Reducing Induced Drag and Maneuver Loads by Active Aeroelastic Alteration

Lin, Jen‐Wei

doi:10.2514/1.c033701

Cited by 4 publications

(2 citation statements)

References 15 publications

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“…5–7 Since these multiple surfaces are redundant in the context of trimming the aircraft for cruise or maneuvers, they can be harnessed for additional benefits in the form of drag reduction and/or load alleviation. 8–10…”

Section: Introductionmentioning

confidence: 99%

“…[5][6][7] Since these multiple surfaces are redundant in the context of trimming the aircraft for cruise or maneuvers, they can be harnessed for additional benefits in the form of drag reduction and/or load alleviation. [8][9][10] In Ref. 6, the large AR Goland wing and a low AR fighter wing were made adaptive by incorporating a large number of trailing edge flaps into them À20 per half wing to be precise.…”

Section: Introductionmentioning

confidence: 99%

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Aerostructural performance improvement in an unmanned long endurance aircraft using adaptive wing concept

Sampath

Padmanabhan

Kattimani

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents an analytical research study to improve the aerostructural performance of an unmanned medium altitude long endurance aircraft using the adaptive wing concept. Aerodynamic drag and wing root loads are minimized by optimal scheduling of multiple trailing edge flaps located on the wing. A trim optimization process is developed specifically for this purpose. The aeroelastic model is based on finite element formulation for the structure and doublet lattice method for the aerodynamics. A nonlinear numerical lifting line method is used, in combination with airfoil wind tunnel data, to estimate the induced and total drags. Results are presented for the current aircraft configuration and a more flexible proposed configuration, thereby providing an uncommon perspective on the effect of flexibility on the adaptive wing. For example, the benefits of optimal flap deployment turn out to be greater for the flexible aircraft than for the rigid one. It is hoped that this work and its insights will also aid the multidisciplinary design optimization of future aircraft.

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