基于偏最小二乘法的翼型稳健设计替代模型

An Airfoil robust design alternative model based on partial least squares

摘要:

翼型的稳健设计就是要实现翼型对外界噪声因素不敏感，使翼型实现性能高且稳定的目标。翼型设计经过了几十年的研究发展，目前常用的翼型稳健设计主要是采用风洞和数值模拟两种方式，但它们也分别有成本高和计算量大的不足。通过对建模方法进行研究，提出了一种基于偏最小二乘法（PLS)的翼型稳健设计方法，采用该方法对基准翼型RAE2822选取11个设计变量（10个外形设计变量和马赫数）进行稳健设计后将其与基准翼型的阻力系数进行对比。结果表明使用偏最小二乘法替代模型所获得的稳健翼型，其阻力系数的均值和方差较基准翼型分别减小了44%和82%，其气动性能更好且性能更加稳定。使用偏最小二乘法替代模型进行翼型稳健设计具有成本低，计算速度快的特点，且能满足基本的结果精度要求，具有实际的应用价值。

Abstract:

The robust design of the airfoil is to achieve the goal that the airfoil is insensitive to external noise factors, enabling the airfoil to achieve high performance and stability. After several decades of research and development of airfoil design, the commonly used airfoil robust design mainly adopts wind tunnel and numerical simulation, but they also have the disadvantages of high cost and large calculation amount. By studying the modeling method, an airfoil robust design method based on partial least squares (PLS) is proposed. This method is used to select 11 design variables (10 shape design variables and Mach number) for the reference airfoil RAE2822. After a robust design, compare it to the drag coefficient of the reference airfoil. The results show that the mean and variance of the drag coefficient of the robust airfoil obtained by partial least squares replacement model are reduced by 44% and 82%, respectively, compared with the reference airfoil, and the aerodynamic performance is better and the performance is more stable. The use of partial least squares instead of model for airfoil robust design has the characteristics of low cost and fast calculation speed, and can meet the basic accuracy requirements of the results, and has practical application value.