Overall Performance Calculation of Dual-mode Scramjet Engine
Dual-mode scramjet engine operation at a flight Mach number of 4 - 7 is characterized by supersonic or subsonic flow throughout the combustor. In this paper, a model based on integral equations for performance computation of scramjet is presented, which includes equations of conservation of mass, momentum and energy of OD control volume coupled with chemical kinetics model. The overall performance of scramjet at different flight Mach numbers had also been computed. The performance of thrust and specific impulse for scramjet with different total stoichiometric fuel-to-air ratio and assigned proportioa The computation results indicated the trend of the maximum of total stoichiometric fuel-toair ratio, and the trend of thrust Fn and the specific impulse Isp with different flight Mach numbers and different assigned proportion of fuel, and scramjet operates within a range of Mach numbers (4. 5-7) and dynamic pressure (50kPa) , and scramjet possesses thrust (1,100 N/) and high specific impulse (1,000 kgN/(kg/s)) when fuel-air ratio of combustor equals fuel-air ratio.
dual-mode scramjet engine performance operation mode thermal throat
HUANG Xing CHEN Yu-chun LI Bo LI Jie CAI Yuan-hu
School of Power and Energy, Northwestern Polytechnical University, Xian, China
国际会议
4th International Symposium on Jet Propulsion and Power Engineering(第四届喷气推进与动力工程国际会议 ISJPPE2012)
西安
英文
509-513
2012-09-10（万方平台首次上网日期，不代表论文的发表时间）