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本研究旨在对涡轮喷管出口流场做详细了解。利用五孔微型探针测量了单级涡轮喷管出口下游两个轴向位置的流场。通过测定区域横向压力分布准确地分析流场，包括喷管尾流、二次流区域、马蹄涡及损失。准确解出了速度的三个分量、滞上压力、静压、俯仰角及侧滑角。观察到叶尖附近和轮毂处存在明显的涡旋中心，表现为马蹄涡和通道涡合并形成一个单损失核心区。在靠近叶尖和轮毂约为叶片高度１／３的通道区域内，二次流占优势。仅通道中间１／３叶片高度区域内流动特性与设计相符合。将该喷管尾流的衰减与其它叶片尾流的衰减作了比较：该喷管尾流的衰减比压气机叶栅尾流、涡轮环形叶栅尾流或动静叶间距较大的涡轮喷管尾流的衰减要快得多。这种较快的衰减是由于受到与静叶间隔很小的下游动叶（动静叶间距为喷管轴向弦长的２０％）的影响。
The purpose of this study is to understand the turbojet exit flow field in detail. The flow field at two axial locations downstream of the single stage turbojet nozzle was measured using a five-hole microprobe. The flow field, including the nozzle wake, secondary flow area, horseshoe vortex and loss, is accurately analyzed by measuring the lateral pressure distribution in the area. Accurately solved the three components of speed, hysteresis pressure, static pressure, pitch angle and side slip angle. The obvious vortex center near the tip and the hub was observed, showing the vortex of the horseshoe vortex and the vortex merged to form a single core loss region. Secondary flow predominates in the region of the passage near the tip and hub about 1/3 of the blade height. Only flow in the middle 1/3 of the blade height area corresponds to the design. The attenuation of the nozzle wake is compared with the attenuation of the other blade wake: the attenuation of the nozzle wake is smaller than that of the compressor cascade wake, the turbine cascade or the turbine nozzle Wake decay is much faster. This faster attenuation is due to the influence of the downstream rotor blade with a very small distance from the stator blade (the distance between the rotor and stator being 20% of the axial chord of the nozzle).