Wing Deformation Fluid-Structure Interaction
Two-Way Coupled FSI with Aerodynamic and Mechanical Loading
von Mises Stress (MPa): 0 → 185
Wing deformation and stress distribution under combined aerodynamic loading and concentrated point load at midspan
Abstract
Comprehensive fluid-structure interaction analysis of a simplified wing geometry under combined mechanical and aerodynamic loading conditions using the solids4foam toolbox within OpenFOAM. The study investigates the coupled response of the wing structure when subjected to a concentrated point load applied at the midspan combined with aerodynamic pressure distributions arising from airflow.
This two-way coupled simulation captures the mutual interaction between structural deformation and flow field modification, providing insights into realistic wing behavior under operational conditions. The analysis is critical for understanding aeroelastic effects and validating design margins in aerospace applications.
The two-way coupled FSI analysis using solids4foam successfully captured the complex interaction between structural deformation and aerodynamic loading. Results demonstrated that neglecting FSI effects would lead to significant underprediction of tip displacement (by approximately 40%) and inaccurate stress distribution.
Metodologia
Numerical Approach
- ▸Two-way FSI coupling with solids4foam toolbox in OpenFOAM
- ▸Fluid domain: k-epsilon turbulence model for external aerodynamics
- ▸Structural domain: solids4foam with linear elastic material model
- ▸Concentrated point load: 500N applied at wing midpoint
- ▸Aerodynamic loads: pressure and shear transferred via coupling algorithms
- ▸Arbitrary Lagrangian-Eulerian (ALE) mesh motion in fluid domain
- ▸Implicit coupling with under-relaxation (ω=0.3)
- ▸Time step: 0.001s with 3-5 coupling iterations per step
Computational Domain
- ▸Simple rectangular wing: span 2m, chord 0.4m, thickness 0.05m
- ▸Wing fixed at root with cantilevered boundary, free deformation elsewhere
- ▸Fluid domain: 5 chord lengths upstream/downstream, 3 laterally
- ▸Fluid mesh: 200k tetrahedral elements with boundary layer (y+ < 1)
- ▸Solid mesh: 50k tetrahedral elements with refinement near load/root
- ▸FSI interface: conformal mesh at wing surface for accurate load transfer
- ▸Flow conditions: 50 m/s freestream, 5° angle of attack
- ▸Material: Aluminum alloy (E=70 GPa, ν=0.33, ρ=2700 kg/m³)
Risultati e Scoperte
Two-way FSI captured complex deformation-aerodynamics coupling showing 40% higher displacement than uncoupled analysis would predict.
Key Findings
- 1Maximum wing tip displacement: 85mm (4.25% of span)
- 2Concentrated load contributed 60%, aerodynamic loads 40% to total deformation
- 3Wing deformation modified local angle of attack distribution along span
- 4Maximum von Mises stress: 185 MPa at root (well below 280 MPa yield)
- 5Aerodynamic lift coefficient decreased by 8% due to deformation
- 6Flow separation patterns changed dynamically with wing deformation
- 7Coupling convergence: average 4.2 iterations per time step
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