A New Implementation of Aeroacoustic Integral Method for Supersonic Deformable Control Surfaces

Delrieux, Yves; Prieur, Jean; Rahier, Gilles; Drousie, Gwénaël

doi:10.2514/6.2003-3201

Cited by 9 publications

(9 citation statements)

References 5 publications

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“…Both surface integrals of formula (2) can be transformed to avoid the calculation for six observation points around X  required for the spatial derivatives i X   [21].…”

Section: Formula Used For Surface Integralsmentioning

confidence: 99%

Additional terms for the use of Ffowcs Williams and Hawkings surface integrals in turbulent flows

2015

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“…Both surface integrals of formula (2) can be transformed to avoid the calculation for six observation points around X  required for the spatial derivatives i X   [21].…”

Section: Formula Used For Surface Integralsmentioning

confidence: 99%

Additional terms for the use of Ffowcs Williams and Hawkings surface integrals in turbulent flows

2015

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“…, and thus avoid acoustic calculation for numerous observation points around X r (six points for usual centered derivatives by finite differences). They can write [13]:…”

Section: Formula Used For Surface Integralsmentioning

confidence: 99%

Comparison of surface and volume integral methods for transonic propeller acoustic predictions

Rahier

2019

Computers & Fluids

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A precise comparison of the surface and volume approaches of the Ffowcs Williams-Hawkings acoustic integral formulation is conducted for a propeller in transonic operating conditions. For both approaches, the calculations are carried out directly starting from CFD input data provided in the propeller rotating frame, i.e. with supersonically moving emission points. No approximation in the volume calculations, which could distort the comparison between both methods, is made. The principle and the calculation algorithm on which this particular integration technique is based are reviewed. Then calculations are carried out for four increasingly refined CFD meshes. They first confirm that both acoustic integral methods provide identical results when the numerical dissipation is negligible in the aerodynamic calculation. These calculations also show that the volume method is slightly less sensitive to the numerical dissipation than the surface method. However, the gain seems low compared to the computational cost of the volume integration. In addition, two techniques for determining the regions of the dominant acoustic sources are explored. With the first one, a rather conventional technique based on the local quadrupole term, the results show that specific terms, chosen according to the phenomenon concerned, may be better indicators of the real noise sources than the original shear and entropy terms. The second one, less known and consisting in calculating the elementary acoustic time signature radiated by each cell of the grid, seems more effective but may turn out to be costly in terms of data storage with the volume method.

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“…The noise radiated by the open rotor at model scale is computed using the ONERA KIM [14,15] code by solving the Ffowcs-Williams-Hawkings (FW-H) equation in the temporal domain. In diis study, die input data used to compute the sound radiation are provided by the unsteady CFD solutions in the form of unsteady surface pressure either from just the propeller blades or also from part of the test rig.…”

Section: Acoustic Simulation Approacbmentioning

confidence: 99%

Computational Fluid Dynamics as a Support to Counter-Rotating Open-Rotor Wind-Tunnel Test Analysis

Boisard

Delattre

Falissard

2014

Journal of Aircraft

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The rising price of oil since the early 21st century produced a regain of interest in the counter-rotating open rotor, seen as an economic propulsive device for future transport aircraft. Although simple methods are used for design and optimization, the need for advanced methods to assess aerodynamic and acoustic performance of a counter-rotating open rotor within a complex configuration and to support wind-tunnel tests analysis is rising. In this paper, a methodology for complex counter-rotating open-rotor installations is set up to compute an actual test-rig geometry using high performance computing capabilities of ONERA computational-fluid-dynamics software elsA. Comparing the numerical results with the wind-tunnel test data enables to assess both the computational-fluid-dynamics code accuracy and the representativity of the wind-tunnel test, which relies on a somewhat intrusive test rig through a better understanding of the flowfield around the test rig.

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A New Implementation of Aeroacoustic Integral Method for Supersonic Deformable Control Surfaces

Cited by 9 publications

References 5 publications

Additional terms for the use of Ffowcs Williams and Hawkings surface integrals in turbulent flows

Additional terms for the use of Ffowcs Williams and Hawkings surface integrals in turbulent flows

Comparison of surface and volume integral methods for transonic propeller acoustic predictions

Computational Fluid Dynamics as a Support to Counter-Rotating Open-Rotor Wind-Tunnel Test Analysis

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