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《Journal of Astronautics》 2009-01
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Configuration Effect Analysis of Scramjet Combustor Based on the Integral Balanceable Method

HUANG Wei,LI Xiao-shan,WU Xian-yu,WANG Zhen-guo (Inst.of Aerospace & Material Engineering,National Univ.of Defense Technology,Changsha 410073,China)  
Combustor configuration makes a great difference in the research of scramjet engine.Its inner flow and combustion mechanism is very complex.The influence of different equivalent ratio and different fuel injection methods to the hot inner thrust and inner thrust integral specific impulse of scramjet combustor was discussed by using the integral balanceable method.It is concluded that the effect of the third and fourth expansion sectors to the performance is the most important,the effect of the first one is the least important.when the fuel injection position moves forward,the effect of the second expansion sector is more important.
【Fund】: 国防科技大学优秀研究生创新资助项目(B070101)
【CateGory Index】: V235.213
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