An investigation of spanwise end effects on deep dynamic stall of a nominally two-dimensional pitching wing section is performed using high-fidelity large-eddy simulations (LES). This study was motivated by the need to reduce uncertainties in comparisons of computations and experiments. A NACA 0012 wing section was employed with freestream Mach number M = 0.1 and chord Reynolds number R e c = 2 × 10 5 . A harmonic pitching motion was prescribed with reduced frequency k = π f c / U = π / 16 and minimum and maximum angles of attack of 4 and 22 deg, respectively. To characterize the effects of spanwise end conditions, several geometrical configurations are considered, including spanwise periodic, end walls, and end gaps. These configurations correspond to either spanwise-homogeneous LES or typical wind-tunnel installations. A comparison among various setups was performed in terms of instantaneous flow structure and aerodynamic loads. It was found that end effects can have a significant impact on the flow structure during the motion downstroke, which limits the agreement to be expected in computational/experimental comparisons. Although these effects are not unforeseen, this work provides a quantification of their magnitude. It is also confirmed that end walls are preferable to end gaps even if the latter are of the order of 1% chord. End-wall configurations with aspect ratio higher than 4 are preferable for improved comparisons.


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    Titel :

    Investigation of Spanwise End Effects on Dynamic Stall of a Pitching Wing Section


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 56 , 6 ; 2118-2130


    Erscheinungsdatum :

    2019-08-30


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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