Numerical assessment of the vibration control effects of porous liners on an over-the-wing propeller configuration

Beck, Silja C.; Müller, Lars; Langer, Sabine

doi:10.1007/s13272-016-0186-3

Cited by 11 publications

(8 citation statements)

References 15 publications

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“…Another important receiver position is located in the interior of the aircraft cabin, i.e., the aircraft passengers. As new aircraft designs probably exhibit new aircraft layouts (e.g., the "gamechanger" used in this paper), the cabin noise will be influenced as well [8,[39][40][41][42]. For example, in the "gamechanger" layout the engines are mounted directly to the fuselage.…”

Section: Discussionmentioning

confidence: 99%

Aircraft Noise Assessment—From Single Components to Large Scenarios

Delfs¹,

Bertsch²,

Zellmann

et al. 2018

Energies

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Abstract:The strategic European paper "Flightpath 2050" claims dramatic reductions of noise for aviation transport scenarios in 2050: ". . . The perceived noise emission of flying aircraft is reduced by 65%. These are relative to the capabilities of typical new aircraft in 2000. . . ". There is a consensus among experts that these far reaching objectives cannot be accomplished by application of noise reduction technologies at the level of aircraft components only. Comparably drastic claims simultaneously expressed in Flightpath 2050 for carbon dioxide and NOX reduction underline the need for step changes in aircraft technologies and aircraft configurations. New aircraft concepts with entirely different propulsion concepts will emerge, including unconventional power supplies from renewable energy sources, ranging from electric over hybrid to synthetic fuels. Given this foreseen revolution in aircraft technology the question arises, how the noise impact of these new aircraft may be assessed. Within the present contribution, a multi-level, multi-fidelity approach is proposed which enables aircraft noise assessment. It is composed by coupling noise prediction methods at three different levels of detail. On the first level, high fidelity methods for predicting the aeroacoustic behavior of aircraft components (and installations) are required since in the early stages of the development of innovative noise reduction technology test data is not available. The results are transferred to the second level, where radiation patterns of entire conventional and future aircraft concepts are assembled and noise emissions for single aircraft are computed. In the third level, large scale scenarios with many aircraft are considered to accurately predict the noise exposure for receivers on the ground. It is shown that reasonable predictions of the ground noise exposure level may be obtained. Furthermore, even though simplifications and omissions are introduced, it is shown that the method is capable of transferring all relevant physical aspects through the levels.

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Section: Discussionmentioning

confidence: 99%

Aircraft Noise Assessment—From Single Components to Large Scenarios

Delfs¹,

Bertsch²,

Zellmann

et al. 2018

Energies

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“…Finally, due to the shielding effects of the wing, flyover noise can be reduced. 11,12 However, in the proposed configuration the propeller is subjected to increased inflow velocities and a vertical velocity gradient. This is detrimental for propeller efficiency 10,13 and leads to unsteady blade loading, thus increasing vibrations and noise production.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Marcus

Vries

Kulkarni

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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This paper addresses the aerodynamic performance and numerical modeling of overthe-wing propellers. Installing the propeller above a wing has the potential to increase wing lift-to-drag ratio, high-lift capabilities, and to reduce flyover noise. However, the prediction of its performance is difficult, since research on the aerodynamic interaction effects of over-the-wing propellers has been limited so far. For this reason, an exploratory wind tunnel campaign was performed with a wing featuring a fowler flap. A single propeller was installed above the wing at different chordwise locations and inclination angles. Wing surface-pressure and wake-pressure measurements showed strong, bilateral aerodynamic coupling between the propeller and wing. A configuration with the propeller attached to the flap showed wing lift increases of 8% and 3% in cruise and high-lift conditions, respectively. The key findings of the wind tunnel campaign were used to validate a low-fidelity numerical tool, which combines a non-uniform inflow blade-element model for the propeller, a panel method for the wing, and a vortex lattice model for the propeller slipstream. The numerical model was used to assess the effect of propeller axial location and diameter. Results indicated that the optimal axial propeller position is near the trailing edge of the wing, and that reducing the propeller diameter at constant thrust coefficient at this location is beneficial for distributed propulsion applications. The tool allows a rapid computation of over-the-wing propeller and wing performance in cruise conditions. This enables an efficient design space exploration during the conceptual design process of such configurations.

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“…The mechanical model of the fuselage is discretised by use of the Finite Element Method (FEM) for the structural and fluid domains in the interioir and weakly coupled to the exterior pressure loads by the CAA computations. 52,53 The work group's inhouse code elPaSo is applied as FE implementation. The final result will be the sound pressure level at the passenger's ear position.…”

Section: Volume Averaged Les Of Porous Materials (Sub Project A8)mentioning

confidence: 99%

Aircraft and technology for low noise short take-off and landing

Delfs

Appel

Bernicke

et al. 2017

35th AIAA Applied Aerodynamics Conference

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This paper discusses characteristic multidisciplinary issues related to quiet short takeoff and landing for civil transport aircraft with a typical short to medium range mission. The work reported here is focussing on the noise aspects and is embedded in the collaborative research centre CRC880 in Braunschweig, Germany. This long term aircraft research initiative focusses on a new transport aircraft segment for operation on airports with shorter runway length in commercial air transport. This calls for a community-friendly aircraft designed for operations much closer to the home of its passengers than today. This scenario sets challenging, seemingly contradictory aircraft technology requirements, namely those for extreme lift augmentation at low noise. The Research Centre CRC880 has therefore devised a range of technology projects that aim at significant noise reductions and at the generation of efficient and flexible high lift. The research also addresses flight dynamics of aircraft at takeoff and landing. Two companion papers, reporting about the research in the field of "Efficient high lift" 1 and "Flight dynamics" 2 complete the presentation of the CRC880. It is envisaged that in general significant noise reduction-compared to a reference turbofan driven aircraft of year 2000 technology-necessarily requires component noise reduction in combination with a low noise a/c concept. Results are presented from all the acoustics related projects of CRC880 which cover the aeroacoustic simulation of the source noise reduction by flow permeable materials, the characterization, development, manufacturing and operation of (porous) materials especially tailored to aeroacoustics, new UHBR turbofan arrangements for minimum exterior noise due to acoustic shielding as well as the prediction of jet noise vibration excitation of cabin noise by UHBR engines compared to conventional turbofans at cruise.

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Numerical assessment of the vibration control effects of porous liners on an over-the-wing propeller configuration

Cited by 11 publications

References 15 publications

Aircraft Noise Assessment—From Single Components to Large Scenarios

Aircraft Noise Assessment—From Single Components to Large Scenarios

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Aircraft and technology for low noise short take-off and landing

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