Study to determine local values of heat flux in rocket engine thrust chambers that incorporated convergent divergent nozzles of 2 different geometries; largest nozzle expansion area ratio investigated was 20 to 1; chamber pressures ranged from 100 to 300 psia at thrust levels between 1000 and 5000 lb-ft; propellants used were nitrogen tetroxide and hydrazine at nominal mixture ratio of 1.0.


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    Title :

    Experimental investigation of heat transfer rates in rocket thrust chambers


    Additional title:

    AIAA J


    Contributors:
    Witte, A.B. (author) / Harper, E.Y. (author)

    Published in:

    AIAA Journal ; 1 , n 2


    Publication date :

    1963


    Size :

    9 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :





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