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。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
This powerful plane combined high supersonic speed (1800 km/h) with significant fire range.
这架威力无比的飞机有着极高的速度（1800公里/小时），同时有着非常远的火力射程。
This powerful plane combined high supersonic speed (1800 km/h) with significant fire range.
这架威力无比的飞机有着极高的速度（1800公里/小时），同时有着非常远的火力射程。
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