本文在中国空气动力研究与发展中心?0.5m高超声速风洞中，开展了非均匀喷流条件下的吸气式高超声速飞行器后体尾喷流/外流干扰测压实验研究。采用非均匀内喷管，模拟飞行器尾喷管非均匀入流，测量了飞行器后体膨胀面及水平翼表面压力，采用高清速纹影观测了喷流干扰区域的流场结构，获得了不同工况下非均匀入流对尾部及水平翼表面压力分布的影响规律。实验结果显示尾喷管非均匀入流对飞行器尾部壁面压力分布及流场结构有明显影响，喷管入流的非均匀特征在吸气式高超飞行器喷流模拟中不可忽视。非均匀喷流核心区压力分布明显高于均匀喷流时的结果；核心区域外，非均匀喷流的作用面积略小于均匀喷流，且非均匀喷流同外流交叉干扰区域的面积和强度要略小于均匀喷流；均匀喷流在喷管出口区域存在明显的膨胀波系，交叉干扰激波及剪切层的扩张角也大于非均匀入口条件时的结果。

The pressure test experiments for the inner-outer flow interaction area are conducted at CARDC’s 0.5m hypersonic wind tunnel. The experiments are conducted at the condition of uniform and non-uniform incoming flow.Using non-uniform inner nozzle, the pressure of aircraft’s afterbody expansion surface and horizontal wing surface can be measured by simulating aircraft nozzle’s non-uniform incoming flow. High speed schlieren is used to observe flow field structure of plume’s interaction areas, and the influence rules of non-uniform incoming flow on aircrafe nozzle’s afterbody expansion surface and horizontal surface pressure distribution can be got under different conditions. The experiment result shows that nozzle’s non-uniform incoming flow has significant influence on aircraft’s wall surface pressure distribution and flow field structure. The non-uniform character of nozzle’s incoming flow can not be ignored in air breathing hypersonic vehicle plume simulation. From experiment result, the pressure of non-uniform plume’s core area is obviously higher than that of uniform plume; while outside the core area, non-uniform plume has a slightly smaller action area than uniform plume, the interaction area and intensity of non-uniform plume and outflow is also smaller than uniform plume. Uniform plume has distinct expansion waves in nozzle’s exit area, the expansion angles of interaction shock wave and shear layer are larger than non-uniform plume.