Wall pressure measurements for a sonic jet injected transversely into a supersonic crossflow

D. E. Everett, M. A. Woodmansee, J. C. Dutton, M. J. Morris

Research output: Contribution to journalArticlepeer-review

Abstract

The pressure-sensitive-paint technique was used to determine the continuous surface-pressure field around a sonic jet injected transversely into a supersonic freestream of Mach 1.6. Three experimental conditions, with jet-to-crossflow momentum flux ratios of approximately 1.2, 1.7, and 2.2, were examined. The maximum static pressure upstream of the jet injection site was observed to increase with increasing momentum flux ratio, as did the size and streamwise extent of the low-pressure region downstream of the injector. About the circumference of the orifice, the pressure was observed to increase with increasing momentum flux ratio at the upstream edge of the jet, but was essentially independent of this ratio about the rest of the injector periphery. As a result of these pressure measurements, the effective back pressure, which is defined here as the circumferentially averaged wall pressure about the orifice periphery, was observed to increase weakly with increasing jet-to-crossflow momentum flux ratio over the range investigated.

Original languageEnglish (US)
Pages (from-to)861-868
Number of pages8
JournalJournal of Propulsion and Power
Volume14
Issue number6
DOIs
StatePublished - 1998

ASJC Scopus subject areas

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

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