Effect of secondary fluid injection on flow through supersonic nozzle

The effect of secondary gas injection on the flow through an axisymmetric Mach 2 nozzle is studied experimentally. The experiments were conducted for a nozzle pressure ratio of 5. The secondary injection locations chosen for this study were  L s  = 0.5 L d and 0.75 L d , and the secondary gas was in...

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Bibliographic Details
Published in:Journal of visualization 2024-12, Vol.27 (6), p.1049-1058
Main Authors: Inturi, Dakshina Murthy, Pinnam, Lovaraju, Vegesna, Ramachandra Raju, Rathakrishnan, Ethirajan
Format: Article
Language:English
Subjects:
Classical and Continuum Physics
Computer Imaging
Engineering
Engineering Fluid Dynamics
Engineering Thermodynamics
Heat and Mass Transfer
Pattern Recognition and Graphics
Regular Paper
Vision
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Summary:The effect of secondary gas injection on the flow through an axisymmetric Mach 2 nozzle is studied experimentally. The experiments were conducted for a nozzle pressure ratio of 5. The secondary injection locations chosen for this study were  L s  = 0.5 L d and 0.75 L d , and the secondary gas was injected at secondary pressure ratios (SPR) 0.5, 1.0, and 1.5. It is found that for injection at 0.5 L d , the flow emanating is not deflected for all SPRs. For injection at 0.75 L d , the flow is deflected by about 5.5 0 , 5.5 0 and 10 0 , for SPRs 0.5, 1.0, and 1.5, respectively. These flow deflections are observed only in the plane of injection. The effect of secondary injection was not observed in the plane normal to the secondary injection. Graphical abstract
ISSN:1343-8875
1875-8975
DOI:10.1007/s12650-024-01013-w