Analysis of comparative numerical simulation of free-jet scramjet combustor

Source term among the continuity equations is specially disposed in order to enlarge the scope of two-dimensional/axisymmetric model especially about the normal injecting issue. To testify the above method, a calculation adopting the above source-addition method has been undertaken to make a comparison with three-dimensional method. Both have obtained a satisfactory result. The flow field in a sketch scramjet engine parts were simulated with the adoption of the above injecting simplified method and 5-species, single step reaction model, obtaining the major aerodynamic parameters and components distribution of the channel. Meanwhile, the influence of to the performance of the total pressure tab to the engine was investigated. The profoundness and robustness of the simplified method is highlighted with the presentation of the above work and it is ready to be applied to the engineering field in terms of calculation precision.