Coupled fluid structure analysis for wing 445.6 flutter using a fast dynamic mesh technology

Zhong, Jize; Zhou, Xu

doi:10.1080/10618562.2016.1254201

Cited by 9 publications

(5 citation statements)

References 31 publications

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“…The elastic modulus in the wingspan and chord directions are 3.151 GPa and 0.416 GPa, respectively, and the shear modulus is 0.4392 GPa. The Poisson's ratio is 0.31 (Zhong and Xu, 2016). The structural model, shown in Figure 1(a), consists of 231 nodes and 200 elements.…”

Section: Numerical Results and Discussionmentioning

confidence: 99%

An efficient evaluation method for wing fuel mass variations effect on transonic aeroelasticity

Wang

Ronch

et al. 2022

AEAT

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Purpose This paper aims to develop an efficient evaluation method to more intuitively and effectively investigate the influence of the wing fuel mass variations because of fuel burn on transonic aeroelasticity. Design/methodology/approach The proposed efficient aeroelastic evaluation method is developed by extending the standard computational fluid dynamics (CFD)-based proper orthogonal decomposition (POD)/reduced order model (ROM). Findings The results of this paper show that the proposed aeroelastic efficient evaluation method can accurately and efficiently predict the aeroelastic response and flutter boundary when the wing fuel mass vary because of fuel burn. It also shows that the wing fuel mass variations have a significant effect on transonic aeroelasticity; the flutter speed increases as the wing fuel mass decreases. Without rebuilding an expensive, time-consuming CFD-based POD/ROM for each wing fuel mass variation, the computational cost of the proposed method is reduced obviously. It also shows that the computational efficiency improvement grows linearly with the number of model cases. Practical implications The paper presents a potentially powerful tool to more intuitively and effectively investigate the influence of the wing fuel mass variation on transonic aeroelasticity, and the results form a theoretical and methodological basis for further research. Originality/value The proposed evaluation method makes it a reality to apply the efficient standard CFD-based POD/ROM to investigate the influence of the wing fuel mass variation because of fuel burn on transonic aeroelasticity. The proposed efficient aeroelastic evaluation method, therefore, is ideally suited to deal with the investigation of the influence of wing fuel mass variations on transonic aeroelasticity and may have the potential to reduce the overall cost of aircraft design.

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Section: Numerical Results and Discussionmentioning

confidence: 99%

An efficient evaluation method for wing fuel mass variations effect on transonic aeroelasticity

Wang

Ronch

et al. 2022

AEAT

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“…Due to its universal applicability, the dynamic‐mesh approach has found broad implementation in various sectors. Applied examples of the dynamic‐mesh module include aircraft projectiles 49, 50, ship motion 51, valve operation 52, wings dynamics 53, 54, rocket separation 55, parachute and balloon dynamics 56, heart valves 57, and bionic engineering 58. During the simulation, the motion of the mesh will cause the quality of the meshes to deteriorate (especially for structural meshes, like hexahedral meshes), such as the skewness of a mesh element, resulting in the simulation convergence to fail.…”

Section: Methodsmentioning

confidence: 99%

Analysis of Hydrocyclone Geometry via Rapid Optimization Based on Computational Fluid Dynamics

et al. 2021

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Hydrocyclones exploit density gradients for the centrifugal separation of dispersions in a continuous liquid. Selection of the geometrics for optimal separation is case specific, like the media characteristics. The existing optimization method based on computational fluid dynamics (CFD) provides a powerful analytical tool but requires long computational times. The most common praxis for CFD optimization is via the single‐factor optimization method (SFOM). In this study, a novel approach is presented as an improved rapid optimization method that implements a dynamic‐mesh and user‐defined function optimization method (DUOM). The DUOM adapts the dynamic‐mesh approach from other applications to the optimization analysis of hydrocyclones. The DUOM reduced the computational time by 31.1 %, compared to the SFOM.

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“…The elastic modulus in the span-wise direction and the chord-wise direction is 3.151 and 0.416 GPa, respectively. The shear modulus is 0.4392 GPa, the Poissons ratio is 0.31 (Zhong and Xu, 2016). The structural model, shown in Fig.…”

Section: Pod/rom Solver Validationmentioning

confidence: 97%

An efficient implementation of aeroelastic tailoring based on efficient computational fluid dynamics-based reduced order model

Gong

Ronch

et al. 2019

Journal of Fluids and Structures

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Current and future trends in the aerospace industry leverage on the potential benefits provided by lightweight materials that can be tailored to realize desired mechanical characteristics when loaded. For aircraft design, the deployment of aeroelastic tailoring is hindered by the need to re-compute, for any possible modification of the structure, the dependence of the aerodynamic field on the underlying structural properties. To make progress in this direction, the work presents a rapid computational fluid dynamics based aeroelastic tool which is built around a reduced order model for the aerodynamics that is updated for any modification of the structure by using the structural dynamics reanalysis method. The aeroelastic tailoring tool is demonstrated in transonic flow for the AGARD 445.6 wing, suitably modified with composite materials. It was found that the proposed method provides accurate engineering predictions for the aeroelastic response and stability when the structure is modified from the baseline model.

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Coupled fluid structure analysis for wing 445.6 flutter using a fast dynamic mesh technology

Cited by 9 publications

References 31 publications

An efficient evaluation method for wing fuel mass variations effect on transonic aeroelasticity

An efficient evaluation method for wing fuel mass variations effect on transonic aeroelasticity

Analysis of Hydrocyclone Geometry via Rapid Optimization Based on Computational Fluid Dynamics

An efficient implementation of aeroelastic tailoring based on efficient computational fluid dynamics-based reduced order model

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