Effect on high-speed boundary-layer characteristics from plasma actuators

Rebecca J. Ostman, Thomas G. Herges, J Craig Dutton, Gregory S Elliott

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

Abstract

An investigation of the effects of a pulsed plasma jet on a Mach 3 crossflow was conducted, with the goal of determining its suitability as a supersonic flow control device. The pulsed plasma jet used an electric discharge, facilitated by a two-circuit, three-electrode design, to heat and pressurize gas in a small cavity. This gas was exhausted transversely through a small orifice into a Mach 3 flow. Particle image velocimetry was used to determine the flow field created by the jet/boundary layer interaction, and it was found that the jet had a modest effect on the flow. The maximum transverse velocity induced by the jet was 61 m/s, approximately 10% of the freestream velocity. Additionally, the jet strength was found to fluctuate over the course of the pulse.

Original languageEnglish (US)
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
DOIs
StatePublished - Aug 19 2013
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: Jan 7 2013Jan 10 2013

Publication series

Name51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
Country/TerritoryUnited States
CityGrapevine, TX
Period1/7/131/10/13

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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