An investigation was conducted in the Langley Research Center 8-foot transonic pressure tunnel to determine the effects of the landing gear, speed brake and the major airplane protuberances on the longitudinal aerodynamic characteristics of an 0.087-scale model of the TF-8A supercritical-wing research airplane. For the effects of the landing gear and speed brake, tests were conducted at Mach numbers of 0.25 and 0.35 with a flap deflection of 20 degrees and a horizontal-tail angle of -10 degrees. These conditions simulated those required for take-off and landing. The effects of the protuberances were determined with the model configured for cruise (i.e., horizontal-tail angle of -2.5 degrees and no other control deflection), and these tests were conducted at Mach numbers from 0.50 to 1.00. The angle-of-attack range for all tests varied from about -5 degrees to 12 degrees.


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    Titel :

    Effects of Landing Gear, Speed Brake and Protuberances on the Longitudinal Aerodynamic Characteristics of an NASA Supercritical-Wing Research Airplane Model


    Beteiligte:
    D. W. Bartlett (Autor:in) / G. Sangiorgio (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    55 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch