The unsteady three-dimensional flowfield over an oscillating wing is investigated with the numerical solution of the compressible, time-dependent, Reynolds-averaged Navier-Stokes equations. Spatial discretization is performed with a third-order accuarate, upwind-biased, vortex-besed, finite volume sheme. An alternative direction implicit, iterative scheme is used for the time integration. The high Reynolds number turbulent flow behaviour is modeled with an one-equation turbulence model. The effect of subiterations, time step and grid density on the accuracy of the computed solutions is investigated. It is found that scaling of the time step with the angular velocity of the motion produces accurate solutions at a reduced computational cost. The computational domain over an aspect ratio 5 wing with rounded tip and NACA-0015 airfoil sections is discretized with a single-block grid. The light stall flowfield over the wing oscillating in a subsonic freestream with a mean angle of attack of 11 deg and an amplitude of 4.2 deg is computed. The structure of the separated, unsteady flowfield is investigated and comparisons with available experimental data are performed.


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    Title :

    Numerical investigation of dynamic stall of an oscillating wing


    Additional title:

    Numerische Untersuchung des dynamischen Strömungsabrisses an einem schwingenden Tragflügel


    Contributors:

    Published in:

    AIAA Journal ; 33 , 10 ; 1803-1808


    Publication date :

    1995


    Size :

    6 Seiten, 12 Bilder, 35 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Numerical Investigation of Dynamic Stall of an Oscillating Wing

    Ekaterinaris, J.A. | Online Contents | 1995



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