| 攻角动态变化的侧压式进气道风洞实验 |
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| 引用本文： | 郭斌,张堃元. 攻角动态变化的侧压式进气道风洞实验[J]. 航空动力学报, 2009, 24(7): 1601-1605 |
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| 作者姓名： | 郭斌 张堃元 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016;南京航空航天大学能源与动力学院,南京,210016 |
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| 摘 要： | 在Ma=3.85的风洞中,对一个设计Ma=6起动Ma=2.5的侧压式进气道完成了攻角从0°→8°→0°的连续吹风实验.实验结果表明:0°攻角时进气道顺利起动,当攻角增大到5.7°时,进气道出现不起动;之后在8°到0°的变化过程中,在5.4°时又恢复了起动.另外,随着攻角的增加,流量系数在起动状态下缓慢减小,在不起动状态下急剧减小.实验中还进行了攻角0°→4°→0°的动态连续吹风实验,进气道全程都处于起动状态.
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| 关 键 词： | 侧压式进气道 攻角可调 风洞实验 |
| 收稿时间： | 2008-07-02 |
| 修稿时间： | 2008-10-25 |
Wind tunnel experiment of sidewall compression inlet with adjustable attack angle |
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| GUO Bin and ZHANG Kun-yuan. Wind tunnel experiment of sidewall compression inlet with adjustable attack angle[J]. Journal of Aerospace Power, 2009, 24(7): 1601-1605 |
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| Authors: | GUO Bin and ZHANG Kun-yuan |
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| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | This paper conducted a wind tunnel experiment at Ma=3.85,during which a continual blowing process was finished at the sidewall compression inlet with designed Ma=6 and starting Ma=2.5,when attack angle changed from 0° to 8°,and again to 0°.Experimental results show that,in the case of Ma=3.85,attack angle=0°,the inlet starts smoothly,and the pressure distribution is consistent with numerical simulation to a large degree.In the dynamic process of attack angle changing from 0° to 8°,when it increases to 5.7°,the inlet fails to start.In the dynamic process of attack angle changing from 8° to 0°,when it decreases to 5.4°,the inlet succeeds in startup.What's more,with the increase of attack angle,the flow coefficient decreases when the inlet starts,and it decreases sharply when the inlet doesn't start.When the attack angle changes from 0° to 4°,and again to 0°,the inlet starts in the entire process. |
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| Keywords: | sidewall compression inlet adjustable attack angle wind tunnel experiment |
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