An Immersed Boundary Method for preliminary design aerodynamic studies of complex configurations

Péron, Stephanie; Renaud, Thomas; Mary, Ivan; Benoît, Christophe; Terracol, Marc

doi:10.2514/6.2017-3623

Cited by 10 publications

(13 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Even if the results get closer to the reference body-fitted solution with the grid resolution, the actual IBM method is not able to predict correctly the friction coefficient. It is more due to the present wall law, as described in [13] (the same wall law applied on a coarse body-fitted grid would exhibit the same discrepancy for the friction coefficient).…”

Section: Figure 1 -Body-fitted (Left) and Ibm (Right) Meshes Around Tmentioning

confidence: 78%

“…The CPU cost for the following test-cases is about 0.4μs/points/iteration on Haswell core (Intel® Xeon® CPU E5-2690 v3 @ 2.60GHz). The FAST IBM approach does not require a lot of memory and, thus, for example, a wing-body configuration with 690M points can be easily simulated on 256 cores [13].…”

Section: Description Of the Solvermentioning

confidence: 99%

“…In the past decades, a wide range of immersed boundary approaches have been developed to deal with incompressible flows for elastic and moving obstacles Due to the increase of the geometrical complexity of configurations studies in aeronautics in the last decade, many researchers have developed immersed boundary approaches to solve compressible flows [6] [7]. An immersed boundary method (IBM) has been developed for five years at ONERA [13] in combination with an automatic adaptive Cartesian mesh generation to deal with complex geometries. This paper focuses on the validation of the immersed boundary method for a wide range of flow regimes and Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Validation of an immersed boundary method for compressible flows

Renaud¹,

Benoît²,

Péron³

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

View full text Add to dashboard Cite

This paper sums up some recent validations of an immersed boundary method for compressible flow simulations. It has been already shown that this method is able to provide accurate results without meshing effort around more or less complex geometries. Here, the authors focus on several simple test cases to assess the application range of the method. From subsonic to hypersonic flows, from steady to large-eddy unsteady simulations, in 2D or 3D, results are compared to classical simulations with body-fitted meshes and experiment. Moreover, the use of an efficient Navier-Stokes solver for all the cases is part of the benefit of the approach to provide a CFD solution in a reduced time.

show abstract

Section: Figure 1 -Body-fitted (Left) and Ibm (Right) Meshes Around Tmentioning

confidence: 78%

Section: Description Of the Solvermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Validation of an immersed boundary method for compressible flows

Renaud¹,

Benoît²,

Péron³

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…A CFD demonstrator named FastS has been developed at ONERA for several years [13][14][15] to provide a software architecture and numerical techniques allowing for a high level of efficiency, flexibility and upgradeability. 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.…”

Section: Cfd Solver: Fastsmentioning

confidence: 99%

“…This function has been generalized to handle also the update of IB (Immersed Boundary) target points, since the first step consists in a kind of Chimera interpolation, but for the IB image points. More details on the IBM implemented in FastS are available in Péron et al [14]. Each CFD solver solves the compressible Euler and Navier-Stokes equations using a second-order accurate Finite-Volume Method only for the interior points of each grid.…”

Section: Cfd Solver: Fastsmentioning

confidence: 99%

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

View full text Add to dashboard Cite

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.

show abstract

Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow

Lugrin

Beneddine

Garnier

et al. 2021

Theor. Comput. Fluid Dyn.

View full text Add to dashboard Cite

A high-fidelity simulation of the massively separated shock/ transitional boundary layer interaction caused by a 15-degrees axisymmetrical compression ramp is performed at a free stream Mach number of 6 and a transitional Reynolds number. The chosen configuration yields a strongly multiscale dynamics of the flow as the separated region oscillates at low-frequency, and high-frequency transitional instabilities are triggered by the injection of a generic noise at the inlet of the simulation. The simulation is post-processed using Proper Orthogonal Decomposition to extract the large scale low-frequency dynamics of the recirculation region. The bubble dynamics from the simulation is then compared to the results of a global linear stability analysis about the mean flow. A critical interpretation of the eigenspectrum of the linearized Navier-Stokes operator is presented. The recirculation region dynamics is found to be dominated by two coexisting modes, a quasi-steady one that expresses itself mainly in the reattachment region and that is caused by the interaction of two self-sustained instabilities, and an unsteady one linked with the separation shock-wave and the mixing layer. The unsteady mode is driven by a feedback loop in the recirculation region, which may also be relevant for other unsteady shock-motion already documented for shock-wave/turbulent boundary layer interaction. The impact of the large-scale dynamics on the transitional one is then assessed through the numerical filtering of those low wavenumber modes; they are found to have no impact on the transitional dynamics.

show abstract

An Immersed Boundary Method for preliminary design aerodynamic studies of complex configurations

Cited by 10 publications

References 23 publications

Validation of an immersed boundary method for compressible flows

Validation of an immersed boundary method for compressible flows

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

Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow

Contact Info

Product

Resources

About