In order to suppress aeroelastic instabilities on a transonically operating aircraft comprising a pair of wing halves at which a transonic flow forms spatially limited supersonic flow regions that each, in a main flow direction of the flow, end in a compression shock, a boundary layer of the flow is temporarily thickened-up in at least one supersonic flow region at at least one of the two wing halves, when approaching a flight envelope of the aircraft with increasing flight Mach number of the aircraft. The boundary layer of the flow is thickened-up to such an extent that the compression shock at the end of the respective supersonic flow region at the present flight Mach number of the aircraft induces a separation of the boundary layer of the flow from the wing half.


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    Titel :

    Method of and Transonically Operating Aircraft having Devices For Suppressing Aeroelastic Instabilities


    Beteiligte:
    BACKHAUS KAI (Autor:in) / ARNOLD JÜRGEN (Autor:in) / HENNINGS HOLGER (Autor:in) / TICHY LORENZ (Autor:in)

    Erscheinungsdatum :

    2022-10-13


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge