| 摘要: |
| 为深入探究唇罩侧板后掠对二元高超声速进气道起动性能的影响规律，采用风洞试验与三维数值模拟分析相结合的方法，对比分析了侧板不同后掠状态下的不起动流场特征，细致地研究了后掠角度影响进气道起动的流动机理。研究结果表明:唇罩后掠能够提高进气道的起动能力，来流Ma=5.0和Ma=4.0时，进气道的最小起动后掠角分别为75°和82.5°。Ma=5.0来流条件下，不起动的分离包前缘形态在一定范围内基本不受后掠角影响。唇罩后掠角度增大时主要通过侧板的展向溢流，改变分离包的位置及形态，进而通过降低分离包内的逆压梯度来影响进气道的起动性能。 |
| 关键词: 高超声速进气道 后掠角 不起动 溢流 分离包 |
| DOI： |
| 分类号: |
| 基金项目:国家自然科学基金(51206077)；江苏省研究生培养创新工程(SJZZ_0044)；中国航天科技集团公司航天科技创新基金。 |
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| Effects of Swept Lip on Starting Characteristics of 2-D Hypersonic Inlet |
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HUA Zheng-xu1,2,YUAN Hua-cheng1,WANG Jin-gang2,CHEN Wen-fang1
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( 1. Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of
Aerospace Power System，Nanjing 210016，China;2. Shenyang Aircraft Design & Research Institute，Shenyang 110035，China)
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| Abstract: |
| To better investigate the effects of swept lip on starting performance of 2-D hypersonic inlet，several configurations with different swept angles were analyzed by wind tunnel test and 3-D numerical simulation. The unstart flow structures of different configurations are compared，and the mechanism that swept angle causes the flow differences is analyzed minutely. The results show that，swept lip can improve the capacity for starting. At Ma=5.0 and Ma=4.0 flow conditions，the minimum start angles are 75° and 82.5°，respectively. Within some swept angles，the leading edge structure of separate bubble is not affected at Ma=5.0 flow conditions. The spanwise spillage caused by swept lip influences the startability mainly，which changes the structure and position of separate bubble so as to decrease the pressure distribution along the separation，thus the startability is affected. |
| Key words: Hypersonic inlet Swept angle Unstart Spillage Separate bubble |
