EROS — a common European Euler code for the analysis of the helicopter rotor flowfield

Renzoni, P.; D'Alascio, A.; Kroll, Norbert; Peshkin, D; Hounjet, M.H.L.; Boniface, Jean-Christophe; Vigevano, Luigi; Allen, Christian B; Badcock, K. J.; Mottura, Lorenzo; Schöll, Eberhard; Kokkalis, A.

doi:10.1016/s0376-0421(00)00006-3

Cited by 45 publications

(15 citation statements)

References 25 publications

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“…4. x (3) : the blade frame of reference after applying rotation, apping and lead-lag. 5. x (4) : the blade frame of reference after applying rotation, apping, lead-lag and pitch.…”

Section: Formulation Of Rotor Blade Motionmentioning

confidence: 99%

“…These block faces are treated as rigid, using Equation (14). 3. The e ect of rotation is subtracted from the mesh updates at this stage.…”

Section: Mesh Movement Deformation and Multi-block Topologymentioning

confidence: 99%

“…The numerical simulation of ows around ÿxed wings has been undertaken by many authors (see Reference [1] among others) and aerodynamic loads can be obtained with relative ease at design conditions. For rotary wings, however, the situation appears to be more complicated and CFD analysis is signiÿcantly harder as documented in References [2][3][4][5][6][7][8][9][10][11][12][13][14]. There are several reasons contributing to this which can be grouped into two categories.…”

Section: Introductionmentioning

confidence: 99%

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A framework for CFD analysis of helicopter rotors in hover and forward flight

Steijl

Barakos

Badcock

2006

Numerical Methods in Fluids

180

157

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SUMMARYA framework is described and demonstrated for CFD analysis of helicopter rotors in hover and forward ight. Starting from the Navier-Stokes equations, the paper describes the periodic rotor blade motions required to trim the rotor in forward ight (blade apping, blade lead-lag and blade pitching) as well as the required mesh deformation. Throughout, the rotor blades are assumed to be rigid and the rotor to be fully articulated with separate hinges for each blade. The employed method allows for rotors with di erent numbers of blades and with various rotor hub layouts to be analysed. This method is then combined with a novel grid deformation strategy which preserves the quality of multi-block structured, body-ÿtted grids around the blades. The coupling of the CFD method with a rotor trimming approach is also described and implemented. The complete framework is validated for hovering and forward ying rotors and comparisons are made against available experimental data. Finally, suggestions for further development are put forward. For all cases, results were in good agreement with experiments and rapid convergence has been obtained. Comparisons between the present grid deformation method and transÿnite interpolation were made highlighting the advantages of the current approach.

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“…4. x (3) : the blade frame of reference after applying rotation, apping and lead-lag. 5. x (4) : the blade frame of reference after applying rotation, apping, lead-lag and pitch.…”

Section: Formulation Of Rotor Blade Motionmentioning

confidence: 99%

“…These block faces are treated as rigid, using Equation (14). 3. The e ect of rotation is subtracted from the mesh updates at this stage.…”

Section: Mesh Movement Deformation and Multi-block Topologymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A framework for CFD analysis of helicopter rotors in hover and forward flight

Steijl

Barakos

Badcock

2006

Numerical Methods in Fluids

180

157

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“…This allows splitting of the fluid domain into several regions and discretisation of them independently, effectively transforming a very intricate mesh generation problem into several simpler and smaller ones. In addition, simple yet powerful high-quality structured grids can be used around each of the moving parts, which translates into more efficient and faster fluid solvers and mesh generators [22,23]. Boundary motions are very much simplified and only a rotation and/or translation of the existing grids is required before the intersection process happens again, hence saving computational effort.…”

Section: Background a Existing Unsteady Cfd Meshing Methodsmentioning

confidence: 99%

“…Due to their block-based nature, Chimera grids are suitable for parallel computations [24] and represent a reasonable alternative when an adaptive refinement mechanism is to be implemented [22]. Despite all of the above, interpolation algorithms needed at the boundaries of two overlapping grids are usually costly and complex [23], and can introduce numerical errors unless special care is taken to minimize them. They still cannot deal with arbitrary motions such as aeroelastic problems [24], where a mesh deformation technique is required in addition, or situations involving topological changes with appearing/disappearing cells, which, once again, rely on interpolations of the solution.…”

Section: Background a Existing Unsteady Cfd Meshing Methodsmentioning

confidence: 99%

Conservative Unsteady Simulation of Arbitrary Motion in Two-dimensional Spacetime Using Central Difference, Upwind and Hybrid Formulations

Ederra

Rendall

Gaitonde

et al. 2017

23rd AIAA Computational Fluid Dynamics Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms A spacetime framework is presented to solve unsteady aerodynamics problems as an alternative to conventional approaches for complex problems involving large deformation or topological change such as store separation, slat and flap deployment or spoiler deflection. It avoids complex CFD meshing methods, such as Chimera, by the use of a finite-volume approach both in space and time. The use of a central-difference scheme in the time direction yields non-physical transient solutions as a consequence of pressure waves travelling backwards in time. Therefore, an upwind formulation is provided and validated against one-dimensional test cases: a semi-infinite piston and a finite piston with a sharp change in direction. Also a hybrid formulation is given and several two-dimensional unsteady aerodynamics cases are computed with all three formulations and compared, demonstrating that the use of an upwind time stencil yields more representative physical solutions and improves the rate of convergence. In particular, the following problems are presented: a pitching NACA-0012 (periodic); a simple flap deflection; a spoiler deployment; a full landing case with a combination of slat, flap and spoiler deployments along with ground effect; and a case where aerofoils fly in opposite directions at subsonic and supersonic speeds.

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Conservative unsteady aerodynamic simulation of arbitrary boundary motion using structured and unstructured meshes in time

Rendall

Allen

Power

2011

Numerical Methods in Fluids

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SUMMARY Simulation of unsteady fluid behaviour with arbitrary boundary motion or topological change remains restricted owing to mesh deformation limitations, and usually requires the application of special techniques using overlapping meshes, sliding planes, remeshing or immersed boundaries. This work presents the application of a spacetime interpretation of the fluid conservation laws that unifies meshes in space and time. This effectively replaces the problem of mesh deformation with the problem of mesh generation and, because connectivity is no longer restricted to being constant in time, any motion or topological change may be simulated. Examples are given applying the method to a piston, a pitching NACA0012 aerofoil, an appearing/disappearing object, a two‐dimensional store separation and a rotation case to validate and then demonstrate the capabilities of the method. Results for the pitching aerofoil case are compared with a conventional moving mesh unsteady computation and shown to be consistent, whereas the demonstration cases show qualitatively correct behaviour and illustrate the general nature of the technique. Copyright © 2011 John Wiley & Sons, Ltd.

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EROS — a common European Euler code for the analysis of the helicopter rotor flowfield

Cited by 45 publications

References 25 publications

A framework for CFD analysis of helicopter rotors in hover and forward flight

A framework for CFD analysis of helicopter rotors in hover and forward flight

Conservative Unsteady Simulation of Arbitrary Motion in Two-dimensional Spacetime Using Central Difference, Upwind and Hybrid Formulations

Conservative unsteady aerodynamic simulation of arbitrary boundary motion using structured and unstructured meshes in time

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