This paper describes the Computation Fluid Dynamics (CFD) model developed to simulate the supersonic rocket exhaust in an entrained flow cylinder. The model can be used to study the plume-induced environment due to static firing test of the Taurus II launch vehicle. The finite rate chemistry is used to model the combustion process involving rocket propellant (RP 1) and liquid oxidizer (LOX). A similar chemical reacting model is also used to simulate the mixing of rocket plume and ambient air. The model provides detailed information on the gas concentration and other flow parameters within the enclosed region thus allowing different operating scenarios to be examined in an efficient manner. It is shown that the real gas influence is significant and yields better agreement with the theory.


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    Title :

    Combustion Model of Supersonic Rocket Exhausts in an Entrained Flow Enclosure


    Contributors:

    Conference:

    20th AIAA Computational Fluid Dynamics Conference ; 2011 ; Honolulu, HI, United States


    Publication date :

    2011-06-27


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English