TY - JOUR
T1 - Development of engineering model providing body force distribution of Tri-electrode Plasma actuator
AU - Nakai, Kumi
AU - Nishida, Hiroyuki
AU - Asaumi, Norio
AU - Tanaka, Yuhi
AU - Matsuno, Takashi
N1 - Funding Information:
The authors are grateful to IHI Corporation for financial support. We also thank Mr. Masaki Tamura and Ms. Asa Nakano for their valuable cooperation.
Publisher Copyright:
© 2019 The Japan Society for Aeronautical and Space Sciences
PY - 2019
Y1 - 2019
N2 - Tri-electrode plasma actuators (TED-PAs) can induce a stronger jet than that of conventional two-electrode plasma actuators (DBDPAs). For practical application of a TED-PA, it is significant to develop a TED-PA engineering model for implementing CFD simulations. In this study, we model the body force distribution generated by a TED-PA utilizing the Suzen model, which is one of engineering models used for DBDPAs. First, we define a function to describe the charge distribution profile on the dielectric surface with two half-Gaussian distributions. Second, we define the maximum values of surface charge as functions of the voltage applied based on the plasma simulation results. Finally, the flow fields numerically obtained using the model developed are compared with the experimental results from our previous study. Although there are some discrepancies mainly due to the two-dimensional laminar flow simulation, the model developed can quantitatively reproduce the voltage characteristics of thrust force and the jet structure induced. Therefore, the model developed is expected to evaluate the flow control effect precisely.
AB - Tri-electrode plasma actuators (TED-PAs) can induce a stronger jet than that of conventional two-electrode plasma actuators (DBDPAs). For practical application of a TED-PA, it is significant to develop a TED-PA engineering model for implementing CFD simulations. In this study, we model the body force distribution generated by a TED-PA utilizing the Suzen model, which is one of engineering models used for DBDPAs. First, we define a function to describe the charge distribution profile on the dielectric surface with two half-Gaussian distributions. Second, we define the maximum values of surface charge as functions of the voltage applied based on the plasma simulation results. Finally, the flow fields numerically obtained using the model developed are compared with the experimental results from our previous study. Although there are some discrepancies mainly due to the two-dimensional laminar flow simulation, the model developed can quantitatively reproduce the voltage characteristics of thrust force and the jet structure induced. Therefore, the model developed is expected to evaluate the flow control effect precisely.
KW - Body Force
KW - Computational Fluid Dynamics
KW - Engineering Model
KW - Plasma Actuator
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U2 - 10.2322/tjsass.62.247
DO - 10.2322/tjsass.62.247
M3 - Article
AN - SCOPUS:85072655666
VL - 62
SP - 247
EP - 255
JO - Transactions of the Japan Society for Aeronautical and Space Sciences
JF - Transactions of the Japan Society for Aeronautical and Space Sciences
SN - 0549-3811
IS - 5
ER -