Prediction of the Model Deformation of a High Speed Transport Aircraft Type Wing by Direct Aeroelastic Simulation

C. Braun (), A. Boucke (), M. Hanke (), A. Karavas () and J. Ballmann ()
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C. Braun: RWTH Aachen, Lehr- und Forschungsgebiet für Mechanik
A. Boucke: RWTH Aachen, Lehr- und Forschungsgebiet für Mechanik
M. Hanke: RWTH Aachen, Lehr- und Forschungsgebiet für Mechanik
A. Karavas: RWTH Aachen, Lehr- und Forschungsgebiet für Mechanik
J. Ballmann: RWTH Aachen, Lehr- und Forschungsgebiet für Mechanik

A chapter in High Performance Computing in Science and Engineering ’03, 2003, pp 331-342 from Springer

Abstract: Abstract The aerodynamic performance, maneuverability and flight stability of aircrafts are highly dependent on the deformation of their wings under aerodynamic loads. The accurate prediction of aeroelastic properties, such as aeroelastic equilibrium configurations under cruise conditions, is therefore crucial in early design stages. Due to increasing computer power and further development of numerical methods, direct numerical aeroelastic simulation, in which the governing equations for the fluid and the structure are solved consistently in time, has become feasible [1, 2]. In the collaborative research center SFB 401 “Flow Modulation and Fluid-Structure Interaction at Airplane Wings” at Aachen University the numerical aeroelastic method SOFIA (SOlid Fluid InterAction) for direct numerical aeroelastic simulation is being progressively developed [4, 5]. According to the coupled field approach, three modules can be identified in SOFIA: flow solver, structural solver and a grid deformation tool, which is necessary since the boundaries of the computational grid for the flow solver always have to coincide with the deforming aerodynamic surface of the structure.

Keywords: Wind Tunnel; Model Deformation; Wing Surface; Local Angle; Wind Tunnel Model (search for similar items in EconPapers)
Date: 2003
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DOI: 10.1007/978-3-642-55876-4_25

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