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Experimental study on the PRE-X vehicle focusing on the transitional shock-wave/boundary-layer interactions

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Title: Experimental study on the PRE-X vehicle focusing on the transitional shock-wave/boundary-layer interactions
Authors: Bur, R. Reynald.Bur@onera.fr, Chanetz, B.
Source: Aerospace Science & Technology. Oct2009, Vol. 13 Issue 7, p393-401. 9p.
Subjects: Micro air vehicles, Shock waves, Boundary layer control, Reynolds number, Thermography, Aerodynamics
Abstract: Abstract: This article is devoted to the experimental works carried out in the R2Ch blow-down wind tunnel in the framework of the atmospheric re-entry PRE-X demonstrator program and to the fundamental studies performed on a hollow cylinder-flare relative to crucial problem of the transitional shock-wave/boundary-layer interaction. Shock-wave/boundary-layer interactions in hypersonic flows may have major consequences on thermal loads, especially if the shock is strong enough to induce separation. The heat-flux density levels in the interaction region strongly depend on the nature, laminar or turbulent of the boundary-layer. Special attention should be paid to transitional interactions, which are likely to exist at altitude where the Mach number is high and the density low. The wide Reynolds number range achievable in the R2Ch facility and reliable heat-flux measurements by infrared thermography have allowed to investigate the viscous interaction on the deflected flaps of the demonstrator model and to point out the laminar-to-turbulent boundary-layer natural and forced transition, in the light of the in-depth analysis of results obtained from the hollow cylinder-flare study. [Copyright &y& Elsevier]
Copyright of Aerospace Science & Technology is the property of Elsevier B.V. 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.)
Database: Engineering Source
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DbLabel: Engineering Source
An: 45071751
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
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  Data: Experimental study on the PRE-X vehicle focusing on the transitional shock-wave/boundary-layer interactions
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  Data: <searchLink fieldCode="AR" term="%22Bur%2C+R%2E%22">Bur, R.</searchLink><i> Reynald.Bur@onera.fr</i><br /><searchLink fieldCode="AR" term="%22Chanetz%2C+B%2E%22">Chanetz, B.</searchLink>
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  Data: <searchLink fieldCode="JN" term="%22Aerospace+Science+%26+Technology%22">Aerospace Science & Technology</searchLink>. Oct2009, Vol. 13 Issue 7, p393-401. 9p.
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  Data: <searchLink fieldCode="DE" term="%22Micro+air+vehicles%22">Micro air vehicles</searchLink><br /><searchLink fieldCode="DE" term="%22Shock+waves%22">Shock waves</searchLink><br /><searchLink fieldCode="DE" term="%22Boundary+layer+control%22">Boundary layer control</searchLink><br /><searchLink fieldCode="DE" term="%22Reynolds+number%22">Reynolds number</searchLink><br /><searchLink fieldCode="DE" term="%22Thermography%22">Thermography</searchLink><br /><searchLink fieldCode="DE" term="%22Aerodynamics%22">Aerodynamics</searchLink>
– Name: Abstract
  Label: Abstract
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  Data: Abstract: This article is devoted to the experimental works carried out in the R2Ch blow-down wind tunnel in the framework of the atmospheric re-entry PRE-X demonstrator program and to the fundamental studies performed on a hollow cylinder-flare relative to crucial problem of the transitional shock-wave/boundary-layer interaction. Shock-wave/boundary-layer interactions in hypersonic flows may have major consequences on thermal loads, especially if the shock is strong enough to induce separation. The heat-flux density levels in the interaction region strongly depend on the nature, laminar or turbulent of the boundary-layer. Special attention should be paid to transitional interactions, which are likely to exist at altitude where the Mach number is high and the density low. The wide Reynolds number range achievable in the R2Ch facility and reliable heat-flux measurements by infrared thermography have allowed to investigate the viscous interaction on the deflected flaps of the demonstrator model and to point out the laminar-to-turbulent boundary-layer natural and forced transition, in the light of the in-depth analysis of results obtained from the hollow cylinder-flare study. [Copyright &y& Elsevier]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Aerospace Science & Technology is the property of Elsevier B.V. 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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      – Type: doi
        Value: 10.1016/j.ast.2009.09.002
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      – Code: eng
        Text: English
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        PageCount: 9
        StartPage: 393
    Subjects:
      – SubjectFull: Micro air vehicles
        Type: general
      – SubjectFull: Shock waves
        Type: general
      – SubjectFull: Boundary layer control
        Type: general
      – SubjectFull: Reynolds number
        Type: general
      – SubjectFull: Thermography
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      – SubjectFull: Aerodynamics
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              Text: Oct2009
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              Y: 2009
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