A chimera grid scheme is adopted to analyze a steady flow field around multi-element airfoil.
A two-dimensional Compressible Inviscid Euler solver is used for the anayses. The numerical fluxes are computed using an upwind algorithm based on Roe's flux difference splitting with higher order MUSCL type extrapolation. The numerical solution is advanced in time using a multi-stage Runge-Kutta Time-Stepping scheme.
Through a steady flow simulation using Chimera grid scheme, the difficulties in grid generation was greatly reduced while maintaining accuracy in space. Also, Steady results of NACA 0012 airfoil show good agreement between single mesh solution and overlapping grid solution.
