Because reliable methods of predicting conditions in the base region of multiple-rocket-powered missiles are non-existent, a wind tunnel test, with a model including hot rockets, was proposed. The main objective of the test was to compare various sustainer turbine exhaust configurations proposed for use on the three-engine missile. Temperature data have been grouped in Table I in a manner which facilitates comparision of the sustainer turbine exhaust configurations.


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    Title :

    Presentation of Temperature Data from the Hot Rocket Jet Effects Test in the Naca Lewis Flight Propulsion Laboratory 8 Feet by 6 Feet Wind Tunnel


    Contributors:
    E. E. Frost (author)

    Publication date :

    1958


    Size :

    23 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English