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Etude, mise au point et validation de modèles de turbulence compressible

Abstract : This work deals mainly with phenomena occurring in Aeronautical and Aerospace domains. The flow occurring in rockets and afterbodies engines as well as shock waves/boundary layers interactions are computed using a mixed finite-volumes / finite elements method. The main motivation of this work is to understand the different factor governing those flows. This work, supported by the SNECMA-group, is mainly devoted to the study and the modeling of the near-wall phenomena using the N3S-Natur software. The goal of this study is to improve the current industrial software and to develop new computation methods (LES/DES) for a better design and control of the propulsive systems. The two-equation turbulence models developed in this study were firstly validated on simple flows (compressible boundary layers, supersonic jet ...) before being applied to complex geometries (nozzle with film cooling, 3D afterbody, viscous interactions and 3D jet separation). A part of the work is devoted to the study of the transient phenomena occurring during the start-up of rocket nozzles. Concerning unsteady aspects, it has been shown, through the study of a shock wave/boundary layer interaction, that the DES (Detached Eddy Simulation), as well as the LES (Large Eddy Simulation) are pertinent tools, which accurately predict the characteristics of both mean and fluctuating flow-fields of complex high-speed aerodynamics.
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Contributor : Abdellah Hadjadj <>
Submitted on : Thursday, March 1, 2007 - 12:06:06 PM
Last modification on : Tuesday, February 5, 2019 - 11:44:12 AM
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  • HAL Id : tel-00134262, version 1


Yohann Perrot. Etude, mise au point et validation de modèles de turbulence compressible. Modélisation et simulation. INSA de Rouen, 2006. Français. ⟨tel-00134262⟩



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