Fluid-Structure Coupling for Aerodynamic Analysis and Design: A DLR Perspective (Invited)

Kroll, Norbert; Heinrich, Ralf; Neumann, Jens; Nagel, Björn

doi:10.2514/6.2008-561

Cited by 14 publications

(6 citation statements)

References 22 publications

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“…10, 12, 13 TAU has been used successfully in numerous multidisciplinary applications. 11 In the simulations described in this paper, a central scheme with artificial matrix dissipation was applied for the discretization of the convective fluxes. Notionally, it is second-order accurate in space.…”

Section: Iiia1 Cfd Solvermentioning

confidence: 99%

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CFD-based Gust Load Analysis for a Free-flying Flexible Passenger Aircraft in Comparison to a DLM-based Approach

Reimer

Ritter

Heinrich

et al. 2015

22nd AIAA Computational Fluid Dynamics Conference

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Gust load analysis is a relevant part of the certification process of aircraft. In need of low computing times, industrial analysis procedures often rely mainly on low-fidelty numerical aerodynamics methods, such as the Doublet Lattice method (DLM). However, their accuracy with respect to loads has not been assessed sufficiently in comparison to high-fidelity methods in the past. In this paper, simulation results of a classical DLMbased gust load analysis process are compared to the results of an alternative process in which the DLM solver is replaced by the CFD solver TAU. The investigation is performed with a realistic modern passenger aircraft. It is studied how the consideration of different levels of multidisciplinarity in the simulations affects the overall loads. The simulation methodologies exploited in the CFD-based analysis process are outlined. It is shown that the gust load factors predicted with CFD are significantly lower than those of the classical DLM-based process-not only in the transonic flow regime, where benefits from the CFDbased analysis are expected, but also in the subsonic flow regime.

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Section: Iiia1 Cfd Solvermentioning

confidence: 99%

“…It involves a flight dynamics (FD) solver, a computational structural dynamics (CSD) solver, and the CFD solver TAU. [10][11][12][13] The overall objective of the investigation is to compare the results of the CFD-based simulations with those of a classical DLM-based approach. In addition, the following extra objectives are pursued.…”

Section: Introductionmentioning

confidence: 99%

CFD-based Gust Load Analysis for a Free-flying Flexible Passenger Aircraft in Comparison to a DLM-based Approach

Reimer

Ritter

Heinrich

et al. 2015

22nd AIAA Computational Fluid Dynamics Conference

View full text Add to dashboard Cite

show abstract

“…Another fluid-structure coupling process is conducted in [16] with a development of an efficient and robust grid deformation technique, an accurate data interpolation to transfer information from CFD to structural mesh grids and vice versa, as well as the implementation of suitable interfaces between CFD and structural analysis solvers. The coupling procedure is designed for steady and unsteady fluid-structure interactions.…”

Section: Introductionmentioning

confidence: 99%

Aero-Structural Coupling Strategy for a Morphing Blade Cascade Study

Abate

Riemenschneider

Hergt

2022

Journal of Turbomachinery

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The coupling of aerodynamics and structural mechanics is an important step in the design process of aeronautical devices with morphing parts. In this paper, a 2D-3D coupling approach is developed to study a morphing blade cascade. Two shape memory alloy actuators are placed on the upper and lower sides of the blade to make possible the change in shape of the leading-edge. In the present work, a preliminary design study is conducted by considering a two-dimensional CFD analysis of an airfoil cascade coupled with a three-dimensional structural analysis of the whole 3D blade. A methodology is developed to match 2D and 3D meshes such that the aerodynamic loads can be easily transferred to the structural analysis. From there, the deformed blade geometry due to both aerodynamic loads and actuator work can be transferred back to the CFD solver, and the iterative aero-structural coupling loop can be repeated until convergence. The aero-structural coupling strategy developed in this work is also applied to a blade cascade study aiming to improve its performance by morphing the leading-edge of the blade. The results of this application show that by morphing the leading-edge blade of only few millimeters (less than 2 mm), it is possible to achieve a relevant performance improvement in terms of total pressure loss coefficient decrease of about 53%.

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“…Another method is based on the computational aeroelasiticity approach to determine the influence of model deformation [25][26][27]. Although the computational aeroelasticity method has been widely used in aircraft design [28,29], there are still some problems predicting the model deformation and variation of aerodynamic force coefficients accurately [19,30]. The third method is a combination of CFD and model deformation measurement (MDM) [31].…”

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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Fluid-Structure Coupling for Aerodynamic Analysis and Design: A DLR Perspective (Invited)

Cited by 14 publications

References 22 publications

CFD-based Gust Load Analysis for a Free-flying Flexible Passenger Aircraft in Comparison to a DLM-based Approach

CFD-based Gust Load Analysis for a Free-flying Flexible Passenger Aircraft in Comparison to a DLM-based Approach

Aero-Structural Coupling Strategy for a Morphing Blade Cascade Study

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

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