Research on Scramjet Full Flowpath Design and Numerical Simulation
Because of the excellent performance and great potentiality at hypersonic range, scramjet engineis becoming the most promising and attractive thruster for next generation hypersonic aircraft. Therefore, the related technologies of scramjet and scramjet -powered hypersonic aircraft were intensively developed all over the world in the past decades. One of the keys for the success of airbreathing hypersonic aircraft is the effective integration design of airbreathing scramjet engine with the airframe. The integrated propulsive flowpath of scramjet configuration was preliminarily designed and analyzed in this paper. The flow-fields characteristics and performance of the designed twodimensional integrated propulsive flowpath were numerically calculated with various equivalent fuelair ratio conditions, using computational fluid dynamics methods. The calculation results were then compared with the experimental data at some typical conditions, and the flow-field and performance of the integrated scramjet flowpath with different equivalent fuel-air ratio were analyzed and discussed in detail. The investigation results from this efforts show that: ①The three oblique shock waves of forebody/inlet compression are well attached to the inlet cowl-lip at the design point flight Mach of 6.0; ②The inlet function is beyond of disturbing by combustion induced shock wave and pressure fluctuations under the equivalent fuel-air ratio condition of 1. 0, which is well-satisfied to the design requirements; ③With the increasing equivalent fuel-air ratio, the combustion intensity in the combustor is significantly enhanced, resulting in a increasing net-thrust of the propulsive flowpath.
scramjet hypersonic propulsive flowpath design numerical simulation performance
Li Jianping Song Wenyan Xiao Yinli Luo Feiteng
School of Engine and Energy, Northwestern Polytechnical University, Xian 710072,China School of Engine and Energy, Northwestern Polytechnical University, Xian 710072, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1135-1138
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）