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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    Titel :

    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


    Beteiligte:
    E. E. Frost (Autor:in)

    Erscheinungsdatum :

    1958


    Format / Umfang :

    23 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch