A subscale injector test program conducted with a ten-inch diameter like-doublet injector to determine performance and heat flux profiles vs chamber pressure and propellant mixture ratio, and to determine stability characteristics with various acoustic cavity configurations is described. Results are presented. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space Shuttle Maneuvering Engine Reusable Thrust Chamber Program. Task 11: High Epsilon Injector Test Report


    Contributors:

    Publication date :

    1974


    Size :

    52 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English