Performance features and possible design configurations for oblique wings which would lower the supersonic drag characteristics of fighter aircraft are described. The oblique shape reduces wave drag in proportion to the wing length, and can achieve reductions by factors of 4-16. Variable sweep would be accompanied by fuel pumping to maintain an acceptable center of gravity and tail loading. The lift forces remain balanced and thus remove fuselage loads considerations. Extra tail loading to handle longitudinal moments of center-of-lift shifts with variable sweep aircraft are also eliminated. However, oblique wings couple the roll, pitch and yaw axes and require digital controls to provide balancing forces. NASA has initiated a four phase design, construction and flight test program to examine the flight envelope of oblique wings on the F-8 aircraft.


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    Titel :

    Oblique wing ready for research aircraft


    Beteiligte:
    Gregory, T. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1985-06-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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