Interior noise radiated by an airplane fuselage subjected to turbulent boundary layer excitation and evaluation of noise reduction treatments

Abstract

The acoustic power radiated by an airplane fuselage structure exposed to a turbulent boundary layer pressure field has been measured at two flight Mach numbers. For a single fuselage panel the radiated power is approximately 90 and 70 dB relative to 10 −13 W at Mach 0·85 and 0·55 respectively. Damping tape and rubber wedge treatments, applied to the structure, reduce the acoustic radiation but they are more effective at Mach 0·85 than at Mach 0·55 The flight test data are in poor agreement with available wind tunnel measurements, indicating the need for improvements in scaling laws.