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为评估圆顶燃烧室中安装锥形旋流器后产生的效能，研究了安装或不装锥形旋流器的管道式侧向进气道冲压火箭复合式发动机流场。锥形旋流器的使用将改善流体图谱并加强燃烧室流体涡旋强度以便以解燃烧室过热部位并进一步提高油／气混合效率。用ＫＩＶＡ３程序对燃烧室流场进行了模拟和计算。模拟结果表明这种锥形旋流器有一定的优越性。燃烧室加装锥形旋流器以后，其流体展现出强的旋涡；已发现切向动能约为总动能的三分之一。这种锥形旋流器也可以破坏旋涡结构，这种破坏起到了气动火焰稳定器作用，也稳定了燃烧流场。然而锥形旋流器结构也确实会带来更多的压力损失，这种压力损失对导弹性能的影响有待进一步加以评估。固体推进剂损失的这种形响也需要进行讨论。
In order to evaluate the performance of a cone-shaped cyclone installed in a dome combustion chamber, the flow field of a ramjet-type rocket compound engine with or without a conical cyclone was studied. The use of a cone swirler will improve the fluid profile and enhance the combustor fluid swirling strength to relieve the overheating section of the combustor and further increase the oil / gas mixing efficiency. The KIVA3 program was used to simulate and calculate the flow field in the combustion chamber. The simulation results show that this cone-shaped cyclone has some advantages. After the combustor is equipped with a conical cyclone, its fluid exhibits a strong vortex; tangential kinetic energy has been found to be about one-third of the total kinetic energy. This conical cyclone can also destroy the vortex structure, this damage played the role of pneumatic flame stabilizer, but also stabilizes the combustion flow field. However, the conical cyclone structure does bring about more pressure loss. The impact of this pressure loss on missile performance needs to be further evaluated. This form of solid propellant loss also needs to be discussed.