Abstract
Nanosecond (ns) and alternating current (ac) dielectric barrier discharge (DBD) plasma actuators are studied in a transient separation control setup. The effects of forcing on flow over a NACA 0012 airfoil in stall (AoA = 18◦) at a Reynolds number of 740,000 are compared. The flow response to single pulse forcing with time scales much less than the convective time is investigated with the aid of 2-D PIV. The experiment is carried out by phase averaging over different time delays after the actuation pulse ranging t/Tconv = 0 to 10. Pulse energy is varied by a factor of three, but minimal impact on the two actuation mechanisms is observed. The results indicate a somewhat surprising similarity in the global flow response to ns-DBD (thermal) and ac-DBD (momentum) actuation mechanisms. The location, structure and strength of the excited vortical structures are compared and local variations originating from different actuation mechanisms are observed. Ns-DBD induced perturbations are found to be stronger at a given level of electrical energy. However the differences in global flow response are small.
| Original language | English (US) |
|---|---|
| Title of host publication | AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Edition | 210059 |
| ISBN (Print) | 9781624105241 |
| DOIs | |
| State | Published - Jan 1 2018 |
| Event | AIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States Duration: Jan 8 2018 → Jan 12 2018 |
Other
| Other | AIAA Aerospace Sciences Meeting, 2018 |
|---|---|
| Country | United States |
| City | Kissimmee |
| Period | 1/8/18 → 1/12/18 |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
A comparative flow physics study of Ns-DBD vs Ac-DBD plasma actuators for transient separation control on a NACA 0012 airfoil. / Durasiewicz, Claudia; Singh, Ashish; Little, Jesse C.
AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - A comparative flow physics study of Ns-DBD vs Ac-DBD plasma actuators for transient separation control on a NACA 0012 airfoil
AU - Durasiewicz, Claudia
AU - Singh, Ashish
AU - Little, Jesse C
PY - 2018/1/1
Y1 - 2018/1/1
N2 - Nanosecond (ns) and alternating current (ac) dielectric barrier discharge (DBD) plasma actuators are studied in a transient separation control setup. The effects of forcing on flow over a NACA 0012 airfoil in stall (AoA = 18◦) at a Reynolds number of 740,000 are compared. The flow response to single pulse forcing with time scales much less than the convective time is investigated with the aid of 2-D PIV. The experiment is carried out by phase averaging over different time delays after the actuation pulse ranging t/Tconv = 0 to 10. Pulse energy is varied by a factor of three, but minimal impact on the two actuation mechanisms is observed. The results indicate a somewhat surprising similarity in the global flow response to ns-DBD (thermal) and ac-DBD (momentum) actuation mechanisms. The location, structure and strength of the excited vortical structures are compared and local variations originating from different actuation mechanisms are observed. Ns-DBD induced perturbations are found to be stronger at a given level of electrical energy. However the differences in global flow response are small.
AB - Nanosecond (ns) and alternating current (ac) dielectric barrier discharge (DBD) plasma actuators are studied in a transient separation control setup. The effects of forcing on flow over a NACA 0012 airfoil in stall (AoA = 18◦) at a Reynolds number of 740,000 are compared. The flow response to single pulse forcing with time scales much less than the convective time is investigated with the aid of 2-D PIV. The experiment is carried out by phase averaging over different time delays after the actuation pulse ranging t/Tconv = 0 to 10. Pulse energy is varied by a factor of three, but minimal impact on the two actuation mechanisms is observed. The results indicate a somewhat surprising similarity in the global flow response to ns-DBD (thermal) and ac-DBD (momentum) actuation mechanisms. The location, structure and strength of the excited vortical structures are compared and local variations originating from different actuation mechanisms are observed. Ns-DBD induced perturbations are found to be stronger at a given level of electrical energy. However the differences in global flow response are small.
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U2 - 10.2514/6.2018-1061
DO - 10.2514/6.2018-1061
M3 - Conference contribution
AN - SCOPUS:85044409687
SN - 9781624105241
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -