The characteristics of transonic flow field around elliptic airfoil of 12% thickness ratio are numerically studied.
In order to solve the unsteady Euler equation in conservative form, finite volume method with artificial dissipative terms and Runge-Kutta time stepping scheme is used.
The numerical calculation is also carried out for NACA 0012 airfoil to know the different characteristics between two airfoils. An automatic generation of body fitted coordinates is used to form an 0-typ mesh system around NACA 0012 airfoil. The result show that the critical Mach number of elliptic airfoil is larger than that of NACA 0012 airfoil.
To investigate the flow field dependence (numerical) on the grid system. O-type and C-type grids are used. O-type grid system is seen to be superior to C-type grid system in overall performance of computation for elliptic airfoil.
