Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. / Semionov, N. V.; Yermolaev, Yu G.; Kocharin, V. L. и др.
19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. ред. / Fomin. Том 2027 American Institute of Physics Inc., 2018. 030156 (AIP Conference Proceedings; Том 2027).Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
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TY - GEN
T1 - An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2
AU - Semionov, N. V.
AU - Yermolaev, Yu G.
AU - Kocharin, V. L.
AU - Kosinov, A. D.
AU - Semenov, A. N.
AU - Smorodsky, B. V.
AU - Yatskikh, A. A.
N1 - Publisher Copyright: © 2018 Author(s).
PY - 2018/11/2
Y1 - 2018/11/2
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. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. 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. Obtained good qualitative correspondence of experimental transition Reynolds number and the calculated dependences obtained for different values of the N factor. For the first time a comparison of the experimental growth rates with the results of calculations for various angles of attack was made. A good agreement between the experimental and theoretical data for the zero angle of attack was obtained. At the same time, there was no such agreement at non-zero angles of attack.
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. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. 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. Obtained good qualitative correspondence of experimental transition Reynolds number and the calculated dependences obtained for different values of the N factor. For the first time a comparison of the experimental growth rates with the results of calculations for various angles of attack was made. A good agreement between the experimental and theoretical data for the zero angle of attack was obtained. At the same time, there was no such agreement at non-zero angles of attack.
KW - TRANSITION
KW - STABILITY
UR - http://www.scopus.com/inward/record.url?scp=85056316351&partnerID=8YFLogxK
U2 - 10.1063/1.5065250
DO - 10.1063/1.5065250
M3 - Conference contribution
AN - SCOPUS:85056316351
VL - 2027
T3 - AIP Conference Proceedings
BT - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
A2 - Fomin, null
PB - American Institute of Physics Inc.
T2 - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
Y2 - 13 August 2018 through 19 August 2018
ER -
ID: 17413182