Numerical Analysis Study of the Reacting Flow in a Scramjet Airbreathing Engine
Tutor / director / evaluatorLizandra Dalmases, José Oriol
Document typeBachelor thesis
Rights accessRestricted access - author's decision
Scramjet engines are the fastest form of propulsion that has been conceived, being capable offlying in a flight regime above Mach number 5. The concept of scramjet engine is not recent,as its development started more than half a century ago. However, a scramjet vehicle has onlyflown three times (by NASA), being the last one in 2004 and reaching a Mach number of 10.The working principle of a scramjet engine is the same as the subsonic engines: compressing,combusting and expanding air to produce thrust. Nevertheless, scramjet engines do not havemoving parts such a compressor or a turbine, as the flow at hypersonic speed is compresseddirectly by the inlet and the combustion is held in supersonic regime.In this study, a parametric model for the combustor and nozzle of a scramjet engine has beendeveloped, focusing in the combustion process. Under quasi-one-dimensional steady flowconditions, the properties at the exit of the combustor and nozzle are computed by calculatingthe composition of the gas at the combustor for different conditions of temperature, fuel ratio,pressure and velocity.Also, in order to assess the performance of the engine, a simplified inlet model is assumed.Finally, the results of this document are compared with those of other studies. Some possibleimprovements of the study are also included.