫数M = 0.03的雷诺数表示。使用笛卡尔切孔法对NACA 64108机翼进行8度AOA（迎角）分析。还与实验数据进行了比较，包括机翼吸力侧和近尾流处的流动结构和压力分布。

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