Aero-Structural Wind Tunnel Experiments with Elastic Wing Models at High Reynolds Numbers (HIRENASD - ASDMAD)

Ballmann, J.; Boucke, Alexander; Chen, B.; Reimer, Lars; Behr, Marek; Dafnis, Athanasios; Buxel, Christian; Buesing, S.; Reimerdes, Hans-Günther; Kordt, M.; Brink-Spalink, Jan; Theurich, Frank; Büscher, Alexander

doi:10.2514/6.2011-882

Cited by 16 publications

(11 citation statements)

References 10 publications

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“…The HIRENASD project was initiated at RWTH Aachen University in 2004. The main purpose of this project is to analyze steady and unsteady aeroelastic experiments in transonic flight regime with a supercritical elastic wing model [25]. The HIRENASD wind-tunnel model was tested in the European Transonic Windtunnel (ETW) in 2006 by Aachen University's Department of Mechanics with funding from the German Research Foundation [26].…”

Section: Static Aeroelastic Analysis Of the Hirenasd Wingmentioning

confidence: 99%

“…The HIRENASD wind-tunnel model was tested in the European Transonic Windtunnel (ETW) in 2006 by Aachen University's Department of Mechanics with funding from the German Research Foundation [26]. The test medium of ETW is nitrogen gas under cryogenic conditions [25]. The wing has a 34 o degree of backward sweep angle and a supercritical wing profile BAC 3-11.…”

Section: Static Aeroelastic Analysis Of the Hirenasd Wingmentioning

confidence: 99%

“…The wing has a 34 o degree of backward sweep angle and a supercritical wing profile BAC 3-11. The aerodynamic reference area is 0.3926 m 2 while the mean chord length is 0.3445 m [25]. The HIRENASD wing model planform and assembly are illustrated in Fig.1.…”

Section: Static Aeroelastic Analysis Of the Hirenasd Wingmentioning

confidence: 99%

See 2 more Smart Citations

Reduced Order Modelling of High-Fidelity Computational Fluid-Structure Interaction Analysis for Aeroelastic Systems

Acar¹,

Nikbay²

2013

Proceedings of the 3rd South-East European Conference on Computational Mechanics – SEECCM III

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Abstract. We investigate model reduction techniques through computational aeroelastic analyses of the HIRENASD and S 4 T wings. The aim of the present work is to construct accurate and computationally efficient reduced order models for high-fidelity aeroelastic computations. Firstly, the aeroelastic analyses of the specified wings are performed by high-fidelity structural and aerodynamic models to substantiate the fluid-structure interaction. Concerning high amount of computational time required to perform such high-fidelity fluid-structure interaction analyses, the model orders are reduced by introducing relevant reduction techniques such as Polynomial Chaos Expansion and Proper Orthogonal Decomposition. The final aeroelastic analyses performed on these reduced models agree well with the initial high-fidelity computational analyses.

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Section: Static Aeroelastic Analysis Of the Hirenasd Wingmentioning

confidence: 99%

Section: Static Aeroelastic Analysis Of the Hirenasd Wingmentioning

confidence: 99%

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Reduced Order Modelling of High-Fidelity Computational Fluid-Structure Interaction Analysis for Aeroelastic Systems

Acar¹,

Nikbay²

2013

Proceedings of the 3rd South-East European Conference on Computational Mechanics – SEECCM III

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“…Now, there are three kinds of methods to obtain the aerodynamic forces on rigid model shape. The first method is to use test data at different dynamic pressures to extrapolate the data at zero dynamic pressure where the aircraft model has no deformation [20][21][22]. This type of test requires the wind tunnel to be able to adjust the temperature and pressure independently.…”

Section: Introductionmentioning

confidence: 99%

A Fast Correction Method of Model Deformation Effects in Wind Tunnel Tests

et al. 2018

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The influence of model deformation needs to be corrected before the aerodynamic force data measured in the wind tunnel is applied to aircraft design. In order to obtain the aerodynamic forces on rigid model shape, this paper presents a fast correction method by establishing a mathematical modelling method connecting aerodynamic forces and wing section torsion. The aerodynamic force coefficients on rigid model shape can then be calculated quickly just by setting section torsion to zero. A 25-point simulation dataset of the High Reynolds Number Aero-Structural Dynamics (HIRENASD) model generated by Computational Fluid Dynamics (CFD) and Static Computational Aeroelasticity (CAE) approach is used to investigate the influence of section locations, basis function type, support radius, and deformation perturbation on the prediction accuracy. Finally, the present correction method is applied to predict the aerodynamic forces on the rigid shape of a NASA common research model. The results of parametric analysis and application show that the present correction method with the Wendland's C6 function and a support radius of 1.0 can provide a reasonable prediction of aerodynamic forces on the rigid model shape.

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“…23,24,25,26,27 The HIRENASD was tested in the European Transonic Wind tunnel (ETW) in 2007, shown in figure 6 using Nitrogen as the test medium. The model has a 34…”

Section: Vc High Reynolds Number Aerostructural Dynamics Hirenasdmentioning

confidence: 99%

Overview of the Aeroelastic Prediction Workshop

Heeg

Chwalowski²,

Florance³

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The Aeroelastic Prediction Workshop brought together an international community of computational fluid dynamicists as a step in defining the state of the art in computational aeroelasticity. This workshop's technical focus was prediction of unsteady pressure distributions resulting from forced motion, benchmarking the results first using unforced system data. The most challenging aspects of the physics were identified as capturing oscillatory shock behavior, dynamic shock-induced separated flow and tunnel wall boundary layer influences. The majority of the participants used unsteady Reynolds-averaged Navier Stokes codes. These codes were exercised at transonic Mach numbers for three configurations and comparisons were made with existing experimental data. Substantial variations were observed among the computational solutions as well as differences relative to the experimental data. Contributing issues to these differences include wall effects and wall modeling, nonstandardized convergence criteria, inclusion of static aeroelastic deflection, methodology for oscillatory solutions, post-processing methods. Contributing issues pertaining principally to the experimental data sets include the position of the model relative to the tunnel wall, splitter plate size, wind tunnel expansion slot configuration, spacing and location of pressure instrumentation, and data processing methods.

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Aero-Structural Wind Tunnel Experiments with Elastic Wing Models at High Reynolds Numbers (HIRENASD - ASDMAD)

Cited by 16 publications

References 10 publications

Reduced Order Modelling of High-Fidelity Computational Fluid-Structure Interaction Analysis for Aeroelastic Systems

Reduced Order Modelling of High-Fidelity Computational Fluid-Structure Interaction Analysis for Aeroelastic Systems

A Fast Correction Method of Model Deformation Effects in Wind Tunnel Tests

Overview of the Aeroelastic Prediction Workshop

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