Computation of unsteady nonequilibrium propulsive flowfields

This paper describes a scheme to numerically predict hypersonic flow fields with emphasis on temporal and nonequilibrium effects in two dimensions. The gas model allows for chemical and thermal nonequilibrium. Finite rate chemistry is used to simulate several possible reactions among 11 chemical species present in air. A two temperature model is employed to simulate the thermal nonequilibrium effects, a vibrational - electronic temperature and a rotationaltranslational temperature being the two temperatures used. The intended applications of this code include the simulation of partially ionized high temperature flow fields including magnetohydrodynamic (MHD) effects. To that end, the formulation includes provisions for MHD terms, which are treated as source terms in the flow equations.