An efficient aerodynamic boundary element method for aeroelastic simulations and its experimental validation

Eller, David; Carlsson, Martin

doi:10.1016/s1270-9638(03)00056-7

Cited by 12 publications

(6 citation statements)

References 10 publications

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“…The unsteady potential flow solver is based on a boundary element method, which includes panel clustering to significantly improve computational efficiency (12) . The method is in terms of fundamental mathematics identical to the method used by Morino et al (13) .…”

Section: Methodsmentioning

confidence: 99%

Steady and unsteady pressure measurements on a swept-wing aircraft

Jansson

Stenfelt

2014

Aeronaut. j. (1968)

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Steady and unsteady pressure measurements are conducted for a tailless aircraft model. The main aim with the presented experimental work is to investigate the difficulties and possibilities involved in using an available pressure sensing system for accurate unsteady pressure measurement. The experimental procedure which is utilised for unsteady pressure measurements is described in detail. In particular, the importance of synchronised timing is recognised. For a harmonically varying pressure a small time delay in the measurement chain can result in a significant phase shift. Also, difficulties and uncertainties that are still present are pointed out. The results from these experiments are compared to numerical results based on unsteady potential flow theory. In general, the experimental and computational results show similar trends. Especially good agreement is found for the steady pressure measurements. For the unsteady pressure measurements a possible Reynolds number dependency is found for the considered test conditions.

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Section: Methodsmentioning

confidence: 99%

Steady and unsteady pressure measurements on a swept-wing aircraft

Jansson

Stenfelt

2014

Aeronaut. j. (1968)

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“…Eller and Carlsson have implemented an unstructured unsteady aerodynamic BEM to investigate the subsonic aeroelasticity in time domain [15]. Their results show good agreement in comparison with experimental studies in wind tunnel.…”

Section: Introductionmentioning

confidence: 97%

“…This special feature brings about the possibility of determining aeroelastic instability directly from eigenanalysis of aeroelastic eigenvalue problem under thickness effect and geometric complexity consideration. It should be noticed, however, that in the earlier studies based on the BEM method the aeroelastic parameters such as damping and modal frequency have bean determined after time domain response analysis [15,22].…”

Section: Introductionmentioning

confidence: 99%

Application of the modified reduced-order aerodynamics modelling approach to aeroelastic analysis

Shahverdi

Nobari

Haddadpour

et al. 2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study presents the application of the Proposed Modified Reduced-Order Aerodynamics Modelling approach for aeroelastic analysis based on the boundary element method (BEM) as a novel approach. The used BEM has the capability to capture the thickness effect and geometric complexity of a general three-dimensional model. In this approach the reduced-order aerodynamic model is defined through the eigenvalue problem of unsteady flow based on the unknown wake singularities. Based on the used aerodynamic model an explicit algebraic form of the aeroelastic equations is derived that reduces computational efforts and complexity. This special feature enables us to determine the aeroelastic instability directly via eigenanalysis of the aeroelastic problem. The eigenanalysis and reduced-order modelling of unsteady flow over a NACA 0012 airfoil are performed as an example and the results are compared with those obtained from conventional reduced-order modelling (CROM) method. The obtained results demonstrate the accuracy and superior efficiency of the present method over the CROM method. The method was then applied to the aeroelastic analyses of a typical section, in order to show the procedure of driving the explicit algebraic form. Furthermore, to illustrate the capability of the method in the handling of the three-dimensional problems, aeroelastic results for a wing are presented and compared with the results of the Theodorsen's aerodynamic theory.

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“…2 Moreover, using simpler linear methods based on the potential flow assumption has led to reliable solutions in a wide range of subsonic and supersonic flight regimes. [3][4][5][6] However, some limitations such as flow separation, high angle of attack, and shock flows exist in this model. In the field of unsteady aerodynamics, some numerical approaches, such as boundary element method (BEM), based on finding unknown parameters only on the boundary of body with lower computational costs than high-fidelity formulations can be a good replacement for CFD methods.…”

Section: Introductionmentioning

confidence: 99%

“…Hence, application of BEM based on the potential flow has recently implemented as an efficient and popular tool in many studies. [3][4][5][6][8][9][10][11] An advantage of the BEM is that the method reduces the problem dimensionality by one.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic numerical approach of a wing based on the finite element and boundary element methods

Dehkordi

Shahverdi

Nobari

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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The aim of this study is to provide a coupled finite element–boundary element method approach for aeroelastic investigations in incompressible flow fields. Hence, an efficient and applicable tool for aeroelastic response computations is developed which uses boundary element method to solve flow fields and finite element method to analyze structural domains. In unsteady flow solution, the potential flow assumptions are considered, while the small deformations are assumed in structural dynamics behavior. Both solution procedures are tightly related by a boundary interface in a sequential coupling procedure. To illustrate the performance of aerodynamic solver for computation of three-dimensional unsteady flow configurations, lift response of a wing–body combination is computed and validated with available results in literature. Also, two test cases are presented that illustrate the accuracy of the developed tool for aeroelastic response analysis in comparison with available experimental results.

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An efficient aerodynamic boundary element method for aeroelastic simulations and its experimental validation

Cited by 12 publications

References 10 publications

Steady and unsteady pressure measurements on a swept-wing aircraft

Steady and unsteady pressure measurements on a swept-wing aircraft

Application of the modified reduced-order aerodynamics modelling approach to aeroelastic analysis

Aeroelastic numerical approach of a wing based on the finite element and boundary element methods

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