TY - JOUR

T1 - Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow

AU - Ermolaev, Yu G.

AU - Kosinov, A. D.

AU - Semenov, A. N.

AU - Semionov, N. V.

AU - Yatskikh, A. A.

PY - 2018/9/1

Y1 - 2018/9/1

N2 - 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.

AB - 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.

KW - laminar-turbulent transition

KW - supersonic boundary layer

KW - swept wing

KW - unit Reynolds number

KW - BOUNDARY-LAYER

KW - NOISE

UR - http://www.scopus.com/inward/record.url?scp=85059053061&partnerID=8YFLogxK

U2 - 10.1134/S0869864318050025

DO - 10.1134/S0869864318050025

M3 - Article

AN - SCOPUS:85059053061

VL - 25

SP - 659

EP - 665

JO - Thermophysics and Aeromechanics

JF - Thermophysics and Aeromechanics

SN - 0869-8643

IS - 5

ER -