When a two-element airfoil for the wing of a racecar has to be inside a rectangle space dictated by regulations or dictated by the available space, the ratio of the flap chord length to the main element chord length, the overlap and gap sizes between the main element and the flap are design parameters, besides the element shapes. To find the configuration for the high downforce-to-drag ratio, CFD simulations were performed in 2D using the FX63-137 airfoil for both the main element and the flap. Some important findings are that the flap chord length should be 50 to 70% of the main element chord length to achieve the high lift-to-drag ratio. This finding will help design better two-element wings.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Optimal Configuration of Two-Element Airfoil Constrained in a Rectangular Space


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Motorsports Engineering Conference & Exposition ; 2006



    Publication date :

    2006-12-05




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    2006-01-3642 Optimal Configuration of Two-Element Airfoil Constrained in a Rectangular Space

    Goto, K. / Sakurai, H. / SAE International | British Library Conference Proceedings | 2006





    Transonic Airfoil Design by Constrained Optimization

    Lee, K. / Eyi, S. / AIAA | British Library Conference Proceedings | 1991