Transonic shock bufiet on civil aircraft wings remains a key challenge for aerodynamicists,with no unequivocal explanation of the ow mechanisms governing bu et onset.This paper presents a delayed detached-eddy simulation of a large civil aircraft wingin the vicinity of bu et onset, set up to reproduce experimental ow data enablingdirect comparisons. Besides conventional post-processing, the unsteady ow eld isanalysed using modal analysis techniques, including proper orthogonal decompositionand dynamic mode decomposition. Both methods reveal dominant modes pertainingto the shock bu et instability, showing outboard-running waves along the shock waveand the presence of bu et cells at a characteristic Strouhal number. Complementaryexperimental data from dynamic pressure-sensitive paint gives critical insight into theow and a modal analysis of this dataset con rms the numerical observations. Thesehigh-quality datasets further the understanding of edge-of-the-envelope ow physics,ultimately informing modern wing design and bu et control strategies.
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