For transonic free stream, sudden performance degradation occurs. For the further supersonic range, performance losses increase slightly with increasing Mach number.
在继续的超声速范围内,性能损失随外流马赫数增加只有小幅增长。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
采用块结构网格与二阶精度流场分区求解技术,对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
对某冲压增程弹用超声速双锥进气道流场特性进行研究,在风洞试验中得到合理的流场结构图谱及试验数据。
应用推荐