Aeropropulsive Coupling Investigation of Boundary Layer–Ingesting Distributed Electric Propulsion Aircraft
Publication: Journal of Aerospace Engineering
Volume 38, Issue 1
Abstract
Compared with conventional aircraft, distributed electric propulsion (DEP) aircraft are recognized for their potential to enhance aerodynamic performance and propulsive efficiency, positioning them as one of the most promising advancements in future aviation. This paper explores the aeropropulsive coupling effects in boundary layer–ingesting DEP aircraft through numerical simulation and ground mobile testing. It employs two computational techniques, i.e., the actuator disk boundary condition and the full blade model, to assess the DEP’s impact on wing aerodynamics and to evaluate the influence of the propulsors’ shroud and design parameters. Ground mobile testing and numerical simulations are conducted on a DEP aircraft. The findings indicate that, with DEP thrust, the wing reduces the drag coefficient by 16% compared with a conventional wing, over a range of small-to-medium angles of attack. This reduction is attributed to the DEP’s enhancement of the suction peak at the wing’s leading edge and the extension of the plateau in pressure distribution. Additionally, incorporating a shroud around the distributed propulsors leads to a 17% increase in mass flow and a 40% rise in net thrust. However, as fan speed increases, while lift and net thrust on the DEP wing increase, the lift-to-drag ratio and overall propulsive efficiency of the system diminish.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
This work was supported by the Fundamental Research Funds for the Central Universities (G2024KY05104).
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Published In
Journal of Aerospace Engineering
Volume 38 • Issue 1 • January 2025
Copyright
© 2024 American Society of Civil Engineers.
History
Received: Jan 8, 2024
Accepted: Jul 18, 2024
Published online: Oct 9, 2024
Published in print: Jan 1, 2025
Discussion open until: Mar 9, 2025
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