Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Xie, Chunhong; Meng, Yunxiao; Wang, Fei; Wan, Zhiqiang

doi:10.1155/2017/2564314

Cited by 6 publications

(1 citation statement)

References 23 publications

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“…e following static structural analysis should be carried out by nonlinear FEM; otherwise, the analysis will yield unrealistic result [15]. Generally speaking, the medium fidelity model is efficient in aeroelastic analysis, so it is widely used in the design optimization process [16,17].…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward‐Swept Wing Model

Ouyang

Zeng

Kou

et al. 2021

Shock and Vibration

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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.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward‐Swept Wing Model

Ouyang

Zeng

Kou

et al. 2021

Shock and Vibration

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Dynamic instability analysis of aeroelastic systems with application to aircraft wings

Al-Thehabey

2021

Physics of Fluids

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In this research, a set of computational algorithms have been developed to obtain a solution for steady and unsteady aeroelastic effects with specific applications to rectangular and swept aircraft wings. The solution includes calculation for the dynamic response and prediction for the occurrence of aeroelastic instability. Two aircraft wing models, under different combinations of flight conditions, were used in testing. Good results that match with those obtained in the lab have been observed, except in certain conditions where severe external conditions, such as shocks, flow separation, or transonic flow occurred. The results were also validated with multiple computational methods. For instance, the pressure coefficient, Cp, calculated with vortex lattice was also calculated with Woodward's method and showed good match. For the unsteady flow, the calculated pressure coefficient and phase angle were compared with the measured values obtained in the lab, and the calculated and experimental results were very close. The generalized aerodynamic force function (QRS) was determined using two different schemes: a direct formula using the interpolation technique and using the downwash vectors. Both schemes produced very close results. The transfer function was calculated using direct and closed form solutions, producing identical results. The instability calculation showed very close match: for case 3A, the flutter point occurred at dynamic pressure, frequency, and flutter velocity of 20.933 Hz, 0.9 Psi, and 566 fps, respectively, compared with measured values of 20.38 Hz, 0.924 Psi, and 565.8 fps. For case 3B, the results showed flutter occurring at (16.015, 0.605, and 973.2) vs (16.09, 0.62, and 973.4) measured.

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Overview of Computational Methods to Predict Flutter in Aircraft

Antimirova,

Jung,

Zhang

et al. 2024

Journal of Applied Mechanics

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Aeroelastic flutter is a dynamically complex phenomenon that has adverse and unstable effects on elastic structures. It is crucial to better predict the phenomenon of flutter within the scope of aircraft structures to improve upon the design of their wings. This review aims to establish fundamental guidelines for flutter analysis across subsonic, transonic, supersonic, and hypersonic flow regimes providing a thorough overview of established analytic, numerical, and reduced-order models as applicable to each flow regime. The review will shed light on the limitations and missing components within the previous literature on these flow regimes by highlighting the challenges involved in simulating flutter. Additionally, popular methods that employ the aforementioned analyses for optimizing wing structures under the effects of flutter, a subject currently garnering significant research attention, are also discussed. Our discussion offers new perspectives that encourages collaborative effort in the area of computational methods for flutter prediction and optimization.

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Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Cited by 6 publications

References 23 publications

Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward‐Swept Wing Model

Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward‐Swept Wing Model

Dynamic instability analysis of aeroelastic systems with application to aircraft wings

Overview of Computational Methods to Predict Flutter in Aircraft

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