Abstract

This paper is devoted to the analyses of the performances of scrarnjet engine which consists of the inlet, combustor and nozzle. In the analysis, there are severe difficulties in the combustor due to the problem such as turbulent diffusion of hydrogen fuel and mixing with air at supersonic speed range, and an axisymmetric flow model is adopted and chemical equilibrium is assumed. 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.