Euler Calculations of Multibladed Rotors in Hover by DLR and ONERA Methods and Comparison with Helishape Tests

Rouzaud, Olivier; Raddatz, J.; Boniface, Jean-Christophe

doi:10.4050/jahs.43.296

Cited by 4 publications

(4 citation statements)

References 8 publications

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“…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%

“…+C rot C ap (x lag −x ap ) + C rotx ap (12) wherex ap ,x lag andx pitch deÿne the locations of the ap hinge, lead-lag hinge and the pitch centre. The velocity of P in terms of the helicopter-ÿxed frame of reference is then…”

Section: Formulation Of Rotor Blade Motionmentioning

confidence: 99%

“…Using this 'reference' grid, Equation (12) can now be used to update the grid from time level n to n + 1 for the blocks tagged for rigid-mesh motion.…”

Section: Mesh Movement Deformation and Multi-block Topologymentioning

confidence: 99%

“…Most of the published works focus on the numerical simulation of hovering rotors, such e orts can be found in References [6,[10][11][12] among others. Regarding forward-ying rotors, References [3-5, 7, 13, 14, 16, 17] document the e orts of several researchers over the last 10 years.…”

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

175

154

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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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Section: Introductionmentioning

confidence: 99%

Section: Formulation Of Rotor Blade Motionmentioning

confidence: 99%

“…Using this 'reference' grid, Equation (12) can now be used to update the grid from time level n to n + 1 for the blocks tagged for rigid-mesh motion.…”

Section: Mesh Movement Deformation and Multi-block Topologymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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

Steijl

Barakos

Badcock

2006

Numerical Methods in Fluids

175

154

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BILU implicit multiblock Euler/Navier–Stokes simulation for rotor tip vortex and wake convection

Zhong

Shaw

Qin

2007

Numerical Methods in Fluids

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SUMMARYIn this paper, a block incomplete lower-upper (BILU) decomposition method is incorporated with a multiblock three-dimensional Euler/Navier-Stokes solver for simulation of hovering rotor tip vortices and rotor wake convection. Results of both Euler and Navier-Stokes simulations are obtained and compared with experimental observations. The comparisons include surface pressure distributions and tip vortex trajectories. The comparisons suggest that resolution of the boundary layer is important for the accurate evaluation of the blade surface loading, but is less so for the correct prediction of the vortex trajectory. Numerical tests show that, using Courant-Friedrichs-Lewy (CFL) number of 10 or 30 with the developed BILU implicit scheme can be 6-7 times faster than an explicit scheme. The importance of solution acceleration schemes that increase the permitted time-step is illustrated by comparing the evolving wake structures at different stages of the calculation. In contrast to fixed wing simulations, the extent of the wake structures is shown to require resolution of large physical time. This observation explains the poor performance that is obtained when employing convergence acceleration strategies originally intended for solution of equilibrium problems, such as the multigrid methods.

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