抽吸对高超声速进气道抗反压能力的影响

常军涛; 鲍文; 崔涛; 于达仁

抽吸对高超声速进气道抗反压能力的影响

哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

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出版历程
- 收稿日期: 2007-02-08
- 修回日期: 2007-04-26
- 刊出日期: 2008-03-28

Effect of suctions on maximum backpressure ratios of hypersonic inlets

School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 对不同抽吸开孔率下某典型高超声速进气道进行了二维数值模拟,简要分析了压比变化对隔离段内部流场的影响,在该分析的基础上讨论了附面层抽吸对进气道最大抗反压能力的影响,给出了最大抗反压能力随抽吸流量之间的变化规律,分析了采用附面层抽吸技术提高进气道抗反压能力的原因.分析结果表明:采用附面层抽吸技术能够提高进气道的抗反压能力,相当于增加了隔离段的长度.抽吸孔面积越大,相对抽吸流量越大,进气道的抗反压能力越大.
- 航空、航天推进系统 /
- 高超声速进气道 /
- 抽吸 /
- 数值模拟 /
- 不起动边界
Abstract: A 2-Dinternal flow field of hypersonic inlets was simulated numerically at different suction rates.The effects of the backpressure on the internal flow field of the isolator were analyzed.The influences of the boundary layer suction on the maximum backpressure were also discussed,showing the variation of the maximum backpressure with the suction rates.The reasons why the maximum backpressure of the hypersonic inlet is improved by the suction technology were analyzed.The results show that,the boundary layer suctions can improve the maximum backpressure of the inlet,which increases the length of the isolator to some extent.The more the suction of airflow is,the stronger backpressure of the inlet will be.
- aerospace propulsion system /
- hypersonic inlet /
- suction /
- numerical simulation /
- unstart boundary

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参考文献(13)

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