关键词: 冲压发动机；燃烧室；一维流分析；跨声速求解；性能计算

Abstract: In order to establish a kind of suitable ramjet model which does not depend on the experimental data and it can be used to solve the multiple regions of transonic，the existent one-dimensional flow analysis models for ramjet were classified，summarized and comparatively analyzed. The results show that one-dimension models relied on the experimental static pressure data were difficult to meet the computing needs of the actual performance calculation. The isotonic section assumption could be removed，the empirical formula of core flow could be replaced with friction term and the transonic region could be solved by defining a new variable. According to this，an improved one-dimensional flow model for ramjet was established，which could get rid of the needs of the experimental data and solve the multiple regions of transonic. The numerical results were compared with the experimental data，the total pressure error was within 5.2%. Compared with other model ’ s results，the maximum difference in total temperature was 1.3% and the maximum difference in Mach number was 2.7%. The results show good agreement in static pressure，Mach number，total pressure，total temperature etc. The consistent results demonstrate that this improved method can be used for ramjet performance calculation.

Key words: Ramjet；Combustor；One-dimensional flow analysis；Transonic solution；Performance calculation