Tests of a finite-span wing with an advanced technology GA(W)-1 airfoil, spoilers, and 30% full-span Fowler flap have been conducted utilizing a reflection-plane model in the WSU low speed wind tunnel. Flap settings from 0° to 40° were tested with a series of 10% chord spoilers of various cross-sectional shapes. Wing force and spoiler hinge moment measurements were made, as well as tuft studies of stalling patterns.Results show that a finite span (aspect ratio 9.5) CLmax value of 3.0 can be obtained with 40° flap at a Reynolds number of 1.0 x 106. Spoiler results correlate well with two-dimensional results, which show that satisfactory roll control can be obtained for all flap settings, with proper lower surface venting. Spoiler gap leak lift and drag penalties were found to be quite substantial, indicating a need for careful design of gaps and seals for flap and spoiler nested configurations.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Reflection-Plane Tests of Spoilers on an Advanced Technology Wing


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    National Business Aircraft Meeting and Engineering Display ; 1976



    Publication date :

    1976-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English






    Aircraft wing, method of deploying spoilers and method of retracting spoilers

    BENJAMIN BISHOP / ANTHONY BRYANT | European Patent Office | 2022

    Free access

    Some effects of aerodynamic spoilers on wing flutter

    Doggett, Robert V., Jr. | NTRS | 1989