Nonlinear disturbance evolution in supersonic boundary layers on the swept wing

Abstract eng:
The paper presented the results on the generation and development of the wave train in uniform and spanwise modulated boundary layer at Mach 2. A swept-wing model was used in the experiments. In 3D boundary layer the oblique breakdown mechanism is detected, which previously observed only in a supersonic boundary layer on flat plate. It was obtained that in the spanwise modulated boundary layer the oblique breakdown mechanism occurs at lower values of the longitudinal coordinate x.

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