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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/外流干扰测压试验研究。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。试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声速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。
In China’s aerodynamic research and development center 0.5m hypersonic wind tunnel, under non-uniform jet flow under the aspirated hypersonic vehicle rear body jet / outflow interference pressure test research. The non-uniform inner nozzle is used to simulate the non-uniform inflow of the tail nozzle of the aircraft. The pressure on the rear body expansion plane and the horizontal wing of the aircraft is measured. The flow field structure in the interference area of the jet flow is observed by the high definition shadowing. Influence of Nonuniform Inflow on Pressure Distribution on Tail and Horizontal Wing Surface. The test results show that the non-uniform inflow of the tail pipe has a significant effect on the pressure distribution and the flow field structure of the rear wall of the aircraft. The nonuniform characteristics of the nozzle inflow can not be ignored in the jet simulation of the aspirated hypersonic vehicle. The pressure distribution in the core area of the non-uniform jet is obviously higher than that of the uniform jet. Outside the core area, the area of the non-uniform jet is slightly smaller than that of the uniform jet and the area and intensity of the non-uniform jet intersecting the outflow The uniform jet flow has obvious expansion wave in the exit of nozzle, and the spread angle of cross interference shock wave and shear layer is larger than that of non-uniform inlet condition.