To quantify the installed performance of high speed (M = 0.8) turboprop propulsion systems, an experimental program designed to assess the magnitude of the aerodynamic interference of a propeller slipstream on a supercritical wing has been conducted. The test was conducted in the NASA Ames 14-foot wind tunnel. An ejector-nacelle propeller slipstream simulator was used to produce a slipstream with characteristics typical of advanced propellers presently being investigated. A supercritical wing-body configuration was used to evaluate the interference effects. A traversing total pressure rake was used to make flow field measurements behind the wing and to calibrate the slipstream simulator. The force results indicated that the interference drag amounted to an increase of ten counts or about 3% of the wing-body drag for a two engine configuration at the nominal propeller operating conditions. However, at the higher swirl angles (11 deg vs. 7 deg nominally) the interference drag was favorable by about the same magnitude.


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    Titel :

    Simulated Propeller Slipstream Effects on a Supercritical Wing


    Beteiligte:
    H. R. Welge (Autor:in) / J. P. Crowder (Autor:in)

    Erscheinungsdatum :

    1978


    Format / Umfang :

    72 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Simulated propeller slipstream effects on a supercritical wing

    Welge, H. R. / Crowder, J. P. | NTRS | 1978


    Analysis of Propeller Slipstream Effects on a Trailing Wing

    Veldhuis, L. L. M. | British Library Online Contents | 1996



    Propeller slipstream wing interactions at Mach no. 0.8

    Bencze, D. P. / Smith, R. C. / Welge, H. R. et al. | NTRS | 1978


    Analysis of Propeller Slipstream Effects on a Trailing Wing

    Veldhuis, L. L. M. / American Institute of Aeronautics and Astronautics / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1996