A 0.1-scale model of an F-8 aircraft was tested over a range of Mach numbers from 1.5 to 2.0. Reynolds number of 4.12 million was based on wing mean-aerodynamic chord for angles of attack varying from -2 deg to +12 deg. The model was equipped with an advanced-technology-conformal-variable-camber wing (ATCVCW) having simple hinge flaps. Data were also obtained for the model equipped with the basic F-8 wing and conventional flaps. Model variables included aileron and wing trailing edge deflections and horizontal tail incidence. The ATCVCW configuration produced slight improvements in lift-curve slope, drag, and static longitudinal stability over that of the basic F-8 wing configuration. Flap effectiveness was essentially the same for both wings.


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    Titel :

    Aerodynamic characteristics of an F-8 aircraft configuration with a variable camber wing at Mach numbers from 1.5 to 2.0


    Beteiligte:
    Boltz, F. W. (Autor:in)

    Erscheinungsdatum :

    1977-12-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch