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Zhou J.,Beijing Mechanical electro Engineering Institute | Wang Y.,Beijing Mechanical electro Engineering Institute
Proceedings of the International Astronautical Congress, IAC | Year: 2013

High Mach scramjet could be a prosperous propulsion choice for hypersonic vehicles. Although some scramjets in the range of Ma 8 to Ma 12 have been investigated around the world, how to design a scramjet to adapt to a HTHL aircraft is still a demanding problem, meaning leaving enough space to install undercarriages, fuel tank, and so on. Focusing on the configuration requirements of a HTHL aircraft, meaning two scramjets installed in the two sides of the aircraft, a possible scramjet configuration was designed and the performance in the flight corridor was investigated with numerical method. The scramjet is designed with stream traced method which can accommodate the requirements of vehicle's forebody shape and downstream of flow passage. Besides, a rectangle to circular isolator was used to connect the inlet throat and the circular combustor and the nozzle with a circular to rectangle shape was designed to adapt the requirements of combustor and the vehicle's afterbody shape. The flow field without fuel injection was simulated through numerical method and performances of full and parts of the scramjet are also presented. And two different strategies, meaning 3-D scramjet flowfield simulation method and 1-D combustor performance analysis combined with 3-D inlet and nozzle flowfield simulation, were used to evaluate the performances of the scramjet with hydrogen fuel injected into the passage. It is shown that the deviation between the two results is located in a reasonable error band. Copyright ©2013 by the International Astronautical Federation.

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