The uninstalled performance of a full-scale scramjet operating over Mach 7 to 10 and altitudes of 28 to 40 km was numerically analyzed by using high-fidelity Improved Delayed Detached Eddy Simulation (IDDES) with 125.10 million cells and Dynamic Zone Flamelet model (DZFM) with 21,294 flamelet zones. The inviscid thrust can be well correlated with dynamic pressure in the form of a gaussian function, whereas the viscous drag increases almost linearly with dynamic pressure. For the examined scramjet, net thrust is achieved for the low dynamic pressure range below 37 kPa and the high range above 55 kPa. The rule of mixed is burnt is observed, and the final combustion efficiencies vary from 66% to 82%. The upstream propagation of combustion occurs for most of the cases in the current strut-based combustor, and unstart occurs for the case of Mach 7 at 30 km.

通过使用具有 1.251 亿个单元的高保真改进延迟分离涡流模拟 (IDDES) 和动态区火焰模型 (DZFM) 对运行速度为 7 至 10 马赫、高度为 28 至 40 公里的全尺寸超燃冲压发动机的卸载性能进行了数值分析有 21,294 个小火焰区。无粘性推力可以以高斯函数的形式与动压力很好地相关，而粘性阻力几乎随动压力线性增加。对于所检查的超燃冲压发动机，在低于 37 kPa 的低动态压力范围和高于 55 kPa 的高范围内实现了净推力。遵守混合燃烧规律，最终燃烧效率在66%到82%之间。燃烧的上游传播发生在当前基于支柱的燃烧器中的大多数情况下，