With regard to performance factors analysis of scramjet for air-breathing hypersonic flight vehi-cle in a state of standard design which include total-pressure recovery coefficient and Mach number of forebody /inlet exit,fuel equivalence ratio,static pressure expansion coefficient of afterbody/nozzle and fuel characteristic.Firstly,based on airflow impulse function of some cross section,the models of internal relation between scramjet performance and airflow parameters were decided through a quasi-one-dimen-sional steady model educed by conservation of mass,momentum and energy.What's more,the performance of supersonic mode for scramjet was researched in combination with instances.The results of research have illustrated that scramjet performance influence factors need to be optimization and compromise,and effection of fuels was determined by theirs caloric caloricity besides by numbers of carbon and hydrogen as well as theirs ratio.%针对设计状态下超燃冲压发动机前体／进气道出口总压恢复系数和马赫数、燃料当量比、后体／尾喷管静压膨胀系数及燃料特性对其性能的影响进行了初步分析。首先通过质量、动量和能量三大守恒定律，利用截面上气流冲量建立了发动机性能与气流参数的内在关系模型，然后对设计状态下超燃冲压发动机的性能进行了研究。研究结果表明，性能影响因素需要最优化折中考虑；燃料对发动机性能影响主要由其热值起决定作用。
展开▼
