Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. / Semionov, N. V.; Yermolaev, Yu G.; Kosinov, A. D. и др.
Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. ред. / Fomin. Том 1893 American Institute of Physics Inc., 2017. 030086 (AIP Conference Proceedings; Том 1893).Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
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TY - GEN
T1 - The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2
AU - Semionov, N. V.
AU - Yermolaev, Yu G.
AU - Kosinov, A. D.
AU - Semenov, A. N.
AU - Smorodsky, B. V.
AU - Yatskikh, A. A.
PY - 2017/10/26
Y1 - 2017/10/26
N2 - The paper is devoted to an experimental and theoretical study of effect of small angle of attack on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach number M=2. The experiments are conducted at the low nose supersonic wind tunnel T-325 of ITAM. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. The transition location is determined using a hot-wire anemometer. Confirmed monotonous growth of the transition Reynolds numbers with increasing of angle of attack from -2°to 2.5°. The experimental data on the influence of the angle of attack on the disturbances evolution in the supersonic boundary layer on the swept wing model are obtained. Calculations on the effect of small angles of attack on the development of perturbations are made in the framework of the linear theory of stability. A good qualitative correspondence of theoretical and experimental data are obtained.
AB - The paper is devoted to an experimental and theoretical study of effect of small angle of attack on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach number M=2. The experiments are conducted at the low nose supersonic wind tunnel T-325 of ITAM. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. The transition location is determined using a hot-wire anemometer. Confirmed monotonous growth of the transition Reynolds numbers with increasing of angle of attack from -2°to 2.5°. The experimental data on the influence of the angle of attack on the disturbances evolution in the supersonic boundary layer on the swept wing model are obtained. Calculations on the effect of small angles of attack on the development of perturbations are made in the framework of the linear theory of stability. A good qualitative correspondence of theoretical and experimental data are obtained.
KW - CROSS-FLOW VORTICES
UR - http://www.scopus.com/inward/record.url?scp=85034262297&partnerID=8YFLogxK
U2 - 10.1063/1.5007544
DO - 10.1063/1.5007544
M3 - Conference contribution
AN - SCOPUS:85034262297
VL - 1893
T3 - AIP Conference Proceedings
BT - Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
A2 - Fomin, null
PB - American Institute of Physics Inc.
T2 - 25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017
Y2 - 5 June 2017 through 9 June 2017
ER -
ID: 9695977