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2003•The proceedings of the JSME annual meetingOpen access

Flow Control to the surface on Airfoil with Plasma Synthetic Jet Actuator

Naoki Nakatani, Kakuji OGAWARA, Souichi SAEKI

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Abstract

This paper presents a novel actuator for flow control, namely Plasma Synthetic Jet Actuator. This is a glow-discharge actuator, which is composed of the electrodes with AC signal. In this present study, it was applied to the separation control of airfoil. To observe behavior of the actuator, in this experiment, flow visualization was used for flow with Plasma Synthetic Jet Actuator. And the NACA0012 blade, in which this actuator was embedded, was set in the wind tunnel. The wake velocity behind blade was measured with or without operating the actuator. Consequently, the desirable effect of proposed actuator could be observed. These results show that the actuator can execute flow control to the surface on airfoil.

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What this paper is about

This paper presents a novel actuator for flow control, namely Plasma Synthetic Jet Actuator. This is a glow-discharge actuator, which is composed of the electrodes with AC signal. In this present study, it was applied to the separation control of airfoil. To observe behavior of the actuator, in this experiment, flow visualization was used for flow with Plasma Synthetic Jet Actuator. And the NACA0012 blade, in which this actuator was embedded, was set in the wind tunnel. The wake velocity behind blade was measured with or without operating the actuator. Consequently, the desirable effect of proposed actuator could be observed. These results show that the actuator can execute flow control to the surface on airfoil.

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Available abstract

This paper presents a novel actuator for flow control, namely Plasma Synthetic Jet Actuator. This is a glow-discharge actuator, which is composed of the electrodes with AC signal. In this present study, it was applied to the separation control of airfoil. To observe behavior of the actuator, in this experiment, flow visualization was used for flow with Plasma Synthetic Jet Actuator. And the NACA0012 blade, in which this actuator was embedded, was set in the wind tunnel. The wake velocity behind blade was measured with or without operating the actuator. Consequently, the desirable effect of proposed actuator could be observed. These results show that the actuator can execute flow control to the surface on airfoil.

Key concepts: Plasma actuator, Airfoil, Actuator, Flow control (data), Synthetic jet, Rotary actuator, Wind tunnel, Flow visualization

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