A numerical study of a reacting flowfield, generated by a single hydrogen jet injected transversely behind a rearward facing step, was performed. A non-reacting, mixing study was followed by a reacting simulation. The computation simulates one of the experimental conditions in the supersonic combustion tunnel in operation at the Aerospace Research Laboratory at the University of Virginia. The validation of the numerical solution was limited to a comparison of the wall pressure distribution along the wall. The comparison indicated an agreement between the experiment and the prediction with a maximum error of 7 %. Addition of the reaction responsible for HO2 production, H+O2+M = HO2+M, to an initially simplified chemical mechanism reduced the exponential growth of the free radicals and reduced the amount of heat released by combustion; as a result, the flowfield was significantly changed. Reversed flow was obtained in limited regions of the flow. The nature of this reversed flow (physical or numerical) is still under investigation.
A numerical investigation of hydrogen combustion in Mach 2 flow
Eine numerische Untersuchung der Wasserstoffverbrennung in einer Mach 2 Strömung
AIAA-Papers ; 1-16
1992
16 Seiten, 18 Bilder, 6 Quellen
Conference paper
English