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Visualization of Supersonic Low-Noise Flow Over Surface-Mounted Two-Dimensional Prisms.

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Titel: Visualization of Supersonic Low-Noise Flow Over Surface-Mounted Two-Dimensional Prisms.
Autoren: Liu, Xiaolin, Yi, Sihe, Gang, Dundian, Lu, Xiaoge
Quelle: Fluid Dynamics; Jan2018, Vol. 53 Issue 1, p169-175, 7p, 5 Diagrams, 1 Chart, 8 Graphs
Abstract: An experimental study of supersonic flow over two-dimensional surface-mounted prisms is carried out in a Mach 3 low-noise wind tunnel. The noise level of this supersonic wind tunnel, defined as the root mean-square Pitot pressure fluctuation normalized by the mean Pitot pressure, can be reduced to about 0.37%. The nanotracer planar laser scattering (NPLS) technique is used to analyze the influence of the prism geometry and the oncoming flow conditions on the typical flow structures including separation and reattachment shocks. With increase in the prism height the induced shocks move upstream. At a constant streamwise length L of a prism the timeaveraged NPLS images show that the length of the downstream recirculation region increases from 0.8L to 1.2L, when the prism height H changes from 3 to 5 mm. As compared with the flow structures occurring downstream of the prisms, the upstream flow structures are more susceptible to the oncoming boundary layer and are considerably different in laminar and turbulent flows. The separation shock wave is clearly visible in turbulent flow even for the 1-mm prism, whereas in the case of laminar flow there is no a distinct shock wave upstream of this prism. At the same time, the location of the flow reattachment and the angle of the reattachment shock wave in the downstream flow remain almost the same in both two flow regimes. [ABSTRACT FROM AUTHOR]
Copyright of Fluid Dynamics is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
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  Data: Visualization of Supersonic Low-Noise Flow Over Surface-Mounted Two-Dimensional Prisms.
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  Data: <searchLink fieldCode="AR" term="%22Liu%2C+Xiaolin%22">Liu, Xiaolin</searchLink><br /><searchLink fieldCode="AR" term="%22Yi%2C+Sihe%22">Yi, Sihe</searchLink><br /><searchLink fieldCode="AR" term="%22Gang%2C+Dundian%22">Gang, Dundian</searchLink><br /><searchLink fieldCode="AR" term="%22Lu%2C+Xiaoge%22">Lu, Xiaoge</searchLink>
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  Data: Fluid Dynamics; Jan2018, Vol. 53 Issue 1, p169-175, 7p, 5 Diagrams, 1 Chart, 8 Graphs
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: An experimental study of supersonic flow over two-dimensional surface-mounted prisms is carried out in a Mach 3 low-noise wind tunnel. The noise level of this supersonic wind tunnel, defined as the root mean-square Pitot pressure fluctuation normalized by the mean Pitot pressure, can be reduced to about 0.37%. The nanotracer planar laser scattering (NPLS) technique is used to analyze the influence of the prism geometry and the oncoming flow conditions on the typical flow structures including separation and reattachment shocks. With increase in the prism height the induced shocks move upstream. At a constant streamwise length L of a prism the timeaveraged NPLS images show that the length of the downstream recirculation region increases from 0.8L to 1.2L, when the prism height H changes from 3 to 5 mm. As compared with the flow structures occurring downstream of the prisms, the upstream flow structures are more susceptible to the oncoming boundary layer and are considerably different in laminar and turbulent flows. The separation shock wave is clearly visible in turbulent flow even for the 1-mm prism, whereas in the case of laminar flow there is no a distinct shock wave upstream of this prism. At the same time, the location of the flow reattachment and the angle of the reattachment shock wave in the downstream flow remain almost the same in both two flow regimes. [ABSTRACT FROM AUTHOR]
– Name: Abstract
  Label:
  Group: Ab
  Data: <i>Copyright of Fluid Dynamics is the property of Springer Nature and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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RecordInfo BibRecord:
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      – Type: doi
        Value: 10.1134/S0015462818010172
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        Text: English
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            NameFull: Liu, Xiaolin
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            NameFull: Yi, Sihe
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            NameFull: Gang, Dundian
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              Text: Jan2018
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              Y: 2018
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