Plasma control of an unstarting supersonic flow

Seong Kyun Im; Hyungrok Do; Mark A. Cappelli

doi:10.2514/6.2011-2360

Plasma control of an unstarting supersonic flow

Seong Kyun Im, Hyungrok Do, Mark A. Cappelli

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

8 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 language	English
Title of host publication	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
DOIs	https://doi.org/10.2514/6.2011-2360
Publication status	Published - 2011
Externally published	Yes
Event	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 - San Francisco, CA, United States Duration: 2011 Apr 11 → 2011 Apr 14

Publication series

Name	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011

Conference

Conference	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
Country/Territory	United States
City	San Francisco, CA
Period	11/4/11 → 11/4/14

Bibliographical note

Funding Information:
This research is performed through the Stanford Predictive Science Academic Alliance Program (PSAAP) Center, supported by the Department of Energy (National Nuclear Security Administration) under Award Number DE-FC52-08NA28614.

ASJC Scopus subject areas

Space and Planetary Science
Aerospace Engineering
Control and Systems Engineering

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10.2514/6.2011-2360

Cite this

Plasma control of an unstarting supersonic flow. / Im, Seong Kyun; Do, Hyungrok; Cappelli, Mark A.
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011. 2011. (17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Im, SK, Do, H & Cappelli, MA 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, 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, San Francisco, CA, United States, 11/4/11. https://doi.org/10.2514/6.2011-2360

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title = "Plasma control of an unstarting supersonic flow",

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.",

author = "Im, {Seong Kyun} and Hyungrok Do and Cappelli, {Mark A.}",

note = "Funding Information: This research is performed through the Stanford Predictive Science Academic Alliance Program (PSAAP) Center, supported by the Department of Energy (National Nuclear Security Administration) under Award Number DE-FC52-08NA28614.; 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 ; Conference date: 11-04-2011 Through 14-04-2011",

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AU - Do, Hyungrok

AU - Cappelli, Mark A.

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N2 - 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.

AB - 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.

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ER -

Plasma control of an unstarting supersonic flow

Abstract

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ASJC Scopus subject areas

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