An implicit pressure correction algorithm developed to solve the Navier-Stokes equations for high-speed flows ranging up to the hypersonic flow regime is described. A multistep pressure correction procedure with an implicit density treatment is used to establish the pressure and velocity fields. A smart numerical dissipation scheme adapting monotonically at extrema is developed to capture strong shocks. Numerical solutions for inlet and reattaching free-shear layer flows are compared with experimental data and other numerical results.

A computational procedure to analyze the reacting flows in supersonic flow regime has been developed. The Navier-Stokes solution algorithm is based on an operator splitting procedure using pressure correction equations. The chemical species solution algorithm is also based on an operator splitting procedure in which the chemical kinetics and the fluid dynamics are solved in separate steps. The predictor step of this chemical kineticsi fluid dynamics coupling procedure evaluates the effective chemical source terms by integrating the linearized chemical kinetics equations. The corrector step then solves the fluid dynamic part of the chemical species equations. The present numerical solutions are validated using the available experimental data. NOMENCLATURE

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