The performance and heat transfer characteristics of a doublet element type injector for the space shuttle orbiter maneuvering engine thrust chamber were investigated. Ths stability characteristics were evaluated over a range of chamber pressures and mixture ratios. The specific objectives of the test were: (1) to determine whether stability has been influenced by injection of boundary layer coolant across the cavity entrance, (2) if the injector is stable, to determine the minimum cavity area required to maintain stability, and (3) if the injector is unstable, to determine the effects of entrance geometry and increased area on stability.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space shuttle maneuvering engine reusable thrust chamber program. Task 11: Low Epsilon stability test plan


    Contributors:

    Publication date :

    1974-01-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English