| 流线追踪Busemann进气道马赫数3.85实验研究 |
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| 引用本文： | 孙波,张堃元,金志光.流线追踪Busemann进气道马赫数3.85实验研究[J].航空动力学报,2007,22(3):396-399. |
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| 作者姓名： | 孙波 张堃元 金志光 |
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| 作者单位： | 南京航空航天大学,能源与动力学院,江苏,南京,210016 |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | 为了研究流线追踪Busemann进气道在低马赫数来流条件下的起动性能、总体性能以及抗反压能力,对设计马赫数5.3、收缩比CR=5的6°截短后的流线追踪进气道进行了马赫数3.85风洞实验.结果表明:该进气道在马赫数3.85来流条件下能够自起动;进气道流量系数为0.83,出口总压恢复0.78,马赫数2.01,增压比11.92;进气道能够承受的最大反压为34倍的来流静压.
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| 关 键 词： | 航空、航天推进系统 超燃冲压发动机 Busemann进气道 流线追踪 风洞实验 |
| 文章编号： | 1000-8055(2007)03-0396-04 |
| 收稿时间： | 2006/3/13 0:00:00 |
| 修稿时间： | 2006年3月13日 |
Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet |
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| SUN Bo,ZHANG Kun-yuan and JIN Zhi-guang.Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet[J].Journal of Aerospace Power,2007,22(3):396-399. |
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| Authors: | SUN Bo ZHANG Kun-yuan and JIN Zhi-guang |
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| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | A wind-tunnel testing of a streamline traced hypersonic Busemann inlet,with a designed Mach 5.3 and shrinkage ratio CR=5,was conducted at Mach 3.85 to study its starting and overall performance as well as back-pressure capability below Mach 5.3 conditions.The results show that,the inlet can be started automatically at Mach 3.85;the flow coefficient of inlet is 0.83,the overall pressure recovery coefficient is 0.78,with a Mach number 2.01 and a compression ratio of 11.92;the inlet can withstand a maximum back-pressure of 34 times static pressure. |
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| Keywords: | aerospace propulsion system scramjet Busemann inlet streamline traced wind-tunnel testing |
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