Aeroacoustic Behaviour of a 1:11 Scale Airbus Model in the Open Anechoic Wind Tunnel CEPRA 19

Abstract

This paper presents the analysis of aeroacoustic experiments performed with an Airbus 1/11 scaled aircraft model in the open anechoic wind tunnel CEPRA 19. This study aimed at checking the aerodynamic condition on the wing and characterizing the airframe noise sources. The results have shown that the flight aerodynamic conditions can be well reproduced in the wind tunnel by adjusting slightly the model pitch angle for each configuration. The main noise sources have been localized using a 2D cross-shaped array of microphones. Near-field/farfield correlations have been performed in order to study the spectral shape of these sources, completed in high frequencies with the analysis of the signals of flush mounted transducers. Different behavior were exhibited between low and high frequency range, for the wing leading edge noise and in the slotted flap region. The wind tunnel data have been transposed at full scale: using a geometric scaling factor, or a one based on Amiet's model for slat noise prediction. Depending on the scaling method used, the transposed data surround the flight