Wind tunnel experiments were conducted to determine the effectiveness of spoilers applied to a finite-span wing which utilizes the GA(W)-1 airfoil section and a 30% chord full-span Fowler flap. A series of spoiler cross sectioned shapes were tested utilizing a reflection-plane model. Five-component force characteristics and hinge moment measurements were obtained. Results confirm earlier two-dimensional tests which showed that spoilers could provide large lift increments at any flap setting, and that spoiler control reversal tendencies could be eliminated by providing a vent path from lower surface to upper surface. Performance penalties due to spoiler leakage airflow were measured.


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    Title :

    Reflection-plane tests of spoilers on an advanced technology wing with a large Fowler flap


    Contributors:

    Publication date :

    1976-07-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :




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