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Effects of Aero-Propulsive Coupling on High Solidity Electric Ducted Fan Performance for Various Wing Integrations

D.A. Safieh, J. Rauleder
The increase in population in urban areas and their surroundings, combined with inefficient and saturated land routes, have sparked a booming interest in regional and urban air transportation options. Electric Ducted Fans (EDF) are expected to help these new concepts meet the ambitious goals set by the aviation industry. While most boundary layer ingestion propulsion methods, like EDFs, have been extensively studied at a system level, little attention has been given to decoupling EDF forces for various wing integrations. This study focuses on understanding the changes in performance that various aero-propulsive integrations have on the EDF, comparing leading edge and trailing edge EDF integrations to an isolated EDF. For both integration cases, the EDF power loading increased over the isolated case. This increase was greater for the higher advance ratios. The leading edge integration pitching moment showed a growing destabilizing moment similar to that of the isolated thruster for the upper surface integration, but showed a constant destabilizing behavior (independent of angle of attack) for the lower surface. While the pitching moment of the isolated case was destabilizing and increased in magnitude with increased angle of attack, the pitching moment of the trailing edge integrated EDF was mostly constant. For the upper surface this moment is stabilizing while for the lower surface its destabilizing. This shows the importance of understanding the EDF's aerodynamic characteristics as they might affect the overall lifting system characteristics. A high-frequency analysis using a short-time Fourier transform (STFT) on the system pitching moment and inlet acoustic signature showed similar dominant frequencies for the isolated EDF and leading edge integration for both the loads and acoustic data, but revealed the existence of new high and low frequency transient loads for the trailing edge integration. Both integration methods showed increases in performance and power reduction. The trailing edge integrated EDF required 12% less power (max value) than the isolated EDF, while the leading edge integrated EDF required 8% less power (max value) for the same operational conditions.
49th European Rotorcraft Forum 2023, Bückeburg, 2023
Conference Paper
21,0 x 29,7 cm, 12 Pages
Published in:
DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-12; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

This Document is part of a superordinate publication:
49th European Rotorcraft Forum 2023 - Proceedings