| 飞机机翼摇滚低速风洞实验研究 |
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| 引用本文： | 孙海生,姜裕标.飞机机翼摇滚低速风洞实验研究[J].实验流体力学,2000,14(4):32-35. |
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| 作者姓名： | 孙海生 姜裕标 |
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| 作者单位： | 中国空气动力研究与发展中心，四川 绵阳 621000 |
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| 摘 要： | 介绍了机翼摇滚低速风洞试验技术，并对试验装置、试验方法、数据采集等进行了描述。重点讨论了一种歼击机模型在气动中心低速所4m×3m风洞进行的机翼摇滚风洞试验的典型结果。最后对形成机翼摇滚的机理进行了探讨与分析。
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| 关 键 词： | 大攻角 机翼摇滚 风洞试验 |
| 文章编号： | 1007-312499(2000)04-0032-05 |
| 修稿时间： | 1999年7月7日 |
Investigation on wing rock in low speed wind tunnel for a fighter configuration |
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| SUN Hai-sheng,JIANG Yu-biao.Investigation on wing rock in low speed wind tunnel for a fighter configuration[J].Experiments and Measur in Fluid Mechanics,2000,14(4):32-35. |
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| Authors: | SUN Hai-sheng JIANG Yu-biao |
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| Abstract: | The wing rock test technique in low speed wind tunnel is presented in this paper, including test apparatus and test methods as well as data acquisition. The typical test results about wing rock for a fighter configuration conducted in CARDC 4m × 3m low speed wind tunnel are also discussed briefly. Finally, the mechanism of wing rock is explored. |
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| Keywords: | high angle of attack wing rock wind tunnel test |
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