A combination of computer analysis and scale model testing was utilized to develop a nozzle which would increase the performance of thrust augmenting ejectors. Scale model tests were conducted on various multi-lobed and vortex generating nozzles. Predicted jet characteristics were obtained by calculating a finite difference solution of Reynolds equations for the three-dimensional flow field. A two-equation turbulence kinetic energy model was used for closure. It is demonstrated that the thrust augmentation of the XFV-12A ejector can be increased from 1.45 to 1.64 by the addition of lobes to the baseline nozzle, and a corresponding increase of throat width.


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    Title :

    Ejector Nozzle Development


    Contributors:
    E. J. Schum (author) / J. H. DeHart (author)

    Publication date :

    1982


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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