| 基于结构网格的操纵面嗡鸣数值研究 |
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| 引用本文： | 周月荣,陈志敏,徐敏.基于结构网格的操纵面嗡鸣数值研究[J].航空计算技术,2012(3):77-80. |
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| 作者姓名： | 周月荣 陈志敏 徐敏 |
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| 作者单位： | [1]西北工业大学航空学院,陕西西安710072 [2]西北工业大学航天学院,陕西西安710072 |
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| 摘 要： | 利用无限插值法生成结构化动网格,耦合求解欧拉方程与结构方程,分别模拟了二维带操纵面翼型以及三维NASP机翼周围跨音速流动。对二维带操纵面翼型嗡鸣发生时的流场进行了分析,发现操纵面上的激波后会产生巨大的分离区,且分离区的变化过程滞后于激波变化过程,认为缝隙的存在对嗡鸣发生有促进作用;对三维NASP机翼的研究发现操纵面质量比的增加可以延缓嗡鸣发展。
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| 关 键 词： | 结构网格 操纵面 嗡鸣 无限插值 NASP机翼 |
Numerical Study of Control Surface Buzz Based on Structured Grid |
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| ZHOU Yue- rong,CHEN Zhi- min,XU Min.Numerical Study of Control Surface Buzz Based on Structured Grid[J].Aeronautical Computer Technique,2012(3):77-80. |
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| Authors: | ZHOU Yue- rong CHEN Zhi- min XU Min |
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| Institution: | 1. School of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China ; 2. School of Astronautics, Northwestern Polytechnical University, Xi＇an 710072, China ) |
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| Abstract: | The flow field around two- dimensions airfoil with control surface and three- dimensions NASP wing was simulated. The deforming structured grid was generated by TFI method. Euler equations were solved coupled with structural equations. By studying the flow field of two- dimensions airfoil when control -surface occurring, it was found that there was a large separated region behind the shock wave on the control- surface and the evolvement of the region was lag behind that of the shock wave. It was inferred the gap could accelerate the control- surface buzz. By studying the NASP wing, it was found the evolvement of control- surface buzz could be deferred by enlarging the specific mass. |
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| Keywords: | structured grid control surface buzz TFI NASP wing |
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