TY - GEN
T1 - Validation study of three-fluid plasma modeling of dielectric barrier discharge for plasma actuator
AU - Nakai, Kumi
AU - Nakano, Asa
AU - Nishida, Hiroyuki
N1 - Funding Information:
This research was supported by Grant-in-Aid for JSPS Research Fellows (17J07566).
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - A parametric study is conducted to evaluate the validity of numerical modeling of discharge plasma in DBD plasma actuator. Discharge plasma behavior is numerically simulated based on the three-fluid plasma model, in which the electron, one type of positive ion and one type of negative ion are taken into account. The simulation results are quantitatively compared with experimental results from the viewpoint of voltage characteristics of thrust force and electric power consumption. The simulation provides the same characteristics as obtained in experiment; the thrust force and electric power consumption increases as a power function of voltage amplitude. However, the simulation cannot reproduce the discharge mode in the case of low voltage amplitude, and it results in quantitative discrepancies between the simulation results and experimental results. It is expected that the simulation successfully reproduces the discharge mode in the case of high voltage amplitude.
AB - A parametric study is conducted to evaluate the validity of numerical modeling of discharge plasma in DBD plasma actuator. Discharge plasma behavior is numerically simulated based on the three-fluid plasma model, in which the electron, one type of positive ion and one type of negative ion are taken into account. The simulation results are quantitatively compared with experimental results from the viewpoint of voltage characteristics of thrust force and electric power consumption. The simulation provides the same characteristics as obtained in experiment; the thrust force and electric power consumption increases as a power function of voltage amplitude. However, the simulation cannot reproduce the discharge mode in the case of low voltage amplitude, and it results in quantitative discrepancies between the simulation results and experimental results. It is expected that the simulation successfully reproduces the discharge mode in the case of high voltage amplitude.
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U2 - 10.2514/6.2018-0937
DO - 10.2514/6.2018-0937
M3 - Conference contribution
AN - SCOPUS:85044373813
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -