The role of aspect ratio on the dynamic stall process of an unswept finite wing is investigated using high-fidelity large-eddy simulations. Three aspect ratios (, 8, and 16) are explored for wings (NACA 0012 cross section) at chord Reynolds number and freestream Mach number . The wings pitch sinusoidally from initial incidence of 4° to a maximum angle of attack of 22° with reduced frequency over one pitching cycle. The three-dimensional unsteady flowfields show similarity among the three wings through laminar separation bubble formation/bursting. The flow topology during dynamic stall exhibits distinctly different evolutions at the higher aspect ratio relative to the lower, baseline aspect ratio. Rather than evolving into a vortex (), the higher-aspect-ratio wings show dramatic three-dimensional deformation of the vortex tube that resembles cellular structures. The vortical structure eventually interacts with the trailing-edge vortex, which contrasts with the lower aspect ratio. Examination of the unsteady loads shows an increase in lift slope, average loads, peak loads, and earlier stall with aspect ratio.
Effect of Aspect Ratio on Finite-Wing Dynamic Stall
AIAA Journal ; 60 , 12 ; 6581-6593
2022-12-01
Conference paper , Article (Journal)
Electronic Resource
English
ASPECT RATIO EFFECT ON FINITE WING DYNAMIC STALL
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