Aerodynamic Investigations in the European Project ROSAS (Research on Silent Aircraft Concepts)

Brodersen, Olaf; Taupin, Karine; Maury, Eric; Spieweg, Rene; Lieser, Jan; Laban, M.; Godard, Jean-Luc; Vitagliano, Pier Luigi; Bigot, Pascal

doi:10.2514/6.2005-4891

Cited by 6 publications

(7 citation statements)

References 4 publications

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“…More recently, similar work were conducted in the frame of the EU-projects ROSAS and NACRE on rear fuselage mounted engine (RFME) configuration. However, in these studies the aerodynamic optimisations were conducted without multiple disciplines coupling [2].…”

Section: Introductionmentioning

confidence: 99%

Engine integration based on multi-disciplinary optimisation technique

Haar¹,

Brézillon²

2011

CEAS Aeronaut J

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The paper presents the work related to the engine integration of a Rear Fuselage Mounted Engine configuration in the frame of the DLR/Onera project MDOrmec ("Multi-Disciplinary Optimisation of Rear-fuselage Mounted Engine Configuration"). The developed multidisciplinary optimization process is based on a multi-level fidelity approach, where the aerodynamics is simulated using CFD methods while the weight and the handling qualities are assessed using preliminary design approach. Finally, the results of the optimisation are presented and discussed in detail.

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Section: Introductionmentioning

confidence: 99%

Engine integration based on multi-disciplinary optimisation technique

Haar¹,

Brézillon²

2011

CEAS Aeronaut J

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“…Analytical shaping using streamline tracing techniques in [8], Euler CFD in [4], and Navier-Stokes CFD in [9] resulted in significant flow quality and drag improvements to the OWN configurations studied, although the installation penalties were not always entirely eliminated. Aside from these studies, however, this sensitivity has generally not be fully exploited in much of the OWN wind-tunnel research because of hardware fabrication costs.…”

Section: Introductionmentioning

confidence: 90%

Aerodynamic Investigations of an Advanced Over-the-Wing Nacelle Transport Aircraft Configuration

Hill

Kandil

Hahn

2009

Journal of Aircraft

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The transonic aerodynamics of an advanced, over-the-wing nacelle, subsonic transport configuration are assessed using both Euler and Navier-Stokes computational fluid dynamics and results are compared to a similar configuration with an under-the-wing nacelle installation and a similar wing-body configuration. The over-the-wing nacelle configuration is designed with a novel inboard wing channel section between the nacelle and the fuselage that produces favorable aerodynamic interference and reduces the overall drag. Qualitative observations and quantitative drag computations are performed for the three configurations at a cruise Mach number of 0.78. It was found that, at the cruise point, the inboard wing channel section of the over-the-wing nacelle configuration effectively produces a favorable pressure distribution but that the overall drag, compared to the under-the-wing nacelle configuration, is higher. This excess drag, however, was found to be largely localized in the nacelle interior. Euler and Navier-Stokes computational fluid dynamics solutions were obtained for additional Mach numbers to assess the transonic drag-rise characteristics. The computational fluid dynamics solutions showed that the over-the-wing nacelle configuration has higher drag at lower Mach numbers than the under-the-wing nacelle configuration but experiences a milder overall drag rise and has lower drag at higher Mach numbers.

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“…To solve the BVP, the acoustic variables are split into known incident and unknown scattered parts. The incident portion of the field satisfies equations (1), (2), and (4) and provides the inhomogeneous source terms in the boundary condition (3). Details of the derivations, FSC solution methodology, applications, and validation with experimental data can be found in references 18-20. Mass conservation:…”

Section: Noise Scattering Modelmentioning

confidence: 99%

“…Results from that effort presented by Ricouard, et al 1 and Brodersen, et al 2 , included conventional fuselage and wing configurations with engines placed in unconventional locations. Other investigators have identified and/or developed noise reduction technology for the flying wing or blended-wing-body (BWB) concept, especially as part of NASA's Quiet Aircraft Technology Program 3 and the Silent Aircraft Initiative 4,5,6 funded by the British government and others.…”

Section: Introductionmentioning

confidence: 99%

The Low-Noise Potential of Distributed Propulsion on a Catamaran Aircraft

Posey

Tinetti

Dunn

2006

12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference)

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The noise shielding potential of an inboard-wing catamaran aircraft when coupled with distributed propulsion is examined. Here, only low-frequency jet noise from mid-wing-mounted engines is considered. Because low frequencies are the most difficult to shield, these calculations put a lower bound on the potential shielding benefit. In this proof-of-concept study, simple physical models are used to describe the 3-D scattering of jet noise by conceptualized catamaran aircraft. The Fast Scattering Code is used to predict noise levels on and about the aircraft. Shielding results are presented for several catamaran type geometries and simple noise source configurations representative of distributed propulsion radiation. Computational analyses are presented that demonstrate the shielding benefits of distributed propulsion and of increasing the width of the inboard wing. Also, sample calculations using the FSC are presented that demonstrate additional noise reduction on the aircraft fuselage by the use of acoustic liners on the inboard wing trailing edge. A full conceptual aircraft design would have to be analyzed over a complete mission to more accurately quantify community noise levels and aircraft performance, but the present shielding calculations show that a large acoustic benefit could be achieved by combining distributed propulsion and liner technology with a twin-fuselage planform.

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Aerodynamic Investigations in the European Project ROSAS (Research on Silent Aircraft Concepts)

Cited by 6 publications

References 4 publications

Engine integration based on multi-disciplinary optimisation technique

Engine integration based on multi-disciplinary optimisation technique

Aerodynamic Investigations of an Advanced Over-the-Wing Nacelle Transport Aircraft Configuration

The Low-Noise Potential of Distributed Propulsion on a Catamaran Aircraft

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