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为了研究吸气式高超声速飞行器尾喷流对飞行器尾部区域气动性能的影响,在中国空气动力研究与发展中心0.5m高超声速风洞中,在来流马赫数为5.0和6.0条件下,开展了不同落压比条件下的尾喷流干扰测压实验研究,同时采用高清纹影观测了喷流干扰区域的流场结构。实验结果表明:不同喷流落压比时,飞行器尾部区域表面压力分布差别明显,高落压比时喷流干扰作用的区域更大,压强数值更高。纹影也显示高落压比时交叉干扰激波更强、剪切层扩张更明显。喷流干扰区域已影响到了飞行器水平翼区域的压力分布,将会对飞行器操纵特性产生影响。
In order to study the influence of tail jet of aspirated hypersonic vehicle on the aerodynamic performance of aircraft aft region, in the 0.5m hypersonic wind tunnel at China Aerodynamics Research and Development Center, under Mach-flow conditions of 5.0 and 6.0, The experimental study on the disturbance of pressure at the end jet with different pressure ratio was carried out. At the same time, the flow field structure of the jet interference area was observed by using the high definition smear. The experimental results show that there are significant differences in surface pressure distributions at the rear of the aircraft when jetting pressure ratios are different, and the area with high jetting pressure jet interference is larger and the pressure value is higher. The striation also shows a higher crosstalk frequency when the pressure ratio is stronger and the shear layer is more pronounced. The jet interference area has affected the pressure distribution in the horizontal wing area of the aircraft and will have an impact on the handling characteristics of the aircraft.