An effect of unit Reynolds number on the laminar-turbulent transition on 3D swept wing with χ = 72° at M = 2

Abstract

This work is devoted to the study of the influence of unit Reynolds number on the position of the laminar-turbulent transition in the supersonic boundary layer on a swept wing. The experiments were carried out in a T-325 supersonic wind tunnel of the Institute of Theoretical and Applied Mechanics named after S.A. Khristianovich on a wing model with a swept angle χ=72° at Mach number 2. That corresponds to a subsonic leading edge. The transition position was determined using a constant temperature hot wire anemometer. Comparison with previously obtained data for a wing model with 45 degree leading edge shown, that for the same flow parameters, the laminar-turbulent transition on the model of a wing with a subsonic leading edge occurs earlier than on a model of a wing with a supersonic leading edge. A unit Reynolds number has less impact on the transition position on a wing model with a subsonic leading edge, in contrast to a model with a supersonic leading edge.