Reynolds-averaged Navier–Stokes and hybrid large-eddy/Reynolds-averaged Navier–Stokes simulations of turbulent flow past an Aérospatiale A-Airfoil near stall at R e c = 2.1 × 10 6 , M = 0.15 , α = 13.3 and a NACA 0012 airfoil under static stall conditions ( R e c = 1.0 × 10 6 , M = 0.1 , α = 16.7    deg ) are described in this paper. In the flow past the A-Airfoil, comparisons with surface skin-friction coefficient and pressure coefficient distribution are generally in good agreement with experimental measurements. Comparisons with experimental velocity profile data and Reynolds-stress data are also generally favorable. Leading-edge laminar separation and turbulent reattachment is predicted when the Menter–Langtry correlation-based transition model is used in combination with either Reynolds-averaged Navier–Stokes or large-eddy/Reynolds-averaged Navier–Stokes strategies, but the level of trailing-edge separation is underpredicted, relative to experimental data and to results obtained without the inclusion of transition model. For the case of flow past a NACA 0012 airfoil under static stall conditions, results from the large-eddy/Reynolds-averaged Navier–Stokes simulations exhibit a sensitivity to mesh refinement, with finer spanwise mesh resolution leading to light stall, characterized primarily by trailing-edge separation, and coarser spanwise mesh resolution leading to deep stall, characterized by the presence of a stabilized leading-edge vortex. Calculations that include wind-tunnel wall effects show better general agreement with experimental measurements but also display the aforementioned sensitivity to spanwise mesh refinement.


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    Title :

    Numerical Simulations of Turbulent Flow over Airfoils Near and During Static Stall


    Contributors:

    Published in:

    Journal of Aircraft ; 54 , 5 ; 1960-1978


    Publication date :

    2017-09-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






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