The flowfield within and around two dimensional thrust reversing and thrust vectoring nozzles has been calculated using a new unfactored implicit method with a multiple zone grid. Computations are done for fully deployed thrust reversing nozzles, partially deployed thrust reversing nozzles with thrust vectoring, and a nozzle transitioning from partially to fully deployed. Agreement with available experimental data is good.


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    Title :

    Numerical solution of 2-D thrust reversing and thrust vectoring nozzle


    Contributors:
    Imlay, S. (author)

    Publication date :

    1986-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English







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