A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

    提出了一种用于飞行器、特别地用于机翼前缘装置的流装置,该流装置包括具有前缘的弯曲的前蒙皮以及与前蒙皮的至少一个翼展边缘联接的至少一个后缘部件,其中,后缘部件包括恒定的横截面轮廓,该横截面轮廓在翼弦方向上渐缩,以形成以后缘终止的两个翼展流动表面,并且其中,后缘部件设计成用于在前蒙皮与两个翼展流动表面中的至少一个翼展流动表面之间提供齐平过渡部。


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    Titel :

    FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT


    Weitere Titelangaben:

    用于飞行器的具有实心后缘部件的流装置


    Beteiligte:
    ERBAN MARCUS (Autor:in) / BENSMANN STEFAN (Autor:in) / FEES MARTIN (Autor:in)

    Erscheinungsdatum :

    2021-09-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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