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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    Title :

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


    Contributors:
    Katz, J. (author) / Corsiglia, V. R. (author) / Barlow, P. R. (author)

    Conference:

    Joint Propulsion Conference ; 1980 ; Hartford, CT


    Publication date :

    1980-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



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