中文摘要：

选取了一组接近超燃发动机内部实际工况的边界条件，对二维平行缝槽形式的超音速气膜冷却进行了数值计算，比较了吹风比、缝槽高度和隔板厚度等因素对壁面冷却效率的影响，并考虑了不同强度的斜激波入射气膜冷却边界层对壁面冷却效果和压力分布的影响。通过回归分析，不受激波影响的超音速气膜冷却的壁面冷却效率可以整理成统一的关联式。计算结果表明，斜激波入射将使入射点及其下游的壁面冷却效率降低，但是这个影响没有向上游传播。

英文摘要：

A typical set of boundary conditions as the practical scramjet was imposed to the 2-D simulation model of supersonic film cooling generated by planar slot. Influence parameters such as slip and slot height, blowing ratio as well as the incidence of oblique shock were considered. The cooling effectiveness could be fitted into a general relation equation with regressive analysis. The cooling protection deterioration with the incidence oblique shock was apparent, which, however, did not spread upstream.