Boundary layer receptivity to acoustic noise in transonic flows

Abstract eng:
In this study we analyse the process of the generation of Tollmien-Schlichting waves in a laminar boundary layer on an aircraft wing in the transonic flow regime. We assume that the boundary layer is exposed to a weak acoustic noise. We develop the receptivity theory, assuming that the Reynolds number is large. In this case we were able to deduce an analytic formula for the amplitude of the generated Tollmien-Schlichting wave.

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