Инд. авторы:	Ermolaev Y.G., Kosinov A.D., Semenov A.N., Semionov N.V., Yatskikh A.A.
Заглавие:	Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow
Библ. ссылка:	Ermolaev Y.G., Kosinov A.D., Semenov A.N., Semionov N.V., Yatskikh A.A. Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow // Thermophysics and Aeromechanics. - 2018. - Vol.25. - Iss. 5. - P.659-665. - ISSN 0869-8643. - EISSN 1531-8699.
Внешние системы:	DOI: 10.1134/S0869864318050025; WoS: 000454442300002; SCOPUS: 2-s2.0-85059053061;
Реферат:	eng: An experimental study of the influence of unit Reynolds number on the position of laminar-turbulent transition in swept-wing boundary layer at supersonic flow velocities was carried out. In the experiments, a swept-wing model with 3-% circular arc airfoil and 45-deg gliding angle of wing edges was used. The position of the transition was iden-tified using a hot-wire anemometer. It was found that at M = 2 and 2.5, an increase in the unit Reynolds number (Re-1) leads to a transition delay. It was shown that an increase in freestream Mach number and in the level of flow pulsations in the wind-tunnel test section leads to a less pronounced influence of Re1 on the transition position. At a high noise level due to the growth of Mach number or due to the introduction of vortical disturbances, no effect due to unit Reyn-olds number on the transition position was observed.
Ключевые слова:	NOISE; BOUNDARY-LAYER; unit Reynolds number; laminar-turbulent transition; swept wing; supersonic boundary layer;
Издано:	2018
Физ. характеристика:	с.659-665