Aeroelastic Dataset Generation Using CFD-CSM Simulations with a Chimera Approach for Control Surfaces

Reinbold, Christopher; Breitsamter, Christian; Sørensen, Kaare

doi:10.2514/6.2022-0564

10.2514/6.2022-0564

Title:: Aeroelastic Dataset Generation Using CFD-CSM Simulations with a Chimera Approach for Control Surfaces
Document type:: Konferenzbeitrag
Contribution type:: Textbeitrag / Aufsatz
Author(s):: Reinbold, Christopher; Breitsamter, Christian; Sørensen, Kaare
Abstract:: An aeroelastic dataset generation method for aircraft, which is based on coupled CFD-CSM simulations and a Chimera approach for control surfaces is presented. It is embedded in the multidisciplinary simulation environment SimServer. The DLR TAU code is employed to obtain the CFD solution by solving the Reynolds-Averaged Navier-Stokes equations. Structural displacements are computed with a modal solver. The aeroelastic dataset production method is applied to the Northrop F-5A aircraft. A CAD surface model of the aircraft and a structural model has been generated and are introduced. Numerical simulations are performed at transonic speed (formula presented) = 0.89, a flight altitude of ℎ = 10668 m and several angles of attack (formula presented) . Control surface deflections of the leading edge flap, trailing edge flap, aileron and horizontal stabilizer are considered. The effect of control surface deflections on the force and moment coefficients are analyzed. The influence of flexibility on the configuration is evaluated by comparing the force and moment coefficients of the aeroelastic simulations to the aerodynamic simulations, where the aircraft is assumed to be fully rigid. A comparison of the results obtained by aerodynamic and aeroelastic simulations show that the flexibility of the aircraft influences the lift, pitching moment and rolling moment coefficient for all considered angles of attack. © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. «
An aeroelastic dataset generation method for aircraft, which is based on coupled CFD-CSM simulations and a Chimera approach for control surfaces is presented. It is embedded in the multidisciplinary simulation environment SimServer. The DLR TAU code is employed to obtain the CFD solution by solving the Reynolds-Averaged Navier-Stokes equations. Structural displacements are computed with a modal solver. The aeroelastic dataset production method is applied to the Northrop F-5A aircraft. A CAD surf... »
Dewey Decimal Classification:: 620 Ingenieurwissenschaften
Book / Congress title:: AIAA SCITECH 2022 Forum
Publisher:: American Institute of Aeronautics and Astronautics
Date of publication:: 03.01.2022
Year:: 2022
Covered by:: Scopus
Language:: en
Fulltext / DOI:: doi:10.2514/6.2022-0564
WWW:: https://arc.aiaa.org/doi/10.2514/6.2022-0564
Notes:: Funding text The fruitful collaboration with Airbus Defence and Space and its partial financial sponsoring is gratefully acknowledged. The authors thank the German Aerospace Center (DLR) for providing the DLR TAU-Code used for the numerical investigations. Moreover, the authors thank the Gauss Centre for Supercomputing e.V. (www.gauss-centre.eu) for supporting this project by providing computing time on the GCS Supercomputer SuperMUC-NG at Leibniz Supercomputing Centre (www.lrz.de).
TUM Institution:: Lehrstuhl für Aerodynamik und Strömungsmechanik
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