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1. Review on the Recent Development of Multi-mode Combined Detonation Engine | |||
JIN Le,FAN Wei,WANG Ke | |||
Aviation 03 March 2012 | |||
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Abstract:In the next few years, the development of hypersonic aircraft will be the priority of national defense strategy of many countries, and the significance of the propulsion system applied on the aircraft is self-evident. At present, there are no propulsion systems for the aircraft can be used independently in wide range of Mach numbers and flight envelop. The multi-mode combined detonation engine, which consists of four modes, is a novel propulsion concept proposed at the beginning of this century for potential application on hypersonic cruise or space access. The multi-mode combined detonation engine is thought to be a promising propulsion system which can be used independently in wide range of Mach numbers and flight envelop. Recently, many countries extremely valued the development of multi-mode combined detonation engine and much progress is obtained. A review is made to the recent development of the multi-mode combined detonation engine in this study. The superiority and disadvantages are comparatively analyzed and the major progress for each mode is detailed introduced in the following text. Also, the problems need to be attention in the future development for multi-mode combined detonation engine is discussed. | |||
TO cite this article:JIN Le,FAN Wei,WANG Ke. Review on the Recent Development of Multi-mode Combined Detonation Engine[OL].[ 3 March 2012] http://en.paper.edu.cn/en_releasepaper/content/4469840 |
2. Experimental Research on Supersonic Combustion in Resistance Heated Facility | |||
Le Jialing,Song Wenyan,Zhong Zipeng | |||
Aviation 03 March 2008 | |||
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Abstract:The resistance heated facility for scramjet combustor experiment is researched in Northwest Polytechnical University. The characteristic and operating parameter of the facility are shown. The maximum total temperature of airflow in the exit of the resistance heater can reach about 1000K corresponding to mass flow rate of 0.73kg/s, heater electric power of 750KW. The preliminary test results of the hydrogen, ethylene and kerosene ignition for the model of scramjet combustor are given at different equivalence ratios. Successful ignition and sustained main stream combustion is achieved with normal fuel injection in combustor entrance total temperature about 1000K, Mach number 2.0 and total pressure 0.8MPa. The preliminary numerical simulation results of flow field of hydrogen combustion are presented. | |||
TO cite this article:Le Jialing,Song Wenyan,Zhong Zipeng. Experimental Research on Supersonic Combustion in Resistance Heated Facility[OL].[ 3 March 2008] http://en.paper.edu.cn/en_releasepaper/content/18960 |
3. PERFORMANCE SIMULTION OF WAVERIDER FOREBODY INTEGRATED WITH HYPERSONIC INLET | |||
Hong Xiao | |||
Aviation 18 November 2005 | |||
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Abstract:The calculation method to compute flow field from given shock wave was developed. With the method, intersected cones that can generate three closed shock waves were designed. The waverider forebody that can generate three attached shock waves and a comparative reference waverider forebody that can generate one attached shock wave and two plane shock waves were designed. To better understand two forebodies’ performance, three dimensional flow field calculation of two forebodies integrated with hypersonic inlet was conducted. The computational results showed that the performance of original waverider with three attached shock wave was great better than that of comparative reference waverider. Compared with the comparative reference model, the flow coefficient and the recovery coefficient of total pressure were increased by 15.38% and 7%, repectively. The uniformity coefficient of inlet outlet was increased by 8.8%.Two waverider forebodies integrated with hypersonic inlet showed better perforemance in high mach number and attack angle than that in low mach number and negative attack angle. CFD predictions showed that the design mach number of waverider forebody should be great than the flight mach number and the design attack angle should be less than that of flight condition. | |||
TO cite this article:Hong Xiao. PERFORMANCE SIMULTION OF WAVERIDER FOREBODY INTEGRATED WITH HYPERSONIC INLET[OL].[18 November 2005] http://en.paper.edu.cn/en_releasepaper/content/3693 |
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