IMECH-IR  > 高温气体动力学国家重点实验室
激波风洞进气道自起动实验方法
岳连捷; 刘红; 徐骁; 彭辉; 张新宇
Source Publication第九届全国实验流体力学学术会议论文集(上册)
2013
Pages29-35
Conference Name第九届全国实验流体力学学术会议
Conference Date2013-07-06
Conference Place中国浙江杭州
Abstract以拓宽激波风洞在高超声速飞行器地面实验为目的,发展了一种适用于激波风洞的进气道自起动实验方法,并在激波风洞和常规风洞中完成一系列的验证实验。结果表明两种风洞实验中,轴对称进气道自起动内收缩比极限完全相同且与Kantrowitz极限相近。对于二元进气道模型,常规风洞自起动极限约为1.8,相比于激波风洞得到的自起动极限为1.91偏小,分析发现进气道出口高压的下降速度是影响进气道自起动的因素。结合数值模拟手段,研究了破膜非定常效应对进气道自起动能力的促进作用的机理及影响程度。最终证实了该实验方法能够有效的在激波风洞中进行进气道自起动实验。
Keyword高超声速进气道 自起动 激波风洞 实验方法 非定常效应
DepartmentLHD高超声速推进技术
Language中文
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/48553
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
岳连捷,刘红,徐骁,等. 激波风洞进气道自起动实验方法[C],2013:29-35.
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