The invention provides a supersonic nozzle arranging method. Three or more supersonic nozzles are evenly distributed on the plane where a circumferential base line locates along a tangent line of the circumferential base line in head-to-tail and staggered modes. The cross section of the outer contour of the part, positioned out of the circumferential base line, of each supersonic nozzle is square, and is provided with four side walls, wherein the four side walls comprise a lower horizontal side wall, an upper horizontal side wall, an inner vertical side wall and an outer vertical side wall, and the outer vertical side wall is tangent with the circumferential base line. When airflow injected by the supersonic nozzles is circulated in a circle, air swirl flow is formed.


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    Titel :

    Supersonic nozzle arranging method


    Beteiligte:
    ZHANG YUAN (Autor:in)

    Erscheinungsdatum :

    2015-07-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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