A semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag or several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center 40 x 80-ft Wind Tunnel. It was found that the cooling air inlet geometry of opposed piston engine installations has a major effect on inlet pressure recovery, but only a minor effect on drag. Exit location showed large effect on drag, especially for those locations on the sides of the nacelle where the suction characteristics were based on interaction with the wing surface pressures.


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    Titel :

    Cooling Air Inlet and Exit Geometries on Aircraft Engine Installations


    Beteiligte:
    J. Katz (Autor:in) / V. R. Corsiglia (Autor:in) / P. R. Barlow (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    7 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Cooling Air Inlet and Exit Geometries on Aircraft Engine Installations

    Joseph Katz / Victor R. Corsiglia / Philip R. Barlow | AIAA | 1982


    Cooling Air Inlet and Exit Geometries on Aircraft Engine Installations

    Katz, Joseph / Corsiglia, Victor R. / Barlow, Philip R. | NTRS | 1982