Analysis for design of axisymmetric rocket motor nozzles is based upon assumptions for reacting flows; method is presented for employing results to determine whether or not given nozzle contour is actually optimum contour; results of analysis are set of partial differential equations for determining Lagrange multipliers and set of algebraic equations for determining initial conditions for these multipliers on boundaries of region.


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    Title :

    General method for determining optimum thrust nozzle contours for chemically reacting gas flows


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 5 , n 4


    Publication date :

    1967


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :