An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of a turboprop-nacelle installation on the pressure distributions over a swept, supercritical wing. The tests were conducted at Mach numbers from 0.20 to 0.80, at angles of attack from 0 to 5 degrees, nacelle nozzle pressure ratios from 1.0 to 1.6, and at propeller tip speeds from 700 to 800 ft/sec. The results of this study indicate that the turboprop nacelle interference, with and without power, on a swept wing is greater on the inboard wing panel than on the outboard wing panel. The over-the-wing nacelle installation with the propeller upwash on the inboard panel had flow separation problems at a Mach number of 0.80. No severe flow separation problems appear to exist for either propeller rotation direction for the under-the-wing nacelle installation. The local flow disturbances caused by the under-the-wing nacelle installation were in general less severe than for the over-the-wing nacelle installation.


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    Titel :

    Experimental Investigation of an Advanced Turboprop Installation on a Swept Wing at Subsonic and Transonic Speeds


    Beteiligte:
    J. R. Carlson (Autor:in) / O. C. Pendergraft (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    242 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch