Mid-Fidelity Approaches for the Non-Linear Aeroelastic Assessment of The Pazy Wing
Alessia BOVE, Giuseppe QUARANTA
Abstract. Predicting the non-linear aeroelastic behavior of very flexible structures and the limit cycle oscillations that often develop is a challenge. This work investigates the nonlinear aeroelastic behavior of the Pazy Wing to determine the nature of its LCOs by coupling a nonlinear structural beam model with different mid-fidelity aerodynamic methods: the vortex lattice method and the panel method. The results demonstrate that the limit cycle originates from nonlinear structural effects, rather than aerodynamic nonlinearities. While both methods successfully predict the onset of the phenomenon, this study highlights that only the panel method accurately estimates the oscillation amplitude when compared to experimental data. This underscores the fundamental role of 3D aerodynamic effects, which are underestimated by the vortex lattice. The study therefore provides clear guidance for selecting efficient models, recommending the coupling of a nonlinear structural model with 3D aerodynamics as the optimal approach for a correct assessment of LCO severity.
Keywords
Aeroelasticity, Limit Cycle, Panel Method, Vortex Lattice, Pazy Wing
Published online 7/20/2026, 6 pages
Copyright © 2026 by the author(s)
Published under license by Materials Research Forum LLC., Millersville PA, USA
Citation: Alessia BOVE, Giuseppe QUARANTA, Mid-Fidelity Approaches for the Non-Linear Aeroelastic Assessment of The Pazy Wing, Materials Research Proceedings, Vol. 69, pp 396-401, 2026
DOI: https://doi.org/10.21741/9781644904251-72
The article was published as article 72 of the book CEAS – AIDAA Conference 2025
Content from this work may be used under the terms of the Creative Commons Attribution 3.0 license. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI.
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