PERFORMANCE ANALYSIS OF SCRAMJET ENGINE WITH QUASI-ONE-DIMENSIONAL FLOW MODEL

In the present study, the quasi-one-dimensional flow model through the scramjet engine which consists of the inlet, combustor and nozzle is proposed. The performances of the components are analysed thermodynamically. In the analysis, there are severe difficulties in the combustor due to problems such as turbulent diffusion of hydrogen fuel and mixing with air at supersonic speed range. For the combustion reaction, the global hydrogen-air combustion model with two-step reaction schemes of hydrogen and oxygen are introduced. To estimate the demerit of weight increase, the axial length of the components is calculated, which presented the basic information about the optimum configuration of the scramjet engine.