LAUSR

ABSTRACT Firstly, a one-dimensional steady-state calculation model of the scramjet including forebody/inlet, combustor and nozzle/afterbody has been established. Secondly, based on the one-dimensional steady-state model of the scramjet, a one-dimensional dynamic model of the scramjet has been established with consideration taken to the combustor’s volume effect and the disturbance wave propagation factor. Finally, the engine combustor experimental data in the scramjet laboratory of Northwestern Polytechnical University were used to prove the one-dimensional dynamic model. The combustor pressure distribution that changed over the time of the calculation result was compared with the experimental data. The steady-state model was also used to calculate the pressure distribution that changed over time. The calculation results of the steady-state model, the calculation results of the dynamic model and experimental data were made a contrast. The results showed that compared with the calculation results of the steady-state model, the calculation results of the dynamic model were closer to the experimental data, which could more accurately describe the change process of the combustor flow parameters along the axial direction.