The response of a supersonic transport fuselage to boundary layer and to reverberant noise

Abstract

The responses of part of the fuselage of a typical supersonic transport to turbulent boundary layer noise for two flight speeds, and to reverberant noise, are computed by the classical modal approach. These responses are used to compute equivalent reverberant acoustic fields which would produce essentially the same response in the structure as would turbulent boundary layer pressure fluctuations of given overall levels, spectra and correlation patterns. The equivalent reverberant acoustic fields may be used for cabin noise calculations, laboratory boundary layer simulation tests, or sonic fatigue studies.