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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    Title :

    Aerodynamic Characteristics of an F-8 Aircraft Configuration with a Variable Camber Wing at Mach Numbers from 1.5 to 2.0


    Contributors:
    F. W. Boltz (author)

    Publication date :

    1977


    Size :

    70 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English