In fluid-structure coupled simulations of complete aircraft configurations, particularly in high-lift configurations, it is necessary to associate parts of the CFD surface mesh to the corresponding parts of the structural mesh, e.g. the CFD surface mesh of wing to the corresponding part in the mesh that discretizes the wing structure, see top row of the left figure. This is necessary to avoid errors in the interpolation of aerodynamic loads and structural deformations. To obtain a correct CFD surface mesh usable for CFD computations subsequent to the deformation transfer, so-called blending techniques are applied. The deformation effect of a structural component, e.g. of the wing, on only indirectly associated CFD components, i.e. the CFD surface mesh of the fuselage in the example, is faded out in a region around the intersection line between the involved components.
In a joint project of Airbus, Cassidian, Onera, DLR and universities the FlowSimulator (FS) software environment is being continuously developed. For the partners FS is meant to serve as the backbone for massively-parallel multi-disciplinary simulations, such as coupled fluid-structure simulations. In FS some parallel methods for load/deformation interpolation in aeroelastic simulations are already implemented. So far, however, no componend-based interpolation is available in FS due to the absence of an implemented blending technique. This issue shall be resolved within the scope of this tendered work by implementing the blending method published in.
You will implement the blending method described in in a parallel manner into the given FS environment. You will verify the correctness of your implementation in aeroelastic applications of increasing complexity.
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Institute of Aerodynamics and Flow Technology
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