Hybrid RANS/LES of an Isolated Engine Nacelle with Crosswind Using an Unstructured CFD Solver
The present contribution focuses on the high-fidelity scale-resolving simulation of an isolated engine nacelle subjected to strong crosswind. The work, carried out with the DLR TAU code, shows shortcomings of a steady RANS approach in predicting total pressure losses for the transonic partially-separated intake flow and proves the higher accuracy of advanced hybrid RANS/LES methods. In particular, an IDDES approach is combined with a hybrid numerical scheme that assures low-dissipation and low-dispersion errors in the focus area and numerical stability in the surrounding regions (hybrid LD2 scheme). The results are validated by means of theoretical turbulence spectra and experimental integral data.
The present work was funded in part by Rolls-Royce within the framework of the FaNcI project (Fan Nacelle Integration) and in part by the DLR within the VicToria project (Virtual Aircraft Technology Integration Platform). The funding as well as the excellent collaboration with the partners from Rolls-Royce Deutschland, DLR and CFD Software GmbH is thankfully acknowledged.
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