Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition

S. A. Gaponov; Yu. G. Ermolaev; N. N. Zubkov; A. D. Kosinov; V. I. Lysenko; B. V. Smorodskii; A. A. Yatskikh

doi:10.1134/S0015462817060052

Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition

Authors: Gaponov S.A.¹, Ermolaev Y.G.¹, Zubkov N.N.², Kosinov A.D.¹, Lysenko V.I.¹, Smorodskii B.V.¹, Yatskikh A.A.¹
Affiliations:
1. Khristianovich Institute of Theoretical and Applied Mechanics
2. Bauman Moscow State Technical University
Issue: Vol 52, No 6 (2017)
Pages: 769-776
Section: Article
URL: https://journals.rcsi.science/0015-4628/article/view/155716
DOI: https://doi.org/10.1134/S0015462817060052
ID: 155716

Cite item

Full Text

Open Access
Restricted Access

Access granted
Restricted Access

Subscription Access

Abstract
About the authors
References
Supplementary files
Statistics

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.