An inlet for a supersonic commercial aircraft is analyzed for noise radiation in low-speed configuration, with auxiliary inlet open. Duct mode amplitudes generated by the fan are determined by post-processing a URANS simulation and become a boundary condition to the inlet. Far-field sound is modeled using commercial acoustics finite element software. The effect of inlet geometry and acoustic liners is simulated and discussed. Absolute levels for inlet tone noise are predicted.


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    Titel :

    Acoustics of a Supersonic Mach 1.4 Axisymmetric Spike Inlet


    Beteiligte:
    David B Stephens (Autor:in) / Edmane Envia (Autor:in)

    Kongress:

    AIAA AVIATION Forum and Exposition ; 2023 ; San Diego, CA, US


    Erscheinungsdatum :

    12.06.2023


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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