Large Eddy Simulation of a Supersonic Turbulent Boundary Layer at M = 2.25
This work deals with numerical simulation of a spatially-developing supersonic turbulent boundary layer at a free-stream Mach number of M = 2.25 and a Reynolds number of R eθ = 5,000 with respect to free-stream quantities and momentum thickness at inflow. Since a shock-capturing scheme is used, a hybrid numerical scheme has been developed to reduce its dissipative properties. The issue of the generation of coherent turbulent boundary conditions is also addressed. A method originally developed by Lund, based on a rescaling technique, has been modified by adjusting the scaling coefficient to provide smooth transition between the inner and the outer parts of the boundary layer. This modification is essential for avoiding the drift previously observed in the mean streamwise velocity profile. The obtained results are analysed and discussed in terms of mean and turbulent quantities. Excellent agreement between LES, DNS and experimental data is obtained. The validity of the assumptions of the strong Reynolds analogy (SRA) is also addressed.
KeywordsUnsteady turbulent supersonic flows Large eddy simulation Turbulent boundary conditions Strong Reynolds analogy Shock-capturing schemes
Part of this work has been carried out within the research activities of the ATAC group (Aérodynamique des Tuyères et Arrière-Corps) supported by CNES and ONERA. Computational facilities were provided by CNRS — IDRIS (Institut du Développement et des Ressources en Informatique Scientifique, Paris) and CRIHAN (Center de Resources Informatiques de HAute Normandie, Rouen).
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