A disclosed method reduces a wave drag on an airfoil (100) traveling at a speed. At least a portion of the airfoil (100) is configured to be selectively moveable between a first position and a second position. The first position is a neutral position, and the second position generates a shock wave near to the leading edge (106) of the airfoil. The method includes the steps of maintaining the airfoil in the first position when the speed is less than a first limit and moving the airfoil to the second position when the speed is greater than a first limit.


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    Titel :

    VARIABLE WING LEADING EDGE CAMBER


    Weitere Titelangaben:

    VARIABLE FLÜGELVORDERKANTENWÖLBUNG
    CAMBRURE VARIABLE DU BORD D'ATTAQUE DE L'AILE


    Beteiligte:

    Erscheinungsdatum :

    28.06.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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