Enhanced Prediction of Three-Dimensional Finite Iced Wing Separated Flow Near Stall

Icing on three-dimensional wings causes severe flow separation near stall. Standard improved delayed detached eddy simulation (IDDES) is unable to correctly predict the separating reattaching due its inability accurately resolve Kelvin-Helmholtz instability. In this study, a shear layer adapted subgrid length scale applied enhance IDDES prediction of around finite NACA (National Advisory Committee for Aeronautics) 0012 wing with leading edge horn ice. It found that applying new contributes more accurate separated (SSL). The reattachment occurs earlier as one moves towards either end downwash effect tip vortex or influence end-wall flow. Consequently, computed surface pressure distributions agree well experimental measurements. contrast, standard severely elongates plateaus. For instantaneous flow, helps rollup and subsequent pairing vortical structures small values in initial SSL. Strouhal numbers motions are approximately 0.2 SSL based vorticity thickness 0.1 bubble length. Both frequencies increase when moving vortex. comparison, excessive viscosity levels from delay spanwise give rise "overcoherent" structures.