In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter airplane, lower surface spoilers were tested on a 0.055-scale wind-tunnel model. The Mach number range of the tests was 0.8 to 1.2 at Reynolds numbers of approximately 4 million. Although the spoilers produced a moderate decrease in the trim change at low altitudes, they also produced a large increase in drag. Pressure-distribution tests with external fuel tanks showed large pressure changes on the lower surface of the wing due to the tanks.


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    Titel :

    Effect of Lower Surface Spoilers on the Transonic Trim Change of a Wind-Tunnel Model of a Fighter Airplane Having a Modified Delta Wing


    Beteiligte:
    R. C. Robinson (Autor:in)

    Erscheinungsdatum :

    1959


    Format / Umfang :

    54 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch