| 引用本文: | 赵玉新,易仕和,何霖,等.超声速湍流混合层中小激波结构的实验研究.[J].国防科技大学学报,2007,29(1):12-15.[点击复制] |
| ZHAO Yuxin,YI Shihe,HE Lin,et al.The Experimental Research of Shocklet in Supersonic Turbulent Mix Layer[J].Journal of National University of Defense Technology,2007,29(1):12-15[点击复制] |
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| 超声速湍流混合层中小激波结构的实验研究 |
| 赵玉新, 易仕和, 何霖, 程忠宇, 田立丰 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 在对流马赫数为1.24的超声速湍流混合层风洞中，以NPLS实验技术为基础观察到了小激波结构。分析了小激波结构产生时的混合层流场参数，给出了从实验图像中确定对流马赫数的方法，避免了理论分析不必要的假设。探讨了小激波结构产生、发展的一般规律。 |
| 关键词: 超声速湍流混合层 小激波 对流马赫数 |
| DOI： |
| 投稿日期：2006-06-29 |
| 基金项目:国家自然科学基金资助项目(10672178) |
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| The Experimental Research of Shocklet in Supersonic Turbulent Mix Layer |
| ZHAO Yuxin, YI Shihe, HE Lin, CHENG Zhongyu, TIAN Lifeng |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24. The flow field parameters of mix layer were analyzed with the appearance of shocklet. The method of calculating convective Mach number from experiment image was presented with the consideration that it can avoid unnecessary hypothesis of theory. Finally, the generation and development of shocklet structure were discussed. |
| Keywords: supersonic turbulent mix layer shocklet convective mach number |
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