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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This work was financially supported by the Russian Science Foundation (Grant No. 17-19-01289).
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Ermolaev, Y.G., Kosinov, A.D., Semenov, A.N. et al. Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow. Thermophys. Aeromech. 25, 659–665 (2018). https://doi.org/10.1134/S0869864318050025
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DOI: https://doi.org/10.1134/S0869864318050025