Numerical Simulation of Dual-Mode Scramjet Combustor with Significant Upstream Interaction

Rahul Ingle and Debasis Chakraborty
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Rahul Ingle: Directorate of Computational Dynamics, Defence Research and Development Laboratory, India
Debasis Chakraborty: Directorate of Computational Dynamics, Defence Research and Development Laboratory, India

International Journal of Manufacturing, Materials, and Mechanical Engineering (IJMMME), 2012, vol. 2, issue 3, 60-74

Abstract: This paper is concerned with a numerical study corresponding to experimental investigation of Chinzei and co-workers on hydrogen fueled dual-mode scramjet engine essentially to understand the key features of upstream interaction, mixing and combustion. Three dimensional Navier Stokes equations along with a K-? turbulence model and infinitely fast kinetics are solved using commercial CFD software. Reasonable agreement has been obtained between the computed surface pressure with experimental values and the results of other numerical simulations. Insights into the flow features inside the combustor are obtained through analysis of various thermochemical parameters. The comparison of surface pressure with experimental results and other numerical results demonstrated that simple kinetics and turbulence – chemistry interaction model may be adequate to address the overall flow features in the combustor. A principal conclusion is that the boundary layer at the combustor entry has a pronounced effect on the flow development in the dual-mode scramjet combustor and causes significant upstream interaction.

Date: 2012
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