Swirling supersonic nozzle flow

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Swirling flow in supersonic propulsion nozzles has been investigated both numerically and experimentally. A time-dependent finite-difference technique has been developed and computations have been performed for a range of nozzle geometries, inlet swirl profiles, and swirl levels. The numerical results demonstrate that, while swirl has a minor effect on the specific impulse efficiency, relatively large reductions in the discharge coefficient and vacuum stream thrust efficiency have been computed at high swirl. For conventional converging and converging-diverging (c-d) nozzles, the major effect of swirl on the flowfield is to cause large increases in the axial velocity near the centerline, while the effects at the wall are much less pronounced. Good agreement between numerical and experimental wall static pressure distributions has been found for a c-d nozzle under nonswirling and two swirling flow conditions.

Original languageEnglish (US)
Pages (from-to)342-349
Number of pages8
JournalJournal of Propulsion and Power
Issue number4
StatePublished - 1987

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science


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