The flow field associated with injecting liquid fuel jets into a hot, supersonic air stream was investigated for three different liquids; kerosene, carbon disulfide and water as a non-burning control. The tests were conducted at a Mach number of 1.8 with a nominal stagnation pressure of 100 psia and the stagnation temperature was varied from 500°F to 2100°F. The flow field was observed by means of direct, top-view photographs, infrared, top-view photographs and nozzle wall temperature measurements, one under the liquid surface formed and the other well removed from it. The infrared photographs are produced by a Thermographic camera which senses the radiation emitted by the surfaces and internally processes these signals to produce a color isotherm image on a color television screen. The nozzle wall temperature was varied from 250°F to 900°F.

For each method of observation, there seemed to be indications that combustion was occurring on the liquid surface layer. However, none of these cases overlapped from one method to another, and as a result, it was difficult to ascertain that combustion did occur. Further testing is needed.