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.

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Modelling, Analysis and Simulation [MAS]
Scientific Computing

Yagua, L. C. Q., & Koren, B. (2004). Application of a chimera technique to the computation of subsonic and transonic bi-airfoil flows. Modelling, Analysis and Simulation [MAS]. CWI.