[Object] To realize an improvement in design accuracy and a reduction in design time in a process of matching an equivalent cross-sectional area of a design shape of a supersonic aircraft to a target equivalent cross-sectional area in a sonic boom reduction method based on an equivalent cross-sectional area.[Solving Means] The technique includes: setting an initial shape of the airframe and a target equivalent cross-sectional area of the airframe; estimating a near field pressure waveform for the initial shape of the airframe assuming that the supersonic aircraft flies at a cruising speed; evaluating an equivalent cross-sectional area from the estimated near field pressure waveform for the initial shape of the airframe; and setting a Mach plane corresponding to the cruising speed, and setting a design curve on the Mach plane, the design curve corresponding to an initial curve at which the initial shape of the airframe and the Mach plane intersect so that the equivalent cross-sectional area approaches the target equivalent cross-sectional area. Then, the shape of the airframe is designed based on the design curve.


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    Titel :

    METHOD FOR DESIGNING SHAPE OF FUSELAGE OF SUPERSONIC AIRCRAFT, SUPERSONIC AIRCRAFT PRODUCTION METHOD, AND SUPERSONIC AIRCRAFT


    Weitere Titelangaben:

    VERFAHREN ZUM ENTWURF DER FORM DES RUMPFES EINES ÜBERSCHALLFLUGZEUGES, VERFAHREN ZUR HERSTELLUNG VON ÜBERSCHALLFLUGZEUGEN UND ÜBERSCHALLFLUGZEUG
    PROCÉDÉ DE CONCEPTION DE FORME DE FUSELAGE D'AÉRONEF SUPERSONIQUE, PROCÉDÉ DE PRODUCTION D'AÉRONEF SUPERSONIQUE ET AÉRONEF SUPERSONIQUE


    Beteiligte:

    Erscheinungsdatum :

    2021-05-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge