吸气式高超声速飞行器非均匀尾喷流试验

doi:10.7527/S1000-6893.2016.0246

流体力学与飞行力学

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吸气式高超声速飞行器非均匀尾喷流试验

贺旭照, 秦思, 卫锋, 乐嘉陵

中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室, 绵阳 621000

收稿日期:2016-03-08 修回日期:2016-08-29 出版日期:2017-03-15 发布日期:2017-04-11
通讯作者: 秦思,E-mail:qs6739639@163.com E-mail:qs6739639@163.com

Test of non-uniform nozzle plume for air-breathing hypersonic vehicle

HE Xuzhao, QIN Si, WEI Feng, LE Jialing

Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2016-03-08 Revised:2016-08-29 Online:2017-03-15 Published:2017-04-11

摘要/Abstract

摘要：

在中国空气动力研究与发展中心ø0.5 m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。

关键词: 吸气式飞行器, 高超声速, 非均匀喷流, 内外流干扰, 测压

Abstract:

The pressure test for the inner-outer flow interaction area are conducted at the 0.5 m hypersonic wind tunnel in China Aerodynamics Research and Development Center. The test are conducted at the conditions of uniform and non-uniform incoming flow. Using non-uniform inner nozzle, the pressure on the afterbody expansion surface and the horizontal wing surface of the aircraft can be measured by simulating the non-uniform incoming flow of the aircraft nozzle. High speed schlieren is used to observe the flow field structure of the interaction areas of the plume, and the rules of influence of non-uniform incoming flow on pressure distribution on the afterbody expansion surface and horizontal surface of the aircraft nozzle can be got under different conditions. The test results show that the non-uniform incoming flow of the nozzle has significant influence on wall surface pressure distribution and flow field structure of the aircraft. The non-uniform characteristic of the nozzle's incoming flow cannot be ignored in simulation of air breathing hypersonic vehicle plume. It can be seen from the test result that the pressure of the non-uniform plume's core area is obviously higher than that of the uniform plume; while outside the core area, the non-uniform plume has a slightly smaller action area than the uniform plume, and the interaction area and intensity of non-uniform plume and outflow is also smaller than those of uniform plume. The uniform plume has distinct expansion waves in the exit area of the nozzle, and the expansion angles of interaction shock wave and shear layer of the uniform plume are larger than those of the non-uniform plume.

Key words: air-breathing vehicle, hypersonic, non-uniform nozzle plume, inner-outer flow interaction, pressure test

中图分类号:

V211

贺旭照, 秦思, 卫锋, 乐嘉陵. 吸气式高超声速飞行器非均匀尾喷流试验[J]. 航空学报, 2017, 38(3): 120199-120199.

HE Xuzhao, QIN Si, WEI Feng, LE Jialing. Test of non-uniform nozzle plume for air-breathing hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(3): 120199-120199.

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E-mail：hkxb@buaa.edu.cn

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吸气式高超声速飞行器非均匀尾喷流试验

Test of non-uniform nozzle plume for air-breathing hypersonic vehicle

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