Thermophysics and Aeromechanics

, Volume 25, Issue 5, pp 659–665 | Cite as

Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow

  • Yu. G. Ermolaev
  • A. D. Kosinov
  • A. N. Semenov
  • N. V. SemionovEmail author
  • A. A. Yatskikh


An experimental study of the influence of unit Reynolds number on the position of laminar-turbulent transition in swept-wing boundary layer at supersonic flow velocities was carried out. In the experiments, a swept-wing model with 3-% circular arc airfoil and 45-deg gliding angle of wing edges was used. The position of the transition was iden-tified using a hot-wire anemometer. It was found that at М = 2 and 2.5, an increase in the unit Reynolds number (Re1) leads to a transition delay. It was shown that an increase in freestream Mach number and in the level of flow pulsations in the wind-tunnel test section leads to a less pronounced influence of Re1 on the transition position. At a high noise level due to the growth of Mach number or due to the introduction of vortical disturbances, no effect due to unit Reyn-olds number on the transition position was observed.

Key words

supersonic boundary layer swept wing laminar-turbulent transition unit Reynolds number 


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Copyright information

© Kutateladze Institute of Thermophysics, Siberian Branch of the Russian Academy of Sciences 2018

Authors and Affiliations

  • Yu. G. Ermolaev
    • 1
  • A. D. Kosinov
    • 1
    • 2
  • A. N. Semenov
    • 1
    • 3
  • N. V. Semionov
    • 1
  • A. A. Yatskikh
    • 1
    • 2
  1. 1.Khristianovich Institute of Theoretical and Applied Mechanics SB RASNovosibirskRussia
  2. 2.Novosibirsk State UniversityNovosibirskRussia
  3. 3.Sobolev Institute of Geology and Mineralogy SB RASNovosibirskRussia

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