本文采用不同的方法验证了相对厚度对机翼气动特性的影响。首先进行机翼风洞试验；然后用数值仿真的方法进行计算，进一步验证了数值方法能够有效的用来评价机翼的气动特性；还将试验结果用经验公式校核，证实了其有效性。这些方法得到的结果一致证实产生升力的因素不是单纯的相对厚度，而是迎角、翼型相对弯度以及中弧线。在迎角为零时，由于零升力主要由机翼中弧线决定，相对厚度对升力几乎没有影响。在此研究基础上，可以改变外界环境条件（如含尘大气或湿空气环境），用数值仿真来评定不同环境中机翼的气动特性。

The purpose of this paper was to validate the effects of airfoil thickness ratio on the characteristics of a family of airfoils. Re-search was carried out in different ways. First, tests were conducted in the wind tunnel. And numerical simulation was performed on basis of tests. Results from calculation were consistent with tests, indicating that numerical method could help evaluate characteristics of airfoils. Then the results were confirmed by compared with empirical data. The study also showed that the determinant of lift was not the thickness ratio, but the angle of attack, the relative camber and the camber line. The thickness ratio appeared to have little effect on lift coefficient at zero angle of attack, since the angle of zero lift was largely determined by the airfoil camber. According to the research, numerical simulation can be used to determine the aerodynamic characteristics of airfoils in different environment such as in the dusty or humid air.