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使用Ｍａ＝２．５的高温气流测量了超燃冲压发动机喷管的推力，高达３１００Ｋ的总温通过燃烧一甲基肼（ＭＭＨ）和四氧化二氮（ＮＴＯ）获得。监测喷管壁压，以估算出喷管的压力，使用相同的喷管进行一组低温氮（Ｎ２）流实验。一种非粘性二维码可模拟低温氮流时的喷管性能。化学动力学计算还预测出了误差在３．６％以内的ＭＭＨ／ＮＴＯ实验结果。对超燃冲压发动机喷管内的动力损失、二维损失和摩擦损失进行了鉴定，还讨论了Ｈ２燃料发动机喷管性能的尺度效应。
The thrust of the scramjet engine nozzle was measured using a high temperature air flow of Ma = 2.5 and the total temperature up to 3100K was obtained by burning monomethylhydrazine (MMH) and dinitrogen monoxide (NTO). The nozzle wall pressure was monitored to estimate the nozzle pressure and a set of low temperature nitrogen (N2) flow experiments were performed using the same nozzle. A non-sticky two-dimensional code simulates nozzle performance at low temperature nitrogen flow. The chemical kinetics calculation also predicted the MMH / NTO experimental results with an error of less than 3.6%. The power loss, two-dimensional loss and friction loss in the scramjet engine nozzle were identified, and the scale effect on the nozzle performance of the H2 fuel engine was also discussed.