Aeroacoustics of Transonic Shock-Boundary Layer Interactions

The interaction of a spatially developing supersonic turbulent boundary layer with a normal shock wave is analyzed by means of direct numerical simulation of the compressible Navier-Stokes equations. At the selected flow conditions, corresponding to a mild shock, no mean flow separation is observed. However, the flow is strongly unsteady, and inter- mittent regions of flow reversal are found near the wall, while large vortical structures are observed away from it. Such structures are mainly responsible for the amplification of noise and turbulence across the interaction zone. The intense acoustic loads occurring in the interaction zone are found to be strictly related to the Reynolds shear stress distribu- tion. The analysis of the pressure energy spectra shows a behavior consistent with that observed in incompressible boundary layers in adverse pressure gradient. In particular, a power-law scaling is recovered: at low frequencies the spectra scale as St0.4, while at high frequencies they decay as St-5. The results show that the interacting shock primarily acts as a low-pass filter for the turbulence spectra. © 2007 by Sergio Pirozzoli and Francesco Grasso.