Ejector Nozzle Development
ROCKWELL INTERNATIONAL COLUMBUS OH NORTH AMERICAN AIRCRAFT OPERATIONS
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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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