...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Numerical prediction and wind tunnel experiment for a pitching unmanned combat air vehicle
【24h】

Numerical prediction and wind tunnel experiment for a pitching unmanned combat air vehicle

机译：俯仰无人战斗机的数值预测与风洞实验

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 low-speed flowfield for a generic unmanned combat air vehicle (UCAV) is investigated both experimentally and numerically. A wind tunnel experiment was conducted with the Boeing 1301 UCAV at a variety of angles of attack up to 70 degrees, both statically and with various frequencies of pitch oscillation (0.5, 1.0, and 2.0 Hz). In addition, pitching was performed about three longitudinal locations on the configuration (the nose, 35% MAC, and the tail). Solutions to the unsteady, laminar, compressible Navier-Stokes equations were obtained on an unstructured mesh to match results from the static and dynamic experiments. The computational results are compared with experimental results for both static and pitching cases. Details about the flowfield, including vortex formation and interaction, are shown and discussed, including the non-linear aerodynamic characteristics of the vehicle.
机译：通过实验和数值研究了通用无人战斗机（UCAV）的低速流场。使用波音1301 UCAV在高达70度的各种迎角下进行了风洞实验，无论是静态的还是俯仰振荡的各种频率（0.5、1.0和2.0 Hz）。另外，在构型的三个纵向位置（鼻子，35％MAC和尾巴）上进行俯仰。在非结构化网格上获得了非稳态，层状，可压缩的Navier-Stokes方程的解，以匹配静态和动态实验的结果。计算结果与静态和俯仰情况下的实验结果进行了比较。显示并讨论了有关流场的详细信息，包括涡流的形成和相互作用，包括车辆的非线性空气动力学特性。

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