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PIV study on a shock-induced separation in a transonic flow.

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Title: PIV study on a shock-induced separation in a transonic flow.
Authors: Sartor, Fulvio1 fulvio.sartor@onera.fr, Losfeld, Gilles1 reynald.bur@onera.fr, Bur, Reynald1 reynald.bur@onera.fr
Source: Experiments in Fluids. Sep2012, Vol. 53 Issue 3, p815-827. 13p.
Subjects: Particle image velocimetry, Shock waves, Boundary layer (Aerodynamics), Transonic aerodynamics, Fluids
Abstract: A transonic interaction between a steady shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally investigated by means of particle image velocimetry (PIV). In the test section, the lower wall is equipped with a contour profile shaped as a bump allowing flow separation. The transonic interaction, characterized by the existence in the outer flow of a lambda shock pattern, causes the separation of the boundary layer, and a low-speed recirculating bubble is observed downstream of the shock foot. Two-component PIV velocity measurements have been performed using an iterative gradient-based cross-correlation algorithm, providing high-speed and flexible calculations, instead of the classic multi-pass processing with FFT-based cross-correlation. The experiments are performed discussing all the hypotheses linked to the experimental set-up and the technique of investigation such as the two-dimensionality assumption of the flow, the particle response assessment, the seeding system, and the PIV correlation uncertainty. Mean velocity fields are presented for the whole interaction with particular attention for the recirculating bubble downstream of the detachment, especially in the mixing layer zone where the effects of the shear stress are most relevant. Turbulence is discussed in details, the results are compared to previous study, and new results are given for the turbulent production term and the return to isotropy mechanism. Finally, using different camera lens, a zoom in the vicinity of the wall presents mean and turbulent velocity fields for the incoming boundary layer. [ABSTRACT FROM AUTHOR]
Copyright of Experiments in Fluids 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: PIV study on a shock-induced separation in a transonic flow.
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  Data: <searchLink fieldCode="AR" term="%22Sartor%2C+Fulvio%22">Sartor, Fulvio</searchLink><relatesTo>1</relatesTo><i> fulvio.sartor@onera.fr</i><br /><searchLink fieldCode="AR" term="%22Losfeld%2C+Gilles%22">Losfeld, Gilles</searchLink><relatesTo>1</relatesTo><i> reynald.bur@onera.fr</i><br /><searchLink fieldCode="AR" term="%22Bur%2C+Reynald%22">Bur, Reynald</searchLink><relatesTo>1</relatesTo><i> reynald.bur@onera.fr</i>
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  Data: <searchLink fieldCode="JN" term="%22Experiments+in+Fluids%22">Experiments in Fluids</searchLink>. Sep2012, Vol. 53 Issue 3, p815-827. 13p.
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  Data: <searchLink fieldCode="DE" term="%22Particle+image+velocimetry%22">Particle image velocimetry</searchLink><br /><searchLink fieldCode="DE" term="%22Shock+waves%22">Shock waves</searchLink><br /><searchLink fieldCode="DE" term="%22Boundary+layer+%28Aerodynamics%29%22">Boundary layer (Aerodynamics)</searchLink><br /><searchLink fieldCode="DE" term="%22Transonic+aerodynamics%22">Transonic aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Fluids%22">Fluids</searchLink>
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  Data: A transonic interaction between a steady shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally investigated by means of particle image velocimetry (PIV). In the test section, the lower wall is equipped with a contour profile shaped as a bump allowing flow separation. The transonic interaction, characterized by the existence in the outer flow of a lambda shock pattern, causes the separation of the boundary layer, and a low-speed recirculating bubble is observed downstream of the shock foot. Two-component PIV velocity measurements have been performed using an iterative gradient-based cross-correlation algorithm, providing high-speed and flexible calculations, instead of the classic multi-pass processing with FFT-based cross-correlation. The experiments are performed discussing all the hypotheses linked to the experimental set-up and the technique of investigation such as the two-dimensionality assumption of the flow, the particle response assessment, the seeding system, and the PIV correlation uncertainty. Mean velocity fields are presented for the whole interaction with particular attention for the recirculating bubble downstream of the detachment, especially in the mixing layer zone where the effects of the shear stress are most relevant. Turbulence is discussed in details, the results are compared to previous study, and new results are given for the turbulent production term and the return to isotropy mechanism. Finally, using different camera lens, a zoom in the vicinity of the wall presents mean and turbulent velocity fields for the incoming boundary layer. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Experiments in Fluids 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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        Value: 10.1007/s00348-012-1330-4
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      – Code: eng
        Text: English
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        PageCount: 13
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      – SubjectFull: Particle image velocimetry
        Type: general
      – SubjectFull: Shock waves
        Type: general
      – SubjectFull: Boundary layer (Aerodynamics)
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      – SubjectFull: Transonic aerodynamics
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      – SubjectFull: Fluids
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              M: 09
              Text: Sep2012
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