Aerodynamic and Structural Behaviour of a Wing Equipped with a Winglet at Cruise

Hantrais-Gervois, Jean-Luc; Rapin, Marc

doi:10.2514/6.2006-1489

Cited by 7 publications

(7 citation statements)

References 3 publications

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“…In flight, during cruise, the twist changes by about 1 deg at the tip (see [2]). Aircraft models are usually stiffer than real aircraft, but similar deformations can be achieved in pressurized wind tunnels, where dynamic pressure is a parameter.…”

Section: B Flexibility In Experimental Fluid Dynamicsmentioning

confidence: 99%

Drag Polar Invariance with Flexibility

Hantrais-Gervois

Destarac

2015

Journal of Aircraft

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International audienceMOST modern transport aircraft wings exhibit high aspect ratios (typically nine), and consequently undergo large deformations between ground and cruise, and beyond. The most noticeable effect is bending.Alarge bendingmodificationwill strongly contribute to the twist law alteration, and twist is amajor aerodynamic parameter.Wind-tunnelmodels undergo smaller deformations than flying aircraft, but these are often by no means negligible. Their aerodynamic effects can be quantified in pressurized wind tunnels by changing dynamic pressure. They can also be modeled by aeroelastic computational simulations.A puzzling thing is that, often in wind-tunnel tests, the effect is obvious on CL(α), Cm(α), and CL(Cm) curves but almost indiscernible on CL(CD) drag polars. The same phenomenon can happen with numerical simulations comparing a rigid-wing polar and a flexible-wing polar.It is the purpose of this Note to explain under which conditions this phenomenon may take place

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Section: B Flexibility In Experimental Fluid Dynamicsmentioning

confidence: 99%

Drag Polar Invariance with Flexibility

Hantrais-Gervois

Destarac

2015

Journal of Aircraft

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“…In this study the aeroelastic issues were not considered because the device concept was built so as not to impact on the wing shape. A further step in the design process would be to include the static aeroelastic behaviour of the wing (12) during the aerodynamic shape optimisation. Such a methodology would enable the optimisation and precise evaluation of the net efficiency of the integrated wing and wing tip device.…”

Section: Discussionmentioning

confidence: 99%

“…Thus a precise numerical assessment requires accounting for the wing flexibility as in Ref. 12. Nevertheless, in the present study we investigated small devices meant to limit the changes in wing structural loading.…”

Section: Numerical Tools For the Design And Assessment Of A Wing Tip mentioning

confidence: 99%

Downward pointing winglet design and assessment within the M-DAW research project

Hantrais-Gervois¹,

Grenon²,

Mann³

et al. 2009

Aeronaut. j.

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The design and performance analysis of a wing tip device proposed within the M-DAW project by ONERA is presented. A proto-design process is described and the device was thoroughly assessed (mainly with Reynolds-Averaged Navier-Stokes simulations). The process was further explained through wind-tunnel tests at both low speed and high speed in the pressurised and cryogenic European transonic wind tunnel in Cologne. The device is a downward pointing winglet designed for a retrofit scenario (the wing could be modified only within the 96% – 100% bounds of the span). It was designed to keep the wing root bending moment of the clean wing at cruise unchanged so that the aerodynamic gains are the net gains provided by the device that can be directly installed without structural modifications of the wing.

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“…The consequence is a reduction of the local Angle of Attack (AoA) on the outermost part of the wing and on the winglet. In [30,31] it is shown that induced drag is reduced with nose up twist, that shifts the loading outward. Therefore, here the nose down deformation will lead to an increase of induced drag and a lift distributions shifted inward.…”

Section: Physical Analysis Of the Optimal Geometry: Focus On Cant Angle Effectmentioning

confidence: 99%

Assessment of the efficiency of an active winglet concept for a long-range aircraft

et al. 2020

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This paper presents the analysis of an active winglet concept applied to a long-range aircraft. The winglet is actuated along the longitudinal axis to control its cant angle. Due to aeroelastic effects, the wing twist changes and therefore impacts aircraft performance. As a consequence, this technology offers the opportunity to optimize aircraft performance throughout the flight. This ability will be evaluated using high-fidelity coupled aerodynamic and structural computations. The consideration of the wing flexibility and the impact of the winglet on the wing shape contributes to more accurate aerodynamic predictions. First, the winglet geometry is optimized for the cruise condition using surrogate models. The designed winglet reduces the drag with a limited impact on loads while ensuring the capability to change the wing tip twist through the control of the cant angle. Then, a mission analysis is performed to assess the benefits of the technology on a variety of flight conditions.

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Aerodynamic and Structural Behaviour of a Wing Equipped with a Winglet at Cruise

Cited by 7 publications

References 3 publications

Drag Polar Invariance with Flexibility

Drag Polar Invariance with Flexibility

Downward pointing winglet design and assessment within the M-DAW research project

Assessment of the efficiency of an active winglet concept for a long-range aircraft

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