A semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag of several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center's 40- by 80-Foot 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 a 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 :

    Study of cooling air inlet and exit geometries for horizontally opposed piston aircraft engines


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

    Kongress:

    Joint Propulsion Conference ; 1980 ; Hartford, CT


    Erscheinungsdatum :

    01.06.1980


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Cooling Air Inlet and Exit Geometries on Aircraft Engine Installations

    J. Katz / V. R. Corsiglia / P. R. Barlow | NTIS | 1982


    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


    Opposed-piston oil engines

    Waring-Brown, R. | Engineering Index Backfile | 1957