Abstract: In order to investigate the effects of nonuniform flow at inlet throat on the flow characteristics of isolators，a direct-connect wind-tunnel facility was designed according to the Ma distribution of typical scramjet isolator inlet. The direct-connect wind-tunnel facilities was divergent，and some cylindrical bumps were placed on the lower wall of boundary layer developed section to accelerate development of boundary layer. Finally，cold-flow test and numerical simulation were conducted. The results show that this direct-connect wind-tunnel facility not only can simulate the real inflow (including the lip shock wave and asymmetric boundary layer) in a scramjet isolator，the difference of Mach number in main flow between simulation and target is within 0.02，but also can avoid the starting problem in the traditional direct-connect wind-tunnel facility. Results of cold-flow test and numerical simulation agree well with each other，which confirms that the design method of direct-connect wind-tunnel facility is fully verified.

Key words: Scramjet engine；Direct-connect wind-tunnel experiment of scramjet isolator；Boundary layer；Non-uniform；Shock wave

摘要： 为了模拟进气道喉道非均匀流场对超燃冲压发动机隔离段流动特性的影响，针对典型超燃冲压发动机隔离段入口流场的马赫数分布要求，设计了隔离段直连试验设备。该设备整个通道采用扩张构型，在附面层发展段的下壁面采用加圆形凸台的方法加速附面层发展，并针对该设备进行了数值模拟和冷流试验。结果表明，该直连试验设备不仅能准确模拟隔离段实际入口流场(即入射激波和非对称附面层)，模拟的主流区马赫数与目标值差值在0.02以内，还解决了传统的直连试验设备存在的启动问题。试验与数值模拟结果吻合较好，验证了该直连试验设备设计方法的可行性。

关键词: 超燃冲压发动机；隔离段直连试验；附面层；非均匀；激波