Prediction of convective base heating rates for a new launch vehicle presents significant challenges to analysts concerned with base environments. The present effort seeks to augment classical base heating scaling techniques via a detailed investigation of the exhaust plume shear layer of a single H2/O2 Space Transportation Main Engine (STME). Use of fuel-rich turbine exhaust to cool the STME nozzle presented concerns regarding potential recirculation of these gases to the base region with attendant increase in the base heating rate. A pressure-based full Navier-Stokes computational fluid dynamics (CFD) code with finite rate chemistry is used to predict plumes for vehicle altitudes of 10 kft and 50 kft. Levels of combustible species within the plume shear layers are calculated in order to assess assumptions made in the base heating analysis.


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    Title :

    Axisymmetric computational fluid dynamics analysis of a film/dump-cooled rocket nozzle plume


    Contributors:

    Conference:

    AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States


    Publication date :

    1993-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English