In this study, a multi-element aerofoil including NACA2415 aerofoil with NACA22 leading-edge slat is experimentally and computationally investigated at a transitional Reynolds number of 2 x 10E5. In the experiment, the single-element aerofoil experiences a laminar separation bubble, and a maximum lift coefficient of 1.3 at a stall angle of attack of 12 is obtained. This flow has been numerically simulated by FLUENT, employing the recently developed, k-k(L)-omega and k-omega shear-stress transport (SST) transition models. Both transition models are shown to accurately predict the location of the experimentally determined separation bubble. Experimental measurements also illustrate that the leading-edge slat significantly delays the stall up to an angle of attack of 20, with a maximum lift coefficient of 1.9. The fluid dynamics governing this improvement is the elimination of the separation bubble by the injection of high momentum fluid through the slat over the main aerofoil - an efficient means of flow control. Numerical simulations using k-k(L)-omega are shown to accurately predict the lift curve, including stall, but not the complete elimination of the separation bubble. Conversely, the lift curve prediction using the k-co SST transition model is less successful, but the separation bubble is shown to fully vanish in agreement with the experiment.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Flow over an aerofoil without and with a leading-edge slat at a transitional Reynolds number


    Additional title:

    Strömung über einen Tragflügel ohne und mit Vorflügel an der Vorderkante bei einer Übergangs-Reynolds-Zahl


    Contributors:
    Genc, M.S. (author) / Kaynak, Ü. (author) / Lock, G.D. (author)


    Publication date :

    2009


    Size :

    15 Seiten, 21 Bilder, 35 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Flow over an aerofoil without and with a leading-edge slat at a transitional Reynolds number

    Genç, M S / Kaynak, Ü / Lock, G D | SAGE Publications | 2009



    AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF LOW RE NUMBER TRANSITIONAL FLOWS OVER AN AEROFOIL WITH LEADING EDGE SLAT

    Genc, M. / Lock, G. / Kaynak, U. et al. | British Library Conference Proceedings | 2008


    An Experimental and Computational Study of Low Re Number Transitional Flows over an Aerofoil with Leading Edge Slat

    Genc, M. / Lock, G. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2008