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EXPERIMENTAL AND NUMERICAL INVESTIGATIONS OF BOUNDARY LAYER TRANSITION ON BLUNTED CONES AT SUPERSONIC FLOW

Volume 40, Issue 3, 2009, pp. 309-319
DOI: 10.1615/TsAGISciJ.v40.i3.30
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ABSTRACT

Presented are the numerical and the experimental results describing laminar/turbulent boundary layer transition on thin blunted cones at freestream Mach numbers of M = 6.1 and 8. Shown is the common influence of cone nose bluntness, semi-angle of cones, and Mach and Reynolds numbers on the boundary layer transition. The present results, concerning the beginning of boundary layer transition, are compared with data obtained previously in wind tunnels at super- and hypersonic flows over the thin blunted cones.

CITED BY
  1. Vaganov A. V., Noev A. Yu., Kashin V. M., Grachikov D. V., Scenarios of laminar-turbulent transition reversal on blunt cone in hypersonic flow, 2027, 2018. Crossref

  2. Chuvakhov P. V., Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness, Fluid Dynamics, 55, 1, 2020. Crossref

  3. Borovoy Volf Y., Radchenko Vladimir N., Aleksandrov Sergey V., Mosharov Vladimir E., Laminar–Turbulent Transition Reversal on a Blunted Plate with Various Leading-Edge Shapes, AIAA Journal, 2021. Crossref

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