| 喷流落压比对高超飞行器尾喷管内外流干扰的实验 |
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| 引用本文： | 秦思,贺旭照,曾学军,乐嘉陵.喷流落压比对高超飞行器尾喷管内外流干扰的实验[J].航空动力学报,2017,32(10):2491-2497. |
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| 作者姓名： | 秦思 贺旭照 曾学军 乐嘉陵 |
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| 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，四川 绵阳 621000 |
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| 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05m高超声速风洞中，在来流马赫数为50和60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。
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| 关 键 词： | 吸气式飞行器 高超声速 落压比 尾喷流 测压实验 |
| 收稿时间： | 2016/3/4 0:00:00 |
Experiment of influence of the nozzle pressure ratio on the interaction between the external flow and nozzle flow of hypersonic aerocraft |
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| QIN Si,HE Xuzhao,ZENG Xuejun,LE Jialing.Experiment of influence of the nozzle pressure ratio on the interaction between the external flow and nozzle flow of hypersonic aerocraft[J].Journal of Aerospace Power,2017,32(10):2491-2497. |
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| Authors: | QIN Si HE Xuzhao ZENG Xuejun LE Jialing |
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| Abstract: | To find out the effect of nozzle plume on aerocraft aerodynamic performance,a pressure measurement experimental study on different nozzle pressure ratios (NPR) of nozzle plume was carried out at a freestream Mach number of 5.0 and 6.0 in the 0.5 m hypersonic wind tunnel of China Aerodynamics Research and Development Center (CARDC).The structure of the nozzle plume interaction area was obtained by using schlieren photography.The result showed obvious different pressure distribution of aerocraft afterbody area at a high NPR.When the NPR was high,the nozzle plume interaction area became bigger with a higher pressure.The schlieren pictures also showed that cross interaction shocks became stronger and the extending of the shear layer tended to be more obvious.Interaction area has affected the pressure distribution of the wings,which would affect the control ability of the aerocraft. |
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| Keywords: | air breathing aerocraft hypersonic nozzle pressure ratio(NPR) nozzle plume pressure measurement experiment |
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