A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 to determine the effects of adding underfuselage speed brakes. The results of brief spoiler-aileron lateral control tests also are included. The tests show acceptable trim and drag increments when the speed brakes are installed at the 32-71-inch fuselage station.


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    Titel :

    Experimental Investigation to Determine the Effect of Speed-Brake Position on the Longitudinal Stability and Trim of a Swept-Wing Fighter Airplane


    Beteiligte:
    R. T. Taylor (Autor:in)

    Erscheinungsdatum :

    1959


    Format / Umfang :

    50 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch