Development of a Chimera unsteady method for the numerical simulation of rotorcraft flowfields

Boniface, Jean-Christophe; Guillen, Philippe; Pape, Marie-Claire Le; Darracq, Denis; Beaumier, Ph.

doi:10.2514/6.1998-421

Cited by 17 publications

(10 citation statements)

References 1 publication

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“…The comparison shows that the results are comparable to the numerical and experimental results from Beaumier et al [6,7]. In order to calculate the whole rotor, the "Snapping grid algorithms" [14], which allows the index exchange at the moving boundaries, or the "Chimera grid scheme" [15], which uses overset mesh systems, has to be implemented.…”

Section: Flows Over Onera Wingssupporting

confidence: 61%

“…With the predictive capability demonstrated in the above validation, the current code is then applied to simulate the flows past oscillating wings based on ONERA 209 and 213 airfoil profiles. Some qualitative comparisons are made between the results from the current investigation and the data reported in [6,7].…”

Section: Introductionmentioning

confidence: 89%

“…The 7A model rotor has rectangular blades, with ONERA 213 airfoils (13% relative thickness) from blade root to 75% radius and ONERA 209 airfoils (9% relative thickness) from 90% radius to blade tip. Beaumier et al [6,7] performed calculations for the rotor flow using both potential and Euler codes under the following conditions: where ψ is the azimuthal angle. As reference for the computed results using the present algorithms, some selected results from Beaumier et al [6,7] are shown in the left columns in Figures 10 and 11.…”

Section: Flows Over Onera Wingsmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Simulation of Oscillating Wings Using a Moving Grid Technique

Yuan¹,

Xu²,

Khalid³

2003

41st Aerospace Sciences Meeting and Exhibit

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Steady flow in nature is a simplified version of the more realistic unsteady flow. A stationary airfoil, by itself, may have to contend with the unsteadiness of the turbulent flow separation, which results in time dependent vortices structures. With increasing emphasis on emerging UAV technologies, there is a renewed interest in being able to model the lowReynolds-number viscous effects in the incompressible flow regimes as well as to account for moving components in small aircraft. The current work makes use of the moving grid technique to investigate the unsteady incompressible flows past three-dimensional (3-D) wings with oscillations in pitch. The modified SIMPLE method is used to solve the unsteady 3-D Navier-Stokes equations with a RNG k-ε turbulence model. As an initial step of LES research, the Smagorinsky sub-grid-scale (SGS) model is implemented and some preliminary LES calculations are performed. In order to preserve the grid conservative property, a space conservation law is implemented in the moving grid calculation. The cell-centered finite volume method is used in the spatial discretisation. A fully implicit temporal differencing scheme permits an unconditional stability in time marching. With the predictive capability demonstrated in the validation using a wing based on the NACA 0012 airfoil, the current code is then applied to simulate the flows past oscillating wings based on the ONERA 209 and 213 airfoil profiles. The results in the current investigation are qualitatively compared with the data reported by other authors.

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Section: Flows Over Onera Wingssupporting

confidence: 61%

Section: Introductionmentioning

confidence: 89%

Section: Flows Over Onera Wingsmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Simulation of Oscillating Wings Using a Moving Grid Technique

Yuan¹,

Xu²,

Khalid³

2003

41st Aerospace Sciences Meeting and Exhibit

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“…Developed at ONERA since 1997 and initially based on its predecessors Canari [8] and Flu3M [9], elsA is a structured multiblock CFD solver based on a cell-centered ¦nite-volume approach [5,10].…”

Section: The Multiblock Structured Solver Elsamentioning

confidence: 99%

elsA-Hybrid: an all-in-one structured/unstructured solver for the simulation of internal and external flows. Application to turbomachinery

Plata

Couaillier

Pape

et al. 2013

Progress in Propulsion Physics

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This paper reports recent work on the extension of the multiblock structured solver elsA to deal with hybrid grids. The new hybrid-grid solver is called elsA-H (elsA-Hybrid), is based on the investigation of a new unstructured-grid module has been built within the original elsA CFD (computational §uid dynamics) system. The implementation bene¦ts from the §exibility of the object-oriented design. The aim of elsA-H is to take advantage of the full potential of structured solvers and unstructured mesh generation by allowing any type of grid to be used within the same simulation process. The main challenge lies in the numerical treatment of the hybrid-grid interfaces where blocks of di¨erent type meet. In particular, one must pay attention to the transfer of information across these boundaries, so that the accuracy of the numerical scheme is preserved and §ux conservation is guaranteed. In this paper, the numerical approach allowing to achieve this is presented. A comparison between the hybrid and the structured-grid methods is also carried out by considering a fully hexahedral multiblock mesh for which a few blocks have been transformed into unstructured. The performance of elsA-H for the simulation of internal §ows will be demonstrated on a number of turbomachinery con¦gurations.

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“…Recently, structured overset grid methods have been used to study the grid-related effect on the numerical results of hovering rotors [7] and to handle the relative motion between the rotor blades and the fuselage [8][9][10]. However, structured overset grid methods are not grid-efficient and requirentxcessi [7]y large number of cells to accurately capturenthe vortical wake because of the regularity required in the grid point distribution.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Unsteady Rotor Flow Using an Unstructured Overset Mesh Flow Solver

Jung¹,

Kwon²

2009

International Journal of Aeronautical and Space Sciences

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An unstructured overset mesh method has been developed for the simulation of unsteady flow fields around isolated rotors and rotor-fuselage configurations. The flow solver was parallelized for the efficient calculation of complicated flows requiring a large number of cells. A quasi-unsteady mesh adaptation technique was adopted to enhance the spatial accuracy of the solution and to better resolve the rotor wake. The method has been applied to calculate the flow fields around rotor-alone and rotor-fuselage configurations in forward flight. Validations were made by comparing the predicted results with those of measurements. It was demonstrated that the present method is efficient and robust for the prediction of unsteady time-accurate flow fields involving multiple bodies in relative motion.

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Development of a Chimera unsteady method for the numerical simulation of rotorcraft flowfields

Cited by 17 publications

References 1 publication

Numerical Simulation of Oscillating Wings Using a Moving Grid Technique

Numerical Simulation of Oscillating Wings Using a Moving Grid Technique

elsA-Hybrid: an all-in-one structured/unstructured solver for the simulation of internal and external flows. Application to turbomachinery

Numerical Simulation of Unsteady Rotor Flow Using an Unstructured Overset Mesh Flow Solver

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