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Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness

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Abstract—

The effect of the entropy layer generated by a small bluntness of the leading edge of a flat plate on laminar-turbulent transition of the supersonic boundary layer in the wake of an isolated roughness element (straight cylinder, 1 mm in diameter and 1 mm in height) situated on the plate surface is experimentally investigated. The bluntness radius varies. The experiments are performed at the Mach number 6 in the Reynolds number range (0.46–2.33) × 106, where the Reynolds number is based on the roughness location and the oncoming flow parameters. The reversal behavior of the roughness-induced turbulent wedges with increase in the bluntness is first revealed.

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ACKNOWLEDGMENTS

The author wishes to thank V. N. Radchenko for assistance in performing the experiments and in the primary data processing.

Funding

The study was supported by the Russian Science Foundation, project no. 17-79-10433.

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Authors and Affiliations

  1. Central Aerohydrodynamic Institute (TsAGI), 140180, Zhukovsky, Moscow oblast, Russia

    P. V. Chuvakhov

  2. Moscow Institute of Physics and Technology (MIPT), 141701, Dolgoprudny, Moscow oblast, Russia

    P. V. Chuvakhov

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Correspondence to P. V. Chuvakhov.

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Chuvakhov, P.V. Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness. Fluid Dyn 55, 62–73 (2020). https://doi.org/10.1134/S0015462820010048

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  • DOI: https://doi.org/10.1134/S0015462820010048

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