Open AccessAn effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2
Author(s) -
Н. В. Семёнов,
Yu. G. Yermolaev,
V. L. Kocharin,
А. Д. Косинов,
A. N. Semenov,
B. V. Smorodsky,
A. A. Yatskikh
Publication year - 2018
Publication title -
aip conference proceedings
Language(s) - English
Resource type - Conference proceedings
SCImago Journal Rank - 0.177
H-Index - 75
eISSN - 1551-7616
pISSN - 0094-243X
DOI - 10.1063/1.5065250
Subject(s) - angle of attack , mach number , swept wing , supersonic speed , wing , airfoil , reynolds number , boundary layer , wind tunnel , mechanics , physics , laminar flow , laminar turbulent transition , delta wing , turbulence , aerodynamics , geometry , mathematics , thermodynamics
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