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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    Title :

    Acoustics of a Supersonic Mach 1.4 Axisymmetric Spike Inlet


    Contributors:

    Conference:

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


    Publication date :

    2023-06-12


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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