应用Delaunay图映射与FFD技术的层流翼型气动优化设计

 采用非均匀有理B样条(NURBS)基函数属性建立了任意空间的自由式变形(FFD)翼型参数化方法,进一步结合基于Delaunay图映射技术建立了结构对接网格变形模式,通过粒子群优化(PSO)算法进行参数化方法、网格变形模式以及计算流体力学(CFD)数值模拟技术之间的整合,研究、构建了气动优化设计系统,并对某型层流理念设计的高空长航时(HALE)飞机基本翼型进行气动优化设计。气动特性目标函数评估方法中,边界层转捩数值模拟技术采用γ-Re_θt转捩模型耦合剪切应力输运(SST)模式湍流模型。优化设计后翼型气动特性表明:采用相关技术建立的层流翼型气动优化设计系统对于层流理念设计的HALE飞机翼型的设计具备较高的优化效率。

Laminar Airfoil Aerodynamic Optimization Design Based on Delaunay Graph Mapping and FFD Technique

In this paper,a free-form deformation(FFD) parameterization method is established based on the non-uniform rational B-splines(NURBS) basic function,and a multi-block structure grid deformation technique is established by the Delaunay graph mapping method.By coupling the parameterization method,the grid deformation technology and computational fluid dynamics(CFD) with particle swarm optimization(PSO) arithmetic,an aerodynamic optimization design system is constructed.This system is applied to a laminar airfoil design of high altitude long endurance(HALE) aircraft.The aerodynamic characteristic object function is evaluated by solving Navier-Stokes equations,and the γ-Reθ t transition model coupling with shear stress transport(SST) turbulent model is introduced to numerically simulate boundary layer transition.The aerodynamic characteristics of the optimized airfoil show that the laminar airfoil aerodynamic optimization design system established in this paper has high efficiency and application value for the airfoil design of HALE aircraft.