This paper presents an overview of the capabilities of a new open-source pre-and post-processing tool for Computational Fluid Dynamics simulations, called Cassiopee. Its architecture, which is basically a set of Python modules, and the handled data, which is based on CGNS standard, are described. Some examples of workflows that can be built with Cassiopee functions are provided. Finally, some applications of Cassiopee functions to realistic CFD configurations are briefly presented.

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International audienceThis article describes a methodology based on overset grid techniques that enables the mesh generation process for aircraft configurations to be simplified and shortened. It is based on the key-concept of partitioning the computational domain: the near-body areas are meshed by a set of body-fitted structured grids while the off-body domain is treated with an automated Cartesian grid method. This state-of-the-art combination allows a complex geometry to be considered as the sum of simple elements such as fuselage, wing, winglets, or tailplanes. As a consequence, the ONERA approach exhibits several decisive advantages: easiness, flexibility, rapid implementation, Cartesian grid adaptation. In order to apply and validate the overall methodology, a well-known configuration, the NASA Common Research Model, has been chosen. It is an open geometry representative of current wide-body commercial aircraft which has been used in the international AIAA Drag Prediction Workshops. In this paper, the complete meshing procedure is described. Then, for near-field and far-field drag as well as for local analyses, the results obtained with this new overset strategy are compared to the data produced by the common point-matched Drag Prediction Workshop grids and a very satisfactory agreement is observed.Moreover, some advantages of Cartesian grid adaptation are highlighted

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