Abstract
The unsteady flowfield about the ONERA–The French Aerospace Lab/Airbus SAS LAGOON two-wheel landing-gear configuration and the associated aerodynamic noise generation are computed using a hybrid approach in which the flowfield is provided by a lattice–Boltzmann simulation, and the noise radiation is computed using the Ffowcs-Williams–Hawkings analogy. A detailed validation study is carried out, following the guidelines of the second AIAA workshop on Benchmark Problems for Airframe Noise Computations and using the complete experimental database for detailed comparisons. The effect of grid resolution on both near- and far-field results is investigated, showing the physical consistency of the numerical model. In addition, an assessment of the numerical prediction is carried out by computing the maximum perceived noise level along a nominal approach trajectory. Finally, an unsteady flow mechanism involving the onset of cavity modes in the two facing rim cavities is analyzed in detail and correlated with the generation of tonal noise components.
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