Aerodynamic Investigation of a General Aviation Aircraft with Distributed Electric Propulsion

Shi, Jin; Zhou, Jun; Wu, Liaoni

doi:10.1109/aeeca52519.2021.9574397

Cited by 2 publications

(1 citation statement)

References 3 publications

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“…Therefore, this subsection utilizes computational fluid dynamics numerical simulation to analyze the effect of propeller slipstream on the aerodynamic force of the wing. There are two main methods to study the propeller and its slipstream effect through numerical simulation [38,39]:…”

Section: Numerical Computational Analysismentioning

confidence: 99%

Distributed Hybrid Electric Propulsion Aircraft Design Based on Convex Optimized Power Allocation Management

Xiao,

Tan,

Zhang

et al. 2024

Aerospace

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In order to ensure that aircraft have medium and long-range flights, enhanced aerodynamic performance, and reduced fuel consumption, this paper presents an original Distributed Hybrid Electric Propulsion Aircraft (DHEPA) design scheme and proposes a novel power allocation management method based on convex optimization. Firstly, by taking the Tecnam P2006T general-purpose aircraft as a reference, key components of DHEPA are selected and modeled. Then, a power allocation management method for DHEPA is proposed on the basis of convex optimization, which takes the minimum fuel consumption as the performance index to realize the reasonable power allocation of the battery and engine, while avoiding sliding into the local optimum of allocation. Finally, momentum theory and numerical simulation methods are used to analyze the aerodynamic enhancement effect of the propeller on the wing in the DHEPA, and a dynamics method is utilized to calculate the dynamics performance of the aircraft at several important stages. The results show that, compared with the reference aircraft, the lift of the DHEPA is increased by 46%. Under typical sectors, the DHEPA has a higher rate of climb and maximum leveling off speed at cruise, and a significantly lower fuel consumption.

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Section: Numerical Computational Analysismentioning

confidence: 99%

Distributed Hybrid Electric Propulsion Aircraft Design Based on Convex Optimized Power Allocation Management

Xiao,

Tan,

Zhang

et al. 2024

Aerospace

View full text Add to dashboard Cite

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Conceptual Design and Optimization of Distributed Electric Propulsion General Aviation Aircraft

Gao

et al. 2023

Aerospace

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The interaction between the slipstream of the propellers and the wing of an aircraft with distributed electric propulsion (DEP) could benefit aerodynamics. A conceptual design and optimization are carried out in order to increase the range of an electric general aviation aircraft without affecting its takeoff and landing velocity in the same fuselage condition. Propellers are modelled using the actuator disk (AD) theory, and the aircraft is modelled using the vortex lattice method (VLM) to obtain DEP aircraft’s aerodynamics in conceptual design. The DIRECT method is used for global optimization. To concentrate on the layout of the propellers and wing, a propeller with the same chord distribution, twist distribution, and number of blades is selected. The design and optimization of DEP aircraft’s range is carried out with the objective of achieving the maximum product of the lift–drag ratio with propeller efficiency under force balance constrains. Additionally, to decrease the takeoff and landing distance, the DEP aircraft’s takeoff and landing performance are optimized with the objective of the smallest velocity at an angle near the tail down angle under the constrains of acceleration bigger than 0 and a Mach number at the tip of blades smaller than 0.7. The CFD simulation was used to confirm the DEP aircraft’s pretty accurate aerodynamics. Compared to the reference aircraft, the improved DEP aircraft with 10 high-lift propellers on the leading edge of the wing and 2 wing-tip propellers may boost cruise performance by 6% while maintaining takeoff and landing velocity. Furthermore, it has been shown that the stall speed of DEP aircraft with smaller wings would rise proportionally when compared to conventional design aircraft, and the power need of DEP aircraft will be increased as a result of the operation of high-lift propellers. The conceptual design and optimal approach suggested in this work has some reference value for the design and research of the fixed-wing DEP general aviation aircraft.

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Aerodynamic Investigation of a General Aviation Aircraft with Distributed Electric Propulsion

Cited by 2 publications

References 3 publications

Distributed Hybrid Electric Propulsion Aircraft Design Based on Convex Optimized Power Allocation Management

Distributed Hybrid Electric Propulsion Aircraft Design Based on Convex Optimized Power Allocation Management

Conceptual Design and Optimization of Distributed Electric Propulsion General Aviation Aircraft

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