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

Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic... 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 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. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

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

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Publisher
Springer Journals
Copyright
2018 Kutateladze Institute of Thermophysics, Siberian Branch of the Russian Academy of Sciences
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/S0869864318050025
Publisher site
See Article on Publisher Site

Abstract

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 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.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Sep 1, 2018

References