Three dimensional magneto-fluid dynamics algorithm development

A previously presented implicit flux vector split algorithm for solving the equations governing magnetofluid dynamics is herein further developed for three dimensional internal flow. The numerical procedure casts the governing equations in strong conservation law form to treat the strong shock waves encountered in hypersonic flow and reduces numerical inaccuracy by interpolating the physical flux vectors directly themselves, instead of the usual state vectors to form the split flux vectors. The finite volume procedure is fully implicit and uses modified approximate factorization with iteration to reduce errors associated with implicit factored methods. Errors associated with the divergence of the magnetic field are controlled by corrections calculated from the solution of a Poisson equation. The procedure can treat air as a perfect gas or as a real gas in either equilibrium or nonequilibrium. Both chemical nonequilibrium, with finite rate air chemistry, including ionization, and thermal nonequilibrium, with distinct translational, rotational and vibrational temperatures are included. The procedure is used to simulate numerically the physics of magnetic field interaction with both external and internal ionized flow. First, it was applied to simulate the nonequilibrium flow surrounding the fore body of a realistic hypersonic flight vehicle at a high Mach number. Magnetic dipoles were placed along the leading edges of the body's delta wing to modify heat transfer. In a second application, magnetic and electric fields were imposed within a channel to accelerate the flow.