Abstract
The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.
Highlights
In static aeroelasticity analysis, the interaction between aerodynamics and structural deflections determines the wing bending and twist at every flight condition. e static aeroelastic deformation in the steady flight condition is of great importance because it governs the aerodynamic performance and flight control characteristics [1]
If the wing structure undergoes large deformation, the linear calculation may lead to inaccurate predictions. e nonlinear effect usually plays an important role in the structure dynamics [2, 3] and may be crucial in statics
According to the aerodynamic and structural models used in the nonlinear aeroelastic analysis, numerical models can be categorized into three levels, namely, low, medium, and high fidelity models [6]
Summary
The interaction between aerodynamics and structural deflections determines the wing bending and twist at every flight condition. e static aeroelastic deformation in the steady flight condition is of great importance because it governs the aerodynamic performance and flight control characteristics [1]. For the high-aspect-ratio wing model, the static and dynamic aeroelastic responses calculated by low fidelity model agree well with the experimental results [8, 9]. E nonlinear beam theory is capable of calculating the postcritical deformation of a compliant forward-swept wing, and its capability is validated by wind tunnel tests [10]. Ough the low fidelity model gives acceptable results of the static aeroelastic characteristics, the high fidelity model can generate more accurate results and detailed aerodynamic characteristics of the compliant forward-swept wing [22]. A feasible method based on single camera and DLTdv program is used to measure the wing tip displacement in the wind tunnel test. We make a comparison between the results of medium and high fidelity models in the aspects of accuracy and efficiency
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