Abstract—

Combustion flow inside the channel of a model scramjet air inlet with transverse hydrogen fuel injection from the bottom wall is investigated. The OH-concentration and pressure distributions that replicate qualitatively the flow structure observed in experiments are obtained. Several different mechanisms of formation of shock waves in the investigated experimental facility are distinguished. In analyzing the structure of fuel jet, satisfactory quantitative agreement with the calculation results of other authors is obtained. It is shown that the shock-wave structure affects significantly combustion enhancement.

中文翻译：

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超音速横流横向氢燃料喷射模型超燃冲压发动机进气口的流动结构研究

摘要——

研究了从底壁横向喷射氢燃料的模型超燃冲压发动机进气道内的燃烧流动。获得定性复制实验中观察到的流动结构的 OH 浓度和压力分布。在所研究的实验设施中形成了几种不同的冲击波机制。在分析燃料射流的结构时，与其他作者的计算结果得到了令人满意的定量吻合。结果表明，激波结构对燃烧增强有显着影响。