NASA-ARC has an ongoing research program to investigate high-angle-of-attack aerodynamic phenomena associated with high-performance aircraft. As part of this research, two rotary-balance apparatuses have recently been developed for testing airplane models in a coning motion. A new 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 a 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 has been 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 Dynamics Model (SDM). Effects of spin-rate parameter and model attitude were investigated. This paper presents a description of the two rigs and a discussion of some of the results obtained in the respective tests.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    1985


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English