Wind-tunnel investigation was conducted to further the development of leading-edge wing inlets. Aerodynamic tests of the basic wing and the original inlet were also made. The original inlet was found to decrease the maximum lift coefficients and to have critical Mach numbers below those of the wing with the basic nose installed. The total pressure recovery in the oil cooler ducts was poor, regardless of the inlet installation. Two inlets were developed that should be satisfactory for a 4-engine airplane.


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    Title :

    Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane


    Contributors:

    Publication date :

    1947


    Size :

    69 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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