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对超燃冲压发动机Ma =6条件下的燃烧性能进行了试验 ,对发动机隔离段长度及支柱进行技术状态调整 ,研究不同状态下燃料当量比分布及燃烧效率和推力的变化关系 ,并找出了对发动机气动轮廓改进的方向。
The combustion performance of the scramjet Ma = 6 was tested. The length of the engine isolation strut and the support pillar were adjusted. The relationship between fuel equivalence ratio distribution and combustion efficiency and thrust under different conditions was studied. Improve the direction of the aerodynamic profile of the engine.