The consideration of static control surface deflections is daily practice in steady CFD simulations. In contrast, the consideration of moving control surface is still challenging. Moving control surfaces can only be realized by employing the so-called Chimera technique, also known as overset grid technique, which is available in DLR’s flow solver TAU. With the Chimera technique, the user has to generate separate overlapping CFD meshes for the different components of the configuration to be simulated, e.g. separate meshes for wing and ailerons. Often, it is difficult to ensure sufficient Chimera overlap during mesh generation, or, just for the sake of ensuring sufficient overlap, disproportionately many grid points must be spent in regions of rather subordinate interest regarding the CFD analysis. A promising alternative may be the so-called sliding-interface technology. With this technique, the component meshes do not overlap but merely slide along each other. Thereby, many grid points and thus computational expenses can be saved.
Besides the described application of the sliding interface technology for control surface motions, this technique may also be exploited in simulations with rotating components such as in helicopter applications.
You will analyze the different variants of the sliding interface method published in literature; you will summarize the differences and similarities; and choose a variant based on criteria to be determined. You will implement the selected variant in the DLR flow solver TAU and you will verify the correctness of your implementation. Finally, in simulations of selected test cases with moving parts you will assess the advantages and disadvantages of the sliding interface technology compared to the conventional Chimera technique.
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