| 吸气式高超声速飞行器前体/进气道一体化设计与试验 |
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| 引用本文： | 焦子涵,邓帆,范宇,刘辉,尘军.吸气式高超声速飞行器前体/进气道一体化设计与试验[J].航空动力学报,2017,32(1):168-176. |
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| 作者姓名： | 焦子涵 邓帆 范宇 刘辉 尘军 |
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| 作者单位： | 1.中国航天科技集团公司 中国运载火箭技术研究院 空间物理重点实验室,北京 100076； |
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| 摘 要： | 针对吸气式高超声速飞行器前体/进气道一体化设计的问题，以总体指标为约束，采用数值设计手段开展了前体/进气道一体化设计，并对高超声速飞行器进行测压/测力试验，考核了前体/进气道的一些主要性能，结果表明:①设计状态下，数值计算结果表明前体/进气道性能符合总体指标要求，设计手段有效；②数值手段模拟结果和风洞试验结果吻合良好，流量系数最大误差为4％，总压恢复系数最大误差为42％，数值算法有效；③前体/进气道的附加阻力随来流马赫数的增大而减小，0°攻角下，在来流马赫数为4时，附加阻力占总阻力的172％，在总体设计时应予以考虑；④在进行吸气式高超声速飞行器通流测压/测力试验设计时，应充分考虑进气道不起动的试验预案，防止由于进气道不起动导致整个试验的失败.
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| 关 键 词： | 吸气式高超声速飞行器 前体/进气道 超燃冲压发动机 一体化设计 风洞试验 |
| 收稿时间： | 2016/1/28 0:00:00 |
Integrated design and test of forebody/inlet for air breathing hypersonic vehicle. |
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| JIAO Zi-han,DENG Fan,FAN Yu,LIU Hui,CHEN Jun.Integrated design and test of forebody/inlet for air breathing hypersonic vehicle.[J].Journal of Aerospace Power,2017,32(1):168-176. |
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| Authors: | JIAO Zi-han DENG Fan FAN Yu LIU Hui CHEN Jun |
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| Abstract: | With constraint of all performance indexes, the integrated design of forebody/inlet and the wind tunnel test of hypersonic vehicle was developed, while the major performance of forebody/inlet was assessed. Results showed that:(1)the performances of forebody/inlet satisfied all the performance indexes at the design condition, and the wind tunnel test validated the numerical design method; (2)the numerical results agreed well with the wind tunnel test results, the max error of mass flow ratio was 4% and the max error of total pressure recovery coefficient was 42%, so the numerical method was efficient;(3)the additional drag of forebody/inlet increased with the increasing of inflow Mach number, the additional drag was up to 172% of the total drag at the angle of attack 0° when the Mach number was 4, which should be considered in the design;(4)the pre arranged planning should be made to avoid failure of the wind tunnel test because the inlet may not be able to start, which should be considered during design of the wind tunnel test scheme. |
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| Keywords: | air breathing hypersonic vehicle forebody/inlet scramjet integrated design wind tunnel test |
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