Penetration and mixing studies of a sonic transverse jet injected into a mach 1. 6 crossflow

W. M. Vanlerberghe, J. C. Dutton, R. P. Lucht, L. S. Yuen

Research output: Contribution to conferencePaperpeer-review


An examination of the basic flowfield surrounding a single, underexpanded, sonic, transverse jet injected into a Mach 1. 6 crossflow is presented. Surface oil flow techniques were used to show the surface streakline patterns around the jet orifice. Shadowgraph methods, planar Mie scattering from ethanol droplets, and planar laser-induced fluorescence from acetone were used to reveal large scale turbulent structures in the streamwise transverse side view planes of the jet. Primary and secondary flow separation regions are indicated upstream of the jet, and a horseshoe vortex system originates upstream of the jet and extends downstream around the jet. Large scale structures are revealed along the jet-crossflow interface. The rotation direction of these eddies indicates that the jet fluid is moving faster than the crossflow fluid at the interface. The large scale structures vary in size and spacing along the jet-crossflow interface, and engulf large portions of crossflow fluid which contributes greatly to the near field mixing. Acetone PLIF images show the rapid expansion of the jet fluid after it leaves the injector and clearly reveal the barrel shock and Mach disk. Jet penetration and jet spreading are found to increase with increasing jet-to-crossflow momentum ratio.

Original languageEnglish (US)
StatePublished - 1994
EventAIAA Fluid Dynamics Conference, 1994 - Colorado Springs, United States
Duration: Jun 20 1994Jun 23 1994


OtherAIAA Fluid Dynamics Conference, 1994
Country/TerritoryUnited States
CityColorado Springs

ASJC Scopus subject areas

  • Aerospace Engineering
  • Engineering (miscellaneous)


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