Результаты исследований: Научные публикации в периодических изданиях › статья по материалам конференции › Рецензирование
Experimental study of the laminar-turbulent transition on models of wings with subsonic and supersonic leading edge at M = 2. / Semionov, N. V.; Yermolaev, Yu G.; Kosinov, A. D. и др.
в: Journal of Physics: Conference Series, Том 1404, № 1, 012097, 06.12.2019.Результаты исследований: Научные публикации в периодических изданиях › статья по материалам конференции › Рецензирование
}
TY - JOUR
T1 - Experimental study of the laminar-turbulent transition on models of wings with subsonic and supersonic leading edge at M = 2
AU - Semionov, N. V.
AU - Yermolaev, Yu G.
AU - Kosinov, A. D.
AU - Kocharin, V. L.
AU - Panina, A. V.
AU - Semenov, A. N.
AU - Shipul, S. A.
AU - Yatskikh, A. A.
N1 - Publisher Copyright: © 2019 IOP Publishing Ltd. Copyright: Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2019/12/6
Y1 - 2019/12/6
N2 - The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings at Mach 2. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models with supersonic or subsonic leading edges. The transition location was determined using a constant temperature hot-wire anemometer. while experiments for the case of a supersonic leading edge are a continuation of previous studies, then for the case of a subsonic leading edge, the first data have been obtained that show the possibility of carrying out studies on the development of unstable perturbations. It was obtained that transition take place parallel to the leading edge for both models. The destabilizing effect of the surface curvature of the model on the position of the laminar-turbulent transition for the case of a supersonic leading edge was confirmed. This experimental data is the room for further investigation.
AB - The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings at Mach 2. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models with supersonic or subsonic leading edges. The transition location was determined using a constant temperature hot-wire anemometer. while experiments for the case of a supersonic leading edge are a continuation of previous studies, then for the case of a subsonic leading edge, the first data have been obtained that show the possibility of carrying out studies on the development of unstable perturbations. It was obtained that transition take place parallel to the leading edge for both models. The destabilizing effect of the surface curvature of the model on the position of the laminar-turbulent transition for the case of a supersonic leading edge was confirmed. This experimental data is the room for further investigation.
UR - http://www.scopus.com/inward/record.url?scp=85077811515&partnerID=8YFLogxK
U2 - 10.1088/1742-6596/1404/1/012097
DO - 10.1088/1742-6596/1404/1/012097
M3 - Conference article
AN - SCOPUS:85077811515
VL - 1404
JO - Journal of Physics: Conference Series
JF - Journal of Physics: Conference Series
SN - 1742-6588
IS - 1
M1 - 012097
T2 - 16th All-Russian Seminar with International Participation on Dynamics of Multiphase Media, DMM 2019
Y2 - 30 September 2019 through 5 October 2019
ER -
ID: 23120600