Effect of injection angle on liquid injection in supersonic flow
Effect of injection angle on liquid injection in supersonic flow
- New search for: Baranovsky, S.I.
- New search for: Schetz, J.A.
- New search for: Baranovsky, S.I.
- New search for: Schetz, J.A.
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 M=3,0 with T 0=ambient and P 0=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. (Stoehr)
Document information
Effect of injection angle on liquid injection in supersonic flow
Einfluss des Einspritzwinkels bei der Fluessigkeitseinspritzung in Ueberschallstroemungen
AIAA Journal ; 18 , 6 ; 625-629
1980
5 Seiten, 12 Bilder, 6 Quellen
Article (Journal)
English
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