F. Di Verniere
info
Please Note
<p>This page displays the records of the person named above and is not linked to a unique person identifier. This record may need to be merged to a profile.</p>
2 records found
1
This work presents a high-fidelity aeroacoustic investigation of a distributed-propulsion eVTOL aircraft during representative urban air mobility departure operations. Three flight conditions are analyzed, namely vertical take-off, transition, and cruise in climb. The aerodynamic analysis highlights substantial differences in wake development and rotor–rotor interactions among the investigated configurations. For the particular vehicle configuration, cruise conditions are characterized by the ingestion of coherent wake structures by the tail-mounted propellers, resulting in significant unsteady loading fluctuations. The aeroacoustic analysis, performed using the permeable and solid formulations of the Ffowcs Williams–Hawkings integral equation, shows that the radiated noise is dominated by tonal components, with cruise conditions exhibiting blade passing frequency levels approximately 10 dB higher than the other configurations. Source identification analyses indicate that the dominant acoustic contribution is associated with the unsteady loading noise generated by the tail-mounted propellers due to wake ingestion. Finally, an on-ground footprint analysis based on a complete reference departure trajectory demonstrates compliance with current EASA certification limits, while also highlighting the strong sensitivity of the acoustic footprint to the transition maneuver. The results highlight the importance of rotor wake interactions in cruise conditions for short-aspect- ratio distributed-propulsion eVTOL configurations, where wake ingestion by downstream propellers significantly increases tonal noise levels and directly affects the resulting certification footprint. These findings emphasize the need to account for rotor interaction effects during both preliminary design and acoustic certification assessment.
...
This work presents a high-fidelity aeroacoustic investigation of a distributed-propulsion eVTOL aircraft during representative urban air mobility departure operations. Three flight conditions are analyzed, namely vertical take-off, transition, and cruise in climb. The aerodynamic analysis highlights substantial differences in wake development and rotor–rotor interactions among the investigated configurations. For the particular vehicle configuration, cruise conditions are characterized by the ingestion of coherent wake structures by the tail-mounted propellers, resulting in significant unsteady loading fluctuations. The aeroacoustic analysis, performed using the permeable and solid formulations of the Ffowcs Williams–Hawkings integral equation, shows that the radiated noise is dominated by tonal components, with cruise conditions exhibiting blade passing frequency levels approximately 10 dB higher than the other configurations. Source identification analyses indicate that the dominant acoustic contribution is associated with the unsteady loading noise generated by the tail-mounted propellers due to wake ingestion. Finally, an on-ground footprint analysis based on a complete reference departure trajectory demonstrates compliance with current EASA certification limits, while also highlighting the strong sensitivity of the acoustic footprint to the transition maneuver. The results highlight the importance of rotor wake interactions in cruise conditions for short-aspect- ratio distributed-propulsion eVTOL configurations, where wake ingestion by downstream propellers significantly increases tonal noise levels and directly affects the resulting certification footprint. These findings emphasize the need to account for rotor interaction effects during both preliminary design and acoustic certification assessment.
Conference paper
(2025)
-
Federico Di Verniere, Emanuele Sticchi, Damiano Casalino, Daniele Ragni, Riccardo Zamponi
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 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.