From the beginning of aviation designers are searching for methods and technologies for reducing the required fuel burn of commercial aircraft. Wingtip devices aim the reduction of induced drag, which is responsible for 30-40% of the total drag of a transport-aircraft at long-range cruise condition and for considerably downgrading the climb performance of an aircraft. Winglet alongside with tip tanks, raked wingtips, aligned fans belong to this class of devices. Better investigation in this field employing CFD tools and extensive wind-tunnel testing has allowed the rising of efficient winglet designs in recent times. Several of newly designed aircraft configurations embody winglets and many older ones are being retrofitted. However, there are discussions concerning the best cost/benefit of reducing induced drag of a transport plane with wingtip devices. Another big issue is the associated penalties to the configuration caused by winglets when compared to a simple wingtip extension. This paper addresses some of these issues based on the expertise obtained designing winglets for several aircraft configurations, ranging from a business jet and a twinjet airliner for 70 passengers to an AEW&C military airplane.

Considerations About Winglet Design

This article presents the preparation of a working physical mock-up wingtip device with morphing functionality. The objective of the mechanical demonstrator is to achieve a technology readiness level to establish confidence that one would proceed to an in-service R&D initiative. To establish the feasibility of scalable technology integration for product development, a tier schedule is employed to demonstrate material compliance, mechanism kinematics and perform bandwidth experimentation. Potential composite materials for design of flexible skins (i.e., Hexweb® , Kevlar® 49 and HexPly® ) were assessed using a spectrum of experimental verification procedures. These results are embodied to benchmark qualitatively and quantitatively the mechanical performance of the potential materials to use in a preliminary optimized morphing schedule.© 2008 ASME

/pdf/technology-integration-for-active-poly-morphing-winglets-29o5r67hjp.pdf

Technology Integration for Active Poly-Morphing Winglets Development

Multidisciplinary Design Optimization (MDO) has been performed on the retrofitting of a morphing wing system to an existing conventionally designed commercial passenger jet. Refined studies have been undertaken in order to confirm initial findings using high-end, low-fidelity aero-structural analysis together with a full engine model and integrated operational performance algorithm

Multidisciplinary design optimization of an active nonplanar polymorphing wing

An increasing number of aircraft is equipped with wing tip devices, which either are installed by the aircraft manufacturer at the production line or are retrofitted after the delivery of the aircraft to its operator. The installation of wing tip devices has not been a popular choice for regional turboprop aircraft, and the novelty of the current study is to investigate the feasibility of retrofitting the British Aerospace (BAe) Jetstream 31 with an appropriate wing tip device (or winglet) to increase its cruise range performance, taking also into account the aerodynamic and structural impact of the implementation. An aircraft model has been developed, and the simulated optimal winglet design achieved a 2.38% increase of the maximum range by reducing the total drag by 1.19% at a mass penalty of 3.25%, as compared with the baseline aircraft configuration. Other designs were found to be more effective in reducing the total drag, but the structural reinforcement required for their implementation outweighed the achieved performance improvements. Since successful winglet retrofit programs for typical short to medium-range narrow-body aircraft report even more than 3% of block fuel improvements, undertaking the project of installing an optimal winglet design to the BAe Jetstream 31 should also consider a direct operating cost (DOC) assessment on top of the aerodynamic and structural aspects of the retrofit.

https://www.mdpi.com/2226-4310/6/10/107/pdf

Conceptual Design and Performance Optimization of a Tip Device for a Regional Turboprop Aircraft

This article presents an optimisation-driven design approach of skins on a wingtip device with morphing functionality to meet operational performance criteria. The aim of the research is to determine material compliance by means of corrugated skin shapes that permit tailored exibility both in the chord and span wise direction whilst still maintaining sucient structural strength to withstand aerodynamic loading. Additional design targets and restrictions include global mass of the morphing skin, global buckling, laminate strength, peak stress and manufacturing constraints in order to translate numerical solution into a production feasible sheet metal and composite solution. Nomenclature HA horizontal amplitude of corrugation geometry HO horizontal oset of corrugation geometry t free parameter in Bezier function VA vertical amplitude of corrugation geometry VO vertical oset of corrugation geometry W relative point weighting of corrugation geometry

Optimisation of a Corrugated Skin for a Morphable Winglet

737–800 Winglet Integration

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737–800 Winglet Integration