Noise radiation of aircraft panels subjected to boundary layer pressure fluctuations
2008 (English)In: Journal of Sound and Vibration, ISSN 0022-460X, E-ISSN 1095-8568, Vol. 314, no 3-5, 693-711 p.Article in journal (Refereed) Published
In this paper, a method which predicts the sound radiation of aircraft panels subjected to turbulent boundary layer excitation is described. The method is the extension of ail earlier deterministic approach, where the modal expansion and modal receptance methods were used to predict random noise transmission through curved aircraft panels with stringer and ring frame attachments. Here, with implementation of the Corcos and Efimtsov models to characterize the dynamic surface pressure cross-spectra, closed-form solutions for the panel displacements, radiation and transmission pressures are derived. Numerical examples are presented to illustrate the effects of the stringers, ring frames, hydrodynamic coincidence, curvature, in-plane tension, structural dissipation and composite material on the structural and acoustic response of the panel.
Place, publisher, year, edition, pages
2008. Vol. 314, no 3-5, 693-711 p.
airplane fuselage structure, randomly excited panel, wave-number approach, flat-plate model, vibration measurements, excitation, turbulence, sound, prediction, element
Fluid Mechanics and Acoustics
IdentifiersURN: urn:nbn:se:kth:diva-6125DOI: 10.1016/j.jsv.2008.01.045ISI: 000256501100019ScopusID: 2-s2.0-43049089683OAI: oai:DiVA.org:kth-6125DiVA: diva2:10745
QC 201009082006-09-152006-09-152010-09-08Bibliographically approved