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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-Reθt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。
The parametric method of freeform deformation (FFD) airfoil in arbitrary space is established by using the properties of NURBS basis functions. The deformation mode of structural docking grid is established based on the Delaunay map mapping technique. The particle swarm optimization (PSO) algorithm for parameterization, grid deformation mode and CFD numerical simulation technology integration, research, construction of the aerodynamic optimization design system, and a type of laminar flow concept of the design of high-altitude long-term (HALE) The aircraft’s basic airfoil is aerodynamically optimized. In the objective function evaluation method of aerodynamic characteristics, the numerical simulation technique of boundary layer transition is adopted the γ-Reθt transition model coupled shear stress transport (SST) model turbulence model. The optimized aerodynamic characteristics of the rear airfoil indicate that the laminar airfoil aerodynamic optimization design system established by the related technology has a higher optimization efficiency for the design of the HALE aircraft airfoil with laminar flow concept.