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This paper provides an overview of the recent development of scale-resolving simulation methods in the DLR-TAU code for flow simulations near the border of the flight envelope. On the numerical side, a hybrid low-dissipation low-dispersion discretization scheme is presented that allows for accurate wall-resolved and wall-modelled LES computations and is shown to provide satisfying hybrid RANS/LES predictions of a Delta wing flow on a unstructured mesh. In the field of physical modelling, the grey-area issue of non-zonal hybrid RANS/LES is addressed through a vorticity-sensitive sub-grid filter scale which is shown to improve the prediction of a backward-facing step flow. Moreover, an embedded-LES functionality based on the Synthetic Eddy Method is implemented in TAU and applied to a complex multi-element airfoil flow.