Receptivity of the transonic boundary layer to acoustic noise

Currently a major priority in passenger aircraft design is to delay laminar-turbulent transition in the boundary layer on aircraft wings. It has been identified that acoustic noise, free-stream turbulence and wall roughness are responsible for the laminar-turbulent transition which starts with the receptivity of the boundary layer to external perturbations. This project will focus on the receptivity in transonic speed regimes. Both the generation of the Tollmien-Schlichting waves and of the Cross-Flow vortices will be studied. For this purpose the asymptotic solutions of the Navier-Stokes equations will be constructed assuming that the Reynolds number is large. Based on these solutions the means to control the laminar-turbulent transition by suppressing the receptivity process will be developed.