Multi-Electrode Plasma Actuator to Improve Performance of Flow Separation Control
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- Asaumi Norio
- IHI Corporation Department of Mechanical and Aerospace Engineering, Tottori University
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- Matsuno Shinsuke
- IHI Corporation
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- Matsuno Takashi
- Department of Mechanical and Aerospace Engineering, Tottori University
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- Sugahara Masataka
- Department of Mechanical and Aerospace Engineering, Tottori University
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- Kawazoe Hiromitsu
- Department of Mechanical and Aerospace Engineering, Tottori University
Abstract
The advantage of a trielectrode (TED) plasma actuator in the flow separation control on the two two-dimensional airfoil model has been investigated experimentally in 30 m/s uniform flow ( Re = 6.0×105). Two exposed electrodes are set on the surface o f a NACA0012 airfoil model. For driving SDBD and TED plasma actuators separately, one exposed electrode for applyin g AC voltages is located at the leadingleading-edge, and DC voltages is applied to another one pla ced in 41.43 mm downstream from the leading edge. The flow field around the model was analyzed using time 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 ( Vdc = -20 kV) was applied, compared to the SDBD p lasma 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.
Journal
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- International Journal of Gas Turbine, Propulsion and Power Systems
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International Journal of Gas Turbine, Propulsion and Power Systems 9 (1), 1-8, 2017
Gas Turbine Society of Japan
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Keywords
Details 詳細情報について
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- CRID
- 1391130851453380352
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- NII Article ID
- 130007945736
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- ISSN
- 18825079
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- Text Lang
- en
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- Data Source
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- JaLC
- Crossref
- CiNii Articles
- KAKEN
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- Abstract License Flag
- Disallowed