Numerical/Experimental Investigation of the Presence of a Protuberance in a Convergent – Divergent Nozzle in Supersonic Regime to Control the Thrust Vector

Document Type : Research Article

Authors

1 Department of Mechanical Engineering, Najafabad Beranch, Islamic Azad University, Najafabad, Iran

2 Department of Mechanical. Engineering, Najafabad Beranch, Islamic Azad University, Najafabad, Iran

Abstract

In this study, the effect of protuberance on the thrust vector of a supersonic jet was investigated as a new method in thrust vector control. For this purpose, a convergent-divergent nozzle was designed and fabricated. This nozzle is such that the nominal Mach number in the nozzle exit in full expansion condition is 2. The wall of the nozzle is equipped with pressure holes to measure pressure variations. Also, there is a hole on the nozzle wall to apply a protuberance inside the nozzle. Pressure sensors for pressure measurement and also the Schlieren system are used to check the outlet flow field. The total pressure in all experiments is constant and equal to NPR=6.6. Three-dimensional and multi-block numerical code is used for flow modeling. Also, the turbulence model k-ε, RNG is used to model the nozzle flow. An unstructured mesh has been used for modeling the flow field within the nozzle and the outside domain. The results of this study show that the depth of penetration of the protuberance in the flow field has a significant effect on the amount of deviation and even the direction of the jet stream exited from the convergent-divergent nozzle. The maximum deviation of the jet outlet from the nozzle is 9.8 degrees, which is equal to a penetration ratio of 0.4. In addition, these results indicate that with the increase in protuberance penetration within the nozzle, the nozzle axial thrust has slightly decreased.

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References

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Amirkabir Journal of Mechanical Engineering
Volume 53, Issue 9
December 2021
Pages 4887-4904

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