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<p>The high-lift system noise is predicted for a landing approach condition for the actual scale Airbus 320-232 “D-ATRA” research aircraft of DLR. Noise simulations are performed for all key elements of the high-lift wing using stochastically derived sources, based on the underlying one-off Reynolds-Averaged Navier–Stokes CFD simulation. Turbulence quantities that are essential for the acoustic source characterisation are derived from the CFD solution by means of eddy viscosity. The acoustic perturbation equations (APE) are solved in close proximity to the aircraft using a volume-resolving discontinuous Galerkin method, valid in a non-uniform medium, assuming uncorrelated source domains. Then, the acoustic data are collected on a permeable Ffowcs Williams and Hawkings (FWH) surface and integrated to a far-field, where the acoustic pressures from different sources are combined for obtaining the overall noise footprint. The aeroacoustic simulation is compared to fly-over measurements in a blind test setting. A very good agreement is reported for the overall sound pressure level (OASPL) predictions.</p>

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Airframe noise simulation of an A320 aircraft in landing configuration

  • 期刊论文

  • 出版模式：

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  • 发表日期：

    2025年5月9日

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  • Stan Proskurov,
  • Michael Moessner,
  • Roland Ewert,
  • Jan W. Delfs,
  • Juergen Dierke,
  • Michael Pott-Pollenske,
  • Daniela Almoneit

摘要

The high-lift system noise is predicted for a landing approach condition for the actual scale Airbus 320-232 “D-ATRA” research aircraft of DLR. Noise simulations are performed for all key elements of the high-lift wing using stochastically derived sources, based on the underlying one-off Reynolds-Averaged Navier–Stokes CFD simulation. Turbulence quantities that are essential for the acoustic source characterisation are derived from the CFD solution by means of eddy viscosity. The acoustic perturbation equations (APE) are solved in close proximity to the aircraft using a volume-resolving discontinuous Galerkin method, valid in a non-uniform medium, assuming uncorrelated source domains. Then, the acoustic data are collected on a permeable Ffowcs Williams and Hawkings (FWH) surface and integrated to a far-field, where the acoustic pressures from different sources are combined for obtaining the overall noise footprint. The aeroacoustic simulation is compared to fly-over measurements in a blind test setting. A very good agreement is reported for the overall sound pressure level (OASPL) predictions.