Experiments on reacting gas jet penetration

Abstract

Studies of reacting transverse gas jets were made in a shock tunnel under conditions of temperature, pressure, and Mach number corresponding to supersonic flight. Two jet nozzles were used: a circular nozzle and a 30° forward canted transverse slot nozzle, both converging-diverging and of area ratio two. Three jet compositions were involved: heated hydrogen, plus the exhausts of solid and liquid propellant motors, the latter at several oxidizer-to-fuel ratios. The test fluid was air, but in some cases duplicate runs were made using nitrogen to allow a measure of the effect of combustion of the jet with oxygen in the air. Measurements were made of the jet bow shock and of the separated region upstream of the jet. Concentration measurements were made at two stations downstream of the jet. Results are compared with data and correlations for jet penetration and mixing at lower temperatures, pressure, and Mach number. Dependence of the measured parameters on nozzle shape, on jet properties, and on combustion (or its absence) is also presented.