Development of Computational Procedures for Reactive Gaseous Flows

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The objective of the present project is to develop finite-difference procedures for simulations of reactive gaseous flows. The computational procedures are intended to apply for high temperature gas behind strong shock waves and for supersonic combusting gas in which fluid motions interact with chemical processes considerably. In these supersonic reactive gases, complicated flowfields are expected to be generated due to interactions between shock waves and boundary layers as well as those between shock waves and chemical processes. In 1989, a computational procedure was developed for simulations of the shock-boundary-layer interactions and it was applied to successfully predict behaviors of reflected-shock waves interacting with side-wall boundary layers in a shock tube. The procedure for ideal gas was extended for ionizing gas and numerical simulations were conducted for phenomena of shock reflection in ionizing argon in a shock tube. In 1990, a finite difference procedure was developed for simulations of combustible flows. This procedure predicts behaviors of reactive flows by numerically solving the thin-layer Navier-Stokes equations with modeled chemical terms by use of a combined method consisting of the FCT scheme, the Crank-Nicolson scheme and a semi-analytical chemical step. It was employed to predict detonation initiation phenomena behind reflected-shock waves in hydrogen-oxygen mixture. Comparisons between numerical results and experimental results indicate that thepresent procedure can reproduce several characteristic aspects of the detonation initiation.