Driven by increasing demands for a sustainable and ecofriendly future in aviation, Distributed Electric Propulsion (DEP) systems have received much attention for their high aerodynamic efficiency. DEP systems with lower noise emissions are desired by customers and policymakers and therefore it is important to understand the noise generation mechanism, propeller-propeller and propeller-wing interactions of DEP aeroacoustics. In this paper, the effect of flow conditions on the aeroacoustics of a propeller-wing integration is investigated numerically with various advance ratios. The integration consists of a Mejzlik 2-blade propeller installed on the leading edge of a NACA0018 airfoil. The propeller is designed using Clark-Y airfoil sections and a constant pitch with a pitch-to-diameter ratio of P/D = 0.5. Different rotating and forward-flight velocities are studied, corresponding to the advance ratio J ranging from 0.485 to 1.575. A hybrid computational aeroacoustics (CaAA) method is performed, where the near-field aeroacoustics is solved by compressible coarse-grid large-eddy simulations (LES), and the corresponding far-field acoustics is calculated by the Ffowcs Williams and Hawkings (FW-H) equation. The results have shown significant effects of the flow conditions on the propeller-wing integration in terms of the aerodynamic and acoustic features. The aerodynamic performance and near-field flow structures are investigated first. Then the sound generation from the propeller and wing is revealed respectively.

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