Numerical and experimental investigation of hydrogen combustion in a mach 2 airflow with an unswept ramp fuel injector

摘要

A computational simulation of reacting and non-reacting 3-D flowfields in a model scramjet combustor has been performed. The 3-D flowfield with Mach 2 incoming air and Mach 1.7 hydrogen injected from the base of an unswept ramp injector is examined in this investigation. A 3-D Navie-Stokes code with a funite-rate kinetics chemistry mechanism, SPARK, has been used for this simulation. The flow conditions in the simulation match those achieved during combustion experiments at Aerospace Research Laboratory (ARL). Compared to the nonreacting flowfield, the reacting flowfield has a less severely underexpanded fuel jet, a larger recirculation region and higher pressure at the base of the ramp. This study provides a set of detailed spatially-resolved results for comparison with planar velocity measurements. Comparisons show that for both the measured and predicted velocity field the stramwise velocity ranges from 200-800m/s and has similar flow features.