A CFD Analysis of Compressible Flow Through Convergent-Conical Nozzles

摘要

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