Energy harvesting using flapping foils has attracted significant attention in the last 10 years. In contrast to conventional turbines, which rely on attached flow for high efficiency, a flapping-foil turbine exploits the separation of fluid flow near the nose of the foil to form a leading-edge vortex, resulting in high instantaneous forces. To reduce the computational cost of simulating a flapping foil undergoing high angles of attack (up to 90 deg), a discrete vortex method that incorporates leading-edge flow separation is used in this study. Corrections using semi-empirical functions are introduced to account for the effects of trailing-edge flow separation. Instantaneous lift and power coefficient as well as the mean power coefficient and efficiency from the discrete vortex method with separation corrections are compared against those from a dynamic stall model and computational-fluid-dynamics results obtained by the lattice Boltzmann method. The discrete vortex method provides better agreement with computational-fluid-dynamics simulations compared to the dynamic stall model.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Discrete Vortex Method with Flow Separation Corrections for Flapping-Foil Power Generators



    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040



    Discrete Vortex Method with Flow Separation Corrections for Flapping-Foil Power Generators

    Liu, Zhengliang / Lai, Joseph C. S. / Young, John et al. | AIAA | 2016


    Flow Separation Control With Vortex Generators

    Gardarin, Benoit / Jacquin, Laurent / Geffroy, Philippe | AIAA | 2008


    Numerical Simulation of the Flapping-Foil Effects by Vortex Particle Method

    Kudela, H. / Kozlowski, T. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010