Stall Behaviour of the EUROLIFT High Lift Configurations

Rudnik, Ralf

doi:10.2514/6.2008-836

Cited by 28 publications

(15 citation statements)

References 11 publications

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“…An increase of the slat cutout further weakens the flow in this area thereby limiting the maximum lift capability of the wing. Passive devices like strakes are a standard measure to counteract the separation [4,5] but are limited in effectiveness with increased slat cutout and nacelle size.…”

Section: Introductionmentioning

confidence: 99%

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Schloesser

Soudakov

Bauer³

et al. 2019

AIAA Journal

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Section: Introductionmentioning

confidence: 99%

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Schloesser

Soudakov

Bauer³

et al. 2019

AIAA Journal

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“…The wind tunnel tests were carried out on the DLR-F11 high lift configuration for low-Reynolds number conditions in the atmospheric wind tunnel of Airbus in Bremen. On the other side, investigations of the stall characteristics on this configuration revealed significant Reynolds number effects 49 . There is at present no evidence, to what extent the sensitive formation of the strake vortex, its spatial development and interference with the fixed wing boundary layer is affected by Reynolds number scaling effects.…”

Section:  Aerial Velocity Measurements Based On Pivmentioning

confidence: 89%

HINVA - High lift INflight VAlidation - Project Overview and Status

Rudnik

Reckzeh

Quest

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…To deal with the local flow separation described above, a passive flow control solution in the form of a strake was positioned on the nacelle [6,10]. However, this solution is insufficiently effective [6].…”

Section: Figure 1 Cfd Simulation Of Wing-nacelle Junction Showing Flmentioning

confidence: 99%

“…The close coupling of the nacelle, wing and slat complicates the flow and creates structures that significantly alter the direction and near-wall momentum of the flow, leading to local separations, reduced lift and increased drag [3][4][5]. As part of several European-Union-funded studies, the effects of this close coupling have been examined in several wind tunnel experiments [3,5,6] and Computational Fluid Dynamics (CFD) simulations [3,[7][8][9]. These studies show that the main harmful effects can be traced to a region downstream of the nacelle, between the inboard side of the pylon and the slats, where the flow is reversed (marked blue in Figure 1), and longitudinal vortices are prominent ( Figure 2).…”

Section: Introductionmentioning

confidence: 99%

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

Shay

Posti

Mizrahi

et al. 2020

Aiaa Aviation 2020 Forum

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An experimental study on the application of active flow control (AFC) to a 1:8.4 scale model of a swept wing in a landing configuration was conducted. The wing is fitted with an Ultra High Bypass Ratio (UHBR) engine nacelle. The highly efficient UHBR engines characterized by a large diameter that interferes with the flow around the wing, degrading its performance. An innovative active flow control device, creating steady suction and pulsed blowing (PB), was installed in the leading-edge region of the wing, above the nacelle, and its performance was experimentally evaluated. The effects of the suction and PB mechanisms were examined individually and simultaneously, using relevant normalized parameters to pave the way to a full-scale wind tunnel test. It was shown that the AFC devices increase the lift by up to 3%, redirected the flow to the desired downstream direction and reduced the size of the separation zone created due to the implementation of the UHBR nacelle. The next step is validating the small-scale results of this study in full-scale wind tunnel tests that hopefully make the technology flight test ready.

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Stall Behaviour of the EUROLIFT High Lift Configurations

Cited by 28 publications

References 11 publications

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

HINVA - High lift INflight VAlidation - Project Overview and Status

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

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