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Thursday, July 11 • 09:00 - 09:20
A PARAMETRIC STUDY ON WALL PRESSURE WAVENUMBER-SPECTRUM MODELS WITH APPLICATION TO AIRCRAFT FUSELAGE VIBRATION PREDICTION

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The wall pressure wavenumber spectra on an aircraft fuselage are calculated analytically and numerically through two-dimensional Fourier transform of the cross-spectral models. The coherence lengths in the streamwise and spanwise directions and the convection velocity required in the cross-spectral models are provided from a flight test with DLR's research aircraft ATRA-A320. A parametric study on the coherence lengths, the convection velocity and the flow angle is performed on the analytical wavenumber-spectrum formulation. The impact of the surface microphone array size and resolution, noise and window function on the derived wavenumber spectra is studied by comparing numerical with analytical results. The fuselage vibration according to different wavenumber-spectrum formulations and the measured spectra as excitation sources is calculated with Statistical Energy Analysis. The obtained vibration spectra in one-third octave bands are compared to the measured vibration spectra. The effect of the parametric changes in the wavenumber-spectral model on the resulting wavenumber spectra is illustrated. Furthermore, the impact of the wavenumber spectra change on the resulting vibration spectra is studied and discussed.

Moderators
ST

Stephan Tewes

Interior Noise Integration & Vibration, Airbus Operations GmbH

Authors

Thursday July 11, 2019 09:00 - 09:20 EDT
St-Laurent 6
  T03 Aero… aircrft noise & vibr., SS04 Aircr cabin noise & vibr cntrl