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Effect of secondary fluid injection on flow through supersonic nozzle

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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 Ls = 0.5Ld and 0.75Ld, 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 Ld, the flow emanating is not deflected for all SPRs. For injection at 0.75 Ld, the flow is deflected by about 5.50, 5.50 and 100, 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.

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Data availability statement

The data that support the findings of this study are available from the corresponding author upon reasonable request.



Nozzle pressure ratio


Secondary pressure ratio

P 0 :

Settling chamber pressure or stagnation pressure

P w :

Wall pressure

P a :

Atmospheric pressure

L s :

Location of secondary injection from nozzle throat

L d :

Length of divergent portion of nozzle

x :

Axial distance

L :

Length of the nozzle


Injection side


Opposite side


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None declared


This work is not supported by any funding agency.

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Correspondence to Lovaraju Pinnam.

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Inturi, D.M., Pinnam, L., Vegesna, R.R. et al. Effect of secondary fluid injection on flow through supersonic nozzle. J Vis (2024).

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