| 弹用模块化Busemann进气道数值研究 |
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| 引用本文： | 孙波,张堃元,武晓松.弹用模块化Busemann进气道数值研究[J].航空动力学报,2009,24(3):573-580. |
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| 作者姓名： | 孙波 张堃元 武晓松 |
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| 作者单位： | 1. 南京理工大学机械工程学院,南京,210094
2. 南京航空航天大学能源与动力学院,南京,210016 |
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| 基金项目： | 江苏省博士后科研资助计划 |
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| 摘 要： | 对经过附面层修正后的模块化扇形流管流线追踪进气道进行了数值模拟,以截短角度和收缩比对这种进气道总体件能的影响进行了研究,主要得到以下结论:附面层修正能够大幅提高进气道的流量系数和流场均匀性;经附面层修正后的扇形流管流线追踪进气道有较好的性能,流量系数能达到0.9以上,在流管内没有大的分离区;进气道流量系数和压缩量随着截短角度的增大而增大,而收缩比越大,流量系数越小,压缩量越大;发动机推力与进气道流量系数有关.发动机推力和比冲基本上均随截短角度的增大而增大,而收缩比对它们的影响并不明显.
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| 关 键 词： | 超燃冲压发动机 Busernann进气道 流线追踪 数值模拟 |
| 收稿时间： | 2008/3/10 0:00:00 |
| 修稿时间： | 2008/11/10 0:00:00 |
CFD analysis of modular hypersonic Busemann inlets |
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| SUN Bo,ZHANG Kun-yuan and WU Xiao-song.CFD analysis of modular hypersonic Busemann inlets[J].Journal of Aerospace Power,2009,24(3):573-580. |
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| Authors: | SUN Bo ZHANG Kun-yuan and WU Xiao-song |
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| Institution: | 1.School of Mechanical Engineering;Nanjing University of Science and Technology;Nanjing 210094;China;2.College of Energy and Power Engineering;Nanjing University of Aeronautics and Astronautics;Nanjing 210016;China |
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| Abstract: | Modular streamtraced Busemann inlets were studied in detail for Mach 7.8 flight at 20 km altitude conditions.Numerical simulations were performed to study the effect of truncation angle and contraction ratio on the performance parameters of inlets,which were created by correcting the inviscid streamlines for turbulent boundary layer displacement obtained from finite difference calculations.To assess these inlets and calculate engine performance,they were coupled to an ideal combustor and nozzle.Mass-weighte... |
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| Keywords: | scramjet Busemann inlet streamline traced numerical simulation |
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