Hybrid RANS/LES of a generic high-lift aircraft configuration near maximum lift

We present hybrid RANS/LES simulations of the JAXA Standard Model high-lift configuration at near-stall conditions, applying the Improved Delayed Detached-Eddy Simulation on a hybrid mesh with local wall-modelled LES resolution. The computations with the DLR-TAU code and accurate hybrid numerics yield highly-resolved turbulent structures in the critical flow regions on the wing and flap, leading to overall satisfying flow predictions and decent agreement with pressure measurements on the wing. Although the corner separation at high angles of attack associated with lift breakdown is not fully captured, we observe some improvements compared the initial RANS simulations. Overall, this work demonstrates the feasibility of highly-resolved hybrid RANS/LES to a complex industry-relevant aircraft flow