Plasma control of an unstarting supersonic flow

Seong Kyun Im, Hyungrok Do, Mark A. Cappelli

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

7 Citations (Scopus)

Abstract

The control of unstart of a supersonic model inlet flow is demonstrated at Mach 4.7 flow conditions using a dielectric barrier discharge (DBD) actuator. Rayleigh scattering from condensed CO2 particles is used to visualize flow features such as boundary layers and shock waves at low freestream static pressure (1kPa) and temperature (60K). Three inlet wall flow conditions - a laminar boundary layer, and a tripped turbulent boundary layer with and without plasma actuation, are tested for comparison in the measured time to unstart. The delay of the unstart process, initiated by mass addition to the supersonic flow, is demonstrated through the plasma actuation of the tripped freestream boundary layer when a single DBD actuator pair is oriented parallel to the freestream flow, generating spanwise disturbances. The effect of DBD actuation on this unstart process is limited to a region within about 3mm from the exposed electrode edge.

Original languageEnglish
Title of host publication17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
DOIs
Publication statusPublished - 2011
Externally publishedYes
Event17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 - San Francisco, CA, United States
Duration: 2011 Apr 112011 Apr 14

Publication series

Name17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011

Conference

Conference17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
CountryUnited States
CitySan Francisco, CA
Period11/4/1111/4/14

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

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  • Cite this

    Im, S. K., Do, H., & Cappelli, M. A. (2011). Plasma control of an unstarting supersonic flow. In 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 (17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011). https://doi.org/10.2514/6.2011-2360