Two rotary balance apparatuses were developed for testing airplane models in a coning motion. A large scale apparatus, developed for use in the 12-Foot Pressure Wind tunnel primarily to permit testing at high Reynolds numbers, was recently used to investigate the aerodynamics of 0.05-scale model of the F-15 fighter aircraft. Effects of Reynolds number, spin rate parameter, model attitude, presence of a nose boom, and model/sting mounting angle were investigated. A smaller apparatus, which investigates the aerodynamics of bodies of revolution in a coning motion, was used in the 6-by-6 foot Supersonic Wind Tunnel to investigate the aerodynamic behavior of a simple representation of a modern fighter, the Standard Dynamic Model (SDM). Effects of spin rate parameter and model attitude were investigated. A description of the two rigs and a discussion of some of the results obtained in the respective test are presented.


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    Titel :

    Recent Developments in Rotary-Balance Testing of Fighter Aircraft Configurations at NASA Ames Research Center


    Beteiligte:
    G. N. Malcolm (Autor:in) / L. B. Schiff (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    28 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch