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Experimental investigation of wakes behind two-dimensional slender bodies at Mach number six

机译:马赫数为6的二维细长体尾迹的实验研究

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摘要

NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.An experimental investigation has been conducted to determine mean flow properties for both near and far wakes behind several two-dimensional slender bodies at M[...] = 6. Three adiabatic wall models consisting of a flat plate model and two 20 [degree] included angle wedge models (H = .15", H = .3") were tested. The effect of wall temperature on wake properties was examined by cooling the larger of these two wedge models with the internal flow of liquid nitrogen ([...] = .19). Free stream Reynolds numbers were varied from [...] to [...] for each of these four configurations. In the far wake, measurements of total temperature, as determined with hot wire probes, and Pitot and static pressures were used to derive all other mean flow properties. The effect of transition on these far wake data was determined. Near wake flows were laminar for all adiabatic wall tests and at least for the two lowest test Reynolds numbers of the cold wall wedge. Base region flow field mappings and shear layer profiles were obtained for the .3"H wedge model by combining Pitot pressure data with hot wire measurements of total temperature and mass flux. These results illustrated that for slender bodies with flat bases, the basic structure for laminar near wakes is appreciably more complex for hypersonic than for supersonic flow primarily because, in hypersonic flow, the corner expansion fan extends into the separated shear layers and base region shocks now become imbedded within the viscous portion of the shear layers.
机译:注意:用[...]表示无法用纯ASCII呈现的文本或符号。摘要包含在.pdf文件中。已经进行了一项实验研究,以确定在M [= 6]处的几个二维细长体后面的近尾和远尾的平均流动特性。graco.com graco.com测试板模型和两个20度夹角楔形模型(H = .15“,H = .3”)。通过使用液氮的内部流冷却这两个楔形模型中的较大模型,来检查壁温对尾流特性的影响(... = 0.19)。四种配置中的每一种,自由流雷诺数从到变化。不久之后,总温度的测量(由热线探针确定),皮托管和静压被用于得出所有其他平均流量特性。确定了过渡对这些遥远数据的影响。对于所有绝热壁测试,至少对于冷壁楔形的最低两个雷诺数,近尾流都是层流的。通过将皮托压力数据与热线测量的总温度和质量通量相结合,获得了.3“ H楔形模型的基础区域流场映射和剪切层剖面。这些结果说明,对于具有扁平基础的细长物体,其基本结构高超声速的层流近尾流比超声速的流复杂得多,这主要是因为在高超声速流中,转角膨胀风扇延伸到分离的剪切层中,并且基区震动现在被嵌入到剪切层的粘性部分内。

著录项

  • 作者

    Batt Richard George;

  • 作者单位
  • 年度 1967
  • 总页数
  • 原文格式 PDF
  • 正文语种 {"code":"en","name":"English","id":9}
  • 中图分类

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