Computational Flight Testing

Kroll, Norbert; Radespiel, Rolf; Burg, J.W. van der; Sørensen, Kaare

doi:10.1007/978-3-642-38877-4

Cited by 3 publications

(2 citation statements)

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“…The iterative process has converged if the difference of the maximum deflection of the model between two consecutive time steps falls below a given value. Comparisons between the presented FSI approach and experimental data always showed good agreement [7,15,[18][19][20], for subsonic as well as for transonic flow.…”

Section: Fluid-structure Coupling Methodologymentioning

confidence: 80%

“…The modal matrixŨ s contains each eigenmode of the structural model and X is the diagonalized eigenvalue matrix. The structural eigenmodesŨ s can be interpolated onto the aerodynamic surface mesh using a spline matrix H [15]. By means of the virtual work, it can be shown that the structural forces f s can be calculated with the same, but transposed interpolation matrix H, from aerodynamic forces f a :…”

Section: Fluid-structure Coupling Methodologymentioning

confidence: 99%

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The influence of fixed transition modeling on aeroelastic simulations in comparison to wind tunnel experiments

2018

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Your article is protected by copyright and all rights are held exclusively by Deutsches Zentrum für Luft-und Raumfahrt e.V.. This eoffprint is for personal use only and shall not be self-archived in electronic repositories. If you wish to self-archive your article, please use the accepted manuscript version for posting on your own website. You may further deposit the accepted manuscript version in any repository, provided it is only made publicly available 12 months after official publication or later and provided acknowledgement is given to the original source of publication and a link is inserted to the published article on Springer's website. The link must be accompanied by the following text: "The final publication is available at link.springer.com".

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Section: Fluid-structure Coupling Methodologymentioning

confidence: 80%

Section: Fluid-structure Coupling Methodologymentioning

confidence: 99%

The influence of fixed transition modeling on aeroelastic simulations in comparison to wind tunnel experiments

2018

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Differential Reynolds-Stress Modeling for Aeronautics

et al. 2015

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A comparison of two differential Reynolds-stress models for aeronautical flows is presented. The ω model herein combines the Speziale-Sarkar-Gatski pressure-strain model with the Launder-Reece-Rodi model toward the wall, where the length scale is supplied by Menter's baseline ω equation. The ε h model from Jakirlić and Hanjalić has been particularly designed for representing the correct near-wall behavior of turbulence and has been adapted to aeronautical needs. Its length scale is provided by a transport equation for the homogeneous part of the dissipation rate. The models are applied to a series of test cases relevant to aeronautics, showing improved predictions compared to eddy-viscosity models particularly in case of axial vortices. 10 September 2014.

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UltraFLoads: A Simulation Suite and Framework for High-Fidelity Flight Loads

Feldwisch

Bauer

2023

Aerospace

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With the progress of high-performance computing, computationally expensive high-fidelity methods can be applied early in the design process of an aircraft. This enables Computational Fluid Dynamics (CFD) for the assesment of flight performance, handling qualities, flight loads due to manoeuver or gusts, and stability such as flutter. Those aeroealstic analyses require coupling of disciplines to adequately address the interplay of flexibility, aerodynamic forces and inertia forces. Previous work at the German Aerospace Center have demonstrated the proof of concept for those multidisciplinary analyses. Now, UltraFLoads is a simulation suite in the FlowSimulator ecosystem to offer standardized, multidisciplinary scenarios. UltraFLoads can be used as a tool, as a library and as a framework. This work describes the architecture, the integration layers, which scenarios are available and which equations are used. Three different applications are presented. The first case involves a steady fluid–structure-coupled simulation with geometrically nonlinear deformation. The second case compares the deformation of a simulated elastic, free-flying aircraft with actual flight test data. The last application demonstrates the flight dynamic capabilities with a bank to bank maneuver.

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Computational Flight Testing

Cited by 3 publications

References 0 publications

The influence of fixed transition modeling on aeroelastic simulations in comparison to wind tunnel experiments

The influence of fixed transition modeling on aeroelastic simulations in comparison to wind tunnel experiments

Differential Reynolds-Stress Modeling for Aeronautics

UltraFLoads: A Simulation Suite and Framework for High-Fidelity Flight Loads

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