定几何二元倒置“X”型混压式超声速进气道数值仿真与实验验证

万大为; 郭荣伟

定几何二元倒置“X”型混压式超声速进气道数值仿真与实验验证

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2007-02-06
- 修回日期: 2007-04-12
- 刊出日期: 2007-08-28

Numerical simulation and experimental verification of a fixed-geometry 2D mixed-compression supersonic inlet with sweepforward high-light and "X"-type missile configuration

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对一种定几何二元倒置"X"型混压式超声速进气道开展了数值仿真研究, 结果表明:随着来流马赫数的增加, 进气道总压恢复系数下降, 而流量系数却先上升, 在设计点达到最大值后下降.当攻角变化时, 小攻角α<6°时迎背风两侧进气道总压恢复系数虽有下降但变化幅度不大, 对于流量系数, 在小攻角α<6°下背风侧进气道高于迎风侧进气道, 但两侧总的流量随攻角变化不大;在大攻角状态下(α=6°～9°), 背风侧进气道总压恢复系数和流量系数均下降剧烈, 而迎风侧进气道总压恢复系数虽然下降但流量系数却有上升.同时, 与实验结果对比表明, 两者规律趋势一致.
- 航空、航天推进系统 /
- 二元混压式 /
- “X”型布局 /
- 数值仿真 /
- 实验验证 /
- 超声速进气道
Abstract: A numerical simulation was conducted for a fixed-geometry two-dimensional mixed-compression supersonic inlet with sweepforward high-light and "X"-type missile configuration.The results indicate:(1) The total pressure recovery declines with the rise of the free stream Mach number, while the mass flow ratio rises firstly and then declines when its maximum value is obtained at the design point.(2)When the angle of attack increases less than 6°, the total pressure recovery of both side inlets decreases in a narrow range;the mass flow ratio of the lee side inlet is higher than that of the windward inlet, the total flow mass of both sides is almost constant.(3) When the angle of attack increases from 6° to 9°, both the total pressure recovery and the mass flow ratio fall rapidly at the lee side inlet, whereas the total pressure recovery declines and mass flow ratio rises at the windward side inlet.(4)The numerical simulation results show a consistent trend with the experimental results.
- aerospace propulsion system /
- two dimensional mixed-compression /
- "X"-type configuration /
- numerical simulation /
- experimental validation /
- supersonic inlet

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参考文献(10)

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