Effect of Injection Angle on Liquid Injection in Supersonic Flow

Abstract

The aim of this experimental work was a study of the influence of injection angle on the penetration and breakup of liquid jets in a supersonic airstream. All tests were conducted in the VPI 23-cm Supersonic Wind Tunnel at A/=3.0 with T0-ambient and P0=4.35 atm. A particular goal was to incorporate injection angle into the penetration correlations previously developed at VPI. This was accomplished. A secondary aim of the work was to assess the performance of liquid fuel jet injection from the top of a strut. This is one method that has been suggested for the mechanical enhancement of penetration. The penetration behavior was found to be essentially the same as for injection from a flat plate. A result of interest was the discovery of waves with sharp crests on the windward side of the jets for downstream angled injection. d d,