An investigation was conducted in the NACA Lewis altitude wind tunnel to determine effect of altitude and flight Mach number on performance of tail-pipe burner equipped with variable-area exhaust nozzle and installed on full-scale turbojet engine. At a given flight Mach number, with constant exhaust-gas and turbine-outlet temperatures, increasing altitude lowered the tail-pipe combustion efficiency and raised the specific fuel consumption while the augmented thrust ratio remained approximately constant. At a given altitude, increasing flight Mach number raised the combustion efficiency and augmented thrust ratio and lowered the specific fuel consumption.


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    Title :

    Altitude Performance Characteristics of Tail-pipe Burner with Variable-area Exhaust Nozzle


    Contributors:

    Publication date :

    1950-08-11


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English






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