| 摘要: |
| 为了改善内转式进气道的性能，采用数值仿真的方法研究了内转式进气道的流动特征及流场控制技术。研究表明:在近壁面唇罩激波诱发了二次流，进而发展形成流向涡，造成低能流堆积，流场分布不均，消弱了进气道的抗反压能力。采用型面流场控制技术，重构进气道肩部压力与边界层分布，能够有效抑制流向涡的强度，减小流动损失，改善隔离段出口流场均匀度，提高其抗反压能力。与原方案相比，在设计状态流场控制方案隔离段出口总压恢复系数提高20%；最大抗反压能力提高28.4%；总阻力增大9.0%，进气道自起动马赫数由原方案4.2下降到该方案3.8。 |
| 关键词: 流向涡 流场特性 流场控制 内转式进气道 数值仿真 |
| DOI： |
| 分类号: |
| 基金项目:高超声速冲压发动机技术重点实验室开放基金(STSKFKT2014002)。 |
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| Study of Flow Control of Inward Turning Inlet |
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WANG Wei-xing1,2,GU Qiang2,GUO Rong-wei2
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( 1. Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute of
CARDC，Mianyang 621000，China;2. Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of
Aerospace Power System，Nanjing 210016，China)
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| Abstract: |
| In order to improve the aerodynamic performances of inward turning inlet，the flow characteristics and flow control technology of an inward turning inlet were numerically studied. The results show that the secondary flow near the wall，which will evolve into streamwise vortex，is induced by the cowl shock. The streamwise vortex promotes the boundary layer accumulation near the compression surface，and this leads to the uneven distribution of flow in isolator which weaken the capability of back pressure resistance. The distribution of pressure and boundary layer near the wall of shoulder are rearranged when the flow control is adopted，and this weakens the streamwise vortex and decreases the flow loss. Meanwhile，the distribution of flow in isolator becomes more uniform and the capability of back pressure resistance becomes stronger. Compared with original inlet，the total pressure recovery and capability of back pressure resistance of the inlet with flow control increase by 20% and 28.4%，respectively，but the drag increases by 9.0%，too. The self-starting Mach number decreases from 4.2 to 3.8. |
| Key words: Streamwise vortex Flow characteristics Flow control Inward turning inlet Numerical simulation |
