Stability and Transition on a Swept Cylinder in a Supersonic Flow |
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Authors: | A. I. Semisynov A. V. Fedorov V. E. Novikov N. V. Semionov A. D. Kosinov |
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Affiliation: | (1) Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk, 630090;(2) Moscow Physicotechnical Institute, Zhukovskii, Moscow Region, 140160 |
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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° and a freestream Mach number 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 hotwire technique as functions of the Reynolds number and height of twodimensional roughness elements. The results are compared with NASA (Ames) experiments. |
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Keywords: | boundary layer transition stability attachment line on a swept wing |
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