The turbulent boundary layer (TBL) pressure fluctuations represent a dominant source of aircraft interior noise during cruise. The wavenumber-frequency characteristics of the TBL pressure field become important when determining its coupling with the aircraft structure and the resulting sound radiation into the interior of the aircraft. A technique is presented to estimate the TBL pressure wavenumber-frequency spectrum using a fixed probe pair consisting of two microphones. Flight test data from the McDonnel Douglas Ultra High Bypass Demonstrator aircraft were used to estimate the TBL pressure wavenumber-frequency spectra. These data were compared with selected wall pressure prediction models based on the existing wind tunnel data. The estimated in-flight spectral levels for the Demonstrator aircraft were in good agreement with the TBL wall pressure prediction models in the medium wavenumber range. The estimated TBL wavenumber spectral levels were found to be on the higher side in the low wavenumber region when compared with the predicted levels.
Estimation of the turbulent boundary layer pressure wavenumber-frequency spectrum using a fixed probe pair
1990-10-01
Conference paper
No indication
English
Wavenumber-Frequency Response of a Panel Excited by Turbulent Boundary Layer Pressure Field
British Library Conference Proceedings | 1995
|A Comparison of Models for the Wavenumber-Frequency Spectrum of Turbulent Boundary-Layer Pressures
British Library Conference Proceedings | 1995
|