Wing sweep effects on laminar separated flows

We reveal the effects of sweep on wake dynamics around NACA 0015 wings at high angles attack using direct numerical simulations and resolvent analysis. The influence is considered for from $0^\circ$ to $45^\circ$ $16^\circ$ $30^\circ$ a spanwise periodic wing chord-based Reynolds number $400$ Mach $0.1$ . Wing affects dynamics, especially in terms stability fluctuations with implications development three-dimensional (3-D) wakes. observe that attenuates fluctuations. Even as angle influences wake, force pressure coefficients can be collapsed low when examined wall-normal wingspan-normal independent flow components. Some small deviations incidence are attributed vortical structures impose secondary aerodynamic loads, revealed through element Furthermore, we conduct global analysis uncover oblique modes disturbance amplification. also reveals presence wavemakers shear-dominated region associated emergence 3-D wakes attack. For flows angles, optimal convection speed response shown faster than suggesting mechanism attenuation perturbations. present findings serve fundamental stepping stone understanding separated higher numbers.