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| 超声速铲形进气道数值计算及试验研究 |
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李宏东1,朱 璞1,王永卫1,朱守梅1,2,王 健1,2,刘汉斌3
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(1.北京动力机械研究所，北京 100074;2.北京动力机械研究所 高超声速冲压发动机技术重点实验室，北京 100074;3.二炮驻31所军代表室，北京 100074)
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| 摘要: |
| 为了研究超声速铲形进气道的气动特性，针对固定几何超声速铲形进气道，利用数值仿真计算及风洞试验，获得了来流马赫数Ma∞=2.5，3.0，3.5，4.0，攻角α=-6°，-3°，0°，3°，6°，8°以及侧滑角β=3°，6°的临界性能。研究结果表明该超声速进气道具有良好的攻角特性，随着攻角的增加，总压恢复系数和流量系数增加；6°侧滑角以内进气道总压恢复系数和流量系数变化量很小。该进气道与飞行器前体一体化设计，能够很好地适应大空域、宽马赫数范围工作需求。 |
| 关键词: 飞行器/进气道一体化 冲压发动机 进气道 数值计算 风洞试验 |
| DOI： |
| 分类号:V231.3 |
| 基金项目: |
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| Numerical Computation and Test for Supersonic Shovel Inlet |
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LI Hong-Dong1,ZHU Pu1,WANG Yong-wei1,ZHU Shou-mei1,2,WANG Jian1,2,Liu Han Wu3
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( 1.Beijing Power Machinery Institute，Beijing 100074，China;2.Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China;3.The second Artillery Representative Office in the 31st Research Institute，Beijing 100074，China)
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| Abstract: |
| Numerical computation and wind tunnel test for supersonic shovel inlet with fixed geometry is carried out with different incoming Mach numbers(2.5，3.0，3.5，4.0)，different angles of attack(-6°，-3°，0°，3°，6°，8°)and different angles of the sideslip(3°，6°). The results indicate that this supersonic inlet has good attack angle characteristic. Inlet mass-flow coefficient and inlet total pressure recovery coefficient increase with increasing angle of attack. Inlet mass-flow coefficient and inlet total pressure recovery coefficient vary very small within 6°angle of the sideslip. This inlet is integrated with the vehicle，and it can be well suited with large airspace and wide Mach number. |
| Key words: Vehicle-inlet integration Ramjet engine Inlet Numerical computation Wind tunnel test |
