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Prikladnaya Mekhanika i Tekhnicheskaya Fizika, 2003, Volume 44, Issue 2, Pages 72–82
(Mi pmtf2481)
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This article is cited in 7 scientific papers (total in 7 papers)
Stability and transition on a swept cylinder in a supersonic flow
A. I. Semisynova, A. V. Fedorovb, V. E. Novikova, N. V. Semenova, A. D. Kosinova a Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk, 630090
b Moscow Physicotechnical Institute, Zhukovskii, Moscow Region, 140160
Abstract:
Results of experimental investigations of the evolution of natural disturbances and laminar–turbulent transition in a supersonic boundary layer on the attachment line of a circular cylinder with a sweep angle of $68^\circ$ and a free-stream Mach number $\mathrm{M}=2$ are presented. The experimental studies are supplemented by calculations of the mean flow and stability characteristics. Flow regimes in the boundary layer on the attachment line are determined by a hot-wire technique as functions of the Reynolds number and height of two-dimensional roughness elements. The results are compared with NASA (Ames) experiments.
Keywords:
boundary layer, transition, stability, attachment line on a swept wing.
Received: 27.05.2002 Accepted: 14.10.2002
Citation:
A. I. Semisynov, A. V. Fedorov, V. E. Novikov, N. V. Semenov, A. D. Kosinov, “Stability and transition on a swept cylinder in a supersonic flow”, Prikl. Mekh. Tekh. Fiz., 44:2 (2003), 72–82; J. Appl. Mech. Tech. Phys., 44:2 (2003), 212–220
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https://www.mathnet.ru/eng/pmtf2481 https://www.mathnet.ru/eng/pmtf/v44/i2/p72
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