Computation of scramjet combustor flows is the main thrust of this work. Computations are done on flow configurations that resemble the reaction zone in the scramjet combustors. Compressible, reacting, turbulent flow solutions are obtained. A two equation (k-epsilon) model with compressibility correction is used to calculate the flow field. A finite rate (9-species, 20-reaction steps) chemistry model for hydrogen-air combustion has been used. Computations are carried out using the Navier-Stokes solver TUFF. Predictions are compared with available experimental data and also those obtained by using the codes UPS and SPARK. A turbulence-chemistry interaction model is included. This model represents the first step in the effort to include these interactions in high-speed reacting flows. A two-dimensional reacting mixing layer has been used for demonstration.
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