基于响应面的翼型稳健设计研究

Robust airfoil optimization based on response surface method

翼型的稳健设计就是要考虑环境中不确定因素的影响，提高翼型的性能，同时保证翼型性能对环境因素的变化不敏感的设计方法。本文应用响应面模型，通过减小翼型在不确定因素变化范围内阻力系数的均值和方差，构建了一个有效的翼型稳健设计的方法。应用本文的方法，选择马赫数作为不确定因素，假设马赫数在0．7—0．8间均匀分布，在满足升力约束条件下最小化阻力系数，结果证明本文的方法进行翼型的稳健设计是可行，高效的。

Practical experience with airfoil optimization techniques has indicated that a deterministic optimization for discrete operating conditions may result in dramatically inferior performance when the actual conditions are different from the given value. Robust airfoil optimization is a method for drag reduction over a given range of operating conditions and keeping the performance fluctuation as low as possible. The present paper gives a BSM-based robust airfoil optimization method which prevents severe degradation in the off-design performance by minimizing the mean and the variance of the drag coefficient over the range of operating conditions. The robust optimization method is verified useful and efficient by solving a lift constrained drag minimization problem for a two-dimensional （2-D） airfoil in transonic viscous flow with Mach number as the uncertain operating condition.