Computational evaluation of the effects of swirl on rocket nozzle dynamics

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Scopus citations

Abstract

In this investigation, computational fluid dynamics simulations are employed to examine the effect of different swirl velocity profiles an on the flow dynamics within a rocket nozzle. A fifteen degree, conical nozzle is subjected to forced vortex, free vortex, uniform, complexlamellar, and constant shear-stress swirl velocity profiles. The relative strength of these swirl velocities is characterized by way of the swirl number to assess any differences in sensitivity between the swirl profiles. To capture a range of operating conditions, the nozzle pressure ratio is varied to produce flow fields in the nozzle with and without shock waves.

Original languageEnglish (US)
Title of host publication53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105111
StatePublished - Jan 1 2017
Event53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 - Atlanta, Georgia
Duration: Jul 10 2017Jul 12 2017

Publication series

Name53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017

Other

Other53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017
CountryGeorgia
CityAtlanta
Period7/10/177/12/17

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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