Abstract
Work presented at the 1 Propulsion Aerodynamics Workshop on the CFD study of compressible ow through convergent-conical nozzles is summarized. This work focused on assessing the accuracy of the CFD study in obtaining nozzle performance and ow structure, including nozzle thrust and discharge coe cients and the shock structure. The CFD studies were performed using Metacomp CFD++ software and compared with the available experimental data during the workshop. We con rmed that the discharge coe cient increases as the nozzle angle decreases and the choked nozzle pressure ratio is lower for a smaller nozzle angle. The discharge coe cient increases with increasing pressure ratio until the choked condition is reached. The thrust coe cient increases as the nozzle angle increases, and for a given nozzle angle, the thrust coe cient decreases as nozzle pressure ratio increases. Results and assessments are presented in this paper and at the 49 AIAA Joint Propulsion Conference.
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