A study was undertaken in the NASA Langley 14- by 22-foot subsonic tunnel to determine the low-speed aerodynamic characteristics of a powered, generic, hypersonic configuration in ground effect. The model was a simplified configuration consisting of a triangular wedge forebody, a rectangular mid-section which housed the flow through, an ejector type propulsion simulation system, and a rectangular wedge afterbody. Additional model components included a delta wing, a rectangular wedge forebody, inlet fences, exhaust flow deflectors, and afterbody fences. Aerodynamic force and moment data were obtaind over an angle of attack range from -4 to 18 degrees while model height above the tunnel floor was varied from 1/4 inch to 6 feet. Variations in freestream dynamic pressure, from 10 psf to 80 psf, and engine ejector pressure yielded a range of thrust coefficients from 0 to 0.8.


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    Titel :

    Low-Speed, Powered Ground Effects of a Generic, Hypersonic Configuration


    Beteiligte:
    G. M. Gatlin (Autor:in)

    Erscheinungsdatum :

    1990


    Format / Umfang :

    62 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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