Correction notice The CL in the title of Fig. 7(b) was corrected from 0.4 in the original version to CL=1.0. (a) Climb local lift spanwise distribution at CL=1 0 0.2 0.4 0.6 0.8 1 0 5 10 10-3 0 0.2 0.4 0.6 0.8 1 0 5 10 10-3 (b) Solid line (suction side)-dashed line (pressure side) Fig. 7 Local lift coefficient distribution with a selected friction coefficient of one section.

A high-fidelity aeroacoustic simulation of a full-scale electric vertical take-off and landing vehicle was performed to investigate the transition maneuver from vertical ascent to forward flight. The study employed a Lattice Boltzmann method, enabling the resolution of complex unsteady aerodynamic phenomena while maintaining manageable computational costs. The analysis revealed that aerodynamic interactions between rotors, nacelles, and the wing significantly affect the distribution of aerodynamic forces, with rotor-wing interference playing a key role in lift and drag behavior. Acoustic emissions were evaluated in the far field using a permeable formulation of the Ffowcs Williams-Hawkings analogy on a spherical array representative of an urban air mobility operational context. The results highlighted clear directional patterns and a harmonic-dominated frequency spectrum. The findings offer critical insights into the coupled aerodynamic and acoustic behavior of eVTOLs during transition and provide a high-fidelity reference to support the validation of lower-order design tools.

A recently proposed far-field aerodynamic force theory based on the concepts of vortex force and Lamb vector is here considered to investigate on the unsteady aerodynamics of flapping wings. Vortical force formulations in the incompressible flow regime are derived, for inertial or non-inertial reference frames, in a form valid for both viscous and inviscid flows. Then a mixed inertial/non-inertial formulation, originally proposed for two-dimensional viscous flows, is extended to three-dimensional and to inviscid flow regimes and used to post-process numerical solutions for a NACA0012 airfoil in pure plunging motion. Results are compared to classical linear theories by Theodorsen-Mutchler (for lift) and Garrick (for drag/thrust), then an analysis of the different terms of the far-field formula is illustrated focusing on their contribution to the thrust force exerted on the flapping wing. Furthermore, the dependence of total force and its far-field decomposition on the choice of the integration domain is also analysed.