Abstract
The effect of distributed tangential injection of heavy SF6 gas into the wall zone of a boundary layer on the supersonic flow stability and laminar-turbulent transition is experimentally and theoretically investigated at the freestream Mach number M∞ = 2. For the first time it is experimentally shown that in the case of this injection laminar-turbulent transition is downstream displaced.
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Original Russian Text © S.A. Gaponov, Yu.G. Ermolaev, N.N. Zubkov, A.D. Kosinov, V.I. Lysenko, B.V. Smorodskii, A.A. Yatskikh, 2017, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2017, No. 6, pp. 61–69.
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Gaponov, S.A., Ermolaev, Y.G., Zubkov, N.N. et al. Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition. Fluid Dyn 52, 769–776 (2017). https://doi.org/10.1134/S0015462817060052
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DOI: https://doi.org/10.1134/S0015462817060052