The Primary Investigation On Effect Of The Baffle Configuration On Multi-Module 2-D Hypersonic Inlet

As an Important component of scramjet, the hypersonic inlet of good performance and reliable work can supply the stable gas flow and flow field by the engine request. Since its simple structure and relatively mature technology, 2D inlet is widely adopted by variety of hypersonic vehicles. For multi-module inlet can meet the needs of making more than one scramjet to work simultaneously, it is got wide attention at the beginning of the development of hypersonic vehicles. In this paper, Multi-module 2D inlet is studied focusing on the impact of different inlet baffle configuration on the performance of multi-module 2D inlet and the discrepancies result from the coupling impact with the commercial software"Ansys Fluent". Through the comparison of inlet performance with different baffle configuration a conclusion can be drawn that baffle thickness and baffle wedge angle can make the total pressure recovery and other parameters worse. Through analysis the unstart process of different inlets with respective baffle configuration, a result show that inhibition the development of cowl separation zone play an important role to maintain the stability of the entire intake system. By the numerical approach a result shows that proper sweep angle of inlet baffle significantly lower the coupling impact on the adjacent module in the meantime get a similar flow field as no sweep baffle inlet under the design condition.