Numerical Investigation of Propeller–Flap Interaction in Inclined Over-the-Wing Distributed-Propulsion Systems

Bölk, Sören; Vries, R. de; Arnhem, Nando van; Veldhuis, L.L.M.

doi:10.2514/6.2021-0603

Cited by 3 publications

(4 citation statements)

References 29 publications

(48 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This leads to a situation comparable to Ref. [19], where the propeller is located behind the suction peak over the flap hinge. It is assumed that, in this configuration, the suction induced upstream by the propeller allows the flow to remain attached without requiring a slot for a fresh boundary-layer on the flap.…”

Section: A) Otwdp Configuration (Top View) C) Conventional Configurat...mentioning

confidence: 70%

“…The values obtained at the bounds of the aerodynamic model are also applied to the flight-performance constraints that are performed with the flap deflected (take-off, approach, and balked landing). This is again considered a conservative approach, since earlier research has shown that an OTW propeller can postpone flow separation [18,19] and reduce the pressure drag [31] in the case of flap deflection, if the system is properly designed. Although these simplifying assumptions could not be verified within the scope of this research due to the sensitivity of high-lift performance to the Reynolds number and specific design of the high-lift system, they should be revisited once a more detailed investigation of the high-lift characteristics has been performed.…”

Section: Applicability and Limitations Of The Aerodynamic Modelmentioning

confidence: 99%

“…The deflection of the propeller in high-lift conditions can contribute to an effective lift increase due to thrust vectoring (see e.g. the Lilium concept [51]), as well as postpone flow separation [19]. However, even for 0.75 < x P /c < 1, changes in the axial propeller location can appreciably affect the performance of the OTWDP system [31].…”

Section: A) Otwdp Configuration (Top View) C) Conventional Configurat...mentioning

confidence: 99%

“…Moreover, over-the-wing propulsion can lead to reduced flyover noise if the wing shielding capabilities are exploited [17]. Additionally, if the OTWDP system is designed to induce a Coandă effect [18], or is inclined with the flap in low-speed conditions [19], flow separation can be postponed and the high-lift capabilities can also be increased. This combination of aerodynamic and acoustic benefits make OTWDP a suitable candidate to enhance the overall performance of regional HEP aircraft.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Vries

Vos

2023

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

The goal of this study is to analyze how the aeropropulsive benefits of an over-the-wing distributed-propulsion (OTWDP) system at the component level translate into an aeropropulsive benefit at the aircraft level, as well as to determine whether this enhancement is sufficient to lead to a reduction in overall energy consumption. For this, the preliminary sizing of a partial-turboelectric regional passenger aircraft is performed, and its performance metrics are compared to a conventional twin-turboprop reference for the 2035 timeframe. The changes in lift, drag, and propulsive efficiency due to the OTWDP system are estimated for a simplified unducted geometry using a lower-order numerical method, which is validated with experimental data. For a typical cruise condition and the baseline geometry evaluated in the experiment, the numerical method estimates a 45% increase in the local sectional lift-to-drag ratio of the wing, at the expense of a 12% reduction in propeller efficiency. For an aircraft with 53% of the wingspan covered by the OTWDP system, this aerodynamic coupling is found to increase the average aeropropulsive efficiency of the aircraft by 9% for a 1500 n mile mission. Approximately 4% of this benefit is required to offset the losses in the electrical drivetrain. The reduction in fuel weight compensates for the increase in powertrain weight, leading to a takeoff mass comparable to the reference aircraft. Overall, a 5% reduction in energy consumption is found, albeit with a [Formula: see text] uncertainty due to uncertainty in the aerodynamic modeling alone.

show abstract

Section: A) Otwdp Configuration (Top View) C) Conventional Configurat...mentioning

confidence: 70%

Section: Applicability and Limitations Of The Aerodynamic Modelmentioning

confidence: 99%

Section: A) Otwdp Configuration (Top View) C) Conventional Configurat...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Vries

Vos

2023

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

show abstract

Novel High-Precision and Efficient Momentum Source Method

et al. 2023

View full text Add to dashboard Cite

Effective and reliable slipstream numerical simulation methods are important for propeller-driven aircraft design. This paper presents a high-precision and efficient momentum source method (HPE-MSM) based on a novel actuator disk load prediction model established by the frozen rotor method and blade element momentum theory. The simulation results of two benchmark test cases of an isolated propeller and a typical turboprop airliner show that the accuracy of the HPE-MSM proposed in this paper is close to the time-averaged unsteady results of the sliding mesh method (SMM), with a maximum error of 5% in aircraft lift and drag coefficients compared with experimental values. Meanwhile, the calculation efficiency of the HPE-MSM is comparable to quasi-steady methods, with only about 3.4% of the computation resources of the SMM in the whole aircraft simulation. This novel approach achieves high-precision and efficient simulation of the slipstream, which has the potential to improve the design level of propeller-driven aircraft.

show abstract

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Vries

Vos

2022

AIAA SCITECH 2022 Forum

Self Cite

View full text Add to dashboard Cite

The goal of this study is to analyze how the aero-propulsive benefits of an over-the-wing distributed-propulsion (OTWDP) system at component level translate into an aero-propulsive benefit at aircraft level, and to determine whether this enhancement is sufficient to lead to a reduction in overall energy consumption. For this, the preliminary sizing of a partialturboelectric regional passenger aircraft is performed, and its performance metrics are compared to a conventional twin-turboprop reference for the 2035 timeframe. The changes in lift, drag, and propulsive efficiency due to the OTWDP system are estimated using a simplified numerical method, which is validated with experimental data. For a typical cruise condition and the baseline geometry evaluated in the experiment, the numerical method estimates a 45% increase in the local sectional lift-to-drag ratio of the wing, at the expense of a 12% reduction in propeller efficiency. For an aircraft with 53% of the wing span covered by the OTWDP system, this aerodynamic coupling is found to increase the average aero-propulsive efficiency of the aircraft by 9%, for a 1500 nmi mission. Approximately 4% of this benefit is required to offset the losses in the electrical drivetrain. The reduction in fuel weight compensates the increase in powertrain weight, leading to a take-off mass comparable to the reference aircraft. Overall, a 5% reduction in energy consumption is found, albeit with a ±5% uncertainty due to uncertainty in the aerodynamic modeling.

show abstract

Numerical Investigation of Propeller–Flap Interaction in Inclined Over-the-Wing Distributed-Propulsion Systems

Cited by 3 publications

References 29 publications

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Novel High-Precision and Efficient Momentum Source Method

Aerodynamic Performance Benefits of Over-the-Wing Distributed Propulsion for Hybrid-Electric Transport Aircraft

Contact Info

Product

Resources

About