Results of a recent low-speed wind-tunnel investigation conducted to define the forebody flow on a 16-percent scale model of the NASA High Angle-of-Attack Research Vehicle, an F-18 configuration, are presented with analysis. Measurements include force and moment data, oil-flow visualizations, and surface pressure data taken at angles of attack near and above maximum lift (36 to 52 deg) at a Reynolds number of one million (based on mean aerodynamic chord). The results presented identify the key flow-field features on the forebody including the wing-body strake.


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    Title :

    Wind-tunnel investigation of the forebody aerodynamics of a vortex-lift fighter configuration at high angles of attack


    Contributors:

    Conference:

    Aerospace Technology Conference and Exposition ; 1988 ; Anaheim, CA, United States


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :