Aero-Propulsive and Aero-Structural Design Integration of Turboprop Aircraft with Electric Wingtip-Mounted Propellers

Leer, Quinty Van der; Hoogreef, M.F.M.

doi:10.2514/6.2022-0167

Cited by 3 publications

(6 citation statements)

References 19 publications

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“…The uncertainty of the slipstream model grows with chordwise discretisation since the odd solution in the Rethorst method is neglected. This assumption is in line with previous literature that uses the Rethorst method [16][17][18]22] but should be noted as a model-limitation. A Weissinger VLM is shown in Figure 3, as taken from Nederlof [18].…”

Section: Wing Modelsupporting

confidence: 85%

“…Several authors (Willemsen [17], Nederlof [16,18], and van der Leer [19]) have used the Rethorst correction in their studies and have verified the numerical results by comparing to either CFD (Willemsen [17], Nederlof [16]) or experimental (van der Leer [19]) data. However, before the Rethorst model can be used, its requirements (and limitations) must be identified.…”

Section: Slipstream Modelmentioning

confidence: 99%

“…• The propeller introduces a velocity distribution, where Rethorst assumes a velocity step increment. Van der Leer and Hoogreef [19] and Prabhu [21] showed that the Rethorst correction is suitable for super positioning: combining several slipstreams, varying in diameter and velocity increment, or decrement, creates a velocity distribution.…”

Section: Slipstream Modelmentioning

confidence: 99%

“…The former two are a simplified version of the coupled optimization. The optimization statement for isolated wing and propeller optimization are given by Equation (22) and Equation (23), respectively. The design vector for the wing optimization contains x wing = [𝜙, c, 𝑡], where the propeller optimization has design vector…”

Section: Optimization Formulationsmentioning

confidence: 99%

See 3 more Smart Citations

Rapid Aerostructural Optimization of Wing-Propeller Systems

Exalto,

Pacini,

Kaneko

et al. 2024

AIAA SCITECH 2024 Forum

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Propeller-wing configurations are expected to return to the aviation industry due to their high propulsive efficiency and applicability in urban and regional air mobility. A knowledge gap exists around wing-propeller optimization because of the complexity of the propeller-wing system and the absence of a computationally efficient way to assess the coupled system. This paper addresses this gap by providing and validating a computationally efficient, mid-fidelity framework. The paper presents optimization results and recommendations for future iterations of the framework. The TU Delft PROWIM propeller is optimized with the framework, comparing sequential isolated optimization, trim optimization, and fully coupled optimization. The studies gives a conservative estimate of the efficiency gains that can be achieved by using coupled optimization, as compared to isolated optimization. Lastly, recommendations are given for future studies, such as including a battery weight model and including swirl velocities. It is expected that such model additions will affect the optimization results, and further emphasize the importance of coupled aerostructural optimization.

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Section: Wing Modelsupporting

confidence: 85%

Section: Slipstream Modelmentioning

confidence: 99%

Section: Slipstream Modelmentioning

confidence: 99%

Section: Optimization Formulationsmentioning

confidence: 99%

See 2 more Smart Citations

Rapid Aerostructural Optimization of Wing-Propeller Systems

Exalto,

Pacini,

Kaneko

et al. 2024

AIAA SCITECH 2024 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…Concerning the wing, load cases account for the discrete loads of engine and wing-mounted components but not for aero-propulsive interactions, such that the aerodynamic loads are that of a 'clean' wing, without any propeller interaction. This approximation was shown to be acceptable [9] with only a minor impact on wing mass (below 1%). Overall, the Initiator should not be comprehended as a tool for the quantitative estimation of KPIs.…”

Section: A System-level Modelingmentioning

confidence: 96%

Distributed Hybrid-Electric Propulsion Benefits for Span-Limited Aircraft

Bonnin

Hoogreef

Vries

2023

AIAA SCITECH 2023 Forum

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The impact of the ICAO code C gate span limit is assessed on the sizing of a serial Hybrid-Electric Aircraft (HEA) of increasing Degree of Hybridization (DoH). For a set of Top Level Aircraft Requirements (TLARs) similar to the ATR-42, it is shown that the increase in MTOM due to the presence of the battery is such that only a maximum DoH under 30% can be achieved before the wing span of the serial HEA reaches the 36 meters gate size. The same aircraft is fitted with Leading Edge Distributed Propulsion (LEDP) to increase the wing loading and relieve the span constraint, though this introduces limitations regarding the available wing volume. It is shown that a combination of high wing loading and of low volumetric energy density for batteries compared to jet fuel can lead to the available wing volume being too small for the required volume of the energy carriers. Finally a value in wing loading is found which simultaneously meets the span and wing-volume constraints. The higher DoH enabled by LEDP leads results in a 33% reduction in fuel burn compared to the fuel-based reference aircraft, while the overall energy consumption is increased by 6%.

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Dual-Solver Hybrid Computational Approach to Integrated Propulsion Aerodynamics

Moushegian

Smith

2023

Journal of Aircraft

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The demand for high-efficiency air vehicles and the development of distributed electric propulsion systems for aircraft are exposing the need for accurate aerodynamic prediction of multiple integrated propulsion systems. Conventional high-fidelity computational methods are too expensive, and low-cost low-fidelity methods make too many aerodynamic assumptions to be applied to these analyses. Dual-solver hybrid computational fluid dynamics (CFD) methods bridge the gap between these two categories of solvers, but many lack capabilities that are needed for complex vehicles. Recent improvements to the hybrid solver OVERFLOW-CHARM provide efficient and accurate analysis of integrated propulsion systems with hybrid CFD methods, as demonstrated on the wing–propeller system of the AIAA Workshop for Integrated Propeller Prediction. Predictions of propeller thrust are within 1% of conventional CFD data, and wing pressure coefficient distributions agree well with both experimental data and conventional CFD methods. The dual-solver results were obtained at half the computational cost of the full CFD simulation.

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Aero-Propulsive and Aero-Structural Design Integration of Turboprop Aircraft with Electric Wingtip-Mounted Propellers

Cited by 3 publications

References 19 publications

Rapid Aerostructural Optimization of Wing-Propeller Systems

Rapid Aerostructural Optimization of Wing-Propeller Systems

Distributed Hybrid-Electric Propulsion Benefits for Span-Limited Aircraft

Dual-Solver Hybrid Computational Approach to Integrated Propulsion Aerodynamics

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