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Thermophysics and Aeromechanics

2018 year, number 5

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

Yu.G. Ermolaev1, A.D. Kosinov1,2, A.N. Semenov1,3, N.V. Semionov1, and A.A.В Yatskikh1,2
1Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
2Novosibirsk State University, Novosibirsk, Russia
3Sobolev Institute of Geology and Mineralogy SB RAS, Novosibirsk, Russia
E-mail: semion@itam.nsc.ru
Keywords: supersonic boundary layer, swept wing, laminar-turbulent transition, unit Reynolds number
Pages: 659–665

Abstract

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 identified 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 Reynolds number on the transition position was observed.

DOI: 10.1134/S0869864318050025