Theoretical flow-fields have been calculated for various nozzle/launch-tube configurations using this flow model. The solutions, thus calculated, are compared with experimental data in the present paper. The principal objectives of the present paper are (1) to present an engineering model for the impingement flow-field which is produced when an underexpanded supersonic nozzle is exhausted into a constant-area tube, (2) to compare the computed flow-field solutions with experimental results, and (3) to use the comparisons to establish the validity of the flow model. (Author)


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    Title :

    The Analysis of Secondary Flows for Tube-Launched Rocket Configurations


    Contributors:
    H. H. Korst (author) / J. J. Bertin (author)

    Publication date :

    1981


    Size :

    50 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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