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Effect of Distributed Suction on the Development of Disturbances on the Wing Profile. / Grek, G. R.; Katasonov, M. M.; Kozlov, V. V. и др.
в: Doklady Physics, Том 65, № 4, 01.04.2020, стр. 157-160.Результаты исследований: Научные публикации в периодических изданиях › статья › Рецензирование
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TY - JOUR
T1 - Effect of Distributed Suction on the Development of Disturbances on the Wing Profile
AU - Grek, G. R.
AU - Katasonov, M. M.
AU - Kozlov, V. V.
AU - Kornilov, V. I.
N1 - Publisher Copyright: © 2020, Pleiades Publishing, Ltd. Copyright: Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2020/4/1
Y1 - 2020/4/1
N2 - The results of experimental investigations of the effect of distributed suction through a perforated section of a symmetric wing profile on the spatial development of disturbances in the boundary layer are presented. It is shown that this method of control makes it possible to reduce by ten times the intensity of natural pulsations of the boundary-layer velocity, while the disturbance intensity decreases by about 20 times, when an acoustic field is applied at the subharmonic frequency of the fundamental wave. The suction also significantly affects the mean flow up to eliminating the separation of the boundary layer near the trailing edge of the wing instead of contributing only a decrease in the intensity of high-frequency pulsations for natural and forced disturbances.
AB - The results of experimental investigations of the effect of distributed suction through a perforated section of a symmetric wing profile on the spatial development of disturbances in the boundary layer are presented. It is shown that this method of control makes it possible to reduce by ten times the intensity of natural pulsations of the boundary-layer velocity, while the disturbance intensity decreases by about 20 times, when an acoustic field is applied at the subharmonic frequency of the fundamental wave. The suction also significantly affects the mean flow up to eliminating the separation of the boundary layer near the trailing edge of the wing instead of contributing only a decrease in the intensity of high-frequency pulsations for natural and forced disturbances.
KW - boundary layer
KW - distributed suction
KW - disturbance spectrum
KW - linear stability
UR - http://www.scopus.com/inward/record.url?scp=85087973527&partnerID=8YFLogxK
U2 - 10.1134/S1028335820040059
DO - 10.1134/S1028335820040059
M3 - Article
AN - SCOPUS:85087973527
VL - 65
SP - 157
EP - 160
JO - Doklady Physics
JF - Doklady Physics
SN - 1028-3358
IS - 4
ER -
ID: 24782667