Numerical simulation of Shock-free Shear layer interaction in reacting flows

The performance of any supersonic combustor system depends on efficient injection and complete burning. Computational analysis of the flow field associated with supersonic combustors is presented. Results are obtained by numerically solving unsteady, compressible, turbulent Navier-Stokes equations, using Unstructured Finite Volume Method (UFVM) incorporating RNG based K-ε two equation model and time integration using three stage Runge-Kutta method. The developed numerical procedure is based on the implicit treatment of chemical source terms by preconditioning. Reaction is modeled using an eight step H₂-air chemistry. The code is validated against standard experimental data. The analysis could demonstrate the effect of interaction of oblique shock wave with hydrogen stream in its mixing with coaxially flowing air and subsequent reaction.