基于多输出高斯过程的超临界翼型优化

A supercritical airfoil design based on multi-output surrogate model

提出了一种基于多输出高斯过程(MOGP)回归模型和模拟退火算法相结合的翼型优化方法。采用拉丁超立方抽样方法在设计空间内构造一系列样本点,其中优化设计采用CST参数化方法对翼型的几何外形进行参数化表示。通过CFD流体计算得到其响应值来建立初始的MOGP代理模型。以阻力最小化为设计目标,考虑面积、升力等约束条件。通过单点优化和多点优化试验表明,发展的翼型优化设计方法达到了优化设计的目的,同时也说明基于MOGP模型的优化设计方法在气动优化设计中的应用是可行的。

An airfoil optimization method based on a MOGP（Muliple Output Gaussian Process）model and the simulated annealing algorithm is developed.The Latin hypercube method is used to construct a series of sample points in the design space,where the CST parameterization method is used to define the airfoil geometry.The initial MOGP model is established based on the response values obtained by CFD（Computational Fluid Dynamics）calculation.The proposed numerical test is to minimize the drag coefficient with consideration of some constrained conditions such as the area of airfoil,the lift coefficient and so on.Experimental results show that the drag coefficient is significantly reduced and the aera of airfoil and the lift coefficient remains,which is exactly meet the expectation of the optimization.Furthermore,the proposed method can be extended to 3Dcases straightforwardly and is applicable to practical engineering problems.