喷流落压比对高超飞行器尾喷管内外流干扰的实验

发布时间：2018-03-14 00:15

  本文选题：吸气式飞行器　切入点：高超声速　出处：《航空动力学报》2017年10期 　论文类型：期刊论文

【摘要】：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鐖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。
[Abstract]:In order to study the effect of the tail jet on the aerodynamic performance in the rear region of an aspirated hypersonic vehicle, a 0.5 m hypersonic wind tunnel with a Mach number of 5.0 and 6.0 was carried out in a 0.5 m hypersonic wind tunnel of the China Center for aerodynamic Research and Development. The experimental study of the tail jet interference pressure measurement under different drop pressure ratios is carried out, and the flow field structure of the jet interference region is observed by using high-definition schlieren. The experimental results show that the flow field structure is measured with different jet drop pressure ratios. The distribution of surface pressure in the rear region of the aircraft is obviously different, the area of jet interference is larger and the pressure value is higher when the falling pressure is higher than that at high drop pressure, and the schlieren also shows that the cross-interference shock wave is stronger when the falling pressure is higher than that at the time of falling pressure. The shear layer expansion is more obvious. The jet interference region has affected the pressure distribution in the horizontal wing region of the aircraft and will have an impact on the aircraft control characteristics.
【作者单位】： 中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室;
【分类号】：V211.7
，

本文编号：1608758