Plasma Synthetic Jet Actuator (PSJA)

Research efforts to improve fluid control by using Plasma Synthetic Jet Actuator (PSJA)¹ by conducting both experiments and computer simulations are ongoing in our laboratory. For example, after confirmed the significant effects of PSJA by quantitative measurements in wind tunnel experiments, then we investigate the detailed flow by computer simulation. PSJA is drawing a lot of attentions in recent years as a flow control device. Our laboratory had started the PSJA-related researches at an early age and conducted pioneering studies.

Look at the above video showing that SS-type PSJA is well controlling the cylinder wake. Synchronized with the activation of PSJA (seen by bluish white light), surrounding flow dynamically changes. Other videos are also available at our YouTube channel.

[YouTube Channel]

Our primary target is the fluid control around aerofoils. We have already confirmed that the airflow around aerofoils can be controlled by introducing PSJA. Above picture shows an experimental setup for measuring the airflow around a aerofoil in our laboratory wind tunnel.

Computer simulation of wing-tip vortexes. PSJA is attached at the location of 73 % of chord length from the leading edge. Left and right figures show airflow patterns under conditions of PSJA-OFF and PSJA-ON, respectively. Airflow changes are observed with activating PJSA.

Micromini sensor for PSJA.

Conceptual view of PSJA.

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1. Alternatively, it is called as Dielectric Barrier Discharge (DBD) actuator or simply plasma actuator. ↩