Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.


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    Title :

    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine. VII. Pressure and Temperature Distributions


    Contributors:
    M. J. Saari (author) / W. R. Prince (author)

    Publication date :

    1948


    Size :

    51 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English