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 ( A R = 4 , 8, and 16) are explored for wings (NACA 0012 cross section) at chord Reynolds number R e c = 2 × 10 5 and freestream Mach number M = 0.1 . The wings pitch sinusoidally from initial incidence of 4° to a maximum angle of attack of 22° with reduced frequency k = π f c / U = π / 16 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 Λ vortex ( A R = 4 ), 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.


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    Title :

    Effect of Aspect Ratio on Finite-Wing Dynamic Stall


    Contributors:

    Published in:

    AIAA Journal ; 60 , 12 ; 6581-6593


    Publication date :

    2022-12-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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