Application of a chimera technique to the computation of subsonic and transonic bi-airfoil flows

This paper describes the application of a composite overset-grid technique to flow computations around a two-dimensional bi-plane. The flow is described by the steady, 2D, compressible Euler equations of gas dynamics. The discretization method used is a central finite-difference method with artificial dissipation. The overset-grid technique is of chimera-type and the bi-plane a bi-NACA0012 airfoil.