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研究了双燃式一体化通道（包含进气道、双燃式燃烧室和尾喷管）的冷态内流场特性． 首次在激波风洞中对内流场进行纹影照相，用ＴＶＤ格式求解三维全Ｎ－Ｓ方程对喷管和一体 化通道进行分区数值模拟，并考察了几何参数对内流场的影响．结果表明：对典型工况（ｈｐ＝ １２.９３ ｍｍ），纹影照片和计算得到的流场波系是一致的，沿下壁面静压分布和相关的实验值符 合较好．计算结果还表明：亚燃室的流动非常复杂，进气道、超燃室和尾喷管的流动相对简单． 进气道下壁面的回流区在下游演变为滑移面，并延伸至亚燃室入口．减小ｈｐ，亚燃室部分超声 速气流通过回流区降为亚声速．保持进气道来流参数不变，减小ｈｐ（隔板位置不变）、隔板上 移和顺时针旋转（ｈｐ不变）都会导致回流区上移、滑移面抬起、亚燃室出现溢流，引起亚、超 燃烧室进气相互干扰．
The characteristics of the internal flow field in the cold state of the dual-combustion integrated duct (including the intake port, the dual-combustion chamber and the tail nozzle) are studied. For the first time, the inner flow field was shaded in the shock tunnel, and the three-dimensional N-S equation was solved in TVD format to numerically simulate the nozzle and the integrated channel. The influence of geometric parameters on the internal flow field was also investigated. The results show that for the typical working condition (hp = 12.93 mm), the smeared photos are consistent with the calculated flow field. The distribution of static pressure along the lower wall meets the relevant experimental data well. The calculation results also show that the flow in the sub-combustion chamber is very complicated, and the flow of the inlet, the super-combustion chamber and the tail nozzle are relatively simple. The recirculation zone of the lower inlet wall evolves downstream into a slip surface and extends to the sub-combustion chamber inlet. Reduce hp, sub-combustion chamber part of the supersonic airflow through the backflow area down to subsonic sound. Maintain the inlet flow parameters unchanged, reduce hp (baffle position unchanged), baffle up and clockwise rotation (hp constant) will lead to the reflux area uplift, slip surface lift, the occurrence of the combustion chamber Overflow, causing Asia, super combustion chamber intake mutual interference.