The influence of the cabin interior treatment on boundary layer noise levels is known to be significant, and we thus extend the model of Part 1 to include it. The extended model consists of the boundary layer excited flat plate, with its internal surface covered by two dissipative layers (representing insulation) and an elastic plate (the trim panel). By comparison with the bare plate, the trimmed plate has much higher modal damping, due to the ability of the insulation to absorb energy at the wavenumbers associated with resonant modes, and greatly reduced radiation efficiency, due to the insulations attenuating effect on supersonic wavenumber disturbances. Most of the conclusions of Part 1 are essentially unaffected by this behavioural modification, but structural damping treatments are now expected to have a negligible effect on the sound radiated by the plate.
Boundary layer induced noise in aircraft, Part II: the trimmed flat plate model
Randschichtinduzierter Lärm bei Flugzeugen, Teil 2: Das abgestimmte flache Platten-Modell
Journal of Sound and Vibration ; 192 , 1 ; 121-138
1996
18 Seiten, 18 Bilder, 2 Tabellen, 17 Quellen
Article (Journal)
English
Boundary layer induced noise in aircraft, part II: The trimmed flat plate model
Online Contents | 1996
|Boundary layer induced noise in aircraft, part I: The flat plate model
Online Contents | 1996
|Boundary layer induced noise in aircraft, Part I: the flat plate model
Tema Archive | 1996
|Boundary-Layer Induced Noise in Aircraft
British Library Conference Proceedings | 1992
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TIBKAT | 1992
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