| The present work numerically analyzes a quasi one-dimensional premixed compressible flow using various finite rate chemistry in a scramjet configuration. The focus of the study is on the effects of various finite rate chemistries on the flow field. First, a quasi one-dimensional premixed laminar compressible flow without the source term was considered. Then, two different finite rate chemistries: one-step finite rate chemistry with three species and fifteen-step finite rate chemistry with six species, are analyzed in this study. Analysis also includes variations in the geometry of converging diverging nozzle on the flow field. The numerical simulations were carried out using a computer code developed in-house using C++ programming language. In order to validate the analysis, computational results of a similar problem with global kinetics (Bussing and Murmani 1985) were compared with the present results. Temperature profiles, velocity profiles, and density profiles along the nozzle are compared at different initial conditions using different finite rate chemistries. The study determines the range of operating conditions to enhance combustion of fuel. The study also analyzes the effect of various fuel oxidizer ratios on the temperature, velocity, density, and mass fractions of various species profiles.; From the results obtained it can be concluded that, fuel oxidizer ratio is the significant parameter affecting the flow field. Fifteen-step finite rate scheme gives better description of flow field as compared to global finite rate scheme. Lower inlet temperature (encountered at high altitude) gives high Mach number at nozzle exit. |
