Data were obtained in an altitude test chamber for a range of altitudes from 20,000 to 58,000 feet at a flight Mach number of 0.9, and for several flight Mach numbers at an altitude of 45,000 feet. Data approximating sea-level operation are also included. Engine component performance data are presented in addition to windmilling, exhaust-nozzle, and ejector performance.


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    Title :

    Preliminary Altitude Performance Data for the J71-A2 (X-26) Turbojet Engine


    Contributors:

    Publication date :

    1954-08-19


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English