Aero-Propulsive and Propulsor Cross-Coupling Effects on a Distributed Propulsion System

Perry, Aaron T.; Ansell, Phillip J.; Kerho, Michael F.

doi:10.2514/6.2018-2051

Cited by 11 publications

(5 citation statements)

References 11 publications

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“…One noteworthy study among these is that of Wick, et al [42] where a variety of ducted fan/airfoil integrations were investigated numerically. Additionally, experimental work has been performed by Rolling Hills Research Corporation (El Segundo, California) and the University of Illinois at Urbana-Champaign (Urbana, Illinois) to characterize the aero-propulsive coupling effects on an array of ducted fans mounted on the upper-surface trailing-edge of an airfoil section [43,44]. An image of the airfoil test article used in this study and resulting influence of uniform throttle across all five electric ducted fans on the airfoil lift and drag performance are shown in Fig.…”

Section: Distributed Electric Propulsion Enabled Aero-propulsive Couplingmentioning

confidence: 99%

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

Kim

Perry

Ansell

2018

2018 AIAA/IEEE Electric Aircraft Technologies Symposium

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183

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The emergence of distributed electric propulsion (DEP) concepts for aircraft systems has enabled new capabilities in the overall efficiency, capabilities, and robustness of future air vehicles. Distributed electric propulsion systems feature the novel approach of utilizing electrically-driven propulsors which are only connected electrically to energy sources or power-generating devices. As a result, propulsors can be placed, sized, and operated with greater flexibility to leverage the synergistic benefits of aero-propulsive coupling and provide improved performance over more traditional designs. A number of conventional aircraft concepts that utilize distributed electric propulsion have been developed, along with various short and vertical takeoff and landing platforms. Careful integration of electrically-driven propulsors for boundary-layer ingestion can allow for improved propulsive efficiency and wake-filling benefits. The placement and configuration of propulsors can also be used to mitigate the trailing vortex system of a lifting surface or leverage increases in dynamic pressure across blown surfaces for increased lift performance. Additionally, the thrust stream of distributed electric propulsors can be utilized to enable new capabilities in vehicle control, including reducing requirements for traditional control surfaces and increasing tolerance of the vehicle control system to engine-out or propulsor-out scenarios. If one or more turboelectric generators and multiple electric fans are used, the increased effective bypass ratio of the whole propulsion system can also enable lower community noise during takeoff and landing segments of flight and higher propulsive efficiency at all conditions. Furthermore, the small propulsors of a DEP system can be installed to leverage an acoustic shielding effect by the airframe, which can further reduce noise signatures. The rapid growth in flight-weight electrical systems and power architectures has provided new enabling technologies for future DEP concepts, which provide flexible operational capabilities far beyond those of current systems. While a number of integration challenges exist, DEP is a disruptive concept that can lead to unprecedented improvements in future aircraft designs.

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Section: Distributed Electric Propulsion Enabled Aero-propulsive Couplingmentioning

confidence: 99%

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

Kim

Perry

Ansell

2018

2018 AIAA/IEEE Electric Aircraft Technologies Symposium

Self Cite

183

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“…The ducted fan at wing upper trailing edge configuration is the most investigated, see MIT H3.1, NASA N3-X and Lilium jet (Pieper, 2018). The benefits of this configuration are summarized by Perry et al (2018).…”

Section: Introductionmentioning

confidence: 99%

Aero-propulsive interaction model for conceptual distributed propulsion aircraft design

Awad

Stumpf

2022

AEAT

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Purpose This research aims to present an aero-propulsive interaction model applied to conceptual aircraft design with distributed electric propulsion (DeP). The developed model includes a series of electric ducted fans integrated into the wing upper trailing edge, taking into account the effect of boundary layer ingestion (BLI). The developed model aims to estimate the aerodynamic performance of the wing with DeP using an accurate low-order computational model, which can be easily used in the overall aircraft design's optimization process. Design/methodology/approach First, the ducted fan aerodynamic performance is investigated using a low-order computational model over a range of angle of attack required for conventional flight based on ducted fan design code program and analytical models. Subsequently, the aero-propulsive coupling with the wing is introduced. The DeP location chordwise is placed at the wing's trailing edge to have the full benefits of the BLI. After that, the propulsion integration process is introduced. The nacelle design's primary function is to minimize the losses due to distortion. Finally, the aerodynamic forces of the overall configuration are estimated based on Athena Vortex Lattice program and the developed ducted fan model. Findings The ducted fan model is validated with experimental measurements from the literature. Subsequently, the overall model, the wing with DeP, is validated with experimental measurements and computational fluid dynamics, both from the literature. The results reveal that the currently developed model successfully estimates the aerodynamic performance of DeP located at the wing trailing edge. Originality/value The developed model's value is to capture the aero-propulsive coupling accurately and fast enough to execute multiple times in the overall aircraft design's optimization loop without increasing runtime substantially.

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“…Moreover, compared to tractor propellers, OTW propellers overcome ground clearance limitations and have the potential to emit less noise to the ground due to shielding by the wing [16]. Although OTW propellers have been studied in channel-wing configurations since the early 1950s [17,18], the recent developments in the field of distributed propulsion have led to an increased interest in ducted OTW systems with reduced propeller diameter and an increased number of propulsors [19][20][21][22]. In these configurations, the array of propulsors can be installed near the trailing edge and deflected with the flap, further enhancing high-lift capabilities by means of thrust vectoring [10,11,19].…”

Section: Introductionmentioning

confidence: 99%