A weak coupling method between the dynamics code HOST and the 3D unsteady Euler code WAVES

Servera, Gaëlle; Beaumier, Philippe; Costes, M.

doi:10.1016/s1270-9638(01)01120-8

Cited by 30 publications

(15 citation statements)

References 1 publication

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“…Indeed, despite the mono-disciplinary aspect of the present study, aeroelasticity and dynamic considerations cannot be totally avoided. In particular, the torsion of the blade has a major influence on the evaluation of hover performance as shown in [1] and [14]. A coupling between HOST and elsA has so been performed: at each optimization step, given the geometry and the collective pitch, the HOST code is able to compute the blade deformations (flap bending and torsion) and the rotor angles (flap and lead-lag).…”

Section: Rigid/soft Blade Assumptionmentioning

confidence: 99%

“…As no re-computations of the trim is performed taken into account the CFD-computed aerodynamics, the present coupling is not fully appropriate. An iterated weakcoupling process should be performed as presented in [14] for forward flight aerodynamic performance evaluation, but such process required several CFD computations and thus important CPU resources that do not fit with optimization procedure requirements.…”

Section: Rigid/soft Blade Assumptionmentioning

confidence: 99%

“…2). These rotors are wind tunnel scaled rotors and have been mainly used for aerodynamic studies [14]. They have a radius of 2.1 m and a chord of 0.14 m, and the tip Mach number is 0.617.…”

Section: A/7ad Rotor Applicationsmentioning

confidence: 99%

See 2 more Smart Citations

Numerical optimization of helicopter rotor aerodynamic performance in hover

Pape

Beaumier

2005

Aerospace Science and Technology

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Section: Rigid/soft Blade Assumptionmentioning

confidence: 99%

Section: Rigid/soft Blade Assumptionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical optimization of helicopter rotor aerodynamic performance in hover

Pape

Beaumier

2005

Aerospace Science and Technology

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“…It decomposes the loads and the surface motions from both parts into Fourier modes per revolution and exchanges these. This scheme is used for example at ONERA, France [20], and seems to have a small performance advantage with respect to faster convergence due to more damping in the system. However, it is difficult to extended to fully instationary cases like manoeuvre flight.…”

Section: Coupling Schemementioning

confidence: 99%

CFD – a key element of helicopter activities at the IAG

Wagner

Keßler

Altmikus

et al. 2004

Aerospace Science and Technology

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“…We use the weak coupling technique [19][20][21][22] between the CFD solver FLOWer (DLR, German Aerospace Research Center) and the flight mechanics/computational structural dynamics (CSD) code HOST (Eurocopter). The rotor is trimmed for thrust, as well as longitudinal and lateral mast moments, in all computations by adaption of the collective and the cyclic pitch angles.…”

mentioning

confidence: 99%

Tip Vortex Conservation on a Helicopter Main Rotor Using Vortex-Adapted Chimera Grids

et al. 2007

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This paper presents a method to improve the tip vortex conservation in a computational fluid dynamics simulation of a helicopter main rotor. Our approach uses vortex-adapted Chimera child grids to achieve a local refinement of the grid in the vicinity of the vortex and thus reduce the numerical dissipation of the vortex. The method is applied to the higher-harmonic-control aeroacoustic rotor test case to evaluate its potential with respect to the prediction of bladevortex interaction airloads. To allow a meaningful comparison with the experimental data, the rotor is trimmed for thrust, as well as for longitudinal and lateral mast moments, using weak fluid-structure coupling with a flight mechanics code. We obtained a good overall agreement with the experimental data for both aerodynamics and blade dynamics. The effect of the improvement in tip vortex conservation is demonstrated by comparison with simulations without Chimera refinement and with the experimental results. It turned out that a very fine grid resolution in the vicinity of the vortex is necessary to capture the blade-vortex interaction airloads. The required grid resolution was provided by a refinement of the vortex-adapted grids, allowing for a very good reproduction of the blade-vortex interaction airloads, especially on the retreating blade side. Nomenclature C m Ma 2 = sectional pitching moment coefficient C n Ma 2 = sectional normal force coefficient F z = rotor thrust, N Ma tip = hover tip Mach number M x = rotor mast rolling moment, Nm M y = rotor mast pitching moment, Nm q = rotor shaft angle, deg c = longitudinal cyclic pitch angle, deg s = lateral cyclic pitch angle, deg 0 = collective pitch angle, deg 3=rev = three-per-revolution higher-harmonic-control amplitude, deg = advance ratio = rotor azimuth angle, deg w = wake age, deg 3=rev = three-per-revolution pitch control phase, deg

show abstract

A weak coupling method between the dynamics code HOST and the 3D unsteady Euler code WAVES

Cited by 30 publications

References 1 publication

Numerical optimization of helicopter rotor aerodynamic performance in hover

Numerical optimization of helicopter rotor aerodynamic performance in hover

CFD – a key element of helicopter activities at the IAG

Tip Vortex Conservation on a Helicopter Main Rotor Using Vortex-Adapted Chimera Grids

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