Zobrazeno 1 - 10
of 12
pro vyhledávání: '"S. G. Shevel'kov"'
Autor:
S. G. Shevel'kov, N. V. Semionov, Yu. G. Ermolaev, V. L. Kocharin, Alexander D. Kosinov, O. P. Minin, Aleksey A. Yatskikh, M. V. Piterimova
Publikováno v:
Thermophysics and Aeromechanics. 26:803-809
The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow i
Publikováno v:
Fluid Dynamics. 25:854-858
The development of three-dimensional wave packets artificially introduced into a boundary layer has been experimentally investigated. The measurements were made by the hot-wire anemometer method in the boundary layer on a flat plate at a Mach number
Publikováno v:
Journal of Applied Mechanics and Technical Physics. 33:191-193
Publikováno v:
Journal of Applied Mechanics and Technical Physics. 31:250-252
Publikováno v:
Laminar-Turbulent Transition ISBN: 9783642797675
In the paper theoretical and experimental results of investigation of the linear and nonlinear development of waves in the supersonic boundary layer are given.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3670e34e0f3cd16b8ad26c7ce689b4c3
https://doi.org/10.1007/978-3-642-79765-1_21
https://doi.org/10.1007/978-3-642-79765-1_21
Publikováno v:
Nonlinear Instability of Nonparallel Flows ISBN: 9783642850868
The present paper reports an experimental study of the nonlinear development of spatial wave packets in the boundary layer on a flat plate at Mach 2. It is shown that subharmonic resonance phenomena may take place in the supersonic boundary layer. Th
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a5b655fbb84d2d251746315428d47e27
https://doi.org/10.1007/978-3-642-85084-4_17
https://doi.org/10.1007/978-3-642-85084-4_17
Autor:
Alexander D. Kosinov, S. G. Shevel'kov
Publikováno v:
Separated Flows and Jets ISBN: 9783642844492
Experimental investigation has been carried out of the development of perturbations in separation zone of supersonic boundary layer with laminar flow-around of the model of the cones with varying angle of taper: α/2=5° and 10°. The Mach number of
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::72491e237893e5ca298cd8ac60ea48b1
https://doi.org/10.1007/978-3-642-84447-8_92
https://doi.org/10.1007/978-3-642-84447-8_92
Publikováno v:
Laminar-Turbulent Transition ISBN: 9783642841057
The present paper describes the carried out experimental studies of the supersonic laminar boundary layer stability on the cone-cylinder model. The method of introducing the artificial disturbances into the supersonic flow is used. The wave character
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0546480a86a735def2bb97f97a019e4a
https://doi.org/10.1007/978-3-642-84103-3_20
https://doi.org/10.1007/978-3-642-84103-3_20
Publikováno v:
Journal of Applied Mechanics and Technical Physics. 30:447-451
Autor:
S. G. Shevel'kov, A. A. Maslov
Publikováno v:
Fluid Dynamics. 20:852-855
The effect of the unit Reynolds number and the Mach number on the transition on a slender circular cone is experimentally investigated. The perturbation spectra in the boundary layer on the cone are measured. It is shown that the location of the tran