SSME nozzle flow field calculations using parc CFD code

The purpose of this research is to validate the use of the PARC computational fluid dynamics (CFD) computer code to calculate the rocket nozzle flow fields and relative performance levels for the Space Shuttle Main Engine (SSME).

Three SSME nozzle flow fields (inviscid, laminar, and turbulent) were calculated using the PARC code. The results were compared to existing data and/or theoretical calculations in order to validate the code.

This thesis describes the process of generating a flow field solution with the PARC code. The generation of the computational grid, the choice of the PARC code inputs, and the user's interaction with the PARC code required to achieve a converged flow field solution are discussed.

The results of the research show that the PARC code inviscid flow field calculations compare well with existing data generated by a highly regarded computational fluid dynamics code. The viscous PARC results show good correlation with theoretical and empirical calculations. The capability of the PARC code as a rocket nozzle design tool was demonstrated by calculating and contrasting the nozzle performance parameters for the various nozzle flow field solutions.