...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>The Aeronautical Journal >Shock-tunnel investigations on the evolution and morphology of shock-induced large separation bubbles
【24h】

Shock-tunnel investigations on the evolution and morphology of shock-induced large separation bubbles

机译：激波隧道研究激波诱发大分离气泡的演化和形态

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

Shock-tunnel experiments are carried out to study the strong interaction between an impinging shock wave and boundary layer on a flat plate, accompanied by large separation bubble with a length comparable to the distance of the location of shock impingement from the leading edge of the plate. For nominal freestream Mach numbers ranging from 6 to 8.5, moderate to high total enthalpies of 1.3 MJ/kg to 6 MJ/kg are simulated in the Indian Institute of Science's hypersonic shock tunnels HST-2 (a conventional Hypersonic Shock Tunnel) and Free Piston Shock Tunnel (FPST) with freestream Reynolds numbers ranging from 4 x 10(6)/m to 0.3 x 10(6)/m. The strong impinging shock is generated by a wedge (or shock generator) at an angle of 30.96 degrees to the freestream. From the time-resolved Schlieren flow visualisations using a high-speed camera and surface pressure measurements on the flat plate using fast response sensors, a statistically steady flow field with a large separation bubble was established within the short test time of the shock tunnels (around 600 mu s in HST-2 and 300 mu s in FPST). The role of various parameters on the interaction - Mach number, location of shock impingement and flow total enthalpy - are investigated from the measured separation length and surface pressure distribution. For the nominal Mach number of 8.5, with shock impingement at 100 mm from the leading edge, the separation length increased from 60 mm to 70 mm as the total enthalpy is increased from 1.6 MJ/kg to 2.4 MJ/kg; whereas it dropped drastically to 30-40 mm at 6 MJ/kg. This is due to the prominence of real gas effects at higher enthalpies.
机译：进行了冲击隧道实验，以研究冲击冲击波与平板边界层之间的强相互作用，并伴随着较大的分离气泡，气泡的长度与冲击冲击位置到板前缘的距离相当。对于名义自由流马赫数（范围从6到8.5），在印度科学院的高超声速冲击隧道HST-2（常规的高超声速冲击隧道）和自由活塞中模拟了1.3 MJ / kg至6 MJ / kg的中高总焓。冲击隧道（FPST），雷诺数为4 x 10（6）/ m至0.3 x 10（6）/ m。强烈的撞击是由楔形件（或撞击产生器）与自由流成30.96度角产生的。通过使用高速摄像机进行时间分辨的Schlieren流量可视化以及使用快速响应传感器在平板上进行表面压力测量，可以在冲击通道的短测试时间内（大约）建立具有大分离气泡的统计稳定流场。在HST-2中为600 s，在FPST中为300 s）。从测得的分离长度和表面压力分布研究了各种参数对相互作用的作用-马赫数，冲击力的位置和流动总焓-。对于标称马赫数8.5，在距前缘100 mm处有冲击力的情况下，随着总焓从1.6 MJ / kg增加到2.4 MJ / kg，分离长度从60 mm增加到70 mm。而以6 MJ / kg的速度急剧下降至30-40 mm。这是由于在较高的焓下突出了实际气体效应。

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