A method for designing a non-waisted fuselage for supersonic wing/fuselage configurations that increases the fuselage volume and improves the supersonic aerodynamic performance compared to a conventional waisted-fuselage configuration. The method entails removing the waisted region of an existing waisted-fuselage configuration by linearly reconstructing cross-sections between the endpoints representing the waisted cross-sectional area portion to create a modified fuselage configuration without waisting. This configuration will have increased fuselage volume and improved supersonic aerodynamic performance. The fuselage camber can then be optimized using non-linear aerodynamic methods to further increase the supersonic aerodynamic performance.


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    Titel :

    Non-waisted fuselage design for supersonic aircraft


    Beteiligte:

    Erscheinungsdatum :

    1999-05-04


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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