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Silent inflow condition for turbulent boundary layers

Article dans une revue avec comité de lecture
Author
ccROBINET, Jean-Christophe
134975 Laboratoire de Dynamique des Fluides [DynFluid]
492366 Airbus Safran Launchers
ccGLOERFELT, Xavier
694 Laboratoire de Mecanique des Fluides et d'Acoustique [LMFA]

URI
http://hdl.handle.net/10985/17837
DOI
10.1103/PhysRevFluids.2.124603
Date
2017
Journal
Physical Review Fluids

Abstract

The generation of a turbulent inflow is a tricky problem. In the framework of aeroacoustics, another important constraint is that the numerical strategy used to reach a turbulent state induces a spurious noise which is lower than the acoustic field of interest. For the study of noise radiated directly by a turbulent boundary layer on a flat plate, this constraint is severe since wall turbulence is a very inefficient source. That is why a method based on a transition by modal interaction using a base flow with an inflection point is proposed to cope with that. The base flow must be a solution of the equations so we use a profile behind a backward-facing step representative of experimental trip bands. A triad of resonant waves is selected by a local stability analysis of the linearized compressible equations and is added with a weak amplitude in the inlet plane. The compressible stability calculation allows the specification of the thermodynamic quantities at the inlet, which turns out to be fundamental to ensure a quiet inflow. A smooth transition is achieved with the rapid formation of Λ-shape vortices in a staggered organization as in subharmonic transition. The dominance of oblique waves promotes a rapid breakdown by the liftup mechanism of low-speed streaks. The quality of the fully turbulent state is assessed and the direct noise radiation from a turbulent boundary layer at Mach 0.5 is obtained with a very low level of spurious noise.

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