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。
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 liftcurve slope of this airfoil is reduced in comparison to that of a conventional airfoil, the center of lift is in the vicinity of 15% of the chord. The pitching moment of this airfoil increases linearly with the angle of attack and the minimum drag angle of attack is not zero, which is different from conventional symmetrical airfoil.
出处
《航空计算技术》
2009年第6期18-20,共3页
Aeronautical Computing Technique
基金
航空科学基金资助项目(2006ZA53009)
关键词
旋转机翼飞机
椭圆翼型
实验研究
气动特性
rotor wing aircraft
elliptic airfoil
experimental investigation
aerodynamic performance
