关键词: 冲压式喷气发动机;计算;航天飞机主发动机

Abstract: The calculation of thermodynamic and thrust performances for liquid hydrogen ramjet engine with Mach number ranged from 1.5 to 6.5 is performed in this paper. A delicated method of iteration, which considerably simplified the computation of thermodynamic process,is adopted.The evaluation of performance for scramjet with cylindrical combustion chamber is also carried cut. The results show that the cylindershape combustion chamber is not the best design. An adequate divergence for combustion chamber of sera mjet is needed in order to get higher performanee.

Key words: Ramjet engine;Computation;Space shuttle main engine