基于几何特征参数控制的翼型设计方法研究

Research on Airfoil Design Method Based on Geometric Characteristic Parameter Control

给出了基于双椭圆弧的中弧线方程式,并推导了由茹可夫斯基翼型公式拓展得到的厚度分布方程式,通过将指定的厚度分布均匀布置在中弧线上得到了一种新的翼型设计方法.该方法通过8个参数控制翼型的型线,其中4个参数具有明确的几何意义,其余4个参数可局部调整翼型的型线.利用Modefrontier优化平台将翼型设计程序与气动性能预测程序集成在一起,实现了翼型的优化设计,并以E387翼型为参考设计了一款翼型.结果显示,新翼型的气动性能相对于参考翼型有了显著的提升。研究表明,本文提出的翼型设计方法能够帮助设计者主动的对翼型的几何特征参数进行精准控制,并更好的理解设计过程,弥补了现有的翼型设计方法在主动进行几何特征参数控制上的不足。

In this research, the equation of the mean camber line based on double elliptic arcs is given, and the thickness distribution equation expanded by the formula of the Joukowski airfoil is derived. A new airfoil design method is obtained by uniformly distributing the specified thickness distribution on the mean camber line. This design method controls the airfoil profile by 8 parameters,4 of which have clear geometric meanings, and the rest can adjust the airfoil profile locally. By using the Modefrontier optimization platform, the airfoil design program is integrated with the aerodynamic performance prediction program. And then the optimization design of the airfoil is realized. A new airfoil is designed with the E387 airfoil as the reference. The results show that the aerodynamic performance of the new airfoil is significantly improved compared with the reference airfoil. This research shows that the airfoil design method proposed in this paper is reliable. It can help the designer to make the control of geometric characteristic parameters accurately, and better understand the design process, which makes up for the shortcomings of other existing airfoil design methods in the active control of geometric characteristic parameters.