Experimental study of the laminar-turbulent transition on a blunt cone

E. A. Aleksandrova, A. V. Novikov, S. V. Utyuzhnikov, A. V. Fedorov

Research output: Contribution to journalArticlepeer-review

17 Citations (Scopus)


Results of an experimental study of the laminar-turbulent transition in a hypersonic flow around cones with different bluntness radii at a zero angle of attack, free-stream Mach number M = 6, and unit Reynolds number in the interval Re∞,1 = 5.79 · 106-5.66 · 107 m-1 are presented. Flow regimes in which a reverse of the laminar-turbulent transition (decrease in the length of the laminar segment with increasing bluntness radius) are studied. Heat flux distributions over the model surface are obtained with the use of temperature-sensitive paints. Lines of the beginning of the transition in the boundary layer are analyzed by using heat flux fields. The critical Reynolds number Re∞,R ≈ 1.3 · 105 beginning from which the laminar-turbulent transition substantially depends on uncontrolled disturbances, such as the model tip roughness, is found. In supercritical regimes, the line of the transition beginning is shifted in most cases toward the model tip (reverse of the transition). The results obtained are compared with available experimental data.

Original languageEnglish
Pages (from-to)375-385
Number of pages11
JournalJournal of Applied Mechanics and Technical Physics
Issue number3
Publication statusPublished - Jun 2014
Externally publishedYes


  • "blunt body paradox" experiment
  • blunt cone
  • hypersonic flows
  • laminar-turbulent transition
  • reverse of the laminar-turbulent transition


Dive into the research topics of 'Experimental study of the laminar-turbulent transition on a blunt cone'. Together they form a unique fingerprint.

Cite this