| 某型飞机高亚声速大迎角横向静稳定性改善研究 |
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| 引用本文： | 陈斌.某型飞机高亚声速大迎角横向静稳定性改善研究[J].实验流体力学,2005,19(1):109-112. |
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| 作者姓名： | 陈斌 |
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| 作者单位： | 成都飞机工业(集团)有限责任公司技术中心,成都,610092 |
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| 摘 要： | 根据某型飞机存在的高亚声速大迎角横向静不稳定性问题，分析了出现该问题的原因，提出了解决问题的方法与措施，最后通过风洞试验验证，以较小的代价成功地解决了飞机的高亚声速大迎角横向静不稳定性问题，保证了飞机在正常使用范围内的飞行安全。
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| 关 键 词： | 高亚声速流 大迎角 风洞实验 静稳定性 |
| 文章编号： | 1672-9897(2005)01-0109-04 |
| 修稿时间： | 2003年11月8日 |
Investigation of improving the lateral static stability for the aircraft applied to high-subsonic flow and high angle of attack |
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| CHEN Bin.Investigation of improving the lateral static stability for the aircraft applied to high-subsonic flow and high angle of attack[J].Experiments and Measur in Fluid Mechanics,2005,19(1):109-112. |
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| Authors: | CHEN Bin |
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| Abstract: | Base on the problem of lateral static stability existing on some aircraft at high attack of angle in the high-subsonic flow, the resource of resulting the problem has been analyzed, the methods and direction for solving this problem has been developed in present paper and verified by wind tunnel test. It is successful and lower cost that appling the method to resolve the lateral static instability of aircraft at high angle of attack in high-subsonic flow; it is ensured the aircraft's flight safety in normal used range. |
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| Keywords: | high-subsonic flow high angle of attack stability wind tunnel test |
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