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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    Title :

    Pressure Available for Cooling with Cowling Flaps


    Contributors:

    Publication date :

    1941-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English



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