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Non-linear aeroelastic analysis in the time domain of high-aspect-ratio wings: Effect of chord and taper-ratio variation

Published online by Cambridge University Press:  20 September 2016

A. Suleman ,
F. Afonso ,
J. Vale ,
É. Oliveira  and
F. Lau
A. Suleman*
Affiliation:
Mechanical Engineering Department, University of Victoria British Columbia, Canada
F. Afonso
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa Lisboa, Portugal
J. Vale
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa Lisboa, Portugal
É. Oliveira
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa Lisboa, Portugal
F. Lau
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa Lisboa, Portugal
*
suleman@uvic.ca
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Abstract

Commercial jets usually have relatively low-aspect-ratio wings, in spite of the associated benefits of increasing the wing aspect-ratio, such as higher lift-to-drag ratios and ranges. This is partially explained by the fact that the wing becomes more flexible by increasing the aspect-ratio that results in higher deflections which can cause aeroelastic instability problems such as flutter. An aeroelastic computational framework capable of evaluating the effects of geometric non-linearities on the aeroelastic performance of high-aspect-ratio wings has been developed and validated using numerical and experimental data. In this work, the aeroelastic performance of a base wing model with 20 m span and 1 m chord is analysed and the effect of changing the wing chord or the taper-ratio is determined. The non-linear static aeroelastic equilibrium solutions are compared in terms of drag polar, root bending moment and natural frequencies, and the change in the flutter speed boundary is assessed as a function of aspect-ratio using a time-marching approach.

Keywords

Aeroelasticityaircraft designnon-linear aeroelasticityhigh-aspect-ratiowing chordand taper-ratio variation
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1235 , January 2017 , pp. 21 - 53
Copyright
Copyright © Royal Aeronautical Society 2016 

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