Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.
采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。
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。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
应用推荐