Synthesis of Aero-Propulsive Interaction Studies Applied to Conceptual Hybrid-Electric Aircraft Design

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This paper presents a synthesis of aero-propulsive interaction studies performed at Delft University of Technology, applied to conceptual aircraft designs with distributed hybrid-electric propulsion. The studied aero-propulsive interactions include tip-mounted propulsion, wing leading edge distributed propulsion and boundary-layer-ingestion combined with different aircraft layouts. This article starts with a description of the applied design framework and an overview of the models to include the aero-propulsive interactions as well as hybrid powertrains. Subsequently, applications of the different aero-propulsive interactions to several propulsion-system configurations are presented for configurations with distributed hybrid-electric propulsion with a partial turbo-electric (hybrid) powertrain. These case studies are sized for a set of top-level requirements covering the range from regional turboprop to typical narrow-body turbofan aircraft. The results identify directions of future detailed investigations and top-level requirements for more sustainable aircraft (in terms of fuel and energy consumption). Results indicate that lower shaft power ratios show better performance, with (unoptimized) DHEP technologies approaching their respective reference aircraft. The shaft power ratio has a significant effect on both PREE and MTOM, and it was shown that beyond 20% shaft power ratio, the PREE decreases and MTOM increases much more than between 10% and 20% indicating a possible local optimum between the latter two values as even lower values did not yield any significant improvements. Tip-mounted propulsion is constrained by the relatively high cruise Mach number of 0.6 by the tip Mach number. It is also shown that longer ranges lead to a higher PREE, especially for those aircraft with a secondary power train that over a longer cruise can overcome their mass penalties. At the high range case for Mach 0.5, it can be seen that the distributed propulsion systems show the largest improvement.
Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
Subtitle of host publication6-10 January 2020, Orlando, FL
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages25
ISBN (Electronic)978-1-62410-595-1
Publication statusPublished - 2020
EventAIAA Scitech 2020 Forum - Orlando, United States
Duration: 6 Jan 202010 Jan 2020


ConferenceAIAA Scitech 2020 Forum
CountryUnited States

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    Hoogreef, M., de Vries, R., Sinnige, T., & Vos, R. (2020). Synthesis of Aero-Propulsive Interaction Studies Applied to Conceptual Hybrid-Electric Aircraft Design. In AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL [AIAA 2020-0503] American Institute of Aeronautics and Astronautics Inc. (AIAA).