Investigation was conducted in Langley transonic blowdown tunnel to compare two methods for reducing pressure drag; results indicate that, for relatively slender configuration, streamline concept of shaping fuselage does not offer pressure drag reduction greater than that obtainable with supersonic-area-rule concept.


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    Titel :

    Effect of streamline contouring in wing-fuselage juncture in combination with supersonic area rule on swept-back-wing-fuselage configuration of high fineness ratio


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:


    Erscheinungsdatum :

    1960


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :