Report presents the results of a full-scale investigation conducted in the NACA 20-foot tunnel to determine the pressure difference available for cooling with cowling flaps. The flaps were applied to an exit slot of smooth contour at 0 degree flap angle. Flap angles of 0 degree, 15 degrees, and 30 degrees were tested. Two propellers were used; propeller c which has conventional round blade shanks and propeller f which has airfoil sections extending closer to the hub. The pressure available for cooling is shown to be a direct function of the thrust disk-loading coefficient of the propeller.


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    Titel :

    Pressure Available for Cooling with Cowling Flaps


    Beteiligte:
    Stickle, George W (Autor:in) / Naiman, Irven (Autor:in) / Crigler, John L (Autor:in)

    Erscheinungsdatum :

    01.01.1941


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch



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    Stickle, G.W. / Joyner, U.T. | Engineering Index Backfile | 1938