| Solid fuel scramjet has the advantages of simple structure, high reliability, easy long-term storage, can be quickly used etc., especially in the field of hypersonic applications have the advantage and become a research hotspot in recent years. As a key part of scramjet the inlet has crucial influence on the overall performance. In recent years all kinds of inward turning inlet of surfaces compression gradually gets the wide attention of each country by its high performance, and become a new hypersonic inlet development direction. The solid fuel scramjet internal flow field has been researched with calculation and analysis, mainly includes the following two parts:First, based on a new basic flowfield design method of the hypersonic inward turning inlet, the design process of the pressure gradient controllable inward turning inlet has been studied, How the pressure gradient coefficient and other design parameters influence the basic flowfield flow characteristics has been researched; The flow characteristics of three kinds of typical gradient coefficient basic flowfield were obtained, and compute the three dimensional compression inlet model of the three pressure gradient basic flowfield with numerical simulation, analysis on flowfield characteristics, obtain the performance of the three inlet model. The results showed that the constant pressure gradient inlet is a more appropriate compromise; Numerical analysis the flow field performance after cut lip mouth on inward turning inlet, the conclusion is that after the appropriate cuting lip operation for three-dimensional inlet model, can improve the work and starting performance of inlet.In second, based on solid fuel scramjet experiments in the literatures, applied its engine model, referenced a solid fuel scramjet combustion flow mathematical model, used solid fuel of PMMA, considered a simplified multi-step reactions, selected of EDM combustion model and standard k-εturbulence model, the combustor of the engine were investigated by numerical simulation and analysis of its flow field characteristics. The numerical results show that the solid fuel scramjet combustor flow field characteristics including mach number distribution, pressure distribution and temperature distribution are in agreement with the theoretical and experimental results; Along the axial wall surface pressure distribution and experimental measurement results are basically consistent; Fuel regression rate and experimental data have certain difference but the data distribution trend approximation. The results shows that this numerical model has a certain reference value for the solid fuel scramjet research. |
