Abstract
The flow separation phenomenon often occurs in large area ratio nozzles of rocket engines, in order to study the relationship between the combustion chamber pressure and the flow separation point and the effect of flow separation on the nozzle. The numerical simulation of nozzle under different chamber pressures is carried out by using computational fluid dynamics (CFD) method. The compressible Navier-Stokes equations are used to calculate the fluid region. One equation Spalart-Allmaras turbulence model is selected. A second-order implicit advection upstream splitting method (AUSM) scheme is employed for the convection term. The flow fields of nozzle under different nozzle pressure ratios are obtained, and the pressure distribution of nozzle and flow separation position are analyzed. The results show that the flow separation point departs from the inlet of the nozzle as the nozzle pressure ratio (NPR) increases. This research can provide a corresponding reference for the design and analysis of relevant nozzle.
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