Abstract
The Roe flux difference splitting scheme is investigated for accuracy in simulating hypersonic reacting flows. The extension of the Roe scheme to include the finite rate chemical kinetic equations follows the approach of Grossman and Cinnella. Formal second-order accuracy is obtained by employing the monotonic upstream schemes for conservation laws (MUSCL) approach in conjunction with the minmod limiter to degenerate the solution to first-order accuracy in the vicinity of strong shock waves. The full Navier-Stokes equations are solved with finite rate chemistry for the flow past an axisymmetric blunt body at zero incidence at several Mach numbers. The vibrational energy is assumed to be in thermodynamic equilibrium with the other internal energy modes
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