The advantage of a trielectrode (TED) plasma actuator in the flow separation control on the two-dimensional airfoil model has been investigated experimentally in 30 m/s uniform flow (Re = 6.0×10 5). Two exposed electrodes are set on the surface of a NACA0012 airfoil model. For driving SDBD and TED plasma actuators separately, one exposed electrode for applying AC voltages is located at the leading-edge, and DC voltages is applied to another one placed in 41.43 mm downstream from the leading edge. The flow field around the model was analyzed using time-resolved PIV in a wind tunnel. The results indicated superior performance of the TED plasma actuator in separation delay when a high negative voltage (V dc =-20 kV) was applied, compared to the SDBD plasma actuator. At the same time, the TED plasma actuator showed higher efficiency in energy consumption, when compared in terms of thrust generated per power supplied.
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.
The measured thrust in the test facility is affected by secondary airdow and the thrust is different f ヒ om gross thrust . Thrust cerrelation paramctcr between outdoor and test facilities is called cell factor . In thispaper , CFD application fbr ceH factor prediCtion has been invcstigated . Both overall test cell model and outdoor cell model are ana 且 yzed by CFD .
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