Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow

Yu G. Ermolaev, A. D. Kosinov, A. N. Semenov, N. V. Semionov, A. A. Yatskikh

Результат исследования: Научные публикации в периодических изданияхстатья

2 Цитирования (Scopus)

Аннотация

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 М = 2 and 2.5, an increase in the unit Reynolds number (Re1) 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.

Язык оригиналаанглийский
Страницы (с-по)659-665
Число страниц7
ЖурналThermophysics and Aeromechanics
Том25
Номер выпуска5
DOI
СостояниеОпубликовано - 1 сен 2018

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