Article Details

Title · Authors · Abstract · Keywords · DOI · References

Nonlinear Flutter Response Analysis of High-Aspect-Ratio Flexible Wings Based on Partitioned Coupling Method

SHEN Yuyang

(AVIC Xi'an Aeronautical Computing Technique Research Institute, Xi'an 710068, China)

Section：Information Application · Vol. 2026, Issue 18 · Pages：188-193,198 · 2096-4706（2026）18-0188-07 · CLC number：TP39；V19 · Document code：A · DOI：10.19850/j.cnki.2096-4706.2026.18.034

Abstract

To accurately predict the flutter response of high-aspect-ratio flexible wings and analyze its influencing factors, this paper combines unsteady aerodynamics, structural dynamics, and Fluid-Structure Interaction (FSI). The open-source framework preCICE is adopted to integrate fluid and structural solvers, and a time-domain aeroelastic analysis method is established. The accuracy of the proposed method is verified through simulations of the two-dimensional FSI benchmark case Turek-Hron-FSI3, and the full transient flutter evolution process is reproduced for a high-aspect-ratio flexible wing. The results show that considering geometric nonlinearity and using C3D8I incompatible mode elements can control the simulation error of structural deformation within 0.1%. An increasing angle of attack enhances modal coupling and softens structural stiffness, thus significantly reducing the flutter speed.

Keywords

aeroelasticity; fluid-structure interaction; preCICE; Computational Fluid Dynamics; Computational Structural Dynamics; high-aspect-ratio flexible wing; modal coupling

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Funding

National Key Research and Development Program (2025YFB3003400)

About the authors

Shen Yuyang (2001-), male, Han ethnicity, from Deyang, Sichuan, master's student, research interests include computational fluid dynamics.