Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow |
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Authors: | Yu. G. Ermolaev A. D. Kosinov A. N. Semenov N. V. Semionov A. A. Yatskikh |
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Affiliation: | 1.Khristianovich Institute of Theoretical and Applied Mechanics SB RAS,Novosibirsk,Russia;2.Novosibirsk State University,Novosibirsk,Russia;3.Sobolev Institute of Geology and Mineralogy SB RAS,Novosibirsk,Russia |
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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. |
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