An investigation was conducted to determine the effects of wing leading-edge flap deflections on the subsonic longitudinal aerodynamic characteristics of a wing-fuselage configuration with a 44 deg swept wing. The tests were conducted at Mach numbers from 0.40 to 0.85, corresponding to Reynolds numbers (based on wing mean geometric chord) of 2.37 x 1,000,000 to 4.59 x 1,000,000 and at angles of attack from -3 deg to 22 deg. The configurations under study included a wing-fuselage configuration and a wing-fuselage-strake configuration. Each configuration had multisegmented, constant-chord leading-edge flaps which could be deflected independently or in various combinations.


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    Titel :

    Effects of Wing Leading-Edge Flap Defections on Subsonic Longitudinal Aerodynamic Characteristics of a Wing-Fuselage Configuration with a 44 Deg Swept Wing


    Beteiligte:

    Erscheinungsdatum :

    1978


    Format / Umfang :

    38 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch