关键词: 超音速燃烧冲压式喷气发动机;燃烧室;计算;航天飞机主发动机

Abstract: In this paper is presented an analysical method for supersonic combustor study, which is based on the Billig model and AHHYMKNH formula.As example,the operating regime,wall profile and performance parameters of supersonic combustors with entry Mach number 2.2 are computed in some detail. Some useful information for supersonic combustor design has been obtained.

Key words: Supersonic combustion ramjet engine;Combustor;Computation;Space shuttle main engine