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Prikladnaya Mekhanika i Tekhnicheskaya Fizika, 2008, Volume 49, Issue 2, Pages 40–46
(Mi pmtf1881)
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This article is cited in 4 scientific papers (total in 4 papers)
Evolution of disturbances in a laminarized supersonic boundary layer on a swept wing
N. V. Semenov, Yu. G. Ermolaev, A. D. Kosinov Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk, 630090
Abstract:
Experimental data on stability of a three-dimensional supersonic boundary layer on a swept wing are presented. The experiments are performed on a swept wing model with a lenticular profile with a 40$^\circ$ sweep angle of the leading edge at a zero angle of attack. The supersonic boundary layer on the swept wing was laminarized with the use of distributed roughness. A pioneering study of interaction of traveling and stationary disturbances is performed. Some specific features of this interaction are identified. The main reason for turbulence emergence in a supersonic boundary layer on a swept wing is demonstrated to be secondary crossflow instability.
Keywords:
supersonic boundary layer, swept wing, transition, stationary disturbances, stability.
Received: 18.05.2007
Citation:
N. V. Semenov, Yu. G. Ermolaev, A. D. Kosinov, “Evolution of disturbances in a laminarized supersonic boundary layer on a swept wing”, Prikl. Mekh. Tekh. Fiz., 49:2 (2008), 40–46; J. Appl. Mech. Tech. Phys., 49:2 (2008), 188–193
Linking options:
https://www.mathnet.ru/eng/pmtf1881 https://www.mathnet.ru/eng/pmtf/v49/i2/p40
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Abstract page: | 21 | Full-text PDF : | 10 |
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