| 基于CFD方法的机翼阵风响应研究 |
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| 引用本文： | 许晓平,张艳敬. 基于CFD方法的机翼阵风响应研究[J]. 飞机设计, 2011, 31(2): 20-24 |
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| 作者姓名： | 许晓平 张艳敬 |
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| 作者单位： | 西北工业大学航空学院;中国航天科工集团公司第九研究院; |
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| 摘 要： | 通过引入＂网格速度＂方法模拟阵风条件,求解非定常欧拉方程实现了不同展弦比0012平直机翼阵风响应的数值模拟。首先采用该方法对NACA0006翼型迎角阶跃型阵风的气动力响应进行了计算,计算结果与文献结果、理论值吻合良好。进一步对展弦比分别为5、10的0012平直机翼在迎角阶跃型、One-Minus-Cosine型阵风作用下的气动力响应过程进行了模拟分析。研究结果表明,当展弦比增大时,阵风作用下机翼的升力系数响应会增加,机翼翼根部位气动响应幅值大于翼尖部位响应特性。
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| 关 键 词： | 数值模拟 阵风响应 非定常 迎角阶跃型阵风 One-Minus-Cosine型阵风 平直机翼 |
Study of the Wing Gust Response for Based-CFD Method |
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| XU Xiao-pin,ZHANG Yang-jing. Study of the Wing Gust Response for Based-CFD Method[J]. Aircraft Design, 2011, 31(2): 20-24 |
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| Authors: | XU Xiao-pin ZHANG Yang-jing |
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| Affiliation: | XU Xiao-pin1,ZHANG Yang-jing2(1.School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China)(2.The 9 th Research Institut of China Aerospace Science & Industry Corp.,Wuhan 430040,China) |
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| Abstract: | Based on unsteady Euler equations,dynamic response in vertical gust flow perturbation are investigated for the 0012 rectangular wing with different aspect ratio.The grid velocity method was introduced to simulate the gust influence.First,after applying this method to simulate typical NACA0006 airfoil gust response to a step change in the angle of attack,it is shown that the calculated lift responses of the airfoil agree well with calculated value in reference.Furthermore,gust responses for the One-Minus-Cos... |
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| Keywords: | numerical simulation gust response unsteady gust to a step change in the angle of attack One-Minus-Cosine gust rectangular wing |
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