The aeroacoustic noise of a simplified wing-flap configuration placed in an open-jet anechoic wind tunnel has been investigated by compressible wall-resolved Large Eddy Simulations possibly coupled with Ffowcs Williams and Hawkings' acoustic analogy. The numerical domain includes the nozzle and the anechoic chamber, which allows taking the installation effects into account directly. The simulated span is the largest one simulated so far for this configuration and more generally at this high Reynolds number. The results of the simulation are validated with the extensive experimental database for the chosen configuration. Good overall agreement with experimental data is achieved for all mean and fluctuating velocities and wall pressures on the wing and the flap. Similar good predictions of the far-field acoustic pressure, using a hybrid approach, are achieved. The acoustic results obtained with the acoustic analogy are also compared with the numerical microphones placed in the far-field, showing a good agreement up to the mesh cut-off frequency. The obtained results show that the flap and wing trailing edges are the dominant noise sources, with significant diffraction effects on the flap side. Evidence of slight boundary-layer instabilities is also shown close to the flap trailing edge.
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