A hybrid computational model is presented to predict scattering and refractive effects on acoustic waves propagating through a boundary layer surrounding an aircraft fuselage. The fuselage is represented by an infinitely long cylinder with a noncircular cross section. The propagation effects through the boundary layer can be significant and should be included in noise predictions. The computational model uses finite elements to solve the acoustic pressure inside the boundary-layer area and boundary elements to calculate the pressure outside the boundary layer. An important advantage of the present model is that complicated geometries can be handled more easily than with prediction models that are based on analytical techniques. Most of these analytical prediction models are limited to circular cross shapes of fuselages. The purpose of the present investigation is to overcome this limitation and to assess the effects of noncircular geometries by comparing the pressure distributions with those of circular geometries. The computational model is applied to the noncircular cross section of a Fokker 50-like fuselage.


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    Title :

    Hybrid computational model for noise propagation through a fuselage boundary layer


    Additional title:

    Hybrides Rechenmodell für die Schallfortpflanzung durch eine Grenzschicht am Flugzeugrumpf


    Contributors:

    Published in:

    AIAA Journal ; 34 , 9 ; 1785-1792


    Publication date :

    1996


    Size :

    8 Seiten, 16 Bilder, 12 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






    A Hybrid Computational Model for Noise Propagation through a Fuselage Boundary Layer

    Schippers, H. / Wensing, J. A. / Confederation of European Aerospace Societies| AIAA | British Library Conference Proceedings | 1995