| 飞机大攻角最大侧向力和偏航力矩预测的风洞试验方法研究 |
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| 引用本文： | 胡汉东,杨其德,祝明红,邓学蓥.飞机大攻角最大侧向力和偏航力矩预测的风洞试验方法研究[J].航空工程进展,2011,2(1):19-26. |
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| 作者姓名： | 胡汉东 杨其德 祝明红 邓学蓥 |
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| 作者单位： | 1. 中国空气动力研究与发展中心,绵阳,621000
2. 北京航空航天大学,北京,100191 |
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| 摘 要： | 具有尖头细长构型的飞行器在实际大攻角飞行和风洞试验中,侧向力系数和偏航力矩系数存在非确定性,给数据分析和使用带来很大困难.为了改变这种情况,本文发展了一种附加头部微扰动的试验技术,并在YF16模型大攻角试验中开展了应用.试验中通过压力分布确定头部分离流动特征,再采用人工转捩和头部微扰动技术在大攻角风洞试验中确定侧向力和...
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| 关 键 词： | 大攻角 分离流 转捩 风洞试验 头部扰动 |
Aircraft Side-force and Yawing Moment Measurement at High Angle of Attack in the Wind Tunnel |
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| Hu Handong,Yang Qide,Zhu Minghong,Deng Xueying.Aircraft Side-force and Yawing Moment Measurement at High Angle of Attack in the Wind Tunnel[J].Advances in Aeronautical Science and Engineering,2011,2(1):19-26. |
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| Authors: | Hu Handong Yang Qide Zhu Minghong Deng Xueying |
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| Institution: | Hu Handong1,Yang Qide1,Zhu Minghong1,Deng Xueying2(1.Chinese Aerodynamics Research and Development Center,Mianyang 621000,China)(2.Beijing University of Aeronautic and Astronautic,Beijing 100191,China) |
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| Abstract: | In the real flight and wind tunnel testing of aircraft configuration with pointed nose slender,the coefficients of side force and yawing moment which are generated by high angle of attack are inconsistency,leading to difficulty for analyzing and using.In order to remove this difficulty,an experimental technique in which a micro-perturbation is attached on nose tip of model is suggested in wind tunnel testing for measuring side force and yawing moment.Based on this technique,an experimental study was conduct... |
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| Keywords: | high angle of attack separated flow transition wind tunnel test nose perturbations |
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