Experimental Study of the Influence of Weak Shock Waves on the Laminar-Turbulent Transition in the Swept Wing Boundary Layer at Mach Number 2.5

   Experimental results on the effect of weak shock waves on the laminar-turbulent transition in the supersonic boundary layer of a three-dimensional wing with a leading edge sweep angle of 45° at a Mach number of 2.5 are considered in the work. A pair of weak shock waves in the oncoming flow is created by a 2D unevenness. The 2D unevenness of surface had dimensions of 150 × 7 × 0.155 mm and was installed vertically on the side wall of the working part of the wind tunnel T-325 ITAM SB RAS. The measurements were made by the constant temperature anemometer. Experimental results show that weak shock waves influence the laminar-turbulent transition in the supersonic boundary layer of a three-dimensional wing and lead to early shear flow turbulization. The most powerful effect on the transition to turbulence in a supersonic spatial boundary layer is produced by a shock wave formed by the flow around a scarp from the trailing edge of a 2D unevenness. The second wave has almost no effect on the position of the transition. Effect of the cross flow on stationary vortices caused by the interaction of weak shock waves with the leading edge of a swept wing is also observed in experiments.

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