...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of Aircraft >Analysis of the Transonic Flow Around a Unmanned Combat Aerial Vehicle Configuration
【24h】

Analysis of the Transonic Flow Around a Unmanned Combat Aerial Vehicle Configuration

机译：无人战斗机周围声速流分析

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 present investigation has been carried out as part of the North Atlantic Treaty Organization/Science and Technology Organization Applied Vehicle Technology 201 Task Group on extended assessment of reliable stability and control prediction methods for North Atlantic Treaty Organization air vehicles. The stability and control configuration is considered. Its geometry as well as the low-speed aerodynamics and the corresponding flow physics are well known from the literature: For medium angles of attack, the flow around the leading edge is governed by three sections: namely, an apex vortex in the front part, a region of attached flow in the middle portion, and a tip vortex in the outer part of the leading edge. The size of these regions varies with the angle of attack. In the present study, the compressible flow around this configuration has been calculated using the computational fluid dynamics DLR TAU code in the Mach number range of 0.55 = M-infinity = 0.85 and angles of attack of 0 deg = alpha = 16 deg for a constant Reynolds number of Re-infinity = 23 x 10(6) corresponding to the cruise condition of the unmanned combat aerial vehicle. With an increasing Mach number, the flow in the central region of the leading edge becomes supersonic and the upstream movement of the tip vortex with an increasing angle of attack is hindered. However, at the rear end of the supersonic zone, shock-induced separation takes place, forming an additional vortex. This shock-induced vortex joins the tip vortex. Thus, the onset of the tip vortex would move upstream again, with an increasing angle of attack passing the rear end of the supersonic zone. The corresponding, very complex vortex formation is analyzed by means of the Mach number and angle-of-attack variation. The effects of these flow phenomena on the aerodynamic characteristics are demonstrated.
机译：本调查是作为北大西洋公约组织/科学技术组织应用车辆技术201任务组的一部分进行的，该任务组对北大西洋公约组织飞行器的可靠稳定性和控制预测方法的扩展评估进行了评估。考虑稳定性和控制配置。它的几何形状以及低速空气动力学特性和相应的流动物理学在文献中是众所周知的：对于中等迎角，围绕前缘的流动由三个部分控制：即，前部的顶点涡旋，在中间部分有一个附加的流动区域，在前缘的外部有一个尖端涡旋。这些区域的大小随攻角而变化。在本研究中，已经使用计算流体力学DLR TAU代码在0.55 <= M-infinity <= 0.85的马赫数范围和0度<= alpha <= 16的迎角范围内计算了围绕此配置的可压缩流恒定的雷诺数Re-infinity = 23 x 10（6）的deg对应于无人作战飞机的巡航条件。随着马赫数的增加，前缘中心区域中的流动变得超音速，并且随着涡旋角的增加，尖端涡流的上游运动受到阻碍。但是，在超音速区域的后端，发生了激振引起的分离，形成了另一个涡流。这种由冲击引起的涡旋与尖端涡旋相连。因此，尖端涡旋的开始将再次向上游移动，其中增加的攻角通过超音速区的后端。通过马赫数和攻角变化来分析相应的，非常复杂的涡旋形成。这些流动现象对空气动力学特性的影响得到了证明。

著录项

  • 来源
    《Journal of Aircraft》 |2018年第2期|571-586|共16页
  • 作者

    Zimper Dirk; Hummel Dietrich;

  • 作者单位

    German Aerosp Ctr DLR, Program Coordinat Def & Secur Res, D-51147 Cologne, Germany;

    Braunschweig Univ Technol, Inst Fluid Mech, D-38108 Braunschweig, Germany;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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