Cassiopee: A CFD pre- and post-processing tool

Benoît, Christophe; Péron, Stephanie; Landier, Sâm

doi:10.1016/j.ast.2015.05.023

Cited by 87 publications

(56 citation statements)

References 26 publications

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“…The computational meshes are built using Cassiopée tools [34], considering a near-body/off-body grid approach [34]. The blade near-body is meshed using a two-block O-type curvilinear mesh and is extruded in the normal direction.…”

Section: Numerical Setupmentioning

confidence: 99%

Aeroacoustic Study of the Interaction of a Rotating Blade with a Batchelor Vortex

Zehner¹,

Falissard²,

Gloerfelt

2016

22nd AIAA/CEAS Aeroacoustics Conference

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The aeroacoustic response of the orthogonal interaction of a rotating blade with an isolated Batchelor vortex is studied by means of numerical simulation. The relative influence of the vortex tangential and axial velocity on the blade aerodynamics and on the acoustics radiated in the far-field is analyzed by comparing the interaction with a Batchelor vortex to the interactions considering the vortex tangential or axial velocity components. Analyses show that the vortex tangential velocity contributes mostly to the noise level at low frequencies, whereas the vortex axial velocity is responsible for the contribution at high frequencies. For the range of frequencies in between, the interaction noise results from constructive interferences of the noise radiated separately by each velocity component of the vortex.

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Section: Numerical Setupmentioning

confidence: 99%

Aeroacoustic Study of the Interaction of a Rotating Blade with a Batchelor Vortex

Zehner¹,

Falissard²,

Gloerfelt

2016

22nd AIAA/CEAS Aeroacoustics Conference

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“…The method has been implemented in templatized C++ in the Cassiopee Software [17]. This section gives some test results for several ascending size problems covering the different boolean operations on different type of operands.…”

Section: Applications and Resultsmentioning

confidence: 99%

Boolean operations on arbitrary polygonal and polyhedral meshes

Landier

2017

Computer-Aided Design

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An O(nlogn) floating-point arithmetic algorithm designed for solving usual boolean operations (intersection, union, and difference) on arbitrary polygonal and polyhedral meshes is described in this paper. This methods does not approximate the inputs which can be both volume meshes, both surface meshes or one of each. It provides exact and conformal meshes upon exit. It can be used in many pre-and post-processing applications in computational physics (e.g. cut-cell volume mesh generation or conservative remapping). The core idea is to consider any configuration as a polygonal cloud. The polygons are first triangulated, the intersections are solved, the polyhedral cells are then reconstructed from the conformal triangles cloud and finally their triangular faces are re-aggregated to polygons. This approach offers a great flexibility regarding the admissible topologies : non-planar faces, concave faces or cells and some non-manifoldness are handled. The algorithm is described in details and some current results are shown.

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“…This demonstrator is made by a set of independent modules, each of them defining a CFD solver dedicated to Cartesian, curvilinear and polyhedral grids, which rely on the CGNS/Python data representation. These modules work in an interoperable way with other modules, most of them being Cassiopee [16] modules devoted to pre-, co-and post-processing. Each component acts through Python functions on the same shared data (CGNS/Python tree in memory).…”

Section: Cfd Solver: Fastsmentioning

confidence: 99%

“…The IBM implemented in sAbrinA_v0 are based on the same numerical environment as those implemented in FastS in order to benefit from mutual developments. The geometrical features required for the IBM process are provided by functions of ONERA's Cassiopee module [16]. The developments specific to aeroacoustics issues are detailed in Mincu et al [1].…”

Section: Caa Solver: Sabrina_v0mentioning

confidence: 99%

“…Following preliminary work on the same configuration presented in [1] but without any mean flow, we use in the present CAA simulation the realistic mean flow computed with the CFD solver FastS (see previous section). The flow field obtained on the CFD grid is interpolated on the CAA grid by the use of the in-house Cassiopee tool [16]. The acoustic source representing a fan/rotor interaction noise with an azimuthal mode m = 5 at a frequency f = 8 kHz is represented by a simplified model consisting of 60 monopoles located inside the nacelle at 90% of the nacelle inner radius.…”

Section: Caa Solver: Sabrina_v0mentioning

confidence: 99%

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Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

Lorteau¹,

Wiart²,

Kopiev³

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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This work is part of the ONERA-TsAGI cooperative project NOWNA (NextGen Over the Wing Nacelle Aircraft) which investigates the potential of fan noise shielding for a transonic transport aircraft by installing a UHBR engine over its wing. The studied configuration is a derivative of the NOVA (Next Generation Onera Versatile Aircraft) for which cruise aerodynamic performance and low speed acoustics are evaluated and compared to a reference configuration with under wing engines. The present activity is a continuation of previous work on the numerical investigation of the acoustic advantages of Over the Wing Nacelle (OWN) configurations using ONERA's in-house CAA solver sAbrinA_v0 (see Mincu et al., AIAA 2017-3504). Whereas early computations did not assume any mean flow, the present work takes into account a realistic mean flow computed with ONERA's CFD solver FastS, at a global Mach number of 0.25 corresponding to take-off/landing flight conditions, and with a simple flow-through condition for the nacelle. Both CFD and CAA solvers use the Immersed Boundary Method (IBM) to deal with the realistic aircraft and nacelle geometries, which greatly simplifies the meshing stage. Here, this OWN configuration is compared to a more classic UWN (Under the Wing Nacelle) configuration, in terms of far field noise directivity.

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Cassiopee: A CFD pre- and post-processing tool

Cited by 87 publications

References 26 publications

Aeroacoustic Study of the Interaction of a Rotating Blade with a Batchelor Vortex

Aeroacoustic Study of the Interaction of a Rotating Blade with a Batchelor Vortex

Boolean operations on arbitrary polygonal and polyhedral meshes

Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

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