An investigation of the effect of moderate sweep on three-dimensional (3D) dynamic stall of a pitching finite-aspect-ratio wing is performed by means of large-eddy simulations. The wings have an aspect ratio A R = 4 and a NACA 0012 section. Three values of sweep angle are considered, Λ = 0 ° , 15 ° , and 30°. The flow parameters are freestream Mach number M = 0.1 and chord Reynolds numbers R e c = 2 × 10 5 . A sinusoidal pitching motion is considered with reduced frequency k = π f c / U = π / 16 and minimum and maximum angles of attack of 4° and 22°. The unsteady flow structure is examined in order to provide a model of 3D dynamic stall over finite swept wings. For all configurations, the dynamic stall vortex evolves into an arch-type structure that is shed following its transformation into a ring vortex. For Λ = 0 ° , there is a single and larger arch vortex centered about midspan. For the swept cases, arch vortices are formed on each side of the wing at a spanwise station that moves farther outboard with increasing sweep. For Λ = 30 ° , the outer leg of the arch vortex interacts strongly with the wing tip flow and abrupt tip stall is observed.


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    Title :

    Effect of Sweep on Dynamic Stall of a Pitching Finite-Aspect-Ratio Wing


    Contributors:

    Published in:

    AIAA Journal ; 57 , 8 ; 3274-3289


    Publication date :

    2019-08-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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