| 椭圆翼型高速气动特性实验研究 |
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| 引用本文： | 邓阳平,高正红,詹浩,黄江涛.椭圆翼型高速气动特性实验研究[J].航空计算技术,2009,39(6):18-20. |
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| 作者姓名： | 邓阳平 高正红 詹浩 黄江涛 |
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| 作者单位： | 西北工业大学,翼型叶栅空气动力学国防科技重点实验室,陕西,西安,710072 |
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| 基金项目： | 航空科学基金资助项目 |
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| 摘 要： | 针对旋转机翼飞机主机翼翼型设计的特殊要求，在中国空气动力研究与发展中心FL-21风洞对16％相对厚度椭圆翼型马赫数0．4下的高速气动特性进行了实验研究，实验采用表面测压和尾排型阻测量技术。实验结果与数值计算结果的对比分析表明，数值计算具有较好的精确度，椭圆翼型的升力线斜率较小，压心位置靠前，力矩系数随迎角线性增大，最小阻力系数迎角并不像传统对称翼型那样为零度。
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| 关 键 词： | 旋转机翼飞机 椭圆翼型 实验研究 气动特性 |
Investigation on Aerodynamics Performance of Elliptic Airfoil at High Speed |
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| DENG Yang-ping,GAO Zheng-hong,ZHAN Hao,HUANG Jiang-tao.Investigation on Aerodynamics Performance of Elliptic Airfoil at High Speed[J].Aeronautical Computer Technique,2009,39(6):18-20. |
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| Authors: | DENG Yang-ping GAO Zheng-hong ZHAN Hao HUANG Jiang-tao |
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| Institution: | DENG Yang- ping, GAO Zheng- hong, ZHAN Hao, HUANG Jiang- tao ( National Key Laboratory of Aerodynamic Design and Research, NWPU, Xi＇an 710072, China ) |
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| Abstract: | The high speed experimental investigation on a 16% thickness elliptic airfoil was performed in two-dimensional testing section of FL-21 wind tunnel at China Aerodynamics Research and Development Center.The techniques of measuring the surface pressure and drag measurement with trail total pressure row tube were used.The experimental results validated the numerical calculation method and also shown that,the lift-curve slope of this airfoil is reduced in comparison to that of a conventional airfoil,the center ... |
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| Keywords: | rotor wing aircraft elliptic airfoil experimental investigation aerodynamic performance |
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