Abstract
The plug nozzle is one of the concepts proposed to improve the overall performance of large liquid rocket engines for launcher first stages. One of the aspects to be investigated is the three dimensional flow field generated by partitioning of the primary nozzle in modules. Three configurations with different size of the gap between two adjacent primary nozzles are selected and numerically simulated. Specific three-dimensional flow structures that take place on the plug are identified comparing the numerical solutions. The relationship between these structure and the skin friction distribution along the plug surface is also investigated. Finally, a performance analysis of the selected test cases based on the thrust coefficient evaluation is presented.
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