空气动力学学报Issue(6)：728-732,746,6.DOI:10.7638/kqdlxxb-2014.0059
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
摘要
Abstract
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 condi-tions 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 3D cases straightforwardly and is applicable to practical engineering problems.关键词
翼型优化设计/输出高斯过程/CST 参数化方法/模拟退火算法/超临界翼型Key words
airfoil design/MOGP/CST method/simulated annealing/supercritical airfoil分类
航空航天引用本文复制引用
吴宽展,刘学军,吕宏强..基于多输出高斯过程的超临界翼型优化[J].空气动力学学报,2015,(6):728-732,746,6.基金项目
国家自然科学基金（61170152）；航空基金重点实验室类 （）
