Grid Generation Analysis of the Airfoil NACA ۰۰۱۲ Flow

For the numerical solution of the partial differential equations governing the fluid flow, agrid of field points is needed so that the equations can be approximated in the physicalspace and converted into finite volume or finite difference equations. There are two typesof grids:structured grid and unstructured grid.In computational fluid dynamics, the methods of generating grids with structuration aredivided into two categories: algebraic methods and differential equation methods. Inalgebraic methods, boundary points are used to generate points inside the field. In themethods of differential equations, the mapping the computational space to the internalspace is obtained as a differential equation. These equations are solved in discretecomputing space and in an iterative algorithm. Solving equations in computational spaceoffers the possibility of using the central difference method to generalize equations. Thisprocess is repeated until a convergence is satisfied. Improve your grid step by step in thismethod. The aim of this paper is to produce a structured grid using Lagrange andhyperbolic sine algebra methods and elliptic differential equations (with and withoutcontrol) around two geometries of airfoil. The type of computational field is C-Type andthe boundary conditions are periodic and Dirichlet.

کلیدواژه ها:

Grid ، Structured ، Unstructured ، Airfoil.