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所属单位：能源与动力学院

发表刊物：Int. Space Planes Hypersonics Technol. Conf.

摘要：The design of tandem type turbine-based combined cycle(TBCC) inlet, which based on the requirement of TBCC engine at wide Mach range was investigated in the present paper. The inlet variable rule was researched at different inflow Mach number. Three dimensional numerical simulation of the inlet was done and the results show that the tandem type TBCC inlet meets the need of mass flow of engines at different inflow Mach number, which is the same as the expectation. Wind tunnel experiment was done at the mode transition Mach number of tandem type TBCC inlet. The results show that the CFD results fit close to the experiment data. The mass flow, the total pressure recovery and distortion of inlet meet the need of the TBCC engine. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

是否译文：否

发表时间：2017-01-01

合写作者：王云飞,刘君,华正旭

通讯作者：袁化成